SERVICE
M00NEY
LOUIS
AND MAINTENANCE-MANUAL
AIRCRAFT CORPORATION
SCHREINER
,ssuED
- DECEMBEr,
1998
FIELD, KERI:tVILLE, TEXAS.
78028
MANUAL NUMBER - 123
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
LDG rlF REI/ISIIINS
ALwaysdestroy superseded pQQeswhenyou Insert revtsed paQes,
BATE OF
REVISION
SECTIONS
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BATE OF
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pages
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12-98
beginning
o? each
ch_p±er,
LOG OF REVISIONS
PAGE1
SERVICE AND MAINTENANCE MANUAL
LOG
M20J
MOONEY AIRCRAFT CORPORATION
OF REVISIONS
Alwo, ys
DATE
OF
REVISION
des-_Po
SECTIONS
AFFECTED
t supePseded
pcLQes
when
you
DATE
OF
REVISION
Inser'_c
r-evlsed
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SECTIONS
AFFECTED
NOTE,
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oF
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p_ges
will _ppe&r
a± ±he
be£1nnln£
o£ e&ch
chapter.
There will be black, vertical lines on the edge of the pages for data that has been changed or added for
the current page revision.
The Electrical Equipment List in Section 91 has been updatedto reflectthe current configuration status and
there will be added electdcal schematics to cover current model year M20J aircraft_
Each page will be noted with applicable revision date at the bottom-center of the page.
LOG OF REVISIONS
PAGE 2
12-98
-
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
INTRODUCTION
This manual provides servicing and maintenance
information for the l_.loeney Model M20J, Serial
Numbers 24-0001 and ON. Maintenance actions that
refer to a limited numb{_rof aircralt will be designated
by
sedal number
of applicable
airplanes.
The Part
Numbers
of replacement
or repair
parts should
be
identified using the Illustrated Parts Catalog (IPC)
applicable to Model & Serial Number of aircraft being
worked on. Part Numbers can be ordered through any
Moeney Marketing Center (MMC). See Section 91 for
identification of electrical components.
The format and content.,;ofthis manual are prepared in
accordance
with
GENERAL
AVIATION
The variousgroups contain major systems information
such as flight controls, landing gear, etc. The systems
are
arranged
numerically
per GAMA
number
assignment,
It is suggested,
for recommended
example, that
"Fuel" be identified with the System/Chapter number
"28". The sequence of numbers, 28-00-00, refers to
General information ofthe Fuel Systems.
SUB-SYSTEM/SECTION
The major systems of an aircraft are broken down into
sub-systems. These sub-systems are identified by the
second element of the sequence of numbers,
SECTION, ie., 28-20-00. The element -20- indicates
the distribution portion of the fuel system.
UNIT/SUBJECT
MANUFACTURER'S , ASSOCIATION
(GAMA)
Specification No. 2. Tfu. manual is supplemented with
widng schematics for the various model year airplanes,
as
necessary.
These
are located in envelopes at the
back
of the manual
text.';pages.
The individual units within a sub-system may he
identified by a third element of the sequence of
numbers, SUBJECT, ie., 28-20-01. This number is
assigned by the manufacturer and may or may not be
used depending upon the complexity of the
maintenance action recommended.
APPLICATION OF NUMBERING SYSTEM
Mooney Aircraft Corporation is in the process of
revising all applicable technical publications to the
GAMA format. When this effort is completed any
publication concerning maintenance of aircraft will
conform to this basic numbering system. Any person
wishing information concerning the Fuel Distdbution
System would refer to the pages identified as,
28-20-00, in any maintenance odented publication.
These pages will be numbered sequentially within each
system breakdown in the current Meoney series of
aircraft. As Mooney aircraft models become more
complex the page numbers may be sequentially
numbered within sub-systems.
NOTE
Revisions of this manual are not automatically
provided to manual holders. Holders of these
and other Mooney Technical Publications
should complete information on YELLOW
CARDS located at the front of the Title Page
and send to Mooney Aircraft Corporation, Louis
SchrienerField, Kerrville, TX., 78028, Attn:
Service Parts Department.
Notification is sent to known manual holders when any
new manual is preparP.d to replace the subscdption
manual and advises that no more revisions will be sent
out. The new issue manual will require a new
subscription
service.
If additional Technical
Publications are desired, contact the Service Parts
Department at Mooney Aircraft Corporation at (830)
896-6000, ext 2092 (direct line (830)792-2092).
The table of contents in the front of each Chapter will
provide
a list of sub-systems covered in the Chapter.
For example:
Correspondence concerning maintenance or part
numbers on an airplane should contain the aircraftmodel
number and sedal number. The sedal number appears
on the identification placsrd located on the aft end, left
hand side of the tailcone below the horizontalstabilizer,
ASSIGNMENT OF SUBJECT MATERIAL
28-00
28-10
28-20
The content of this publication is organized at four
levels:
General
Storage
(Tanks, vents, repair,
etc.)
Distribution
(Boost pumps, fuel
lines, etc.)
28-40
]ndicating
(Sender Units, quantity
gauges, etc.)
If there is a reason to distinguish between LEFT HAND
or RIGHT HAND fuel quantity sending units then the
number would be expended to 28-40-01 (Left Hand)
and 28-40-02 (Right Hand). This concept will apply to
any expanded informationthroughout the publications.
Group
System/Chapter
Subsystem/Section
Unit,'Subject
GROUP
These are primary divisions of the manual that enable
broad separation of content, ie., Airframe systems VS
Powerplant systems. These groups are identified by
tabs.
12-98
INTRODUCTION
Page 1
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
SUPPLEMENTARY PUBLICATIONS
The following list of M_nufacturem and/or publicationscan provide servicing and maintenance informationon
components of the Mooney - 201, 201LM, 205 ATS USE, Allegro (Model M20J). No avionics equpment
Manufactummor publicationsare sted due to the manyconfigurationsthat can be installedin the aircraft_These
can be obtainedfrom the repairstationsfor e padicularavionicsmanufacturer.
Publicationsavailablefrom Mooney Aircraft Corporationare listedin the Parts PAce List and are availablethrough
any Mooney Marketing/,_,erviceCenter.
As publicationson vado,Jscomponentsbecome available,they willbe added to the listbelow.
ENGINE
VENDOR ADDRESSES or PUBLICATIONS
The
followingmaintenance publicationscan be obtainedthroughTEXTRON LycomingDivision,Williamsport,PA.,
17701.
OverhaulManual for TE_I'RON LycomingAircraftEngines,Direct Drive Models,Manual No. 60294-7.
UlustratedPads Catalog _ Manual No. PC-206 for TEXTRON LycomingIO-360, AIO-360, HIO-360, LIO-360 and
TIO-360 series aircraftengines.
Operators Manuel - N(=. 60297-12, for TEXTRON Lycaming 0-360, HO-360, 10-360, AI0-360, LIO-360 and
TI0-360 aircraft:engines,
ServiceBulletins- Specify model of engineforwhich maintenancedata is desired.
PROPELLER
McCauley Propellers - Obtain publicationsfrom McCauley Accessodes Division,Cessna Aircraft Company,3635
McCauleyDAve Vandalis, OH.,45377.
ServiceManual- No. 78_630 for McCauley C200 sedes constantspeed propellers.
Hartzell Popellers - Obtain publicationsfrom Hadzell Propeller, Inc. 350 WashingtonAvenue, Piqua,OH., 45356.
Blade Specification- Manual No. 133-A.
OverhaulInstructions- I_lanualNo. 113-B.
MAGNETO
BendixScintillaMagneto _ Obtain Service data for BendixSedes 2000 or 3000 magnetosfrom Bendix Corporation,
ElectricalComponents[:ivision, Jacksonville,FL. 32245-7880.
FUEL II_J]ECTOR
Fuel 98204
Injector- Obtain sen_icedata for fuel injectorsfrom PrecisionAirmotive,3220-100th Street, S.W. #E, Everett,
WA
VACUUM PUMP
Airborne Division, Parker Hannifin Corporation, 711 Taylor Street, PO Box 4032, Elyda, OH, 44036, USA, Tel.
(216) 284-6300, Fax. (216) 322-6094
STAND-BY VACUUM PUMP SYSTEMS
AERO-SAFE, 10160 Bufl"aloGrove Rd., Fort Worth, TX 76101, (800) 433-5689
ELECTR0-MECH, 2600 So. Custer, Wichita, KS 67217, (316) 942-3271
SPEED BRAKES
PreciseFlight,Inc., 63120 Powell Butte Rd. Bend. OR, 97701, USA, Tel. (800) 547-2558.
INTRODUCTION
Page 2
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
SYSTEM/CHAPTER, SUB-SYSTEM/SECTION INDEX GUIDE
SYSTEM/
CHAPTER
1-4
SUB-SYSTEM/
SECTION
TITLE
RESERVED BY GAMA - MAY BE
USED AT LATER DATE
5
TIME LIMITS/MAINTENANCE
CHECKS
00
GENERAL
10
20
TIME LIMITS
SCHEDULED MAINTENANCE
CHECKS
6
DIMENSIONS AND AREAS
GENERAL
00
7
LIFTING
10
JACKING
8
LEVELING AND WEIGHING
00
LEVELING
9
TOWING AND TAXIING
00"
GROUND HANDLING
10
TOWING
20
TAXIING
00
PARKINGAND MOORING
GENERAL
10
PARKING
20
MOORING
O0
PLACARDSAND MARKINGS
GENERAL
10
MARKINGS
20
PLACARDS - EXTERIOR/INTERIOR
10
11
12
SERVICING
00
SERV]CING
10
REPLENISHING
20
SCHEDULED SERVICING
12-98
INTRODUCTION
Page 3
SERVICE AND MAINTENANCE MANUAL
SYSTEM/
CHAPTER
M20J
SUB-SYSTEM/
SECTION
TITLE
20
STANDARD PRACTICES - AIRFRAME
00
GENERAL
21
ENVIRONMENTAL SYSTEMS
00
CABIN VENTILATION SYSTEM
40
HEATING
24
25
MOONEY AIRCRAFT"CORPORATION
ELECTRICALPOWER
00
GENERAL
30
DC GENERATION
50
ELECTRICALLOAD
DISTRIBUTION
SEATS
CURRENTLY NOT USED
00
GENERAL
10
FLIGHT COMPARTMENT
20
50
PASSENGER COMPARTMENT
CARGO COMPARTMENT
27
FLIGHT CONTROLS
00
GENERAL
10
AILERON SYSTEM
20
RUDDER SYSTEM
30
ELEVATOR SYSTEM
40
50
STABILIZERTRIM SYSTEM
WING FLAP SYSTEM
90
MISCELLANEOUS
28
FUEL
00
GENERAL
10
STORAGE
20
30
DISTRIBUTION
DUMP
40
INDICATING
90
MISCELLANEOUS
30
INTRODUCTION
Page 4
ICE AND RAIN PROTECTION
00
GENERAL
30
PITOT AND STATIC
60
PROPELLERS
12-98
MOONEY AIRCRAFT CORPORATION
SYSTEM/
CHAPTER
M2OJ
SERVICE AND MAINTENANCE MANUAL
SUB-SYSTEM/
SECTION
TITLE
32
LANDING GEAR
00
GENERAL
10
MAIN LANDING GEAR AND
DOORS
20
NOSE LANDING GEAR AND
DOORS
30
40
EXTENSION AND RETRACTION
WHEELS AND BRAKES
50
STEERING
60
POSITION AND WARNING
80
MISCELLANEOUS
00
LIGHTS
GENERAL
33
20
INTERIOR LIGHTS MAINTENANCE
PRACTICES
40
EXTERIOR LIGHTS MAINTENANCE
PRACTICES
34
NAVIGATION
00
GENERAL
10
PITOT & STATIC AIR PRESSURE
SYSTEM
20
DIRECTIONAL GYRO COMPASS
35
OXYGEN
00
GENERAL
37
VACUUM
00
GENERAL
10
DISTRIBUTION
20
INDICATING
39
ELECTRICAL PANELS AND
COMPONENTS
00
GENERAL
10
INSTRUMENT AND CONTROL
PANELS
ELECTRICAL AND
ELECTRONICS
EQUIPMENT RACKS
20
12-98
INTRODUCTION
Page 5
SERVICE AND MAINTENANCE MANUAL
SYSTEM/
CHAPTER
M20J
SUB-SYSTEM/
SECTION
TITLE
51
STRUCTURES
00
GENERAL
10
STRUCTURAL REPAIR GENERAL
52
DOORS
00
10
GENERAL
CABIN DOOR- MAINTENANCE
PRACTICE
30
BAGGAGE COMPARTMENT
DOOR MAINTENANCE PRACTICE
53
FUSELAGE
00
10
GENERAL
MAIN FRAME
20
AUXILIARY STRUCTURE
30
PLATES/SKIN
40
ATTACH FITTINGS
50
FILLETS/FAIRINGS
55
STABILIZERS
00
GENERAL
10
HORIZONTAL STABILIZER
20
ELEVATOR
30
VERTICAL STABILIZER
40
RUDDER
56
WINDOWS
00
20
GENERAL
WINDSHIELD & CABIN
WINDOWS
50
PLEXIGLASS DRILLING
57
INTRODUCTION
Page 6
MOONEY AIRCRAFT CORPORATION
WINGS
00
GENERAL
30
PLATES/SKINS
40
ATTACH FITTINGS
50
FLIGHT SURFACES
12-98
MOONEY AIRCRAFT CORPORATION
SYSTEM/
CHAPTER
M2OJ
SERVICE AND MAINTENANCE MANUAL
SUB-SYSTEM/
SECTION
TITLE
60
STANDARD PRACTICES PROPELLERS
[NO TAB DIVIDER]
61
PROPELLERS
00
GENERAL
I0
PROPELLER ASSEMBLY
20
CONTROLLING
71
POWERPLANT
00
GENERAL
10
COWLING
72
ENGINE - RECIPROCATING
O0
GENERAL
00
ENGINE FUEL SYSTEM
GENERAL
10
DISTRIBUTION
20
CONTROLLING
30
INDICATING
73
74
IGNITION
00
GENERAL
10
POWER CONTROL
20
EMERGENCY SHUTDOWN
76
CURRENTLY NOT USED
ENGINE CONTROLS
00
GENERAL
10
POWER CONTROL
20
EMERGENCY SHUTDOWN
00
ENGINE INDICATING
GENERAL
10
POWER
20
TEMPERATURE
77
12-98
INTRODUCTION
Page 7
SERVICE AND MAINTENANCE MANUAL
SYSTEM/
CHAPTER
M20J
SUB-SYSTEM/
SECTION
TITLE,
78
OO
EXHAUST
GENERAL
10
30
INSTALLATION
EXHAUST SYSTEM
40
REPLACEMENT COMPONENTS
79
OIL
0O
GENERAL
10
STORAGE
20
DISTRIBUTION
30
INDICATING
80
STARTING
00
GENERAL
10
CRANKING
81
CURRENTLY NOT USED
TURBINES
OO
10
GENERAL
POWER RECOVERY
20
TURBOCHARGER
00
SCHEMATICS
GENERAL
91
95
MOONEY AIRCRAFT CORPORATION
20
ELECTRICAL SYSTEM
HARDWARE
CHARTS
30
SCHEMATICS
SPECIAL EQUIPMENT
CURRENTLY NOT USED
INTRODUCTION
Page 8
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 5
TIME LIMITS/MAINTENANCE CHECKS
SERVICEAND MAINTENANCEMANUAL
M20J
MOONEY AIRCRAFTCORPORATION
CHAPTER5
TIME UMITS/MAINTENANCECHECKS
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CHAPTER
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MOONEYAIRCRAFTCORPORATION
M20J
SERVICEAND MAINTENANCE MANUAL
CHAPTER5
TIME UMITS/MAINTENANCECHECKS
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
5-00-00 ........
5-00-01 .......
5-00-02.
5-00-03 ........
5-00-04 ..........
5-00-05 ........
5-00-06 ..........
5-00-07 ..........
5-10-00
5-10-01 .........
5-20.00
5-20-01 ........
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5-20-02 ..........
5-2003 .........
5-20-04.
5-20-05 ..........
5-20-06 ..........
5-20-07 ..........
............
.....
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SUBJECT
.........
General.........
Landing Gear System
......
FlightControlSystems
Wing FlapSystems ..........
ElectricPowerSystem .........
Instruments .......
Cabin Heating & VentilsUngSystems .....
Fuel System ..........
Time LimitComponents ..........
Overhauland ReplacementSchedule .....
Schedule MaintenanceChecks ........
InspectionCheek Points .........
Torque Values ..........
Aircro_FileInspection ......
Engine FunctionalCheck ........
Fimt 25 Hours- Inspection ........
50 Hour Inspection .........
100 Hour Inspection(Annual) .......
Access Coverldentif_tion,
Lubricationand ServiceGuide ......
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5-CONTENTS
3/4BLANK
SERVICE AND MAINTENANCE MANUAL
M2OJ
54)0-00
- GENERAL
AIRCRAFT DESCRIPTION. The M20J series of
aircraft are four place high-performancesingle-engine
low-wing monoplanes. The all-metal airframe has a
tubular-steel cabin frame covered with nonstructursl
aluminum skins, a semi-monocoque tailcone, and a
full-cantileverlaminar-flowwing. Controlsurfaces have
structuralspar constructionwith stressed skins riveted
to the spars and dbs. Dual controlwheels accompany
the conventional flight controls. The pilot's rudder
pedals have toe brakes linked to individual hydraulic
cylinders that supply pressure to the hydraulic disc
brakes on each main gear wheel. Removable co-pilot
rudder pedals are standard equipment. The tdcycle
landinggear, havinga steerable nose wheel controlled
by rudder pedal action, is fully retractable. The
wide-span trailing-edge wing flaps are electrically
operated. For stabilizer trim, the entire empennage
pivotsverticallyabout its attaching points,
5-00-01
- LANDING GEAR SYSTEM
The electriclanding gear system has a steerable nose
wheel. Single disc self-adjusting hydraulic brakes are
featured on the main gear. Gear position lights, a
warning horn and a gear position indicator on the
floorboard are standard equipment. Bungee springs
that preload the retraction mechanism in an
over-center position lock the gear down. An air
pressureactuated safety switch in the pitot system or a
squat switch in the electricalsystem prevents electric
gear retractionon takeoff until a safe flying speed is
attained. A gear throttle warning sounds when the
manifold pressure is less than a pre-set value with the
landing gear up. The electdc gear retraction system
has a manual extension system connected to the gear
actuatorthat permitsmanuallowering of the gear inthe
event of an electricalmalfunction,
5-00-02
- FLIGHT CONTROL SYSTEMS
The dual flight control systems can be operated from
either the pilot or co-pilot seat. All flight controls are
conventionalin operation, using pushpulltubes to link
the control surfaces to the control wheels and rudder
pedals. Formica guide blocks maintain control tube
alignment and dampen vibration. An interconnect
springmechanismlinksthe aileron and ruddersystems
to assistin controlcoordination.The standard co-pilot's
rudder pedals are removable. The trim system sets the
stabilizer angle of attack.
5-00-03
- WING FLAP SYSTEM
Wing flaps are electdcafiy actuated and are controlled
by a spdng loaded =up-off-down"switch on the center
console.
5-00-04
-ELECTRIC POWER SYSTEM
1. The master switch and power relay control the
electrical power system, comprised of a 60 amp, 14
volt alternator, a voltage regulator and a 12V, 35 AMP
HR battery (24-0001 {hru 24-299g), or a 70 amp, 28
volt alternator, a voltage regulator and a 24V, 10 AMP
HR battery -- (24-3000 thru 24-TBA). The alternator
system has an overvoltage protective relay and an
MOONEY AIRCRAFT CORPORATION
overvoltageannunciatorlight. Circuitbreakersor circuit
breaker switches protect the electrical wiring and
equipment from overloads. Standard electrical
equipmentincludes: 1-250 watt landing light(24-0001
thru24-3153)(2-100 watt landing, 2-100 watt taxi lights
S/N 24-3154 thru 24-TBA), navigation lights, interior
lights,gear and stall warning system, an electrical fuel
boost pump, an electdc starter, an electric gear
retractionsystem with manual extension override, an
electrical flap system and an electdc cowl flap
actuatingsystem.
5-004)5
-INSTRUMENTS
All flight instrumentsare in the shock-mountedflight
panel. Engine instrumentsare in the co-pilot'spanel.
The pitat system provides air pressure to operate the
airspeed indicator. The instrument static pressure
system has two static air pickup ports--one on each
side of the tailcone--that open to the atmosphere. An
alternate static source is provided on lower flight
instrumentpanel. The instrumentpanel lightingsystem
has manualdimmingmechanisms.
5-00-06
-CABIN HEATING & VENTILATING
SYSTEMS
The heater muff encasing the exhaust system is the
cabin heat source. Hot air from the heater muff mixed
with ambientair controlscabintemperature.Air routed
from the main heater duct system to nozzles at the
windshieldbase defroststhewindshield.
An optional defrost blower motor system is available
for 24-3000 thru 24-TBA and for retrofit on eadJer
aircraft.
5-00-07
- FUEL SYSTEM
The fuel systemhas sealed, integralwing tanks in the
forward, inboardsectionof each wing. Vents at the aft.,
outboard top comer of each tank vent through the
lowerwing surface. Fuel sump drains are at the lowest
point in each tank. The electric fuel pump is in the
bottom lefl forward section of the fuselage just aft of
the firewall. The engine-driven fuel pump mounts on
the enginecrankcase.Two fuel quantity transmittersin
each tank are wired to fuel quantity gauges in the
engine cluster gauge. The master switch, lefl side of
the pilot'spanel, turns on the fuel quantity indicating
systems.Optionalvisualsight gauges are availablefor
wingtankson aircraft24-0001 thru 24-TBA.
NOTE
A low fuel warning annunciator light for each
tank is activated
when
usable
fuel quantity
goes below
2 1/2
gallons.
5-10-00
- TIME LIMIT COMPONENTS
It is recommendedthat overhaul or replacement of
componentsshouldbe accomplishednot later thanthe
specified period of operationfor that componentor in
accordance w_h manufactures service data or
airworthiness directives, whichever allows longest
operation.
The specified overhaul time limits, if applicable to a
component, do not constitute a guarantee that the
component will reach that time limit without requiring
maintenance.
12-98
5-OO-OO
5
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
NOTE
"ON CONDITION" itemsare to be repaired,replaced or overhauledwhen inspectionor performance
revealsan unserviceablecondition.
5-10-01
- OVERHAUL AND REPLACEMENT SCHEDULE
ITEM
RECOMMENDED OVERHAUL OR
REPLACEMENT TIME LIMITS
LANDING GEAR
ActuatorNo-Back Spring
All other Components
1000 Hours
On Condition
POWERPLANT
Engine
Propeller
Magneto-Bendix
Refer to LycomingSI 1009AJ(or currentrevision)
Referto Mfg's. Maintenancedata
O/H every4 years or @ EngineO/H - Ref. TCM
SB #SB643 & Manual X42003 (currentrevision).
@ EngineO/H or on Condition
500 Hours
On Condition
- Slick
InductionAir Filters (Paper)
All other Components
FUEL & OIL SYSTEM
Fuel Selector Valve (Anderson-Brass)*
Fuel Selector Valve (otherthan above mfgr.)
FlexibleHoses (ALL Except as Below& Teflon)
Aemquip 601 Fuel Hoses
Teflon Hoses
All otherComponents
500 Hours *
On Conditionor 500 Hrs.
7 years or Engine O/H, whichever occursfirst.
24 Months
On Conditon
On Condition
INSTRUMENTS
Vacuum RegulatorGarter Filter
Filters -Vacuum Pump
CV1J4 Filter
Filters- Gym Instrument
Other Components
100 Hours
500 Hours oronce a year
On Condition
500 Hours oronce a year
On Condition
ELECTRICAL COMPONENTS
All Components
On Condition
FLIGHT CONTROLS
All Components
On Condition
MISCELLANEOUS SYSTEMS
Vacuum Pump, Primary
Stand-byVacuum Pump
E.L.T. Battery
OxygenCylinders
Lt. Wt. Steel Cylinders
CompositeCylinders
All other Components (excludingAvionics)
On Conditionor 500 Hours &@ EngineO/H (TBO
Inspect@ 500 Hours
2 years or 1 Hourtotal usetime
AVIONICS (General Systems)
Refer to ManufacturersPublications
24 yearsor 10,000 recharge cycles
15 years or 10,000 recharge cycles
On Condition
Bendix-KingSystems
KingServiceMemo No. 292
* Applicable on SIN's 24-0084, 24-0378 thru 24-1176 only.
5-10-01
6
12-98
SERVICE AND MAINTENANCE MANUAL
M20J
NOTE
Components should be inspected and serviced
at regular intervals perthe servicing,
lubrication
inspection
chart
atthe end of
thisand
SECTION
of this
Manual
5-20-00
- SCHEDULED MAINTENANCE
CHECKS
Inspection Intervals. Perform 25, 50, or 100-hour
inspectionsof the aircraRand engine at recommended
intervalsas outlinedin the followingparagraphs,
NOTE
Aircraft operated in salt air environment are
considered high risk for corrosion damage, and
should be cleaned and inspected at more
frequent intervals. RefertoAC43-4.
8-20-01
- INSPECTION CHECK POINTS
The general points to be covered duringinspection
are groupedin accordancewiththe natureand function
of the items discussed,
1. Moving Parts shall be inspected and checked as
applicablefor. properoperation,securityof attachment,
sealing, cleanliness, lubrication, servicing safetying,
adjustment, tension, travel, condition of hinges,
binding, excessive wear, cracking, corrosion,
deformation,and any otherapparent damage,
2. Metal Parts shall be inspected and checked as
applicable for: security of attachment, condition of
finish and sealant, distortion fatigue cracks, welding
cracks,corros on, and any other apparent damage.
3. Fuel, air and hydraulicoil lines and hosesshall be
inspected as applicable for: cracks, dents, kinks,
deterioration, obstruction, chaffing, improper bend
radius, and insecure installation. Hose clamp
installationson fuel and hydraulic systems between
systemsor between systems and the engine shall be
torquedto 25 inch pounds.Hose clamp installationson
blast tubes, air ducts, vacuum lines, drain and vent
linesshall be torquedto 15 inch pounds,
MOONEY AIRCRAFT CORPORATION
4. Pipe Threads - Tightening and Torque procedures.
Lubricatepipe threadsasfollows:
Oxygen Lines - Use only MiL-T-5542 thread
compound or Teflon thread seal tape on threads of
valves, connectors,fittings,parts or assemblieswhich
might come in contact with oxygen. The thread
compoundmust be appliedsparinglyto the first three
threads of the male fittingonly.No compoundis to be I
used on the couplingsleevesor on the outside of the =
tube flares. Extreme care should be exercised to
preventthe contaminationof the thread compoundor
teflon tape with oil, greaseor otherlubricant.
Fuel, Hydraulic,Air,Oil Lines- Use "Parker Thread
Lube" or equivalent on male fittings only. Apply
lubdoant,omittingthe first two threads, sparingly and
carefully.
Engine Fittings - Use only aircreR engine oil to
lubricater_ings threadeddirectlyto engine.
Vacuum Lines- No lubdcaflonis to be used. Check
manufacturers
instructions
when
installing
components. Refer to Section 37 for maintenance
procedureson vacuumsystem.
Tapered Threads - Use TeflonThreadsealTape.
(1) Continue to tighten until fitting is correctly
positionedbut do notoverrunor backoff.
(2) If leaks are detected, tighten one full turn
more.
3) If leaks persist, the parts should be
disconnected and rejected; replace with new
components.
5. Electricalwiring shall be checked as applicable
for. loose, corroded, or broken terminals; chaffed,
broken, or worn insulation;insecure installation;heat
deterioration;and any otherapparentdamage.
6. Bolts and nuts in criticalareas shall be checked
for: fretting, wear, damage, stretch, proper torque,
(Figure 5-2) and safetying.
7. Filtersand screensshall be removed,cleaned and
inspected for contaminationor damage that would
requirereplacement.
Torque Values - See following pages.
12-98
5-20-00
7
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
TORQUE VALUES
FLARE NUT TORQUE VALUES- Tighten to minimum torque valuefor appropriate size as shown (Figure 5-1).
I SIZE
FITTING
ALUMINUM TUBING
MINIMUM.
-3 ..............
-4 ....
-5 ....
-6 ....
-8.
-10
-12
-16
-20
.
-24
40
60
75
150
200
300
500
600
600
.
.
....
....
....
....
....
....
....
....
STEEL TUBING
TORQUE - IN. LBS,
MAXIMUM.
MINIMUM.
30
....
65
....
50
80
.
.
.
70
....
125
.
.
.
90
....
250
....
155 ....
350
300 ....
500 ....
430 ....
.
700
....
550 ....
900
900
I
MAXIMUM
70
90
120
150
250
400
575
750
FLARE NUT TORQUE - FIGURE 5-1
BOLT - NUT TORQUE VALUES
METRIC BOLTS, SCREWS & NUTS
Failure of threaded fasteners due to over-tightening can occur by bolt shank fracture or by stripping of the nut
and/or bolts thread. A bolt or screw assembled with a nut of the appropriate class is intended to provide an
assemblycapableof beingtightenedto the boltproof loadwithoutthread strippingoccurring.
The torquevalue to be set for a particularsize of screw is dependentupon:
1) Materialof the screw.
2) Parent matedal (steel, non-ferrousmetal orplastic).
3) Whetherthe screw is untreatedor plated.
4) Whether the screw isdry or lubricated.
5) The depthof the thread.
TIGHTENING TORQUES - Untreated Screw(BlackFinish)- Friction Coeficient 0.14
NOMINAL
DIAMETER
(CoarseThread)
M3
M4
M5
M6
M7
M5
M10
M12
M14
M16
M1a
M2O
M22
M24
M27
M30
M33
M36
M39
5-20-01
8
PROPERTY_
._
TORQUE Ma
5.6
8.8
1o.9
0.60/0.44
1.37/1.01
2.70/1.99
4.6/3.3
7.6/5.6
11/9.1
22/16
39/28
62/45
95/70
130195
184/135
2501184
315/232
470/346
6351468
8651637
1111/819
144011052
1.37/1.01
3.10/2.29
6.15/4.54
10.5/7.7
17.5/12.9
26119
51137
89165
141/103
215/158
295/217
420/309
5701420
725/534
1070/789
145011089
197011452
253011865
3290/2426
1.92/1.42
4.40/3.25
8.6516.38
15111
25/18.4
36/26
72/53
125192
198/146
3051224
4201309
5901435
8001590
1020/752
1510/1113
2050/1511
277012042
3560/2625
4620/3407
12-98
2.3011.70
5.2513.87
10.4/7.6
18113
29/21.3
43/31
87164
150/110
2401177
365/269
500/368
710/523
960/708
12201899
1810/1334
245011806
333012455
4260/3156
555014093
f'
SERVICE AND MAINTENANCE MANUAL
M2OJ
MOONEY AIRCRAFT CORPORATION
(METRIC TORQUE TABLES CONTINUED)
NOMINAL
DIAMETER
(Fine Thread)
PROPERTY
CLASS
TORQUE Ma
M8 x 1
MI0 x 1.25
M12 x 1.25
M 14 x 1.5
M 16 x 1,5
M18 x 1.5
M20 x 1.5
M22 x 1.5
M24 x 2
8.8
Nmlft.lb.
1O.9
NmlftJb.
12.9
NmlftJb.
27/19
52/38
95/70
150/110
2251165
325/239
4601339
6101449
7801575
38128
73153
135199
2101154
315/232
460/339
6401472
8601634
11001811
45/33
88184
1601118
250/184
3801280
5501405
770/587
105O/774
13001958
TIGHTENING TORQUES - ElectricallyZinc Plated - Friction Ceeficient O.125
DIAMETER
(Coarse Thread)
M3
M4
M5
M6
M7
M8
M10
M12
M 14
M16
M18
M2O
M22
M24
M27
M30
M33
M36
M39
TORQUE Ma
5.6
Nm/ft.lb.
8.8
Nm/It.lb.
10.9
Nm/ft.lb.
12.9
Nm/R.ib,
0.5610,41
1.28/0.94
2_50/1,84
4,3/3.1
7.1/5.2
10.5/7.7
21115
36/26
58/42
88/64
121/39
171/126
230/169
295/217
435/320
5901435
8001590
1030/759
13401988
1.28/0,94
2-9012-14
5.7514,24
9.9/7.3
16.5/12_1
24/17.7
46/35
83161
132/97
200/147
25/202
3901287
5301390
6751497
995/733
13501995
183011349
236011740
305012249
1,60/1.33
4.1013.02
8.1015.97
14/10.3
23116.9
34/25
67149
117/86.2
185/136
285/210
3901287
5501405
7,451549
960/708
140011032
190011401
258011902
3310/2441
4290/3163
2-15/1.59
4.95/3.65
9.70/7.15
16.5/12.1
27/19.9
40129
81159
140/103
2201162
340/250
470/346
6601486
8901656
1140_40
168011239
228011651
309012278
3980/2935
515013798
8.8
Nm/R.Ib.
10.9
Nm/ft.lb.
12.9
Nm/ft.lb.
25118
49/35
88/64
140/103
210/154
3051224
425/313
5701420
7201531
35/25
68150
125/92
195/143
2951217
4251313
6001442
800/390
1000/737
42/30
82/60
1501110
2351173
350/258
510/376
7201531
960/708
1200/885
NOMINAL
DIAMETER
(Fine Thread)
M8 x I
M1Ox 1,25
M12 x 1,25
M14 x 1.25
M16 x 1.5
M18 x 1.5
M2Ox 1.5
M2.2x 1.5
M24 x 2
OPJ]D_gFJ_,]_
CLASS
TORQUE Ma
METRIC CONVERSION FACTOR: One Nm(NewtonMeter) = .7375 Foot Pound;
One Foot Pound= 1.355818 Nrn
12-98
5-20-01
9
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
AN/MS STANDARD BOLTS, NUTS TORQUE TABLES
TORQUE VALUES
(Unitsare Inch-pounds)
NUT
BOLT
SIZE
TENSiON-type
AN( ) BOLTS;
AN-3651AN-310
NUTS
SHEAR-type
AN( ) BOLTS;
AN-364/AN320
NUTS
TENSION-type
NAS() BOLTS
AN-365/AN310
NUTS
!
SHEAR-type
NAS( ) BOLTS;
AN-364/AN320
NUTS
FINE - THREAD SERIES
8-36
10-32
114-28
5116-24
318-24
7116-20
112-20
9/16-18
5/8-18
314-16
7/8-14
1-14
1 115-12
1 114-12
12-15
20-25
50-70
100-140
160-190
450-500
480-690
800-1000
1100-1300
2300-2500
2500-3000
3700-5500
5000-7000
9000-11000
7-9
12-15
30-40
60-55
95-110
270-300
290-410
480600
600-780
1300-1500
1500-1800
2200-3300
5000-4200
5400-6600
25-30
80-100
120-145
200-250
520-630
770-950
1100-1300
1250-1550
2650-3200
3550-4350
4500-5500
6000-7300
11000-13000
15-20
50-60
70-90
120-150
300-400
450-550
650-600
750-950
1600-1900
2100-2600
2700-3300
3600-4400
6600-8000
-COARSE - THREAD SERIES
8-32
10-24
114-20
5116-18
3/8-16
7/10-14
1/2-13
9/16-12
5/8-11
3/4-10
7/8-9
12-15
20-25
40-50
80-90
160-185
235-255
400-480
1500-700
700-900
1150-1600
2200-3000
7-6
12-15
25-30
48-55
95-100
140-155
240-290
300-420
420-540
700-950
1300-1800
Figure5-2
Reference: Federal AviationAgencyAdvisoryCircularNo. 43.13-1(*) (*=currentrev.)
RecommendedTorqueValues for Nut-Boltcombination
1. Be surenut and/or boltthreads are clean and dry(unlessMfg. states otherwise).
2. Run boltdownnear contact withwasher or beadngsurface and check=frictiondragtorque=requiredto turn
bolt/nut.
3. Add"frictiondrag torque"to the recommendedtorque value from Figure 5-2. This value is considered"Final
Torque Value".
(RRICTION DRAG TORQUE + REC'MD TORQUE = FINAL TORQUE).
CAUTION
DO NOT REUSE LOCKNUTS IF THEY CAN BE RUN UP FINGER TIGHT,
5-20-01
10
12-98
SERVICE AND MAINTENANCE MANUAL
M2OJ
MOONEY AIRCRAFT CORPORATION
CAUTION
These torque values are derived from oil-free cadmium-plated threads.
CAUTION
DONOTREUSE LOCKNUTS IF THEYCAN BE
RUN UP FINGER TIGHT.
5-20-02
8. Check pitotand static systemsfor obstructions.
9. Inspect aircraft exterior for security of bolts,
screws, etc.
- AIRCRAFT FILE INSPECTION
Aircraft 1O0-hour and annual inspections cover, in
additionto examining the aircraft proper, a review of
the statusof compliancewith current Federal Aviation
Regulations. This review includes inspection of the
Airplane Flight Manual, Aircraft Log Book, Engine Log
Book,
Registration
Certificate,
Airworthiness
Certificate, Weight & Balance Record, Lycoming
Service Information, Aircraft Radio Station License (if
applicable), FAA Airworthiness Directives, and Mooney
sedvce documents.
5-20-03
-ENGINE FUNCTIONAL CHECK
Pdor to a scheduled 100-hour or annual inspection,
and/or 25 hours after installation of new or overhauled
engine, wash down the engine and engine
components. Then perform an engine runup in accord
with procedure recommended in the Airplane Flight
Manual. Make a record of all malfunctions and
abnormalities. After the engine runup, complete a
differential (hot engine) compression check. To verify
correction of malfunctions and abnormalities, perform a
second engine runup and a flight test after completing
the inspection.
5-20-04
- FIRST 25 HOURS - INSPECTION
The one time 25-hour inspection consistsof a visual
inspection of:.--propeller, engine and aircraft general
condition,includinga preflightinspectionas outlined in
the Flight Manual. The inspection does not require
removal of access panels or disassembly of all
components;however it should include completion of
all lubdcaton and service requirements. Inspection
should be extensive enough to detect any damage or
condition which might jeopardize flight safety. Atter the
first 25 hours of new or overhauled engine operation,
refer to paragraph 5-20-05 for the recommended
engine inspection.
1. Visually inspect propeller, spinner, and cowling;
remove cowling. .
2. Inspect and clean induction air filter if aircraft has
been operating under dusty conditions. Check
operation of alternate air door. Check Ram air door
operation SIN 24-0001 thru 24-3153.
3. Inspect engine compartment for evidence of fuel,
oil or exhaust leaks,
4. Check security and condition of equipment
installed on engine.
5. Inspect fuselage wing and empennage for
external evidence of damage. Pay particular attention
to scratches and dents.
10. Check and service battery.
5-20-05
-50 HOUR INSPECTION
The 50-hour inspection includes all requirements for
the 25-hour inspection,plus the necessary removal of
inspection doors, panels, or faidngs. After the first 25
hours of operating time, a new, remanufactured, or
newly overhauled engine should be given a 50-hour
inspection including replacement of the lubricating oil.
1. ENGINE
A. Drainengineoilsump.
B. Remove and clean suction oil strainer; reinstall
strainerand plug.Safety wire strainer plug.
C. Remove and replace the full-flow oil filter
cartridge.
D. Drain and clean fuel strainer.
E. Remove and clean fuel injector fuel strainer.
F. Service engine oil sump with proper type, grade,
and amount of lubricating oil.
G. Inspect engine intake and exhaust systems for
evidence of leakage and looseness.
H. Check spark plug elbows and shielding nuts for
security.
I. Checkcylindersfor evidence of overheating.
J. Check baffles for secure anchorage, close fit
aroundcylinders,and freedom from cracks.
K. Checkengine controlsfor full travel, freedom of
movement,and security.
L. Visually check fuel and oil lines for secudty of
connections and evidence of leakage or damage.
M. Visually inspect induction air system; check
operation of alternate-air door (refer to paragraph
71-60-01).
N. Inspect engine mount & bolts for security and
con0iflon. Inspect eng'ne mount tubes (bolt attach
tubes), at firewall for moisture accumulation and
corrosion.
2. PROPELLER
A. Check propeller ano spinner for general
condition, looseness, and oil leakage.
B. Inspect blades for nicks and cracks. Repair pdor
to next flight.
3. CABIN
A. Check brake and parking brake control systems
for proper operation and fluid level.
6. Inspect windshields and windows for crazing,
cracks, and scratches.
7. Check control systems for binding, excessive
freeplay, and damage.
12-98
5-20-02
11
MOONEY AIRCRAFT CORPORATION
M20J
B. Check trim system and indicator for free
operationand travel,
C. Check cabin and baggage doors for damage,
properoperation,and sealing.
Check cabin, instrument, position,anticollision,
andD.
landinglight.
E. Check fuel selector valve, gascelator,and boost
pumpfor pmperoperation,
F. Checkoxygensystem(if installed),
4. LANDING GEAR
A. Check tiresfor cuts,blisters,wear, and inflation,
B. Check shock discs for proper extension at
aircraft,staticweight per Section 32-81-00.
C. Check hydraulicbrakes for wear, warpage and
properinstallation,
5. WINGS
A. Checksurfaces and tips for damage,
B. Check ailerons, aileron attachments, and
bellcranksfor damage and properoperation,
C. Check flaps and attachments for damage and
properoperation.
D. Lubdcatecontrols if necessary.
6. FUSELAGE and EMPENNAGE
A. Check stabilizer, elevators, fin, and rudder for
damage and properattachmenL
B.Lubdcete controls if necessary.
7. Lights
"
A. Check operationof extedor and intedorlights,
8. See Section 5-20-07 for repetitive 50 Hour
inspectionsand servicingof componentsinformation.
5-20-06
- t00 HOUR INSPECTION (or
ANNUAL) (REF, FIG. 6.4)
The 100-hour (or annual) inspection is a thorough,
searchinginspectionof the entire aircraft. Preparation
for the inspection includes the thorough cleaning of
exteriorand
engine compartment,removalof
fuselage,
wing,
and empennage
inspectiondoors, cover
plates,
and faidngs at all systems attach, hinge, and beadng
locations (includingwing and empennage to fuselage
matingpoints).Operatinglimitreplacement and special
testing of components is to be included at this interval
when applicable. Comply with applicable FAA
Directives, AD Notes, and applicable Mooney and
Vendor mandatory Service Bulletins and Instructions.
Check for aircraft conformance to FAA Specification
2A3. Recommended 100-hour and special inspection
requirementsare outlined in the followingparagraphs.
SERVICE AND MAINTENANCE MANUAL
A.
Complete a
differential (hot engine)
compressioncheck: clean and gap or replace spark
plugsif necessary.Repairdiscrepanciesfound.
B. Inspectenginefor evidence of excessivefuel or
oil leakage. Inspect oil cooler and oil hoses for
condition.Repairas needed.
C. Drain engine oil sump; remove, inspect and
clean oil suctionscreens;reinstalland safety. Remove
full-flow oil tilter cartridge;replace with new cartridge
and safety. Check crank case breather hoses for
obstruction.Safety wireoil tilter installation.
D. Refill engine oil sump with the proper type,
grade, and quantityof lubdcatingoil.
E. Inspectfuel injectorand all fuel lineconnections
forsecurityand condition.
F. Remove, inspect and clean fuel selectorvalve or
gascalator strainer, reinstall strainer, lubricatedetent
track, ball and spring disc. Inspect fuel lines and
connections;pressurecheck fuel system with mixture
controlat IDLE CUTOFF and BOOST PUMP ON.
G. Inspect all air ducting and connections in the
heating and inductionair systems for leaks. Remove
and clean inductionair tilter;,replace at 500 Hrs.
H. Leak check all exhaust manifold connections,
engine exhaust manifolds and muffler connections.
Inspectfor properattachment.
I. Inspect alternate air door for condition and
proper preload.To inspect for praloed remove lower
cowlingand PUSH on alternate air door seal bolt with
an appropriatespdngscale. A praloadof 3 to 4 pounds
should be requiredto start door to open. Add ordelete
AN960-416L washersunder belt head to obtainproper
tension. Replace all components removed. Coat Seal
with TEFLON spray/lubricant.
CAUTION
CHECK SECURITY of seal to Induction Box
Door. If necessary use (3M) EC1403 cement to
secure seal to door.
J.
Check magnetos for
grounding and
synchmnizalton;check
magneto
points
for condition,
clearance,and timing.Inspectdistributorblockfor
erosion
and cracks.Checkcam followerfelt for properlubrication,
and remove excessiveoil from breaker compartment.
Repairor mplacs componentsif required,per BendixSB
No. 612 at 500 Hrs.for routinemaintenance.
K. Check baffles for secure anchorage, cracks,
holes, deformation, and for close fit around cylinders.
Check cylinders for burned paint and cracked or
brokentins. Checkbafflesealant.
L. Check engine and propeller controls for free
operation, proper security of cable at housingswage,
full travel, and securityof attachment.
NOTE
CaMe Craft control cables are lubricated for the
life of the control cable. DO NOT remove seals
or lubricate control cable.
1. ENGINE INSPECTION. Prior to the inspection,
remove the engine cowling and propeller spinner,
Wash downthe engine and enginecompartment.Then
perform an engine mnup in accord with the procedure
recommendedin the LycomingOperators Manual, To
M. Inspect Propeller Governor for security in
vadty correction of malfunctions and abnormalities,
mounting and unrestricted operation of governor
performa second engine runupand flighttest after the
control. Check for proper operation dudng post
100-hourinspectionengineset-upcheck,
inspectionflight.
5-20-06
12-98
12
SERVICE AND MAINTENANCE MANUAL
M20J
N. Inspect tubular engine mount for cracks,
damage or corrosion; oheck all bolts and robber
mountsfor securityand conditlen,
O. Check battery cables, electrical wtdng, and
ignitionharness for condition,secure anchorage,loose
terminals,and burnedorchaffed insulation,
P. Inspectbattery,battery box, and vent systemfor
condition and corrosion. Check blast tube for
obstruction. Flush battery box and battery case if
necessary,
Q. Inspect accessory case, vacuum pump, hose,
flrewalland fittingsfor securityor damage,
R. Check alternator and mounting bracket for
secodty and ddve belt for conditionand propertension.
Checkstarterinstallaticnfor secority.Checkstmter ddve
and drivegear condition.Lubricatedriveifnscessary.
S. Inspect studs, nuts, belts, etc. for damage &
propertmque,
T. Inspect Exhaust System for leaks or cracks &
proper clearance from other components.Repair any
discrepancies.Replace or repair muffler if any intemal
damage isfound. Inspectforpreperaifachment,
U. Inspect and reinstallcowling. Check cowl flaps
for operationcondition,proper opening and cowl flap
positionindication(24-3000 thre 24-TBA).
V. Inspect landing light for securityand condition
(24-0001 thru 24-3153).
2. PROPELLER INSPECTION.
A. Remove spinner('dnot already removed).
B.Check securityof propellerinstallation,
C. Check hubbelts for securityand damage.
D. inspect hub parts and blades for craoks and
nicks.Repairpdorto nextflight,
,
E. Q-tip blade inspectionand repair. The tip of the
blade is formed at the factory with a bend of 90
degrees toward the blade face (aft). The material
thickness in the radius of bend is closely controlled
such that the cold bend allowance is not exceeded. A
sketchof the "Q"tip is shownbelow (Figure 6-3).
F. Checkfor oil leaks, lossof grease,and lubricate
as requiredby appropdstemanufacturershandbook.
INSPECTION: Inspect =Q-Tip" for stone nicks and
scratches using the same procedure as on the
completeblade. Inspectfor evidenceof the bend being
deformed by assuring that the bend edge is 90
degrees. Also inspect for deformed waviness of the
bend. REPAIR: Material in the bend area (.110 plusor
minus
.010)tomay
be removed
for repair
of nicks
and
scratches
a minimum
blade
thckness
of .065.
Correspondingly,reduce the very tip region, when
required,to a minimumof .010 less than _e resulting
thicknessofthe bend area. The bend may ne reduced
in length for repair from the one inch dimension to
appreximately.75 inches.The g0 degree bendthat has
been deformed by 20 degrees or less may be
straightened by using a rubber mallet and block
assuring that no waviness or other damage results
from the straighteningprocess;inspectfor cracks.The
chord length may be reducedfor repair similarto the
procedureof a standard blade essudng that all blades
are the same so that the aerodynamicbalance of the
propellerwillnot be affected.
G. DELETED PROCEDURE
H. Inspectanti-icingboots for properoperationand
for obviousdefects.
I. Inspectspinnerandbu_P..adforcracksandcondition.
J. Check spinner bulkheadfor correct interference
fit with prop cylinder. (Use Teflon Tape to obtain
correct fit.) (See Section61-00-20, pare. 10)
INSPECTION.
11
0 __
..L
,,-_
"_'I_
C2_{_"_._
MOONEY AIRCRAFT CORPORATION
)
_
A. Check tires for proper inflation,cuts, blisters,
slippage,and heavywear.
3. LANDING GEAR and RETRACTION SYSTEM
corrosion,boltfailure. Check conditionof felt seals and
beadngs;repackbeadngsat 250 hourintervals.
C. Checkbrake pads& discs for warpingandwear.
D. Checkhydraulicreservoirfor properfluid level.
B. Checkwheelsfor oracks,distortion,misalignment,
dents,crackschaffing,
kbrakelinesand
inks,andsecurityof
anchorage.
E. Check hydraulic
hosesfor
leakage,
F. Check parking brake system for proper
engagementand release.
G. Check nose gear for cleanliness and damage.
I
_-----_
_
SH.JK--5--3
NI
or broken roll pins.Check shock disc gap per Section
32.81-O0.
Check nose gear retractiontube bungeesfor sheared
NOTE
Maximum allowable towing damage on leg
assembly is 1132inch dent.
H. Check nose wheel steering mechanismfor
adjustment,alignment,corrosion,and lubrication.
12-98
5-20-06
13
MOONEY AIRCRAFT CORPORATION
M20J
I. Check main gear for cleanliness or damage.
Check shock disc gap per Section 32-81-00.
J. Jack aircraftas recommendedin pemgmph7-10-00.
K. Check landing gear retraction linkage, beUcranks,
pivots, and beadngs for wear, damage, distortion,
misalignment, corrosion, cleanliness,and lubrication,
L. Check the landing gear actuator for secudty of
mounting,
cleanliness,
andinindication
of overheating or
damage. Inspect
brushes
motor for wear.
SIN 24-0001 - 24-0377 with Dukes Actuator
Lubricate actuator ball screw with recommended
lubricant for Dukes actuator only per procedures
below,
(1) After 500 hours of operation and each 200
hoursthereafter.
(a) Remove the actuator from the aircraft,
(b) Remove the end cap and wipe excess
grease from gears,
(c) Visually inspect gears for wear as follows:
With open end of actuator toward you, rotate jack screw
shaft counter clockwise to remove all slack from dng and
worm gears. Make an index mark on one gear tooth and
on the inside of housing. Turn jack screw shaft clockwise
until dng gear contacts worm gear and check index
marks. Visible wear or backlash of 1/2 tooth or more
requires immediate replacementof gears.
Reference SECTION 32-30-04, SIN 24-0001 thru
24-0377, for additional inspection and rigging
procedures,
ALTERNATE PROCEDURE:
(Dukes actuatoCs)Measure backlash by using a .025"
diameterwire of .025" thick shim as a feeler gauge. If
feeler can be inserted between gear teeth, replace
gears,
Repeat above procedure after rotating the dng gear
thru 90 degrees; 180 degrees; and 270 degrees.
(d) Repack gear box with recommended lubdcanL
(e) Reinstall end cap and resafety.
(f) Refer to Section 32-30-02 for proper actuator
adjustment and reinstallation instructions,
M. Perform landing gear operational check per
Section 32-30-01.
4. FUELSYSTEM INSPECTION.
SERVICE AND MAINTENANCE MANUAL
G. Check boost pump for leaks, security of
mounting, adequate fuel pressure, switch operation,
and condition of wiring and electrical connections.
H. Check fuel quantity gauges and transmitters for
secudty of mounting and condition of widng and
electrical connections.
I. Check fuel tank filler caps for O'dng condition,
cleanliness, secudty and condition of servicing
placards (Ref. 28-00-01).
5. EXTERIOR INSPECTION.
A. Thoroughlyclean aircraft exterior.
B. Inspect fuselage exterior surfacesfor corrosion,
damage, loose or popped rivets, dents, cans,
scratches,cracks,and deterioratedpaint.
C. Inspect windshields and windows for cracks,
crazing, scratches, condition of seals, and security of
installation.
D. Inspect wings, flaps, and ailerons for corrosion,
damage, loose or popped dvets, dents, scratches,
cracks, condition of attaching points, lubrication,
freedom of operation, free-play, travel, and balance
weight attachment.
. E. Inspect empennage for corrosion,damage, loose
or popped dvets, free-play, dents, scratches, cracks,
condition and lubdcafion of hinge points, attachment of
balanceweights, and freedom of operation.
F. Inspect cabin door and door frames for damage,
corrosion, nicks, dents, hinge security, and lubrication.
O. Inspect cabin door lock mechanism for
lubrication and proper engagement. See Section
52-11-00 for rigging procedures.
H. Inspect baggage door and baggage
compartment for damage, corrosion,warpage, hinge
security, condition to door frame and door seals,
condition and operation of door locking mechanism,
and conditionof cargotiedowns.
I. Inspect ventilatingsystemdrain linefor obstruction.
J. Inspect the alignment and lubrication of
overhead vent push-pull cable for smooth operation
(SIN 24-0001 thru 24-0377).
K. Inspect Landing/Taxi lights for security,
condition and proper adjustment. See Section
33-43-00 for adjustment procedures.
6. INTERIOR INSPECTION.
A. Inspect seats, seat tracks, and upholsteryfor
cleanliness and mounting security; check seats for
conditionand operation of positionlocks; inspect seat
structure for cracks, deformation, corrosion, and
mechanismlubrication.
B. Inspect safety belts, harnesses and attaching
bracketsfor cleanliness,condition,latch operation,and
securityof attachment.
C. Inspect for loose equipment that might restrict
controlmovement.
D. InspectOxygenSystem(ifinstalled)perChapter35.
A. Inspect
fuel tank exterior for evidence of fuel
seepageand
stain.
B. Drain tank and inspect tank interior when
seepageis evident.
C. Check fuel tank drains for leakage, sediment,
and water contamination,
D. Check fuel-tank vents for obstruction.
E. Check fuel selector valve for proper tank
selecfion, smooth operation, and leakage in OFF
position.
F. Check gaseolator for leakage; check sump for
sediment, water or other contamination. Inspect fuel
filter, clean or replace.
5-20-06
12-98
14
SERVICE AND MAINTENANCE MANUAL
M20d
7. INTERNAL INSPECTION.
A. Open access panels and inspectiondoom, and
removefaidngs as required,
B. Inspect wing/fuselage attaching bolts for proper
torque and safetying and evidence of damage or
corrosion,
C. Inspectforward sideof firewallfor damage,
D. Inspecttubularstructurefor corrosionor damage
(intedorpanelsand insulationmay requireremoval),
E. Check wires, lines, and ducts for security,
damage, interference,chaffing,and bonding,
F. Inspect wing dbs and stringers for cracks and
evidenceof damage or corrosion.
G. Inspectwingsparsfor damage,distorlion,
cracks,or
corrosion.
H. Inspect wing interior for foreign material,
corrosion, and evidence of fuel leakage.
I. Inspect Baggage Compartment floorboard
assembly, stdngers and doublers,
J. Inspect empennage attachment brackets and
hardware forcorresion,
NOTE
Seal all receptacles and plugs outside cabin
environment with Dow Coming #4.
8. FLIGHT CONTROL INSPECTION.
A. Inspect control column and control wheels for
full travel, proper dgging, free-play, binding, security of
mounting, proper lubrication, and direction of control
surface movement with relation to control movement,
CAUTION
All flight control components should be
checked to are
verify
all moisture drain holes
freethat
of obstructions.
B. Inspect elevator system for rigging, travel, stop
adjustment, condition of all bearings, bellcranks,and
hinges, secudty of mounting, damage, corrosion,
lubdcation and proper relations to control movement.
C. Inspect aileron system for damage corrosion,
lubdcation, rigging, travel, stop adjustment, condition of
hinges, bellcranks, pivots and rod end bearings, and
link bolt security.
D. Inspect rudder system linkage for damage,
corrosion, lubrication, security of link bolts, rod end
beadngs and proper relationship to control movements,
Check for free movement of toe-brake pedals and
proper rudder and nose wheel travel.
MOONEY AIRCRAFT CORPORATION
NOTE
All control rigging checks should be made with
the aircraft jacked and leveled and with the
landing gear retracted.
NOTE
Some elevatortrimtubes have polytape
wrapped at bulkhead penetrations. If tape
shows signs of wear, rerap (1/2 lap)tube with
2" wide Y9265 polyurethane tape. Trim tubes,
without tape, which show signs of abrading
grommet should be wrapped. See SB M20-185.
Maximum tube wear is .007 in. per wall or.014
in. diameter reduction.
9. INSTRUMENT/AVIONICS INSPECTION.
A. Inspect all instrumentwiring and plumbing for
conditionand properconnections.
B.Cleanand inspect
vacuum filter.
Replacegarter
filter on vacuum regulator.
C. Check vacuum regulator at vacuum manifold.
Check operation of high-and low-vacuum warning
lights or vacuum gauges.
D. Inspect all instruments for proper pointer
indication, range and limit markings, condition of
indicator markings, cracked or loose glass, slippage
marks, and secudty of installation.
E. Check compass for
proper
lighting,
compensation, secudty of mounting, liquid leakage,
and discoloration. Swing compass at annual inspection
and after any new equipment has geen Installed.
F. Inspect altimeter for scale error, discolored
markings, proper pointer readings, setting knob
freedom, and syncronization of barometric scale with
reference markers.
G. Inspect flight panel for security of mounting,
condition of shock mounts, freedom from interference
with structure,and conditionof groundstraps.
H. InspectAvionicsEquipmentfor poper operation&
seom_.
I. Inspect Avionics antennas, wiring & shielding for
obvious damage or defects.
J. Inspect pitot head for port obstruction; check lines
for cracks, dents, kinks, proper bend radius, and security
of attachmenLDrain system and check for leaks.
K. Inspect static ports for obstruction and
aerodynamic smoothness at port installations. Inspect
lines for bends, cracks, dents, kinks, and security of
attachment. Drain system and check for leaks. Check
alternatestaticpressuresource locatedon le_tflightpanel.
10. ELECTRICAL FUNCTIONAL TEST
E. Inspect stabilizertrim controlsystemfor security
A. Check operationof navigationlights.
and proper adjustment, sha_ and stop nutsfor proper
B.Checkoperationof landinglightor landing/taxi
lights.
dgging, trim control wheel for smooth operation,
C. Checkoperationof dome lightsand cigarlighter.
universaljoints for free-play and good working order
actuator threads for lubrication, linkage for corrosion,
D. Check operationof anticollisionlights.
and guide blocks for Io(_senessor excessivewear. See
E. Check operation of instrument and placard
Section27-42-00 for Electric Pitch Trim Inspection.
lights.Check rheostat.
F. Inspect flap system for rigging,travel, and stop
F. Check operationof pitothead heater.
adjustment;flap positionindicator for properoperation
actuator, push-pull tubes, interconnects, bellcranks &
G. Check operation of cluster gauge.
bingesfor corrosion,security, and lubrication.
12-98
5-20-06
15
MOONEY AIRCRAFT CORPORATION
M2OJ
SERVICE AND MAINTENANCE MANUAL
H, Chock operation of fuel gauges,
11. MISCELLANEOUS/OPTIONAL EQUIPMENT
I. Check operationof annunciatorlight pP.ss-to-test Inspect any installed equipment not covered by
switch,
previousparagaraphsfor proper operation, attachment
J. Check operation of ignition switch, and starter
or obvious defects,
solenoid.
12. POST INSPECTION FLIGHT TEST
K. Flight check operation of landing gear position
lights and warning horn.
L. Flight check operation of stall warning horn.
M. Check operation of "Prop De-Ice" (if installed).
Push switch =ON", observe prop de-ice ammeter for:.
(1) needle in green arc (8 to 12 AMPS -24-0001 thru
24-2999) and (2) fluctuation every 90 seconds as
heating elements are switched.
Observe aircraft ammeter on S/N 24-3000 thru
24-TBA for fluctuation as each boot cycles (8 AMPS
-24-3000 thru 24-TBA).
N. Inspect battery & battery connections for proper
installation and cleanliness.
5-20-06
16
Flight test the aircraft to verify correction of all
malfunctions and abnormalities. Make proper entdes in
aircraft log book.
12-98
r
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
13
-11
10
15-_
27 J
19
31
27
19
27
15&16
14
\
G_
_
_24-0001
-- _
27
- 24-1417
27
....
24-1418 -thru24-TBA
28
27 _
WING ACCESS CnVERS MAY VARY BETWEEN MFI])EL YEAR
AIRCRAFT, ,COMPONENT LnCATII3NS REMAIN BASICALLY UNCHANGED,
ACCESS COVER IDENTIFICATION, LUBRICATION & SERVICE GUIDE
FIGURE 5-4
NOTE
Access covers riveted in place during production need not be removed for routine inspections.
12-98
5-2O-O6
17
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
5-20-07
-ACCESS COVER IDENTIFICATION, LUBRICATION AND SERVICE GUIDE
ITEM
ITEM DESCRIPTION .......
LUBRICATION .....
NO.................
SYMBOL * , .......
1
....
....
....
....
....
....
....
....
Flight Instruments
Vacuum Regulator ..................
Turn Coordinator
.......
Q ...........
Vacuum System Filters--Replace at ..............
Control System Adjustments:
Control Column Bearing Ball ....
_ ...........
Rod End Beadngs .......
_ ...........
Universal Joints ........
_: ...........
Bellcranks .........
]C ...........
2
Engine Cowling ........
Vacuum Pump ........
AlternateAir Door Seals
....
....
3
....
....
....
....
4
.
....
....
....
....
....
....
5
....
....
....
....
....
....
....
....
....
6
....
....
....
....
.
.
INTERVAL
(HRS)
500 **
100
500 **
100
100
100
100
Q ...........
Q ...........
_
...........
100
500
50
Nose Gear Grease Fittings .....
_ ...........
RetractionTube Rod End Bearings
_ ...........
Bellcranks..........
_ ...........
Bungees ..........
_ ...........
Gear Door Rod End Bearings.....
_
...........
Main GearGrease Fittings .....
,Q
RetractionTube Rod End Beadngs .
. . _
Bellcranks..........
_; ...........
Bungees ..........
Z ...........
Gear Door Rod End Bearings .....
_
...........
ElectricGear Actuator Gear Box ....
e/_ .........
ElectricGear ActuatorBall Screw.
e ...........
ElectricGear ActuatorNo-back Spring .............
Elevator & Rudder Controls:
ControlTube Rod End Bearings
_ ...........
Bellcranks .........
_ ...........
Battery,Battery Relay .......
Q ...........
Stabilizer Trim ControlShalt:
UniversalJoints........
_: .....
Guide Blocks ........
& ...........
HydraulicReservoir .......
13 ...........
Oxygen, High Pressure Fittings ....
® .........
100
100
100
100
50
100
100
100
100
50
AR/AR ***
100
1000 ****
.....
ELT Transmitter (14 Volt) ......
Elevator & Rudder Controls:
Control Tube Rod End Beadngs
Bellcranks .........
Stabilizer Trim Jack Screw/Actuator .
Tail Strobe Light Power Supply ....
_
........
_11...........
]C ...........
? ...........
u ...........
100
100
100
......
.
.
.
.
.
100
100
50
50
100
100
1gO
100
100
*
See last page of section for lubrication symbol legends.
** Change garter tilter on vacuum regulator every 100 hours. Change instrument filters at 500 hours, clean
every
100 hrs.
*** No pedodic lubricant on Avionics Products #102000-1#2. If necessary to relubdcate, use Aeroshell 22,
Mobil 28 or MIL-G-81322 ONLY.
**** Replace No-back spring in Avionics Products (Ref. SI M20-52B) & Plessy Actuators (Ref. SI M20-92)
5-20-07
18
12-98
.......
SERVICE AND MAINTENANCE MANUAL
,
_'
M20J
ITEM
ITEM DESCRIPTION .......
NO.................
7
Empennage Attach Points......
. . .
.
Stabilizer Trim Attach Point .....
8
MOONEY AIRCRAFT CORPORATION
LUBRICATION .....
SYMBOL * . .......
_ ...........
O ............
INTERVAL
(HRS)
100
100
....
....
Elevator & Rudder controls:
Control Tube Rod End Beadngs
Trim Assist Bungee Attach Point
_lJ ...........
}: ...........
100
100
9
....
....
Elevator & Rudder Controls:
Control Tube Rod End Bearings
Trim Assist Bungees
......
_F ...........
:E ...........
100
100
10
Aileron Control Tube Guide Blocks
Z_ ...........
100
11
....
....
Aileron Controls:
Control Tube Rod End-Bearings
Bell Cranks .........
yl ...........
:E ...........
100
100
12
Aileron Control Tube Guide Blocks
A ...........
100
13
Main Gear Retraction Spdng/Bellcranks .
:_ ...........
100
14
....
Wing Attach Points
.......
Control Tube Guide Blocks
_ ...........
A ...........
100
100
15
....
....
Stabilizer Trim Screw & Stops .....
Indicator Adjustment Point
Stabilizer Trim Chain & Gear .
(p
100
16
....
....
....
....
....
....
....
....
17
....
....
18
....
....
....
....
....
....
Elevator & Rudder Controls:
Control Tube Rod End Beadngs
Bellcranks .........
Guide Blocks ........
Flap Indicator Cable .......
Electdc Flap Actuator Gear Box ....
(Lube gearbox and ballscrew)
Electric Flap Actuator Ball Screw ....
Baggage Compartment Floorboard Assy.
Electric Boost Pump
Gascolator ..........
Fuel Selector Valve .......
Control Systems:
Control Tube Rod End Beadngs
Control Yoke (Lower Section) ....
Nose Gear Steering Link ......
Rudder Pedal Cross Shall
.....
Rudder-Aileron Bungee ......
Hydraulic Brake Cylinder Pedal Linkage .
19
....
Aileron Control Tube Rod End Beadngs .
Outboard Flap Stops .......
.....
12-98
..........
q) ...........
100
W ...........
:_ ...........
_ ...........
:E ...........
_ ...........
100
100
100
100
500
8 ...........
_ ...........
100
100
_
}:
...........
.........
50
100
_ ...........
:_ ...........
_ ...........
_ ...........
:E ...........
:E ...........
100
100
100
100
100
100
_
u
100
100
...........
...........
5-20-07
19
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
ITEM
NO..
ITEM DESCRIPTION .......
SYMBOL * ..........
20
....
....
....
....
21
....
....
....
....
....
Baggage CompartmentDoor:.
Hinges ..........
Latches ..........
Seals ..........
Lock...........
Cabin Door:.
Hinges ..........
Latches
Seals ..........
Hold-OpenAnn ........
Lock...........
22
....
Engine Instruments
Radios
23
24
....
....
....
Oil Dip Stick, Oil FillerTube .....
Wheels & Brakes:
Wheel Beadngs........
Brake PressurePlates AnchorBolts
ShockDiscs.
25
26
....
....
....
Elevator& RudderControlStops ....
Nose Wheel:
Wheel Beadngs........
Shock Absorber........
Shock Discs.........
(]
27
ControlSurface Hinges
_: ...........
28
....
....
29
Propeller ..........
Starter Drive .........
Aitemator Drive Bell .......
Cowl Flap Motor and IndicatorCable.
=3 . . .
ray ...........
i] .........
D ...........
30
Remote CompassSender......
O .......
31
32
Strobe LightPower Supply .....
ELT Transmitter(28 Volt) ......
a
a
33
Speedbrake Cartridges
SYMBOL
MIL. SPEC. NO
I;
MIL-L-7870
MIL-G-81322
MIL-L-3545
MIL-H-5606
MIL-G-23827
A
5
LUBRICATION
(HRS)
_
9
_
5
.
......
100
100
100
_; ...........
9
_ ...........
q_ ...........
6
100
100
100
100
V ...........
AR
'_ ...........
w ...........
(I
250
50
50
...........
. . .
...........
250
100
50
........
100
:
.......
100
20
Each Flight
100
....
...........
........
100
.
......
0 ...........
LUBRICATION SYMBOL LEGEND
........
INTERVAL
...........
...........
...........
............
_
a
0
.
.
100
100
1000
DESCRIPTION
.........
.........
.........
.........
.........
LowTemperatureOil (General Purpose)
Grease (AvionicsProducts)
Grease (High Temperature)
HydraulicFluid (Red)
Graphite& MIL-G-3278 Grease or MIL-G-23827
PowderedGraphite
Teflon Spray (Td-flow) or equivalenL
................
................
5-20-07
2O
.
.....
12-98
SERVICE AND MAINTENANCE MANUAL
SYMBOL
MIL. SPEC. NO
M2OJ
........
DESCRIPTION
.£. ................
e
................
....
................
fi
................
V ................
r
Stick Lubricant (Door Ease or Equivalent)
Lubriplate 630AA (10% by Volume
Molybdenum Disulfide Mixture Permissible)
Seal Dressing
Inspect
TEXTRON-Lycoming Spec-No. 301F.
Mineral Oil per MIL-L-6082 or Compounded
Oil per MIL-L-22851 are approved when
used per following Viscosity Chart below.
(See Lycoming SLL229A, for Mobil AV1
approval)
Graphite and Kerosene, Lubdplate 797
................
¢P ................
®
.................
MOONEY AIRCRAFT CORPORATION
MIL-T-27730
Aeroshell Grease NO. 7 (On jackscrew
and inside Actuator Bearing Housing)
TAPE, Tetra fiuoroethylene
(Permacel Tape Corp)
GREASE (Dukes)
.........
MIL-G-23827, MOBIL # 27
.....
VISCOSITY CHART
Average Ambient
Air Temperature
MIL-L-6082
or SAEJ 1966
All Temperature
MIL-22851
SAE 15W50 or SAE 2gw50
Above 80 Deg. F
Above 60 Deg. F
30 Deg. to 90 Deg. F
0 Deg. to 70 Deg. F
SAE 60
SAE 50
SAE 40
SAE 30
g Deg. to 90 Deg. F
Below 10 Deg. F
SAE 20W-50
SAE 20
SAE 60
SAE 40 or SAE 50
SAE 40
SAE 30, SAE 40 or
SAE 2gw-40
SAE 20W50 or SAE 15W50
SAE 30 or SAE 20W-30
NOTE
Mooney Aircraft are delivered with the proper break-in oil; MIL-L-6082. Oil and filter should be
changed after 25 hours. Continue to use mineral oil for 50 operating hours or after oil consumption
has stabilized then change to oil conforming to Lycoming Specification 301F. Multi-viscosity oil,
both Mineral and Additive, is recommended.
NOTE
Refer to Textron Lycoming Service instruction No. 1014 ( * ) for lubricating oil recommendations.
( * ) = current revision or subsequent revisions.
\
12-98
5-20-07
21
MOONEY AIRCRAFT CORPORATION
M20J
BLANK
5-20-07
22
12-98
SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 6
DIMENSIONS AND AREAS
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 6
DIMENSIONS AND AREAS
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ..........
6-Effectivity/Contents .......
6-00-00 ............
6-00-00 ............
6-00-02 ............
6-00-03 ............
6-00-03 ...........
6-00-03 ............
CHAPTER
SECTION
SUBJECT .........
6-00-00 ........
6-00-01..........
6-00-02..........
6-00-03..........
PAGE
..........
DATE
1/2BLANK ..........
3 ...........
4 ...........
5
..........
6 ...........
7 ...........
8
..........
12-98
12-98
12-98
12-98
12-98
12-98
12-98
TABLE OF CONTENTS
SUBJECT
...........
Dimensions and Areas
..........
Aircraft.Specification ..........
Aircraft Dimensions ..........
Aircraft Stations ...........
12-98
PAGE
3
3
5
6
6-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
6-00-00
.
6-00-01
- AIRCRAFT SPECIFICATIONS
EngineMfgr.
EngineModel
- DIMENSIONS AND AREAS
ENGINE
No. Cylinders
Rated Horsepower
RPM
Min.Fuel Octane
Fuel CapacityTotal
TEXTRON-Lycoming
IO-360-AIB6D or
IO-360-A3B6D or
IO-360-A3B6
4
200 @ Sea Level
2700
100/130 or 100 LL.
66.5 U.S. Gal.
Useable
64.0 U.S. Gal
1 Oil Specification
Oil GradeNiscosity- Above
60 Deg.F
30 to 90 Deg. F,
0 to 70 Deg. F.
Oil Grade/Niscosity- Below
10 Deg. F.
LycomingSpec. No. 301F
Oil Capacity
MinimumSafe
Oil Level
(251.8 Liters)
(55.4 IMP Gal.)
(242.4 Liters)
(53.3 IMP Gal.)
SAE 50
SAE 40
SAE 30
SAE 40 or 50
SAE 40
20W-40
SAE 20 W
SAE 20W-30
8 qts
7,57 Liters
(LEVEL FLIGHT ONLY)
NOTE
Approved Multiviscosity oil is recommended, especially during cold weather operations.
INLET OIL TEMP
@ AMBIENT AIR TEMP:
2 qts.
_
MAXIMUM
Above 60 Deg. F.
30to 90 Deg. F.
0 to 70 Deg. F.
Below10 Deg. F.
• Oil Pressure
NormalOperation
Idle,Minimum
Max. Allowable (cold oil)
Start & Warm up
Cylinder Head
Temperature (CHT)
Max. Allowable
Recm'd Cruise
180 Deg. F.
180 Deg, F.
170 Deg. F.
160 Deg. F.
245 Deg. F.
245 Deg. F,
225 Deg. F.
210 Deg, F,
4750 F.
300 to 450° F.
246° C.
149 to 232° C.
PROPELLER
PropellerMfg.
Type
Model
STANDARD
McCauley
ConstantSpee_d
B2D34C214 _
OPTIONAL
Hadzell (Optional)
ConstantSpeed
HC-C2YK-1BF
60-90 P.S.I.
25 P.S.I.
100 P.S.I.
1
First 50 hours of operation - mineral (non-detergent) oil or equivalent corresponding to MIL-L-6082.
2
REPLACEMENT FOR B2D34C212/78C DA-4
12-98
6-00-00
3
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
PROPELLER (con't.)
STANDARD
OPTIONAL
Blade
Pitch Angle (High)
90DHB-16E
33(+/-)9.5Deg,
F7666A-3Q
29.3 Deg. to31.3
Deg.
Pitch Angle (Low)
Diameter
@ 30 IN. STA,{
13.9(+A) 0.2Dog.
74.0 In. Max/73 In. Min,
McCauley(C290D5/T17)
High- 27.5 (+/-) 0.2Dog,
Low- 14.0(+/-) 0.2Deg.
High-2g,5 (+/-) 0.5Deg.(Eft. after C/W S.B. #198)
Governor
14.1(+/-) .1 Deg.
73 Inches
McCauley
AIRFRAME
._
A. Approximate
EmptyWeight
B. GrossWeight
C. Useful Lead
D. Wing Loading
E. PowerLoading
METRIC/OPT/MISC
1700 lb.
2740 Ib./2900 lb. *
1040 lb./1209olb.*
16.4 lb./sq,tl _/16.59 Ib./sq.ft*
13.7 Ib/hp114.5Ib./HP *
771 kg.
1243 kg./1315kg. *
473,.7 kg./544.3,_,g.*
76.58 kg/m=/81.02 Kg/m'*
6.22kg/HP/6.58 kg/HP*
WINGS:
A. Airfoil At Root
B. Airfoil At Tip
C. Mean Aerodynamic
Chord @ Wing Sta. 93.83
D. CG Range
E. Geometdc Twist (DEG)
F. Incidence Angle
(DEG) From Sta 20.
to W_ngTip
G. Dihedral angle (DEG)
H. Aspect Ratio
I. Taper Ratio (CS/CT)
NAC632215
NAC641412
59.18 inches
13.4 to 28.7%
-1.5 Degree
* SIN 24-3201,24-3218 thru 24-TBA &
24-1686 thru 24-3200, 24-3202 thru
24-3217 when CANSL91-2 end MAC
drawing 940071 is incorporated.
2.5 Degree
5.5 Degree
7.338
1.935
FUSELAGE:
A. Cabin Dimensions:
(1) Height
(2) Width
(3) Length
(4)
(5) Cabin
Cabin Door
Door Width
Height
44 5"
43.5"
114"
29"
35"
113.03 cm
110.49 cm
289.56
cm
73.66 cm
88.9 cm
3
15,68 Ib/sq 11.(S/N 24-1038 thru 24-3200, 24-3202 thru24-3217)
6-00-00
4
12-98
f
MOONEY AIRCRAFT CORPORATION
VV'I'S& LOADINGS: (cont.)
B. Baggage Compartment:
(1) MAX. Loading
(2) Baggage Space
(3) Baggage Door
Width
(4) Baggage Door
Height
(5) Hat Rack
Capacity
C. Landing Gear.
(1) Type
(2) Operation
(3) Wheel Track
(4) Wheel Base
(5) Tire Size-- Nose
(6-Ply Rating
(6) Tire Size-- Main
(6-Ply Rating)
(7) Tire Pressure,.-(8) Tire Pressure-6-00-02
M20J
STANDARD
SERVICE AND MAINTENANCE MANUAL
.
:_.,
.
120 Ibs
17.0 Cu. Ft.
(24-0001 thin 24-3153)
15.3 Cu. Ft.
(24-3154 thru 24,TBA)
54.43 kg
0.476 Cu. M.
17"
43.18 cm
20.5"
52.07 cm
10 lbs
4.54 kg
Tdcycle Retractable
Electrical
9' 2"
5'11 9116"
279.4 cm
181.73 cm
5.00 x 5
(TYPE III)
6.00 x 6
Nose - 49 Ibs/sq.in.
Main - 30 Ibs/sq.in.
(TYPE Ill)
36'1''4
10.998 meters
24'8"
8'4"
11'9"
7.52 meters
1.321 meters
3.581 meters
174.786 sq. Ft.
11.4 sq. It.
17.9 sq. It.
7.9 sq. It.
6.25 sq. ft.
16.238 sq. meters
1.059 sq. meters
1.663 sq. meters
0.725 sq. meters
0.518 sq. meters
21.5 sq. ft.
13.0 sq. It.
1.900 sq. meters
1.208 sq. meters
0.433 Cu. M
- AIRCRAFT DIMENSIONS
DIMENSIONS
A. Wing Span
B. Fuselage
Length
C. Tail Height
D. StabilizerSpan
AREAS:
A. Wing
B. Ailerons
C. Flaps
D. Vertical Fin
E. Rudder
F. Hodzontal
Stabilizer
G. Elevators
4
Prior to SIN 24-1038--35'0"
12-98
6-00-02
5
SERVICE AND MAINTENANCE
6-00-03
- AIRCRAFT
MANUAL
M20J
MOONEY AIRCRAFT
CORPORATION
STATIONS
(751.BcFO
24' 8 °
•=
•
(18
(254c_)
I 5,1,9,16.
I1,,,i..I _181'73_
I
.-,i.. I
h
11'9" (358,1cm)
-_
I
36" 1" (1099.8cm)
i
24--0001 Thru 24--3153
_I
_
I
9' P" _
( 279.4 cr_ )
PRINCIPAL AIRCRAFT
6-00-03
6
_
=
24-3154 Thru
_/INGS
TBA
I
_RAM
AIR
DELETED
ON
SIN 24-3154 THRU 24-TBA
I
DIMENSIONS - FIGURE 6-1
12-98
MOONEY AIRCRAFT CORPORATION
STA
210,97
M20J
STA
147,75
SERVICE AND MAINTENANCE MANUAL
STA
103,50
STA
59,25
STA
24,50
193,50
FIGURE 6- 2
ST A
24-3000 THRU 24-3078
-- 5,3
7 5
STA
3,68
STA
199,50
STA
164,00
STA
130,00
STA
88,00
FUSELAGE
STA
53,00
STA STA
;:'1,80 -5,00
STATIONS
SMK-6-3
FUSELAGE STATIONS - FIGURE 6-3
NOTE
The datum line station e.0 is 5 inches aft of the nose gear trunnion pivot point.
(Reference Figure 8-1.)
12-98
6-00-03
7
SERVICE AND MAINTENANCE MANUAL
STA
G7,75
M20J
STA
42,25
MOONEY AIRCRAFT CORPORATION
STA
4,43
STA
42,25
STA
70,0
I
STA
52,50
STA
25,75
STA
5,25
z_
EMPENNAGE
STATIFINS
SMK6-4
EMPENNAGE
6-00-03
8
STATIONS -FIGURE 6-4
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 7
LIFTING AND SHORING
SERVICEAND MAINTENANCEMANUAL
M20J
MOONEY AIRCRAFTCORPORATION
CHAPTER7
MFTINGAND SHORING
LISTOF EFFECTIVEPAGES
CHAPTER
SECTION
SUBJECT ...........
7-Effectivity/Contents .......
7-10-00 ............
7-10-00 .......
CHAPTER
SECTION
SUBJECT .........
7-10-00 .........
PAGE .........
1/2BLANK ..........
3
4
DATE
.......
.....
12-98
12-98
12-98
TABLE OF CONTENTS
SUBJECT ........
Jacking .......
12-98
PAGE
3
7-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
7-10-00
-JACKING
When it is necessary to raise the aircraft off the
ground:
CAUTION
Do not raise the aircraft on jacks out of doors
when wind velocity is over 10 MPH. Jacks
should be on hard surface,
CAUTION
Do not place jack directly on propeller de-icing
boots. Cushion with a layer of 3/8 inch thick
hard rubber or equivalent,
4. Raise aircraft, keeping wings as nearly level as
possible.
5. Secure safety lockson eachjack.
CAUTION
When lowering aircraft on jacks, bleed off
pressure on all jacks simultaneously and
evenly to keep aircraft level as it is lowered.
CAUTION
Individual wheels may be raised without raising
the entire aircraft. Wheels not being raised
should be chocked fore and aft.
1. Install jack points in fiedown mounting holes
outboard of each main gear.
2. Use standardaircraft jacks at both wing hoist points
(wing tiedown eyebolt receptacles) outboard of the
main gears. While holding jack point in place, raise
jack to firmlycontactjack point.
3. Use a yoke-flame jack under propeller to lift the
nose.
NOTE
It is not recommendedto use tail-tie down
fitting during jacking process to lift nose wheel
off ground.
CAUTION
Do not leave aircraft on jacks for extended
periods of time with a tail stand in place. The
wing jack may bleed down, putting excessive
loads on the front jack point and tail cone.
12-98
7-1O-00
3
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
/
BLANK
7-10-00
4
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 8
LEVELING AND WEIGHING
SERVICEAND MAINTENANCEMANUAL
M20J
MOONEY AIRCRAFTCORPORATION
CHAPTER8
LEVELINGAND WEIGHING
UST OF EFFECTIVEPAGES
CHAPTER
SECTION
SUBJECT ...........
8-Effectivity/Contents .......
8-00-00
i
•
*
8-00-01
PAGE ........
,
•
i
1/2BLANK ...........
3
•
•
*
4
............
DATE
•
•
•
•
,
•
,
o
12-98
12-98
12-98
TABLEOF CONTENTS
CHAPTER
SECTION
SUBJECT
..........
8-00-00 .......
8-00-01 .......
SUBJECT
Leveling ............
Weight and Balance.......
12-98
PAGE
3
3
8-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
8-00-00
M20J
- LEVELING
Placea
spiritlevel
onaccess
the skindoor
spliceor
levelingscrews
above the
tailcone
when
leveling the
aircraft longitudinally.Level the aircraft by increasingor
decreasingair pressurein the nosewheel tire.
Level aircraft laterally (wing tip to wing tip by placing
Spirit.Level oncenterseattracksin frontofspar,
Front seats must be in the full forward position when
weighing.(Use skin splice SIN 24-0001 thru 24-0083,
24-0085 thru 24-0900 and leveling screws SIN
24-0084, 24-0901 & ON.) (See FIGURE 8-1)
8-00-81
SERVICE AND MAINTENANCE MANUAL
8. Find reference point by dropping a plumb-bob from
center of nosegear trunion(retractingpivotaxis) to the
floor. Markthe pointof intersection.
9. Locate centerline of the main wheel axles in the
same manner.
10. Measurethe horizontaldistancefrom the reference
point to main wheel axle center line. Measure
horizontaldistancefrom center line of nose wheel axle
to centerlineof mainwheel axles.
- WEIGHT AND BALANCE
To weigh the aircraft select a level and draft free work
area, then:
1. Checkfor installationof all equipmentas listedin the
Weightand BalanceRecord.
2. Ground aircraft and drain fuel tanks per Section
12-10-02, 2.
3. Add unusable fuel to each tank, (see applicable
P'lot'sOperat ng Handbook for a rcraft be'ng serv=ced
for properquantityof unusablefuel).
4. Fill oilto capacity(8 quarts).
5. Position a 2000-pound capacityscale undereach of
the three wheels.
6. Level aircraft as described in Section 8-00-00 and
centernose wheel.
7. Weigh the aircraft.
12-98
8-00-00
3
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
11. Record weights and measurements and compute basic weight and CG as follows:
Lc/G = LM/R- 5 - LM
_
a. CG Forward of Main Wheels
LBS
Weight of Nose
X
(WN)
b. CG Aft of Datum (Station0).
IN. -Distancefrom Center
Nose Gear Tmnion to
Center of Main Wheel
Axles (Hodzontal)
(LM/R)
IN.
-:DistanceBetween
Main and Nose Wheel
Axle Centers
(LM/N)
5
IN.
Distancefrom
Nose Gear
Trunion to Datum
--
LBS.
Total Weight of
Aircraft
N.
CG Forwardof
Main Wheels
(Wr)
(LM)
IN.
Resultof Computation
Above (a.)
CONSTANT
=
(LM)
=
IN.
CG (FUS STA)
Distance Aft of
Datum (Empty
Weig.ht CG)
(LC/G)
NOTE: Empty weight includes unusable fuel and full oil and is computed with gear down and flaps up.
REF,PDINT
(NOSE GEAR
TRUNNION
REFERENCE
]]ATUM(STA,0)
LEVEL REF,
(SKIN SPLICE DR
STA,_-5)
__
II I"--LCC
LM
L" -'-'----,."
LM/R _
LM/N
WN
WR
_a/L
__
_
MEASUREMENTS
LM/R
INCHES
LM/N
INCHES
WEIGHT AND BALANCE DIAGRAM - FIGURE 8-1
8-00-01
4
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 9
TOWING AND TAXIING
SERVICEAND MAINTENANCEMANUAL
M20J
MOONEY AIRCRAFTCORPORATION
CHAPTER9
TOWING AND TAXIING
LIST OF EFFECTIVEPAGES
CHAPTER
SECTION
SUBJECT ..........
9-Effestivity/Contents
9-00-00
9-30--00
CHAPTER
SECTION
SUBJECT ...........
9-00-00 .......
9-10-00 ..........
9-20-00 ..........
9-30-00 ......
PAGE .......
.......
......
DATE
1/2BLANK ..........
8
........
4
12-98
12-98
12-98
TABLE OF CONTENTS
SUBJECT
Ground Handling ..........
Towing
...........
Warmup and Taxiing.........
Emergency Procedures ......
12-98
......
PAGE
3
3
3
3
9-EFF/CONTENTS
I/2BLANK
MOONEY AIRCRAFT CORPORATION
9-00-00
- GROUND HANDLING
9-10-00
-TOWING
M20J
SERVICE AND MAINTENANCE MANUAL
9-30-00
- EMERGENCY PROCEDURES
1. Engine Fire During Starting.
Use a towbar for moving the aircraft. The towbar
attaches to the nose gear crossbar. One man can
move the aircraft providing the ground surface is
relatively smooth and the tires are properlyinflated.
When no towbar is available, or when assistance in
movingthe aircraft is required, push by hand: (1) on
the wing leadingedges, and (2) on the inboardportion
of propeller blades adjacent to the propeller hub.
Towing by tractor or other powered equipmentis not
recommended.
CAUTION
Exercise care nottoturn the nose wheel past
its normal swivel angle of 14 degrees either
side
center.
Exceeding
thecause
turn limits
shown
onof
the
turn indicator
may
structural
damage. Maximum allowable damage to nose
gear leg assembly is 1132inch dent.
9-20-00
- WARMUP AND TAXIING
Before attempting to warmup or taxi the aircraft,
ground personnelshould be checked out by qualified
pilotsor otherresponsiblepersonnel,
1. Start and warmup engine. (Refer to Pilots
OperatingHandbook)
2. Taxi forward a few feet and check brake
effectiveness,
3. While taxiing, make shallow turns to test nose
gear steering.
4. Check operation of gyro instruments and turn
coordinatorduringturns.
5. Checkengineinstrumentsfor sluggishresponseto
enginecontrolmovements.
A, Continuecrankingenginewith starter,
B, Set mixturecontrolat IDLE, CUTOFF.
C. Turn fuel selector handleto OFF.
D. Open throttleto FULL.
E. Turn MASTER switchOFF.
F. Pushcabinheat controlto OFF.
G. Closecowlflaps.
H. If fire is not extinguished,proceed as follows:
(1) Turn electricalswitchesOFF.
(2) Discharge fire extinguisher into engine
compartment throughnose cowlopeningsand through
cowlflap openings.
(3) Callfor fire-fightingequipment.
2. Fuselage or Wheel Well Fire. In case of fire in
wheel well (or in the cabin or fuselage area), turn all
fuel, electrical,and ignitioncontrolsto the OFF position
beforeevacuatingthe aircraftto extinguishthe flames.
3. Electrical Fire. Circuit breakers (or circuit-breaker
switches),that automaticallyinterruptthe flowof power
when an overload or short circuit occurs, protect all
electrical circuits(exceptthe ignition-startercircuits).In
the event of an electricalfire, immediatelyturn off the
master/alternator field switch. Make sure that only a
fire extinguisherapproved for electricalfires is used.
12-98
9-00-00
3
SERVICE AND MAINTENANCE MANUAL
M20J
BLANK
9-30-00
4
12-98
MOONEY AIRCRAFT CORPORATION
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 10
PARKING AND MOORING
SERVICEAND MAINTENANCEMANUAL
M20J
MOONEY AIRCRAFTCORPORATION
CHAPTER10
PARKINGAND MOORING
UST OF EFFECTIVEPAGES
CHAPTER
SECTION
SUBJECT .........
lO-Effectivity/Contents.......
10-00-00 ............
10-10-03 ...........
PAGE ...........
DATE
1/2 BLANK ..........
8
..........
4
...........
12-98
12-98
12-98
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT .....
10-00-00 .....
10-10-00 .....
10-10-01 .........
10-10-02 .........
10-10-03 .........
10-20-00 ........
SUBJECT ......
PAGE
General...........
Parking...............
Storage (Flyable)...........
Storage (Prolonged) ..........
Returnto Service...........
Mooring
.............
3
3
3
3
4
4
12-98
IO-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
10-00-00
M20J
- GENERAL
SERVICE AND MAINTENANCE MANUAL
10-10-02
- STORAGE (PROLONGED)
The parkingbrakes are set by applyingthe brakes and
pulling out on the parking brake knob. Release the
brakes by pushing in on the parking brake control
if the aircraftis to be stored for an extended period of
time, the following steps are recommended for
protection:
knob.
1. Refer to paragraph 10-20-00 for mooring
instructions.
2. Run engine (minimum of 15 minutes at 1500
RPM) until oil temperature reaches normal operating
range,
NOTE
There is no need to depress the brake pedals to
relieve the pressure in the lines during release
of parking brake control,
There are three tiedown points on the aircraft, one on
each wing outboard of main gear (fledown rings are to
be threaded into built in receptacles) and the tail
skid/Uedownfitting onthe aft end ofthetailcone.
10-10-00
3. Drain engine oil sump and refillthe sump with a
preserative oil (Socony Aurex 901 or equivlent)
preheated between 200 and 220 degrees F.
4. Start engine and run at 1000 RPM for five
minutes.
- PARKING
5. Shut engine downand remove spark plugs.
When parkingthe aircraft, placewheel chocks fore and
aft of the main wheels. The parking brakes may be
usedfor short-durationparking.
6. While motodng engine with starter, spray each
cylinder(throughspark plug holes)with approximately
2 oz. of hot preservativeoil.
CAUTION
Do not set parking brakes when they are
overheated
or slush
when accumulation
cold weather could
moisture and
in the freeze
brake
CAUTION
Do not exceed starter operating limits when
motoring engine.
mechanism. Do not set parking brakes when
aircraft
down.
For maximum
protection,
hangar is
thetied
aircraft
during
severe weather
and
high winds,
7. When all cylindershave been sprayed, position
propellerhorizontallyand resprayeach cylinderwithout
movingpropeller.
8. Attach a warningtag to one of the blades stating
that propelleris notto be rotated.
10-10-01
- STORAGE (FLYABLE)
Outdoor storage requires adequate moodng and
tiedown facilities. The following precautionary
measures are recommended for keeping the aircraft
serviceable and ready-to-fly.
1. Refer to
instructions,
paragraph 10-20-00 for
mooring
2. Maintain an propellerthrough.
oil film on internal
pads,
frequentlypullthe
Runengine
enginefor
15
minutes at 1500 RPM (or until oil temperature
normalizes)once every seven days.
3. After engine run, pressurize the fuel system (turn
electric fuel boost pump on) push mixture controlto
R CH, and open throttle half way to fill the fuel injector
with fuel.
4. Keep fuel tanks filled at least one-half full to
minimize moisture condensation. Keep battery fully
charged,
9. Installdehydratorplugsin spark plugholes.
10.Cap ignitionharnessleads.
11.Drainpreservativeoilfrom sump.
12.Attach a warning tag to the throttle control in
cockpitstatingthat engine has no lubdcatingoil.
13.Drainall fuel from fuel injecto[;then, pumpoil into
the fuel injector at five PSI untilinjector is full; do not
drain the injectoralter flushing.
14.Lubricate aircra_ in accordancewith instructions
givenin the LubricationGuide.
15.Tape or coverallopenings.
16.Remove battery, charge fully, and store in a cool
place.
17.Raise aircraft to remove weight from the tires, and
block up the wheels.
5. Install protective covers over pitot head, engine
cowl openings,staticports,etc.
CAUTION
If weight is not removed from tires, rotate
wheels to a new position at least once each 30
days to prevent fiat-spotting the tires.
6. Maintain a good wax finishon all exterior surfaces,
18. See appropdate TEXTRON-LYCOMING Service
Bulletin for engine preservation. Attach warning
placards if preservation procedures make engine
inoperable.
12-98
10-00-00
3
SERVICE AND MAINTENANCE MANUAL
10-10-03
M20J
MOONEY AIRCRAFT CORPORATION
-RETURNING TO SERVICE
14. Check fuel tank vents for obstruction,and drain
If the aircraft has been storedfor an extended period of
time, it is advisable to perform a 50-hour periodic
inspectionalter completionof the following preliminary
steps:
t. Remove blocksfrom wheels. Check tire inflation.
2. Check and install battery.
sumpsto removemoistureand sediment.
15. Complete50-hour and preflightinspections.
16. See appropriateTEXTRON-Lycoming Service
Bulletinfor servicingof the engine.
10-20-00
- MOORING
When mooringthe aircraftout of doors:
3. Remove tape and coversfrom openings.
4. Remove warningplacards (if any).
1. Head aircraftintothe wind.
2. Place chocksfore and alt of each mainwheel.
5. Replace engineei[filter.
6. Clean engine oilsuctionand pressurescreens,
7. Clean and checkoil pressurerelief valve.
3. Driveofstakes
ground
outboard
each inmain
gearapproximatelythree
and to either sidefeet
of
tailskid.
4. Installtiedown rings in wing receptaclesoutboard
8. Clean and check oil temperaturebypass valve,
9. Fill engine sump with proper grade of lubricating
oil.
10. Clean and reinstall engine air-inlet filter,
of
each
mainwing
gear.tiedown
Tie a 600-pound
tensiletostrength
rope
to each
ring and anchor
ground
stake.Allowa littleslackin eachtiedown rope.
5. Tie the center of a rope to tail skid tiedown ring
and anchor rope ends to ground stakes at either side
oftaU.
6. For additional security, attach a rope to the nose
gear and anchor to a ground stake.
7. Lock controls by looping right front seat safety belt
through the control wheel and drawing belt snug.
11. Check ignition hamess.
12. Remove dehydrator plugs and install spark plugs,
13. Check and clean fuel injector nozzles and
screens. Drain oil from fuel injector,
10-10-03
4
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 11
!
PLACARDS AND MARKINGS
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 11
PLACARDS AND MARKINGS
LIST OF EFFECTIVE PAGES
CHAPTER
BEC'IION
SUBJECT ...........
11-Effect./Contents ........
11-00-00 ............
11-20/30-00 ...........
PAGE
..........
DATE
1/2BLANK ..........
3 ...........
4 ...........
12-98
12-98
12-98
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
11-00-00 ........
11-10-00 .........
11-20/30-00 ........
SUBJECT
........
General ..............
Markings .............
Placards,Exterior/Interior.
12-98
........
PAGE
3
3
3
11-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
11-00-00
M20J
- GENERAL
FAA requiredplacardsand markings.
NOTE
All placards should be inspected for proper
location readability and security during
ma ntenance actions, When an airplane has
been painted inspect all placards to assure that
they are not obscured by paint.
SERVICE AND MAINTENANCE MANUAL
11-19-00
- MARKINGS
The exteriorpaint schemes for the various model year
aircraft are depicted in the M20J Illustrated Parts
Catalog.
11-20/30-00
- PLACARDS,
EXTERIOR/INTERIOR
All requiredplacards and their locations,both interior
and exterior, are listed in Section II of the FAA
Approved Flight Manual and Pilot's Operating
Handbook.
12-98
11-00-00
3
SERVICE AND MAINTENANCE MANUAL
M20J
BLANK
11-20/30-00
4
12-98
MOONEY AIRCRAFT CORPORATION
MOONEY AIRCRAFT CORPORATION
M20J
CHAPTER 12
SERVICING
SERVICE AND MAINTENANCE MANUAL
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 12
SERVICING
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
12-Eff./Contents
12-00-00 ............
12-10-04 ............
12-20-00 ............
12-20-05 ............
12-20-06 ............
12-20-06 ............
PAGE
........
..........
DATE
1/2BLANK ..........
3............
4............
5............
6 ...........
7 ............
8............
12-98
8-93
5-93
5-93
12-98
5-93
5-93
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
12-00-00 ........
12-00-01 .........
12-10-00
12-10-01
..........
12-10-02
..........
12-10-03
..........
12-10-04
..........
12-20-00 ........
12-20-01 .........
12-20-02
12-20-03 .........
12-20-04 .........
12-20-05 .........
12-20-06 .........
SUBJECT
......
......
........
PAGE
Servicing ..............
Servicing Intervals ..........
Replenishing ............
Fuel Tanks ...........
Fuel Drains ...........
Engine Oil ...........
Oxygen System ..........
Scheduled Servicing ...........
Induction Air Filter ..........
Battery .............
Tires & Wheels ...........
Brake Reservoir ...........
Hydraulic Brake ...........
Cleaning .............
3
3
3
3
3
3
4
5
5
5
5
5
6
6
12-98
12-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
-
12-00-00
-SERVICING
12-00-01
- SERVICING INTERVALS
M20J
SERVICE AND MAINTENANCE MANUAL
C. After draining, be sure fuel drain valve control is
returned to the closed position and the valve is not
leaking outsidethe aircraft.
The specified intervals (refer to Chapter 5) are
considered adequate to meet average requirements
under normal operating conditions. It is advisable,
however, to shortenserviceand maintenanceintervals
when operating under abnormal environmental
conditions,suchas extreme temperature ranges, dusty
atmospheric conditions, high humidity and moisture,
unimproved airport facilities, or unusual operating
requirements,
12-10-00
NOTE
Isopropyl Alcohol may be added to fuel tanks. It
is extremely important to thoroughly BLEND
the isopropyl alcohol in with the fuel supply in
quantities not to exceed 1% of the total by
volume.
- REPLENISHING
12-10-01
-FUEL TANKS
Keep fuel tanks at least half filled to minimize
condensation and moisture accumulation in tanks.
(Fuel capacityis given in SECTION 6.)
WARNING
Ground the aircraft
and fuel service vehicle.
Groundor
servicing
nozzle
to wing.
Permit
no
smoking
open flame
within
50 feet
of aircraft
or vehicle.
2. Dafueling. Fuel tanks may be drained by pumping
fuel out with the electric fuel boost pump, siphoning
fuel through the filler ports, or removing tank quick
drainvalves.
WARNING
Allow no smoking or open flame within 50 feet
of the defueling area. Ground the aircraft and
fuel container during all defueling operations.
A. To defuelthe aircraftusingfuel boostpump:
(1) Disconnectfuel line from electric boost pump
outlet atthe f'_ng forward ofthe firewall.
WARNING
Each fuel tank is vented to the atmosphere at
its outboard aft corner; vent openings are on
the lower wing surface. Check vents for
obstruction before each flight,
12-10-02
WARNING
During cold weather operation, frequently
check fuel selector drain for ice formation by
repeating procedures 1., A, B and C above.
(2) Connectto outputfittinga flexible linethatwill
reach fuel receptacle.
(3) Turn fuel selector valve to the tank to be
drained, and remove filler capfrom fuel fillerport.
- FUEL DRAINS
A fuel-drain valve is located in the aft inboardcomer of
each tank to provide for drainage of moisture and
sediment. Use the small plasticcup furnishedwith the
flyaway kitto drain the fuel sumps. Drainwing tank and
selector valvesumpsor gascolatorbeforethe firstflight
of the day and after each fuel service to inspect for
water
and/ororcontamination.
free of water
contamination.Continue draining until
(4) Tum on fuel boost pump untiltank is empty.
Repeat steps(3) and (4)to drain other tank.
(5) To completelydrain fuel system also drain
wing sumps and the fuel gascolator valve sump until
fuel stopsrunning.
NOTE
When defuefing using removable tank quick
drains it is only necessary to remove the drains
and to operate the gascolator drain.
NOTE
SIN 24-0378 & ON. The gascolator (fuel drain) is
separate from the fuel selector. The fuel
selector is located aft of the console on the
floor and the gascolator is located to the left of
the fuel selector. Separation of the gascolator
and the selector does not change fuel drain
procedures.
WARNING
After servicing the aircraft with fuel, wait at
least five minutes for moisture and sediment to
settle before draining and checking both the
fuel tank sumps and the fuel selector valve
drain,
1. Fuel Selector Drain. The fuel gascolator is at the
lowest point in the fuel system and has a drain valve
operated by a controlon the floor in the cabin.To drain
the fuel selactorvalve:
A. Switch fuel selector valve handleto L and pull
fuel drain valve controlringfor 10 seconds,
B. Switch fuel selector valve handle to R and pull
fuel drain valve controldng for 10 seconds,
12-10-03
-ENGINE OIL
Check engine oil level after engine has been stopped
long enough for oil to drain back into sump. The oil
fillercap accessdoor is locatedin the top cowling.Any
lubricating oil, either straight mineral (MIL-L-6082) or
compounded(TEXTRON LycomingSpec. No. 301F) or
MIL-L-22851are acceptable for use after break-in
period. Approved products and engine oil viscosity
requirementsare shown in Chapter 5-20-07.
12-98
12-00-00
3
SERVICE AND MAINTENANCE MANUAL
M20J
CAUTION
The terms "detergent", "additive", and
"compounded" used in this manual are
intended to refer to a class of aviation engine
lubricating oils to which certain substances
have been added to improve them for aircraft
use. These terms do not refer to such materials
commonly known as "top cylinder lubricant",
"dopes" and "carbon remover" which are
sometimes added to fuel or oil. These products
may damage the engine and therefore, should
not be used. Under no circumstances should
automotive oil be used, since such oils could
cause engine damage.
MOONEY AIRCRAFT CORPORATION
When changing from straight mineral oil to additive or
compounded oil, after several hundred hours of
operation on straight mineral oil, take the following
precautionarysteps:
1. Do not mix additive oil and straight mineral oil.
Drain straightmineraloilfrom engine, changefilterand
fillwith additiveoil.
2. Do not operate engine longer than five hours
beforeagainchangingoil.
3. Check oilfilterfor evidence of sludge.
Change oil and replace oil filter element every 10
HOURS if sludgeis evident. Resume normal oil drain
periodsafter sludgeconditionsimprove.
Oil Recommendations for New-Engine or Newly
Overhauled Engine Break-In.
New or newly overhauledengines should be operated
on aviationgrade straight mineral oil during the first 50
hours of operation or until oil consumption has
stabilized.The aircraft is delivered from Mooney with
•
i_roperbreak-in
oil (MIL-L-6082) or SAE 20W-50 Type
OIL CHANGING RECOMMENDATIONS.
The oil sump is equipped with a quick drain fitting.On
aircraft equippedwith either an internalor external oil
filter, the recommended engine oil change intervals is
at 50-HOUR FLIGHT OPERATION INTERVALS•
If an enginehas been operating on straight mineral oil
for several hundred hours, a change to additive oil
shouldbe undertaken with caution. If the engine is in
an extremely dirty condition,the switchto additive oil
should be deferred until after engine has been
overhauled,
NOTE
During periods of prolonged operation in dusty
areas or in cold climates, or when flights have
been of short duration with prolonged idling
time, change oil and filter element each 25
HOURS, or morewarrant.
often when conditions
12-10-04
- OXYGEN SYSTEM (OPTIONAL)
The oxygen cylinder, when fully charged, contains
approximately 76 cubic feet of aviators breathing
oxygen (SpecificationsNo. MIL-O-27210). Recharging
of this oxygen cylinder should be accomplished by
using the appropriate Scott rechargingfittings to the
pressure shown on (Figure 12-1), Pressure vs.
Temperature Table.
:
WARNING
Oil, grease or other lubricants in contact with
oxygen create a serious fire hazard, and such
contact must be avoided when handling oxygen
equipment.
AMBIENT
TEMPERATURE
DEGREES F
FILLING
PRESSURE
PSIG
AMBIENT
TEMPERATURE
DEGREES F
FILLING
PRESSURE
PSIG
O
10
20
30
40
1650
1700
1725
1775
1825
50
60
70
80
90
1875
1925
1975
2000
2050
OXYGEN PRESSURE VS TEMPERATURE TABLE
FIGURE 12-1
12-10-04
4
12-98
MOONEY AIRCRAFT CORPORATION
M20J
NOTE
The oxygen cylinder should not be run down to
less than 100 p.s.i. Below this pressure
atmospheric contamination of the cylinder may
occur, requiring valve removal and cylinder
cleaning and inspection at an FAA approved
repair stations,
9. Reinstall filler in aircrafl making sure of proper
sealingand secodty.
t 2-20-02
- BATrERY
Service the battery with distilled water to maintain
electrolyteabove plates.After adding water in freezing
weather, chargebattery long enoughto mix electrolyte
and water. Keep battery electrolyte above a specific
gravity of 1.225 to avoid freezing. To service the
battery:
NOTE
Refer to Section 35-00-00 for periodic bottle
pressure check,Any time fittings are
disconnected on the oxygen system the
threads should be treated with
tetrafluoroethylene tape (MIL-T-17720). Prior to
reconnection the system should be checked for
leaks with leak testing compound
(MIL-L-25567). if no leaks are found wipe the
system clean and dry.
12-20-00
SERVICE AND MAINTENANCE MANUAL
1. Remove battery box cover. Check electrolyteand
service battery as required.
CAUTION
Battery gases may be explosive.
. SCHEDULED SERVICING
12-20-01
-INDUCTION AIR FILTER
The importanceof keeping the inductionair filterclean
cannotbe overemphasized. A clean filter promotesfuel
economyand longer engine life. The dry-typefilter can
usuallybe washed six to eight times within 500 hours
or one yearbefore replacement is necessary,
To clean the dry-type induction air filter:,
1. Remove filter element,
2. Direct a jet of air against down or clean side of
filter (opposite to normal airflow). Keep air nozzle at
least two inches from filter element. Cover entire filter
area withairjet.
CAUTION
Do not usa a compressor unit with a nozzle
pressure greater than 100 p.s.i.
3. After cleaning, inspect filter and gasket for
damage. Discard a rupturedfilter or brokengasket.
2. Check battery box for corrosion and spl[led
electrolyte.To cleancables,terminals, and batterybox,
use a solutionof bicarbonateof soda and clean water
to neutralizecorrosionand spilledelectrolyte.
CAUTION
When cleaning, do not allow bicarbonate of
soda to enter battery cells - permanent damage
will result if soda mixes with electrolyte.
3. Rinse battery with clean water, and wipe clean
with a dry cloth.
4, To retard corrosion, coat terminals with petroleum
jelly a_er cleaning and tightening them.
5. Check battery ram air and vent for obstruction, line
kinks, etc.
12-20-03
- TIRES AND WHEELS
Keep the tires at recommendedair pressure. (Refer to
Chapter6-00-01.
1. Checktires for wear, cuts,and bruises.
2. Checkvalve stems for evidence of tire slippageor
pulling.
3. Check wheelsfor damage.
NOTE
If filter shows an accumulation of carbon, soot,
or oil, continue with cleaning steps 4 through 7.
4. Check wheel bearings for condition and
lubrication.
12-20-04
- BRAKE RESERVOIR
4. Soak filter in nonsudsing detergent for 15 minutes;
then agitate filter back and forth for two to five minutes
to free filter element of deposits.
5. Rinse filter element with a stream of clean water
until rinse water is clean.
Frequently check the brake reservoir for proper fluid
level. See Chapter 12-20-05 for locations.
CAUTION
Do not fill reservoir while parking brake is set.
6. Dry filter thoroughly. Do not use light or air above
180 deg. F. for filter drying,
7. Inspect for damage or ruptures by holding before a
light. If damage is evident, replace filter with new one.
8. Check induction air door through lower front
cowling opening for good working order, and check
alternate air door inside the lower cowling at the
induction air box for proper operation, The alternate air
should just start to open when a force of 3-4 pounds is
applied.
Use only hydraulic fluid (red), per specification
MIL-H-5606. Do not fill reservoir above two inches
belowfiller port.
12-98
:
12-20-00
5
SERVICE AND MAINTENANCE MANUAL
M20J
12-20-05
- HYDRAULIC BRAKE (Bleeding)
CAUTION
Fluid in the wheel cylinders may be under high
pressure due to expansion. Therefore, be sure
parking brakes are released prior to beginning
hydraulic system servicing.
For best results, use a hydraulic pressure service unit
(pressure pot) to back bleed the system through the
wheel cylinderbleedervalves. Allow pressurizedpot to
set 10-12 hours to dissapate air from fluid pdor to
bleedingbrake lines.
1. Remove hydraulic fluid reservoir filler plug, and
installa suitable fittingfor attachinga flexibledrain line
to the reservoirfiller port.
2. Immerse open end of drain line in a hydraulicfluid
container,
3. Attach pressudzed hydraulic fluid service unit to
wheel cylinder bleeder valve and open valve. On
aircraft with dual brakes and shuttle valves, depress
_ilot's brake pedals to reposition shuttle valve while
eing bled.
Fluid in hydraulicservice unitshould be free of air pdor
to servicingaircraft system.
4. Feed fluid from service unit into brake system,
Check for air bubbles at end of drain line immersed in
fluid. On aircraft with dual brakes, depress co-pilot's
brake
pedals to repositionbrake
shuttle valve, then
proceedwithbleedingthis
side.
5. When fluidflow is clear of air bubbles,close wheel
cylinderbleedervalve and remove serviceline.
NOTE
Brake pedal may need to be pulled back in
order for fluid to bleed back into reservoir,
6. To bleed oppositebrake, repeat steps3 through 5.
7. Remove drain line from reservoir,
8. Lower fluid level in reservoirto two inches below
fillerport.
9. Reinstallfiller plug.
10. Check brake linings for excessive wear and
properinstallation.Refer to Section32-40-04 for Brake
Removaland inspectionProcedures.
11. Depress brake pedals to check for sponginess,
Resistance should be solid and even when brake
pedalsare depressed,
12-20-06
B. Flush away loosedirt and mud.
C. Wash exterior with a mild aircraft detergent in
coolwater, and a soft cleaning cloth or chamois.Rinse
away soapfilm.
CAUTION
Do not use so called "mild" household
detergents to wash aircraft exterior. Such
detergents may damage finish and corrode
aluminum components.
CAUTION
Do not apply wax or use pre-wax cleaners
during initial paint curing period. Use only mild
aircraft detergent and cool water when washing
exterior during the first 90 days after repainting.
D. To remove heavy oxidationfilm, use a pre-wax
cleaner.
E. Apply an exterior-finishwax recommended for
protectionof urethaneenamel. Apply a heavy coating
of wax to leading edges of wings, empennage, and
nose sectionto reducedrag and abrasion.
CAUTION
When fuel, hydraulic fluid, or other fluid
Containing dye is spilled on painted surfaces,
remove it at once to prevent staining. Flush
away spilled battery electrolyte immediately
with water. Treat the area with bicarbonate of
soda solution followed by thorough washing
with a mild aircraft detergent solution.
2. WINDSHIELDS, WINDOWS AND DOORS
A. Flush windshield and windows with water pdor
to wiping. Never wipe while dry.
B. Remove grease or oil with a soft clothsaturated
in kerosene.
CAUTION
Never use gasoline, benezene, carbon
tetrachloride, acetone, fire extinguisher fluid,
de-icer fluid, lacquer thinner, or household
window cleaning sprays on windows or
windshields. Such solvents will soften or craze
the plexiglas surface.
C. Clean windows and windshields with an
antistaticplexiglascleaner.
D. Check door seals for damage that could cause
leakage.
E. Check cabin and baggage door mechanism for
goodworkingorder.
- CLEANING
NOTE
Minor scratches or abrasions may be polished
out by using plexiglas resurfacing kits, ie,
Micro-Mesh, available from aircraft accessory
suppliers.
3. ENGINE COMPARTMENT
Cleanliness is a major prerequisite to adequate
inspectionand maintenance of an aircraft. Cleanliness
enhances the appearance of an aircraft and reduces
the probabilityof corrosion.
1. EXTERIOR
A. Before washing aircraft exterior, cover brake
discs, pitot head, and static ports,
12-20-05
6
MOONEY AIRCRAFT CORPORATION
Accumulation of dirt and oil within the engine
compartment creates a fire hazard and hampers
inspection.
12-98
MOONEY AIRCRAFT CORPORATION
M20J
A, Wash down engine cowling and engine
compartmentusinga nonflammablesolvent.
B. Dry engine cowling and engine compartment
afterwashing,
4. CABIN INTERIOR
Use normal household cleaning practices for routine
interiorcare.
A. Frequently vacuum seats, rugs, upholstery
panels,and headlinersto remove surfacedust and dirt.
B. Clean leather or vinyl upholstery and panels
with a mild aircraftdetergent. Clean with a slight damp
cloth,and dry with a softcloth.
NOTE
Foam-type shampoos and cleaners for vinyl,
leather, and plastic materials can be used to
remove stains and to condition the entire
interior. Spray-on dry cleaners are also
recommended.
12-98
SERVICE AND MAINTENANCE MANUAL
CAUTION
Never apply furniture polish to interior
furnishings. Most poslishes contain solvents
harmful to vinyl. Do not use alcohol or strong
solvents on interior plastics. When using
commercial cleaning and finishing compounds,
carefully follow the manufacturer's instructions.
Never saturate fabrics with solution which
could damage the backing and padding
materials. To minimize wetting of carpets, keep
foam as dry as possible and rub in circles. Use
a vacuum cleaner to remove foam. Do not allow
carpets to remain damp; dry them thoroughly.
12-20-06
7
SERVICE AND MAINTENANCE MANUAL
M2OJ
BLANK
12-20-06
8
12-98
MOONEY AIRCRAFT CORPORATION
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 20
STANDARD PRACTICES - AIRFRAME
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 2O
STANDARD PRACTICES - AIRFRAME
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
20-Eft/Contents.........
20-00-00 ............
20-00-01 ............
20-00-02 ............
20-00-02 ............
20-00-03 ............
20-00-03 ............
PAGE
..........
DATE
1/2BLANK ..........
3 ...........
4 ...........
5 ...........
6 ...........
7
..........
8
..........
12-98
12-98
12-98
12-98
12-98
12-98
12-98
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
20-00-00 ........
20-00-01 .........
20-00-02 .........
20-00-03 .........
SUBJECT
........
General ..............
Skin Specifications ..........
CorrosionDetectionand Prevention......
Painting .............
12-98
PAGE
3
3
5
7
2O-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
20-00-00
- GENERAL
This chapter of the manual discusses treatment of
metal surfaces for corrosion control and the
identificationof skin panels for replacement purposes,
Those who inspect or repair aircraft should consult
FAR 43, Maintenance, Preventive Maintenance,
20-00-01
- SKIN SPECIFICATIONS
STA
210,97
STA
193,50
Rebuildingand Alterationand Sub PartsA, D and E of
FAR 65, Certification.
Advisory Circular 43.13-1(*) outlines inspectionand
repair practicesacceptableto the F.A.A. Administrator.
Torque valuesare shown in SECTION 5-20-01.
NOTE
Refer to FAA AC 43.4 for CORROSION
TREATMENT.
(* = currentrevision)
STA
147,75
STA
103,50
STA
59,25
4
3
STA
24.50
2
6"
7
19
13
8
12
17
ii
10
16
14
9
WING SKIN PANELS
iNDEX
NO..
SKiN
THICKNESS
MATERIAL
.........
1.
2.
3.
0.063
0.050
0.040
5.
6.
7.
8.
9.
10.
11.
0.025
0.025
0.032
0.040
0.025
0.025
0.025
4.
0.032
.....
$M2o-1
INDEX.
NO..
SKiN
THICKNI_SS
MATERIAL
2024 T-3 CLAD .
2024 T-3 CLAD ....
2024 T-3 CLAD ....
12.
13.
14.
0.025 (o)
0.020 (a)
0.032 __
2024 T-3 CLAD
2024 T-3 CLAD
2024 T-3 CLAD
2024 T-3 CLAD ....
2024 "1"-3CLAD .
2024 T-3 CLAD .
2024 T-3 CLAD ....
2024 T-3 CLAD
2024 T-3 CLAD
2024 T-3 CLAD
16.
17.
18.
19.
0.040 (d)
2024 T-3 CLAD
0.016 (a)
2024 T-3 CLAD
0.050 (b)
_ 2024 T-3 CLAD
PolyesterGlass-Fiber Reinforced
2024T-3
cLAo....
15.
(a) Same thioknesson top and bottom
(b) Top of wingonly.
0040 )
2024T-30O
(c) Top aft flap skin(hat section)
(d) Top inboardflap skin
WING SKIN PANELS
FIGURE 20-1
12-98
20-00-00
3
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
8
5
6
7
3
14
2
12
0
I....
L
I
J
1
6
10
11
1
5
9
STA
199,50
5
STA
164.00
STA
130,00
STA
88,00
SKIN
MATERIAL
THICKN_:SS ....
1.
2.
3.
4.
5.
6.
7.
8.
9.
0.025
0.040(d) i
0.025(c)(b)
0.025
0.025(b) i
0.020
0.025
0.032(d)ie)
0.025
.....
.....
2024T-3CLAD
2024 -0CLAD
2024 T-4 CLAD
2024 T-3 CLAD
2024 T-3 CLAD
2024 "1"-3CLAD
2024 T-3 CLAD
2024-0 CLAD
2024 T-3 CLAD
STA
53,00
STA
21,80
SKIN PANELS
FUSELAGE
INDEX
NO..
1
13
....
....
....
....
....
SM20-2
INDEX.
NO..
SKIN
MATERIAL
THICKNF:SS"
10..
11..
12..
13..
14..
0.032
2024 T-3CLAD
O.032(a)i
2024 T-3 CLAD
0.032
2024 T-3 CLAD
0.025(a) i . 2024 T-3 CLAD
Polyester Glass-Fiber Reinforced
"
(a) Left side only
(b) Right side only.
(c) 0.032 can be used.
(d) Heat treated to T-42 condition afterforming.
(e) Shell.
FUSELAGE SKIN PANELS
FIGURE 20-2
20-00-01
4
12-98
STA
-5,00
MOONEY AIRCRAFT CORPORATION
M20J
SKIN PANELS
EMPENNAGE
INDEX .
NO..
SKIN
MATERIAL
THICKNESS" .........
1.
2.
3.
4.
5.
6.
7.
.................
0.025
0.025
0.025
0.025
0.025
0.020
0.025
.
.
.
2024 T-3 CLAD
2024 T-3 CLAD
2024 T-3 CLAD
2024 T-3 CLAD
2024 T-3 CLAD
2024 T-3 CLAD
2024 T-3 CLAD
.
SERVICE AND MAINTENANCE MANUAL
.
INDEX
NO..
....
....
....
....
....
....
8.
9.
10.
11.
12.
13.
SKIN
THICKN;=S8'
MATERIAL
0.025
2024 T-3 CLAD
0.020
2024 T-3 CLAD
0.032
2024 T-3 CLAD
Polyester Giass-Fiber Reinforced.
0.020
2024 T-3 CLAD
0.025(a) i
. 2024 T-3 CLAD
(a) Heat treated to T-42 condition.
EMPENNAGE SKIN PANELS
FIGURE 20-3
20-00-02
- CORROSION DETECTION &
PREVENTION
Most metallic fabrication materials are susceptibleto
corrosion. Corrosion may occur on aircraft in any
climate,but itwill be a problemmore often in climates
where the aircraft is .exposed to salt air or high
humidity,or where there are industrialcontaminantsin
the atmosphere. The aircraft should be inspected
frequently to detect and correct corrosion before
seriousdamage occurs.
Any form of corrosion shouldbe removed at once. If it
is necessary to remove paint, only an approved
aircraft paint remover such as Eldorado PR-3400
(Eldorado Chemca Co., nc., 6700 Lookout Road,
P.O. Box 32101, San Antonio, -IX. 78216) shouldbe
used. Paintremovingsubstances left in metalcrevices
will cause further corrosion.Turco 2662C or 3002 will
remove corrosionfrom aluminum and treat the metal
surfacein one application.
12-98
20-00-02
5
SERVICE AND MAINTENANCE MANUAL
M20J
This paragraph discusses corrosion types and their
prevention along with suggested procedures for
pdming intemalairframe surfaces,
1. Types of Corrosion. Corrosion normally appears
in one or more of four forms. Each type of corrosion
can be precluded or controlled by a preventative
maintenance program,
A. Chemical corrosion. Chemical corrosion
normally occurs where battery acid or exhaust gases
come in contact with metal surfaces. A few simple
precautions will prevent chemical corrosion,
(1) Be sure battery vent is free from obstruction
at all times.
(2) Repaint all scratches and worn spots found in
areas painted with acid-resistant paint,
(3) If acid is spilled on metal surfaces, flush
entire area with sodium bicarbonate and water. The
solution should be rinsed away at once and the area
dried by ddving all water from crevices with an air hose
before wiping surface dry with a clean cloth,
(4) Frequently clean exhaust gas deposits from
metal surfaces.
B. Local-Cell Corrosion. On bare metal surfaces,
in an early stage development, local-cell corrosion
appears as a light, whitish powder deposit. Surface
pitswarn of advanced local-cellcorrosion. On painted
surfaces, the first indication of corrosion will be
evidenced by paint blistering.
(1) Intergranular Corrosion - Selective attack
along grain boundaries of metal alloys is referred to as
intergranular corrosion. Aluminum alloys 2024 and
7075 are vulnerableto this type of attack. Aluminum
extrusions may contain nonuniform areas, which in
turn may result in galvanic attack along grain
boundaries.This type of corrosion is difficult to detect
in its original stages. When the attack is well
advanced, the metal is usually blistered or
delaminated. This is referred to as "exfoliation". It is
very dimcultto completelyremove and stopthis type of
corrosion, and replacement of the affected part is
recommendedwherever possible,
C. Concentration Cell Corrosion. Corrosion
forming under dvet heads, along laying surfaces, at
skin to Iongeron contact surfaces and other similar
areas is called concentrationcell corrosion. Detection
requiresclose inspection.Rivets must be removed and
skin laps must be separated to remove concentration
cell corrosion.Use aluminum wool soaked in solvent
such as methyl-ethyl-ketone to scour corrosion
deposits from the surface before painting both laying
surfaces with zinc chromate or eoxy-polymide pdmer
and reassembling.
D. Galvanic Corrosion- Dissimilarmetals, such as
stainless steel and aluminum, in contact with each
other sometimes develop galvanic corrosions. To
remedy this form of corosion, separate the parts,
remove the corrosion_and paint both surfaces with
Epoxy-Polymide pdmer
or equivalent before
reassembling.
2. CorrosionPrevention
A. Thoroughlyexamine unpainted metal surfaces
at inspections, and check corrosion when found.
20-00-02
12-98
6
MOONEY AIRCRAFT CORPORATION
Carefully examine seams, lap joints, and crevices
where moisture or dirt can collect. Areas exposed to
exhaust gases require frequent inspection and
cleaning.
B. Corrosion may attack metal even though the
surface is painted. Inspect painted areas for a
blistered or scaly appearance that warns of corrosion
below the paint layer.
C. Use only liquid (non-alkaline) soap to wash the
extedor airframe. Cover vent scoops when the aircraft
is being washed. Rinse aircraft extedor after exposure
to salt air or industrial fallout.
D. Since moisture promotes corrosion, thoroughly
and frequently inspect areas where water is apt to
collect. Use an air hose to ddve water from crevices
before wiping the exterior surface dry after washdown.
E. Hangarthe aircraft when not in use.
F. If battery acid is spilled on any part of the
aircraft, immediately wash the area with a solution of
sodium bicarbonate in water. Rinse with water and dry
with clean towels.
NOTE
ACF-50 or equivalent can be fogged into
fuselage empennage or wing skin areas. It is
recommended that electrical connections and
electrical components be protected during
fogging.
NOTE
FAAAdvisory Circular 43-4addresses
corrosion problems and treatment.
3. Surface Protection.Surface protectionof intemal
airframe surfaceswill not eliminate the necessity for
pedodic inspections. The most likely areas for
corrosionto beginare in hidden crevicessuch as skin
laps, underrivetheads or any openingwhere moisture
can collect. Pedodicinspectionof these areas is most
importantso that any corrosionwhich may be present
can be detectedand treated in its very earlieststages.
When corrosion is detected, it should be treated as
follows:
A. Remove all corrosionproduct (usually white or
grey-white powder on aluminum) from the corroded
area downto soundmetal.
(1) If the base metal is aluminum,clean off the
corrosionproductby scrubbingwith aluminumwool or
a nonmetallicscouring pad such as the nylon pads
made by the Carborundum Company, P.O. Box 277,
Niagara Falls, N.Y. 14302.
MOONEY AIRCRAFT CORPORATION
M20J
(2) If the base metal is steel, remove the
corrosionproductwith emery cloth (320 grit or finer) or
steel wool.
SERVICE AND MAINTENANCE MANUAL
B. CleanlngPrucedums.
NOTE
Fiberglass components are attacked and
deteriorated by products containing the
following chemicals: Ketone, atiphatic esters,
chlorinated hydrocarbons and slightly softened
by aromatic hydrocarbons,
(3) If the corrosionis too advancedto remove by
the light mechanicalcleaning methods of (1) and (2),
refer to Advisory Circulars43.13-1(*) and/or 43-4 for
alternate methodsof cleanup and repair. (* = current
revision)
(4) Chemical
cleaning
solutionsshould
be used
with extreme
caution
on both
aluminum and
steel
parts. Such solutionsare not recommended for use in
areas where they cannot be easily and completely
neutralized,
B. Wash all areas to be pdmed with a cleaning
solvent such as methylethylketone (MEK), Turco
T-657 (Tumo Products,Inc., 6135 SouthCentral Ave.,
Los Angeles, California), lacquer thinner,#3094 wash
thinner (Pratt & Lambert, Inc., 25th and N.Y. Avenue,
V_chita,Kansas) or similarsolvents,
(1) To get a good clean surfacefor pdminguse a
clean cloth or piece of cheesecloth and apply one of
the solvents noted above. The surface should be
wiped dry with a second piece of clean cloth. Do not
allowthe solventto dry on the cleaned area as it will
redepositdissolvedsoiland gdme uponevaporation,
CAUTION
Wipe solvents are generally flammable and
toxic and should not be used without adequate
ventilation and fire precautions,
C. Apply Epoxy-Polymlde pdmer or equivalentto
cleaned area by spray or brush. Area needs to be
paintedwithin24 hours of pdmer coat.
20-00-03
- PAINTING
The extedor is painted with urethane enamel. When
exposed to humidsalt air or to an atmospherehaving
corrosivefallout,the aircrait should be hangaredwhen
not in use.
1. Paint Repairs.
A. Matedals.
(1) Aluminumwool, nylonscoudngpads,320 grit
or fineremery clothor steel wool.
(2) Tack rags.
(3) Wipe solventssuch as: Methylethyl ketone,
T-657 -- Turco Products, Inc., #3094 wash thinner
-- Pratt & Lambert, Inc., lacquer thinner or equivalent
solvents,
(4) Body putty or aerodynamic filler such as:
Flex-Bond-- Taylor& Art Plastics,Flex-- 3M Co.,or
Cuz polyester body filler #6372 -- NAPA (Martin
Senour Paints).
NOTE
Fuel Servicing Decal Removal:
1. Cover the decal with a hot, wet towel for
approximately 2 minutes.
2. Lift one corner of the decal and slowly
remove.
(1) Remove all old loose paint by one of the
followingmethods:
(a) On aluminum - for uniformity of finish
appearance,the entireskin panel shouldbe prepared
for repainting.If the paint is in very bad conditionor if
a filler is to be used, remove all of the paint by use of
lacquer thinner, MEK or similar solvent. Careful
applicationof approved paint stdpper is acceptable.
The solventshould be wiped on and wiped off beforeit
evaporates. If the solvent is allowed to evaporate it
will redeposit the so s and paint that were being
can-led.Any scoudng requiredshould be done at this
poinLScoudngwith nylonpads or aluminumwool may
be done dry or wet with one of the wipe solventslisted
above. After the old paint, gdme, etc. has been
loosened and removed, the scoured area should be
wiped with a tack rag, and again cleaned with fresh
wipe solvent. The part should now be ready for
pnmmg and painting.
(b) On steel - Remove all grease,gdme, loose
paint, etc. by wipingwith a wipe solventand rags. Do
not allowthe wipe solventto evaporate.Wipe it dryl
Steel pads may be cleanedto bare metal by sanding
with emery cloth or steel wool. If the pads are
removable, they can be cleaned by sandblasting.
Regardlessof the scoudngmethod, allparts shouldbe
wiped with a tack rag and cleaned with fresh wipe
solvent.The part shouldnow be ready for pdmingand
painting.
C. Pdmingand Painting.
(1) On aluminum- Cleaned and driedsurfacesto
be painted should be coated with a wash primer
conformingto MIL-C-8514 or MIL-P-15328. Read and
follow the manufacturer'sinstructionscarefully. The
wash primer should be applied to attain a dry film
thicknessof 0.3 to 0.4 mils(a transparentfilm).
(5) Compatible paints for the item (such as steel
tubular structure or extedor skin) and for the year and
model being repainted. (Refer to Mooney Pads
Manual).
(6) Thinnerswhich are compatiblewith the paints
being used both for paint thinning and for bum-down
thinners.
12-98
20-00-03
7
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
A good wash primer coating is a must since the top
coating can be only as good as the pdmer coat. As a
general rule the wash primer should dry from .05 to 1.5
hours but not more than 2 hours before application of
the
top or epoxy
intermediate
primer
coat. it When
intermediate
primer coat
is applied,
should an
be
mixed very carefully per the manufacturer's
instructions. It should be thinned per manufacturer's
instructions and applied to a dry film thickness of 0.8 to
1.0 MILS. The intermediate primer should be allowed
to dry a minimum of 0.5 to 1.5 hours depending upon
the application temperature and relative humidity,
Follow manufacturer's instructions. The intermediate
primer coat can be dry-scoffed lightly with No. 409 to
No. 600 sandpaper pdor to top coat application and
give a higher glossfinish. As many coats of paint as
desiredmay be applied.A higherglosswill be attained
if the surface is scuffed lightly and tack rage cleaned
between each coat.
D. Painting.
(1) Apply three coats of white base and/or color
finish allowing three to five minutes between coats
depending upon weather conditions. Allow five to ten
minutes between coats in cold, dry weather; in humid
weather, allow fifteen minutes between coats.
(2) Use a small round watercolor brush trimmed
to a point for application of undiluted touch-up paint to
small scratches and bare spots. Do not thin acid
resistant black paint or extedor finish touch-up paint
for brush-on application.
NOTE
M2OJaircraft are painted with Enflex III
urethane enamel. Inquiries concerning
application of this finish should be directed to:
Pratt & Lambert, P.O. Box 2153, Wichita, KS.
67201.
(2) On steel - The same general procedure used
on aluminum can be applied to steel. However,
MIL-P-8585 primer or epoxy primer is recommended
for the steel coat. If epoxy primer is use¢ it should
have a wash primer(MIL-C-8514) pre-treatment,
CAUTION
Any flight control surface that is to be
repainted should be stripped of all paint prior
to repainting. It is required that repainted
control surfaces be removed and rebalanced
prior to flight per paragraph 27-91-00.
NOTE
Never use abrasive polish compounds or harsh
soaps and detergents on ureathane finishes.
Once the surface gloss is damaged it cannot
be restored by polishing.
20-00-03
8
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 21
ENVIRONMENTAL SYSTEMS
SERVICEAND MAINTENANCEMANUAL
M20J
MOONEY AIRCRAFTCORPORATION
CHAPTER 21
ENVIRONMENTALSYSTEMS
UST OF EFFECTIVEPAGES
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SECTION
SUBJECT .....
21-Effectivity/Contents.......
21-O0-00 ........
21-40-00 ............
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DATE
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4
.........
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TABLEOF CONTENTS
CHAPTER
SECTION
SUBJECT .........
21-00-00
21-40-00
SUBJECT ......
.......
PAGE
Cabin VentilationSystem ..........
Heating .............
3
3
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21-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
M20J
21-00-00
-CABIN VENTILATION SYSTEM
The cabin environmental system consist of three
ventilatingsystemsthat supply heated or fresh air as
the pilot or passengers prefer. CABIN AIR, CABIN
HEAT and OVERHEAD VENTILATION. The cabin air
and heat system controlsand ventsare locatedon the
consolebetweenthe pilotand co-pilotseats. Individual
fresh air outletsare locatedon each side of the cabin
side panels just forward of the pilots and co-pilots
knees. The overhead ventilation system consists of
individualoutlets (Wemac valves) locatedabove each
seat position,
S/N 24-0901 & later aircraft have a regulator system
with
the control
located above
pilots
head.
The systems
areknob
basicallytrouble
freethebut
inspection
should be made at regular intervalsto ensure proper
operation,
SERVICE AND MAINTENANCE MANUAL
S/N 24-0001 thru 24-0757 aircraft have an overhead
airscoopoperatedby rotatingthe knobabove the pilots
seat to extend or retract as desired, to controlair flow
or to preventair-buffetingat high criuse speeds. Small
overhead vent deflectors, with inner knob volume
controls,distributeincomingair as individuallydesired.
21-40-00
- HEATING
Heat is supplied to the cabin through flexible hoses
connected to a heat distribution box assembly and
shroud assemblieslocated on the exhaustmanifold on
the engine. It is recommended that the conditionof
these items be checked each time the cowling is
removed.This will provide a continuingcheck for the
prevention of carbon monoxide in the cabin. Any
deteriorated flexible ducts should be replaced. Heat
shrouds should be inspected for cracks or other
deteriorations and repaired or replaced promptly.
Inspectthe exhaustsystemfor any leaksor cracks and
replace or repairas needed.
12-98
21-00-00
3
SERVICE AND MAINTENANCE MANUAL
M20J
BLANK
21-40-00
4
12-98
MOONEY AIRCRAFT CORPORATION
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 24
ELECTRICAL POWER
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 24
ELECTRICAL POWER
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
24-Effectivity .........
24-Contents..........
24-00-00.
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24-31-02 .............
24-32-00.
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24-34-00 ............
24-35-00 ............
24-39-00
...........
24-39-01
...........
24-39-02
...........
24-39-04
...........
24-39-05
...........
24-39-05
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24-39-06
...........
24-39-96
...........
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...........
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...........
24-51-00
...........
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..........
DATE
1/2BLANK ..........
3/4BLANK ..........
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1/2BLANK
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER24
ELECTRICAL POWER
CHAPTER
SECTION
SUBJECT
TABLE OF CONTENTS
...........
24-00-00 ........
24-30-00 .........
24-31-01 ............
24-31-02 ...........
24-31-03 ............
24-32-00
..........
24-33-00
..........
24-34-00
..........
..............
24-35-00
..........
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..........
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..........
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..........
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24-39-04 ............
24-39-05 ............
..............
24-39-06 ............
..............
24-50-00 .........
24-51-00
..........
SUBJECT
........
General ..............
D.C. Generation ...........
AlternatorChargingSystem Maintenance.
Voltage RegulatorMaintenance ....
AuxiliaryPowerSystem ......
Battery Maintenance ........
Warning Circuits .........
PowerPlantCircuits ........
--Low BatteryStartingProcedures
LightingCircuits..........
LandingGear Circuits ........
Fuel SystemCircuits ........
MiscellaneousCircuits ........
Trouble ShootingCharts . . .....
Alternator Trouble Shooting .
RESERVED ......
Battery Trouble Shooting ......
Starter Trouble Shooting ......
Annunciator Trouble Shooting
(24-0001 thru 24-3153) ......
Annunciator Trouble Shooting
(24-3154thru 24-TBA) ......
Electrical Load Distribution ........
Power Distribution System
.....
12-98
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5
5
5
5
6
7
7
8
8
9
9
9
9
10
10
12
12
13
14
16
20
20
24-CONTENTS
3/4BLANK
SERVICE AND MAINTENANCE MANUAL
M20J
24-00-00
- GENERAL
(24-0001 thru 24-2999)
A 14 volt alternator with a transistorized voltage
regulator and an overvoitage relay supplies electric
power.A 12 volt, 35 ampere-hour storage battery is
installedin the tailcone.The alternator, dudng normal
operation,
supplies
powerswitch
in conjunction
with
the
battery when
the master
is on. The
circuit
breaker panel is on the right subpanel. The electrical
system is capable of supplying current for
simultaneous operation of multiple radios, an
anticollision beacon, and navigation lights. A shunt
type ammeter mounts in the power plant instrument
cluster.
(Similar systern-24-3079 thru 24-'rBA ,except 28
volts)
(24-3000 thru 24-3078)
A 28 volt, 70 AMP alternator utilizing a transistodzed
voltage
regulator/over
control
electrical power.
A 24 volt voltage
10 AMP HR
storagesupplies
battery
is installed n the tailcone. The alternator, during
normal operation,will supply power in conjuction with
the batterywhen the master switch and alternator field
switchis ON. The circuitbreaker panel is on the right
subpanel.The
electricalsystem is capable
of supplying
current for simultaneousoperation
of multiple
radios,
anticollisionlights and navigationlights.A shunt type
combination gauge gives alternator output and line
loadin % of rated capacity plusbus voltage.
MOONEY AIRCRAFT CORPORATION
D. Do not leave the master switch ON when the
aircraftis parked.
E. Use an auxiliarygroundpower unitwhen trouble
shooting electrical accessory equipment or when
performingelectrical landing gear maintenance and
retractionsystemtesting.
2. AlternatorSystem Inspection.
A. Check alternator circuit breaker on the main
circuit breaker panel. Reset breaker If open.
B. Check alternator field circuit breaker on main
circuit breaker panel. Reset if open.
C. Inspect battery for corroded cable connections;
remove and Cleancable if corrosion is found.
D. Check ddve belt for proper tension and
excessiveglazing.
E. Checkchargingsystem widng connectorsto be
surethey are clean and tight.
F. Inspectalternator, voltageregulator,and widng
fordamage.
CAUTION
Do notattemptto polarizealternator. Alternatoris
polarizedevery time master switch is turnedon.
3. AlternatorRemovaland Installation.
A. Aitemator Removal.
24-30-00
- D.C. GENERATION
(1) Turn master switchOFF beforedisconnecting
alternatorwiring.
24-31-01
-ALTERNATOR CHARGING SYSTEM
MAINTENANCE
(2) Remove attaching hardware and slip drive
belt from pulley.
1. Alternator System Servicing
(24-0001 thru 24-2999, 24-3079 thru 24-TBA)
When the ammeter shows a discharge at higher
engine speeds, a charging system component
(alternator, voltageregulator,drive belt, circuit breaker,
orwidng) is malfunctioning,
(24-3000 thru 24-3078)
When the Ioadmeter shows a higher % than the
alternator output at higher RPM, a charging system
componentis malfunctioning.
On-the-plane testing should indicate which component
is faultyand needs to be removed from the aircraft for
benchtesting and repair or replacement.
The alternator charging system requires no special
attention;however, improper maintenance procedures
can damage the alternator and widng. There are
several precautions that must be observed when
servicingthe alternator system:
A. Be sure the master switch is OFF when
repaidngthe alternatororvoltageregulator,
B. When the battery is removed fi'om the aircraft.
for charging, be sure that the charger is correctly
connected. Use the correct charging rate, refer to
battery manufacturers 'procedures. It is possible to
reverse the polarity of a battery by connecting a
charger backwards.
C. Be sure to check battery polarity by using a
voltmeterpdor to reinstallationin the aircraft.
NOTE
Ifblast
replacement
alternator
a cooling
fan or a
tube housing,
they has
MUST
BE REMOVED
prior to installation. Replace cooling fan with
Lycoming spacer (LW-15403) which was
already on alternator when aircraft was
delivered from Mooney. Reinstall pulley after
spacer is installed and torque pulley retaining
nutto 35-40 ft. Ibs.
B. Altematorlnstallation.
(1) Be sure master switch is turned OFF. Do not
turn master switchON untilall wiringconnectionshave
beensecurea.
(2) Installattaching hardware;place ddve belt on
pulleyand adjust beit tension.
(3) Connect alternator wiring and check widng
connectorsthroughoutsystam.
CAUTION
Donot attemptto polarizealternator.Alternatoris
polarizedeverytime masterswitch isturnedon.
24-31-02
-VOLTAGE REGULATOR
MAINTENANCE
The battery charging rate depends upon the battery
condition and the voltage regulator setting. With all
equipmentturned off and the engine runningat 2000
RPM or faster, the normal batterycharging ratewill be
5 to 35 amperes.
12-98
24-00-00
5
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
1. Excessively High Charging Rate. Check the
amperes). The regulator should not be considered
following:
detective because of a low charging rate until:
A. Fly aircraft for 15 to 20 minutes; charging rate
A. A voltmeter check indicates that voltage at the
should slowly drop to 10 amperes or less. A very low
bus is below requirements.
battery will take longer to show a drop in charging
B. A battery hydrometer check indicates that
current,
battery is not fully charged.
B. Measure voltage with a voltmeter connected to
3. Hydrometer Reading. If battery electrolyte
the bus. At 80 degree F., voltage should be 13.75 to
temperature is below 80 degree F., subtract four points
14.0. An excessively high voltage regulator setting will
from hydrometer reading for every 10 degrees F. below
cause excessive battery heating and water loss.
80 degrees F. If battery acid temperature is above 80
2. Excessively Low Charging Rate. Check battery
degrees F., add four points to hydrometer reading for
charging rate (normal rate is not to exceed four
everyl0degreesF, above 80 degrees F. Example:
Hydrometer reading = 1.260
Battery electrolyte temperature = 30 degree F.
80 degrees - 30 degrees = 50 degrees
5 x 4 = 20 points
Corrected reading 1.260 - 20 = 1.240
•
.
....
....
....
....
.
HYDROMETER.
READING ....
1.280..........
1.250 ..........
1.220 ..........
1.190 ..........
1.130 or below
PERCENT OF CHARGE
100
75
50
25
Ve_ little useful capacitT--Dtscharcled.
"Hi" or Overvolt Adjustment at Regulator - Bench
Adjustment. (Electro-Delta)
Connect a variable voltage power supply to the
regulator,positive (+) to pin "A" or =1" and negative to
pin "C" or "3" (24-0001 thru 24- 2999); positiveto pin 5
& negativeto pin 9 for (24-3000 thin 24-TBA). Connect
a voltmeterto the regulator (+) to pin "D" or =4" and (-)
to pin "C" or "3" (24-0001 thru 24-2999); (pin 6 and pin
9 for 24-3000 thru 24- TBA). Adjust voltageto 16 volts
+/- .1 volt (24-0001 thru 24-2999);(28.7 volts for
24-3000 thin 24-TBA). Adjust tnm pot (accessable
throughholein case marked "OV'_to relaytrip pointas
indicated by voltage indication on test voltmeter.
Decrease voltage until relay closes and note voltage,
Readjust as necessary until a trip point of 16 +/- .1
volts is attained(24-0001 thin 24-2999); 31.8 (+/-).3
voltsfor 24-3000 thru 24-TBA).
Regulator
(Electro-Delta)
ConnectanAdjustment
accurate voltmeterto
the aircraft bus. Turn
off all electrical equipment and start engine. Run
engine at moderate RPM (1500-1800) until ammeter
drops to low charge rate. Increase RPM to 2000 and
adjust trim pot (accessable through hole in case
marked "REG") for a voltage reading of between 13.75
and 14.0 volts (24-0001 thru 24-2999);(28.6 and 28.8
volts for 24-3000 thru 24-TBA). Increase throttle to full
RPM and observe that voltage does not exceed 14
volts (24-0001 thru 24-2999);(30 volts for 24-3000 thru
24-TBA).
Low Voltage Warning should occur on Annunciator at
approximately 12.5/12.75 Volt output from regulator,
Electro-Delta Volt. Reg. are adjustable for HI & LOW
volts.
24-31-03
6
NOTE
Use bushings provided with replacement
VR-415F voltage regulator to mount in location
of old regulators.
NOTE
No field adjustment authorized for Mooney
Voltage regulators. Max. voltage for 14 volt
system is 14.2+.21-0.m 28 volt system is 28.3
+.21-0.
24-31-03
-AUXILIARY POWER SYSTEM
An auxiliary power plug and related circuitryis installed
to providean outsidesource of electrical power to the
aircraft, to charge the battery, or to start the engine.
The Auxiliary Power Plug guide pin must have A+
voltage connectedto it in order to activatethe Auxiliary
Power Relay. The battery can be charged using the
approvedAuxiliary Power Cableconnected to a charge
cart capable of regulating the charging current. To
prevent battery damage, the charging current should
be low (3 - 4 amps) to beginand then increasedas the
battery voltage capacity is increased. The MASTER
SWITCH is not required to be ON for the auxiliary
power source to charge the battery.
A. When auxiliary power or a booster battery is
used, be sure cables are connected correctly--positive
to positive and negative to negative. DO NOT by-pass
battery when using an auxiliary power source.
B. See paragraph 24-34-00, A for additional
information.
12-98
NOTE
It is recommended that the approved Auxiliary
Power Cable be connected to booster battery,
then the plug inserted into auxiliary power
receptacle.
SERVICE AND MAINTENANCE MANUAL
24-32-00
M20J
- BATTERY MAINTENANCE
CAUTION
Battery gases are explosive,
1. Battery Removal.
A. Turn master switch off.
B. Remove tailcone access cover and battery box
lid.
C. Disconnect battery cables, negative lead first,
remove battery from aircraft,
D. Install battery in reverse sequence of removal.
Use a voltmeter to check battery polarity before
installation.
2. Battery Cleaning and Corrosion Removal.
A, Mix one pound of baking soda in one gallon of
water.
B. Wash battery box and flush battery with the
mixture.Do not allowsoda water to enter battery cells;
permanent damage will result if soda mixes with
electrolyte,
C: Rinse thoroughlywith clear water and dry the
area.
D. Test each cell with a temperature corrected
hydrometer. Specific gravity should be 1.265 to 1.280
for s fullycharged battery,
E. Check electrolytelevel and maintainat split ring.
F. Clean battery terminals with emery cloth,
reinstall and tighten cables. Coat terminals and
connectorswithPetroleumjeUyto retardcorrosion,
24-33-00
- WARNING CIRCUITS
1. Landing gear position lights and warning horn.
RED and GREEN landinggear positionlightsare in the
annunciatorpanel. The gear-down limitswitch controls
the GREEN gear-down lighL Both limitswitches control
the RED gear unsafe light. The throttle control
operates landing gear warning horn (intermittent tone)
when the power setting is reduced below 10 IN. Hg.
with the gear up. Check gear warning system during
flightfor properoperation.
2. PrestallWarning Circuit. The prestallWarning hom
has a high frequency continuous tone that sounds
when airspeed drops to 5 to 10 MPH IAS (4.3 to 8.7
KIAS) above stalling speed. A vane in the left wing
leading edge actuatesthe prestallwaming horn switch.
(This vane is made of heat treated steel, and any
attempt to adjustswitch operationby bendingthe vane
will damage the switch). Refer to Section 27-93-00 for
adjustmentprocedures.
3. High and Low Vacuum Warning Circuit.A switch
in the vacuum system controls the vacuum warning
light on the instrument panel or annunciator panel.
Vacuum below 4.25 IN. Hg. causes the vacuum
warning light to flash. Vacuum above 5.5 IN. Hg. tdps
the high-vacuum switch causing the vacuum warning
light to 'llum nate steadily. (S/N 24-0001 thru 24-0083
and 24-0085 thru 24-0377 have a vacuum gauge
mounted above the radio panel).
MOONEY AIRCRAFT CORPORATION
4. Low Fuel Warning Circuit. The low fuel indicators
will illuminatewhen a minimum of 2 1/2 gallons usable
fuel remains in either left or right hand tank. When it
becomes necessary to replace the annunciator pane[
for any reason other than "low fuel" warning
malfunction, the following procedure should be used to
set the =low fuel" warning circuits. The calibration
transfer standard, I.A.I. PIN 500D0045 (24-0001 thru
24-3153) or I.A.I. PIN 9500324000 (24-3154 thru
24-TBA) is required for this procedure. Adapters can
be
ordered through Mooney Marketing or Service
Centers.
A. Calibration Procedures
500D0045 or PIN 9500324000.
using
I.A.I. PIN
(1) Remove glareshield, disconnect plug from
rear of annunciator, remove annunciator front panel,
and place"Norm-Car switchin "Cal" position.
(2) Plug appropriate calibration transfer standard
on rear of old annunciatorand reconnectharnessplug.
(3) Turn on master switch and turn right hand
variable resistor on transfer standard slowly counter
clockwise until right "low fuel" light just turns on. (If
necessarytam variableresistorclockwiseto extinguish
low fuel light).(Do not adjust annunciatorcalibration
screws). Repeatfor left "lowfuel".
(4) Turn off master switch and remove old
annunciator assembly after disconnectionof harness
and transfer standardunit.
(5) Install new annunciator and connect
calibration transfer standard to annunciator panel and
harness plug. Remove front plate and legend on new
annunciatorpanel to expose the Norm-Cal switch and
the Left and Right trim potienometers.(Switchmust be
in =Cal"position).
(6) Adjust left and right annunciator fuel
calibrationscrews clockwise(not the adapter variable
resistors) until "low fuel" lights just turn on. (If
necessary turn annunciatorcalibration screw counter
clockwiseto extinguish=lowfuel" light).
(7) Remove
calibration panel,
transfer
standard,
reconnect
plug to annunciator
set switch
to
=Normal" position,install annunciator front panel and
installglareshield.
B. Alternate method for calibration without I.A.I.
unit.
If calibration transfer standard, PIN 500D0045 or
9500324000, is not available use the followingmethod
to calibrate =lowfuel" warning:
12-98
24-32-00
7
MOONEY AIRCRAFT CORPORATION
M203
(1) Remove glareshield and remove annunciator
assembly.
CAUTION
Do net operate the starter in excess of 15
seconds or re-engage the starter without
allowing it time to cool.
(2) Install and connectnew annunciator assembly
leavingoff front panel. (Set switchto "Cai").
(3) Drainfuel from tanksand replacewith unusable
fuel plus2 112gallonsin bothtanks,
(4) Turn on master switch and adjust calibration
potsto positionwhere "low fuel" lamps just turn on for
left and righttanks.
(5) Turn OFF master switch, set annunciator"Car
switchto =Norm"position, install annunciatorfront and
installglareshield,
(6) Refuel aircraft.
5. RAM Air Light Warning Circuit - Annunciator
Panel.
The light illuminateson the annunciatorpanel when the
RAM air door is open and the gear is extended,
6. Hi/Low Voltage Warning CircuitAnnunciator
Panel. Remove annunciator top cover. Connect a
voltmeter to the aircraft bus. Start engine and run at
idle. Add load to bus until =Low Volt" light starts to
flash.Adjust RPM to obtaina bus voltage of 12.5 volts
(24-0001 thru 24-2999); 26.5 volts (24-3000 thru
24-TBA). Adjust trim pot (located at center, rear of
circuitboard tillflashinglightjust comes on.
NOTE
It may be necessary to adjust trim pot to turn
out light at 12.5 volts (24-0001 thru 24-2999);
26.5 volts (24-3000 thru 24-TBA) first. Increase
RPM until light goes out and note voltage,
Decrease RPM until light flashes on and note
voltage.
at avoltage
betweenLight
12.4 should
and 12.6come
voltson
(24-0001
thru
24-2999); 26.4 to 26.6 volts (24-3000 thru
24-TBA).
24-34-00
-POWERPLANTClRCUITS
1: Starter-IgnitionCircuit. The starter-ignitionswitch
has five positions:OFF, R (right), L (lefl), BOTH, and
START. In the OFF position both magnetos are
grounded.At the R positionthe left magneto grounds.
At the L position the right magneto grounds. At the
BOTH position both magnetos are HOT and the
ignitionsystem
is ON.
to
start and pushing
in, Turning
closes the
the ignition
starter switch
solenoid,
engagesthe starter and allowsthe impulse couplingto
automatically retard the magneto until the engine is
alsoat its retard fidng position.The spring action ofthe
impulse couplingis then released to spin the rotating
magnetand produce the spark to fire the engine. Alter
the engine starts, the impulse couplingflyweights do
notengage due to centrifugal action.The couplingthen
acts as a straight drive and the magneto fires at the
normalfiring positionof the engine. The starter-ignition
switch is spring loaded to return from START to the
BOTH positionwhen released.
24-34-00
8
SERVICE AND MAINTENANCE MANUAL
A. LowBattery startingprocedures.
Batteriesthat have been dischargedto the pointwhere
they will not turn the engine but have sufficientpower
remainingfor other equipment;should NOT be jumped
with another powersource for two major reasons:
(1) The discharged aireraft battery is not
airworthy because it will not have the necessary
reserve capacity required to operate the aircraft
electricalsystemand avionicsin the eventof the failure
of the generatingsystemduringflight.
(2) Active material on the positive plate expands
when the battery is discharged and the fast recharge
from the higher potential source, battery, alternator,
generator, rectifier, etc., will severly damage the
battery and will result in premature battery failure. A
slow charge is recommended priorto flight.
WARNING
Do not turn the propeller when the magnetos
are not grounded. Ground the magneto points
before removing switch wires or electrical
connectors. All spark plug leads can be
removed as an alternate safety measure.
2. Oil and Cylinder Head Temperature Gauge
Circuits. Both the oil and cylinder head temperature
indicators operate electrically. The oil temperature
gauge circuit has a resistance bulb in the oil surnp.
Changes in resistance caused by changes in oil
temperaturealter current flow rate, thereby varying the
magneticfield in the indicatorcoils.The cylinder head
temperature indicator connects to a tip sensitive
resistance bulb in a cylinder head. Increase or
decrease in temperature causes an increase or
decrease in bulbresistance,varying the magnetic field
in the indicatorcoils.
3. Fuel Pressure Gauge. The Fuel Pressure Gauge
is an electricallyoperated gauge located in the cluster.
The Manifold Pressure Gauge is a simple direct
readinginstrument.
4. Exhaust Gas Temperature Indicator.Exhaust Gas
Temperature Gauge is combined with the Outside Air
Temperature Gauge in a single instrument.
5. The oil pressure instrument circuit contains an
electrical instrument used as a reference, and a
transducerwhich vades resistancewith pressure.
6. Fuel Flow (if installed) is indicated on either an
electrical instrument usinga pressure transducerwhich
varies resistance with pressure or with an electrical
instrumentwhich counts electrical pulses produced by
a turbine flew transducer.
12-98
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
24-3540
-LIGHTING CIRCUITS
1. NavigationLights.A circuit breaker switchon the
flight panel controls navigation lights. GEAR DN
GREEN, annunciatorlightis dimmed when navigation
lightsore ON.
2. Landing Light. A circuit breaker switch on flight
panelcontrols landinglightin the lower engine nacelle
on SIN 24-0001 thru 24-3153.
The rocker switch is connected through MASTER
Switch
on these
aircraft
andisaft
intedor
lights
will go
OFF when
MASTER
switch
turned
OFF
if door
is
Landing/TaxiLights.S/N 24-3154 thin 24-'fBA uses a
splitswitchon Flightpanelto controlwingmountedlights,
3. Cabin Lights. A thrse-position (Bdght, Off, Dim)
rocker switch adjacent to door, in headliner, controls
cabinlights,
CAUTION
On SIN 24-0001thru 24-3153this lightswitchis
connecteddirectlyto battery.The switch MUSTBE
TURNED OFFto keepfrom dischargingbattery,
i. Limit switchesand relays operatethe landinggear
actuator,a reversible motor [14 volt DC (SIN 24-0001
thru 24-2999) or 28 volt DC (SIN 24-3000 thru
24-TBA)]. A landinggear safety system, actuated by a
pitot air pressure switch or a squat switch (24-0001
thru 24-0237) prevents landing gear retraction until
safe flyingspeed ls attained.
The landing gear control switch operates actuator
motorthroughone of these safety switchesand relays.
When landinggear controlswitch is UP and safe flying
speed has been attained, the safety switch closesto
activatethe controlrelay, startingthe actuator. As the
gear reachesthe up and locked position,a mechanical
stop opens limit switch and the actuator stops. When
landinggear controlswitch is placed in downposition,
the gear motordown-relay closes and actuator starts.
When gear reaches down-and-locked position, the
mechanicalstopopens limitswitchand actuatorstops.
Later modelshave a red lightfor gear unsafe;no lights
illuminatewhen gear is up. See Section 32 for squat
switchinformation.
2. Gear Safety By-Pass Switch. Gear will not retract
if airspeed above set limit has not been attainedwhen
gear handle is placed in UP position.Warning hornwill
sound and both "GEAR DOWN" and " GEAR UNSFE"
lights will illuminate. PUSH and HOLD red button
switchbesidelandinggear handle untilgear is UP and
bothlightsgo out.Pull circuitbreaker =GEARCON_ or
=GEAR RELAY" to stop warning hom. Reset circuit
breaker priorto extendinggear.
Aircraft 24-3154 thru 24-3200 may have a door
switch/timer mechanismthat illuminateforward set of
interior lights while cabin door is open. After door is
closed,if rocker switchis left ON, forward interiorlights
willremainON for approximately2 minutes,
The rocker switch is connected through MASTER
Switch on these aircraft and forward interior lightswill
go OFF when MASTER switchis turnedOFF if door is
closed.
4. Anti-Collision Lights. A circutt breaker switch
controlsthe white anti-collisionstrobelights,
5. instrument and Radio Lights. Rheostats control
the glareshield, and radio lights. The flight panel
instrument light rheostat controls the compass light,
Lightingloads are controlledby transistorsbiased with
manual!y controlledrheostats. The transistorscan be
checked bythe followingmethods:
A. Connect ohmeter between the emitter and the
collector;,shouldbe infinite ohms.
B. BhorLbase to collector;shouldbe a direct short,
zero ohms.
:
NOTE
If readings are incorrect reverse the loads.
CAUTION
Care must be exercised to preventshorting light
wires when
installing
or replacinginstruments,
Shorted
wires
will cause
blown fuses or burned
out transistors in the control box.
6. Baggage Compartment Lights. A three-position
(Bright, Off, Dim) rocker switch in headliner controls
this dome light,
CAUTION
On 24-0001thru 24-3153this lightswitch is
connecteddirectlyto battery. The switch MUST BE
TURNED OFFto keep from dischargingbattery,
closed.
7. Map Light.A push buttonswitch on top of control
wheel center sectioncontrolsmap light. Co-pilotsmap
lightis optional.
24-36-00
- LANDING GEAR CIRCUITS
24-37-00
The fuel system has an electric auxiliary fuel pump.
The fuel quantityindicatingsystem is comprisedof two
transmittersin each fuel tank and two fuel quantity
gaugeson instrumentpanel.
1. Fuel Pump Circuits.A single auxiliary fuel pumpis
controlledby a switchlocatedon the instrumentpanel.
2. Fuel QuantityGauge Circuits. Fuel level changes
vary fuel quantity transmitter resistance that operates
fuel quantity gauges. Master Switch activates fuel
quantity indicating system. Refer to Section 28-43-00
for Adjustment Procedures.
24-38-00
Aircraft 24-3154 thru 24-3200 may have a door
switch/timer mechanism that illuminate aft set of
interior lights while baggage door is open. After door is
closed, if rocker switch is left ON, aft interior lights will
remain ON for approximately 2 minutes.
- FUEL SYSTEM CIRCUITS
- MISCELLANEOUS CIRCUITS.
1. Turn CoordinatorCircuit. The turn coordinatoris a
flight instrument which operates from an electrical
powersource.
2. Heated Pitot Tube. A circuit breaker switch
controls the pitot tube heater.
12-98
24-35-00
9
MOONEY AIRCRAFT CORPORATION
M20J
3. Hour Meter (Optional). The hour meter operates
directly from the alternator =Aux."terminal through a
fused wire. SIN 24-1418 and later models hour meter
24-39-00
24-39-01
SERVICE AND MAINTENANCE MANUAL
operates from the electric tachometer. A Hobbs meter
may be installedas an option.
4. Cigar Lighter. A cigar lighter is mounted in the
rightinstrumentpanel.
- TROUBLE SHOOTING CHARTS
- ALTERNATOR TROUBLE SHOOTING
TROUBLE
PROBABLECAUSE
REMEDY
Alternator overchargesbattery;
battery uses excessivewater.
Regulatorfaulty.
ALT FIELD circuitbreakertrips.
Circuitshorted in wiring.
Checkbus voltagewith enginerunning.
Observeaircrattammeter.Ammeter
shouldindicatenear zero atterten
minutesof engineoperation.Replace
voltagemgualtorif defective.
Disconnectleadfrom pinA or 1 of
regulator,*and resetcircuitbreaker.If
circuitbreakertrips,checkwidng.Repair
as required.If breakerdoesnottrip,
replaceregulator.Reconnectleadto
regulator.Set MASTER switchto ON
and checkfor 12V at pinA orI of
regulator.**Repairwiringif novoltageis
present.
*(24-0001 thin 24-2999); Pin 5 for 24-3000 THRU 24-TBA.
**(24-0001 thru 24-2999); Set alternatorfield & Master switchto ON & checkfor 24 voltsat Pin 5 of regulatorfor
SIN (24-3000 thru24-TBA).
ALT circuit breaker trips.
Short circuit in wiring.
Disconnect lead from + postof
alternator, and reset ALT circuit
breaker. If circuit breaker trips, check
wiring between alternator and circuit
breaker.
Short circuit in alternator.
Reconnectleadto + post of alternator.
WARNING: ENSURE THAT
MAGNETO SWITCH IS OFF WHEN
TURNING PROPELLER
Rotatepropeller by hand to rotate
alternatorthrough360 degrees of
travel.
Ifcircuitbreakertdps replacealtemator.
Alternator will not keep battery
charged.
Battery malfunction.
1. StarLengine and adjust for 1500
RPM. Ammeter should indicate a
heavy charge rate with all electdcal
equipment turned off. Rate should
taper off in 1 - 3 minutes.
A _ge
checkatthe busshouldindicatea
readingof 13.75to 14.0volts.
***If charge rate tapers off very quickly
and voltage is normal, check battery for
malfunction.
**'24-0001 thru 24-2999; 28.6 to 28.8 volts for 24-3000 thru 24-TBA.
If ammeter shows a low charge rate or
any discharge rate, and voltage is low,
proceed to step 3.
24-39-00
10
12-98
SERVICE AND MAINTENANCE MANUAL
TROUBLE (cont.)
!
M20J
MOONEY AIRCRAFT CORPORATION
E_
REMEDY
Defective widng.
2. Check voltage at A or 1 terminal of
regulator with master switch ON.****
Meter should indicate bus voltage.
If voltage is not present, check widng
between regulator and bus.
***'24-0001 thin 24-2999;
...@ terminal 5 for 24-3000 thin 24-TBA, with AIt. FId. &
Master switch ON.
Regulator faulty.
3. Remove connector from regulator
and start engine. Momentarily jump A &
B or 1 and 2 pins***** together on the
_lug. Aircraft ammeter should show
eavy rate of charge. If heavy charge
rate is observed, replace regulator. If
heavy rate is not observed, proceed to
step 5.
"***'24-0001 thru 24-2999; pins 5 & 7 for 24-3000 & ON
CAUTION: Pull alternator field CIB. Start engine; while at idle RPM reset C/B. slowly increase RPM
while monitoring bus voltage. DO NOT EXCEED 14 volts for 24-0001 - 24-2999; or 28 volts for
24-3000 thru 24-TBA.
Defective wiring regulatorto
alternator,
4. Check resistance from F2 terminal +
of alternator to pin B or 2 ++of reg. plug.
Normal indication is a very low
resistance. If reading indicates no, or
poor continuity, repair or replace wiring
from regulator to alternator.
+ 24-0001 thru 24-2999, field terminal for 24-3000 thru 24-TBA
++24-0001 thru 24-2999; Pin 7 on 24-3000 thru 24-TBA
Defective alternator.
+++ 24-0001 thru 24-2999; case to field on 24-3000 thin 24-TBA
5. Check resistance from F2 to F1
term.+++of alternator. Normal indication
is 3 - 4 ohms. If rasistance is high or
low, repair or replace alternator.
6. Check resistance from F2 terminal of
alternator to altemator case. Normal
indication is high.
If resistance is low, repair or replace
alternator. (24-0001 thru 24-2999)
12-98
24-39-00
11
MOONEY AIRCRAFT CORPORATION
24-39-02
24-39-03
M20J
SERVICE AND MAINTENANCE MANUAL
- RESERVED
- BA'n'ERY TROUBLE SHOOTING
TROUBLE
_
REMEDY
Dischargedbattery.
Battery worn out.
Replace battery.
Improperchargingrate setting.
Excessive discharging,
Reset chargingrate.
Turn off some equipmentwhen
alternator is notcharging. Decrease
starter usage by usingexternalpower
whenever possible,
Standing too long.
Remove and recharge battery.
Equipment accidentally lefton.
Remove and recharge battery.
Impure electrolyte.
Replace battery.
Short circuit (ground) in widng.
Check widng.
Low charging rate.
Adjust voltage regulator.
Loose hold-down bracket.
Replace battery and secure firmly.
Frozen battery.
Charging rate too high.
Replace battery.
Reduce charging rate by adjusting
voltage regulator.
Too much water added to
battery and charging rate too
high.
Spillage from overfilling.
Drain battery and keep at proper level;
adjust voltage regulator.
Leaking or clogged vent lines.
Repair or clean vent lines.
Charging rate too high.
Adjust voltage regulator.
Discharged battery.
Replace battery.
Water added and battery not
charged
Always recharge battery for 1/2 hour
following addition of water in freezing
weather.
Leaking battery case.
Frozen electrolyte.
Replace battery,
Reversed battery polarity.
Cables connected backwards on
battery or charger,
Battery should be slowly discharged
completely, then charged correctly and
tested.
Excessive water consumption
in all cells.
Charging rate too high.
Correct charging rate.
Excessive water consumption
in one cell only.
Cracked jar.
Replace battery.
Cracked cell jars.
Compound on top of battery
melts,
Electrolyte runs out of vent
plugs,
Excessive corrosion inside
container,
Battery freezes,
24-39-02
12
12-98
Flush container with baking soda
solution.
SERVICE AND MAINTENANCE MANUAL
24-39-04
M20J
MOONEY AIRCRAFT CORPORATION
- STARTER TROUBLE SHOOTING
TROUBLE
PROBABLECAUSE
REMEDY
Motorfails to operate.
Lowbattery.
Checkand_=charge
I_te_yifnecessa_.
Defective,improper,or loose
wireconnections,
Refer to electricalwiring diagram and
checkallwiring.
Binding,worn,or improperly
seated brushes;brusheshave
excessive side play.
Brushesshouldfitfree in brushboxes
withoutexcessivesideplay.Clean
brushesand brush boxeswith vareol
moistenedcloth. New brushes should be
run-inuntilat least 50 percent seated;
however,if facilitiesare not available for
runningin brushes,seat brush by
insertingstrip of No. 00O0sandpaper
between brushand commutator with
sanded side next to brush. Pull
sandpaper indirectionof rotation,being
carefulto keep it in same contoursas
commutator.
Dirty commutator
If commutator is rough or dirty, smooth
and polish with No. 000Osandpaper. If
too rough and pitted, remove
commutatorand turn on lathe. Blow out
all foreign material.
Shorted, grounded, oropen
armature,
Grounded or open field circuit.
Rernoveandreplacewith an armsture
knownto bein goodworkJngorder.
Test and repair circuit if possible or
replace with new parts.
Defective master switch or
circuit.
Defective solenoid switch.
Check and repair.
Defective starter.
Remove and repair or replace.
Slow cranking speed.
Worn, rough, or improperly
lubricated motor or starter,
Starter motor runs but will not
crank engine,
Same causes as listed with
"Motor fails to operate."
Damaged pinion gear or
crankshatl gear.
Dirty starter drive.
Disassemble, clean, inspect &
relubricate components, replace ball
bearing if worn.
Same remedies.
CAUTION: Do not use coarse
sand-paper or emery cloth.
Alter seating, thoroughly clean
brushes and commutator to
prevent excessive wear. Keep
motor bearing free from sand or
metal particles.
Starter drags.
Excessive motor brush arcing.
Check and repair.
Remove and replace.
Clean and lubdcate with graphite &
kerosene.
Low battery charge.
Check and recharge.
Relay or solenoid contacts
bumed or dirty.
Defective power cable.
Worn or dirty commutator.
Remove and replace.
Binding, worn, or improperly
seated brush or brushes have
excessive side play.
Dirty, rough, pitted, or scored
commutator.
12-98
Remove and replace.
Turn down commutator.
Repair as outlined above.
Clean as outlined.
24-39-04
13
MOONEY AIRCRAFT CORPORATION
TROUBLE
-STARTER TROUBLE SNOOTING (eon't,)
_
Excessive motor brush wear /
arcing,
Noisy starter.
M20J
SERVICE AND MAINTENANCE MANUAL
REMEDY
Rough or scored commutator.
Remove and turn down commutator on
lathe.
Armature assembly not
concentdc.
Worn starter ddve pinion.
Reface commutator.
Worn or broken teeth on
crankshaft,gear.
Check teeth and replace gear if
damaged.
Remove and replace starter drive.
24-39-05
- ANNUNCIATOR TROUBLE SHOOTING (24-0001 thru 24-3153)
The followingis a bdef failurecause analysis which pertains to the annunciator(IAI P/N 500D0061) onthe Mooney
M20J. Each cause is listed in probable order. All designator references are made from IAI drawings 710D0125A,
900D0134 and 900D0135.
1. The "gear-down" lampwillnot lightduring"TEST butwill lightwiththe gear-down.
CR1 (Assy A2) open
2. The "gear-down"lampwillnot lightduring"TEST" or with the landinggear-down.
Filamentof DSI (AssyA2) open
3. The "gear-down"lampis dim when the positionlightsare off.
CR24 (Assy A1) open
4. The "gear-unsafe"lampwill not lightduring"TEST" but doeslightwhen the gear is in transit.
CR3 (AssyA2) open
5. The "gear-unsafe"lampwill lightduring=TEST"but notwhen gear is in transit.
CR2 (Assy A2) open
6. The =gear-unsafe"lampwill not lightdudng"TEST" orwhenthe gear is in transit.
Filamentof DS2 (AssyA2) open
CR2 (Assy A2) and CR3 (AssyA2) open
7. The "left low fuel" lamp will not lightduring =TEST" or in a left low fuel situation.
Filament of DS3 (AssyA2) open
Q2 (AssyA1) defective
U1 (Assy A1) defective
Wire fromP1-7 (Assy A1) to leltfuel gauge open
8. The "left low fuel" channel functionsproperly but the lampis alwaysdim.
CR22 (Assy A2) open
9. The "lettlow fuel" lampflickerson and off.
Switch $1 (AssyA1) is in the "Cal" positioninsteadofthe "NORM" position.
Intermittentground on the wirefrom P1-7 (Assy A1) to the left fuel gauge.
C2 (Assy A1) defective
10. The "left low fuel" will not light during "TEST only when the left fuel tank is full.
R10 (Assy AI) should be replaced with a 47K, 1/4 watt, 5% resistor
11. The "right low fuel" lamp will not light during "TEST" or in a right low fuel situation.
Filament of DS4 (Assy A2) open
Q6 (Assy A1) defective
U1 defective
The wire from P1-8 to the right fuel gauge is open
12. The "right low fuel" channel functions properly but the lamp is alwaysdim.
CR23 (Assy A2) open
13. The "right low fuel" lamp flickers on and off dudng flight.
$1 (Assy A1) is in the "Car position instead of the "Norm" position
An intermittent ground on the wire from P1-8 (Assy AI) to the gauge
C3 (Assy A1) defective
14. The =dghtIo_; fuel" will not light during "TEST only when the dght fuel tank is full.
R10 (Assy A1) should be replaced with a 47K, 1/4 watt, 5% resistor
15. The "right low fuel" orthe "left low fuel" lamps light before a low fuel situation has occured.
Recalibrate the appropriate channel CR1 (Assy A1) open.
24-39-05
14
12-98
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
- ANNUNCIATOR TROUBLE SHOOTING (24-0001 thru 24-3153) (con't.)
16, Both the "let1 low fuel" and the "dght low fuel" channels stay dim when they annunciate a low fuel
situationor during "TEST',
Q3 (AssyA1) defective
Q5 (AssyA1) defective
U2 (Assy A1) defective
Q4 (AssyA1) defective
CR22 (Assy A1) and CR23 (Assy A1) open
17, Neitherthe "left low fuel" northe "rightlow fuel" lightsduring "TEST".
CR1 (Assy A1) shorted
U1 (Assy A1) defective
18. The "high low vac" lamp will not light during "TEST" but does annunciate a high or low vacuum
situation.
CR14 (Assy A1) open
19. The =highlow vac" lamp will not lightdudng "TEST" or in a high orlowvacuumsituation.
Filament of DS5 (Assy A2) open
Q7 (AssyA1) defective
20. The =high low vac" lamp will not light in a low vacuum situation but does light in a high vacuum
situation.
Q8 (Assy A1) defective
CR12 and/or CR13 (Assy A1) open
21. In a low vacuum situation the "high low vac" lamp lights but does not flash.
CR16 (Assy A1) open
Q8 (Assy A1) defective
U2 (Assy A1) defective
CR1 (Assy A1) shorted
22. The "high low volts" lamp will not light dudng "TEST" or in a high or low voltage situation.
Filament of DS6 (Assy A2) open
Q10 (Assy A1) defective
Q9 (Assy A1) defective
23. The "high low volts" lamp will not "TEST" but does annunciate a low or high voltage situation.
CR20 (Assy A1) open
24. The "high low volts" lamp lights but does not flash in a low voltage situation.
CR17 (Assy A1) open
Q8 (Assy A1) defective
U2 (Assy A1) defective
25. The "high low volts" lamp will not light in a over voltage situation.
CR21 (Assy A1) open
26. The "high low volts" lamp flashes before a low voltage situation has occured.
RG0(Assy A1) out of calibration
U2 (Assy A1) defective
CR1 (Assy A1) open
27. The "high low volt" will not light in a low voltage situation.
RG0(Assy A1) out of calibration
U2 (Assy A1) defective
CR19 (Assy A1) open
Q8 (Assy A1) defective
CR1 (Assy A1) shorted
28. The "RAM air'' will not light dudng "TEST" or in normal operation.
Filament of DS8 (Assy A2) open
CR6 and CR7 (Assy A2) open
29. The "RAM air" will not light dudng "TEST" but does in normal operation.
CR7 (Assy A2) open
30. The "RAM air" will light during "TEST" but not during normal operation.
CR6 (Assy A2) open
31. The "START POWER ON" light does not illuminate when "TEST" switch is pushed.
This is normal operation; all circuits OK.
32. Once dimmed the "low fuels" cannot be reset to bdght by momentadly depressing the "TEST" switch.
CR11 (Assy A1) open.
12-98
24-39-05
15
MOONEY AIRCRAFT CORPORATION
M2OJ
SERVICE AND MAINTENANCE MANUAL
-ANNUNCIATOR TROUBLE SHOOTING (24-0001 THRU 24-3153) (con't.)
33. Neither the "high low vac" orthe "high low volts" will flash when low vacuum and/or low voltage occurs.
Q8 (Assy A1) defective
U2 (Assy A1) defective
CR1 (Assy A1) not suppling +5 VDC
C5 (Assy A1) defective
24-39-06
ANNUNCIATOR TROUBLE SHOOTING (24-3154 thru 24-TBA)
The following is a brief operational analysiswhich pertains to the I.A.I. annunciator on the Mooney M20J SIN
24-3154 thru 24-TBA..
1.0 GENERAL
2.0 POWER SUPPLY
This document is intended to be a guide to assist a
service technician in understanding the theory and
operation of International Avionics, Inc. (!AI) Part
Numbers, 9500326000 & 9500326001 annunciators.It
is not intended to serve as a bench service aid in that
reference designators in various Figures are not
consistent with those found in actual annunciators,
Service literature is available from International
Avionics, Incorporated (IAI), 1611 N. 1-35, Suite 428,
Carrollton, TX 75006, telephone number (214)
446-1185, to identify location of a particular component
and exact manner in which components are
interconnected,
The following sections address nine (9) basic circuits
which, used singulady or in multiple combinations,
comprise the annunciators. These sections are as
follows:
Section 2
Power Supply, with Test and
Dim
switches
Section 3
Flasher
Section 4
Landing Gear Indicators
Section 5
Let_and Right Low Fuel
Section 6
Hi/Lo Vac
Section 7
Alternator/Low Volts/Over Volt
Section 8
NOT USED
Section 9
Typical Positive Apply W/Dim
Section 10
Typical Positive Apply W/O/Dim.
,_"',,
;'
";
,,_,'=,,
The Power Supply, shown in Figure 1, provides 12
VDC, reverse voltage protectionby means of CR1,
spike and overvoltage filtering by means of the low
pass network of R1, R2, C1 and C2 with spike
clamping provided by CR2. The actual power supply is
a 12VDC, integrated circuit regulator. Output filtering
is provided by C2. The Test Switch, $1, switches
unfiltered aircraft 28 VDC to the internal test line,
identified with the mnemonic TEST+. This signal, diode
isolated by CR5, is also supplied as OUTTEST+.
Additionally TEST+ is applied to the inverter to supply
the internal test line, TEST-, and the diode isolated
our-FEST-. The dimmer circuit, applicable to certain
channels, requires a bias source, DIMBIAS, with a
magnitude of 12 VDC to dim the applicable ACTIVE
channels, approximately 3 VDC to maintain the dim
level of those channels previously dimmed, and near 0
VDC to reset the dimmed channels to a bright
condition. The channels having the capability of being
dimmed by the above circuitry are channels x, x, x, x,
x, x, and x. Channel 1, Landing Gear, dims by means
of a separate circuit and is discussed in Section 4.0
below. With both the Dim Switch and Test Switch
relaxed, transistor Q3 is in saturation and 02 is off,
giving DIMBIAS a value of approximately 9 VDC.
When the Dim Switch is depressed Q3 comes out of
saturation and DIMBIAS rises to 12 VDC, and when
the Test Switch is depressed Q2 saturates and
DIMBIAS drops to near O VDC. In the event that both
switches are depressed simultaneously, the 0 VDC
value of DIMBIAS will prevail and the dimmed
c_
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bright cond t on
channels, with the exception of Channel 1, are reset to
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24-39-06
16
2. 2K
12.98
4. ?_t_
_IGURE:
2
-
FLftSI.IgI_
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
3.0 FLASHER
The Flasher, shown in Figure 2, provides the circuit to
flash the outputs of the left and right aitemator
warnings, the low voltage warning and the low vacuum
warning. The flasher consists of an astable oscillator
ddving an NPN common emitter connected transistor,
Q4.
Thistoallows
open from
collector
Q4, amplifiers
identified as
FLASH,
sink the
the drive
the of
output
of
the appropriate warning channels.
bdlliance. The GEAR UNSAFE channel accepts +28
VDC, INPOS2, through isolation diode CR10,
illuminates at full brilliance and does not dim. A test
signal, TEST+ is applied to both GEAR DOWN and
GEAR UNSAFE through CR8 and CRll respectively.
6.0 LEFT AND RIGHT LOW FUEL
The Left and Right Low Fuel circuits are shown in
Figure
4. The
the dght
channels
are similar,
and only
the left
left and
channel
will be
discussed
herein.
4.0 LANDING GEAR INDICATORS
The Landing Gear Indicators, shown in Figure 3,
provide the status of the landing gear position, that is,
whether the landing gear is Down or not and whether
the landing gear is safe or unsafe, unsafe being in
transit. The circuitshownis the identicalcircuitthat has
been used for many years in the IAI annunciators used
on Mooney aircraft. The GEAR DOWN channel is
dimmed for night operation; however, in the interest of
reliability, the dimming circuit is separate from the
dimming technique used on the other dimmed
channels. The gear down signal, +28 VDC, is applied
through isolation diode CR7, to the INPOS1 input and
CHIRET is returned to the Nay Light bus. When +28
VDC is applied to INPOS1 and the Nay Lights are off,
the impedance of this point is very low due to the low
filament resistance of the Nav Light bulbs, and GEAR
DOWN illuminates at near full brilliance. When the Nov
Lights are on, however, CH1RET is also +28 VDC and
DR9 switches this return path off, the return path for
the GEAR DOWN lamp being through R15 to Ground
and GEAR DOWN now illuminates at reduced
Signals from the junction of the le£_ and dght fuel
transducers and the left and dght fuel quantity gauges
are applied, respectively, to each of the inputs INPOB3
and INPOS4. This signal is an analog signal that
indicates the quantity of fuel measured, the typical low
fuel point being on the order of 0.1 volt. The low fuel
circuits can, however, annunciate an input up to
approximately 0.7 volt. The input, INPOS3, is applied
through an isolation resistor R55 to the inverting input
of open collector comparator U5:C. The input is
compared with the set point effected by the setting of
R51, accessible through the front of the annunciator,
and, when the input is less than the set point, the
comparator's output is allowed to rise by means of the
pull-up resistor R54 and the network R48, R49, and
C9. Feedback resistor R53 provides a small amount of
hystedsis to preclude oscillation at the transition point.
The exponentially rising output of U5:C is applied to
the inverting input of open collector comparator U5:B
and is compared with a reference voltage of
approximately 6 VDC. When U5:B switches its output
to ground Q10 conducts and drives Q8 into saturation
to light the L LOW FUEL channel lamp, DS3. The
Q10 - Q8 network is required to provide the transition
between the internal 12 VDC and aircraft +28 VDC.
The delay provided by the charge of C9 through R48
and R49 provides filtering to preclude false
annunciation in rough air. When the fuel level dses,
c_?
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psi
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the charging rate of the filter C9, thus reducing the
delay to approximately 2 seconds. In order to
applying
through
- CR15
to accelerate
R49. The TEST+
delaythe
time
of theR42
charging
network
provides
adjusted
with
screwdriver
adjustment
accessible
through the front of the annunciator while there is a
preset
number
of fuel
gallons
in thethe
tank.
timeR51,
delay
calibrate
the low
channel
setThe
point,
is
must be removed from the circuit by moving $3,
accessible through the front of the annunciator, from
This opens the return for capacitor C9 and the
the
NORMAL
position
to the
CALIBRATE
indication
on the
L LOW
FUEL
channel willposition.
not be
[
time delay by moving $3 from the CALIBRATE
position
the NORMAL
position. The
position
delayed. back
After to
calibration
is accomplished,
restore
the
$3 can be determined without removing the front of
the annunciator. When the TEST switch is depressed
observe the indication of L LOW FUEL and R LOW
FUEL. With 83 in the NORMAL position there is a
delay of approximately 2 seconds in Illumination, but
with B3 in the CALIBRATE position there is no delay
in illumination.
LMPPeSz_
_1
_[CURE 3 - LnNDtHC _
low output state, C9 is discharged rapidly through
a
delay
in low fuel
annunciation
approximately
20
due
to sloshing
and of
U5:C
a
seconds.
A test inofthe
thetank
functioning
of switches
the low to
fuel
channel is accomplished by applying TEST+ through
R43 - CR18 to the input of U5:C to switch U5:C and
_N_C_TO_S
12-98
24-39-06
17
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
Up to this point the circuits used to annunciate low fuel
are the same circuits that have been used for many
_
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The method of dimming, however, has been changed
and expanded from what has been used in the past. In
the pastonlythe low fuel channelsdimmed, excluding
yearn
GEAR
inDOWN
IAI annunciators
discussed
used
above,
Mooney
whileadditional
now
aircraft.
the5
dimming
has
been
expanded
to on
include
channels. From the perspective of the pilot the
switchand
operation
is the same,
depressthe
theTEST
DIM switch and
active channels
dim, depress
active dimmed channels return to bright. When a
dimmed channel is extinguished and then reactivates
it will reactivate bright. The method to accomplish this,
however, is considerably different from the past. Each
,
;,,_>_
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,,_ IL,.
_.,
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=_
case Q8 which returnsthe lamp to ground through two
parallel paths. The path to provide a dim indication is
channel to
be dimmed
is driven
by a transistor,
in this
through
resistor
R29 which
reduces
the brilliance
of
the lamp. In the bdght mode R29 is shorted by Q6 and
CR13 which provide a low impedance path to ground.
I Trans stor Q6 s contro ed in conduction by a latch
composed of U3 and its associated resistors R22,
R23, R24, R25, R26 and R27 as well as the signals
DIMBIAS and DIMIN3. If the channel is active DIMIN3
will be near ground and with DIMSIAS near 3 VDC,
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the output ofWhen
U3 will
high,Switch
thus ddving
Q6 into
conduction.
thebe DIM
is depressed
momentadly, DIMBIAS goes high to 12 VDC and U3
switchesits outputlow and latches thmugh R26. This
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When the TEST Switch is depressed momentarily,
DIMBIAS goes low and U3 switches its outputhigh,
latches through R26, and drives Q6 into conduction.
When the channel deactivates, Q8 opens the retum to
ground and DIMIN3 rises which returns latch U3 to a
high outputstate.
6.0 HI/LO VAC
The High/Low Vacuum circuits are shown in Figure 5.
This channel is designed to accept two +28 VDC
signals, one from a low vacuum sensor and one from
a high vacuum sensor. When low vacuum is detected
the annunciator will flash and when high vacuum is
detected the annunciator will illuminate steady. A +28
VDC signal applied to LOW VAC INPUT will drive Qll
into conduction through the bias network R56, R57,
CR17, and
thus
illuminating
DS9.
The as
signal
FLASH
will, CR22,
however,
remove
this ddve
signal
the
flasher cycles, thus flashing Dsg. A +28 VDC signal
applied to HIGH VAC OVERRIDE will bypass the
above network and drive Qll
into conduction
regardless
the state
LOW
VAC INPUT.
Similarly
TEST+
willofddve
Qll of
into
conduction
regardless
of
the state of LOW VAC INPUT. The channel High/Low
Vac does not dim.
0=
_u_
24-39-06
18
12-98
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
zeuae
DS9
7_27
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channel flashes, and when
detected
overvoitage
tdpped
the
annunciator
is detected
the
annunciator
channel
illuminates steady. Comparator
U6 monitors the aircraft 28 VDC
by comparing the voltage at the
_
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CR19
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OUEeRIDE _.
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Indicates that the aircraft bus
voltage is less than 26.5 VDC.
When low voltage is detected
internally or when low current is
_11
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arm of R68 with the regulated
voltage
at The
the output
junction
and R65.
of of
ue,R64
an
open collector comparator is
normally low. When low Voltage
is detected the output of U6
conduction through the bias
t
rises
Q12CR28,
into
networkand
R6O,drives
CR24. and
thus illuminating DS1O. In a
manner similar to the Hi/Lo Vac
channel, the signal FLASH will
FIGLIRE 5 - HI/LO
ut_c
remove this ddve signal as the
flasher cycles, thus flashing
DS10. A +28 VDC signal applied
7.0 ALTERNATOPJLOWVOLTS/OVER VOLT
to LOVERRIDE will bypass the above network and
The Alternator/Low Volts/Over Volts circuits are shown
ddve Q12 into conduction regardless of the state of the
in Figure 6. This channel is designed to accept two
comparator U6. Similarly TEST+ will ddve Q12 into
signals, the +28 VDC signal LOVERRIDE from the
conduction regardless of the state of the comparator
overvoltage tdpped output on the left alternator
U6. A +28 VDC signal applied to LOVERRIDE also
regulator, and one signal derived internally that
drives Q12 into conduction regardless of the states of
either comparator U6 or U7. Similarly TEST+ will
drive Q12 into conduction regardless of the states of
either cemparator U6 or U7. The channel Left
2evoc
_2voc
2BV0C asia Alternator/LowVolts/Over Volt does not dim.
, , ,
8.0 NOT USED
_4.'7K
;15K
.21{
, RB2
(FIGURE7 NOTUSED)
{:R29
4
TPh
LOW VOLT SET
g.o TYPICAL POSITIVE APPLY W/DIM
_N_05
Re0
CR24
A
typical PositiveApply, Dimmable circuit is shownin
U6
1OK
1N4005
IN4OQ5
....
Figure
8. This
is designed
to accept
CR20
VDC signal
to channel
illuminate
an indicator
channela +28
and
].oo I
!R.5 IR.,
R67
L2K
,R64
._
,
provide for dimming of that channel, as well.
Dimming is accomplished in a manner similar to that
CR_S
L
]VERRIDE
"1
]T_%
LASH
described isfor
low fuel
channel
Theto input,
XlNPUT,
applied
through
CR35above.
and R84
drive
Q15 into saturation and light DS-X. TEST+ is applied
through CR36 and R84 to also ddve Q15 into
saturation and light DS-X. These 5 channels may be
dimmed by depressing the DIM switch to dim the
active channels. Depressing the TEST switch returns
the active dimmed channels to bdght. When a
dimmed channel is extinguished and then reactivates
it will reactivate bdght. Each channel to be dimmed is
ddven by a transistor, in this case Q15 which retums
the lamp to ground through two parallel paths. The
path to provide a dim indication is through resistor
lrl_10a5
RB3
CR27 _B_
CR2B
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RT4
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H
RSg
1.SBO001XXX
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.....
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oc
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_i1/_-uC33°_
R85
which
reduces
the
brilliance
of
the
lamp.
In the
bdght mode R85 is shorted by Q14 and CR34 which
providea low impedance path to ground. Transistor
Q14 is controlled in conduction by a latch composed
of U9 and its associated resistors R86, R87, R88,
R89, R9O and R91 as well as the signals DIMBIAS
and DIMINPUT. If the channel is active DIMINPUT
will be near ground and with DIMBIAS near 3 VDC,
INPUT
1.SBO0DIXXXR_72 J
FIGURE
5 -- ALTERNATOR,
LO'_WOLTS/OVER
VOLT
12-98
24-39-06
19
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
LAMP
3.2 UDC
DS--X
q14
7a27
DIMOUTPUT
ZH6e_9
4
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t
Re4
cR 36
"_
Req
4va
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47B
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CR34
RBB
6. DE
RB6
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47_
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e. et
UDC
47K
12
LIDC
up_L u9
-_-
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2_3a t9
IMBIAS
t N4_IB_
%,
'EST+
FIGURE 8 -
TYPICAL POSITIVE APPLY W/DIM
the output of U9 will be high, thus driving Q14 into
conduction. When the DIM Switch is depressed
momentarily, DIMBIAS goes high to 12 VDC and U9
switches its output low and latches through R87. This
low output removes the ddve from Q14 and DS-X
dims. When the TEST Switch is depressed
momentarily, DIMBIAS goes low and U9 switchesits
outputhigh, latches throughR87, and drives Q14 into
conduction.When the channeldeactivates, Q15 opens
the returnto ground and DIMINPUT rises which returns
latch U9 to a highoutputstate.
10.0 TYPICAL POSITIVE APPLY W/O/DIM
24-50-00
24-51-00
- POWER DISTRIBUTION SYSTEM
The power bus distributesdirect current power to the
electrical system from the alternator and from the
battery throughthe battery relay.The negative battery
lead attaches to a structural ground on the airframe.
The master switch"ON" closesthe relay and supplies
powerto the aircraftelectricalsystem.
A typical Positive Apply, Non-Dimmable cimuit is
shown in Figure 9. This channel is designed to accept
a +28 VDC signal to illuminatean indicatorchannel,
but does not providefor dimmingof that channel.The
input,YINPUT,
is applied through
to light DS-Y.
TEST+
is appliedthroughCR37
to CR38
also lightDS-Y.
CR 38
TEST-,-
CR37
tFI400S
[_#]]
_
tb14005
F '['GURE
7YPICRL
24-50-00
2O
POS_T[UE
{
9
_
DS-y
_
2322
--_
_PPLY
- ELECTRICAL LOAD
DISTRIBUTION
NO/DI_
12-98
CAUTION
Do not reset a circuit breaker after it has tripped
a second time. If necessary to do so to locate
the malfunction, be alert for a possible
electrical fire. Breakers are "Trip Free" type and
cannot be held in the closed position.
MOONEY AIRCRAFT CORPORATION
M20J
CHAPTER 25
SEATS
SERVICE AND MAINTENANCE MANUAL
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M20J
SERVICE AND MAINTENANCE MANUAL
CURRENTLY NOT BEING USED
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M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 27
FLIGHT CONTROLS
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 27
FLIGHT CONTROLS
LIST OF EFFECTIVEPAGES
CHAPTER
SECTION
SUBJECT ...........
27-EffecUvity .........
27-Content ..........
27-00-00 ............
27-20-00 ............
27-29-00 ............
27-30-00 ............
27-30-03 ............
27-31-00
...........
27-40-01
...........
27-50-00
...........
27-50-00
...........
27-60-00
...........
27-93-01
...........
27-94-00
...........
27-95-01
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27-96-00
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PAGE
..........
DATE
1/2BLANK ..........
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5 ...........
6 ...........
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9 ...........
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12 ...........
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1/2BLANK
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 27
FLIGHT CONTROLS
CHAPTER
SECTION
SUBJECT
TABLE OF CONTENTS
...........
27-00-00 ........
27-10-g0 .........
27-20-00 .........
27-30-00 .........
27-30-03
..........
27-31-00
..........
27-40-00 .........
27-40-01
..........
27-42-00 .........
27-50-00 .........
27-60-00 .........
27-90-00 .........
27-91-00
..........
27-92-00 ..........
27-93-00
..........
27-93-01 ............
27-94-00
..........
27-95-00
..........
27-95-01 ............
27-96-00 .........
27-96-01
..........
SUBJECT
........
General ..............
Aileron System ...........
Rudder & Steering System ........
Elevator System ...........
Empennage Free Play ........
Trim Assist Bungee Rigging ......
StabUizerTdm System .........
Trim System Troubleshooting......
Electric Tdm Pitch Maintenance ......
Wing Flap System ..........
Aileron/Rudder Interconnect System .....
Miscellaneous ...........
Control Surface Static Balancing .....
Equipment - Static Balancing ......
Balancing Procedures - Static Balancing.
Detail Procedures-Static Balancing .
Control Surface Trailing Edge ......
StalIWaming Maintenance Practices..
.
TroubleShooting- Stall Warning System
Speed Brakes System .........
Maintenance - Speed Brakes ......
12-98
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9
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12
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14
14
14
14
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16
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18
18
27-CONTENTS
3/4BLANK
SERVICE AND MAINTENANCE MANUAL
M2OJ
MOONEY AIRCRAFT CORPORATION
27-00-00
- GENERAL
The aircraft,has dual flight controlsand can be flown
from eitherthe pilotor co-pilotseat. Dual pairs of foot
pedals control the rudder and nose wheel steering
mechanisms. The co-pilot pedals are removable if
optionaldual brakes are not installed.Push pull tubes
actuate the all-metal flight control surfaces. Rod-end
beatings are used throughout the flight control
systems.These bearings are simple and require little
maintenance other than occasional lubdcation.
Specially designed aluminum-alloy extrusions, that
permit flush skin attachment, form the leading edges of
the rudder and elevators. Electrically actuated wing
flap systems are installed on all models. Longitudinal
pitch trim is achieved through a trim control system that
pivots
the entire empennage around the tailcone
attachmentpoints.
at rod end (7) (Figure 27-2) so that aileron (in neutral
position) is 0° to -2 ° down (with no additional
tolerance) as measured with travel board at wing
station indicatedon travel board GSE 030003.
NOTE
Wing station 147.76 is located at skin splice line
between flap outboard end and aileron inboard
end.
27-10-00
G. Rotate the left control wheel clockwise until
the ailerons contact the aileron stops (8) (Figure
27-2). Adjust control tube (B) at rod ends (1) and (5)
(Figure 27-1) by looseningthe lock nut and turning
tube clockwise or counterclockwise to attain .020
maximum clearance using feelergauge (N), (Figure
27-1). Secure Iocknuts (1) and (5) and recheck .020
dimension. Repeat the operation on right control
wheel by turning wheel counterclockwise until
ailerons contact the stops, then proceed as
described for the left control wheel. Rigging is now
complete.
4. AileronRigging(S/N 24-1426 & ON).
A. Level controlwheels - (Reference 27-10-00, 3,
B Procedures).
B. Install3/15 dia. rig-pinsat:
-AILERON SYSTEM
1. Ailerons.
The ailerons are of all-metal constructionwith beveled
trailing edges. Three hinges of machined, extruded
aluminum attach the ailerons to the air wing spar
outboard of the wing flaps. The ailerons link to the
controlwheel through push-pulltubes and bellcranks,
Lead counter-weightsstaticbalancethe ailerons,
2. AileronRemoval and Intallation.
A. Remove control tube attaching bolt, nut, and
washer at aileronhorn.
B. Remove bolts,nuts, and washersfromthe three
attachinghinges.
C. Remove aileron by pulling it straight air until
hinges are clear, rotate inboard portion down and
forward to allow aileron balance weights to clear wing
tip (if configured).
D. Reinstall aileron in reverse sequence of
removal.
E. Recheckboltsfor securityand safety.
3. Aileron Rigging and Control Adjustment (SIN
24-0001 thru 24-1424).
A. Use a straight
edge (A),
(Figure
controlwheels
in accordance
withstep
B.27-1) to align
B. Adjust control tube (B) linking control wheel
shaft (C) at rod ends (5). Clamp or otherwisesecure
controlwheels in the level positionuntil stepsC thru E
are completed,
F. Remove clamps from control wheels, then
adjust aileron stoj0s (8), (Figure 27-2) so the down
travel is 8° +/- lU. Aileron up travel may vary from
12-1/2 ° to 17° (with no additionaltolerance), (12-112o
to 14-1/2° SIN 24-1038 and ON).
NOTE
The aboveaUeron rigging and adjustment
instructions apply to both the left and right
ailerons.
(1) Jackshal_(C) (Figure 27-1)
(2) Bellcrank(E) (Figure27-1)
(3) Bellcranks (9) (Figure 27-2) (Both L.H. and
R.H.)
C. Adjust controltubes (F) (Figure 27-2) (L.H. and
R.H.) to positionailerons at 0 degrees to 2 degrees
down.
D. Adjust remaining control tubes (F), (B), (D),
(Figure 27-1) (L.H. and R.H., if applicable) in order to
freely attach to the bellcranksand jackshatt.
E. Remove rig-pros.
F. Adjust aileronstops (Reference Figure 27-2) per
paragraph27-10-00, 3, G. Tolerances are specified in
paragraph27-10-00, 3, F.
C. Adjust control tube (D) at rod end (2) so that
aileron center bellcrank (E) is 1/16 inch left of center
facingforward, FIGURE 27-1.
D. Adjust aileron control tubes (F) by removing
bolt, nut and washer (4) (Figure 27-1) and loosening
Iocknut(6) (Figure 27-2). The aileron control tube (F)
can then be rotated clockwise or counterclockwiseso
that the center of the outboard bolt (K), (Figure 27-2),
is 4 3 nches from spar web (M). Replace bolt, nut and
washer (4), (Figure 27-1), and recheck 4.3 inch
dimension.
NOTE
Refer to SECTION 27-60-00 for Aileron/Rudder
Interconnect System Rigging Procedures
E. Adjust aileron push-pull tube (J) (Figure 27-2)
12-98
27-00-00
5
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
5
]3
H
SM27-I
AILERON & ELEVATOR CONTROL WHEEL RIGGING - FIGURE 27-1
27-20-00
- RUDDER AND STEERING
SYSTEM
1. Rudder. The rudderattaches to the aft vertical fin
spar at four hinge points. Push-pull tubes and
bellcrankslinkthe rudderto the rudderpedals,
2. Rudder Removal and Installation.
A. Detach rudderpush-pulltube fromrudder horn.
B. Remove attachinghardware at rudderhinges,
C. Remove rudder by pullingitstraightaft.
D. Install rudder in reverse sequence of removal,
Recheckattaching boltsfor security and safety.
3. Rudder Rigging and Adjustment.
A. Raise aircraft nose. (A propelleryoke jack may
be used.)
B. Set stabilizer tdm control in neutral position
27-20-00
6
(stabilizer parallelwith aircraftcenter line).
C. Clamp pilotsrudder pedals (A), (Figure 27-3), in
neutral position
D. Adjust Rod Eng beadng (B)(Fig. 27-3)
approximately9-11 turns outto start.
E. Adjustrudder control tube (C) at rear tailcone
bulkhead bellcrank, (Figure 27-5), approximately 6
turns out at startingpoint.
F. Adjust ruddercontroltube (D), (Figure27-6), rod
end bearing (at 2) 11 turns outto start.
NOTE
Rudder bellcrank, aft tailcone, should be
modified per SI-M20-44.
G. Adjust Rod End Beadng (B) (Fig. 27-3) to
positionRudder 1° to the right.
12-98
SERVICE AND MAINTENANCE MANUAL
M20J
H. Unclamp rudder pedals,
I. Adjust rudder stops (paddles) (M), (Figure 27-8),
so that rudder travel is 23 degrees (+1,-0 degrees)
MOONEY AIRCRAFT CORPORATION
dght and left.
J. Rudder stop limiter (R), (Fig. 27-8), may be bent
to obtain clearances and contact with stops (M).
NOTE
/
between adjustment stop (3) and gear truss
assembly (4) (Figure 27-¢) when rudder is at
extreme left and right travel position.
K. After setting NLG steedng stops, retighten all
jam nuts, boltsand secure recheck all travel limits.
I On aircraft SIN 24-1464
& ON steedng stops (3)
NOTE
Measure
rudder
travel
with
travel
board exists
on rivet
should be adjusted so .020
clearance
line at station indicated on travel board GSE
030005, and with longitudinal trim (stabilizer)
set in the 0 degree position. (8ta. 26.50 is
located at skin splice on vertical fin).
O
I
L. Adjust nose wheel steedng by removingnut,
o
steering idter linkage at (2). Bolts, nuts and washers
at (5) & (6) must be installed from rear to front.
washer
& bolt (1),
(FigureLimits
27-4), atand
adjusting
4. Allowable
Free-Play
RUDDER
VERTICAL MOVEMENT
A. Maximum vertioal movement allowable at
rudder trailing edge -.08 inches.
(1) If excessive free-pray exists check the
fallowing areas for wear:
(a) Trim screw jackshalt.
(b) Trim link connecting empennage to trim
screw.
AILERON STOP ADJUSTMENT - FIGURE 27-2
TRAVEL BDARD
LrlCATIDN
_'TA,
a_
t/amA_IOVE C/L
LEVELINr,
SCREWS
TRAV'-_ IlrlAp-_ LDCATIrlN
BETWEENFLAP & AILERON
STA. 147.75
m
( ..
RUDDER PEDAL ADJUSTMENTS - FIGURE 27-3
SI427-3A
TRAVEL BOARD LOCATIONS - FIGURE 27-3A
12-9B
27-20-00
7
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
47
o
SMJK_'7-4
NOSE GEAR STEERING LINKAGE ADJUSTMENT - FIGURE 27.4
(c) Bolls and brackels atlach_g empennageto
ta#oone.
5. Rudder Torque Tube Removal, The rudder
torquetubeshouldbe inspectedthoroughlyand replaced
if any damage is found. Remove shield from front of
cabin floorboard that covers torque tube. Remove
attachinghardware from hingesand rudder pedal control
rods.Carefully removetorque tube by slidingout toward
the rightside of cabinand throughcabindoor.
NOTE
Control tube wear allowables. If any portion of
the control tube exceeds .007 wear per wall or
.014 in reduction in diameter, the tube must be
replaced.
27-30-00
-ELEVATOR SYSTEM
1: Elevators. Elevator constructionis essentiallythe
same as that of the ailerons. Both elevators attachto
SNX27-7
SMP7-9
RUDDER & ELEVATOR TRAVEL ADJUSTMENT
FIGURE 27-5
27-30-00
8
RUDDER HORN ADJUSTMENT - FIGURE 27-6
12-98
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SERVICE AND MAINTENANCE MANUAL
M2OJ
MOONEY AIRCRAFT CORPORATION
wa k ng beams and bellcranks link both elevators to the
control yoke. Both elevators are connected by control
tubes to a common bellcrank in empennage. Lead
counterweightsstatic balance both elevators.
the stabilizer at four hinge points. Push-pull tubes
.,,//1_"_
A. Remove
push-pull
control
tubesbolls,
fromnuts,
elevator
control
horns by
taking off
attaching
and
2. Elevator
Removal
andallInstallation.
washer.
_/_-_/
_
B. Remove bolls, nuts, and washers from the four
attaching hinges.
C. Remove elevator to the rear.
D. Install elevatorsin reversesequence of removal.
Recheck attaching bolls for secudty and safety.
3. Elevator Rigging and Adjustment
A. Adjustrodend beating(3), (Figure27-1), at control
yoke (G) for controlshaft (H) clearancefrom firewalland
controlyoke(G) clearance fromfuselagestructure.
B. Level aircraft and set control column in neutral
withstabilizer parallelto center lineof aircraft.
NOTE
Measure elevator travel from O degrees
stabilizer thrust line with travel board
positioned at stabilizer station indicated on
travel board GSE 030004 and with stabilizer at
0 degrees aircraft thrust line.
(See Figure 27-3A & 27-11)
NOTE
Elevator bellcrank, aft tailcone, should be
modified per SI-M20-44.
C. Adjust rod end bearings of control tube (L),
(Figure 27-5), at rear tailcone bulkhead out
approximately5 turns to start.
D. Adjust elevator horn rod end (9), (Figure 27-7)
out 7 or 8 rums to start.
y...----
•
O
\
\
ELEVATOR HORN ADJUSTMENT- FIGURE 27-7
27-30-03
- EMPENNAGE FREE PLAY LIMITS
Allowable free-play movement of the empennage
assembly on the tailcone of the airplane, with the
tailcone fixedat the tailskid:
Horizontalstabilizer @ Tip:
0.12 inchma_ -Fore &Art
0.10 inchma_- Up&Down
Rudder @ Lower trailingedge:
0.08 inchma_ - Up & Down
E. Main spar adjustable rod end bearingis turned
out approximately6 turns to start. To obtain additional
elevatortravel, adjust as required.
F. Set elevator stops (P), (Figure 27-8), in
empennage stinger for elevator uptravel 22 +/- 2
degrees and downtravel of 22 +/- 2 degrees,
G. After elevator stops (P) are set, rotate elevators
thru full range of travel to assure solid contact with
stops and that nuts and bolt heads clear stop limiter.
Elevator stop limiter (E) may be bent to obtain
clearances and positive contactwith (P) (Figure 27-8).
H. Rotate stabilizer trim full down to check
clearance of bellcrank at wing stub spar. Adjust md
end beadng at rear tancone bulkhead (C)(Fig. 27-5), if
needed, for clearance. Recheck elevator up and down
travel.
o
o
/
//
1. Rotate elevator trim _.dL.u_;check that Elevator
up stop(P) makes solid,contacton elevator stoplimiter
(E).
J. Retighten all jam nuts, attach bolts and secure
as necessary; recheck all control tube clearances and
travel limits.
o
RUDDER _, ELEVATNR
o
o TUBE
STDP AJ]JUSTMENT
FIGURE 27-8
12-98
27-30-03
9
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
27-31-00
- TRIM ASSIST BUNGEE RIGGING
Bungee units in the elevator control systems assist in
stabilizertrim adjustment.
NOTE
Negative stabilizer (- degrees) settings mean
that stabilizer leading edge is moved down
relative to the thrust line.
[/7
FW9
A, Set stabilizerto -3 degrees position.
B. Adjust trim bungees(N), Figure27-9 at rod-end
beadng (10) for elevator up angle of 19 degrees + 1
degree.
STnp
E:-
f
P
SH27-TRIM
TRIM ASSIST BUNGEE RIGGING - FIGURE 27-9
nut
27-10), break
torque
jamor nut/stepped
(if
installed) and turn
stopon(A)
jamnut/stepped nut
(A&E)ofclockwise
alignthread
ronsard
edge
UP stop or
or counterclockwise
stepped nut, withtofront
of
tdmscrew (C) (Figure 27-10). Tighten setscrew and
%\
10
N
sHJa7-9
TRIM ASSIST BUNGEE RIGGING - FIGURE 27-9
NOTE
Rig trim assist bungees before installation of
elevator extension springs (P), Figure 27-9.
27-40-00
- STABILIZER TRIM SYSTEM
To provide pitch trim control, the entire empennage
pivots around its main hinge points. The system
consistsof a manuallyoperated actuator that operates
a series of torque tubes and universal joints connected
to a jack screw on the afl.tailcone bulkhead.
NOTE
A "stepped stop nut", with a "jam nut"
configuration has been incorporated. This can
be retrofitted to all M2OJaircraft if desired. This
allows trim screw nut (F) to contact stepped
portion of these two nuts and not bind.
screw
nutcontrolwheel
(F) against UPtostop
stepped
(E). (trim
turn trim
full or
NOSE
UP nut
position
(Figure 27-10). Rotate trim screw nut (F') against UP
stopor
nut(E); full nose up
position.
B. Disconnecttorque
shaft
(B) from trim screw (C),
C. Tum disconnectedtorquesha_ (B) clockwiseor
counterclockwise until horizontal stabilizer as
measured,usingthe travel board, PIN 030004-503, as
shown by (Figure 27-11), is withinthe following limits.
-5.5 degrees leading edge down. (Approx. 4.5 inches
measured).
NOTE
Negative (-degrees)stabilizer degrees mean
that stabilizerleadingedge is moved down
relative to thrust line.
D. Connect torque shaft. (B) to trim screw (C)
(Figure 27-10). NOSE UP stabilizer trim control rigging
is now complete.
2. Nose Down Stabilizer Trim Control Riggingand
Adjustment.
A. Loosensetscrew in down stop orjamnut (A) and
turn stop(s) on threaded shaft to move it toward AlL
Turn trim controlwheel toward NOSE DOWN position
until horizontalstabilizer is within the following limits:
+.75 degrees leading edge up (Approx. 2.75 inch
measurement).
NOTE
Positive stabilizer (+degree) settings mean that
stabilizer leading edge is moved up relative to
thrust line.
Basic rigging, for either configuration, is identical to
procedures below except that stepped nut and jam nut
require
beingnuttorqued
together,
withagainst
two wrenches,
prior to jam
set screw
tightened
threaded
trim screw (C). Stepped nuts are required at the nose
up and nose down positions, facing trim screw nut (F).
1. Nose Up Stabilizer Trim Control Rigging and
Adjustment.
A. Loosen setscrew in up stop/jamnut (A) (Figure
27-31-00
12-98
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MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
WHEEL
WHEEL_.
I
STEPPED
_
SMK27-12
1
1
GEAR Brlx
ASSEMBLY
........
_
JAM NUT-"_
_m-r--'_v_
II
II
I I
I I
ra-.i - I
\
!
'--GEAR lID×
_q-1
ASSEMBLY
S27CHAIN
STD. STOP NUTS -- STABILIZERTRIM CHAIN ADJUSTMENT
-FIGURE 27-12-- STEPPED STOP NUTS
torquetube.
D.Remove nuts,
washers,bolts/screws
fromupper
and
lowerpitch
tdm servobrackets
holding
brackets
to
bulkhead.
3. Carder bearing can now be inspected. If carder
bearing or torque tube sleeve show evidence of
scodng or wear, replace damaged items with new
parts.
Bendix-King
PIN's
are:- 047-04143-000
BEARING
BLOCK
ASSY.
TORQUE TUBESLEEVE-076-00971-000
ROLL PIN (for torque tube sleeve) - 090-00052-0022
When scodng orwear is not present, clean any dded
grease and/or dirt from beadng and torque tube sleeve,
Relubdcate, using MIL-G-23827 or MIL-G-81322
grease. Use a grease needle or other suitable tool to
apply grease,
4. Reinstall carder bearing to aft side of electdc pitch
tdm servo bracket. Re-tension ddve Chain.
5. Clean any dirt and grease from placard location on
forward side of tailcone bulkhead. Install annual
service placard (057-05747-0001) on forward, vertical
podion of bulkhead, @ fuselage Sta. 142.
6. If bearing block assembly replacement is
required, refer to following procedures:
E. Carefully lilt torque tube/pitch trim servo
assembly up and pull aft end of torque tube from tdm
actuator socket on aft tailcone bulkhead. Support aft
end of torque tube if needed.
F. Pull torque tube/trim servo assembly from
tailcone through access cover on left side of tailcone.
G. Place torque tube/pitch trim servo assembly on
work bench for removal and replacement of beadng
block.
H. Remove components carefully until access to
beadng block is obtained. Install new bearing block
and assemble in reverse sequence.
1. Reinstall torque tube/pitch trim servo assembly
into taUcone.
J. After reinstallation and reconnection of all
components, electrical and mechanical, it will be
essential to check stabilizer pitch trim system rigging in
accordance with Section 27-40-01.
27-50-00
WING FLAP SYSTEM
Trim torque tube/pitchtrim servo assembly should be
removed from aircraft to replace bearing block,
therefore manual tdm wheel and electdc trim switch
should be flagged so inadvertent movementwill not
occur,
Wing Flaps - General
Push-pulltubes and beUcranksinterconnectthe flaps.
The flaps are operated by an electdcal motor driven
actuator (1) connected to a jack shaft (2) (Figure
27-13). The jack shaft is connectedto actuatorbracket
(3) (Figure27-13) on each flap just outboardof hinges
(4) by a push-pullrod end beadng (5) and hardware.
Each flap pivotsaboutfour hinges.Travel is controlled
by limitswitches(6) and (7) and stopslocated at O.B.
hinges (Figure27-13). Flap position is indicatedin the
cockpitthrough a cable link system (B) connectedto
the jack sha_.actuator horn (9).
A. Disconnect universal joint located between
tailcone bulkhead, Sta. 142, and pitch trim servo
assemblymountingbrackets.
B. Disconnect electrical widng, to servo motor, at
connector,
C. Disconnect ELT harness from connector and
any other widng that may interfere with the removal of
torque tube assembly from tailcone.
27-50-00
12
m
12-98
SERVICE AND MAINTENANCE MANUAL
M20J
B. Rotate stop (A), (Figure 27-10) clockwise or
counterclockwise to make contact with trim screw nut
(F). Tighten setscrew. NOSE DOWN stabilizer trim
control rigging is now complete.
3. Stabilizer Trim Indicator Rigging. The indicator is
geared to the tdm control wheel and indicates stabilizer
position mlaUve to the aircralt thrust line. Set horizontal
stabilizerto an angle of incidence of minus 2 degrees O0
minutes to minus 2 degrees 30 minutes. Adjust tdm
indicator cable at (F) (Figure27-10) to set indicator in the
cabin to the center of thetakeoff range mank.
A. MAXIMUMHORIZONTALSTABILIZER
ALLOWABLE FREE PLAY LIMITS-
MOONEY AIRCRAFT CORPORATION
\\
\
(1) Fore and aft movement at stabilizer tip:
0_
(2) Vertical movement at stabilizer tip:
0_.
NOTE
When removing trim screw from empennage
use a block of wood cut to fit opening between
tailcone and empennage to prop empennage up
when trim screw is removed.
4. Electric Trim.
R
A. The clutch torque for the electdc trim system
should be checked and adjusted by an Avionics shop
SN27-11
for the following settings to operate the autopilot
systems properly:
STABILIZER TRIM CONTROL RIGGING-FIGURE 27-11
(1) KFC 200
-- 21 +/- 2 inch lbs.
(2) KAP 100
--21 +/-2 inch Ibs.
(3) KFC 150
--21 +/- 2 inch Ibs.
5. Stabilizer Trim Chain Adjustment.
(4) EDO AIRE Systems -- 18 inch Ibs.
(Reference Figure 27-12).
A. Wuththe four mounting bolts (1) slack, adjust the
(5) S-TEC
--30 inch Ibs.
two NAS428-3-4 bolts (2) to obtain maximum tension
on chainwithout causing binding.
27-40-01
- TRIM SYSTEM TROUBLESHOOTING
BINDING
CHECK controltubes at bulkhead
grommets for rub marks,
Check Tdm Actuator threads for galling or not
lubdcated; lube per Section 5.
ELECTRIC CLUTCH SLIPPING'
Check BINDING symptoms above.
Check for proper clutch settings.
Confirm full bus voltage is available at trim
motor.
27-42-00
-ELECTRIC PITCH TRIM SYSTEM
MAINTENANCE
1. Gain access to area by removing electrical bay
access cover from left hand side of tailcone Locate
Electdc Pitch Trim servo system,just a_ of Fuselage
If installed,the AIliedSignal (Bendix-King)ElectricPitch
Sta. 142 bulkhead. Carrier beadng is located around
TAm System requires pedodic maintenance at each
existing pitch trim torque tube, aft of lower chain
annual
inspectionfor
carrier
beadng
added
to
existing
sprocket,
on aft side of electricpitchtrim servo bracket
aimralt pitch trim torque tube. If not already installed,
an annual service placard, 057-05747-0001, (available
and below electricpitchtrim servo motor.
from AIliedSignal)MUST be added to the ElectdcPitch
2. Loosen electric pitch trim servo dave chain.
TAm servo bracket area to call attention to the annual
Remove four lock nuts which secure carder beadng
maintenance requirement. Carder bearing assembly
block to al_ side of electric pitch tAm servo bracket.
must be inspected and lubricated per the following
Slide bearing block aft until it is clear of stainlesssteel
procedures:
sleeve which is secured to existing airplane pitch trim
12-98
27-40-01
11
SERVICE AND MAINTENANCE MANUAL
M2OJ
MOONEY AIRCRAFT CORPORATION
POSITION ADJUSTMENT
SIN 24-0001 thru 24-2999.24-3079 thru 24-:_200,
A. Adjust right and left.inboard linkage at rod end
beadn.g(1), (Eigure 27-14) to obtaLna flaE deflection
of 33= (+g/-2"). Retract flaps to 0u +/- 2_. Set flap
outboardtravel stops (not illustrated)so that flaps align
withaileronwhilein neutral position.
24--3D00
_
2.=1---807B
_MJ2';'--I_
FLAP ACTUATOR ASSEMBLY & INSTALLATION
FIGURE 27-13
SNX27-14
On S/N 24-0001 thru 24-2999 the flap swtch (10) s
se f centering from the down position and located on
the console adjacent to the flap position indicator. The
flaps can be retracted completely by placing the switch
in the UP position or to any setting between 0 and 33
degrees by placing in UP position to setting desired
and then centeringto stopthe actuator,
On SIN 24-3000 thru 24-3078 and 24-3201 and
24-3218 thru 24-TBA, the flap system incorporates a
flap preselect feature which allows the flaps to be
positionedas desired: UP, TAKEOFF or DOWN.
Lubricatethe flap actuatorgear box and ball screw at
required
intervalsandwithlubricantsprescribed
inChapter5.
1. Wing Flap Removal and Installation.
A. Remove wing flap hinge faidng to expose flap
push-pulltube.
B. Remove bolt, nut, and washer from
flap-actuating attachment,
C. Remove bolts, nuts, and washers at flap hinge
points.
D. Remove flap by pulling it down and af_
E. Install wing flaps in reverse sequence of removal,
Recheck security and safety of attaching bolts.
2. Wing Flap Rigging and Adjustment.
' NOTE
Flap deflections areto be measured with travel
board GSE 030003 at the station indicated on
the travel board. (See SECTION 27-10-00,
Fig ure 27-3A)
WING FLAP ADJUSTMENT - FIGURE 27-14
B. Retract flapsto 15° (+/-1°), and set flap position
indicatorcable (B) at attachment screw (2), (Figure
27-15), to TAKEOFF positionas shownon flap position
indicatorin Cabin. This indicates the degree of flap
deflectionfrom 0° to 33°, with a 15° takeoffsetting
C. The limitswitches,#3, (Figure 27-15) shouldbe
adjustedso that under flightloadsthe actuatorover run
will not allow the flaps to exceed either up or down
positions.
NOTE
The flaps may be rigged asymetrically (within
tolerances) to facilitate aircraft rigging or to
compensate forany rolloff during flap
operation,
POSITION ADJUSTMENT
SIN 24-3000 thru 24-3078. 24-3201.
24-3218 thru 24-TBA
Before rigging take-off position, verify flap travel is
correct for full UP and DOWN.
Micro-Switches must strike tang on flap jack properly.
Lower switch roller should make contact in the cut-out
area; top switch roller should make contact with the
non-cut-out area. Adjust switches to accomplishthis.
A. Rig flaps per para. 2., A. & B. above.
B.Extendflapsto TAKEOFFposition(15° +/-1o)
C. Adjust switch stack until bottom Micro-Switch
just opens.
12-98
27-50-00
13
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
applicable) balance weight, control attachment horn
and attaching hardware, static wicks (when installed as
optional equipment), and rudder taillight and/or strobe
light assembly installed.
Control surfaces must be rebalanced in accordance
with the procedures in Section 27-93-00.
CAUTION
All control surfaces should be stripped prior to
repainting.
3
27-92-00
- BALANCING EQUIPMENT STATIC
The design of the balancing fixture is not odtical
2
1. Obtain or otherwise fabricate two (2) knife edge
supports approximately one (I) foot in height so that
.11
prevent tipping (see Fig. 27-15).
The knife edge
providingthe
requirements
of this be
sectionLEVEL
are met. and
nmge
supports
MUST
PERPENDICULAR to the hinge axis of the control
surface.
"_/_
.,_-
2. Weight Scales:
Scales
used
to recordon
weights
must
accurate
within
they Ibs
can
a table
andbebe
stabilized
to
0.02
orbe
1/2placed
oz.
s_7-_s _
WING FLAP INDICATOR ADJUSTMENT
(NON -PRESELECT) - FIGURE 27,15
D. Top switchwill be automaticallyadjusted.
E. Cycle flaps UP, TAKEOFF & DOWN; verify
propersetting at TAKEOFF while Flapsare goingdown.
27-60-00
- AILERON/RUDDER
INTERCONNECT SYSTEM
1. With controls in neutral position, locate
110002-101 bracket, on aileron controltube, so the
end of 110002-005 bellcrank assembly will be 2.25 in.
AFT of 310020 fuselage former.
2. Holding both, rudder and aileron,
controls in neutral position, install two
springs, PIN 110003-007, on -005
27-93-00
- BALANCING
PROCEDURE
27-93-01
- DETAIL PROCEDURES STATIC BALANCING
1. A line drawn throughthe hinge line support points
must be level and perpendicularto the supporting knife
edges.
2. The supportingknife edges must be horizontaland
parallelto each other within the requirements of Step
1. above.
3. Elevators and rudders are balanced with the
"Control Horn" pointing upward. Ailerons are balanced
UPSIDE DOWN. (See Fig. 27-18)
/ t" ---
brackets and position -025 and -027
brackets
control tube
the
bellcrank on
andrudder
on 110002-025
andso -027
KNIFEEDG
E/-----..........._
Clamp brackets in place and ddll through
brackets
and ofinto
tube
installed
length
eachcontrol
spring is
4.90 for
in.
AN530-4R6
PK screws.
SUPPDRT
27-90-00
J
"_
_'_
Ill
'"
J /
_" -..
>
./i
_" 7 f
Si7
-
- MISCELLANEOUS
27-91-00
- CONTROL SURFACE
STATIC BALANCING
Controlsurface balance must be checked
when control surfaces .is repaired, altered
or repainted. It is recommended that
secure
3. MakesurePKscrewsare
all
three brackets,
control
surfaces
be stripped npaceto
prior to
repainting. The control surface balance
limits shown in Figure 27-17 apply to a
complete painted control surface only.
Complete control surfaces include (as
27-60-00
14
i
CONTROL SURFACESTATIC BALANCE SUPPORTS
FIGURE27-15
12-98
SERVICE AND MAINTENANCE MANUAL
M20J
4. All control surfaces are balanced with the hinge
center line and the tip db chord line level. Two tooling
holes are located in the tip ribs and are on the rib chord
line (rib center line). Chordwise level can be obtained
by using a spidt level and pins inserted into these
tooling holes,
5. Install a 1/4 inch bolt or pin through the inboard
and outboard AILERON hinge bracket. Install a No. 10
bolt or pin through inboard and outboard ELEVATOR
hinge bearing, and top and bottom RUDDER hinge
bearing.
6. Positon and level the control surface on the knife
edge hinge supports.
MOONEY AIRCRAFT CORPORATION
7. Accurately measure control surface load at a
measured distance from the hinge axis as far from the
hinge axis as possible (Figure 27-18). Measuremen_
should be taken in a draft free environment. Calculate
the moment (arm times weight) and compare the
results with Figure 27-17.
8. Control surfaces MUST BE RECHECKED for
balance after any painting, stripping, repair or
alteration.
SURFACE DESCRIPTION
AIRCRAFT EFFECTIVITY
BALANCE MOMENT LIMITS *
!430026-001 &-002
ELEVATOR
24-0001THRU24-1543
24-1545 THRU 24-1551
24-3000 THRU 24-3038
UNDERBALANCE 16.751N.#TO
14.00 IN, #
24-1544, 24-1552 THRU 24-2999,
24-3039 THRU 24-TBA
UNDERBALANCE 16.75 IN. # TO
11.00 IN. #
24-0001THRU24-1543,
24-1545 THRU 24-1551
24-3000 THRU 24-3038
UNDERBALANCE 18.001N.#TO
13.00 IN. #
24-1544, 24-1552 THRU 24-2999
124-3039THRU 24-3200
24-3202 THRU 24-3217
UNDERBALANCE 18.00 IN. # TO
12.50 IN. #
24-3201,24-3218 THRU 24-TBA
UNDERSALANCE 15.50 IN. # TO
12.50 IN. #
430043-000
RUDDER
NOTE: NC SIN 24-1688 THRU UNDERBALANCE 15.501N. #TO
24-3200, 24-3202 THRU 24-3217
12.50 IN.#
MAY BE IN COMPLIANCE WITH
KIT DWG 940071 (2900 LB, GROSS
WT.) IF SO, USE UNDERBALANCE
MOMENT LISTED IN COLUMN TO
THE RIGHT.
230015-503 & -504
AILERON
230015-505 & -506
AILERON
230015-507 & -508
AILERON
230015-511 & -512
AILERON
24-0001 THRU 24-0942
UNDERBALANCE 8.00 IN. # TO
5.25 IN. #
24-0943 THRU 24-1037
UNDERBALANCE 7.23 IN. # TO
5.25 IN. #
24-1038 THRU 24-1543
24-1545 THRU 24-1551
UNDERBALANCE
7.10 IN#TO
5.25 IN #
24-1544, 24-1552 THRU 24-1621
24-3000 THRU 24-3038
UNDERBALANCE
6.23 IN. #TO
0.00 IN#
24-1622 THRU 24-2999
24-3039 THRU 24-3110
UNDERBALANCE
6.23 IN. # TO
0.00 IN. #
24-3111 TO 24-TBD
UNDERBALANCE
5.30 iN. # TO
0.00 IN. #
24-TBD TO 24-TBA
UNDERBALANCE
5.30 IN. # TO
0.00 IN #
• UNDERBALANCE = TRAILING EDGE HEAVY
M20J FLIGHT CONTROL SURFACE BALANCE LIMITS - FIGURE 27-17
12-98
27-93-01
15
MOONEY AIRCRAFT CORPORATION
=
M20J
DISTANCE
(Refer
to
Figure
AFT
27-17
for
(NOTE: Aileron
is
SERVICE AND MAINTENANCE MANUAL
OF HINGE
LINE
dimensions
limits)
balanced
&
upside
-
UNBALANCE
down.)
FORCE
FIGURE 27-18 - DISTANCE FROM HINGE POINT TO UNBALANCE POINT
NOTE
If specified moments cannot be met (reference Figure 27-17), heavier balance weights can be
obtained through a Mooney Service Center. This approach should be examined before reworking
any repair or restripping and repainUng the affected control surface. A lighter weight can be
produced by shaving existing balance weighL
FIGURE 27-19 NOT USED.
NOTE
The aileron trailing edge MUST NOT BE BENT
UP under any circumstance. Any deformed
rivets must be replaced after trimming aileron
or rudder trailing edge.
B. Rudder. The rudder trailing edge may be
trimmed right Orlelt as required.
27-94-00
- CONTROL SURFACE TRAILING
EDGE
NOTE
Verify flight control rigging is correct before
bending trailing edge.
1. Trimming. A pair of widenose (2.0 - 3.0 in.)
ViceGripstyle pliers may to used to bend the trailing
edges as necessary (See Figure 27-20).
NOTE
Glue 1116in. thick rubber strips to inside of
jaws of ViceGrip pliers to reduce possibility of
damage to trailing edges.
27-95-00
-STALLWARNINGMAINTENANCE PRACTICES
A. Aileron. To correct for a left wing-heavy
condition, bend right aileron trailing edge down; to
correct for a right wing-heavy condition, bend left
ailerontrailing edge down.
wing leadingedge.
C. Disconnecttwowires from the switch.
1. Stall WarningSwitch Removal.
A. Remove screws or rivets attachingthe access
coveraft of stallswitchon lower wing surface.
B. Remove two screws which secure switch to
ADJUSTUP TO ACTUATESOONER
X
"08FFLMEAc_,
oANL
L_EWAFTB
LE
R"'°',
RUDDER. /
q-
D DO
STALL VANE ADJUSTMENT - FIGURE 27-21A
TRAILING EDGE TRIMMING - FIGURE 27-20
27-94-00
16
CT
SIN 24-0001 THRU 24-3153
12-98
SERVICE AND MAINTENANCE MANUAL
M2OJ
2. StallWarning SwitchInstallation.
A. Connect electricalwires to switch connections,
B.Positionswitch in opening on lower wing leading
edge, install two attach screws.
C. Replace the access cover securely.
D. Adjust the switch. See STALL WARNING
SWITCH ADJUSTMENT (Para. 3 or 4 below),
The stallwarning switch is adjustedwhen the airplane
is test flown at the factory. Should it require
readjusting, proceed asfollows (Para. 3 or4):
3. Stall Warning Switch (Vane) Adjustment
SIN 24-0001 thru 24-3153 (Figure 27-21A)
Locatethe stall switch on the lower surfaceof the left
wing leading edge and loosen the two phillips head
screws, one on either side of the vane (See Fig.
27-21A). If the stall warning has been activating too
early, pull the vane back and down. if the stall warning
has been activating too late, push the vane up and
ADJUST
UP TOACTUATE
SOONER
ADJUST
[:)OWN
TO ACTUATE
SCREWS
STALL VANE ADJUSTMENT - FIGURE 27-21B
SIN 24-3154 THRU 24-TBA
27-95-01
MOONEY AIRCRAFT CORPORATION
forward. Moving the vane with the phillips head screws
loosened moves the entire unit up or down inside the
wing, causing the switchto be closed earlier or later.
Retighten the screws JEer making each adjustment.
NOTE
NEVER TRY TO ADJUST THE SWITCH BY
BENDING THEVANE. This part has been heat
treated and cannot be bent without damaging
or breaking the vane or switch.
¢.StaltWaming Switch (Vane)Adjustment
SIN 24-3154 thru 24-TBA (Figure 27-21B)
Locate the stall switch on the lower surface of the left
wing leading edge and loosen the two screws on both
sides of the wing leading edge cutout (See Fig.
27-2tB). If the stall warning has been activating too
early, pull the vane back and down. If the stall warning
has been activating too late push the vane up and
forward. Moving the vane with the ph ps head screws
loosened moves the entire unit up or down inside the
wing causing the switah to be closed eadier or later.
Retighten the screws after mak ng each adjustment.
GENERAL
As a role of thumb, moving the vane tip 1/4 inch will
change the time the stall warning acurates by about 5
MPH of indicated air speed. The only way to test the
accuracyo1the settingis to fly the airplane into a stall,
noting the speed at whichthe warning horncomes ON
and the speed at which the FULL stalloccurs.The stall
must be made in various configurations,clean, gear
and flaps down and power on and power off. It may be
necessary to make several alternate adjustmentsand
test flights before the desired setting can be reached.
The stall warningshouldactuateat no lessthan 5 KTS.
nor more than 10 KTS. preceding the stall and shall
continue until the stall occurs in power off
configuration.The rate of speed reduction shall not
exceed one knot per second with the airplane tdmmed
to 1.5 times the stall speed. The switchsetting should
be checked and adjusted as necessary whenever a
wing or wing leading edge is replaced or extensively
repaired, or if a new switch is installed. The switch
should require no adjustment in normal service.
- TROUBLE SHOOTING - STALL WARNING SYSTEM
i
TROUBLE
Warning system inoperative.
Horn continues to blow.
PROBABLE CAUSE
REMEDY
Warning circuit breaker tripped.
If circuit breaker persist in tripping,
check for grounded circuit.
Open circuit.
Check for continuity.
Defective warning horn switch.
Replace switch.
Defective warning horn.
Replace horn.
Defective warning hom switch.
Replace switch.
12-98
27-95-01
17
MOONEY AIRCRAFT CORPORATION
M20J
27.96-00
- SPEED BRAKE SYSTEM
A Speed Brake System Is currentlyoptionalequipment
installed on some M20J aircraft. The manufacturer,
Precise Flight, Inc. can provide detail parts and
maintenanceinformationfor the cartridge assemblies.
Some of the electdcal cimuitry, widng, relays, cimuit
breakers, etc. are installed by Mooney pmduction
drawings.Componentsfor these are available through
yourMooney ServiceCenter.
The relay for the electric Speed Brake System is
locatedunder the rear seat area, on the LH bulkhead,
The schematic, located in the envelope, and the
electricalpads list, SECTION 91, of this S & M covers
the electricalsystemcomponentidentification,
27.96-01
- MAINTENANCE - SPEED BRAKE
SYSTEM
1. ELECTRIC OR VACUUM SYSTEMS
@ Every1000 hours:
A. Remove the speedbrakecartridgesfromwing:
(1) Remove access cover from bottom of wing
beneaththe Speed Brake cadddge,
(2) Remove the single screwfrom bottom of wing
whichsecures the strapstrip of the cartridge,
(3) Disconnect vacuum or electrical connection
fromSpeedbrake cartridge,
(.4)Remove Speedbrake cartridge from wing by
remo_nngscrews from top of wing from around the
Speedbrake carlridge and remove the cartridge
throughthe bottom access hole.
B. Inspect removed cart_lge, mounting area and
relatedcomponents for the following:
(1) Visually check doubler and mounting
hardwarefor structuralintegrity.
(2) Visually inspect for chafing on all moving
parts,
(3) Manually operate the speedbrake doors and
feel fur smooth operation,
(4) Inspect cable (on vacuum units) especially
aroundpulleysfur fraying.
C. Report any deficienciesof cartridge (if any) to
PreciseFlight, Inc.
D. Repair any defects found. If no deficienciesof
the cartridges exist, reinstall spoedbrake cadddges
and connections. Cycle to verifyproperoperation,
2.
REPLACEMENT
OF
MALFUNCTIONING
CARTRIDGES.
A. When replacement of a malfunctioning
Speedbrake Cadridge with a new cadddge is
necessary, the following proceduresmay be required
to installthe new cartridge:
NOTE
There is no left or right hand configuration on
the electrical units. The speedbrake doors are
not located in the center oftbe cartridge. The
side of the cartridge that has the narrowest
flange goes forward.
27-96-00
18
SERVICE AND MAINTENANCE MANUAL
Therefore, the motor/gear assembly will be
outboard on the left hand wing side and
inboard on the right hand wing side.
(1)Onsome mplacamentcartddgesadrain hole,
(0.27 in.) is required in the aft, inboard comer of
Speedbrake cartridge bottom.The drain tube from the
old cadddge Is to be securedin place in this hole with
siliconeadhesiveused as sealant.
On laterconfigurationcadddges, the drain hole already
existsin the bottomof each end of the cartridge.Install
drain tube in inboard hole. Some drain tubes have a
heat formed flange and mountingplates to mountthe
tube to the hole which already exists in the new
cartridge.These do not requireany siliconesealant to
seal the tube, however,the drainholes in the outboard
end of the cartddge must be sealed with silicone
sealant pdorto installationof cartridgeintowing.
Route drain tube through hole in bottom of access
cover.
(2) The bottom,mountingstrap stripfrom the old
cartridgewill require relocatingto the new cartridge.
Alter the cartridge is secured in place with the top
screws, position the strap strip over the single
mounting hole in the wing bottom skin. Mark the
locationfur the two holes in the bottom of the cartridge
housing. Ddll proper hole (#30 ddll) to install
ChenyMax CR3243-4-2 dvets (2 ca.) to attach strap
stripto cartridgebottom housing.
(3) Door caps may need to be installedon some
replacement cadddge doors in accordance with the
following:
a. Mark dvet locationson flange legs of all cap
strips to be installed.One is located 2.0 inches from
the angled end of cap stdp and another is located 5.0
inchesfromthe angledend.
CAUTION
Be certain of which cap strip goes on which
door and that the angled end of cap strip
matches up with angled edge of each door.
(Reference existing cartridge to determine
which cap strip is to be installed on a new
cartridge door.)
b. Place correct door cap stdps on speedbrake
doors (while speedbrakes are retracted into cartridge)
untilflush with top of wing skin surface. Line angled
end of cap strip up with angled end of speedbrake
door.
c. Cycle spoedbrake doors to verify sufficient
clearance exists (0.0625 in.) between cap strip and
wing skinand doublers.
d. Extend doors to continue with cap strip
installation.
e. Drill #40 holes in cap strips and door at the
locationsmarked
in (3) a.
Countersinkholes
on both
sides of cap stdps.
Flush
dvet in place
with
AN426A-3-7 rivets.
3. FINAL OPERATIONAL CHECK AND CLOSE-UP
A. After vedfication of proper operation, reinstall
accesscover plate on each wing.
12-98
MOONEY AIRCRAFT CORPORATION
M20J
CHAPTER 28
FUEL
SERVICE AND MAINTENANCE MANUAL
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 28
FUEL
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
28-Effectivity .........
28-Contents
.........
28-00-00 ............
28-10-00 ............
28-11-00 ............
28-12-00 ............
28-13-00 ............
28-20-00
...........
28-30-00
...........
28--42-00 ...........
28-91-00
...........
28-92-00
...........
PAGE
..........
DATE
1/2BLANK ..........
3/4BLANK ..........
5 ...........
6 ...........
7 ...........
8 ...........
9 ...........
10 ...........
11 ...........
12 ...........
13 ...........
14 ...........
12-98
12-98
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12-98
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12-98
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12-98
12-98
12-98
12-98
28-EFFECTIVITY
1/2BLANK
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 28
FUEL
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
28-00-00 ........
28-00-01 .........
28-10-00 .........
28-11-00
..........
28-12-00
..........
28-13-00
..........
28-14-00
..........
28-20-00 .........
28-21-00
..........
28-22-00
..........
28-23-00 ..........
28-24-00
..........
28-25-00
..........
28-30-00 .........
28-31-00
..........
28-32-00
..........
28-40-00 .........
28-41-00
..........
28-42-00
..........
28-43-00
..........
28-43-01 ............
28-43-02 ............
28-90-00 .........
28-91-00
..........
28-92-00
..........
SUBJECT
........
General ..............
Filler Cap Maintenance .........
Storage .............
Fuel Tank Field Repair ........
Fuel Tank Leak Repair ........
Soapless Bubble Fluid Formula Preparation
for Leak Check .........
Fuel Additives ..........
Distribution ............
Fuel Boost Pump Removal and Installation .
Selector Valve & Gascolator Screen Cleaning
Fuel Injection System ........
Engine Priming
.........
Full Selector Valve Removal and Installation.
Dump .............
Fuel System Drains ........
Fuel Vents ...........
Indicating ............
Fuel Quantity Indicating Transmitters
Fuel Quantity Indicator .......
Fuel Quantity Adjustment Procedure.
Fuel Tank Transmitter Adjustment .
Fuel Quantity Gauge Adjustment
Miscellaneous ...........
Trouble Shooting .........
Flared Fittings..........
12-98
PAGE
5
5
6
6
8
9
9
10
10
10
10
10
10
11
11
11
11
11
11
11
11
12
12
12
13
28-CONTENTS
3/4BLANK
SERVICE AND MAINTENANCE MANUAL
M20J
28-00-00
-GENERAL
Internally sealed, integralfuel tanks are in the forward
inboardsections of the wings. Fuel feeds from either
tank to a selector valve thin a gascolator,(integralwith
selectorvalve, 24-0001 thru 24-0377), with a low-point
drain, through the emergency pump to the
engine-drivenfuel pumpand to the fue/injestor system
on the engine. Fuel quantity indicatorsare electrically
operated with 2 transmitters located in each tank (1
inboard& 1 outboard). Fuel level indicatortabs, at the
25-.gallonlevel, in each tank, can be seen through the
(1
w_
FUEL SYSTEM - FIGURE 28-1
Optional visual fuel quantity gauges are located in
each wing tank end are to be used only for padial fuel
MOONEY AIRCRAFT CORPORATION
to prevent bindingwhile opening or closingthe cap
assembly.This should also lubdcatethe o'dng (4) that
seatsthisshaft..
WARNING
Water can enter the fuel tank through a loose
fitting or damaged cap. This should be
corrected as soon as possible.
3. The seating capabil_ of each cap assembly
should be checked pedodicallyand at each annual
inspection.
This can be accomplished per the following
procedures:
A. Remove cap assemblyfrom wing filler pod and
inspect o'ring (1) for. any damage or brittleness
Removeand replaceif needed.
B.Adjusttension of shaft (2) and rotatinglockplate
(3) by removingcotter pin (5) from nut (6) on threaded
portionof shaft (2). T'q]htennut (6) so cap assembly
handle(7) can be opened, fumed and shutwith hand
pressure and still providethe necessary seal of cap
assemblyto keep water from entedngfeel tank.
NOTE
Fuel selector should be in the OFF position
before proceeding with paragraph C. to
pressurize the fuel tanks.
C. Connect rubber hose to each tank's vent line.
Apptyonly one-half pound (1/2 lb.} air pressure.Check
for _el cap leaksby soapingcircumferenceof fillercap
assemblyand observingbubbles.Replace o'dng if
bubbtesare
observed
_
and
t
7
adjustment _
_
v
ofthe nut /
U
does not
I
J
stopthe
I
A J
7 ¶
#108 sealant.
loadingas desired. The dial is held in positionby RTV
leak.
,_ J,__---__
_
_'_ _'_
weather fading or other damage. After documenting
dial orientation on wing, pry dial from cavity. Clean
cavityand secure correct, new dial into properposition
with RTV #108. The float assemblywhich activates the
magnetic
portion of the dial needle as fuel level
Occesionatiythediaimayrequirechangingdueto
_i_!__
changes in the tank, can be replaced by removing the
access cover that the float assembly is attached to on
pressure
top side of wing and replace the floatassembly,
in tank.
28-00-0t
- FUEL FILLER CAP ASSEMBLY
MAINTENANCE
Fuel filler port cap assembfies should be checked
periodicallyfor proper sealing and should be serviced
occasionally to prevent bard to open or close
conditions.
1. The o'dng seal (1) (Figure 28-2) around the cap
assembly should be kept clean and free of did or grit
that might cause abrasive action on seal or mating
flange. Occasional lubdcationwith petroleumjelly or
2
Td-Flow will keep the o'ringsoit and pliable.
2. The shaft (2) runningthroughthe center of the cap
FUEL FILLER CAP ASSEMBLY
housing,that actuates the rotatinglockplate (3) should
MAINTENANCE - FIGURE 28-2
be lubricatedoccasionallywith Tri-Flow, or equivalent,
12-98
28-00-00
5
=r
;
MOONEY AIRCRAFT CORPORATION
28-10-00
28-11-00
M20J
-STORAGE
- FUEL TANK FIELD REPAIR
C. Metal cleaningsolvent- Turco 657 wipe solvent.
D. Cheese cloth.
This paragraph outlines the procedures recommended
for repair of the integral fuel tanks. Tank repairs should
not be attempted until these instructions are fully
understood. Refer to Service Bulletin M20-230 dudng
resealing of the tanks for drain holes to be lett open.
1. Approved Materials.
A. Sealants.
WARNING
Sealants are safe only when handled with
reasonable care. Avoid ingestion and all
contact with the body, especially with open
breaks in the skin. Wash hands before eating or
smoking. If accelerator contacts the skin, flush
area with warm water,
(1) Brush sealant - PR1422-A-1/2 or A-2 or
CS3204 A-1/2, A-2 (MIL-S-8802D Class A).
(2) Filleting Compound - PR1422 B-1/2, B-2 or
CS3204 B-112,B-2 (MIL-S-8802D Class B).
(3) Removable
PR1403-G-B2,
PR1428 oraccess
CS3330. panel
sealant
(4) Protectivesealant - PR1005-L (MIL-S-4383B).
B. Gloves-- Polyethylene.
a) - BrushableType Sealant
........
CLASS A ....
PR1422 A-1/2
....
PR1422 A-2 . .
.
CS3204 A-1/2
....
CS3204 A-2 .
PRO-SEAL 890-Al/2.
PRO-SEAL 890-A2
SERVICE AND MAINTENANCE MANUAL
E. Turco leak detector or bubblefluid.
F. Methylethyl keytone0VIEK)(thinnerfor PR 1005-L).
NOTE
Approved materials may be obtained from your
local Mooney
Marketing
or Service
Center.
Sealants
may also
be obtained
from Products
Research Co., 5454 San Fernando Road,
Glendale, CA 91209; or Chem Seal Corp., 11120
Sherman Way, Sun Valley, CA 91352.
2. Handlingand MixingSealants.
A. Sealant Matedal Characteristics.
(1) Application life is the time that the mixed
compoundremainssuitable for application.Application
life ratingsare always based on standard conditionsof
75 degrees F. and 50 percent relative humidity. For
every10 degree F. rise in temperature, applicationlife
and cure time is reduced by half; for every 10 degree
F. drop in temperature,applicationlife and cure time is
doubled. High humidityat the time of mixing slightly
reducesthe sealant applicationlife.
(2) Maximum unopened container life, with
sealant at 80 degree F., is six months.
(3) Sealant application life, tack-free curing time,
and curingrates are as follows:
Tack-Free Time ....
(HOURS) ......
10
.......
36
.......
8 ........
24
.......
10
.......
36
.......
Cure Rate
(HOURS) ......
30
.......
72
.......
30
.......
72
.......
30
....
72
.......
ApplicationLife
(HOURS)
1/2
2
1/2
2
1/2
2
(b) FilletingCompound(and on wingwalk access panel)
.......
Tack-Free Time ....
Cure Rate
CLASS B ....
(HOURS) ......
(HOURS) ......
PR1422 B-1/2
....
10
.......
45
.......
PR1422 B-2 .....
36
.......
72
.......
CS3204 B-1/2
....
8 ........
30
.......
CS3204 B-2 .....
24
.......
72
.......
CS3204 S-4 .....
36
.......
76
.......
Followproceduresaccompaningsealantto propedy seal fuel tanks.
ApplicationLife
(HOURS)
1/2
2
112
2
4
(c) Access Door Sealant (excepton wingwalk access panel)
........
Tack-Free Time ....
CLASS B ....
(HOURS) ......
CS-3330-B .....
8 ........
PR1403-G-B2
....
10
.......
PR1428-B
.....
8 ........
Cure Rate
(HOURS) ......
16
.......
48
.......
16
.......
ApplicationLife
(HOURS)
2
2
2
(d) Brushable Top Coat Protective Sealant
........
Tack-Free Time ....
........
(HOURS) ......
PR1005L ......
1/3 .......
CS3600 ......
-.......
Cure Rate
(HOURS) ......
4 ........
-.......
ApplicationLife
(HOURS)
-__
Allow 24 hours cure time prior to refueling tanks.
28-10-00
6
12-98
/
SERVICE AND MAINTENANCE MANUAL
.
M20J
B. Sealant Mixing
(1) For best results, use kits with proper
propodions ofbase compound and accelerator,
(2) To avoid excessive air entrapment, slowly stir
accelerator into base compound. Continue mixing for
SEVEN to TEN MINUTES. Scrape sides and bottom of
container to include all compound in mixture and to
insure uniform blending. Scrape mixing
paddle on edge of container to remove
unmixed compound. Be sure to use all of
the accelerator.
MOONEY AIRCRAFT CORPORATION
(1) Use a spatula or an extrusion gun with a 1/8 to l/4 - inch nozzle opening for laying fillets at edges of
all seams. When using an extrusion gun, hold gun
perpendicular to seam so that extruded sealant will
pack tightly.
(2) Use a spatula to pack sealant firmly in place
while working out air pockets. Shape each fillet evenly.
(3) Place a small amount of mixture
on a clean stdp of aluminumand spread
3/e
determine whether accelerator is visible in
particleform. If particlesof acceleratorare
visible, continuemixing operation.If course
particlesof accelerator persistafter mixing
thomughiy, rejectthe mixed batch.
NOTE
Sealant in tube form have mixing
instructions on each tube. Read and
comply with these mixing
instructions prior to sealant
3. Cleaning Surfaces
to be Sealed.
application.
!
SEAL
_/ITH
3/8
TO
1/2
IN, LI_
GAPS
8, HnLES
FILLETING
3/16
A. Clean metal surfacesto be sealed
with Turco 657 Wipe Solvent or Methyl
Ethyl Ketone. Wipe surface dry with a
clean cloth:Do not allow solvent to
evaporate.
B. Allow cleaned surface to dry five
to
ten
minutes
before
sealant
application.
1/,$
_I
TO i_Lr
IN.
prk
2: IN.
APPLY ]BRUSH
SEALANT
COMPOUND
FIRST STEP
3/t6
Tn 1/_ IN,
I-'1
THIRD STEP
TD 1/4 IN.
"1 P"
FILLET
'_k
APPLY
FILLETING
COMPOUND
rL _FILLET
SECONDSTEP
1 IN.
"1 P"
1/ 1w6
__
- IN.
I I '"_J_r*ir
"-_IIP PROTECTIVE
APPLY
SEALANT
FOURTH STEP
FASTENER
SEALING
WITH ]BRUSH SEALANT
(1132 Tn 1116 IN, THICK)
NOTE
Apply sealant as soon as possible
after cleaning. Store and handle
parts in a manner that will prevent
finger prints, dust, dirt, or other
foreign substances
from to be sealed.
accumulating
on surfaces
SHH2EI-3
FUEL TANK SEALING - FIGURE 28-3
NOTE
Refer to Mooney SB M20-230 for proper
application and drain holes to be left open.
4. Sealant Application. Old sealant must be removed,
Use a sharp non-metallic scraper (formica or lexan),
When sealant has been removed, clean area
thoroughlyand resealtank as foUows:
A. FilletSealing.
(1) Be certain that the surface to be sealed is
totallyclean and free from oil,grime, finger prints,etc.
(2) Referto (Figure 28-3) for typicalfilletsize.
(3) Join fillets laid on intersection joints to
produce a continuousfillet,
•
(4) Seal all difficult and hard-to-reach areas first
to preclude the possibility of their being overlooked or
improperly sealed.
C. Brush Sealing.
(1) Brushsealant (PR1422-A-1/2, A-2 or CS3204
A-1/2, A-(2) over all seams, rivets, nuts, and bolts.A
one inch stiffbdstie brush is recommended for sealant
application. Force sealant into all gaps with brush
strokes parallelto seams. Use a circular brushaction
to deposit an even coating of sealant around dvets,
nuts, and bolts. Coating should be approximately
1/32-inchthick. Use considerablebrushactionto force
sealant into all small crevices and to obtain good
adhesion. Air pocketsunder the sealant,that will open
up in the form of holes or voids soon after application,
will resultfrom improperapplication.To repair holesor
voids,presssealant in place usinga spatula.
(2) When the edge of a flange protrudes0.040
inch or less, or where the seam cannot be cleady
defined, applytwo 1/32-inchbrush coats.Allowthe first
coat to cure about four hours or until it becomes
rubbery before applying the second coat. The second
coat should overlap the edges of the first coat by about
1/4 inch.
B. Filleting Compound Application - (PR1422 B-2)
12-98
28-11-00
7
MOONEY AIRCRAFT CORPORATION
M2OJ
SERVICE AND MAINTENANCE MANUAL
£/_
D. Protective Sealant.
(1) Using short, even strokes, brush on a smooth
and continuouscoat of PR1005-L over sealant. The
protectivesealant coat shouldextend one inch beyond
edge of the filletingcompound.
(2) Allow the first protective coat to cure 20
minutesat 75 degree F., or untiltack-free; then apply a
second brush coat of PR1005-L. Make every effort to
obtain a completelybubble-free, continuoustop coaL
DO NOT REBRUSH over areas, as doing so will only
3-1/2 TD 4 IN,
cause dragging and will break coating continuity.
E. Upper Wing Tank Access Panel Sealing.
(1) Apply a coat of access door sealant (CS3330,
PR1428 or PR1403-G-B2) to either laying surface
_
HEAVYSEEP
using
short
stiff bristle
brush,
gun. Ifa an
extrusion
gun is
used,spatula,
smoothor
theextrusion
sealant
with a brush or spatula. Cover the entire faying surface
with a sealant coat of sufficientthickness (1/32 to 1116
inch)to assure extrusion alongthe edges of the laying
surface when the mating parts are assembled. Access
panels in wing walk area should be sealed with
PR1422, Class [] filleting compound.
(2) Assemble parts immediately after application
of sealant and tighten screws to obtain as near as
possible a metal-to-metal contacL
(3) Remove the extruded sealant from the wing
surface after installing the fasteners.
28-12-00
1-1/2 IN.
-_-
".-:-.--' ..'-':. ..--'...-:---.
-_._.I.:-_-_.'._Q.:...:._.I.I-_{.I
'._'i-:_:'.(_.._
.....................
_SEEP
U
STAIN
, ,,, u^v
i. 4 TD 5 IN.
° "_' '_^
l-
_..?_{.-.-.;j,"
' """ "
''-_u__
lU
3/4 IN,
"" "_'_"':"• ''_ '-'_.....
_uM==__
FUEL LEAK CLASSIFICATION - FIGURE 28-4
- FUEL TANK LEAK REPAIR
1. Leak Description. It is necessary to periodically
inspect the fuel tanks. Inspection is particularly
importantin confined areas of the aircraft that are not
exposed to the airstream. Identification and
classification of fuel leaks that occur in both confined
and
necessary
differentiate
between
thoseopen
leaksareas
that is
require
repairtobefore
flight and
those
which do not constitute a flight hazard. The size of the
wetted area around a leak is an indication of the leak
intensity. All fuel leaks must be recorded by descdbing
the location and intensity of the leak in the aircraft log
book.
2. Classification of leaks as to Intensity and Location.
(Referto Figure 28-4).
A. Intensity Classification.
(1) Stain--A slow fuel leak that tends to
evaporate as soon as it is exposed to air.
(2) Seep--A fuel leak that reappears shortly after
area is wiped clean.
(3) Heavy Seep---A fuel leak that reappears
immediately after area is wiped clean,
(4) Running Leak--A fuel leak that flows steadily,
B. Location Classification.
(2) A running leak and any leak in a confined
area that is not exposed to the airstream should be
repaired beforethe next flight.
3. Leak Detection.
A. External Leak Detection After Refueling. To be
able to trace a leak from where it appears on an outer
tank
wingwhere
skin tofuel
its true
source inside
the tank,
exactorpoint
is escaping
from tank,
must the
be
determined.
(1) Use compressed air to blow and evaporate
fuel from seams and crevices of leak area. Attempt to
define exact point where fuel is escaping from tank.
(2) Small seep leaks can be traced with raw
edges of tom paper. The fuzzy edge absorbs fluid and
gives a good visual indication of fuel presence when
brought in contact with suspected leak points.
(3) After tracing leak to its extedor source, mark
location and drain fuel tank.
B. Internal Leak Detection. To make a permanent
repair, it is mandatory that the true source of the
intedor leak be located. The fuel tank is a network of
seams, and fuel may flow through or along a seam or
from one seam to another. Fuet may channel a few
inches or several feet to where it appears on external
skin surface.
Slow-to-heavy
occuring
open areas,
(1) Enter tank through inspection access panels
such (1)
as wing
surfaces, seeps
exposed
to the in
airstream,
are
leaks which do not constitute a flight hazard and need
and inspect sealant in general area of outside leak
not be repaired prior to flight, providing the condition
point. Look first for bare seams, dvets, and bolts in
causing the leak cannot result in a leak of greater
difficult-to-seal areas. Inspect sealant for blisters, pin
intensity during flight. Seeps considered permissible for
holes, cracks, splits, and loss of adhesion. Mark all
flight must be frequently inspected to insure that no
suspected flaws with masking tape.
increase in intensity has occured.
28-12-00
12-98
8
f
SERVICE AND MAINTENANCE MANUAL
M2OJ
(2) Test each suspected flaw from inside tank
using compressed filtered air at 20 to 30 PSI. Hold air
nozzle against flaw and closely check outside leak
point for evidence of fuel.
(3) After testing each suspected flaw from inside
tank as outlined above, and if no leak source can be
discovered, apply soapless bubblefluid to exterior and
againapplyair pressureto flawsfrom insidetank.
(4) If above tests fait to locate leak source, apply
air pressure (10 PSI MAX) to external leakpoint after
removing all traces of fuel from tank and applying
soapless bubble fluid to tank interior seams per
Section28-13-00.
4. Leak Repair.
A. Temporary Repair of Fastener Leaks. Generally,
allleaks in enclosed areas and runningleaks in open
areas constitutea flight hazard. Fastener leaks of this
category may be temporarily repaired by applying a
sealant fillet over fastener head on fuel tank extedor.
For a temporary repair to be satisfactory, structural
integrity must be retained in leak area. To make a
temporaryfastener-leak repair:
(1) Remove enough fuel from tank to drop fuel
levelbelow leaking fasteners,
MOONEY AIRCRAFT CORPORATION
(5) Apply sealant as required for repair (See
Figure 28-3). Repaired fillets must be blended into
existing fillets with a spatula or an appropriate tool.
(6) Allow all repaired sealant to cure tack-free
and apply two brush coats of PR1005-L to repair area
(Refer to paragraph 28-11-00,4.D.).
28-13-00
-SOAPLESS BUBBLE FLUID
FORMULA PREPARATION FOR LEAK
CHECK
1. Materials.
A. Three ounces of either sodium bichromate,
potassiumchromate,or potassiumdichromate.
B. Three and one-quarterouncesThickeningWax
(Carbo Wax 1500).
C. Thirteen ouncesAlkaryl Sufonatewettingagent.
D. Distilledwater.
2. SolutionPreparation.
A. Mix one of the compounds listed in item (A)
above withone cup distilledwater.
B. Mix item (B) abovewith one cup distilledwater.
C. Mix item (C) abovewith fourto four and one half
gallons distilled water until wetting agent dissolves
(2) Clean fastener head and adjacent surrace
with Turco 657 Wipe Solvent or MEK and dry
thoroughly.Fastener head and adjacent metal must be
entirelyfree from paint, dirt, and oil.
completely.
D. Mix the three ingredients (A), (B) and (C)
together and add enough distilledwater to make five
gallons of solution.
(3) Apply a 1/8 inch thick coat of PR1422 (or
CS3204) B-1/2 or B-2 over head and around fastener.
NOTE
Amount of each ingredient may he reduced for
a smaller quantity of solution. Solution life is
about one week.
(4) Allow sealant to cure until firm and rubbery,
(5) Refill tank and examine repair periodically. If
leak recurs, sealant must be removed and area
recleaned prior to making another temporary repair.
B. Permanent Leak repair. If leak source is found
to be around a rivet or threaded fastener the repair
procedureshall be to restdke rivet or retorquefastener
to maximum permittedtorque value. ANY ONE RIVET
MAY BE RESTRUCK ONLY ONE TIME. If leak
continues,replacethe rivet,
(1) Repair any sealant damage due _.orestdking
or retorqueinga fastener,
(2) Remove sealant in immediate area of leak
source using a sharp, non-metallic tool. A
chisel-shaped formica tool is recommended. Scarf or
taper ends of existing sealant so that new sealant can
form a continuous and smooth overlap.
(3) Thoroughly clean repair area using Turco 657
Wipe Solvent or MEK. Wash one small area at a time.
To prevent redeposit of oil and dirt on surface, dry with
a clean cloth before solvent evaporates.
NOTE
Always pour solvent onto wash cloth to prevent
contamination of solvent supply; do not dip
cloth into solvent.
CAUTION
Soapless bubble fluid is slightly corrosive and
must be completely removed by washing freely
with water followed by scrubbing.
CAUTION
S/N 24-1038 and later model aircraft: When
removing lower inboard access panels, caution
should be exercised during removal so fuel
outlet tubes will not be damaged or bent.
28-14-00
-FUELADDITIVES
Under certain conditions of temperature and humidity,
water can be present in the fuel in sufficient quantities
to create ice formations within the fuel system.
To prevent this, add ISO-PROPYL Alcohol to the fuel
supply in quantities not to exceed 1% of total fuel
volume per tank.
CAUTION
Ethylene glycol monomethyl ether (EGME) or
other additives are not recommended due to
potential deteriorating effects within the fuel
system.
(4) Thoroughly dry clean area by flowing filtered
air over immediate area until there is no possibility of
solvent or fuel entrapment under adjacent sealant.
12-98
28-13-00
9
MOONEY AIRCRAFT CORPORATION
M20J
28-20-00
- DISTRIBUTION
The fuel system includesof two fuel pumps, an engine
driven pump and an electricallydriven auxiliary boost
pump.The boostpumpis connectedto a switchon the
strumentpanel,
28-21-00
- FUEL BOOST PUMP REMOVAL
AND INSTALLATION
1. Auxiliary Electric Boost Pump Removal.
A. Remove electrical leads,
B. Turn fuel selector valve OFF.
C. Disconnect inlet and outletfuel lines,
D. Remove fuel pump.
2. Reverse the removal procedurefor reinstallation,
CAUTION
Do not run pump dry for more than 15 seconds,
NOTE
Refer to S.B. M20-222 (latest revision) when
replacing fuel boost pump. (Ref. A.D. 80-13-03)
NOTE
When the aircraft will not be flown for a period
of time, refer to Section 10-10-01 thru 10-10-03.
28-25-00
- FUEL SELECTOR VALVE
REMOVAL & INSTALLATION
1. (For SIN 24-0001 thru 24-0377) The fuel selector
valve isbelow the left floorboard just aft of the firewall.
A. Disconnect right and left inlet lines at valve
body.
- SELECTOR VALVE AND
GASCOLATOR SCREEN
CLEANING
1. Fuel selector and drain valve screen or gascolator
screen should be cleaned every 50 hours. Both valves
are safety wired, (notice should be taken of exact
wiring technique before removal) and upon completion,
rewiring should be identical to odginal installation.
To clean fuel selector screen,
(a) Remove left hand exhaust cavity,
(b) Turn selector valve to off position,
(c) Remove AN-3 bolt from center of bottom of
valve,
(d) Remove bowl and clean, (e) Reverse
process to re-install taking care not to damage o-rings
seal. (Torque AN-3 bolt 15 to 20 inch pounds per
Service Bulletin M20-200).
2. SIN 24-0378 & On: Gascolator screen removal
and cleaning: Remove belly skin just aft of nose
wheelwell; turn selector valve to off position; remove
safety wire on bottom nut and remove nut; remove
sump and screen by pulling down; clean screen and
reverse pmcass to reinstall (take care not to damage
O-rings); lubricate O-rings with clean engine oil before
installing.
Torque 15 to 20 inch pounds per Service
Bulletin M20-200.
28-20-00
10
28-23-00
- FUEL INJECTION SYSTEM
The Bendix RSA-5AD1 fuel injectionsystem measures
airflow and uses an airflow signal In a stem-type
regulator to convert the air pressure into a fuel
pressure.This fuel pressure (fuel pressuredifferential),
when applied across the fuel metering section of the
fuel injector (jetting system), makes fuel flow
proportional to airflow. The injection system is
comprised of the injector, flow divider, air-bleed
nozzles, and associated lines and fittings.
CAUTION
Fluid can easily enter the air section of the
injector through the impact tubes or the annular
groove around the venturi. For this reason, a
protective covering should be installed on the
induction air intake when performing engine
maintenance, such as washing down the engine
and induction air ducts or when injecting
preservative oil into the engine and fuel injector
prior to storing or shipping.
28-24-00
, ENGINE PRIMING
The Lycoming fuel injectioncontrolsdo not include an
engine primer. Fuel will be sprayed into the intake
manifolds whenever there is pressure in the fuel
systemand the mixturecontrol is open. It is necessary,
therefore,to exercise cautionwhen operatingthe boost
pumpto be sure that the mixture controlis in the IDLE
CUTOFF position.
CAUTION
Mixture control should be in IDLE CUTOFF
dPositionto check operating pressure, however
o not operate the boost pump for more than a
few seconds to prevent excessive flooding of
the engine.
28-22-00
SERVICE AND MAINTENANCE MANUAL
B. Disconnect outlet line at valve body.
C. Remove clevis pin from valve control linkage.
D. Loosen set screw on fuel valve drain control.
E. Remove bolts from supporting bracket at
floorboardand beam.
F. Reverse the selector valve removal procedure
for reinstallation. Pressure check fuel system for leaks
after installation.
(For 24-0378
24-TBA)
The
selector valve
is 2.
located
aft of thethru
console
below
thefuel
floorboard.
A. Drain both fuel tanks.
B. Disconnect dght and left inlet lines at valve
body.
C. Disconnect outlet line at valve body.
D. Remove handle above floorboard in fuel
selector pan.
E. Remove screws mounting valve to the tubular
structure.
F. Remove valve.
G. Reverse the selector valve removal procedure
for reinstaIlation. Pressure check fuel system for leaks
after installation.
12-98
SERVICE AND MA NTENANCE MANUAL
M20J
NOTE
It is recommended that the fuel selector valve
be replaced each 500 hours of operation or if
the valve becomes difficult to operate,
(Anderson-Brass Valve only)
28-26-00
- FUEL FILTER
MOONEY AIRCRAFT CORPORATION
(3) Locate& remove transmitter wires.
(4) Removesix screws attachingtransmitter to rib
doubler.
(5) Removetransmitterfrom rib.
B. O/B Transmitterremoval
(1) Gain access through lower access cover
outsideoftank area.
Fuel filter shouldbe inspected,cleaned or replacedat
each annual or 100 hour inspection. (See
TroubleShootingChart)
28-30-00
- DUMP
(2) Locate& removetransmitter wires.
(3) Remove six screws attaching transmitterto rib
doubler.
The
fuel tanks can be emptied for maintenance
purposesby:
(1) removingthe sump drains in the lower panel
of each fuel tank and allowingfuel to drain into suitable
containeror
(2) disconnect the fuel line at outlet of the fuel
pump; usa boostpumpto transfer fuel from bothtanks
to a suitablestorage container,
28-31-00
- FUEL SYSTEM DRAINS
(4) Removetransmitterfromrib.
2. For REINSTALLATION, reverse the fuel quantity
transmitterremovalprocedure.
A. A calibrated, certifiedtorque applicationdevise
2. Remove fuel tank filler cap; blowgentlyinto rubber
hose.Air should be felt comingout of filler port.
3. If Stoppageis found, clear vent priorto flightsince
fuel starvationcould resultfrom vent stoppage,
NOTE
It is important that the fuel tank vent tube
protrude only enough to be flush with lower
wing skins.
mustbe usedto installthe fuel quantitytransmitters.
B. Snug each screw, then TORQUE each screw
to 20-25 INCH LBS. in a cross flange-random order.
C. The torque and screw clamp load will naturally
relaxas the gasketflowsto a normal condition.
NEVER RETORQUE JUST TO RESTORE THE 20-25
INCH LBS.
"DO NOT OVERTORQUE"
-- DO NOT RETORQUE UNLESS LEAKING
D. Excessive torque or retorquing may warp or
distort the transmitter mounting flange and cause a
malfunction.
E, Make certain wire from outboard transmitter
goes under head of insulating sleeve against the
inboardtransmitter flange and not under the mounting
screw head.
F. Systemvoltageshould NOT BE APPLIED to the
transmitter terminal. The exicitation from the fuel
quantity indicatormust be current and voltage limited
and incapable of causing ignition of fuel vapor if
transmitterwire is inadvertentlyshortedto ground.
G. Care must be taken to insure that the bottom
nut on the terminal stud is not disturbed when the
electrical connection is made. This bottom terminal
stud nut torque is factory set to provide the correct
terminal studseal preload.
H. Other nuts on the electrical terminalsshould be
tightened as follows:
#6 - 6 in. Ibs./#6 - 12 in. Lbs./#10 - 14 in. Ibs.
28-40-00
- INDICATING
28-42-00
28-41-00
- FUEL QUANTITY INDICATING
TRANSMITTERS
Two fuel quantity gauges are in the instrumentcluster
gauge. These gauges indicate pounds or gallons of
fuel remaining.Each gauge operates by the changein
resistanceoftwotransmitters locatedin the fueltanks.
Fuel drains are installedin the inboardcomers of the
wing tanks and at the fuel selector valve or gascolator,
the
lowest point
in the fuel
Thejoin
engine
manifoldand
engine-driven
fuel system.
pumpdrains
at a
juncture on the right side of the engine. A single drain
line dumps fuel overboard below the cowling. Tank
drains are recessed and spring loaded. An O-ring at
the lower flangeseals the valveseat.
28-32-00
-FUELVENTS
The fuel tanks are vented from the outboard upper
edge. This vent is routed outboard and is vented
overboardthrougha NACA vent on lowerwing surface,
To checkfuel tank vents:
1. Block entire fuel tank vent by slipping a short
length
of rubber hose over tube and projectingbelow
wing lowersurface.
The fuel quantity indicating system has two fuel
quantitytransmitters in each wing tank, one on lib wing
tank fib and one on O/B wing tank rib. The transmitters
are electrically connected to the fuel gauges in the
clustergauge and work in series witheach other.
1. Fuel QuantityTransmitter Removal.
Drain fuel from tank. Reference 28-30-00.
- FUEL QUANTITY INDICATOR
28-43-00
- FUEL QUANTITY ADJUSTMENT
PROCEDURE
28-43-01
ADJUSTMENT"
FUEL TANK TRANSMITTER
A. lib Transmitter removal
(1) Remove Pilot or Co-Pilot seat as needed.
(2) Remove intedor panel, LH or RH as needed.
12-98
AIRCRAFT MUST BE LEVEL TO CALIBRATE
FUEL GAUGES
NOTE
See Section 24-33-00 for low fuel calibration.
28-26-00
11
MOONEY AIRCRAFT CORPORATION
M20J
(PRIOR TO SIN 24-1050 - approximately)
1. Fueltanks-EMPTY.
2. Add unusable fuel (1.3 Gal.). Indicatorshould read
%" to 1/2 needle width below =E". Inboard floats may
be adjusted by holding arm near transmitter and
bendingouter arm, (do not bend by forcingarm against
stops).
3. Add 2 1/2 to 3 gal. (part of additional 8 gal.
required for 1/4 gauge reading). Adjust low fuel
warning trimmer in annunciator panel so that warning
lightjust comes on (see Section24-33-00, 4. A and B).
4. Continue calibration by adding fuel in 8 gal.
increments,(-1, +2 gal.) for 1/4, 1/2, and 3/4 gauge
readings. Gauge to read within 112 needle width.
Outboardfloat may be adjustedif required for 1/2 and
314gauge readings.
SERVICE AND MAINTENANCE MANUAL
2843-02
Clustergauges installedon MID 1981 aimraft and any
spare units installed on earlier aircraft have this
adjustment.
1. Remove plastic plugs from holes in top left of
cluster gauge case. With "unusable" fuel in tanks,
adjust
pot marked
"null" so gauge
%". as
If
intermediate
or =P"indicationsare
out ofreads
tolerance
tank
is filled, adjust pot marked "gain" for correct
calibration.
28-90-00
28-91-00
Fuel gauge notindicating
Fuel gauge indicatesfull
when tanks are not full.
No fuel pressure indication
(calibratedtest gauges
connected.
Fuel pressurelow or surging
(calibrated test gauges
connected.)
28-43-02
12
-MISCELLANEOUS
-TROUBLESHOOTING
When trouble shooting,checkfrom the powersupplyto
the suspect item. If trouble is not located, proceed to
check the item itself. If necessary, remove the item and
install an identical unit tested and known to be in good
operational condition.
5. Finish filling tank and verify total quantity leas
unusable fuel.
TROUBLE
- FUEL QUANTITY GAUGE
ADJUSTMENT (Approx. S/N
24-1051 THRU 24-TBA)
PROBABLE CAUSE
REMEDY
Brokenwire.
Check and Repair.
Faultytransmittingunit.
Open circuitbreaker.
Replace.
Check and reset.
Incomplete ground.
Check groundconnectionat
transmitter.
Broken wire.
Check and repair.
Tank empty.
Check and servicetank.
Defective fuel pump.
Check pump for proper pressure
buildup.
Checkfor obstructionin boost pump
screen. Checkengine fuel pumpand
checkvalve.
Fuel Filter Clogged
Clean or replace Fuel Filter
Open fuel line.
Repair or replace line.
Fuel selector in "OFF"
position.
Obstructionin inlet side of
pump.
Select proper position
Faulty engine pump.
Check fuel lines and connection for
leakage or damage.
Fuel Filter partially clogged.
Clean or replace fuel filter.
Fuel selector not in proper
position.
Air leak in system.
Select proper position.
12-98
Check and clear fuel lines. Replace
or rebuild pump.
Repair leak.
SERVICE AND MAINTENANCE MANUAL
M2OJ
28-92-00
- FLARED FITTINGS
When installing flared fittings and hoses, make sure
the threads are properly lubricated with W-P-236
petrolatumper (Figure 28-5). When previouslyinstalled
MOONEY AIRCRAFT CORPORATION
fittings are removed, they should be wiped clean and
relubricated before they are reinstalled. Toque all
fittings in accordance with flare fitting torque chart,
Chapter5, Figure5-1.
TAPERED
STRAIGHT--/
TH READS
LUBRICATE
FEMALE
THREADS
/
/
NEVER ALLOW LUBRICANT
TO CONTACT THESE
SURFACES
LUBRICATION OF FLARED FITTINGS - FIGURE 28-5
12-98
28-92.00
13
MOONEY AIRCRAFT CORPORATION
M20J
BLANK
28-92-00
14
12-98
SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 30
ICE PROTECTION
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 30
ICE PROTECTION
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
30-Effectivity .........
30-Contents..........
30-00-00
..........
30-61-01 ........
30-61-02 ............
30-61-02
.........
30-61-02 ............
30-62-00
...........
30-63-00
...........
30-67-00
...........
30-69-00
...........
30-70-00
...........
PAGE
._.
.
..........
DATE
1/2BLANK ..........
3/4BLANK ..........
5 ...........
. . 6 ...........
7 ...........
8 ...........
9 ...........
10 ...........
11 ...........
12 ...........
13 ...........
14 ...........
12-98
12-98
12-98
12-98
12-98
12-98
12-98
12-98
12-98
12-98
12-98
12-98
12-98
30-EFFECTIVITY
1/2BLANK
MOONEY AIRCRAFT CORPORATION
M2CJ
SERVICE AND MAINTENANCE MANUAL
CHAPTER 30
ICE PROTECTION
TABLE OF CONTENTS
CHAPTER
8EC'IICN
SUBJECT
...........
30-00-00 ........
30-30-00 .........
30-60-00 .........
30-60-01
..........
30-61-00
..........
30-61-01 ............
39-61-02 ............
30-62-00
..........
30-63-00
..........
30-64-00
..........
30-65-00
..........
30-66-00
..........
39-67-00
..........
30-68-00
..........
30-68-01 ............
30-69-00
..........
30-79-00 .........
SUBJECT
........
General ..............
Pitot, DescdpUon& Operation .......
Propellers, Description & Operation ......
Schematic - Propeller De-Ice ......
Service Guide ..........
Helpful Tips
.........
Trouble Shooting Chart ......
Ammeter Test ..........
De-Icer Timer Check ........
Heat Test ...........
Continuity Test. .........
Brush to Slip Ring Resistance Test
Brush Assembly Resistance Check
Brush Replacement ........
Brush (Module) Replacement
Alignment of Slip Ring ........
Servicing/Cleaning ..........
12-98
PAGE
....
....
....
5
5
5
5
5
5
7
10
11
11
11
11
11
11
12
13
13
"0-CONTENTS
3/4BLANK
SERVICE AND MAINTENANCE MANUAL
30-00-00
(
....
M2OJ
- GENERAL
The M20J aircraft incorporatesan alternate air system
that is designed to open automaticallyany time the air
intakesystembecomesblocked.
A standard heated pitottube is locatedon the left wing
at Wing Station No, 145. The pitotheat circuit breaker
switch located on the panel in front of the pilots right
kneesuppliespowertothe pitottube heatingelement.
I
' PROPELLERS, DESCRIPTION AND
OPERATION
Propeller ice removal is accomplished by optional
electrically heated de-ice boots bonded to each
propeller blade,
The system uses the airplanes electrical power to heat
portions of the de-ice boots in cycles controlled by a
timer. The ON-OFF switch is located on the switch
panel in front of the pilots right knee. A current flow is
depicted,(8 to 12 Amps, 24-0001 thru 24-2999) (8
Amps, 24-3000 thru 24-TBA) on the ammeter located
in front of the co-pilot at the top of the radio panel. A
slight deflection of the ammeter needle may be noticed
approximately every 90 seconds; this is due to the
cycling action of current flow to the circuits within the
boot as controlled by the timer. This is normal
operation. The timer is located on the circuit breaker
panel side tray above the co-pilots right knee. Deqcer
boot replacement should be done per B.F. Goodrich
Report No. 59-728J which is supplied with the kits for
replacement boots.
_
./-3E1964--3
#_ TIMER
'@J,
l
--O05B
I
]('_1
_ --O03B
I_
I /
AMMETER
30-61-00
- SERVICE GUIDE
30-61-01
- HELPFUL TIPS
1. Normal current isshown as a shaded range onthe
ammeter for each propeller De-Icer system with engine
running. The ammeter reading will he slightly lower
when the system is operated on battery voltage.
2. Use the "heat test" (30-64-00) and "ammeter test"
(30-62-00) to determine which De-Icers are not
operating. Use wiring schematic to trace circuits.
SLIP RING ASSY.-_._
./_
L
- PROPELLER DE-ICE
3. Excess current reading on the ammeter always
indicates a power lead is shorted to ground. Thus,
when trouble of this nature is found, it is vital that the
grounded power lead be located and corrected.
4. A considerable number of timers have been
returned for repair which proved, on test, to be fully
operable. Before concluding that the timer ls faulty, test
it per"De-lcerTimer Check" (30-63-00).
5. For insulation resistance tests, use a "megger"
("Meg" type insulation tester, James G. Biddle
Company,
Plymouth
PROP DE-ICER
Meeting, PA.) or
4E2351-3
4E24-06
30-60-01
INTRODUCTION. Whether in flight or during ground
testing, the ammeter can be used to determine the
general nature of most electdcal nroblems. The
TroubleShooting Chart is based, pnmanly, on the use
of the ammeter and it is assumed that the user
understandsall normaloperatingmodesof the system.
(See Section IX of P.O.H.). Read all of the "Trouble"
entriesto locatethe one matchingthe conditionsof the
system being checked. The "Probable Cause" and
=Remedy" entries pertinent to each trouble are
arranged in the recommended checking sequence.
B.F. Goodrich maintenance Manual Report No.
68-04-712B will be required for complete maintenance
actions.
This aircraft includesas standard equipmenta heated
pitottube assembly and may also include an optional
electdcallyoperated propellerde-ice system,
30-30-00
- PITOT, DESCRIPTION AND
OPERATION
30-60-00
._
G-_0"
JJ
;o
c_[__
2_IP-L_
" " 2ihtCOgA'-
(1A)_,..USE_
J(1
/--002F__L_
SHUNT
--'_'-_B"
(MS91586-1_J"
J
having°ther
a tester500
_
VDO,megoh
m
1000
6.
Defective
widng in propeller
I-°°_
'
e
DE-ICE
/
MOONEY AIRCRAFT CORPORATION
)
I
I II
SWITCH 930023--1
12 VOLT SYSTEM
ULAF
/ "E,_, ,_-,,
_
_
_
ASSY.
mounted
--
I_
\
be indicated by
components
normal
current
may
readings
in
ground checkouts
(propellers
not
_,
_ E2130
currentprope
with
--001z_
'_ "IP_GWIRING
cmiseHARNESS
rotating at
RPM.
CZZ_
"-q
BUS BAR + 14- VDC
FIGURE 30-1A - PROPELLER DE-ICE SCHEMATIC (14 VDC)
12-98
3O-0O-0O
5
SERVICE AND MAINTENANCE MANUAL
TIME CYCLE
D
F
TIME CYCLE
D
.....
M20J
MOONEY AIRCRAFT CORPORATION
POWER REQUIREMENTS FOR 14 VDC SYSTEM
ELEMENT HEATED
TIME (IN SEC'S.)
OUTBOARD
90
INBD
90
TOTAL CYCLE TIME = 3 MINUTES
LOAD (AMPS)
8 TO 12
8 TO 12
POWER REQUIREMENTS FOR 28 VDC SYSTEM
ELEMENT HEATED
TIME (IN SEC'S.)
ALTERNATING BLADES
90
TOTAL CYCLE TIME = 3 MINUTES
LOAD (AMPS)
8
RECOMMENDED WIRE SIZE CHART
............
AWG SIZE
.....
MAZ_.ENG_T_
BUSS BAR TO TIMER ...........
#14
.......
15 t_.
TIMER TO GROUND ...........
#18
.......
5 ft.
#14
.......
151_.
#20
.......
5 it.
TIMER TO BRUSH MODULE
BRUSH MODULE TO GROUND
........
SHUNT LEADS .............
30-61-02
- TROUBLESHOOTING CHART-PROPELLER DE-ICE
TROUBLE
PROBABLE CAUSE
REMEDY
Ammeter reads 0 currentall
phasesof the timer cycle,
-No powerfrem aimraft.
If no voltageintocircuitbreaker, locate
and coned open.
-Trippedcircuitbreaker.
Locate and correctshortbefore
resettingcircuitbreaker.
-Circuitbreaker or switchfaulty.
If novoltageat circuitbreakeroutputwith
voltageat inputand circuitbreakerdoes
notreset,replacecircuitbreaker.If
voltageis OKat output,checkswitchin
samemanner.If voltageisOK at switch
output,goto =AmmeterFaulty".
Test ammeter per Section30-62-00.
-Ammeter Faulty.
-Open in ammeter to timer
circuit,
:Open in timer to brush
assembly(ies) circuit,
12-98
Disconnectharness at timerand check
for appropriatevoltageat harness Pin
B,12V,TerminalC,28V to ground.If
none, locateand correct open.
Disconnect wire harness at brush
assembly and check voltage to ground
from pins or leads. (See de-icing
system wiring schematic for power and
ground lead and pin identification.) If
low or no voltage,locate and correct
open or high resistance in wire harness.
30-61-02
7
MOONEY AIRCRAFT CORPORATION
TROUBLE (cant.)
Ammeter reads normal current
part of cycle, zero current rest
af cycle,
Ammeter reads normal current
part of cycle, low current rest af
cycle,
Ammeter reads low current
over entire cycle,
M20J
SERVICE AND MAINTENANCE MANUAL
PROBABLE CAUSE
REMEDY
Check continuityfrom appropriate pin
or lead to ground; if high resistance is
indicated, check ground wire for
breakage and ground connections for
correctness and tightness. Correct as
required
-Open circuit ta De-Icer Boot,
De-Icer wire harness ar slip ring
assembly leads.
DisconnectDe-Icer leads and check
resistance per B.F. Goodrich Report No.
59-728. If not OK, replace faulty De-Icer.
If OK, check for (and fix) open in slip
rings leads. See Section 5-4.5, B.P.
Gooddch ReportNo. 68-04-712B.
Ohmmeter needle must not flicker when
leads are stretchedor flexed. Replace as
required.
See "Open Timer te Brush Assembly"
above.
-Open circuit in wiring between
timer and brush block assembly
or brush assembly.
-Open in De-Icer boot or slip ring
assembly lead circuits.
See "Open in De-Icer' above.
-Timer faulty.
-Inner and outer De-Icer Boot
elements heating same phase (in
series), should be in parallel.,
Test timer per Section 30-63-00.
Locate and repair incorrect lead
connections. See widng
schematic.(24-0001 - 24-2999)
-Open circuit or high resistance
in De-Icer Boats, slip ring
assembly leads or wire harness.
-High resistance in circuit with
low current,
See "Open in De-Icer" above.
-Worn or dirty brushes and/or
slip rings.
Inspect & clean brushes or slip ring.
Check contact of brushes to slip rings
per Section 30-66-00 or B.F. Goodrich
Report No. 68-04-714; correct as
indicated; check wiring from timer to
De-Icers for oose or corroded
connections or partially broken wiring.
Correct as required.
-Aircraft.voltage low under
normal operating conditions.
Check voltage into switch.
30-61-02
8
-Ammeter, switch,or circuit
breaker faulty,
Check voltage up to and out of
ammeter, switch, and circuit breaker.
Test ammeter per Section 30-62-00.
Report No. 68-04-712B. If low output
and input OK, replace defective
component.
-High contact resistance up to
timer,
Check for partially broken wire, or
loose or corroded connection in wiring
between aircrelt supply and timer input.
Correct as required.
-High contact resistance in timer.
Test timer per Section 3-2.4 B.F.
Goodrich Report No. 68-04-712B.
12-98
SERVICE AND MAINTENANCE MANUAL
TROUBLE (cont.)
Ammeterreads excesscurrent
overentirecycle,
Ammeter reads normal current
part of cycle, excess current
rest of cycle.(24-0001 thru
24-2999) (12V)
Ammeter does not "cycle" each
90 seconds,
Ammeter flicks between 90
second phase periods,
M20J
MOONEY AIRCRAFT CORPORATION
PROBABLE CAUSE
REMEDY
-One De-Icer Bootelement (or
wiringconnectionsto De-Icer) in
each cycle open.
Performa heat test on each De-Icer.
Turn De-Icer switch ON, and, alter
locatingthe De-Icer section being
heated, followthe heatingcycle, fueling
each sectionfor heatingin turn.
Replacedefective components.
Check power leadsfrom ammeter to
timer andthen to De-Icers for evidence
of damage or arcing.With de- icing
systemswitchOFF and timer harness
disconnected,check insulation
resistance(use "Megger") to ground
fromtimer harnessPin B. 12V, Terminal
C, 24V.
Disconnectharness at brush assembly
and repeat check for applicable brush
assembly harness connections. (See
widng schematic Section 30-60-01). If
ground is indicated, locate and correct
it.
-Power lead shortedto ground.
-Ammeter faulty.
Test ammeter per Section 30-62-00.
-Short to ground or short
between adjacent circuits,timer
to brush block,
Disconnect leads at brush assembly
and timer. With "Megger", check
insulation resistance from power leads
to ground and between adjacent
circuits. Eground or short is indicated,
locate and correct.
-Short to ground or between
adjacent timer circuits in brush
block.
Electrically isolate brush assembly and
test per Section 4-6, B.F. Goodrich
Report No. 68-04-712B.
-Short to propeller or short
between two adjacent circuits slip dngs to De-Icers.
Isolate brush assembly. With "Megger",
check insulation resistance from one
ring of slip ring assembly to bare prop.
Reading should be at least .5 megohms
after one minute. If not OK, disconnect
the slip ring leads one set at a time to
trace short. If OK, disconnect slip dng
leads and check insulation resistance
between slip rings; reading should be at
least .5 megohrns after one minute. If
not OK, clean assembly thoroughly with
standard solvent and wipe clean with
MEK and retest. Replace as required.
Test timer per Section 30-63-00.
Disconnectharnessat timer and check
ground connectionwith ohmmeterfrom
PinA,12V;TerminalG,24V.
-Timer faulty.
-Timer ground open; timer not
cycling,
-Timer contacts welded together
(caused by short in electrical
system),
Test timer per Section30-63-00. Iftirner is
faulty, repairor replaceit but insurethat
short causingodginalfailure has been
locatedand corrected.
-Loose connection between
aircraft power supply and timer
input,
Trace wiring from power source to timer
input. Insure that good electrical
contacts are made at each connection
in circuit.
12-98
30-61-02
9
MOONEY AIRCRAFT CORPORATION
TROUBLE (cont.)
Radionoise or interferencewith
Deqcere Boots ON.
M20J
SERVICE AND MAINTENANCE MANUAL
PROBABLE CAUSE
-Loose or poor connection;
timer to De-Icers.
REMEDY
If trouble occursonly part of the cycle,
determinewhich De-Icer is affected
and checkfor roughor dirty sliprings
causingbrushto skip. Also, check
circuitsfor looseor poorconnections.
-Timer cycleserratically.
Test timerper Section30-63-00.
-Brushes arcing.
Checkbrushalignmentper B.F.
GooddchReportNo.68-04-714. Check
fordirtyor roughsliprings.If so, clean,
machineor replaceslipringassembly.
(See B.F. GooddchReportNo,
68-04-712B,Section5-4.)
Checkslip ringalignmentper Section
4-5, B. F. GoodrichReport No,
68-04-712B.
-Loose connection.
See 4-3.8.a. and b., B.F. Gooddch
Report No. 68-04-712B.
-Switch or circuit breakerfaulty.
Placejumperwire acrossswitchor circuit
breaker,if radionoise disappearsreplace
switchor circuitbreaker.
-Widng too close to radio
equipment or associated widng,
Relocate De-Icer wiring at least 8" from
radio equipment and wiring.
Cycling sequence not correct.
-Crossed connections between
timer and De-lcars.
Check system widng against circuit
diagram.
Rapid brush wear or frequent
breakage.
-Brush block out of alignment.
Check brush alignment per B. F.
Goodrich Report No. 68-04-714.
Correct as Required.
-Slip ring wobbles.
Check slip ring alignment with dial
indicator per Section 30-69-00.
Refinish per Section 5-4, B.F. Goodrich
Report No. 68-04-712B.
-Rough slip rings.
30-62-00
-AMMETER TEST
At some convenient point between bus bar and
ammeter, connect a volt ohmmeter with an ammeter
scale or a standard ammeter into the circuit and, with
the De-Icer switch ON, check the amperage being
used by the De-lcar system. The reading of the
standard ammeter should closely agree with the
reading obtained from the De-Icer ammeter. Turn
De-Icer switch OFF and remove volt-ohmmeter or
standard ammeter from circuit. If ammeter readings
were significantly different and rest of de-icing system
checks out satisfactorily, see Ammeter Checkout,
Section 4-7 of B.F. Gooddch Report No. 68-04-712B.
30-63-00
- DE-ICER TIMER CHECK
Experience in the field has indicated that often the
timer is considered defective when the source of the
trouble lies elsewhere. For this reason, the following
test should be performed before the timer is removed
as defective.
'
1. With the wiring harness disconnected from
Terminal B at the timer and the deicer switch in the ON
30-62-00
10
position, check the voltage from Pin B(12V);from wire
from shunt (28V) of the harness to ground. If no
voltage is present, the timer is NOT at fault; however, if
system voltage is present, check the circuit from
harness Pin A (12V); from Terminal G (28V)to ground
with an ohmmeter. If no circuit is indicated, the fault is
in the ground lead rather than the timer. If ground
connection is open, the timer step switch will not
change position.
2. After the ground and power circuits have been
checked, connect a jumper wire between pin B of the
timer receptacle and terminal B of the connector plug
and from pin A of the timer receptacle to ground. With
the de-icing system switch ON, check the voltage to
ground from pin B of the timer. The voltmeter should
indicate approximately 12 volts (24-0001 thru 24-2999)
or 24 volts (24-3000 thru 24-TBA) when the aircraft
battery supply is being used. Next, check the DC
voltage to ground from Pins D and F (12V); Pin C
(24V), the points at which the system voltage is
impressed in sequence to cycle power to the propeller
de-icers. Each of the plugs should read 12 volts
(24-0001 thru 24-2999), 24 volts (24-3000 thru
24-TBA) in sequence of cycle.
12-98
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
TIMING
SEQUENCE
Pin O
TIME
ON
90 sea.
AREAS OF PROP DE-ICERS HEATE0
Pin F
90 see.
Inboard Section tbru 24-2999)
(12 VoltA/C)
Pin C
90 see.
Both blades ON/OFF(24 Volt NC)
Outboard Section-
(24-0001
NOTE
Timer does not reposition itselfto start at Pin D when systemis turned off, but will begin cycling from
same position as it was when turned off. Cycling will then proceed as before (24-0001thru 24-2999).
After a voltage reading of 12 volts DC (24-0001 thru
24-2999) or 24 volts (24-3000 thru 24-TBA) is
obtained, hold the voltmeter probe on the pin until the
voltage drops to zero before moving the probe on to
the next pin in the sequence noted above. After the
cycling sequence has been established, turn the
de-icingsystem switch OFF at the beginningof one of
the =on-time"pedods and record the letter of the pin at
which the voltage supply is present to facilitate
performance of the following test.
30-64-00
-HEATTEBT
Before this test can be performed, the jumper wire
installed in paragraph 30-63-00, 2, for the timer test must
be removed so that the connector plug can be replaced
in the timer receptacle. Two men are requiredto perform
this test, one in the pilot's compartment to monitor the
ammeter while the other checks the De-Icer boots. The
man in the pilot's compartment tums the De-Icer system
ctmu'rtbreaker switch ON while the man outside feels the
De-Icer boots to see if they are heating propedy. The
man in the pilot's compartment observesthe ammeter for
the proper readings (8 to 12 amps)(24-0001 thru
24-2999), (8 amps)(24-3000thru 24-TBA) throughoutthe
timing sequence. The ammeter needle should deflect
eve_/90 secondsin responseto the switchingaction of
the timer. Each time this occurs,the man in the pilot's
compartment must notifythe man inspectingthe propeller
De- Icer boots so that the latter can change the position
of his hands to check the proper heating sequence of the
propeller De-Icer areas. If any irregularitiesare detected,
a continuity check should be performed on the widng
from the timer to the brush block holders end the
propeller De-Icer terminal connections,
CAUTION
Stand clear of propeller, verify magnetos OFF.
Use extreme caution during thistest procedure.
30-65-00
I
3. Pin A of the plug(12V),Terminal G (24V) to the
airframeground.
4. Groundterminal of one prop bootto ground.
30.66-00
To check for incorrect resistance or the presence of a
short or open circuit at the brush-to-slip ring contact,
disconnect
the each
hamess
at the
timer
check
resistance from
De-Icer
circuit
leadand
(pins
D andtheF
of the harness plug) to ground with a low range
ohmmeter. If the resultant readings are not 1.55 to 1.78
ohms, disconnect the De-Icer lead straps to measure
heater resistance individually. Individual boot
resistance should measure between 4.58 and 5.26
ohms. If the readings in the first check are not within
the accepted limits but those In the second check are,
the trouble is probably in the brush-to-slip ring area. If
the readings in the second check are also off, the
De-Icer concerned is damaged and must be replaced.
30-67-00
- BRUSH ASSEMBLY RESISTANCE
CHECK
To checkfor an open circuit,a short, or high resistance
in the brush assembly, measure the resistance from
the face of the brush to its terminal studs with a low
range ohmmeter, if this resistance measures over
0.013 ohms, locate and repair the cause of excessive
resistance. If the resistance is infinite, locate and
correct the open circuit or ground, or else replace the
brush assembly. Check the resistance between the
three terminal studs. This resistance should not be less
than 5 megobms.
30`08-00
-CONTINUITY TEST
After removing the plug from the timer, use an
ohmmeterto check continuityfrom:
1. Pin D of the plug'(12V),TerminalC (24V) to the
outboardterminal of one prop boot.
2. Pin F of the plug(12V) to the outboard terminal of
one prop boot.
. BRUSH TO SLIP RING RESISTANCE
TEST
- BRUSH REPLACEMENT
The propeller De-Icer brush module should be
replacedwhen a minimumof 1/4 inch of brush matedal
remains. It is good practice, however, to replace the
modules when 318 inch of the brash material stitt
remains.
12-98
30-64-00
11
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
(24 Volt system has only 2 modules stacked)
30-68-01
- BRUSH (MODULE)
REPLACEMENT
(See Figure 30-3),
X-SIMENSION (JIN_H_)
1. Measure brash wear as shown (Figure
30-2); X-dimension (inches) given indicates
when modules MUST be replaced.
2. Brushes are not offered, individually, as
replacements. When a brush wears out, the
module containing it should be replaced as
.__AR IIRUSH
ASSE3HIBLIES
_u..onu_sHAVING
SRLL_HE=VilliRB_
_u__D_.ESHAVZ,6
SRUSHES
VITHI]IJT
RODS
MUST
RF.PLACE
17164
1-7164
aircraft by removing attaching hardware, and
disconnectenginewire harness.
B. Remove assemblyscrews and separate
A. Dismountmodular
brush assemblyfrom
modulesand
spacers.
C. The part number of each module is ___L._/_ \_
follows:
__
etched into the surface of the plastic housing;
SuRING
,_ASURB4CNT
O_-Y_16InCH
_r BRUSHH
SH_U_ \
replace with the same part number module.
_E
TI] PRBTRLll]E
FROM
BRUSH
BLOGI(,
"tHIS IR
THE ALL£1VF_I)
NaP.HAL POSITION
BF THE
BRUSH
',/HEN
INSTALEID
D. Restack modules and spacers as shown
ONTHE
AIRCRAFT.
(FIGURE 30-2). Check NB/C (12V),NB (24V)
stackingarrangement and location of spacers. If
there is interference between adjacent ring
terminals, reorient center module as shown
(Figure30-4).
E. On 3E2042 sedes assemblies, make
sure flat washer is positioned between star
washer and housing. Make sure that assembly is
square,thentighten screws.
F. Reconnect aircrafl wire harness to applicable
"A","B",or "C" terminals of modules. Insure that
adjacentdng terminals are nottouching.
G. Install assembly on aircraft with attaching
hardware removed.
H. Check assemblyfor proper alignment.
I. Refer to B.F. Gooddch Report No. 68-04-712(B)
forcomplete maintenance information.
REFERENCE FIGURE 30-3
SHM30-S
MEASURING BRUSH WEAR-FIGURE 30-2
1. BrushAssy. 3E2011-1
2. Brush Assy.3E2011-1
3. BrushAssy. 3E2011-1
6. Spacer 4E2218-3
7. Spacer4E2218-1
10. Screw MS24693-$35 (6-32 x 1-3/8)
12. Washer AN960C6
13. LockwasherM835333-7
14. Nut MS35649-262
1OOJ
o_._
....._.
o.
RINGS "i_RU 361_ OP
SLiP SlHO ROTATION
14-_
.,,/t-10
6
13_:
,
-,
f
p(. (
FORE & AFT POSITIONING
I
i
\.
.J LS=
.-.o°u..,u...,.
_3
MEASURING BRUSH WEAR - FIGURE 30-2
30-68-01
12
i
12-98
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
30-09-00
- ALIGNMENT OF SLIP RING
To check alignment of slip ring assembly, securely
attach a dial indicatorto the engine and place the
pointer on a slip ring (see Figure 30-5). Grasp the
propellerblade and rotateitslowly,notingthe deviation
of the slip ring from a true plate as indicated on the
gauge. Check that the total run-out does not exceed
0.010 inch (+/- 0.0025 inch) for reciprocatingengines
withinany 4 inchesof slipringtravel.
CAUTION
Due to the loose fit of some propeller thrust
bearings, a considerable error may be induced
in the readings by pushing in or pulling out on
the propeller while rotating it. Care must be
taken to exert a uniform push or pull on the
propeller to hold this error to a minimum.
I
l
SH30-4
ALTERNATE MODULE STACKING ARRANGEMENT
FIGURE30-2
corrective action is required. If it is not within the limits,
If the slip
withinthe
limits specified,
no
check
for ring
dirt run-out
on the isring
gear mounting
surfaces,
clean, and recheck alignment. If run-out is still out of
tolerance, return the slip ring assembly to the B.F.
Goodrich Co.
30-70-00
- SERVICING/CLEANING
Thoroughly cleaning the slip ring area with MEK or
standard engine degreaser on a routine basis is
recommeded. Keeping the brushes free of dirt, oil,
grease and carbon build-up will prevent those
contaminantsfrom beingtransferred to theslip ring.
(Only 2 modules for 24 volt systems)
ALIGNMENT OF SLIP RING - FIGURE 30-5
12-98
30-69-00
13
MOONEY AIRCRAFT CORPORATION
M20J
BLANK
30-70-00
14
12-98
SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 32
LANDING GEAR
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 32
LANDINGGEAR
_
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
32-Effectivity .........
32-Contents ...........
32-Contents ...........
32-00-00 ............
32-10-02 ............
32-10-05 ............
32-10-06 ............
32-20-03 ............
32-30-02
...........
32-30-04
...........
32-30-04
...........
32-30-04
...........
32-30-05
...........
32-30-05
...........
32-31-01
...........
32-31-02
...........
32-31-03
...........
32-31-05
...........
32-32-00
...........
32-40-00
...........
32-40-03
...........
32-40-04
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32-40-04
...........
32-40-04
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32-41-01
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32-50-02
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32-60-00
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32-60-04
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32-82-00
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PAGE
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DATE
1/2BLANK ..........
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32-EFFECTIVITY
1/2BLANK
MOONEY AIRCRAFT CORPORATION
M2OJ
SERVICE AND MAINTENANCE MANUAL
CHAPTER 32
LANDING GEAR
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
32-00-00 ........
32-10-00 .........
32-10-01
..........
32-10-02
..........
32-10-03
........
............
32-10-04
.........
32-10-05
..........
32-10-06
..........
32-20-00 .........
32-20-01
........
32-20-02
..........
32-20-03
..........
32-30-00 .........
32-30-01
..........
:32-30-02 ..........
32-31-01 ............
32-31-02 ............
32-31-03 ............
32-30-03
..........
..............
32-30-04
..........
32-30-05
..........
32-30-06
..........
32-30-07
..........
32-30-08
..........
SUBJECT
........
PAGE
General ..............
Main Landing Gear and Doors .......
Main Gear Removal.........
Main Gear Installation ........
Main Gear Door Rigging .......
(24-0378 thru 24-2999, 24-3079 thru 24-TBA)
Main Gear Door Rigging (24-3000 thru 24-3078)
Inboard Door Rigging (24-3000 thru 24-3078) .
Assist Bungee Installation .......
Nose Gear and Doors .........
Nose Gear Removal
........
Nose Gear Installation ........
Nose Gear Rigging .........
Extension and Retraction
........
Gear System Operational Check .....
Main Landing Gear System Rigging ....
(24-0001 thru 24-2999, 24-3079 thru 24-TBA)
(24-0001 thru 24-0377 ......
(24-3000 thru 24-3078) ......
Nose Landing Gear System Rigging
(24-3000 thru 24-3078) ......
Emergency Gear Extension System Rigging.
Landing Gear Actuator, Clutch Spdng, R & R.
Landing Gear Actuator, Recoiler Spdng, R&R
Manual Emergency Gear Extension System.
Final Check ..........
5
5
5
6
6
6
7
8
8
8
8
9
9
9
10
10
11
14
16
16
17
18
19
19
TABLE OF CONTENTS CONTINUED ON NEXT PAGE!
12-98
32-CONTENTS
3
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
TABLE OF CONTENTS (con't.)
CHAPTER
SECTION
SUBJECT
32-32-00
32-40-00
32-40-01
32-40-02
32-40-03
32-40-04
32-41-00
32-41-01
32-50-00
32-50-01
32-50-02
32-60-00
32-60-01
32-60-02
32-60-03
32-60-04
32-80-00
32-81-00
32-82-00
...........
.........
.........
..........
..........
..........
..........
.........
..........
.........
..........
..........
.........
..........
..........
..........
..........
.........
..........
..........
32-CONTENTS
4
SUBJECT
........
Trouble Shooting ..........
Wheels and Brakes..........
Main Wheels ..........
Main Wheel Disassembly/Assembly ....
Nose Wheel Disassembly/Assembly....
Brake Assembly .........
Trouble Shooting- Brake System ......
Shuttle Valve ..........
Steering.............
Nose Gear SteeringSystem ......
Nose Gear Steering &Tracking .....
Position and Warning .........
ElectricGear Safety Devices ......
Landing Gear Warning System .....
Airspeed Safety SwitchAdjustment ....
Squat SwitchAdjustment .......
Miscellaneous ...........
Landing Gear ShockDisc Inspection ....
Recommended Hard LandingInspections
12-98
PAGE
20
21
21
21
22
22
26
20
26
26
27
28
28
28
28
29
29
29
30
MOONEY AIRCRAFT CORPORATION
M20J
32-00-00
-GENERAL
The landing gear is operated by an electdcal motor
driven actuator. The travel dudng the extend and
retract cycle is controlled by down and up limit
switches located beneath the floorboard under the
pilotsseat. Power is suppliedto the actuatorthrough a
set of relays actuatedby the gear selectionswitch. The
gear selection switch is located at the top of the
instrument panel in front of the pilot. The actuator
worm gear ball nut is connectedto the retract bellcrank
which is connected to push-pull retract tubes and
bellcranksthroughoutthe entire retractionsystem. An
airspeed safety switch (24-0084, 24-0238 and on) is
mounted to the back of the airspeed indicator and
incorporated into the landing gear electricalcircuit to
prevent landing gear mtracUon while on the ground
untila safe takeoff speed is reached. A squat switch is
locatedon the lee main landinggear leg (SIN 24-0001
thru 24-0237, except 24-0084). A by-pass switch is
installed adjacentto the gear selectionswitch in order
to override
not
retract.the safety switch circuitryif the gear does
The gear legs are constructed of welded
chrome-molybdenum tubular steel, heat treated for
greater strength and wear resistance. Main gear
attaching points have bushings installed in the gear
mountingbox attached to the wing spar. The steerable
nose gear mountsto the cabintubularsteel frame,
NOTE
Heat treated components should NOT be
repaired; replace them.
The main gear wheels have hydraulic disc
brakes with a parking brake valve incorporated
into the system. Rubber discs in the gear leg
assemblies absorb the shock of landing and
taxiing.
MANUAL-EMERGENCY LANDING GEAR SYSTEM.
Emergency gear extension is available through a
manual override system. This system is built into the
actuatorunit.Refer to Section 32-31-05 and 32-30-03.
LANDING GEAR WARNING SYSTEM. The landing
gear warning system providesthe pilot with an audible
warningthat the landing gear is not down and locked
when the throttle is retarded to within 1/4 to 3/8 in.
throttle position. When the landing gear is down and
locked the electrical circuit is opened and the
intermittent horn is stopped. This warning switch is
mounted on the throttle housing forward of the
instrument panel (24-0378 & ON) and can be adjusted
for the proper setting by loosening the screw and
repositioning the switch. This switch is located inside
the
throttleby quadrant
(24-0001
thru was
24-0377)
and
operated
a cam when
throttle
retarded.
Adjustment procedures are similar,
BRAKE
The the
brake
system
is hydraulically
operatedSYSTEM.
by depressing
brake
pedals
mounted on
the pilotsrudder pedals. (Dual brake system is optional
for co-pilot). Individual wheel brakes are available by
depressingeither left or right pedal. Parking brakes are
actuated by depressingboth brake pedals and pulling
the parking brake control cable knob. This cable
actuates a lever on the parking brake valve and traps
the hydraulicfluid from the valveto the wheel cylinders
SERVICE AND MAINTENANCE MANUAL
thus holding the pucks to the discs. Release the
parkingbrakes by pushingthe parking brake knob in.
This releaseshydraulicpressureat the wheel cylinders
and thereforereleases thebrake discs.
32-10-00
-MAIN LANDING GEARAND
DOORS
32-10-01
-MAIN GEAR REMOVAL
(SIN 24-0001 thru 24-2999, 24-3079 thru 24-TBA)
1. Raise aircraftonjacks.
2. For SIN 24-0084, 24-0378 and ON partially retract
gear as descdbedin Section32-60-01.
For SIN 24-0001 thin 24-0377, except 24-0084)
Partiallyretract gear by operatingthe emergency gear
extensionmechanismin reverse.
CAUTION
ON SIN 24-0001 THRU 24-0377, except 24-0084
DO NOT fully retract gear using emergency
gear extension system. Partial retraction using
emergency extension system is permissible
only during gear rigging. DO NOT operate gear
electrically with emergency extension system
engaged.
3. Disconnectgear door links and brake lines. Cap
all linesand fittings.
4. Removegear door and mud guard (if desired).
5. Detach main gear retracting tube (V), (Figure
32-9) from retractingtruss (G), and remove bolts (H)
from retractingtress mountingblock.
NOTE
Steps 7 thru 9 apply to 24-0001 thru 24-2999
and 24-3079 thru 24-TBA only.
6. Remove grease fittingsfrom forward gear support
trunnion-shaft.bearing.
7. Retractthe gear by hand until a 2 inchthickwood
block(C), (Figure 32-1), can be inserted,as shown,to
holdgear in retractedposition.
A. Remove cotter key and nut at springconnecting
link(F), (Figure 32-1).
B. Removegear retractionspring (A) at (F), (Figure
32-1), by attachingspringinstallationtool (B), PIN GSE
030012, (old PIN was 8186) using an AN3-12A bolt
(E). Remove grease fitting pdorto usingtool.
NOTE
Apply MIL-G-23827 grease to bolt at (F) for
better rotation of Link (D).
8. Extend gear three to four inches from down-lock
position and secure.
9. Remove six mounting bolts from rear gear
trunnionshatt mounting block assembly at stubspar.
12-98
32-00-00
5
SERVICE AND MAINTENANCE MANUAL
M2OJ
2. Check main gear up against bumper pads.
3. Normally once the doors are installed at the
factory no further adjustment should be required.
However, should the inboard doors be removed for
any reason the followingdgging procedureshould be
usedwhen reinstallingthem:
A. Disconnectoutboard gear doors at the forward
and all linkages (B) (Fig. 32-2).
APPLY MIL-G-23827
GREASE TO BOLT
FOR ROTATION OF
LINK =D"AT =F".
• 03 IH.
t 3 iN.
"_"
l
C._.
E
- ---...
_
|
___S._
•
'
F
""-"
MOONEY AIRCRAFT CORPORATION
D
J-
J" Jk
iJ'_l
rP
skininboard
and
fairgear
witheadng
the should
aftedge
bubble
fairing.
Spacers
(A)
the
C.
Forward
be
and
tight
aR
trailing
the
edge
wing
of
B. Raise
geardoor
electrically
to
the
fullagainst
up position.
to
obtain a good fit with
no bindingor
distortionwith
(Figure32-2)should
be added
or removedas
required
be usedas spacers.
4. Reconnect outboard gear doors and check that
the forward edge of outboard gear doors are falrea
with wing skin/wheel well opening and that there is no
binding or distortion where links attach to door.
5. If adjustments are required, adjust outboard gear
door rod ends (B)(Fig 32-2) at forward or ett linkages
the
gear in the
UP gear
position.AN960-10
washers
may
as required.
Extend
to adjust links, then
retract
to
checkadjustment.
=
_.....
GEAR RETRACTION SPRING REMOVAL
FIGURE 32-1
10. Slide out aft bearing block.
11. Slide front bearing block aft and remove.
12. Slide gear assembly aft until clear of front beadng,
and carefully remove gear assembly from wing.
13. Identify all components removed, and DO NOT
intermix right and leRgear components.
14. DO NOT attempt to repair any heat treated
component of main landing gear assembly.
32-10-02
',
-MAIN GEAR INSTALLATION
1. Lubricate wheel beatings, retraction linkage, and
fore and att trunnion beadngs pdor to installation (refer
to Section 5-20-07 for recommended lubdcants).
2. installation of main gear is the exact revereat of
the main gear removal procedure.
3. Check fore and aft movement of gear in bearing
blocks, Maximum allowable movement is .020. Shim
excess by inserting shims at rear block (maximum of
any 2 shims).
4. Temporary attach gear door link _odsto gear leg
brackets.
5. Retract gear while checking for binding in door
linkage and proper contact of gear door edges with
wing. DO NOT make final gear door adjustments until
gear has been rigged (Ref. 32-30-02).
32-10-O3
- MAIN GEAR DOOR RIGGING
•
(24-0001 thru 24-2999 and 24-3079 thru 24-TBA)
1. Raise aircraft on jacks.
NOTE
Gear system must be properly rigged prior to
gear door rigging, see Section 32-30-01.
32-10-02
6
MAIN GEAR DOOR ADJUSTMENT POINTS
FIGURE 32-2
(SIN 24-0001 THRU 24-2999 8, 24-3079 THRU
24-TBA)
32-10.-04
, MAIN GEAR DOOR RIGGING
(24-3000 thru 24-3078)
1. Raise aircraft onjacks.
12-98
MOONEY AIRCRAFT CORPORATION
M20J
NOTE
Gear system must be properly rigged prior to
gear door rigging, see Section 32-30-01.
SERVICE AND MAINTENANCE MANUAL
3240-05
- INBOARD GEAR DOOR RIGGING
(24-3000 thru24-3078)
1, Adjust inboard door link to close doors with =0"
gap. Doors must be closed with gear extended and
retracted. If door is not closed in both positionsrefer to
landinggear dggingprocedures in Section 32-31-03.
2. Normally once the doors are installed at the
factory no further adjustment should be required,
However, should Mid-Gear doors be removed for any
reason the following rigging procedures should be
used when reinstallingthem:
A. Disconnect outboard doors at forward and aft
linkages(El)(Fig. 32-2A).
B. Disconnectinboard doors at the forward linkage
and springs(A) (Fig. 32-2B).
C. Raise gear electricallyto the fullUP position,
D. Forward leading edge and aft trailing edge of
Mid-Gear Door should be tight againstthe wing skin .
Spacers (A) (Figure 32-2A) should be added or
removed as required to obtain a good fit with no
bindingor distortionwith the gear in the UP position .
AN960-10 or AN970-3 washers may be used as
spacers.
3. Reconnect outboard and Mid-Gear doors and
check that the doors are faired with wing skin/wheel
well opening and that there is no bindingor distortion
where links attach to door. Adjust linkage if required
(Fig. 32-3A), Extend gear to adjust, then retract to
check adjustment.
4. Check main gear overcenter preload torque for
proper values. Re-dg entire LDG system, if necessary.
Any adjustmentto rod end on retract tube (L) Fig
32-5) and rod endon retraction tube (V) (Fig. 32-9) is
at a 2 to 1 ratio, respectively; this adjustment will
changerigging values,Recheck preloadvalues.
EXAMPLE: (1) The door is open a small amountwhen
gear is DOWN, but closedwhen gear is UP. Adjust by
turningretract tube (V) rod end IN 1/2 turn, and retract
tube (L)(Fig. 32-5) rod end OUT 1 turn.
EXAMPLE: (2) The door is closed when gear down,
but open a small amountwhen gear is UP. Adjust by
turning retract tube (V) rod end OUT 1/2 turn, and
retracttube (L) (Fig.32-5) md end IN 1 turn.
2. Tightenjamb nuts and connect springs on inboard
gear doorbettcranks(A)(Fig. 32-2B).
/
/
V
/
MAIN GEAR DOOR RIGGING - FIGURE 32-2B
I
I
i
.
MID-GEAR DOORADJUSTMENT POINTS
FIGURE 32-2A
(24-3000 THRU 24-3078)
this rig
may
resultshut
in higher
actuator
loads. as
DOnot
doors
more than
necessary
3. Adjust outboarddoor link to close gap at leading
edge of door. If the dooris rigged too tight, the skinwill
be under stress (concave) at the point where the
linkageis attachedto the door. It could also causethe
midand inboard doors to gap open.
12-98
32-10-05
7
SERVICE AND MAINTENANCE MANUAL
M20J
4. Cycle gear manually and electrically while
inspecting for clearances Re-check MLG system
riggingvalues.,
5, Remove aircraftfromjacks.
6. Returnaircraftto service,
NOTE
To remove INBOARD GEAR DOORS use a
sharpened punch less than .093 dia. or a short
piece of hinge pin to open the crimped hinge
assembly pin hole.
32-10-06
INSTALLING ASSIST BUNGEE
(560213-501)
(24-3000 THRU 24-3078)
1. Retract gear.
2. Pull gear down with emergency extension until
main retract bellcrank and md end bungee line up.
InstallAN3 bolt, washers & nut through Helm rod end
beadng and AN4 bolt, washers & nut through block.
Torque and safety.
MOONEY AIRCRAFT CORPORATION
32-20-00
- NOSE GEAR AND DOORS
32-20-01
- NOSE GEAR REMOVAL.
1. Raise aircraftonjacks.
2, Remove exhaustcavityfaidngs,
3. Partially retract gear as described by Section
32-60-10.
4. Remove firewall nose gear box (if needed) to gain
accessto bolts.
5. Disconnectlink (A) on nose gear truss assy.
(Figure 32-3).
6. Disconnectnosegear steeringhorn link(B)
(Figure 32-3).
7. Remove left and rightgear mountingbolts(D) and
(E)(Fig 32-3) from tubular structure and nose gear
trussassembly.
a
NOSE GEAR RETRACTION TUBE ADJUSTMENT
POINTS - FIGURE 32-3
9. DO NOT attempt to repair any heat treated
componentof nose landinggear assembly.
32-20-02
- NOSE GEAR INSTALLATION
ASSIST BUNGEE - FIGURE 32-2C
(24-3000 THRU 24-3078)
CAUTION
Bump gear up, CAREFULLY, just to take the
load offthe 3/16 in. installation pin at (B).
Remove pin from (B) (Fig. 32-2C).
1. Lubricatewheel bearings, retraction linkage and
left and rightmountbearings.
2. Installgear in reverse order of removal procedure.
3. With bungee installed recheck pre!oad per steps
30 thru34 of Section 32-31-03.
32-10-06
8
12-98
MOONEY AIRCRAFT CORPORATION
M20J
32-20-03
- NOSE GEAR DOOR RIGGING
1. Raise aircraft onjacks. (Refer to Section7-10-00.)
NOTE
Gear system must be properly rigged prior to
gear door rigging, see Section 32-30-03.
SERVICE AND MAINTENANCE MANUAL
completely. Check for any tire interference as tire
enterswheelwell.
3. Closethrottleand confirmgear hornsounds.
2. Adjust gear door link rods (H) and (J) (Fig 32-3)
to obtai_pmperdoorfltwhen closed.
3. To increaseor decrease nose gear-uptravel in
wheel well, adjustboth eccentricson trunnionbearings
4. Inspectgear doors for proper closing. Referenc
Section32-10--03, 3C., 32-10-04, 2,D, or 32-10-05, 1.
Lowergear to fullyextendedposition.
5. With zero airspeed place gear switch in UP
position.Gear hom shouldsoundregardlessof throttle
position,both gear positionlights and safety by-pass
switchwill illuminate.
(J) (Figure 32-4) as required.
6. Push RED gear safety by-passswitch and holdIN
to partiallyretract gear.
7. Pull=GEARACT circuit breaker.
F
A. Measure nose gear bungees (Figure 32-8).
/
-'1/
_
"_G,,
. , .,
_'_
stopping extension the moment the GREEN Gear
Extend
gear
manually
(See in
Section
32-30-04)
8. B.
Checknose
gear
overcenterpreload
as follows:
Down
Light
comes
ON.
Gearswitch
down
position.
_,
"'_'J.'_'7 _ _,/""/
C. Measure nose gear bungee springs. Deflection
.070 inches for each bungee (Fig 32-6). (.010 to .030
inch for M20J with Dukes Actuator PIN 1057-00-56).
D. If spring deflection is not within prescribed limits,
adjust tube rod ends (F) (Fig 32-4) @ (G) in
incrementsof 1/2 turns as required.
==.,.,-,-K
A Place rigging tool (T) PIN GSE030007 (Fig
32-9)" on retraction truss. Hold tool stationary by
placing
thumb
rear
end of tool
at (S)
and press
9. Check
mainon
gear
overcenter
preload
asfollows:
forward.
__
B. Place 10" torque wrench (R) on rigging tool.
Place thumb on wing bottom;applyforce untiljoint (4)
breaksopen slightly.Insertshim stock(.005 to .008 in.
thickness)between link and trussat (P). Release force
on wrench.
NOSE GEAR RETRACTION TUBE & DOOR
ADJUSTMENT POINTS - FIG. 32-4
NOTE
Eccentrics permit nose sheel to move quicker
to clear nose gear doors & also will allow nose
wheel to be positioned further or less further
into nose wheel well.
CAUTION
Nose gear overcenter preload must be
rechecked after any
adjustment to nose wheel
eccentrics.
4. Readjust nose gear door linkage (K) as required
after eccentricshave been adjusted. (Fig 32-4).
32-30-00
- EXTENSION AND RETRACTION
32-30-01
- GEAR SYSTEM OPERATIONAL
CHECK
(S/N 24-0084, 24-0238 thru 24-TBA)
1. Raise aircraft on jacks. (See Section 7-10-00).
2. With Master Switch ON and gear switch in UP
position apply pressure to pitot tube (see Section
32-60-01). Verify gear retraction occurs at 69 MPH +/5 MPH (60 +/- 5 KIAS). Allow gear to retract
C. With fingers on torque wrench and thumb on
wing bottom apply force on wrench while maintaining a
pulling force on shim stock. Read torque value on
wrench at the exact moment the shim stock pulls
loose. Torque valueshouldbe 250 to 280 inchpounds.
D. Repeat on other main gear.
E. If preload is notwithin prescribedlimitsproceed
to applicable SIN main landing gear rigging
proceduresin Section32-31-03.
F. If main gear preload needs re-adjusting, the
nose gear bungees should be re-checked per 8,(C)
above. On SIN 24-3000 thru 24-3078 proceed to
Section32-30-03 for nosegear riggingprocedures.
NOTE
When gear overcenter preload check is
completed, electrically extend the gear and
check the nose gear tube bungee springs to
assure they have not compressed completely
resulting in no remaining deflection. This would
indicate excessive preload or weak bungees.
12-98
32-20-03
9
SERVICE AND MAINTENANCE MANUAL
M20J
SQUAT SWITCH OPERATIONAL CHECK
(24-0001 thru 24-0237,Except 24..0084)
A
squat
switchis above
incorporated
on theNumbered
left main Aimralt.
landing
gear
assemblyof
listedSedal
The followingoperationalcheckshouldbe made:
1. Raise aircraftonjacks (see Section7-10-00).
2. With master switch ON place gear switch in UP
position.Gearshould retract normally.
3. Extendgear to downand locked.
4. Refer to Section 32-60-04 for squat switch
adjustmentprocedures,
32-30-02
-MAIN LANDING GEAR SYSTEM
RIGGING
32-30-03
- (AVIONICS PRODUCTS - 24-0378
thru 24-2999 & 24-3079 thru 24-TBA)
1. Raise aircraft onjacks and remove 3 belly access
panels locatedconsecutivelyjust aft of nose wheel well
or the one piece belly access effective 24-1418 and
later aircraft. DISCONNECT ALL GEAR DOORS.
2. Disconnect electdcal power from landing gear
actuator by pulling actuator circuit breaker. Make sure
landinggearwaming lightcircuit breaker is pushedIN.
3. Disconnect main gear retraction tubes (L) (Figure
32-5) at inboard bellcranks (M). Loosen Iocknuts (E).
Disconnect nose gear retraction tubes (F) (Fig 32-,3)at
main refraction bellcrank (A) (Fig 32-t0B). Loosen
Iocknuts (G) (Fig 32-4). Disconnect rod end beadng on
barrel nut (D) from bellcrank (A) at N (Fig 32-10B)
NOTE
Do not loosen Helm rod end bearing from barrel
nut (D) on Avionics Products actuator,
MOONEY AIRCRAFT CORPORATION
Disconnectnose and main gear door links.Check gear
for bindingat pivot pointswhile moving gear legs by
hand. Lubricate retraction system as indicated in
Section 5-20-07.
4. Positionretractionbellcrank(A) (Fig 32-10B) so that
center of forward hole in left outboard arm of the
bellcrankis 1.56 * IN. (approximately)from forwardface
oftruss at FuselageStation33. (See Fig 32- 10B).
* NOTE
This is a starting point only. This dimension
may vary to permit retraction tubes to connect
with zero preload.
5. With the bellcrank (A) (Fig 32-10B) in position,
turn barrel nut (D) on actuator until Helm bearing aligns
with holein bellcrankat (N). Installconnectionbolt
NOTE
LH & RH adjustable retraction tubes should be
approximately same length to start rigging
procedures.
6. With bellcrank in position and all gears fully
extended, adjust main and nose gear retraction tubes
sothattubescanbeslippedinplacewithzeropreload.
7. With bellcrank, retraction tubes, and the gear
positioned as indicated in step 4, set down-limit switch
striker arm (J) so that gear down light switch is just
closed and GREEN gear-down light is ON. Secure
striker arm in position.
8. Reset actuator circuit breaker and partially retract
gear (use Master Switch to control motor). Screw rod
end (E) (Fig. 32-5), on aft end of each main gear
retracting tube, OUT two (2) full turns, screw each
nose gear retractiontube rod end (G) (Fig. 32-4) IN
one (1) full turn, then slip attaching bolts back in place.
'- :°
MAIN GEAR RETRACTION TUBE ADJUSTMENT POINTS - FIGURE 32-5
32-30-02
10
12-98
MOONEY AIRCRAFT CORPORATION
M20J
9. Check nose and main gear overcenter preload
described in Section 32-30-01, steps 8 and 9. Adjust
as instructed.
10. Complete operational check descdbed in
32-30-01 steps2 3 5 & 6. Reset landinggear system
c rcuitbreaker and fullyextend gear.
11. When step 10 is complete,the retractionsystem
SERVICE AND MAINTENANCE MANUAL
between down-stop and end of barrel nut (C)
(Fig 32-7).
NOTE
Use 1 to4,560252-11 shims with 560252-009
allowance for actuator overrun after cutoff.
12. Disengage manual system.
13. Leave all gear doors disconnected, and run
gear-up electrically until main gears are .03 inches
minimumfrom bumper pads (.06 in. thk. rubberstrips
installedon W.S. 43.50 false rib). Positiongear-up limit
switchstrikerarm
(H) (Fig. 32-5) so that switch
iswith
just
is rigged for the gear-down-and-locked
position
D
'_
_r__=
B'_
strikerarm in position.The gear is nowproperlyrigged
in the gear-up position with allowance for actuator
overrunafter cutoff.
para.
8.C.
closed,
and RED gear unsafe light is OFF. Secure
14. Electrically extend gear to down-and-locked
position.Connectand adjust gear doors (refer to Main
Door and Nose Gear Door Rigging Procedures in
Section 32-10-03, Main, and 32-20-03, Nose).
15.
AdjustNose
the mechanical
down
stop,per
on32-30-01,
actuator
Recheck
Gear Bungee
Spdngs
housing,and up stop, per the followinginstructionsand
Fig. 32-7 & 32-5.
_..__
g.p
--LITBD
A"-
_[
_r_-_,,_-__..__._
_'_
MECHANICAL DOWN STOP - FIGURE 32-7
y560245
stop to achieve proper clearance as an
alternate for 560252-001, -003, -005, or -007.
C. Actuatorballnut(C)(Fig. 32-7).
(REF) Nose Gear Bungee
J VH/_JJ__ _
I_
D. 560252-011
shim (use with 560252-009 only,
maximum
of 4).
Deflection of spring _rom static length
to rigged posttton to be . 030 to . 0"/0 In.
E. AN515-6R screw*
AN936A6 LockWasher
Cryp.2 plc.) (usewith 560252-009 only).
*Use .063 longer screws with each additional shim.
(Securescrew with Blue Locktite#83-31 grade C).
NOSE GEAR BUNGEE SPRING - FIGURE 32-6
MECHANICAL DOWN STOPS
A. 560252-001
560252-003
560252-005
560252-007
560252-009
Fixed Stops
Use one dn/stop
Fixed Stops
on each side as
Fixed Stops --required (Use
Fixed Stops
existing hdw).
Adjustable
(use -011 shim)
Stop
NOTE
Tube assemblies are allowed .010 in. per foot
bend allowance.
MECHANICAL UP STOP
With gear fully retracted, adjust stop for .050 - .070
clearance between UP STOP (A) (Figure 32-8) and
retracting truss (B), then tighten set screw (C).
NOTE
B. With gear fully extended, select down stop of
proper thickness to give .050 - .100 clearance @ (B)
12-98
The main gear preload torque should not
exceed 325
inchprocedure
lb. using the
torque
wrench/shim
stock
after
electrical
extension.
32-30-04
(NON-AVIONICS PRODUCTS
ACTUATOR) 24-0001 thru 24.0377)
1. Raise aircraft on jacks (refer to Section 7-10-00,
and removebellyaccess panels.
32-30-04
11
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
2. Partially retract gear (Refer to Section 32-10-01).
Disconnectmain gear retractiontubes (L)(Fig 32-5) at
F'WD
OUTBD
_
,_,
_
Disconnect nose gear retraction tubes (F)(Fig 32-,3)at
inboardbellcranks
(M). Loosen
Iocknuts(E).
the
retraction bellcrank
(A) (Fig
32-10A). Disconnect
nose gear and main gear door links. Check gear for
binding at pivot points while moving gear legs by hand.
Lubdcate retractionsystem as indicated in Section5.
3. Adjust Heim end bearing on actuator stud so that
the Heimthreaded end at (E) is 7.50 inches +.125 inch
from the far end of ball nut (C)(Fig 32-10A).
NOTE
Helm bearing is locked in position with a set
screw extending into a slot in the actuator stud.
Set screw must be removed prior to making any
adjustment (non-Avionics Prod. or Plessey).
CAUTION
Adjust Heim end only - Do not loosen actuator
set screw or Iocknut and attempt to adjust
actuator stud.
"_
MECHANICAL UP STOP - FIGURE 32-8
1.56
Checkdistancefrom the Helm bearing centedineto the
face of the actuator.Dimensionmust not exceed 2.35
inches, readjust making sure that 7.50 dimension is
within the +.125 tolerance. Align slot in actuator stud
with setscrew in Heim bearing shank. Loctite Heim
beadng setscrew and secure. Tighten Iocknut. Rotate
actuator barrel until ball return (or returns) on ball nut
(
W
Z
V
R ETRACTI O N
LINK
NG
R
RETRACTION
TOOL
TORQUE
TRUSS
G
050007-100
WRENCH
LEFT MAIN GEAR
(VIEW
LOOKING
FWD)
MAIN GEAR RIGGING TOOL APPLICATION - FIGURE 32-9
32-30-04
12
12-98
250 28(
INCl LBS.
FoR
cE
MOONEY AIRCRAFT CORPORATION
M20J
bC) is facing actuator motor. Reattach Helm to
ellcrank,
NOTE
When installing helm bearing end in the
bellcrank,
position
freelyscrew.
so there
willONE
be no
lateral bind
on theit jack
Place
AN960-716L washer NEXT TO THE BALL JOINT,
(can be placed on either side) and shim
remaining space with AN960-616 washers. This
installation will prevent helm bearing from
twisting too far, yet provide adequate
movement,
NOTE
Previous installation may have contained one
large AN960-916 washer next to the balljoint.
This washer MUST NOT be reinstalled, the
AN960-716L smaller and ththnerwasher
described above is used as a replacement,
4. Position
(A) outboard
(Fig 32-10A)
that
center ofretraction
forward bellcrank
hole in left
arm so
of
bellcrank is 1.56 * inches from forward face of tress (B)
at FUS. STA. 33.0 (Fig 32-10A). This can be
accomplished by engaging the emergency gear
extension system hand crank and turning to position
the bellcrank,
See SI M20-89B for Dukes Actuator Drive
Coupling Inspection.
• NOTE
This is a starting point only. This dimension
may vary to permit retraction tubes to convert
with zero prelead,
II
"----"
FWD
\\--
C
Disengat_e
I rT,_--._
FL_CC_t"
SERVICE AND MAINTENANCE MANUAL
5. With bellcrank in position and gear fully extended
and overcenter, adjust main gear retraction tube rod
ends (E) (Fig 32-5) and nose gear retraction tube at
rod ends (F) (Fig 324) so that tubes can be slipped in
place with zero preload. Reattach ends of retraction
tubes at the belicrankand slip boltsin place.
6. Disconnect electrical power from landing gear
actuator by pullingcircuitbreaker. Make sure landing
gear warninglightcircuitbreaker is pushedin.
7. With bellcrank, retraction tubes, and the gear
positionedas indicated in step 5, set down-limit switch
strikerarm (J) (Fig 32-5) so that gear-downlightswitch
is just closedand green gear-down light is on. Secure
stdkerarm in position.
8. Use manual crank to padially retractgear. Screw
rod end (E) (Fig 32-5) on aft end of each main gear
retractingtube, out two full turns, then slip attaching
boltsback in place.
9. Manually extend gear; stop extension just as
greengear-downlightcomes on.
10. CHECK PRELOAD TORQUE on each main gear
per Section 32-30-01,
CAUTION
Check that bungee springs are not "bottomed"
out. Torque difference between each gear
should not be more than 25 IN. LBS. If torque is
not within limits, repeat steps 8 and 9 to adjust
rod ends one-half turn in or out as required.
11. Partiallyretract gear with manual crank, screw in
each nose gear retraction tube rod end one full turn,
then slipattachingboltsback in place.
tube and then extend gear manually, stopping just as
12. Check
length
of nose
gear
green
gear-down
light
comes
on. bungee spring in each
13. Check length of nose gear bungee spdngs in
gear-extended position. Nose gear bungee spdng
.030 to .070 inch for each bungee (Fig 32-6). (.010 to
.030 inch for M20J with Dukes Actuator, PIN
_K.__.-_
deflection fromRecheck
zero load main
condition
12) must
be
1057-00-5G).
gear(step
preload
torque
"_==:::'=='==';":'_=_="value. If nose gear bungee spdng deflection and/or
,:._..._.:_.:_main gear preload torque is not within prescribed limits,
7.50 + • i25zN.,ii_ii_iii}i
!_
adjust retraction tube rod ends in increments of 1/2
-....'_='_:_"_"
turn as required. Use manual crank dudng
.ii._ii_i;i_r
readjustment, and stop extension just as gear-down
light comes on. (When step 15 is complete, the
retraction
system
is
dgged
for
the
gear-down-and-locked position with allowance for
actuator overrun aftercutoff.)
14. Disengage manual crank and reconnect landing
gear system circuit breaker.
15. Leave all gear doors disconnected, and run gear
up electdcaily (ref. Section 32-60-01) until main gear
each side is .13 to .03 inches from bumper pads (see
•
Fig 32-1). Position gear-up limit switch stalkerarm (H)
---(Fig 32-5) so that the switch is just closed and the red
intransitlight goes out. Secure striker arm in position.
The gear is now properlyrigged in the gear-upposition
with allowancefor overrun after cutoff.
i
MAIN GEAR RIGGING - FIGURE 32-10A
12-98
32-30-04
13
SERVICE AND MAINTENANCE MANUAL
M20J
Extend gear to down-and locked position. Adjust gear
doom. (Ref. Section 32-10-03 and 32-20-03 for rigging
gear doors.)
16. Cycle the retraction system electrically through at
least five trouble-free test operations. Manually extend
gear, stop extension just as green light comes on, and
check main gear preload torque and nose gear bungee
deflection for limits specified in steps 10 and 13. If
values are within limits specified, the retraction system
is properly rigged and ready for use. If preload and/or
deflection is not within limits, readjust retraction tube
rod ends as required,and repeat test operations.
NOTE
Check main gear preload torque and/or nose
gear bungee deflection after extending the gear
manually and stopping just as the gear-down
light comeson. Gearpreload, after electric
extension, may vary due to inconsistency in
actuator overrun; therefore, the gear must be
only manually extended during all rigging
checks. Rigging values after electric extension
may exceed the values obtained after manual
extension,
8. Disconnect nose gear doors, outboard main gear
doors, and inboard door links. On outboard main gear
doors disconnect springs. On inboard door bellcranks,
disconnect spdngs. Loosen jamb nut (X) on retraction
tube (V) (Fig 32-9) and back off pressure on spring by
loosening adjustment nut (Y). Disconnect retraction
tube (V) from bellcrank (C) (Fig. 32-2B)
9. Position main retraction bellcrank (A) so that
center of forward hole in the left outboard arm of
bellcrank is 1.56 *** inches from forward face of
fuselagetmss at F.S. 33 (Fig32-10B, detailA).
NOTE
This dimension*** may vary to permit
connection of the retraction tubes with zero
preload at bolt hole.
17. When
gear
rigging
completed,
center
locks on
all gears
to is
ascertain
that check
none ofover
the
down lock bungee springs have compressed to solid
heightand have no remainingdeflection. If any bungee
has reached solid height, readjust system and/or
replace bungee springs,
WARNING
Lack of compliance with Mooney mandatory
Service Bulletin No. M20-177 may result in
unsatisfactory electrical extension of the
electric gear.
32-30-05
(SIN 24-3000 thru 24-3078)
1. Raise the aircrafton jacks and remove one piece
bellyaccess panel.
2. Assist Bungee Assy. Removal. Retract landing
gear untilrigging pinhole lines up on bungee assembly
and insert 3/16 in. pin.
CAREFULLY BUMP the gear UP with the gear
safety bypassswitchuntilthere is zero load on bungee
assy rod end. Remove AN3 bolt/hardware at rod end
and AN4 bolt/hardware at block and remove bungee
assy.
3. Pullthe landinggear actuator circuitbreaker OUT.
4. Loosenjam nuts (E) on the main retractiontubes
(L) (Fig 32-5); disconnect the tubes at the inboard
bellcranks(M).
5. In nose gear well, loosenjam nuts (G) (Fig 32-4)
on nose gear retractiontubes (F) (Fig 32-3 & 32-4).
6. At main retraction bellcrank (A) (Fig 32-10B)
disconnectactuator barrel nut at (N) (Fig 32-10B) and
nose gear retractiontubes (F).
7. On Avionics Products actuator, verify dimension
from rod end center to end of barrel nut housing on
actuator;,it should be 1;25 +.000/-.010. Adjust rod end
bearing, if necessary and secure with set screw and
jam nut. Plessey actuatorsare not adjsutable.
32-30-05
14
MOONEY AIRCRAFT CORPORATION
10. With main retraction bellcrank (A) held in
position,turn actuator barrel nut until rod end bearing
alignswith hole in bellcrank; install connection bolt at
(N) (Fig. 32-10B).
11. Position bellcrank(C) (Fig. 32-2B), so centerof
attachpin(D) in top leg is 1.35 inchesfrom bottom side
of spar cap (E). This will be the startingpositionwhen
landing gear is in down and locked over center, with
outanypreloadset.
12. Adjust retractiontube (V) (Fig 32-9), at rod end,
wnitl it will connectto bellcrank (C) (Fig 32-2B) with
zero preload. Install connection bolt/hardware, leave
loose.
13. Adjust rod end on retraction tube (L) (Fig 32-5)
so attach hole is aligned with inboard bellcrank at (M).
Install connectionbolt/hardware.
14. Disconnect retraction tube (V) at bellcrank ((3)
rod end; position disconnected gear full down and
locked over center. Both LH and RH landing gear
should be in this configuration at this time.
15. PUSH landinggear actuator C/B - IN.
16. Turn MasterSwitch- ON.
17. Extend main gear actuator to fully extended
position.Make certain lugson main retract belicrankdo
no contact fuselagetube, floorboard or actuator barrel
nut Ifthere is any contact, runactuator back upslightly.
18. There should be .050 to .100 inch clearance (B)
obtained between actuator barrel (C) (Fig 32-7) and
mechanicaldown stop (A). Shims (D) (.050 thk.) (Fig
32-7) may be added or deleted to mechanical
downstop(A) (4 max).
19. Cycle landinggear UP. Run actuatordown and
recheck retraction bellcrank clearance at F.S. 33.
Check clearance of bellcranks (M) (Fig 32-5) and
center section.
20. Reconnect retractiontubes (V) (Fig 32-9). With
main gear fully extended, if necessary, adjust main
gear retraction tubes (L)(Fig 32-5) so they can be
re-connectedwith zero preload.
21. Adjust nut (Y) (Fig 32-9) until main gear is
preloaded.Preload is correctwhen a "CLEAN BREAK"
can be felt when pushing up on retraction link at (P)
(Fig 32-9).
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
2_7
/-
"-"d _"--1.56IN (APPRnX.)
]DETAIL
A
LANDING GEAR ACTUATOR
ADJUSTMENTS
22,NOSE GEAR RETRACTION TUBES ARE TO
REMAIN DISCONNECTED at the main retraction
bellcrank (A) (Fig 32-10B) dudng remainder of
procedure,
23. Place landinggear switchin UP position,
24. Push RED gear safety by-pass switch IN
INTERMITTENTLY to =BUMP UP" (retract) landing
gear until lelt main tire just contacts bumper bracket
which covers bulbstringer in wheel well. Make certain
actuator barrel does not contact main retract bellcrank
inthe UP position,
25. Set UP limitswitchstdker arm (H) (Fig.32-5) so
GEAR UP limit switchis just CLOSED and RED "GEAR
UNSAFE"light is- OFF. Securestdker arm in position,
26. Loosen
set screw
(C)32-8)
Figure
Adjust
mechanical
up-stop
(A) (Fig.
for a 32-8.
clearance
of
.050 to .070 inches at main retractiontruss (B); tighten
set screw(C).
27. Reinstallassistbungee per Section32-10-06.
28. Using emergency gear extension, move gear
downuntil GREEN, gear down lightJUST illuminates.
29. Turn Master Switch - OFF.
30. Place riggingtool (T) (Fig.32-9), P/N 030007-100,
on retractiontruss assembly (G). Hold tool stationaryby
pushingat point(S) towardmaingear leg.
c
:.,'c/_,'cv'u'o,
DETAIL
B
- FIGURE 32-IOB
NOTE
The left main geartrusswill probably lock over
centerfirst. Continuetoslowlylowerthegear
manually while monitoring the compression of
bungee spring on retraction tubes (V
)(Fig.32-9). If the spring coils (W) are fully
compressed, retract tube (V) must be removed
from aircraft for modification. Dismantle the
bungee portion of tube (V); remove one spacer
washer (Z) and reassemble. Reinstall the
modified retraction tube and complete above
overcentar requirement. Removal of additional
spacer washers may be required prior to
obtaining the final configuration for the
retraction tube (V).
31. Place 10 inch torque wrench (R) on riggingtool
('1)
as shown in Fig.32-9 and apply an unlockingforce
to retractiontruss.
32. When joint at (4) breaks open slightly,insertshim
stock (.005 to .008 in. thickness)between retractionlink
andtrussat (P), releaseforceon torquewrench.
33. While applyinga pullingforce on the shim stock
exertan increasingunlockingforce withtorque wrench.
34. Read torque wrench value at the EXACT
momentshimstock pulls loose.
35. Repeat steps 30 through 34 on the other main
landinggear leg.
36. Use adjusting nuts (Y) (Fig. 32-9 ) on retract
tubes (V) to equalize breakaway torque values within
10.0 inch Ibs. Adjust the torque to 250 to 280 inch
pounds.
12-98
32-30-05
15
SERVICE AND MAINTENANCE MANUAL
M20J
37. Turn Master Switch ON.
33. RUN GEAR DOWN ELECTRICALLY AND
CHECK THAT TORQUE VALUES DO NOT EXCEED
325 INCH POUNDS USING THE TORQUE
WRENCH/SHIM STOCK METHOD.
MOONEY AIRCRAFT CORPORATION
15. Measure nose gear bungee assemblies,
dimension "P", as shown in Fig 32-6. If the springs
have deflected less than .030 inches or more than .070
inches from the static dimension (as recorded in Step
2) adjust length of bungee assemblies to bdng
deflectionwithintolerance.
LANDING GEAR WARNING ADJUSTMENT
32-31-02
1. Check that landing gear warning light circuit
breaker is pushedIN.
2. Check
pulled
OUT.that landing gear actuator circuit breaker is
3. Turn Master Switch - ON.
- EMERGENCY GEAR EXTENSION
SYSTEM RIGGING.
DISENGAGE RIGGING:
(24-0084, SIN 24-0378 & ON)
1. Insert cable thru hole in actuator disengage arm,
(B) (Fig 32-10B).
4. Set DOWN limit switch striker arm (J) (Fig 32-5)
so that gear downlimit switchisjust CLOSED and the
GREEN,
GEAR DOWN lightis ON. Secure stdker arm
in position.
5. Turn Master Switch- OFF.
NOTE
The main gear preload torque should not
exceed 325 inch lb. using the torque
wrencWshim stock procedure after electrical
extension,
32-31-51
- NOSE LANDING GEAR RIGGING
PROCEDURE (24-3000 thru 24-3078)
1. Check eccentric bushings (J) (Fig 32-4) on gear
truss assembly to be installed with bolt hole in upper
forward position.
2. Adjust nose gear retraction tubes (F) (Fig 32-3),
so they can be reconnected to the main retraction
bellcrankwithzero preload.
2. With red lever
(Fig 32-11A)
in full disengaged
position(down
and(1)
latched)
push actuator
disengage
arm (B) to full forwardpositionand applyapproximately
5 Ibs.pullto cableto removeslack.
3. InstallD222 wire stop, (C) tighten nutand connect
spdng(E) to clevispin, (D).
4. Lilt RED leverand pull"T" handle (2) (Fig 32-11A)
aside; re-engage RED lever. Check manual extension
systemto verifythat it is fullydisengagedby pulling=T"
handle;no resistanceshould be felt. If a resistance is
felt, check cable routingthrough pulleys3 and 4 (Fig
32-11A) to vedfy if it is cable routing or actuator
resistance.
AVIONICS PRODUCTS ACTUATOR
(SIN 24-0084, 24-0378 THRU 24-TBA)
The eccentric bushings may require rotation to
a new position in order to meet the zero preload
condition.
NOTE
¢43t'B_
.
l
. .._._-_
(Fig 32-6) and record for future reference.
4. Pushlandinggear actuator C/B - IN.
5. Place landing gear switchin UP position.
6. Turn Master Switch - ON.
7. Push RED, GEAR SAFETY BYPASS SVVITCH-
,¢n_,=-_¢,_,_-_c
_,uE
3. Measure nose gear bungees dimension (P)
____
8. Turn Master Switch - OFF.
IN and hold it to partially retract landing gear;, release
9. Pull landing gear actuator C/B - OUT.
switch.
10. Screw each nose gear retractiontube (F) (Fig
32-3) IN (clockwiselookingtoward front of aircmlt) one
(1) full turn, then re-attachto main retractionbellcrank.
11. Place landinggear switch in DOWN position.
12. Push latch(5) (Fig 32-11) FORWARD on manual
emergency extension controls (on floorboard).
13. Pull RED lever (1) (Fig 32-11) back and upward
to engage manual emergency gear extension system,
14. Pull "T" handle (2) UP (slowly until engaged) and
return itto its original position. Continue this procedure,
stopping when the gear down light JUST illuminates.
32-31-01
16
__'
_=.__. _
_-=-
•
EMERGENCY GEAR SYSTEM - FIGURE 32-11A
5. Move RED lever to full UP position; pull "T" handle
slowly to verify manual extension system is engaged.
Resistance should be felt at once.
6. Replace "T" handle under RED lever and return
RED lever to disengage position, (down and latched).
Manual extension system is now rigged.
12-98
II
I
MOONEY AIRCRAFT CORPORATION
M2OJ
SERVICE AND MAINTENANCE MANUAL
Rigging
of
Manual
Emergency
Landing
Gear
32-11B):
1. WCLh
aircmltonjacks,insurethatdisengage operating
handle(1)(Fig 32-11B)in the cabin is in the full forward
Disengage
positionand that
Unit the
ascable(2)(Fig32-11B)is
Follows (Ref. Fig 32-10A
insertedthru
and
holein existingboltattachedat (K)(Fig32-10A).
•7S.._._ _]/_'"
_,CTUATOR
"
_.
-
_-_.
1
_.
"\
2. V_thbolt
unit(K)
full engaged
position(K full
aft)apply
and
existing
(M) in
inserted
thru disengage
arm,
_' '/
connect spdng.
3.
readjust
stops
(L) and
4. Tighten
Turn crank
(3)
(Fig
32-11B)
to assure
full
approximately
5nut
Ibs.(M),
pullto
cable
to wire
removeslack.
3
5. Move disengage operating handle (1) to full aft
position and operate hand crank (3) to assure full
disengagement.Returnhandle (1)to full forward position.
6. Rigging is nowcomplete.
_
(_x_'
i
(SIN 24-0001 THRU 24-0377,
NOTE EXCEPT 24-0084)
_"_
_'_
EMERGENCY GEAR SYSTEM - FIGURE 32-11B
DISENGAGE RIGGING:
(S/N 24-0001tbru 24-0377, Except 240084) (Other
than Avionic Productsor PlesseyActuator)
PLESSEY
SEE SERVICE
ACTUATOR
INSTRUCTION
inspect
rubber
drive
coupling
between
motor/gearbox and jackshaft/gearbox for signs of
During
200 hour
gear inspection,5-20-O6,3,L,(1),
deterioration,
hardness
or wear. Loosen and
remove 2 nuts/washers/bolts from
bracket
connecting the two components. Separate motor
assy. from jackshaft assy. Remove rubber coupling
from which ever shaft it remains on and inspect,
Replace if damaged or deteriorated. Reassemble
motor assy. to jackshaft assy. and secure all
M20-92
9 MOb. IDENT. PLATI
8
"">
i3 EATIqN ACTUATE]R
le_
SMbt32-14
3 __"
7
It
SEESERVICE
INSTR.
HaO-52B
(P/N IOPO00)
LANDING GEAR ACTUATOR(S) [EXPLODED VIEWS] - FIGURE 32-12
12-98
32-31-02
17
SERVICE AND MAINTENANCE MANUAL
M20J
components. Complete gear inspection per Section
5-20-06,3,L,(1).
See SI M20-89B for Dukes Actuator Drive Coupling
Inspection.
NOTE
Plessey
Actuators
should
be lubricated
every
2000 cycles w/MIL-G-81322
grease. Run
actuator to mechanical "extend", fill tube cavity
with grease thru MS15001-1 grease fitting until
old grease is purged from screw assy. Remove
old grease from & relube exposed screw
threads. Run actuator to within approx. 0.5 inch
of mechanical "retract" & remove major excess
grease extruded from ball nut assembly during
this retraction step.
32-31-03
- LANDING GEAR ACTUATOR, PIN
102000(*), CLUTCH SPRING
REPLACEMENT,
MOONEY AIRCRAFT CORPOFLATION
3. Reinstallrecoiler assemblymake sure to fully seat
gear, bearing, and gear tang into manual drive slot of
recoilerassembly.
4. ApplyLoctiteGrade A (Catalog Number 88-31, not
suppliedin kit) to four new screws suppliedand install;
take care to use the two longest screws in bottom
holesof item (5).
NOTE
Torque to approximately 10 - 12 inch pounds.
5. Reinstallcable supportbracketand retainingnuts.
6. Retest unit for proper electrical and mechanical
operation.
7. Installmodificationplate adjacentto I.D. plate (first
1000 hours only). Mark the first block of modification
plate with the figure "1" using metal stamp or etching
tool. Mark plate at each succeeding clutch spring
replacementwith the next consecutivenumber.
(* currently -1, -2, -3, -4, & ON)
KIT No. A10-85.
Landing gear actuator clutch spring replacement is
mandatoryat each 1000 hoursof aircraft operation.
DISSASEMBLY - (P/N 102000(*)
1. Remove two nuts, item (1). Note positionof cable
supportbracket, item (2), and remove (Figure 32-12).
2. Remove manual extension system disengage
cablefrom actuatordisengage arm.
3. Remove two long screws,item (3).
4. Remove two shortscrews, item (4).
5. Remove recoilerassembly, item (5).
6. Remove gear assembly, item (6), from clutch
housing, item (8), by rotating gear and pulling with
slightto moderatepressure.
7. Remove two screws, item (7), and remove
housing, item (8), clutch spring item (9), and gear
assembly,item (10) from actuatorbody.
8. Remove clutchspring, item (9), from housingusing
gear assembly,item (6), as removal tool. Insert,item(6),
intospring from flangedend of housing;rotateCCW and
pull slightly. Alter disassembly, clean clutch gear
thoroughly.Discardremovedscrews(3) & (4).
CAUTION
Use extreme care to prevent ball bearing from
dropping out of recoi er assembly, avoid
damage to gear and do not allow dirt to enter
clutch housing bore.
32-31-04
- LANDING GEAR ACTUATOR, PIN
102000-(*), RECOILER SPRINGS /
CABLE AND DRUM ASSEMBLY
REPLACEMENT
1. Carefullyseparate pulleyhousingfrom recoiler
assembly(5) by removing screws (14). Retain pulley
onshaft.
* All dash no'sapplicablefor PIN 102000(*) actuator.
2. Slide pulleydrum and cable offshatt.
3. Removethe two (2) recoilersprings, and two (2) of
the three (3) springspacers leavingthe thirdspacer in
housing. Be certain that spacer is in place before
installation of two (2) new recoiler springs and
previouslyremovedspacers.
4. Install new recoiler springs placing a spacer
betweeneach spring and overtop spring.
IMPORTANT - Recheck properinstallationof springs.
NOTE
When looking at recoiler assembly with shaft
end toward you, the spring tabs in the housing
slot should curve to the right as shown (Figure
32-12).
5. Inspect cable for sheathing damage. Replace
cable if sheathing is cut or stripped. Measure overall
cable length prior to reassembly. Cable length should
be 31 1/2" +/- 1/2" long.
6. Slide drum ontoshaft; be certain that spring detent
on drum engages both recoiler springs by slightly
rockingdrum end.
9. See 32-30-06 procedure prior to reassembly for
additionalmaintenance if needed,
7. When full engagement is obtained wrap cable
arounddrum
n a clockwisedirection-leaving2" to 5" of
cable free of drum.
ASSEMBLY -PIN 102000(*)
1. Lubricate gear and new clutch spring thoroughly
withlube(MIL-G-81322) poly-lube.
2. Using gear to rotate spring, insert clutch spring
into bore until fully seated,
6. Align slot in pulley housing with cable and slide
pulleyhousingover cable and drum assembly.
9. Holding the housings together, pull properly
aligned cable several times to ensure the absence of
binding conditions. Measure cable length from side of
housing. At full extend, the length of cable should be
29" minimum. In retracted position, cable length should
be 5" to 8" long.
NOTE
Be sure spring around
is all thecam.
way in and seated
32-31-03
18
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
NOTE
Cable
length
in retract
may be
adjusted
shorter
or longer
by position
holding clutch
with
the
1. Pull landing gear circuit breaker.
2. Move landinggear controlswitchto DOWN position.
finger of one hand (to prevent shaft rotation),
and then with the other hand, rotating pulley
housing one full turn CW (to shorten) or CCW
(to lengthen). Retention of clutch with finger
will not allow pretensioning of springs. Slight
spring tension should be noted starting at 8" to
10".
10. Bronze clutch (13) should be inspected for
damage or wear at slot where gear assembleengages
duringmanualextensionof the landinggear.
11. If damaged or worn, remove pin (11) from
disengage arm (12) and slide disengage arm out so
bronzeclutch(13) can be pulledfrom itsddveshalt,
12. Replace bronze clutch and reassemble
disengagearm into recoiler assembly,
13. Attach clutch recoiler assembly to actuator gear
housingwith the four (4) screws removedin 32-30-05
(suppliedin clutchspring kit).
3. Push crank engage handle forward to engage
drive mechanism.
4. Crank handleclockwiseto lower gear. The gear is
down and lockedwhen green down-gear indicatorlight
is on and when the lines on the visual gear position
indicatoron thefloorboard are aligned.
CAUTION
DO NOTretractgearmanually; use electrical
system to retract gear. DO NOT operate gear
electrically with hand crank engaged.
CAUTION
To prevent partial engagement and subsequent
damage to drive spline or flexible shaft, check
disengage arm (K), Figure 32-10A. This is
covered under disengage rigging. (Section
32-30-04).
32-31-06
FINAL CHECKS
( 24-3000 thru 24-3078)
1. Raise and lower the landing gear through five
complete cycles, pausing after each cycle to check
re-quired tolerances and dimensions and annunciator
lightindications.Make certain that no bungee spdngs
are compressed to a solid height and that nose gear
tire clearstop of wheel well a minimum of .25 In. when
landinggear is retracted.
Make adjustments per the above procedures, as
required, to correct any discrepancies.
2. Re-torque all jam nuts.
3. Reattach main and nose landing gear door links.
Check to see that nose and main landing gear doors
are still rigged per paragraph 32-10-04.
32-31-05
- MANUAL EMERGENCY GEAR
EXTENSION SYSTEM (T-HANDLE)
(SIN 24-0084, 24-0378 THRU 24-TBA)
The manualemergency gear extension systemis used
to extend the gear only. The controlsare on floorboard
aft and between the front seats. To manually extend
the gear:
1. Pull landing gear actuator circuit breaker,
2. Move landinggear control switch to DOWN position.
3. Push latch forward with rightthumb.
4. Pull lever back and upward (engaging manual
emergency gear),
5. Pull "T" handle UP, (slowly to engage gears) then
RETURN to original position; continue until GREEN
GEAR DOWN indicator light is ON and/or the lines on
the visual gear position indicator on floorboard att of
console are aligned when viewed from directly above
the indicator (this will nromally take 12 to 20 pulls).
CAUTION
DO NOT operate landing gear electrically with
manual extension system engaged. Landing
gear circuit breaker will trip.
CAUTION
DO NOT continue to pull T-Handle after GEAR
DOWN light is ON. Actuator barrel nut may bind
on DOWN STOPS.
- MANUAL EMERGENCY GEAR
EXTENSION SYSTEM
(CRANKDOWN SYSTEM)
(SIN 24-0001 thru 24-0377, Except 24-0084)
The emergency manual override system may be used
to extend the gear. The override systemhas a flexible
shaft geared to the landing gear actuator driven by a
hand crank on the left side of the cabin panel. To
manuallyextend the gear:.
12-98
32-31-05
19
SERVICE AND MAINTENANCE MANUAL
32-32-00
M20J
MOONEY AIRCRAFT CORPORATION
- TROUBLE SHOOTING - LANDING GEAR SYSTEM
TROUBLE
Incompleteretraction.Gear
retractsto an intermediate
positionand stopsshort.
Gear will not retract at 70 to 80
MPH IAS.
PROBABLE CAUSE
REMEDY
-Bind in gear retractionsystem
becausegear is out of rig.
Malfunctionin gear electrical
cimuit, inoperativeactuating
motor,or weak battery,
Referto landinggear riggingprocedure.
Examineall movable partsfor proper
lubricationand freedomfrom binding.
Checkfor actuatorjackscrew binding
and lubricate as needed. Any
malfunction can cause the landing gear
circuit breaker to trip: therefore check
electric circuit for loose connection,
broken wires, or defective relay
switches, Recharge battery if
necessary.
-Oversize/stretched tire will not
go into wheelwell properly.
Replace with smaller diameter tire.
-Insufficient air-speed, pressure
switch inoperative, circuit
breaker tdpped or actuator ball
nut binding on DOWN STOPS.
Check pitot tube and line for
obstructions. Examine pressure switch
for proper adjustment and operation.
Reset circuit breaker.
Does gear retract using override; check
systems operation.
Gear may have been extended
manually & ball nut is tight against
STOPS; use wrench on ball nut flat to
loosen.
-Squat switch not properly
rigged. Cold weather,
-Manual engage handle in
engaged position
Adjust and check squat switch
operation. - Ref.SB-M20-196
Disengage Manual System.
Aircraft does not Track or steer
properly.
-Nose wheel location improper.
See Section 32-50-02,
Gear will extend; green
indicator-light (press-to-test) will
notilluminate,
Actuating motor extends gear to
an intermediate position,
-Lamp burned out in green
indicator-light circuit. Down-limit
switch is inoperative,
-Same causes as listed with "In
complete Retraction" above.
Replace burned out lamp. Check
indicator-light circuit and/or down-limit
switch.
Same remedies as listed with
=IncompleteRetraction" above,
Gear will extend manually, but
green indicator light will not
illuminate.
-Gear switch is not in DOWN
position.
-Lamp burned out in green
indicator light.
Place gear switch in DOWN position.
Replace burned out lamp
Manual system will not lower
gear.
-Avionic Products Actuator
internal clutch spring broken.
-Manual engage arm improperly
rigged.
-Sheared female spline in drive
connector,
Replace spring.
-Drive connector is out of rig.
Adjust control cable tension of ddve
connector.
-Any of the above or Brushes in
motor worn.
Applicable remedy listed above or
replace motor or brushes.
Gear will not retract & Landing
Gear Actuator C/B trips,
Manual system will not lower
gear.
(con't.)
LDG actuator will not.retract or
will not extend gear.
32-32-00
2O
12-98
Rig manual engage arm.
Replace drive connector assembly if
female spline is stripped.
MOONEY AIRCRAFT CORPORATION
3240-00
M20J
SERVICE AND MAINTENANCE MANUAL
- WHEELS AND BRAKES
14. Inflatetire to 30 PSI.
32-40-01
-MAIN WHEELS
The main wheels have standard brand, 6:00 x 6,
six-ply ratedtireswithstandard tubes. To remove main
wheels fromaimrafl:
15. Install wheel assembly, washer, and axle nut.
Tighten axle nut until _adng binds slightly.,back nut
offto nearest castellation,and installcotterpin.
1. Remove eitherIB or MID gear door.
2. DetachdtL_tshield.Removethreescowsandwashem.
3. Remove 2 boltsfrom brake caliper,
4. Remove wheel by removing cotter key and nut
from axle. (See Fig 32-13).
5. Slide wheal off axle.
NOTE
Position Spacers as needed to positon Brake
Disc .12 inches away from MLG leg assembly.
NOTE
When properly installed, wheel will turn with a
slight resistance.
16. Installdustshieldand IB/MID gear door.
17. Reinstallbrake caliper& safety.
CAUTION
Conduct a retraction/extension check (6 cycles)
to varify tire enters and exits whealwell without
interference. [Ref. AC 43.13-1(*) ]
(* = current revision).
32-40-02
- MAIN WHEEL DISASSEMBLY ASSEMBLY
1. Remove snap fng, (10) grease seal rings,(8) and
feltseals (9), (See Fig 32-14).
2. Remove bearings(7).
3. Completelydeflatetire.
Do not loosen wheal
WARNING
half retaining nuts before
tire is completely deflated. Failure to observe
this warning may result in bodily injury.
/--SCREW
///"_--_
///
| ]
(TYP. 3 PLCS.)
_NUT
/
_--SPACER
bolts, (5); separate halves, (3, 4) and removetire and
tube.
NOTE
Bearing cups are shrink fated; do not remove
them unless necessary for replacement.
(Federal
Specification
PS-661).
special
care
4. Remove
nuts, washers,
andExercise
wheel half
retaining
Clean allbeadng
wheel parts
cleaningfluid
in5.cleaning
cones_omughly
and felt in
dngs
to insure
thoroughcleaning.
6. Inspectal pads f_ crocks,conosion,or evidence
wear.
7. Inspect bearing cups and replace if cups are
damaged or worn. If necessary to remove bearing
cups heat wheel in boiling water for at least 30
minutes.Then remove cup by tapp ng evenly.To insta
cup, heat wheel half again; cool cup with dry ice.
Positioncup and tap lightlyto insureproperseating.
8. Polish smell burrs or nicks out of wheel halves
with No. 400 gdt sandpaper, clean thoroughly, and
refinishprotectivecoatingas requital.
g. Replsce bearing cones that showsignsof wear or
beadng fretting.
10. Repack wheel bearings and lubricateseals with
grease. Installbearings, closurerings,and felt seals in
___//._
COTER
MAIN WHEEL
e_.=
NOSE TIRE
wheel
halves. Secure
with
snap
11. Positiontire
and
tube
onrings.
one wheel half; then
NOSE GEAR-J_\\\
positionotherwheel half on tire.
12. Install brake disc (2) and wheel half retaining
bolts,washers, and nutS(Fig. 32-14).
13. T'_htan nutsevenlyand torqueto 150 inchpounds.
CAUTION
Uneven or improper torque may cause bolt or
wheel failure,
LEG ASSY.
12-98
_//_F
"_,//
/
COTTERPIN
-J
/
WASHERS---'
//
NUT-J
NOSF
WHFFI
LANDINGGEAR WHEEL REMOVAL - FIGURE 32-13
32-40-00
21
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
C. Visually inspect linings for wear and brake disc
they are wom to a minimum thickness of 1/8 inch. If
lining replacement is necessary proceed with steps D
thru O. Otherwise reassemble in reve[se sequence of
15
disassembly.
CAUTION
Brake
disc
should
be replaced
if width
is ,205
for warpage. Brake linings
should be
replaced
when
_4
108
8
"_,_
NOSE WHEE"L-_SSY._
"--
____
"1_
inch or less.
cylinder assembly. Remove nuts from anchor bolts.
13
-GI_
v
- ¢_1_}_.._.
_
MAIN WHEEL ASSY.
WHEELASSEMBLIES
- FIGURE 32-14
(5) sliding
it offthe anchor
(6). Note
D. Disconnect
and capbolts
hydraulic
linethe
(4) condition
at brake
of the anchor bolts. If they are nicked or gouged they
should be sanded smooth to prevent binding with the
pressure plate (5) or torque plate(8). When the anchor
bolts are replaced they should be pressed out. New
ones can be installed by tapping them in place with a
soft hammer.
F. Ddll out rivets (9) attaching linings (7) to back
lining plate (2) and the pressure plate (5). Remove
piston assembly (10) and "O"ring (11). It is permissible
E. Remove pressure plate assembly (Fig 32-15)
to remove
use compressed
applied
to the
brake
line fitting
to
the pistonair
(10)
from the
brake
cylinder.
G. Clean parts in cleaning solvent (Federal
Specification PS-661 or equivalent) and dry with
oil-free compressed air.
18. Remove aircraft from jacks.
32-40-03
- NOSE WHEEL
DISASSEMBLY-ASSEMBLY
The standard brand, tube-type, 5:00 x 5 nose wheel
tire is six-plyrated.
1. Nose wheel removal.
A. Remove cotter key, nut, and washer from axle.
(Figure32-13).
B. Remove nose wheel.
2. Installation is in reverse sequence of removal.
C8
_
-7
__i
.._c_
o_
°%o/4_._
_
_\
'--.
1 0]_ 1
3 --
CI_j
4
A. Completely deflate tire by removing valve core.
3. Nose wheel disassembly.
bolts (15) from wheel. (Fig 32-14).
B. Remove nuts, washers, and wheel half retaining
tire and tube. Refer to Section 32-40-02 steps 5 thru 10
D. Reassemble nose wheel in reverse sequence of
for wheel inspection.
torque
disassembly.
to 90 inch-pounds.
Tighten retaining
Inflate tire
bolttonuts
49 PSI.
evenly and
__-"T_
32-40-04
- BRAKE SYSTEM
]3 [_ E F- D V (_ [_ V E--//_
J
1. BRAKE REMOVAL AND INSTALLATION: Lining
inspection and/or replacement or cylinder repair.
C _ V _-R
A. Place aircraft on jacks.
B. Remove inboard or mid gear doors. Remove
safety wire and two AN4H17A bolts (1) attaching back
lining plate assembly (2) to brake cylinder assembly
(Fig. 32-15).
BRAKE ASSEMBLY - FIGURE 32-15
32-40-03
22
12-98
]
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
A. Perform a minimum of six (6) light pedal effort
braking
two Allow
(2) hard
from
25 to
to
40
MPHapplicationsand
(21 to 35 KIAS).
thestops
brake
discs
¢_...1..u
_.:_...
--
'"_;_6
,.,= n I .=_
partially cool between stops.
resins in the lining, but will not cause the material to
become carbudzed due to excessive heat.
3. MASTER CYLINDER
24-0001 thru 24-3200, 24-3202 thru 24-3217
REMOVAL. DISASSEMBLY AND REASSEMBLY.
ull
The procedure will generate sufficient heat to cure the
B. Disconnecthydrauliccylinderfrom pedal linkage.
C. Disconnect and cap hydraulic lines.
D. Disconnect hydraulic cylinder from bracket;
remove cylinder.
E. To disassemble master cylinder:. (Gerdes or
Parker-Hannifin) (Reference Fig 32-17A).
(1) Unscrew and remove rod end clevis and nut
from piston rod (9).
(2) Remove snap ring (13) and lift out compete
piston rod assembly, item 3 thru 12.
(3) Remove spacer (11) and O-ring packings, (10
and 12) from piston and assembly.
TORQUE PLATE ASSY. INSTALLED RELATIVE TO CYL
(4) Disassemble piston rod assembly by
FIGURE 32-16
removing roll pin (4), (spring guide (3) will be pushed
out by spring (5) when roll pin is removed), spdng (5)
H. Replace linings with Cleveland 65-30 linings
and piston (7).
using
#561-2 rivets.
Rivetsand
must
be rolled to
(5) Remove O-ring packing (6) from piston.
obtainCleveland
proper fit between
dvet shank
hole.
I. Inspect brake cylinder bore for scodng. A scored
(6) Remove stat-o-seal (8) from piston rod.
cylinder may _use the "O" dng to leak or cause rapid
(7) Clean all parts with cleaning Solvent (Federal
wear of the O dng. A scored brake cylinder should be
Specification No. PS-661).
replaced.
(8) Inspect cylinder for cracks, scodng, or
J. Replace AN6230-2 "O" dng (11) with a new one.
groovesin bore.
Do not reusethe old=O"dng.
(9) Inspect piston (7) for damage,checkfor nicks
K. Lubricatecylinder and piston with MIL-H-5606
and scratches.
red hydraulicfluid and assemble componentswith care
to preventdamage to the "O" ring.
(10) Inspect spacer (11) for damage.
(11) Inspectpush rod for scoring,grooves, nicks
L. Service and inspectmain wheels as describedin
and scratches.
Section 32-=
. Inspect torque plate assembly
making sure the .125 thickness is toward brake
(12) Inspectpistonreturnsprings(2) for permanent
cylinderassembly (outboard). If thicker 250 protruson
set and properlength(3.670 in.min., 4.05 in. max.).
is outboard, remove torque plate from axle mounting
(13) Replaceall faultyparts and all O-rings.
flangeand installas shown (Figure 32-16).
(14) Reassemble in reverse sequence of
M. Reassembly brake cylinder assemblyand back
disassembly. Immerse all parts in hydraulicbrake fluid
liningplate assembly onto the airplane in the reverse
pdorto reassembly.
sequence of disassembly.
F. Reinstallmaster cylinder in reverse sequence of
N.Beed h_raulicsystemasdesm'bedin 8ec_n 12-20-05.
removal.
O. Remove aircraft from jacks.
NOTE
Brake pad conditioning is required to properly cure the
resins binding the asbestos lining composition
together. Excessive heat created prior to conditioning
will carbudze the linin'g matedal and prevent the
attainment of maximum braking coefficient.
2. BRAKES - BREAK IN PROCEDURES.
Proper conditioning may be accomplished as follows:
12-98
G. Bleed brake system (refer Section 12-20-05).
NOTE
S/N 24-3201,24-3218 thru 24-TEA have larger
capacity Master Cylinders (P/N 10-24D)installed.
REMOVAL. DISSASSEMBLY AND ASSEMBLY
(24-3201, 24-3218 THRU 24-TBA)
A. Remove left. hand, lower fuselage skin aft of
firewall and exhaust cavity.
32-40-04
23
SERVICE AND MAINTENANCE MANUAL
112
_-
M20J
MOONEY AIRCRAFT CORPORATION
_0 \_
,5 _-
3 2
'3_-
u
_
_-
/
_
-
4
k'--z7
_--u "
_-7
_-7
BRAKE MASTER CYLINDERS - FIGURE 32-17A
(7) Clean
parts with cleaning solvent (Fed.
Specification
No.all
PS-661).
(8) lnspect cylinder for cracks, scodng or grooves
In bore.
(2) Remove snap dng (11) from cyhlinder
housing assembly; lift out complete piston rod
assembly, items 2 thin 12. Spring (13) can be removed
at this time.
_t
sMx3,-i_:,01.,,,thru24.TBA
'(3) Remove snap ring (2) from end of piston rod
assembly.
(4) Remove bushing (3) and spdng (4) from end
of pistion rod.
(5) Remove piston assembly (5) and o'dng (7)
from piston assembly and o'ring (6) from piston rod
shaft.
(6) Remove end cap (8) and o'dngs (9) [ID] and
(7) [OD] from end cap assembly.
B. Disconnect hydraulic cylinder from pedal
linkage.
C. Disconnect and cap hydraulic lines,
D. Disconnect hydraulic cylinder from bracket and
remove cylinder,
E. To disassemble master cylinder. (Gerdes or
Parker-Hannifin) (Reference Fig 32-17A, 24-3201,
24-3218 thru 24-TBA).
(1) Unscrewand remove rod end clevis (17), nut
(16) and washers(14 & 15) from pistonrod (12).
i
s"_-_l_202thru24"3217
[
(9) Inspect piston (5) for damage; check for nicks
and scratches.
(10) Inspect end cap (8) for damage.
NOTE
j
1991 single brake systems, with shuttle valve, have to
be bled somewhat differently. The plug (that would
normally go to ca-pilots side)has to be loosened se
fluid can be purged from shuttle valve cavity dudng
bleeding to keep shuttle valve from locking up one side
lo
9
11
T
e
•
I
BRAKE MASTER CYLINDER (PARAMONT) - FIGURE 32'17B
32-40-04
24
12-98
MOONEY AIRCRAFT CORPORATION
....
(
M20J
SERVICE AND MAINTENANCE MANUAL
(11) Inspect push rod for scoring, grooves, nicks
and scratches.
(12) Inspect spring (4) for free height - .500 in. +/.030.
(13) Replace all faulty parts and all c'dngs,
(14) Reassemble in reverse sequence of
disassembly.
Immerse all parts in hydraulic brake fluid
pdor to reassembly.
4. PARKING BRAKE VALVE Removal.
A. Remove left hand exhaust cavity.
B. Disconnect parking brake control at parking
brake valve arm.
C. Disconnect and cap hydrauliclines.
D. Remove parking brake valve.
(15) Check piston rod and return spdng (13) for
proper compression during stroke (9 Ibs. (@ start of
stroke)to 32 Ibs. (@ 3/4 stroke).
F. Reinstallmaster cylinder in reverse sequence of
removal.
G. Bleed brakesystem (refer to Section12-20-05).
PARAMOUNT MASTER CYLINDER
A. To disassemble Paramount master cylinder
(Reference Fig. 32-17B).
(1) Unscrew and remove rod end beadng and nut
from pistionrod.
(2) Remove snap ring (1) and lift out complete
pistonrod assembly.
(3) Remove piston top (2), o'dng packings (3),
and brass washer (4) from pistonrod assembly.
(4) Disassemble piston rod assembly .by
removing cotter pin (5), valve stop (6), and spnng
washer (7). Valve assembly (8) willfall out when cotter
pin is removed.
NOTE
DO NOT attempt to remove O-ring packing (9)
under valve head. If valve or packing is faulty,
replace the valve assembly,
(5) Remove o'dng packing (10) from piston (11).
Do
not
unscrew
piston
from push rod. Replace entire
pistonrod
assemblyif
faulty.
(6) Remove spring (12) from cylinder.
(7) Clean all parts with cleaningsolvent(Federal
SpecificationNo. PS-661).
(8) Inspect cylinder for cracks, scoring, or
groovesin bore.
(9) Inspect pistonfor damaged valve seat, nicks
and scratches.
(10) Inspectvalve assemblyfordamage.
(11) Inspect push rod for scodng, grooves, nicks
and scratches.
(12)proper
Inspectlength
piston (3-3/16
return spring
for permanent
set and
IN. MIN.:
3-5/16 IN.
MAX).
(13) Replace all faulty parts.
(14) Reassemble in reverse sequence of
disassembly. Immerse all parts in hydraulic brake fluid
pdor to reassembly.
B. Reinstall master'cylinder in reverse sequence of
removal,
C. Bleed brake system (refer Section 12-20-06).
Disassembly & assembly parking brake valve:
(SIN 24-0758 THRU 24-TBA;
Refer Figure 32-18 A).
A. Remove bothfittings(1) from valve housing(7),
spdngs(8) will comeoutwiththe fittings.
B. Remove poppet valves (2) and pins (3), from
housingby bumpingontabletop.
C. Remove bothfittings(4) from end of housing.
D. Remove snap ring (5) from end of camshaft
assembly(6).
E. Camfullyrsmovecamshaltassembly(6)from
housing.
F. Inspect all components for damage, nicks,
grooves,etc.
G. Clean all parts with cleaning solvent (Federal
SpecificationNo. PS-561).
H. Replace all o'dngs(9).
1. Reassemble parking brake valve in reverse
sequenceof disassembly.
J. Connectvalve assemblyto the hydrauliclines.
K. Bleed system and service hydraulic reservoir
with hydraulicfluidas deacdbed in Section12-20-04.
Disassembly & assembly parking brake valve.
(SIN 24-0001 thru 24-0757;
Refer to Figure 32-18 B).
A. Remove dvetsor screws (1) attachingvalvearm
(2) to valve body (3) and stem (4).
B. Remove end plug(5) and square out gasket (6).
C. Withdraw valvestem assembly (7) and remove
o'dng packings(8 & 9) from valve body.
D. Clean all parts with cleaning solvent (Federal
SpecificationNo. PS-661).
E. Inspect valve stem (4) for nicks, scratches,
burrs, and grooves.
F. Inspectvalve seat for nicks,scratches, and scodng.
G. Inspect all threads for damage.
H. Replace o'dng packings.
I. Replace end plug gasket (6).
J. Reassemble brake valve in reverse sequence of
disassembly.
K. Install brake valve on hydraulic reservoir,
L. Reinstall hydraulic reservoir and connect lines
and brake control.
M. Bleed system and service hydraulic reservoir
with hydraulic fluid as described in Section 12-20-04.
12-98
32-40-04
25
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
6
8
PARKING BRAKE VALVE (24-0758 THRU 24-TBA)
FIGURE 32-18A
3241-00
PARKING BRAKE VALVE (24-0001 THRU 24-0757
FIGURE 32-18B
- TROUBLE SHOOTING - BRAKE SYSTEM
TROUBLE
" -_
Solid pedal and no brakes.
Replace lining.
Spongy brake.
-Brake lining worn beyond
allowable limit.
-Air in system.
Pressure will not hold.
-Leak in brake system.
Visually check entire system for
evidence of leaks.
Parkingbrake willnot hold.
-Air insystemor leakin system
(downstreamof parkingbrake
valve),
-Defective parkingbrake valve.
See remedies above.
-Warped or bentdisc,
Replacedisc.
-Foreign matter lockingdisc.
Cleandisc and lining.
-Master cylindershaft or linkage
misaligned.
Checkthat shaft travels in straightline
& not bindingin linkage.
Brake grabs.
Brake pedalwill not return to
neutralposition,
.'-I'L
:-
:
- SHUTrLE VALVE
SIN 24-0001 thru 24-0763 (If Installed)
Shuttle valve removal and testing (optionaldual brake
system.)
1, Disconnect inlet lines from master cylinders and
cap line ends.
2. Disconnect outlet line leading to brake cylinder
and cap lineend,
REMEDY
3241-01
3. To test valve operation, seat shuttle valve by
applying1500 PSI hydraulic pressure to one inlet port
with outletplugged,
4. Apply pressure to opposite port. Shuttle valve
shouldunseat at 15 to 50 PSI.
32-41-01
26
Bleed brake system per 12-20-05.
Repair or replacethe valve.
5. Repeat step C and D to test oppositeport.
6. Reinstallshuttlevalvein reversesequenceof removal.
7. Bleed brake system per 12-20-05.
32-50-00
-STEERING
32-50-01
- NOSE GEAR STEERING SYSTEM
The nose gear steering system consistsof a steedng
horn on gear leg linked to the rudder pedals by
push-pull tubes and bellcranks. Gear retraction
automatically disengages steedng mechanism from
nosewheel,
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
3. Check steering ham assembly (5) collars and
spacers for looseness. Replace any bushings or
spacersthat are worn.
4, Adjust turn limiterstop bolts (7) to contact cross
member (8) of trues assembly (.020 gap permissible)
when rudder is at its extreme left and right travel
position.
STRUCTURE
6,
32-50-02
- NOSE GEAR STEERING AND
TRACKING
1. Levelaircraft as described in Chapter 8,
2. Center nose wheel.
7
3. Place plumb line over and forward of nose gear
trunnion (see Figure 32-20) part number 540001-503.
4. Measure forward from aft edge of plumb line to
axle center line. Modification relocating nose wheel
should be accomplished if axle position, forward of
plumb line, exceeds ,06.
5. Add SB M20-202-3 spacer .under collar to
reposition the axle if required.
NOTE
Some collars have holes drilled off center and
may be turned overto change axle position.
NOSE
LEGASS'(.
6, Run gear through up/down cycle. Check nose
gear door and wheel well tire clearances. Re-rig if
required.
NOSE WHEEL STEERING - FIGURE 32-19
fiSection 27-20-00 outlines the nose gear steering
gging.) A centering cam aligns the nose wheel for
entry intowheel well.
NOTE
Check nose gear leg assy. for towing damage.
Replace if any dent exceeds 1132inch.
NOTE
Aircraft SIN 24-1464 & ON have twin limiter
pads and adjustable stops (7) (Figure 32-19)
installed on the nose gear leg assembly (A) that
will prevent turning damage to leg assembly.
COLLAR
NOSE GEAR
TRUNNION
SPACER
1. Every 100 hours remove cotter pin (1)(Fig 32-19)
and retorque nut (2) to 450-500 inch Ibs. Check holes
in leg assembly where pivot bolt (3) is located for any
wear. If holes are worn, replace leg assembly.
NOTE
Shock absorber (6) and related attaching
hardware may be removed from all Mooney
M20J aircraft if desired. (Ref 940052 Dwg.)
CAUTION
Bolt, washer, nut (9) and (10) (Figure 32-19)
must be installed as shown, from rear to front.
PLUMB UNE
I
SEE
ITEM 4I
2. Rod end beadng (4) (Figure 32-19) should be
inspected at least every 100 hours for any damage or
bending.
12-98
CENTER
LINE
NOSE WHEEL LOCATION - FIGURE 32-20
32-50-02
27
SERVICE AND MAINTENANCE MANUAL
32-60-00
- POSITION AND WARNING
32-60-01
- ELECTRIC GEAR SAFETY;DEVICES
M20J
32-00-03
The gear switch operates the landing gear actuator
relays. Pullingwheel-shaped knobout and moving itto
upper detentraises gear. However, an airspeed safety
switchor a squat switchis incorporatedin the electrical
systemto prevent landinggear retractionwhile on the
ground. On aircratt equipped with airspeed safety
switchto allowgear retractionwith the aircraft on jacks;
attach a 12-inchlength of 3/8 inch pliable rubber hose
(surgicaltubing) over pitot head, and pinch open end
with a larger cotter pin; roll the tubing with the cotter
pin until compressed air within the twisted tube
actuates airspeed pressure switch. Maintain pressure
on the switch until retraction is complete. To adjust
airspeed switch refer to Section 32-60,03. To adjust
the squatswitchrefer to Section 32-60-04.
The up-limitswitch will stop the gear in its retracted
position.Moving control knob to its lower detent lowers
landing gear. The down limit switch will Stop gear
actuating
motor when
the proper force is exerted to
holdlandinggear
in down-and-lockedposition.Refer
to
Section32-30-02,6. for proper limitswitchrig ging. The
gear down-and-lockedpositionis indicated by:
1. Illuminationof the GREEN gear downannunciator
light. GEAR DOWN annunciator light is dimmed when
NAV Lightswitchis ON.
2. The warning horn will not sound with the throttle
retarded to within 1/4 - 318 in. of panel,
3. The indicator marks will be aligned on the visual
gear-position indicator.
CAUTION
When running gear up or down electrically DO
NOT use circuit breaker as a switch,
Partial retraction or extension may be accomplished
electricallyas fellows:
1. Place Master Switchin OFF position,
2. Move gear switchto GEAR UP or GEAR DOWN
as desired,
-AIRSPEED SAFETY SWITCH
ADJUSTMENT (24-0084, 24-0238 & ON)
The airspeed safety switch, located inside cabin, is
mounted behind airspeed indicator.An airspeed safety
switch is incorporatedinto electrical system to prevent
landing gear retraction while on the ground and at
airspeedsbelow69 +/- 5 MPH (60 +/-5 KTS).Additionally
the RED gear unsafe lightcomeson and warninghornis
soundedwhen gear controlhandleis placed in gear-up
positionbelow69 +/- 5 MPH (60 +/-5 KTS).
NOTE
Whitman-General switches can be adjusted
using thefollowing procedures:
1. Using a water manometer to measure pressure,
graduallyapplyair pressureto inlet at cap.
2. Connectan ohmmeterbetweenmicroswitchleads.
3. Gradually increase pressure to 2.775 inches of
water untildiaphram movement closesmicroswitch.
4. Slowlydecreasepressureuntilmicmswitchopens.
5. Adjust knuded body until switch closes at an
increasingpressure of 2.775 +.384/-.359 in. water (69
+/- 5 MPH or 60 +/-5 KTS).
6. Secure set screw and repeat step (5), fivetimes.
V.E.P. switches can be adjusted using the
following procedures:
V.E.P. manufactured switches are field adjustable. They
should close at 2.8 +# .4 inches water. Adjust slotted
screw head on center of switch to obtain correct settings.
CAUTION
The airspeed safety switch is designed to
operate within a specified range during
increasing airspeed only. Due to hysteresis of
the switch/diaphram assembly the switch MAY
NOT deactivate the landing gear circuitry until
approximately 57 MPH (49.5 KTS). This could
allow the landing gear to retract if the gear
switch is inadvertently placed in the UP
position during the landing roll.
3. Momentarilyactuate master switchuntilgear is in
desiredposition.
32-60-02
- LANDING GEAR WARNING SYSTEM
The landinggear wareing system Consistsof:.
1. Landinggear positionlights:(GEAR DOWN-white
indicatorlighton floor and green lighton annunciator;,
GEAR IN TRANSIT - up or down - red unsafe on
annunciator;GEAR UP - no lights),
2. A warning horn in cabin is actuated by throttle
controlwhen gear controlswitch handle is up and the
throttleis retarded to within 1/4-3/8 in. of panel. Check
warninghornfor volume in flight periodically.Horn will
sound if gear is not DOWN and LOCKED even if
switch is in DOWN position or if airspeed is below 60
KIAS & gear switch is in UP position,
32-60-00
28
MOONEY AIRCRAFT CORPORATION
12-98
WARNING
Do not turn knurled knob on back of switch
housing (WhitmaI-General Switches) when
disconnecting switch from electrical
connections. This is airspeed adjustment knob.
NOTE
Referto proper electrical schematic when
replacing with
switches from another
manufacturer.
CAUTION
During Pitot-Static System Inspection,
compensating pressure MUST be applied to
pitotside ofA/S Safety switch diaphramwhen
"static presssure" is applied. Failure to equalize
pressure on diaphram could cause it to rupture.
MOONEY AIRCRAFT CORPORATION
32-00-04
,
!
M20J
-SQUATSWITONADJUSTMENT
(24-0001 THRU 24-0237 except 24-0084)
The squat switch, located on the left main gear, is
incorporated into the electrical system to prevent
landing gear retraction while aimraft is on ground.
Adjustmentof squat switchis accomplishedas follows:
1. Raise
aircraft
onjacks.
2.
Remove
safety
wire from adjustment nuts on
switch.
3. Adjustswitchbodyuntilswitchjust closes,
4. Check switch by slowlyIowedngaircraftto ground.
Switch shouldnow be open.
5. Resafety adjustmentnuts.
32-80-00
32-81-00
-MISCELLANEOUS
- LANDING GEAR SHOCK DISC
INSPECTION
SERVICE AND MAINTENANCE MANUAL
(3) Careful application of the shock disc
replacmanttool is recommendedduringreplacementof
main gear shock disc to keep from damaging grease
f'rttings.
NOTE
Shock disc retention collar should be installed
with the chamfer facing down and forward.
B. Nose Gear Shock Discs.(See Fig 32-22)
(1) Check for gap between retainingcollar (D),
(Figure 32-22) and top retaining plate (E). Top
retainingplate must be in contactwith retainingcollar.
(2) Replace shock discs if gap is found. Use
shock discreplacementtool (F), P/N GSE 030010, (old
PIN ME120), to remove and install nose gear shock
discs. Use removable pad from tool as a guide on top
of shock link to align discs as they are being
compressed.
NOTE
1. Aircraft with full fuel load and weight on landing
gear.
Dimension ('r), (Figure 32-22), is critical to
properly locate nose wheel position. The leg
A. Main gear shockdiscs. (See Fig 32-21).
(1) Check gap between retainingcollar (A) (Fig.
32-21) and top retaining plate (B). Allowable gap is
0.00 to 0.60 inches.
assemblies can tolerances.Vary'
due to manufacturers
The dimension (T) in a no load fully extended
position should be approximately 3.0 inches.
Add spacer under collar (D) per 8B M20-202, as
needed. See (Figure 32-20), paragraph 30-50-02,
for proper steering/tracking rigging.
(2) Replace discs when gap exceeds tolerance,
Use shock disc replacement tool (C), PIN GSE
030011, (old PIN ME 121), to remove and install main
gear shock discs. Use removable pad from tool as a
guide on top of shock link to align discs as they are
beingcompressed.
MAIN GEAR SHOCK DISC REPLACEMENT TOOL
APPLICATION - FIG 32-21
12-98
NOSE GEAR SHOCK DISC REPLACEMENT/TOOL
FIGURE 32-22
32-60-04
29
SERVICE AND MAINTENANCE MANUAL
M20J
2. Raise airerafl onjacks - shocksfullyextended.
A. Inspectnose and main gear shocksfor evidence
of gap between retainingcollarand retainingplate.The
disc preload must be great enough to maintain
completewheel extensiondudngretraction,
B. Replace shock discsthat have lost resilience,
C. Inspectretainingcellar and bolt for deformation,
wear, and cracks.
D. Replace defectiveboltand cellar.
CAUTION
Both collar and bolt must be replaced when one
or the other is defective,
E. Inspect nose gear snubber (shock absorber)(if
installed) for proper shock absorbing action. Replace
snubber when effectiveness is impaired--the unit is
sealed and cannot be repaired.
NOTE
Shock absorbers may be removed if desired.
Refer to Drawing 940052.
'
NOTE
For Nose Gear Steering/Tracking see Section
32-50-02, (Figure 32-20).
32-82-00
3O
MOONEY AIRCRAFT CORPORATION
32-82-00
- RECOMMENDED HARD LANDING
INSPECTIONS
The followingare areas recommendedto be inspected
when a "hard landing" has occured. Since a =hard
landing"is a relativeterm, it is up to the owner/operator
to advise maintenance personnel when
the
inspectionsare to be accomplished.
1. Mud Shield missingor damaged on eitheror both
main landinggear.
2. Main landing gear shock bisquits condition,
compressedor extrudedrubber.
3. Tail skid damage or damage to bulkhead that
attachestail skid.
4. Propellerstrike/marksor other visualdamage.
5. Engine or engine mount damage.
6. Nose landing gear leg assembly damage near
steering lugs.
7. Pilot/Co-Pilot's seat adjustment supports/tubes
bentfrom excessiveG-loads.
If any evidence of
damage or abnormal visual
observations are found, it is recommended that a
thorough inspectionof all the above areas be done and
repairs be made as necessary.Contact FAA personnel
for incidentreportrequirements.
12-98
'
SERVICE AND MAINTENANCE MANUAL
M20J
CHAPTER 33
LIGHTS
MOONEY AIRCRAFT CORPORATION
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 33
LIGHTS
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
33-Effectivity .........
33-Contents..........
33-00-00.
...........
33-21-02.
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33-22-00 ............
33-23-00 ............
33-41-01.
...........
33-41-03
...........
33-42-00
...........
33-43-01
...........
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DATE
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3/4BLANK ..........
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12-98
12-98
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33-EFFECTIVITY
1/2BLANK
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 33
LIGHTS
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
33-00-00 ........
33-20-00 .........
33-21-00
..........
33-21-01
..........
33-21-02
..........
33-22-00 .........
33-22-01
..........
33-23-00 .........
33-23-01
..........
33-40-00 .........
33-40-01
..........
33-41-00
..........
33-41-01 ............
33-41-02 ............
33-41-03 ............
33-42-00 .........
33-42-01
..........
33-43-00 ........
33-43-01
........
SUBJECT
........
PAGE
GeneraI-Descdption and Operation .......
Intedor Lights - Maintenance Practices .....
Cabin Lights- Overhead Lights ......
Light Bulb Replacement
.......
Cabin Light Switch Replacement .....
Instrument/Right Panel and Glareshield Lights .
Light Bulb Replacement
.......
Gear Down Indicator Light (Floorboard) .....
Light Bulb Replacement
.......
Extedor Lights - Maintenance Practices .....
Trouble shootingExterior Lights .....
High Intensity, Strobe Lights - Maintenance
. ,
Power Supply Unit- Removal or Replacement
Power Supply Unit Installation
....
Strobe Light Replacement ......
Navigation/Position Lights ........
Position Light - Replacement Service ....
Landing/Taxi Lights--24-1354 thru 24-TBA .....
Landing/Taxi Light Adjustment Procedures
12-98
5
5
5
5
6
7
7
8
8
8
8
8
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9
9
11
11
11
11
33-CONTENTS
3/4BLANK
MOONEY AIRCRAFT CORPORATION
33-00-00
M20J
-GENERAL-DESCRIPTION AND
OPERATION
High intensitystrobe lights are standard equipment on
M20J aircraft. The lights are located adjacent to the
wing tip navigation lights and incorporated in the
taillight assembly. Separate power supplies are utilized
for each strobe light and are located in each wing
outboard section, mounted on inspectioncover, and
insidethe tailcone adjacent to the left rear inspection
cover. The system is actuated by a circuit
breaker/switchlocatedon the instrumentpanel in front
of the pilot. SIN 24-0001 thru 24-1037 have a
combined Nav-Strebe light assembly on each wing tip
and has no strobe lighton the rudder,only a navigation
light,
Navigation lights are located on each wing tip and
rudder trailing edge (24-0001 thru 24-2999). (24-3000
thru 24-TBA) A/C have the aft facing navigation light
(clear)located on each fiberglasswingtip trailing edge.
The
lightsthe
areinstrumentpanel
activated by a incircuit
locatedon
front ofbreaker/switch
the pilot.
S/N 24-0001 thru 24-3153
The landinglightis locatedin lower engine cowling.
SERVICE AND MAINTENANCE MANUAL
One 290,000 candle power sealed beam bulb is
incorporatedand mounted in a housing designed to
isolate the bulb from engine heat and vibration.The
light is activatedby a circuitbreaker/switch locatedon
the instrumentpanelin front of the pilot.
S/N 24-3154 thru 24-TBA
Two 110,000 candle power sealed beam bulbs are
locatedin LH & RH side ofwing.
Two intedor lights are located on the overhead panel
(SIN 24-0768 thra 24-3373). The forward cabin
overhead lights are located between the pilot and
co-pilot seats and are actuated by a three position
switch, (dim, off, bright)adjacent to the light near the
co-pilotshead. The passengercompartment lights are
locatedabovethe rear seats in the overhead paneland
are activatedby a similar three positionswitch located
adjacentto the light.The rear cabin light is accessible
from the baggage compartmentdoor also.
S/N 24-0001 thru 24-0787 - A switchin the dome light
base controlsthe overheaddome light.
CAUTION
SIN 24-0001 thru 24-3153-cabin lights are
connected directly to battery through their
switches and WILL ILLUMINATE WITHOUT
MASTER SWITCH ON.
LAMP BULB REPLACEMENT CHART
APPLICATIONS
Glareshield Lights
Post Lights
Map Light
Cabin Interior Lights
Trim & Flap Indicator
Gear Down Light
Tail Position Light
Wing Tip Position Light
-(24-0001 thru 24-1425)
-(24-1426 thru 24-1708,
24-3000 thru 24-TBA)
LandingLight
-(24-0001 thru 24-3153)
-(24-3154 thru 24-TBA)
RecognitionLight
BULB PART NUMBER
(SIN 24-0084, 24-0378
thru 24-1168)
(SIN 24-1169 & ON)
(Floorboard Indicator)
(Whelen/SDI)
(Grimes)
(Whelen)
14 VOLT
28 VOLT
GE 330
GE 330
GE 330
GE 1816
W]-7046
GE 327
GE 327
GE 327
GE 1818
N/A
GE 370
GE 327
34-0212080-85 *
GE 327
GE 327
34-0228030-85 w
A-7512-12
W1290-14
A508-14
(Whelen)
W1290-28
(GE)
(GE)
(Whelen)
GE 4522
01-0770303-00
• Use S.D.I. Tool No. 203541 to removelamp.
33-20-00
- INTERIOR LIGHTS - MAINTENANCE
PRACTICES
33-21-00
- CABIN LIGHTS - OVERHEAD
LIGHTS
GE 4553
GE 4596
•
Use same lightassy.
butdroppingresistor
RH-50-7.6 req'd.
33-21-01
- LIGHT BULB REPLACEMENT
(S/N 24-0768 thru 24-3373)
1. Remove light cover panel (2) (Figure 33-1) from
the headlinerassembly(1) by removingscrews(3).
NOTE
The front and rear light bulbs are replaced in
the same manner.
12-98
33-00-00
5
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
2. Remove and replace the bulbs and check for
properoperation.
- LIGHT BULB REPLACEMENT
(SIN 24-3374 thru 24-TBA)
1. Carefullyslide smooth,fiat sharp blade underlip of
light assembly flange and pop light assembly out of
mountinghole. (Ref. Figure 33-1A)
2. Disconnectblade terminals from lightassembly.
3. Hold light assembly body and rotate bulb holder
counter-clock-wiseto remove,
PILOT'S & REAR SEAT PASSENGER'S LIGHTS
1. Remove cover from arm rest assembly by
removing2 screws holding coverto arm rest.
2. Switches are snap-fit and may be removed by
pressingsnap tabs and pushingswitchthroughcover.
3. Disconnectwire terminals and replace with new
switch.Check for properoperation.
4. Re-assemble switch assembly into cover by
snapping in from top side. Re-install cover into arm
rest, securewith 2 screws.
4. Pull bulbfrom bulb holder, replacewith new bulb.
Reinstallbulbholder.
5. Re-assemblelightassemblyinto mountinghole.
6. Check for properoperation.
CO-PILOT'S SWITCH
1. Co-pilot'scabin lightswitch is located in front of
cabindoor hingeabove co-pilot'sright knee.
2. Remove 1 screwabove switch.Removedoorframe
cap.Pull panelfrom velcmfastnersto accessswitch.
33-21-02
- CABIN LIGHT SWITCH
REPLACEMENT
(SIN 24-0768 thru 24-3373)
1. Remove cover (4) from headliner assembly(1) by
removing screws (3) holding panel in place (Figure
33-1).
NOTE
SIN 24-0901 and ON have a butterfly shut-off
valve for the overhead ventilation that must be
freed from the panel prior to removal.
2. Switch (5) is a press and snap in fit and may
requirebendingof springtabs to release for removal.
3. Disconnect wire connections and replace with new
switch. Check for proper operation.
4. Reassemble panels and ventilation control, if
app icable,to headliner.
CABIN LIGHT SWITCH REPLACEMENT
(24-3374 thru 24-TBA)
BAGGAGE COMPARTMENT
|
BAG.CMPT.
UGHT7
3. Press snap tab & pushfrom panelto remove.
4. Re-assemble in reverse swquence when
maintenanceactioncompleted.
BAGGAGE COMPARTMENT SWITCH
1. Switch is located at rear of baggage door at front,
top of hat rack opening (Figure 33-1A)
2. Remove 1 screw inboard of switch. Pull door
frame down slightly from velcro fastners to access
baggage compartmentlightswitch.
3. Press snaptabs; PUSH switchthrough panel.
4. Disconnectterminals;replaceswitch.
5. Re-assemble in reverse order.
33-22-00
- INSTRUMENT/FLIGHT PANEL
AND GLARESHIELD LIGHTS
33-22-01
- LIGHT BULB REPLACEMENT
1. instrumentpanel lights.
(UNDER
COVER) _
SONALERTS_
_=_=_w_,J_.._,.,
SWITCH
PANEL _,
EXERIORUGHTS--_
_,
,_,_
____ __:_!(
REAR SEAT_/"/
/DAFRONTSA'_Tf
...... "-_
PASSENGER'S-EIGHTS
/
...... !"rG-_l'_
-"
"_"
SPEAKERS../
t rp-r _A_ ¢_'AT
UNDE_
COVER
FINTER]OR UGHTSMASTER
SWITCI"
* r,_._=_N_._,,
\
/r
PILOTSOVERHEAD
uun. _w,.un \
_ _
_
/
UGHTSWITCH
RIGHT,REAR SEATPASSENE
UGHTSW1TCH
ON RIGHTSIDE
PANEL.TYPICALTO LEFTSIDE
,OCA O.
........
_p_'_NG_ O_TLSIGEHA.
12-93
_ _._l
SWI CA
FIGURE 33-1A - INTERIOR LIGHTS (24-3374 THRU 24-TBA)
33-21-02
6
/_
_
/_::1_
--"
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
FWD
OUTBD
@
.,r...._ / _I
\
I
t
----_,
_" 3-/
I
4
I
I
TRIM/FLAP INDICATOR LIGHT - FIGURE 33-2
(SIN 24-0084, 24-0378 thru 24-1188)
F. Check for proper operation.
A. Unscrew the black knurled button (1) (Figure
3-3) to gain access to the bulb.
B. Bulb is a friction fit type in button; remove and
replace with new bulb.
C, Replace knurled button with new bulb installed
into console.
D. Check for proper operation.
INTERIOR LIGHTS FIGURE 33-1
SIN 24-0001 THRU 24-3373
A. Internally lit instruments are not being
considered in this information,
B. Post light bulbs are replaced by pulling hood
straight out from post light base and then pulling bulb
from this hooded portion.
C. Insert new bulb into hood and push hood back
onto post light base.
D. Check for proper operation and hood orientaUon.
2. Glareshield lights.
A. Remove outer housing by unscrewing from light
assembly base.
B. Remove bulb and insert new bulb.
C. Screw outer housing back onto base.
P FWD
D. Check for proper operation.
3. Trim/Flap Indicator Light
A. Gain access to light assembly (1) (Figure 33-2)
by reaching in over console side par
(2) from
co-pilots side of cabin.
B. Disconnect wires at knife disconnects (3) and
carefully unscrew socket portion (4) from light
assembly lens (5). The lens is glued to trim/flap
indicator reflector (6).
c. Bulb will come out with socket portion of light
assembly; bulb is bayonet type, push, twist and pull to
remove. Insert new bulb.
D. Carefully screw socket back into lens.
E. Connectthe knife connectionsand ty-rap securely.
12-98
O U TB D
-LAP
S Wl TC
H
TRIM/FLAP INDICATOR LIGHT - FIGURE 33-3
(24-1169 thin 24-TBA)
33-22-01
7
SERVICE AND MAINTENANCE MANUAL
M2OJ
33-23.00
- GEAR DOWN INDICATOR LIGHT
(FLOORBOARD)
33-23-01
- LIGHT BULB REPLACEMENT
1. Remove lower belly panel to gain access to light
asse-m_-bl.E-_=-..=-==========
.........
33-40-00
33-40-01
MOONEY AIRCRAFT CORPORATION
2. Remove and replace bulb.
3. Check for properoperation.
4. Reinstallbellypanel.
-
- EXTERIOR LIGHTS - MAINTENANCE PRACTICES
- TROUBLE SHOOTING EXTERIOR LIGHTS
TROUBLE
PROBABLE CAUSE
REMEDY
STROBE LIGHTS
Lightsinoperative.
One bulbdoes not light.
-Circuitbreaker/switch
tripped,
Checkfor shortcircuit.Reset circuit
breaker.
-Loose connection.
Check and tighten electrical
connections.
-Battery defective.
Replace battery or use external power.
-Circuitbreaker/switch
defective,
Checkcontinuitythroughswitch;
replaceif necessary.
-Faulty power supply.
Disconnectsynch wiresto identify
faulty power supply.
-Bulb burned out.
Replace bulb.
-Power supply inoperative.
Replace.
-Fixturenot grounded.
Checkfor good bondingbetween
fixture and structure.Tighten mounting
screws.
-Loose connection.
Check all connections in circuit.
-Defective fixture
Replace fixture.
LANDING/TAXI LIGHTS, NAVIGATION LIGHTS AND TAILLIGHT
Lampfails to light.
33-41-00
-Circuit breaker/switch tripped.
Check for shortcircuit.Reset circuit
breaker.
-Lampburned out.
Replace lamp.
-Looseconnection or
defectivewire.
Tightenconnectionsand checkwire
circuitcontinuity. Replaceor repairwire
if necessary.
-Circuit breaker/switch
defective.
Check continuity through switch.
Replace if necessary.
-HIGH INTENSITY, STROBE
LIGHTS-MAINTENANCE
The strobe light power supply requires a 14 VDC
(24-0001 thru 24-2999); 28 VDC (24-3000 thrc
24-TBA) input across the red and black wires. Red is
positiveand black is negative, or common.The voltage
for the strobe light is supplied through Pin 1 and 3 of
the power supply connector with Pin 2 as the trigger
pulse. The strobe light assembly is a pottedassembly
and cannot be repaired:
33-23-00
8
!
The power supplies may be synchronized by
connecting each yellow wire together between all
powersupplies (Hoskins only).
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
TROUBLE SHOOTING AIDS
When
no lights
are flashing:
1. Check
circuitbreaker/switch.
2. To determine powersupplyor flashtubeproblems,
first check the input voltageto the power supply. The
red and black line should have 14 VDC (24-0001 thru
24-2999); 28 VDC (24-3000 thin 24-TBA). If novoltage
is present check for shorted power leads or tripped
circuit breaker. If input voltage is present, then
disconnect the yellow sync wires. This will allow
unaffectedunitsto flash. Determine defectivelight and
proceedto =onelightnotflashing"below.
When one light not flashing:
1. To determine power supplyor flashtubeproblems,
first check the input voltageto the power supply. The
red and black line should have 14 VDC (24-0001 thin
24-2999); 28 VDC (24-3000 thru 24-TBA). If no voltage
is presentthen check for shorted power leads, blown
inline fuses, or circuit breaker. If input voltage is
present, then disconnect the connector to the
flashtube.400V-500VDC should be presentacross Pin
1 and 3 of the power supply. If not, the power supply
has no outputand is defective.Turn off master switch.
2. If voltage is present across Pin 1 and 3 of the
power supply, connect a known good flashtube to the
power supply. If good flashtube fails to operate power
supply is defective. If good flashtube operates, the
flashtube is defective. Replace flashtube.
0
0
0
L_.I
0
LJ
2\,"
'-_
1
POWER
SUPPLY
LOOKING UP - LEFT WING
INSPECTION
COVER
- TYPICAL
LOCATION
- RIGHTWIN(;
VIEW
STROBE LIGHT POWER SUPPLY- FIGURE 33-4
3. Be sure yellow sync wire is insulated and not
grounded,
power supply is physically mounted to this inspection
cover.
3341-01
B. Disconnectthe widng connectionsbetween the
switchand the powersupply.
- POWER SUPPLY UNIT - REMOVAL
OR REPLACEMENT
1. wing tip strobe power supply.
A. Gain access to wing tip power supply through
bottominspectioncover (1) near wing tip (See Figure
33-4). Power supply (2) is physically attached to this
inspectioncover.
B. Disconnect widng connections between switch
and power supply:
C. Steps B thru D, and Warning of paragraph
33-41-01, 1, applyfor removalofthis powersupplyunit.
WARNING
High voltage is involved in the circuit between
the power supply and strobe light assemblies,
Although a bleed-off resistor is incorporated in
the power supply circuit, turn the control switch
for the strobe lights OFF and allow at least 20
minutes to elapse prior to disconnecting the
cables at the power supply or strobe light
assemblies before handling either of these
units in any way. Failure to observe these
precautions may result in physical injury from
electrical shock.
CAUTION
STROBE LIGHT WIRING -An incorrect hook-up
of the wires at either the power input or
between the strobe light assemblies and the
power supply unit will cause a reversal of
polarity that results in serious component
damage and failure. Care must be taken to
ensure that the red wire is connected to
positive power and the black wire to ground.
3341-02
, POWER SUPPLY UNIT
INSTALLATION
The installation of any of the power supplies is a
reverse sequenceof the removalprocedures.
33-41-03
C. Disconnect wiring harness between power
supply and strobe light. (See warning above).
D. Remove the screws secudng the power supply
to the inspection panel and remove the unit.
2. Tail strobe light power supply (SIN 24-1038 and
on).
A. Gain access to this unit through the inspection
cover on the aft, let_ hand side of the tailcone. The
- STROBE LIGHT REPLACEMENT
1. WING TIP STROBE LIGHT, (24-1038 THRU
24-TBA)
A. Remove the wing tip lens (1) (Figure 33-5) to
gain access to malfunctioning strobe light.
B. Remove the two screws holding the
navigation/position light lens (2) and the one screw (3)
below the flashtube assembly. This will allow the light
assembly (4) and mounting plate (5) to be pulled away
fromtip db.
12-98
33-41-01
9
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
2. TAIL STROBE/NAVIGATION LIGHT REMOVAL.
(S/N 24-1038 thru 24-2999). SIN 24-3000 thin 24-TBA
have only a strobe light assembly located on the
rudder. Removal is
same
as combination
NAV/STROBE lightassembly.
NOTE
The Whelen Strobe-Nay light assembly is
installed slightly different but is removed and
replaced in a similar manner,
_.
connections from the power supply rotate the round
access cover (1) on the lower left side of the
empennage stinger (Figure 33-6).
%_2
2
7
oPTIoNAL I
A. To gain access to the wire harness and
3 I
28 VDC\
(Z_I
TYPICAl
WING TIP STROBE LIGHTS
TAIL LIGHT
FIGURE 33-5
C. Remove the two screws (6) from the back side
of the mountingplate.
WARNING
High voltage is involved in the circuit between
the power supply and strobe light assemblies.
Although a bleed-off resistor is incorporated in
the power supply circuit, turn the control switch
for the strobe lights OFF and allow st least 20
minutes to elapse prior to disconnecting the
cables st the power supply or strobe light
assemblies and before handling either of these
units in any way. Failure to observe these
precautions may result in physical injury from
electrical shock.
D. Disconnectthe widng harness plugand remove
the flashtube assembly,
NOTE
On some aircraft the plug may not come
through the wire routing holes. Remove the
pins from the plug and pull individual wires
through the holes to allow the flashtube
assembly to come free.
E. The flashtube assembly must be replaced if
determined to be bad; the flashtube is soldered in
place and is not readily removeablefrom the assembly,
F. If required, the clear lens can be removed from
the flashtube assembly by removing the two lens
retaining screws (7) and pulling the lens free for
replacement orcleaning,
G. Installthe new strobe light assembly in reverse
sequence of removal.
33-41-03
10
TAILLIGHT ASSEMBLY
FIGURE 33-6
(24-1038 thru 24-2999)
(24-3000 thru 24-TBA has only strobe light
assembly in rudder)
B. Disconnect strobe wiring harness connector
fromstrobe power supply hamess and disconnectthe
connectorsfor taillightassembly.
C. Remove the connector plug (2) from the strobe
light widng harness leaving the pins connected to
individualwires.
D: Tie and tape a strong, small diameter cord, 4 to
5 feet long, to the entire wire harness after plug has
been removed.
E. Remove the two screws (3) that secure
strobe/taillightassemblyto rudder (4) and pullthe light
assemblyout so it clears the mounting hole. The wire
harnesswillbe stretchedtightat this point.
F. Carefully begin working the wire harness
throughthe empennage and rudder bulkheadsuntilthe
wire harness can be pulled through the light mounting
hole in the rudder. The rubber grommets at each
bulkheadwill require removal from bulkhead but leave
attached to wire harness. See (Figure 33-6) for this
detail.
12-98
MOONEY AIRCRAFT CORPORATION
M20J
G. Pull light assembly and entire wire harness
through mounting hole in rudder. DO NOT PULL THE
STRONG CORD ALL THE WAY THROUGH ACCESS
PANEL
willduring
need installation.
this to pull Remove
the new cord
wire
harness HOLE.
back inYou
place
from wire harness.
H. Replace complete flashtube/base assembly (5)
if strobelight portion is malfunctioning. The flashtube is
not a replaceable component.
I. Place bulkhead grommets at relative positions on
new harness, after plug (2) is removed from new
harness.
3. AFT POSITION LIGHT
(24-3000thru 24-TBA)
A. Remove two screws that secure aluminum
cover (1) to wing tip (2). Refer to Figure 33-7.
1_
4
5
J. Tie and tape cord to new hamess and carefully
begin to feed wire and grommets back to their
positions.
K. Place all grommets in the bulkheads. Reinstall
plug (2) on new harness and secure the
strobe/navigation light assembly to the rudder.
L. Connect the completed harness and plug from
the strobe light assembly to the harness socket from
the strobe power supply.
M. Check for proper operation.
N. SIN 24-1418 and LATER aircraft have a new
style strobe light installation. There is sufficient wire
available, when ty-raps are cut from coiled harness at
(1), to pull this strobe light assembly out the rudder
light mounting hole. See item (10) (Figure 33-6).
Disconnect light assembly pigtail (11) from connector
at (12) and replace assembly if needed. Secure light
assembly, coil hamess@ (1) and ty-rap harness coils.
3342-00
- NAVIGATION/POSITION LIGHTS
33-42-01
- POSITION LIGHT -
SERVICE AND MAINTENANCE MANUAL
2
/--
_M33-AFT
AFT POSITION LIGHT (24-3000 THRU 24-TBA)
FIGURE 33-7
B. Remove clear lens (3) & gasket to gain access
to lightbulb(4).
REPLACEMENT/SERVICE
1. WING TIP POSITION LIGHTS
(SIN 20-1038 THRU 24-TBA ).
A. Remove the wing tip lens (1) (Figure33-5).
B. Remove the two screws (2) holdingthe position
light lens in place.
C. Pull the lens (red or green) from mounting plate
(5) and removethe lamp (8).
D. Install new lampinto base.
E. Reassemble the light assembly in reverse
sequence.
2. TAIL POSITION LIGHT
(24-0001 thru 24-2999).
A. Remove two screws (3) (Figure 33-6) from the
taillighthousing that secures the lightassembly (5) to
the rudder(4).
B. Remove the clear lens (8), mountingdng (9)
and gasket (7) to gain accessto positionlightlamp (6).
C. Remove lamp (6) with S.D.I. special tool no.
203541 or equivalent.
D. Replace with new lamp and reassembletaillight
assemblyin reversesequence,
C. Pulllight bulb(withspecialpuller if needed)
D. Replacewith new lamp & reassemble lightassy.
in reversesequenceof removal.
33-43-00
- LANDING/TAXI LIGHTS
33-43-01
- LANDING/TAXI LIGHT ADJUSTMENT
PROCEDURES
0NING MOUNTED LANDING/TAXI LIGHTS ONLY)
1. Positionaircraft to face a vertical wall with frontof
nosewheel 7 1l.6 in. from wall. PositionL/H and PJH
main landinggear at exact distance from vertical wall,
IE. parallelto wall.
2. Place four target crosses(+) on verticalwall at the
followingpositions:
A. 36.5 inches up vertical wall from same ground
planeaircraitis restingon.
B. 9.85 feet left and right of nosewheel centerline.
C. 12.375 inchesfurther outboard on both left and
rightside of Step B. target position.
3. Remove access cover behind each landing/taxi
light location on with lower surface.
12-98
33-42-00
11
SERVICE AND MAINTENANCE MANUAL
M20J
4. Turn taxi lights ON, exit aircralt, turn adjusting
screws until light beams are centered on outboard
target crosses(+), left and right,
33-43-01
12
MOONEY AIRCRAFT CORPORATION
5. Repeat Step 4 for landing lights, except center
light beams on inboard target crosses (+), left and
right.
6. Turn lightsOFF, reinstall access covers.
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 34
NAVIGATION AND PITOT STATIC
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 34
NAVIGATION AND PITOT STATIC
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
34-Effectivity .........
34-Corltents..........
34-00-00 ............
34-11-O0............
34-20-00 ............
34-21-00 ............
34-23-00 ............
34-90-00
...........
PAGE
..........
DATE
1/2BLANK ..........
3/4BLANK ..........
5 ...........
6 ...........
7 ...........
8 ...........
9 ...........
10 ...........
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12-98
34-EFFECTIVITY
1/2BLANK
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 34
NAVIGATION AND PITOT STATIC
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
34-00-00 ........
34-10-00 .........
34-10-01
..........
34-11-00 .........
34-11-01
..........
34-12-00 .........
34-12-01
..........
34-13-00 .........
34-13-01
..........
34-20-00 .........
34-20-01
..........
34-21-00 .........
34-21-01
..........
34-22-00 .........
34-22-01
..........
34-23-00 .........
34-23-01 ..........
34-90-00 .........
34-90-01
..........
34-90-02
..........
SUBJECT
........
General ..............
Pitot & Static Air Pressure System ......
Heated Pitot-Trauble Shooting ......
Airspeed Indicator ..........
Airspeed Indicator-Trouble Shooting ....
Vertical Speed Indicator .........
Rate-Of-Climb (VSI) Indicator Trouble Shooting
Altimeter .............
Altimeter-Trouble Shooting.......
Directional Gyro Compass ........
Directional Gyro-Trouble Shooting .....
Turn Coordinator ...........
Turn Coordinator-Trouble Shooting
....
Magnetic Compass ..........
Compass - Trouble Shooting ......
Artificial Hodzon ...........
Gyro-Hodzon - Trouble Shooting .....
Miscellaneous Instruments ........
Clock ............
Outside Air Temperature .......
12-98
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5
5
5
6
6
6
6
6
7
7
7
8
8
8
8
9
9
10
10
10
34-CONTENTS
3/4BLANK
SERVICE AND MAINTENANCE MANUAL
M20J
34-08-00
- GENERAL
All flight instruments are grouped on the shock
mounted panel directly in front of the piloL Flight
instrumentsare operated by: (1) barometricpressure
or bemmetdc impact air pressure differences (2)
vadationsin e ectdc currentdue to mechanicallyvaded
resistance,(3) reference to the earths magneticfield or
(4) aimralt electricalpower,
The glareshisld must be removed and widng or
plumbing disconnected on many of the flight
mstrumenta before they can be removed. Remove
glareshieldattaching screws,center post coverscrews
and carefullyliftcanter postcover and glareshieldfrom
the panel. Disconnect the glareshield lights. Reinstall
the glareshielclin reversesequence,
34-10-00
- PITOT & STATIC AIR PRESSURE
SYSTEM
Static pressureinstrumentsare extremely sensitive to
pressure changes; therefore, the pitot and static
system must be kept free from moisture and
obstructions.Drain the pitot and static systems after
humidor wet weather. If iesthJmentoperation is erratic
or inoperativeafter draining,performthe following:
1. Pitotsystem leak test. (Make sure Master switchis
OFF and Gear Controlis in DOWN position.)
A. Slipendofashortrubberhoseoverpitottube.
B. Close open end of hose;slowlyroll up hose until
airspeedindicatorreads 150 KIAS.
C. Clamp hose and holdfor one minute.
D. If airspeed indicatorfalls more than 10 KIAS,
within one minute, check system for leaks and tighten
linefittings,
E. Repeat steps B, C, and D until obtainingless
than a 10 KIAS indicatorreadingdrop.
34-10-01
MOONEY AIRCRAFT CORPORATION
CAUTION
Release the air pressure slowly by unrolling the
rubbertubing, a sudden release oftheair
pressure may damage the airspeed indicator.
2. Pitot system hose inspections. Alter the pitot
system is checked for leaks, inspect the hose sections
for signs of detariomtion. Check all tubing for
brittleness,checks or cracks particularlyat the bends
or connecting points. When new hose is installed,
recheck the system for leaks using the PITOT
SYSTEM LEAKTEST procedureabove.
3. Static system cleaning. Blow low air pressure
(10-25 PSI). through the lines from the disconnected
line at the aimpeed indicatorto the static ports. Cover
each staticport separatelywhen blowingto insurethat
each line is dear. Instrumenterroror possibledamage
may result if even one pert is clogged with did or
foreignmatter.
CAUTION
NEVER BLOWAIRthroughthelineTOWARD
the INSTRUMENT panel; to do so will seriously
damage the instruments. When blowing back
through
theisinstrument
make the
sureline
thatfrom
no air
blown intopanel,
the
instruments.
4. Static system leak test. The static system should
be checked for leaks in accordance with the
instructionsin Federal AviationRegulation91.411.
CAUTION
To avoid damaging either the airspeed indicator
or the landing gear airspeed safety switch an
equal pressure should be applied to the pitot
side of the indicator while leak testing the static
system.
5. Alternate static source.An alternate static source
valve is providedto change the static air source from
outside the aimraft to inside the cabin. The valve is
located on the lowerpanelimmediatelyto the lett of the
pilots control column.Airspeed indicatorand altimeter
readings will be slightly affected when using the
alternate static source.
- HEATED PITOT TROUBLE SHOOTING
TROUBLE
PROBABLE CAUSE
REMEDY
Tube does notheat or clear
itselfof ice with switchon.
Switchcircuitbreakertdpped.
Reset cimult breaker.
Open circuit.
Repair.
Excessivevoltagedropbetween
batteryand pltot head.
Checkvoltageat pltot head.
Heatingelement burned out.
Replace pitothead.
12-98
34-00-00
5
MOONEY AIRCRAFT CORPORATION
M20J
34-11-00
SERVICE AND MAINTENANCE MANUAL
- AIRSPEEB INDICATOR
Registers airspeed in knots. Air pressure difference between impact air, pitottube, and static air (static ports on
each side of the aircraft tailoone) operates the airspeed indicator.An electricallyheated pitot head prevents ice
obstructionin flight.
The airspeed indicatordial markingsare as follows:
Radial Red Line ..............
YellowAm ................
Green Arc ................
White Arc ......
NOTE m
34-114) 1
195 KIAS
174-195 KIA8
64-174 KIAS
57-110 KIAS
..........
See Section 27-95-00 for stall warning systems.
- AIRSPEED INDICATOR TROUBLE SHOOTING
TROUBLE
PROBABLE CAUSE
Instrumentpointerdoes not
indicateproperly,
-Leak in instrument
Checkfor leak and seal case or in
staticlines lines.
-Obstructionin pitottube.
-Leak in instrumentcase or =n
pitotlines.
Clean outobstruction.
Checkfor leak and seal lines.
Instrumentpointeroscillates.
34-12-00
REMEDY
- VERTICAL SPEED INDICATOR
Convertsbarometricpressure changeswithin the static port linesto aircraftascent or descent rate; readingsare in
feet per minute.
This instrument has a single needle and two adjoining scales that read from 0 to 2000 feet per minute, top side for
ascent rate and bottom side for descent rate. The recessed, slotted screw at the lower left of the instrument case is
used to "zero" the indicator when the aircraft is on the ground.
34-12-01
TROUBLE
- RATE-OF-GMMB INDICATOR TROUBLE SHOOTING. (VERTICAL SPEED INDICATOR).
PROBABLE CAUSE
REMEDY
Pointer does not set on zero.
-Aging ofdiaphragrn.
Pointerfails to respond.
-Obstructionin staticline.
(Includeswater)
Pointer oscillates.
-Leaks in static line.
Disconnectall instrumentsconnected
to the staticline. Check individual
instrumentsand test installationfor
leaks.
-Defective mechanism.
Replace instrument.
34-13-00
Turnsettingscrewto reset pointerat
zero.Tap instrumentwhileresetting.
Disconnectstatic linefrom instruments.
Apply low pressureair (10-25 PSI
max.)to instrumentend of static line.
Check both staticportsfor air flow.
Depress staticdrain valveand check
for water. Keep depressed untilair is
free of moisture.Reconnectstaticline
to instrumentsand leak check.
- ALTIMETER
The altimeter operates by absolute pressure and converts barometric pressure to altitude;reading is in feet above
mean sea level. The altimeter has a fixed dial with three pointers to indicate hundreds, thousands, and tens of
thousands of feet. Barometric pressure is sensed through the static vents. A knob adjusts a movable dial behind a
small window in the face of the main dial to indicate local barornetdc pressure. This corrects the altimeter reading
for prevailing conditions.
34-11-00
6
12-96
SERVICE AND MAINTENANCE MANUAL
34-13-01
M20J
MOONEY AIRCRAFT CORPORATION
- ALTIMETER TROUBLE SHOOTING
TROUBLE
PROBABLE CAUSE
REMEDY
Excessscale error.
-Improper calibratio_adjustment.
Replaceinstrument.
Excessivepointeroscillation,
-Defective mechanism.
Replace instrument.
High reading.
Setting knob is hard to turn.
-Static pressure system leak.
-Wrong lubdcant or lack of
lubdcation.
-Marker out of engagement.
Biminateleakinstaticpressuresystem.
Replace instrument.
-Excessive vibration.
T_hteninstmmontscrewffloose.Replace
_stmmentifscrewis missing.
Cracked or loose cover glass.
-Excessive vibration.
Replace instrument.
Dull or discolored luminous
markings,
Barometdc scale and reference
markers are out of
synchronization with pointers.
Barometric scale and reference
markers are out of
synchronization.
-Age.
Replace instrument.
-Shift in mechanism.
Reset pointers.
-Slippage of mating parts.
Replace instrument.
Innerreferencemarkerfailsto
mow when setlingknob is misted.
Setting knob set-screw is loose
or missing.
34-20-00
Replaceinstrument.
- DIRECTIONAL GYRO COMPASS
This vacuum-operated instrument indicates the heading reference. The directional gym rotor is air ddven and
rotates with its spin axis horizontal The _:nobis used to reset basic directional heading. Vacuum pressure for
satisfactory operation is 4.25 +/- .2 to 5.5 +0.0/-0.2. The vacuum system filters should be changed each 500 hours
or at one year intervals, whichever occurs first. (See Trouble Shooting Chart, for maintenance instructions.)
34-20-01
- DIRECTIONAL GYRO TROUBLE SHOOTING
TROUBLE
PROBABLE CAUSE
Excessivedrift in either
direction,
-Dirty air filter (high vacuum
indication).
-Excessive vibration.
REMEDY
Inspectfilter.Replace if necessary.
Testwithvibmmoter.If vibrationamplitudeis
morethan.004inch,examineshock
mountingsto see ifconneclJons
are
restifctinginstrument.
-Insufficient vacuum.
If vacuum indication is below 4.25 IN. Hg. check as follows:
1. Vacuum regulating valve
1. Adjust vacuum regulating valve.
improperly adjusted.
2. Pump failure.
2. Repair or replace pump.
Instrument is sluggish.
Dial spins continuously in one
direction,
3. Vacuum line kinked, leaking or
too long for its diameter,
3. Locateand if deflective,replace or
repairvacuum line. Check for collasped
innerwall of flexible hose.
-Defective mechanism (worn or
dirty pivots and bearings.)
-Operating limits have been
exceeded
Replace instrument.
Defective mechanism.
Reset the instrument with the aircraft in
level flight.
Replace instrurnenL
12-98
34-20-00
7
MOONEY AIRCRAFT CORPORATION
34-21-00
M20J
SERVICE AND MAINTENANCE MANUAL
- TURN COORDINATOR
A gyro instrumentthat indicates controlcoordinationand rate oftum. This instrumentis electricallydriven.
34-21-01
- TURN COORDINATOR TROUBLE SHOOTING
TROUBLE
PROBABLE CAUSE
Pointerfails to respond.
-Foreign matter lodgedin
instrument.
-No electric current.
Bar does not set level,
In lowtemperature, bar fails to
respond or responds sluggishly
and with insufficient deflection.
Bar sluggish in returning to
level and does not set on level
when stationary.
34-22-00
REMEDY
Replace instrument.
Check voltageat instrument.
-Gimbal and rotorassemblyout
of balance.
-Pitted orworn pivotsor
bearings.
Replace instrument.
-Oil has become too thick.
Replace instrument.
-Insufficient beadng clearance.
Replace instrument.
-Oil or dirt between damping
pistons and cylinders.
Replace instrument.
-Excessive clearance between
rotor and rotor pivots.
Replace instrument.
Replaceinstrument.
- MAGNETIC COMPASS
The magneticcompassdial, graduatedin five-degree increments,is encased in a liquidfilled glass and metalcase.
The unit mountson the stainlesssteel windshieldcenterpost above the glareshield.The compass shouldbe swung
and compensatedat each annual inspectionand whenever new equipmentis installed.To compensatefor N-S
deviation,adjust leftscrew; to compensatefor E-W deviation,adjustdghtscrew.
Degausingof the tubular structuremay be required if compass cannot be compensatedwithin limits.Carefully go
over the entire steel structure with degauser to remove residual magnetism. Recommend Armature Growler to
degausesteel structure.
NOTE
Refer to S.B. M20-15OA, Instruction III, for degausing procedures.
NOTE
Check for outside magnetic influences if excessive compensation is required.
34-22-01
-MAGNETIC COMPASS TROUBLE SHOOTING
TROUBLE
PROBABLE CAUSE
Excessive card error.
-Compass not properly
compensated.
-External magnetic interference.
Compensate instrument.
-improper instrument mounting.
Insufficient liquid.
Align Instrument.
Replace instrument.
Excessive card oscillation.
34-22-00
8
12-98
REMEDY
Locate magnetic interference and
eliminate if possible.
SERVICE AND MAINTENANCE MANUAL
TROUBLE (cont.)
Sluggish card.
Liquid leakage.
Discolored luminous markings
or
discolored damping liquid.
Defective light.
34-23-00
M20J
MOONEY AIRCRAFT CORPORATION
PROBABLE CAUSE
-Weak card magnets.
REMEDY
Replace Instrument.
-Excessive pivot friction or
broken jewel.
-Instrument too heavily
compensated.
-Loose bezel screws.
-Broken cover glass.
Replace instrument.
Correct excess compensation.
Tighten screws.
Replace instrument.
-Defective sealing gaskets.
Replace Instrument.
-Age
Replace instrument.
-Burned out lamp or broken
ctmuit.
Check lamp or wiring continuity.
- ARTIFICIAL HORIZON
The vacuum-powered artificial horizon gyro indicates aircraft, attitude relative to straight and level flight,
Maintenanceis similarto that requiredfor the directionalgyrocompass.
34-23-01
- GYRO-HORIZON TROUBLE SHOOTING
TROUBLE
PROBABLE CAUSE
REMEDY
Horizon bardoes not respond.
-Dirty air filter (highvacuum)
indication,
Examinefilter and clean or replace
instrument,if necessary.
-Insufficientvacuum resulting
from the following:
Correctinsufficient
vacuumasfollows:
1. Vacuum regulatingvalve
impropedyadjusted.
2. Pump failure.
3. Vacuum line kink,lealdngor
too long for its diameter,
Hodzon bar does not settle.
Horizon bar oscillates or
vibrates excessively,
1. Dirty air filter.
1. Adjust valve.
2. Repair or replacepump.
3. Locateand repair.Checkfor collapsed
innerwaUof flexible hose.
-Defective mechanism.
Replace instrument.
-Excessive vibration.
Test with vibrometer. If amplitude is
more than .004 inch, examine
installation to determine whether
connectionsare restrictingmovement of
instrument.
-Shock mountedpanel is
contactingstructure(inadequate
clearance).
Examineshock mountingsand replace
if necessary.
-Excessivevacuum resulting
from the following:
Con_ctfor_ivevacuumasfol[ows:
1. Examine filter and clean or replace if
necessary.
2. Adjust valve.
2. Vacuum regulating valve
improperly adjusted.
3. Defective mechanism.
4. Excessive vibration.
3. Replace instrument.
4. Test withvibrometer, if amplitudeis
morethan .004 inch, examine installation
to determinewhether connections are
restrictingmovement of instrument.
5. Shock mounted panel is
contacting structure
(inadequate clearance).
5. Examine shock mountings and
replace if necessary.
12-98
34-23-OO
9
MOONEY AIRCRAFT CORPORATION
34-90-00
34-90-01
M20J
SERVICE AND MAINTENANCE MANUAL
- MISCELLANEOUS
34-90-02
INSTRUMENTS
Provides the pilot with the free stream outside air
temperaturein degrees centigrade.
- CLOCK
Variousclockoptions are available.The standardclock
ismountedin the left sideof the instrumentpanel,
34-90-00
10
12-98
- OUTSIDE AIR TEMPERATURE
SERVICE AND MAINTENANCE MANUAL
M20J
CHAPTER
OXYGEN
MOONEY AIRCRAFT CORPORATION
35
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 35
OXYGEN
UST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
PAGE
35-Effectivity/Co ntents .......
35-00-00.
• ..........
35-00-02 ............
35-00-02 ............
35-00-02 ............
..........
DATE
1/2BLANK ..........
3 ...........
4 ...........
5 ...........
6 ...........
12-98
12-98
12-98
12-98
12-98
CONTENTS
CHAPTER
SECTION
SUBJECT
...........
35-00-00 ........
35-00-01
35-(:0-02
.........
.........
SUBJECT
General
........
...........
Recharging Procedures .........
Maintenance Practices .........
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35-EFF/CONTENTS
1/2BLANK
SERVICE AND MAINTENANCE MANUAL
M2OJ
MOONEY AIRCRAFT CORPORATION
38-00-00
- GENERAL
The oxygensystem is an optionalinstallationfor sedal
number24-0001 and ON. The system consistsof a 76
(metal),77.1 (composite)or 115.7 (composite)cubic1_.
cylinder located in the tailcone immediatelyeR of the
baggage compartment bulkhead. A reducing valve and
an altitude compensatingvalve are connected to the
_iYlinder
to regulatethe oxygen flow for a givenaltitude,
nes connected to the altitude compensating valve
distributeaviatorsoxygento the pilot and passengers,
The system is activated by either the control handle
being pushed forward (SIN 24-0001 thru 24-1417) or
the control knob rotated (24-1418 & ON) to open the
reducingvalve. A gauge, located on the pilotsarm rest
adjacent to the control, indicates the pressure of the
cylinder. When the cylinder is full the pressure will
indicate 1850 P.S.I. at 21 degree C. (70 degree F.).
The system is serviced through an access opening
located aft of the baggage compartment door.
Standard refill fittings are required to fill the cylinder
WARNING
Proper safety measures must be employed
while oxygen system maintenance is being
performed or a serious fire hazard will be
created. Avoid making sparks and keep all
burning cigarettes or fire away from the vicinity
of oxygen. Make sure that your hands, tools,
and clothing are clean, particularly with respect
to oil or grease, for these will IGNITE upon
contact with pure oxygen under pressure.
35-00-01
- RECHARGING PROCEDURES
with aviatorsoxygen. (Spec. No. MIL-O-27210).
1.The oxygen cylinder should not be used to less
than 100 P.S.I.; contamination may occur to the
cylinder and valve. The valve must be removed and
the cylindercleaned and inspected if this happens.
2. Refill the cylinder with aviators oxygen
Specification No. MIL-O-27210, through the Oxygen
Access
WARNING
Oil, grease or other lubricants in contact with
oxygen create a serious fire hazard, and such
contact must be avoided when handling oxygen
equipment.
WARNING
NO SMOKING when refilling oxygen cylinder.
ure
9
8
li
S/N 24-000]
THRU 24-14J7
(2)
must be Valve
used.
Recharging
Mooney
PIN
870025-501
oxygen recharge
hose assembly is
recommended.
3. The cylinder
contains
1850
P.S.I.
at
21
degree C. (70
degree F.) when
fully
charged.
has
on the
k_
7
3/
CYLINDER
3
2
i\
\
10
DUTLETS
-TO
\
fittings
are
required for this
servicing,
-icwever several
of standard
oxygen
fittings
are in use and a
compatible fitting
for
the
Scott
pressure;charging
correct
See
(Figure 35 - 2) for
4
vs.
.
charging
S/N
I
OXYGEN SYSTEM
24.1418
THRU 24-TBA
pressure.
FIGURE 35-1
12-98
35-00-00
3
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
charged
to
capacity.
Conduct high pressuretest
using cylinder pressure.
Using the su.pplygauge on
the pilot's side wall, note
cylinder pressure. There
shall be no pressure loss
alter 30 minutes.If leakage
exists apply MIL-L-25567,
test solution to
,_
wipe clean and dry. Make
necessary repairs and
retest.
_,
5.
Oxygen
system
purging. Offensive odors
may be removed from the
oxygen system by purging.
The system should also be
purged any time the lines
are left open and subjectto
contamination. Purging is
accomplished
by
connecting a recharging
cart into the system and
to flow
and
outlets until any offensive
odors have been carded
away.
(ReEAC 43.13-1 (*) (* = cun'entrevison)
1. The control cable (3) (Fig. 35-1) is attached to an
actuating arm (4) on reducingvalve (5). This cable is
muted through vadous bulkheads along the leit side
panelto the control(6) at pilotsposition.The control is
WARNING
Avoid making sparks
and keep all burning
cigarettes or fire away
from the vicinity of the
airplane when the outlets are in use. Inspect the
filler connection for cleanliness before
attaching it to the filler valve. Make sure that
your hands, tools, and clothing are clean,
perticuledy from grease and oil stains, for these
contaminants will IGNITE upon contact with
oxygen.
a
posh-pull
assembly
is activated
by a
control
lever cable
assembly
for S/Nthat
24-0001
thin 24-1417
and a rotating knob assembly for S/N 24-1418 & ON.
The supply gauge (7) located adjacent to this control
indicates the pressure of oxygen available in the
system;
The followingprocedures are recommendedto purge
the system:
A. Connect a recharge cart to the tiller valve. Set
the cart pressure regulator to deliver 50 PSI to the
system.
OXYGEN SYSTEM
FIGURE 35-1A
S/N 24-3373 THRU 24-TBA
35-00-02
' MAINTENANCE PRACTICES
2. The pilots outlet (8) and passenger outlets (9)
B. Plug in an oxygen mask at each outlet in the
shou_ be inspected for damage and cleanlinessduring
cabin.
set, crag.
C. Open the cabin doorand place the control knob
3. Inspect the individualoxygen masks, and fittings
in the halfopen position.
fordamage.
D. Allow the system to purge for one hour. If an
4. Oxygen system test procedures.Remove oxygen
offensiveodorstill lingers,continue purgingthe system
line from the regulator and plug the line. Cap open
for an additional hour. If such odors still remain,
regulator port with a clean plastic cap to prevent
replacethe supplycylinder.After the system has been
contamination of the regulator. Conduct the low
adequatelypurged, removethe masks fromthe outlets,
pressure system leak.test using a 70 +1- 10 PSI
place the control knob in the closed position and
oxygen supply plugged into one of the cabin outlets
servicethe systemas describedin 35-00-01.
and a test gauge plugged into another outlet.Apply 70
6. Oxygen cylinder removal. The oxygen cylinder is
+/- 10 PSI to the system, allow 2 minutes for the
locatedin the tailcone aft of the baggage compartment
systemto stabilize,remove oxygen supply.The drop in
bulkhead.Access to the cylinder is obtainedthru the
pressure after 15 minutes shall not exceed five PSIG.
radio compartment access door or the left side of the
Remove temporary plugand ensurethat the cylinderis
aircraftbehind leftwing post.
35-00-02
12-98
4
i
SERVICE AND MAINTENANCE MANUAL
M20J
WARNING
Keep fire, cigarettes and sparks away from the
vicinity of the oxygen cylinder. Oil and grease
will IGNITE upon contact with oxygen under
pressure,
A. Place pilots control lever/knob in the closed
position.
B. Gain access to the cylinderthrough the large
radiocompartmentdoor.
C. Slowly loosen the supply line fittings at the
cylindervalves, (reference Figure 35-1), to relieve any
pressure that may exist in the supply lines. After
presure is relieved,removethe lines.
D. Disconnectthe control cable (3) from the arm
(4) on reducingvalve (5).
E. Cap all open lines and regulatoropenings with
cleanmetal cops.
F. Note relative position of regulator valves and
controlarm priorto removal.
G. Loosen the clamps (11) retaining the cylinder,
while supporting the cylinder, and carefully remove
cylinderand regulatorsfrom its position.
7. Oxygencylinderinstallation.
MOONEY AIRCRAFT CORPORATION
B. Remove caps from lines and carefully inspect all
connections for damage or any foreign substance
before connectionto the new cylinderand valves.
C. Connect all lines to proper fitting and connect
the controlcable (3) to the arm (4) on reducer valve
(5)°
D. Charge the cylinder, if required, to the correct
pressure,see rechargingtable on (Figure 38-2).
E. Place the pilotscontol lever/knob to the open
positionand plug on oxygenmask intothe pilotsoutlet
to checkfor propersystemoperation.
F. Repeat this checkoutprocedurefor alloutlets.
G. Test the system for leaks per leak test check,
paragraph35-00-02, D.
H. Reinstallthe radio compartmentaccess door.
NOTE
Oxygen cylinders must be hydrostatic tested in
accordance with DOT Code of Federal
Regulations,Title 49,ehap.1,para. 173.34.
CAUTION
All oxygen cylinders MUST be replaced every
10,000 recharge cycles.
NOTE
Maximum life for composite oxygen cylinders is
18 years.
NOTE
Maximum life for light weight steel oxygen
cylinders is 24 years.
A. Placeand
new secure.
cylinderand
into position
in clamps
The regulators
new cylinder
should
bepositioned with regulator valves and control arm in
the same position as the removed cylinder assembly
components.
Filling pressures will vary due to ambient temperature in the filling area and the rise of temperature resulting from
compression of the oxygen. Because of this merely filling to 1850 PSIG will not result in a propedy filled cylinder.
Fill to pressures indicated on FIGURE 35-2 for ambient temperatures.
AMBIENT
TEMPERATURE
-OF
FILLING PRESSURE
-PSIG
AMBIENT
TEMPERATURE
2F
FILLING PRESSURE
-PSIG
0
10
20
30
40
1650
1700
1725
1775
1825
50
60
70
80
90
1875
1925
1975
2000
2050
OXYGEN FILLING PRESSURES VS TEMPERATURE
FIGURE 35-2
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35-00-02
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MOONEY AIRCRAFT CORPORATION
M20J
BLANK
35-00-02
6
12-98
SERVICE AND MAINTENANCE MANUAL
SERVICE AND MAINTENANCE MANUAL
M20J
CHAPTER 37
VACUUM
MOONEY AIRCRAFT CORPORATION
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 37
VACUUM
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
37-Effectivity
.........
37-Contents ..........
37-00-00 ............
37-11-04 ............
37-13-09 ............
37-21-95 ............
37-49-99 ............
37-41-09
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SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 37
VACUUM
UST CF EFFECTIVE PAGES
37-00-00 ........
37-10-00 .........
37-11-00
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37-11-01 ............
37-11-02 ............
37-11-03 ............
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37-13-02
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37-13-03
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37-13-04
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37-14-00
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37-14-01 ............
37-14-(_2 .........
37-14-03 ............
37-14-04 ............
37-20-00 .........
37-21-00
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37-21-02 ............
37-21-03 ............
37-21-04 ............
37-21-05 . . ..
37-30-00 .........
37-30-01
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37-30-02
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37-40-00 .........
37-40-01
..........
37-41-00
..........
.........
General ..............
Distribution ............
DryAir Pump ..........
MaintenancePractices ......
Servicing ..........
Removal ..........
Installation-NewPump.......
Vacuum Regulator .........
MaintenancePractices ......
Servicing ..........
Removal ..........
Installation..........
Adjustment..........
Filters ............
MaintenancePractices ........
Servicing ...........
Removal ...........
Installation ...........
Hoses ............
MaintenancePractices ......
- . . . _¢ervicing ..........
Removal ..........
Installation..........
Indicating.............
VacuumSwitch ..........
Description..........
MaintenancePractices ......
Removal ..........
Installation..........
Adjustment..........
Dry Air PumpRepair..........
CouplingInspection& Replacement ....
DryAir Pump Inspection .......
Stand by VacuumSystem (Optional) .....
Servicing ...........
OperationalProcedures. .......
12-98
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3/4BLANK
MOONEY AIRCRAFT CORPORATION
{
M20J
37-00-00
- GENERAL
An engine driven dry air vacuum pump supplies
suction for the vacuum operated gyroscopic flight
instruments, Directional Gyro and Artificial Horizon.
The air is passedthroughseveral filters before entering
the instruments. A vacuum regulator valve is
incorporated to maintain the required operating
vacuum throughoutthe engine power range. Idle RPM
settingswill normally not provide adequate vacuum to
satisfactorilyoperate the instruments.
A vacuum annunciator light will illuminate and flash
when vacuum drops below the setting required to
operatethe instruments.
A standbyvacuum system kit is availablefor the M20J
aircraft.This kitcan be installedby the factory or in the
field. The standbyvacuum system should be activated
manually
whensystem.
=low Vac"
light
on regular
engine driven
Refer
to flashes
Vendor Manual
for
standby vacuum system repair; also refer to Section
37-41-00).
37-10-00
- DISTRIBUTION
37-11-00
- DRY AIR PUMP
A dry air pump (1) (Figure 37-1) requires no
maintenance between replacement. Replacement is
recommendedat 500 Hrs. & engine overhaul.
NOTE
Always replace inoperative pump with new air
pump.
NOTE
Aircraft with optional radar use vacuum pump
(outlet) pressure side to pressurize RTA
compartment in right wing.
I_L
_HU"
'_
•
" '_=_=
_
SERVICE AND MAINTENANCE MANUAL
37-11-01
- MAINTENANCE PRACTICES
Protectionof pneumaticdry air pump when cleaning
the enginecompartmentis veryimportant.
WARNING
Failure to protect the dry air pump from
contamination by engine cleaning solvents may
result in failure of the dry air pump within a
short period of operation.
Prior to washing down engine compartment, the
followingprecautionsmust be taken for better service
life of the pneumaticdryair pump.
1. Dry air pumpcoupling.
CAUTION
Do not blast the air pump coupling area or
other pneumatic system components with
cleaning solvent under high pressure.
Protect coupling area between the pump mounting
flange and the pump housingby wrappinga protective
coveringaroundthat area dudngenginecleaning.
CAUTION
Do not allow protective covering around the
coupling or filterstobecomesaturatedwith
solvent.
The seals in the front frame ofthe housingbehindthe
coupling are designed to keep out foreign material
such as dirt, dust and lightfluid. However, fluid under
highpressurecan be forced by the seals and enter the
pump.
2. Dry air pumpfittings.Before washingthe engine
off, check pump fittings for loosenessof the threaded
fittings.Fluid canseep throughloosethreads and enter
the pump.
I 3. Dry air pump discharge hose
_=_'_
_"1,_
with a red =Remove Before Running
Engine" tag. then clean the engine.
end
of theinstrument
hose
CAUTION
or thesystem)
fitting and
flag
it
(vacuum
Plug
the
Remove plug prior to running
engine.
NOTE
Vacuum pump exhaust tube
should be installed, if not installed
at time of manufacture.
¢_:_
_
retrofit kit
940064,
4.assembly,
Replace vacuum
relief
valve filter
_,w.,,=,,,
_
_
BEFORE
engine.
37-11-02 starting
- SERVICING
The dry air pump requires no servicing.
The internal parts are self-lubricating
and
requirethe NO
afler c,eaning
engine ADDITIONAL
compartment
lubricating.
37-11-03
- REMOVAL
1. Disconnect hoses from dry air
pump.
VACUUM SYSTEM FIGURE 37-1
12-98
37-00-00
5
SERVICE AND MAINTENANCE MANUAL
M20J
2. Remove air pump from engine and discard old
mountinggasket and lockinghardware.
3. Remove fittingsfrom pump. Retain fittingsif they
are serviceable and clean thoroughlybefore reusing,
Discardtwistedffitings and nutswith roundedcomers.
4. Pad inspection. Check the conditionof the AND
20000 pad seal, If the seal shows any signs of oil
leakage, replace the seal. Replace seal if there is any
doubtas to its serviceability.
37-11-04
- INSTALLATION OF NEW PUMP
CAUTION
Never install a pump that has been dropped.
1. Consultthe airframe manufacturer'scurrent parts
manual, Airborae's Application List, or the PMA label
on the pump box to vedfy that the pump is the correct
modelforthe engineand/orsystem.
2. Place the pump mounting flange in a
jaw-protectedvise, with the drive coupling downward
Protect the pump mounting flange with soft metal or
wood.
CAUTION
Pump housing should never be placed directly
in a vise, since clamping across the center
housing will cause an internal failure of the
carbon rotor.
3. Spray the fitting threads with silicone and LET
DRY.
lube. DO NOT use teflon tape, pipe dope or thread
4. Install f_ings in the pump. Hand tighten,
5. Use only a box wrench to tighten fittings to desired
Position. DO NOT make more than one and one half (1
/2) turns beyond hand-tight position.
6. Install new pump mountinggasket (suppliedwith
new pump).
7. Always replace ALL locking washers when
installinga new pump. Tighten all four (4) mounting
nuts- 90 to 110 in. Ibs.
8. Prior to reconnecting hoses, inspectthe inside of
the hose carefully to make sure it is clean and free of
all debds, oils or solvents. Use vacuum or air pressure
to cleanthe lines. Remove the hoses fromthe aircraftif
necessary.
MOONEY AIRCRAFT CORPORATION
37-12-00
-VACUUM REGULATOR
The vacuum regulator (2) (Figure 37-1) is a
spdng-contrulled diaphragm valve for regulating
vacuum for the aircraft pneumatic instrumentsystem.
The vacuum regulator is located on the left.firewall
insidethe cabin,just under glareshield.Adjustvacuum
regulatorvalveaccordingto Section 37-12-05.
37-12-01
- MAINTENANCE PRACTICES
Check general condition of regulator to insure it is
secure and in airworthycondition.
37-12-02
- SERVICING
No servicingis requiredto the regulator otherthanfilter
replacement per Section 5. See Section 37-13-00 for
detailprocedures.
37-12-03
- REMOVAL
1. Underneath the instrument panel, remove both
instrumentlines from vacuumregulator;cap to prevent
foreignobjectsfrom entering them.
2. Engine compartment, remove hose from vacuum
regulator;,cap to prevent foreign objects from entering.
3. Loosen and remove large nut at firawall on
vacuum regulator.
4. Pullregulatoraft to removefrom aircraft.
37-12-04
- INSTALLATION
1. Insideaimratt, insertthe vacuum regulatorthrough
the mountinghole in the firewall.
2. Install large nuton regulator and tighten.
3. Engine compartment, install hose from pump to
regulator and secure.
4. Inside aircraft, install both instrument lines to
regulator and secure.
37-12-05
-ADJUSTMENT
1. Tee a calibratedvacuum gauge into the system
upstreamof the regulator,(see Figure 37-1).
2. Operate engine at a minimum of 1700 engine
RPM. If the vacuumregulatoris not set at 4.75 +/- 0.25
In. Hg., then bend locking tab away from thumb
adjustment screw. Turning screw in, will increase
vacuum;turning screw out, will decrease vacuum. Set
vacuumto read 4.75 +/- .25 In. Hg.
When hose clearance is tight, making it difficult to
reinstallonto the pump fitt rig, spray the rriting at the
hose end with silicone. LET DRY, then installhose by
pushingit straight on.
CAUTION
Do not wiggle hose from side to side. This
could cause particles to be cut from hose ID.
These particles WILL damage the pump.
CAUTION
Change all the filters in the system. This MUST
BE DONE or pump warranty may be voided,
37-11-04
12-98
6
NOTE
After setting regulator, rebend tab back to lock
adjusting screw.
MOONEY AIRCRAFT CORPORATION
37-13-00
M20J
- FILTERS
SERVICE AND MAINTENANCE MANUAL
37-14-03
- REMOVAL
All filters, except the vacuum regulator filter are of
paper-pleatedmaterial design. The vacuum regulator
filteris a foam-gaiter design,
Replace old, hard, cracked or brittle hose, particularly
on the pump inlet. Sections of the inner layers may
separate, causinga pumpfailure.
37-13-01
37.14-04
- MAINTENANCE PRACTICES
- INSTALLATION
1.Airfilterreplacement intervals:
A.Vacuum regulator,garter filter (2),every 100 hours,
B. Instrument filters (5) every 500 hours or at least
once a year, Ref. SECTION 5-10-01.
Where hose clearance is tight, making it difficultto
reinstallit ontothe pumpfitting,spray the fitting at the
hose end with silicone.LET DRY then install hose by
pushing it straight on.
NOTE
2, All filters require routine inspection of condition of
elementand securityof filter in system,
3. ALL RLTERS MUST BE CHANGED WHEN A
NEW PUMP IS INSTALLED,
Do not wiggle hose from side to side. This
could cause particles to be cut from hose ID.
These particles WILL damage the pump.
37-13-02
- SERVICING
All filters require no service except routine inspections.
Replaca with new current configurationfilters,
The alternate instrument filter installation (6) (Figure
37-1) should follow the same cleaning and
replacement schedule,
37-13-03
- REMOVAL
Make certain hoses are connected to the correct
fittings. Incorrectinstallationwill cause damage to the
gyrosystem. Installclamps and secure.
37-20-00
- INDICATING
The indicating system contains a low vacuum light
which illuminates (flashes) when the vacuum is below
4.25 +/- ,2 In. Hg. and a high vacuum light which
illuminates (steady) when the vacuum goes 5.5 (+,2-.0)
In, Hg. or above.
37-21-00
- VACUUM SWITCH
I. Vacuum regulator garter filter is removed by
stretchingit over and offthe regulatorframe,
2. Individual gyro instrument filters unscrew from the
back of the instruments. Some installations have one
main gyro filter in a manifold line.
The vacuum switch (7), Fig. 37-1, is located on either
the Artificial Hodzon (3) or Directional Gyro (4). The
illuminating low and high light adjustments are done on
the switch, not on the annunciator panel.
37-13-04
-INSTALLATION
1. Prior to installing a new vacuum regulatorfilter,
checkthe regulatorto insurethat it is clean from any
foreign material.
The switch is a low and high vacuum sensing
adjustableunit.
2 Reinstallnew gyro filters into instrument bossand
tightensecurely.
CAUTION
Don't over tighten; overtightening will crack the
rear housing,
37-14-00
- HOSES
The hosesare of the aircraf_MIL-H-type.
37-14-01
- MAINTENANCE PRACTICES
Dudngenginecleaning, protectthe dischargehose:
1. Plugthe end 0fthe hoseand flag it witha red"Remove
BeforeRunningEngine"tag, then cleanthe engine.
CAUTION
Remove plug prior to running engine.
Periodic check of all clamps for security is
recommended.
37-14-02
37'21-01
- DESCRIPTION
37-21-02
- MAINTENANCE PRACTICES
Check for switch secudty in instrumentand all wires
secure at switch.
37-21-03
- REMOVAL
Disconnect wires and unscrew from art instrument
housing.
37-21-04
- INSTALLATION
Installswitchin housingand tighten.Reconnectwires.
CAUTION
Do not over tighten. Over tightening will cause
cracking of the aft instrument housing.
- SERVICING
Inspect the inside of the hose carefullyto make sure it
is clean and free of all debris, oils or solvents.
Use vacuum or air pressure to clean the lines. Remove
the hoses from the aircraft if necessary.
12-98
37-13-00
7
SERVICE AND MAINTENANCE MANUAL
M20J
37-21-05
- ADJUSTMENT
1. Remove switch from instrument.Reinstall wires if
removed. Attach poly-vinyl hose, _T_ fitting and
calibratedgauge to vacuumswitch. Connect other end
of hoseto a vacuumsource.
37-30-00
2. Turn aircrall power on. The "HIGH/LOW VAC"
lightshouldflash.
3. App[y vacuumand adjustsourceto 4.25 (+/- .2) ln.
Hg. AdjustLow settingscrew (connectorend of switch)
to illuminatethe low vacuum circuit on the annunciator
panel.
4. Increase vacuum source to 5.5 (+.2-.0) in. Hg.
Punch a small jewelers screw driver through the
poly-vinyltube and into the fitting where the high
setting screw is located and adjust until the
=HIGH/LOWVAC" lighton annunciatoris illuminated.
5. After you have completed switchadjustment turn
aircral_power off.
6. Remove switchfrom hose and gauge,
7. Reinstallswitchin Gyro. Reconnectwires.
CAUTION
Crossing the electrical wires on vacuum switch
will cause the annunciator lights to act in
reverse.
MOONEY AIRCRAFT CORPORATION
- DRY AIR PUMP REPAIR/
REPLACEMENT
37-30-01
-COUPLING INSPECTION AND
REPLACEMENT
1. Remove vacuum pumpfrom engine in accordance
with maintenancemanual, Section37-11-03).
2. If coupling (1) has sheared, remove engine
couplingdrivegear
(2) from engine gear housing and see Section
37-30-20 below.
3. Use a screwdriver or similar tool, remove pump
drive coupling (1) from engine couplingdrive gear (2)
and pump drive gear (3) being careful not to damage
drivepins.
4. Push new drive coupling(1) into place on pump
drivegear (3).
5. Push engine couplingdrive gear (2) into place on
pumpdrive coupling(I).
6. Turn by hand, checkfor rotationof pump.
7. Reinstall pump on eng'_neand test run, refer to
Section37-11-04.
8. Make logbook entry.
37-30-02
- DRY AIR PUMP INSPECTION
VACUUM PUMPS ARE A NON-REPAIRABLE UNIT.
Remove malfunctioningpump and replace with new
pump.
VACUUM PUMPS MAY VARY, BUT
SHEAR COUPLING WILL BE SIMILAR
FOR MOST VACUUM PUMPS.
SMX57-2
DRY AIR PUMP COUPLING INSPECTION
37-21-05
8
12-98
FIGURE 37-2
MOONEY"AIRCRAFT CORPORATION
M20J
NOTE
After installation if regulator valve requires
adjustment refer to Section 37-124)5.
37-40-00
3740-01
37-414)0
SERVICE AND MAINTENANCE MANUAL
- OPERATIONAL PROCEDURES
The OptionalStand-by Vacuum pump for the M20J is
located in the tailcone. Its location is standard, but can
vary slightlydependingon optionalequipmentinstalled
on aircraft.
- STAND BY VACUUM SYSTEM
(OPTIONAL)
-SERVICING
Refer to manufacturersservice and maintenancedata
forthe particularunitinstalled,
If no specificmaintenanceinformationis availablefrom
the manufacturerthefollowingis recummended:
1. Inspectto verify hoses and wires are clear of any
obstructionor interferencawith other componentsthat
may chafe hoses orwires,
2. Inspecthose clampson all fittingsto vedfytightand
secure.
3. Every 100 hour/annual inspection - inspect set
screws in motor/air pump coupling for tightness and
security,
4. A dry air pump requires no maintenance between
replacement. Replacement is recommended at 500
hoursoperatingtime. It is recommended that stand-by
vacuumsystem operatingtime be documented.
5. It is recommended that if the Stand-by Vacuum
System is not used regularly, that every g0 days
(approximately)the Stand-by Vacuum System should
be turned on, in flight, for 20 - 30 minutesto get the
pump and drive motor warm enough to dry out any
condensation that may have accumulated. The
exhaust pert of the dry air pump is routed into the
housing of the electric motor to assist in purging
moistureand debd from the motorassembly.
The Stand-bypumpisto be used only as needed when
the main Vacuum pump malfunctions. The VAC
annunciatorlight will illuminate (RED) either flashing
(low vacuum) or steady (high vacuum) when this
situation occurs. If annunciatorlight is flashing RED,
push STEY VAC switch ON and annunciator light
should extinguishas stand-by vacuum system takes
over for all instrumentoperation.s, if annunciator is
steady RED, monitor flight instruments with
non-vacuumgauges and continuewith flight if feasible,
or land and have vacuum sytem inspected and
repaired.
It is recommendedthat priorto aircraftengine start,the
stand*byvacuum pumpbe tumed ON to verifythat the
vacuum gauge (if equipped)indicatesnormal operating
vacuum and that the gyms spin up and erect. When
the engine starts the check valve closes and the
stand-by vacuum pump system will not produce
enough additional vacuum for any indicationon the
gauge (if equipped)to be noticeable.
12-98
37-40-00
9
SERVICE AND MAINTENANCE MANUAL
M20J
BLAN K
37-41-00
10
12-98
MOONEY AIRCRAFT CORPORATION
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTANANCE MANUAL
CHAPTER 39
ELECTRICAL PANELS AND COMPONENTS
SERVICE AND MAINTANANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 39
ELECTRICAL PANELS AND COMPONENTS
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
39-Effectivity .........
39-Contents..........
39-00-00 ............
39-10-02 ............
39-11-00 ............
39-11-01 ............
39-11-02 ............
39-12-00
...........
39-12-04
...........
39-21-00
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DATE
1/2BLANK ..........
3/4BLANK ..........
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MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTANANCE MANUAL
CHAPTER 39
ELECTRICAL PANELS AND COMPONENTS
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
39-00-00 ........
39-10-00 .........
39-10-01
..........
39-10-02
..........
39-10-03
..........
39-11-00 .........
39-11-01
..........
.............
39-11-02
..........
39-11-03
..........
39-12-00 .........
39-12-01
..........
39-12-02
..........
39-12-03
..........
39-12-04
..........
39-20-00 .........
39-21-00 .........
39-21-01
..........
SUBJECT
........
General ..............
Instrument and Control Panels .......
Flight Instruments .........
Avionics Equipment.........
Engine Instruments and Circuit Breakers .
Flight Instrument Panel .........
Cluster Gauge ..........
-Troubleshooting Guide
.......
LandingGear Switch ........
Landing Gear Safety Override Switch ....
Avionics/Radio Panel .........
Annunciator Panel .........
Emergency Locator Transmitter (ELT) Switch.
Instrument and Radio Light Control Box .
Cigar Lighter ..........
Electrical/Electronic Equipment Rack .....
Miscellaneous Maintenance .......
Equipment Maintenance .......
12-98
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6
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39-CONTENTS
3/4BLANK
SERVICE AND MAINTANANCE MANUAL
M20J
39-00-00
- GENERAL
The instrument panel is divided into three basic
groupings:
MOONEY AIRCRAFT CORPORATION
located steel tubular structurethat will allow the radar
indicatorto be installed,
The panel illustrationdepicted in Figure 39-1 shows
phantom lines for some installations. Model year
improvements, technical improvements or vadous
avionics installationsdictate which instrumentwill be
installedin a givenlocation.
See Section91 for ElectricalSystem Hardware Charts
and Schematics.
l. Flightlnstmments.
2. Avionics/RadioPanel.
3. Engine Instrumentsand CircuitBreaker Panel.
The flight instrument panel is shock mounted. The
radio/avionicspanel generally, has individual racks for
the componentsand are ofthe quick removaltype. The
engine instruments and circuit breaker panel are
located in a quick removal panel which is slanted
toward the pilot.
The
circuit breaker/switches
for theare
standard
optionalaccessoriesand
equipment
locatedand/or
at the
bottom of the flight instrumentpanel on either side of
the pilotscontrolcolumn,
The clustergauge containingfuel quantity and engine
operating gauges is located at the top of the flight
instrumentpanel.
The
annunciatoris located at the top of the avionics
panel.
39-10-00
- INSTRUMENT AND CONTROL
PANELS
39-10-O1
- FLIGHT INSTRUMENTS
1. Glareshield/InstmmentRemoval:
A. Remove the screws attachingthe glareshield
and cover plate and carefullylilt glareshieldto expose
the disconnectsfor the glareshield lights. Disconnect
the wiresand littthe glareshieldoff.
B. Disconnect the plumbing and/or electrical
connectionsfromthe flightinstrumentsto be removed.
The avionics panel has two configurations: Serial
Numbers24-0001 thru 24-0900 has a tubular structure
configurationthat will not accept the radar installation;
Sedal Number24-0901 and ONaircratt have a re-
C. Disconnectand remove anypostlights.
D. Remove the mounting screws securing the
instrumenttothe panel.
E. Removethe instrument by slidingit att from the
panel.
@
_'V
I('_)](_-J
FLIGH_T
INSTRUMENT _-)
i
PANEL
//S/N
t
I)
24-0001 THRU 24-0900 _
_(SHOCK MOUNTED)
I_-_"
@
_
E3_l ATS
ENGINE
CIRCUIT
INSTR.
BKR.
PANEL_,
\
II FLIGHT
INSTRUMENT
I _'1
V
_
lr,r-,,_l fT"-. fT'..... _
UUUll
d
W
,"--"- _
PANEL..
_
_
V
h --''1
_
.11
_
oooo
.....
[AVUNIU.
(
.......
I-'ANLL5
v
S/N
24--0901
& ON
TYPICAL INSTRUMENT AND CONTROL PANEL
I OOOOO(
_laooooc
loB[]a=o
F/mmaaam0 onal
He12-98
PANEL
DOG0(
FIGURE 39-1
39-00-00
5
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTANANCE MANUAL
A. Place instrument into the proper location on
panel.
2.,nste,,ation.
I
B. Insert and secure mounting screws to hold
instrumentto panel.
C. Connect the post lights.
D. Connect all plumbing and/or electrical
connections to the instrument; perform pitot/static leak
check.
/?
/_/
C
_
1]
E. Position the glareshield
so electdeal
connectionscan be madeand secured.
F. Secure glareshieldand cover plate withscrews.
39-10-02
(SnNELATERMDDELS
MAYHAVERIVETS
IN THESELBCATInNS,
THEYMUSTBE gRILLE]]
nUT,& THENREPLACED,)
-AVIONICS EQUIPMENT
customized package to meet the requirements of the
Each avionics harness,
package any
installed
is basically
a
customer.Widng
associated
plumbing or
mechanical mechanisms required for a particular
avionics installation are well secured to prevent any
interference with other components. Removal of these
avionics components will require evaluation of each
installation to determine the proper procedure or
sequence to follow.
1. Removal. Most individual avionics components are
mounted in slide out chassis racks. Loosen the screw
on the face of the component and slide the unit straight
aft to remove.
Some components are not mounted in slide out
chassis. Removal of these units will require the same
sequence as removal of flight instruments in Section
39-10-01.
CAUTION
Radio panel must be stacked from the bottom
to the top.
2. Installation. Install the repaired or new unit in
reverse sequenceof removal.
39-10-03
-ENGINE INSTRUMENTS AND
CIRCUIT BREAKERS
The engine instruments and circuit breaker panel is an
assemblythat can be pulled out as a unit for removal
of any instrument or circuitbreaker,
1. Removal.
A. Remove the glareshield per Section39-10-01.
B. Remove two fiat head screws (B) on outside of
the airplane (Fig. 39-2). These are located forward of
the cabin door hinge and above the cabin air inlet
scoopapproximately4 inchesbelow the windshield.
C. Remove two screws from the face of the panel
at the upper left corner (C)(Figure 39-2).
D. Remove two screws (D) from underneath,
near the edge of the panelface.
39-10-02
6
L
Si IDE AFTF/JRREMBVA
SMX39-£
ENGINE AND CIRCUIT BREAKER PANEL
FIGURE39-2
E. Remove the NAS21919DG clamp (E) from the
steel structure cross brace, underneath the panel,
forward section, see (Figure 39-2).
F. The panel should now be free to slide aft.
approximately 4'5 inches. This will allow access to the
plumbing and electrical connections.
G. Remove the plumbing or the electrical
connections from the instrument or component that will
be removed.
NOTE
In some instances instruments, other than the
one to be removed, must be removed or at least
some wiring, or plumbing disconnected to gain
access to the desired one.
H. Remove thin lexan glass insulation strip if
requiredwhen removingcomponents.
I. Remove the Instrument by removing any post
lights and mountingscrewswhich secure instrumentto
the panel and pull forward. Remove the circuit
breakers by unscrewing nut from stem on each circuit
breaker and pushthe breaker throughthe panel.
2. Installation.
A. Installationof new instrument or circuit breaker
into the panel is accomplishedin reverse sequence of
removal.
B. Insert the lexan insulator sheet in proper
locationto preventany shortcircuits.
39-11-00
- FLIGHT INSTRUMENT PANEL
The flight instrument panel is a shock mounted panel
containing vadous flight instruments for a particular
installationgroup.These instrumentsvaryslightly
12-98
SERVICE AND MAINTANANCE
MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
--MASTER SWITCH
/-AL_RNATOR
,E_SWOON
o
o
FtFTNoFI
VIEW -LOOKING AT FWD SIDE OF PILOT'S PANEL
(TYPICAL EXAMPLE OF LAYOUT - LOCATION OF
IGNITION OPTIONAL SWITCHES MAY VARY WITH INDIVIDUAL
swrrca
AIRCRAFT INSTALLATIONS)
VIEW --
LOOKING AT BACKSIDE OF PILOT'S PANEL.
NOTE: LOCATION OF OPTIONAL SWITCHES MAY VARY WITH
INDIVIDUAL AIRCRAFT INSTALLATIONS.
LANDING
PITOT
TAXI
SHOOK
MOUNT
SPARE
NAVICATI
REOOC"
IJNLIGHTS_
:o..om.u::.Y"
SPAREALTERNATE STATIC SOURCE VALVE
I
CIRCUIT BREAKER/SW]TCHES
12-98
SHOCK MOUNT
SMX39--3
FIGURE 39-3
39-11-00
7
MOONEY AIRCRAFT CORPORATION
M20J
depending upon the avionics package installed. The
panel containsa row of circuit breaker/switches,along
with the master switch, which control most of the
systemsofthe airplane. Referto Figure39-3).
Access for maintenance of the switches or related
widng is obtained by removing the two attachment
screws and pushing the switch through the panel,
There is a common bus bar on some of the switches
that will require loosening or removal for switch
replacement,
CAUTION
Care should be exercised when replacing
wiring or switches to ensure proper alignment
of terminal connections to prevent shorting
between switches,
SERVICE AND MAINTANANCE MANUAL
39-1t-01
-CLUSTER GAUGE
The cluster gauge is located at the top of the flight
panel. Access is obtainedby removingthe glareshield
per section 39-10-01. Cluster gauges have the
capabilityof individualmodulereplacement.
One some configurationsthe entire cluster gauge will
require removal from the panel to allow room to pull
modules out. The nuts on terminal studs need to be
removed so wire terminals can be pulled from studs to
remove the modules from the cluster gauge chassis.
Remove and replace the defective module. Some
configurations have individually removeable gauges.
Loosen screw in lower LH corner, remove gauge by
pullingfrom pilot'sside of instrumentpanel. Replace by
carefully pushinggaugein & securingscrew.
LIGHT BULB ACCESS
®®®®®®
? JoJ
MODULE TERMINAL STUDS ("f"fP)
CONFIGURATION OF CLUSTER GAUGE WILL
VARY BETWEEN MODEL YEAR AIRCRAFT.
LOOSEN SCREW OF INDIVIDUAL GAUGE AND PULL GAUGE OUT.
REPLACE GAUGE INTO CLUSTER, SECURE SCREW.
CLUSTER GAUGE
FIGURE 39-4
TROUBLE SHOOTING GUIDE FOR CLUSTERS
PRESSURE INSTRUMENTS
GAUGE CONDITION
CHECK FOR THESE POSSIBILITIES
Gauge reads full scalewith engineshut down.
39-11-01
8
Wire between sender and gauge disconnected
or open.
Faulty sender.
Faulty gauge.
12-98
SERVICE AND MAINTANANCE MANUAL
M20J
Gauge reads zero when engine is running.
MOONEY AIRCRAFT CORPORATION
Wire between sender and gauge grounded.
Faulty sender.
Faulty gauge
TEMPERATURE INSTRUMENTS
Gaugereadsfullscalewithenginecoolorcold.
Wire between sender and gauge grounded.
Defectivegauge.
Defectivesender.
Gauge readszero when engine is hot.
Wire between sender and gauge is open or
disconnected.
Defective,gauge
Defectivesender.
FUEL SYSTEM
CHECK FOR THESE POSSIBILITIES
GAUGE CONDITION
Gauge indicates empty in the tank.
Grounded wire between sender and gauge.
Defective sender.
Inoperative gauge.
Open sender lead.
Open sender (open resistance element).
Sender not properly grounded to airframe.
Gauge off calibration.Note: Some clusters are
equipped with fuel gauges that have trim pots
and may need re-calibration.
On dual sender systems, the isolated sender
may be grounded.
The lead between the isolated sender and the
grounded sender grounded.
Either sender defective.
Gauge off calibration.
Gauge indicates past full when tank is less than full.
Gauge indicates 1/2 when tank is full.
39-11-02
- LANDING GEAR SWITCH
The landing gear switch is a two position switch
located at the top right side of the flight instrument
panel. The wheel shaped knob must be pulledaft pdor
to raisingor loweringthe switchto activatethe landing
gear actuator.
KNURLED
NUT FOR
REMOVING",.__
SWLTCH -II I_
=_
/
_
_
-
_
I,
_
_
_
_
/LoG
GEAR
OVERRIDE
SWITCH
39-11-03
.
(SOME
OVERRIDE
_
X_/A_SWITCHESARE
LOCATED
ESIOE
THE
I_
Ikl(JL) ([_
__
/
_
L°G
GF'ARsWITCH)
_'LDG GEAR
SELECTOR
SWITCH
1. The glareshieldwill require removalto gain access
to switch for maintenance action (refer to Section
39-10-01).
2. Remove the wire connectionsfrom the back of the
landinggear switch,(Figure39-5),
3, Turn the wheel shaped knob counterclockwiseto
removefrom stem.
4. Remove the nut and washer from the face of the
switch and push switch through the panel.
- LANDING GEAR SAFETY OVERRIDE
SWITCH
(SIN 24-0084, 24-0238 thru 24-TBA)
Landing
gear
safety
overdde
switch
is located
to
landing
gear
switch.
Proper
operation
ofadjacent
landing
65gear
below+7/.4
safety
KIAS.
system will not allow gear to retract
CAUTION
Activation of the gear safety override switch
while the the
aircraft
is on
the to
ground
may cause
landing
gear
retract.
VIEW-LOOKING
ATBACK SIDEOFPILOT'S
PANEL SMX3g-5
1. The landing gear switch or cluster gauge will
require removal to gain access for the removal of the
overrideswitch.
LDG GR SWITCH &LDG GR SAFETY OVERRIDE
FIGURE 39-5
2. Disconnect wire connectors; approximately 6
inches from the switch, by cutting with wire cutters or
opening the knife disconnects.
12-98
39-11-02
9
MOONEY AIRCRAFT CORPORATION
M20J
3. Loosen the nut on the stem and hold the nut
located inside the mounting bracket. The red lens may
need to be removed to fully remove the switch from the
panel and bracket.
4. The light bulb (GE 330) can be replaced a_er the
glareshield is removed by bending a nail or similar rod
(approximately 3/32" diameter) and pushing the red
lens off to the front of the panel. Use a small vacuum
tube puller or soft nosed instrument to pull the bulb
from the socket.
39-12-00
- AVIONICS/RADIO PANEL
The avionics/radiopanel containsequipment installed
per sales order by Mooney Aircraft and other
equipment installed by other sources as the owner
desires.The maintenanceinformationcontained in this
Service and Maintenance Manual describes the
Mooneyfactory installationonly.
The avionics/radio components are removed
installed acoordingtoSection39-10-02,1
and2,
39-12-01
- ANNUNCIATOR PANEL
and
The annunciator panel is located at the top of the
center-mostavionics/radio panel and is not mounted
witha slidein type chassis. Remove this component by
removing the two screws holding cover plate in
position.Remove the glareshield and disconnect the
electricalhamess from back side of the unit. Remove
the screws holding unit in place on the panel and
removefromthe back side of the panel,
SERVICE AND MAINTANANCE MANUAL
A. To gain access to the remote switch and widng
the glareshield will require removal (refer to section
39-10-01).
B. Remove the switch retainilig nut and washer
and push switch through face of panel. Disconnect
wires, remove and replace defective switch.
C. Reconnect wires and test switch for proper
operation.
D. Reinstall glareshield.
NOTE
Other switches located in the ELT placard area
of avionics panel can be removed and replaced
in similarmanner.
39-12-03
-INSTRUMENT AND RADIO LIGHT
CONTROL BOX
The control box for the instrument, radio and
glareshield lights consists of two vadable rheostat
switches, two transistors, two fuses and miscellaneous
wiring contained in a metal box assembly. The
transistors installed in M2OJ aircraft, prior to 24-1214,
are P/N 2N2016 and are no longer being
manufactured.
Check appropriate schematics for proper
wiring.
LOW FUEL WARNING CIRCUIT CALIBRATION.
Refer to Section 24-33-00 paragraph 4.
39-12-02
- EMERGENCY LOCATER
TRANSMITTER (ELT) SWITCH
The remote ELT switch is located at the top of the
avionics panel. The ELT is located in the tailcone and
is accessible by removing the radio access panel on
the leRside of the aircraft fuselage. The ELT antenna
is located on top of the tailcone underneath the
fiberglass dorsal fin. The unit has a three position
switch "ON", "OFF" and "ARM". The correct position of
this switch is "ARM". The remote switch is connected in
parallel to the ELT circuit and will operate correctly
either in the "ARM" mode or the "ON" mode. Normal
operation is in the =ARM" position. Place the remote
switch in the "ON" position and tune the
communication
radio to
121.5
to switch
verify back
that to
a
warbling
tone is heard.
Place
the Mhz
remote
=ARM"positionfor normal operation.
(S//N
24--3201,
24-3218
& ON
HAVE
THE
TRANSISTERSLOCATED
CAUTION
THE
LWR BAGGAGE
COMPARTMENT
Testing of ELT should be conducted only
during the first five (5) minutes after any hour
and no longer than three (3) audible sweeps,
INTHETAILCONE.
"m._NS
RHEOSTATS
.FUSES
view- LOOKING
INTOCONTROL
BOX (UNDER
CAP)
(COVERREMOVED)
1. If the warbling tone is not heard, replacement of
the ELT battery or the unit may be necessary. Follow
ELT manufactures instructionsfor battery replacement.
2. If ELT unit is found to be operating properly and
the system still will not work correctly through the
remoteELT switch, repair or replacementof the switch
or wiringwillbe required.
39-12-00
12-98
10
INSTRUMENT & RADIO LIGHT CONTROL BOX
FIGURE 39-6
(SIN 24-1214 THRU 24-TBA)
SERVICE AND MAINTANANCE MANUAL
f
/'
M20J
The replacement transistors are included in a spares
modification kit, PiN 919003-907, which includes a
transistor,resistor,and instruction sheet describing the
modification
kit will
modify one circuit
only,two kitsprocedures.
are requiredThe
for both
circuits.
M20J aircraft, SIN 24-1214 thru 24-2999, have a
different light control assembly (12V)using a different
transistor and circuitry. (See Figure 39-6).
NOTE
A retrofit kit is available to use the latest light
control assemblyonany12Vaircraff
(940013-#,11Kit).
39-12-04
- CIGAR LIGHTER
The cigar lighter is located at the bottom of the radio
panel immediatelyto the dght of the co-pilotscontrol
column shaft. It is a standard cigar lighter similar to
automotivetype.
MOONEY AIRCRAFT CORPORATION
39-20-00
- ELEOTRICAUELECTRONIC
EQUIPMENT RACK
The electrical equipment rack for the M20 series
aircratt is located in the tailcene just aft of the baggage
compartment bulkhead. Access is gained through the
large access door in the tailcone aft of the left wing
trailing edge. The battery and battery box, auxiliary
power plug receptacle (if installed), ELT and the
various avionics black boxes are mounted on the
electrical equipment rack (See Figure 39-7), (12V NC
only). 24V A/C have the ELT mounted on an accessory
rack further aft in the tailcone. Access is gained
through a panel aft of avionics bay access panel. The
ELT antenna is [ocated under the dorsal fin.
(FIGURE 39-7 REPRESENTS 12 VOLT AIRCRAFT
ONLY)
ELECTRICAL/ELECTRONICS EQUIPMENT RACK
12-98
FIGURE 39-7
39-12-04
11
MOONEY AIRCRAFT CORPORATION
39-21.00
- MISCELLANEOUS
MAINTENANCE
39-21-01
- EQUIPMENT MAINTENANCE
M20J
Refer to SECTION 27-42-00 for Electric Pitch Trim
system Maintenance.
39-21-00
12
12-98
SERVICE AND MAINTANANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20J
CHAPTER 51
STRUCTURES
SERVICE AND MAINTENANCE MANUAL
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 51
STRUCTURES
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT•
51-Effectivity .........
51-Contents ........
51-00-00.
51-10-01 .
51-11-00.
...........
51-12-01 ............
51-12-01
............
51-12-02
...........
51-12-04
...........
51-13-02
...........
51-13-03
51-13-03
...........
51-13-04
51-13-07
51-14-00
...........
51-14-03
•
,
•
.....
51-15-01
51-15-02
...........
51-15-04
...........
51-15-05
...........
PAGE
DATE
1/2BLANK ..........
3/4BLANK ..........
5
6
7 ...........
8 ...........
...........
9
10 ...........
11 ...........
12 ...........
13
14 ...........
15
16
17 ...........
•
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•
18
19
20
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21 ...........
22 ...........
....
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•
°
•
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•
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12-98
51-EFFECTIVITY
1/2BLANK
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 51
STRUCTURES
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT ..........
51-00-00 ........
51-10-00 .........
51-10-01
..........
51-11-00 ..........
51-12-00
..........
51-12-01 ............
51-12-02 ............
51-12-03 ............
51-12-04 ............
51-13-00
..........
51-13-01 ............
51-13-02 ............
51-13-03 ............
51-13-04 ............
51-13-05 ............
51-13-06 ............
51-13-07 ............
51-14-00
..........
51-14-01 ............
51-14-02 ............
51-14-03 ............
51-14-04 ............
51-15-00
..........
51-15-01 ............
51-15-02 ............
51-15-03 .........
..............
51-15-04 ............
51-15-05 ............
51-16-00
..........
DESCRIPTION
........
PAGE
General ............
Structural Repair- General ......
Fastener Replacement ........
Reserved ........
Fuselage Repair
.........
Tubular Structure Repair ,
Taileone Repairs ........
LandingGear & Retraction System Repair .
Flight Control System Repair.....
Wing Repair ..........
8tdnger Repair ........
Main Spar Repair........
Stub Spar Repair ........
Rear Spar Repair ........
Rib Repair
.........
Wing Tip Repair ........
Wing Skin Panel Repair ......
Horizontal Stabilizer & Vertical Fin Repair.
Leading Edge Skin Repair .....
Main spar Repair Outboard of STA. 9.00
Rib Repair
.........
Remating Horizontal Stabilizer to Stinger
Fiberglass Laminates,Repair Procedures . .
Cracks, In Surface Areas ......
Non-Structural Repair
......
Common Structural Laminate Repair
(Metal Insert) ........
Common Structural Laminate Repair
Fiberglass DelaminationRepair ....
Miscellaneous ..........
12-98
5
5
5
7
7
7
10
10
11
11
11
11
13
15
15
15
15
17
17
17
18
18
18
19
20
20
21
22
22
51-CONTENTS
3/4BLANK
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
51-00-00
- GENERAL
The Mooney M20J is an all metal, low wing airplane,
The fuselage cabin area is constructedof a welded
4130 chreme-melybdenumsteel tubular structure.The
steel tubular struutum is covered with non-structural
aluminumskins fastened to the tubular structure by
rivets,boltsand screws,
The tailcone is of semi-monocoque type construction
and is fastened to the tubular structurewith structural
bolts,
at the leadingedge and dvetedtogether at the trailing
edge.
Belly skins are connectedto fuselage bulkheads (SIN
24-0001 thin 24-1417) and are removablefor access
to various componentsand controls located between
thefirewalland the rear spar. These skinscontributeto
the strengthof the aimmft and secodty of each panel is
mandatory.AircraftS/N 24-1418 and later have a one
piece composite bellyskin that coversthe undersideof
the aircraftfromthe exhaustcavityaftto the tailcone.
The wing is a tapered laminarflow one piece wing. It
is constructedwith a one piece, full lengthmain spar.
The spar is constructed from tapered cap strips(7075
aluminum) bolted (huck bolts) to webs (2024
aluminum).Aluminumribsconnectthe mainspar to the
aft stub spar and the rear spar. Extrudedstringers run
the full length of the wing, spaced chordwise for
strengthand skin reinforcement. The skins are sketch
formed, wrap around, 2024-T3 aluminum ranging in
thicknessfrom .025 at the tipto .050 at the fuel tanks,
The front seats are installed on rails which are
attached to the floorboardand structure beneath the
floorboard.The rear seat 2 place, is builtinto the top
of the w ng center sectionfrom the main spar aft to the
rear spar. Aimrsft SIN 24-0001 thru 24-1213 containa
bench type seat with a one piece non-recliningback
rest. S/N24-1214 and ON contain a split type seat,
usingseat
cushions in molded wells over the wing spars and
individuallyrecliningrearseat backs.
TIl.ecompletedwing assemblyis mated to the fuselage
tuoular structure duringfinal assembly at the Mooney
facility. Removal of the wing from the fuselage
structure is required for most over land type
transportation.
51-10-00
The empennage is of similarconstructionto the wing.
A main spar spans the length of the stabilizer. Ribs
connect the main spar to the stub and rear spar. A
stretchformed skin wraps aroundthe leadingedge ribs
and
attachesto
the rear spar
top and
bottom.skins
The
elevators
are constructed
of on
formed
aluminum
fastened to a spar extrusionat the leadingedge and
dvetadtogetherat the trailingedge.
The vertical stabilizer is constructed around a
fabdcatad mainspar assemblywith ribs connectingthe
main and rear spar. A stretch formed, aluminumskin
wraps around the leading edge ribs and is riveted to
the rear spar on both sides. The rudder is constructed
of formed aluminumskins fastenedto a spar extrusion
- STRUCTURAL REPAIR - GENERAL
This section outlines structural repair procadures for
the M20J airplane. It is intended to supplementFAA
Advisory AC 43.13-1( * ) by showing repair methods
specificto MooneyAirplanes. (* = currentrevision)
All structural repair must be: in compliance with AC
43.13-1( * ), unlessspecificMooney factoryrepairs are
recommended, or with the specific approval of a
Federal AviationAdministrationrepresentativewhich is
the final authority in all repairs. This manual is for
general
guidance
and Support
has no Department,
authorized approval
status. The
Customer
Mooney
Aircraft Corporation,Kerrville,Texas, (830) 792-1904
(830) 896-6000 (switchboard),should be consultedfoi"
special repair procedures when repair of damaged
structureis notcovered by publishedinstructions.
51-16-01
- FASTENER REPLACEMENT
1. HUCKBOLT INSTALLATION. The Huck LockboRis
an interference fit fastener used in a dgid joint
structure.A looseor slip fit Huckboft is unacceptable.
The recommendedlimitsfor Huckboltholesare:
HUCK FASTNER
PRE-DRILLED SIZE
DRILL SIZE
HOLE LIMITS
2LPH-T5
ALPPH-T6
R3001-T6
2LA426H-T5
R3007-T6
No. 26 (.147 IN.)
No. 18 (.1695 IN)
No. 18 (.1695 IN)
No. 26 (.147 IN.)
3/16 (.187 IN.)
No. 20 (.161 IN.)
No. 13 (.185 IN.)
No. 13 (.185)
No. 20 (.161 iN.)
No. 7 (201 IN)
.161 TO .1635 IN
.185 TO .187 IN.
.185 TO .187 IN.
.161TO .1635IN.
.2005TO .2025IN
H-ilok fastners may be substitited for Huck
fastners of same diameter and grip.
A. When the Huckbolt is enlarged beyondthe above
limits but is straight and round, the hole may be
considered acceptable, provided that the Huckboft
cannot be pressed into the hole, with normal hand
pressure,
to a depth
thanCheck
50 percent
of hole
the
heaviest matadal
beingmore
secured.
enlarged
size
at beth ends. Select-fit Huckboitsto the oversize
holes.
B. Oversize Huckbolt holes may be repaired by
replacing 2LPH-T5 Huckboits with ALPPH-T6
Huckboltsor NAS 623-2 screws and NAS 1021 No. 8
Hex-lock nuts (or equivalent), provided the pitch
distance is greater than .56 inches and the edge
distance is greater than .33 inches. Huckbolis
ALPPH-T6 and R3001-T6 may be replaced with
R3007-T6 Huckbolts as necessary. Consult the
Customer Support Department, Mooney Aircraft
uorporetion, Kenville, Texas, (830) 896-6000 for
factory recommendations when the preceding
instructionsare inadequateto accomplishthe repair.
12-98
51-00-00
5
MOONEY AIRCRAFT CORPORATION
M20J
To compensate for material thickness tolerances
Huckboltlengthmay be ncreased by one dash number
from the prescribed length.When a Huckboltpin of the
proper length is not available use a pin of the next
longer length. To adjust the grip length, install a
cadmium-plated steel washer .065 inch thick (or a
combinationof not more than two washers .065 inch
and .032 inchthick) underthe Huckboit collar.
SERVICE AND MAINTENANCE MANUAL
The combinedthickness of any two washers shall not
exceed .098 inch. Huckboltsor conical KeystoneLock
blind rivet heads may be cocked no more than .004
inch. Not more than 20 percentofthe fasteners in any
pat-tern, nor more than three fasteners in succession,
may be cocked.
NOTE
Where access
is limited orfor
replacement/repair the following substitution is
permissible.
2. RIVET REMOVAL AND REPLACEMENT.
HUCKBOLT PIN
SUBSTITUTE P/N
(VENDOR)
DESCRIPTION
NAS1465 or R3001-T5
HL2O-5PIN (HI-LOCK)
HL86-5 COLLAR
PIN-PROTRUDING TENSION 160
KSI Ftu
NAS1466 or R3001-T6
HL2O-6PIN (HI-LOCK)
HL86-6 COLLAR
PIN-PROTRUDING TENSION 160
KSI Flu
NAS1475 or R3014-T5
HL19-5 PIN (HI-LOCK)
HL94-5 COLLAR
PIN-100 D. FLUSH SHEAR- 95 KSI
Fsu
NAS1476 or R3014-T6
HL19-6 PIN (HI-LOCK)
HL94-6 COLLAR
PIN-100 D. FLUSH SHEAR- 95 KSI
Fsu
[PART NUMBER CODE]
Hr0
/
"
r
/
"
P
Gdp in 1/16the" (8/16 = .500)MAX
Nominal Dia. in 1/32nds" (5/32 = .156)
Pin Part Number
A. REPLACEMENT-STANDARD SIZE RIVETS,
HOLE OVERSIZE. This repair applies only to odginal
aluminum alloy, steel, or monel rivets of 1/16, 3/32,
1/8, and 5/32 inch diameters. Such rivets may be
replaced as noted and limited below and in the General
Limitations,when the hole only is oversize,
(1) Protruding
Headthe
Joint.
If the edge
distance
is
a minimum
of two times
diameter
of the
original
dvet, it will be permissible to drill for and install the next
standard size larger diameter rivet of the same type
and material as the odginal rivet.
3/32
1/8
5/32
(2) Machine Countersink Joint, Method I. If the
edge distance is a minimum of two times the diameter
of the next standard size larger diameter dvet and the
sheet thickness involved are within the limits specified
for machine countersinking for the next standard size
larger diameter dvet, it will be permissible to drill and
countersink for and install the next size dvet of the
same type and matedal as the original rivet.
The following are limits for machine countersinking:
.025
.032
.040
(3) Machine Countersink Joint, Method II. If the
standard size larger diameter rivet of the same type
edge distance is a minimum of two times the diameter
and matedal as the odginal rivet. Do not redimple. Alter
of the original rivet, it will be permissible to dd]l for and
installation, mill the excess head height flush with the
install the next standard size larger diameter rivet of
surface. This method is subject to the same limitations
the same type and material as the original rivet. Do not
as paragraph 2, A (3).
remachine the countersink. A_er installation, mill the
B. REPLACEMENT-STANDARD SIZE RIVETS,
excess head height flush with the surface.
HOLE AND COUNTERSINK OR DIMPLE OVERSIZE.
(4) Dimpled Joint. If the edge distance is a
This repair applies only to original countersunk head
minimum oftwo times the diameter of the original rivet,
aluminum alloy dvets of 1/16, 3/32, 1/8, and 5/32 inch
it will be permissible to drill for and install the next
diameters. Such dvets may be replaced (as noted and
51-10-01
12-98
6
SERVICE AND MAINTENANCE MANUAL
.....
M20J
limitedbelow)when the hole and countersinkor dimple
is oversize,
(1) Machine Countersink Joint. If the edge
distanceis a minimumof two timesthe diameterof the
next standard size larger diameter dvet and the
countersinkdepth is not beyond the thicknessof the
countersunk sheet, it will be permissibleto rework
accordingto paragraph2, A (3).
(2) Dimpled Joint. If the edge distance is a
minimumof two timesthe diameterof the next standard
size diameterdvetand allthe pads are dimpled,it willbe
permissibleto rework the smaller dimplesto a size to
matchthe oversizedimpleand installDimples in 75S-T6
mustbe hotformedwhen mworked,
(3) Combined Countersink and Dimpled JoinL If
the edge distance is a minimum of two times the
diameter of the next standard size larger diameter
dvet, it will be permissible to rework the smaller
countersinkor dimple to a size t;omatch the oversize
MOONEY AIRCRAFT CORPORATION
dimpleor countersinkand installthe next standardsize
larger dvet accordingto paragraph2, A (4). Dimples in
756-T6 mustbe hot formed when reworked.
C. RIVET HEAD TOLERANCE.
(1) A dvet head will be consideredopen if .001
feeler gauge can be inserted betweenthe head of the
flush or protrudinghead dvet end the top skin. The top
of a flush head rivet must not be below the skin in
whichit is installedby a dimensionof morethan .OO4.
D. RIVET HOLE TOLERANCE.
(1) An enlarged hole is defined as having an
internal diametric dimension in any direction which
exceeds the sum of the ddll diameter normally used
plusten percentofthe diameterof the dvet shank.
(2) The followingtable specifies the maximum
acceptable diametricdimensionsfor the vadous dvst
sizes that occurin multiplelayer assemblieswhichare
"ddlledon assembly=.
DIMENSION
AN470AD3 orAN426AD3
#40 (.095 dia.)
.105 IN.
AN470AD4 or AN426AD4
#30 (.1285 die.)
.141 IN.
NOMINAL DRILL SIZE
AX. ACCEPTABLE DIAMETRIC
I RIVET SIZE
(3) When a hole becomes enlarged beyond the
acceptable diametric limit and the prescribed rivet
cannot be used, the next larger diameter rivet may be
used if (a) four-diameter (4£)) dvet spacing is
maintainedand if (b) two-diameter (2D) edge distance
is maintained,
3. BLIND RIVET INSTALLATION. Ordinadly,where
dvet bur,king is impossible,ChenyLock (CR-2248 and
CR-2249) dvets may be substituted for AD rivets to
repair skins and structuralmembers. However, consult
the Customer Support Department or a representative
of the Federal Aviation Administration before using
blind-typeor hollowdvetsin primarystructure.
CAUTION
The use of blind dvets normally require morefrequent
inspection of the area where used. Inspect for
evidence of loosening of the rivet(s) or crack
developmentthat may cause detedodationof structural
integrity. Solid rivet replacement of blind dvets is
recommended at eadiast possiblemaintenance.
Check existing rivet hole size before installing blind
rivets. When hole is marginal, use the next larger size
dvet to assurefirm attachmenL
4. AN- BOLT, NUT AND WASHER INSTALLATION.
To compensate for matedal thickness tolerances,the
lengthof AN bolts may be increased or decreased by
one dash numberfrom prescribedlength.AN960 regular
washers and AN960L thin washers may be used
interchangeabty
for properbo|tand nutinstallafion.
One regularwasheror one thinwasher may be added to
any boltinstallation.Washers may be usedunderthe bolt
head and/orunderthe nut.AN365 and AN363 nutsmay
be used interchangeably.The AN363 nut is acoeptabie
for higheroperatingtemperatureinstallations.
5. HI-SHEAR RIVET INSTALLATION. When a
hi-sbear rivet pin of the prescribed length is not
available,the next longer lengthpin may be used with
cadmium-platedsteel washers to adjust the pin grip
length. The combined washer thickness shall not
exceed .096inch.
6. MS 20470-AD4 of MS20426-AD4 dyers may
replace spotwelds,(1) per spot, head side & double
flush requirementsdeterminedby form, fit& functionof
assemblyunlessaltematefasteners are specified.
51-11-00
-RESERVED
51-12-00
-FUSELAGE REPAIR
51-t2-01
- TUBULAR STRUCTURE REPAIR
Check tubular structure annually for corrosion and
damage. Intedor panels may require removal to gain
accosstoaraaswhicharedifferenttoinspect.
Refer to AC 43.13-1(*) ( *= current revision letter of
AC43.t3-t)
for ALL tubular
frame repair
procedures. Warped or bent tube memberscan often
be straightened;however,all surroundingweldsshould
be dye checkedfor cracksalter tube straightening.
Use proper material when making weld repairs.
Welding rod meeting the requirementof specification
MIL-R-5632, class2, is recommendedfor oxyacetylene
welding. Electrodes meeting the requirement of
specificationMIL-F-5632-A, class2, (MIL-E-23765/1C,
(Type MIL-70S-2)or AWS A5.18-69, class E705-2
0Jnde 85, Linde CMS-32 or Page AS-35) are
recommended for non-heated area, inert-gas
shielded-arcwelding (Hellarc),Use AIS14130 condition
N steel for replacement and repair of tubes, and for
makingrepairsleeves.
Replacing a member or subassembly is often
advantageousand more feasiblethan repair. Alldetail
12-98
51-11-00
7
MOONEY AIRCRAFT CORPORATION
M20J
tubes or assemblies needed for replacement can be
purchased from Service Parts Department, Mooney
Aircraft Corporation, Louis Schdener Field, Kerrville,
Texas, 78028, tele. (830) 792-2092.
SERVICE AND MAINTENANCE MANUAL
A. Make a 30-degree cut to remove the damaged
portion of the tube; then, remove the burr from the
remaining end.
B. Cut a replacement tube of the same material
(AISI 4130 steel, condition N), same diameter and the
same wall thickness as the original tube.
C. Select a tube with an outer diameter equal to
the inner diameter of the tube to be repaired and with
the same wall thickness.
D. Cut tube to a length five times the outer
diameter of the tube to be spliced.
E. Installinnersleeve in tubeto be repairedso that
its outer end is one and one-half of the original tube
diameter from the nearest end of the diagonal cut;
secure in positionwith a rosetteweld on each side at
one-half the odginal tube diameter from the
inner-sleeve end.
F. Install replacement tube over the inner sleeve
allowing a 1/8 inch gap for welding between the
original and replacement tubes.
1. WELDED PATCH REPAIR OF LOCAL DAMAGE.
Use a welded patch to repair dents, small holes, and
cracks no longer than the outside diameter of the tube
and covering a maximum of 1/4 of the tube
circum-erence. Drill out the crack, smooth the hole
edges, weld the hole or dent, and file the repaired
surfacesmooth.
Form a patchthat will cover twice the diameter of the
tube aroundthe edge ofthe damaged area and twice
the circumferential area of damage as shown in
(Figure 51-1). Weld patchin place,
2. INNER SLEEVE SPLICING.
Use an inner sleeve spliceto partiallyreplace a tube
without increasingthe outside diameter (see Figure
51-2).
LIF NOT GREATER THAN "A"(DIAH.OF TUBE))
DANA
WELDED PATCH-LOCAL DAMAGE REPAIR
FIGURE 51-1
o.
A
innerstubs
sleeve
to the
tube
through
the 1/8 inch gap,
U2A
...............
="=-_
_:_""-----O-"=-i -
,TL.
I
nRI_NAL
EPAIR
TUBE
TUBE/
INS;mE ='_
/ZL-A
RnsErTE
VEL_
"_
forming
anoveda d
bead across the
gap
\
wel
replacement
____
]/2A
_r.].rr._.T_
...........
TL_E
RDSE'-rTE WEL_
C
REPAIR
TUBE
INS._E
_A
IIEA ---_
"
LEAVE 1/8
IN, GAP _
= :
_5A
I/2A
-
INNER SLEEVE SPLICING - FIGURE 51-2
51-12-01
8
12-98
VELBING
2
the
Rosette
tube
to the inner sleeve
in
t_NO
or
more
SERVICE AND MAINTENANCE MANUAL
WELD
HERE
M20J
MOONEY AIRCRAFT CORPORATION
FIRST--_
,
I/2A
FIR
WELI]ING
j-1/2A !2-1/2A,I
SPLIT-SLEEVE SPLICE
,
3. SPLIT-SLEEVE SPLICING. Use the split-sleeve
splice to repair a damaged tube when the parts on
each side of the damage cannot be separated to insert
an inner sleeve (see Figure 51-3).
A. Form the split sleeve from steel tube or sheet
steel when outside diameter of odginal tube is less
than one inch.
B. Form the split sleeve from sheet steel when
outside diameter of the original tube is one inch or
more.
C. Form the split sleeve from the same rnatedal
(AISI 4130 steel, condition N) with at least the same
gauge as the odginal tube.
D. Allow a 1/8 inch gap between sleeve halves for
welding.
E. Weld parallel edges of sleeve to original tube
through 1/8 inch gaps.
F. Weld center of each sleeve half to odginal tube
with two rosette welds spaced one original tube
diameter apart,
4. TENSION FI-FFINGREPLACEMENT
(see Figure 51-4).
A. Cut A and B tubes loose from tension F_ing
340034-7,-8 at welds,
B. Cut C tube at a 30 degree angle seven inches
from bottom of tension fitting.
C. Cut a replacement C tube at a 30 degree angle
and at an appmpdate length to position the tension
fitting. Weld tension fitting in proper position.
D. Drill four 1/4 inch holes for rosette welds 1.9
inches from center of 30 degree cut.
E. Make an inner sleeve five inches long from 4130
steel tube, condition N, with outside diameter to match
inside diameter of tube (3 and with a .085 inch wall
thickness.
F. Insert the inner sleeve in C tube and weld in
place as shown (Figure 51-4).
5. REPAIRS FOR WELDED ASSEMBLIES General. This section does not apply to any control
system tubing or assemblies, engine mounts or heat
treated steel components (except as stated below).
A. Small holes up to a #20 ddil may be closed by
welding with the inert gas shielded arc method.
B. Nicks and ddll marks that are no longer than
1/8" and do not exceed four percent of walt thickness in
depth after cleanup may be smoothed out and
repdmed. Nicks, holes, and cracks that will clean up
with a #20 drill may be drilled and repaired per item A.
.125IN,_/EL]]GAP
",....
FIGURE 51-3
TUBE
== =
TUllE7
I
INSIDE-J!=
_l
TENSIONFITTING
TENSION FITTING REPLACEMENT - FIGURE 51-4
12-98
51-12-01
9
MOONEY AIRCRAFT CORPORATION
M20J
C. The repair of weld beads on best-treated
assemblies may be accomplished without reheat
treatmentwithinthe followinglimits,
(1) The repair bead will not exceed .375 in length
or 113of total lengthof weld, whichever is the lesser,
(2) Onlyone repair perweld bead is allowed.
6. REPAIR OF SPOT WELDS. Failed spot welds' on
aluminum may be repaired by installing an AD470`4
rivetthroughtheweld ifthe damaged area willclean up
witha #30 drill,
7. DENTS. Smell dents which do not exceed five
percentof the diameterof the tube in depthand are no
longerthan one-halfthe tubediameter are acceptable.
81-12-02
-TAILCONE REPAIRS
1. LONGERON SPLICING. Use procedure outlined
in current AC 43.13-1(*) (*=current revision) for
repairingand splicingtailcone Iongerons.(Figure 51-5)
shows acceptable methods for splicing Iongerens.
ConsultAC 43.13-1(*), figures2.28, 2.29 and 2.30 for
fastenerrequirements.
2. TAILCONE STRUCTURAL SKIN REPAIR. Repair
minor tailcone skin damage as shown in current AC
.
:
•
iooI oooooo',
SERVICE AND MAINTENANCE MANUAL
43 13-1(*), I=igum2.24. The dvet pattern for stressed
skin repaim shall be the same as the rivet pattern in
the skin joint immediately forward of the damaged
area. Replace severely damaged structural skin
panels. Install new skin panels to exactly match the
originalskininstallation.
3. NON STRUCTURAL SKIN REPAIR. The skin
covedngthe M20J aircraft tubular fuselage structureis
considerednonstmctural.Patches in nonstructuralskin
are not restricted as to size or shape; however,
appearance and possiblevibrationdamage should be
considered.Either a flush patch, a plate patch, or a
plugpatch may be used.
51-12-03
- LANDING GEAR & RETRACTION
SYSTEM REPAIR
Replace any damaged landing gear or retraction
systemcomponentwith a new part. Repairing landing
gear or retraction system components is not
recommended.After installingnew components,check
gear and retraction system rigging as outlined in
Section 32-20-02. Before retuming the aircraft to
service performa retractiontest and operationalcheck
of the landinggear and retracton system per Section
32-30-01.
7..
"-1
',072
"-_
"-,07;=
.
o o o o io o
M51-5
LONGERON SPLICING - FIGURE 51-5
51-12-02
10
12-98
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
51-12-04
- FLIGHT CONTROL SYSTEM REPAIR
Replace any damaged pdmary control system
componentwith a new part. Repairingprimarycontrol
system components is not recommended. Use only
new hardware when installing new parts. Alter
installationof new parts, check control system travel
and dggingas outlinedin Chapter 27. Before returning
the aircraftto service,flight test the aircraft for proper
controlsystemrigging....
51-13-02
- MAIN SPAR REPAIR
The spar caps inboardof STA 103 are made of 7075
high-strengthmaterial.Replacement of the spar cap is
preferable to repair. However, if a spar cap repair is
thoughtnecessary,an exactdescriptionof the damage
showing location and extent should be sent to the
Customer Service Department, Mooney Aircraft
Corporation,to obtainfactory recommendationsprior
to beginningthe repair.
51-13-00
-WING REPAIR
S1-13-01
- STRINGER REPAIR
1. SPAR CAP REPLACEMENT. To replace a spar
cap, remove the skin covedngthe area to be repaired.
Before removing a laq]e area of wing sldn, attach
temporaryjigsor holdingfixturesto the wingto prevent
wing warpage. When attachinga new spar cap, assure
proper interferencEfitof the replacedhuckbolts.
Stringer splicing may require drilling new holes and
adding rivets between existing rivets to obtain the
requiredtotal number of rivets. Add extra dvsts where
the distance between existing dvets is the greatest.
The p_ch and edge dLstance must conform to AC
43.13-1(*) (*=current revision) requirements (see
Figure 51-6).
I
06E
0;E
LL)
,050
91HENS;IRNSEF EXISTING STRINGERS
._
II
I,,of--1
7
I
_L..l_ ,0BE
Hag SERIES, aO24-T4
H_ SERIESI 20t4-T6
8,0
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¢,u
o\o:,*
oe
,FUCE
.,,E,.,L.
a014-T6
SMH51-6
CF
_
(6 PER SIgE)
STRINGER REPAIR - FIGURE51-6
12-98
_
_.16_!
51-12-04
11
MOONEY AIRCRAFT CORPORATION
M20J
Dudng Installation of the new spar cap all holes
damaged
drilling
or reaming
be
reamed toby
themproper
hole size
recommended
forshould
oversize
huckbolt installation. When installing oversize
huckbolts, consult the Huck Fastener Standards
Manual for proper tolerances. Use proper length
huckbolts.If the bolt is too long, the collar will not
swage properly;if the bolt is too short, the shank will
notcompletelyfill the hole.
Repairscratcheson spar caps that are not deeper than
.003 inch by sanding with No. 400 abrasive paper,
Remove no more than .005 inch of material. Inspect
the sandedarea; use dye penetrantto be sure that the
scratch is completelyremoved. Clean and prime area
where the protectivecoatinghas been removed.
SERVICE AND MAINTENANCE MANUAL
2. SPAR CAP REPAIR. Spar cops outboardof 8TA
103 consist of sheet metal angles backed up with
aluminumextrusionsfrom STA 103 to near STA 150.
Replace or repair damaged extrusions.Do not allow
sphces in a repaired extrusion to coincide with a
spar-web splice when avoidable. Splice sheet-metal
angles with an extrusion of equal area, picking up
existing fasteners. Add extra fasteners to bdng the
minimum number of fasteners to six AD-5 rivets per
side in the vertical flange, and nine AD-4 (or six AD-5)
rivets per side in the horizontal flange. (See Figure
-_1-7).
RIVET CODE FOR STRUCTURAL REPAIRS
4
-_ 5
MS20470AD4-XX
MS20470AD5-XX
_' 4
MS2046AD4-XX
BP
5
CR518-XX
MS2046AD5-XX
SPLICEANGLE NATERIALI7075-T6
._CF_
(4 MIN,EACH SIDE)
_
;5 o5e
I
L_
•7
F
•130
__3
ALPPH-TP (4 HIN,EACH SIDE)
VIEV LOOKING UP
I
VIE'_ LOOKINGI)nVN
SPAR CAP REPAIR - FIGURE 51-7
51-13-02
12
12-98
SMM51-7
SERVICE AND MAINTENANCE MANUAL
!
M20J
3. SPAR WEB REPAIR. Repair all damage to Spar
webs in accordance with AC 43.13-1(*). If there is
extensivedamage to a web that cannot be repairedas
outlined
in AC 43.13-1(*)
(*=current revision),location
consult
the
CustomerService
Departmentgivingexact
and extent of damage.
2. Smooth all roughor sharp edges, and pdme area
to be spliced.
3. Locate new outboardsectionand trim spliceto
witha maximumgap of .020 inch.
4. Fabdcate -501 angles to pick up 30 existing
fastener holes (30 recommended, but 22 minimum),
-503 angles to pick up 15 existing fastener holes (12
minimum), and -505 plate and -507 spacer. (See
Figure 51-8). Pdme angles, plate, and spacer. Rivet
partstogetherusingwet pdmeron all rivets.
51-13-03
-STUB SPAR REPAIR
(Stubspar spliceat wing STA 34.5 +/- 3.0)
(See Figure 51-8).
1. Cut the stub spar halfway between existing rivets
as required by the damage incurred.
\-r_
1
Iq--
98 =
--501 FLAT PATrlERN(.091 NSI C 130,
(
P_m (_1
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MOONEY AIRCRAFT CORPORATION
+
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--503 FLATPATI_RN ('O40 NSJ 4130,
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PICK UP (15) B/P F/_IENERS EACH Sl0E;OF S_LICE 8= -503 ANGLE
PICK UP (30) B/P F/_'IEHERS EACH_DE OF SPLICEc_
i
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SM51--8
STUB SPAR REPAIR - FIGURE 51-8
12-98
51-13-03
13
MOONEY AIRCRAFT
CORPORATION
M20J
SERVICE AND MAINTENANCE
5,9
,,
,,
,,
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0
0
0
0
0
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0
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7,111
REAR SPAR REPAIR
-
FIGURE 51-9
_l-|O
RIB REPAIR
51-13-03
14
-
FIGURE 51-10
12-98
MANUAL
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
51-13-04
- REAR SPAR REPAIR
The rear spar may be spliced between ribs in
accordance with AC 43.13-1(*) (*=current revision)
(see Figure 51-9).
7. Install cherrylock(CR-2248) blind rivets in places
inaccessible for dvet bucking. Add one extra
countersunkblind dvet between every other pair of
cherrylockdvets.
51-13-05
- RIB REPAIR
Replace dbs that are severely damaged. Minor
damage may be repairedas shown (Figure 51-10).
51-13-07
-WING SKIN PANEL REPAIR
Repairwing skinpanelsas prescribedin AC 43.13-1(*)
(*=currantrevision),unlessan entireskinpanel is to be
replaced. Install new skinpanels to exactly match the
odginalskininstallation.Preformedskinpanels may be
obtained _'om the Mooney Service and Marketing
Centers.
1. DamagedDimpleRepairAround InspectionHoles.
Repair damaged dimples around inspection holes
when (a) there are three or more cracked adjacent
dimples, (b) the crack in one or more of the dimples
extendsbeyondthe radiusof the dimpleinto the skin,
and (c) when there are four or more cracked dimples
aroundan inspectionhole (see Figure 51-11).
To repair damaged dimples(a) cut a doublerfrom the
same matedal and gauge as the skin to be repaired,
(b) ddll and countersink100-degree fastener holes in
the doublerto match dimpled fastener holes in skin,
and (c) install doubler around inspectionhole. Use
AN426-AD4 dvets when matedal is .040 inch thick or
greater. Ddll holes using s No. 30 (.128 IN.) drill as
shown in the above illustration.Use AN426-AD3 dvets
when matedal is .032 inch thick or less. Ddll holes
usinga No. 40 (.098 IN.) ddll.
51-13-06
- OUTBOARD WING TiP ASSEMBLY
REPAIR
To repair severe damage to the wing tip outboard of
STA 193.5, it is advisableto replacethe entiretip skin
and db.
1. Locate the new tip db in the exact originaltip db
positionto preventwing tip twisting. Use a temporary
support
position.or Iocator pins to maintain correct wing tip
2. Rivetnew tip db to main and rear spars.
3. Locate new skin, and ddll rivet holesthrough skin
to match existingholesin dbs and stdngers.
4. Rivetskinto db at STA 193.5.
5. Roll skin back on lower wing surface to gain
access to stringers for dvet bucking. Rivet skin to
upperstringers,
6. Rivet skin to tip db starting at leadingedge. Buck
dvetsas far back as possible,
ACCESS COVER
- FIGURE51-11
12-98
51-13-04
15
MOONEY AIRCRAFT CORPORATION
EXlSmNG
',_;-"-_
I
i
M20J -
CRACKED
Radius.
Cracks
extend
through Beyond
the face Dimple
of the
3. Repair
of that
Cracks
Extending
dimple into tile surrounding skin can be repaired as
follows: (see Figure 51-13 ).
DIMPLE
B. Cut a doubler from the same matedal as the
ddll crack
with No.six
60dvets
bit. at four-diameter
skinA.
toStop
be repaired.
Allowfor
I/
ADD"_--
._%..__
"O") ir /_
O_ i
----J
RIB
STRINGER-_i,
circularpatternaroundthe cracked dimple.
rivetC.spacingswith
two-diameter
edge distances
in a
Round the comers
ofthe doubler,
and scarfthe
?
D. Ddll holes for six rivets (same size as those in
sandwiched edges to about .010 inch by .250 inch.
degree dimples in doubler. E. Pdme area to be
repaired
anddvet
installdoubler
with
wet
primer.
the
odginal
pattern), and
drill
and
countersink 1O0
--_"__'i-----'_'J
_oe_1;""
(_
_}--_EXlSTING
SERVICE AND MAINTENANCE MANUAL
'_F
="
SM51-_2
DIMPLE CRACKS REPAIR - FIGURE 51-12
2. Repair of Cracks Wholly Within Dimple Radius.
Surfacecracks on inside (bearing) face of a dimplethat
do not extend through the matedal can be repaired by
sandingout the crack. Cracks in dimpleswhich do not
extend beyond the dimple radius can be repaired by
(a) stop drilling the crack with a No. 60 drill and (b) by
adding dvets, the same size as those in the original
fPoattem,to each side of the cracked dimple. Maintain
ur-diameter (4D) spacing and two-diameter (2D)
edge distances. When odginal dvet pattern has dvets
on only one or two sides of a dimple, only one or two
dvets need be added (see Figure 51-12).
4. Repair of cracked
Circumferentially
Cracked
Dimples.
Circumferentially
dimples (dimples
with
cracks
'.hatappear as an annular mark around the dimple) can
_e repaired by installinga conical washer.
A. Drill throughdimple usinga ddll large enough to
removethe damagedarea.
B. Install doubler as shown in Figure 51-14. Wet
pdme priorto assembly.
C. Countersink dimple hole in skin allowing the
countersinkto extendinto substructure.
D. Install conical washer, use next oversize rivet
size. Wet prime washer and adjacent skin and doubler
surfaces priorto assembly.
E. Drill remainder of the hole to allow installation of
next larger diameter rivet than the rivets in the odgina[
pattern.
I/
6 FASTENERS(SAMESIZE AS ORIGINAL
FASTENERWITHCRACKEDDIMPLE)
WET PRIMER
100 ° CONICAL WASHER
{........ .........
:;T
......
.........
/
/
CRACKED /
DOUBLER(SAMEGAUGE
+
DIMPLE
L_. AS SKIN)--SCARF EDGESTO |
APPROX..010 IN. DEEPAND |
SCARF EDGES
.25 IN. WIDE;ROUNDCORNERS
I
SM51-13
NEXT OVERSIZE RIVET
SM51--1,
DIMPLE CRACKS REPAIR - FIGURE51-13
51-13-07
16
DOUBLER
SUBSTRUCTURE
OVERSIZE HOLE REPAIR - FIGURE 51-14
12-98
SERVICE AND MAINTENANCE MANUAL
51-14-00
M2OJ
MOONEY AIRCRAFT CORPORATION
- HORIZONTAL
STABILIZERFIN
VERTICAL
&
51-14-01
<4_N.PERS_DD
___
- LEADING EDGE
SKIN REPAIR
The hodzontai stabilizer and
vertical fin leading edge intedom
are inaccessiblenear the tailcone.
To repair damage in these areas,
cut a standard (3.0 inches by 6.5
inches) access hole in the lower
side of the stabilizerleading
edge 4_0
REPAIR
and close the access hole by
installing
inspection cover PIN
913000-501.
,7s
_f
j
.o402a24T-_
CLAn
CHERRY
<4Hm._ER
StudLDGK £R 2248
SHSt-16
51-14-02
- MAIN SPAR
REPAIR
SPAR REPAIR (STA. 48.5 Approx.) - FIGURE 51-16
OUTBOARD OF
STA. 9.00
Repairdamage to the horizontalstabilizermainspar by
2. Repair main spar cap damage between STA 34
sfrai;]htening the damaged area and inspecting it
and STA 48.5 by forminga splice angle from 3/4 inch
tullyfor cracks. If cracks are formed, stop ddll or
by 3/4 inch.050 2024-T3 sheet aluminum.Pick up five
remove cracked area.
existing holes and ddll six new dvet holes between
1. Repair damage between S'I:A 9.00 and STA 34.0
existing holes in the skin on each side of damaged
on the spar upper flange, and between STA 9.00 and
area. Install 11 AD4 dvets through angle and skin and
STA 40.0 on the spar lower flange with a splice angle
10 AD4 dvets through angle and web on each side of
formed from .070 AISI 4130 steel, condition N. The
the damaged area. (See Figure 51-15, ViEW B).
splice angle flanges must be as wide as the original
3. Repair main spar damage from STA 48.5 outboard
spar flanges. The splice angle must be long enough to
by installing splice angles made from .040 2024-T3
install 11 AD4 rivets through the skin and 11 dvets
matedal on both side of web using 12 AD4 rivets (6
through the spar web on each side of the damaged
through skin and 6 through web on each side of
area (see Figure 51-15, VIEWA).
damaged area). Pick up three existing holes and drill
Prime splice angle before riveting it to spar. Pick up
three new holes between existing holes on each side
five existingrivet holes and drill six new holesbetween
of damaged area. (See Figure 51-16).
existing rivet holes in the skin at each side of the
4. Repair main spar web damage outboard of STA
damaged area. Install 22 AD4 rivets through splice
34.0, top flange, and STA 48.5, lowerflange by forming
angle and skin, and 22 AD4 dvets throughsplice angle
a splice angle from .050 2024-T3 aluminum.The splice
and sparweb. (See Figure 51-15, VIEWA).
angle web flange should be cut to allow sufficient
coverage of the damaged area of existing web and
long enough to install5 AD4 rivets on the flange on
each side of the damaged area. Pick up 3 existing
dvet holeson flange of spar and ddll 3 new dvst holes
r--.o_o
I
I
'
SAME
LENGTH
_S
_aUE
aB_ SPUCED
"/
.oso splice angle and web on each side of the damauea
between existing holes. Drill 10 rivet holes throuon
r
I
•
_
17_.
35 --t
-,--.To .--•
SPAR REPAIR (BETWEEN STA. 9.0 & 34.0)
FIGURE 51-15
12-98
cracked
area
priorandtodeburr
splice
installation.
Pdmeremoved
splice angle
sparangle
web
and flange before installing spl=-e (see Figure 51-17).
5. Spar webs outboard of STA 48.5 cracked more
than
50% The
of the
web height
may be
(see
web area"
damaged
web sh°uld
be repaired
stop ddlled
°r
aluminum to fit the inside dimensions 0fthe web and
Figure at
51-18).
Form a splice
2024-T3
flange
the damaged
area.plate
Pick from
up 3 .050
existing
dvet
holes on top and bottom flange on each side of
damaged area and drill 2 new AD4 dvet holes
between these existing holes. Pick up all dvet holes
on web under splice plate and drill new rivet holes on
equal spacing around the damaged area similar to
that on Figure 51-18 dvets on each side of damaged
area.
51-14-00
17
MOONEY AIRCRAFT CORPORATION
M2OJ
SERVICE AND MAINTENANCE MANUAL
d:l_
4 (10 EACH SIDE OF CRACK)
_
(6 EACH SIDE OF
HUCKSUMP
COLLAR
GUN
l_-v
SWAGE
SET
oooooooo
STOP
OLO
ov00
CRACKED SPAR WEB AREA)
2024--T3
SM51-17
ET
SPAR REPAIR (O/B of STA. 34.0) - FIGURE 51-17
51-14-03
- RIB REPAIR
The repair of damaged stabilizer and fin dbs is not
feasible in most cases. Damaged dbs should be
replacedwith new parts.
51-14-04
SM51-19
RP-MATINGHORIZON [AL STABILI/-I::RTO
STINGER
FIGURE51-19
51-15-00
- REMATING HORIZONTAL
STABILIZER TO STINGER
- FIBERGLASS LAMINATES,
REPAIR PROCEDURES
When stabilizer repair necessitates removal from the
stinger, remating can be facilitated by using huckbolt
substitutioninformationcontained in Section 51-10-01.
When mating stabilizerto stinger use bent rivet swage
set #5 (see Figure 51-19).
Despitethe fact that fiberglasslaminatesare designed
to withstand considerable abuse, occasional repairs
will be necessary. It is difficult to cover all the various
repair techniques due to such limiting factors as
accessibilityand the extent of damage. The following
stepsoutlinethose procedureswhich are used to make
repairs for the more common type damage to a
fiberglasslaminate.
,_/,4(5 EACH SIDE)
1. Materials used for repairs shall be as specified
below and compatible with the basic resin used in the
.050
2024-T-3
CLAD
o J_ o _ ok _ o _ o '",_
I o _ o _o _ o_,j._
o
o I o
o o
="
o
o
I
o
o
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o
o
o I o
o
I o o o o
oLo
.,_ • • _,. .,, -,_ .'_ _'. _
o
o
'_
_'_
,_1,4(5
fiberglass
Resin - Aerospace
laminate.
Adhesive EA934 Part A
HysolDivision
The Dexter Corporation
Catalyst - AerospaceAdhesive EA934 Part B
Hysol Division
The Dexter Corporation
Alternates:
Resin - Epoxical #606 PatchingAdhesive Resin
o
t_
EACH SIDE)
States
Catalyst -United
Epoxical
#606Gypsum
Patching Adhesive Hardner
United States Gypsum
OR
Resin- Ren Epoxy CG 1304
Ren Plastics company
Lansing, Michigan
Catalyst- Ren Hardener CG 1304
Ren Plastics company
Lansing, Michigan
SM51-1 8,
SPARREPAIR
51-14-03
18
- FIGURE51-18
12-98
SERVICE AND MAINTENANCE MANUAL
M20J
Fire retardation- Antimony Trioxide for fire
retardation, 5% minimum, 10% maximum by Weight of
Resin Content. Must be added to the base resin
(cowling and airintake assembly only).
The manufacturer's bulletins shall be followed for all
mixing ratios and preparation pdor to application.
2. General.
2. Remove any loose particles and frayed fiberglass
strands from the cracked portion.
3. Prepare surface for repair as shown in (Figure
51-20, Figure 51-21, and Figure 51-22).
4. Prior to continuing the repair, all surfaces in the
area of the repair must be cleaned of all contaminates
by wiping the area with a clean cloth saturated with
Methyl-EthYl Ketone.
A. The configuration of repairs are shown for fiat
surface areas; for simplicity; however, the same
techniques can be used for contoured surfaces.
Contoured repairs will require additional considerations
and the proper shapingof the backupplates used for
clamping the laminates together dudng the cudng
cycle,
B. The degree of laminate chamfer and size will
vary based on accessibility, shape of part and the
extent of damage,
CAUTION
Methyl-Ethyl-Ketone (M.E.K.) is a flammable
liquid and should be used with proper
ventilation andthe prescribed safety
equipment.
CAUTION
Fiberglass components are attacked and
deteriorated by the following products: Ketone,
aliphatic esters, chlorinated hydrocarbons, and
slightly softened by aromatic hydrocarbons.
51-15-01
- CRACKS, IN SURFACE AREAS
1. Stop drill all cracks per standard aircraft
procedure.
Q
MOONEY AIRCRAFT CORPORATION
0.5iiiI_
sToP
o.,__
ii:iiii)ii
iiiii_ ';ii!:/__>_'- , i:iiiiiiiiiil)iiiiii_.ii)il-,.)))).)I(IIIIIIIIII)IVlIII
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C,AMFE,
A,_
I
/
CRACK _[-,
(_
_ .....
""
1.5"
:-=
CHAMFER 1.5" EACH
........ ,:-2:
RNBHEBSURFACE ' _
A B
SIDE OF CRACK
THtCKNESS
.02 TO.04
CD
o""',N,S.E"
_
SURFACE
_
'
MASKINGTAPE
T
i
_M_NAT_
THICKNESS
SM51-20
NON-STRUCTURAL REPAIR - FIGURE 51-20
12-98
51-15-01
19
MOONEY AIRCRAFT CORPORATION
51-15-02
M20J
- NON-STRUCTURAL REPAIR
SERVICE AND MAINTENANCE MANUAL
51-15-03
1. Applymaskingtape over crack on finishedsurface
side.
2. Apply wet coat of catalyzed epoxy resin to
chamferedsurface.
3. Apply one layer of #181 fiberglass cloth saturated
withcatalyzedepoxy resin.
4. Add additional plys of #181 fiberglass cloth,
saturated with epoxy resin to attain original laminate
thickness.
5. Applyone additionalply of #181 cloth bridgingthe
totalrepaired area and bond in place,
- COMMON STRUCTURAL
LAMINATE REPAIR
1. Cut away laminateper sketch, roughenrepair area
with 240 sandpaper, clean repair area with M.E.K. apply a wet coat of catalyzed epoxy resin to surfaces.
Then IMMEDIATELY performSteps 2. thru 5.
2. Install chemically cleaned .025 T-3 aluminum
straps, perforatedwith #40 holesapproximately.35 on
centeralldirections.
3. Applywet coat of epoxy resin to aluminumstraps
and apply one or more layers of resin saturated#181
fiberglass cloth to equal the thickness of the original
laminate.
4. Lay wax paper over both sides of the repaired
area while still wet. This prevents adhesion to the
pressureclamp application(paragraph5).
,
375" _
•
,rl
r........_::::.:::::::::_::::_:::_:.._:_:_:/._:..:.::_.:_:_:_=:::_:_._::_:=_::=_=_i
J
I
I
#181 FIBERGLASS
!
ii I
•025 T-3 ALUM.
(SEE SECTION
1
I I
2 O"
I
=
I-]
II
I.
=i:-
/_///////_'_./
_J
/ ,/../
I
/ / //
il
1
,.,_(/ / / / / _/,
5
i
cRAcK
__1
!
"1
CLOTH
51-15-03,
2)
1
/ ,,
Y//////////'/q"-_"LAMINATE
.o3"-J
"
!
!-I
I=
2.75
I
I
I'.:-:::::::::=
":._
"::=._-::::.':-::
"-:.':::-;,--':::.'::
:::::.'.-.-:
::-:::::::-,'=
="::':_":.--._
:::-::_'::":'::=":
"":::::""::":l_
I
I
I
'
S
F
.025 T-3 ALUM
(SEE SECTION
51-15-03,
2)
# 181
CLOTH
BERGLASS
OVERLAP(1) LAYER FIBERGLASS
///"
//]---
ALUM• PLATES
_........._.
...................
....
,...............
;.,.;.;.-:--;
;;i;,,.
,._,,_---,;--_;:;:;--;,.;-/-;
;,,. ........
,;..,.:.:..:_:_
_/////Z_L_
,............
,,.........
,_((_...._::.?./?...-.,
)rz...........
//////_
//_2 ..........................
'.....................................
'.............
" ...........................
" ...........................
'
F
LAMINATE
FINISHED
SURFACE
_
\
X
I_
_FIBERGLASS-- BOND
_
FLUSH
RIVET (TYP.)
IN
PLACE
OVERLAP (1) LAYER RBERGLASS ONLY IF THIS
SM51-21
SIDE IS A NON--FINISHED SURFACE.
COMMON STRUCTURAL LAMINATE REPAIR(METAL INSERT)-FIGURE 51-21
51-15-02
2O
12-98
SERVICE AND MAINTENANCE MANUAL
(
M20J
5. Place rigid aluminum plates on both sides of repair
area and clamp into place with "C" clamps. Permit
laminated repairtocure.
6. Alter the fiberglass repair has cured, remove the
clamps and install #3 AN426A rivets. Flush head to be
on the finishedsurface side. The number of rivets and
spacing will be determined by the size of the repair.
MOONEY AIRCRAFT CORPORATION
Permit this surfacing coat to cure pdor to any additional
applications or further rework.
11. Using #240 sandpaper, sand and blend the
repaired area to match the surrounding surface. Steps
10 and 11 may be repeated to acquire a satisfactory
surface finish.
51-15-04
- COMMON STRUCTURAL LAMINATE
REPAIR (FIBERGLASS-RESIN
COMBINATION)
1. Apply wet coat of catalyzed epoxy resin to
chamfered surface.
2. Apply one layer of#181 fiberglass cloth saturated
with catalyzed epoxy resin.
3. Add additional plys of #181 fiberglass cloth
saturated with epoxy resin to attain original laminate
thickness.
4. Apply one layer of #181 fiberglass cloth to the
non-finished side of laminate, extending 1/2" each side
ofthe chamfer and bond in place.
5. Lay wax paper over both sides of the repaired
area while still wet. This prevents adhesion to the
pressure clamp application (paragraph 6).
7. Apply one on
additional
overlapping
layerand
of #181
fiberglasscloth
the non-finished
surface
bond
in place. Should the opposite side be a non-finished
sudace, an additional layer of fiberglass should be
applied to this side.
8. Upon completion of steps 1 thru 7, permit the
repair to cure before attempting further treatment of
appearance surfaces, if required.
9. Appearance surfaces will normally require the
application of a filler-sealer coating. The appearance
area is to be wiped clean, using a clean cloth saturated
with M.E.K. prior to applying a filler-sealer coating,
10. Mix epoxy resin and catalyst per manufacturers
specifications and apply to the appearance surface
area. Care should be taken to assure as smooth as
possible surface In this particular operation.
4
r-- 0.5"
/1'/
_
STOP DRILL
i
OUTLINE
I_
f
ON--FINISHED
SURFACE
CRACK
...........
.................
"---F, ,SHEO
SURFACE
/y_.LTHICKNESS
_
"---q
O.AM EI TH,O
N
LAM'"A
.02 TO .04 EACH SIDE ('[YP.)
t" .....
_.
@-"l
F
(FIBERGLASS--RESIN
COMBINATION)
COMMON STRUCTURAL LAMINATE REPAIR
12-98
-q
F
SM51-22
FIGURE 51-22
51-15-04
21
MOONEY AIRCRAFT CORPORATION
M20J
6. Place rigid aluminum plates on both sides of repair
area and clamp into place with "C" clamps. Permit
laminate repairto cure.
7. After fiberglass repair has cured, remove clamps
and install #3 AN426 rivets. Flush head to be on
finished surface side. The number of rivets and
spacing will be determined bythe size of the repair,
8. Upon completionof steps 1 thru 7, allow the repair
to cure before attempting further treatment of the
appearancesurface.
9. Appearance surfaces will normally require the
applicationof a filler-sealer coating. The appearance
area isto be wiped clean, usinga clean cloth saturated
with M.E.K. priorto applyinga filler-sealercoating,
10. Mix epoxy resin and catalyst per manufacturer's
specificationsand apply to the appearance surface
area. Care should be taken to assure as smooth as
possiblesurfacein this particularoperation.
Permitthis surfacingcoat to cure prior to any additional
applicationorfurtherrework,
11. Using#240 sandpaper, sand and blend repaired
area to match surroundingsurface. Steps 10 and 11
may be repeated to acquire a satisfactory surface
finish.
51-15-05
-FIBERGLASS DELAMINATION
REPAIR
1. Delamination or ply separation of a fiberglass
product is usuallya result of poorbonding of fiberglass
layers. Generally,this conditionis localized and can be
readilyrepaired by carefullyspreadingapart the plysin
the delamination, and removing loose particles by
blowingclean compressedair intodamaged area.
51-15-05
22
SERVICE AND MAINTENANCE MANUAL
2. Proceed by inserting catalyzed epoxy resin into
the delamination and then immediately clamp the
delamination together. Permit the repair to cure a
minimum of 8 hours before removing clamps.
3. Extensive delamination of a part will be reason
fortotal rejection of the part and shall be scrapped per
standardpractices.
51-16-00
- MISCELLANEOUS
1. ProtectiveCoatings.
A. Parts with protective coatings (such as
Conversion Coated or zinc pdmer) on which the
coatingis scratched, spotfaced, drilled, or in any way
removedmust
beis
recoatedwith
chromateprimer.
EXAMPLE: Part
Conversion zinc
Coated
as detail part.
Dudng replacement the part is spotfaced to receive
bolt and washer. This part must be primed after
spoffacing.
2. Low Pressure, Plastic, or Rubber Line Splices.
Static system lines may be lengthened, shortened, or
spliced to allow the replacement of sections of
damaged lines. The fittings are called out in the Parts
Catalog text pages followingthe illustrationdepicting
the assemblyor componentin question.
If splices are made, the system must be checked for
leaks.
3. Shortening and Lengthening of Tubing, Hoses,
and Flexible Ducting. Mooney manufactured
assemblies of plumbing, tubing, hoses, and flexible
ducting may be modified to allow the use of longer
parts of the same size and materialto be cut and used
as replacements. When the manufactured ends of
flexible ducting are removed the raw edge must be
taped with 3M aluminumfoil tape.
12-98
SERVICE AND MAINTENANCE MANUAL
M20J
CHAPTER 52
DOORS
MOONEY AIRCRAFT CORPORATION
MOONEY AIRCRAFTCORPORATION
M20J
SERVICEAND MAINTENANCE MANUAL
CHAPTER52
DOORS
LIST OF EFFECTIVEPAGES
CHAPTER
SECTION
SUBJECT .........
52-Effectivity.
52-00-00 ...........
52-10-00 .........
52-11-00 ...........
52-30-00 ............
52-31-00 ............
52-31-00 ............
PAGE .......
1/2BLANK ..........
3 ...........
4 ...........
5 ...........
6 ...........
7 ...........
8 ...........
DATE
12-98
12-98
12-98
12-98
12-98
12-98
12-98
TABLEOF CONTENTS
CHAPTER
SECTION
SUBJECT ..........
52-00-00 .
52-10-00
52-11-00 ...........
52-12-00 ........
52-30-00 ......
52-31-00 ...........
SUBJECT .........
PAGE
General..............
•
Cabin Door- MaintenancePractices..
, .
Cabin Door Rigging/AdjustmentProcedures .
. Cabin DoorSeal,
• • . . , . . . .
Baggage CompartmentDoor-MaintenancePractices .
BaggageCompartmentDoor-LatchingMechanism
12-98
3
3
5
5
5
7
52-EFF/CONTENTS
I_2BLANK
SERVICE AND MAINTENANCE MANUAL
52-00-00
M2OJ
-GENERAL
The cabin door is constructedof an inner and outer
aluminum shell fastened together by rivets. It is
providedwith a dual latchingmechanism,1) a lockpin
extends into a mating recaptacle in the lower door
frame and 2) a jaw type latch clamps a special
designed nut in the upper door frame to hold door
securely in place. The door is hinged at the forward
edge by an extruded aluminum hinge. The inner
handle and the outer handle are intemonnected.by
adjustablepush pull tubes. This mechanismis spnng
loadedto an over center positionin the latchedposition
for positive security. Adjustment for each push pull
tube is providedto accurately dg the latching pin and
the jaw type latch. Adjustmentto the special nut at the
top of the door frame can be made for proper closure,
The baggage compartment door is constructedof an
inner and outer aluminum shell fastened together by
rivets. It has dual pin latches that extend into
receptacle fittings on both sides of the door frame
when the exterior handle is closed properly.
The auxiliary exit handle is located on the insideof the
baggagedoor. This handle can be operated onlyfrom
the inside even if the outer handle is locked. A cam
mechanism allows a clevis pin to bypass the outer
handle latch groove and open the two latching pins
which hold the baggage door closed. (Refer to
AFM/POH Section III for specificproceduresto operate
auxiliary exit handle.) This door is hinged at the top
with an extruded pianotype hinge.
A hold open arm is attachedon both doors to assistin
holdingthe dooropenwhen desired.
A door lockis providedfor bothdoors.A single keywill
operate either door lock. The intedor panels require
removal if the door locks are to be removed and
replaced,
52-10-00
- CABIN DOOR - MAINTENANCE
PRACTICES
MOONEY AIRCRAFT CORPORATION
The original door assembly, with hinge attached, is
assembledto the doorframe priorto installationof the
outer skin. The door is placed into position and the
hinge held in place on its mounting plate by sealant
and Iocator rivets or bolts. (The number of Iocator
fastners may vary). These fastners will be underneath
the outer skin.After removal of the outer rivets and/or
screwswork a putty knife or a thin piece of aluminum
betweenthe outer skinand the hinge and betweenthe
hinge and the mountingplate from the inside in order
to break the sealant bond. During this procedure
determinationcan be made where the Iocator fastners
are positioned.If rivets, locate these rivets from the
inside and ddll the bucked head carefully. DO NOT
DRILL THROUGH THE OUTER SKIN. Attempt to
movethe door and hinge att and away from the attach
pointafter each rivet stem is drilled out. The door and
hinge should come free when all sealant bond and
rivetsare removed.
2. Door Repair.
A. The door should be repaired, if applicable,
accordingto standard proceduresin AC 43.13-1( * ).
B. Remove the intedordoor panel if necessaryto
repairthe door assembly.
3. Installation.The old door can be relocated by
usingthe existingholes.The mountingplate shouldbe
thoroughlycleaned of all sealant and foreign material
beforereinstallationof thedoor.
A new door or hinge will require proper positioningof
the doorto obtain proper sealing.
A.
Place door, with new hinge installed, into
position between the outer skin and the mounting
plate.
B. When door is properly positionedmark the new
hingefor mountingusingexistingholes, eitherfrom the
outer skin locationsor from the hinge mountingplate
insidethe cabin.
C. Drill the new holes in hinge carefullywhile door
1. Removal. The cabin door may be removed to
replace or repair the door or to replacea damaged
hinge,
issecurelyin place.
D. Remove the door- deburr holes and clean the
shavingsfromthe area.
A. Remove the interior panel around the door
frame.
NOTE
The rivets and rivet holes originally used as
Iocators do not have to be utilized when
B. Remove the hold open arm at the door frame.
Remove the cotter pinand washers fromthe holdopen
arm shaft. Pull the shaft up from the doubler plate and
clear of the doorframe,
C. Remove the eight (8) screws from outsidethe
airplanethat holdthe front portionofthe hinge in place,
There are also three (3) flush dyers that will require
removalat this location.
D. Carefully drill center of rivet head with a l/8th
inch drill bit until head pops off and rivet stem can be
punchedout.
installing a new door or hinge if proper
alignment can be obtained using another
method.
E. Apply sealant, PRC 1321-B2, or equivalent,
betweenouter skin and hinge support plate on tubular
structure.
F. Reinstalldoor hinge to mountingplate usingthe
eight (8) fiat head screws removedearlier and three (3)
fiat head AD4 standard (AD5 oversize) dvets.
G. Adjustdoor latching mechanismso door closes
and seals during flight. (See door dgging procedures
paragraph52-11-00).
12-98
52-00-00
3
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
"6.
9. ADJUSTMEN"
7. SLIDE
POINT
_
®
LATCH JAWS
,
®
®
""
® _COVER
PLATE
FWD
3. SPRING-_
f
i _:_
4.
,,
Z
HOUSING
ASSEMBLY
8, ADJUSTMENT
POINT
5. UPPER// LINK
"1
/ \
\
ARM
VIEW-LOOKING
L_ 1. LOWER LINK
OUTBOARD AT CABIN DOOR
CABIN DOOR- RIGGING/ADJUSTMENT - FIGURE 52-1
52-10-00
4
[:--_q
12-98
SERVICE AND MAINTENANCE MANUAL
M20J
H. Reinstall the hold open arm with new cotter pin.
i
A. The seal is held to inner door frame with
adhesive.
I. Reinstall interior panels and intedor tdm to door
and cabin.
J. Paint door to match airplane,
52-11-00
MOONEY AIRCRAFT CORPORATION
B. Remove the door inner tdrn panel to gain
access to the door seal.
C. Pull the seal from the door frame.
-CABINDOOR
RIGGING/ADJUSTMENT
PROCEDURES
D. Clean the area with lacquer thinner to help
solten the remaining adhesive. Remove excess
adhesive.
The
cabin door latching
mechanism
has several
adjustmentpointsthat
may be
utilizedto obtain
proper
rigging. (See Figure 52-1.) Removal of the intedor
door panel will be required to gain access to the
adjustmentpoints,
CAUTION
Care should be exercised to keep the lacquer
thinnerfrom dripping on the wing or any other
portion of the airplane.
• Adjust cabin door linkage to satisfy requirements
listedbelow.
A. Latchingpin must contact stdker plate on door
frame the full circumferenceof pinwhen mechanism is
in fulllatchedposition.
B. Latching pin must clear striker plate when
openingor closingthe doorwith latchingmechanism in
full open position,
C. As the lower link (1) and bellcrankarm (2), (Fig.
52-1) travel over center, the spdng (3), is to be
compressedto 1.000 +/- .030.
E. Coat cleaned door frame with adhesive (St.
Clair#4587).
F. Coat bond area of new seal with adhesive (St.
Clair#4587).
G. Let bothapplicationsdry untiltacky.
H. Carefully
place
end of sealthe
into
position
at
bottomof
door and
continuearound
door
untilthe
seal isfirmlyattached.Do not pull tightaround comers.
Cut off any excessseal.
I. When
is propedyattached the door should close
with
littleseal
effort.
NOTE
Washers may be added between spring and link
or 310294-501with
housing
itemsassembly
B and C. (4) to comply
NOTE
Door contour can be altered slightly to conform
with cabin contour, if needed, for proper fit and
sealing•
D. The lower link (1) and bellcrank arm (2), in full
locked position,should be overcenter a minimumof .3
inches,(Figure 52-1).
52-30-00
- BAGGAGE COMPARTMENT
DOOR - MAINTENANCE
PRACTICES
NOTE
It is not necessary that the lower link (1) contact
the upper link (5), (Figure 52-1).
1. Removal.The baggagecompartmentdoor may be
removed
replace or repair the door or to replacea
damaged to
hinge.
E. The outside handle is to be flush with outside
skin when mechanism is in full latched position,
A. Remove the coat hanger anti headliner panel
located inside and directly under the baggage door
F. In full latched position, the upper latch jaws (6)
must be closed and the latch slide cam (7) at the end
of its full travel. See adjustment points (8) and (9).
G. In full open position the upper latch jaws must
be open and slide cam at the end of its full travel.
NOTE
Slide cam (7) moves 1.13 from the full latched
to full open position,
hinge area.
B. Pull insulation backto clear rivet shanks.
C. Center punch rivet heads holding the hinge half
to the fuselage.
D. Carefully ddll dvet heads and punch dvets from
holes.
E. Work a putty knife or thin piece of aluminum
between outer skin and hinge and inner skin frame and
hinge to break sealant bond.
52-12-00
-CABIN DOOR SEAL
The cabin door seal is an extruded rubber seal filled
with a soft foam. Unless deformed or tom, the sealwill
provide adequate sealing around the periphery of the
door during flightconditions.
F. Remove hinge and baggage door assembly
carefully.
G. Clean hinge and hinge mounting area
thoroughlyof all sealantor foreignmaterial.
1. Cabin doorseal replacement,
2. Repair. The baggage door may be repaired per
standard repair procedures in accordance with AC
43.13-1(). Repairsmay be made to the baggage door
on the airplaneif feasible.
12-98
52-11-00
5
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE
NOTE
MANUAL
NEW HINGE
If repairs are to be made the interior trim panel
may require removal.
A. Place old door assembly with new hinge or new
door assembly and new hinge into position and latch
the door in place.
NOTE
3. Installation.
OLD HINGE
A. Place repaired baggage door with old hinge into
paOSitionand cleco securely to assure fit of door;, check
tching operations.
B. Remove door - assure attachment area is clean
of old sealant,
Hinge mounting area should be clean of old
sealant and debris.
B. Push in on door assembly at top, while door is in
the latched position to properly locate the door and
seal in the door frame.
C. Apply sealant, PR 1403-G-B2 or equivalent, to
hinge attachment area between outer skin and inner
frame.
D. Reinstall door assembly with old hinge and
cleco hinge for proper placement.
E. Install rivets (AD4 standard, AD5 oversize) in all
holes,
C. While door is held in place mark holes in new
hinge using holes in outerskin as Iocators.
D. Verify correct position of door prior to ddlling
holes in hinge.
E. Center punch all holes and carefully drill the two
end holes. Fasten clecoes in these and recheck door
assembly fit, if satisfactory continue drilling all holes.
FABRFC C 0VF_R_
BACK)
LATCH
ROD
HITCH
PIN
SPRING--(OVER
CENTER TENSION)
STIFFENER
ANGLE
O
3OOR FRAME
AUX.
(RED)
Q
INSIDE
(CAM SLOT)
CLEVIS PIN
CAM FOLLOWER
y
GOES HERE
LOCK
HANDLE_
CAM SLOT) _"
SPRING ADDED
PER SJ. M20-63
PIN
0
0
{NOB (WHITE)
Q
©
DOOR SEAL NOT SHOWN
EARLY CONFIGURATION LATCH KNOB
BAGGAGE DOOR LATCH MECHANISM
52-30-00
6
12-98
-
FIGURE 52-2
SERVICE AND MAINTENANCE MANUAL
M20J
F, Remove door assembly. Deburr and clean the
area completely pdor to reinstallation of door
assembly,
G. Apply sealant, PR 1403-G-B2 or equivalent, to
hinge mounting are between outer skin and door
frame.
H. Reinstall door assembly and cleco securely in
place,
I. Install rivets, (AD4 standard, AD5 oversize) in all
holes. Remove clecoes as rivets are being installed to
keep door aligned,
52-31-00
-BAGGAGECOMPAR'rMENT
DOOR-LATCHING MECHANISM
The baggage compartment door has a direct
non-adjustablelatching linkage that inserts two pins
into hard points in the door frame. This latching
mechanism can be locked from the outside. An
auxiliary exit mechanism is inconporatedinto this
latching mechanism which allows the door to be
opened, in an emergency, from the inside even if
outsidehandleis locked.
CLIP/PIN
A_Y
S
CR3213-4____===_==
RIVET
_ _
(2 PLC)
LANYARD
(ORIENTATION
CRITICAL)
MOONEY AIRCRAFT CORPORATION
The outside handle has to be unlatched arid fully
opened to correctly re-engage the latching mechanism
alter use of the inside auxiliary exit handle.
(See Figure 52-2).
S/N 24-0001 thru 24-1381 were manufactured without
the spring attached to the clevis pin to actuate the latch
pin linkage. Mooney Service Instruction M20-63 dated
Apdl, 1953 adds this modification to these aircraft. This
ensures a positive reengagement of the clevis pin into
the cam slot of outside handle for proper actuation of
the outside latching mechanism (see Figure 52-2).
See Mooney Service Bulletin M20-239 for retrofit
configurationof auxiliary exit handle, inside latching
mechanism(See Figure 52-3).
NOTE
FollowtheproceduresintheAirplane
Flight
ManuaI-PilotsOperating Handbook(AFM/POH)
for reengagement of the mechanism for proper
outside handle operation.
NITCH
PIg/f_HANDLE
_
CR32:3-4-3 RIVET
AN960-4 WASHER (2)
(i UNDER RIVET HEAD 8, 1
ON BACK SIDE OF HANDLE,)
NOT
HSP0470-4
RIVET
(OPT)
SH52"2
AUXILIARY EXIT LATCH RETROFIT (CNVSB M20-239)-FIGURE 52-3
12-98
52-31-00
7
MOONEY AIRCRAFT CORPORATION
M20J
BLANK
52-31-00
8
12-98
SERVICE AND MAINTENANCE MANUAL
SERVICE AND MAINTENANCE MANUAL
M20J
CHAPTER 53
FUSELAGE
MOONEY AIRCRAFT CORPORATION
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 53
FUSELAGE
UST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
53-Eff/Contents .........
53-00-00 ............
53-30-00 ............
53-30-00 ............
53-40-00 ............
53-40-02 ............
53-40-03 ............
PAGE
..........
DATE
1/2BLANK ..........
3 ...........
4 ...........
5 ...........
6 ...........
7 ...........
8 ...........
12-98
12-98
12-98
12-98
12-98
12-98
12-98
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
53-00-00 ........
53-10-00 .........
53-10-01
..........
53-10-02
..........
53-30-00 .........
53-40-00 .........
53-40.01
..........
53-40-02
..........
53-40-03
..........
53-40-04
..........
SUBJECT
........
General ..............
Main Frame ............
Tubular Structure Frame .......
Tailcone Structure .........
Plates/Skins ............
Attach Fittings ...........
Wing Attach Fittings. ........
Empennage Attach Fittings .......
Main Landing Gear Atta{ h Points .....
Engine Mount Attach Points
......
12-98
PAGE
3
3
3
3
4
6
6
7
8
8
53-EFF/CONTENTS
1/2BLANK
SERVICE AND MAINTENANCE MANUAL
(
M20J
53-00-00
-GENERAL
The Mooney M20J forward fuselage is constructed
from 4130 chromemolybdenum tubular steel. The
tubular steel sub-assemblies are hellarc welded in
fixtures, inspected and then assembled intothe main
cabin fixtureand heliaro welded into a cabin enclosure.
The assembled steel structure is sand blasted and
dipped in zinc chromate palmerfor corrosionprotection.
The tailcone bulkheads,formers, etc., are formed from
sheet aluminumon a hydro press or drop hammer at
Mooney Aircraft Corporation. These components,
along with stringers, clips, brackets, etc., are
assembled together on a fixture and built into the all
fuselage assembly. All air ducts, control brackets,
electricalharnesses and antennas are assembled into
the tailconeduring this manufacturingstage.
The forward cabin enclosure and the taiicone are
mated and this fuselage assembly advances down the
MOONEY AIRCRAFT CORPORATION
production line to the point of mating with the wing
assembly.
53-10-00
-MAIN FRAME
53-10-01
- TUBULAR STRUCTURE FRAME
The basic cabin enclosure is shown in (Figure 53-1).
Serial No. 24-0001 thru 24-0900 have a windshield
frame that will not accept the radar display unit. SIN
24-0901 and ON have had the wishbonesubassembly
(1) changed to allow this unit to be installed.
53-10-02
. TAILCONE STRUCTURE
The tailcone is of semi-monocoqueconstruction.The
internal structure is shown on (Figure 53-2). The
forward cabin structure (1) is bolted to the tailcone with
TUBULAR STRUCTURE FRAME - FIGURE 53-1
12-98
53-00-00
3
MOONEY AIRCRAFT CORPORATION
M20J
load beadng portion of the assembly. The avionics
equipmentshelf (3) spans the tailcone widthto provide
rigidityand space for avionics components.The battery
box (5) and battery are located in this area also. The
hat rack shelf (4) provides rigidity as well as storage
space.
SERVICE AND MAINTENANCE MANUAL
The empennage attach points(6) are attached to the
rear bulkhead (7) with tabs extending forward and
attachedto the tailcone structure.
NOTE
Refer to Mooney Service Instruction M20-76 for
sealing of tailcone and smooth belly skin.
8
8
4-,
/-8
/ .-i
/ /
0
23
3
_HJK53-2
TAILCONE STRUCTURE - FIGURE 53-2
53-30-00
- PLATES/SKINS
The fuselage tubular structure is covered with
aluminumskins after mating to the tailcone. The skins
are riveted and boltedto support angles, formers and
brackets. These skins are non structural coveringsto
form the outside contour of the forward fuselage
section.
The skins covering the tailcone are an integralpart of
the structure. Repair or replacement of these skins
should be according to AC 43.13-1(*) (*--currentrev.)
SECTION 3.
The belly skins are removableto provideaccessto all
components and control systems located below the
floorboard. See (Figure 53-3) and table following for
component location and identification.SIN 24-1418
and lateraircrafthave a one piece fiberglassbelly skin.
The fuselage assembly and tailcone have panels,
coversor doors at various locationsto provideaccess
to the interiorfor inspectionor maintenance purposes.
(See Figure 53-3).
53-30-00
4
12-98
NOTE
PR-1766-B2 sealant should be used on all
fuselage skin laps to provide a good electrical
ground plane.
SERVICE AND MAINTENANCE MANUAL
M20J
/
3
MOONEY AIRCRAFT CORPORATION
2
21
1713
'
,
(24-1418
AND
_/N)
SMJ53-3
INSPECTION PANEL AND COVERS - FIGURE 5&-3
12-98
53-30-00
5
MOONEY AIRCRAFT CORPORATION
M2OJ
SERVICE AND MAINTENANCE MANUAL
TABLE FOR FIGURE 53-3 - COMPONENT IDENTIFICATION
1. Cabin Door.
12.
Landing GearActuator, Gascolator, Fuel
Selector Valve.
13. Landing Gear Retract Tubes, Flap Indicator
Cable.
14. Electdc Flap Actuator.
15. Stabilizer Trim Screw and Stops.
16, 17, 18. Elevator/Rudder/Aileron Control
System, Bellcranks, Rod End Beadngs.
19. Nose Wheel Steering System, Cowl Flap
Controls.
20. RudderTorque Tube.
21. LandingGear RetracUonTubes.
22. Tail-LightHarness Connections.
23. EmpennageAttachment, Trim Jack Screw.
2. Engine Compartment ,Oil access
3. Baggage Door.
4. Elevator/Rudder Control Stops.
5. Empennage Attachment.
6. AvionicsBlackboxes, Batteries.
6A. E.L.T. access.
7. StabilizerTrim Jack Screw.
8. EmpennageAttachment.
9. Elevator/RudderControls,Rod End
Bearings& Travel Stops.
10. RudderControls,Elevators& Rudder
Be,cranks.
24.
All components (12-18, 21).
11. Brake Master Cylinders, Rudder Torque
Tube, Electdc Fuel Pump.
53-40-00
- ATTACH FITTINGS
53-40-01
- WING ATTACH Frn'INGS
The wing assembly (1) is attached to the fuselage
assembly (2) using structural hardware (4); (see
Figure 53-4 for locations). Vadous type of fittings (3)
are used to propedy distribute the load between the
wing andthe fuselage.
2
3 (TYP. LH
3
_
12-98
(TYP.
LH & RH)
4
(TYP,
LH 8, RH)
& RH)
(TyP,
WING/FUSELAGE ATTACH FII-rINGS
53-40-00
6
(TYP. LH
8, RH)
4
FIGURE 53-4
SERVICE AND MAINTENANCE MANUAL
M2OJ
53-40-02
- EMPENNAGE ATTACH FITTINGS
The empennage assembly is manufactured as a unit
(1), (Figure 53-5) with the vertical fin and the
horizontal stabilizer using common components.This
unit attaches to the tailcone empennage attach points
(1) (Figure 53-6), using two structural bolts (2) (Figure
53-5) passing through two top hinges (3) (Figure 53-5).
The bottom attac[n point (4) (Figure 53-5) on the
MOONEY AIRCRAFT CORPORATION
empennage assembly secures the stabilizer trim jack
screw (5) (Figure 53-5) and (4) (Figure 53-6). Lateral
stabilityofthe empennageassemblyis controlledwith
an articulated hinge assembly (2) (Figure 53-6)
attachedto the rear bulkhead (3) (Figure 53-6) of the
tailcone. The hinge attach pin (6) (Figure 53-5) is held
in place with a coffer pin at each end.
/
$H53-5
I
EMPENNAGE ASSEMBLY ATTACH FiTTiNGS - FIGURE 53-5
12-98
53-40-02
7
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
53-40-03
- MAIN LANDING GEAR ATTACH
POINTS
The main landing gear assembly is a welded heat
treated 4130 chromemolybdenum steel assembly.
The leg assembly(1) is supported at the forward end
by the tension strap fitting (2) attached to the wing
main spar assembly (3) (Figure 53-7) and provides
one of the hard points for the main landing gear
assembly. The leg assembly (1) is supported at the
rear by a bracket (4) attached to the stub spar
assembly (5), This is the rear hard point. The main
landing gear truss assembly (5) also attaches to the
tension strap fitting (2) on the main spar, The brass
beadng (7) should be inspected at any scheduled
maintenance action for wear. Grease fittings (8) are
1 installed at pivot points of the main landing gear
assembly for lubrication per Section 5. (Reference
Figure 53-7).
3
53-40-04
- ENGINE MOUNT ATTACH POINTS
4
The engine mount is attached to hard points built into
2 the forward portion ofthe tubular structure.
The upper hard points (1) (Figure 53-8) are for
NAS1304 boiLsinstalled for tension loads. The lower
hard points (2) are for fittings outside the firewa[I
which allow a clevis on each side of the engine mount
to be attached for shear loads. AN4 bolts are used for
this application.
_4s3--6
TAILCONE-EMPENNAGE
ATTACH POINTS
FIGURE 53-6
SMX53-7
SNJK53-8
MAIN LANDING GEAR ASSEMBLY ATTACH POINTS
FIGURE 53-7
53-40-03
8
12-98
ENGINE MOUNT ATTACH POINT - FIGURE 53-8
SERVICE AND MAINTENANCE MANUAL
M20J
CHAPTER 55
STABILIZERS
MOONEY AIRCRAFT CORPORATION
MOONEY AIRCRAFT CORPORATION
M20J
SERVlCE AND MAINTENANCE MANUAL
CHAPTER 55
STABILIZERS
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ........
55-Eft/Contents.........
55-00-00 ..........
55-20-00 ............
55-30-01 ............
55-40-02 ............
PAGE
..........
DATE
1/2BLANK ..........
3 ...........
4 ...........
5 ...........
6 ...........
12-98
12-98
12-98
12-98
12-98
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
55-90-90 ........
55-10-00 .........
55-10-01
..........
55-10-02
..........
55-20-00 .........
55-20-01
..........
55-20-02
..........
55-30-00 .........
55-30-01
..........
55-30-02
..........
55-40-00 .........
55-40-01
..........
55-40-02
..........
SUBJECT
........
General ..............
Horizontal Stabilizer .........
Horizontal Stabilizer- Removal ......
Horizontal Stabilizer- Installation .....
Elevator .............
Elevator- Removal .........
Elevator- Installation ........
Vertical Stabilizer. .........
Vertical Stabilizer- Removal ......
Vertical Stabilizer- Installation .....
Rudder .............
Rudder - Removal ........
Rudder- Installation
........
12-98
PAGE
3
3
3
3
4
4
4
4
5
5
5
5
5
55-EFF/CONTENTS
1/2BLANK
SERVICE AND MAINTENANCE MANUAL
55-00-00
(
M20J
- GENERAL
MOONEY AIRCRAFT CORPORATION
55-10-00
The M20J empennage assembly is a vadable
incidence tail-plane consisting of a horizontal and
vertical stabilizer built as a unit. (Refer to Chapter 53
for the attachment of the empennage to the fuselage.)
The hodzontal and vertical stabilizer are constructed of
formed sheet metal ribs attached to a forward and aft
spar assembly covered with stretch formed skins. The
hodzontal stabilizer has a stub spar that spans a
portion of the stabilizer.
The elevator and rudder are constructed from an
extruded loading edge spar assembly covered with
formed skins,
The elevators and the rudder have balance weights
permanently installedforstabilization during flight.
- HORIZONTAL STABILIZER
The main sparassembly (1) (Fig. 55-1) is formed from
aluminumsheet into a channel. Angle doublers (2, 3
and 4) are formed and riveted to the spar through the
web section. The stub spar (5) is a channel formed
from aluminum sheet reinforced with a joggled channel
(6) at the center section. The rear spar (7) is an
extrusion attaching to the aft end of the ribs and
containsthehingefittings(8)fortheelevators.
The ribs (9) are assembled in sections to the front and
rear face of each spar assembly to form the air foil.
Stretch formed skins (10) are fastened to the ribs,
spars and doublers to form the complete horizontal
stabilizer structure.
The aft vertical fin spar (11) is attached to the
horizontal stabilizer structure through a bracket (12)
which is fastened securely to the stabilizer rear spar
assembly (7). (Reference Figure 55-1),
11
8
9
_
g
s
DETAIL A
5
8
3
8
SHX55-1
HORIZONTAL STABILIZER - FIGURE 55-1
55-10-01
- HORIZONTAL STABILIZER REMOVAL
The faidng located on the tailcone, covering the gap
between the tailcone and empennage assembly, will
require removal to gain access to empennage
attaching hardware. Section 53-40-02 describes the
attaching points for the empennage assembly. Refer to
this section for the removal of the empennage
assembly from the airplane.
55-10-02
- HORIZONTAL STABILIZER INSTALLATION
Referto Section 53-40-02 for installation.
12-98
55-00-00
3
MOONEY AIRCRAFT CORPORATION
M20J
55-20-00
-ELEVATOR
The elevators on the M20J consist of a left. and fight
hand assembly attached through ball bearing fittings
(1) to the rear spar of the horizontal stabilizer
reference Figure 55-2).
SERVICE AND MAINTENANCE MANUAL
The elevator control horn (2) is connected to the
inboardleadingedge
eachconnectedto
elevator (R.H.
L.H.).
Both controlhorns areofthen
theand
elevator
flight controlbellcrank.
6
3
6
2
A
ELEVATOR - FIGURE 55-2
55-20-02
The elevator skins (4) are stretch formed for the upper
and lower surface of the elevator. There are no ribs in
the elevator between the inboard and the outboard
fibs. The skins are attached to the leading edge
extrusion(5) and the fibs (6) with blind rivets. Each
formed corrogationis matchedon top and bottomskins
and rivetsare installedfor strength and dgiditythrough
each corrogation,
A lead balance weight (7) is installed in each elevator
tip with iron rivets (8). (Reference Figure 55-2). See
Section 27-91-00 for balancing procedures on the
elevators,
55-20-01
- ELEVATOR - REMOVAL
Remove the AN3 bolts from each control horn and
push-pulltube bearing, then remove the AN3 boltsand
hardware from each hinge fitting on both elevators.
55-20-00
4
- ELEVATOR - INSTALLATION
WARNING
Each new, repaired or repainted elevator should
be checked for balance per Section 27-91-00.
The elevators are installed in reverse order of
removal. Nominal torque values for AN3 bolts
are to be used (see section 5-20-01 for torque
table.)
55-30-00
-VERTICALSTABILIZER
The main spar assembly(1) (Ref. Fig. 55-3) is formed
from aluminumsheet. Formed angle doublers(2) are
nested insidethe main spar channel and dvetedto the
web. The rear spar (3) is an extrusionused to attach
the art end of the sectioned fibs (4). The stub spar (5)
is also formed from sheet aluminum.A doubler channel
(6) is attached to the vertical stabilizer stub and the
stub spar of the horizontal stabilizer. This attach
channel is securely bolted to stinger bulkhead
brackets.
12-98
SERVICE AND MAINTENANCE MANUAL
M20J
The mainspar doublers and angles 7, 8 and 9 provide
attach points for the stinger and the horizontal
stabilizerspar. (Refer to Figure 55-3).
The skins (1 IN are stretch formed in 2 sections and
rivetedto the lbs and spar.
The three rudder attachfittings(11) are mountedto the
rear spar extrusion.
55-30-01
-VERTICALSTABILIZERREMOVAL
The
hodzontalstabilizerare
removed
as a
unit verticaland
with the stinger
assembly. Remove
the faidng
located on
theempennage.
tailcone which
coversthe
gapdescdbes
between
tailcone
and
Section
53-40-02
the attaching points for the complete empennage
assembly. Refer to this section for removal of the
empennage assemblyfrom the airplane,
4
_
J
MOONEY AIRCRAFT CORPOP,ATION
55-30-02
- VERTICAL STABILIZER INSTALLATION
Refer to Section53-40-02 for installation.
55-40-00
The rudder on the M20J is constructedthe same as
the elevator with stretch formed skins (1) (Ref. Fig.
55-4) riveted to an extruded leading edge (2) and
rivetedtogether at the trailing edge. The rudder lower
skins (3) are drop hammerformed left and right halves
rivetedto the upperskins,a rib assembly (4) and at the
leadingand trailing edge. A stiffener (5) is to support
the lower rudder ball bearing hinge fitting (6). A
weather seal (7) is includedin the assembly.
The rudder controlhorn (8) is attached with the center
hinge fitting (9) to the rear flange of the front spar at
the junction of the lower db assembly (10). A brace
arm on the horn assemblyis attached to a f_ing (11)
on the lower rib (10). The upper hinge fitting (12) is
attachedto the rear flange of the frontsparjust under
the top rib assembly(13) and the balanceweight (14),
(refer to Figure 55-4).
The balance weight (14) is installed with four iron
dvets (15). See section 27-91-00 for balancing
procedures on the
rudder. - REMOVAL
55-40-01
- RUDDER
Remove the AN3 bolt from the control horn and
push-pull tube bearing, then remove the three AN3
bolts
and hardware
from per
eachparagraph
hinge fitting.
Disconnect
electdcal
connections
33-41-03,2,A
_
13/f
thru E.
55-40-02
- RUDDER INSTALLATION
WARNING
Each new, repaired or repainted rudder should
be checked for balance per section 27-91-00
prior to installation,
The rudder is installed in reverse order of removal.
Nominaltorque valves for AN3 bolts are to be used.
(See Section 5-20-01 for torquetable).
10
VERTICAL STABILIZERASSEMBLY
- RUDDER
- FIGURE 55-3
12-98
55-30-01
5
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
15
, 1
\
\
11
\
\ 12
\
1
\
9
\
I
/"
16
\2
4
_
5
7
RUDDER ASSEMBLY
55-40-02
6
-/
'
5
3
4
6
3
\
12-98
- FIGURE 55-4
MOONEY AIRCRAFT CORPORATION
M20J
CHAPTER 56
WINDOWS
SERVICE AND MAINTENANCE MANUAL
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 56
WINDOWS
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
PAGE
56-Eft/Contents .......
56-00-00...........
56-22-00 ............
56-50-00 ............
58-50-00 ............
..........
DATE
1/2BLANK ........
3 ...........
4 ...........
5 .........
6 .........
12-98
12-98
12-98
12-98
12-98
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
56-90-00 ........
56-00-01
..........
56-20-00 .........
56-21-00 .........
56-21-01
..........
56-21-02
..........
5B-22-00 .........
56-22-01
..........
56-22-02
..........
56-23-00 .........
56-50-00 .........
SUBJECT
General
........
..............
Cleaning Acrylic..........
Windshield and Cabin Windows .......
Windshield ............
Windshield Removal ........
Windshield - Installation........
Cabin Windows ...........
Cabin WIndows - Removal .......
Cabin Windows - Installation .....
Storm Windows ...........
Acrylic
Ddlling . . ; _ . .......
12-98
PAGE
3
3
3
3
3
3
4
4
4
4
¢
56-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
56-00-00
M20J
- GENERAL
56-21-01
The windshieldfor the M20J is .187 inch thick acrylic
heat formed to contour.The pilotsside windowis also
.187 inch thick acrylic with a hole cut out to
accommodatethe .312 inch thick storm window. The
storm window is milled to fit the hole and to be flush
withoutsideof pilotswindowsurface when closed.The
other three side windows are .125 inch thick acrylic,
Serial Number 24-0001 thru 24-1213 and 24-1418 and
ON have single pane side windows installed. Serial
Number 24-1214 thru 24-1417 have a double panel
cabindoorwindow.The inner pane is a .060 inchthick
acrylicfittedto clips and bracketson the doorframe.
All the windows are heated in an auto-clave to
approximately300 degrees F. and placed on a plaster
moldto coolwhile maintainingthe correct shape,
The windows are tinted green or gray for visual
comfort,ultra-violetfliteration and coolingeffectfor the
cabin,
The windows are all sealed to the outside skin with
PR1403-G-B2 or equivalent sealant. Retainers and
clips are used on the frame to hold the windows in
place.
56-00-01
SERVICE AND MAINTENANCE MANUAL
- WINDSHIELD - REMOVAL
1.The aluminumretainer (1) at bottom of windshield
(2) must be removed by drillingout the rivets attaching
ittothecowldeck(3), (referenceFigure56-1).
A puttyknife or thinaluminumstripwillbe necessaryto
work underneaththe top skin (4) and the side post skin
(5) to break the sealant bond betweenthe acrylicand
the skins.
CAUTION
Exercise care during this operation to avoid
scratching the acrylic. Considerable effort may
be required to break the bond.
2. Carefullypullthe windshieldaway from its location
startingat the lower portionand work it loose as the
sealantbondis brokenaroundthe edge of acrylic.
When windshieldis removed, all residualsealant must
be removed prior to installation of the replacement
windshield. Careful scraping with putty.knife and the
application of M,E.K. will assist in remm,qng the excess
sealant.
66-21-02
- WINDSHIELD - INSTALLATION
When old sealant is removed brush M.E.K. or
equivalentcleaningsolventin the cavity(8) where new
windshieldwill be located. Wipe solventbefore it dries
and redistdbutescontaminates.(Fi£1ure56-1).
- CLEANING ACRYLIC
A commercial cleaning solution manufactured for
acrylic may be used to clean routine grit and grime
7
commercial cleaner used.
If no commercial cleaner is available these procedures
should be followed:
1. Flush windows with water prior to wiping with
clean, soft cloth soaked in kerosene.
CAUTION
from the windows.
the when
instructions
on the
Never wipeFollow
windows
dry.
_
8
2. Flushwithwater after cleaningwith kerosene.
J
CAUT,ON
Never use gasoline, benezene, carbon
tetrachloride, acetone, lacquer thinner, deicer
fluid, house hold cleaning fluid or any other
questionable fluid to clean acrylic windows.
These solvents will soften or craze the surface.
_1
f
5
Minor scratches or abrasions may be polished
out by using acrylic resuffacing kits, ie.,
Micro-Mesh, available from aviation accessory
suppliers.
56-20-00
The
- WINDSHIELD AND CABIN
WINDOWS
removal and
NOTE
installation
of windshield and
__
windows are accomplished in the following paragraphs.
66-21-00
6 --1
WINDSHIELD INSTALLATION - FIGURE 56-1
- WINDSHIELD
12-g8
56-00-00
3
SERVICE AND MAINTENANCE MANUAL
M2OJ
MOONEY AIRCRAFT CORPORATION
NOTE
Exercise care with application of these
solvents. Damage may result if drops of
solvents come in contact with either the
exterior paint, interior trim or plexiglass.
-
1. Apply sealant, PR1403-G-B2 or PRC1321-B-2,
into the cavity (8) until approximately half filled. Apply
The new windshield being forced into the cavity
between the outer skin (4) and the interior retainer (7)
will extrude excess sealant. After the windshield is in
place wipe the excess sealant off with a damp clean
cloth.
Priorto rivetingthe aluminumretainer (1) into position
coatretainerwith a uniformthicknessof either sealant.
a bead of sealaot along the recessedjoggle (6) of the
into place. Use 113212-5-2 cherry rivets to realach
the retainer (1) to cowl deck (3), (reference Figure
,
_'
__
- CABIN WINDOWS
56-22-01
- CABIN WINDOWS - REMOVAL
=
•
'
,
-2
WINDOW INSTALLATION - FIGURE 56-2
The window will be bonded to the outside skin with
sealant. Considerable effort may be requiredto break
the bond betweenthe acrylic and the outer skin. Care
should be exercisedto keep windowfrom twisting and
possiblycracking,
1. Remove the window and clean all remaining
sealant from the skin. Use M.E.K. and a scraper to
removethe sealant.
Aircralt SIN 24-1214 thru 24-1417 have an inner (5)
and outer window (1) installation on the cabin door
window. Removat is basicaly the same procedure as
single window installations,
-CABIN WINDOWS- INSTALLATION
1. Removeall old sealantand clean skinareawith M.E.K.
Place window (1) into positionto assure proper It. Trim
if necessa_/; refer to Figure 56-2.
2. Apply a uniform thickness of PR1403-GB2 or
PRC1321-B sealant to' the skin and window area
where window (1) will be located. Sufficient sealant
should be used so that excess sealant is extruded from
all edges of windows, both inside and outside,
(approximately 5 tubes (3.5 oz.) for 4 side windows).
56-22-00
4
,f
'
_k,
1. Remove interior trim from the window (1) to be
replaced. Remove the retainers (2) or dips (3) which
holdthe window in positionfrom the inside, (reference
Figure56-2).
NOTE
Some retainers are held in place with screws (4)
and some with rivets. Drill out rivets carefully.
56-22-02
"
'
3. Repaint retainer and rivetsto match aircraft.
56-22.00
__
'
After
56-1).the sealant cures the excess may be removed
with a sharp razor knife.
2. Checkfor water leaks.
'
3. Force window (1) into place with retainers (2) or
clips (3) and securewith Avex 1601-410 blindrivetsor
existingscrews and hardware (4). The sealant will be
forced out and seal the window to the outside skin.
Carefullywipe excess sealant off acrylic before it sets
up.After sealant cures the excess can be cut off with a
sharp razorknife, (reference Figure 56-2).
4. Checkreplacedwindowfor leaks.
5. Reinstal interiortrim panels.
56-23-00
-STORM WINDOW
The storm window (6) is mounted with two aluminum
hinges (7), attaching hardware (8) and held closed by a
latch (9). A gasket (10) is bonded to the storm window
for seeing purposes when closed, (reference Figure
56-2).
56-50-00
- ACRYLIC DRILLING
Drill bits for acrylic should be ground per (Figure 56-3).
A slow tuming ddll bit with light pressures is desirable.
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
0
I
i" NEGATIVE
(,03 FLAT WIDTH)
5 ° CLEARANCE
--STOVE
BURNER TYPE BIT
(NO FLUTE RELIEF)
JOBBER FLUTE LENGTH
& JOBBER LENGTH OVERALL
DRILL DIAMETER TOLERANCE =
!
TOTAL
+,0000
-,0000
INDICATED RUNr]UT = ,0002
ACRYLIC PLASTIC DRILL BIT - FIGURE 56-3
(
12-98
56-50-00
5
SERVICE AND MAINTENANCE MANUAL
M20J
BLANK
56-50-00
6
12-98
MOONEY AIRCRAFT CORPORATION
MOONEY AIRCRAFT CORPORATION
M20J
CHAPTER 57
WINGS
SERVICE AND MAINTENANCE MANUAL
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 57
WINGS
LIST CF EFFECTI_E PAGES
CHAPTER
SECTION
SUBJECT ...........
PAGE
57-EffectMty .........
57-00-00 ............
57-20-02 ............
57-20-02 ............
57-20-02 ............
57-30-00 ............
57-40-00 ............
57-50-20 ............
57-50-21
..........
..........
DATE
1/2BLANK ..........
3 ...........
4 ...........
5 ...........
6 ...........
7 ...........
8 ...........
9 ...........
10 ...........
12-98
12-98
12-98
12-98
12-98
12-98
12-98
12-98
12-98
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
57-00-00 ........
57-00-01
..........
57-00-02
..........
57-10-00 .........
57-20-00 ........
57-20-01
..........
57-20-02
..........
57-30-00 ........
57-40-00 .........
57-50-00 .........
57-50-1g
..........
57-50-11 ............
57-50-20
..........
57-50-21 ............
SUBJECT
General
........
..............
Wing Removal and INstallation......
Stall Strip Installation ........
Main Frame ............
Auxiliary Structures ..........
Jack Points ...........
Wing Tips ...........
Plafes - Skin ............
Attach F_ings
...........
Flight Surfaces ...........
Flaps
............
Flap Removal and Installation .....
Ailerons ............
Aileron Removal and Installation ....
12-98
PAGE
3
3
3
3
3
3
3
7
8
8
8
8
9
9
57-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
(
M20J
SERVICE AND MAINTENANCE MANUAL
57-00-00
- GENERAL
The all metal wing is a one piece assemblyattachedto
the fuselage at structural hard points with structural
hardware.
(SeeisSection
53-40-01).
span
spar assembly
connected
to the The
stubfull
spar
andmain
rear
spar assembly by dbs, doublers and skins. The main
landing gear forward attach assembly is an integral
part of the main spar and the rear fitting is boltedto the
stub
spar and
assembly.
The spar
are 7075-T6
aluminum
the webs,
ribs caps
and doublers
are
2. Wing installation:Installationof the wing assembly
is direct reversalof removal.
57.00-02
-STALL STRIP INSTALLATION
1. Position stall strip on wing leading edge so that
during stall recovery normal use of controls would
prevent:
A. More than 15 degree roll.
B. Morethan 15 degree yaw.
2024-T3, T4 or T42 aluminum. Repair of these
componentsis covered in Section51-13-00.
Moldedwing tips (SIN 24-1038 and ON) are fabricated
from compositesand house the navigation and strobe
lights,
The fuel is contained in wet wing type fuel cells
betweenthe main spar and bafflesforward ofthe spar.
The tanks are sealed duringmanufacturingwithcurrent
state ofthe art technology sealant. (See Section 28 for
fuel system details).
C. More than 30 degree pitchbelow flight level.
2. Place stall strips on leading edge at stations
shown on Figure 57-2, attach securely withduct tape
for test flights.Re-positionstall stdps, up ordown, until
aircratt flies to criteria in paragraph 57-00-02, 1, A, B
and C. Secure stall strip per installationinstructionsin
(Figure 57-2).
57-00-01
-WING REMOVAL AND
INSTALLATION
The major subassembliesof the wing may be removed
individually,or the wing may be removed as a unit. To
remove a wing, a fuselage supporting cradle is
needed,
1. Wing removal:
A. Remove wing-root faidngs and bottomfuselage
access panels,
B. Drain allfuel from tanks,
C. Drain brake lines and reservoir. Disconnect
hydrauliclinesat wing mainspar.
D. Remove front and rear seats. Remove the two
inspectionplates under rear seat area. '
E. Jack aircratt.
F. AttachA-frame hoistto propeller,or supportwith
a propellerjack.
G. Disconnector removethe following:
(1) Two landinggear assistsprings.
(2) Aileron controltubes at inboard bellcranks.
(3) Trim controltube at station59.3 and 94.5.
(4) Main gear retractiontubes,
(5) Rudder controltubes.
(6) Elevatorcontroltube.
(7) Elevatorand rudder push-pulltubes,
(8) Floorboardsat rear attach points.
(9) Bellyskin stringersplice angles.
57-10.00
- MAIN FRAME
The integral fuel cells, shaded area (1) start at wing
station 24.5 and continueto the rib at station74.0 on
both wings.(Reference Figure 57-3). Sealer is applied
to alljointson ribs,spar and baffle plates. (See section
28 for resealing procedures).
The wing is manufactured in three sections;the center
section (2), the left outboard section (3) and an
opposite right outboard section (not shown) (Figure
57-3). These three sections are then assembled into
one full span wing assemblyasthe skinsare installed.
A spares, outboard wing tip assembly is available
which includes completed section from wing station
118.25 and outboard. The assembly includes the
stringers (4) required to complete the spliceto the old
centersection.
57-20.00
- AUXILIARY STRUCTURES
57-20.01
- JACK POINTS
The jack points are located on the under side of the
wing. The threaded wing tie down eyebolt fittingsare
designed to accept the non threaded jack points.
These are located outboard of each main gear. See
Section7-10-00 for completejacking procedures.
57-20-02
- FIBERGLASS WING TIPS
(SIN 24-1038 and on)
The M20J wing tips are non-structural fiberglass
components. They are riveted to the upper and lower
wing skinsduringfinalassembly of the wingstructure.
1. W_ngtip removal.
A. Remove the navigationstrobe light lens (1) by
removing4 screwsand washers (2) that retainthe lens
to wing tip (3) (24-0001 tbru 24-2999). SIN 24-3000
thru 24-TBA - Disconnectaft positionlightconnections.
Refer to Figure 57-4).
(10) Airspeed indicator line, pitot lines, and pitot
heater wires (if installed).
(11) Hardware shown in (Figure 57-1).
CAUTION
Have a suitable cradle ready to carry the
fuselage before removing all mating hardware.
12-98
57-00-00
3
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
WING ATTACHING HARDWARE - FIGURE 57-1
57-20-02
4
12-98
MOONEY AIRCRAFT CORPORATION
LEFT WING -
SHOWN
RIGHT WING -
OPP.
M20J
^/
R,_ KIN
LL
!_!!!-!-_7!27
SERVICE AND MAINTENANCE MANUAL
,
SKIN
/-_
C BORE STALL
.06/.10"
DEEP
AN515--RR1¢)
"_.
ST
-scREw-UstE
LOCKTITE
D
DRILL
/USE
.1_]g/'.193
A6-75
_PEcv_
A/_'/_
TYPICAL INSTL.
DIA
RIVNUT
FWD
"==
STALL
STRIP ALTERNATE INSTL
STALL STRIP INSTALLATION
W_
(
"",,L_/
\
./_
.//
FIGURE 57-2
103,5
W_ 118,25
wS 59,_5
"
I
SNJ57-3
WING STRUCTURE - FIGURE 57-3
12-98
57-20-02
5
SERVICE AND MAINTENANCE MANUAL
24-1038
M20J
MOONEY AIRCRAFT CORPORATION
24-3000
THRU 24-TBA
THRU
24-2999
4
7
3
•..
8
•
6
2
1
STROBE LIGHTS (7) AN]] POWER SUPPLY
CONNECTORS (8) WILL VARY,
SNJ57-4
WING TIP ASSEMBLY (24-:1038THRU 24-TBA) ..- FIGURE 57-4
B. Drill out rivets (4) holding tip to upper and lower
wing skins (5). Remove all rivet shanks with a punch.
C. Carefully pull wing tip away from wing db (6)
and skins (5). Disconnect the strobe and navigation
light harnesses at the quick disconnect plug (8) pdor to
completely removing the tip.
NOTE
The strobe or navigation lights can be removed
from wing tip either before or after its removal
from wing.
57-2O-O2
6
2. Wing tip installation.
A. Place the new or repaired wing tip in place.
CAUTION
Be sure aileron and aileron balance weights are
not restricted in movement either direction.
B. Secure wing tip and ddll holes to match wing
skins. Cleco as holes are ddlled into tip. When all holes
are ddlled remove wing tip assembly and deburr.
NOTE
Connect strobe and navigation light connectors
(8) prior to final attachment of the tip.
12-98
MOONEY AIRCRAFT CORPORATION
,
I
M20J
SERVICE AND MAINTENANCE MANUAL
C. Use Avex 1604-0412 blind dyers to attach the
wing tip to the top and bottom skins,
D. Repaintto match the aircraft.
57-30-00
- PLATES - SKIN
They are flush mounted covers and when installed
continue the aerodynamic contour of the wing. SIN
24-1418 and ON have a one piece fiberglassskin that
can be removed to gain access to component located
inthat area.
The wing access and inspection covers shown in
(Figure 57-5) provide maintenance access to
components,plumbingand controlbellcranksenclosed
withinthewing.
NOTE
One piece belly skin panel on 24-1418 & ON
7_--_
L_
L7-,___
_
, _
19-- _= _-- -19
-2
7- -0
8
19--- I]
0-- -19
--_7
9
0---0s--7i2
FIVESEPARATE
BELLY SKINS
ALUMINUM
S/N ;=4-0001 THRU 24-1417
-- 3
7--0
([]00
3--
_
7
0__0__9
i9-
17
8-49---ii
_4
19 ,--
_ H
4-
17
DNE PIECE L
FIBERGLASS J
BELLY SKIN
S/N 24-1418 THRU £4-T3A
5--
6 --
l
TOP
LEFT
WING
19--
--13
16
-5
14
15
BOTTOM
SMJ57-5
0
--9
LEFT WING
O0 =- -6
WING SKINS AND INSPECTION COVERS - FIGURE 57-5
LEGEND FOR FIGURE 57-5.
1. Wing skin - .050 thickness._fueltank)
2. Wing skin - .040 thickness. (fueltank)
3. Wing skin- .040 thickness.
4. Wing skin- .032 thickness,
5. Wing skin - .025 thickness.
6. Wing skin - .025 thickness.
7. Fueltank access,
8. Fueltank filler.
9. Controltube guide blocks.
10. Wing - fuselage attach points.
11. OAT probe, rightwing only.
12. Controltube guide blocksand flighttimer.
13. Pitot post- left wing only.
14. Strobe lightpower supply.
15. Aileronbellcrankand controlrods.
18. Auto pilotservos.
17. Gyro compassflux valve (one of these, depending
on installedequipment),(leftwing only).
18. Main landinggear retractionspring.
19. Elevator and rudder controls - rod end bearings,
bellcranks.
20. RetractionBungee Spring (205 only)
21. Speed Brakes (if equipped)
SIN 24-1418 & ON have a one piece fiberglass belly
skin;removefor access.
12-98
57-30-00
7
SERVICE AND MAINTENANCE MANUAL
M20J
NOTE
Access covers on bottom of wing that require
removal for inspection intervals are secured
with screws. Any access covers that are riveted
in place are required for manufacturing only
and NOTfor routine inspections,
MOONEY AIRCRAFT CORPORATION
The flap actuator jack shaft is connected by a push-pull
rod end bearing to the actuator bracket (1) (Figure
57-6) locatedjust inboard of the inboardhinge (2). All
four hinges(2) and (3) are faired (4) to reducedrag.
The intemal structureof the flaps consistsof a leading
edge extrusion(5) trailing edge stiffener (6), ribs (7)
and top and bottomskins (8). These componentsare
riveted together into a leit hand and right hand
assembly.
57-50-11
- FLAP REMOVAL AND
INSTALLATION
Refer to Section27-50-00 for removal and installation
procedures.
57-40-00
-ATTACH FITTINGS
Refer to Section 57-00-01 for wing fuselage
attachment.
57-50-00
- FLIGHT SURFACES
Refer to Section 27-90-00 for flight control surfaces
balancingprocedures
57-50-10
- FLAPS
Refer to Section 27-50-00 for maintenance and rigging
procedures.
4
7
4
8
6
1
7
2
4
3
5
3
3
FLAP ASSEMBLY - FIGURE 57-6
57-40-00
8
12'98
3
4
MOONEY AIRCRAFT CORPORATION
M20J
57-50-20
-AILERONS
Referto Section27-10-00 for maintenanceand rigging
procedures.
The ailerons are of all metal construction.The main
spar (1), (Figure 57-7), is attachedto the rear spar (2)
through dbs (3). These components are riveted
togetherand a top and bottom skin(4) and (5) dveted
to this sub-assembly.To completethe controlsurface,
hinges(6) and balance weights (7) are installed.The
SERVICE AND MAINTENANCE MANUAL
weights (7) are bolted(10) through an outboard rib (8)
and bracket(9) on each aileronassembly.
57-50-21
- AILERON REMOVAL AND
INSTALLATION
Refer to Section 27-10-00 for removal and installation
procedures.
i6
BEI'AIL
I
_
_'v'/]]ETAIL
5
2
A
I0
B
]]ETAIL C
/_'_o_
SMX57-7
AILERON ASSEMBLY - FIGURE 57-7
12-98
57-50-20
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SERVICE AND MAINTENANCE MANUAL
M20J
BLANK
57-50-21
10
12-98
MOONEY AIRCRAFT CORPORATION
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 60
STANDARD PRACTICES - PROPELLER
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 60
STANDARD PRACTICES - PROPELLER
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
PAGE
60-EIT/Contents.........
60-00-00 ............
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DATE
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TABLE OF CONTENTS
CHAPTER
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SUBJECT
...........
60-00-00 ........
SUBJECT
Gene_l
........
PAGE
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3
1_98
60-EF_CONTENTS
I_BLANK
MOONEY AIRCRAFT CORPORATION
60-00-00
+
i
M20J
- GENERAL
SERVICE AND MAINTENANCE MANUAL
CAUTION
The standard M20J aircraft has a McCauley Propeller,
controlledby a governor for constantRPM settingsat
the pilotsdiscretion,
An option for the M20J is a Hartzell Propeller with
Q-Tip blades.
Each propellerhas its ownmatchingspinnerassembly.
Repairs may be made to metal propellers in
accordance withAC 43.13-1(*), and in conjunctionwith
the definitionsof FAR 43.
Refer to Textron-Lycoming maintenance
publications for engine inspection procedures
after a propeller strike.
* Currentissueof AC 43.13
12-98
60-00-00
3
MOONEY AIRCRAFT CORPORATION
M20J
CHAPTER 61
PROPELLERS
SERVICE AND MAINTENANCE MANUAL
SERVICE AND MAINTENANCE
MANUAL
M20J
MOONEY AIRCRAFT
CORPORATION
CHAPTER 61
PROPELLERS
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
61-Effectivity
.........
61-OO-00 ............
61-90-20 ............
61-20-90 ............
61-20-90 ............
61-40-00 ............
61-40-00 ............
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TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
61-00-00
61-00-10
61-00-20
61-10-00
61-10-10
61-20-00
61-20-10
61-20-20
61-20-30
61-20-90
61-40-00
...........
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.........
.........
..........
.........
..........
..........
..........
..........
.........
SUBJECT .........
General
..............
Spinner Dome and Propeller Removal .....
Propeller Installation ..........
Propeller Assembly ..........
Minor Propeller Blade Repair
......
Propeller Controlling ..........
Propeller Governor Installation ......
Propeller Governor Rigging .......
Propeller Governor Adjustment ......
Propeller Governor Troubleshooting
....
Propeller Balancing ..........
12-98
DATE
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7
61-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
61-00-00
M20J
SERVICE AND MAINTENANCE MANUAL
" GENERAL
NOTE
The propelleris a constantspeed type which operates
by oil pressure opposing natural centrifugaltwisting
moment of rotating blades and rome of a spring (in
McCauley propellers) to obtain correct pitch for the
selected engine load. Engine lubricatingoil is supplied
to a powerpistonin propellerhubthroughthe propeller
shall The amountand pressureof oil supplied(0-300
PSI) is controlled by an engine driven governor.
Govmor oil pressure acting on a piston (and spring)
increase propeller blade pitch, thus decreasingengine
RPM. As governor oil pressure is reduced, centrifugal
twistingmoments and spring force on propellerblades
decrease propellerblade pitchand increaseRPM.
Propeller overhaulshall coincide with engine overhaul,
but interval between overhauls shall not exceed 1500
hours (McCauley) or 2000 hours (Hartzell). Refer to
propeller manufacturers' overhaul manual for complete
maintenance action and time limits.
Approved propeller shops only are authorized
for overhaul or major repairs to these
propellers. Referto Federal Aviation
Regulations, Part 43, (FAR 43) and Federal
Aviation Agency Advisory Circular No. 43.13 (*)
for the definition of major or minor repairs or
alternations and who may accomplish them.
(See Textron LycomingService and
Maintenance Instructions).
61-00-10
- SPINNER DOME AND
PROPELLER REMOVAL
1. Spinnerdome removal(if necessary).(See Figure
61-1)
NOTE
It is not necessary to remove spinner when
removing propeller assembly.
A. Remove screws (1) from spinner (2).
B. Remove doubler plates (3).
C. Remove spinner dome (2).
i
I"--
_X
\
7
3
_
l
SPINNER DOME & PROPELLER REMOVAL - FIGURE 61-1
12-98
61-00-00
3
SERVICE AND MAINTENANCE MANUAL
M20J
D. Remove safety wire and loosen bolts (4)
attachingpropellerto engine crankshal_,about 114inch
and pull propellerforward.
NOTE
Bolts (4) will have to be backed out evenly so
that propeller may be pulled forward
(approximately 1/4 inch at a time) until all bolts
are disengaged from the engine crankshaft
flange. As the propeller is separated from the
engine crankshaft, oil will drain from the
propeller and engine crankshaft cavities,
8. INSTALL SAFETY WIRE THROUGH ROLL PINS
SAFETYING BOLTS IN PAIRS.
9. Adjust alternator drive belt tension as outlined in
Section24-31-01.
10. Install spinner dome (5) making sure fiber
washersare installedunder all screws.
E. Pull propeller from engine crankshaft.
F. if necessaryto remove the aft spinnerbulkhead,
remove bolts, washers and nuts (5) attaching
bulkheads to the starter ring gear support.
NOTE
After removal of the propeller, the starter ring
gear support assembly may be removed from
the engine crankshaft to allow easier access of
the aft spinner bulkhead attaching bolts,
Loosen alternator adjusting arm and disengage
alternator drive pulley belt from pulley on aft
face of starter ring gear support assembly.
6t-00-20
- PROPELLER INSTALLATION
1. If aft spinner bulkheadwas removed,re-thstallon
ring gear supped, using bolts, nuts and washers in the
reverse order of removal.
2. If starter ring gear support and aE spinner
bulkhead were removed, clean mating surfaces of
suppo[tassembly and engine crankshaftflange.
3. Place alternator drive belt in the pulley groove of
the starter ring gear support. Fit starter ring gear over
propeller flange bushings on cranksha_,
NOTE
Make sure the bushing hole in the ring gear
support, that bears the identification "O", is
assembled at the "O" identified crankshaft
flange bushing. This bushing is marked "O" by
an etching on the crankshaft flange next to the
bushing. The starter ring gear must be located
correctly to assure proper alignment of the
timing marks on the ring gear.
NOTE
The teflon tape (9) on hub (6) should be
checked for smoothness of tape layers and that
inner bulkhead (7) fits snug as spinner dome is
being installed.
11. Conductoperational and leak check on propeller
installationpriorto flight.
6t-10.O9
, PROPELLER ASSEMBLY
No externallubricationis required on M2OJpropellers.
Preflight inspection should be accomplishedprior to
each flightto determine: if bladeshave been damaged,
if any abnormal Ioosness is evident between hub and
bladesor if there is any evidence ofoil leakage.
6t-t0-10
-MINOR PROPELLER BLADE REPAIR
1. Minor nicks, dents and gouges may be dressed
out by approvedpersonnel;Blend any nicksor gouges
intothe leading edge with smooth curvesor generous
radiias shownin (Figure 61-2). Repaint area to reduce
corrosive action.
61-20.00
- PROPELLER CONTROLLING
61-20-10
-GOVERNOR INSTALLATION
1. Clean mountingpad and bottom of governor.
2. Coat new gasket w/ DOW Coming 7 compound
release agent or equivalent before installation.
3. Installnewgasketon mountingstuds. Insuregaskethas
raisedsurfaceof the gasketscreentowardthe governor.
4. Positiongovernoron mountingstuds, aligningthe
governorspttnes andthe splinesof the accessorydrive.
5. Installall mountinghardware. Torgue nuts.
6. Connectgovernor controlto governorand rig.
NOTE
All dggingto match governorarm Ioction.Do not
adjustgovmor high RPMstopto match the dgging.
CAUTION
Remove all rags or plugs placed in crankshaft
or hub during propeller removal.
61-20-20
4. Clean propeller hub cavity and mating surfaces of
propellerhub and ring gear support.
5. Lightly lubdoate a new O-ring (8) (Figure 61-1) and
the crenkshal_ pilot with clean engine oil and install
O-ring in the propeller hub.
6. Align propeller mounting bolts (4) with proper
holes in engine crankshaft flange and slide propeller
carefully over crankshaft pilot until bolts can be started
in crankshaft flange bushing,
7. "l-_Jhtenbotts evenly and work propeller aft on
crankshaft flange. Tcjhtsn bolts to 55-65 FT-LBS on
McCauley propellers and 60-70 FT-LBS on Hartzell
propellers.
61-00-20
4
MOONEY AIRCRAFT CORPORATION
- PROPELLER GOVERNOR CONTROL
RIGGING
1. Disconnect propeller govemor control rod.
A. Remove cotter pin, nut, bolt and washers from
rod end at propeller governor control arm.
B. Remove bracket installed with propeller
governor mounting bolts.
C. Disconnect control rcd fromgovemorcontrolarm.
2. Adjust control arm spring to minimum tension
which will return control arm to maximum RPM.
3. Push propeller control in cockpit futt forward. Putt
control back approximately 1/8 inch and lock in this
position,
12-98
_
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
MINOR PROPELLER BLADE REPAIR - FIGURE 61-2
4. Place governor control arm against high RPM stop
screw (325 degrees from governor centerline).
5. Adjust propeller control rod end to coincidewith
thegovernor arm position.
6. Attach control rod end to governor arm and
secure.
7. Operate the propellercontrolfrom cockpitto verify
fulltravel of control arm in both directions,high RPM to
minimumRPM stop.
NOTE
When propeller control rigging is complete,
check controls in cockpit to be sure there is 118
inch cushion between control knob and
adjustment nut on instrument panel. The
control should not bottom out when pushed full
forward,
CAUTION
Recheck safety wire, security and thread
engagement on all engine controls after
adjustment rigging or assembly.
NOTEcan be adjusted by
Vernier controls friction
loosening the lock nut on back side of panel
and either tighten the nut on front of panel to
increase friction or loosen the nut to decrease
friction. Retighten the lock nut on back side to
secure cable to the panel.
NOTE
Takeoff RPM should not exceed 2700 RPM.
(Static RPM may be 50 RPM less than 2700).
61-20-30
- PROPELLER GOVERNOR
ADJUSTMENT
!. Fly aircraft an drecord max. RPM at T/O or cruise
flight atfull power.
NOTE
No adjustment can be done before a test flight
to obtain max. governor RPM.
2. Remove upper engie cowlfor accessto governor.
3. LoosenhighRPM screw jam nut.
4. Turn screw in (CW) or out (CCW) to match RPM
recordedduring governortest flight. One (1) fullturn of
the screw equalsapproximately25 RPM.
5. Tighten jam nut an make propeller control linkage
adjustmentsas necessaryto maintain full travel.
6. Re-dg discennectaed controls and reinstall
cowling.
7. Perform propeller and governor operationaltests.
Fly aircraft and repeat governor test flight and record
max. RPM in flight at max power. Repeat this process
untilthe proper max. RPM setting is achieved.
NOTE
When installing a governor, insure the oil
system is purged of all air by cycling the
propeller seveal times before flight.
12-98
61-20-30
5
SERVICE AND MAINTENANCE MANUAL
61-20-90
M20J
MOONEY AIRCRAFT CORPORATION
- PROPELLER GOVERNOR TROUBLE SHOOTING
TROUBLE
PROBABLE CAUSE
REMEDY
Leakage: Between controlshaf_
and head.
-Damaged O-Ring.
Replace with new O-Ring.
Betweenhead and body.
-Damaged head and body
gasket.
Replace gasket.
Betweenmliefvalveplugand body.
-Damaged relief valve plug
gasket.
Replace gasket.
Between body and base.
-Damaged body and base
gasket.
Replace gasket.
Between govemor base and
engine mounting pad.
-Damaged governor mounting
gasket.
Replace gasket.
-Loose governor attaching nuts.
Retighten nuts.
-Warped engine mounting pad.
Consult engine manual.
-Wrong high-RPM governer
setting,
Reset governor external high RPM
adjustment screw.
-Incorrect system dgging.
-Low engine power.
Adjust control system.
Consult engine manual.
-Erroneous reading tachometer.
Calibrate or replace instrument.
-Sticky pilot valve.
Remove head and clean pilot valve with
crocus cloth. Maintain sharp pilot valve
land corners. Check for straightness of
pilot valve; if bent, replace valve.
-Sludge in governor pilot
valve or relief valve.
Disassemble and clean.
-Burrs on pilot valve lands.
Disassemble and clean with crocus
cloth.
-Backlash in governor control
system.
Redg or adjust control system.
-Sticky relief valve.
Inspect for burrs, and clean.
-Erroneous reading
tachometer.
Calibrate or replace instrument.
_Excessive oil leakage in propeller shaft transfer bearing.
Refer to engine manual.
Inability to attain takeoff RPM
dudngflight,
RPM fluctuates. The RPM can
fluctuate +/-30 RPM.
High propeller friction.
Refer to propeller overhaul manual.
Governor function upset by
malfunctioning engine.
Repair engine for smooth operation.
-Air trapped in propeller.
61-20-90
6
-Sticky oilot valve.
Cycle Power Lever from MIN to MAX
several times to purge air.
Remove head and pilot valve. Clean
away sludge and varnish. Check
speeder spring ends for proper settings.
-Bent pilot valve.
Remove head and replace pilot valve.
-Excessive intemal leakage
in governor,
Check rigging and make necessary part
replacements,
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
TROUBLE (CONT.)
PROBABLE CAUSE
REMEDY
Excessive over-speeding.
-Wrong governor setting.
Reset governor. Use test rig if
available.
-Damaged or wrong gasket
between governor base and
engine mounting pad.
Install correct new gasket.
-Sticky governor pilot or relief
valve,
-Erroneous reading tachometer.
-High-RPM screw adjusted
too far IN, causingrestricted
arm travel,
Disassemble, clean, and check for
burrs.Replace bent pilot valves.
Calibrate or replace instrument.
Remove control arm and rotate one
serratioaclockwise. Back out
high-RPM screwto required maximum
RPM.(One turn equals 27 RPM.)
-Excessivepropeller
bladeseatfriction,
Examine propellerhub for cause of
friction.
Inability to attain positive high
RPM:
Surging.
61-40-00
- PROPELLER BALANCING
Balancing of the propeller by means of an approved
system is recommended to provide smoother
operation. The vendor system used should be an
approved system and the procedures followed very
carefully.The propeller may have been balanced with
another vendor system previoulsy and may require
removalof
balancing. old balanceweights and/or other means of
Log book entdesmust be made when the propeller is
dynamicallyor staticallybalanced
CAUTION
Place weights, washers, or whatever balance
weights are specified atthe locations specified
bythe balancing procedures. Be careful placing
weights on spinner dome.
12-98
61-40-00
7
SERVICE AND MAINTENANCE MANUAL
M20J
BLANK
61-40-00
8
12-98
MOONEY AIRCRAFT CORPORATION
MOONEY AIRCRAFT
CORPORATION
M20J
CHAPTER 71
POWERPLANT
SERVICE AND MAINTENANCE
MANUAL
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 71
POWERPLANT
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
71-Effectivity .........
71-Contents ..........
71-0O-0O............
71-00-01 ............
71-00-40 ............
71-00-61 ............
71-00-92 ............
71-10-00
...........
71-11-02
...........
7%13-03
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1/2BLANK
MOONEY AIRCRAFT CORPORATION
M2OJ
SERVICE AND MAINTENANCE MANUAL
CHAPTER 71
POWERPLANT
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
71-00-00 ........
71-00-01 .........
71-00-10 .........
71-00-20 .........
71-00-30 .........
71-00-40 .........
71-00-60 .........
71-00-61
..........
71-00-70 .........
71-00-80 .........
71-00-90 .........
71-00-91
..........
71-00-92
..........
71-10-00 .........
71-10-01
..........
71-11-00
..........
71-11-01 ............
71-11-02 ............
71-12-00
..........
71-12-01 ............
71-12-02 ............
71-13-00
..........
71-13-01 ............
..............
71-13-02 ............
...........
71-13-03 ............
..............
71-13-04 ............
..............
71-30-00 .........
71-60-00 .........
71-60-01
..........
71-61-00
..........
SUBJECT
........
General ..............
Engine Data ............
Engine Removal ...........
Engine Inspection & Repair ........
Engine Installation ..........
Engine Ground Checkout
........
Fuel Injection Maintenance ........
Fuel Injector Idle & Mixture Adjustment
Starter System Maintenance ........
Engine Mixture Control Rigging .......
Trouble Shooting ...........
Starter Trouble Shooting .......
Engine Trouble 8hooting .......
Engine Cowling ...........
Cleaning,Inspection and Repair .....
Cowling Removal .........
Top Cowling .........
Bottom Cowling ........
Cowling Installation ........
Bottom Cowling ........
Top Cowling .........
Engine Cowl Flap(s) ........
Engine Cowl Flap Rigging .....
(24-0001 thru 24-2999)
Engine Cowl Flap Rigging .....
. . . .
(24-3000thru24-TBA)
Cowl Flap Indicator Adjustment ....
(24-3000thru 24-3410)
Cowl Flap Indicator Adjustment ....
(24-3411thru 24-TBA)
Fireseals ............
Air Intakes ............
Engine Induction System Maintenance
Air Intake Duct Replacement ......
12-98
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71-CONTENTS
3/4BLANK
SERVICE AND MAINTENANCE MANUAL
M2OJ
MOONEY AIRCRAFT CORPORATION
71-00-00
- GENERAL
The M20J SIN 24-0001 and ON has either a TEXTRON-Lycoming IO-360-AIB6D, IO-360-A3B6D or IO-360-A3B6
series engineinstalled.These arefour cylinder,200 H.P., fuel injectedengines.
71-00-01
- ENGINE DATA
AIRCRAFT MODEL .............
ENGINE MANUFACTURER
.............
ENGINE MODEL ...................
BHP (rated MAX) ........................
RPM ...........................
NO. CYLINDERS .........................
DISPLACEMENT (Cu. In.) .....................
BORE (Inches) ........................
STROKE (Inches) .......................
COMPRESSION RATIO ......................
MAGNETOS
Manufacturer ...................
Model . . ......................
...........................
ADVANCE BTC**
.....................
VALVE ROCKER CLEARANCE
(HydraulicTappets Collapsed)
............................
RIGHT MAG FIRES
Top Plugs.........................
BottomPlugs ....................
LEFT MAG FIRES
Top Plugs.........................
BottomPlugs
........................
R bank
FIRING ORDER
........................
FUEL INJECTOR
Manufacturer .......................
Model ........................
OIL CAPACITY (QTS)
.................
OIL VISCOSITY
RECOMMENDATIONS
NOTE:Multi-viscosity
oil is recommended
for all operations.
ALTERNATOR
...............
...............
"..........
Bendix- Scintilla****
D4LN-2021
D4LN-3021
25 Degrees**
028 to 080
R bank
L bank
L bank
1-3-2-4
" ....
AVERAGE AMBIENT
.
AIR TEMPERATURE.
Above60 Deg. F
30 Deg to 90 Deg. F
0 Deg. to 70 Deg. F
Below 10 De_l. F
.
SINGLE VISCOSITY
GRADES *.
.
..............
.
BENDIX
RSA-5ADI
8
MULTI-VISCOSITY
GRADES *
SAE 50
SAE 40
SAE 30,SAE 40
SAE 20, SAE 30
SAE 40 or 50
SAE 40
SAE 20W-40
SAE 20W-30
PRESTOLITE
(24-0001 thin 24-2999) 14V, 60 AMP
(24-3000 thru24-TBA) 28V, 70 AMP
STARTER ..............
.................
SPARK PLUG GAP
Fine Wire ................
Massive ................
MAX CYLINDER HEAD TEMP
M20J
TEXTRON LYCOMING
IO-360-A3B6D***/****
200
2700
4
361.0
5.125
4.375
8.7:1
(24-0001 thru 24-2999) 12V
(24-3000 thin 24-TBA) 24V
015 to .018
015 to .022
..........
475 Degrees F
• Refer to latest edition of LycomingService Instruction No. 1014.
•* Refer to latestedition of LycomingInstructionNo. 1325.
•** EngineModelIO-360-AIB6D (Effective24-0377 and earlierM20J) con be convertedto an IO-360-A3B6D
enginewithSB M20-206 compliance.
•*** S/N 24-3374 thru 24-TBA have IO-360-A3B6 engineconfigurationinstalled.This configurationutilizestwo
Slick Magnetos.
12-98
71-00-00
5
MOONEY AIRCRAFT CORPORATION
71-00-0t
M20J
SERVICE AND MAINTENANCE MANUAL
- ENGINE DATA (CON'T.)
START & WARMUP OIL PRESSURE
Maximum
...............
Minimum ................
NORMAL OIL PRESSURE
Maximum ................
Minimum ................
71-00-19
100 PSi
25 PSI
90 PSi
60 PSi
- ENGINE REMOVAL
-- Remove engine mounting bolts. --
To assistin installation,identifyand tag each part as it
is removed.Plug or cap all lines, hoses, and f_ings as
the_/are disconnected.
1. Make surethat all cockpitswitches are OFF.
2. Tum fuel selector valve OFF.
NOTE
IDENTIFY AND MARK SEQUENCE OF
WASHERS ON RUBBER BISQUITS AS WELL
AS THE ORIENTATION
OF THE
BISQUITS FOR
EACH MOUNTING
POSITION.
17. Slowlyraise engine. Be surethat all lines, hoses,
and wires are flee.
3. Rerno_ enginecowl'_gandba_es (SeeSection71-10).
4. Disconnect battery ground cable.
71-00-20
- ENGINE INSPECTION & REPAIR
For specific engine inspection and overhaul
instructions,consult engine manufacturer's overhaul
manual and service instructions. Refer to Bendix
Maintenanceproceduresfor magnetos.
5. Remove propeller(referto section61-00-10).
6. Drain engine oilsump.
7. Disconnectthefollowing:
A. Vacuum line.
B. Cabinheat ducts (at engine).
C. Fuel vent lines (at firewall).
D. Tachometerddve shatl (if installed).
E. Oil temperature bulb.
F. Oil pressure line.
G. Manifold pressure line.
H. Cylinder headtemperature bulb.
I. Breather hose.
71-00-30
- ENGINE INSTALLATION
Reverse the engine removal procedurefor installation.
1. Engineinstallationtorquevalues are as follows:
A. Spark plugs-360 to 420 _nchLbs.
B. Hose clamps-10 to 29 Inch Lbs.
C. Engine shock mount bolts-450 to 500 Inch Lbs.
D. 1/4to 70
inch
upper engine mount to fuselage
bolts---50
in-lbs.
E. #10-32 lower engine mount attach block to
fusalage-2Oto 25 Inch Lbs.
NOTE
Make sure the J7763-1 Lord mounts (load
bearing) are positioned aft on upper ring and
forward on lower. (Gold--load bearing,
Silver--non-load bearing).
8. Disconnect the following control linkage:
A. Tbruttle control
B. Propeller govemor control.
C. Mixturecontrol,
D. Alternate Air.
9. Disconnect ignition switch wires from magnetos.
WARNING
Ground magneto breaker points.
10. Disconnect engine ground strap.
11. Disconnectvoltage regulatorwires (opt.).
2. Reinspect to see that:
A. Propeller and spinner are properly torqued.
B. Engine mounting bolts are properly torqued.
NOTE
Positionwasherssame sequenceas when removed.
12. Disconnectalternator and starterwires.
13. Disconnectheater muff and exhaust tail pipe.
14. Disconnectfuel line at enginefuel pump.
15. Shore up fuselage at tail skid usingshodngstand
to preventtail from dropping.
16. Attach hoist to lifting eye at top of crankcase.
S_ightlyli_.engine to relieve weight from engine mounts.
C. Enginecontrols are properlydggedand safeUed.
(Recheckrod-endsfor properthreadgdplength.)
D. Oil drain plugs aretightened and safetied.
E. Oil sump is filled to eight quarts.
71-00-01
6
12-98
SERVICE AND MAINTENANCE MANUAL
M20J
F. Spark plugs are tight and ignition hamese is
propedy installed.
G. Magneto ground wires are properly installed
and secured•
H. Alternator drive belt(s) tight•
I. Oil temperature bulb is tight and safetied.
J. Oil pressure relief valve plug is safefled.
K. Cylinderhead temperature connectionis secure.
L. Tachometer drive is secure (if installed),
M. Starterceble connection is secure.
N. Alternator(s) wiring is secure,
O. Exhaust system is secure.
P. Vacuum lines and connections are secure.
Q. Fuel connections are tight and pressure checked,
R. Manifold pressure lines are tight.
S. Oil pressure lines are tight and pressure checked,
T. Oil pressure transducer is positioned correctly
so no interference with any part of engine installation.
U. Fuel Injectionlines are fight and pressurechecked,
V. Oil filter is installed and secure.
W. Induction manifolds are secure,
X. All lines, hoses, and wires are pmpedyanchored,
Y. Induction air filter; installed and secure,
• Z. Ram Air opening between cowling and air
induction duct is aligned,
AA. Heat shrouds and baffling are installed and
secure,
BB. Engine area is free of loose objects, tools, etc.
CC. Cowling is installed and secure (See Section
71-11).
DD. Cowl flap control rods are connected,
71-00-40
- ENGINE GROUND OPERATION
CHECKOUT
1. Prestarflngprocedure(withaimraltheadedintowind):
A. Turn ignitionswitch OFF.
B. Check magnetoground connections,
C. Check engine oil level.
D. Checkfuel quantity,
E. Operate all controlsthrough full range to check
for binding,
F. Checkbaffles and cowlingfor security,
G. Open cowl flaps; check operation,
H. Drain fuel sumps, fuel selector drain or
gascolator.Check for sediment and water,
I. Place wheel chocks and set parkingbrake,
2. Starting procedure_
A. Set propeller governor control: FULL FWD
(HIGH RPM).
B. Tum fuel valve ON.
MOONEY AIRCRAFT CORPORATION
C. Set mixture control at: IDLE-CUTOFF.
D. Turn boost pump ON.
E. Open throttle 1/4. Push mixture control toward
FULL RICH for 3 to 5 seconds; then return to
IDLE-CUTOFF.
F. Boost pump OFF.
G. Clear propeller area.
H. Engage starter switch. When engine starts,
advance mixture to FULL RICH.
I. Start engine. Check oil pressure. If no oil
pressure is indicated within 30 seconds, shutdown
engine and trouble shoot oil system. Refer to AVCO
LYCOMING maintenance publications for procedures.
J. Set thrOttle for 900 to 1000 RPM for one minute;
then, advance throttle slowly to 1200 RPM for engine
warmup.
3. Ground run and warmup. Always head the aircraft
into the wind during warmup. Always select HIGH RPM
blade-angle setting when ground running the engine.
NEVER idle for extended periods at LOW RPM (LOW
RPM WILL FOUL SPARK PLUGS). Always operate
with the mixture control at FULL RICH, and maintain
RPM in the 1000 to 1200 RPM range during warmup
and ground run.
A. Warm up engine until temperature indications
are normal. Monitor cylinder head and oil temperature
instruments for overtempereture.
B. Check magnetos at 1900-2000 RPM with
propeller at HIGH RPM blade angle. Switch
ignition-starter switch from BOTH to LEFT to check
magneto drop. Switch back to BOTH until RPM returns
to normal. Switch from BOTH to RIGHT and check
magneto drop. Return switch to BOTH. magneto drop
should not exceed 175 RPM on either magneto (drop
should be within 50 RPM of each other). A smooth
drop off past normal is usually a sign of too lean ortoo
rich mixture. If no drop in RPM, check for open or
broken P-leads.
71-00-60
- FUEL INJECTION SYSTEM
MAINTENANCE
For injection system inspection and overhaul
instructions, consult engine manufacturer's overhaul
manualand serviceinstructions.
The fuel injection system consists of the following
major components:
(1) the fuel injector assembly comprised of the servo
regulator, fuel control,and airflow sensing system; (2)
the flow divider; and (3) the four air bleed nozzles.The
fuel injection system operates by measuring airflow
through the throttle body of the servo valve regulator
controland usingthis measurement to operate a servo
valve within the control. This regulated pressure
con-troisthe distributorvalvewhich schedules fuelflow
in proportionto airflow.
12-98
71-00-40
7
MOONEY AIRCRAFT CORPORATION
M20J
71-00-61
- FUEL INJECTOR IDLE SPEED &
MIXTURE ADJUSTMENT
1. For operationin normalor low ambienttemperature
conditions,adjustidleand mixtureasfollows:
A. Start engine and warm up in the usual manner
untiloil and cylinder head temperatures are normal.
B. Check magnetos; if magneto drop is normal,
proceed with idle adjustment,
C. Close throttle to IDLE, approximately 600 RPM.
If RPM changes appreciably alter making idle mixture
adjustment during succeeding steps, readjust idle
speed to desired RPM.
NOTE
Idle mixture must be adjusted with fuel boost
pump on.
D. When idling speed has stabilized, pull mixture
control smoothly and steadily toward idle cutoff, and
observetachometer for an RPM changeduring leaning
process.Care must be exercisedto return the mixture
control to full rich before RPM can drop to where
engine cuts out. An increase of more than 50 RPM
while leaning indicatesan excessivelyrichmixture.An
immediate decrease in RPM (if not preceded by a
momentaryincrease) indicatesidlemixture is too lean.
E. If above check indicatesthat mixtureistoo lean
or too rich, tam idle mixture adjustment in direction
required for correction.
F. Repeat step D. to check new position.
G. Make additionaladjustmentsand checksas required,
NOTE
Each time idle speed mixture adjustment is
changed, Runup to 2000 RPM to clear engine
before proceeding with step D. Allowance
should be made for weather and field altitude
when adjusting idle mixture.
71-00-90
- TROUBLE SHOOTING
71-00-91
- STARTER TROUBLE SNOOTING
SERVICE AND MAINTENANCE MANUAL
NOTE
If above procedures do not result in stabilized
idle speed, check idle linkage for looseness.
2. For operation in high ambient temperature
conditions,adjustidle and mixture as follows:
A. Adjustidleto 700-750 RPM,or as high as practical.
B. In the cool of the morning adjust mixture to
provide a 50 RPM rise when the mixture contro s
slowly pulled to idle cutoff.
C. Maintain cooling airflow by keeping engine RPM
as high as practicaldudng ground runup.
71-00-70
- STARTER SYSTEM
MAINTENANCE
Refer to Section 80 for starter system maintenance
procedures.
CAUTION
Do not operate starter in excess of 30 seconds;
allow cooling time before re-engaging.
71-00-00
-ENGINE MIXTURE CONTROL
RIGGING
1. Disconnectmixture control.
A. Remove cotterkey.
B. Remove nut, bolt, and two washers from clevis
and mixture controlarm.
2. Reconnect mixture control.
A. Reverse disconnect procedure to reconnect
mixture control.
3. Adjustment of mixture control arm.
A. Loosen Iocknut on control rod end and adjust
controlarm rod as required.
B. Check for full travel.
C. Check for properthread grip.
D. Secure Iocknut.
See Section 24-39-04 for procedure. TEXTRON-LYCOMING OPERATORS MANUAL should be consulted.
71-00-92
- ENGINE TROUBLE SHOOTING
TROUBLE
Enginewill not start.
-:
; :
: _-I ;
-No fuel.
Check fuel system for leaks. Fill fuel
tanks. Clean lines, strainers, and fuel
valves.
-Incorrect throttle setting.
Open throttle 1/4.
-Defective spark plugs.
Clean and adjust or replace spark
plugs.
Check with tester and replace defective
wires.
-Defective ignition wire.
71-00-61
8
12-98
SERVICE AND MAINTENANCE MANUAL
IEQU_BLE
Engine does not idle propedy.
Low.power and uneven
running,
Engine does not develop full
power,
--
M20J
..:
'
EEMEDt
-Improper magneto operation.
Clean points. Check timing.
Internal failure.
Check oil screens for metal particles; if
found, remove foreign material and
overhaulengine.
-Incorrect idle mixture.
Adjust mixture control.
-Incorrect idle speed.
Adjust idle speed.
-Induction system leak.
Tighten all connections and replace any
defective parts. Clean injector nozzles.
-Mixture too rich as indicated
by black exhaust stacks.
(Extremely dch mixtures are
indicated by black exhaust
smoke.)
Readjust fuel injector.
-Mixture too lean as indicated
by overheatingand backfiring.
Check fuel lines for restrictions.
Readjust mixture. Clean injector
nozzles.
-Leak in induction system.
Tighten all connections and replace
defective parts.
-Defective spark plugs.
-Improper fuel,
Clean and gap or replace spark plugs.
Drain and fill tanks with recommended
grade of fuel.
-Magneto breaker points not
working properly.
Clean points and check timing.
-Defective ignition wire.
Check with tester and replace defective
wires.
-Defective spark plug terminal
connectors,
Check and replace connectors if
required.
.
-Leak in induction system.
Tighten all connections and replace
defective parts.
-Partial clogging of injector
nozzle or fuel screens.
Clean nozzle or fuel screens.
-Throttle lever out of adjustment.
Check throttle linkage travel.
Check strainers. Check flow at fuel
injector.
-Restdction in air scoop.
Examine air scoop and remove
obstruction.
-Faulty ignition.
Check Ignition system.
-Cracked engine mount.
-Partial clogging of injector
nozzles or fuel screens.
Replace or repair mount.
Clean nozzles or fuel screens.
-Defective mount bushing.
Replace bushing.
-Uneven compression.
Check compression.
-Damaged, out of track, or
unbalanced propeller.
Check propeller, track, and balance.
-Insufficient oil.
Fill sump with oil and inspect screen
and filter for metal particles after
running engine. If particles are found,
overhaul engine.
-Stuck relief valve.
Check and replace if necessary.
Improper fuel flow.
Rough running engine.
Low oil pressure.
MOONEY AIRCRAFT CORPORATION
12-98
71-00-90
9
MOONEY AIRCRAFT CORPORATION
TROUBLE
High oil temperature.
M20J
SERVICE AND MAINTENANCE MANUAL
EP_OE&gLE_AU_
BEMED__
-Air lock or dirt in relief valve.
Remove and clean oil relief valve.
-Dirty oil strainers.
Remove and clean strainers,
-High oil temperature.
See "High Oil Temperature" in Trouble
column below.
'Defective pressure gauge,
Replace gauge.
-Obstruction in oil pump
intake passage.
Check for obstruction,
-Defective pressure
transducer,
Replace transducer. (Do not over
torque fittings).
-Insufficient oil supply.
Fill sump with oll of recommended
grade and inspect engine for metal
particles in screen and filter after
running engine. If particles found
overhaul engine.
-Low grade of oil.
Drain and fill sump with oil conforming
to specifications.
-Stuck thermostatic valve:
-Clogged oil lines or
strainers.
Check and replace as necessary.
Clean oil lines and strainers.
Excessive blow-by.
Excessive oil consumption,
71-10-00
Check compression. Check for worn or
stuck rings.
-Oil cooler restdction.
Check and replace,
-Failing beadngs.
Check oil strainers for metal particles; if
found, remove foreign material and
overhaul engine.
-Defective temperature
gauge.
Replace gauge.
-Low grade of oil.
Drain and fill sump with oll conforming
to specifications.
-Failing bearings.
Check sump for metal particles.
-Worn rings.
Install new rings.
-Improper piston dng installation,
-Failure of rings to seat.
Install new rings.
Use mineral-base oil. Climb to cruise
altitude at full power; operate at 75
percent power or higher until oil
consumption stabilizes.
- ENGINE COWLING
71-11-00
- COWLING REMOVAL
The engine cowling is in two sections.The lower cowl
(SIN 24-0001 thru 24-3153) containsthe ram-air inlet,
landing lightand cowl flaps. SIN 24-3154 thru 24-TBA
containonlythe cowl flaps. Quick-disconnectfasteners
attach the cowlingpanels. The oil filler access door is
in the top cowling section,
71-il-01
-TOP COWLING
71-1fi-01
3. Unlatch cam locks on the aE edge of the top
cowlingjust ahead of windshield.
- ENGINE COWLING CLEANING,
INSPECTION & REPAIR
1. Remove two (2) screws from top cowlingon each
inboardside of enginecoolingair intakes.
2. Remove (1) screw from each side of top cowling,
forwardand outboa_l.Then unlatchcam lockson each side.
Clean cowl by spraying with solvent (PS-661 or
equivalent) and wiping, clean. At_er cleaning, inspect
cowlingfor dents, cracks, and loose fasteners. Repair
defects.
71-10-00
10
12-98
4. Carefullylifttop cowlingoff.
SERVICE AND MAINTENANCE MANUAL
'
71-11-02
- BOTTOM COWLING
1. Disconnect landing light wiring
connectors near firewall. (24-0001 thru
i
24--3153)
M20J
MOONEY AIRCRAFT CORPORATION
- ADJUSTING
-/"
A. Cut ty-raps secudng insulatingtubes
over knife disconnects.
.._
B-
E0_L
FLAP
ROD
FLUSH
ENGINE
COWLING
B
_/ITH
11_
J_
towardflrewalL
C. Disconnect knife disconnects and
2. Disconnect cowl flap control md ends
at the quick disconnects located on the cowl
flap brackets. See Figure 71-1.
NOTE
Reach up through the cowl flap
opening tOcontroldisconneCtrods,
flap
slide insulaflng
tube back over cowl
disconnect.
3. Unlatch cam lockslocated on bottomof
cowlingbetweenor aroundthe cowl flaps.
4. Unlatch the remaining cam locks on
bottomcowlingwhilesupportingthe cowl.
5. Carefullylowercowlingclear of spinner
and removefrom aircraft.
71-12-00
- COWLING INSTALLATION
i
'_
F
7_.1____
COWL FLAPRIGGING (24-0001 THRU 24-2999) FIGURE 71-1
71-13-02
NOTE
Check condition of tape on firewall flange
where cowling rests. It is recommended that
vinyl tape be replaced with polyethylene
tape,(3M tape, PIN 5421, (UHMW) 1', wide). This
will decrease the streaking during wet weather,
71-12-01
-BOTTOM COWLING
1. The bottom cowling is installed ,first" in reverse
sequence of removal.
CAUTION
Be sure landing lights and cowl flaps are
connected prior to installation of top cowling,
(24-0001 thru 24-3153)
71-12-02
,TOP COWLING
1. The top cowling is installedin reversesequence of
removal,
71-13-00
- ENGINE COWL FLAPS
71-13-01
, COWL FLAP RIGGING
(24-0001 thru 24-2999)
1. Adjust both the left and dght cowl flaps so that in
the closed position the outboard trailing edges are
flush with the lower engine cowling, (Figure 71,1) (B).
Maintain .06 - .12 in. "cushion"on cowl flap control at
the instrument panel when cowl flaps are closed. The
scissorsshould be in an overcenter positionwhen cowl
flaps are closed.
• NOTE
For improved cooling during summer months
or above normal temperature operations, cowl
flaps may be rigged to have a .25 max inch gap
at "B" when at the closed position,
- COWL FLAP RIGGING
(24-3000 thre 24-TBA)
The cowl flapsare activatedUP and DOWN by an idler
arm connected, by a push-pullrod, to the actuatorarm
on a geared motor.A cowl flap switch, locatedon the
cockpit console directly under the mixture control,
activates the geared motor. The- switch has three
positions: a center (OFF), an up (CLOSED) and a
down (OPEN) position. The cowl flaps may be
positionedto any angle by selectingthe switcheither
UP or DOWN untilthe desired position,as shown on
the positionindicator,has been reached. Then return
the switch to the center (OFF) position. Limit switches,
which are not adjustable, prevent the cowl flaps from
exceeding the fullopen or full closed position.
A cowl flap positionindicator is located on the cockpit
console adjacent to the flap switch. The indicatoris
operatedby a cable connectedto the actuatorarm and
routed to the indicator on the console (24-0001 thre
24-3410). A potentiometerelectrically controlsthe LED
indicatorfor 24-3411 thru 24-TBA).
The cowl flaps are riggedfor a flush contourbetween
the cowl flaps trailingedges and cowling,when in the
closedposition.Adjust per followingprocedures:
1. With the cowl flaps open, adjust the linkage rods
from the idler arm to the cowl flaps to their maximum
length.
2. Close the cowl flaps and measure the distance
betweenthe cowlflaps trailingedges and cowling.
3. Open the cowlflaps and readjust the linkage rods,
decreasingthe lengthby the measuredamount.
4. Close the cowl flaps and ensure that cowlflaps
are not outside the cowling contour or that the cowl
flaps are not preloaded against the nose gear box.
Readjust as required.
12-98
71-11-02
11
MOONEY AIRCRAFT CORPORATION
71-13-03
M20J
- COWL FLAP INDICATOR
ADJUSTMENT
6. Cycle cowl flap system to vedfy proper movement
of indicator.
(24-3000 THRU 24-3410)
1. Position the actuator and indicator in the down
position.
2. Insertcable thru drilled bolt (2) in actuator arm (1)
and tighten. Reference Fig. 71-2.
3. Cycle cowl flaps actuation system a minimumof
five timesto insurefree movementofthe indicator,
4. Readjust push-pull cable wire at actuator arm, as
required,for proper indicatortravel and secure.
71-30-00
Firewall fireseals and grommets, If removed and
replacedfor any reason, shouldbe sealed alter routing
the cable or wire assembly from the engine
compartment into the cockpit area. Alter installation
cover cable or wire and grommet undemeath the
flreseal with Coast Pro-Seal 700 on engine side of
firewall.
71-60-00
- AIR INTAKES
71-60-01
"_
2
/
duct permits alternate air to enter the engine from
within
the engine valve
cowling.
door should
A spring-loaded
in The
the alternate
induction air
system
intake
be inspected for proper preload and condition per 100
1
hour inspection in SECTION 5-20-06, 1, G.
CAUTION
Check security of seal to induction box door.
Use EC1403 or EC1300L adhesive to secure
LOOKING
,"
AT CENTER
CONSOLE FROM
RIGHT
SIDE
{
COWl. FLAP INDICATOR RIGGING - FIGURE 71-2
(24-0001 THRU 24-3410)
71-13-04
-COWL FLAP INDICATOR
ADJUSTMENT
(24-3411 THRU 24-TBA)
1. Positioncowl flaps in closed position.
2. Adjust cowl flap p0tentiometer on aircraft, to
illuminatetop bar in display.
3. Positioncowlflaps to OPEN position.
4. AdjustR1 on AID board, if necessary, to illuminate
bottom bar on display,
5. Repeat steps 2 'through 4, until no further
adjusment is required,
71-13-03
12
- ENGINE INDUCTION SYSTEM
MAINTENANCE -
is
ducteda to
theAir
fuel
injector.
On aSIN
24-0001 thru
24-3153
Ram
control
moves
two-positiondoor
manually
operated
24-3153). filtered or
in
the ram-air
duct (24-0001
to permitthru
the selectionof
unfiltereddirect
ram air. portin the lower cowlingand
Ram air entersthrougha
/___¢:_
_'/
/_
- FIRESEALS
The engine coolingair intakes and exits are calculated
for optimumcooling requirements and minimumdrag.
Normal engine operating temperatures are at the
optimumto facilitateengine efficiency.
The engine inductionair intake is an aluminum duct
that picks up impact air and routes it through the air
filter to the engine injector assembly. The air intake
system includes a RAM AIR intake system that is
COWL FLAI
INDICATOR
I
SERVICE AND MAINTENANCE MANUAL
seal to door.
A dry-type,panel, air filter mountsinthe air intake duct.
Filter maintenance is directly related to engine wear;,
therefore, the filter should be removed and cleaned
every 25 hours or more frequently under dry and dusty
operating conditions. Replace the filter alter 500
operating hours or once each year, whichever occurs
first.
1. Clean the dry-type induction air filter with
compressed air. (Ref. to Section 12-20-01). Replace
the filter if it has a damaged housing,tom element, or
damaged gaskets.
2. Reverse the air filter removal procedure for
reinstallation. Make certain that the filter is tightly
sealedand securelyfastened in place.
71-61-00
-REPLACEMENT
AIR INTAKE DUCT
When the air induction duct must be replaced it is
essential that the duct be positioned exactly as the
odginal installation to prevent any interference with the
cowling.
12-98
MOONEY AIRCRAFT CORPORATION
M20J
CHAPTER 72
ENGINE
SERVICE AND MAINTENANCE MANUAL
SERVICE AND MAINTENANCE MANUAL
M29J
MOONEY AIRCRAFT CORPORATION
CHAPTER 72
(
ENGINE
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
72-Eft/Contents.........
72-00-00.
...........
72-50-00.
...........
PAGE
..........
DATE
1/2BLANK ..........
3 ...........
4 ...........
12-98
12-98
12-98
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
72-00-00 ........
72-50-00 .........
SUBJECT
General ..............
Lubrication ............
12-98
........
PAGE
3
3
72-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
M20J
72-00-00
- GENERAL
Refer to TEXTRON-Lycoming Operators Manual No.
60297-12 and Overhaul and Maintenance ManualNo.
60294-T f or detailedinformationon above topics,
72-50-00
- ENGINE LUBRICATION SYSTEM
MAINTENANCE.
The
engine
lubrication
is a pump.
full-pressure,
wet-sump
system
with asystem
gear-driven
An oil
coolerattaches to the firewall on the M20J model.The
oil filter is locatedat the rear end of the oil sump. (Oil
pressure:60 PSI MIN, 90 PSI MAX, 26 PSI at IDLE,
100 PSI MAX duringenginewarmup),
1. FilterServicing.
A. Oil Filter Removal and Installation.
SERVICE AND MAINTENANCE MANUAL
2. Oil Pressure Relief Valve. The oil pressure relief
valvemaintainsoil pressurewithinspecified limits.The
valve is not adjustable; however, the addition of a
maximum of three (TEXTRON-LycomIng P/N STD
425) washers under the cap will increase pressure.
Using a spacer (LycomingPIN 73629 or 73630) under
the cap decreasespressure.The oil relief valve should
be disassemblied, inspected, and cleaned when
excessivefluctuationsin oil pressure are noted.
3. Oil Cooler Thermostatic Bypass Valve. The oil
coolerthermostaticbypass valve or vematherm valve
is not adjustable.This valve allowsoil to bypassthe oil
coolerwhen the coolerbecomes obstructed or when oil
congeals in the cooler due to low ambient
temperatures.
(1). Remove old filter and replace with new filter
after light film of oil has been spread on gasket.
Tightento a torqueof 18 - 20 ft. Lbs.
12-98
72-00-00
3
SERVICE AND MAINTENANCE
MANUAL
M20J
BLANK
72-50-00
4
12-98
MOONEY AIRCRAFT CORPORATION
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 73
ENGINE FUEL SYSTEMS
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 73
ENGINE FUEL SYSTEMS
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
73-Effectivity .........
73-00-00 ............
73-31-91 ............
73-81-01 ............
73-31-02 ............
73-31-03 ............
73-31-94 ............
PAGE
..........
DATE
1/2BLANK ..........
3 ...........
4 ...........
5 ...........
6 ...........
7 ...........
8 ...........
12-98
12-98
12-98
12-98
12-98
12-98
12-98
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
73-00-00 ........
73-30-00 .........
73-31-00
..........
73-31-01 ............
73-31-02 ............
..............
..............
..............
73-31-03 ............
73-31-04 ............
73-31-05 ............
..............
73-31-06 ............
..............
73-50-00 .........
SUBJECT
........
PAGE
General ..............
Indicating .............
Fuel Flow System - General System Description
Panel Mounted Instrument......
Fuel Flow Transducer .......
FT-101 SYSTEM
ALCOR-TRU FLOW SYSTEM
SHADIN SYSTEM
General Operating Procedures ....
Test Function .........
Troubleshooting "FT 101"
Fuel Management Systems .....
Troubleshooting ALCOR
Fuel Management Systems .....
Druck Transducer Test Procedure ......
12-98
3
3
3
3
6
7
8
8
8
8
73- EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
M20J
73-00-00
- GENERAL
The engine and its accessories am certificatedunder
TEXTRON-Lycoming Type Certificate. Refer to
LycomingOperators or Overhaul Manual for specific
instmcfions,
73-30-00
- INDICATING
73-31-00
-FUEL FLOW SYSTEMGENERAL SYSTEM DESCRIPTION
The Fuel Flow totalizer system utilizes the latest in
microcomputer technology products, The fuel flow
system is designed to maximize the efficiencyof fuel
system management by displaying the fuel
consumption rate (fuel flow) of the engine and the
preciseamount of fuelthe engine has consumed.This
informationis displayedin one of the followingformats
US Gallons, Pounds,Litersor Imperial Gallons (Alcor)
depending on internal switch arrangement, see
(Figures 73-t and 73-2).
The system consists of a panel mounted instrument
and a fuel flow transducer which is installed in the
aircraftfuel line.
The systemis designed for use in all single enginefuel
injected aircraft having no more than 60 GAL/HR
continuous consumption or 78 GAL/HR Intermittent
consumption.CTakeOff power),
73-31-O1
-PANEL MOUNTED INSTRUMENT
The panel mounted instrument contains all system
electronicsand may be divided intofour groups.
SERVICE AND MAINTENANCE MANUAL
FT-101 (SYMBOLIC DISPLAYS-SDI)
1. DISPLAY- The display uses one minilamp and four
seven segment incandescent digits that are fully
sunlight readable and dim automatically during night
and low lightflight conditions.
2. MICROPROCESSOR - The microprocessorin the
FT-101 contains a crystal controlled oscillator that
controlsall timing and computingfunctions for precise
fuel flowand tutalizingcomputations.
3. POWER SUPPLY - The FT-101 powersupply is a
high speed switching regulator type for optimum
efficiencyand the lowestpossible power drain on the
aircraftelectricalsystem.
4. MEMORY - The FT-101 microprocessor
continuouslystores and updates the totalizecl fuel
quantity in a random access memory chip. The Total
Fuel Used quantityis retainedduring aircraft shutdown
by connectingthe FT-101 memory wire to the aircraft
battery through a memory switch. The drain on the
aircraft battery =ssmall due to the low power CMOS
memorychipwhichusesonly 0.7 milliampsat 12 VDC.
5. INTERNAL SWITCH ARRANGEMENT - The
programmingswitch block (see Figure 73-2) IocateP
inside the FT-101 panel mounted unit has several
arrangements to change data readout if desired.
Switches $1 and $2 (see Figure 73-1) should not be
changed unless the transducer "K" factor of a
replacementtransducer differsfrom the original unit's
"K" factor (see Section 73-31-02, 3, for "K" factor
description).
$3 thin $7 can be positionedin vadous arrangements
to change fuel flow readoutto galIons, poundsor liters
as the situationmay require,(see Figure 73-1).
FT-101 SWITCH ARRANGEMENT
....
................
K- FACTOR
........
....
....
....
....
L ...........
M ..........
H ...........
HH ............
....
................
FUNCTION
....
....
....
GALLONS ..........
POUNDS ..........
LITERS
..........
SWITCH ARRANGEMENT
$1
$2
ON
ON
OFF
OFF
.........
ON
OFF
ON
OFF
SWITCH ARRANGEMENT
$3
$4
$5
$6
$7
ON
OFF
OFF
OFF
ON
OFF
OFF
OFF
ON
NA
NA
NA
NA
NA
NA
FT-101 TRUTH TABLES
FIGURE 73-1
12-98
73-00-00
3
SERVICE AND MAINTENANCE MANUAL
M2OJ
MOONEY AIRCRAFT CORPORATION
2. ELECTRONICS - The TRU FLOW 1 amplification
systemis located in the indicator away from the engine
.=nvironment.The TRU FLOW 1 operates on a low
)ower requirement and is protected against voltage
_urges.
3. MEMORY - The TRU FLOW 1 microprocesser
IN_INSULATOR
'
luantity. The total fuel usedquantity is retained dudng
aircraft shutdown through a low power drain memory
;ircuit connected to the battery.
4. INTERNAL CONTACT ARRANGEMENT - The
INSULATOR
_S-REWSC
_'__joT
configuration
selection
block
located
the
TRU
FLOW
;ontinously
1 indicator
updates
has and
several
stores
arrangements
the inside
total to
fuel
change
used
.ta
..at.......e
be
changed uness the K-factor of the transducer has
changed due to replacement. (See Section 73-31-02,
6 7
Alcor contactarrangement.
'\' 1
t-HOUSING
_o_
._,_/_C_K_
FT-101 SWITCH ARRANGEMENT- FIGURE 73-2
TRU FLOW 1 (ALCOR)
1. DISPLAY - The unit features a liquid crystal
display(LCD) to indicate fuel flow and total fuel used
simultaneously. The display is back lighted and
features automaticdimmingthrough a photosensor.
K1
K3
STEP 1. Remove 4 screws (2 on rear of indicator,
which also removes connector latch, and 2 on side).
Then remove electronic assembly by simultaneously
pushing on rear connector and pulling on front bezel.
DO NOT BEND THE BOARD CONNECTOR PINS.
K5
b---Oqo
iCL_DJ
o
K7
b----O]
0
o LO__OJ
O Io ol
O LQ_QI
o o o
o o o
o o o
o o o
o o o
o o o
O O O
O O O
O O O
O O O
O O O
O O O
o o o
o o o
o o o
o o o
N
N
N
N
K-FACTI]R_
NOT USED_
UNITS
CAUT,ON
Some components in the indicator can be
damaged by static electricity. Dissassemble the
at
static controlled
DOfor
3, indicator
for
K-fac
)r adescrpton).
Refer workstation.
to
Fgure
73-3
NOT
LEAVE
THE iNDICATOR
UNTIL
IT HAS
BEEN REASSEMBLED.
L
K
L
K
U,S, GALLONS IMP, GALLONS
0
K-FACTOR_
NFIT US
O0
o o o
73-31-01
4
K
L
K-FACTOR
K
prlUNDS
LITERS
JO00
000
000
i,o o o
o o o
o o o
"IZ)
o o
iooo
o o
!
o o o
ooo
o o o
o o o
oooo o
o
UNITS
O O O
O O O
O O O
UNITS
L
A
_
J_)
o -_o
o8
I N73-31
TRU-FLOW
UM ERARRANGEMENTF,GURE73-3
12-98
MOONEY AIRCRAFT CORPORATION
M20J
STEP 2. Remove front bezel assembly from main
assembly by grasping edges and slowly pulling bezel
from main assembly,
STEP 3. Remove one of the two screws holding the
main assy,boardsto the standoff,Separate the boards
by graspingthe edges and pullingthem apart, DO NOT
BEND THE PINS,
STEP 4. Locate the circuit board and the
CONFIGURATION SELECTION BLOCK inside the
indicator,
STEP 5. Determine the K-factor to be selected to
match the K-factor of the Flowscan 201-B transducer.
Use one of the following K-factors to match:
Flowscan
Alcor K-Factor
Transducer
Code
Code
L
EQUATES TO
K7
M
K5
H
K3
HH
K1
Arrangethejumpers according to Figure 73-3, partA,
STEP 6. Determine the desired unit of measurement,
Reposition the jumpers according to the examples in
Figure 73-3, par[ B.
STEP 7. Pdnt the K-factor and unit of measurement on
the dot label located on the back orthe Indicator case.
STEP 8. Atter reposiUoning the jumpers, reassemble
the indicator in the reverse order of disassembly,
CAREFULLY LINE UP THE PINS.
STEP 9. Alter reassembly, power up indicator and
check configuration.For approximately 2 seconds the
dght side of the indicator display will depict numbers
that indentifythe configurationsof units.(Figure73-5).
STEP 10. If fuel flow or quantity used totals do not
match actual values after several hours of flying
contact the manufacturer (Alcor) for trouble shooting
procedures,
Aeresonic Transducer
Floscan Transducer
SERVICE AND MAINTENANCE MANUAL
NOTE
Repnsition the jumpers by grasping with needle
nose pliers and pulling straight up to remove
them, then reinsert to select the appropriate
K-factors and units,
SHADIN SYSTEM
SHADIN SYSTEM MEMORY
System includes a non-volatile memory for retaining
basic settings and Fuel Remaining and Fuel Used
dudng power shut down.
TEST FUNCTIONS AND ERROR MESSAGES
Press "TEST" button. Program checks hardware and
display. If test is successful, "good" is displayed; if not
"bad" is displayed and system is to be considered
unserviceable untilcorrective action is taken.
When "test routine" is completed, system will display
the following:
1. Softwarebasic # and revision level.
2. K factor setting in flow window (pulse count per
gallon). This number MUST match pulse count
stamped on fuel flow transducer, otherwise errors will
occur.
3. Display units (Gal., LB 5.8), part of checking
internal settings.
4. Loran-C (GPS) distances as shown on Loran-C
(GPS) receiver to check Data Interface Integrity. If
system is not capable of reading Loran-C (GPS) data,
the word "LbAd" will be displayed.
REPLACEMENT OF SHADIN SYSTEM
COMPONENTS
Replacementof either flow flow transducer or display
unit must have new units set to same K- factor as old
unit. Transducers are pre-set by manufacturer and
display unit must be set to agree with transducer
setting.Refer to table below:
K-Factor
3 (85000 pulses/gal.)
L
M
H
IndicatorSetting
3 or 85000
82000
85000
87000
To change K-Factor in Shadin Minifio display unit:
1. Remove can from indicator
2. Locate switch "0". (Ref. Figure 73-6)
3. Set switch to one of the following positions:
K-Factor
Sw. #
Display will read
K-Factor
Sw. #
Display will read
K-0
K-1
K-2
K-3
K-4
B
A
9
8
7
88.0
87.0
86.0
85.0
84.0
K-5
K-6
K-7
K-8
K-9
6
5
4
3
2
83.0
82.0
81.0
80.0
79.0
12-98
73-31-01
5
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
Transducers are categorized by
output for a given GPH flow rate
("K Factor)". This will be noted
as: L, M, H, or HH scribed on the
end of the serial no. For accurate
readings, replacement
transducers should have the
_ cDnjE_'l'_lo_
.n_
A SDUCERi
-_
u_
replaced,
Specify
"K"
thebeing
number
of pulses
per second
new.
factorSame
unitScode
"K" factor
when ordering
as the
4. Fuel flow transducer removal.
TURBINE FUEL FLOW TRANSDUCER - FIGURE 73-4
A. Remove top and bottom
transducers.
cowling from
aircraft. See Section
71-10-00 for procedures.
B. Cut and remove ty-raps from
insulator
sleeves
on
knife
disconnectsof electricalwires.
- FUEL FLOW TRANSDUCER
C. Slide insulationsleevingup on
electdcalw!re harness.
1. The turbine flow transducer, mounted in the
enginefuel line, measures flow of fuel. The transducer
is rated for a continuousoperation to 60 gallons per
hour. In addition,the transducer is accurate down to
0.6 gallonsper hour.
2. Thetransducersuppliesthefuelflowindicatorwith
a pulse signal from a self contained opte-electronic
pickup.A neutrally buoyant rotor spins with the liquid
between V-jewel bearings. The rotor movement is
sensed when notchesin the rotor interruptan infra-red
light beam between a light emitting diode and a
photo-transistor.
D. Disconnecttheknifediscennects.
E. Remove safety wire from flresleeve around
turbinetransducer and unwrapfiresleeve to exposethe
transducer.
F. Loosen and remove nuts, washers and bolts
from transducer and bracket. Pull transducer and
hoses awayfrom engine as far as possible.
G. Disconnect the hose nuts from transducer
fittings.The transducershould now be free for removal.
Note positionof fittingson oldtransducer.
H. Cap all linesto preventcontamination.
3. The transducer design is fail safe; complete rotor
blockagecannot interruptfuel flow. The transducerlife
expectancyis 1500 hours.
5. Fuel flow transducer(replacement)installation.
73-31-O2
r_
SOFTWAREVERSIONNO.
,
t
iCO
El
.
_ _
,
:
K - FA TOR
.-
FLOW
./
UNIT OF MEASUREMENT
TOTAL
J
UNITS:
4 = U.S. GALLONS
3 = IMPERIALGALLONS
2 = POUNDS'(5.85 X U.S. GALLONS)
K-FACTORS ARE DISPLAYEDAS ACTUAL K-FACTOR RANGE, ie., 1 = K1, 2 = K2, etc.
TRU-FLOW 1 CONFIGURATION - FIGURE 73-5
73-31-02
6
12-98
MOONEY AIRCRAFT CORPORATION
us
M20J
us
SERVICE AND MAINTENANCE MANUAL
II
[U9
i374HC74II I,-L,'I. I us
\
-[E;
_)
U1
i
]_'l
RN,
I
I
J1
L
27cxxx
[SN73-SHA
SHADIN
FUEL
PLOW
C ROUITFIGURE
73-B
NOTE
The "K" factor of the replacement transducer
should match the "K" factor of the replaced
unit. Refer to "NOTE" following Section
73-31-02, paragraph 3 for detaUed explanation,
A. Notethe positionof fittingson old transducerand
placethem insimilarposiflononthe newtransducer,
B. Connect hose nuts to transducer fittings, tighten.
C. Connect the new transducer to bracket using
belts, washers and nuts.
CAUTION
Make sure the hoses are not being put into a
bind or twist when securing the transducer to
the bracket,
D. Tighten all nuts on fuel hoses and bolts to
securethetransducer,
E. Connect the knife disconnects and slide
insulatingsleeving over connections. SeciJresleeving
withty-raps.
F. Leak check all fuel connectionsby pressudzing
the fuel lines with boost pump. Correct any leaks or
discrepancies,
G. Wrap flresleeving over transducer and secure
into positionwithsafetywire.
NOTE
Installation of the newtransducer may affect
the engine fuel flow adjustment. It is
recommended that the procedures of Section
71-00-00 be followed to assure engine is set up
for proper operation,
H. When all adjustments have been made and all
connections checked for security, install the cowling
per Section71-12-00.
73-31-O3
- GENERAL OPERATING
PROCEDURES
1. Turn on the aircraft master switch. On activating
the aircraft electrical system, the FT-101 display will
flash zeros (000.0). This flashingis a reminderfur the
pilot to reset or check the fuel used number by
pressing either the RESET or USED/TEST buttons.
Once the RESET or USED/TEST button is depressed,
the display will stop flashing and read fuel flow.
The TRU FLOW 1 will display the configuration unit
and K-factor on the right side of display window (Refer
to Figure 73-5).
After starting the aircraft engine, the FT-101 will
continuouslydisplayfuel flow. Total Fuel Used may be
displayed by pressing and holding the USED/TEST
buttonon the rightof the instrument.Total Fuel Used
will be displayed as long as the USED/TEST buttonis
depressed (or for 2 seconds), whichever comes first.
This number may be reset to zero (0.0) by depressing
and holdingthe RESET button for at least 1 second.
The TRU FLOW 1 displays both functions
simuitaneoulsy.
2. The totalizer function in both systemsbe used as
a single flighttotalizer or as a long term totalizer.Both
methods are explained below.
A. SINGLE FLIGHT TOTALIZER. The aircraft
should be topped with fuel before each flight so the
total usable fuel will be known. Turn on the aircraft
master switch. On activating the aircraft electrical
system, the FT-101 will flash zero (000.0) fuel flow.
Push and hold the reset button, located on the left of
either instrument, for at least 1 second. The RESET
button has a one half second delay to prevent
accidentalreset.
On startingthe engine, the FT-101 will begin displaying
fuel flow. Total fuel used may be checked by
depressingthe USED/TEST button.
12-98
73-31-03
7
SERVICE AND MAINTENANCE MANUAL
M20J
B. LONG TERM TOTALIZER. Tum on the aircraft
master switch. On activating the airoreit electdcal
system, the FT-101 will flash zero (000.0) fuel flow.
Depress and hold the USED/TEST button the FT-101
willdisplaythe total fuel used from previousflights. DO
NOT push the RESET button! On starting the engine,
the
will
fuel flow9999
and continuecounting
fuelFT-101
used up
todisplay
999.9 gallons,
pounds, or 9999
liters depending on the model. The Alcor unit will
displayfuel flow and totalused from pastflights,
73-31-04
- TEST FUNCTION
A test function is provided in the FT-101, so the pilot
may vedfy that all digits are functioning pdor to each
flight. To use the test function, depress and hold the
USED/TEST button two times within one second and
the FT-101 will display all eights (888.8).
73-31-05
-MANAGEMENT
TROUBLESHOOTING
FT-101 FUEL
SYSTEMS
Troubleshootingthe FT-101 fuel management system
should be approached in a systematic manner. All
problemscan be put in one of five categories:
- Improper operation due to lack of knowledge about
the system,
- Inoperativecomputer or main instrument.
- Inoperativetransducer.
wires. Check BLACK wire for A/F ground. Check RED
wire for bus voltage. Check WHITE wire for 2-3 volts
with no fuel flow and increasing to near bus voltage at
fullflow.
(2) If no increase in voltage is seen on WHITE
wire as flow increasesor if too high a voltageindication
isseen with noflow, change transducer.
(3) If RED wire does not have bus voltage, check
wiringfrom transducerto Pin 3 of indicator.
(4) If BLACK wire is not grounded, check widng
from transducerto Pin 6 of indicator.
3. ERRATIC INDICATIONS
A. Checkwidng forloose connections.
B. Check wiring for intermittent shorts.
C. Check transducer for foreign particles,
D. If all checks OK, replace transducer.
4. INACCURATE READINGS
A. Check transducer K-factor. The letter
"L","M","H",or =HH" inscribedafter the serial number.
B. Remove indicator from instrument panel and
case. Check switch settings and correct to match
transducer.
NOTE
Each switch setting
changes reading by
approximately 2 %. If settings are OK, replace
transducer.
CAUTION
- Improperwiring,
- Impropertransducerinstallation,
1. MEMORY LOSS A. Loses memory when "MASTER" switch is
turned OFF.
(1) Check =Fuel Flow Memory"switchON.
Whenever transducer or indicator is replaced,
care must be taken to set indicator switches to
match transducer.
If after makingthese checksyou still do not isolatethe
problemor do not find a problem, contactthe Product
SupportDepartment of Mooney AircraR Company for
further assistance.
(2) If switchis ON, check clockfor operation,
(3) If clock inoperative,replacefuse at battery.
(4) If no problem found, remove connector from
unit,check Pin 9 for buss voltage.
(5) If voltage present,replace FT-101.
B. Memory scrambles when engine starts.
ExchangeFT-10_ for modifiedunit.
2. DOES NOT INDICATE
A. No display,
(1) Remove connector from indicator.Check Pin
1 of harnessconnector for bus voltage. Check Pin 8 for
airframe ground. If OK, changeindicator.
B. Displayszeros (withengine running)
(1) Remove cowling for access to transducer.
Remove insulating sleeving from connections on all
73-31-04
8
MOONEY AIRCRAFT CORPORATION
73-31-06
- TROUBLESHOOTING THE TRU
FLOW 1 (ALCOR) FUEL
MANAGEMENT SYSTEM
If problemis determined to be in the indicatorand all
transducerand wiring checks have been made, contact
Alcor, Inc., 10130 Jones-MaltsbergerRoad,
PC Box 32516, San Antonio, Tx. 78284, telephone
(210) 349-3771 for further assistance.
73-50-00
- DRUCK TRANSDUCER TEST
PROCEDURE
Referto Section 79-40-00
12-98
MOONEY AIRCRAFT CORPORATION
M20J
CHAPTER 74
(
IGNITION
SERVICE AND MAINTENANCE MANUAL
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 74
_
!
IGNITION
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ........
PAGE
74-Effectivity/Contents .......
74-00-00 ............
74-30-00 ............
..........
DATE
1/2BLANK ..........
3 ...........
4 ...........
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TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT " .
..........
74-00-00 ........
74-10-00 .........
74-10-01
..........
.............
74-10-02
..........
74-20-00 .........
74-30-00 .........
SUBJECT
........
PAGE
General ..............
Electrical Power ...........
Magneto Inspection, Maintenance, Installation
& Timing ...........
Ignition System Troubleshooting .....
Engine Firing Order ..........
Switching .............
12-98
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3
3
3
3
3
74-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
74-00-00
M20J
SERVICE AND MAINTENANCE MANUAL
- GENERAL
engines are equipped with Bendix 2000 or 3000
Sedes magnetos. The magneto incorporates an
impulse coupling that retards the spark for starting.
When the engine starts, counter weights hold the
impulse coupling latch pawls away from stop pins.
The magneto then will fire at its advanced firing
position.
The magneto/starter switch combines both ignition
and startingfunctions.Turn the key clockwisethrough
R, L and BOTH to START position;push forward on
key while in START and the starter relayis energized.
Release of the key, after engine starts,will return the
switchto the BOTH positionwhere both magnetosare
operative.
In the OFF positionboth magnetosare grounded.At
the R positionthe left magnetois groundedand atthe
L positionthe rightmagnetois grounded.
NOTE
Mooney Service Instruction M20-59A, or later
revision, should be complied with for improved
starting.
74-10-00
- ELECTRICAL POWER
74-10-01
ENGINE FIRING ORDER - FIGURE 74 -1
- MAGNETO INSPECTION,
MAINTENANCE, INSTALLATION &
TIMING
3. MagnetoDrop Out of Limits.
Refer to engine and magneto manufacturers Service
Manual for magneto inspection, maintenance,
installation and timing,
A. Checkmagneto-to-enginetiming.
B. Inspect contact breaker points for proper
clearances.
74-10-02
C. Check spark plugs and leads.
NOTE
Service.ignition system per
TEXTRON-Lycommg Service Manual Section 4.
74-20-00
- ENGINE FIRING ORDER
74-30-00
- SWITCHING
- IGNITION SYSTEM TROUBLE
SHOOTING
1. Hard starting.
A. Assure thatthe impulse couplingis operating.
B.Check magneto timingto engine.
2. Engine Roughness.
A. Install newsparkplugs.
B. Check plug leads for detedoretion,
C. Check magneto contact points for burning and
dirt accumulation.
The Magneto/Starter switch is connected to the
magneto grounding wires ("P" leads) of both magnetos.
Turning this switch from "BOTH" to "OFF" or from =R"
to "L" to "OFF" will ground out both or either magneto.
(See SECTION 74-00-00 for grounding sequence.)
12-98
74-00-00
3
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BLANK
74-30-00
4
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MOONEY AIRCRAFT CORPORATION
MOONEY AIRCRAFT CORPORATION
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SERVICE AND MAINTENANCE MANUAL
CHAPTER 76
ENGINE CONTROLS
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CURRENTLY NOT BEING USED
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76-ENGINE CONTROLS
1
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BLANK
76-ENGINE CONTROLS
2
12-98
SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
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SERVICE AND MAINTENANCE MANUAL
CHAPTER 77
ENGINE INDICATING
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 77
ENGINE INDICATING
LIST OF EFFECTIVEPAGES
CHAPTER
SECTION
SUBJECT ...........
77-Eft/Contents.........
77-00-00 ............
77-10-02 ............
PAGE
..........
DATE
1/2BLANK ..........
3 ...........
4 ...........
12-98
12-98
12-98
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
77-00-00 ........
77-00-01 .........
77-10-00 .........
77-10-01
..........
77-10-02
..........
77-10-03
..........
77-20-00 .........
77-20-01
..........
77-20-02
..........
SUBJECT
........
General ..............
Ranges .............
Power Indicating ...........
Tachometer ...........
Manifold Pressure .........
Fuel Flow Indicating System ......
Temperature Indicating .........
Exhaust Gas Temperature .......
Cylinder Head Temperature
......
12-98
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3
3
3
3
4
4
4
4
4
77-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
77-00.00
M20J
SERVICE AND MAINTENANCE MANUAL
- GENERAL
Engine indicatinginstrumentsand their sending units,
transducers,probes, etc., must be operatingproperly
to preventengine damage. It is recommendedthat all
engine indicatingcomponentsbe checkedat each 100
hour or annual inspectionto vedfy proper operation.
Calibrated instruments may be "Tee'd" into the
J_harticular
systems for a compadson check between
em and the aircraft'sinstruments.
77.00.01
- RANGES
POwer plant instruments operate electrically through
variations in resistance caused by pressure or
temperature changes, by vadations _n current output
caused by varying engine RPM or alternatoroutput, or
by pressurefrom engine inductionsystem.
1. Ammeter.
NOTE
The oil pressure relief valve may be honed to
improve low idle oil pressure.
5. Tachometer.
A. Green arc---1950 to 2700.
B. Red line---2700.
C. Yellow arc--1500 to 1950 RPM (1600-1950 S/N
24-0001 thru24-0377 except24-0084).
6. Cylinderheadtemperaturegauge.
A. Green arc--300 to 450 degrees F.
B. Redline---475degreesF.
7. ManifoldPressureGauge
A. Normaloperatingrange 10.0 to 35.0 In. Hg.
77-10.00
, POWER INDICATING
A. Range--+60
to 24-2999
-60 AMPS 24-0001 thru
77-10.01
B. Range--+70 to -70 AMPS 24-3000 thru 24-TBA
C. Tolerance--1.2 AMPS.
(S/N 24-0001 thru 24-1417)
These aircraft have a mechanical
installation.
2. Fuel pressure gauge.
tachometer
The electric tachometer (24-0001 thru 24-2999) counts
ignition pulses from the magneto to indicate engine
speed in revolutions per minute (RPM). The
tachometer is connected to the "L" and "R" terminals
on the Magneto/Starter switch and senses the
magneto impulses through this wire connection. Two
15K ohm resistors are in series between the "L" and
"R" terminals and the connection of these two wires
and the single wire going to the tachometer. These two
resistors, located immediately adjacent to the
Magneto/Starter switch inside the insulating sleeve,
protect the magnetos from grounding out if a short
develops in the tachometer.
The electric tachometer on SIN 24-3000 thru 24-TBA
gets its signal from a second set of breaker points in
the magneto. The tachometer counts the impulse and
records the correct RPM.
A. Green arc--14.0 PSIto 30 PSI.
B. Red line---14 MIN, 30 PSI MAX.
3. Oiltemperaturegauge.
A. Green arc--150 degreesto 245 degrees F.
B. Red line--245 degrees F.
C. Tolerance--3 degrees F.
4. Oil pressure gauge.
A. Green arc--60 to 90 PSI.
B. Yellow arc--(1) Idle range--25to
- TACHOMETER
60 PSI.
(2) Starting & warmup range--90 to 100 PSI.
C. Red line---25 PSI MIN, 100 PSI MAX.
TACHOMETER TROUBLE SHOOTING.
TROUBLE
PROBABLE CAUSE
REMEDY
No permanent or intermittent
indicator reading.
-Broken shaft.
Replace shaft.
-C/B out (IGN/CIG LTR)
Reset C/B.
-Broken wire
Check & repair wiring.
-Faulty instrument.
Replace instrument.
-Rough spot on, orsharp bend
in shalt.
Repair or replace shaft.
-Excessivefriction in instrument.
Replace instrument.
-Magnetotimingtoo wide
betweenmags.
ReUmemagnetos
-Isolation resistors at mag. sw.
increased in resistance value
Replace resistors.
Pointer Oscillates excessively.
12-98
77-00-00
3
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
TROUBLE (con't.)
PROBABLE CAUSE
REMEDY
PointerOscillatesexcessively
(con't)
-Wiringconnectionsbad.
Locateand repair
77-10-02
- MANIFOLD PRESSURE
pressure in the induction air manifold. Manifold
pressure varies somewhat with pitch attitude in flight
and therefore small oscillations may occur in flight,
particularly in turbulent air.
Manifold pressure is an indication of engine power
affected pdmadly by throttlesetting. The instrumentis
calibratedin inchesof mercury (Hg) and indicatesthe
MANIFOLD PRESSURE TROUBLE SHOOTING.
TROUBLE
PROBABLE CAUSE
REMEDY
Excessiveerror at existing
barometricpressure.
Pointer sh_ed.
Replace instrument.
Excessiveerror when engine
is running.
Lineleaking.
Tighten line connection.
Sluggishor jerky pointer
movement.
improperdampingadjustment.
Adjustdampingscrew.
Brokenor loosecover glass.
Vibrationor excessivepressure.
Replace glass and reseat case.
Dull or discolored luminous
markings.
Incorrect reading.
Age.
Replace instrument.
Moisture or oil in line.
Disconnect lines and purge with air.
77-10-03
- FUEL FLOW INDICATING SYSTEM
Aircralt with a combination EGT/OAT gauge utilize a
non-grounded EGT probe. An ohmmeter connected
between either lead and the probe case should
indicate high resistance. If zero or low resistance is
indicated the probe has shorted and should be
replaced.
77-20-02
- CYLINDER HEAD TEMPERATURE
Referto Section 73-30-00 forthis data.
77-20-00
-TEMPERATURE INDICATING
77-20-01
- EXHAUST GAS TEMPERATURE
(EGT) INSTRUMENT
A thermocouple, attached to the exhaust stack or all
exhaust stacks (optional) sends an electrical signal to
the E.G.T. Instrument. As the exhaust gas temperature
rises, the thermocouple sends an electrical current
through the field coils of the instrument, moving the
pointer to indicate temperature rise.
77-10-02
4
The cylinder head temperature (CHT) instrument
provides the operator with an indication of how hot or
cool the cylinders are operating during flight. A
resistance type temperature probe is installed in the
number 3 cylinder (standard configuration). An optional
system provides a probe in each cylinder to provide
monitoring of each cylinders temperature.
12-98
MOONEY AIRCRAFT CORPORATION
M20J
CHAPTER 78
EXHAUST
SERVICE AND MAINTENANCE MANUAL
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 78
EXHAUST
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
78-EFF/CONTENTS
78-00-00 ............
78-00-00 ............
PAGE
.......
..........
DATE
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4 ...........
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TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
78-00-00 ........
78-10-00 .........
78-30-00 ........
78-40-00 ........
SUBJECT
........
General ..............
Exhaust System Installation........
Exhaust System Servicing
.........
Pedodic Replacement Components .......
12-98
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3
3
4
78-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
I
M2OJ
78-00-O0
- GENERAL
The exhaust system's headers and exhaust pipes are
made from 321 CRES steel. They are designed to
optimallyscavengethecylinders exhaustgasesdudng
normalengineoperation.Inspectionsfor cracks, bums,
etc. are requireddudng each maintenanceactivityand
recommendedbefore each flight.
78-10-08
- EXHAUST SYSTEM
INSTALLATION
1. EXHAUST PIPE HEADERS TO ENGINE.
A. Place new exhaust gaskets in position on the
LH & RH engine exhaust flange studs,
B. Place
either LH
or RH flanges.
header pipes
into position
on engine
cylinder's
exhaust
Be careful
during
this procedureto ensure that exhaust gaskets remain
in proper positionon each cylinder exhaustflange.
NOTE
Attach new headers with existing exhaust
flange stud nuts. (If nuts have been damaged,
replace them with new nuts
SERVICE AND MAINTENANCE MANUAL
J. Tighten bolts/nutson ball joint flange. Spring will
begin to compress pdor to castellation on nuts
reaching cotter pin hole in bolt. Continue tightening
until any one of the nut castellaUons reach the
completehole in bolt. Install cotter pins in all bolts &
nuts.
K. Hangtailpipewith hanger assemblyattachedto
flrewallor exhaustcavitySupports.
L. Verify all hardware is secure on header pipes,
mufflerand tailpipe.
3. EGT PROBE INSTALLATION/SECURITY
A. EGT probe clamp assembly should be safety
wired after positioning and tightening of clamp to
prevent possible loosening due to engine operation.
78-30-00
- EXHAUST SYSTEM SERVICING
1. CLEANING
To properlyinspectexhaust system,componentsmust
be cleanand free of oil,grease, etc. Clean as follows:
Leave exhaust flange stud nuts looseso header pipes
are movable.
C. Lubricate outside of inner and inside of outer
slipjoints on headers and inside of mufflerpipe flanges
with Hi-temp anti-seize compound, C5-A (FeI-Pro) or
equivalent.
D. Have someone assist withthe placementof the
mufflerassemblyintothe already installedheaders,
E. Assemble muffler assemblyintothe not installed
header pipes; position headers onto the aircraft engine
exhaust flanges. Be careful during this procedure to
ensure that the exhaust gaskets remain in proper
posiflon on each cylinder exhaust flange,
F. When muffler and headers are attached to
engine, flange nuts snug but not torqued, check
that the muffler is free to move laterally, lee to dght,
with moderate push/pullforce. This insuresthat header
and muffler pipes are aligned properly,
NOTE
Proper lateral movement may be obtained by
loosening cylinder exhaust stud/flange nuts
and gently re-positioning header pipes (at the
upper flanges)inboard or outboard as the
situation requires. The stud/flange nuts can
then be re-tightened and the lateral muffler
A. Spray engine exhaust system componentswith
a suitable solvent (Stoddard Solvent), allow to drain
and wipedrywith clean cloth.
WARNING
Never use highly flammable solvents on engine
exhaust systems.
WARNING
Never use a wire brush or abrasives to clean
exhaust systems or mark on system with lead
pencils.
2. VISUAL INSPECTION OF COMPLETE SYSTEM
A thorough inspection of engine exhaust system will
detect any breaks or cracks causing leaks which might
result in loss of efficiency, loss of engine power or
engine compartment fire. Inspect per following
procedures:
NOTE
This inspection should be conducted when
engine is cool.
Remove all muffler shrouds/shields to permit full visual
inspection.
movement checked again,
G. When free movement of muffler is obtained,
torque exhaust flange stud nuts -- 100 to 110 inch Ibs.
Recheck for freedom of movement after nuts have
beentorqued,
H. Attach tailpipe to exhaust pipe ball joint flange
(3 bolts/springs/nutsat balljoint flange) with existingor
new hardware.
I. Orientate tailpipe'and muffler exhaustpipe so the
continuingplane is approximately parallel to the ball
joint connection. Verify tailpipe exhaust end is 1.5 +/0.5 inches from nose gear door assembly and the
exhaust opening is not pointed toward nose gear door.
A. LOOK FOR LEAKS - Examine surfaces
adjacent to exhaust system componentsfor signs of
exhaustsoot. Look for gray, red or black gas stains at
welds, clamps,flanges, etc. Inspect exhaust systemfor
chaffing by cowling, engine mount, cables or any
airframecomponents.
Inspect exhaust stacks for burned areas, cracks and
looseness.
B. LOOSE CONNECTIONS - Inspect exhaust
clampsfor cracks, loosenessand propersecurity.
NOTE
During inspection, particular attention should
be given to condition and security of flanges,
spot welds, slip joints, and welded areas.
C. INTERNAL EROSION - Examine bends and low
spots forthinning or pitting.
12-98
78-00-00
3
SERVICE AND MAINTENANCE MANUAL
M20J
D. STANDOFFS (PINS) AND HEAT TRANSFER
FINS - Look for missing or damaged heat transfer pins
or fins. Lookfor holes at these locations,
E. METAL FATIQUE - Inspect all surfaces for
bulging and distortion, and for groups of small cracks.
CAUTION
DO NOT mark any surface with lead pencils or
any carbon-containing markers.
F. BAFFLE
BREAKDOWN
Lookrestrictthe
inside mufflerfor
broken
bafflesor
tubes. These- can
outlet,
causingpowerloss.
G. HIDDEN DAMAGE - Carefully inspect all
internal surfaces that lie hidden under external
gussets,stiffeners,etc. CAborescopeis recommended)
78-40-00
4
MOONEY AIRCRAFT CORPORATION
H. INSTALLATION TIPS - Install only correct parts.
DO NOT FORCE FIT any component. Properly align
connectingcomponents.
Do not reuse gaskets.
Insure that attach bolts are propedy torqued. Exhaust
flange stud nuts are to be torqued to 100-110 inch Ibs.
78-40-00
- PERIODIC REPLACEMENT
COMPONENTS
It is recommended that all exhaust system
components, pipes, clamps and miscellaneous
mounting hardware be replaced at engine overhaul
time (2000 Hours).However,thorough inspection of all
componentsshould be made any time exhaustsystem
is removed from engine for component replacement.
The inspection should be made in the interest of
preventivemaintenance.
12-98
----
MOONEY AIRCRAFT CORPORATION
M20J
CHAPTER 79
OIL
SERVICE AND MAINTENANCE MANUAL
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
CHAPTER 79
OIL
LIST OF EFFEC'i'IVE PAGES
CHAPTER
SECTION
SUBJECT ...........
79-Effectivity/Contents .......
79-00-00 ............
79-30-02 ............
PAGE
..........
DATE
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4 ...........
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TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
!
...........
79-00-00 ........
79-0(:}-01 .........
79-00-92 .........
79-20-00 .........
79-30-00 .........
79-30-01
..........
79-30-02
..........
79-40-00 .........
SUBJECT
........
General ..............
Oil Filter Removal ..........
Oil Filter Installation ..........
Distribution ............
indicating .............
Oil Pressure............
Oil Temperature..........
Druck Transducer Test Procedure
12-98
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3
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79-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION
79-00-00
M20J
- GENERAL
2. Cut and remove safety wire on filter.
The oil system is a wet sump, pressure type system.
The engine sump has an 8 quart (U.S.) capacity.
Servicing of the oil quantity is provided through an
accessdoorlocated ontop of the enginecowling.
The aircraft is delivered with the proper weight,
non-detergent,mineral oil (MIL-L-6082). This oil should
be replaced at 50 hours or when oil consumptionhas
stabilized. The replacement oil should conform to
LycomingSpecification301F. The routine oil change
interval is 100 hours, however if operating in a dusty
environmentthe interval should be more often.
NOTE
A new, remanufactured or newly overhauled
engine should be operated on straight mineral
oil for a minimum of 50 hours or until oil
consumption has stabilized. Change to a
TEXTRON - Lycoming approved additive oil and
begin the 100 hour oil change interval.
NOTE
Refer to Section 5-20-07 or to Lycoming
Operator's Manual for approved oil products
and servicing information.
79-00-01
SERVICE AND MAINTENANCE MANUAL
3. Loosenthe spinoff oil filterand remove.
79-00-02
- OIL FILTER INSTALLATION
1. Positionnew tilter on adapter.
2. Tighten per instructionsonfilter.
3. Safetywire filter.
4. Perform leak check priorto flight.
5. Reinstall lower and upper cowling (see Sectio_
71-11-00).
6. Connectand secure all electdcal and mechanical
connections.
79-20-00
- DISTRIBUTION
Reference - FIGURE 79-1
- OIL FILTER REMOVAL
The engine oil filter should be replaced each 50 hours
and at evenj oil change.
1. Remove top and bottom cowling (see Section
71-10-00).
79-30-00
- INDICATING
79-30-01
- OIL PRESSURE
Oil pressureindicatingis providedthrough a pressure
transducer plumbed into the engine oil system.
Pressure variations change the resistance within the
transducer and this signal ddves the oil pressure
gaugelocatedwithin the clustergauge.
LUBRICATION DIAGRAM SCHEMATIC - FIGURE 79-1
12-98
79-00-00
3
SERVICE AND MAINTENANCE MANUAL
79-30-02
M20J
- OIL TEMPERATURE
The oil temperature gauge is an electric unit receiving
its signal from a temperature bulb in the engine case,
locatedbetweenthe oil coolerand the case. The probe
resistance changes as the oil temperature changes
and this vadesthe readouton the instrument,
79-40-00
-DRUCKTRANSDUCER
TEST
PROCEDURE
The DruckTransducer Test Box, GSE 030036, can be
used to simulatefuel and oil pressure in Mooney M20J
models that have the Druck pressure transducer
installed,
To use the unit for troubleshooting, the box is
connected to the aircraft harness in the engine
compartment,by disconnectingthe appropriate Druck
transducerelectrical connectorand connectingthe test
box in its place.
Turn aircraft Master Switch ON (insure engine gauge
circuit breakers are in) and adjust box to approximate
pressure desired. The engine gauge should read this
approximate pressure.
If pressure reading is.c.or.r_e__:
1. Verify Oil/Fuel pressure to Druck transducer with
mechanicalpressure gauge,
A. If correct--probable failure is Drucktransducer.
B. If incorrect--truubleshootoil/fuelsystem.
79-30-02
4
MOONEY AIRCRAFT CORPORATION
If pressure reading is_;
zero or pegged condition:
1. ROCHESTER gauge (S/N 24-0001 thin 24-3153)
A. Move transducer test box to connector on the
input of apprspdate pressure amplifier(located behind
instrumentpanel, right side). Check pressure reading
on Rochester gauge to see if it approyJmatelyagrees
with test box. If it does, repair wire harness from
pressure gauge amplifier, to the engine compartment,
If pressurereading is incorrectgo to step (b),
B. At the appropriateRochestergauge WIPER lug
read the following voltages to ground. (digital
mulfimeter or 20K ohrns/voitmultimeter)
201/205Fuel
201/205 Oil
14PSI
60 PSI
4.4 to 4.7 volts.
5.3 to 5,5 volts
1. If correct, probable failure in Rochester gauge
module.
2. If incorrect, probable failure in pressure gauge
amplifier.
2. SIGMA-TEK gauge (SIN 24-3154 thru 24-TBA)
A. Check widng for continuity between engine
compartment connector and Sigma Tek cluster. If
wiring is correctgo to (b).
B. Probablefailure in Sigma-Tek gauge module or
cluster.
12-98
MOONEY AIRCRAFT CORPORATION
M20J
CHAPTER 80
STARTING
SERVICE AND MAINTENANCE MANUAL
SERVICE AND MAINTENANCE
MANUAL
M20J
MOONEY AIRCRAFT
CORPORATION
CHAPTER 80
(
STARTING
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
80-Effectivity/Contents
80-00-00 ............
80-10-00 ............
PAGE
.......
..........
DATE
1/2BLANK ..........
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4 ............
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10-95
5-93
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
!
...........
80-00-00
80-00-01
80-00-02
........
..........
..........
80-00-03
80-00-04
80-00-05
80-10-00
..........
..........
..........
.........
SUBJECT
General
........
..............
Starter Troubleshooting
Starter Maintenance
PAGE
........
........
Starter Removal ..........
Starter Installation
.........
Starter Brushes ..........
Cranking .............
3
3
3
3
3
3
3
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1/2BLANK
MOONEY AIRCRAFT
80-00-00
CORPORATION
M20J
- GENERAL
MANUAL
6. Remove (3) nuts and (1) 5/16 inch bolt from starter
The airplane is equipped with a 12 volt starter (24-0001
thru 24-2999), 24 volt C24-3000 thru 24-TBA), supplied
with the engine package. (NOTE: Some M20J ATS
aircraft may be equipped
with 24 volt electrical
systems). The starter is located on the front of the
engine. The drive ratio of the starter drive pinion to the
crankshaft is 16.556:1.
When the ignition switch is placed in the "START"
position, current is supplied through the main bus to
engergize the starter solenoid which in turn connects
the battery to the starter.
Electrical
power is
automatically cut off from the radios when the starter
current is engaged.
80-00-01
SERVICE AND MAINTENANCE
- STARTER TROUBLESHOOTING
1. Refer
to
Section
24-39-04
for
TroubleShooting Chart
80-00-02
-STARTER MAINTENANCE
1. Inspect
and ser_,ice starter
per
Maintenance Instructieiqs Overhaul Manual.
mounting pad.
7. Remove starter and starter drive assembly.
80-00-04
-STARTER INSTALLATION
1. Before installation, clean any rust corrosion or dirt
from the starter motor.
2. Check all connections for tightness.
3. Reverse
reinstallation.
Lycoming
starter
removal
procedure
for
4. Recheck torque, security and safetying.
5. Install cowling.
80-00-05
Starter
the
- STARTER BRUSHES
The starter brushes shauld slide freely in the holder
and make full contact an the commutator. The brushes
should be replaced when they have worn to 1/2 of
original length. Brush tension should be 32 to 40
ounces as measured with a spring scale hooked under
the brush spring and pulled in e straight line opposite
the force exerted by the spring. Read the tension just
or 2.
starter
drive except
at overhaul. is required on starter
Lubrication
- No lubrication
80-10-00
- CRANKING
as the spring leaves
the brush.
3. Check electrical leads for security and condition of
wire.
CAUTION
Do not clean the statler in any degreasing tank or
grease dissolvin 9 solvents. Avoid excessive
lubrication. Use only kerosene orVarsoL
The starter solenoid is located on the cabin side of the
firewall. The solenoid is energized by placing the
ignition/magneto
switch in the start position. Battery
current is then directed to the starter. Aircraft serial
number 24-1214 and ON are equipped with a "START
POWER ON" annunciator light. This light illuminates
when the starter switch is in start position or when the
starter switch or starter solenoid has malfunctioned
and the starter is engaged while the engine is running.
This malfunction shauld be corrected before the engine
is started again.
CAUTION
80-00-03
-STARTER
REMOVAL
1. Remove upper and lower cowling.
2. Remove (4) bolts between AIR INTAKE
and fuel Injector pad.
DUCT
3. Remove (2) screws on outer end of air intake duct.
Do not operate starter in excess of 30 seconds
4. Remove bolt at front of air intake duct. Carefully
remove the duct.
without allowing cooling time before re-engaging.
5. Disconnect electrical wiring from starter terminals
and tag wiring for ID.
REV. 10-95
80-00-00
3
SERVICE AND MAINTENANCE
MANUAL
M20J
BLANK
80-10-00
4
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MOONEY AIRCRAFT CORPORATION
M20J
CHAPTER 81
TURBINES
SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M2OJ
SERVICE AND MAINTENANCE MANUAL
CURRENTLY NOT BEING USED
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81-TURBINES
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MOONEY AIRCRAFT CORPORATION
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 91
ELECTRICAL WIRING DIAGRAMS
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY"AIRCRAFT CORPORATION
CHAPTER 91
ELECTRICALWIRING DIAGRAMS
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
SUBJECT ...........
91-EFFECTIVITY ..........
91-CONTENTS ..........
91-00-00 ............
91-00-02 .............
91-00-02 .............
91-00-03 ........
91-20-00 ......
91-20-00 ............
91-20-01 ............
91-20-02 ...........
91-20-03 ...........
91-20-04 ...........
91-20-05 ...........
91-20-06 ...........
91-30-00 ............
....
;
.....
PAGE ..........
DATE
1 ...........
2 ...........
3 ...........
4 ...........
5 ...........
6 ...........
7 ...........
8 ...........
9 thru 34 ..........
35 thru60 .........
61 thru 76..........
77 thru80..........
81 thru94..........
95 thru 110 .........
111
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91- EFFECTIVITY
Page I
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CHAPTER 91
ELECTRICAL WIRING DIAGRAMS
(
TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT
...........
SUBJECT
91-00-00 ........
91-00-01
..........
91-00-02
..........
91-00-03
..........
91-20-00 .........
91-20-01
..........
91-20-02
..........
91-20-03
..........
........
91-20-05
91-20-06
..........
..........
..........
..............
ElectricalSystemNotes........
WIdng IdentificationSystem ......
Abbreviations- EquipmentList ......
ElectricalSystemHardwareCharts ......
24-0001 THRU 24-1685 (14V) ......
24-3000 THRU 24-3153 (28V)
.....
24-3154 THRU 24-3200, 24-3202 THRU 24-3217
•
(28V).
24-1686-14 THRU 24-2999-14 (14V) (ATS) .
24-3201, 24-3218 THRU 24-3410 (28V) .
24.-3411THRU 24-3431 (28V)
.....
61
77
81
95
91-30-00
.........
ElectricalSystemSchematics(ENVELOPES)
111
•
.
,
91-20-04
•
,
General
PAGE
•
,
•
•
•
.
,
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91-CONTENTS
SERVICE AND MAINTENANCE MANUAL
9140-00
M20J
MOONEY AIRCRAFT CORPORATION
- GENERAL
The electrical system hardware lists and related schematics are sequenced in this section by serial number
effectivity.The chapterisdividedintothefollowingsections:
-ElectdcalSystems SchematicNotes
-Widng IdentificationSystem
-ElectdcalSystem Hardware Charts (By Effectivity)
-ElectricalSchematics(By Effectivity)
91-00.01
- ELECTRICAL SYSTEMS
SCHEMATICS NOTES
1. All electrical widng, assemblies,and instalitionsmust be in accord with FAR 43 and AC 43,13-1(*).
2. All splicesmust be "AMP" disconnector equivalent.
3. All circuitbreakem are trip-free.
4. All terminalsare Spec. MS25036 (or equivalentorthey mustbe soldered.)
5. All terminalsmust be preinsulatedor must be insulatedwith =Ampsulation"(or equivalent),
6. Wireswithoutdash numbersare furnishedby the manufacturerand are includedwith the equipment.
7. The symbol=--" indicatesa knifedisconnect.
8, Optionalequipmentmay be installedas required,
9. Wires denotedby .........
symbolsto be twisted counterclockwisewith a minimumofthree (3) wraps per
foot.
10. "F" denotesgroundthroughframe (no wires).
11. All knifedisconnectsplicesto be insulatedwith PVC105 and securelystringtied with airtex no,417 cord.
12. All wiresizes are minimumsizes acceptable.
13. Use 913127 bus bars as necessary for vadousconfigurationchanges and manufacture interconnectingbus
using no. 2170 tubular braid coveredwith PVC105/5/16" (bothAlpha Wire Co.) and terminatedwith AMP terminals
of appropriatesizes.
(* = currentrevisionofAC 43.13-1)
35108
PVC
TermlnaL
105/ 5/16
'.170TubuLar
3P7P18 AmpsuLa ;ion
,3P1P98 Terminal
EXAMPLE - FIGURE 91-1
12-98
91-00-00
Page 3
MOONEY AIRCRAFT CORPORATION
91-00-02
M20J
SERVICE AND MAINTENANCE MANUAL
-WIRING IDENTIFICATION SYSTEM
The Mooney Aimralt Corporation wiring/electricalsystem, originally depicted a typical electrical component
identificationnumber as _
or _.
This 7 or 9 character number is composed of four
functionalgroups, each of which communicatescertain specificinformation.The 5th functionalgroup is the wire
size of the wireconnectingthe variouscomponents.These functionalgmups are as follows:
(Functional .
GroupNo.) ,
(1)
(1)
....
(3)
(4)
(5)
....
Functional ..............
Group
21 - first two numerals (24-0001 thru 24-1685).....
JKL- firstthree letters(24-3000 thin 24-TBA) .....
(=-"is used if not applicableto a model)
14- - firsttwo numerals(24-1686-14 thin 24-2999-14).
PA - first(or second) two letters ........
03 or 102- second set of numerals........
A - singleletter in the series .........
Descriptionof identifiers
- AircraftType (14V) (Not ATS)
- AircraftType (28V)
.
.
-AircraftType (14V) (ATS)
- CircuitFunction
- V_re Sequence
-Configuration
18 - lasttwo numerals in the sedss ........
- Wire Size
(does not appear for components;just wires)
CIRCUIT FUNCTION LI=GI=ND
DV_. NO's 8003301600350
CB DefrosterBlower
LS Lighting- Instrument& Strebe/Navigation
CC Cowl Flap
Lights
CD PC Dump
LT Lighting- Taxi Lights
CF Wing Flaps- Electric
CT Trim - Stabilizer
MA Miscellaneous- AuxiliaryPowerPlug
CV Stand-byVacuum
MB Miscellaneous- Radio Cimuits
MC Miscellaneous- Cigar Lighter
DA Instruments- Ammeter
MD Misceflaneous-Clock Light
DB Instruments- Turn Coordinator
ME
Miscellaneous-ElectricClock
DC Instruments- CylinderHead
MIC Miscellaneous- Microphone
Temperature
MM Miscellaneous- MadderBeacon
DD Instruments- OutsideAir Temperature
MP Miscellaneous- Pmpeller De-ico
DE Instruments- CarburetorAir
Temperature
NF Fuel- Fuel Pump
DF Instruments- Fuel Quantity
NP Fuel- Primer
DG Instruments- Cluster Gauge
DH Instruments- Oil Temperature
PA Power- Aitemator (output& Control)
DJ Instruments- Oil Pressure
PB Power- Battery (Output & Control)
DK Instruments- Fuel Pressure
PG Power- Generator (Output& Control)
DL Instruments- Tachometer
PS Power- Starter (input& Control)
DM Instruments- Hour Meter
DN Instruments- Pressurization
RB Radio Blower
DP Instruments- PitotHeat
DR Instruments- Turbine Inlet Temperature
SPK Speaker
DS Instruments- CompressorDischarge
Temperature
VB Vent Air Blower
DT Instruments- E_haust Gas Temperature
DU Instruments- ManifoldPressure
WA Warning System- Aitemator- Voltage
DV Instruments- Fuel Flow
Warning
DW Instruments- VSI
WB Waming - EngineBoost
WE Wsming System- Gear Position
EG ElectricGear- Gear Contmis
Warning (Electric)
EL
Lighting- Electroluminescence
WF WarningSystem - Fuel Pressure
ELT Emergency LocatorTransmitter
WL WarningSystem- LandingLight
WM WarningSystem - Gear Position
FON Phones
Warning (Manual)
WN WarningSystem- Pressurization
JM Ignition- Magneto
VVS Warning System- Stall Waming
LB Lighting- RotatingBeacon
WT WarningSystem- Press-to-Test
. (AnticollisionLight)
WV Waming System- Vacuum Warning
LC Lighting- Cabin Lights
WW WarningSystem- Aitemate Air
LL Lighting- LandingLights
WD WarningSystem- StarterPower
LN Lighting- NavigationLights
LP Lighting- Instrument& Placard Lights
LR Lighting- RecognitionLights
91.00-02
Page 4
12-98
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
dT_e.e.Mooney
.Ai.'rc_a..lt
Co.q_orationwidng/ele_stdcal
equipmentidentification
system used in conent productionaircraft
letes me MOael P_umeerannotation, i ne purpose of this is to standardizethe identificationof a system
function/coroponent
for all model of aircraft.The functionalgroups are basicallythe same as earlier identification
numbers.These newfunctionalqroupsapplyto schematicdrawinq800304.The newfunctional,qroupsareas follows:
04 ....
A ....
I 20
CR..... .
.
--_.
--
.
.
Firstset of numerals
.
Singleletter in series
.
numeralsin series
. Lasttwo
Firsttwo/threeleters
----.
--
.
.
.
.
I
Wire Sequence
Configuration
. CircuitFunction
Wire size
|
CODE/COMPONENT or SYSTEM (CIRCUIT FUNCTION) - 800304 ( ) SCHEMATIC DRAWING
ACT/SWITCH ACTUATOR
DL/ELECTRIC TACHOMETER
MA/AUXILIARYPOV_ER
BS/RELAY BASE
DM/HOUR METER
ME/AVIONICS MASTER
BUS/BUSS BARS
DPIPITOT HEAT
MC/DIGAR LIGHTER
C/CAPACITORS
DR/TIT
ME/CLOCK
CB/DEFROSTER BLOWER
DT/FUEL FLOW
MP/PROPELLER DE-ICE
CC/COWL FLAPS
CL/CLAMPS
CM/CURRENT MONITOR
DG/LANDING GEAR, ELEC.
ELT/ELT
F/FUSES
NF/BOOST PUMP
PAJALTERNATORPOWER
PB/BATTERY POWER
CR/RUDDER TRIM
CT/STABILIZER TRIM
FHIFUSEHOLDER
FON/PHONE
PL/PLUGS, ELECTRICAL
PSISTART POWER
CV/STANDBY VACUUM
D/DIODES
JMIIGNITION, MAGNETO
L/LIGHT BULBS
R/RESISTORS
RB/RADIO BLOWER
DAJAMMETER
DB/TURN COORDINATOR
LB/BEACON
LENS/ANNUNCIATOR LENS
RC/RECEPTACLES, ELECTRICAL
RL/RELAYS
DC/DHT
LH/LAMP HOLDER
SP/SPEEDBRAKE
DD/OAT
LL/LANDING LIGHTS
SW/SWlTCHES
DC-.-dENGINE
INSTRUMENTS
DH/OIL TEMPERATURE
LP/PANEL LIGHTS
LR/RECOGNITION LIGHTS
VR/VARISTOR
WS/STALLWARNING
DJ/OIL PRESSURE
DK/FUEL PRESSURE
LS/STROBE LIGHTS
LT/TAXI LIGHTS
WT/STANNUNCIATOR WARNING
CODE/COMPONENT or SYSTEM (CIRCUIT FUNCTION) - 800383 ( ) SCHEMATIC DRAWING
AC
AH
AT
AV
AIR CONDITIONER
ARTIFICIAL HORIZON
ACTUATOR, SWITCH
AVIONICS
BR
BS
BU
CIRCUIT BREAKERS
RELAY BASE
BUS BARS
CA
CB
CC
CD
CF
CL
CR
CT
CV
CAPACITORS
DEFROSTER BLOWER
COWL FLAPS
PC DUMP
WING FLAPS
CLAMPS
RUDDER TRIM
ELEVATOR TRIM
STAND-BY VACUUM
DA
DB
DC
INSTRUMENTS - AMMETER
INSTRUMENTS - TURN COORDINATOR
INSTRUMENTS - CYLINDER HEAD
TEMPERATURE
DD
INSTRUMENTS - OUTSIDE AIR
TEMPERATURE
DE
INSTRUMENTS - CARBURETOR AIR
TEMPERATURE
DF
INSTRUMENTS - FUEL QUANTITY
DG
INSTRUMENTS - ENGINE
DH
INSTRUMENTS - OIL TEMPERATURE
DI
DIODES
DJ
INSTRUMENTS - OIL PRESSURE
DK
INSTRUMENTS - FUEL PRESSURE
DL
INSTRUMENTS - TACHOMETER, ELECTRIC
DM
INSTRUMENTS - HOUR METER
DN
INSTRUMENTS - PRESSURIZATION
DP
INSTRUMENTS - PITOT HEAT
12-98
91-00-02
Page 5
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
CODE/COMPONENT or SYSTEM (CIRCUIT FUNCTION) - 800383 ( ) SCHEMATIC DRAWING (con't.)
INSTRUMENTS - TURBINE INLET
MO
PROP'OVERSPEED
TEMPERATURE
MP
PROP DE-ICE
DS
INSTRUMENTS - COMPRESSOR
MS
MISCELLANEOUS, RADIO-SPEAKER
DISCHARGE TEMPERATURE
MW
MISCELLANEOUS, RADIO-WARNING
DT
INSTRUMENTS - EXHAUST GAS
TEMPERATURE
NE
FURL ENRICHMENT
DU
iNSTRUMENTS - MANIFOLD PRESSURE
NF
FUEL PUMP
DV
INSTRUMENTS - FUEL FLOW
NP
FUEL PRIMER
DW
INSTRUMENTS - ENGINE VACUUM
NS
FUEL COLD START
DR
EG
EL
ET
GEAR, ELECTRIC
ELECTROLUMINESCENCE
EMERGENCY LOCATOR BEACON
PA
PB
PG
FA
FH
FN
FU
FW
ALT-EMER (FRENCH)
FUSE HOLDERS
PHONES
FUSES
ALT-EMER FIELD (FRENCH)
PL
PS
POWER, ALTERNATOR
POWER, BATTERY
POWER, GENERATIOR (OUTPUT &
CONTROL)
PLUGS
POWER, START
GD
GROUND
RB
RC
RL
RS
BLOWER, RADIO
RECEPTACLES
RELAYS
RESISTORS
HS
HORIZONTAL SITUATION INDICATOR
JE
JM
JV
IGNITION, ELECTONIC
IGNITION, MAGNETO
IGNITION, VIKBRATOR
SA
SB
SP
SW
STAND-BY ALTERNATOR
SPEEDBRAKE
SPEAKER
SWITCHES
LA
LB
LC
LE
LG
LH
LI
LL
LN
LP
LR
LS
LT
LIGHT BULBS
BEACON, ROTATING
LIGHT, CABIN
LENS, ANNUNCIATOR
LIGHTS, LOGO
LAMP HOLDER
LIGHT, ICE
LIGHT, LANDING
LIGHTS, NAVIGATION
LIGHTS, PANEL
LIGHTS, RECOGNITION
LIGHTS, STROBE
LIGHTS, TAXI
VB
VC
VR
VENT, AIR BLOWER
VOLTAGE CONVERTER
VARISTOR
WA
WB
VVC
WD
WE
WF
WG
WH
WJ
WK
MA
MB
MC
ME
MH
MJ
MK
MM
AUXILIARY POWER
RADIO, MASTER
CIGAR LIGHTER
CLOCK, ELECTRIC
MISCELLANEOUS, ANTI-ICE
MISCELLANEOUS, JUNCTION BOX
MICROPHONE
MISCELLANEOUS, MARKER BEACON
WM
WN
WP
WS
WT
WV
VWV
WARNING, ALTERNATOR
WARNING BOOST PUMP
WARNING PROP DE-ICE
WARNING POWER START
WARNING ELECTRIC GEAR
WARNING FUEL QUANTITY
WARNING TACHOMETER
WARNING CHIP DETECTOR
WARNING TRIM FAIL
WARNING FUEL PRESSURE
WARNING CANOPY LOCK
WARNING MASTER
WARNING PRESSURIZATION
WARNING PITOT HEAT
WARNING STALL
WARNING, ANNUNCITOR
WARNING, VACUUM
WARNING, ALTERNATE AIR
YD
YAW DAMPER
91-004)3
- ABBREVIATIONS - EQUIPMENT
LIST
The abbreviationsto the electdcal system hardware charts are necessary due to space limitationsin the fields of
the computer.
Aimpeed - A/S
Placard- Plcd
Altemate - Altn
Radio - Rad
Circuit Breaker- Ckt. Bkr. or C/E
Receptacle- Recpt
Console- Cnsl
Regulator- Regltr
Control- Cntd
Remote - Rein
Coordinator- Coordtr
Resistor- Res
Cylinder- Cyl
Rheostat- Rheo
Down - Dn
Right- R
91-00-03
Page 6
12-98
SERVICEAND MAINTENANCE MANUAL
M20J
MOONEYAIRCRAFTCORPORATION
ABBREVIATIONS. EQUIPMENT UST (con't.)
91-20-00
Electric- Elsc
Safety- Sffy
Flight- Fit
Selector- Sel
Glareshield- Glmhld
Supply- Sply
Landing- Ldg
Switch- Sw
Lelt - L
Transducer- XDCR
Lights- Lts
Transmitter- XMTR
Panel - Pnl
Transistor- XSTR
Pilot- Pit
Warning - Wrn
- ELECTRICAL SYSTEM HARDWARE CHART
.
Refer to the Electrical Schematic (located in the envelopes at the back of this manual) that depicts the Serial
Number configurationof the aimrett beingserviced.The SIN's vs. Schemafic's areshown below:
A/C SERIALNUMBER.
.
DRAWING/SCHEMATICNUMBER
(14 VOLT AIRCRAFT)
24-0001 thru 24-0237, except 24-0084................
24-0238 thru 24-0377 .....
24-0378 thru 24-0757, includes24-0084 .............
24-0758 thru 24-0900 ..................
24-0901 thru24-0942 .......
-..........
240943 thru 24--1037 ....................
24-1038 thru24-1213 .........
24-1214.thru24-1417 ...............
24-1418 thru 24-1499 ..................
24-1500 thru24-1528 ..............
24-1529 thru24-1685 .....................
SCl-800269L-3
SCI-800269L-3A
800330 E1
800330 E2
800330 E3
800330 E4
800330 E5
800330 E6
800330 E7
800330 E8
800330 E9
24-1686-14thru24-2999-14(ATS).
.,- 8.VO;.rAIRCRAF.r
-.
)
24-3000 thru24-3078
24-3079 thru24-3153 .....
24-3154 thru24-3200, 24-3202 thru 24-3217 .
800263
800350
800350
800263
24-3201, 24-3218 thru 24-3270 .............
...............
800304 J1 (SHT1) (REV. F)
(SHT 2) (REV. H)
24-3271 thru24-3350
............
.................
24-3351 thru 24.,3,373
.......................
24-3374 thru24-3377
........................
J2
J1
J,?.
J1
......
. . .............
800304 J2 (REV.W)
(SHEET 1 of 2; 2 of 2)
800304 J3 (FIEV.W)
(SHEET 1 of 1)
800304 J4 (REV W)
(SHEET 1 of 1)
24-3378 thru 24-3363 ...................
..........................
800304 J5 (REV.Y)
(SHEET 1 of 1)
24-3384
thru 24-3392 ...................
.........................
800304
J6 (REV,Z)
(SHEET
1 of 1)
24-3393 thru 24-3404 .................
.....................
800304 J7 (REV,Z)
(SHEET 1 of 1)
24-3405 thru 24-3410 .............
.....................
24-3411 thru 24-3420.
...................
800304 J8 (REV.AA)
(SHEET 1 of 1)
24-3421 thru 24-3431 ....................
........................
800383 J2 (REV.H)
(SHEET 1 of 1)
800383 J1 (REV.G)
(SHEET 1 of 1)
CAUTION
These schematics address different serial numbered aircraft. Make sure the applicable schematic Is
being used for the alrcralt being serviced.
12-98
91-20-00
Page 7
MOONE'{ AIRCRAFTCORPORATION
M20J
SERVICE AND MAINTENANCEMANUAL
The Vendor and Part Number will be depictedwhere the applicableelectricalequipment identifieris shown on the
followinghardwarecharts: Order replacementor repair part numbersfor electricalcomponentsfrom the following
electricalsystemhardwarechartsthat are applicableto the aimreftmodel and S/N being worked on.
91-20-01
- ELECTRICAL SYSTEM HARDWARE CHART - 24-0001 thru 24-1685 (14 VOLT),
DRAWING NUMBER SCI - 800269L-3,-3A & 800680
91-20-02
- ELECTRICAL SYSTEM HARDWARE CHART - 24-3000 thru 24-3153 (28 VOLT),
DRAWING NUMBER - 800350
91-20-03
- ELECTRICAL SYSTEM HARDWARE CHART - 24-3154 thru 24-3200, 24-3202 thru 24-3217
VOL
D(_8
.
.
AWI_i_'NUMBER
800263
(E),
24
1688-14
thru
24-2999-14 common components,
( 28V & 14 V) (See 91 20-04 for 14 Volt
peculiar
components).
91.2004
- ELECTRICAL SYSTEM HARDWARE CHART - 24-1686-14 thru 24-2999-14 (ATS ONLY)
(_4 VOLT SYSTEMS),
AWING NUMBER - 800268 (E)
91-20.05
-ELECTRICAL EQUIPMENT HARDWARE CHART. S/N 24-3201, 24-3218 THRU 24-3270,
DRAWING NO - 800304 - (JI) (REV. F Slit 1/REV. H SliT 2)
-ELECTRICAL EQUIPMENT HARDWARE CHART. S/N 24-3271 THRU 24-3350
DRAWING NO - 800304 - (J2) (REV. W) (2 sheets)
-ELECTRICAL EQUIPMENT HARDWARE CHART - S/N 24-3351 THRU 24-3373
DRAWING NO - 800304 - (J3) (REV. W) (1 sheet)
.ELECTRICAL EQUIPMENT HARDWARE CHART - S/N 24-3374 thru 24-3377
DRAWING NO - 800304 - (J4) (REV. W) (1 sheet)
-ELECTRICAL EQUIPMENT HARDWARE CHART - S/N 24-3378 thru 24-3383
DRAWING NO - 800304 - (J5) (REV. Y) (1 sheet)
-ELECTRICAL EQUIPMENT HARDWARE CHART - S/N 24-3384 thru 24-3392
DRAWING NO - 800304 - (J6) (REV. Z) (1 sheet)
-ELECTRICAL EQUIPMENT HARDWARE CHART - S/N 24-3393 thru 24-3404
DRAWING NO - 800304 - (JT) (REV. Z) (1 sheet)
-ELECTRICAL EQUIPMENT HARDWARE CHART - S/N 24-3405 thru 24-3410
DRAWING NO - 800304 - (Ja) (REV. AA) (1 sheet)
91-20.05
91-20-05
91-20-05
91-20-05
91-20-05
91-20-05
91-20-05
91-20-08
91-20-08
91-20-00
Page 8
-ELECTRICAL EQUIPMENT HARDWARE CHART - S/N 24-3411 thru 24-3420
DRAWING NO - 800383 - (J1) (REV. G) (1 sheet)
-ELECTRICAL EQUIPMENT HARDWARE CHART - S/N 24-3421 thru 24-3431
DRAWING NO - 800383 - (J2) (REV. H) (1 sheet)
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
9%20-01
- ELECTRICAL SYSTEM HARDWARE CHART - 14 VOLT
S/N's 24-0001 THRU 24-1685, MOONEY DRAWING NO.'S SCI-800269L-3, -3A & 800330 (CP)
CODE
DESCRIPTION
VENDOR
PART NO.
21
21
21
21
21
CB101A
CD01A
CD02A
CD02B
CD03A
21
21
21
21
CF01B
CF02A
CFO3A
CF04A
C/B DEFROSTER BLOWER
SOLENOID-PC DUMP
SW-PILOTS DUMP
SW-PILOTS DUMP
SW-CO-PILOTS DUMP
SW-P.C. ON-OFF (ALT)
C/B FLAP ACT
RELAY-LEFT
RELAY-RT
ACTUATOR. FLAP
21
-21
CFO5A
21
-21
CF07A
21
21
CF09A
CF09B
SWITCH, LIMIT, DOWN
ACTUATOR
SWITCH, LIMIT, UP
ACTUATOR
SWITCH, LIMIT, DOWN
ACTUATOR
SWITCH, LIMIT, UP
ACTUATOR
SWITCH, CONTROL
SWITCH. CONTROL, FLAP
KLIXON
BRI'I-rlAN
MICRO
C-H
MICRO
ALCO
MERIDEN or EQUIV.
MAGNECRAFT
MAGNECRAFT
COMM. NC PROD
MOONEY
MICRO
MICRO
MICRO
MICRO
MICRO
MICRO
MICRO
MICRO
MICRO
C-H
7277-2-2
4085
111SM1-T
SA31SDT12-2
111SM1-T
MST215-N
AHW4-15
W97CSX-1
W97CSX-1
D14500-36
(750105-501)
V3-1
JV-5
V3-1
JV-5
V3-1
JV-5
V3-1
JV-5
2TL75-10
6906K3149
21
21
21
CTO1A
CT01B
CT01D
C/S, ELECTRIC TRIM
C/S, ELECTRIC TRIM
C/B, ELECTRIC TRIM
MOONEY
MOONEY
MOONEY
930023-009
930023-109
930023-209
21
21
21
21
21
DA01A
DA01B
DA01C
DA01D
DAO2A
21
DA02B
21
DA03A
21
DAO3B
21
DA04A
SHUNT
SHUNT
SHUNT
SHUNT
FUSE
RETAINER
FUSE
RETAINER
FUSE
RETAINER
FUSE
RETAINER
AMMETER
BULB
EMPRO or EQUIV.
STEWART-WARNER
EMPR0
EMPRO
UI-rEL
UI-EEL
McGRAW-EDISON
McGRAW-EDISON
LITTEL
LITTEL
McGRAW-EDISON
McGRAW-EDISON
MOONEY
ROCHESTER
MLA-60-50
SW-813489
MLA-60-100
MLA-70-100
312010
155020
FM01-5A
FHN42W
311010
155202
FM01-5A
FHN42W
640281-509
0153500003
21
21
21
DB01A
DB01B
DBO2A
21
21
DB02B
DB03A
C/B,TURN COORD
C/B TURN COORD
TURN CO-ORDINATOR
TURN CO-ORDINATOR
TURN CO-ORDINATOR
PLUG, TURN COORD
CLAMP
MERIDAN OR EQUIV
KLIXON
BRITTIAN
AEROSONIC (ALT)
AEROSONIC
AHW4-2
7277-2-5
604-200-200
ANS50M
ANS50ML
MS3106A-10SL-3S
MS3057-4A or-4B
CF06A
CF08A
12-98
NOTES
23/24
23/24
23/24
91-20-01
9
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
--L
DB50A
T/C
UNITED INST
9551B CODE N.541
21
21
DC01A
DC01B
PROBE, CYL HD TEMP
PROBE, CHT
21
DC01C
PROBE, GriT
STEWART-WARNER
ROCHESTER
MOONEY
MOONEY
SW-333-B
8080-00014
(880010-501)
880010-503
21
21
21
DD01A
DD01B
DDO1C
GAUGE, OUTSIDE AIR TEMP
GAUGE, OAT
CAUGE, OAT/EGT
21
21
DD01E
DD01F
GAUGE, OAT/EGT(UGHTED)
GAUGE, OAT (UGHTED)
GARWlN
]NSTR.& FLT RES.
B&D INSTRUMENT
MOONEY
MOONEY
MOONEY
22-295
IFR-11A
C203-005
880010-501
880001-505
880023-505
21
DD02A
21
DD02C
21
DD02D
21
21
21
DD03A
DD03B
DD03C
PLUG -GAUGE
CLAMP
PLUG,OAT/EGT
CLAMP
PLUG,OAT
CLAMP
PROBE, OAT
PROBE, OAT
PROBE, OAT
21
DD04A
C/B, OAT/EGT
21
DE01A
GAUGE, CARB AIR TEMP
21 .
DE02A
21
DE02B
21
DE03A
PLUG, GAUGE
CLAMP
PLUG, GAUGE
CLAMP
PROBE, CARB AIR TEMP
RICHTER AERO
660014-005
22-995-04
MS3106A-14S-1S
MS3057-6B
MS3106B-14S12S
MS8057-68
B-5
21
21
21
21
21
21
DF01A
DF01B
DF02A
DF03A
DF03B
DF04A
XMTR, FUEL QIY, LT, IB
XMTR, FUEL QTY, LT, IS
XMTR, FUEL Q'I'Y, LT, OB
XMTR, FUEL QTY, RT, IB
XMTR, FUEL QTY, RT, IB
XMTR, FUEL QTY', RT, OB
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
6i0242-001
610242-003
610243-003
610242-001
610242-003
610243-001
21
21
21
DG01A
DG01B
DG02A
C/B, CLUSTER GAUGE
C/B, CLUSTER GAUGE
GAUGE, CLUSTER
FUEL QTY', LH
FUEL QFY, RH
AMMETER
OIL PRESS
OIL TEMP
CYL HEAD TEMP
MERIDEN
KLIXON
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
AHW4-2
7277-2-2
640281-503
640281-105
640281-107
640281-115
640281-117
640281-149
640261-111
91-20-01
10
AMP
AMP
WESTBERG
B&D INSTR
MOONEY
KLIXON
MOONEY
GARWIN
12-98
MS3106A-14S-2S
MS3057-6B
205838-1
206062-1
MS3106A-14S-2S
MS3057-6A
MS2803403
399W
0203-100
880004-501
727%2-2
NOTES
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
21
DG02G
21
DG02G
i
(ALT)
21
DG02H
(ALT)
i
21
DG02J
21
DG02K
21
21
DH01A
DH01B
--
DESCRIPTION
VENDOR
PART NO.
GAUGE, CLUSTER
FUEL QTY, LH
FUEL QTY, RH
FUEL PRESS
OIL PRESS
OIL TEMP
CYL HEAD TEMP
GAUGE, CLUSTER
FUEL QTY, LH
FUEL QTY', RH
FUEL PRESS
OIL PRESS
OIL TEMP
OIL TEMP (ALT)
CYL HEAD TEMP
CYL HEAD TEMP (ALT)
GAUGE, CLUSTER
FUEL QTY, LH
FUEL Q'I-Y, RH
AMMETER
OIL PRESS
OIL TEMP
CYL HEAD TEMP
GAUGE, CLUSTER
FUEL QTY, LH
FUEL QTY, RH
AMMETER
OIL PRESS
OIL TEMP
OIL TEMP (ALT)
CYL HEAD TEMP
CYL HEAD TEMP (ALT)
GAUGE, CLUSTER
FUEL QTY, LH
FUEL QTY, RH
FUEL PRESS
OIL PRESS
OIL TEMP
CYL HEAD TEMP
GAUGE, CLUSTER
FUEL Q'P(, LH
FUEL QTY, RH
AMMETER
OIL PRESS
OIL TEMP
CYL HEAD TEMP
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
640281-507
640281-105
640281-107
640281-119
640281-121
640281-149
640281-511
640281-511
640281-125
640281-127
640281-131
640281-129
640281-133
640281-155
640281-135
640281-157
640281-513
840281-147
840281-145
640281-137
640281-141
640281-139
640281-143
640281-515
640281-153
640281-151
640281-137
640281-141
640281-139
640281-159
640281-143
640281-161
640281-519
640281-163
640281-165
640281-171
640281-133
640281-155
640281-135
640281-521
640281-153
640281-151
640281-137
640281-169
640281-139
40281-143
PROSE, OIL TEMP
PROBE, OIL TEMP
STEWART-WARNER
ROCHESTER
MOONEY
362-CR
3080-37
880099-501
AN909-10
MS35769-11
ROCHESTER
MOONEY
MOONEY
3080-37
880098-501
889046-501
MS3106A10SL-3S
MS3057-4NB
WASHER
(ALl-)
21
DJ01A
. XDUCR, OIL PRESS
21
21
DJ01B
DJ02A
XDCR, OIL PRESS
PLUG, XDCR, OIL PRESS
CLAMP
12-98
NOTES
33
32
34
34
91.20,01
11
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO,
21
21
21
DJ175A
DJ177A
DJ178A
XDCER, OIL PRESS
AMPLIFIER, OIL PRESS
PLUG, OIL PRESS, 4 PIN
CLAMP
DRUCK
IAI
AMP
AMP
PDCR821-0662-100
950D0311-002
206060-1
206062-1
21
DJ179A
21
-21
DJ180A
RECPT, OIL PRESS, 4 PIN
CLAMP
PLUG, 4 PIN
CLAMP
RECPT, 4 PIN
CLAMP
AMP
AMP
AMP
AMP
AMP
AMP
206153-1
206062-1
206060-1
206082-1
206153-1
206062-1
21
DK01A
21
21
21
21
21
DK01C/D
DK01D
DK01E
DK01F
DK02B
21
21
21
21
21
21
21
21
21
DK02D/E
DK02F
DK03A
DK03B
DK03C/D
DK03E/F
DK04A
DK05A
DK06A
21
21
21
DK175A
DK176A
DK177A
21
DK178A
21
DK179A
21
DK180A
21
21
21
21
21
21
21
-21
21
21
DL01A
DL01B
DL01C
DL01D
DL01E
DL01F
DL02A
21
91-20-01
12
DJ181A
XDUCR, FUEL PRESS
ROCHESTER
MOONEY
XDUCR, F/F(OPr)
MOONEY
XDUCR, FUEL PRESS
MOONEY
XDUCR, FF
MOONEY
XDUCR, FUEL FLOW
MOONEY
GAUGE, FF/MP
MOONEY
GAUGE, FF/MP, LIGHTED (OPT)MOONEY
GAUGE, FF (OPT)
MOONEY
GAUGE, (GALS/HR)
MOONEY
PLUG, FF/MP GAUGE
BENDIX
PLUG, FF
BENDIX
PLUG, FF
]l-r CANNON
PLUG, FF (OPT)
CANNON
C/B, FF
KLIXON
SWITCH, MEMORY, FF (OPT) ALCO
PLUG, FF, XDCR
CLAMP
XDUCR, FUEL PRESS
DRUCK
AMPUFIER, FUEL PRESS
IAI
PLUG, 4 PIN
AMP
CLAMP
AMP
REOPT, 4 PIN
AMP
CLAMP
AMP
PLUG, 4 PIN
AMP
CLAM P
AM P
RECPT, 4 PIN
AMP
CLAMP
AMP
3060-17
880007-501
880030-501
880045-501
880030-503
880030-505
880031-501
880031-503
880034-501
880034-513
PT06A-10-98S(SR)
PT06A-15-15S(SR)
DE-gS
DE-9S
7277-2-2
MST215N
MS3106A10SL-3S
MS30507-4A
PDCR821-0662-30
950D0311-031
206060-1
206062-1
260153-1
206062-1
206060-1
206062-1
260153-1
206062-1
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
DL03A
DL04A
DL05A
TACH, ELEC
TACH, ELEC
TACH, ELEC
TACH, ELEC
TACH, ELEC
TACH, ELEC, (LIGHTED)
PLUG, TACH
CLAMP
RESISTOR, L
RESISTOR, L
CABLE ASSY
OHMITE
OHMITE
MOONEY
880002-501
880039-503
880002-503
880039-501
880039-507
880039-505
MS3106A-14S-5S
MS3057-6A
OL1535
O!_1535
880003-501
DM01NB
' HOUR METER
MOONEY
880035-501
12-98
NOTES
25
3
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
C/B, PITOT HEAT
C/B, PITOT HEAT
C/B, PITOT HEAT
HEATED PITOT
PITOT, HEATED
(ALl)
PLUG, PITOT HEAT
SOCKETS
MOONEY
MOONEY
MOONEY
AEL or EQUIV
AERO INST
930023-005
930023-105
930023-205
425936
PH502-24
AN5812-1
AN3115-1
AN3116-1
21
21
21
21
21
DP01A
DP01B
DP01D
DPO2A
DP02B
21
DP03S
21
21
21
21
21
DR01A
DR01B
DR02A
DR03A
DR04A
C/B, TIT/CDT
GAUGE, TIT/CDT, LIGHTED
PLUG, TIT/CDT INDICATOR
PROBE, TIT
C/B, TIT/CDT
KUXON
MOONEY
AMP
MOONEY
KLIXON
7277-2-2
880000-503
205838-1
880005-501
7277-2-2
21
DS01A
PROBE, CDT
MOONEY
880006-501
21
DTOlA
PROBE, EGT
B&O INSTR
MOONEY
0204-100
880005-501
21
21
21
21
21
21
EG01A
EG01B
EG01C
EG0?-A
EG02B
EG03A
21
21
21
21
21
21
21
EG04A
EG04B
EG04C
EG04D
EG04E
EG04F
EG04G
C/B, ELEC. GEAR
C/B, ELEC. GEAR
C/B, ELEC. GEAR CONTROL
SWITCH, CONTROL
SWITCH, GEAR UP/DN
SWITCH, LIMIT
ACTUATOR
ACTUATOR, GEAR, ELEC
ACTUATOR, GEAR, ELEC
ACUTATOR, GEAR, ELEC
ACUTATOR, GEAR, ELEC
ACUTATOR, GEAR, ELEC
ACUTATOR, GEAR, ELEC
ACUTATOR, GEAR, ELEC
21
21
21
21
21
EG05A
EG05C
EG05D
EG05E
EG05F
21
EG06A
21
21
21
21
21
21
21
21
21
21
21
EGO6B
EG06C
EG06D
EG07A
EGO8C
EGO8D
EGO8E
EGOBF
EG09A
EG09B
EG10A
MERIDEN or EQUIV
KLIXON
KUXON
MICRO
....
C-H
MICRO
MICRO
I'l-r
DUKES
DUKES
ITr
ITT
DUKES
AVIONICS PROD
MOONEY
RELAY, GEAR
RBM
RELAY, GEAR UP
MAGNECRAFT
RELAY, GEAR UP
C-H
RELAY, GEAR UP
RBM
RELAY, GEAR UP
C-H
COLE-HERSEE
SQUAT SWITCH
MICRO
MOONEY
SWITCH SAFETY, AIRSPEED WHITMAN-GENERAL
SWITCH SAFETY, AIRSPEED MOONEY
SWITCH SAFETY, AIRSPEED MOONEY
SWITCE DOWN UMIT
MICRO
RELAY GEAR DOWN
MAGNECRAFT
RELAY GEAR DOWN
C-H
RELAY GEAR DOWN
RBM
RELA_ GEAR DOWN
C.,-H
C/B, GEAR ACT
MECHANICAL PROD
. C/B, GEAR ACT
KLIXON
SWITCH, GEAR OVERIDE
C-H
LAMP
GE
: 12-98
AHW4-15
7277-2-15
7277-2-5
2TL149-3D
8906K2875
DT-2R-A7
MCD-2711
LAllC21101
1057-00-1
4196-00-1D
LAllC2115
LAllC2114
1057-00-5E
102000-1
560254-501
70-111221
W97CSX-1
6041H50A
70311221
6041H53
24401
1CH1-6
800335-501
SK75-1N-K3L
880013-503
880013-505
1CH1-6
W97CSX-1
6041H105A
70-311221
6041H105A
700-01-25
7277-2-15
SBIDDX492-2
388
NOTES
26
3
1
1
22
22
5
5
5
22
91-20-01
13
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
DIODE, GEAR UP BELAY
DIODE,GEAR DN RELAY
TRANSISTOR
FUSE
HOLDER
RESISTOR
RHEOSTAT/SW
PLACARD, CB
PLACARD, FUEL SEL
PLACARD, ANNUN
PLACARD, CK. LIST
SARKES TARZlAN
SARKES TARZlAN
RCA
McGRAW-EDISON
1=4
F4
2N2016
FM01-SA
FHN42W
4599
JS1N055P251MA
150082-009
150082-011
150082-015
150082-013
21
21
21
21
EG11A
EG12A
EL01A
EL02A
21
21
21
21
21
21
EL03A
ELO4A
ELOBA
EL07A
ELOBA
EL09A
21
ELT1A
21
21
ELT1B
ELT2A
21
EW01B
21
-21
21
21
21
21
21
21
21
21
21
21
JM01A
21
21
21
21
LB01A
LB01B
LB01D
LB02A
C/B, ROTATING BEACON
MOONEY
C/B, ROTATING BCN(SPARES) MOONEY
C/B, ROTATING BEACON
MOONEY
LIGHT, ROTATING BEACON
WHELEN
ADAPTER
WHELEN
930023-003
980023-103
980023-203
WRML-12
WRM-65
21
LC01A
21
LC02A
21
LC02B
21
21
21
21
21
21
LC03A
LC03B
LC03C
LC03D
LC03E
LC04A
LITTEL FUSE
LI-CFELFUSE
LUMINATOR
GE
GRIMES
GE
C-H
CABLING
CABLING
CABLING
CABLING
OHMITE
155020/155120
318005
20145
1003
B-3550
89
8144(BK-09)
TILC64-1S-WH-FN
TILC64-1S-WH-FN
TILC84-1S-WH-FN
TILC64-1S-WH-FN
4561
21
21
LC04B/C
LC07A
FUSEHOLDER, CLOCK, 5AMP
FUSE,(5A-SAG-SLO-BLO)
LIGHT, CABIN, OVERHEAD
BULB
UGHT, CABIN, OVERHEAD
BULB
SWITCH, CABIN LIGHT
SWITCH, CABIN LIGHT, FWD
SWITCH, CABIN LIGHT, REAR
SWITCH, CABIN LIGHT, FWD
SWITCH, CABIN LIGHT, REAR
RESISTOR, DIM, CABIN LT
(10 OHM 5W)
. RESISTOR, DIM., CABIN LT
SWITCH, MAP LT, PILOTS
DALE
C-H
RH-10-5 OHM
SA25SCT12-3
JM01B
JM02A
JM02B
JM02C
JM02D
JM02E
JM03A
JM03C
JM03D
JM03E
JV01A
OHMITE
ALLEN/BRADLEY
MOONEY
MOONEY
MOONEY
MOONEY
ELT
(ALT)
ELT, TRANSMITFER (OPT)
SWITCH, REMOTE ELT
(ALT)
C/B, GEAR WARNING
DORNE & MARGOLIN
DOBNE & MARGOUN
DORNE & MARGOUN
C&K
KLIXON
DM-ELT-6
DM-ELT -6M
DM-ELT-8
DM-U65-1
7101K
7277-2-2
SWITCH, MAGNETO
PLACARD
SWITCH, MAGNETO
MAGNETO LEFT
MAGNETO DUAL
MAGNETO LEFT
MAGNETO LEFT
MAGNETO LEFT
MAGNETO RIGHT
MAGNETO RIGHT
MAGNETO RIGHT
MAGNETO, RIGHT
STARTING VIBRATOR
BENDIX-SCINTILLA
BENDIX- SCINTILLA
BENDIX-SCINTILLA
BENDIX-SCINTILLA
BENDIX-SCINTILLA
BENDIX
_
SLICK
SUCK
BENDIX
BENDIX
SUCK
SUCK
BENDIX-SCINTILLA
10-857290-17
10-187-468
10-357210-91
S41_N20O
D4LN2021
10-79020-18
6214
6224
$4LN204
10-79020-18
6214
6224
10-176487-121
CAP
FACE NUT
91-20-01
14
SW53AA2
15-1049-3
12-98
NOTES
28
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
VENDOR
PART NO.
LIGHT, MAP, PILOTS
BUlB
SW, MAP LT, CO-PILOT
CAP
FACE NUT
UGHT, MAP, CO-PILOT
BUlB
UGHT, CABIN, (F1-R)
LAMP
LIGHT, CABIN, (F2-R)
LAMP
LIGHT, CABIN, (F1-L)
LAMP
LIGHT, CABIN, (F2-L)
LAMP
SLOAN
GE
C-H
SLOAN
GE
H.H. SMITH
GE
H.H. SMITH
GE
H.H. SMITH
GE
H.H. SMITH
GE
855-$1-0-PE
330
SA25SCT12-3
SW53AA2
15-1049-3
855-$1-0-PE
330
1930
1816
1930
t816
1930
1816
1930
=1816
LIGHT, CABIN, (R1-R)
LAMP
LIGHT, CABIN, (R2-R)
LAMP
LIGHT, CABIN, (R1-L)
LAMP
LIGHT, CABIN, (R2-L)
LAMP
H.H. SMITH
GE
H.H. SMITH
GE
H.H. SMITH
GE
H.H. SMITH
GE
1930
1816
1930
1816
1930
1816
1930
1816
21
LC08A
21
LCO9A
21
LC10A
21
LC11A
21
LC12.A
21
LC13A
21
LC14.A
21
LC15A
21
LC16A
21
LC17A
21
LC18A
21
21
21
21
21
21
21
LL01A
LL01B
LL01C/D
LL02A
LL03A
LL03B/C
LL04A
C/B, LDG LT
C/B, LDG LT
C/B, LDG LT
RELAY, LDG LT
LIGHT, LDG (BULB)
LIGHT, LDG (BULB)
SWITCH, LDG LT
CAP
FACE NUT
MERIDEN
MOONEY
MOONEY
MAGNECFIAFT
GE
GE
C-H
AHW4-20
930023-15
930023-115/-215
WB9CQX-2
4522
4509
; SA25SCT12-3
SW53AA2
15-1049-3
21
21
21
LN01A
LN01B/D
LN02A
C/B, NAV LIGHTS
C/B, POSITION LTS
LIGHT, POSITION (RED)
BUlB, POSITION (14V)
MOONEY
MOONEY
GRIMES
930023-001
930023-101/-201
AI285-R-12
A7512-12
800022-501
W1290-14
W1285-PR
21
21
21
21
=
DESCRIPTION
LN02B
LN03A
I_NO3B
LN04A
BUlB, POS TION(14V)
UGHT, POSITION,(14V) (RED)
LIGHT, POSITION,
TAIL _NHITE)
BULB, 14V, TAIL LT.
BULB, 14V, TAIL LT.
LIGHT, POS, TAIL,
(14V) CVERT.MT)
BUlB, POS., TAIL (14V)
UGHT, POS, (GREEN)
BUlB, POSITION (14V)
21
I_N04B
BULB, POSITION (14V)
LIGHT, POS, (GREEN)
21
21
21
21
LP01A
LP01B
LP01C/D
LP02A
C/B, PANEL LIGHTS
C/B, PANEL LIGHTS
C/B, INSTR LTS
C/B, PANEL LIGHTS
MOONEY
WHELEN
GRIMES
GRIMES
WHELEN
WHELEN
MOONEY
MERIDEN
KLIXON
KLIXON
MERIDEN
AHW4-10
7277-2-10
7277-2-10
AHW4-10
MOONEY
12-98
9
9
9
9
9
9
9
9
23
28
A2064-1777
203529
1777-266P-12.SV
A48OA
A506-14
A1295-G-12
A7512-12
880022-503
W1290-14
W1285-PG
880022-503
GRIMES
NOTES
91-20-01
15
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
21
21
21
21
21
21
21
21
21
21
LPO3A
LP03C
LP03B
LP04A
LP05A
LP08A
LP06B/C
LP07A
LP08A
LP09A
21
21
LP10C
LP13A
21
LP14A
21
LP15A
21
-21
LP16A
21
LP18A
21
LP18B
21
LP18C
21
LP18D
21
LP18E
-21
LP19A
21
LP20A
21
21
LP21A
LP22A
21
LP22B
21
LP22C
21
LP24A
LP17A
21
LP24B
21
21
21
21
LP25A
LP25B
LP25C
LP25D
21
LP25E
91-20-01
16
DESCRIPTION
VENDOR
PART NO.
XSTR, INSTR LIGHTS
XSTR, RADIO LIGHTS
XSTR, (ALT LP03NC)
XSTR, RADIO LIGHTS
XSTR, RADIO LIGHTS
RHEOSTAT/SWITCH
RHEOSTAT/SWITCH, RADIO
RHEOSTAT/SWITCH, RADIO
RHEOSTAT/SWITCH, RADIO
SWITCH, RED/WHITE, UGHT
ROCKER
C/B, INSTR LIGHTS
FUSE, INSTR LTS
HOLDER
FUSE, INSTR LTS
HOLDER
FUSE, INSTR LTS
HOLDER
LAMPS (RED)
HOLDER (4 EA)
LAMPS (RED)
HOLDER (7 EA)
LAMPS 0NHITE)
HOLDER (4 EA)
LAMPS
HOLDER (10 EA)
LAMPS
HOLDER (9 EA)
LAMPS
HOLDER (10 EA)
UGHTS, GLARESHIELD
RCA
RCA
DELCO
RCA
RCA
ALLEN/BRADLEY
ALLEN/BRADLEY
ALLEN/BRADLEY
ALLEN/BRADLEY
MICRO
MICRO
KLIXON
McGRAW-EDISON
2N2016
2N2016
2N3079
2N2016
2N2016
JS1N056P251MA
JSIN056P251MA
JS1N056P261MA
JSIN056P251MA
8H2011
8Z0023
7277-2-6
FM01-5A
FHN42W
FM01-5A
FHN42W
FM01-SA
FHN42W
1836R
1930
1836R
1930
1836
1930
1816
1930
1816
1930
1816
1930
8858-9-1
130285-003
McGRAW-EDISON
McGRAW-EDISON
GE
H.H. SMITH
GE
H.H. SMITH
GE
H.H. SMITH
GE
H.H. SMITH
GE
H.H. SMITH
GE
H.H. SMITH
SLOAN
MOONEY
BULB (7 EA)
GE
LAMPS
GE
HOLDER (6 F_A)
H.H. SMITH
N# LIGHT (2 EA)
KORRY
BULBS
GE
LIGHT, COMPASS
GE
LIGHT-CONSOLE
WESTERN IND CO.
LAMP
WESTERN IND CO
LIGHT-CONSOLE
WESTERN IND CO
LAMP
WESTERN IND CO
LIGHT HOLDER, FLAP & TRIM DIALIGHT
LAMP
GE
FUSE (5 AMP)(3AG-SLO-BLO)LFI-TEL
HOLDER
LI'I-rEL
FUSE, MAP LITE
LITTEL
HOLDER
LITTEL
RESISTOR
RESISTOR, INSTR LITES
OHMITE
RESISTOR, RADIO LITES
OHMITE
RESISTOR, INSTR LITES
DALE
(24-0901THRU 24-0926)
RESISTOR, INSTR LITES
DALE
12-98
330
1836
1930
250-650-5821-008
327
330
501-611<-11K3BP
Wl-7046
501-61K-11K3BP
Wl-7046
270-1930-01710702
370
NOTES
8
8
8
8
9
9
9
9
9
9
9
9
9
9
313005
155020
313001
155020 or 155120
100 OHM 2W
4599
4599
RH-10-50 OHM
RH-10-50 OHM
10
10
/
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
21
LP26A
21
LP27A
21
LP28A
21
LP29A
21
LPSOA
21
21
21
21
21
LP31A
LP32A
LP33A
LP34A
LP35A
21
21
21
21
21
21
21
21
LP36A
LP37A
LP38A
LP39A
LP40A
LP41A
LP42A
LP43A
21
LP44A
21
LP45A
21
21
21
LR01A
LRO2A
LRO3A
21
21
--
LRO4A
LRO5A
21
21
21
21
LSOIA
LS01B/D
LS02A
LS02B
21
21
21
21
21
LS02C
LS02E
LSO2F
LS03A
LS03B
21
LS03B
21
21
LS03C
LS03D
DESCRIPTION
VENDOR
PART NO.
UGHT, POST, M/P
LAMP
LIGHT, POST,TACH
LAMP
UGHT, POST, CLOCK
LAMP
UGHT, POST,OAT
LAMP
HOLDER, OXYGEN LIGHT
LAMP
BUSS, RADIO LIGHT
POST LIGHT
POST LIGHT
POST LIGHT
POST LIGHT
LAMP
LAMP, CLUSTER #1
LAMP, CLUSTER #2
LAMP, CLUSTER #3
LAMP, CLUSTER #4
LAMP, CLUSTER #5
CONNECTOR, MALE
CONNECTOR, FEMALE
FUSE, (1A)
HOLDER
CONNECTOR, PLUG
CLAMP
CONNECTOR,
CLAMP
GRIMES ....
GE
GRIMES
GE
GRIMES
GE
GRIMES
GE
SLOAN
GE
MOONEY
GRIMES
GRIMES
GRIMES
GRIMES
GE
G/E
G/E
G/E
G/E
G/E
DEANS
DEANS
LI'I-IEL
UTTEL
AMP
AMP
AMP
AMP
A-8970B1
330
A-8970B1
33O
A-897081
330
A-8970S1
330
855S-0-U
330
800233-060
A-897081
A-6970S1
A-8970S1
A-8970B1
330
.
330(AVIATION BLUE)
330(AVIATION BLUE)
330(AVIATION BLUE)
330(AVIATION BLUE)
330(AVIATION BLUE)
DEA 90020
DEA 90020
313001
155020 or 155120
206060-1
206062-1
206153-1
206062-1
C/B RECOGNITION LIGHTS
RECOG. UGHT, LT
PLUG, RECOG. LIGHT, LT
SOCKETS
RECOGNITION LIGHT, RT
PLUG, REGOG. LIGHT, RT
SOCKETS
MOONEY
MOONEY
AMP
AMP
MOONEY
AMP
AMP
930023-231
990044-001
1-480318-0
60619-1
880049-001
1-480318-0
60619-1
C/B, STROBE LIGHTS
C/B, STROBE LIGHTS (AL-r)
PWR SUPPLY, STB, I_]WG
PWR SUPPLY, STB, L,NVG
MOONEY
MOONEY
WHELEN
SD|
MOONEY
PWR SUPPLY, STB, I_/WG
MOONEY
PWR SUPPLY, STB, LANG
MOONEY
CABLE, PWR SUPPLY, L/WG
MOONEY
STROBE LITE(FLASHTUBE)
WHELEN
STROBE, LITE, L/VVG
SDI
FLASHTUBE
MOONEY
STROBE LT, L/WG
SDI
MOONEY
STROBE LT, LANG
MOONEY
CABLE ASSY, STROBE, LfWG SDI
MOONEY
930023-007
930023-107/-207
A490, T14
701295-3A
880018-501
880023-507
980928-505(ALT)
880017-503(ALT)
A429
701303A
880019-501
702000-1
860021-501
880038-501
702000-3
880017-501
NOTES
28
31
29, 32
29
30
31
29
64
30
29,34
i
12-98
.............................
91-20-01
17
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
MOONEY
WHELEN
SDI
MOONEY
MOONEY
SDI
MOONEY
MOONEY
MOONEY
WHELEN
SDI
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
AMP
AMP
AMP
880017-503
A490, T14
701295-3A
880018-501
880028-507
702000-3
880017-501
880028-505(ALT)
880017-503(ALT)
A429
702000-2
880019-501
880021-502
880038-502
880038-501
880028-507
880017-505(ALT)
880017-507
880020-501
880041-501
206708-1
1-480305-0
61118-1 OR 60629-1
AN2552-3A
6041H105A
6041H105A
10H3P
1N2483
21
21
21
LS03E
LS04A
LS04B
CABLEASSY, STROBE, L/WG
PWR SUPPLY, STROBE,R/WG
P/S, STROBE, R/WG
21
21
LS04C
LS04D
P/S, STROBE, R/WG
CABLE ASSY, R/WG
21
21
21
21
LB04E
LS04F
LS05A
LS05B
P/S, STROBE, R/WG
CABLE, P/S, R/WG
FLASHTUBE, R/WG
STROBE, UTE, R/WG
FI..ASHTUBE
21
21
21
21
21
21
21
21
21
LS05C
LS06A
LS06B
LS06C
LS06D
LS07A
LS07B
LS08A
LS09A
21
21
21
21
21
MA01A
MA02A
MA02B
MA03A
MA04A
STROBE LT, R/WG
P/S, TAIL STROBE
P/S,TAIL STROBE
CABLE, TAIL STROBE
CABLE, TAIL LITE
STROBE, TAIL
STROBE, TAIL
PLUG, TAIL STROBE
RECPT, TAIL STROBE P/S
PINS (3 EA)
AUX. PWR. RECEPTACLE
RELAY, AUX. PWR
RELAY
DIODE, AUX PWR RELAY
DIODE
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
MB01A
MB01B
MB02A
MB02B
MB03A
MB03B
MB04A
MB04B
MB05A
MB05B
MB06A
MB06B
MB07A
MB07B
MB08A
MB08B
MB09A
MB09B
MB10A
21
MB11A
21
MB12A
91-20-01
18
C/B, COM 1
C/B, COM 1
C/B, NAV 1
C/B, NAV 1
C/B, COM 2
C/B, COM 2
C/B, NAV 2
C/B, NAV 2
C/B, XPN1A
O/B, XPN
C/B, AUD 1
C/B, AUD
C/B, ADF 1A
C/B, ADF
C/B, DME 1A
C/B, DME
SPEAKER, MSO1A
SPEAKER
JACK, MIC 1
WASHERS
JACK, MIC 2
WASHERS
MIC KEY, PILOTS
'CAP
.FACE NUT
C-H
C-H
SARKES TARZIAN
MERIDEN
KUXON
MERIDEN
KLIXON
MERIDEN
KUXON
MERIDEN
KLIXON
MERIDEN
KLIXON
MERIDEN
KUXON
MERIDEN
KUXON
MERIDEN
KUXON
MOONEY
ARA
SWITCHCRAFT
SWlTCHCRAFT
SWlTCHCRAFT
SWITCHCRAFT
C-H
C-H
C-H
12-98
AHW4'7277-2AHW47277-2AHW47277-2AHW47277-2AHW47277-2AHW47277-2AHW47277-2AHW47277-2810195
6707001
C-128
S-102B, S-1029
C-128
S-102B, S-1029
SA25SAT12-3
SW53AA2
15-1049-3
NOTES
31
29, 34
30
29, 34
31
34
29
34
30
29,34
30
29
29, 34
30
30
11
11
11
11
11
11
11
11
11
11
11
11
11
11
11
11
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
C-H
C-H
C-H
SWITCHCRAFT
SWITCHCRAFT
KUXON
MERIDEN
ALCO
KLIXON
KLIXON
KUXON
KUXON
KLIXON
KLIXON
KUXON
KLIXON
KUXON
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
KLIXON
KING
KLIXON
KLIXON
KLIXON
KI\LIXON
KLIXON
MOONEY
KLIXON
MOONEY
MOONEY
BORG INSTR
BORG
MITCHELL
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
DUKES
SA2.5SAT12-3
SW53AA2
15-1049-3
C-11
C-11
7277-2AHW4MST215N
7277-27277-27277-27277-27277-27277-27277-27277-27277-2930023-023
930023-123/-223
930023-021
930023-121/-221
800233-000
800233-000
800233-000
930023-125/-225
7277-2KA20
7277-27277-27277-27277-27277-2930023-127/-227
7277-2800336-501
800336-503
CA-7212 or CA-7286
CA7616
98470-1LW
930023-011
930023-117
930023-111
930023-117/-217
930023-211
4140-00-19A (R/B)
1499-00-19
610153-501
1499-00-19
610153-501
930023-019
21
MB13A
21
21
21
MB14A
MB15A
MB16A/B
MIC KEY, COPILOT
CAP
FACE NUT
JACK, FONE 1
JACK, FONE 2
C/B, NP
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
MB17A
MB18A/B
MB19A
MB20A
MB21A
MB22A
MB23A
MB24A
MB25A
MB26A
MB27A
MB27B/D
MB28A
MB28B
MB29A
MS30A
MB31A
MB32A/B
MB33A
MB34A
MB35A
MB38A
MB37A
MB38A
MB39A
MB40ND
MB41A
MC01A
MC01B
ME01A
MEOIB
MEOlC
NF01A
NF01 B
NFOl C
NFOl D/F
NF01 E
NF02A
SWITCH, RADIO MASTER
C/B R-NAV
C/B HSI
C/B ENCODER
C/B FUEL FLOW
C/B TELEFONE
C/B VME
C/B TELEPHONE
C/B INVERTER
C/B, RMI
C/B, PROP DE-ICE
C/B, PROP DE-ICE
C/B,WX RADAR
C/B, WX RADAR
BUSS, GRD 1
BUSS, GRD 2
BUSS, GRD 3
C/B, WX RADAR, COLOR
C/B, RADIO BLOWER
RADIO BLOWER ASSY
C/B, STEREO
C/B, ALT, SERVO
C/S, ALT SELECT
C/B, CONVERTER
C/B, LORAN
C/B, STANDBY VACUUM
C/B, STORMSCOPE
CIGAR LIGHTER
CIGAR LIGHTER
CLOCK, ELECTRIC
CLOCK (OPT)
CLOCK,LIGHTED)
C/B, FUEL PUMP
C/B, FUEL PUMP-LO
C/B, FUEL PUMP-LO
C/B, FUEL PUMP-LO
C/B, BOOST PUMP
FUEL PUMP
21
NF02B
FUEL PUMP
21
NF03A
C/B, FUEL PUMP-HI
MOONEY
DUKES
MOONEY
MOONEY
12-98
NOTES
11
11
11
11
11
11
11
11
11
11
11
11, 28
28
28
11
11
11
11
11
11
11,28
11
37
37
28
91-20-01
19
SERVICE AND MAINTENANCE MANUAL
M2OJ
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
21
21
21
DESCRIPTION
VENDOR
PART NO.
C/B, FUEL PUMP-HI
RESISTOR
VOLT REG, AUX PUMP
RECPT, V/R
CLAMP
PLUG, V/R
CLAMP
RECPT, PUMP
CLAMP
PLUG, PUMP
CLAMP
MOONEY
CLARSTAT
ELECTRO-DELTA
MOONEY
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
930023-119/-219
VP-50-KA
VR-436
880047-505
206153-1
206062-1
206060-1
206062-1
206153-1
206062-1
206060-1
206062-1
NOTES
21
NF03B/D
NF04A
NFO4B
ALT
NF05A
21
NF06A
21
NF07A
21
NF08A
21
21
21
NP01A
NP02A
NP03A
SWITCH
SOLENOID
FUSE/HOLDER
CARUNG
CONTINENTAL
LI'I-FEL
T1GK6B-1F-WH-A
642200
311010 or312010
21
21
21
PA01A
PA01B
PA02A
C/B, ALTERNATOR, FIELD
C/B, ALT FIELD
ALTERNATOR
MERIDEN
KLIXON
PRESTOLITE
21
21
21
21
21
21
21
21
21
21
21
PA02B
PA02C
PA02D
PA03A
PA03B
PA03C
PA03D
PA04A
PA04B
PA05A
PA06NB/C
21
PA07A
21
PA07B
21
PA08B
ALTERNATOR
FORD
ALTERNATOR
LYCOMING
ALTERNATOR
CONTINENTAL
FILTER
ELPAC
FILTER
SPRAGUE
FILTER
CAPTOR
FILTER
CAPTOR
C/B, ALT
MECH. PROD.
C/B, ALT. OUTPUT
ETA
CAPACITOR
SANGAMO
VOLTAGE REG.
MOONEY
REPLACES OECO P/N 20082,
& ELECTRO-DELTA P/N's VR414 & VR415
ADAPTER CABLE
MOONEY
PLUG, VOLT REG
CLAMP
PLUG, VOLT REG
AMP
CLAMP
AMP
RECPT, VOLT REG
AMP
CLAMP
AHW4-5
7277-2-5
ALY-9403 or8420 or
ALY6420LS OR ALY8420M
DOFP-10300J
LW 15404
641669
27-3-99-01021
JN-14-1356A
A2637
A2638
1648-001-70
41.-3-$14-LN2-70
500-1041-01
880016-501
38
880270-505 (SPARES)
13
800331-721
MS3106A-18-4S
MS3057-10B
206060-1
206062-1
206153-1
206062-1
21
21
21
21
21
PB01A
PB01B
PB02A
PB02B
PB03A
21
21
21
21
21
21
21
PB03B
PB04A
PB04B
PB05A
PB06A
PB06B/D
PB07A
91-20-01
20
BATTERY
BATTERY
RELAY,,BA-[-IERY,MASTER
RELAY, MASTER
C/B, AUX BUSS
(AL'r)
C/B, AUX POWER
RELAY, RADIO
RELAY, RADIO MASTER
SWITCH, MASTER
C/B BUS, RADIO RELAY
C/B, RADIO MASTER
BUSS BAR, MAIN FLEX
GILL
PRESTOLITE
C-H
C-H
MERIDEN
MECHANICAL PROD
ETA
MAGNECRAFT
P &B
C-H
MOONEY
MOONEY
12-96
G-35(PS6-11)
R-35
6041H231
6041H105A
AHW1-50
700-001-50
41-3-$14-LN2-50
W89CQX-2
MB-4413
9811K828
930023-013
930023-113/-213
28
12
17
6
28
14
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
....
!
DESCRIPTION
21
21
21
PB07B
PB07C
PB07D
BUSS BAR MAIN FLEX
BUSS BAR MAIN FLEX, #1
BUSS BAR MAIN FLEX, #2
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
21
PB07E
PB07F
PB07G
PB07H
PB07J
PB07K
PB07L
PB08A
PB09A
PB09B
PB09C
PB09D
PB09E
PB09F/M
PB09G
PB09H
PB09J
PB09K
PB09L
PB10A
PB10B
PB10C
PB11A
PB11B
PB12A
PB12B
PB12C
PB12D
PB12E
PB12F
PB13A
PB13B
PB14A
PB14B
PB14C
PB15A
PB16A
PB20A
PS21A
PB21B
PB21C
PB21D
PB21E
PB22A
PB23A
PB24A
PB25A
PB26A
PB27A
BUSS BAR MAIN POWER
BUSS BAR MAIN POWER
BUSS BAR MAIN POWER
BUSS BAR MAIN #7
BUSS BAR MAIN POWER
BUSS BAR
BUSS BAR
BUSS BAR RADIO FLEX
BUSS BAR AUX
BUSS BAR AUX. #1
BUSS BAR AUX. #2
BUSS BAR CONN 1 &2
BUSS BAR AUXl
BUSS BAR AUX
BUSS BAR AUX. #2
BUSS BAR AUX. #1
BUSS BAR AUX. #2
BUSS BAR AUX.
BUSS BAR AUX. #2
BUSS BAR MAIN #1
BUSS BAR MAIN #1
BUSS BAR MAIN #1
BUSS BAR MAIN #2
BUSS BAR MAIN #2
BUSS BAR MAIN #3
BUSS BAR RADIO #3
BUSS BAR MAIN #3
BUSS BAR RADIO #3
BUSS BAR RADIO #3
BUSS BAR RADIO #2
BUSS BAR RADIO #1
BUSS BAR RADIO #2
BUSS BAR RADIO #2
BUSS BAR RADIO #2
BUSS BAR RADIO #3
DIODE, RADIO MASTER
BUSS BAR MAIN #1
JUMPER
BUSS BAR, RADIO FLEX
BUSS BAR, RAD, FLEX #2
BUSS BAR, RAD, FLEX
BUSS BAR
BUSS BAR
DIODE, MASTER RELAY
DIODE, RADIO RELAY
SHUNT, RADIO RELAY
SHUNT, RADIO RELAY
C/B, BATTERY POWER
. BUSS BAR, MAIN POWER
VENDOR
PART NO.
NOTES
14
14
14
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
SARKES TARZlAN
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
SARKES TARZIAN
SARKES TARZIAN
KULKA
KULKA
ETA
MOONEY
12-98
14
14
14
14
14
14
14
14
913127-009
913127-093
913127-003
913127-011
913127-013
913127-023
913127-025
913127-027
913127-029
913127-113
913127-125
913127-005
913127-017
913127-019
913127-005
913127-019
913127-005
913127-019
913127-001
913127-003
913127-019
913127-019
913127-005
913127-019
913127-005
913127-019
913127-019
F-4
913127-003
40
41
41
15
14
15
15
15
F-4
F-4
600RJ-2
600RJ-2
41-3-S14-LN2-70
913127-031
91-20-01
21
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
21
21
21
21
21
21
21
21
21
21
PB28A
PB29A
PB30A
PB31A
PB32A
PB33A
PB34A
PB35A
PB36A
PB37A
DIODE
BUSS BAR,RADIO #5
BUSS BAR, RADIO #4
BUSS BAR, MAIN PWR, #3
BUSS BAR, RADIO #3
BUSS BAR, RADIO #2
BUSS BAR, MAIN PWR#3
BUSS BAR, MAIN PWR #3
BUSS BAR, RADIO #1
BUSS BAR, MAIN #1
SARKEB TARZIAN
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
F-4
918127-001
918127-001
918127-003
913127-005
913127-019
913127-035
913127-035
913127-035
913127-037
21
21
PG01A
PGO2A
ELECTRO MECH
LI'I-FEL
LITTEL
21
PG03A
21
21
21
PG04A
PGO5A
PG06A
21
-21
PG07A
GENERATOR, STANDBY
FUSE HOLDER
FUSE(15A SLO-BLO)
PLUG, REGULATOR
CLAMP
VOLTAGE REGULATOR
C/B, STANDBY GEN
RELAY, BUSS SWITCHING
SOCKET
RELAY, CONTROL
SOCKET
LIGHT, ON
LAMP
LIGHT, O.V.
LAMP
DIODE, ON LIGHT
DIODE, O.V. LIGHT
RECPTACLE
CLAMP
PLUG
DIODE
DIODE, RADIO RELAY
RECEPTACLE
CLAMP
CLAMP
8012
155020 or 155120
313015
MS3106A-18-1S
MS3057-10A or-10B
2073-2
7277-2-15
JD1B
50-1049-8309
W67CSX-2
70-303
501-61K-11K3BP
Wl-7046
501-61K-11K3BP
Wl-7046
F-4
F-4
206153-1
206062-1
206060-1
F-4
F-4
206705-2
206708-1
206062-1
PLUG, C/B PANEL
CLAMP
PLUG, FLT PNL #1
CLAMP
PLUG, FLT PNL #1
PLUG, ELEC GEAR
CLAMP
PLUG, ELEC GEAR
PLUG, L/WING
CLAMP
PLUG, I../WING
PLUG, L/WG STUB
CLAMP
PLUG, L/WG STUB
CLAMP
PLUG, L/WG STUB
AMP
AMP
AMP
AMP
MOONEY
AMP
AMP
MOONEY
MP
PGO8A
21
-21
21
21
PG09A
21
21
21
21
PG13A
PG14A
PG15A
PG16A
21
PLOIA
21
-21
21
PL02A
21
21
PL03B
PL04A
21
21
PL04B
PL05A
21
PL05B
21
PLO5C
91-20-01
22
PG10A
PG11A
PG12A
PL02B
PLO3A
ELECTRO MECH
KLIXON
LEACH
MAGNACRAFT
WESTERN IND
WESTERN IND
SARKES TARZlAN
SARKES TARZIAN
AMP
AMP
SARKES TAP,ZIAN
SARKES TAFIZIAN
AMP
AMP
AMP
MOONEY
AMP
AMP
AMP
MOONEY
12-98
206037-1
206070-1
206037-1
206070-1
930021-505
206037-1
206070-1
930021-001
206037-1
206070-1
930021-001
206037-1
206070-1
206708-1
206966-1
930021-001
NOTES
.....
--
,
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
21
PL06A
21
PL07A
21
PL07B
21
PL08A
21
-21
PL08B
21
-21
PL10A
21
-21
PL11B
21
-21
PL12B
21
PL13B
21
PL14A
21
21
PL14B
PL15A
21
PL16A
21
PL16B
21
PL17A
21
PL16A
21
PL16B
21
-21
PL19A
21
P1_21A
21
21
PL22A
PL22B
21
--
PL23A
PL09A
PL11A
PL12A
PL13A
PL20A
VENDOR
PLUG, SQUAT SWITCH
AMP
CLAMP
AMP
PLUG,CONSOLE #1
AMP
CLAMP
AMP
PLUG,CONSOLE #1
AMP
CLAMP
AMP
PLUG, HEADUNER
AMP
CLAMP
PLUG, HEADLINER
AMP
CLAMP
PLUG, FIREWALL
CLAMP
PLUG, I_/SIDE CABIN, MIDDLE AMP
CLAMP
PLUG, FLT PNL #2
AMP
CLAMP
PLUG, FLT PNL #2
AMP
CLAMP
PLUG, GLARESHIELD
AMP
CLAMP
PLUG, ANNUNCIATOR PANEL AMP
CLAMP
PLUG, FIREWALLJUNC. PNL AMP
CLAMP
AMP
PLUG, ACCESS. PNL
AMP
CLAMP
AMP
PLUG, I_/SIDE CABIN
AMP
CLAMP
AMP
PLUG, L/SIDE PANEL
MOONEY
PLUG, ELEC. FLAPS
AMP
CLAMP
AMP
PLUG, CONSOLE #2
AMP
CLAMP
AMP
CLAMP
AMP
PLUG, CONSOLE
AMP
CLAMP
AMP
PLUG, RELAY PANEL
AMP
CLAMP
AMP
PLUG, CLUSTER GAUGE
AMP
CLAMP
AMP
PLUG, CLUSTER GAUGE
AMP
CLAMP
AMP
PLUG, PILOT'S WHEEL
AMP
CLAMP
AMP
PLUG, COPILOTS WHEEL
AMP
CLAMP
AMP
PLUG, VAC WARN SW
AMP
CLAMP
AMP
PLUG, RADIO PWR, C./BPNL
AMP
PLUG, AUX PWR, C/B PNL
AMP
CLAMP
AMP
PLUG, RADIO PWR, RELAY PNLAMP
' CLAMP
AMP
12-98
PART NO.
206060-1
202062-1
206037-1
202070-1
206060-1
202062-1
206037-1
206070-1
206708-1
206966-1
MS8106A-22-14S
MS3057-12B
206060-1-001
206062-1
206037-1
206070-1
206708-1
206966-1
206087-1
206070-1
206060-1
206062-1
206037-1
206070-1
206708-1
206966-1
206037-1
206070-1
030021-001
206037-1
206070-1
NOTES
19
206037-1
206070-1
206966-1
206708-1
206966-1
206037-1
206070-1
206037-1
206070-1
206708-1
206966-1
206060-1
206062-1
206060-1
206062-1
206060-1
206062-1
206070-1
206037-2
206070-1
206037-2
206070-1
91-20-01
23
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
21
PL24A
21
PL24S
21
PL24C
21
PL25A
21
PI-25B
21
PL2.SC
21
PI.-25D
21
PL26A
21
PL26B
21
PL26C
21
PL2.TA
21
PL28A
21
PL29A
21
PL29B
21
PL30A
21
PL30B
21
PL30C
21
PL31A
21
PL32A
21
PL33A
21
PL34A
21
PL34B
21
PL35A
21
PL35B
21
PL35C
21
PL35D
21
PL36A
PLUG, CABIN TAIL CONE
CLAMP
PLUG, CABIN TAIL CONE
CLAMP
PLUG, CABIN/TAIL CONE
CLAMP
PLUG, R/WG
CLAMP
PLUG, R/WG
CLAMP
PLUG, R/WG
CLAMP
PLUG, R/WG
CLAMP
PLUG, R/WG STUB
CLAMP
PLUG, R/WG NAV
CLAMP
PLUG, R/WG STUB
CLAMP
PLUG, TRIM POS. IND
CLAMP
PLUG, PILOT'S TRIM
CLAMP
PLUG, TAIL
CLAMP
PLUG, EMPENNAGE
CLAMP
PLUG, RADIO, C/B PNL
CLAMP
PLUG, C/B PNL(OPT)
CLAMP
PLUG, C/B PNL(OPT)
CLAMP
PLUG, RADIO PKG CABLE
CLAMP
PLUG, XSTRS, CONSOLE
CLAMP
PLUG, PWR, FLT PNL
CLAMP
PLUG, PANEL LT CONTROL
CLAM P
PLUG, LT CONTROL
CLAMP
PLUG, GEAR CONTROL
CLAMP
PLUG, GEAR CONTROL
CLAMP
PLUG, GEAR CONTROL #1
CLAMP
PLUG, GEAR CONTROL #2
CLAMP
. PLUG, GEAR OVERRIDE
. CLAMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
MOONEY
AMP
AMP
AMP
AMP
AMP
MOONEY
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
206037-1
206070-1
206706-1
208966-1
206037-1
206070-1
206037-1
206070-1
206060-1
206062-1
206708-1
206966-1
930021-001
206966-1
206060-1
206062-1
206708-1
206966-1
930021-001
206966-1
206060-1
206062-1
206060-1
206062-1
206060-1
206062-1
206708-1
206966-1
206037-1
206070-1
206706-1
206966-1
206060-1
206062-1
206037-1
206070-1
206037-1
206070-1
206037-2
206070-1
206060-1
206062-1
206706-1
206966-1
206708-1
206966-1
206060-1
206062-1
206705-2
206966-1
206060-1
206062-1
205060-1
206062-1
91-20-01
24
12-96
NOTES
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
21
PL37A
21
PL38A
PLUG, VAC WARN
CLAMP
PLUG, ELT SWITCH
CLAMP
PLUG, OVERHEAD LITE
CLAMP
PLUG, EMERG FLD
CLAMP
PLUG, GLARESHIELD
CLAMP
PLUG, HOUR METER
CLAMP
PLUG, FLT PNL
CLAMP
PLUG, GR SAFETY SW
CLAMP
PLUG, FIREWALL #2
CLAMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
266060-1
206062-1
205060-1
206062-1
206060-1
206062-1
206060-1
206062-1
206060-1
208062-1
206060-1
206062-1
206708-1
206966-1
206060-1
206062-1
MS3106A-22-14S
MS3057-12B
PLUG, AVIONIC PWR
PLUG, AUDIO INTERCN
CLAMP
PLUG, FLT PNL DIM
CLAMP
CLAMP
PLUG, C/B DIM
CLAMP
PLUG, NP TRIM SW RELAY
CLAMP
PLUG, A/P
CLAMP
PLUG, NP GRND
CLAMP
PLUG, AVIONICS GRND
CLAMP
PLUG MAIN CABLEGRND
CLAMP
PLUG AVIONICS GRND #2
CLAM P
PLUG INT PWR
CLAMP
PLUG COM/NAV POWER
CLAMP
PLUG ROLL SERVO CABLE
CLAMP
PLUG AZIMUTH CABLE
CLAMP
PLUG AVIONICS DIM
CLAMP
PLUG K-4/C-2 NAV REC/NP
CLAMP
MOONEY
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
930021-501
205839-1
206070-1
206037-1
205838-1
206062-1
206062-1
206062-1
206037-1
206070-1
206037-1
206070-1
206037-1
206070-1
206839-3
206070-1
206037-1
206070-1
2067839-3
206070-1
206708-1
206966-1
206060-1
206062-1
206768-1
286866-1
206708-1
206966-1
206037-1
206070-1
205839-3
206070-1
21
-21
PL39A
PL40A
21
-21
PL41A
21
PL43A
21
PL44A
21
PL45A
21
21
PL46A
PL47A
21
PL48A
21
-21
-21
PL50A
21
-21
PL53A
21
-21
PL53C
21
PL54A
21
PL55A
21
PL57A
21
PL58A
21
PL59A
21
--
PL60A
PL42A
PL51A
PL52A
PL53B
PL53D
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
12-98
NOTES
:
91-20-01
25
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
21
PL61A
21
PL62A
21
PL63A
21
PL64A
21
PL65A
21
PL66A
21
PL67A
21
PL68A
21
PL69A
21
PL670A
21
PL71A
21
PL72A
21
PL73A
21
PL74A
21
PL75A
21
PL76A
21
PL77A
21
PL78A
21
PL79A
21
21
21
PS01A
PS01B
PS02A
21
PS03NB
21
PS04A
21
PSO4B
21
PS05A
91-20-01
26
DESCRIPTION
VENDOR
PART NO.
PLUG, K-14 NAV REC/NP
CLAMP
PLUG, K-14 NAV REC/NP
CLAMP
PLUG, NP XFER
CLAMP
PLUG, K-2/K-3 NAV REC/NP
CLAMP
PLUG, TRIM RELAY
CLAMP
PLUG TRIM SW
CLAMP
PLUG AZIMUTH
CLAMP
PLUG ADF RMI
CLAMP
PLUG TRIM RELAY
CLAMP
PLUG TRIM PWR
CLAMP
PLUG NP RELAY
CLAMP
PLUG, VOR/GS TRANSFER
CLAMP
PLUG, MKR INVERTER
CLAMP
PLUG, NAV/REC NP
CLAMP
AMP
206839-3
206070-1
206037-1
206070-1
206037-1
206070-1
205839-3
206070-1
205838-1
206062-1
205838-1
206062-1
206708-1
206966-1
205838-1
206062-1
205838-1
206062-1
206060-1
206062-1
205839-3
206070-1
205838-1
206062-1
205838-1
206062-1
205839-3
206070-1
PLUG. ADF/RMI
CLAMP
PLUG, GRND
CLAMP
PLUG, XPDR/ENCODER
(KFC 200)
CLAMP
PLUG, RADIO PKG CABLE
CLAMP
PLUG, NAV REC/NP, I<-4/(]-2
CLAMP
C/B, IGN/TACH/CIG UGHTER
C/B, IGN/TACH/CIG LIGHTER
SWITCH, STARTER
HOUSING
SCREEN, DISPLAY
RING, GUARD
RELAY
STARTER
(ALT)
(ALT)
STARTER
• (ALT)
DIODE
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
206037-1
206070-1
205839-3
206070-1
20037-1
AMP
206070-1
206037-1
206070-1
205839-3
206070-1
MERIDEN
KLIXON
MICRO
MICRO
MICRO
MICRO
C-H
R/B MOONEY
PRESTOLITE
PRESTOLITE
PRESTOLITE
PRESTOLITE
LYCOMING
SARKES TARZIAN
AHW4-10
7277-2-10
2D72
2M1
2J5
2K6
6041H105A
940020-501
MZ4206
MZ4218
MZ4222
MCL-6501
LW15572
F-4
12-98
NOTES
22
39
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
21
PS06A
21
RC01A
21
RC01B
21
RC02A
21
21
RC02B
RC03A
21
21
-21
21
RC03B
RC04A
RC04B
RC05A
21
RC05B
21
21
RC05C
RC06A
21
RC07A
21
RC07B
21
RC08A
21
-21
RC09B
21
RC10A
21
-21
RC11A
21
RC12A
21
RC13A
21
RC13B
21
RC14A
21
21
21
RC14B
RC14C
RC15A
21
RC16A
RC09A
RC11B
DESCRIPTION
FUSE HOLDER
FUSE
RECPT, C/B PNL
CLAMP
RECPT, C/B PNL
CLAMP
RECPT, FLT PNL #1
CLAMP
RECPT, FLT PNL #1
RECPT, ELEC GEAR
CLAMP
RECPT, ELEC GEAR
RECPT, L/WING
CLAMP
RECPT, L/WING
RECPT, L/WING
CLAMP
RECPT, L/WING STUB
CLAMP
RECPT, L/WING STUB
RECPT, SQUAT SWITCH
CLAMP
RECPT, CONSOLE #1
CLAMP
RECPT, CONSOLE #1
CLAMP
RECPT, HEADLINER
CLAMP
RECPT, HEADLINGER
CLAMP
RECPT, FIR_ALL
CLAMP
RECPT, L/SIDE CABIN, MID
CLAMP
RECPT, FLT PNL#2
CLAMP
RECPT, FLT PNL #2
CLAMP
RECPT, GLARESHIELD
CLAMP
RECPT, FIREWALLJUNC PNL
CLAMP
RECPT, ACCESS. PNT
CLAMP
RECPT, L/SIDE CABIN LOW
CLAMP
RECPT, L,/SIDE PNL
RECPT, L/SIDE PNL
RECPT, FLAPS, ELEC
CLAMP
RECPT, CONSOLE #2
CLAMP
VENDOR
UTTEL
LI'I-FEL
AMP
AMP
AMP
AMP
AMP
AMP
MOONEY
AMP
AMP
MOONEY
AMP
AMP
MOONEY
AMP
AMP
AMP
AMP
MOONEY
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
MOONEY
MOONEY
AMP
AMP
AMP
AMP
12.98
PART NO.
155020 or 155120
313001
206036-3
206070-1
20515%1
206138-1
206036-3
205070-1
930021-506
206036-1
206070-1
930021-002
206036-3
206070-1
930021-002
206036-3
206070-1
206705-2
206966-1
930021-002
' 206153-1
206070-1
206036-3
206070-1
206153-1
206062-1
206036-3
206070-1
206705-2
206966-1
MS3100A22-14P
MS3057-12B
206153-1
206062-1
206036-3
206070-1
206705-2
206966-1
206036-6
206070-1
206066-3
206070-1
206705-2
206966-1
206036-3
206070-1
930021-002
930021-502
206036-1
206070-1
206036-3
206070-1
NOTES
19
19
91-20-01
27
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
21
RC16B
21
RC17A
21
RC18A
21
RC18B
21
RC19A
21
RC20A
21
RC21A
21
RC22A
21
RC22B
21
RC23A
21
RC24A
21
RC24B
21
RC24C
21
RC25A
21
RC25B
21
RC25C
21
RC25D
21
RC26A
21
RC26B
21
RC26C
21
RC27A
21
RC28A
21
RC29A
21
RC29B
21
RC30A
21
RC30B
91-20-01
28
VENDOR
RECPT, CONSOLE
AMP
CLAMP
AMP
RECPT, RELAY PNL
AMP
CLAMP
AMP
RECPT, CLUSTER GAUGE
AMP
CLAMP
AMP
RECPT, CLUSTER GAUGE
AMP
CLAMP
AMP
RECPT, PILOT'S WHEEL
AMP
CLAMP
AMP
RECPT, COPILOT'S WHEEL
AMP
CLAMP
AMP
RECPT, MACWARN SW
AMP
CLAMP
AMP
RECPT, RADIO PWR C/B PNL AMP
CLAMP
AMP
RECPT, C/B PNL, AUX PWR
AMP
CLAMP
AMP
RECPT, RADIO PWR RELAY PNL AMP
CLAMP
AMP
RECP'I" CABIN TAILCONE
AMP
CLAMP
AMP
RECP't" CABIN TAILCONE
AMP
CLAMP
AMP
RECP'[ , CABIN TAILCONE
AMP
CLAMP
AMP
RECP'f , R/WING
AMP
CLAMP
AMP
RECPT, R/WING
AMP
CLAMP
AMP
RECPT R/WING
AMP
CLAMP
AMP
RECPT R/WING
MOONEY
CLAMP
AMP
RECPT R/WIGN STUB
AMP
CLAMP
AMP
RECPT R/WING STUB
AMP
CLAMP
AMP
RECPT R/WING STUB
MOONEY
CLAMP
AMP
RECPT TRIM POS IND
AMP
CLAMP
AMP
RECPT PILOT'S TRIM
AMP
CLAMP
AMP
RECPT, TAIL
AMP
CLAMP
AMP
RECPT, TAIL
AMP
CLAMP
AMP
RECPT, RADIOS, C/B PNL
AMP
CLAMP
AMP
RECPT, C/B PNL
AMP
CLAMP
AMP
12-98
PART NO.
206705-2
206966-1
206036-1
206070-1
206036-8
206070-1
296708-2
206966-1
206153-1
206062-1
206153-1
206062-1
206153-1
206062-1
206207-1
296070-1
206036-2
206070-1
206036-1
206070-1
206036-3
205070-1
206705-2
206966-1
206036-3
206070-1
206036-3
206070-1
206153-1
206062-1
206705-1
206070-1
930021-002
2060966-1
206153-1
206062-1
206705-2
206966-1
930021-002
206966-1
206153-1
206062-1
206153-1
206062-1
206153-1
206062-1
206705-2
206966-1
206036-3
206070-1
206705-2
206966-1
NOTES
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
21
RC30C
21
RC31A
21
RC32A
21
RC33A
21
RC34B
21
RC34B
21
RC35A
21
RC35B
21
RC35C
21
RC35D
21
RC37A
21
RC38A
21
-21
RC39A
21
RC41A
21
RC42A
21
RC43A
21
RC43C
21
RC44A
21
RC45A
21
21
RC46A
RC47A
21
RC48A
21
RC49A
21
RC5OA
21
RC51A
RC40A
....
VENDOR
RECPT, C/B PNL (OPT)
AMP
CLAMP
AMP
RECPT, RADIO PKG CABLE
AMP
CLAMP
AMP
RECPT, TRANSISTORS, CONSOLE AMP
CLAMP
AMP
RECPT, F:_NRFLT PNL
AMP
CLAMP
AMP
RECPT, PNL LT CONTROL
AMP
CLAMP
AMP
RECPT, LIGHT CONTROL
AMP
CLAMP
AMP
RECPT, GEAR CONTROL
AMP
CLAMP
AMP
RECPT, GEAR CONTROL
AMP
CLAMP
AMP
RECPT, GEAR CONTROL #1
AMP
CLAMP
AMP
RECPT, GEAR CONTROL #2
AMP
CLAMP
AMP
RECPT, VAC WARN
AMP
CLAMP
AMP
RECPT, ELT, SW
AMP
CLAMP
AMP
RECPT, O/H LIGHT, AFT
AMP
CLAMP
AMP
RECPT, EMERG FLD
AMP
CLAMP
AMP
RECPT, BLARESHIEDL
AMP
CLAMP
AMP
RECPT, HOUR METER
AMP
CLAMP
AMP
RECPT, FLT PNL
AMP
CLAMP
AMP
RECPT, GO AROUND/WX RADAR
CLAMP
AMP
RECPT, GR SAFETY SW
AMP
CLAMP
AMP
RECPT, FIREWALL#2
CLAMP
RECPT, AVIONICS PWR
MOONEY
RECPT, AUDIO INTER
AMP
CLAMP
AMP
RECPT, FLT PNL GRND/DIM
AMP
CLAMP
AMP
RECPT, C/B GRND
AMP
CLAMP
AMP
RECPT, C/B DIM
AMP
CLAMP
AMP
RECPT, NP TRIM SW RELAY AMP
CLAMP
AMP
12-96
PART NO.
NOTES
206060-1
206062-1
206036-3
206070-1
206036-3
206070-1
206207-1
206070-1
206153-1
206062-1
206705-2
206966-1
206705-2
207008-1
206153-1
206062-1
206705-2
206966-1
206153-1
206062-1
206153-1
206062-1
206153-1
206062-1
206153-1
206062-1
206153-1
206062-1
206153-1
206062-1
206153-1
206062-1
206705-2
206966-1
206705-2
206966-1
206153-1
206062-t
MS3100A-22-14P
MS3057-12B
930021-502
206152-1
206070-1
206036-1
206070,-1
206841-2
206062-1
206153-1
206062-1
206036-3
206070-1
91-20-01
29
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
21
RC52A
21
RC53A
21
RC53S
21
RC53C
21
RC53D
21
-21
RC54A
21
RC57A
21
-21
RC58A
21
-21
RC59B
21
RC61A
21
RC62A
21
RC63A
21
-21
RC64A
21
-21
RC66A
21
RC68A
21
RC69A
21
RC70A
21
RC71A
21
-21
-21
RC72A
91-20-01
3O
RC55A
RC59A
RC60A
RC65A
RC67A
RC73A
RC74A
DESCRIPTION
VENDOR
PART NO.
RECPT, NP PWR
CLAMP
RECPT, NP GRND
CLAMP
RECPT, AVIONICS GRND #1
CLAMP
RECPT, MAIN CABLE GRND
CLAMP
RECPT, AVIONICS GRND #2
CLAMP
RECPT, INTERFACE PWR
CLAMP
RECPT, COMM/NAV PWR
CLAMP
RECPT, ROLL SERVO CABLE
CLAMP
RECPT, AZIMUTH CABLE
CLAMP
RECPT, AVIONICS DIM
CLAMP
NP DIM
CLAMP
RECPT, K-4/C-2,NAVREC/A/P
CLAMP
RECPT, K-14, NAVREC/NP
CLAMP
RECPT, K-14, NAVREC/NP
CLAMP
RECPT, A/P TRANSFER
CLAMP
RECPT, K-2/K-3, NAVREC/A/P
CLAMP
RECPT, TRIM RELAY
CLAMP
RECPT, TRIM SW
CLAMP
RECPT, AZIMUTH
CLAMP
RECPT, ADF/RMI
CLAMP
RECPT TRIM RELAY
CLAMP
RECPT TRIM PWR
CLAMP
RECPT A/P RELAY
CLAMP
RECPT VOR/GS TRANSFER
CLAMP
RECPT MKR INVERTER
CLAMP
RECPT NAVREC/A/P
CLAMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
206036-3
206070-1
206036-3
206070-1
206152-1
206070-1
206036-3
206070-1
206152-1
206070-1
206705-2
206966-1
206153-1
206062-1
206705-2
206966-1
206705-2
206966-1
206036-3
206070-1
206153-1
206062-1
206152-1
206070-1
206152-1
206070-1
206036-3
206070-1
206036-1
206070-1
206152-1
206070-1
205841-2
206062-1
205841-2
206062-1
206705-2
206966-1
205841-2
206062-1
205841-2
206062-1
206153-1
206062-1
206152-1
206070-1
205841-1
206062-1
205641-1
206062-1
206152-1
206070-1
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
12-98
NOTES
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
21
RC75A
21
RC76A
21
RC77A
21
RC78A
21
RC79A
21
WA01A
21
21
21
WA02A
WA03A
WA03B
21
21
21
WE01A
WE01B
WE02A
21
WE03A
21
21
-21
21
21
WE03B
WE03C
21
WE07A
21
21
21
21
21
WE08A
WE09A
WE10A
WE11A
WE12A
21
WF01A
21
21
WF03A
WF04A
21
WL01A
21
WL02A
21
VENDOR
PART NO.
RECPT, ADF/RMI
CLAMP
AMP
RECPT, GRND
AMP
CLAMP
AMP
RECPT, XDCR/ENCODER (KFC-200) AMP
CLAMP
AMP
RECPT, RADIO PKG CABLE
AMP
CLAMP
AMP
RECPT, K..4/C-2NAVREC/A/P
AMP
CLAMP
AMP
206036-3
206070-1
206152-1
206070-1
206036-2
206070-1
206036-3
206070-1
206152-1
206070-1
LIGHT, ALT WARN
BULB (2)
RECTIFIER
SWITCH, LO VOLT DET
SWITCH, LO VOLT DET
KORRY
GE
SARKESTAFIZIAN
ELECTRO DELTA
ELECTRO DELTA
250-650-5821-003
330
F-4
LV 14
LV-14F
C/B, GEAR WARN
C/B, GEAR WARN
UGHT, GEAR UNSAFE
BULB
SWITCH, THROI-rLE
ACTUATOR
SWITCH, THROTTLE
SWITCH, THROTTLE
ACURATOR
HORN, GEAR UP, WARN
RECTIFIER
LIGHT, GEAR POSITION
BULB (1)
LIGHT, GEAR DOWN
BULB (2)
DIODE, GEAR UNSAFE
DIODE, GEAR DOWN
DIODE, GEAR HORN
RESISTOR, DIM
DIODE, DIM
MERIDEN
KLIXON
KORRY
SARKES TAP,ZIAN
AHW4-2
7277-2-2
250-650-5821-006
GE
1SM1-T
JS-221
SS12ET10-102L3
V3-1
JV-5
SC628P
F-4
855S-0-U
327
250-650-5821-007
GE
F-4
F-4
F-4
(50 OHM -5 WAll')
F-.4
LIGHT, LOW FUEL PRESS
BULB (2)
RECTIFIER
PLUG-SWITCH
KORRY
GE
SARKES TARZIAN
AMPHENOL
250-650-5821-004
330
F-4
126-223-1000
WL03A
FUSEHOLDER
FUSE
LIGHT, LANDING IND
BULBS (2)
RECTIFIER
LITTEL
LI'I-['EL
KORRY
GE
SARKES TAP,ZIAN
155020
311011
250650-5821-005
330
F-4
21
21
WS01A
WS01B
C/B, STALL WARN HORN
C/B, STALL WARN HORN
MERIDEN
KLIXON
AHW4-2
7277-2-2
21
21
WS02A
WS03A
HORN, STALL WARNING
SWITCH, PRE-STALL WARN
MALLORY
SAFE FLIGHT
SC628
C46001
21
21
21
WT01A
WT02A
WT03A
SWITCH, PRESS TO TEST
C/B, ANNUNCIATOR
.ANNUNCIATOR
LAMPS
ALCO
MSP205R
KLIXON
7277-2-2
IAI
500D0024
CHICAGO MINIATURE CM7-7330
WE04A
WE05A
WE06A
MICRO
MICRO
C-H
MICRO
MICRO
MALLORY
SARKESTARZIAN
SLOAN
GE
KORRY
SARKES TARZIAN
SARKES TARZIAN
SARKES TARZIAN
12-98
NOTES
330
330
91-20-01
31
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
NOTES
500D0038B
CM7-7330
20
21
WT03B
ANNUNCIATOR
LAMPS
IAI
CHICAGO MINIATURE
21
WT03F
21
WT03G
21
21
WT03H
WT03J
21
WT03K
ANNUNCIATOR
LAMPS
ANNUNCIATOR
LAMPS (8)
ANNUNCIATOR
ANNUNCIATOR
LAMPS
ANNUNCIATOR
IAI
500D0038-007
CHICAGO MINIATURE CM7-7330
MOONEY
880025-501
CHICAGO MINIATURE CM7-7330
MOONEY
880025-515
MOONEY
880025-511
CHICAGO MINIATURE CM7-7330
MOONEY
880025-513
21
WT04A
PLUG, ANNUNCIATOR
PIN
MOLEX
MOLEX
09-50-8121
08-50-106
21
21
21
WV01A
WV01B
WV02A
C/B, VACUUM WARN
C/B, VACUUM WARN
SWITCH, VACUUM WARN
MERIDEN
KLIXON
MOONEY
AHW4-2
7277-2-2
880012-501
21
21
21
WV02B
WVO2C
WV03A
21
WV04A
21
WV04B
21
21
21
WV05A
WV06A
WV07A
SWITCH, VAC. WARN LO
SWITCH, VAC. WARN HI
LIGHT, LOW VAC
BULB (2)
LIGHT, HIGH VAC
BULB (2)
LIGHT, VAC
BULB (2)
RECTIFIER, LO
RECTIFIER, HI
SWITCH, VAC LT, FLASHER
WHITMAN GENERAL
WHITMAN GENERAL
KORRY
GE
KORRY
GE
KORRY
GE
SARKES TARZIAN
SARKES TARZlAN
ELECTRO DELTA
P118V-IN-K5L-1
PllSV-IN-K4L-2
250-650-5821-002
330
250-650-5821-001
330
250-650-5821-009
330
F-4
1=-4
FL1
21
WW01A
21
WW01B
SWITCH, RAM AIR
ACTUATOR
SWITCH, ALTERNATE AIR
MICRO
MICRO
CHERRY
V3-1
JV-5
E51-50B
UGHT DIMMER SW
BOX RHEOSTAT
TRANSISTOR
TRANSISTOR (ALl')
FUSE
::IECEPTACLE
MOONEY
ALLEN-BRADLEY
RCA
RCA
McGRAW-EDISON
AMP
8800344
JS1N056P02MA
2N3055
2N3773
FM01-5A
206705-2
91-20-01
32
12-98
20
21
21
21
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
NOTES
1.
2.
3.
4.
Switch8906k2876 may be used by painting black handle with white epoxy paint.
Alternate for V3L-3 is V3-1 switch with JV-5 actuator.
0506-505 is replacementfor-004; S/N 18928 & UP are modified.
Or equivalent Sprague
RB1535
Dale
MFS-1/2(15K)
TWX
1/2 W (15k)
5.
6.
Set for75 MPH (+/-5.0) (65 +7/4 KIAS) increasingactuation.(2.775 in. H20, +0.384/-0.358 in.)
Use withsocket,27E122; spring,206176; stand-off,(2 ea) 21B212. (AN515-6R5 screw,
AN936-A6 washer).
Aitemete L110-1-N-K3L or Mooney P/N 880013-501.
MountingHardware
RCA
KC2B
Mica InsulatingWafer
H.H. Smith
6291
NylonShoulder Washer
H.H. Smith
2666
SolderLug
H.H. Smith
1410-10
Metal Washer
H.H. Smith
1152
Nut
H.H. Smith
1367
7.
8.
9.
Altemete Holders
Drake
Leecraft
4151-014
10.
AIt. Resistors
243E2015
VC5E-200
11.
Maximum circuitbreakerratingis shown, amperageof installedcircuitbreakerisdetermined
by particularunit installed.
Aitemate
Ohmite
0561
Mallory
5AV10
12.
13.
14.
15.
16.
17.
18.
19.
20.
21.
22.
23.
24.
25.
Sprague
Drake
07-05
ReplaceVR414 & 20082 with 880016-501 & 800331-721 cable.
Manufactureusing"AlphaWire Co." braid #2172 or#1233/2 (2 ea) & AMP terminalsas
necessaryto connectthe bussbars as shownon schematic.Cover braidwith PVC 105/A
tubingfor insulation.
Same as 14 except use (1 ea) braid.
Groundtabs ( 250" series)
"As required" AMP
41478
AMP
41480
Altemate
Prestalite
R35
Replacewith MS3106A-22-14P when used in conjunctionwithMS3450KT22-14S.
Replace withMS3450K-r22-14S receptacle & MS3417-22-N cableclamp or
Matrix#9440KT22-14S.
MFG Chicago Minature Lamp Co.
Set switcheswithroomtemperature between 60° F and 80° F. Set low at 4.25" Hg. +/-0.25"
and highat 5.50" Hg. +0.20/-0.00" increasing vacuum.Switchesmay not vary morethan 0.50"
Hg. between 0_ F and 110° F.
Replace with 940020-501, (Cutler-Hammer solenoid P/N 6041H53).
Alternate Turn Coordinators:
Talley Corp. (w/out lights)
1394T100-7Z
United Instr.(w/out lights)
9100 Code No. 6
Alternate Turn & Bank:
Talley Corp. (w/out lights)
1234T100-7TZ
Talley Corp. (w/out lights)
1284T100-3TZ
Aitemate Fuel Flow Gauges:
Mooney (Gals/hr - lighted)
880034-501
Mooney (liters/hr - lighted)
880034-503/-509
Mooney (Imperial gals/hr - lighted)
880034-511
Mooney (Pounds/hr)
880034-505
12-98
91_20-01
33
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
NOTES (con't,)
26.
27.
28.
29.
30.
31.
32.
33.
34.
35.
36.
Alternate Landing Gear:
Mooney
880037-501
Use buss bar 913127-029, -023 or -013 as required by installation of optional equipment.
Effective 25-0821 & ON (All are 930023-2xx C/B's). Effective 24-1464 & ON also.
Effective25-0001 thru 25-0788 or 24-0024 thru 24-1037.
Effective25-0789 & ON or 24-1426 & ON.
Effective 24-0001 thru 24-0023 (24-0024 thru 24-1037 use 21 LS02B, 21 LS03B, 21 LS04B &
21 LS05B)
Effective25-0447 thru 25-0780 or24-1038 thru 24-1425.
Standardon 24-1211 & ON.
Effective25-0613 thru 25-0780.
AltemataTurn Coordinator(w/lights):
United Instr
9112-Code No. 9
Astronautics 303990-113MSC
Talley
1394T100-3Z
37.
Use 1 ea. MS35334-21 or MS2898 (Alan-Bradley)internaltoothIockwasherwith each lightif
notsupplied
by Sloan.
Altemata Clock (lighted):
Mid-Continent MD-88L
Mid-Continent MD-88L(ET)
(w/light tray) BA14-24-BW2
38.
AlternateVoltage Regulator:
39.
Altamate Starter (21 PS04B):
40.
41.
Use bussbars913127-123,-125 as required, by installationof OptionalEquipment.
CUT TO SIZE
91-20-01
34
Lamar
B-00371-6.
TCM
646238
12,98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
91-20-02
- ELECTRICAL SYSTEM HARDWARE CHART - 28 VOLT SYSTEMS
SERIALNUMBER's 24-3000 THRU 24-3153, MOONEY DRAWING NO. 800350 (AV-9)
CODE
JKL
JKL
JKL
JKL
JKL
JKJK-KJKJKJKJKJKL
JKL
JKL
JKL
JKJKJKL
JKJKJKJKJ--J----L
--L
--L
--L
---L
DESCRIPTION
VENDOR
CB101A
CB102A
CB103A
CB104A
C/B DEFROSTER BLOWER
KUXON
SWITCH, DEFROST BLOWER CHERRY
MOTOR, DEFROSTER BLOWER MOONEY
RECPT, DEFROSTER BLOWER AMP
PINS
AMP
CB105A
PLUG, DEFROSTER BLOWER AMP
SOCKETS
AMP
CCI01A
C/B, COWL FLAP
KLIXON
CC102A
SWITCH, COWL FLAP
MICRO
CAP, WHITE
MICRO
CC103A
ACTUATOR, COWL FLAP
MOONEY
CC104A
SWITCH,OPEN LIMIT
MICRO
ACTUATOR
MICRO
CC105A
SWITCH, CLOSE LIMIT
MICRO
ACTUATOR
MICRO
CC106A
RECPT, 4 PIN
AMP
CLAMP
AMP
CC107A
PLUG, 4 PIN
AMP
CLAMP
AMP
CF101A
C/B FLAP ACT
KLIXON
CF102A
SWITCH, FLAP
C-H
CF103A
SWITCH, UP LIMIT
MICRO
CF104A
SWITCH, DOWN LIMIT
MICRO
CF106A
SWITCH, TAKEOFF, UP
MICRO
CF107A
SWITCH, TAKEOFF, DOWN
MICRO
ACTUATOR
MICRO
CF105A
ACTUATOR, FLAP
MOONEY
CF108A
RELAY, UP
MAGNACRAFT
CF109A
RELAY, DN
MAGNACRAFT
BASE
MAGNACRAFT
CFI1OA
SWITCH, FLAP
C-H
(ALl')
MICRO
KNOB
MOONEY
CF111A/112A DIODE
CF113A
PLUG, 4 PIN
AMP
CLAMP
AMP
CF114A
RECPT, 4 PIN
AMP
CLAMP
AMP
CF150A
C/B TRIM/FLAP IND
KUXON
CF151A
INDICATOR,TRIM/FLAP
PENN AIRBORNE
CF152A
: PLUG, TRIM/FLAP IND
13-1"
CLAM P
I'IF
LOCK RETAINER
ITT
CF153A
PLUG,FLAP POSITION, 4 PIN AMP
CLAMP
AMP
CF154A
RECPT,FLAP POSITION, 4 PIN AMP
CLAMP
AMP
12-98
PART NO.
7277-2-2
E51-50B
640317-501
1-408319-0
60620-1
1-480318-0
60619-1
7277-2-5
12TW1-1
15PAg0-4W
880050-501
1SE1-T
JE-5
1SE1-T
JE-5
206153-1
206062-1
206060-1
206062-1
7277-2-5
8906K3148
V3-1
V3-1
V3-1
V3-1
JV-5
750105-501
W67RCSX-3
W67RCSX-3
70-303
8906K4064
2TL148-12L
917026-501
1N2483
206060-1
206062-1
206153-1
202062-1
7277-2-1
9A1590
DA15S
DA51210-1
DA51220-1
206060-1
206062-1
206153-1
._ 206062-1
NOTES
4
4
4
4
4
91-20-02
35
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
--L
CF155A
JKL
JKL
CT101A
C/B ELECTRIC TRIM
KUXON
CT101A
C/B ELECTRIC TRIM
KUXON
CT150A
POTENIOMEFER, TRIM POSITION
WA2-G056S502UA
CT151A
PLUG, TRIM POSITION, 4 PIN AMP
CLAMP
AMP
CT152A
RECPT,TRIM POSITION, 4 PIN AMP
CLAMP
AMP
7277-2-3
7277-2-5
ALLEN-BRADLEY
JKJKJK-
CV101A
CV102A
CV103A
JKJKJKJK-JK-JK-JK-
CV104A
CV105A
CV106A
CV107A
930023-245
$6112-472
155020 or155120
313001
800846-501
830131-511
1N2483
1-480319-0
60619-1
1-480319-0
60620-1
1-480319-0
60620-1
1-480318-0
--L
--L
CV108A
-CV109A
CV110A
JKJKJ--
DA101A
DA101B
DA101D
-JKJKJK-
DA102A
DA102A
DA103A
JKJKJK-
DA104A
DA104B
DA105A
JK-
DA106A
JKJKJKJKJK-
DA107A
DA107B
DA107C
DA107D
DA108A
JK-
DA109A
JK-
DA110A
JK-
DA111A
91-20-02
36
POTENTIOMETER,FLAP POSITION
C/B, STBY VAC
CLUTCH, STBY VAC PUMP
FUSE HOLDER
FUSE
ANNUNCIATOR
RELAY
DIODE
PLUG
SOCKETS
RECPT, 2 PIN
PINS
RECPT, 2 PIN
PINS
PLUG, 2 PIN
ALLEN-BRADLEY
PART NO.
MOONEY
AEROSAFE
LI'I-rEL
LITTEL
MOONEY
MOONEY
-- AMP
AMP
AMP
AMP
AMP
AMP
AMP
SOCKETS
AMP
LOADMETER (SINGLE)
B& D
LOADMETER (DUAL)
B& D
AMMETER
MOONEY
UGHT BULBASSY
ROCHESTER
BULB
GE
CONN, AMMETER
S.E.C.
CONN, AMMETER (ALl')
BENDIX
SWITCH, PUSH, VOLTAGE
C-H
LIGHT BULB ASSY
ROCHESTER
(ALT)
ROCHESTER
BULB
GE
SHUNT, AMMETER (ALT'NR #1) EMPRO
SHUNT, AMMETER (ALT'NR)
EMPRO
FUSEHOLDER (+ ALl" # 1)
McGRAW-EDISON
FUSE, 5A
McGRAW-EDISON
FUSEHOLDER (- ALE# 1)
McGRAW-EDISON
FUSE, 5A
McGRAW-EDISON
SHUNT, AMMETER, LOAD
EMPRO
SHUNT, AMMETER, LOAD
EMPRO
SHUNT, AMMETER, LOAD
EMPRO
SHUNT, AMMETER, LOAD
EMPRO
FUSEHOLDER (-LOAD)
McGRAW-EDISON
FUSE, 5A
McGRAW-EDISON
FUSEHOLDER, (+LOAD)
McGRAW-EDISON
FUSE, 5A
McGRAW-EDISON
.AMMETER, SHUNT (ALT #2)
EMPRO
AMMETER, SHUNT (ALT.)
EMPRO
FUSEHOLDER (+ ALT. #2)
McGRAW-EDISON
FUSE, 5A
McGRAW-EDISON
12-98
NOTES
WA2-G056S502UA
206060-1
206062-1
208153-1
206062-1
60619-1
0326-004
0326-003
640281-509
0105S00004
313
PW06B12-10S
PT06A-12-10S-SR
SA31SDT12-1
0105S00003
0153500003
313
MLA-70A-50MV
MLA-55A-50MV
FHN42W
FM01-5A
FHN42W
FM01-5A
MLB-210A-50MV
MLB-165A-50MV
MLB-105A-50MV
MLA-60A-100MV
FHN42W
FM01-5A
FHN42W
FM01-5A
MLA-70A-50MV
MLA-55A-50MV
FHN42W
FM01-5A
5
5
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
JK--
DAl12A
FUSEHOLDER (- ALT. #2)
FUSE, 5A
McGRAW-EDISON
McGRAW-EDISON
FHN42W
FM01-5A
--L
--L
--L
--L
DA150A
DA151A
DA152A
DA153A
---L
DA154A
C/B VOLT/AMP IND, LT
C/B VOLT/AMP IND, RT
INDICATOR, VOLT/AMP, RT
PLUG, VOLT/AMP IND
CLAMP
LOCK RETAINER
INDICATOR, VOLT/AMP, RT
KLIXON
KLIXON
PENN AIRBORNE
ITT
I'1-1"
ITT
PENN AIRBORNE
7277-2-1
7277-2-1
9A1570
DA15S
DA51210
DA51220-1
9A1570
--L
DA155A
--L
--L
---L
--L
--L
DA156A
DA157A
DA158A
DA159A
DA160A
--L
-
DA161A
--L
DA162A
--L
DA163A
DA164A
--L
---L
DA165A
--L
DA167A
JKL
JKJKJKL
DB101A
DB102A
DB102B
DB103A
--L
DB150A
JK--L
--L
--L
DC101A
DC150A
DC151A
DC152A
--L
DC153A
--L
DC154A
--L
DC155A
DA166A
PLUG, VOLT/AMP IND
ITT
CLAMP
ImLOCK RETAINER
InSHUNT, LEFT LOAD
EMPRO
SHUNT, LEFT ALTERNATOR
EMPRO
SHUNT, RIGHT LOAD
EMPRO
SHUNT RIGHT ALTERNATOR EMPRO
FUSEHOLDER, LT LOAD SHUNT (-) McGRAW-EDISON
FUSE 5A
McGRAW-EDISON
FUSEHOLDER, LT LOAD SHUNT(+) McGRAW-EDISON
FUSE 5A
McGRAW-EDISON
FUSEHOLDER, LT ALT SHUNT (+) McGRAW-EDISON
FUSE 5A
McGRAW-EDISON
FUSEHOLDER, LT ALT SHUNT (-) McGRAW-EDISON
FUSE 5A
McGRAW-EDISON
FUSEHOLDER,RTLOAD SHUNT(+) McGRAW-EDISON
FUSE 5A
McGRAW-EDISON
FUSEHOLDER, RT LOAD SHUNT (-) McGRAW-EDISON
FUSE 5A
McGRAW-EDISON
FUSEHOLDER, RT ALT SHUNT (-) McGRAW-EDISON
FUSE 5A
McGRAW-EDISON
FUSEHOLDER, RT ALT SHUNT (+) McGRAW-EDISON
FUSE 5A
McGRAW-EDISON
DA15S
DA51210
DA51220-1
MLA-105A
MLA-70A-50MV
MLA-105A
MLA-70A-50MV
FHN42A
FM01-5A
FHN42A
FM01-5A
FHN42A
FM01-5A
FHN42A
FM01-SA
FHN42A
FM01-SA
FHN42A
FM01-5A
FHN42A
FM01-5A
FHN42A
FM01-5A
C/B TURN COORD
TURN CO-ORDINATOR
TURN CO-ORDINATOR
PLUG, TURN COORD
CABLE CLAMP
TURN COORDINATOR
KLIXON
U.I.
ASTRONAUTICS
7277-2-2
9013CODE N.5
303990-028MSC
MS3106A-10SL-3S
MS3507-4A or-4B
9551B CODE N.541
CYL HD TEMP PROBE
C/B OIL TEMP/CHT
CHT/OIL TEMP IND
PLUG, CHT/OIL TEMP
CLAMP
LOCK RETAINER
-SWITCH, CHT
KNOB
PLUG, CHT, 16 PIN
, CLAMP
RECPT, CHT, 16 PIN
CLAMP
MOONEY
KUXON
PENN AIRBORNE
I1[
ITT
I'I-T
GRAY HILL
RAYTHEON
AMP
AMP
AMP
AMP
UI
12-98
_
NOTES
50MN
50MN
880010-503
7277-2-1
9A1630
DB25S
DB51212
DB51221-1
71AD30-02-2-AJN
50-3-1G
206037-1
206070-1
206036-3
206070-1
91-20-02
37
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
--L
--L
--L
---L
--L
-_-
DESCRIPTION
DC156A
DC157A
DC158A
DC159A
DC160A
DC161A
VENDOR
PROBE, CHT-CYL #1
PROBE, CHT-CYL #2
PROBE, CHT-CYL #3
PROBE, CHT-CYL #4
PROBE, CHT-CYL #5
PROBE, CHT-CYL #6
PART NO.
MS24482-1 **
MS24482-1 **
MS24482-1 **
MS24482-1 **
MS24482-1 **
MS24482-1 **
** AN5546-1 (ALT) -EITHER REQUIRES AN4076-1 ADAPTER
J-J-J_
J--
DD101A
DD102A
DD102B
DD103A
C/B, OAT/EGT
KLJXON
GAUGE, OAT/EGT
MOONEY
GAUGE, OAT/EGT, 4 PROBE (OPT) B & D
PLUG,, OAT/EGT
AMP
7277-2-2
880001-507
0230-003
205838-1
CLAMP, CABLE
AMP
206062-1
MOONEY
KUXON
PENN AIRBORNE
ITr
ITT
I-ri-
880004-501
7277-2-1
9A1580
DA15S
OA51210
DA51220-1
JKL
--L
--L
--L
DD104A
DD150A
DD151A
DD152A
PROBE, OAT
C/B OAT IND
INDICATOR, OAT
PLUG, OAT
CLAMP
LOCK RETAINER
J-J-JKL
JKL
-KL
-KL
--L
DF101A
DF103A
DF102A
DP104A
DF105A
DF106A
DF150A
TRANSMTR, FUEL QTY, LT, I/B MOONEY
TRANSMTR, FUEL QTY, RT, I/B MOONEY
TRANSMITTER, FUELQTY, O/B, LT MOONIEY
TRANSMITTER, FUEL QTY, O/B, RT MOONEY
TRANSMI]-rER, FUEL QTY, I/B, LT MOONEY
TRANSMI'I-I'ER, FUEL QTY, I/B, RT MOONEY
C/B FUEL QTY',LH/RH
KLIXON
610242-001
610242-001
610243-003
610243-001
610242-003
610242-003
7277-2-1
--L
--L
DF151A
DP152A
FUEL QTY IND, L/R
PLUG, FUEL QTY, L/R
CLAMP
LOCK RETAINER
PENN AIRBORNE
ITT
ITT
I'l-l"
9A1620-2
DB25S
DB51212
DB51221-1
JKJ--K--L
--L
--L
DG101A
DG102A
DG103A
DG150A
DG151A
DG152A
--L
--L
DG153A
DG154A
--L
DG155A
--L
DG156A
--L
DG157A
--L
DG158A
C]B, CLUSTER GAUGE
GAUGE, CLUSTER
GAUGE, CLUSTER
C./BINSTRUMENT DISPLAY
INSTRUMENT DISPLAY
PLUG, INSTR. DISPLAY
CLAMP
LOCK RETAINER
C/B INSTRUMENT P]-r
SWITCH, INSTRUMENT PTT
CAP, BLACK
PLUG, 9 PIN, P-I-r
CLAMP
RECPT, PTT, 9 PIN
CLAMP
PLUG, GRND #7, 28 PIN
CLAMP
' RECPT, GRND #7, 28 PIN
•CLAMP
KLIXON
MOONEY
MOONEY
KLIXON
PENN AIRBORNE
1"17I'IF
ITF
KUXON
ALCOSWlTCH
ALCOSWlTCH
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
7277-2-5
640281-523
640281-525
7277-2-1
9A1600-2
DB25S
DB51212
DB51221-1
7277-2-1
MPE106F
0-22
206708-1
206966-1
206705-2
206966-1
205839-3
206070-1
206152-1
206070-1
91-20-02
38
12-93
NOTES
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
JK-
DH101A
--L
DH150A
JKJK-
DJ101A
DJ102A
--L
DJ150A
--L
DJ151A
--L
DJ152A
JK-
DJ175A
JKJK-
DJ176A
DJ178A
JK-
DJ179A
JK-
DJ180A
JK-
DJ181A
J-J---L
--L
--L
DK101A
DK102A
DK150A
DK151A
DK152A
--L
DK153A
--L
---L
DK154A
J--
DK175A
J-J--
DK176A
DK177A
J--
DK178A
J--
DK179A
J--
DK180A
J--K-K-K-
DL101A
DL102A
DL102B
DL102C
DK155A
DESCRIPTION
VENDOR
PART NO.
PROPE, OIL TEMP
WASHER
PROSE, OIL TEMP
MOONEY
880009-501
AN900-10 or MS35769-11
938.606.002.00
XDUCR, OIL PRESS
PLUG, OIL PRESS
CLAMP, CABLE
XDUCER, OIL PRESS
MOONEY
PLUG, OIL PRESS, 4 PIN
CLAMP
RECPT, OIL PRESS, 4 PIN
CLAMP
XDUCR, OIL PRESS
(ALl')
AMPUFIER, OIL PRESS
PLUG, 4 PIN
CLAMP
RECPT, 4 PIN
CLAMP
PLUG, 4 PIN
CLAMP
RECPT, 4 PIN
CLAMP
AMP
AMP
AMP
AMP
DRUCK
KULITE
IAI
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
XDUCR, FUEL PRESS
PLUG, FUEL PRESS XDUCR
C/B FUEL/OIL PRESSURE
INDICATOR, FUEL/OILPRESS
PLUG, FUEL/OIL PRESS
CLAM P
LOCK RETAINER
XDUCER, FUEL PRESS
MOONEY
PLUG, FUEL PRESS, 4 PIN
CLAMP
RECPT, FUEL PRESS, 4 PIN
CLAMP
XDUCR, FUEL PRESS
(ALl)
AMPLIFIER, FUEL PRESS
PLUG, 4 PIN
CLAMP
RECPT, 4 PIN
CLAMP
PLUG, 4 PIN
CLAMP
RECPT, 4 PIN
CLAMP
AMP
AMP
AMP
AMP
DRUCK
KULITE
IAI
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
PORSCHE
DRUCK
KLIXON
PENN AIRBORNE
ITT
ITI"
I-I-r
DRUCK
TACHOMETER (POINTS)
MOONEY
TACHOMETER
MOONEY
,TACHOMETER
MOONEY
TACH (RPLCMT FOR - DL102B) MOONEY
B& D
12-98
NOTES
880046-501
MS3106A10SL-3S
MS3057-4A/B
PDCR 821-0662
(100 PSIG)
206060-1
206062-1
206153-1
206062-1
PDCR821-0662-100
APT-154-1000-100PSIG
950D0811-003
206060-1
206062-1
206153-1
206062-1
206060-1
206062-1
206158-1
206062-1
880045-501
MS3106A10SL-SS
7277-2-1
9A1640
DB25S
DB51212-1
DB51221-1
PDCR 821-0062
(100 PSIG)
206060-1
206062-1
206153-1
205062-1
PDCR821-0662-30
APT-153-1000-30PSIG
950D0311-001
206060-1
206062-1
260163-1
206062-1
206060-1
206062-1
260163-1
206062-1
880039-511
880039-509
880039-513
880039-517
0520-006
91°20-02
39
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
JK-K-JK-
DL103A
DL103A
JK-
DL105A
J-J_
DLIO7A
DL108A
PLUG-TACH
TACH SENSOR
TACH SENSOR (ALl')
RECPT, 4 PIN
CLAMP
PLUG
CLAMP
TACHOMETER
TACH GENERATOR
J-J
DL109A
DLl10A
CABLE ASSY
TACHOMETER
--L
---L
DL150A
DL151A
DL152A
DL153A
PENN AIRBORNE
ITT
I'Cl"
13-1"
PORSCHE
PORSCHE
DL104A
B& D
B& D
AMP
AMP
AMP
AMP
MOONEY
MOONEY
B &D
MOONEY
MOONEY
B&D
--L
DL157A
DL158A
DIODE, RPM/FUEL FLOW, LT
DIODE, RPM/FUEL FLOW, RT
INDICATOR, RPM/FUEL FLOW
PLUG, RPM/FUEL FLOW
CLAMP
LOCK RETAINER
SENSOR, RPM #2, RT
SENSOR, RPM #1, LT
J
-KL
DM101A
DM102A
DM150A
HOUR METER
HOUR METER
HOUR METER
MOONEY
MOONEY
AIRPAX
--L
DM151A
--L
DM152A
RECPT, HOUR METER, 4 PIN
CLAMP
PLUG, HOUR METER, 4 PIN
CLAMP
AMP
AMP
AMP
AMP
JKL
JKJKl.
DPIO1A
DP101A
DP102A
C/S, PITOT HEAT
C/B, PITOT HEAT (SPARES)
PITOT, HEATED
MOONEY
MOONEY
AERO INST
JKL
DP103A
JKJKJK-JK-
DP104A
DPIO4B
DPIO5A
JK-
DP107A
JKL
---L
L
DP108A
DP150A
DP150B
DP151A
L
DP152A
91-20-02
40
DP106A
PLUG, PITOT HEAT
SOCKETS
BOARD ASSY
MOONEY
CURRENT MONITOR (SPARES) MOONEY
FUSEHOLDER
LITI'EL
FUSE, 1A
LI]-rEL
PLUG
AMP
SOCKETS
AMP
RECPT
AMP
PINS
AMP
MGHT ASSY
MOONEY
RELAY BOX, CURRENT DETECTOR MOONEY
RELAY BOX, CURRENT DETECTOR MOONEY
PLUG, CUR/DECT RELAY
AMP
CLAMP
AMP
FUSEHOLDER
LI'I-FEL
. FUSE, 5A-SAG-SLO-BLO
LI'I-I'EL
12-98
PART NO.
NOTES
MS3106A14S-SS
0402-102
0402-104
206183-1
206662-1
206060-1
206062-1
880039-507
880053-501
0400-004
680003-501
680039-515
0620-003
1N2483
1N2483
9A1610-2
DB25S
DB51212
DB51221-1
933.602.002.01
933.602.002.01
880035-507
880035-505
K4205 ***
*** K4207 or KF4207 (ALl-)
206153-1
206062-1
206060-1
206062-1
930023-205
930023-241
PH502-24****
**** AN5812-1 (ALT)
AN3115-1
AN3116-1
940002-001
800221-501
155020 or 155120
313001
1-480303-0
60619-1
1-480305-0
60620-1
800346-503
800221-501
800221-503
206660-1
206062-1
155020 or 155120
313065
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
C/B, TIT
INDICATOR, TIT
INDICATOR, T1T/EGT
PLUG, TIT
CLAMP
PLUG, 28 PIN
CLAMP
PROBE, TIT
PROVE, TIT (ALl')
PROBE, TIT
KLIXON
MOONEY
MOONEY
AMP
AMP
AMP
AMP
MOONEY
MOONEY
MOONEY
7277-2-2
890051-501
880051-503
205838-1
206062-1
205839-3
206070-1
880005-501
680005-503
680055-501
PROBE, EGT - CYL#1
PROBE, EGT - CYL #1 (ALl)
PROBE, EGT - CYL #1 (ALl-)
PROBE, EGT- CYL #1
PROBE EGT- CYL #1 (ALT)
PROBE EGT- CYL #2
PROBE EGT- CYL #2 (ALT)
PROBE EGT-CYL #3
PROBE EGT-CYL #3 (ALl')
PROBE EGT-CYL #4
PROBE EGT-CYL #4 (ALl')
PROBE EGT-CYL #5
PROBE EGT-CYL #5 (ALl')
PROBE EGT-CYL #6
PROBE EGT-CYL#6 (ALE)
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
880005-501
880005-503
660110-000
889005-501
880005-503
880005-501
880005-503
880005-501
680005-503
580005-501
880005-503
880005-501
880005-503
880005-501
880005-503
-K-K-K-K-
DR101A
DRIO2A
DR102B
DR103A
-K-
DR103B
-K-K-K-
DR104A
DRIO4A
DRIO4B
J--
DT101A
-K-
DT101A
-K-
DTIO2A
-K-
DT103A
-K-
DT104A
-K-
DT105A
-K-
DT106A
JKJKJKJKJKJKJKJKJK--L
DV101A
DV102A
DV102B
DV102C
DV103A
DV104A
DV104A
DV104C
DV105A
DV150A
C/B, FUEL FLOW
KLIXON
INDICATOR, FUEL FLOW
MOONEY
INDICATOR, FUEL FLOW(OPT) MOONEY
INDICATOR, FUEL FLOW (OPT) MOONEY
PLUG, FUEL FLOW
CANNON
XDUCR, FUEL FLOW
MOONEY
XDUCR, FUEL FLOW (OPT)
MOONEY
XDUCR, FUEL FLOW (OPT)
MOONEY
SWITCH FURE FLOW MEMORY C & K
XDUCER, FUEL FLOW
PORSCHE
--L
DV151A
PLUG
CLAMP
BOOT
CONTACTS
--L
--L
--L
--L
DW150A
DW151A
DW151A
DW151A
INDICATOR, VERTICAL SPEED UI
PLUG, VSI, 3 PIN
BENDIX
PLUG, V/S (ALT)
CANNON
PLUG, VSI (ALT)
CLAMP
7201-2 CODE C.146
PTO6E-8-SS
KPTO6E-8-SS
MS3116-8-3S
MSS057-3Aor -3B
JKL
JKL
JKL
EGIO1A
EGIO2A
EGI03A
C/B GEAR RELAY
SWITCH, GEAR UP/DN
SWITCH, GEAR OVERIDE
LOCKING RING
LOCK WASHER
HEX NUT (2 EA)
LAMP (28 V)
7277-2-5
8906K2875
SBIDDX492-2
29-761
16-886
15-966-6
388
PORSCHE
PORSCHE
PORSCH E
PORSCHE
KLIXON
C-H
C-H
C-H
C-H
C-H
GE
12-98
NOTES
7277-2-2
860084-501
880034-507
880034-513
DE-9S
880030-501
880030-503
880030-505
7101K
933-110-377-02
(FUELCONTROL)
933-612-403-00
999-615-032.-40
944-612-128-00
999-652-456-22
91-20-02
41
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
JKL
JKL
JKL
EG104A
EGIO5A
EGIO6A
JKL
JKL
JKL
JKL
JKL
JKL
JKL
EGIOTA
EG1OTA
EG106A
EG109A
EG110A
EG110A
EG111A
JKL
EG112A
JKL
JKL
ELT101A
_ ELT101A
JKL
L
---L
--
ELT102A
ELT150A
JK--L
--L
--L
--L
--L
--L
--L
PART NO.
SWITCH, GEAR SAFETY(NSPEED) MOONEY
C/B, GEAR ACTUATOR
KLIXON
SWITCH, GEAR UP LIMIT
MICRO SWITCH
ACTUATOR
MICRO SWITCH
SWITCH, GEAR DN UMIT
MICRO SWITCH
SWITCH, GEAR DN LIMIT (ALT) SAINT SWlTCH,INC
RELAY, GEAR UP
C-H
RELAY, GEAR DOWN
C-H
ACTUATOR, LANDING GEAR
MOONEY
ACTUATOR, LDG. GR (ALT)
MOONEY
DIODE,GEAR UP RELAY
LOCK RETAINER
I'IF
DIODE, GEAR DOWN RELAY
680013-507
7277-2-15
DT-2R-A7
MCD-2711
ICHI-6
MLl116
6041H220
6041H220
560254-503
880037-507
1N2483
DB51221-1
1N2483
SWITCH, REMOTE ELT
SWITCH,REMOTE ELF (ALT)
D &M
C &K
DM-U65-1
7101K
ELT TRANSMI'I-I'ER
PLUG, ELT
CLAMP
RECPT, ELT
CLAMP
D&M
AMP
AMP
AMP
AMP
DM-ELT-8
206060-1
206062-1
206153-1
206062-1
FON101A
PHONE-JACK
WASHERS
SWlTCHCRAFT
SWITCHCRAFT
C-11
S-1028 & S-1029
JE150B
JE151B
JE152B
JE153B
JE154B
JE154B
JE154B
C/B IGNITION, LT
KLIXON
C./BIGNITION, FIT
KUXON
IGNITION BOX, LT
PORSCHE
IGNITION BOX, RT
PORSCHE
PLUG, IGN BOX, LT
CANNON
PLUG, IGN BOX, LT (ALE)
CANNON-GERMANY
PLUG, IGN BOX, LT (ALT)
PORSCHE
TINEL-LOCK ADAPTER
RAYCHEM
ADAPTER (AL'r)
SUNBANK
BOOT
RAYCHEM
BOOT (ALT/SUPPLEMENT)
RAYCHEM
PLUG, IGN BOX, RT (ALT)
CANNON-GERMANY
PLUG, IGN BOX, RT (ALT)
PORSCHE
TINEL-LOCK ADAPTER
RAYCHEM
ADAPTER (ALT)
SUNBANK
BOOT
RAYCHEM
BOOT (ALT/SUPPLEMENT)
RAYCHEM
PLUG, IGN BOXCOIL LT (ALT) CANNON-GERMANY
PLUG, IGN BOX COIL, LT (ALT) PORSCHE
TINEL-LOCK ADAPTER
RAYCHEM
ADAPTER (ALT)
SUNBANK
ADAPTER (ALT)
SUNBANK
COUPLING
SUNBANK
BOOT
RAYCHEM
PLUG, IGN BOX COIL, RT (ALT) CANNON-GERMANY
PLUG, IGN BOX COIL, RT (ALT) PORSCHE
.TINEL-LOCK ADAPTER
RAYCHEM
ADAPTER (ALT)
SUNBANK
ADAPTER (ALT)
SUNBANK
COUPLING
SUNBANK
BOOT
RAYCHEM
ELT151A
JE155B
JE155B
--L
--L
JE156B
JE156B
--L
--L
JE157B
JE157B
91-20-02
42
VENDOR
12-99
NOTES
7277-2-7.5
7277-2-7.5
933.602.007.07
933.602.007.07
CA3106A-20A-48S-B-03
CA3106A-20A-48S-B-15
933.612.440.00
"T'XR18AB45-C2012AI
S2900AA1912AI-S034-O00
202C621-51/164
202S142-25S
CA3106A-20A_48S-B-15
933.612.440.01
TXR16AB45-C201PAl
S2900AA1912AI-SO34-000
202C621-51/164
202S142-25S
CA3106E-10SL-3P-B-14
933.612.409.01
TXR18AB00-C1104AI
S2900ASO604AI-S034-000
S2909AS1004AI-SO34-000
S3292
202S121-25S
CA3106E-1OSL-3P-B-14
933.612.409.01
TXR18ABOO-C1104AI
S2900AS0504AI-S034-000
S2900AS1004AI-S034-000
$3292
202S121-25S
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
--L
--L
JE162B
JE162B
--L
JE163B
JE163B
--L
--L
--L
--L
--L
JE164A
JE165A
JE168A
JE169A
JE170C
---L
JE171C
--
--L
JE172B
--L
JE173B
--L
JE174C
---L
JE175C
DESCRIPTION
VENDOR
PART NO.
PLUG, IGN COIL, LT
PLUG, IGN COIL, LT
TINEL-LOCK ADAPTER
ADAPTER (ALT)
ADAPTER (ALT)
COUPLING
BOOT
PLUG, IGN COIL, RT
PLUG, IGN COIL RT
TINEL-LOCK ADAPTER
ADAPTER (ALT)
ADAPTER (ALl')
COUPLING
BOOT
CANNON-GERMANY
PORSCHE
RAYCHEM
SUNBANK
SUNBANK
SUNBANK
RAYCHEM
CANNON-GERMANY
PORSCHE
RAYCHEM
SUNBANK
SUNBANK
SUNBANK
RAYCHEM
CA3106E-10SL-4S-B-14
933.612.407.01
TXR18AB00-C1104AI
S2900AS0504AI-S034-000
S2900AS1004AI-S034-O00
S3292
202S121-25S
CA3106E-10SL-4S-B-14
938.612.407.01
TXR18AB00-C1104AI
S2900AS0504AI-S034-O00
S2900AS1004AI-S034-000
$3292
202S121-25S
IGNITION COIL, LT
IGNITION COIL, RT
SENSOR, TDC #1
SENSOR, TDC #2
RECPT, 3 PIN
RECPT, 3 PIN (ALT)
ADAPTER
ADAPTER (ALl")
ADAPTER (ALE)
COUPLING
BOOT
PLUG, 3 PIN
PLUG, 3 PIN (ALT)
ADAPTER
ADAPTER (ALT)
ADAPTER (ALl')
COUPLING
BOOT
RECEPT, IGN, COIL, LT, 4 PIN
ADAPTER
ADAPTER (ALT')
BOOT
PLUG, IGN, COIL, LT,4 PIN
ADAPTER
ADAPTER (ALT)
BOOT
RECPT, 3 PIN
RECPT, 3 PIN (ALl)
ADAPTER
ADAPTER (ALE)
ADAPTER (ALT)
COUPLING
BOOT
PORSCHE
PORSCHE
PORSCHE
PORSCHE
CANNON-GERMANY
PORSCHE
RACHEM
SUNBANK
SUNBANK
SUNBANK
RAYCHEM
CANNON-GERMANY
PORSCHE
RACHEM
SUNBANK
SUNBANK
SUNBANK
RAYCHEM
CANNON
RAYCHEM
SUNBANK
RAYCHEM
CANNON
RAYCHEM
SUNBANK
RAYCHEM
CANNON-GERMANY
PORSCHE
RACHEM
SUNBANK
SUNBANK
SUNBANK
RAYCHEM
N/A
N/A
N/A
N/A
CA121001-633
983-612-411-00
TXR18AB000-C1104AI
S2900AS0604AI-S034-O00
S2900AS1004AI-S034-OO0
$3292
202S121-25S
CA06EH10Sl-3PB14
983-612-412-00
TXR18AB000-C1104AI
S2900AS0804AI-S034-000
S2900AS1004AI-S034-O00
$3292
202S121-25S
MS3100K-14S-2P
"rXR18AB000-C1404AI
$2900AS1004AI-S034-000
202S121-25S
MS3106E-14S-2S
TXR18AB000-C1404AI
S2900AS1004AI-S034-000
202S121-25S
CA121001-633
933-612-411-00
TXR18AB000-C1104AI
S2900AS0604AI-S034-000
$2900AS1004AI-S034-000
$3292
202S121-25S
PLUG, 3 PIN
PLUG, 3 PiN (ALT)
ADAPTER
. ADAPTER (ALE)
ADAPTER (ALT)
COUPLING
BOOT
CANNON-GERMANY
PORSCHE
RACHEM
SUNBANK
SUNBANK
SUNBANK
RAYCHEM
CA06EH10SL3PB14
933-612-412-00
TXR18AB000-C1104AI
S2900AS0604AI-S034-000
S2900AS1004AI-S034-000
$3292
202S121-25S
12-98
NOTES
91-20-02
43
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
--L
JE176B
--L
---
JE177B
--L
JE178A
--L
JE179A
--L
JE180A
--L
JE181A
--L
JE182A
--L
--
JE183A
JKI_
JM101A
J-J--K-
PART NO.
NOTES
RAYCHEM
SUNBANK
RAYCHEM
AMP
AMP
AMP
AMP
AMP
AMP
MS3100K-14S-2P
TXR18AB000-C1404AI
S2900AS1O04AI-S034-000
202S121-25S
MS3106E-14S-2S
"FXR18ABO0O-C1404AI
S2900AS1004AI-S034-O00
202S121-25S
1-490303-0
60619-1
1-480305-0
60620-1
1-480318-0
60619-1
RECPT, C/B, 2 PIN
PINS
PLUG, TACH/FUEL FLOW
SOCKET
RECPT, TACH/FUEL FLOW
PINS
AMP
AMP
AMP
AMP
AMP
AMP
1-480319-0
60820-1
1-480318-0
60619-1
1-480319-0
60620-1
JM102A
JMIO2B
JM103A
SWITCH, IGNITION
PLACARD
MAGNETO
MAGNETO (ALl')
MAGNETO, RIGHT
-K-K-
JMIO3B
JM104A
MAGNETO, RIGHT
MAGNETO, LEFT
-K-
JMIO4B
MAGNETO, LEFT
BENDIX- SCINTILIJk
BENDIX- SCINTILLA
BENDIX-SCINTILLA
BENDIX-SCINTILLA
BENDIX-SCINTILLA
TCM
SUCK
BENDIX-SCiNTILLA
TCM
SLICK
10-357210-9
10-187-468
10-682555-1
10-682555-111
10-79020-120
640896-1
6224
10-79020-120
640896-1
6224
JKJKJK-
LB101A
LB101A
LB102A
JKL
JKL
JKL
LB102B
LB102B
LB103A
JKL
LB104A
C/B, ROTATING BEACON
MOONEY
C/B, ROTATING BCN (SPARES) MOONEY
LIGHT, ROTATING BCN
WHELEN
ADAPTER
WHELEN
LT, ROTATING BCN, RED (ALl') WHELEN
LT, ROTATING BCN, WTE (ALT) WHELEN
PLUG, 2 PIN
AMP
SOCKET
AMP
RECPT, 2 PIN
AMP
PINS
AMP
930023-203
930023-243
WRML-24
WRM-65
90033-19
90033-20
1-480318-0
60619-1
1-480319-0
60820-1
JKL
LC101A
JKL
JKL
JKL
-JKL
-JKL
LC102A
LC103A
LC104A
JKL
--
LC107A
FUSEHOLDER, CLOCK, 5AMP UTTEL
FUSE,(5A-3AG-SLO-BLO)
LI-I-FEL
SWITCH, CABIN LIGHT, FWD
CARLING
RESISTOR, CABIN LIGHT, FWD DALE
LIGHT, CABIN, FWD, LT
H.H. SMITH
LAMP
GE
UGHT, CABIN, FWD, RT
H.H. SMITH
LAMP
GE
LIGHT, CABIN, FWD, LT
H.H. SMITH
LAMP
GE
'LIGHT, CABIN, FMVD,RT
H.H. SMITH
LAMP
GE
155020/155120
313005
TILC64-1S-WH-FN
RH-10-20 OHM
1930
1818
1930
1818
1930
1818
1930
1818
91-20-02
44
LC105A
LC106A
RECPT, IGN. COIL, RT, 4 PIN
ADAPTER
ADAPTER (ALT)
BOOT
PLUG, (ALl-)
ADAPTER
ADAPTER (ALT)
BOOT
PLUG, 3 PIN
SOCKET
RECPT, C/B, 3 PIN
PINS
PLUG, 2 PIN
SOCKET
VENDOR
RAYCHEM
SUNBANK
FIAYCHEM
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
JKL
JKl.
JKL
-JKL
-JKL
-JKL
---L
---L
--
LC108A
LC109A
LC110A
J-J-JK-
LL101A
LL102A
LL103A
JK-
LL104A
-K-K-K-K-K--L
LL105A
LL106A
LL107A
LL108A
LL109A
LL150A
--L
LL151A
--L
--L
--L
--L
--L
--L
LL152A
LL154A
LL155A
LL156A
LL157A
LL158A
JKL
JKL
LN101A
LN102A
JKL
JKL
LN103A
LN104A
JKL
LN105A
JKL
LN106A
JKL
LN107A
JKL
JKL
JKL
LP101A
LP102A
LP103A
LC111A
LC112A
LC113A
LC114A
LC115A
VENDOR
PART NO.
SWITCH, CABIN LIGHT, REAR CARLING
RESISTOR, CABIN LIGHT SW DALE
LIGHT, CABIN, REAR, LT
H.H. SMITH
LAMP
GE
LIGHT, CABIN, REAR, RT
H.H. SMITH
LAMP
GE
LIGHT, CABIN, REAR, LT
H.H. SMITH
LAMP
GE
LIGHT, CABIN, REAR, RT
H.H. SMITH
LAMP
GE
LIGHT, CABIN, REAR, LT
H.H. SMITH
LAMP
GE
LIGHT, CABIN, REAR, RT
H.H. SMITH
LAMP
GE
TILC64-1S-WH-FN
RH-10-20 OHM
1930
1818
1930
1818
1930
1818
1930
1818
1930
1818
1930
1818
SWITCH, LDG LT
LANDING LIGHT
RECPT, LDG LT
CLAMP
PLUG, LDG LT
CLAMP
C/B, LDG LT, LEFT
LIGHT, LDG, LEFT
C/B, LDG LT, RIGHT
LIGHT, LDG, RIGHT
SWITCH, LDG LT
C/B, LANDING LIGHT, LEFT
C/B, LDG LT, LEFT (ALl')
C/B LANDING UGHT, RIGHT
C/B, LDG LT, RIGHT (ALl')
SWITCH, LANDING LIGHT
LANDING LIGHT-RT WING
TAXI LIGHT-RT WING
SWITCH, TAXI LIGHT
TAXI LIGHT, LEFTWING
LANDING UGHT, LEFT WING
MOONEY
GE
AMP
AMP
AMP
AMP
KLIXON
GE
KUXON
GE
C-H
KU×ON
MECHANICAL PROD
KUXON
MECHANICAL PROD
C-H
GE
GE
C-H
GE
GE
930023-235
4553
206153-1
206062-1
206060-1
206062-1
7277-2-10
4596
7277-2-10
4596
8143-K21-E13-M50
7277-2-20
4200-002-25
7277-2-20
4200-002-25
8162-K22-E13-M50
4596
4596
8162-K22-E13-M50
4596
4596
C/B NAV LIGHTS.
UGHT, TAIL, LT WING
BULB, 28V
LIGHT, TAIL RT WING
PLUG, TAIL LIGHT, RT WING
SOCKETS
RECPT, TAILUGHT RTWlNG
PINS
PLUG, TAIL NAV UGHT
SOCKETS
RECPT, TAIL NAV LIGHT
PINS
MOONEY
MOONEY
WHELEN
MOONEY
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
930023-201
800051-501
34-0228030-85
800051-501
1-480318-0
60619-1
1-480319-0
60620-1
1-480318-0
60619-1
1-480319-1
60620-1
C/B PANEL LIGHTS
. C/B GLARESHIELD LIGHTS
LAMP, COMPASS LIGHT
KLIXON
KLIXON
GE
7277-2-5
7277-2-5
AVIATION RED 327
or327
12-98
NOTES
91-20-02
45
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
JKJKL
JKL
JK-
LP104A
LP105A
LP106A
LP107A
JK-
LP108A
JKJK-
LP109A
LP109B
JKJKJKJKJKJK-
LP110A
LP111A
LP112A
LPl13A
LP114A
LP115A
JKJKJKJKJKJKJK-KJK---!---L
LP116A
LP118A
LP119A
LP120A
LP121A
LP122A
LP123A
LP125A
LP126A
LP150A
LP151A
--L
LP162A
--L
--L
LP153A
LP154A
LP155A
L
LP156A
--L
LP157A
L
LP158A
--L
LP159A
--L
LP160A
JKL
JKL
JKL
LR101A
LR102A
LR103A
91-20-02
46
VENDOR
PART NO.
RECPT, COMPASS LT
DEANS
PLUG, COMPASS LIGHT
DEANS
LIGHTS, GLARESHIELD (14 EACH) GE
LIGHT HOLDER, TRIM/FLAP
DIAUGHT
LAMP
GE
LAMP (ALT)
GE
UGHT, COWL FLAP
DIAUGHT
LAMP
GE
LIGHT, OXYGEN
SLOAN
LIGHT, OXYGEN
SLOAN
LAMP
GE
LIGHT, CLUSTER
GE
LIGHT, CLUSTER
GE
LIGHT, CLUSTER
GE
LIGHT, CLUSTER
GE
LIGHT, CLUSTER
GE
UGHT TRAY, AMMETER
B&D
DEAg0020MALE
DEAg002OFEMALE
827
270-1930-0171-702
327
385
270-1930-0171-702
327
855S-0-U
865S-0-U
327
327
327
327
327
327
0221-128
UGHTTRAY TACHOMETER
B&D
UGHT TRAY AIRSPEED
U.I.
LIGHT TRAY TURN CO-ORD
U.I.
LIGHT TRAY ALTIMETER
U.I.
LIGHT TRAY VERTICAL SPEED U.l.
UGHT TRAY ARTIFICIAL HORIZON SIGMA-TEC
UGHTTRAY DIRECTIONAL GYRO SIGMA-TEC
LIGHTTRAY TIT
B &D
LIGHT TRAY EGT/OAT
B &D
DIMMER CONTROL BOX
IAI
PLUG, DIMMER CONTROL BOX ITT
CLAMP
Ill"
LOCK RETAINER
I-[-r
RECPT (2 EA)
ITT
SWITCH, PANEL LIGHTS, DIMR C & K
0221-128
BA28-BW3
BA28-BW3
E]A28-BW3
BA28-BW3
IV-192-971
IV-192-971
0221-128
0221-126
950D0307-000
DBM17W2S
DB51212
D651221-1
DM53744-7
7105-JI-Z-Q
SWITCH, G/SHIELD LIGHTS, DIM C & K
LIGHT, FLAP SWITCH
MOONEY
LAMP
GE
UGHT, CONSOLE SWITCH, RT MOONEY
LAMP
GE
RECPT, 9 PIN
AMP
CLAMP
AMP
PLUG, 9 PIN
AMP
CLAMP
AMP
UGHT, CONSOLE SWITCH, LT MOONEY
LAMP
GE
PLUG, 16 PIN
AMP
CLAMP
AMP
RECEPT, DIMMER CONTROL BOX AMP
CLAMP
AMP
7105-J1-Z-Q
130285-003
327
130265-003
827
206706-2
206966-1
206708-1
206966-1
130285-003
327
206037-1
206070-1
206036-3
206070-1
C/B RECOGNITION LIGHTS
RECOGNITION LIGHT, LTWG
PLUG, RECOG. LIGHT, LT WG
SOCKETS
930023-231
660049-501
1-480318-0
60619-1
MOONEY
MOONEY
AMP
AMP
12-98
NOTES
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
JKL
JKL
LR104A
LR105A
JKL.
LR106A
JKL.
LR107A
JKL
JKL
-JKL
LR108A
LR109A
VENDOR
PART NO.
JKL
LR111A
RECOGNITION LIGHT, RT
MOONEY
PLUG, RECOG. LIGHT, RT
AMP
SOCKETS
AMP
RECPT, RECOG.LIGHT, LEFT AMP
PINS
AMP
PLUG, RECOG. LIGHT, LEFT
AMP
SOCKETS
AMP
RESISTOR, RECOG. LIGHT, LEFT DALE
RECPT, RECOG. LIGHT, RT
AMP
PINS
AMP
PLUG, RECOG. LIGHT, RT
AMP
SOCKETS
AMP
RESISTOR, RECOG. LIGHT, RT DALE
JKL
JKL
JKL
JKL
JKL
LS101A
LS101A
LS102A
LSIO3A
LSIO4A
C/B STROBE LIGHTS
MOONEY
O./13STROBE LIGHTS (ALT)
MOONEY
POWER SUPPLY, STROBE, LT WG WHELEN
RECPT, STROBE P/S, LTWG
AMP
RECPT, STROBE P/S,LT WG
AMP
930023-207
930023-287
01-0770329-00
1-480305-0
1-480305-0
JKL
JKL
JKL
JKL
JKL
JKL
JKL
JKL
LS105A
LS106A
LS107A
LS108A
LS109A
LS110A
LS111A
LSl12A
PLUG, NAV/STROBE, LTWG
AMP
LIGHT, NAV/STROBE, LTWG
WHELEN
STROBE PWR SUPPLY, RT WG WHELEN
RECPT, STROBE PWR SUPPLY, RT AMP
RECPT,STROBE LIGHT P/S, RT AMP
PLUG,STROBE UGHT, FIT
AMP
NAY/STROBE LIGHT RT. WING WHELEN
POWER SUPPLY, TAIL STROBEWHELEN
1-480303-0
A650-PR-D-M
01-07'/0329-00
1-480305-0
1-480305-0
1-480303-0
A650-PG-D-M
01-0770329-00
JKL
JKL
JKL
-JKL
LSl13A
LS114A
LSllSA
JKL
JKL
JKJKJK-
LS117A
LS118A
LSllgA
LS120A
LS121A
RECPT, TAIL STROBE PWR SUPPLY AMP
RECPT, TAIL STROBE PWR SUPPLY AMP
PLUG, TAIL STROBE
AMP
CLAMP
:
AMP
RECPT, TAIL STROBE
AMP
CLAMP
AMP
PLUG, TAIL STROBE
AMP
STROBE LIGHT, TAIL
MOONEY
RECPT
AMP
RECPT
AMP
RECPT
AMP
1-480305-0
1-480305-0
206060-1
206062-1
206153-1
206062-1
1-480303-0
470013-501
1-480305-0
1-480305-0
1-480305-0
JKL
JKL
MA101A
MA102A
JKL
JK-
MA103A
MA104A
ALJX.PWR. RECEPTACLE
RELAY, AUX. PWR
(ALT)
DIODE, AUX PWR RELAY
DIODE
AN2562-3A
6041H202
6041H202A
IOH3P
1N2483
JKL
MB101A
J-JKJ-JKL
JK-
MB101B
MB102A
MB102A
MBI03A
MB104A
LR110A
-
--
LS118A
AVIONICS CONTROL RELAY
BASE
DIODE
DIODE
DIODE
DIODE
' RELAY, AVIONICS MASTER
SOCKET
SPRING
STANDOFF
C-H
C-H
SARKES TARZ.IAN
MAGNACRAFT
MAGNACRAFT
P-B
P-B
P-B
P-B
12-98
880049-501
1-480318-0
60619-1
1-480319-0
60620-1
1-480318-0
60619-1
RH-50-7.5OHMS
1-480319-0
60620-1
1-480318-0
60619-1
RH-50-7.5 OHMS
NOTES
W67CSX-3
70-303
1N2463
1N2483
1N2483
IN2483
MB4443
27E122
20C176
21B212
91-20-02
47
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
JKJKL
J-JKL
JKL
JKL
JKL
JKL
JKL
JKL
JKL
JKL
JKL
JKL
JKL
JKL
JKL
JKL
JKL
MB104A
MB107A
MB107B
MBI09A
MB110A
MB111A
MB112A
MB113A
MB114A
MB115A
MB116A
MB117A
MB118A
MB119A
MB120A
MB121A
MB122A
MB123A
MB124A
RELAY, AVIONICS MASTER (ALT) P-B
SWITCH, AVIONICS MASTER C & K
SWITCH, MASTER, AVIONICS MOONEY
C/B HSI
KLIXON
C_ COM1
KUXON
C/B NAV1
KUXON
C/B AUDIO
KUXON
C/B PHONE
KUXON
C/B ADF
KUXON
C/S COM2
KUXON
C/B NAV2
KLIXON
C/B TRANSPONDER
KLIXON
C/B ENCODER
KLIXON
C/B AUTOPILOT/I"RIM
KLIXON
C/B RADAR
KLIXON
C/B DME
KLIXON
C/B LORAN
KUXON
C/B STORMSCOPE
KLIXON
C/B TELEPHONE
KLIXON
MB4443-1
7101K
930023-213
7277-2-XX(VARIES)
7277-2-XX(VARIES)
7277-2-XX(VARIES)
7277-2-XX(VARIES)
7277-2-XX(VARIES)
7277-2-XX(VARIES)
7277-2-XX(VARIES)
7277-2-XX(VARIES)
7277-2-XX(VARIES)
7277-2-XX(VARIES)
7277-2-_(VARIES)
7277-2-XX(VARIES)
7277-2-XX(VARIES)
7277-2-XX(VARIES)
7277-2-XX(VARIES)
7277-2-XX(VARIES)
JKL
JKL
JKL
JKL
JKL
JKL
JKL
JKL
JKL
JKL
JKL
JKL
-_--L
--L
--L
--L
--L
1_
--L
L
MB125A
MB126A
MB127A
MB128A
MB129A
MB131A
MB132A
MB133A
MB134A
MB135A
MB136A
MB137A
MB150A
MB151A
MB152A
MB158A
MB154A
MB155A
MB156A
MB157A
MB158A
C/B RMI
C/B P,/NAV
C/B INVERTER
C/B STEREO
C/B PROP DE-ICE
BUS BAR #10
BUS BAR #11
BUS BAR #12
BUS BAR #13
C/B, YAW DAMPER
C/B, RADAR ALTIMETER
C/B, ARTIFICIAL HORIZON
AVIONICS BUS BAR #1
AVIONICS BUS BAR #2
AVIONICS BUS BAR #3
AVIONICS BUS BAR #4
AVIONICS BUS BAR #5
AVIONICS BUS BAR #6
AVIONICS BUS BAR #7
SHUNT
AVIONICS MASTER RELAY
RECEPTACLE
DIODE
72T7-2-XX(VARIES)
7277-2-XX(VARIES)
7277-2-XX(VARIES)
7277-2-XX(VARIES)
930023-223
913127-019
913127-019
913127-019
913127-005
7277-2-7.5
7277-2-7.5
7277-2-5
913127-73
913127-73
913127-73
913127-73
913127-73
913127-73
913127-73
913127-049
HG4-DC24V
HG4-SF
1N2483
MB159A
--L
MB160A
--L
--L
L
L
--L
JKL
--L
91-20-02
48
KLIXON
KLIXON
KLIXON
KLIXON
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
KLIXON
KLIXON
KLIXON
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
AROMAT
AROMAT
MB162A
MB163A
MB164A
MB165A
MB166A
FUSE HOLDER
U-i-FEL
FUSE 1A
LI'I-IEL
DIODE, STARTER SOLENOID, LT
DIODE, STARTER SOLENOID
ARTIFICIAL HORIZ
CASTLEBERRY
PLUG, ART.HORIZ
AMPHENOL
C/B, AUTOPILOT ALERT
KLIXON
155020 or 155120
313001
1N2483
1N2483
300-2BL
126-222
7277-2-XX(VARIES)
MC101A
MC150A
CIGAR LIGHTER
C/B, CIGAR LIGHTER
800336-503
7277-2-10
MOONEY
KLIXON
12-98
NOTES
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
MID-CONT.
MD-88L
BA,?.B-24-BW2
MD-88L (ET)
BA28-24-BW2
950D0312.000
944.641.213.00
206705-2
206966-1
206708-1
206966-1
NOTES
.....................................................................................
(
JK-
ME101A
JK-
ME101B
--L
--L
--L
ME150A
ME150B
ME151A
--L
ME152A
JK---L
MIC101A
JK-
MJ101A
JK-
MJ102A
JK-
CLOCK, ELECTRIC
LIGHT TRAY
CLOCK, (OPT)
LIGHT TRAY
CLOCK, (ALT)
CLOCK, CONTROL WHEEL
RECPT, CONTROL WHEEL
CLAMP
PLUG, CONTROL WHEEL
CLAMP
MID-CONT.
IAI
PORSCHE
AMP
AMP
AMP
AMP
JACK, MICROPHONE
SWlTCHCRAFT
WASHERS
SWlTCHCRAFT
JACK, MICROPHONE,CONSOLE SWlTCHCRAFT
WASHERS
SWITCHCRAFT
C-12B
S-1028 or S-1029
C-12B
S-1028 or S-1029
JUNCTION BLOCK (GND)
JUMPER EDGE ON
JUNCTION BLOCK (GND)
JUMPER EDGE ON
BEAU
BEAU
BEAU
BEAU
77014-52
7233-16
71106-52
7233-8
MJ103A
JUNCTION BLOCK (DIM)
JUMPER EDGE ON
BEAU
BEAU
71106-52
7233-8
JKJKJK-JK-
MP101A
MP102A
MP103A
JKJK--L
--L
--L
--L
MP105A
MP106A
MP150A
MP151A
MP152A
MP153
--L
--L
MP154A
MP155A
TIMER
B.F. GOODRICH
SHUNT
B.F. GOODRICH
FUSE HOLDER
UTTEL
FUSE, 1A
U'I-I'EL
FUSE HOLDER
UTTEL
FUSE, 1A
LITTEL
AMMETER
B.F. GOODRICH
SLIP-RING BLOCK
B.F. GOODRICH
C/B-SWITCH, PROP DE-ICE (15A) ETA
TIMER
B.F. GOODRICH
SLIP RING, MODULAR BRUSH ASSY
FUSEHOLDER
U'I-FEL
FUSE, 1A
U'I-rEL
RELAY BOX, CURRENT
MOONEY
PLUG, 4 PiN
AMP
CLAMP
AMP
3E1899-1
MS91586-1
155020 or 155120
313001
155020 or 155120
313001
3E1872-1
3E2062-1
930023-223
3E2311-4
B.F. GOODRICH
155020 or 155120
313001
600221-505
206060-1
206062-1
MSxxx
SPEAKER
ARCHER
40-1197
--L
--L
NE15OA
NE151A
KLIXON
MICRO SWITCH
MICRO SWITCH
7277-2-1
1SE1-T
JE-5
--L
NE153A
PORSCHE
--L
--L
--L
NE154A
NE155A
NE156A
C/B FUEL ENRICH
SWITCH, ENRICHMENT
ACTUATOR
VALVE, SOLENOID, MIXTURE
ENRICHMENT
DIODE, ENRICH SW.
DIODE, ENRICH SW.
DIODE, ENRICH SW.
933.606.012.00
1N2483
1N2483
1N2483
JKJ-JK-
NF101A
NF102A
NF103A
JK-
NF104A
C/B, FUEL PUMP
' PUMP, FUEL
PLUG, FUEL PUMP
CLAMP
RECPT, FUEL PUMP
CLAMP
MOONEY
WELDON
AMP
AMP
AMP
AMP
930023-211
8163B
206060-1
206062-1
206153-1
206062-1
MIC102A
MP104A
12-98
3E2062-1
91-20-02
49
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
-K-K-K-K-K-
NF105A
NF106A
NF107A
NF108A
NF109A
-K-
NFl10A
--L
--L
--L
---L
NF150A
NF151A
NF152A
NF153A
--L
NF154A
---L
NF155A
--L
NF156A
--L
--L
NF157A
NF158A
--L
NF159A
--L
--L
NF160A
NF161A
-K-
NP101A
-K-K-
NP102A
NP103A
--L
--L
--
NS150A
NS151A
--L
NS153A
JKJK!_
JKJKJK-
PA101A
PA102A
PA103A
PAl 04A
PAl 05A
JK-
PA106A
-K-JKL
JKL
JK-
PA107A
91-20-02
5O
PA108A
PA109A
PAl 10A
VENDOR
PART NO.
C/B, HIGH BOOST, FUEL
MOONEY
PUMP, FUEL
WELDON
C/B, LOW BOOST, FUEL
MOONEY
REGULATOR, FUEL PUMP
ELECTRO-DELTA
RECPT.
AMP
CLAMP
AMP
PLUG
AMP
CLAMP
AMP
C/S FUEL PUMP, MAIN
KLIXON
C/B FUEL PUMP, EMERGENCY KLIXON
SW., FUELPUMP,MAIN/BOOST C-H
GUARD
MOONEY
SWITCH,FUEL PUMP, EMER.
C-H
GUARD
MOONEY
RECPT, FUEL PUMP
AMP
CLAMP
AMP
RECPT, FUEL PUMP
AMP
CLAMP
AMP
C/B, BOOST PUMP
KL[XON
930023-219
10054B
930023-217
VR536
208153-1
206062-1
206060-1
206062-1
7277-2-10
7277-2-10
8162-K22-E13-MS0
930028-501
8142-K21-E7-T50
930028-501
206060-1
206062-1
206153-1
206082-1
7277-2-10
FUEL PUMP, BOOST
PLUG
CLAMP
RECPT, FUEL PUMP
CLAMP
FUEL PUMP, MAIN
FUEL PUMP, EMERGENCY
PORSCHE
AMP
AMP
AMP
AMP
PORSCHE
PORSCHE
933.620.001.00
206060-1
206062-1
206153-1
206062-1
933.620.001.00
933.620.001.00
FUSEHOLDER, PRIMER
FUSE, 10A,SLO-BLO
SWITCH, PRIMER
DIFFUSER, PRIMER
LI-I-FEL
U'I-I'EL
CARLING
CONTINENTAL
155020 or 155120
313010
T1GK6B-1F-WH-A
633862-2
SWITCH, COLD START/ENRICH MOONEY
NOZZLE, COLD START
PORSCHE
PLUG
PORSCHE
CLAMP
PORSCHE
BOOT
PORSCH E
CONTACTS
PORSCHE
DIODE, COLD START SW
880052-511
933.612.401.00
933.615.032.40
999.615.032.40
944.612.128.00
999.652.456.22
1N2483
C/B, ALTERNATOR #1
C/B, ALTERNATOR FIELD, #1
SWITCH, ALTERNATOR FIELD
VOLTAGE REGULATOR, #1
RECPT, VOLTAGE REG.
CLAMP
PLUG, VOLTAGE REG.
CLAMP
ALTERNATOR #1
GEAR ASSY
FILTER
. CAPACITOR
C/B, ALTERNATOR #2
41-3-$34-LN2-041800
7277-2-5
8133K-21-E13-T52
VR-802
206705-2
206966-1
206708-2
206966-1
649280 or 646719
649123
880014-501
CGS302U-050R2C
41-3-$34-LN2-041800
ETA
KLIXON
C-H
ELECTRODELTA
AMP
AMP
AMP
AMP
CONTINENTAL
CONTINENTAL
MOONEY
MALLORY
ETA
12-98
NOTES
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
{
DESCRIPTION
JKL
JKJK-
PAl 11A
PA112A
PAl 13A
JK-
PAl 14A
-KJKL
JKL
J
PAl 15A
PAl 16A
PAl 17A
PAllSA
JK-
PA119A
PA120A
JK-
PA121A
JK-
VENDOR
PART NO.
7277-2-5
VR-802
205705-2
206966-1
205709-2
206966-1
649283 or 649172
660014-501
CGS302U-056R20
LW-14367
ALU-6421-LS
PA122A
C/B ALTERNATOR FIELD, #2
KUXON
VOLTAGE REGULATOR, #2
ELECTRODELTA
RECPT, VOLTAGE REG.
AMP
CLAMP
AMP
PLUG, VOLTAGE REG.
AMP
CLAMP
AMP
ALTERNATOR #2
CONTINENTAL
FILTER
MOONEY
CAPACITOR
_IALLORY
ALTERNATOR #1 (RIGHT)
LYCOMING
ALTERNATOR (ALT)
PRESTOUTE
( #2 ALTERNATOR NOT USED AT THIS TIME)
FUSEHOLDER
LI'I-I'EL
FUSE 5A
LI3-FEL
SWITCH, EMERGENCY, FIELD C-H
LOCKING RING
C-H
LOCKWASHER
C-H
NUT, HEX
C-H
LAMP
GE
DIODE
SARKES-TARZIAN
JKJKJKJKL
L
--L
PA123A
PA124A
PA125A
PA126A
PA150A
PA151A
PA152A
DIODE
SARKES-TARZIAN
SWITCH, ALTERNATOR FIELD C-H
DIODE
SARKES-TARZIAN
DIODE
SARKES-TARZlAN
ALTERNATOR, LT
PORSCHE
ALTERNATOR, FIT
PORSCHE
OVERVOLTAGE CONTROL, LT ELECTRO DELTA
10H3P
880052-503
10H3P
10H3P
933.603.604.00
933.603.004.00
OS-400
--L
PAl 53A
PLUG, OVERVOLTAGE
CONTROL, LT
AMP
CLAMP
AMP
OVERVOLTAGE CONTROL, RT ELECTRO DELTA
PLUG, OVERVOLTAGE
CONTROL, RT
AMP
CLAMP
AMP
SWITCH, OVERVOLTAGE
RESET, LT
C-H
LOCKING RING
C-H
LOCKING WASHER
C-H
NUT, HEX (2 ea)
C-H
LAMP
GE
SWITCH, OVERVOLTAGE
RESET, RT
C-H
LOCKING RING
C-H
LOCKING WASHER
C-H
NUT, HEX (2 ea)
C-H
LAMP
GE
C/B ALTERNATOR, LT
ETA
C/B ALTERNATOR, LT (ALT)
ETA
C/B ALTERNATOR, RT
ETA
C/B ALTERNATOR, RT (ALT)
ETA
. RECPT, O/VOLTAGE CONTROL, LT AMP
CLAMP
AMP
L
--L
--L
--L
PA154A
PA155A
PA156A
PA157A
--L
PA155A
--L
PA159A
L
PA160A
12-98
NOTES
155020 or 155120
313005
SBIDDX492-2
29-761
16-686
15-996-6
388
10H3P
206708-1
206966-1
OS-400
206708-1
206966-1
SSl DDX492-2
29-761
16-886
15-966-6
388
SB1DDX492-2
29-761
16-886
15-966-6
368
41-3-S14-LN2-70A
41-3-S34-LN2-70A
41-3-S14-LN2-70A
41-3-S34-LN2-70A
206705-2
206966-'1
91-20-02
51
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
--L
PA161A
RECPT,OVERVOLTAGE CONT'L, RT AMP
CLAMP
AMP
206705-1
206996-1
JKJKL
PB101A
PB102A
JKL
JKJKL
PB103A
PB104A
PB105A
JKL
PB106A
JKJKJKJKJKJK-
PB107A
PB108A
PB109A
PB110A
PB111A
PB112A
BA'I-I'ERY
GILL
RELAY,MASTER,BA-I-I'ERY,LEFT C-H
(ALl')
C-H
DIODE,LEFT BA'I-rERY RELAY
SWITCH, MASTER
C-H
CiB BA-FI'ERY, LT (ALE)
ETA
C,tB BATTERY, LT
ETA
C/B BUS, FLI PNL SWITCH (ALl') ETA
C/B BUS, FLT PNL SW
ETA
BUSS BAR #1
MOONEY
BUSS BAR #2
MOONEY
BUSS BAR #3
MOONEY
BUSS BAR #4
MOONEY
BUSS BAR #5
MOONEY
BUSS BAR #6
MOONEY
G-242
6041H202
6041H202A
1N2483
880052-501
41-3-S14-LN2-70A
41-3-S34-LN2-70A
41-3-S14-LN2-70A
41-3-S34-LN2-70A
913127-005
913127-039
913127-001
913127-019
913127-019
913127-239 *
NOTES
•BUSS BARS 913127-045,-213,-223 or -227 MAY BE USED, AS REQUIRED, BY CIRCUIT BREAKER
INSTALLATION.
-KPBl13A
BUSS BAR #7
MOONEY
913127-129
JKPB114A
BUSS BAR #8
MOONEY
913127-041
JKPB115A
BUSS BAR #9
MOONEY
913127-043
JKPB116A
SHUNT
KULKA
600RJ-2
--L
PB150A
BATTERY, RIGHT
GILL
G-243
--L
PB151A
RELAY, BA'I-rERY, RT
C-H
6041H202
(ALT)
C-H
6041H202A
--L
PB152A
DIODE, BA3-I-ERY RELAY, RT
1N2483
--L
PB153A
SWITCH, BATTERY, LT
MOONEY
880052-507
--L
PB154A
SWITCH, BATTERY, RT
MOONEY
880052-509
--L
PB155A
C/B BATTERY, RT
.ETA
41-3-S14-LN2-70A
--L
PB155A
C/B BA'I-I'ERY, RT (ALT)
ETA
41-3-S34-LN2-70A
--L
PB156A
BUSS BAR #1
MOONEY
913127-51
--L
PB157A
BUSS BAR #2
MOONEY
913127-51
--L
PB158A
BUSS BAR #3
MOONEY
913127-51
--L
PB159A
BUSS BAR #4
MOONEY
913127-51
--L
PB160A
BUSS BAR #5
MOONEY
913127-19
--L
PB161A
BUSS BAR #6
MOONEY
913127-19
--L
PB162A
BUSS BAR #7
MOONEY
913127-19
--L
PB163A
BUSS BAR #8
MOONEY
913127-19
--L
PB164A
BUSS BAR #9
MOONEY
913127-53
--L
PB165A
BUSS BAR #10
MOONEY
913127-53
--L
PB166A
BUSS BAR #11
MOONEY
913127-53
--L
PB167A
BUSS BAR #12
MOONEY
913127-TBA
--L
PB168A
C/B EMERGENCY CROSSOVERETA
41-3-S14-LN2-50A
--L
PB168A
C/B EMERGENCY
CROSSOVER (ALT)
ETA
41-3-S34-LN2-50A
C/B COVER PLACARD
MOONEY
150080-802
GUARD
MOONEY
800232-503
--L
PB169A
SHUNT, AVIONICS RELAY
MOONEY
913127-047
--L
PB170A
BA'I-I'ERY, LEFT
GILL
G-243
--L
PB171A
C/B LOAD, A/C, LT
ETA
41-3-S14-LN2-60A
--L
PB171A
'C/B LOAD, A/C, LT(ALT)
ETA
41-3-S34-LN2-6OA
91-20-02
52
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
--L
--L
--L
---L
--L
--L
--L
--L
---4L
i
DESCRIPTION
VENDOR
PART NO.
--L
PB172A
PB172A
PB173A
PB174A
PB175A
PB176A
PB177A
PB178A
PB179A
PB180A
PS18OA
PB181A
--L
L
L
--L
L
----L
---L
PB182A
PB183A
PB184A
PB185A
PB186A
PB186A
PB187A
PB187A
PB188A
--L
PB189A
C/B LOAD, A/C. RT
ETA
C/B LOAD, A/C RT (ALE)
ETA
BUSS BAR #13
MOONEY
BUSS BAR #14
MOONEY
BUSS BAR#15
MOONEY
BUSS BAR#16
MOONEY
BUSS BAR#17
MOONEY
BUSS BAR#18
MOONEY
BUSS BAR#19
MOONEY
FUSEHOLDER, LEFT MASTER Lll-FEL
FUSE 5AMP
UTTEL
MASTER RELAY
C-H
(ALl')
C-H
DIODE
MASTER SWITCH
MOONEY
RELAY, Nil PWR
MAGNACRAFT
DIODE
FUSEHOLDER, NH, RT
UI-I-EL
FUSE, 5AMP
LII-FEL
FUSEHOLDER, MASTER, RT
LITTEL
FUSE, 5AMP
UI-I-EL
MASTER RELAY, ENGINE BUS, RT C-H
(ALE)
C-H
DIODE
--L
PB190A
MASTER SWITCH (OPT)
C-H
8133K-21-E13-T52
--L
PB191A
GRND/DIMMER BOX
MOONEY
800228-501
JKL
PL01A
JKL
PL02A
JKL
PL02B
JKL
JKL
JKL
JKL
JKL
PL03A
PL04A
PL03B
PL04A
PL05A
PLUG, C/B PANEL #1,37 PIN
AMP
CLAMP
AMP
PLUG, CONSOLE #1, 16 PIN
AMP
CLAMP
AMP
PLUG, CONSOLE #1,28 PIN
AMP
CLAMP
AMP
PLUG, LEFT SIDE PANEL, 20 PIN MOONEY
PLUG, FLT PNL #1, 26 PIN
MOONEY
PLUG, LEFT SIDE PANEL, 26 PIN MOONEY
PLUG, FLT PNL #1,26 PIN
MOONEY
PLUG, NS SWITCH #1, 4 PIN
AMP
CLAMP
AMP
206150-1
206138-1
205837-1
206070-1
205839-3
206070-1
930021-501
930021-505
930021-505
930021-505
206060-1
206062-1
JKL
PL06A
JKL
JKL
PL07A
PLOBA
JKL
JKL
JKL
JKL
JKL
PL09A
PL09B
PL10A
PL11A
PL12B
JK-
PL13A
PLUG, AUTOPILOT POWER, 16 PIN AMP
CLAMP
AMP
PLUG, 16 PIN, CLUSTER GAUGE AMP
PLUG, FIREWAL.L#1, 19 PIN
CLAMP
PLUG, RT.WG. 14 PIN
MOONEY
PLUG, RT. WING, 20 PIN
MOONEY
PLUG, RT. WING STUB, 14 PIN MOONEY
PLUG, LEFT WING, 14 PIN
MOONEY
PLUG, FIREWALL #2, 19 PIN
CLAMP
PLUG, RT. RADIO PNL, 9 PIN
AMP
CLAMP
AMP
206037-1
202070-1
206037-1
MS3105A-22-14S
MS3057-12B
930021-001
930021-501
930021-001
930021-001
MS3106A-22-14S
MS3057-12B
206708-1
206966-1
12-98
41-3-S14-LN2-60A
41-3-S34-LN2-60A
913127-55
913127-57
913127-57
913127-59
913127-59
913127-61
913127-19
155020 or 155120
313005
6041H202
6041H202A
1N2483
880052-501
W389CX-3
1N2483
155020 or155120
313005
155020 or155120
313005
6041H202
6041H202A
1N2483
NOTES
91-20-02
53
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORRORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
JKL
PL13B
JKL
PL14A
JKL
JKL
PL15A
PL16A
JKL
JK-
PL17A
PL18A
JKL
PL19A
JKL
PL20A
JKL
PL21A
JKL
PL22A
JKL
PL23A
JKL
PI-24A
JK-
PL25A
JK-
PL26A
JK-
PL27A
JKL
JKJKJK-
PL27B
PL28A
PL29A
PL30A
JK-
PL.31A
JK-
PL32A
JKL
PI.-33A
JKL
PL34A
JKL
PL.34B
JK-
PL35A
JK-
PL36A
JK-
PL37A
JK-
PL38A
91-20-02
54
VENDOR
PART NO.
PLUG, AVIONICS MASTER, 4 PIN AMP
CLAMP
AMP
PLUG, HOUR, 4 PIN
AMP
CLAMP
AMP
206060-1
208062-1
205060-1
206062-1
PLUG, LEFTWING STUB, 14 PIN MOONEY
PLUG, GEAR CONTROL, 9 PIN AMP
CLAMP
AMP
PLUG, ELECTRIC GEAR, 14 PIN MOONEY
PLUG, DIMMER, 16 PIN
AMP
CLAMP
AMP
PLUG, A/S SWITCH #2, 4 PIN
AMP
CLAMP
AMP
PLUG, TAILCONE, 16 PIN
AMP
CLAMP
AMP
PLUG, HEADLINER, 9 PIN
AMP
CLAMP
AMP
PLUG, OVERHEAD, REAR, 4 PIN AMP
CLAMP
AMP
PLUG, GRND #1, 16 PIN
AMP
CLAMP
AMP
PLUG, GRND #2, 16 PIN
AMP
CLAMP
AMP
PLUG, LIGHT CONTROL, 9 PIN AMP
CLAMP
AMP
PLUG, G/SHIELD HARNESS, 4 PIN AMP
930021-001
206708-1
206966-1
930021-001
206037-1
206070-1
206060-1
206062-1
206037-1
206070-1
206708-1
206966-1
206060-1
206062-1
206037-1
206070-1
206037-1
206070-1
206708-1
206966-1
206060-1
CLAMP
206062-1
AMP
PLUG, FLT PNL #2, 16 PIN
AMP
CLAMP
AMP
PLUG, FLT PNL #2, 20 PIN
MOONEY
PLUG, AVIONICS POWER, 20 PIN MOONEY
PLUG, DIM, GND, 20 PIN
MOONEY
PLUG, DIM, GND 4 PIN
AMP
CLAMP
AMP
206037-1
206070-1
930021-501
930021-501
930021-501
206060-1
206062-1
PLUG, STANDBY VAC, 6 PIN
CLAMP
PLUG, GEAR RELAY, 4 PIN
CLAMP
PLUG, C/B PNL, 9 PIN
CLAMP
PLUG, GRND BUSS, 9 PIN
CLAMP
PLUG, GRND BUSS, 16 PIN
CLAMP
PLUG, FLT PNL #3, 4 PIN
CLAMP
PLUG, CONSOLE # 2, 8 PIN
CLAMP
PLUG, LT SIDE PNL, 8 PIN
, CLAMP
PLUG, FLAP RELAY, 8 PIN
"CLAMP
205838-1
206062-1
206060-1
206062-1
206708-1
206966-1
206708-1
206966-1
206037-1
206070-1
206060-1
206062-1
205838-1
206062-1
206838-1
206062-1
205708-1
206062-1
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
12-98
NOTES
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
JK-
PL39A
-K-
PL40A
JK!._
PL50A
JKL
JKL
PL51A
PL52A
JKL
PL55A
JKL
PL56A
JKL
JKL
PL57A
PL58A
JKI.
JK-
PL59A
PL76A
JK-
PL77A
--L
PL152A
VENDOR
PART NO.
PLUG, FLAP MOTOR, 9 PIN
AMP
CLAMP
AMP
PLUG, THROTTLE SWITCH, 4 PIN AMP
CLAMP
AMP
PLUG, C/B PNL #2, 37 PIN
AMP
FLANGE
AMP
RECPT, IGNITION SWITCH,26 PIN MOONEY
PLUG, ALT/STARTER, F/W
CANNON
CLAM P
PLUG, EMPENNAGE, 9 PIN
AMP
CLAMP
AMP
PLUG, GRND #4, 9 PIN
AMP
CLAMP
AMP
PLUG,GRND #5, 14 PIN
MOONEY
PLUG, DIM. #2, 16 PIN
AMP
CLAMP
AMP
PLUG, GRND #6, 26 PIN
MOONEY
PLUG, 9 PIN
AMP
CLAMP
AMP
PLUG, 28 PIN
AMP
CLAMP
AMP
PLUG, GR/STALL WARN
HARNESS, 4 PIN
AMP
CLAMP
AMP
206708-1
206968-1
206060-1
206062-1
208150-1
207299-4
930021-505
MS3106A2.B-22S
MS3057-16
206708-1
206966-1
206708-1
206966-1
930021-001
206037-1
206070-1
930021-505
206708-1
206986-1
205839-3
206070-1
7277-2-10
6041H-202 or-202A
155020 or 155120
313001
KLIXON
C-H
UTTEL
LITTEL
206060-1
206062-1
JKJKL
JK-
PSIO1A
PS102A
PS103A
C/B, IGN/TACH/CIG LIGHTER
SOLENOID, STARTER,LT
FUSEHOLDER
FUSE, 1A
J---
PS105A
-K-
PS106A
JKL
--L
--L
--L
--L
--L
PSIOTA
PS150A
PS151A
PS152A
PS153A
PS154A
STARTER
PRESTOUTE
(ALl')
LYCOMING
STARTER
TCM
(ALT)
TCM
DIODE, STARTER SOLENOID,LT
DIODE, PWR START,LT
DIODE, PWR START,RT
SOLENOID, STARTER, RT
C-H
DIODE, STARTER SOLENOID
STARTER
PORSCHE
MHB.-4016
LW15572
646275
637847
1N2483
1N2483
1N2483
6041H-202 or -202A
1N2483
933.602.007.03
JKL
JKL
JKL
JKL
RB101A
RB102A
RB103A
RB103A
C/B RADIO BLOWER
RADIO BLOWER
FILTER, RADIO BLOWER
FILTER, RAD. BLWR, (ALT)
7277-2-2
19A2790
273-103
5JX5104A
JKL
JKL
RCO1A
RCO2A
JKL
RCO2B
JKL
JKL
JKL
JKL
RC03A
RCO3B
RC04A
RCO5A
RECPT, C/B PNL #1, 37 PIN
AMP
RECPT, CONSOLE #1, 16 PIN AMP
CLAMP
AMP
RECPT, CONSOLE#I, 28 PIN AMP
CLAMP
AMP
.RECPT, LEFT SIDE PANEL, 20 PIN MOONEY
RECPT, LEFT SIDE PANEL, 26 PIN MOONEY
RECPT, FLT PNL #1, 26 PIN
MOONEY
RECPT, NS SWITCH #1, 4 PIN AMP
CLAMP
AMP
KLIXON
TRW
ARCHER
SPRAGUE
12-98
NOTES
206151-2
206036-3
206070-1
206152-1
206070-1
930021-502
930021-506
930021-506
205153-1
208082-1
91-20-02
55
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
JKL
-JKL
RC06A
JKL
RC08A
JKL
RC08B
JKL
JKL
JKL
JKL
JKL
RC09A
RC09B
RC10A
RC11A
RC12A
JKL
RC12B
JK
RC13A
JKL
RC13B
JK-
RC14A
JKL
JKL
RC16A
RC16A
RC07A
VENDOR
PART NO.
RECPT, A/P POWER, 16 PIN
AMP
CLAMP
RECPT, CLUSTER GAUGE, 16 PIN AMP
CLAMP
RECPT, PIRE'WALL#1, 19 PIN
CLAMP
RECPT, FIREWALL #1, 19 PIN
(ALT)
CLAMP
RECPT, RT. WG, 14 PIN
MOONEY
RECPT, RT WING, 20 PIN
MOONEY
RECPT, RT. WING STUB, 14 PINMOONEY
RECPT, LT.WG., 14 PIN
MOONEY
RECPT, FIREWALL #2, 19 PIN
CLAMP
RECPT, FIREWALL #2
(ALT)
CLAMP
RECPT, RT.RADIO PNL, 9 PIN AMP
CLAMP
AMP
RECPT, AVIONICS MASTER, 4 PIN AMP
CLAMP
AMP
RECPT, HOUR METER, 4 PIN AMP
CLAMP
AMP
RECPT, LEFT WING STUB, 14 PIN MOONEY
RECPT, GEAR CONTROL
AMP
206036-3
206070-1
296036-3
206070-1
MS3100A22-14P
MS3057-12B
MS3100K22-14P
MS3100KE22-14P
MS3057-12B or 12A
930021-2
930021-502
930021-2
930021-002
MS3100A22-14P
MS3057-12B
MS3100K22-14P
MS3100KE22-14P
MS3057-12B or-12A
208705-1
206966-1
206153-1
206062-1
206153-1
206062-1
930021-002
206705-2
CLAMP
AMP
206966-1
JKL
RC17A
RECPT, ELECTRIC GEAR
MOONEY
930021-002
JK-
RC18A
JKL
RC18B
JKL
RC19A
JKL
RC20A
JK-
RC21A
JK-
RC22A
JK-JK--
RC23A
RECPT, DIMMER, 16 PIN
CLAMP
RECPT, PNL LT DIM#l, 14 PIN
CLAMP
RECPT, NS SWITCH #2, 4 PIN
CLAMP
RECPT, TAILCONE, 16 PIN
CLAMP
RECPT, TAILCONE, 16 PIN
CLAMP
RECPT, O/H REAR, 4 PIN
CLAMP
RECPT, GRND #1, 16 PIN
CLAMP
RECPT, GRND #2, 16 PIN
CLAMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
206036-3
206070-1
206044-1
206070-1
206153-1
206062-1
206036-3
206070-1
206036-3
206062-1
206153-1
206062-1
206036-3
206070-1
206036-3
206070-1
JKL
RC26A
JK-
RC27A
JKL
JKJK-
RC27B
RC28A
RC29A
91-20-02
56
RC24A
RECPT, COMPASS LT HARNESS, AMP
CLAMP
AMP
RECPT, FLT PNL #2,4 PIN
AMP
CLAMP
AMP
:RECPT, FLT PNL#2, 20 PIN
MOONEY
RECPT, AVIONICS POWER, 20 PIN MOONEY
RECPT, DIM/GRND, 20 PIN
MOONEY
12-98
206153-1
206062-1
206153-1
206062-1
930021-502
930021-502
930021-502
NOTES
:
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
JK-
RC30A
JK-
RC81A
JK-JKL
RC31B
JK
RC33A
JKL
RC34B
JK-
RC35A
JK-
RC36A
JK-JK-
RC37A
JK
RC89A
-K-
RC40A
JKL
RCSOA
JKL
RC51A
JKL
RC32A
DESCRIPTION
VENDOR
PART NO.
RECPT, DIM/GRND, 4 PIN
CLAMP
RECPT, STBY VAC, 8 PIN
CLAMP
RECPT, STBY VAC, 8 PIN
CLAMP
RECPT, GEAR RELAY, 4 PiN
CLAMP
RECPT, C/B PNL#2, 9 PIN
CLAMP
RECPT, GRND BUSS, 16 PIN
CLAMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
206153-1
206062-1
205841-2
206062-1
205841-2
206062-1
206153-1
206062-1
206705-2
206966-1
206036-3
206966-1
RECPT, FLT PNL #3, 4 PIN
AMP
CLAMP
AMP
RECPT, CONSOLE #2, 8 PIN
AMP
CLAMP
AMP
RECPT, LT.SIDE PNL, 8 PIN
AMP
CLAMP
AMP
RECPT, FLAY RELAY, 8 PIN
AMP
CLAMP
AMP
RECPT, FLAP MOTOR, 9 PIN
AMP
CLAMP
AMP
RECPT, THRO-I-FLESWITCH, 4 PIN AMP
CLAMP
AMP
RECPT, C/B PNL #2
AMP
CLAMP
AMP
RECPT, IGNITION SWITCH
MOONEY
206153-1
206062-1
205841-2
206062-1
205841-2
206062-1
205841-2
206062-1
206705-2
206966-1
206153-1
206062-1
206151-2
206138-1
930021-506
RC52A
RECPT, ALT/STARTER
(ALT)
MS3160K28-2P
MS3100KE28-2P
JKL
-JKL
RC55A
JKL
JKL
RC57A
RC58A
--L
RC58B
JKL
JK-
RC59A
RC76A
JK-
RC77A
--L
RC150A
RECPT, EMPENNAGE, 9 PIN
AMP
CLAMP
RECPT, GRND RECPT. #4, 9 PIN AMP
CLAMP
RECPT, GRND RECPT #5, 14 PIN MOONEY
RECPT, DIM RECPT. #2, 16 PIN AMP
CLAMP
AMP
RECPT, PNL LT DIM #2, 14 PIN AMP
CLAMP
AMP
RECPT, GRND RECPT #6, 26 PIN MOONEY
RECPT, 9 PIN
AMP
CLAMP
AMP
RECPT, 28 PIN
AMP
CLAMP
AMP
RECPT, ENGINE HARNESS, LT CANNON-GERMANY
--L
RC38A
RC56A
RC15OA
CANNON
NOTES
206705-2
206966-1
206705-2
206966-1
930021-002
206036-3
206070-1
206044-1
206070-1
930021-506
206705-2
206966-1
206152-1
206070-1
CA121006-518
CLAMP
CANNON-GERMANY
057-8557-000
FERRULE END RING
CANNON-GERMANY
304-8553-000
RECPT, ENGINE, LT F/WALL (ALT) CANNON-GERMANY CA121006-600
RECPT, ENGINE HARNESS,LT (ALT) PORSCHE
933.612.415.00
. CLAMP *
PORSCHE
933.612.417.00
ENDBELL *
PORSCHE
933.612.425.00
• NOTE:
ALTERNATE HIGH TEMPERATURE COMPONENTS FOR ITEMS:
12-98
91-20-02
57
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
L
RC151A
--L
RC151A
VENDOR
RECPT, ENGINE HARNESS, RT CANNON-GERMANY
CLAMP *
CANNON-GERMANY
FERRULE END RING *
CANNON-GERMANY
RECPT, ENGINE HARNESS, FiT PORSCHE
CLAMP *
PORSCHE
ENDSELL *
PORSCHE
PART NO.
CA121006-518
057-8557-000
304-8553-000
933.612.415.00
933.612.417.00
933.612.425.00
• NOTE:
ALTERNATE HIGH TEMPERATURE COMPONENTS FOR ITEMS:
RC152A
RECPT, GR/STALL WARN
HARNESS, 4 PIN
AMP
206153-1
CLAMP
AMP
206062-1
JKL
SB101A
C/B, SPEED BRAKE
KUXON
7277-2-2
--L
SPK101A
SPEAKER, CABIN
ARCHER
12-1703
JK-
WA101A
WESTERN IND
WESTERN IND.
JKJK-
WA102A
WA103A
UGHT, OVERVOLTAGE
CLAMP
DIODE
DIODE
501-61K-11K-3RP
Wl-7049
1N2483
1N2483
--L
WD150A
-WD150A
FUSEHOLDER, STARTER
SOLENOID
FUSE, 1AMP
LI'CI-EL
U'I'TEL
155020 or155120
313001
WE101A
WE102A
C/B, GEAR WARN HORN
UGHT, GEAR DOWN
KUXON
SLOAN
7277-2-2
855S-O-U
BULB
GE
327
SWITCH, THROI-rLE
ACTUATOR
HORN, GEAR WARNING
DIODE
DIODE
SWITCH, THROTTLE
ACTUATOR
SWITCH, THROTTLE
ACTUATOR
PLUG, 4 PIN
CLAMP
RECPT, 4 PIN
CLAMP
MICRO
MICRO
MALLORY
V3-1
JV-1
SC628P
1N2483
1M2483
1SE1-T
JE-17
1SE1-T
JE-5
206060-1
206062-1
206153-1
206062-1
JKL
JKL
JK-
WE103A
JKJKL
JKL
-K-
WE104A
WE105A
WE106A
WE107A
--L
WE150A
L
WE151A
--L
WE152A
JKL
JKJKL
--L
L
WS101A
WS102A
WS103A
WS150A
WS151A
--L
L
WS152A
WS153A
--L
WS154A
01-20-02
58
MICRO
MICRO
MICRO-SWITCH
MICRO-SWITCH
AMP
AMP
AMP
AMP
C/B STALL WARN HORN
KLIXON
HORN, STALL WARNING
MALLORY
SWITCH, STALL WARN
SAFE FUGHT
ALERT, GR/STALL WARNING
IAI
PLUG,GR/STLWRN ALRT, 25 PIN ITT
CLAMP
I1-£
LOCK RETAINER
ITT
SPEAKER, GR/STALL WARN
ARCHER
PLUG, INTER PHONE, 4 PIN
AMP
'CLAMP
AMP
PLUG, MATE N LOCK, 2 PIN
AMP
SOCKETS
AMP
i2-98
7277-2-2
SC628
C46001
950D-0309-000
DB25S
DB51212
DB1212-1
40-1333C
206060-1
206062-1
1-480318-0
60619-1
NOTES
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
--L
WS155A
RECPT, MATE N LOCK, 2 PIN
PINS
AMP
AMP
1-480319-0
60620-1
JKJ--
WTI01A
WT102A
-K-
WT103A
C/B, ANNUNCIATOR
ANNUNCIATOR
LAMPS
ANNUNCIATOR
LAMPS
KLIXON
MOONEY
CHICAGO MINIATURE
MOONEY
CHICAGO MINIATURE
7277-2-2
880025-521
CM7327
880025-523
CM7327
JK-
W3"104A
--L
--L
WT150A
WT151A
WT153A
--L
WT154A
PLUG, ANNUNCIATOR
SOCKETS
C/B, ANNUNCIATOR, LT
C/B, ANNUNCIATOR, RT
ANNUNCIATOR
LAMPS
PLUG, ANNUNCIATOR
CLAMP
LOCK RETAINER
MOLEX
MOLEX
KLIXON
KLIXON
IAI
CHICAGO MINATURE
ITT
ITT
ITT
09-50-3151
08-50-0105
7277-2-1
7277-2-1
950D0308-000
CM7327
DB25S
D551212-1
DB51221-1
JKJKJK-
WV101A
WV102A
V¢#103A
JK-
WVlO4A
C/B, VACUUM WARNING
SWITCH, VACUUM WARNING
RECPT, VAC WARN, 4 PiN
CLAMP
PLUG, VAC WARN, 4 PIN
CLAMP
KUXON
MOONEY
AMP
AMP
AMP
AMP
7277-2-2
880012-501
206153-1
208062-1
208060-1
206082-1
J--
WWlO1A
SWITCH, RAM AIR
ACTUATOR
MICRO
MICRO
V3-1
JV-5
-K--L
_"¢VIO2A
WW150A
SWITCH, ALTERNATE AIR
SWITCH, ALTERNATE AIR
CHERRY
CHERRY
E51-508
E51-508
NOTES
NOTES
1. Use 1 ea. MS35334-21 or MS2898 (Alan Bradley) internal tooth Iookwasherwith each light if not supplied
by Sloan.
2. Maximum circuit breaker rating is shown, amperage of installed circuit breaker is determined by particular
unit installed.
3. Buss bar may be shortened as required by circuit breaker installation.
4. Alternate for V3-1 switch w/JV-5 actuator is V3L-3 assembly.
5. Varies with AutoPilot System installed.
12-98
91-20-02
59
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
RESERVED
91-20-02
60
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
91-20-03
(
- ELECTRICAL SYSTEM HARDWARE CHART - 28 VOLT SYSTEMS
S/N's 24-3154 THRU 24-3200, 24-3202 THRU 24-3217, MOONEY DRAWING NO. 800263 (E7),
24-1686-14thru 24-2999-14 commoncomponents,28V & 14V - (See 91-20-04 for 14 Volt peculiarcomponents)
** - ACTUAL USAGE DETERMINED BY MASTER SCHEMATICS - **
DESCRIPTION
VENDOR
PART NO.
CODE
(
JKJKJKJKJK-JK-JKJKJKJKJK-
CB101A
CB102A
CB103A
CB103S
CB104A
CC101A
CC102A
CC103A
CC103B
CC104A
JK-
CC105A
JK-
CC106A
JK-JKJKJK-
CC107A
JK-
CF104A
JKJKJKJKJK-
CF105A
CF108A
CV101A
CV102A
CV103A
JK-
CVl04A
JK-
CV105A
JK-
CV106A
JKJKJKJKJK-
DA101A
DA102A
DA103A
DB101A
DB102A
CB105A
CC108A
CF101A
CF103A
C/S, DEFROSTER BLOWER
KLIXON
SWITCH, BLOWER MOTOR
CHERRY
MOTOR, BLOWER
MOONEY
MOTOR, BLOWER
MOONEY
PLUG, 2 PIN
AMP
SOCKET
AMP
RECEPTACLE, 2 PIN
AMP
PIN
AMP
C/B, COWL FLAP
KLIXON
SWITCH, COWL FLAP
MICRO
ACTUATOR, COWL FLAP
MOONEY
ACTUATOR, COWL FLAY
MOONEY
SWITCH, OPEN LIMIT
MICRO
ACTUATOR
MICRO
SWITCH, CLOSED LIMIT
MICRO
ACTUATOR
MICRO
PLUG, 9 PIN
AMP
CLAMP
AMP
RECEPTACLE, 9 PIN
AMP
CLAMP
AMP
VARISTOR
GE
C/B, FLAP ACTUATOR
KLIXON
SWITCH, UP LIMIT
MICRO
ACTUATOR
MICRO
SWITCH, DOWN UMIT
MICRO
ACTUATOR
MICRO
ACTUATOR, FLAP
MOONEY
SWITCH, FLAP
CUTLER-HAMMER
C/S, STAND-BY VACUUM
MOONEY
CURRENT MONITOR, STD-BY VAC MOONEY
PLUG, 9 PIN
AMP
CLAMP
AMP
PLUG, 2 PIN
AMP
SOCKET
AMP
RECEPTACLE, 2 PIN
AMP
PIN
AMP
PUMP, VACUUM
AEROSAFE
7277-2-5
E51-50B
640317-501
640317-503
1-480318-0
60619-1
1-480319-0
60620-1
7277-2-5
12TW1-1
880050-501
880050-505
1SE1-T
JE-5
1SE1-T
JE-5
206708-1
206966-1
206705-2
206966-1
V47ZA05
7277-2-5
V3-1
JV-5
V3-1
JV-5
750105-501
8906K3149
930023-233
800221-505
206708-1
206966-1
1-480318-0
60619-1
1-480319-0
60620-1
820904-2
SHUNT, LOAD
FUSEHOLDER
FUSEHOLDER
C/B, TURN COORDINATOR
TURN COORDINATOR
TURN COORDINATOR (ALl')
TURN COORDINATOR (ALl')
TURN COORDINATOR (ALE)
MLA-70A-100MV
FHN42W
FM01-SA
7277-2-2
9013 CODE N.5
303990-028MSC
1394T100-3Z
9114 CODE N.21
EMPRO
McGRAW EDISON
McGRAW EDISON
KLIXON
U.I.
ASTRONAUTICS
ELECTRO GYRO
U.I.
!2-98
NOTES
91-20-03
61
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
JK-
DB103A
PLUG
CABLE CLAMP
(ALT)
MS3106A-10SL-3S
MS35074A
MS3507-4B
JK-
DC101A
PROBE, CHT, (CYL #3)
(ALT)
MS24482-1
AN5546-1
JKJ-J-J--
DDIOIA
DD102A
DD102B
DD103A
JKJK-
DD104A
DD105A
JK-
DD106A
JKJKJKJKJKJ-JK-
DF101A
DF102A
DF103A
DF104A
DG101A
DG103A
DG104A
-KJ--
DG105A
DH101A
-K-K-
DH101A
DH102A
JK-
DJ101A
JK-
DJ102A
JK-JK-
DJ103A
JK-
DK102A
JK-
DK103A
C/B, EGT/OAT
KUXON
GAUGE, EGT/OAT
MOONEY
GAUGE (4 PROBE)
MOONEY
PLUG, 8 PIN
AMP
CLAMP
AMP
PROBE, OAT
MOONEY
PLUG, 2 PIN
AMP
SOCKET
AMP
RECEPTACLE, 2 PIN
AMP
PIN
AMP
TRANSMI'I-FER, LT IN/BD, FUEL MOONIEY
TRANSMll-rER, LT OUT/BD, FUEL MOONEY
TRANSMITTER, RT IN/BD, FUELMOONEY
TRANSMll-FER, RT OUT/BD, FUEL MOONEY
C/B, INSTR. MODULE #1
KUXON
MODULE, INSTR.
MOONEY
PLUG, 28 PIN
AMP
CLAMP
AMP
MODULE, INSTRUMENT
MOONEY
PROBE, OIL TEMP
MOONEY
(AL'r)
LEWIS ENGRG
PROBE, OIL TEMP
PLUG, 2 PIN
CLAMP
TRANSDUCER, OIL PRESS
DRUCK
(ALT)
KULITE
PLUG, 4 PIN
AMP
CLAMP
AMP
RECEPTACLE, 4 PIN
AMP
CLAMP
AMP
TRANSDUCER, FUELPRESS
DRUCK
(ALT)
KUIJTE
PLUG, 4 PIN
AMP
CLAMP
AMP
RECEPTACLE, 4 PIN
AMP
CLAMP
AMP
7277-2-2
880001-507
880001-509
205838-1
206082-1
880004-501
1-480318-0
60619-1
1-480319-0
60620-1
610242-003
610243-003
610242-003
610243-001
7277-2-1
880059-507
205839-3
206070-1
880059-509
880061-501
56B3A9
MS28034-1
MS3108A-12S-3S
MS3057-4A
PDCR821-0662-100
APT-154-1000-100PSIG
206060-1
206062-1
206153-1
206062-1
PDCR821-0862-30
APT-153-1000-30PSIG
208060-1
206062-1
206153-1
206062-1
J--
DLIOIA
-K-
DL101A
JK-
DL102A
J--K-
DL103A
DL103A
JK-
DLIO4A
JK-
DLIO5A
TACHOMETER
(AL'r)
TACHOMETER
(ALT)
PLUG, 5 PIN
CLAMP
SENSOR, TACH
SENSOR, TACH
.(ALT)
PLUG, 4 PIN
CLAMP
RECEPTACLE, 4 PIN
CLAMP
880039-515
0520-003
880039-517
0520-006
MS3106A-14S-5S
MS3057-TA/B
0400-004
0402-102
0402-104
206060-1
206062-1
206153-1
206062-1
91-20-03
62
DK101A
MOONEY
B &D
MOONEY
B& D
B& D
B& D
B& D
AMP
AMP
AMP
AMP
12-98
NOTES
1
1
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
J--K-
DM101A
DMIO1A
HOUR METER
HOUR METER
MOONEY
MOONEY
880035-507
660035-505
JK-
DMIO2A
RECEPTACLE, 4 PiN
CLAMP
AMP
AMP
206153-1
206062-1
JK-
DM103A
J--
DMIO4A
PLUG, 4 PIN
CLAMP
FUSEHOLDER
(ALT)
AMP
AMP
LI'I-]'ELFUSE
LITTEL
206060-1
206062-1
155020
155120
JKJK-
DPIOIA
DP102A
LITTEL
MOONEY
AERO INSTR
JK-
DPIO3A
JK-
DP104A
JK--
DPIO5A
FUSE (5A-3AG-SLO-BLO)
C/B, PITOT HEAT
PITOT, HEATED
(ALl)
PLUG
SOCKET
PLUG, 2 PIN
SOCKET
RECEPTACLE, 2 PIN
PIN
313005
930023-205
PH502-24
AN5812-1AN3115-1
AN3116-1
1-480316-0
60619-1
1-480319-0
60620-1
-K-K-K-K--K-
DR101A
DR102A
DR102B
DR103A
-KJK-
DR104A
DT101A
J-JK-
DT101A
DT102A
J-JK-
DT102A
DT103A
J-JK-
DTIO3A
DTIO4A
J-J--
DT104A
DT105A
-K-
DTIOIA
-K-
DT102A
-K-
DT103A
-K-
DTIO4A
-K-
DTIOSA
-K-
DT106A
JK-
DV101A
DR103B
AMP
AMP
AMP
AMP
C/B, TIT
KLIXON
TIT INDICATOR
MOONEY
TIT/EGT INDICATOR (6 PROBE) MOONEY
PLUG, 8 PIN
AMP
CLAMP
AMP
PLUG, 28 PIN
AMP
CLAMP
AMP
PROBE, TIT
MOONEY
PROBE, EGT, (CYL #1)
MOONEY
(ALl-)
MOONEY
(ALT)
MOONEY
PROBE, EGT (CYL#2)
MOONEY
(ALT)
MOONEY
(AL'r)
MOONEY
PROBE, EGT (CYL#3)
MOONEY
(ALT)
MOONEY
(AL'r)
MOONEY
PROBE, EGT (CYL#4)
MOONEY
(ALl-)
MOONEY
(ALl)
MOONEY
EGT INDICATOR
MOONEY
LEAD WIRE)
ALCOR
PROBE, EGT (CYL #1)
MOONEY
(ALT)
MOONEY
PROBE, EGT (CYL#2)
MOONEY
(ALT)
MOONEY
PROBE, EGT (CYL#3)
MOONEY
(ALT)
MOONEY
PROBE, EGT (CYL#4)
MOONEY
(ALT)
MOONEY
, PROBE, EGT (CYL#5)
MOONEY
(ALT)
MOONEY
' PROBE, EGT (CYL #6)
MOONEY
(ALl-)
MOONEY
C/B, FUEL FLOW
KLIXON
12-95
NOTES
7277-2-2
680051-501
880051-503
205838-1
206062-1
205839-503
206070-1
880055-501
850005-503
860005-501
660110-000
880005-503
880005-501
660110-000
680005-503
880005-501
660110-000
880005-503
680005-501
650110-000
660109-003
01-005-78
850005-503
880005-501
880005-503
650005-501
880005-503
880005-501
680005-503
880005-501
880005-503
680005-501
880005-503
550005-501
7277-2-1
91-20-03
63
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
29 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
NOTES
!
JKJK-
DV102A
DV102A
JK-
DV102B
JK-
DV103A
JK-
DV103B
JK-
DV104A
JKJK-
DV164B
DV105A
JK-
DVIO6A
JKJK-
DV107A
DV108A
JK-
DV109A
JKJKJKJK-
DW101A
EG101A
EG102A
EG103A
JKJKJK-
EG104A
EG105A
EG106A
JKJKJK-
EG107A
EG107B
EG108A
JK-
EG109A
91-20-03
64
INDICATOR, FUEL FLOW
(ALl')
(ALl')
(ALl') INDICATOR, F/F (GAL)
MOONEY
MOONEY
MOONEY
SHADIN
880034-501
680034-503
880034-505
912021
(ALl') (LBS)
SHADIN
912023
INDICATOR, F/F (OPT) (GAL)
(ALr) (LBS)
(ALT) (LITER)
(ALT) (GAL)
(ALT) (I.BS)
(ALE) (LITER)
PLUG, 9 PIN
CLAMP
LATCH ASSY (2 ea)
PLUG, 9 PIN
CLAMP
LATCH ASSY (2 ea)
TRANSDUCER, FUEL FLOW
(ALT)
TRANSDUCER, FUEL FLOW
PLUG, 4 PIN
CLAMP
RECEPTACLE, 4 PIN
CLAMP
SWITCH, FUEL FLOW
PLUG, 4 PIN
CLAMP
RECEPTACLE, 4 PIN
CLAMP
SHADIN
SHADIN
SHADIN
SHADIN
SHADIN
SHADIN
Il-r CANNON
I1-1"CANNON
ITT CANNON
II-F CANNON
I'FTCANNON
Il-r CANNON
MOONEY
MOONEY
FLOSCAN
AMP
AMP
AMP
AMP
C&K
AMP
AMP
AMP
AMP
912041
912043
912047
912081
912083
912087
DE-9S
DE-24657
DE-51224-1
DE-gS
DE-24657
D-110278
890030-501
880030-503
680501B
206060-1
206062-1
206153-1
206062-1
7101K
206060-1
206062-1
206153-1
205062-1
VERTICAL SPEED INDICATOR U.I.
C/B, GEAR RELAYS
KLIXON
SWITCH, GEAR UP/DOWN
CUTLER/HAMMER
SWITCH, GEAR OVERRIDE
CUTLER/HAMMER
RING, LOCKING
CUTLER-HAMMER
WASHER, LOCK
CUTLER-HAMMER
NUT, HEX (2 ea) .
CUTLER-HAMMER
LAMP (28V)
GE
LAMP (14V)
GE
SWITCH (ALT)
NKK CORP
SUTI-ON
NKK CORP
LOCKING RING
NKK CORP
LOCKWASHER
NKK CORP
NUT, HEX (2 EA)
NKK CORP
LAMP (29V)
NKK CORP
SWITCH, AIRSPEED, GEAR SAFETY MOONEY
C/B, GEAR ACTUATOR
KLIXON
SWITCH, GEAR UP LIMIT
MICRO
ACTUATOR
MICRO
SWITCH, GEAR DOWN LIMIT
MICRO
. SWITCH, GEAR DOWN LIMIT (ALT) SAINT
PLUG, 4 PIN
AMP
CLAMP
AMP
RECEPTACLE, 4 PiN
AMP
CLAMP
AMP
12-98
7000 CODE C.83
7277-2-2
8906K2875
SBIDDX492-2
29-761
16-886
15-966-6
334
336
DBL2141-3BL
AT406
AT406
AT508
AT503
AT604-28
880013-507
7277-2-7.5
DT-2R-A7
MCD-2711
1CHl16-6
MLl116
206060-1
206062-1
206153-1
206062-1
4
4
4
5
5
5
2
2
2
3
3
3
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
CUTLER-HAMMER
6041H220
1N2483
6041H220
1N2483
560254-503
880037-507
JKJKJKJKJK-
EG110A
EG111A
EG112A
EG113A
EG114A
RELAY, GEAR UP
DIODE
RELAY, GEAR DOWN
DIODE
ACTUATOR, GEAR
(ALT)
JKJKJK-
ELT101A
ELT101B
ELT102A
JKJKJK-
ELT103A
ELT103B
ELT104A
JK-
ELT105A
JK-
ELT106A
JK-
ELT107A
JK-
ELT108A
JK-
FON101A
JK-
JM101A
J--K-K-
JM102A
JM102A
JM102B
-K-K-
JM103A
JMI03B
JK-
LB101A
TRANSMITTER, ELT
TRANSMITTER, ELT
RECEPTACLE, 12 PIN
PIN
SWITCH, REMOTE
SWITCH, REMOTE
PLUG, 9 PIN
SOCKET
PLUG, 8 PIN
CLAMp
RECEPTACLE, 8 PIN
CLAMP
PLUG, 8 PIN
CLAMP
RECEPTACLE, 8 PIN
CLAMP
PHONE JACK
WASHERS
WASHERS (ALl')
SWITCH, MAGNETO
PLACARD
MAGNETO
MAGNETO, LEFT
MAGNETO, LEFT
CONNECTOR
MAGNETO, RIGHT
MAGNETO, RIGHT
CONNECTOR
C./B, BEACON, FLASHING
JK-JKJKJK-
LB102A
JK-JK-
LB104A
LB102A
LB102B
LB103A
LC101A
-JKJKJK-
LC102A
LC103A
LC104A
JK-
LC105A
JK-
LC106A
CUTLER-HAMMER
MOONEY
MOONEY
NOTES
ARTE.X
ELT110-4
DORNE & MARGOMN DM-ELT-8
MOLEX
03-06-2122
MOLEX
02-062103
ARTEX
110-416
C &K
7101K
MOLEX
03-06-2092
MOLEX
02-06-1103
AMP
205838-1
AMP
206062-1
AMP
205841-2
AMP
206062-1
AMP
205838-1
AMP
206062-1
AMP
205841-2
AMP
206062-1
SWITCHCFIAFT
C-11
SWITCHCRAFT
S-1028
SWlTCHCRAFT
S-1029
BENDIX/SCINTILLA 10-357210-9
BENDIX/SCINTILLA 10-187-468
BENDIX/SCINTILLA D-4LN2021
SLICK
6224
BENDIX/SCINTILLA 646979-1
BENDIX/SCINTILLA 10-382698
SLICK
6224
BENDIX/SCINTILLA 646979-1
BENDIX/SCINTILLA 10-382698
MOONEY
930023-24,3
UGHT, BEACON
WHELEN
ADAPTER
WHELEN
LIGHT,ANTI-COLLISION0NHITE) (AL'I-) WHELEN
UGHT,ANTI-COLUSION (RED) (ALT) WHELEN
PLUG, 3 PiN
AMP
SOCKET
AMP
WRLM-24
WRM-65
90038-20
90033-19
1-380303-0
60619-1
RECEPTACLE, 3 PIN
AMP
PIN
AMP
FUSEHOLDER
LITTEL
(ALT)
LITFEL
FUSE, 5A-3AG-SLO-BLO
LITTEL
SWITCH, CABIN LIGHT, FRONT CARLING
RESISTOR, DIM. (20 OHM 10W) DALE
LAMP HOLDER
H H SMITH
.LAMP
GE
LAMP HOLDER
H H SMITH
LAMP
GE
LAMP HOLDER
H H SMITH
LAMP
GE
1-480305-0
60620-1
155020
155120
313005
TILC64-1S-WH-FN
RH-10-20 OHM
1930
1818
1930
1818
1930
1818
12-98
91-20-03
65
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
JK-
LC107A
JKJKJK-
LC108A
LC109A
LC110A
JK-
LC111A
JK-
LC112A
JK-JK-
LC113A
JKJK-
LC118A
LC118B
JK-
LC119A
JK-
LC120A
JK-
LC121A
JK-
LC122A
JKJK-
LC123A
LC124A
JK-JKJK-
LC125A
JK-
LC128A
JKJKJKJKJKJK-
VENDOR
PART NO.
LAMP HOLDER
H H SMITH
LAMP
GE
SWITCH, CABIN UGHT, REAR CARUNG
RESISTOR, DIM. (20 OHM 10W) DALE
LAMP HOLDER
H H SMITH
LAMP
GE
LAMP HOLDER
H H SMITH
LAMP
GE
LAMP HOLDER
H H SMITH
LAMP
GE
LAMP HOLDER
H H SMITH
LAMP
GE
PLUG, 9 PIN
I1-FCANNON
CLAMP
LATCH
MODULE, AUTO OFF LIGHT
MOONEY
RECEPTACLE, 9 PIN
CLAMP
RING, LOCKING
DIODE
(ALl')
(ALl')
GE
DIODE
(ALl-)
(ALl')
GE
PLUG, 4 PIN
AMP
CLAMP
AMP
RECEPTACLE, 4 PIN
AMP
CLAMP
AMP
SWITCH, CABIN DOOR
NEWARK
RECEPTACLE, 2 PIN
AMP
PIN
AMP
PLUG, 2 PIN
AMP
SOCKET
AMP
SWITCH, BAGGAGE DOOR
NEWARK
RECEPTACLE, 2 PIN
AMP
PIN
AMP
PLUG, 2 PIN
AMP
SOCKET
AMP
1930
1818
TILC64-1S-WH-FN
RH-10-20 OHM
1930
1818
1930
1818
1930
1818
1930
1818
DE-9S
DE24657
DE51224-1
800268-501
DE-9P
DE24657
206514-1
1N2483
IN5080
3720-GE
1N2483
1N5060
3720-GE
206060-1
206062-1
206153-1
206062-1
89F5544
1-480319-0
60620-1
1-480318-0
60619-1
89F5544
1-480319-0
60620-1
1-480318-0
60619-1
LL101A
LL101A
LL102A
LL103A
LL104A
LL105A
C./B,LANDING LIGHT
C/B, LANDING LIGHT
SWITCH, LANDING LIGHT
LIGHT, LANDING, RIGHT
LIGHT, LANDING, LEFT
LIGHT, LANDING (COWL)
7277-2-25
930023-215
880052-521
4596
4596
4553
JKJK-
LN101A
LN102A
JK-
LN103A
JK-
LN104A
C/B, NAV LIGHT
MOONEY
UGHT ASSY, NAV, TAIL (LT WING) MOONEY
BULB
WHELEN
UGHT ASSY, NAV, TAIL (RT WING) MOONEY
BULB
WHELEN
. PLUG, 9 PIN (RT WING)
AMP
CLAMP
AMP
930023-201
800051-501
34-022-8030-85
800051-501
34-022-8030-85
206708-1
206062-1
• JK-
LN105A
RECEPTACLE, 9 PIN (RT WING)AMP
CLAMP
AMP
206705-1
206062-1
91-20-03
66
LC117A
LC126A
LC127
KLIXON
MOONEY
MOONEY
GE
GE
GE
12-98
NOTES
MOONEY AIRCRAFT CORPORATION
M20J
. SERVICE AN D MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
i
DESCRIPTION
VENDOR
PART NO.
AMP
AMP
206708-1
206062-1
JK-
LN106A
PLUG, 9 PIN (LT WING)
CLAMP
JK-
LN107A
JKJKJKJK-
LPIO1A
LP102A
LP103A
LP104A
JK-
LPIOSA
JK-
LP106A
JK-
LP107A
JK-
LP108A
JKJKJK-
LP109A
LP110A
LP111A
JKJK-
LP112A
LP113A
JK-
LP114A
JK-
LP115A
JK-
LP116A
JK-
LP117A
JK-
LP118A
JK-
LP119A
JK-
LP120A
JK-
LP121A
JK-
LP12?-A
JKJKJKJKJKJK-
LP123A
LP124A
LP125A
LP126A
LP127A
LP130A
JK-
LP133A
JKJK-
LP134A
LP134A
RECEPTACLE, 9 PIN (LT WING) AMP
CLAMP
AMP
C/B, GLARESHIELD UGHTS
KUXON
C/B, PANEL LIGHTS
KLIXON
DIMMER CONTROL BOX
MOONEY
PLUG, 9 PIN
AMP
CLAMP
AMP
UGHT, CONSOLE
DIAUGHT
LAMP (28V)
GE
LAMP (ALE)
GE
LIGHT, CONSOLE
DIALIGHT
LAMP (28V)
GE
LAMP (ALT)
GE
PLUG, 4 PIN
AMP
CLAMP
AMP
RECEPTACLE, 4 PiN
AMP
CLAMP
AMP
RECEPTACLE, COMPASS LIGHT DEANS
PLUG, COMPASS LIGHT
DEANS
LAMP, COMPASS LIGHT (28V) GE
(ALE).
GE
LAMPS, GL,/SHLDLIGHTS (14 ea) GE
LIGHT, OXYGEN
SLOAN
LAMP (28V)
GE
UGHT, OXYGEN
SLOAN
LAMP (28V)
GE
PLUG, 2 PIN
AMP
SOCKET
AMP
RECEPTACLE, 2 PIN
AMP
PIN
AMP
PLUG, 2 PIN
AMP
SOCKET
AMP
RECEPTACLE, 2 PIN
AMP
PIN
AMP
PLUG, 2 PIN
AMP
SOCKET
AMP
RECEPTACLE, 2 PIN
AMP
PIN
AMP
POST LIGHT
WHELEN
LAMP (14V)
GE
POST LIGHT
WHELEN
LAMP (14V)
GE
LIGHTING TRAY (RPM)
B& D
LIGHTING TRAY (M/P)
UI
LIGHTING TRAP (-I-IT/EGT)
B &D
PLUG, 20 PIN
MOONEY
RECEPTACLE, 20 PIN
MOONEY
RHEOSTAT, MAP LIGHT (500 OHM) NEWARK
KNOB
NEWARK
.RHEOSTAT, MAP LIGHT (500 OHM) NEWARK
KNOB
N_ARK
MAP LIGHT
SLOAN
LAMP (28V)
GE
LAMP (14V)
GE
12-98
NOTES
206705-1
206062-1
7277-2-5
7277-2-5
800049-501
206708-1
206956-1
270-1930-0171-702
327
385
270-1930-0171-702
327
385
206060-1
206062-1
206153-1
206062-1
DEA90020MALEHALF
DEA90020FEMALEHALF
327
327 (AVIATION RED)
327
855S-0-U
327
855S-0-U
327
1-480318-0
60619-1
1-480319-0
60620-1
1-480318-0
60619-1
1-480319-0
60620-1
1-480318-0
60619-1
1-480319-0
60620-1
A350CN1W-BK-SH14
330
A350CN1W-BK-SH14
330
0221-128
BA28-24-BW3
0221-128
930022-501
930021-502
09F981
57F2368
09F981
57F2368
855S-0-U
327
330
6
6
6
91-20-03
67
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
JK-
LP135A
-JK-
LP136A
JK-
LP137A
-JKJKJK-
LR101A
LR102A
LR103A
JKJK-
LR104A
LR105A
JK-
LR105A
JKJK-
LR107A
LR108A
JKJK-
LR109A
LRllOA
JK-
LR111A
JKJKJK-
LSIO1A
LSIO2A
LS103A
JK-
LS104A
JK-
LS105A
JKJKJK-
LS106A
LSIOTA
LSIO8A
JK-JK-
LS109A
JKJKJK-
LS111A
LS112A
LS113A
JK-
LS114A
JK-JK--
LS115A
91-20-03
68
LS110A
LS116A
DESCRIPTION
VENDOR
PART NO.
MAP LIGHT
LAMP (28V)
LAMP (14V)
POST LIGHT
LAMP (28V)
SLOAN
GE
GE
WHELEN
GE
855S-0-U
327
330
A350CN1W-BK-SH28
327
POST LIGHT
WHELEN
A350CNIW-BK-SH14
LAMP (14V)
GE
C/B, RECOGNITION LIGHTS
MOONEY
LIGHT, RECOGNITION, LW
MOONEY
PLUG, 2 PiN
AMP
SOCKET
AMP
RESISTOR
DALE
RECEPTACLE, 2 PIN
AMP
PIN
AMP
PLUG, 2 PIN
AMP
SOCKET
AMP
UGHT, RECOGNITION, RW
MOONEY
PLUG, 2 PIN
AMP
SOCKET
AMP
RESISTOR
DALE
RECEPTACLE, 2 PIN
AMP
PIN
AMP
PLUG, 2 PIN
AMP
SOCKET
AMP
C/B, STROBE UGHT
MOONEY
POWER SUPPLY, LT WING
WHELEN
RECEPTACLE, POWER SUPPLY AMP
PIN
AMP
RECEPTACLE, POWER SUPPLY AMP
PIN
AMP
PLUG, STROBE LIGHT ASSY
AMP
330
930023-231
880049-501
1-480318-0
60619-1
RH50-7,5 OHM
1-480319-0
60620-1
1-480318-0
60619-1
880049-501
1-480318-0
60619-1
RH50-7.5 OHM
1-480319-0
60620-1
1-480318-0
60619-1
930023-237
01-0770329-00
1-480305-0
60620-1
1-480305-0
60620-1
1-480303-0
SOCKET
AMP
STROBE/NAV LIGHT, LT WING WHELEN
POWER SUPPLY, LT WING
WHELEN
RECEPTACLE, POWER SUPPLY AMP
PIN
AMP
RECEPTACLE, POWER SUPPLY AMP
PIN
AMP
PLUG, STROBE LIGHT ASSY
AMP
60619-1
A650-PR-D-M-28
01-0770329-00
1-480305-0
60620-1
480305-0
60620-1
1-480303-0
SOCKET
AMP
STROBE/NAV LIGHT, RT WING WHELEN
POWER SUPPLY, TAIL
WHELEN
RECEPTACLE, POWER SUPPLY AMP
PIN
AMP
RECEPTACLE, POWER SUPPLY AMP
PIN
AMP
PLUG, 4 PIN
AMP
CLAMP
AMP
.RECEPTACLE, 4 PIN
AMP
CLAMP
AMP
60619-1
A650-PR-D-M-28
01-0770329-00
1-480305-0
60620-1
1-480305-0
60620-1
206060-1
206062-1
206153-1
206062-1
12-98
NOTES
6
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
JK-
LS117A
JKJK-
LS118A
LS119A
JK-
LS129A
JK-
LS121A
JKJKJKJKJKJK-
LTI01A
LT102A
LT103A
LT104A
MA101A
MA102A
JKJK-
MA103A
MA104A
JKJKJK-
MB101A
MB102A
MB103A
JKJKJKJKJKJKJKJKJKJKJKJKJKJKJKJKJKJKJKJKJKJKJKJKJKJKJKJKJK-
MB104A
MB105A
MB106A
MB107A
MB108A
MB109A
MB110A
MB111A
MB112A
MBl13A
MB114A
MB115A
MB116A
MBl17A
MB118A
MBl19A
MB120A
MB121A
MB122A
MB128A
MB124A
MB125A
MB126A
MB127A
MB128A
MB129A
MB130A
MB131A
MC102A
DESCRIPTION
VENDOR
PART NO.
PLUG, STROBE LIGHT ASSY
SOCKET
UGHT ASSY, TAIL STROBE
RECEPTACLE, 3 PIN
PIN
RECEPTACLE, 3 PIN
PIN
RECEPTACLE, 3 PIN
PIN
AMP
AMP
MOONEY
AMP
AMP
AMP
AMP
AMP
AMP
1-480303-0
60619-1
470013-501
1-480305-0
60620-1
1-480305-0
60620-1
1.480305-0
60620-1
C/B, TAXl LIGHT
SWITCH, TAXI LIGHT
BULB, TAXI, R/W (28V)
BULB, TAXI, L/W (28V)
RECEPTACLE, AUX POWER
RELAY, AUX POWER
(ALT)
DIODE
DIODE
(ALl')
(ALT)
C/B, AVIONICS MASTER
RELAY, AVIONICS MASTER
DIODE
(ALT)
(ALT)
AVIONICS BUS BAR #1
AVIONICS BUS BAR #2
AVIONICS BUS BAR #3
C/B, INTERCOM
C/B, COM 1
C/B, NAV 1
C/B, AUDIO
C/B, PHONE
C/B, ADF
C/B, COM 2
C/B, NAV 2
C/B, TRANSPONDER
C/B, ENCODER
C./B,STERO
C/B, DME
C./B,R/NAV
C/B, STORMSCOPE
C/B, LORAN
C/B, RMI
C/B, AUTOPILOT/TRIM
C/B, NP ALERT
C/B, INVERTER
C/B, ART. HORIZ.
C/B, HSI
C/B, YAW DAMP.
C./B,TELEPHONE
' C/B, VME
C/B, RADIO ALT.
CIGAR LIGHTER
KLIXON
MOONEY
GE
GE
7277-2-25
880052-523
4596
4596
AN2552-SA
6041H202
6041H202A
10H3P
1N2488
i N5060
8720-GE
930023-213
26.64.01
1N2483
1N5060
8720-GE
913127-67
913127-67
913127-87
7277-2-7.5
7277-2-10
7277-2-7.5
7277-2-7.5
7277-2-7.5
7277-2-7.5
7277-2-10
7277-2-7.5
7277-2-7.5
7277-2-7.5
7277-2-7.5
7277-2-7.5
7277-2-7.5
7277-2-7.5
7277-2-7.5
7277-2-7.5
7277-2-107277-2-7.5
7277-2-7.5
7277-2-2
7277-2-2
7277-2-7.5
7277-2-7.5
7277-2-7.5
7277-2-7.5
800336-503
CUTLER-HAMMER
CUTLER-HAMMER
SARKES-TARZlAN
GE
MOONEY
KISSLING
GE
MOONEY
MOONEY
MOONEY
KLIXON
KLIXON
KUXON
KLIXON
KLIXON
KLIXON
KLIXON
KUXON
KLIXON
KLIXON
KLIXON
KLIXON
KLIXON
KLIXON
KUXON
KLIXON
KLIXON
KLIXON
KLIXON
KLIXON
KLIXON
KLIXON
KLIXON
KUXON
KUXON
MOONEY
12-98
NOTES
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
7
91-20-03
69
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
JKJK-
MC102A
ME101A
(ALT)
CLOCK
(OPT)
LIGHT TRAY
CASCO
MID-CONTINENT
MID-CONT.
MID-CONT.
208292
MD-88L
MD-88L (ET)
BA28-24-BW2
JK-
MIC101A
JKJK-
MIC102A
MIC103A
JACK, MICROPHONE
WASHERS
WASHERS (ALT)
SWITCH, MIC KEY, PILOT
SWITCH, MIC KEY, CO-PILOT
SWlTCHCRAFT
SWlTCHCRAFT
SWlTCHCRAFT
CUTLER-HAMMER
CUTLER-HAMMER
C-12B
S-1028
S-1029
SAIRV20
SAIRV20
JKJKJKJK-
MP101A
MP102A
MP103A
MP104A
JK-
MP105A
J-J--
NF101A
NF102A
-KJK-
NF102A
NF103A
JK-
NF104A
-K-K-K-K-K-
NF105A
NF107A
NF108A
NF108B
NF109A
-K-
NF110A
-K-
NP101A
-K-K-K-
NP102A
NP103A
NP104A
JKJKJK-KJK-
PA101A
PAl 02A
PAl 03A
PAl 03B
PA104A
JK-
PA105A
JK-J--
PA106A
91-20-03
70.
PA107A
C/B, PROP DE-ICE
MOONEY
TIMER, PROP DE-ICE
B.F. GOODRICH
MONITOR,CURRENT, PROP DE-ICE MOONEY
PLUG, 9 PIN
AMP
CLAMP
AMP
TERMINAL BLOCK
McCAULEY
930023-223
3E1899-1
800221-505
206708-1
206966-1
C-40521
C/B, BOOST PUMP
PUMP, FUEL BOOST
(ALl')
PUMP, BOOST
PLUG, 4 PIN
CLAMP
RECEPTACLE, 4 PIN
CLAMP
C/B, HI BOOST PUMP
C/B, LO BOOST PUMP
REGULATOR, FUEL PUMP
REGULATOR, FUEL PUMP
RECEPTACLE, 4 PIN
CLAMP
PLUG, 4 PIN
CLAMP
980023-211
8163B
A8163B
10054B
206060-1
206062-1
206153-1
206062-1
930023-219
930023-217
VR-536
DGB-1
206153-1
206062-1
206060-1
206062-1
MOONEY
WELDON
WELDON
WELDON
AMP
AMP
AMP
AMP
MOONEY
MOONEY
ELECTRO-DELTA
AMER. PROD
AMP
AMP
AMP
AMP
FUSEHOLDER, PRIMER, DIFFUSER LI']'TEL
(ALT)
LITTEL
FUSE (10A SLO BLO)
LI'I-FEL
SWITCH, PRIME R
CARLING
PRIMER, DIFFUSER
TCM
DIODE
(ALE)
(ALl')
GE
155020
155120
313010
TIGK6B-IF-WH-A
633862-2
1N2483
1N5060
3720-GE
C/B, ALTERNATOR, RT
C/B, FIELD, RT. ALT
SWITCH, ALT. FLD.(OPT)
SWITCH, ALT. FLD. (STD)
VOLTAGE REGULATOR
(ALT)
(ALT)
RECEPTACLE, 9 PIN
CLAMP
'PLUG, 9 PIN
'CLAMP
ALTERNATOR (STD)
(ALl)
41-3-$34-LN2-041800
7277-2-5
880052-525
880052-503
880270-501
VR-802
DGR-2
206708-1
206966-1
206705-2
206966-1
LW-14367
ALU-6421-LS
ETA
KLIXON
MOONEY
MOONEY
MOONEY'
AUXILEC
AM PROD
AMP
AMP
AMP
AMP
LYCOMING
PRESTOLITE
12-98
NOTES
'MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
NOTES
(
-
-K-
PA107A
JKJK-
PA108A
PA109A
-K-K-K-
PAl 10A
PAl 11A
PAl12A
-K-K--K-
PA112A
PAl 13A
-K-
PAl 15A
-K-K-
PAl 16A
PAl 17A
JK-
PAl 18A
-K-
PAl 19A
JK-
PA120A
JK--KJK-
PA121A
JK-
PA123A
JK--
PA124A
JKJK-
PB101A
PB102A
JK-
PB103A
JKJKJKJKJKJKJKJKJKJKJK-
PB104A
PB105A
PB106A
PB107A
PB108A
PB109A
PB110A
PB111A
PB112A
PB113A
PB114A
PAl 14A
PA122A
PA122A
ALTERNATOR (STD)
TCM
649280
(ALl')
TCM
649172
GEAR ASSY
TCM
649123
FILTER
MOONEY
880014-501
CAPACITOR
MALLORY
CGS302U-05OR2C
(ALT)
MALLORY
CGS292U-050R3C
C/B
ETA
41-3-$34-LN2-041800
C/B
KUXON
7277-2-5
VOLTAGE REGULATOR (DUAL) ELECTRODELTA
VR-802
(ALT)(DUAL)
AM. PROD/PREC.FLT DGR-2
REGULATOR, DUAL ALTERNATOR MOONEY
800270-503
RECEPTACLE, 9 PIN
AMP
206708-1
CLAMP
AMP
206966-1
PLUG, 9 PIN
AMP
206705-2
CLAMP
AMP
206966-1
ALTERNATOR (OPT)
TCM
649280
(ALT)
TCM
649172
GEAR ASSY
TCM
649123
FILTER
MOONEY
880014:501
CAPACITOR
MALLORY
CGS302U-050R2C
(ALT)
MALLORY
CGS292U-050R30
SENSOR, CURRENT
MICRO
CSLA1GE
ELEMENT, SENSOR
MICRO
SS-37126
SENSOR, CURRENT
MICRO
CSLA1GE
ELEMENT, SENSOR
MICRO
SS-37126
PLUG, 9 PIN
AMP
206705-2
CLAMP
AMP
206966-1
RECEPTACLE, 9 PIN
AMP
206708-1
CLAMP
AMP
206966-1
ADPT'R, ANALOG, CUR. SENSOR MOONEY
810088-504
PLUG, 16 PIN
AMP
208037-1
CLAMP
AMP
206070-1
RECEPTACLE, 16 PIN
AMP
206036-3
CLAMP
AMP
206070-1
DIODE
1N2483
(AL-F)
1N5060
(ALT)
GE
3720-GE
BA'I-I-ERY
RELAY, BAI-I-ERY
(ALT)
DIODE
(ALT)
(ALT
SWITCH, MASTER
C/B, BA'I-I'ERY
C/B
BUS BAR #1
BUS BAR #2
BUS BAR #3
BUS BAR #4
BUS BAR#5
.BUS BAR #6
BUS BAR #7
BUS BAR #8
GILL
CUTLER-HAMMER
CUTLER-HAMMER
GE
MOONEY
ETA
ETA
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
12-98
10
10
10
G-243
6041H202
6041H202A
1N2483
1N5060
3720-GE
880052-501
41-3-$34-LN2-041800
41-3-S34-LN2-40A
913127-89
913127-75
913127-75
913127-77
913127-77
913127-73
913127-81
913127-77
91-20-03
71
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
JKJKJKJKJ--
PB115A
PB116A
PBl17A
PB120A
PB121A
J---
PB122A
JK-
PL201A
JK-
PL203A
JKJK-
PL204A
PL205A
JKJKJKJK-
PL.206A
PL207A
PL208A
PL2.09A
JK-
PI-210A
JKJKJK-
PL211A
PL212A
PL216A
JK-
PL217A
JK-
PL218A
JK-
PL.219A
JK-
PL220A
JK-
PL221A
JK-
PL222A
JK-
PL2.22S
JK-
PL225A
JK-
PI-226A
JK-
PL227A
JK-
PL228A
91-20-03
72
DESCRIPTION
VENDOR
PART NO.
BUS BAR #9
BUS BAR #10
BUS BAR #11
GROUND/DIMMER BOX
PLUG, 3 PIN
CLAMP
RECEPTACLE, 3 PIN
CLAMP
MOONEY
MOONEY
MOONEY
MOONEY
AMP
AMP
AMP
AMP
913127-75
913127-83
913127-59
800228-501
206037-2
206070-1
206207-1
206070-1
PLUG, 37 PIN
CLAMP
PLUG,
CLAMP
PLUG, 26 PIN
PLUG, 28 PIN
CLAMP
PLUG, 20 PIN
PLUG, 20 PIN
PLUG, 14 PIN
PLUG, 9 PIN
CLAMP
PLUG, 9 PIN
CLAMP
PLUG, 84 PIN
PLUG, 14 PiN
PLUG, 16 PIN
CLAMP
PLUG, 16 PIN
CLAMP
PLUG, 16 PIN
CLAMP
PLUG, 28 PIN
CLAMP
PLUG, 4 PIN
CLAMP
PLUG, 4 PIN
CLAMP
PLUG, 9 PIN
CLAMP
PLUG, 16 PIN
CLAMP
PLUG, 32 PIN
CLAMP
SOCKET
SOCKET
PLUG, 32 PIN
CLAMP
SOCKET
SOCKET
PLUG, 6 PIN
CLAMP
(ALT)
. SOCKET
SOCKET
PLUG, 20 PIN
AMP
AMP
AMP
AMP
MOONEY
AMP
AMP
MOONEY
MOONEY
MOONEY
AMP
AMP
AMP
AMP
MOONEY
MOONEY
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
MATRIX SCIENCE
MAT/SCI
MAT/SCI
MAT/SCI
MATRIX SCIENCE
MAT/SCI
MAT/SCI
MAT/SCI
MATRIX SCIENCE
MAT/SCI
MAT/SCI
MAT/SCI
MAT/SCI
MOONEY
206150-1
206138-1
206037-1
206070-1
930021-505
205839-3
206070-1
930021-501
930021-501
930021-001
206708-1
206966-1
206708-1
206966-1
930021-507
930021-001
206037-1
206070-1
206037-1
206070-1
206037-1
206070-1
205839-3
206070-1
206060-1
206062-1
206060-1
206062-1
206708-1
206966-2
206037-1
206070-1
M83723/86R2232N
M85049/52-1-22N
5100-001-0012
5100-001-0020
M83723/86R2232N
M85049/52-1-22N
5100-001-0012
5100-001-0020
MS3106A-28-22S
MS3057-16B
MS3057-16A
5100-001-0012
5100-001-0020
930021-501
12-98
NOTES
-
8
8
8
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
JK-
PL229A
JKJK-
PL230A
PL231A
JKJK-
PL232A
PL233A
JKJK-
PS101A
PS102A
JK-
PS103A
J--
PS104A
-K-
PS104A
JKJKJKJK-
RB101A
RB102A
RB102B
RB103A
JK-
RB104A
JKJK-
RC201A
RC203A
JKJK-
RC204A
RC205A
JKJKJKJK-
RC206A
RC207A
RC208A
RC209A
JK-
RC210A
JKJKJK-
RC211A
RC212A
RC214A
JK-
RC215A
JK-
RC220A
JK-
RC221A
JK-
RC222A
JK-
RC222B
DESCRIPTION
VENDOR
PART NO.
PLUG, 16 PIN
CLAMP
PLUG, 14 PIN
PLUG, 16 PIN
CLAMP
PLUG, 14 PIN
PLUG, 4 PIN
CLAMP
AMP
AMP
MOONEY
AMP
AMP
MOONEY
AMP
AMP
206037.-1
206070-1
830021-001
206037-1
206070-1
930021-001
206060-1
206062-1
C/B, STARTER SOLENOID
SOLENOID, STARTER
(ALT)
DIODE
(ALT)
(ALT)
STARTER
(ALl')
STARTER
(ALl)
KLIXON
CUTLER-HAMMER
CUTLER-HAMMER
GE
PRESTOUTE
LYCOMING
TCM
TCM
7277-2-5
6041H202
6041H202A
1N2483
1N5060
3720-GE
MHB-4016
LW-15572
646275
637847
C/B, RADIO BLOWER
BLOWER, RADIO
BLOWER, RADIO
FILTER, NOISE
(ALl')
PLUG, 2 PIN
SOCKET
KLIXON
TRW
BENDIX-KING
ARCHER
SPRAGUE
MOLEX
MOLEX
7277-2-5
19A2790
KA0033-01
278-103
5JX5104A
03-06-1023
02-06-1103
RECEPTACLE, 37 PIN
RECEPTACLE, 3 PIN
CLAMP
RECEPTACLE, 26 PIN
RECEPTACLE, 28 PiN
CLAMP
RECEPTACLE, 20 PIN
RECEPTACLE, 20 PIN
RECEPTACLE, 14 PIN
RECEPTACLE, 9 PIN
CLAMP
RECEPTACLE, 9 PIN
CLAMP
RECEPTACLE, 34 PIN
RECEPTACLE, 14 PIN
RECEPTACLE, 14 PIN
CLAMP
RECEPTACLE, 14 PIN
CLAMP
RECEPTACLE, 4 PIN
CLAMP
RECEPTACLE, 4 PiN
CLAMP
RECEPTACLE, 4 PIN
, CLAMP
RECEPTACLE, 9 PIN
CLAMP
AMP
AMP
AMP
MOONEY
AMP
AMP
MOONEY
MOONEY
MOONEY
AMP
AMP
AMP
AMP
MOONEY
MOONEY
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
AMP
206151-2
206036-2
206070-1
930021-506
206152-1
206070-1
930021-502
930021-502
938021-002
206705-2
206966-1
206705-2
206966-1
930021-508
930021-002
206044-1
206070-1
206044-1
206070-1
206153-1
206062-1
206153-1
206062-1
206706-1
206966-1
206037-1
206070-1
12-98
NOTES
91-20-03
73
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
JK-
RC225A
--JK--
RC226A
JK-
RC227A
JKJK-
RC230A
RC231A
JKJK-JK-
RC232A
RC233A
JKJKJK-
SB101A
SB102A
SB103A
JK-
SB104A
JKJK-
SB105A
SB106A
JK-JK-
SB107A
JK-
SB109A
JK-
SB110A
JKJKJKJKJK-
SB111A
SB112A
SB113A
SB114A
SB115A
JK-
SB116A
JK-
SB117A
91-20-03
74
RC277A
SB108A
DESCRIPTION
VENDOR
PART NO.
RECEPTACLE, 32 PIN
CLAM P
PIN
PIN
BOOT
(ALT)
RECEPTACLE, 32 PIN
CLAMP
PIN
PIN
BOOT
(ALT)
RECEPTACLE, 6 PIN
(ALT)
CLAM P
(ALl')
RECEPTACLE, 14 PIN
RECEPTACLE, 16 PIN
CLAMP
RECEPTACLE, 14 PIN
RECEPTACLE, 4 PIN
CLAMP
RECEPTACLE, AUDIO
CLAMP
MATRIX SCIENCE
MAT/SCI
MAT/SCI
MAT/SCI
MAT/SCI
MAT/SCI
MAT/SCI
MAT/SCI
MAT/SCI
MAT/SCI
MAT/SCI
MAT/SCI
M83723/83K2232N
M85049/52-1-22N
5000-054-0020
5000-054-0012
MS3420-14
MS3420-16
M83723/83K2232N
M85049/52-1-22N
5000-054-0020
5000-054-0012
MS3420-14
MS3420-16
MS3100K-28-2P
MS3100KE-28-2P
MS3057-16B
MS3057-16A
930021-002
206036-1
206070-1
930021-002
206060-1
206062-1
206152-1
206070-1
C/B, SPEED BRAKE
SWITCH, SPEED BRAKE
PLUG, 3 PIN
SOCKET
RECEPTACLE, 3 PIN
PIN
RELAY, SPEED BRAKE
DIODE
(ALT)
(ALl-)
PLUG, 4 PIN
(ALl-)
RECEPTACLE, 4 PiN
CLAMP
PLUG, 8 PIN
CLAMP
RECEPTACLE, 8 PIN
CLAMP
MOTOR, LEFT
SWITCH, DEPLOY LIMIT
SWITCH, RETRACT LIMIT
SOLENOID, CLUTCH
PLUG, 8 PiN
CLAMP
RECEPTACLE, 8 PIN
CLAMP
PLUG, 8 PIN
. CLAMP
MOONEY
AMP
AMP
MOONEY
AMP
AMP
AMP
AMP
KUXON
PRECISE FLT
AMP
AMP
AMP
AMP
PRECISE FLT
GE
AMP
AMP
AMP
AMP
AMPM
AMP
AMP
AMP
PRECISE FLT
PRECISE FLT
PRECISE FLT
PRECISE FLT
AMP
AMP
AMP
AMP
AMP
AMP
12-98
7277-2-3
01265
1-380303-0
60619-1
1-380305-0
60820-1
01384
1N2483
1N5060
3720-GE
206060-1
206062-1
206153-1
206062-1
205838-1
206062-1
205841-2
206062-1
01532
01505
01505
01678
205838-1
206062-1
205841-2
206062-1
205838-1
206062-1
NOTES
.
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
r'
DESCRIPTION
VENDOR
PART NO.
RECEPTACLE, 8 P]N
CLAMP
MOTOR, RIGHT
SWITCH, DEPLOY LIMIT
SWITCH, RETRACT UMIT
SOLENOID, CLUTCH
PLUG, 8 PIN
CLAMP
RECEPTACLE, 8 PIN
CLAMP
AMP
AMP
PRECISE FLT
PRECISE FLT
PRECISE FLT
PRECISE FLT
AMP
AMP
AMP
AMP
205841-2
206062-1
01582
01505
01505
01678
205838-1
206062-1
205841-2
206062-1
NOTES
JK-
SB118A
JKJKJKJKJK-
SB119A
SB120A
SB121A
SB122A
SB123A
JK-
SB124A
JKJK-
SPK101A
SPK102A
SPEAKER, CABIN
PLUG, 2 PIN
SOCKET
ARCHER
AMP
AMP
12-1703
1-480318-0
60618-1
JK-
SPK108A
RECEPTACLE, 2 PIN
PIN
AMP
AMP
1-480818-0
60620-1
JK-
WD101A
FUSEHOLDER
(ALT)
FUSE, 1A
MTTEL
LII-rEL
LITTEL
155020
155120
313001
JKJK-
WE101A
WE102A
J--
WE103A
"K--
WE103A
JKJK-
WE104A
WE105A
KLIXON
SLOAN
GE
MICRO
MICRO
MICRO
MICRO
MALLORY
JK-
WE106A
JKJK-
WE107A
WE108A
JK-
WE109A
C/B, GEAR WARNING
LIGHT, GEAR DOWN
BULB
SWITCH, THROI-rLE
ACTUATOR
SWITCH, THROI-rLE
ACTUATOR
HORN, GEAR WARNING
DIODE
(ALT)
(ALT)
DIODE
(ALl-)
(ALT)
RESISTOR
PLUG, 4 PIN
CLAMP
RECEPTACLE, 4PIN
CLAMP
7277-2-1
855S-0-U
327
V3-1
JV'5
lSE1-T
JE-17
SC628P
1N2483
1N5060
3720-GE
1N2483
1N5060
3720-GE
RC42GF102JIK OHM2W
206060-1
206062-1
206153-1
206062-1
JKJK-
WP101A
WP102A
JK-
WP106A
JKJKJKJK-
WS101A
WS102A
WS103A
WS104A
JK-
WT101A
GE
GE
ALLEN BRADLEY
AMP
AMP
AMP
AMP
MONITOR, CURRENT, PITOT HEAT MOONEY
PLUG, 9 PIN
AMP
CLAMP
AMP
FUSEHOLDER
LITI'EL
(ALT)
Lll-FEL
FUSE (5A)
Lll-rEL
800221-505
206705-2
206966-1
155020
155120
313005
C/B, STALL WARNING
HORN, STALL WARN
RESISTOR
SWITCH, STALL WARN
'(ALl')
(ALT)
KLIXON
MALLORY
ALLEN BRADLEY
SAFE FLIGHT
MICRO SWITCH
MOONEY
7277-2-1
SC628
RC42GF102J1K OHM2W
C46001
V3-2451-D8
800364-507
C/B
KUXON
7277-2-2
12-98
9
91-20-03
75
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
28 VOLT ELECTRICAL EQUIPMENT CHART
CODE
J--
WT102A
DESCRIPTION
VENDOR
PART NO.
ANNUNCIATOR
MOONEY
880048-501
(ALT)(USA)
(ALT')(FRANCE)
ANNUNCIATOR
(ALT) LEGEND (USA)
(AL'r) LEGEND (FRANCE)
PLUG, 87 PIN
CLAMP, RT ANGLE
LOCK RETAINER
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
880048-601
880048-603
880048-501
880048-805
880048-607
DC-87S
DC19977-3
DC51222-1
ANNUNCIATOR (ATS)
BULB
C/B, VACUUM WARN
SWITCH, VACUUM WARN
RECEPTACLE, 4 PIN
CLAMP
MOONEY
880025-521
CHICAGO MINATURE CM-7327
KLIXON
7277-2-2
MOONEY
880012-501
AMP
206153-1
AMP
206062-1
-K-
WT102A
JK-
WT103A
JK-
W'I'104A
JKJKJK-
WV101A
WV102A
WV103A
JK-
WV104A
PLUG, 4 PIN
CLAMP
AMP
AMP
206060-1
206062-1
JK-
WWl01A
SWITCH, ALTERNATE AIR
CHERRY
E51-50B
NOTES
NOTES:
1. USE AN4076-1 ADAPTER.
2. USE WITH FT101/FT101A FUEL FLOW SYSTEM.
3. USE WITH SHADIN FUEL FLOW SYSTEM.
4. SHADIN MODEL NO. INTERFACE WITH II MORROW APOLLO, ARNAV AND NORTHSTAR LORAN
SYSTEMS.
5. SHADIN MODEL NO. INTERFACE WITH BENDIX/KING KLN88.
6. USE 1 EACH M885334--21OR M2898 (ALAN BRADLEY) INTERNAL TOOTH LOCKWASHER WITH EACH
LIGHT IF NOT SUPPLIED BY SLOAN.
7. MAXIMUM CIRCUIT BREAKER RATING IS SHOWN. AMPERAGE OF INSTALLED CIRCUIT BREAKER IS
DETERMINED BY PARTICULAR UNIT INSTALLED.
8. USE MS3420 OR AN3420-14 OR -16 BOOT WITH CONNECTOR.
9. PART OF 800336-501 INSTALLATION.
10.
800270-503 REPLACES SINGLE UNIT VOLTAGE REGULATORS (2 EA) FOR DUAL ALTERNATOR
INSTALLATIONS.
91-20-03
76
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
91-20-04
- ELECTRICAL SYSTEM HARDWARE CHART - 14 VOLT SYSTEMS
S/N 24-1686-14 THRU 24-2999-14 (ATSONLY), MOONEY DRAWING NUMBER 800263 (E7)
(Peculiar14 voltcomponentslistedhere - See 91-20-03 for commoncomponents28 voltand 14 volt)
** -ACTUAL USAGE DETERMINED BY MASTER SCHEMATIC - **
CODE DESCRIPTION
VENDOR
PART NO.
NOTES
1414-
CF105A
CVl06A
FLAP ACTUATOR
VACUUM PUMP
MOONEY
AEROSAFE
750105-001
820904-1
14-
DB102A
TURN CO-ORDINATOR
(ALT)
U.I.
ELEC GYRO
9112 CODE N.9
1394T100-3Z
14-
DG102A
INSTUMENT MODULE
MOONEY
880059-511
14-
DM101A
HOUR METER
HOUR METER IALT)
HOBBS
15006
DATCON INSTR CO SG-70
14-
DP102A
PITOT, HEATED
PITOT, HEATED CALT)
AERO INSTR.
PH502-12
AN5812
14-
DT105A
INDICATOR, EGT
WIRE, LEAD
MOONEY
ALCOR
660109-008
01-005-78
14141414-
EG105A
EG110A
EGl12A
EG114A
C/B,ACTUATOR, GEAR
RELAY, GEAR UP
RELAY, GEAR DOWN
ACTUATOR, GEAR
ACTUATOR, GEAR (ALT)
KLIXON
CUTLER-HAMMER
CUTLER-HAMMER
MOONEY
MOONEY
7277-2-15
6041H105A
6041H105A
560254-501
880037-501
14-
JM102A
MAGNETO
BENDIX/SCINTILLA
D-4LN2021
14-
LB102A
BEACON, ROTATING
ADAPTER
WHELEN
WHELEN
WRML-12
WRM-65
1414-
LC103A
LC104A
14-
LC105A
14-
LC106A
14-
LC107A
1414-
LC109A
LC110A
14-
LC111A
14-
LC112A
14-
LCl13A
RESISTOR, DIMMING C5OHM 10W) DALE
LAMP HOLDER
HH SMITH
LAMP
GE
LAMP HOLDER
HH SMITH
LAMP
GE
LAMP HOLDER
HH SMITH
LAMP
GE
LAMP HOLDER
HH SMITH
LAMP
GE
RESISTOR, DIMMING (5 OHM 10 W) DALE
LAMP HOLDER
HH SMITH
LAMP
GE
LAMP HOLDER
HH SMITH
LAMP
GE
LAMP HOLDER
HH SMITH
LAMP
GE
LAMP HOLDER
HH SMITH
LAMP
GE
RH-10-5 OHM
1930
1816
1930
1816
1930
1816
1930
1816
RH-10-5 OHM
1930
1816
1930
1816
1930
1816
1930
1816
141414-
LL101A
LL102A
LN102A
14-
LN103A
14-
LP103A
C/B, LANI_ING LIGHT
MOONEY
LANDING LIGHT
GE
. LIGHT ASSY, NAV, TAIL (LT WING) MOONEY
BU LB
WH ELEN
LIGHT ASSY, NAV, TAIL (RT WING) MOONEY
BULB
WHELEN
DIMMER CONTROL BOX
MOONEY
930023-215
4522
800051-505
34-021-2030-85
800051-505
34021-2030-85
800049-503
12-98
91-20-04
77
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
:
VENDOR
PART NO.
NOTES
!
14-
LP105A
UGHT, CONSOLE
DIAUGHT
LAMP
GE
LIGHT, COMPASS
GE
LIGHT, COMPASS (ALE)
GE
GLARESHIELD UGHTS (14 F_A)GE
RHEOSTAT, MAP LIGHT (100 OHM) NEWARK
KNOB
NEWARK
RHEOSTAT, MAP LIGHT (100 OHM) NEWARK
KNOB
NEWARK
LIGHTASSY, STROBE/NAV(LWG) WHELEN
LIGHT ASSY, STROBE/NAV(R WG) WHELEN
270-1930-0171-702
370
330
930 AVIATION RED
330
09F976
57F2366
99F976
57F2366
A650-PR-D-M-14
A650-PR-D-M-14
14-
LP111A
1414-
LPl12A
LP131A
14-
LP182A
1414-
LS106A
LS111A
141414-
MA102A
MB102A
ME101A
RELAY, AUX POWER
RELAY, AVIONICS MASTER
CLOCK
CLOCK (ALl)
CONNECTOR, 4 PIN
PINS
CONNECTOR, 4 PIN (ALT)
PINS
CUTLER-HAMMER
KISSLING
MID-CONT.
PORSCHE
MID-CONT.
MID-CONT.
PORSCHE
PORSCHE
6041HI05A
26.64.21
MD-89
944.641.213.00
6016117
6016125
944.612.217.00
999.652.351.12
14-
ME102A
14-
NF102A
PUMP, BOOST
PUMP, BOOST (ALl')
WELDON
WELDON
8163A
A8163A
14-
PA104A
14-
PA107A
14.:
1414-
PB101A
PB102A
PL204B
REGULATORI VOLTAGE (STD)
REGULATOR, VOLTAGE (ALT)
REGULATOR, VOLTAGE (ALT)
ALTERNATOR, (STD)
ALTERNATOR (ALE)
BATTERY
RELAY, BA"i-IERY
PLUG, 14 PIN
MOONEY
680016-503
AM. PROD/PREC.FLT DGR-1
MOONEY
660270-505
LYCOMING
LW-15404
PRESTOLITE
ALY-8420
GILL
G-35
CUTLER-HAMMER 6041H105A
MOONEY
930021-001
1414-
PS102A
PS104A
1414-
RB102A
RB102B
SOLENOID, STARTER
STARTER
STARTER (ALT)
STARTER (AL-r)
BLOWER, RADIO
BLOWER, RADIO
CUTLER-HAMMER
PRESTOLITE
PRESTOLITE
PRESTOLITE
MOONEY
KING
6041H105A
MZ-4206
MZ-4218
MZ.-4222
810414-501
KA0033-00
14-
RC204B
RECEPTACLE
MOONEY
930021-002
14-
WE103A
1414-
WP103A
WP104A
MICRO
MICRO
MOONEY
14-
WPIO5A
14.-
WT102B
14-
WT103B
SWITCH, THROTTLE
ACTUATOR
ANNUNCIATOR
DIODE
(ALE)
(ALE)
DIODE
(ALE)
(ALE)
ANNUNCIATOR
BULB (8 EA)
.PLUG, 15 PIN
SOCKETS
V3-1
JV-5
800346-503
1N2483
1N5050
3720-GE
1N2483
1N5060
3720-GE
880025-511
CM7-7330
09-50-3151
06-50-0106
GE
GE
MOONEY
CHICAGO MINA
MOLEX
MOLEX
i
91-20-04
76
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE
14 VOLT ELECTRICAL EQUIPMENT CHART
MANUAL
RESERVED
12-98
91-20-04
79
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
RESERVED
91-20-04
80
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
J
91-20-05
- ELECTRICAL EQUIPMENT HARDWARE CHART
S/N 24-3201, 24-3218 THRU 24-3270 - SCHEMATIC NO. 800304-(J1) (REV. F)
S/N 24-3271 THRU 24-3350 - SCHEMATIC NO. 800304-(J2) (REV. S)
S/N 24-3251 THRU 24-3373 - SCHEMATIC NO. 800304 (J3) (REV. W)
S/N 24-3274 THRU 24-3377 - SCHEMATIC NO. 800304 (J4) (REV. W)
S/N 24-3278 THRU 24-3383 - SCHEMATIC NO. 800304 (,.15)(REV. Y)
S/N 24-3284 THRU 24-3392 - SCHEMATIC NO. 800304 (JS) (REV. Z)
S/N 24-3293 THRU 24-3404 - SCHEMATIC NO. 800304 (J7) (REV. Z)
S/N 24-3405 THRU 24-3410 - SCHEMATIC NO. 800304 (,.18)(RE-V.AA)
CODE
DESCRIPTION
VENDOR
PART NO.
ACT1
ACT2
ACT3
ACT4
ACT5
ACT6
ACTUATOR
ACTUATOR
ACTUATOR
ACTUATOR
ACTUATOR
ACTUATOR
MICRO SWITCH
MICRO SWITCH
MICRO SWITCH
MICRO SWITCH
MICRO SWITCH
MICRO SWITCH
JE-5
JV-5
JV-26
MCD-2711
JE-17
JV-82
AIR101A
AIR102A
AIR103A
AIR103B
AIR104A
AIR105A
SWITCH, A/C
COMPRESSOR, A/C
EVAP. BLWR (FRT)
EVAP. BLWR, (REAR)
CONDENSER BLWR
SWITCH, A/C PRESS.
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
880067-501
770028-1
770002-501
770002-503
770016-501
770029-501
BL1
BL6
BL7
BL8
BL9
BULB
HOLDER FOR BL1
BULB
HOLDER FOR BL.2
BULB (NAV-T/L)
BULB (NAV-T/L)
BULB (CONSOLE)
(ALl)
BULB (COMPASS)
BULB (POST LIGHT)
BULB (ANNUNCIATOR)
BULB (ANNUNCIATOR)
GE
HH SMITH
GE
HH SMITH
WHELEN
WHELEN
GE
GE
GE
GE
CHI, MIN.
CHI. MIN.
1818
1930
1816
1930
84-022-8030-85
34-021-2030-85
327
385
327(AV RED)
330
CM7-7730
CM7-7327
BR1
BR2
BR3
BR5
BR7.5
BR10
BR15
BR20
BR25
BR30
BR35
BR40
BR50
BR70
CIRCUIT BREAKER (1A)
CIRCUIT BREAKER (2A)
CIRCUIT BREAKER (3A)
CIRCUIT BREAKER (5A)
CIRCUIT BREAKER (7.5A)
CIRCUIT BREAKER (10A)
CIRCUIT BREAKER (15A)
CIRCUIT BREAKER (20A)
CIRCUIT BREAKER (25A)
CIRCUIT BREAKER (30)
CIRCUIT BREAKER (35A)
CIRCUIT BREAKER (40A)
CIRCUIT BREAKER (50A)
CIRCUIT BREAKER (70A)
KUXON
KLIXON
KLIXON
KUXON
KLIXON
KLIXON
KLIXON
MECH PROD
MECH PROD
MECH PROD
ETA
ETA
ETA
ETA
7277-2-1
7277-2-2
7277-2-3
7277-2-5
7277-2-7.5
7277-2-10
7277-2-15
4200-002-20
4200-002-25
700-001-30
41-2-S14-LN2-35A
41-3-S34-1_N2-40A
41-2-S34-LN2-50A
41-3-S14-LN2-70A
BRSW3
BRSW7.5
BRSW8
BRSW10
BRSW15
BRSW25
. C/B-SWITCH
C/B-SWITCH
C/B-SWITCH
C/B-SWITCH
C/B-SWITCH
C/B-SWITCH
KLIXON
KUXON
KLIXON
KLIXON
KLIXON
KLIXON
7270-5-3
7270-5-7.5
7270-5-8
7270-5-10
7270-5-15
7270-5-25
BI_2
BL3
BL4
BL5
12-98
NOTES
91-20-05
81
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
BS1
RELAY, BASE
MAGNACRAFT
70-803
BUS2A
BUS2B
BUS2C
BUS3A
BUS3B
BUS3C
BUS4A
BUS4B
BUS4C
BUS5A
BUS5B
BUS5C
BUS5D
BUS6A
BUS6B
BUS7A
BUSSA
BUS8B
BUSS BAR (2 PLC)
BUSS BAR (2 PLC)
BUSS BAR (
)
BUSS BAR (3 PLC)
BUSS BAR (3 PLC)
BUSS BAR (8 PLC)
BUSS BAR (4 PLC)
BUSS BAR (4 PLC)
BUSS BAR (4 PLC)
BUSS BAR (5 PLC)
BUSS BAR (5 PLC)
BUSS BAR (5 PLC)
BUSS BAR (5 PLC)
BUSS BAR (6 PLC)
BUSS BAR (6 PLC)
BUSS BAR (7 PLC)
BUSS BAR (8 PLC)
BUSS BAR (8 PLC)
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
913127-033
913127-097
913127-099
913127-087
913127-059
913127-073
913127-069
913127-089
913127-005
913127-093
913127-077
913127-085
913127-019
913127-035
913127-079
913127-081
913127-095
913127-083
C1
CAPACITOR
MALLORY
CGS302V-050R2C
CAP1
CAP2
CAP3
CAP, WHITE
CAP, BLACK
CAP, DUST
MICRO SW
ALCO SW
MATRIX SCIENCE,
15PA90-8W
C-22
M83723/60-122RC
CB101A
BLOWER, DEFROST
MOONEY
640317-503
CC101A
CCl02A
CC103A
CC103B
CC103C
MOTOR, COWL FLAP
INDICATOR, COWL FLAP
SWITCH, COWL FLAP
SWITCH, COWL FLAP (M20J)
SWITCH, COWL FLAP
MOONEY
MOONEY
MOONEY
MICRO-SWITCH
MOONEY
880050-505
880242-505
880052-517
12TW1-10
880052-117
CF101A
CF102A
OF103A
CF108A
ACTUATOR, FLAP
INDICATOR, TRIM/FLAP
INDICATOR, FLAP
SWITCH, FLAP
MOONEY
MOONEY
MOONEY
C-H
750105-501
800242-501
800242-505
8906K3149
CL03A
CL03B
CL03C
CLAMP 3/14/16128PIN
AMP
CLAMP 3 PIN
AMP
CLAMP 3 PIN
(ALl')
CLAMP 4/8 PIN
AMP
CLAMP 5 PIN
CLAMP 6 PIN
CLAMP 9 PIN, LT. CONTROL BOX AMP
CLAMF 9 PIN
AMP
CLAMF 9 PIN
/LOCK RETAINER
/LOCK RETAINER (ALE)
CLAMP, 9 PIN
./LOCK, RETAINER
CLAMP, 15 PIN
'/LOCK, RETAINER
CLAMP, 17 PIN
/LOCK, RETAINER
CL04A
CL05A
CL06A
CL09A
CL09B
CL09C
--CL09D
-CL15A
-CL17A
-91-20-05
82
12-98
206070-1
M85049-41-4A
MS3057-4A
MS3057-4B
206062-1
MS3057-6NB
MS3057-16A/B
206966-1
P/O 126-222
DE-24657
DE-51224-1
D110278
DE-19977-5
DE51224-1
DA51210-1
DA51220-1
DB51212
DB51221-1
NOTES
MOONEY AIRCRAFT CORPORATION
CODE
DESCRIPTION
CL25A
-C1..25B
-CL25C
-CL32A
CL32B
CL37A
CL37B
--
i'
M20J
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
VENDOR
CLAMP, 25 PIN
/LOCK, RETAINER
CLAMP, 25 PIN
/LOCK, RETAINER
CLAMP, 25 PIN
/LOCK, RETAINER
CLAMP, 32 PIN
CLAMP, BOOT
(ALl')
CLAMP, 37 PIN
CLAMP, 37 PIN
/LOCK, RETAINER
PART NO.
DB51212
DB51221-1
DB19977-2
DB51221-1
DB-24659
D-20418-2
M85049/52-1-22N
MS3420-14
MS3420-16
206138-1
DC19977-3
DC51222-1
CM1
CURRENT MONITOR
MOONEY
800221-505
CR101A
CR101B
CR102A
CR103A
SWITCH, RUDDER TRIM
SWITCH, RUDDER TRIM
MOTOR, RUDDER TRIM
INDICATOR, RUDDER TRIM
MOONEY
MOONEY
MOONEY
MOONEY
880052-519
880052-119
880050-503
800242-503
CT101A
CT102A
CT103A
CT104A
SWITCH, ELEV TRIM
INDICATOR, ELEV TRIM
MOTOR, ELEV TRIM
INTERFACE, TRIM
MOONEY
MOONEY
S-TEC
MOONEY
930023-233
800242-519
01165-0-T14
800313-501
CV101A
CV101B
CV102A
CV103A
CV104A
CV1O4B
CV105A
C/B-SW, STAND-BYVACUUM
MOONEY
C/B-SW, STAND-BY VAC
MOONEY
PUMP, STAND-BY VACUUM
AEROSAFE
PUMP, STAND-BY VACUUM
AEROSAFE
C/B-SW, STAND-BY VAC
MOONEY
C/B-SW, STAND-BY VAC
MOONEY
PUMP/CLUTCH, STAND-BY VAC AIRBORNE
930023-233
930023-343
820904-2
820904-1
930023-247
930023-344
28C214CW-2
DIODE
(AL'r)
(AL'r)
DIODE
(AL'r)
(ALT)
DIODE BRIDGE
DIODE BRIDGE
GE
SARKES-TARZIAN
ECG
NTE
FAGOR
FAGOR
1N2483
1N5O6O
3720GE
10H3P
5854
5854
FB50Ol
F85006
AMMETER SHUNT
(ALl')
AMMETER SHUNT
(ALT)
EMPRO
JANCO
EMPRO
JANCO
MLA-7OA-1OOMV
8406-70
MLA-150A-100MV
8406-150
----
TURN COORDINATOR
TURN COORDINATOR (ALT)
TURN COORDINATOR (ALT)
TURN COORDINATOR (ALT)
TURN COORDINATOR
UNITED INSTRUMENTS 9013 CODE N.5
ASTRONAUTICS
303990-028MSC
ELECTRO GYRO CORP 1394"['100-3Z
UNITED INST.
9114 CODE N.21
UNITED INST.
9112 CODE N.9
--
. PROBE, CYLINDER #1
(ALT)
* USE AN4076-1 ADAPTER.
MS24482-1
AN5546-1"
INDICATOR, O.A.T.
O.A.T. PROBE
880059-159
880004-501
D1
--D2
D4
D5
---
DA101A
DA101B
---
DB101A
DB102A
DC101A
DD101A
DD102A
NOTES
MOONEY
MOONEY
12-98
91-20-05
83
SERVICE'AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
DDIO3A
SOCKET, 4 PIN
CINCH-JONES
S-894-CCT
DF101A
DF102A
DF1O3A
DF104A
FUEL XMTR, LH/RH I/B
FUEL XMTR, LH O/13
FUEL XMTR, RH O/B
FUEL XMTR, LH/RH O/B
MOONEY
MOONEY
MOONEY
MOONEY"
610242-003
610243-003
610248-001
610242-005
DG101A
DG192A
DG103A
DG104A
DG105A
IND, INSTRUMENT MODULE
MOONEY
IND., INSTRUMENT, MODULE MOONEY
IND., INSTRUMENT MODULE #1 MOONEY
IND., INSTRUMENT MODULE #2 MOONEY
IND., INSTRUMENT MODULE
MOONEY
880059-507
880059-511
880059-513
880059-505
880059-517
DG106A
IND., INSTRUMENT MODULE
MOONEY
880059-519
DH101A
DH102A
PROBE, OIL TEMP
PROBE, OIL TEMP
MOONEY
880061-501
MS28034-1
DJ101A
NOTES
---
TRANSDUCER, OIL PRESSURE DRUCK
(ALT) (M20M)
KULITE
(ALT) (M2OJ)
KULITE
PDCR 821:0862-100
APT-291-1000-100G
APT-154-10O0-100PSIG
--
TRANSDUCER, FUEL PRESSURE DRUCK
(ALT)
KULITE
PDCR-821-0662-30
APT-158-1000-,30PSIG
TRANSDUCER, FUEL PRESSURE
DRUCK
(ALT)
KULITE
APT-155-1O00-50D
IND., TACH
(OPTIONAL)
SENSOR, TACH
IND., TACH
(OPTIONAL)
TACH SENSOR
TACH SENSOR
TACH SENSOR
TACH SENSOR
INDICATOR, TACHOMETER
INDICATOR, TACHOMETER
MOONEY
B&D
B&D
MOONEY
B&D
B&D
B&D
B&D
B& D
MOONEY
MOONEY
880039-515
0520-003
0400-004
880039-517
0520-006
(SLICK MAGS) 0402-102
0406-003 * (NOTE 3)
(BENDIX MAGS) 0402-104
0406-004 * (NOTE 3)
880039-519
880039-523
DK101A
DK102A
PSID
--
PDCR 920-U143 50
i
DL101A
-DL102A
DL103A
-DL104A
DL104B
DL105A
DL106A
• INSTALLED ON IO-550 ENGINE BY TELEDYNE CONTINENTAL MOTORS.
DM101A
DM102A
DM103A
DM104A
---
DP101A
DP101B
DP102A
-DP103A
-DP104A
DP105A
91-29-05
84
HOUR METER
HOUR METER
HOUR METER
(ALE)
HOUR METER
(ALT)
MOONEY
MOONEY
HOBBS
DATCON
HOBBS
HOBBS
880035-507
880035-505
15006
SG-70
85000
15000
C/B, PITOT HEAT
C./B,PITOT HEAT
HEATED PITOT
(ALT)
' PITOT, HEATED
.(ALl")
MOONEY
MOONEY
AERO INSTR
930023-205
930023-605
PH502-24
AN5812-1
PH502-12
AN5812
AERO INSTR
PLUG, 2 PIN
SOCKET
AN3115-1
AN3116-1
12-98
MOONEY AIRCRAFT CORPORATION
CODE
DESCRIPTION
VENDOR
PART NO.
DR101A "
PROBE, TIT
MOONEY
880055-503
DT101A
DT101B
DT102A
DT103A
IND., EGT
IND., EGT
SWITCH, EGT, 4 POSITION
PROBE, EGT
/ALTERNATE
TRAY, LIGHT (28VDC)
TRAY, LIGHT (14V)
ALCOR
ALCOR
ALCOR
MOONEY
ALCOR
ALCOR
ALCOR
46361
OEM-46161
OEM-80825
660110-000
86255
41338
41337
INDICATOR FUEL FLOW
MOONEY
INDICATOR FUEL FLOW (OPT) MOONEY
INDICATOR FUEL FLOW (OPT) MOONEY
INDICATOR F/F (GALS)
SHADIN
INDICATOR F/F (LBS) (OPT)
SHADIN
INDICATOR F/F (GALS)(OPT) SHADIN
INDICATOR F/F (LBS)(OPT)
SHADIN
INDICATOR F/F (LITERS)(OPT) SHADIN
INDICATOR F/F (GALS)(OPT) SHADIN
TRANSDUCER, FUEL FLOW
MOONEY
(OPTIONAL)
MOONEY
TRANSDUCER, F/F
SHADIN
880034-501
880034-503
880034-505
912021
912023
912041
912043
912047
912081
880030-501
880030-503
680501B
EG103A
EG104A
ACTUATOR, LDG GR
MOONEY
(ALT)
MOONEY
ACTUATOR, LDG GR
MOONEY
(ALT)
MOONEY
ACTUATOR, LDG GR
MOONEY
SWITCH, LDG GR. NS SAFETY MOONEY
880037-507
560254-503
880037-501
560254-501
560254-505
880013-507
ELT101A
ELT102A
SWITCH, ELT PANEL
TRANSMII-IER, ELT
ARTEX
ARTEX
110-416
453-0150
F1
F2
F3
F4
FUSE, 1 AMP
FUSE, 5 AMP-3AG-SLO-BLO
FUSE, 10 AMP SLO-BLO
FUSE, 5 AMP
LI3-FEL
U'REL
UI-IEL
McGRAW-EDISON
313001
313005
313010
FM01-5A
HOLDER, FUSE
(ALT)
HOLDER, FUSE
U'I-FEL
LI'FI'EL
McGRAW-EDISON
155020
155120
FHN42W
PHONE JACK
/WASHER
/WASHER
PHONE JACK
/WASHER
/WASHER
SWlTCHCRAFT
SWITCHCRAFT
SWlTCHCRAFT
SWITCHCRAFT
SWlTCHCRAFT
SWITCHCRAFT
C-11
S-1028
S-1029
C-112B
S-1028
S-1029
IGNITION CONTROL
CABLE
LASAR (SUCK)
LASAR
CD-1001-02
CH1001-XX
SWITCH, MAGNETO
./PLACARD
/TERMINAL LUG
SWITCH, MAC. (W/CONN.)
MAGNETO
(ALT)
(ALT)
BENDIX SCINTILLA
BENDIX SCINTILLA
BENDIX SCINTILLA
JANCO
BENDIX SCINTILLA
BENDIX SCINTILLA
LYCOMING
10-357210-9
10-187-468
10-126656
97-2273-1
D-4LN2021
D4LN-3000
LW-682555-11
-DT104A
DT105A
DV101A
--DV101B
-----DV102A
-DV102B
EG101A
-EG102A
-/
M20J
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
FH1
-FH2
FON1
--FON2
--JE101A
JM101A
--JM101B
JM102A
---
12-98
NOTES
1
1
1
2
91-20-05
85
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
JM103A
PLUG, MAGNETO
BENDIX SCINTILLA
10-382698
JM104A
JM105A
JM106A
JM107A
JM108A
JM109A
JM110A
JM111A
JM112A
JM112A
JM
JM
MAGNETO
MAGNETO, LEFT
MAGNETO, RIGHT
SWITCH, IGNITION
MAGNETO, LH
MAGNETO, RH
IGNITION, PULSAR
MAGNETO, [JR
MAGNETO, LH
MAGNETO, RH
MAGNETO, LH
MAGNETO, RH
SLICK
SLICK
SLICK
TCM
SUCK
SUCK
MOONEY
BENDIX
SLICK (LASAR)
SLICK (LASAR)
SLICK (W/O LASAR)
SLICK (W/O LASAR)
6244
6261
6260
10-357240-1
6393
6350
800315-501
$6RN-25-10
CD-4771
CD-4770
4372 (Rev.C)
4370 (Rev.C)
L1
1__2
1_3
L4
1_5
L6
L7
L8
L9
L10
Lll
L12
BULB, 28V
BULB, 14V
BULB
BULB, 14V
BULB
BULB
BULB
BULB
BULB
BULB (28V)
BULB
BULB
GE
GE
GE
GE
CHI. MINI.
CHI. MINI.
GE
GE
GE
GE
GE
GE
464-T-3 1/4
168-T-3 1/4
385
330
CM7-7330
CM7-7327
370
1816
327 (AV RED)
327
1818
1495
LB101A
LB101B
LB102A
LB102B
LB102C
C/B, BEACON, ROTATING
MOONEY
C/B, BEACON, ROTATING
MOONEY
UGHT, ROTATING BEACON
WHELEN
/ADAPTER
WHELEN
LIGHT, ANTI-COLLISION (RED) WHELEN
LIGHT, ANTI-COLUSION (WHITE) WHELEN
930023-243
930023-343
WRML-24
WRML-65
90033-19
90033-20
LENS1
LENS2
LENS3
ANNUNC. LENS (US)
ANNUNCIATOR LENS (FRAN)
ANNUNCIATOR LENS (US)
MOONEY
MOONEY
MOONEY
880048-613
880048-615
880048-617
LENS4
LENS5
LENS6
ANNUNCIATOR LENS (FRANCE) MOONEY
ANNUNCIATOR LENS
MOONEY
ANNUNCIATOR LENS
MOONEY
880048-619
880048-621
880048-623
LG101A
LG102A
C/B, LOGO LIGHT
LIGHT, LOGO
MOONEY
WHELEN
930023-357
A730-1-28
LH1
LH2
LH3
LH4
LAMP HOLDER
LAMP, HOLDER
LAMP HOLDER
LAMP HOLDER
/WASHER, LOCK, INT. TOOTH
/WASHER, LOCK, INT. TOOTH
LAMP HOLDER
LAMP HOLDER
' LAMP HOLDER
LAMP HOLDER
(ALT)
(ALT)
(ALT)
MOONEY
DIALIGHT
WHELEN
SLOAN
914083-1
270-1930-0171-702
A-350-CN-CL-BK-SH-28
855S-O-U
MS35334-21
M2898
0211-128
BA28-24-BW3
1V-192-971
1930
7-05
931-3103)
LSL-11-128U
--
LH5
LH6
LH7
LH8
---
---91-20-05
86
ALLEN BRADLEY
INSTRUMENTS
INSTRUMENTS
SIGMATEC
HH SMITH
LEECRAFT
ALLIED
SPC
12-98
NOTES
MOONEY AIRCRAFT CORPORATION
CODE
M20J
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
DESCRIPTION
VENDOR
PART NO.
(ALE)
NEWARK
81N2561
1-1-19
LAMP HOLDER
HH SMITH
1925
LH10
LH11
LH12
LAMP HOLDER
WHELEN
LAMP HOLDER, COCKPIT UTILITY) TEK-LITE
(ALT)
LAMP HOLDER, BAGGAGE LT WHELEN
01-0770437-00
LC-28-5
MS1745-51A
01-077-0142-04
LL101A
LL101B
LL102A
LL103A
SWITCH, LANDING LT
MOONEY
SWITCH, LANDING LT
MOONEY
UGHT, TAXI/LANDING, LH/RH (28V) GE
LIGHT, TAXI/LANDING, LH/RH (14V) GE
880052-521
880052-121
4596
4509
LN101A
LN101B
LN102A
C/B, NAV UGHTS
C/B,NAV UGHTS
UGHT ASSY, WING, NAV-TAIL
930023-251
930023-351
800051-501
LP101A
LP102A
LP103A
LP104A
LP105A
DIMMER CONTROL BOX (28V/14v) MOONEY (ELECT.) 800299-501
DIMMER CONTROL BOX (28V) MOONEY (RHEOSTAT) 800299-503
DIMMER CONTROL BOX (14V) MOONEY (RHEOSTAT) 800299-505
SWITCH, UGHT ASSY
MOONEY
150085-501
INVERTER, PLACARD (O/H)
ERG
LPS28-3-SP
LR101A
LR101B
LR102A
C/B, RECOGNITION LIGHT
C/B, RECOGNITION LIGHT
RECOGNITION LIGHT
LS101A
LS101B
LS102A
LS102B
LS103A
LS104A
LS105A
LS106A
C/B, STROBE LIGHT
MOONEY
C/B, LIGHTS, STROBE
MOONEY
POWER SUPPLY, STROBE
WHELEN
POWER SUPPLY, STROBE
WHELEN
STROBF_JNAVLIGHTASSY (LH/WG) WHELEN
STROBE/NAV LIGHTASSY (RH/WG) WHELEN
STROBE/TAIL LIGHT ASSY
MOONEY
POWER SUPPLY (TAIL)
WHELEN
930023-237
930023-337
01-0770329-00
01-0770329-01
01-0770054-12
01-0770054-13
470013-501
A413A,HDA,DF-28
LT101A
LT101B
LT102A
SWITCH, TAXI LIGHT
SWITCH, TAXI LIGHT
TAXI LIGHT LT/RT
880052-523
880052-128
4596
MA101A
RECEPTACLE, AUX POWER
AN2552-3A
MB101A
MB101B
C/B-SWITCH, AVIONICS MASTER MOONEY
C/B-SWITCH, RADIO MASTER MOONEY
930023-213
930023-313
MC101A
CIGAR LIGHTER
MOONEY
800336-503
----
CLOCK
(ALT)
CONN, 4 PIN (ALT)
PIN
CONN, 4 PIN
PIN
MID-CONT
PORSCHE
MID-CONT
MID-CONT
PORSCHE
PORSCHE
MD-89
944.541.213.00
6015177
5016125
944.512.217.00
999.652.351.12
---
MICROPHONE JACK
/WASHER
/WASHER
SWITCHCRAFT
SWITCHCRAFT
SWlTCHCRAFT
C-12B
S-1028
S-1029
LH8
--
--
ME101A
-ME102A
MIC1
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
G.E.
12-98
NOTES
930023-231
930023-331
880049-501
91-20-05
87
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
MP101A
MP101B
MP102A
MP102B
MP103A
C/B-SW, PROP DE-ICE
C/B-SW., PROP. DE-ICE
TIMER, PROP DE-ICE
TIMER, PROP DE-ICE
TERMINAL BLOCK
MOONEY
MOONEY
B.F. GOODRICH
McCAULEY
McCAULEY
930023-245
930023-345
3E1899-1
B-45018
C-40521
NF101A
NF101B
NF102A
C/B-SW, LOW-BOOST PUMP
MOONEY
C/B-SW., BOOST PUMP
MOONEY
PUMP, BOOST
WELDON
(ALE)
WELDON
PUMP, BOOST
WELDON
(ALE)
WELDON
PUMP, BOOST
WELDON
PUMP, BOOST
WELDON
PUMP, BOOST
WELDON
REGULATOR, FUEL BOOST PUMP MASSEY
C/B-SW, HI-BOOST PUMP
MOONEY
930023-211
930023-311
A8163B
8163B
8163A
A8163A
10054B
A10051D
A8152-B
VR536
930023-219
REGULATOR, VOLTAGE
(ALE)
(ALE)
SWITCH, ALT FLD (DUAL)
SWITCH, ALT FLD (SINGLE)
ALTERNATOR
(ALl')
ALTERNATOR
(ALE)
ALTERNATOR
(ALE)
\GEAR ASSEMBLY
ALTERNATOR
/INSTALL KIT (REF 600180)
MOONEY
AMERICAN PROD
ELECTRODELTA
MOONEY
MOONEY
LYCOMING
PRESTOLITE
LYCOMING
PRESTOUTE
TCM
TCM
TCM
ELECTRO SYSTEMS
LYCOMING
800270-501
DGR-2
VR-802
880052-525
880052-503
LW-14367
ALU-6421-LS
LW15404
ALY-8420
649280
649172
649123
ES 4009-LS
05K-21065
PA109A
PAl 10A
PAl 11A
PAl 11B
PAl 12A
FILTER
(ALE)
SENSOR, CURRENT
REGULATOR, VOLTAGE
SENSOR, CURRENT (110 A)
SENSOR, CURRENT (175 A)
ALTERNATOR (100A)
MOONEY
MOONEY
MICRO SW
MOONEY
KLIXON
KLIXON
TCM
880014-501
800307-501
CSLAIGE
800270-503
7235-1-110
7236-1-175
649304
PB101A
PB102A
PB102B
PB103A
PB103B
PB105A
BATi-ERY
SWITCH, MASTER
SWITCH, MASTER
SWITCH, BATTERY SELECT
SWITCH, BATTERY SELECT
BATrERY
GILL
MOONEY
MOONEY
MOONEY
MOONEY
CONCORDE
G-243
880052-501
880052-101
880052-527
880052-127
RG24-11M
PL02A
PL02B
PL02C
PL02D
PL03A
PLUG, 2 PIN
PLUG, 2 PIN
PLUG, 2 PIN(FEMALE)
PLUG, 2 PIN
PLUG, 3 PIN
AMP
MOLEX
DEAN
1-480318-0
03-06-1023
DEA900020
MS3106A-24-9S
1-380303-0
PL03B
PL03C
PLUG, 3 PIN
' PLUG, 3 PIN
AMP
PL03D
PL04A
PLUG, 3 PIN
PLUG, 4 PIN
-NF103A
-NF104A
NF105A
NF106A
NF108A
NF109A
PA101A
--PA102A
PA103A
PA104A
-PAl 05A
-PA106A
--PA107A
-PAl 08A
--
91-20-05
88
AMP
AMP
12-98
206037-2
MS3106A-10SL-3S
MS3106A-28-6P
206060-1
NOTES
MOONEY AIRCRAFT CORPORATION
CODE
M20J
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
DESCRIPTION
VENDOR
PL04B
PL05A
PLO6A
PLOBA
PL09A
PL09S
PL09C
PLQ9D
PL09E
PL14A
PL14B
PL140
PL15A
PL16A
PL17A
PL20A
PL25A
PL25B
PI_26A
PL28A
PL32A
PART NO.
PLUG, 4 PIN
PLUG, 5 PIN
PLUG, 6 PIN
MATRIX SCIENCE
PLUG, 8 PIN
AMP
PLUG, 9 PIN
AMP
PLUG, 9 PIN
AMPRENOL
PLUG, 9 PIN
PLUG, 9 PIN
MOLEX
PLUG, 9 PIN
AMP
PLUG, 14 PIN
MOONEY
PLUG, 14 PIN
MOONEY
PLUG, 14 PIN
AMP
PLUG, 15 PIN
PLUG, 16 PIN
AMP
PLUG, 17 PIN
PLUG, 20 PIN
MOONEY
PLUG, 25 PIN
=
PLUT, 15 PIN
AMP
PLUG, 26 PIN
MOONEY
PLUG, 28 PIN
AMP
PLUG, 32 PIN****
MATRIX SCIENCE
****USE MS3420-14 OR-16 BOOTWITH CONNECTOR.
PL,34A
PLUG, 34 PIN
MOONEY
PL.34B
PLUG, 84 PIN
MOONEY
PL37A
PLUG, 37 PIN
AMP
PI_37B
PLUG, 37 PIN
MS3106A-32-17S
MS3106A-14S-5S
MS3106A-28-22S
2058,38-1
206708-1
126-222
DE-gS
03-06-2092
206485-1
930021-1
930021-513
206043-3
DA15S
206037-1
DBM17W2S
930021-501
DB25S
205208-1
930021-505
205839-3
M83723/86R2232N
PS101A
PS102A
PS103A
7277-2-10
7277-2-5
MHJ-4016
LW-15572
646275
537647
BSO206-149
-PS104A
-PS105A
R1
R2
R3
R4
R5
R6
R7
C/B, STARTER SOLENOID
C/B, STARTER SOLENOID
• STARTER
(ALl)
STARTER
(ALT)
STARTER
KLIXON
KLIXON
PRESTOL[TE
LYCOMING
TOM
TCM
B & C SPECIALITY
930021-507
930021-515
206150-1
DC37S
R9
R10
Rll
R12
R13
RESISTOR (20 OHM/10W)
DALE
RESISTOR (50HM/10W)
DALE
RESISTOR,MAPLIGHT (500 OHM) NEWARK
RESISTOR (100 OHM)
NEWARK
RESISTOR (7.5 OHM)
DALE
RESISTOR (1K OHM/2VV)
ALLEN-BRADLEY
RESISTOR (5K OHM)
ALLEN BRADLEY
(ALl)
SELECTROL
(ALT)
BOURNS
(ALl')
NEWARK
RESISTOR (150 OHM/3W)
CLAROSTAT
(ALT)
OHMITE
RESISTOR (3.9K OHM/1/2W)
OHMITE
RESISTOR (3.0K OHM/1/2W)
OHMITE
RESISTOR (10HM/25W)
DALE
RESISTOR (70 OHM/10W)
DALE
REStSTOR (10.0K OHM/lW)
OHMITE
RH-10-20 OHM
RH-10-5 OHM
919029-501
09F976
RH-50-7.5 OHM
RC42-GF102J
WA2-G056S502UA
149-11-502
8862C-282-502A
12F9905R 5.0K
VC3D
23J
N/A
N/A
RH-25-1 OHM
RH-10-70 OHM
N/A
RB101A
. SLOWER, RADIO
KING
071-4037-01
RC02A
RCO2C
RC02D
RECEPTACLE, 2 PIN
RECEPTACLE, 2 PIN (MALE-)
RECEPTACLE, 2 PIN
AMP
DEAN
1-480319-0
DEAg00020
MS3100-24-9P
R8
--
.....
12-98
..........
NOTES
91-20-05
89
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
RC03A
RC03B
RC03C
RC03D
RC04A
RC04B
RC08A
RC08A
RC09A
RC09B
RC09C
RC09E
RC12A
RC14A
RC14B
RC14C
RC16A
RC16B
RC20A
RC26B
RC28A
RC32A
RC34A
RC34B
RC37A
RECEPTACLE, 3 PIN
RECEPTACLE, 3 PIN
RECEPTACLE, 3 PIN
RECEPTACLE, 3 PIN
RECEPTACLE, 4 PIN
RECEPTACLE, 4 PIN
RECEPTACLE, 6 PIN
RECEPTACLE, 8 PIN
RECEPTACLE, 9 PIN
RECEPTACLE, 9 PIN
RECEPTACLE, 9 PIN
RECEPTACLE, 9 PIN
RECEPTACLE, 12 PIN
RECEPTACLE, 14 PIN
RECEPTACLE, 14 PIN
RECEPTACLE, 14 PIN
RECEPTACLE, 16 PIN
RECEPTACLE, 16 PIN
RECEPTACLE, 20 PIN
RECEPTACLE, 26 PIN
RECEPTACLE, 26 PIN
RECEPTACLE, 32 PIN
RECEPTACLE, 34 PIN
RECEPTACLE, 34 PIN
RECEPTACLE, 37 PIN
AMP
AMP
AMP
1.-480305-0
206036-2
206207-1
MS8100-28-6S
206153-1
MS3100-32-17P
MS3100C-28-22P
205841-2
206705-2
208705-1
DEgP
205486-1
03-06-2122
930021-2
203540-1
206044-1
206037-1
206036-1
930021-502
930021-506
206152-1
M83723/83K2232N
930021-508
204814-1
206151-1
RL1
---RL2
RL3
RL4
RL5
--RL6
RL7
RL8
RL9
R10
--SA101A
RELAY, BATT. (28V/200A)
(ALE)
(ALE)
(ALE)
RELAY, BAN'. (14V/200A)
RELAY
RELAY
RELAY, LDG. (28V/50A)
(ALT)
/BRACKET (2 E.A)
RELAY (28V/100A)
RELAY, (14V/200A)
RELAY
RELAY
RELAY
SOCKET
TERMINAL
AMP
MATRIX SCIENCE
AMP
AMP
AMP
AMP
MOLE)(
MOONEY
AMP
AMP
AMP
AMP
MOONEY
MOONEY
AMP
MATRIX SCIENCE
MOONEY
AMP
AMP
C-H
C-H
KISSLING
KISSLING
C-H
KISSLING
KISSUNG
C-H
KISSLING
MOONEY
C-H
C-H
MAGNACRAFT
. KISSLING
P&B
P& B
P& B
6041H-202
6041H-202A
26.57.01
26.57.02
6041H-105A
26.64.01
26.64.21
6041H-220
26.72.03
800375-001
6041H-53
6041H-105R
W67RCSX-3
28.08.01
VF4-15-H11
VCF4-1002
26A1348C
SA102A
ALTERNATOR, STAND-BY
HOUSING, CONNECTOR
TERMINAL (1/4")
CONTROLLER, STBY. ALT.
B& C
B& C
B& C
B& C
BC410-1
12-003
14-026
BC203-2
SB101A
SB102A
SS103A
C/B, SPEEDBRAKE
SWITCH, CONTROLWHL
RELAY, SPEEDBRAKE
KLIXON
PRECISE FLT
PRECISE FLT
72T'/-2-3
01265
01384
GE
PRECISE FLT
PRECISE FLT
1N2483
1N5060
3720-GE
01532
01505
SB104A
--SB105A
SB106A
91-20-05
9O
. DIODE
(ALE)
(ALT)
MOTOR, SPEEDBRAKE
SWITCH, SPEEDBRAKE
12-98
NOTES
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
SB107A
SB108A
SOLENOID, CLUTCH
INTERFACE, SPEEDBRAKE
PRECISE FLT
MOONEY
01678
800314-501
SPK1
SPK2
SPK3
SPEAKER, ALERT
SPEAKER, CABIN
SONALERT
ARCHER
ARCHER
MALLORY
40-1338C
40-1325
SC628
SWl
SW2
SW3
SW4
SW5
SWITCH
SWITCH, DEF. BLWR.
SWITCH, LIMIT, RUD.TRIM
SWITCH,UP LIMIT, LDG
SWITCH, DN UMIT, LDG
(ALT)
SWITCH, CABIN LTS
SWITCH
SWITCH, LOG
SWITCH, MIC-KEY
(ALT)
SWITCH, CHT
SWITCH, FLAP
SWITCH, CABIN LTS(MASTER
MICRO
CHERRY
MICRO
MICRO
OTFO
MICRO
CARLING
MOONEY
C-H
ALCO
C-H
GRAYHILL
C-H
CARLING
1SE1-T
E51-50B
V3-1
DT-2R-47
P6-24014
1CH116-6
RC911-VBBOW
580013-507
8906K2875
MPE-106F-C-22-9
SA1RV20
71AD30-02-2-AJN
8908K4731
RA911-VBBOW
MICRO
MICRO
SW14
SWITCH (ALT)
/CAP, WHITE
(AL'r)
SWITCH, F/F MEM.
12TW1-10
15PAg0-sw
MS27753-38
7101K
SW15
SWITCH, LDG, OVERRIDE
NKK
SW18
SW19
SW20
SW21
SW22
SW23
SW25
SW35
SWl01A
DLB241-W01-L3C/
ATS06M/AT503MB
/BUTFON/LOCK RING/LOCK WASHER/HEX NUT (2 EA) (NKK)
/SWITCH (ALT)
C-H
SB1DDX492-2
/LOCK RING
C-H
29-761
/LOCK WASHER
C-H
16-885
/HEX NUT (2 EA)
C-H
15-966-6
SWITCH, VAC. HI/LO
MOONEY
880012-501
SWITCH
CARLING
TILC64-1S-WHFN
SW (ALT)
TSCHUDIN
504202
LENS
TSCHUOIN
464415
BUlB
TSCHUDIN
590002
SWITCH
MOONEY
880062-501
SWITCH
CARLING
TIGM64-1S-WHFN
SWITCH
MS35058-22
SWITCH, MIKE KEY
CROUZET
83-450-001
SWITCH, SPDBRK
CROUZET
83-452-504
SWITCH
ALCO
MPE106F
SWITCH
NKK
MB2085SB1W01-EA
SWITCH
NKK
MB2085SB1W01-EA
SWITCH, ALT. AIR DOOR (M20J) SAINT
ZS-10O9
VR1
VARISTOR
GE
V47ZAO5
WM101A
WM102A
MASTER WARNING
MASTER WARNING
MICRO SWITCH
MICRO SWITCH
DSK-104-GYR
DSB-11-RRRR-LR2
WS101A
WS103A
ALERT, STALLWARN/GEAR WARN IAI
SWITCH, STALL WARNING
MOONEY
-SW6
SW7
SW8
SW9
-SWl 0
SWl 1
SW12
SWl 3
---
-----SW16
SW17
C&K
NOTES
950D0309-000
800364-507
12-98
;
91-20-05
91
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
WT101A
WTIO2A
WT103A
WTIO4A
ANNUNCIATOR
ANNUNCIATOR
ANNUNCIATOR
ANNUNCIATOR
MOONEY
MOONEY
MOONEY
MOONEY
880048-501
880048-506
880048-507
880048-509
NOTES
NOTES:
1. SHADIN MODEL NO. INTERFACE WITH II MORROW APOLLO, ARNAV AND NORTHSTAR LORAN
SYSTEMS.
2.
3.
SHADIN MODEL NO. INTERFACE WITH BENDIX/KING KLN-88OR KLN90 SERIES.
B & D TACH SENSOR'S P/N 0406-004 IS 9/16" DIAMETER FOR BENDIX MAGNETOS. 0406-003 IS 11/16"
DIAMETER FOR SLICK MAGNETOS
91-20-05
92
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
RESERVED FOR FUTURE ENTRIES
12-98
91-20-05
93
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
i,
RESERVED FOR FUTURE ENTRIES
91-20-05
94
12-98
MOONEY AIRCRAFT CORPORATION
91-20-06
M20J
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
- ELECTRICAL SYSTEM HARDWARE CHART - 28 VOLT
S/N 24-3411 THRU 24-3420, SCHEMATIC NO. 800383 (J1) (REV. G)
S/N 24-3421 THRU 24-3431, SCHEMATIC NO. 800383 (J2) (REV. H)
DESCRIPTION
VENDOR
PART NO.
CODE
AC101A
AC102A
AC103A
AC103B
AC104A
AC105A
AC106A
SWITCH, AIR COND.
COMPRESSOR, AIR COND.
BLOWER, EVAP. (FRON_
BLOWER, EVAP. (REAR)
BLOWER, CONDENSOR
SWITCH, AIR COND. PRESS
CONNECTOR, AIR COND
CONTACTS
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
CORY COMP.
CORY COMP.
880067-501
770028-1
770002-501
770002-503
770016-501
770029-501
CSLT-21PA
CB017-5S
ACTUATOR, SWITCH
ACTUATOR, SWITCH
ACTUATOR, SWITCH
ACTUATOR, SWITCH
ACTUATOR, SWITCH
ACTUATOR, SWITCH
MICRO SWITCH
MICRO SWITCH
MICRO SWITCH
MICRO SWITCH
MICRO SWITCH
MICRO SWITCH
JE-5
JV-5
JV-26
MCD-2711
JE-17
JV-82
BR50
B270
CIRCUIT BREAKER (1A)
(ALE)
CIRCUIT BREAKER (2A)
(ALT)
CIRCUIT BREAKER (3A)
(ALT)
CIRCUIT BREAKER (SA)
(ALT)
CIRCUIT BREAKER (7.5A)
(ALT)
CIRCUIT BREAKER (10A)
(ALT)
CIRCUIT BREAKER (15A)
(ALT)
CIRCUIT BREAKER (20A)
CIRCUIT BREAKER (25A)
CIRCUIT BREAKER (30A)
CIRCUIT BREAKER (35A)
CIRCUIT BREAKER (40A)
(ALT)
CIRCUIT BREAKER (50A)
CIRCUIT BREAKER (70A)
MECH PROD.
KLIXON
MECH PROD.
KLIXON
MECH PROD.
KLIXON
MECH PROD.
KLIXON
MECH PROD.
KUXON
MECH PROD.
KUXON
MECH PROD.
KLIXON
MECH PROD.
MECH PROD.
MECH PROD.
ETA
ETA
MECH. PROD.
ETA
ETA
4200-002-1
7277-2-1
4200-002-2
7277-2-2
4200-002-3
7277-2-3
4200-002-5
7277-2-5
4200-002-7.5
7277-2-7.5
4200-002-10
7277-2-10
4200-002-15
7277-2-15
4200-002-20
4200-002-25
4200-002-30
41-2-S34-LN2-35A
41-3-S34-LN2-40A
700-001-40
41-2-S34-LN2-50A
41-3-S34-LN2-70A
BS101A
BASE, RELAY
MAGNACRAFT
70-303
BU2A
BU2B
BU2C
BU2D
BU2E
BU3A
BU3B
BU3C
BU4A
SU4B
BU4C
BU4D
BU5A
BU5B
BU5C
BUS BAR (2 PLC)
BUS BAR (2 PLC)
BUS BAR (2 PLC)
BUS BAR (2 PLC)
BUS BAR (2 PLC)
BUS BAR (3 PLC)
BUS BAR (3 PLC)
BUS BAR (3 PLC)
BUS BAR (4 PLC)
' BUS BAR (4 PLC)
BUS BAR (4 PLC)
BUS BAR (4 PLC)
BUS BAR (5 PLC)
BUS BAR (5 PLC)
BUS BAR (5 PLC)
-AT101A
AT102A
AT103A
AT104.4,
AT105A
AT106A
BR1
-BR2
-BR3
-BR5
-BR7.5
-BR10
-BR15
-BR20
BR25
BR30
BR35
BR40
--
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
12-98
NOTES
913127-33
913127-97
913127-99
913127-75
913127-65
913127-87
913127-59
913127-73
913127-69
913127-89
913127-5
913127-53
913127-93
913127-77
913127-85
91-20-06
95
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
BU5D
BU6A
BU6B
BUTA
BUSA
BUS BAR (5 PLC)
BUS BAR (6 PLC)
BUS BAR (6 PLC)
BUS BAR (7 PLC)
BUS BAR (8 PLC)
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
913127-19
913127-35
913127-79
913127-81
913127-95
BW3
BW7.5
BW10
BW15
SW25
SWITCH, C/B (3A)
SWITCH, C/B (7.5A)
SWITCH, C/B (10A)
SWITCH, C/B (15A)
SWITCH, C/B (25A)
KUXON
KLIXON
KUXON
KLIXON
KLIXON
7270-5-3
7270-5-7.5
7270-5-10
7270-5-15
7270-5-25
CA101A
CA102A
CAPACITOR
CAPACITOR (1000 PF')
MALLORY
NEWARK
CGS302V050R2C
18F2711 TYPE 5GAD10
CB101A
BLOWER, DEFROSTER
MOONEY
640317-503
CC101A
CC102A
CC103A
CC103B
CC103C
MOTOR, COWL FLAP
INDICATOR, COWL FLAP
SWITCH, COWL FLAP
SWITCH, COWL FLAP (J)
SWITCH, COWL FLAP
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
880050-505
800242-505
880052-517
12TW1-10
880052-117
CF101A
CF102A
CF103A
CF104A
ACTUATOR, FLAP
INDICATOR, TRIM/FLAP
INDICATOR, TRIM/FLAP
INDICATOR, TRIM/FLAP
MOONEY
MOONEY
MOONEY
MOONEY
750105-501
800242-501
800376-501
800391-502
CL03A
CL03B
CL03C
CLAMP, 3,14,16,28 PIN
CLAMP, 3 PIN
CLAMP, 3 PIN
(ALT)
CLAMP, 4, 8 PIN
CLAMP, 4 PIN
CLAMP, 5 PIN
(ALT)
CLAMP, 5 PIN
(ALT)
CLAMP, 7 PIN
CLAMP, 9 PIN
CLAMP, 9 PIN
CLAMP, 9 PIN
RETAINER, LOCK
(ALE) RET. LOCK
(ALT) RET. LOCK
CLAMP, 9 PIN
RETAINER, LOCK
CLAMP, 15 PIN
LOCK RETAINER
CLAMP, 15 PIN (ALT)
CLAMP, 17 PIN
LOCK RETAINER
CLAMP, 25 PiN
• LOCK RETAINER
CLAMP, 25 PIN
LOCK RETAINER
CLAMP, 25 PIN
LOCK RETAINER
CLAMP, 32 PiN
AMP
206070-1
M8049-41-4A
MS3057-4A
MS3057-4B
206052-1
10-101971-8-3
MS3057-TA
MS3057-6B
MS3057-16A
MS3057-16B
MS3057-12B
206966-1
P/O 126-222
DE-24657
DE 51224-1
Dl10278
D-20419-16
DE-19977-5
DE-51224-1
DA51210-1
DA51220-1
DA19977-1
DB51212
DB51221-1
DB51212
DB51221-1
DB19977-2
DB51221-1
DB24659
D-20418-2
M85049/52-1-22N
CL04A
CL04D
CL05A
CL06A
CL07A
CL09A
CL09B
CL09C
---CL09D
CL15A
-CL17A
CL25A
CL25B
CL25C
CL32A
91-20-06
96
AMP
BENDIX
AMP
AMP
12-98
NOTES
MOONEY AIRCRAFT CORPORATION
CODE
DESCRIPTION
CL32B
-CL37A
CL37B
M20J
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
--
VENDOR
CLAMP/BOOT
(ALT)
CLAMP, 37 PIN
CLAMP, 37 PIN
LOCK RETAINER
PART NO.
MS3420-14
MS3420-16
206138-1
DC19977-3
DC51222-1
CM 101A
CURRENT MONITOR
CR101A
CR101B
CR102A
CR103A
SWITCH, RUDDER TRIM (WHITE) MOONEY
SWITCH, RUDDER TRIM (BLACK) MOONEY
MOTOR, RUDDER TRIM
MOONEY
INDICATOR, RUDDER
MOONEY
880052-519
880052-119
880050-503
800242-503
CT101A
CT102A
CT103A
CT104A
CT105A
SWITCH, TRIM
INDICATOR, ELEV. TRIM
MOTOR, ELEV. TRIM
TRIM INTERFACE
INDICATOR, ELEV. TRIM
930023-233
800242-519
01165-0-T14
800313-501
800391-501
CV101A
CV101B
CV102A
CV103A
CV104A
CV104B
CV105A
CIRCUIT BREAKER/SWITCH
MOONEY
CIRCUIT BREAKER/SWITCH
MOONEY
PUMP, STAND-BY VACUUM
AEROSAFE
PUMP, STAND-BY VACUUM
AEROSAFE
SWITCH/O-B, STAND-BY VACUUM MOONEY
SWITCH/C-B, STAND-BY VACUUM MOONEY
PUMP/CLUTCH ASSY, STDBY VAC. AIRBORNE
930023-233
930023-333
820904-2
820904-1
930023-247
930023-347
28C214-CW-2
SHUNT, AMMETER
(ALT)
SHUNT, AMMETER
(ALr)
EMPRO
JANCO
EMPRO
JANCO
MLA-7OA-10OMV
8406-70
MLA-150A-100MV
8406-150
TURN COORDINATOR
(ALT)
(ALl)
(ALT)
TURN COORDINATOR
UI
ASTRONAUTICS
ELEC. GYRO CORP.
UI
UI
9013 CODE N.5
303990-028MSC
1394T100-3Z
9114 CODE N.21
9112 CODE N.9
PROBE, CHT
(ALl)
(ALl)
NORWICH
MS24482-1
AN5546-1
102-00007
DD101A
DD102A
DD103A
INDICATOR, OAT
PROBE, OAT
SOCKET, 4 PIN
MOONEY
MOONEY
CINCH-JONES
880059-159
860004-501
S-304-CCT
DF101A
DF102A
DF103A
DF104A
DF105A
DF106A
DF107A
DF108A
DF109A
DF110A
DF111A
XMTR, FUEL, INBD, LH/RH
XMTR, FUEL, OUTBD, LH
XMTR, FUEL, OUTBD, RH
XMTR, FUEL, OUTBD, LH/RH
XMTR, FUEL
FLOAT/ARM, RH I/B
FLOAT/ARM, RH O/B
FLOAT/ARM, LH I/B
FLOAT/ARM, LH O/B
TRANSDUCER
PROCESSOR
MOONEY
MOONEY
MOONEY
MOONEY
AVAQ
AVAQ
AVAQ
AVAQ
AVAQ
AVAQ
AVAQ
610242-3
610243-3
61024.3-1
610242-5
9450563001
9400563102
9400563104
9400563101
9400563103
9450563002
9450563303
DA101A
-DA101B
-DB101A
DB102A
----
DC101A
---
NOTES
MOONEY
MIL-S-9419
MOONEY
S-TEC
MOONEY
MOONEY
12-98
800221-505
91-20-06
97
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
DG101A
DG102A
DG103A
DG104A
DG105A
DG106A
DG107A
DG108A
DG109A
DG110A
DG111A
DG112A
DG113A
DG114A
DGl15A
MODULE INSTRUMENT
MODULE INSTRUMENT
MODULE INSTRUMENT, #1
MODULE INSTRUMENT, #2
MODULE INSTRUMENT
MODULE INSTRUMENT
MODULE INSTRUMENT, #1
MODULE INSTRUMENT, #2
MODULE INSTRUMENT
CLUSTEF_,-D/A
CLUSTEI_, D/A
CLUSTEF_ DIGITAL
CLUSTEF DIGITAL
CLUSTEF , D/A
CLUSTEI_ DIGITAL
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
880059-507
880059-511
880059-513
880059-515
880059-517
880059-519
880059-523
880059-525
880059-521
880093-501
•880093-503
880093-505
880093-507
880093-509
880093-511
DH101A
DHIO2A
PROBE, OILTEMP
PROBE, OIL TEMP
MOONEY
880061-501
MS28034-1
DIIOIA
DIODE
(ALT)
DIODE
(ALT)
(ALT)
BRIDGE, DIODE
BRIDGE, DIODE
DI102A
--DI104A
DI105A
DJIO1A
DJIO1B
DKIOIA
-DK102A
-DL101A
DL102A
DLIO3A
DL104A
DL104B
DLI04C
DL104D
DL105A
DL106A
DL107A
DL108A
DM101A
DM102A
DM103A
DM104A
91-20-06
98
NOTES
EGG
NTE
FAGOR
FAGOR
1N2483/1N5060
3720-GE
10H3P
5854
5854
FB5001
FB5006
XDCR, OIL PRESS
(ALT) (M2OJ)
(ALT)
XDCR, OIL PRESS (M2OM)
DRUCK
KUUTE
PATRIOT
KULITE
PDCR 821-0662-100
APT-154-1000-100PSlG
KA21-014-100G
APT-201-1000-100G
XDCR, FUEL PRESS
(ALE)
XDCR, FUEL PRESS
(ALT)
(ALT)
DRUCK
KULITE
DRUCK
KULITE
PATRIOT
PDCR-821-0662-30
APT-153-1000-30 PSIG
PDCR-920-U143-50 PSID
APT-155-1000-50D
KA21-016-50D
TACHOMETER
(OPTIONAL)
SENSOR, TACH
TACHOMETER
(OPTIONAL)
SENSOR, TACH (SLICK)
SENSOR, TACH (BENDIX)
SENSOR, TACH (BENDIX)
SENSOR, TACH (SLICK)
TACHOMETER
TACHOMETER
SENSOR, TACH (SLICK)
SENSOR, TACH (BENDIX)
MOONEY
B&D
B&D
MOONEY
B&D
B&D
B&D
B&D
B&D
MOONEY
MOONEY
J-P INSTR.
J-P INSTR.
880039-515
0520-003
0400-004
880039-517
0520-006
0402-102
0402-104
0406-004
0406-003
880039-519
880039-523
420809
420807
HOUR METER
. HOUR METER
HOUR METER
(ALT)
HOUR METER
(AI_T)
MOONEY
MOONEY
HOBBS
DATCON
HOBBS
HOBBS
880035-507
880035-505
15006
SG-70
85000
15000
GE
12-98
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
DP101A
DP101B
DP101C
DP102A
C/B
C/B
C/B
P]TOT, HEATED
(ALT)
PITOT, HEATED
(ALT)
PLUG
SOCKET
MOONIEY
MOONEY
MOONEY
AERO INSTR
930023-205
930023-305
930023-353
PH502-12
AN5812
PH502-12
AN5812
AN3115-1
AN3116-1
DR101A
DR101B
PROBE, TIT
PROBE, TIT
MOONEY
MOONEY
880055-503
880055-505
DT101A
DT101B
DT102A
DT103A
INDICATOR, EGT
INDICATOR, EGT
SWITCH, EGT (4 POSITION)
PROBE, EGT
(AL'F)
LIGHT TRAY (28V)
UGHT TRAY (14V)
ALCOR
ALCOR
ALCOR
MOONEY
ALCOR
ALCOR
ALCOR
46361
OEM-46161
OEM-80825
660110-000
86225
41338
41337
TRANSDUCER, MAP
(ALT)
(ALE)
KULITE
PATRIOT
PATRIOT
APT-231-100O-25A
KA21-015-25A
SP100-110-25A
INDICATOR, FUEL FLOW
(OPTIONAL)
(OPTIONAL)
INDICATOR, FUEL FLOW
TRANSDUCER, FUEL FLOW
(OPTIONAL)
TRANSDUCER, FUEL FLOW
MOONEY
MOONEY
MOONEY
SHADIN
MOONEY
MOONEY
SHADIN
880034-501
880034-503
880034-505
912041TD
880030-501
880030-503
680591B
ACTUATOR, LDG
(ALl')
(ALl-)
ACTUATOR, LDG
(ALl')
ACTUATOR, LDG
SWITCH, AIRSPEED
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
880037-507
560254-503
560254-507
880037-501
560254-501
560254-505
880013-507
SWITCH, ELT PANEL
TRANSMITTER, ELT
CABLE ASSY, REMOTE
REMOTE UNIT ASSY
(OPTIONAL)
MAIN UNIT ASSY.
ARTEX
ARTEX
AMERI-KING
AMERI-K1NG
AMERI-KING
AMERI-KING
110-416
453-0150
4500041
450004
450004-1V/-1H
AK-450
FUSE HOLDER
(ALl')
FUSE HOLDER
LITTEL FUSE
LI'I-rEL FUSE
McGRAW EDISON
155020
155129
FHN42W
JACK, PHONE
WASHERS
'JACK, PHONE
WASHERS
SWITCHCRAFT
SWITCHCRAFT
SWlTCHCRAFT
SWlTCHCRAFT
C-11
S-1028/S-1029
C-112B
S-1028/S-1029
-DP103A
DP104A
DP105A
--
-DT104A
DT105A
DU105A
--DV101A
--DV101B
DV102A
-DV102B
EG101A
--EG102A
-EG103A
EG104A
ET101A
ET102A
ET103A
ET104A
ET105A
--
FH101A
FH102A
--
FN101A
--FN102A
--
AERO INSTR
12-98
NOTES
1
91-20-06
99
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
FU101A
FU102A
FU103A
FU104A
FU105A
FU106A
FUSE (1 AMP)
FUSE (5 AMP - 3AG-SLO-BLO)
FUSE (10 AMP, SLO-BLO)
FUSE (5 AMP)
FUSE (0.5 AMP)
FUSE (2 A MP)
LITTEL
LITTEL
LI1-FEL
McGRAW-EDISON
McGRAW-EDISON
LITTEL
313001
313005
313010
FM01-5A
FM01-.50A
JE101A
JE102A
JE103A
JE104A
CONTROL, IGNITION
CABLE
MAGNETO, LEFT
MAGNETO, RIGHT
LASAR (SLICK)
LASAR (SLICK)
SLICK (LASAR)
SLICK (LAZAR)
CD-1001-02
CH-1001-XX
CD-4771
CD4770
JM101A
swITcH, IGNITION
BENDIX SCINTILLA
/PLACARD
BENDIX SCINTILLA
/LUG, TERMINAL
BENDIX SCINTILLA
SWITCH, IGNITION (INCL CONN.) JANCO
MAGNETO
BENDIX SCINTILLA
(ALT)
BENDIX SCINTILLA
(ALT)
LYCOMING
PLUG, MAGNETO
BENDIX SCINTILLA
MAGNETO
SLICK
MAGNETO, LEFT
SLICK
MAGNETO, RIGHT
SUCK
SWITCH, IGNITION
BENDIX-SCINTILLA
MAGNETO, LEFT
SLICK
MAGNETO, RIGHT
SUCK
IGNITION, PULSAR
MOONEY
MAGNETO, L & R
TCM/BENDIX
MAGNETO, L & R
TCM
MAGNETO, L & R (OPT.)
BENDIX
10-357210-9
10-187-468
10-126656
97-2273-1
D4LN2021
D4LN3000
LW-682555-11
10-382698
6224
6261
6260
10-357240-1
6393
6350
800315-501
10-79020-10
640896-1
10-79020-120
LA101A
LA102A
LA103A
LA104A
LA105A
LA106A
LA107A
LA108A
LA109A
LA110A
LA111A
LA112A
LA113A
LA114A
LA115A
LIGHT BULB, 28V
LIGHT BULB, 14V
LIGHT BULB
LIGHT BULB
UGHT BULB
UGHT BULB
LIGHT BULB
LIGHT BULB
LIGHT BULB
LIGHT BULB
UGHT BULB
LIGHT BULB
UGHT BULB
LIGHT BULB
LED
400
168-T-3 1/4
385
330
CM7-7330
CM7-7327
370
1816
AVIA. RED, 327
327
1818
1495
4596
P26028
351-0003
LB101A
LB101B
LB102A
LB102B
LB102C
C/B-SW, BEACON, WHITE
MOONEY
C/B-SW, BEACON, BLACK
MOONEY
BEACON, ROTATING
WHELEN
/ADAPTER
WHELEN
LIGHT, ANTI-COLLISION (RED) WHELEN
UGHT, ANTI-COLLISION 0NHITE) WHELEN
930023-243
930023-343
WRML-28
WRML-65
90033-19
90033-20
LC101A
CONTROL BOX, UGHT
800268-509
--JM101B
JM102A
--JM103A
JM104A
JM105A
JM106A
JM107A
JM108A
JM109A
JM110A
JM111A
JM113A
--
--
91-20-06
100
GE
GE
GE
GE
CHICAGO MINI
CHICAGO MINI
GE
GE
GE
GE
GE
GE
GE
PACIFICPREC.PROD
MOUSER
MOONEY
12-98
NOTES
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
LE101A
LE102A
LE103A
LE104A
LE105A
LE106A
LE107A
LE108A
LE109A
LEl10A
LE111A
LE112A
LE113A
LEl14A
LE115A
LE116A
LE117A
LE119A
LENS, ANNUNC. (US) (M20J)
MOONEY
LENS, ANNUNC. (FRANCE) (M20J) MOONEY
LENS, ANNUNC. (US) (M20M) MOONEY
LENS, ANNUNC. (FRANCE) (M20M) MOONEY
LENS, ANNUNC. (M20T)
MOONEY
LENS, ANNUNC. (M2OT)
MOONEY
LENS, ANNUNC. (US) (M20J)
MOONEY
LENS, ANNUNC. (FRANCE) (M20J) MOONEY
LENS, ANNUNC. (US) (M20R) MOONEY
LENS, ANNUNC. (FRANCE) (M20R) MOONEY
LENS, ANNUNC. (US) (M20R) MOONEY
LENS, ANNUNC. (FRANCE) (M20R) MOONEY
LENS, ANNUNC. (US) (M20K) MOONEY
LENS, ANNUNC. (US) (M20K) MOONEY
LENS, ANNUNC. (M2OK)
MOONEY
LENS, ANNUNC.
SLOANE
LENS, ANNUNC. (M20J)
MOONEY
LENS, MASTER WARN
MOONEY
880048-613
880048-615
880048-617
880048-619
880048-621
880048-523
880044-633
880044-635
880048-625
880048-627
880048-629
880048-631
880048-605
880048-607
880089-001
855-SE-C
880089-003
150080-6097
LG101A
LG102A
CIRCUIT BREAKER, LOGO LIGHT MOONEY
LIGHT, LOGO
WHELEN
930023-357
A730-1-28
LH101A
LH102A
LH103A
LH104A
LH105A
LH106A
LH107A
LH108A
MOONEY
DIAUGHT
WHELEN
SLOAN
INSTRUMENTS
INSTRUMENTS
SIGMA-TEC
HH SMITH
LEECRAFT
ALLIED
SPC
NEWARK
HH SMITH
WHELEN
TEK-LITE
LH112A
LH113A
LAMP HOLDER
LAMP HOLDER
LAMP HOLDER
LAMP HOLDER
LAMP HOLDER
LAMP HOLDER
LAMP HOLDER
LAMP HOLDER
(ALl-)
(ALr)
(ALT)
(ALl')
LAMP HOLDER
LAMP HOLDER
LAMP HOLDER
(ALE)
LAMP HOLDER
LAMP HOLDER
WHELEN
MOUSER
914083-1
270-1930-0171-702
A-350-CN-CL-BK-SH-28
855S-O-U
0211-128
BA28-24-BW3
1V-192-971
1930
7-05
931-3103
LSL-11-128U
81N2561
1925
01-0770437-00
LC-28-5
MS1745-51A
01-077-0142-04
351-0003
LL101A
LL101B
LL102A
LL103A
SWITCH, LDG LIGHT
SWITCH, LDG LIGHT
BULB, LIGHT, LDGfFAXl
BULB, LIGHT, LDG/TAXl
MOONEY
MOONEY
GE
GE
880052-521
886052-121
4596
4509
LN101A
LN101B
LN102A
LN102A
CIRCUIT BREAKER
C/B
LIGHT, NAV. (TAIL)
UGHT, NAV. (TAIL)
MOONEY
MOONEY
MOONEY
MOONEY
930023-251
930023-351
800051-501
800051-509
LP101A
LP102A
LP103A
LP104A
LP105A
DIMMER, BOX
DIMMER, CONTROL BOX
. DIMMER, CONTROL BOX
SWITCH, O/H LIGHT ASSY
_INVERTER,E-L PLACARD
MOONEY
MOONEY
MOONEY
MOONEY
ERG
800299-501
800299-503
800299-505
150085-005
LPS28-3-3P
----LH109A
LH11OA
LH111A
--
VENDOR
12-98
PART NO.
NOTES
2
91-20-06
101
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
LR101A
LR101B
LR102A
C/B
C/B
LIGHT, RECOGNITION
MOONEY
MOONEY
MOONEY
930023-231
930023-331
880049-501
LS101A
LS101B
LS102A
LS102B
LS103A
LS104A
LS105A
LS106A
CIRCUIT BREAKER
CIRCUIT BREAKER
POWER SUPPLY, STROBE
POWER SUPPLY, STROBE
LIGHT, STROBE-LT WING
LIGHT, STROBE-RT WING
LIGHT, STROBE, TAIL
LIGHT, STROBE, DUAL
MOONEY
MOONEY
WHELEN
WHELEN
WHELEN
WHELEN
MOONEY
WHELEN
930023-237
930023-337
01-0770329-00
01-0770329-01
01-0770054-12
01-0770054-13
470013-501
A413A-HDA-CF
LT101A
LT101B
LT102A
SWITCH, TAXI LIGHT
SWITCH, TAXI LIGHT
BULB, LIGHT, TAXI, LH & RH
MOONEY
MOONEY
GE
880052-523
880052-123
4596
MA101A
RECEPTACLE, AUX. POWER
(ALT)
AN2552-3A
MS3503-1
MB101A
MB101B
C]I_SWlTCH, RADIOMASTER(WriT) MOONEY
C/B-SWITCH,RADIO MASTER (BLK) MOONEY
930023-213
930023-313
MO101A
MC102A
MC103A
LIGHTER, CIGAR
CAP & TETHER
LIGHTER, SOCKET
(ALT) w/WIRE
MOONEY
CASCO
CASCO
CASCO
800336-503
216550
216510
200402
----
CLOCK
(ALT)
CONNECTOR, 4 PIN
PINS
(OPT)
(OPT) PINS
MID-CONT.
PORSCHE
MID-CONT
MID-CONT
PORSCHE
PORSCHE
MD-89
944.641.213.00
6016177
6016125
944.612.217.00
999.652.351.12
---
JACK, MICROPHONE
WASHERS
WASHERS
SWlTCHCRAFT
SWlTCHCRAFT
SWlTCHCRAFT
C-12B
S-1028
S-1029
--
--ME101A
-MIE102A
MK101A
MP101A
MP101B
MP102A
MP102B
MP103A
C/B-SW, PROP DE-ICE (WHITE) MOONEY
C/B-SW, PROP DE-ICE (BLK)
MOONEY
TIMER, PROP DE-ICE
BF GOODRICH
TIMER, PROP DE-ICE
McCAULEY
TERMINAL BLOCK
McCAULEY
930023-245
930023-345
3E1899-1
B-45018
C-40521
NF101A
NF101B
NF102A
SW/C-B, LOW BOOST FUEL PUMP MOONEY
SW/C-B
MOONEY
PUMP, FUEL BOOST
WELDON
(ALT)
WELDON
PUMP, FUEL BOOST
WELDON
(ALT)
WELDON
PUMP, FUEL BOOST (M20K)
WELDON
PUMP, FUEL BOOST
WELDON
PUMP, FUEL BOOST
WELDON
'(ALT)
MASSEY
REGULATOR, FUEL PUMP
MOONEY
SW/C-B, HI-BOOST FUEL PUMPMOONEY
GUARD ASSY, HI-BOOST SW. MOONEY
930023-211
930023-311
A8163B
8163B
8163A
A8163A
10054B
A10051-D
A8152-B
VR536
800270-523A
930023-219
930028-501
-NF103A
-NF104A
NF105A
NF106A
NF108A
NF108B
NF109A
NF110A
91-20-06
102
12-98
NOTES
MOONEY AIRCRAFT CORPORATION
CODE
DESCRIPTION
PAl 01A
--PA102A
PA103A
PA104A
PAl 05A
M20J
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
---
PA106A
--PA107A
-PA108A
-PA109A
PAl 10A
PA111A
PAlllB
PAl 12A
PAl 13A
PAl 14A
--
VENDOR
PART NO.
REGULATOR, VOLTAGE
MOONEY
809270-601
(ALT)
AM.PROD,,'PRECISE
FiT DGR-2
(ALT)
AUX]_ODELTA
VR-802
SWITCH, ALT'NTR FIELD (DUAL) MOONEY
880052-525
SWITCH,AL3"NTR.FIELD (SINGLE) MOONEY
680052-508
ALTERNATOR
LYCOMING
LW-14367
(ALl)
PRESTOLITE
ALU-6421-LS
ALTERNATOR
LYCOMING
LW-15404
(ALl')
PRESTOLITE
ALY-8420
ALTERNATOR, RIGHT
TCM
649719
(ALT)
TCM
649280
GEAR ASSY
TCM
649123
ALTERNATOR
ELECTRO SYSTEMS
ES-4009-LS
KIT, INSTALL
LYCOMING
05K-21065
(REFERENCE 600160)
FILTER
MOONEY
880014-501
(ALT)
MOONEY
800307-501
SENSOR, CURRENT
MICRO SWITCH
CSLA1GE
REGULATOR, VOLTAGE
MOONEY
800270-503
SENSOR, CURRENT (110A)
KUXON
7235-1-110
SENSOR, CURRENT (175A)
KLIXON
7235-1-175
ALTERNATOR
TCM
649304
MONITOR, CURRENT
MOONEY
800287-501
ALTERNATOR, LEFT
TCM
649172
(ALT)
TCM
649283
PB101A
PS102A
PB102B
PB103A
PB103B
PB105A
PS105B
BATTERY
SWITCH, MASTER
SWITCH, MASTER
SWITCH, BAT 1-2
SWITCH, BAT 1-2
BATTERY, 24V
BA3-rERY, 24V
GILL
MOONEY
MOONEY
MOONEY
MOONEY
CONCORDE
CONCORDE
G-243
880052-501
880052-101
880052-527
880052-127
RG24-11M
RG24-15
PL01A
PL02A
PL02B
PL02C
PL02D
PL03A
PL03S
PL03C
PL03D
PL03E
PLUG, 1 PIN
PLUG, 2 PiN
PLUG, 2 PIN
PLUG, 2 PIN (FEMALE)
PLUG, 2 PIN
PLUG, 3 PIN
PLUG, 3 PIN
PLUG, 3 PIN
PLUG, 3 PIN
PLUG, 3 PIN
SOCKET (ALUMEL)
SOCKET (ALUMEL)
PLUG 4 PIN
PLUG 4 PIN
PLUG 4 PIN
PLUG 4 PIN
PLUG 5 PIN
PLUG 5 PIN
PLUG 6 PIN
.PLUG 7 P|N
(ALT)
PLUG, 8 PIN
AMP
AMP
MOLEX
DEAN
1-480349-0
1-480318-0
03-06-1023
7021
_ MS3106A-24-9S
1-380303-0
206037-2
MS3106A-10SL-3S
MS3106A-28-6P
PWF06F08-33B
01-2020-245
01-2020-244
206060-1
MS3106A-32-17S
1-480424-0
PW06FS-4S
MS3106A-I 4S-5S
BVD06E0205SN
MS3106A-28-22S
MS3106A-20-15S
MS3106R-20-15S
205888-1
PL04A
PL04B
PLO4C
PL04D
PL05A
PL05B
PL06A
PL07A
---
-PL08A
NOTES
AMP
AMP
ARRAY
CDI
CDI
AMP
AMP
ARRAY CONN
DEUTSCH
MATRIX SCIENT.
AMP
12-98
4
91-20-06
103
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
VENDOR
PART NO.
PL09A
PL09B
PL09C
PL09D
PL09E
PL14A
PL14B
PL14C
PL15A
PL16A
PL17A
PI_20A
PL20B
PL20C
PL25A
PL25B
PL26A
PL28A
PL32A
PL34A
PL34B
PL37A
PL37B
PL50
PL104A
PLUG 9 PIN
PLUG 9 PIN
PLUG 9 PIN
PLUG 9 PIN
PLUG 9 PIN
PLUG 14 PIN
PLUG 14 PIN
PLUG 14 PIN
PLUG 15 PIN
PLUG 16 PIN
PLUG 17 PIN
PLUG 20 PIN
PLUG 20 PIN
PLUG. 20 PIN
PLUG 25 PIN
PLUG 25 PIN
PLUG 26 PIN
PLUG 28 PIN
PLUG 32 PIN
PLUG 34 PIN
PLUG 34 PIN
PLUG, 37 PIN
PLUG, 37 PIN
PLUG, 50 PIN
PLUG, 104 PIN
AMP
AMP
MOONEY
POSITRONICS
206708-1
126-222
DE9S
03-06-2092
206485-1
930021-1
930021-513
206043-3
DA15S
206037-1
DSM17W2S
930021-501
CC148-003-0.00
CC149-003-0.00
DB25S
205208-1
930021-505
205839-3
M83723/86R2232N
930021-507
930021-515
206150-1
DC37S
930021-511
GMCT104FOTH000
PS101A
PS102A
PS103A
PSI05A
C/B, START POWER
C/B, START POWER
STARTER (M20J)
(ALr)
STARTER (M20K & M20R
(ALT)
STARTER (M20M)
KLIXON
KLIXON
PRESTOLITE
LYCOMING
TCM
TCM
B &C
7277-2-10
7277-2-5
MHB4016
LW-15572
646275
637847
BSC206-149
RB101A
RB102A
SLOWER, RADIO
SLOWER RADIO
KING
GLOBE
071-4037-01
19A2790
RC01A
RC02A
RC02C
RC02D
RC02E
RC03A
RC03B
RC03C
RC03D
RC04A
RC04B
RC04C
RC04D
RC05B
RC06A
RC08A
RC09A
RC09B
RC09C
RC09E
RC12A
RC14A
91-20-06
104
RECEPTACLE 1 PIN
RECEPTACLE 2 PIN
RECEPTACLE 2 PIN (MALE)
RECEPTACLE 2 PIN
RECEPTACLE 2 PIN
RECEPTACLE 3 PIN
RECEPTACLE 3 PIN
RECEPTACLE 3 PIN
RECEPTACLE, 3 PIN
RECEPTACLE 4 PIN
RECEPTACLE 4 PIN
RECEPTACLE 4 PIN
RECEPTACLE 4PIN
RECEPTACLE 5 PIN
RECEPTACLE, 6 PIN
RECEPTACLE, 8 PIN
. RECEPTACLE, 9 PIN
. RECEPTACLE, 9 PIN
RECEPTACLE, 9 PIN
RECEPTACLE, 9 PIN
RECEPTACLE, 12 PIN
RECEPTACLE, 14 PIN
AMP
AMP
DEAN
1-480351-0
1-480319-0
7022
MS3100-24-9P
03-06-2023
t-480305-0
206036-2
206207-1
MS3100-28-6S
206153-1
M3100-32-17P
1-480426-0
PW01F8-04P
BVD04E0205PN
MS3100C-28-22P
205841-2
206705-2
206705-1
DE9P
205486-1
03-06-2122
980021-2
-PS104A
--
MOLEX
AMP
MOONEY
MOONEY
AMP
AMP
MOONEY
POSITRONICS
POSITRONICS
AMP
MOONEY
AMP
MOONEY
MOONEY
AMP
MOLEX
AMP
AMP
AMP
AMP
AMP
ARRAY
DEUTSCH
MATRIX SCIENCE
AMP
AMP
AMP
AMP
MOLEX
MOONEY
12-98
NOTES
4
MOONEY AIRCRAFT CORPORATION
CODE
M20J
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
DESCRIPTION
VENDOR
PART NO.
RECEPTACLE, 14 PIN
(ALT)
RECEPTACLE, 14 PIN
RECEPTACLE, 16 PIN
RECEPTACLE, 16 PIN
RECEPTACLE, 20 PIN
RECEPTACLE, 20 PIN
RECEPTACLE, 26 PIN
RECEPTACLE, 28 PIN
RECEPTACLE, 32 PIN
RECEPTACLE, 34 PIN
RECEPTACLE, 34 PIN
(AL'I_
RECEPTACLE, 37 PIN
RECEPTACLE, 104 PIN
RECEPTACLE, 170 PIN
SOCKETS (22CA)
SOCKETS (20-18 GA)
SOCKETS (20-14GA}
AMP
POSITRONIC
AMP
AMP
AMP
MOONEY
POSITRONICS
MOONEY
AMP
MATRIX SCIENCE
MOONEY
AMP
POSITRONIC
AMP
POSITRONICS
HYPERTRONICS
HYPERTRONICS
HYPERTRONICS
HYPERTRONICS
203540-1
G14000H000-1265.0
206044-1
206036-2
206036-1
930021-502
GMCT2MOE100J0
930021-506
206152-1
M83723/83K2232N
930021-508
204814-1
SK2114
206151-1
GMCT104M0000Z0
NEBV23-077
YSK006-011
YSK006-089
YSK015-025AH
RELAY, 28V/200A
(ALT)
(ALT) (OBSOLETE)
RELAY, 14V/200A
RELAY
RELAY
RELAY, 28V/5OA
BRACKET (2 REQ'D.)
(AL'r)
RELAY, 28V/100A
RELAY 14V/200A
RELAY
RELAY
RELAY
SOCKET
TERMINAL
KISSUNG
KISSLING
C-H
C-H
KISSLING
KISSUNG
KISSUNG
MOONEY
C-H
C-H
C-H
MAGNACRAFT
KISSLING
P&B
P&B
P&B
26.57.01
26.57.02
6041H-202/202A
6041H-105A
26.64.01
26.64.21
26.72.03
800375-1
6041H-220
6041H-53
6041H-105R
W67RCSX-3
28.08.01
VF4-15-H 11
VCF4-1O02
26A1348C
RS101A
RS102A
RS103A
RS104A
RS105A
RS106A
RS107A
RESISTOR, 20-OHM/10W
RESISTOR, 5 OHM/10W
RESISTOR, 500 OHM
RESISTOR, 100 OHM
RESISTOR, 7.5-OHM
RESISTOR, 1K OHM/2W
RESISTOR, 5K OHM
DALE
DALE
MOONEY
NEWARK
DALE
ALLEN BRADLEY
SPECTROL
RH-10-20 OHM
RH-10-5 OHM
919029-501
09F976
RH-50-7.5 OHM
RC42-GF102J
789-B_E_02
RS115A
RS116A
RESISTOR
.RESISTOR
OHMITE
OHMITE
1.6K OHM/1/2W
1.00HM/1/SW
RC14B
--RC14C
RC16A
RC16B
RC20A
RC20B
RC26A
RC28A
RC32A
RC34A
RC34B
RC37A
RC104A
RC170A
--
----RL101A
--RL102A
RLIO3A
RL104A
RL105A
..
--RL106A
RL107A
RL108A
RL109A
RL110A
---
SA101A
---
ALTERNATOR, STAND-BY
B&C
HOUSING, PLASTIC CONNECTOR B&C
TERMINAL, 1/4 INCH
B&C
12"90
:
NOTES
3D
BC410-1
12-003
14-026
....
91-20-06
105
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
CODE
DESCRIPTION
SA102A
SA103A
CONTROLLER, 8TBY ALTERNATOR B&C
SWITCH, STBYALT./EMERG BUS MOONEY
B0203-2
880052-531
SB101A
SB102A
SB103A
SB104A
C/B, SPEEDBRAKE
KLIXON
SWITCH, SPEEDBRAKE, YOKE PRECISE FLT
RELAY, SPEEDSRAKE
PRECISE FLT
DIODE, SPEEDBRAKE
(ALl]
GE
MOTOR, SPEEDBRAKE
PRECISE FLT
SWITCH, SPEEDBRAKE
PRECISE FLT
SOLENOID, CLUTCH, SPEEDBRK PRECISE FLT
S/B INTERFACE
MOONEY
7277-2-3
01255
01384
1N2483/1N5060
3720-GE
01532
01505
01679
900314-501
SPEAKER, ALERT
SPEAKER, CABIN
(ALl')
SONALERT
40-1333C
40-1325
PCx352
SC628
-SB105A
SB106A
SB107A
SB108A
SP101A
SP102A
-SP103A
SW101A
-SW102A
SWIO3A
SWIO4A
-SWl05A
SWl06A
SW107A
SWl08A
SWl08A
SW110A
SW111A
SW112A
SW113A
SW114A
SW115A
--
--
---
--
-SWl 16A
SW117A
SW118A
SW119A
SW120A
SW121A
SW122A
SW123A
SW124A
SW125A
SW126A
91-20-06
106
VENDOR
ARCHER
ARCHER
BLAUPUNK-r
MALLORY
SWITCH
MICRO
(ALT)
SAINT
SWITCH, DEFROSTER BLWR CHERRY
SWITCH
MICRO
SWITCH, UP-LIMIT
MICRO
(ALT)
SAINT
SWITCH, DN-LIMIT
MICRO
(ALT)
O3-i"OCONT.
SWITCH
CARLING
SWITCH
MOONEY
SWITCH
C-H
SWITCH
C-H
(ALl')
ALCO
SWITCH
GRAYHILL
SWITCH
C-H
SWITCH
CARUNG
SWITCH
MICRO
SWITCH, WHITE CAP
MICRO
(AKT)
SWITCH
C&K
SWITCH
NKK
INCLUDES - BUTTON, LOCKRING,
LOCKWASHER, HEX NUT (2)
(ALT)
C-H
LOCK RING
C-H
LOCK WASHER
C-H
HEX NUT (2)
C-H
(ALT)
TSCHUDIN
LENS
TSCHUDIN
BULB
TSCHUDIN
SWITCH
MOONEY
SWITCH
CARUNG
SWITCH
MOONEY
SWITCH
CARLING
SWITCH
, SWITCH
CROUZET
SWITCH
CROUZET
SWITCH
ALCO
SWITCH
SWITCH
NKK
SWITCH
EATON
12-98
PART NO.
1SE1-T
ZS-1009
E51-50S
V3-1
DT-2R-47
ML-1409
1CHl16-5
P6-24014
R0911-VBBOW
880013-507
89061<2375
SA1RV20
MPE-106F-C-22-9
71AD30-02-2-AJN
89061<4731
RA911-VBBOW
12TW-10
15PAg0-8W
MS27753-38
7101K
DLB241-W01-1-3(3/
AT506M/ATS03MB
SB1DDX492-2
29-761
16-856
15-966-6
504102
464415
590002
880012-501
TILC64-1S-WHFN
880062-501
TIGM64-1S-WHEN
MS35058-22
83-450-001
83-452-504
MPE106F
MB2085SB1W01-EA
1501-11E
NOTES
5
MOONEY AIRCRAFT CORPORATION
CODE
M20J
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
DESCRIPTION
VENDOR
PART NO.
----
SWITCH, MASTER WARN
SW. (w/LENS)
SW. (w/LEGEND)
SW. (w/BULB)
SWITCH
OMRON
OMRON
OMRON
OMRON
NKK
A3BA-7011-1
A3BA-500R
A3BA-5202
A3B-028
MB2085SB1W01-EA
--
VOLTAGE CONVERTER, 28-14 TERRA
(ALT)
TERRA
MLC28-8
C28-5
VR101A
VARISTOR
GE
V47ZA05
WMIO1A
WM102A
WARNING, MASTER
WARNING, MASTER
MICRO
MICRO
DSK-104-GYR
DSB-11-RRRR-LR2
WS103A
ALERT, STALL/GEAR WARN
(ALT)
SWITCH, STALL WARN
IAI
tAI
MOONEY
950D809-000
950D519-000
800364-509
WT101A
WT101B
WT102A
WT103A
WT104A
ANNUNCIATOR
ANNUNCIATOR
ANNUNCIATOR
ANNUNCIATOR
ANNUNCIATOR
MOONEY
MOONEY
MOONEY
MOONEY
MOONEY
880048-501
880090-XXX
880048-503
880048-507
880048-509
SW127A
SW135A
VC101A
WS101A
--
NOTES
6
NOTES:
1. ALL P/N's ARE ACCEPTABLE. SEE VENDOR INFORMATION FOR APPLICABLE CONFIGURATION.
2. 1 EACH MS35334-21 OR M2898 (ALLEN BRADLEY) INTERNALTOOTH LOCKWASHER, REQUIRED
WITH EACH LIGHT, IF NOT SUPPLEDBY SLOAN
3. SEAL BACK OF POTENTIOMETER WITH DOW CORNING #738 ELECTRICAL SEALANT AFTER
WIRES ARE SOLDERED TO TERMINALS.
4. PL02C & RC02C MAY BE PURCHASED FROM DEAN AS P/N 7020.
6. SEAL BACK OF SWITCH WITH DOW CORNING #738 ELECTRICAL SEALANT AFTER
WIRES ARE SOLDERED TO TERMINALS WHEN USED AS "I-HROTFLE SWITCH-GEARWARNING".
6. ANNUCIATOR P/N WILL BE DETERMINED BY OPTIONS INSTALLED. REF. DRAWING # 880090.
12-98
91-20-O6
107
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
RESERVED FOR FUTURE ENTRIES
91-20-06
108
12-98
MOONEY AIRCRAFT CORPORATION
(
M20J
SERVICE AND MAINTENANCE MANUAL
ELECTRICAL EQUIPMENT CHART
RESERVED FOR FUTURE ENTRIES
12-98
91-20-06
109
SERVICE AND MAINTENANCE MANUAL
M20J
MOONEY AIRCRAFT CORPORATION
ELECTRICAL EQUIPMENT CHART
RESERVED FOR FUTURE ENTRIES
91-20-06
110
12-98
SERVICE AND MAINTENANCE MANUAL
91-30-00
M20J
MOONE'YAIRCRAFT CORPORATION
- ELECTRICAL SYSTEM SCHEMATICS (SEE ENVELOPES)
(
12-98
91-30-00
111/112BLANK
MOONEY AIRCRAFT CORPORATION
M20J
CHAPTER 95
SPECIAL
EQUIPMENT
SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
M20J
SERVICE AND MAINTENANCE MANUAL
{
!
CURRENTLY NOT BEING USED
12-98
95-SPECIAL EQUIPMENT
1
SERVIGEAND MAINTENANCE MANUAL
M20J_
INTENTIONALLY
LEFT
BLANK
95-SPECIAL EQUIPMENT
2
12-98
MOONEY AIRCRAFT CORPORATION