OLDWILLWAYNE

O O

SERVICE AND MAINTEN ANC E

MANUAL

~3 r 1

MOONEY AIRCRAFT CORPORATION

LOUIS SCHREINER FIELD, KERRVILLE, TEXAS. 78028
BY FAR PARr23"
~IS HANDBOOK INCLUDES THE MAINTENANCE INFORMATION REQUIRED TO BE AVAILABLE

1997 MANUAL NUMBER 134

ISSUED September,
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
LOG OF REVISIONS
insert revised pages.
Always destroy superseded pages when you

CHAPTERS AFFECTED DATE OF RR/ISION CHAPTERS AFFECTED

DATE OF RNISION

9/97 Reissue

list of effective pages will appear at the beginning of each

SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
INTRODUCTION SYSTEMICHAPTER

This manual provides servicing and maintenance The van’ous groups contain major systems information
information for the Mooney Model M20K, Sen’al such as flight controls, landing gear, etc. The systems
Numbers 25-0001 and ON. Maintenance actions that are arranged numen’cally per GAMA recommended
refer to a limited number of aircraft will be designated number assignment, It is suggested, for examplethat
by serial number of applicable airplanes. "Fuel" be identified with the SystemlChapter number
in ’28~ The sequence of numbers, CHAPTER, 26-99-99,
The format and contents of this manual are prepared
GENERAL AVIATLON refers to the General information of the Fuel Systems.
accordance with
MANUFACTURER’S ASSOCIATION (GAMA) SUBSYSTEM/SECTION
Specification No. 2. The manual is supplemented with
wjring schematics for the various model year The major systems of an aircraft are broken down into
airplanes,as necessary. These are located in sub-systems. These sub-systems are identified by the
envelopes at the back of the manual te~ds pages. second element of the sequence of numbers,
SECTION, ie., 28-20-00. The element -20- indicates
NOTE
the distribution portion of the fuel system.
Revisions reissues ofthis manual are nat
or
automatically provided to manual holders. Holders UNITISUBJECT
of tf~se and other Mooney Technical Publications
should complete the information on die YELLOW The individual units within a su~system may be
CARDS located atthe front of the Trtle Page and identified by a third element of the sequence of
sendto: numbers, SUBJECT, ie.,28-20-01. This number is
Mooney Aircraft Corporation assigned by the manufacturer and may or may not be
Attn:Service Parts Department. used depending upon the complexity of the
Louis Schreiner Field maintenance action recommended.
Kerrville, Texas., 78028, U.SA.
Notification is sent to known manual holders when APPUCATION OF NUMBERING SYSTEM
another manual is prepared to replace the subscription
and advises that no more revisions will be sent out. The Mooney Aircraft Corporation is in the process of
new manual will require a new subscnption service. If revising all applicable technical publications to the
additional Technical Publications are desired, contact GAMA format~.When this effort is completed any
the above department at Mooney Aircraft Corporation publication conceming maintenance of aircraft will
conform to this basic numbering system. Any person
at (830) 896-6000, e~ct. 2092.
wishing information concerning the Fuel Distribution
Correspondence concerning maintenance or part System would refer to the pages identified as
numbers on an airplane should contain the aircraft ,28-20-00, in any maintenance oriented publication.
model number and sen’al number. The sen’al number These pages will be numbered sequentially within each
appears on the identification placard located on the aft system breakdown in the current Mooney series of
end, left hand side of the tailcone below the hon’zontal aircraft. As Mooney aircraft models become more
stabilizer, complex the page numbers may be sequentially
numbered within sub-systems.
ASSIGNMENT OF SUBJECT MATERIAL
The table contents
of in the front of each
The content of this publication is organized at four of su~systems
SystemlChapter will provide a list
levels: covered in the Chapter. For example:
Group
System/Chapter
Sub-system/Section 28-00 General
Unit/Subject
28-10 Storage
GROUP
CTanks, vents, repair, etc.)
These are pn’mary divisions of the manual that enable
28-20 Distribution
broad separation of content, ie., Airframe systems VS
(Boost pumps, fuel lines, etc.)
Powerplant systems. These groups are identified by
tabs. 2&40 Indicating
(Sender Units, quantity gauges, etc.)

the number
If there is a reason to distinguish between LEFT HAND or RIGHT HAND fuel quantity sending units then
would be expanded to 28-40-01 (Left Hand) and 28-40-02 (Right Hand). This concept will apply to any expanded
information throughout the publications

INTRODUCTION
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
SUPPLEMENTARY PUBLICATIONS
The following list of Manufacturew and/or publications can provide servicing and maintenance information on
comoonents of the Mooney 231, 252, TSE, or ENCORE Model M20K. No avionics equipment Manufacturers or
publications are listed due to the many configurations that can be installed in the aircraft. These can be obtained
from the repair stations for a particular avionics manufacturer.
Publications available from Mooney Aircraft Corporation are listed in the Parts Pn’ce List and are available through
any Mooney Marketing/Service Center.
As publications on various components become available, they will be added to the list below.

VENDOR ADDRESSES or PUBLICATIONS

ENGINE
The following maintenance publications can be obtained through Teledyne Continental Motors CTCM) Aircraft
Products Divi~sion distn’butors in your area or from TCM, P.O. Box 90, Mobile, AL. 36601, Tele.: (334) 438-3411.
OVERHAUL MANUAL Form Number’s X30596A, for TCM TSle360-GB, -LB,-MB series aircraft engines 8
X30596A for -SB series engines.

ILLUSTRATED PARTS CATALOG Form Number’s X30597A, for-GB, -LB, -MB sen’es engines 8 X30597A/S2 for
-SB engines.

OPERATORS MANUAL Form Number’s X30536 forTSIO-360-G~GB series engines, X30571 for TSIO-360-LB
series engines, X30584 for -MB sen’es engines and X30671 for SE series engines.

MAINTENANCE AND
OPERATOR’S MANUAL Form Number’s X30584 forTSIO-360-MB sen’es engine 8 X30672A for -SB engines.

SERVICE BULLETINS Specify model of engine for which maintenance data is desired.

PROPELLER
McCauley Propellers Obtain publications from McCauley Accesson’es Division, Cessna Aircraft Company, 3535
McCauley Drive, Vandalia, OH.,45377.

SeM’ce Manual No. 780630 for McCauley C200 series constant speed propellers.

Harizell Popellers Obtain publications from Hartzell Propeller, inc. 350 Washington Avenue, Piqua, OH., 45356.

Blade Specification Manual No. 133-A.

Overhaul Instructions- Manual No. 113-8.

MAG NETO
Bendix Sclntilla Magneto Obtain Service data for Bend’uc Series 2000 or 3000 magnetos from Bendix Corporation,
Electrical Components Division, Jacksonville, FL. 32245-7880.
Slick Magnetos Obtain Service data for Slick magnetos From Slick Aircraft Products, Unison Indust., 530
Blackhawk Park Ave., Rockford, IL. 61104, (815) 965-7704.

TURBOCHARGER

Maintenance and Overhaul Manual Number 070 for the RAJAY/Rotomaster turbocharger can be obtained from

RotoMaster, c/o Garrett Airesearch Aftermarket Div., 2511 So. Edison Way, Compton, CA, 90220-6035.

Maintenance and Ovemaul data on Airesearch turt~ocharger, Model No. TA0401, is available from Garrett
-Airesearch Industrial Div. (Allied-Signal), Los Angeles, CA.
INTRODUCTION
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE

SYSTEM/CHAPTER, SUB-SYSTEM/SECTION INDEX GUIDE

CHAPTER SUB-SYSTEM/ TITLE

SECTION

i 4 RESERVED BY GAMA MAY BE USED

AT LATER DATE

5 TIME LIMITS/MAINTENANCE CHECKS

00 GENERAL
10 TIME LIMITS
20 SCHEDULED MAINTENANCE CHECKS

6 DIMENSIONS AND AREAS

00 GENERAL

7 LIFTING

10 JACKING

8 LEVELING AND WEIGHING

00 LEVELING

9 TOWING AND TAXIING

00 GROUND HANDLING

10 TOWING

20 TAXIING

10 PARKING AND MOORING

00 GENERAL

10 PARKING

20 MOORING

11 PLACARDS AND MARKINGS

00 GENERAL

10 MARKINGS

20 PLACARDS- DCTERIORnMERIOR

INTRODUCTION
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CHAPTER SUB-SYSTEM/ TITLE
SECTION

12 SERVICING

00 SERVICING

10 REPLENISHING

20 SCHEDULED SERVICING

20 STANDARD PRACTICES -AIRFRAME

00 GENERAL

21 ENVIRONMENTAL SYSTEMS

00 CABIN VENTILATION SYSTEM

40 HEATING

24 ELECTRICAL POWER

00 GENERAL

30 DC GENERATION

50 ELECTRICAL LOAD DISTRIBUTION

27 FLIGHT CONTROLS

00 GENERAL

10 AILERON SYSTEM

20 RUDDER SYSTEM

30 ELEVATOR SYSTEM

40 STABILIZER TRIM SYSTEM

50 WING FLAP SYSTEM

90 MISCELLANEOUS

IMRODUCTION
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE

CHAPTER SU&SYSTEM/ TITLE

SECTION
28 FUEL

00 GENERAL

10 STORAGE

20 DISTRIBUTION

30 DUMP

40 INDICATING

90 MISCELLANEOUS

30 ICE AND RAIN PROTECTION

00 GENERAL

30 PITOT AND STATIC

60 PROPELLERS

32 LANDING GEAR

00 GENERAL

10 MAIN LANDING GEAR AND DOORS

20 NOSE LANDING GEAR AND DOORS

30 MTENSION AND RETRACTION

40 WHEELS AND BRAKES

50 STEERING

60 POSITION AND WARNING

80 MISCELLANEOUS

33 LIGHTS

00 GENERAL

20 INTERIOR LIGHTS
MAINTENANCE PRACTICES

40 DCTERIOR LIGHTS
MAINTENANCE PRACTICES

INTRODUCTION
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE

CHAPTER SUB-SYSTEMI TITLE

SECTION
34 NAVIGATION

00 GENERAL

10 PITOT STATIC AIR PRESSURE SYS-

TEM

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

20 ELECTRICAL AND ELECTRONICS

EQUIPMENT RACKS

51 STRUCTURES

00 GENERAL

10 STRUCTURAL REPAIR GENERAL

52 DOORS

00 GENERAL

10 CABIN DOOR
MAINTENANCE PRACTICE

30 BAGGAGE COMPARTMENT DOOR

MAINTENANCE PRACTICE

INTRODUCTION
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER SUB-SYSTEM/ TITLE
SECTION
53 FUSELAGE

00 GENERAL

10 MAIN FRAME

20 AUXILIARY STRUCTURE

30 PLATES/SKIN

40 ATTACH FITnNGS

50 nLLETS/FAIRINGS

55 STABIUZERS

00 GENERAL

10 HORIZONTAL STABILIZER

20 ELEVATOR

30 VERTICAL STABILIZER

40 RUDDER

56 WINDOWS

00 GENERAL

20 WINDSHIELD CABIN WINDOWS

50 PLMIGLASS DRILLING

57 WINGS

00 GENERAL

30 PLATES/SKINS

40 ATTACH AmNGS

50 FLIGHT SURFACES

60 STANDARD PRACTICES-PROPELLER

61 PROPELLERS

00 GENERAL

10 PROPELLER ASSEMBLY

20 CONTROLLING

INTRODUCTION
 MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CHAPTER SUBSYSTEMI TITLE
SECTION
71 POWERPLANT

0 GENERAL

10 COWLING

72 ENGINE- RECIPROCATING

00 GENERAL

73 ENGINE FUEL SYSTEM

00 GENERAL

10 DISTRIBUTION

20 CONTROLLING

30 INDICATING

74 IGNITION

00 GENERAL

10 POWER CONTROL

20 EMERGENCY SHUTDOWN

76 ENGINE CONTROLS

00 GENERAL

10 RIGGING

77 ENGINE INDICATING

00 GENERAL

10 POWER

20 TEMPERATURE

78 U(HAUST

00 GENERAL

10 INSTALLATION

30 SERVICING

40 REPLACEMENT COMPONENTS.

79 OIL

00 GENERAL

10 STORAGE

20 DISTRIBUTION

30 INDICATING
INTRODUCTION
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER SUBSYSTEMI TITLE
SECTION

80 STARTING
00 GENERAL
10 CRANKING

81 NRBINES
00 GENERAL
10 POWER RECOVERY
20 NRBOCHARGER

91 SCHEMATICS
00 GENERAL
20 ELECTRICAL SYSTEM
HARDWARE CHARTS
(14V 28 V)
30 SCHEMATICS (ENVELOPES)

95 SPECIAL EQUIPMENT

INTRODUCTION
~1100NEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE

BLANK

INTRODUCTION
10
 CHAPTER
OLDWILLWAYNE

TIME LIMITS/
MAINTENANCE
CH EC KS
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPOWI\TION

OLDWILLWAYNE
CHAPTER 5

TIME LIMITS/MAINTENANCE CHECKS

TABLE OF CONTENTS
CHAPTER
SECTION SUBJECT PAGE
SU&IECT

5-00-00 Gene~-al 5
5-00-01 Landing Gear System 5
5-00-02 Flight Control Systems 5
5-00-03 Wing FlapSystems 5
5-00-04 Electn’e Power System 5
5-00-05 Instruments 5
5-00-06 CabinHeating Ventilating systems 5
5-00-07 FuelSystem S
5-10-00 Time Limit Components 5
5-10-01 Airworthiness Limitations 6
(Ovemaul and Replacement Schedule)
5-20-00 Schedule Maintenance inspections 6

5-20-01 Check Points, Torque Values 6

5-20-02 Aircraft File Inspection 12
5-20-03 Engine Functional Check 12
5-20-04 First25 Hourlnspection 12
5-20-05 50 Hour Inspection 12
5-20-06 .100 Hour Inspection 13
5-20-07 Access Cover Identification,
Lubrication and Service Guide 18
Viscosity Requirements 21

SCONTENTS
3/4B LANK
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CHAPTER 5

TIME LIMITS/MAINTENANCE CHECKS

LIST Of EFFECTIVE PAGES

CHAPTER
SECTION PAGE DATE
SUBJECT

1/2BLANK 9-97
5-Effectivity
ti-Contents 3/4BLANK 9-97
5´• 997
5-00-00
5-00-04 6´• 9’97

5-1 0-01 7´• 997

5-20-01 8´• 997

5-20-01 9´• 997

5-20-01 10 997

5-20-05 11 9-97

5-20-06 12 9’97

5-20-06 13 9-97

5-20-06 14 9-97

5-20-06 15 9-97
5-20-06 16 997

5-20-06 17 9-97

5-20-07 18 9-97

5-20-07 19 9-97
5-20-07 20 9-97

5-20-07 21 9-97

5-20-07 22 9-97

SEFFECTIVITY
1/2BLANK
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND ~AINTENANCE MANUAL

OLDWILLWAYNE
5-0090 -GENERAL annunciator light. Circuit breakers or circuit breaker
switches protect the electrical wiring and equipment
AIRCRAFT DESCRIPTION. The M20K series of from overloads. Standard electrical equipment
aircraft are four place high-performance turt~ocharged includes: 2-100 uvatt landing lights, navigation lights,
single-engine low-wing monoplanes. The all-metal
interior lights, gear and stall warning system, an
airframe has a tubular-steel cabin frame covered with
electn’cal fuel boost pump, an electric starter, an
nonstructural aluminum skins, a semi-monocoque
electric gear retraction system with manual extension
tailcone, and full-cantilever laminar-fio~nr wing. Control
a
ovem’de and an electn’cal flap system.
surfaces have structural spar construction with
stressed skins n’veted to the spars and ribs. Dual 2. An optional standby generator (12V, 10 amp) is
control wheels accompany the conventional flight available to operate basic essential components in the
controls. The pilot’s rudder pedals have toe brakes event of main a8temator failure on S/N 25-0613 thru
linked to individual hydraulic cylinders that supply 250999 aircraft. An optional second 70 ampere, belt
pressure to the hydraulic disc brakes on each main driven alternator will be available on S/N 25-1000 and
gear wheel. Removable cc-pilot rudder pedals are ON aircraft.
standard equipment. The tn’cycle landing gear, having
5-00-05 -INSTRUMENTS
a steerable nose wheel controlled by rudder pedal
action, is fully retractable. The wide-span trailing-edge Allflight instruments are in the shock-mounted flight
wing flaps are electrically operated. For stabilizer tn’m, panel. Engine instruments are in the cc-pilot’s panel.
the entire empennage pivots vertically about its The pitot system provides air pressure to operate the
attaching points, airspeed indicator. The instrument static pressure
system has two static air pickup ports tone on each
5-00-01 LANDING GEAR SYSTEM
side of the tailcone) that open to the atmosphere. An
The electric landing gear system has a steerable nose alternate static source is provided on lower flight
wheel. Single disc self-adjusting hydraulic brakes are instrument panel. The instrument panel lighting system
featured on the main gear. Gear position lights, a has manual dimming mechanisms.
warning hom and a gear position indicator on the
floorboard are standard equipment. Bungee spn’ngs 5-00-06 CABIN HEATING 5 VENTILATING
that preload the the retraction mechanism in an SYSTEMS
over-center position lock the gear down. An air The heater muff encasing the exhaust system is the
pressure actuated safety switch in the eledn’cal system cabin heat source. Hot air from the heater muff m’uted
prevents electric gear retraction on takeoff until a safe with ambient air controls cabin temperature. Air routed
flying speed is attained. A gear throttle waming hom f,, the main heater duct system to nonles at the
sounds when the manifold pressure is less than a windshield base defrosts the windshield.
pre-set value with the landing gear up. The electn’c
gear retraction system has a manual e~dension system 590-07 FUEL SYSTEM
connected to the gear actuator that permits manual
lowen’ng of the gear in the event of an electn’cal
The fuel system has sealed, integral wing tanks in the
malfunction. forward, inboard section of each wing. Vents at the aff,
outboard top comer of each tank vent through the
5-00-02 FLIGHT CONTROL SYSTEMS lower wing surface. Fuel sump drains are at the lowest
The dual flight control systems can be operated from point in each tank. The electric fuel pump is in the
bottom left forward section of the fuselage just aft of
either the pilot or cc-pilot seat. All flight controls are
the firewall. The engine-driven fuel pump mounts on
conventional in operation, using pushpull tubes to link
the engine crankcase. Two fuel quantity transmitters in
the control surfaces to the control wheels and rudder
each tank are wired to fuel quantity gauges in the
pedals. Formica guide blocks maintain control tube
alignment and dampen vibration. An interconned engine cluster gauge. The master switch, left side of
the pilot’s panel, turns on the fuel quantity indicating
spring mechanism links the aileron and rudder systems
to assist in control coordination. The standard co-pilot’s systems. Visual sight gauges are available for partial
rudder pedals are removable. The tn~m system sets the fueling of wing tanks on aircraft 250001 and UP.
stabilizer angle of attack. A low fuel waming annunciator light for each tank is
activated when usable fuel quantity goes below 2 1~2
5-00-03 -WING FLAP SYSTEM
gallons.
Wing flaps are electrically actuated and are controlled
by a spring loaded "up-off-down" switch on the center 5-10-00 TIME LIMIT COMPONENTS
console. It is recommended that overhaul or replacement of
5-00-04 ELECTRIC POWER SYSTEM components should be a accomplished not later than
the specified period of operation for that component or
i. The master switch and power relay control the i,,ccordance with manufactures service data or
electrical power system, comprised of a 70 amp 14 Mit ,i,,rthiness directives.
altemator, voltage regulator, and a 12 volt, 35 AMP
a
HR battery (S/N 25-0001 thru 25-0999). Aircraft S/N The specified overhaul time limits, if applicable to a
25-1000 and ON have a 70 AMP, 28 volt altemator and component, do not constitute a guarantee that the
a 24 volt, 22 AMP HR battery). The altemator system component will reach that time limit without requiring
has an ovenroltage protective relay and an overvoltage maintenance.

5-00-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
NOTE
UON CONDITION" items are to be repaired, replaced or overhauled when inspection or performance
reveals an unserviceable condition.
610-01 -AIRWORTHINESS LIMITATIONS

´•IIEM RSCOM ME LIM ITS

I"

i
Ai~fhatar:NolBack Clutch Spn’ng.-iAvionics Products ~DODHours
PIessey Actuator;s)
:i: 13n Condition
ir

I.i´•~, ii -r~t’:...:ri.’ for specific

Bi~ndix. r
,;:II so~ihFS ´•0r;~
I.. i:i
4 years 1
i;
~Piiifi)tei-
:’I On Condition
i. Fi~gl :&..~I S3sterii:
’i.i~uei Selectbr’Vatve 500 I;tours
.’Ii7 years:Of;´•i~ which ever occurs first.
!:;6Ieici~le .-1 Condition
i

I~c;rbRuip801 Fuettldses-:(rfil~itel$d) _
’i i~ k;nanuls
."tl::; :´•:i´•.´• Cjii7 Conditidri:
InsfrulitentSi´• r:
~cuum aookou~
.i;
-:’~.:’j t’ 5~13t0 Hours~oF annually
.o~ Chndition
500 ~msor annually
i:´•:´•i CnfieFidampahenflj: On Condition
~ystem
I: :;~I’Components On Condition
Fli~ht Controls
On Condition
M~cellaneoGs Systems
Pirinp ’´•ii .Ii ~ifEilgine OIH
ii.
;´•i:i:.
´•ti.´•
;´•I .:i´• .i´•’ ,f-ii‘
:’;il/,:’ljiA1I ~Of her; On Condition
:14iCionics ´•ii:´•-
Pti~liwtlbns
´•.ii ..i:. ...i’i .ir- hji-,m~l:Na. 292

NOTE
Components should be
inspected and serviced at regular intervals perthe servicing, lubrication
and inspection chart of this manual.
The general points to be covered dun’ng inspection are
5-20-00 -SCHEDULED INSPECTIONS
grouped in accordance with the nature and function of
the items discussed.
Inspection Intervals. Perform 25, 50, or 100´•hourinspedions
of the aircraff, components and engine at recommeslded 1. Moving Parts shall be inspected and checked as
fnte~vals as outlined h the following paragraphs. applicable for: proper operation, security of attachment,
sealing, cleanliness, lubn’cation, servicing, safetying,
NOTE adjustment, tension, travel, condition of hinges, binding,
Aircraft operated in salt air environment are excessive wear, cracking, corrosion, deformation, and
considered high risk for corrosion damage, and a"Y Other apparent damage.
should be cleaned and inspected at more 2. Metal Parts shall be inspected and checked as
frequent intervals. Refer to AC43,4 applicable for: security of attachment, condition of finish
and sealant, distortion, fatigue cracks, welding cracks,
corrosion, and any other apparent damage.
5-20-01 INSPECTION CHECK POINTS
5-10-01
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
3. Fuel, air, oil andhydraulic oil lines and hoses shall Fuel, Hydraulic, Air, Oil Lines Use "Parker Thread
be inspected as applicable for: cracks, dents, kinks, Lube" or equivalent on male frttings only. Apply
deten’oration, obstruction, chaffing, Improper bend lubn’cant, omitting the first two threads, span’ngly and
radius, and insecure installation. Replace or correct if carefully.
any of these conditions e~dst. Hose clamp installations Engine Fittings Use only aircraft engine oil to
on fuel and hydraulic systems between systems or lubn~cate fittings threaded directly to engine.
between systems and the engine shall be torqued to 25
Vacuum Lines No lubrication is to be used. Check
inch pounds. Hose clamp installations on blast tubes,
manufacturers instructions when installing components.
air ducts, vacuum lines, drain and vent lines shall be
Refer to Section 37 for maintenance procedures on
torqued to 15 inch pounds. vacuum system.
4. Pipe Threads Tightening and torque procedures.
Lubric~ite pipe threads as follows: Tapered Threads Use TeRon Threadseal Tape.
Oxygen Lines Use only Mil-T-5542 thread (1) Continue to tighten until frtting is correctly
compound or Teflon thread seal tape on threads of positioned but do not overrun or backoff.
valves, connectors, fittings, parts or assemblies which (2) If leaks are detected, tighten one full turn more.
might come in contact with o~cygen. (3) If leaks pers~t, the parts should be disconnected
The thread compound must be applied sparingly to the and rejected; replace with new components.
first three threads of the mail fitting only. No compound 5. Bolts and nuts in critical areas shall be inspected
is to be used on the coupling sleeves or on the outside for: fretting, wear, damage, stretch, proper torque,
of the tube flares. Extreme care should be exercised to
(Figure 52) and safetying.
prevent the contamination of the thread compound or
teflon tape with oil, grease or other lubn’cant.

TORQUE TABLES
FLARE NUT TORQUE VALUES- Tighten to minimum torque value for appropn’ate size as shown (Figure 5-1).

FITTING
SIZE I ALUMINUM TUBING STEEL TUBING

TORQUE- IN. LBS.

MINIMUM MAXIMUM MINIMUM MAXIMUM

-3 30 70

-4 40 65 50 90

-5 60 80 70 120

-6 75 125 9 150

-8 150 250 155 250

-10 200 350 300 400

-12 300 500 30 575

-16 500 700 550 750

-20 600 900

-24 600 900

FLARE NUT TORQUE

FIGURE 51

5-20-01
8ERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

BOLT OLDWILLWAYNE
NUT TORQUE VALUES

METRO BOLTS, SCRR~IS 8 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 appropn’ate class is intended to provide an
assembly capable of being tightened to the bolt proof load without thread stn’pping occurring.
The torque value to be set for a particular size of screw is dependent upon:

1) Maten’al of the screw.

2) Parent material (steel, non-ferrous metal or plastic).
3) \I~hether the screw is untreated or plated.
4) V~hether the screw is dry or lubricated.
5) The depth of the thread.
TIGHTENING TORQUES Untreated Screw(Black Finish) Fiiction Coeficient 0.14

NOMINAL PROPERTY
DIAMETER CLASS

(Coarse Thread)
TORQUE Ma
5.6 8.8 10.9 12.9
Nm/ft.lb. Nm/ft.lb. Nmift.lb. Nm/ft.lb.

M3 0.60/0.44 1.37/1.01 1.92/1.42 230/1 .70

M4 1.37/1.01 3.10/2~29 4.40/3~25 5.25/3.87
M5 2.70/1.99 6.15/4.54 8.65/6.38 10.4/7.6
M6 4.6/3.3 10.5/7.7 15/11 18/13
M7 7.6/5.6 17.5M 2.9 25/1 8.4 29121 .3
M8 11/8.1 26/19 36/26 43/31
Mig 22/16 51/37 72/53 87164
M?2 39/28 89/65 125/92 150/110
M14 62/45 141/103 198/146 240/177
M?6 95/70 215/158 305~224 365/269
M18 130/95 295/217 420/309 500/368
M20 184/135 420/309 590/435 71 0/523
M22 250/1 84 570/420 800/590 960/708
M24 31 5/232 725/534 1020/752 1220/899
Mn 470/346 1070/789 1510/1113 1810/1334
M30 635/468 1450/1 069 2050/1 511 2450/1 806
M33 865/637 i 970/1 452 2770/2042 3330/2455
M36 1111/819 2530/1 855 3560/2625 4280/3156
M39 1440/1062 3290/2426 4620/3407 5550/4093

5-20-01
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
C TORQUE TABLES CONTI

NOMINAL
DIAMETER
ine Thread)
TORQUE Ma
10.9 12.9
8.8
Nm/ft.lb. Nm/ft.lb.
Nmlft.lb.

38/28 45/33
M8 x 1 27/19
73153 88164
M10 x 1.25 52/38
135/99 160/118
M12 x1.25 95/70
210/154 250/1 84
M14x1.5 150/110
315/232 380/280
M16x1.5 22511 65
460/339 550/405
M18x1.5 325/239
640/472 770/567
M20 x 1.5 460/339
860/634 1050/774
M22 x 1.5 610/419
1100/811 1300/958
M24 x 2 780/575
-1

3´•

TIGHTENING TORQUES Electrically Zinc Plated Friction Coeficient 0. 125

DIAMETER
(CoarseThread)
TORQUE Ma
8.8 10.9 12.9
5.6
Nm/ft.lb. NmPlb. Nmm.lb.
Nm/ft.lb.

1.28/0.94 1.80/1.33 2.15/1.59

M3 0.56/0.41
2.90/2.14 4.1 013.02 4.95/3.65’
M4 1.28/0.94
5.75/4.24 8.1 0/5.97 9.70/7.15
M5 2.50/1 .84
9.9/7.3 14/10.3 16.5/12.1
M6 4.3/3.1
16.5/1 2.1 2311 6.9 27/19.9
M7 7.115.2
2411 7.7 34/25 40/29
M8 10.5/7.7
48135 67/49 81/59
M10 21/15
83/61 117/86.2 140/103
M12 36/26
132/97 185/1 36 220/1 62
M14 58/42
200/1 47 285/210 340/250
M16 88/64
25/202 390/287 4701346
M18 121/89
3901287 550/405 660/486
M20 171/126
530/390 7451549 890/656
M22 230/169
295/217 675/497 960/708 1140\840
M24
995/733 1400/1 032 1680/1239
M27 435/320
1350/995 1900/1401 2280/1 681
M30 590/435
1830/1 349 258011 902 3090/2278
M33 800/590
2360/1 740 331 0/2441 3980/2935
M36 1030/759
3050/2249 4290/3163 5150/3798
M39 1340/988
i

5-20-01
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
METRIC TORQUE TABLES CONTINUED
NOMINAL PROPERTY
DIAMETER CLASS

TORQUE Ma
8.8 10.9 12.9
Nm/ft.lb. Nm/ft.lb. Nm/ft.lb.

M8 x 1 25/18 35/25 42/30

M10 x 1.25 49/36 68/50 82/60
M12 x 1.25 88/64 125/92 150/110
M14 x 1.25 140/103 195/143 235/173
M16 x 1.5 210/154 295/217 350/258
M18x1.5 305/224 425/313 510/376
M20 x 1.5 425/313 600/442 720/531
M22 x 1.5 570/420 800/590 960/708
M24 x 2 720/531 1000/737 1200/885

METRIC CONVERSION FACTOR: One Nm(Newton Meter) .7375 Foot Pound;

One Foot Pound 1.355818 Nm

CAUTION
These torque values are derived from oil-free cadmium-plated threads.

5-20-01
10
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE
AN/MS STANDARD BOLTS, NUTS TORQUE TABLES

Fine-Thread Series

Tension-type Shear-type TENSION-type SHE\R -type

NUT-BOLT AN()BOLTS AN()BOLTS NAS() BOLTS NAS() BOLTS
SIZE AN-365/AN 310 AN-364/AN320 AN-365/AN-310 AN-364/AN320
NUTS NUTS NUTS NUTS

8-36 12-15 7-9

10-32 20-25 12-15 25-30 15-20

1/4-28 50-70 30-40 80-100 50-60

5/16-24 100-140 60-85 120-1 45 70-90

3/8-24 160-190 95-110 200-250 120-150

7/16-20 450-500 270300 520-630 300-400

112-20 480-690 290-410 770-950 450550

9~1 6-18 800-1 000 480-600 1100-1300 650-800

5/8-18 1100-1300 600-780 1250-1550 750-950

3/4-16 2300-2500 1300-1500 2650-3200 1600-1 900

2500-3000 1500-1800 3550-4350 2100-2600
7/8-14
1-14 3700-5500 2200-3300 4500-5500 2700-3300

11/8-12 5000-7000 8000-4200 6000-7300 3600-4400

11/4-12 9000-11000 5400-6600 11000-13000 6600-8000

Coarse-Thread Series

8-32 12-15 7-9

10-24 20-25 12-15
1/4-20 40-50 2530
5/1 6-18 80-90 48-55
3/8-16 160-185 95-1 00
7/1 6-1 4 235-255 140-155
1/2-13 400-480 240-290
9~1 6-12 1500-700 300-420
5/8-11 700-900 420-540
3/4-10 1150-1600 700-950
7/8-9 2200-3000 1300-1 800

Figure 5-2

Reference: Federal Aviation Agency Advisory Circular No. 43.13-1% p. 118

Recommended Torque Values for Nut-Bolt combination (Units are inch-pounds)

1. Be sure nut and/or bolt threads are clean and dry(unless Mfg. states otherwise.
2. Run bolt down near contact with washer. or bearing surface and check’friction drag torque" required to tum

bolt/nut.
3. Measure torque required just before contact of bolt’s washer face to surface C’FRICTION DRAG
to turn bolt
TORQUE"). Add this "friction drag torque" to the recommended torque value from Figure 5-2. This value is con-
sklered "Final Torque Value".
(FRICTION DRAG TORQUE REC~MD TORQUE FINAL TORQUE VALUE).

CAUTION
DO NOT REUSE LOCKNUTS IF MN CAN BE RUN UP FINGER TIGHT.
5-20-01
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SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
5-20-01 -INSPECTION CHECK POINTS (con’t) 3. Check pitot and static systems for possible
obstructions.
B. Electn’cal wiring shall be checked as applicable
for: loose, corroded, or broken terminals; chaffed, 9´• Inspect aircraft e>der’or for security of bolts,
broken, or wom insulation; insecure installation; heat screws, etc.
deten’oration; and any other apparent damage. 1G. Check and service battery.
7. Filters and screens shall be removed, cleaned 5-20-05 -50-HOUR INSPECTION
and inspected for contamination or damage that would
require replacement. The 50-hour inspection includes all requirements for
the 25-hour inspection, plus the necessary removal of
5-2092 AIRCRAFT FILE INSPECTION inspection doors, panels, or fain’ngs. After the first 25
hours of ope~ating time, a new, remanufactured, or
Aircraft 1 GO-hour and annual inspections cover, in addition
newly overhauled engine should be given a 50-hour
to examining the aircraft proper, a review of the status of inspection including replacement of the lubricating oil.
compliance with current Federal Aviation Regulations. This
review includes inspection of the Airplane Fight Manual, 1. Engine.
Airc~aff Log Book, Engine Log Book Registration A. Drain oil sump.
engine
Certificate, Certificate, ~NeigM 3 Balance
B. Remove and clean suction oil strainer; reinstall
Record, TCM Service Information, Aircraft Radio Station
License Cd applicable), FAA AiMlorthiness Diredives, and strainer and plug. Safety wire strainer plug.
Mooney serivce documents. C. Remove and replace the full-flow oil filter cartridge.
5-20-03 ENGINE FUNCTIONAL CHECK D. Drain and clean fuel str~iner.

Prior to a scheduled 100-hour or annual inspection, E. Remove and clean fuel injector fuel strainer.
andlor 25 hours affer installation of new or overhauled F. Service engine oil sump with proper type, grade,
engine, wash down the engine and engine components. and amount of lubricati?g oil.
Then perform an engine Nnup in accord with procedure
G´• I"sped engine intake and exhaust systems for
recommended in the Airplane Flight Manual. Make a
evidence of leakage and looseness.
record of all malfunctions and abndrmalities. After the
engine runup complete a differential (hot engine) H. Check spark plug elbows and shielding nuts
compression Jleck. To verify corection of malfunctions for security.
and abnormalities, perform a second engine runup and a
I. Check cylinders for evidence of overheating.
flight test after completing the inspection.
J. Check turbocharger for security of clamps and
5-20-04 FIRST 25HOUR INSPECTION attachments.
The time 25-hour inspection consists of a visual
one K. Check baffles for secure anchorage, close fit
Inspection of the propeller, engine, and aircraft general around cylinders, and freedom from cracks.
condition, including a preflight inspection as outlined in L. Check engine controls for full travel, freedom of
the Airplane Flight Manual. The inspection does not
movement and security.
require removal of all access panels or disassembly of
components; however, it should include completion of M. Visually check fuel and oil lines for security of
all lubn’cation 3 service requirements. The inspection connections and evidence of leakage or damage.
should be e~densive enough to detect any damage or N. Visually inspect induction air system; check
maladjustment which might jeopardize flight safety. operation of altemate-air door (refer to paragraph
After the first 25 hours of new or overhauled engine
71-62-00).
operation refer to paragraph 5-20-05 for the
recomme;lded engine inspection. 2. Propeller.
A. Check propeller and spinner for general
1. Visually inspect propeller, spinner, and engine
cowling; open cowling. condition, looseness, and oil leakage.
2. Inspect and clean induction air filter if aircraft has
B. Inspect blades for nicks and cracks. Repair prior
tO "e>d flight.
been operating under dusty conditions. Check
operation of altemate air door. 3. Cabin.

3. Inspect engine compartment for evidence of fuel, A. Check brake and parking brake control systems
oil or exhaust leaks. for proper operation and fluid level.

4. Check security and condition of equipment B. Check tn’m system and indicator for free
installed on engine. operation and travel.

5. Inspect fuselage, wing and empennage for C. Check cabin and baggage doors for damage,
extemal evidence of damage. Pay particular attention proper operation, and sealing.
to scratches and dents. D. Check cabin, instrument, position, anticollision,
Inspect windshields and windows for
6. crazing, a"d landing lights.
cracks, and scratches. E. Check fuel selector valve, gascolator, and boost

7. Check control systems for binding, excessive pump for proper operation.
freeplay, and damage. F. Check oxygen system (if installed).
5-20-01
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MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
4. Landing Gear. E. Inspect fuel injector and all fuel line connections
for security and condition.
A. Inspect tires for cuts, blisters, wear, and
inflation. F. Remove, inspect and clean gascolator strainer,
reinstall strainer. Inspect fuel lines and connections:
B. Inspect shock discs for proper e>dension at
pressure check fuel system with mi~dure control at IDLE
aircraft static weight per Section 32-81-00. CUTOFF and BOOST PUMP ON.
C. Inspect hydraulic brakes for wear, warpage and air ducting and connections in the
G. Inspect all
proper installation. heating and induction air systems for leaks. Remove
5. Wings. and clean induction air filter (replace at 500 Hrs). Leak
check all exhaust manifold connections, engine
A. Inspect surfaces and tips for damage, exhaust manifolds and resonator connections (if
aileron attachments,
ailerons, and equipped). Inspect turbochalger housing per TCM SE
damage and proper operation.
for damage and H´• Inspect altemate air door and magnet for
C. Inspect flaps and attachments
proper operation. security and operation.
i. Check magnetos for grounding and
D. Lubncate controls if necessa~y.
synchronization; inspect magneto points for condition,
6. Fuselage and Empennage. cle~rance, and timing. Inspect distributor block for
and rudder for erosion and cracks. inspect cam follower felt for proper
A. Inspect stabilizer, elevators, fin,
damage and proper attachment, lubrication, and remove excessive oil from breaker
compartment. Inspect magneto pressurization. Repair
B. Lubn’cate controls if necessary, or replace components,if required, per Bendix SE No.

50 HOUF 612 500 hrs) and Slick SL 1-84.

7. See Section 5-20-07 for any repetitive
Inspections and/or Component Senn’ce Guide. J. Inspect baffles for secure anchorage, cracks,
holes, deformation, and for close fn around cylinders.
5-20-06 -´•100-HOURiNSPECTION (orANNUAL) Inspect cylinders for burned paint and cracked or

(Refer to Fig. 5-4) broken fins. Inspect baffle sealant.

The 100-hour (or annual) inspection is a thorough, K. Check engine and propeller controls for free
searching inspection of the entire aircraft. Preparation operation, proper lubrication, travel, proper
full
for the inspection includes the thorough cleaning of connection (security) of cable housing swage at head
aircraft exten’or and engine compartment, removal of tube and security of attachment.
fuselage, wing, and empennage inspection doors,
cover plates, and fain’ngs at all systems attach, hinge,
NOTE
and bean’ng locations (including wing and empennage Cablecraft control cables are lubricated for life
to fuselage mating points). Operating limit replacement of control cable. DO NOT remove seals or
and special testing of components is to be included at lubricate control cable.
this interval when applicable. Comply with applicable
L. Inspect tubular engine mount for cracks,
FAA Directives, AD Notes, and applicable Mooney and
Vendor mandatory Service Bulletins and Instructions. corrosion; inspect all bolts and rubber mounts for
Check for aircraft conformance to FAA Specification security and condition.
2A3. Recommended 100-hour and special inspection M. inspect battery cables, electrical win’ng, and
requirements are outlined in the following paragraphs. ignitionharness for condition, secure anchorage, loose
terminals, and bumed or chaffed insulation.
1. ENGINE INSPECTION. Prior to the inspection,
remove the engine cowling and propeller spinner. Wash N. Check engine fuel pump pressure. (See T.C.M.
do~nm the engine and engine compartment. Then perform Service info. and Section 71-00-50 for this procedure).
an engine runup In accord with the procedure O. inspect battery, battery box area, and vent system
recommended in the TCM Maintenance and Operators
for condition, corrosion. inspect Mast tube for obstruction.
Manual, Section VIII. To verify correction of ma~fundions Flush battery box and battery case with soda if necessary.
and abnormalaies, perform a second runup and fight test
after the 1GO-hour inspection engine set-up. P. Inspect accessory case, starter, altemator,

A. Complete a differential (hot engine) compression

standby generator (if installed) (SM 25-0001 thru
25-0999) or No. 2 altemator (25-1000 and ON ,if
check: clean and gap or rep)acespark plugs if necessary.
installed), vacuum pump, hose, firewall and frttings for
B. Inspect engine for evidence of excessive fuel or security or damage.
oil leakage. Inspect oil cooler. Inspect oil 3 fuel hoses Q. Inspect for condition per T~C.M. Service
for condition 3 security. Bulletin No.M833 orlaterinformation (Ref.AD 82-07-03).
C. Drain engine oil sump; remove, inspect, g dean R~ Inspect turi~charger control components for
oil suction screens; reinstall and safety. Remove
damage and condition.
full-flow oil filter cartridge; replace with new cartridge
and safety, inspect crank case breather lines for S.inspect intercooler for damage or obstrudions.
obstruction. Safety wire oil filter installation. T. inspect exhaust system for cracks, looseness
D. Refill engine oil sump with the proper type, and for evidence of leakage. Replace or repair
grade, and quantity of lubn’cating oil, damaged components.
5-20-06
13
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
been deformed by 20 degrees less may be
or
,110t-,010 straightened by using a rubber mallet and block
assun’ng that no waviness or other damage results from
the straightening process; inspect for cracks.
3 The chord length may be reduced for repair similar to
the procedure of a standard blade assun’ng that all
blades are the same so that the aerodynamic balance
j INCtl of the propeller will not be affected.
F. Check for loss of grease; lubricate per Mfgr’s. data.

I I G. Inspect anti-icing boots for security and defects.

H. Inspedspinnerand bulkhead for crad(s and condition.
I. inspect spinner bulkhead for corred interference fit
with prop cylinder. (Use Teffon Tape to obtain conect fit.)
3. LANDING GEAR and RETRACTION SYSTEM
INSPECTION.
A. Inspect tires for proper inflation, cuts, blisters,
slippage, and heavy wear.
B. Inspect wheels for cracks, distortion,
SMIK-5-3 misalignment, corrosion, bolt failure, inspect condition of
felt seals and bearings; repack bearings at 250 hour
P/P(CAL "Q" TIP BLADE- FIGURE 53 intervals.
C. Inspect brake pads 3 discs for warping and
U. Inspect exhaust stacks for bumed areas, cracks, wear. Ref. Section 32-40-04.
distortion and looseness.
D. Check hydraulic reservoir for proper fluid level.
V. Inspect exhaust couplings, seals, clamps and
slip-joints for cracks, deformation, leaks and secun’ty. E. Inspect hydraulic brake lines and hoses for
leakage, dents, cracks chafing, kinks, and security of
W. Inspect studs, nuts, bolts, etc. for damage and
anchorage.
proper torque.
F. Check parking bi~ake system for proper
X. Inspect and reinstall cowling. Check cowl flap(s)
engagement and release.
for operation condition, proper opening and position
indication (25-1000 thru 25-TEA). G. Inspect shock disc gap, Main and Nose gear,
pe’ section 32-81-00.
Y. Insped landing lights for security and condition.
Light beams down 2 degrees ma~a’mum from level. Jack aircraft as recommended in paragraph 7-10-00 for
the following inspections:
(SM 25-0001 thru 25-1224)
2. PROPELLER INSPECTION. H. Inspect nose gear for dearhes~ ~nd damage. i-sped
orbroicen ioli pins
A. Remove spinner (if not already removed).
NOTE
B. Inspect security of propeller installation. Maximum allowable towing damage on leg
C. Inspect hub bolts for security and damage, assembly is 1132 inch dent.
D. Inspect hub parts and blades for cracks and I. Inspect nose wheel steen’ng mechanism for
nicks. Repair prior to next flight,
adjustment, alignment, corrosion, and lubn’cation.
E. Q-tip blade inspection and repair. The tip of the J. inspect main gear for cleanliness or damage.
blade is formed at the factory with a bend of 90
degrees toward the blade face (aft). The material K. Inspect landing gear retraction linkage, bellc~anks,
thickness in the radius of bend is closely controlled pivots, and bean’ngs for wear, damage, distortion,
such that the cold bend allowance is not exceeded. A misalignment, corosion, cleanliness, and lubrication.
sketch of the "Q" tip is shown (Figure 5-3). L. Insped the landing gear aduator for searty of
INSPECTION: Inspect "Q-Tip" for stone nicks and mounting, deanliness, and bxlication of wemeathg or dar~ge.
scratches using the same procedure as on the Insped actuator motorope~atjon and brush wear.
complete blade.Inspect for evidence of the bend being M. Perform landing gear operational check per
assun’ng that the bend edge is 90
deformednt~Yo
degrees, inspect
Section 32-30-01.
4´• FUEL SYSTEM INSPECTION.
bend. REPAIR: Maten’al in the bend area (.110 plus or
minus .010) may be removed for repair of nicks and A. Inspect fuel tank for evidence of fuel
scratches to a minimum blade thickness of .065. seepage and stain.
Correspondingly, reduce the very tip region, when B. Drain tank and inspect tank inten’or when
required, to a minimum of.010 less than the resulting
thickness of the bend area. Tt~e bend may be reduced Seepage is evident
In length for repair from the one inch dimension to C. Inspect fuel tank drains for leakage, sediment,
approximately .75 inches. The 90 degree bend that has and water contamination.
5-20-06
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
D. Inspect fuel-tank vents for obstruction. 6. INTERIOR INSPECTION.

E. Check fuel selector valve for proper tank selection, A. Inspect seats, seat t~acks, and upholstery for
smooth operation, and leakage in OFF position. cleanliness and mounting security; check seats for
condition and operation of position locks; inspect seat
F. for leakage; check sump for
Inspect gascolator structure for c~acks, deformation, corrosion, and
sediment, water or other contamination. mechanism lubrication.
G. Inspect boost pump for leaks, security of B. inspect safety bets, harnesses, and att~fiing bad(ets for
mounting, adequate fuel pressure, switch operation, deanhess, operation, and securi~j dbdac~hment
and condition of wiring and electrical connections.
C. Inspect for loose equipment that might restn’ct
(1) Check eledn’e fuel boost pump for proper controlmovement.
operation by’T’ ing into the line with a calibrated fuel
D. Inspect Oxygen system ginstaCed3. Referto Chapeer35.
pressure gauge.
7- INTERNAL INsPECT1ON.
(a) High boost operation should result in a 23.5
to 24.5 P.S.I. reading (mixture full RICH, throttle-IDLE). A.Open access panels and inspection doors, and
(b) Low Boost pump pressure check 6-8 P.S.I.
’emove fain’ngs as required.
See Se~lon 24-37-00 for adjustment procedures. B. Inspect wing attaching bolts for proper~torque
and safetying and evidence of damage or corrosion.
H. Inspect fuel quantity gages and transmitters for
secun’ty of mounting and condition of win’ng and C. Inspect forward side of firewall for damage.
electrical connections. D. Inspect tubular structure for corrosion or

I. Inspect fuel tank filler port for cleanliness, cap damage (interior panels may require removal).
secun’ty, and condition of servicing placards. Inspect Reference Mooney Service Bulletin M20-2088 or
cap O’n’ngs for condition and replace if needed. subsequent revisions.
5. EXTERIOR INSPECTION. E. inspect wing n’bs and stringers for cracks and
evidence of damage or corrosion.
A. Thoroughly clean aircraft e>derior
F. hsped~ng spanrw~m;ge, cCsbrtig aacks, orcarosicn
B. Inspect fuselage exten’or surfaces for corrosion,
G. Inspect wires, lines, and ducts for security,
damage, loose or popped rivets, dents, cans,
scratches, cracks, and deten’orated paint. damage, interference, chaffing, and bonding.
and windows for cracks, NOTE
C. Inspect windshields
scratches, condition of seals, and security of Seal all receptacles and plugs outside cabin
crazing,
installation, environment with Dow Coming #4.

D. Inspect wings, flaps, and ailerons for corrosion, H. Inspect wing inten’or for foreign material,
damage, loose or popped rivets, dents, scratches, corrosion, and evidence of fuel leakage.
cracks, condition of attaching points, lubn’cation, i. Inspect empennage attachment brackets and
freedom of operation, free-play, travel, and balance hardware for corrosion.
weight attachment and
J. Inspect empennage attaching brackets
E. Inspect speedbrake cartridges for damage and hardware for corrosion.
wear. Check for proper operation. Every 1000 hour
8. FLIGHT CONTROL INSPECTION.
inspections see 27-96-02.
A. Inspect control column and control wheels for
F. Inspect empennage for corrosion, damage, loose
full travel, proper rigging, free-play, binding, security of
or popped rivets, ftee-playt dents, scratches, cracks,
condition and lubrication of hinge points, attachment of mounting, proper lubrication, and direction of control
surface movement with relation to control movement.
balance weights, and freedom of operation.
door and door frames for damage, CAUTION
G. Inspect cabin
corrosion, nicks, dents, hinge security, and lubn’cation. All flight control components should be
inspected to verify that all moisture drain holes
H. Inspect cabin door lock mechanism for are free of obstructions.
lubn’cation and proper engagement. See Section
52-11-00 for rigging procedures. 8. Inspect elevator system for rigging, travel, stop
I. Inspect the baggage baggage
door and adjustment, condition of bearings, bellcranks, and hinges,
wear on downspn‘ng eyes, cable pulley and frttings,
compartment for damage, corrosion, warpage, hinge Security of mounti~g, damage, corrosion, proper
secun’ty, condition to door frame and door seals, lubn’cation and proper relation to control movement.
condition and operation of door locking mechanism,
and condition of cargo tiedowns. C. Inspect aileron system for damage, corrosion,
drain line for
lubn’cation, rigging, travel, stop adjustment, condition of
J. Inspect ventilating system bellcranks 8 hinges, pivots and rod end bean’ngs, and
obstruction.
link bolt security.
K. Inspect landing and taxi lights for security, D. Inspect rudder system for damage, corrosion,
condition and proper adjustment. See Section 33-43-00
lubrication,rigging, condition of hinges, bellcranks,
for adjustment procedures,
security of link bolts, rod end bean’ngs, and proper
relationship to control movement. Check for free
5´•20-06
15
SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

OLDWILLWAYNE
movement of toe-brake pedals and proper rudder and freedom, and syncronization of barometric scale with
nose wheel travel. reference markers.

E. Inspect stabilizer tn’m control system for security G. inspect flight panel for security of mounting,
and proper adjustment, shaft and stop nuts for proper condition of shock mounts, freedom from interference
rigging, trim control wheel for smooth operation, with structure, and condition of ground straps.
universal joints for free-play and good working order, H. Inspect Avionics Euipment for proper operation
actuator threads for lubrication, linkage for corosion, g,,,urity.
and guide blocks for looseness or excessive wear.
I. Inspect Avionics Antennas, wiring 6 shielding for
F. Inspect flap system for rigging, travel, and stop obvious damage or defects.
adjustment; flap tubes, interconnects, bellcranks 8
J. inspect pitot head for port obstruction; Inspect lines
hinges for corrosion, security, and lubn‘cation.
for cracks, dents, kinks, proper bend radius, and security
NOTE of attachment. Drain system and check for leaks.
All control rigging checks should be made with
the aircraft jacked and leveled and with the
K. inspect static ports for obstruction and
landing gear retracted,
aerodynamic smoothness at port installations. Inspect
lines for bends, cracks, dents, kinks, and security of
NOTE
attachment. Drain system and check for leaks. Inspect
Some elevator trim tubes have poly tape
aitemate static pressure source located on left flight
wrapped at bulkhead penetrations. If tape pa"el.
shows signs of wear, rerap (1/2 lap) tube with
2" wide Y9265 polyurethane tape. Trim tubes, 10. ELECTRICAL FUNCTIONAL TEST.
vvithout tape, which show signs of abrading A. Check operation of navigation lights.
grommet should be wrapped. See SE M20-185.
B. Check operation of landing lights.
MAX. TUBE WEAR .007 in, per wall or .014 in.
C. Check operation of dome lights and cigar lighter.
diameter reduction.
D´• Check operation of anticollision lights.
Inspect Speedbrake Cartn~dge every 1000 hours per
the following: E. Check operation of instrument and placard
G. Remove Speedbrake Cartn’dge from access lights. Check meostat.
cover beneath LH 6 RH side ofwing. F. Check operation of pitot head heater.
1. Visually Inspect doubler and mounting G. Check operation of cluster gauge.
hardware for structrual integrity.
H. Check operation of fuel gauges.
2. Visually Inspect for chafing on all moving parts. I. Check operation of annunciator light press-to-test
3. Manually operatae speedbrake doors an feel switch.
forsmooth operation.
J. Check operation of ignition switch, and starter
4. Inspect cable ton Vacuum Units) expecially solenoid.
around pulleys for fraying.
K. Flight check operation of landing gear position
H. Report any deficjences Cdany) to Precise FliSM, Inc. lights and warning hem.
I. Relnstall Speedbrake Cartn’dges through access L. Flight check operation of stall warning hem.
panels in bottom of LH 8 RH side of wing. M. Check operation of "Prop De-ice" (if installed).
9. INSTRUMENT/ AVIONICS INSPECTION. Push switch "ON", observe prop de-ice ammeter for:
A. Inspect all instrument win’ng and plumbing for (1) needle in green are (8 to 12 amps), and (2)
condition and proper connections. fluctuation every 90 seconds as heating elements are
switched. (S/N 25-0001 thru 25-0999). Observe ship
B. Clean and inspect vacuum filter. Replace garter ammeter on S/N 251000 thru 25TBA for a flicker as
filter on vacuum regulator. each blade boot cycles.
C. inspect vacuum regulator at vacuum manifold. N. Inspect battery 8 battery connection for proper
Check ope~ation of high-and low-vacuum waming lights installation and cleanliness.
or vacuum gage.
11. MISCELLANEOUSIOPnONAL EQUIPMENT
D. Inspect all instruments for proper pointer
indication, range and limit markings, condition of A. Inspect any installed equipment not covered by
indicator markings, cracked or loose glass, slippage previous paragraphs for proper operation, attachment
marks, and security of installation. and obvious defects.

E. Inspect compass for proper lighting, 12. POST INSPECTION FUGHT TEST.. Flight test
compensation, security of mounting, liquid leakage, and the aircraft to ven’fy correction of all malfunctions and
discoloration. Swing compass at annual inspection and abnormalities. Make proper entn’es in aircraft log book.
after any new equipment has geen installed. Wingaccess covers may vaiy to some degree between
F. Inspect altimeter for scale error, discolored model year aircraft.
markings, proper pointer readings, setting knob Component locations remain basically unchanged.

5-20-06
16
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE

23 ~1 33

~1
o

a 5 6 8
2’ 7
4

10 18
OAT
13
17 10 12
11 10
12 32
16
11
32 13
14 14

o~I´• n0 o o

D
o
;30 O´•L~lq o
00
o o

27
27
19 24 19
24 27
27
14 14
15&16 31
16

25-0001 25-0780
o o

O
Oo e,

27 27

25-0781 TEA

(25-1000 THRU TEA)

20 r 21 r 22 r 22
27 7/ 1 28 I r 2

7’ Y 29
25 ’24 26 26 30
28

WING ACCESS COVERS MAY VARY TO SURE DEGREE BETWEEN MODEL YEAR
AIRCRAFT. COMPONENT LnCATIONS REMAIN BASICLLY UNCHANGU).
ACCESS COVER ID, LUBRICATION SERVICE GUIDE FIGURE 5 -4

NOTE
Access covers riveted in place during production need not be removed for routine inspections.

5-20-06
17
 SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

5-2097 OLDWILLWAYNE
ACCESS COVER IDENTIFICATION, LUBRICATION AND SERVICE GUIDE
ITEM ITEM DESCRIPTION LUBRICATION INTERVAL
NO, SYMBOL~ (HRS)
1 Fl$h; Ins;rumdts
Vacuum Regulator 500
Tum Coordinator
Vacuum Fiiters-RepIace at 500
Control Sytem Adjustments:
Control Column Bean’ng Ball yr 100
Rod End Bean’ngs ~1 100
Universal Joints C 100
Bellcranks C 100

2 Engine Cowling
Vacuum Pumps 503

3 Nose Gear Grease Frttings ST 100

Retraction Tube Rod End Bearings yr 100
Bellcranks C 100
Bungees C 100
Gear Door Rod End Beari~gs ~I 50

4 Main Gear Grease Fittings a 100

Retraction Tube Rod EndBearlngs yl 100
Bellcranks 100
Bungees Z 100
Gear Door Rod End Beanhgs W 50
Electn’c Gear Actuator Gear Box +/ST AWAR
Uectn’e Gear Actuator Ball Screw r 1000

5 Elevator Rudder Controls:

Control Tube Rod End Bearings ~y 100
Bellcranks C 100
AIP electric pftch carder bearing assembly 100

Battery
Stabilizer Tn’m Control Shaft:
Universal Joints 3 100
Guide Blocks 0 100
Hydraulic Reservoir B 50
Oxygen, High Pressure Fntings 0 50
ELT Transmitter 8 100

8 Elevator Rudder Controls:

Control Tube Rod End Bearings y, 100
Bellcranks C 100
Stabilizer Trim jack Screv;/Actuator Ems.’ 100
Van’able Downspn’ng System \y 100
Tail Strobe Light Power Supply
7 Empennage Attach Points 8 100
Stabilizer Tn’m Attach Point 8 100
8 Elevator 8 Rudder controls:
Control Tube Rod End Bean’ngs ~y 100
See last pabe of section for lubrication symbol legend.
No periodic lubn’cant on Avionics Products #102000´•2. If necessary to relubricate use Aeroshell 22, Mobil 28 or
MlL-G-81322 ONLY,
Change garter filter on vacuum regulator every 100 hours. Change instrument filters at 500 hours, clean every
100 hours,
Change instrument filters at 500 hours, clean every 100 hours.

5-20-07
 M20K SERVICE AND MAINTENANCE MANUAL
MOONF/ AIRCRAFT CORPORATION
OLDWILLWAYNE
LUBRICATION INTERVAL
ITEM ITEM DESCRIPTION
SYMBOLt (HRS)
NO.

9 Elevator Rudder Controls:

100
Control Tube Rod End Bearings tY

0 100
10 Aneron Control Tube Guide Blocks

11 Aleron Controls:
100
Control Tube Rod End Bearings ly
Z 100
Bellcranks

0 100
12 Aneron Control Tube Guide Blocks

P 100
13 Main Gear Retraction Beilcranks

100
14 Wing Points 100
Control Tube Guide Blocks O

100
15 Stabilizer Trim Screw Stops
Indicator Adjustment Point
0 100
Stabilizer Trim Chain Gear

16 Elevator Rudder Controls:

100
Control Tube Rod End Bean~ngs 9
Z 100
Bellcranks
O 100
Guide Blocks
Z 100
nap Indicator Cable 500
Electde Flap Actuator Gear Box n
r 100
Electric Flap Actuator Ball Screw

17 Electn’c Boost Pump

Z 50
Gascdator

18 Control Systems: 100

Control Tube Rod End Bean~ngs 9
Contml Yoke (Lower Seclion)
Nose Gear Steering Unk Rod End Bearings
C: 100
Rudder Pedal Cross Shaft
C 100
Rudderdileron Bungee
100
Hydraulic Brake Cylinder Pedal Unkage
100
19 Aileron Control Tube Rod End Bean’ngs 1V
Outboard Flap Stops 8

20 Baggage Compartment Door:

100
Z
Hinges 100
Latches
100
Seals X
100
Lock .V

21 Cabin Door: 100

Hinges 100
Latches L~
100
Seals X
100
Hold-Open Arm
100
Lock .V

22 Engine Instruments
Radios
5-20-07
19
 SERVICE AND MAINTENANCE MANUAL M20K IVIOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE

ITEM ITEM DESCRIPTION LUBRICATlON INTERVAL

NO. SYMBOL" (HRS)

23 Oil Dip Stick, Oil Filler Tube AR

24 Wheels Brakes:
Wheel Bean’ngs ’Y ~50
Brake Pressure Plates Anchor Bolts 1Y ~50
Guide Pins
Shock Discs 8 50

25 Elevator Rudder Control Stops 8

26 Nose Wheel:
Wheel Bean’ngs ~1 250
Shock Absorber (May be deleted from aircraft) 100
Shock Discs 8 50

27 Control Surface Hinges Z 100

28 Turbocharger Assy/Exhaust Assy B 100

29 Air Induction Filter 8 50

30 Cowi Flap Indicator Cable 8 100

31 Remote Compass Flux Valve

32 Strobdight Power Supply

33 ELT (Batteries) (28 Volt) 8 100

LUBRICATION SYMBOL LEGEND

SYMBOL MIL SPEC. NO. DESCRIPTION

I: I MlL-L-7870 Low Temperature Oil (6eneral Purpose)

nP MIL-G-81322 Grease
\ET ´•I MlL-L3545 Grease (High Temperature)
B I MlL-l-l-5636 Hydraulic Fluid (Red)
0 P Graphite MIL-G-3278 Grease or Mil-6-23827
V 31 Powdered Graphite
iy Teffon Spray CTRI-FLOW)
P Stick Lubricant (Door Ease or Equivalent)
5 P Aeroshell Grease NO. 7
(66 jackscrew and inside Actuator
Bearing Housing)
V I Lubn’plate 630AA (10% by Volume MdyWenum
Disuifide M’ccture PermissiMe)
X" Seal Dressing
BP Inspect
Tape, Tetrafluoroethylene
(M1L-T-27730) Permacei Tape Corp.,
New Brunswick, NJ
P TCM Spec. MHS-24()
M’ll-6-;382;, MO’BIL #27 Grease

5-20-07
20
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
VISCOSIN REQUIREMENTS:

TS1O360-GB, IB or -MB Sen’es Engines:

Above 300 F Ambient, S.L 50 WT

Below 500 F Ambient, S.L. 30 WT. or 10W30

TSIO-360SB Series Engines:

Above 400 F ambient, SL 50 or 20VIilj5

Below 400 F ambient, SL 30, 10W30, 15W50 or 20W50

Approved Oil:

Phillips Aviation Oil, Type A;

Aeroshell W; Conoco Aero S;

Texaco Aircraft Engine Oil Premium AD;

MobilAero Oil;
Castrol Aero AD Oil; Pennzoil Aircraft Engine Oil;
Sinclair Avoil;

Ejocon Aviation Oil EE; BP Aero Oil; Delta Avoil;

NOTE
Unlan Aircraft Engine Oil i-ID;
Mooney Aircraft are delivered with the proper
breakin oil; MIL-L-6032, MIL-C-6529C Type II or
Gulfpride Aviation AD; Quaker State AD Aviation SAE 20Wb0 Type I. This oil should be changed,
after 25 hours after oil consumption has
Engine Oil. or
stabilized, to oil conforming to
’TCM Spec MHS-24(B or subsequent revision.

Mu(tiviscosity Oils:
For aircraft SIN 25-1000 ON Mooney
WC Aviation Multiviscosity Oil SAE 20W-50; Aircraft Corporation recommends using
Red Ram X/C.Aviation 20W- 50; multiviscosity oil in these aircraft, both mineral
Aeroshell Oil WSAE 15W/50. additive oil.

5-20-07
 SERVICE AND MAINTENANCE MANUAL M20K MOONN AIRCRAFT CORPORATION

OLDWILLWAYNE

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5-20-07
22
 OLDWILLWAYNE

CHAPTER

DIMENSIONS
AND AREAS
SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTERG

DIMENSIONS AND AREAS

LIST OF EFFECTIVE PAGES

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3 9-97
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4 9-97
6-00-01
5. 9-97
6-00-01
6´• 9-97
6-00-01
7´• 9’97
6-00-01
8´• 9’97
6-00-02

TABLE OF CONTENTS
CHAPTER
SECTION
SUBJECT PAGE
SUBJECT

DimensionsandAreas 3
6-00-00
AircraffSpecifications 3
6-00-01
Aircraff Dimensions 8
6-00-02
Aircraff Stations 8
6-00-03

6-EFWCONTENTS
1/26 LANK
MOONN AIRCdAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE

6-0040 -DIMENSIONSAND AREAS 6-00-01 AIRCRAFT SPECIFICAT(ONS

STANDARD METRICIOPTIMISC.
ENGINE

Engine Manufacturer Teledyne Continental Motors (TCM)

TSIO-360-GB(1), -GB(3), -GB(4) 25-0001 thru 25´•0780
Engine Model 250781 thru 25-0999
TSIO´•360-LB(1)
TSIO-360-MB1 25-1000 thru 251999
TSIO´•360-MB7 25-2000 thru 252012
TSIO-360-SB 25-2013 thru 25TBA’

Horse power
TSIO-360-GB, LB, MB Sen’es 210 HP
TSIO-360-SB Series 220 HP
RPM
-GB, -LB, -MB Sen’es 2700
-SB Sen’es 2600

-MB7 engines may be retrofitted into -SB configuration when ciw Mooney Retrofit Kit is accomplished.

Min. Fuel Octane 1000r100LL.

Fuel Capacity
80 U.S. Gal. 302.8 Liters
Total
Useable 72 U.S. Gal. 264.5 Liters

SM 25-0447 and ON have total fuel of78.6 U.S. Gals. (297.5 Liters) and useable of 75.6 U.S. Gals. (286.1 Liters).

Oil Specification MHS-24(B) or later revision

Oil Grade (Vicosity)

SAESOW,
Below 500F. SAE 30 Wor 20W-50.
All temperatures ....´•15W-50

50 or 50W 65
Below 400F. 30, 10W 30, 15W50 or 20W50
Oil Capacity 8 qts. 7.57 Liters
Minimum Safe OiiLevel 5 qts. 4.73 Liters
Oil Consumption LiterslBHPlhr
Up to 75% Power .0032
Above 75% Power .0048
m
First 25 hours of operation mineral (non-detergent) oil or equivalent corresponding to MIL-C6529 Type II.

Maximum Operational Induction

Air Temperature 2800 F. 1380 C.
Continous Operation
Turbine Inlet Temperature 16500 F. 8990 C.
Operational Umit Turbine Inlet Temperature
zGB, -LB) (25-0001 thru 25-0999) 17250 F. 941" C
17000 F. 9270 C
-MB) (25-1000 thru 25-2012)
16500 F 9000 C
-SB) (25-2013 thru 25- TEA)
Oil Pressure
Normal Operation (-GB,-LB,-MB,-SB) 30-80 P.S.I. 25´•0001 thruZ5TBA
Idle, Minimum- 10 P.S.I.
Max. Allowable (cold Gro;nd’Run
bill 100 P.S.I.

Oil Temperature Max. Allowable 2400 F 1160C.

Recommended Takeoff- Min i=:(abo;e 4b~ F. Ojs~T) j356
C.
.Cevoba(~elow 50 C.
4:1C

1500 F.(below400 F. OAT)

Recon;me;ldeci night dperation Cruise 160 l~oO F. 71.1 82:20 C.
Recommended Operating Range 1000- 2000 F 37.8- 93.30 C.

6-00-00
SERVICE AND MAINTENANCE MANUAL M20K MOONC( AIRCRAFT CORPORATION

OLDWILLWAYNE
STANDARD METRICIOPTIMISC
ENGINE (con’t.)

Cylinder Head Temperature (CHT) 237.80 C.

Max Allowable 4600 F.
Recommended Cruise 360 4400 F. 182.2 226.70 C.
Recommended MAX., Operational 4200F 215~C
Minimum T/O 8 Descent 2400F 1160C

Turbocharger
Roto-Master 25-0001 thru 25-0999
Turbocharger Mfg.
Garl-ett-Airesearch 25-1000&ON
Tyi~e Exhaust Driven
Turbo Charger Model ’L-B)’ TCM 640955 Roto-Master
Garrett-Airesearch
Turbo Charger Model (-MB) TCM 649151-1
TEA0411 Garrett-Airesearch
Turbo Charger Model (-SB)
TCM 641404-1 "GB" Engines
Overboost Valve
ICM 643511-3 "LB" Engines
TCM 649006-5 "MB" Engines
"SB" Engines
Adsol;te Firess. delie’r Valve’ TCCM64351i-3 "MB" Engines
"SB" Engines

Variable Absolute Press. Controller TCM640655´•28 Used with Airesearch

Turbocharger
oneraiional P;ess’ure’Raiio

PROPELLER (25-0001 thru 25-1999)

McCauley Harhell Q-Tip (Optional)
Propeller Mfg.
Speed
Constant Constant Speed
.(2600i~l ti~Rli5d991j) 2A34C216190DH&18E BHCJ2YF-1BFIFSa59A-.110
(25-1000 thN 25-2012)+ 2A34C~1/90DHC-16E or-1GEP (250001 thN 25-2012)*
Pitch Angle O-1IGH)
33.0 (+/-).5 Deg. 30 Deg to 32 Deg
(25-0001 thru 25-0999)
38.0 (+/-).5 Deg. 36.5 1 Deg
(25-1000 thru 25-2012)* 14.7 Deg ~-).1 Deg
Pitch Angle (LOW) 1 4.7 (+/-).2 Deg.
Diameter 74.0 Inches 73.01nches
Governor McCauley McCauley

PROPELLER -(25-2000 thru 25-TEA)

Propeller Mfg. McCauley
Type ConstantSpeed
Model 2A34C221/S0DHC-16E or-1GEP
Pitch Angle (HIGH)
(25-2000 --25-2012) 33.0 (+/-).5 Deg.
l~s-zo13 fhru 25-TEA) 38.0 (+/-).5 Deg.
Pitch Angle (LOW) 14.7 (+/-).2 Deg.
Diameter 74.0 Inches
Govemor McCauley

-MB7 engines may be retrofitted into -SB configuration when Mooney Retrofit Kit is complied with.

800-01
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
AIRFRAME STANDARD METRICIOPTIMISC

WEIGHTS LOADINGS:
A. Approximate Empty Weight
2000 Ib. 907 kg.
(25-0001 thru 251999)
~5-2000 thru 25-2012) 2000 Ib. 907 kg.’
(25-2013 thru 25-TEA) 2059 Ib. 934 kg.

B. Gross Weight
2900 Ib. 1315 kg.
(25-0001 thru 25-1999)
2900 Ib. 1315
(25-2000 thru 25-2012)
3130 Ib. 1420
(25-2013 thru 25-TEA)
C.Usefulload
900 Ib. 408 kg.
(25-0001 thru 25-1999)
1071 Ib. 486 kg.
(25-2000 thru 25-TEA)’
D. Wing Loading
(25-0001 thru 25-1999) 16.59 IbJP2 80.98
16.59 IbJft: 80.98
ti5-2000 thru 25-2012)
17.91 IbJft~’ 87.44
(25-2013 thru 25-TEA)’
E.PowerLoading
13.8 Ib/hp 6.3 kg/hp
(25-0001 thru 25-1999)
13.8 Ib/hp’ 6.3 kglhp
(25-2000 thru 25-2012)
14.2 Ib/hp 6.45 kg/hp’
(25-2013 thru 25-TEA)’

25-2000 thru 25-2012 may have Gross Weight increased when compliance with Mooney Gross Weight Retrofit Kit
is accomplished.

WINGS:
A. Airfoil At Wing Root 632215
B. Airfoil At Wing Tip 641412
C. Mean Aerodynamic Chord
At Wing Sta.94.848 61 inches 154.94 cm
D. Center-of-Gravity Range 43.5 to 49.3 in. 110.5 to 125.2 cm
E. Geometric Twist @EG) 1.5 Degree
F=. Incidence Angle @EG)
From Sta 20. to Wing Tip 2.5 Degree
G. Dihedral angle (DEG) 5.5 Degree
H. Aspect Ratio 7.448
I. Taper Ratio (CS/CT) 2.271
FUSELAGE:
A. Cabin Dimensions:
44.5" 113.03 cm
(1) Height
43.5" 110.49 cm
(2) Width
114" 289.56 cm
(3) Length
Cabin Door Width 29" 73.66 cm
I~ Cabin Door Height 35" 88.9 cm
B. Baggage Campartment:
120 Ibs 54.4 kg
(1) MAX.Loading
17.0 Cu.Ft.(25-0001 thru 25-1224) 0.476 Cu. M.
(2) Baggage Space
15.3 Cu.Ft.(25-1225 thru 25-iBA) 0.433 Cu. M
17" 43.2 cm
Baggage Door Width
20.5" 52.1 cm
Baggage DoorHeight
Hat Rack Capacity 10 Ibs 4.5 kg
(5)
C. Landing Gear:
(1) Type Tricycle Retractable
Operation Electrical
Wheel Track 9’ 2" 279.4 cm
5’11 9/16" 181.73 cm
(4) Wheel Base
(5) Tire Size--Nose (6-Ply Rating) 5.00~c5
(6) Tire Size-Main (6-PIy Rating) 6.00~6
O Tire Pressure--Nose 49 Ibs/sq. in.
(8) Tire Pressure--Main 42 Ibs/sq. in.
6-00-01
 SERVICE AND MAINTENANCE MANUAL M20K MOONEV AIRCRAFT CORPORATION
OLDWILLWAYNE
25’ 5’

I- (774.7cm)

Tn i~T\f
74’ _71 8’ 4’
7 ~5\ <254cm>

11’U -1 (181.73cn)
I-

(27.9 cm) I

11’ 9’ (358~1cm>

S/N 25-1225 thru 25-TEA

have landingltaxi lights in
k--
9’ 3/4’ ---c’

<276.2cm>
wings.

DIMENSIONS FIGURE 6 I

6-00-03
MOONN AIRCRAFT CORPORATION MZOK SERVICE AND IUAINTENANCE AIANUAL

OLDWILLWAYNE
6-00-03 AIRCRAFT STATIONS

STA STA STA STA STA

210,97 147,75 103,50 59.25 24,50
STA
193,50

WING STATIDN RIBS

STA
S/N 25-1000 thru 25-TEA
-51375
WING STATIONS FIGURE 6 -2

STA
3,68

r 1
r 1
I j

STA STA STA STA STA STA STA

~99,50 164,00 130,00 88,00 53,00 21,80 -5,00

FUSELAGE STATIDNS
SMK-6-3
FUSELAGE STATIONS FIGURE 6 -3

NOTE
The datum line station 0.0 is 5 inches ah of the nose gear tfllnnion pivot point. (Reference

6-00-03
 M20K MOONF/AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL

6-00-02 AIRCRAFT DIMENSIONS OLDWILLWAYNE

DIMENSIONS:
36’1" 10.998 meters
A. Span
25’5" 7.747 metew
B. Fuselage Length
8’4" 2.54 meters
C. Tail Height
11’9" 3.581 meters
D. Stabilizer Span

AREAS:
174.786 sq. ft. 16.24 sq. meters
\Mng
11.4 so. ft. 1.06 so. meters
B. Ailerons
17.9 so. fl. 1.66 so. meters
C. Flaps
7.8 so. ft. 0.73 so. meters
D. Vertical Fin
625 se. ft. 0.52 so. meters
E. Rudder
21.42 so. ft. 1.90 so. meters
I=. Horizontal Stabilizer
180sq.ft. 1.21 so. meters
G. Elevators
6-00-03 AIRCRAFT STATIONS
NOTE
The datum line station 0.0 is 5 inches aft of the nose geartrunnion pivot point (Reference Figure 8-2.)

STA STA STA STA STA

67,75 42,25 4,43 4~,25 70.0

STA
52150

STA
25.75

STA
5,25

EMPENNAGE STATIDNS
SMK6-4

EMPENAGE STATIONS FIGURE 6 4

600-02
 OLDWILLWAYNE
CHAPTER

LIFTING AND
SHORING
 M20K MOONC/ AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE
CHAPTER 7

LIFTING AND SHORING

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SECTION
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SUBJECT

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7-1 0-00 Jacking

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 M20K SERVICE AND MAlNTENANCE MANUAL
MOONC/ AIRCRAFT CORPORATION

710-00 JACKING OLDWILLWAYNE

5. Secure safety locks on each jack.
V\ihen it is necessary to raise the aircraft off the
CAUTION
ground: When lowering aircraft on jacks, bleed off
and evenly
CAUTION pressure on all jacks simultaneously
Do not raise the aircraff on jacks out of doors to keep aircraft level as it is lowered.
when wind velocity is over ~O MPH. Jacks
should be on hard surface. CAUT1ON
Individual wheels may be raised without raising
CAUTION
the entire aircraff Wheels not being raised
Do not place jack directly on propeller de-icing should be checked fore and aff.
boots. Cushion with a layer of 3/8 inch thick
hard rubber or equivalent. NOTE
It is not recommended to use tail-tie do~Yn
i. Install jack points in tiedown mounting holes
fitting dun’ng jacking process to lift nose wheel
outboard of each main gear.
off ground.
2. Use standard aircraft jacks at both wing hoist
points (wing tiedown eyebolt receptacles) outboard of CAUTION
the main gears. V~ile holding jack point in place, raise
point.
contact jack Do not leave aircraft on jack for extended
jack to firmly
3. Use a yoke-frame jack under propeller to lift the pen’ods of time with a tailstand in place. The
nose, wing jack(s) may bleed down and place
4. Raise aircraft, keeping wings as nearly level as excessive loads on the front jack point and
tailcone.
possible.

7-10-00
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OLDWILLWAYNE

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i -10-00
 OLDWILLWAYNE

C H A PT E R

LEVELING AND
VVEIGHING
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OLDWILLWAYNE
CHAPTER 8

LEVELING AND WEIGHING

LIST OF EFFECTIVE PAGES

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8-00-00 Leveling 3

8-00-01 Weightand Balance 3

8-EFF/CONTENTS
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 M20K SERYICE AND MAINTENANCE MANUAL
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OLDWILLWAYNE
NOTE
8-00-00 -LEVELING
See Pilot’s Operating Handbook for Weight and
Place a spirit level on the skin splice or leveling screws Balance reference data.
the
above the tailcone access door when leveling
Level the aircraft by increasing or 3. Ground aircraft and drain fuel tanks per
Section
aircraft longitudinally,
air in the nose wheel tire. Front 12-10-02, 2.
decreasing pressure
seats must be in the full forward position when weigh- 4~ Add unusable fuel to each tank, (see applicable
ing, (Use skinsplice S/N 25-0002 thru 25-0246 and Pilot’s Operating Handbook for aircraft being serviced
leveling screws S/N 25-0001, 25-0247 8( ON.) for proper quantity of unusable fuel),
(See Figure 8-2.) 5. Fill oil to capacity (8 quarts).
6. Position a 2000-pound capacity scale under each
8-00-01 WEIGHT AND BALANCE
of the three wheels.
the aircraft select level and draft free work and
To weigh a
7. Level aircraft as described in Section 8-00-00
area, then: center nose wheel.
equipment listed in
1. Check for Installation of all as
8~ Weigh the aircraft.
the Weight and Balance Record. 9. Find reference point by dropping a plumb-bob
2. Charlie Weight Installation. The aircraft as from center of nose gear trunion (retracting pivot axis)
delivered from the factory has the correct ballast added to the floor. Mark the point of intersection.
addi-
(if any) to compensate for installed equipment. If r0. Locate centerline of the main wheel axles
in the
future time affect the
tion or deletion of equipment at a
same manner.
weight and balance of the aircraft sufficiently to require 11. Measure the horizontal distance from
the refer-
ballast the proper Charlie Weight Installation shown ence point to main wheel axle center line, Measure
(Figure 8-1) is to be used. horizontal distance from center line of nose wheel axle
to center line of main wheel axles.

501
i i

503
s/

~o.o’ ~c.o’
C.O. LOCI~10* LYITI
~t.o’
~o

Chart A n

EXAMPIE: ALrp~ae EmFty~ Weighs 18451 ´•rfth C,G, at 11.55’

IromChut, th~ zlrpkDe repldns -501 Chulle Weight IIletJlation,
For Ilocnce alcukte rue wr.,C,C, at Momtd,

Airplane as Weighed 1WS l1,55

-501 charlie Weight +1

Ileenud EmI~I WLtght 18511 17w5

505 /Mg
Ltcenccd Em~y Weight C,C, Location 1 12;06"

CHARLIE WEIGHT INSTAUATION FIGURE 8 1

8-00-00
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
12. Record weights and measurements and compute the basic weight and CG as follows:

LC/G LM/R-5 -LM

a. CG Forward of Main Wheels

LBS X IN. s LBS. IN.

Weight Nose Distance Between Total Weight of CG Forward of
Main 8 Nose Wheel Aircraft Main Wheels
Axel Centers
OYN) (LMIN) D~VT) (LM)

b. CG Aft of Datum (Station O)

IN. 5 IN. IN. IN.

Distance from center Distance from Result of computation CG (FUS STA)
Nose Gear Trunnion to Nose Gear Above (a.) Distance Aft of
Center of Main Wheel Trunnion to Datum (Empty
Axles (Horizontal) Datum Weight CG)
(LMIR) (CONSTANT) (LM) (LC/G)
NOTE:
Empty weight includes unusable fuel and full oil (8 Qts.) and is computed with gear down and flaps up.

REF.POINT REFERENCE LEVEL REF.

(NOSE GEAR DANH<STA~O) (LEVEUNG SCRRJS>
TRUNNICIN
STA, -5)

1 1
I 1

M20K

_I I MEASUREMENTS
r
Lm/n
Wn Wr LM/R INCHES/CM
WI

LM/N INCHES/CM

WEIGHT AND BALANCE DIAGRAM FIGURE 8 2

8-00-01
 OLDWILLWAYNE

CHAPTER

TOVVING AND
TAXIING
SERVICE AND MANINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTERS

TOWING AND TAXIING

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CHAPTER
SECTION
SUBJECT

3
9-00-00 Ground Handling
3
9-10-00 Towing
3
9-20-00 T~ua’ing
3
9-30-00 Emergency Procedures

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OLDWILLWAYNE
9-00-00 GROUND HANDUNG 4. Check operation of gyro instruments and turn
coordinator dun’ng turns.
9-10-00 -TOWING
5. Check engine instruments for sluggish response
Use a towbar for moving the aircraft.The towbar at- to engine control movements.
taches to the nose gear crossbar.One man can move
the aircraft providing the ground surface is relatively 9-30-00 EMERGENCY PROCEDURES
smooth and the tires are properly inRated.When no
1. Engine Fire During Starting.
towbar is available, or when assistance in moving the
A. Continue cranking engine with starter.
aircraft is required, push by hand:(l) on the wing lead- B. Set mixture control at IDLE, CUTOFF.
ing edges, (2) on the wing tips, and (3) on the inboard C. Turn fuel selector handle to OFF.
portion of propeller blades adjacent to the propeller D. Open throttle to FULL
hub.Towing by tractor or other powered equipment is E. Turn Master switch OFF
NOT RECOMMENDED.
F. Push cabin heat control to OFF.
CAUTION G. Close cowl Rap/(s).
Exercise care not to turn the nose wheel past its H. If fire is not extinguished, proceed as follows:
normal swivel angle of 14 degrees either side of (1) Tum electrical switches OFF.
center.Exceeding the turn limits shown on the turn (2) Discharge fire extinguisher into engine
indicator may cause structural damage.Maximum compartment through nose cow) openings and through
allowable damage to nose gear leg assembly is cowl Rap opening/(s).
1/32 inch dent. (3) Call for fire-fighting equipment.
2. Fuselage or Wheel Well Fire.ln case of fire in
9-20-00 WARMUP AND TAXIING wheel well (or in the cabin or fuselage area), turn all
Before attempting to warmup or taxi the aircraft, fuel, electrical, and ignition controls to the OFF position
ground personnel should be checked out by qualified before evacuating the aircraft to extinguish the flames.
pilots or other responsible personnel. 3. Electrical Fire.Circuit breakers (or circuit-breaker
1. Start and warmup engine.(Refer to AFM/POH switches), that automatically interrupt the Row of power
Manual.) when an overload or short circuit occurs, protect all
2. Taxi forward a few feet and check brake effective- electrical circuits (except the ignition-starter circuits).ln
ness, the event of an electrical fire, immediately turn off the
3. While taxiing, make shallow tums to test nose master/alternator field switch.hnake sure that only a fire

gear steering, extinguisher approved for electrical fires is used.

9-00-00
SERVICE AND MANINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

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BLANK

9-30´•00
 CHAPTER
OLDWILLWAYNE

PARKING,
MOORING,
STO RAG E,
RTN TO SVC.
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 10

PARKING AND MOORING

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....´•´•´•´•´•4´• 9-97
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SECTION
SUBJECT

General 3
10-00-00
3
10-10-00 Parking
3
10-10-01 Storage (Flyable)
Storage(Prolonged) 3
10-10-02
Return to SeM’ce 3
10-10-03
3
i 0-20-00 Moon’ng

?O-EFWCONTENTS
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 M20K SERVICE AND MAINTENANCE MANUAL
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OLDWILLWAYNE store in a cool

-GENERAL 3. Remove battery, charge fully, and
10-00-00
brakes and
place.
from the tires, and
The parking brakes are set by applying the A Raise aircraft to remove weight
out the parking brake knob. Release the block up the wheels.
pulling on
brake control
brakes by pushing in on the parking
CAUTION
knob. wheels
If weight is not removed from tires, rotate
NOTE to a new position at least once
each 30 days to
There is no need to depress the brake pedals
to
prevent flat-spotting the tires.
in the lines during release of
relieve the pressure
brake control. 5. See appropriate TCM Service Bulletin for engine
parking if preservation
preservation. Attach warning placards
There are three tiedown points on the aircraft,
one on procedures make engine inoperable.
n’ngs are to
each wing outboard of main gear (tiedown 10-10-03 RETURNING TO SERVICE
into built in receptacles) and the tail
be threaded extended period of
If the aircraft has been stored for an
skid/tiedown fitting on the aft end of the tailcone. 50-hour periodic in-
time, it is advisable to perform a

10-10-00 -PARKING spection after completion of the following preliminary

fore and
When parking the aircraft, place wheel chocks steps:
wheels.Check tire inflation.
brakes may be 1~ Remove blocks from
aft of the main wheels. The parking
2. Check and install battery.
used for short-duration parking.
3. Remove tape and covers from openings.
CAUTION 4. Remove warning placards (if any).
Do not set brakes when they are
parking 5. Replace engine oil filter.
overheated or when cold weather could freeze 6. Clean engine oil suction and pressure screens.
in the brake valve.
moisture and slush accumulation 7. Clean and check oil pressure relief
mechanism,Do not set parking brakes when 8. Clean and check oil temperature bypass valve.
aircraft is tied down. For maximum protection, 9. Fill engine sump with proper grade of lubricating
and high
hangar the aircraft during severe .sdniwrehtaew Oi1.10. Clean and reinstall engine air-inlet filter.

11. Check ignition harness.

lo-lo-ol STORAGE (FLYABLE) 12. Clean and regap spark plugs.
noules and
and 13. Check and clean fuel injector
Outdoor storage requires adequate mooring
tiedown fac[litles. The following precautionary screens.Drain oil from fuel injector.
and drain
the aircraft 14. Check fuel tank vents for obstruction,
measures are recommended for keeping
sumps to remove moisture and sediment.
serviceable and ready-to-fly.
1. Refer to paragraph 10-20-00 for moon’ng instruc- 15. Complete 50-hour and preflight inspections.
servic-
tions. 16. See appropriate TCM Service Bulletin for
2. Magneto switches..........0fF ing of the engine.
3. Throttle...............CLOSED 10-20-00 -MOOR1NG
4, Mixture...........lDLE CUTOFF
When mooring the aircraft out of doors:
5. Rotate propeller 6 revolutions every seven days;
1´• Head aircraft into the wind.
STOP propeller 45 to 90 degrees from original position. main wheel.
2´• Place chocks fore and aft of each
6. Keep fuel tanks filled at least one-half full to mini- three feet
fully 3. Drive stakes in ground approximately
mite moisture condensation. Keep battery and to either side of
outboard of each main gear
charged. tailskid.
protective covers over pitot head, engine
7. Install
4~ Install ti~down rings in wing receptacles
outboard
cowl openings, static ports, etc. tensile strength
surfaces of each main gear.Tie a 600-pound
8. Maintain a good wax finish on all exterior tiedown ring and anchor to ground
rope to each wing
after 90 days, stake.Allow a little slack in each tiedown rope.
10-10-02 STORAGE (PROLONGED) 5. Tie the center of a rope to tail skid tiedown ring
of and anchor rope ends to ground stakes at either side
If the aircraft is to be stored for an extended period
recommended for protec- of tail.
time, the following steps are to the nose
6. For additional security, attach a rope
tron: stake.
1. Refer to paragraph 10-20-00 for mooring
instruc- gear and anchor to a ground
front seat safety
7. Lock controls by looping right
tions. wheel and drawing belt snug.
belt through the control
2. Tape or cover all openings.

10-00-00
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BLANK

10-20-00
 CHAPTER
OLDWILLWAYNE

PLACARDS AND
MAR KI NGS
SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

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CHAPTER 11

PLACARDS AND MARKINGS

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SUBJECT

General 3
11-00-00
........´•Markings 3
11-10-00
11-20/30-00 .......´•Placards, f~cterior/lnterior .....´•´•´•3

11-EFFICONTENTS
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MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
-GENERAL 11-10-00 -MARKINGS
11-00-00

FAA required placards and markings. The exten’or paint schemes for the various model year
aircraft are depicted in the M20K Illustrated Parts
NOTE Catalog.
All placards should be inspected for proper 11-20/30-00 PLACARDS, EXTERIOR/INTERIOR
location, readability and security during and their locations, both interior
maintenance actions. When an airplane has been
All required placards
and exterior, are listed in Section II of the FAA Ap-
painted inspect all placards to assure that they are
not obscured by paint. proved Flight Manual and Pilot’s Operating Handbook,

11-00-00
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OLDWILLWAYNE

BLANK

11-20130-00
C H A PT E R
OLDWILLWAYNE

SERVICING
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 12

SERVICING

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4. 9-97
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5. 9-97
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TABLE OF CONTENTS

SUBJECT PAGE
CHAPTER
SECTION
SUBJECT

12-00-00 Servicing .....´•´•´•´•´•´•´•3

3
12-00-01 SeM~cing Intervals
3
12-10-00 Replenishing
FuelTanks 3
12-10-01
Fuel Drains 3
12-10-02
Engine Oil 3
12-10-03
4
12-10-04 Oxygen System
Scheduled Senricing 4
12-20-00
Indudion Air Filter 4
i 2-20-01
4
12-20-02 Battery
Tires Wheels 5
i 2-20-03
Brake Reservoir 5
12-20-04
5
12-20-05 Hydraulic Brake
Cleaning 5
12-20-06

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12-00-00 -SERVICING NOTE
If conditions conducive to fuel system icing
12-00-01 -SERVICING INTERVALS exist isopropyl Alcohol may be added to fuel
tanks (refer to TCM S.B. M30-17). h is extremely
The specified intervals (refer to Chapter 5) are
important to thoroughly BLEND the isopropyl
considered adequate to meet average requirements alcohol in with the fuel supply in quantities not
under normal operating conditions. It is advisable, to exceed 3% of the total by volume.
however, to shorten service and maintenance intervals
when operating under abnormal environmental 2. Defueling. Fuel tanks may be drained by pumping
conditions, such as extreme temperature ranges, dusty fuel out with the electn’c fuel boost pump, siphoning fuel
atmospheric conditions, high humidity and moisture, through the filler ports, or removing tank quick drain
unimproved airport facilities, or unusual operating valves.
requirements. WARNING
12-10-00 REPLENISHING Allow no smoking or open flame within 50 feet
of the defueiing area. Ground the aircraft and
1210-01 FUEL TANKS fuel container during all defueling operations.

Keep fuel tanks at least half filled to minim’u~e A. To defuel the aircraft using fuel boost pump:
condensation and moisture accumulation in tanks.
(i) Disconnect fuel line from electric boost pump
(Fuel capacity given in Chapter 6~
is
outlet at the fitting forward of the firewall.
WARNING (2) Connect to output fitting a flexible line that will
Ground the aircraft and fuel service vehicle. reach fuel receptacle.
Ground servicing noule to wing. Permit no
(3) Tum fuel selector valve to the tank to be
smoking or open flame within 50 feet of aircraft
drained, and remove filler cap from fuel filler port.
or vehicle.

(4) Turn on fuel boost pump until tank is empty.

WARNING
Repeat steps (3) and (4) to drain other tank.
Each fuel tank is vented to the atmosphere at
its outboard ah comer, vent openings are on (5) To completely drain fuel system also drain
the lower wing surfalce. Check vents for wing sumps and the fuel gascolator valve sump until
obstruction before each flight. fuel stops running.
NOTE
12-10-02 FUEL DRAINS When defueling using removable tank quick
A fuel-drain valve is located in the aft inboard comer of drains it is only necessary to remove the drains
and to operate the gascolator drain.
each tank to provide for drainage of moisture and
sediment. Use the small plastic cup fumished with the
12-10-03 ENGINE OIL
flyaway kit to drain the fuel sumps. Drain wing tank
sumps and gascolator before the first flight of the day Check engine oil level after engine has been stopped
and after each fuel service to inspect for water and/or long enough for oil to drain back into sump. The oil filler
contamination. Continue draining until free of water or cap access door is located in the top cowling. Any
contamination. lubricating oil, either straight mineral (MIL-L-6032) or
compounded, CTChn Spec MHS-24( are acceptable
WARNING
for use after break-in pen’od. Approved products and
After servicing the aircraft with fuel, wait at
least five minutes for moisture and sediment to
engine oil viscosity requirements are shown in Chapter
5-20-07.
settle before draining and checking both the
fuel tank sumps and the fuel selector valve CAUTION
drain. The terms"detergenr’, %ddaive", and
"compounded" used in this manual are
i. Fuel Selector Drain. The fuel gascolator is at the intended to refer to a class of aviation engine
lowest point in the fuel system and has a drain valve lubricating oils to which certain substances
operated by a control on the floor in the cabin. To drain have been added to improve them for aircraft
the fuel selector valve: use. These terms do not refer to such materials
A. Switch fuel selector valve handle to L and pull commonly known as "top cylinder lubricant",
fuel drain valve control n’ng for 10 seconds. "dopes" and "carbon remover" which are
sometimes added to fuel or oil. These products
B. Switch fuel selector valve handle to R and pull
may damage the engine and therefore, should
fuel drain valve control n’ng for 10 seconds. not be used. Under no circumstances should
C. After draining, be sure fuel drain valve control is automotive oil be used, since such oils could
retumed to the closed position and the valve is not cause engine damage.
leaking outside the aircraff. Oil Recommendations for New-Engine or Newly
WARNING Overhauled Engine Break-IN. New or newly overhauled
During cold weather operation, frequently engines should be operated on aviation grade straight
check fuel selector drain for ice formation by mineral oil dun’ng the first 25 hours of operation or until
repeating procedures 1., A, B and C above. oil consumption has stabilized.
12-00-00
SERVICE AND MAINTENANCE MANUAL M20K MOONE/ AIRCRAFT CORPORATION

OLDWILLWAYNE
The aircraft is delivered from Mooney with proper 12-´•10-04 OXYGEN SYSTEM (OPT1ONAL)
break-in oil (MIL-L-6082, MIL-L-6529C Type II, SAE
The oxygen when fully charged, contains
cylinder,
20W-50 Type I or 15W-50).
approximately cubic
76 feet of aviators breathing
OIL FILTER The oil finer should be changed at 50 oxygen (Specifications No. MIL-O-27210). Recharging
hour intervals using TCM filter or approved equivalet. of this oxygen cylinder should be accomplished by
When changing from mineral oil to additive oil the finer using the appropriate Scott recharging fittings to the
should be changed regardless of the operation time. pressure shown on (Figure 12-1), Pressure vs
Check screens and finers for sludge or plugging every Temperature Table.
10 hours when switching from mineral oil to ashless
dispersant (additive) oil. \NARNING
Oil, grease other lubn’carrts in contact with
or

oxygen create a sen~ous fire hazard, and such

contact must be avoided when handling
oxygen equipment.

AMBIENT FILLING AMBIENT FILLING

TEMPERATURE PRESSURE TEMPERATURE PRESSURE
DEGREES F PSIG DEGREESF PSIG

0 1650 50 1875
10 1700 60 1925
20 1725 70 1975
30 1775 80 2000
40 1825 90 2050

OXYGEN PRESSURE VS TEMPERATURE TABLE

F(GURE 12-1
NOTE CAUTKIN
The oxygen cylinder should not be run down to Do not use a compressor unit with a nonle
less than 100 p.s.i. Below this pressure pressure greaterthan 100 ps.i.
atmospheric contamination of the cylinder may 3. After cleaning, inspect finer andlor gasket for
occur, requiring valve removal and cylinder
damage. Discard a ruptured filter or broken gasket.
cleaning and inspection an at FAA approved
repair stations. NOTE
NOTE lffilter shows an accumulation of carbon, seat,
Refer to Section 35-00-00 for periodic bottle or oil, continue with cleaning steps 4 through 7.
pressure check.
4. Soak finer in nonsudsing detergent for 15 minutes;
Any time fittings are disconnected on the oxygen then agitate finer back and forth for two to five minutes
system the threads should be treated with to free finer element of deposits.
tetrafluoroethylene tape (MIL-T-i7720). Prior to
reconnedion the system should be checked for leaks 5. Rinse finer element with a stream of clean water
w8h leak testing compound (MlL-L-25567). If no leaks until n’nse water is clean.
are found wipe the system clean and dry. 6. Dry finer thoroughly. Do not use light or air above
i 80 deg. F. for filter drying.
12-20-00 -SCHEDULED SERVICING
7. Inspect for damage or ruptures by holding before
12-20-01 1 INDUCTION AIR FILTER alight or by holding light bulb inside filter (25-1000 3
ON). If damage is evident, replace fitter with new one.
The importance of keeping the induction air finer clean
cannot be overemphasized. A clean finer promotes fuel 8. Ched< altemate aidoorfor proper operation and sealing.
economy and longer engine life. The dry-type fitter can 9. Reinstall finer in aircraft making sure of proper
usually be washed six to eight times within 500 hours sealing and security.
or one year before replacement is necessary.

To clean the dry-type induction air finer (25-0001 thru 12-20-02 -BATTERY
25-0999): Service battery with distilled water to maintain
i. Remove finer element. electrolyte above plates. After adding water in freezing
weather charge battery long enough to m’u< electrolyte
2. Direct a jet of air against down or clean side of ,,d water. Keep battery electrolyte above a specific
filter (opposite to normal airflow). Keep air noule at to avoid freezing. To service battery:
least two inches from finer element (250001 thru
gravity
Direct a jet of air from inside of fitter out Remove battery box cover (if equipped). Check
(251000 thru 25TBA). Cover entire finer area with airjet. electrolyte and service battery as required.

12-10-04
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CAUTION 3. Attach pressurized hydraulic fluid service unit to
Battery gases may be explosive. wheel cylinder bleeder valve and open valve. Hydraulic
service unit should be free of air prior to servicing
2. Inspect battery box or battery mounting area for aircraft system.
corrosion and spilled electrolyte. To clean cables,
4. Feed fluid from service unit into brake system.
terminals, and battery box, use a solution of Check for air bubbles at end of drain line immersed in
bicarbonate of soda and clean water to neutralize
fluid.
corrosion and spilled electrolyte.
5. When fluid flow is clear of air bubbles, close wheel
CAUTION and remove service line.
cylinder bleeder valve
When cleaning, do not allow bicarbonate of
soda to enter battery cells pennanent damage NOTE
will result if soda mixes with electrolyte. Brake may need to be pulled back in
pedal
orderfornuid to bleed back into reservoir.
3. Rinse battery with clean water, and wipe clean
6. To Meed opposite brake, repeat steps 3 through 5.
with a dry cloth.

4. To retard corrosion, coat terminals with petroleum 7. Remove drain line from reservoir.
jelly after cleaning and tightening them, 3. Lower fluid level in reservoir to two inches below
air and vent for obstruction, filler port.
5. Inspect battery ram
line kinks, etc. 9. Reinstall filler plug.
10. Inspect brake linings for excessive wear and
12-2043 TIRES AND WHEELS
proper installation. Refer to Section 32-40-04 for Brake
Keep the tires at recommended air pressure. (Refer to Removal and Inspection Procedures.
Chapter 6-00-01. ii. Depress brake pedals to check for sponginess.
1. Inspect tires for wear, cuts, and bruises. Resistance should solid and even when brake

2. Inspect valve stems for evidence of tire slippage pedals are depressed.
or pulling. 12-20-06 CLEANING
3.inspect wheels for damage. Cleanliness is a major prerequisite to adequate
4. Inspect wheel bearings for condition and inspection and maintenance of an aircraft. Cleanliness
lubrication. enhances the appearance of an aircraft and reduces
the probability of corrosion.
12-20-04 BRAKE RESERVOIR
1. EXTERIOR
Frequently check the brake reservoir for proper fluid A. Before washing aircraft exterior, cover brake
level. See Chapter 12-20-05 for locations.
discs, pitot head, and static ports.
CAUT1ON B. Flush away loose dirt and mud.
Do not fill reservoir while parking brake is set.
C. Wash exterior with a mild aircraft detergent in
Use only hydraulic fluid (red!, per specification cool water, and a soft cleaning cloth or chamois. Rinse
Mll-l-l-5506. Do not fill reseNolr above two inches away soap film.
below filler port. CAUTION
Do not called "mild" household
use so
12-2045 -HM)RAUUC BRAKE (Bteeding)
detergents to wash aircraft exterior. Such
CAUTION detergents may damage finish and corrode
Fluid in the wheel cylinders may be under high aluminum components.
pressure due to expansion. Therefore, be sure CAUTION
parking brakes are released prior to beginning apply wax or use pre-wax cleaners
Do not
hydraulic system servicing. during initial paint curing period. Use only mild
For best results, use a hydraulic pressure senrice unit aircraft detergent and cool water when washing
exten~or during the first 90 days after repainting.
(pressure pot) to back bleed the system through the
wheel cylinder bleeder valves. D. To remove heavy oxidation film, use a pre-wax
1. Remove hydraulic fluid reservoir filler plug, and cleaner.
install a suitable fitting for attaching a flexible drain line E. Apply an e~denor-finish wax recommended for
to a filler port,
protection of urethane enamel. Apply a heavy coating
2. Immerse open end of drain line in a hydraulic fluid of wax to leading edges of wings, empennage, and
container, nose section to reduce drag and abrasion.

i 2-20-03
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OLDWILLWAYNE

CAUTION 3. ENGINE COMPARTMENT

When fuel, hydraulic fluid, or other fluid containing Accumulation of dirt and oil within the engine compart-
dye spilled on painted surfaces, remove it at
is ment creates a fire hazard and hampers inspection.
prevent staining. Flush away spilled
once to k Wash down engine cowiing and engine com-
battery electrolyte immediately with water. Treat partment using a nonflammable solvent.
the area with bicarbonate of soda solution
B. Dry engine cowting and engine compartment
followed by thorough washing with a mild aircraft
after washing.
detergent solution.
4. CABIN INTERIOR
AND DOORS Use normal household cleaning practices for routine in-
2. WINDSHIEU)S, WrNDOWS
A. Flush windshield and windows with water pn’or ten’or care.
to wiping. Never wipe while dry. k Frequently vacuum seats, rugs, upholstery
B. Remove grease or oil with a soft cloth panels, and headliners to remove surface dust and dirt.
saturated in kerosene. B. Clean leather or vinyl upholstery and panels
with a mild aircraft detergent. Clean with a slight damp
CAUTION cloth, and dry with a soft cloth.
Never gasoline, benezene, carbon
use
tetrachloride, acetone, fire extinguisher fluid, NOTE
de-icer fluid, lacquer thinner, or household window Foam-type shampoos and cleaners for vinyl,
cleaning sprays on windows or windshields. Such leather, and plastic materialscan be used to
solvents viill ioften or craze the plexiglas surface. remove stains and to condition the entire interior.
Spray-on dry cleaners are also recommended.
C. Clean windows and windshields with an antis-
tatic plexiglas
cleaner.
CAUTION
D. Check door seals for damage that could cause
Never apply furniture polish to interior furnishings.
leakage. Most polishes contain solvents harmful to vinyl
E. Check cabin and baggage door mechanism for Do not use alcohol or strong solvents on interior
goal working order. plastics. When using commercial cleaning and
finishing compounds, carefully follow the
NOTE manufacturer’s instructions. Never saturate fabrics
Minor scratches a polished out
abrasions may be with solution which could damage the backing and
by using plexiglas resurfacing kit~s, ie, Micro-Mesh, padding materials. To minim’ze wetting of carpets,
available from aircraft accessory suppliers. 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
CHAPTER
OLDWILLWAYNE

STANDARD
PRACTIC ES
(AIRFRAME)
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 20

STANDARD PRACTICES- AIRFRAME

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TABLE OF CONTENTS

SUBJECT PAGE
CHAPTER
SECTION
SUBJECT

General 3
20-00-00
3
20-00-01 Skin Specifications
Corrosion Detection and Prevention 6
20-00-02
Painting 7
20-00-03

20-EFF/CONTENTS
1/2BLANK
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
-GENERAL Alteration and Sub Parts A, D and E of FAR 65. Cer-
20-00-00
tification. Advisory Circular 43.13-1() outlines inspec-
This chapter of the manual discusses treatment of tion and repair practices acceptable to the F.A.A. Ad-
metal surfaces for corrosion control and the identifica- ministrator.
tion of skin panels for replacement purposes. Those
20-00´•01 SKIN SPECIFICATIONS
who inspect or repair aircraft should consult FAR 43,
Maintenance, Preventive Maintenance, Rebuilding and

STA STA STPI STA

STA
210,97 147.75 103.50 59~25 24,50

STA
193.50
5 1 r4 I r3 I r2

18

15

19 13
12
i
17 11 10 i
-J L9
14

WING SKIN PANELS

WING SKIN PANELS FIGURE 20 1

.MATERIAL INDEX SKIN MATERIAL

INDEX SKIN
THICKNESS NO. .THICKNESS
NO.
12. 0.025(c) 2024 T-3 CLAD
1. 0.063 2024 T-3 CLAD
2024 T-3 CLAD 13. 0.020(a) 2024 T-3 CLAD
2. 0.050
14. 0.032 2024 T-3 CLAD
3. 0.040 2024 T-3 CLAD
15. 0.040(b) 2024 T-3 CLAD
4. 0.032 2024 T-3 CLAD
16. 0.040(d) 2024 T-3 CLAD
5. 0.025 2024 T-3 CLAD
20241-3 CLAD 17. o.ols(a) 2024 T-3 CLAD
6. 0.025
2024 T-3 CLAD 18- 0.050(b) 2024 T-3 CLAD
7. 0.032
0.040 2024 T-3 CLAD 19- Polyester Glass-Fiber Reinforced
8.
9. 0.025 20241-3 CLAD
10. 0.025 2024 T-3 CLAD
11. 0.025 2024 T-3 CLAD

(a) Same thickness on top and bottom.

(b) Top of wing only.
(c) Top aft flap skin that section).
(d) Top inboard flap skin.

20-00-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE

8 7 5

67 6-\ r7 ~1 ~4 r3
14 /I 2

12

r 1 I 1 I I I
I~ I

1
1-’ I 6 --1 I 5

9 1 I I I \I L5 I L1
10 1 L
11 13

SIA STA STA STP1 STA STA STt4

299,50 164,00 130,00 88,00 53,00 21,80 -5,00

~USELAGE SKIN PANELS

FUSELAGE SKIN PANELS FIGURE 20 2

INDEX SKIN .MATERIAL INDEX SKIN MATERIAL

NO. THICKNESS NO. .THICKNESS

1. 0.025 2024 T-3 CLAD In. 0.032 2024 T-3 CLAD

2. 0.040(d) 2024 -0 CLAD II. 0.032(a) 2024 T-3 CLAD
3. .0.025(c) (b) 2024 T-4 CLAD 12. 0.032 2024 T-3 CLAD
.4. 0.025 2024 T-3 CLAD 13. 0.025(6) 2024 T-3 CLAD
5. 0.025(b) 2024 T-3 CLAD 14. Polyester Glass-Fiber Reinforced
6. 0.020 2024 T-3 CLAD
7. 0.025 2024 T-3 CLAD
8. .0.032(d) (e) 2024 -0 CLAD
9. 0.025 20241-3 CLAD

(6) Left side only.

(b) Right side only.
(6) 0.032 can be used.
(d) Heat treated to T-42 condition after forming.
(6) Shes.

20-00-01
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE

STA 4 STA rl 7-\ 9

5
42,25 242,25

3-1 1 I STA
25,75

11
10

6 6 13

EMPENNAGE SKIN PANELS

EMPENNAGE SKIN PANELS FIGURE 20 3

SKIN .MATERIAL INDEX SKIN MATERIAL

INDEX
NO. THICKNESS NO. .THICKNESS

1. 0.025 2024 T-3 CLAD 8. 0.025 2024 T3 CLAD

2. 0.025 2024 T-3 CLAD 9. 0.020 2024 T-3 CLAD

3. 0.025 2024 T-3 CLAD 10. 0.032 2024 T-3 CLAD

4. 0.025 2024 T-3 CLAD 11. Polyester Glass-Fiber Reinforced.

5. 0.025 2024 T-3 CLAD 12. 0.020 2024 T-3 CLAD

6. 0.020 2024 T-3 CLAD 13. 0.025(a) 2024 T-3 CLAD

7. 0.025 2024 T-3 CLAD

(a) Heat treated to T-42 condition.

20-00-01
SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

OLDWILLWAYNE
2040-02 ~CORROSION DETECTION C. Concentration Cell Corrosion
PREVENTION Corrosion forming under rivet heads, along faying
surfaces, at skin to longeron contad surfaces other
Most metallic fabn’cation materials are susceptible to
cormsion. Corrosion may occur on aircraft in any similar areas is called concentration cell corrosion.
climate, but it will be a problem more often in climates Detection requires close inspection. Rivets must be
where the aircraff is exposed to salt air or high removed and skin laps must be sepal-ated to remove
where there are industnal contaminants in concentration cell corrosion. Use aluminum wool soaked
humidity or
the atinbsphere. The aircraft should be inspected in solvent such as methyl-ethyl-ketone to scour corosion
to detect and correct corrosion before deposits from the surface before painting both faying
frequently surfaces with zinc chromate primer and reassembling.
senous damage occurs.
D´• Galvanic Corrosion
Any form of conosion should be removed at once. If it is
necessary to remove paint, only an approved aircraft Dissimilarmetals, such as stainless steel and
paint remover such as Eldorado PR-3400, (EMoradc aluminum, in contact with each other sometimes
Chemical Co., Inc., 6700 Lookout Road, P.O. Box 32101, develop galvanic corrosions. To remedy this form of
San Antonio, TX. 78216) should be used. Paint removing corosion, separate the parts, remove the corrosion, and
substances~leff in m~tal crevices will cause further paint both surfaces with Zinc Chromate or
corrosion. Turco 2662C or 3002 will remove corrosion epoxy-polymide pn’mer before reassembling.
from aluminum and treat the metal surface in one
2. Corrosion Prevention
application. This paragraph discusses corrosion types
and their prevention along with suggested procedures for A. Thcroughly examine unpainted metal surfaces at
zinc chromating intemal airframe surfaces. inspections, and check cormsbn when found. Carefully
examine seams, lap joints, and crevices where moisture
1.Types of Corrosion Aluminum or dirt can celled. Areas e~cposed to e~haust gases
Corrosion normally appears in one or more of four require frequent inspection and cleaning.
forms. Each type of corrosion can be precluded or B. Corrosion may attack metal even though the surface
controlled by a preventative maintenance program, is painted. Inspect painted areas for a blistered or scaly
A. Chemical Corrosion. appearance that warns of conosion below the paint layer.
Chemical corrosion normally occurs where battery acid C. Use only liquid (non-alkaline) soap to wash the
e>den’or airframe. Cover vent scoops when the aircraft
or exhaust gases come in contact with metal surfaces.
A few simple precautions will prevent chemical is being washed. Rinse aircraft e>derior after e~q>osure
corrosion, to salt air or industrial fallout.

is free from obstruction at D. Since moisture promotes con~osion, thoroughly

(1) Be sure battery vent
alltimes. and frequently inspect areas where water is apt to
collect. Use an air hose to drive water from crevices
(2) Repaint all scratches and wom spots found in before wiping the e~derior surface dry after washdown.
areas painted with acid-resistant paint E. Hangarthe aircraft when not in use.
(3) If acid is spilled on metal surfaces, flush entire F. If battery acid is spilled on any part of the
area with sodium bicarbonate and water. The solution
aircraft, immediately wash the area with a solution of
should be rinsed away at once and the area dried by
sodium bicarbonate in water. Rinse with water and dry
driving all water from crevices with an air hose before with clean towels.
wiping surface dry with a clean cloth.
NOTE
(4) Frequently clean exhaust gas deposits from FAA Advisory Circular 434 addresses
metal surfaces.
corrosion problems.
B. Local-Cell Corrosion.
3. Zinc Chromating (or Equivalent).
On bare metal surfaces, in an early stage development,
local-cell corrosion appears as a light, whitish powder Zinc chromating or equivalent of intemal airframe
surfaces will not eliminate the necessity for periodic
deposit. Surface pits wam of advanced loca~cell
corrosion. On painted surfaces, the first indication of inspections. The most likely areas for corrosion to
corrosion will be evidenced by paint blisten’ng. begin are in hidden crevices such as skin laps, under
rivet heads or any opening where moisture can collect.
(1) Intergranular Corrosion Selective attack periodic inspection of these areas is most important so
along grain boundaries of metal alloys is referred to as that any corrosion which may be present can be
Intergranular corrosion. Aluminum alloys 2024 and detected and treated in its very earliest stages.
7075 are vulnerable to this type of attack. Aluminum
Vli~en corrosion is detected, it should be treated as foll~Ns:
extrusions may contain nonuniform areas, which in tum
may result in galvanic attack along grain boundaries. product (usually white or
A. Remove all corrosion
7hls type of corrosion is difficult to deted in its original grey-white powder on aluminum) from the corroded
stages. When the attack is well advanced, the metal is area down to sound metal.
usually blistered or delaminated. This is referred to as (1) If the base metal is aluminum, clean off the
"exfoliation". It is very difficult to completely remove conosion produd by scrubbing with aluminum wool or
and stop this type of corrosion, and replacement of the nonmetallic scouring pad such as the nylon pads
affected part is recommended wherever possible, made by the Carborundum Company, P.O. Box 277,
Niagara~Falls, N.Y. 14302.

20-00-02
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
If the base metal is steel, remove the B. Cleaning Procedures.
(2)
corrosion product with emery cloth (320 grit or finer) or
NOTE
steel wool.
Fiberglass components are attacked and
(3) If the corrosion is too advanced to remove by deteriorated y products containing the
the light mechanical cleaning methods of (1) and (2), following chemicals: Ketone, aliphatic esters,
refer to Advisory Circulars 43.13-~1() and/or 43-4’f;i; chlon’nated hydrocarbons and siightly softened
aitemate methods of cleanup and repair. by aromatic hydrocarbons.
(4) Chemical cleaning solutions should be used (1) Fuel Servicing Decal Removal:
with extreme caution on both aluminum and steel parts.
Such solutions are not recommended for use in areas (8) Cover the decal with a hot, wet towel for
where they cannot be easily and completely approximately 2 minutes.
neutralized. Lift one comer of the decal and slowly
B. Wash all areas to be zinc chromated with a remove.

cleaning solvent such as methyl ethyl ketone (MEK), (2) Remove all old loose paint by one of the
Turco T-657 CTurco Products, Inc., 6135 South Central following methods:
Ave., Los Angeles, Califomia), lacquer thinner, #3094 for uniformity of finish
wash thinner (Pratt 3 Lambert, Inc., 25th and N.Y. (a) On alurrinum
Avenue, Wichita, Kansas) or similar solvents. appearance, the entire skin panel should be prepared for
repainting. paint is
if the in very bad condition or if a filler is
(1) a good clean surface for zinc chromate
To get t, b,,sed, remove all of the paint by use of lacquer
priming clean cloth or piece of cheesecloth and
use a thinner, MEK or similar solvent Careful application of paint
apply one of the solvents noted above. The surface stripper is acceptable. The solvent should be wiped on and
should be wiped dry with a second piece of clean cloth. wiped off before it evapo~ates. h the solvent is allowed to
Do not allow the solvent to dry on the cleaned area as it evaporate, it will redeposit the soils and paint that were
will redeposit dissolved soil and gn’me upon being canied. Any scoun~ng required should be done at this
evaporation, point. Scouring with nylon pads or aluminum wool may be
done dry or wet with one of the wipe solvents listed above.
CAUTION
AAer the old paint, grime, etc. has been loosened and
Wipe solvents are generally flammable and removed, the scoured area should be wiped with a tack
toxic and should not be used without adequate The part
rag, and again cleaned with fresh wipe solverd
ventilation and fire precautions. should now be ready for priming and painting.

Apply zinc chromate pn’mer to cleaned area by

C. (b) On steel Remove all grease, gn’me, loose
spray brush. Area needs to be painted within 24
or paint, eic:by wiping with a wipe solvent and rags. Do not
hours of zinc chromate primer coat. allow the wipe solvent to evaporate. Wpe it dryl Steel
parts may be cleaned to bare metal by sanding with
20-0093 PAINTING emery cloth or steel wool. If the parts are removable, they
can be cleaned by sandblasting. Regardless of the
The exterior is painted with urethane enamel. When
scouring method, allparts should be wiped with a tack rag
exposed to humid salt air or to an atmosphere having and cleaned with fresh wipe solvent. The part should now
corrosive fallout, the aircraft should be hangared when
be ready for pn’ming and painting.
not in use.
C. Priming and Painting.
1. Paint Repairs.
(1) On aluminum Cleaned and dried surfaces to
A. Materials.
be painted should be coated with a wash primer
(1) Aluminum wool, nylon scoun’ng pads, 320 grit conforming to MIL-C-8514 or M1L-P-15328. Read and
or finer emery cloth or steel wool. follow the manufacturer’s instructions carefully. The
wash pn’mer should be applied to attain a dry film
(2) Tack rags, thickness of 0.3 to 0.4 mils (8 transparent film). A good
(3) V~pe solvents suc~ as: methyl ethyl ketone, T-657 wash primer coating is a must since the top coating can
--CTurco Products, Inc~; ~3094 wash thinner --(Pratt 3 be only as good as the primer coat. As a general rule
Lambert, Inc.); lacquerthinner or equivalent sohRnts. the wash pn’mer should dry From .05 to 1.5 hours but
not more than 2 hours before application of the top or
(4) Body putty or aerodynamic filler such as: intermediate primer coat. When an intermediate epoxy
Flex-Bond --CTaylor Art Plastics); Flex --(3M
filler #6372 (NAPA primer coat is applied, it should be mixed very carefully
Co.);or Cut polyester body per the manufacturer’s instructions. h should
be thinned
[Martin Senour Paintsl). per manufacturer’s instructions and applied to a dry film

(5) Compatible paints for the item (such as steel thickness of 0.8 to 1.0 MILS. The intermediate primer
tubular structure or e~derior skin) and for the year and shoukl be allowed to dry a minimum of 0.5 to 1.5 hours
model being repainted. (Refer to Mooney Parts depending upon the application temperature and
Catalog). relative humidity.
Follow manufacturer’s instrctions. The intermediate
(6) Thinners which are compatible with the paints primer coat can be dry-scuffed lightly with No. 400 to
being used both for paint thinning and for bum-down No. 600 sandpaper prior to top coat application and
thinners. give a higher gloss finish. As many coats of paint as
desired may be applied. A higher g(oss will be gttained
20-00-03
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
if the surface is scuffed lightly and tack rag cleaned NOTE
between each coat. M20K aircraft arepainted with urethane enamel.
used Inquiries concerning application of this finish
(2) On steel The same general procedure should be directed to: Pratt b Lambert, P.O.
on aluminum can be applied to steel. However, Box 2153, Wichita, KS. 07201.
Mll-P-8585 primer or epoxy pn’mer is recommended
for the steel coat. If epoxy primer is used, it should CAUTION
have a wash pn’mer(MIL-C´•8514) pre-treatment. Any flight control surface that is to be
D. Painting. repainted should be stripped of all paint prior
to repainting. h is required that repainted
(1) Apply three coats of white base andlor color control surfaces be removed and rebalanced
finish allowing three to five minutes between coats prior to flight pet paragraph 2’191-00.
depending upon weather conditions. Allow five to ten
minutes between coats in cold, dry weather; in humid NOTE
weather, allow fifteen minutes between coats. Never abrasive polish compounds or harsh
use
soaps and detergents on ureathane finishes.
(2) Use a small round watercolor brush trimmed Once the surface gloss is damaged it cannot be
to a point for application of undiluted touch-up paint to restored by polishing.
small scratches and bare spots. Do not thin acid
resistant black paint or exterioi finish touch-up paint for
brush-on application.

20-00-03
 CHAPTER
OLDWILLWAYNE

AIR
CON DITIONI NG
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORTION
OLDWILLWAYNE
CHAPTER 21

ENVIRONMENTAL SYSTEMS

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SUBJECT

Cabin Ventilation System 3

21-00-00
21-40-00 Heating .........´•´•3

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MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CABIN VENTILATION SYSTEM 21-40-00 HEATING
21-00-00
The cabin environmental system consist of three ven- Heat is supplied to the cabin through Rexlble hoses
connected to a heat distribution box assembly and
tilating systems that supply heated or fresh air as the
shroud assemblies located on the exhaust manifold on
pilot or passengers prefer. CABIN AIR, CABIN HEAT
and OVERHEAD VENTILATION. The cabin air and heat the engine. It is recommended that the condition of
these items be checked each time the cowling is
system controls and vents are located on the console
between the pilot and co-pilot seats. Individual fresh air removed. This will provide a continuing check for the
prevention of carbon monoxide in the cabin. Any
outlets are located on each side of the cabin side
deten’orated flexible ducts should be replaced. Heat
panels just fonn~ard of the pilots and co-pilots knees.
The overhead ventilation system consists of individual shrouds should be inspected for cracks or other
outlets (Wemac valves) located above each seat posi- deteriorations and repaired or replaced promptly. In-
cracks and
tion. S/N 25-0247 and later aircraft have a regulator spect the exhaust system for any leaks or

system with the control knob located above the pilots replace or repair as needed.
head. The systems are basically trouble free but in-
spection should be made at regular intervals to ensure
proper operation.

21-00-00
SERVICE AND MAINTENANCE MANUAL M20K MOONN AIRCRAFT CORPORATION

OLDWILLWAYNE

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21-40-00
 CHAPTER
OLDWILLWAYNE

ELECTRICAL
POVVEF~.
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CHAPTER 24

ELECTRICAL POWER

TABLE OF CONTENTS

CHAPTER SU&IECT PAGE

SECTION
SUBJECT

General 5
24-00-00
D.C. Generation 5
24-30-00
Altemator Charging System Maintenance 5
24-31-01
Voltage RegulatorMaintenance 6
24-31-02
Battery Maintenance 7
24-32-00
Warning Circuits 7
24-33-00
Power Plant Circuits 8
24-3600
Low Battery Starting Procedures 8
9
24-35-00 Lighting Circuits
9
24-3600 Landing Gear Circuits
9
24-37-00 FuelSystem Circuits
Miscellaneous Circuits 11
24-38-00
TroubleShooting Charts 11
24-39-00
AltematorTrouble Shooting 11
24-39-01
24-39-02 GeneratorTrouble Shooting
(For Standby Gene~ator) 13

24-39-03 Battery Trouble Shooting 14

24-39-04 Starter Trouble Shooting 15

24-39-05 Annunciator Trouble Shooting 16

(SM 25-0001 thnr 25-0999)

24-39-06 Annunciator Trouble Shooting 18

(SM 25-1225 thru 25-TBA)

24-50-00 Electn’cal Load Distn’bution 24

24-51-00 Power Distribution System 24

24-CONTENTS
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OLDWILLWAYNE
CHAPTER 24

ELECTRICAL POWER

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24-00-00 -GENERAL NOTE
It is recommended that the approved Auxiliary
S/N 25-0001 thru 251)999 Power Cable be connected to the booster
A 14 volt, 70 AMP altemator utilizing a trans~torized battery and the plug inserted into the auxiliary
voltage regulator/overvo~tage control supplies electrical power receptacle, if equipped.
power. An optional 12 volt, 10 amp. standby generator
C. When the battery is removed from the aircraft
may be installed. A minimum of pilot effort is required to
properly use this backup source of eledn’city. A 12 voft, for charging, be sure that the charger is correctly
35 ampere-hour storage battery is installed in the connected. Use the correct charging rate when
tailcone. The aitemator, dun’ng normal operation, supplies charging battery, refer to Manufacturers procedures. It
is possible to reverse the polarity of a battery by
power in conjunction with the battery when the master
switch is on. The circuit breaker panel is on the right connecting a charger backwards.
subpanel. The eledn’cal system is capable of supplying D. Be sure to check battery polarity by using a
current for simultaneous operation of multiple radios, an voltmeter priorto reinstallation in the aircraft.
anticollision beacon, and navigation lights. A shunt type
ammeter mounts in the power plant instrument cluster. E. Do not leave the master switch ON when the
aircraft is parked.
S~ 25-1000 thru 25-TEA
F. Use an auxiliary ground power unit when trouble
A 28 volt, 70 AMP altemator utilizing transistorized
a
shooting electn’cal accessory equipment or when
voltage regulator/over voltage control suupplies performing electrical landing gear maintenance and
electrical power. An optional 28 vo~t, 70 AMP second retraction system testing.
alternator may be installed. A 24 volt, 22 AMP HR
2. ALTERNATOR SYSTEM INSPECTION.
storage battery is installed in the tailcone. The
alternator, during normal operation, supplies power In A. Check altemator(s) circuit breaker(s) on the
conjuction with the battery when the master switch and main circuit breaker panel. Reset breaker if open.
alternator field switch are ON. The circuit breaker panel
B. Check applicable altemator field circuit breaker
Is on the right subpanel. The electrical system is
on main circuit breaker panel. Reset if open.
capable of supplying current for simuRaneous
operation of multiple radios, anticollision lights and C. Inspect batteryfor corroded cable connections;
navigation lights. On S/N 25-1 000 thru 25-1224 a shunt remove and clean cable if corrosion is found.
combination gauge gives alternator output and connectors to be
~Y,PB"
load in of rated capacity plus
sure
D. Check charging system
they are clean and tight.
wiring
S/N 25-1225 thru 25-TEA a shunt type ammeter is
mounted in the power plant instrument cluster. E. Inspect altemator(s), voltage regulator, and
win’ng fordamage.
2430-00 -D.C. GENERATION
CAUTION
2431-01 ALTERNATOR CHARGING SYSTEM DO NOT ATTEMPT TO POLARIZE
MAINTENANCE ALTERNATORS. Alternators are polarized
1. ALTERNATOR SYSTEM SERVICING. every time Master Switch is turned ON.

(25-0001 thru 25-0999, 25-1 225 thru 25-TEA) 3. ALTERNATOR(S) REMOVAL 3 INSTALLATION
When the ammeter shows a discharge higher
at
A. Altemator(s) Removal.
engine speeds, a charging system component
Tum Master Switch OFF. Disconnect affected
(altemator, voltage regulator, circuit breaker, or wiring)
is malfunctioning. altemator witing.
Selt Dn’ven Altemator
(25-1000 thru 25-1224)
(1) Loosen and remove adjustment bolt from
Wnen the loadmeter shows a higher than the
altemator output at higher RPM, a charging system tension adjustment bracket.
component is malfunctioning. On-the-plane testing (2) Remove drive belt from altemator pulley.
should indicate which component is faulty and needs to
(3) Remove cooling air duct from altemator.
be removed from the aircraft for bench testing and
repair or replacement. (4) Remove lower pivot point hardware and
’emove altemator from mounting bracket.
The altemator charging system requires no special
attention; however, improper maintenance procedures Main, Gear Driven, LowerAUtemator
can damage the aRemator and wiring. There are to
any components to gain access
several precautions that must be observed when
servicing the altemator system:
A. Be sure the master switch is off when repain’ng
(2) Remove mounting bolts.
the aitemator or voltage regulator. NOTE
B. When auxiiiary power or a booster battery is The main alternator is very difhcult to remove.
used, be sure the cables are connected The lower enginelfirewall mount bolts may
correctly--positive to positive and negative to require loosening, the upper bolts may require
negative. DO NOT by-pass the battery when using removal and the engine pivoted around the
Auxiliary Power Source. lower attach points.
24-00-00
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
Position engine hoist to hold engine in position. 4. STANDBY GENERATOR MAINTENANCE
(3)
(4) Loosen lower engine mount~firewall bolts (259001 thru 25-0999).
slightly so engine mount can pivot. The standby generator brushes should be replaced at
150 to 200 hours of operation under load. The
(5) Lower engine hoist to allow engine to pivot
downward just enough to permit altematorto be removed. generator manufacturer recommends the brushes be
replaced every 2000 hours of no load operation.
(6) Remove cooling air duct and any wiring form Mooney AircFaff Corporation recommends the generator
alternator, connections, brushes and general conditions be
inspected every 100 hours and repaired if necessary.
B. Altemator(s) Installation.
Refer to vendor overhaul manual for specific
Main, Gear Dn’ven, LowerAltemator maintenance procedures. Minimum brush length is .700
(1) Place new attemator into position on drive pad. inch overall. Replace with new brushes; minimum spnng
tension on new brushes should be 5 ounces.
(2) Attach cooling air duct and widng to alternator.
2431-02 -VOLTAGE REGULATOR
(3) install mounting bolts into accessory case
dn’ve pads and secure alternator. Use standard torque MAINTENANCE
table fn Chapter 5. The battery charging rate depends upon the battery
to position upper engine condition and the voltage regulator setting. Wnh all
(4~ Raise engine hoist
mouni/fiiewall attach points and secure with engine equipment turned off and the engine running at 2000
mount bolts. RPM or faster, the normal battery charging rate will be
5 to 35 amperes.
(5) Torque upper and lower engine mount/firewall Rate. Check the following:
boist per Section 71-00-30. 1.Ej(cessively High Charging
(6) Reposition any components moved dun’ng A. Fly aircraft for 15 to 20 minutes; charging rate
altematbr removal process. should slowly drop to 10 amperes or less. A very low
battery will take longerto show a drop in charging current.
Belt Dn’ven Alternator
B. Measure voltage with a voltmeter connected to
(1) Place ne\N alternator on iower pivot attach point the bus. At 800 F., voltage should be 13.75 to 14.0
(2) Insert pivot point mounting hardware. (25-0001 thru 25-0999), (S/N 25-1000 8 01\/27.5 to
28.0 volts). An excessively high voltage regulator
(3) Re-attach win’ng and cooling air duct to
setting will cause excessive battery heating and water
alternator, loss.
(4) Place drive belt over altemator pulley. Make 2~ Excessively Low Charging Rate. Check battery
sure b~oih drive sheave and altemator pulley are properfy charging rate (normal rate is not to exceed four
aligned so belt will travel in straight line. Use Burrough amperes). The regulator should not be considered
Tool #8082. Reposition AN960-716 washers on bottom defective because of a low charing rate until:
bolt and add TCM #849268 washers for alignment.
A. A voltmeter check indicates that voltage at the
(5) Position altemator to obtain proper belt
b,s is below requirements.
tension 45-501bs..
B. A battery hydrometer check indicates that
(6) Tighten tension adjustment hardware to
battery is not fully charged.
standard torque tables in Chapter 5.
3. Hydrometer Reading. If battery eledrolyte
O Run engine with aftemator loaded, minimum temperature is below 800 F., subtract four points from
of 20 minutes, maximum of 2.0 hours, then retension hydrometer reading for every 100 F. below 800 F. If
belt 45 50 Ibs. battery acid temperature is above 800 F., add four points
to hydrometer reading for every 100 F. above 800 F

U(AMPLE:
Hydrometer reading 1.260
Battery electrolyte temoerature 300 F.
80"- 300 500
5 x4 20 points
Corrected readina 1260 -20~

HYDROMETER READlNG PERCENT OF CHARGE

1.280 100
1.250 75
1.220 50

1.190 25
1.130 or below Very little useful
capacity-discharged

24-31-02
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
"Hi" or Overvolt Adjustment at Regulator- F. Clean battery terminals with emery cloth,
BENCH ADJUSTMENT (ELECTRO DELTA). reinstail and tighten cables. Coat terminals and
connectors with petroleum jelly to retard corrosion.
Connect a variable voltage power supply to the
regulator, positive to pin "A" or "1" and negative to 2633-00 -MIARNING CIRCUITS
pin "C" or "3"(25-0001 thru 25-0999), positive to pin 5
1. Landing gear position lights and waming hem.
negative to pin 9 for 25-1000 8 ON). Conned a Red and green landing gear position lights are in the
voltmeter to the regulator to pin "D" or "4" and to
annunciator panel. The gear-down limit switch controls
pin "C" or’3" (25-0001 thru 25-0999), (pin 6 and pin 9 the green gear-down light. Both limit switches control
for 25-1000 ON). Adjust voltage to 16 volts +I- .1 volt the red gear unsafe light. The throttle control operates
(25-0001 thru 25-0999),(28.7 volts for S/N 25-1000 8 landing gear warning hom (intermittent tone) when the
ON). Adjust tn’m pot (accessable through hole in case power setting is reduced below 12 IN. Hg. SIN 25-0001
marked "OV~ to relay tn’p pointas indicated by voltage thru 250780 with the gear up; and on 25-0781 thru
indication on test voltmeter. Decrease voltage until
25-TEA when the throttle is retarded below 16" to 18"
relay closes and note voltage. Readjust as necessary
Hg~ and the landing gear is still in the up position.
until a tn’p point of 16 +I- .1 volts is attained(25-0001 Check gear warning system during flight for proper
thru 25-0999); 31.8 ~1-).3 volts for 25-1000 a ON).
,peration.
Regulator Adjustment (ELECTRO DELTA) Warning Circuit. The prestall warning horn
2. Prestall
Conned an accu~ate voltmeter to the aircraft bus. Tum has h~h frequency continuous tone that sounds
a
off all eledn’cal equipment and start engine. Run engine when airspeed drops to 5 to 10 MPH IAS (4.3 to 8.7
at moderate RPM (1500-1800) until ammeter drops to KIAS) above stalling Speed. A vane in the left wing
low charge rate. Increase RPM to 2000 and adjust tn’m leading edge aduates the prestall warning horn switch.
pot (accessable through hole in case marked "REG3 for C~his vane is made of heat treated steel, and any
a voltage reading of between 13.75 and 14.0 volts attempt to adjust switch operation by bending the vane
(25-0001 thru 250999);(28.6 and 28.8 volts for 251000 will damage the switch). Refer to Section 27-93-00 for
thrr 25-TEA). Increase throttle to full RPM and observe adjustment procedures.
that voltage does not exceed 14 volts (25-0001 thru 3. High and Low Vacuum Waming Circuit. A switch
25-0999);(30 voltsfor 25-1000 thru 25-TEA). in the vacuum system controls the vacuum´• waming
NOTE light on the annunciator panel. Vacuum below 4.25 IN.
Use bushings provided with replacement Hg. causes the vacuum warning light to flash. Vacuum
above 5.5 IN. Hg. hips the high-vacuum switch causing
VR-415F voltage regulator to mount in location
the vacuum waming light to illuminate steadily.
of old regulators,
NOTE 4. Low Fuel Waming Circuit. The low fuel indicators
No field adjustment authorized for Mooney will illuminate when a m’nimum of 2 112 gallons usable
Voltage Regulator. fuel remains in either left or right hand tank. When it
Max. Voltage for 14 Volt system: 14.2 +~2/-0. becomes necessary to replace the annunciator panel for
the
Max. voltage for 28 volt sytem: 28.3 +.2/-0 any reason other than "low fuel" waming maifundion,
following procedure should be used to set the "low fuel"
24-32-00 BATTERY MAINTENANCE waming circuits. The calibration t~ansfer standard (I.A.I.
PM 500D0045 for SM 250001 thru 25-1224) or IA.I.
CAUTION PM 9500324000 for SM 25-1225 thru 25TBA) B
Battery gases are explosive, required for this procedure. Adapters can be ordered
I. Battery Removal.
through Mooney Marketing or Service Centers.
A. Calibration Procedures using IA.I.
A. Tum Master Switch OFF.
PM 500D0045 or P/N 9500324000.
B. Remove tailcone access cover and battery box lid.
(1) Remove glareshield, disconnect plug from
C. Disconned battery cables, negative lead first, rear of annunciator, remove annunciator front panel,
remove battery from aircraft. and place "Norm-Cal" switch in "Cal" position.
D. Install battery in reverse sequence of removal. Use (2) Plug model TS201I231-001 (P/N 500D0045)
a voltmeter to ched~ battery polaritybefore installation. calibration transfer standard on rear ofokf annunciator
and Corrosion Removal. and reconnect hamess plug.
2. Battery Cleaning
k Mbe one pound of baking soda h one gallon of water. (3) Tum on master switch and tum right hand
variable resistor on transfer standard slowly counter
B. Wash battery box and flush battery with the mb(ture. clockwise until right "low fuel" light just tums on. (If
Do not allow soda water to enter battery cells; permanent necessary turn van’able resistor clockwise to e~dinguish
damage will result if soda mixes with eledrolyte. "low fuel" light). @o not adjust annunciator calibration
C. Rinse thoroughly with clearwater and dry the area, screws). Repeat for left "low fuel".
D. Test each cell with a temperature corrected (4) Turn off master switch and remove old
hydrometer. Specific gravity should be 1265 to 1280 annunciator assembly after disconnection of harness
fora fully charged battery, and transfer standard unit.
E. Check electrolyte level and maintain at split ring.

24-32-00
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
(5) Install new annunciator and connect ignition system is on. Turning the ignition switch to start
calibration transfer standard to annunciator panel and and pushing in, closes the starter solenoid, engages
harness plug. Remove front plate and legend on new the starter and allows the impulse coupling to
annunciator panel to expose the Norm-Gal switch and automatically retard the magneto until the engine is
the Leg and Right tn’m potienometers. (Switch must be also at its retard fin’ng position. The spn’ng action of the
in "Cal" position). impulse coupling is then released to spin the rotating
left and dght annunciator fuel magnet and produce the spark to fire the engine. After
(6) Adjust the engine starts, the impulse coupling flyweights do
calibration screws clockwise (not the adapter van’able
not engage due to centrifugal action. The coupling then
resistors) until "low fuel" lights just turn on. (If
acts as a straight dn’ve and the magneto fires at the
necessary tum annunciator calibration screw counter
normal fin’ng position of the engine. The starter-ignition
clockwise to e~dinguish "low fuel" light),
switch is spn~ng loaded to retum from START to the
O Remove calibration transfer standard, BOTH position when released.
reconnect plug to annunciator panel, set switch to
"Normal" position, install annunciator front panel and CAUTION
install glareshield. Do not operate the starter in excess of 15
seconds or re-engage the starter without
B. Altemate method for calibration without unit.
allowing it time to cool.
If calibration transfer standard, P/N 500D0045, is not
available use the following method to calibrate "low A. Low Battery Starting Procedures.
fuel" wamlng: Batten’es that have been discharged to the point where
and annunciator they will not tum the engine but have sufficient power
glareshiald remove
remaining for other equipment; should NOT be jumped
with another power source fortwo major reasons:
(2) Install and connect new annunciator assembly (1) The discharged aircraft battery is not
leaving off front panel. (Set switch to "ca1’3. airworthy because it will not have the necessary
(3) Drain fuel from tanks and replace with resenre capacity required to operate the aircraft
unusable fuel plus 2 1/2 gallons in both tanks. electn’cal system and avionics in the event of the failure
(4) Tum Master Switch ON; adjust calibration of the generating system dun’ng flight.
pots to position where "low fuel" lamps just tum on for (2) Adive material on the positive plate e~cpands
left and right tanks. when the battery is discharged and the fast recharge
Turn Master Switch OFF; set annunciator from the higher potential source, battery, aitemator,
(5)
"Cal" Switch to "Norm" position, install annunciator generator, rectifier, etc., will severely damage the
front and install glareshield. battery. A slow charge is recommended priorto flight.
(6) Refuel aircraft. WARNING
5. Aftemate Air Light Warning Circuit Annunciator Do not turn the propellerwhen the magnetos
Panel. The light illuminates on the annunciator panel are not grounded. Ground the magneto points
when the altemate air door has opened for any reason. before removing switch wires or electrical
connectors. All spark plug bads can be
6, Hifl-ow Voltage Waming Circuit Annunciator
removed as an alternate safety measure.
Panel. Remove annunciator top cover. Connect a
voltmeter to the aircraff bus. Start engine and Nn at 2. Oil and Cylinder Head Temperature Gauge
idle. Add load to bus until "Low Volt" light starts to Circuits. Both the oil and cylinder head temperature
flash. Adjust RPM to obtain a bus voltage of 12.5 volts indicators operate eledrically. The oil temperature
(25-0001 thru 25-0999);(26.5 volts for 25-1000 thru gauge circuit has a resistance bulb in the oil sump.
25-TEA). Adjust trim pot (located at center, rear of Changes in resistance caused by changes in oil
circuit board) till flashing light just comes on, temperature alter current flow rate, thereby varying the
NOTE
magnetic field in the indicator coils. The cylinder head
temperature indicator conneds to a t~p sensitive
It may be necessary to adjust trim pot to turn resistance bulb in a cylinder head,normally No. 5
out light at 42.5 volts (25-0001 thru Increase or decrease in temperature causes
cylinder.
25-0999);(26.5 volts for 25-1000 thru 25-TEA) anincrease or decrease in bulb resistance, varying the
first. Increase RPM. until light goes out and
note voltage. Decrease RPM until light flashes
magnetic field in the indicator coils.
on and note voltage. Light should come on at a 3. The oil pressure instrument circuit contains an

voltage between 12.4 and 12.6 volts (25-0001 electn’cal instrument used as a reference, and a

thru 259999);(26.4 and 26.6 volts for 25-1000 transducerwhich varies resistance with pressure.
thru 25-TEA). 4. Fuel Flow is indicated on either an electrical
instrument using a pressure transducer which varies
24-34-00 POWER PLANT CIRCUITS
resistance with pressure or with an electrical
i. Starter-ignition Circuit. The starter-ignition switch instrument which counts electrical pulses produced by
has five positions: OFF, R (right), L (leff), BOTH, and a turbine flow transducer.
START. In the OFF position both magnetos are
grounded. At the R position the left magneto grounds.
At the L position the n’ght magneto grounds. At the
BOTH position both magnetos are HOT and the

24-34-00
SERVICE AND MAINTENANCE MANUAL M20K MOONfi~ AIRCRAFT CORPORATION

OLDWILLWAYNE
2435-00 -LIGHTING CIRCUITS remain ON for appro>dmately 2 minutes. The rocker
switch is connected through the MASTER switch on
Navigation Lights. A circuit breaker switch on the these aircraft and inten~or lights will gp out when the
flight panel controls the navigation lights. The GEAR MASTER switch is turned OFF if door Is closed.
DOWN, GREEN, annunciator light is dimmed when
NAV Light switch is ON. 7. Map Light. A push button switch on top of control
wheel center section controls map light (S/N 25-0001
2. Landing/Taxi Lights. A circuit breaker switch
thru 25-1224. S/N 25-1225 thru 25-1230 have a
(25-0001 thru 25-0009) (split switch for 25-1000 thru switch/rheostat on control wheel to control light 3
25-~230) on flight panel controls the landing/taxi lights brightness. The cPpilots map light is optional.
in the lower engine nacelle (25-0001 thru 25-1224), in
each wing leading edge (25-1225 thru 25-1230). 24-36-00 LANDING GEAR CIRCUITS
3. Cabin Lights. A three-position (Bright, Off, Dim) 1. Limit switches and relays operate the landing gear
rocker switchadjacent to the door, in headliner, actuator a 12 volt DC (250001 thru 25-0999) (24 volt
controls cabin forward inten’or lights. for 25-li)00 thru 25-TEA) reversible motor assembly. A
landing gear air pressure safety switch, actuated by
CAUTION
pitot air pressure, prevents landing gear retraction until
On S/N 25-0001 thru 25-1224 this light switch is a safe flying speed is attained. The landing gear
connected directly to the battery. The switch control switch operates the actuator motor through the
MUST BE TURNED OFF to keep from safety switch and relays. Wnen the landing gear
discharging the battery. control switch is up and a safe flying speed has been
attained, the safety switch closes to activate control
Aircraft SIN 25-1225 thru 25-1999 may have a door
relay, starting the actuator. As the gear reaches the up
switch and timer mechanism that illuminate forward set ,,d locked position, a mechanical stop opens the up
of inten’or lights while cabin door is open. After door is limit switch and the actuator stops. When the landing
closed, if rocker switch is left ON, forward interior lights gear control switch is placed in the down position, the
will remain ON for appro>a’mately 2 minutes,
gear motor down-relay closes and the actuator starts.
The rocker switch is connected through the MASTER When the gear reaches the down-and-locked position
switch on these aircraft and forward inten’or lights will the mechanical stop opens the dawn limit switch’anci
no OFF when MASTER switch Is turned OFF if door b actuator stops. The gear-up limit switch controls the
closed,
landing gear un-safe light. The red light comes on
4. Anti-Collision Lights. A circuit breaker switch when gear is in transit. The green light comes on when
controls the white anti-collision strobe lights. the gear reaches down-and-locked position; the
5. Instrument and Radio Lights. Rheostats control gear-down limit switch controls the green gear-down
and radio lights. The flight panel light.
rheostat controls the compass light. 2. Gear Safety By-Pass Switch. The gear will not
Lighting loads are controlled by transistors biased with retract if airspeed above the set limit has not been
manuallY controlled rheostats. The transistors can be attained when gear handle is placed in the UP position.
checked by the following methods: A waming hom will sound and both "GEAR DOWN"
and GEAR UNSFE" lights will illuminate. Push and
A. Conned ohmeter between the emitter and the
hold the red button switch beside the landing gear
collector- should be infinite ohms.
handle until the gear is up and both lights go out. Pull
B. Short base to collector should be a direct the circuit breaker "GEAR CONT" or "GEAR RELAY
short, zero ohms, to stop warning hem. Reset circuit breaker prior to
e~xtending gear.
NOTE
If readings are incorrect reverse the loads. 243~90 FUEL SYSTEM CIRCUTTS
CAUTION
The fuel system has an electric, auxiliary fuel pump.
Care must be exercised to prevent shorting The fuel quantity indicating system is comprised of two
light wires when installing or replacing transmitters in each fuel tank and two fuel quantity
instruments. Shorted wires will cause blown
gauges (L 3 R) in the instrument panel.
fuses or burned out transistors in the control
box. 1. Fuel Pump Circuits. A single auxiliary fuel pump is
controlled by 3 switches for different functions:
6. Baggage Compartment Lights. A three-position A. Engine Pn’me This switch, located on
(Bright, Off, Dim) rocker switch in headliner controls instrument panel above the throttle control, when
the aft interior lights. depressed and held "ON" causes fuel to be vaporized
and injected directly into the induction manifold and
CAUTION
On S/N 25-0001 thru 25-1224 this light switch is
engine cylinders for starting.
connected directlyto the battery. The switch B. Low Boost This switch is located on instrument
MUST BE TURNED OFF to keep from panel, lower left, near master switch and is used when
discharging the battery. switching fuel tanks and certain emergency situations.
Aircraft S/N 25-1225 thru 25-1230 may have a door
switch and timer mechanism that illum~nate aft set of
inten’or lights while baggage door is open. After door is
closed, if rocker switch is left ON, aft interior lights will
24-35-00
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
Low Boost Auxiliary fuel system
(1) adjustment (b) Set mWure control "FULL RICH" and throttle
S/N 25-0001 thru 25-0780: closed.

(a) Install a calibrated pressure gauge, tee into the (c) Conned a voltmeter to the aircraft bus.
fuel line between the eledric fuel pump and the engine.
(d) Tum "MASTER" switch ON and assure that bus
NOTE voltage is at least 12 voBs(25-0001 thru 25-0999);(24
The fuel line must remain connected to the volts for 25-1000 8 ON) minimum. An e~demal power
engine with the pressure gauge ’T’ed into the source may be connected to the aircraft system if
line. voltage is less than12 volts (25-0001 thru 25-0999);
(24 volts for 25-1000
8 ON).
(b) Insure that the aircraft master switch is in the
OFF position, mixture full rich, throttle at idle. (e) Turn "LO BOOST" switch ON.

(c) Disconnect the eledn’cal wire from the circuit (O Remove rubber plug from "Boost Pump
protector. Conned the negative lead from an external Regulator"and adjust tn~m pot for a calibrated pressure
power source to ground; connect the positive lead to gauge reading of 6 to 8 P.S.I. (Reference Figure 24-2.)
the slide resistor HIGH POSITION. (Reference F~ure
24-1.)
(d) Using a calibrated voltmeter, adjust the e~demal
power source to indicate 13.75 .25 volts (250001
thru 25-0999) (28.6 .25 for 251000 thru 25-TEA)
direct current VDC) at the auxiliary fuel pump. Note the
voltage reading on the external power source
voltmeter.
(e) The calibrated pressure gauge shall indicate
23,5 to 24.5 P.S.I.
nn\
(f) Conned the positive lead to the slide resistor
LOW POSITION. Adjust the power supply voltage level
to 13.75 .25 volts (25-0001 thru 25-0999);(28.6
t~-.25 volts for 25-1000 thru 25-TEA). Adjust the slider

1
on the variable resistor to obtain a pump pressure of 6
to 8 P.S.I. Secure the slider.

DECREASE
~REASE VOLTAGE
VOLTAGEI(I
HIGH
POSITION

LOW BOOST PUMP VOLTAGE REGULATOR

TO
PUMP At- I ~--LOW POSITION
S/N 25-0781 thru 25-1230 FIGURE 24-2

LOW BOOST PUMP ADJUSTING RESISTOR

NOTE
S/N 25-0001 thru 25-0780 Turn pot clockwise to increase pressure.

NOTE
Boost Pump Regulator located on top of power
plant controls approximately 8 inches aff of the
NOTE face of console where controls come through.
Slide resistor located on console tubular Access to rubber plug and adjustment is from
structure adjacent to pilots right knee, behind top of panel after glareshield removal.
riveted panel.
C. High Boost This switch is located adjacent to
low boost and is colored red. A protedive cover is
placed over a to prevent inadvertent activation. The
(2) Low Boost Auxiliary Fuel System Adjustmen switch can be held on for tempomry use or the cover
S/N 25-0781 thru 25-TEA.
rotated and switch depressed for continuous use when
(a) Install a calibrated pressure gauge in the fuel engine driven pump has become inoperative.
line between the electric fuel pump and the engine.
2. Fuel Quantity Gauge Circuits. Fuel level changes
NOTE vary fuel quantity transmitter resistance that operates
The fuel line must remain connected to the the fuel quantity gauges. The master switch adivates
engine with the pressure gauge ’T’ed into the the fuel quantity indicating system. Refer to Sedion
line, 2&43-00 forAdjustment Procedures.

24-37-00
10
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
26~38-00 -MISCEUANEOUS CIRCUITS CURRENTSENSOR -ADJUSTMENT
Effective SIN 25-2000 thru 25-TEA
i. Tum Coordinator Circuit.
The tum coordinator is a flight instrument which A. Remove front cover from Annunciator.
operates from an electrical power source.
B. Start engine and Nn at moderate speed until
2. Heated Pitot Tube. ammeter charge rate drops to near zero.
A circuit breaker switch controls the pitot tube heater.
C. Tum all equipment OFF avionics, lights, pitot
3. Hour Meter (Optional).
heat, etc., only the equipment connected to buss is
so
The hour meter operates directly from the altemator
operating (instruments only).
"Aux" terminal through a fused wire on SM 25-0001
thru 25-0445. SM 25-0447 and later models hour D. Tum Right Altemator field switch OFF.
meter operates from the electn’c tachometer. A Hobbs E. Adjust LH potentiometer clockwise until light
meter may be installed as an option. illuminates; then counterclockwise until light is
4. Cigar Lighter. e>dinguished.
A cigarlighter is mounted in the n’ght instrument panel. F. Tum Left AReemator OFF and turn Right
5. Current Sensor (Monitor). Alternator ON.

(Reference Figure 24-3) G. Repeat Steps E 3 F with RH potentionmeter.

H. Turn both attemators ON; if either light
illominates, adjust apppropn’ate potentionmeter slightly
counterc(ockwise until light is e>dinguished.
I. Replace cover and secure in original location.

INSTRUMENT LIGHT BULBS (TYPICAL) ALTERNATOR NULL ADJUST. SCREWS

O (3
NORM CAL

000 0000

O O b 000 O
O O b o
LEFT FUEL (LH)CHIO-ALT AD3-CHI i (RH)

Fuel Warn. Adi. Screws

FIGURE 24-3 CURRENT MONITOR ADJUSTMENT

24-39-00 -TROUBLE SHOOTING CHARTS

2439-01 -ALTERNATOR TROUBLE SHOOTING

TROUBLE PROBABLE CAUSE REMEDY

Alternator over-charges battery; Regulator faulty. Check bus voltage with engine
battery uses excessive water. running. Observe aircraft
ammeter. Ammeter should
indicate near zero after ten
minutes of engine operation.
Replace voltage regulator if
defective.

ALT FIELD circuit breaker trips. Circuit shorted in wiring. Disconnect lead from pin A or 1 of
regulator, and reset circuit
(25-0001 thru 25-0999; Pin 5 for 25-1000 thru 25-1230) breaker. If circuit breaker trips,
check win’ng.
24-38-00
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
Repair as required. If breaker does

not tn’p, replace regulator.

Reconnect lead to regulator. Master
switch to ON and check for 12V at
pin A or 1 of regulator. Repair
win’ng if no voltage is present.

(25-0001 thru 25-0999; Set alternator field 8 MASTER switch to ON 8 check for 24 volts at Pin 5 of regulator
(25-1000 thru 25-~230)

ALT circuit breakertrips. Short circuit in win’ng. Disconnect lead from post of
aRemator, and reset ALT circuit
breaker. If circuit breaker tn’ps,
check wiring between alternator and
circuit breaker.
Short circuit in aRemator. Reconnect lead to post of
altemator.

WARNING
ENSURE THAT MAGNETO SWITCH IS OFF WHEN TURNING PROPELLER.
Rotate propeller by hand to rotate
altemator through 360 degrees of
travel. If circuit breaker tn’ps replace
aitemator,

Altematorwill not keep Battery malfunction. i. Start engine and adjust for 1500

battery charged. RPM. Ammeter should indicate a

heavy charge rate with all electrical
equipment tumed off. Rate should
taper off in 1 3 minutes. A voltage
check at the bus should indicate a
reading of 13.75 to 14.0 volts.
m
If charge rate tapers off very
quickly and voltage is normal, check
battery for malfunction. If ammeter
shows a low charge rate or any

discharge rate, and voltage is low,

25-0001 thru 25-0999; 28.6 to 28.8 volts for 25-1000 thru 25-1230.
proceed to step 3.

Defective wiring. 2. Check voltage at A or 1 terminal of

**f*
regulator with master svvitch ON.
Meter should indicate bus voltage. If
voltage is not present, check win’ng
between regulator and bus.

25-0001 thru 25-0999; ...~terminal 5 for 25-1000 thru 25-1230, with Att.nd. a Master Switch ON.

Regulator faulty. 3. Remove connector from regulator

and start engine.
**H"
25-0001 thru 25-0999;pins 5 8 7 for 25-1000 thru 25-1230.

Momentan’ly jump A 8 B or 1 and 2

pins together on the plug.
Aircraff ammeter should show heavy
rate of charge. If heavy charge rate
is observed, replace regulator. If
heavy rate is not observed, proceed
to step 5.

24-39-00
12
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
CAUTION
Pull alternator field GIB. Start engine; while at idle RPM reset GIB. Slowly increase RPM while
volts for (25-1000 thru
monitoring bus voltage. DO NOT EXCEED 14 vo~ts,(25-0001125-0999);28
25-TEA).
4. Check resistance from F2
Defective wiring regulatorto
a8emator. terminar of attemator to pin B or

2 cc of reg. plug. Normal

indication is a very low resistance.
If reading indicates no, or poor
continuity, repair or replace wiring
from regulator to altemator.

+25-0001 thru 25-0999; field terminal for 25-1000 thru 25-1230.

cc25-0001 thru 25-0999; Pin 7 on 25-1000 thru 25´•1230.

Defective alternator. 5. Check resistance from F2 to F1

term. of attemator. Normal
indication is 3 4 ohms. If
resistance is high or low, repair or
replace alternator.
25-0001 thru 25-0999; case to field, 25-1000 thru 25-TEA.

6. Check resistance from F2

terminal of attemators to altemator
case. Normal indication is high. If

low,repair
resistance is or replace
a~1250001--25-0999)

243992 GENERATOR TROUBLE SHOOTING. (For Standby Generator) (25-0001 thru 25-0999)

TROUBLE PROBABLE CAUSE REMEDY

within Generator operating residual. Check for loose or high resistance
Generator operating on

but connections; clean and tighten

speed range,
t~ated voltage
terminals.
outputlow.
Clean and tighten all electrical
Loose or high-resistance electrical
connections. connections.
Excessively wom brushes. When brush wears down to .700
inch, replace with a new one.Do
not use abrasives of any
descn’ption to seat brushes.
Brushes binding in brush box Brushes should fd free without
excessive side play in brush
boxes. Clean binding brushes and
brush boxes with a cloth
moistened in Varsol or unleaded
gasoline.
Excessive brush side play in Replace brushes.
brush box
Brushes not properly seated. Reseat brushes.
Low brush spn’ng tension. Brush spn’ng should bear centrally
on top of brushes, insuring full
brush contact with face of
commutators.
commutator. Clean commutator with a cloth
Dirty
moistened in Varsol or unleaded
gasoline.
commutator. Tum down or replace commutator.
Scored or pitted
24-39-02
13
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
Shorted or open armature cells. Replace generator or armature.
Improper voltage regulator Adjust or replace regulator.
operation.

Generator operating within Win’ng not properly connected. See electn’cal system win‘ng
rated speed range, but diagram.
voltmeter indicates zero.

Generator operating within Unstable voltage regulator Replace voltage regulator. Use
rated speed range, but operation. Same as listed with remedy for "Generator operating
voltage output is erratic. "Generator operating within within rated speed range, but
rated speed range, but voltage voltage output low."above.
output low." above.

Excessive sparking at Same cause as listed with Same remedies.

generator brushes. "Generator operating within

rated speed range, but voltage
output low." above.

Loose connections. Tighten connections.

Burned-out in line fuse. Defective win’ng. Check wiring for shorts and repairs.

24-3943 BAITtRY TROUBLE SHOOTING

TROUBLE PROBABLE CAUSE REMEDY

Discharged battery. Battery worn out. Replace battery.

Improper charging rate setting. Reset charging rate.
Excessive discharging. Tum off some equipment when
aitemator is not charging. Decrease
starter usage by using e>demal power
whenever possible.
Standing too long. Remove and recharge battery.
Equipment accidentally left on. Remove and recharge battery.
Impure electrolyte. Replace battery.
Short circuit (ground) in win’ng. Check wiring.

Low charging rate. Adjust voltage regulator.

Cracked cell jars. Loose hold-down bracket. Replace battery and secure firmly.
Frozen battery. Replace battery.

Compound on top of battery Charging rate too high. Reduce charging rate by adjusting
melts. voltage regulator.

Electrolyte runs out of vent Too much water added to Drain battery and keep at proper
plugs, battery and charging rate too level; adjust voltage regulator.
high.

Excessive corrosion inside Spillage from overfilling. Flush container with baking soda

container, solution.
Leaking or clogged vent lines. Repair or clean vent lines.
Charging rate too high. Adjust voltage regulator.
24-39-03 REV 3 97
14
SERVICE AND MAINTENANCE MANUAL M20K MOONE/ AIRCRAFT CORPORATION

OLDWILLWAYNE
Battery freezes. Discharged battery. Replace battery.
Water added and battery not Always recharge battery for 1/2
charged immediately. hour following addition of water in
freezing weather.

Leaking battery case. Frozen electrolyte. Replace battery.

Reversed battery polarity. Cables connected backwards on Battery should be slowly

discharged completely, then
battery or charger,
charged corectly and tested.

rate too high. Correct charging rate.

Excessive water consumption Charging
all cells.

Excessive water consumption Cracked jar. Replace battery.

one cell only.

2639-04 STARTER TROUBLE SHOOTING

TROUBLE PROBABLE CAUSE REMEDY

Check and recharge battery if
Motor does not operate. Low battery.
necessary.
Defective, improper, or loose wire Refer to electrical win’ng diagram
connections. and check all wiring.
Binding, wom improperly seated BNshes should fit free in brush
brushes; brushes have boxes without excessive side
excessive side play. play. Clean binding brushes and
brush boxes with a Varsol
mo~tened cloth. A new brush
should be run-in until at least 50
percent seated; however, if
facilities are not available for
Nnning in brushes, seat brush by
inserting a stn’p of No. .0000
sandpaper’between brush and
commutator with sanded side next
to brush. Pull sandpaper in
direction of rotation, being careful
to keep it in same contours as

commutator.
*CAUTION
Do not use coarse sandpaper or emery cloth.
After seating, thoroughly clean
brushes and commutator to

prevent excessive Keep

wear.

motor bean’ng free from sand or

metal particles.
Dirty commutator. If commutator is rough or dirty,
smooth and polish with No. 0000
.sandpaper. If too rough and pitted,
remove commutator and turn
down. Blow out all foreign
material.
Remove and replace with an
Shotted, grounded, or open
armature. armature known to be in good
working order.

24-39-04
15
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
Grounded or open field circuit. Test and repair circuit if possible or

replace with new parts.

Slow cranking speed. Worn, rough, or improperly Disassemble, clean, inspect, and
lubricated motor or starter. relubn’cate components, replacing
ball bearing ifwom.
Same causes as listed with Same remedies.
"Motor fails to operate."

Excessive motor brush Binding, worn, or improperly Repair as outlined above.

arcing, seated brush or brushes have

excessive sideplay.
Dirty, rough, pitted, or scored Clean as outlined.
commutator.

Excessive motor brush wear Rough or scored commutator. Remove and tum down commutator

and arcing, on lathe.

Armature assembly not Reface commutator.
concentn’c.
24-39-05 ANNUNCIATOR TROUBLE SHOOTING (SIN 25-0001 thru 25-1224)
the Mooney
The following Is a brief failure/cause analysis which pertains to the annunciator (LAI P/N 500D0061) on
M20K. Each cause is listed in probable order. All designator references are made from iAl drawings 710D0125A,
900D0134 and 900D0135.
1 The "gear-down" lamp will not light dun’ng ’ITEST" but will light with the gear-down.
CR1 CAssy A2) open
2. The "gear-down" lamp will not light dun’ng ’ITEST" or with the landing gear down.
Filament of DSI (Assy A2) open
3. The "gear-down" lamp is dim when the position lights are off.
CR24 (Assy A?) open
4. The "gear-unsafe" lamp will not light dun’ng ’’TEST’ but does light when the gear is in transit.
CR3 (Assy A2) open
5. The "gear-unsafe" lamp will light during ’rrS‘r’ but not when gear is in transit.
CR2 (Assy A2) open
6. The "gear-unsafe" lamp will not light during ’7ESr’ orwhen the gear is in transit.
Filament of DS2 (Assy A2) open
CR2 (Assy A2) and CR3 (Assy A2) open
7. The "left low fuel" lamp will not light during rEST" or in a left low fuel situation.
Filament of DS3 (Assy A2) open
02 (Assy Al) defective
U1 (Assy Al) defective
Wire from P1-7 (Assy Al) to left fuel gauge open
3. The "left low fuel" channel functions properly but the lamp is always dim.
CR22 (Assy A2) open
9. The "left low fuel" lamp flickers on and off.
S1 (Assy Al) is in "Cal" position instead of"Norm" position
Intermittent ground on the wire from P1-7 (Assy Al) to the left fuel gauge
C2 CAssy Al) defective

light dun~ng "TEST’ only when the left fuel tank is full.
in. The "left low fuel" will not
RiO (Assy Al) should be replaced with a 47K, 1/4 watt, 5% resistor
11. The "n’ght low fuel" lamp will not light during ’ITEST" or in a n’ght low fuel situation.
Filament of DS4 (Assy A2) open
06 (Assy A?) 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 always dim.
CR23 (Assy A2) open
24-39-05
16
 M20K MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
(ANNUNCIATOR TROUBLE SHOOT1NG (S~ 25-0001 thru 25-1224)- conY.)

13. The and off dun’ng flight.

"right low fuel" lainp flickers on
S1 (Assy Al) is in "Cal" position instead of"Norm" position
An intermittent ground on the wire from P1-8 (Assy Al) to the gauge
C3 ~Assy Al) defective
is full.
14. The"right low fuel" will not light dun~ng YEST only when the right fuel tank
R10 (Assy Al) should be replaced with a 47K, 114 watt, 50~ resistor
"left low fuel" lamps light before low fuel situation has occured.
i 5. The "right low fuel" orthe a

Recalibrate the appropn’ate channel

CR1 (Assy Al) open
low fuel" channels stay dim when they annunciate a low fuel situation or
18. Both the "left low fuel" and the "right
during ’7EST".
03 (Assy Al) defective
05 (Assy Aidefective
U2CAssyAl defective
04 (Assy Al) defective
CR22 (Assy Al) and CR23 (Assy Al) open
17. Neither the "left low fuel" nor the "right low fuel" lights dun’ng ’ITEST".
CR1 (Assy Al) shorted
U1 CAssy Al) defective
’7EST’ but does annunciate high or low vacuum situation.
i8. The "high low vac" lamp will not light during a

CR14 CAssy Al) open

19. The "high low vac" lamp will not light dun’ng ’ITEST’ or in a high or low vacuum situation.
Filament of DS5 (AssyA2) open
07 (Assy Al) defective
low vacuum situation but does light in a high vacuum situation.
20. The "high low vac" lamp will not light in a

08 (Assy Al) defective

CR12 and/or CR13 (Assy Al) open
21. In a low vacuum situation the "high low vac" lamp lights but does not flash.
CR16 (Assy Al) open
08 (Assy Al) defective
U2 CAssy Al) defective
CR1 (Assy Al) shorted
22. The "high low volts" lamp will not light dun’ng ’ITEST’ or in a high or low voltage situation.
Filament of DS6 CAssy A2) open
Q10 (Assy Al) defective
09 (Assy Al) defective

23. The "high low volts" lamp will not’’TEST’ but does annunciate a low or high voltage situation.
CR20 ~Assy Al) open

24. The "high low volts" lamp lights but does not flash in a low voltage situation.
CR17
~ssy Al) open
08 (Assy Al) defective
U2 (Assy Al) defective

25. The "high low volts" lamp will not light in a over voltage situation
CR21 (Assy Al) open

28. The "high low volts" lamp flashes before a low voltage situation has occured.
R42 (Assy Al) out of calibration
U2 (Assy Al) defective
CR1 (Assy Al) open
27. The "high low volt" will not light in a low voltage situation.
R42 (Assy Al) out of calibration
U2 (Assy Al) defective
CR19 (Assy Al) open
08 (Assy A?) defective
CR1 (Assy Al) shotted

28. The "alt air" will not light during ’ITEST’ or in normal operation.
Filament of DS8 (Assy A2) open
CR6 and CR7 (Assy A2) open
24-3405
17
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
ANNUNCIATOR TROUBLE SHOOTING (S/N 25-0001 thru 25-1 224) conY.)
29. The "alt air" will not light dun’ng ’’TEST" but does in normal operation.
CR7 CAssy A2) open
30. The "alt air" will light dun’ng "TEST’ but not dun’ng normal operation.
CR6 (Assy A2) open
31.The "area nav" is the only channel that lights during TEST’. "area nav" if used, effectivity 250001 thru 25-0717;
"start power on" (effectivity 25-0718 thru 25-1224) have no "TEST" indication.
Q1 (Assy Al) defective
CR2 CAssy Al) open
32. Once dimmed the "low fuels" cannot be reset to bright by momentan’ly depressing the "TEST" switch.
CRI? (Assy Al) open
33. Neither the "high low vac" or the "high low volts" will flash when low vacuum and/or low voltage occurs.
08 (Assy Al) defective
U2 (Assy Al defective
CR? (Assy Al) not suppling +5 VDC
C5 (Assy Al) aefective~
34. All the channels, except for "area nav", light up when the landing gear is e~dended.
CR1 (Assy A2) shorted
24-39-06
-ANNUNCIATOR TROUBLE SHOOT1NG (S/N 25-1225 thru 25-TEA)
The following is a brief operational analysis which pertains to the IA.I. annunciator on Mooney M20K, S/N 25-1225
thru 25-TEA.
1.0 GENERAL the internal test line, TEST-, and the diode isolated
OUTTEST-. The dimmer circuit, applicable to certain
This document is intended to be a guide to assist a channels, requires a bias source, DIMBIAS, with a
service technician in understanding the theory and magnitude of 12 VDC to dim the applicable ACTIVE
operation of International Avionics, Inc. (IAl) Part channels, approximately 3 VDC to maintain the dim
Numbers, 9500326000 8 9500326001 annunciators. It level of those channels previously dimmed, and near 0
is not intended to serve as a bench service aid in that VDC to reset the dimmed channels to a bright
reference designators in various Figures are not condition. The channels having the capability of being
consistent with those found in actual annunciators. dimmed by the above circuitry are channels x, x,x, x, x,
Service literature is available from International x, and x Channel i, Landing Gear, dims by means of a
Avionics, Incorporated (IAl), 1611 N. 1-35, Suite 428, separate circuit and is discussed in Section 4.0 below.
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 paragraphs address nine (9) basic 3
ct
circuits which, used singularly or in multiple
combinations, compn’se the annunciators. These
paragraphs are as follows:
"";i J
Paragraph 2 Power Supply, with Test 8 Dim
switches
Paragraph 3 Flasher
Paragraph 4 Landing Gear Indicators
Paragraph 5 Left and Right Low Fuel
Paragraph 6 HiRo Vac
Paragraph 7 Left Altemator/Low Volts/Over Volt
Paragraph 8 Right Alternator/Over Volt
Paragraph 9 Typical Positive Apply W/Dim
Paragraph 10 Typical Positive Apply W/O/Dim.
2.0 POWER SUPPLY J]
The Power Supply, shown in Figure i, providesl2 ps

VDC, voltage protection by means of CR1,

la
reverse
spike and overvoltage filten’ng 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 12 VDC, integrated circuit regulator. Output filtering is
provided by %2. The Test Switch, S1, switches
unflltered 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
24-39-06
18
 M20K MOONC/ AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
Lights are on, however, CH1RET is also +28 VDC and
With both the Dim Switch and Test Switch relaxed,
transistor Q3 is in saturation and 02 is off, giving CR9 switches this return path off, the retum path for the
GEAR DOWN lamp being through Ri5 to Ground and
DIMBIAS a value of approximately 9 VDC. When the
Dim Switch is depressed 03 comes out of saturation GEAR DOWN now illuminates at reduced brilliance.
and DIMBIAS n’ses to 12 VDC, and when the Test The GEAR UNSAFE channel accepts +28 VDC,
Switch is depressed 02 saturates and DIMBIAS drops INPOS2, through isolation diode CRIO, illuminates at
to near 0 VDC. In the event that both switches are
full brilliance and does not dim. A test signal, TEST+ is
depressed simultaneously, the 0 VDC value of applied to both GEAR DOWN and GEAR UNSAFE
DIMBIAS will prevail and the dimmed channels, with through CR8 and CR11 respectively.
the exception of Channel i, are reset to a bright
condition.
CR7
3.0 FLASHER
In4ees

The Flasher, shown in Figure 2, provides the circuit to i rnPosi

flash the outputs of the left and n’ght alternator

warnings, the low voltage waming and the low vacuum CR8
LI1PPOSI

warning. The flasher consists of an astable oscillator DSI

driving an NPN common emitter connected transistor, 73~7
Q4. T711s allows the open collector of 04, identified as
FLASH, to sink the drive from the output amplifiers of
the appropn’ate warning channels. CR9

CH1RET

POS1R
R1S
28UDC
1BVDC I

jR13 I
331( 2. 21
R14
331 CRi(j
FLRS
~wceos
lnPOS2
1/4-11(33382
Ri2
U2 P4
4. 71 tnPPOS
CRI1
cNeeQS
2n3eisl I IPEST+
RS
CS R10 j I -I I I FIGURE 3 tRNDlnG GE~R IWDICMORS

;214FD 331 i 331(

5.0 LEFT AND RIGHT LOW FUEL

BIGURE Z rtAsusR The Left and Right Low Fuel circuits are shown in
Figure 4. The left and the right channels are similar,
and only the left channel will be discussed herein.
Signals from the junction of the left and n’ght fuel
transducers and the left and n’ght fuel quantity gauges
are applied, respectively, to each of the inputs
INPOS3
4.0 LANDING GEARINDICATORS and INPOS4. This signal is an analog signal that
The Landing Gear Indicators, shown in F~ure 3, indicates the quantity of fuel measured, the typical low
provide the status of the landing gear position, that is, fuel point being on the order of 0.1 volt. The low fuel
circuits however, annunciate an input up to
whether the landing gear is Down or not and whether can,
the landing gear is safe or unsafe, unsafe being in approximately 0.7 volt. The input, INPOS3, is applied
transit. The circuit shown is the identical circuit that has through an isolation resistor R55 to the inverting input
been used for many years in the iAI annunciators used of open collector comparator U5:C. The input is
on Mooney aircraft. The GEAR DOWN channel compared with the set point effected by the setting of
dimmed for night operation; however, in the interest of R51, accessible through the front of the annunciator,
reliability, the dimming circuit is separate from the and, when the input is less than the set point, the
dimming technique used on the other dimmed comparator’s output is allowed to rise by means of the
channels. The gear down signal, +28 VDC, is applied pull-up resistor R54 and the network R48, R49, and C9.
through isolation diode CR7, to the INPOS1 input and Feedback res~tor R53 provides a small amount of
CH1RET is returned to the Nav Light bus. Wnen +28 hysterisis to preclude oscillation at the transition point.
VDC is applied to INPOS1 and the Nav Lights are off, The rising output of U5:C is applied to the
the Impedance of this point is very low due to the low inverting input of open collector comparator U5:B and is
filament resistance of the Nav Light bulbs, and GEAR compared with a reference voltage of approximately 6
DOWN illuminates at near full bn’lliance. When the Nav VDC. When U5:B switches its output to ground QiO
24-39-06
19
MOONEY AIRCRAFT CORPORAT1ON M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
thus reducing Ule delaylo approdmately 2 seconds. In
83 ;;z i9 order to calibrate the law fuel channel the set point,
3
B a
R51, is adjusted with the screwdriver adjustment
I%
f accessible through the front of the annunciator while
there is a preset number of gallons in the tank. The
time delay must be removed from the circuit by moving
S3, accessible through the front of the annunciator,
4 from the NORMAL position to the CALIBRATE
ae i‘9 I f ~r position. This opens the retum for capacitor C9 and the
indication on the L LOW FUEL channel will not be
delayed. After calibration is accomplished, restore the
time delay by moving S3 from the CALIBRATE position
back to the NORMAL positio?. The position S3 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
kt ~I I P ~g FUEL. With S3 in the NORMAL position there is a
delay of approximately 2 seconds in illumination, but
with S3 in the CALIBRATE position there is no delay in
pa 1 9 1~ B~
annunciate low fuel are the same circuits that have
been used for many years in IAI annunciators used on
Mooney aircraft. The method of dimming however, has
been changed and e>cpanded from what i~as been used
in the past. In the past only the low fuel channels
sr I 1 s~i s~
dimmed, excluding GEAR DOWN discussed above,
while now the dimming has been e~panded to include
X
additional 5 channels. From the perspective of the pilot
cic ~x 5 the operation is the same, depress the DIM switch and
active channels dim, depress the TEST switch and
active dimmed channels return to bright. When a
I~ dimmed channel is e>dingu~hed and then reactivates it
will reactivate bright. The method to accomplish this,
however, is considerably different from the past. Each
eb channel to be dimmed is driven by a transistor, in this
s~
g case 08 which returns the lamp to ground through two
parallel paths. The path to provide a dim indication is
np through resistor R29 which reduces the brilliance of the
lamp. In the bright mode R29 is shorted by 06 and
nH g ,a CR13 which provide a low impedance path to ground.
Transistor 06 is controlled in condudion by a latch
oX
95 composed of U3 and as associated resistors R22, R23,
a 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 DIMBIAS near 3 VDC, the
output of Us will be high, thus dn’ving Q6 into
conduction. When the DIM Switch is depressed
2~Xn momentan’ly DIMBIAS goes high to 12 VDC and U3
I f switches its output low and latches through R26. This
low output removes the dn’ve from 06 and DS3 dims.
When the TEST Switch is depressed momentarily,
DIMBIAS goes low and U3 switches its output high,
conducts and drives 08 into saturation to light the L latches through R26, and drives 06 into conduction.
LOW FUEL channel lamp, DS3. The Q10 08 network When the channel deactivates, 08 opens the return to
is required to provide the transition between the internal ground and DIMIN3 rises which returns latch U3 to a
12 VDC and aircraft +28 VDC. The delay provided by high output state.
the charge of C9 through R48 and R49 provides
6´•0 HULOVAC
filtering to preclude false annunciation in rough air.
When the fuel level rises, due to sloshing in the tank Th, Highnow Vacuum circuits are shown in Figure 5.
and U5:C switches to a low output state, C9 is This channel is designed to accept two +28 VDC
discharged rapidly through R49. The delay time of the signals, one from a low vacuum sensor and one from a
char~ing network provides a delay In low fuel high vacuum sensor. ~hen low vacuum is detected the
annuncfation of approximately 20 seconds. A test of the annunciator will flash and when high vacuum is
functioning of the low fuel channel is accomplished by detected the annunciator will illuminate steady. A +28.
applying TEST+ through R43 CR18 to the input of VDC signal applied to LOW VAC INPUT will drive Qi?
U5:C to switch U5:C and applying TEST+ through R42 into conduction through the bias network R56, R57,
CR?5 to accelerate the charging rate of the filter C9, CR17, and CR22, thus illuminating DS9.
24-39-06
20 ALSO SEE FIGURE AS HORIZONTAL (NE~IflC)
 OLDWILLWAYNE

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 M20K MOONN AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE

DS9
3323

tASH

CR19
1NS8b5
?B
R57 CR\7 CR22

tOW UAC 6.OK INSebS 1#$865 ~3\ 911

tNPttT I LI LI ’Y)2N663S

Ri R513
6. OK
i6. BK CR4
IN$665

l-ItGH V~C OVGRRIDE

TeST+

CRBI
IN46b5

The signal FLASH will,’ however, remove this drive

signal as the flasher thus flashing DS9. A +28

cycles,
VDC signal applied to HIGH VAC OVERRIDE will
bypass the above network and drive Q11 into
conduction regardless of the state of LOW VAC
INPUT. Similarly TEST+ will drive Q~1 into conduction
regardless ofihe state of LOW VAC INPUT. The
j~e 565 !R61 28vDC~ DStO

R62
ckannel HighRow Vac does not dim. VOLT

7.0 LEFTALTERNATOR now VOLTSI CR29

R60 CR2a
OVER VOLT U6 IN4005

The Left AltematorRow Volts/Over Volts circuits are /4-UCJ302 CR23

shown in Figure 6. This channel is designed to accept
three signals, the analog signal LAINPUT from a iPs~4
current sensor, the +28 VDC signal LOVERRIDE from
the overvoltage tripped output on the left altemator
regulator, and one signal derived intemally that R63
indicates that the aircraft bus voltage is less than 26.5 CR27
VDC. When low voltage is detected internally or when IN~005
low current is detected the annunciator channel
flashes, and when overvoltage tripped detected the
annunciator channel illuminates steady. Comparator
U6 monitors the aircraft 28 VDC by compan’ng the
voltage at the arm of R68 with the regulated voltage at
the junction of R64 and R65. The output of U6, an SVDC
When low
open collector comparator is normally low. t.ssoootxxx ~.6soqqtxxx ~R78
voltage is detected the output of U6 rises and drives 573

012 into conduction through the bias network R60, u7

CR24, and CR28, thus illuminating DS10. In a /4-UC3X)2

similar to the Hi/Lo Vac channel, the signal FLASH will R72
remove this drive signal as the flasher cycles, thus ~.saoootxxx
flashing DS10. A +28 VDC signal applied to
LOVERRIDE will bypass the above network and drive _ LOWVOLTS/OVER VOLT
012 into conduction regardless of the state of the
comparator U6. Similarly TEST+ will drive 012 into
conduction regardless of the state of the comparator
24-39-06
21
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
U6. Comparator U7 monitors the output of a Hall Effect functions in a similar manner to the Left AnematorRow
current sensor which measures the left altemator VolWOver Volts circuit with the single exception that
this circuit does not detect low aircraft bus voltage.
output current. The signal from the Hall Effect sensor is
When low current is detected the annunciator channel
compared with a predetermined bias set by adjusting
R59. It should be noted that the divider ofR74, R59, flashes, and when overvoltage tn’pped is detected the
and R75 actually consists of R74, R59 in pai~ailel with annunciator channel illuminates steady. Comparator U8
R83 (see f=igure 7), and R75. The points labeled monitors the output of a Hall Effect current sensor
ALTBIASH and ALTBIASL are common to both left and which measures the right anemator output current. The
right aitemator sense circuits. As LAINPUT is reduced signal from the Hall Effect sensor is compared with a
in value below the voltage set by R59 the comparator predetermined bias set by adjusting R83. h should
U7 goes high and again drives 012 into conduction again be noted that the divider of R74, R59, and R75
through the bias network R70, CR23, and CR28, thus (see Fig 6) actually consists of R74, R59 in parallel with
illuminating DS10, but the signal FLASH will remove R83, and R75. The points labeled ALTBIASH and
this drive signal as the flasher cycles, thus flashing ALTBIASL are common to both left and right altemator
sense circuits. As RAINPUT is reduced in value
below
DS10. A *28 VDC signal applied to LOVERRIDE also
drives Q12 into conduction regardless of the states of the voltage set by R83 the comparator Us goes high
either comparator U6 or U7. Similarly TEST+ will dn’ve and drives 013 into conduction through the bias
Q12 into conduction regardless of the states of either network R82, and CR33, thus illuminating DS11, but
the signal FLASH will remove this dn~ve signal as the
comparator U6 or U7. The channel Left A~tematorRow
Volts/Over Volt does not dim. The van’able resistor R59 flasher cycles thus Rashing DS11. A +28 VDC signal
Is accessible through the front of the annunciator on IAl applied to ROVERRIDE also drives Q13 into
Part Number 9500326001, while an equivale?t variable conduction regardless of the state of comparator U8.
resistor mounted e>demal to the annunciator Is required Similarly TEST+ will drive 013 into conduction
forthe 9500326000 annunciator. regardless of the state of comparator U8. The channel
Right Aitemator/Over Volt does not dim. The van’able
8.0 RIGHT ALTERNATOWOVER VOLT resistor R83 is accessible through the front of the
The Right Alternator/Over Volts circuits are shown in annunciator on IAl Part Number 9500326001, while an
I=igure 7. This channel is designed to accept two equivalent variable resistor mounted e>demal to the
signals, the analog signal RAINPUT from a current annunciator is required for the 9500326000
the
sensor, and the +28 VDC signal ROVERRIDE from annunciator.
overvoltage tn’pped output on the n’ght alternator
regulator. This circuit is an exact duplicate of and

2VDC

R77
4. 7K

tTB~ASH
CDV8Kj(i3UR

DS11
7327

R7U rZVDCtRSH
tTBI~SL) csueeelxss
R79
IR76
~soeeurxxx
CR3B
5. ,K 2 2BR,,~,
INCUOS

CR
U8 INcYe5 4 L3
CL3 ZNb83$
(j.O(
l/o-(1C3382
RBi

R88 )6- OK
INPUT
CR 31
1BUO~MISSS
1HCe8S
OVERRIDE

TEST+

FIGURE 7 ~tTERNRTOR/OUER VOLT

24-39-06
22
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE

12 VDC r2 UDC

LP~P

i
I
DS-x

R89 F1BB
9r~
11Bb2~r
DIMOUTPUT
RB5 R98 PB7

xtnPUt
2BUDC
CR3~
~Y4DsS R91 I ,I U9
CR35 I i DI~INPUT
471(
RB1 ~-i, 915
I yl,.-nclYI1
CR36
b.D((
213819 DI~LcBmS
1(4SIS

TeST+
FIGURE 8 T/PICAL POSITIVE.APPLY W/DIM

9.0 TYPICAL POSITIVEAPPLYW/DIM

A typical Positive Apply, Dimmable circuit is shown in
Figure 8. This channel is designed to accept a +28
VDC signal to illuminate an indicator channel and
Drovide for dimming of that channel, as well. Dimming
is accomplished in a manner similar to that descn’bed
for low fuel channel above. The input, XINPUT, is CR 313
applied through CR35 and R84 to drive 015 into YINPUT
saturation and light DS-X. TEST+ is applied through
INSb(jg
CR36 and R84 to also dn’ve 015 into saturation and
light DS-X. These 5 channels may be dimmed by
DS-Y
depressing the DIM switch to dim the active channels. CR37
Depressing the TEST switch returns the active dimmed TESTt 7327
channels to bright. V\hen a dimmed channel is
extinguished and then reactivates a will readivate INSbbS
bright. Each channel to be dimmed is dn’ven by a
transistor, in this case 015 which returns the lamp to
ground through two parallel paths. The path to provide
a dim indication is through resistor R85 which reduces
the brilliance of the lamp. In the bn’ght mode R85 is
shorted by 014 and CR34 which provide a low
impedance path to ground. Transistor 014 is controlled
in conduction by a latch composed of U9 and its F IGURE 9
Y
associated resistors R86, R87, R88, R89, R90 and R91
as well as the signals DIMBIAS and DIMINPUT. If the APPtY GJ O D I
YP1CRZ, POSITIVE
channel is active DIMINPUT willbeneargroundand
with DIMBIAS near 3 VDC, the output of U9 will be
high, thus driving 014 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 dn’ve from
014 and DS-X dims. When the TEST Switch is
depressed momentan’!y, DIMBIAS goes Low and U9
switches its output high, latches through R87, and +28 VDC s~nal to illuminate an indicator channel, but
drives 014 into conduction. When the channel does not provide for dimming of that channel.
deactivates, 015 opens the retum to ground and
DIMINPUT n’ses which retums latch U9 to a high output The input, YINPUT, is applied through CR38 to light
DS-Y. TEST+ is applied through CR37 to also light
state.
DS-Y.
10.0 TYPICAL POSITIVE APPLYWIOIDIM
A typical Positive Apply, Non-Dimmable circuit is
shown in Figure 9. This channel is designed to accept a

24-39-06
23
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
24-60-00 ELECTRICAL LOAD DISTRIBUTION STANDBY GENERATOR Optional (25-0001 thru
25-0999) When attemator failure occurs, the altemator
24Si-00 POWER DISTRIBUTION SYSTEM
output and battery circuit breakers must be pulled to
The power bus distributes direct current power to the de-energize the control relay and connect the standby
electn’cal system from the aitemator and from the generator to the standby generator bus. This will allow
battery through the battery relay. The negative battery limited equipment to be operated until aircraft can be
lead attaches to a structural ground on the airframe, landed and the alternator system repaired.
Master Switch "ON" closes the relay and supplies
CAUTION
power to the aircraft electrical system.
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 Yn’p Free" type and
cannot be held in the closed position.

24-50-00
24
 OLDWILLWAYNE
C H A PT E R

FLIGHT
CONTROLS
 M20K MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CHAPTER 27

FLIGHT CONTROLS

TABLE OF CONTENTS

SUBJECT PAGE
CHAPTER
SECTION
SUBJECT

General 5
27-00-00
Aileron System 5
27-10-00
Rudder System 6
27-20-00
8
27-30-00 ElevatorSystem
Van’able Downspring System 9
27-31-00
Stabilizer Tn’m System 9
27-40-00
27-40-01 Trim System Tro;bleshabting 11
11
27-50-00 Wing Flap System
Aileron/Rudder Inter-conned System 12
27-60-00
27-90-00 Miscellaneous
Control Surface Static Balancing 12
27-91-00
12
27-92-00 Equipment Maten’als Static Balancing
General Procedures Static Balancing 13
27-93-00
Detail Procedures Static Balancing 13
27-93-01
Control Surface Trailing Edge 15
27-94-00
Stall Warning Maintenance Practices 16
27-95-00
Trouble Shooting Stall Warning system 16
27-95-01
Brake System 17
27-96-00 Speed
Removal Replacement 17
27-96-01
Maintenance Service 17
27-96-02

27-CONTENTS
3/4BUVI~K
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CHAPTER 27

FLIGHT CONTROLS

LIST OF EFFECTIVE PAGES

PAGE DATE
CHAPTER
SECTION
SUBJECT

1/2BLANK 9-97
a’l-Effedivity
3/4BLANK 997
27-Contents
5. 9-97
27-00-00
6. 997
27-20-00
7. 9-97
27-20-00
8, 997
27-30-00
9. 9-97
27-31-00
10 9-97
27-40-00
9-97
27-40-01
12 9-97
27-60-00
13 9-97
27-93-00
14 9-97
27-93-01
15 9-97
27-94-00
16 9-97
27-95-00
17 9-97
27-96-00
18 9-97
27-96-02

27-EFFECTIVTTY
1I2BLANK
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

GENERAL
OLDWILLWAYNE
board wing Raps. The ailerons link to the control
of the
2790-00
wheel through push-pull tubes and bellcranks. Lead
The aircraft has dual Right controls and can be Rown counter-weights static balance the ailerons.
from either the pilot or co-pilot seat. Dual pairs of foot 1. Aileron Removal and Installation.
pedals control the rudder and nose wheel steering A Remove control tube attaching bolt, nut, and
mechanisms. The co-pilot pedals are removable a dual washer at aileron hem.
brakes are not installed. Push pull tubes actuate the B. Remove bolts, nuts, and washers from the
all-metal Right control surfaces. Rod-end bearings are three attaching hinges.
used throughout the Right control systems. These bear- C. Remove aileron straight aft until
by pulling it
ings are and require little maintenance other
simple hinges are clear; rotate inboard portion down and for-
than occasional lubrication. Specially designed
ward to allow aileron balance weights to clear wing tip.
aluminum-alloy extrusions, that permit Rush skin at- D. Reinstall aileron In reverse sequence of
tachment, form the leading edges of the rudder and
removal.
elevators. Electrically actuated wing Rap systems are
E. Recheck bolts for security and safety.
Installed on all models. Longitudinal pitch trim is
2- Aileron Rigging and Control Adjustment
achieved through a trim contrd system that pivots the
entire empennage around the tailcone attachment (S/N 250001 thru 25-0705).
A. Use a straight edge (A), (Figure 27-1) to align
points.
control wheels in accordance with step B.
27-10-00 AILERON SYSTEM B. Adjust control tube (B) linking control wheel
shaft (C) at rod ends (5). Clamp or otherwise secure
The ailerons of all-metal construction with beveled
are
control wheels in the level position until steps C thru E
trailing edges. Three hinges of machined, extruded
aluminum attach the ailerons to the aft out- are

i-i 0.20

5 ,B

B rG

j H

i-
3
C

1/16
FIGURE 27-1 AILERON AND RUDDER CONTROL WHEEL RIGGING
27-00-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY ArRCRAFT CORPORATION
OLDWILLWAYNE
C. Adjust control tube (D) at rod end (2) so that locknuts (1) and (5) and recheck .020 dimension.
alleron center bellcrank (E) is 1/16 inch left of center Repeat the operation on right control wheel by tuming
facing forward (FIGURE 27-1). wheel counterclockwise until ailerons contact the
D. Adjust aileron control tubes (F) by removing stops, then proceed as described for the left control
bolt, nut and washer (4) (Figure 27-1) and loosening wheel. Rigging is now complete.
locknut (6) (Figure 27-2). The aileron control tube (F) 3. Aileron Rigging (S/N 25-0786 ON).
can then be rotated clockwise or counterclockwise so A. Level control wheels (Reference 27-10-00, 3,
that the center of the outboard hole (K), (Figure 27-2), B procedures).
is 4.3 inches from spar web (M). Replace bolt, nut and B. Install 3/16 dia rig-pins at:
washer (4), (Figure 27-1), and recheck 4.3 inch dimen- (1)Jackshaft (C) (Figure 27-1)
sion. (2)Bellcrank (E) (Figure 27-1)
E. Adjust aileron push-pull tube (J) (FIGURE 27-2) (3)Bellcranks (9) (Figure 27-2) (Both LH. and
at rod end (7) (FIGURE 27-2) so that aileron tin neutral R.H.)
position) is 0 degree to -2 degrees down (wah no addi- C. Adjust control tubes (J) (Figure 27-2) (LH. and
tional tolerance) as measured with travel board at wing R.H.) to position ailerons at 0 degrees to 2 degrees
station indicated on travel board GSE 030003. down.
D. Adjust remaining control tubes (F), (B), (D),
(Figure 27-1) (1H. and R.H., if applicable) in order to
freely attach to the bellcranks and jackshaft.
E. Remove n’g-pins.
F. Adjust aileron stops (Reference Figure 27-2)
per paragraph 27-10-00, 3, F G. Tolerances are
o F.
specified paragraph
in 27-10-00, 3,
o 27-20-00 RUDDER AND STEERING SYSTEM

1. Rudder. The rudder attaches to the aft vertical fin

spar at four hinge points. Push-pull tubes and
o

I bellcranks link the rudder to the rudder pedals.

2. Rudder Removal and Installation.
~T Defah rudder push-pdl Ubs Imn rudder
Bal Uo
hom.*
B. Remove attaching hardware at rudder hinges.
I C. Remove rudder by pulling it straight aft.
D. Install rudder in reverse sequence of removal.
Recheck attaching bolts for security and safety.

7j
FIGURE27-2 AILERON STOPADJUSTMENT

NOTE
Wing station 147.75 is located at skin splice line
between flap outboard end and aileron inboard end.

F. Remove clamps from control wheels, then

adjust alleron stops (8), (Figure 27-2) so the down
.travel is 8 degrees 1 degree. Aileron up travel may A
vary from 12-1/2 degrees to 14-1/2 degrees (wah no
additional tolerance).

NOTE
The above aileron rigging and adjustment
instructions apply to both the left and right
ailerons.

G. Rotate the left control wheel clockwise until the

ailerons contact the aileron stops (8) (Figure 27-2). Ad-
just control tube (6) at rod ends (1) and (5) (FIGURE
27-1) by loosening the lock nut and tuming tube clock- FIGURE273 RUDDER PEDALADJUSTMENT
wise or counterclockwise to attain .020 maximum
clearance using feeler gauge (N), (Figure 27-1). Secure
27-20-00
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
3. Rudder Rigging and Adjustment.
A. Raise aircraft nose. (A propeller yoke jack may TRAVEL BOARD LDCATIDN
be used.)
STCL e550
B. Set stabilizer trim control in neutral position r~uvn BMRD
SKIW
(stabilizer parallel With aircraff center line). C/L
a RIvn ROY
C. Clamp pilots rudder pedals (A), (Figure 27-3), in
neutral position. LM1WG
D. Center nose wheel by removing nut, washer scREus

bolt (1), (Figure 27-4), and adjusting steering linkage at

(2). Bolt, nut and washer (5) and (6) must be installed laoo

as shown from rear to front.

snw
E. Adjust control tube (C) at rear tailcone bulkhead
bellcrank, (Figure 27-5), and set rudder, by adjusting
control tube (D), (Figure 27-6), at rod end bean’ng (2),
10 to the n’ght.
STA. 147.75
NOTE
TIUML B[URD U3CAnPI
Rudder bellcrank, aft tailcone, should be BETYEW FUP t AILERPI
modified per SINIZO-44. S1(27-3A

F. Unclamp rudder pedals.

FIGURE 27-3A TRAVEL BOARD LOCATIONS
G. Adjust rudder stops (M), (F~ure 27-8), so that
rudder travel is 23 degrees ~1/-0 degrees) right and left. clearances and travel
may be bent to obtain
NOTE requirements.
ON steering stops (3)
On aircraft S/N 25-0824 i. After setting stops, retighten all jam nuts, bolts
should be adjusted so .020 clearance exists and secure; recheck all travel limits.
between adjustment stop (3) and gear truss
assembly (4) (Figure 274) when rudder is at NOTE
extreme left and right travel position. Measure rudder travel with travel board on rivet
line at station indicated on travel board GSE
H. After rudder stops are set, move rudder through 030005, and with longitudinal trim (stabilizer) set
full leff/right travel to assure solid contact between in the 0 degree position. Sta 26.50 is located 3/4
stops and rudder stop limiter. Stop limiter (R) Fig. 27-8, in. above skin splice on vertical fin.

.020

USE .020 FEELER GAUGE

TO SET TURNING STOPS
FIGURE 27-4 NOSE GEAR STEERING LINKAGE ADJUSTMENT

27-20-00
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
4. Allowable Free-Play Limits at Rudder -Vertical.
k M~dmum vertical movement allowed at rudder trailing
edge -a8 inches.
If excessive free-play exists check the
(1) D
following areas for wear:

(a) Tn’m screw jackshaft.

(b) Trim link connecting empennage to
tn’mscrew.
Bolts and brackets attaching empennage to
(c)
tailcone.
5. Rudder Torque Tube Removal. The rudder
torclue tube should be inspected thoroughly and
tl
replaced If any damage is found. Remove shield from
front of cabin floorboard that covers torque tube.
Remove attaching hardware from hinges and rudder
pedal control rods. Carefully remove torque tube by
sliding out toward the n’ght side of cabin and through
cabin door.
NOTE
Conbol tube wear allowables. h any portion of the I II srcn-s

control tube exceeds .007 wear per wall or .014 in

reduction in diameter, the tube must be replaced. FIGURE 27-6 RUDDER HORN ADJUSTMENT

27-30-00 ELEVATOR SYSTEM C. Remove elevator to the rear.

Elevator construction is essentially the same as that of D. Install elevators in reverse sequence of removal.
the ailerons. Both elevators attach to the stabilizer at Recheck attaching bolts for security and safety. Set
four hinge points. Push-pull tubes and bellcranks link elevators (L 3 R) to be even with horizontal stabilizer.
the elevators to the control yoke. Lead counterweights Adjust at 91500jHEIM bearings at elevator hems.
static balance the elevators. A lead bob-weight under 2. Elevator Rigging and Adjustment
the instrument panel refines aircraft handling in flight.
A. Adjust rod end bean’ng (3), (Figure 27-1), at
1. Elevator Removal and Installation. control yoke (G) for control shaft (H) clearance from
A. Remove push-pull control tube by taking off all firewall and control yoke and bob weight (P) clearance
attaching bolts, nuts, and washer. from fuselage strcture.

B. Remove bolts, nuts, and washers from the four

O r´•--~ O

O
o\ II 1 c

~t ~O s

SMe7-7
SMi~7-5
FIGURE 27-5 RUDDER& ELEVATOR ADJUSTMENT FIGURE 27-7 ELEVATOR HORN ADJUSTMENT

27-30-00
 M20K SERVICE AND MAINTENANCE MANUAL
MOONN AIRCRAFT CORPORATION

OLDWILLWAYNE
2731-00 -VARIABLE DOWNSPRING SYSTEM
8. Level aircraft and set control column in neutral
with stabilizer parallel to center line of aircr‘aff.

NOTE
Adjust rod end bearings of control tube (L),
(Figure 27-6), at rear tailcone bulkhead, at
elevator horn rod end (9), (Figure 27-7) or as
last resort at main spar adjustable rod end
bearing to obtain additional elevator travel.

R’ ,E

M SMK27-9

P I FIGURE 27-9 VARIABLE DOWNSPRING

A spn’ng hooked into the elevator control system in the

tailcone refines the feel of the elevator in flight. A
bellcrank and cable tailors the spring tension
SM27-8 appropn’ate to the tn’mmed position of the stabilizer.
FIGURE 27-8/RUDDER 8 ELEV. STOP NOTE
NOTE Negative stabilizer degrees) settings mean
that stabilizer leading edge is moved down
Measure elevator travel from 8 degrees
relative to the thrust line.
stabilizer thrust line with travel board
positioned at stabilizer station 16.00 as Wrth stabilizer set at maximum positive setting and
indicated on travel board PM GsE 030004 and elevators FULL DOWN, adjust turnbuckle for a 14.0 to
with stabilizer at O degrees. (See Figure 27-11 16.0 Lb. tensiometer reading on cable (20 Lb. max
and Figure 273A for travel board placement.
permissable). Check for positive clearance betuYeen
cable and pulley sheave.
C. Set stops (P) (Figure 27-8), in empennage
stinger for elevator ;ptravel and downtravel of 20 A. Set stabiber to maximum negative position and

degrees to 22 degrees. elevators full down.

B. Adjust turn buckle to remove slack in cable
NOTE
Elevator bellcrank, aft taiicone, should be
(Figure 27-9).
modified perSIN120-44. C. Retrim to maximum positive setting and check
for clearance between cable end and pulley sheave.
D. After elevator stops are set, rotate elevators thru Tensionmeter reading should be 20 Ib. maximum.
full range of travel to assure solid contact with stops
27~0-00 STABILIZER TRIM SYSTEM
and that nuts and bolt heads clear stop limiter (E). Stop
limiter may be bent to obtain clearances and contact To provide pitch tn’m control, the entire empennage
(Figure 27-8). pivots around its main hinge points. The system
consists of a manually operated actuator that operates
E. Rotate tn’m full down to check clearance of connected
a sen’es of torque tubes and universal joints
bellcrank at wing rear spar. Adjust rod end bean’ng at
to a jack screw on the aft tailcone bulkhead.
rear tailcone bulkhead a needed for clearance.
Recheck elevator up and down travel.
F. Rotate tn’m full up; check that elevator up stops
(P) make solid contact on elevator stop limiter (E).
G. Retighten alljam nuts, attach bolts and secure
and
as necessary; recheck all control tube clearances
travel limits.
27-31-00
 M20K MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
NOTE
A Ustepped stop nut", with a Ujam nut",
configuration has been incorporated. This
configuration can be retrofitted to all M20K
aircra4 if desired. This allows trim screw nut
(F) (FIG 27-10) to contact stepped portion of
these two nuts and not bind.

fYD

e 19 I
SM27-ll
FIGURE 27-11 STABILIZER TRIM ADJUSTMENT

2. Nose Up Stabilizer Trim Control Rigging and

Adjustment.
A. Loosen setscrew in stop O and tum stop on
r threaded shaft to move it toward the tn’m screw gear
SH27-10
box Tum tn~m control wheel toward NOSE UP position
FIGURE 27-10 TRIM CONTROL ACTUATOR RIGGING Until horizontal stabilizer is within the following
limits:(-6.50 to -7.04.
Basic rigging is identical to the procedures below
NOTE
except that stepped nut and jam nut require being
torqued together with two wrenches prior to set screw Negative stabilizer (-degree) settings mean that
In jam nut being tightened against threaded trim screw. stabilizer leading edge is moved down relative
to thrust line.
Stepped nuts are required at the nose up (E) and the
nose down positions (A) facing trim screw nut (F).
B. Rotate stop O, (Figure 27-10) clockwise or
?.Nose Down Stabilizer Trim Control Rigging and counterclockwise to make contact with him screw nut
Adjustment, (F). Tighten setscrew. NOSE UP stabilizer trim control
n’gging is now complete.
A. Loosen setscrew in stop (A) (Figure 27-10)~ Turn
stop (A) clockwise or counterclockwise to align aff edge 3. Stabilizer Tr’un Indicator Rigging.
of stop (A) with last thread of trimscrew (C) (Figure
The indicator is geared to the tn’m control wheel and
27-10), Tighten setscrew and turn tn’m control wheel to indicates stabilizer position relative to the aircraft thmst
full NOSE DOWN position (tn’m screw nut (F) against
line. Set horizontal stabilizer to an angle of incidence of
stop (A). O degree 00 minutes to minus O degree 30 minutes.
B. Disconnect torque shaft (B) from trim screw (C), Adjust tn’m indicator cable at (F) (Figure 27-10) to set
(Figure 27-10). indicator in the cabin to the center of the takeoff range
mark.
C. Turn disconnected torque shaft (B) clockwise or
counterclockwise until hon’zontal stabilizer as A. Maximum Stabilizer Free Play Limits
measured, using the travel board, P/N 030004-503, Allowed:
and a bubble protractor as sho_wn by 27-11), is Fore and aft movement at stabilizer tip .12
within the following limits: ~3.80 to )1(.sehcni

NOTE (2) Vertical movement at stabilizer tip .10

Positive degrees) stabilizer degrees mean inches.
that stabilizer leading edge is moved up relative
to thrust line. NOTE
When removing trim screw from empennage
D. Connect torque shaft (B) to tn’m screw (C) use a block of wood cut to fit opening between
tailcone and empennage to prop empennage up
(Figure 27-10). NOSE DOWN stabilizer trim control
when tnm screw is removed.
rigging Is now complete,
27-40-00
10
IMOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
4. Electric Trim. EDO AIRE
(4) 18 inch Ibs.
AThe clutch torque for the electric trim system S-TEC
(5) -30 inch Ibs.
should be checked and adjusted (by an Avionics Shop) 5. Stabilher Trim Chain Adjustment. (Reference
for the following settings to operate the autopilot sys- Figure 27-12).
tems properly: k With the four mounting bolts (1) slack, adjust
(1) KFC 200 21 2 inch Ibs. the two NAS428-3-4 bolts (2) to obtain maximum ten-
(2) KAP 100 21 2 inch Ibs. sion on chain without causing binding.
(3) KFC 150 21 +/-2 inch Ibs.

2740-01 Trim System Troubleshooting

BINDING Check control tubes at bulkhead grommets for rub marks.

Check Trim Actuator threads for galling/not lubricated, lube per Ch. 5.

ELECTRIC CLUTCH SLIPPING Check BINDING symptoms above.

Check for proper clutch settings.
Confirm full bus voltage is available at tn’m motor.

NOTE through a cable link system (8) connected to the jack

Maximum trim tube, where it passes thru
wear on shaft actuator horn (9).
bulkhead grommets, is .007 inch per wall or.014 The flap switch (10) is self centen’ng from the down
inch diameter.
position and located on the console adjacent to the
flap position indicator. The flaps can be retmcted com-
pletely by placing the switch in the up position or to
WHEEL any setting between 0 and 33 degrees by holding in up
ASSEMBLY position to setting desired and then centen’ng to stop
the actuator.
Lubricate the actuator gear box and ball screw at inter-
vals with lubn’cants prescribed in Chapter 5.
1. Wing Flap Removal and Installation
k Remove wing flap hinge fairing to expose flap

push-pull tube.
B. Remove bolt, nut, and washer from Rapactuat-
attachment.
FLOORBOARD

STEPPED
STOP NUT
O ‘3~yC2 2

81X ul
GEC\R
JAM NUT-Y U U \L 1 ASSEMBL

S27
FIGURE 27-12 STABILIZER TRIM CHAIN ADJUSTMENT
0’ ’f
~-7
27-50-00 WING FLAP SYSTEM

Push-pull tubes and bellcranks interconnect the flaps. 3

The flaps are operated by an electn’cal motor driven

actuator (1) connected to a jack shaft (2). The jack s
shaft Is connected to actuator bracket (3) (Figure 27-
13) on each flap just outboard of hinges (4) by a push-
pull rod end bean’ng (5) and hardware. Each flap pivots
about four hinges. Travel is controlled by limit switches
(6) and (7) and UP stops located at outboard hinges I P

(Flgure 27-13). Flap position is indicated in the cockpit LlGURE 27-13/FV\P ACTUATOR ASSY. INSTAL

27-40-01
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
A Adjust tight and left inboard linkage at rod end
bearing (1), (Figure 27-14) to obtain a flap deflection of
33 degrees (+O degree/-2 degrees). Retract Raps to 0
degree (+/-2 degrees); set Rap outboard travel stops
(not illustrated) so that Raps align with anerons in
neutral position.
f
B. Retract Raps to 10 degrees 1 degree,
and set flap position indicator cable (B) at attachment
’’e
screw (2), (Figure 27-15), to TAKEOFF position as
shown on flap position indicator in cabin. This indicates
1
the degree of flap deflection from 0 degree to 33 de-
C
gree, with a 10 degree takeoff setting.
r, C. The limit switches, #3, (Figure 27-15) should
be adjusted so that under Right loads the actuator over
run will not allow the Raps to exceed either up or down

positions.
27-60-00 -AILERON/RUDDER
INTERCONNECT SYSTEM

1. With controls in neutral position, locate 110002-

SMK27-14 101 bracket, aileron control tube, so that the end of
on
110002-005 bellcrank assembly will be 2.25 in. AFT of
FIGURE 27-14 WING FLAP 310020 fuselage former.
2. Holding both rudder aileron controls in neutral
C. Remove bolts, nuts, and washers at flap hinge position, install spn’ngs, P/N 110003-007 on -005
bellcrank and 110002-025 -027 brackets position
points,
D. Remove Rap by pulling it down and aft. -025 -027 brackets on rudder control tube so the in-
E. Install wing flaps in reverse sequence of Stalled length of each spn’ng is 4.90 in. Clamp bracket
in place dnll through brackets and into control tube
removal. Recheck security and safety of attaching 70r AN530-4R6 PK screws.
bolts. 3. Make sure PK screws are in place to secure all
2. Wing Flap Rigging and Adjustment. three brackets.

27-90-00 -MISCEUANEOUS
NOTE
Flap deflections are to be measured with travel 27-91-00 CONTROL SURFACE STATIC
board GSE 030003 at the station indicated on the BALANCING
travel board. (See Section 27-20-00.Fia. 27´•
When repairing or repainting the control surfaces they
must be rebalanced according to the following proce-
dures.

CAUTION
AII control surfaces should be stripped prior to
repainting.
NOTE
Maximum and minimum static unbalance moments
apply only to ailwons that have been painted.

27-92-00 EQUIPMENT AND MATERIALS

STATIC BALANCING

The design of the balancing fixture is not critical

~t /I providing the requirements of this section are met.
Obtain or otherwise fabricate two (2) knife edges and
supports appro>dmatdy one (1) foot in height such that
they can be placed on a table and be stabilized to
prevent tipping (See Fig. 27-16).
Fabricate or otherwise obtain a ’control weight" and
SIIE7-U I hanging stn’ng (Fig.27-16,item A) such that the total
FIGURE 27-15 WINGFLAP INDICATOR ADJUSTMENT weight of the stn’ng and weight agrees exactiy with the
values listed for the control surface to be balanced.
27-60-00
12
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE

12 OZ. (.754>
GAGE WEIGHT

KNIFE EDGE I II _>

SUPPORT

STRING OR WIRE
LOOP 2.12 DIA.

4.00’

TRAILING EDGE
RESTING SUPPORT
(ADJUST VERTICALLY
TO PLACE SURFACE IN
A
CONTROL WEIGHT
3~50 LBS~ M20J K RUDDER
V
NORMAL FLIGHT 3.50 LBS. M20J K ELEVATOR
2.00 LBS. M20J K AILERON SM27-1

FIGURE 27-16 CONTROL SURFACE STATIC BALANCE SETUP DIAGRAM

NOTE 5. The balancing device must include a means to

Accurate weight measurements can be obtained at accurately measure the distance of the gauge weight
any United States Post Office. from the hinge line.
6. Control surfaces must be rechecked for balance
1.ELEVATOR: 3.50LBS. 6.232 Arm after any painting, stn’pping, repairs or alterations to
2. RUDDER: 3.50LBS. 5.853 Arm any control surface.
3. AILERON: 2.00LBS. 5.590Arm
27-93-01 DETAIL PROCEDURES STATIC
Fabricate or otherwise obtain a "gauge weight", item B,
BALANCING
ng. 27-16, of exactly 12 oz. (.75 lb.)[28 ot (1.75 Ib.)for
S/N 25-1000 thru 25-TEA] such that all three dimen- I. Devise a bearing surface for supporting the con-
sions are approximately equal (cube, cylinder or trol surface hinge line on the knife edges providing a
pyramid). The size of the gauge weight is not critical as Friction free support.
long as its weight in oz, is accurately known. However, 2~ Place surface on knife edges and level hinge line
if a 12 oz, gauge weight is used (28 oz. SM 25-1000
(RISM control surfaces should be balanced inverted for
thru 25-TEA), computation of moments will not be
be greater sensit’rvity). Rest trailing edge on aft support
necessary and the dimensions in Table 27-18 may and adjust aft support to put the surface in as normal
used.
(0 degree) chordwise Right attitude.
27-93-00 GENERAL PROCEDURES STATIC 3. Place correct gauge weight (2) on top and near
BALANCING the trailing edge of the surface to hold surface down.
4. Suspend the control weight (A) from the balance
1. A line drawn through the hinge line support points
hom in the following positions:
must be level and perpendicular to the supporting knife
A Rudder Elevator: Suspend weight at the
edges.
knife edges must be horizontal seam formed by the balance weight and balance hom
2. The supporting
and parallel to each other within the requirements of ribs (See Figure 27-17).
step 1. above. B. Aileron: Loosen forward most balance weight
3. The control surface must be supported in normal from shank of bolt
bolt and suspend weight
flight attitude with the hinge line level (except as
specified in 27-93-01, 2.) (See Figure 27-17).
4. The area in which balancing operations are per- 5. Gradually move gauge weight forward toward
formed must be free of drafts or other air movement hinge line until the point is reached where the trailing
which might affect the balancing operation. edge tends to leave the trailing edge support.
27-93-00
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
oo‘
~cr rr
I)U II1

CLLYIIOI)
IILI)ICII(O C~OCEDUI)I

mapu ru
DLZ

FIGURE 27-17 FLIGHT CONTROL BALANCING PROCEDURES

6. Accuratelymeasure and record the distance "X" 8. If the gauge weight is aft of the distance limit the
perpendicular from the hinge line to the center of the surface is overbalanced and weight must be removed,
gauge weight. The gauge weight distance must be and the balance rechecked.
within the limits provided CTaMe 27-18). 9. Table 27-19 provides the absolute balance limits
7. If the gauge weight is forward of the distance limit used in developing the "X" distance limits.
the surface is underbalanced and weight must be
added, and the balance rechecked.
NOTE
The "absolute limits" must be satisfied if a different balance procedure is used requiring calculation of
balancing moments.

CONTROL SURFACE CONTROL WEIGHT UMIT GAUGE WEIGHT (12

DESCRIPTION DISTANCE

Elevators 430026-503 6 3.50 LB. Underbalance +6.76 in to

604 Overbalance +11.07 in.
Rudder 460043-BASIC 3.50 LB. Underbalance +3.36 in, to
-505 Overbalance +10.027 in.
Aileron 230015-505 -506 2.00 LB. Underbalance +5.45 in, to
Overbalance +8.07in.-Note3
NOTE:
1. (-t) Positive dimension indicates distance ah of hinge line.
2. \jajues in this column only applicable for gauge weight used in combination with specified control weight.
3. Value for aileron distance limit adjusted for C.G. of gauge weight on inclined surface (6.8 degree) maximum
error when measuring top point of "cubic proportioned right circular cone" gauge weight.

GAUGE WEIGHT DISTANCE LIMITS

control weight)
(for balancing with specified
TABLE 27-18

27-93-01
14
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CONTROL ELEVATOR RUDDER RUDDER AILERON

SURFACE S/N 25-0001 S/N 25-1000

thru 25-0999 thru 25-TEA

ABSOLUTE +16.75 In-tbs +18.001n-Lbs 12.50 In-Lbs +7.10 In-Lbs

to to to
BALANCE UMITS- to
+13.00 In-tbs +13.00 In-Lbs +5.00 In-Lbs
Note 1 +13.50 In-tbs

CONTROL 3.50 tbs -6.232 3.50Lbs~-5.863 3.50 Lbs -5.863 2.00 Lbs @6.59
In´• Effective Arm In. Effective Arm In. Effective Arm
WEIGHT in. Effective Arm
-20.52 In-Lbs -20.52 Inlbs -11.1804 In-Lbs
MOMENT Note 2 -21.813 In-Lbs

BALANCE LIMITS -5.063 in-tbs -2.521n-Lbs -8.02 InrLbs -4.08 In-Lbs

to to to
WITH CONTROL to
-7.52 In-Lbs -15.52 In-Lbs -6.18 In-Lbs
WEIGHT 8.313 In-Lbs

DISTANCE LIMITS +6.751 In. to +3.3610. to +4.59 In. to +5.440 In. to

10.027 In. +8.869 In. 8.240 In.
(Dkride .75 1_8) 1 1.084 In.

NOTES:
1. Type design data requirements.
2. Effective arm determined by balance test ~Lith calibrated gauge and control weights.
3. Positive moments indicate T.E. Heavy condition.
4. (-t) Positive dimensions indicate distance ah of hinge line.

COMPUTATION FIELD BALANCE LIMITS

TABLE 27-19

NOTE B. Rudder. The rudder trailing edge may be

If balance limits cannot be met with existing trimmed right or left as required.
weight on any control surface a lighter or heavier C. Elevator. A full span tab is built Into each
weight can be obtained through a Mooney Service elevator trdJing edge and is fDted 7 degrees 1/2
Center. This approach should be examined before down. No further tolerance is al-
degree trailing edge
reworIing any repair or restripping and repainting lowed.
the affected control surface.

27-94-00 CONTROL SURFACE TRAILING

EDGE

.070 HAX. ALLOWABLE

NOTE
Verify flight control rigging is correct before II""""
bending trailing edge.
AILERONS
1. Trimming. A special pair of widenose vicegrip .os ~4X. ALLOWABLE
pliers are to be used to bend the trailing edges as omEcrloN Lm
OR RKIKT
necessary (See Figure 27-20).
A. Aileron. To conect for a left wing-heavy condi-
lion, bend right aileron trailing edge down; to correct
II
bend IF?I1
condition, YOIIU aileron
left alter

~-liart
for a right wing-heavy """U"’Y,,. ull

I RUDDER
NOTE
The aileron trailing edge MUST NOT BE BENT UP
under any circumstance. Any deformed rivets must
be replaced after trimming aileron or rudder FIGURE27-20 TRAILlNG EDGE TRIMMING
trailing edge.
27-94-00
15
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
2795-00 STALL WARNING MAINTENANCE proceed as follows: Locate the switch installation on the
PRACTICES under surface of the left wing leading edge and loosen
the two phillips head screws, one on either side of the
vane. If the stall warning has been activating too early,
pull the vane back and down. If the stall waming has
MUUST UP TO SOONER been activating too late, push the vane up and forward.
Moving the vane with the phillips head screws
loosened moves the entire unit up or down inside the
wing, causing the switch to be dosed earlier or later.
Retighten the screws after making each adjustment
NOTE
NEVER TRY TO ADJUST THE SWITCH BY
BENDING ME VANE. This part has been heat
treated and cannot be bent without damaging
or breaking the vane or switch.

ADJUST DOWN TO ACTUATE LATER As a rule of thumb, moving the vane tip 1/4 inch will
ADJUSTMEM
change the time the stall warning actuates by about 5
SCREWS
,ph of indicated air speed. The only way to test the
accuracy of the setting is to fly the airplane into a stall,
noting the speed at which the warning hom comes on
FIGURE 27-21 STALL VANE ADJUSTMENT and the speed at which the full stall occurs. The stall
must be made in van’ous configurations, clean, gear
and flaps down and power on and power off. It may be
1.Stall Warning Switch Removal. necessary to make several aPemate adjustments and
test flights before the desired setting can be reached.
A. Remove the screws or rivets attaching the
The stall waming should actuate at no less than 5 KTS.
access cover aft of the switch on the lower wing
nor more than 10 KTS. preceding the stall and shall
surface, continue until the stall occurs in power off configuration.
B. Remove the two adjustment screws which hold The rate of speed reduction shall not exceed one knot
the
the switch to the wing leading edge. per second with the airplane trimmed to 1.5 times
stall speed. The switch setting should be checked and
C. Disconnect the two wires from the switch.
adjusted as necessary whenever a wing or wing
2. Stall Warning Switch Installation. leading edge is replaced or extensively repaired, or if a
A. Connect the electn’cal wires to the switch. new switch is installed. The switch should require no
adjustment in normal service.
B. Position the switch in the opening of the lower
wing leading edge, install the two adjustment screws.
C. Replace the access cover securely.
D. Adjust the switch. See STALL WARNING
INDICATION SYSTEM ADJUSTMENT.
3, Stall Warning Indicating System Adjustment
(Figure 27-21). (Adjustment locations may vary slightly)
The stall waming switch is adjusted when the airplane
Is test flown at the factory. Should it require readjusting,

27-95-01 TROUBLE SHOOTING STALL WARNING SYSTEM

TROUBLE PROBABLE CAUSE REMEDY

Warning system inoperative. Waming circuit breaker tn’pped. If circuit breaker persist in tn’pping,
check for grounded circuit.

Open circuit. Check for continuity.

Defective warning hom switch. Replace switch.

Defective warning hem. Replace hem.

Horn continues to blow. Defective warning hom switch. Replace switch.

27-95-00
16
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
27-9690 SPEED BRAKE SYSTEM (2) Tighten all screws.
is optional equipment and (3) On vacuum units, adjust turnbuckle/cable
A Speed Brake system connection so no slack is in cable and speed brakes
installed on some M20K aircraft. The manufacturer,
Precise Flight, Inc. can provide detail parts and just begin to e~dend from cartridge.
the
maintenance information for the cartridge assemblies. (4) Test operation of Speed Brakes on
circuit binding either up or down.
Some of the electrical circuitry, wiring, relays, ground to assure there is no

breakers, etc. are installed from Mooney drawings. Airloads on Speed Brakes can cause a slightly different
Components for these are available through your alignment during deployment, therefore
it Is
electric
Mooney Service Center. The relay for the recommended that a TEST FLIGHT be done to test
is located under the rear seat
Speed Brake System operation Speed Brake System to verify proper
of
located in
area, on the LH bulkhead. The schematic, operation. Readjust alignment of cartridge to wing
slots
the envelope,and the electrical parts list, Section 91,
U"til proper operation in night is obtained.
of this S M cover the electrical system components
identification. 27-96-02 -MAINTENANCE -SPEED BRAKE
SYSTEM
27-96-01 -SPEED BRAKE CARTRIDGE,
REMOVAL AND REPLACEMENT ELECTRICAL OR VACUUM SYSTEMS
1. Every 1000 hours:
1. REMOVAL
A. Remove speedbrake cartridges in accordance
A. Remove access panel from under side of wing, with Section 27-96-01, 1.
directly beneath the cartridge. and mounting
(1) Visually ins’peddoubler
B. Disconnect either the vacuum line connection or
hardware for strudural integrity.
the electn’cal connector on the cartridge. all moving
(2) Visually inspect for chafing on
C. Remove screwfrom bottom of wing just aft of
parts.
cartridge holding mount strap to bottom of wing. for
(3) ManuBlly operate speedbrakes and feel
D. Remove screws from top of wing around top of smooth operation, both extending and retracting.
cartridge slot. (4) Insped cable ton vacuum units) esecially
E. Slide cartridge forward to start mount strap around pulleys for fraying
through bottom hole, slide cartridge out from bottom of (5) Inspect pulleys ton vacuum units) for any
wing, wear or damage.
2. INSTALLATION B. Report any deficiencies (if any) to Precise

A. Reverse removal procedures. Flight, Inc.

C. Reinstall speed bi~ake cartridges into wing in
(1) Leave attachment screws loose until proper accordance with Section 27-96-01, 2.
alignment of cartridge to slots in wing is verified,

27-96-00
17
SERVICE AND MAINTENANCE MANUAL M20K MOONN AIRCRAFT CORPORATION

OLDWILLWAYNE

BLANK

27-96-02
18
CHAPTER
OLDWILLWAYNE

FUEL
 M20K SERVICE AND MAINTENANCE MANUAL
MOONET AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 28

FUEL

TABLE OF CONTENTS

PAGE
CHAPTER SUBJECT
SECTION
SUBJECT

.5
2&00-00 General
Maintenance .5
28-00-01 Filler Cap
.6
28-10-00 Storage
.6
28-11-00 Fuel Tank Field Repair
.8
28-12-00 Fuel Tank Leak Repair

28-13-00 Soapless Bubble Fluid Formula

.10
Preparation for Leak Check
.10
28-1 4-00 Fuel Additives
.10
28-20-00 Distribution
zs-21-oo
Fuel Boost Pump’Removal and Installatlo .10
.11
28-22-00 Gascdator Screen Cleaning
.11
2&23-00 FuelInjection System
.11
28-24-00 Engine Priming
.11
2&25M) Fuel Selector Valve Removal and Installation
.11
2830-00 Dump
Drains .11
2831-00 Fuel System
.li
28-32-00 Fuel Vents
.11
28´•40-00 Indicating
.11
28-41-00 Fuel Quantity Indicating Transmitters
.11
28-42-00 Fuel Quantity Indicator
.11
28-43-00 Fuel Quantity Adjustment Procedure
.11
Fuel Tank Transmitter Adjustment
28-43-01
(25-0001 thru 25-0446)
.12
2&43-02 Fuel Tank Transmitter Adjustment
(25-0447 and ON)
.12
2&43-03 Fuel Quantity Gauge Adjustment
.12
28-90-00 Miscellaneous
.12
28-91-00 Trouble Shooting
.13
28-92-00 Flared Fittings

28-CONTENTS
3/4BLANK
 MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CHAPTER 28

FUEL

LIST OF EFFECTIVE PAGES

CHAPTER
SECTION
PAGE DATE
SUBJECT

1/2BLANK 997
28-Effectivity
3/4BLANK 9-97
28-Contents
5. 9-97
28-00-00
6. 9-97
28-10-00
7. 9-97
28-11-00
8. 9-97
28-12-00
9. 9-97
28-12-00
10 9-97
28-13-00
11 9-97
28-22-00
12 9-97
28-43-02
13 9-97
28-92-00
14 9-97
28-92-00

2&EFFECTIVIP/
1I2BLANK
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
28-00130 GENERAL 28-00-01 FUEL FILLER CAP ASSEMBLY
IMAINTENANCE
Internally sealed, integral fuel tanks are in the forward
inboard sections of the wings. Fuel feeds from either Fuel filler port cap assemblies should be checked
tank to aselector valve thru a gascolator, with a periodically for proper sealing and should be serviced
low-point drain, through the emergency pump to the occasionally to prevent hard to open or close
engine-driven fuel pump and to the fuel injector system conditions.
on the engine. Fuel quantity indicators are electn~cally i. The o’dng seal (i) (F~ure 28-2) around Be cap
operated with 2 transmitters located in each tank. assembly should be kept clean and free of dirt or grit
that might cause abrasive action on seal or mating
flange. Occasional lubrication with petroleum jelly or
Tri-Flow will the o’n’ soft and

FILLER PORT
FUE L GAGES

FUFL OUINTIIY

IUPPLY
LINE
LEFT TANK RIGHT TANK

DRAIN IILE ,UI1 MNT AND

RETUP’´• RETURN LINE

SUPPLY LINE
L)riE
SELECTOR wL~

BOOST PUMP
taSCOU!Cs ’IJ~--SETU)N LINE
SwlTCHES
InER SwlTCH

HI~

ENCI~I -)l~f r´•

fCE: P,~P
FCEL FLJ; 2~LCI

80051 PU~P I

"Ir’ C"I:

´•’(E (I II ,DPI"Lc \r‘_LI

FUEL SYSTEM FIGURE 28 1

2. The shaft (2) running through the center of the inspection. This can be accomplished per the following
cap housing, that actuates the rotating lack plate (3) procedures:
should be lubn’cated occasionally with Tri-Flow, or A. Remove cap assembly from wing filler port and
equivalent, to prevent binding while opening or closing inspect o’ring (1) for any damage or brittleness.
the cap assembly. This should also lubricate the o’n’ng Remove and replace if needed.
(4) that seals this shaR. a. Adjust tension of shaff (2) and rotating lock plate
WARNING (3) by removing cotterpin (5) From nut (6) on threaded
Water enter the fuel tank through a loose
can
portion of shaft (2). TigMen nut (6) so cap assembly
handle O can be opened, turned and shut with hand
fitting or damaged cap. This should be
corrected as soon as possible. pressure and still provide the necessary seal of cap
assembly to keep water from entering fuel tank.
3. The sealing capability of each cap assembly
should be checked periodically and at each annual
28-00-00
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
NOTE 1.Approved Maten’als.
Fuel selector should be in the OFF position
A. Sealants.
before proceeding with paragraph C to
pressurize the fuel tanks.
WARNING
C. Connect rubber hose to each tanks vent line. Sealants are safe only when handled with
Apply only one-half pound (1/2 psi) air pressure. Check reasonable care. Avoid ingestion and all
for fuel cap leaks by soaping circumference of filler cap contact with the body, especially with open
assembly and obseM’ng bubbles. Replace o’n’ng if breaks in the skin. Wash hands before eating or
bubbles are observed and adjustment of the nut does smoking. If accelerator contacts the skin, flush
not stop the leak, area with warm water.

CAUTION
of air
(1) Brushable sealant PR1422-A-1/2 or A-2 or
Use only one-half pound (0.5 psi) CS3204 A-1/2, A-2 or Pro-Seal 890-A (M1L-S-8802D
in tank.
Class A).
7 (2) Filleting Compound PR1422 &1/2, &2 or
CS3204 B1/2, 82 (MILS-8802D Class B).
(3) Removable access panel sealant
I PRI 403-EB2 or PR 1428-B or CS3330-B.

(4) Protective sealant PR1005-L or CS3600,

2 (MIL-S-4383B).
B. Gloves- Polyethylene
C. Metal cleaning solvent Turco 657 wipe
solvent.

r3 D. Cheese cloth.

I E. Turco leak detector or bubble fluid.

F.Methyl ethyl keytone (MEK) (thinner for

PR 1005-L).
57 6 NOTE
Approved materials may be obtained from your
local Mooney Marketing or Service Center.
Sealants may also be obtained from
SMX28-2
Products Research Co., 5454 San Fernando
Road, Glendale, CA. 91209, Ph. (800) 423-2411;
FUEL FILLER CAP ASSEMBLY MAINTENANCE or
FIGURE 28 2 Sun
Chem Seal Corp., 11120 Shernan Way,
Valley, CA. 91352;
or
28-1 0-00 STORAGE
Coast Pro-Seal 19451 Susana Rd.,
2811-00 FUEL TANK FIELD REPAIR Compton, CA 90221.
This paragraph outlines the procedures recommended
for repair of the integral fuel tanks. Tank repairs should 2. Handling and Mi~dng Sealants.
not be attempted until these instructions are fully
A. Sealant Maten’al Characten’stics.
understood. Refer to Service Bulletin SE M20-230
dun’ng resealing oftanks. (1) Application life is the time that the m’uced
compound remains suitable for application. Application
CAUTION life ratings are always based on standard conditions of
S/N 25-0447 and later model aircraft have the 750 F. and 50 percent relative humidity. For every 100
fuel outlet relocated in the aft inboard section P rise in temperature, application life and cure time is
of the wing tanks. Damage to this outlet and reduced by half; for every 100 F. drop in temperature,
screen can be done when removing the tower
application life and cure time is doubled. High humidity
inboard access panel unless extreme caution is at the time of mixing slightly reduces the sealant
used during removal. Do not push the access
application life.
panel upward inside the tank to break the
sealant unless the outlet assembly has been (2) Ma>dmum unopened container life, with
removed from the tank, sealant at 800 F.,
is six months.

28-1 0-00
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
and cun’ng rates are as follows:
(3) Sealant application life, tack-free curing time,

(a) BrushableType Sealants

Cure Rate Application Life
Tack-Free Time
CLASS A (HOURS) (HOURS) (HOURS)
30 112
PR1 422 A-1/2 10
72 2
PR1422 A-2 36
8 In
CS3204 A-1/2 30
72 2
CS3204A-2 24
30 112
PRO-SEAL890-A112 10
72 2
PRO-SEAL890-A2 36

(b) F=illeting Compound land on wing walk access panel).

Cure Rate Application Life
Tack-Free Time
CLASS B (HOURS) (HOURS) (HOURS)
45 1/2
PR~ 422 8-1/2 10
72 2
PR1422 8-2 36
30 112
CS3204 B-1M 8
72 2
CS3204 8-2 24
76 4
CS3204 8-4 36
Follow procedures with sealant materials/kits to properly seal tanks.

(c) Access Door Sealant (except on wing walk access panel)

Cure Rate Application Life
Tack-Free Time
CLASS B (HOURS) (HOURS) (HOURS)
16 2
CS-3330-8 8
48 2
PR1403-G-B2 10
8 16 2
PR1 42&-8

(d) Brushable Top Coat Protedive Sealant Cure Rate Application Lifse
Tack-Free Time
(HOURS) (HOURS) (HOURS)
1/3 4
PR1005L
CS3600
Allow 24 hours cure time prior to refueling tanks. Air must be allowed to circulate through tank access covets.

B. Sealant Mi>dng NOTE

(1~ For best results, use kits with proper Sealant in tube form have mixing instructions
proportions of base compound and accelerator. on each tube. Read and comply with these
(2) To avoid excessive air entrapment, slowly stir mixing instructions priorto sealant application.
accelerator into base compound. Continue m’udng for
seven to ten minutes. Scrape sides and bottom of 3. Cleaning Surfaces to be Sealed.
container to include all compoundin m’udure and to
A. Clean metal surfaces to be sealed with Turco
Insure uniform blending. Scrape mi>dng paddle on edge
657 Wipe Solvent or Methyl Ethyl Keytone (MEK).
of container to remove unmixed compound. Be sure to
use all of the accelerator.
Wipe surface dry with a clean cloth. Do not allow
solvent to evaporate.
(3) Place a small amount of mixture on a clean B. Allow cleaned surface to dry five to ten minutes
stn’p of aluminum and spread sealant Visually examine before sealant application.
sealant film to determine whether accelerator is visible
in particle form. If particles of accelerator are visible,
continue mixing operation. If course particles of
accelerator persist after m’w’ng thoroughly, reject the
mixed batch,

28-11-00
 AND MAINIENANCE MANUAL M20K MOONEY AIRCRAFT CORPORAT10N

OLDWILLWAYNE
3/8 TO 1/2 IN. C. Brush Sealing.
_fl
(1) Brush sealant (PR 1422-A-1/2, A-2 or CS3204
1/2, A-2) over all seams, rivets, nuts, and bolts. A one
,,3, 1, inch stifibn’stle brush is recommended for sealant
3/8 TO application. Force sealant into all gaps with brush strokes
1/2 IN, parallel to seams. Use a circular brush action to deposit
APPLY BRUSH an even coating of sealant around n’vets, nuts, and bolts.
SEAL EAPS b HOLES
WITH FILLETING
SEALANT Coating shoukl be approximate~y 1132-inch thick. Use
considerable brush action to force sealant into all small
COMPOUND
crevices and to obtain good adhesion. Air pockets under
FIRST STEP THIRD STEP the sealant, that will open up in the form of holes or voids
soon after application, will result from Improper
3/16 TO 1/4 IN. 1 3N,
application. To repair holes or Mids, press sealant in
~L
place using a spatula.
(2) When the edge of a flange protrudes 0.040 inch
1/16 IN. Or less, or where the seam cannot be clearty defined,
APPLY F~LLETING
3/16 70
COMPOUND
APPLY apply two 1/32-inch brush coats. Allow the first coat to
1 IN.
1/~ IN. PROTECTIVE Icure about four hours or until it becomes rubbery before
FILLET SEALANT applying the second coat. The second coat should
overlap the edges of the first coat by about 114 inch.
SECOND STEP FOURTH STEP
D. Protective Sealant.

(1) Using short, even strokes, brush on a smooth

and continuous coat of PR 1005-L over sealant. The

FASTENER SEALING WITH BRUSH SEALANT

protective sealant coat should extend one inch beyond
U/32 TO 1/16 IN. THICK> edge of the filleting compound.
SM28-3
(2) Allow the first protective coat to cure 20
FUEL TANK SEALlNG FIGURE 28 3 minutes at 750 F., or until tack-free; then apply a
second brush coat of PR 1005-L. Make every effort to
NOTE obtain a completely bubble-free, continuous top coat.
Apply sealant as soon as possible after DO NOT REBRUSH over areas, as doing so will only
cleaning. Store and handle parts in a manner cause dragging and will break coating continuity.
that will prevent finger pn’nts, dust, dirt, or
E. Upper Wing Tank Access Panel Sealing.
other foreign substances from accumulating on
surfaces to be sealed. (1) Apply a coat of access door sealant (PR
1403-EB2) to either faying surface using a short stiff
NOTE bristle brush, spatula, or extrusion gun. If an extrusion
Refer to Mooney SE M20-230 for proper brush or
gun is used, smooth the sealant with a
application and drain holes to be left open. spatula. Cover the entire faying surface with a sealant
coat of sufficient thickness (1/32 to 1/16 inch) to assure
4. Sealant Application. Old sealant must be e~drusion along the edges of the faying surface when
removed. Use a sharp non-metallic scraper (Formica th, mating parts are assembled. Access panels in wing
or lexan). When sealant has been removed clean area
walk area should be sealed vvith PRC 1422, Class B
throughly and, reseal tank as follows: filleting compound.
A. Fillet Sealing. (2) Assemble parts immediately after application
of sealant and tighten screws to obtain as near as
(i) Be certain that the surface to be sealed is
totally clean and free from oil, gn’me, finger pn’nts, etc. possible a metal-to-metal contact.
(2) Referto (Figure 283) fortypical fillet size. (3) Remove the e~druded sealant from the wing
surface after installing the fasteners.
(3) Join fillets laid on intersection joints to
produce a continuous fillet. 28-12-00 FUEL TANK LEAK REPAIR

(4) Seal all difficult and hard-to-reach areas first ´•I~ Leak Descn’ption. It is necessary to periodically
to preclude the possibility of their being overlooked or inspect the fuel tanks. Inspection is particularly important
Improperly sealed. in confined areas of the aircraft that are not e>cposed to
B. Filleting Compound Application. the airstream. Identification and classification of fuel leaks
that occur in both confined and open areas is necessary
(1) Use a spatula oran e~chusion gun with a 1/8 -to 1/4 t, differentiate between those leaks that require repair
inch nonle opening for laying fillets at edges of all seams, before flight and those which do not constitute a flight
V~hen using an e>drusion gun, hold gun perpendicular to hazard. The size of the wetted area around a leak is an
seam so that ex rud8d seahntwtll packtightly. indication of the leak intensity. All fuel leaks must be
recorded describing the location and intensity of the
while
(2) Use
working
a spatula to pack sealant firmly in place
out air pockets. Shape each fillet evenly. by.
leak in the arrcraft log book.

28-1 2-00
 MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
1/2 TO a good visual indication of fuel presence when
3-1/2 TO 4 IN. 1-1/2 IN. 3/4 IN. brought in contact with suspected leak points.
(3) After tracing leak to its exten’or source, mark
location and drain fuel tank.
B. Intemal Leak Detection. To make a permanent
repair, it is mandatory that the true of the interior
source
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. Fuel may channela few inches or several feet
where a appears on e~demal skin surface.

(1) Enter tank through inspection access panels

HEAVY SEEP and inspect sealant in general area of outside leak
point. Look first for bare seams, rivets, and boas in
seal areas. Inspect sealant for blisters, pin
holes cracks, sp)as, and loss of adhesion. Mark~all
suspected flaws with masking tape.
(2) Test each suspected flaw from inside tank
using compressed fiRered air at 20 to 30 PSI. Hold air
nozzle against flaw and closely check outside leak
::ii:iijjjjjjj::ijjii::jij:~jjjjiij::a point for evidence of fuel.
After testing each suspected flaw from inside
(3)
RUNNING LEAK tank outlined above, and if no leak source can be
as
discovered, apply soapless bubble fluid to e>den’or and
SHH28-4 lagain apply air pressure to flaws from inside tank.
FUEL LEAK CLASSIFICATION FIGURE 28 4 (4) If above tests fail to locate leak source, apply
air pressure (10 PSI MAX) to e>demal leak point after
2. Classification of leaks as to Intensay and removing all traces of fuel from tank and applying
Location. (Referto Figure 28-4). soapless bubble fluid to tank inten’or seams per
A. Section 28-13-00.
Intensity Classific~tion.
4. Leak Repair.
Stain A slow fuel leak that tends to
evaporate as soon as it is e>cposed to air. A. Temporary Repair of Fastener Leaks. Generally,
all leaks in enclosed areas and running leaks in open
(2) Seep A fuel leak that reappears shortly areas constitute a flight hazard. Fastener leaks of this
after area iswiped clean.
category may be temporan’ly repaired by applying a
Heavy Seep A fuel leak that reappears sealant fillet over fastener head on fuel tank e~derior.
immediately after area is wiped clean. For a temporary repair to be satisfactory, structural

(4) Running Leak A fuel leak that flows i"tegrity must be retained in leak area. To make a
steadily, temporary fastener-leak repair:
(1) Remove enough fuel from tank to drop fuel
level below leaking fasteners.
Slow-to-heavy seeps occun’ng in open areas, such as
wing surfaces exposed to the airstream, are leaks (2) Clean fastener head and adjacent surface
which do not constitute a flight hazard and need not be wah Turco 657 Wipe Solvent or MEK and dry
repaired pn’or to flight, providing the condition causing thoroughly. Fastener head and adjacent metal must be
the leak cannot result in a leak of greater intensity entirety free from paint, dirt, and oil.
during flight. Seeps considered permissible for flight (3) Apply a 1/8 inch thick coat of PR 1422 (or
must be frequently inspected to insure that no increase
in intensity has occured.
CS3204) &112 or 8-2 over head and around fastener.
(4) Allow sealant to cure until firm and rubbery.
A running leak and any leak in a confined area that
Is not exposed to the airstream should be repaired (5) Refill tank and examine repair periodically.
If
before the next flight, leak recurs, Sealant must be removed and area
recleaned pn’or to making another temporary repair.
3. Leak Detection.
B. Permanent Leak repair. If leak source is found to
A. ~demal Leak Detection After Refueling. To be able be around a rivet or threaded fastener the repair
to trace a leak from where it appears on an outer tank or
procedure shall be to restrike rivet or retorque fastener to
wing skin to its true source inside the tank, the exact point m~udmum permitted torque value. Any one rivet may be
where fuel is escaping from tank, must be detemlned. restruck only one time. If leak continues, replace the rivet.
(1) Use compressed air to blow and evaporate (1) Repair any sealant damage due to restriking
fuel from seams and crevices of leak area. Attempt to or retorqueing a fastener.
define exact point where fuel is escaping from tank.
(2) Remove sealant in immediate area of leak
(2) Small seep leaks can be traced with raw source using a sharp non-metallic tool. A
edges of tom paper. The fuzzy edge absorbs fluid and chisel-shaped formica tool is recommended. Scarf or
28-1 2-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
taper ends of existing sealant so that new sealant can CAUTION
form a continuous and smooth overlap. Ethylene glycol monomethyl ether (EGME) or other
additives are not recommended due to potential
(3) Thoroughly clean repair area using
Turco 657
Wipe Solvent or MEK. Wash one small area at a time. deteriorating effects within the fuel system.
To prevent redeposit of oil and dirt on surface, dry with
28-20-00 DISTRIBUTION
a clean cloth before solvent evaporates. Always pour
solvent onto wash cloth to prevent contamination of The fuel system is comprised of two fuel pumps, an
solvent supply; do not dip cloth into solvent. engine driven gear type pump and an electrically
driven auxiliary boost pump. The boost pump is
(4) Thoroughly dry clean area py blowing filtered connected to three separate switches on the
air over immediate area until there Is no possibility of
instrument panel. The LO boost is used to purge fuel
solvent or fuel entrapment under adjacent sealant.
vapor bubbles when operating at extreme high
(5) Apply sealant as required for repair (See temperatures or e~reme high altitudes, if necessary.
Figure 28-3). Repaired fillets must be blended into The HI boost is used to provide sufficient fuel pressure
ex7sting fillets with a spatula or an appropriate tool. to operate the engine at approximately 76016 power in
case of engine driven fuel pump malfunction.
(6) Allow all repaired sealant to cure tack-free
and apply two brush coats of PR 1005-L to repair area On S/N 25-0001 thru 25-1225 the primer switch
(Refer; to~patagraph 28-11-00,4,D). energizes a valve on the engine and tums on the boost
28-13-00 -SOAPLESS BUBBLE FLUID pump to supply atomized fuel to the engine induction
FORMULA PREPARATION FOR LEAK
system for engine starting.
CHECK On S/N 25-1226 thru PSITBA the pn’ming is

1. Materials.
accomplished by pressing the LO boost pump switch
ON, with M’octure control in Idle-~ut- Off. Use the Prime
A. Three ounces of either sodium bichromate, vs Temperature chart in the M20K POH/AFM.
potassium chromate, or potassium dichromate.
The engine driven pump incorporates a by-pass which
B. Three and one-quarter ounces Thickening Wax allows excess fuel to return to the supplying tank
(Carbo Wax 1500). through a separate retum line.
C. Thirteen ounces Alkaryl Sufonate wetting agent. 28-21-00 FUEL BOOST PUMP REMOVAL AND
D. Distilled water. INSTALLATION

2. Solution
Preparation. 1.Auxiliary Electn’c Boost Pump Removal.

A. Mix one of the compounds listed in item (A) A. Remove eledn’cal leads.
above with one cup distilled water. B. Turn fuel selector valve OFF.
B. Mix item (6) above with one cup distilled water. C. Disconnect inlet and outlet fuel lines.
C. Mix item (C) above with four to four and one half D. Remove fuel pump.
gallons distilled water until wetting agent dissolves
2. Reverse the removal procedure for reinstallation.
completely.
D. Mix the three ingredients (A), (6) and (C) CAUTION
together and add enough distilled water to make five Do not run pump dry for more than 15 seconds.
gallons ofsolution.
3. Adjust voltage for low boost pump operation to not aaceed
NOTE 8 PSI fuel pressure. This ~tage wlllvarywith incrividual pumps.
Amount of each ingredient may be reduced for See Section 2437-00 pocedures.
a smaller quantity of solution. Solution life is
about one week. NOTE
8 PSI is maximum fuel pressure to be supplied
CAUTION to engine when engine fuel pump is operating
Soapless bubble fluid is slightly corrosive and in low mode. Install calibrated gauge in fuel
must be completely removed by washing freely
line, with T-fitting between boost pump and
with water followed by scrubbing,
engine driven fuel pump. See detailed
instructions in chapter 24-37-00, paragraph 1.
CAUT(ON
B. (1) and 12).
S/N 259447 and later model aircraft: When
removing lower inboard access panels, caution CAUTION
should be exercised during removal so fuel Mixture control should be in FULL RICH
outlet tubes will not be damaged or bent.
position to check operating pressure, however
do not operate the boost pump for more than a
28-14-00 FUEL ADDITIVES
few seconds to prevent excessive flooding of
Under certain conditions of temperature and humidity, the engine.
water can be present in the fuel in sufficient quantities
to create ice formations within the fuel system. To NOTE
prevent this, add Anhydrous ISO-PROPYL Alcohol to When the aircraft willnot be flown for a period
the fuel supply in quantities not to exceed 3% of total of time, refer to Sections 10-1 0-01,10-1 0-02 3
fuel volume per tank. (Refer to TCM S.B. No. M82-8). 1 0-10-03.
28-1 3-00
10
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE

2&´•22-00 GASCOLATOR SCREEN CLEANING 2&31-00 FUEL SYSTEM DRAINS

Gascolator screen removal and cleaning; Fuel drains are installed in the inboard corners of the

(a) Remove belly skin just aft of nose wheel well, wing tanks and at the gascolator, the lowest point in
(b) Tum selector valve to OFF position, the fuel system. The engine manifold and engine-driven
(c) Remove safety wire on bottom nut and remove fuel pump drains join at a juncture on the right side of
nut, the engine. A single drain line dumps fuel overboard
(d) Remove sump and screen by pulling down, below the cowling at the left cowf flap opening. Tank
(e) Clean screen and reverse removal process to drains are Tank drains are recessed and spring loaded.
relnstall, Take care not to damage O-rings, An O-ring at the lower flange seals the valve seat.

(f) Lubricate O-rings with clean engine oil before in- 28-32-00 FUEL VENTS
stalling,
The fuel tanks are vented from the outboard upper
(g) Torque 10 to 15 in. Ibs.,
(h) Safety wire exactly as original installation. edge. This vent is routed outboard thru the wing struc-
ture and on S/N 25-0001 thru 25-0446, connect to an
2&23-00 FUEL INJECTION SYSTEM expansion tank located at W.S. 155.0. The expansion
Manual X30091 for service in- tank is vented overboard thru a NACA flush vent lo-
See TCM Fuel Injection
structions, cated on the lower wing surface. S/N 25-0447 and later
model aircraft have the expansion tank removed and
28-24-00 ENGINE PRIMING
the fuel filler inlet relocated so expansion takes place in
A diverter valve is installed in the fuel injection system the tank and is vented overboard through a NACA vent
between the throttle body and the manifold valve, on lower wing surface.

Operating the primer switch in the cockpit turns on the NOTE

auxiliary fuel pump to the high boost position and ac-
tlvates the diverter valve. The diverter valve bypasses
important that the fuel tank vent tube protrude
It is

some of the fuel going to the manifold valve and

only enough to be flush with lower wing skins.
directs the fuel to two atomizing nozzles in the forward 2&40-00 INDICATING
end of the induction risers. See TCM engine overhaul
28-41-00 FUEL QUANTITY INDICATING
manual for servicing instructions.
TRANSMITTERS
Use the Prime vs Temperature chart in the M20K
POC-(/AFM (SECTION IV). The fuel quantity indicating system has two fuel quan-
tity transmitters in each wing tank. The transmitters are
28-25-00 FUEL SELECTOR VALVE REMOVAL
INSTALLATION
electrically connected to the fuel gauges in the cluster
gauge and work in series with each other.
The fuel selector valve is located below the floor board 1. Fuel Quantity Transmitter Removal.
lust aft of the console. A. Drain fuel from tank.
1. Drain both fuel tanks. B. Remove transmitter wires.
2. Disconnect inlet lines at valve body. C. Remove the six screws attaching transmitter to
3, Disconnect outlet line at valve body, doubler.
4, Remove handle above floorboard in fuel selector D. Remove transmitter.
pan. 2. For reinstallation, reverse the fuel quantity trans-
5. Remove screws that mount valve to the tubular mitter removal procedure.
structure. A. Make certain wire from outboard transmitter
6, Remove valve, goes under head of insulating sleeve against the in-
7, Reverse the removal procedure to install valve. board transmitter ffange and not under the mounting
8, Leak check fuel system, screw head.

NOTE 2&42-00 FUEL QUANTITY INDICATOR

It is recommended that the fuel selector valve be Two fuel quantity gauges are in the instrument cluster
replaced each 500 houre of operation or if the gauge. These gauges indicate gallons of fuel remain-
valve becomes difficult to operate. ing. Each gauge operates by the change in resistance
(Anderson-Brass valve only) of two transmitters located in the fuel tanks.

2&´•30-00 DUMP 2&43-00 FUEL QUANTITY ADJUSTMENT

PROCEDURE
The fuel tanks can be maintenance pur-
emptied for
the drains in the lower 2&43-01 FUEL TANK TRANSMITTER
poses by (1) removing sump
ADJUSTMENT
panel of each fuel tank and allowing fuel to drain into
suitable container or (2) disconnect the fuel line at out- (S/N 25-0001 thru 25-0446)
let of the electric fuel pump and use HI boost to trans-
AIRCRAFT MUST BE LEVEL
fer fuel from both tanks into a suitable storage con- -TO CALIBRATE FUEL GAUGES-
tainer,

28-22-00
 MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE

S/N 25-0001 thru 25-0446 S/N 25-0447 thru 25-TEA.

1, Fuel tanks-EMPTY. 1. Fuel tanks EMPTY.
2, Add unusable fuel (3.7 Gal.). Indicator should 2. Add 1.5 gallons unusable fuel gauge to read "E"
read "E" to 1/2 needle width below "E". Inboard floats to 1/2 needle width below "E".
may be adjusted by holding arm near transmitter and 3. Add 2 1/2 to 3 gallons (part of additional 9 gallons
bending outer arm, (do not bend by forcing arm required for 1/4 gauge reading). Adjust low fuel warn-
against stops), ing trimmer in the annunciator panel so low fuel warn-
3, Add 2 112 to 3 gal, (part of additional 9 gal. re- ing light just comes on (See Section 24-33-00, 4. A and
quired for 1/4 gauge reading). Adjust low fuel warning B).
trimmer in annunciator panel so that warning light just 4. Add 6-6.5 gals, for 114 gauge reading. Continue
comes on (see Section 24-33-00, 4. A and B). adding fuel in 9 gallon increments for 1/2 and 3/4
4, Continue calibration by adding fuel in 9 gal, incre- gauge readings. Gauge to read within 1/2 needle width.
ments, (-1, +2 gal.) for 1/4, 1/2, and 3/4 gauge read- 5. Finish filling tank until fuel just starts to spill over
ings, Gauge to read within 112 needle width. Outboard outer wing surface and record total quantity less the
float may be adjusted if required for 1/2 and 314 gauge unusable fuel.
readings. 28-43-03 FUEL QUANTITY GAUGE
5, Finish filling tank and verit~ total quantity less un-
ADJUSTMENT
usable fuel.
Cluster gauges installed on MID 1981 aircraft and any
spare units installed on earlier aircraft have this adjust-
28-43-02 FUEL TANK TRANSMITTER ment.
1. Remove plastic plugs from holes in top left of
ADJUSTMENT
cluster gauge case. With "unusable" fuel in tanks, ad-
(S/N 25-0447 thru 25-TEA just pot marked "null" so gauge reads "E". If inter-
mediate or "P’ indications are out of tolerance as tank
is filled, adjust pot marked "gain" for correct calibration.

28-90´•00 -MISCELLANEOUS

28-91-00 TROUBLE SHOOTING FUEL

SYSTEM

TROUBLE PROBABLE CAUSE REMEDY

Fuel gauge not indicating. Broken wire. Check and Repair.

Faulty transmitting unit. Replace and adjust.

Open circuit breaker. Check and reset.

Fuel gauge indicates full when tanks Incomplete ground. Check ground connection at transmitter.
are not fun,

Broken wire. Check and repair.

No fuel pressure indication Tankempty. Check and setvice tank.

(callbrated test gauges connected).

Defective fuel pump. Check pump for proper pressure buildup.

Check for obstruction in boost pump
screen. Check engine fuel pump and
check valve.

Open fuel line. Repair or replace line.

Fuel selector in "OFF" Select proper position.

position.

28-43-02
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
TROUBLE SHOOTING FUEL SYSTEM (conY.)

TROUBLE PROBABLE CAUSE REMEDY

Fuel pressure low or surging Obstruction in inlet side of Check and clear fuel lines. Replace
(calibrated test gauges connected.) pump. Faulty engine pump. rebuild Dump. Check fuel lines and
nection ~ot leakage or damage.

Fuel selector not in proper Select proper position.

position.
Air leak in system. Repair leak.

28-92-00 FLARED FITTINGS relubricated before they are reinstalled. Torque all fit-
tings in accordance with flare fitting torque chart,
When installing flared fittings and hoses, make sure the
Chapter 5, Figure 5-1.
threads are properly lubricated with W-P-236
petrolatum per (Figure 28-5). When previously installed
flttlngs are removed, they should be wiped clean and

~-LUBRICATE LUBRICATE
TAPERED ~-LUBRICATE I
PIPE THREADS

DO NOT LUBRICATE
STRAIGHT THREADS~ \I FEMALE TH‘READS

’NEVER ALLOW LUBRICANT

TO CONTACT THIS SURFACE

LUBRICATION OF FLARED FITTINGS FIGURE 28 5

28-92-00
13
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE

BLANK

28-92-00
14
 OLDWILLWAYNE

CHAPTER

ICE AND RAIN

PROTECTION
 MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CHAPTER 30

ICE PROTECTION

LIST OF EFFECTIVE PAGES

CHAPTER
SECTION
PAGE DATE
SUBJECT

1/2BLANK 9-97
a0-Effectivity
3. 9-97
30-Contents
5. 9-97
30-00-00
6. 9-97
30-61-01
7. 997
30-61-02
8. 9-97
30-61-02
9. 9-97
30-62-00
10 9-97
30-67-00

TABLE OF CONTENTS

CHAPTER
SECTION
SUBJECT PAGE
SUBJECT

General 3
30-00-00
30-30-00 Pitot, oeschptidn g Operation 3
3
30-60-00 Propellers, Descn’ption 8 Operation
Schematic Propeller De-ice 4
30-60-01
SeM’ce Guide 4
30-61-00
HelpfulTips 4
30-61-01
30-61-02 TroubleShooting Chart 4
AmmeterTest 8
30-62-00
De-lcerTimer Check 8
30-63-00
HeatTest 9
30-6600
9
30-65-00 Continuity Test
Brush to Slip Ring Reastance Test 9
30-6800
Brush Assembly Resistance Check 9
30-67-00
Brush Replacement 9
30-68-00
Brush ReplacementlAlignment 11
30-68-01
Alignment of Slip Ring 11
30-69-00
Senricing/Cleaning 12
30-70-00

30-EFFECTIVITY
I/2BLANK
SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

OLDWILLWAYNE
30-0040 -GENERAL Propeller ice removal is accomplished by optional
electrically heated de-ice boots bonded to each
The M20K aircraft incorporates an alternate air system
that is designed to be opened manually (25´•0001 thru
propeller blade. The system uses the airplane’s
electrical power to heat the de-ice boots in cycles
25-0780) or automatically (25-0781 thru 25-TEA) any controlled by a timer. The ON/OFF switch is located on
time the air intake system becomes blocked. This
the switch panel in Front of the pilots right knee. A
system should be inspected to assure that no heated current flow of 8 12 amps (12 Volt system) (8 amps
air is enten’ng the induction system dun’ng mutine
24 Volt System) is depicted on the propeller de-ice
engine operation. (See Section 71-62-00 for n’gging ammeter located in front of the co-pilot at the top of the
instructions). radio panel. On the 12 Volt aircraft, a deflection of the
This aircraff includes as standard equipment a heated ammeter needle will be noticed approximately every 90
pitot tube assembly and may also include an optional seconds; this is due to the cycling action of current flow
electn’cally operated propeller de-ice system. to the circuits within the boot as controlled by the timer.
On the 24 Volt system aircraft, S/N 25-1000 8 ON, the
30-3090 -PIIOT, DESCRIPTIONAND ammeter will go full defledjon each 90 seconds as the
OPERATION
timer turns the de-ice boots ON/OFF/ON. SM 25-1225
A standard heated pitot tube is located on the left wing thru 25-TEA have a BLUE light, "PROP DE-ICE", on
at Wing Station No. 145. The pitot heat circuit breaker the annunciator panel. This light will illuminate at each
switch located on the panel in front of the pilots n’ght cycle (every 90 seconds) the boots are drawing current
knee supplies power to the pitot tube heating element. (cycling ON/OFF/ON). The BUS LOAD meterwill show
A BLUE light will illuminate on the annunciator panel an additional 8 amps each 90 second interval as the
when the Pitot Heat switch has been pushed ON and timer tums the de-ice boots ON/OFF/ON. This is
current is being drawn by the element. On some normal operation. The timer is located on the circuit
foreign aircraft a RED light will illuminate when the pitot breaker panel side tray above the co-pilots n’ght knee.
heat element is NOT drawing any culient and will be Deicer boot replacement should be done per B.F.
OFF when properly operating. Goodrich Report 59-728J which is supplied with the

306090 PROPELLERS, DESCRIPTION AND

kits for replacement boots (Fig. 30-1).
OPERATION

mli --I´•

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14 VOLT SYSTEM UIWIUIK

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28 VOLT SYSTEM

PROPELLER DE-ICESYSTEMS FIGURE30-1

30-00-00
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
3060-01 -PROPEU-ER DE-ICE
POWER REQUIREMENTS FOR 14 VOLT SYSTEM

TIME CYCLE ELEMENT HEATED TIME ON SEC’s) LOAD (AMPS)

OUTED 90 8-12
D
INBD 90 8-12
F

TOTAL CYCLE TIME 3 MINUTES

POWER REQUIREMENTS FOR 28 VOLT SYSTEM

ON/OFF 90 8

TOTAL CYCLE TIME 3 MINUTES

RECOMMENDED WIRE SIZE CHART

AWG SIZE MAX LENGTH

LOCATION

#14 15’
BUS BAR TO TIMER

#18 5’
TIMER TO GROUND

15’
TlMER TO BRUSH MODULE
BRUSH MODULE TO GROUND

~20 5’
SHUNT LEADS

2. Use the "heat test" (30-64-00) and "load meter test"

30-6140 -SERVICE GUIDE
(30-62-00) to determine which De-leers are not
INTRODUCTION operating. Use win’ng schematic to trace circuits.
Wnether in flight or during ground testing, the BUSS
3. Excess current reading on the BUS LOAD meter
LOAD meter can be used to determine the general
nature of most electn’cal problems. The Trouble may indicate a power lead shorted to ground. Thus,
when trouble of this nature is found, it is vital that the
Shooting Chart is based, pn’man’ly, on the use of the
load meter and it is assumed that the user understands grounded power lead be located and correded.
all normal operating modes of the system. (See 4. A conside~able number of timers have been returned
Section IX of P.O.H.). Read all of the "Trouble" entn’es for repair which proved, on test, to be fully operable.
to locate the one matching the conditions of the system Before concluding that the timer is faulty, test it per
being checked. The "Probable Cause" and "Remedy" "De-lcer Timer Check" (30-63-00).
entries pertinent to each trouble are arranged in the resistance tests, use a "megger"
5. For insulation
recommended checking sequence. B.F. Goodn’ch
C’Meg" type insulation tester, James G. Biddle
maintenance Manual, Report No. 68-04-712B is
recommended for complete maintenance actions. Company, Plymouth Meeting, PA.) or other tester
having a 500 VDC, 1000 megohm capacity.
30-61-01 HELPFUL TIPS 6. Defective win’ng in propeller mounted components
in ground
1. The meter reading will be slightly lower when the may be indicated by normal current readings
checkouts @ropellers not rotating) but low current with
systemis operated on battery voltage than when the
engine is running. propellers rotating at cruise RPM.

30-6192 -TROUBLE SHOOTING CHART-PROPELLER DE-ICE

PROBABLE CAUSE REMEDY

TROUBLE

Ammeter shows 0 current No power from aircraft. If no voltage into circuit breaker,
all phases of the timer cycle. locate and correct open.

30-60-01
 ~1120K MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE
TROUBLE SHOOTING CHART-PROPELLER DE-ICE (conY.)

PROBABLE CAUSE REMEDY

TROUBLE

Locate and correct short before

Ammeter shows 0 current Tn’pped circuit breaker.
all phases of the timer cycle. resetting circuit breaker.
Circuit breaker or switch faulty. If no voltage at circuit breaker output
with voltage at input and circuit
breaker does not reset, replace
circuit breaker. If voltage is OK at
output, check switch in same
manner. If voltage is OK at switch

output, 90 to "Ammeter Faulty".

Ammeter Faulty Test ammeter per Section 30-62-00.

Open ammeter to timer. Disconnect harness at timer and

check for appropn’ate voltage at
hamess Pin B (12V); Terminal C
(24V) to ground. If none, locate and
correct open.
Disconnect wire harness at brush
Open timer to brush assembly.
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 coreet open or high
resistance in wire harness.
Check continuity from appropriate
pin or lead to ground; if high
resistance is indicated, check

ground wire for breakage and

ground connections for correctness
and tightness. Comet as required.

Open in De-leer, DPlcer wire Disconnect De-leer leads and check

hamess or slip ring assembly resistance per B.F. Goodrich,
leads. Report No. 59-728 If not OK,
replace faulty De-leer boot. If OK,
check for(and repair) open in de-ice
boot wiring harness leads. See
Section 5-4.5, 8.8. Goodrich Report
6&04-7218. Ohmmeter needle
must not flicker when leads are
stretched or flexed. Replace as

required.

Open on both ground brushes. Remove brush block assembly and

check both ground brushes for

continuity between the brush and

pigtail lead. If an open is found,
repair brush block assembly. If OK,
reinstall and check for proper face
alignment and brush projection per
8.8. Goodrich, Report No. 59-728.
30-61-02
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
TROUBLE SHOOTING CHART-PROPELLER DE-ICE (con’t.)

TROUBLE PROBABLE CAUSE REMEDY

See "Open Timer to Brush

Ammeter shows normal current Open in win’ng between timer and
brush block assembly. Assembly" above.
part of cycle,zero current rest of
cycle.
Open in De-leer or de-ice boot See "Open in De-leer" above.
wire harness.
Timer faulty. Test timer per Section 30-63-00.
Faulty brush block assembly. Check for broken brushes and test
for opens.

Ammeter Sh(MS normal current part Open circuit or high resistance in See "Open in De-leer" above.

ofcyde, lanr cun~nt rest of cyde. De-leer or slip n’ng assembly leads.

Inner and Outer De-leer elements Locate and repair incorrect lead
heating same phase tin sen~es) connections. See wiring
schematic. (12 V aircraft only).

High resistance in circuit Check contact of brushes to slip

with low current. n‘ngs per Section 30-66-00 or B.F.
Goodrich Report 6804-714;
correct as indicated; check wiring
from timer to De-leers for loose or

corroded connections partially

or

broken win’ng. Correct as required.

Ammeter shows low current over Aircraft voltage low under Check voltage into switch.
entire cycle, normal operating conditions.

Ammeter, Switch, or C/B faulty. Check voltage up to and out of

ammeter, switch and C/B. Test
ammeter per Section 30-62-00 or
B.F. Goodrich Report 68-04
-712B. If low
output is found
through any of these items,
replace defective component.
High resistance up to timer. Check for partially broken wire, or
loose or corroded connection in
win’ng between aircraft supply and
timer input Correct as required.
High contact resistance in timer. Test timer per Section 4-2.4, B.F.
Goodn’ch, Report No. 59-728.
One De-leer element (or wiring Perform a heat test on each
connections to De-leer) in each De-leer per Section 30-64-00.

cycle out. Replace defective components.

Ammeter shows excess current Power lead shorted to ground. Check power leads from ammeter
over entire cycle, to timer, then to De-leers for
evidence of damage or arcing.
With de-icing system switch OFF
and timer harness disconnected,
check insulation resistance (use
"Megger) to ground from timer
harness Pin B (12V);
30-61-02
 M20K MOONEY AIRCRATT CORPORATION
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE
TROUBLE SHOOTING CHART-PROPELLER DE-ICE (con’t~)

PROBABLE CAUSE REMEDY

TROUBLE

Power lead shorted to ground. Teminal C (28V). Disconnect

Ammeter shows excess
harness at brush assembly and
current over entire cycle.
repeat check for applicable brush
assembly hamess connections.
(See Section 30-60-01). If ground is
indicated, locate and correct.
Ammeter faulty. Test ammeter per Section 30-62-00.

short Disconnect leads at brush block

Ammeter indicates normal Short to ground or
between adjacent circuits, timer assembly timer. With "Megger",
current part of cycle, excess
check insulation resistance from
current remainder of cycle. to brush block

(12V aircraff only) power leads to groung and between

adjacent circuits. If shorted or

grounded, repair.
locate 8
Clean slip ring assembly with MEK.
Short between slip rings.
Short to ground or between Eledn’cally isolate brush assembly
adjacent circuits in brush block. and test per Section 4-6, B.F.
Goodrich Report 68-04-7128.
short Isolate brush assembly. WRh
Short to propeller or

between two adjacent "Megger", check insulation

circuits-slip n’ngs to De-leers. resistance from one rign of slip n’ng

assembly to bare prop. Reading
should be as least .5 Megohoms
after one minute. If not OK,
disconnect the slip ring leads one

set at a time to trace short. If OK,

disconnect slip n’ng leads and check
insulation resistance between slip
rings; reading should be at least .5
megohms after one minute. If not
OK, clean assembly thoroughly with
standard solvent and wipe clean
with MEK and retest. Replace as
required.
Timer faulty. Test timer per Section 30-63-00.

Disconnect harness at timer and

Ammeter does not cycle Timer ground open; timer not
check ground connection with
("flicker") each 90 seconds, cycling.
ohmmeter from Pin A (12V) or

TerminalG (24V).
Timer contacts welded together Test timer per Section 3063-00. If

(caused by short in electn’cal timer is faulty, repair or replace it,

system). but insure that short causing original

failure has been located and
corrected.

Ammeter flickers between 90 Loose connection between Trace win’ng from power source to
second phase periods.(l2V) aircraft power supply and timer timer input. Insure that good
input, electrical contaets are made at each
connection in the circuit
30-61-02
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
TROUBLE SHOOTTNG CHART-PROPELLER DE-ICE (conY.)

PROBABLE CAUSE REMEDY

TROUBLE

Ammeter flickers between 90 Loose or poor connection; timer to If trouble occurs only part of cycle,
De-lcew. detemnine which De-leer is
second phase peniods.(l2V)
affected, check for rough or dirty
slip n’ngs causing brush to skip.
Check circuits for loose or poor
connections.
Timer cycles erratically. Test timer per Section 30-63-00.

Radio noise or interference with Brushes arcing. Check brush alignment. Check for
De-leers on, dirty orrough slip n’ngs. If found,
clean, machine or replace slip ring
assembly. Check slip ring
alignment.
Loose connection. See ammeter flickers between 90
secondperiods" above.
Switch or circuit breaker faulty. Place jumper wire across switch
or circuit breaker; if radio noise
disappears, replace switch or
circuit breaker.
Win’ng too close to radio Relocate De-leer wiring at least 8"
equipment or associated wiring. From radioequipment and wiring.

not cor~-ect. Crossed connections between Check system wiring against

Cycling sequence
timer and De-leers. circuit diagram.

Rapid brush wear or frequent Brush block out ofalignment. Check brush alignment. Correct
breakage, as required.See section 3.33 of
B.F. Goodn’ch, Report No.
68-04-714. Correct as necessary.

Slip ring wobbles. Check slip n’ng alignment with dial

indicator per Section 30-69-00.
Rough slip n’ngs. Re-machine/re-finish.
Dirty slipring surfaces. Clean slip n’ngs with MEK.
Brushes arcing. Check brush alignment.

i. With winng harness disconnected from Terminal a

30-62-00 -AMMETER TEST at the timer and the de-=icer switch in the ON position,
check voltage from Pin B (12V), Ifrom wire from shunt
At some convenient point between bus bar and
(24Vll of the harness to ground. If no voltage is
ammeter, connect a volt ohmmeter with an ammeter
scale or a standard ammeter into the circuit and, with
present, the timer is NOT at fault; however, if system
voltage is present, check circuit from hamess plug Pin
the De-leer Switch ON, check the amperage being A (12V) [from Terminal G (24Vll to ground with an
used by the De-leer system. The reading of the
ohmmeter. If no circuit is indicated, the fault is in the
standarCI ammeter should closely agree with the
ground lead rather than the timer. If ground connection
reading obtained from the De-leer ammeter. Tum is open, the timer step switch will not change position.
De-leer Switch OFF and remove volt-ohmmeter or
standard ammeter from circuit. If ammeter readings 2. After ground and power circuits have been
were significantly different and rest of de-icing system checked, connect a jumper wire between Pin B of the
checks out satisfacton’ly, see Ammeter Checkout, timer receptacle and Terminal B of the connector plug
Section 67 of B.F. Goodn’ch Report No. 68-04-7126. and from Pin A of the timer receptacle to ground. With
the de-icing system switch ON, check voltage to
30-63-00 DE-ICER TIMER CHECK ground from Pin B of the timer (12V). The voltmeter
should indicate approximately 12 volts (or 24V) when
Experience in the field has indicated that often the the aircraft battery supply is used. Ne~, check DC
timer is considered defective when the source of the voltage to ground from pins D and F (12V) [Pin C
trouble lies elsewhere. Forthis reason, the tests should 24V]; the points at which the system voltage is
be performed before the timer is removed as defective.
30-62-00
 M20K MOONCIAIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
volts for S/N 251000 thru 25TBA. Also refer to B.F.
impressed in sequence to cycle power to the propeller
de-icers. Each of the pins should read 12 volts in Goodn’ch, Report No. 59-728, section 4.2.4. for test
thru 25´•0999 8 24 criten’a.
sequence of cycle for S/N 25-0001

TIME ON AREAS OF PROP DE~ICERS HEATED

TIMING SEQUENCE
================================================---===i~====---=;--======I’==

Pin D 90 sec. Outboard Section )-12VAIC only

Pin F 90 sec. InboardSection )12VAIConly

90 sec. Both Blades ON then OFF )24V

Pin C
AIC only
==============I-==--==---=---====--=======================---==---=========

NOTE
is turned OFF, but will begin its
The timer does not reposition itself to start at Pin D when the system
cycling atthe same position in which is was when last turned OFF. Cycling will then proceed as
before. (25-0001 thru 25-0999)
of 12 volts DC (25-0001 thru 1. Pin D (12V) of plug CTerminal C 24V) to the
After a voltage reading
the pin outboard tenninal of one prop boot.
25-0999) is obtained, hold voltmeter probe on

until the voltage drops to zero before moving the probe 2. Pin F of plug (12V) to outboard terminal of one
to the ne>d pin in the sequence noted above. After the propeller boot
cycling sequence has been etablished, turn de-icing
the 3. Pin F of plug (12V) CTerminal G 24V) to airframe
system switch OFF at the beginning of one of
"on-time periods and record the letter of the pin at ground.
which the voltage supply is present to facilitate 4. Ground terminal of one prop boot to ground.
performance of the following test. (25-0001 thru
25-0999). 30-66-00 BRUSH TO SUP RING RESISTANCE
TEST
30-64-00 HEAT TEST
To check for incorrect resistance or the presence of a
Before this test can be performed, the jumper wire
short or open circuit at the brush-to-slip ring contact,
installed in paragraph 30-63-00, 2, for the timer test disconnect the hamess at timer and check resistance
must be removed so that the connector plug can be
from each De-leer circuit lead, (Pins D 8 F of hamess
replaced in timer receptacle (25-0001 thru 25-0999);’ plug, 12V) CTerminal C, 24V) to ground with a low
reconnect wire to Terminal B of timer for 25-1000 thru are not 1.55
range ohmmeter. Ifthe resultant readings
25-TEA. Two men are required to perform this test, disconnect De-leer lead straps to
ammeter to 1.78 ohms,
one in the pilot’s compartment to monitor the Individual boot
boots. The man in measure heater resistance individually.
while the other checks the De-leer
resistance should measure between 4.58 and 526
the pilot’s compartment tums the De-leer system circuit
ohms. If readings in the first check are not within
breaker switch ON while the man outside feels the
De-leer boots to see if they are heating properly. The
accepted limits but those in second check are, the
for trouble is probably in the brush-to-slip ring area. If
man in the pilot’s compartment observes ammeter
readings in the second check are also off, the De-leer
proper readings 8 12 amperes_!12V) [(8 amps 24~3] concemed is damaged and must be replaced.
throughout timing sequence. Tne ammeter needle
should deflect every 90 seconds in response to the 30-6790 BRUSH ASSEMBLY RESISTANCE
switching action of the timer. Each time this occurs, the CHECK
man in the pilot’s compartment must notify
the man
inspecting propeller De-leer boots so that the latter can To check for an open circuit, a short, or high resistance
change position of his hands to check proper heating in the brush assembly, measure resistance from face
sequence of propeller De-leer areas (12
volt AIC) If of the brush to its terminal studs with a low range
any irregularities are detected a continuity check ohmmeter. If this resMance measures over 0.013
should be performed on the win’ng from timer to brush ohms, locate and repair cause of excessive resistance.
block holders and propeller De-icer terminal If resistance is infinite, locate and correct open circuit
or ground, or else replace brush assembly.
Check
connections.
resistance between the three terminal studs. This
CAUTION resistance should not be less than 5 megohms.
Stand clear of propeller, verify magnetos OFF.
Use extreme caution during this procedure. 30-68-00 BRUSH REPLACEMENT

The propeller De-leer brush module should be

CONTlNUITY TEST
30-65-00 replaced when a minimum of 114 inch of brush
After removing the plug from the timer, use an ;material remains. It is good practice, however, to
ohmmeterto check continuity from: replace modules when 3/8 inch of brush still remains.
30-6600
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
X-DIMENSION (IINCHES>
MODULAR BRUSH ASSEMBLIES MUST REPLACE

ALL MODULES HAVING

BRUSHES WITH RODS 17/64

ALL MODULES HAVING

BRUSHES WITHOUT RODS 1-7/64

DURING MEASUREMENT ONLY 1/16 INCH OF BRUSHH SHOULD

BE ALLOWED TO PROTRUDE FROM BRUSH BLOCK. THIS IS
THE NORMAL POSITION OF THE BRUSH WHEN INSTALEI)
ON THE AIRCRAFT. SMM30-2

MEASURING BRUSH WEAR FIGURE 30-2

Qol
3E2042-1

O
V~g;Su cEwnn BRUSHES ON
RINGS ~HRU 364 OP
1 SUP RING ROTITION

14 10 6

FORE 8 AFT POSITIONING

I

1-9/64 3/8

7 11~) t 1/6 1/32

2’

SPRING PRESSURE;/ LIODUUR BRUSH

P/N 3E2042-1 2
7
3 soo-j

MODULAR BRUSH ASSEMBLIES 6 ALIGNMENT POSITIONS -382042-?

30-68-00
10
 M20K MOONN AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE

B~P,

~PI

~I

SM30-4

ALIGNMENT OF SLIP RING FIGURE 30 5

ALTERNATE MODULE STACKING ARRANGEMENT
FIGURE 30 4
H. Check assembly for proper alignment.
30-68-01 BRUSH REP LACEMENTIAUGNMENT i. Refer to B.F. Goodrich Report No. 6&04-712(8)
brush wear as shown (Fig. 30-2); for complete maintenance informantion.
1. Measure
X-dimension (inches) given indiates when modules 1.Brush Module Assy. 3E2011-1
MUST be replaced. 2. Brush Module Assy. 382011-1
not offered, individually, as 3. BNsh Module Assy. 382011-1
2. Brushes are
brush wears out, the module 6. Spacer4E2218-3
replacements. When a
7. Spacer4E2218-1
containing it should be replaced as follows:
10. Screw MS24693S35 ~-32 x 1-3/8)
A. Dismount modular brush from aircraft
assembly 12. WasherAN960CG
and disconnect 13. Lockwasher MS35333-7
by removing attachng hardware,
engine wire harness. 14. Nut MS35649-262

B. Remove assembly screws and separate The above components make up a 3E2042-Q stack
modules and spacers. Refer to B.F. Goodn’ch, Report No. 59-728, Section
8 3.3.4.
part number of each module is etched into
C. The 6.52 for brush replacement and Section 3.3.3.
surface of plastic housing; replace with same part for brush to slip ring alignment.
number module. 30-69-00 ALIGNMENT OF SUP RING
Restack modules and spacers as shown
D. To check alignment of slip n’ng assembly, securely
(Figure 30-2). Check AIB/C or A/B (24V) stacking attach a dial indicator to the engine and place the
arrangement and locatio of spacers. If there is pointer on a slip n’ng (Figure 30-2). Grasp the propeller
interference between adjacent n’ng terminals, re-orient blade and rotate it slowly, noting the deviation
of the
center module as shown. (Figure 30-4). indicated on the gauge.
slip ring from a tiue plate as

E. On 382042 series assemblies, make sure fiat Check that the total run-out does not exceed 0.008
washer is positioned between star washer and inch total indicator reading CLlR).
housing. Make sure that assembly b square, then CAUTION
tighten screuvs.
propeller thntst
Due to the loose fit of some
F. Reconnect aircraft wire harness to applicable bearings, a considerable error may be induced
"A", "B", or "C" terminals of modules. Insure that i, the readings by pushing in or pulling out on
adjacent n’ng terminals are not touching. the propeller while rotating it. Care must be
aircraft with attacfiing taken to exert a uniform push or pull on the
Install assembly
G. on

hardware removed. propeller to hold this error to a minimum.

30-6&01
MOONN AIRCRAFT CORPORAT~ON M20K SERVrCE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CAUTION 30-70-00 -SERVICINGICLEANING
Do not, under any citcumstances, attempt to Thoroughly cleaning the slip n’ng area with MU< or
correct run-out of slip ri gs by shimming standard engine degreaser on a routine basis is
assembly or changing the torque of mounting recommended. Keeping the brushes rree of dirt, oil
screws or bolts. those
grease and carbon build-up will prevent
contaminants from being transferred to the slip n’ng.
If the slip ring run-out is within the limits specified, no
corrective action is required. If it is not within the limits,
check for dirt on the n’ng gear mou ting surfaces,
clean, and recheck alignment. If run-out is still out of
tolerance, return slip ring assembly to B.F. Goodn~ch
Co.

30-70-00
12
 OLDWILLWAYNE

CHAPTER

LANDING GEAR
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CHAPTER 32

LANDING GEAR

TABLE OF CONTENTS
SUBJECT PAGE
CHAPTER
SECTION
SU&IECT

Gene~al 5
32-00-00
Main Landing Gear and Doors 5
32-10-00
Main Gear Removal 5
32-10-01
Main Gear Installation 6
32-10-02
Main Gear Door Rigging 6
32-10-03
Main Gear Door Rigging 6
32-10-04
Inboard Door Rigging 7
32-10-05
installingAssist Bungee 8
32-10-06
Nose Gear and Doors 8
32-20-00
Nose Gear Removal 8
32-20-01
Nose Gear Installation 8
32-20-02
Nose Gear Door Rigging 9
32-20-03
E~dension and Retraction 9
32-30-00
Gear System Operational Inspection 9
32-30-01
Main Ldg Gear System Rigging 10
32-30-02
SM 25-0001 thru 25-0999 10
S/N25-1000thru25TBA~ 11
Nose Ldg Gear System Rigging 13
32-30-03
32-30-04 Emergency Gear E>dension System Fiigging 14

Landing Gear Actuator, Clutch 15

32-30-05
Landing Gear Actuator 16
32-30-06
Manual Emergency Gear E~dension System 16
32-30-07
FinalCheck 16
32-30-08
Trouble Shooting 17
32-32-00
Wheels and Brakes 18
32-40-00
Main Wheels 18
32-40-01
Main Wheel Disassembly/Assembly 18
32-40-02
Nose WMleel Dissassembly/Assembly 19
32-40-03
Brake SystemlBreak-ln Procedures 19
32-40-04
Trouble Shooting Brake System 22
32-41-00
Steen’ng 22
32-50-00
Nose GearSteen~ng System 22
32-50-01
NoseGearSteer’ng &Tracking 23
32-50-02
Position and Warning 23
32-60-00
Electiic Gear Safety Devices 23
32-60-01
Landing GearWaming System 24
32-60-02
32-60-03 Airspeed SafetySwitchAdjustment 24
Miscellaneous 24
32-80-00
Landing Gear ShockDisc’lnspection 24
32-81-00

SZCONTENTS
Page 3/4BLANK
SERVICE AND MAINTENANCE MANUAL ~20K MOONfl AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 32

LANDING GEAR

LIST OF EFFECTIVE PAGES

CHAPTER PAGE DATE

SECTION
SUBJECT

1I2BLANK 9-97
32-Effedivity
32-Contents 3/4BLANK ´•9-97

32-00-00 5´• 9’97

32-1 0-02 6´• 9-97

32-1 0-05 7´• 9’97

32-1 0-06 8´• 997

32-20-03 9´• 897

32-30-02 10 897

32-30-02 11 9-97

32-30-02 12 9-97

32-30-03 13 9-97

32-30-04 14 9-97
32-30-05 15 9-97

32-30-06 16 9-97

32-32-00 17 9-97

32-40-00 18 9-97

32-40-03 19 9-97
32-40-04 20 9-97

32-40-04 21 9-97
32-41-00 22 9-97

32-50-02 23 9-97

32-60-02 24 9-97

32-81-00 25 997

32-81-00 26 997

32-EFFECTIVITY
Page I/2BLANK
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
32-00-00 GENERAL pedals. @ual brake system is optional for co-pilots). In-
dividual wheel brakes are avanaale by depressing
The landing gear is operated by an electn’cal motor either left or right pedal. Parking brakes are actuated
driven actuator. The travel during the extend and
by depressing both brake pedals and pulling the park-
retract cycle is controlled by down and up limit
ing brake control caMe knob. This cable actuates a
switches located beneath the ffoorboard under the lever on the parking brake valve and traps the
pilots seat. Power is to the actuator through a
supplied hydraulic fluid from the valve to the wheel cylinders
set of gear selection switch. The
relays actuated by the thus holding the pucks to the discs. Release the park-
gear selection switch is located at the top of the instru- ing brakes by pushing the parking brake knob in. This
ment panel in front of the pilot. The actuator worm releases hydraulic pressure at the wheel cylinders and
gear barrel nut is connected to the retract bellcrank therefore releases the brake discs.
which Is connected to push-pull retract tubes and
bellcranks throughout the entire retraction system. An 32-10-00 MAIN LANDING GEAR AND DOORS

airspeed safety switch is mounted to the back of the 32-10-01 MAIN GEAR REMOVAL
airspeed indicator and incorporated into the landing
gear electrical circuit to prevent landing gear retraction 1. Raise aircraft on jacks.
while on the ground until a safe takeoff speed is 2. Partially retract gear as described in Section 32-
reached. A by-pass switch is installed adjacent to the 60-01, pam 1.
gear selection switch in order to override the safety 3. Disconnect gear door links and brake lines. Cap
switch circuitry if the gear does not retract. all lines and fittings.
4. Remove gear door(s) and mud guard (if desired).
The gear legs are constructed of welded chrome- 5. Detach main gear retracting tube M, (Ftgure 32-
mdybdenum tubular steel, heat treated for greater 9) from retracting truss (G), and remove bolts (H) from
strength and wear resistance. Main gear attaching retracting truss mounting Mock.
points have bushings installed in the gear mounting 6. Remove small skin panel covering aft trunnion
box attached to the wing spar. The steerable nose gear bearing (25-1000 thru 25-TEA).
mounts to the cabin tubular steel frame.
NOTE
NOTE Steps 7 thru 9 apply to 250001 thru 250999 only.
Heat treated components should NOT be repaired;
replace them. 7. Remove grease fittings from forward gear support
trunnion-shaft bearing.
The main gear wheels have hydraulic disc brakes with 8. Retract gear by hand until a 2 inch thick wood
a parking brake valve incorporated into the system. Mock (C), (Figure 32-1), can be inserted, as shown, to
hold gear in retracted position.
Rubber discs in the gear leg assemblies absorb the A Remove cotter key and nut at (F) from spring
shock of landing and taxiing. connecting link (D), (Figure 32-1).

MANUAL-EMERGENCY LANDING GEAR SYSTEM.

Emergency gear extension is available through a
manual ovenide system. This system is bunt into the .03 IN.
actuator unit. The disengage controls are located aft .13 IN. E
and between the front seats. F

LANDING GEAR WARNING SYSTEM.

The landing gear warning system provides the pilot
with an audiMe warning that the landing gear is not
down and locked when the throttle is retarded beSow
10 inches manifold pressure on S/N 25-0001 thru 25-
I
0780. The waming system on aircraft S/N 25-0781 I
ON is activated when the throttle is retarded below 16
to 18 inches MP. When the landing gear is down and
locked the electrical circuit is opened and the intermit- Yi-it~-B
tent hom is stopped. This warning switch is mounted
on the throttle housing forward of the instrument panel
and can be adjusted for the proper setting by loosen-
Ing the screw and repositioning the switch.

BRAKE SYSTEM. GEAR RETRACIION SPRING REMOVAL

The brake system is hydraulically operated by depress- FIGURE 32 1
ing the brake pedals mounted on the pilots rudder

32-00-00
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
B. Remove gear retraction spn’ng (A) and link at gear in the UP position. AN960-10 washers may be
(F), (Figure 32-1), by attaching spn’ng installation tool used as spacers.
(B), P/N GSE 030012, told P/N was 8186) using an 4. Reconnect outboard gear doors and check that
AN3-12A bolt at (E) to relieve pressure at (F). Remove the forward edge of outboard gear doors are faired with
grease Mting priorfo using tool, wing skin/wheel well opening and that there is no
9. E>ctend gear three to four inches from down-lock binding or distortion where links attach to door.
position and secure.
10. Remove six mounting bolts from rear gear
trunnlon shaff mounting block assembly at stub spar. "cb~31
il.Slide out aft bean’ng block.
12. Slide front bean’ng block aft and remove.

13. SIMe gear assembly aft until clear of front bean’ng,

and careful(y~remove gearassembly from wing.
14, Identify all components removed, and DO NOT
intermix n’ght and left gear components.
15, 00 NOT attempt to repair any heat treated jl dl
component of main landing gear assembly.
32-1092 -MAIN GEAR INSTALLATION I
i. Lubn’cate wheel bean’ngs, retraction linkage, and
fore and aft trunnion bean’ngs prior to installation (refer
to Section 5-20-07 for recommended lubn’cants).
2. Installation of main gear is the exact reversal of
the main gear removal procedure.
NOTE
Torque 510078901,403 or1)05 bolts from
270 to 300 In. Lbs.

3. Check fore and aft movement of gear in bean’ng

blocks. Maximum allowable movement is .020. Shim
excess by inserting shims at rear block
INBOARD GEAR DOOR ADJUSTMENT POINTS
4. TemporBn’ly attach gear door link rods to gear leg thru 25-0999)
(25-0001
brackets.
FIGURE 32 2
5. Retract gear while checking for binding in door
5´• If adjustments are required, adjust outboard gear
linkage and proper contact of gear door edges with
door rod ends (Fig. 32-2A) at forward or aft linkages as
wing. DO NOT make final gear door adjustments until
gear has been rigged (Ref. 32-30-02). required. E>dend gear to adjust links, then retract to
check adjustment.
32-10-03 MAIN GEAR DOORS RIGGING
32-10-04 -MAIN GEAR DOORS RIGGING
(25-0001 thru 25-0939)
(25-1000 thru 25-TEA)
NOTE
Gear system must be properly n’gged prior to NOTE
gear door rigging, see Section 32-30-02. Gear system must be properly rigged prior to
1. Raise aircraft on jacks. gear door rigging, see Section 323002.

2. Check main gear up against bumper pads. 1. Raise aircraft on jacks.

3. Normally once the doors are installed at the 2. Normally once the doors are installed at the
factory no fi~rther adjustment should be required. factory no further adjustment should be required.
However, should the inboard doors be removed for any However, should the MID-GEAR doors be removed for
reason the following n’gging procedure should be used any reason the following rigging procedures should ~e
when reinstalling them: used when reinstalling them:
A. Disconnect outboard gear doors at the forward A. Disconnect outboard doors at forward and aft
and an linkages (6) (Fig. 32-2A). linkages (B) (Fig.32-2A).
position.
B. Raise gear electn’cally to the full up B. Disconnect inboard doors at fo~ward linkage and
C. Forward leading edge and aft trailing edge of the springs (A) (Fig.32-2B).
inboard gear door should be tight against the wing skin C. Raise gear electn’cally to the full UP position.
and fair with the aft bubble fain’ng. Spacers (A) (Figure
32-2) should be added or removed as required to D. Forward leading edge and aft trailing edge of the
obtain a good fit with no binding or distortion with the Mid-Gear doors should be tight against wing skin.
32-1 0-02
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE

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II !I I, II ji INBOARD GEAR DOOR RIGGING FIGURE 32-25
MID-GEAR DOOR ADJUSTMENT POINTS
gear UP. Adjust by turning retract tube 03 rod end

(25-1000 THRU 25-TEA) Ibl 112 turn, and retract tube (L) (Fig. 325) rod end
FIGURE 32-2A OUT 1 turn.

EXAMPLE: If the inboard gear door is closed with

Spacers (A) (Figufe 32-2A) should be added or landing gear in the DOWN position, but open a small
removed as required to obtain a good fit with no bind amount with landing gear in the UP position. Adjust
ing or distortion with the gear in the UP position by turning retract Or) (Fig.32-9) rod end PIlI iR
AN960-10 or AN970-3 washers may be used as tum, and retract tube (L) (Fig.325) rod end IN 1 turn.
spacers. 2. Tighten jamb nuts and reconnect springs on

3. Reconnect outboard and Mid-Gear doors and inboard gear door bellcrank (A) (Fig.32-2B).
check that doors are faired with wing ski~lwheel well
opening and that there is no binding or distortion where NOTE
link attaches to door. Adjust linkage if required (Fig. Do not rig doors shut more than necessary as
32-2A). Fjdend gear to adjust, then retract to check this may result in higher actuator loads than
adjustment, necessary.

4. Check main gear overcenter preload torque for

3. Adjust outboard door link to close all gap at
proper values. Re-n’g entire landing gear system, if leading edge of door. If the door is n’gged too tight, the
necessary. skin will be under stress (concave) at the point where
32-10-05 INBOARD DOOR RIGGING the linkage is attached to the door. It could also cause
the mid and inboard doors to gap open.
(S/N 25-1000 thru 25-TEA) 4. Cycle gear manually and electn’cally while
inspecting for clearances. Recheck landing gear
Adjust inboard door link to close doors with "O" System n’gging values.
gap. Doors must be closed with gear e>dended and
retracted. If door is not closed in both positions refer to 5. Remove aircraft from jacks.
landing gear rigging procedures in Section 32-30-02. 6. Retum aircraft to service.
Any adjustment to rod end on main retract tube (L)
(Fig. 325) and rod end on retract tube 03 (Fig. 32-3) NOTE
is at a 2 to 1 ratio, respectively; this adjustment will To INBOARD GEAR DOORS use a
remove
change rigging values. Re-check preload values, sharpened punch less than .093 dia. or a short
EXAMPLE: If the inboard gear door open a small piece of hinge pin to open the crimped hinge
amount when landing gear is down, but closed when assembly pin hole.

32-10-05
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE

~dC: I I X\/ F e

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B
1~ NOSE GEAR RETRACTION TUBE ADJUSTMENT
fWD

ASSIST BUNGEE INSTAU4TION FIGURE 32 2C POINTS FIGURE 32 3

32-10-06 INSTALLING ASSIST BUNGEE 7. Remove left and right gear mounting bolts and
(560213601) (E) (Figure 323) from tubular structure and nose gear
(25-1 000 thru 25-TEA) truss assembly.

1. Retract gear. 6. Carefully remove nose gear assembly.

2. Pull gear down with emergency extension until 9. DONOT attempt to repair heat treated
main retract bellcrank and rod end bungee line up. components of nose landing gear assembly.
Install AN3 bolt through Heim ~d end bean~ng and AN4
32-20-02 NOSE GEAR INSTAUA’TION
bolt through block. Torque and safety.
1. Lubricate wheel bean‘ngs, retraction linkage and
CAUTION left and right mount bearings.
Bump gear up, CAREFULLY, just to take load
off the 3M6 in, installation pin at (B). Remove
pin from (B) (Fig. 32-2C).
3. Wnh bungee installed recheck
30 thru 34 of Section 32-31-02..
preload per steps
F
i
32-20-00 NOSE GEAR AND DOORS G U

32-20-01 NOSE GEAR REMOVAL.

!J
1. Raise aircraft jacks per Section 7-10-00.
on

2. Remove exhaust cavity fain’ngs.

3. Partially retract gear as described by Sedion
32-80-01.
4. Remove firewall nose gear box (if needed) to gain
access to bolts.
5. Disconnect link (A) on nose gear truss assy.
(Figure 32-3). K
6. Disconnect nose gear steen’ng hom link (B)
(Figure 323). ~h

NOSE GEAR RETRACTION TUBE/DOOR

ADJUSTMENT POINTS FIG 32 4

32-1 0-06
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
32-20-03 NOSE GEAR DOOR RIGGING 6. Push RED gear safety bypass switch and hold IN
to partially retract
gear. Pull "GEAR ACT" circuit
1. Raise aircraft on jacks. (Refer to Section 7-10-00.) breaker.
7. Check nose gear overcenter preload as follows:
NOTE k Measure nose gear bungees (Figure 32-6).
Gear system must be properly rigged prior to gear B. Extend gear manually (See Section 32-30-04)
door rigging, see Section 32-30-02.
stopping extension the moment the green Gear Down
Light comes on. Gear switch in DOWN position.
2. Adjust gear door link rods (H) and (J) (Figure 32-
C. Measure nose gear bungee springs (Fig.32-6).
3)to obtain proper door fit when closed.
Deflection from zero load condition in (A) above must
3. To increase or decrease nose gear-up travel in
be.030 to .070 inches for each bungee.
wheel well, adjust eccentrics on trunnion bean’ngs (J),
D. Ii spring deflection is not within prescribed
(Figure 32-4) as required.
limits, adjust tube rod ends (Figure 32-4 (F)) in incre-
ments of 1/2 turns as required.
CAUTION
8. Check main gear overcenter prdoad as follows:
Nose gear overcenter preload must be rechecked
A Place n‘gging tool Cr) PIN GSE 030007 (Figure
after any adjustment to nose wheel eccentfics.
32-9) on retraction truss. Hold the tool stationary by
4. Readjust nose gear door linkage as required after placing thumb on rear end of tool (S) and press for-
eccentrics have been moved. (Figure 32-4, IC) ward.
B. Hold 10" torque wrench (R) and place thumb
32-30-00 EXTENSION AND RETRACTION
on wing bottom; apply force until joint (4) breaks open
slightly, insert shim stock (.005 .008 in. thickness) be-
32-30-01 GEAR SYSTEM OPERATIONAL
INSPECTION tween link and truss at (P). Release force on wrench.
C. With fingers on torque wrench and thumb on
1. Raise aircraft on jacks. (See Section 7-10-00).
wing bottom apply force on wrench while maintaining a
2. With Master Switch ON and gear switch in UP
pulling force on shim stock. Read torque value on
position, apply pressure to pitot tube (see Section 32- wrench at the exact moment the shim stock pulls
60-01). Verify gear retraction occurs at 75 MPH 5
loose. Torque value should be 250 to 280 inch pounds.
MPH (55 +7/-4 KIAS). Allow gear to raise completely.
D. Repeat on other main gear.
Check for any tire interference as tire enters whee~well.
E. If preload is not within prescribed limits
3. Close throttle and confirm gear hom sounds.
Inspect gear doors for proper closing; lower gear.
4. proceed to applicable S/N, Main Landing Gear Rigging
5. With zero airspeed place gear switch in UP posi- procedures in Section 323101or 32-31-02.
tion. Gear horn should sound regardless of throttle F. If main gear preload needs readjusting, the

position, both gear position lights and safety bypass nose gear bungees should be rechecked per 7, (C)

switch will illuminate. above (Fig. 32-6).

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o,

E oo

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MAIN GEAR RETRACTION TUBE ADJUSTMENT POINTS FIGURE 32 5

32-20-03
MOONEY AIRCRAFT CORPOW\TION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
NOTE 11. When step 10 is complete, the retraction system
When gear overcenter preload check is is n’gged for the gear-down-and-locked position with
completed, electrically extend the gear and allowance for actuator overrun after cutoff.
check the nose gear tube bungee springs to 12. Reset landing gear system circuit breaker and
assure they have not compressed completely
disengage manual system.
resulting in no remaining deflection. This would
indicate excessive preload or weak bungees, 13. Leave all gear doors disconnected, and run
gear-up electn’cally until main gears are .03 inches
minimum from bumper pads. Position gear-up limit
32-30-02 MAIN LANDING GEAR SYSTEM
RIGGING switch striker arm (H) (Fig.325) so switch is JUST
closed, and RED gear unsafe light is OFF. Secure
(SIN 25-0001 thru 25-0999) stn’ker arm in position. The gear is now properly rigged
in the gear-up position with allowance for actuator
1. Raise aircraft on jacks and remove 3 belly access overrun after cutoff.
panels located consecutively just aft of nose wheel well
or the one piece belly access effective 25-0781 and 14. Electn~cally extend gear to down-and-locked
later aircraft. position. Adjust gear doors (refer to Main Door and
Nose Gear Door Rigging Procedures in Section
2, Disconnect main gear retradion tubes (L) (Figure 32-10-03, Main, and 32-20-03, Nose).
32-5) at inboard bellcranks (M). Loosen locknuts (E).
Disconnect nose gear retraction tubes (F) (Figure
32-3) at main retraction bellcrank (A) (Figure 32-10). 245 (REF) Nose ~eor Bungee
Loosen locknuts (G) (Figure 32-4). Disconnect actuator
rod end at (N) from bellcrank (A) Fig. 32-10.
Disconnect nose gear and main gear door links. Check
gear for binding at pivot points while moving gear legs
by hand. Lubricate retraction system as indicated in
S~ECTION 5-20-07.
3. Position retraction bellcrank (A) Figure 32-10, so
that center of forward hole in left outboard arm of the
bellcrank is 1.56* IN. (approximately) from forward face
of truss at Fuselage Station 33. (See Figure 32-10.) Deflection of spring from static
NOTE o rigged position to be .OJO to .070 in.
This is a starting point only. This dimension
may vary to permit retraction tubes to connect NOSE GEAR BUNGEE SPRING FIGURE 32 6
with zero preload,
15´• Adjust mechaniwl down stop on actuator
4. ~Tth bellcrank (A), Figure 32-10, in position, turn
barrel nut (D) on actuator until rod end aligns with hole housing and up stop per the following instructions and
in bellcrank at (N). Install connection boitlhardware. Figure 32-7 and Figure 32-8.
5, With bellcrank in position and landing gear fully MECHANICAL DOWN STOP
e~dended, adjust main (L) (Fig. 326) and nose gear (F) A. 560252-1 Fixed Stops Use one DOWN STOP
(Fig, 32-10) retraction tubes so that tubes can be
560252-3 Fixed Stops on each side as
slipped in place with zero preload. 560252-5 Fixed Stops required (Pick up
6. Disconnect electn’cal power from landing gear 560252-7 Fixed Stops existing hdw).
actuator by pulling actuator circuit breaker. Make sure 560252-9 Adjustable Stop (use -11 shims)
landing gear warning light circuit breaker is pushed IN. a. V\Mh gearfulfy e~tended, select d~Mn stop of proper
7. With bellcrank, retraction tubes, and the gear thickness to give .650 .100 clearance at (6) between
positioned as indicated in step 4, set down-limit switch down-stop and end of barrel nut (C). (Figure 32-7).
striker arm (J) (Fig.325) so gear down limit switch is
NOTE
just closed and GREEN gear-down light is ON. Secure Use 1 to 4 560252-11 shims with 5602529 stop
striker arm in position.
to achieve proper clearance as an alternate for
8. Reset actuator circuit breaker and partially retract 560252-1, -3, 5, or -7,
gear (use master switch to control motor). Screw rod
end (E) (Fig,326), on aft end of each main gear C. Actuator barrel nut.
retrading tube, OUT two full turns, screw each nose D. 560252-11 shim (use with 560252-9 only,
gear retraction tube rod end (F) (Fig.324) IN one full ma>dmum of4).
tum, then slip attaching bolts back in place. E. AN515-6R screw
9. Check nose and main gear overcenter preload
AN936A6 Lock Washer
described in Section 32-30-01, steps 7 and 8. Adjust as
instructed. CTyp. pie.) (use with 560252-9 only).
2

10. Complete operational check described in Use.063 longer screws with each additional shim.
32-30-01 steps 2, 3, 5 and 6. (Secure screw with Blue LocMite #83-31 grade C).

32-30-02
10
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
R"YD

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MECHANICALDOWN STOP FIGURE32-7

MECHANICAL UP STOP
With gear fully retraded, adjust stop for.050 .070
clearance between up stop (A) and retrading truss (B),
MECHANICALUP STOP FIGURE32- 8
then tighten set screw (C). (Figure 328)
NOTE 2. Assist Bungee Assy. (560213501) Removal.
The main gear preload torque should not Retrad landing gear until rigging pin holes (B) (Fig.
exceed 325 inch Ib. (using the torque 32-2C) lines up on bungee assy. and insert 3/16 in. pin.
wrenchlshim stock procedure after electrical CAREFULLY BUMP the gear UP with the gear safety
extension. bypass swrtch.untii there is zero load on bungee
254000 thru 25-TEA) assembly rod end at retraction bellcrank. Remove AN3
(SIN bolt and hardware at rod end and AN4 bolt/hardware at
1. Raise aircraft on jacks and remove one piece block and remove bungee assy.
fiberglass belly access panel. 3. Pull landing gear actuator circuit breaker OUT.

~3) 1.56(MPX.)

R~TRACTION
LINK\
T
IGCINC; ~-250 f 280
RETRACTION~ TOOL TORQUE INCHILBS.
TRUSS G 030007-1 00 WRENCH
LE~I MAIN GEAR ii
(VIEW LOOKING; TWD)
MAIN GEAR RIGGING TOOL APPLICATION FIGURE 32 9

32-30-02
 MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
4.Loosen jam nuts (8) on the main retraction tubes 19. Run actuator down and recheck retraction
(L), Fig.32-5; disconnect tubes at inboard bellcranks bellcrank clearance at F.S. 33.. Check clearance of
(M). bdlcranks (M) (F$.32-5) and center section.
5. In nosegear well loosen jam nuts (G), Fig.32-4, 20. Reconnect retraction tubes C~ (Fig 32-9). With
on nose gear retraction tubes (F), Fig.32-3 and 32-4. main gear fully extended, if necessary, adjust main
6. At main retraction bellcrank (A), Fig.32-10, dis- gear retraction tubes (L) (Fig.32-5) so they are con-
connect actuator barrel nut at (N), and nose gear nected with zero preload.
retraction tubes (F). 21. Adjust nut 03 of retraction tube N (Fig. 32-9)
7 On Avionics Products Actuator, verify dimension until main gear is preloaded. Preload is correct when a
from rod end center to end of banel nut housing on "clean break" can be felt when pushing UP on retrac-
actuator; k should be 1.25 +.000/-.010. Adjust rod end tion link (Fig. 32-9).
bearing if necessary and secure with set screw and 22. NOSE GEAR RETAACIION IUBES ARE TO
jam nut. Plessey Actuators are not adjustable. REMAIN DISCONNECTED at main retraction bellcrank
8. Disconnect nose gear doors, outboard main gear (A), Fig.32-10, dun’ng remainder of procedures.
doors, and inboard door links. On outboard main gear 23. Place landing gear switch in UP position.
doors disconnect springs. On inboard door bellcranks, 24. PUSH RED gear safety by-pass switch IN inter-
disconnect spn’ngs. Loosen jamb nut on retraction mittently to "8UMP UP" (retract) landing gear until left
tube (V) (Fig.32-9) and back off pressure on spring by main tire just contacts bumper bracket which revers
loosening nut (y). Disconnect retraction tube (V) from bulb stn’nger in wheel well. Make certain actuator barrel
bellcrank (C) (Fig. 32-28). does not contact main retract bellcrank in the UP posi-
9. Position main retraction bellcrank (A) (Fig.32-10) tion.
so center of forward hole In left outboard arm of 25. Set UP limit switch paddle (stn’ker arm) (H),
bdlcrank is 1.56X"* inches from forward face of Fig.32-5, so GEAR UP limit~ switch is just CLOSED and
fuselage truss at F.S. 33 (Fig.32-10, detail A). RED "GEAR UNSAFE" light is OFF. Secure striker arm
in position.
NOTE 26. Loosen set screw (C) Fig. 32-8 Adjust mechani-
This dimension **X may vary to permit connection cal upstep (A),FiS. 32-8, for a clearance of .050 to
of the retraction tubes with zero preload at bob .070 inches at main retraction truss (8); tighten set
hole. screw (c).
27 Reinstall assist
bungee per Section 32-1~
10. With main retract bellcrank held in position, tum 28. emergency gear extension, move gear
Using
actuator barrel nut until rod end bean’ng aligns wah down until GREEN gear down light JUST illuminates.
hole in bellcrank; Install connection bolt at (N), Pig. 32- 29 Tum Master switch OFF.
10.
11. Position bellcrank (C) (Fig. 32-28), so center of
attach pin (D) on top leg is 1.35 inches from bottom NOTE
The left main gear truss will probably lock over
side of spar cap (E). This will be the starting posaion
center first. Continue to slowly lower gear
when landing gear is in down and locked over center,
with out any preload set. manually while moniton’ng comression of bungee
spnng on retraction tubes M Pig. 32-9.
12. Adjust retraction tube (V) (Fig. 32-9), at rod end, If spring coils are fully compressed, retract tube
until It will connect to bellcrank (C) (Fig. 32’-28) with (V) mustbe removed from aircraft for modification:
zero preload. Install connection bdt/hardware, leave Dismantle bungee portion of tube (V); remove one
loose, space washer (2) and reassemble. Re-install
13. Adjust rod end on retraction tube (L) (Fig. 32-5) modified retraction tube and complete above
so attach hole is aligned with inboard bellcrank at (M). overcenter requirement. The removal or addition of
Install connection bolt/hardware. spacer washers may be required pn’or to obtaining
final configuration for the retraction tube (V).
14. Disconnect retraction tube 03 at bellcrank (C)
rod end; position disconnected gear full down and
locked over center. Both LH and RH landing gear 30. Place tool m (Fig.32-9) P/N 030007-100
rigging
should be in this configuration at this time. on assembly (G). Hold tool stationary
retraction truss
15. PUSH landing gear actuator C/B IN. by pushing at point (8) toward main gear leg.
16. Tum MASTER Switch ON. 31. Place 10 inch torque wrench (8) on n’gging tool
17 Extend main gear actuator to fully extended O as shown in Fig.32-9 and apply an unlocking force
position. Make certain lugs on main retract bell crank to retraction truss.
do not contact fuselage tubes, floorboard or actuator 32. When joint at (4) breaks open slightly Insert
banel nut. If there is any contact, run actuator back up shim stock (.005 to .008 in. thickness) between retrac-
slightly, tion link and truss at (P), then release force on torque
18. There should be .050 to .100 inch clearance f8) wrench.
obtained between actuator barrel (C) (Fig.32-7) and 33. While applying a pulling force on the shim stock
mechanical down stop (A). Shims (8) (Fig. 32-7) may exert an increasing unlocking force with torque wench.
be added to the mechanical downstop (A) (4 max).
32-31-02
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
34. Read torque wrench value at the UV\CT me 32-3093 NOSE LANDING GEAR RIGGING
ment shtm stock pulls loose. PROCEDURE (25´•10001hru 25TBA)
35. Repeat steps 30 through 34 on other main land- 1. Check eccentn’c bushings (J), Fig.32-4, on gear
ing gear leg, truss assy. to be installed with bolt hole in upper for-
36. Use adjusting nuts (Y) on retract tubes 01) to ,,d position.
equalize breakaway torque values within 10.0 inch Ibs. 2 Adjust nose gear retraction tubes (F), Fig. 32-3,
Adjust torque to 250 to 280 inch Ibs. so they can be reconnected to main retraction
37. Tum Master Switch ON. bellcrank with zero preload.
38. RUN GEAR DOWN ELECTRICALLY AND CHECK
THAT TORQUE VALUES DO NOT U(CEED 325 INCH NOTE
POUNDS USING TORQUE WRENCH/SHIM STOCK The eccentric bushings may require rotation to a
METHOD. new position in order to meet zero preload
condition.
LANDING GEAR WARNING ADJUSTMENT
3. Measure nose gear bungees dimension (P), Fig.
1. Check that landing gear waming light circuit
32-6, and record for future reference.
breaker is pushed IN. IN
4. Push landing gear actuator C/B
2. Check that landing gear actuator circuit breaker is Place landing gear switch in UP position.
5.
pulledOUT. ON.
6. Turn Master Switch
3. Turn Master switch ON.
7. Push RED GEAR SAFETY BYPASS SWITCH IN;
4. Set DOWN limit switch striker arm (J), (Fig. 32-5),
hold it IN to partially retract the landing gear; release
so gear down limit switch is just CLOSED and the
switch.
GREEN GEAR DOWN light is ON. Secure striker arm in
8. Turn Master switch OFF.
position. 9. Pull landing gear actuator C/B OUT.
5. Turn Master Switch OFF.
in. Screw each nose gear retraction tube (F)

The main landing gear system is now n’gged for the (Fig.32-3) IN (clockwise looking toward front of the
aircraft) one (1) full turn, then reattach to main retrac-
gear down and locked condition, tion bellcrank.

FJ I I B

FUS. STA. 33.0

1 DETATL B

ELECTRIC GEAR ACTUATOR ADJUSTMENTS FIGURE 32 10

3290-03
13
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE

lcS~’
COVER
,:i 2

FLOORBOARD

~b.

RETRACTION CABLE

ACTUATOR

I I
DISENGAGE CABLE D
ROUTING

EMERGENCY GEAR SYSTEM FIGURE 32 11

11. Place landing gear switch in DOWN position. 2 With RED lever (1) (Fig. 32-11) in full disengaged
12. Push latch O),Fig. 32-11, FORWARD on manual position (down and latched) push actuator disengage
emergency controls ton ffoorboard). arm (5) (Fig.32-10) to full forward position and apply
13. Pull RED lever (1),Fig. 32-11, back and upward approximately 5 Ibs. pull to cable to remove slack
to engage manual emergency gear e>ctension system. 3. Install D222 wire stop, (C) tighten nut and con-
14. Pull "T" handle (2) up (slowly until engaged) and nect spn’ng (5) to devis pin, (D).
return it to its original position. Continue this proce- 4.Lift RED lever and pull r" handle (2) (Fig. 32-11)
dure, stopping when gear down light JUST illuminates. aside; re-engage RED lever. Check manual extension
15. Measure nose gear bungee assemblies dimen- system to verify that it is fully disengaged by pulling T
sion "P", as shown in Fig. 32-6. If spn’ngs have handle; no resistance should be felt Check cable rout-
deflected less than .030 inches or more than .070 in- ing through pulleys 3 and 4 (Fig. 32-11) if a resistance
ches from the static dimension las recorded in Step 2), is felt to verify if it is cable routing or actuator resis-
adjust length of bungee assembly’s to bn’ng deflection tance.
within tolerance. 5. Move red lever to full UP position; pull r" handle
32-30-04 EMERGENCY GEAR UC~NSION
slowly to verify manual e~ctension system is engaged.
Resistance should be felt at once.
SYSTEM RIGGING.
6. Replace r" handle under RED lever and return
Dlsengage rigging: RED lever to disengage position, (down and latched).
1, Insert cable thru hole in actuator disengage arm, Manual extension system is now ngged.
(B) (Figure 32-10).

32-30-04
SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

OLDWILLWAYNE

PLESSEY ACTUATOR
SEE SERVICE INSTRUCTION M20-92

iC 1Y i,
I1~ 2

~v
i
18~
5
i’, 9
MOD. IDENT. PLATE

*i~
13 AVIONICS PRODUCTS
L
11 (P/N 102000>
SEE SERVICE INSTR. M20-52A
SMM32-14
LDG ACTUATOR U(PLODED VIEW FIGURE 32 12

NOTE
Run actuator to
Plessey actuators should be lubricated every 2000 cycles with M1L-G- 81322 grease.
mechanical extended position. Fill tube cavity with grease thru MS15001-1 grease fitting until old
from and relubricate exposed screw
grease is purged from screw assembly; remove old grease
threads. Run actuator to approximately 0.5 in. of mechanical retract and remove major excess
grease extruded from the ball nut assembly.
IN
SEE MOONN SERVICE INSTRUCTION M20-92 FOR REPLACEMENT OF CLUTCH SPRING
PLESSC/ ACTUATOR.

3230-05 LANDING GEAR ACTUATOR, P/N 102000, CLUTCH SPRING REPLACEMENT, --KIT Al 0-85.
Landing gear actuator clutch spn’ng replacement is into spn’ng from flanged end of housing; rotate CCW
mandatory at each 1000 hours of aircraft operation. and pullslightly.
(Reference S.I. M20-52 forAvionics Products actuator.) CAUTION
DISASSEMBLY (AVIONICS PRODUCTS) Use extreme care to prevent ball bearing from
i. Remove two nuts, item 1. Note position of cable dropping out of recoiler assembly, avoid
support bracket, item 2, and remove (Figure 32-12). damage to gear and do not allow dirt to enter
clutch housing bore.
2. Remove manual e>dension system disengage
cable from actuator disengage arm.
After disassembly, clean clutch gear thoroughly.
3. Remove two long screws, item 3. Discard removed screws (3) 8 (4).
4. Remove two short screws, item 4. 9. See 32-30-06 procedure prior to reassembly if
additional maintenance is necessary.
5. Remove recoiler assembly, item 5.
ASSEMBLY (AVIONICS PRODUCTS)
6. Remove gear assembly, item 6, from clutch
1. Lubn’cate gear and new clutch spring thoroughly
housing, item 8,by rotating gear and pulling with slight
to moderate pressure,
with lube (MIl-E81322) poly-lube.
2. Using gear to rotate spring, insert clutch spring
7. Remove two screws, item 7, and remove housing,
into bore until fully seated.
item 8, clutch spn’ng, item 9, and gear assembly, item
10 from actuator body.
8. Remove clutch spring item 9, from housing using
gear assembly, item 6, as removal tool. Insert, item 6,
32-30-05
15
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
NOTE In retracted position, cable length should be 5" to 8"
Be sure spring is all the way in and seated long.
around cam,
NOTE
3. Reinstall recoiler assembly; make sure to fully Cable in retract position may be
length
seat gear, bearing, and gear tang into manual drive adjusted shorter or longer by holding clutch
slot of recoiler assembly. with finger of one hand (to prevent shaft
rotation), and then with the other hand, rotating
4, Apply Loctite Grade A (Catalog Number 8&31,
not supplied in kit) to four new screws supplied and
pulley housing one Il) full turn CW (to shorten)
or CCW (to lengthen). Retention of clutch with
Install; take care to use the two longest screws in finger will not allow pretensi oning of springs.
bottom holes of item 5.
Slight spn’ng tension should be noted starting
at 8" to 10".
NOTE
Torque to approximately lO -12 inch pounds.
10. Bronze clutch (13) should be inspected for
5. Reinstall cable support bracket and retaining nuts. damage or wear at slot where gear assemble engages
dun’ng manual e>ctension of landing gear.
6. Retest unit for proper electn’cal and mechanical
ii. If damaged or worn, remove pin (11) from
operation,
disengage arm (12) and slide disengage arm out so
7. Install modification plate adjacent to I.D. plate bronze clutch (13) can be pulled from its driveshaft.
(first1000 hours only). Mark first block of modification
plate with the figure~’l" using metal stamp or etching
12´• Replace bronze clutch and reassemble
tool. Mark plate at each succeeding clutch spn’ng disengage amn into recoiler assembly.
replacement with the ne~d consecutive number. 13. Attach clutch recoiler assembly to actuator gear

LANDING GEAR ACTUATOR, P/N

housing with four (4) screws removed in 32-30-05
3230-06
(supplied in clutch spn’ng kit).
102000-1, RECOILER
SPRINGS/CABLE AND DRUM 3230-07 MANUAL EMERGENCY GEAR
ASSEMBLY REPLACEMENT U(TENSION SYSTEM
i. Carefully separate pulley housing from recoiler The manual emergency gear e~dension system is used
assembly (5) by iemoving screws (14). Retain pulley to extend the gear only. The controls are on the
on shaR floorboard aft and between front seats. To manually
extend the gear:
pulley drum and cable offshaft.
2. Slide
3. Remove two (2) recoiler spn’ngs, and two (2) of 1´• Pull landing gear actuator C/B.
three (3) spring spacers leaving the third spacer in 2. Move landing gear control switch to DOWN
housing; Be certain that spacer is in place before position.
installation of h~Jo (2) new recoiler spn’ngs and
3. Push latch forward with right thumb.
previously removed spacers.
4. Pull lever back and upward (engaging manual
4. Install new recoiler spn’ngs placing a spacer
extension system).
between each spn’ng and over top spn’ng.
IMPORTANT Recheck proper installation of springs. 5. Pull ’T’ handle UP (slow(y to engage gears);
return to original position; continue cycle until GREEN
NOTE gear-down indicator light is illuminated and/or the lines
When looking at recoiler assembly with pulley on the visual gear position indicator on fioortsoard aft of
shaft end toward you, the spn’ng tabs in console are aligned when viewed from directly above
housing slot should curve to the right as shown th, indicator (this will normally take 12 to 20 pulls).
(Figure 32-12).
CAUTION
5. Inspect cable for sheathing damage. Replace DO NOT operate landing gear electrically with
cable if Sheathing is cut or stripped. Measure overall manual extension system engaged.
cable length pn’or to reassembly. Cable length should
be 31 1/2" 1/2" long. CAUT1ON
6. Slide drum onto shaft; be certain that spring DO NOT continue to pull i-Handle after GEAR
detent on drum engages both recoiler spn’ngs by DOWN light is ON. Actuator barrel nut may bind
on Down Stops.
slightly rocking drum end.
7. When full engagement is obtained, wrap cable 3230-08 FINAL CHECKS 25-1000 thru 25-TEA
around drum in a clockwise direction-leaving 2" to 5" of
cablefreeofdrum. 1. Raise and lower landing gear through five
complete cycles, pausing after each cycle to check
8. Align slot in pulley housing with cable and slide
required tolerances and dimensions, and annunciator
pulley housing over cable and drum assembly. light indications. Make certain that no bungee spn’ngs
9. Holding housings together, pull properly aligned are compressed to solid height and that nose gear tire
cable several times to ensure absence of binding clears top of wheel well a minimum of 25 in. when
conditions. Measure cable length from side of housing, landing gear is retraded. Make adjustments per above
At full e>dend, length of cable should be 29" minimum. procedures, as required, to correct any deficiencies.
32-30-06
16
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
2. Retorque all jam nuts. 3. Re-attach main and nose landing gear door links.
Check to see that main and nose landing gear doors
are still rigged per paragraph 32-10-04 and 32-20-03.

3232-00 TROUBLE SHOOT1NG LANDING GEAR SYSTEM

TROUBLE PROBABLE CAUSE REMEDY

Incomplete ret~action. Gear Bind in gear retraction system Refer to landinggear rigging
retracts to an intermediate because gear is out of n’g. procedure. Examine all movable

position and stops short. Malfunction in gear electrical parts for proper lubrication and
circuit, inoperative actuating freedom from binding. Check for
motor, or weak battery. actuator worm gear 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
defedive relay switches.
Recharge battery if necessary.
Oversized/Stretched tire will not go Replace tire with smaller diameter
into wheehwell properly. tire.

Insufficient airspeed, pressure Check pitot tube and line for

Gear will not retract at 70 to 80
MPH IAS. switch inoperative, circuit breaker obstructions. Examine pressure
tn’pped or actuator ball nut binding switch for proper adjustment and
on mechanicaC DOWN STOPS. operation. Reset circuit breaker.
Does gear ret~act using override
check system operation.
Gear may have been extended
manually 3 ball nut is jammed
tight against STOPS on motor;
use wrench on ballnut flat 3 move
ballnut off STOPS.

Gear will not retract and gear Manual engage handle in engaged Disengage manualsystem.
ad. C/B tn’ps. position.

Aiaa3tdoes Nose wheel location improper. See Section 32-50-02.

Gear will e~dend; green Lamp burned out in green Replace bumed out lamp. Check
Down-limit indicator-light circuit and/or
indicator-light @ress-to-test) will indicator-light circuit.
not illuminate. switch is inoperative. down-limit switch.

Same listed with Same remedies as listed with

Actuating motor e>ctends gear to causes as

"Incomplete Retraction" above. "lncomplete Retraction" above.

an intermediate position.

but Gear switch is not in DOWN Place gear switch in DOWN

Gear will extend manually,
green indicator light will not position. Lamp burned out in green position. Replace bumed out lamp.
illuminate. indicator light.

Manual system will not lower gear. Actuator internal clutch spn’ng Replace spring.
broken.
Manual engage arm improperly Rig manual engage arm properly.
ed.
32-32-00
17
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
32-40-00 -WHEELS AND BRAKES 4. Remove nuts, washers, and wheel halt retaining
bolts, (5); separate halves, (3, 4) and remove tire and tube.
32-4061 MAIN WHEELS
The main wheels are standard brand, 6:00 x 6, six-ply NOTE
rated tires with standard tubes. Bean~ng cups areshn~nk fitted; do not remove
them unless necessary for replacement.
To remove main wheels from aircraft:
1. Remove either IB or MID gear door. 5. Clean all wheel parts thoroughly in cleaning fluid

and
(Federal Specification PS-661). Exercise special care
A. Detach dust shield. Remove three screws
i, cleaning bean’ng cones and felt rings to insure
washers.
thorough cleaning.
B. Remove 2 bolts from brake caliper. 6. Inspect all pads for cracks, corrosion, or evidence
C. Remove wheel by removing cotter key and nut orwear.
from axle. (See Figure 32-13.) 7. Inspect bean’ng cups and replace if cups are
D. Slide wheel off axle. damaged or wom. If necessary to remove bean’ng
cups, heat wheel in boiling water for at least 30
32-40-02 MAIN WHEEL DISASSEMBLYI minutes. Remove cup by tapping evenly.
ASSEMBLY To install cup, heat wheel half again and then cool cup
i. Remove snap n’ng, (10) grease seal n’ngs, (8) and with dry ice. Position cup and tap lightly to insure
felt seals (9), (See Figure 32-14). proper seating.
2. Remove bearings (7). 8. Polish small burrs or nicks out of wheel halves
with No. 400 grit sandpaper, clean thoroughly, and
3. Completely deflate tire. refinish protective coating as required.
WARNING 9. Replace bean’ng cones that show signs of wear or
Do not loosen wheel half retaining nuts before bean’ng fretting.
tire is completely deflated. Failure to observe
?O. Repack wheel bean’ngs and lubricate seals with
this warning may result in bodily injury.
grease. Install bean’ngs, grease seal n’ngs, and felt
seals in wheel halves. Secure with snap n’ngs.
3 PLcS.) CAUTION
Spacer required to position brake disc .12
ACER inches away from MLG leg assy. Refer to
Figure 32-13.

COTTER PIN--~ /(C~,// ~;iLCW I I

MAIN
SP
MAIN GEAR LEG ASSY.
TIRE
14 ~i
MAIN WHEEL ’Ps NOSE

7 13

2
NOSE TIRE
L\h I I 4 I(lr IYBYB~ h s

NOSE
LEG ASSY.
MAIN WHEEL ASSY.
f
COTIERW
NUT

NOSE WH
WHEEL ASSEMBLIES FIGURE 32 14
LANDING GEAR WHEEL REMOVAL FIGURE 32 13

32-40-00
18
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
11. Position tire 8 tube on one wheel half; then 3. Nose wheel disassembly.
position other wheel half in tire. A. Completely deflate tire by removing valve core.

12. Install brake disc (2), Fig.32-14, and wheel half B. Remove nuts, washers, and wheel half retaining
retaining bolts, washers and nuts, bolts (15), Fig. 32-14.
is. TylMen nuts evenly and torque to 150 inch pounds. C. Separate wheel halves, (13 and 14) and remove
CAUTION tire and tube. Referto Section 32-40-02 steps 5 thru 10
Uneven or impropertorque may cause bolt or
forwheel inspection.
wfieelfailure. D. Reassemble nose wheel in reverse sequence of
dissassemMy. TigMen wheel half retaining bolt nuts evenly
14. Inflate tire to 42 PSI. and torque to 90 inch-pounds. Inflate tire to 49 PSI.
15. Install wheel assembly, washer, and axle nut.
NOTE
Tighten axle nut until bean’ng binds slightly, back nut
off to nearest castellation, and install cotter pin. When ANY tire and/or wheel assembly is
removed or replaced and re-installed, conduct
NOTE at least 5 complete retractionlextension cycles
When properly installed, wheel will tum with a to verify tires enter and exit wheelwells without
slight resistance. interference. [Ref. AC 43.13-1( Chap.8, pam.
332, a, (sn
16. Install dust shield and IB/MID gear door.
32-40-04 BRAKE SYSTEM
17. Reinstall brake caliper 8 safety.
1. BRAKE REMOVAL AND INSTALLATION
NOTE
When ANY tire and/or wheel assembly is Lining inspection and/or replacement or cylinder repair.
removed or replaced and re-installed, conduct A. Place aircraft on jacks.
at least 5 complete retractionlextension cycles
B. Remove inboard/mid gear doors. Remove
to verify tires enter and exit wheelvvells without
interference. [Ref. AC 43.13-1( Chap.8, pam. safety wire and two AN4H17A bolts (1) attaching back
332, a, <sn lining plate assembly (2) to brake cylinder assembly
(Figure 32-15).
18. Remove aircraft from jacks. C. Visually inspect linings for wear and brake disc
32-40-03 NOSE WHEEL for warpage. Brake linings should be replaced when
DISASSEMBLY/ASSEMBLY they are wom to a minimum thickness of 1/8 inch. If
wheel tire is a standard brand, 5:00 5,
lining replacement is necessary proceed with steps D
The nose x
thru O. Otherwise reassemble in reverse sequence of
six-ply rated tire with standard tubes.
disassembly.
1. Nose wheel removal.
CAUTION
A. Remove cotter key, nut, and washer from axle.
Brake disc should be replaced if width is .205
(Figure 32-13). in. or less.
B. Remove nose wheel.
D. Disconnect and cap hydraulic line (4) at brake
2. Installation is in reverse sequence of remoMI.
cylinder assembly. Remove nuts from anchor bolts.
E. Remove pressure plate assembly (Figure
32-15) (5) sliding it off the anchor bolts (6). Note the
condition of the anchor bolts. If they are nicked or
gouged they should be sanded smooth to prevent
binding withthe pressure plate (5) or torque plate (8)
4
1 When anchor bolts are replaced they should be
pressed out. New ones can be installed by tapping
them in place with a soft hammer.
b
F. Dn~ll out rivets (9) attaching linings O to back
6 I’ lining plate (2) and pressure plate (5). Remove piston
assembly (10) and "0" ring (11). It is permissible to use
5 ~3, compressed air applied to the brake line fitting to
remove piston (10)from brake cylinder.

10ii G. Clean parts in cleaning solvent (Federal

Specification PS661 or equivalent) and dry with
oil-free compressed air.
LEED VALVE~P H. Replace linings with Cleveland 66-30 linings
using Cleveland #561-2 rivets. Rivets must be rolled to
COVER obtain proper fit between rivet shank and hole.
BRAKE ASSEMBLY FIGURE 32 15 i. Inspect brake cylinder bore for scon~ng. A scored
cylinder may cause "O" ring to leak or cause rapid
32-40-03
19
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
M. Reassembly brake cylinder assembly and back
lining plate assembly onto the airplane in the reverse
ClcvolMd
75´•1C Axle Moun(l~ TLnge sequence of disassembly.
PLIe Ally.
N. Bleed hydraulic system as described in Section
12-20-05.
12~
I O. Remove aircraft from jacks.
2. BRAKE PAD CONDITIONING (BREAK IN)
PROCEDURES.
Wheel end tire RCI~UIL PII1C
Allcmblr NOTE
Brake pad conditioning is required to properly
cure the resins binding the asbestos lining
composition together. Excessive heat created
prior to conditioning will carbun’ze the lining
maten’al and prevent the attainment of

i/
maximum braking coefficient.

1 Brl~e tyl(ndtr
Proper conditioning may be accomplished as follows:
A. Perform a minimum of six (6) light pedal effort
braking applications and two (2) hard stops from 25 to
40 MPH (21 to 35 KIAS). Allow the brake discs to
TORQUE PLATE ASSY-CORRECT RELATION TO partially cool between stops.
BRAKE CYLINDER The procedure will generate sufficient heat to cure
resins in the lining, but will not cause the maten’a) to
wear of "0" ring. A scored brake cylinder should be become carburized due to excess’n~e heat.
replaced. 3. MASTER CYLINDER REMOVAL,
J. Replace AN6230-2 "O" n’ng (11) with a new one. D)SASSEMBLY and REASSEMBLY
Do not reuse old "O" n’ng.
A. Remove left hand exhaust cavity.
K. Lubricate cylinder and piston with Mll-H-5606
B. Disconnect hydraulic cylinder from pedal
red hydraulic fluid and assemble components with care
to "0" n’ng, linkage.
to prevent damage
C. Disconnect and cap hydraulic lines.
FIGURE 32 -16 and
D. Disconnect hydraulic cylinder from bracket
L. Senrice and inspect main wheels as descn’bed remove cylinder.
In Section 32-40-02. inspect torque plate assembly (S~ 25-0001 THRU 25-1999)
making sure the .125 thickness is toward brake To disassemble small fluid capacity master cylinder:
cylinder assembly(outboard) Ifthicker.250 protrusion
is outboard, remove torque plate from a~e mounting (Gerdes or Parker-Hannifin) Figure 32-111).
flange and install as shown (Figure 32-16). (1) Unscrew and remove rod end clevis (15) and
nut from piston rod (9).

12
8,5
14

9 Lg

L 13 4
15 7

S/N 25-0001 THRU 25-1999

BRAKE MASTER CYLINDER FIGURE 32 17

32-40-04
20
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
(2) Remove snap n’ng (13) and lift out complete snap ring (2) from end of piston rod
piston rod assembly, item 3 thru 12.
(3) Remove spacer (11) and O-ring packings, (10 (4) Remove bushing (3) and spring (4) from end
and 12) from piston and assembly. of piston rod.
(4) Disassemble piston rod assembly by (5) Remove piston assembly (5) and O-ring O
removing roll pin (4), (spring guide (3) will be pushed from piston assembly and O-n’ng (6) from piston rod
out by spn’ng (5) when roll pin is removed), spring (5) shaft.
and piston (7).
(6) Remove end cap (8) and O-n’ngs (9 [IDD (7
(5) Remove O-n’ng packing (6) from piston. [ODD from end cap assembly.

(6) Remove stats-seal (8) from piston rod. O Clean all parts with cleaning solvent (Federal
C~ Clean all parts with cleaning solvent (Federal
Specification No. PS661).
Speci~dation PS-661).
No. (8) Inspect cylinder for cracks, scoring, or
cracks, grooves in bore.
(8) Inspect cylinder for scon~ng, or
(9) Inspect piston (5) for damage, check for nicks
grooves in bore.
and scratches.
(9) inspect piston C/) for damage, check for nicks
and scratches (10) Inspect end cap (8) for damage.
(10) Inspect valve for damage. (11) Inspect push rod for scon’ng, grooves, nicks
and scratches.
(11) Inspect push rod for scoring, grooves, nicks
and scratches. (12) Inspect spn’ng (4) for free height .500 in.
+/-.030.
(12) Inspect piston return springs (2) for
permanent set and proper length (3.670 in. mi?., 4.05 (13) Replace all faulty parts and all O-rings.
in.max.). (14) Reassemble in reverse sequence of
(13) Replace all faulty parts and all O-rings. disassembly. Immerse all parts in hydraulic brake fluid
priorto reassembly.
(14) Reassemble in reverse sequence of
disassembly. Immerse all parts in hydraulic brake fluid (15) Check piston rod and return spring (13) for
priorto reassembly, proper compression dun’ng stroke (9 Ibs. bottom
to 32 Ibs. 3/4 stroke)
(S~ 25-2000 THRU 25-TEA)
These aircraft have large capacity Master Cylinders. F. Reinstall master cylinder in reve~se sequence of
’emoval.
To disassemble large fluid capacity master cylinder:
(Parker-Hannifin) (Figure 32-17A). G. Bleed brake system (referto Section 12-20-05).
(1) Unscrew and remove rod end clevis (17), nut 4. PARKING BRAKE VALVE-REMOVAL,
(16) and washers (14 8 15)from piston rod (12). DISASSEMBLY and REASSEMBLY

(2) Remove snap n’ng (11) from cylinder housing REMOVAL

assembly; lift out complete piston rod assembly, (items A. Remove left hand exhaust cavity.
2 thru 12). Spn’ng (13) can be removed at this time.
B. Disconnect parking brake control at parking
brake valve arm.

14 1

~"7O
5

L 12
15

17 Lt1 ~--7 L7

S/N 252000 ’THRU 25TBA

BRAKE MASTER CYLINDER FIGURE 32 17A

32-40-04
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAlNTENANCE MANUAL

OLDWILLWAYNE
C. Disconnect and cap hydraulic lines.
D. Remove parking brake valve.
-DISASSEMBLY 5
Disassemble parking brake valve (Refer Figure 97
32-/8). o
L
housing O, I fi\ S 9 4
A. Remove both Mtings (1) from valve
springs (8) will come out with the fittings.
B. Remove poppet valves (2) and pins (3), from
housing by bumping on table top.
C. Remove both fittings (4) from end of housing. 1 3
D. Remove snap ring (5) from end of camshaff
2
assembly (6).
E. Carefully remove camshaft assembly (6) from
housing.
F. Inspect all components for damage, nicks,
gr00VeS, etc. PARKING BRAKE VALVE FIGURE 32 -18
G. Clean all parts with cleaning solvent (Federal
B. Connect valve assembly to hyd~aulic lines.
Specification No. PS-661).
i-i. Replace all O-rings (9).
C. Bleed system and service hydraulic reservoir
with hydraulic fluid as described in Section 12-20-05.
-REASSEMBLY
A. Reassemble parking brake valve in reverse

sequence of disassembly.

32-41-00 TROUBLE SHOOT1NG BRAKE SYSTEM

TROUBLE PROBABLE CAUSE REMEDY

Solid pedal and no brakes. Brake lining wom beyond Replace lining.
allowable limit.

Spongy brake. Air in system. Bleed brake system.

Pressure will not hold. Leak in brake system. Visually check entire system for
evidence of leaks.

Parking brake will not hold. Air in system or leak in system See remedies above.
(downstream of parking brake
valve).
Defective parking brake valve. Repair or replace the valve.

Brake grabs. Warped or bent disc. Replace disc.

Foreign matter locking disc. Clean disc and lining.

Brake pedal will not return to Master cylinder shaft or other Check that shaft travels in straight
neutral position, linkage misaligned. line and not binding in linkage.

3280-00 -STEERING NOTE

Check nose gear leg assy. for towing damage.
326091 NOSE GEAR STEERING SYSTEM if any dent exceeds 1/32 inch (SIN
Replace
The nose gear steen’ng system consists of a steen’ng 25-0001 thru 25-0823).
hom on gear leg linked to the rudder pedals by
NOTE
push-pull tubes and belicranks. Gear retradion
Aircraft S~ 25-0824 8 ON have twin limiter
automatically disengages steering mechanism from
nose wheel. (Sedion 27-20-00 outlines nose gear pads and adjustable stops (7),Fig. 32-19,
wheel installed on the nose gear leg assembly (A) that
steering rigging.) A centering cam aligns nose
for ent~y into wheeCell. will prevent turning damage to leg assembly.

32-41-00
22
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
Every 100 hours remove cotter pin (1) (Figure 4. Measure forward from aft edge of plumb line to
32-19) and retorque nut (2) to 450-500 inch Ibs. Check axle center line. Modification relocating nose wheel
holes 7n leg assembly where pivot bolt (3) is located for shoukl be accomplished if axle position, forward of
any wear. If holes are worn, replace leg assembly. plumb line, exceeds .06.
5. Add SE M20-202-3 spacer under collar to
NOTE
reposition the ~ude if required.
Shock absorber (6) and related attaching
hardware may be removed from all Mooney
NOTE
M20K aircraft if desired per Mooney drawing
Some collars have holes drilled off center and
940052.
may be turned over to change axle position.
CAUTION
6. Run gear through up/down cycle. Check nose
Dolt, washer, nut (9) and (10) (Figure 32-19)
must be installed as shown, from rear to front. gear door and wheel well tire clearances. Re-rig if
required.
2. Rod end bean’ng (4) (Figure 32-19) should be
inspected at least every 100 hours for any damage or
bending.
3. Check steen’ng hom assembly (5) collars and
spacers for looseness. Replace any bushings or
spacers that are worn. 51
4. Adjust turn limiter stop bolts O to contact cross COLLAR
member (8) of truss assembly ~Oib gap permissible)
when rudder is at its e~xtreme leg and right travel
position. SB20-
326092 NOSE GEAR STEERING AND SPACER
PLU)AB LINE
TRACKING
1. Level aircraft as described in Chapter 5.
2. Center nose wheel.
3. Place plumb line over and foMlard of nose gear
trunnion (see Figure 32-20) part number 540001-503.
SEE

6 1 I
IUBUIAR STRUCTURE j
o

ESON00-06-23 WHEEL LOCATION

CENTERFIGURE
LINE

32 20

POSITION AND WARNING

7
32-60-01 ELECTRIC GEAR SAFETY DEVICES
The gear switch operates the landing gear actuator
relays. Pulling wheel-shaped knob out and moving it to
upper detent raises gear. However, an airspeed safety
switch, is incorporated in the electrical system to
prevent landing gear retraction while on the ground. To
allow gear retraction with aircraft on jacks; attach a
12-inch length of 3/8 inch pliable rubber hose (surgical
tubing) over pitot head, and pinch open end with a
larger cotter pin; roll tubing with cotter pin until
compressed air within the twisted tube actuates
aiIspeed pressure switch. Maintain pressure on switch
until retraction is complete. To adjust airspeed switch
NOSE GEAR referto paragraph 32-60-03.
LECi ASsY.
The uplimit switch 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 proper force is exerted to hold
NOSE WHEEL STEERING FIGURE 32 19
landing gear in down-and-locked position. Refer to
Section 32-30-02,7. for proper limit switch rigging. The
gear down-and-locked position is indicated by:
32-50-02
23
 MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
1. Illumination of the GREEN gear down annunciator V,E,P. manufactured switches are field adjustable.
light, This "GEAR DN" annunciator light is dimmed They shoukl dose at 2.8 .4 inches water. Adjust slotted
when navigation lights are ON. screw head on center of swach to obtain coned settings.

2. The warning hom will not sound with the throttle CAUTION
retarded below 1200 RPM (10 in. MP, SM 25-000~
thru 25-0780) or(16 in. MP. SM 25-0781 8 ON).
The airspeed safety switch is designed to
operate witt~in a specified range during
3. The indicator marks will be aligned on the visual increasing airspeed only. Due to hysteresis of
gear-position indicator, the switchldiaphram assembly the switch MAY
NOT deactivate the landing gear circuitry until
CAUTION approximately 57 MPH (49.5 KTS). This could
When running gear up or do\nn electrically DO allow the landing gearto retract if the gear
NOT use circuit breaker as a switch, switch is inadvertently placed in the UP
position dun’ng tbe landing roll.
Partial retraction or extension may be accomplished
electn’cally as follows: WARNING
Do not turn knurled knob on back of switch
1. Place Master Switch in OFF position.
housing (Whitma(-General Switches) when
2. Move gear switch to GEAR UP or GEAR DOWN disconnecting switch from electrical
as desired, connections. This is airspeed adjustment knob,
3. Momentan’ly actuate master switch until gear is in
CAUTION
desired position.
During Static system checks, pressure
32-60-02 LANDING GEAR WARNING SYSTEM compensation on the Pitot side of switch
diaphram MUST be considered or switch
gearwaming system consists of:
The landing
diaphram may rupture.
1. Landing gear position lights: (GEAR
DOWN-WHITE indicator light on floor and GREEN light NOTE
onannunciator; GEAR IN TRANSIT up or down Referto proper electrical schematic when replacing
RED unsafe on annunciator; GEAR UP NO LIGHTS.)
with switches from another manufacturer.
2. A warning hom in cabin is actuated y throttle
32-80-00 -MISCELLANEOUS
control when gear control switch handle a ,p ,,d
throttle is less than 10 inches (25-0001 thru 25-0780) 32-81-00 LANDING GEAR SHOCK DISC
or 16 inches (25-0781 8 ON) Manifold Pressure. INSPECTION
Check warning hom for volume in flight pen’odically.
Hom will sound if gear is not DOWN and LOCKED 1 Aircraft with full fuel load and we~M on landing gear.
even if switch is in DOWN position or if airspeed is A. Main gear shock discs.
below 65 KIAS 8 gear switch is in UP position.
(1) Check gap between retaining collar (A)
326043 AIRSPEED SAFETY SWITCH (Figure 32-21) and top retaining plate (B). Allowable
ADJUSTMENT gap is 0.00 to 0.60 inches.
The airspeed safety switch, located inside cabin, is discs when gap exceeds tolerance.
(2) Replace
mounted behind airspeed indicator. The airspeed safety Use shockdisc replacement tool (C), P/N GSE
switch is incorporated into eledn’cal system to prevent 030011, told PM ME121), to remove and install main
landing gear retraction while on the ground and at gear shock discs. Use removable pad from tool as a
airspeeds below 75 5 MPH (65 +7/-4 KTS). Additionally guide on top of shock link to align discs as they are
the RED gear unsafe light comes on and warning hom being compressed.
sounds when gear control handle is placed in ’GEAR UP"
5 MPH (65 +7/-4 KTS). (3) Careful application of shock disc replacment
position below 75 tool is recommended during replacement of main gear
shock disc to keep from damaging grease fittings.
NOTE
Whitman-General switches can be adjusted
NOTE
using the following procedures: Shock disc retention collar should be installed
with chamfer facing down and forward.
1, Using a water manometer to measure pressure,
gradually apply air pressure to inlet at cap. B. Nose Gear Shock Discs.
2. Conned an ohmmeter between microswitch leads.
(1) Check for gap between retaining collar (D),
3. Gradually increase pressure to 2.775 inches of (Figure 32-22) and top retaining plate (E). Top
water until diaph~am movement closes microswitch. retaining plate must be in contact with retaining collar.
4. Slowly decrease pressure until microswitch opens. (2) Replace shock discs if gap is found. Use
shockdisc replacement tool O, P/N GSE 030010, told
5. Adjust knurled knob at Fear of switch housing until
PM ME120), to remove and install nose gear shock
switch closes at an increasing pressure of 2.775
discs. Use removable pad from tool as a guide on top
.3841-.359 in. water C/5 5 MPH or 65 +7/-4 KTS).
,f shock link to align discs as they are being
6. Secure set screw and repeat step (5) five times. compressed.
32-60-02
24
 M20K MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE

A
B-\ IU~V ~C
f‘
A r

/3 1

NOSE GEAR SHOCK DISC REPLACEMENT

FIGURE 32- 22

MAIN GEAR SHOCK DISC REPLACEMENT TOOL B. Replace shock discs that have lost resilience.
FIGURE 32 21 C. Inspect re~ltaining collar and bolt for deformation,
wear, and cracks.
NOTE
D. Replace defective bolt and collar.
Dimension (T), (Figure 32-22), is critical to
properly locate nose wheel position. The leg CAUTION
assemblies can vary, due to manufacturers
Both collar and bolt must be replaced when
tolerances, where the position for proper nose one or the other is defective.
wheel rigging cannot be met without additional
spacers (5) being used. The dimension (T) in a E. Insped nose gear snubber (shock absorber) (if
no load fully extended position should be a
nominal 3.0 inches. Add spacers to either top installed) for proper shock absorbing action. Replace
snubber when effediveness is impaired--the unit is
or bottom of the shock discs as needed. See
sealed and cannot be repaired.
(Figure 32-20), paragraph 30-50-02, for proper
steering/tracking rigging. NOTE
Shock absorbers may be removed if desired
2. Raise aircraft on jacks shocks fully e~dended. per Mooney drawing number 940052.
A. Inspect nose and main gear shocks for evidence NOTE
of gap between retaining collar and retaining plate. The
disc preload must be great enough to maintain For Nose Gear SteefinglTracking see Section
3250-02, (Figure 32-20).
complete wheel e~dension during retraction.

32-81-00
25
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

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BLANK

32-81-00
26
 OLDWILLWAYNE

CHAPTER

LIGHTS
SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 33

LIGHTS

LIST OF EFFECTIVE PAGES

PAGE DATE
CHAPTER
SECTION
SUBJECT

1/2BLANK 9-97
33-Effedivity
3. 9-97
33-00-00
4 9-97
33-21-02
5. 9-97
33-22-00
6. 9-97
33-23-00
7. 9-97
33-41-01
8 9-97
33-41-03
9 9-97
33-41-03
10 9-97
33-42-00

TABLE OF CONTENTS

SUBJECT PAGE
CHAPTER
SECTION
SUBJECT

General Descn’ption and Operation 3

33c00-00
Inten’or Lights Maintenance Practices 3
33-20-00
CabinLights-Overfiead Lights 3
33-21-00
Light Bulb Replacement 3
33-21-01
Cabin Light Switch Replacement 4
33-21-02
33-22-00 Instrument/flight Panel and Glareshield iights 5

Light Bulb Replacement 5

33-22-01
Gear Down Indicator Light (Floorboard) 6
33-23-00
6
33-23-01 Light Bulb Replacement
Merior Lights Maintenance Practices 6
33-40-00
Trouble shooting E>aen‘or Lights 6
33-40-01
High Intensity, Strobe Lights Maintenance 6
33-41-00
Power Supply Unit Removal or Replacement 7
33-41-01
PowerSupply Unitlnstallation 7
33-41-02
Strobe Light Replacement 7
33-41-03
NavigationlPosition Lights 10
33-42-00
Position Light Replacement SeM’ce 10
33-42-01
Landing/Taxi Lights (S/N 25-1224 thru 25-TEA) 10
33-43-00
Landing~Taxi Light Adjustment Procedures 10
33-43-01

SS-EFF/CONTENTS
1/2BLANK
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
33-00-00 GENERAL DESCRIPTION AND the light near the cc-pilots head. The passenger/
OPERATION baggage compartment lights are located above the
rear seats in the overhead panel and are activated by a
High intensity strobe lights standard equipment on
are
similar three position switch located adjacent to the
M20K aircraft. The lights located adjacent to the wing
light. The rear cabin light switch is accessible from the
are

tip navigation lights and incorporated into the taillight baggage compartment door also.
assembly. Separate power supplies are utilhed for each
strobe light; these are located in each wing outboard CAUTION
section, mounted on inspection covers, and inside the These cabin ligMs are connected directly to the
tallcone adjacent to the left rear inspection cover. The battery through their switches and will
system is actuated by a 10 amp circuit breaker/switch illuminate without the Master Switch ON.
located on the instrument panel in front ofthe pilot
SM 251225 thru 25-1999 aircraft may have optional
Navigation lights are located on each wing tip and in switches on both cabin door and baggage door frames
rudder trailing edge (25-0001 thru 25-0999). S/N 251000
that tum applicable interior lights ON when either door
thru 25-TEA aircraft have the aft facing navigation ligM
is opened. The fo~ward cabin interior lights are
(clear3 located on each wing tip trailing edge. The ligMs connected to cabin door switch and the aft
are activated by a 7.5 amp circuit breaker/switch
located
inten~or lights are connected to baggage
on the instrument panel in ofthe pilot egaggablnibac.hCfiWS

door
On SM 25-0001 thru 25-1224, landing lights are Rocker switches, located overhead, between pilot and
located in lower engine cowling. Two 110,000 candle co-pnot, for cabin interior lights will tum selected set of
and
power sealed beam bulbs are incorporated lights ON, as desired. The rocker switch light circuits are
mounted in a housing designed to isolate the bulbs muted through a timer and the Master Switch and will go
from engine heat and vibration. The lights are activated OFF when Master Switch is tumed Off, with the rocker
the
amp circuit breaker/switch located on switch(es) left ON.
panel in front of the pilot. The lights will go OFF in appro~dmately 90-120 seconds
ON 25-1225 thru 25-TEA, landingAa>a’ lights ate after door(s) are closed when Master is OFF and mcker
located in leading edge of each wing. Two 110,000 switch(es) are left ON. Lights will go OFF when door(s)
candle power sealed beam bulbs are located in each is(are) closed (timer delay) if Master Switch is ON or OFF
wing. The lights are activate by two 25 amp split ,,d if light rockerswitch(es) are OFF.
switches located on the pilots instrument panel. The
The light timer box is located on firewall diagonal tube
switches are use to illuminate both landing and taxi or
ahead of pilot’s right foot; it is a non-reparable unit.
either one, as desired.
Two sets of interior lights are located on the overhead CAUTION
panel. The forward cabin overhead lights are located LIGHTS WILL STAY "ON" IF DOORS ARE OPEN.
between the pilot and co-pilot seats and are actuated
by a three position switch, (dim, off, bn’ght) adjacent to
LAMP BULB
APPLICATIONS BULB PART NUMBER
14 VOLT 28 VOLT

GE 330 GE327
Glareshield Lights
GE 330 GE 327
Post Lights
GE 330 GE 327
Map Light
GE 1816 GE 1818
Cabin Inten’or Lights
Trim 8 Flap Indicator
Wl-7046 N/A
(S/N 25-0002 thru 25-0575)
GE 370 GE 327
(S/N 250576 8 ON)
Gear Down Light
GE 327 GE327
(Floorboard Indicator)
32-0228030-85* NIA
Tail Position Light (S.D.I.)
A508-14 W1290
ONHELEN)
Wing iip Position Light (GRIMES) A-7512-12 Wt 290
GE 4509 GE 4596
Landing Light (GE)
Recognition LightlBulb Assy OM-iELEN) 01-0770303-00 Same (use resistor)
Use S.D.I. Tool No. 203541 to remove lamp.

33-20-00 INTER(OR LIGHTS MAINTENANCE 33-21-01 LIGHT BULB REPLACEMENT

PRACTICES (25-0001 thru 25-1999)
1. Remove the light cover panel (2) (Figure 33-1)
33-21-00 -CABIN LIGHTS -OVERHEAD LIGHTS
from the headliner assembly (1) by removing screws

(3).
33-00-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
NOTE (25-2000 THRU 25-TEA)
The front and rear light bulbs are replaced in (Figure 33-1A)
the same manner.
Carefully slide smooth, flat sharp blade under lip
i.
2. Remove and oflight assembly flange and pop light assembly out of
replace the bulbs and check for
proper operation, mounting hole.
2. Disconnect blade terminals from light assembly.
3. Hold light assembly body and rotate bulb holder
3 counter-clock-wise to remove.

4. Pull bulb from bulb holder, replace with new bulb.

Q\ I Reinstall bulb holder.

5. Re-assemble light assembly
6. Check for proper operation.
into mounting hole.

o 1 33-2192 CABIN LIGHT SWITCH

REPLACEMENT
(25-0001 THRU 25-1300)
1. Remove cover (4) from headlinerassembly (1)
5
by removing the screws (3) holding panel in place
3-~-A II ii A i (Figure 33-1).
NOTE

I rwn
S/N 25-0247 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

require bending of spn’ng tabs to release for removal.
3. Disconnect wire connections and replace with
new switch. Check for proper operation.
4. Reassemble panels, and ventilation control if
applicable, to the headliner.
(25-2000 thru 25-TEA)
PILOTS REAR SEAT PASSENGER’S SWITCHES
i.
Remove cover from arm rest assembly by
INTERIOR LIGHTS FIGURE33-1 removing 2 screws holding cover to arm rest.

EXTERIOR
SWITCH PANEL
BAGGAGE CO~PARTMENT
BAG. CMPT. LIGHT
UGHT

FRONT SEAT
REAR SEAT

O (UNDER COVER) LIGHTS L(ASTER

´•P PILOTS OVERHEAD
SWITCH LIGHT SWITCH

RIGHT, REAR SEAT

LIGHT SWITCH ON RIGHT SIDE
RIGHT SEA’
PANEL, MPICM TO LEFT SIDE
PANEL LOCATION.

INTERIOR LIGHTS (25-2000 THRU TEA) PIG. 33-1A

33-21-02
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
2. Switches are a snap-fit and may be removed by
pressing snap tabs and pushing switch through cover.
Gjl 1 i~FwD
3. Disconnect wire terminals and replace with new
switch. Check for proper operation.
4. Reassemble switch assembly into cover by 4 OUTE3
in from top side. Re-install cover into arm
snapping
rest, secure with 2 screws.
GO-PILOTS SWITCH 3
i. Go-pilot’s cabin light switch is located in front of
cabin door hinge aboveco-pilot’s rightknee.
2. Remove i screw above switch. Remove door frme
O
switch.
cap. Pull panel from velcro fastners to access
3. Press snap tab 3 push from panel to remove.

4. Re-assemble in reverse sequence when LAP

maintenance action completed. SWI TCH
BAGGAGE COMPARTMENT SWTTCH
i. Switch is located at rear of bagage door at front,
top of hat rack opening. (Figure 33-1A).
2.Remove I screw inboard of switch. Pull door frame
down slightly from velcro fastners to access baggage FIGURE 33-2
TRIM/FLAP INDICATOR LIGHT
compartment light switch.
panel. (S/N 250001 THRU 25-0575
3. Press snap tabs and PUSH switch through
4. Disconnect terminals; replace switch.
D. Carefully screw socket back into lens.
E. Conned the knife connections and ty-rap
5. Re-assemble in reverse order.
securely.
33-22-00 INSTRUMENT/FLIGHT PANEL AND F. Check for proper operation.
GLARESHIELD LIGHTS
4. Trim/Flap Indicator Light.
33-22-01 LIGHT BULB REPLACEMENT (SRJ250576thru25-1999 Figure 333).
A. Unscrew the black knurled button (1) (Figure
i, Instrument panel lights. access to bulb.
333) to gain
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. 1
C. Insert new bulb into hood and push hood back
onto post light base.
D. Check for proper operation and hood on’entation.
2. Glareshield lights.
A. Remove outer housing by unscrewing from light I U TB D
assembly base.
B. Remove bulb and insert new bulb.
C. Screw outer housing back onto base.

D. Check for proper operation.

3. Tn’m/f=lap Indicator Light.
(S/N25-0001 THRU25-0575 Figure33-2)
A. Gain access to light assembly (1) (Figure 33-2)
FLAP
by reaching in over console side panel from co-pi(ots
stde ofcabin. WI TCH
B. Disconnect wires at knife disconneds (3) and
carefully unscrew socket portion (4) from light assembly
lens (5). The lens is glued to tn’mlffap indicator reflector
(6). TRIM/FLAP INDICATOR LIGHT FIGURE 33 3
C. Bulb will come out with socket portion of light THRU 25-1999)
(S/N 25-0576
assembly; bulb is bayonet type, push, twist and pull to
remove. Insert new bulb.
33-22-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONE/ AIRCRAFT CORPORATION

OLDWILLWAYNE
B, Bulb is a friction fit type in button; remove and 33-23-00 GEAR DOWN INDICATOR LIGHT
replace with new bulb, (FLOORBOARD)
C, Replace knurled button with new bulb installed
33-23-01 LIGHT BULB REPLACEMENT
into console,
1. Remove lower belly panel to gain access to light
D. Check for proper operation,
assembly.
5, Map Light
2. Remove and replace bulb.
A, Place wrench on fiat of exposed metal housing
on bulb assembly from receptacle.
3. Check for proper operation.
B, Screw on new bulb assembly and tighten. 4. Reinstail belly panel.

33-40-00 EXTERIOR LIGHTS MAINTENANCE PRACTICES

3340-01 TROUBLE SHOOTING EXTERIOR LIGHTS

TROUBLE PROBABLE CAUSE REMEDY

STROBE LIGHTS

Lights inoperative. Circuit breaker/switch tn’pped. Check for short circuit. Reset C/B.

Loose connection. Check and tighten electrical

connections.
Battery defective. Replace battery or use e~dernal
power.
Circuit breaker switch defective. Check continuity through switch;
replaceif necessary.
Faulty power supply. Disconnect synch wires to identify
faulty power supply.

One bulb does not light. Bulb burned out. Replace bulb.
Power supply inoperative. Replace.
Fixture not grounded. Check for good bonding between
focture and structure. Tighten
mounting screws.

Loose connection. Check all connections in circuit.

Defective fi~dure Replace fudure.
LANDING LIGHTS. NAVIGATION LIGHTS AND TAILLIGHT

Lamp fails to light. Circuit breaker/switch tn’pped. Check for short circuit. Reset
circuit breaker.
Lamp bumed out. Replace lamp.
Loose connection or defective Tighten connections and check
wire, wire drruut continuity. Replace or
repair wire if necessary.
Circuit breaker/switch defective. Check continuity through switch.
Replace if necessary.

33-41-00 HIGH INTENSITY, STROBE LIGHTS TROUBLE SHOOTING AIDS

MAINTENANCE
When no lights are flashing:
The strobe light po~ver supply requires a 14 VDC
28 VDC (25-1000 thru 1´• Check circuit breaker/switch.
(25-0001 thru 25-0999)
25-TBA) input across the red and black wires. Red is 2. To determine power supply or flashtube problems,
positive and black is negative, or common. The voltage first check the input voltage to the power supply. The
for the strobe light is supplied through Pin 1 and 3 of ~d and blade line should have 14 VDC (25-0001 thru
the power supply connector with Pin 2 as the trigger
25-0999)/ 28 VDC (25-1000 thru 25-TEA). If no voltage
pulse. The strobe light assembly is a potted assembly is present check for shorted power leads or tripped
and cannot be repaired.
circuit breaker. If input voltage is present, then
power supplies may be synchronized disconnect the yellow sync wires. This will allow
The
connei~ing each yellow wire together between ball unaffected units to flash. Determine defective light and
power supplies (Hoskins only). proceed to "one light not flashing" below.
33-23-00
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
When one light not flashing: WARNING
High voltage is involved in the circuit between
1. To determine power supply or flashtube problems, the power supply and strobe light assemblies.
first check the input voltage to the power supply. The
Although a bleed-off resistor is incorporated in
red and black line should have 14 VDC (25-0001 thru the power supply circuit, him the control
25-0999)/ 28 VDC (25-1000 thru 25-TEA). If no Mltage switch for the strobe lights OFF and allow at
is present then check for shorted power leads, blown least 20 minutes to elapse pn~or to
inline fuses, or circuit breaker. If input voltage is
disconnecting the cables at the power supply
present, then disconnect the connector to the or strobe light assemblies before handling
flashtube. 400-500VDC should be present across Pin 1 either of these units in any way. Failure to
and 3 of the power supply. If not, the power supply has observe these precautions may result in
no output and is defedive. Tum off master switch.
physical injury from electrical shock.
2. If voltage is present across Pin 1 and 3 of the
power supply, conned a known good flashtube to the C. Disconnect win’ng harness between power
power supply. If good flashtube fails to operate, power supply and strobe light. (See warning above).
supply is defective. If good flashtube operates, the D. Remove the screws secun’ng the power supply
flashtube is defective. Replace flashtube.
to the inspection panel and remove the unit.
3. Be sure yellow sync wire is insulated and not
2. Tail strobe light power supply.
grounded. (SM 25-0001 thru 250446).
3341-01 POWER SUPPLY UNIT REMOVAL
A. Gain access to tt~is unt through the enpennage
OR REPLACEMENf
(sti~gerj inspection coverbcated onthe leftside ofthe airplane.
1. Wing tip strobe power supply. a. The power supply unit is mounted on the vertical
A. Gain access to wing tip po~ver supply through bulkhead forward of the inspection access hole.
bottom inspection cover (1) near wing tip (See Figure
C. Steps B and C and waming of 33-41-01, 1,
33-4). Power supply (2) is physically attached to this above apply for removal of this power supply unit also.
inspection cover.
D. Remove the screws that secure the power
B. Disconnect win’ng connections between switch
supply to the vertical bulkhead and remove the unit.
and power supply.
3. Tail strobelight power supply.
(SM 25-0447 thru 25-TEA).
A. Gain access to this unit through the inspedion
cover on the aft, left hand side of the tailcone. The power

ooorlFWD supply is physically mounted to thb inspedion cover.

B. Disconnect the win’ng connections between the
switch and the power supply.
C. Steps B thru D, and Waming of paragraph
go 2
removal of this power supply unit.

33-41-02 POWER SUPPLY UNIT

INSTAUATION
O The installation of any of the power supplies is a

reverse sequence of the removal procedures.

CAUTION
STROBE LIGHTWIRING -An incorrect hook-up
of the wires at either the power input or
d; between the strobe light assemblies and the
1 power supply unit will cause a reversal of
O la~i polarity that results in serious component
damage and failure. Care must be taken to
ensure that the red wire is connected to
O positive power and the black wire to ground.
POWER SUPPLY
33-41-03 STROBE LIGHT REPLACEMENT

i, Wing tip strobe liaM.

A. Remove the wing tip lens (1) (Figure 335) to
VIEW LOOKING UP LEFT WING gain access to malfundionng strobe light.

INSPE~TION COVER MPICAI B. Remove the two screws holding the

navigationlposition light lens (2) and the one screw (3)
LOCATION below the flashtube assembly. This will allow the light
STROBE LIGHT POWER SUPPLY FIGURE 33 4 assembly (4) and mounting plate (5) to be pulled away
from tip rib.
33-41-01
 SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

OLDWILLWAYNE

5
S.D.I.
6

3
8

dr

10

SM3 3-NAV
WINGTIP LIGHTS FIGURE33-5

NOTE E. The ffashtube assembly must be replaced if

The Whelen Strobe-Nav light assembly is determined to be bad; the flashtube is soldered in
installed slightly different but is removed and place and is not readily removeable from the assembly.
replace~d in a similar manner. F. If required, the clear lens can be removed from
the ffashtube assembly by removing the two lens
C. Remove the two (6) from the back side
screws
retaining screws O, Fig. 33-5, and pulling the lens
of the mounting plate, free for replacement or cleaning.
G. Install the new strobe light assembly in reverse
WARNING
High voltage is involved in the circuit between sequence of removal.
the power supply and strobe light assemblies. 2. Tail strobelnaviaation .liaM removal 12V, (25-0001
Although a bleed-off resistor is incorporated in thru 250999) (See Figure 33-S A). See Figure 33-6 B
the power supply circuit, turn the control for S/N 25-1000 thru 25-TEA, 24V. Only a strobe light
switch for the strobe lights OFF and allow at assembly is located on 24V aircraft Removal is same
least 20 minutes to elapse prior to as combination 12V NAV/STROBE light assembly.
,dirsconnecting the cables at the power supply A. To gain access to the wire harness and
or strobe light assemblies and before handling
connections from the power supply rotate the round
either of these units in any way. Failure to
access cover (1) on the lower left side of the
observe these precautions may result in
physical injury from electrical shock, empennage stinger (Figure 33-6 A).
B. Disconnect strobe win’ng hamess connector
D. Disconnect the wiring harness plug and remove from strobe power supply harness and disconnect the
the flashtube assembly, connectors f6r taillight assembly.
C. Remove the connector plug (2) from the strobe
NOTE
On earlier aircraft the plug will not come
light wiring harness leaving the pins connected to the
individual wires.
through the wire routing holes. Remove the
pins from the plug and pull individual wires D. Tie and tape a strong, small diameter cord, 4 to
through the boles to allow the flashtube 5 feet long, to the entire wire hamess after plug has
assembly to come free. been removed.

33-41-03
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
E. Remove the two screws (3) secure the
that M. Check for proper operation.
strobe/taillight assembly to the rudder (4) and pull the N. S/N 25-0781 and later aircraft have a new
light assembly out so it clears the mounting hole. The strobe light installation. There is sufficient wire
wire hamess will be stretched tight at this point available to pull this strobe light assembly out the
F. Carefully begin working the wire hamess through rudder attach hole. See item (10) (Figure 33-6 A).
the empennage and rudder bulkheads until the wire Disconnect light assembly (11) from connector (12)
harness can be pulled through the light mounting hole in and replace assembly if needed.
the rudder. The Nbber grommets at each bulkhead will 33-42-00 NAVIGATIONIPOSIT(ON LIGHTS
require removal from bulkhead but leave attached to wire
hamess. See (Figure 33-6 A) forthis detail. 33-42-01 POSITION LIGHT
REPLACEMENTISERVICE
G. Pull light assembly and entire wire hamess
through mounting hole in rudder. DO NOT PULL THE i Wing tip wsition lights.
STRONG CORD ALL THE WAY THROUGH ACCESS A. Remove the wing tip lens (i) (Figure 33-5).
PANEL HOLE. You will need this to pull the new wire
B. Remove the two screws (2) hokling the position
harness back in place dun’ng installation. Remove cord
from wire harness. light lens in place.
H. Replace complete flashtube/base assembly (5) C. Pull the lens (red or green) from mounting plate
if strobe light portion is malfunctioning. The ffashtube is (5~ andremove the lamp (8).
not a replaceable component. D. Install new lamp into base.
I. Place bulkhead grommets at relative positions on E. Reassemble the light assembly in reverse
new hamess, after plug (2) is removed From new sequence.
harness.
2. Tail oosition light (25-0001 thru 250999~.
J. Tie and tape cord to new harness and carefully
A. Remove two screws (3) (Figure 33-6 A) from
begin to feed wire and grommets back to their that secures the light assembly (5)
the taillight housing
positions, totherudder(4).
K. Place all grommets in the bulkheads. Reinstall
B. Remove the clear lens (8), mounting ring (9)
plug (2) on new harness and secure the and gasket O to gain access to position light lamp (6).
strobe/navigation light assembly to the nrdder.
C. Remove lamp (6) with S.D.I. special tool no.
L. Connect the completed hamess and plug from
203541 orequivalent.
the strobe light assembly to the harness socket from
the strobe

4 3
7 ´•-~a

1
r’
12

10 1 117 5

SH123-~

B S/N 25-~ 000 thru 25-TEA

A S/N 25-0001 THRU 25-0999

TAIL LIGHT ASSEMBLY FIGURE 33-6

33-42-00
SERVICE AND MAINTENANCE MANUAL M20K MOONN AIRCRAFT CORPORATION

OLDWILLWAYNE
a. Remove clear lens (3) 8 gasket to gain access
Replace with new lamp and reassemble taillight
D.
assembly in reverse sequence. tolight bulb (4).
3. Aft Position Light (251000 thru 25-TEA) C. Pull light bulb (with special puller if needed).

A. Remove two screws that secure aluminum D. Replace with new lamp 6 reassemble light
cover (1) to wing tip (2) (FIG. 33-7). assembly in reverse sequence of removal.
-LAND1NGTTAXI LIGHTS

33-43-01 LANDINGTTAXI LIGHT ADJUSTMENT

4 PROCEDURES
1. Position aircraft to face a vertical wall with front
5 of nose wheel 7 R 6 in. from wall. Position UH 6 RR1
main landing gear at exact distance from vertical wall,
ie, parallel to wall.
2. Place four target crosses on vertical wall at
1
2 \i’ the following positions:
A. 36.5 inches up vertical wall from same ground
plane aircraft is resting on.
B. 9.85 feet left and right of nose wheel center
line.
C. 12.375 inches further outboard on both left 3
n’ght side of Step B. target position.
3. Remove access cover behind each landing/taxi
on wing lower surface.
light location
4. Tum ta>d turn adjusting
lights ON, exit aircraft,
until beams are centered on outboard

.thg’nthgil
screws
target crosses left 6 right.
5. Repeat Step 4 for landing lights, except center
light beams on inboard target crosses left and
SM33-AFT
WING TIP/AFT POSITION LIGHT FIGURE 33-7 6. Turn lights OFF, re-install access covers.

33-43-00
 OLDWILLWAYNE

CHAPTER

NAVIGATION
SERVICE AND MAINTENANCE MANUAL M20K MOONfl AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 34

NAVIGATION AND P(TOT STATIC

LIST OF EFFECTIVE PAGES

PAGE DATE
CHAPTER
SECTION
SUBJECT

1/2BLANK 9-97
34-EFF/CONTENTS
3. 9-97
34-00-00
4 9-97
34-11-00
5. 9-97
34-1 3-01
6. 9-97
34-21-00
7. 997
34-22-01
8´• 9-97
34-90-00

TABLE OF CONTENTS

SUBJECT PAGE
CHAPTER
SECTION
SUBJECT

General 3
34-00-00
Pitot 8 Static Air Pressure System 3
34-10-00
Heated Pitot-Trouble Shooting 3
34-10-01
Airspeed Indicator 4
34-11-00
4
34-11-01 Airspeed Indicator-Troublesh,otins
Vertical Speed Indicator 4
34-12-00
34-12-01 Rate-Of-Climb Indicator Trouble Shooting
4
Olertical Speed Indicator)
Aitimeter 4
34-1 3-00
Aitimeter-Trouble Shooting 5
34-13-01
Directional Gym Compass 5
34-20-00
Directional Gym-Trouble Shooting 5
34-20-01
Tum Coordinator 6
34-21-00
Tum Coordinator-Trouble Shooting 6
34-21-01
Magnetic Compass 6
34-22-00
Compass-Trouble Shooting 7
34-22-01
Artificial Horizon 7
34-23-00
Gyro-Horizon-Trouble Shoot~ng 7
34-23-01
Miscellaneous Instruments 8
34-90-00
Clock 8
34-90-01
Outside Air Temperature 8
34-90-02

34-EFF/CONTENTS
1/28 LANK
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
34-00-00 -GENERAL CAUTION
Release air pressure slowly by unrolling rubber
AllRight instruments are grouped on shock mounted tubing, a sudden release of air pressure may
panel directly in front of pilot. Flight instruments are damage airspeed indicator.
operated by:
(1) filtered air drawn into an evacuated instrument 2. Pitot system hose inspections. After pitot system
case, is checked for leaks, inspect hose sections for signs of
air deterioration. Check all tubing for brittleness, checks or
(2) barometric pressure or barometn’e impact
cracks particularly at bends or connecting points.
pressure differences,
When new hose is installed, recheck system for leaks
~3) van’ations in electn’c current due to mechanically using PITOT SYSTEM LEAK TEST procedure.
vaned resistance,
3. Static system cleaning. Blow low air pressure
(4) reference to the earths magnetic field (10-25 PSI). through the lines from the disconnected
(5) aircraft electn’cal power, line at the airspeed indicator to the static ports. Cover
each static port separately when blowing to insure that
The glareshield must be removed and plumbing each line is clear. Instrument error or possible damage
disconnected on many flight instruments before they
may result if even one port is clogged with dirt or
can be removed. Remove glareshield attaching
foreign matter.
screws, center post cover screws and carefully lift
center post cover and glareshield from the panel. CAUTION
Disconnect glareshie(d lights. NEVER BLOW AIR through lines TOWARD the
Reinstall glareshield in reverse sequence. INSTRUMENT panel; to do so will seriously
3610-40 PITOT STATIC AIR PRESSURE damage instruments. When blowing back
SYSTEM throughlines from the instrument panel, make
sure that no air is blown into instruments.
Static pressure instruments are e>ctremely sensitive to
pressure changes; therefore, the pitot and static 4. Static system leak test. The static system shoukl
system must be kept free from moisture and be checked for leaks In accordance w~h the
obstructions. Drain the pitot and static systems after instructions in Federal Aviation Regulation 91.171.
humid wet weather. If instrument operation is erratic
or
or inoperative after draining, perform the following: CAUTION
1. Pitot system leak test. (Make sure Master switch To avoid damaging either the airspeed
is OFF and Gear Control is in DOWN position.) indicator or the landing gear airspeed safety
switch an equal pressure should be applied to
A. Slip end of a short rubber hose over pitot tube.
pitot side of the indicator while leak testing the
B. Close open end of hose; slowly roll up hose until static system.
airspeed indicator reads 150 MPH (132 KIAS).
5. Alternate static source. An anemate static source
Clamp hose and hold for one minute.
C.
valve is provided to change the static air source from
D. If airspeed indicator falls more than 10 MPH
outside aircraft to inside cabin. The valve is located on
(9 KIAS), within one minute, check system for leaks
the lower panel immediately to the left of the pilots
and tighten line fbtings. control column. Airspeed indicator and altimeter
E. Repeat steps B, C, and D until obtaining less readings will be slightly affected when using the
than a ?O MPH (9 KIAS)indicator reading drop. altemate static source.

361091 HEATED PITOT TROUBLE SHOOTING

TROUBLE PROBABLE CAUSE REMEDY

Tube does not heat or clear Switch circuit breakertripped. Reset circuit breaker.
itself of ice with switch on.
Open circuit. Repair.
Excessive voltage drop between Check voltage at pitot head.
battery and pitot head.

Heating element bumed out. Replace pitot head.

3600-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
34-11-00 -AIRSPEED INDICATOR Radial Red Line 225 MPH/GAS (195 KCAS)
Registers airpseed in miles per hour and/or knots. Air Yellow Are 200-225 MPH/GAS (174-195 KCAS)
pressure difference between impact air, pitot tube, and
static air (static ports on each side of the aircraft Green Are 72-200 MPWCAS (63-174 KCAS)
tailcone) operates the airspeed indicator. An White Are 66125 MPH/GAS (58-109 KCAS)
electn’cally heated pitot head prevents ice obstruction
in flight.
NOTE
The airspeed indicator dial markings are as follows: See Section 27-95-00 for stall warning systems.

34-11-01 AIRSPEED INDICATOR TROUBLE SHOOTING

TROUBLE PROBABLE CAUSE REMEDY

Instrument pointer does not Leak in instrument and seal case Check for leak.
indicate properly. or in static lines lines.

Obstruction in pitot tube. Clean out obstruction.

Instrument pointer oscillates. Leak in hsbur~ent case orin paot lines. Check for leak and seal lines.

361290 VERTICAL SPEED INDICATOR

Converts barometn’c pressure changes within the side for ascent rate and bottom side for descent rate.
static port lines to aircraft ascent or descent rate; The recessed, slotted screw at the lower left of the
readings are in feet per minute. instrument case is used to "zero" the indicatorwhen
the aircraft is on the ground.
This instrument has a single needle and two adjoining
scales that read from 0 to 2000 feet per minute, top

34-1 261 RATE-OF-CLIMB INDICATOR TROUBLE SHOOTING. (VERTICAL SPEED INDICATOR).

TROUBLE PROBABLE CAUSE REMEDY

Pointer does not set on zero. Aging of diaphragm. Tum setting screw to reset pointer
at zero. Tap instrument while
resetting.

Pointer fails to respond. Obstruction in static line. (Includes Disconnect static line from
water) instruments. Apply low pressure air
(1625 PSI max) to instrument end
of static line. Check both static
ports for air Row. Depress static
drah valve and check for water.
Keep depressed until air is free of
moisture. Reconnect static line to
instruments and leak check

Pointer oscillates. Leaks in static line. Disconnect all instruments

connected to the static line. Check
individual instruments and test
installation for leaks.

Defective mechanbm. Replace instrument.

361 390 -ALTIMETER

The altimeter operates by absolute pressure, and pressure is sensed through the static vents. A knob
converts barometric pressure to altitude; reading is in adjusts a movable dial behind a small window in the
feet above mean sea level. The aitimeter has a foced face of the main dial to indicate local barometric
dial with three pointers to indicate hundreds, pressure. This corrects the altimeter reading for
thousands, and tens of thousands of feet. Barometn’c prevailing conditions.

34-11-00
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
3413-01 -ALTIMETER TROUBLE SHOOT1NG

TROUBLE PROBABLE CAUSE REMEDY

Excess scale error. Improper calibration Replace instrument.

adjustment.

Excessive pointer oscillation. Defective mechanism. Replace instrument.

High reading. Static pressure system leak. ETm’nate leak in static pressure system

Setting knob is hard to turn. Wrong lubn’cant or lack Replace instrument.

of lubrication.

Inner reference marker fails to Marker out of engagement. Replacement instrument.

knob is rotated
mxR wf~en setting

Setting knob set-screw is Excessive vibration. Tighten instrument screw if loose.

loose or missing. Replace instrument if screw is missing.

Cracked or loose cover Excessive vibration. Replace instrument.

glass.

Dull or discolored luminous Age. Replace instrument.

markings.

Barometric scale and Shift in mechanism. Reset pointers.

reference markers are out of
synchronization with pointers.

Batometn’e scale and Slippage of mating parts. Replace instrument.

reference markers are out

of synchronization.

34-2090 DIRECTIONAL GYRO COMPASS directional heading. Vacuum pressure for satisfactory
This operation is 4.25 ~-.2 to 5.5 +0.0/-.2. The vacuum
vacuum-ope~ated instrument indicates the
systemfilters should be changed each 500 hours or at
heading reference. one year intervals, whichever occurs first. (See
The directional gym rotor is air driven and rotates with Trouble Shooting Chart, for maintenance instructions.)
its spin a>ds horizontal. The knob is used to reset basic

34-2091 DIRECTIONAL GYRO TROUBLE SHOOT1NG

TROUBLE PROBABLE CAUSE REMEDY

Excessive drift in either Dirty air filter thigh vacuum Inspect filter. Replace if necessary.
direction, indication).
Excessive vibration. Test with vibrometer. If vibration
amplitude is more than .004 inch,
examine shock mountings to see if
connections are pulling on

instrument.

Insufficient vacuum. If vacuum Correct for insufficient vacuum as

indication is below 4.25 IN. Hg., follows:

check as follows:
Vacuum regulating valve 1. Adjust vacuum regulating valve.
improperly adjusted.

34-13-01
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
DIRECTIONAL GYRO TROUBLE SHOOTING (con’t~

TROUBLE PROBABLE CAUSE REMEDY

2. Pump failure. 2. Repair or replace pump.

3. Vacuum line kinked, leaking, 3. Locate and if defective replace or

or too long for its diameter. repair vacuum line. Check for
collasped innerwall ofRexible hose.

Defective mechanism (wom or Replace instrument.

dirty pivots and bearings.)

Dial spins continuously in one Operating limits have been Reset the instrument with the
direction. exceeded aircraft in level flight.
Defective mechanism. Replace instrument.

34-21-00 -TURN COORDINATOR

A gym instrument that indicates control coordination and rate of tum. This instrument is electrically driven.

34-2191 TURN COORDINATOR TROUBLE SHOOTING

TROUBLE PROBABLE CAUSE REMEDY

Pointer fails to respond. Foreign matter lodged in Replace instrument.

instrument.
No electn’c current. Check voltage at instrument.

Bar does not set level. Gimbal and rotor assembly out Replace instrument.
of balance.
Fitted orwom pivots or Replace instrument.
bean‘ngs.

In low temperature, bar fails to Oil has become too thick. Replace instrument.
respond or responds sluggishly
and with insufficient deflection.
Insufficient bean~ng clearance. Replace instrument.

Bar sluggish in returning to level Oil or dirt behnreen damping Replace instrument.
and does not set level when pistons and cylinders.
stationary
Excessive clearance between Replace instrument.
rotor and rotor pivots.

34-22-00 MAGNETIC COMPASS Degausing of the tubular structure may be required if

compass cannot be compensated within limits.
The magnetic compass dial, graduated in five-degree Carefully go over the entire steel structure with
increments, is encased in a liquid filled glass and degauser to remove residual magnetism. Recommend
metal case. The unit mounts on the stainless steel Armature Growler to degause steel structure.
windshield center post above the glareshiekd. The
compass should be swung and compensated at each NOTE
annual inspection and whenever new equipment is Refer to S.B. M20-1S0A, Instruction Ill, for
installed. To compensate for N-S deviation, adjust left degausing procedures.
screw; to compensate for E-W deviation, adjust n’ght
screw.

NOTE
Check for outside magnetic influences if excessive compensation is required.

34-21-00
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
34-22-01 COMPASS TROUBLE SHOOTING

TROUBLE PROBABLE CAUSE REMEDY

Excessive card error. Compass not properly Compensate instrument.

compensated.
Memal magnetic interference. Locate magnetic interference and
eliminate if possible.

Excessive card oscillation. Improper instrument mounting. Align instrument.

Insufficient liquid. Replace instrument.

Sluggish card. Weak card magnets. Replace instrument.

Excessive pivot fn‘ction pr Replace instrument.

broken jewel.

Instrument too heavily Correct excess compensation.

compensated.

Liquid leakage. Loose bezel screws. Tighten screws.

Broken cover glass. Replace instrument.
Defective sealing gaskets. Replace instrument.

Discolored luminous Age Replace instrument.

markings or discolored
damping liquid.

Defective light. Burned out lamp or broken Check lamp or wiring continuity.
circuit.

34-23-00 ARTIFICIAL HORIZON Maintenance is similar to that required for the

directional gym compass.
The vacuum-powered artificial horizon gym indicates
aircraft attitude relative to straight and level flight.

34-23-01 GYRO-HORIZON TROUBLE SHOOTING

TROUBLE PROBABLE CAUSE REMEDY

Examine filter and clean or replace if

Horizon bar does not Dirty air fitter thigh vacuum
respond, indication). necessary.
Insufficient vacuum resulting Correct insufficient vacuum as

from the following: follows:

1. Vacuum regulating valve 1.Adjust valve.

improperly adjusted.
2. Pump failure. 2.Repair or replace pump.
3. Vacuum line kinked, leaking, 3. Locate and repair. Check for
ortoo long for its diameter. collapsed inner wall of flexible hose.

Horizon bar does not settle. Defective mechanism. Replace instrument.

Insufficient vacuum. Correct for insufficient vacuum as

outlined above.

34-22-01
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
GYRO-HORIZON TROUBLE SHOOTING (con’t~

TROUBLE PROBABLE CAUSE REMEDY

Excessive vibration. Test with vibrometer. If amplitude

is more than .004 inch, examine
installation to determine whether
flexible hose connections are
restricting movement of
instrument

Shock mounted panel is Examine shock mountings and

contacting structures replace if necessary.

(inadequate clearance).

Horizon bar oscillates or vibrates Excessive vacuum resulting from Correct for excessive vacuum as

thefollowing: follows:
excessively,
i. Examine filter and clean or
1.Dirtyairfiiter.
replace if necessary.

2. Vacuum regulating valve 2. Adjust valve.

improperly adjusted.

3. Defective mechanism. 3. Replace instrument.

4. Excessive vibration. 4. Test with vibrometer. If

amplitude is more than.004 inch,
examine installation to determine
whether Re~ble hose connections
are restn’cting movement of

instrument.

5. Shock mounted panel is 5. Examine shock mountings and

contacting structure replace if necessary.
(inadequate clearance).

36´•9040 MISCELLANEOUS INSTRUMENTS 34-90-02 OUTSIDE AIR TEMPERATURE

34-90-01 CLOCK Provides the pilot with the free stream outside air
temperature in degrees centigrade.
Various clock options are available. The clock is
mounted in the left side of the instrument panel.

34-90-00
 OLDWILLWAYNE

C H ~A PT E R

OXYGEN
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 35

OXYGEN

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35-00-02 6´• 897

TABLE OF CONTENTS

CHAPTER SUBJECT PAGE

SECTION
SUBJECT

35-00-00 General 3
35-00-01 Recharging Procedures 3

35-00-02 Maintenance P~actices 3

35-EFF/CONTENTS
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35-00-00 GENERAL 25-0001 thru 25-1 999 and to Figure 35-1B for S/N
25-2000 thru 25-TEA configurations.
The oxygen system is an optional installation for serial
number 25-0001 thru 25-TEA. The system consists of
WARNING
a 76, (steel) 77.1 (composite) or a 115.7 (composite)
proper safety measures must be employed
cubic ft. cylinder located in the tailcone immediately aff
while oxygen system maintenance is being
of the baggage compartment bulkhead. A reducing
valve and analtitude compensating valve are performed or a serious fire hazard will be
created. Avoid making sparks and keep all
connected to the cylinderto regulate oxygen flow for a
given altitude. Lines connected to the aHitude burning cigarettes or fire away from the vicinity
of oxygen. Make sure that your hands, tools,
compensating valve distn’bute aviators oxygen to pilot and clothing are clean, particularly with respect
and passengers. The system is activated by eitherthe
to oil or grease, for these will IGNITE upon
control handle being pushed forward (S/N 25-0001
contact with pure oxygen under pressure.
thru 25-0780) or the control knob rotated (250781 thru
25-TEA) to open the reducing valve. A gauge, located
on the pilots arm rest adjacent to the control, indicates 35-00-01 RECHARGING PROCEDURES
pressure of the cylinder. When cylinder is full,
pressure will indicate 1350 P.S.I. at 210 C. C/OO F.). WARNING
The system is serviced through an access opening Oil, grease or other lubricants in contact with
located aff of the baggage compartment door. oxygen create a serious fire hazard; such
Standard refill fntings are required to fill the cylinder contact must be avoided when handling oxygen
with aviators oxygen. (Spec. No. MIL-O-27210). equipment.
The new inten’or dictated slight changes forthe
oxygen system outlets. Refer to Figure 35-1A for S/N WARNING
NO SMOKING when nder.

7‘

2
O

3 6 .cv~B

s/N 25-0001 THRU 25-0780

11

OOfSTELTUOII

CYLINDER 0?

1 2
sin 25-0’181 THRU 25-1999

OXYGEN SYSTEM FIGURE 35 iA (25-0001 THRU 25-1999)

35-00-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AlRCRAFT CORPORATION

OLDWILLWAYNE
supply gauge Olocated
adjacent to this
control
indicates the pressure of
/O
oxygen available in system.
2. The pilot’s 6 cc-pilot’s
outlets (8) and passenger
outlets (9) should be
g inspected for damage and
cleanliness dun’ng servicing.
8 3. Inspect each individual
oxygen mask, and fdtings
for damage.
1.4 1(14)
12 4. Oxygen system test
procedures.
1 A. Remove oxygen line
from regulator and plug the
3 line.
B. Cap open regulator
port with a clean plastic cap
to prevent contamination of
I’egulator.
10 ----tt-RT I C. Conduct low pressure
system leak test using a 70
12 10
PSI oxygen supply
plugged into one of the cabin
;1 3 outlets and a test gauge
2 plugged into another outlet.
1 Apply 70 10 PSI to the
system; allow 2 minutes for
the system to stabilize;
remove oxygen supply. The
drop in pressure after 15
OXYGEN SYSTEM FIGURE 35 1B (25-2000 MRU 25-TEA) minutes shall not exceed 5
PSIG.
1.The oxygen cylinder should not be used to less
than 100 P.S.I.; contamination may occur to the D. Remove temporary plug and ensure that the
cylinder and valve. The valve must be removed and cylinder is charged to capacity.
the cylinder cleaned and inspected if this happens.
E. Conduct high pressure test using cylinder
2. Refill the cylinder with aviators oxygen pressure. Using supply gauge on pilot’s side wall, note
Specification No. MIL-O-27210, through the Oxygen cylinder pressure. There shall be no pressure loss after
Servicing Access Door (1) (Figure 35-IA or-1B No 30 minutes.
special fittings are required for this servicing, however F. If leakage exists apply MIL-L-25567, leak test
several types of standard oxygen fittings are in use and
solution to suspected areas. After test, wipe clean and
a compatible fitting for the Scott Recharging Valve (2)
must be used, dry. Make necessary repairs and retest.
Mooney P/N 870025-501 oxygen recharge hose 5. Oxygen system purging.
assembly is recommended.
Offensive odors may be removed from oxygen system
3. The cylinder contains 1850 P.S.I. at 210 C. (700 by purging. The system should also be purged any
F.) when fully charged. Temperature has an affect on time the lines are left open and subject to
the correct charging pressure; See Section 12-10-04 contamination. Purging is accomplished by connecting
and (I=igure ~21) for pressure vs. temperature a recharging cart into system and permitting oxygen to
charging pressure, flow through lines and outlets until any offensive odors
have been carried away.
359092 MAINTENANCE PRACTICES
WARNING
(Ref: AC 43.13-1(8), chap. 8, pam. 363)
Avoid making sparks and keep all burning
i. The control cable (3) is attached to an actuating cigarettes or fire away from vicinity of airplane
arm (4) on reducing valve (5). This cable is routed when outlets are in use. Inspect filler
through van’ous bulkheads along left side panel to connection for cleanliness before attaching it
control (6) at pilots position. The control is a push-pull to filler valve. Make sure that your hands, tools,
cable assembly that is activated by a control lever and clothing are dean, particularly from grease
assembly for SM 25-0001 thru 25-0780 and a rotating and oil stains, for these contaminants will
knob assembly for S/N 25-0781 thru 25-TEA. The IGNITE upon contact with oxygen.

35-00-02
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OLDWILLWAYNE
The following procedures are recommended to purge 7. Oxygen cylinder installation.
the system: new cylinder and regulators into position
A. Place
A. Conned a recharge cart to the filler valve (2). in clamps (11) and secure. New cylinder should be
Set cart pressure regulator to deliver 50 PSI to system. positioned with regulator valves and control arm In
same position as removed cylinder assembly
B. Plllg an ox~gen maskknoe~ wHet (8)&(9)in cabin
components.
C. Open cabin door and place control knob (6) in
hair open position. B. Remove caps from lines (12) (13); carefully
all connedions for damage or any foreign
inspect
D. Allow system to purge for one hour. If offensive substance before connection to new cylinder and
odor still lingers, continue purging system for an valves.
additional hour. If such odors still remain, replace
supply cylinder. After system has been adequately C. Conned all lines (12) 3 (13) to proper fitting and
purged, remove masks from outlets (8) 3 (9). Place connect control cable (3) to arm (4) on reducer valve
control knob in closed position and service system as (5).
described in 35-00-01.
D. Charge cylinder, if required, to coned pressure,
6. Oxygen cylinder removal. see recharging table on (Figure 35-2).
The oxygen cylinder is located in tailcone, aft of to OPEN
E. Place pilots contol leverlknob (6)
baggage compartment bulkhead. Access to cylinder is
obtained thru radio compartment access door or left position.
side of aircraff behind leff wing. F. Plug one oxygen mask (14) into pilots outlet (8)
to check for proper system operation.
WARNING
Keep fire, cigarettes and sparks away from G. Repeat this checkout procedure for all outlets
vicinity of oxygen cylinder. Oil and grease will (8) (9).
IGNITE upon contact with oxygen under
H. Test system for leaks per leak test check,
pressure.
paragraph 35-00-02, D.
A. Place pilots control lever/knob (6) in closed H. Reinstall radio compartment access door in
position. tailcone.
B. Gain access to´•cylinder through large radio
compartment door. NOTE
C. Slowly loosen supply line fittings at cylinder Oxygen cylinders must be hydrostatic tested
of
valve (5), (reference figure 35-1A or B), to relieve any every 3 years in accordance with DOT Code
pressure that may exist in supply lines (12 3 13). After Federal Regulations, Title 49, chap. 1, pam.
173.34,
pressure is relieved, remove lines.
D. Disconnect control cable (3) from arm (4) on NOTE
reducing valve (5). All oxygen cylinders must be replaced every
E. Cap all open lines (12) 3 (13) and regulator 10,000 recharge cycles.
openings (5) 3 (10) with clean metal caps.
NOTE
F. Note relative position of regulator valves (5) 3
Maximum life for composite oxygen cylinders
(10) and control arm (4) pn’or to removal. is 15 years.
G. Loosen clamps (11) retaining cylinder, while
supporting cylinder. NOTE
H. Carefully remove cylinder and regulator from its Maximum life for light weight steel oxygen
position, cylinders is 24 years.

35-00-02
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OLDWILLWAYNE

vary due to ambient temperature at filling area

Filling pressures will and the rise of temperature resulting from
compression of oxygen Because of this, merely filling to 1850 PSIG will not
result in a properly filled cylinder. Fill to
pressuresindicated on Figure 35-2 for ambient temperatures.

FILLING AMBIENT FILLING

AMBIENT
PRESSURE TEMPERATURE PRESSURE
TEMPERATURE
eF, PSIG eF, PSIG

0 1650 50 1875
1700 60 1925
10
1725 70 1975
20
30 1775 80 2000
1825 90 2050
40

OXYGEN FILLING PRESSURES vs. TEMPERATURES FIGURE 35´•2

35-00-02
 OLDWILLWAYNE

CHAPTER

VACUUM
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CHAPTER 37

VACUUM

TABLE OF CONTENTS

CHAPTER SUBJECT PAGE

37-00-00 General .5

37-1 0´•00 Distribution .5

37-11-00 Dry Air Pump .5

37-11-01 Maintenance Practices ´•5

37-11-02 Servicing .6

37-11-03 Removal .6

37-11-04 Reinstall .6

37-12-00 Vacuum Regulator .6

37-12-01 Maintenance Practices ´•6

37-1 2-02 Servicing .6

37-1 2-03 Removal .6

37-1 2-04 Reinstall .6

37-1 2-05 Adjustment ´•6

Filters .7
37-1 3-00
Maintenance Practices 7
37-13-01
Servicing .7
37-1 3-02
Removal .7
37-1 3-03
37-1 3-04 Reinstall .7

37-1 4-00 Hoses .7

37-14-01 Maintenance Practices 7

37-1 4-02 Servicing .7

37-1 4-03 Removal .7

37-1 4-04 Reinstall .7

37-20-00 Indicating .7

37-21-00 Vacuum Switch ´•7

37-21-01 Description ´•7

37-21-02 Maintenance Practices 7

37-21-03 Removal .7

37-21-04 Reinstall .7
´•7
37-21-05 Adjustment
´•8
37-30-00 Dry Air Pump Repair
37-30-01 Coupling Installation ´•8

37-40-00 Stand-by Vacuum System ´•8

37-40-01 Maintenance Procedures .8

37-CONTENTS
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CHAPTER 37

VACUUM

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SUBJECT

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37-1 1-02
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37-1 3-00
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37-00-00 GENERAL 37-11-01 MAINTENANCE PRACTICES

An engine driven dry air vacuum pump supplies suc- Protection of pneumatic dry air pump when cleaning
tlon for vacuum operated gyroscopic Right instruments: engine compartment is very important.
Dirctional Gyro and Artificial Horizon. The air is passed
WARN(NG
through several filters before entering instruments. A
vacuum regulator valve is incorporated to maintain re- dry air pump from contamination
Failure to protect
quired operating vacuum throughout the engine power by engine cleaning solvents may result in failure of
range. Idle RPM settings will normally not provide ade- dry air pump within a short period of operation.
quate vacuum to satisfactorily operate instruments.
A vacuum annunciator light will illuminate and flash Prior to washing down engine compartment, the follow-
when vacuum drops below the setting required to ing precautions must be taken for better service life of
operate instruments. pneumatic dry air pump.
A standby vacuum system kit is available for M20K 1´• Dry air pump coupling.

aircraft. This kit can be installed by the factory or in the

CAUTION
field. The standby vacuum system should be activated
coupling
Do not blast air pump area or other
manually when "low vac" light flashes on regular engine
driven system. Refer to Vendor Manual for standby pneumatic system components with cleaning
vacuum system repair. Aircraft with optional radar in-
solvent under high pressure.
stallation use vacuum pump (outlet) pressure side to
Protect coupling area between pump mounting Range
pressurize RTA compartment in right wing.
and pump housing by wrapping a protective covering
37-10-00 DISTRIBUT1ON around that area dun’ng engine cleaning.

37-11-00 DRY AIR PUMP CAUTION

Do not allow’protective covering around coupling
A dry air pump (1) (Figure 37-1) requires no main-
tenance between replaceme~t. Replacement is recom- or filters to become saturated with solvent.

mended at 500 hours at engine overhaul.

The seals in front frame of housing behind coupling are
NOTE designed to keep foreign material such as dirt, dust
out
Always replace inoperative pump with new air and light?uid. However. fluid~under high pressure can

cADXlsTuEwr Olllr)

~HSTRUUEHT PAHEL

6;s~´•-, s~

EH6~HE

FlREWALL

ALTERN*TE INSTRUUDIT
FILTER ~STALUfK)H

VACUUM SYSTEM FIGURE 37 1

37-00-00
 MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
2. Dry air pump fittings. Before washing engine off, When hose clearance is tight, making it difficult to
check pump fittings for looseness of threaded fittings. reinstall onto pump fitting, spray fitting at hose end
Fluid can seep through loose threads and enter pump. with silicone. LET DRY, then install hose by pushing it
3. Dry air pump discharge hose (vacuum instrument straight on.

system) Plug end of the hose or fitting and flag it with a CAUTION
red "Remove Before Running Engine" tag, then clean
Do not wiggle hose from side to side. Wiggling
engine.
could cause particles to be cut from hose ID.
CAUTION These particles would damage the pump.
Remove plug prior to running engine.
CAUTION
37-11-02 SERVICING Change all filters in the system. This must be done
or pump wananty may be voided.
The dry requires no servicing. The intemal
air pump
parts self-lubricating and require NO ADDITIONAL
are 37-12-00 -VACUUM REGULATOR
lubricating. The regulator (2) (Figure 37-1) is a spring-con-
vacuum

37-11-03 -REMOVAL trolled diaphragm valve for regulating vacuum for

1, Disconnect hoses from dry air pump.
aircraft pneumatic instrument system. The vacuum
2, Remove air pump from engine and discard old
regulator is located on left firewall, inside cabin, just
under glareshield. Adjust vacuum regulator valve ac-
mounting gasket and locking hardware.
3, Remove from pump. Retain
cording to Section 37-12-05.
fittings fittings a they
are serviceable; clean thoroughly before re-using. Dis- 37-12-01 MAINTENANCE PRACTICES
card twisted fittings and nuts with rounded corners. to insure it is
Check general condition of regulator
4. Pad inspection. Check condition of AND 20000
secure and inairworthy condition.
pad seal, If seal shows any signs of oil leakage, replace
seal. Replace seal If there is any doubt as to its serv- 37-12-02 SERVICING
iceability. No servicing is required to the regulator other than fil-
37-11-04 INSTALLATION OF NEW PUMP ter replacement. See Section 37-13-00 for details.
37-1;-03 -REMOVAL
CAUTION
Never install 1. Undemeath instrument panel, remove both instru-
a pump that has been dropped.
ment lines from vacuum regulator; cap to prevent
1. Consult airframe manufacturer’s current parts foreign objects from entering them.
manual, Airborne’s Application List, or PMA label on 2. Engine compartment, remove hose from vacuum
the pump box to verify that the pump is correct model regulator; cap to prevent foreign objects from entering.
for engine and/or system. 3. Loosen and remove large nut at firewall on
2. Place pump mounting Range in a jaw-protected vacuum regulator.
vise, with drive coupling downward. Protect pump 4. Pull regulator aft to remove from aircraft.
mounting Range with soft metal or wood. 37-12-04 REINSTALL
CAUTION 1. Insideaircraft, insert vacuum regulator thru
Pump housing should never be placed directly in a
mounting hole in firewall.
vise, since clamping across center housing will 2. Install large nut on regulator and tighten.
cause an internal failure of carbon rotor. 3. Engine compartment, install hose from pump to

thread with silicone and LET DRY.

regulator and secure.
3. Spray fitting 4. Inside aircraft, install both instrument lines to
DO NOT teflon tape, pipe dope or thread lube.
use
4. Install fittings in pump. Hand tighten.
regulator and secure.
5. Use only a box wrench to tighten fittings to 37-12-05 -ADJUSTMENT
desired position. DO NOT make more than one and into
1. Tee a calibrated vacuum gauge system
one half (1 1/2) turns beyond hand-tight position,
upstream of regulator, (see Figure 37-1).
6. Install new pump mounting gasket (supplied with
2.Operate engine at a minimum of 1700 engine
new pump). RPM. If vacuum regulator is not set at 4.75 0.25 In.
7. Always replace ALL locking washers when install-
Hg., then bend locking tab away from thumb adjust-
ing a new pump. Tighten all four (4) mounting nuts 90 ment screw. Tuming screw in, will increase vacuum;
to 110 in. Ibs.
tuming screw out, will decrease vacuum. Set vacuum
3. Prior to reconnecting hoses, inspect inside of the to read 4.75 t-/-.25 In. Hg.
hose carefully to make sure it is clean and free of all
debris, oilsor solvents. Use vacuum or air pressure to NOTE
clean lines. Remove hoses from the aircraft if neces- After setting regulator, re-bend tab back to lock
sary. adjusting screw.
37-11-02
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OLDWILLWAYNE
37-13-00 -FILTERS 37-14-04 -REINSTALL

All filters, except vacuum regulator filter are of paper- Where hose clearance is tight, making it difficult to
pleated material design. The vacuum regulator filter is a reinstall a onto pump fitting, spray fitting at hose end
foam-garter design, with silicone. LET DRY, then install hose by pushing it

37-13-01 MAINTENANCE PRACTICES straight on.

NOTE
Air filter replacement intervals:
A. Vacuum regulator filter (2) every 100 hours. Do not wiggle hose from side to side. Wiggling
B. Instrument filters (5) at least once a year(see could cause particles to be cut from hose ID.
These particles would damage the pump.
Chapter 5-10-01)
routine inspection of condition of
2. All filters require Make certain hoses are connected to correct fittings.
element and security of filter in system. Incorrect installation will cause damage to gyro system.
3. All filters must be changed when a new pump Install clamps and secure.
is installed.
37-20-00 -IND1CATING
37-13-02 -SERVIC)NG
The indicating system contains a low vacuum light
All filters requireservice except routine inspections.
no which illuminates (Rashes) when vacuum is below 4.25
Replace with new current configuration filters. .2 In. Hg. and a high vacuum light which il-
The alternate instrument filter installation (6) (Figure 37- luminates (steady) when vacuum goes 5.5 (+.2-.0) In.
1) should follow the same cleaning and replacement Hg. or above.
schedule.
37-21-00 -VACUUM SWITCH
37-13-03 -REMOVAL
The vacuum switch (7), Pig. 37-1, is located on either
i. Vacuum regulator garter filter is removed by th, Artificial Horizon (3) or Directional Gyro (4). The il-
stretching it over and off regulator frame.
luminating low and high light adjustments are done at
2. Gyro instrument filters unscrew from the back of switch, not on annunciator panel.
the instruments.
37-21-01 -DESCRIPTION
37-13-04 -INSTALLATION
The switch is a.low and high vacuum sensing adjus-
i. Prior to installing a new vacuum regulator filter, table unit.
check regulator to insure that a is clean from any
37-21-02 -MAINTENANCE
foreign material.
2. Reinstall new filter in fitting and tighten. Check for switch security in instrument and all wires
secure at switch.
CAUTION
Don’t over tighten; overtightening will crack rear 37-21-03 REMOVAL
housing. Disconnect wires and unscrew from aft instrument

37-1 4-00 -HOSES housing.

37-21-04 -REINSTALL
The hoses are of the aircraft MIL-H-type.
Install switch in housing and tighten. Reconnect wires.
37-14-01 MAINTENANCE PRACTICES
CAUTION
During engine cleaning, protect the discharge hose:
1. Plug end of hose and Rag it with a red "Remove Do not over tighten. Over tightening will cause
Before Running Engine" tag, then clean engine. cracking of aft instrument housing.

CAUTION 37-21-05 -ADJUSTMENT

Remove plug prior to running engine. 1. Remove switch from instrument. Reinstall wires if
removed. Attach poly-vinyl hose, ’T’ fitting and
Periodic check of all clamps for security is recom-
calibrated gauge to vacuum switch. Connect other end
mended.
of hose to a vacuum source.
37-14-02 SERVICING 2. Turn aircraft power on. The "low vac" light should
flash.
Inspect inside of hose carefully to make sure it is clean
and free of all debris, oils or solvents. Use vacuum or 3- Apply vacuum and adjust source to.4.25 (i/- .2)
air pressure to clean lines. Remove hoses from aircraft In´• Hg. Adjust Low setting screw (connector end of
if necessary, switch) to illuminate low vacuum circuit on annunciator
panel.
37-14-03 -REMOVAL 4. Increase vacuum source to 5.5 (+.2-.0) In. Hg.
Replace old, hard, cracked brittle hose, particularly
or Punch a small jewelers screw driver through poly-vinyl
on pump inlet. Sections of inner layers may separate, tube and into fitting where high setting screw is located
causingpump failure, and adjust until "HI/LOW VAC’ light on annunciator is
illuminated.
37-1 3-00
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OLDWILLWAYNE
5. After completion of switch adjustment, turn 2. Ifcoupling (1) has sheared, remove engine cou-
aircraft power OFF. pling drive gear (2) from engine gear housing and see
6. Remove switch from hose and gauge. Section 37-30-02 below.
7. Relnstall switch in Gyro. Reconnect wires. 3. Use a screwdriver or similar tool, remove pump
drive coupling (1) from engine coupling drive gear (2)
CAUTION and pump drive gear (3) being careful not to damage
Crossing electrical wires an vacuum switch will drive pins.
cause annunciator lights to act in reverse. 4. Push new drive coupling (1) into place on cou-
pling drive gear (3).
37-30-00 DRY AIR PUMP REPAIR
5. Push engine coupling drive gear (2) into place on
It is not recommended that the Airborne Dry Air Pump pump drive coupling (1).
be repaired. Remove the faulty pump and install a new 6. Tum by hand, check for rotation of pump.
pump and all new filters. 7. Reinstall pump on engine and test run (refer to
Chapter 37-11-04)
37-30-01 COUPLING INSPECTION AND 3. Make log book entry.

REPLACEMENT (FIGURE 37-2) NOTE

After installation, if regulator valve requires
1. Remove vacuum pump from engine in accord- adjustment refer to Section 37-12-05.
ance with maintenance manual, Chapter 37-11-03.

O 1
;,Oo o
o
o

f
2 1 3

DRY AIR PUMP COUPLING INSPECTION FIGURE 37 2

37-40-00 STAND BY VACUUM SYSTEM 37-40-01 MAINTENANCE/REPAIR

(OPTIONAL) Refer to manufacturers service and maintenance data
for the particular stand-by system installed.

37-30-00
 OLDWILLWAYNE

CHAP~ER
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CHAPTER 39

ELECIRICAL PANELS AND COMPONENTS

TABLE OF CONTENTS

CHAPTER SUBJECT PAGE

SECTION
SUBJECT

39-00-00 General .5
39-10-00 instrument and Control Panels .5
39-10-01 Flight Instruments .5
39-10-02 Avionics Equipment .6
39-10-03 Engine Instruments and Circuit Breakers .6
3411-00 night Instrument Panel .6
39-11-01 Cluster Gauge .7
39-11-02 Landing Gear Switch .8
39-11-03 Landing Gear Safety Override Switch .8
39-12-00 Avionicsmadio Panel .9
39-12-01 Annunciator Panel .9
39-12-02 Emergency Locator Transmitter (ELT) Switch .9
39-12-03 Instrument and Radio Light Control Box .9
39-12-04 Cigar Lighter .10
39-20-00 Equipment Rack .10

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CHAPTER 39

ELECTRICAL PANELS AND COMPONENTS

LIST OF EFFECTIVE PAGES

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39-00-00 -GENERAL The panel illustration depicted in Figure 39-1 shows
is divided into three basic group- phantom lines for some installations. Model year Im-
The instrument panel
provements, technical improvements or various
ings: avionics installations dictate which instrument will be
(1) Flight Instruments installed in a given location.
(2) Avionics/Radio Panel See Section 91 for Electrical System Hardware Charts
(3) Engine Instruments and Circuit Breaker Panel. and Schematics.
The flight instrument panel is shock mounted. The
radio/avionics panel generally, has individual racks for 39-1Q´•00 INSTRUMENT AND CONTROL
the components and are of the quick removal type. PANELS
The engine instruments and circuit breaker panel are
located in a quick removal panel which is slanted 39-10-01 -FUGHT INSTRUMENTS
toward the pilot.
1. Removal.
The circuit breaker/switches for the standard and/or
A. Remove screws attaching glareshield and
optional accessories and equipment are located at the
bottom of the Right instrument panel on either side of cover plate; carefully lift glareshield to expose discon-
nects for glareshield lights. Disconnect wires and lift
the pilots control column,
The cluster gauge containing fuel quantity and engine glareshield off.
B. Disconnect plumbing and/or electrical connec-
operating gauges is located at the top of the Right in- tions from Right instruments to be removed.
strument panel,
C. Disconnect and remove any post lights.
The annunciator is located at the top of the avionics
D. Remove mounting screws securing instrument
panel.]The avionics panel has two configurations:
fo panel.
Serial Numbers 25-0001 thru 25-0246 has a tubular
E. Remove instrument by sliding it aft from panel.
structure configuration that will not accept the radar in-
2´• I"stallation.
stallation; Serial Number 25-0247 and ON aircraft have
A. Place instrument into proper location on panel.
a relocated steel tubular structure that will allow the
B. Insert and secure mounting screws tq hold in-
radar indicator to be installed

S/N 25-0001 TNRU 25-02(6

´•I

ENGINE INST
PANEL

~41 10 1~]
FLIGHT INSTRUMENT---’
pnul~s
O oooo

PANEL
~I
o o o o oao
ooooo

S~H’dCK MCUNfED PANEL)

ooooo

FFFAB Ee3Ff~EB a oooo

S/N 25-0247~THRU 25-1999

CIRCUIT BKR
PANEL

TYPICAL INSTRUMENT AND CONTROL PANELS FIGURE 39 1

39-00-00
 MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
C. Connect post lights.
D. Connect all plumbing and/or electrical connec-
tions to instrument; perform pitot-static leak check.
E. Position glareshield so electrical connections
can be made and secured.
F. Secure glareshield and cover plate with
C
screws.

39-10-02 -AVIONICS EQUIPMENT

I rB
Each avionics package installed is basically a cus-
tomized package to meet the requirements of the cus-
tomer. Wiring harness,
any associated plumbing or I Flooli
mechanical mechanisms required for a particular
avionics installation are well secured to prevent any in-
terference with other components. Removal of these
avionics components will require evaluation of each in- CIRCUIT
stallation to determine proper procedure or sequence
to follow. O
1. Removal. PANEL Li

Most individual avionics components are mounted in o o

slide out chassis racks. Loosen screw on the face of

component and slide unit straight aft to remove.
Some components are not mounted in slide out chas- E
sis. Removal of these units will require same sequence
as removal of flight instruments in Section 39-10-01.

CAUTION
Radio ENGINE AND CIRCUIT BREAKER PANEL
panel must be stacked from the bottom to
the top. FIGURE 39 2

H. Remove thin lexan glass insulation strip if re-

2. Installation. Install repaired or new unit in reverse
quired when removing components.
sequence of removal. I. Remove instrument by removing any post lights
39-10-03 ENGINE INSTRUMENTS AND and mounting screws which secure irlstrument to panel
CIRCUIT BREAKERS and pull forward. Remove circuit breakers by unscrew-

The engine instruments/circuit breaker panel is an as- i"g "Ut from stem on each circuit breaker and push
circuit breaker through panel.
sembly that can be pulled out as a unit for removal of
2. Installation.
any instrument or circuit breaker.
1. Removal. A. Installation of new instrument or circuit breaker
A. Remove glareshield refer to Section 39-10-01. i"to panel is accomplished in reverse sequence of
B. Remove two flat head screws on outside of ’emoval.
B. Insert lexan insulator sheet in proper location
airplane (B) (Fig. 39-2). These are located forward of
cabin door hinge and above cabin air inlet scoop ap- to prevent any short circuits.

proximately 4 inches below windshield. 39-11-00 FLIGHT INSTRUMENT PANEL

C. Remove two screws from face of panel at
upper left corner (C) (Figure 39-2). The Right instrument panel is a shock mounted panel
D. Remove two screws (D) from underneath, near containing various Right instruments for a particular in-
the edge of panel face. stallation group. These instruments vary slightly
E. Remove NAS21919DG clamp (E) from steel depending upon avionics package installed. The panel
structure cross brace, underneath panel forward sec- co"tains a row of circuit breaker/switches, along with
tion, (Figure 39-2).
see the master switch, which control most of the systems
F. The
panel should now be free to slide aft ap- of the airplane.
proximately 4-5 inches. This will allow access to plumb- Access for maintenance of s~Yitches or related wiring is
ing and electrical connections. obtained by removing two attachment screws and
G. Remove plumbing or electrical connections pushing switch through panel. There is a common bus
from instrument or component that will be removed. bar on some switches that will require loosening or
removal for switch replacement.
NOTE
In some instances instruments, other than the one CAUTION
to be removed, must be temporarily removed or, at Care should be exercised when replacing wiring or
least, some wiring or plumbing disconnected to switches to ensure proper alignment of terminal
gain access to the desired unit. connections to prevent shorting between switches.
39-1 0-02
 MZOK MOONN AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CLUSTER GAUGE To remove entire cluster gauge, the wiring harness can
39-11-91
be disconnected at connector adjacent to cluster
The cluster gauge is located at the top of the Right gauge unit. The nuts on terminal
studs need to be
panel. Access is obtained by removing glareshield per removed so wire terminals can be pulled from studs to
section 39-10-01. Cluster gauges have the capability of modules from cluster gauge chassis. Remove
individual module replacement. The entire cluster and replace defective module.
gauge willrequireremoval from panel to allow room to
pull modules out.
LIGHT BULB ACCESS

m YN *r(
s~o sM, SMD

VIEW-LOOKING AT BACK SIDE

OF PILOT’S PANEL
MODULE TERMINAL SIU~S

CONFIGURAT1ON OF CLUSTER GAUGE WILL

VARY BETWEEN MODEL YEAR AIRCRAFT.

tar Nn pnlP1Cw nm Nd-Pwss

’F
OUlf)lP CHT k~j
(MP)
LOOSEN SCREW OF INDMDUAL GAUGE AND PULL GAUGE
OUT.
REPLACE GAUGE INTO CLUSTER. SECURE SCREW.
FIGURE 39 3
CLUSTER GAUGE OIIEW LOOKING AF~

TROUBLE SHOOTING GUIDE FOR CLUSTERS

PRESSURE INSTRUMENTS

CHECK FOR THESE

GAUGE CONDITION
POSSIBILITIES

full scale with WTre between sender and gauge

Gauge reads
disconnected or open.
engine shut down.
Faulty sender.
Faulty gauge.

Wire between sender and gauge

Gauge reads zero when engine
is running, grounded.
Faulty sender.
Faulty gauge.

39-11-01
MOONEY AIRCRAI=T CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
TROUBLE SHOOTING GUIDE FOR CLUSTERS (con’t.)

TEMPERATURE INSTRUMENTS

GAUGE CONDITION CHECK FOR MESE

POSSIBILITIES

Wire between sender and gauge

Gauge reads full scale with
engine cool or cold. grounded.
Defective gauge.
Defective sender.

reads when Wire between sender and gauge is

Gauge zero

engine is hot. open or disconnected.

Defective gauge.
Defective sender.

FUEL SYSTEM

GAUGE CONDITION CHECK FOR MESE

POSSIBI1ITIES

Gauge indicates tank empty. Grounded wire hehveen sender and

gauge.
Defective sender.
Inoperative gauge.

Gauge indicates past full Open sender lead.

when tank is less than full. Open sender (open resistance
element).
Sender not properly grounded to
airframe.
Gauge off calibration.
Note: Some dusters are equipped
with fuel gauges that have tn’m pots
and may need re-calibration.

On dual sender systems, the

Gauge indicates 1/2 when
tank is full. isolated sender may be grounded.
The lead between the isolated
sender and the grounded sender is
grounded.
Either sender defective.
Gauge out of calibration.

3. Tum wheel shaped knob counterclockwise to

39-1192 LANDING GEAR SWITCH
remove from stem.
The landing gear switch is a two position switch
4. Remove nut and washer from face of switch and
located at the top n’ght side of the flight instrument push switch through panel.
panel. The wheel shaped knob must be pulled aft pn~or
toraising or lowering the switch to activate the landing 39-11-03 LANDING GEAR SAFEN OVERRIDE
gearactuator. SWITCH

i. The glareshieldwill require removal to gain The landing gear safety ovenide switch is located
access to switch for maintenance action (refer to adjacent to landing gear switch. Proper operation of
Section 39-10-01). landing gear safety system will not allow gearto retract
below 65 +7/-4 KIAS.
2. Remove wire connections from back of landing
gear switch.
39-11-02
 M20K MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
LOW FUEL WARNING CIRCUIT CALIBRATION.
Refer to Section 24-33-00 paragraph 4.
U)G GEAR
OVERWDE 39-12-02 EMERGENCY LOCATOR
KNURLED TRANSMITTER (ELT) SWITCH
NUT FOR SWITCH
The remote ELT switch is located at the top of the
NG~ avionics panel. The ELT is located in tailcone and is
SWITCH (SOUE OYERWDE
SWTTCHES accessible by removing radio access panel on left side
ARE LOCATED of aircraft fuselage. The ELT antenna is located on top
BESIDE SHE of tailcone undemeath fiberglass dowal fin. The unit
aD LDC GEAR has a three position switch "ON", "OFF" and "ARM".
tr! swrrc~1) The corred position of this switch is "ARM". The
remote switch is connected in parallel to ELT circuit
U)G GEAR and will operate correctly either in "ARM" mode or
SELECTOR "ON" mode. Normal operation is in "ARM" position.
SWTTCH Place the remote switch in "ON" position and tune
communication radio to 121.5 Mhz to verify that a
warbling tone is heard. Place remote switch back to
"ARM" position for normal operation.
VINI-LQOKING AT BACK SIDE OF PILOTS PAE~R SUX39-5
CAUTION
LANDING GEAR SWITCH LANDING GEAR Testing of ELT should be conducted only
SAFETY OVERRIDE SWITCH during first five (5) minutes after any hour and
no longer than three (3) audible sweeps.
FIGURE 394
1. If tone is not heard replacement of ELT
warbling
CAUTION battery the unit may be necessary. Follow ELT
or
Activation of gear safety override switch while manufactures instructions for battery replacement.
aircraft is on the ground may cause landing 2. If ELT unit is found to be operating properly and
gear to retract
system still will not work correctly through the remote
cluster gauge will
ELT switch, repair or replacement of switch or win’ng
1. The landing gear switch or
Will be required.
require removal to gain access for the removal of
override switch. A. To gain access to remote switch and wiring,
removal of glareshield will be required (refer to section
2. Disconnect wire connectors, approximately 6
3910-01).
inches from switch, by cutting with wire cutters or
opening knife disconnects. B. Remove switch retaining nut and washer and

3. Loosen nut on stem and hold nut located inside

push switch through face of panel. Disconnect wires,
’emove and replace defective switch.
mounting bracket The red lensmay need to be removed
to fully remove switch from panel and bracket C. Reconned wires and test switch for proper
operation.
4. The light bulb (GE 330, 12 vo~t); GE 327, 28 volt)
can be replaced after glareshield is removed by D. Reinstali glareshield.
bending a nail or similar rod (approximately 3/32"
NOTE
diameter) and pushing red lens off to front of panel.
Use a small vacuum tube puller or soft nosed Other switches located in ELT placard area of
instrument to pull bulb from socket. avionics panel can be removed and replaced in
similar manner.
39-12-00 -AVIONICSIRADIO PANEL
The avionics/radio panel contains equipment installed 39-12-03 INSTRUMENT AND RADIO LIGHT
and other CONTROL BOX
per sales order by Mooney Aircraft
equipment installed by other sources as the owner The control box for instrument, radio and glareshield
desires. The maintenance information contained in this
lights consists of two van’able meostat switches, two
Service and Maintenance Manual descn’bes the transistors, two fuses and miscellaneous wiring
Mooney factory installation only. contained in a metal box assembly. The light control
The avionics/radio components are removed and box for S/N 250001 thru 25-0246 is located at the top
installed according to Section 39-10-02, 1 and 2. of radio panel. The light control box for SIN 25-0247
and ON is located at the bottom of radio panel. The
39-1291 -ANNUNCIATOR PANEL transistors installed in M20K aircraft, S/N 25-0001 thru
The annunciator panel is located at the top of 25-0279, PM 2N2016, are no longer being
center-most avionics/radio panel and is not mounted manufactured. The replacement transistors are
included spares modification kit, P/N
with a slide in type chassis. Remove this component by In a

removing two screws holding cover plate in position. 919003´•907", which includes a transistor, resistor, and
Remove glareshield and disconnect electrical harness instruction sheet describing modification procedures.
The kit will modify one circuit only, two kits are
from back side of unit. Remove screws holding unit in
place on panel and remove from back side of panel, required for both circuits.
3912-00
 MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
NOTE
ORS
RHEOSTATS A retrofit kit is available to use the latest light
control assembly in older 12 volt aircraft
(940013511 Kit).

Check appropriate schematics for proper wiring.

39-12-04 -CIGAR LIGHTER

I The cigar lighter is lomted a~the bottom of radio panel

immediately to the right of cc-pilots control column
shaft. It is a standard cigar lighter similar to automotive
type.

39-2090 -ELECTRICAUELECTRON IC
EQUIPMENT RACK

The electrical equipment rack for M20K aircraft is

VIMr- LOOKING INTO CONTROL BOX (UNDER CAP)
located in tailcone just aft of baggage compartment
COMR
bulkhead. Access is gained through the large access
door in tailcone, aft of the left wing trailing edge. The
INSTRUMENT AND RADIO LIGHT CONTROL BOX
FIGURE 39 -5 battery and battery box, auxiliary power plug
receptacle (if installed), ELT
and the van’ous avionics
S/N 25-0280 thru 25-0999 (12 Volt) have a different black boxes are mounted on electrical equipment rack.
Ilght control assembly using a different transistor and (See Figure 39-6) (12 volt A/C only). 24 Volt AIC have
circuitry. (See Figure 395). the ELT mounted on an accessory rack further aft in
tailcone.
(ILLUSTRATION REPRESENTS 12 VOLT CONFIGURATION)

;It

itt;

t~C

VA R I O O S~A V t O N r k-~
EQUIPMENT

ELECTRONIC
AUXILIARY
C" EQUIPMENT RACK
POWER PLUG
v IE w- L O o K I N G iL
THOUGH ’RADIQ ACCESS PANEL

ELECTRICAL/ELECTRONICS EQUIPMENT RACK FIGURE 39 6

39-12-04
10
 OLDWILLWAYNE

CHAPTER

STANDARD
PRACTICES-
STRU CTU RES
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 51

STRUCTURES

TABLE OF CONTENTS

CHAmER SUBJECT PAGE

SECTION
SUBJECT

51-00-00 General .5
51-1 0-00 Structural Repair- General .5
51-10-01 Fastener Replacement ~5
51-11-00 Reserved .7
51-12-00 Fuselage Repair .7
51-12-01 Tubular StructureRepair .7
51-12-02 Tancone Repairs .10
51-12-03 Landing Gear Retraction System Repair .10
51-12-04 Flight Control System Repair .10
51-13-00 Wing Repair .10
51-13-01 Stn’ngerRepair .10
51-13-02 Main Spar Repair .10
51-13-03 Stub Spar Repair .11
51-13-04 Rear Spar Repair .13
51-13-05 Rib Repair .13
51-13-06 Wing Tip Repair .13
51-13-07 Wing Skin PanelRepai; .13
51-14-00 Horizontal Stabilizer Vertical Fin Repair .15
51-14-01 Leading Edge Skin Repair .15
51-1 4-02 Main Spar Repair Outboard of STA. 9.00 .15
51-14-03 Rib Repair .17
51-14-04 Remating Horizontal Stabilizer to stinger .17
51-15-00 Fiberglass Laminates, Repair Procedures .17
51-15-01 Cracks, In Surface Areas .18
51-15-02 Non-Structural Repair .18
51-15-03 Common Structural Laminate Repair (Metal Insert) .19
51-15-04 Common Structural Laminate Repair ~20
51-15-05 Fiberglass Delamination Repair .21
51-16-00 Miscellaneous .21

51/CONTENTS
3/4BLANK
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CHAPTER 51

STRUCTURES

LIST OF EFFECTIVE PAGES

CHAPTER PAGE DATE

SECTION
SUBJECT

1/2BLANK.........´• 997
51-Effedivity
51-Contents ......´•´•3/4BLANK 9-97

51-00-00 ......´•´•´•5´•´•´•´•´•´•´•´•´• 997

51-10-01 ...´•6´•´•´•´•-´•´•´•´•´•´•´• 897

51-11-00 .....´•´•´•´•7´•´•´•´•´•´•´•´•´• 997

51-12-01.. ......´•´•´•8´•´•´•-´•´•´•´•´• 897

51-12-01.. .....´•´•´•´•9´•´•´•´•´•´•´•´•´• 9’97

51-12-02.. .....´•´•´•10´•´•-´•´•´•´•´•´• 997

51-13-03 ......´•11 997

51-13-03.. ......´•´•´•~2´•´•´•´•´•´•´•´• 997

51-13-04 ....´•´•´•13´•´•´•´•´•´•´•´•´•´• 9-97

51-13-07 .......´•´•14´•´•´•´•´•´•´•´• 9-97

51-14-00 ......´•´•´•15´•´•´•´•´•´•´•´• 9-97

51-14-02.. ....´•´•´•16´•´•´•´•´•´•´•´•´•´• 997

51-14-03 ....´•17´•´•´•´•´•´•´•´•-´•´• 9-97

51-15-01.. .......´•´•18´•´•´•´•´•´•´•´• 997

51-15-03.. .......´•19´•´•´•´•´•´•´•´•´• 9-97

51-1 5-04 ....´•´•´•20-´•´•´•´•´•´•´•´•´• 897

51-15-05 ......´•´•´•21 9-97

51-16-00 22 997

51/EFFECTIVITY
1/2BLANK
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
51-00-00 -GENERAL wraps around the leading edge ribs and is riveted to
the rear spar on both sides.
The Mooney M20K is an all metal, low wing airplane. The rudder is constructed of formed aluminum skins
The fuselage cabin area is constructed of a welded fastened to a spar e~rusion at the leading edge and
4130 chrome-molybdenum steel tubular structure. The riveted together at the trailing edge.
steel tubular structure is covered with non-structural
aluminum skins fastened to the tubular structure by A one piece composite belly skin covers the underside
of the aircraft from the exhaust cavity aft to the
rivets, bolts and screws.
tailcone.
The tailcone is of semi-monocoque type construdion
The front seats are installed on rails which are
and is fastened to the tubular structure with structural
attached to the floort~oard and structure beneath the
bolts.
floorboard.
The wing is a tapered, laminar flow, one piece wing. It
The M20K has a split type rear seat, using seat
is constructed with a one piece, full length main spar.
cushions in molded wells over the wing spars and
The spar is constructed from tapered capStn’ps C1075
individually reclining rear seat backs.
aluminum~ bolted Oluck bolts) to webs (2024
aluminum). Aluminum n’bs connect the main spar to the 51-10-00 STRUCTURAL REPAIR GENERAL
ah stub spar and the rear spar. E>druded stringers run
This section outlines structural repair procedures for
the full length of the wing, spaced chordwise for
the M20K airplane. It is intended to supplement FAA
strength and skin reinforcement. The skins are stretch Advisory AC 43.13-1() by showing repair methods
formed, wrap around, 2024-T3 aluminum ranging in
thickness from .025 at the tip to .050 at the fuel tanks.
Specific to Mooney airplanes.
All structural repair must be: in compliance with AC
The completed wing assembly is mated to the fuselage unless specific Mooney factory repairs are
43.13-1(
tubular structure during final assembly at the Mooney recommended, or with the specific approval of a
facility. Removal of the wing from the fuselage Federal Aviation Administration representative which is
structure is essential for most over land type the final authority in all repairs. This manual is for
transportation, general guidance and has no authorized approval
The empennage is of similar construction to the wing. status.The PRODUCT SUPPORT DEPARTMENT,
A main spar spans the length of the stabilizer. Ribs Mooney Aircraft Corporation, Kenville, Texas, should
connect the main spar to the stub and rear spar. A be consulted for special repair procedures when repair
stretch formed skin wraps around the leading edge n’bs of damaged str~jdure is not covered by published
and attaches to the rear spar on top and bottom, instructions.
The elevators are constructed of formed aluminum 51-10-01 -FASTENER REPLACEMENT
skins fastened to a spar e>drusion at the leading edge
and riveted together at the trailing edge. i. HUCKBOLT INSTALLATION. The Huck Lockbolt
The vertical stabil~er Is constructed around a is an interference fit fastener used in a rigid joint
fabn’cated main spar assembly with n’bs connecting the structure. A loose or slip fit Huckboit is unacceptable.
main and rear spar. A stretch formed, aluminum skin The recommended limits for Huckbolt holes are:

Huck Fastener Pre-Drill Size Drill Size Hole Limits

2LPH-T5 No.26 (.1471N~ No. 20 (.161 IN.) .161 to .1635 IN.

ALPPH-TG No. 18 (.1695 IN.) No. 13 (.185 IN.) .185 to .187 IN.
R3001-T6 No. 18 (.1695 IN.) No. 13 (.185 IN.) .185 to .187 IN.

2L426H-T5 No.26 (.1471N~ No. 20 (.161 IN.) .161 to .1635 IN.

R3007-T6 3/16 187 IN.) No. 7 201 IN.) 2005 to 2025 IN

When the Huckbolt is enlarged beyond the above limits recommendations when the preceding instructions are

but is straight and round, the hole may be considered inadequate to accomplish the repair.
acceptable, provided that the Huckbolt cannot be T, compensate for maten’al thickness tolerances,
pressed into the hole, with normal hand pressure, to a Huckbolt length may be increased by one dash number
depth more than 50 percent of the heaviest maten‘al f,, the prescribed length. V\lhen a Huckbolt pin of the
being secured. Check enlarged hole size at both ends. proper length is not available, use a pin of the next
Select Huckbolts to M the oversize holes.
longer length. To adjust the gn’p length, install a
Oversize HuckboB holes may be repaired by replacing cadmium-plated steel washer .065 inch thick (or a
2LPH-T5 Huckbolts with ALPPH-TG Huckbolts or with combination of not more than two washers .065~inch
NAS 623-2 screws and NAS 1021 No. 8 Hex-lock nuts and .032 inch thick) under the Huckbolt collar. The
(or equivalent), provided the pitch distance is greater combined thickness of any two washers shall not
than .56 inches and the edge distance is greater than exceed .098 inch. Huckbolts or conical Keystone Lock
.33 inches. Huckbolts ALPPH-TG and R3001-T6 may blind rivet heads may be cocked no more than .004
be replaced with R3007-T6 Huckbolts as necessary, inch. Not more than 20 percent of the fasteners in any
Consult the Product Support Department, Mooney pattern, nor more than three fasteners in succession,
Aircraft, Corporation, Kermille, Texas, for factory may be cocked.

51-00-00
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
NOTE
Where ir the fo substitution is
HUCKBOLT SUBSTITUTE
P/N P/N OIENDOR) DESCRIPTION

NAS 1465 or HL20-5 Pin (Hi-Shear) Pin-Protruding

R3001-T5 HL86-5 Collar Tension 160 KSI Ftu

NAS 1466 or HL20-6 Pin (Hi-Shear) Pin-Protruding

R3001-T6 HL86-6 Collar Tension 160 KSI Ftu

NAS 1475 or HL19-5 Pin (Hi-Shear) Pin-100 D.

R3014tT5 HL94-5 Collar Shear- 95 KSI Fsu

NAS 1476 or HL19-6 Pin (Hi-Shear) Pin-100 D.

R3014-T6 HL9d5 Collar Shear- 95 KSI Fsu

PART NUMBER CODE remachine the countersink. A‘fter installation, mill the
HL20 5 8 excess head height flush with the surface.

j+IGn’p in 1/161hs" (8M6 .500) MAX

(4) Dimpled Joint. If the edge distance Is a
minimum of two times the diameter ofthe original rivet,
Nominal Dia. in 1/32nds" (5/32 .156) it will be permissible to drill for and install the ne~xt
Pin Part Number standard size larger diameter rivet of the same type
2. RIVET REMOVAL AND REPI,L\CEMENT. and maten’al as the on’ginal rivet. Do not redimple. After
installation, mill the excess head height flush with the
A. REPLACEMENT-STANDARD SIZE RIVETS, surface. This method is subject to the same limitations
HOLE OVERSIZE. This repair applies only to original ,s paragraph 2, A (3).
aluminum alloy, steel, or monel rivets of 1/16, 3/32,
B. REPLACEMENT-STANDARD SIZE RIVETS,
1/8, and 5/32 inch diameters. Such n’vets may be
HOLE AND COUNTERSINK OR DIMPLE OVERSIZE.
replaced as noted and limited below and in the General This repair applies only to original countersunk head
Limitations, when the hole only is oversize.
aluminum alloy rivets of 1/16, 3/32, 1/8, and 5/32 inch
(1) Protruding Head Joint. If the edge distance is diameters. Such n’vets may be replaced las noted and
a minimum of two times the diameter of the on~ginal limited below) when the hole and countersink or dimple
rivet, it will be permissible to drill for and install the ne~d is oversize.
standard size larger diameter rivet of the same type
and maten’al as the original n’vet. (1) Machine Countersink Joint. If the edge
distance is a minimum of two times the diameter of the
(2) Machine Countersink Joint, Method I. If the next standard size larger diameter rivet and the
edge distance is a minimum of two times the diameter countersink depth is not beyond the thickness of the
of the next standard size larger diameter rivet and the countersunk sheet, it will be permissible to rework
sheet thicknesses involved are within the limits according to paragraph 2, A (3).
specified for machine countersinking for the ne~d (2) Dimpled Joint. If edge distance is a minimum
standard size larger diameter rivet, it will be
of two times the diameter of the ne~d standard size
permissible to drill and countersink for and install the diameter rivet and all the parts are dimpled, it will be
next size rivet of the same type and maten’al as the
on’glnal rivet. The foilowing~gre limits for machine permissible to rework the smaller dimples to a size to
match the overs’ne dimple and install the ne~d standard
countersinking: size larger diameter rivet of the same type and material
RIVET SIZE MIN. GAUGE as the original rivet Dimples in 75S-T6 must be hot
formed when reworked.
3/32 .025
.032
(3) Combined Countersink and Dimpled Joint If
118
the edge distance is a minimum of two times the
5/32 .040
diameter of the next standard s~e larger diameter
(3) Machine Countersink Joint, Method II. If the rivet, it will be permissible to reworkthe smaller
edge distance is a minimum of two times the diameter countersink or dimple to a size to match the oversize
of the on’ginal rivet, it will be permissible to drill for and dimple or countersink and install the ne>d standard size
install the next standard size larger diameter n~vet of larger rivet according to paragraph 2, A (4). Dimples in
the same type and material as the original n’vet. Do not 75S-T6 must be hot formed when reworked.

51-10-01
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
C. RIVET HEAD TOLERANCE. (1) An enlarged hole is defined as having an
internal diametn’c dimension in any direction which
(1) A rivet head will be considered open if.001 exceeds the sum of the dn’ll diameter normally used
feeler gauge can be inserted between the head of the plus ten percent of the diameter of the rivet shank.
flush or protruding head n’vet and the top skin. The top
of a flush head rivet must not be below the skin in
(2) The following table specifies the maximum
which it is installed by a dimension of more than .004.
acceptable diametric dimensions for the various rivet
s~nes that occur in multiple layer assemblies which are
D. RIVET HOLE TOLERANCE. "drilled on assembly".

MAX. ACCEPTABLE DIAMETRIC

NOMINAL
DRILL SIZE DIMENSION
RIVET SIZE

#40 (.098 dia.) 108 in.

AN470AD3 or AN426AD3
#30 (.1285 dia.) 141 in.
AN470AD4 or AN426AD4

Refer to AC 43.13-1( for tubular frame repair

(3) When a hole becomes enlarged beyond the
acceptble diametric limit and the prescn’bed rivet procedures. Warped or bent tube members can often
cannot be used, the ne>d larger diameter rivet may be be straightened; however, all surrounding welds should
used if (9) four-diameter (4D) rivet spacing is be dye checked for cracks after tube straightening.
maintained and if two-diameter (2D) edge distance Use proper maten‘al when making weld repairs.
is maintained. Welding rod, meeting the requirement of specification
3. BLIND RIVET INSTALLATION. Ordinan’ly, where MIL-R-5632, class 2, is recommended for o~acetylene
welding. Electrodes meeting the requirement of
rivet bucking is impossible, cherrylock (CR-2248 and
CR-2249) rivets may be substituted for AD rivets to specification MIl-F-5632d, class 2, MIL-E-23765/1C,
repair skins and structural members. However, consult Type MIL-70S-2, or AWS A5.18-69, class E70S-2
the Product support Department or a representative of (Linde 65, Linde CMS-32, or Page AS-35) are
the Federal Aviation Administration before using recommended for unheat treated parts inert-gas
blind-type or hollow nvets in primary structure. shielded-are welding ~-leliarc). Use AISI 4130 condition
N steel for replacement and repair of tubes, and for
Check e>a’sting rivet hole size before installing blind
making repair sleeves. Replacing a member or
rivets. When hole is marginal, use the ne~d larger size
subassembly is often advantageous and more feasible
rivet to assure firm attachment. than repair. AIl detail tubes or assemblies needed for
4. "AN’~ BOLT, NUT AND WASHER replacement can be purchased from SERVICE PARTS
INSTALLATION. To compensate for material thickness DEPARTMENT, Mooney Aircraft Corporation, Louis
tolerances, the length of AN bolts may be increased or Schreiner Field, Kemn’lle, Texas 78028, U.SA.
decreased by one dash number from prescribed
1´• WELDED PATCH REPAIR OF LOCAL DAMAGE.
length. AN960 regular washers and AN960L thin Use a welded patch to repair dents, small holes, and
washers may be used interchangeably for proper bolt
cracks no longer than the outside diameter of the tube
and nut installation.
and coven’ng a maximum of 1/4 of the tube
One regular washer or one thin washer may be added to circumference. Drill out the c~ack, smooth the hole
any bolt installation. Washers may be used under
the edges, weki the hole or dent, and file the repaired
bolthead and/or under the nut. AN365 and AN363 nuts surface smooth. Form a patch that will cover twice the
may be used interchangeably. The AN363 nut
is diameter of the tube around the edge of the damaged
acceptable for higher operating temperature installations. area and twice the circumferential area of damage as
shown in (figure 51-1). Weld patch in place.
5. HI-SMEAR RIVET INSTALLATION. When a
hi-shear rivet pin of the prescribed length not 2 INNER SLEEVE SPLICING. Use an inner sleeve
available, the next longer length pin may be used with spliceto partially replace a tube without increasing the
cadmium-plated steel washers to adjust the pin gn’p outside diameter (see Figure 51-2).
length. The combined washer thickness shall not A. Make a ~(kiegree cut to remove the damaged
exceed.096 inch.
portion of the tube; then, remove the bum from the
6. MS20470-AD4 MS20426-AD4 n’vets may
or remaining end.
replace spotwelds, (1) per spot unless a8emate B. Cut a replacement tube of the same material
fasteners are specified on engineering drawing. Head
side and double flush requirements determined by (AISI 4130 steel, condition N), same diameter and the
same wail thickness as the original tube.
form, fit function of assembly.
C. Select a tube with an outer diameter equal to
5111-00 -RESERVED and with
the inner diameter of the tube to be repaired
51-1290 FUSELAGE REPAIR the same wall thickness.

5112-01 TUBULAR STRUCTURE REPAIR D. Cut tube to a length five times the outer
diameter of the tube to be spliced.
Check tubular structure at each annual inspection for
corrosion and damage. Interior panels may require E. install inner sleeve in tube to be repaired so that
removal to gain access to areas which are difficult to its outer end is one and one-half of the original tube
diameter from the nearest end of the diagonal cut;
inspect,
51-11-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE

IF NOT GREATER THAN ’A’ (DIAM. OF TUBE)

1/4 OF TUBE
CIRCUM. (MAX.>

I
DAMAGE

WELDED PATCH -LOCAL DAMAGE REPAIR FIGURE 51-1

II A

;Ilr -I 300

I
~T---------- ~v -----1----

Al i C~
~-------------------1 _,,,

ORIGINAL SLEEVEREPAIR I_ ,_i i *~I C 1/2A

TUBE TUBE LRDSETTE WELD REPLACEMENT
INSIDE TUBE

~41 r LEAVE 1/8 IN. GIAP FOR WELDING

ROSETTE WELD
300

-r

.I ’----------1,’,--

SLEEVE
REPAIR
TUBE 1/2A 1/2A
INSIDE
5A

INNER SLEEVE SPLICING FIGURE 51-2

secure in position with a rosette weld on each side at G. Weld the inner sleeve to the tube stubs through
one-half the on’ginal tube diameter from the the ~/8 inch gap, forming an overlayed bead across the
inner-sleeve end. gap.
F. Install replacement tube over the inner sleeve H. Rosette weld the replacement tube to the inner
allowing a 1/8 inch gap for welding between the sleeve in two or more places.
original and replacement tubes. 3. SPLIT-SLEEVE SPLICING. Use the split-sleeve
splice to repair a damaged tube when the parts on

51-12-01
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE

WELD HERE FIRST

4 RI~SETTE WEU)S
r""~
A
IN. GAP
R3R WELDING

=1 300

1-1/2A I 1-1/2A

SPLIT-SLEEVE SPLICE FIGURE 51-3

each side of the damage cannot be separated to insert B. Form the split sleeve from sheet steel when
an inner sleeve (see Figure 51-3). outside diameter of the original tube is one inch or
A. Form the split sleeve from steel tube or sheet more.

steel when outside diameter of original tube is less

than one inch.

TUBE
TUBE

~25 IN, WEU) GAP

A~ IB
TUBE

g~ tC

I_ L9 I 2
3~U1(134-7
5 _1 TPISI[3W FITTING

SLER/E
TUBE
INSIDE

TENSION F~TING REPLACEMENT FIGURE 51-4

51-12-01
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
C. Form the split sleeve from the same material 2. TAILCONE STRUCTURAL SKIN REPAIR. Repair
(AISI
4130 steel, condition N) with at least the same minor tailcone skin damage as shown in AC 43.13-1(
gauge as the original tube. Figure 2.24. The rivet pattern for stressed skin repairs
D, Allow a 1/8 inch gap between sleeve halves for shall be the same as the rivet pattern in the skin joint
welding, immediately forward of the damaged area. Replace
E, Weld parallel edges of sleeve to original tube Seve’ely damaged structural skin panels. Install new
skin panels to exactly match the original skin installa-
through 1/8inch gaps,
tio".
F, Weld center of each sleeve half to original tube
3. NON-STRUCTURAL SKIN REPAIR. The skin
with two rosette welds spaced one original tube
diameter apart,
covering the M20K aircraft tubular fuselage structure is
considered nonstructural. Patches in nonstructural skin
4. TENSION FITTING REPLACEMENT (see Figure
are not restricted as to she or shape; however, ap-
51-4),
A, Cut A and B tubes loose from tension pearance and possible vibration damage should be
fitting considered. Either a Rush patch, a plate patch, or a
340034-7, -8 at welds.
8, Cut C tube at
plug patch may be used.
a 30 degree angle seven inches
from bottom of tension fitting. 51-12-03 LANDING GEAR 8 RETACTION
C, Cut a replacement C tube at a 30 degree angle SYSTEM REPAIR
and at an appropriate length to position the tension fit- Replace any damaged landing gear or retraction sys-
ting,Weld tension fitting in proper position, tem component with a new part. Repain’ng landing
D, Drill four 1/4 inch holes for rosette welds 1.9 gear or retraction system components is not recom-
inches from center of 30 degree cut, mended. After installing new components, check gear
E. Make an inner sleeve five inches long from and retraction system rigging as outlined in Section 32-
4130 steel tube, condition N, with outside diameter to 20-02. Before returning the aircraft to service, perform
match Inside diameter of tube C and with a .085 inch a ’etraction test and operational check of the landing
wall thickness, gear and retraction system per Section 32-30-01.
F, Insert the inner sleeve in C tube and weld in 51-12-04 FLIGHT CONTROL SYSTEM REPAIR
place gs shown (Figure 51-4).
Replace any damaged primary control system com-
5. REPAIRS FOR WELDED ASSEMBLIES General.
ponent with a new part. Repairing primary control sys-
This section does not apply to any control system
tem components is not recommended. Use only new
tubing or assemblies, engine mounts or heat treated hardware when installing new parts. After installation of
steel components (except as stated below),
new parts, check control system travel and rigging as
A. Small holes up to a #20 drill may be closed by
outlined in Chapter 27 Before retuming the aircraft to
welding with the inert gas shielded are method, service, flight test the aircraft for proper control system
B, Nicks and drill marks that are no longer than
rigging.
1/8" and do not exceed four percent of wall thickness
51-13-00 -WING REPAIR
In depth after cleanup may be smoothed out and
reprimed, Nicks, holes, and cracks that will clean up 51-13-01 -STRINGER REPAIR
with a #20 drill may be drilled and
repaired per item A. Stringer splicing may require drilling new holes and ad-
C. The repair of weld beads on heat-treated as- ding rivets between existing rivets to obtain the re
semblies may be accomplished without reheat treat- quired total number of rivets. Add extra rivets where
ment within the following limits. the distance between existing rivets is the greatest. The
(1) The repair bead will not exceed .375 in pitch and edge distance must conform to AC 43.13-1(
length or 1/3 of total length of weld, whichever is the requirements (see Figure 51-6).
iesser.
51-13-02 MAIN SPAR REPAIR
(2) Only one repair per weld bead is allowed.
6, REPAIR OF SPOT WELDS. Failed spot welds on The spar caps inboard of STA 103 are made of 7075-
aluminum may be repaired by installing an AD470-4 T6 high-strength aluminum. Replacement of the spar
rivet through the weld if the damaged area will clean cap is preferable to repair. However, if a spar cap
up with a #30 drill, repair is thought necessary, an exact description of the
7, DENTS. Small dents which do not exceed five damage showing location and extent should be sent to
percent of the diameter of the tube in depth and are no the PRODUCT SUPPORT DEPARTMENT, Mooney
longer than one-half the tube diameter are acceptable. Aircraft Corporation, to obtain factory recommenda-
tions prior to beginning the repair.
51-12-02 -TAILCONE REPAIRS
1. SPAR CAP REPLACEMENT. To replace a spar
1. LONGERON SPLICING. Use procedure outlined cap, remove the skin covering the area to be repaired.
in AC 43.13-1( for repairing and splicing tailcone Before removing a large area of wing skin, attach tem-
longerons, (Figure 51-5) shows acceptable methods porary jigs or holding fixtures to the wing to prevent
for splicing longerons. Consult AC 43.13-1( Figures wing warpage. When attaching a new spar cap, assure
2,28, 2,29 and 2.30 for fastener requirements. proper interference fit of the replaced huckbolts.
51-12´•02
10
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE

1~"
ooooooo ioooooool~ 617,
O O O

oooooIooooo

o o o

Ir´•-
000000 f000000

oo o o q o o o o

SWN5l-5

LONGERON SPLICING FIGURE 51-5

RIVET CODE FOR STRUCTURAL REPAIRS

During installation of the new spar cap, all holes
damaged by improper drilling or reaming should be
reamed to the hole size recommended for oversize
huckbolt installation. When installing oversize
dzs 4 MSE~0470AD4-xx
huckbolts, consult the Huck Fastener Standards
Manual for proper tolerances. Use proper length 4~ 5 MS~0470AD5-xx
huckbolts. If the bolt is too long, the collar will not
properly; if the bolt is too short, the shank will
swage
notcompletely fill the hole.
~7 4 MS~0426AD4-xx
Repair scratches on spar caps that are not deeper than
.003 inch by sanding with No. 400 abrasive paper. ~5 MS~0426AD5-xx
Remove no more than .005 inch of material. Inspect
the sanded area; use dye penetrant to be sure that the
scratch is completely ~BP CR516-xx
where the protective coating has been removed.
3. SPAR WEB REPAIR. Repair all damage to spar
2. SPAR CAP REPAIR. Spar caps outboard of STA webs in accordance with AC 43.13-( If there is
103 consist of sheet metal angles backed up with e~densive damage to a web that cannot be repaired as
aluminum e~dtusions from STA 103 to near STA 150. outlined in AC 43.13-( consult Mooney Aircraft
Replace or repair damaged e~husions. Do not allow Corporation, PRODUCTSUPPORT DEPARTMENT
splices in a repaired e>drusion to coincide with a giving exact location and extent of damage.
spar-web splice when avoidable. Splice sheet-metal
angles with an e>drusion of equal area, picking up 51-13-03 -SNB SPAR REPAIR
existing fasteners. Add e~dra fasteners to bring the (Stub spar splice at wing STA 34.5 +1-
minimum number of fasteners to six AD5 rivets per side 3.0) (See Figure 51-8).
in the vertical flange, and nine AD-4 (or s’oc AD-5) rivets existing rivets
1. Cut the stub spar halfway between
per side in the horizontal flange. (See Figure 51-7). as required by the damage incurred.

2. Smooth all rough or sharp edges, and prime area

to be spliced.

51-1 3-03
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
.750 .750
260~057. ~6)1057.
SPLICE NATaML
a40 a50 1(20 SERIESI 2024-74
Cl22 SERIES 2014-76
DMD(SWS OF WSTIHG STTZIHGERS

~5 PER smo

WC O

0 0000100QOOI .750

~057. ~5 (5 RR Spg

SPLICE
2014-76
1)82

000000
O000000
~d-" a; PER smo

SNi15Id

STRINGER REPAIR FIGURE 51-6

SPLICE ANGLE HATERIAL17075-T6

.875

rid
15
160
~f <4 nas. EACH SIDD

~WO
OiQO O ~688

ALPPH-TP <4 we EACH SmD

VIEV LLWNG LR

ca i a a o

VIRI LOOKING D[NN

SHNR1-7

SPAR CAP REPAIR FIGURE 51-7

51-13-03
12
MOONEY AIRCRAFT CORPORATTON M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE

887
PUTE

2100bC~
’FB

(rm,

I I
tao
FIAT ~mwe <oD1 ALP C 1JO. A
OONR ’K ST09

2raas UP (r~ SECT B--B

A--A
DETUL TT(ES,.Y
THCU Ha CWD -605
-JaJ FIIET PA~TWI ~0(0 W ~1JQ
COHL -K rrnC)

SIEP UP
x,ADS 5HRU SPAR
AH) --un
wo U(ECL

´•o,
-´•f~

(~sl AH clo~m rwEa

aM ax a ~PUCE Ysc~

it* i
57D-Aa
~P)
eJ~J
Pa a (~a) B/P FA61DER5 DCH 30E a SPUCE I ~03 CJJDLE

SY~td
RQ( UP 00) B/P FAS~DEJCS FKH SDE OF SPUQ QNIEI~UNE

STUB SPAR REPAIR FIGURE 51-8

3. Locate new outboard section and tn’m splice to fit support or locator pins to maintain correct wing tip
with maximum gap of.020 inch,
a position.
4. Fabricate -501 angles to pick up 30 existing fas- 2. Rivet new tip rib to main and rear spars.
tener holes (30 recommended, but 22 minimum), -503 3. Locate new skin, and drill rivet holes through skin
angles to pick up 15 existing fastener holes (12 mini- to match existing holes in ribs and stringers.
4. Rivet skin to db at STA 193.5.
mum), and -505 plate and -507 spacer. (See Figirre
51-8). Prime angles, plate, and spacer. Rivet parts 5. Roll skin back on lower wing surface to gain ac-
together using wet primer on all rivets, cess to stn’ngers for rivet bucking. Rivet skin to upper
stn’ngers.
51-13-04 REAR SPAR REPAIR 6. Rivet skin to tip rib starting at leading edge. Buck
rivets far back as possible.
as
The rearspar may be spliced between ribs in accord-
7. Install cherrylock (CR-2248) blind rivets in places
ance with AC: 43.13-1( (see Figure 51-9). inaccessable for rivet bucking. Add one extra counter-
51-13-05 RIB REPAIR sunk blind rivet between every other pair of cherrylock
rivets.
Replace ribs that areseverely damaged. Minor damage
51-13-07 WING SKIN PANEL REPAIR
may be repaired as shown (Figure 51-10).

51-13-06 WING TIP REPAIR Repair wing skin panels as prescribed in AC 43.13-1(
unless an entire skin panel is to be replaced. Install
new skin panels to exactly match the original skin
in-
To repair severe damage to the wing tip outboard of
stallation. Preformed skin panels may be obtained from
STA 193.5, it is advisable to replace the entire tip skin
and rib, the Mooney Service and Marketing Centers.
1. Locate the new tip rib in the exact original tip rib 1. Damaged Dimple Repair Around Inspection
position to prevent wing tip twisting. Use a temporary Holes. Repair damaged dimples around inspection
51-13-04
13
 SERVICE AND NTENANCE MANUAL AIRCRAFT CORPORATION
OLDWILLWAYNE

Ip´•D~u sm
5999

o o o o o o o o o o

o oo 9

4i
o oo o

ooo 909 o

9959

rrpurr vr~ 999

99 mcc-n 995 9 REIYP 599
RV~ ~m Hmr~rri
950 ama
9 99 99)

o D o o o o o o

I,o oo o

oooooooooo

7AO 4

On [r REPUCD
PIOr
9e9L)

REAR SPAR REPAIR FIGURE 51-9 RIB REPAIR FIGURE 51-10

1 I I 1

a e~ql
11%-i i IiC~3 I I r ~B

ll------´•-/I Llnm-IC

Sn51-ll

ACCESS COVER REPAIR FIGURE 51-11

51-13-07
14
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
rivet spacings with two-diameter edge distances in a
holes when (5) there are three or more cracked ad-
circular pattern around the cracked dimple.
jacent dimples, (b) the crack in one or more of the
C. Round the comers of the doubler, and scarf
dimples extends beyond the radius of the dimple into
the skin, and (0) when there are four or more cracked the sandwiched edges to about .010 inch by .250 inch.
D. Drill holes for six rivets (same size as those in
dimples around an inspection hole (see Figure 51-11).
To repair damaged dimples (0) cut a doubler from the the original rivet pattern), and drill and countersink 100

same material and gauge as the skin to be repaired, degree dimples in doubler.E. Prime area to be repaired
and install doubler with wet primer.
(b) drill and countersink 100-degree fastener holes in
the doubler to match dimpled fastener holes in skin.
4. Repair of Circumferentially Cracked Dimples. Cir-
and (c) install doubler around inspection hole. Use cumferentially cracked dimples (dimples with cracks
AN426-AD4 rivets when material is .040 inch thick or that appear as an annular mark around the dimple) can
be repaired by installing a conical washer.
greater. Drill holes using a No. 30 (.128 IN.) drill as
shown in the above illustration. Use AN426-AD3 rivets A. Drill through dimple using a drill large enough
when material is .032 inch thick or less. Drill holes
using aNo. 40 (.098 IN.) drill.
2. Repair of Cracks Wholly Within Dimple Radius. a FELrEMRS (sAuE sm As oRK;IHAL
Surface cracks on inside (bearing) face of a dimple F4STENER wmt CRACKED DIMPLE)
that do not extend through the material can be
repaired by sanding out thecrack. Cracks in dimples
which do not extend beyond the dimple radius can be
b
repaired by (a) stop drilling the crack with a No. 60 drill
and (b) by adding rivets, the same size as those in the
original pattern, to each side of the cracked dimple. d t) d
Maintain four-diameter (4D) spacing and two-
diameter(eD) edge distances. When original rivet pat-
tern has rivets on one o~ two sides of a dimple,
only d

only one or two rivets need be added (see Figure 51-

CRACKED
12). DMPLE As SKIN)--SCA~F EDGES TO
3. Repair of Cracks Extending Beyond Dimple APPROX 101 IN. DEEP AND
.u uc. mDE; RWND COfl~ERS
Radius. Cracks that extend through the face of the
dimple into the surrounding skin can be repaired as SL151-13
follows: (600 Figure 1-13).
A. Stop dr/ii crack with No. 60 bit. FIGURE 51-13
DIMPLE CRACKS
B. Cut a doubler from the same maten’al as the

to remove the damaged area.

B. Install doubler as shown in Figure 51-14. Wet

IYc~ prime prior to assembly.
I I C. Countersink dimple hole in skin allowing the
D(ISIING ´•cpa~3to)
i I
CRACKED countersink to extend into substructure.
DIMPLE
D. Install conical washer, use next oversize rivet
jI size. Wet prime washer and adjacent skin and doubler
surfaces pn’or to assembly.
ADD
I E. Drill remainder of the hole to allow installation
I I of next larger diameter rivet than the rivets in the
III( original pattern.
II Iiiv’ I 1 51-14-00 HORIZONTAL STABILIZER
VERTICAL FIN REPAIR

iiIAoD 51-14-01 LEADING EDGE SKIN REPAIR

~P" The horizontal stabilizer and vertical fin leading edge

ma
ii I interiors are inaccessable near the tailcone. fo repair
-I I damage in these areas, cut a standard (3.0 inches by
STRINGER
I i ~----MISTING ~P 6.5 access hole in the lower side of the stabi-
inches)
lizer leading edge and close the access hole by install-
SM51-12 I ing inspection cover P/N 913000-501.

DIMPLE CRACKS REPAIR FIGURE 51-12

51-14-00
SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

OLDWILLWAYNE

WET PRIMER 100" CONICAL WASHER

.070

.7s

1
yyE LDK~ AS
SKIN AlJcLE BDIKi SPUCED

DOUBLER

SUBSTRUCTURE
1
SCARF EDGES NEM OVERSIZE RIVET

SM51-14

OVERSIZE HOLE FIGURE 51-14

SPAR REPAIR (STA. 9.0 8 OUTED.)- FIGURE 51-15
51-14-02 MAIN SPAR REPAIR OUTBOARD OF
STA, 9.00
Pn’me splice angle before riveting it to spar. Pick up
Repair damage to the hon’zontal stabilizer main spar by five e~a’sting n’vet holes and drill six new holes between
straightening the damaged area and inspecting it existing rivet holes in the skin at each side of the
carefully for cracks. If cracks are formed, stop dn’ll or damaged area. Install 22 AD4 rivets through splice
remove cracked area,
angle and skin, and 22 AD4 rivets through splice angle
i. Repair damage between STA 9.00 and STA 34.0 and spar web. (See Figure 51-15).
on the spar upper flange, and between STA 9.00 and
2. Repair main spar cap damage between STA 34
STA 40.0 on the spar Ibwer flange with a splice angle
and STA´•48.5 by forming a splice angle from 3/4 inch
formed from.070 AISI 4130 steel, condition N. The
by 314 inch .050 2024-T3 sheet aluminum. Pick up five
splice angle flanges must be as wide as the on’ginal existing holes and dn’ll six new rivet holes between
spar flanges, The splice angle must be long enough to existing holes in the skin on each side of damaged
Install 11 AD4 n’vets through the skin and 11 n~vets
area. Install 11 AD4 rivets through angle and skin and
through the spar web on each side of the damaged 10 AD4 rivets through angle and web on each side of
area (see Figure 51-i15). the damaged area. (See Figure 51-15).

4
(4 MIN. PER SIDE>

4 .040
(3 MIN, PER SIDE) Lt~ .040

oo‘o oc::o ooo~l

o
o

o o

CR 2248 CHERRY LDCK

<4 MIN. PER SIDE>
.040 2024f-3 CLAD
SH5~-16

SPAR REPAIR (STA. 48.5 APPROX.)- FIGURE 51-16

51-14-02
16
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
of damaged area). Pick up three existing holes and drill
3. Repair main spar damage from STA 48.5
outboard by installing splice angles made from .040 three new holes between existing holes on each side
2024-73 maten’al on both side of web using 12 AD4 of damaged area. (See Figure 51-16).
rivets (6 through skin and 6 through web on each side

~4 (?O EACH SIDE OF~ CRACK)

(6 EACtl SIDE Or CRACK)
rp4

aaboooiooaaa
O O It\ O O
d I~ O

STOP-DRILL (OR REMOVE ,050

CRACKED SPAR WEB AREA) 2024-T3
SM51-17

SPAR REPAIR (OUTBD. of STA. 34.0) FIGURE 51-17

51-14-03 RIB REPAIR

4. Repair main spar web damage outboard of STA
34.0, top flange, and STA 48.5, lower flange by forming Th, repair of damaged stabilizer and fin ribs is not
a splice angle from .050 2024-73 aluminum. The splice feasible in most cases. Damaged ribs shoukl be
angle web flange should be cut to allow sufficient replaced with new parts.
and
coverage of the damaged area of existing web
51-14-04 -REMATING HORIZONTAL
long enough to install 6 AD4 rivets on the flange on
each side of the damaged area. Pick up 3 existing rivet
STABILIZER TO STINGER
holes on ffange of spar and dn’ll 3 new rivet holes When stabilizer repair necessitates removal from the
between existing holes. Drill 10 rivet holes through stinger, remating can be facilitated by using huckbolt
splice angle and web on each side of the damaged substitution information contained in Section 51-10-01.
web area. The damaged web should be stop drilled or When mating stabilizer to stinger use bent rivet swage
cracked area removed pn’or to splice angle installation. set#5 (see Figure 51-19).
Prime splice angle and deburr spar web and flange
51-15-00 -FIBERGLASS LAMINATES, REPAIR
before installing splice (see Figure 51-17).
PROCEDURES
5. Spar webs outboard of STA 48.5 cracked more
than 50% of the web height may be repaired (see Despite the fact that fiberglass laminates are designed
to withstand considerable abuse, occasional repairs
Figure 51-18). Form a splice plate from .050 202dT3
aluminum to fit the inside dimensions of the web and will be necessary. It is difficult to cover all the various
flange at the damaged area. Pick up 3 existing rivet repair techniques due to such limiting factow as
holes on top and bottom flange on each side of accessibility and the e~dent of damage. The following
outlines those steps which are used to make repairs of
damaged area and drill 2 new AD4 rivet holes between
these existing holes. Pick up all rivet holes on web the more common type damage to a fiberglass
under splice plate and drill new rivet holes on equal laminate.
spacing around the damaged area similar to that on
Figure 51-18 rivets on each side of damaged area.

51-14-03
17
 OLDWILLWAYNE
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

GUN
~ENRRAUOC
~4 (5 EAC~H SIDE) .050 2024T-3 CLAD HUCK SUMP
SWAGE SET

o
0

O
O O

O
O

o o
0

O
0 0

O
0

ol
O
I
mpl
I DRM HUCK
STUMP
~4´•
STEP2
INSTALL
HUCK COUAR
PSWAGE STEP 3

COUAR
oO O
O ol I 1 I BUCKING BAR
O
oooioooo
RNET GUN

~(5 EACH SIDE)

SPAR REPAIR FIGURE 51-18

SM51-18

a S~RAIGHT#5
h ~6
SWAGE SET
BENT #5
SWAGE SE~

SM51--19
1. Materials used for repairs shall be as specified I
and compatible with the basic resin´•used in the
REMATING HORIZONTAL STABILIZER TO STRINGER
fiberglass laminate.
Resin FIGURE 51-19
Aerospace Adhesive EA934 Part A
Hysol Division
The Dexter Corporation proper shaping of the backup plates used for clamping
the laminates together during the curing cycle.
8. The degree of laminate chamfer and size will
Catalyst Aerospace Adhesive EA934 Part B
Hysol Division vary based on accessibility, shape of part and the ex-
The Dexter Corporation tent of damage.
Alternates:
Resin
51-15-01 CRACKS, IN SURFACE AREAS
Epoxical #606 Patching Adhesive
Resin 1. Stop drill all cracks per standard aircraft proce-
United States Gypsum dure.
2. Remove any loose particles and frayed fiberglass
Catalyst Epoxical ~606 Patching Adhesive
strands from the cracked portion.
Hardner
3. Prepare surface for repair as shown in (Figure
United States Gypsum
OR 51-20, Figure 51-21, and Figure 51-22).
Resin Ren Epoxy CG 1304 4. Prior to continuing the repair, all surfaces in the

Ren Plastics Co. area of the repair must be cleaned of all contaminates

Lansing, Michigan by wiping the area with a clean cloth saturated with
Methyl-Ethyl Ketone.
Catalyst Ren Hardener CG 1304
Ren Plastics Co. CAUTION
Lansing, Michigan Methyl Ethyl Ketone (M.E.K.) is a flammable liquid
Fire retardation Antimony Trioxide for fire retardation, and should be used with proper ventilation and the
5% minimum; 10% maximum by Weight of Resin Con- prescribed safety equipment.
tent. Must be added to the base resin (cowling and air CAUTION
intake duct assemblies). Fiberglass components are attacked and
The manufacturer’s bulletins shall be followed for all deteriorated by the following products: Ketone,
mixing ratios and preparation prior to application. aliphatic esters, chlorinated hydrocarbons, and
2. General. slightly softened by aromatic hydrocarbons.
A. The configuration of repairs are shown for flat
51-15-02 NON-STRUCTURAL REPAIR
surface areas; for simplicity; however, the same techni-
(FIGURE 51-20)
ques can be used for contoured surfaces. Contoured
i. Apply masking tape over crack on finished sur-

repairs will require additional considerations and the face side.

51-15-01
18
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE

Y STOP D.LL
0.5

I
CRACK

I...´•
OLmJNE OF
CHAMFER AREA
(SEE SECTION
1.......´•--´•´•´•´•´•-\´•´•´•´•´•-´•´•´•´•´•-´•-´•1 51-13-00. B. 2)

CRACK 15---I-- CHAMFER EACH

SIDE OF CRACK
(SEE SECTION
51--13--00, B, 2)

FINISHED SURFACE THICKNESS .02 TO .04

ABCDE

C
O ,LAMINATE
I

FINISHED SURFACE MASKING TAPE

SM51-20

NON-STRUCTURAL REPAIR FIGURE ~1-20

2. Apply wet coat of catalyzed epoxy resin to cham- 3. Apply wet coat of epoxy resin to aluminum straps
fered surface. and apply one or more layers of resin saturated #181
3. Apply one layer of #181 fiberglass cloth saturated fiberglass cloth to equal the thickness of the original
laminate.
with epoxy resin.
catalyzed
fiberglass cloth, 4. Lay wax paper over repaired
both sides of the
4. Add additional plys of #181
saturated with epoxy resin to attain original laminate area prevents adhesion to the pres-
while still wet. This

thickness. sure clamp application (paragraph 5).

5. Place rigid aluminum plates on both sides of
5. Apply one additional ply of #181 cloth bridging
the total repaired area and bond in place. repair area and clamp into place with "C" clamps. Per-
mit laminated repair to cure.
51-15-03 COMMON STRUCTURAL 6. After the fiberglass repair has cured, remove the
LAMINATE REPAIR (METAL INSERT) clamps and install #3 AN426A rivets. Flush head to be
The number of rivets and
(FIGURE 51-21) on the finished surface side.

spacing will be determined by the size of the repair.

1. Cut away laminate per sketch, roughen repair of #181
7. Apply one additional overlapping layer
with 240 sandpaper, clean repair area with M.E.K.
fiberglass cloth on the non-finished surface and bond
area

apply a wet coat of catalyzed epoxy resin to surfaces. in place. Should the opposite side be a non-finished
Then IMMEDIATELY proceed with steps 2 thru 5.
surface, an additional layer of fiberglass should be ap--´•
2. chemically cleaned .025 T-3 aluminum
Install
with #40 holes approximately .35 on
plied to this side.
straps, perforated
center all directions.
51-15-03
19
SERVICE AND MAINTENANCE MANUAL OLDWILLWAYNE
M20K MOONEY AIRCRAFT CORPORATION

ilsl FIBERGLASS
CLOTH

.025 T-3 ALUM.

Li
.375
i/ i
i
zcr

LAMINATE

CRACK .03~
.025 T-3 ALUM.
275’
(SEE SECTK)N
51-15-00. a 2)

Ilsl FIBERGLASS
CL(T~

OVERLAP (1) LAYER FlBERGLASS

ALUM, PLATES

LAMINATE FLUSH RIVET CMP.)

LlNISHED SURFACE IL~
LlBET~GLASS BOND IN PLACE
SM51-21

COMMON STRUCT. LAMINATE REPAIR-METAL INSERT FIGURE 51-21

8. Upon completion of steps 1 thru 7. permit the 1. Apply wet coat of catalyzed epoxy resin to cham-
repair to cure before attempting further treatment of fered surface.
appearance surfaces, if required. 2. Apply one layer of #181 fiberglass cloth saturated
9. Appearance surfaces will normally require the ap- withcatalyzed epoxy resin.
plication of a filler-sealer coating. The appearance area 3. Add additional plys of #181 fiberglass cloth
is to be wiped clean, using a clean cloth saturated with saturated with epoxy resin to attain original laminate
M.E.K. prior to applying a filler-sealer coating, thickness.
10. Mix epoxy resin and catalyst per manufacturers 4. Apply one layer of #181 fiberglass cloth to the
specifications and apply to the appearance surface non-finished side of laminate, extending 1/2" each side
area. Care should be taken to assure as smooth as of the chamfer and bond in place.
possible surface in this particular operation. 5. Lay wax paper over both sides of the repaired
Permit this surfacing coat to cure prior to any addition- area while still wet. This prevents adhesion to the pres-
al applications or further rework, sure clamp application (paragraph 6).
11. Using #240 sandpaper, sand and blend the 6. Place rigid aluminum plates on both sides of
repaired area to match the surrounding surtace. Steps repair area and clamp into place with "C" clamps. Per-
10 and 11 may be repeated to acquire a satisfactory mit laminate repair to cure.
surface finish. 7. After fiberglass repair has cured, remove clamps
and install #3 AN426 rivets. Flush head to be on
51-15-04 COMMON STRUCTURAL
finished surface side. The number of rivets and spacing
LAMINATE REPAIR (FIG. 51-22) will be determined by the size of the repair.
(FIBERGLASS-RESIN COMBINATION)
51-15-04
20
MOONEY AIRCRAFT CORPORATION OLDWILLWAYNE
M20K SERVICE AND MAINTENANCE MANUAL

8. Upon completion of steps 1 thru 7, allow the 3. Extensive delamination of a part will be reason for
repair to cure before attempting further treatment of the totalrejection of the part and shall be scrapped per
appearance surface. standard practices.
9. Appearance surfaces will normally require the ap-
51-16-00 MISCELLANEOUS
plication of a filler-sealer coating. The appearance area
is to be wiped clean, using a clean cloth saturated with 1. Protective Coatings.
M.E.K. prior to applying a filler-sealer coating. A. Parts with Conver-
protective coatings (such as

10. Mix epoxy resin and per manufacturer’s

catalyst sion Coated or zinc primer) on which the
is coating
specifications and apply to the appearance surface scratched, spotfaced, drilled, or in any way removed
area. Care should be taken to assure as smooth as must be recoated with zinc chromate primer.

possible surface in this particular operation. EXAMPLE: Part is Conversion Coated as detail part.
Permit this surfacing coat to cure prior to any addition- During replacement the part is spotfaced to receive
al application or further rework. bolt and washer. This part must be primed after spot-
11. Using #240 sandpaper, sand and blend repaired facing.
area to match surrounding surface. Steps 10 and 11 2. Low Pressure, Plastic, or Rubber Line Splices.
Static system lines may be lengthened, shortened, or
may be repeated to acquire a satisfactory surface
finish, spliced~to allow the replacement of sections of
damaged lines. The fittings are called out in the Parts
51-15-05 -FIBERGLASS DELAMINATION
Catalog text pages following the illustration depicting
REPAIR
the assembly or component in question.
1. Delamination or ply separation of a fiberglass If splices are made, the system must be checked for
product is usually a result of poor bonding of fiberglass leaks.
layers. Generally, this condition is localized and can be 3. Shortening and Lengthening of Tubing, Hoses,
readily repaired by carefully spreading apart the plys in and Flexible Ducting. Mooney manufactured as-
the and removing loose particles by
delamination, semblies of plumbing, tubing, hoses, and flexible duct-
blowing clean compressed air into damaged area, ing may be modified to allow the use of longer parts of
2. Proceed by inserting catalyzed epoxy resin into the same size and material to be cut and used as re-
the delamination and then immediately clamp the placements. When the manufactured ends of flexible
delamination together. Permit the repair to cure a mini- ducting are removed, the raw edge must be taped with
mum of 8 hours before removing clamps. 3M aluminum foil tape.

smp oau

I ´•t´• I L-- CRACK

CHAMFERDD SURFACE
I............... a GLASS PATCH
I O"~NE:

I--- 1´•~ 1-r

---I
CRACK

t
1

T THICKNESS

EACH SIDE OYP.)

MKXNESS .02 TO .04

O
(LlBERGLASS-RESIN COYBINATK~N)
SM51 -22

COMMON STRUCTURAL LAMINATE REPAIR-FIGERGLASS/RESIN-FIG.SI -22

51-15-05
 OLDWILLWAYNE
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

BLANK

51-16-00
22
 OLDWILLWAYNE

CHAPTER

DOQRS
 M20K MOONE/ AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CHAPTER 52

DOORS

LIST OF EFFECTIVE PAGE

PAGE DATE
CHAPTER
SECTION
SUBJECT

1/2BLANK 997
52-EFF/CONTENTS
3. 9-97
52-00-00
4. 997
52-11-00
5. 9-97
52-12-00
6´• 9-97
52-31-00

TABLE OF CONTENTS

SUBJECT PAGE
CHAPTER
SECTION
SUBJECT

General 3
52-00-00
Cabin Door- Maintenance Practices 3
52-10-00
Cabin Door Rigging/Adjustment Procedures 4
52-11-00
Cabin Door Seal 5
52-12-00
5
52-30-00 Baggage Compartment Door- Maintenance Practices
6
52-31-00 Baggage Compartment Door- Latching Mechanism

52-EFWCONTENTS
i /2BLANK
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
52-00-00 -GENERAL outer rivets and screws work a putty knife or a thin

piece of aluminum between outer skin and hinge and

The cabin door is constructed of an inner and outer
between hinge and mounting plate from the inside in
aluminum shell fastened together by rivets. It is
order to break sealant bond. During this procedure
provided with a dual latching mechanism, determination can be made where locator rivets are
into a mafing receptacle in lower
d~oar positioned. Lacaie these rivets from the inside and drill
bucked heads carefully. DO NOT DRILL THROUGH
2) a latch clamps a special designed nut in
jaw type THE OUTER SKIN. Attempt to move door and hinge
upper door frame to hold door securely in place. The
aft and away from attach point after each rivet stem is
door is hinged at the forward edge by an extruded
drilled out. The door and hinge should come free when
aluminum hinge. The inner handle and the outer handle
all sealant bond and rivets are removed.
are interconnected by adjustable push pull tubes. This
mechanism is spring loaded to an over center position
NOTE
In the latched position for positive security. Adjustment
Some aircraft may have "AN" bolts instead of rivets.
for each push pull tube is provided to accurately rig
latching pin and jaw type latch. Adjustment to special
nut at the top of door frame can be made for proper
2- DOO’ Repair.
closure. repaired, if applicable, ac-
A. The door should be

The baggage compartment door is constructed of an cording procedures in AC 43.13-1(

to standard
B. Remove interior door panel, a necessary, to
inner and outer aluminum shell fastened together by
rivets. It has dual pin latches that extend into recep- repair door assembly.
3- I"stallation.
tacle fittings on both sides of door frame when the ex-
The old door can be relocated by using existing holes.
terior handle is closed properly.
The mounting plate should be thoroughly cleaned of all
The auxiliary exit handle is located on inside of bag-
sealant and foreign material before reinstallation of
gage door. This handle can be operated only from the
doO’.
inside, even if outer handle Is locked. A cam
A nevni door or hinge will require proper positioning of
mechanism allows a clevis pin to bypass outer handle
the door within door frame to obtain proper sealing.
latch groove and open two latching pins which hold
A. Place door, with new hinge installed, into posi-
baggage door closed. (Refer to AFM/POH Section III
tion (hinge placed between outer skin and mounting
for specific procedures to~operate auxiliary exit hand-
le.) This door is hinged at the top with an extruded plate).
B. When door is properly positioned mark new
piano type hinge.
A hold open arm is ´•attached on both doors to assist in hinge for mounting using existing holes, either from
outer skin locations or from hinge mounting plate in-
holding door open when desired.
Side cabin.
A door lock is provided for both doors. A single key
C. Dn’ll holes in new hinge carefully while door is
will operate either door lock. The interior panels require
held securely in place.
removal if door locks are to be removed and replaced.
D. Remove door deburr holes and clean shav-
52-10-00 CABIN DOOR MAINTENANCE
ings from area.
PRACTICES

Removal. The cabin door may be removed to

1. NOTE
replace or repair door or to replace a damaged hinge. The rivet holes originally used as locators do not
A. Remove interior panel around door frame, have to be utilized when installing a new door or
B. Remove hold open arm at door frame. Remove hinge if proper alignment can be obtained using
cotter pin and washers from hold open arm shaft. Pull another method.
shaft up from doubler plate and clear of door frame.
C. Remove eight (8) screws from outside the E. Apply sealant, PR1403-G-B2, or equivalent, be-
airplane that hold front portion of the hinge in place. tween outer skin and hinge support plate on tubular
There are also three (3) flush rivets that will require structure.
removal at this location. F. Reinstall door hinge to mounting plate using
D. Carefully drill center of rivet head with a 1/8th the Rat head screws removed earlier and three
eight (8)
inch drill bit until head pops off and rivet stem can be (3) Rat head AD4 standard (AD5 oversize) rivets.
punched out. G. Adjust door latching mechanism so door
The original door assembly, with hinge attached, is as- closes and seals during Right. (See door rigging proce-
sembled to door frame prior to installation of outer dures paragraph 52-11-00).
skin. The door is placed into position; the hinge is held H. Reinstall hold open arm with new cotter pin.
in place on its mounting plate by sealant and locator i. Reinstall interior panels and interior trim to door
rivets. CThe number of locator rivets may vary). These and cabin.
rivets will be undemeath outer skin. After removal of J. Paint door to match airplane.

52-00-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
52-11-00 -CABIN DOOR rigging. (See Figure 52-1). Removal of inten’or door
RIGGING/ADJUSTMENT panel will be required to gain access to adjustment
PROCEDURES points.
The cabin door latching mechanism has several 1. Adjust cabin door linkage to satisfy requirements
adjustment points that may be utilized to obtain proper listed below.

7. SLID
OYP13_6. LATCH JAWS

9. ADJUSTME
POINT a,
a, II~COVER PLATE

FWD

8
e 3. SPRING

/II_

4. HOUSING
ASSEMBLY

8. ADJUSTMENT 5. UPPER LINK

POINT

2. BELLCRANK
ARM I ~-1. LOWER LINK

VIEW-LOOKING OUTBOARD AT CABIN DOOR

CABIN DOOR RIGGING/ADJUSTMENT FIGURE 52 1

52-11-00
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
must contact striker plate, on i. When seal is properly attached, door should
A. Latching pin
door frame, full circumference of pin, when mechanism close with little effort.
Is In full latched position.
NOTE
B. Latching pin must clear striker plate when
Door contour can slightly to conform
be altered
opening or closing door with latching mechanism in full with cabin contour, if needed, for proper fit and
open position, sealing.
C. As lower link (1) and bellcrank arm (2), (Fig.
52-1) travel over center, spring (3), is to be com-
52-30-00 BAGGAGE COMPARTMENT DOOR
pressed to 1.000 +/-.030. MAINTENANCE PRACTICES
NOTE 1. Removal.
Washers may be added between spring and link or Baggage compartment door may be removed to
310294-501 housing assembly (4) to comply with
replace or repair door or to replace a damaged hinge.
items B and C, (Figure 52-1), A Remove coat hanger and headliner panel lo-

D. Lower link (1) and bellcrank arm (2), in full cated inside and directly under baggage door hinge
locked position, should be overcenter a minimum of.3 area.

inches, (Figure 52-1). B. Pull insulation back to clear rivet shanks.

C. Center punch rivet heads holding hinge half to
NOTE
fuselage.
It Is not necessary that lower link (1) contact upper
D. Carefully drill rivet heads and punch rivets from
link (5), (Figure 52-1).
holes.
E. Outside handle is to be flush with outside skin E. Work a putty knife or thin piece of aluminum
when mechanism is in full latched position. between outer skin and hinge and inner skin frame and
F. In full latched position, upper latch jaws (6) to break sealant bond.
hinge
must be closed and latch slide cam (7) at end of its full F. Remove hinge and baggage door assembly
travel. See adjustment points (8) and (9), (Figure 52-1).
carefully.
G. In full open position upper latch jaws must be
G. Clean hinge and hinge mounting area
open and slide cam at end of its full travel.
thoroughly of all sealant or foreign material.

NOTE 2. Repair.
Slide cam (7) moves 1.13 in. from the full latched The baggage door may be repaired per standard repair
to full open position. procedures in accordance with AC 43.13-1A. Repairs
may be made to baggage door on airplane, if feasible.
52-12-00 CABIN DOOR SEAL
NOTE
The cabin door seal is an extruded rubber seal filled
If repairs are to be made the interior trim panel
with a soft foam. Unless deformed or torn, seal will pro- removal.
may require
vide adequate sealing around periphery of door dun’ng
flight conditions. 3. Installation.
1. Cabin door seal replacement. OLD HINGE
A. The seal is held to inner door frame with ad- A. Place repaired baggage door with old hinge
hesive. into position and cleco securely to assure fit of door;
B. Remove door inner tn’m panel to gain access
check latching operations.
to door seal. is clean
B. Remove door assure attachment area
C. Pull seal from door frame.
Of Old sealant.
D. Clean area with lacquer thinner to help soften
C. Apply sealant, PR 1403-G-B2 or equivalent, to
remaining adhesive. Remove excess adhesive.
hinge attachment area between outer skin and inner
CAUTION frame.
Care should be exercised to keep lacquer thinner D. Reinstall door assembly with old hinge and
from dripping on wing or any other portion of
cleco hinge for proper placement.
airplane. E. Install rivets (AD4 standard, AD5 oversize) in all

E. Coat cleaned door frame with adhesive (St. holes.

Clair #4587). NEW HINGE
F. Coat bond area of new seal with adhesive (St. A. Place old door assembly, with new hinge, or
Clair #4587). new door assembly and new hinge, into position and
G. Let both applications dry until tacky. latch door in place.
H. Carefully place end of seal into position at bot-
tom of door and continue around door until seal is NOTE
Hinge mounting should be clean of old
firmly attached. Do not pull tight around corners. Cut area

off any excess seal. sealant and debris.

52-12-00
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
B. Push in on doorassembly, at top, while door is i. Install rivets, (AD4 standard, AD5 oversize) in all
in latched position to properly locate door and seal in holes. Remove cleco’s as rivets are being installed to
door frame. keep door aligned.
C. While door is held in place mark holes in new
52-31-00 BAGGAGE COMPARTMENT DOOR
hinge using holes in outer skin as locators. LATCHING MECHANISM
D. Verify correct position of door prior to drilling
holes in new hinge. The baggage compartment door has a direct non-ad-

E. Center punch all holes and carefully drill the justable latching mechanism that inserts two pins into
two end holes. Fasten cleco’s in these two holes and hard points in the door frame. This latching mechanism
recheck door assembly fit, if satisfactory continue drill- can be operated and locked from the outside.

ing all holes. An auxiliary exit mechanism is incorporated into this

F. Remove door assembly. Deburr and clean area latching mechanism which allows the door to be
completely prior to reinstallation of door assembly. opened, in an emergency, from the inside, even if out-
G. Apply sealant (PR 1403-6-82 or equivalent) to side handle is locked.
hinge mounting area between outer skin and door The outside handle has to be unlatched and fully
frame. opened and inside mechanism secured to correctly re-
H. Reinstall door assembly and cleco securely in engage latching mechanism after use of inside auxiliary
place, exit handle. See Figure 52-2 and POH/AFM to close.

98335A044 HITCH PIN

AN393-7 PIN
(PRESS FIT INTO CLIP/PIN ASSY)
350190-9007
CLIP/PIN ASSY
350191-009 HANDLE

CR3213-4-2 RIVET
CR3213-4-3 RIVET
(2 PLC> WASHER (2)
AN960-4
903~2A21 iANYARD (1 UNDER RIVET HEAD 1
(ORIENTATI[3N N17T ON BACK SIDE OF: HANDLE.)
CRITICAL)
MS20470-4 RIVET (OPT)

SM52-2

BAGGAGE DOOR UI\TCHING MECHANISM FIGURE 52 2

S/N 25-0001 thru 25-0754 were manufactured without a

spring attached to clevis pin to assist in proper

engagement of the latch pin linkage after operation of
the inside handle. Mooney Service Instruction M20-63
NOTE
dated April, 1983 adds this modification to these
aircraft. This ensures a positive re-engagement of the Follow procedures in Pilots Operating Handbook
clevis pin into the cam slot of outside handle for proper and Airplane FIISM Manual (POH/AFM) for re
actuation of the outside latching mechanism, engagement of the mechanism for proper outside
handle operation.
Service Bulletin M20-239 (AD 88-25-11) has been is-
sued to modify the baggage door latch also. It includes
the modifications depicted in Mooney Service Instruc-
tion M20-63 and SI M20-82. It is recommended that
this be accomplished on all aircraft (see Figure 52-2).

52-31-00
 OLDWILLWAYNE

CHAPTER

FUSELAGE
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 53

FUSELAGE

LIST OF EFFECTIVE PAGES

CHAPTER PAGE DATE

SECTION
SUBJECT

i /2BLANK 9-97
53-Effedivity/Contents
53-00-00 3´• 9-97

53-30-00 4´• 9’97

53-30-00 5´• 9’97

6´• 9’97
53-40-00
53-40-02 7´• 9’97
8´• 9’97
53-40-03

TABLE OF CONTENTS

CHAPTER SUBJECT PAGE

SECTION
SUBJECT

53-00-00 General 3

53-10-00 Main Frame 3

53-1 0-01 Tubular Structure Frame 3

53-10-02 Tailcone Structure 3

53-30-00 Plates/Skins 4

53-40-00 AttachFittings 6

53-40-01 Wing Attach Fittings 6

53-40-02 EmpennageAttach Fittings 6

53-40-03 Main Landing GearAttach Points 8

53-40-04 Engine Mount Attach Points 8

53-EFF/CONTENTS
1/2BLANK
IVIOONFI AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
53-00-00 GENERAL The forward cabin enclosure and the tancone are
mated and this fuselage assembly advances down the
The Mooney M20K forward fuselage is constructed
from 4130 chrome molybdenum tubular steel. The production line to the point of mating with the wing and
the empennage assemblies.
tubular steel sub-assemblies are heliarc welded in fDc-
tures, inspected and then assembled into the main 53-10-00 MAIN FRAME
cabin fb(ture and heliarc welded into a cabin enclosure. 53-10-01 TUBULAR STRUCTURE FRAME
The assembled steel structure is sand blasted and
The basic cabin enclosure is shown in (Figure 53-1).
painted with epoxy pn’mer for corrosion protection. Sen’al No. 25-0002 thru 25-0246 have a windshield
Earlier aircraft had the tubular structure dipped in zinc
frame that will not accept the radar display unit. S/N
chromate primer after sand blasting,
The tailcone bulkheads, forners, etc., are formed from 25-0001, 25-0247 thru 25-TEA have had the wishbone
sheet aluminum on a hydro press or drop hammer at subassembly (1) changed to allow this unit to be in-
Stalled.
Mooney Aircraft Corporation. These components,
along with stringers, clips, brackets,etc., are as- 53´•10-02 TAILCONE STRUCTURE
sembled together on fixture and built into the aft
a
The tailcone is of semi-monocoque construction. The
fuselage assembly. Al air ducts, control brackets, intemal structure is shown on (Figure 53-2). The for-
electrical harnesses and antennas are assembled into ward cabin structure (1) is bolted to tailcone with struc-
the tailcone during this manufacturing stage. tural bolts. The tailcone skin (2) is an integral load

SMJK53-1

TUBULAR STRUCTURE FRAME FIGURE 53 1

53-00-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
bearing portion of the assembly. The avionics equip- The empennage attach points (6) are attached to rear
ment shelf (3) spans the tailcone width to provide bulkhead (7) with tabs (8) extended foMlard and at-
rigidity and space for avionics components. The bat- tached to tancone structure.
tery box (5) and battery (12 volt) (battery only on 24
volt aircraft) are located in this area also. The hat rack NOTE
shelf (4) provides rigidity as well as storage space. Refer to Mooney Service Instruction M20-76 for
sealing of tai(cone and smooth belly skin.

TAILCCNE STRUCTURE FIGURE 53 2

53-30-00 PLATES/SKINS to the interior forinspection or maintenance purposes.

The fuselage tubular structure is covered with (See Figure 53-3).
aluminum skins after mating to tailcone. The skins a~e The belly skins are removable to provide access to all
riveted and bolted to support angles, forners and components and control systems located below Roor-
brackets. These skins are non structural coverings to board. See Figure 533 and the following table for com-

form the outside contour of forward fuselage section. Po"e"t location and identification. S/N 25-0781 and
The skins coven’ng the tailcone are an integral part of later aircraft have a one piece fiberglass/composite
the structure. Repair or replacement of these skins belly skin.
should be according to AC 43.13-1( Section 3.
The fuselage assembly and tailcone have panels, NOTE
PR-1766 B2 sealant should be used for all fuselage
covers or doors at various locations to provide access
skin lap joints to provide a good electrical ground
plane.
53-30-00
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE

II\

k \4 1

25

~II I

6A
6 :81~22;0

11 12 13 12

23
21

18

1’9 i ~17

2-~ 15 16

24

28-2131 AND~ON

INSPECTION PANEL AND COVERS FIGURE 53 3

53-30-00
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
TABLE FOR FIGURE 53-3 COMPONENT IDENTIFICATION

1. Cabin Door. 12. Landing Gear Actuator, Gascolator, Fuel Selector

Valve.
2. Engine Compartment, Turbocharger. 13. Landing Gear Retract Tubes, Flap Indicator Cable.
3. Baggage Door. 14. Electric Flap Actuator.
4. Elevator/Rudder Control Stops. 15. Stabilizer Trim Screw and Stops.
5. Empennage Attachment.
6. Avionics Blackboxes, 16, 17, 18. Elevator/Rudder/Aileron Control System,
Bellcranks, Rod End Bearings.
6A Battery Access. 19. Nose Wheel Steering System, Cowl nap Controls.
7. Stabilizer Trim Jack Screw.
8. Empennage Attachment. 20. Rudder Torque Tube.
21. Landing Gear Retraction Tubes.
9. Elevator/Rudder Controls, Rod End Bearings 22. Tail-Light Harness Connections.
Travel Stops
23. Empennage Attachment, Trim Jack Screw.
10. Rudder Controls, Elevators Rudder Bellcranks.
11. Brake Master Cylinders, Rudder Torque Tube, 24. All components (12-18, 21).
Electric Fuel Pump. 25.0ii access

53-40-00 ATTACH FITnNGS 53-40-02 EMPENNAGE ATTACH FITnNGS

53-40-01 WING ATTACH FITnNGS The empennage assembly is manufactured as a unit

(1), (Figure 53-5) with the vertical fin and horizontal
The wing assembly (1) is attached to fuselage assemb-
stabilizer using common components. This unit at-
ly (2) using structural hardware (4); (see Figure 53-4
taches to tailcone/empennage attach points (1) (Figure
for locations). Various type of fittings (3) are used to
properly distribute the load between wing and fuselage. 53-6); using two structural bolts (2) (Figure 53-5) pass-
ing through two top hinges (3) (Figure 53-5).

i3~ 0~

25-0001 THRU 25-0780

sns3-4

WING/FUSELAGE ATTACH FITnNGS FIGURE 53 4

53-40-00
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
The bottom attach point (4) (Figure 53-5) on the articulated hinge assembly (2) (Figure 53-6) attached
empennage assembly secures stabilizer trim jack to rear bulkhead (3) (Figure 53-6) of tailcone. The
screw (5) (Figure 53-5) and (4) (Figure 53-6). Lateral hinge attach pin (6) (Figure 535) is held in place with
stability of empennage assembly is controlled with an a cotter pin at each end.

sns3-s

EMPENNAGE ASSEMBLY ATTACH FITTINGS FIGURE 53 5

53-40-02
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
The main landing gear assembly is a welded heat
treated, 4130 chrome molybdenum steel assembly. The
leg assembly (1),Fig. 53-7, is supported at the forward
end by the tension strap fitting (2) attached to the wing
main spar assembly (3) (Figure 53-7 insert) 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 as-
sembly (5). This is the rear hard point. The main land-
ing gear truss assembly (6) also attaches to the ten-
sion strap fitting (2) on main spar. The brass bearing
(7) (insert) should be inspected at any scheduled main-
r tenance action for wear. Grease fittings (8) are installed
at pivot points of main landing gear assembly for
lubrication per Section 5. (Reference Figure 53-7).
53-40-04 ENGINE MOUNT ATTACH POINTS

The engine mount is attached to hard points built into

4-/ the forward portion of tubular structure.
I
2
The upper hard points (1) (Figure 53-8) are for
NAS1304 bolts installed for tension loads. The lower
hard points (2) are for iittings outside the firewall which
TAILCONE/EMPENNAGE ATTACH POINTS
allow a clevis on each side of the engine mount to be
FIGURE 53 6
attached for shear loads. AN4 bolts are used for this
application.
53-40-03 MAIN LANDING GEAR ATTACH

POINTS

k;
S 2

(HBO*RD
i
Ij i
3
8 I

MAIN LANDING GEAR ASSEMBLY ATTACH POINTS ENGINE MOUNT ATTACH POINTS
FIGURE 53 -7 FIGURE 53 8

53-40-03
 OLDWILLWAYNE

CHAPTER

STABILIZERS
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 55

STABILIZERS

LIST OF EFFECTIVE PAGES

PAGE DATE
CHAPTER
SECTION
SUBJECT

1RBLANK 9’97
55-EFWCONTENTS
3. 9-97
55-00-00
4. 9-97
55-10-02
5. 9-97
55-30-00
6´• 9-97
55-40-02

TABLE OF CONTENTS

SUBJECT PAGE
CHAPTER
SECTION
SUBJECT

General 3
55-00-00
Horizontal Stabilizer 3
55-1 0-00
HorizontalStabilizer- Removal 3
55-1 0-01
Horizontal Stabilizer- Installation 4
55-1 0-02
Elevator 4
55-20-00
Elevator- Removal 4
55-20-01
Elevator- Installation 4
55-20-02
Vertical Stabil~er 5
55-30-00
Vertical Stabil’ner- Removal 5
55-30-01
Vertical Stabilizer -Installation 5
55-30-02
Rudder 5
55-40-00
55-40-01 Rudder-Removai 5
Rudder- Installation 5
55-40-02

55-EFF/CONTENTS
112B LANK
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
55-00-00 GENERAL from aluminum sheet reinforced with a joggled channel

The M20K empennage assembly is a variable incidence (6) at the center section. The rear spar (7) is an ex-
trusion attaching to aft end of ribs and contains hinge
tail-plane donsisting of a horizontal and vertical stabi-
lizer built as a unit. (Refer to Chapter 53 for the attach- fittings (8) for the elevators.
The ribs (9) are assembled in sections to front and rear
ment of empennage to fuselage.)
face of each spar assembly to form the air foil. Stretch
The horizontal and vertical stabilizer are constructed of
formed skins (10) are fastened to ribs, spars and
formed sheet metal ribs attached to a forward and aft
doublers to form the complete horizontal stabilizer
spar assembly covered with stretch formed skins. The
Structure.
horizontal stabilizer has a stub spar that spans a por-
The aft vertical fin spar (11) is attached to horizontal
tion of the stabilizer.
stabilizer structure through a bracket (12) which is fas-
The elevator and rudder are constructed from an ex-
truded leading edge spar assembly covered with
tened securely to stabilizer rear spar assembly (7).
formed skins. The elevators have a fixed tab between (Reference Figure 55-1).
the skins that run the full length of the trailing edge. 55-10-01 HORIZONTAL STABILIZER
The elevators and the rudder have balance weights REMOVAL
permanently installed for stabilization during flight. The fairing located on tailcone, covering gap between
55-10-00 HORIZONTAL STABILIZER tailcone and empennage assembly, will require removal
to gain access to empennage attaching hardware. Sec-
The main spar assembly (1) (Ref. Fig. 55-1) is iormed
tion 53-40-02 descn’bes attaching points for empen-
from aluminum sheet into a channel. Angle doublers (2,
3 and 4) are formed and riveted to the spar through the nage assembly. Refer to this section for the removal of
web section. The stub spar (5) is a channel formed empennage assembly from airplane.

8
9 S

7 11
12 7

HORIZONTAL STABILlZER FIGURE 55 1

55-00-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

OLDWILLWAYNE
55-10-02 HORIZONTAL STABILIZER The elevator control hom (2) is connected to inboard
INSTALLATION leading edge of each elevator (R.H. and L.H~. Both
control hems are then connected to elevator flight
Refer to Section 53-40-02 for installation. control bellcrank. The full length trim tab (3) may not be
55-20-00 -ELEVATOR re-adjusted from factory installed configuration. This is
factory set at 70 down.
The elevators on the M20K consist of a left and n’ght The elevator skins (4) are stretch formed for upper and
hand assembly attached through ball bean’ng fttings lower surface of elevator. There are no ribs in the
(1) to rear spar of the horizontal stabilizer (reference elevator between inboard and outboard ribs.
Figure 55-2).

7 1 i r4

1- 5

2 e~ 1

DETAIL A Al:

ELEVATOR FIGURE 55 -2

The skins are attached to leading edge e~drusion (5) 55-20-01 -ELEVATOR-REMOVAL
and n’bs (6) with blind n’vets. Each formed corrogation Remove AN3 bolts from each control horn and
is matched on top and bottom skins and rivets are
push-pull tube bean’ng, then remove AN3 bolts and
installed for strength and n’gidity through each hardware from each hinge fitting on both elevators.
corrogation.
55-20-02 ELRIATOR INsTAUATION
A lead balance weight O is installed in each elevator
tip with iron n’vets (8). (Reference Figure 55-2). See CAUTION
Section 27-91-00 for balancing procedures on the Each new, repaired or repainted elevator
elevators. 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.)

55-1 0-02
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
55-30-00 VERTICAL STABILIZER
55-30-01 VERTICAL STABILIZER REMOVAL
The main spar assembly (1) (Ref. Fig, 55-3) is formed
from aluminum sheet. Formed angle doublers (2) are The vertical and horizontal stabilizer are removed as a
nested inside the main spar channel and riveted to the unit with stinger assembly. Remove fairing located on
web. The rear spar (3) is an extrusion used to attach tailcone which covers gap between tailcone and em-
ah end of sectioned ribs (4). The stub spat (5) is also pennage. Section 53-40-02 describes attaching points
formed from sheet aluminum. A doubler channel (6) is f,, the complete empennage assembly. Refer to this
attached to the vertical stabilizer stub and the stub section for removal of empennage assembly from
channel is
spar of horizontal stabilizer. This attach airplane.
securely bolted to stinger bulkhead brackets. The main
5&30-02 VERTICAL STABILIZER
doublers and angles 7, 8 and 9 provide attach
spar INSTALLATION
points for stinger and horizontal stabilizer spar. (Refer
toFigure 55-3). Refer to Section 53-40-02 for installation.
The skins (10) are stretch formed in 2 sections and -RUDDER
5540-00
riveted to ribs and spar.
mounted to the The rudder on the M20K is constructed the same as
The rudder attach fittings (11) are rear
the elevator with stretch formed skins (1) (Ref. Fig. 55-
spar extrusion.
4) riveted to an extruded leading edge (2) and riveted
together at the trailing edge. The rudder lower skins (3)
are drop hammer formed left and right halves
riveted to
if
upper skins, a assembly (4) and at leading and trail-
rib
4
ing edge. A stiffener(5) is to support lower rudder ball
bearing hinge fitting (6). A weather seal (7) is included
in the assembly.
The rudder control horn (8) is attached with center

/3 hinge fitting (9) to the rear fiange of front spar at the

junction of the lower rib assembly (10). A brace arm on
if hom assembly is attached to a fitting (11) on lower rib
10~ 4 (1 0).
The upper hinge fitting (12) is attached to the rear
1
Range of front spat just under top rib assembly (13)
and balance weight (14), (refer to Figure 55-4).
The balance weight (14) is installed with four iron rivets
4~jl 1 (15). See section 27-91-00 for balancing procedures on
WI ~s rudder.

it 5540-01 -RUDDER- REMOVAL

6 Remove AN3 bolt from control hom and push-pull tube

2
bearing, then remove three AN3 bolts and hardware
from each hinge fitting. Disconnect electrical connec-
tions per paragraph 33-41-03.2.A thru E.
7
4 4 5540-02 -RUDDER INSTALLATION

CAUTION
9 Each new, repaired or repainted rudder should be
checked for balance per section 27-91-00 prior to
8 installation.

The rudder is installed in reverse order of removal.

VERTICAL STABILIZER ASSEMBLY FIGURE 55 3
Nominal torque valves for AN3 bolts are to be used.
(See Section 5-20-01 for torque table).

55-30-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE

’?1,4 1:1
10 i,
8
1~
z

1
c~

9 7
\;r ,j

4´• 5

RUDDERASSEMBLY FIGURE55-4

55-40-02
 OLDWILLWAYNE

CHAPTER

VVIN DOVVS
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 56

WINDOWS

LIST OF EFFECTIVE PAGES

PAGE DATE
CHAPTER
SECTION
SUBJECT

1/2BLANK 9-97
56EFF/CONTENTS
3´• 9-97
56-00-00
4. 9-97
56-21-00
5´• 9-97
56-22-00

TABLE OF CONTENTS

SUBJECT PAGE
CHAPTER
SECTION
SUBJECT

Gene~al 3
56-00-00
56-00-01 Clean6g Acrylic 3

Windshield and Cabin Windows 3

56-20-00
Windshield 4
56-21-00
Windshield Removal 4
56-21-01
Windshield-lnstallation 4
56-21-02
Cabin Windows 5
56-22-00
Cabin Windows-Removal 5
56-22-01
Cabin Windows-installation S
56-22-02
StormWindows 5
56-23-00
56-50-00 Acryiic Dn’lling 5

56-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
56-00-00 -GENERAL If no commercial cleaner is available, the following
procedures should be followed:
The windshield for the M20K is .187 inch thick ac~ylic
heat formed to contour. The pilots side window is also i. Flush windows with water pn’or to wiping with a

.187 inch thick acrylic with a hole cut out to clean, soft cloth soaked in kerosene.
accommodate the .312 inch thick storm window. The
storm window is milled to fit the hole and to be flush CAUTION
with outside of pilots window surface when closed. The Never wipe windows when dry.
other three side windows are .125 inch thick acrylic.
Serial Number 25-0001 thru 25-0612 and 25-0781 and
2. Flush with water after cleaning with kerosene.
ON have single pane side windows installed. Serial
Number 25-0613 thru 25-0780 have a double panel
CAUTION
cabin door window. The inner pane is a .060 inch thick
acrylic fitted to clips and brackets on door fr~me. Never gasoline, benezene, carbon
use

tetrachloride, acetone, lacquer thinner, deicer

All the windows heated in an auto-dave to
are
fluid, house hold cleaning fluid or any other
approximately 3000 F and placed on a plaster mold to
questionable fluid to clean acrylic windows.
cool while maintaining the correct shape. These solvents will soften or craze the surface.

The windows are tinted for visual comfort, ultra-violet

filteration and cooling effect for the cabin. NOTE
The windows are all sealed to the outside skin with Minor scratches or abrasions may be polished
sealant. Retainers and clips are used on the frame to out by using acrylic resurfacing kits, ie.,
hold windows in place. Micro-Mesh, available from aviation accessory
suppliers.
56-00-01 -CLEANING ACRYLIC
A cleaning solution manufactured for
commercial 56-20-00 WINDSHIELD AND CABIN WINDOWS
acrylic may be used to clean routine grit and grime
The 7emoMI and installation of windshield and
from windows. Follow instructions on the commercial
cleaner used, windows are accomplished in the following paragraphs.

d II

SMX56-1
WINDSHIELD INSTALLATION FIGURE 56 i

56-00-00
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
56-21-00 WINDSHIELD windshield will be located (refer to Fig. 56-1). Wipe sd-
5621-01 WINDSHIELD REMOVAL vent dry to prevent re-deposit of contaminates.

The aluminum retainer (1) at bottom of windshield (2) NOTE

must be removed by drilling out rivets attaching it to Exercise with application of these solvents.
care
cowl deck (3), (reference Figure 56-1). Damage may result if drops of solvents come in
A putty knife or thin aluminum stn’p will be necessary to contact with either exterior paint, interior trim or
work undemeath top skin (4) and side post skin (5) to plexiglass.
break sealant band between the acrylic and skins.
Apply sealant, PR1403G-B2 or PRC1321-8-2, into
CAUTION cavity (8) until approximately half filled. Apply a bead of
Exercise care during this operation to avoid sealant along recessed joggle (6) of cowl deck (3), (ref-
erence Figure 56-1).
scratching the acrylic. Considerable effort may be
required to break bond. The new windshield being forced into cavity between
outer skin (4) and inten’or retainer (7) will extrude ex-
Carefully pull the windshield away from its location cess sealant After windshield is in place wipe excess
starting at lower portion and work a loose as the sealant off with a damp clean cloth.
sealant bond is broken around edge of acrylic. Prior to riveting aluminum retainer (1) into position coat
When windshield Is removed all residual sealant must retainer with a unifon thickness of either sealant. A
be removed prior to installation of replacement positive bond will be made as retainer is riveted into
windshield. Careful scrapeing with putty knife and ap- place. Use CR1312-5-2 cherry rivets to reattach retainer
plication of M.E.K. will assist in removing excess (1) to cowl deck (3), (reference Figure 56-1).
sealant. After the sealant cures, excess may be removed with a
5~-2192 WINDSHIELD-INSTAUATION sharp razor knife.
Check for water leaks.
When old sealant is removed brush M.E.K. or
Repaint retainer and rivets to match aircraft.
equivalent cleaning solvent in cavity (8) where new

SM56-2

CABIN WINDOW INSTALLATION FIGURE 56 2

56-21-00
MOONDI AIRCRAFT CORPORATION M20K SERV1CE AND MAINTENANCE MANUAL

OLDWILLWAYNE
5~22-00 CABIN WINDOWS Place window (1) into position to assure proper fit.
Tn’m if necessary (See Figure 56-2).
5622-01 CABIN WINDOWS REMOVAL
Apply a uniform thickness of PR1422-82 or PR1403-G-
Remove interior trim from window (1) to be replaced. 82 or PR1428-8 sealant to the skin area where window
Remove retainers (2) or clips (3) which hold window in (1) will be located.
position from inside, (reference Figure 56-2). Force window (1) into place with retainers (2) or dips
(3) and secure with Avex 1601-410 blind rivets or exist-
NOTE ing screws and hardware (4). The sealant will be forced
Some retainers are held in place with screws (4) out as window is sealed to outside skin. Carefully wipe
and some with rivets. Drill out rivets carefully. excess sealant off acryiic before it sets up. After
sealant cures, excess can be cut off with a sharp mzor
The window will be bonded to outside skin with knife, (reference Figure 56-2).
sealant. Considerable effort may be required to break Check replaced window for leaks.
bond between acryfic and outer skin. Care should be Reinstali interior tn’m panels.
exercised to keep window from twisting and possibly STORM WINDOW
5~23-00
cracking.
Remove window and clean all remaining sealant from The storm window (6) is mounted with two hinges (7),
skin. Use M.E.K. and a scraper to remove sealant attaching hardware (8) and held closed by a latch (9).
Aircraft S/N 25-0613 thru 25-0780 have an inner (5) and A gasket (10) is bonded to storm window for sealing
outer window (1) installation on cabin door window. purposes when closed, (ieference Figure 56-2).
Removal is basically the same procedure as single win- 5B50-00 ACRYUC DRILUNG
dow installations.
INSTAUATION
Drill bits for acrylic should be ground per (Figure 58
5622-02 CABIN WINDOWS
3). A slow turning drill bit with light pressures is
Remove all old sealant and clean skin area with M.E.K. desirable.

75,"
O
NEGATIVE RAK
(,03 FLAT WIDTH)

5" CLEARANCE
ST[7VE BURNER TYPE BIT
(NCI FLUTE RELIEF)

JOBBER ~LUTE LENGTH

a JCIBBER LENGTH IIVERAL

+,0000
DRILL DIAMETER TOLERANCE
-,0000
ISM5~-31
TOTAL INDICATED R 1I_N_OVT _,0_0_0_2_
ACRYUC PIASTIC DRILL BIT SHARPENING FIGURE 56 3

56-22-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE

B LAN K

56-50-00
 OLDWILLWAYNE

C H A PT E R

MIINGS
SERVICE AND MAINTENANCE MANUAL M20K MOONN AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 57

WINGS

LIST OF EFFECTIVE PAGES

PAGE DATE
CHAPTER
SECTION
SUBJECT

1/2BLANK 9-97
57-EFDF/CONTENTS
3´• 897
57-00-00
4´• 997
57-00-02
5´• 897
57-20-00
6´• 897
57-30-00
7´• 9’97
57-30-00
8´• 997
57-50-11

TABLE OF CONTENTS

SUBJECT PAGE
CHAPTER
SECTION
SUBJECT

General 3
57-00-00
57-00-01 Wing Removal and Installation 3
Stall Stn’p installation 4
57-00-02
Main Frame 4
57-10-00
Au~a’liary Strudures 5
57-20-00
57-20-01 Jack Points 5

57-20-02 Wing Tips 5

57-30-00 Plates-Skin 7
Attach Fittings 7
57-40-00
57-50-00 Flight Surfaces 7

57-50-10 Flaps 7
FlapRemovaland Installation 8
57-50-11
57-50-20 Ailerons 8
Aileron Removal and Installation 8
57-50-21

57-EFF/CONTENTS
1/2BLANK
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
GENERAL 57-00-01 -WING REMOVAL AND INSTALLATION
5790-00
The all metal wing is a one piece assembly attached to Major subassemblies of wing may be removed
the fuselage at structural hard points with strudural individually, or wing may be removed as a unit. To
remove a wing, a fuselage supporting cradle needed.
hardware. (See section 53-40-01). The full span main
and rear
spat assembly is connected to the stub spar Wing removal:
1.
The main
spar assembly by ribs, doublers and skins. A. Remove wing-root fairings and bottom fuselage
landing gear forward attach assembly is an integral part access panels.
of the main spar and the rear fitting is bolted to the stub
spar assembly. The spar caps are 7075-16
aluminum B. Drain all fuel from tanks.
and webs, ribs and doublers are 2024-T3, T4 or T42 Drain brake lines and reservoir.
C. Disconnect
aluminum. Repair of these components is covered in
hydraulic lines at wing main spar.
Section 51-13-00.
D. Remove front and rear seats. Remove two
The wing tips are fabn’cated from fiberglass and house
inspection plates under rear seat area.
navigation and strobe lights.
E. Jack aircraft per Chapter 7-10-00.
The fuel is contained in wet wing type fuel cells
between main spar and baffles forward of spar. The F. Attach A-frame hoist to propeller, or support with
tanks are sealed dun’ng manufacturing with current a propellerjack.
technology sealant. (See Section 28 for fuel system
details).
sn TABLE FMI LENGTHS )F
wn B3SULL SHI~CS BEPYIW SHEAR
~Y;o. loll usHa
US) NOT UNDER BOLT HEAD OR NUT.
WQJ21
319139-3
510131-9 ~ns6M1Q t W3Q-~ ANC~ BOLT (4)
AW96M1Q )W#F~ AN960-S16 WASHER
J1O1JCU UC(-CA ANWD´•S1Q IW18-)2~ AW6S-428 NUT (4)
310131-11 UI(-(A
Auull
O vlrs-lal CTYPICK ~QR1 SIIiES-ACCESSIBLE INSIDE

SHUR
BoLT O)-
U16-)6A, BOLTJ1UJ)AN~-1‘IA
AcCFlWWF THRu ~HIEn´•
ANs6O-6l6 WASHER
WELL
AI363-634 NUT
AN960-S16 WASHER (3)
IloOOl-3 OR -5 SPACER (43)
NUT (2)--
~IYP1CU BOTH SDES--
ACCESSIBLE ~NSIDE CABIN
ACCESSIBLE INSIDE CAB~N) CMYCU BOTH SIDES)
BOL1 (I1--KMSSIBLE
O
INSIDE CABIN
Ai960o-16a
AN9S0-S16 WASHER (5)~
AUs3-436 NUT (5)--CCESSSBLE
RY fbP WNC FURING
(NPlCAL BOTH SDES)

ca~

E~g
AN4-17A--
I XY(PIEWUE
ACCESSIBLE UNDER WAR WATS
ANB6PJ16 WASHER (2)
I 39-33 AN36S-428 NUT (2)-
ACCESSIBLE’THRU WING BOTTOLI
ACCESS PWL;
SHIY AS NECESS~RY

W-4A BOLT-ACCESSIBLE By WLKI~NG U37H-17A BOLT-ACCESSIBLE THROUGH ACCESS

CO~R UNDER REAR SEAT. SAFRY WIRE BOLT HEAD
TOP WINC FURW;
AN060-1O WASHER~(8) TO AnIYCENT SPAR-~MB SI~FFEWR
AN363-1633 NIII (8) ACCESSIBLE THROUGH ANObD-T1Q WASHER
WHmrmL (TYPICAL BOTH SDES) CMPICK BOTH SIDES)

WING ATTACHING HARDWARE FIGURE 57 1

57-00-00
 SERVICE AND MAIF?TENANCE MANUAL M20K MOONCI AIRCRAFT CORPORATION

OLDWILLWAYNE
G. Disconnect or remove the following: A. More than 15 degree roll.
(a) Two landing gear assist springs. B. More than 15 degree yaw.

(b) Aileron control tubes at inboard bellcranks. C. More than 30 degree pitch below flight level.
(c) Tn’m control tube at station 59.3 and 94.5. 2. Place stall strips on leading edge at stations
shown on Figure 57-2; attach securely with duct tape
(d) Main gear retraction tubes, for test flights. Adjust stall strips until aircraff flies to
(e) Rudder control tubes. criten~a in paragraph 57-00-02, 1, A, B and C. Secure
stall strip per installation instructions in (Figure 57-2).
(f) Elevator control tube.
(0) Elevator and rudder push-pull tubes. 57-10-00 MAIN FRAME

(h) Floorboards at rear attach points. The integral fuel cells, shaded area (1) start at wing
station 24.5 and continue to the rib at station 88.75 on
(i) Belly skin stringer splice angles. both wings. (Reference Figure 573). Sealant is
(D Airspeed indicator line, paot lines, and pitot applied to all joints on ribs, spar and baffle plates. (See
heater wires (if installed). Section 28 for resealing procedures).
(k) Hardware shown in (Figure 57-1). The wing is manufactured in three sections; the center
CAUTION section (2), the left outboard section (3) and an
Have a suitable cradle ready to carry fuselage opposite right outboard section (not shown) (Figure
before removing all mating hardware. 573). These three sections are then assembled into
one full span wing assembly as the splice plates and
2. Wing installation: overlapping skin is installed while on the fixture.
Installation of the wing assembly is direct reversal of A spares outboard wing tip assembly is available which
removal, includes completed section from Wing Station 103.50
and outboard. The assembly includes the stn’ngers (4)
57-00-02 STALL STRIP INSTALLATION required to complete the splice to the old center
1. Adjust stall stn’ps so that, dun’ng stall recovery, section.
normal use of controls should prevent:

LEFT WING SHOWN

RIGHT WING OPP.

SKIN LAP STA. 103.5

FW D
SKIN
SKIN AN520-6-7 SCREW AI C’BORE STALL
AN345-6 NUT STRIP .406"
AN960-6 WASHER .06/.16’ DEEP
STALL STRIP
DRILL .189/.193 DIA
AN515--6R10
USE A6-75 RIVNUT
SCREW USE
LOCKTITE

FWD
"PE CV
FWD

A
A/
TYPICAL INSTL. STALL STRIP ALTERNATE INSTL.
STALL STRIP INSTALLATION F(GURE 57 2

57-00-02
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
1033
VS 11825

VS 178.25
VS 133~0
VS 147.75
VS 163.0 i o 4

VS 193.5
5

VS 245
VS 435
VS 59~25
VS 740

VS 88.75
11]35
SV52.8~1
VS

o
SU(R5~-3

WING STRUCTURE FIGURE 57 3

NOTE
57-20-00 -AUXIIIARV STRUCTURES
The strobe or navigation lights can be removed
57-20-01 JACK POINTS from wing tip either before or after its removal
from wing.
Jack points are located on under side of wing. The
threaded wing tie down eyebon fittings are designed to
also accept the non-threaded jack points. These are 2. Wing tip installation.
located outboard of each main gear. See Chapter A. Place new or repaired wing tip in place.
7-10-00 for complete jacking procedures.

57-20-02 FIBERGLASS WING TIPS CAUTION

Be sure aileron and aileron balance weights are
The M20K wing tips are non-structural fiberglass not restn’cted in movement either direction.
components. They are riveted to the upper and lower
wing skins during final assembly of the wing structure. B. Secure wing tip and drill holes to match wing
1. Wing tip removal. skins. Cleco as holes are drilled into tip. When all holes
are drilled remove wing tip assembly and deburr.
A. Remove navigation strobe light lens (1) by
removing 4 screws and washers (2) that retain lens to
NOTE
wing tip (3) (see Figure 51~.
Connect strobe and navigation light connectors
B. Drill out rivets (4) holding tip to upper and lower prior to final attachment of tip.
wing skins (5). Remove all n’vet shanks with a punch.
C. Carefully pull wing tip away from wing rib (6) C. Use Avex 1604-0412 blind rivets to attach wing
and skins (5). Disconnect strobe and navigation light tip to top and bottom skins.
hamesses at quick disconnect plug (8) prior to
D. Repaint to match aircraft.
completely removing tip.

57-20-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
S/N 25-0001 THRU 25-0999

S/N 25-1000 THRU 25-TEA

4
7 3
8

I,:

1
2
e‘

1
STROBE LIGHTS (7) AND POWER SUPPLY
CONNECTORS (8> WILL VARY. SMK57-4
FIBERGLASS WING TIP ASSEMBLY FIGURE 57 4

9 tttul~ rr+ 10
3mi(I ILL 1
TVD

OLt--12
19

O
4
-I- I I I I O O-ts
19

9
17 Bc-+
BO’ITM
CEN?ER SECTION 0
LODKING UP 13
7
NOrEl 15 O
Pn PIECE BELLYSKIN 5
SM 25-0781 b TEA
16
O

14 -t-n 0
7
~-´•t i 0

mp Bmmn
LD7 VINt 51157-3
RIC+Tr VING

WING SKINS AND INSPECTION COVERS FIGURE 57 5

57-20-02
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEl AIRCRAFT CORPORATION

OLDWILLWAYNE
5730-00 -PLATES-SKIN plumbing and control bellcranks enclosed within wing.
They are flush mounted covers and when installed
Wing access and inspection covers shown in (Figure continue the aerodynamic contour of wing.
575) provide maintenance access to components,
LEGEND FOR FIGURE 57-5.

1. Wing skin .050 thickness (Fuel Tank). 11. OAT probe, n~ght wing only.
2. Wing skin .040 thickness (Fuel Tank). 12. Control tube guide blocks and flight timer.

3. Wing skin .040 thickness. 13. Pitot post left wing only.
4. Wing skin .032 thickness. 14. Strobe light power supply.
.025 thickness. 15. Aileron bellcrank and control rods.
5. Wing skin
6. Wing skin .025 thickness. 16. Auto pilot servos.
7. Fuel tank access. 17. Gym compass flux valve tone of these,
depending on installed equipment), (left wing only).

8. Fuel tank filler. 18. Main landing gerar retraction spring.

19. Elevator and rudder controls rod end bean’ngs,
9. Control tube guide blocks.
10. Wing fuselage attach points, bellcranks.

NOTE 5750-00 FUGHT SURFACES

Access covers on bottom of wing that require flight control surface’s
Refer to Section 27-90-00 for
removal for inspection intervals are secured
balancing procedures.
with screws. Any access covers that are riveted
in place are required for manufacturing only
and NOT for routine inspections. 5750-1 0 FLAPS

Refer to Section 27-50-00 for maintenance and rigging

57-40-00 -A~TACHFITnNGS
procedures.
Refer to Section 57-00-01 for wing fuselage
attachment.

8 67

FLAP ASSEMBLY FIGURE 57 6

57-30-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONN AIRCRAFT CORPORATION

OLDWILLWAYNE
The flap actuatorjack shaft is connected by a push-pull Refer to Section 27-10-00 for maintenance and n’gging
rod end bean’ng to actuator bracket (1) (Figure 57-6) procedures.
located just inboard of inboard hinge (2).
The ailerons are of all metal construction. The main
All three hinges (2) and (3) are faired (4) to reduce spar (1), (Figure 57-7), is attached to the rear spar (2)
drag (excluding 231 Lean Machines). through n’bs (3). These components are n’veted
The internal structure of flaps consists of a leading together and a top and bottom skin (4) and (5) riveted
to this sub-assembly. To complete control surface,
edge extrusion (5), trailing edge stiffener (8), n’bs O
and top and bottom skins (8). These components are hinges (6) and balance weights O are installed. The
riveted together into a left hand and n’ght hand weights O are bolted bolted (10) through an outboard
rib (8) and bracket (9) on each aileron assembly.
assembly.
5730-21 AILERON REMOVAL AND
57-50-11 FLAP REMOVAL AND INSTALLATION
INSTALLATION
Refer to Section 27-50-00 for removal and installation Refer to Section 27-10-00 for removal, installation 8
procedures. balancing procedures.
5750-20 -AILERONS

3 3

6~ 5

~P 1 ~2

4 1

~e oP 3J gC
6

DETAIL A 3

7~-CI
1

91 8

r1"o

DETAIL B DETAIL C

SMX57-7

AILERON ASSEMBLY FIGURE 57 7

57-50-11
 OLDWILLWAYNE

CHAPTER

STANDARD
PRACTICES
(PROP/ROTOR)
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CHAPTER 60

STANDARD PRACTICES-PROPELLER

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General 3
60-00-00

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6090-00 -GENERAL Repairs may be made to metal propellers in
accordance with AC 43.13-1( Chapter 12 and in
The standard configuration M20K aircraft S/N 25-0001
thru 25-0999 has a 2 blade McCauley Propeller
CO"jU"CtiO" With the definitions of FAR 43.
Installed; Sn~ 25-1000 thru 25-TBA~ have a slightly CAUTION
different McCauley 2 blade propeller installed. Refer to Teledyne Continental Motors (TCM)
maintenance publications for engine inspection
An option forthe M20K, S/N 210001 thru 25-1999, is a
Hartzell, 2 blade propeller with Q-Tip blades. procedures after a propeller strike.
All propellers are controlled, at the pilot’s discretion, by
a propeller governor for constant RPM settings.

Each propeller has its own matching spinner assembly.

S/N 25-1000 thru 25-TEA have different blade settings from 250001 thru 25-0999. Refer to TCDS 2A3,
Revision 44, for configuration effedivities.

60-00-00
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60-00-00
 OLDWILLWAYNE

eHAPTE R

PROPELLERS/
PROPU LSO RS
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OLDWILLWAYNE
CHAPTER 61

PROPELLERS

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......´•´•´•8´•´•´•´•´•´•´•´•´• 9~97
61-40-00

TABLE OF CONTENTS

CHAPTER SUBJECT DATE

SECTION
SUBJECT

General 3
61-00-00
61-00-10 Spinner Dome’and Propeller RemoMI 3
PropellerInstallation 4
61-00-20
61-10-00 Propeller Assembly 4

61-10-10 Minor Propeller Blade Repair 4

61-20-00 Propeller Controlling 5

61-20-10 Propeller Govemor Control Rigging 5

61-20-90 Propeller Govemor Trouble Shooting 5

61-40-00 Propeller Balano’ng 7

61-EFFICONTENTS
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61-00-10 SPINNER DOME AND PROPELLER
61-00-00 GENERAL
REMOVAL
The propeller is a constant speed type which operates
1. Spinner dome removal (if necessary).
by oil pressure opposing natural centrifugal ~wisting
moment of rotating blades and force of a spring tin
NOTE
McCauley propellers) to obtain correct pitch for the
selected engine load. Engine lubricating oil is supplied h is not necessary to remove spinner when
to a power piston in propeller hub through the propeller removing propeller assembly,
shaft. The amount and pressure of oil supplied (0-300
PSI) is controlled by an engine driven govemor. A. Remove 14 screws and fiber washers (1) from
Govmor oil pressure acting on a piston land spring) bulkhead assembly (2) and 4 screws (3)
aff spinner
increase propeller blade pitch, thus decreasing engine from each doubler plate (4). (Reference Figure 61-1).
RPM, As governor oil pressure is reduced, centrifugal
twisting moments and spring force on propeller blades B. Pull doubler plates from behind propeller.
decrease propeller blade pitch and increase RPM. to clear
Carefully pull spinner
C. dome (5) forward
Propeller overhaul shall coincide with engine overhaul, propeller and hub (6).
but interval between overhauls shall not exceed 1500
hours (McCauley) or 2000 hours (Hartzell). Refer to NOTE
propeller manufacturers’ overhaul manual for complete Forward spinner bulkhead (7) is riveted to
maintenance action and time limits, spinner dome and need not be removed except
for repair of spinner or bulkhead.
NOTE
Approved propeller shops ONLY are authorized 2. Propeller removal.
for overhaul or major repairs to these
propellers. Refer to Federal Aviation A. Loosen nuts (8) attaching propeller to engine
Regulations, Part 43, (FAR 43) and Federal crankshaft (9) propeller flange about 1/4 inch and pull
Aviation Agency Advisory Circular No, 43.13 propeller forward.
for the definition of major or minor repairs or
alternations and who may accomplish them,

h lo

1´•I

SPINNER DOME AND PROPELLER REMOVAL FIGURE 61 -1

61-00-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONN AIRCRAFT CORPORATION

OLDWILLWAYNE
NOTE NOTE
Nuts (8) will have to be backed off evenly so The guide pins in the propeller hub must be
that the propeller may be pulled forward aligned with respective holes in the crankshaft
(approximately 114 inch at a time until all nuts flange.
are disengaged from the propeller studs. As
the propeller is separated from the engine 5. Tighten nuts (8) evenly and work propeller aft on
crankshaft flange. Tighten bolts to 5565 ft. pounds on
crankshaft, oil will drain from the propeller and
engine crankshaft cavities. McCauley propeller, 60-70 R pounds on Hartzell
propeller.
B. Pull propeller from engine crankshaff (9). Use 6. Install spinner dome making sure fiber washers
clean rags to cover cavity in crankshaft and hub. are installed under all screw heads (1).
C. If necessary to remove the aft spinner bulkhead
NOTE
(2) (Figure 61-1), the spinner dome (5) must be
The tefion tape (12) on hub (6) should be
removed, refer to 61-00-10 (1). Remove bolts, washers
and nuts (10) which attach bulkhead to propeller hub checked for smoothness of tape layers and
that inner bulkheads (7) fits snug as spinner
flange. Remove aft bulkhead from propeller flange.
dome is being installed.
61-00-20 -PROPELLER INSTALLATION
7. Conduct operational and leak check on propeller
i. If aft spinner bulkhead was removed, re-install,
i"stallation prior to flight.
using bolts, nuts and washers in the reverse order of
removal. 61-10-00 PROPELLER ASSEMBLY
2. Clean propeller hub cavity and mating surfaces of No extemal lubrication is required on the M20K
propeller hub, propellers.
3. Lightly lubricate a new O-Ring (11), (Figure 61-1), Preffight inspection should be accomplished prior to
and the crankshaft pilot with cleanengineoil and install each flight to determine: if blades have been damaged,
O-Ring in the propeller hub. a any abnormal looseness is evident between hub and
blades or if there is any evidence of oil leakage.
CAUTION
Remove all rags or plugs placed in crankshaft 61-10-10 MINOR PROPELLER BLADE REPAIR
or hub ~uring propeller removal.
1. Minor nicks, dents and gouges may be dressed
out by approved personnel. Blend any nicks or gouges
4. Align propeller mounting studs with proper holes
into the leading edge with smooth curves or generous
in engine crankshaft flange and slide propeller carefully
(Figure 61-2). Repaint area to reduce
over crankshaft pilot until nuts (8) can be started
propeller studs.

~s,,

sr~-9
DRESSED A-A A

MINOR PROPELLER BLADE REPAIR FIGURE 61 2

61-00-20
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
61-20-00 PROPELLER CONTROLLING 7. Operate the propeller control from cockpit to
verify full travel of control arm in both directions, high
61-20-10 PROPELLER GOVERNOR RPM to minimum RPM stop.

CONTROL RIGGING NOTE

When propeller control n’gging is complete, check
i. Disconnect propeller govemor control rod. controls in cockpit to be sure there is 1/8 inch
A. Remove cotter pin, nut, bolt and washers from
cushion between control knob and adjustment nut
rod end at propeller governor control arm. on instrument panel. The control should not

B. Disconnect control rod from governor control bottom out when pushed full forward,

arm. CAUTION
2. Adjust control $rm spring to minimum tension Recheck safety wire, security and thread
which will return control arm to maximum RPM. engagement on all engine controls after
3. Push propeller control in cockpit full forward. Pull adjustment rigging or assembly.
control back approximately 1/8 inch and lock in this
position. NOTE
4. Place governor control arm against high RPM Vemier controls friction can be adjusted by
stop screw, loosening lock nut on back side of panel and
5. Adjust propeller control rod end to coincide with either tighten nut on front of panel to increase
the governor arm position. friction or loosen the nut to decrease friction,
6. Attach control rod end to governor arm and RetigMen lock nut on back side to secure cable to
replace cotter pin. panel.

61-20-90
PROPELLER GOVERNOR TROUBLE SHOOT1NG

TROUBLE PROBABLE CAUSE REMEDY

Leakage:Between control shaft and Damaged O-Ring. Replace with new O-Ring.
head.

Between head and body. Damaged head and body gas- Replace gasket.
ket.

Between relief valve plug and body. Damaged relief valve plug gas- Replace gasket.
ket.

Between body and base. Damaged body and base gas- Replace gasket.
ket.

Between governor base and engine Damaged governor mounting Replace gasket.
mounting pad. gaskef.
Loose govemor attaching nuts. Retighten nuts.

Warped engine mounting pad. Consult engine manual.

Inability to attain takeoff RPM during Wrong high-RPM governor set- Reset govemor extemal high RPM ad-
static ground run: ting. justment screw.

Incorrect system rigging. Adjust control system.

Low engine power. Consult engine manual.
Erroneous reading tachometer Calibrate or replace instruments.
or manifold pressure gauge.

Sticky pilot valve. Remove head and clean pilot valve with
crocus cloth. Maintain sharp pilot valve
land comers. Check for straightness of
pilot valve; a bent, replace valve.
RPM will not stabilize: Sludae in aovemor pilot valve Disassemble and clean.
or re~ief val~e.

Buns on pilot valve lands. Disassemble and clean with crocus cloth.

61-20-00
 SERVICE AND MAINTENANCE MANUAL M20K MCONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
PROPELLER GOVERNOR TROUBLE SHOOTING (con’r,)

TROUBLE PROBABLE CAUSE REMEDY

Backlash in governor control Rerig or adjust control system.

system.

Short control lever makina fine Rerig control system.

speed adjustment impossible.

Sticky relief valve. Inspect for burrs, and clean.

Erroneous reading tachometer. Calibrate or replace instrument.

Excessive oil leakage in engine Refer to engine manual.

transfer bearing.

High propeller friction. Refer to propeller overhaul manual.

Governor function upset by Repair engine for smooth operation.

malfunctioning engine.

Air trapped in propeller. Cycle propeller from MIN to MAX pitch

several times to purge air.

Sticky pilot valve. Remove head and pilot valve. Clean

aw~y sludge and varnish. Check speeder
spnng ends for proper settings.

Bent pilot valve. Remove head and replace pilot valve.

Excessive internal leakage in Check ngglng and make necessary part

govemor. replacements:

Excessive over-speeding: Wrong setting. Reset governor. Use test if available.

governor rig

Too rapid throttle opening. Advance throttle evenly and slowly.

Damaged or wrong gasket be- Install correct new gasket.

tween govemor base and en-
gine mounting pad.

Sticky govemor pilot or relief Disassemble, clean, and check for

valve, burrs.Replace bent pilot valves.

Erroneous reading tachometer Calibrate or replace instrument.

or manifold pressure gauge.

Inability to attain positive high pitch: High-RPM screw adjusted too Remove control arm and rotate one ser-
fai I caus~ng restiicted arm ration clockwise. Back out high-RPM
screw to required maximum RPM.(One
tum equals 2i~ RPM.)

Surging: Excessive propeller bladeseat Examine propeller hub for cause of fric-
friction, tion.
61-20-90
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
61-40-00 PROPELLER BALANCING Log book entries MUST be made when the propeller is
dynamically or statically balanced.
Balancing of the propeller by means of an approved
system is recommended to provide smoother opera- CAUTION
tion. The vendor system used should be an approved Place weights, washers or whatever balance
system and the procedures followed very carefully. The weights are specified specified by
at the locations
propeller may have been balanced with another vendor the balancing procedures. Be careful of placing
system previously and may require removal of old weights on spinner dome.
balance weights and /or other means of balancing.

61-40-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

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BLANK

61-40-00
 OLDWILLWAYNE

CHAPTER

POVVERP LANT
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

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CHAPTER 71

POWERPLANT

TABLE OF CONTENTS

CHAPTER SUBJECT PAGE

SECTION
SUBJECT

71-00-00 General 5
71-00-10 Engine Removal 5

71-00-20 Engine Inspection 8 Repair 5

71-00-30 Engine Installation 5

71-00-40 EnSineGroundOperation Checkout 6

71-00-50 Engine Set Up Procedure 6

25-0001 thru 25-0999
25-1000 thru 25-2012
25-2013 thru 25-TEA
71-00-60 Fuel injection system Maintenance 16
71-00-70 StarterSystem Maintenance 16

71-00-80 Engine Mi~dure Control Rigging 16

71-00-90 StarterTrouble Shooting 16
71-10-00 Engine Cooling 16

71-10-01 Engine Cooling, Cleaning, Inspei~tion Repair 17

71-11-00 Cowling Removal 17
71-11-01 TopCowling .........17
71-11-02 Bottom Cowling 17
71-12-00 Cowling Installation .........17
71-12-01 Bottom Cowiing 17
71-12-02 TopCowling .........17
71-13-00 Engine Cowl naps (25-0001-25-0999) 17
71-13-01 Cowl Flap Rigging 17

71-14-00 Engine Cowl Flap (251000 thru 25-TEA) 17

71-14-01 Cowl Flap Rigging 18
71-15-00 Cowl nap Position Indicator 18
71-15-01 Cowl Flap IndicatorAdjustment 18
71-20-00 Engine Mountsnnstallation 18
71-30-00 Fireseals ............19
71-60-00 Air Intakes ...........19
71-61-00 Air Intake Duct Replacement 19
71-62-00 Alternate Air Door Rigging 20
71-62-10 S/N25-0001 thru25-0780 20
71-62-20 S/N 25-0781 8 LaterAircraff 20

71-CONTENTS
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CHAPTER 71

POWERPLANT

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5´• &97
71-00-00
71-00-40 6´• 997
........´•´•7´•´•´•´•´•´•´•´• 997
71-00-50
.......´•´•´•8´•´•´•-´•´•´• 997
71-00-50
.......´•´•´•9´•´•´•´•´•´•´•´• 497
71-00-50
.......´•´•´•10´•´•´•´•´•´•´• 997
71-00-50
.......´•´•´•il 9-97
71-00-50
71-00-50 ........´•´•´•12´•´•´•´•´•’ 997

.........´•´•´•~3´•´•´•´•´• 497
71-00-50
....´•´•´•´•14´•´•´•´•´•´•´•´•´• 997
71-00-50
.........´•´•15´•´•´•´•´•´• 997
71-00-50
........´•´•´•16´•´•´•´•´•´• 897
71-00-60
71-10-01 .......´•´•´•17´•´•´•´•´•-´• 9-97

71-14-01 ........´•´•´•18´•´•´•´•´•´• 9-97

71-30-00 .......´•´•´•19´•´•´•´•´•´•´• 497

71-62-00 .....´•´•20´•´•´•´•´•´•´•´•´•´• 9-97

71-EFFECTIVTTY
i /2BLANK
 MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
71-00-00 -GENERAL WARNING
The M20K (S/N 25-0001 thru 25-0999) has a Teledyne Ground magneto breaker points.
Continental Motor (TCM) TS10360-GB or -LB sen’es
11’Disconnect engine ground strap.
engine installed. This six cylinder, 210 H.P., fuel
injected engine has a Roto-Master (Rajay) 12. Disconnect voltage regulator wires (optional).
turbocharger installed to give sea level power capability ´•13.Disconnect attemator and starter wires.
up to 15,000 feet density altitude and high altitude
performance up to 24,000 feet 14. Disconnect heater muff and exhaust tail pipe.
The turbocharger fixed waste gate valve can be ground 15. Disconnect fuel line at
engine fuel pump.
adjusted to obtain the proper critical altitude dun’ng 16. Disconnect turbocharger hose connections.
engine set up.
17. Shore up fuselage at tail skid using shoring stand
Aircraft S/N 25-1000 thru 25-1999 have a TCM
t,p,,,ttailfrom dropping after engine is removed.
TSIO-360-MB, 210 HP engine installed. This
installation utilizes an Airesearch Mn’able wastegate 18´• Attach hoist to lifting eye at top of crankcase.
turbocharger and a tuned induction system. Sea level Slightly lift engine to relieve weight. from engine
power can be maintained up to 23,000 feet density mounts. Remove engine mounting bolts.
altitude with a certified ceiling of 28,000 feet
19.Slowly raise engine. Be sure that all lines, hoses,
Production aircraft, S/N 252000 thru 252012 have a and wires are free.
TCM TSIO-360-MB7, 210 HP engine installed. This
installation is basically the same as the -MB installation. 71-00-20 ENGINE.INSPECTION REPAIR
TCM standardized their P/N callout for engines with dual
For specific engine inspection and overhaul
altemators. Retrofit to -SB configuration (see below) is
instructions, consult engine manufacturer’s overhaul
possible at owners discretion.
manual and senn’ce instructions.
Aircraft S/N 252013 thru 25TBA have a TCM
TSIO-360-SB, 220 HP engine installed. This engine 71-0030 -ENGINE INSTALLATION
configuration increases Manifold Pressure from 36 In. Hg. Reverse the engine removal procedure for installation.
to 39 In. Hg. and reduces RPhi~ from 2700 RPM to 2600
RPM. Sea level power can be maintained up to 20,000 i. Engine installation torque values are as follows:
feet density altitude with a certified ceiling of25,000 feet. A.Spark pIugs-300 to 420 inch Ibs.
71-00-10 ENGINE REMOVAL B. Hose ciamps-15 to 25 inch Ibs.
To assist in installation, identify and tag each part as it C. Engine shock mount botts-450 to 500 inch Ibs.
is removed. Plug or cap all lines, hoses, and fittings as 0~ 114 inch upper engine mount to fuselage
they are disconnected. botts50 to 70 inch Ibs.
1.Make sure that all cockpit switches are OFF.
E. #10-32 lower engine mount attach block to
2. Tum fuel selector valve OFF. fuselage-20 to 25 inch Ibs; 1/4 inch lower mount bolt
3. Remoc~ ellgine cc~Nlhg and baffles (See Section 71-10~ torque is 50-70 inch Ibs.
4. Disconnect battery ground cable. NOTE
5. Remove
Reinstall shock mounts in same position as
propeller (referto section 61-OD-10). they were or’ginally installed. Refer to
6. Drain engine oil sump. paragraph irl-20-00 for sequence of assembly.
7. Disconnect the following: 2. Re inspect to see that:
A. Vacuum line.
A. Propeller and spinner are properly torqued.
B. Cabin heat ducts (at engine). B. Engine mounting bolts are properly torqued.
C. Fuel vent lines (at firewall).
C. Engine controls are property rigged and safetied.
D. Oiltemperature bulb. (Recheck rod-ends for properthreadgn~p length.)
E. 011 pressure line. D. Oil drain plugs are tightened and safetied.
F. Manifold pressure line. E. Oil sump is filled to eight quarts.
G. Cylinder head temperature bulb. F. Spark plugs are tight and ignition harness is
H. Breather hose. properly installed.
8. Disconnect the following control linkage: G. Magneto ground wires are properly installed and
A. Throttle control. safetied.

B. H. Oil temperature bulb is tight and safetied.

Propeller governor control.
C. Mi~dure control. I. Oil pressure relief valve
plug is safetied.
9. Disconnect J. Cylinder head temperature connection is
ignition switch wires from magnetos. secure.

10. Disconnect pn’mer wires from primer valve and K. Starter cable connection is secure.
fuel flow wires from fuel flow transducer.

71-00-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
L. ABemator and standby generator (if installed) control at FULL RICH, and maintain RPM in the 1000
win’ng is secure. to 1200 RPM range during warmup and ground run.

M. Exhaust system is secure. A. Warmup engine until temperature indications

are normal. Monitorcylinder head and oil temperature
N. Vacuum lines and connections are secure.
instruments for overtemperature.
O. Fuel connedions are tight and pressure checked.
B. Check magnetos at 1800-2000 RPM with
P. Manifold pressure lines are tight.
propeller at high RPM blade angle. Switch
Q. Oil pressure lines are tight and pressure checked. ignition-starter switch from BOTH to LEFT to check
R. Fuel injection lines are tight and pressure checked, mag drop. Switch back to BOTH until RPM returns to
normal. Switch from BOTH to RIGHT and check mag
S. Oil filter is installed and secure. drop.Retum switch to BOTH. Mag drop should not
T. Induction manifolds exceed 150 RPM on either magneto (drop should be
are secure.
within 50 RPM of each other). A smooth drop off past
U. All lines, hoses, and wires are properly anchored, normal is usually a sign of too lean or too rich mi~dure.
V. Induction air filter is installed and secure. If no drop in RPM, check for open or broken P-leads.

W. Engine area is free of loose objects, tools, etc. 71-0050 ENGINE SET UP PROCEDURE
X. FOR TS10360-GB, IB, NIB, SE
Cowling is installed and secure (See Section 71-11).
Y. Cowl flap control rods are conneded. It is recommended that the TSIO-360-GB,-LB, -MB or
-SB engine installed on Mooney M20K aircraft be set
7190-40 ENGINE GROUND OPERATION up according to the following instructions in conjundion
CHECKOUT with Teledyne Continental Motow Operator’s Manual
1.Prestarting procedure (with aircraft headed into wind): and appropn’ate Service Bulletins CTCM SE M89-10
and subsequent issues). There are several steps
A. Tum ignition switch OFF.
required to ensure proper setup of engine in all
B. Check magneto ground connections. operating ranges.
C. Check engine oil level, i. Maten’alsTTools Required:
D. Check fuel quantity. A. Ground support equipment kit PIN GSE
all controls full range to check 030027-501.
E. Operate through
for binding. B. Miscellaneous hand tools. Required for
I=. Check baffles and cowling for security. adjustment and to disconnect or conned frttings and
hoses.
G. Open cowl flaps; check operation. Single cowl
flap on 25-1000 and ON. C. Safety wire.
H. Drain fuel sumps and gascolator; check for D. Ty-rap and installation tool.
sediment and water. E. Pressure gauge, with pressure source (sqeeze
I. Place wheel chocks and set parking brake, bulb) for leak checks pn’or to connection of calibrated
gauges to aircraft systems.
2.Starting procedure:
Set propeller govemor
A. control: FULL FWD.
2. Procedures for Calibrated Gauges Connections.
(HIGH RPM). A. Reference Figure 71-1 for location of
connections on the TSIO-360-GB or -LB engine and
B. Turn fuel valve ON.
Figure 71-4B for the -MB or -SB engine.
C. Set mi~dure control: FULL RICH.
B. On aircraft S/N 250247 thru 25-0835 there are
D. Open throttle FULL. Push primer for 3-5 firewall fittings installed which can be used for routing
seconds or use "HI BOOST" until positive indication of test gauge lines into the cabin. S/N 25-0836 and ON
fuel flow is obtained. Retard to 1/4 open. have an access cover on footwell. This cover can be
E. Clear propeller area. removed and a fitting adapter cover, Pn\l 050006-501,
installed during engine set up to allow hoses to be
F. Start engine. Checkoil pressure. If no oil
routed dun’ng adjustment procedures. The adapter
pressure is indicated within 30 seconds, shutdown cover is available thru Mooney Service Centers as part
engine and trouble shoot oil system. Refer to TCM of GSE 030027 kit of step 1, A.
maintenance publications for procedures.
C. Installation ofTest Gauges
G. Set throttle for idle at 900 to 1000 RPM for one
minute; then, advance throttle slowly to 1200 RPM for 1. S/N 25-0001 thru 25-0999 Remove cap from the
engine warmup. unmetered fuel tee on the right side of the throttle
3. Ground run and warmup. Always head aircraft into body. S/N 25-1000 3 ON Disconnect the unmetered
fuel line on n’ght side of the throttle body. Install a tee
the wind dun’ng warmup. Always select the high RPM
a"d Short length of hose to reconnect the line.
blade-angle setting when ground running engine.
Never idle for e~dended periods at low RPM (low RPM Install a 0 to 60 PSI calibrated pressure gauge using
will foul spark plugs). Always operate with m~ture suitable length of hose.

71-00-40
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE

FUEL FLOW
GAUGE CONNECTION
FUEL FLOW
MANIFOLD PRESSURE
GAUGE CONNECTION

IDLE
MIXTURE
CW-LEAN
j (VENT) CONNECTION
(~/8 PLUG) OR’T’FTG
WITH PRESSURIZED MAGS).
IDLE SPEED
CW-INC.
CCW-RICH RPY.
CCW-DEC.
RP.Y

r t

ii:.:

UNMETERED FUEL
PRESSURE GAUGE bROP, RPM
CONNECTION IDLE PUMP PRESSURE CW-DEC,
(REMOVE CAP) CW-INC.PRES CCW-INC,
CCW-DEC, PRESS.
FULL THROTTLE
FUEL FLOW
CW-DEC.FLOW
CCW-INC, FLOW r7’SIO -360-GB -LB ENGINES

ADJUSTMENT LOCATIONS FIGURE 71 1

NOTE
2. Remove plug from deck reference port. Connect
deck reference hose between this port and test fitting Back up the manifold pressure ftrewall
on right hand side of firewall. Connect another hose
connection with wrench to keep aircraft fitting
from cabin side of firewall fitting to the deck reference from becoming loose when connecting or
(fuel vent) port on test gauge, disconnectingMtings. This line is connected to
manifold pressure port on calibrated gauge.
3. Remove cap from manifold valve (ffow divider).
Connect fuel pressure hose between this port and
D. AII connedions should be leak checked with a
fitting on right hand side of firewall. Connect another
hose from cabin side of the fitting to pressure port on pressure bulb and gauge prior to connecting any
test gauge (metered fuel pressure gauge),
cabrated gauges to the required ports. Any pressure
drop shoukl be noted and leak repaired on either fuel or
4. Install tee fitting between manifold pressure line manifold pressure lines as necessary pn’or to installation.
and firewall fitting. Reconnect manifold pressure line to
firewall fitting. Conned test hose from tee fitting to test E. When ail hose connections are made for
fitting on right hand side of firewall. Connect another calibrated gauges, and ships gauges reconnected, a
hose from cabin side of this frtting to manifold pressure leak check with fuel boost pump on HIGH (throttle and
port on test gauge (calibrated MP gauge). mixture full forward) should be made. No leaks should
be in evidence while engine is being run for
adjustments.
71-00-50
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
F. When verification that no leaks are present the D. FULL POWER PERFORMANCE
boost pump should be turned on HIGH again to purge S~ 25-0001 thru 25-0999
the calibrated gauge hoses of air.
(Ground check). Check and adjust full power
3. PROCEDURE FOR ENGINE ADJUSTMENTS. performance as follows:
(Use the table, Figure 71-2B to record all data). (1)Setthrottle for 39.8 to 40.0 In. Hg. manifold pressure
and engine at 2700 +0/-25 RPM. Readjust the throttle as
NOTE required to maintain 39.8 to 40.0 In. Hg. manifold pressure.
The engine must be THOROUGHLY WARMED
(2) Adjust fuel flow to 143 145 Ibs. per hour
up forall tests. 19.1 PSI) (NASA Standard Day)
CAUTION (equivalent to 18.6
with m’udure controls in the full rich position. Clockwise
Watch for rotating propeller during adjustment.
adjustment of the screw decreases fuel flow reading;
one full turn will cause a 6.0 to 9.0 Ib. per hr. change
A. IDLE FUEL PRESSURE ADJUSTMENT.
(use 6.0 Ibs/gaV.). Record the difference in reading
between the calibrated fuel flow gauge and the AVC
Check and adjust idle fuel pressure as follows:
gauge for Mure reference.
(1) Back off the idle speed adjusting screw two
NOTE
(2) tums (CCW). Fuel now will vary with temperature changes.
(2) Start engine and warm up at 1500 to 1800 Temperature Mn‘ations from NASA STANDARD
.7 IbsJhr.
RPM until oil pressure is in the green are, cylinder head DAY temperature causes apporoximate~y
temperature is in the lower one-quarter of the green fuelflowchangewitheach 1 C.variation(minus
are, and oil temperature is 1600 to 1800 F. a hotter, plus if colder).
NOTE
(3)Maintain 700 25 RPM and set the idle fuel The fuel flow gauge used for -GB engine adjusb.nent
pressure to 6.5 .25 PSI by adjusting the idle pump is different from the gauge to be used for the IB,
adjustment screw (see Figure 71-1) for -GB 8 -LB nnB and SE eng’me adjustment; it is mandatory that
engines and Figure 71-4B for -MB 8 -SB engines) use ofthe correct gauge (or corrected dial face) be
located on the pump body centerline: used during adjustment procedures,
B. IDLE MIXTURE E. FULL POWER PERFORMANCE (-MB engine)
S/N 25-1000 thru 25-2012
Check and adjust the idle m’udure as follows:
(Ground check) Check and adjust full power
(1) Operate engine at 1500 to 1800 RPM until performance as follows:
cylinder head temperature is in the lower one-q_uarter of
GREEN are, and oil temperature is 1600 to 180P F. (1) Operate engine until oil temperature has
reached a needle width past center of GREEN are
(2) Reduce engine speed and stabilize it at 700 (approx 1800. F.). Slowly, but positively advance
25 RPM. throttle control to full power stop, ensure 2700 25
RPM, and note manifold pressure. Adjust manifold
(3) Slowly, but positively, move mixture control pressure adjustment to maintain 35.8 to 362 in. Hg. at
from full rich to idle cut-off. Engine speed should
2700 RPM+I- 25. Clockwise adjustment decreases
increase 50 RPM 25 RPM) before beginning to
manifold pressure; one full tum equals approximately
drop toward zero. 1.0 in. Hg.(See Figure 714B).
(4) If engine speed increase is less than 25 RPM, (2) Adjust fuel flow to 130-135 IbsJhr.(NASA STD.
adjust idle m’udure adjustment to enrich the mi>dure. If DAY) with mbdure control in full rich position. Clockwise
engine speed increase is more than 75 RPM, adjust adjustment of screw decreases fuel Pow reading; one full
idle ml>dure (Figure 71-1 for -GB 8 IB and Figure t,, will cause a 6.0 to 9.0 IbJhr. change. Record
71-4B for -MB 8 SE) to lean mi>dure. difference in reading between calibrated fuel flow gauge
and aircraft gauge for future reference.
(5) Recheck as required to insure idle mi~dure is
adjusted within limits specified above. (Recheck idle F. FULL POWER PERFORMANCE (-SB engine)
pressure per paragraph 3.A. (3) above. srm 25-2013 thru 25-TEA

C. IDLE SPEED S/N 252001 dim 25-2012 may be retrofitted to -SB

configuration by compliance with Mooney RetroM Kit.
Check and adjust idle speed as follows:
(Ground check) Check and adjust full ~power
(1) Operate engine at 1500 to 1800 RPM until performance as follows:
cylinder head temperature is in lower oneguarter of ~1) Operate engine until oil temperature has
GREEN are, and oil temperature is 1600 to 1800 F. reacnea a needle width past center of GREEN are
(2) Reduce engine speed and stabilize it at 700 (approx 180". F.). Slowly, but positively advance
25 RPM. throttle control to full power stop, ensure 2600 25
RPM, and note manifold pressure. Adjust manifold
(3) Adjust idle speed adjusting screw until contact pressure adjustment to maintain 38.8 to 392 in. Hg. at
is made with throttle arm stop. See Figure 71-1 for 2600 RPM 25. Clockwise adjustment decreases
-GB 8 -LB engine and Figure 71-4B for -MB 8 SE manifold pressure; one full tum equals approximately
engines). 1.0 in. Hg.(See Figure 71-4B).

71-00-50
MOONC/ AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
fuel flow per Section 71-00-60, L (2) CAUTION
with control in full n’ch position. Cloclcwise s by turning knob.
adjustment of screw decreases fuel flow reading; one full
NOTE
tum will cause a 6.0 to 9.0 IbJhr. change. Record
difference in reading between calibrated fuel flow gauge Any vemhr control which tends to creep can be
and aircraft gauge for Mure reference, tightened by loosening housing nut in back of
panel and tightening face nut at pilot side of panel.
G. RECHECK. Recheck as follows:
(3) Adjust controls by adjusting rod end on the
Recheck idle settings as
(1) specified in A, B and forward end of the control. If additional adjustment is
C above and adjust as required.
required the control arm may be repositioned to adjust
100 percent power fuel flow as the throttle or m’udure. Additional adjustment may be
(2) Recheck
25-0001 thru 25-0999 and E for obtained on the prop govemor by removing the safety
specified in D for
25-1000&ON, wire thru the six screws on the govemor head and
loosening those screws. After loosening the screws
(3) Recheck full power manifold pressure as rotate governor head to obtain required adjustment.
specified in E for 25-1000 ON.
3 (4) Tighten all screws and resafety.
H. GROUND CRITICAL ADJUSTMENTS
J. PROPELLER RPM ADJUSTMENT. Run engine
S/N 25-0001 thru 25-0999
and.verify that propeller govemor will allow engine to
(1) Set altimeter to 29.92 inches and record operate at 2700 RPM. Adjust forward stop screw on
pressure altitude. With engine operating at 2300 RPM, govemor head as required to obtain required RPM.
m’udure control FULL RICH proceed as follows: Recheck control for required cushion after setting RPM.

(2) Reduce engine speed to 2000 RPM with the K FLIGHT CHECK
propejler control. S/N 25-0001 thru 25-0999

(3) Set throttle FULL OPEN. The following checks shall be performed in flight:
(4) Using propeller control, increase engine (1) Set altimeter at 29.92 In. Hg. and record
speed until 40 In. Hg. .2 manifold pressure pressure altitude on data table, (Figure 713). Remove
obtained. Engine speed should be within ground critical calibrated gauges prior to check flight. Aircraft is not
limit band (Figure 71-4). If engine RPM is outside approved for flight with these gauges installed.
these limits readjust turbocharger by-pass valve. (One Reconnect the hoses, fRtings, etc, required to connect
tum in equalsappro~a’mately 100 RPM reduction). the ships gauges. Utilize recorded delta for the fuel flow
Safety wire before flight. (9 threads showing (fine thds~ gauges dun’ng this flight check.
is starting point if no reference is known) (2) Wrth full rich mixture, throttle at 40.0 In. Hg.,
CONTROL 2700 RPM and 96 2 knots IAS climb until 40.0 In.
I. CHECK AND ADJUST ENGINE
RIGGING as follows: Hg. manifold pressure can no longer be maintained,
this is termed critical altitude. Record pressure altitude,
(1) Operate each control thru its full range of OAT and fuel flow each 2000 feet until critical altitude is
travel and check that it operates smoothly and contacts reached. Fuel flow shall be 135 to 145 Ib. per hour
the stops at each end oftravel. (23.0 to 24.7 GPH) dun‘ng the entire climb at NASA
Standard Day temperature.
(2) Check each control at instrument panel for.06
to .12 cushion with the control pushed full forward.

71-00-50
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
ENGINE SET-UP DATA SHEET FIGURE 71 2

FOR MECHANIC’S USE DURING ENGINE SETUP PROCEDURES

DATA DATE DATE DATE DATE DATE

IDLE PERFORMANCE
Umn Fuel Press
.25 PSI
I~ 6.25
00RPM)
7~
Idle Mi>dure Rise
(50 25 RPM)
700 RPM

Idle Speed
(700 25 RPM)

FULL POWER PERFORMANCE

MP (SHIP~ST)
RPM 0 /-25)
F/F SHIP

F/F TEST IbsJHr)

GROUND CRITICAL

OAT

PRESSURE ALT. (29.92 Hg)

DENSITY ALT.

RPM

FLIGHT CRITICAL

OAT

PRESSURE ALT. (29.92 "Hg)

*F/F(SHIPTTEST)~ IbsJHr)
DENSITY ALT.

Use coned fuel flow gauge for-GB or -LB, or-MB or SE engines.

CAUTION
Use correct RPM, Fuel Flow and fuel flow gauge for: -GB or -LB or -MB or SE engine.
Referto SECTION 71-0050 for specific engine set up procedures.

71-00-50
10
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
FLIGHT CRITICAL DATA SHEET FIGURE 71 3

FOR MECHANIC’S USE DURING ENGINE SET-UP PROCEDURES

PRESSURE OAT TIT FA NIP RPM C,AI... INST REMARKS

ALTITUDE F/F MP RPM SHIP INST.

Temperature variations from NASA Standard Day temperature causes approximately .7 Ibs. per
hour fuel now change with each 1 degree C. variation (minus if hotter, plus if colder). The critical
altitude will vary on each flight depending on density altitude as shown on (Figure 714), 500 feet
tolerance.

71-00-50
11
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE

Grolmd 0101011 E~tampb F~ght Emmpls iT::

F ;1
Tsmg; ~ODC O.*.T.
T´•mp:d~C O.n-r.
1000 Ft. Prssltus A~t. Rsachsd
Pres~urs :s
Pqlmt´•atoDanyA~. d: 1150’ ntlr’~Bla.p.: IS.(WR. (WLthlnB~d)
i~/ Dendty A~toQ 11 1I, 050 n.
:1
RP.H. dSt~tic): 2250
Rslult 11 WIlMn B~d
i
iiii~ -I.ii~ t~
1~

14

Fl

i
Irr~ i i 1 I rr-i i ~I LILLLI
IY~ii
~1

nl~W1 tipr (r

it

O -40 -10 -10 -10 O 10 10~0 I0 00

2 26001 i~
Ic..ri II

tt

ENGINE RPM GROUND/FLIGHT CRITICAL CHECK CHART FIGURE 71 4

CTS10360-GB -LB ENGINES)

71-00-50
12
 OLDWILLWAYNE

i´• .~i
8
Prcrf
I~C-
4 ~r?

I ib ~f71
.Z tie,:
I~•´:61 t. :e fr ti ~´•1 i ,a~ a‘~

54~
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iT1%: ;lc~ 7
g ´•c´•I~
C k:- pg
’O

YK 61
m ;iii
~.2´•´• -´•,n.:´•;/
L1 Z!,’s‘;~ti´•
A!7.
;i: B

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o

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T´• 11 .s´•e
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Y´•;

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o
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sye IC*ec’’’
;r B~lt
mn
n
´•Bi
I Fj
P m
m
5
r
,7 1
f3

2. DECK REF. PORT

g, FUEL MANIFOLD VALVE (TEST FTTflJG OI~I AF~ 910E) m

4, IDLE 80880 AD3082MENT 8CREW

6. IDLE FUEL PRESSURE ADJUSTMENT (c,w. INCREASE)
8. IDLE MIXTURE tC,w, LEAN) m

4( 7. FULL POWER PUEL FLOW ADJUSTMENT(.Clw, OEORE~8E)

b FULL POWER MANIFOLD PRESSURE ADJUSTMENT (o,v~. DECREASE) Z

-.8 F
00 1 I r
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
CRITICAC ALTITUDE CHART

26000

o
~pq
~o.

o
24000 8

22000

20000

18000

c
O
w
w 16000

Y Y X /r /I /r\~ X Y~

P
14000

6PL
8
12000

P I/ I/ V y y y My vr I/ I~P,
ioooo

soool/l/-l/ I/ y y y y/ y I/ I~p

6000 r n

4000

4:

2000

O -50-40 -30 -20-10 1’0 20 32) 4’0 SO

OAf DEGR~ES C

CRITICAL ALTITUDE CHART CTSIO-360-MB ENGINE) FIGURE 71 4C

71-00-60
14
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE

CRITICAL ALTITUIIE VARIATICM WlfH AMBIENT TEMPERATURE

41

t~P/
a a a a 4) a 3) a, a

MT DECBES C

1.Aircraft in climb configuration 96 KIAS, 2600 RPM (+0/-50)

Record below: Pressure Altitude, OAT, and Fuel Flow when MAP decreases below 38" Hg. at full throttle.

.Enter point on chart at Pressure Altitude and OAT. If point is within the depicted altitude band, critical altitude is
within tolerance. If outside the altitude band, the engine will have to be retrimmed.

CRITICAL ALTITUDE REPORT

FLT 1 FLT 2 FLT 3 FLT 4 FLT 5

Altitude (Feet)
Air Temp (C)
Flow (GPH)
Date

Aircraft Serial Number

Aircraft Registration Number

CRITICAL ALTITUDE CHART CTSIO-360-SB ENGINE) FIGURE 71 4D

71-00-50
15
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
K. FLIGHT CHECK Temperature Mn‘ations from NASA STD. DAY
S/N 25-0001 thru 25-0999 (conS~ TEMPERATURES causes approx .7 IbsJhr. fuel flow

(3) If cha"ge with each 10 C. Mriation, minus if hotter, plus if

a discrepancy in critical altitude was noted,
Colder. The critical attitude will vary on each flight
adjust~the exhaust by-pass valve. CTuming the e~aust
by-pass valve screw IN one full tum (CW) will increase depending on density attitude as shown on Figure 71-4C
1500 ft. tolerance. If a discrepancy in critical altitude
the critical altitude approximately 1000 feet).
was noted, check the engine indudion system for leakage
CAUTION or blockage or turbocharger for malfunction, until problem
Adjustment in excess of one turn should not be is found. indication should be well over the red line. DO
made, If major adjustments are required to NOT MCEED 40.0 In. Hg.
obtain published criticala~titudes, troubleshoot M. CLEAN UP
engine as to exhaust leaks, turbo and engine
condition. All adjustments are interrelated, After all flight checks and adjustments are complete,
engine must be at operating temperatures, and condud a leak check of all connedions. SM 250001 thru
adjustments should be rechecked after final 25-0999 safety wire the e~aust by-pass screw and
set-up to detennine all values are as specified. check nut to the by-pass screw housing. Reconned and
NOTE secure the landing light wire connedions on bottom cowl

h induction or exhaust system leak is and reconned the cowl flap rod ends.
suspected, 3 to 5 PSI can be applied to either
’11-00-60 -FUEL INJECT(ON SYSTEM
system and check with soap solution.
MAINTENANCE
Re-fly aircraft to ven’fy cn’tical altitude settings. For specific injection system inspection and overhaul
Adjustments of critical altitude in excess of 500 feet instructions, consult engine manufacturer’s overhaul
may require retn’mming of fuel flows at 100% power. All manual and service instructions.
adjustments to fuel flow shall be made per paragraph
71-00-50, 3, A thru F. 3.). 71-00-70 STARTER SYSTEM
(4) Wnh full n’ch m’ucture, 2700 RPM, 96 knots IAS MAINTENANCE
airspeed, and 1000 to 3000 feet pressure altitude, Insped and service starter per TCM Service Instrudions.
check the operation of the manifold pressure relief
valve. Slowly advance the throttle to the wide open CAUTION
The manifold pressure should stabilize Do not operate starter in excess of 30 seconds;
g~;tfk0e";l
42.0 and 44.0 In. Hg., there should be no loss allow cooling time before re-engaging,
of power, and the fuel flowindication should be well
over the red line. DO NOT U(CEED 40.0 in. Hg 71 -00-80 ENGINE MU(TURE CONTROL
manifold pressure for more than TEN SECONDS. RIGGING

L. FLIGHT CHECK 1. Disconnect m’udure control.

The following checks shall be performed in flight: A. Remove cotter key.
S/N 25-1000 thru 25-TEA B. Remove nut, bolt, and two washers from clevis
(1) Set altimeter at 29.92 in. Hg. and record pressure and mi~dure control arm.
altitude on data table (Figure 713). Remove calibrated 2. Reconnect mi>dure control.
gauges pn’or to check flight. Aircraff is not approved for
A. Reverse disconnect procedure to reconned
flight with these gauges installed. Reconned hoses,
mb<ture control.
fittlngs, etc, required to conned the ships gauges. Util’ne
recorded delta for the fuel flow gauges dun’ng this fight. 3. Adjustment of mixture control arm.
-S~N 25-1000 thru 25-2012 (-MB ENGINE) A. Loosen locknut on control rod end and adjust
Wnh full n’ch mi~dure, full throttle (36´•0 control arm rod as required.

27I?J~
in. Hg.),
RPM and 96 2 KIAS climb until 36.0 in. Hg. B. Check for full travel.
can no longer be maintained. This is termed critical
C. Check for proper thread grip.
altitude. Record pressure altitude OAT and fuel flow
each 3000 ft. until critical altitude is reached. Fuel flow D. Secure locknut.
shall be 125 to 135 Ibs./hr. (21.5 to 23.2 GPH) dun’ng
the entire climb to critical altitude. 71-0090 STARTER TROUBLE SHOOTING

S/N 25-2013 thru 25-TEA (-SB ENGINE) See Section 24-39-04 for procedure. TCM
MAINTENANCE AND OPERATORS MANUAL should
Wnh full rich mixture, full throttle (39.0 in. Hg~,
26Sb RPM and 96 2 KIAS climb until 39.0 in. Hg.
be consulted.

can no longer be maintained. This is critical altitude. 71-10-00 -ENGINE COWUNG

Record pressure altitude OAT and fuel flow each 3000
ft. until critical altitude is reached. Fuel flow shall be The engine cowling is in two sections. The lower cowl
151 to 157 Ibs./hr. (25.5 to 26.5 GPH) during the entire c0"tains the Idnding lights (250001 thru 25-0999) and
climb to critical altitude, cowl flaps. The induction inlet ducts are also located on
the lower cowl. The top cowl contains the oil filler
CAUTION access door. Quick-disconnect, 1/4 tum fasteners
Use correct fuel flow gauge for the NIB 8 SE attach the induction duct panels to the cowl and the
engine (same as -LB engine) versus -GB engine, upper and lower cowling to the aircraff.

71-00-60
 MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
71-10-01 -ENGINE COWUNG CLEANING,
INSPECTION a REPAIR A *djusling Rod
Clean cowl by spraying with solvent (PS~61 or equivalent)
8 CG*I Ibp I)u~h ~ilh
and wiping dean. After deaning, inspect cowling for dents,
cracks and loose fasteners. Repair defects. ´•ngin cowling

71-1190 -COWLING REMOVAL

71-11-01 -TOP COWUNG

i. Remove two screws from top cowling on inboard
side of LH 3 RH engine cooling air intakes:
2. Remove one screw from both LH 3 RH sideoftop
cowling, forward and outboard. Then unlatch seven
cam locks on each side.
3. Unlatch seven cam locks on the aft edge of the
top cowling just ahead ofwindshield.
4. Carefully lift top cowiing off. ENGINE COWL FLAP RIGGING (25-0001/25-0999
FIGURE 71 5
71-11-02 -BOTTOM COWLING
i. Disconnect landing light wiring connectors near 71-12-02 -TOP COWLING
firewall (S/N 25-0001 thru 25-1224).
i. The top cowIing is installed h re\Rrse sequence of remoMl.
A. Cut ty-raps secun’ng insulating tubes overknife
disconnects. 71-13-00 ENGINE COWL FLAPS
B. Slide
(25-0001 thru 25-0999)
insulating tubes upwire hamess toward firewaa
The cowl flaps are activated OPEN and CLOSED by a
C. Disconnect knife disconnects and slide scissors~dler arm mechanism connected to the cowl
insulating tube back over disconnect, flaps. A push/pull knob on the console is used to open or
2. Disconnect both cowl nap control rod ends at close cowl flaps. Cowl flaps are either OPEN or CLOSED
quick disconnect fitting (1) (Figure 715) located on (two positions) while airc~aft is on the ground; however,
cowl flap brackets (S/N 25´•0001 thru 25-1224). there is an intermediate "trail position" in flight. The cowl
flaps will seek an aerodynamic position between
NOTE CLOSED and OPEN when push/pull knob is pulled out
Reach up through owl flap opening to This can be used for cooling if needed dun~ng cruise.
disconnect cowl flap control rods.
71-13-01 COWL FLAP RIGGING
3. Unlatch 2 cam locks located on bottom cowling
between cowl flaps (S/N 250001 thru 25-0999).
(25-0001 thru 25-0999)
i. Adjust both the left and right cowl flaps so that in the
4. Unlatch 8 remaining cam locks (4 on each side) closed position the outboard trailing edges are flush with
on bottom cowling while supporting cowl.
the lower engine cowling, (Figure 715). Maintain .06 -.12
NOTE in. "cushion" on cowl flap control at the instrument panel
S/N 25-0001 thru 25-0999 have two cowl flaps, whe" cowl flaps are closed. The scissors should be in an
S/N 25-1000 thru 25-TEA have one center cowl Ove’ce"ter position when cowl f~aps are closed.
flap. Camlock locations vary slightly from NOTE
aircraft with two cowl flaps. For improved cooling during summer months
5. and warm temperature operations, cowl flaps
Carefully lower cowling clear of spinner and
remove from aircraff. may be rigged to have a .25 max inch gap at
"B" when at the closed position.
71-12-00-COWLING INSTALLATION
71-14-00 ENGINE COWL FLAP
NOTE (25-1000 thru 25-TEA)
Check condition of tape on firewall flange The single cowl flap
is activated OPEN and CLOSED
where cowling will rest. Polyethylene tape, P/N
by an idler connected by a push-pull rod to the
arm
5421(UHMW) (3M), 1 inch wide is actuator arm on a geared motor. A cowl tlap switch,
recommended. This will decrease streaking located on the cockpit console directly under the
during wet weather operations, m’ucturecontrol, activates the geared motor. The switch
has three positions: center (OFF),
71-12-01 -BOTTOM COWLING up (CLOSED) and
down (OPEN). The cowl flap may be positioned at
any
i. The bottom cowling is installed "first" in reverse angle by selecting the switch either up or down until the
sequence of removal. desired position, as shown on the position indicator,
has been reached. Then return switch to the center
CAUTION (OFF) position. Limit switches, which are not
Be sure landing lights and cowl flaps are adjustable, prevent the cowl flap from exceeding the full
connected prior to installation of top cowling.
open or full closed position.

71-10-01
17
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE

COWL FLAP
INDICATOR

i
11 /"4~4

VIEW LOOKING
INBOARD AT CENTER

’i/AJ j
CONSOLE CONSOLE FROM
RIGHT SIDE

COWL FLAP INDICATOR RIGGING

COWL FLAP RIGGING (25-1000/25-TEA) FIGURE 71 6 (25-1000MS-TBA) FIGURE 71 7
71-14-01 COWL FLAP RIGGING 71-16-00 ENGINE COWL FLAP POSITION
(25-1000 thru 25-TEA) INDICATOR (25-2000 thru 25-TEA)
The cowl flap is rigged for a flush contour between the A cowl flap position indicator is located on the lower
cowl flap trailing edge and cowling, when in the closed console adjacent to the cowl flap switch. This indicator
position( Fig. 71-6). is operated eledn~cally through a potentiometer
co""ected to cowl flap actuator shaft.
1, Wdh cowl flap open, adjust 2 linkage rods (1), Figure
71-6, from idler arm to cowl flap to maximum length. 71-16-01 COWL FLAP INDICATOR ADJUSTMENT
2. Close cowl flap. Measure distance between cowl 1. Position cowl flaps in closed
position.
flap trailing edge and cowling. 2. Adjust cowl flap potentiometer on aircraft, to
3, Open cowl flap. Readjust linkage rod, decreasing illuminate top bar in display.
length by above measured amount. 3. Position cowl ftaps to OPEN position.
4. Close cowl flap. Verify that cowl flap is not outside 4. Adjust R1 on AID board, if necessary, to illuminate
cowling contour nor that cowl flap is preloaded against bottom bar on display.
nose gear box. Readjust as required.
5. Repeat steps 2 through 4, until no further
71-15-00 COWL FLAP POSITION INDICATOR adjusment is required.
(25-1000 thru 25-1999) 6. Cycle cowl flap system to verify proper movement
of indicator.
A cowl flap position indicator is located on cockpit console
directly under Flap Switch. Indicator is operated by a 11-20-00 -ENGINE MOUNTS
cable connected to the actuator arm and routed to a
bellcrank arm located behind the console. This bellcrank The M20K engine mount is a welded dyna-focal bed
arm is then connected by another cable to the indicator. type mount assembly of chrome-moly, 4130 steel.
The shock mounts are installed in a specific sequence
71-15-01 INDICATOR ADJUSTMENT for proper dampening of engine and propeller power
(25-1000 thru 25-1999) pulses. Effective production aircraff S/N 25-0781 and
ON and for Spares replacement on prior aircraft, (a
1.Position actuator and indicator in down position.
complete set required) the following sequence of
2. Hold bellcrank arm (1) in position shown in assembly must be observed:
Fig,71-7; tighten both wire end clamps (2). i. Assembly sequence for 600376-503, -505 and
3. Cycle cowl flap actuation system a minimum of five -507 installation.
times to verify free movement of indicator. Adjust push-pull 2. All positions are looking from
wires at bellcrank,
cockpit forward and
as necessary for proper indicatortravel. down from top of engine.
4. Install cotter pins in pivot nuts. 3. Al assembly sequences are from bottom to top of stack

71-14-01
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
ENGINE MOUNT INSTALLATION/STACK-UP 25-0781 thru 25-1 999 5 Spares Replacement 25-0001 5 ON

LEFT FRONT (507) RIGHT FRONT (505)

Bolt -AN7-46A Bolt -AN7-47A

Washer -AN960-71 6L Washer -AN960-716
Heat Shield -600394-1 Heat Shield -600394-1
Lord Mount J9612-43 Lord Mount J9612-43

Engine Sequenced in at this point (LH 5

Mount RH)
600364-005 Spacer- A~t. to Y1374&532
LEFT REAR (503) R(GHT REAR (503)

J10931-2 Spacer, Bolt -Yi 6440-2-497

Spacer, Bolt
Lord Mount J9612-42 Lord Mount J9612-44
Heat shield -600394-3 Washer, Special -Yi 374&532
Heat Shield -600394-3

Engine is Sequenced in at this point (LH 5 RH)

Washer -AN96Q716L Washer -AN960-716

Nut -AN363-720 Nut -AN363-720
Bolt -AN7-47A Bolt -AN7-47A
Washer -AN960-716 Washer -AN960-716
Heat Shield -600394-1 Heat Shield -600394-1

Washer, Special -Y1374&532 Washer, Special -Yi 3748-532

Lord Mount ’J9612-44 Lord Mount -J9612-44

Engine Mount Sequenced in at this point (LH 5 RH)

Spacer, Bolt -Y16440-2-497 Spacer, Bolt -Y16440-2-497

Lord Mount J9612-43 Lord Mount J9612-43
Heat Shield -600394-3 Heat Shield -600394-3

I------------
Engine is Sequenced in at this point (LH 5 RH)

Washer -AN960-716 Washer -AN960-716

Nut -AN363-720 Nut -AN363-720

TORQUE BOLTS TO 450 500 INCH LBS.

f
600364-005 Spacer Alt. to Yi 374&532

7130-00 -FIRESEAIS side of the lower cowling. The cowling duct joins a
flexible duct attached to the filter housing 5 routes
Firewall fireseals and grommets, if removed and replaced
induction air through the filter and turbocharger
for any reason, should be sealed after routing the cable or
wire assembly from the engine compartment into the
housing, then to the engine.
cockpit area. After installation cover cable or wire and The air intake system includes an altemate air intake system
grommet undemeath the fireseal with Coast Pro-Seal 700 that is manually operated on SM 250001 thru 250780 and
on engine side offirewall. automatically operated on 250781 and on. A manual
operation contro~ is provided on the later ainxaft also.
71-60-00 -AIRINTAKES
NOTE
The engine cooling air intakes and exits are calculated Alternate induction air hose should be secured
for optimum .cooling requirements and minimum drag. with clamps to avoid contact with engine mount.
Normal engine operating temperatures are at the Reference M20K IPC Figure 71-00-00 71-60-00.
optimum to facilitate engine efficiency.
The engine induction air intake is a fiberglass, 71-61-00 -AIR INTAKE DUCT REPLACEMENT
insulated, duct that picks up impact air at the right hand 25-0001 thru 25-0999
air intake and routes it through the air filter to the When the air induction duct must be replaced it t
turbocharger housing and eventually to the engine essential that the duct be positioned exactly as the
(25-0001 thru 25-0999). original installation to prevent any interference with the
S/N 251000 thru 25-TEA aircraft induction air is cowling or the exhaust system. Reseal duct to baffle
provided through a NACA inlet 5 duct on the right hand with Proseal 700 sealant.

71-30-00
19
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
71-621)0 -ALTERNATE AIR DOOR RIGGING 1. Clamp housing of altemate air intake control
assembly at the bracket on altemate air box so housing
71-62-10 S/N 25-0001 thru 25-0780 extends only .13 inches beyond clamp. This will allow
maximum travel of altemate air door lever assembly.
(Unless modified IIAMISI M20-71).
2. The altemate air lever assembly should be rigged
1. Adjust actuating lever arm, n’ding in the door slot,
so .06 to .13 gap remains when the altemate air box
to be in the detent of the slot when closed.
door is held dosed with the magnetic catch assembly.
2. There should be 1/8 inch cushion between the control 3. The annunciator light switch is mounted on the
cable knob and the panel in the cabin atthis position, altemate air box and should be n’gged to extinguish the
3. An electn’cal switch on the cockpit control light with bottom of door .25 in. (max) from full closed.
activates the "Alt Air" annunciator light on A/C 25-0001 4. Check opening force of door. It should take
through 25-0780. between 4.5 and 7.5 pounds to open the door. Take
readings at approximate location of the magnetic catch
71-62-20 S/N 25-0781 LATER AIRCRAFT assembly.
(Inciudes earlier AIC modified IIAIW 5. Comply with SI M20-83 to inspect and replace
st M20-71) (REF. FIG. 71-8) magnet.

FWD
OUJBOARD

REQ’D. TO ALLOW
FOR MAX TRAVEL
O~ LEVER PSSY.

to

,06 In,
.13 In,

~3 In,

GAP REQ’D. BRWEEN

ACTUATOR ROD h
DOOR ASSY. WTTH
CONTROL KNOB IN
CLOSED POSmON
M20-83 installs a bolt inplace of the safety wire
secure magnet.

ALTERNATE AIR DOOR RIGGING (25-0781125-TEA) FIGURE 71 8

71-62-00
20
 OLDWILLWAYNE

CHAPTER

ENGINES
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 72

ENGINE

LIST OF EFFECTIVE PAGES

PAGE DATE
CHAPTER
SECTION
SUBJECT

1/2BLANK 9-97
72-Effedivity/Contents
3´• 9-97
72-00-00
4´• 897
72-00-00

TABLE OF CONTENTS

SUBJECT PAGE
CHAPTER
SECTION
SUBJECT

General 3
72-00-00

72-EFWCONTENTS
?/2BLANK
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
-GENERAL (-MB), Manual No. X30671 (-SB) and Ovemaul and
72-00-00
Maintenance Manual No.’s X30030A (-GB, -LB, -MB) or
Refer to Teledyne Continental Motors CTCM) X30672A (-SB) for detailed information.
Maintenance and Operators Manual No. X30536 (-GB),
Manual No. X30571 (-LB), or Manual No. X30564

72-00-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

OLDWILLWAYNE

BLANK

72-00-00
 OLDWILLWAYNE

CHAPTER

ENGINE FUEL
AND CONTROL
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 73

ENGINE FUEL SYSTEMS

LIST OF EFFECTIVE PAGES

PAGE DATE
CHAPTER
SECTlON
SUBJECT

1RBLANK 9-97
73-Effedivity/Contents
3. 9-97
73-00-00
4. 497
73-31-01
5. 9-97
73-31-01
6´• 9-97
73-31-02
7´• 997
73-31-03
8´• 997
73-31-06

TABLE OF CONTENTS

SUBJECT PAGE
CHAPTER....
SECTION
SUBJECT

General 3
73-00-00
3
73-30-00 Indicating
73-31-00 Fuel Flow System-General System bescription 3
Panel Mounted Instrument 3
73-31-01
Fuel Flowi~ansducer 6
73-31-02
General Operating Procedures 7
73-31-03
Test Function 7
73-31-04
73-31-05 Troubleshooting SDIcHoskins~
Fuel Management Systems 7

73-3;-0$ Troubleshooting Tru-Flow 1 (Alcor)

Fuel ManagementSystems 8

DNck Transducer Test Procedures 8

73-50-00

73-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
73-00-00 -GENERAL continuous consumption or 78 GAUHR Intermittent
consumption. CTake off power).
The engine and its accessories are certificated under
7331-01 -PANEL MOUNTED INSTRUMENT
Teledyne Continental Motors CTCM) Type Certificate.
Refer to TCM Operators or Ovemaul Manual for The panel mounted instrument contains all system
specific instructions. electronics and may be divided into groups.

73-3090 -INDICATING OHOSKINS) SYSTEM

1. FT-101
A. DISPLAY The display usesone mini lamp and
S/N 25-0001 thru 25-0612 have an analog readout four seven segment incandescent digits that are fully
style fuel flow indicator which receives its signal from a sunlight readable and dim automatically dun~ng night
transducer (Mooney SI M20-48 descn’bes adjustment ,,d I,, light flight conditions.
of Aerosonic analog F/F gauge). SIN 250001 through
B. MICROPROCESSOR The microprocessor
S/N 25-0171 originally had a pressure transducer
installed. SI M20-49 described a recommended contains a crystal controlled oscillator that controls all
modification to a turbine type transducer and matching timing and computing functions for precise fuel flow
indicator. This turbine transducer has been the and totalizing computations.
production configuration since S/N 25-0172, however, C. POWER SUPPLY The power supply is a high
the indicators have varied. S/N 25-0613 3 ON, the speed switching regulator type for optimum efficiency
standard indicator has been a digital readout type. and the lowest possible power drain on the aircraft
Digital indicators have been optional equipment for all electrical system.
aircraft up to S/N 25-0613.
D. MEMORY- the microprocessor continuously
All aircraft should now have the turbine transducer stores and updates the totafu~ed fuel quantity in a
Installed per SI M20-49. random access memory chip. The Total Fuel Used
quantity is retained dun~ng aircraft shut down by
73-31-00 FUEL FLOW SYSTEM GENERAL connecting the memory wire to the aircraft battery
SYSTEM DESCRIPTION through a memory switch. The drain on the aircraft
battery is small due to the low power MOS memory
The Fuel Flow Totalizer system, utilizes the latest in
chip which uses only 0.7 milliamps at 12 VDC (13
microcomputer technology products. The fuel flow milliamps at 24 VDC, FT1OIA).
system is designed to maximize the efficiency of fuel The
E. INTERNAL SWTTCH ARRANGEMENT
system management by displaying the fuel
flow) of the engine and the programming switch block (see Figure 73-2) located
consumption rate (fuel
precise amount of fuel the engine has consumed. This inside the PT-101 panel mounted unit has several
information may be displayed in one of the following arrangements to change data readout if desired.
Switches S1 and S2 (see Figure 73-1) should not be
formats, US Gallons, Pounds, Liters or Imperial
Gallons (Alcor) depending on switch or contact changed unless the transducer "K" factor of a
arrangement, see (Figure 73-1 and 73-2). replacement transducer differs from the on’ginal unit’s
"K" factor (see Section 73-31-02, 3, for "K" factor
The system consists of a panel mounted instrument description).
and a fuel flow transducer which is installed in the in various
aircraft engine fuel line,
Switches S3 thru S7 can be positioned
arrangements to change full flow readout to gallons,
The system is designed for use in all single engine fuel pounds or liters as the situation may require, (see
injected aircraft having no more than 60 GALRHR Figure 73-1).

FT-1O1SWITCH ARRANGEMENT/ FT-~101 TRUTH FIGURE 73,1

K-FACTOR SWITCH ARRANGEMENT

S1 S2

L ON ON

M ON OFF
H OFF ON
HH OFF OFF

FUNCTION SWITCH ARRANGEMENT

S3 S4 S5 S6 S7

GALLONS ON OFF OFF NA NA

POUNDS OFF ON OFF NA NA
LITERS OFF OFF ON OFF NA

73-00-00
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
3. TRU FLOW 1 (ALCOR) SYSTEM
A. DISPLAY -The unit features a liquid crystal dis-

play (LCD) to indicate fuel flow and total fuel used

simultaneously. The display is backlighted and features

FT 101
SCAEW uHlr
automatic dimming through a cell sensor.
photo
B. ELECTRONICS The TRU FLOW 1 amplifica-

I tion system is located in the indicator away from the

engine environment. The IRU FLOW 1 operates on a

SCREW
~7 low power requirement and is protected against volt-

SCREWS HOUSIHO age surges.

3 C. MEMORY The TRU FLOW 1 micropressor
BICURITY
12\
stores the total fuel used
~I I continously updates and

I quantity. The total fuel used quantity is retained during

aircraft shutdown through a low power drain memory
PRCCR*YYING
SWITCH BLOCI(
ciruit connected to the battery.
D. INTERNAL CONTACT ARRANGEMENT The

configuration selection block located inside the TRU

FT-101 SWITCH ARRANGEMENT FIGURE 73 2
FLOW 1 indicator has several arrangements to change
2. f=T1O1A (HOSKINS) System data readout a desired. Jumpers should not be
A. Basically same as FT101.
B. Refer to Hoskins Operators changed unless the K-factor of the transducer has
C. or Maintenance Manual changed due toreplacement. (See Section 73-31-01,3,
D. for specific data.
for K-factor description). Refer to Figure 73-3 for Alcor
E. See Figure 73-1A for FT1OIA Switch
arrangement. contact arrangement. To reconfigure the unit proceed

K-FACTOR ADJUSTMENT FT1O1A

SWITCH NUMBERS S1 S2 S3 S4 S5 S6 S7

(1111) LOW LOW LOW CLOSED OPEN OPEN X X N X

(2222) LOW LOW OPEN CLOSED OPEN X X O X

(3333) LOW CLOSED CLOSED OPEN X X T X

(4444) MEDIUM OPEN OPEN CLOSED X X U X

(5555) HIGH CLOSED OPEN CLOSED X X S’ X

(6666) HIGH HIGH OPEN CLOSED CLOSED X X E X

(7777) HIGH HIGH HIGH CLOSED CLOSED CLOSED X X D X

FUNCTIONS

GALLONS X X X OPEN OPEN CLOSED

LITERS X X X CLOSED OPEN OPEN

POUNDS X X X OPEN CLOSED OPEN

FIGURE 73-1A FT1O1A SWITCH ARRANGEMENT

73-31-01
MOONEY AIRCRAFT CORPORATION M20K SERV(CE AND MAINTENANCE MANUAL

OLDWILLWAYNE
K1 K3 K5 K7
ol IK) -0101 IK) OJ OI IK) ~010
K-FACT17R(lro c~ 0
o
I lo K, -oll Irol o I lo
A
ooo ooo ooo ooolK-F~ACT[7R
NI3T USED o o o o o o o o o o o o
000 000 000 000
000 000 000 000
UNITS 000 000 000 000
M L K M L K M L K M L K

US, GALLONS IMP. GAUJ3NS POUNI)S UTERS

oool To ool lo oO_l looo
K-FACTI7R(lo ool
o 0
loool ioool looo
B
ooo ooo 000 oool UNITS
NOT USED(lo 0 ol lo 0 ol lo 0 ol lo o o
000 000 000 000
O OK>-C~ O O
UNITS or ILO 01 0 0 lo at to to at rSM73-31
MLK MLK MLK MLK

TRU-FLOW 1 JUMPER ARRANGEMENT FIGURE 73 3

CAUTION Step 5. Determine the K-factor to be selected

Some components in the indicator be
can to match the K-factor of the transducer. Should the
damaged by static electricity. Disassemble the need arise to match the K-factor with a SDI (Hoskins)
indicator at a location away from static generating transducer use one of the following K-factors:
materials, such as styrofoam, plastic, wool,
HOSKINS TRANSDUCER ALCOR TRANSDUCER
nylon(carpets), etc, Once disassembly of the
(Flowscan) Code Code (K-FACTOR)
indicator has started DO NOT LEAVE the indicator
until it is reassembled to help eliminate the
L EQUATES TO K7
possibility of static discharge. K5
M
H K3
Step 1. Remove 4 screws, 2 on rear of in-
HH K1
dicator (which also removes connector latch) and 2 on
side of indicator. Then remove electronicassembly by
connector and pulling
Arrange the jumpers according to Figure 73-3, A.
simultaneously pushing on rear Step 6. Determine the desired unit of measure-
on front bezel (front bezel may seperate from main as-
ment, there are four (the pounds measurement is not
sembly at this time, this is normal). BE CAREFUL NOT true pounds, but calculated from 5.85 times U.S. gal-
TO BEND THE BOARD CONNECTOR PINS.
ions, which is accurate only at 59 degrees Fl. Reposi-
Step 2. Remove front bezel assembly from tion the jumpers according to the examples in Figure
main assembly by grasping edges of the boards and
73-3,B.
pulling them apart.
Step 7. Print the K-factor and unit of measure-
ment on the dot label located on the back of the in-
CAUTION
dicator case.
Do not bend the connector pins.
Step 8. After repositioning the jumpers, reas-
semble the indicator in reverse order of disassembly.
Step 3. Remove one of the 2 screws holding
Be careful in lining up the board connector pins.
main assembly boards to standoff. Separate boards by
grasping edges and pulling them apart. DO NOT BEND Step 9. After reassembly, power up indicator
and dheck configuration to make certain that the
THE PINS.
P’oper changes were made.
Step 4. Locate the circuit board pictured and
the "configuration selection block" (where the 5 con-
figuration jumpers are located).
73-31-01
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
Step 10. If fuel flow quantity
used totals do
or
not match actual values contact the manufacturer for
troubleshooting procedures.
NOTE
Reposition the jumpers by grasping with needle
nose pliers or tweezers and pulling straight
up to
remove them, then reinsert to select the
appropriate K-factor and units.

73-31-02 FUEL FLOW TRANSDUCER

I
1. The turbine flow transducer, mounted in the en-
gine fuel line, measures Row of fuel. The transducer is
rated for a continuous operation to 60 gallons per
hour. In addition, the transducer is accurate down to
0.6 gallons per hour.
2. The transducer supplies the Fuel Flow Totalizer
with a pulse signal from a self contained opt~-
electronic pickup. A neutrally buoyant rotor spins with
B En~Sine driven
the Ilqu[d between V-jewel bearings. The rotor move- fuel pump
ment is sensed when notches in the rotor interrupt an
infra-red light beam between alight emitting diode and
TURBINE FUEL FLOW TRANSDUCER FIGURE 73 4
a photo-transistor.
3. The transducer design is fail safe; complete rotor ´•NOTE
blockage cannot interrupt fuel Row. The transducer life The "K" factor of the replacement transducer
expectancy is 1500 hours. should match the "K" factor of the replaced unit.
Refer to "NOTE" following Section 73-31-02,
NOTE
Transducers are categorized by the number of paragraph 3 for detailed expianation.
pulses per second output for a given GPH flow A. Note the position of finings (8) on old
rate ("K Factor)".
This will be noted as: L, M, H, or
transducer (3) and place them in similar position on the
HH scribed on the end of the serial no. For
accurate readin~s, replacement transducers new transducer.
should have the same "K" factor as the units being B. Connect the nuts of lines (4) and (5) to fRtings
replaced. Specify "K" factor code when ordering (8), leave them snug, not tight.
new transducers. C. Connect the new transducer (3) to bracket (7)
4. Fuel Row transducer removal. using bolts, washers and nuts (6).
A. Remove top and bottom cowling from aircraft.
CAUTION
See Section 71-10-00 for procedures. Make sure the lines (4) and (5) are not being put
B. Cut and remove ty-raps from insulator sleeves into a bind or twist when securing the transducer
on knife disconnects of electrical wires (1) (see to the bracket.
Figure
73-4). D.
C. Slide insulation Tighten all fuel lines and bolts to secure the
sleeving up on electrical wire
harness, transducer.
E. Connect the knife disconnects and slide in-
D. Disconnect the knife disconnects.
E. Remove safety wire from firesleeve (2) around Sulating sleeving over connections. Secure sleeving
turbine transducer (3) and unwrap firesleeve to expose Wah ty-raps.
the transducer. F. Leak check all fuel connections by pressurizing
F. Loosen nuts on tubes (4) and (5) at fittings (8) the fuel lines with hi-boost pump. Correct any leaks or

prior to loosening nuts on attaching bolts (6). discrepancies.

G. Loosen and remove nuts, washers and bolts G. Wrap firesleeving (2) over transducer (3) and
(6) from transducer and bracket (7). secure into position with safety wire.
H. Disconnect the fare nuts from transducer fa-
tlngs (8).The transducer should NOTE
now be free for
Installation of the new transducer may affect the
removal. Note position of fittings (8) on old transducer
engine fuel flow adjustment. It is recommended
(3). that the procedures of Section 71-00-50 be
i. Cap all lines to prevent contamination. followed to assure engine is set up for proper
5. Fuel flow transducer (replacement) installation.
operation.
73-31-02
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
H. When all adjustments have been made and all 73-31-05 TROUBLESHOOTING SDI (Hoskins)
connections checked for security, install the cowling FUEL MANAGEMENT SYSTEMS
per Section 71-10-00.
Troubleshooting any Hoskins fuel management sys-
73-31-03 GENERAL OPERATING tems should be approached in a systematic manner.
PROCEDURES All problems can be put in one to five categories:
Improper operation due to lack of knowledge
i. Turn aircraft master switch ON. When the aircraft
electrical system is activated, the FT-101 display will about the system.
flash zeros (000.0). This flashing is a reminder for the Inoperative computer or main instrument.
pilot to reset or check the fuel used by pressing either Inoperative transducer.
the RESET USED/TEST button. Once the RESET or
or Improper win’ng.
USED/TEST button is depressed, the display will stop Improper transducer installation.
flashing and read fuel flow. 1. MEMORY LOSS
The TRU FLOW 1 will display the configuration unit of A. Loses memory when Master switch is turned
measure and K-factor on the right hand side of display
OFF.
window (refer to Fig. 73-5).
(1) Check "Fuel Flow Memory" switch ON.
After starting the aircraft engine, the FT-101 will con-
(2) If switch is ON, check clock for operation.
tinuously display fuel Row. Total Fuel Used may be dis- (3) If clock inoperative, replace fuse at battery.
played by pressing and holding the USEDTTEST button (4) If no problem found, remove connector
on the right of the instrument. Total Fuel Used will be
from unit, check Pin 9 for bus voltage.
displayed as long as the USEDTTEST button is (5) If voltage present, replace FT-101/101A.
depressed (or for 2 seconds), whichever comes first. B. Memory scrambles when engine starts.
This number may be reset to zero (0.0) by depressing
and holding the RESET button for at least 1 second. Exchange FT-101 for modified unit.
The TRU FLOW 1 displays both functions simul- 2´• DOES NOT INDICATE

taneously. A. No display.
2. The totalizer function in either system may be (1)Remove connector from indicator. Check
used as a single night totalizer or as a long term Pin 1 of harness connector for bus voltage. Check Pin
totalizer.Both methods are explained below. 8 for airframe ground. If OK, change indicator.
A. SINGLE FLIGHT TOTALIZER. The aircraft B. Displays zeros (with engine running)

should be topped with fuel before each Right so the (1) Remove cowling for access to transducer.
Remove insulating sleeving from connections on all
total usable fuel will be known. Turn the aircraft
wires. Check BLACK wire for ~VF ground. Check RED
MASTER switch ON. Push and hold the reset button, wire for bus voltage. Check WHITE wire for 2-3 volts
located on the left of either instrument, for at least 1 with no fuel flow and increasing to near bus voltage at
second. The RESET button has a one half second fullRow.
(2) If no increase in voltage is seen on WHITE
delay to prevent accidental reset.
wire as Row increases or if too high a voltage indica-
On starting the engine, the FT-101 will begin displaying
tion is seen with no Row, change transducer.
fuel flow. Total fuel used may be checked by depress-
(3) If RED wire does not have bus voltage,
ing the USED/TEST button. check wiring from transducer to Pin 3 of indicator.
B. LONG TERM TOTALIZER. Tum the aircraft
(4) If BLACK wire is not grounded, check
MASTER switch ON. On activating the aircraft electrical
wiring from transducer to Pin 6 of indicator.
system, the FT-101 will flash zero (000.0) fuel flow. 3. ERRATIC INDICATIONS
Depress and hold the USED/TEST button. The FT-101 A. Check win’ng for loose connections.

will display the total fuel used from previous Rights. DO B. Check win’ng for intermittent shorts.
C. Check transducer for foreign particles.
NOT push the RESET button! On starting the engine,
D. If all checks OK, replace transducer.
the PT-101 will display fuel flow and continue counting 4. INACCURATE READINGS
fuel used up to 999.9 gallons, 9999 pounds, or 9999 A. Check transducer K-factor. The letter
liters depending on the internal setting. The Alcor TRU- "HH" inscribed after the serial number.
"L"."M","H", or
FLOW 1 will display fuel Row total fuel used. B. Remove indicator from instrument panel and
73-31-04 TEST FUNCTION case. Check switch settings and correct to match

A test function is provided in the FT-101, so the pilot transducer.

may verify that all digits are functioning prior to each
Right. To use the test function, depress and hold the NOTE
USED/TEST button two times within one second and Each switch setting changes reading by
the FT-101 will display all eights (888.8). approximately 2 If settings are OK, replace
transducer.

73-31-03
SERVICE AND MAINTENANCE MANUAL M20K MOONE/ AIRCRAFT CORPORATION

OLDWILLWAYNE
CAUTION 7331-06 -TROUBLESHOOT1NG-
Whenever transducer or indicator is replaced, TRU- FLOW 1 (ALCOR)
care must be taken to set indicator switches to FUEL MANAGEMENT SYSTEM
match transducer. If problem is determined to be in the indicator and all
transducer and win’ng checks have been made, contact
If after making these checks you still do not isolate the Alcor, Inc., 10130 Jones-Maftsberger Road, PO Box
problem or do not find a problem, contact the Customer 32516, San Antonio, Tx. 78284, telephone (830)
Service Department of Mooney Aircraft Company for 3493771 for further assistance.
further assistance.

7350-00 DRUCK TRANSDUCER TEST

PROCEDURES

Refer to Chapter 79-40-00.

SOFTWARE VERSION NQ. K

DASH (NO)

u" D?; II
tco

I FLOW TOTAL
UNTT OF MEASUREMENT

UNITS: 4 U.S. GALLONS

3 IMPERIAL GALLONS
2 POUNDS(5.85 X U.S. GALLONS)
1 LITERS
K-FACTORS ARE DISPLAYED AS ACTUAL K-FACTOR RANGE. ie.. 1= Kr. 2 K2. ETC.

TRU-FLOW 1 CONFIGURATION FIGURE 73 5

73-31-06
 OLDWILLWAYNE

CHAPTER

IGNITION
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CHAPTER 74

IGNITION

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General 3
74-00-00
74-1 0-00 Electrical Power 3

Ignition System Troubleshooting 3

74-10-01
Engine Fin’ng Order 3
74-20-00
Switching 3
74-30-00

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OLDWILLWAYNE
-GENERAL magneto rotor turns counterclockwise, passing in
74-0090
succession the terminals of spark plug cables in engine
The TS10360-GB,-LB,-MB or -SB series engines are firing order. Cables are connected to the magnetos so
equipped with either Bendix 25 Series magnetos, S/N that the n’ght magneto fires the upper plugs on the right
25-0001 through 25-0526, or Slick 6200 Sen’es, S/N side and lower plugs on the left. The left magneto fires
25-0527 thru 25-TEA. Both magnetos incorporate an the upper plugs on the left and the lower plugs on the
impulse coupling that retards the spark 30 degrees for n~ght. The magneto cases, spark plugs, cables and
starting. When the engine starts, counter weights hold connections are shielded to prevent radio interference.
the latch pawls away from stop pins. The magneto then S,, (Figure 74-1) for ignition wiring diagram.
will fire at its advanced firing position.
The magneto/starter switch combines both ignition and
starting functions. Turn the key clockwise through R, L
and BOTH to START position; push forward on key LIPPER SPARK PLUGS
while in START and the starter relay is energ~ed.
Release of the key, after engine starts, will return the
switch to the BOTH position where both magnetos are mmw svntlu
operative, aocMn
wac
In the OFF position both magnetos are grounded. At Evrrew svrrcw
the R position the left magneto is grounded and at the
L position the n’ght magneto is grounded.

NOTE I I I mEm LEr7

Mooney Service Instruction M2059A (or later

revisions) should be complied with for
improved starting.

74-10-00 ELECTRICAL POWER

74-10-01 IGNITION SYSTEM TROUBLE

SHOOLlNG

1. Hard starting.
A. Assure that the impulse couplings are operating.
B. Check magneto timing to engine. LOWER SPARK PLUGS

2. Engine roughness.
A. Install new spark plugs.
IWN: FIROt mOrn 1-633-5-1 f(Q1IC1
B. Check plug leads for deten’oration. ~me rmee 13-~fcSb
Iw~Em
C. Check magneto points for wear or improper
setting.
out of limits. IGNITION WIRING DIAGRAM FIGURE 74 1
3. Magneto drop
A. Check magneto-to-engine timing.
service magnetos per TCM Service
NOTE
B. Insped and
Instruction. TCM recommends all spark plugs be removed,
inspected, cleaned, reagapped and reinstalled
C. Check spark plugs and leads. in the same cylinder but in a different spark
4. Check magneto pressurization hoses, plug hole every 100 hrs. Replace the spark
connections and filter (if installed). (FiBer not used with plugs after 400 Hrs. of operation.
Bendix magnetos.)

NOTE 7630-00 -SWITCHING

Aircraft which are flown at higher altitudes
during normal flight operations require more
The Magneto/Starter switch is connected to the
frequent maintenance on ignition components magneto grounding wires C’P" leads) of both magnetos.
than aircraft flown at lower altitudes. (Service Turning this switch from "BOM" to "OFF" or from "R"
to ’L" to "OR" will ground out both or either magneto.
ignition system per TCM Service Instructions.)
(See Section 74-00-00 for grounding sequence.)
74-20-00 ENGINE FIRING ORDER REUABLIITY: Wrth proper installation and compliance
with prescn’bed maintenance procedures Slick or
Engine fin’ng order is 1-6-3-2-5-4 CTS10-360-GB,-LB,
-MB 5 -SB) (Figure 74-1). Observe the position of the Bendix Magnetos should last the life of the engine
No. 1 cable terminal in the magnetor outlet plate in before overhaul or replacement is required. (Refer to
relation to the magneto case. As viewed from the Slick Service Bulletin SB1-86A, March, 1987 or
distn’butor end, the TS10-360-GB,-LB, -MB or -SB subsequent revision).
74-00-00
 M20K MOONCI AIRCRAFT CORPORATION
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74-30-00
 OLDWILLWAYNE
C H A PT E R

ENGINE
CO NTRO LS
 M20K MOONC/ AIRCRAFT CORPORATION
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CHAPTER 76

ENGINE CONTROLS

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3
76-00-00 Engine Controls
3
76-10-00 Engine Controls Rigging

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7640-00 ENGINE CONTROLS 76-10-00 ENGINE CONTROLS RIGGING

See Section 71-00-52 for Engine Controls Rigging/Adjustments

76-00-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

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76-10-00
CHAPTER
OLDWILLWAYNE

ENGINE
INDICATING
 SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

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CHAPTER 77

ENGINE INDICATING

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77-00-00 General´• 3
77-00-01 Ranges 3
77-1 0-00 Power Indicating 3
77-1 0-01 Tachometer 3
77-10-02 Manifold Pressure 4
77-10-03 Fuel Fiow
Indicating System 4
77-20-00 Temperature Indicating 4
77-20-01 TIT/CDTlnstrument 4
77-20-02 CylinderHead Temperature 5

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77-00-00 GENERAL 9. Manifold pressure gauge.
A. Normal range-
Engine indicating instruments and their sending units, thru 25-0999)
transducers, probes, etc., must be operating properly to 10to40 Inches Hg. (250001
prevent engine damage. 10to36 InchesHg. (251000thru25-201~*
10 to 39 Inches Hg. (252000 thru 25-TEA)
It is that all
recommended engine indicating (-88)’
components be checked at each 100 hour or annual
inspection to verify proper operation. Calibrated B. Red line--
instruments may be "Tee’d" into the particular systems 4OlnchesHg. (25-0001 thru25-0999)
for a comparison check between them and the aircraft’s 36 InchesHg. (25-10001hru25-2012)’
Instruments. 391nchesHg. (25-2000thru25-TBA) (-88)"
S/N 252000 thru 25-2012 may be retrofitted to -SB
71-00-01 -RANGES
configuration by compliance with Mooney retrofit kit, if
Power plant instruments operate electrically through desired by owner.
variations in resistance caused by pressure or
temperature changes, by variations in current output 77-10-00 -POWER INDICATING
caused by varying engine RPM or altemator output, or
by pressure from engine induction system. 77-10-01 TACHOMETER
1.Ammeter. (25-0001 thru 25-0999)
A. Range--+70 to -70 AMPS.
The electric tachometer counts ignition pulses from the
B. Tolerance--1.2 AMPS. magneto to indicate engine speed in revolutions per
2. Fuel flow gauge (except digital) minute (RPM). The tachometer is connected to the "L"
and "R" terminals on the Magneto/Starter switch and
A. Green are--5.5 to 25 GPH.
senses the magneto impulses through this wire
3. Oil temperature gauge. connection. Two 15K ohm resistors are in series
2400 F between the "L" and "R" terminals. The junction of
A. Green are--100 to
these two resistors forms the tachometer signal wire
B. Red line--2400 F connection point These two resistors, located
C. Tolerance--30 F. immediately adjacent to the Magneto/Starter switch
inside the insulating sleeve, protect the magnetos from
4. Oil pressure gauge.
grounding out if a short develops in the tachometer.
A. Green are--30 to 80 PSI (-GB 8 -LB engines)
(25-1000 thru SS-TBA)
Green are--30 to 60 PSI (-MB 8 -SB engine)
8. Yellow arc--l0 to 30 PSI. The tachometer indicating system is a fully solid state
electronic system that senses engine RPM by magneto
(1) Idle range--i 0 to 60 PSI. rotation speed. A "Hall-effed" sensor is installed on the
(2) Starting warmup range--90 to 100 PSI. magneto bleed source. This sensor is excited by 12
volts DC provided by the tachometer indicator. The
C. Red line--i 0 PSI MIN.(idle only), 100 PSI MAX.
"Hall-effect" sensor incorporates a switching transistor
NOTE that is actuated by north to south pole switching of the
The oil pressure relief valve seat may be honed main rotor magnet within the magneto. The switch
to improve low idle oil pressure. HIGH (+5 VDC) to switch LOW(GRD) creates a square
wave frequency output from 0 to 75 HERTZ
which is
5. Tachometer. monitored by the electronic tachometer. Because the
sensor does not rely on magneto output pulses
for
A. Green are --1800 to 2700 (-GB, -LB, -MB) and
generating signals the magneto may be disabled
1800 to 2600 (SB) still maintain signal output from the hall effect sensor.
B. Red line --2700 (-GB, -LB, -MB) The electronic tachometer is a micro-processor
2600 (-SB) controlled stepper motor. The micro-processor receives
the square wave frequency signal from the Hall-effect
6. Cylinder head temperature gauge (CHT). of the
sensor and computes the relative position
A. Green are--250 to 4600 F. pointer. The micro-processor then generates pulsed
B.Redline "60"8. signals to drive the stepper to its pre-computed
position. A DC activated solenoid engages the gear
7. Turbine inlet temperature CnT). train drive to locate the pointer in its respective position.
A. Green are--1300 -16500 F. Upon loss of the +28 VDC input, the solenoid then
deactivates and disengages the drive train, thus
B. Red line--16500 F.
returning the pointerto below 500 RPM.
8. Compressor discharge temperature (CDT) indicating system is provided
Power far the tachometer
(25-0001 thru 25-0999) to Pin A of the tachometer. Power requirement is 28
A. Green arc--1000 F-2800 F. VDC with a typical current drain requirement of250
B. Red line "80" F. milliamps.

77-00-00
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OLDWILLWAYNE
TACHOMETER TROUBLE SHOOTING.

TROUBLE PROBABLE CAUSE REMEDY

No permanent or intermittent C/B out (IGN/CIG LTR) Reset C/B.

indicator reading.
Broken wire Check 3 repair win’ng.
Faulty instrument. Replace instrument.
Pointer Oscillates excessively. Mag. tim’ng too wide behnreen mags. Retime magnetos.

Isolation resistors at mag. switch Replace resistors.

increased in resistance value.

77-1042 MANIFOLD PRESSURE CAUTION

Do not over boost the engine during any
Manifold pressure is an indication of engine power normal operation. (Do not exceed 40 inches
affected pn’marily by throttle setting. The instrument is manifold pressure for 25-0001 thru 25-0999) (Do
calibrated in inches of mercury (Hg) and indicates the not exceed 36 inches manifold pressure for
pressure in the induction air manifold. The RED line of 40 25-1000 thru 25-2012 (Do not exceed 39
Inches I-In. (25-0001 thru 250999), 36 inches Hg inches manifold pressure for 253013 thru
(25-1000 thru 252012) (-MB)* or 39 inches Hg. (252013 25-TEA
thru 25TBA) (-SB)* can be exceeded easily due to
turtocharger pressure also being applied to the induction The waste gate bypass on the turbocharger (25-0001
system. Manifold pressure varies somewhat with pitch thru 25-0999) is a ground adjustable system, (see
attitude in flight and therefore small oscillations may occur Section 71-00-50) that must be adjusted properly.
in flight, particularly in turbulent air. 252000 thru 25-2012 may be retrofitted to -SB
if desired by owner.
configuration

MANIFOLD PRESSURE TROUBLE SHOOTING.

TROUBLE PROBABLE CAUSE REMEDY

Excessive error at e>cisting Pointer shifted. Replace instrument.

barometric pressure.
Excessive error when engine is Line leaking. Tighten line connection.
running.
Sluggish orjerky pointer movement. Improper damping adjustment. Adjust damping screw.

Vibration excessive pressure. Replace glass and reseat case.

Broken or loose cover glass. or

Dulordiscdored h~inous Age. Replace instrument.

markings.
Incorrect reading. Moisture or oil in line. Disconnect lines and purge with air.

77-10-03 FUEL FLOW INDICATING SYSTEM The compressor discharge temperature (CDT)
instrument depicts the temperature of air enten’ng the
Refer to Section 73-30-00 for this data. air induction system to mix with the fuel for combustion.
This temperature does not normally become critical
77-20-00 -TEMPERATURE INDICATING except at high altitudes and high power settings
(250001 thru 25-0999). Aircraft using a combination
TIT/CDT gauge utilize a non-grounding TIT probe. An
77-20-01 -TIT/CDT INSTRUMENT ohmmeter connected between either lead and the
The turbine inlet temperature CTIT) instrument depicts probe case should indicate high resistance. If zero or
low resistance is indicated the probe has shorted and
the temperature of the exhaust gases as they enter the
ShOUld be replaced.
turbocharger. This temperature is controlled by power
setting, RPM and the fuel air ratio entering the NOTE
combustion chamber of the engine cylinders. The TIT S/N 25-1000 thru 25-TEA do not use a CDT gauge.
should never exceed 16500 F. continuous operation.

77-10-02
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OLDWILLWAYNE
77-20-02 CYUNDER HEAD TEMPERATURE number 5 cylinder (25-0001 thru 25-0999), (No. 3
cylinder for 251000 thru 25TBA). An optional system
The cylinder head temperature (CHT) instrument provides a probe in each cylinder to provide moniton’ng
provides the operator with an indication of how hot or or each cylinders temperature.
cool the cylinders are operating dun’ng flight. A
resistance type temperature probe is installed in the

77-20-02
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77-20-02
CHAPTER
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EXHAUST
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U(HAUST

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General 3
78-00-00
3
78-10-00 Exhaust System Installation
Exhaust System SeM’cing 3
78-30-00
Pen’odic Replacement Components 3
78-40-00

’I&EFFICONTENTS
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 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
7890-00 -GENERAL LOOSE CONNECTIONS
B. Inspect exhaust
clamps for cracks, looseness and proper security.
The e>d~aust system’s headers, exhaust pipes and
turbocharger interface components are manufactured NOTE
by Teledyne Continental Motors CTCM) as part of the During inspection, particular attention should
certified TSIO-360 sen’es engine. The turbocharger is be given to condition and security offlanges,
manufactured by either Rotomaster or Garrett- spot welds, slip joints, and welded areas.
Airesearch Corporation. (See Section 81)
C. INTERNAL EROSION Examine bends and low
Inspections for cracks, bums, damage, etc, are spots forthinning pitting.
or
required dun’ng each maintenance activity and STANDOFFS (PINS) AND HEAT TRANSFER
D.
recommended before each flight.
FINS Look for missing or damaged heat transfer pins
or fins. Look for holes at these locations.
78-10-00 EXHAUST SYSTEM INSTALLATION
E. METAL FATIQUE Inspect all surfaces for
i. EXHAUST RISERS/PIPES TO ENGINE. bulging and distrotion and for groups of small cracks.

Exhaust components are certified with the engine by CAUTION

TOM. It is recommended that reference be made to DO NOT mark any surface with lead pencils or
TCM Overhaul Manual, No. X30596A, and TCM
any carboncontaining markers.
Illustrated Parts Catalog, No. X30597A for assembly
and dissasembly of the exhaust system components. F. HIDDEN DAMAGE Carefully inspect all
internal surfaces that lie hidden under extemal
78-30-00 EXHAUST SYSTEM SERVICING gussets, stiffners, etc. (A borescope is recommended)
i. CLEANING G. INSTALLATION TIPS:

To properly inspect exhaust system, components must Install only correct parts.
be clean and free of oil, grease, etc. Clean as follows: DO NOT FORCE FIT any component.
A. Spray engine exhaust system components with Properly align connecting components.
a suitable solvent (Stoddard Solvent), allow to drain Do not reuse gaskets.
and wipe dry with clean cloth.
Insure that attach bolts are properly torqued.
Exhaust flange stud nuts are to be torqued in
WARN1NG accordance with TCM Overhaul Manual, Torque Chart,
Never use highly fiammable solvents on engine Section 72, Figure 72-50-01A.
exhaust systems.
78-401)0 -PERIODIC REPLACEMENT
COMPONENTS
WARNING
It is recommended that all exhaust system risers,
Never use a wire brush or abrasives to clean
exhaust systems or mark on system with lead pipes, clamps and miscellaneous mounting hardware
be replaced at engine overhaul time (2000 Hours).
pencils.
However, thorough inspection of all components
should be made any time exhaust system is removed
2. VISUAL INSPECTION OF COMPLETE SYSTEM from engine for component replacement. The
inspection should be made in the interest of preventive
A thorough inspection of engine exhaust system will maintenance.
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 shrouds/shields to permit full visual

inspection.
A.LOOK FOR LEAKS Examine surfaces
adjacent to e~aust system components for signs of
exhaust soot. Look for gray, red or black gas stains at
welds, clamps, flanges, etc. Inspect system for
chaffing by cowling, engine mount, cables or any
airframecomponents.
Inspect exhaust stacks for burned areas, cracks and
looseness.

78-00´•00
SERVICE AND MAINTENANCE MANUAL M20K MOONC( AIRCRAFT CORPORAIION

OLDWILLWAYNE

B LAN K

78-40-00
 OLDWILLWAYNE

CHAPTER

OIL
SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 79

Oil

LIST OF EFFECTIVE PAGES

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CHAPTER
SECTION
SUBJECT

112BLANK 9-97
79-Effectivity/Contents
3´• 9-97
79-00-00
4´• 997
79-30-00
5´• 997
79-30-02
6´• 997
79-30-02
7´• 997
79-30-02
8´• 997
79-30-02
9´• 997
79-40-00
10 997
79-40-00

TABLE OF CONTENTS

CHAPTER SUBJECT PAGE

SECTION
SUBJECT

General 3
79-00-00
Oil Filter RemoMI 3
79-00-01
Oil Filterlnstallation 3
79-00-02
Distribution 3
79-20-00
Indicating 4
79-30-00
OilPressure 4
79-30-01
Oil Temperature 4
79-30-02
Druck Transducer Test Procedure 9
79-40-00

79-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
79-0090 -GENERAL The engine oil filter, TCM P/N 641583, should be
replaced each 50 hours and at every oil change (refer
The oil system is a wet sump, pressure type system. to Figu~ 742 for location).
The engine sump has an 8 quart (U.S~ capacsty.
Servicing of the oil quantity is provided through an 1. Remove top and bottom cowling (see Sedion
access door located on top of the engine cowling. 71-10-00).
The airaaff is delivered with the proper non-detergent, 2. Cut and remove safety wire on filter
mineral oil (MIL-C-6529 Type II). This oil should be off oil filter and
3. Loosen the spin remove.
changed at 25 hours or when oil consumption has
stabilized. The replacement oil should conform to TCM 79-00-02 OIL FILTER INSTALLATION
Specification MHS-24( The routine oil change
interval is 100 hours, however a operating in a dusty 1´• Position new filter on adapter.
environment the interval should be more often. 2. Tighten per instructions on filter.

NOTE 3. Safety wire filter.

A new remanufactured newly overhauled
or
4. Perform leak check prior to flight.
engine ~hould have the oil and filter changed at
50 hours of operation after changing to 5. Reinstall lower and upper cowling (see Sedion
detergent oil, then begin the 100 hour oil 71-11-00).
change interval. 6. Conned and secure all electrical and mechanical
connedions.
NOTE
Refer to Section 5-20-07 or to TCM TS10360-GB 79-20-00 DISTRIBUTION
Operator’s Manual Form No. X30536, Section
The oil system on the TSIO-360-GB,-LB, -MB 3 -SB
VIII, Form No. X30571 for the -LB engine or
Form No. X30584, Section VIII, for the -MB engine is internal within the engine except for
SE engine for approved oil products, turbocharger lubrication and oil pressure transducer
plumbing. This portion of the system contains pressure
hoses, fittings and check valves to route oil through the
turbocharger back to the engine case for cooling; (refer
to Figure 79-2, 793 and 79-4 for 25-0001 thru 25-0999
7990-01 OIL FILTER REMOVAL and Figure 79-5, 79-6 for 25-1000 thru 25-TEA).

CIYYUTI ~lll*G

CRINIYUII ~IIIING

nla~la OVY(IYO

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wctssorcr DRIVL

hlVru;r NNI

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gl~ rlYrl~rUR( COIIIIOC VUYL f

I
1
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at coaro

OPlOlr ´•S´•~UP

O(L T~YLRINR(
C(LUI~M VUVL

IUI~OC)uRGIO

LUBRICATION DIAGRAM (OIL SCHEMATIC) FIGURE 79 1

79-00-00
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE

OIL PRESSURE 9 c.

TRANSDUCER a

Fw

I’ ~;Grz B O, C H A~´• G E R I,,

OIL FILTER

OIL PRESSURE
TRANSDUCER LINE

TURBO CHARGER OIL

SCAVENGER LINE t

TURBO CHARGER
OIL PRESSURE LINE

VIEW LOOKING INBOARD FROM R.H. SIDE ENGINE

TURBOCHARGER OIL LUBRICATION SYSTEM FIGURE 79 2

(25-0001 thru 25-0999)

79-30-00 INDICATING 79-30-02 OIL TEMPERATURE

The oil temperature gauge is an electric unit receiving

79-30-01 OIL PRESSURE
its signal from a temperature bulb in the engine case.
Oil pressure indicating is provided through a pressure located between the oil cooler and the case. The probe
transducer plumbed into the engine oil system, see resistance changes as the oil temperature changes and
(Figure 79-2). Pressure variations change the resis- this varies the readout on the instrument.
tance within the transducer and this signal drives the
oil pressure gauge located within the cluster gauge.

79´•30-00
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE

j.
RBOCHARGER

tlRBO
OtL P :I´•

ort PRESSUR
TRANSD

s;i~
WD
I --1

URBOCf´•1ARGER Oft
SCAVENGE LINE
FllE~W-t00iCIEIGUP AT

TURBOCHARGER O(L LUBRICATION SYSTEM FIGURE 79 3

(25-0001 thru 25-0999)

79-30-02
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE

1PF"
O1L .SEPARATOR
fFW
TURB O
OIL SCAVENGE

DRY Al
VACUUM PUMP

Oit PRESSURE~
TRANSDUSER~
rr

Ifs
i.

L DOWN At REAR

TURBOCHARGER OIL RETURN SYSTEM FIGURE 79 4

(25-0001 thru 25-0999)

79-30-02
 OLDWILLWAYNE

OIL LINE FRO~H 7URBOCHARGER o

TO SCAVENGE PUMP

OsL LINE FROM ~ic2 GALLERV E

TO TURBOCHAROER
-a I
.´•.1~. 8
c’
o
p

E d
mn
-lo
B 2; fi5
c O
Z .~:´•t
2:
r

o
c
g
I iri
E 3m$ I

3 F
I
~I% i I

g
VIEW LOOKING UP z

,8
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE

OIL TRANSDUCER
VIEW LOOKINC=D0WN OH
UPPER LEFT ENGINE
HDUHT

FWD

ENGINE IUOUNf
-E~

VIEW LOOKING:
UP UNDER CENTER
C Y L I no E R ~9 4)
LEFT SIDE ENGINE
FURBOCHARCER
LINE

TURBOCHARGER O1L LUBRICATION SYSTEM FIGURE 79 6

(25-1000 thru 25-TEA)

79-30-02
 M20K SERVICE AND MAINTENANCE MANUAL
MOONC/ AIRCRAFT CORPORATION

OLDWILLWAYNE
If pressure reads incorrectly, zero or pegged
79-40-00 DRUCK fRANSDUCER TEST
PROCEDURE condition:
1. Rochester Gauge 250001 thru 25-1224
CAUTION transducer installed).
(with Druck
This unit is for troubleshooting only. DO NOT on the
ATTEMPT TO CALIBRATE WITH MIS UNIT. A. Move transducer text box to connector
input of the appropn’ate pressure amplifier (located
be
The DNck Transducer Test Box, GSE030036, can behind instrument panel, right side). Check pressure
in Mooney
used to simulate Fuel and Oil pressure reading on Rochester gauge to see if a approximately
model M20K that have the DNck pressure transducer agrees with the te>d box If does, repair
it wire harness
installed, from pressure gauge amplifier, to the engine
To use the unit for troubleshooting, the box is compartment. If pressure reading is incorrect go to step
connected to the aircraff harness in the engine
compartment, by disconnecting the appropriate Druck B. At the appropriate Rochester gauge
WIPER lug
transducer electrical connector and connecting the test to ground. (digital
read the following voltages
box in its place, multimeter or 20K ohmsivolt multimeter).
Tum on Airc~aff Master Switch (insure engine gauge "O PSI C.1 to 6.6 volts
Oil
circuit breakers are in) and adjust box to appro~dmate
should read thb
pressure desired. The engine gauge
approximate pressure. 2. SIGMA TEK Gauge 25-1225 thru 25-TEA
If pressure reading is correct: (with Druck transducer installed)
i. Verify OiVFuel pressure to DNck transducer
with A. Check win’ng for continuity between engine
mechanical pressure gauge. compartment connectorand Sigma Tek cluster. If

A. If correct-probable failure is Druck Transducer win’ng is cormcd go to (2.,8.).

module
B. Probable failure is Sigma Tek gauge
on
B. If incorrect-troubleshoot oillfuel system.
cluster, replace module.

79-40-00
 M20K MOONCI AIRCRAFT CORPOWATION
SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE

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79-40-00
10
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SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 80

STARTING

LIST OF EFFECTIVE PAGES

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SECTION
SUBJECT

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80-Effedivity/Contents
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8-1 0-00 4´• 897

TABLE OF CONTENTS

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SECTION
SUBJECT

80-00-00 General 3

80-00-01 StarterTroubl&hdoting 3

80-00-02 Starter Maintenance 3

80-00-03 Starter RemoMI 3

80-00-04 Starter Installation 3

80-00-05 Starter BNshes 3

80-1 0-00 Cranking’ 3

80-EFF/CONTENTS
1/2BLANK
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
80-00-00 -GENERAL 80-00-04 -STARTER INSTALLATION

The airplane is equipped with a 12 volt starter (25-0001 1. Before installation, clean any rust corrosion or dirt
thru 25-0999); 24 volt starter (25-1000 thru 25-iBA) from the mounting surface of the starter motor.
supplied with the engine package. The starter is lo- 2. Check all ground straps connections for tightness.
cated on the accessory case at the rear of the engine. 3. Install new o’ring on starter flange.
A 90 degree worm gear adapter provides the shaft 4. Position starter onmounting pad.
rotation and alignment to engage the starter gear train. attaching nuts and washers.
5. Install
When the ignition switch is placed in the "start" posi- 6. Torque nuts 220.0 to 260.0 inch Ibs.
tion, current is supplied through the main bus to ener- 7- Connect electrical wiring to starter terminals.

gize the starter solenoid which in tum connects the 8- Check starter mounting fiange for oil leakage

battery to the starter. before cowling is installed.

9. Install cowling.
80-00-01 STARTER TROUBLESHOOTING
80-00-05 STARTER BRUSHES
1. Refer to Section 24-39-04.
The starter brushes should slide freely in the holder
80-00-02 -STARTER MAINTENANCE
and make full contact on the commutator. The brushes
1. Inspect and service starter per TCM Service In- should be replaced when they have worn to 1/4 inch in
structions or Overhaul Manual. length. Brush tension should be 32 to 40 ounces as
2. Lubrication No lubrication is required on the mneasured with a spring scale hooked under the brush
starter motor except at overhaul, spring and pulled in a straight line opposite the force
exerted by the spn~ng. Read the tension just as the
CAUTION
spring leaves the brush.
Do not clean the starter in any degreasing tank or
80-10-00 CRANKING
grease dissolving solvents. Avoid excessive
lubrication. Use only kerosene or Varsol. The starter solenoid is located on the cabin side of the
firewall. The solenoid is energized by placing the igni-
80-00-03 -STARTER REMOVAL
tionlmagneto switch in the start position. Battery cur-
1. Remove upper cowling land lower a desired),(See rent is then directed to the starter. Aircraft serial num-
Section 71-10). ber 25-0613 thru 25-iBA are equipped with a "START
2. Disconnect electrical wiring from starter terminals. POWER ON" annunciator light. This light illuminates
3. Remove nut and washer from studs on adapter when the starter switch is in start position or when the
mounting pad. starter switch or starter solenoid has malfunctioned
4. Remove starter and o’ring from adapter. and the starter is engaged while the engine is running.
This malfunction should be corrected before the engine
is started again.

80-00-00
 M20K MOONEY AIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE

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ao~om

I
 OLDWILLWAYNE

CHAPTER

TURBINES
SERVICE AND MAINTENANCE MANUAL M20K MOONN AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 81

TURBINES

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81 -Effedivity/Contents
3. 9-97
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4. 9-97
81-20-00
5. 997
81-20-00
...´•´•´•´•´•´•6´• 9-97
81-20-00

TABLE OF CONTENTS

SUBJECT PAGE
CHAPTER
SECTION
SUBJECT

General 3
81-00-00
81-10-10 Turt~ochader con;rol system (Rotomastkr) 3
Test Procedures 3
81-10-11
Turt~ocharger Control System (Airesearch) 3
81-10-20
Adjustment and Test Procedures 3
81-10-21
ARemate Air SystemTuibocharger Operation 3
81-10-30
Turbocharger Troubleshooting 4
81-20-00

81-EFF/CONTENTS
1MBLANK
MOONC/ AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
81-00-00 GENERAL 81-10-20 TURBOCHARGER CONTROL SYSTEM
(AIRESEARCH)
TURBOCHARGER OPERATION
(25-1000 thru 25-TEA)
The turbocharger increases the power output and
efficiency of the engine by supplying compressed air to The turbocharger output is controlled through
the intake manifold. The engine exhaust is routed to coordinated action of the variable wastegate valve and
turbine wheel ofturbocharger assembly. The amount of absolute pressure controller system when set up
exhaust gas passing over the turbine wheel is properly. (See Figure 81-2).
controlled by a waste gate assembly. Exhaust gas CAUTION
passing over the turbine wheel causes the compressor, h is mandatory that the turbocharger system be
mounted on the same shaft, to rotate. Ambient ram air,
properly adjusted prior to operation. See
supplied through an air intake on right side of cowling, Section 714050 for -MB 3 SE engine set up
is filtered and routed to the compressor where it is
procedures.
compressed and delivered to engine. As engine power
is increased, the flow of exhaust over turbine wheel TURBOCHARGER OVERBOOST PROTECTION
also increases, resulting in a proportionate increase in (25-1000 thru 25-TEA)
the speed of the rotating assemblies and turbocharger
The -MB 3 -SB engines overboost
incorporate
output. relief valve located
protection through pressure
a
between the compressor and the throttle body. The
81-10-10 TURBOCHARGER CONTROL SYSTEM
relief Mlve will open to prevent excessive manifold
--(ROTOMASTER)
pressure a a malfunction in the tu~ocharger regulation
thru system occurs.
(srm 99-9991 25-0999)
81-~10-21 -Adjustment 3 Test Procedures
The turbocharger output is controlled by the throttle
See Section 71-00-50.
control in the cockpit indirectly dun’ng flight operations.
The fuced waste gate assembly is a ground adjustable SM 25´•~ 000 through 252012*
unit only (Ref. Fig. 81-1). The overboost valve should open and allow the engine
manifold pressure to stabilize between 37.0 3 38.0
CAUTION
inches Hg. if operating properly. If manifold pressure
It is mandatory that the waste gate be properly exceeds 38.0 inches Hg. dun’ng this check, the
adjusted prior to aircraft operation. See Section overboost valve should be replaced.
71-0050 for -GB or -LB Engine Setup
Procedures. CAUTION
DO NOT exceed 38.0 Inches Hg. manifold
TURBOCHARGER OVERBOOST PROTECTION pressure for more than ten (10) seconds.
(SrN 25-0001 thru 25-0999) S/N 25-2013 through 25-TEA’

The overboost valve should open and allow the engine

The -GB 5 -LB engine incorporate overboost protedion manifold pressure to stabilize between 39.0 3 40.0
through a pressure relief valve located between the inches Hg. if operating properly. If manifold pressure
compressor and throttle body. The relief valve will open exceeds 40.0 inches Hg. dun~ng this check, the
to prevent excessive manifold pressure if the throttle is
overboost valve should be replaced.
inadvertently opened beyond limits.
Referto Airesearch and TCM Service and Maintenance
Manuals for detailed maintenance data.
81-10-11 -Test Procedures
’SM 252000 thru 25-2012 may be retrofrtted to-SE
(See Section 71-00-51, 3, 1, (3). engine configuration, if desired by owner, by complying
With Mooney Aircraft Corporation retrofit drawing.
The overboost valve should open and allow the engine
manifold pressure to stabilize between 42.0" and 44.0" -ALTERNATE AIR SYSTEM
81-1030
Hg. if his operating properly. If manifold pressure TURBOCHARGER OPERATION
exceeds 44.0" Hg. during this test, the overboost valve
should be replaced. The tu~charger system will continue to operate when
the pn’mary air source is obstructed. An engine
CAUTION altemate air system is provided (automatic system on
Do not exceed 40.0" Hg. for more than ten (10) SM 25-0781 thru 25-TEA) to allow air from inside the
seconds. cowling to pass through the compressor and into the
engine. This air is warmer than primary air so less
NOTE power will be available at normal throttle settings.
Inspect turbocharger per TCM Service Bulletin NOTE
No. M833 later information
or Inspection of the induction system and
(Ref. AD 82-07-03). turbocharger assembly should be conducted
after any obstruction of the primary air source
prior to the next engine operation.

81-00-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE

oveReoosr
s*Fm V*LYE
COUPRE~SOR

LEGEWD
rHRorrLE I e´•´• R*Y~I

IIR

Cr, EXHIUSI GIS

c:3

r:3
I I- IUABI~E

\Ll\n~´•ll,

cRovao

I*ILPIPE
WISTLCITEY*LVE

TURB.OCHARGER SYSTEM (25-0001/25-0999) FIGURE 81-1

IHTt~tCObLElt

OVL~BDOSI
IIFE1~ VILYE
COYILt~O(l

u~wD

’"9"" I e´•´• (uuw

ucl

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:=;3

VIII)*ILL
1UCI+E
IllfLOllt Y*LII

TURBOCHARGER SYSTEM (25-1000125;TBA) RGURE 81-2

81-20-00
 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
81-20-00 TURBOCHARGER TROUBLESHOOTING

PROBABLE CAUSE REMEDY

TROUBLE

Excessive noise or vibration. Improper bearing lubrication. Supply required oil pressure. Clean
or replace oil line. If trouble
continues, remove turbocharger and
return to approved overhaul station
for overhaul or repair.

Leak in engine intake or Tighten loose connections, or replace

manifold. manifold gaskets as necessary.

will not deliver rated Clogged manifold system. Clean all ducting.
Engine
power.
in Remove turbocharger and return to
Foreign maten~al lodged
approved overhaul station for
compressor impeller or
turbine. overhaul or repair.

Excessive dirt buildup in Service engine induction air tilter and

check for leakage. Remove
compressor.
turt~ocharger and return to approved
overhaul station for overhaul or repair.

Leak in engine intake of Tighten loose connections, or replace

exhaust manifold, manifold gaskets as necessary.

Remove turbocharger and retum to

Rotating assembly bean’ng
approved overhaul station for
seizure.
overhaul or repair.

Remove turbocharger and return to

Compressor blades chipped,
approved overhaul station for
bent or missing,
overhaul or repair.

frozen. Remove turbocharger and return to

Impeller binding or

approved overhaul station for

overhaul or repair.

Critical altitude lower than Waste gate not properly Refer to Engine Set-Up Procedures,
adjusted. (25-0001--210999) Section 71-00-50.
specified,

Induction or exhaust system Perform leak checks.

leaks.

Remove turbocharger and return to

Compressor blades chipped,
approved overhaul station for
bent or missing.
overhaul OF repair.

Remove turbocharger and return to

Engine surges or smokes. Oil leaking into turbine wheel
approved overhaul station for
chamber.
overhaul or repair.

Clogged breather. Check breather for restn’ction to air

flow.

81-20-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE

BLANK

81-20-00
 OLDWILLWAYNE

C H A PT E R
SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

OLDWILLWAYNE
CHAPTER 91

ELECTRICAL WIRING PARTS LIST 8 DIAGRAMS

LIST OF EFFECTIVE PAGES

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91-00-00
4. 997
91-00-02
5. 9-97
91-00-02
6. 997
91-00-03
7. 997
91-20-01
9 thru 34 497
91-20-01
35 thru 60 897
91-20-02
61 thru 76 9-97
91-20-03
77 thru 89 9-97
91-20-04
90 9-97
91-30-00

TABLE OF CONTENTS

SUBJECT PAGE
CHAPTER
SECTION
SUBJECT

General 3
91-00-00
Notes
Electrical System 3
91-00-01
4
91-00-02 Wiring Identification System
Abbreviations Equipment List 7
91-00-03
Electn’cal System Hardware Charts 7
91-20-00
250001 THRU 25-0999 (14V) 9
91-20-01
25-1000 THRU 25-1224 (28V) 35
91-20-02
25-1225 THRU 25-1999 (28V) 61
91-20-03
252001 THRU 25-2012 (28V) 77
91-20-04
25-2013 THRU 25-TBD (2sV) 77
91-20-04
25TBDTHRU 25TBA (2sV) 77
91-20-04
Eledrical system Schematics (ENVELOPES) 90
91-30-00

91-EFF/CONTENTS
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MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
91-00-00 -GENERAL
The electrical system hardware lists and related schematics are sequenced in this section by setial number
effectivity. The chapter is divided into the following sections:
-Electrical Systems Schematic Notes
-Win’ng Identification System
-Electn~cal System Hardware Charts (By Effectivity)
-Electn’cal Schematics (By Effectivity)

91-00-01 ELECTRICAL SYSTEMS SCHEMATICS NOTES

1. All eledricalwin’ng, assemblies, and installtions must be in accord with FAR 43 and AC 43.13-1A.
2. All splices must be "AMP" disconnect or equivalent.
3. All circuit breakers are trip-free.
4. All terminals are Spec. MS25036 (or equivalent orthey must be soldered.)
5. All terminals must be preinsulated or must be insulated with "Ampsulation" (or equivalent).
6. Wires without dash numbers are furnished by the manufacturer and are included with the equipment.
7. The symbol indicates a knife disconnect.
8. Optional equipment may be installed as required.
9. Wires denoted by symbols to be twisted counter clockwise with a minimum of three (3) wraps
per foot.
10. "F" denotes ground through frame (00 wires).
cord.
11.All knife disconnect splices to be insulated with PVC105 and securely stn~ng tied with airtex no. 417
12. All wire sizes are minimum sizes acceptable.
bus
13. Use 913127 bus bars as necessary for van’ous configuration changes and manufacture interconnecting
2170 tubular braid covered with PVC105/5/16" (both Alpha Wire Co.) and terminated with AMP
using no.
terminals of appropn’ate sizes.

35108 Termin~l

PVC 105/ 5/16"

170 Tubula
Braid

3~7218 Ampsula-tion
Termino~l

U(AMPLE- 91-1

91-00-00
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
91-0092 -WIRING IDENTIFICATION SYSTEM
Under the Mooney win’ng system, a typical Wire Identification Number is 21PA03A18. This 9-character number is

composed of five functional groups, each of which communicates certain specific information. These functional
groups are as follows:

21 first two numerals (25-0001 thru 25-0999) Aircraft Type (12V)

or
JK first two numerals (251000 thru 251999) Aircraft Type (24V)
PA first two letters Circuit Function
03 -second setofnumerals Wire Sequence
A single letter in the series Configuration
18 lasttwo numerals in the series Wire Size

CIRCUIT FUNCTION LEGEND

The Eledn’cal Item numbers listed below referto item number identification (the first two letter portion of the
identification numbers) as listed on drawing schematic 800330, 800350 and 800263 only.

CB Defroster Blower
CC Cowl Flap
CD PC Dump
CF Wing Flaps- Electn’e
CT Trim
CV Stand-by Vacuum

DA Instruments- Ammeter
DB Instruments Tum Coordinator
DC Instruments Cylinder Head Temperature
DD Instruments Outside Air Temperature
DE Instruments Cart~uretor Air Temperature
DF Instruments- Fuel Quantity
DG Instruments Cluster Gauge
DH Instruments- Oil Temperature
DJ Instruments- Oil Pressure
DK Instruments- Fuel Pressure
DL Instruments- Tachometer
DM Instruments Hour Meter
DN Instruments- Pressun’zation
DP Instruments Pitot Heat
DR Instruments Turbine Inlet Temperature
DS Instruments Compressor Discharge Temperature
DT Instruments Exhaust Gas Temperature
DU Instruments- Manifold Pressure
DV Fuel Flow

EG Eledn’e Gear Gear Controls

EL Lighting- Electroluminescence
ELT Emergency Locator Transmitter
FON Phones

JM Ignition- Magneto
JV Ignition- Vibrator
LB Lighting Rotating Beacon (Anticollision Light)
LC Lighting- Cabin Lights
LL Lighting Landing Lights
LN Lighting Navigation Lights
LP Lighting Instrument 8 Placard Lights
LS Lighting Instrument 8 Strobe/Navigation Lights
LT Lighting -Taxi Lights

91-00-02
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
CIRCUIT FUNCTION LEGEND (con’t~

MA Miscellaneous Au>dliaryPower Plug

MB Miscellaneous Radio Circuits
MC Miscellaneous Cigar Lighter
MD Miscellaneous Clock Light
ME Miscellaneous Electric Clock
MIC Miscellaneous- Microphone
MM Miscellaneous Marker Beacon
MP Miscellaneous Propeller De-ice
MS Miscellaneous Radio Speaker
NF Fuel- Fuel Pump
NP Fuel- Primer

PA Power Altemator (output Control)

PB Power Battery (Output Control)
PG Power- Generator (Output 8 Control)
PS Power Starter (input 8 Control)

SPK Speaker
VB Vent Air Blower

WA Warning System -ARemator- Voltage Waming

WE Warning Engine Boost
WE Waming System Gear Position Warning (Electric)
WF Warning System- Fuel Pressure
WL Waming System Landing Light
WM Warning System Gear Position Waming (Manual)
WN Warning System Pressurization
WS Warning System Stall Warning
WT Waming System Press-to-Test
WV Warning System Vacuum Warning
WW Waming System Alternate Air
WD Warning System Starter Power
CIRCUIT FUNCTION LEGEND
The Electrical Item numbers listed below referto item number identification as listed on drawing schematic
800383.

AC AIR CONDITIONER
AH ARTIFICIAL HORIZON
AT ACTUATOR, SWITCH
AV AVIONICS

BR CIRCUTT BREAKERS
BS RELAY BASE
BU BUS BARS

CA CAPACTTORS
CB DEFROSTER BLOWER
CC COWL FLAPS
CD PC DUMP
CF WING FLAPS
CL CLAMPS
CR RUDDER TRIM
CT ELEVATOR TRIM
CV STAND-BY VACUUM

DA INSTRUMENTS-AMMETER
DB INSTRUMENTS- TURN COORDINATOR
DC INSTRUMENTS CYLINDER HEAD TEMPERATURE
DD INSTRUMENTS OUTSIDE AIR TEMPERATURE
DE INSTRUMENTS CARBURETORAIR TEMPERATURE
DF INSTRUMENTS FUEL QUANTITY
DG INSTRUMENTS- ENGINE

91-0M)2
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
DH INSTRUMENTS O1L 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
DR INSTRUMENTS TURBINE INLET TEMPERATURE
DS INSTRUMENTS COMPRESSOR DISCHARGE TEMPERATURE
DT INSTRUMENTS EXHAUST GAS TEMPERATURE
DU INSTRUMENTS MANIFOLD PRESSURE
DV INSTRUMENTS FUEL FLOW
DW INSTRUMENTS ENGINE VACUUM

EG GEAR, ELECTRIC
EL ELECTROLUMINESCENCE
ET EMERGENCY LOCATOR BEACON

FA ALT-EMER (FRENCH)
I=H FUSE HOLDERS
FN PHONES
FU FUSES
NV ALT-EMER FIELD (FRENCH)

GD GROUND

HS HORIZNTAL SITUATION INDICATORO

JE IGNITION, ELECTONIC
JM IGNITION, MAGNETO
JV IGNITION, VIKBRATOR

LA LIGHT BULBS
LB BEACON, ROTATING
LC LIGHT, CABIN
LE LENS, ANNUNCIATOR
LG LIGHTS, LOGO
LH LAMP HOLDER
LI LIGHT, ICE
LL LIGHT, LANDING
LN LIGHTS, NAVIGATION
LP LIGHTS, PANEL
LR LIGHTS, RECOGNITION
LS LIGHTS, STROBE
LT LIGHTS, TAXI

MA AUXILIARY POWER
MB RADIO, MASTER
MC CIGAR LIGHTER
ME CLOCK, ELECTRIC
MH MISCELLANEOUS, ANTI-ICE
MJ MISCELLANEOUS, JUNCTION BOX
MK MICROPHONE
MM MISCELLANEOUS, MARKER BEACON
MO PROP OVERSPEED
MP PROP DE-ICE
MS MISCELLANEOUS, RADIO-SPEAKER
MW MISCELLANEOUS, RADIO-WARNING

NE FURL ENRICHMENT
NF FUEL PUMP
NP FUEL PRIMER
NS FUEL COLD START

91-00-02
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
PA POWER, ALTERNATOR
PB POWER, BATTERY
PG POWER, GENERATIOR (OUTPUT CONTROL)
PL PLUGS
PS POWER, START

RE BLOWER, RADIO
RC RECEPTACLES
RL RELAYS
RS RESISTORS

SA STAND-BY ALTERNATOR
SE SPEEDBRAKE
SP SPEAKER
SW SWITCHES

VB VENT, AIR BLOWER

VC VOLTAGE CONVERTER
VR VARISTOR

WA WARNING, ALTERNATOR
WE WARNING, BOOST PUMP
WC WARNING, PROP DE-ICE
WD WARNING, POWER START
WE WARNING, ELECTRIC GEAR
WF WARNING, FUEL QUANTITY
WG WARNING, TACHOMETER
WH WARNING, CHIP DETECTOR
WK WARNING, FUEL PRESSURE
WL WARNING, CANOPY LOCK
WM WARNING, MASTER
WN WARNING, PRESSURIZATION
WP WARNING, PITOT HEAT
WS WARNING, STALL
WT WARNING, ANNUNCITOR
WV WARNING, VACUUM
WW WARNING, ALTERNATE AIR

9140-03 -ABBREVIATIONS EQUIPMENT LIST

The abbreviations to the electn’cal system hardware charts are necessary due to space limitations in the fields of
the computer.

Airspeed- AIS Placard- Pled

AItemate- Alt Radio- Rad
Circuit Breaker CM. Bkr. or C/B Receptacle Recpt
Console- Cnsl Regulator- RegItr
Control- Cntrl Remote- Rem
Coordinator- Coordtr Resistor- Res
Cylinder- Cyl Rheostat- Rheo
Down- Dn Right-R
Electn’c- flee Safety- Sfty
Flight- Fit Selector- Sel
Glareshield- Glrshld Supply- Spry
Landing- Ldg Switch- Sw
Leff-L Transducer- XDCR
Lights- Lts Transmitter- XMTR
Panel- Pnl Trans~tor- XSTR
Pilot- Pit Waming- Wm

91-00-03
 SERVICE AND MAINTENANCE MANUAL M20K MOONN AIRCRAFT CORPORATION

OLDWILLWAYNE
91-20-00
ELECTRICAL SYSTEM HARDWARE CHARTS
Refer to the Electrical Schematic (located in the envelopes at the back of this
manual) that depicts the Sen’al
Number configuration of the aircraft being serviced. The S/N’s vs. Schematic’s are shown below:
A/C SERIAL NUMBER SCHEMATIC DRAWING NUMBER

(14 VOLT AIRCRAFT)

25-00021 thru 25-0171 800330 F
25-0238 thru 25-0246 800330 F1
25-0001,25-0247 thru 25-0298 800330 F2
25-0299 thru 25-0446 800330 F3
25-0447 thru 25-0612 800330 F4
25-0613 thru 25-0780 800330 F5
250781 thru 25-0841 800330 F6
25-0842 thru 25-0999 800330 R

(28 VOLT
25-1000 thru 24-1224 AIRCRAFT~ 800350 K1

25-12251hru 25-1999 800263 K1

25-2000 SCHEMATIC NOT rNCLUDED IN ENVELOPES 800383 K1

25-2001 thru 25-2012 800383 K2
25-2013 thru 25-TBD 800383 K3
25-TBD thru 25-TEA 800383 K4

The Vendor and Part Number will be depicted where the

applicable eledrical equipment identifier is shown on the
following hardware charts.

91-20-00
 MOONE/ AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMENT CHART

91-20-01 ELECTRICAL SYSTEM HARDWARE CHART -14 VOLT

SERIAL NUMBER’s 25-0001 THRU 25-0999, MOONC/ DRAWING NUMBER. 800330
(CP)
CODE DESCRIPTION VENDOR PART NO. NOTES

21 CB1OIA C/B DEFROSTER BLOWER KLU(ON 7277-2-2

21 CDO1A SOLENOID-PC DUMP BRITIUU\I 4085
21 CD02A SV\FPILOTS DUMP MICRO I11SM1-T
21 CDO28 SWPILOTS DUMP CUTLER-HAMMER SA31SDT12-2
21 CD03A SWCO-PILOTS DUMP MICRO I11SM1-T
SWP.C. ON-OFF (ALT) ALCO MST21 5-N
21 CFO1B C/B FLAP ACT MERIDU\I orEQUIVALENT AHVW-15
21 CF02A RELAY-LEFT MAGNECRAFT Wl97CSX-1
21 CF03A RELAY-RT MAGNECRAFT ~97CSX-1
21 CFO4A ACTUATOR, FLAP COMMERCIAL AIC PROD D~4500-36
MOONEY (750105501)
21 CFOSA SWITCH, LIMIT, D0~1 MICF~O V3-1
ACTUATOR MICF~O JV-5
21 CFOGA SWITCH, LIMIT, UP MICRO V3-1
ACTUATOR MICRO JV-5
21 CFO7A SWITCH, LIMIT, DOV~ MICRO V3-1
ACTUATOR MICRO JV-5
21 CF08A SWITCH, LIMIT, UP MICRO V3-1
ACTUATOR MICRO JV-5
21 CFOSA SWITCH, CONTROL MICRO 2TL75´•10
21 CFOSB SWITCH, CONTROL, FLAP CUTLER-HAMMER 8906K3149

21 CTO1A C/B, ELECTRIC TRIM MOONEY 93002~009

21 CTO?B C/B, ELECTRIC TRIM MOONE/ 930023´•109
21 CTO1D C/B, ELECTRIC TRIM MOONC/ 930023-209

21 DAO1A SHUNT EMPRO or EQUIV. MLA-60´•50

21 DAO1B SHUNT STEVVART-V\WWER SV\C81 3489
21 DAO1C SHUNT EMPRO MLA-60´•1 00
21 DAO1D SHUNT EMPRO MLA-70-1 00
21 DA02A FUSE LTTTEL 312010
RETAINER LTTTEL 155020
21 DAOZB FUSE McGRAWEDISON FMO1-5A
RETAINER McGRAWEDISON FHN42W
21 DA03A FUSE LTTTEL 311010
RETAINER LTTTEL 155202
21 DA03B FUSE McGRAWEDISON FM01-5A
RETAINER McGRAWEDISON FHN42W
21 DA04A AMMEIER MOONEY 640281-509
BULB ROCHESTER 0´•1 53500003

21 DBO1A C/B, TURN COORD MWDAN OR EQUIV AHVW-2

21 DBO1B C/B TURN COORD KLlXON 7277-2-5
21 DB02A TURN GO-ORDINATOR BRITT1AN 604-200´•200 23/24
TURN GO-ORDINATOR AEROSONIC (ALT) ANSS0M 23/24
21 DB02B TURN GO-ORDINATOR AEROSONIC ANSS0ML 23124
21 DB03A PLUG, TURN COORD MS3106A-10SL-3S
CLAMP MS3057-4A or-4B

91-2Q´•01
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMENT CHART

--L DBS0A T/C UNITED INST 95516 CODE N.541

21 DCO1A PROBE, CYL HD TEMP STNWRT-VU4RNER S\N333-B
21 DCO1B PROBE, CHT ROCHESTER 3080-00014
MOONEY (88001 0-501)
21 DCO1C PFIOBE, CHT MOONEY 88001 0-503
11
21 DDO1A GAUGE, OU7SIDE AIR TEMP GARV\nN 22-295
21 DDO1B GAUGE, OAT INSTR& FLT RES. IFR-1IA
21 DDO1C GAUGE, OAT/EGT B&D INSTRUMENT C203-005
MOONfr’ 88001 0-501
21 DDO1E GAUGE, OAT/EGT(LIGHTED) MOONEY 880001-505
21 DDO1F GAUGE, OAT(LIGHTED) MOONEY 880023´•505
21 DD02A PLUG -GAUGE MS31 06A-1 4S2S
CLAMP MS3057-6B
21 DD02C PLUG,OAT/EGT AMP 205838-1
CLAMP AMP 206062-1
21 DD02D PLUG,OAT MS31 06A-1 4S2S
CLAMP MS3057-6A
21 DD03A PROBE, OAT MS2803403
21 DDOBB PROBE, OAT V~STBERG 399\1\1
21 DD03C PROBE, OAT B&D INSTR 0203-1 00
MOONN 880004-501
21 DD04A C/B, OAT/EGT KUXON 7277-2-2

21 DEO1A GAUGE, CARE AIR TEMP MOONEY 660014-005

GARWIN 22-99504
21 DE02A PLUG, GAUGE MS3106A-1 4S1 S
CLAMP MS3057-6B
21 DE02B PLUG, GAUGE MS31 06&14S12S
CLAMP MS3057-6B
21 DE03A PROBE, CARE AIR TEMP RIGHTER AERO 85

21 DF=O1A XMTR FUEL QTY, LT, IB MOONEY 610242-001

21 DFO1B XMTR, FUEL QTY, LT, IB MOONEY 610242-003
21 DF02A XMTR FUEL QTY, LT, OB MOONEY 610243403
21 DF03A XMTR FUEL QTY, RT, IB MOONEY 61 0242-001
21 DFOBB XMTR, FUEL QTY, RT, IB MOONEY 61 0242-003
21 DF04A XMTR FUEL QP~ RT, OB MOONEY 61 0243-001
21 DGO1A C/B, CLUSTER GAUGE MERIDW AHW4-2
21 DGO1B C/B, CLUSTER GAUGE KLIXON 7277-2-2
21 DG02A GAUGE, CLUSTER MOONN 640281-503
FUEL QTY, LH MOONEY 640281-1 05
FUEL QTY RH MOONN 640281-107
AMMETER MOONfl 640281-115
OIL PRESS MOONEY 640281-117
OIL TEMP MOONEY 640281-149
CYL HEAD TEMP MOONEY 640281-111
21 DGMG GAUGE, CLUSTER MOONEY 640281-507
FUEL QP~ LH MOONC/ 640281-1 05
FUEL QTY, RH MOONEY 640281-107
FUEL PRESS MOONEY 640281-119

91-20-01
10
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
OLDWILLWAYNE
OIL PRESS MOONEY 640281-121
21 DG02G
OIL TEMP MOONEY 640281-149
Cn HEAD TEMP MOONN 640281-511
GAUGE, CLUSTER (ALT) MOONN 640281-511
(ALT)
FUEL QTY, LH MOONE/ 640281-125
FUEL QTY, RH MOONE/ 640281-127
FUEL PRESS MOONEY 640281-131
OIL PRESS MOONEY 640281-129
OIL TEMP MOONEY 640281-133
MOONN 640281-155 33
OIL TEMP (ALT)
Cn HEAD TEMP MOONEY 640281-135
MOONEY 640281-157
CnL HEAD TEMP (ALT)
DG02H GAUGE, CLUSTER MOONEY 640281-513
21
FUEL QTY, LH MOONEY 640281-147
FUEL Q7Y, RH MOONEY 640281-145
AMMETER MOONEY 640281-137
OIL PRESS MOONEY 640281-141
OIL TEMP MOONEY 640281-139
CYL HEAD TEMP MOONEY 640281-143
MOONEY 640281-515 32
(ALT) GAUGE, CLUSTER
FUEL QTY, LH MOONE/ 640281-153
FUEL QTY, RH MOONCI 640281-151
AMMRER MOONEY 640281-137
OIL PRESS MOONE/ 640281-141
OIL TEMP MOONEY 640281-1 39
MOONN 640281-159 34
OIL TEMP (ALT)
CM HEAD TEMP MOONEY 640281-143
MOONE~ 610281-161 34
CYL HEAD TEMP (ALT)
21 DGOU GAUGE, CLUSTER MOONEY 640281-519
FUEL QPr~ LH MOONEY 640281-163
FUEL QTY, RH MOONN 640281-165
FUEL PRESS MOONEY 640281-171
OIL PRESS MOONEY 640281-133
OIL TEMP MOONN 640281-155
CML HEAD TEMP MOONN 640281-135
21 DG02K GAUGE, CLUSTER MOONEY 640281-521
FUEL QP~ LH MOONEY 640281-153
FUEL QTY, RH MOONEY 640281-151
AMMEIER MOONEY 640281-1 37
OIL PRESS MOONEY 640281-169
OIL TEMP MOONEY 640281-1 39
CYL HEAD TEMP MOONEY 640281-1 43

21 DHO1A PROBE, OIL TEMP STEV\rAFIT-VWRNER 362-CR

21 DHO1B PROBE, OIL TEMP ROCHESTER 3080-37

MOONEY 880004501
\RtASHER AN900-10 or MS3576411

21 DJO1A XDUCR, OIL PRESS ROCHESTER 3080-37

MOONE/ 880008´•501
21 DJO1B XDCR, OIL PRESS MOONE/ 880046-501
21 DJ02A PLUG, XDCR OIL PRESS MS3106A10SL-3S
CLAMP MS3057-4AIB

91-20´•01
?1
SERVICE AND MAINTENANCE MANUAL M20K MOONN AIRCRAFT CORPORATION

OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMENT CHART

21 DJ175A XDCER, OIL PRESS DRUCK PDCR821-0662-100

21 DJ177A AMPLIFIER, OIL PRESS IAI 950D0311-002
21 DJ178A PLUG, OIL PRESS, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
21 DJ179A RECPT, OIL PRESS, 4 PIN AMP 206153-1
CLAMP AMP 206062-1
21 DJ180A PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
21 DJ1S1A RECPT, 4 PIN AMP 206153-1
CLAMP AMP 206062-1
21 DKO1A XDUCR FUEL PRESS ROCHESTER 3060´•17
MOONfl 880007-501
21 DKO1C/D XDUCFFFFFOOm) MOONEY 880039501
21 DKO1D XDUCR FUEL PRESS MOONE/ 880045-501
21 DKO1E XDUCR FF MOONEY 880030-503
21 DKO1F XDUCR, FUEL FLOW MOONEY 880030-505
21 DK02B GAUGE, FF/MP MOONEY 880031-531
GAUGE, FF/MP, LIGHTED (OPT) MOONEY 880031-503
MOONEY 880034-501 25
21 DK02D/E GAUGE,FF(Om)
21 DKO2F GAUGE, (GALS/HR) MOONEY 880034-513
21 DK03A PLUG, FF/MP GAUGE BENDIX mDGA-i 0-98S(SFi)
21 DKOBB PLUG, FF BENDD( m06A-1515S(SFP
21 DK03C/D PLUG,FF TTT CANNON DE-SS
21 DK03UF PLUG, FF tom, CANNON DE-SS
21 DK04A C/B, FF KLIXON 7277-2-2
21 DKOSA SWITCH, MEMORY, FF (OPT) ALCO MST21 5N
21 DK06A PLUG, FF, XDCR MS3I 06A~1 0SL-3S
CLAMP MS30507-4A
21 DK1 75A XDUCR, FUEL PRESS DRUCK PDCR821-0662-30
21 DK176A AMPLIFIER, FUEL PRESS W 950D0311-031
21 DK1 77A PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
21 DK178A RECPT, 4 PIN AMP 260153-1
CLAMP AMP 206062-1
21 DK179A PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
21 DK180A RECPT; 4 PIN AMP 260153-1
CLAMP AMP 206062-1
21 DLO1A TACH, ELEC MOONEY 880002-501 3
21 DLO1B TACH, ELEC MOONEY 880034503
21 DLO1C TACH, ELEC MOONEY 880002-503
21 DLO1D TACH, ELEC MOONE/ 880039501
21 DLO1E TACH, ELEC MOONE/ 880039507
21 DLO1F TACH, ELEC, (LIGHTED) MOONC/ 880039505
21 DL02A PLUG, TACH MS31 06A-1 4S5S
CLAMP MS3057-6A
21 DL03A RESISTOR, L OHMITE 535
OL~1
21 DL04A RESISTOR, L OHMITE 535
OL~1
21 DLOSA CABLE ASSY MOONEY 880003-501

21 DMO1AIB HOURMETER MOONEY 880035-501

91-20-01
12
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMENT CHART

21 DPO1A C/B, PITOT HEAT MOONEY 930023´•005

21 DPO1B C/B, PITOT HEAT MOONE/ 930023-105
21 DW1D C/B, PITOT HEAT MOONEY 930023-205
21 DP02A HEATED PITOT AEL or EQUIV 425936
21 DW2B PITOT, HEATED AERO INST PH502-24
AN5812-1 (ALT)
21 DP03B PLUG, PITOT HEAT AN31 i 51
SOCKETS AN31181
21 DRO1A C/B, TIT/CDT KLIXON 7277-2-2
21 DROIB GAUGE, TIT/CDT, LIGHTED MOONC/ 880000-503
21 DR02A PLUG, TIT/CDT INDICATOR AMP 20583&1
21 DR03A PROBE, TIT MOONC/ 88000~501
21 DR04A C/B, TIT/CDT KLIXON 7277-2-2

21 DSO1A PROBE, CDT MOONEY 88001~501

21 DTO1A PROBE, EGT B&D INSTR 0204-1 00

MOONEY 880005501
21 EGO1A C/B, ELEC. GEAR MDUDEN or EQUIV AHWW-15
21 EGO1B C/B, ELEC. GEAR KWON 7277-2-15
21 EGO1C C/B, ELEC. GEAR CONTROL KUXON 7277-2-5
21 EG02A SWITCH, CONTROL MIC~O 2TLi49-3D
21 EG02B SWITCH, GEAR UP/DN CUTLER-HAMMER 8906K2875
21 EGOBA SWITCH, LIMIT MICF~O DT-2R-A7
ACTUATOR MICRO MCD2711
21 EG04A ACTUATOR, GEAR, ELEC ITT LAiiC21101
21 EG04B ACTUATOR, GEAR, ELEC DUKES 1057-0~1
21 EGO4C ACUTATOR, GEAR, ELEC DUKES 4196-00-1D
21 EG04D ACUTATOR, GEAR, ELEC ITT LAliC2115
21 EG04E ACUTATOR, GEAR, ELEC TTT LAI 1 C2114
21 EG04F ACUTATOR GEAR, ELEC DUKES 1057-00-5E
21 EG04G ACUTATOR, GEAR, ELEC AVIONICS PROD i 02000-1 26
MOONC/ 560254-501 3

21 EG05A RELAY, GEAR RBM 70-11 1221

21 EG05C RELAY, GEAR UP MAGNECRAFT V~’ICSX-I 1

21 EGOSD RELAY, GEAR UP CURER-HAMMER 6041H50A 1

21 EGOSE RELAY, GEAR UP RBM 70311221 22

21 EGOSF RELAY, GEAR UP CURER-HAMMER 6041H53

COLE-HERSEE 24401 22

21 EGOGA SQUAT SWITCH MICRO 1CHI-6

MOONEY 800335501
\M-IITMAN-GENERAL SK751N-K3L 5
21 EGOGB SWITCH, SAFETY, AIRSPEED
21 EGOGC SWITCH, SAFEP~ AIRSPEED MOONEY 880013-503 5

21 EGOGD SWITCH, SAFETY, AIRSPEED MOONEY 880013-505 5

21 EGO7A SWITCH, DOV~ LIMIT MICRO ICHIS

21 EG08C RELAY, GEAR DO\R´•N MAGNECRAFT V~37CSX-1
21 EGO8D RELAY, GEAR DOV\IN CUTLER-HAMMER 6041Hi 05A
21 EGO8E RELAY, GEAR DOVI~N RBM 7~311221 22
21 EG08F RELAY, GEAR DOV~ CUTLER-HAMMER 6041H105A
21 EGOSA C/B, GEAR ACT MECHANICAL PROD 700-01-25
21 EGOSB C/B, GEAR ACT KLO(ON 7271-2-15
21 EG1OA SWITCH, GEAR OVWDE CUTLER-HAMMER SBIDDX492-2
LAMP GE 388

91-20-01
13
 SERVICE AND MAINTENANCE MANUAL M20K MOONCIAIRCRAFT CORPORATION

OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMENT CHART

21 EG11A DIODE, GEAR UP RELAY SARKES TARZIAN F4

21 EG12A DIODE,GEAR DN RELAY SARKES TARZIAN F4
21 ELO1A TRANSISTOR RCA 2N2016
21 EL02A FUSE McGRAWEDISON FM01-5A
HOLDER FHN42W
21 EL03A RESISTOR OHMTTE 4599
21 EL04A RHEOSTAT/SW AIl~EN/BRADLEY JS1 N056P251 MA
21 ELOGA PLACARD, CB MOONN 150082-009
21 EL07A PLACARD, FUEL SEL MOONEY 150082-011
21 EL08A PLACARD, ANNUN MOONEY 150082-015
21 ELOSA PLACARD, CK. LIST MOONEY 150082-013

21 ELT1A ELT DORNE MARGOLIN DM-ELT-6 or-GM

21 ELT1B ELT,TRANSMITTER (OPT) DORNE MARGOLIN DM-ELT-8
21 EL72A SWITCH, REMOTE ELT DORNE MARGOLIN DM-U651
(ALT) C&K 71 01K
21 EV~O1B C/B, GEAR V~ARNING KLIXON 7277-2-2
21 JMO1A SWITCH, MAGNETO BENDIXSCINTILLA 10-357290-17
PLACARD BENDIX- SCINTILLA 10´•187-468
21 JMO1B SWITCH, MAGNETO BENDIXSCINTILlA 10´•357210-91
21 JM02A MAGNETO, LEFT BENDIX-SCINTILlA S4LN200
21 JM02B MAGNETO, DUAL BENDIX-SCINTILlA D4LN2021
21 JM02C MAGNETO, LEFT BENDIX 10-79020-18
21 JMO2D MAGNETO, LEFT SLICK 6214
21 JM02E MAGNETO, LEFT SLICK 6224
21 JM03A MAGNETO, RIGHT BENDIX S4LN204
21 JM03C MAGNETO, RIGHT BENDIX i 0-79020-18
21 JM03D MAGNETO, RIGHT SLICK 6214
21 JM03E MAGNETO, RIGHT SLICK 6224
21 JM1A STARTING VIBRATOR BENDIX-SCINTILLA 10-176487-121

21 LBOIA C/B,’ROTATING BEACON MOONEY 930023-003

21 LBO1B C/B, ROTATING BCN(SPARES) MOONEY 930023-103 28
21 LBO1D C/B, ROTATING BEACON MOONN 930023-203
21 LB02A LIGHT, ROTATING BEACON WHELEN \R´•RML-12
ADAPTER V~WI-65
21 LCO1A FUSEHOLDE, CLOCK, 5AMP LITTEL FUSE 155020/155120
FUSE,(5A-3AGSLO-BLO) LITTEL FUSE 31 3005
21 LC02A LIGHT, CABIN, OVERHEAD LUMINATOR 20145
BULB GE 1003
21 LCO2B LIGHT, CABIN, OVERHEAD GRIMES B-3550
BULB GE 89
21 LC03A SWITCH, CABIN LIGHT CUTLER-HAMMER 8144(8K-09)
21 LCOSB SWITCH, CABIN LIGHT CARLING TILC64-IS\RM-M
21 LC03C SWITCH, CABIN LIGHT REAR CARUNG TlLC64-1 SV\M-M
21 LC03D SV~TCH, CABIN LIGHT, F~ CARUNG TILCGdlSV\M-FN
21 LC03E SWITCH, CABIN LIGHT, REAR CARUNG IILC64-ISV\M-M
21 LC04A RESISTOR, DIM, CABIN LT OHMTTtZ 4561
(10 OHM 5W)
21 LCO4B/C RESISTOR, DIMMING, CABIN UGHTDALE RH-10-5 OHM
21 LC07A SWITCH, MAP LIGHT, PILOTS CUTLER-HAMMER SA25SCT12-3
CAP SV~j3AA2
FACE NUT 15-i 0443

91-20-01
14
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMENT CHART

21 LC08A LIGHT, MAP, PILOTS SLOAN 855S1-0-PE

BULB GE 330

LCOSA SV\nTCH, MAP LIGHT, GO-PILOT CUTLER-HAMMER SA25SCT12-3

21
CAP
I
S~i3AA2
FACE NUT
I
i 510443

21 LC1 OA LIGHT, MAP, GO-PILOT SLOAN

BULB GE 330
H.H. SMITH i 930 9
21 LC11A LIGHT, CABIN, (FI-R)
LAMP GE 1816
H.H. SMIT-I 1930 9
21 LC12A LIGHT, CABIN, (F2-R)
LAMP GE 1816
H.H. SMITH 1930 9
21 LC13A LIGHT, CABIN, (F1-L)
LAMP GE 1816
H.H. SMITH 1930 9
21 LC14A LIGHT, CABIN, (F2-L)
LAMP GE 1816
H.H. SMITH 1930 9
21 LC1SA LIGHT, CABIN, (R1-R)
LAMP GE 1816
H.H. SMITH 1930 9
21 LC1GA LIGHT, CABIN, (~2-R)
LAMP GE 1816
H.H. SMITH i 930 9
21 LC1’IA LIGHT, CABIN, (R1-L)
LAMP GE 1816
H.H. SMITH 1930 9
21 LC18A LIGHT, CABIN, (~2-L)
LAMP GE 1816

21 LLO1A C/B, LDG LT MWDEN AHW4-20

21 LLO1B C/B, U3G LT MOONN 930023-15

MOONN 930023-115/-215 28
21 UOIC/D C/B, LDG LT
21 U02A RELAY, LDG LT MAGNECRAFT VlS9CQX-2

21 LL03A LIGHT, LDG GE 4522

21 U03B/C LIGHT, LDG GE 4509

21 LL04A SV\nTCH, LDG LT CUTLER-HAMMER SA25SCTi2-3

CAP
I
SM63AA2
FACE NUT
1
15-10493
21 LJO1A C/B, NAV LIGHTS MOONEY 930023-001
MOONEY 930023-1 01/-201 28
21 UI~O1B/D C/B, POSITION LTS
21 LN02A LIGHT, POSITION (RED) GRIMES A1285R-12
MOONEY 800022-501
21 U\102B LIGHT, POSITION,(14V) (RED) W1285PR
21 LNO3A LIGHT, POSITION, TAIL OI\MITE) GRIMES A2064-1 Tn
21 LN03B LIGHT, POS, TAIL,(14V) OIERT.MT) \RMELEN A480A

21 LN04A LIGHT, POS, (GREEN) GRIMES Ai285G12

MOONN 880022-503
21 LN04B LIGHT, POS, (GREEN) V\MELEN W1285PG
MOONfl 880022-503
21 LPO1A C/B, PANEL LIGHTS MERIDEN AHVW-10

21 U>OIB C/B, PANEL LIGHTS KUXON 7277-2-10

21 LW1C/D C/B, INSTR LTS KUXON 7277-2-10
21 LP02A C/B, PANEL LIGHTS MERIDEN AHVW-10

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SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION

OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMENT CHART

21 LW3A XSTR, INSTR LIGHTS RCA 2N2016 8

21 LP03C XSTR RADIO LIGHTS RCA 2N2016 8

21 LPOSB XSTR (ALT LP03AIC) DELCO 2N3079

RADIO LIGHTS RCA 2N2016 8
21 LP04A XSTF1
RADIO LIGHTS RCA 2N2016 8
21 LPOSA XSTR,
21 LWGA RHEOSTAT/SWITCH ALLEN/BRADLC/ JS1 N056P251 MA
21 LPOGB/C RHEOSTAT/SWITCH, RADIO ALLU\UBRADLN JS1 N056P251 MA
21 LP07A RHEOSTAT/SWITCH, RADIO ALLU\UBRADLC/ JS1 N056P251 MA
21 LP08A RHEOSTAT/SWITCH, RADIO AUUJ/BRADLEY JSI N056P251 MA
21 LPOSA SWITCH, REDMMITE, LIGHT MICRO 8H2011
ROCKER MICRO 820023
21 LP1OC C/B, INSTR LIGHTS KLIXON 727/-2-5
21 LP13A FUSE, INSTR LTS McGRAWEDISON FMOI-SA
HOLDER FHN42W 9

21 U>14A RISE, INSTR LTS McGRAWEDISON FMOI-5A

HOLDER FHN42W 9

21 LP15A FUSE, INSTR LTS McGRAWEDISON mM01-5A

HOLDER RiN42W 9

21 LP1GA LAMPS (RED) GE 1836R

HOLDER (4 EA) H.H. SMITH 1930 9

21 LP17A LAMPS (RED) GE 1836R

HOLDER (7 EA) H.H. SMITH ’1930 9

21 LP? 8A LAMPS O~MITE) GE 1836

HOLDER (4 EA) H.H. SMITH 1930 9

21 LP1 88 LAMPS GE 1816

HOLDER (10 EA) H.H. SMITH 1930 9

21 U>1 8C LAMPS GE 1816

HOLDER (9 EA) H.H. SMITH 1930 9

21 LP1 8D LAMPS GE 1816

HOLDER (10 EA) H.H. SMITH 1930 9

21 LP1 8E LIGHTS, GLARESHIELD SLOAN 855S9-1

MOONEY 130285003
BULB (7 EA) GE 330
21 LP1 9A LAMPS GE 1838
HOLDER (6 EA) H.H. SMITH 1930 9

21 LP20A N# LIGHT(2 EA) KORRY 250-650-5821-008

BULBS GE 327
21 LP21A LIGHT, COMPASS GE 330
21 LP22A LIGHT-CONSOLE WESTERN IND CO. 501-61K-11K3BP
LAMP WESTERN IND CO WI-7046
21 LP22B LIGHT-CONSOLE WESTERN IND CO 501-61K-i 1K3BP
LAMP WESTERN IND CO V\n-7046
21 LP22C LIGHT HOLDER, FW> 8 TRIM DIALIGHT 270´•193M)1710702
LAMP GE 370
21 U>24A FUSE (5 AMP)(3AGSLO-BLO) L~EL 313005
HOLDER LITTEL i 55020
21 LP24B FUSE, MAP LITE LITTEL 313001
HOLDER LITTEL 155020 or 155120
21 LP25A RESISTOR 100 OHM 2W
21 LP25B RESISTOR, INSTR LITES OHMITE 4599 iO
21 LP25C RESISTOR, RADIO LT~ES OHMITE 4599 10
21 LP25D RESISTOR, INSTR LITES DALE RH-~0´•50 OHM (260901MRU24-09’
21 LP25E RESISTOR, INSTR LmS DALE RH-10-50 OHM

91-20-01
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 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
OLDWILLWAYNE
1Q VOLT ELECTRICAL EQUIPMENT CHART

GRIMES A-8970B1
21 LP26A LIGHT, POST, MIP
GE 330
LAMP
GRIMES A-8970B1
21 LP27A LIGHT, POST,TACH
GE 330
LAMP
GRIMES A-8970B1
21 LP28A LIGHT, POST, CLOCK
GE 330
LAMP
GRIMES A-8970B1
21 LP29A LIGHT, POST,OAT
GE 330
LAMP
SLOAN 855SO-U
21 LP30A HOLDER, OXYGEN LIGHT
GE 330
LAMP
MOONC/ 800233-000
21 LP31A BUSS, RADIO LIGHT
GRIMES A-8970B1
21 LP32A POST LIGHT
GRIMES A-8970B1
21 LP33A POST LIGHT
POST LIGHT GRIMES A-8970B1
21 LP34A
POST LIGHT GRIMES A-8970B1
21 LP35A
LAMP GE 330

LP36A LAMP, CLUSTER #1 G/E 330(AV1ATION BLUE)

21
GIE 330(AV1AT1ON BLUE)
21 LP37A LAMP, CLUSTER#2
LP38A LAMP, CLUSTER 3 G/E 330(AV1ATION BLUE)
21
G/E 330(AV1AT1ON BLUE)
21 LP39A 14MP, CLUSTER #4
LP40A LAMP, CLUSTER 5 G/E 330(AV1ATION BLUE)
21
DEANS DEA 90020
21 LP41A CONNECTOR, MALE
DEANS DEA 90020
21 LP42A CONNECTOR, FEMALE
LITTEL 313001
21 LP43A FUSE, (1A)
HOLDER L~EL 155020 or 155120
AMP 206060-1
21 LP44A CONNECTOR, PLUG
CLAMP AMP 206062-1

CONNECTOR, AMP 2061 53-1

21 LP45A
CLAMP AMP 206062-1

C/B RECOGNITION LIGHTS MOONEY 930023-231

21 LRO1A
RECOGNITION LIGHT, LT V\K; MOONEY 880044-001
21 LR02A
AMP 1-48031 8-0
21 LR03A PLUG, RECOG. LIGHT, LTV\K;
SOCKETS AMP 6061 91

RECOGNITION LIGHT, RT MOONEY 880049001

21 LR04A
AMP 1-48031 80
21 LR05A PLUG, RECOG. LIGHT, RT
SOCKETS AMP 6061 91
MOONEY 930023-007
21 LSO1A C/B, STROBE LIGHTS
MOONN 930023-107/-207 28
21 LSO1BID C/B, STROBE LIGHTS (ALT)
V\MELEN A490, T14 31
21 LS02A POV~ER SUPPLY, STROBE, UV~S
SDI 701295-3A 29, 32
21 LS02B POV~ SUPPLY, ST~OBE, UV~3
MOONEY 88001 &501 29

MOONEY 880028507 30
21 LS02C POV~R SUPPLY, STROBE, UWG
21 LS02E PO\I~ER SUPPLY, S~OBE U\RFG MOONN 880028-505(ALT)
21 LS02F CABLE, POVMR SUPPLY, UV\A3 MOONEY 880017-503(ALT)
LI~S \RMELUI~ A429 31
21 LS03A STROBELT~E(FLASHTUBE),
SDI 701 303A
21 LS03B STROBE, LTTE,
MOONN 88001 9501 29
FLASHTUBE
LS03B STROBE LT, ~K; SDI 702000-1
21
MOONEY 880021-501 34

MOONN 880038-501 30
21 LS03C STROBE LT, UV\K;
CABLE ASSY, STROBE, L~C; SDI 70200~3
21 LS03D
MOONEY 88001 7-501 29,34

91-20-01
17
SERVICE AND MAINTENANCE MANUAL M20K MOONFY AIRCRAFT CORPORATION

OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMENT CHART

21 LS03E CABLE ASSY, STROBE, L/WG MOONN 880017-503

POV~R SUPPLY, STROBE, RN~ V\MELEN A490, Ti4 31
21 LS04A
21 LS04B P/S, STROBE, WV\K; SDI 7012953A
MOONEY 88001 8501 29, 34
MOONEY 88002&507 30
21 LSO4C P/S, STROBE, W~S
21 LS04D CABLE ASSY, WWG SDI 70200~3
MOONEY 880017-501 29, 34
21 LS04E P/S, STt~lOBE,WV\AS MOONEY 880028505(ALT)
21 LS04F CABLE, P/S, RN\I~ MOONEY 880017-503(ALT)
V\MELEN A429 31
21 LSOSA FLASHTUBE, WWG
SDI 702000-2 34
21 LSOSB STROBE, LITE, WV\K;
FLASHTUBE MOONE/ 88001 9501 29
MOONEY 880021-502 34

LSOSC STROBE LT, WV\XS MOONEY 88003&502 30

21
21 LSOGA P/S, TAIL STROBE MOONEY 880038501 29,34
MOONEY 88002&507 30
21 LSOGB P/S;TAIL STROBE
21 LSOGC CABLE, TAIL STROBE MOONEY 880017-505(ALT)
MOONEY 880017507 29
21 LSOGD CABLE, TAIL LITE
21 LSO7A STROBE, TAIL MOONEY 880020´•501 29, 34
MOONEY 880041301 30
21 LS07B STROBE, TAIL
AMP 2067081 30
21 LS08A PLUG, TAIL STROBE
21 LSOSA RECPT, TAIL STROBE P/S AMP 1-4803050
PINS (3 EA) AMP 61118-1 OR 606291
21 MAO1A AUX PV~R RECEPTACLE AN2552-3A
21 MA02A RELAY,AUX PV~R CUTLER-HAMMER 6041H105A
21 MA02B RU4Y CUTLER-HAMMER 6041Hi05A
21 MA03A DIODE, AUX PV~R RUAY SARKES TARZIAN 10H3P
21 MA04A DIODE 1 N2483
MERIDEN AHVW- 11
21 MBO1A C/B, COM 1
KLU(ON 7277-2- 11
21 MBO1B C/B, COM i
MERIDEN AHVW- 11
21 MB02A C/B, NAV 1
KUXON 7277-2- 11
21 MB02B C/B, NAV i
MERIDEN AHVW- 11
21 MB03A C/Bt COM 2
21 MBOBB C/B, COM 2 KLD(ON 7277-2- 11
MWDEN AHVW- 11
21 MB04A C/B, NAV 2
21 MB04B C/B, NAV 2 KLIXON 7277-2- 11
MERIDEN AHWd 11
21 MB05A C/B, XPN1A
KLIXON 7277-2- 11
21 MBOSB C/B, XPN
MERIDEN AHVW- 11
21 MB06A C/B, AUD 1
KUXON 7277-2- 11
21 MBOGB C/B, AUD
MERIDEN AHVW- 11
21 MB07A C/B, ADF 1A
KUXON 7277-2- ii
21 MB07B C/B, ADF
MWDEN AHV\CQ- 11
21 MB08A C/Bt DME 1A
KUXON 727/-2- ii
21 MB08B C/B, DME
21 MBOSA SPEAKER, MSO1A MOONEY 81 0195
21 MBOSB SPEAKER ARA 6707001
21 MB1 OA JACK, MIC 1 SWITCHCRAFT C-128
VUL\SHERS S\MTCHCRAFT S-iO2B, S1029
21 MB11A JACK MIC 2 SWITCHCRAFT C-128
V\14SHERS SWITCHCW\FT S-iO2B, S1029
21 MB12A MIC KC~ PILOTS CUTLER-HAMMER SA25SAT12-3
CAP CUTLER-HAMMER SV~3AA2
FACE NUT CUTLER-HAMMER 1510443

91-20-01
18
 MZOK SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
OLDWILLWAYNE
CU~ER-HAMMER SA25SAT12-3
21 MB13A MIC Kfl, COPILOT
CUTLER-HAMMER SW53AA2
CAP
CUTLER-HAMMER 1510493
FACE NUT
21 MB14A JACK, FONE 1 SV~TCHCRAFT
SWITCHCRAFT C-l i
21 MB15A JACK FONE 2
7271-2- 11
21 MBIGAIB C/B,A/P KLU(ON
AHVW- 11
MERIDEN
ALCO MST215N
21 MB17A SWITCH, RADIO MASTER
7277-2- 11
21 MB18AIB C/B,R-NAV KLIXON
727/-2- ii
21 MB1 9A C/B, HSI KLIXON
7271-2- 11
21 MB20A C/B, U\SCODER KLD<ON
727/-2- 11
21 MB21A C/B, FUEL FLOW KLIXON
7277-2- 11
21 MB22A C/B, TELEFONE KLIXON
7277-2- 11
21 MB23A C/B, VME KUXON
7277-2- 11
21 MB24A C/B, TELEPHONE KIlXON
7277-2- ?1
21 MB25A C/B, INVERTER KLD(ON
7277-2- ii
21 MB26A C/B, RMI KUXON
MOONC/ 930023-023
21 MB27A C/B, PROP DE-ICE
MOONEY 930023-123/-223 ii, 28
21 MB27B/D C/B, PROP DE-ICE
MOONfl 930023-021
21 MB28A C/B, WX RADAR
930023-121/-221 28
21 MB28B C/B, WX RADAR MOONC/
MOONC/ 800233-000
21 MB29A BUSS, GRD 1
MOONEY 800233-000
21 MB30A BUSS, GRD 2
MOONEY 800233´•000
21 MB31A BUSS, GRD 3
MOONCI 930023-125/-225 28
21 MB32A/B C/B, WXRADAR COLOR
7277-2- ii
21 MB33A C/B, RADIO BLOVMR KUXON
KING KA20
21 MB34A RADIO BLOWER ASSY
7277-2- 11
21 MB35A C/B, STEREO KLIXON
KLIXON 7277-2- 11
21 MB36A C/B, ALT. SERVO
7277-2- ?1
21 MB37A C/B, ALT SELECT KLU(ON
7271-2- 11
21 MB38A C/B, CONVEF~TER KI\ UXON
727/-2- 11
21 MB39A C/B, LORAN KLIXON
MOONN 930023-127/-227 11,28
21 MB40AID C/B,STANDBYVACUUM
7277-2- 11
21 MB41A C/B, STORMSCOPE KLIXON
MOONN 800336-501
21 MCO1A CIGAR LIGHTER
MOONEY 800336-503
21 MCO1B CIGAR LIGHTER
BORG INSTR CA-7212 or CA-7286
21 MEO1A CLOCK ELECTRIC
CA7616 37
21 MEO1B CLOCK(OPT) BORG
98470-1LW 37
21 MEO1C CLOCYLIGHTED) MITCHELL
FUEL PUMP MOONC/ 930023011
21 NFO1A C/B,
930023-117 28
21 NFO1B C/B, FUEL PUMP-LO MOONC/
FUEL PUMP-LO MOONEY 930023-111
21 NFO1C C/B,
FUEL PUMP-LO MOONEY 930023-117/-217
21 NFO1D/F C/B,
MOONEY 930023-211
21 NFO1E C/B, BOOST PUMP
DUKES(4140-00-19A) WE 1499-00-19
21 NF02A FUEL PUMP
MOONC/ 610153-501

FUEL PUMP DUKES 14940L~i 9

21 NF02B
MOONC/ 610153-501
MOONC/ 930023-019
21 NF03A C/B, FUEL PUMP-HI

91-2(M1
19
SERVICE AND MAINTENANCE MANUAL M20K MOONN AIRCRAFT CORPORATION

OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMENT CHART

21 NF03B/D C/B, FUUPUMP-HI MOONEY 930023-11 9/-219 28

21 NF04A RESISTOR CLARSTAT VP-50-KA 12

21 NF04B VOLT REG, AUX PUMP ELECTRO-DELTA VR-436

ALT MOONE/ 880047-505
21 NFOSA RECPT, V/R AMP 2061 53-1
CLAMP AMP 206062-1
21 NFOGA PLUG, V/R AMP 206060-1
CLAMP AMP 206062-1
21 NF07A RECm, PUMP AMP 2061 53-1
CLAMP AMP 206062-1
21 NF08A PLUG, PUMP AMP 206060-1
CLAMP AMP 206062-1
21 NPO1A SWITCH CARUNG Ti GKGB1 F-\M-1-A
21 NP02A SOLENOID CONTINENTAL 642200
21 NP03A FUSE/HOLDER LITIEL 311 010 or 312010

21 PAO1A C/B, ALTERNATOR FIELD MERIDEN AHVW-5

21 PAO1B C/B, ALT FIELD KLIXON 7277-2-5
21 PA02A ALTERNATOR PRESTOUTE ALY-8403 or 8420 or

ALY~420LS OR ALY8420M
21 PA02B ALTERNATOR FORD DOFF-i 0300J
21 PA02C ALTERNATOR LYCOMING LW 15404
21 PA02D ALTERNATOR CONTINENTAL 641669
21 PA03A FILTER ELPAC 27-3-9401 021
21 PAOBB FILTER SPRAGUE JN-i4-1356A
21 PA03C FILTER CAPTOR A2637
21 PA03D FILTER CAPTOR A2638
21 PA04A C/B, ALT MECHANICAL PRODUCTS 1648-001-70
21 PA04B C/B, ALT. OUTPUT ETA 41-3S14-LN2-70
21 PA05A CAPACITOR SANGAMO 500-1 041-01
21 PAOGA/B/C VOLTAGE REG. MOONEY 880018501 38

REPLACES OECO 20082, 880270´•505 (SPARES)

8 ELECTRO-DELTA VR414 8 VR415 13

ADAPTER CABLE MOONE/ 800331-721

21 PA07A PLUG, VOLT REG MS31~A-18-4S
CLAMP MS3057-1 OB
21 PAO7B PLUG, VOLT REG AMP 206060-1
C14MP AMP 206062-1
21 PA08B RECPT, VOLT REG AMP 206153-1
CLAMP 206062-1
21 PBO1A BATTERY GILL G35(PS6-1 1) 17
21 PBO1B BATTERY PRESTOUTE R-35
21 PB02A RELAY,,BAT~ERY,MASIER CUTLER-HAMMER 6041H231
21 PB02B RELAY, MASTER CUTLER-HAMMER 6041 Hi 05A
21 PB03A C/B, AUX BUSS MERIDEJ AHWldO
(ALT) MECHANICAL PROD 700-001-50
21 PBOBB C/B, AUX PO~ ETA 41-3S14-LN2-50
21 PB04A RELAY, RADIO MAGNECRAFT W89CQX-2
21 PB04B RELAY, RADIO MASTER POTTER 8 BRUMFIELD MB4413 6
21 PB05A SWITCH, MASTER CUTLER-HAMMER 9811 K828
21 PBOGA C/B BUS, RADIO RELAY MOONEY 930023-013
21 PBOGB/D C/B, RADIO MASTER MOONEY 930023-113/-213 28
21 PB07A BUSS BAR, MAIN FLD( 14

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20
MOONEY AIRCRAFT CORPORATION MZOK SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMENT CHART

14
21 PB07B BUSS BAR, MAIN FLD(
14
21 PBOIIC BUSS BAR, MAIN FLM, #1
14
21 PBO7D BUSS BAR, MAIN FLD~ #2
MOONC/ 14
21 PB07E BUSS BAR, MAIN PO~R
MOONN 14
21 PBO’IF BUSS BAR, MAIN POV~R
MOONC/ 14
21 PB07G BUSS BAR, MAIN PO~R
MOONEY 14
21 PB07H BUSS BAR, MAIN #7
21 PBO’N BUSS BAR, MAIN POV~R MOONC/
MOONEY 14
21 PBO7K BUSS BAR
MOONEY 14
21 PB07L BUSS BAR
MOONfi~ 14
21 PB08A BUSS BAR, RADIO FLD(
PBOSA BUSS BAR, AUX MOONEY 913127-009
21
PBOSB BUSS BAR, AUX #1 MOONEY 913127-003
21
21 PBOSC BUSS BAR, AUX #2 MOONE/ 913127-003
PBOSD BUSS BAR, CONN 1 3 2 MOONE/ 913127-011
21
21 PBOSE BUSS BAR, AUXI MOONEY 913127-013

21 PBOSF/M BUSS BAR AUX MOONN 913127-023

21 PBOSG BUSS BARAUX #2 MOONEY 913127-025

PBOSH BUSS BAR,AUX #1 MOONEY 913127-027
21
PBOSJ BUSS BARAUX #2 MOONEY 913127-029
21
MOONEY 913127-113 40
21 PBOSK BUSS BAR, AUX
21 PBOSL BUSS BAR, AUX #2 MOONN 913127-125

21 PB1OA BUSS BAR MAIN #1 MOONEY 913127-005

21 PB1OB BUSS BAR MAIN i MOONN 913127-017
21 PB1OC BUSS BAR MAIN #1 MOONEY 913127-019

21 PB11A BUSS BAR MAIN #2 MOONEY 913127-005

21 PB11B BUSS BAR MAIN #2 MOONEY 913127-019

21 PB12A BUSS BAR MAIN #3 MOONE/ 913127-005

21 PB12B BUSS BAR RADIO #3 MOONN 913127-019

21 PB12C BUSS BAR MAIN #3 MOONEY 913127-001

21 PBI2D BUSS BAR RADIO #3 MOONN 913127-003
MOONEY 913127-019 41
21 PB12E BUSS BAR RADIO #3
MOONEY 913127-019 41
21 PB12F BUSS BAR RADIO #2
21 PB13A BUSS BAR RADIO #1 MOONEY 913127-005
21 PB13B BUSS BAR RADIO #2 MOONEY 913127-019
21 PB14A BUSS BAR RADIO #2 MOONE/ 913127-005
21 PB14B BUSS BAR RADIO #2 MOONEY 913127-019
21 PB?4C BUSS BAR RADIO #3 MOONN 913127-019
21 PB15A DIODE, RADIO hllASIER SAW(ES TARUAN F-4

21 PB1GA BUSS BAR MAIN #1 MOONEY 913127-003

21 PB20A JUMPER
BUSS BAR RADIO FLD( 15
21 PB21A
BUSS BAR, RAD, FLM 2 MOONE/ 14
21 PB21B
BUSS BAR, RAD, FLD( MOONE/ 15
21 PB21C
BUSS BAR MOONEY 15
21 PB21D
BUSS BAR MOONN 15
21 PB21E
21 PB22A DIODE, MASTER RUAY SARKES TARUAN F-4
21 PB23A DIODE, RADIO RELAY SARKES TARZIAN F4
21 PB24A SHUNT, RADIO RELAY KUU(A 600RI-2
21 PB25A SHUNT, RADIO RELAY KUU<A 600RI-2
21 PB26A C/B, BA~ERY POV~R ETA 41-3S14-U1~2-70
21 PB27A BUSS BAR, MAIN PO\R(ER MOONN 913127-031

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SERVICE AND MAINTENANCE MANUAL M20K MOONE/ AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
OLDWILLWAYNE
21 PB28A DIODE SARKES TARZIAN F-4
BUSS 5 MOONEY 913127-001
21
21
PB29A
PB30A
BAFI~RADIO
BUSS BAR, RADIO #4 MOONEY 913127-001
21 PB31A BUSS BAR, MAIN PVI~R,#3 MOONEY 913127-003
21 PB32A BUSS BAR, RADIO #3 MOONEY 913127-005
21 PB33A BUSS BAR, RADIO #2 MOONEY 913127-019
21 PB34A BUSS BAR, MAIN PV~R 3 MOONEY 913127-035
21 PB35A BUSS BAR, MAIN P~ 3 MOONN 913127-035
21 PB36A BUSS BAR, RADIO #1 MOONE/ 913127-035
21 PB37A BUSS BAR, MAIN #1 MOONEY 913127-037
21 PGO1A GENERATOR, STANDBY ELECTRO MECH 8012
21 PG02A FUSE HOLDER LTTTEL 155020 or 155120
FUSE(1SA SLO-BLO) LITTEL 313015
21 PG03A PLUG, REGULATOR MS3106A-1 &i S
CLAMP MS3057-10A or -10B
21 PG04A VOLTAGE REGULATOR ELECTRO MECH 2073-2
21 PG05A C/B, STANDBY GEN KLIXON 7277-2-15
21 PGOGA RU4Y, BUSS SWITCHING LEACH JD1B
SOCKET 50-1 0498309
21 PG07A REI4Y, CONTROL MAGNACRAFT V~7CSX-2
SOCKET 70-303
21 PG08A LIGHT, ON WESTERN IND 501-61 K-i 1 K3BP
LAMP WI-7046
21 PGOSA LIGHT, O.V ~STERN IND 501-61 K-iiK3BP
LAMP V\n-7046
2i PG1OA DIODE, ON LIGHT SARKES TARZIAN F-4
21 PG11A DIODE, O.V. LIGHT SARKES TARUAN F-4
21 PG12A RECPTACLE AMP 2061 53-1
CLAMP 206062-1
21 PG1 3A PLUG AMP 206060´•1
21 PG14A DIODE SARKES TARUAN F-4
21 PGI5A DIODE, RADIO RELAY SARKES TARZIAN F-4
21 PGIGA RECEPTACLE AMP 2067052
CLAMP AMP 206062-1
21 PG17A PLUG AMP 20670&1
CLAMP AMP 206062-1
21 PLOIA PLUG, C/B PANEL AMP 206037-1
CLAMP AMP 206070-1
21 PL02A PLUG, FLT PNL #1 AMP 206037-1
CLAMP AMP 20607Q´•i
21 PL02B PLUG, FLT PNL #1 MOONEY 930021-505
21 PL03A PLUG, ELEC GEAR AMP 206037-1
CIJWIP AMP 206070-1
21 PLOSB PLUG, ELEC GEAR MOONEY 930021-001
21 PL04A PLUG, UV\nNG AMP 206037-1
C14MP 206070-1
21 PL04B PLUG, UWING MOONEY 930021-001
21 PL05A PLUG, UWG STUB AMP 206037-1
CLAMP 206070´•1
21 PLOSB PLUG, UWG STUB AMP 20670&1
CIJ\MP AMP 20696~1
21 PL05C PLUG, VWG STUB MOONEY 930021-001

91-20-01
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 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
OLDWILLWAYNE
AMP 206060-1
21 PLOGA PLUG, SQUAT SWITCH
C14MP AMP 202062-1
AMP 206037-1
21 PL07A PLUG,CONSOLE #1
C14MP AMP 202070-1
AMP 2060681
21 PL07B PLUG,CONSOLE #1
CLAMP AMP 202062-1
AMP 206037-1
21 PL08A PLUG, HEADLINER
CLAMP 206070-1
AMP 206708´•1
21 PL08B PLUG, HEADLINER
2069681
CLAMP
MS31 06A-22-1 4S 19
21 PLOSA PLUG, FIREV\IAU.
MS3057-12B
CLAMP
AMP 20060-1-001
21 PL1OA PLUG, V SIDE CABIN, MIDDLE
206062-1
CLAMP
AMP 206037-1
21 PL11A PLUG, FLT PNL #2
2060781
CLAMP
AMP 20670&1
21 PL11B PLUG, FLT PNL #2
CLAMP
2069681
AMP 206037-1
21 PL12A PLUG, GLARESHIELD
CLAMP 206070´•1
AMP 206060-1
21 PL12B PLUG, ANNUNCIATOR PANEL
206062-1
CLAMP
AMP 206037-1
21 PL13A PLUG, FIRRRC9LL JUNC. PNL
CLAMP AMP 206070-1
AMP 2067081
21 PL1 38 PLUG, ACCESS. PNL
CLAMP AMP 2069681
AMP 206037-1
21 PL14A PLUG, V SIDE CABIN
CLAMP AMP 206070-1
MOONEY 930021-001
21 PL14B PLUG, V SIDE PANEL
AMP 206037-1
21 PL1SA PLUG, ELEC. FLAPS
CLAMP AMP 2060781
2 AMP 206037-1
21 PL1GA PLUG, CONSOLE
CLAMP AMP 2060781
AMP 206966-1
CLAMP
AMP 206708-1
21 PL1GB PLUG, CONSOLE
CLAMP AMP 206966-1
AMP 206037-1
21 PL17A PLUG, RELAY PANEL
CLAMP AMP 2060781
AMP 206037-1
21 PL18A PLUG, CLUSTER GAUGE
CLAMP AMP 206070-1
AMP 20670&1
21 Pt18B PLUG, CLUSTER GAUGE
CLAMP AMP 206966-1
AMP 206(3~0´•1
21 PL1SA PLUG, PILOTS V\MEEL
CLAMP AMP 206062-1
AMP 206060-1
21 PL20A PLUG, COPILOTS VIMEEL
CLAMP AMP 206062-1
AMP 2060681
21 PL21A PLUG, VAC VVARN SW
CLAMP AMP 206062-1
AMP 206037-2
21 PL22A PLUG, RADIO P~t C/B PNL
CLAMP AMP 2060781
AMP 206037-2
21 PL22B PLUG, AUX PVMt CIB PNL
CLAMP AMP 206070-1
AMP 206037-2
21 PL23A PLUG, RADIO P~Mt RELAY PNL
CLAMP AMP 2060781

91-20-01
23
 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
OLDWILLWAYNE
21 PL24A PLUG, CABIN TAIL CONE AMP 206037-1
CLAMP AMP 206070-1
21 P124B PLUG, CABIN TAIL CONE AMP 20670&1
CLAMP AMP 206466-1
21 PL24C PLUG, CABIN TAIL CONE AMP 206037-1
CLAMP AMP 206070-1
21 PL25A PLUG, WWT; AMP 206037-1
CLAMP AMP 206070-1
21 PL25B PLUG, WVIAS AMP 206060-1
CLAMP AMP 206062-1
21 PL25C PLUG, R/ V\X3 AMP 206708-1
CV4MP AMP 206966-1
21 PL25D PLUG, WV\XS MOCNEY 930021-001
CLAMP AMP 206966-1
21 PL26A PLUG, W VIA3 STUB AMP 206060-1
CLAMP AMP 206062-1
21 PL26B PLUG, W V~ NAV AMP 2067081
CLAMP AMP
21 PL26C PLUG, RI VVI; STUB MOONC/ 930021-001
CLAMP AMP 206966-1
21 PL27A PLUG, TRIM POS. IND AMP 206060-1
CLAMP AMP 206062-1
21 PL28A PLUG, PILOTS TRIM AMP 20606Q´•i
CLAMP AMP 206062-1
21 PL29A PLUG, TAIL AMP 206060-1
CLAMP AMP 206062-1
21 PL29B PLUG, EMPENNAGE AMP 206708-1
CLAMP AMP 20696~1
21 PL30A PLUG, RADIO, C/B PNL AMP 206037-1
CLAMP AMP 206070-1
21 PL30B PLUG, C/B PNL(OPT) AMP 2067081
CLAMP AMP 206966-1
21 PL30C PLUG, C/B PNL(OPT) AMP
CLAMP AMP 206062-1
21 PL31A PLUG, RADIO PKG CABLE AMP 206037-1
CLAMP AMP 206070-1
21 PL32A PLUG, TRANSISTORS, CONSOLE AMP 206037-1
CLAMP AMP 206070-1
21 PL33A PLUG, PV~ FLT PNL AMP 206037-2
CLAMP AMP 206070-1
21 PL34A PLUG, PANEL LT CON~IOL AMP 206060-1
C14MP AMP 206062-1
21 PL34B PLUG, LT CONTROL AMP 206708-1
CLAMP AMP 206966-1
21 PL35A PLUG, GEAR CONTROL AMP 206708-1
CLAMP AMP 206966-1
21 PL35B PLUG, GEAR CONTROL AMP 206060-1
CLAMP AMP 206062-1
21 PL35C PLUG, GEAR CONTROL #1 AMP 20670~2
CLAMP AMP 206966-1
21 PL35D PLUG, GEAR CONTROL #2 AMP 206060-1
CLAMP AMP 206062-1
21 PL36A PLUG, GEAR OVEWUDE AMP 205060´•~
CLAMP AMP 206062-1

91-20-01
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 MOONEY AIRCRAFT CORPORATION nn20K SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMWT CHART

21 PL37A PLUG, VAC WARN AMP 206060´•1

CLAMP AMP 206062-1
21 PL38A PLUG, ELT SWITCH AMP 205060-1
CLAMP AMP 206062-1
21 PL39A PLUG, OVERHEAD LITE AMP 206080-1
CLAMP AMP 206062-1
21 PL40A PLUG, EMERG FLD AMP 206060-1
CLAMP AMP 206062-1
21 PL41A PLUG, GLARESHIELD AMP 206060-1
CLAMP AMP 206062-1
21 PL42A PLUG, HOUR METER AMP 206060-1
CLAMP AMP 206062-1
21 PL43A PLUG, FLT PNL AMP 2067081
CLAMP AMP 206966-1
21 PL44A PLUG, GR SAFETY SW AMP 206060-1
CLAMP AMP 206062-1
21 PL45A PLUG, FIREW4LL #2 MS3106A-22-14S
CLAMP MS3057-12B
21 PL46A PLUG, AVIONIC MOONEY 930021-501
21 PL47A PLUG, AUDIO INTERCN AMP 205839-1
CLAMP AMP 206070-1
21 PL48A PLUG, FLT PNL DIM AMP 206037-1
CLAMP AMP 206070-1
21 PL49A PLUG, C/B, GRND AMP 205838-1
C14MP AMP 206062-1
21 PLSOA PLUG, CIB DIM AMP 206062-1
CLAMP AMP 206062-1
21 PL51A PLUG, A/P TRIM SW RUAY AMP 206037-1
CLAMP 206070-1
21 PL52A PLUG, AIP AMP 206031-1
CLAMP 206070-1
21 PL53A PLUG, A/P GRND AMP 206037-1
CLAMP 206070-1
21 PL53B PLUG, AVIONICS GRND AMP 2068383
CLAMP 206070-1
21 PL53C PLUG, MAIN CABLE GRND AMP 206037-1
CLAMP 206070-1
21 PL53D PLUG, AVIONICS GRND #2 AMP 20678343
C14MP 206070-1
21 PL54A PLUG, INT PV~R AMP 2067081
CLAMP 206966-1
21 PL55A PLUG, COM/NAV PO~R
j 21 PL57A
CLAMP
PLUG, ROLL SERVO CABLE
AMP
AMP
AMP
206060-1
206062-1
206708-1
CLAMP 206966-1
21 PL58A PLUG, AUMUTH CABLE AMP 2067081
CLAMP AMP 206966-1
21 PL59A PLUG, AVIONICS DIM AMP 206037-1
CLAMP 206070-1
21 PLGOA PLUG, K-4/C-2 NAV RECIAIP AMP 2058393
CLAMP 206070´•1

91-20-01
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 M20K MOONElAIRCRAFT CORPORATION
SERVICE AND MAINTENANCE MANUAL
OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMENT CHART

AMP 2058343
21 PLG1A PLUG, K-14 NAV REC/AIP
206070-1
CLAMP
AMP 206037-1
21 PL62A PLUG, K-14 NAV RECIAIP
206070-1
CLAMP
AMP 206037-1
21 PL63A PLUG, AVP XFER
206070-1
CLAMP
AMP 2058343
21 PL64A PLUG, K-2/K-3 NAV RECIAIP
206070-1
CLAMP
AMP 205838-1
21 PL65A PLUG, TRIM RELAY
206062-1
CLAMP
AMP 205838-1
21 PL66A PLUG, TRIM SW
206062-1
CLAMP
AMP 206708-1
21 PL67A PLUG, AZIMUTH
206966-1
CLAMP
AMP 205838-1
21 PL68A PLUG, ADF RMI
206062-1
CLAMP
AMP 205838-1
21 PLGgA PLUG, TRIM RELAY
206062-1
C14MP
AMP 206060´•1
21 PL670A PLUG, TRIM PVMZ
206062-1
CU~WIP
AMP 2058343
21 PL71A PLUG, A/P RELAY
206070-1
CLAMP
AMP 2058381
21 PL72A PLUG, VOWGS TRANSFER
206062-1
CLAMP
AMP 205838-1
21 PL73A PLUG, MKR INVERTER
206062-1
CLAMP
AMP 2058343
21 PL74A PLUG, NAVIREC AIP
206070-1
CLAMP
21 PL75A PLUG. ADWRMI 206037-1
206070-1
CLAMP
AMP 2058343
21 PL76A PLUG, GRND
206070-1
CLAMP
AMP 20037-1
21 PLnA PLUG, XPDWUI~CODER(KFC 200)
AMP 206070-1
C14MP
21 PL78A PLUG, RADIO PKG CABLE 206037-1
206070-1
CLAMP
21 PUSA PLUG, NAV RECIAIP, K-4/C-2 2058393
20607(F1
CLAMP

MWDEN AHW4-1O
21 PSO1A C/B, IGNTTACH/CIG LIGHTER
KUXON 7277-2-10
21 PSO1B C/B, IGN/TACWCIG LIGHTER
MICRO 2D72
21 PS02A SWITCH, STARTER
MICRO 2M~
HOUSING
MICRO u5
SCREEN, DISPIAY
MICF~O u<6
RING, GUARD
CU~NR-HAMMER 6041H105A
21 PS03A/B RELAY
940020501 22
WE MOONEY
PRESTOUTE MZ4206
21 PS04A STARTER
PRESTOLT~E M24218
(ALT)
PRESTOUTE M24222
(ALT) 39
PRESTOLITE MCL-6501
21 PS04B STARTER
LYCOMING LW1 5572
(ALT)
SARKES TARZIAN F4
21 PSOSA DIODE

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MOONF/ AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL

OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMENT CHART

21 PSOGA FUSE HOLDER LITTEL 155020 or 155120

FUSE L177EL 313001

21 RCO1A RECPT; C/B PNL AMP 206036-3

CLAMP AMP 206070-1
21 RCO1B RECPT, C/B PNL AMP 206151-1
CLAMP AMP 2061 38-1
21 RC02A RECPT; FLT PNL #1 AMP 206036-3
CLAMP AMP 206070-1
21 RC02B RECPT, FLT PNL #1 MOONC/ 930021-506
21 RC03A RECPT, ELEC GEAR AMP 206036-1
CLAMP AMP 206070-1
21 RC03B RECPT, ELEC GEAR MOONEY 930021-002
21 RC04A AMP 206036-3
CLAMP AMP 206070-1
21 RC04B RECPT, UWING MOONC/ 930021-002
21 RC05A RECPT, UV\nNG AMP 206036-3
CLAMP AMP 20607~1
21 RC05B RECPT, UV\nNG STUB AMP 2067052
CLAMP AMP 20696~1
21 RC05C RECP, UV\nNG STUB MOONfl 930021-002
21 RCOGA RECPT, SQUAT SWITCH AMP 206153´•1
CLAMP AMP 206070-1
21 RCO7A RECPT, CONSOLE #1 AMP 206036-3
CLAMP AMP 206070´•1
21 RCO7B RECPT, CONSOLE #1 AMP 206153-1
CLAMP AMP 206062-1
21 RC08A RECPT, HEADLINER AMP 206036-3 19
CU´•WIP AMP 206070-1
21 RC08B RECPT; HEADUNGER AMP 2067052
CLAMP AMP 206966-1
21 RCOSA RECPT, FIRNWLL MS31 00A22-1 4P 19
CLAMP MS3057-12B
21 RC1OA RECPT, U SIDE CABIN, MIDDLE AMP 206153-1
CLAMP AMP 206062-1
21 FIC11A RECPI; FLT PNL #2 AMP 206036-3
CLAMP AMP 206070-1
21 RC11B RECPT, FLT PNL #2 AMP 206705-2
CLAMP AMP 206966-1
21 FIC12A RECPT; GLARESHIELD AMP 20603~3
CLAMP AMP 206070´•1
21 RC13A RECPT, FIREVVALL JUNC PNL AMP 20603~3
CLAMP AMP 206070-1
21 RC1 38 RECPT; ACCESS. PNT AMP 2067052
CLAMP AMP 206966-1
21 RC14A RECPT, U SIDE CABIN LOW AMP 2060383
CLAMP AMP 206070-1
21 RC14B RECPT, V SIDE PNL MOONEY 930021-002
21 RC14C RECPT, U SIDE PNL MOONN 930021-502
21 RC1 5A RECPT, FLAPS, ELEC AMP 206036-1
CLAMP AMP 206070-1
21 RC1GA RECPT, CONSOLE #2 AMP 206036-3
CLAMP AMP 206070-1

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 SERVICE AND MAINTENANCE MANUAL MZOK MOONN AIRCRAFT CORPORATION

OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMENT CHART

21 RC1GB RECPT, CONSOLE AMP 206705-2

CLAMP AMP 20696~1
21 RC1 7A RECPT, RELAY PNL AMP 206036-1
CLAMP AMP 20607~1
21 RCI8A RECPT, CLUSTER GAUGE AMP 206036-3
CLAMP AMP 2060781
21 RC18B RECPT; CLUSTER GAUGE AMP 2067052
CLAMP AMP 206966-1
21 RC1SA RECPT; PILOTS V~HEEL AMP 206153-1
CIAMP AMP 206062-1
21 RC20A RECPT, COPILOTS V\MEEL AMP 206153-1
CLAMP AMP 206062-1
21 RC21A RECPT, VAC WARN SW AMP 206153-1
CLAMP AMP 206062-1
21 RC22A RECPT, RADIO PVLR C/B PNL AMP 206207-1
CLAMP AMP 206070-1
21 RC22B RECP, C/B PNL, AUX PV~ AMP 206036-2
CLAMP AMP 20607~1
21 RC23A RECPT, RADIO PV~R RELAY PNL AMP 206036-1
CLAMP AMP 206070´•1
21 RC24A RECPT, CABIN TAILCONE AMP 206036-3
CLAMP AMP 206070-1
21 RC24B RECPT, CABIN TAILCONE AMP 206705-2
CLAMP AMP 206966-1
21 RC24C RECPT, CABIN TAILCONE AMP 206036-3
CLAMP AMP 206070´•1
21 RC25A RECPI; WWING AMP 206036-3
CLAMP AMP 206070-1
21 RC25B RECPT, WWING AMP 2061 53-1
CLAMP AMP 206062-1
21 RC25C RECPT, R/ WING AMP 206705-1
CLAMP AMP 206070-1
21 RC25D RECPT; R( WING MOONEl 930021-002
CLAMP AMP 2060966-1
21 RC26A RECPT, R/ WIGN STUB AMP 206153-1
CLAMP AMP 206062-1
21 RC26B RECPT, RI WING STUB AMP 206705-2
CLAMP AMP 206966-1
21 RC26C RECPT, R/ WING STUB MOONEY 930021-002
CLAMP AMP 206966-1
21 RC27A RECPT, TRIM POS IND AMP 206153-1
CLAMP AMP 206062-1
21 RC28A RECPT, PILOTS TRIM AMP 206153-1
CLAMP AMP 206062-1
21 RC29A RECPT, TAIL AMP 2061 53-1
CLAMP AMP 206062-1
21 RC29B RECPI; TAIL AMP 206705-2
CLAMP AMP 206966-1
21 RC30A RECPT, RADIOS, C/B PNL AMP 206036-3
CLAMP AMP 206070-1
21 RC30B RECPT, C/B PNL AMP 206705´•2
CLAMP AMP 206966-1

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 M20K SERVICE AND MAINTENANCE MANUAL
MOONFI AIRCRA~T CORPORATION
OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMENT CHART

AMP 206060-1
21 RC30C RECm, C/B PNL (OPT)
AMP 206062-1
CLAMP
AMP 206036-3
21 RC31A RECP, RADIO PKG CABLE
AMP 206070-1
CLAMP
206036-3
21 RC32A RECPT, TRANSISTORS, CONSOLE AMP
AMP 20607~1
CLAMP
AMP 206207-1
21 RC33A RECPT, PV\(R FLT PNL
AMP 20607~1
CLAMP
AMP 206153-1
21 RC34B RECPT, PNL LT CONTROL
AMP 206062-1
CLAMP
AMP 20670~2
21 RC34B RECPT, LIGHT CONTROL
AMP 20696~1
CLAMP
AMP 206705´•2
21 RC35A RECPT, GEAR CONTROL
AMP 20700&1
CLAMP
AMP 206153-1
21 RC35B RECPT, GEAR CONTF~OL
AMP 206062-1
CLAMP
AMP 2067052
21 RC35C RECPT, GEAR CONTROL #1
CLAMP AMP
AMP 206153-1
21 RC35D RECPT, GEAR CONTflOL #2
AMP 206062-1
CLAMP
AMP 206153-1
21 RC37A RECPT, VAC VWRN
AMP 206062-1
CLAMP
AMP 206153´•1
21 RC38A RECPT, U-T, SW
AMP 206062-1
CLAMP
AMP 206153-1
21 RC39A RECPT, O/H Ll(jiHT, AFT
AMP 206062-1
CLAMP
AMP 2061 53-1
21 RC40A RECPT, EMERG flD
AMP 206062-1
CLAMP
AMP 206153-1
21 RC41A RECPI; BLARESHIEDL
AMP 206062-1
CLAMP
AMP 206153-1
21 RC42A RECPT, HOUR METER
AMP 206062-1
CLAMP
AMP 206705´•2
21 RC43A RECm, FLT PNL
AMP 206966-1
CLAMP
206705-2
21 RC43C RECPT, GO AROUNDN\6( RADAR
AMP 206966-1
CIAMP
AMP 206153-1
21 RC44A RECPT, GR SAFEN SW
AMP 206062-1
CLAMP
MS31 00A-22-1 4P
21 RC45A RECPT, FIREVWIl, #2
MS3057-12B
CLAMP
MOONC/ 930021-502
21 RC~A RECPT; AVIONICS PVI~R
AMP 206152-1
21 RC47A RECPT; AUDIO INTER
AMP 206070-1
CLAMP
AMP 206036-1
21 RC48A RECPT, FLT PNL GRND/DIM
AMP 206070-1
CLAMP
AMP 206841-2
21 RC49A RECPT, C/B GRND
AMP 206062-1
CLAMP
AMP 206153-1
21 RCSOA RECPT, C/B DIM
AMP 206062-1
CLAMP
AMP 206036-3
21 RCS1A RECPT, AIP TRIM SW RUAY
AMP 206070-1
CLAMP

91-20-01
29
SERVICE AND MAINTENANCE MANUAL MZOK MOONM AIRCRAFT CORPORATION

OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMENT CHART

RC52A RECPT, A/P PV~ AMP 206036-3

21
CLAMP AMP 206070-1

RC53A RECPT, AIP GRND AMP 206036-3

21
CLAMP AMP 206070-1

RC53B RECPT, AVIONICS GRND #1 AMP 206152-1

21
CLAMP AMP 206070-1

21 RC53C RECm, MAIN CABLE GRND AMP 206036-3

CLAMP AMP 206070-1
RC53D RECF, AVIONICS GRND #2 AMP 206152-1
21
CLAMP AMP 206070-1

21 RC54A RECF, INTERFACE PV~R AMP 2067052

CLAMP AMP 206966-1

21 RC55A RECPT, COMM/NAV PV~R AMP 206153-1

CLAMP 206062-1

21 RC57A RECP, ROLL SERVO CABLE AMP 206705-2

CLAMP 206966-1

21 RC58A RECF, AZIMUTH CABLE AMP 206705-2

CLAMP AMP 206966-1
21 RC59A RECPT, AVIONICS DIM AMP 206036-3
CLAMP AMP 206070-1
21 RC59B A/P DIM 206153-1
CLAMP AMP 206062-1

21 RCGOA RECPT, K4IG2,NAMIECIAIP 2061 52-1

CLAMP AMP 206070-~
21 RCG1A RECPT, K-14, NAVRECIAIP 2061 52-1
CLAMP AMP ’206070-1

21 RC62A RECPT, K-14, NAVRECIAIP 2060363

CLAMP AMP 206070´•1

21 RC63A RECPT, AIP TRANSFER 206036-1

CLAMP AMP 206070´•~
21 RC64A RECm, K-2/K-3, NAVRECIAIP 2061 52-1
CLAMP AMP 206070-1
21 RC65A RECPT, TRIM RELAY 205&21-2
CLAMP AMP 206062-1
21 RC66A RECm, TRIM SW 205841-2
CLAMP AMP 206062-1
21 RC67A RECPT, AZIMUTH 206705´•2
CLAMP AMP 206966-1
21 RC68A RECP, ADWRMI 205841-2
CLAMP AMP 206062-1

21 RC69A RECPT, TRIM RELAY 205841-2

CLAMP AMP 206062-1

21 RC70A RECP, TRIM PVMI 206153-1

CLAMP AMP 206062-1

21 RC71A RECPT, AIP RELAY 206152-1

CLAMP AMP 206070´•1
21 RC72A RECm, VOWGS TRANSFER 205841-1
CLAMP AMP 206062-1

21 RC73A RECPT, MKR INVEF~TER 205841-1

CLAMP AMP 206062-1

21 RC74A RECPI; NAVRECIAIP 2061 52-1

CLAMP AMP 206070´•1

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 MOONEV AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
OLDWILLWAYNE
21 RC75A RECm, ADF/RMI 20603~3
CLAMP AMP 206070-1
21 RC76A RECP, GRND AMP 206152-1
CLAMP AMP 206070-1
21 RC77A RECPT, XDCWENCODER (KFC200) AMP 20603~2
CLAMP AMP 20607~1
21 RC78A RECP, RADIO PKG CABLE AMP 206036-3
CLAMP AMP 206070-1
21 RC79A RECm, K-4/C-2 NAVREC/AIP AMP 206152-1
CLAMP AMP 206070-1
21 V~901A LIGHT ALT WARN KORRY 25~650-5821-003
BULB (2) GE 330
21 WA02A RECTIFIER SARKES TARZIAN F-4
21 WA03A SWITCH, LO VOLT DET ELECTRO DELTA LV 14
21 WA03B SWITCH, LO VOLT DET ELECTRO DELTA LV-14F
21 VI~EO1A C/B, GEAR V\19RN MERIDEN AHW4-2
21 V\fiO?B C/B, GEAR WARN KUXON 727/-2-2
21 WlE02A LIGHT, GEAR UNSAFE KORRY 250-650-5821-006
BULB GE 330
21 V~E03A SWITCH, THFtOT~LE MICRO 1SM1-T
ACTUATOR MICRO JS221
21 W(E03B SWITCH, THROT~LE CUTLER-HAMMER SS12FT10-1 02L3
21 V(E03C SWITCH, THROT~LE MICF~O V3-1
ACURATOR MICF~O JV-5
21 V\JE04A HORN, GEAR UP, WARN MALLORY SC628P
21 \1~05A RECTIFIER SARKES TARZIAN F-4
21 ~06A LIGHT, GEAR POSITION SLOAN 855SO´•U
BULB (1) GE 327
21 LIGHT, GEAR DOV\R~ KORRY 250-650-5821-007
BULB (2) GE 330
21 WlE08A DIODE, GEAR UNSAFE SARKES TARZIAN F-4
21 VLE09A DIODE, GEAR DOVM\I SARKES TARZIAN F-4
21 V~E1OA DIODE, GEAR HORN SARKES TARZIAN F-4
21 V~E11A RESISTOR DIM (50 OHM -5 V~TT)
21 V~E12A DIODE, DIM SARKES TARZIAN F-4
21 V(FO1A LIGHT, LOW FUEL PRESS KORRY 250-650-5821-004
BULB (2) GE 330
21 VM03A RECTIFIER SARKES TARZIAN F-4
21 V1~404A PLUGSV(ITCH AMPHENOL 12~-223-1000
21 VlhO?A FUSEHOLDER LITTEL 155020
FUSE LTT~EL 311011
21 WlL02A LIGHT, LANDING IND KORRY 250650-5821-005
BULBS (2) GE 330
21 VIb03A RECTIFIER SARKES TARZIAN F-4
21 WSO?A C/B, STALL V\WI~ HORN MWDU\I AHVW-2
21 WSO1B C/B, STALLWARN HORN KLD(ON 7277-2-2
21 WS02A HORN, STALL WARNING MALLORY SC628
21 WS03A SWITCH, PRE-STALL WARN SAFE FLIGHT C46001
21 WTO1A SWITCH, PRESS TO TEST ALCO MSP205R
21 WT02A C/B, ANNUNCIATOR KLIXON 7277-2-2
21 Wm3A ANNUNCIATOR W 500D0024
LAMPS CHICAGO MINIATURE CM7-7330

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 SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION

OLDWILLWAYNE
14 VOLT ELECTRICAL EQUIPMENT CHART

21 WT03B ANNUNCIATOR IAl 500D0038B 20

LAMPS CHICAGO MINIATURE CM7-7330
21 WT03F ANNUNCIATOR IAl 500D003&007 20
LAMPS CHICAGO MINIATURE CM7-7330
21 WT03G ANNUNCIATOR MOONN 880025-501
LAMPS (8) CHICAGO MINIATURE CM7-7330
21 WT03H ANNUNCIATOR MOONEY 880025515
21 WT03J ANNUNCIATOR MOONEY 880025511
LAMPS CHICAGO MINIATURE CM7-7330
21 WT03K ANNUNCIATOR MOONC/ 880025-513
21 WT04A PLUG, ANNUNCIATOR MOLD( 09-50´•3121
PIN MOLD( 0850-1 06

21 WVD1A C/B, VACUUM VIWW MWDEN AHW4-2

21 VWO1B C/B, VACUUM VWRN KLIXON 7277-2-2
21 VW02A SWITCH, VACUUM WARN MCONEY 880012-501 21

21 WV02B SWITCH, VAC. W4RN LO V\MITMAN GENERAL P118V-IN-K5L-~ 21

21 VW02C SWITCH, VAC. V\IARN HI V\MITMAN GENERAL P118V-IN-K4L-2 21
21 VW03A LIGHT, LOWVAC KORRY 25~650-5821-002
BULB (2) GE 330
21 WV04A LIGHT, HIGH VAC KORRY 250-650´•5821-001
BULB (2) GE 330
21 WV04B LIGHT, VAC KORZY 250-650-5821-009
BULB (2) GE 330
21 WVOSA RECTIFIER, LO SARKES TARZIAN F-4
21 WVOGA RECTIFIER, HI SARKES TARZIAN F4
21 VW07A SWITCH, VAC LT, FLASHER ELECTRO DELTA FL?
21 VWU)1A SWITCH, RAM AIR MICRO V3´•~
ACTUATOR MICRO JV-5
21 VW~O1B SWITCH, ALTERNATE AIR CHERRY E51-50B

LIGHT DIMMER SW MOONEY 8800344

BOX RHEOSTAT ALLEN-BRADLC/ JS1N056P02MA
TRANSISTOR RCA 2N3055
TRANSISTOR (ALT) RCA 21\13773
FUSE McGRAWEDISON mn01-5A
RECEPTACLE AMP 206705´•2

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 MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
14 VOLT ELECTRICAL EQUIPMENT CHART
OLDWILLWAYNE
NOTES

i. Switch 89061<2876 may be used by painting black handle with

white epoxy paint.
2. Altemate for V3L-3 is V3-1 switch wah JV-5 actuator.
3. 0506-505 is replacement for-004 SM 18928 8 UP are modified.
4. Or equivalent Sp~ague RB1535
Dale
MFS-1/2(15K)
TWX
1/2W(15k)
5. set for 75 MPH (+/-5.0) (65 +7/-4 KIAS)
6.
increasing actuation. (2.775 in. H2O, +0.384/-0.358 in.)
Use with socket, 276122; spn’ng, 206176;
stand-off, (2 ea) 218212. (AN515-6R5 screw,
AN936-A6 washer).
7. Altemate L110-?-N-K3L or Mooney PM 880013-501.
8. Mounting Hardware RCA KC2B
Mica Insulating Wafer H.H. Smith 6291
Nylon Shoulder Washer H.H. Smith 2666
Solder Lug H.H. Smith 1410-10
Metal Washer H.H. Smith 1152
Nut H.H. Smith 1367

9. Alternate Holders Leecraft 07-05

Drake 4151-014
in. Alt. Resistors Sprague 243E2015
Drake VC5E-200
ii. Maximum circuit breaker rating is shown,
amperage of installed circuit breaker is determined
U"it installed.
12. Ohmite 0561
Mallory 5AV10
13. Replace VR414 20082 with 880016-501 8 800331-721 cable.
14. Manufacture using "Alpha Wire Co." braid #2172 or#1233/2
(2 ea) 8 AMP terminals as
necessary to connect the buss bars as shown on schematic. Cover braid with PVC i 05!A
tubing for insulation.
15. Same as 14 except use (1 ea) braid.
16. Ground tabs C’250" sen’es)
"As required" AMP 41478
AMP 41480
17. Altemate Prestolite R35
18. Replace with MS3106A-22-14P when used in conjunction with MS3450KT22-14S.
19. Replace with MS3450KT22-14S receptacle MS3417-22-N cable clamp or
Matrix #9440KT22-14S.
20. MFG Chicago Minature Lamp Co.
21. Set switches with room temperature between 600 F and 800
F. Set low at 4.25 Hg. ~-025"
and high at 5.50" Hg. +0.20/-0.00"
increasing vacuum. Switches may not va~y more than 0.50"
Hg. between 00 F and 1100 F.
22. Replace with 940020-501 (Cutler-Hammer solenoid PRJ 6041H53).
23. Altemate Tum Coordinators:
Talley Corp. (w/out lights) 1394T100-72
United Instr.(w/out lights~ 9100 Code No. 6

24. Altemate Tum Bank:

Talley Corp. (w/out lights) 1234T100-T~Z

Talley Corp. (w/out lights) 1234T100-3TZ

25. Aitemate Fuel Flow Gauges:
Mooney (Gals/hr- lighted) 880034-501
Mooney (liters/hr- lighted) 880034-503/-509
Mooney (Imperialgals/hr-T~Med) 880034-511
Mooney (Pounds/hr) 880034-505

91-20-01
33
 SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION
14 VOLT ELECTRICAL EQUIPMENT CHART
OLDWILLWAYNE
NOTES (con’t.)
26. Attemate Landing Gear.
Mooney 880037-501

27. Use buss bar 913127-029, -023 or-013 as required by installation of optional equipment.
28. Effective 25-0821 8 ON (All are 930023-2>0( C/B’s). Effective 24-1464 g ON also.
29. Effective 25-0001 thru 25-0788 or 24-0024 thru 24-1037.
30. Effective 25-0789 8 ON or 24-1426 8 ON.
31. Effective 24-0001 thru 24-0023 (24-0024 thru 24-1037 use 21 LS02B, 21 LS03B, 21 LS04B 8
21 LS05B)
32. Effective 250447 thru 25-0780 or 24-1038 thru 24-1425.
33. Standard on 24-1211 8 ON.
34. Effective 25-0613 thru 25-0780.
35. Alternate Turn Coordinator (w/ lights):
United Instr 9112-Code No. 9
Astronautics 303990-113MSC
Talley 1394T100-32

36. Use i ea. MS35334-21 or MS2898 (Alan-Bradley) intemal tooth lockwasher with each light if
not supplied by Sloan.
37, AItemate Clock (lighted):
Mid-Continent MP88L
Mid-Continent MD-88L(ET)
(W/ light tray) BA14-24-BW2

38. Aitemate Voltage Regulator.

Larnar &00371-6.

39. Alternate Starter(21 PS04B):

TCM 646238

40. Use buss bars 913127-123,-125 as requ’ired, by installation of Optional Equipment.

41. CUT TO SIZE

91-20-01
34
 M20K SERVICE AND MAINTINANCE MANUAL
MOONEY AIRCRAFT CORPORATION
28 VOLT SM 25-1000 THRU 251224
OLDWILLWAYNE
91-20-02
ELECTRICAL SYSTEM HARDWARE CHART 28 VOLT SYSTEMS
_

SERIAL NUMBER’S 251000 MRU 25-1224, MOONEY DRAWING

NO. 800350 (AV-9)

VENDOR PART NO. I\IOTES

CODE DESCRIPTION

KLD(ON 7277-2-2
JKL CB1O1A C/B DEFROSTER BLOWER
CHERRY E51-50B
JKL CB102A SWITCH, DEFROST BLOWER
MOONEY 640317-501
JKL CB1OBA MOTOR, DEFROSTER BLOWER
AMP 1-4083190
JKL CBI04A RECPT, DEFROSTER BLOWER
AMP 60620-1
PINS
1-4803180
JKL CB1OSA PLUG, DEFR6STER BLOWER AMP
AMP 6061 9-1
SOCKETS
KLIXON 7277-2-5
JK- CC1OIA C/B, COWL FLAP
MICRO 12TW1-1
JK- CC102A SWITCH, COWL FLAP
MICRO 15PA90-4W
CAP, WHITE
MOONEY 880050-501
-K- CC103A ACTUATOR, COWL FLAP
MICRO 1 SE1-T
JK- CC104A SWITCH,OPEN LIMIT
MICRO JE-5
ACTUATOR
MICRO 1SE1-T
JK- CC1OSA SWITCH, CLOSE LIMIT
MICRO JE-5
ACTUATOR
AMP 2061 53-1
JK- CC106A RECPT, 4 PIN
AMP 206062-1
CLAMP
AMP 206060-1
JK- CC1 07A PLUG, 4 PIN
AMP 206062-1
CLAMP
KLD(ON 7277-2-5
JKL CF1O1A C/B FLAP ACT
C-H 8906K3149
JKL CF102A SWITCH, FLAP 4
MICRO V3-~
JKL CF103A SWITCH, UP LIMIT 4
MICRO V3-i
JKL CF104A SWITCH, DOWN LIMIT 4
MICRO V3-~
JK- CF1 06A SWITCH, TAKEOFF, UP 4
MICRO V3-1
JK- CF1 07A SWITCH, TAKEOFF, DOWN 4
ACTUATOR MICRO JV-5
MOONEY 7501 05-501
JKL CI=105A ACTUATOR, FLAP
MAGNACRAFT V~j7RCSX-3
JK- CF1 08A RELAY, UP
MAGNACRAFT V~7RCSX-3
JK- CF1 09A RELAY, DN
NLAGNACRAFT 70-303
BASE
C-H 8906)<4064
JK- CF11OA SWITCH, FLAP
MICRO 2TL14412L
(ALT) 91 7026-501
KNOB MOONEY
1N2483
JK- CF111A/112A DIODE
J- CF?~3A PLUG, 4 PIN A’MP 206060-1
AMP 206062-1
CLAMP
AMP 206153-1
J- CF114A RECPT, 4 PIN
CLAMP AMP 202062-1
C/B TRIM/FLAP IND KLD(ON 7277-2-1
-L CF1SOA
PENN AIRBORNE 9A1590
-L CF151A
TTT DA~ 5S
-L CF152A PLUG, TRIM/FLAP IND
CLAMP TTT DA51210-?
LOCK RETAINER TTT DA51220-1
AMP 206060-1
-L CF153A PLUG,FLAP POSITION, 4 PIN
CLAMP AMP 206062-1
AMP 206153-1
-L CF154A RECPT,FLAP POSITION, 4 PIN
CLAMP AMP 206062-1

91-20-02
35
SERVICE AND MAINTINANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 251000 THRU 25-1224
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES
===============’~=============L,,,---------´•---

-L CI=155A POTENTIOMETER, FLAP POSITION ALLEN-BRADLC/ WA2-G056S502UA

JKL CT1O1A C/B ELECTRIC TRIM KLIXON 7277-2-3 5

JKL CT1O1A C/B ELECTRIC TRIM KLIXON 7277-2-5 5
-L CT1SOA POTENIOMETER TRIM POSITION ALLEN-BRADLEY WA2-G056S502UA
-L CTIS1A PLUG, TRIM POSITION, 4 PIN AMP 206060´•1
CLAMP AMP 206062-1
-L CT152A RECPT,TRIM’POSITION, 4 PIEi AMP 206153-1
CLAMP AMP 206062-1

JK- CV1OIA C/B, STBY VAC MOONEY 930023-245

JK- CV102A CLUTCH, STBY VAC PUMP AEROSAFE S8112-472
JK- CV1O3A FUSEHOLDER LITTEL 155020 or 155120
FUSE LTT~EL 313001
JK- CV1 04A ANNUNCIATOR MOONEY 800346-501
JK- CV1 05A RELAY MOONEY 8301 31-511
JK- CV1 06A DIODE 1N2483
JK- CV1 07A PLUG AMP 1-48031 90
SOCKETS AMP 6061 9-1
JK- CV1 08A RECPT, 2 PIN AMP i -480319-0
PINS AMP 60620-1
JK- CV1 09A RECPT, 2 PIN AMP 1-4803190
PINS AMP 60620-1
JK- CV11OA PLUG, 2 PIN AMP 1-48031&0
SOCKETS AMP 6061 9-1
JK- DA1OIA LOADMETER (SINGLE) B&D 0326004
JK- DA1O1B LOADMETER (DUAL) B&D 0328003
J- DA1O1D AMMETER MOONEY 640281-509
LIGHT BULB ASSY ROCHESTER 0105S00004
BULB GE 313
JK- DA1 02A CONN, AMMETER S.E.C. PWDGB12-1 OS
JK- DAI 02A CONN, AMMETER (ALT) BENDIX PTO6A-I2-1 OS-SR
JK- DA1 03A SWITCH, PUSH, VOLTAGE C-H SA3I soT´•12-1
LIGHT BULB ASSY ROCHESTER 0105S00003
(ALT) ROCHESTER 0153500003
BULB GE 313
JK- DA? 04A SHUNT, AMMETE’R (ALTNR #1) EMPRO MLA-7OA-50MV
MLA-55A-5OMV
JK- DA1 048 SHUNT, AMMRERI~LTNR)
ALT
EMPRO
McGRAW-EDrSON FHN42W
JK- DA1OSA FUSEHOLDER 1)
FUSE, 5A McGRAW-EDISON FMOi -5A
JK- DA1OGA FUSEHOLDER ALT i) McGRAW-EDISON FHN42W
FUSE, 5A McGRAV~tEDISON FMOi -5A
JK- DA1 07A SHUNT, AMMETER, LOAD EMPRO ML&21 0A-50MV
JK- DA1 078 SHUNT, AMMETER, LOAD EMPRO ML&I 65A-50MV
JK- DA1 07C SHUNT, AMMETER, LOAD EMPRO ML&1 05A-5OMV
JK- DA1 07D SHUNT, AMMETER, LOAD EMPRO MLA-GOA-I OOMV
JK- DA1O8A FUSEHOLDER (-LOAD) McGRAV~EDISON FHN42W
FUSE, 5A McGRAW-EDISON FMO1-5A
JK- DA1 09A FUSEHOLDER ~LOAD) McGRAV~EDISON FHN42W
FUSE, 5A McGRAW-EDISON FMO1-5A
JK- DA11OA AMMETER, SHUNT (dLT #2) EMPRO MLA-7OA-SOMV
AMMETER, SHUNT (ALT~ EMPRO MLA-55A-5OMV
JK- DAI ?1A FUSEHOLDER ALT. #2) McGRAW-EDISON FHN42W
FUSE, 5A McGRAW-EDISON FMO1-5A

91-20-02
36
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTINANCE MANUAL
28 VOLT- S/N 25-1000 THRU 25-1224
OLDWILLWAYNE
DESCRIPTION VENDOR PART NO. NOTES
CODE

JK- DAl 12A FUSEHOLDER ALT. #2) McGRAW-EDISON FHN42W

FUSE, 5A McGRAW-EDISON FMO1-5A

-L DA150A C/B VOLT/AMP IND, LT KLIXON 7277-2-1

-L DA1S1A C/B VOLT/AMP IND, RT KLIXON 7277-2-1
-L DA152A INDICATOR, VOLT/AMP, RT PENN AIRBORNE 9A1570
-L DAi53A PLUG, VOLT/AMP IND TTT DA15S
CLAMP TTT DA51210
LOCK RETAINER TTT DA51220-1
-L DA154A INDICATOR, VOLT~’AMP, RT PENN AIRBORNE 9A1570

-L DA155A PLUG, VOLT/AMP IND TTT DA15S

CLAMP TTT DA51210
LOCK RETAINER TTT DAS1220-1
EMPRO MLA-105A 50MV
-L DA156A SHUNT, LEFT LOAD
-L DA157A SHUNT, LEFT ALTERNAlbR EMPRO MLA-70A-50MV
EMPRO MLA-I05A 50MV
-L DA158A SHUNT, RIGHT LOAD
-L DA159A SHUNT, RIGHT ALTERNATOR EMPRO MLA-70A-50MV
-L DA1GOA FUSEHOLDER, LT LOAD SHUNT(-) McGRAW-EDISON FHN42A
FUSE, 5A McGRAW-EDISON FMO1-5A
-L DA1G1A FUSEHOLDER, LT LOAD SHUNT~ McGRAW-EDISON FHN42A
FUSE, 5A McGRAW-EDISON FMOI3A
-L DA162A FUSEHOLDER, LT ALT SHUNT McGRAW-EDISON FHN42A
FUSE, 5A McGRAV~EDISON FM01-5A
-L DA163A FUSEHOLDER, LT ALT SHUNT McGRAW-EDISON FHN42A
FUSE, 5A McGRAW-EDISON FMO1-SA
-L DA164A FUSEHOLDER,RTLOAD SHUNT~ McGRAW-EDISON FHN42A
FUSE, 5A McGRAWEDISON FMO~ -5A
-L DA165A FUSEHOLDER, RT LOAD SHUNT(-) McGRAW-EDISON FHN42A
FUSE, 5A McGRAWEDISON FMO1-5A
-L DA166A FUSEHOLDER, RT ALT SHUNT McGRAW-EDISON FHN42A
FUSE, 5A McGRAW-EDISON FMO1-5A
-L DA167A FUSEHOLDER, Ri ALT SHUNT ~j McGRAV\F-EDISON FHN42A
FUSE, 5A McGRAW-EDISON FMOI-5A

JKL DB1O1A C/B TURN COORD KLIXON 7277-2-2

JK- DB102A TURN GO-ORDINATOR U.I. S013CODE N.5
JK- DB102B TURN GO-ORDINATOR ASTRONAUTICS 303990-028MSC
JKL DB1OSA PLUG, TURN COORD MS3106A-10SL-3S
CABLE CLAMP MS3507-4A or-4B
-L DB1S0A TURN COORDINATOR Uj 9551B CODE N.541

JK- DC?OIA CYL HD TEMP PROBE MOONE/ 880010-503

-L DC1S0A C/BOILTEMP/CHT KLIXON 7277-2-1
-L DC151A CHT/OILTEMP IND PENN AIRBORNE 9A1630
-L DC152A PLUG, CHT/OIL TEMP TTT DB25S
CLAMP TTT DB51212
LOCK RETAINER TTT DB51221-1
-L DC153A SWITCH, CHT GRAY HILL 71AD30-02-2-AJN
KNOB RAYTHEON 50-3-1G
-L DC154A PLUG, CHT, i6 PI’N AMP 206037-1
CLAMP AMP 206070-1
-L DC155A RECPT, CHT: 16 61N AMP 206036-3
CLAMP AMP 206070-1

91-20-02
37
SERVICE AND MAINTINANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 25-1000 THRU 25´•1224
OLDWILLWAYNE
DESCRIPTION VENDOR PART NO. NOTES
CODE

-L DC156A PROBE, CHT-CYL W1 MS24482-i

-L DC157A PROBE, CHT-CYL #2 MS24482-1
-L DC158A PROBE, CHT-CYL #3 MS24482-i
-L DC159A PROBE, CHT-CYL #4 MS24482-1
-L DC1GOA PROBE, CHT-CYL #5 MS24482-1
-L DC1G1A PROBE, CHT-CYL #6 MS24482-1

AN5546-1 (ALT) -EITHER REQUIRES AN4076-1 ADAPTER

J- DD1O1A C/B, OAT/EGT KLU(ON 7277-2-2

J- DD?02A GAUGE, OAT/EGT MOONEY 880001-507
J- DDI02B GAUGE, OAT/EGT, 4 PRO’PE iOPi) B aD 0230-003
J- DD1OSA PLUG,, OAT/EGT AMP 20583&1

CLAMP, CABLE AMP 206062-1

JKL DDI04A PROBE, OAT MOONEY 880004-501

-L DD150A C/B OAT IND KLD(ON 7277-2-1
-L DDI51A INDICATOR, OAT PENN AIRBORNE 9A1 580
-L DD152A PLUG, OAT ITT DAI5S
CLAMP ITT DA51210
LOCK RETAINER TTT DA51220-1

J- DF1OIA TRANSMTR, FUEL QTY, LT, VB MOONEY 610242-001

J- DF103A TRANSMTR, FUEL QTY, RT, IW MOONEY 610242-001
JKL DM02A TRANSMITTER, FUEL QTY, O/B, L’T MOONEY 610243-003
JKL DF104A TRANSMITTER, FUEL QTY, O/B, RT MOONEY 610243-001
-KL DFIOSA TRANSMITTER, FUEL QTY, I/B, LT MOONEY 610242-003
-KL DF1OGA TRANSMITTER, FUEL QTY, I/B, RT MOONEY 610242-003
-L DF150A CIB FUEL QTY, LH/RH KLU(ON 7271-2-1

-L DF1S1A FUEL QTY IND, L/R PENN AIRBORNE 9A1620-2

-L DFi52A PLUG, FUEL QTY, L/R ITT DB25S
CLAMP ITT DB51212
LOCK RETAINER ITT DB51221-1

JK- DG1O1A C/B, CLUSTER GAUGE KLIXON 7277-2-5

J- DG1 02A GAUGE, CLUSTER MOONEY 640281-523
-K- DG1 03A GAUGE, CLUSTER MOONC/ 640281-525
-L DG1SOA C/B INSTRUMENTDISPLAY KLIXON 7277-2-1
-L DG1S1A INSTRUMENT DISPLAY PENN AIRBORNE 9A1600-2
-L DG152A PLUG, INSTR. DISPLAY ITT DB25S
CLAMP ITT DB51212
LOCK RETAINER ITT DB51221-1
-L DG153A C/B INSTRUMENT PTT KUXON 7277-2-1
-L DG154A SWITCH, INSTRUMENT PTT ALCOSWTTCH MPE1OGF
CAP, BLACK ALCOSWTTCH C-22
-L DG155A PLUG, 9 PIN, PTT AMP 20670&1
CLAMP AMP 2069661
-L DG156A RECPT, PTT,’S PI’N AMP 206705-2
CLAMP AMP 206966-1
-L DG157A PLUG, GRND #7, 28 PIN AMP 205839-3
CLAMP AMP 206070-1
-L DG158A RECPT, GRND 2sblN
#j, AMP 206152-1
CLAMP AMP 206070-1

91-20-02
38
 M20K SERVICE AND MAINTINANCE MANUAL
MOONEY AIRCRAFT CORPORATION
28 VOLT- S/N 251000 THRU 25-1224
OLDWILLWAYNE
VENDOR PART NO. NOTES
CODE DESCRIPTION

PROPE, OIL TEMP MOONEY 880009-501

JK- DH1OIA
WASHER AN900-I0 or MS35769-11
-L DH1S0A PROBE,OILTEMP PbRSCHE 933.606.002.00

DJ1O1A XDUCR, OIL PRESS MOONEY 880046-501

JK-
DJ102A PLUG, OIL PRESS MS3106AiOSL-3S
JK-
CLAMP, CABLE MS3057-4AIB
-L DJ1SOA XDUCER, OIL PRESS 6RUdK PDCR821-0662
(100 PSIG)
-L DJ1S1A PLUG, Oil PRESS, 4 PIN AMP 206060-1
CLAMP AMP 206062-1

DJ?52A RECPT, OIL PRESS, 4 PIN AMP 206153-1

-L
CLAMP AMP 206062-1

JK- DJ175A XDUCR, OIL PRESS DRUCK PDCR821-0662-100

KULTTE APT-1 54-1 000-1 00PSIG
(ALT)
JK- DJ176A AMPLIFIER, OIL PRESS IAl 950D0311-003
DJ178A PLUG, 4 PIN AMP 206060-1
JK-
CLAMP AMP 206062-1
JK- DJ179A RECPT, 4 PIFj AMP 206153´•1
CLAMP AMP 206062-1
DJi 80A PLUG, 4 PIN AMP 206060-1
JK-
CLAMP AMP 206062-1
JK- DJ181A RECPT, 4 PIN AMP 2061 53-1
CLAMP AMP 206062-1

DK1O1A XDUCR, FUEL PRESS MOONEY 880045-501

J-
J- DK102A PLUG, FUEL PRESS XDUCR MS3106A10SL-3S
-L DK1SOA CIB FUELIOIL PRESSURE KilXdN 7277-2-1
-L DK1S1A INDICATOR, FUEUOIL PRESS PENN AIRBORNE 9AI 640
DK152A PLUG, FUEL/OIL PRESS ITT DB25S
-L
CLAMP TTT DB5121 2-1
LOCK RETAINER TTT DB5I221-1
DK153A XDUCER, FUELPRESS DRUCK PDCR 821-0062
-L
(100 PSIG)
-L DK154A PLUG, FUEL i)RE’SS,;1 PII;1 AMP 206060-1
CLAMP AMP 206062-1
-L DK955A RECPT, FUEI: PRESS, 4 PIN AMP 206153-1
CLAMP AMP 206062-1
J- DK175A XDUCR, FUEL PRESS DRUCK PDCR821-0662-30
KULTIE APT-I 53-1 000-30PSIG
(ALT)
J- DK1’IGA AMPLIFIER, FUEL PRESS IAl 950D0311-001
J- DK177A PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
J- DK178A RECPT, 4 PIN AMP 260153-1
CLAMP AMP 206062-1
J- DKI79A PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
J- DK180A RECPT, 4 PIN AMP 260153-1
CLAMP AMP 206062-1

J- DL1O1A TACHOMETER (POINTS) MOONC/ 880039-511

-K- DL1 02A TACHOMETER MOONEY 880039-509
-K- DL1 02B TACHOMETER MCONC/ 880039-513
-K- DL1OZC TACH (RPLCMT FOR DLi028) MOONEY 880039-517
B&D 0520´•006

91-20-02
39
SERVICE AND MAINTINANCE MANUAL M20K MOONN AIRCRAFT CORPORATION
28 VOLT SM 251000 THRU 25-1224
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES
,,,,,-----------I-----------------~-
=======si,===================‘------------------

JK- DL1 03A PLUG-TACH MS31 06A14S-5S

-K- DL103A TACH SENSOR Ba D 0402-102
TACH SENSOR (ALT) B&D 0402-104
JK- DL104A RECPT, 4 PIN AMP 206153-1
CLAMP AMP 206062-1
JK- DL1 05A PLUG AMP 206060-1
CLAMP AMP 206062-1
J- DL1O’IA TACHOMETER MOONEY 880039-507
J- DL108A TACH GENERATOR MOONEY 880053-501
B&D 0400-004
J- DL1OSA CABLE ASSY MOONEY 880003-501
J- DLiiOA TACHOMETER MOONEY 880039515
B&D 0520-003
--L DL1SOA DIODE, RPM~UEi FLOW LT 1N2483
--L DL1S1A DIODE, RPM/FUEL FLOW, RT 1N2483

-L DLi52A INDICATOR, RPM/FUEL FLOW PENN AIRBORNE 9A1610-2

-L DL153A PLUG, RPM/FUEL FLOW rTT DB25S
CLAMP ITT DB51212
LOCK RETAINER ITT DB51221-1
-L DL157A SENSOR, RPM #2, RT PORSCHE 933.602.002.01
-L DL158A SENSOR, RPM #1, LT PORSCHE 933.602.002.01

J- DM?O1A HOUR METER MOONEY 880035-507

-K- DM? 02A HOUR METER MOONEY 880035505
-L DMISOA HOUR METER AIRPAX K4205

K4207 or KF4207 (ALT)

-L DM1S1A RECPT, HOUR METER, 4 PIN AMP 206153-1

CLAMP AMP 206062-1
-L DM152A PLUG, HOUR METER, 4 PIN AMP 206060-1
CLAMP AMP 206062-1

JKL DPIO1A C/B, PITOT HEAT MOONEY 930023-205

JK- DP1OIA C/B, PITOT HEAT (SPARES) MOONE/ 930023-241
JKL DP102A PITOT, HEATED AERO INST PH502-24

AN5812-1 (ALT)

JKL DP103A PLUG, PITOT HEAT AN31151

SOCKETS AN3116-i
JK- DP104A BOARD ASSY MOONEY’ 940002-001
JK- DP104B CURRENT MONITOR (SPARES) MOONEY 800221-501
JK- DP1OSA FUSEHOLDER LITTEL i 55020 or 155120
FUSE, 1A LTTTEL 31 3001
JK- DP1OGA PLUG AMP i -480303-0
SOCKETS AMP 6061 9-1
JK- DP1 07A RECPT AMP 1-480305-0
PINS AMP 60620-1
JK- DP108A LIGHT ASSY MOONEY 800346-503
-L DPiSOA RELAY BOX, CURRENT DETECTOR MOONEY 800221-501
-L DP150B RELAY BOX, CURRENT DETECTOR MOONEY 800221-503
-L DP1S1A PLUG, CUR/DECT RELAY AMP 206060-1
CLAMP AMP 206062-1
-L DP152A FUSEHOLDER LTTTEL i 55020 or i 55120
FUSE, 5A-3AG-SLO-BLO LTTTEL 31 3005

91-20-02
40
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTINANCE MANUAL
28 VOLT S/N 25-1000 THRU 25-1224
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

-K- DR1OIA C/B, TIT KLIXON 7277-2-2

-K- DR1 02A INDICATOR, TIT MOONEY 880051-501
-K- DR1 028 INDICATOR, m/EGT MOONEY 880051-503
-K- DR1 03A PLUG, TIT AMP 20583&1
CLAMP AMP 206062-1
-K- DR103B PLUG, 28 PIN AMP 205839-3
CLAMP AMP 206070-1
-K- DR1 04A PROBE, iii MOONEY 880005-501
-K- DR1 04A PROVE, TlT (ALT) MOONEY 880005503
-K- DR1 048 PROBE, nT MOONEY 880055-501

J- DT1O1A PROBE, EGT CYL #1 MOONC/ 880005501

PROBE, EGT CYL #1 (ALT) MOONEY 880005-503
PROBE, EGT CYL #1 (ALT) MOONEY 660110-000
-K- DT1OIA PROBE, EGT- CYL #1 MOONEY 880005-501
PROBE, EGT- CYL #1 (ALT) MOONCI 880005-503
-K- DT102A PROBE, EGT- CYL ti2 MOONEY 880005-501
PROBE, EGT- CYL #2 (ALT) MOONEY 880005-503

-K- DT103A PROBE, EGT-CYL #3 MOONN 880005-501

PROBE, EGT-CYL #3 (ALT) MOONN 880005-503
-K- DT104A PROBE, EGT-CYL #4 MOONEY 880005-501
PROBE, EGT-CYL #4 (ALT) MOONEY 880005-503
-K- DT1 05A PROBE, EGT-CYL#5 MOONC/ 880005-501
PROBE, EGT-CYL #5 (ALT) MOONEY 880005-503
-K- DT1OGA PROBE, EGT-CYL #6 MOONEY 880005-501
PROBE, EGT-CYL #6 (ALT) MOONEY 880005-503

JK- DV1OIA C/B, FUEL FLOW KLIXON 7277-2-2

JK- DV102A INDICATOR, FUEL FLOW MOONEY 880034-501
JK- DV102B INDICATOR, FUEL FLOW(OPT) MOONEY 880034-507
JK- DV102C INDICATOR, FUEL FLOW (OPT) MOONN 880034-513
JK- DV103A PLUG, FUEL FLOW CANNON DE-SS
JK- DV104A XDUCR, FUEL FLOW MOONE/ 880030-501
JK- DV104A XDUCR, FUEL FLOW (OPT) MOONC/ 880030-503
JK- DV104C XDUCR, FUEL FLOW (OPT) MOONEY 880030-505
JK- DV105A SWITCH FUREFLOWMEMORY C&K 7101K
-L DV150A XDUCER, FUEL FLOW PORSCHE 933-110-377-02
(FUEL CONTROL)
-L DVlslA PLUd PORSCHE 933-612-403-00
CLAMP PORSCHE 999-61 5-032-40
BOOT PORSCHE 944-612-1 28-00
CONTACTS PORSCHE 999652-456-22

-L DW1SOA INDICATOR, VERTICAL SPEED UI 7201-2 CODE C.146

-L DW1S1A PLUG, VSI, 3 PIN BENDIX PTO6E-&3S
-L DW1S1A PLUG, V/S (ALT) CANNON KPTO6E-&3S
-L DW1S1A PLUG, VSI (ALT) MS3116-8-3S
CLAMP MS3057-3Aor-3B

JKL EG1O1A C/B GEAR RELAY KLIXON 7277-2-5

JKL EG102A SWITCH, GEAR UP/DN C´•H 8906K2875
JKL EG103A SWITCH, GEAR OVERIDE C´•H SBIDDX492-2
LOCKING RING C-H 29-761
LOCK WASHER C-H 16-886
HU( NUT (2 EA) CH 15-966-6
LAMP (28 V) GE 388

91-20-02
41
SERVICE AND MAINTINANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 25-1000 THRU 25-1224
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

JKL EG104A SWITCH, GEAR SAFETY(A/SPEED) MOONEY 880013-507

JKL EG1OSA C/B, GEAR ACTUATOR KLIXON 7277-2-15
JKL EG1OGA SWITCH, GEAR UP LIMIT MICRO SWITCH DT-2R-A7
ACTUATOR MICRO SWITCH MCP2711
JKL EG1O’IA SWITCH, GEAR DN LIMIT MICRO SWITCH ICHI-6
JKL EG?O’IA SWITCH, GEAR DN LIMIT (ALT) SAINT SWITCH,INC ML1116
JKL EG108A RELAY, GEAR UP C-H 6041H220
JKL EG1OSA RELAY, GEAR DOWN C-H 6041H220
JKL EG11OA ACTUATOR, LANDING GEAR MOONEY 560254-503
JKL EG11OA ACTUATOR, LDG. GR (ALT) MOONEY 880037-507
JKL EG111A DIODE,GEAR UP RELAY 1N2483
LOCK RETAINER TTT DB51221-1
JKL EG112A DIODE, GEAR DOWN RELAY 1N2483

JKL ECMO1A SWITCH, REMOTE ELT D&M DM-U651

JKL ELT1O1A SWITCH,REMOTE ELT (ALT) C&K 7101K

JKL ELT102A ELT TRANSMITTER D&M DM-ELT-8

-L ELT150A PLUG, ELT AMP 206060-1
CLAMP AMP 206062-’1
-L ELT1S1A RECPT, ELT AMP 206153-1
CLAMP AMP 206062-1

JK- FON1O1A PHONE-JACK SWITCHCRAFT C-l 1

WASHERS SWITCHCRAFT S-i 028 8 S-1029

-L JEiSOB C/B IGNITION, LT KLUXON 7277-2-7.5

-L JEi51B C/B IGNITION, 2iT KLU(ON 7277-2-7.5
-L JE152B IGNITION BOX, LT PORSCHE 933.602.007.07
-L JE153B IGNITION BOX, RT PORSCHE 933.602.007.07
-L JE?54B PLUG, IGN BOX, LT CANNON CA3106A-20A-48S-B-O3
-L JE154B PLUG, IGN BOX, LT (ALT) CANNON-GERMANY CA3106A-20A-48S-&15
-L JE154B PLUG, IGN BOX, LT (ALT) PORSCHE 933.612.440.00
TINEL-LOCK ADAPTER RAYCHEM TXRi 8AB45C2012AI
ADAPTER (ALT) SUNBANK S2900AA1 912AI-S034-000
BOOT RAYCHEM 202C621-51/164
BOOT (ALT/SUPPLEMENT) RAYCHEM 202S1 42-258
-L JE155B PLUG, IGN BOX, RT (ALT) CANNON-GERMANY CA3106A-20A-48SB-15
-L JE155B PLUG, IGN BOX, RT (ALT) PORSCHE 933.612.440.01
TINEL-LOCKADAPTER RAYCHEM TXR1 8AB45C2012AI
ADAPTER (ALT) SUNBANK S2900AA191 2AI-S034-000
BOOT RAYCHEM 202(=621-51M 64
BOOT (ALT/SUPPLEMENT) RAYCHEM 2028142-258
-L JE156B PLUG, IGN BOX COIL, LT (ALT) CANNON-GERMANY CA3106E-10SL-3P-&14
-L JEi56B PLUG, IGN BOX COIL, LT (ALT) PORSCHE 933.612.409.01
TINEL-LOCK ADAPTER RAYCHEM TXR18AB00-Cli 04AI
ADAPTER (ALT) SUNBANK S2900AS0604AI-S034-000
ADAPTER (ALT) SUNBANK S2900AS1 004AI-S034-000
COUPLING SUNBANK S3292
BOOT RAYCHEM 202S121-25S
-L JE157B PLUG, IGN BOX COIL, RT (ALT) CANNON-GERMANY CA3106E-10SL-3P-&14
-L JE157B PLUG, IGN BOX COIL, RT (ALT) PORSCHE 933.612.409.01
TINEL-LOCK ADAPTER RAYCHEM TXR18ABOO-C1104AI
ADAPTER (ALT) SUNBANK S29 OOAS 0504A I-S034-000
ADAPTER (ALT) SUNBANK S2900ASi 004AI-S034-000
COUPLING SUNBANK S3292
BOOT RAYCHEM 202S121-25S

91-20-02
42
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTINANCE MANUAL
28 VOLT SM 25-1000 THRU 25-1224
OLDWILLWAYNE
DESCRIPTION VENDOR PART NO. NOTES
CODE

-L JE162B PLUG, IGN COIL, LT CANNON-GERMANY CA3106E-iOSL-4S-B-14

-L JE162B PLUG, IGN COIL, LT PORSCHE 933.612.407.01
TINEL-LOCK ADAPTER RAYCHEM TXR18AB00-C1~ 04AI
ADAPTER (ALT) SUNBANK S2900AS0504AI-S034-000
ADAPTER (ALT) SUNBANK S2900ASi 004AI-S034-000
COUPLING SUNBANK S3292
BOOT RAYCHEM 202S1 21-25S
-L JE163B PLUG, IGN COIL, RT CANNON-GERMANY CA3106E-10SL-4S-B-14
-L JE163B PLUG, IGN COIL, RT PORSCHE 933.612.407.0~
TINEL-LOCK ADAPTER RAYCHEM TXR18AB00-C1104AI
ADAPTER (ALT) SUNBANK S2900AS0504AI-S034-000
ADAPTER (ALT) SUNBANK S2900AS1 004AI-S034-000
COUPLING SUNBANK S3292
BOOT RAYCHEM 202S1 21-25S

-L JE164A IGNITION COIL, LT PORSCHE N/A

-L JE165A IGNITION COIL, RT PORSCHE NIA
-L JE168A SENSOR, TDC #1 PORSCHE N/A
-L JE169A SENSOR, TDC #2 PORSCHE N/A
-L JE170C RECPT,3PIN CANNON-GERMANY CA121001-633
RECPT, 3 PIN (ALT) PORSCHE 933-612411-00
ADAPTER RACHEM TXRI 8AB000-Ci1 04AI
ADAPTER (ALT) SUNBANK S2900AS0604AI-S034-000
ADAPTER (ALT) SUNBANK S2900ASi 004AI-S034-000
COUPLING SUNBANK S3292
BOOT RAYCHEM 202S1 21-25S
-L JE171C PLUG,3PIN CANNON-GERMANY CAOGEHiOSLSPB14
PLUG, 3 PIN (ALT) PORSCHE 933-612-412-00
ADAPTER RACHEM TXR18AB000-Cli 04AI
ADAPTER (ALT) SUNBANK S2900AS0604AI-S034-000
ADAPTER (ALT) SUNBANK S2900ASi 004AI-S034-000
COUPLING SUNBANK S3292
BOOT RAYCHEM 202S121-25S
-L JE?72B RECEPT, IGlj, COIL, iT, 4 PIN’ CANNON MS31 OOK-i 4S´•2P
ADAPTER RAYCHEM TXRi 8AB000-Ci 404AI
ADAPTER (ALT) SUNBANK S2900AS1 004AI-S034-000
BOOT RAYCHEM 202S121-25S
-L JE173B PLUG, IGN, deli LT, PI’N CANNON MS3106E-14S-2S
ADAPTER RAYCHEM TXR1 8AB000-C1 404AI
ADAPTER (ALT) SUNBANK S2900AS1 004AI-S034-000
BOOT RAYCHEM 202S121-25S
-L JE174C RECPT,3PIN CANNON-GERMANY CAi21001-633
RECPT, 3 PIN (ALT) PORSCHE 933-612-411-00
ADAPTER RACHEM TXR18AB000-Ci i 04AI
ADAPTER (ALT) SUNBANK S2900AS0604AI-S034-000
ADAPTER (ALT) SUNBANK S2900ASi 004AI-S034-000
COUPLING SUNBANK S3292
BOOT RAYCHEM 202S121-25S

-L JE?75C PLUG,SPIN CANNON-GERMANY CAOGEH~OSL3PB14

PLUG, 3 PIN (ALT) PORSCHE 933-612-412-00
ADAPTER RACHEM TXR1 8AB000-C11 04AI
ADAPTER (ALT) SUNBANK S2900AS0604AI-S034-000
ADAPTER (ALT) SUNBANK S2900ASi 004AI-S034-000
COUPLING SUNBANK S3292
BOOT RAYCHEM 202S1 21-25S

91-20-02
43
 SERVICE AND MAINTINANCE MANUAL M20K MOONN AIRCRAFT CORPORATION
28 VOLT SR\I 25-1000 THRU 25-1224
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

-L JE176B RECPT, IGN. COIL, RT, 4 PIN MS3100K-14S2P

ADAPTER d4YdHEM TXR1 8AB000-C1 404AI
ADAPTER(ALT) SUNBANK S2900AS1 004AI-S034-000
BOOT RAYCHEM 202S121-25S
-L JE177B PLUG, (ALT) MS3106E-14S2S
ADAPTER dAYdHEM TXR18AB000-Ci 404AI
ADAPTER(ALT) SUNBANK S2900ASi 004AI-S034-000
BOOT RAYCHEM 202S121-25S
-L JE178A PLUG, 3 i>lN AMP 1-480303-0
SOCKET AMP 6061 9-i
-L JE179A RECPT, C/B, 3 PII;I AMP 1-480305-0
PINS AMP 60620-1
-L JE180A PLUG, 2 PIN AMP 1-48031&0
SOCKET AMP 6061 91
-L JE181A RECPT, C/B, 2 PIN AMP 1-480319-0
PINS AMP 60620-1
-L JE182A PLUG, TACH/FUEL FLOW AMP i -48031&0
SOCKET AMP 60619-1
-L JEi83A RECPT, TACH/FUEL FLOW AMP 1-480319-0
PINS AMP 60620-1
JKL JM?O1A SWITCH, IGNITION BENDIX- SCINTILLA 10-357210-9
PLACARD BENDIX- SCINTILLA 10-1 87-468
J- JM102A MAGNETO BENDIX-SCINTILLA 10-682555-1
J- JMI02B MAGNETO (ALT) BENDIXSCINTILLA 10-682555-111
-K- JMi 03A MAGNETO, RIGHT BENDIX-SCINTILLA 10-79020-120
TCM 6408961
-K- JM103B MAGNETO, RiGHT SLICK 6224
-K- JMI 04A MAGNENTO, LEFT BENDIXSCINTILLA 10-79020-120
TCM 640896-1
-K- JM1 048 MAGNET’O, LEFT’ SLICK 6224

JK- LB1O1A C/B, ROTATING BEACON MOONEY 930023´•203

JK- LB1O1A C/B, ROTATING BCN (SPARES) MOONEY 930023-243
JK- LB102A LIGHT, ROTATING BCN WHELEN WRMI
ADAPTER WHELEN WRM-65
JKL LB102B LT, ROTATING BCN, ilED‘(ALi) WHELEN 90033-19
JKL LB102B LT, ROTATING BCN, WTE (ALT) WHELEN 90033-20
JKL LB103A PLUG, 2 PIN AMP 1-480318-0
SOCKET AMP 60619-1
JKL LB104A RECPT, 2 PIN AMP 1-480319-0
PINS AMP 60620-1
JKL LC1O1A FUSEHOLDER, CLOCK, 5AMP LTTTEL 155020/155120
FUSE,(SA-3AG-SLO-BLO) LITTEL 313005
JKL LCI02A SWITCH, CABIN LIGHT, FWD CARLING TILC64-IS-WH-FN
JKL LCPO3A RESISTOR, CABIN LIGHT, MID DALE RH-10-20OHM
JKL LC104A LIGHT, CABIN, FWD, LT H.H. SMITH 1930
LAMP GE 1818
JKL LC1OSA LIGHT, CABIN, FWD, KT H.H. SMITH 1930
LAMP GE 1818
JKL LC1OGA LIGHT, CABIN, FWD, iT H.H. SMITH 1930
LAMP GE 1818
JKL LC107A LIGHT, CABIN, FWD, RT H.H. SMITH 1930
LAMP GE 1818

91~20-02
44
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTINANCE MANUAL
28 VOLT SM 25-1000 THRU 251224
OLDWILLWAYNE
VENDOR PART NO. NOTES
CODE DESCRIPTION

LC108A SWITCH, CABIN LIGHT, REAR CARLING TILC64-1S-WH-FN

JKL
LCIOSA RESISTOR, CABIN LIGHT SW DALE RH-10-20 OHM
JKL
H.H. SMTTH i 930
JKL LC1?OA LIGHT, CABIN, REAR, LT
LAMP GE 1818
JKL LC111A LIGHT, CABIN, REAR,RT H.H. SMITH 1930
LAMP GE 1818
JKL LCI?2A LIGHT, CABIN, REAR,LT H.H. SMTTH 1930
LAMP GE 1818
LC113A LIGHT, CABIN, REAR, RT H.H. SMTTH 1930
JKL
LAMP GE 1818
-L LC114A LIGHT, CABIN, REAR,LT H.H. SMITH 1930
LAMP GE 1818
-L LC?ISA LIGHT, CABIN, REAR,RT H.H. SMITH 1930
LAMP GE 1818

LL1OIA SWITCH, LDG Li MOONEY 930023-235

J-
LL102A LANDING LIGHT GE 4553
J-
AMP 206153-1
JK- LL103A RECPT, LDG LT
CLAMP AMP 206062-1
JK- LL104A PLUG, LDG LT AMP 206060-1
CLAMP AMP 206062-1
-K- LL1 05A C/B, LDG LT, LEFj KLIXON 7277-2-10
-K- LL1 06A LIGHT, LDG, LEFT GE 4596
-K- LL107A C/B, LDG LT, RIGHT KLIXON 7271-2-10
-K- LL1 08A LIGHT, LDG, RIGHT GE 4596
-K- LL1OSA SWITCH, LDG LT C-H 8143-K21-E13-M50
-L LL1SOA C/B, LANDING LIGHT, LEFT KLIXON 7277-2-20
C/B, LDG LT, LEFT (ALT) MECHANICAL PROD 4200-002-25
-L LL151A C/B LANDING LIGHT, RIGHT KLIXON 7271-2-20
C/B, LDG LT, RIGHT (ALT) MECHANICAL PROD 4200-002-25
-L LL152A SWITCH, LANDING LIGHT C-H 8162-K22-Ei 3-M50
-L LL154A LANDING LIGHT-RT WING GE 4596
-L LL155A TAXI LIGHT-RT WING GE 4596
-L LL156A SWITCH, TAXI LIGHT C-H 8162-K22-Ei 3-M50
-L LL157A TAXI LIGHT, LEFT WING GE 4596
-L LL158A LANDING LIGHT, LEFT WING GE 4596

JKL LN1O1A C/B NAV LIGHTS MOONEY 930023-201

JKL LN102A LIGHT, TAIL, LT WING MOONEY 800051-501
BULB,28V WHELEN 34-0228030-85
JKL LN103A LIGHT, TAIL RT WING MOONEY 800051-501
JKL LN?04d PLUG, TAIL LIGHT, RT WING AMP 1-480318-0
SOCKETS AMP 6061 91
JKL LN1OSA RECPT, TAIL LIGHT RT WING AMP 1-480319-0
PINS AMP 60620-1
JKL LN1OGA PLUG, TAIL NAV LIGHT AMP 1-480318-0
SOCKETS AMP 6061 9-1
JKL LN1O’IA RECPT, TAIL NAV LIGHT AMP 1-480319-1
PINS AMP 60620-1

JKL LP1O1A C/B PANEL LIGHTS KLLXON 7277-2-5

JKL LP102A C/B GLARESHIELD LIGHTS KLIXON 7277-2-5
JKL LP103A LAMP, COMPASS LIGHT GE AVIATION RED 327
or327

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45
SERVICE AND MAINTINANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 25-1000 THRU 25-1224
OLDWILLWAYNE
DESCRIPTION VENDOR PART NO. NOTES
CODE

JK- LP104A RECPT, COMPASS LT DEANS DEA90020MALE

JKL LP1OSA PLUG, COMPASS LIGHT DEANS DEA90020FEMALE
JKL LP1OGA LIGHTS, GLARESHIELD (14 EACHj GE 327
JK- LP107A LIGHT HOLDER, TRIM/FLAP DIALIGHT 270-1930-0171-702
LAMP GE 327
LAMP (ALT) GE 385
JK- LP108A LIGHT, COWL FLAP DIALIGHT 270-1930-0171-702
LAMP GE 327
JK- LP1 09A LIGHT, Oj(YdEN SLOAN 855S-0-U
JK- LP1 09B LIGHT, OXYGEN SLOAN 855S-0-U
LAMP GE 327
JK- LP11OA LIGHT, CLUSTER’ GE 327
JK- LP11IA LIGHT, CLUSTER GE 327
JK- LPI 12A LIGHT,CLUSTER GE 327
JK- LP143A LIGHT,CLUSTER GE 327
JK- LP114A LIGHT,CLUSTER GE 327
JK- LP115A LIGHT TRAY, AMMETER B&D 0221-128

JK- LP1?GA LIGHT TRAY, TACHOMETER B&D 0221-128

JK- LP118A LIGHT TRAY, AIRSPEED U.I. BA28-BW3
JK- LP11SA LIGHT TRAY, TURN CO-ORD U.I. BA2&BW3
JK- LP120A LIGHT TRAY, ALTIMETER U.I. BA2&BW3
JK- LP121A LIGHT TRAY, VERTICAL SPEED U.I. BA28-BW3
JK- LP122A LIGHT TRAY, ARTIFICIAL HORIZON SIGMA-TEC IV-192-971
JK- LP123A LIGHTTRAY, DIRECTIONALGYRO SIGMA-TEC IV-192-971
-K- LP125A LIGHT TRAY, TIT B&D 0221-128
JK- LP126A LIGHT TRAY, EGT/OAT B&D 0221-128
-L LP1SOA DIMMER CONTROL BOX IAl 950D0307-000
~-L LP1S1A PLUG, DIMMER CONTROL BOX ITT DBM17W2S
CLAMP TTT DB51 212
LOCK RETAINER ITT DB51221-1
RECPT (2 EA) ITT DM53744-7
-L LP152A SWITCH, PANEL LIGHTS,’DIM’R C&K 7105-JI-Z-Q

-L LP353A SWITCH, G/SHIELD LIGHTS, DIM C&K 7105-J1-Z-Q

-L LP154A LIGHT, FLAP SWITCH MOONEY 130285-003
LAMP GE 327
-L LP155A LIGHT, CONSOLE SWITCH, Ri MOONEY 130285003
LAMP GE 327
-L LP156A RECPT, 9 PIN AMP 206705-2
CLAMP AMP 206966-1
-L LP157A PLUG, 9 PIN AMP 206708-1
CLAMP AMP 206966-1
-L LP158A LIGHT, CONSOLE SWITCH, LT MOONN 130285-003
LAMP GE 327
-L LP159A PLUG, 16 PIN AMP 206037-1
CLAMP AMP 206070-1
-L LP1GOA RECEPT, DlhljNIEk CONTkOLOX AMP 206036-3
CLAMP AMP 206070-1

JKL LR1O1A C/BRECOGNITION LIGHTS MOONEY 930023-231

JKL LR102A RECOGNITION LIGHT, LT WG MOONEY 880049-501
JKL LR103A PLUG, RECOG. LIGHT, LT WG AMP 1-48031&0
SOCKETS AMP 6061 81

91-20-02
46
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTINANCE MANUAL
28 VOLT S/N 25-1000 THRU 25-1224
OLDWILLWAYNE
DESCRIPTION VENDOR PART NO. NOTES
CODE

LR104A RECOGNITION LIGHT, RT MOONEY 880049-501

JKL
LR105A PLUG, RECOG. LIGHT, RT AMP 1-480318´•0
JKL
SOCKETS AMP 6061 9-1
JKL LR1OGA RECPT, RECOG.LIGHT, LEFT AMP 1-480319-0
PINS AMP 60620-1
JKL LR?07A PLUG, RECOG. LiGHi, LEFT AMP 1-480318-0
SOCKETS AMP 60619-1
LR108A RESISTOR, RECOG. LIGHT, LEFT DALE RH-50-7.5 OHMS
JKL
LR1OSA RECPT, RECOG. LIGHT, RT AMP 1-480319-0
JKL
PINS AMP 60620-1
JKL LR11OA PLUG, RECOG. Ri
LiGHi, AMP 1-48031 8-0
SOCKETS AMP 60619-1
JKL LR111A RESISTOR, RECOG. LIGHT, dT DALE RH-50-7.5 OHMS

JKL LS1O1A C/B STROBE LIGHTS MOONEY 930023-207

JKL LS1O1A C/B STROBE LIGHTS (ALT) MOONEY 930023-237
JKL LS102A POWER SUPPLY, STROBE, LTW~ WHELEN 01-077032800
JKL LS103A RECPT, STROBE P/S, LT WG AMP 1-480305-0
JKL LS104A RECPT, STROBE P/S,LT WG AMP 1-4803050

JKL LS1OSA PLUG, NAV/STROBE, LT WG AMP 1-480303-0

JKL LS1OGA LIGHT, NAV/STROBE, LT WG WHELEN A650-PR-D-M
JKL LS107A STROBE PWR SUPPLY, RT WG WHELEN 01-0770329-00
JKL LS108A RECPT, STROBE PWR SUPPLY, RT AMP 1-4803050
JKL LS1OSA RECPT,STROBE LIGHT P/S, RT AMP 1-4803050
JKL LS11OA PLUG,STROBE LIGHT, RT AMP i -480303-0
JKL LS111A NAV/STROBE LIGHT RT. WING WHELEN A650-PG-D-M
JKL LS112A POWER SUPPLY, TAIL STROBE WHELEN 01-0770329-00
AMP 1-4803050
JKL LS113A RECPT, TAIL STROBE PWR SUPPLY
AMP 1-4803050
JKL LS114A RECPT, TAIL STROBE PWR SUPPLY
JKL LS11SA PLUG, TAIL STROBE AMP 206060-1
CLAMP AMP 206062-1
JKL LS11GA RECPT, TAIL’STROBE AMP 206153-1
CLAMP AMP 206062-1
JKL LS117A PLUG, TAIL STROBE AMP 1-480303-0
JKL LS11E)A STROBE LIGHT, TAIL MOONEY 470013-501
JK- LS?1SA RECPT AMP 1-4803050
JK- LS1 20A RECPT AMP 1-480305-0
JK- LS121A RECPT AMP i -4803050

JKL MA1O1A AUX. PWR. RECEPTACLE AN2552-3A

JKL MA102A RELAY, AUX. PWR C-H 6041H202
(ALT) C-H 6041 H202A
JKL MA103A DIODE, AUX i>V~i RELAY SARKES TARZIAN iOH3P
JK- MA1 04A DIODE 1N2483

JKL MB1O1A AVIONICS CONTROL RELAY MAGNACRAFT V~j7CSX-3

BASE MAGNACRAFT 70-303
J- MB1O1B DIODE 1N2483
JK- MB1 02A DIODE 1 N2483
J- MB102A DIODE 1N2483
JKL MB103A DIODE 1N2483
JK- MB1 04A RELAY, AVIONICS MASTF~R P:B MB4443
SOCKET P-B 27E122
SPRING P-B 20C176
STANDOFF P-B 21 8212

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47
SERVICE AND MAINTINANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 25-1000 THRU 251224
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES
==========================I==---===

JK- MB? 04A RELAY, AVIONICS MASTER (ALT) P-B MB4443-1

JKL MB107A SWITCH, AVIONICS MASTER C&K 7101K
J- MB1 078 SWITCH, MASTER, AVIONICS MOONEY 930023-213
JKL MB1OSA C/B HSI KLIXON 7277-2-XXOIARIES)
JKL MB11OA C/B COM1 KLIXON 72n-2-XXO/ARIES)
JKL MB11?A C/B NAV1 KLU(ON 7277-2-XXOIARIES)
JKL MB112A C/BAUDIO KLIXON 72n-2-XXOIARIES)
JKL MB113A C/B PHONE KLIXON 7277-2-XXOIARIES)
JKL MB114A C/B ADF KLIXON 7277-2-XXOIARIES)
JKL MB115A C/B COM2 KLIXON 7277-2-XXOIARIES)
JKL MB116A C/B NAV2 KLIXON 7277-2-XXOIARIES)
JKL MB117A C/B TRANSPONDER KLIXON 7277-2-XXO/ARIES)
JKL MB118A C/B ENCODER KLIXON 7277-2-XXOIARIES)
JKL MB11SA C/B AUTOPILOT/TRIM KLIXON 7277-2-XXOIARIES)
JKL MB120A C/B RADAR KLIXON 7277-2-XXOIAR1ES)
JKL MB1Z1A C/B DME KLIXON 7277-2-XXOIARIES)
JKL MB122A C/B LORAN KLU(ON 7277-2-XXOIARIES
JKL MB123A C/B STORMSCOPE KLIXON 72n-2-XXO/ARIES
JKL MB124A C/B TELEPHONE KLIXON 7277-2-XXO/ARIES)
JKL MB125A C/B RMI KLIXON 7277-2-XXO/ARIES)
JKL MB126A C/BR/NAV KLIXON 7277-2-XXOIARIES)
JKL MB127A C/BINVERTER KLIXON 7277-2-XXOIARIES)
JKL MB128A C/B STEREO KLIXON 7277-2-XXOIARIES)
JKL MB129A C1B PROP DE-ICE MOONEY 930023-223
JKL MB?31A BUS BAR #10 MOONEY 913127-019
JKL MB132A BUS BAR #11 MOONEY 913127-019
JKL MB133A BUS BAR #12 MOONEY 913127-019
JKL MB134A BUS BAR #13 MOONEY 913127-005
JKL MB135A C/B, YAW DAMPER KLIXON 7277-2-7.5
JKL MB136A C/B, RADAR ALTIMETER KLIXON 7277-2-7.5
JKL MB137A GIB, ARTIFICIAL HORIZON KLIXON 7277-2-5
-L MB150A AVIONICS BUS BAR #i MOONE/ 913127-73
--L MB1S1A AVIONICS BUS BAR #2 MOONEY 913127-73
--L MB152A AVIONICS BUS BAR #3 MOONEY 913127-73
-L MB153A AVIONICS BUS BAR #4 MOONEY 913127-73
-L MB154A AVIONICS BUS BAR #5 MOONEY 913127-73
-L MB155A AVIONICS BUS BAR #6 MOONEY 913127-73
--L MB156A AVIONICS BUS BAR #7 MOONEY 913127-73
-L MB157A SHUNT MOONEY 913127-049
-L MB158A AVIONICS MASTER RELAY AROMAT HG4-DC24V
RECEPTACLE AROMAT HGdSF
-L MB159A DIODE 1N2483

-L MB1GOA FUSEHOLDER LTTTEL 155020 or 155120

FUSE iA LITTEL 313001
-L MB162A DIODE, STARTER SOLENOID, LT 1N2483
-L MB163A DIODE, STARTER SOLENOID 1N2483
-L MB164A ARTIFICIAL HORIZ C’AS~LEB’ERRY 300-2BL
-L MB165A PLUG, ART.HORIZ AMPHENOL 126-222
-L MB166A C/B, AUTOPILOT ALERT KLU(ON 7277-2-XXOIARIES)

JKL MC1O1A CIGAR LIGHTER MOONEY 800338503

-L MC1S0A C/B, CIGAR LIGHTER KLIXON 7277-2-10

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MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTINANCE MANUAL
28 VOLT SM 25-1000 THRU 25-1224
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

JK- ME1OIA CLOCK, ELECTRIC MIDCCON. MD-88L

LIGHT TRAY BA28-24-BV\12
JK- ME1O1B CLOCK. (OPT) M’IDdONj. MD-88L O
LIGHT TRAY BA28-24-B\RR
--L ME~BOA CLOCK, (ALT) IA;I 950[)0312.000
-L ME1SOB CLOCK, CONTROL WHEEL PORSCHE 944.641.213.00
-L ME1S1A RECPT, CONTROL WHEEL AMP 206705-2
CLAMP AMP 206966-1
-L ME152A PLUG, CONTROL WHEEL AMP 20670&1
CLAMP AMP 206966-1

JK- MIC1O1A JACK, MICROPHONE SWITCHCRAFT C-i 2B

WASHERS SWTTCHCRAFT S-1028 or S-l 029
-L MIC102A JACK, MICROPHONE,CONSOLE SWITCHCRAFT C´•I2B
WASHERS SWITCHCRAFT S-1028 or S-l 029

JK- MJ1OIA JUNCTION BLOCK (GND) BEAU 77014-52

JUMPER EDGE ON BEAU 7233-16
JK- MJ102A JUNCTION BLOCK (GND) BEAU 71106-52
JUMPER EDGEON BEAU 7233-8

JK- MJ103A JUNCTION BLOCK (DIM) BEAU 711 06-52

JUMPER EDGE ON BEAU 7233-8

JK- MP?O1A TIMER B.F. GOODRICH 3E1 899-1

JK- MP1 02A SHUNT B.F. GOODRICH MS91 586-1
JK- MP103A FUSEHOLDER LITTEL 155020 or i 55120
FUSE, 1A LITTEL 313001
JK- MP? 04A FUSEHOLDER LITTtEL i 55020 or 155120
FUSE, 1A LITTEL 313001
JK- MP1 05A AMMETER B.F. GOODRICH 3E1 872-1
JK- MP1OGA SLIP-RING BLOCK B.F. GOODRICH 3E2062-1
-L MP?50A C/B-SWITCH, PROP dE-ldE (15A)’ ETA 930023-223
-L MPiS1A TIMER B.F. GOObRICH 3E2311-4
-L MP152A SLIP RING, MODULARBRUSHASSY B.F. GOODRICH 3E2062-1
-L MP153 FUSEHOLDER LITTEL 155020 or 155120
FUSE, 1A LTT~EL 31 3001
-L MP154A RELAY BOX, CURRENT MOONEY 800221-505
-L MP155A PLUG. 4 PIN AMP 206060-1
CLAMP AMP 206062-1
MS~ooc SPEAKER ARCHER 40-1197
-L NE1SOA C/B FUEL ENRICH KLIXON 7277-2-1
-L NE1S1A SWITCH, ENRICHMENT MICROSWITCH 1SEI-T
ACTUATOR MICROSWITCH JE-5
-L NE153A VALVE, SOLENOID, MIXTURE
ENRICHMENT PORSCHE 933.606.012.00
-L NE154A DIODE, ENRICH SW.’ 1N2483
-L NE?55A DIODE, ENRICH SW. 1N2483
-L NE156A DIODE, ENRICH SW. 1N2483

JK- NF?OIA C/B, FUEL PUMP MOONEY 930023-211

J- NF1 02A PUMP, FUEL WELDON 81 63B
JK- NF1 03A PLUG, FUELPUMP AMP 206060-1
CLAMP AMP 206062-1
JK- NF1 04A RECPT, FUEI: PUMP AMP 2061 53-1
CLAMP AMP 206062-1

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49
SERVICE AND MAINTINANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 25-1000 THRU 251224
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

-K- NF1O5A C/B, HIGH BOOST, FUEL MOONF/ 930023-219

-K- NF1OGA PUMP, FUEL WELDON 10054B
-K- NF107A C/B, LOW BOOST, FUEL MOONEY 930023-217
-K- NF108A REGULATOR, FUEL PUMP ELECTRO-DELTA VR536
-K- NF1 09A RECPT. AMP 2061 53-1
CLAMP AMP 206062-1
-K- NF11OA PLUG AMP 206060-1
CLAMP AMP 206062-1
-L NF1SOA C/B FUEL PUMP, MAIN KLU(ON 7277-2-10
-L NI=151A C/B FUEL PUMP, EMERGENCY KLIXON 7277-2-10
-L NF152A SW, FUELPUMP,MAIN/BOOST GH 8162-K22-E1 3-M50
GUARD MOONEY 930028-501
-L NF153A SWITCH,FUEL PUMP, EMER.’ C-H 81 42-K21-E7-T50
GUARD MOONEY 93002&501
-L NF154A RECPT, FUEI: PUMP AMP 206060-1
CLAMP AMP 206062-1
-L NF155A RECPT, FUEI: PUMP AMP 206153-1
CLAMP AMP 206062-1
-L NFi56A C/B, BOOST PUMP KLIXON 7277-2-10

-L NF157A FUEL PUMP, BOOST PORSCHE 933.620.001.00

-L NF158A PLUG AMP 206060-1
CLAMP AMP 206062-1
-L NF159A RECPT, FUEI: PUMP AMP 206153-1
CLAMP AMP 206062-1
-L NF1GOA FUEL PUMP, MAIN PORSCHE 933.620.001.00
-L NF1G1A FUEL PUMP, EMERGENCY PORSCHE 933.620.001.00

-K- NP1O1A FUSEHOLDER, PRIMER LITTEL i 55020 or 155120

FUSE, 1 OA,SLO´•BLO LITTEL 313010
-K- NP102A SWITCH, PRIMER CARLING Ti GKGB-1 F-WH-A
-K- NP103A DIFFUSER, PRIMER CONTINENTAL 633862-2

-L NS1SOA SWITCH, COLD START/ENRICH MOONEY 880052-511

-L NS1S1A NOZZLE, COLDSTART PORSCHE 933.612.401.00
PLUG PORSCHE 933.61 5.032,40
CLAMP PORSCHE 999.61 5.032.40
BOOT PORSCHE 944.612.1 28.00
CONTACTS PORSCHE 999.652.456.22
-L NS153A DIODE, COLD START SW 1 N2483

JK- PA1O?A C/B, ALTERNATOR #1 ETA 41-3S34-LN2-041800

JKL PA102A C/B, ALTERNATOR FIELD, #1 KLIXON 7277-2-5
JK- PA103A SWITCH, ALTERNATOR FIELD CH 8133)<-21-Ei 3-T52
JK- PA104A VOLTAGE REGULATOR, #1 ELECTRODELTA VR-802
JK- PA105A RECPT, VOLTAGE REG. AMP 206705-2
CLAMP AMP 206966-1
JK- PA1OGA PLUG, VOLTAGE REG. AMP 206708-2
CLAMP AMP 2069681
-K- PA107A ALTERNATOR #1 CONTINENTAL 649280 or 646719
GEAR ASSY CONTINENTAL 649123
JKL PA108A FILTER MOONEY 880014-501
JKL PA1OSA CAPACTTOR MALLORY CGS302U-050R2C
JK- PA?1OA C/B, ALTERNATdR #i ETA 41-3S34-LN2-041800

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50
 M20K SERVICE AND MAINTINANCE MANUAL
MOONEY AIRCRAFT CORPORATION
28 VOLT SM 25-1000 MRU 25-1224
OLDWILLWAYNE
VENDOR PART NO. NOTES
CODE DESCRIPTION

C/B ALTERNATOR FIELD, #2 KLIXON 7277-2-5

JKL PA?11A
VOLTAGE REGULATOR, #2 ELECTRODELTA VR-802
JK- PA112A
AMP 206705-2
JK- PA113A RECPT, VOLTAGE REG.
CLAMP AMP 2069661
AMP 20670&2
JK- PA114A PLUG, VOLTAGE REG.
CLAMP AMP 206966-1
ALTERNATOR #2 CONTINENTAL 649283 or 649172
-K- PA1I 5A
FILTER MOONEY 88001 4-501
JKL PA11GA
CAPACITOR MALLORY CGS302U-050R2C
JKL PA117A
ALTERNATOR #1 (RIGHT) LYCOMING LW-14367
J- PA1I8A
ALTERNATOR (ALT) PRESTOLITE ALU-6421-LS
J- PA11SA (#2 ALTERNATOR NOT USED AT MIS TIME)
FUSEHOLDER LITTEL 155020 or i 55120
JK- PA1 20A
FUSE 5A LITTEL 313005
JK- PA121A SWITCH, EMERGENdY, FIELD C-H SBiDDX492-2
LOCKING RING C-H 29-761
LOCK WASHER C-H 16-886
C-H 15-996-6
NUT, HU(
LAMP GE 388
DIODE SARKES-TARZIAN 10H3P
JK- PA122A
DIODE SARKES-TARZLAN 10H3P
JK- PA1 23A
JK- PA1 24A SWITCH, ALiERNAT~R FIELD C-H 880052-503
DIODE SARKES-TARZIAN 10H3P
JK- PA1 25A
DIODE SARKES-TARZV\N 1 0H3P
JK- PA1 26A
-L PA1S0A ALTERNATOR, LT PORSCHE 933.603.004.00
ALTERNATOR, RT PORSCHE 933.603.004.00
-L PA1S1A
OVERVOLTAGE CONTROL, LT ELECTRO DELTA OS-400
-L PA152A
-L PA153A PLUG, OVERVOLTAGE
CONTROL, LT AMP 20670&1
CLAMP AMP 206966-1
OVERVOLTAGE CONTROL, RT ELECTRO DELTA OS-400
-L PA154A
-L PA155A PLUG, OVERVOLTAGE
CONTROL, RT AMP 206708-1
CLAMP AMP 2069661
-L PA156A SWITCH, OVERVOLTAGE
RESET, LT C-H SE? DDX492-2
LOCKING RING CH 29-761
LOCKING WASHER C-H 16-886
C-H 15-966-6
NUT, HU( (2 ea)
LAMP GE 388
-L PA?57A SWITCH, OVERVOLTAGE
C-H SB1 DDX492-2
RESET, RT
LOCKING RING C´•H 29-761
LOCKING WASHER C-H 16-886
C-H 15-966-6
NUT, HU( (2 ea)
LAMP GE 388
-L PA158A C/B ALTERNATOR, LT ETA 41-3S14-LN2-70A
C/B ALTERNATOR, LT (ALT) ETA 41-3-S34-LN2-70A
-L PA159A C/B ALTERNATOR, RT ETA 41-3Si 4-LN2-70A
C/B ALTERNATOR, RT (ALT) ETA 41-3S34-LN2-70A
-L PA1GOA RECPT, ONOLTAGE CONTROL, LT AMP 206705-2
CLAMP AMP 206966-1

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51
 SERVICE AND MAINTINANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 251000 THRU 251224
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

-L PAIG1A RECPT,OVERVOLTAGE CONTL,RT AMP 206705-1

CLAMP AMP 206996-1
JK- PB1OIA BATTERY GILL G-242
JKL PB102A RELAY,MASTER,BATTERY,LEFT C-H 6041H202
(ALT) C-H 6041 H202A
JKL PB~03A DIODE,LEFT BATTERY RELAY 1N2483
JK- PB1 04A SWITCH, MASTER C-H 880052-501
JKL PBIOSA C/BBATTERY, LT(ALT) ETA 41-3S14-LN2-70A
C/B BATTERY, LT ETA 41-3S34-LN2-70A
JKL PB1OGA C/B BUS, FLI PNL SWITCH (ALT) ETA 41-3S14-LN2-70A
C/B BUS, FLT PNL SW ETA 41-3S34-LN2-70A
JK- PB107A BUSS BAR #1 MOONEY 913127-005
JK- PB~ 08A BUSS BAR #2 MOONEY 913127-039
JK- PB1OSA BUSS BAR #3 MOONEY 913127-001
JK- PB11OA BUSS BAR #4 MOONEY 913127-019
JK- PB111A BUSS BAR #5 MOONEY 913127-019
JK- PB?12A BUSS BAR #S MOONEY 913127-239

*BUSS BARS 913127-045,-213,-223 or -227 MAY BE USED, AS REQUIRED, BY CIRCUIT BREAKER

INSTALLATION.

-K- PB113A BUSS BAR #7 MOONEY 913127-129

JK- PBI1 4A BUSS BAR #8 MOONEY 913127-041
JK- PB115A BUSS BAR #9 MOONEY 913127-043
JK- PB11GA SHUNT KULKA 600RJ-2
-L PB150A BATTERY, Rli;Hj GILL E243
-L PB1S1A RELAY, BATTERY, Ri C-H 6041H202
(ALT) C-H 6041 H202A
-L PB152A DIODE, BATTERY 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 41-3S14-U1~2-70A
-L PB155A C/B BATTERY, RT (ALT) ETA 41-3S34-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 PB1GOA BUSS BAR #5 MOONEY 913127-19
-L PB1G1A BUSS BAR #6 MOONEY 913127-19
-L PB162A BUSS BAR #7 MOONEY 913127-19
-L PB163A BUSS BAR #8 MOONEY 913127-19
-L PB?64A BUSS BAR #9 MOONEY 913127-53
--L PB165A BUSSBAR#10 MOONEY 913127-53
--L PB166A BUSS BAR #11 MOONEY 913127-53
-L PB167A BUSSBAR#12 MOONEY 913127-TEA
-L PBi68A C/B EMERGENCY CROSSOVER ETA 41-3S1 4-LN2-50A
-L PB168A C/B EMERGENCY
CROSSOVER(ALT) ETA 41-3S34-LN2-50A
C/B COVER PLACARD MOONEY 150080-802
GUARD MOONEY 800232-503
-L PB169A SHUNT, AV16NICS RELA~ MOONEY 913127-047
-L PB1’IOA BATTERY, LEFT GILL G-243
--L PB171A C/B LOAD, A/C, LT ETA 41-3-614-LN2-60A
-L PB171A C/B LOAD, A/C, LT(ALT) ETA 41-3S34-LN2-60A

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52
 M20K SERVICE AND MAINTINANCE MANUAL
MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 25-1000 THRU 25-1224
OLDWILLWAYNE
VENDOR PART NO. NOTES
CODE DESCRIPTION
===================--======’--=---=------========I-=’-----=----=--==--=----=---=

-L PB172A C/B LOAD, AIC. RT ETA 41-3S14-LN2-60A

-L PB172A C/B LOAD, A/C RT (ALT) ETA 41-3S34-LN2-60A
PB173A BUSS BAR #13 MOONEY 913127-55
-L
PB174A BUSS BAR #14 MOONEY 913127-57
-L
PB175A BUSS BAR #15 MOONEY 913127-57
-L
PB176A BUSS BAR #16 MOONEY 913127-59
-L
BUSS BAR #17 MOONEY 913127-59
-L PB177A
-L PB178A BUSS BAR #18 MOONEY 913127-61
-L PB179A BUSS BAR #19 MOONEY 913127-19
-L PBISOA FUSEHOLDER, LEFT MASTER LTTTEL 155020 or 155120
PB180A FUSE SAMP LTTTEL 313005
-L PB181A MASTER RELAY C-H 6041H202
C-H 6041 H202A
(ALT)
-L PB182A DIODE 1N2483
-L PB183A MASTER SWITCH M’00r;lf/ 880052-501
-L PB184A RELAY, AIH PWR MAGNACRAFT W389CX-3
-L PB185A DIODE 1N2483
-L PB186A FUSEHOLDER, AR1, RT LIT~L 155020 or 155120
PB1 86A FUSE, 5AMP LTTTEL 31 3005
-L PB187A FUSEHOLDER, MASTER, RT LTTTEL 155020 or 155120
PB1 87A FUSE, 5AMP LITTEL 31 3005
-L PB188A MASTER RELAY,’ENdlNE’BUS, RT C-H 6041H202
C-H 6041 H202A
(ALT)
-L PB189A DIODE 1N2483

-L PB1SOA MASTER SWITCH (OPT) C-H 8133K-21-E13-T52

-L PB1S1A GRND/DIMMER BOX MOONEY 80022&501

JKL PLO1A PLUG, C/B PANEL #1, 37 PIN AMP 206150-1

CLAMP AMP 2061 38-1
JKL PL02A PLUG, CONSOLE #1, 16 PIN AMP 205837-1
CLAMP AMP 206070-1
JKL PL02B PLUG, CONSOLE #1, 28 PIN AMP 205839-3
CLAMP AMP 206070-1
JKL PL03A PLUG, LEFT SIDE PANEL, 20 PIN MOONEY 930021-501
JKL PL04A PLUG, FLT PNL #1, 26 PIN MOONEY 930021-505
JKL PL03B PLUG, LEFT SIDE PANEL, 26 PIN MOONEY 930021-505
JKL PL04A PLUG, FLT PNL #1, 26 PIN MOONEY 930021-505
JKL PLOSA PLUG, AIS SWITCH #1, 4 PIN AMP 206060-1
CLAMP AMP 206062-1

JKL PLOGA PLUG, AUTOPILOT POWER, 16 PIN AMP 206037-1

CLAMP AMP 202070-1
JKL PL07A PLUG, 16 PIN, CLUSTER GAUGE AMP 206037-1
JKL PL08A PLUG, FIREWALL #1, 19 PIN MS3106~4-22-14S
CLAMP MS3057-12B
JKL PLOSA PLUG, RT.WG. 14 PIN’ MOONCI 930021-0D~
JKL PLOSB PLUG, RT. WING, 20 PIN MOONEY 930021-501
JKL PL1OA PLUG, RT. WING STUB, 14 Plt;l MOONEY 930021-001
JKL PL1IA PLUG, LEFT WING, 14 PIN MOONEY 930021-001
JKL PL12B PLUG, FIREWALL #2, 19 PIN MS3106A-22-14S
CLAMP MS3057-12B
JK- PL13A PLUG, RT. RId PNL, 9 PIN AMP 206708-1
CLAMP AMP 206966-1

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SERVICE AND MAINTINANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 251000 THRU 25-1224
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

JKL PL13B PLUG, AVIONICS MASTER, 4 PIN AMP 206060-1

CLAMP AMP 206062-1
JKL PL14A PLUG, HOUR, 4 PIN AMP 206060-1
CLAMP AMP 206062-1

JKL PL15A PLUG, LEFT WING STUB, 14 PIN MOONEY 930021-001

JKL PL1GA PLUG, GEAR CONTROL, 9 PIN AMP 20670&1
CLAMP AMP 206966-1
JKL PL?7A PLUG, ELECTRIC GEAR, 14 PIN MOONEY 930021-001
JK- PL18A PLUG, DIMMER, 16 PIN AMP 206037-1
CLAMP AMP 206070-1
JKL PL1SA PLUG, A/S SWITCH #2, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
JKL PL20A PLUG, TAILCONE, 16’PIN’ AMP 206037-1
CLAMP AMP 206070-1
JKL PLZ1A PLUG, HEADLINER, 9 PIN AMP 20670&1
CLAMP AMP 206966-1
JKL PL22A PLUG, OVERHEAD, dEAd, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
JKL PL23A PLUG, GRND #1, i6 P’IN AMP 206037-’1
CLAMP AMP 206070´•1
JKL PL24A PLUG, GRND #2, j6 P’IN AMP 206037-1
CLAMP AMP 206070-1
JK- PL25A PLUG, LIGHT CONTROL, 9 PIN AMP 20670&1
CLAMP AMP i06966-1
JK- PL26A PLUG, G/SHIELDHARNESS,4PIN AMP 206060-1

CLAMP AMP 206062-1

JK- PL27A PLUG, FLT PNL #2, 16 PIN AMP 206037-1

CLAMP AMP 206070-1
JKL PL27B PLUG, FLT PNL #2, 20 PIN MOONEY 930021-501
JK- PL28A PLUG, AVIONICS POWER, 20 PIN MOONEY 930021-501
JK- PL29A PLUG, DIM, GND, 20 PIN MOONEY 930021-501
JK- PL30A PLUG, DIM, GND 4 PIN AMP 206060-1
CLAMP AMP 206062-1

JK- PL31A PLUG, STANDBY VAC, 8 PIN AMP 20583&1

CLAMP AMP 206062-1
JK- PL32A PLUG, GEAR RELAY, 4 PI’N AMP 206060-1
CLAMP AMP 206062-1
JKL PL33A PLUG, C/B PNL, 9 PIN AMP 206708-1
CLAMP AMP 2069661
JKL PL34A PLUG, GRND BUSS, 9 PIN AMP 20670&1
CLAMP AMP 206966-1
JKL PL34B PLUG, GRND BUSS, i6 PI’N AMP 206037-1
CLAMP AMP 206070-1
JK- PL35A PLUG, FLT PNL #3, 4 blN AMP 206060-1
CLAMP AMP 206062-1
JK- PL36A PLUG, CONSOLE#2, 8 PIN AMP 205838-1
CLAMP AMP 206062-1
JK- PL37A PLUG, LT SIDE PNL, 8 PIN AMP 20683&1
CLAMP AMP 206062-1
JK- PL38A PLUG, FLAP RELAY, 8 PIN AMP 20570&1
CLAMP AMP 206062-1

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54
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTINANCE MANUAL
28 VOLT S/N 25-1000 THRU 25-1224
OLDWILLWAYNE
DESCRIPTION VENDOR PART NO. NOTES
CODE

JK- PL39A PLUG, FLAP MOTOR, 9 PIN AMP 20670&1

CLAMP AMP 206966-1
-K- PL40A PLUG, THROTTLE SWITCH, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
JKL PLSOA PLUG, C/B PNL #2, 37 PIN AMP 206150-1
FLANGE AMP 207299-4
JKL PLS1A RECPT, IGNlilOEi SVljlTCH,28 PIN MOONEY 930021-505
JKL PL52A PLUG, ALT/STARTER, FMI CANNON MS3106A2822S
CLAMP MS3057-16
JKL PL55A PLUG, EMPENNAGE, 9 PIN AMP 20670&1
CLAMP AMP 206966-1
JKL PL56A PLUG, GRND #Q, 9 PIN AMP 20670&1
CLAMP AMP 206966-1
JKL PL57A PLUG,GRND #5, i4 PjN MOONEY 930021-001
JKL PL58A PLUG, DIM. #2, 16 PIN AMP 206037-1
CLAMP AMP 206070-1
JKL PL59A PLUG, GRND #6, 26 PIN MOONEY 930021-505
JK- PL76A PLUG, 9 PIN AMP 20670&1
CLAMP AMP 206966-1
JK- PL77A PLUG, 28 PIN AMP 205839-3
CLAMP AMP 206070-1
-L PL152A PLUG, GWSTALL’WAKN
HARNESS, 4 PIN AMP 206060-1
CLAMP AMP 206062-1

JK- PS1O1A C/B, IGNTTACH/CIG LIGHTER KLD(ON 7277-2-10

JKL PS102A SOLENOID, STARTER,LT C-H 6041H-202 or-202A
JK- PS? 03A FUSEHOLDER LITTEL 155020 or i 55120

FUSE, iA LITTEL 313001

J- PS1OSA STARTER PRESTOLITE MHB-4016

(ALT) LYCOMING LW1 5572
-K- PS1 06A STARTER TCM 646275
(ALT) TCM 637847
JKL PS1O’IA DIODE, STARTER SdLENOID;LT 1N2483
-L PS1SOA DIODE, PWR START,LT 1N2483
-L PS1S1A DIODE, PWR START,RT 1N2483
-L PS152A SOLENOID, STARTER, RT C´•H 6041H-202 or -202A
-L PS153A DIODE, STARTER SOLENOID 1N2483
-L PS154A STARTER PbRSCHE 933.602.007.03

JKL RB1O1A C/B RADIO BLOWER KLIXON 7277-2-2

JKL RB102A RADIO BLOWER TRW i 9A2790
JKL RB103A FILTER,RADIO BLOWER ARCHER 273-103
JKL RB103A FILTER, RAD. BLWR, (ALT) SPRAGUE 5JX5104A

JKL RCO1A RECPT, C/B PNL #1, 37 PIN AMP 206151-2

JKL RC02A RECPT, CONSOLE #1, 16 PIN AMP 206036-3
CLAMP AMP 206070-1
JKL RC02B RECPT, CONSOLE #I’, 28’PIN AMP 206152-1
CLAMP AMP 206070-1
JKL RCOSA RECPT, LEFiSldEPANEL,20PIN MOONEY 930021-502
JKL RC03B RECPT, LEFTSIDEPANEL,26PIN MOONEY 930021-506

JKL RC04A RECPT, FLT PNL #1, 26 PIN MOONEY 930021-506

JKL RCOSA RECPT, AVS SWITCH #1, 4 PIN AMP 206153-1
CLAMP AMP 206062-1

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55
SERVICE AND MAINTINANCE MANUAL M20K MOONC1 AIRCRAFT CORPORATION
28 VOLT SIN 251000 THRU 25-1224
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

JKL RCOGA RECPT, A/P POWER, 16 PIN AMP 2060363

CLAMP 206070-1
JKL RCO7A RECPT, CLUSTER GAUGE, 1~ PIN AMP 2060383
CLAMP 206070´•1
JKL RC08A RECPT, FIRE’WALL #i, 19’PIN’ MS3100A22-14P
CLAMP MS3057-12B
JKL RC08B RECPT, FIRE’WALL #i, 19’ PIN’ MS3100K22-14P
MS31 00KE22-1 4P
C~ALT)MP MS3057-12B or 12A

JKL RCOSA RECPT, RT. WG, 14 PIN MOONEY 930021-2

JKL RCOSB RECPT, RT WING, 20 PIN MOONC/ 930021-502
JKL RC1OA RECPT, RT. WING STUB, 14 P’IN MOONC/ 930021-2
JKL RC11A RECPT, LT.WG., 14 PIN MOONEY 930021-002
JKL RCP2A RECPT, FIREWALL #2, 19 PIN MS31 00A22-1 4P
CLAMP MS3057-12B
JKL RC12B RECPT, FIRE’WAiL#i MS3100K22-14P
(ALT) MS3100KE22-14P
CLAMP MS3057-12B or-12A
JK RC13A RECPT, RT.RAD16 PNL, 9’PIN’ AivlP 206705-1
CLAMP AMP 2069681
JKL RC?SB RECPT, AVIONICS MAST1~R, 4 PII;1 AMP 206153-1
CLAMP AMP 206062-1
JK- RC14A RECPT, HOUK METER, 4 ’PIN AMP 206153-1
CLAMP AMP 206062-1
JKL RC15A RECPT, LEFT WING STUB, 14 PIN MOONC/ 930021-002
JKL RC1GA RECPT, GEAR CONTROL AMP 2067052
CLAMP AMP 206966-1
JKL RC17A RECPT, ELECTRIC GEAR MOONEY 9j0021-002
JK- RC18A RECPT, DIMMER, 16 PIN AMP 2060363
CLAMP AMP 206070-1
JKL RC18B RECPT, PNL iT dlM#i, 14 PIN’ AMP 206044-1
CLAMP AMP 206070-1
JKL RC1SA RECPT, AIS SWITCH #2, 4´• Pll\j AMP 206153-1
CLAMP AMP 206062-1
JKL RC20A RECPT, TAILCON’E, lij PIN AMP 2060383
CLAMP AMP 206070-1
JK- RC21A RECPT, TAILCON’E, 16 PII;J AMP 206036-3
CLAMP AMP 206062-‘1
JK- RC22A RECPT, O/H REAK, 4’PIN AMP 206153-1
CLAMP AMP 206062-1
JK- RC23A RECPT, GRND #i, 16blN AMP 2060363
CLAMP AMP 206070-1
JK- RC24A RECPT, GRND #i, 16’PIN AMP 206036-3
CLAMP AMP 206070-1
JKL RC26A RECPT, COMPASS LT HARNESS, AMP 206153-1
CLAMP AMP 206062-1
JK- RC27A RECPT, FLT PNL #2,4 PIN AMP 206153-1
CLAMP AMP 206062-1
JKL RC27B RECPT, FLT PNLkt2, iO PiN MOONC/ 930021-502
JK- RC28A RECPT, AVIONICS POWER, 20 PIN MOONEY 930021-502
JK- RC29A RECPT, DIMIGRND, 20 PIN MOONEY 930021-502

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56
MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTINANCE MANUAL
28 VOLT S/N 25-1000 THRU 25-1224
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

JK- RC30A RECPT, DIM/GRND, 4 PIN AMP 206153-1

CLAMP AMP 206062-1
JK- RC31A RECPT, STsY VAC, 8’PIN~ AMP 205841-2
CLAMP AMP 206062-1
JK- RC31B RECPT, STBY VAC, 8~PIN AMP 205841-2
CLAMP AMP 206062-1
JKL RC32A RECPT, GEAK RELA\j, 4 PIN AMP 206153-1
CLAMP AMP 206062-1
JK RC33A RECPT, C/B PNL #2, 9 Pll\j AMP 206705-2
CLAMP AMP 206966-1
JKL RC34B RECPT, GRND sUSS,1G blN AMP 206036-3
CLAMP AMP 2069661
JK- RC35A RECPT, FLT PNL #3, 4 PIN AMP 206153-1
CLAMP AMP 206062-1
JK- RC36A RECPT, CONSOLE #i, 8 PIN AMP 205841-2
CLAMP AMP 206062-1
JK- RC37A RECPT, LT.SI’DE PNL: 8 PiN AMP 205841-2
CLAMP AMP 206062-1
JK- RC38A RECPT, FLA\j RELAY, 8 PiN AMP 205841-2
CLAMP AMP 206062-1
JK RC39A RECPT, FLAP MOTOR, 9 PIN AMP 206705-2
CLAMP AMP 2069681
-K- RC40A RECPT, MR6TTiE S’WITCH,‘4 PIN AMP 206153-1
CLAMP AMP 206062-1
JKL RCSOA RECPT, C/B PNL kc2 AMP 206151-2
CLAMP AMP 20613&1
JKL RCS1A RECPT, IGNITION SV\jITCI-I MOONEY 930021-506
JKL RC52A RECPT, ALT/STARTER CANNON MS3100K28-2P
(ALT) MS3100KE28-2P
JKL RC55A RECPT, EMPENNAGE, 9 PIN AMP 2067052
CLAMP 206966-1
JKL RC56A RECPT, GRND RiCPi. #4, 9 PIN AMP’ 2067052
CLAMP 2069661
JKL RC57A RECPT, GRND RECPT#SI 14 PIN MOONEY 930021-002
JKL RC58A RECPT, DIM RECPT.#2, 16 PIN AMP 206036-3
CLAMP AMP 206070-1
-L RC588 RECPT, PNL iT dlM fi2, 14 PII;J AMP 206044-1
CLAMP AMP 206070-1
JKL RC59A RECPT, GRND RECPT#GI26 PIN MOONEY 930021-506
JK- RC76A RECPT, 9 PIN AMP 206705-2
CLAMP AMP 2069661
JK- RC77A RECPT, 28 PI’N AMP 206152-1
CLAMP AMP 206070-1
-L RC150A RECPT, ENGI’NE HAdNESS, L’T CANNON-GERMANY CA121006-518
CLAMP CANNON-GERMANY 057-8557-000
FERRULE END RING CANNON-GERMANY 304-8553-000
RECPT, ENGINE, LTFMIALL(ALT) CANNON-GERMANY CAi21006~00
-L RC~SOA RECPT, ENGINE HARNESS,LT (ALT)PORSCHE 933.612.415.00
CLAMP PORSCHE 933.61 2.41 7.00
ENDBELL PORSCHE 933.612.425.00

NOTE: ALTERNATE HIGH TEMPERATURE COMPONENTS FOR ITEMS:

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SERVICE AND MAINTINANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 25-1000 THRU 251224
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

-L RC1S1A RECPT, ENGINE HARNESS, RT CANNON-GERMANY CA121006-518

CLAMP CANNON-GERMANY 057-8557-000
FERRULE END RING CANNON-GERMANY 304-8553-000
-L RC1S1A RECPT, ENGINE HARNESS, RT PORSCHE 933.612.415.00
CLAMP PORSCHE 933.61 2.41 7.00
ENDBELL PORSCHE 933.61 2.425.00

NOTE: ALTERNATE HIGH TEMPERATURE COMPONENTS FOR ITEMS:

-L RC152A RECPT, GR/STALL WARN
HARNESS, 4 PIN AMP 206153-1
CLAMP AMP 206062-1

JKL SB1O1A C/B, SPEED BRAKE KLIXON 7277-2-2

-L SPK1O1A SPEAKER, CABIN ARCHER 12-1703

JK- WA1OIA LIGHT, OVERVOLTAGE WESTERN’IND 501-61 K-11K-3RP

CLAMP WESTERN IND. W1-7049
JK- WA1 02A DIODE 1 N2483
JK- WA1 03A DIODE 1 N2483

-L WD1SOA FUSEHOLDER, STARTER

SOLENOID LITTEL 155020 or 155120
-WD150A FUSE, 1AMP LITTEL 313001

JKL WE1O1A C/B, GEAR WARN HORN KLIXON 7277-2-2

JKL WE102A LIGHT, GEAR DOWN SLOAN 855S-0-U

BULB GE 327

JK- WE103A SWITCH, THROTTLE MICRO V3-1

ACTUATOR MICRO JV-1
JK- WE104A HORN, GEAR WARNING MALLORY SC628P
JKL WE105A DIODE 1N2483
JKL WE1OGA DIODE 1M2483
-K- WE107A SWITCH, THROTTLE M’ICRO 1 SE1-T
ACTUATOR MICRO JE-17
-L WE1SOA SWITCH, MROTnE MICRO-SWITCH 1SEI-T
ACTUATOR MICRO-SWITCH JE-5
-L WE1S1A PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
-L WE?52A RECPT, 4 PIN AMP 206153-1
CLAMP AMP 206062-1

JKL WS1O1A C/B STALL WARN HORN KLIXON 7277-2-2

JK- WS102A HORN, STALL WARNING MALLORY SC628
JKL WS103A SWITCH, STALL WARN SAFE FLIGHT C46001
-L WS150A ALERT, GRISTALL WARNING IAl 950D-0309-000
-L WS1S1A PLUG,GR/STL WRN ALRT, 25 PIN DB25S
CLAMP 17T DB51212
LOCK RETAINER TTT DB1212-1
-L WS152A SPEAKER, GWSTALL WARN ARCHER 40-1333C
-L WS153A PLUG, INTER PHONE, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
-L WS154A PLUG, MATE N LOCK, 2 PIN AMP 1-48031&0
SOCKETS AMP 6061 9-1

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MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTINANCE MANUAL
28 VOLT S/N 25-1000 THRU 25-1224
OLDWILLWAYNE
VENDOR PART NO. NOTES
CODE DESCRIPTION

-L WSi55A RECPT, MATE N LOCK 2 PIN AMP 1-480319-0

PINS AMP 60620-1

WT1OIA C/B, ANNUNCIATOR KLIXON 7277-2-2

JK-
WT102A ANNUNCIATOR MOONEY 880025-521
J-
LAMPS CHICAGO MINIATURE CM7327
WT1 03A ANNUNCIATOR MOONEY 880025-523
-K-
LAMPS CHICAGO MINIATURE CM7327

WT1 04A PLUG, ANNUNCIATOR MOLD( 09-50-3151

JK-
SOCKETS MOLM 0&50-0106
-L WT150A GIB, ANNUNCIATOR, LT KLIXON 7277-2-1
KLIXON 7277-2-1
-L VVT151A C/B, ANNUNCIATOR, RT
Wr153A ANNUNCIATOR iAl 950D0308-000
-L
LAMPS CHICAGO MINANRE CM7327
WT154A PLUG, ANNUNCIATOR TTT DB25S
-L
CLAMP DB5i 212-1
LOCK RETAINER ITT DB51221-1

WV?O1A C/B, VACUUM WARNING KLIXON 7277-2-2

JK-
JK- WV102A SWITCH, VACUUM WARNING MOONEY 880012-501
WV103A RECPT, VAC WARN, 4 PIN AMP 206153-1
JK-
CLAMP AMP 206062-1
JK- WV104A PLUG, VAC WARN, 4 PIN AMP 206060-1
CLAMP AMP 206062-1

WW1O1A SWITCH, RAM AIR MICRO V3-1

J-
ACTUATOR MICRO JV-5

-K- WW102A SWITCH, ALTERNATE AIR CHERRY E51-508

-L WW1SOA SWITCH, ALTERNATE AIR CHERRY E51-508

NOTES
if not supplied
1. Use 1 ea. M835334-21 or MS2898 (Alan Bradley) internal tooth lockwasher with each light
by Sloan.
2. Ma>dmum circuit breaker rating is shown, amperage of installed circuit breaker is determined by particular
unit installed.
3. Boss bar may be shortened as required by circuit breaker installation.
4. Altemate for V3-1 switch w/ JV-5 actuator is V3L-3 assembly.
5. Varies with AutoPilot System installed.

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SERVICE AND MAINTINANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 25-1000 THRU 25-1224
OLDWILLWAYNE

RESERVED

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MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
28 VOLT S/N 25-1225 THRU 25-1999
OLDWILLWAYNE
91-2093
ELECTRICAL SYSTEM HARDWARE CHART 28 VOLT SYSTEMS
S/N’s 25-1225 THRU 25-1999 MOONEY DRAWING NO. 800263 (E7)

ACTUAL USAGE DETERMINED BY MASTER SCHEMATICS

CODE DESCRIPTION VENDOR PART NO. NOTES

--==,,_--==--====---==--=--

JK- CB1OIA C/B, DEFROSTERBLOWER KLIXON 7277-2-5

JK- CB102A SWITCH, BLOWERMOTOR CHERRY E51-50B
JK- CB1 03A MOTOR, BLOWER MOONEY 64031 7-501
JK- CBI 03B MOTOR, BLOWER MOONEY 64031 7-503
JK- CB104A PLUG, 2 PIN AMP 1-48031&0
SOCKET AMP 6061 9-1
JK- CB1 05A RECEPTACLE, 2 PIN AMP 1-4803190
PIN AMP 60620-1
JK- CC1OIA C/B, COV;h FLAP’ KLIXON 7277-2-5
JK- CC102A SWITCH, COWL FLAP MICRO 12TW1-1
JK- CC103A ACTUATOR, COWL FLAP MOONE/ 880050-501
JK- CC103B ACTUATOR, COWL FLAY MOONEY 880050-505
JK- CC104A SWITCH, OPEN LIMIT MICRO lSM-T
ACTUATOR MICRO JE-5
JK- CC1OSA SWITCH, CLOSED LIMIT MICRO 1SEI-T
ACTUATOR MICRO JE-5
JK- CC1OGA PLUG, 9 PIN AMP 206708-1
CLAMP AMP 206966-1
JK- CC107A RECEPTACLE, 9 PIN AMP 206705-2
CLAMP AMP 206966-1
JK- CC1 08A VARISTOR GE V47ZA05
JK- CF1O~A C/B, FLAP ACTUATOR KLIXON 7277-2-5
JK- CFI03A SWITCH, UP LIMIT MICRO V3-1
ACTUATOR MICRO JV-5
JK- CF104A SWITCH, DOWN LIMIT MICRO V3-~
ACTUATOR MICRO JV-5
JK- CF1 05A ACTUATOR, FLAP MOONEY 7501 05-501
JK- CF1 08A SWITCH,FLAP C-H 8906K31 49
JK- CV1OIA C/B, STAND-BY VACUUM MOONEY 930023-233
JK- CV102A CURRENTMONITOR, STD-BYVAC MOONEY 800221-505
JK- CV103A PLUG, 9 PIN AMP 206708-1
CLAMP AMP 206966-1
JK- CV104A PLUG, 2 PIN AMP 1-480318-0
SOCKET AMP 6061 9-1
JK- CV1OSA RECEPTACLE, 2 PIN AMP 1-480319-0
PIN AMP 60620-1
JK- CV1OGA PUMP, VACUUM AEROSAFE 82090A
JK- DA1OIA SHUNT, LOAD EMPRO MLA-70A-~ OOMV
JK- DA102A FUSEHOLDER McGRAW EDISON FHN42W
JK- DAI 03A FUSEHOLDER McGRAWEDISON FMO1-5A
JK- DB?O1A C/B, TURN COORDINATOR KLIXON 7277-2-2
JK- DB102A TURN COORDINATOR UNTTED INSTR. 9013 CODE N.5
TURN COORDINATOR (ALT) ASTRONAUTICS 303990-028MSC
TURN COORDINATOR (ALT) ELECTROGYRO 1394T100-32
TURN COORDINATOR i,ALTj UI. 9114 CODE N21

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SERVICE AND MAINTENANCE MANUAL M20K MOONC/ AIRCRAFT CORPORATION
28 VOLT S/N 25-1225 THRU 251999
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

JK- DB103A PLUG MS3106A-1 0SL-3S

CABLE CLAMP MS3507-4A
(ALT) MS3507-4B

JK- DC1OIA PROBE, CHT, (CYL. #3) MS24482-1 1

(ALT) AN5546-1 1

JK- DD1O1A C/B, EGT/OAT KLU(ON 7277-2-2

J- DD102A GAUGE, EGTIOAT MOONEY 880001-507
J- DD?02B GAUGE (4 PROBE) MOONEY 880001-509
J- DD103A PLUG, 8 PIN AMP 20583&1
CLAMP AMP 206062-1
JK- DD1 04A PROBE, OAi MOONEY 880004-501
JK- DD~ 05A PLUG, 2 PIN AMP 1-48031&0
SOCKET AMP 60619-1
JK- DD1OGA RECEPTACLE, 2 PIN AMP 1-480319-0
PIN AMP 60620-1
JK- DF1OIA TRANSMITTER, LT IN/ED, FUEL MOONEY 61 0242-003
JK- DF102A TRANSMITTER, LT OUT/ED, FUEL MOONEY 610243-003
JK- DF1 03A TRANSMITTER, RT IN/ED, FUEL MOONEY 61 0242-003
JK- DF104A TRANSMITTER, RTOUT/BD,FUEL MOONEY 610243-001
JK- DG1OIA C/B, INSTR. MODULE #1 KLD(ON 7277-2-1
J- DG103A MODULE, INSTR. MOONEY 880059-507
JK- DG104A PLUG, 28 PIN AMP 2058383
CLAMP AMP 206070-1
-K- DG105A MODULE, INSTRUMENT MOONC/ 880059509
J- DH1O1A PROBE, OIL TEMP MOONEY 880061-501
(ALT) LEWIS ENGRG 56B3A9
-K- DH1OIA PROBE, OIL TEMP MS28034-1
-K- DHI02A PLUG, 2 PIN MS3108A-~ 2S-3S
CLAMP MS3057-4A
JK- DJ1O1A TRANSDUCER, OIL PRESS D’RUCK PDCR821-0662-100
(ALT) KULITE APT-1 54-1 000-1 00PSIG
JK- DJ? 02A PLUG, 4 blN AMP 206060-1
CLAMP AMP 206062-1
JK- DJ103A RECEPTACLE, 4 PIN AMP 206153´•1
CLAMP AMP 206062-1
JK- DK1OIA TRANSDUCER, FUEL PRESS DRUCK PDCR821-0662-30
(ALT) APT-1 53-1 000-30PSIG
JK- DK102A PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
JK- DK103A RECEPTACLE, 4 PIN AMP 206153-1
CLAMP AMP 206062-1

J- DL1O1A TACHOMETER MOONEY 880038515

(ALT) B&D 0520-003
-K- DL?OIA TACHOMETER MOONEY 880039517
(ALT) B&D 0520-006
JK- DLI02A PLUG, 5 PIN MS3106A-? 4S-5S
CLAMP MS3057-6AIB
J- DL103A SENSOR, TACH B& d 0400-004
-K- DL1 03A SENSOR, TACH B&D 0402-1 02
(ALT) B&D 0402-1 04
JK- DL1 04A PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
JK- DL1OSA RECEPTACLE, 4 PIN AMP 206153-1
CLAMP AMP 206062-1

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MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
28 VOLT S/N 251225 THRU 25-1999
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

J- DM1O1A HOUR METER MOONEY 880035507

-K- DM1OIA HOUR METER MOONEY 880035505

JK- DM102A RECEPTACLE, 4 PIN AMP 206153-1

CLAMP AMP 206062-1

JK- DM103A PLUG, 4 PIN AMP 206060-1

CLAMP AMP 206062-1
J- DM104A FUSEHOLDER LIT~EL 155020
(ALT) LITTEL 155120

FUSE (5A-3AG-SLO-BLO) LITTEL 31 3005

JK- DP1O1A C/B, PITOT HEAT MOONEY 930023-205
JK- DP1 02A PITOT, HEATED AEROINSTR PH502-24
(ALT) AN5812-i
JK- DP103A PLUG AN31 i 5-1
SOCKET AN3116-1
JK- DP104A PLUG, 2 PIN AMP i -480318-0
SOCKET AMP 6061 91
JK- DP105A RECEPTACLE, 2 PIN AMP i -4803190
PIN AMP 6~620-1
-K- DR1OIA C/B, TIT KLIXON 7277-2-2

-K- DR1 02A TIT INDICATOR MOONEY 880051-501

-K- DR1028 TIT/EGT INDICATOR (6 PROBE) MOONEY 880051-503
-K- DR103A PLUG, 8 PIN AMP 20583&1
CLAMP AMP 206062-1
-K- DR1 038 PLUG, 28’ PIN AMP 205839503
CLAMP AMP 206070-1
-K- DR1 04A PROBE, TIT MOONEY 880055501
JK- DT1OIA PROBE, EGT, (CYL #i) MOONEY 880005-503
(ALT) MOONEY 880005501
J- DT1O1A (ALT) MOONEY 660110-000
JK- DT102A PROBE, EGT (CYL #2) MOONEY 880005503
(ALT) MOONEY 880005501
J- DT102A (ALT) MOONEY 660110-000
JK- DT103A PROBE, EGT (CYL #3) MOONEY 880005503
(ALT) MOONEY 880005-501
J- DT103A (AL~T) MOONEY 660110-000
JK- DT104A PROBE, EGT (CYL #4) MOONEY 880005503
(ALT) MOONEY 880005501
J- DT104A (ACn MOONEY 660110-000
J- DT1OSA EGTINDICATOR MOONEY 660109-003
LEAD WIRE) ALCOR 01-00578
-K- DT1OIA PROBE, EGT (CYL #1) MOONEY 880005-503
MOONEY 880005-501
-K- DT102A EGT.(CYL#2j MOONC/ 880005-503
(ALT) MOONEY 880005-501
-K- DT103A PROBE, EGT ten #3) MOONEY 880005-503
(ALT) MOONEY 880005-501
-K- DT104A PROBE, EGT (CYL #4) MOONEY 880005-503
(ALT) MOONEY 880005-501
-K- DT105A PROBE, EGT (CYL #5) MOONEY 880005-503
(ALT) MOONEY 880005501
-K- DT1OGA PROBE, EGT (CYL #6) MOONEY 880005-503
(ALT) MOONEY 880005-501
JK- DV1OIA C/B, FUEL FLOW KLU(ON 7277-2-1

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63
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 25-1225 THRU 25-1999
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

JK- DV102A INDICATOR, FUEL FLOW MOONEY 880034-501

JK- DV1 02A (ALT) MOONEY 880034-503
(ALT) MOONN 880034-505
(ALT) INdlCAjod, F/F (G~L) SHADIN 912021

(ALT) (LBS) SHADIN 912023

JK- DV1 028 INDICATOR, F/F (OPT) (GAL) SHADIN 912041 4

SHADIN 912043 4
(ALT) (LBS)
SHADIN 912047 4
(ALT) (LITER)
(ALT) (GAL) SHADIN 912081 5
(ALT) (LBS) SHADIN 912083 5
(ALT) (LITER) SHADIN 912087 5
JK- DV103A PLUG, 9 PIN TTT CANNON DE-SS 2
CLAMP ITT CANNON DE-24657 2
LATCH ASSY (2 ea) TTT CANNON DE-51224-1 2
JK- DV103B PLUG, 9 PIN TTT CANNON DE-SS 3
CLAMP TTTCANNON DE-24657 3
LATCH ASSY(2 ea) ITT CANNON D-110278 3
JK- DV104A TRANSDUCER, FUEL FLOW MOONEY 880030-501
(ALT) MOONEY 880030-503
JK- DV1 048 TRANSDUCER, F’UEL’FLOW FLOSCAN 6805018
JK- DV105A PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
JK- DV1 06A RECEPTACLE, 4 PIN AMP 206153-1
CLAMP AMP 206062-1
JK- DV107A SWITCH, FUEL FLOW C&K 7101K
JK- DV108A PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
JK- DVi 09A RECEPTACLE, 4 PIN AMP 206153-1
CLAMP AMP 206062-1
JK- DWIOIA VERTICAL SPEED INDICATOR U.I. 7000 CODE C.83
JK- EGiOiA C/B, GEAR RELAYS KLIXON 7277-2-2
JK- EG1 02A SWITCH, GEAR UP/DOWN C-H 8906)<2875
JK- EG103A SWITCH, GEAR OVERRIDE C-H SBi DDX492-2
RING, LOCKING C-H 29-761
WASHER, LOCK C-H i 6886
NUT, HU( (2 ea) C-H 15-966-6
LAMP (28V) GE 334
LAMP(14V) GE 336
SWITCH (ALT) NKK CORP DBL2141-3BL
BUTTON NKKCORP Ai406
LOCKING RING NKKCORP AT406
LOCK WASHER NKKCORP AT508
NUT, HD( (2 EA) NKK CORP AT503
LAMP (28V) NKK CORP AT604-28
JK- EG1 04A SWTTCH, AIRSPEED, GEAR’SAF~LTY MOONC/ 88001 3-507
JK- EG1 05A C/B, GEAR ACTUATOR KLIXON 7277-2-7.5
JK- EG1OGA SWITCH, GEAR UP LIMIT MICRO DT-2R-A7
ACTUATOR MICRO MCD-2711
JK- EG107A SWITCH, GEAR DOWN LIMIT MICRO 1CHii6-6
JK- EG1078 SWITCH, GEAR DOWN LIMIT(ALT) SAINT ML1116
JK- EG1 08A PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
JK- EG1OSA RECEPTACLE, 4 PIN AMP 206153-1
CLAMP AMP 206062-1

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 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 251225 THRU 25-1999
OLDWILLWAYNE
VENDOR PART NO. NOTES
CODE DESCRIPTION

C-H 6041H220
JK- EG11OA RELAY, GEAR UP
11\12483
JK- EG111A DIODE
C-H 6041H220
JK- EG112A RELAY, GEAR DOWN
11\12483
JK- EG113A DIODE
MOONEY 560256503
JK- EG114A ACTUATOR, GEAR
MOONC/ 880037-507
(ALT)
ARTU( ELTI 10-4
JK- ELT1OIA TRANSMITTER, ELT
D&M DM-ELT-8
JK- ELT1 01B TRANSMITTER, ELT
MOLM 03-06-21 22
JK- ELT102A RECEPTACLE, 12 PIN
MOLD( 02-062103
PIN
ARTU( 110-416
JK- ELT1 03A SWITCH, REMOTE
C&K 71 01K
JK- ELT1 038 SWITCH, REMOTE
MOLD( 03-06-2092
JK- ELT104A PLUG, 9 PIN
MOLM 02-06-1103
SOCKET
AMP 20583&1
JK- ELT1OSA PLUG, 8 PIN
AMP 206062-1
CLAMP
AMP 205841-2
JK- ELT1OGA RECEPTACLE, 8 PIN
AMP 206062-1
CLAMP
AMP 20583&1
JK- ELT107A PLUG, 8 PIN
AMP 206062-1
CLAMP
AMP 205841-2
JK- ELT108A RECEPTACLE, 8 PIN
AMP 206062-1
CLAMP
SWITCHCRAFT C´•l~
JK- FON1O1A PHONE JACK
SWITCHCRAFT S-1028
WASHERS
SWTTCHCRAFT S-1029
WASHERS (ALT)
BENDIX/SCINTILLA 10-357210-9
JK- JM1OIA SWITCH, MAGNETO
BENDIXISCINTILLA 10-1 87-468
PLACARD
MAGNETO BU~DIXISCINTILLA P4LN2021
J- JM102A
SLICK 6224
-K- JM1 02A MAGNETO, LEFT
BENDIXISCINTILLA 646979-1
-K- JM102B MAGNETO, LEFT
BENDIXISCINTIUA 10-382698
CONNECTOR
SL(CK 6224
-K- JM1 03A MAGNETO, RIGHT
BENDIX/SCINTILLA 6469741
-K- JM1 038 MAGNETO, RIGHT
BENDIX/SCINTILLA 10-382698
CONNECTOR
MOONEY 930023-243
JK- LB1OIA C/B, BEACON, FLASHING
WHELEN WRLM-24
JK- LB1 02A LIGHT, BEACON
WHELEN WRM-65
ADAPTER
90033-20
JK- LB1 02A
WHELEN 90033-19
JK- LB1 028 LIGHT,ANTI-COLLISION(RED)(ALT)
AMP 1-380303-0
JK- LB103A PLUG, 3 PIN
AMP 6061 91
SOCKET
AMp 1-480305-0
JK- LB104A RECEPTACLE, 3 PIN
AMP 60620-1
PIN
LIT~EL 155020
JK- LC1OIA FUSEHOLDER
LTT~EL 155120
(ALT)
31 3005
FUSE, SA-3Ai;Sio-BLO LII~EL
CARLING TILC64-1S-WH-FN
JK- LC1 02A SWITCH, CABIN LIGHT, FRONT
DALE RH-~0-20 OHM
JK- LC103A RESISTOR, DIM. (20 OHM 10W)
H H SMITH 1930
JK- LC104A LAMP HOLDER
GE 1818
LAMP
H H SMITH 1930
JK- LC10SA LAMP HOLDER
GE 1818
LAMP
H H SMITH 1930
JK- LC1OGA LAMP HOLDER
GE 1818
LAMP

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SERVICE AND MAINTENANCE MANUAL M20K MOONCI AIRCRAFT CORPORATION
28 VOLT S/N 251225 THRU 25-1999
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

JK- LC1 07A LAMPHOLDER HHSMITH 1930

LAMP GE 1818

JK- LC? 08A SWITCH, CABIN LIGHT, REAR CARLING TILC64-1S-WH-FN

JK- LCIOSA RESISTOR, DIM. (20 OHM iOW) DALE RH-i 0-20 OHM
JK- LC11OA LAMP HOLDER H H SMITH 1930
LAMP GE 1818

JK- LC111A LAMPHOLDER HHSMITH 1930

LAMP GE 1818
JK- LCI 12A LAMPHOLDER HHSMITH i 930
LAMP GE 1818
JK- LC1 13A LAMPHOLDER HHSMITH i 930
LAMP GE 1818
JK- LC117A PLUG, 9 blN ITT CANNON DE-SS
CLAMP DE24657
LATCH DE5122Pi
JK- LC118A MODULE, AUTO OFF LIGHT MOONEY 80026&501
JK- LC118B RECEPTACLE, 9 PIN DE-SP
C14MP DE24657
RING, LOCKING 206514-1
JK- LC11SA DIODE 1 N2483
1N5060
dE 3720-GE
JK- LC1 20A DIODE 1 N2483
(ALT) 1N5~0
(ALT) dE 3720-GE
JK- LC121A PLUG, 4 f~lN AMP 206060-1
CLAMP AMP 206062-1
JK- LC?22A RECEPTACLE, 4 PIN AMP 206153-1
CLAMP AMP 206062-1
JK- LC123A SWITCH, CABIN DOOR NEWARK 89F5544
JK- LC124A RECEPTACLE, 2 PIN AMP 1-4803190
PIN AMP 60620-1
JK- LC125A PLUG, 2 PIN AMP 1-480318-0
SOCKET AMP 6061 91
JK- LC126A SWITCH, BAGGAGE DOOR NEWARK 89F5544
JK- LC127 RECEPTACLE, 2 PIN AMP 1-4803190
PIN AMP 60620-1
JK- LC128A PLUG, 2 PIN AMP i-480318-0
SOCKET AMP 6061 81

JK- LL1OIA C/B, LANDING LIGHT KLIXON 7277-2-25

JK- LL1OIA C/B, LANDING LIGHT MOONEY 930023-215
JK- LL102A SWITCH, LANDING LIGHT MOONEY 880052-521
JK- LL1 03A LIGHT, LANDING, RIGHT GE 4596
JK- LL1 04A LIGHT, LANDING, LEFT GE 4596
JK- LL1 05A LIGHT, LANDING (COWL) GE 4553

JK- LN1OIA C/B, NAV LIGHT MOONEY 930023-201

JK- LN102A LIGHT ASSY, NAV, TAIL (LT V\jlNGj MOONEY 800051-501
BULB V\MELEN 34-022-8030-85
JK- LN103A LIGHT ASSY, NAV, TAIL (kT WING) MOONEY 800051-501
BULB WHELEN 34-022-8030-85
JK- LN104A PLUG, 9 PIN (RT WINi;) AMP 206708-1
CLAMP AMP 206062-1

JK- LN105A RECEPTACLE, 9 PIN (RT WING) AMP 206705-1

CLAMP AMP 206062-1

91-20-03
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MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
28 VOLT SM 25-1225 THRU 25-1999
OLDWILLWAYNE
VENDOR PART NO. NOTES
CODE DESCRIPTION

AMP 20670&1
JK- LN1OGA PLUG, 9 PIN (LT WING)
CLAMP AMP 206062-1

LN107A RECEPTACLE, 9 PIN (LT WING) AMP 206705-1

JK-
CLAMP AMP 206062-1
KLIXON 7277-2-5
JK- LP1OIA C/B, GLARESHIELD LIGHTS
KLIXON 7277-2-5
JK- LP102A C/B, PANEL LIGHTS
DIMMER CONTROL BOX MOONEY 800049-501
JK- LP103A
LP1 04A PLUG, 9 PIN AMP 206708-1
JK-
CLAMP AMP 206966-1
DLALIGHT 270-1 930-0171-702
JK- LP1 05A LIGHT, CONSOLE
GE 327
LAMP (28V)
GE 385
LAMP (ALT)
LIGHT, CONSOLE DIALIGHT 270-1930-0171-702
JK- LP1 06A
GE 327
LAMP (28V)
GE 385
LAMP (ALT)
PLUG, 4 PIN AMP 206060-1
JK- LP107A
CLAMP AMP 206062-1
LP108A RECEPTACLE, 4 PIN AMP 206153-1
JK-
CLAMP AMP 206062-1
LP1OSA RECEPTACLE, COMPASS LIGHT DEANS DEA90020MALEHALF
JK-
JK- LP11OA PLUG, COMPASS LIGHT DEANS DEA90020FEMALEHALF
JK- LP111A LAMP, COMPASS LIGHT (28Vj GE 327
(ALT) GE 327 (AVIATION RED)
JK- LP112A LAMPS, GUS’HLL’ LIGHTS (14a) GE 327
SLOAN 855S-0-U 6
JK- LP113A LIGHT, OXYGEN
GE 327
LAMP (28V) 6
LP114A LIGHT, OXYGEN SLOAN 855S-0-U
JK-
GE 327
LAMP (28V)
AMP 1-48031&0
JK- LP11SA PLUG, 2 PIN
SOCKET AMP 60619-1
LP11GA RECEPTACLE, 2 PIN AMP 1-480319-0
JK-
PIN AMP 60620-1
LP117A PLUG, 2 PIN AMP 1-48031&0
JK-
SOCKET AMP 60619-1
LP118A RECEPTACLE, 2 PIN AMP 1-4803180
JK-
PIN AMP 60620-1
LP11SA PLUG, 2 PIN AMP 1-48031&0
JK-
SOCKET AMP 6061 9-1
LP120A RECEPTACLE, 2 PIN AMP 1-4803190
JK-
PIN AMP 60620-1
LP121A POST LIGHT WHELEN A350CN1W-BK-SH14
JK-
LAMP (14V) GE 330
LP122A POST LIGHT WHELEN A350CN1W-BK-SH14
JK-
LAMP (14V) GE 330
JK- LP123A LIGHTING TRAY iRPh;l) B&D 0221-128
LP124A LIGHTING TRAY (M/P) UI BA2&24-BW3
JK-
LP125A LIGHTING TRAP (TTT/EGT) B&D 0221-128
JK-
LP126A PLUG, 20 PIN MOONEY 930022-501
JK-
LP127A RECEPTACLE, 20 PIN MOONEY 930021-502
JK-
JK- LP130A RHEOSTAT, MAP LIGHT (500 OHM) NEWARK 09F981
KNOB NEWARK 57F2368

LP1 33A RHEOSTAT, MAP LIGHT (500 OHM) NEWARK 09F981

JK-
KNOB NEWARK 57F2368
SLOAN 855S-0-U 6
JK- LP134A MAP LIGHT
GE 327
JK- LP1 34A LAMP (28V)
GE 330
LAMP (14V)

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67
SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 25-1225 THRU 25-1999
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

JK- LP135A MAP LIGHT SLOAN 855S-0-U 6

LAMP (28V) GE 327
LAMP (14V) GE 330
JK- LP1 36A POST LIGHT WHELEN A350CNiW-BK-SH28
LAMP (28V) GE 327

JK- LP137A POST LIGHT WHELEN A350CNi W-BK-SH14

LAMP (14V) GE 330
JK- LR1OIA C/B, RECOGNITION LIGHTS MOONEY 930023-231
JK- LR1 02A LIGHT, RECOGNITION, LW MOONEY 880049-501
JK- LR103A PLUG, 2 PIN AMP 1-4803180
SOCKET AMP 60619-1
JK- LR104A RESISTOR DALE RH50-7.5 OHM
JK- LR105A RECEPTACLE, 2 PIN AMP 1-480319-0
PIN AMP 60620-1
JK- LR1OGA PLUG, 2 PIN AMP 1-480318-0
SOCKET AMP 6061 9-1
JK- LR1 07A LIGHT, RECOGNITION, RW MOONEY 880049-501
JK- LR108A PLUG, 2 PIN AMP 1-480318-0
SOCKET AMP 60619-1
JK- LR1OSA RESISTOR DALE RH50-7.5 OHM
JK- LR11OA RECEPTACLE, 2 PIN AMP 1-4803190
PIN AMP 60620-1
JK- LR111A PLUG, 2 PIN AMP 1-480318-0
SOCKET AMP 6061 81
JK- LS1OIA C/B, STROBE LIGHT MOONEY 930023-237
JK- LS102A POWER SUPPLY, LT WING WHELEN 01-0770329-00
JK- LS103A RECEPTACLE, POWER SUPPLY AMP 1-480305-0
PIN AMP ‘60620-1
JK- LS104A RECEPTACLE, POWER SUPPLY AMP 1-480305-0
PIN AMP 60620-~
JK- LS105A PLUG, STROBE ilGHiASSY AMP 1-480303-0
SOCKET AMP 60619-1
JK- LS1OGA STROBE/NAV LIGHT, LT\i\nNe WHELEN A650-PR-D-M-28
JK- LS? 07A POWER SUPPLY, LT WING WHELEN 01-0770329-00
JK- LS108A RECEPTACLE, POWER SUPPLY AMP 1-480305-0
PIN AMP 60620-1
JK- LS? 09A RECEPTACLE, POWER SUPPLY AMP 480305-0
PIN AMP 60620-1
JK- LS11OA PLUG, STROBE ilGHi ASSY AMP 1-480303-0
SOCKET AMP 60619-1
JK- LS111A STROBUNAV LIGHT, RT WING WHELEN A650-PR-D-M-28
JK- LS112A POWER SUPPLY, TAIL WHELEN 01-0770329-00
JK- LS?13A RECEPTACLE, POWER SUPPLY AMP 1-4803050
PIN AMP 60620-1
JK- LS11 4A RECEPTACLE, POWER SUPPLY AMP 1-480305-0
PIN AMP 60620-1
JK- LS1?5A PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
JK- LS11GA RECEPTACLE, 4 PIN AMP 206153-1
CLAMP AMP 206062-1

91-20-03
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 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
28 VOLT SM 25-1225 THRU 25-1999
OLDWILLWAYNE
VENDOR PART NO. NOTES
CODE DESCRIPTION

AMp 1-480303-0
JK- LS1 i 7A PLUG, STROBE LIGHT ASSY
SOCKET AMP 6061 9-1
JK- LS118A LIGHT ASSY,’TAli STROBE MOONfl 470013-501

RECEPTACLE, 3 PIN AMp 1-480305-0

JK- LS11SA
PIN AMP 60620-1
JK- LS120A RECEPTACLE, 3 i>lN AMP 1-480305-0
PIN AMP 60620-1
AMP 1-480305-0
JK- LS121A RECEPTACLE, 3 PIN
PIN AMP 60620-1

KLIXON 7277-2-25
JK- LT1 01A C/B, TAXI LIGHT
MOONC/ 880052-523
JK- LT1 02A SWITCH, TAXI LIGHT
GE 4596
JK- LT1 03A BULB, TAXI, WW(28V)
GE 4596
JK- LT1 04A BULB, TAXI, UW(28V)
RECEPTACLE, AUX POWER AN2552-3A
JK- MAIOIA
RELAY, AUX POWER CH 6041H202
JK- MA102A
C-H 6041 H202A
(ALT)
DIODE SARKES-TARZIAN 1 0H3P
JK- MA1 03A
DIODE 1N2483
JK- MA1 04A
1N5060
(ALT)
(ALT) de 3720-GE
MOONEY 930023-213
JK- MB1O1A C/B, AVIONICS MASTER
KISSLING 26.64.01
JK- MB102A RELAY, AVIONICS MASTER
DIODE 1 N2483
JK- MB1 03A
1N5060
(ALT)
(ALT) dE 3720-GE
AVIONICS BUS BAR #1 MOONEY 913127-67
JK- MB104A
AVIONICS BUS BAR #2 MOONEY 913127-67
JK- MB1OSA
AVIONICS BUS BAR #3 MOONEY 913127-87
JK- MB1OGA
KLIXON 7277-2-7.5 7
JK- MB1 07A C/B, INTERCOM 7
KLIXON 7277-2-10
JK- MB1 08A C/B, COM 1 7
KLIXON 7277-2-7.5
JK- MB1 09A C/B, NAV 1 7
KLIXON 7277-2-7.5
JK- MB11OA C/B, AUDIO 7
KLUXON 7277-2-7.5
JK- MB111A C/B, PHONE 7
KLD(ON 727/-2-7.5
JK- MB?12A C/B, ADF 7
COM 2 KLIXON 7277-2-10
JK- MB113A C/B, 7
NAV 2 KLUXON 7277-2-7.5
JK- MB11 4A C/B, 7
TRANSPONDER KLDXON 7277-2-7.5
JK- MB11SA C/B, 7
ENCODER KLIXON 7277-2-7.5
JK- MB1IGA C/B, 7
STERO KLDXON 7277-2-7.5
JK- MB117A C/B, 7
DME KLUXON 7277-2-7.5
JK- MB118A C/B, 7
R~NAV KLIXON 7277-2-7.5
JK- MB11SA C/B,
KLD(ON 7277-2-7.5 7
JK- MB120A C/B, STORMSCOPE
KLIXON 7277-2-7.5 7
JK- MB121A C/B, LORAN
KLDXON 7277-2-7.5 7
JK- MB122A C/B, RMI
KLDXON 7277-2-1 0- 7
JK- MB123A C/B, AUTOPILOT/TRIM
KLIXON 7277-2-7.5 7
JK- MB124A GIB, AIP ALERT
KLIXON 7277-2-7.5 7
JK- MB125A C/B, INVERTER
KLD<ON 7277-2-2 7
JK- MB126A C/B, ART. HORIZ.
KLU(ON 7277-2-2 7
JK- MB127A C/B, HSI
KLIXON 7277-2-7.5 7
JK- MB128A C/B, YAW DAMP.
KLD(ON 7277-2-7.5 7
JK- MB129A C/B, TELEPHONE
KLDXON 7277-2-7.5 7
JK- MB130A C/B, VME 7
KLU(ON 7277-2-7.5
JK- MB131A C/B, RADIO ALT.
CIGAR LIGHTER MOONEY 800336-503
JK- MC102A

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SERVICE AND MAINTENANCE MANUAL M20K MOONN AIRCRAFT CORPORATION
28 VOLT S/N 25-1225 THRU 25-1999
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

JK- MC1 02A (ALT) CASCO 208292

JK- ME1OIA CLOCK MID-CONT MD-88L
(OPT) MID-CONT. MD-88L (ET)
LIGHT TRAY MID-CONT. BA28-24-BW2
JK- MIC1OIA JACK, MICROPHONE SWITCHCRAFT C-i2B
WASHERS SWITCHCRAFT S-1028
WASHERS (ALT) SWITCHCRAFT S-l 029
JK- MIC1 02A SWITCH, MIC KEY, PILOT C-H SAIRV20
JK- MIC103A SWITCH, MIC KEY, GO-PILOT C-H SAIRV20

JK- MP1OIA C/B, PROP DE-ICE MOONEY 930023-223

JK- MP102A TIMER, PROP DE-ICE B.F. GOODRICH 3E1899-1
JK- MP103A MONITOR,CURRENT,PROP DE-ICE MOONEY 800221-505

JK- MP104A PLUG, 9 PIN AMP 206708-1

CLAMP AMP 2069681
JK- MP105A TERMINAL BLOCK McCAULEY C-40521
J-- NF1O?A C/B, BOOST PUMP MOONC/ 930023-211
J- NFI02A PUMP, FUEL BOOST WELDON 8163B
(ALT) WELDON A8163B
-K- NFI 02A PUMP, sbOST WELDON 100548
JK- NFI03A PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
JK- NF104A RECEPTACLE, 4 PIN AMP 206153-1
CLAMP AMP 206062-1
-K- NF1OSA C/B, HI BOOST PUMP MOONEY 930023-219
-K- NFI07A C/B, LO BOOST PUMP MOONEY 930023-217
-K- NF108A REGULATOR, FUEL PUMP ELECTRO-DELTA VR-536
-K- NF108B REGULATOR, FUEL PUMP AMER. PROD DGB-i
-K- NFIOSA RECEPTACLE, 4 PIN AMP 206153-1
CLAMP AMP 206062-1
-K- NF11OA PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
-K- NP1OIA FUSEHOLDER, PRIMER, DIFFUSER LTT~L i 55020
(ALT) LITTEL 155120
FUSE (10A SLO BLO) LTT~EL 313010
-K- NP1 02A SWITCH, PRIMER CARLING TIGKGBIF-WH-A
-K- NP1 03A PRIMER, DIFFUSER TCM 633862-2
-K- NP1 04A DIODE 1N2483
(ALT) 1N5060
(ALT) de 3720-GE
JK- PAI 01A C/B, ALTERNATdR, dT ETA 41-3-S34-LN2-041 800
JK- PA1 02A C/B, FIELD, RT. ALT KLIXON 7277-2-5
JK- PA1 03A SWITCH, ALT. FLD.(OPT) MOONEY 880052-525
-K- PA1 03B SWITCH, ALT. FLD. (STD) MOONEY 880052-503

JK- PA? 04A VOLTAGE REGULATOR MOONEY 880270-501

(ALT) AUXILEC VR-802
(ALT) AM PROD DGR-2
JK- PA1OSA RECEPTACLE, 9 PIN AMP 20670&1
CLAMP AMP 2069661
JK- PA1OGA PLUG, 9 PIN AMP 206705-2
CLAMP AMP 206966-1
J-- PAI07A ALTERNATOR (SjD)~ LYCOMING LV\i114367
(ALT) PRESTOLITE ALU6421-LS

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 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 25-1225 THRU 25-1999
OLDWILLWAYNE
VENDOR PART NO. NOTES
CODE DESCRIPTION

ALTERNATOR (STD) TCM 649280

-K- PA1 07A
TCM 649172
(ALT)
GEAR ASSY TCM 649123
FILTER MOONEY 88001 4-501
JK- PA1 08A
CAPACITOR MALLORY CGS302U-050R2C
JK- PA1 09A
MALLORY CGS292U-050R3C
(ALT)
C/B EIA 41-3-S34-LN2-041 800
-K- PA1 1 OA
C/B KLIXON 7277-2-5
-K- PA111A 10
VOLTAGE REGULATOR @UAL) ELECTRODELTA VR-802
-K- PA112A 10
(ALT)(DUAL) AM. PROD/PREC.FLT DGR-2
DU’ALALTfRNA;TOk MOONEY 800270-503 10
-K- PA112A REGUIJ\TOR,
RECEPTACLE, 9 PIN AMP 20670&1
-K- PA113A
CLAMP AMP 206966-1
AMP 206705-2
-K- PA114A PLUG, 9 PIN
CLAMP AMP 2069661

ALTERNATOR (OPT) TCM 649280

-K- PA?1SA
TCM 6491 72
(ALT)
GEAR ASSY TCM 649123
FILTER MOONN 880014-501
-K- PAI 16A
CAPACITOR MALLORY CGS302U-050R2C
-K- PA117A
MALLORY CGS292U-050R3C
(ALT)
JK- PA~18A SENSOR, CURRENT MICRO CSLAI GE
MICRO SS-371 26
ELEMENT. SENSOR
SENSOR, CURRENT MICRO CSLA1GE
-K- PA11SA
MICRO SS-371 26
ELEMENT, SENSOR
AMP 206705-2
JK- PA120A PLUG, 9 PIN
CLAMP AMP 206966-1
RECEPTACLE, 9 PIN AMP 20670&1
JK- PA121A
CLAMP AMP 206966-1
PA122A ADPTR, ANALOG, CUR. SENSOR MOONEY 810088-504
-K-
AMP 206037-1
JK- PA122A PLUG, 16 PIN
CLAMP AMP 206070-1
RECEPTACLE, 16 PIN AMP 206036-3
JK- PA123A
CLAMP AMP 206070-1
DIODE 1 N2483
JK- PA1 24A
1 N5060
(ALT)
(ALT) dE 3720-GE

BATTERY GILL G-243

JK- PB1OIA
C-H 6041 H202
JK- PBi 02A RELAY, BATTERY
C-H 6041 H202A
(ALT)
DIODE 1 N2483
JK- PB1 03A
1N5060
(ALT)
(ALT dE 3720-GE

SWITCH, MASTER MOONEY 880052-501

JK- PB1 04A
PBi 05A C/B, BATTERY ETA 41-3S34-U~2-041800
JK-
C/B ETA 41-3S34-LN2-40A
JK- PB1 06A
PB107A BUS BAR #1 MOONEY 913127-89
JK-
PB108A BUS BAR #2 MOONEY 913127-75
JK-
PB1OSA BUS BAR #3 MOONEY 913127-75
JK-
PB1 1 OA BUS BAR #4 MOONEY 913127-77
JK-
PB111A BUS BAR #5 MOONEY 913127-77
JK-
PB112A BUS BAR #6 MOONEY 913127-73
JK-
PBI13A BUS BAR #7 MOONEY 913127-81
JK-
PBi 4A BUS BAR #8 MOONEY 913127-77
JK-

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28 VOLT S/N 25-1225 THRU 25-1999
OLDWILLWAYNE
DESCRIPTION VENDOR PART NO. NOTES
CODE
========================--==---=I-=

JK- PB~1SA BUS BAR #9 MOONEY 913127-75

JK- PB11GA BUS BAR #10 MOONC/ 913127-83
JK- PB117A BUS BAR #11 MOONEY 913127-59

JK- PB120A GROUND/DIMMER BOX MOONEY 80022&501

J- PB121A PLUG, 3 PIN AMP 206037-2
CLAMP AMP 206070-1
J- PB122A RECEPTACLE, 3 PIN AMP 206207-1
CLAMP AMP 206070-1
JK- PL201A PLUG, 37 PIN AMP 206150-1

CLAMP AMP 2061 38-1

JK- PL203A PLUG, AMP 206037-1
CLAMP AMP 206070-1

JK- PL204A PLUG, 26 PIN MOONEY 930021-505

JK- PL205A PLUG, 28 PIN AMP 205839-3
CLAMP AMP 206070-1
JK- PL206A PLUG, 20 PIN MOONEY 930021-501

JK- PL207A PLUG, 20 PIN MOONEY 930021-501

JK- PL208A PLUG, 14 PIN MOONEY 930021-001
JK- PL209A PLUG, 9 PIN AMP 206708-1
CLAMP AMP 206966-1

JK- PL210A PLUG, 9 PIN AMP 206708-1

CLAMP AMP 206966-1
JK- PL211A PLUG, 34 PIN MOONEY 930021-507
JK- PL212A PLUG, 14 PIN MOONEY 930021-001
JK- PL216A PLUG, 16 PIN AMP 206037-1
CLAMP AMP 206070-1
JK- PL217A PLUG, 16 PIN AMP 206037-1
CLAMP AMP 206070-1
JK- PL218A PLUG, 16 PIN AMP 206037-1
CLAMP AMP 206070-1
JK- PL219A PLUG, 28 PIN AMP 205839-3
CLAMP AMP 206070-1
JK- PL220A PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
JK- PL221A PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
JK- PL222A PLUG, 9 PIN AMP 20670&1
CLAMP AMP 206966-2
JK- PL222B PLUG, 16 PIN AMP 206037-1
CLAMP AMP 206070-1
MAT/SCI M83723/86R2232N 8
JK- PL225A PLUG, 32 PIN
CLAMP MAT/SCI M85049/52-1-22N
SOCKET MAT/SCI 51 00-001-0012
SOCKET MAT/SCI 51 00-001-0020
MATISCI M83723/86R2232N 8
JK- PL226A PLUG, 32 PIN
CLAMP MAT/SCI M85049/52-1-22N
SOCKET MAT/SCI 5100-001-0012
SOCKET MAT/SCI 51 00-001-0020
MAT/SCI MS3106A-28-22S 8
JK- PL227A PLUG, 6 PIN
CLAMP MAT/SCI MS3057-1 6B
(ALT) MAT/SCI MS3057-1 6A
SOCKET MAT/SCI 51 00-001-0012
SOCKET MAT/SCI 51 00-001-0020
JK- PL228A PLUG, 20 PIN MOONEY 930021-501

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 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 25-1225 MRU 25-1999
OLDWILLWAYNE
VENDOR PART NO. NOTES
CODE DESCRIPTION

AMp 206037-1
JK- PL229A PLUG, 16 PIN
AMP 206070-1
CLAMP
MOONEY 930021-001
JK- PL230A PLUG, 14 PIN
AMP 206037-1
JK- PL231A PLUG, 16 PIN
AMP 206070-1
CLAMP
MOONEY 930021-001
JK- PL232A PLUG, 14 PIN
AMP 206060-1
JK- PL233A PLUG, 4 PIN
AMP 206062-1
CLAMP
KLIXON 7277-2-5
JK- PS1OIA C/B, STARTER SOLENOID
CH 6041H202
JK- PS1 02A SOLENOID, STARTER
CH 6041H202A
(ALT)
JK- PS1OBA DIODE
(ALT)
(ALT) dE 3720-GE
PRESTOLITE MH&4016
J- PS104A STARTER
LYCOMING LW-1 5572
(ALT)

TCM 646275
-K- PS1 04A STARTER
TCM 637847
(ALT) 7277-2-5
JK- RB1OIA C/B, RADIO BLOWER KLIXON
TRW 19A2790
JK- RB1 02A BLOWER, RADIO
BENDIX-KING KA0033-01
JK- RB1 028 BLOWER, RADIO
ARCHER 273-103
JK- RB1 03A FILTER, NOISE
SPRAGUE 5JX5104A
(ALT) 03-06-1023
RB104A PLUG, 2 PIN MOLM
JK-
MOLD( 02-06-1 i 03
SOCKET
AMP 206151-2
JK- RC201A RECEPTACLE, 37 PIN
AMP 206036-2
JK- RC203A RECEPTACLE, 3 PIN
AMP 206070-1
CLAMP
MOONEY 930021-506
JK- RC204A RECEPTACLE, 26 PIN
AMP 2061 52-1
JK- RC205A RECEPTACLE, 28 PIN
CLAMP AMP 206070-1
20 PIN MOONEY 930021-502
JK- RC206A RECEPTACLE,
20 PIN MOONC/ 930021-502
JK- RC207A RECEPTACLE,
14 PIN MOONEY 930021-002
JK- RC208A RECEPTACLE,
9 PIN AMP 206705-2
JK- RC209A RECEPTACLE,
AMP 2069661
CLAMP
AMP 2067052
JK- RC210A RECEPTACLE, 9 PIN
AMP 206966-1
CLAMP
MOONEY 930021-508
JK- RC211A RECEPTACLE, 34 PIN
MOONEY 930021-002
JK- RC212A RECEPTACLE, 14 PIN
AMP 2060461
JK- RC214A RECEPTACLE, 14 PIN
CLAMP AMP 206070-1
AMP 206044-1
JK- RC215A RECEPTACLE, 14 PIN
CLAMP AMP 206070-1
AMP 2061 53-1
JK- RC220A RECEPTACLE, 4 PIN
CLAMP AMP 206062-1
AMP 2061 53-1
JK- RC221A RECEPTACLE, 4 PIN
CLAMP AMP 206062-1
AMP 20670&1
JK- RC222A RECEPTACLE, 4 PIN
AMP 2069661
CLAMP
AMP 206037-1
JK- RC222B RECEPTACLE, 9 PIN
AMP 206070-1
CLAMP

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SERVICE AND MAINTENANCE MANUAL M20K MOONE/ AIRCRAFT CORPORATION
28 VOLT S/N 25-1225 THRU 251999
OLDWILLWAYNE
DESCRIPTION VENDOR PART NO. NOTES
CODE

JK- RC225A RECEPTACLE, 32 PIN MAT/SCI M83723/83K2232N

CLAMP MAT/SCI M85049/52-1-22N

PIN MAT/SCI 5000-054-0020

PIN MAT/SCI 5000-0560012
BOOT MAT/SCI MS3420-14
MAT/SCI MS3420-16
(ALT)
JK- RC226A RECEPTACLE, 3i PIN’ MAT/SCI M83723/83K2232N
CLAMP MAT/SCI M85049/52-1-22N
PIN MATISCI 5000-054-0020
PIN MAT/SCI 5000-054-0012
BOOT MAT/SCI MS3420-14
MAT/SCI MS3420-16
(ALT)
JK- RC227A RECEPTACLE, 6 PIN MS3100K-2&2P
(ALT) MS3100KE-28-2P
CLAMP MS3057-16B
MS3057-16A
(ALT)
JK- RC230A RECEPTACLE, 14 PIN MOONEY 930021-002

JK- RC231A ’RECEPTACLE, 16 PIN AMP 206036-1

CLAMP AMP 206070-1
JK- RC232A RECEPTACLE, 14 PIN MOONEY 930021-002
JK- RC233A RECEPTACLE, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
JK- RC277A RECEPTACLE, AUDIO AMP 2061 52-1
CLAMP AMP 206070-1

JK- SB1OIA C/B, SPEED BRAKE KLIXON 7277-2-3

JK- SB102A SWITCH, SPEED BRAKE PRECISE FLT 01265
JK- SB103A PLUG, 3 PIN AMP i -380303-0
SOCKET AMP 6061 9-1
JK- SB104A RECEPTACLE, 3 PIN AMP 1-380305-0
PIN AMP 60620-1
JK- SB1OSA RELAY, SPEED BkAKE PRECISE FLT 01384
JK- SB1 06A DIODE 1 N2483
1N5060
(ALT)
(ALT) dE 3720-GE
JK- SB107A PLUG, 4 i)lN AMP 206060-1
(ALT) AMP 206062-1
JK- SB108A RECEPTACLE, 4 PIN AMP 206153-1
CLAMP AMP 206062-1

JK- SB1OSA PLUG, 8 PIN AMPM 20583&1

CLAMP AMP 206062-1
JK- SB11OA RECEPTACLE, 8 PIN AMP 205841-2
CLAMP AMP 206062-1
JK- SB111A MOTOR, LEFT PRECISE FLT 01532
JK- SB112A SWITCH, DEPLOY LIMIT PRECISE FLT 01505
JK- SB113A SWITCH, RETRACT LIMIT PRECISE FLT 01505
JK- SB1?4A SOLENOID, CLUTCH PRECISE FLT 01678
JK- SB11SA PLUG, 8 PIN AMP 205838-1
CLAMP AMP 206062-1
JK- SB1IGA RECEPTACLE, 8 PIN AMP 205841-2
CLAMP AMP 206062-1
JK- SB1?7A PLUG, 8 PIN AMP 205838-1
CLAMP AMP 206062-1

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74
 MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
28 VOLT S/N 25-1225 THRU 25-1999
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

JK- SB118A RECEPTACLE, 8 PIN AMP 205841-2

CLAMP AMP 206062-1
JK- SB11SA MOTOR, RIGHT PRECISE FLT 01532
JK- SB120A SWITCH, DEPLOY LIMIT PRECISE FLT 01505
JK- SB121A SWITCH, RETRACT LIMIT PRECISE FLT 01505
JK- SB122A SOLENOID, CLUTCH PRECISE FLT 01678
JK- SB123A PLUG, 8 PIN AMP 20583&1
CLAMP AMP 206062-1
JK- SB124A RECEPTACLE, 8 PIN AMP 205841-2
CLAMP AMP 206062-1

JK- SPK1OIA SPEAKER, CABIN ARCHER 12-1703

JK- SPK102A PLUG, 2 PIN AMP 1-480318-0
SOCKET AMP 60619-1
JK- SPK103A RECEPTACLE, 2 PIN AMP 1-480319-0
PIN AMP 60620-1

JK- WD1O1A FUSEHOLDER LITTEL 155020

(ALT) LITTEL 155120
FUSE, 1A LITTEL 313001
JK- WE1OIA C/B, GEAR WARNING KLIXON 7277-2-1
JK- WE? 02A LIGHT, GEAR DOWN SLOAN 855S-0-U
BULB GE 327
J- WE1OBA SWITCH, THROTTLE MICRO V3-1
ACTUATOR MICRO JV-5
-K- WE1 03A SWITCH, THROTTLE MICRO 1SEI-T
ACTUATOR MICRO JE-17
JK- WE104A HORN, GEAR WARNING MALLORY SC628P
JK- WE1 05A DIODE 1 N2483
(ALT) 1N5060
(ALT) GE 3720-GE
JK- WE1OGA DIODE 1N2483

G’E 0605N1EG-0273

JK- WE107A RESISTOR ALLEN BRADLEY RC42GF10ulK OHM2W

JK- WE108A PLUG, 4 PIN AMP 206060-1
CLAMP AMP 206062-1
JK- WE1OSA RECEPTACLE, 4 PIN AMP 206153-1
CLAMP AMP 206062-1
JK- WP1OIA MONITOR, CURRENT, PTTOTHEAAT MOONEY 800221-505
JK- WP102A PLUG, 9 PIN AMP 2067052
CLAMP AMP 206966-1
JK- WP1OGA FUSEHOLDER LITTEL 155020
(ALT) LITTEL 155120
FUSE (5A) LTT~TEL 313005

JK- WS1OIA C/B, STALL WARNING KLIXON 7277-2-1

JK- WS102A HORN, STALL WARN MALLORY SC628
JK- WS103A RESISTOR ALLEN BRADLEY RC42GF102J 1K OHM2W
JK- WS104A SWITCH, STALL WARN SAFE FLIGHT C46001
MICRO SWTTCH V3-2451-D8 9
MOONEY 800366507
JK- WT1OIA C/B KLU(ON 7277-2-2

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SERVICE AND MAINTENANCE MANUAL M20K MOONEY AIRCRAFT CORPORATION
28 VOLT S/N 25-1225 THRU 25-1999
OLDWILLWAYNE
DESCRIPTION VENDOR PART NO. NOTES
CODE

J- VVT102A ANNUNCIATOR MOONEY 88004&501

(ALT)(USA) MOONEY 880048-601

MOONEN 880048-603
-K- WT1 02A ANNUNCIATOR MOONEY 880048-501
(ALT) LEGEND (USA) MOONEY 880048-605
(ALT) LEGEND (FRANCE) MOONEY 880048-607
JK- WT103A PLUG, 37 PIN DC-37S
CLAMP, RT ANGLE DC19977-3
LOCK RETAINER DC51222-1

JK- WT1 04A ANNUNCIATOR (ATS) MOONEY 880025521

BULB CHICAGO MINATURE CMF7327
JK- WV1OIA C/B, VACUUM WARN KLU(ON 7277-2-2
JK- WV102A SWITCH, VACUUM WARN MOONEY 880012-501
JK- WV103A RECEPTACLE, 4 PIN AMP 206153-1
CLAMP AMP 206062-1

JK- WV104A PLUG, 4 PIN AMP 206060-1

CLAMP AMP 206062-1

JK- WW1OIA SWITCH, ALTERNATE AIR CHERRY E51-50B

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 MS35334-21 OR 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.

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MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
28V SM 25-2000 THRU 25-TEA
OLDWILLWAYNE
91-20-04
ELECTRICAL SYSTEM HARDWARE CHART 28 VOLT

SERIAL NUMBER’s 25-2001 THRU 25-2012, MOONE/ DRAWING NUMBER, 800383 (PG 5.1.2) (REV. E)
SERIAL NUMBER’s 252013 THRU 25-TBD, MAC DWG NO. 800383 (PG 5.1 3) (REV. Fl
SERIAL NUMBER’s 25-TBD THRU 25-iBA, MAC DWG NO. 800383 (PG 5.1.4) (REV. Fl
DESCRIPTION VENDOR PART NO. NOTES
CODE

AC1O1A SWITCH, AIR COND. MOONC/ 880067-501

AC102A COMPRESSOR, AIR COND. MOONEY 77002&1
ACI 03A BLOWER, EVAP. (FRONT) MOONC( 770002-501
ACI 04A BLOWER, CONDENSOR MOONEY 770018501
ACIOSA SWITCH, AIR COND. PRESS MOONEY 770029-501

ACIOGA CONNECTOR, AIR COND COND GORY COMP. CSLT-21 PA

CONTACTS GORY COMP. CB017-5S

AT1OIA ACTUATOR, SWITCH MICRO SWITCH JE-5

AT102A ACTUATOR, SWITCH MICRO SWITCH JV-5
AT103A ACTUATOR, SWITCH MICRO SWITCH JV-26
AT104A ACTUATOR, SWITCH MICRO SWITCH MCD-2711
AT105A ACTUATOR, SWITCH MICRO SWITCH JE-17
AT1OGA ACTUATOR, SWITCH MICRO SWITCH JV-82
BR1 CIRCUIT BREAKER (1A) MECH PROD. 4200-002-1
KLIXON 727/-2-1
(ALT)
BR2 CIRCUIT BREAKER ~A) MECH PROD. 4200-002-2
(ALT) KLIXON 7277-2-2
BR3 CIRCUIT BREAKER (3A) MECH PROD. 4200-002-3
(ALT) KLIXON 7277-2-3
BR5 CIRCUIT BREAKER(SA) MECH PROD. 4200-002-5
(ALT) KLIXON 7277-2-5
BR7.5 CIRCUIT BREAKER (7.5A) MECH PROD. 4200-002-7.5
(ALT) KLIXON 7277-2-7.5
BR10 CIRCUIT BREAKER (10A) MECH PROD. 4200-002-10
(ALT) KLIXON 7277-2-10
BR15 CIRCUIT BREAKER (15A) MECH PROD. 4200-002-15
(ALT) KLIXON 7277-2-15
I

BR20 CIRCUIT BREAKER (20A) MECH PROD. 4200-002-20

BR25 CIRCUIT BREAKER (25A) MECH PROD. 4200-002-25
BR30 CIRCUIT BREAKER (30A) MECH PROD. 4200-002-30
BR35 CIRCUIT BREAKER (35A) ETA 41-2-S3dLN2-35A
BR40 CIRCUIT BREAKER (40A) ETA 41-3S34-LN2-40A
MECH. PROD. 700-001-40
BR50 [50A) ETA 41-2S34-LN2-50A
6270 CIRCUIT BREAKER CIOA) ETA 41-3S34-LN2-70A
BS BASE,RELAY MAGNACRAFT 70-303
BU2A BUS BAR (2 PLC) MOONEY 913127-33
BU2B BUS BAR (2 PLC) MOONEY 913127-97
BU2C BUS BAR PLC) MOONEY 913127-99
BU2D BUS BAR PLC) MOONEY 913127-75
BU2E BUS BAR (2 PLC) MOONC/ 913127-65
BU3A BUS BAR (3 PLC) MOONfl 913127-87
BU3B BUS BAR (3 PLC) MOONEY 913127-59
BU3C BUS BAR (3 PLC) MOONEY 913127-73
BU4A BUS BAR (4 PLC) MOONEY 913127-69
BU4B BUS BAR (4 PLC) MOONEY 913127-89
BU4C BuS BAR (4 PLC) MOONEY 913127-5
BUSA BuS BAR (5 PLC) MOONEY 913127-93
BUSB BuS BAR (5 PLC) MOONEY 913127-77
BUSC BUS BAR (5 PLC) MOONC/ 913127-85
BUSD BUS BAR (5 PLC) MOONEY 913127-19

BU6A BUS BAR (6 PLC) MOONC/ 913127-35

BUGB BUS BAR (6 PLC) MOONEY 913127-79
BU7A BUS BAR C/ PLC) MOONEY 913127-81
BU8A BUS BAR (8 PLC) MOONEY 913127-95
CA1O?A CAPACITOR MALLORY CGS302V050R2C

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 SERVICE AND MAINTENANCE MANUAL M2OK MOONEY AIRCRAFT CORPORATION
28V S/N 25-2000 THRU 25-TEA
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

CC1OIA MOTOR, COWL FLAP MOONEY 880050-505

CC1 02A INDICATOR, COWL FLAP MOONEY 800242-505
CC1O3A SWITCH, COWL FLAP MOONEY 880052-517
CC1O3B SWITCH, COWL FLAP (J) MOONEY i 2Mn -i O
CC1O3C SWITCH, COWL FLAP MOONEY 880052-117
CI=1OIA ACTUATOR, FLAP MOONEY 7501 05-501
CM 02A INDICATOR, TRIM/FLAP MOONEY 800242-501
CT=l 03A INDICATOR, TRIM/FLAP MOONEY 800376-501
CF1 04A INDICATOR, TRIM/FLAP MOONEY 800391-502
CLO3A CLAMP, 3,14,16,28 PIN AMP 206070-1
CLO3B LAMP, 3 PIN M8049-41-4A
CLO3C CLAMP, 3 PIN MS3O57-4A
(ALT) MS3O57-4B
CLO4A CLAMP, 4, 8 PIN AMP 206062-1
CLOSA CLAMP, 5 PIN MS3057-6A
(ALT) MS3057-6B
CLOGA CLAMP, 6 PIN MS3057-1 6A
CLOSA c~np, iPllj AMP B61-7503SM1~-669602

CLOSE CLAMP, 9 PIN AMP P/O 126-222

CLOSC CLAMP, 9 PIN DE-24657
LOCK RETAINER DE 51224-1
(ALT) LOCK D1i0278
CLOSD CLAMP, 9 PIN DE-1 9977-5
LOCK RETAINER DE-51224-1
CL1SA CLAMP, 15 PIN’ DA5121 0-1
LOCK RETAINER DA51220-1
CL? 7A CLAMP, 17 PIN DB51212
LOCK RETAINER DB51221-1
CL25A CLAMP, 25 PIN DB51212
LOCK RETAINER DB51221-1
CL25B CLAMP, 25 PIN DB19S77-2
LOCK RETAINER DBS1221-1
CL25C CLAMP, 25 PIN D824659
LOCK RETAINER D-20418-2
CL32A CLAMP, 32 PIN M85O49/52-1-22N
CL32B CLAMP/BOOT MS3420-14
(ALT) MS3420-16
CL37A i=LA~inP, 37 PIN 206138-1
CL37B CLAMP, 37 PIN DC1SS77-3
LOCK RETAINER DC51222-1
CMiOiA CURRENT MONITOR M’00r;lEY‘ 800221-505
CR1OIA SWITCH, RUDDER TRIM iWHiTE)’ MOONEY 880052-519
CR1O1B SWITCH, RUDDER TRIM (BLACr~ MOONEY 880052-119
CR1O2A MOTOR, RUDDER TRIM MOONEY 880050-503
CR1 03A INDICATOR, RUDDER MOONCI 800242-503
CT1OIA SWITCH, TRIM MIL-S-9419 930023-233
CT1 02A INDICATOR, ELEV. TRIM MOONC/ 800242-519
CT1 03A MOTOR, ELEV. TRIM S-TEC 01165-0-T14
CT? 04A TRIM INTERFACE MOONN 80031 3-501
CT1 05A INDICATOR, ELEV. TRIM MOONEY 800391-501
CV1O?A CIRCUIT BRUU<ERISWITCH MOONEY 930023-233
CV1O1B CIRCUIT BRUU<ER/SWITCH MOONfl 930023-333
CV1O2A PUMP, STAND-BY VACUUM AEROSAFE 820904-2
CV1O3A PUMP, STAND-BY VACUUM AEROSAFE 820904-1
CV1O4A SWITCH/C-B, STAND-BY VACUUM MOONEY 930023-247
CV1O48 SWITCH/C-B, STAND-BY VACUUM MOONEY 930023-347
CV1OSA PUMP/CLUTCH ASSY, STDBY VAC. AIRBORNE 28C214-CW-2
DA1OIA SHUNT, AMMETER EMPRO MLA-70A-1 OOMV
(ALT) JANCO 8406-70
DA?O1B SHUNT, AMMETER EMPRO MLA-15OA-100MV
(ALT) JANCO 8406-1 50

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 M20K SERVICE AND MAINTENANCE MANUAL
MOONEY AIRCRAFT CORPORATION
28V SM 25-2000 THRU 25-TEA
OLDWILLWAYNE
VENDOR PART NO. NOTES
CODE DESCRIPTION

UI 9013 CODE N.5

DB1OIA TURN COORDINATOR
ASIRONAUTICS 303990-028MSC
(ALT) 1394Ti00-32
(ALT) ELEC. GYRO CORP.
UI 9114 CODE N21
(ALT)
TURN COORDINATOR UI 9112 CODE N.9
DB102A
MS24482-1
DC1OIA PROBE, CHT
AN5546-1
(ALT)
DD1OIA INDICATOR, OAT M’001;IEY 880059159
MOONEY 880004-501
DD102A PROBE, OAT
CINCH-JONES S-304-CCT
DD103A SOCKET, 4 PIN
XMTR, FUEL, INBD, LCURH MOONEY 61 0242-3
DF1OIA
MOONEY 610243-3
DF1 02A XMTR, FUEL, OUTED, LH
MOONEY 61 0243-1
DF1 03A XMTR, FUEL, OUTED, RH
MOONEY 610242-5
DF1 04A XMTR, FUEL, OUTED, LH/RH
MOONEY 880059-507
DG1O1A MODULE, INSTRUMENT
MOONEY 880059-511
DG102A MODULE, INSTRUMENT
MOONEY 880059-513
DG1 03A MODULE, INSTRUMENT, #1
MOONEY 880059515
DG1 04A MODULE, INSTRUMENT, #2
MOONEY 880059517
DG~ 05A MODULE, INSTRUMENT
MOONEY 880054523
DG1 07A MODULE, INSTRUMENT, #1
MOONEY 880059-525
DG108A MODULE, INSTRUMENT, #2
MOONEY 880059521
DG1OSA MODULE, INSTRUMENT
MOONW 880061-501
DH1O1A PROBE, OIL TEMP
MS28034-1
DH102A PROBE, OIL TEMP
DIODE 1N2483/1 N5060
DI1O1A
(ALT) dE 3720-GE
DIODE 10H3P
D1102A
(ALT) ECG 5854
NTE 5854
(ALT)
D1104A BRIDGE,’DIO’DE FAGOR FB500i
FAGOR FB5006
D1105A BRIDGE, DIODE
DRUCK PDCR 821-0662-100
DJ1OIA XDCR, OIL PRESS
KULITE APT-1 54-1 000-1 00PSIG
(ALT) (M20J)
XDCR, OIL PRESS (M20Mj KULITE APT-201-1 000-100G
DJ1OIB
DRUCK PDCR-821-0662-30
DK1OIA XDCR, FUEL PRESS
KULITE APT-i 53-1000-30 PSIG
(ALT) PDCR-920-U143-50 PSID
DK102A XDCR,FUELPRESS DRUCK
KULITE APT-1 55-1 000-50D
(ALT)
MOONEY 880039515
DL1OIA INDICATOR, TACHOMETER
B&D 0520-003
(OPTIONAL)
B&D 0400-004
DL1 02A SENSOR, TACH
MOONEY 880039517
DL1 03A INDICATOR, TACH
B&D 0520-006
(OPTIONAL)
B&D 0402-1 02
DL1 04A SENSOR, TACH (SLICK)
B&D 0402-1 04
DL1 048 SENSOR, TACH (BENDIX)
B&D 0406-004
DL1 04C SENSOR, TACH (BENDIX)
B&D 0406-003
DL1 040 SENSOR, TACH (SLICK)
MOONCI 880039519
DL? 05A INDICATOR, TACHOMETER
MOONC/ 880039-523
DL1 06A INDICATOR, TACHOMETER
HOUR METER MOONEY 880035-507
DMIO1A
HOUR METER MOONEY 880035-505
DMI02A
HOUR METER HOBBS 15006
DM103A
DATCON SE70
DM104A METEk HOBES 85000
HOBBS 15000
(ALT)
C/B MOONEY 930023-205
DP1O1A
C/B MOONEY 930023-305
DP1O1B
DP1 02A PITOT, HiiEATi3D AERO INSTR PH502-12
AN5812
(ALT)
DP103A PITOT, H’EATi~D AERC; INSTR PH502-12
AN5812
(ALT)

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CODE DESCRIPTION VENDOR PART NO. NOTES

AN31I 5-1
OLDWILLWAYNE
DP104A PLUG
DP1OSA SOCKET AN3116-1

DR1O1A PROBE, TIT MOONEY 880055-503

DRIO1B PROBE, TIT MOONEY 880055-505
DT1OIA INDICATOR, EGT ALCOR 46361
DT1OI B INDICATOR, EGT ALCOR OEM-46161
DT102A SWITCH, EGT (4 POSITION) ALCOR OEM-80825
DTI03A PROBE, EGT MOONEY 66011 0-000
(ALT) ALCOR 86225
DT104A LIGHT TRAY (28V) ALCOR 41338
DT1OSA LIGHT TRAY (14V) ALCOR 41337
DV1O1A INDICATOR, FUEL FLOW MOONEY 880034-501
(OPTIONAL) MOONEY 880034-503
(OPTIONAL) MOONEY 880034-505
DV1O1B INDICATOR, FUEL FLOW’ SHADIN 912041TD 1

DV102A TRANSDUCER, FUEL FLOW MOONEY 880030-501

(OPTIONAL) MOONEY 880030-503
DV1028 TRANSDUCER, FUEL FLOW SHADIN 6805018
EG1OIA ACTUATOR, LDG MOONEY 880037-507
(ALT) MOONEY 560254-503
EG102A ACTUATOR, LDG MOONEY 880037-501
(ALT) MOONEY 560254-501
EG1 03A ACTUATGR, LDG’ MOONEY 560254-505
EG104A SWITCH, AIRSPEED MOONEY 88001 3-507
ET1O1A SWITCH, ELT PANEL ARTEX 110-416
ET1 02A TRANSMITTER, ELT ARTEX 453-0150
ET1 03A CABLEASSY, REMOTE AMERI-KING 4500041
ETi 04A REMOTE UNIT ASSY AMERI-KING 450004
(OPTIONAL) AMERI-KING 450004-1V/-1H
ETIOSA MAIN UNIT ASSY. AMERI-KING AK-450
FH1OIA FUSEHOLDER LITTEL FUSE 155020
(ALT) LITTEL FUSE 155120
FH102A FUSE HOLDER McGRAW EDISON FHN42W
FO101A PHONE JACK SWTTCHCRAFT C-i 1
WASHERS SWITCHCRAFT S-1028 OR 51029
FOi 02A PHONE JACK SWITCHCRAFT C112B
WASHERS SWITCHCRAFT S-1028 OR S-1029

FU1OIA FUSE (1 AMP) LITTEL FUSE 313001

FU102A FUSE (5 AMP 3AG-S’LO-BLOj LITTEL FUSE 313005
FU103A FUSE (10 AMP, SLO-BLO) LITTEL FUSE 313010
FUI04A FUSE (5 AMP) McGRAW-EDISON FMO1-SA
FU105A FUSE (0.5 AMP) McGRAW-EDISON FM01-.50A
JEi 01A CONTROL, IGNITION LASAR (SLICK) CD-1001-02
JE1 02A CABLE LASAR (SLICK) CH-1 001-XX
JE103A MAGNETO, LEFT’ SLICK (LASAR) CD-4771
JE1 04A MAGNETO, RIGHT SLICK (LAZAR) CD4770
JM1OIA SWITCH, IGNITION BENDIX SCINTILLA 10-357210-9
PLACARD BENDIX SCINTILLA 10-187-468
LUG, TERMINAL BENDIX SCINTILLA 10-126656
JMiOiB SWITCH, IGNITION (INCL’CONN.) JANCO 97-2273-1
JM102A MAGNETO BENDIX SCINTILLA D4LN2021
(ALT) BENDIX SCINTILLA D4LN3000
(ALT) LYCOMING LW682555-ii

JMI03A PLUG, MAGNETO BENDIX SCINTILLA 10-382698

JM104A MAGNETO SLICK 6224
JM1OSA MAGNETO, LEFT’ SLICK 6261
JMIOGA MAGNETO, RIGHT SLICK 6260
JMI07A SWITCH, IGNITION BENDIX-SCINTILLA 10-357240-1
JMI 08A MAGNETO, LEFT SLICK 6393
JMI 09A MAGNETO, RIGHT SLICK 6350

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MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
28V S/N 25-2000 THRU 25-TEA
OLDWILLWAYNE
DESCRIPTION VENDOR PART NO. NOTES
CODE

JM11OA IGNITION, PULSAR MOONEY 80031 5-501

JM111A MAGNETO, L8R TCM/BENDIX 10-79020-10
JM1?3A MAGNETO, L&R TCM 640896-1
MAGNETO, L&R(OPT.) BENDIX 1 a-79020-120

V4101A LIGHT BULB, 28V GE 400

LA102A LIGHT BULB, 14V GE 168-T-3 114
LA103A LIGHT BULB GE 385
LA104A LIGHT BULB GE 330
LA105A LIGHT BULB CHICAGO MINI CM7-7330
LA1OGA LIGHT BULB CHICAGO MINI CM7-7327
LA107A LIGHT BULB GE 370
LA108A LIGHT BULB GE 1816
LA1OSA LIGHT BULB GE AVIA. RED, 327
LA11OA LIGHT BULB GE 327
LA111A LIGHT BULB GE 1818
LA112A LIGHT BULB GE 1495

LA113A LIGHT BULB GE 4596

LA114A LIGHT BULB PACIFIC PREC. PROD P28028

LA115A LED MOUSER 351-0003
LB1O1A C/Bsw, i3EA’COEi, V~ITE MOONN 930023-243
LB1O1B C/B-SW, BEACON, BLACK MOONEY 930023-343
LB1 02A BEACON, ROTATING WHELEN WRML-28
ADAPTER WHELEN WRML-65
LB1 028 LIGHT, ANTI-COLLISION (RED) WHELEN 90033-19
LB1 02C LIGHT, ANTI-COLLISION (WHITE) WHELEN 90033-20
LE1OIA LENS, ANNUNC. (US) (M20J) MOONEY 88004&613
LE1 02A LENS,ANNUNC. (FRANCE)(M20J) MOONEY 880048-615
LE1 03A LENS, ANNUNC. (US) (M20M) MOONEY 88004&617
LE1 04A LENS, ANNUNC. (FRANCE)(M20M) MOONEY 880048-619
LE1 05A LENS, ANNUNC. (M20T) MOONEY 88004&621
LE1 06A LENS, ANNUNC. (M20T) MOONEY 88004&623

LE1 07A LENS, ANNUNC. (US) (M20J) MOONEY 880044-633

LE108A LENS,ANNUNC. (FRANCE)(M20J) MOONEY 880044-635
LE1 09A LENS, ANNUNC. (US) (M20R) MOONEY 88004&625
LE11OA LENS, ANNUNC. (FRANCE)(M20R) MOONEY 88004&627
LE111A LENS, ANNUNC. (US) (M20R) MOONEY 880048629
LE112A LENS, ANNUNC. (FRANCE)(M20R) MOONEY 88004&631
LE113A LENS, ANNUNC. (US) (M20K) MOONEY 88004&605
LE114A LENS, ANNUNC. (US) (M20~ MOONEY 880048607
LEI 15A LENS, ANNUNC. (M20K) MOONEY 880084001
LG1O1A CIRCUIT BREAKER, LOGO LIGHT MOONEY 930023-357
LG1 02A LIGHT, LOGO WHELEN A730-1-28
LH1OIA LAMP HOLDER MOONEY 914083-1
LH102A LAMP HOLDER DIALIGHT 270-1930-0171-702
LH103A LAMP HOLDER WHELEN A-350-CN-CL-BK-SH-28
LAMPHOLDER SLOAN 855S-0-U 2
LH104A
LH1OSA LAMP HOLDER INSTRUMENTS 0211-128
LH1OGA LAMP HOLDER INSTRUMENTS BA2&24-BW3
LH107A LAMP HOLDER SIGMA-TEC 1V-192-971
LH1 08A LAMPHOLDER HHSMITH 1930
LEECRAFT 7-05
ALLIED 931-3103
(ALT) SPC LSL-11-~28U
(ALT) NEWARK 81N2561
LH1OSA LAMP HOLDER HH SMITH 1925
LH11OA LAMPHOLDER WHELEN 01-0770437-00
LH111A LAMP HOLDER TEK-LITE LC-28-5
(ALT) MS1745-51A
LH112A LAMP HOLDER V;MELEN 01-077-0142-04

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SERVICE AND MAINTENANCE MANUAL M20K MOONfl AIRCRAFT CORPORATION
28V S/N 25-2000 THRU 25-TEA
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

LH113A LAMPHOLDER MOUSER 351-0003

LL1OIA SWITCH, LDG LIGHT MOONEY 880052-521
LL1 02A BULB, LIGHT, LDG/TAXI GE 4596
LL1 03A BULB, LIGHT, LDG/TAXI GE 4509
LN1O1A CIRCUIT BREAKER MOONEY 930023-351
LN1 02A LIGHT, NAV. CTAIL) MOONEY 800051-501
LN1 02A LIGHT, NAV. CTAIL) MOONEY 800051-509

LP1OIA DIMMER, BOX MOONEY 800299-501

LP102A DIMMER, CONTROL BOX MOONEY 800299503
LP103A DIMMER, CONTROL BOX MOONEY 800299505
LP104A SWITCH, ORI LIGHT ASSY MOONEY 150085-005
LP105A INVERTER, E-L PLACARD ERG LPS28-3-3P
LRI 01A C/B MOONEY 930023-231
LR1O1B C/B MOONEY 930023-331
LR1 02A LIGHT, R’ECOGNI’TIOI;I MOONEY 880049501
LS1O1A CIRCUIT BREAKER MOONEY. 930023-237
LS1O1B CIRCUTT BREAKER MOONEY 930023-337
LS102A POWER SUPPLY, STROBE WHELEN 01-0770329-00
LS102B POWER SUPPLY, STROBE WHELEN 01-0770329-01
LS103A LIGHT, STROBE-LT WING WHELEN 01-0770054-12
LS104A LIGHT, STROBE-RT WING WHELEN 01-0770054-13
LS1 05A LIGHT, STROBE, TAIL MOONEY 47001 3-501
LS1OGA LIGHT, STROBE, DUAL WHELEN A41 3A-HDA-CF
LT1OIA SWITCH, TAXI LIGHT MOONEY 880052-523
LT1O1B SWITCH, TAXI LIGHT MOONEY 880052-1 23
LT102A BULB, LIGHT, TAXI, LH 8 RH GE 4596
MA1O1A RECEPTACLE,AUX.POWER AN2552-3A

MBi 01A C/BSWTTCH, RADIO MASTER CINHT) MOONEY 930023-213

MBi 01 B C/&SWITCH, RADIO MASTER (BU~ MOONEY 930023-313
MC1OIA LIGHTER, CIGAR MOONEl 800336-503
ME1O1A CLOCK MID-CONT. MD-89
(ALT) PORSCHE 944.641 .21 3.00
ME102A CONNECTOR, 4 PIN MIPCONT 6016177
PINS MIPCONT 6016125
(OPT) PORSCHE 944.61 2.21 7.00
(OPT) PINS PORSCHE 999.652.351.12
MK1O1A JACK, MICROPHONE SWTTCHCRAFT C´•12B
WASHERS SWTTCHCRAFT S-1028
WASHERS SWTTCHCRAFT S-i 029
MP1O1A C/B-SW PROP DE-ICE (WHITE) MOONEY 930023-245
MP1O1B C/BsSW PROP DE-ICE (BLK) MOONEY 930023-345
MP102A TIMER, PROP DE-ICE BF GOODRICH 3E1899-1
MP102B TIMER, PROP DE-ICE McCAULEY &45018
MP103A TERMINAL BLOCK McCAULEY C´•40521
NF1O1A SW/C-B, LOWBOOSTFUELPUMP MOONEY 930023-211
NF1O1B SW/C-B MOONEY 930023-311
NF102A PUMP, FUEL BOOST WELDON A8163B
(ALT) WELDON 81 638
NF1 03A PUhAP, FUEL BOOST WELDON 81 63A
(ALT) WELDON A81 63A
NF1 04A PUMP, FUELBOOST (M20K) WELDON 10054B
NF1 05A PUMP, FUEL BOOST WELDON Al 0051-D
NF1OGA PUMP, FUEL BOOST WELDON A8152-8
NF108A (ALT) MASSEY VR536
NI=1088 REGULATOR, FUEL PUMP MOONEY 800270-523A
NF1OSA SW/C-B, HI-BOOST FUEL PUMP MOONEY 930023-219
NF11OA GUARD ASSY, HI-BOOST SW MOONEY 93002&501

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MOONEY AIRCRAFT CORPORATION M20K SERVICE AND MAINTENANCE MANUAL
28V SM 25-2000 MRU 25-TEA
OLDWILLWAYNE
VENDOR PART NO. NOTES
CODE DESCRIPTION

REGULATOR, VOLTAGE MOONEY 800270-501

PA?OIA
AM.PROWPRECISE FLT DGR-2
AUXILECIELECTODELTA VR-802
PA102A SWITCH, ALT;NTk FIELD iDUkl) MOONEY 880052-525
SWTTCH, ALTNTR. FIELD (SINGLE) MOONEY 880052-503
PA1 03A
ALTERNATOR LYCOMING LW-~4367
PA104A
PRESTOLITE ALU-6421-LS
(ALT)
ALTERNATOR LYCOMING LW-I 5404
PA1OSA
PRESTOLITE ALY-8420
(ALT)
ALTERNATOR, RIGHT TCM 649719
PA1 06A
TCM 649280
(ALT)
GEAR ASSY TCM 649123

ALTERNATOR ELECTRO SYSTEMS ES-4009-LS

PA107A
LYCOMING 05K-21 065
KIT, INSTALL
(REFERENCE 600180)
FILTER MOONEY 880014-501
PA1 08A
MOONEY 800307-501
(ALT)
PAIOSA SENSOR, CURRENT MICRO SWITCH CSLAI GE
REGULATOR, VOLTAGE MOONEY 800270-503
PAI 1 OA
SENSOR, CURRENT (110A) KLIXON 7235-1-110
PA111A
SENSOR, CURRENT (175A) KLIXON 7235-1-1 75
PA111B
ALTERNATOR TCM 649304
PA112A
MONITOR, CURRENT MOONEY 800287-501
PA113A
ALTERNATOR, LEFT TCM 649172
PA114A
TCM 649283
(ALT)
PB1OIA BATTERY GILL 6243
SWITCH, MASTER MOONEY 880052-501
PB102A
SWITCH, MASTER MOONEY 880052-101
PB1 028
SWITCH, BAT 1-2 MOONEY 880052-527
PB1 03A
SWITCH, BAT 1-2 MOONEY 880052-1 27
PB1 038
BATTERY, 24V CONCORDE RG24-1 1M
PB1 05A
PLUG, 2 PIN AMP i -480318-0
PL02A
PL02B PLUG, 2 PIN MOLD( 03-06-1023
DEAN 7021
PL02C PLUG, 2 PIN (FEMALE)
PLUG, 2 PIN MS31 06A-24-9S
PL02D
PLOSA PLUG, 3 PIN AMP 1-380303-0
3 PIN AMP 206037-2
PL03B PLUG,
3 PIN MS3106A-1 0SL-3S
PL03C PLUG,
PL03D PLUG, 3 PIN MS3106A-28-6P
PL04A PLUG, 4 PIN AiinP 206060-1
PL04B PLUG, 4 PIN MS3106A-32-17S
PLO4C PLUG, 4 PIN ANIP 1-480424-0
PLOSA PLUG, 5 PIN MS3106A-14S5S
PLOGA PLUG, 6 PIN MATFilX SCIENT. MS3106A-2&22S
PL08A PLUG, 8 PIN AMP 205838-1
PLOSA PLUG, 9 PIN AMP 206708-1
PLOSB PLUG, 9 PIN AMP 126-222
PLOSC PLUG, 9 PIN DESS
PLOgD PLUG, 9 PIN MOLM 03-06-2092
PLOSE PLUG, 9 PIN AMP 206485-1
MOONEY 930021-1
PL14A PLUG, 14 PIN
MOONEY 930021-513
PL148 PLUG, 14 PIN
PL?4C PLUG, 14 PIN AMP 206043-3
PL1SA PLUG, 15 PIN DA15S
PL1GA PLUG, 16 PIN AMP 206037-1
PL1’IA PLUG, 17 PIN DBM17W2S
PL20A PLUG, 20 PIN MOONEY 930021-501
PL20B PLUG, 20 PIN POSTTRONICS CC14&003-0.00
PL20C PLUG, 20 PIN POSTTRONICS CC149003-0.00
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28V S/N 25-2000 THRU 25TBA
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES
==~,==--z;====,,=

PL21A PLUG, 21 PIN MOONEY CSLT-

PL25A PLUG, 25 PIN DB25S
PL25B PLUG, 25 PIN AMP 20520&1
PL26A PLUG, 26 PIN MOONEY 930021-505
PL28A PLUG, 28 PIN AMP 2058393
PL32A PLUG, 32 PIN M83723/86R2232N
PL34A PLUG, 34 PIN MOONEY’ 930021-507
PL34B PLUG, 34 PIN MOONEY 930021-515
PL37A PLUG, 37 PIN AMP 206150-1
PL37B PLUG, 37 PIN DC37S
PL50 PLUG, 50 PIN MOONEY’ 930021-511
PLP 04A PLUG, 104 PIN POSITRONICS GMCT104FOTH000
PS1O1A C/B, START POWER KLIXON 7277-2-10
PS102A C/B, START POWER KLIXON 7277-2-5
PS1 03A STARTER (M20J) PRESTOLITE MHB4016
(ALT) LYCOMING LW-1 5572
PS104A STARTER (M20K 8 M20R) TCM 646275
(ALT) TCM 637847
PS1OSA STARTER (MiOMj B&C BSC206149
RB1O1A RADIO BLOWER KING 071-4037-01
RC02A RECEPTACLE, 2 PIN AMP 1-480319-0
RC02C RECEPTACLE, 2 PIN (MALE) DEAN 7022
RC02D RECEPTACLE, 2 PIN MS3100-24-9P
RC03D RECEPTACLE, 3 PIN AMP 1-480305-0
RC03B RECEPTACLE, 3 PIN AMP 206036-2
RCO3C RECEPTACLE, 3 PIN AMP 206207-1
RC03D RECEPTACLE, 3 PIN M3100-28-68
RC04A RECEPTACLE, 4 PIN AMP 206153-1
RC04B RECEPTACLE, 4 PIN M3100-32-17P
RC04C RECEPTACLE, 4 PIN AMP 1-480426-0
RCOGA RECEPTACLE, 6 PIN MATRIX SCIENCE MS3100C-2&22P
RC08A RECEPTACLE, 8 PIN AMP 205841-2
RCOSA RECEPTACLE, 9 PIN AMP 206705-2
RCOSB RECEPTACLE, 9 PIN AMP 206705-1
RCOSC RECEPTACLE, 9 PIN DESP
RCOSE RECEPTACLE, 9 PIN AMP 205486-1
RC12A RECEPTACLE, 12 PIN MOLEX 03-06-2122
RC14A RECEPTACLE, 14 PIN MOONEY 930021-2
RCI4B RECEPTACLE, 14 PIN AMP 203540-1
RC14C RECEPTACLE, 14 PIN AMP 206044-1
RC~GA RECEPTACLE, 16 PIN AMP 206036-2
RC1GB RECEPTACLE, 16 PIN AMP 206036-1
RC20A RECEPTACLE, 20 PIN MOONEY 930021-502
RC20B RECEPTACLE120 PIN POSITRONICS GMCT2MOE1 OOJO
RC26A RECEPTACLEI26 PIN MOONN 930021-506
RC28A RECEPTACLE, 28 PIN AMP 206152-1
RC32A RECEPTACLE, 32 PIN MATRIX SCIENCE M83723/83K2232N
RC34A RECEPTACLE, 34 PIN MOONEY 930021-508
RC34B RECEPTACLEI34 PIN AMP 204814-1
RC37A RECEPTACLE, 37 PIN AMP 206151-1
RCSOA RECEPTACLE, 50 PIN MOONEY 930021-512
RC104A RECEPTACLE1104 PIN POSITRONICS GMCT104MOOOOZO
RL1OIA RELAY, 28V/200A KISSLING 26.57.01
(ALT) KISSLING 26.57.02
(ALT) C-H 6041 H-202M02A
RL1 02A RELAY, 14V/200A C-H 6041 H-l 05A
RL1 03A RELAY KISSLING 26.64.01
RL1 04A RELAY KISSLING 26.64.21
RL1 05A RELAY, 28V/50A KISSLING 26.72.03

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OLDWILLWAYNE
DESCRIPTION VENDOR PART NO. NOTES
CODE

BRACKET (2 REQD.) MOONEY 8003751

C-H 6041 H-220
(ALT)
RL1 06A RELAY, iSVliOOA CH 6041 H-53
RL1 07A RELAY 14V/200A C-H 6041 H-l 05R
RL1 08A RELAY MAGNACRAFT \Mi7RCSX-3
RL1 09A RELAY KISSLING 28.08.01
RL1I OA RELAY P&B VF4-15-Hi 1
SOCKET P&B VCF4-1002
TERMINAL P&B 26A1348C
RS?OIA RESISTOR, 20-OHM/10W DALE RH-10-20 OHM
RS102A RESISTOR, 5 OHM/IOW DALE RH-10-5 OHM

RS103A RESISTOR, 500 OHM MOONEY 919024501

RS104A RESISTOR, 100 OHM NEWARK 09F976

RS1OSA RESISTOR, 7.5-OHM DALE RH-50-7.5 OHM

RS1OGA RESISTOR, 1KOHM/2W ALLEN BRADLEY RC42-GF102J
SPECTROL 14911-502 3
RSi 07A RESISTOR, 5K OHM
RS108A RESISTOR, 150 OHM/3W CLAROSTAT VC3D
OHMITE 23J
(ALT)
RS1OSA RESISTOR, 3.9K bHNill/2~W OHMITE
RS11OA RESISTOR, 3.OK OHM/1/2W OHMITE
RS111A RESISTOR, 1 OHM/25W DALE RH-25-1 OHM
RS112A RESISTOR, 70 OHM/1OW DALE RH-10-70 OHM
RS113A RESISTOR, 10.OK OHMI1W OHMTTE
RS114A RESISTOR, DUAL, 5.OK OHM ALLIED 753-8059
SA1OIA ALTERNATOR, STAND-BY B&C BC41 0-1
HOUSING, PLASTICCONNECTOR B&C 12-003
TERMINAL, 1/4 INCH B&C 14-026
SA102A CONTROLLER, STBY ALTERNATOR B&C 8(=203-2
SA103A SWITCH, STBY ALT./EMERG BUS MOONEY 880052-531
SBIO1A C/B, SPEEDBRAKE KLIXON 727/-2-3
SB102A SWITCH, SPEEDBRAKE, YOKE PRECISE FLT 01265
SBi 03A RELAY, SPEEDBRAKE PRECISE FLT 01384
SB1 04A DIODE, SPEEDBRAKE 1 N2483/1.N5060
(ALT) dE 3720´•GE
SB1OSA MOTOR, SPEEDBRAKE PRECISE FLT 01532
SB1OGA SWITCH, SPEEDBRAKE PRECISE FLT 01505
SB1 07A SOLENOID, CLUTCH, SPEEDBRK PRECISE FLT 01678
SB1 08A S/B INTERFACE MOONEY 800314-501
SP1O1A SPEAKER, ALERT ARCHER 40-1 333C
SP1 02A SPEAKER, CABIN ARCHER 40-1 325
SP103A SONALERT MALLORY SC628
SW101 SWITCH MICRO 1 SE1-T
SW1 02 SWITCH CHERRY E51-50B
SW1 03 SWITCH MICRO V3-1
SW1 04 SWITCH MICRO DT-2R-47
SW1 04A SWITCH, UP-LIMTT SAINT ML-1409
SW1 05 SWITCH, DN-LIMIT MICRO 1 CH116-6
(ALT) OTTO CONT. P6-24014
SW1 06 SWITCH CARLING RCSI1-VBBOW
SW1 07 SWITCH MOONEY 88001 3-507
SW1 08 SWITCH C-H 8906K2875
SW1 09 SWITCH C-H SA1 RV20
(ALT) ALCO MPE-I 06F-C-22-9
SW110- SWITCH GRAYHILL 71AD3M32-2-AJN
SW111 SWITCH C-H 8906K4731
SW?12A SWITCH CARLING RASII-VBBOW

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28V S/N 25-2000 THRU 25-TEA
OLDWILLWAYNE
CODE DESCRIPTION VENDOR PART NO. NOTES

SW1 13A SWITCH MICRO 12NV-10

SWITCH, WHITE CAP MICRO 15PA90-8W
(AKT) MS27753-38
SW114A SWITCH C&K 71 01 K
SW11SA SWITCH NKK DLB241-W01-L3Cl
INCLUDES- BUTTONI LOCKRINGT AT506M/AT503MB
LOCKWASHER, HU< NUT (2)
(ALT) C-H SB1 DDX492-2
LOCK RING C-H 29-761
LOCK WASHER C-H 16-886
HD( NUT (2) C-H 15-966-6
(ALT TSCHUDIN 5041 02
LENS TSCHUDIN 464415
BULB TSCHUDIN 590002
SW1 16A SWITCH MOONEY 880012-501
SW1 17A SWITCH CARLING TILC64-i S-WHFN
SW118A SWITCH MOONEY 880062-501
SW11SA SWITCH CARLING TIGM64-1 S-WHEN

SW1 20A SWITCH MS3505&22

SW121A SWITCH dROljZEi 83-450-001
SW122A SWITCH CROUZET 83-452-504
SWI 23A SWITCH ALCO MPEI 06F
SW124A SWITCH
SW1 35A SWITCH N’KK MB2085SB1WD~ -EA
VR1OIA VARISTOR GE V47ZA05
WM1 01A WARNING, MASTER MICRO DSK-1 04-GYR
WM102A WARNING, MASTER MICRO
WS1OIA ALERT, STALL/GEAR WARN IAl 9500309000
(ALT) IAl 950051 9-000
WS1 03A SWITCH, STALL WARN MOONEY 800364-509
WT1OIA ANNUNCIATOR MOONEY 88004&501
WT1 02A ANNUNCIATOR MOONEY 88004&503
WT1 03A ANNUNCIATOR MOONEY 880048-507
WT1 04A ANNUNCIATOR MOONEY 880048-509

NOTES:

1. ALL P/N’s ARE ACCEPTABLE. SEE VENDOR INFORMATION FOR APPLICABLE CONFIGURATION.

2. 1 EACH MS35334-21 OR M2898 (ALLEN BRADLEY) INTERNAL TOOTH LOCKWASHER, REQUIRED

WITH EACH LIGHT, IF NOT SUPPIED BY SLOAN

3. SEAL BACK OF POTENTIOMETER WITH DOW CORNING #738 ELECTRICAL SEALANT AFTER
WIRES ARE SOLDERED TO TERMINALS.

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28V SM 25-2000 THRU 25-TEA
OLDWILLWAYNE

RESERVED FOR FUTURE ENTRIES

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28V S/N 25-2000 MRU 25TBA
OLDWILLWAYNE

RESERVED FOR FUTURE ENTRIES

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MOONEY AIRCRAFT CORPORATION
28V SM 25-2000 MRU 25-iBA
OLDWILLWAYNE

RESERVED FOR FUTURE ENTRIES

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OLDWILLWAYNE
9130-00
ELECTRICAL SYSTEM SCHEMATICS (SEE ENVELOPES)

FOR THE ELECTRICAL SYSTEM

SCHEMATICS, PLEASE SEE THE NEXT

PAGE FOR THE LOCATIONS OF THE

SCHEMATICS.

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 OLDWILLWAYNE
ELECTRIC~L SYSTEM SCHEMATICS

SCHEMATIC M20K EFFECTIVIPI BLOW-UP FICHE NO. ITEM NO.

800330 6: 25-0002 thru 25-0171 AMOB303 A

800330 Fl 25-0172 thru 25-0246 AMOB303 E

800330 F=2 25-0001, 25-0247 thru 25-0298 AMOB303

800330 F3 25-0299 thru 25-0446 AMOB303 M

800330 F4 25-0447 thru 25-0612 AMOB303 Q

800330 F5 25-0613 thru 25-0780 AMOB303 U

800330 F6 25-0781 thru 25-0841 AMOB304 A

800330 F7 25-0842 thru 25-0856 AMOB304 E

800330 F=8 25-0857 thru 25-0999 AMOB304

800350 Kl 2511000 thru 25-1199 AMOB304 M

(sheet 1 of 2)

800350 K1 251~000 thru 25-1199 AMOB304 Q

(sheet 2 of 2)

800350 M2 25-1200 thru 25-1224 AMOB305 A

(sheet 4 of 2)

800350 K2 25-1200 thru 25-122$ AMOB305 E

(sheet 2 of 2)

800263 Kl 25-1225 thru 25-1999 AMOB305

800383 K2 25-2001 thru 25-2012 AMOB305 M

800383 K3 25-2013 thru 25-2025 AMOB305 Q

800383 K4 25-2026 thru 25-TEA AMOB306 U