MOONEY M 20 SERIES

SERVICE MAINTENANCE
MANUAL
APPLICABLE TO THE FOLLOWING AIRCRAFT
MODEL SERIAL NUMBERS MODEL SERIAL NUMBERS
MARK 21 MASTER

1962-M20C S/N 2207,

1940 thru S/N 2209 thru 2255, 1963-M20D S/N 101 thru 200 and S/N 1
S/N 2296,
2257 thru and S/N
1852 1964-M20D \S/N 201 thru 251
1963-M20C S/N 2297 thru 2622, S/N 2208, and S/N 2256 1965-M20D S/N 252 thru 259
1964-M20C SjN 2623 thru 2741, S/N 2743 thru 2806 1966-M20D S/N 260 Only
1965-M20C S/N 2807 thru 3184 and S/N 2742
1966-M20C SJN 3185 thru 3466
1967-M20C S/N 670001 thru 670149

EXECUTIVE 21
SUPER 21

1964-M20E S/N 101 thru 399, 401 thru 469 1967-M20F S/N 660003, 660004, and
1965-M20E S/N 470 thru 831, and S/N 400 S/N 670001 thru 670539
1966-M20E S/N 832 thru 1308
1967-M20E SjN 670001 thru 670062

THIS REVISED EDITION SUPERSEDES ALL MOONEY M20C,D E ~1962-1965) SERVICE

gr MAINTENANCE MANUALS.

PART NUMBERS AND STATION CAUOUTS IN THIS MANUAL MAY NOT APPLY TO ALL
MODELS.

ALL REFERENCES IN THIS MANUAL TO M20E MODEL AIRCRAFT ARE ALSO APPLICABLE
TO M20F MODEL AIRC~UFT UNLESS OTHERWISE NOTED.

A SIX-DIGIT SERIAL; NUMBER CODE WILL BE USED FOR ALL 1967 AND SUBSEQUENT M20
SERIES MODELS. CONSEQUENTLY, ALL FOUR-DIGIT (1962-1966) SERIAL NUMBER CALL-
OUTS M THIS MANUAL WITH "6 ON" DESIGNATIONS SHOULD BE UNDERSTOOD TO INCLUDE
ALL SUBSEQUENT FOUR-DIGIT AND SIX-DIGIT SERIAL NUMBERS FOR THE MODEL(S)
SPECIFIED.

MOONEY AIRCRAFT CORPORATION

P. O. BOX 72
KERRVILLE, TEXAS
18028
REVISED 3ULY1980

MANUAL NUMBER MAN 104

 LOC OF REVISED PAGES
INSERT LATEST REVISED PAGES--DESTROY SUPERSEDED PAGES.

DATE Of DATE OF
PAGE NUMBER LATEST REVISION PAGE NUMBER LATEST REVISION

i ii July 1980 6-1 6-2 May 1979

iii November 1966 6-3 6-4 November 1966
vi vii November 1966 6-7 November 1966
1-5 1-6 November 1966 6-9 thru 6-14 November 1966
1-12 thru 1-14 November 1966 6-17thru 6-26 November 1966
1-15 Q 1-16 Added November 1966 6-33 6-34 AddedNovember 1966
2-1 November 1966 1-3 thru 7-8 july 1980
2-3 November 1966 7-11 July 1980
2-3A Added November 1966 8-1 November 1966
2-3B Added November 1966 8-9 November 1966
2-a November 1966 8-22 thru 8-24 November 1966
2-1 November 1966 8-25 8-26 Added November 1966
2-8 November 1966 8-27 thru 8-36 November 1966
2-11 October 1975 9-2 thru 9-4 November 1966
2-12 thru 2-14 July 1980 10-3 10-4 November 1966
2-15 Added October 1975 10-5 October 1975
3-1 November 1966 10-7 November 1966
3-2 July 1980 100-HOURINSPECTION GUIDE
4-1 thru 4-3 November 1966 SSEET 1 Novemder 1966
4-5 %4,6 Added November 1966 11-3 November 1966
5-1 thru 5-4 November 1966
5-6 November 1966
5-9 November 1966
5-10 November 1966
5-14 November 1966
5-15 5-16 October 1912
5-17 May 1919
5-19 thru 5-22 November 1966
5-23 5-24 October 1915
5-25 thru 5-30 November 1966

*THE ASTERISK INDICATES PAGES REVISED, ADDED, OR DELETED BY THE

CURRENT REVISION.

ADDITIONAL COPIES OR CURRENT REVISIONS OF THIS PUBLICATION MAY BE

PURCHASED FROM YOUR LOCP;L MOONEY MARKETING OR SERVICE CENTER
 TABLE OF CONTENTS
SECTION PAGE

I. INTRODUCTION.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .~. . . . . . . . . . . . . . . . . . . . . . . . . 1-1

A. GENERAL.. . . . . . . . . . . . . . . . .,. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1

B. SCOPE OF MANUAL.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1
C. DESCRIPTION.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .:. . . . . . . . . . . . . . . . . . . . . . . . 1-1
D. SPECIFICATIONS OUTLINE.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-4

11. HANDLING AND SERV1CING.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1

A. GENERAL.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1
B. ACCESS PROVISIONS.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1
C. GROUND HANDLING.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1
1. Jocking.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1
2. Mooring 2-1
3. Towing 2-1
4. Leveling 2;3
5. Weight 8 balance 2-3
DI SERVICING.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4
1~ Fuel system............. 2-4
2. Engine lubricotion.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7
3. Brake sysrem.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7
4. Bortery. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7
5. Induction sysrem.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7
6. Vacuum step system.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7
E. LtlBRICATION.. . . . . . . . . . . ~. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7
F. EXTERIOR AND INTERIOR CARE.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9

111. POWER PLANT.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1

A, GENE RAL.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1

B. TROUBLE SHOOTING.. . . . . . . . . . .~. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1
C. )NDUCT1ON AIR FILTER CARE.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1
D. ENGINE R EMOVAL.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1
E. PROPELLER REMOVAL.. ,. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-2
F. INSTALLATION OF ENGINE.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-2
G. INSTALLATION OF PR´•OPELLER.............................................................................. 3-2
H. ENGINE CONTROL AD~USTMENTS............................................................................ 3-2

IV, STRUCTUR E.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ~. 4-1

A. 4-1
B. REMOVAL OF WING.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1
1. Removal of wing.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1
2. Installation of wing.. . . . . ,. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-2

V. LANDING GEAR AND BRAKE SYSTEM 5-1

A. GENE RAL.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1

B. REMOVAL OF LANDING GEARS’.............................................................................. 5-1
i. Main gear. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1
2. Nose geor. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1
C. REMOVAL AND DISASSEMBLY OF SHOCK D iSCS...................´•..............~................. 5-3
D. REASSEMBLY AND INSTALLATION OF LANDING GEAR..................................... 5-3
1, Main geor. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-3
2. Nose geor. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ~. . . . . . . . . . . . . . . . . . . . . . . . . . 5-3
E. BRAKE AND WHEEL MAINTENANCE........................................................................ 5-6
1. Blake lining inspection and ~eplacement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-6
2. Brake bleeding.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-15
3. Wheel assembly inspection.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-15

REVISED NOVEMBER 1966 iii

SECTION PAGE

F. LANDING GEAR RIGGING PROCEDURE 5-15

1. Rigging instructions 5-15
2. Inspection of preload 5-16
3. Adiustment of prelood 5-17
G. INSPECT1ON OF LANDING GEAR SHOCK ABSORBER- 5-20
1. Rubberdiscs 5-20
2. Collars and bolts 5-20
3. Nose gear snubber 5-20
H. ELECTRIC GEAR SYSTEM (OPTIONAL) 5-23
1. Operation 5-23
2. Manual operation of electric gear 5-23
3. Gear inspection 5-23
4. Electric gear rigging procedure 5-24

VI. CONTROL SYSTEMS 6-1

A. GENERAL 6-1
B. REMOVAL AND INSTALLATION 6-1
1. Ailerons 6-1
2. Rudder 6-1
3. Elevators 6-1
4. Flaps 6-1
C. CONTROL SURFACE BALANCE DATA 6-2
D. RIGGINGAND ADJUSTMENT 6-2
i. Aileron rigging and adiustment 6-2
2. Trim rigging and odiustment 6-3
3. Flap rigging and adiustment 6-3
4. Rudder rigging and adiustment 6-3
5. Elevator rigging and adiustment 6-4
6. Trailing edgetrimming 6-4
7. Hydraulic flap bleeding 6-4
E. CONTROL TRAVEL AND RIGGING SPECIFICATIONS 6-7
F. POSITIVE CONTROL SYSTEM. 6-17
1. Introduction 6-17
2. System description 6-17
3 Ground test procedure .,....,.._
6-18
Roll,/yaw system 6-21
5. Operating instructions and flight test.. ........._.,
6-22
6. Emergency procedures ...,.....,_
6-22
7 Ma r.tenance 6-23
8. ’:ouble shooting 6-23
9 T´•~sSie shooting tests 6-25

Vli. FUELSYSTEM 7-1

A. GENERAL 7-1
B. TROUBLE SHOOTING 7-1
C. REMOVAL AND INSTALLATION OF FUEL PUMPS 7-2
Electric fuel pump removal 7-2
2. Electric fuel pumpremoval 7-2
3. Installation of electric fuel pump. 7-2
4. Engine-driven fuel pump 7-2
D. REMOVAL AND INSTALLATlaN OF FUEL SELECTOR VALVE. 7-2
E. FIELD REPAIR OF FUEL TANi;S 7-3
i. General 7-3
2. Approved materials 7-3
3. Handling and mixing sealant 7-4
4. Sealantappjication instructions 7-5
5. Description of leaks 7-8
6. Leak detection 7-8
7. Leakrepairprocedure. 7-11
Vllt. ELECTRICAL 8-1

A. GENER4L.. . . . . . . . .~. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ,. . . 8-1

B. TROUBLE 8-1
7. Electrical switches and circuit breakers 8-1
2. Batter . . . . . . .´•. . . . . . . . . . . . . . . . ;. . . . . . . . . . ,. . . . . . . . . . . . . . . . . . . . . . . . . 8-1
3. Battery charging system.. . . . . . . . . . . . . . .,. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-2
4. Voltage regula´•tor~.-.,. . . . . . . . . . . . . . . . . . . . . . . . . . . . . ,. . . . . . . . . . . . . . . . . . . 8-2

IX. INSTRUMENTS 9-1

A. GENERAL.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9-1
B. TROUBLE SHOOTING.. . . . :. . . . . . . . . . . .~. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9-1

X. INSP ECTI 10-1

A. 10-1
8. PREFLIGHT INSPECTIONS.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-1
C. 25-HOUR INSP ECTIONS.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .~. . . . 10-2
D. 50-HOUR INSPECT1ONS.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-3
E. 100-HOUR .INSPECTIONS.. . . . . . . . . . . . . . . . . . . ;. . . . . . . . . . . . . . . . ~. . . . . . . . . . . 10-4
F. OVER-LIMITS INSPECTIONS.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ~. . . . . . . . 10-4
G. POST INSPECTION 10-4
H. ELECTRIC GEAR INSPECTION (OPTIONAL INSTALLAT.ION)...................... 10-5

X1. PAINTING AND PREVENTION OF CORROSION......................................................~....... 11-1

A. GENERAL.. . . . . . . . . . ~. . . . .´•. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17-1

B. PAINTING.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11-1
1. Materia Is.......,.., 1:1-1
2. Procedures.,. . . ,. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17-2
C. CORROSION DETECTION PREVENTION................................................ 11-4
1. Types of cot´•rosion.. . . . . . . . . . . . . . . . . . . ,. . . . . . . . . . . . . ,. . . . . . . . . . . . . . . . 11-4
2. Hints on preventing corros ion.. . . . . . . . . . . . . . . . . . . . . . ,. . . . . . . . . . . . . . . . . 11-4
3. Zinc chromare. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ,. . . . . . . . 11-4

APPENDIX

Tool and equipment list

Four-to-six digit cross-reference index
Mooney technical publications list
 INDEX OF ILLUSTRATIONS

FIGURE TITLE PAGE

1-7 M20C (1 962-1964) TH R E E V1 EW 1-7

I-1A M20D (1963-1964) THREE VIEW--..´•´•´•´•´•´•.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-8
1-1B M20E (f 964-1965) THREE VIEW ’1-9
7-7C M20C (1965) THREE VIEW 1-10
l-1D M20D (1965’) THREE VIEW 1-1’1
7-7E M20C (7 966 8 ON) TH RE E VI EW...................... 1-12
~r-7 F M20D (1966 8 ON) TH R E E V I EW.....~..... 1-13
M20E (1966 8 ON) THREE XIEW.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-14
7-1H M20F (7967 8 ON) THREE VIEW.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-15
2-1 2-2
2-2 LEVELING.. . . . . . . ~. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-2
23 PLUMBING.. . . . . . ~. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3
2-3A WEIGHT 8 BALANCE COMPUTATION (M20C,D,&E)............................................ 2-3A
2-38 WEIGHT 8 BALANCE COMPUTATION (M20F).....~............................................... 238
2-4 FUEL SELECTOR VALVE ASSEMBLY.................................................................. 2-5
2-5 Oil DIPSTICK ACCESS-.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . :. . . . . . . . . . . . . . ~2-5
26 Oil QUICK DRAIN 2-6
2-7 011 SCREEN STRAINER LOCATIONS................................................................... 2-6
2-8 VACUUM STEP SYSTEM INSTALLATION..............................................,.............. 2-8
2-9 LUBRICATION DIAGRAM 2-11
3-1 COWL FLAP OPEN~NG.. . . . . . . ,. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-3
4-1 W ING AND FCIS E LAGE MATING D IAGRAM 4-3
4-2 WING SKIN CHART.. 4-4
43 TA 1L S KIN CHA RTS 4-5
4-4 FUSELAGE SKIN CHARTS 4-6
5-7 GEAR R ETRACTION SPRING REMOVA L............................................................. 5-2
5-2 NOSE GEAR SHOCK 31SC REPLACEMENT TOOL APPLICATION................. 5-4
5-3 MAIN GEAR SHOCK DISC REPLACEMENT TOOL APPLICATION 5-5
5-4 NOSE GEAR DOOR RIGGING DIAGRAM;............................................................... 5-7
3-5 BRAKE CYLINDER ASSEMBLY 5-9
5-6 WHE EL ASSEMBLY CHART 5-1 0
5-7 HYD RAULIC BRAKE MASTER CYLIND ER ASS EMBLY..........................~........... 5-1 1
5-8 PARKING BRAKE VALVE ASSEMBLY 5-12
5-9 PARKING BRAKE VALVE ASSEMBLY (ALTERNATE) 5-13
5-10 GEAR RIGGING DIAGRAM 5-14
5-11 TORQUE WRENCH APPLICATION DIAGRAM 5-19
5-12 LAND ING GEAR SHOCK D ISCS INSP ECTION D IAGRAM.................................... 5-21
5-13 LANDING GEAR SHOCK D~ISCS INSPECTION DIAGRAM (1966) M20C 8 E...... 5-22
5-14 ELECTRIC GEAR RIGGING COMPONENT 5-24
5-15 SAFETY SWITCH AND EMERGENCY GEAR CRANK INSTALLATION´•..´•.´•´•--´•-- 5-25
5-76 ELECTRIC GEAR RETRACTION SYSTEM INSTALLATION.............................. 5-26
5-17 ELECTRIC GEAR \YIR ING SCH EMATIC (1 965).-.-............-..........................~......... 5-27
5-7 8 ELECTRIC GEAR WIRING SCH EMATIC (1 966).................,................................... 5-28
5-79 ELECTRIC GEAR WIRING SCHEMATIC (1 967)...........................................:.......... 5-29
6-1 CONTROL SURFACE BALANCING 6-2
6-2 TRAILING EDGE TRIMMING DIAGRAMS-.- - . - -´•´•- -´•- .´•-´•- ´•´•´•- -´•´•´•´•- - -´•´•-´•- ´•´•-´•-´•´•´•- - -´•´•-´• 6-5
63 APPLICATION OF TRAILING EDGE TRIMMING VICE-GRIP PLIARS 6-6
6-4 CONTROL TRAVEL ~iGS.. . . . . . . . . . ,. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-8
6-5 RUDDER CONTROL SYSTEM INSTALLATION 6-9
6-6 ELEVATOR CONTROL SYSTEM INSTALLATION 6-10
6-7 AI1EROA CONTROL SYSTEM INSTALLATION-.................................................. 6-11
6-8 TRIM CONTROL SYSTEM INSTALLATIOU........................................................... 6-12
6-9 TRIM CONTROL ACTUATOR ASSEMBLY 6-13
6-10 FLAP CONTROL SYSTEM INSTALLATION 6-14
6-11 FLAP PUMP AND VALVE ASSEMBLY.....................,.............................................. 6-15
0-12 FLAP CYLINDER ASSEMBLY 6-16
6-13 CUTOFF VALVE OPERATING CHECK DIAGRAM.,.............................................. 6-19

vi
REYISED NOYEMBER 1966
 FIGURE TITLE PAGE

6-14 PILOT VALVE OPERATING CHECK DIAGRAM.................................................... 6-20

6-15 PRIMARY VACUUM READING DIAGRAM (1965 1966 MODELS)...................... 6-20
6-15A GYRO ROTOR SPEED ADJUSTMENT (1965 1966 MODELS)............................ 6-21
6-16 RATE GYRO VALVE CENTERING DIAGRAM (1965 1966 MODELS) 6-22
6-17 POSITIVE CONTROL SYSTEM INSTALLATION (8 SHEETS).............................. 6-27
7-’1 TANK SEALANT APPLICATION DIAGRAM...........-..............................................´• 7-6
7-2 FUEL LEAK CLASSIFICATION DIAGRAM............................................................´• 7-9
7-3 TANK AREAS WHERE FUEL LEAKS CONSTITUTE A FLIGHT HAZARD....... 7-10
7-4 FUEL TANK -LEAK DETECTION DIAGRAM 7-12
8-1 VO LTAGE R EGO L;4TO R S ETT1N G CHA RT.. 8-4
8-2 ELECTRICAL SYSTEM DIAGRAM (1962 M20Cr..................................................... 8-11
8-3 ELECTRICAL SYSTEM DIAGRAM (1963 M20C)..........................................1.......... 8-12
8-4 ELECTRICAL SYSTEM DIAGRAM (1963 M20b) 8-’13
8-5 ELECTRICAL SYSTEM DIAGRAM (1964 8-14
8-6 ELECTRICAL DIAGRAM 11964 M20C) 8-15-
8-7 ELECTRICAL SYSTEM DIAGRAM 11964 8--16
8-8 ELECTRICAL SYSTEM DIAGRAM (1964 M20E)....~................................................ 8-17
8-3 ELECTRICAL SYSTEM DIAGRAM (1954 M20E).......:.............................................. 8-1e
8-10 ELECTRICAL SYSTEM DIAGRAM 11965 M20C) 8-19
8-11 ELECTRICAL SYSTEM DIAGRAM 11965 M20D) 8-20
8-12 ELECTRICAL SYSTEM DIAGRAM i1965 hn~CE) 8-21
8-13 ELECTRICAL SYSTEM DIAGRAM i1966 M20C) 8-22
8-14 ELECTRICAL SYSTEM DIAGRAM 11966 ON M200).......................................... 8-23
8-15 ELECTRICAL SYSTEM DIAGRAM (1966 M20E).................................................... 8-24
8-16 ELECTRICAL SYSTEM DIAGRAM (1967 M20C&E)................................................ 8-24A
8-17 ELECTRICAL SYSTEM DIAGRAM (1967 M20F).............~...................................... 8-30
10-i ACCESS PANEL REMOVAL DIAGRAM (’100-HOUR INSPECTrON).................... 10-7
10-2 POWER BOOST DOOR SEAL INSPECTION D IAGRAM........................................ 10-8

LIST OF TABLES

TABLE TITLE PAGE

1 ENGINE AND PROPELLER SPECI FICATIONS..................................................... i-6

2 POSITIVE CONTROL SYSTEM TROUBLE SHOOTING 6-23
3 FUEL SYSTEM TROUBLE SHOOT;NG..... 7-1
3 TANK SEALANT APPLICATION LIFE CURING TIME.................................... 7-4
5 HYDROMETER READING VS. BATTERY CHARGE PERCENT 83
6 ELECTRICAL SYSTEM TROU BLE SHOOT ING 8-5
7 INSTRUMENT TROUBLE SHOOTING 9-2
8 EXTERIOR PAINT CHART-´•----------´•-.--.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11-3

REVISED NOVEMBER 19~6 vii

 MOONEY AIRCRAFT

TWELVE-MONTlH
c~

WARRANTY

Company warrants airplane manufactured by it to be free from defects in material and work-
each new

manshiD under normal and service, Drovidsd, however. that this warranty is limited to making good
use

at Company’s
factory any oan or ~ans hereoF which shall, within 12 months from date of original Air-
worthiness certificate, be returnkr to Com_oany with transportation charges prepaid, and which upon
Company’s examination shall disclose to Company’s satisfaction to have been thus defective; this warranty
being expressly in lieu of an other warranties or implied and all other obligations or liabilitia~

on the part of the Com_Dany, and Com~any neither assumes nor authorizes any other person to assume for
it any other liability in connection with the sale of its airplanes. Ihis warranty shall no: apply to any air-
plane which shall have been repaired or altered outside of Com_oany’s ~ctory which in the judgment of
Company affects the airplane’s ~ability or reliability, nor which in the ooinion of Company has been sub-
Ject misuse, accident. Zcpipment and accessories manufactured by seller
to
negligen~e or not are guzr-
anteed only to the extent of the original manufacturer’s

YIZ1 REYISED NOVEMBER 1966

 SECTION

INTRODUCTION
 SEC~ION I
1NTRODUCTION

A~

cr~
This manual contains service and maintenance information pertaining to all M20 series aircraft
-r

listed on the title page.. All affected aircraftare identified by year of manufacture, model designation,
and serial number ~ouning. When service and maintenance instructions in the body of the manual
refer to a sDecific year and model, applicability of dtm information to an individual aircraft may be
determined dy referring to the title page serial-number listing.
If it becomes necessary to consult the factory concerning a specific maimenance problem, contact
the Customer Service Department, Mooney Aircraft, inc., Kerrville, Texas, 78028. Telephone, Area
Code 5~2, 257-4043.. When ~eryin,o the factory or forwarding information, the model designation,
serial number, and re~istration number of the aircraft concerned shouldbefurnished. Total in-
service rime for the item in c~estion should also be furnished,

Spare pans are available throu~ the ~Ylooney distributor in your area. Consult the Mooney Parts
Catalog for the latest pan numbers and the correct ordering procedure. Mooney manufactured parts
were changed from a four digit to a six digit numbering system in Enarch of 1962. New pans may
be ordered by either their four or six digit numbers. A six-to-four digit cross reference index is
included in the aDpendix.

9. SCOPE

For ready reference,this manual has been divided into eleven sections, each dealing with a major
system group
or of comionents. Sections Ii and X comprisetheservice porrian oithehzndbook;
the remaining sections are devoted to maintenance. Service instructions include ground handling,
servicing, and periodic inspection. Maintenulce instructions include trouble shooting, corrective
maintenance and functional testing, and removal and installation of assemblies andcomoonents.
Only qualified personnel should _oerform inspections and maintenance procedures described in this
manual.

Basic information in this manual is limited to service anh maintenance procedures peculiar to the
aircraft concPJ~ed; no attempt is made to cover standard shop procedures. Refer to the applicable
Owner’s Manual for oDerating details. For niore complete maintenance infonnation concerning en-
~nes, oro_Dellers, and other vendor items, the manufacturer’s handbooks should be consulted. An
annual service information subscription or a complete back-issue file of Mooney service information
is available from your local Mooneydistributor.

C. IIESCilIPTIO~

Mooney X1120 series aircraft are desi~ed and manufactured as high performance, low maintenance,
versatile aircraft for the oersonal and business aviation field.

The M20 series aircraft discussed in this manu~al are four-place all-metal low-wing aircraft. All
models are powered by Lycoming engines. RefertoTzble 1 for propeller and governor specifications.

Conventional rudder Dodals and control wheels are provided. Entrance to the cabin is made through
the cabin door locste~ on the right side of the airplane. The from seats fold forward to allow passen-
ger enrry to the rearsezts. Theba~,oagetompanment is located aft of the rear seat and has an access
door on the right side of the aircraft. During flight, the baggage compamment is accessible from
the rear seat.

1-1
 1. ENCINEII

a. An M20C aircraft are powered by a Lyc~ming_O-360-A1D engine equip_Ded with a constam-speed

propeller,

b, M20D aircraft (1963) are e~ipped with a Lycoming 0-360-AlD engine~having a governor control

c. M20D aircraft (1964 thru 1966) are ec~ip_oed with a Lycoming 0-360-A2D enginehaving a fixed-
~c. pitch propeller. The 0-360-,41D engine may be installed as oDtiondl
d. Lycoming 0-360-A1D and 0-360-A2D engines are both rated I-~0 hp at 270~rpm.

e. All M20E aircraft are powered by a Lycoming 10-360-.4W engine rated 200 hp at 27(30 rpm.

f. An M20E aircraft are orovided with a ram induction air source. Filtered air
is used during takeoff, ~andLng,
and under dusty conditions. Air source selection is made by man-
ual control, An emergency fn_c~uction air source is provided; in ti,e event of filter icing, a spring-
loaded valve, located behind the filter inside the engine compartment, will open automatically to
maintain air flow;o the engine. To Drevent ice iorma~fon in the induction system, the power boost
control must be set for ffltlred air ii icing conditions are present,

2. PROPELLER

Those models with constant-s_oeed propellers have low pitch setting capabilities for maximum take-
on’ power. Propeller pitch is regulated by an engine-mounted governor that insures maximum power
efficiency at cruising speeds, Engine oil pressure actuates the pitch changing mechanism.
3. WZNG

All M20 series aircraft have laminar-flow wings. Laminar air flow over the wines is insured by
I’lush rivets attaching the leading edge or’the "wraD-around" wing skins. Wing construction features
multiple ribs attached to main and stub s_Dars incorPorating aluminum spar caps.

4, ~TSEL4GE

The cabin suDersuucmre is built of 4130 ntb~ilar steel and covered with non-structural aluminum
skins. The taTZ section (baggage com_oanmem and aftstruoture) has a stressed-skin
semi-monoco$re
design. Aluminum skins are riveted to heat-treated alumimun bulkheads with extruded aluminum
stringers reinforcing the tail cone sectioh

5, EMPENNAC~

The empennage is constructed on qDtically aligned jigs to insure uniformity and close tolerance fit
for all parts. Construction is of sheet metal, riveted to formed ribs and s_Dars. To provide srabi-
lizer trim, the entire empennage pivots around the tail cone attachment points.

6. LANI~INCGEAR

The landing gear is unicpe in ~hat it is manually retracted by the pilot. Gear-assist s_Drings in the
wings, aided by bungee springs in the fuselage, make manual o_Deration of the gear cIuite simple.
Gear-mounted rubber discs are used for shock absorption. Grease fittings are provided at important
lubrication points on the landing gear, The standard M20D has a fixed landing gear, but can be con-
verted to a retractable gear identical to the M20C gear system. Electrically ooerated gear retrac-

ing systems are optional for all models.

7. ~RAKESYSTEM

aydraulic disc brakes are featured on all models. The hydraulic fluid reservoir is located in the
inside upper left-hand area of the firewall. Toe-actuated rudder_oedals operate the left and right
main gear brakes independently. Dual brake systems are optional for all models.

1-2
 8. FL3GHT CONTROLS

The ailerons, elevators, and rudder are of an all-metal jig-built construction incorporating hinges of
machined extrusions, Push-pulltubes, rather than the conventional cable systems, are used to actu-
ate the control surfaces.

9. FMPSYSTEM

The wide-span all-metal flaps are hydraulically controlled by

a hand-operated pump which actuates

a hydraulic cylinder., it relief valve is provided which releases hydraulic pressure at a slow rate
as retraction springs (or air pressure) raise the naps. Ihehydra~lic fluid reservoir is common
to both the brake and flap systems. Maintenance of the fla_o system is similar to the brake system.

10, TRIMSYSTEM

X small control wheel on the floor between the front seats actuates the adjustable stabilizer via a
~ar reduction box and torque tube Linkage which actuates the empennage jack screw. The torcIue
tubes are connected by universal joints and are supported by-formica guide blocks.

11. NELSESTEM

The fuel system consists of integral fuel tanks located in the front inboard portion of each wing.
These tanks are Formed by setling off a portion of the wing through the use of a special com- sealir;g
pound. Fuel is fed from the wing, to a tank selector valve, on to an electric boost pump and then
to the engine-driven iuel_oumo and fuel injector or carburetor.

12. mSTEM

The electrical system is provided with a 50-amp 12-volt generator and a 3S-amp/hour battery. AII
electrical systems can be turned off with the master switch which actuates a relay located at the
battery, Circuit breakers are provided on the lower right side of the instrument panel. Standard
equipment includes a 250-watt landing light, navigation lights, interior lights, an electric starter,
gear and stall warning systems, and an electric boost pump.

13, INSIlltTMENT Pi\NEL

The instrument panel has been designed to provide functional location of all flight, radio, and engine
instrument grouDs, The flight instiumems onthepilois side are installed in a rubber shock-mounted
Danel to reduce;ibrztion transmission to the instruments.

14. HEATING, VENTIL~TION. AND DEFROSTING mSTFMS

Cabin heat is obtained from a muff which surrounds the engine exhaust manifold. From the muff a
flexible duct transmits heated air to a junction box zft of the firewall on the co-pilors side. Cold
air is also ducted to this junction box from the flush air scoop on the right side of the airplane. The
hot and col~ air entering the junction box can be controlled to provide the combination required for
the desired tem_Derature. From the junction box, air is ducted to the piler and co-pilot’s feet, wind-
shield defroster, and rear cabin.

15, SZ.iiTS

X11 seat backs are contour formed. The seats are padded with plastic polyfoam and covered with

durable u_dnolstery. The from seats have a three-position reclining adjustment and are adjustable
fore and air on the floorboard seat rails. The rear seat back may he removed to provide a larger
cargo area.

1-3
D. SPECIFICATIONS OUTLINE

1. ~NGINE

a, M20C:

Model 0-360-A1D
F4A Type Certificate 286
Rated Horsepower and Speed (RPM) 280 at 2700
ProDeller Drive Ratio 1:1
ProDeller Shaft Rotation Clockwise
Bore (Inches) 5.125
Stroke (Inches) 4.375
(Cubic Inches) 361
ComDression Ratio 8.50:1
(witfi Starter and Generator) 284
Dimensions: Height(Inches) 24.59
(Incl?es)
Width 33.52
Length (Inches) 29.81
Oil Sum_b Capacity (Quarts) 8
Fuel Oc;ane<Aviation grade) 91/96
Magnetos (Bendix) S4LN-204 (Right)
S4LN-200 (Left)
Tachometer Drive (Rztio to Crznkshaft) 0.5:1
Rotation Clockwise
Starter Drive (Ratio to Crznkshaic at aendiu
Drive) 13.55:1 (Coumerclockwise)
Starter(Geared 3.38:1) 12 Volt
Generator Drive (Ratio to Crankshaic) 1.91:1
Generator @elco-Remy, 12 v) 50 AMP
A-N Vacuum Pum_n Drive (Ratio to Crznkshzit zndRotation) lSO:1 (Counterclockwise)
PrqDeller Governor Drive AN20010 (Type XX)
Ratio to Crankshzft and Rotation 866:1 (Clockwise)
fuel Pum_D AC (Type JT)

b. M20D: The 0-360-A2D Lycoming engine is basically the same as the 0-360-A1D engine ex-
ce~t that the 0-360-~2D engine has no constant-speed propeller governor.

c M20E:

Model I0-360-A1A
E~A Type Certificate 1E10
Rated Horsewwer and SDeed (RP~VI) 200 at 2700
ProDeller D;ive Ratio 1:I
Pro’beller Shaft Rotation Clockwise
Bore (Inches) 5.125
Stroke (Inches) 4.375
Disdacement (Cllbic Inches) 361
Com~ression Ratio 8.7:1
Dry Weight (witfi Starter and Generator) 323
Dimensions: Heighn(Inches) 26.61
Width (Inches) 34.25
29.81
Len,oth (Indhes)
RSA-5ADI
Fuellnjector (Bendix)
Order 1-3-2-4
Firing
25
Spark Occurance @egrees ETC)
0.028" to 0.080"
Valve Roc~4er Clearance (Ta_qDets Collapsed)
8
Oil Sump Capacity (Ouarts)
100/130
Fuel
Octane~(Aviarion Grade)
Magnetos (Beradix)
S4LN-204 (Right)
S´•ZLN-200 (Left)
Tachometer Drive (Rztio to Crznkshait) 0.5:1
Rotation Clockwise
Crankshaft ~endix Drive) I3.55:1 (Counterclockwise)
Starter Drive ~iiado to at

1-4
 Starter (Geared 3.38:1) 12 Volt
Generator Drive (Rado to Crankshaft) 2.50:1
Generator (Delco-Remy, 12 V) 50 AhlP
A-N Vacuum Pump Drive (Ratio to Crankshaf~ and Rotation) 1.30:1 (Counterclockwise)
Pro_Deller Governor Drive AS20010 (Type XX)
Ratio to Crankshaft and Rotation .Srib’:1 (Clockwise)
FuelPump AC(TypeJT)

2. OVER-ALL

Wing Span 35 ft. 3 ih

23 ft. 3 1/2 in.
Length (M20C,D&E)
Len~h (MZOF) 24 ft, 0 in.
Height 8 ft. 4 1/2 in.
Clearance (Prqoeller’lios) 9 3:’4 in. (Approx.)

3.
2, Standard X120C.S.&F
Type Manually Retracted
Tread 9 ft. 3/4 in,
Main Wheel Cleveland Air Products
Type
Main Tire 6 Pl)F,F100 x 6
Main Tire Pressure 30 pounds
Bra~te Type Cleveland Hydraulic
2luidRequired Hydraulic (MIL-0-5606 Red)
Cleveland Air Products
Nose Type
4
Ply, 5:00 X 5
Nose Tire (MZOC.D,&E)
6 Ply, 5:00 x 5
Nose Tire (120F)
Nose Tire Pressure 30 P3I
49 PSI
Nose Tire Pressure (5120F)
Electric gear retraction kits are available from Mooney distributors.

b, Standard M20D:

Type Fixed
Other specifications are same as M20C E aircraft. Retractable gear is optional on all
~v120D aircraft; conversion kits are available from Mooney distributors.

L1. F~TEL CAPACIIIES

M20C [1962-1963)
48 gallons total
M20D (1963)
48 galIons total
hi20C (1964 ON) 52,oaLZons total
M20D (1964 Oiu3 52,oallons total
52 gallons total
M20E (1964 Oh3
X120F 64 gallons total
(1967 0~3
5. WING

span 35 Ft. 0 in.

Length of Flap (Trailin,o Edge) 10 ft. 8 in.

Length of Aileron (Trailing Edge) 5 rt. 3 1/4 in.
omearzl (Lezdin,o Edge) 5"30 minutes
Incidence, 2"30 minutes
Airfoil Section at Root NXCA 63-215
Airfoil Section at Tip ~IEOC,D.&E) NACi\ 64-412
Airfoil Section at Tip (hP-GF~) NACX 64-412 ~lod.
wing Area 167 sq. fr.
Aileron Area 11.2 sq. ft.
Flap Area 17.2 so. ft.

6. EhlPE~TNACZ

Vertical Fin Area 7.9 sq´• ft,

Rudder Area (XIZOC.D,&E) 5.01 sq. ft.
Rudder Area (M20F) 6.23 so. ft.
21.5 sq. ft.
Horizontal Stabilizer Area
12.0 sq. it.
Elevator Area
1-5
REVISED NOVEMBER 1966
 TABLE 7 PROPELLER AND GOVERNOR SPECIFICATIONS

Std, for M20C Opt, far M20C Std. for M20C Opt. for M20C
1962-1963 1962-1963 1964 1964
s/lt 1940-2622 S~ 1940-2622 S/N 2623-2806 SM 2623-2806
Manufacturer Hartzell McCauley Har~ell NIcCauley
Type Constant Speed Speed
Constant Constant Speed Constant Speed
Hub RC--22YE;--1 2D3~C53-A HC-C2YI~--1A 21)34CS3--A
i4Eu 7666--2 743--8
Woodward: Hartzell: Woodward:
D--l~ (1940C-24MXC 210452 D--1’-6 (2623C"704C) 210452
o-la (2401(=-2622(3 H--l (2705C-2806C)
Blade Angle, Low 130 12.7" r 20 130 3 0’ ’,2.7" t 20
Blade Angle, High 290 i~ 20 27.50 I .050 290 z 20 27.50 1..050

Std. for M20C Sid, for M20C Std, for M20C Std, for M20C
1965 1966 1966 1967
SlN 2807-3184 S~ 3185-3230 SM 3231-3466 S~i 670001 g ON
Hartzelr Hartzell Hanzell Hartzell
~Spe Constant Speed Constant Speed Speed
Constant Constant Speed
Hub HC--C~YIC--IA HC-C2YIC-IA HC-C2YIC--1B HC- CZYK--1B
Blade 7666--2 7666--2 7666--2 1 7666--2
Prop. Governor Hartzell: r Har~ell: Haruell: Hartzell:
H-r H-l H--L
H--1L If--IL H--1L H--IL
Blade Angle. Low 130 I 0" 130 3 00 130 00 130 f 00
Blade ~ngle, High 290 20 29",’ 20 2P~ 20 290 20
Srd, for M20D Std, for M200 Opt, for M20D Opt, for M20D
1963 1964-1967 1964 1965 g ON
SM 303-200 Sntiol-z60 SM 201´•251 S/N 252 g ON
Manufacturer Hartzell ~cCauley Hartrell Haruell
Tgpe Constant Speed Fixed Pitch Constant Speed Constant Speed
Hnb lC173 HC-C1YIC--1A HC-CZY~--LB
Blade 7666--2 41FA74d0 1 7666--2 7666-2
Prop. Governor Hartzell: i I Hartzell: Hartzell:
0--1--4 (1011)-1230) 1 i I)--r--4(101D--123D) H~
D--16 (124D-220D) D--1--6 (1241)--2201)) H-rL
Blade Angle, Low 130 O0 130 00 130 00
Blade Angle. High 29" s~ 1 1 29"=20 290 r 20

Std, for M20E Std, for M20E Std, for M20E Std, for M20E
1964 1965 1966 1967
Si~ 101-169 s~ 470´•831 S~ 832-1308 SM 670001 g ON
Manufacturer Hartzell Haraell Hartzell Hartzell
h~pe Constant Speed Constant Speed Constant Speed Constant Speed
Hub HC--7-YK--1A CHC--CZYK--1A HC--C?YIC--I HC--C’YK--I
HC--C2YK--1
Alternate
Blade 7666-2 17666--2 7666--2 7666--2
Prop. Governor Hartzell: I Hartzell: Hattzell:
I)--16 (102E--303E)I H--l H--l H--l’
H-2 (304E--169E) H--IE
Blade Angle. Ipw 140 I 00 14" ~:00 rC C oO 140 i´• oO
Blade Angle. High 1 2p’ i:30 29U ~:2C 7-90 _
20 soO i 7’C

Srd,forM20F 1967
Sr~ 660003
S.iN 670001 g CN

Manufacturer f Hartzell
~-pe Constant Speed
Hut, HC--3YEi--1
Blade ;666--2
hop. Governor Hartzen:

H--1L
Blade Angle. Low ~O I OJ
?O
Blade Angle. High 19J r

REVISED NOVEMBER 1966

1-b
FIG1IRE 1-7 M20C (1962-1964) THREE V1

-c---------- It 9 -----r:

;1/
35 3

3C7~_

t-- 9

;----r

8’4f

1-7
 FIGURE l-1A M20D (1963-1964) THREE VIEW

Ooo_

1-8
FIGURE 1-1B M20E (1964-1965) THREE VIEW

1-3
 FIGURE l-1C M20C (1965) THREE VIEW

i
’3 7~1

1-10
FIGURE l-1D M20D (1965) THREE VIEW

I\
p

1-11
FIGURE l-1E M20C (1966 a ON) THREE VIEW

I-,
I

1-12 REVISED NOVEMBER 196S

FIGL’RE 7-1F M200 (1966 ON) THREE VIEW

i I

REVISED NOVEMBER 19L6 1-13

FIGURE I-1G M20E (1966 ON) THREE VIEW

~1 n

REVISED NOVEMBER 1966

1-14
FIGURE l-1H M20F (1967 a ON) THREE VIEW

35’3"

Et,,~ I
24"

i
13

9~-"

REVISED NOVEMBER 1966 1-15

 SHOP NOTES

1-16
 SECTION

HAND LING AND

SERVICING
 SECTION II
HANDLING SERVICING

A. GENERAL

This section provides ground handling and servicing instructions.

B. ACCESS PROVISIO~S

Figure 10-1 shows the location of the access panels and plates that provide access for purposes of
service and maintenance.

C. HANI)L3h~G

The following instructions are recommended to avoid damage to the airplane during ground opera-
tions. If improperly handled, extensive damage to the airplane and its equipment may result. The
airplane may be taxied as required for normal maneuvers. Brakes or rudder pedals may be used
for turning. If a towbar is used, one man may move the airplane providing it is on a fairly smooth
level surface. Points where pushing the airplane are permitted are leading edge of the wing, wing
tips, and the inboard position of the propeller blades adjacent to the propeller hub,

i. Jacking

When it is desired to raise the airplane off the ground to check operation of the landing gear,
the following jacking procedure is recommended. By using jackpoints provided outboard of
each main gear (Figure 2-1), it is possible to use standard aircraft jacks to raise the main gear
off the ground. A yoke-frame jack may be used under the propeller. Care must be taken not to
damage the pro_Deller or spinner. The nose may also be raised by anchoring the tail skid tfe-
down ring to a fixed point in the shop floor while jacking the aircraft at the wing hoist points.

2. hiooring

When mooring aircraft,the following method is recommended. Place chocks fore and aft of
each main wheel. Stakes may then be driven in the ground outboard of each main gear, approx-
imately three feet, and at the tail skid location. Tie down rings are provided, two feet outboard
of each main gear, at the jack point. A tiedown ring is also provided at the tail skid location.

3. Towing

A suitable towbar is provided as standard ec(uipment with each airplane. The lower bar of the
towbar is placed t~rough the gear spindle upper crossmember. Care must be exercised that the
nose gear is notrotatedpastits normalswivel angels. Towing with a tractor or by other mechani-
cai means is not recommended.

Note: See that parking brake is off before towing airplane.

REVISED NOVEMBER 1966 2-1

 FIGURE 2-1 JACKING

~ACI< POINT

TII DOWN RING

FIGURE 2-2 LEVELING

a~7

~i slst~

’"~c:

t:?-~ r’i
:i-";:""’"

2-2
FIGURE 2-3 PLUMBING

:r
s~T

~I´• i

r~

ii
3.
Pi´•´•
I

L;:
-~1
c~

4. Leveling
splice skin above
is determined by placing a spirit level on the tail cone
Longitudinal leveling be made by increasing or decreasing air pres-
the access door. (Figure 2-2) Adjustments may
tire when the airplane is on the ground or on a set of scales for weighing.
sure in the nose wheel

Balance (Fuel and Oil Drained)

5. ~Teight
List in the Weight Balance Data form or Weight
Check installed ec~ioment using the Ecluipment
s~ale in front of each of the three wheels. Place a ramp on each
Balance Record. Position a the air-
scales. Remove the ramps and proceed to ~Yeigh
scale and tow the alcr~fr up onto the
bob from centerline of the nose gear attach
craft when level. Find the datum by dropping plumb
a

bolts (retracting axis) and then mark the floor (see Figure
2-3). Measure axle locations from
this mark (See Figure 2-3A or Figure 2-3B).
Record the weight at each urheel as shown in
in
Record the distances between points as shown
figure 2-3A and 2-3B. Total the weights. of the main wheels. Compute the CG’s Fus.
the CG forward
Figure 2-3A and 2-3B. ComPute Balance Record or
Sta. aft of datum. Post weight and CG in section III of Weight
empty
form.
equivalent‘tireight Balance Data

2-3
REVISED NOVEMBER 1966
FIGURE 2-3A WEIGHT BALANCE COMPUTATION (M20C,D,&E)

HORIZONTAL
DATUM
NOSE GEAR
TRUNION W~NT
STA O

~r?
n

ELst:L
WEIGHT

LEFTMAINWHEEL WmA
Wm/l
W W
N kYR NOSE WHEEL W,
W
MfL TOTAL WEIGHT Wt

a. CG Forwardof Main~heels:

LBS. LBS. IN.

X
Weight of Nose Distance Between Total Weight CG Forward of
Main and Nose Wheel of Aircraft Main Uheels
Axle Centers
(WN)
(LN/H) (WT) (LM)

b. CG AZt of Datum (Station Of:

IN.

Distance from Center Result of CG (FUS. STA.) Distance

Nose Gear Trunion to Computation Aft of Datum.
Center of Main W’heel Above (Empty Weight CG)
Axles (Horizontal)

(LM) (Ly~)

2-3A REWSED NOVEMBER 1966

 FIGURE 2-38 WEIGHT a BALANCE COMPUTATION (M20F)

BEfFPOINT BO-SIZONTAL
~OSE GEAfl IIATUMS~AO
TR~NION I:
S~A -j)

%1 C[C3

WEIGBT

11)5~
ii
LM,C~ ---L
tEFTMAINPTBEEL
W~
w, 1NYfi RIGHTMAINWBEEL

W
NOSE ~HEEL W,
M/t
TOTALWEIGHT W1

a CG Forward of Main Wheels:

LBS. IN. LBS. IN.

X
Weight of Nose Distance Between Total Weight CG Forward
Main and Nose Wheel of Aircraft of Main Wheels
Axle Centers

(Wu) (W,) (L.)

CG Aft of Datum (Station O):

IN. 5 N. IN. IN.

Distance from Center Distance from Result of CG (FUS. STA.)
Nose Gear Tnmion to Nose Gear Trunion Computation Distance Aft
Center of JIIain Wheel to Datum Above of Datum.
Axles (Horizontal) (Empty Weight CC)

Con.tant
(LM)
(L~) (LC/G)

REVISED NOVEMBER 1966 2-38

 D. SERVICISC

1~ FU~LSYSTEM
a. Fillingrheiuelr~nks(L964 bOS!

Each fuel tank has a ca_oacity of 26 t’S. gallons (32 gallons for M20F models)
wing integral
and is filling by flipping the filler cap latch up and turning it to release the
accessible for
cap. A vent is pro~ided at the outboard forward corner of the tank to compensate for fuel
expansion, depletion, and ove,nlow. A fuel sumr, drain is located on the inboard corner of
each wing tK~k. This is the lowest point of each f;el tank.
NOTE: Visual fuel level indicators at the 25 gallon level are installed in both tanks on Z~f?OF
models 5~ 670074 3i OS.

1962-63 MZOC 1963

B~ch wfng imegral fuel rank bar; a crpacj´• Q124 U.S. gallo~ and it acce~sihle Far iillfng
by lifting a door and removing the exoansion-type gas cap. A scuDDer-box drain is provided
to drain off any gasoline spilled outside the filler neck opening.

C~UTION: Aircraft and fuel seNice vehicle must be grounded when refueling the aircraft.
Ground servicing nozzle to aircraft wing. No smoking within SO ft. of aircraft
or vehicle.

b. Drainingfuelsystem
To drain fuel from the syst~n, disconnect fuel line at electric boost pump, attach another
Zlex line leadino to a drain barrel, and turn boost pump on. The fuel will be pumped out of
the ranks throuifh
the boost pump. Fuel tanks may also be siphoned as an alternate method.
Aircraft and barrel must be orcunded. Allow no smoking or open flame within 50 ft. of air-
craft. Fire extinguisher (foa~
type) should be immediately available.

c. Strainer removal

Remove and clean the following nrainers every 50 hours:

~SCOMTOR
(Located in the nose wheel well)
OILT
ELECTRIC BOOST PUMP 1963
(Loczted under floorboard)
FUEL-SEI~CTOR VALVE
(Located beneath the rloorboard
in the from portion of the cabin) j Figure 2-4.
All M20 series aircraft

d. Drainingselecrorvalveand fueltanksum_Ds

To check for water and sediment in the fuel system or to completely drain the fuel system,
the sumps may be drained as follows:

Wing Tanks: insert prong of Plastic cuD (suDolied with each aircraft) into the drain hole at
the rear inboard side of the fuel ranks an~ press upward.

Selector Valve: Pull ring adjacent to selector valve inside the cabin. Switch valve handle
to right and left tanks to drain resbective lines. On 1962-63 M2OC and 1963 N20D aircraft,
drain fuel selector valve on under side of fuselage using the plastic sampling cup.

2. ENGINE Lt’BRICXTION

a. Filling engine sum_o

Fill engine sum_r, (Figure 2-3) with lubricating oil specified on the lubrication chart
(Figure 2-9).
b. Draining enginesump
The engine sump can easily be drained by means of the oil quick drain that is installed on

each engine as standard (Figure 2-6).

2-4 REVISED NOVEMBER 1966

FIGURE 2-4 FUEL SELECTOR VALVE ASSEMBLY

;3i

~ss

STRAINER

Z~"ri:

FIGURE 2-5 OIL DIPSTICK ACCESS

F1

2-5
 FIGURE 2-6 OIL QUICK DRAIN (M20E)

-7

r~zl

~21
FIGURE 2-7 011 SCREEN SiRAINER LOCATIONS lM20E)

s´•~

´•i.

g
I: i´•

s~´•
~e :w

OIL PRESSURE SCREEN

THERMOSTATIC OIL COOLER
REAR VIEW OF ENGINE BY-PASS VALVE (REMOVE g
CLEAN EVERY 50 HOURS)

OIL SUCTION SCREEN

(REMOVE g CLEAN EVERY
so HOURS)

2-6
 c. Cleaning oilscreen strainers

Remove two strainers (Figure 2-7) and flush with kerosene every 50 hours or each time oil
is changed. (MZ0E&F)
3. BRAKESYSTEM

The brake cylinder reservoir must be filled with the brake fluid specified in Figure 2-9.
The reservoir fluid level should be checked at every 50-hour inspection and replenished as
necessary. After a periodic installation, the brakes require no adjustment during the serv-
ice life of the brake lining.

CAUTION: Do not fill reservoir while parking brake is set or when flaps are extended. (See
page 5-15 for brake bleeding procedure.]
4. BATTERY

Check battery fluid level and battery condition every 25 hours. Use only distilled water when
servicing; avoid comaminarion of cells.
5. INDUCTION SYSTEM

Check air filter visually at each pre-flight inspection. If cleaning is necessary, remove filter
and clean in accordance with Section III C. Check power boost door seal(MSOE&F).

6. VACtUM STEP SYSTEM (1965 Models and subsequent)

A vacuum servo will raise the stC~p when the engine is started and sufficient vacuum is Produced.
A spring will pull the step down when the engine is stopped and vacuum is relieved (Figure 2-8).

NOTE: To lubricate the step strut, spray a light coatof a Silicone-type lubricant on all four
sides of shaft. This substance will not attract dust or soil clothing.

E. LUBRICATION

Refer to Lubrication Diagram (Figure 2-9) for instructions regarding lubrication points, intervals,
and type of lubricant recommended. Crease finings are provided on the nose gear and main gear.
Bearings used in bell cranks, hinge points, and rod ends should be l;bricated periodically to prevent
corrosion. Avoid excessive application of lubricants. Excess lubricant onemerior surfacesof
bearings tends to attract dirt and grit and may lead to malfunction of the unit.

Where a reservoir is not a bearing, gpply the lubricant sparingly and wipe off ex-
provided around
cess. Remove wheel from the wheel hub and clean thoroughly with a suitable solvent. When
bearings
repacking with grease, be sure lubricant enters space between rollers and retainer ririg. Do not
pack grease into wheelhub. (See Fig~re 2-9 for recommended lubricant.)

Whenever specific instructions for lubrication of mechanisms are not available, observe the follow-
ing precautions:

I. Apply sparingly, never more than enough to coat bearing surfaces.

oil
2. At theregularinspection intervals, squeeze the magneto cam follower felts with the fingers.
If oil appears on fingers, do not add oil to the felts. If felt is dry, moisten with light oil. Be
careful not to add too much oil, because an excess will be thrown off during operation and will
cause pining and burning of magneto points.

Refer to Lycoming Service Instruction 1014 (latest revision) for engine oil specifications.

REVISED NOVEMBER 1966 2-7

 FIGURE 2-8 VACUUM STEP SYSTEM INSTALLATION
(1965 MODELS AND SUBSEQUENT)

AN 364- 524A N1/7-

11691 WASWER CZ,
ANJ64-S~4A NUT
17691 H’AS~IER
SEI~YO 11660-/ STRRP
AN 3-ba tiYXrr
PoLLEY ASS)I
AN960-/0 WAdl´•ltX

aNSsr-/o3za Nor
AN 5-SA BOLT

STRING T/E EiVD C4" TUBE

NAS 5~57- 4A GRoMMET

Ai~L3-3 BcrT
1Nsrc-/o v~nEA
NUT

SnrmWR

JCRYO

PVLLY ASJ1I

lorr 739-rr-12-~ 7
CLIYP V /I ~IWliZP BOLT
AHSbD-K) W~FHEA
AKJ-CI NUT
IXSCO-ld VISHDT(tl
Nvr
CUP

~7 GALV

TH/MSLr
;G NAJO-PREfS S~LEYE-

ANIW-J 7H/HB12
8f~Ua KN/tO-P~E?iS
AMN JlrOP BEAR/NG
*N ´•It- ~24EYEBLXT
BLOCK

AN Jb~-/OJL NLlT

SNSLI;ZB
cwJ-zsa
IW ~60-l,b
AN 960- LWISHER
1N 565-9~8 NM

D
D/REC~ONAL
GYRO

SERVO
CovER TREno

2-8 REYISED NOVEMBER 1966

FI EXTERIOR ~NTERIOR CARE

As any palm applied to a metal surface, an initial curingperiod is rec~ired to develop the
with
desired ~Iualides of durability and appearance. Therefore, wax or polish should not be applied to
the exterior until two or three months after delivery. Wax substances will seal the paint from the
air and prevent curing. Hold buffing to a minimum until curing is complete and there is no danger
of disturbing the undercoat.

Before washing the e9terior, be certain the brake discs are covered, thepitot shield is in place.
and both static air buttons are masked off. Loose dirt and mud deposits should be flushed away
before washing the exterior with an aircraft detergent and cool water. Use soft cleaning cloths or a
chamois and avoid harsh or abrasive detergents thatmight scratch or corrode the surface. To remove
a heavy oxidadon film, use a prewar cleaner (example: HarlyCarnuba). For nonoxidized or pre-
cleaned surfaces, apply a good exterior-finish wax (example: Harry Wax) recommended forpro-
tection of acrylicenamel finishes. Follow the manufacturer’s instructions carefully. Aheavier
coating of wax on the leading edges of the wings, empennage, and nose section willhelp reduce drag
and abrasion in these areas.

If fuel, hydraulic oil or any other fluid containing dyes ia found on the exterior paint, wash the area
at once to prevent staining. Spilled battery acid must be flushed away immediately and the area
treated with an alkali and water solution followed by a thorough washing with an aircraft detergent
solution.

Household window cleaning compounds are not recommended, as some contain abrasives or sol-
vents which could harm the Plexiglas. Furthermore, it is essentialthat allcleaningcompounds
and application cloths be free ot abrasives, grit, or otherforeignmaaer. Never usedenantred
alcohol, benzene, carbon tetrachloride, acetone, or leaded gasoline for cleaningPlexiglas or in-
terior plastics. Before wiping the window surfaces, flush the exterior with clear waterto remove
panicles of dirt. Grease or oil can be removed by wiping the panel with a cotton cloth saturated
with unleaded gasoline or kerosene. An anti-static Plexiglas cleaner is recommended for cleaning
and polishing the windshield and windows.

Normal household cleaning practices recommended for routine interior care. The seats, rugs,
are

upholstery panels, and headliner should be frequently vacuum cleaned to remove as much surface
dust and dirt as possible. The fine leather or vinylupholstery and kickpanels need occasional
washing with an aircraft deteroent solution to prevent the working of dirt into the surface. Wipe clean
with a slightly damp cloth and~rywirha soft cloth. Never apply furniture polishes. Foam type sham-
poos and cleaners (example: Garry’s VLP) for vi?yl, leather, and plastic materials can be used to
remove stains and to condition the entire interior. Spray-on dry cleaners are also recommended.

When using commercial cleaning and finishing com_oounds, carefully follow the manufacturer’s in-
structiorts. Never saturate fabrics with a solvent which coulddamagethebaciting andpadding
materials. To minimize wetting of carpets, keep foam as dry as possible and rub gently in circles.
To remove foam, use a vacuum cleaner. Royalite, vin~jl, and metal surfaces may be cleaned with
a damp cloth or an aircraft detergent solution. Do not use alcohol or strong solvents on Royalite
plastics.

2-9
 SHOP NOTES

2-10
 2 3

7 8 9 10 11

20

19

12 13 14- 15 ,Is ’,5 ’B ’12

b o o
o o o I- o ~1 9
o

O 00 o_
POO O
010 OO

30
SO 21
21 30
30 18
27 27
16 18 16
22

o I o

O\IO

30 30

30, 1 .23 24 25 26

9 28

27 29(vl 4

Figure 2-9. Service, lubrication, inspection access guide.

REVISED OCTOBER 1975 2-11

 ACCESS COVERIDENTIFICATION LUBRICATION GUIDE

~PTEM ~EM DESCRIPTION LUBRICATION MTERVAL

NO. SYMBOL* (HRS)
1 Propeller 0 100
Starter Drive 20
1~
2 BATTERY (M20 C D)
3 Flight Instruments
Positive Control Pilot Valve
Vacuum Regulator
Turn Coordinator
Vacuum Filters--Replace at 500
Ifydraulic Reservoir. 0 50
Control System Adjustments:
Control Column Beari~g Ball 100
Rod-End Bearings 100
Universal Joints 100
BellCranks... 100

4 Engine Cowling
5 Nose Gear Grease Fittings 100
RetractionTube 100
BellCranks 100
Bungees 100
Shock Absorber 100
Gear Door Rod-End Bearings 50

6 Main Gear Grease Fittings 100

Retraction Tube Rod-End Bearings.........,, 1 100
Bell Cranks 100
Bungees 100
Gear Door Rod-End Bearings 50
Electric Gear Actuator Gear Boir. 100
Electric Gear Actuator BallScrew 100

Elevator Rudder Controls:

Control Tube Rod-End Bearings 100
Bell Cranks. 100
P.C. Servos
Baftery(M20E F &J1~
Baffery Relag IM2~, F, J)
Retractable Step. 100
Stabilizer Trim Control Shaft:
Universal Joints ~L 100
Guide Blocks.. 100

8 Elevator Rudder Controls:

Control Tube Rod-End Bearings....,.,.... 100
Bell Cranks ~L 100
Stabilizer Trim Jack Screw. 100

9 Empennage Attach Points 100

Stabilizer Trim Attach Point 100

10 Elevator Rudiler Controls:

Control Tube Rod-End Bearings........... 1 100
Trim Assist Bune~ee Attach Point 100

*See last page of section for lubrication symbol legend.

2-12 REVISED JULY 1980

 ITEM DESCRIPTION INTERVAL
XTO. SYMBOL* (HRS)
11 Elevator Rudder Controls:
Control Tube Rod-End Bearings 1 100
Trim Assist Bug~ees I 100
~L
Elevator Down Springs 100

12 Aiferon P. C, Servos

13 Aileron Controls:
Control Tube Rod-End Bearings 1 100
Bell. cranks......... 1........... 100
100

14 Aileron Control T~ibe G~ride Blocks 100

15 ~Aain Gear Retraction Spring.........,.... 100

16 tT~Tin3o Attach Points

ControlTube Grride Blocks 100

1? Hydraulic Flap Pump TdnF~oe..,......... 100

Stabilizer Trim Screw Stops 100
Indicator Adjustment Point
Stabilizer Trim Chain Gears. 1 100

18 Elevator Rudder Controls:

ControlTube Rod-End Bearings 100
Bell Cranks 1, 100
100
Hydraulic Flap Cylinder Rod-End Bearing. 100
Flap Indicator Cable 100
Electric Flap Actuator Gear Box. 200
Electric Flap Actuator
BaLlScrew: 100

19 Electric Boost Pump.

Fuel Selector Valve Detent Track Ball 100

20 Control Systems:
Control Tube Rod-End Bearings 100
ControlYoke (Lower Section); 100
Nose Gear Steering Link 100
Rudder Pedal Cross Shaft.........,..., 100
Rudder-Aileron BuIgee 100
Hydraulic Brake Cylinder Pedal Linkage...... 1, 100

21 Aileron Control T~e Rod-End Bearings. 1 100

Orrtboard Flap Stops

22 Retractable Step 1 100

23 Baggage Conpartmerrt Door:

iiinges 100
Latches n 100
Seals 0 100

24 Cabin Door:
Hinges 100
Latches a 100
0 100
hold-OpenArm 100

*See last page of section for lubrication symbol legend.

REVISED JULY 1980 2-13

 rT~ M ITEM
NO.
DESCRIPTION LUBRICATION INTERVAL
SYMBOL’ (HRS)
25 Engine Instruments
Radios

26 OilDip Stick.
~f
27 Wheels Brakes:
Wheel Bearings. 250
O
Brake Pressure Plate Anchor Bolts.......,, 50

28 Elevator Rudder Control Stops

29 Nose Wheel:
Wheel Bearings. 250
O
Shock Absorber. 100

30 ControlSurface Rinoes 100

LUBRICATION SYMBOL LEGEND

SYMBOL MIL. SPEC. NO. DESCRIPTION

1~ MILE?870 Low Temperature Oil (General Purpose)

MIEG-??11 or MILG-81322 Grease
C3 MILL3545 ..........Grease Temperature)
O MILG-23827 or Hartzell DG Grease
O MIGH-5606 ..........Hydraulic Fluid (Red)

Graphite MIEG-3278 Grease or MILG-23821

O Powdered Graphite
Ter’lonSpray ~Tri-Flon)
n ..Stick Lubricant @oor Ease or Equivalent)
..Standard OilAviation Grease No. 5
With Id~e by Volume Molybdenum
Disulfide or MILG-23827 AMI
Lubriplate 630~ (10C~ by Volume
Molybdenum Disulfide Mixture
Permissible)
O

1$3 ENGINE OIL RECOMMENDATIONS

For All Lyc0min~ Aircraft Engines

Average Ambient Single Operating

Air Temperature Viscosity Multi-Viscosity OilInlet
for Starting Grades Grades Te
OTE II*) I RTOTE m~ I Desired Maximum

Above 600F SAE 50 SAE 40 or SAE 50 1800F 2450F

700F900F SAE
S-4E
40
30
SAE 40
SAE 40 or 20~Y-30
1800F
1800F
2450F
Z25~F
Below 100F SAE 20 SAE 20W-30 1700F 210"F

*Refer to the following page for Notes I, II III.

2-14 REVISED JULY1980

NOTES: ENGINE OIL RECOMMENDATIONS

MODELSAFFECTED: A11Lycomingopposedseries aircraftengines

TIME OF COhlPLIANCE: Any time after initial 25 hour preservation run or whenlubricating oil is

changed or added.

Engine lubricating oil viscosity recommendations are on. RECOMMENDATIONS FOR NEW
shown the previous page. However. the over-all ac-
on ENGINE BREAK-IN
ceptance of derer~ms. compounded, or additivelubri-
caring oils is not sui"nciem reason for recommending New, or newly overhauled engines should be oper-
their use in Lycorping aircraft engines. Inferior base ated on straight mineral oil during the first 50hours
oils are sometimes doctored with detergents to disguise of operation, or until oil consumption has stabilized, if
their true characteristics; there detergent oilsthat
are an additive oil is used in a new
engine, or a newly over-
can cause spark plug fouling and preignirion; and there hauled engine, high oil consumption might possibly be
are those that are incomoatible with other oils. But, experienced. The anti-friction additives ofsomeofthese
regardless of such factors, there are some aviation ad- oils will retard the break-in of the piston
rings and cyl-
ditive oils that appear to be supMor in performance to inder walls. This condition can be avoided
bythe use
straight mineral oil, and their use in Lycoming aircraft of straight mineral oil until normal oil consumption is
engines Is recommended. Included fn these oils are obtained, then change to the additive type.
the multi-viscosity ashless dispersant oils essentially
conforming to Specification MiL-L-228j1 exceptforcor Preservative oil should be removed at the end of the
net seasonal viscosity grade suitable to Lycomtng first 25 hours of operation-it must never beused
series
beyond
engines. 50 hours. When adding oilduringtheperiod preservative
oil is In the engine, use only avf
ationgrade straight min-
eral oil of the viscosity desired.
CAUTION´•

Any lubricating oil, Either straight mineral

or compounded, must conform withlycom- RECOMMENDATIONS FOR CHANGING OIL
ing Specification No. 301~ to be acceptable
for use in Lycoming aircraft engines. Proof In engines that have been operating on straight min-
of such conformity is the responsibility of eral oil for severalhundred hours, a change to additive
the lubricating oil manufacturer. oil’ should be made witha degree of caution, the clean-

Ing action of some additive oils will tend toloosen

NOTES sludge deposits and cause plugged ollpassages. When
an engine has been operating on
straight mineral oil,
and is ~cnown to be in excessively dirty condition, the
I AVERAGE TEMPERATURES The listed ambient
switch to additive or compounded oil should be deferred
ground air temperatures are meant only as a guide. Ac-
until after the engine is overhauled.
tually a great deal of personal Erdgment must be used
wben selecting the seasonal grade on to put into the
When changing from straight mineral oil to com-
engine. For example if a plane is to be flown into an
area which is much warmer or much colder, only per-
pounded oil, the following precautionary steps should
sonal judgnem on the parr of the opelator can determine
be taken:

what grade of oil to use. When oil inlet temperatures

i. Do nor add additive oil to straight mineral oil.
approach the maximum allowable dnring operation, it is
Drain the straight mineral oil from the engine and fin
a good indication that a higher viscosity on should be
with additive oil.
considered.

2. Do not operate the engine than five hours

n SIh’CLE VISCOSITY GRADES This classification longer
of before the first on change.
lubricating oils includes any aviation grade (straight
miwrsf, detergent and dispersam) that is designated
3. Check all oil screens for evidence of sludge or plug-
by a single viscosity number. The SAE Grades 20, 30,
40 and 50 shorm in the chart are equivalem of Grades ging. Change oil every ten hours if sludge conditions
are evident. Resume normal oil drain periods after
55, 65, SO and 1M) respectively.
sludge conditions improve.
m MULTI-VISCOSITY GRADES This classification
includes additire oils with viscosities the same as
straight mineral oil at high temperatures, but which
provide a lower viscosity at low temperatures. The
CAUTION
additives in these oils extend operating temperature
range. impro~ing cold engine starting and lubrication The terms "detergem". "additive" and"com-
of the engine during the critical warm-up period, thus
pounded" used herein are intended to refer
permitting flight through wider ranges of climatic to a class of aviation
change without the necessity of changing oit Themulti- engine lubricating oils
to which certain substances have been added
viscosity grades are recommended for aircraft engines to improve them for aircraft use. These
subjected to wide variations in ambient air tempera-
terms do not refer to such materials com-
n~es. particularly when cold starring of the engine
must be accomplished at temperatures of 300F. and be~-
monly known as "top cjrlinder
lubricant",
"dopes", carbon remover" which are some-
low. The SAE Grades 20W-30, 40 and 50 shown on the
times added to fuel or oil. Theseproducts
charr are equivdlent to multi-viscosity grades of 65, 80
and 100 respectively. It must not be presumed, how-
may cause damage to the engine and their
presence in an engine will void the owner’s
ever. that multi-viscosity oils will alleviate all of the
warranty. Under no circumstances should
problems encountered in extremely cold enviromnents automotive oil be used. The use of automo-
Cbelow +10DF.). Ar these temperatures preheating of tive lubricants in
the engine and on supply tank will be re~ired Lycoming engines is not
regard- recommended because its use could cause
less of rhetype of on used.
engine failure.

~LEVISED OCTOBER 1915

2-15
 SECTION

POVVER PLANT
 SECTIBN III
POWER PLANT

A. GENERAL

The M20C and M20D are powered by a Lycoming 0-360-A1D, 180 hp engine. The standard M20D is
equipped with a Lycoming 0-360-A2D, 180 hp engine, the 0-360-AlD engine being optional for a con-
stant-speed propeller, Both engines have a compression ratio of 8.5:1 and require a minimum grade
of 91/98 octane fuel.

The M20E is ecpipped with a Lycoming 10-360-A1A, 200 hp engine having a constant-speed all-metal
propeller.This engine must be serviced only with a fuel having a minimum grade of 100/130 octane.

Two Bendix magnetos are furnished, the left magneto being ecluipped with a set of retard breaker
points for a starter vibrator which furnishes long duration, boosted spark for starting. The ignition
switch combines both starting and ignition functions. To supress radio static, shielded spark plugs
and ignition harness is furnished as standard equipment.

For derailed engine and propeller information, refer to manufacturers’ handbooks,

B, TROUBLE SHOOT~G

Refer to the a_bpropriate Lycoming or Bendix manual for engine trouble shooting procedures.
C, AIR FILTER CARE

The incorDoration of an induction air filter in the engine air intake system significantly increases

engine lifd. Dust panicles accumulate on the filter element and must be removed every 25 hours,
or more frequently in dusty atmospheric conditions, to prevent obstruction of air intake during
engine
operation.

To clean induction air filter (paper element):

i. Removefilter from aircraft.
2. Direct a jet of air up and down the entire filter element lair nozzle must he kept at least 2 inches
from filter).
3. Inspect filter for damage, holes, and presence of rec~uired gaskets before reinstalling.

To clean air-maze toil) type filter:

i. Removefilterfrom aircraft.
2. Washinsolvent.
3. Apply a light coating of lubricating oil.
4. Reinstall onaircraft.

2). ESGI~E REMOVAL

NOTE: Experience has proven that it is much easier to remove and reinstall this engine with the
mount attached toit.

1. Remove thepropeller
2. Removetheside cowls
3. Removethetopcowl
4. Removethebonom cowl
5. Disconnectthe following:
a. ground cablefrombattery
b. vacuumline
c. landinglightwires (2)
d. oilradiator.oil~ines.4bolts andclamps
e. bracerods(connected tofirewall)
f. cowl flap control rods

REVISED NOVEMBER 1966 3-1

 g. cabin heat duct Cfrom elSoine)
h. fuelventline
i. tachometerdrive shaft
j. oiitemperature bulb
k. oilpressureline
i. fuelpressureline
m. manifold pressure line
n. cylinder head temperature ~e thermocouple line
6. 3isconnectthefollowi~,o controls:
a. throttle control
b. propeller governor control
c. mixture control
d. cowlflap control and spring
e. carburetor hot air control
7. Disconnect ignition switch wires from (Ground Magnetos)
8. Disconnect the engine ground strap
9. Disconnect allvoltage regulator wires
10. Disconnect 2 generator wires and 1 starter wire
11. Disconnect muffler, tailpipe, and support springs
12. Disconnect line from boost pump to engine fuel pump
13. Remove top engine baffle to expose hoisting hook and attach an "A" Frame type hoist or other
suitable hoist to the e~cine hoisting hook and relieve the tension on the engine mount.
14. Disconnect four bolts from the engine mounts at firewall and slide engine forward slowly and
carefully to check if any wires orcables are still connected to the elgine. (If it is desirable to
remove the mount from the engine, it can be accomplished easier at this time).

E. PROPELLERREMOVAL (CONSTANT SPEEDTYPE)

1. Remo7e propeller spinner (M20E F remove screws at forward bulkhead).
2. Remove 6 bolts and washers from propeller flange and gently remove propeller from the engine
shaft. ~hen the propeller is removed from the engine crankshaft there will be a small amount
of oilthat will run out of the propeller hub and crankshaft.)
3. Carefully remove the "0" Ring from the engine shaft.

F. INSTALLATION OF ENGINE

Reverse engine removal procedure. Allinstallations must be rechecked for proper torque and safetg-
ing. Fuel and oil lines must be pressure checked. Engine mount torque val~res: Eng. Shock Mts.:
450 500 inch pounds; At Firewall: Top Bottom 50 70 inch pounds.

G. INSTALLATION OF PROPELLER (CONSTANT SPEED TYPE)

i. Install spinner adaptor ring to engine starter gear.

2. Clean engine shaft and propeller hub at flange.
3. Insert the "0" Ring into the groove located inside the flange mounting lubricating it libernllv with
clean lubricating oil.
4. Line up the small "O" mark on the hub flange outer diameter with the short bushing in the cranlr-
shaft flange.
5. Install propeller onto ego;ine shaft. Torque the 1/2 in. studs to 60-70 ft. Ib. Safety wire pairs of
studs together.
6. Install spinner dome.

H. ENGINE CONTROL ADJUSTMENTS

Refer to appropriate Lycomine: manual for idle mixture, adjustment, etc.

I. COWL FLAP OPENING ADJUSTMENT (See Figure 3-1)

i. For M20C, adjust left cowlflap for 1. 1 in.-i-. 1 in. measured at the trailing edge when
fully extended.
2. For M20D, adjust left cowlflap opening for 2.4 in.+.l in. measured at the trailing edge when
fully extended.
3. For the 1964 1965 M20E, adjust left cowl flap opening for 2. 00 in. measured at the trailing edge
when fully extended.
For 1966 and subsequent M20E aircraft, adjust left cowlflap opening for 1. 65 in. measured at the
trailing edge when fully extended.
4. For M20F, adjust left cowlflap opening for 1. 65 in. measured at the trailing edge when fully ex-
tended.

3-2 REVISED JULY1980

J. COWLFLAP RIGGING

Rig right co~l flap to match left nap in up position.

FIGURE 3-1 COWL FLAP OPE~ING AD~USTMENT

C f~
C

I C

:-i~: -r

NOTE: All meosurements ore mode on left cowl flop only~ Rig right co\NI flap
to motch left flop in ~p position.

´•-i
 SHOP NOTES

3-4
SECTION

STRUCTURE
 SECTION IV
SIRUCTURE

A. GENERAL

and 4-4skin materials used onMooneydircraft. Repairs such as skin

identify
Figures 4-2, 4-3,
patching, welding, may be made
etc., in accordance with the regulations given in Civil Aeronautics
Manual 18. Skin repairs must result in a surface which is as strong as, or stronger than, the original
skin. However, flexibility must be retained so that the surrounding areas will not receive extra
stress.

B. REMOVALOFWING COMPONENTS

The major subassemblies of the wing may be removed individually or the wing may be removed as a

unit. To remove a wing, a fuselage supporting cradle is recpdred.

i. Removal ofWing(Figure4-~)

a. Remove wing root fairings, and the bottom fuselage access panels.
b. Drain allgas fromthewing.

c. Drainbrakelines andreservoir. I)isconnectatwingmainspar.

d. Remove front and rear seats. Remove 2 inspection plates under rear seat area.

e. Settheairplaneonjacks. (Usejackpoints as showninFigure2-l,)

f. Set "A" frame on propeller.

X´• Remove the following:

i. Twolandinggear assistsprings.

2. Disconnect flap hydraulic line at pump fitting.

3. Disconnect flap indicator housing in cabin.

4. Ailerontubes-two.

5. Disconnecttrimlinktube atstation59.3 andstation94.5.

6. Maingear retractiontubes.

7. Ruddertubes.

8. Elevatortube.

9. Elevator and rudder push-pull tubes-two.

10. Disconnect floorboard.

11. Disconnect seat rails.

12. Stringer assembly doublers- one each side

13. fourteenbolts fromshearplares.

14. Sixteen attachbolts-eight each side(ANB-M).

REVISED NOVENBER 19~6 4-1

 15. Bolts, nuts. and washers from front attach fittings on both sides.

16. Gas lines and wires from wing root.

17. Airspe~d indicator line. pitot lines, pitot heater wires if insta~ed.

18. Rear mating bolts (two AN4-I7A).

19. Two tension bolts (7H-16A).

~OTE: Have suitable cradle ready for fuselage before accomplishing last three steps
of wing removal.

2. installation of the wing assembly is direct reversal of removal.

SHOP NOTES

REVISED NOVEMBER 1966

4-2
 m II1D9o -n
IIIYI Uu.T I~R *IUIM IflP ´•~tllM
IHU1)KI I I I1IU( I I Illru I I atu I I grm G)
;o C
)IOll(-P ;O
iSi I
I *HweclcL
rn
m I,lollc-l, I*sc-chl I I*awectrl 1 I I IAWlbJ-(11 I
b AN7H-)6A BOLT
VIEW LOOKIHC DOWH ~L,
SMEAR PLATE L.H. SHOWN
SEE ABOVE ttlART FOR HARDWARE C/O
R.H.OPPOSITE
m i

m ANI DOLTS (SEE ABOVE CHART FOR LENGTHS IOGA SAFETY WIRE Z
C)
m
4 EACH SIDE USING RESPECTIVE SHIMS)
;o
P
FITTING I 71
o. C
SHIM v,
m
AN3-4A BOLT r
S~1EAR FITTING (REF.)
AN363-1032 NUT \(8 EACH SIDE)
AH96elOWASnER ’j
(NUTS ACCESSIBLE 3:
TI1ROUGH WI´•1EELWELL] g

Z
AN363-428 NUTS (4) ACCESSIBLE C,
THROUGH BOTTOM ACCESS PANEL rj
(DOTTED) g

C]
;D

SMEAR FITTING PLATE

AN6-16A BOLT
AN363-624 NUT
AN960-616 WASHER
(ONE EACH SIDE)
AN4-15A BOLT (BOTTOM)
NUT AND BOLT TORQUE VALuel EOY AN4-17A BOLT (fOP)
SIZE (INCH- POUNDS)I ONE EACH SIDE
AN960-416 WASHERS
AN 3 12- 15
TWO EACH SIDE
AN 4 30- 40

AN 6 1 95 110 1 ~AN7H-16A BOLT (SAFETY WIRED AS SHOWN ABOVE)

AN960-716L WASHER
AN 7 450 500
(BOLTS ACCESSIBLE THROUGH ACCESS PANELS
~J UNDER REAR SEAT AREA INSIDE CABIN)
 FIGURE 4-2_ WING SKIN CHART

igOh~i ~CI

I -I -I

I I I NO. THICKNESS Nt4TEEUAL

t

Z I ’I \9) 1´• a´•os9 2024 T-3 CI~9D

I I~Lj h
Z 0.050 (3 2024 T-4 CLAD

5TA. 59.25 1 j
3. 0.040 2024 T-3 CLAD

V
i I 4. 0.032 2024 T3 O~AD

~--J----i I i 5. 0.025 2024 T3 CLAD

6. 0.032 (a) 2024 -O CLAD

i 0.032 2024 -O CLAD

I i 0.025 (9) 2024 r3 CLAD
I

STA. )03.500 a 0.040 2024 T-3 CLAD

,,,C,
9. 0.025 2024 T3 CLAD

f I 1 10. 0.020 (51 2024 T-3 CLAD

i I 1 0.025 (e) 2024 T3 CLAD

I I I v 11. 0.040 (9) 2024 T-3 CLAD

i
12 0.032 2024 T~ CLAD
I
I
I 1 ~3. 0.025 2024 T3 CLAD

SSA. 347,750
r4. 0.020 (d) 2024 T-3 CLAD

15. 0.025 2024 T-3 CLAD

16. 0.020 (6) 2024 T3 CLAD

1~ 0.016 (6) 2024 T-3 CLAD

0.025 (e) 2024 T-3 CLAD

18. 8.025 2024 T3 CLAD

STA. 193.500

(a) Neat Treated to T-42 condition after

forming

b) (51 9929 thicknur on bottom tide or

flap.
(c) Top ot wip~ only.
ILIGHT WING SHOWING (d) Sune thicknas on both dde~

!e) Prior to 1965.

4-4
FIGURE 4-3 TAIL SKIN CHART

7) (6) (4) (3) (2

i’
i I

9) 1 (9)1(10)(5)h0~ _L(9) 1 (9
12) (11)-

3~ (13

6) 1

ci~
18

1
15
21:

QP
M20F M20C,D,&E

NUMBER THICKNESS MATERIAL NUMBER THICKNESS MATERIAL

1. 0.040 (a) 20’4 -OCLAD 13´• 0.040 (a) 2024 T-4 CLAD
2. 0.025 2024 T-3 CLAD 14´• 0.025 2024 T-3 CLAD
3. 0.025 2024 T-3 CLAD 15. 0.025 2024 T-3 CLAD
4. 0.020 2024 T-3 CLAD 16´• 0.012 (c) 2024 T-3 CLAD
5. 0.025 (b) 2024 T-3 CLAD 17´• 0.012 (c) 3024 T-3 CLAD
6. 0.025 2024 T-3 CLAD 18´• Mooney Extrusion -L;4142
’1. 0.025 202? T-3 CLAD 19´• O.ozo 20241;-3 CLAD
8. 0.040 (a) -O CLAD 20´• 0.012 (c) 2034 T-3 CLAD
9. 0.012 (c) 2024 T-3 CLAD 21´• 0.0Zj 2014 T-3 CLAD
10. 0.012 (c) 2024 T-3 CLAD 22´• 0.025 2024 T-3 CLAD
Exlrusion ,"1142 23. 0.020 2024 T-3 CLAD
11. Mooney
12. 0.020 202~ T-3 CLAD 24- 0.040 3003 -0

(a) Heat Treated to T-$2 condition after forming.

(b) Bottom 0.025 2023-0. H.T. to T~2 condition.

(c) 0.016 may be used as alternate.

REVISED NOVEMBER 1966 4-5

 FIGURE 4-4 FUSELAGE SKIN CHART

9)
41 (1

9)/(8

r’-7

9U
1

91* rr*
I$ a*
i

111.11 Iri.oo 11.00 1(.00 19.60 0.00

MZOC,D&E

0 8 iii 165
B
5)(4) (1

9)/(2

1) 1 (14) (1)1 (8) (16‘) 1 (15)(ii~ I (i~ (i

arA aL\ --STA SU XA
99.10 111.11 llD.00 1(.00 51.00 11.11 0.00

M20F

NUMBER THltKNESS MATERIAL

1. 0.025 2024 T-3 CLAD

2. 0.032 2024 T-3 CLAD
0.020 (6) 2024-T-3 CLAD
3. 0.032 2024 -0 (9) CLAD
4. 0.040 3003 -0
5. 0. 025 2024 -0 CLAD
6, (9) 0.025 (9) 2024 T-4 CLAD
0,025 2024 T-3 (d) CLAD
8. (9) 0.025 2024 T-3 CLAD
9.~ 0.020 2024 T-3 CLAD
la (6) 0.020 2024 T-3 CLAD
11. 0.(n5 2024 -0 (9) CLAD
12. 0.025 2024 T-3 CLAD
o.cno (8) 2024 T-3 CLAD
13. 0.032 2024 T-3 CLAD
14. (6) 0.032 2024 T-3 CLAD
15. 0.032 2024 T-4 CLAD
16. (f) 0.025 2024 T-3 CLAD

NOTES
(9) Heat Treat to T-42
(9) Right side only
condition after forming
(6) Leftsideonly
(c) 0.032 can be used
(9) prior to 1965
(d) 2024 T’-3 matetial
on right side

4-6 REVISED NOVEMBER 1966

 SECTION

LAN DING G EAR AN D

BRAKE SYSTEM
 SECIION V
LANDING GEAR BRAKE SYSTEM

A. GENERAL

The is a tricycle gear type.

landing gear It is constructed of~eavy, chrome-molydenum tubular
ste~ heat treated for greater strength and resistance to wear. Neoorene rubber discs absorb the
shoc8 of normal taxiing and landing. The attaching points of the main gear are in metal bushings
embedded in the gear-mounting box and attached to the soars. The nose wheel is mounted to the
cabin’s tubular-steel frame. The main gear wheels are eciuipped with hydraulic brakes.

B. REMOVALOF LANDINCCEARS

i. MainGear, Retractable.

a. Placeaircrzftonjacks. (RefertoFiguretl.)
b. Unlock and move gear handle air a short distance. Disconnect the gear doors, brake lines,
and the retraction tube.

c. Retractgear alltheway.

d. Remove the main gear retraction s~ring (see Figure 5-1).

e. Extend gear to about 3 or i inches from down lock position and secure it or have someone
hold it in this position.

f Remove two bolts from retracting truss bracket.

g. Remove six bolts from rear landing gear at attachment bracket,

h. Slideout rearpartor bearng sideways.

i Slide from part ofbearing aft and remove.

i. Slide gear assembly aft slightly until clear of from bearing and carefully take out of wing.

Main Gear- Fixed.

Airer placing aircraft on jacks, remove fairing and linkNo. 510011-9. Repeat steps g
through i in procedure above.

2. NoseGear, Rerraaable.

a, Set aircraft on jacks (Refer to Figure 2-1).

b. Remove exhaust cavities.

c. Removebolronaftend ofretractingLink.

5-1
UI Z!
r: AN3-S BOLT AN3-12A BOLT c,
c
AN310-3 NUT fl
CONNECTING LINK rn
AN380-2-2 PIN I cn
~Le

IL_ I II F
;o

I I I T?I
;o
(I’i o

V
o

zcn
--y ----c-)-c-
3i- 1 Il.r I ~O
RETRACTION SPRING z
o
MAIN SPAR
70
_----
OLDING BLOCK
_

o
~AIN GEAR, RH Ec-------8186 TOOL

VIEW LOOKING FWD, AT RETRACTED RIGI1T HAND MAIN GEAR

C! PROCEDURE FOR USING 8186 TOOL:

Remove the gear door. Remove the cotter Itey and nut at the spring
o
connecting linh. Retract the gear and
Insert a a"-thicle wood blocle to hold’ tlie
gear in the retracted position after detac!lment of the spring.
Remove~ grease fitting in the gear attach bearing. Attach 8)86 tool forward of the
connecting linle with on
I\N3-12A bolt as shown In the Illustration. Rotate the tool in an outboard direction using the
m
upper trunion
shaft of the gear fralne as a fulcrum. The linle attach bolt (AN3-5) can be withdrawn
by hand when suf-
´•o ficient leverage is applied to the tool.
NOTE: Installation of the gear retraction spring Is die direct opposite of the removal procedure.
 d. Partially retract nose gear by hand and remove bolt from nose gear steering horn.

e. Bend flange of firewall to clear bolts of support truss.

f. Remove right and left bolts of support truss.

8. Carefully removenosegear assembly.

hTose Gear Fixed.

Remove fairing and fixed links. Repeat steps "d" through "g" above.

C. REhlOVAL AND DISASSEMBLY OF SHOCK DISCS (SEE FIGURES 5-2 AND 5-3)

D. REASSEh´•IBLY AND INSTALWTION OF LANDING GEAR

Installation of the landing gear is essentially the reversal of removal. On reinstalling the main gear
in the airdlane, be sure to keep parts from the right and left gear separated.. Do not attach gear door
brackets to gear legs with sheet metal screws until doors are finally adjusted as explained in the fol-
lowing procedure.

i. MainGear.

a. Grease wheel bearings, retraction linkage, and fare and aft bearings which attach to the spar
(See Figure 2-9 for recommended lubricants).

b. Slide front end of gear leg into front bearing; slide bearing plate of rear attachment over

rear end of main gear leg, spotfaced side forward.

c. Slide rear part of attachment bracket between spar and landing gear.
d. Line up holes in rear attachment and spar. Attach with six bolts.

e. Attach retracting truss through retracting bracket with two bolts and secure with safety
wire.

f. Connect retraction tube and fully retract gear.

g. Connect,oearassistspring andlowergear.
h. Attach gear door links to brackets on gear legs. Raise gear to see that there is no bind
in door link
bearings.
Door edge should seat evenly against wing without excessive distor-
tion where liriks attach to door. Adjustment may be made by slightly shifting the position
of the gear door brackets on the gear leg or by changing the length of the links. This is a
preliminary adjustment. Do not attach gear door brackets to gear leg with sheetmetal screws
until door adjustment is rechecked after gear is rigged.

2. NoseGear.

Installation of the nose gear is a direct reversal of the removal procedure.

REVISED NOVEMBER 1966 5-3

FIGURE 5-2 NOSE GEAR SHOCK DISC REPLACEMENT TOOL APPLICATION

DATUkLLINE (STA. O.OQ)

BELLY SKIN LINE

COLLAR

BOLT

HOQK

TOOLHO.ME120
SCPEW_

j
j
i

Two pins (chained

PROCEDURE FOR USING TOOL: Remove wheel and spindle. Attach tool os shown.
to tool) ore placed in geor Ieg bolt holes. Torn compression screw
clockwise vntil tension on collar
it relieved. Remove collar bolt and collar, Relieve tension on
shock discs by tuming compression
screw Shock discs may then be removed.
NOTE: Geor doers need not be removed.

5-4
 FIGURE 5-3 MAIN GEAR SHOCK DISC REPLACEMENT TOOL APPLICATION

SPINDLE

´•´•...;´•´•´•´•´•..I´•:

.X:
i3‘

.r.r.l.´•.´•.´• ~j
´•r´•-´•´•´•.´•.´•.
’"’´•:2~.
.;~-:y.
´•_´•´•´•´•~´•´•´•´•-´•´•´•-´•´•

t´•-:´•:´•´•-?.-.´•.~::;._,,
´•´•.´•.´•.´•;´•;i´•-´•.´•’´•´•.

CMIPREIIIO*SCREa
I-- ´•´•.r

ii´•´•´•.´•´•´•´•
´•-´•´•´•´•r´•-´•´•. -.Ti´•(´•-´•.
c´•
´•’´•´•-:´•X´•-:I´•
-´•;.´•.´•;2;´•:´•~´•:´•.-:
;TZ´•´•

-.´•´•´•´•...i
2~I´•

´•-´•-i´•-i´•
j TOOL NO, ME121

:´•:´•:´•:´•:´•i::::´•:’:’´•´•
;:::::::::.:i:jj:;.;´•1:;.´•...´•..
~:2:j;i::´•:

:ij
rr
I

PROCEDURE FOR USING TOOL: Remove spindle attach bolt at shock disc guide, swing wheel forward
and ottach tool os shown. Turn compression tool clockwise until collar bolt on collar is aligned
with access hole. Remove collar bolt through access hole and relieve tension on shock discs by
turning compression screw counterclockwise. Shock discs may then be removed.
NOTE: Gear doors need not be removed.

5-5
 3. Instructionsfor ri~,oingnosegeardoors.

a. Raise airplane off of ground by method described in Section n-C-I.

b. Connect gear door links to gear doors (upper holeinbracket). Gear retracrionsystem
must be before gear doors can be rigged properly.
rigged

c. Gear doors must correctly without contactingthe gear. On

be timed td open and close
1962-1964 models, timing is accomplished by adjusting a screw on the cam. Turning the
screw clockwise speeds closing. Turning the screw counterclockw;se slows closing.

d. M-20C E Models (1965 gr OrJ) incorporate door retraction arms on the nose gear retrac-
tion truss. To rig nose gear doors, adjust links shown in Figure 5-4.

e. Doors must be checked for a tight fit when in c~e closed position. Play may be taken up by
adjusting the gear door links.

f. If the gear, in the retracted position, prevents the doors from closing completely, the ec-
centrics on the retract truss must be reset to raise the gear in the wheel well. The same
applies for lowering if the gear is retracted too high in the wheel well.
NOTE: if item "f’ is incorporated, items "c" and "e" must be repeated.

E. BRAKE ANDWHEELMAINTENANCE

i. Braltelininginspectionand replacement (FigureS-5).

Visually inspect the brake while it is insta~ed on the airplane. No adjustment of brake clear-
ance is necessary. If, after extended service, the brake linings become excessively worn, re-
place with new linings as follows:
a. Removedustcover fromwtieel.

b. Remove spindle nut from one side of wheel and two bolts from the other side (2 bolts that
hold back brake plate stationzry).

c. Slide wheel out and remove pressure plate that has the worn lining on it.

d. The linings can easily be replaced by drilling out three rivets from thepressureplate and
three rivets from the back plate.

e. Replace old linings with the new Cleveland brake linings and Cleveland 561 rivets. A 561-R
rivet kit is available through your local Mooney distributor. This
setting special rivet set-
ting kit should be used, as rolling of the rivet is very important to get atight fit between
the rivet and the rivet hole.

REVISED NOVEMBER 19Lb

5-6
 ´•,p
I
IkrWC~y
5t 71
r
t:

:I!n ´•´•I’I‘UB~f
o
c
;a
rn
I´•I r*! Cn

------´•-n...,´•--
d
´•n;~ (L J i

ly~)
~flB, V i Z
r4
*I´•I
~i Q
411:l~f
i i1,, n" v,
rr rn
a
I c,
´•´•1~ ´•’’~i´• m

r,´•

NOSE GEAR
irl i O
RETR4CflON TRUSS
´•Il)"tr’ ´•rS;L
1
O
i ;O
ECCENTRIC
BUSHING AMD
HARDWARE ~C4Y. 4:
r_qog~ NOSE GEAR
X1
C,
2 PLACES.

.s LINKS AND.CLOSING C,
ADJUSTMENT Z
2 PLACES G)
’I\
.IY tl

O
70

´•9´•I´•r´•~
’4´•
~1.
 SHOP NOTES

5-s
FIGURE 5-5 BRAKE CYLINDER ASSEMBLY

PRESSURE PLATE ASSEMBLY

LINING
RIVET
PLATE PRESSURE
BACK PLATE ASSEMBL
LINING
RIVET 3
PLATE BACK CYLINDER

O-RING

PISTON

BUSHING BLEEDER
SCREW BLEEDER
CAP BLEEDER

5-9
REVISED NOVEMBER 1966
FIGURE 5-6 WHEEL ASSEMBLY CHART

5---8
6~--s
4

1. DUSTSHIELD

2. SCREW

4--~ 3. LOCKWASHEt(

4. HUBCAP

5. SCREW

6. LOCKWASHER

7. TIMKEN BEARING CONE

8. TIMKEN BEARING CUP

9. SPLINE-NUT(ESNA)

10. OUTER WHEEL HALF WITH BEARING CUP

AND SPLINE-NUTS.

11. INNER WHEEL HALF WITH BEARING CUP

12. THROUGH BOLTS

P~S
14 13. WASHER

15 14. GREASE SEALRING

15. BRAKEDISC ASSEMBLY

16. GREASESEAL FELTWASHER

17. WNERDUST SHIELD

13--9
~--1S
12-
17

5- 10 REVISED NOVEMBER 19ib

 TI
O
c:
70
m
cn

3:

;a

AN-6227-10 "O" RING r

AN-6227-9 ’~O" RING
m
70

00
r

r v,

00
70
n
AN-6227-3 "Q" RING
AN-6227-5 "O" RINt;
(REPLACED OHLY WITH
NEW A-1/7G-045 VALVE)
00
70

v,
v,
m
r
m
MODEL V-l r
FIGURE 5-8 PARKING BRAKE VALVE ASSEMBLY

CLOSED OPEN

4207 GASKET

X AN62n-5 "O" RING

AN6227-1 "O" RING

5-12
 FIGURE 5-9 PARKING BRAKE VALVE ASSEMBLY (AI;TERNATE)
3*T
5~21-

MODEL 4500-A1 USED a

AS ALTERNATE FOR I"
4200A1.

PAR’TS LIST
O
So. Port h´•o. Usfd On Nama N.Raq’

L500 1 I ~9
I 4501-2 L500-XI Body 1
4500-~2
Modal 4500
4500C
1 4500-1
4500C-~I
BOdy I

45005
1 4501 45005-;\1 8cdy 1
45005-A2

4504 bun k~embly

4505 Stem Induded in
2 4506-1 VolveHeod A~unblyNo.
4507 Spnns 4504
19649 Spn’ng Pin

6500 1 POSITION 2

3 4511-2 :500-~1 SM´• ’"Ive 1

4500-;\2 l--i
FULCa’JM 1 I
4500C
3 14511-1 See’ "--le 1
4500C-X1
PORT B
45005 I I I V?
3 4511 45005-A1 San’ \’-lve 1
4500S-A2
I I I nrJ OHVI 23’
18048 0-Ring 3/4" O.D. x 9/16" I.D. 1 PORfA rPtl 1 1_131
5 1 18033 O-Bing 3/8" O.D. x 1/4" I.D. 1

6 4503 Spocer (used with Ann Pos. r) 1 I ~O

6 4503-1 Spccer lured with Arm Per. 2) t
7 4208 Ann Auembty 1 POSITION I
8 18286 River 3/32" x 5/8" it H. 5:eal 2
9 4222 WDJhH 3Urr, Steel 4

1:

a4
5

7~
O
5-13
 ´•Z!
k RETRACTINGTRUSS ~X.4‘r 2
10
m
RETRAC’TING LINK ---t r

3/16" OVER CENTER

n

DETAIL OYERCEHTER LINKAGE so

1(1

C)
Z
G)
t3

MAIH GEAR
ADJUSTMENT

8
NOSE OEAR ADJUSTMENT
8\

m
I
c
m
cl

a REMOVf THES~
m BELLY ACCESS PANELS
r
ra
m
;o
O
 2. BrakeBleeding.
When braking action becomes spongy and erratic or when repairs require the replacement of
actuating components, it will be necessary to bleed che hydraulic brake system. Sest results
are achieved with the use of a hydraulic fluid system bleeder (pressure poi) pressurized with
air to approximately 35-40 Ibs. When bleeding dual brake systems, both the pilot’s and co-
pilot’s brakes must he depressed alternately during bleeding to reposition the shuttle valves.

First, remove the vent cap from atop the firewall fluid re~ervoir and attach a fitting and hose
that will carry expelled fluid from the reservoir to a clean catch pan positioned next to the hose
section. Remove the rubber cap at one of the main wheel brake cylinder assemblies, open the
valve by backing off the small center pin, and attach -~e pressure pot hose. Air bubbles in the
fluid being expelled from the reservoir will give the stream a milky appearance. When the
fluid Nos clear and transparent into catch pan, close the bleed valve, disconnect the pressure
pot hose, and cap the bleed valve. Repeat the procedure with the other side of the system, After
disconnecting the overflow tube from the reservoir, remove excess fluid from the reservoir
through its side plug to re-establish the proper fluid level.
3. Wheel Assembly Inspection.
a. Placeairplaneonjacks (SeeFigureZ-l).

b. Remove axle nut and two bolts from back plate and slide the wheel off.

c. Check for bolt failure. Replace any bolts found to be defective (Figure 5-6).

d. Check the internal diameter of the felt grease seals. Replace the:elt grease seal if surface
is hard or gritty.

e. Inspect the casting for visible signs of cracks or corrosion. If there are any indications
of cracks, the tire and tube should be removed and the wheel disassembled for a closer in-
spection.

f. Replace any wheel casting having visible cracks.

F. MANUALLANDING GEARRIGGINGPROCEDURE

The ~ar retraction system is designed to hold the gear down-and-locked only when the retraction
linkage is in the overcenter configuration. Collapse of the gear, at landing or during taxiing, due to
a disengagement of the locking mechanism, can be caused by improper adjustment of the overcenter
lock mechanism or by disengagement of the retraction handle from its down-lock block under the

instrument panel.

1. Rigging Instructions.

a. Raise airplane and remove access panels shown in Figure 5-10.

b. Remove retraction handle from gear-down lock. Tiehandle loosely to prevent bungee from
forcing it down. In order to preventdamage to retraction tubes, do not move gear legs Trom
outside until step C has been accomplished,

c. Disconnect retraction tubes at point B (Figure 5-10). Loosen hearing, check nuts on tubes
at point E and on tubes at point A.

d. Check nose gear and main gears (2) for any binding at hinge points (Figure 5-10) while mov-
ing gear legs back and forth by hand. Tubes may be disconnected at point C during checle of
main gear. Lubricate gear retraction system at points indicated in Figure 2-9.

e. Place the retractionhandle inrhe gear-down lock. Check for and remove any foreign matter
lodged between the retraction truss and retraction link connection at points Z Sas shown
in Figure 5-11. Place all gears in the down-and-locked position. it is recommended th,7t
C-clamps be attached at points X R (Figure 5-11) to hold the retraction truss firmly in
the overcenter configuration.

REVISED OCTOBER 1972 5-15

 f. By turning tubes, adjust retraction tubes so that a 3/16" OD bolt can be inserted through re-
traction lever and bearings at point B (Figure 5-10). This will give a zero preload in the
system wit~ the handle in the gear-down lock.

g. By turning tubes, shorten retraction tubes two turns and lenghen retraction tubes two to
two and one-half turns. Tighten check nuts (4) at points A and E (Figure 5-10).

h. Remove retraction handle from gear-down lock positipll and connect tubes. Replace retrac-
tion handle in gear-down lock position.

i. Inspectionof System Preload.

a, Nosegear (seeFigureS-ll).

1. Place rigging tool (8442) on retraction link with sloped edge aft. Hold tool inplace
against retraction link.

2, Placefinger atpointR.
3. Apply force on torcF~e wrench and read torque at the instant point R first begins to move.
Movement of retraction truss may be felt at point R and may be seen in area of ~oint S.
Practice this several times before recording torque. should be between 100
and 130 inch pounds.

NOTE: Take reading on torque wrench when .005 to .010 inch movement is observed
at points R and X (Figure 5-11).

4. After release of force, retraction truss should snap back to full overcenter and should
bear tightly against retraction link at point S, This should be carefully checked by
pulling down on retraction truss. If retraction truss moves down, then the preload in
tubes is not sufficient.

5. Eccentric bushings at point A on the nose gear retracting truss may be rotated as re-

cluired to obtain the proper gear-up travel and proper gear door rigging.

CAUTION: Nose gear dowrlock rigging must be rechecked after eccentric bushings are

changed.
b. Main Gear (see Figure 5-11).

1. Place rigging tool (8444) as shown in Figure 5-11. Hold in place with thumb at point Y
pressing forward.
2. Placefinger atpointX.

3. Apply force on torcpe wrench and read tor~e at instant that point X first begins to move.
Movement of retracting truss may be felt at point X and may be seen in area of point 2,
Practice this several times before recording tor~e. Tor~e should be between 240 and
280 inch pounds. The difference in left and right gear tor~e should register within t25
inch pounds of each other.

4. After release of force, retracting truss should snap hack to full overcenter and should
bear tightly against retracting link at poirit Z. This should be carefully checked by
pulling down on retracting truss. If retracting truss moves down, the preload in tubes
is not sufficient.

CAUTOOT: Do not attempt to rig the gear to increase or decrease gear-up travel.

5-16 REVISED OCTOBER 1972

3. ~djustmenr ofPreload.

If the torque values do not fall within the limits then the system preload should be
specified,
chan~Sed by changing the lenghs of retraction tubes.
This is done by taking a turn on the rod
end bearings in theprsper direction. One-half turn is usually sufficient. Any adjustment made
to the nose gear should be made identically to both retraction tubes since they should carry the

szme~reload.
Since the retraction rubes from all gears are attached to the gear retraction lever. a change in
preload in the retraction tube at one gear can affect the preload in the retraction tubes at the
remaining gears. Therefore, after an adjustment is made at one gear. the other gears must be
rechecked. This process must continue until the proper preloads are obtained in the retraction
tubes at all gears.

The amount of freedom of the gears las determined from the check made under item 4 of rigging
instructions above) will affect the torque readings. Gear systems with free joints will be ade-
quately rigged when the torque is on the low end of the range while the gears that are stiffer
on the high end of the range for adequate preload.
may require torque values

A final check should be made of the force required to place the gear handle in the gear-down lock
(,oear extended position). If the force re~uired to move thegear handle forward the last one to
two inches is escesshe, then the system prelozd
may be reduced slightly within the prescribed
torque limits. Check for and relieve any bind in the sliding hand grip at the top of the
gear lever
since a bind at this point may make it difficult to lock the
gear handle in place.

SOTE: Gear rigging tools (8442, 8444, 8186) may bepurchased at a nominal cost through
the ~iooney dealer and distributor organization.

SHOP NOTES

5-17
RGVISED iUAY 1919
FIGURE 5-11 TORQUE WKtNLn I IUN UIA~KAM

Retraction Tube
Main Gear 1
L´•s J I i, a y

Retraction
Truss

.f

9~´•--,

Retrclcrion
Link
r-7

RiggingTool L,~

(8444)

Torque
MAIN GEAR Wrench
(VIEW LOOKING AFT
FROM FRONT OF RIGHT GEAR)

force

Retraction Truss
O

i.
L*
iFZ ~L f~.

~f-
S

Retraction Upper Gear

Link P´•-~9 Structure
I~

~i F.
i
ar
.1 ii

’i,

1.

Rigging Tool
(8442!

Torque Wrench

NOSE GEAR
!VIE\Y LOCKING IN FROM RIGHT
HAND SIDE OF NOSE GEAR)

REVISED NOVEMBER 1966 5-19

G. INSPECTIONOF WNDINGGEARSHOCK

1. RubberDiscs.

If a landing gear shock unit fails to pass the inspection described in Figure 5-12 5-13, t~e
rubber shock discs must be replaced.

NOTE: A check of the nose gear shock unit can also be accomplished by checking the propeller
clearance as follows: With the unloaded aircraft on a flat surface and the tires inflated
to the proper pressure, a 74-inch propeller should have a minimum of 9 I/2 inches
clearance from the ground. Less clearance may indicate that the rubber discs are r’.e-
fective and that a more thorough check should be made.

2. Collars andBolts.

a. Inspect landing gear shock absorber bolts and collare(See Figs. 5-12 5-13) for deformation
or indications of failure.

b. Remove collars and bolts at each annual inspection and check for bends, wear, and cracks.
Replace if necessary. it is that s_Dare pans be obtained prior to this inspection.
suggested
I)o not replace a bolt without replacing the collar, or a collar without replacing the bolt.

c. See Figures 5-2 and 5-3 for removal of shock discs and collar.

3. Nose Gear Snubber.

A hydraulic shock absorber is installed on the nose gear of 1966 O?! ~IZOC,E,&F models. The
shock absorber housing is sealed and the unit requires no maintenance. When worn to a degree
that effectiveness is impaired, the entire unit should be replaced.

5-20 REVISED NOVEMBER 1966

FIGURE 5-12 LANDING GEAR SHOCK DISC INSPECTION DIAGRAM
1962-’65 M20C INSTALLATION
1963 g ON M20D INSTALLATION (WITH CONSTANT-SPEED PROPELLER)
1964-’65 M20E INSTALLATION

COLLAR MAIN GEAR:

With the aircraft at static
weight, the gap between th~
main gear collar and plate
Ut 1 should be 0.00 to 0.13 inches
BOLT, h c;,l~n ~Mox. clearance of 1/8 inch:~

NOSE GEAR:
With the aircraft at static
weight, there must be no gap
between the nose gear collar
’PLATE and plate.

EIOTE: Static weight

full fuel, less passengers.
SHOCK UNIT

O
O

WHEEL

5-21
REVISED NOVEMBER 1966
FIGIIRE 5-13 LANDING GEAR SHOCK DISC INSPECTION DIAGRAM
1966 B ON M20C. E d F INSTALLATION

(ALSO LORD DISC RETROFIT INSTALLATION)

AN6-15A BOLT
E~41N GEAR:
AN960-616 WASHER
There should be no gap
between the collar and AN960-616 WASHER
upper retclining plate LLAR AN363-624 NUT
when inspected with the
aircraft on lacks. The
preload in the rubber
discs must be great
enough to maintain a
PLATE
complete extension of
the wheel during re-
traction. Understatic
weight,
ibie (0.00
a gap
to
Is permiss-

0.43 in.
SHD
E
~7/16 inl).
NOSE GEAR:
I /O
Under static weight, there
should be no gap between
GUIDE
the collar and upper ’e’
i ~3Y 1 PIN ASSY.
taining plate.

NOTE: Static weisht=

full fuel, less
passengers.

AN6-13A BOLT
WASHER
AN960-616L WAS HER
(2) I
AN363-624 NUT

5-22 REVISED NOVEMBER 196~

 H. ELECTRIC GEAR SYSTEM (OPTIONAL)

I. Operation.

T;ia gear retraction system is by the wheel-shaped switch

knob the upper portion of the flight panel. To raise the gear, the knob is pulled out and
on

moved up to its upper detent. An "air switch" is incorporated in the electrical circuit which
prevents landing gear retraction until a safe airspeed is ~ittained (See NOTE). The action of
the system may be monitored visually by watching the movement of the indicator mark through
the glass in the floorboard aft of the nose wheel well. A limit switch will stop the gear in its
retracted position. To lower the landing gear, the is pulled out, moved down, and placed
in the lower detent. A limit switch will stop the gear extension when the proper locking force
has been exerted to hold the gear down. There are three ways to check that the gear is com-

pletelydown and locked:

a. The green "safe-to-land" indicator light ton the left ~nel) will come on.
b. The black indicator marks, as deen through the glass in the floorboard, will be aligned.
c. No audible warning horn sound willbe heard when the throttle is retarded.

NOTE: An 80 mph air pressure equivalent must be applied to the pitot tube orifice to actuate
the airspeed pressure switch which permits retraction of the gear. Attach a 12-inch
length of 3/8-inch rubber hose (surgicaltubing) over the pitot tube end and pinch the
open end of the hose with a cotter pin. Rotate the cotter pin until the compressed air
in the hose activates the air switch.

2. Manual Operation of the Electric Landing Gear System.

a. Pull landing gear circuit breaker OFF.

b. Put pear switch in the gear-down position.
c~ Push crank engage handle forward.
d. Crank clockwise approximately fifty (50) turns to lower the gear.
e. Gear is down when green gear light is on-check gear position visual indication.

CAUTION: Do not retract gear with the manual handcrank. Use electrical retraction.

3. Electric Gear Inspection.

At each 100 hours of service, the electric gear system pivot points should be lubricated (See
Figure 2-9) and test run with the aircraft on jacks (See Figure 2-1). Check the landing gear
actuator for security of mounting, cleanliness, and indication of overheating or damage. Lubri-
cate actuator ball screw with recommended lubricant every 100 hours.

a. After 500 hours of operation and each 200 hours thereafter:

(1) Remove the actuator from the aircraft.
(2) Remove the end cap and wipe excess grease from gears.
(3) Visually inspect gears for wear as follows:
With open end of actuator toward you, rotate jack screw shaft counter clockwise to
remove all slack from ring and worm gears. ~Iake an index mark on one gear tooth
and on the inside of housing. Turn jack screw shaft clockwise until ring gear contacts
worm gear and check index marks.

Visible wear or backlash of 1/2 tooth or more requires immediate replacement of gears.
ALTERNATE PROCEDURE: Measure backlash by using a .025" diameter wire or .025"
thick shim as a feeler gage. If feeler can be inserted between gear teeth replace gears.
Repeat above prccedure after rotating the ring gear thru 900; Ie0O; and.2;00:
Repack gear box with recommended lubricant.
~5) Reinstall end cap and resafety.
(6) Reattach helm bearing to bellcrank (refer to page 5-24 Section 5,
paragraph B
for proper actuator adjustment and reinstallation instructions).

d. Perform retraction test through at least two trouble-free cycles. Check for:
Proper limit switch adjustments.
Position indicator adjustment and operation.
Excessive friction or binding.
Nose and main gear rigging.
Main and nose gear door-to-jamb rigging.

REVISED OCTOBER 1975 5-23

 5. Electric Gear Rigging Procedure.
a. Jack aircraft (See Figure 2-1) and remove access panel (See Figure 5-10).
b. Disconnect all retraction tubes and the actuator helm end from the retraction bellcrank.
Check the 7.50 actuator dimension (See Figure 5-14, Item 1). Adjust helm end as neces-
sary to obtain the 7.50 dimension. Position the ball returns on the actuator barrel so that
they face the actuator motor, then reinstall helm end on to the bellcrank.

NOTE: When installing helm bearing end in the bellcrank, position it freely so there
will be no lateral bind on the jack screw. Place one AN960-716L washer next to the
ball joint, (can be placed on either side) and shimremaining space with AN960-616
washers. This installation will prevent helm bearing from twisting too far, yet
provide adequate movement.

NOTE: Previous installation may have contained one large AN960-916 washer next
to the balljoint.
This washer must not be reinstalled, the AN960-716L smaller and
thinner washer described above is used as a replacement.

c. Rotate the emergency gear extension handcrank to obtain the 1.56 dimension (See Figure 5-14).
Adjust the retraction tubes so they can be slipped in place with zero preload.

d. The bell crank is now in the gear down-and-locked position (green light on). Now adjust
main gear retraction tubes so that the main gear rigging torque is between 240 and 280 inch
pounds (refer to figure 5-11). The difference in left and right gear torque should register
within 25 inch pounds of each other. Adjust nose gear retraction bungees so that they have
a deflection of 0. 060 inch in the down-and-locked position (Refer to paragraph VF2 and
figure 5-14, items 2 and 3).
e. Position limit switch striker arm so that the gear-down light switch has just closed (green

light on); secure the striker arm in this position. The gear is now rigged for the gear-
down position with allowance for overrun of the actuator after cutoff.
f. With all gear doors disconnected, run the gear up until the main gear is 0. 13 inch from the
bumper pad. Position the gear-up limit switch striker arm so that the switch has just closed,
then secure the striker arm in this position. The red gear-up light is now on and the gear
is properly rigged in the gear-up position.
g. Extend gear to down-and-locked position. Adjust gear door linkage (Refer to paragraph
VD Ih VD 3 for door rigging instructions). Cycle the retraction system through at least
two trouble-free test operations. Manually extend gear and recheck nose and main gear pre-
load for limits specified inparagraph d. above. The gear is now properly rigged and ready
for use.

ITEMI
FUS STA 33.0

,.,,i BALL NUT

BELLCRANK

7.50 .125 -I
1.56

ITEMB

GEAR BUNGEE
ITEMS

NOSE GEAR BUNG~E

L I
.060 --1~-- .060 DEFLECTION OF SPRING FROM
STATIC TO RIGGED POSITION FOR 1965
1962, ’63, ’64 MSTALLATIONS ONINSTALLATIONS

Figure 5-14
5-24 REVISED OCTOBER 1975
 FIGURE 5-15 SAFETY SWITCH g EMERGENCY GEAR CRANK INSTALLATION

F. S. 19~5 eRKT.

AEj742-8 CLAMP (Taps end Shellack Tube

Under Clomp)
i
AN3-3A
AN960-10
i
AN365-1032
2 PLACES

i FUSELAGE TUBULAR
STRUCTURE

SKIN

1MPERIAL272P ~EE1/4x1/8

AN526-63254 LINE
AN960-6
2 PLACES
PRESSURE SWITCH

SAFETY SWITCH DRIVE CONNECTOR

CABLE
ASSEMBLY

EMERGENCY CRANK 3

ol/Xi~

CIRCUIT BR

CIRCUIT BREAKER
(ONLY‘1966 g ON) 1 /5~ MSZ1919DG18
MSZ1919DG6
AN3-5A
AN960-10
ADEL 750-8 CLA~P AN365-1032
ANS26-832R8 (2) 2 PLACES
AN960-8 f2)
NN365-832 (2)

AN526-1032R6
AN960-10
4 PLACES

ARENS 141 NUT(4)

XN970-3 (2)

CABLE
HOUSING

REVISED NOYEMBER 1966 5-25

 71
rn
AN’J-S~ C)
hN960-10 C
m
AN365-1032 AN960-516L jtl
2 PLACES UOTI( SIDES OF BALL 71
cn
MICHO SWITCII
hN3-7h (2)
SWITC~I ACTUATOR OI
AN36J-1032 (2)
2PLhCeS

Fl
m

COVER
~J;
WINDOW ;O
AN4-22A
*I~sao-nla c~
AN365-121E\ CAL t)
AN3-12A
*NPb0-IO p
AN965-1032 jO
2 PLACES

~N3-IOA
ANPb0110
AH365-1032 VAH3-13A(2) i13

nN96a-I012b)
AN363-IOjZ n
-i
.´•´•J
DUKES DRIVE Z
CONNECTOR v,

AN536-10j2R4 V,
AN960-10(3~ -1
~N365-1032 71
2PLACES
DECAL
Z
GELL CRANK V,

AN)-IIA -S
AN960-10(5)
AN365-I 032 DUKES ACTUATOR I~
I~

;i) AN060-016
m AN4-2IA hN6-14A
AN060-416 AN060-616(4) O
AN365-42D AN365-1?4
~C
liv
Z
 YELLOW 71
m j, RED
-3
r/L~
-35~ CC)
r
ELECTRIC FUEL PUPP
CIRCUIT DHEAKER
;D
m
ACTUATORLANUI~IG GEAR
uc
~1-1
U
m -5
L. GEAR WAR)(I)(C
rn
m BL clCK llOR1(
r
m
-Z I- -´•ir
X
(h
I I/ss
n

00YIH ~O
neLAY n
-17
u,-J--: -15´•
38
c,
m

j
GEAII WX, DUSS
SWITCII CIRCUIT OREAKER
L~P
;o
-11
i

’/ss I --I~ I I I I
DN Z
up
RCLAY -7 1 I "t I I I I I I
x,
n
=r
-/9 TIIROTTLE
m
-9 SWITCII

-23 C POWER BOOST DOOR

SWITCI1 (MZOE)
UP LIMIT IWITCII xr n

NC
~t---’3Q0\
SAFETY SWITCH 1 I I Ln
v

DOWII LIMIT YWITCII

1 =198
-3/

-27
~-29 -s´• --29

’33----1 I;
NOTE:
ALL DASH NUMBERS

GEAR DOWN LIGIIT POWER BOOST DOOR I ASSOCIATED WITI1 AN

ASTERISK ARE PRECEDED

L
9 WARNING L IGHT F BY TtlE NUMBER 800007
’3b ~;r´•9 ALL OTHER DASI1 NUMBERS
(M20E1
~I ARE PRECEDED BY
I: -C41 NUMBER 950090
-.I

23 ´•92

GEAR UP LIGIIT
 YELLoW ry\
D
>------3 AUX. BUSS OJIR
LANDING GEAR
-51
71
IL~ ACTU~TOR
1 o
tx,
c
;o
m
Ln
s
PO

"I I I 1 -5’0 1
RELIAY -15
GEAR
SWITCH
mm
r

n
u,
-II
03 70
n
AUX, BUSS OAR C)
UP CIRCUIT DREAKER
RELAY -II
m;a
5~

70

-21 YWPITL Z
O
rto
-23 u,
39 I I I I I n
=0
SAFETY 1 SWITCH "I
POWER DOOST DOOR
-31 SWITCH (MZOE)
-25
61
--I
eL,
DOWN LIMIT
SWITCII -29
-61 JC-13 NI

o\
-"53 z
Yljl
IL
t 5( 1 IP

m
-21
65
-----nalGEAR
Y
30
DOWN LIGHT
1
I I
o
(I pnWcg tOOST DOO11
z
WARIvIlJG LIGHT (M20E)
o ajl 12
SC)IEMATIC S~IOWN WITH GEAR
DOWN 8 LOCKED, TI1ROTTLE I
CLOSED, ZERO AIR SPEED, GEAR UP LIGHT
m AND FILTERED hlR ON

~o 65--------------

THROTTLE
SWITCH GEAR WARNING HORN
 71

r: G,
nED
C
~n
m
YELLOW
rn
’2 GEAR SWITCI1 V1
O AIR PRESSURE
SdFETY SWITWI
‘O
m
ACTUATOR q;
s~7 I I I I
L
01 2
m m
;0 90 r
as
p m
n
1
;O
T)1ROTTLE GEAR I I I n
WARNING SWlfCH AUX, OUS
GEAR WARNING )IORN O

~1111 11 i o
ancul~roAR
onEnHER ;Dm
Y 1\PP 1(1 22
ZP
;o
Z
O
v,
n
1
rn
r
ON LIMIT SWrrcH UP LIMIT SWITCH
-1
POWER BOOST SWITCH \MZOELF)
t
n
POWER ROOST

h,
LIGHT I c,
x \O
No I~I/-----’ J~hl-, I ´•1
III( A
(M20EBFI OI

IP
34
85
O
Z
v

GEAR Y2
DOWN /-1~II. OEARUP
LIGHT \~JI11’ LIGHT
GREEN ~T RED

IO 14

cn
 SHOP NOTES

5-j0
 SECTION

CONTROL SYSTEIVIS
 SECTION VI
CONTROL SYSTEMS
A.

The ailerons, flaps elevators, and rudder are of all-metal construction. They are jig-built, using
hinges of machined e?L~rusions. The elevator and rudder incorporate an unusual method of construc-
tion. The leading-edge spar of these controls consists of a specially designed extrusion that allows
flush attachment of the skin. Lead counterweights are provided for dynamic balancing to prevent
flutter.

Push-pulltubes, rather than the conventional cable system, are used to actuate the controls. Rod
endbearings are used throughout the control system. These bearings are simple and dependable
and require very little maintenance.

B. fiE~VjOVAL ANDINSTALWTION

I. fiemowl and Installation of Aileron.

a. Remove controltube attachment from inboard end of aileron.

b. Remove bells, nuts, washers from three attach hinges.
c. Remove aileron by pulling straight back.
d. Replacement is accomplished by reversing the above steps.
e~ Rig the ailerons in accordance with rigging instructions.

2. Removal and Installation of Rudder.

a, Remove the rudder controltube attachment by taking off one bolt, nut and washer.
b. Remove bolts, nuts and washers from three attaching hinges.
c. Remove the rudder by pulli~ straight back.
d. Replacement is accomplished by reversing the above steps.
e. Rig the rudder in accordance with rigging instrucitons.

3. Removal and Installation of Elevators.

a, Remove control tube and assist bungee attachments by taking off all attaching bolts, nuts
and washers on each elevator.
b. Remove bolts, nuts and washers from four
attaching hinges on each elevator.
c. Remove elevator by pulling straight back.
d. Replacement is accomplished by reversing above steps.
e. Rig the elevators in accordance with rigging instructions.

4. ilemovalandInstallationof Flaps.~

a. fieomve ai~a-flap hinge fairing to expose flap link.

b. Remove flap link attachment by taking off one bolt, nut, and washer from flap attachment.
c. Remove hinge bolts.
d. Remove flap by pullipP down and out.
e. Replacement is accomplished by reversing above steps.
f. Rig the flaps in accordance with the rigging instructidns.

5. fiemovaland Installation of Empennage.

a. Remove fairing from both sides of tailcone at empennage attaching point.

b. Remove access panels from aft tail cone as needed to accomplish empennage removal.
c. Disconnect electrical and antenna connectors and clear
through bulkheads as needed.
d. Remove elevator and rudder control attachments from aft side of bell cranks.
e. Remove trim jack screw fitting from empennage fitting by taking off bolt, washers and nut.
f. Remove hinge pin from lower hinge assy after removing cotter pin from one end of pin.
g. Remove bells, washers and nuts from upper hinge brackets, one on each side of
empennage bulkhead while keeping weight of empennage neutralized by a cradle or man
power.
h. Set empennage in cradle until ready for replacing.
i. Replacement is the reverse of the above steps..

CAUTION: Be certain the elevator and rudder rod ends are properly lomted when attachment
bolts, washers and nuts are installed through bellcranks.

j. Rig trim system, elevator and rudder in accordance ’with rigging instructions.

dFI)TCCT\ n.T~V 1979 6-1

 FIGURE 6-1 CONTROL SURFACE BALANCING DIAGRAM

HINGE LINE

(Refer to parograph C. below for dimensions oml limits) UNBALANCE

FORCE

C1 CONTROL SURFACE BALANCI~fG

CAUTION: When repairing or repainting the control surfaces, the following limits must
not be exceeded.

Ailerons: M20D, SIN 101 thru 260, P/N 230000. M20C, S/N 1940 thru 2741, 2743 thru
2806. M20E, S/N 10lthru 399, 401thru 469.
Maximum allowable static unbalance force: 9. 6 inch/pounds
753 pounds or 12.00 ounces) at 12.75 inches aft of hinge line.
Balance weights: P/N 230009 1 2.

M20C, S’N 2742, 2807 thru 3466, MiOE, S/N 400, 470-1308, P/N 230015-1 -2.
Mavimum allowable static unbalance force: 7. 282 inch/pounds
57 pounds or 9. 1 ounces) at 12. 80 inches aft of hinge line.
Balance weights: P/N 230016 1 -2.

M20C E, S/N 610002 ON, P/N 230015 1 -2.

Maximum allowable static unbalance force: 7. 928 inch/pounds
62 pounds or 9. 9 ounces) at 12. 80 inches aft of hinge line.
Minimum allowable static unbalance force: 5.25 inch/pounds
41pounds ounces)
or 6.55 at 12. 80 inches aft of hinge line.
Balance weights: P/N 260016 501 502.

R’120F, S/N 660002, P/N 230015 503 504.

hr~a-uimum allowable static unbalance force: 12. 00 inch/pounds
94 pounds or 12.5 ounces) at 12. 80 inches aft of hinge line.
Minimum allowable static unbalance force: 10. 0 inch/pounds
78pounds or 12.5 ounces) at 12. 80 inches aft of hinge line.
Balance weights: 230016 503 -504.

M20F, SIN 66003 thru 370040, P/N 230015 503 -504.

Maximum static unbalance force: 7. 282 inch/pounds
57 pounds or 9. 1 ounces) at 12. 80 inches aft of hinge line.
Balance weights:’PI’N 230016 1 -2.

h120F, S/N 670041 gr ON, P/N 230015 503 -504.

Maximum static unbalance force: 8. 00 inch/pounds
625 pounds or 10. 000 ounces) at 12. 80 inches aft of hinge line.
Minimum static unbalance force: 5.25 inch/pounds
41 pounds or 6. 55 ounces) at 12. 80 inches aft of hinge line.
Balance weights: PIN 230016 501 502.

6-2 IiEVlSED MAY 1979

 Elevators: M?OC,D&E.
~Iaximum allowable static unbalance force: 15.5 inch ipounds
(1.22 pounds) at 12.75 inches aft of hinge line.

XI70F.
SIaximum allowable static unbalance force: 22.0 inch/pounds
(1.725 pounds) at 12.75 inches aft of the hinge line.
~iinimum allowable static unbalance force: 20.0 inch/pounds
(1.57 pounds) at 12.75 inches aft of hinge line.

Rudder: hiSOC, D E,
Maximum allowable static unbalance force: 6.9 inch/pounds
(.57 pounds) at 12.12 inches aft of hinge line.

h120F,
Xl~ximum allowable static unbalance force: 21.0 inch/pounds
(1.733 pounds) at 12.12 inches aft of hinge line.
Xlinimum allowable static unbalance force: 13.0 inch/pounds
(1.073 pounds) at 12.12 inches aft of hinge line.

D. RIGCC;G ASD

I. AileronRi~cring andAdjustment.

a. Use a straight edge to line up controlwheels. Adjust tubes linking control wheels to center
cross shaft untilwheels are level.

b. Adjust vertical control tube so that the inboard aileron bell crank is located l;lij-in. to the
left of center.

c, Adjust control tubes in wings so that the center of the mo-ct c?ntboard hole in outboard bell
cran4 is 4 and 39/~4 inches from the spar web.

d. Adjust aileron push-pull tubes so that the ailerons are adjusted from OI re 2"rlnsop in die
static position. All aileron travels are measured from the static position.

e. ?he aileron stops are located at the outboard bell. crank assembly and are accessible through
the access panel outboard of Sta. 147.75.

f. Set: Fi~re 6-4 (aileron travel jig which is used at wing Station 147.75).

g. See Fi~re 8-7 for aileron control system drawing.

h. See Figure 6-2 6-3 and Section VI-D.B. for wing-heavy correction procedure.

i. See page 6-7 for travel and rigging information.

2. ~rim Rigging and Adjustment.

a. Set stops jlocated in the belly under the floorboard-accessible through the fuselage access
panel) at trim for extreme travel (Figure 6-9~.

b. Adjust screw at rear bulkheads !Sta. 194.0~ so that trim travels in excess of specification
requirements.

c. set stops at trim to travels given in control surface specifications page 6-7.

d, See Fi~re 6-8 for trim control system drawing.

3, flapEii,ogin,o and Adjustment.

a. Adjust inboard linkage and outboard hinge stop to obtain travels given in control surface
s_Decifications page 6-7.

b. SeeFigureG-lOforflap conrrolsysremdrawing.

c. Adjust outboard hinge stop to align with aileron trailing adge.

REVISED NOVEMBER 1966
6-3
 d. Rudder Rigging and Adjustment.

a. Raise aircraft nose (refer to Section n-C.1).

b. Settrim controlinneutral.

c. Clampco-pilot’s rudderpedalsinneutral.

d. Adjust rod end bearing on nose wheel interconrlect to center the nosegear.

2. Adjust bungee in left exhaust cavity to neutral.

f. Adjust rod end of coarol n:0- at main .;par and control tube at f~uelage burk-
bearing rear

head and set rudder at approximately 1’ to the ri~e

g. Unclamp rudderpedal.

h. Set stops of control tube (accessible through the access panels in the left side of the empen-
nage) in stinger for rudder travels as given in Section VI-E.
i. See Figure 6-5 for rudder control system diagram.

j. See page 6-7 for travel and rigging information.

k. SeeFigureG-4 fortravelji,o.

5. Elevator Rigging and Adjustment.

a. Adjust the rod end bearing of control tube at control column for clearance of control shaft
to firewall and control column to fuselage structure.

b. Set trim control in neutral with stabilizer parallel to centerline of airplane.

c. Adjust rod end bearing of control tube at elevator attachment, and control tube at rear of
bulkhead for excess travel of elevators.
d. Set stops (accessible through the access pa.lels in the left side of the empennage) in stinger
for travels as given on page 6-7.

e. Adjustbungees as described inSectionVI-E.

f. See Figure 6-6 for elevator control system diagram.
g. Seep~,oeG-7fortraveland ri~gin,oinformation.
h. See Figure d-4 for travel jig.
6. Trailing EdgeTrimming.

A special pair of wide-nose vice-grip pliars are to be used to bend the trailing edges as neces-
sary (Refer to Figures 6-2 and 6-3.). To correct for left wing-heavy condition, berid down trail-

ing edge on right aileron; to correct for right wing-heavy condition, bend down trailing edge on
left aiIeron.

7. Hydraulic Flap System Bleeding (See Fi~res 6-10, 6-11. and 6-12.).

When flap action becomes erratic or when repairs recIuire the replacement of actuating com-

ponents, it is necessary to bleed the hydraulic flap system. Best results are achieved with the
use of clean hydraulic fluid from a hydraulic fluid system bleeder (pressurepot) pressurized
with air to approximately 35-40 Ibs.
a. R~movehydraulicfiuid reservoirventcap.
b. Disconnect hydraulic cylinder piston rod from jack shaft.
c. Open bleed valve in T-fiaing at hydraulic cylinder.
d. Pump handle and observe flow of fluid from bleeder valve into catch pan.
actuating
e. When fluid clear~ of bubbles and runs transparent, slide shaft and piston to bottom to expell air.
f. Pump actuating handle to re-extend piston and shaft.
g. Repeat steps e and f until all traces of air is removed from expelled fluid.
h. Closebleed valveand
i. Remove excess fluid from reservoir through side plug to re-establish proper level.

REVISED NOVEMBER 1966

6-4
 FIGURE 6-2 TRAILING EDGE TRIMMING DIAGRAMS

ILOMINi?L CO~IF!GLIRATiOr\l

S’)
C´•

FIED CONFIGURATIOF!

NOMINAI, CONFIGURATION

090.\ 07.t MAX.

NOTE: UNDER NO CIRCUMSTANCES MAY THE

TRAILING EDGE BE BENT UP. ANY MODIFIED CONFIGURATION
OPEN-HEAD RIVETS MUST BE REPLACED
AFTER MODIFICATION.

AILERON TRAILING EDGE TRIMMING

g~L
NOTE: ANY OPEN-HEAD RIVETS MUST
.os MAX. (BOTH DIRECTIONS)

BE REPLACED AFTER MODIFICATION.

RUDDER TRAILING EDGE TRIMMING

a-5
FIGURE 6-3 APPLICATION OF TRAILING EDGE TRIMMING VICE-GRIP PLIARS

iC~y

´•-~;-:n

6-6
E. CONTROLTRAVELA~ RICGI1~G SPECiFICr\TIOh’S (SEE FIGURE 6-4)

1. WINGFLAPS

Measured from wirt;T chord with travel board at wing Stgdon 147.75.

UP position 00 (alin with aileron) Tolerance 20

Takeoff position 15" GL120C,Eg;F) Tolerance i 1"
Approach landing position 33" Tolerance 00 -2"

2. AILERONS

hleasured from aiieron chord with aileron in the static position with travel board at wing Sta-
tion 147.75.

Down travel, both ailerons 8" Tolerance r 1"

Down travel, both ailerons 8" Tolerance i: 1"
UP travel, either aileron, may vary from 124i" to 17" with no additional tolerance.
Static position from 0" to 2" down

3. RUDDER AND NOSEWHEEL

Measured from fin c’nord with cavel hoard centered on river line at fin Station 13.5.

Left travel 73 Right travel ’3" Tolerance -O" i=L" for either

With rudder pedals in neutral and with trim assist unit at zero spring travel, rudder and
nosewheel settings are approximately 1’ right, i2"right.

3. STXBILIZER

nose-down setting (?~IZOC,D&E) 1" to 23~0

Maximum nose-down setting G~I?OF) ~4"to 2"
~ulaximurr nose-up setting C~?2OC,D&E) 44i" to 50
~laximum nose-up serring (M20F) 51/40 to 5!/40

5. ELEVXTORS

Measured from stabilizer c’nord with travel hoard centered on rivet line at stabilizer Station
lS.O and with stabilizer at 00 thrust line.

UP travel (M20C,D&E) 2´•1" Tolerance i 1"

Up travel UL2OF) 310 Tolerance i 7"
Down travel (~20C,D&E) 10W Tolerance ii"
Down travel (M20F) 23" Tolerance i 2"

6. ELEVXTORTR~1 ASSISTZ~NITS-

With stabilizer set at 3,50 for nose-up flight, adjust trim-assist units for el-
(Retractable evator-up of 19" i ~40at the zero
angle spring-travel position. ~L1ZOD (fixed
Gear) gear) aircraft must have an elevator-up angle of 13~" 4i" at the zero spring-
travel position.

~30F: With stabilizer set at j.50 for nose-up flight. adjust trim-assist units for el-
cvaror-up angle of ~5i" i 44" at the zero spring travel position.

7. ALLOWABLE FREE-PLAY LL~IITS

Allowable fore and aft movement at stabilizer tip .13"
Allowable vertical movement at stabilizer tip .10"
Allowable vertical movement at rudder trailing. edge .08"

REVISED NOVEMBER 1966 6-7

rlu BUBBLE: PROTRACTOR 71
\d o
C
;6
33 STh rn
16.0
ch

-----_s
b

~L-
~2, n
o
z

j;J
o
,EVATOR STABALIZER r

;6

rn

n
cn

FIN 9PA (3.3

~L-
s=--´•-

RUDDER

WING 6TA IC7.6

NOIE: SEE FIGURES 4-2 4-3 FOR STATION NUMBER

CALLOUTS
AILERON
 ~1 o
m a
;a
m
t7 /CA~ I
Z In
0<
5? ;a
c
m a
;a ‘4Vl’ll
m
;o
n
o
z

o
r
cn

v,

m
ADJUSTMENTS 3=
(3 PLACES)
z
cn
-I

-i

R
a
LUBRICATION APPLY z
a(MIL-L-7B70) OIL TO
ALL LINKAGE JOINTS.
HOURS-100 (See Fig. 2-9.)

BUNGEE
 71
t,
o I C
70
m
o*
rfh

r-"
r!
d
xl

z
-I
;a
o
r-´•

r-7 z
in

F
-I
o
c~S z

;o
m

2 LUBRICATION-APpLy L~ (MIL-L-7870)
OIL TO ALL LINKAGE JOINTS,
EACH 100 HOURS. (See
Fig. 2-~.)
P APPLY~POWDERL2D
GRAPNITE TO 710001 BALL,
CONTROL TUBE,
EACH 100 HOURS. (See Fig. 2-9.)
 LUBRICA.TION- APPLYL1(MIL-7-7870) 71
’2 OIL TO ALL LINKAGE JOINTS ~i
EACH 100 tlOURS. (Seo Fl,. 2.9.,
APPLY -r;- GRAPHITE rn
z

9 MIL-C-3278 GREASE TO
m GUIDE BLOCKS, 4 EACH SIDE,
m
EACH 100 HOURS. (Seo Flg. 2-9.) 5~
am r
00
;;O
(h( O
Z

5:
Z
--I

r
v,
´•i
v,

f
Z
I?
r

6
Ej
Z
 T1
C)
c=
70
rn
ch
ItD

a
z

Q
r

r
r

-I
c3
z

LUBR ICAT IOtJ A PP LY

;o
~MIL-G-3378 GREASE 59

~C-
I LUBRICATION APPLY
L/MIL-G-3278 GREASE TO
~cr
SCREW THREADS (740021)
EACH 250 HOURS.
APPLY--c2GRAPHITE
AND MIL-G-3278 GREASE
TO GUIDE BLOCKS,
EACH 100 HOURS.

(See Fig. 2-9.)

;D 1

ON ASSEMBLY NOS, 740002 AND 7400,s0-1, TRIM CONTROL WHEEL

z CHAIN ADJUSTMENT IS MADE BY LOOSEN-
;D
O< ING SIX SCREWS AROUND SI1AFT ON TRIM rn
m
AND ROTATING ECCENTRIC BUSH´•
mm ING,

OIr) :I CHAIN (BACK SIDE)

r

Irir") S:
z

CHA;N ADJUSTMENT.
BOL TS (2)
;a

ALLEN WRENCH SOCKET ~TO HOLD

BOLT WHILE NUT 1S LOOSENED) r

SET SCREWS (2)

HL18’-6-30 HI-LOK FASTENER
AN363 1032 NUT

GEAR BOX ASSEMBLY

ti’.
‘~FE1‘

STOPS
(REFER TO TRIM RIGGING 4 NUTS MUST BE LOOSENED BEFORE CHAIN
AND ADJUSTMENT IN SEC-
CAN BE TIGHTENED BY CHAIN ADJUSTMENT
TION VI)
STOP BLOCK ´•j I BOLTS,
 ’i

1
n
~L´•
RELEASE CONTROL
m
RESERVOIR
o

;I!
-a
n
o
z

Y
Y
m
3e~

5L
v,

I~
I~

HYD CYL
o
z

HYD PUMP VALVE ASSY

?D

z
o
FLAP HANDLE LUBRICATION Apply d
(MIL-Lo7870) OIL TO ALL
LINKAGE JOINTS
EACH 100 HOURS.
(See Fig. 2-9.)
 c,
c

AN6227-8 "O" RINGS (2)

E-1517 SEALS (2)
AN6227-1 "O" RING /HE-1516 SPRING

71

ap
a
c
0) 3:
a

´•~´•´•,i
AN6227-3 O RING ~3

S~t AN6246-3 s~ACK UP RINGS

r
s
rn
AN6290-8 O RING
1/4" STEEC BALL
V)

SPRING
m
r

AN6290-S "O" RING

3/16" STEEL BALL

HE-1518 SPRING

AN6227-6 "O" RING

(BETWEEN CAP AND SHAFT\

ASSEMBLY NO, HE-626 L- TURN THIS SCREW CLOCKWISE

TO SLOW
THE RATE OF "BLEED OFF" OF FLUID
8 12 SECONDS.
 ’I,

71
o
c
;o
rn

’;1
AN6227-16" O RING r
z
AN6246-16RING cl
rn
xl

t~
in

m
r

ASSEMBLY NOV HE-625

F. POSITIVE CONTROLSY~TEXI

I. Introduction.

a. The purpose of this section is to assist service and maintenance personnel in testing and
calibrating the SIooney PC System. Table 2 lists the most probable troubles that may be
encountered and the procedures to be taken to isolate and correct the cause of malfunction.
Para. 9 provides a step-by-step procedure for system analysis in the event that Table 2
does not cover the Drocedure.

b. Reference should be made to paragraph 3 (Ground Test Procedure) for ground checking of
the unit for proper vacuum settings, leaks, and command functions. Reference should be
made to paragraph 5 (Operating Instructions) for proper iii-flight checking and setting of
the unit.

c. This section deals primarily with the two-axis PC system. Sc h made to tile.
D~ertial Pitch Control (elevator control) system or to the hiagnetic i-leading Lock, as both
of these systems are dealt with in a separateOperationh Service Manual,

2. System Description.

a. General

The system is a pneumatically operated two-axis automatic-control device, which sanses

both roll and yaw while deriving its power from the aircraft engine-driven vacuum pump.
The system consists basically of a gyro-sense element which meters vacuum pressure to
a cylinder-piston servo assembly. On all aircraft in which this system is installed, these
servos are attached to the aileron and rudder controls, providing for a dual-control system.

~ZOTE: The 1967 and subsequent ~IZOC,E F models have a turn coordinator which replaces
the rate ~ro and operates by vacuum and electrical power simultaneously. The turn
coordinator also replaces the turn-and-bank indicator in these models.

b. Operation

I. Stability and control of the airplane about both the roll and yaw axes is Lbtained by tilt-
ing the rate-gyro (or turn coordinator) assemblyto a predetermined angle. This permits
a part of the roll rate and a pan of the yaw rate to act on the sensitive gyro-rotcr ele-
ment, producing an output signal. In this manner, a singlegyro elemant :s sensing
motion about two axes-roll and yaw-the~eby providing basically a two-axis system.

2. Roll y~y of the airplane caused by wind gusts, out-of-trim conditions, or airspeed
or

changes displaces the rate gyro (or tum coordinator). The resulting output signal is
coupled to a spool-sleeve rotary valve. The spool is rotated’inside the sleeve in pro-
portion to both yaw and roll rates of the airplane. The spool moves to a location be-
tween the vzcuum-su_Dply port and one of the outputports. The other output port is
qDened to atmosphere, bleeding the vacuum. The resulting vacuum differential is cirec-
red to the proper pneumatically operated servo so as to correct the original roll or yaw
error. In straight-and-level flight,, the vacuum differential is zero and the servos are
balanced.

3. Desired roll and yaw rate proportions of the total si~al are obtained by mounting the
rate ~ro (or turn coordinator) at a predetermined incline angle from truehorizontal
at cruise attitude. Changes in this angle, due to changes in the pitch attitude of the air-
plane, compensate for the corresponding change inaircraftstability
orily partially
characteristics. Foras the aircraft pitches up to climb, the decreased air-
instance,
speed and lower aerodynzmic loads necessitate more aileron control motion to main-
tain stability. The corresponding change in rate-gyro (or turn coordinator) tilt angle
produces increased roll-rate sensitivity, which partially compensates for the change in
aircraft stability. The opposite occurs as the airplane pitches down and airspeed in-
creas es.

REVISED NOVEMBER 1966 6-17

 4. Provisions have been made in this system to allow for a roll trim pilot command func-
tion. This roll trim may be used to compensate for asymmetrical fuel and passenger
loading and to optimize system performance in climb, cruise, and letdown configura-
tions. During normal aircraft operation in low-speed climb, it is necessary to utilize
a combination of right rudderlaileron control to maintain wings-level flight. Dispiac-
ing the roll-trim knob to the right will partially compensate for this condition. Like-
wise, during high-speed descent the normal left rudderfaileron trim required may be
accomplished by displacing the roll-trim valve to the left. However, the application
of the roll-trim valve is not intended to substitute for proper rigging of the aircraft
control system.

5. If the aircraft is properly trimmed by means of roll-trim adjustment, the unit will main-
tain average heading over a fairly long period of time; however, the unit will not
an
maintain an absolute preselected heading without the addition of a magnetic heading lock.
For optimum performance the aircraft must be rigged to fly needle-hall (or turn co-
ordinator) centered.

6. The system push-button disconnect, located in the control wheel, operates a pneumatic
relay which provides vacuum to the gyro-sense element (or turn coordinator), When
the push button is depressed, all servo vacuum supply is relieved and the is im- system
mediately inoperative. The pilot may then command turns in the normal manner without
overriding the system. Releasing the push button reactivates the system. However,
normal maneuvers may be readily accomplished without disengaging the
system, as
over-power forces recluired are small and no damage will result to either the aircraft
or the system.

c. System Performance.

The Mooney Lateral Stability Augmentation System is designed to be capable of maintaining

aircraft ecF~ilibrium over the o_Derational speed range under conditions that would otherwise
cause rapid spiral divergence. The device is also intended to maintain lateral stability and
prevent excessive changes in heading and airplane gyrations in turbulent air.

3. GroundTest Procedure.

Perform the following ground tests and procedures after completion of component replacement
and prior to starting engine or conducting flight tests:
a. All vacuum lines must be free of kinks and sharp bends.
Make certain that lines have been
purged or blown free of foreign panicles before the system.
operating
NOTE: Do nor operate the system at any time with lines disconnected From servo units.
Also, do not fly aircraft with servo unit bibs capped or lines plugged when they are
connected to servo units. Expansion within servo cylinder can block movement of
ailerons when aircraft is flown to altitude.

b. AircraftVacuum (PrimaryVacuum)
Stan the engine and increase the rpm to 1700 (If desired, an external vacuum pump may be
utilized if the vacuum source is attached to the engine side of the aircraft vacuum relief

valve.). Adjust the vacuum-relief valve to 4.75 4 .25j in. Hg. on the horizon or
gyro
directional gyro The primary vacuum reading on the PC system will be approx-
case.

imately 1/2 in Hg. lower than that read at the ~ro horizon (See ~ig. 6-15 and Fig. 6-17,
Sheet 2, PC 3.). ~Iake cenainthatthe vacuum relief valvl ´•sl!d regulator arefunctioning
properly.
NOTE: The vacuum-relief vdlve setting shoula bemaintained onthehigh side of the limit.

CAUTION

Permit no oil, grease, or thread lube, etc. to enter internal parts of the dry
vacuum pump. Clean all lines before reinstallin,o. Do notusethreadlube
on fittings.

6-18 REVISED NOVEMBER 1966

 c. Cutoff Valve Operation

i. The pneumatic cutoff vahe Inounted in the control wheel actuates the pneumatic relay
sequencing vacuum to the rate ~ro valve (or turn coordinator).

FIGURE 6-13 CUTOFF VALVE OPERATING CHECK DIAGRAM

PILOT VALVE

To _
I~eh’-l To VACUuw SOURCE
REMOTE
´•CC
GYRO
OR
TURN COORDINATOR
t
ApPLy SUCTION
TO f
HERE
ROLL TRIM
VALVE

To CUT-OFF
OTO10 in.
MU GAGE
CAV.GH VALVE
i
j!iI f

2. Disconnect,orzy line at pilot valve, insert aTee as per Figure 6-13 with a suction gauge
on one side and the other line open so that suction can be applied.

3. By mouth, apply about 5 in. Hg suction. Valve should not leak more than 2 in. Hg in 30
seconds.

4. Depress valve and vacuum should drop immediately, proving that tubes in control wheel
and valve are not restricted.

5. Upon release of valve, burton should return immediately to its normal position.

d. PilotValve-Operation

The pilot valve is in effect a pneumatic relay that shuts off the vacuum supply to the rate gyro
valve (or Nm coordinator) when cutoff valve is depressed and at the same time relieves the
vacuum in the servos so that the system does not load the controls when system is cut off.

1. Proper

a. To test pilot disconnect the gray line as shown in Figure 6-14 on the se-
vahe.
qsenced vacuum side and attach a 0-10 in. vacuum gauge. Witfi vacuum on the sys-
tem and the cutoff Valve not depressed, the reading on gauge should be 4.0 in. Hg.+
(wiSn primary vacuum at 4.75 in. Hg.!.

REV1SED NOVEMBER 1966

6-19
 FIGURE 6-14 PILOT VALVE OPERATING DIAGRAM

TO VAOuvn
SOURCE

In

TG PUSH BUTtON
VALVE
ill’ r
PILOT VALVE

OTO10 ilGHG
VACUUM GAUGE

b. tTFon depressing cutoff valve, gauge should drop to 0 in. Hg. If vacuum is not re-
lieved and there still remains a reading on gauge, pilot valve is not shutting off
completely and should be replaced.

e. PrimaryVacuum Reading

FIGURE 6-15 PRIMARY VACUUM READING DIAGRAM

(1965 1966 MODELS)
TEST PO I NT ~I REMOVE CAP AND ATTACH 0-10 in,
HG VACUUM GAUGE ON TO TEST
BIB
GYRO

i
0-10
(A)
(B)

PRIMARY
VACUUM
REMOTE GrRO READING

(A) TEST VACUUM GAUGE TO READ (~PRIMARY

(8) LSA-I GYRO

6-20 REVISED NOVEMBER 1966

 f. Gyro Rotor Speed Adjustment (1965 8 1966 models)

To assure proper gyro response it is necessary that the gyro rotor be operated at the proper
rotor speed. Fast active corrections. Rotor speed can be checked
by the following test: (A vacuum reading of 3.5 in:Hg..il.0 in. -0 in. Hg.. is recommended
for proper operation.).

FIGURE 6-15A GYRO ROTOR

SPEED AD~USTMENT (~965 8 1966 MODELS)

1. Installa0-10 in.Hgvacuumgauge
RE3tRI ttOR
as shown in FigureG-15A. Con-
ADSUSTMENt ~37 ,TESt Ble nect the vent side to test bib#2.
Connect the suction side to test
bib 81. The vacuum gage will in-
dicate the vacuum (3.5 in. Srg,
f1.0 -0 in. Hg) across the rotor
which control~ its speed.
G’YRO XtEST Ble
n\ i 1\1 2. To change the rotor speed, adjust
point ,U3, shown in
Figure 6-15A,
SUCtlON VEHt /I fO Obtain the required 3.5 in. Hg

(f1.0 -0 in. Hg) on the vacuum

O
0_10ii-~9. gauge. Also ref~r to FigureG-17,
Sheet 2, PC 2. Clockwise rota-
VACtIUM tion of adjustment #3 on Figure
GAUQE 6-15A will decrease the vacuum

REnotE GYRO reading.

NOTE: This adjustment is EXTREMELY IMPORTANT, and care shauld;betakento

make certain this adjustment is accurate. With Group i and Group nI auto-
pilot installations, the differential vacuum reading across test bibs~land
j~2 (Figure 6-15A) should read 4 in. Hg.

3, For further Group I and Group III autopilot maintenance information covering 1965
8 1966 models, refer to Operation Service Instruction manuals 11968-1 (Mooney
Nzv-couplerfHeading Lock) and 11968-2 (Mooney Pitch Control). Manuals 11990-1
and 21990-2 cover 1967 and subsequent models.

4. Replace the test bib caps and make certain that no leaks exist around these caps.
Manually displace the roll-trim knob counter-clockwise as far as possible, ~he
control wheel should tend to turn to the left. Turn the roll-trim valve fully clock-
wise and the control wheel should tend to turn to the right. Center the roll-trim
valve. During taxi operations the control wheel will tend to turn opposite to the air-
craft if the ~ro is properly phased.
4. Roll-Yaw System.
a. Rate Gyro Val~e Cencermg (1965 1966 models)
Vacuum differential may result from the rate-gyro
valve be~ing off center while the aircraft
is stationary the ground. Yawing the aircraft will precess the rate gyro. In this manner
on

it may be deten?ined whether or not the pneumatic null is permanently offset. If there ap-
pears to be a permanent offsk to the right or left, greater than a .2 in. Hg differential, the
rate-gyro valve should be repositioned. Only minute movements of the valve stub are re-
quired.
b. Roll-Trim ValveCenterin,o
rorr
Roll trim valve stops are factory adjusted and should not be moved. The
knob should be centered (dot at top) with same degree of rotation right
and left (Fi~re 6-17, Sheet 2, PC 3).

NOTE: 1967 C, E 8 F models have a turn coordinator which has a roll-trim knob on the in-
strument front. If the turn coordinator is removed (rec~iring removal of the knob),
the knob should first be centered for ease of relocation.

REVISED NOVEMBER 1966 6-21

 FIGURE 6-16 RATE GYRO VALVE CENTERING
DIAGRAM (1965 a 1966 MODELS)
~UTE: ~lake certain aircraft i- in
CE*TEIIUG ITUS

wiIlgs-level attitude for this

check.
ILLEN SiT IOE´•
´•urrOCr C*LI1F

I1LOrS~I Adjust vahe 10-0-10 in.

to center
r rPvEri*~
Hg. differential gaugeinstalled a-
cross red and green #yro bibs. It
will be necessary to temporaril~

j remove the red and green servo

tubes for this test.

i SOTE: The turn coordinator in-

stalled on 19(i7 sub´•e-
quent models is pre-centered
and the gyro speed is pre-
set at the factory. The in-
strument should be replaced
when a malfunction is found

ku´•k´•l*~l
J I that i; attributed to the in-
strument itself.

GaEE*

c. Tazri the aircraft check for proper movement of the controls. Yaw to the left to see if the
to
control wheel moves to the Yawinp to the right should nra;te the control wheel turn
right.
to the left. if the rate gyro or turn coordinator phasing is reversed wheel moves
in the direction of the turni the tubing leading from the ~jro or rum coorhinator to the servo
is reversed at the bulkhead fitting.

5. Operatin,oInsrructions and

a. Before takeoff. check force, required to overpower the vacuum servos. Depress the cutoff
button to see if vacuum forces are rdieved.

b. Climb to a safe altitude in smooth air and trim airplanefor straight-and-level flight at
cruise configuration. IF it is apparent that aircraft is notproperly rigged. rerigging will
be necessary before continuing with the flight test.

c. Depress the control wheel mounted cutoff button; the system should become inoperative.
Upon release of this cutoff button the system should re-engage. Depress the cutoff button
and command a era. Release the cutoff button and the aircraft should re-

cover smoothly.
d. Szrring the Per :´•oli rrirll rnnr-nl ~nr’ ~i!! normally compensate for asymmetrical fuel and
passenger !nads i´•, rn~i-- r;zlkcted roll trim settings
T~iilj´• aenerally will not bank
the aircraft Illsre than ’L To J ~r one burrh of standard-rate turn.

NOTE: The roll-trim %nob should be aPF..~hlll:2T-iJ centered during level Flight. However.
a roll-trim knee setting as much as 90.’;rom center during wings-level flight doe:
not necessarily indicate a Pr3 system mali~lnction.

e. The PC system may easily be overpowered at any time. ~ince the system has no rlutche~
or electric motors. it can be overridden indefinitely with no resulting harm.

f. Upon completing the flight test. make a log hook entry showing that the PC (or autopilod
system has been test flOwn b~1211 appropriately rated pilot (Ref. FAR Part 91.16 A.!.

6. Emergency Procedures.

a. If a malfunction should occur in the unit. it can be overridden merely withpressure on the

flight ~conrrols, and the entire system can be disengaged by depressing the pushbutton.
6-22 REVISED NOVEMBER 1966
 b. If a loss of vacllum supply occurs as indicated by a low-~acuuln ~arllirlR li~ht. the ~vsrzm
will become inoperative. So adverse effect ilpon the air-worthiness of the aircraft will be
encountered. check for leaks in the entire vacuum system should be conducted as soon
as possible. If no leaks are found. check the vacuum source (pump) and the aircraft vacuum-

relief valve.

hIaintenance.

a. Once the system has been adjusted, it should require no further maintenance other than in-
spection of the various units for security and general condition.

h. The gyro filter should be replaced as required. X partially clogged filter will produce a
sluggish gyro sense-element response. However. the turn coordinator jinstalled on 1967
and modds’i will function by electric power should the vacuum filter become
clogged.
c. If the high or low vacuum light illuminates, inspect the entire aircraft vacuum system for
leaks, stop_Da,oes, etc.

8. Trouble Shooting.

Table 2 below lists the most li~ely-to-be-encountered flight control malfunctions, with causes
and steps to be taken to isolate and correct the malfunction. In the event that a malfunction is
not covered here, refer to paragraph 9.

TABLE 2 POSITIVE CONTROL SYSTEM TROUBLE SHOOTING

MALFUNCTION PROBABLE CAUSE REMEDY

I. Hi or I,o vacuum Faulty vacuum pump or

Perform Test gl and adjust
light. relief vafre. vacuum if necessary.
Faulty svirch. Replace switch.

2. Aircraft hunts in (1) Partial closure or leak- Perform Test ,"2.

ni~ht. ing servo vacuum line.

(2) Improper ,oyro operation. Perform Test 93.

(3! Improper vacuum supply Perform Test ~1 and adjust

to valves and instruments, vacuum if necessary.

(4) Faultyservo. Perform Test ~2.

3. Xircraft does not (I) incorrecttrim of Check aircraft rigging and

hold directional aircraft. adjust as recluired.
heading.

Exco,ss friction in Examine the primary control

(2!
system determine that
to no
system.
excessive friction exists.
~Lubricate all hinge points as
depicted in Figure 2-9.)

(3) Improper vacuum to valves Perform Test ~1 and ~2 and

and instn~ments. adjust vacuum.

(8 Faulty rategyro. Perform Test f3.

REVISED NOVEMBER 1966

6-23
 TABLE 2 (Conrinued)

MALFUNCTION PROBABLE CAUSF, REMEDY

4. Aircrafr recovers in one (1~ Restriction or leak in Perform ~est ,"2.

direction but not the I servo vacuum line.
other.
i2, I.oose or disconnected Perform Test a?.
servo cable.

(3‘! Inoperztive servo. Perform Test 92.

t~i Faulty rategyro or Perform Test ge.

turn coordinator.
Replace turn coordinator.

5. .-tircrzft tends to roll i I.eak or pdrtial rznrictionin Perform Test

to one side. servo vacuum line.

!2’1 Improper gyro operation. Perform Test g3.

!3,’ I72Ul~y,-ervO; lo0seordis-

connected cable. Perform Test j7,.

Faulty rate gyro, valve Perform lest f´•l.

off center.

(55 Faulty turncoordinator. Replace turn coordinator.

Continuous wheel osci- (li Gyro rotor speed iinproper. Perform rest 43.
lation in smooth air.
(2j Too hi~h vacuum setting. Perform Test 51.

13) Inoperative rate gyro. Perform Test ~4.

(4! Faulty turn coordinator. Replace turn coordinator.

recovery from turn (1~ Excessive friction in Examine the primary control
in onedirection. primary control system. system to see if excessive
friction exists. Lubricate
all hinge points as depicted
in Figure 2-9.

!1~ Leak or partial restric- Perform Test e2.

tion in servo line.

i3i Loose ordisconnectcd Perform Test

servo cable.

14i Faulty servo. Perform Test ,"2.

(5! Improper rate gyro operation.) Perform Test

REVISED NOVEMBER 1966

\;-24
 9. Trouble Shoorin,oTests.

a. The following tests are to~ be conducted as directed in Table 2. As each of the tests is con-

ducted, the reading or indication should be if, in any test, the reading differs from
the correct indication, follow the corrective measures as indicated.

In the event that malfunctions are not covered specifically in Table 2, the following tests
should be used as a step-by-step procedure for thorough system analysis.

b. Test #I-Vacuum Settings

Start the engne and increase the rpm to 1700 gJhen desired, an external vacuum pump may
be utilized if the vacuum source is attached to the engine side of the aircraft vacuum-relief
valve~.

Adjust the aircraft vacuum-relief valve to produce 4.75 Hg(-I-.25 in. Hg) output as read
at the of either the ~ro horizon or directional gyro (See Figure 6-15 and Figure 6-17,
case

Sheet 2, PC 3.). Always adjust to the high side of the limit.

c. Test 32-Vacuum Line and Servo Leak Test

Visually inspect all lines to eliminate possible defects such as kinks, restrictions. or obvi-
ous breaks.

Disconnect line from the back of the gyro sense element and install vacuum-test gauge in
the open end of the line (See Figure 6-15 and Fi~re 6-17, Sheet 2, PC 2.!. Rotate aircraft
controls so as to extend the piston of the respective servo. This will provide a vacuum in
the system which may be read off of the test suction,azuge. Hold the control surfaces solid-
certain that the
ly. making piston is stationary. If no leak in the system exists, the test
suction gauge reading will remain constant. Exercise care that all tubing connections are
d~t and will not produce a leak. When checking that tubing which connects to the roll-trim
valve, they must be removed from the valve and securely plugged. The valve has atmosphere-
bleed ports which preclude this leak test unless the tubing is plugged.

Li´• TeSt~3-GyrOROtOT Speed

Refer to Figure 6-15i\. Attach a 0-10 in. Hg vacuum gauge to test bib,U1. With the vacuum
relief valve set as described in paragraph 3.b., a reading of approximately 4.25 in. Hg should
be obtained at this point. This reading will vary depending upon the setting within the coler-
ance of 1.75 in. Hg (+.25 in. Hg).

UncaD rest bib 82 as shown in Figure 6-15A and Figure 6-17, Sheet 2, PC 2, and attach a
line from the vent side of the suction gauge to test bib f2. Adjust the set screw called out
in Fi~re d-15A andfigure6-17, Sheet 2, PC 2 to a reading of 3 in. Hg(f.5 in. Hg, -0 in. Hg!.

e. Test ~d-Rate GyroValveCentering

Refer to Figure 6-16. (1965 1966 models). Disconnect red and green tubing from back of
rate ~ro. Attach a differential gauge across~the two´•bibs and rotate valve until a 0 in, dif-
ferentialis obtained.

Yaw aircraft and note needle deflection on differential

gauge indicating rate gyro deflection.
When aircraft stops yawing. gyro should come back to center within ~.2 in.
Hg. The rate
EIY’O O’ Nm coordinator should be replaced if it does not center properly.

REVISED NOVEMBER 1966 6-25

 f. Test ,U5-lnstallation Inspection

Rotate the aircraft controlwheel. The attachment to the respective servos must be tig’nt and
the servo piston extended with rubber seal not stretched (See Figure 6-17, Sheet 3, PC 8.).

Examine the primary control system to determine that no excessive friction exists. Lubri-
cate all hinge points as-depicted in Figure 2-9.

Also refer to Figure 6-17, Sheet 3, PC 4 when trouble shooting system. Be sure the chain
between the aileron bell crank and the aileron servo does not have a twist. This can be
corrected by repositionin,o the rubber boot on the servo.

Refer to Figure 6-17, PC 2. 3, ´•i. 5, 6, 7. and schematics for proper line routing and color
coding.

SHOP NOTES

6-26 REVISED NOVEMBER 1966

 ~22!
PC 1 "C,
m
C

133
F,S, 125

uc
U
F,S, 103 z
-c--5TA.16
F,S, 03

~1415;:-I ~Tfv, rQ

2" m
~lsfi’ n
’i; o
z

i: o
r

TUBING
YRO AND RUDDER SERVOS v,

CROSSOVER SEE PC 2
SEE PC rn
OTE 1 5
NOTE 2
NOTE 3

AILERON SERVO
SEE PC 4

PILOT VALVE, VACUUM REG,

CONTROL WHEEL
SEE ec 3

W,S, 59.25

NOTE 1 500-6 I-tvCO GROMMET 1N VI.S. 43.50, W.S. 59.25.

G51B NYLON CATERPILLAR CROMMET 1N ALL W,S, 147.75
OTHER RIGS. W.S, 103.5
NOTE 2 AN742-60 CLIP, ANS16-8-R7 OR EQUIVALENTS.
~n
NOTE 3 3/ 81’ I.D, 7" LG SCUFF COVERING FLEXCO
~i 4199 OR EQUIVALENT.
 SHEET 2,
C7965) INSTALLATION
ADIUSTMENT SET SCREW
FOR 3 in t.5-.0 Hg DIFFERENTIAL PRIMARY VACUUM
BETWEEN BIBS 1AND 2

AFT RUDDER
SERVO 2980
TEE 11873-10
2 PLACES

Alft FILTERS

PC 2

GREEN

I BLACK

RED
1190-25
REMOTE GYRO
I: GRAY

ADEL 668-12-6 FR
CLAMP or
TEST BIB TEST BIB EQUIVALENT
NO. 2 NO. i FORWARD RUDDER
SERVO 2980-1
AIRCRAFT VACUUM
REGULATOR

PC 3

ROLL TRIM VALVE

2985
PUSH BUTTON i
VALVE 2960

I’ x

PILOT VALVE

1124’6-3 FITTINGS
2 PLACES

8-28
 SHEET 3

~CATERPILLAR
GROMMET
WING STA,
147,75

I;

29s3~
AILERONSERVO

PC 4
AILERON

BELL CRANU

210152 BRACKET .’i r.

A6 CORBIN CLAMP

3/8 O.D. POLY FLOW (RED) L.H. YjlNG INSTALLATION

(GREEN) R.H. WING INSTALLATION
1

AN36j-524A NUT
I AN970-5 WASHER

500-6 HYCO GROMMETS

PC 5

3" G518 NYLON CA;TIERPILLAR~ ADEL 758-6 CLAMP OR EQUIVALENT

Z PLACES
GROMMB US.E 3M 2´•140-2609
kDHE’S’rW;E OR EQUlVA’LENT SECURE WITH:
AN515-8-R8 SCREW
2 P’LI;ACES
el AN365-832A NUT
500-6 HYCO GROMMET

F.S. 103

2" STRIP G51B CATERPILLAR

GROMMET USE 3M 2140-2609 6-29
ADHESIVE OR EQUIVALENT
 SHEET 4
(1965 PC SCHEMATIC)
AIRCRAF~ YACUUY
REGULATOR

IILICI:

PILOT
VALVE BUtr (IUCL:
2965

DIRECTIONAL I I I IGYRO
GYRO I I I I HORIZON

tPFI

BL*CX

BUCI:
ROLL Ti~lll
PUSH
VALVE
BUTTOX
2385
VALVE
2960
tREr

GREEI( I I RED

FED RED

GI1EEII, GIEEN
LEFT AILERON
SERVO
2983 RIGHT AILERON
1 Icnrw I I IRED
SERVO
2983
LEFT SEPUEWCED PRIYI~PI FIGHT
TUlln VltVUY Y*CUUY TURH

11900-25 REYOTE GYRO

I(ED

FORIARD
RUDDER SERVO
2980-1

AFf
RUDDER SERVO
2980

CREEII

6-30
 SHEET S
(1966 INSTALLATION)

FORWARD RUODER
ROLL TRIM VALVE PUSH BUTTON
SERVO 2980´•1
2985 VALVE2960

AFT RUDDER
5ERY0191~

AILERON SERVO
298)

WING STA.
147.75

1~
PC 6
fr\u
AILERON
BELL CRANK

BELL CRANK EXTENSION

ASSEMBLY 1783
REa.. GROUP 1 8 3. OPT. PC
INSTALLATION(I INCH)

TEST 818 NO. 1

REMOTE GYRO
119830
AIR FILTERS
AIRCRAFT VACUUM
REGULATOR TEST 818 NO. 2
o

PILOT VALVE

6-31
SHEET 6
(1966 SCNEMATIC)

AIRCRAFT VAaJUI
RH;OLATOR

BLAQC

BLACI(

tR*Y _I T\L rY leurx

11#Oj0 PILOT
FILTER BLACK
VALVE
REF. 2~5

DIRECTICE14L I I nCRIZCNTAL
GMK) I I I I OYRO

ROLL TRIM
VALVE
2985
RED

BcACn
tiiEEN

C~A’I I
ICUJOFF
an, I I VALVE PILOT CCFFTROL
2S~Y1 WHEEL

GREEN

RED t1EW

LEFT nlLERON i I R!CHT AILERON

SERVO I I SERVO
2983 1 1 298]
GREEh

FCRYAKD
RCM)Ea SERVO
29801

AFI
RUDDiS SERVO
2980

RED

6-32
 SHEET 7
(7967 ON INSTALLATION)

PUSH BUTTON VALVE

RUDDER
TUBES

a
TURN COORDINATOR

3
ROLL TRIM
CONTROL
IO´•COB
FILTERS 1

ROLL TRIMVALVE
I RUDDERSERVOS
I~

~s-"
VACUUM
REGULATOR O~d BULKHEAD
FITTINGS

PILOT VALVE TURN COORDINATOR INVERTER

AILERON SERVO

REVISED NOVEMBER 1966

6-33
SHEET 8
(1967 g ON SCHEMATIC)

BLACK

BLACK
VACUUM
BLA_CK_ I 1 REGULATOR

BLACK I ~L. 1. ~L I BLACK

FILTER

BLACK

PILOT VALVE

MIS BIB
PERMANENTLY
CAPPED

TURN COORDINATOR

FfinHN1S GRAY

CUTOFF VALVE
GREEN
(PUSHBUTTON)
LEFT WING AILERON
AT PILOT CONTROL
SERVO (RIOHT TURN)
WHEEL
RED

RED I n_ GREEN

RIGHT WING AILERON

SERVO (LEFT TURN)
RED

FORWARD
RIGHT
TURN

AFT
LEFT
TURN

GREEN

RUDDER SERVOS

8-34 REVISED NOVEMBER 1966

 SECTION

FUEL SYSTENI
 SECTION VII
FUEB. SYSTEM

A. GENEIUL

The fuel system consists of inte,oral sealed fuel cells located in the front portion of each wing. These
cells feed to a selector valve which includes a strainer and sump drain. From the selector, fuel is
fed to the electric boost pump, engine-driven pump, and then to the carburetor or fuel injector.

13. TROUBLE SHOOTIf*TG

Troubles peculiar the fuel system are listed in Table 3 along with their probable causes and sug-
to

gested remedies.When trouble shooting, check from the power supply’to the items affected. if no
trouble is found by this method, the trouble probably exists inside individual pieces of dcluipment;
which may be removed from the aircraft and an identical unit, tested and known to be in good con-
dition, should be installed in place.

TABLE 3 FUEL SYSTEM TROUBLE SHOOTING

TROUBLE CAUSE REMEDY

Fuel gage not indicating. Broken wire Check and repair.

Transmitting unit faulty Replace.

Float hung in fuel cell Check and repair.

Circuit breaker out Check and reset.

Fuel gage indicates full incomplete ground Check ground connections at fuel
when tanks are not full. transmitter in tank.

No fuel pressure indica- No fuel in tanks Check and fill ranks.

tion.

I~efective fuel pump Check pump for proper fuel pressure

buildup. Check for obstruction in elec-
tric fuel pump screen. Check engine
fuel pump diaphragm and check-valve.

Pressure low or pressure Obstruction in inlet side Check fuel lines and remove obstruc-
surge. of pump tions.

Faulty diaphragm in en- Replace pump.

gine pump Check fuel lines and repair or tighten.

7-1
 C. REMOVAL AND INSTi~LLATION OF FtrEL PUMPS

i. Electric Fuel Pump Remova1(1964 ON).

a. Removetheelectricallead attheknifedisconnect.
b. Disconnectground wire.
c. Disconnect outlet hose and drain line.
d. Removeleftexhaust cavitypane1(310010).
e. Disconnect pump inlet line (from inside).
f. Remove jam nut and washer from pump inlet fitting.

g. Remove clamp and lift pump off attach bracket.

2. Electric Fuel Pump Remova1(1962-1963 M20C; 1963 M20D).

a. Removetheelectricallead attheknifedisconnect.
b. Disconnecttheinletand outletfuellines.
c. Remove two fuel pump mounting bolts and carefully removepump.
d. Hold the pump manually and turn the cover in a counterclockwise direction and remove

core.

e. Carefully remove the screen and rinse it in gasoline or kerosene to thoroughly clean it. If
screen is badly distorted or collapsed, replace it.
f. Clean fuel pump cover in the same manner as in Step "e".

3. InstallationofElectric FuelPumps.

Reverse procedure above.

4. Engine-driven Fuel Pump.

Refer tothe appropr;ate Lycomin,o overhaul manual for instructions in removal and assembly
of the engine-driven fuel pump.

D. REMOVAL AND MSTALLATION OF FUEL SELECTOR VALVE

i. Remova1(1964 &ON).

a. Removefuel selector valvehandle.

b. Unscrew quickdrainpull ring.
c. Disconnect right and left fuel inlet lines at valve body.
d. Remove fuel outlet line at body.
e. Remove four screws holding fuel valve assembly to mounting plate(610038). Fuel valve
assembly can now be removed.
f. SeeFigure 2-4 for illustration of fuel selector valve assembly.

2. Remova1(1962-1963 M20C; 1963 M20D).

a. Remove fuel selector valve handle and pointer.

NOTE: Use caution when removing pointer plate as this plate releases the tension of the
detene pin and spring.
b. Remove detent mechanism (610021) carefully.
c. Remove ri~t and left fuel inlet lines at valve body.

7-2
 d. Remove fuel outlet line at valve body.
e. Remove four screws holding fuelvalve assembly to mounting plate. Fuel valve assembly
can now be removed,

3. Installation.

Reverse the procedure above.

E. FIELD REPAIR OF FUELTAMS

1. General.

This instruction establishes the procedure to be used in repairing the integral fuel tank. Tank
repairs should not be attempted untilthese instructions are read.
2. Approved Materials.

a. Sealants: (NOTE: Sealant must meet U.S. Government specifications as indicated.)

A2 or CS3204-A 1/2, A2 Brush coat sealant.

~ES-8802 ClassA)
PR1~22-B 1/2, B2 or CS3204-B 1/2, B2 Filleting compound
(hi~EES-8802, Class B) wing-wallpanel
sealant.
I?IZ1403-G-B2 Sealant-removable
access panel.

b. PR1005-L Protecting-coat
sealant.

c. Gloves-Polyethylene

d. Turco 657 T~iipe Solvent

e. Cheesecloth

f. Turco LeaBDetector

g. Methyl Ethyl Kegton (thinner for PR 1005-L)

All of the above materials may be obtained from your local Mooney distributor or dealer.
Sealants may be obtained from either the Products Research Co.,~(PRXXX) at the follow-
ing address: 5454 San Fernando Glendale, Cdlifornia, 91209; or Chem Seal Co.,
(CSXXXX) at the following address: Roa4
120 Sherman Wag, Sun Valley, California, 91352.

REVISED JULY1980 7-3

 3. Handling and Mi~ing´• Sealant.

a. Sealant Material Characteristics:

1. Application life is the time that the mixed compound remains suitable for application.
Application life is always based on standard conditions of 750F and 50~ relative humidi-
ity. For every 100F rise in temperature, application life is reduced by half, and for
every 100F drop in temperature, application life is doubled. High humidity at the time
of mixing shortens the application life.

2. Maximum unopened container storage life is six (6) months at 850F.

TABLE 4 TANK SEALANT APPLICATION LIFE AND CURING TI~UE

AT 750F AND 50 PERCENT RELATIVE HUMIDITY: PR 1221 SEALANT

Class A Tack-free Time tin hours) Curing Rate tin hours) Application Life tin hours)

PR1422-A 1/2 10 30 1/2

PR1422-A2 36 72 2

CS3204-A 1/2 8 30 1/2

CS3204-A2 24 72 2

Class B

PR1422-B 1/2 10 1 45 1/2

PR1422-B2 36 1 72 2

CS3204-B 1/2 8 30 .1 1/2

CS3204-B2 24 12 2

PR14,03-G-B2 ACCESS DOOR SEALANT

Class B

B-2 10 36 2

b. Mixing of Sealants

1. Handmixing.
2. Kits consisting of the proper proportions of base compound and accelerator should be
used.

3. Slowly stir, to avoid excessive air entrapment, the accelerator into the base compound
and thoroughly mix approximately seven to ten minutes. Be sure to scrape the sides
and bottom of the container in order to include all compound in the mixture and to in-
sure uniform blending. Scrape mixing paddle periodictillg to remove unmixed compound.

7-4 REVISED JULY1980

 4, Take a small amount of sealant from the mixture with a clean alumnium strip and spread
the sealant, then visually examine the film of sealant to ascertain if the accelerator is
visible in particle form. If particles of accelerator: are visible, continue the mi~ing
operation. If coarse particles of accelerator persist after mixing, the mixed batch and
rem~iTlinP- accelerator willbe rejected.

5. Put a small amount of sealant in the accelerator container and mix to assure that all
of the accelerator is mixed into the sealant.

4. Sealant applicationIns~uctions.

The following instructions are for the reapplication of sealant removed in order to repair tank
leaks.

a. BrushSeakant

1, Apply a brush coat of sealant compound PR1422-A 1/2, A2 or CS3204-A 1/2, A2 over
seams, rivets, nuts, and bolts if removed for repair.
2. A one-inch stiff paint brush is recommended for this operation. Brush strokes should
be parallelto seams forcing the sealant into all gaps. Use a circular brush action to
deposit an even coat of sealant around rivets, and bells. Coat should be approx-
imately 1/32 of an inch thick.

3. Coll3iderable brush action should be used to force sealant into all small crevices to ob-
tain good adhesion. Air pockets trapped under the sealant due to improper application
will open up in the form of a hole or void soon after it has been applied. Repair should
be made by pressing the sealant in place with 9 spatula while it is still in the applica-
tion life state.

4. In cases where the to_D of a fla~ge is .040 inches or less and where application of a suc-
cessful fillet would not be clearly defined, apply two brush coats of sealant compound in
appro~imately 1/32 inch thick coats. Allowfirst coat to cure approximately four hours
or until it becomes nibbery before application of the second coat. The second coat should
extend 1/4 of an inch past the previous coat.

b.

1. Generdl Req~rirements.

a. Filleting sealant (PR1422-B 1/2, B2 or CS3a04-lj 1/2, B2) must be tack free.

b. See Figure 7-5 for typicalfillet size.

c. Filletingsealants laid on intersecting joints shallbe joined together to produce a

continuous fillet.

d. All and hard to reach areas should be sealed first, to prevent the possibil-
ity of their being overlooked or incorrectly sealed.

REVISED JULY1980 7-5

 FIGURE 7-1 TANK SEALANT APPLICATION DIAGRAM

TYPICAL FILLETS FOR FUEL TANK REPAIRS

TYPICAL PR 1422 or CS 3204, Class B APPLICATION

2415 RTb~ J MAIN SPAR (REF)

i -r
I EXTEND
1 I 3/8" TO
TSA~2/1
SEAM
COAT
\i/ APX 1/32"

3/8 TO1/2"
FILL VOIDS, GAPS HOLES

FIRST STEP
SECOND STEP

BRUSH-COAT FILLER 3/16" TO 1/4"

TE~ICKNESS r

d 1/16" APX SEALANT

3/16" to 1/4" PR 1005-L THICKNESS
(Ij
FILLET SEAL ALL
SEAMS WITH
INSIDE TANK
CLASS B
APPLY PR 1005-L OVER ALL
SEALc~NT. EXTEND BEYOND
SEALANT 1-INCB.
THIRD STEP

FOURTH STEP

APPLY BRUSH COAT OF CLASS B TO ALL

FASTENERS- 1/32" TO 1/16" THICK.

7-6 REVISED JULY1980

 2. Application of Fillets.

a. Use a spatula or extrusion gun with 1/8 inch to 1/4 inch nozzle openings for ap-
plying filletinp compo;md on the edges of all seams.

b. If an extrusion gun is used, hold ~un perpendii~ular to seam when applying filletirSo
compound so that extruded sealant will be packed tightly.

c. Use a spatula to pack sealant firnilv in place; work out air pockets and properly
form each fillet.

c, Protective Coating Procedure (Brush).

i. Brush on a smooth, coat of PR 1005-L over sealant with a paint brush
short, strokes.
even The fihn should extend one inch beyond the sealant on td the ad-
jacent metal.

2. Allow the top coat to cure 20 minutes at 750F or until tack-free.

3. Apply second brush coat of PR 1005-L.

4. Every effort mustbe takento obtain a complete bubble-free, continuous top coat.´• Do
nottry to rebrush over areas during the drying period as this will only cause dragging
or will break the contin~ty of the coating.

d. Senli~P of Removable Panels.

I. General Req~ements,
a. Clean metal surfaces to be sealed with Turco 657 Wipe Solvent or M.E.X.
Do not allow solvent to dry on surface; wipe off to prevent redeposit of con-
taminants.

b. Cleaned surfaces need dry only 5~to 10 min~rtes before application of sealant.
Sealant should be applied as soon as possible after cleaning.

c. Parts should not be stored or handled in any manner which will allow fingerprints,
dust, dirt, and other foreign substances to contaminate the surfaces to be sealed
after the cleaning operation.

2. Sealin~g´•Procedure (for upper right wing-walk access panel).

a. Apply coat of access door sealant PR1422-B 1/2 or CS3204-B 1/2, B2 to
a
either surface using a short,stiff bristle brush, spatula or filleting gun.
faying
If the gun is used for application, the sealant must: be smoothed with a brush or
spatula.

b, Cover the entire faying surface with a sealant coat of sufficient thickness (1/32 to
1/’16 inch)
to assure extrusion along the edges of the faying surface when the mating
parts are assembled.

c. Assemble parts immediatelq- after application of sealant, tighten screws to obtain,

as near as possible, a metal-to-metal contact.

d. After fastener installation, remove the extruded sedia~rt from the wing surface.

REVISED JULY1980 7-7

 3. Sealing ~rocedure (for wing tank access panels other than wing-walk panels).

a. Apply a coat of 3R1403-G-~2 to either faying surface using a stiff, short bristle brush,
a spatula, or filleting gun. If a gun is used for application, the sealant, must be
smoothed with a brush or ssatula.

b. Cover the entire faying surface with a sealant coat of sufficient thickness (1/32 to
1/16 inch) to assure extrusion along the edges of the faying surface when the mating
parts are assembled.

c. Assemble parts immediately after application of sealant; tighten screws to obtain

as near as possible a metal-to-metal contact.

d. After fastener installation, remove the extruded sealant from the wing surface.

5. Description of Leaks.

It is important to make careful periodic fuel tank inspections. These inspections are
particularly important in co~fined areas of the airplane which are not exposed to air
stream in flight. Classification of fuel leaks, which occur in both confined areas and
open areas, is necessnrv to differentiate between those leaks which require repair be-
fore flight and those which do not constitute a flight hazard. The wetted area around
a leak is an indication of the intensity of the leak. All leaks should be mar~ed and the
location and intensity of the leak should be recorded.

a. Classification of Leaks as to Intensity and to Location.

1. Classification as to intensity (See Figure 7-2).

a. Stain is a slow fuel seepage which tends to dry as it is exposed to the air.

b. Seep: A seep is a fuel leak which reappears in a short period of time after
being wiped clean.
c. IIeavy seep: A fuel leak which appears immediately after being wiped clean.

d. Running leak: A leak which nows steadily.

2. Cbassficationasto Location.

a. Slow to seeps occurring in open areas, such as the surfaces of the

heavy
wing orwheel well which are exposed to the air stream in flight, are leaks
which do not constitute a flight hazard. Such leaks need not be repaired
before flight, provicling the condition causing the leak cannot result in a
leak: of greater intensity after a flight is in progress. Seeps considered
permissible for flight should be inspected frequently to see that an increase
in tensity has not occurred.

b. Leaks which constitute a flight hazard.

1. A leak and any leak in a confined area not exposed to the air
stream should be repaired before the next flight. (See Fi~ure 7-3.)

6. Leak Detection.

a. External LeakDetectionAfter Fueling.

1. To be able to trace the leak from where it appears on the o~rter boundary
to its true source inside the tank, the exact point where the fuel is escaping
from the tank must be determined. Locating this point will help determine
from which fitting or seam the leak originates.

2. By usi~ an air gun to blow and evaporate fuel from the seams and crevices
of the leak area, the exact point where the fuel is escaping from the tank
may be more clearly defined.

7-8 REVISED JULY 1980

FIGURE 7-2 FUEL LEAK CLASSIFICATION DIAGRAM

D1A

A STAIN

i l/t" DtA

B-SEEP 4’5"D1A

6" MAX
C HEAVY SEEP

D RUNNING STAIN

AREA WHERE FUEL APPEARS TO

FLOW OR RUN FOLLOWING CON-
TOUR OF SKIN WHEN THIS AREA
IS WIPED DRY.

FUEL WILL USUALLY BEGIN TO DRIP AFTER

REACHING THIS POINT.

7-9
 FTGURE 7-3 TANK AREAS WHERE FUEL LEAK

REMOVE ONLY TOP INSPECTION

PLATES TO PERFORM
PERMANENT TANK REPAIRS.

LEAKS 1N THESE AREAS SHOULD BE

REPAIRED BEFORE NEXT FLIGHT.

7-LO
 3. Small seep leaks can be traced with the raw edge of torn paper. The Fuzzy
edge of torn paper adsorbs fluid and gives a good visual indication of the
presence of any fuel when brought in contact with suspected leak points.

4. After the leak has beentraced to its exterior source and marked, drain
fuel from tanks.

b. Internal LeakDetection.

1. It is very important that the true source of the ir~terior leak be found in order
to make a permanent repair. The fuel tank is a network of seams, and fuel
may flow through or along a seam, or from one seamto another and may
channel a few inches or several feet to the point where it appears on the
external boundary of the tank.

2. Enter the tank thro~h the top inspection plates only (see Figure 7-3) and
illspect the sealant in the general area of the o~rtside leak point. Look first
for bare seams, rivets, and bolts in difficult-to-seal areas. Inspect sealant
for blisters, pin holes, cracks, splits, and loss of adhesion. Mark all
flaws with masking tape.

3. Test each flaw inside the tank with 20 to 30 PSIair Cfiltered) line pressure
by holding the air nozzle against the flaw and check the o~rtside leak point
closely for sjo~s of fuel.

4. After testing allflaws inthis manner, and if no leak source has been dis-
covered, apply bubble fluid to outside of tank and again apply air pressure
to flaws inside of tank.

5. See Figure 7-4 for suggested method of leak detection when a leak is sus-
pected around a rivet or when the above mei~hods have been unsuccessful.

7. Leak Repair Procedure.

a. Temporary Repair of Fastener Leaks.

1. Generally all leaks located in enclosed areas and runnino leaks in open
areas constitute a flight hazard. Fastener leaks in these categories ma~
be repaired temporarily by the application of a sealant fillet over the fas-
tener head on the fuel tank exterior.

2. In order for satisfactory temporary repair of a leak to be made at a fastener,

structural integrity must exist in the area of the leak.

3. Temporary repair procedure for fastener leaks.

a. Remove sufficient fuelto drop the fuel level below the leak.

b. Clean the head of the fastener and the adjacent surface with Turco 657
t~ipesolvent orequivale~t anddrythroughly. Fastenerheadand
adjacent met~ must be free)from paint, dirt, and oil.

c. Apply 1/8 inch thick coat of PR 1422-B 1/2, B2 or CS3204-B 1/2, B2 over
the head and around the fastener.

d. Cure the sealant untilfirm and rubbery.

e. Refillthe tombs and carefully examine the repair periodically. If leak

reoccurs, remove the sealant and either make a new temporary
repair or make a permanent repair.

REVISED JULY 1980 7-11

 b. Permanent LeakRepair.

1. If the leak source is determined to be around a rivet or threaded fastener, the

repair procedure shall be to restriki the rivet or retorque the fastener to the
maximum torque valve permitted. Any rivet can be resttck only once. If the
leak continues, the rivet must be replaced. Repair any sealant damage due to
the restriking or retorquing operation.

2. Remove sealant in immediate area of leak source using a sharp non-metalic

tool; a chisel-shaped formica tool is suggested. Bevel or slope end ends of
existing sealant so that the new sealant canform a continuous and smooth tie-in.

3. Thoroughly clean repair area using a metal cleaning solventto allowgood

adhesion. Wash one small area at a time. Then dry with a clean cloth before
the solvent evaporates to prevent redisposition of oil and dirt on the surface.
Always pour the solvent on the washing cloth to prevent contamination of the
solvent supply.

4. Cleaned area must be thoroughly dried by blowing filtered air over the im-
mediate area until there is no possibility of solvent or fuel entrapment under

adjacent sealant.

5. Apply sealant as required for repair (See Figure 7-1). Repaired fillets must
be blended into existing fillets and worked with a filleting tool as required.

6. Allow all repaired sealant to cure to, a tack-free condition, and apply two brush
coats of PR 1005-L to the repaired area.

7. Recheck for leaks by applyinp; a coating of Turco leak detector to the outside
of the sealed tank with the rank cap and vent closed as the tank is pressure
tested with 2 psi of filtered air for a minimum of 30 minutes. Do not exceed
2 psi pressure. Leaks uiill-be indicated by the presence of bubbles in the Turco
leak detector.

FIGURE 7-4 FUEL TANK LEAK DETECTION DIAGRAM

INTERIOR OF
TANK

C3

t-J

LEAK SOURCE

NOTE:

i. USE THIS METHOD WHEN rch V~ _

LEAK EXIT
LEAK IS AT RIVET OR SCREW.

2. PAINT THE SUSPECTED AREA

ON THE INSIDE OF THE TANK
WITH BUBBLE FLUID. REMOVE
ALL TRACES OF FUEL BEFORE
II AIR HOSE
APPLYING FLUID.

MAX PRESSURE
OF 10PSI
7-12
 SECTION

ELECTRICAL SYSTEM
 SECTION VIII
ELECTRICAL SYSTEM

A. GE~RAL

The M 20 series aircraft have a 12-volt electrical system. A 50-amp, heavy-duty generator provides
adequate current so that, even when high electrical loads are placed on the system by multiple radios,
a rotating beacon, and navigational lights, the heavy-duty 33- or 35´•´•amp battery will remain at full
Charge. The 1962 M20C is eedpped with a 33-amp battery.

The battery the M20C and D is located at the forward left-hand side of the firewalI. The circuit
on

breakers, designed to relieve the electrical system of any over-loads, are located on the lower ri~ht-

hand side of the co-pilot’s instrument panel. ThebatteryontheMzoE&F Is located aft of the baggage

compartment and is accessible through the radio access door.

The master switch for the electrical system is located at the top I~ft-hand side of the instrument

panel.

B. TROUBL~ SHOOTING

Malfunctions peculiar to the electrical system are listed in Table 6 along with their causes and sug-
pested remedies. When trouble shooting, check from the power supplyto the item affected. If no
trouble is found by this method, the trouble probably exists inside an individual piece of ec[uipment
which may then be removed from the airplane and an identical unit or units, tested and known to be
good. installed in its place.

I. ElectricalSwitches andCircuitBreakers.

Electrical switches and circuit breakers, located in the lower left and lower right instrument
panels, control the navigation and instrument lights, landing light, electric turn-and-bank indi-
cator, electric fuel pump, and other electrical components. The circuit breakers automatically
break the electrical circuit if an overload is applied to the system, thus preventing damage to
the electrical wiring. To reset the circuit breakers, simplypushinthebuttons. Allowsuf-
ficient time for cooling before resetting circuit breakers. When a circuit breaker has tripped
a second successive rime, the cause of the overload should be determined prior to attempting

to reset the circuit breaker.

2. Battery.

The battery should be maintained in a fully charged condition at all times, and the water level
should be checked at regular intervals; never add anything but distilled water. Do not overfill
as the electrolite will overflow and corrode the belly of the airplane. A hydrometer check should
be performed periodically to determine the percent of charge presentin the battery (Refer to
Table 5~. A fully charged battery will not freeze. All connections must be kept clean and tight.
If the battery is not uD to normal charge, recharge, starting with a rate of four amperes and fin-
ishing with two amperes. When cleaning the battery care must be exercised to avoid contamina-
tion of the electrolyte.

REVISED NOVEMBER 1966 8-1

 NOTE: Quick charges are not recommended.

3. Battery ChargingSystem.

The charging rate of the battery depends upon the condition of the battery and the voltage regu-
lator setting. With all loads off and the engine running at 2000 rpm or higher, the normal battery
charging rate will be 5 to 35 amperes.
if the charging current is considered excessive, check the following:
a. Charging rate should slowly drop to 10 amperes or less after 15 to 20 minutes of flight.
NOTE: A very low battery will take longer to show a drop in charging current.
b. Too high a voltage regulator setting will cause excessive heating and loss of water.

NOTE: Measure the voltage with a voltmeter at "Batt" terminal of the voltage regulator.
At 800 F., the voltage should be 13.8 to 14.8. This voltagewill behigher if the
temperature is less than 80" F, and loner if the temperature is higher than 80" F.

If charging rate is low, check the following:

a. The charging rate of a fully charged battery is normally from 1 to 4 amperes.

b. The regulator should not be considered defective because ofalowchargingrateuntil:

i. A voltmeter check indicates that the voltage at the’’Batt" terminal is below require-
ments given in NOTE above.
2. A hydrometer check of the battery indicates that the battery is not fully charged. Refer
to Table 5 for hydrometer reading vs. battery charge percent.

4. Voltage Regulator.

See Figure 8-1 for voltage and gap settings.

SHOP NOTES

8-2
TaBLE 5 HYDROMETER READING VS. BATTERY CHARGE PERCENT

Hydrometer Reading Percent of Qlarge

1280 I00

1250 ’15

1220 50

1190 25

1160 Very little useful capacity

1130 or below I)ischarged

Based on battery electrolyte temperature of 80" F.

If battery electrolyte temperature is below 80 F, subtract 4 points from the hydrometer reading for every
10" F below 805 F. If the battery acid temperature is above 80" F, add 4 points to the hydrometer reading
for every 10" f- above 80" F

Example: Hydrometerreading (1260)

Battery electrolyte temperature (300F)
Subtract 300 from 800 500 (5 x 4 20)
Correct reading (1260 20 1240)

SHOP NOTES

8-3
FIGURE 8-1 VOLTAGE REGULATOR SETTING CHART

CUTOUT
RELAY

VOLTAGE O:
REGULATOR

CURRREGULATOR

#1119224 DELCO REMY ~OLTAGE REGULATOR

GAP SETTINGS

CUTOUT RELAY VOLTAGE REGU‘LATOR CURRENT REGULATOR

AIR POENT CMSMG AIR AIR

GAP OPENING VOLTAGE GAP GAP

,020 .020 11.8-13.5 .075 .075

8-4
TABLE 6 ELECTRICAL SYSTEM TROU BLE SHOOTING

BATTERY

TROUBLE CAUSE REMEDY

Discharged battery. Battery worn out. Replace battery.

Char~n,o rate not set Reset (Refer Lycoming Manual).

right.
Remove load when generator is not
Dischar~ng rate too great. reduce use of starter,
charging and
II
etc.. on ground; use external power
whenever possible.

long. Remove and recharge battery.

II Standing too

Equipment left on
Remove and recharge battery.
II
accidentally.

a Impurities in electrolyte. Replace battery.

Short circuit (ground) in
II
Check wiring.
wiring.

II Broken cell partitions. Replace battery.

Battery life is short. Insufficient electrolyte. Maintain electrolyte level.

11 Heavy discharge. Remove loads when generator is not

charging.

II Sulfation due to disuse. Long slow charge for 60-100 hours at

1/2 regular charging rate.
II
Impurities in electrolyte. Replace battery.

II Low charging rate. Adjust voltage regulator.

Cracked cell jars. Hold-down bracket loose. Replace battery and tighten.

II
Frozen battery. Replace battery.

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

Too much water added to

Elecrrolyre runs out of Drain and keep at proper level and
banery and charging rare
adjust voltage re~lator.
vent plugs. too high.

Forr~ision inzide
Spillage from overfilling. Use care in adding water.

Vent lines leaking or

Repair or clean.
ii
clogged.

8-5
TABLE 6 (Continved)

TROUBLE CAUSE RE;MEDY

II Charging rate too high. Adjust voltage regulator.

Battery freezes. Discharged battery. Replace battery.

Water added and battery Always recharge battery for 1/2 hour
following addition of in freez-
II
not charged immediately. water
int weather.

Leaking battery case. Frozen. Replace battery.

Battery polarity reversed. Connected backwards on

Battery should be slowly discharged
airplane or charger. completely and then charged correct-
ly and tested.

Batteryconsumes excessive Charging ratetoohigfi. I Correct charging rate.

water tin all cells).

Battery consumes excessive Cracked jar. Replace battery.

water tone cell orily).

GENERATOR

Generator operating within If the voltage is low, gen- Check for loose or high-resistance con-
rated speed range but volt- erator is operating on resi-
,,ti,ns; clean and tighten.
age output low. dual magnetism.
Clean and tighten all electrical con-
Loose or high-resistance
II electrical connections. nections.

Brushes excessively worn. When brush wears down to 1/2 inch,

replace with new one.

II Caution: Do not use abrasives of any

description in seating brushes.

Brushes binding in the The brushes should be a free fit with-

brush box, out excessive side play in the brush

boxes. Bindingbrushes andbrushbox-

II es should be wiped clean with a cloth

moistened in Varsol or unleaded gas-

oline.

Excessive side play of Replace the brushes as outlined above.

II brushes in brush box.

Brushes not properly Reseat brushes as outlined above.

II seated.

Low brush spring tension. Brush spring should bear centrally on

top of the brushes, insuring full brush
II contact with the face of the commuta-

tors.

Clean the commutator with a cloth mois-

Dirty commutztor.
II tened in Varsol or unleaded gasoline.
TABLE 6 (Continved)

TROUBLE CAUSE REMEDY

Scored or pitted Turn down commutator or replace.

II commutator.

Shorted or open armature

11 cells, Replace renerator or armature,

Improper operation of
II Adjust regulator or replace.
voltage regulzcor.

Generator operating with-

properly See electrical system wiring diagram,
in rated speed range but
voltmeter indicates zero.

Unstable operation of the

voltaoe re~ilator. Same
Replace voltage regulator. Use remedy
Ceneracar operating with- under "Generator within rated
as "CeneraEor operating operating
in rated speed but speed range but
range, within rated speed range voltage output low,
voltage output is erratic.
but voltage output low",
above.

above.

Excessive sparking at Same as "Generator oper- Use remedy

under "Generator oper-
generator brushes. ating within rated speed within rated speed range but volt-
ating
range but voltage output age,,tput low".
low." above.

Generator oiDerating with- Generator field marm~t- Flash field with a jumper wire on
in rated speed range but
ized in the wrong direc- regulator’between generator and bat-
system ammeter or load-
tion. tery.
meter reads off scale.

System ammeter fluctuates Check the system for abnormal loads.

iS
ercessively when indicat-
ing full rated load.

lm_oroper operation of Readjust

II
to operate properly.
generator reverse-cur-
rent relay.

II Loose connections, Tighten connections.

Burned-out system Discharged battery. Replace with fully charged battery. Re-
ammeter or line fuse.
Defect~ive wiring. Replace all defective wiring.

STARTER

Motor fails to operate.

LOW battery charge. Check and recharge if necessary.

Defective or improper wir- Refer electrical

ii
to wiring diagram and
ing or loose connections. check all wiring.
Defective starter solenoid Replace faulty unit.
or control switch.

8-7
TABLE 6 (Continued)

TROUBLE CAUSE I RE~EDY

Binding, worn, or improp- Brushes should be a free fit in the

erly seated brush, or brush boxes without excessive sideplay.
brushes with excessive Binding brushes and brush boxes should
side play, be wiped clean with a gasoline-mois-
tened cloth. A new brush should be
run-in ~nril at least 50~ seated; how-
ever, if iscilities are not available for
running-in brushes, then the brush should
be properly seated by inserting a strip
of No. .0000 sandpaper between the
brush and commutator, with Sanded side
next to brush, Pun sandpaper in the
direction of rotation, being careful to
keen it in the same contour as the com-
mutator.
Caution: Do not use coarse sandpaper
or emery cloth. After seating, clean
thoroughly to remove all sand and
metal particles to prevent excessive
wear. Keep motorbearingfreefrom
sand or metal panicles.

Dirty commutator. If commutator is rough or dirty, smooth

and polish with ~0000 sandpaper. If too
II
rough and pitted, remove and Nm down.
Blow out all particles.

Shorted,grounded, or Remove and replace with an armature

II known be condition.
open armature. to in,aood

Grounded or open field Test and repair if possible or replace

circuit. with a new pan.

Low motor and cranking Worn, rough, or improp- Disassemble, clean, inspect, and re-
speed. erly lubricated motor or lubricate, replacing ball bearing if
starter gearing. worn.

Same electrical causes as

listed under "Motor fails Same remedies listed for those mal-
II
functions.
to operate".

Binding, worn, or improp-

Excessive arcing of motor -erly seated brush or See information above dealing with this
brushes. brushes with excessive malfunction.
side play.
Dirty, rough, pitted, or
Clean as outlined above.
II scored commutator.

Excessive wear and arcing Remove and turn down commutator

Rough or scored on

of motor brushes. commutator,

lathe.

II
Armature assembly not
Reface commutator.
concentric.

8-8
TABLE 6 (Conrinvedj
ELECTRIC GEAR

TROUBLE CAUSE REMEDY

Bulb burned out in red

Gear will retract but red indicator light. Broken Replace burned out bulb. Check indi-
indicator light (press-to- wire in cato’-light circuit and/or the down-
indicator-light
rest) ~cill not show. circuit. limit switch.
Up-limitswitch
inoperative.

Incomplete Retraction- Bind in gear retraction Refer to Section V for landing gear
Gear retracts to an inter- system because gear is rigging proceduredescription. Examine
mediate position and out of rig. Malfunction all movable retraction system pans
stops short, in gear electrical cir- for proper lubricaiion and freedomfrom
cult, inoperative actu- binding. Check for actuator worm gear
ating motor, or weak binding and lubricate as needed. Any
battery. malfunction can cause the 2S-amp land-
ing gear circuit breaker to trip. Check
gear electrical circuit for loose con-
nections, broken wires, or defective
relay switches. Recharge battery if
necessary.

Gear will not retract at

Insufficient airspeed, Check pitot tube and
line for obstruc-
or above 80 mph IAs
pressure switch inoper- tions. Examine pressure switch for
(M20C~. ative, or circuit breaker
Gear will not retract at or
proper adjustment and operation. Reset
tripped, circuit breaker.
above 70 mph IAS (M20E F~

Bulb burned out in green

Gear will extend but green burned out bulb. Check indi-
indicator
indicatorlight. Brokenwire Replace
light (press-to- i,indicator-light circuit. cator-light circuit and/or the down-
test) will not show.
Down-limit switch is inop-
limit switch.

erative.

Actuatmg motor extends Same causes as listed with

Same remedies as listed with "Incom-
gear to an intermediate "Incomplete Retraction"
a’oove. plete Retraction" above.
position andstops.

Actuating motor will not Same causes as listed with Same remedies as listed with "Incom-
initiate extension. "Incomplete Retraction" plete Retraction" above. Also, check
above. circuit breaker.

Gear will extend manually

but green indicator light Gear switch is not in down Place gear switch in down position.
(press-to-test) will not position. Bulbburnedout Replace burned out bulb.

show.
in green indicator light.

Manual cranking will not Drive-connector is out of Adjust control-cable tension at drive-
lower gear. rig. Sheared female spline I connector lever. Replacedrive-connec-
in drive-connector. tor assembly if female spline is stripped.

REVISED NOVEMBER 1966

8-9
 SHOP NOTES

8-10
 FIGIIRF 11-7 F1 ~r7Rlrdl ~YSTEM DIAGRAM (1962 M20C S/N 1910-2296:
CII1C(IIT
r-----^ Urlll~KtnS
_J -15
-´•11--(11
sc II r -I

I
SWITCI~
PAOBE GEAR WARNING PL~.(nLI VI.)IIJIC
a*
hz_ SWI~CII (~1(1 urttc~on)
a*rt VII(H~
INDICA1OR -I RADIO -16E --IG
c*nu *la trur.
sp_
-164 am (YT )10(t: (6

RADIO -174
I\ADIO Smal(ER
OPT AAMO

GENE)IATOR
SWITCI( VI~RHII O´•Pe.´• a INOICATO[)-IUns(
~16111) I IwlfCII )i)ltllOL1

L IllnolrLE

IlORN LICIITS
or*n v.laao ~e v
-19
O R

LIGI IT LIGIIT 11,

cr*n IQRIIII(O
IQ sr*n H*nlllao
79
-IW

A -111
SWITCI(
VOLTAGE P-o InOlCAtdl UOlll)
REGVLI\TOR r
~24. LAMP I.AMP
VACUUM SWITCII r(l( IIIIC(n~ ~0111*9
c ~u,o I´•aot
S)(UNT

~Z
1

87 ,o*
2L FUSE CIGAR LIGIITER

~s L_1 L1-.1 --I----´•---- I I L-----l t -I

-1....-

PnOBE ~a- rugql

-119 -:1--161)-´•-111
--110
MASTER GUAGE _BB
-169
hhC~IC-is7 SWITCH 3’
-i33111 n~

BVLB m
OILTI)(P .68 U-
-120
--117
-121

~ANDING
´•-138’ 1
LIGHT MAGKTO
44 Alc,n
SWITCH
IOltlOH (laR~
LIGI-(T ASSEMBLY
worrlp) ulaG, bALEH rvr~

MnoNiTo .p _I I-_LI 1-1 -152 -142-111 LQL 12L

)3 LEII
a
4~? 81 ’0"

64 TAIL CIGI1T ASSEMBLY

~h IssinRrER sus om
82 5*
62 --5-O~ol’’

g
VIBRATOR lo*

90

r
-12~7
Xt

TERY
se lo~
-Ino~lllu loruws oEloac-oPr

U
LIGHT ASSEMBLY
VIHG~RLD
C 40 65 PITOT ~e
ELtCrRIC OPIIOHIC
STARTER POWEII~ a ~VtL PU)b

SOLENOID RELAY

ALLjTEM I ISTI.
NUMBERS ARE UNDERLINED (REFER TO ELECTRICAL EQUIPMENT
 tlrru
ft~UKt: ~´•j II~LECTRICAL SYSTEM DIAGRAM (1963 M20C S/N 220U, 2256. 22Y/ 262L)

cmcu-r
_22
CONNEC~:nG
(llctlllc
ungAKE"5
m
II -(II
t; enOOE GSAFI WAI1NIFIG
swl rcle
mt-~ulL
SWITCII (Ilr1 Dltl~Jnn)
-I
UrE l110111(1*11 VIRH~
volc~nlon

-K;4LI.
"1
c*ns llla 1I)(P~’. ~lm MPIO
Ss
csaE ,core ,6)
1’12-´•----(11
04010
T
ss nADIO SMAKER
-jg =T~E OPT AADIO
GENER~TOR
SWITCI(
QR
c~*n wAnlllna-
i*
-143--~21-152 --Hsf)n~oo*L (a*la
LKJI1)J LWILII )I~1L)INI
L rllnortLE
II
HOAN 1.101175
oLln Wlnmlld -14 4 ----,t-- 40----~-- -49 -51
(i R t

LIGHT
ec*n v*nllllla
UZ LIGIIT
sl*n HlnlllllO
’----53-´•0:as
VOLTAGE SWITCI~
REGULATOR Bq m ~95. 11)01C110n
LAMP LAMP
TZ. VACUVM SWITCII TUIL ~ILCC1OA COIIFII~

SHUNT +-----´•-113-------1---1 1\\ ruto PILO1

-II1-----------~. c

z.
nDOTtLD LIHSB IIIDICATE
I~EMS USED 01( II1M2OCIJ
82 91711 SERUL 11111122112
I FUSE ~o*
CIGAR LIGIITER
22011,2229 AWll 1297
I I I I _
L----l-----l-------l TIIIIWGII 21211 O)(LY~
--I
Pnoea FU5E9i~ nLIlECTlYE BEIII*L WULI-
CIL. (ILID ILHR -119 -139--111 OEnS
-IOB V
--110 I-----------~--fl I /F"O ’I la~a,

I I IslusTEn GUMIE .na_

1 I -!09 SWITCII 2
-1331)1
u_

-11
-Ilo------l 1~------’ I 137---1)--1
CANDING-
LIGHT HAGNETO -124
-130 Y
1 I
-69 -71
~9. ap~r

-b~´• B
SWITCII

MAONETO
LcEt
-152
102
I(IHIIIDH

HOIC

-142--11~
(I1*1I1
IF)
B LPL
LIGIIT I\SSENOLY
wlllsl cPrca
O*UGL VI.1
reci 1*)1*´•116111
L?L

f~. I I I _i_l_ 811 IY-i~’O"

r, W ’~-91-----J TAIL LIGHT ASSEMRLY
3-’6~7 8~ 5~

~I´• ~R
nl SlnRltR
YIBR1IOR
59
Ina----O´•j~-(l’
--60´•-------------7~-
S

42 65
´•´•-~f-’l TER~
4s_
-141
nOmlNGDE*Cal-OP~

,-93--~1)-1_3’1
I

T
PITOT
OPIIOHLL
I

)55
B 100
LIGHT I\SSEMBLY
H1110I RCO

STAAIER
SOLENOID
WWER
RELAY
4
a4 ~j-jt731’2-lool lLlCrnlC
iVCL PUIIP

NOTE: 4LL ITEM NUMBERS ARE UNDERLINED (REFER TO ELECTRICAL EQUIPMENT LIST).
 FIGURE 8-4 ELECTRICAC SYSfEM DIAGRAM (1963 MZOD S/H 101-200)

CONNECTOA r------ll
(LLe~ale rLVC
Sil -149 ---~2-- 07----0--
-154 B

r
5WllCll
GEAR WARNING 92. rllT´•IrILL Wlnllllll
Pnoec: DL1IClOn)
SWlrCI~ (Llr I
Z1L
E rLlall~ (I~IWA1

"1 I"‘~". 1
c~nl rtn IIHP.
B9
-IGs IIIII (nrrl (IEB l(OTE Il) I
RADIO
T nADIO SPLAHEFI
@2 OPT IIAMO
-jg

GENERATOR

L
HORN
SWITC)I
~I u LICII1II~HIICII US[)IBL*
VJ6

LlO)lfS
dLlk ´•I-Is -51 NliT~ *L.lllllr(
WlnlBl(O 78

.1-~)9I
a R

LIGIIT
ct´•cl~ v~nllllco
la I.lGlIT
sr*n v~nlllllo
-U-0’---111
SWITCII
VOLTAGE GEAR RLTAACTMN SYSTEM 8~ I)IPICIIOI
LAMP
REGULATOR 72
~IXL LAMP
i vAcUUM SWITCI( rULL IL~CCIOR COI(P*II

11110 P1101
-111 SHUNT
’I
L
L~o-l D HO.~I IVITCH -I((
9 ,oA -I
V1RL( V1LO MI HtOO~l VIIH
)IUHtltn( 1 1110 101
oub IIIII
87 tl~nousll Ico OHLI.
91. FUSE clonn LICI~TER

69 -I
1Q
PROBE
crl.II(*D IL~P.
crusEg2
-119 -139-111
-100
--110
-159
1 IcumEn cvAae _86_
SWIIC)1
-131------ -133111
O~LVILLIIP h~i 1L

--II

--138
LI\NDING
LIGHT MAGNTO -124 -69
44 bIWlr -I_
SWITC)1

U40NETO
I LI ’-I ---1_1 102
IONI~IOH (IBR1
m)lEIP)
-142--(11 H LIGHT ASSEMBLY

19L
wlwc, cnrrH

1ZL
I*ll*´•abH1

81 ’0"

r
.-li5--
3e- =S-;l,-16 -I -64--------1)------ TAIL ~IGI1T ASSEMBLY

46
"5
OUI
BZ -6t
-´•-c~r
(SLE HOTCO)

r;
’01
vlonaron 50
-127 ROIUIWS DELLIW-OPI ~--1
XI
IOI
-141-~>--93--’>..94tlu LIGHT ASSEMBLY
ulnG,RED
~Y TERY M9 PITOT IOQ
42 65 OPIIONI~
ELCCIAIC
POWER 4 3) -le4-~,)--J’VEL PV"P
STAFCTER a~
1´•´•
SOLENOID
 ´•III~´•

CIRCIIIT
CONNEC!I)IG
IICtlRIC I I)(IF~nKERS _2_4
-I-171 -)5j

P Il-rPnoeE GEAR WAR~´•IING

9

SWITCI(
SWITC)I
22
INDlr,ATOA LV*nH~

-164r~ll
e~ns ~ln tt~tr.
-141
qe
(Icr ,lotrldj -152---(11
,,,r -39
OPT RAMO
RAGIG
I~hDIO SPEAKER

GENERATOA!k -145---"1)-- -170-111

I~
SWITC)I
3. 25 r*
"C::I8~o’ INDICATO~n-IUnl( (a~ln OO"E Iloll~, I WI1EII I~)tlll)L1
-52-~-----111
I~nnN
cLlkkiiiinso
~UL
-so-----tt--------3~/ll VJC

R Lii-~144 -40 ~---19

Ilr.llT
LIGH1’

VOLTAGE
tr*nWlnlilll~ae n
(I .__

-161
-53 -f~3.ti---111
REGULATOR 10"
.r SWITCI(
.7it gp
se at ~10111)
LAMP LAMP
VACVUM SWITCI(
-III C-;IUNT 1 ,111 -1]2 rVtLSLILCfO. tollnlr
ruto FILO1
L

LZ~-l.
n -1

,9L 97
69 CIGI\R LICI(TER
-1
Pnoee
CIL.1ILIO 1L)III
lg -1
ruse 9Z
-100 ~"9_1 1
--110
-ltis
SMWAISTTCE~ GUhOE Ue

-II
L~NDING- -1
LIGHT
14
MACNETO
"cHr
,I_I_I, -108 -124 38 Y I- (
-69
-150 SWITC~1

,F!
lBHlllON (~aRI
MAOMTO Holr19) LIGHT ASSEMBLY
HIHG) GRtEH
UrT G*UGF~!
NIL
IQL

cj I I I ´•Is
atru
~ol

-64´•----~-------- r,TAIL LIGHT ASSEHMY

SIAR’IER
VIBnl\TOn

[_.
_42 I
ncRl eH
SOLCNOID
1 65

POWER
RELAY
x,

´•´•-~i-’ TERY

4
~tl

108
loA.
-140-----f~I´•J(I
IOII1IWb BEICCXCOT~

199 PITOT
OPIIOH*I.
8 LIGHT ASSEMOLY
HlllO,nCO

NOTE: ALL ITEM NLJMB~RS ARE UNDERLINED (REFER TO ELECTRICAL EQUIPMENT

LIST).
 FIGURE 8-6 ELECTRICAL SYSTEM DIAGRAM (1961 M20C S/N 2657 thru 2741; 2743 thru 2806)
OIIICUIT
I!Ht~l\tnS
CONNECTDF(
clrctnle PLUL

ecD~ ----<t---171 lt4-

~jl´•nR waPNI~JG
9
SWITCL1
VIRIIIH(
SWITC~I (Ilrr ~EIIEIOR)
i’2 tDICnT(i~R
r.t"_:
CII)WHIIOH
INDICATOII
i11. I~rt

-147--
IllOlll((tllL V1IIII~
RADIO
-lo,

7
E*IB *1R Il)lh
r~
mool)rll ou) 3*3 (ntr) (StL kDIT)(I)
nAOlO

GENEnATOn1nl
1´•´•3r; VL)I!I I I~^:J
lIADIO SPEAHER
-J9-r
jB--´•--´•e s~ c
-´•e OPT I~AUO
I- -1SG
7

L
’JWITC)I
LCIA
..I -157-----~-----
INDICATOI~-tuna (a*llr
DOHI LIOlll( I IVlrRI I)ICHWY

LIGllfS
)IORN
cr*il v*RHao ~a -144----1)--- -´•18 -r P*IPL

li,la
C~*P 911nII(G
B
r; LIGI(T

i ~9,6-c;
1(1’ SWITCI(
VOLTAGE 90 IHDIEI1OR LICI(II
LAMP LAMP
REGULATOR r 1Z VACIIIM SWITC)1 rULL III(EI~OR COHPA~U
*uro ruol
5HllN~ C---´• ´•´•113--´• --.1--7 c

-le-´•2. 1l1
1~61-I´• 49

co~
?I F115E CIGAI~ LIGIITER

1P-
i L._,,,~ -206

-211
Pnoec:
CILIII*D I(HP. I 1--

"CO~’ -IOI--C
st
IJI
-IE9 NASTEA
swlrcll
~lrt´•-i -IUII( 11I CONNECTOR
ol~aHp .u. I 1!1 I- ~I ´•I
1’
-210
-121 -207 ~F,cuKnR
GAUGE
LA~IONG -213
LIGHT HbSINTO
-rjtf_
7/
B
uun

SWITCHloHl~loH

PIPL~1L
I~G
1 11~11
--IE´•l LIGHT ASSEMDLY
HOt(lO) V1HCI 6RI(H
UII
NIL
WnGNETO ggl
ss Irc´•r -142--111
19L
PI lo*

B_ -91
Y TAIL LIGHT ASSEMBLY
-64
45 a~

119
-Ipe vil~aUilR 10*
-140---------0~)11 -8~;-111
nor*rull OEILO~´•OPI T1
03

1 42- 1´• 1 65 TERV

se
10*
_94---f_l LIGHT ASSEMBLY
VU(G,RED
t; !49 PITOT
STAF(TER
SOLCNOIO
POh’EII
MLm
4
!s~ C3-3r- ~LLCIRIC
iuri UHP
OPrlOn*L
FIGURE 8-7 ELEC’I’RICAL SYSTEM DIAGRAM (1964 M20D S/N 202 tliru 251)

ITT~
--17 UAEAHLRS
CONNEC3~th
9

-154- 7-164
SWITCI1
GEAR WI\RNING rRr-,u~l
hZ SWITC)( (Ll~f DEILC1OR)
CI1)WRIIOR
)LTI ILIOII~(ITILL V*~H)
_,,,
RAP!Q\
-(gc?-~ll
eoooV_lI BW s*R (I~) worC 16~
jiP.Lbl9
ss RAMO SPEAKER
-jg ,--rt: OPT nnMO

LGENEII~TORHOnN YIAHIIIO
SWITCII
rltnornr
ZB

ZP r
---157---1>------
INDICATOnJUnH I s~a*
PM(L L1OII~I 1 LVIIR(

LIGHTS
r~ocL A(UHOLIO
)A
O R I

LIGHT LIG~(T
Iq. -Uo"--,
~1I
OLIR ~RWIIIO (ILUI W11\1(11(0
-167
’i)--´•´•´•r~-´•-
CEAR RETRACTION SYSTEM OPTldHAL OH M 20 D
60
SWITCH
eolc~rol LIGI)I:
I :tL ~9U. LAMP LAMP
VACUUM SWITC)I TULL 1ELLC~OR COIUYU

-I S~IUNT *uro PIIOT

~Z lo~ -IJ´•I
~tB

91 FusE 81
CIGAR LIGIITER
69 206
3e -206
PnouE F~)5E q2 -211

49 -16Y MASTER .1.

‘1
SWITCH
DULO GZ -133111 i. CONNECTOR
UIL rEHP 69 7L
-210-------~----
-207 CLUSTER
L´•u_LANDING--~ -206 GAUGE

75ft 94 1 -124

I-
HO~C 19) ;3\ LIGHT ASSEMBLY
MA(INETO VIHCI ORI~H
43 LLfr -142--111 LPL 93´•
l9L
109

t
Fi.~
81 lo*

-64-------~--------,, TAIL LIGHT ASSEHBLV

st at

S’IAIITER
VIBRs;lOR lo*
-la7

POTIIUt6 BC40H-M1

I----1)--
4e LIGHTASSEMBLY
_II r;s TEAY VWO,RCD
~9 PITOT
STARSEI\ POWER 6 OPOOH*L
MI.EN(~, RELAY 109 -MI I:::LC‘bH~CHp

NOTE: ALL ITEM NUMBERS ARE UNDERLINED (REFER TO ELECTRICAL EQUIPME

 FIGURE 8-8 ELECTnlCAL SYSTEM DIAGRAM (1964 M20E S/N 104 thru 230 rS/N 101 fkru 103 differs only in minor Jetails_J)
CIRCUIT
CONNECTOR
cll(lnle
UllrKERS
ysn
\---~;--fc-
PROOE
--171
I F~o GEl\fl WARNING
e
-149

2~
01-----~2--

SWI1C)I
Pnl´•I1~LL Vlnlll[((
SWITCII JI
~t (llT1 DC1[Cltl)ll
,*re v*nlc.)
INOIQTOR 1L

"1
~ln tlllP´•

-197
-IG4
eP ~I
(ui wolrlb
1 4,,
-192---111
-IOe
105 -14ti--------
-)-t hAt)lO
bo O
t-
O
T
-39 as RADIO Sl’EAHER
EOPT RADIO

.j:
(iENEnAfOn ee
sw(rol
-199 cr~k w*nlllllc- INDiCi~TOllausl (o~lla
Iwlrcll
~llnot ILL

I IcnnN
aa*iikiii8,to
0) I ’A
-144-----~--- -40-----~-- -49 -51
LIGl(fS
FIILL *5I[1(1111)

LIO~IT
oc*n v*nlllllo
Ig LIGHT
~L*n Hlnl(ll(O
´•jl~ L9
-167 dl
-U-O~kc,
VOLTAGE
80
5WITCI( IGO-111 Clllllt)
REGULATOR ~se ’L--’r"lD’F*’O" LAMP LAMP
I
VACUUM SWITCI~ rUCL ILLLCIDI COI(IXII

-III----------~ B(VNT ~-------115-------1-----´•1 1\\ c ~ulo PICO1

z
g 154

81
91 FUSE ~0*
CIGAR LIGHTER
1 I 1
-175
I 1P. I
-108
--110

b~( lr -181-4 -169 MASTER culiaE

SWITCI~
ouLe m -195 -133111
on ICI(P ha U-
-ILO
-lal I L---------’
-I
LANDING
CIOHT
80
MAGNETO
40 RIWIT -63

-6´•´•Irn
SWITCH

B
-150
laH(TIOH (llliR7
LIGHT ASSEMDLY
HOIC~P) WlaG, CAI(H
OUIMII blV6CMT
NI~

113
-152-------- -142--111 J9.? LZL
102
81 lo*

8´•´•
-204
202
-215 15

57nAIEn
aanarcn
Bi:

~e
-64-------~-------- gl--------I

60~-61--1)---62

-$;-11’ ~90
TAIL LIGHT ASSE~BY

v,

5 42

STARTER
-)93

POWER
-199
I8C;TTERY(
4
491

108
14
nomlllcw*uxc-or~

109
rVLL PUHP
m

PITOT
;2 I.IGHT ASKMBLY

~LOe
WII(O, REO

SOLENOID RELAI K1~

FIGURE 8-9 ELECTRICAL SYSTEM DIAGRAM (1964 M20E S/N 231 thru J99; 401 thru 469)
CIRCUIT
311.
cLlc~nle
0"4~KEs
ec~= SL
-9_
SWITCI1
PnOOF. FEI\R WAREIII(G WIIIIINI
tt)H IIHIIHI´• SWITC~I i
(L)lt BfllCloR)
ElnWmon
-148 IN~CATOR
INDICSITOR
C/I~ /I1CW)´•´•
JL
,~rr

-141
rCIO)I1()IlLL VIRH3
tVIDIO -189 /7tt-_:
Pe
(ic( IIO1EI(() -1921-1)1
nAolo
U]4i T
-29 a OPT nl\MO RAMO SPEAI(ER

cEIEnllTon ee
SWITCI~
s ZZ IND1CATO~1-run,e (s~,tn LDIII)IIWltell )111[1(8U
-199 L

~---149----1)----IO------1)--
(C3LIOI~TS
mlxL ~r,rHale
O P
L(GI1T
ELAR WlnlllllO
UZ 6ELnL~IO ILL
-(61
’1 I
VOLTAGE SWITCH
Bq ~9P 95 II(OIClmA LlOl(tl
LAMP LnMP
VACUUM SWITC)( IULI. CO)lr~ll
-Ill-----------C SHUNT *uro Pnol

91 FUS~E 87
L~D--h CIGAR
48
PROSE -205
ErL~ILIO 1U(F. F 9Z -211
-809

--110
I P,,;nS1T~-- I -i69
I
SMWn:TTCE~ -212---1

1
TCI(
OULO ht
48
-131 -1JJlll UL CONNECTOR
-ZL
-210
-207
-208
U\NOWO GAUGE
LIO)1T HAG~TO -21$
14WT
-108
-150 SWITCH
((URI

B
IOHIIIOH
LIGIIT ASSEMBLI’
HOICIPI
MAOKTO ul~o, cntrs
43- Irr~
-142--1(1 LQL

43 I I I _LL a~ln-ll´•´•

0~". ulon*ron
~U
BL
69-----~----- TAIL LIGHT ASYMBCY

:-~´•d
i
~z
nou~,ns scMFoPr

se.
-14 I----t>---SJ-´•t)-
42 LIGHT ASSEMBLY
65 ul,lc,nro
res PITOT
STARIER POWER ~e
S(XENO(D RELAY 4-XII rrrc~nle
rucL py~p
OPIIDH*L

"~IC´• "1 I ITEM NUMBERS ARE UNDERLINED (REFER TO ELECTRICAL EQUIPMENT LI

FIGURE 8-10 ELECTRICAL SYSTEM DIAGRAM (1965 M20C S/N 2742, 2807 thru 3184)
CIRCUIT .24
CONNECTOR
PLUG
IIRSAKEIIS
rlrcInle
---(t---Il 11-I--- P
-154 _9
5W17CH
GEAR W~RNINGZZ1 pllr ´•ra~ 1 w~ alllpr
PROBE SWITCH 1~1" UlI[ClUIll
2Z
c~rr r~lP,n(a*LL Mlnlc~
INDICATOR ~U -1 RADIO’ -218---1-~---4(6
c~np *IA IIHP.
99
(1\(1) (YL )101L )111
c~----219---111
YDUOII-II UU)LI*n
nAOlO
-r RADIO SPEAI(ER
99 OPT RADIO
-39

r
SWITC)I1. 98
23. INDICATbR-TuI\Il (u*lln
00)(r LW)ItIL 1 LWI1CII I((~)(BLY
22´•0~--111
L
LIG)1TS
IlORN rA
61~11 U*11111110 19 -223 223 -i?27 HIIL *(IIHOllr~

I t~LI III
LIGIIT LIGIIT
1l1 Iq´• 19

\t9´•86;
cr~n u*cwlao cE*n UUU(IHI

SWITCII
i II
VOLTAGE IIIOIC*IOR LIOIIlI
94 PB 93 LAMP LAMP
REGULATOR r), I ~ZL. VACUUM SWITCI( rUrL IrLccIol CDHP*II

Ulro PILOT
s)uNT c---´•-113----------(---1
L

82
9L FUSE ’o*
CIGAR LK;HTER

89 -206
1- -205
PROBE 2e -211
L_-LII~E_;?Z__-2""
.´•~.,ll´•oa*p.
loo-
-1
--1 I-
´•´•cD-
a
MASTER -212’
-181 SWITCH i
alllCoNNECroR
OILTTHP i IL
-uo LI--´•
-IZI 1LZtLUSTER
-208 GAUGE
L.ANI)IEIG 213
MaGKTO 1
se Illtl(l -69

qa
MAGNETO

43_
--151--------´•

81 lo*
SWITC)1Here
I6NI~ION

-142---111
IF)
LICIIT ASSEMBLY
YIHO) CALEH
Ya~´• L2L
PULL
MI

FlTAnTEn -Ila
I I I ss

uBRaTOR
at

’~L
-64-------~-----91--------1

140--0~-111
TAIL LIGHT ASSEMBLV

S
-127 98
X1 nol*rucb DEIMN-OPI

,~lmll LIGHT ASSEMBLY

IO* VWG,RED
42_ 1 1 65 ~L4 PITOT
OPIIO)(IL
STARTER POWER 4 ILTCIRIC
TUCL PU*P
501 tNOII) RELAY L~B
t-

,´•nsr I I hDE IlhlnFDI IhlFn ~RFFFR Tn FI Fr7Rlr~hl FOIIIPMFNT I I.ST\.

FIGURE 0-11 ELECTRICAL SYSTEM DIAGRAM (1365 M20D S/N 252 fhtu 253)

CIRCUIT

C~HJNEC3T?R,
IL(C1IIC
bl 9

1
SWITCI(

~8´•- GEAR W~nNING IRC.III

PROBE
SWITC11 INDICATOR
ure ILIUI~(IT*LL YUU(~

5´•INOICAlOn
I~
clla IIR 1IHI´•
sa
IQOP~II1 MI (~tr Here 141
IW]IO
99 RADIO SPEAKER
-29 OPT RAMO

(IENCI(ATORU--
SWITC)1 OOHr LIYI1( 1 LV~IO( I(ILU~LI
bC*ll V*RNIH~-
22 INDICATOR-IUw (I~HI 26
L
HORIJ Ilh
LIGHTS
or*n VI)IH110 ~ZB ’222 "222 --J>--- -2127 *IfL *IX)(BCYL

W(E05TAT
LIGIIT LIG)IT ~L
crARcunlll,olZL U*A WIUHO ~g 3t
I,
VOLTAGE GEAR RETRACTION SYSTEUL OPTIONAL OII M 20 D 20
10* SWITCI1
IHOICIIOR LIOIII)
12 ~9P 92 LAMP LAMP
VACUUM SWITC)( rU~L IFL(C~O)1 CO)(F*L(
L
-III S)(UNT )----113---1---7 1\\~ II)IOPILO(

3
nlTi~l L--134------1

Pt
9L FUSE co*

~cD PnooE -1Y.

-206

´•´•211
CIGAR L.IG)(TER

n,SE 92
CIIIIIEIO IIHP.
-N9

--110
-212

1
ct"
-IBI
BULB -Iulr CONNECTOR
71. :"’:.:I’L"’aq
-210
-207 T1Ul~clllslrR
-206 OAUBE
LAlrDING
LIG,1T MnCNIO -213v
;124
qe blW1T
-7.1
SWITCI1
I~unloH (Ibu~
HOrE 19)
LIGHT ASSEMBLY
MnONETO ulHC, ORE(H
_42 LLTI laL
~2L
IP~
BLI 1*1-1~20* 1
64---1)-- TAIL LIGHT ASSEHBLY
45 82.
-6i)-))--
START~R
vlenAToR
7

6
Xt

´•´•~I"´•
ROWIHb
I----1)---93---,t-
ss_ LIGHT ASSEMBLY
lo*
41 1
VIHG~ REO
PITOT ~ze
SIARSER POWER
RELAY
4
KPl
h10* pUHp
OPrlOH*L

NOTE: ALL ITEM NUMBERS ARE UNDERLINED (REFER TO ELECTRICAL EQUIPMENT LIST).
 thru 031)
FIGURE 8-12 ELECfRICAL SYSTEM DIAGRAM (1’)65 MZOE S/N 400, 470

--17
CIACUITUnEAKtRS
CO(~INECTOR
-149 --~t- 07--~--.
I\- -17
(LtCIAIC
PL61UE Q
SWITCH
mr´•,r*ll wlnl,llto
1/McEnn WARNING (LIT~ OEI(CTO~)
PROBE SWITC)I 22.

_Z(Ba,
rrw trll,lllo´• BZ .LL\
U. 1 RADIO
INDICATOR
C*RI IIA 1(HC´• QP
CI>--2~9----lll
(XL ItOtCI(I)
nAOlO
pnMo SPEAI(ER
T 99 OPT RADIO
-39

CENEII~TOI\
91J ne -170---((1uoNr Llbllll *II[(IOLI

-199 L
Miu. SWITC)( tr 23. (NDICAtOn-rulac(a~,lle
´•a
LIGI1TS
-228 ----3)-- -627 -220-1)- rr,aL ~lnHalrl

-L ~LB -229
PZZ
d

LIG)IT M
LIGIIT
wwl*o14. 19 98
cPl~ijSj/\T‘‘3q
PZ
3h_4~1 -O~ill
cr~n VIRIIII(I -~67
II
lo* SWITC)( I1IOIC*IOR LIG~I))
VOLTAGE PQ ~qp LAMP LAMP
1Z VACUUM SWITCI( TULL IIL~CIOR CO~PISI
REGULATOR
1UrO PICOI

-I 5HUNT’.

I I ---------I -I!
BZ I CIGAR LIGHTER
91 FUSE
-208
~i9 -205
-211
PROBE 1P. F 4i~
c´•c~. Ilr*o I~HH
-209

--110
-a12~---j

1
-169 MASTER
SWITCH
Ss_,_~tJ__I,I62 -IJI´•------ -Ijjlll ill CONNECTOR
OuLU 1L
MLIIHP 69 -1
’-210
-207
GAUGE
-208
I.ANOING
Il(illl H*GKTO -1114

93~I´• B
-25
1- 4" .ICHI
SWITCH

q3
MAGNETO
ur~
Icnnlon

Ho~rlY)

-142--111 F LIGHT ASSENBC’

IPL
ulnc, cnEEw
OUU´•I´•I

l2L
ML
UHII

43 91 ’O*

PTn(l En 64 -91----~--1 TAIL LIG~IT_ASYMBLY

I I 1 82
45STARTER A
LrS~
vun~ran
~e -140 II’

42 1 1 65
4
!P_A
IOA
I---1>-

1´•1---73--9)--18$~--1
AOIIIING ~E*tOH.OPI

UlL PUHP
U~
PITOT
OPIIO1(IL
6 L.GHT ASSEMBLY
HWGIRI’D

I I (TF~( )\IIIMRFRF hilt IINI?L:RI INED [REFER TO ELECTRICAL EQUIPMENT L15T)´•

FIGURE 8-13 ELECTRICAL SYSTEM DIAGRAM (1966 M20C S/N 3185 tliru 3466)
CIRCUIT
CONNECTOR ------173-------- URSAKLR’J
rtlCTRIC

P~C rc~l
-249--t)-- 01----)t-- ---F~t´•´•-li
i
89 .9
5W1TC)(
PIIOCIE GEAR WI\RNINO 29 pnr-rTllI WIR(III((
1EHR 1E1111)10-
~Z SWITCI(
2Z -240 INMCATOII (LlrT UElrLIOA)
c~nwnuon
r*rr rLserIlr*IL YIIIH.J lseE WOTE 331
INDICATOA U --197 -210----L9)---216
nAOIO
qp
ooaal-ll eu, Run ("E 1(01( 31)
119 -----111
RADIO
T RAMo SPEAKER
-39 99 OPT RAWO L-

GENEIIATOR
SWI’ICH
P&
d
-143----~--
INoICATOR-TuNl (eAsl
-170----111ooHr LIGIII) (IU(ltll IUEHOLY -230 -f;i~ ’’II
L v~
ImnN LIGHTS
pllii WH*IIO
~ZB --~----2111 -----1>---234 -21-----~Y NH(L AII(HYIO
O

LIG)IT
bTIR H*HIIIIIO
U1
R

LIGHT
L9
)ABWITCI1 -2

~-L,
’23"~

-2~ae
;ih

VOLTAGE co*
612´•Ir
)~Oc--L(II
I\EGULATOR 8e LAMP LAMP
.r ~ZZ. 31
IULL (ILICI(IR COHPIII
12L~
-202 S~IUNT
*uro IILDT
-230

LICI1TER-2)6t)- L1 11-237
z
54 128
d so*
48
W01211

acu~i" I 82 ,o*
CIGAR
INSII~UMENT PANEL I’OS1

Pnonr Ila. L1O"TS

FUS~92 I
CIL~IILID TEI(R -200---111

-C?
CLUST~R
-110
-19 MASTER
-IOI SW1T CII
BZ
-IIIFONNE
ou.u
OIL~T)IP ~P 1L
-210

300 -212
L,~NDING
LIGHT MAGNTO -123
_d, _,a
-j~ ~t RIGHT
tu
-188

SWITC11lo,~lnol( rr*RI C LIGHT ASSEMBLY

worra)’ -280 ulsc, cnrcH
MAONETO
-142--111 -I- I~L
LEIT
II -2TO 1ZL

81 ’0*
I~----------

4´•_
-200
Io

82
-64 ------1>---~ -91 TAIL LIGHT ASSYs.BLY I
JZL -sl--1>-- 02-,>- -28~ -28 r
124 -285 -274 122
STARTER
VIORATOR
~fL
DE*cac-oPr

-126 141 ----~---gj----t)-Rowwc LIGHT ASSEMBLY

HUIO, RED
42_ bS 189 PITOT Isre
li~3. OPIIOWIL
STARTER WWER 4
1~B
SOLENOLD RELAY

NOTE: ALL ITEM NUMBERS ARE UNDERLINED (REFER TO ELECTRICAL EQUIPMENT LIST).
 FIGURE 8-14 ELECTRICAL SYSTEM DIAGRAM (1966 M20D S/N 260 8,ON)
CIRCUIT
CONNECTIIURe
LL(C1AIC
Unrl(ER5
117 I

swl~ol
PROOE W PLI´•II*LL
In rrllw (rllll)lP´• Et 22, (Llrl UL~(LIOI))
C*ROUIIIIOII -211
m r*rr ~LIOIII(IULL u*n,c.) (6EE NOTE Sq)
13 INDICATOR
CIAOIIHrEHII RADIO’
2
o
99
PVI .II! CNI) (ILTHOILII)
-?ls ---le
RADIO
m
99 RADIO SPEAKER
x OPT RADIO ,1
t~
m
cerann
;0 ZS LLIIII( IV(IRI
(o~un I’

u,
L

_L I I I
-212,0-11’ CIGI(TS
~LB szs --1)-=-237 -----t)--- F*ICL AIILHOCIL)

-241 ’233
-109 VACUUM
´•o"--~e
VOLTAGE
._I zs

IoA
GWITC~I

Y
-221

REGULATOR .r
99 LAMP CAMP
12

;j’
SYJI rULLSLICCIOH COIIYIU
814 1211
-232-----1 -273-8
~ulo ruo~
-230 23 7 -230~
L
ao* 34
49

CIGAR LIG~ITER
LP 1 INSTIIUMENT PANEL POS1
-233 LIWITS
PROOEY (IS~
ICVL)IEIO rlllP.
FUSESZ
.211
?60--1111
CLC’iTER
-Ilo
GVAOEt
-169 MASTERI~I I II i,

-119--´•~37
SWITCH
m -lJJlll m~
OIL~IHP U-
-210

-121
~u -200 -212
Ll\NOING 1 -2~2 L -21"
LIGHT --123
MAGNETO

"@"P"a -a-´•´• B
slclll -lee
Iv swlrcll
IOWlrl(lH (Slld~
LIGHT ASSEMBLY
WIHC~ CREEH
MAONETO
qa LECT -142--111 19L
7-
Iz?r -270
PL

~264´•´•_
to .Ir
us
-64 ----t)-- -91
82 -209
*L
nas- -eea
--274 12il ~v
~55 STARTER ~d-- "3--- -~72

b. iT
VIBRATOR
IQ
ROT*TWG OE*COHOPI

8~- -126 ss_

141 LIGI1T ASSEMBLY
HIHG,RED
42 res PITOT
t: lOe
w STAI\TER WWER 4
ms
SOI.ENOID RELAY

FnlllPLIFFIT I IS’1I
FICORE 13-15 ELEC’TRICAL SYSTE~ DIAGIIIAM (196~ M20E S/~J 514, U32 Ilrru 13UU)

cmcul-r

-153
""5""""
9

1
’I~-- -199--- -190--- 107 ----1------ ~WITCII
GEAR WAIINING pnr´•,uLI HIHIII)(E
MB SWITCH
ZZ -24o INDICAOR (LIFI UEIEL(OR)
,Irr WIRLI~ 1665 NOTEENOTE

GENERATORII
-2l0--Lf)--216

ma3
-14 RADIO

BMIM2-II BUI sIR (NF) (1(1 )IOTC 3(

RADIO
T
99 RADIO SPEAKER
OPT RADIO L---- --1
´•las ==I[APP~1
SWITC)(
-143----1>-- -170--111
GCAA VIRlllltO.
ZS 2A
INDICATOR Junle (olvn
DO)(L LIG(II( I ~VIICH ~LIIHOLI
I´•
i. IIIROT~LE v~s
)-(ORN LIGHTS
crAn w~slallo 929 --3>--~-2151 ----1)---234 -231------lyr PlbLL *~ILHOLIEL
O ifR r- -241 "259

aLAMP
LIG)IT LIGI(T (*PP
GEAA ~IRWI1(0 ~r*n u*nlello
I~L 29 SWITCI1

VOLTAGE -112-1v
Bq -;M5´•b~
REGULATOR .r ~22.
-262 S)IUNT
mro ,Ilo~
ii.´• FUEL 1ELLC~OR
236
-237 -250 -------~r,
z
~Z to* -134 ´•2~0 ------´•71
48

glu~- I I CIGAR L.IGIITER 251

6P C_I 1 I t- I -eo6 PANEL I’O~’
re -211-------- LIGIITS
PROBE FUSE YZ
CIL´• IIL*D ~O(P.
´•-260--(11
-100 ’1 CLUSTER
-110
~la ouAo E
-169 MASTEA
SWITCI( U1
liZ -133111 ´•---CONNE

OIL Ir~P ha 3L 37
-210

-121
-200

LIGHT MAGNETO -125

AICHT -203 t
262

-d´•uvr
IH
SWIICH
-150

B
laalrlole (illRr
--151 LIG)1T ASSEMBLY
’I HINb) bAEEH
MAONETO ´•Rlb(tl
-260 IQL
rtrr
-152
a T ~ZL
.u
-270
I
81

0""’"
-266

129
-215
Io Il

BZ 5*
-\jq ------1)--- 91
~-269
-i TAIL LIGHT ASSE)c.OLY
12L
-61.--~-- 62-,)-- --~r ´•265
STARTER 11~---- -273~)-- -lii2~--274 -es
1140~
fi.
VIBRATOR Io*
.4 A
ROWIHG OE*CON´•OP~
-I´•,J --194 9s_ LIGHT ASSEMBLY
lo*
42 HIIG,RED
LPI PITOT
OPIOH*L
STARTER WWER 4
~na FUEL PUHPELEe’lkle
SOLENOID RELAY

NOTE: AI.L ITEM NUMBERS ARE UNDERLINED (REFER TO ELECTRICAL EQUIPMENT LIST).
 FIGURE 8-16 ELECTRICAL SYSTEM DIAGRAM (1967 M20C&E SiN 670001 8( ON)

m M2OE ONLY
203
105
ii;
m
b
,t.. an
GEAR WI\IININ~ 120 PIIESTI\LL WARNING
z POWER BOOST PoWCR BOOST
sWlrC,1 9 (LIFT DETECTOA)
0 WnRNINO LIGIIT WnnNINO SWITCI1 n an
-217
-175 -104 nnolo

1
´•2(13 7 216
m M2OC ONLY

i
0
L o
1-11---- ---171- 9g OPT
JL~PLe-_nAPlo -----111
it] PROBE G-I rucmlo 99 RADIO SPEAKER
TEMP SE)/SINO CY~UVnE70n PLUG

.Jj 3 t-----´•111
OENTIIATOI1 -as
T
-54
GEAR WIUININC
TIIROTTLE
-112
r3
TURN COORDINATOn
DOME LICI(T D SWITCII nSSEMDLY
F
-zso-ff,-o--EJII
I I I LIGHTS

INDICATOR
LIGHT 2 19 PANEL A98EMOLIC9
O 11 51\ a
WnRNINO -259
cnna nlR TEMP. LIGHT -233
IP 14 R)IEOSMT

-30--~---51
CEnn WAnNINo an
-29~ 95 SWITCH
-241 ´•235
L~
-250
-221
-Os;n~-lll
va~mer lo* 1 -~c‘00--)I
4811114$)- -243
(10 ul
AtcuL~ron

Z
F

-2az
r SI(UNt
3
14
LI\M[’
FueLsELEcron
-230
30
~itl
SHUNT LIG)ITS
13~ nllEosTnT
120
000011-1 F
ou~ n~n
FUSE Ill 07
CIGAR LICIITER
69
05 9.,,,
PROBE
CYL.)IEAD TEMP.
FUSE 92
209 -260 --111~1
CLUSTER ~J:
MASTER 4 GUAGE
66 -169
SWITCH (I! CONNECTOR COMPASS
6ULB
OIL TEMP.

a
LANDING
213 I
,L~nr HaoaEm
RIGHT
Iw
-203
SWITCH
102 -69 -71
LIGHT ASSEMBLY

:B
IGNITION 8 START
WING,OREEN INBOI\RD INBOnRD
151 (COHNECT Y1IIlOIWO IH .277 FUEL aUIHTITI FUEL OUIHTITY
Rer RECLPTIUI. INO 0110)
TAIHSLllrTERS TR~NS)IITTERI

43 MALGENF~TO -142 ----111 1 93

F
LEFT
~I
F
RIO(1T
I
~_ -$2

8- ~193
-215
121
STARTER
VIBRATOR
.00012-13
BVS B~R

IOA
11~-----261 56 LIGHT
IS 122

50LIGM
-204
LIGHT ASSEMBLY
TP~IL, WHITE
ASSEMBLY
49 -3)--93-))---94 55 WING,REO
42 SLOPE
MARKER BEACON PITOT HEAT
00 109
STARTER POWER ELECTRIC
SOLENOID RELAY iiji733~.’84 FUEL PUMP

NOTE: ALL ITEM NUMBERS ARE UNDERLINED (REFER TO ELECTRICAL EQUIPMENT LIST).
 SHOP NOTES

S-2d
 ELECTRICAL EQUIPMENT LIST (M20C, D a E)

NOTE: Item numbers refer to underlined numbers on ELECTRICAL SYSTEM DIAGRAMS

NO. ITEM QTY. RATING M~IUFACTURER MODEL/PARTNO.

I Generator 1 50A Delco Remy 1101915

2 Voltage Regulator 1 50A Delco Remy 1119224C
3 Circuit Breaker-Generator 1 50A Wood 2350
4 Battery 1 35A Auto-Lite R-35
5 Switch-Generator 1 55A AN3022-2
6 Switch-Master 1 55A AN3023-2
7 Starter 1 Delco Remy 1109689
8 Switch-ignition andStarter 1 Bendix 10-126690-1
9 Circuit Breaker-Gear Warning 1 5A Klixon PSM-5N
10 Light-GearWaming (Green) 1 .08A Dialco VM9118M-3A
11 Switch-Gear Warning
(Retr. Handle) 1 3A Micro BZ-7-RWT80
12 Switch-Gear Warning
(Throttle) 1 25A Micro BZ-7-RQIT
13 Horn-Gear Warning 1 .7A Edwards 319
14 Light-GeatWaming (Red) 1 .08A Dialco VM911-M-2A
15 CircaitBreaker-Fuel Pump 1 5A Klixon PSM-SN
16 Switch-FuelPump 1 40A Micro AN3021-2 (511TS1-2)
17 Pump-FuelEIectric 1 1.5A Bendix 476087
18 CircuitBreaker-Fuel Gauge 1 5A Klixon PSM-SN
19 Gauge-FuelQuantity 1 AC 5643860
20 Switch-FuelGauge 1 40A Micro AN3021-3 (511TS1-3)
21 Gauge Unit-Fuel Tank, Right 1 AC 5641991
22 Circuit Breaker-Stall
Warning 1 5A Klixon PSZllI-5N
23 Indicator-Safe Flight
(Stall Warning) 1 Safe Flight 164-R
24 Pre-StallWarning Switch-
Lift Detector 1 Safe Flight C-46001
25 CircuitBrealrer-Turn and Bank 1 2A Klixon PSM-ZN
26 Indicator-Turn andBank 1 4.2W Schwein NS27200-A1
27 CircuitBreaker-Nav, Lights 1 10A Klixon PSM-1ON
28 Switch-Navigation Lights I 40A Micro AN3021-2 (511TS1-2)
29 Lights Assembly-Wing 2 1.6A Grimes A1285
30 Light Assembly-Tail 1 1.15A Grimes A2064-12
31 CircuitBreaker-Landing Light 1 35A Klixon PSM-35N
32 Switch-Landing Light 1 55A AN3021-2
33 Light-Landing 1 100W #4537
34 CircuitBreaker-Paner Lights 1 5A Klixon PSM-5N
35 Rheostat(25r)-Panel Lights 1 Clarostat #25-25
36 Light-Panel Assemblies 2 .63A Grimes A1425-R
37 LampCompass 1 .08A 330
38 Lamp-FuelSelector 1 .08A Dialco 83B1310-117
39 CircuitBreaker-Dome Lights I IOA Klixon PSM-ION
40 Lights and Switch Assembly
Dome 1 1.15A Grimes B3j55-A-93
41 Ammeter 1 0.60A AC 1502373
42 Solenoid-Starter 1 Delco Remy 001464
43 Magneto-Left 1 Bendix S4LN200
44 Magneto-Right 1 Bendix S4LN7,04

8-27
REVISED NOVEMBER’1966
 NO. ITEM QTY. RATING MANUFACTURER MODEL/PARTNO.

45 Vibrator-Starting 1 3A Bendix 10-87998-1

46 Switch-Starter Solenoid
Cutout 1 40A Micro AN3021-2 (511TS1-2)
47 Voltmeter-Turn and Bank I Weston Elec. 840 (or Equiv.)
Inst. Corp.
48 CigarLighter 1 8A Balcamp n"4-2272
49 Heated PitotCircuitBreaker 1 10A Klixon 0-7270-5-10
50 Rotating Beacon Circuit
Breaker I 10A Klixon D-7270-5-10
51 ADF Radio Circuit Breaker
(For ADF-29) 1 2A Klixon PSM-ZN
52 ADF Radio CircuitBreaker
(For ADF T-12) 1 5A Klixon PSM-SN
53 Fnse andFuseRetainer 1 IOA Little Fuse lo AMP 311014
and 155020A
54 LoudSpeaker 1 Oxford 46 AMS
55 Pitot-Optional 1 8A Aero Instrument P.H. 502-12
56 Rotating Beacon-Optional 1 6.62A Grimes G-8400-8-12 or
0-7080-1-12
57 Radio-Optional
58 ADF Radio-Optional
59 Receptical-Extemal Power 1 AN2552-3A
60 Solenoid 1 Delco Remy 001464
61 Connector-Electric Plug 1 AN3106-14S-1S
62 Indicator-Carbu~etorAir Temp. 1 1.5 AMP Richter C-12
63 Probe-Temperature Sensing I Richter B-5
64 Adaptor-Electrical
Accessory to Cable 1 AN3057-6
65 PowerRelay 1 100A Cntler-Hammer 6041H34B
66 Bulb-OilTemperature I. AN5525-1
67 Plug-Connector 1 AN3106A-125-3S
68 Clamp-Cable 1 AN3057-4
69 Probe-CylinderHead Temp. 1 AN5546-1
70 Adaptor 1 AN4076-1
71 Switch-Master 1 AN3027-2
72 Shunt 1 60A Weston Elect. 105918
73 Speaker-Radio 2 Jensen P4-W
74 Light-Landing 1 250W G.E. or Equiv. 4522
75 Circuit Breaker-Radio 2 10A Klixon PSM-1ON
76 Circuit Breaker-Radio 1 2A Klixon PSM-2N
(Por ADF-T29)
77 Circuit Breaker-Radio 1 5A Klixon PSM-SN
(For ADF-TL2)
78 Circuit Breaker-Instrument
and Domt: Light 1 5A Klixon PS(M-SN
79 Circuit Breaker-Instrument 1 5A Klixon PSM-SN
80 Circuit Breaker-Ignition 1 10A Klixon PSM-ION
81 Circuit Breaker-LandingLight I 20A KIixon D7270-5-20
82 Circuit Breaker-Navigation
Light 1 5A Klixon 07270-5-5
83 Circuit Breaker-Rotating
Beacon 1 10A Klixon 07270-5-10

8-28
 NO. ITEM Qm. RATING MANUFACTURER MODEL/PART i~iO.

84 CircuitBreaker-Fuel Pump 1 SA Klixon D7270-5-5

85 Indicator Lights-High and
Low Vacuum I .08A Garvin 23-602
86 ClusterGage 1 0.1A Garwin 22-166-01
87 CircuitBreaker-Buss Bar 1 50A Wood 2350
88 Switch-Landing Gear
Warning-Throttle 1 10A Micro V3-1 (AN3234-1)
89 Indicator-Turn andBank 1 .3A Garwin 23-323-01
90 Switch-Press to Test
High and Low Vacuum 1 SwitchCraft 974-TF
91 Fuse andFuseRetainer 1 10A Littlefuse 10 AMP 311010
and 155020
92 Fuse andFuseRetainer 1 10A Littlefuse 10 AiMP 311010
and 155020
93 Fuel Quantity Transmitte~-
Left I AC 5642354
94 Connector-Electric Plug 1 MS 3108B 10
SL-3S
95 Vacuum Switch
(High and Low Vacuum) 1 Garwin 22-1280-04
96 Indicator-Carburetor Air Temp. 1 Garwin 22-995-04
97 Connector-Electric Plug I AIu’3106B-14S-7,S
98 Circuit Breaker 1 (See Notes 31 and 32)
99 Circuit Breaker As (See Note 32)
needed
100 LightAssembly-~Ving, Red 1 1.6A Grimes A1285-EI-12
101 LightAssembly-Wing, Green 1 1.6A Grimes A128j-G-12
102 Switch-Ignition and Starter 1 Bendix 10-126680-2
103 Speaker-Radio 1 Dare 721120 (V5F43)
10~ ClusterGauge 1 0.1A Garwin 22-166-04-A
105 SwitchAlt. Air\arming
(Ait. Air Control) 1 25A Micro V3-1 (AN3731-1)
106 Indicator Lamp 1 .08A Dialco 39-14-371
7538-XP13
7538-XP51
107 Electric FuelPump 1 5A Dukes Ast. Co. 4140-00-19
108 CircuitBreaker-Fuel Pump 1 10A Klixon D7270-5-10
109 Electric Fuel Pump I 5A Dukes Ast. Co. 4140-00-21
110 Cluster Gauge 1 0.1A Garwin 22-166-05-A
111 Connector-Cluster Gauge 1 AN3106B-18-85
AN3057-10
11’ ClusterGauge 1 O.IA Garwin 27,-166-010
113 ClusterGauge 1 0.1A Garvin 22-166-09
11~ Speaker 1 Tramm SP-1
115 Rheostat Panel Lihts 1 3,.O~A Ohmite 919006-1
116 Lights-Panel Asseirlblies 2 .63A Grimes A-1435A-1-12
117 Li_ehtBr SwitchAss?-Dome 1 .58A Grimes B-3555A-89
118 ClusterGage 1 0.1A Garwin 660100
27-169-07
119 ClustrrGa_ge 1 0.1A Garwin 660099
22-169-08
170 Rheostat Post Lights 1 1.19.~ Ohmi tz 919006-501
1’1 StarterVibrator 1 2.75A Gar\t´•in 31-324
122 Light Assv-Tail 1 l.f2A Grimes A-3064-1’777
173 Power Relav 1 100.4 Cutler-Hammer 604111231
124 TerminalStrip 1 Kulka 599-7_003-6
125 Turn Coordinator 1 Brittain Ind. TC100-12
1’6 Turn Coordinator 1 Brittain Ind. 2900TC100-11,
137 Shunt 1 Garwin 7,2-370-60
138 Horn-DualWarning 1 Safe-Flight 283
139 Switch-Ignition gi Starter 1 Bendix 10-357201-1

REVISE~ NOVEMBER 1966 5-29

 I. All splices are A~IP knife or equi~alerlr.
2. I\llcircuitbrlskers areof dtrlp-freetype
3, r\ll terminals are A5~59 (or equivaient\, or wire e~id´• ar~ 4uldc-c~1
4. All unshielded cable is to conform to.rpzc (~i´•I ~otr
5. All terminals will be of a prein;nlated type or will :,e inplllar~d tllhl~Lm
q325134 may be used on ~ci tennin~lJ; amp´•uiatior? r3W11- Illav be ~,cd r´•rr ~=et-nlir:Jlr
i;. Deleted
teads without dash nlllTlbrTS are iu´•rn~hej with ths co;.celilcd.
8. Plastic resin-core rolder is used.
9. Deleted
10, "F" symbol indicates groundilig through iralnz Ino wires,,
r-
Yymbol jigmii~ a kllifedirc´•oFliec~
12, Connect optional equipment wires to oower ~o.lrce ~IIIY ~ilZ:lot?ti3lidl is tll~tallid II;
sulate terminals rzirh Sco~ch t53 tape wi~err terlniujls 3rz r.L´•~ canr:~c´•iP-d
13, Install items 49 or 90 jcircuit breakers’) only whal hcrt:ed pl:n; or rotiltillg br?df~ll Ir inji;t[li(j
14,. 15,. 16,. 17.. 18, Deleted

19, Wires, knife disconnects. gage, probe. and gage coane~tors a´•~ In tiicczi
Probe Kit,
21,, 22,. 23, Deleted

24, All,j18 ~ielded electrical cable is to conform to ´•pecification S1!1,-<:-~O’x I ype

25., 2(i,. 2;. DEler~d

2x. Ppare parts replacement for -58 wire should also irtclude -15: ~ire´• 15 I;i)l-i~SI s
29. IDare parts replacement for -IS wire should al.;o incl~lde -1;-i wire. 1;01-1431 y 1Y53-I~:(9i.
30, An external power supply plug installation is available as cp´•ior;al eqliplrlenc.
31, This circuit breaker is for one Sav:Coln uilit only. Do not add other eailp~nc´•nr to this clrcua
32, Deleted
33, Install ANP 32446 knife disconnect to shielding on each end of -189 or -218 wire froln 1.00" to 1.SO’’
from terminal ends of inner wire,
34. Shielding from wires -19. -20. and -21 is connected together in receptical ASii59-5 and connected
to ground terminal of item 8 (ma~eto switch),
35. Shielding from wires -150. -151. and -152 it connected together in receptical AS(i59-5 and is con-
nected to ground terminal of item 8 or item 102 (ma~eto switchesl.
36, Xutolite R-35 battery is interchangeable with R-33 and may be used as spare parts replacement on

prior M20B and hiZOC models,

37, The high and low warning lights. with their wiring and twitches. are optional equipment on
vacuum
the h´•f20D. and are to be installed
only in conjunction with the vacuum system installation,
38, Install X~IP 32121, ampsulation (0.5" lon~ and A~IP 327216 ampsulation on soldered colnections
at gear warning lights, and cover with AXfP 32;219 ampsularion(O.r5"
lon~-effecdvz ~1’20C S
2657 Sr 0?5); h´•i20E 131 5: t3S). Also iiLc:all.L\.\IP 327217 ampsnlation i0.5" arld
327216 ampsulation on oldered connections at the vacuum rr;trIlirlg ~ILOC i,; S 3155
and ErI20E (S~S 833, Sr OSi.
39 The compass light shall be connected tothepo-~;-lidnr. when optional post I~htd are installed,
I~he -230 wire, when not attached to thepost lights. will be insulated at the knife disconnect with A~II-’
32’7217 ampsulation and also string tied with Airter !CZass 2,
string,
40. The following pairs of wires will be twisted together counter-clockwise with a minimum of three i3)
wraps per foot, (Effective M70C S~ 3287 OS, hi?OD,C;S 260 ~L OS~ hi20E S~ 951 Sr OS\:

Wires -267 Sr -91 Wires -2Ci-!&-5

-7ci2 Sr -92 -263 -90
-268 Sr -6´•1 -269 -39
-2:0 Sr -tjO -274 Sr -94
-266 Sr -81 -272 -93
-1?65 Sr -82 -273 Sr -1:1
-261~ -1´•10

41, Use 919012 overhead light as replacement part on M20B E ’S 1701-1851: 1853-1939. h121X: ~35L
1940 Sr O~: hi20D S,’S 1. 101 Sr )h’; Xf20E 5 i~ 101& OS. Use 919012-501 overhead Zi~ht on ~1200
S/N 1701-1851, 1853-1939; ~IZOC S/h’ 1852. 1940-3184: XIPOD S/~ 1. 101-2591 ~170E 8 ´•S IOI-YRI.
Use 919012 overhead light on M20C S~ 3185 Sr OS. 113-OD S 260 Sr O~. alld S120E 5 IS 832 c)S.

8-30
REVISED NOVEMBER 1966
 Item So. 125 may be used to replace Item No. 89 without changing wires or connector. (Effective
~120C S:S 3135 g: O~i; ?cI20D S;S 260 a; OZc~; ~20E S~i 832 a; oN.

´•13. The polarity of wires 800007-180 and -181 is not eritical.

;1. On Zvi20C, 1~ 670001 OS. and Af20E. 670001 ON’, wire 800007-143 connects to positive lead
from Brittain turn coordinator ltem No. 126.

45. Garwin shunt parr no. 22-370-60 replaces shunt pan no. 105913, effective M20C. S~J 670001 8i 05,
and hI20E, S~ 610001 ON.

REVISED NOVEMBER r966 8-31

 FIGURE 8-17 ELECTRICAL SYSTEM DIAGRAM (1967 M20F S/N 660003 6’/0001 ON)

2
111---122 SWITCI1
4-0vp! GEAR WARNING PRESTIILL WARNING
POWER ROOST POWER ROOST SWITCII ILIFT DETECTOR)
54
WARNING LIO)(T wARNINO 9WITCll ~T??
II

a.
´•123 ~Mple,

t L~ 1
-079 1022
..nAPlo
60 -o(B
d,,,, _.
--111
´•I dbP~e, RADIO SPEAKER

GENERATOR

-117
-124
T T
_
SWITEII
GEAR WI\RNINO a
24 TURN COORDINATOR
DONE LIGI(T D ASSEMOLY
V 35
TIIROTTLE
------~--´•-054 STHGIL"
´•lor I 1 2
-12C,D LIOIIT
WnnNII~O
LI611T
~U
an o
-oso
PANEL ASSEMOLIES

3 re cEnn WAnNINC
19. (14 -043
SWITC)I
-043
I(~IEOSTAT

.055"9 -~-aol-tt F
III

VOLTI\~E
REGULATOR r af
IOA
´•01(4

HI
´•i4--´•ll~
LI\MI’
1~ FUEL SELECTOR
S)(UNt SIIUNT LIGL(TS
2
1 r
IIIIEOSTAT
42
D ZR eP ZP ~.osi
--OUIOln10 Ce4
osolll´•o wlnr(nrr~2 26 FUSE SL CIGAR LIOIITER ´•062
1l

PF(OOE
CYL.)ICdU rEMI1
1? -1 I FUSE 29
-132
-020
-040
-041
~-063
---111
-192 CLUSTER

´•011 I 10 ounoc:
SWITCII COMPASS
4,BCONNECTOR
ullll,~ a LIOI1T
OILTEMP
I I I I 1-131
g7

ILnNolNo
LIG~(T
1~
I
MAONETO
AI[I~IT
IW
-100
SWITC~I
I
-036 -038
LIGHT ASSEMDLY
IGNITION B START
WINO,OREEN IN0OnnD INOO~R3
(CONHFCr IIIIELDIH~ IH
RLELPTIWL*HDWIO) .IJ6 31 TULL OUll(flr´•l
MAONETO

.a
IR*hlSUlll~ltS
;0
4_3 LEFT
--II’ Lrrr AIGI(I
m 33 -140
67 A
~-:o7jfF-lll

´•0-´•-lc~´•xIx
11---088 -087
V
B 92 OUTBOIUIO 9’
-084
1
C~ La 5n llt----096 -095 --~-cirJ4
-009 F
2 OUS OAR 75
~--09- ,--;139
O STARTER 11’ -050 ANTI-COLLISION
LIGIII 32
VIDRATOR n

3
-003
m
LIGHT I\SSEMBLY
111----111---1)_-110 TAIL, IV)IITE
LICI1T ASSEI~BLY
m 65
WINO,RED
a g ´•-CLIOL ELOPE
MARKER DEACON PITOT )1EAT 90
42 .B ~4
´•o STARTER POWER ELECTRIC
o~ 9 69 3~-113
OI
SOLENOID I(ELI\Y FUELPUMP
1OA

NOTE: ALL ITEM NUMBERS ARE UNDERLINED (REFER TO ELECTRICAL EQUIPMENT LIST~.
 ELECTRICAL EQUIPMENT LIST
(M20F)

KOTE. Item numbers refer to underlined numbers on ~120F ELECTRICAL SYSTEM DIAGRAMS

ITEhl QTY. RATING iLIANUFACTURER MODEL/PART NO.

1 Generator 1 12V Deico Remy 1101915

50A
2 Regulator-Voltage 1 Delco Remy 1119724C
3 Vibrator-Starter 1 2.75A Garwin 31-324
12V
4 Battery- 1 35AHR Rebat R-35
5 RelaJ’-Powlr 1 12V Cutler-Hammer 6041H231
0.67A
6 Gage-Cluster 1 0.1A Garwin 23-169-07-1
hrlooney P/N 660114
7 Starter 1 12V Prestolite M24206
8 Probe-OilTemp. 1 AN5525-1
9 PlilS-OilTemp.Probe 1 MS3106A-125-35
10 (GzarDown) 1 12V D.ialco VM911~1-3A
0.08A
11 Switch-Gear Warning Handle 1 Mirco BZ-7R\YTBO
13 Clamp-Cable(Oil Temp. Plug) 1 MS-3057-4B
13 Plobr-Cly. Bad Temp. 1 AN-5546-1
1~ Light-Warning (Gzarup) 1 1’V Dialco VM911M-2A
0.08A
15 Light-Warning (HighVacuum) 1 12V I)ialco VM911M-2A
0,08A
16 Light-Warning (LowVacuum) 1 12V Dialco VM911M-2A
0.08A
17 Adapter-CylinderHzad Temp. 1 AN4076-1
Probe
1S Switch-~laster 1 Mirco 512TS1-2
MS35059-22
19 Shunt 1 Garwin 22-370-60
20 Trans.-Fuei Qty. (L TanL Inbd.)l A-C
21 Trans.-Fuel Oty.(RTankInbd.)l A-C
22 Switch-Gear Warning V3-1
Throttle switch with actuator 1 Mirco JV-5
23 Turn Coordinator 1 12V Brittain 820166
0.75A
2~ Suritch-Warnin_p pre stall I Safe Flight C-46001
Mooney P/N 800218
35 Fuse gr Fuse Retainer 1 Littlefuse 311010
155020
26 Fuse&Fuse Retainer 1 Littlefuse 311010
155020
37 Light-Landing 1 250\Y GE or Equiv. 4522
12V
25 Relay-Over Voltage 1 RBM 136-8
Mooney P/N 800165
19 Vacuum) 1 Garwin 22-1280-04
30 Light-Position !Red) 1 1.6A Grime s A1285-R-12
12\’ Mooney P~I 800223-Basic
31 Light-Position (Green) 1 1.6A Grimes A1385-G-12
l’-V Mooney P/N 800223-501

REVISED NOVEMBER 1966 8-33

NO. ITEM OTY´• RATING SIANUFACTURER MODEL/PART NO

32 Light-Position-tail 1 1.6A Grimes A1064-1777

12V Mooney P/N .500274
33 Switch-Ignition andStarter 1 Bendis 10-357210-1
34 Switch-Warning 1 Mirco 53-1
(Alt. Air Control) JV-5
35 Light-Panel(left) 1 0.63A Grimes A1425A-1-12
12V ~ooney P/N 919012-Basic
36 Light-Panel(Right) 1 0.63A Grimes A1125A-1-2
12V ~looney P/N 919012-Basic
37 Compass 1 0.08A Airpath C-2350-DL-4VF
38 Light-FuelSelector 1 0.08A Dialco 203-1310-01117-201
12V
39 Speaker 1 Tramm SP-1
40 Light--Warning 1 0.08A Dialco 39-14-373
(Alt. Air Control) 12V
41 Pump-Electric Fuel 1 5.GA Dukes 4140-00-19A
12V
42 Solenoid-Starter 1 3~0A Delco Remy 001466
12V
43 Magneto-Left 1 Bendix S4LN200
44 Magneto-Right 1 Bendix S4LN204
45 Plug-Cluster Gage 1 SIS3106A-18-85
46 Rheostat-Panel Lights 1 Ohmite H-8-F2-352A
Mooney P/N 919006-1
47 Rheostat-Post Lights 1 Ohmite H-8-F2-352A
Mooney PIN 919006-501
48 Lighter--Ciger 1 8.GA Balcamp 4-2272
12V
49 Light-Dome 1 ~58A Grimes B-3555A-89
12V
50 Circuit Breaker-Generator 1 50A Wood 109-250-101
51 CircuitBreaker-Buss Bar 1 50A Wood 109-250-101
52 CircuitBreaker-Pre Stall 1 5A Klixon PSIM-SN
Warning Mooney P/N 919000-9
53 CiIcuitBreaker-Inst, &Dome 1 5A Klixon PS~M-SN
Lights ~viooney PfN 919000-9
54 Circuit Breaker-Cluster Gage 1 5A Klixon PS1M-M
Vacuum Warning Mooney P/N 919000-9
55 Circuit Breaker-GearWarning 1 5A Klixon PSM-jN
Mooney PIN 919000-9
56 CircuitBreaker-Torn Coord. 1 2A Klixon PS~M-2N
hiooney PIN 919000-5
57 Circuit Breaker-Ignition I 10A Klixon PSXS1ON
Cigarette Lighter Mooney P~N 919000-13
58 Circuit Breaker-Audio Cent. 1 2A Klixon PShl-2N
h.looney P/N 919000-5
59 Circuit Breaker-Radio 1 Klixon
h~ooney P/N
60 Circuit Breaker-Radio 1 Klixon
Mooney P/N
61 Circuit Breaker-Radio 1 Klixon
Mooney P/IN

8-34 REVISED NOVEMBER 1966

 NO. ITE~1 QTY. RATING MANUFACTURER MODEL/PART NO.

62 Circuit Brcaker-GzarCont. 1 5A Klixon PSM-SN

Mooney P/N 919000-9
63 CircuitBrealrlr Switch 1 Klixon D-7270-5
Glide Slope
64 CircuitBrlalcer Switch 1 Klixon D-7270-5
Mark Beacon
65 CircuitBreaker Switch 1 10A Klixon D-7270-5-10
Heat Pitot
66 CircuitBrcalrer Switch 1 10A Klixon D-7270-5-10
A-C Light
67 CircuitBreaker Switch 1 20A Klixon D-727d-5-20
Landing Light
68 Circuit Breaker Switch 1 5A Kiixon ~ji70-5-5
Position Lights
69 CircuitBreaker Switch 1 10A Klixon D-7270-5-10
Fuel Pump
70 Horn-DualWanring 1 014A Safe Flight 283
0.3A Mooney P/N 800185
71 Pitot-Heated 1 8.GA Aero-Inst. R.H. 502-12
12V AN 5812
72 Light-AntiCollision 1 6.62A Grimes D-7080-1-12
12V
73 Reiay-ExternalFbwer 1 0.69 Cole-Hersee 24059-
74 Buss Bar-~lain 1 Mooney P/N 800012-1´•1
75 Buss Bar-Ausiliary I Mooney P/N 800012-13
76 Buss Bar-Power 1 Mooney P/N 800012-7
77 Buss Bar-Radio 1 Mooney P./N 800012-7
78 Terminal Strip--ShuntLights 1 Joy Ailfg. Co. 520077-251
Mooney P/N 919008
79 Light ~aming-Generator 1 0.08A Sloan 1065-R-F32
Mooney P/N 913067-Basic
80 Clamp-Cable(Cluster Gage) 1 MS3057-10B
81 Connector-Ait. Air 1 Dialco 7538-XP12
82 Speed Clip-Alt. Air light 1 Dialco 7538-XP51
83 CircuitBreaker--Gear Actuator 1 25A Klixon D7271-8-25
84 Switch-Up Limit (w./actuator) 1 Mirco DT-2R-A7
Mirco iMCD2711
85 Switch-Down Limit 1 Mirco DT-2R-A7
(u~/actuatoI) Mirco MCD2711
86 Srdtch-Gear Safety 1 Dukes 3203-00
Mooney P/N 950161
87 Switch-Gear Control 1 Mirco 1TL149-30
88 RelaS´•-GearUp 1 ~50A Cutler-Hammer 6041H50A
12V
89 Rtla~-Gzar Down 1 0.50A Cutler-Hammer 6041H50A
12V
90 Actuator-Landing Gear 12V Dukes 4196-00-1B-
Mooney P./N 950158-501
91 Receptical-E~.uterna1 Ebwer AN2552-3A
93 Trans.-FuelOty.(L. Otbd.) A-C
93 Trans.--FueiOty.(R. Otbd.) A-C

REVISED NOVEMBER 1966 S-35

 NOTES
.1120F
(ELECTRICAL SYSTEM DMGR~SI)

i. All splices are AMP knife disconnects or equivalent.

2. Allcircuitbreakers areofatrip-freetype,
3. All terminals are AN659 (or equivalent), or wire ends are soldered together:
4. All terminals will be of a preinsulared type or will be insulated with ampsulation or equivalent ma-

terial.
5. Wires without dash numbers are furnished with the ecluipment item.
6. "F" indicates grounding through frame (no wires).
7. symbolindicates a knifedisconnect.
8., All wires may have any revision letter.
mil-spec.
Example: Mil-W-50S6 may be MiI-W-5086A
9. The symbol signifies optional erpipmenr that maybe installed as desired.
10. The following‘ pairs of wires must be twisted together counter-clockwise with a minimum of three
wraps per fodt:

Wires -085 -088 Wires -139 Sr -138

-084 -087 -097 Sr -105
-083 Sr -088 -098 Sr -099
-089 Sr -096 -050 Sr -114
-090 Sr -095 -106 -111
-091& -094 -107& -110
-092 Sr -093 -108 Sr -109

8-36 REVISED NOVEMBER 19ib

 SECTION

IN STRU NIEN TS
 SECTION IX
INSTRUMENTS

A. GENERAL

The instrument panel has been designed to provide functional location of all flight, radio, and engine
instrument groups.

All flight instruments are grouped on a shock-mounted panel directly in front of the pilot. They are
located in such a manner as to provide maximum efficiency for instrument cross-check, a most im-
portant item for IFR flying. A radio panel is located in the center of the instrument panel and has
sufficient room for tworadios. The glove compartment slot serves as a mounting area for a third
radio. All of the engine instruments are grouped on the co-pilot’s panel.

B. TROUBtE SHOOTIE~G

When trcuble shooting having an electrical power source, check from the power supply
instruments
to the instrument affected. malfunction is found, the trouble probably exists inside the individual
If no

instrument. The instrument then should be replaced by an identical instrument, tested and known to
.be operating properly. See Table 7 for instrument trouble shooting procedures.

SHOP NOTES

9-1
TABLE 7 INSTRUMENT TROUBLE SHOOT1NG

TROUBLE CAUSE RES1EDY

COhlPASS

Excessive card error Compass not properly Compensate instrument.

compensated Refer to Service Instruction M20-23.

External magnetic Locate magnetic interference and

I interference or aircraft eliminate if possible. Demagnetize
structure magnetized. structure.

Excessive card Improper mounting an Align instrument.

oscillation instrument panel

1 Insufficient liquid. Replace instrument.

Card Sluggisk Weak card magnets. Replace instrument.

Excessive pivot friction or i Replace instrument.

II
broken jewel.

H Instrument too heavily Remove excess compensation.

compensated. and compensate instrument.

Liquid leakage. Loose bezel screws. Replace instrument.

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

Discolored luminous mark- Age. Replace instrument,

Ings or damping liquid.

Defective light. Burnt out lamp or bmken Check lamp or continuity of wiring.
circuit.

No reading on indicator Broken Shaft.

Replace shaft
(either permanent or inter-
mittent). Springs weak Replace instrument.

Pointer oscillates I Rough spot or sharp Repair or replace.

excessively. bend in shaft.

Excessive friction in Replace instrument.

11 instrument.

9-2
REVISED NOVEMBER 1966
 TABLE 7 (Continued)

TROUBLE CAUSE REMEDY

ALTIMETER

Escessive scale error. Improper calibration Replace instrument.

adjustment.

Excessive pointer Defective mechanism Replace instrument.

oscillation

High reading. Improper venting. Eliminate leak in static pressure sys-

tem

Setting knob is hard to Wrong lubrication or lack Replace instrument.

turn. of lubrication.

Inner reference marker Out of engagement. Replace instrum~nt.

fails to move when setting
knob is rotated.

Setting knob setscre~ir I Excessive vibration. Tighten instrument screw, if loose.

loose or missing. Replace screw, if screw is
missing.

Cracked or loose cover i Excessive vibration Replace instrument.

glass.

Dull or discolored lumi- Age. Replace instrument.

nous markings.

Barometric scale and ref- i Shift in mechanism. Reset pointers and recalibrate.
ernencemarkers are out of
synchronism with pointers

Barometric scale and ref- Slippage of mating parts. Replace instrument.

ernce markers out of sgn-
chronisa

AIRSPEED INDICATOR

Pointer of instrument Leak in instrument case Check for leak and seat
does nor indicate or in pitot lines.

properly.

Pointer of instrument Leak in instrument case Check for leak and seal.
oscillates. or in pitot lines.-

HEATED PITOT TUBE (IF USED)

Tube does not heat or clear Circuit breaker switch Reset.

rtself of ice with swich ON. tripped. Replace.
Defective breaker.

REVISED NOVEMBER 1966

9-3
TABLE 7-(Continued

TROUBLE CAUSE RE~IEDY

a Open circuit. Repair.

Excessive voltage drop be- Check voltage at pitot head.

II tween battery and pitot
head.

1 Heating element burned Replace pitot head.

out.

TURN AND BANK INDICATOR

Pointer fails to respond. Foreign matter lodged Replace instrument.

in instrument.

II No electric circuit. Check for voltage at instrument.

Incorrect sensitivity. Misadjustment of sensi- Adjust by means of sensitivity spring

tivity spring. screw. If this pulls the pointer from

zero, replace instrument.

Pointer does not set on Gimbal and rotor assembly Replace instrument.
zero, out of balance.

II Pointer incorrectly set on Replace instrument.

its staff.

Sensitivity adjustment Replace instrument.

pulls pointer off zero.

Vibrating pointer. Gimbal and rotor assembly ReDlace instrument.

out of balance.

Fitted or worn pivots or Replace instrument.

bearings.

In low temperature, point- Oil has become too thick t Replace instrument.
er fails to respond or does

so sluggishly and with in- Insufficient bearing Reoiace instrument.

Suificient deflection. clearing.

Pointer sluggish in return- Oil or dirt detween damp- Replace instrument.

ing to zero and does not ing pistons and cylinders.
set when sation-
ary.

Excessive clearance be- Replace instrument.

II tween rotor and rotor
pivots.

Ball inclinometer does not Instrument out of align- Correct alignment.

center. ment on panel.

*NOTE: Turn andbank indicatorshavebeen replacedbytum coordinators on all models (l’ttj7 OX). Refer
to Section VI for turn coordinator trouble shooting procedures.

REVISED NOVEMBER 1966

9-4
TABLE 7-(Conrinued)

RATE OF CLIMB INDICATOR

Pointer does not set on Aging of diaphragm. Reset pointer to zero by means of
zero. setting knob. Tap instrument while
resetting.
Disconnsct all instruments connected
Pointer fails to respond. Oa-tn~ction in static line. to the static line. Check individual
instruments for leaks. Testlines for
leaks.

Pointer oscillates. Leaks in static line. Disconnect all instruments connected

to the static line. Check individual
instruments for leaks. Reconnect in-
struments to static line and test instal-
lation for leaks.

It
Defective mechanism. Replace instnunent.

MANIFOLD PRESSURE

Excessive ~mr at e~dsting Pointer shifted Replace instrument.

barometric pressure

Excessive error when Line leaking. Tighten line connections.

engine is running.

sluggish or jerky pointer Improper damping Adjust damping screw.

movemezlt. adjustment.

Broken or,loose cover Vibration or excessive Replace glass and reseat case.
glass pressure.

Dull or discolored Age. Replace instrument.

luminous markings.

Incorrect reading. Moisture or on in line. Disconnect lines and purge with air.

SHOP NOTES

9-s
TABLE 7 (Continued)

TROUBLE PROBABLE CAUSE

DIRECTIONAL GYRO INDICATOR

Excessive drift in either 1965: instrument air filter Inspect filter. Replace if necessary.
direction. dirty @igh vacuum indica-

ted).
1966: Vacuum regulating
valve filter dirty @igh vac- Test with vibrometer. If amplitude is
uum indicated). more than .004 inch, examine shock
mountings and note whether connections
Excessive vibration ate pulling on instrument.

Insufficient vacuum. Correct for insufficient vacuum as fol-

If vacuum indication is be- lows:
low 3.5 inches Hg´• check
as follows:

i. Vacuum regulating valve i. Adjust vacuum regulating valve.

improperly adjusted.

2. Faulty vacuum gage 2. Check calibration of gage.

3. Pump failure 3. Repair or replace pump.

4. Vacuum line kinked, 4´• Locate and, if defective, replace or

le~aking, or too long for repair vacuum line. Check for col-
its diameter lapsed inner wall of flexible hose.

I>efective mechanism (worn Replace indicator.

or dirty pivots and bearings)

I)ial spins continuously in Operating limits have been Cage and reset the instrument with
one direction. I exceeded the aircraft level.

I>efective mechanism Replace indicator.

GYRO-HORIZON INDICATOR

TROUBLE PROBABLE CAUSE REiL1EDY

1965: Instrument air filter

dirty thigh vacuum indica-
Horizon bat fails to re-
ted). Examine filter. Clean or replace if
spend. 1966: Vacuum regulating necessary.
valve filter dirty Ihigh vac-
uum indicated).

9-6
 TABLE 7 (Continued)

TROUBLE PROBABLE CAUSE REMEDY

Horizon bar fails to re- Insufficient vacuum Correct insufficient vacuum as follows:
spend. (Continued) resulting from the following:

i. Vacuum regulating valve i. Adjust vacuum regulating valve.

improperly adjusted

2. Faulty vacuum gage 2. calibration of gage.

3. Pump failure 3. Repair ct replace pump.

4. Vacuum line kinked, A Locate and repair. Check for col-

leaking, or too long for lapsed inner wall of flexible hose.
its diameter

Horizon bar does not set- Defective mechanism

Replace indicator.
tie.

Insufficient vacuum Correct for insufficient vacuum as out-

lined above.

Excessive vibration Test with vibrometer. If am’plitude is

more than.004 inch, examine installa-
tion to determine whether flexible hose
connections are restricting movement of
instrument; examine shock mountings
and replace if necessary.

1965: Instrument air filter for excessive fol-

Correct vacuum as
Horizon bar oscilates or dirty thigh vacuum indica-
lows:
vibrates excessively, ted).
1966: Vacuum regulating
valve filter dirty thigh vac-
uum indicated). Examine filter, and clean or replace
if necessary.

Vacuum regulating valve

Adjust vacuum regulating valve.
improperly adjusted

Faulty vacuum gage

Check calibration of gage.

Defective mechanism Replace indicator.

Excessive vibration i Test with vibrometer. If amplitude is

more than.004 inch, exarr´•ine~installa-
tion to determine whether flexible hose
connections are restricting movement of
instrument; examine shock mountings
and replace if necessary.

9-7
 SHOP NOTES

9-s
SECTION

INSPECTION
 SECTION X
INSPECTION

A. GENERAL

This section provides instructions for conducting routine periodic inspections. Repair or replace-
ment instructions for those components Found to be unserviceable at inspection may be found in the
section covering the application aircraft system.

WARNZh7G: When working on engines, ground the magneto primary circuit or remove all the spark
plug leads before performing any checks on the ignition system.

B. PREFLIQFTINSPECTION

This inspection is required to determine the generalcondition of the airplane and to detect any damage
or maladjustment which might interfere with flight ieliability. The following safety procedure in-
structions must become an integral pan of the aircraft owner’s operating routine and/or preflight
inspection. The airplane should be visually inspected to determine any obvious defects or damage
to the foTlowing corn_ponents:

Wings Landing gear

Fuselage Fuel tanks(Check for evidence of leaks.)
Empennage Engine cowling
Control surfaces Fuel tank filler caps

Check the operation of the following control surfaces for full travel and smooth operation:

Ailerons Rudder Empennage trim system

Elevators Wingflaps
Check the following electrical ecluipment for proper operation:

Transmitter and receiver Landing light

Position lights Fuel cIuantity gages for both fuel tanks

Check the following po~er plant items:

Carburetor heat control (Check rv120E power boost door seal for leaks.).
En,oine oil for cIuality and quantity.
Air filter for cleariliness.
Fuel and oil system for any evidence of leakage.
Ignition wiring for tightness of connections and conditions of wires.
Engine in general for any loose or missing nuts, palnuts, and forproper safetying of allplugs.
hla~eros for rpm drop at approximately 1700 rpm or 50 to 65?7, rated power as indicated on manifold
pressure gage. The normal drop from both magnetos to one magneto is not to exceed more than
135 rpm.
Oil pressure (rninimum idle-25 psi).
fuel Pressure (0.5 to 6.0 psi. XI20C D; Is. to 30. psi. M20E).
En,oine for proper tune up (650 to 18d0 rpm).

Visually inspect the following pans of the propeller:

Hub: Allbolts and nuts for ti~tness.
Blades: Excessive loss of grease from bearings.
If propeller runs rough, check the pitch of the blades (t_0.5" allowable difference) and blade ttack
(116 in. allowable difference).

10-1
C. 25-HOUR

required to determine the ~eneralcondition of the airplane and to detect any damage
This inspection is
or maladjustment which mi~ht interfere with fli~t reliability. The following inspection ~ide is
recommended by the factory and should be performed only by qualified personnel.

25-HOUR INSPECTION GUIDE

Remove both engine side cowls.

Clean engine.
Remove and clean air filter. (Check power boost door seal for leaks on all M20E models.)
Inspect engine compartment for oil and fuel leaks. Check for security and condition of all ec~ipment
in accessory section.
Check wing, fuselage, and tail section for dents or damage.
Check complete airplane for any damage to control surfaces.
Check all instruments for operation, dials for proper markings, and placards for legibility.
Check static and pressure system for leaks or stoppage.
Inspect airplane in,oeneral for security of all bolts, nuts, screws, etc.

Check the battery.

D. 50-HOUR lNSPECTIONGUIDE

Complete all steps in the 25-hour inspection plus the following:

Engine: (Refer to Lycoming Operator’s Manual for other 50-hour inspection items.)
Drain oil; inspect and clean screens.
Check engine for oil leaks.
Check ignition harness for fray, wear, etc.
Check throttle, carburetor heat, mixnrre, and propeller governor control for general condition, travel,
and free operation (M20C D). Inspect power boost control on M20E models.
Check engine mount structure and en~ne rubber dynafocal mounts.
Check exhaust stacks for general condition.
Check engine baffles for wear or cracks.
Check fluid in brake reservoir.
Check battery and cables.
Check cowl for cracks, loose or missing screws, etc.

Propeller:
Remove and inspect spinner.
Check propeller for oil leaks and general condition.
Inspect blades for nicks and cracks.
Clean and reinstall spinner.

Cabin:
Check parking brake cylinder for leaks.
Check trim operation.
Check cabin door and pilot window for damage and proper operation.
Check cabin, navigation, instruments, and landing lights.
Check fuel-selector valve For proper operation.

10-2
 Landin,o Gear:
Check tires for freedom from escessive ~ear and proper inflation. (Refer to Section I page 1-5.)
Check for general condition.
Check collars and bolts for damage (Refer to Section V-G).

tv‘ing:
Check surfaces and rips for danlaage.
Check ailerons, aileron attachments, and bell cranks for damage and operation.
Check flaps and attachments for damage and operation.
Lubricate controls as directed in Fi~re 2-9.

Fuselage and Empennage:

Check stabilizer, fin. and rudder surfaces for dama,oe.
Check rudder and elevators for proper attachment.
Lubricate controls and trim systems as directed in Fi~re 2-9).

E. CZ~DE

Perform all steps in 25-and 50-hour inspection plus the following:

En,oine: (Refer to Lycomin,o O_Derator’s ~Ianual for other 100-hour inspection items.)
Remove en,oine COwl and clean engine. Perform a hot engine differential con7pression check.
Check and.’or re-place siDark plugs as req~iired.
Check ma,oneto points for proper gap. Reset or retime if necessary.
Clean fuel strainers and check fuel system for leaks.
Check vacuum pump.
Check condition of flex fuel lines.
Check en~ine and electric fuel pumps for proper operation.
Flush battery bos.
Remove and check e?chaust stacks and heater muff.

Propeller:
Rotate blades and check for tightness.
Visnafly inspect hub parts for cracks.
Check propeller mounting bolts for 60-70foot pounds of torcIue.
Check sDinner and bulkhead for cracks and general condition.
Check
f~r
adequate grease level in hub.

Cabin:
Remove instrument access panels.
Check control and linkage.
Check instruments. lines. and attachments. (Check vacuum filter on all 1966 and subsequent models.!
Check uDholstery for tears.
Check sears. belts, securing brackets and bolts.

Landing Gear:
Remove and repack rJheel bearin~. (Refer ro Figure 2-9 for recommended lubricant.)
Check brake shoes and discs for wear.
Check brake lines.
Check wheels for
ChecZi,oear doors and attachments.
Check nose gear linkage and travel.
steering-control
Check shock discs (Refer to Section V-G).
Check 3f20D gear fairings.

REVISED NOVEMBER 1966 10-3

 Check tire pressure (Refer to Section I. paXe 1-5,.
Lubricate in accordance with Figure 2-9.
Check and rig gear (Refe: to Section V-F.).

Wing:
Remove inspection plates and fairin,os, and check wing for general condition (Refer to Fi~re 10-1.).
Check fuel sells for leaks.
Check wing-attach bolts for security.

NOTE: A reasonable amount of care should be exercised wheninstallingthedimpled inspection

plateson the wings of those airplanes having dimpled screw holes in the wing skins. The
use of improper screws or over-torcIuin,o of screws is not recommended as this could result

in cracking of the ~in,o skins in the dimpled area,

Fuselage and Empennage:

Check stabilizer bearings,bungees, and horns for damage and proper operation.
Check rudder, horns, and attachments for damage and proper operation.
Check trim mechanism.
Check bulkheads and stringers for damage.
Check electrical wiring, loops, loopmounw, and antennas.
Check fuel lines. valves, and gages for damage and proper operation.
Lubricate in accordance with Fi~re 2-9,

F. OVERLIMITS INSPECTIONGLrIDE

If the aircraft has been operated so that any of its components have exceeded their maximum opera-
tional limits, check with the appropriate manufacturer’s manual.

G. CHECK

Following the 50- and 100-hour inspections, start the engine and check the following items for proper
functioning:
Check fuel pump and fuel tank selector valve.
Check fuel cpanrity and pressure gages.
Check oil pressure and temperature gages.
Check generator output.
Check manifold pressure.
Check operation of carburetor heat control. (Inspect power boost control on h120E F models.)
Check parking brake.
Check gyros for noise and rough operation.
Check cabin heater operation.
Check magneto switch for grounding at idle RPSI.
Check magneto rpm variation (~claxlmum allowable variation is 50 RP~I).
Check throttle operation.
Check propeller for smoothness of operation.
Check propeller governor action.
Check radio operation.
Check engine idle at 650 rpm.

GENERAL:
See that aircraft conforms to FAA Aircraft Specifications 2~3.
See that FAA Airworthiness Directives have been complied with.
See that Manufacturers’ Service Bulletins have been complied with.
See that aircraft logs and certificates are in proper order.

See that the Weight Balance Record is up to date and in the aircraft.
See that the Owners Manuz1(1967 and subsequent editions) or the Airplane Flight hianual is complete
and in the aircraft.

10-4 REVISED NOVEMBER 1966

H. ELECTRIC GEAR. INSPECTION (OPTIONAL INSTALLATION)

Raise aircraft on jacks to allow operational testing of both the electrical and emergency gear ex-
tension systems. (Refer to Section V-R.).

An 80 mph air pressure equivalent must´•he applied to the pitot tube orifice to activate the airspeed
pressure switch to permit retraction of the gear. Attach a Ii-inch length of 3/8-inch plyable rubber
hose eurgicaltubing) over the pitot tube end and pinch the open end of the tube with a cotter pin.
Rotate the coffer piri zmtil the compressed air within the rolled tube activates the airspeed pressure
switch (located in the cabin near the hydraulic reservoir). Then raise the gear electrically.

Refer to page 5-23 for emergency gear extension instructions (Manual Operation of th~ Electrical
Landing Gear System). Test emergency gear extension. Do not retract the gear with the emergency
handcrank; to do so will damage the flexible drive shaft.

Thoroughly inspect and lubricate both the electrical and emergency gear extension systems (See
Lubrication Diagram, Figure 2-9 for proper lubricant)

The drive connector should be removed from the actuating motor and inspected for a worn or stripped
f~male spline. Clean and Lubricate the motor worm gear.

Test the drive connector to check for proper functioning.

NOTES

If thepilot experiences difficulty with gear extension or retraction, ~he gear system should be lubri-
cated and the malfunction corrected before the next flight.- Raise the aircraft on jacks, locate and
correct the trouble, and cycle-test gear operation. Refer to page 5-23, Section H, paragraph 3 for
periodic lubrication and inspection specifications for the electric gear system actuator.

Always make certain the handcrank is fully disengaged before operating the gear electrically.

In trouble shooting the system, remember that a binding or maladjusted gear door may overload
the actuating system. Remove the belly panels to examine the knife disconnects under the floor
boards for loose or faulty connections. An electrical overload in the system can be discovered by
connecting an ammeter in the motor circuit (red wire leading from the actuating motor to
the electric fuel pump circuit breaker) beneath the floor boards. Open the red wire knife disconnect
and connect the ammeter poles to the disconnect terminals. During gear extension, the ammeter
should read 15 to 18 amp; during retraction, 25-30 amp. An amperage reading exceeding the max-
imum indicates a faulty motor or electrical circuit and/or a binding in the gear action due to impro-
per rigging or misalignment of the gear actuator and its mounting bracket.

Dual waroi~ horns (1967models) replace the landing gear-throttle warning horn and prestail
ON
indicator installed on The low-pitch, interrupted (beep), 100 CPM horn is wired
1962-1966 models.
to the landing gear-throttle switch. The high-pitch, continuous, 2000 CPS warning horn is wired to
the prestall warning switch.

REVISED OCTOBER 1975 10-5

 FIGURE 10-1 ACCESS PANEL REMOVAL DIAGRAM

(100-MOOR INSPECTION)

2 3

I /1S\ 4 6 5 6 6

NOTE: M20F access panel locations are the same as M20E.

7 7
f\

14 13 12 11 9 8 11 12 13 14

oo
oo
C10 C3I3 t7Clo

11 10 8 11

C>

1. COHLING-Engine access.

2. ACCESS DOOR-Electrical storage battery (M20C&D)

3. ACCESS COVER-Flight instruments, hydraulic fluid reservoir and parking brake valve, PC rate
gyro (1966, M20CgE)
NOTE: The turn coordinator replaces the rare gyro and turn and bank indicator on all models
1967 on.

RNISED NOVEMBER 1966 10-7

 4. ACCESS COVER-Electrical storage battery (M20E), PC gyro and servos, pneumatic step, con-

trol tubes, trim guide blocks.

5. FAIR1NGS-Empennage attach bearings, trim jack screw.
6. INSPECTION COVERS STINGER-Control bvngees, elevator and r’udder stop adiustmenrs.
7. EXHAUST CAVITY FAIRINGS-Electric boost pump (1965 Models On), selector valve and sump
drain, fuel lines, control tubes and bungees, broke cylinders and lines.
8. ACCESS PANELS-Control rubes, main spar, flap indicator cable.
9. INSPECTION COVER-Hydraulic flap pump, stabilizer trim stop indicator adjustment.
10. INSPECTION COVER-Control rubes g guide blocks, hydraulic flap cylinder, flap indicator cable.
11. INSPECTION COVERS-Wing attach, control tube guide blocks.
12. INSPECTION COVERS-Main gear retraction spring.
l3. INSPECTION COVERS-Control tube guide blocks.
14. INSPECTION COVERS-Aileron bellcranks and stop ossemblies, control tubes.

FIGURE 10-2 POWER BOOST DOOR SEAL INSPECTION DIAGRAM (M20E)

I 1

O O 9.99.-.9-\ INSPEtTFOR
TIGHT SEAL

d ’f ~e oC~I o

O O O O O

CAUTION: To prevent engine damage during ground or dusty air operation, induction air through the
Ram Air Scoop must be shut off completely so that the engine is forced to receive its air
through the filter.
Therefore the Seal around the Shut-Off Door must be INSPECTED REG-
ULARLY FOR LEAKS to insure that unfiltered air cannot bypass the door when the Power
Boost Control is in the "OFF" position.

10-8
 (For Company Use Only)

SRR No.
Probable Cause of Mal-
IWOONEY A/RCRAFT, /NC.

,~hP’’
function: Confirmed O
KERRVILLE. TEXAS Unconfirmed O

UNSATISFACTORY REPORT

Model Serial No. Beg. No.

Geographical Location
IEy state or country) Engine Model SerialNo.

Propeller Model Serial No. Total Time Since Overhaul

Total Time on Airplane Total Time on Malfunctioning Part

Part No. (Mooney) Manufacturer (if other than Mooney)

Model No. Iif vendor part) SerialNo. (if vendor Part)

Rarranty Replacement Yes C7 No n

Airplane Owner’s Name Address

Brief Narrative of Ma~function (or accident)

Probable Cause of Malfunction

Corrective Action Taken

Date Signature

Mooney Rep. n SerticeCenter 1Z!

Distributor rj Owner C]
Dealer O Pilot I I
ENG.FORM109
 SHEET N0, 1

spshP~t MOONEY M208 M20C

100-HOUR INSPECflON GUIDE
M20D M20E M20F

Date. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Ouner’s

Reg, No......l................. A/C Serial ~ib.......................Aircraft tach, time..........Hrs. Date of last periodic......................................

Engine Model and Serial ~b.........................................................Prop design and Serial No...............................................................

Engine time.. ....l........hrs. Brand of oil and weight used......................................................................

i. Is approved owners or flight manualin aircraft? Yes No Current and in proper condition? Yes No

Are current log books in aircraft? Yes No Current and in proper condition? Yes No

3, Is Registration Certificate.in aircraft? Yes No Current and in proper condition? Yes No

-t. Is Airworthiness Certificate in aircraft? Yes No Current and.in proper condition? Yes No

5. Is all factory service information complied with? Yes No

6. Are all applicable FAA.4irworthiness Directives complied with? Yes No

7. Is H’eight Balance Record current? Yes No

ESGINE SECTION: (Refer to Lycoming Operator’s Manual and Mooney Mechanic’s Inspector’s
Service Maintenance Mannal,) Initials Initials

i, Remove and clean engine cowling and baffling; inspect for cracks
and wash engine

2, Perform a hot engine differential compression check: cyl. read-

ing 1. 2. 3, 4,

3, Lubricating System (Refer to Lycoming Operator’s Manual.)

a. Drain sump and change oil filter (if installed)
b, Remove pressure and suction screens. Check for metal

c, Clean and inspect screens. Reinstall and safetjr screens

d, Check engine for oil leaks (note correct)-

e, Inspect condition of oil cooler
f, Service engine with recommended lubricating oil (Refer to

Mooney S M Manual,)

Ignition System (Refer to Lycoming Operator’s Manual.)

a, Inspect spark plugs, replace or clean and regap
b, Inspect ignition harness for general condition and freedom from

fraying or chaffing
c. Inspect magnetos and points; check magneto-timing

_5. Electrical System (Refer to Mooney S gr ;M Manual.)

a. Inspzct battery for security, battery box for corrosion,

and vent for obstruction
b. Inspect´•gznerator and accessories
c. Inspect electrical components and wiring

REVISED NOVEMBER 196~

 SHEET NO. 2
sA~PLE
d. Inspect starter and starter drive; lubricate starter drive.
(Refer to LSlcoming Operator’s Manual and Figure 2-9, Mooney S&M;Llanual)-
e. Inspect landing light and navigation lights for
and operation
f. Inspect panel lights and dimming system for operation
6. Fuel System, M-20B,C,D (Refer to Mooney S 8; M Manual.)
a. Inspect carburetor, clean screens, and check fuel flow
b. Inspect carburetor heat system for leaks and proper operation
c. Remove, clean, inspect, and reoil air filter
d. Inspect carburetor airbox and induction system for condition
e. Inspect fuel selector valve for operation and proper pointer indication
f. Operate boost pump; check pressure and all lines for leaks
g. Clean electric fuel pump screen (1963 and previous models)
h. Drain fuel sumps and fuel selector valve (R L tanks)
6A. Fuel System, M-20E (Refer to Mooney S M Manual.)
a. Inspect fuel injection system, clean screens, and injector nozzles
(Refer to Bendix Service Manual.)--
b. Check power boost system for proper operation and door seal for leaks
c. Remove, clean, and inspect dry-air filter
d. Inspect air induction system and alternate-air valve
e. Inspect fuel selector valve for operation and proper pointer indication
f. Operate boost pump; check pressure and ail lines for leaks
g. Drain fuel sumps and fuel selector valve (R L tanks)
7. Remove heater jacket and inspect exhaust system for leaks and cracks.
Remove exhaust cavities and inspect area
8. Inspect fire wall for sealing and freedom from cracks
proper
9. Inspect engine mount, bolts, and rubber mounts for security
10. Lubricate engine controls and inspect for security, full travel, and free movement

11. Lubricate cowl flaps and inspect for proper opening and operation
12. Remove propeller spinner and check for cracks and general condition
13. Inspect propeller hub for grease leakage; check hub bolts and mounting bolts
for proper torque; inspect blades for cracks, nicks, and dents; lubricate as

needed (Refer to appropriate manufacturers’ handbooks.)

AIRFRAME SECTION (Refer to Moonev Service Maintenance Manual.)

1. Inspect exterior and interior of aircraft for general condition, collision

damage, loose rivets, dents, and corrosion
2. Inspect wings and empennage for general condition, collision damage,
loose ri~ets, dents, and corrosion
3. Inspect control surfaces for security of attachment, proper rigging, free
movement, collision damage, loose rivets, dents, and corrosion
4. Lubricate flight control system guide blocks, hinge points, rod end
bearings, and bell cranks (Refer to Mooney S M Manual, Figure 2-9.)
5. inspect all wing, fuselage, and empennage drain holes for obstruction
6. Inspect empennage trim system for proper operation and rigging.
Lubricate in accordance with Figure 6-8 in ~koney S 51 Manual
7. Inspect flap system LM-20B, mechanical; M"OC,D,E, hydraulic) for proper
operation and rigging. Lubricate in accordance with Figure 1-9 in
Mooney S M Manual
8. Inspect flight instmments, filters, and vacuum system for proper operation,
marking, and condition. Clean vacuum air filter (1966 and subsequent models)
SHEET NO, 3 samP~
9. Inspect cabin lights, circuit breakers, and electrical components
for proper operation
10. Inspect PC system components for security, leaks, and proper operation.
(Refer to Mooney S g: M Manual)
11. Inspect vacuum step for security and proper operation.
(Lubricate in accordance with Mooney S M Xlanual)
12. Inspect wing interior in fuel tank area for fuel leaks, fuel tanir vents for
obstruction, and fuel filler caps forsecurity and proper operation
13. Inspect cabin and baggage doors for condition, proper operation, and- sealing
Inspect windshields and windows for cracks, crazing, scratches, and distortion
15. Inspect seats and seat belts for security, proper operation, and condition
16. Inspect compass and compass deviation card forproper indication and
compensation. (Refer to Mooney Bulletin No. 8 ~Serv.ice Instruction M20-23~.
17, Inspect radio equipment for proper installation and operation
18. Inspect cabin for proper sealing
LANDING GEAR OPERATIONCHECK (Refer to Moonev S M Manual.)

1. Raise aircraft on jacks. (Refer to iMooney S M Manual.)

Inspect brakes, hydraulic brake cylinders, and hydraulic
system for leaks and general condition
3. Remove wheels, inspect, repack, reinstall, and safety. Lubricate
brake guide pins using Silicone-base lubricant. Check wheels for
free rotation and proper brake action. (Refer to Mooney S M Manual.)
4. Lubricate and inspect landing gear pivot points and moving parts.
(Refer to Mooney S M Manual, Figure 2-9.)
5. Manual gear retraction system: check operation, rigging, gear warning
system (lights hem), down-lock preload, and doors for proper
closing. (Refer to Mooney S& M Manual.)-
5A. Electric gear retraction system:. check operation, rigging, gear
warning system (lights horn), up-lock mechanism, air-pressure safety
switch, down-lock preload, and doors for proper sequencing and sealing
5B. Lower gear with the emergency gear extension system. Dd not attempt
gear retraction using emergency system. (Refer to Mooney S M Manual.)
6. Inspect shock absorbers (main nose gears) in accordance with
Figures 5-12 or 5-13, Mooney S M Manual
7. Fixed gear: inspect landing gear fairing (M-20D)-
8. Check operation of stall warning system
9. Check air seals in flap and wheel well areas

10. Operate flap system. Service hydraulic reservoir. (Refer to Mooney

S g,M Manual for fluid specifications.)
POST-INSPECTION OPERATION CHECK (Refer to Mooney Owner’s Manual.)

1. Check propeller governor operation with engine running at 2000 rpm and
pitch control at low pitch thigh rpm); when propeller control is pulled out
to high pitch (low rpm), engine speed should decrease at least 500 rpm

2. Check ease of operation for all engine controls with engine running
3. Check generator output indication
´•1. Check oil pressure indication
5. Check fuel pressure indication
SHEET NO. 4 SAIPL~
6. Check fuel quantity indication
7. Check cylinder head temperature indication
8. Check oil temperature indication
9. Check idle rpm, idle mixture, and idle cutoff-
10. Check propeller pitch through range
11. Check cabin and panel lights
12. Check radio operation
13. Check autopilotoperation
14. Check magneto drop and ground
15. Check brake operation
16. Check fuel selector valve operation
17. Test vacuum warning lights and instruments for proper operation
18. Flight check gear-up warning horn at 12" manifold pressure
19. Flight check aircraft rigging and PC system for proper operation
20. Make a cabin ventilation and heating system carbon monoxide check
 SECTION

PAINTING AND
PREVENTION OF
CORROSION
 SECTION XI
PAINTING PREVENTION OF CORROSION

A. GENERAL

This section lists paint materials and recommended painting procedures. Corrosion control tech-
nicFres are also discussed along with suggested procedures for zinc chromating internal airframe
surfaces.

E3. PAINTING

The exteriors of all new lu120 series aircraft are painted with acrylic enamel. This finish should be
freplently cleaned with an aircraft-type washing compound when exposed to salt air or an atmosphere
having corrosive fallout. Aircraft should be hangared when not in use.
1. Materials.

a. 83319 (Code 033650) solvent-type cleaner, Dupont Prepsol

b. Cheesecloth; Sandpaper, 3M, 180-400-600 grit.

c. T-657 cleaningsolvent
309´•6 (Code 035210) wash thinner. Enmar

d. Body puny or aerodynamic filler (Taylor Art Plastics, Flax-Bond "C" or 3M Co. Flex)

e. EX2858A (Code 034150) filler/primer, Enmar Gray

MX22B (Code035130) dopeandlac~erthinner

f. EX2016G (Code 034175) vinyl-type zinc chromate primer, Enmar

EX2016G (Code 035120) vinyl-type reducer

g. 82A25414 (Code 030730) exterior base acrylic enamel, Enmar Ermine White
T1866A (Code035170) acrylicenamelthinner

h. Refer to Table 8 for exterior color coat material callout.

i. Refer to Table 8 for exterior trim material callout.

Factory recommended replacement exterior trim finish:

61P-34929, P-38502 Enmar Sierra Gold (syrithetic finish)
C-85 thinner
Do not use sealcoat with synthetic finish.

j. T1411 (Code 035150) burn-down thinner

k. 271125414 (Code 033550) laccluer, Enmar Ermine White (tubular steel structure)
MX22B (Code 035130) dope and lacc[uer thinner
8585A (Code 034105) low moisture sensitive zinc chromate primer

i. EX-1707 (Code 033130) acid-resistant black paint (banery case and exhaust areas)
MX22B (Code 035130) dope and lacquer thinner

m. Refer to Table 8 for interior trim material callout.

ii-i
 2. Procedures

a. For urliformity of finish appearance, prepare only entire skin panels for repainting. First,
clean the area to be repaintedwith the solvent-type cleaner. Wipe on, then wipe off cleaner
with cheese cloth or clean towels until surface is dry. Second, sand areas to be painted as
needed-start with No. 400 grit (wet or dry) and finish with 600 to 800 grit. Third, reclean
entire area to be painted with the solvent-type cleaner, wipe clean, and mask-off adjoining
areas that will not be painted.

b. To fill dents, use a flexible plastic welding compound (bodyputty or aerodynamic filler).
Carefully follow instructions printed on the container.

c. All spray-applied paints must be mixed in a one-to-one proportion(50-50) with their ap-

propriate thinners. When using a large compressor unit and re,oulator, maintain a 60 PSI
spraying pressure and be sure intake air is properly filtered. A portable spray pot should
be set to maintain a 40 PSI minimum spraypressure. Work only in a dust and moisture
controlled painting area.

d. Use a face respirator to prevent inhalation of paint dust. It is recommended that the work-
man apply a li~t of vaseline to his hair and exposed skin to allow easy removal of paint
coat
stains with a mild soap solution

e. Always test-spray a new paint mixture on masking paper before proceeding with the appli-

cation. Hold the spray nozzle eight to ten inches from the surface. Spray in cross patterns
with verticdl stroke movements first and then withhorizontal movements over the same area.

f. Apply vinyl-chromate primer mixed with vinyl-type reducer to newly installed unpainted
skins. Apply one coat of appropriately thinned gray primer (Enmar filler) to previously
painted surfaces that have been properly prepared for repainting. Allow primer to dry run-
free, then spray three coats of the properly mixed finish paint.

g. All acrylicenamel paints have a tendency to "orangepeel" when sprayed too close to the
panel when the paint viscosity is too high. The ~tddition of an equal pan of burn-down
or

thinner to the thinned finish paint will eliminate orange peel effect due to improper thinning.

h. Apply three of white base and/or color finish allowing three to five minutes between
coats
coats dependingupon weather conditions. Allow five to ten minutes between coats in cold,
dry weather; in humid weather, each coat should dry in fifteen minutes.

i. Do not thin acid-resistant black paint or exterior finish touch-up paint for brush-on appli-
cation. Use a small round watercolor brush trimmed to a point for ap~lication of undiluted

touch-up paint to small scratches and bare spots. A handy rack for touch-up paint storage
can be made from babyfood jarsmounted in a wooden rack.

11-2
 TABLE 8 EXTERIOR PAINT CHART

YEAR I MODEL I PART NO. DESCRIPTION LOCATION

1962 M-20C 82A-28378 TITIAN RED, Acrylic Enamel Exterior Trim
1962 M-20C 82A-27633 BLUE METALIC, Acrylic Enamel Exterior Trim
1962 NI-ZOC 82A-28161 DARK GOLD, Acrylic Enamel Exterior Trim
1962 M-20C 82A-27630 BLUE METALIC, Acrylic Enamel Exterior Bottom
_

1962 M-20C 82A-28303 ROMAN RED, Acrylic Enamel Exterior Bottom

1962 g 1963 M-20C 27H-20800 SPICE BROWN, Acrylic Enamel Interi4r Trim
)962 8 1963 M´•ZDC 82A-26183 LIGHT GOLD, Acrylic Enamel Exterior Bottom
1963 M-20C 82A-29626 GUNMETAL, Acr2lic Enamel Exterior Trim
1963 M-20C 82A-29629 FROSTED TURQUOISE, Acrylic Enamel Exterior Bottom
1963 M-2DC 82A-29744 FROSTED GREEN, Acrylic Enamel Exterior Bottom
1963 M-20C 82A-29745 FROSTED COPPER, Acrylic Enamel Exterior Bottom
1963 M-20C 828-29801 FROSTED RED, Acrylic Enamel Exterior Bottom
1963 M-~OD 82A-29801 FROSTED RED, Acrylic Enamel Exterior Bottom
1964 M-20C,DgEI 82A31495 METALLIC ORANGE, Acrvlic Enamel Exterior Bottom
1964 M-20C.DgEI 82A-32014 SILVER BLUE, Met. Acrylic Enamel Exterior Bottom
1964 M-20C.DgEI 82A-32015 LIGHT EMERALD, Met. Acrylic Enamel Exterior Bottom
1964 M-20C.DgEI 82A-32016 BERLY BLUE, Met. Acrylic Enamel Exterior Bottom
1964 M-20C.DgEI 27H-23455 SAND BEIGE, Acrylic Lacquer interior Trim
1964 M-20C.DgEI 27H-20800 SPICE BROWN, Acrylic Lacquer Interior Trim
1964 M-20CgD 82831885 CANYON GOLD, Met. Acrylic Enamel Exterior Trim
1964 M-20E 82A-32264 DARK CANYON GOLD,EAet. Acrylic Enamel Exterior Trim
1965 M-2DC.DgEI 828-34923 YELLOW, Acrylic Enamel Exterior
1965 M-20C.DgEI 82834924 BLUE, Acrylic Enamel Exterior
1965 M-20C.D&EI 828-34925 RED, Acrylic Enamel Exterior
1965 M-20C.DgEI 828-33929 SIERRA GOLD, Acrylic Enamel Exterior
i966 M-2DC.DgEI 828-37781 GREY, Acrylic Enamel Exterior
1966 M-20C.DgEI 828-37778 RED, Acryiic Enamel Exterior
1366 M-20CgD 82B37780 BLUE/GREEN, Acrylic Enamel Exterior
1966 M-20E 828-37775 BRILLIANT BLUE, Acrylic Enamel Exterior
1966 M-20E 828-37776 BRILLIANT GREEN, Acrylic Enamel Exterior
1967 MZ0C,E,gFI 82834925 POPPY RED Acryiic Enamel Exterior
1967 M20C,E,gq 82839276 BRITE ROSE Acrylic Enamel Exterior
1967 MZOC,E, 82839283 BRITE ORANGE Acryiic Enamel Exterior
1967 MPOC.E.&q 82839295 GOLD Acrylic Enamel Exterior Trim
1967 M20C,E,g 82840054 MOONEY WHITE Acrylic Enamel Base Color
1967 MPOCIEI& 82B37781 GRAY Acrylic Enamel Exterior Trim

MISCELLANEOUS PAINTS 8 MATERIALS

ALL ALL 828-25414 WHITE, Acrylic Enamel General Exterior

ALL ALL MX-lld3 OVERCOAT, I General Exterior
ALL ALL MX-22B THINNER, Lacquer General Exterior
ALL ALL MIL-5041 BLACK. Non-skid Wing Walld General Exterior
ALL ALL 6633 TAPE, Gold Decorating General Extnr;or
ALL ALL r630 TAPE, Chrome Decorating General Exterior
ALL ALL MX-144B BLACK, Temporary Marking
ALL ALL MiL-D-8585A PRIMER. Zinc Chromate Structure
ALL ALL EX-1707 BL4CK, Acid Proof Structure
ALL ALL E-6889 PRIMER, Zinc Chromate
(spray can) Structure
ALL ALL EX-2016G PRIMER, Zinc Chromate
(vinyl type) Structure
ALL ALL 1 =23-622 BLACK, Lacquer Structure
ALL ALL EX-1858-A-6q PRIMER. Light Gray Structure
ALL ALL 1 T-6073 THINNER, Zinc Chromate Structure
1965 M20t.D,gE! EX-617Cj BEIGE Baked Enamel Interior Trim
1965 8 1966 M20t,D,gEI n"4205 LAREDO TAN Lucite Interior Trim
1966 M20t,D,gEI 27H-25988 ECRU Lacquer Interior Trim
1966 MZOC,D,gEJ 27H-3808 GRAY Lacquer Interior Trim
1966 M20C,D,&EI 27H-24697 CARPET BEIGE Lacquer Interior Trim

NOTE: 1967 and 1966 M20D points and materials are identical.

REVISED NOVEMBER’1966
11-3
C. CORROSION DETECTION PREVENTION

Most metalic fabrication materials are susceptible to corrosion. Corrosion may occur an aircraft
in any climate, but it will be a problem more often in areas where the aircraft is exposed to salt air
or high humidity, or where there are industrial contaminants in the armosphere. The aircraft should
be Inspected frequently to detect and correct corrosion before serious damage occurs.

I. Types of corrosion.

Corrosion normally appears in one or more of four forms. Eacb type of corrosion can be pre-
cluded or controlled by a preventative maintenance program.

a. Chemical corrosion

Chemical corrosion normally occurs where battery acid or exhaust gases come in contact
with metalsurfaces. A few simple precautions will prevent chemical corrosion.

1. Be sure that the battery vent is free from obstruction at all times.

2. All scratches and worn spots, found in areas painted with acid-resistantpaint, should
be repainted at once.

3. If acid is spilled on metal surfaces, flush the entire area with sodium bicarbonate add
water. The solution should be rinsed away at once and the area dried by driving all
water from crevices with an air hose before wiping the surface dry with a clean cloth.

4. Frequently clean exhaust gas deposits from metal surfaces.

b. Local-cell corrosion

Local-cell corrosion is easy to detect. On baremetal surfaces, in an early stage of develop-

ment, it appears as a light, wfiitish powder deposit. Surface pits warn of advanced local-
cell corrosion. On painted surfaces, the first indication of corrosion will be evidence of
paint blistering.

Any form of corrosion should be removed at once upon detection. If it is necessary to re-
move paint, only an approved aircraft paint remover should be used. Care should be taken
that paint removing substances are not allowed to remain in metal crevices, for this will
cause further corrosion. Turco 2662(3 or 3002 will remove corrosion and treat the metal
surface in one application.

c. Concentrationcell corrosion.

Corrosion forming under rivet heads, along faying surfaces, or at skin to longeron contact
surfaces is called concentration cell corrosion. Detection recFdres close inspection. Rivets
must be removed and skin laps must be separated to remove concentration cell corrosion.
Use aluminum wool soaked in kerosene to scour corrosion deposits from the surface before
painting both fayin,a surfaces with zinc chromate primer and reassemblying.

d. Galvanic corrosion

Galvanic corrosion sometimes occurs between dissimilar metals such as stainless steel and
aluminum. To remove this form of corrosion, separate the pans, remove the corrosion, and
paint both surfaces with zinc chromate primer before reassembling.

Further recommended procedures for corrosion control areoutlined in Turco Products Tech-
nical Data Bulletin g184. Write Turco Products. inc., P.O. Box 1055, Wilmington, California.

11-4
2. Hints onpreventingcorrosion.

a. Thoroughly examine unpaimed metal surfaces at inspections and check corrosion when found.
Carefully examine seams, lap joints, and crevices wheremoisture or dirt can collect. Areas
exposed to exhaust gases require frequent inspection and cleaning.

b. Corrosion may attack metal even though the surface is painted. Inspect painted areas for
a blistered or scaly appearance that warns of corrosion below the paint layer.

c. Use only aircraft detergents to wash the exterior airframe. Cover vent scoops whenthe
aircraft is being washed. Rinse the exterior after exposure to salt air or industrial fallout.

d. Since moisture promotes corrosion, areas where water is apt to collect must be inspected
thoroughly and frequently. Use an air hose to drive water from crevices before wiping the
exterior surface dry after washdown.

e. Hangar the aircraft when not in use.

f. If battery acid is spilled on any part of the aircraft, wash the area immediately with a solu-
tion of sodium bicarbonate in water. Rinse with water and dry with clean towels.

3. Zincchromating.
Zinc internal surfaces of the airframe will greatly retard corrosion. However,
chromating
chromating eliminate the necessity of periodic inspection aimed at detection of trouble
will not

s_aots, especially in those areas where it is impracticableto apply zinc chromate (skin laps,
fayings, etc.). If deep corrosion is found, it should be removedby sandingwith emery cloth
of approximately 320 grit. Aluminum etching compounds are not recommended for corrosion
removing, because they cannot be readily neutralized.

a. Materials

i. Cleaning solvents

a. T-657 cleaning solvent-Turco Products, Inc., 6135 South Central Avenue, Los
Angeles, California.

b. ,U394 wash thinner Enmar, Inc., 25th N.Y. Avenue, Wichita, Kansas.

2. Zincchromate

a. zinc chromate primer (Mil. Spec. P-8585A)-Enmar, Inc., 25th N.Y.

Avenue, Wichita, Kansas.

3. Safetymixingcan

a. ~10308 Justrite Manufacturing Co., Chicago, Illinois.

b. Procedure

1. Cleaning

a. Pour a portion of the cleaning fluid into the safety mixing can.

b. Wipe the area to be cleaned with a clean rag dipped in the cleaning fluid.

c. Wipe the cleaned area with a rag dipped in the cleaning solvent. The entire area

to be painted should be cleaned before application of the primer.

CAUTION: Wipe solvent is toxic and flammable. Do not smoke within 25 feet of
the exposed solvent. Force air through the painting area and use only
explosion-proof lights.

11-5
 SHOP NOTES

11-6
APPENDIX
 SERVICE SHOP TOOPS EQUIPMENT

I. AIRFRAME

SOURCE TOOL PART NUMBER

Commercial Jack and stand

Mooney Distributors Gearretractioq spring replacement tool 8186

Mooney Distributors Landing gear retracting truss torque tool 010011

010008

Mooney Distributors Travel boards 010013001-R~udder

01001i0001-Elevator
010007001-Flap
Mooney Distributors Shock disc replacement tools ME 120
ME 121
Commercial Torque wrench TQ-51-A (or equiv.)
Peterson Mfg. Co., Wide-jaw vice grips for control surface
De\rc’itt, Neb. trimming (See Figure 6-3 in Mooney Service
Maintenance Manual)
Brittain Industries Positive Control system test kit TS-100
Mooney Distributors AMP connector kit

Mooney Distributors Solderless terminal tool (3 sizes available)

Commercial Battery charger
Commercial OHM meter
Commercial k~lP meter

Commercial Grease gun

Tools for sheet metal work:
Commercial Rivet gun
Commercial Air drill
Commercial Cutters

Note: No. 5 and 6 huckrivet tool for landing gear conversion or wing spar
repair can be obtained from Aircraft Tools, Inc., 9030 Bellanca Ave.,
Los Angeles 45, California.

II~ ENGINE AND ACCESSORIES

Commercial Differential compression tester

Commercial Spark plug cleaner

Commercial Gap setting tool
Commercial Growler
Lgcoming Cylinder base nut wrench 64943-64942

Lycomirlg Valve spring compressor 1130-B

Lycoming Ring compressor

Bendix. Timing kit (Bendix) 11-8150

Bendix Timing light (Bendix) Model A1D (or equiv.)

Bendix Piston position indicator
 MOONEY AIRCRAFT FART NUMBER

CROSS REFERENCE INDEX

New No. Old No. New No. Old No. New No. Old No.

01 0000 2286 140000 3522 150000 8705

010001 8188 140001 3521 150001 8522
010002 2312 140002 3519 150004 6458
010003 3302 140003 3518 150011 8519
010004 3149 140004 3028 150012 8520
010005 8577 140005 3047 150013 8521
010006 3301 140006 3057
010007 8663 140007 3323
010008 8444 140008 3438
010009 8443 140009 3439
010010 8441 140010 3505 160000 8015
010011 8442 140011 3506 160001 8551
140012 3507 160002 8552
140013 3508 160003 8654
140014 3509
140015 3510
110000 8670 140016 3511
110001 8585 140017 3512 200000 8600
110002 7344 140018 3513
110003 7345 140019 3515
110004 7274 140020 3527
110009 8610 140021 3652 210000 2182
140022 -3653 210001 2169
140023 3654 210002 2170
140024 3655 210003 2167
140025 3656 210004 2168
120000 8062 140026 3657 210005 2171
120001 8122 140030 3664 210006 2172
120002 8282 140031 3666 210007 2173
120003 8704 140033 3668 210008 2174
120004 8531 140034 3669 210009 2226
140035 7083 210010 2227
140036 8527 210011 2228
140037 8536 210012 2229
140038 3045 210013 2198
130000 8300 140039 3397 210014 2199
130001 8318 140062 3299 210015 2221
130002 8319 140063 3660 210016 2222
130025 8325 140064 3662 210017 2233
130026 8326 140065 3667 210018 2241
130027 8327 140066 8248 210019 2191
130041 8341 140067 3659 210020 2230
130042 8343 140068 3661 210021 2271
130044 8345 140069 8035 210022 2217
130054 8354 140070 8007 210023 2236
130055 8596 140071 3650 210024 2192
130056 8671 140072 3651 210026 2195
130057 8532 140073 3658 210027 2190
130058 8310 140074 3663 210028 2201
130065 8504 140075 3961
130066 8576 140076 3058 210025 2234
New No. Old No. New No. Old No. New No. Old No.

210029 2211 210085 2303 230004 2292

210030 2210 210086 2309 230005 2293
210031 2209 210087 2310 230006 2295
210032 2208 210088 2301 230007 2297
210033 2207 216089 2300 230008 2289
210034 2206 210090 2304 230009 2296
210035 2205 210091 2280 230010 2308
210036 2204 210092 2281 230011 2175
210037 2223 210093 2284 230012 2177
210038 2193 210094 2250 230013 2178
210039 2202 210095 2270
210040 2203 210096 2267
210041 2194 210097 2231
214042 2189 210098 2238 240000 2248
210043 2184 210099 2235 240001 2160
210044 2188 210100 22~40 240002 2161
210045 2185 210101 223 240903 2162
210046 2187 210102 2214 240004 2163
210047 2179 210103 2323 240005 2164
210048 2186 210104 2220 240006 2245
210049 2224 210105 2249 240007 2246
210050 2225 210106 2219 240008 2247
210051 2244 210107 2181 240009 2268
210052 2216 210108 2277 240010 2269
210053 2218 210109 2274 240011 2298
210054 2213 210110 2276
210055 2165 210111 2275
210056 2166 210112 2307 300000 8017
210057 2212 210113 2313
210058 2242 210114 2326
210059 2237 210115 7302
210060 2251 210116 7231
210061 2252 210117 7232
310000 3011
210062 2253 210118 7252
310001 3016
210063 2254 210119 7273
310002 3032
210064 2255 210120 2232
310003 3037
210065 2256 210121 2315
310004 3038
210066 2266 210122 2243
310005 3039
210067 2257 210123 2258
310006 3052
210068 2259 210124 2518
310007 3053
210069 2196 210125 i31~9
310008 3123
210070 2183
310009 3124
210071 2215
3100i0 3150
210072 2260
310011 3155
210073 2261 220000 2180
310012 3159
210074 2262 220001 2288
310013 3161
210075 2263
310014 3162
210076 2264
310015 3163
210077 2265
310016 3165
2i0078 2272 230000 2200
310017 3166
210079 2278 230001 2294
310018 3167
210080 2279 230002 2290
310019 3169
210081 2282 230003 2291
210082 2287
210083 2285
210084 2283
New No. Old No. New No; Old No. New No. Old No.

310020 3185 310076 3358 310132 3984

310021 3192 310077 3361 310133 3988
310022 3193 310078 3364 310134 3990
310023 3194 310079 3336 310135 3991
310024 3196 310080 3367´• 310136 3992
310025 3197 310081 3368 310137 3995
310026 3200 310082 3369 310138 3996
310027 3212 310083 3370 310139 3997
310028 3214 310084 3371 310140 3524
310029 3215 310085 3372 310149 3359
310030 3216 310086 3373 310150 3360
310031 3217 310087 3374 310151 3213
310032 3218 310088 3375 310152 3263
310033 3219 310089 3376 310153 3985
310034 3220 310090 3377
310035 3222 310091 3378
310036 3227 310092 3379
310037 3228 310093 3380
310038 3233 310094 3381 320000 3520
310039 3236 310095 3382 320091 8257
310040 3237 310096 3384 320004 3261
310041 3285 310097 3385 320005 3128
310042 3286 3101398 3388 320006 3951
310043 3292 310099 3389
310044 3246 310100 3390
310045 3250 310101 3528
310046 3251 310102 3394 340000 3900
310047 3252 310103 3396 340001 3020
310048 3253 310104 3413 340002 3022
310049 3254 310105 3414 340003 3023
310050 3255 310106 3415 340004 3044
310051 3256 810107 3416 340005 3051
310052 3257 310108 3418 340006 3093
310053 3259 310109 3422 340007 3131
310054 3266 310110 3437 340008 3132
310055 3268 3~0111 3483 340009 3271
310056 3300 310112 3486 340010 3272
310057 3310 310113 3494 340011 3274
310058 3311 310114 3429 340012 3275
310059 3312 310115 3530 340013 3276
310060 3318 310116 3543 340014 3277
310061 3319 310117 3953 340015 3278
310062 3321 310118 3955 340016 3279
310063 3324 310119 3956 340017 3280
310064 3325 310120 3957 340018 3283
310065 3326 310121 3958 340019 3331
310066 3321 310122 3959 340020 3347
310067 3328 310123 3973 340021 3348
310068 3329 310124 3974 340022 3349
310069 3332 310125 3975 340023 3455
310070 3333 310126 3976 340024 3456
310071 3352 310127 3977 340025 3488
310072 3353 310128 3978 340026 3525
310073 3355 310129 3979 340027 3526
310074 3356 310130 3981 340028 3531
310075 3357 310131 3982
 Old No New No. Old No. New No. Old No.
New No.

350039 6126
340029 3606 340090 3964
3965 350040 3289
340030 3611 340091
350041 3308
340031 3612 340092 3966
350042 3401
340032 3613 340093 3972
3129 350043 3402
340033 3614 340094
3130 350045 3406
340034 3901 340095
3940 350046 3417
340035 3902 340097
3034 350047 3424
340036 3903 340098
350048 3425
340037 3904 340099 3937
3938 350049 3434
340038 3905 340100
3936 350050 3436
340039 3906 340101
3042 350051 3445
340040 3907 340102
3949 350052 3446
340041 3954 340103
350053 3451
340042 3968
350054 3475
340043 3969
350055 3910
340044 3970
350000 3911 350056 3912
340045 3971
350001 3031 350057 3913
840046 3987
350002 3036 350058 3914
340047 3989
350003 3041 350059 3915
340048 3993
3998 350004 3050 350060 3916
340049
3999 350005 3060 350061 3917
340050
340051 3994 350006 3061 350062 3918
3~0052 3500 350007 3062 350063 3919
340053 3501 350008 ~3064 350064 3920
340054 3502 350009 3065 350065 3921
340055 3503 350010 3066 350066 3922
340056 3504 350011 3067 350067 3923
340057 3391 350012 3068 350068 3924
340058 4012 350013 3069 350069 3925
340059 350014 3070 350070 3926
7061
340060 350015 3071 350071 3927
7062
340061 350016 3072 350072 3928
7047
340062 350017 3073 350073 3929
7069
340063 350018 3074 350074 3930
7070
340064 350019 3075 350075 3931
7137
340065 350020 3076 350076 3932
7138
340066 350021 3077 350077 3934
8146
340067 350022 3078 350078 3935
8117
340068 350023 3079 350079 3943
8163
340069 350024 3082 350080 3945
8173
340070 350025 3083 350081 3948
8174
340071 350026 3099 350082 3950
8176
340072 350027 3100 350~83 3960
8164
340073 8505 350028 3101 350084 3980
340074 8506 350029 3104 350085 3986
340075 350030 3106 350086 3485
8529
340076 350031 3108 350087 3498
8376
340077 350032 31-10 .350088 3334
8240
340078 8209 350033 3111 350089 3335
340079 3025 350034 5112 350090 3336
340080 7473 350035 3113 350091 3337
340081 3118 350036 3114 350092 3338
340087 3939 350037 3119 350093 3341
340088 3941 350038 3120 350094 3342
340089 3942 350095 3345
New No. Old No. New No. Old No., New No. Old No.

350096 3365 410028 4173 440015 4137

350097 4175 410029 4178 440016 4212
350098 4176 410030 4179 440017 4171
350099 6158 410031 .4192 440019 4190
350100 8535 410032 4193
350101 8258 410033 4194
350102 8273 410034 4199
350103 8274 410035 4202
350104 8275 410036 4203
350105 8276 410037 4205
4211 450000 4101
350106 8~77 410035
350107 8284
350105 8285
350109 8286 420000 4102
350110 8279
350111 8283
8034 430000 4103 460000 4104
350119
8231 430001 4152 460001 4105
350120
4157 460002 4151
350121 3267 430002
430003 4162 460003 4158
430004 4164 460004 4159

8601 430005 4165 460005 4160

400000
8602 430006 4166 460006 4161
400001
430007 4167 460007 41.63
430008 4168 460008 4269
4145 430009 4170 460009 4191
410000
410001 4115 430010 4185 460010 4198
410002 4106 430011 4188 460011 4206
4119 430012 4189 460012 4181
410003
410004 4120 430013 4195
410005 4121 430014 4196
410006 4122 430015 4197
410007 4123 430016 4204 470000 3175
410008 4124 430017 4180 470001 3290
410009 4125 470002 3933
410010 -1126
410011 4127
410012 4128 440000 4107 480000 4100
410013 4129 440001 4108 480001 4174
410014 4130 440002 4109 480002 4182
410015 4131 440003 4110 480003 4155
410016 4136 440004 4111
410017 4138 440005 4112
410018 4139 440006 4113 500000 8603
410019 4146 440007 4114
410020 4147 440008 4116
410021 4148 440009 4117 510000 5003
410022 4149 440010 4118 510001 5004
410023 4150 440011 4132 510002 5005
410024 4153 440012 4133 510003 5006
410025 4154 440013 4134 510004 5266
410026 4156 440014 4135 510005 5014
410027 4172 510006 5267
New No. Old No. New No. Old No. New No. Old No.

510007 5019 540003 5070 560018 5225

510008 5021 54004 5074 560019 5226
510009 5022 540005 5078 560020 5227
510010 5023 560021 5228
510011 5026 560022 5229
510012 5027 560023 5230
510013 5028 550000 8591 560024 5231
510014 5029 550001 5237 560025 5232
510015 5030 550002 5238 560026 5233
510016 5258 550003 8590 560027 5234
510017 5259 550004 8367 560028 5236
510018 5049 550005 8368 560029 5239
510019 5051 550006 8053 560030 5240
510020 5058 550007 8651 560031 5241
510021 5067 550008 8051 560034 5244
510022 5080 550009 8052 560038 5250
510023 5083 550010 8054 560039 5251
510024 5084 550011 8058 560040 5253
510025 5093 550012 8059 560041 5254
510026 5100 550013 8075 560043 5275
510027 5131 550014 8110 560044 5085
510029 5186 550015 8111 560045 8653
550016 8128 560046 5286
550017 8124 560047 5287
550019 8125 560048 5288
520000 5257 550020 8126 560049 5289
520001 5071 550021 8129 560050 8005
520002 5018 550022 8130 560051 5264
520003 5013 550023 8131
520004 5031 550024 8133
520005 5256 550025 8134 590000 3409
550026 8149 590001 3407
530000 5012 550027 8526 590002 3040
530001 5010 590004 3410
530002 5017 560000 5252
530003 5032 560001 5009
530004 5066 560002 5033 600000 6000
530005 5077 560003 5034 600001 6010
530006 5081 560004 5038 600002 6005
530007 5106 560005 5039 600003 6004
530008 5109 560006 5040 600004 6008
530009 5133 560007 5041 600005 6021
530010 5164 560008 5047 600006 6084
530011 5187 560009 5056 600007 6076
530012 5272 560010 5057 600008 6077
530013 5273 560011 5059 600009 6078
560012 5092 600010 6079
560013 5099 600011 6080
540000 5048 560014 5169 600012 6081
540001 5015 560015 5170 500013 6082
540002 5062 560016 5182 600014 6083
560017 5183 600015 6088
600016 6090
 Old No. New No. Old No. New No. Old No.
New No.

6091 600073 6229 620008 6438

600017
6092 600074 6231 620011 6199
600018
6093 600075 6235 620012 6405
600019
600020 6094 600076 6245
600021 6095 600W7 6260
6096 600078 6372 630000 6489
600022
600079 6374 630001 6490
600023 6097
6100 600080 6383 6~30002 6371
600024
600081 6384 630003 6365
600025 6101
6385 630004 6362
600026 6103 600082
6397 630005 6358
600027 6104 600083
6413 630006 6357
600028 6105 600084
600085 6496 630007 6063
600029 6107
6108 600086 6457 630008 6035
~00030
8262 630009 6400
600031 6110 600087
6112 600088 6215 630010 6364
600032
600104 722 630011 6261
600033 6113
600105 6128 630012 6172
600034 6114
630013 6037
6190
630014 6003
600036 6225
6048 630015 6185
600037 6239 610000
610001 6058 630016 6184
600038 6241
6059 630017 6187
600039 6242 610002
610003 6075 630018 6363
600040 6243
600041 6246 610004 6132
600042 6249 610005 6152
6460 640000 6483
~00043 6415 610006
6463 640001 6484
6416 610007
610008 6465 640002 6461
600045 6417
610009 6466 640003 3287
6!10046 6418
610010 6468 640004 6047
600047 6467
610011 6414 640005 8074
600048 6052
610012 8614 640006 8042
600049 6053
610018 6049 640007 8043
600050 6197
610019 6050 640008 8044
600051 6219
610020 6119 640009 8046
d00052 6220
610021 6121 640010 8047
600053 6237
610022 6131 640011 8080
600054 6259
610023 6446 640012 8081
600055 6420
610024 6447 640013 8082
600056 6479
610025 6459 640014 8083
600057 6098
600058 6064 610026 6122 640015 8098
600059 6173 610027 6452 640016 8107
600060 6174 610028 6073 640017 8121
600061 6175 640018 8189
600062 6176 640019 8190
600063 6178 620000 6223 640020 8191
600063 6179 620001 6382 640021 8192
600065 6181 620002 6407 640022 8193
600066 6186 620003 t491 640023 8194
600067 6195 620004 6492 640024 8195
600068 6196 620005 6501 640025 8198
~00069 6209 620006 6203 640026 8200
600WO 6210 62GOW 6480
600071 6211
600072 6213
New No. Old No. New No. Old No. New No. Old No,

640027 8201 650038 6161 710000 7247

640028 8202 650039 6168 710001 7030
640029 8203 650040 6244 710002 7031
640030 8204 650041 6499 710003 7037
640031 8252 650042 1003 710004 7044
640032 8253 710005 7057
640033 8354 710006 7058
640034 8255 660000 6409 710007 7059
640035 8377 660001 6471 710008 7073
640036 8539 660002 6472 710009 7104
640037 3288 660003 6473 710010 7109
640038 6504 660004 6476 710011 7267
640043 8048 660005 6494 710012 7268
640044 6257 660006 6493
660007 6456
660008 649~ 720000 7248
650000 6001 660009 6497 720001 7019
690001 6009 660010 6477 720002 7063
650002 6014 660011 6485 720003 7064
650003 6015 660012 6486 720004 7065
650004 6044 660013 6487 720005 7066
650005 6039 660014 6488 7´•20006 7114
650006 6041 660015 6503 720007 7118
650007 6136 660016 6502 720008 7119
650008 6146 660020 8108 720009 7136
650009 6147 660021 8534 720010 7148
650010 6148 660022 6117 720011 7149
650011 6481 660023 6140 720012 7150
650012 6482 660024 6252 720013 7151
650013 6380 660025 6258 720014 7152
650014 6381 660026 6390 720015 7269
650015 6389 660027 6391 720016 7330
650016 6395 660028 6394 720017 7332
650017 6469 660029 6392 720018 7039
650018 6498 660031 6202 720019 7040
650019 6019 660032 6393 720020 7041
650020 6040 6~0033 6255 720021 7125
650021 6042 660034 6247
650022 6045 660035 6166
650023 6074 660036 6250 730000 7067
650024 6159 660037 6167 730001 7071
650025 6160 660038 6163 730002 7072
650026 6254 660039 6054 730003 7139
650027 6272 660040 8235 730004 7262
650028 6356 660041 6248 730005 7270
650029 6373 660042 6164 730006 7271
650030 6375 660043 6253 730007 7341
650031 6377 730008 7263
650032 6060 730009 7264
650033 6061 700000 730010 7265
650034 6222 700001 7256 730011 7266
650035 6474 730012 7115
650036 6475
650037 6162
New No. Old No. New No. Old No. New No. Old No.

740000 7280 140072 7051 800008 8565

740001 7295 740073 3029
800009 8557
740002 7296 740074 7076
800010 8580
740003 7282 740075 ~7096
800011 8570
740004 7283 740076 7054
800012 8669
740005 7284 740077 8033
800013 8525
740006 7292 740078 7216
800014 8474
740007 7293 740079 7200
800015 8512
740008 7294 740081 7227
800016 8113
740009 7324
800017 8139
740010 7326
800018 8208
740011 7327 750000 7300
800019 8221
740012 7328 750001 7123
800020 8222
740013 7329 750002 7075
800021 8224
740014 7331 750003 7112
800022 8225
740015 7333 750004 7301
800023 8226
740016 7336 750005 7303
800024 8227
740017 7337 750006 7304
800025 8236
740018 7278 750007 7306
800026 8237
740019 7279 750008 7307
800027 8250
740020 7298 750009 7310
800028 6464
740021 7217 750010 7312
800029 8728
740022 7214 750011 7314
800030 8666
740023 7208 750012 7315
800031 8662
740024 7207 750013 7316
800034 8511
740025 7204 750014 7317
800035 8251
740026 7201 750015 7318
800036 8166
740027 7202 750016 7319
800037 8157
740028 7203 _750017 7325
800038 8136
740029 7210 750018 8706
800039 8085
740030 7206 750019 7339
800040 8074
740031 7212 750020 7055
800041 8664
740033 7275 750021 7238
80004´•2 8073
740034 7276 750022 7099
800043 8573
740035 7277 750023 7098
740036 7320 750024 7097
740037 7321 750025 7092
810009 8089
740038 7322 750026 7079
740039 7338 750027 7078
740040 7237 750028 7077
820000 8550
740041 7033 750029 7074
820001 8549
740042 7035 750030 7250
820002 8548
740043 7036 750031 7076
820003 8342
740044 7038
820004 8578
740060 7126 800000 8547 820005 8667
740061 7257 8546
800001 820006 8680
740062 7254 8545
800002 820007 8681
740063 7253 8544
800003 820008 8682
740064 7251
800004 8543 820009 8683
740065 7219
800005 8542 820010 8684
740066 7218
800006 8541 820011 8685
740067 7095
800007 8572 820012 8688
740068 7094
740069 7056
740070 7053
740071 7052
New No. Old No. New No. Old No. New No. Old No.

820013 8652 830016 8749 850007 7313

820014 8582 830017 8750 850008 8369
820015 8563 830018 8751 850009 7122
820016 8514 830019 8752 850010 7016
820017 8515 830020 8714
820018 8517
820019 8660 860000 8228
8210020 8668 840000 8265
820021 8688 840001 7110
820022 8687 840002 8266
820023 8393 840003 8267 911000 2176
820024 840004 8268 911001 2197
8689
820025 8690 840005 8269 911002 2321
820026 8691 840006 8270 911003 3140
820027 8703 840007 8271 911004 4140
820028 8720 840008 8272 911005 4141
820030 8722 840009 8278 911006 4142
820031 8734 840010 8281 911007 4207
820032 8518 840011 8289 911008 5261
820039 8616 840012 8290 912000 2306
820040 8615 840013 8291 912001 3313
820041 8508 840014 8292 912002 3317
820042 8507 840015 8293 912003 6120
820043 8509 840016 8294 912004 28556
820044 8564 840017 8295 912005 ~524
820045 3952 840018 8296 913000 870
82004-6 8210 840019 8297 913001 452
820047 3393 840020 8298 913002 587
820048 6443 840021 8299 913003 592
820049 6444 840022 8355 913004 595
820050 6436 840023 8361 913005 721
820051 6435 840024 8363 913006 722
820052 6065 840025 8364 913007 822
820053 6437 840026 8365 913008 1177
820054 6451 840027 8370 913009 2316
840028 8371 913010 2317
840029 8372 913011 2327
830000 8709 840030 8373 913012 2328
830001 8710 840031 8374 913013 3403
830002 8711 840032 8388 913014 3404
830003 8721 840033 8280 913015 3135
830004 8723 840034 8247 913016 3136
830005 8735 913017 3264
830006 8736 913018 3243
830007 8737 850000 7021 913019 3244
830008 8738 850001 6129 913020 3245
830009 8739 850002 7116 913021 4201
830010 8743 850003 7117 913022 5044
830011 8744 850004 7121 913023 5082
830012 8745 850005 7323 913024 5089
830013 8746 850006 7309 913025 5271
913026 7340
83003~4
830015
8747
8748
New No. Old No. New No. Old No, New No. Old No.

913027 7034 915003 7101 950013 8655

913028 7025 915004 7132 950014 8609
913029 7020 915005 7135 950015 8676
913030 7220 915006 -7144 950016
913031 7221 915007 7224 950017
913032 7222 915008 7225 950018 8234
913033 7223 915009 7235 950019 8716
913034 7228 915010 7236 950020 2320
913035 7229 915011 7240 950021 7346
913036 7230 915012 7241 950022 7347
913037 7233 915013 7242 950024 8608
913038 7234 915014 7243 950025 8658
913039 7205 915015 7244 950026 8675
913040 7272 915016 7245 950027 8719
913041 7226 915017 7246 950028 8755
913042 8357 915019 5242 950029 8731
913043 8106 915020 5243 950030 8732
913044 8554 915021 5245 950031 8756
913045 8569 915022 5248 950032 8782
913046 8592 915023 5249 950033 8771
913047 8584 915024 5263 950034 8772
913048 585 915025 7018 950035 8773
914000 3983 915026 7281 950036 8774
914001 4143 916000 976 950037 8775
914002 4144 916001 3665 950038 8776
914003 5132 916002 5053 950039 8777
914004 5042 916003 5069 950040 8778
914005 5262 916004 5098 950041 8779
914006 5280 916005 5255 950042 8780
914007 5046 916006 6226 950043 8761
914008 5270 916007 7032 950044 8762
914009 5246 916008 8659 950045 8764
914010 5247 916009 508 950046 8770
914011 5091 917000 5075 950047 8760
914012 5090 917001 986 950048 8763
914013 7006 917002 7124 950049 8769
914014 7239 917003 8538 950050 8768
914015 7249 917004 8571 950051 8767
914016 7022 917007 7105 950052 8766
914017 7215 950053 8765
914018 7311 950054 8742
914019 8027 950055 8754
914020 7042 950056 8759
914021 8021 950000 8698 950057 8781
914022 8022 950001 8700 950058 8783
914023 8023 950002 8702 950066 8218
914024 8026 950003 8707 950067 8567
914025 8165 950004 8708 950075 8238
914026 8182 950005 8656 950076 8661
914027 8183 950006 8557 950077 8540
914028 8378 950007 8693 950078 8533
914029 8733 950008 8692
914´•039 8025 950009 8679
915000 7084 950010 8678
915001 7085 950011 8677
915002 7100 950012 8673
 p~"

NOTICE OF MISSING INFORMATION

Issue\Section TECHNICA~I PUBLICATIOMS LIST

PAC~S
Page Number(s)

The above has been ordered from the source.

As soon as it is received, ATP will reissue
this fiche to include the above.