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TABLE OF CONTENTS
SECTION PAGE
I GENERAL INFORMATION
1-1
II GROUND HANDLING,
SERVICING INSPECTION 2-1
m POWER PLANT 3-1
IV FUEL SYSTEM. P1
V LANDING GEAR 5-1
VI FLIGHT CONTROLS 6-1
VII INSTRUMENTS. 7-1
wI
DISASSEMBLY,
CORROSION CONTROL
PAINTING
8-1
TX ELECTRICAL SYSTEM 9-1
APPENDM
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SECTION
GENERAL
IN FOR NI AT ION
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IMOONEY
SERVICE IVIAINTENANCE NIANUAL
SECTI ON I. GEN~RAL INFORMATION
TABLE OF CONTENTS
PARA PAGE PARA
PAGE
1-1. Aircraft
Description........ 1-1 1-8. Positive
ControlSystem 1-6
1-2.
Engine 1~1 1-9. Electric Power
System 1,6
1-3. Propeller
1-2 1-10. Instruments
1-7
1-4. Airframe
1-3 1-11. Cabin
Beating Ventilating
1-5.
Landing~Gear System 1-6
Systems 1-7
1-6.
Flight
Control
Systems 1-6 1-12.
FuelSystem 1-7
1-7.
wine; Flap System 1-6
1-1. AIRCRAFT DESCRIPTION. The M20
hydraulic cylinders
that
supply pressure
to
series aircraft are four-place high-perfor- the
hydraulic
disc brakes on each main
gear
mance single-engine low-wing monoplanes.
wheel. Removable
co-pilot
rudder
pedals
The all-metal airframe has a tubular-steel are standard
equipment.
The
tricycle landing
cabin frame covered with nonstructural alumi-
gear, having
a steerable nose wheel controlled
num skins, a semi-monocoque
aft
fuselage, by
rudder
pedal action,
is
fully
retractable.
and a full-cantilever laminar-flow
wing.
Con- The
wide-span trailing-edge wing flaps are
trol surfaces have
extruded-spar
construction hydraulically
actuated on 1968 models. All
with stressed skins riveted to the
spars
and 1969 and later models have
electrically operated
ribs. Dual control wheels
accompany
the con-
wing flaps.
For stabilizer trim,
the entire
ventional
flight
controls. The
pilot’s
rudder
empennage pivots
around its
attaching points.
pedals
have toe brakes linked to individual
1-2. ENGME
AIRCRAFT MODEL M20C G
M20E F M20J
ENGINE MFR
LYCOMING LYCOMMG
LYCOMMG
ENGINE MODEL O- 36 ~A1D IO- 36 O-A1A 10-360-A1B6D or
10-360-A3B6D*
NO. CYLINDERS 4 4 4
RATED HP 180 200 200
RPM
2700 2700 2700
MTN FUEL OCTANE 100 or 100 LL 100 or 100 LL 100 or 100 LL
FUEL CAPACITY
(US GAL)
’52 64 M20 F 52 M20E 64
*Effective 785 Model and earlier M20J models with SE M20-206
compliance.
REVISED 11-15-77
1-1
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MOONEY
SERVICE MAINTENANCE
MANUAL
AIRCRAFT MODEL M20C G M20E F
M20J
FUEL PRESSURE 01 O O O
MIN MAX MIN MAX MIN MAX
PSI 0. 5 8. 0 w 14 w 30 *14 "30
OIL CAPAC~rY (QTS)
8 8 8
MIN SAFE OIL LEVEL (QTS)
2 2 2
MAX OIL CONS. (6~PH) .80 .89 .89
INLET OIL TEMP DESIRED P6AX DESIRED MAX DESIRED MAX
AT AMBIENT AIR TEMP OF:
Above 600F 1800F 2450F 1800F 2450F
1800F 2450F
300
to
900F 1800F
2450F 1800F 2450F 1800F 2450F
oO to
700F 1700F 2250F 1700F 2250F 1700F 2250F
Below 100F 1600F 2100F 1600F 2100F 1600F 2100F
OIL PRESSURE MIN MAX MIN MAX MIN MAX
NORMAL PRESS.
(PSI)
60
90 60 90 60 90
START WARMUP $SI) 100 100 100
PUIAX CHT 5 F 4150F 4750F
1-3. PROPELLER
Aircraft Model M20C G M20E F M20J M20J
Optional
Prop.
Mfr. Hartzell Hartzell
McCauleg Hartzell
Type
Constant
Speed
Constant
Speed
Constant
Speed
Constant
Speed
Model HCBYK-1BF
O
HCBYK-1BF
O
B2D34C212
OIHC-CBYK-1BF~
Blade F7666A-2
O
F7666A-2
O 78CDA-4
Pitch
Angle
290 20 30 290 20 30 27. 5 .2" 29. 30 to 31. 30
(High) In. Sta. In. Sta. 30 In,Sta. O
Pitch
Angle
130 00 30 140 00
30 14. 0 .2" 14. 10 .1"
(Low) In. Sta. In. Sta. 30 In,Sta.
Diameter 74In.
Max.,
74In.
~ur.,
74In.
Max.,
73 In.
73In. Min. 73In. Min. 13 In. Min.
Governor Edo-Aire Edo-Aire
McCaulev
McCauley
(Garwin-Weston) (Garwin-CYeston) (C290D5JT17)
or Hartzell or Hartzell
O
INLET TO FUEL INJECTOR
O Prior to 1975
models,
model
designation
was
HCBYK-1B and blade
designation
was 7666A-2.
O B2D34C214 Effective 785 Model
production
and
replacement
on
prior
SjN’s.
90DHB-16E Effective 785 Model
(Low pitch:
13. 9 .2", Righ pitch:
330
.5")
0 29. 53´• 5 Effective after S. B. 198
~M20J S/N
24-1038 ON.
REV E 9-1-81
1-2
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MOONEY
SERVICE MAINTENANCE MANUAL
1-4. AIRFRAME. M20~E M20F M20G M20J
1. Dimensions:
a. Wing span.
35’ 0" 35’ 0" 35’ 0" 35’ 0"-36’1"**
b. Fuselagelength
23’ 2" 24’ 0" 24’ 0" 24’ 8"
c.
Tail
height
8’ 4" 8’ 4" 8’ 4" 8’ 4"
d. Stabilizer
span
11’ 9" 11’ ´•9" 11’ 9" 11’ 9"
2. Areas:
a. Wing(SQFT).
166. 93 166. 93 166. 93 166. 93-168, 42**
b. Ailerons (SdZ FT)
11. 4 11.4 11.4 11.4
c. Flaps (SQ FT)
17. 9 17.9 17. 9 17. 9
d. Vertical fin (SQ FT)
7. 9 7. 9 7. 9 7. 9
e. Rudder (SQ FT)
6. 25 6. 25 6. 25 6. 25
f. Horisontal stabilizer (SQ FT)......
21.5 21.5 21.5 21.5
g.
Elevators (SQFT).............
12. 0 12. 0 12. 0 12. 0
3.
Weights
and
Loadings:
M20C M20E M20F M20G M20J
a. Approximate empty weight (LBS)
1525 1600 1645 1593
1700
b. Grossweight(LBS)
2575 2575 2740 2525
2740
c. Usefulload(LBS)
1050 975 1095 932
1040
d.
Wing 19ading (LBS/SQ FT)......,
15.4 15. 4 16.4 15.1
16. 4 -16.27**
e. Powerloading (LBS/HP).........
14. 3 12. 9 13. 7 14. 0
13.7
4,
Wings:
a. Airfoilatwingroot
NAC
632-
NAC
632-
NAC
632-
NAC
632-
215 215 215
215
b. Airfoilatwingtip
1-
NAC
641’
NA(3
641-
NAC
641- NAC 64
412 412 412 412
c. Mean
aerodynamic
chord (IN.
at
wing
STA 93. 83
59.18 59.18 59.18 59.18
d. Center-of-gravity range (o~ MAC)...
15 to 13.4 to 12. 4 to 13.4 to
26.8~’0 28.7Yo 28.7~’0
28.70/e
e.
Geometrictwist -1030’ -lo 30’ -10 30’
-10 30’
f. Ii~cidence angle @EG)
from
wing
STA 20, towingtip
iO 30’ 20 30’
20
30’ 20 30’
g. Dihedralangle @EG)
5O 30’
50 30’
50 30’ 50 30’
h.
Aspect
ratio
7. 338 7. 338 7. 338 7. 338
i.
Taper
ratio 1. 935 1. 935 1. 935 i. 935
5. Fuselage:
a. Cabin Dimensions:
(1) Height (IN,) 44.5 44. 5 44.5 44. 5
(2)
Width 41* 41* 41* 43.5
(3) Length ~T.)
104 114 114 114
(4)
Cabin door width (IN,)
29 29
29 29
(5)
Cabin door
height
35 35
35 35
b.
Baggage Compartment:
(i) MAXloading (LBS) 120 120 120 120
(2) Baggage
15 18. 6 18.6 18. 6
(3) Baggage
door width ~N.)
17 17 17 17
(4) Baggage
door
height
20. 5 20. 5 20. 5 20. 5
(5)
H$t rack
capacity (LBS)
10 10 10
10
c. Landing
Gear (Standard
1968
M20C, F, &G)
(1) Type
Tricycle Tricycle Tricycle
Retract- Retract- Retract-
able able able
I
Width is 43.5 Irt.
*1975 Models S/N’20-1157
On
21-1171& On
22-1224 On
1981 On M20J
Only
REV. E 9/1/81 1-3
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IMOO~VEY
SERVICE MAINIENANCE MANUAL
1-
24’
-1
T
~nrs
8’ 4"
e,
2"1~s-
1/2"
1 I
i
-f--;l
5’ 11-9/16"
Ic
M20~
11
95’
-1
1~-
9´•
1~
23’ 2"
-1
f
5
71~1
8’ 4"
2"
LL
O
9- 1/2"
-f --c(
5’
6-9/16" 1L
M20~
Figure
1-1.
mcincipal
Aircraft DimensionsM20
C,E,F
G.
1-4
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IMOONEY SERVICE
MAINTENANCE MANUAL
74" ~\8’4
*73’
5’11-9/16
I
i-´•´•
I9"-------~1
I,
1981 i On Model´•
-1
Figure
1-2.
Principal
Aircraft Dimensions M20 J.
Optional
Hartzell IIC-C2YK-1BF
propeller
with
F7666A-3Q blade.
1-4 AIRFRAME (continued)
M20C E M20F MZOG
M20J
(2) Operation
Manual Manual Manual
N/A
(3) Wheeltrack(FT)
9’ 3/4" 9’
3/4" 9’ 3/4"
(4)
Wheelbase
(FT) 5’ 6 9j16 5’ 11 9~’16" 5’ 11 9/16"
(5)
Tire size--nose (9-pig rating)....’’’ 5: 00 x 5 5:00 x 5 5:00 x 5
(6)
Tire size--main
(6-ply rating)
6: 00 x 6 6: 00 x 6 6: 00 x 6
(7)
Tire
pressure--nose
CPSI) 30 49 49
(8)
Tire
pressure--main (PSI) 30 30 30
N/A
d.
Electrical Tanrlinp Gear (Optional
1968
Models;
Standard 1969
on, C,E,F,C, &J):
(1) Type. Tricycle Tricycle Tricycle Tricydle
Retract- Retract- Retract- Retract-
able able able able
REV E 9-1-81
1-5
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MoonrEv
SERVICE
MAINTENANCE
MANUAL
1-4 AIRFRAME (continued) M20C E M20F M20G
M20j
(2) Operation Electrical Electrical Electrical
Electrical
(3) Wheeltrack(FT) 9’
3/4" 9’
3/4" 9’
3/4" 91
3/4"
(4) wheelbase
(FT) 5’ 6 9/16 5’119/18"
5’ 11 9/16"
(5) Tire size-nose
(6´•ply rating).... 5:00 x 5 5:00 x 5 5: 00 x 5
5:00 x 5
(6)
Tire size--main
~-ply rating)
6: 00 x 6 6: 00 x 6 6: 00 x 6
6:00 x 6
(1)
Tire
pressure--nose ~SI) 30 49 49
49
(8) Tire
pressure--main (PSI) 30 30 30
30
1-5. LANDING GEAR SYSTEM. The
gear sys- WING FLAP SYSTEM (1969 and on).
tem has been modified to reduce
operating
Firing flaps on these models are
electrically ac-
forces. (Mooney
distributors stock retrofit re-
tuated and are controled
by a
spring-loaded
traction kits for models not covered in this
up-off-an switch on the
engine
control
pedestal.
manual.) The manual
system, as well, as the
The 1975 models have a three
position switch
electric
Ianding gear system,
has a ste~rable
to
pre-select flap settings.
nose wheel.
Single-disc self-adjusting hydraulic
brakes are featured on the main
gear.
The
hy-
draulic brake reservoir also furnishes fluid for
1-8. POSPTIVE CONTROL SYSTEM.
ehru
´•I The
Mooney
position lights
and a
warning
horn are standard trol
(P. C.) system
is a dual-axis
flight control
equipment. Bungee springs
that
preload
the re-
aid. P. C. is a vacuum
pump powered lateral
traction mechanism in an overcenter
position
stability control
system
that
provides a high
hold the
gear
down. An
air-pressure
actuated
degree
of roll and
yaw stability.
The
system
safety-switch
in the
pitot system or
squat
switch
is
super-imposed on the
manualflight control
systems
and consists of a
ggro
sense element
in the electrical
system prevents
electric
gear
re-
in the turn coordinator that meters vacuum
traction on takeoff until a safe
flying speed
is
pressure
to
cylinder-piston servo units. The
attained. A
gear-throttle warning
horn sounds
servos are linked to the aileron and rudder bell
when the throttle is set for 12 IN.
I´•Ig
with the cranks. Positive Control
operates
from takeoff
landing gear up.
The electric
gear
retraction
through landing
and is controlled
by a c~rtaff
system
has a manual override
system
connected
button on the
pilot s controlwheel, The button
to the
gear
actuator that
permits
manual
lowering
operates a
relay
which
supplies vacuum to the
gyro
sense element,
Depressing
the cutoff
of the
gear
in the event of an electrical malfunc-
button relieves all servo vacuum and renders
tion.
the
system inoperative. The
system can be
overpowered
with little effort and with no dam-
1-6. FLlGIlT CONTROL SYSTEMS. The dual
age
to the aircraft or P.C.
system components,
night control
systems can be
operated from
either the
pilot or
co-pilot
seat.
Allflight con-
trols are conventional in
operation, using push-
pull
tubes to link the control surfaces to the
1-9. ELECTRIC POm’ER SYSTEM. The master
control wheels and rudder
pedals.
switch and
power relay
control the electrical
power system, comprised
of a 50-AMP 12-volt
Formica
guide
blocks maintain control tube
generator or a 60-AMP la-volt
alternator,
alignment and
dampen vibration. An intercon-
a
voltage regulator,
and a 35-AMP tIR
battery.
nect
bungee spring
mechanism links the aileron Alternator
systems
have an
overvoltage pro-
and rudder
systems
to assist in control coor- tective
relay
and
overvoltage
annunciator
light.
dination. The
co-pilot‘’s rudder
pedals are All 1969 thru 1974 models have automatic annun-
removable. The trim
system
sets the stabi-
ciator
light dimming systems.
lizer
angle
of attack.
1-7. WING FLAP SYSTEM.
(1968 MODELS)
A
hand-operated hydraulic pump operates
the
Circuit
breakers or circuit breaker switches
flap actuatir~ cylinder.
A
valve, operated by
an
airfoil-shaped
control on the instrument
protect the electrical
wiring
and
equipment
from
panel,
controls the
flaps
and releases
hydraulic
Overloads. Standard electrical
equipment
pressure
at a slow rate as air
pressures
and
includes: a 250-watt
landing light, navigation
retraction
springs raise the
flaps.
The
hydraulic
lights, interior
lights, gear
and stall
warning
fluid reservoir is common to both the
flap
and
SSstems, an electrical boost
pump,
and an
brake
systems.
ele~tric
starter, electric
gear
retraction
system
with manual override.
1~B
REV E 9-1-81
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1968-1976 Mooney M20F Service & Repair Manual
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This complete Factory Mooney Executive M20F 1968-1976 Service and Maintenance Manual provides essential instructions for maintaining and servicing your Mooney Aircraft using detailed diagrams and manufacturer specifications.
The Manual covers the following Years, Models, and Serial Numbers:
- 1968 - M20F - 680001 thru 680206
- 1969 - M20F - 690001 thru 690092
- 1970 - M20F - 700001 thru 700072
- 1971 - M20F - 22-0001 thru 22-0012
- 1974 - M20F - 22-0013 thru 22-0078
- 1975 - M20F - 22-1179 thru 22-1305
- 1976 - M20F - 22-1306 thru 22-1438
This improved manual includes bookmarks, searchable text, index, and improved quality.
* INSTANT - NO WAITING
* LANGUAGE: English
* FORMAT: PDF
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* PAGES: 291
* SEARCHABLE - BOOKMARKED - INDEXED
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