Mooney M20F Executive User manual

MOONEY
OPERATORS MANUAL
MODEL SERIAL NUMBERS
M2O F22-1306 &ON
OCTOBER 1975 ISSUE
MOONEY AIRCRAFT CORPORATION
KERRVILLE, TEXAS 78028
MANUAL NUMBER 191O

ONEY OPERATORS MANUAL
O
OM NEY WARNING: Up to 2000 feet of altitude may
be lost in a one-turn spin and recovery;
therefore stalls at low altitude are extremely
critical.
On entering a spin, the aircraft will roll, very much
like abarrel roll. The wings will be near vertical at
EXECL/77// VE about the first quarter turn of the spin. At about the
half turn point, the wings are approaching level but,
now, the nose will be very low--approaching vertical.
After one full turn has been completed, the nose will
come up somewhat, but will remain well below the
horizon. The rate of rotation during the first portion
of the spin is quite rapid and occupants of the aircraft
OPERATORS MANUAL šÏii.isbecob
esn eho Onuoe orn
e
pointing mo¡;p nearly toward the ground than the hori-
zon, as the airplane revolves and descends. As the
spin progresses, it may enter into what is referred
MODEL SERIAL NUMBERS to as aflat spin. When the spin becomes flat, the
M2O F22-1306 &ON aircraft nose comes up and remains more on the hori-
zon, with possibly some shallow up and down oscillation.
The rate of descent and rate of rotation both become
slower. An air'craft in aflat spin becomes stabilized
into autorotation and once in this condition, the controls
become ineffective and recovery is very difficult or may
not be possible.
In complying with the FAA Regulation for Normal Cate-
gory aircraft, it has been demonstrated that the air-
plane will recover after delayed stall recovery up to
OCTOBER 1975 ISSUE and including one-turn spins.
This one-turn "margin of safety" is designed to pro-
MOONEY AIRCRAFT CORPORATION vide adequate controllability when recovery from a stall
is delayed. The one-turn "margin of safety" is jeopar-
KERRV ILL E, TEX AS78028 dized if'the airplane is not recovered when the first
evidence of astall is detected.
MANUAL NUMBER 1219
3-19

ONEY PERATORS MANUAL
POSITIVE CONTROL
Positive Control will hold an approximate heading
over aperiod of tifne; however, it will not hold an
exact heading without the installation of amagnetic
heading lock. To check for aP. C. malfunction
while in flight,_ first establish amoderate bank; then,
release the controls to see if the aircraft will return
to straight wings-level flight as indicated by the arti-
ficial horizon. Repeat the procedure with a turn in
the opposite direction. Sluggish, erratic, or in-
complete bank recovery warns of a malfunction in the
P. C. system.
WARNING: Thoroughly familiarize yourself
with the flight characteristics of the aircraft
with Positive Control inoperative. This can
be done by simply holding down the cutoff
button while making turns and maneuvers.
Check the P. C. system frequently during each
flight to insure that it is functioning properly,
particularly when IFR or marginal weather
may be encountered.
In the event of a complete engine power loss, P. C.
will continue to operate as long as the propeller is
windmilling at 1000 RPM or more. Loss of vacuum
will automatically make the P. C. system inoperative.
However, the turn coordinator will continue to oper-
ate on electrical power. The turn coordinator can
be used as a flight reference if other gyro instru-
ments become inoperative.
3-20

ONEY OPERATORS MANUAL ONEY OPERATORS MANUAL
FUELMANAGEMENT
LOG OF PAGES Proper fuel management during flight will help main-
tain lateral trim and will also serve as afuel quantity
ONLY the pages listed herein are applicable check. After takeoff with both tanks full, use fuel
to Model M20 F, Serial Numbers from one tank for one hour; then, switch to the other
tank and note the time. Use all the fuel from the sec-
Page Date SECTION III ond tank. The remaining fuel endurance in the first
Title 10/20/75 Page Date tank can be calculated from the time it took to deplete
i. . . . . . . ...10/20/75 3-1 10/20/75 the second tank, less one hour. You must remember,
ii .... . . . . . . . 10/20/75 3-2 .......10/20/75 however, that this endurance calculating procedure can
iii . ...... . .. . 10/20/75 3-4 .. . .. . . . ..10/20/75 be relied upon only if power and mixture remain the
iv . ... . . .....10/20/75 3-5 ...... . .. . 10/20/75 same and an allowance is made for the extra fuel used
3-6 .. . . . . . .. . 10/20/75 during climb. For estimation purposes, consider fuel
3-7 . . . . . . . . . . 10/20/75 consumption during afull-power climb to be 40 percent
SECTION I•••••••••higher than that of best-power cruise, and 50 percent
Page Date 3-10 .. . . ...10/20/75 higher than that of best-economy cruise.
3-11..........10/20/75
1-1 . . .... . . . . 10/20/75 3-12 . . ....... . 10/20/75 CAUTION: Do not allow the engine to lose power
11-2 . . ........1 2200 3-13 ... . .. . ...10/20/75 or quit before switching friel tanks. If atank
1-4 . . . . . . . . . 10/20/75 3-1 .. . . ......2runs dry and the engine quits, retard the throttle
1-5 . . . . . . . . . . 10/20/75 3-16 10/20/75 before restarting. Restarting with an advanced
1-6 . . . . . . . .. . . 10/20/75 3-17 . . . .. . . . . 10/20/75 throttle may cause engine overspeeding that can
3-18 .... . .....10/20/75 lead to mechanical malfunction.
SECTION II 3-19 .... .
.· .,. . . 10/20/75
3-20...........10/20/75
Page Date 3-21 ... . . . . . ..10/20/75 INFLIGHT RESTARTING
3-22..........10/20/75
2-1 . . ..... . . . 10/20/75 3-23 10/20/75
2-2 ...... . ...10/20/75 3-24 . . . . . 10/20/75 1. Propeller--HIGH RPM.
2-3 ..........10/20/75 3-25..........10/20/75
2-4 ... . .. . ...10/20/75 3-26 .. . . . .... . 10/20/75 2. Fuel Selector--Fuller tank.
2-5 ..........10/20/75
2-6 . . ... .. . . . 10/20/75 SECT ION IV 3. Mixture Control--IDLE CUTOFF.
2-7 . . ... .. . . . 10/20/75 (FAA APPROVED)
2-8 ..........10/20/75
2-9 ..........10/20/75 Page Date 4. Boost Pump--ON.
2-10..........10/20/75 4-1 ..........10/20/75
2-11 . . . . ......10/20/75 4-2 ... . . . . . ..10/20/75 5. Throttle--OPEN 1/4 travel.
2-12..........10/20/75 4-3 ..........10/20/75
2-13..........10/20/75 4-4 ..........10/20/75
2-14..........10/20/75 4-5 ..........10/20/75
2-15..........10/20/75 4-6 ..........10/20/75
2-16..........10/20/75 4-7 ..........10/20/75
2-17..........10/20/75 4-8 ..........10/20/75
2-18 ... . . .. . . . 10/20/75 4-9 . . .. . . . . ..10/20/75 3-21
4-10..........10/20/75

ONEY OPERATORS MANUAL
OONEY OPERATORS MANUAL -
6. Ignition Switch--BOTH. LOG OF PAGES (CONT.)
7. Mixture Control--Move slowly and smoothly SECTION VSECTION Vil
to FULL RICH. (FAA APPROVED)
Page Date Page Date
8. Re-establish cruise power and RPM, then lean 5-1 ····..... . 10/20/75 7-1 ........ . .10/20/75
mixture. 5-2 •• • • · ·····10/20/75 7-2 .... . . . ...10/20/75
5-3 •• • •••····10/20/75 7-3 .... . .. . . .10/20/75
LETDOWN 5-4 • • • ···· · ··10/20/75 7-4 . . .... . .. . 10/20/75
7-5 . . . . . . . .. . 10/20/75
Plan your letdown well in advance of estimated landing 7-6 ... . . . . . . .10/20/75
time. Generally, apower-on descent is most desir- SECTION VI 7-7 . . .. . . . . . .10/20/75
able. A gradual rate of descent at cruising speed per¯ Pa eD7-8 ..... . . . . .10/20/75
mits power settings sufficiently high to maintain proper 9ate 7-9 ..... . . ...10/20/75
engine temperatures and to prevent spark plug fouling. 6-1 .... . . . . . . 10/20/75 7-10 . . . . . . ... . 10/20/75
Sudden power reductions at higher airspeeds can damage 6-2 .. . . . . . .. . .10/20/75 7-11 ....... . . .10/20/75
the engine by causing it to cool too rapidly. 6-3 ... . . . . ...10/20/75 7-12 ... . . . . . . . 10/20/75
6-4 . . . . . . . .. . 10/20/75
Establish a gradual letdown by reducing power below 6100/2200
cruise while maintaining cruise airspeed throughout 6-7 . . ..... . ..10/20/75
the descent. Monitor cylinder head and oil tempera- 6-8 . . . . . . . . . .10/20/75
tures throughout descent to guard against over cooling. 6-9 . . . . . .. . ..10/20/75
Oil in the oil cooler can congeal very rapidly after a 6-10 . . . . . . . . ..10/20/75
power reduction when flying in cold weather. 6-11 ....... . ..10/20/75
6-12 ..... . . . . .10/20/75
6-13 .. . . . .. . ..10/20/75
CAUTION: Do not lower gear above 120 MPH 6-14 .. . . . . . . ..10/20/75
(104 Knots) IAS. Do not lower flaps above
125 MPH (109 Knots) IAS. Do not exceed 125
MPH (109 Knots) IAS with the flaps down or
120 MPH (104 Knots) IAS with gear down.
BEFORE-LANDING CHECK
1. Seat Belts--FASTENED.
2. Fuel Selector Handle--SET for fuller tank.
3. Electric Fuel Pump--ON.
4. Mixture Control--FULL RICH.
5. Ram Air Control--CLOSED; warning light off.
3-22

ONE_Y OPERATORS MANUAL
GENERAL DESCRIPTION . . . . . . . . . . SECTION 6. Airspeed--REDUCE to 120 MPH (104 Knots).
7. Propeller--FULL INCREASE.
8. Landing Gear--DOWN and LOCKED; green an-
nunciator light on.
SYSTEMS OPERATIONS . . . . . . . . ...SECTION 9. Flaps--As required.
10. Trim--As required.
NORMAL PROCEDURES .... . . . . ...SECTION O i r ly, you should complete the Before-Landing
Check on the downwind leg. To allow for asafe mar-
gin above stall speed throughout approach, hold air-
speed above 90 MPH (78 Knots) until the flaps are
lowered. Degree of flap deflection needed will vary
according to landing conditions, but for most landings you
LIMITATIONS .... . . . . ........ . . SECTION should lower flaps to TAKEOFF position just prior to
turning on to base leg. Extend flaps as required on
final approach to adjust for variations in wind, glide
angle, and other variables.
WARNING: The stall warning horn and the
landing gear warning horn are inoperative when
EMERGENCY PROCEDURES ...... . . SECTION the master switch is in the OFF position.
On final, trim the aircraft to fly hands-off at an
approach speed of about 80 MPH (70 Knots). As you
cross the runway end markers, reduce power to idle.
Slow the rate of descent by increasing back pressure
PERFORMANCE ....... . ... . .. . .SECTION on the control wheel until the aircraft settles on the
runway in aslightly nose-high attitude. (When high,
gusty winds prevail, or when landing crosswind,
approach at a higher airspeed.) Slowly relax back
pressure and gently lower the nose wheel to the run-
way after main gear contact so the nose gear steering
system can be used to help control landing rollout
SERVICING....................SECTION direction.
3-23

ONEY OPERATORS MANUAL ggg ...............
CAUTION: Do not allow the aircraft to touch
down in anose-low attitude or at too high an This manual is issued as your operating guide for the
airspeed. Either of these conditions will allow Mooney Executive. It is important that you--regardless
the nose wheel to contact the runway first, of your previous experience--carefully read the hand-
which may cause the aircraft to porpoise and book from cover to cover and review it frequently.
damage the gear.
Unless ashort roll is necessary, you should allow the IMPORTANT: THIS MANUAL CONTAINS
aircraft to slow to amoderate taxi speed before ap- Federal Aviation Adininistration APPROVED
plying brakes. After leaving the runway, turn off the LIMITATIONS AND MUST BE CARRIED IN
electric fuel pump, open the cowl flaps, retract the THE AIRCRAFT AT ALI TIMES.
flaps, and reset the trim to TAKEOFF. Hold taxi
power setting between 1000 and 1200 RPM to permit All information and illustrations in this manual are
uniform engine cooling• based on the latest product information available at
the time of publication approval. The right is reserved
Execute short-field landings with partial power and to make changes at any time without notice. Every
full flaps on final approach. Reduce power to idle effort has been made to present the material in aclear
during flareout, and touch down first on the main and convenient manner to enable you to use the manual
wheels. before allowing the nose wheel to make con-
tact. You may apply brakes as soon as all wheels as aready reference. Your cooperation in reporting
are firmly on the ground. For maximum braking presentation and content recommendations is solicited.
effect, raise the flaps and apply back pressure on
the control wheel as you apply brakes. Do not skid
the main wheels, as doing so will reduce braking
effectiveness and damage the tires.
AFTER LANDING
1. Wing Flaps--RETRACT.
2. Electrical Fuel Pump--OFF.
3. Cowl Flaps--OPEN.
TAX1 CHECK
1. Throttle--1000 to 1200 RPM.
2. Lighting--As required.
3. Stabilizer Trim--TAKEOFF.
3-24 i i

.. . . . . . . . . . . . . . ONEY PERATORS MANUAL
Mooney warrants each Aircraft (which includes SHUTDOWN CHECK
its accessories and equipment) sold hereunder,
to be free from defects in materialand workman- 1. Throttle--IDLE at 1000 to 1200 RPM until cy-
ship under normal use and service when operated linder head temperature starts to drop.
in accordance with Mooney's operating instruc-
tions during the period of six (6) months following 2. Cowl Flaps--OPEN.
delivery of the Aircraft to the original retail pur-
chaser or the first user or during the period of 3. Radios--OFF.
one (1) year foÈowing the date of issue of the ori- 4. Electrical Switches--OFF.
ginal airworthiness certificate for the Aircraft,
whichever period first terminates. Mooney does 5. Mixture Control--IDLE CUTOFF.
not make any warranties with respect toequipment
and accessories not manufactured by Mooney but 6. Throttle--RETARD as engine stops firing.
Mooney assigns to any owner of such Aircraft (to
the extent same may be assignable) any warranties 7. Ignition Switch--OFF when propeller stops.
Mooney has received from the manufacturers of
such equipment and accessories and will, on re- 8. Parking Brake--Set (for short-term parking).
quest, provide and execute such instruments as may
be reasonably required to evidence such assignment. 9. Trim--TAKEOFF.
Mooney's obligation under this warranty is limited
to repairing or replacing, at Mooney's option, any 10. Flaps--RETRACTED.
part or parts which within the applicable warranty 11. Master Switch--OFF.
period set forth above, shall be returned, trans-
portation charges prepaid, to Mooney's plant in 12. Control Wheel--LOCK with seat belt.
Kerrville, Texas or to such other location desig-
nated by Mooney, and which upon examination, shall 13. Overhead Air Scoop--CLOSED.
disclose to Mooney's satisfaction that such part is
defective. Anew warranty period is not established 14. Wheel Chocks and Tiedown--As required.
for parts replaced hereunder. Parts replaced here-
under are warranted for the remainder of the original
warranty period applicable to Aircraft sold hereunder.
The repair or replacement of defective parts under
this warranty shall be made by Mooney without charge
for the parts, or labor for removal, installation and/
or actual repair of defective parts.
This warranty does not apply to Air craft, equipment,
accessories, or other parts manufactured or sold by
iii3-25

Mooney which have been subject to misuse, negligence,
accident or improper installation, or which have been
repaired or altered outside of Mooney's plant in a
way which, in the opinion of Mooney, adversely
affects its performance or reliability. Further, this
warranty does not include normal maintenance ser-
vices (such as engine tune-up; cleaning, control rig-
ging, brake and other mechanical adjustments,
maintenance inspections, etc.) and the replacement
of service items (such as sparksplugs, brake linings,
filters, hoses, belts, tires, etc.) made in connection
with such services or required as maintenance, nor
to normal deterioration of soft trim and appearance
items (such as, paint, upholstery, rubber-like items,
etc.)dueto wear and exposure.
This warranty shall extend to any owner (hereafter
"Owner") of the Aircraft making claim within the
specified warranty period.
THIS WARRANTYBY MOONEY IS MADE EXPRESSLY IN
LIEU OF ANY OTHER WARRANTIES EXPRESSED OR IM-
PLIED IN FACT OR BY LAW, INCLUDING ANY IMPLIED
WARRANTYOF MERCHANTABILITY OR FITNESS FOR A
PARTICULAR PURPOSE, AND IS IN LIEU OF ANY OTHER
OBLIGATION OR LI.ABILITY ON THE PART OF MOONEY
TO ANYONE OF ANY NATURE WHATSOEVER BY REASON OF
THE MANUFACTUREAND/OR THE SALE AND/OR THE USE
OF SUCH AIRCRAFT. MOONEY SHALL IN NO EVENT BE
LIABLE TO ANY OWNER OR TO ANY OTHER PARTY OR
PARTIES FOR SPECIAL, INCIDENTAL OR CONSEQUEN-
TIAL LOSS OR DAMAGES 08 FOR ANY OTHER LOSS OR
DAMAGE TO PROPERTY AND/OR INJURY OR DEATH TO
PERSONS OTHER THAN FOR THE PROPERTY DAMAGETO
SUBJECT AIRCRAFT PROXIMATELY RESULTING FROM ANY
BREACH BY MOONEYOF THE AFORESTATED WARRANTY,
MOONEY NEITHER ASSUMES .NOR AUTHORIZES BUYER OF
ANYCNE ELSE TO ASSUME FOR IT ANY OBLI.GATION OR
LIABILITY IN CONNECTION WITH THE AIRCRAFT SUB-
JECT HEREOF, OTHER THAN THOSE EXPRESSLY SET.0UT
HEREIN. NO BILL OF SALE OR TRANSFER OF TITLE
TO THIS AIRCRAFT SHALL NULLIFY THE PROVISIONS
HEREOF.
iv

SECTION I. GENERAL DESCRIPTION
DESIGN FEATURES SECTIONS IV. &V.
AIRFRAME...........................1-2
POWERPLANT........................1-2 FAA APPROVED
FLIGHTCONTROLS.....................1-3 AIRPLANEFLIGHTMANUAL
LANDINGGEAR .......................1-3
SPECIFICATIONSOUTUNE
POWERPLANT........................1-3
PROPELLER .........................1-4 SECTION IV.
LANDINGGEAR .......................1-4 AIRCRAFT LIMITATIONS
FUEL&OIL..........................1-5 AND OPERATIONS
WEIGHT&LOADING....................1-5
BAGGAGE COMPARTMENT . . . . .. . .. . . . . ..1-5
MOONEY MODEL M20F
EXECUTIVE
MOONEY AIRCRAFT CORPORATION
SERIAL NO.:
REGISTRATION NO.:
This Manual Must Be Kept Onboard The Airplane At All Times
APPROVED BY:
CHIEF,ENGINEERING &MANUFACTURING BRANCH,
SOUTHWEST REGION,FEDERAL AVIATION ADMINISTRATION
DATE:
1-1 4-1

FAA APPROVED MOONEY M20F 1_Y
10/20/75 MOONE OPERATORSMANUAL
LOG OF REVISIONS .DESIGN FEATURES
LETTER PAGE DATE APPROVED
The MOONEY EXECUTIVE is alow-wing four-place air-
craft with aretractable gear. A four-cylinder engine powers
the aircraft for economical, high-performance flight. Li-
censing under Federal Aviation Administration regulations
assures that your Mooney meets the requirements of Normal
Category aircraft.
AIRFRAME
The airframe has a welded, tubular-steel cabin structure
enclosed in sheet-aluminum skins. Stressed skins rivet to
main and auxiliary spars in the wing, stabilizer, and ver-
tical fin. The laminar-flow wing has full wrap-around skins
with flush riveting over the forward top two thirds of the
wing area.
For pitch trim control, the empennage pivots on the aft fuse-
lage. Atorque-tube-driven jack screw, bolted to the rear
tailcone bulkhead, sets the stabilizer angle.
The forward-opening cabin door provides access to both
front and rear seats. The baggage compartment door is
above the wing trailing edge to enable baggage loading from
the ground.
POWER PLANT
The power plant is afour-cylinder fuel-injected engine that
develops 200 horsepower. A60-ampere 12-volt alternator
supplies ample electrical power for all standard and optional
equipment at all engine speeds from warmup to flight power
settings.
The hydraulic propeller governor, using oil pressure for
increasing blade pitch to control engjne speed, regulates
the controllable-pitch constant-speed propeller. Spring
and blade aerodynamic forces decrease blade pitch.
4-2 1-2

ONEY PERATORS MANUAL FAA APPROVED MOQNEY M20F
10/20/75
FLIGHT CONTROLS OPERATING LIMITATIONS
Conventional dual controls link to the control surfaces
through push-pulÎ
tubes. The copilot's rudder pedals The following limitations must be observed in the
are removable. operation of this airplane:
The Mooney Positive Control (P. C.) system is optional
equipment. P. C. is alateral stability augmentation AIRSPEED LIMITATIONS
system that provides ahigh degree of roll and yaw sta-
bility, thereby enhancing the inherent wings-level flight Never Exceed Speed. .200 MPH (174 Knots) CAS
characteristics of the aircraft. The system works full
time from takeoff through landing but can be easily Max Man. Speed ...135 MPH (117 Knots) CAS
deactivated or overpowered for flight maneuvers. P. C.
allows you, the pilot, to devote more time to navigation, MC ui ng Seaed
...175 MPH (152 Knots) CAS
traffic surveillance, and communications. Max Gear Operating
LANDING GEAR Speed ... . . . . 120 MPH (104 Knots) CAS
Max Gear Extended
The tricycle landing gear allows maximum taxi vision Speed .. . . . ..120 MPH (104 Knots) CAS
and ground maneuvering. Hydraulic disc brakes and a
steerable nose wheel aid in positive directional control Max Flap Operating
during taxiing and crosswind landings. Speed ... . . . . 125 MPH (109 Knots) CAS
The landing gear is electrically retracted. Agear
warning horn along with agreen "geardown" light help AIRSPEED INSTRUMENT MARKINGS
prevent inadvertent gear-up landings. The retraction
system incorporates asquat switch that prevents gear Radial Red Line . . .200 MPH (174 Knots) CAS
retraction when the landing gear mechanism is com- (Denotes never exceed speed which is the maxi-
pressed by the weight of the aircraft. An emergency mum safe airspeed)
gear extension system is provided. Yellow Arc ..175 to 200 MPH (152 to 174 Knots) CAS
(Denotes range of speeds in which operations
should be conducted with caution and only in
smooth air)
SPEClFICATIONSOUTLINE Green Arc. .69 to 175 MPH (60to 152 Knots) CAS
(Denotes normal operating speed range)
POWER PLANT White Arc . . 64 to 125 MPH (56 to 109 Knots)CAS
(Denotes speed range in which flaps may be
TYPE: Four-cylinder, air cooled, horizontally opposed, safely lowered)
1-3 4-3

FAA APPROVED MOONEY M20F
10/20/75 DONEY OPERATORSMANUAL
POWER PLANT and fuel-injected engine with awet-sump lubricating
Engine . . . .. . Lycoming Model IO-360-A1A system.
Model (Lycoming) . . . . . . . . IO-360-A1A
Engine limits for all Rated Horsepower @2700 RPM .. . 200 BHP
operations ....200 BHP, 2700 RPM. Bore . . . .......... . .5. 125 IN.
Stroke ..............4.375IN.
Fuel .. . . . ..100/130 octane aviation Displacement . . . ......361. O CU. IN.
gasolme. Compression Ratio ........ . 8.7:1
Fuel Injector, Bendix .. . .. . RSA-5-ADI
Propeller .....Hartzell Constant Speed Magnetos, Scintilla ... . S4LN-200 Series
Hub HC-C2YK-1BF
Blade F7666A-2
Pitch setting at 30-inch
station: High 29°+ 2° •PROPELLER
Low 14° +00 .
¯
TYPE: Constant-speed, hydraulically controlled pro-
Cowl Flaps ... . Open for takeoff, climb, and peller with asingle-acting governor.
ground operations. Open as re-
quired for continuous opera- Model (Hartzell) .. . .HC-C2YK-1BF/F7666A-2
tion to maintain cylinder head Diameter ... . . . ... . . . . . 74 IN.
temperature below 4000F. Blade Angle @30 IN. STA):
(Do not open above 150 MPH -Low . . ...... . .... . . 14°+0°
130 Knots). High ... . . . . . . . ... .
290¯20
POWER PLANT INSTRUMENTS LANDING GEAR
Tachometer TYPE: Electrically retracted tricycle gear with rubber
Radial Red Line (Rated) . . ...2700 RPM shock dises, steerable nose wheel, and hydraulic disc
Green Arc--Narrow (Rated opera- brakes.
ting range) . . ..... . 2500-2700 RPM
Green Arc--Wide (Recommended Wheel Base ........5FT 11-9/16 IN.
operating range) . . .. . 2350-2500 RPM Wheel Tread .... . . . . . 9FT 3/4 IN.
Red Arc--Wide (No continuous operation Tire Size:
in this range) ...... . 2100-2350 RPM Nose .. . .... . .. . .. . 5. 00 x5
Main............... 6.00x6
Tire Pressure:
Nose............... 49PSI
Main............... 30PSI
4-4 1·4

ONEY OPERATORS MANUAL FAA APPROVED MOONEY M20F
¯¯¯ 10/20/75
Cylinder Head Temperature
FUEL &OIL Radial Red Line (Maximum) . . .475 DEG F
Green Arc (Operating range) .300-450 DEG F
Usable Fuel Capacity ........ . 64 GAL
Minimum Fuel Octane Rating Oil Pressure
(aviation grade) .. . . . . . . . 100/130 Radial Red Line (Minimum idling) ..25 PSI
Oil Capacity (6 QTS MIN for flight) .. . 8QTS Radial Red Line (Maximuni) . . . . . 100 PSI
Green Arc (Operating range). . . 60 to 90 PSI
Yellow Arc (Idling range) . . . . 25 to 60 PSI
WEIGHT & LOADING Yellow Arc (Starting &
Gross Weight .......... . 2740 LBS warm-up range) .. . . . . . 90 to 100 PSI
Approximate Empty Weight (with
standard equipment) . . . . . .1640 LBS Fuel Pressure
Useful Load ....... . . .. . 1100 LBS Radial Red Line (Minimum) . . . . . 14 PSI
Wing Loading @Gross Weight ... . 16.4 PSF Radial Red Line (Maximum) .. . . . 30 PSI
Power Loading @Gross Weight .. . 13. 7PHP Green Arc (Operating range) ..14 to 30 PSI
BAGGAGE COMPARTMENT Oil Temperature
Radial Red Line (Maximuin) . . .245 DEG F
Maximum Loading (unless limited by loading Green Arc (Operating range) 100to 225 DEG F
envelope):
Baggage Area .. . . . . . . . 120 LBS
Hat Rack .. . .. . ... . . 10 LBS OTHER INSTRUMENTS
AND MARKINGS
Vacuum Gage
Normal operating range (Green Arc) 4.5 to 5.0 Hg
The following equipment is vacuum operated:
1. Artificial horizon (if installed)
2. Directional gyro (if installed)
3. Turn coordinator (will operate electrically)
4. Positive control system.
1-5 4-5

FAA APPROVED MOONEY M20F
10/20/75 nŒY OPERATORS MANUAL
WEIGHT &CENTER-OF-GRAVITY LIMITS
MaximumWeight................ 2740LBS
Center of Gravity (Gear Down): .-4-
Most Forward 41. OIN. (Fus. Sta. in IN.)
13.4%MAC................... 2250LBS t#
Intermediate Forward 41.8 IN. (Fus. Sta. 1/2
inIN.)14.7%MAC............. 2470LBS UN/16"
Forward Gross 45. OIN. (Fus. Sta. in IN.)·
20.1%MAC..................2740LBS
Rear Gross 50. IIN. (Fus. Sta. in IN.)
28.7%MAC.................. 2740LBS
MAC (IN. at Wing Sta. 93.83). .. . .. ..59.18
Datum (station zero) is 5inches aft of the center line
of the nose gear attaching bolts, and 33 inches IO
forward of the wing leading edge at wing station
59. 25.
MANEUVERS
This airplane must be operated as a Normal Category
airplane. Aerobatic maneuvers, including spins,
are not approved.
NOTE: Maneuvers involving approach to stal-
ling angle or full application of elevator, rud-
der, or aileron should be confined to speeds
below maneuvering speed. No snap maneuvers
or whip stalls are approved at any speed. No __.
inverted maneuvers are approved.
9 3/4" i
FIGURE 1-1. DIMENSIONED THREE VlEW
4-6 1-6

FAA APPROVED MOONEY M20F
SECTION 11. SYSTEMSOPERATIONS 10/20/75
POWER PLANT FLIGHT LOAD FACTORS
ENGINE CONTROLS. ... . . . . . .......... . 2-4 Maximum Positive Load Factor,
IGNITIONSYSTEM.....................2-5 FlapsUp .........................3.8
FUELSYSTEM ....................... 2-6 Maximum Positive Load Factor,
OILSYSTEM...................······ 2-6 FlapsDown (330) ....... .......... .. .2.0
ENGNE COOLNG ... . ..... . . . ... . .....2-7 Maximum Negative Load Factor
VACUUMSYSTEM.....................2-7 FlapsUp ...............'..........1.5
INSTRUMENTS
FLIGHT INSTRUMENTS ...... . . .. . .. . ...2-7 TYPES OF OPERATION
FLIGHT CONTROLS Do not operate in known icing conditions.
PRIMARY FLIGHT CONTROLS . . .... . . . . . .2-8 This is aNormal Category aircraft approved for
POSITIVE CONTROL . . .. ... . . . . . ..... . .2-9 VFR/IFR, day or night operations, provided the
TRIM CONTROLS . . .. . .... . . . . . .. . ....2-10 following instruments and equipment are installed
WNG FLAP CONTROLS ....... . . . . . . . .. . 2-10 and operating properly.
LANDING GEAR
ELECTRIC GEAR RETRACTION SYSTEM .... . 2-11 REQUIRED EQUlPMENT
EMERGENCY GEAR EXTENSION SYSTEM .....2-12
BRAKE &STEEREG SYSTEMS ... . . . . .. . . . 2-12 VISUAL FLIGHT RULES -DAY
ELECTRICAL
POWER Airspeed indicator
ALTERNATOR &BATTERY. . . . . . ...... . ..2-12
CIRCUIT BREAKERS ..... . ... . .... . ....2-13 Altimeter
ANNUNCIATOR LIGHTS ...... . .... . . . . . .2-15 Magnetic direction indicator (Mag compass)
INSTRUMENT &PLACARD LIGHTS ......... 2-16 Tachometer
CABIN LIGHTING . . . . ..... . ... . ... . . . .2-16 Manifold pressure gage
CABIN ENVIRONMENT Oil pressure gage
HEATNG &VENTILATNG SYSTEMS ...... . . 2-16 Oil temperature gage
WNDSHIELD DEFROSTNG SYSTEM .... . .. . 2-19 Cylinder head temperature gage
Fuel quantity gage for each tank
CABIN Fuel pressure gage
SEATS &SAFETY BELTS . . . . . . . . . . . . . . . .2-17 Landing gear position indicator
BAGGAGE&CARGOAREAS .............. 2-18

FAA0/ /7R5OVED MOONEY M20F OPERATORS MANUAL
Gear warning horn Acquiring aworking knowledge of the aircraft's controls
Stall warning system
Master switch and equipment is one of your important first steps in de-
veloping a fully efficient operating technique. This Systems
Battery and alternator
. . Operations section describes location, function, and oper-
Circuit breakers and fuses ation of systems' controls and equipment. It is advisable
Seat belts for all occupants for you, the pilot, to familiarize yourself with all controls
Emergency locator transmitter and systems while sitting in the pilot's seat and rehearsing
the systems operations and flight procedures portions of
VISUAL FLIGHT RULES --- NIGHT this manual.
All equipment and instruments specified for
VFR --- day
Position lights
Electric landing light (if used for hire)
Instrument lights e
ANntST EonN
FIGHT RULES
46 6
11 13 14
All equipment and instruments specified for
VFR --- night
Gyroscopic rate-of-turn indicator
Bank indicator °--- 0oooo
Sensitive altimeter adjustable for barometric
pressure
Clock with sweep second hand a22
Artificial horizon
Directional gyro
Adequate power source for each gyro instrument
Two-way radio communications system and navi-
gational equipment appropriate to the ground faci-
lities to be used
NOTE: Caution should be exercised when in-
stalled communications equipment interrupts
the navigation signal during transmissions.
FIGURE 2-1. INSTRUMENT PANEL
4-8 2-2

FAA APPROVED MOONEY M20F
¯MOONEY OPERATORS MANUAL 10/20/75
1. Clock 23. Quadrant Friction Controi PERFORMANCEINFORMATION
2. Airspeed Indicator 24. Parking Brake Control
3. Artificial Horizon .25. Cabin Vent Control Up to 220-foot altitude loss may occur during stalls
4. Altimeter 26. Cabin Heat Control at maximum weight.
5. Engine Cluster Gage- 27. Microphone Jack
Fuel Quantity, 28. Headset Jack
Oil Temp, 29. Trim Control Wheel OPERATINGPROCEDURES
Oil Pressure, 30. Fuel Tank Selector Valve
Cylinder Head (Located on Floor)
Temperature, 31. Trim and Flap Position NORMAL
Ammeter Indicator
6. Landing Gear Switch 32. Heater and Vent Outlet This airplane must be operated as a Normal Cate-
7. Landing Gear 33. Ash Tray gory airplane in compliance with the operating lim-
Position Lights 34. Aircraft Registration itations stated in the form of placards, markings,
8. Outside Air 35. Instrument Panel and manuals. No acrobatic maneuvers, including
Temperature Gage(Opt.) Light Controls spins, are approved.
9. Magnetic Compass 36. Propeller Governor
10. Pilots Check List Control Circuit breakers are located on the right hand side
11. Annunciator Lights -37 Throttle of the co-pilot's instrument panel. The alter-
High and Low Voltage nator circuit breaker is on the circuit breaker panel.
"38. ELT Remote Switch
Ram Air Circuit breakers are push-pull or push-to-reset type.
39. Electrical
12. Radio Panel
13. Vacuum Gage Circuit Breaker/Switches Retract flaps after landing.
14. Manifold Pressure and 40. Rate of Climb Indicator
Fuel Pressure Gage 41. Master Switch Turn ram air off for takeoff, landing, or any
15. Exhaust Gas Temp 42. Directional Gyro time when operating in dusty conditions.
16. Circuit Breaker Panel 43. Not Used
17. Tachometer 44. Turn Coordinator All warning devices are inoperative when the master
18. Cigar Lighter 45. Magneto/Starter Switch ,switch is off.
19. Ram Air Control 46. Omni Indicator
20. Cowl Flap Control 47. Omni Indicator Do not open storm window above 150 MPH (130 Knots).
21. Flap Control Switch 48. ADF Indicator
22. Mixture Control 49. Radio Microphone A horn emitting a steady tone warns of approaching
stall.
Ahorn emitting an intermittent tone warns of are-
tracted landing gear when power is reduced below
about 12 IN. Hg manifold pressure.
2-3 4-9

FAA APPROVED MOONEY M20F
10/20/75 _N_ OPERATORS MANUAL
The PC system cutoff switch in the left hand grip
of the pilot's control wheel, deactivates PC when
squeezed. POWER PLANT
The roll-trim knob on the turn coordinator provides ENGINE CONTROLS
acommand trim function. Rotation in aclockwise
direction trims right; counterclockwise rotation trims The engine control levers are centrally located, between
left. the pilot and co-pilot, on the engine control pedestal. The
throttle lever regulates manifold pressure. Pushing the
To preclude fuel starvation, avoid extreme sus- lever forward increases the setting; pulling the lever aft
tained side slips toward the tank in use when that decreases the setting.
tank contains less than 48 pounds of fuel. The propeller control lever, with its crowned knob, con-
trols engine RPM through the propeller governor. Push-
EMERGENCY ing the lever forward increases engine RPM; pulling the
Emergency procedures are contained in the Emer- lever aft decreases the setting.
gency Procedures section on the next page. The mixture control lever, with its red hexagon knob, es-
tablishes the fuel-air ratio (mixture). Pushing the lever
full forward sets the mixture to full-rich, pulling the lever
LOADING INFORMATION aft leans the mixture, and pulling the lever to its maximum
aft travel position closes the idle cutoff valve, shutting
down the engine. Precise mixture settings are established
It is the responsibility of the airplane owner and by observing the EGT gage on the pilot's instrument panel
the pilot to insure that the airplane is properly load- while adjusting the mixture
ed. Load the aircraft in accordance with the loading control lever.
schedule. O
WARNING: See Weight &Balance Record Alarge friction-lock knob
for loading schedule. 'RN =On the right side of the en-
,y. gine control pedestal.holds
The front seat positions can adversely affect CG the controls in the desired
limitations at the most rearward loading. Allow- RAM AIRON Setting and prevents control
able baggage weight may be dictated by seat posi- creeping during flight.
tions. Maximum allowable weight in the baggage
compartment is 120 pounds. The ram air control knob,
WARNING: Maximum allowable weight in RAMAIROFF ALTERNATEAIR MOunted in front of the
the hatrack is 10 pounds. Carry only soft '*"'"""""--' right control wheel, al-
objects in the hatrack. lows the selection of fil-
FIGURE 2-2. ENGINE tered induction air or
AIR INDUCTION SYSTEM unfiltered direct ram air.
2-4
4-10

Y_ROPERATORS MANUAL FAA APPROVED
10/20/75
An amber warning light above the radio panel illuminates
when the ram air control is not closed and the landing gear
is down. When operating at full throttle, using ram air will
increase the manifolti pressure by allowing engine induction
air to bypass the induction air filter. The use of ram air SECTION V
must be limited to clean, dust-free air at altitude. The
engine will operate on direct unfiltered air when the ram air EMERGENCY OPERATION
control knob is out. The amber warning light reminds the AND PROCEDURES
pilot to push the ram air control in for filtered air before
landing. Should the induction air filter clog, aspringloaded
door in the induction system will open by induction vacuum to
allow alternate air to enter the engine.
Cylinder head temperature, oil pres'sure and oil temperature MOONEY MODEL M20F
gages are located above the flight instruments. EGT, tach- EXECUTIVE
ometer, manifold pressure and fuel pressure gages are to the MOONEY AIRCRAFT CORPORATION
right of the radio panel. Color arcs on instrument faces mark
operating ranges. Proper interpretation of engine instrument
readings is essential for selecting optimum control settings
and for maintaining maximum cruise fuel economy. Engine
limitations are given in Section IV.
IGNITION SYSTEM
The left magneto has aset of fixed retard breaker points
that aid in smoother, easier starting. A battery-powered
starting vibrator supplies along-duration, boosted spark.
The starter-ignition switch, mounted on the left of the in-
strument panel, combines both ignition and starting func-
tions. Turning the ignition key clockwise through R, L,
and BOTH to the START MAG position and then pushing
forward on the key and receptacle engages the starter. Re-
leasing the key when the engine starts allows the switch to
return by spring action to the BOTH position. For safety,
the starter-ignition switch must be left at OFF when the
engine is not running.
2-5 51