Mooney M20 F User manual

MOONEY
OPERATORS MANUAL
OCTOBER 1975 ISSUE
R/rOONEYAIRCRAFT CORPORATION
KERRVILLE, TEXAS 78028
MANUAL NUMBER 121 9

.
~OON~V
OPERATORS MANUAL
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SECTION VI I
Page Date

GENERAL DESCRIPTION .......... SECTION
SYSTEMS OPERATIONS
........... SECTION
NORMAL PROCEDURES ........... SECTION
LmnATIONS .................. SECTION
EMERGENCY PROCEDURES
........ SECTION
PERFORMANCE
................ SECTION
SERVICING.
................... SECTION

This manual is issued as your operating guide for the
Mooney Executive. It
is important that you--regardless
of your previous experience-- carefully read the hand-
book from cover to cover and review
it frequently.
IMPORTANT: THIS MANUAL CONTAINS
Federal Aviation Adininistration APPROVED
LIMITATIONS AND MUST BE CARRIED IN
THE AIRCRAFT AT ALL TIMES.
All information and illustrations in this manual are
based on the latest product information available at
the time of publication approval. The right
is reserved
to make changes
at any time without notice. Every
effort has been made to present the material in
a clear
and convenient manner to enable you to use the manual
asa ready reference. Your cooperation in reporting
presentation and content recommendations
is solicited.

Mooney warrants each Aircraft (which includes
-, its accessories and equipment) sold hereunder,
to be free from defects in materialand workman-
ship under normal use and service when operated
in accordance with Mooney's operating imtruc-
tions during the period of six (6) monthsfollowing
delivery of the Aircraft to the original retail pur-
chaser or the
first user or during the period of
one
(1) year following the date of issue of the ori-
ginal airworthiness certificate for the Aircraft,
whichever period
first terminates. Mooney does
not make any warranties with respect toequipment
and accessories not manufactured by Mooney but
Mooney assigns toany owner of such Aircraft (to
the extent same may be assignable) any warranties
Mooney has received from the manufacturers of
surG equipment and accessories and will, on re-
quest, provide and execute such instruments as may
be reasonably required to evidence such assignment.
Mooney
's obligation under this warranty is limited
to repairing or replacing, at Mooney's option, any
part or parts which within the applicable warranty
period set forth above, shall be returned, trans-
portation charges prepaid, to MooneyTsplant in
Kerrville, Texas or to such other location desig-
nated by Mooney, and which upon examination, shall
disclose to Mooney's satisfaction that such part
is
defective. A new warranty period is not established
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 shallbe 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 toAircraft, equipment,
accessories, or other parts manufactured or sold by
iii

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 mainteriance ser-
vices (such
as engine tune-up, cleaning, ccntrol rig-
ging, brake and other mechanical adjustments,
maintenance inspections, etc.
) and the replacement
of service items (such as
spark,plugs, brake linings,
filters, hoses, belts, tires, etc.) made in connection
with such services or required as maintenance, nor
to nor
ma1 deterioration of soft trim and appearance
items (such
as, paint, upholstery, rubber-like items,
etc.
) due towear and exposure.
This warranty shall extend to any owner (hereafter
"Owner") of the Aircraft making claim within the
specified warranty period.
THIS WARRANTY BY MOONEY IS MADE EXPRESSLY IN
LIEU OF ANY OTHER \r!ARRANTIES EXPRESSED OR IM-
PLIED IN FACT OR BY LAW, INCLUDING ANY IMPLIED
WARRANTY OF MERCHANTABILITY OR FITNESS FOR A
PARTICULAR PURPOSE, AND IS IN LIEU OF ANY OTHER
OBLIGATION OR LIABILITY ON THE PART OF MOONEY
TO ANYONE OF ANY NATURE WHATSOEVER BY REASON OF
THE MANUFACTURE AND/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 0 FOR ANY OTHER LOSS OR
DAMAGE TO PROPERTY AND
7 OR INJURY OR DEATH TO
PERSONS OTHER THAN FOR THE PROPERTY DAMAGE TO
SUBJECT A1RCRAFT PROXIMATELY RESULTING FROM ANY
BREACH BY MOONEY OF THE AFORESTATED WARRANTY,
MOONEY NEITHER ASSUMES NOR AUTHORIZES BUYER OF
ANYONE ELSE TO ASSUME FOR IT ANY OBLIGATION OR
LIABILITY IN CONNECTION WITH THE AIRCRAFT SUB-
JECT HEREOF, OTHER THAN THOSE EXPRESSLY SET OUT
HEREIN, NO BILL OF SALE OR TRANSFER OF TITLE
TO THIS AIRCRAFT SHALL NULLIFY THE PROVISIONS
HEREOF
s

SECTION I . GENERAL DESCRIPTION
DESIGN FEATURES
AIRFRAME ........................... 1.2
POWERPLANT ....................... -1-2
FLIGHTCONTROLS ..................... 1.3
LANDING GEAR
...................... -1-3
SPECIFICATIONS OUTLINE
POWERPLANT ........................ 1-3
PROPELLER
......................... 1.4
LANDINGGEAR ....................... 1-4
FUEL&OIL .......................... 1.5
WEIGHT & LOADING .................... 1.5
BAGGAGE COMPARTMENT ............... 1.5

DESIGN FEATURES
The MOONEY EXECUTIVE is a low-wing four-place air-
craft with
a retractable gear. A four-cylinder engine powers
the aircraft for economical, high-perfor mance 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.
A torque-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 lrailing edge to enable baggage loading from
the ground.
POWER PLANT
The power plant is a four-cylinder fuel-injected engine that
develops 200 horsepower.
A 60-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 engj~espeed, regulates
the controllable-pitch constant-speed propeller. Spring
and blade aerodynamic forces decrease blade pitch.

FLIGHT CONTROLS
Conventional dual contr01s link to the control surfaces
through push-puli tubes. The copilot's rudder pedals
are removable.
The Mooney Positive Control
(P. C.) system is optional
equipment.
P. C . is a lateral stability augmentation
system that provides a high degree of roll and yaw sta-
bility, thereby enhancing the inherent wings-level flight
characteristics of the aircraft. The system works full
time from takeoff through landing but can be easily
deactivated or overpowered for flight maneuvers.
P. C .
allows you, the pilot, to devote more time tonavigation,
traffic surveillance, and communications.
WNDING GEAR
The tricycle landing gear allows maximum taxi vision
and ground maneuvering. Hydraulic disc brakes and a
steerable nose wheel aid in positive directional control
during taxiing and crosswind landings.
The landing gear
is electrically retracted. A gear
warning horn along with a green "gear down" light help
prevent inadvertent gear-up landings. The retraction
system incorporates a squat switch that prevents gear
retraction when the landing gear mechanism
is com-
pressed by the weight of the aircraft. An emergency
gear extension system
is provided.
SPECIF/CATIONS OUTLINE
POWER PLANT
TYPE: Four-cylinder , air cooled, horizontally opposed,

and fuel-injected engine with a wet-sump lubricating
system.
........
Model (Lycoming) 10-360-A1A
Rated Horsepower @ 2700 RPM ... 200 BHP
...............
Bore 5.125 IN.
..............
Stroke 4.375 IN.
.........
Displacement 361.0 CU. IN.
.........
Compression Ratio 8.7: 1
......
Fuel Injector, Bendix RSA-5-AM
....
Magnetos, Scintilla S4LN-200 Series
PROPELLER
TYPE : Constant-speed, hydraulically controlled pro-
peller with a single-acting governor.
....
Model (Hartzell) HC-~2~~-1~~/~7666~-2
..............
Diameter 74 IN.
Blade Angle
@ 30 IN. STA):
...............
Low 140+0°
..............
High 290720 -
iANDlNG GEAR
TYPE: Electrically retracted tricycle gear with rubber
shock discs, steerable nose wheel, and hydraulic disc
brakes.
........
Wheel Base 5 FT 11-9/16 IN.
.........
Wheel Tread
9 FT 3/4 IN.
Tire Size :
..............
Nose 5.00 x 5
...............
Main 6.00 x 6
Tire Pressure:
...............
Nose 49 PSI
...............
Main 30 PSI

FUEL & OIL
Usable Fuel Capacity ......... 64 GAL
Minimum Fuel Octane Rating
(aviation grade)
......... 100/130
Oil Capacity (6 QTS MIN for flight) ... 8 QTS
WEIGHT & LOADING
Gross Weight ........... 2740 LBS
Approximate Empty Weight (with
standard equipment)
...... 1640 LBS
Useful Load
............ 1100 LBS
Wing Loading
@ Gross Weight .... 16.4 PSF
Power Loading
@ Gross Weight ... 13.7 PHP
BAGGAGE COMPARTMENT
Maximum Loading (unless limited by loading
envelope)
:
Baggage Area ......... 120 LBS
Hat Rack
........... 10 LBS

FIGURE 1- 1.
DIMENSIONED THREE VIEW

SECTION II . SYSTEMS OPERATIONS
POWER PLANT
....................
ENGINE CONTROLS 2-4
.....................
IGNITION SYSTEM 2-5
.......................
FUEL SYSTEM 2-6
OIL SYSTEM
......................... 2-6
.....................
ENGINE COOLING 2-9
VACUUM SYSTEM ..................... 2-7
INSTRUMENTS
FLIGHT INSTRUMmTS ................. 2-7
FLIGHT CONTROLS
............
PRIMARY FLIGHT CONTROLS 2-8
POSITIVE CONTROL ...................2-9
TRIM CONTROLS ..................... 2-10
.................
WING FLAP CONTROLS 2-1Q
bNBING GEAR
ELECTRIC GEAR RETRACTION SYSTEM
..... 2-11
EMERGENCY GEAREXTENSIONSYSTEM
..... 2-12
BRAKE
$I. STEERING SYSTEMS ............ 2-12
ELECTRICAL POWER
ALTERNATOR & BATTERY ............... 2-12
CIRCUIT BREAKERS
................... 2-13
ANNUNCIATOR LIGHTS .................2-15
INSTRUMENT
& PLACARD LIGHTS ......... 2-16
CABIN LIGHTING
..................... 2-16
CABIN ENVIRONMENT
HEATING & VENTILATING SYSTEMS ........ 2-16
WINDSHIELD DEFROSTING SYSTEM
........ 2-17
CABIN
SEATS & SAFETY BELTS ................ 2-17
BAGGAGE & CARGO AREAS .............. 2-18

Acquiring aworking knowledge of the aircraft's controls
and equipment is one of your important first steps in de-
veloping a fully efficient operating technique. This Systems
Operations section describes location, function, and oper-
ation of systems' controls and equipment. It
is advisable
for you, the pilot, to familiarize yourself with all controls
and systems while sitting in the pilot's seat and rehearsing
the systems operations and flight procedures portions of
this manual.
FIGURE 2- 1. INSTRUMENT PANEL

Clock 23.
Airspeed Indicator 24.
Artificial Horizon 25.
Altimeter 26.
Engine Cluster Gage- 27.
Fuel Quantity, 28.
Oil Temp,
29.
Oil Pressure, 30.
Cylinder Head
Temperature, 31.
Ammeter
Landing Gear Switch 32.
Landing Gear 33.
Position Lights
34.
Outside Air 35.
Temperature Gage(Opt
.)
Magnetic Compass 36.
Pilots Check List
Annunciator Lights
-
37.
High and Low Voltage, 38.
Ram Air
Radio Pallel 39.
Vacuum Gage
Manifold Pressure and
40.
Fuel Pressure Gage 41.
Exhaust Gas Temp 42.
Circuit Breaker Panel 43.
Tachometer 44.
Cigar Lighter 45.
Ram Air Control 46.
Cowl Flap Control 47.
Flap Control Switch 48.
Mixture Control 49.
Quadrant Friction Contr01
Parking Brake Contr01
Cabin Vent Control
Cabin Heat
C ontr 01
Microphone Jack
Headset Jack
Trim Control Wheel
Fuel Tank Selector Valve
(Located on Floor)
Trim and Flap Position
Indicator
Heater and Vent Outlet
Ash Tray
Aircraft Zegistration
Instrument Panel
Light Controls
Propeller Governor
Control
Throttle
EL? Remote Swltch
Electric.al
Circuit ~r eaker/~witches
hteof Climb Indicator
Master
Switch
Directional Gyro
Not
Used
Turn Coordinator
Magneto/Starter Switch
Oinni Indicator
Omni Indicator
ADF Indicator
Radio hlicropllone

POWER PLANT
ENGINE CONTROLS
The engine control levers are centrally located, between
the pilot and co-pilot, on the engine control pedestal. The
throttle lever regulates manifold pressure. Pushing the
lever forward increases the setting; pulling the lever aft
decreases the setting.
The propeller control lever, with
its crowned knob, con-
trols engine RPMthrough the propeller governor. Push-
ing the lever forward increases engine
RPM; pulling the
lever aft decreases the setting.
ALTERNATE AIR
RAM AIR OFF
,,,, ,,,n, ,, ,,,D,
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
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
by observing the FGT gage on the pilot's instrument panel
-whileadjusting the mixture
control lever.
A large friction-lock knob
on the right side of the en-
gine control pedestal.holds
the controls in the desired
setting and prevents control
creeping during flight.
The ram air control knob,
mounted in front of the
right control wheel, al-
lows the selection of fil-
FIGURE 2-2. ENGINE tered induction air or
AIR INDUCTION SYSTEM unfiltered direct ram
air.
2-4

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 manifolM pressure by allowing engine induction
air to bypass the induction air filter. The use of ram
air
must be limited to clean, dust-free air at altitude. The
engine will operate on direct unfiltered
air when the ram air
control knob is out. The amber warning light reminds the
pilot to push the ram air control in for filtered air before
landing. Should the induction air filter clog, a springloaded
door in the induction systemwill open by induction vacuum to
allow alternate air to enter the engine.
Cylinder head temperature, oil pressure and oil temperature
gages are located above the flight instruments.
EGT, tach-
ometer, manifold pressure and fuel pressure gages areto the
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 a set of fixed retard breaker points
that aid in smoother, easier starting. A battery-powered
starting vibrator supplies a long-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.

FUEL SYSTEM
Two integral sealed sections carry the fuel in the for-
ward inboard area of the wings. Full fuel capacity
is
64 gallons. There are sump drains at the lowest point
in each tank for taking fuel samples to check for sedi-
ment contamination and condensed water accumulation.
Section
VII discusses the fuel sampling procedure.
The recessed three-position fuel selector handle on the
cabin floor setsthe selector valve below the floorboard
for LEFT tank, RIGHT tank, or the OFFposition. The
fuel selector valve assembly contains
a valve for draining
condensed water and sediment from the lowest point in
the fuel lines before the first flight of the
day and after
each refueling. Section VII discusses the selector valve
flushing procedure.
Fuel feeds from one tank at a time tothe selector valve
and through the electric fuel pump enroute tothe engine-
driven pump and the fuel injector unit. Electric fuel-
level transmitters in the tanks operate fuel gages in the
engine cluster. The master switch actuates the fuel
quantity indicator system to maintain an indication of
fuel remaining in each tank. The fuel pressure gage
registers fuel pressure in the line to the injector, Vents
in each fuel tank allow for overflow and ventilation.
OIL SYSTEM
The engine has a full-pressure wet-sump oil system with
an
8 quart capacity. The automatic bypass control valve
routes oil flow around the oil cooler when operating tem-
peratures arebelow normal or when the cooling radiator
is blocked.
The engine oil should be kept at 6 to
8 quarts. Lycoming
Service Instruction 1014 (latest revision) gives recommended
oil specifications and oil change intervals.