Mooney Ranger M20C User manual

MOONEY
OPERATORS MANUAL
MODEL
M2OC SERIAL NUMBERS
20-1 147
& ON
DECEMBER 1974 ISSUE
MOONEY AIRCRAFT CORPORATION
KERRVILLE, TEXAS
78028
m
MANUAL NUMBER 74-20C-O~-~
G#

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C. Serial Numbers
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(FAA APPROVED)
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LOG OF PAGES(CONT.)
SECTION V
(FAA APPROVED)
Page Da f e
SECTION VI
Page Date
SECTION VII
/
Page Date

GENERAL DESCRIPTION .......... SECTION
SYSTEMS OPERATIONS
........... SECTION
NORMAL PROCEDURES
........... SECTION
..................
LIMITATIONS SECTION
........
EMERGENCY PROCEDURES SECTION
................
PERFORMANCE SECTION
.................
SERVICING. .4 SECTION

This manunl isissued as your operating guide for the
Vooney IIANGEIt. It is important that you--regardless
of your previous experience-- carefully read the hand-
boolc from cover to cover and review it frequently.
IMPORTANT: THIS MANUAL CONTAINS Federal
Aviation Administration APPROVED LIMITATIONS
AND MUST I'IE CARRIED
IN THE AIRCRAFT AT
ALL, TIMES.
All ~~ilormation:incl illustrations in this manual are based
on the latest procluct information available at the time of
1)ut)lic~ttional)provnl. 'The right is reserved to ~nalce
cliangcs :it any tillic without notice. Every etfort has been
m:itle 1 o present the material in ;L clc:ir ancl convenient
ni:lnllrr to c~iablcyou to use the m;i~iii:~l :is :I ready ore-
sent:~tion:incl (*ontentrecommenclations is solic.itec1.

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 Mooneyfsoperating instruc-
tions during the period of six
(6) montlls following
delivery of the Aircraft to the original retail pur-
chaser or the first user or during the period of
one
(1) year follo~vingthe date of issue of the ori-
ginal airworthiness certificate for the Aircraft,
whichever period
fir st terminates. Mooney does
not malie ally warranties with respect toequipment
-
and accessories not manufactured by Mooney but
Mooncy assigns Gnyowner of sucll Aircraft (to
the extent same may be assignable) any warra~ities
Mooney has receivecl from the manufacturers of
such ecluipment
ancl accessories and will, on re-
quest, provide and execute such instruments as may
be reasonably required to evidence such assignment.
Mooneyfsobligztion 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 Mooney's plant 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 periocl applical~leto Aircraft solcl hereunder.
The repair or replacement of defective parts under
this warranty shall be macle by Mooney without charge
for the parts, or labor for removal, installation and/
or actual repair of defective parts.
5,
This warranty does not apply to Aircraft, equipment,
accessories, or other parts manufactured or sold by

Mooney which have been subject to misuse, negligence,
accident or improper installation, or which"1ave 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 norinal maintenance ser-
vices (such as engine tune-up, cleaning, control rig-
ging, brake and other mechanical adjustn~ents,
n~aintenanceinspections, etc. ) and the replacelllent
of service items (such as sparlr plugs, brake linings,
filters, hoses, belts, tires, etc.
) nlade in connection
with such services or required as maintenance, nor
to normal deterioration of soft trim and appearance
itellis (such as, paint, upholstery, rubber-like items,
etc. ) clue to wear anct exposure.
This warranty shall extend to any owner (hereafter
"Owner") of the Aircraft making claiill within the
specified warranty period.
THIS WARRANTY BY IdIOONEY IS tIADE EXPRESSLY IN
LIEU OF ANY OTHER P'ARRANTIES EXPRESSED OR
III-
PLIED IN FACT OR BY LAW, INCLUDING ANY IIIPLIED
WARRANTY OF MERCHANTABILITY OR FITNESS FOR A
PARTICULAR PURPOSE, AND IS IN LIEU OF ANY OTHER
OBLIGATION OR LIABILITY CPJ THE PART OF iiOONEY
TCI ANYONE OF ANY NATURE PIHATSOEVER BY REASON OF
THE IIANUFACTURE AND/OR THE SALE AND/OR THE USE
OF SUCH AIRCRAF1 , 1100NEY SHALL IN NO E'JENT BE
LIABLE TO ANY OWNER OR TO ANY OTHER PARTY OR
PARTIES FOR SPECIAL, INCIDENTAL OR CONSECUEN-
TIAL LOSS OR DAiiAGES OR FOR ANY OTHER LOSS OR
DAMAGE TO PROPERTY AND/OR INJURY OR DEATH TO
PERSONS OTHER THAN FOR THE PROPERTY DAliAGE TO
SUIIJECT AIRCRAF r PROXIMAl-ELY RESULT I I'JG FRO/, ANY
BRtACH BY MOONEY OF THE AFORESTATED l.!ARRANTYt
IIOONEY NEITHER ASSUMES NOR AUTHORIZES BU'IER OF
ANYONL ELSE TO ASSUllE 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,

SECTION I . GENERAL DESCRIPTION
DESIGN FEATURES
AIRFRAME ........................... 1. 2
POWERPLANT ........................ 1-2
FLIGHT CONTROLS
..................... 1. 3
LANDING GEAR ....................... 1. 3
SPECIFICATIONS OUTLINE
POWERPLANT ........................ 1-3
PROPELLER ......................... 1-4
LANDING GEAR ...................... -1-4
FUEL & OIL ......................... -1-5
WEIGHT & LOADING ................... -1-5
BAGGAGE COMPARTMENT .............. -1-5

MANUAL
DESIGN FEATURES
The MOONEY RANGER (M20C) is a low-wing four-
place aircraft with a retractable gear.
A four-
cylinder engine powers the aircraft for economical,
high-performance flight. Licensing 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 struc-
ture enclosed in sheet-aluminum skins. Stressed skins
rivet to main and auxiliary spars in the wing, stabilizer,
and vertical 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
fuselage. A torque-tube-driven jack screw, bolted to
the rear
tail con^ 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 powerplant is a four-cylinder air cooled engine that
develops 180 horsepower.
A 60-ampere 12-volt alterna-
tor 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 engine speed, regulates
the controllable-pitch constant-speed propeller. Spring
and blade aerodynamic forces decrease blade pitch.

FLIGHT CONTROLS
Conventional dual controls link to the control surfaces
through push-pull tubes. The co-pilot's rudder pedals
are removable.
The Mooney Positive Control (P.C.
) system is standard
equipment.
P. C. is a lateral stability augmentation sys-
tem that provides a high degree of roll and yaw stability,
thereby enhancing the inherent wings-level flight charac-
teristics 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 to navigation, traffic sur-
veillance, and communications.
LANDING GEAR
The tricycle landing gear allows maximum taxi vision and
ground maneuvering. Hydraulic disc brakes and a steer-
able nose wheel aid in positive directional control during
taxiing and crosswind landings.
The landing gear is electrically actuated. A gear warning
horn along with red and green position lights help prevent
inadvertent gear-up landings. The retraction syste11l in-
corporates
a squat switch that prevents gear retraction un-
til a safe airspeed is attained. An emergency gear exten-
sion system is provided.
SPECIFICATIONS OUTLINE
POWER PLANT
TYPE : Four-cylinder, air cooled, horizontally opposed,
$4

* x,~~~~~ e-
OPERATORS MANUAL
and carbureted engine with a wet-sump hubricating
system.
.......
Model (Lycoming). 0-360-AID
Rated Horsepower
@ 2700 RPM . . 180 BHP
.............
Bore 5.125 IN.
............
Stroke 4.375 IN.
.......
Displacement 361.0 CU. IN.
........
Compression Ratio 8. 7:l
...
Carburetor, Marvel-Schebler MA-4-5
...
Magnetos, Scintilla S4LN-200 Serie
PROPELLER
TYPE : Constant-speed, hydraulically controlled
propeller with a single-acting governor.
Model (Hartzell)
... HC-C~YK- 1B/7666 A-2
............
Diameter. 74 IN.
Blade Angle
(@ 30 IN. STA) :
............
Low 130 + 0°
............
High 2g0+20 -
LANDING GEAR
TYPE: Electrically retracted tricycle gear with rub-
ber shock discs, steerable nose wheel, and hydraulic
disc brakes.
.......
WheelBase 5FT6-9/16IN.
........
Wheel Treaci
9 FT 3/4 IN.
Tire Size
:
.............
Nose 5.00~5
............
Main. 6.00~6
Tire Pressure:
..............
Nose 30 PSI
Ma .............. 30 PSI

*
-~~ONEV OPERATORS MANUAL
FUEL & OIL
Usable Fuel Capacity .......
52 GAL
Minimum Fuel Octane Rating
(aviation grade)
........ 91/96
Oil Capacity
(6 QTS MIN for flight) . 8 QTS
WEIGHT & LOADING
Gross Weight .......... 2575 LBS
Approximate Einpty Weight
(with standard equipment)
... 1525 LBS
Useful Load
........... 1050 LBS
Wing Loading
@ Gross Weight . . 15.1 PSF
Power Loading @ Gross Weight . . 14.3 PHP
BAGGAGE COMPARTMENT
Maximum Baggage Loading (unless limited by
weight envelope) ......... 120 LBS

FIGURE 1-1 DIMENSIONED THREE VIEW
1-6

SECTION II . SYSTEMS OPERATIONS
POWER PLANT
.....................
ENGINE CONTROLS 2-4
.....................
IGNITION SYSTEM 2-5
.......................
FUEL SYSTEM 2-5
.........................
OIL SYSTEM 2-6
ENGINE COOLING
..................... 2-6
.....................
VACUUM SYSTEM 2-6
INSTRUMENTS
.................
FLIGHT INSTRUMENTS 2-7
FLIGHT CONTROLS
............
PRIMARY FLIGHT CONTROLS 2-8
POSITIVE CONTROL ................... 2-9
TRIM CONTROLS
..................... 2-10
WING FLAP CONTROLS
................. 2-10
LANDING GEAR
ELECTRIC GEAR RETRACTION SYSTEM ..... 2-11
EMERGENCY GEAR EXTENSION SYSTEM
..... 2-12
BRAKE
& STEERING SYSTEMS ............ 2-12
ELECTRICAL POWER
ALTERNATOR & BATTERY ............... 2-12
CIRCUIT BREAKERS
................... 2-13
ANNUNCLATOR 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 & SAFI~Y BELTS ................ 2-18
BAGGAGE
& CARGO AREAS .............. 2-18

Acquiring a working knowledge of the aibcraft's controls
and equipment is one of your important first steps in de-
veloping a fully efficient operating technique. This Sys-
tems Operations section describes location, function and
operation of systems' controls and equipment. It is ad-
visable 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.

- moo~evE
OPERATORS MANUAL
POWER PUNT
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 RPM through the propeller governor. Push-
ing the lever forward increases engine
RPM: pulling the
lever aft decreases RPM.
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 may be esta-
blished by observing the optional
EGT gage while adjusting
the mixture control lever.
A large friction lock on the right side of the engine control
pedestal locks the controls in the desired setting and pre-
vents creeping during flight.
The carburetor heat control knob, mounted in the subped-
estal to the right of the engine control pedestal, allows the
selection of heated induction air to prevent carburetor icing
or to melt accumulated ice in the carburetor venturi. The
engine will operate on unfiltered air when the carburetor
heat control
knob is pulled out, and dirt and foreign sub-
stances can
l-te taken into the engine causing rapid cylinder
and piston wear. Therefore, the use of carburetoi heat o13
the ground, except for testing system operation, is not
recommended.
',

-ar
~sJONE~ OPERATORS MANUAL
Clock 21.
Airspeed Indicator 22.
Artificial Horizon
23.
Altimeter 24.
Engine Cluster Gage- 25.
Fuel Quantity, 26.
Oil Temp,
2 7.
Oil Pressure, 28.
Cylinder Head
2 9.
Temperature, 30.
Ammeter 31.
Landing Gear Switch
Landing Gear 32.
Position Lights 33.
Outside Air 34.
Temperature Gage
Magnetic Conlpass
Pilots Checlr List 35.
Annunciator Lights
-
Aircraft Registration, 36.
Landing Lights
,
Fuel Pressure, 37.
High
& Low Vacuum, 38.
High and Low Voltage 39.
Radio Panel
Radio Panel 40.
Manifold Pressure
and 41.
Fuel Pressure Gage
Carburetor Air Temp 42.
Gage or Exhaust Gas 43.
Temperature Gage 44.
Circuit Breaker Panel
45.
Tachometer 46.
Cigar Lighter 47.
Not Used. 48.
Carburetor Heat Control 49.
Flap Contr01 Switch
Mixture Control
Quadrant Friction Control
Parking Brake Control
Cabin Vent Control
Cabin Heat Contr
01
Microphone Jack
Headset Jack
Trim Control Wheel
Fuel TankSelectorValve
Trim and Flap Position
Iildicator
Heater and Vent Louvers
Ash Tray
Instrument Light
Color Selector
-
Red & White
Instrument Panel
Light Controls
Propeller Governor
Control
Throttle
Landing Light Switch
Electrical
Circuit ~reaker/~witch
Rate of Climb Indicator
Electrical
Circuit ~reaker/~witches
Directional Gyro
Not Used
Turn Coordinator
Magneto/Starter Switch
Omni Indicator
Omni Indicator
ADF Indicator
Radio Microphone

-
~OONEV
OPERATORS MANUAL
All engine instruments except the EGT gage, tachom-
eter and fuel and manifold pressure gages are grouped
in the left instrument panel. Color arcs on instrument
faces mark operating ranges. Proper interpretation of
engine instrument readings
is essential for selecting
optimum contr
01 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 for-
ward 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 forward
inboard area of the wings. Full fuel capacity
is 52 gallons.
There are sump drains
at the lowest point in each tank for
taking fuel samples to check for sediment contamination
and condensed water accumulation. Section VII discusses
the fuel sampling procedure.
The .recessed three-position fuel selector handle on the
cabin floor sets the selector valve below the floorboard
for LEFT tank, RIGHT tank, or the OFF position. The
fuel selector va%e assembly contains
a valve for draining
condensed water and sediment from the lowest point in the

=.LIF
~OONEV OPERATORS MANUAL
fuel lines before the first flight of the da~and after
each refueling. Section VII discusses the selector
valve flushing procedure.
Fuel feeds from one tank at
a time to the selector valve
and through the electric fuel pump enroute to the engine-
driven pump and the carburetor 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 carburetor.
Vents in each fuel tank allow for overflow 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 recom -
mended oil specifications and oil change intervals.
ENGINE COOLING
The down-draft engine cooling system provides ground
and inflight power plant cooling. Engine baffling directs
air over and around the cylinders and out the cowl flap
openings. Cowl flap doors are fixed in
a position that
allows proper air flow on the ground and in flight.
VACUUM SYSTEM
An engine-driven vacuum pump supplies suction for the
vacuum-operated gyroscopic flight instruments and the