Mooney Ranger M20C 1968 User manual

--
OWNERS MANUAL
OPERATE THIS AIRCRAFT ONLY -
after reading
owners manual-
@ with owners manual on board
@ after you are fully qualified & understand all of
the aircraft operating characteristics& limitations

OWNERS MANUAL
SERIAL NUMBERS
680001 & ON
Neither this document (nor any amendment hereto)
nor anything contained herein shall be constrild as
an assilmptisn by Mooney Aircraft Corprat on
+a
Pennsylvania corporation, of any of the obligations
or liabilities of its predecessors. Mooney Aircraft. Inc.
or Moaney Corporation, both Texas corporations, or
as otherwise imposing on Mooney Aircraft Corporation
my of the obligations or liabilities of its predecessor@,
NOVEMBER 1967 ISSUE
MBONEY A IRCRAFT, INC.
KERRVI 6 LE, TEXAS 78028
MANUAL NUMBER 68-20C-OM-B

LIST OF REVISED PAGES ISSUED
PlNSERT LATEST REVISED PAGES -- DESTROY SUPEWEDED PAGES.
PAGE DATE OF PAGE DATE OF
NUMBER LATEST WEVlSlORl NUMBER LATEST REVlSBON
*THE ASTERISK INDICATES PAGES REVISED, ADDED, OR DE-
LETED BY THE CURRENT REVISION.
ADDITIONAL COPIES OR CURRENT REVISIONS OF THIS PUBLICATION
MAY BE PURCHASED FROM YOUR LOCAL MOONEY DISTRIBUTOR OR
DEALER.

7dIt a&
GENEME DESCRIPTION .. : ....... SECTION
SYSTEMSOPERATIONS
........... SECTION
NORWL PROCEDURES ........... SECTION
........ EMERGENCY PROCEDURES SECTI[BN
%mP%ATIONS .................. SECTION
PERPBRWNCE ................ SECTION
SERVICIONG. ................... SECTION

This manual is issued as your operating guide for the
Moomy Ranger. It is important that you--regardless of
your previous experience--carefully read the handbook
from cover to cover and review it frequently.
IMPORTANT: THIS MANUAL CONTAINS Federal
Aviation Agency-Delegation Option Authority AP-
PROVED 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 reservedto 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 as a ready reference. Your
cooperation in reporting presentation and content recom-
mendations
is solicited.
eO@BeeBseeeBe@t3
Company warrants each new airplane manufactured by it to
be free from defects in material and workmanship under
normal use and service, provided, however, that this war-
ranty
is limited to making good at Company's factory any
part or parts thereof which shall within
12 months from
date of original airworthiness certificate be returned to
Company with transportation charges prepaid, and which
upon Company's examination shall disclose to Company's
satisfaction to have been thus defective; this warranty be-
ing expressly in lieu of all other warranties expressed or
implied, and all other obligations or liabilities on the part
of Company, and Company neither assumes or authorizes
any other person to assume forit any other liability in con-
nection with the sale of its airplanes. This warranty shall
not apply to any airplane whichshall have been repaired or
altered outsideof Company's factory, whichin thejudgment
of Company affects the airplane's stability or reliability,
norwhich in theopinion of the Company has been subject to
misuse, negligence, or accident. Equipment and acces-
sories not manufactured by seller are guaranteed only to
the extent of the original manufacturer's guarantee.

SECTION I. GENERAL DESCRIPTION
DESBGN FEATURES
..........................
AIRFRAME. 1-2
........................
POWERPLANT 1-2
FLIGHTCONTROLS .................... -1-3
LANDING GEAR ....................... I- 3
SPECIFICATIONS OUTLINE
POWERPLANT ........................ 1-3
...................
PRQPELLER 00smes1-4
MNDmGGEAR ....................... 1-4
..........................
FUEL&OIL 1-5
WEIGHT
& ILOADmG .................... 1.5
............... BAGGAGECOMPARTMENT 1.5

DESIGN FEATURES
The MOONEY BANGER is a low-wing four-place air-
craft with
a retractable gear. A four-cylinder engine pow-
ersthe aircraft for economical, high-performance flight.
Licensing under Federal Aviation Agency regulations
as-
sures that your Mooney meets all 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-flowwing hasfull wrap- aroundskins
with flush riveting over the forward 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 cone bulkhead, sets the stabilizer angleof attack.
The forward-opening cabin door provides access to both
front and rear seats. The baggage compartment door
is
above thewing trailingedge to enable baggage loading from
the ground.
POWER PLANT
The power plant is a four-cylinder Lycoming engine that
develops
180 horsepower.
A 50-ampere 12-volt generator
or a 6bampere 12-volt alternator supplies ample electri-
cal power for all standard and optional equipment when the
engine
is operating at 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 Mooney Positive Control
(P.C.) system is standard
equipment,
P, C. is a lateral stability control system 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
throughlmdingbut canbe easilydeactivated oroverwwered
for flight maneuvers. P,C. allows you, the pilot, to devote
more time to navigation, traffic surveillance, and com-
munications,
The tricycle landing gear allows maximum taxi vision and
ground maneuvering. Hy&aulic disc brakes ad
a steer-
able nose wheel aid in positive directional control during
taxiing and crosswind landings.
The standard gear is manually retracted. A gear warning
horn along with red and green position lights help prevent
inadvertent gear-up landings. An electrically operated
gear
is available at extra cost. The electric gear system
incoqorates an airspeed-achated switch that prevents
gearretraction until
a safe airspeed is aeained, Amemer-
gency gear e~ensionsystem is installed with the optional
electric gear system*
SPECIFICATlONS OUTLINE
POWER PUNT
TYPE: Four-cylinder, air-cooled and horizontally opposed
engine with a wet-sump lubricating system.

.................
Model (I.jyconling). 0- 360-AID
.............
Rated Horsepower @ 2700 RPM
180
...........................
Bore 5.125 IN.
..........................
Stroke 4.375 IN.
..................
Displacement 361.0 CU. TN.
.....................
Con~pressionRatio 8.5: 1
Carburetor, Marvel- Schebler ...........
MA- 4- 5
............
Magnetos, Scintilla S4W- 2OQ Series
PROPELLER
TYPE: Constant- speed,hydraulically controlled propeller
with a single-acting governor.
..........
Model (Hartzell) HC- C2YK- 1B/7666
A- 2
Diameter .......................... .74 IN.
Blade Angle (@ 30 IN. STA):
..........................
Low. P3O 2 oO
..........................
High 29O + 2'
LANDlNG GEAR
TYPE: Manually retractedtricyclegear with rubber shock
discs, steerable nose wheel, and hydraulic disc
brakes.
Wheel Base ................... 5 FT 6-9/16 IN.
Wheel Tread .................... 9 FT 314 IN.
Tire Size:
Nose .......................... 5.00 x 5
Main .......................... 6.00 x 6
Tire Pressure:
........................... Nose 30 PSI:
Main ........................... 30 PSI

Usable Fuel Capacity ................. 5% GAL
Minimum Fuel Octane Rating (aviation grade) . 91/96
Oil Capacity
(6 QTS MIN for flight) ......... .8 QTS
Gross Weight ..................... 2575 IAN
Approximate Empty Weight (with standard
equipment)
....................... 1525 LBS
Useful Load ...................... 1050 LBS
Wing Loading
@ Gross Weight (PSF) ......... 15.4
Power Loading @ Gross Weight (PNP) ........ -14.3
BAGGAGE COMPARTMENT
Mzimum Baggage bading (unless limited by weight
envelope)
........................ 120 LBS

FIGURE 1- 1. DIMENSIONED THREE VIEW
1 -6

SECTION
SYSTEMS OPERATIONS
POWER PLANT
....................
ENGINE CONTROLS -2-4
IGNITION SYSTEM ..................... 2-4
....................... FUELSYSTEM 2-5
-
OILSYSTEM ......................... 2-5
ENGINE COOLING
..................... 2-6
VACUUMSYSTEM ..................... 2-6
INSTRUMENTS
FLIGHT INSTRUMENTS ................. 2-6
FLlGHP CONTROLS
PRImRY FLIGHT CONTROLS ............ 2-7
POSITIVE CONTROL ................... 2-7
TRIM CONTROLS ..................... 2-9
WING IFUP GONT128W ................. 2-9
LANDlNG GEAR
MANUAL GEAR RETMCTICON SYSTEM
......................... (STANDARD) 2-10
ELECTRIC GEAR RETMCTION SYSTEM
(OPTIONAL)
.........................
2-11
EMERGENCY GEAR-EXTENSION SYSTEM
(WITH ELECTRIC GEAR)
................ 2-12
BMKE & STEERING SYSTEMS ............ 2-12
ELECTRICAL POWER
GENERATOR O R AIjTERMIATOR ............
2-13
CIRCUIT BREAKERS
................... 2-13
INDICATOR LIGHTS
.................... 2-14
CABINLIGHTING ..................... 2-17
CABIN ENVIRONMENT
HEATING & VENTILATBNG SYSTEMS ........ 2-17
WmDSHIELD DEFROSTING SYSTEM ........
2-18
CABIN
SEATS & SAFETY BELTS ................ 2-19
BAGGAGE
& CARGO AREAS
.............. 2- 19

Acquiring a working 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 seatand rehearsing
the systems operations and flight procedures portions of
this manual.
FIGURE 2- 1. INSTRUMENT PANEL

WINDSHIELD CENTER POST
1. Magnetic Compass
LEFT PANEL
2. Master Switch
3. Ignition-Starter Switch
4. Gear-Up Signal Light
5. Gear-Down Signal Light
6. HELO Vacuum Warning
Lights
9. Airspeed Indicator
8. Artificial Horizon
(optional)
9. Directional Gyro
(optional)
10. Rate-of- Climb Indicator
(optional)
11. Altimeter
12. EGT Gage (optional)
13, Turn Coordinator
14, P.C. Roll-Trim Knob
RADIO PANEL
15. Radio Equipment
(optional)
RIGHT PANEL
16. Tachometer
17. Alternator Overvoltage
Warning Light
18. Manifold Pressure/Fuel
Pressure Gage
19. Engine Cluster Gage:
Fuel Quantity Gage
(L tank)
Fuel Quantity Gage
@ tank)
Ammeter
Oil Pressure Gage
Oil Temperature Gage
Cylinder Head Temp-
erature Gage
20. Cigarette Lighter
21. Circuit Breakers
22. Head Phone & Microphone
Jacks (optional)
23. Electric Fuel Pump Switch
24. Pitot Heat Switch
25. Anticollision Light Switch
26. Position Eights Switch
27. L,anding Light Switch
28. Park Brake Control
29. Cabin Neat Control
30. Cabin Vent Control
31. Wing Flap Control Knob
32. Wing Flap Pump Handle
33. Gear Lever Safety Latch
ENGINE CONTrn%.S:
34. Throttle Control
35. Mixture Control
36. Propeller Control
37. Carburetor Heat Control
d ENTER CONSOLE
38. Stabilizer Trim Position
Indicator
39. Wing Flap Position Pndi-
cator
40. Gear Retracting Lever
41. Main Cabin Heat Inlet
Handle
42. Pilot Heat Inlet Handle
43. Co-pilot Heat Inlet Handle
SIDE PANEL
44. Main-Power Circuit Breake:
Button (Alternator)
CABIN FLOOR
45. Stabilizer Trim Control
Wheel
46. Fuel Tank Selector Handle
& Drain (not shown)

PLANT
The throttle, mixture, and propeller controls are centrally
located on the instrument panel; the push-pull throttle con-
trol regulates manifold pressure.
The push-pull mixture control between the throttle and
propeller control regulates the engine fuel-air ratio. The
propeller control regulates the propeller governor which
in turn controls engine RPM. Pushing the propeller con-
trol forward increases RBM (low pitch), and pulling the
control aft decreases RPM (high pitch). Fine pitchchanges
are made
by turning the vernier knob counterclockwise to
decrease RPM and clockwise to increase RPM.
All engineinstrumentsare functionallygrouped inthe right
instrument panel. Color arcs on instrument faces mark
operating ranges. Proper interpretation of engine instru-
ment readings is essential for selecting optimum control
settingsand for
maintairaing mmimum cruisefuel economy.
Engine limitations are given in Section
V.
IGNITION SYSTEM
The left magneto has a set of fixed-retard breaker points
thataid in smoother, easier starting.
A battery-powered
startingvibrator 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 position and then pushing forward
on the key and receptacle engages the starter. Releasing
the key when the engine starts allows the switchto return
by spring action to the
BOTH position. For safety, the
starter-ignition switch must be left
at OFFwhen theengine
is not running.

FUEL SYSTEM
Two integral sealed sections carry the fuel in the forward
inboardarea of the wings. Full fuelcapacity
is 52 gallons.
There are sump drains at the lowest point in each tank for
taking fuel samplesto checkforsedimentcontamination and
condensed water accumulation. Section
VII discusses the
fuel sampling procedure.
An illuminated three-position fuel selector handle on the
cabinfloor setsthe selector valve below the floorboard for
LEFT tank,
RIGHT tank, or the OFFposition. The fuel
selector valve assembly contains a valve for draining con-
densedwater andsediment fromthe lowestpoint in the fuel
linesbeforethe first flightof the day and after each refuel-
ing. Section
VII discussesthe selector valve flushing pro-
cedure.
F~elfeeds from one tank at a time through the selector
valveand the electric fuelpumpenroute to theengine-driven
pump and the carburetor. 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 remalnhg in each tank.
The fuel pressure gage registers line pressure delivered
to the carburetor. Vents in each fuel tank allow for over-
flow and ventilation,
Olb 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 orwhen 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 specif'ications and oil change intervals.

The down-draft engine coollng system provides ground and
inflightpower plant cooling. Engine bafflingdirectsairover
and around the cylinders and out the cowl flap openings.
VACUUM S"SSPEM
An engine- drivenvacuum pump supplies suction for the op-
tional gyroscopic flight instruments and the Mooney Posi-
tive Control system. Air entering the vacuum-powered
instruments
is filtered; hence, sluggish orerratic opera-
tion of vacuum-driven instruments may indicate that
a
clogged vacuum filter element is preventing adequate air
intake. The
HI or LO indicator light will glow if vacuum
is above or below limits.
INSTRUMENTS
FLIGHT INSTRUMENTS
All primary flight instruments are grouped on the floating
shock-mounted flight panel directly in front of the pilot's
seat. Standard flight instrumentation includes theairspeed
indicator, the altimeter, and the turn coordinator. The op-
tional flight instruments are the artificial horizon, the
direction gyro, and the vertical speed indicator. The flap-
position indicator
is in the centerconsole below the instru-
ment panel.
An optional eight-day clock can be mounted in the pilot's
control wheel. The magnetic compass
is mounted on the
windshield post above the instrument panel. The outside
air temperature gage with probe is installed through the
windshield.

A pitot tube, mounted on the lower surface of the left wing,
picks up airspeed indicator ram air. An optional heated
pitot prevents pitot tube icing. Static ports on each side
of the tail conesupply static airpressure for the altimeter
and the airspeed indicator. An optional alternate static
pressure source valve may be installed.
A stall warning horn, triggered by a sensing vane on the
left wing leading edge, will sound when airspeed drops to
near stall speed. Landing gear position lights on the panel
will show red when the gear
is retracted, Reducing power
below
10 inches manifold pressure when the gear is not in
the down- and- locked position will cause the gear warning
horn to sound.
FLIGHT CONTROLS
PR%MARPI FLIGHT CONTROLS
Push-pull tubes withself-aligning rodend bearings actuate
the primary flight eo~tsolsurfaces. Beveled aileron trail-
ing edgeshelp reducepilot controlforces requiredforflight
maneuvering. Aspring- loaded interconnectdevice indirect-
ly joins the aileron and rudder controlsystems to assist in
lateral
aund directional stability during flight maneuvers.
Control surface gap strips minimize airflow sooilageat the
hinge sbtsand reduce drag. The co-pilot's rudder pedals
are removable.
POSITIVE CONTROL
The Mooney PositiveControl (B.C.) system provides a high
degree of roll and yaw stability, thereby enhancing the in-
herent wings- level flight characteristics of the aircraft.
Positive Control will hold an average heading over a long
periodof time whenthe aircraft is trimmed properly. How-
ever, without the installation of a magnetic heading lock,
P.C. will not maintain an absolute preselected heading.

The system is a pneumatic-
ally operated, two- axisau-
tomatic control installation
superimposeduponthe pri-
mary flight control sys-
tems. An electro-vacuum-
powered turn coordinator
supplies pneumatic inputs
to servo units that link to
the aileron andrudder con-
trol systems. Since the
engine-drivenvacuumpump
is the power source, B.C.
is operative whenever the FIGURE'2- 2 P.C.
propeller is windmilling SYSTEM CONTNLS
at more than 1000 RPM.
CUTOFF VALVE BUTTON
The thumb-operated cutoff button onthe left hand grip of the
pilot's control wheel
is shown in Figure 2-2. Depressing
this button any time during flight will render the Positive
Controlsystem completely inoperative forflight maneuvers
or manual flying. When the eutoff valve button isre.leased,
the aircraft will return unassisted to wings-level flight.
P.C. can be manually overriden with little effort if the sys-
tem should malfunction. Manually over-powering the sy
s-
tem will not damage the aircraft or the Be@. components.
The roll-trim knob on the turn coordinator,
as showrl in
Figure 2-2, provides an aileron trim function throughthe
P.C. system. Rotating the knob trims the aircraft about
its roll axis to compensate for asymetrical fuel and pas-
senger loadings.
The
P.C. system is installed to help alleviate pilot fatigue.
But like any other system in the aircraft,
P.C. must be
monitored frequently to check for proper functioning.
The RANGER
(M20C) is certified as a Normal Category
aircraft. No acrobatic maneuvers including spins are ap-
proved. However, if a spin is inadvertently approached or
entered, depressingthe cutoff valve button on the left hand-

grip of the pilot's control wheel will de-energize the P.C.
system while using normalspin recovery techniques. Spin
recovery can be executed from the co- pilot's side
by over-
powering the
P.G. system.
TRIM CONTROLS
For pitch trim control, the entire empennage pivots on the
tailcone attachmentpointsto increaseordecreasethe hori-
zontal stabilizer angle of attack. This design allows flight
trimestablishmentwithminimum controlsurfacedeflection.
A pointer in a slot located in the center console below the
instrument panel indicates stabilizer trim position. For-
ward rotation of the trim wheel lowers the nose; rearward
rotation raises the nose in flight.
WING FMP CONTROLS
Thewide- span flaps are hydraulically controlled by a hand-
operated pump that actuates
a hydraulic cylinder. A relief
valve releases the hydraulic pressure
at a slow rate as
FIGURE 2- 3. GEAR &
FLAP CONTROLS
springs(and/or air forces)
raise the flaps. Hydrau-
lic fluid used in the system
is common to both the flap
and brake systems. Set-
tingtheairfoil- shaped con-
trol adjacent to the pump
handle in the
DOWN posi-
tion and pumping the han-
dle lowers the flaps to the
desired angle of deflection.
Flap position
is indicated
by
a pointer in the center
console below the instru-
ment panel. The interme-
diate mark in the pointer
range
is the flap TAKEOFF
setting. The airfoil shaped