Mooney EXECUTIVE 21 1969 User manual

1969
MOONEY
OWNERS MANUAL
MODELS
1969-M20F
SERIAL NUMBERS
690001 & ON
JULY 1968 ISSUE
MOONEY AIRCRAFT CORPORATION
KERRVILLE, TEXAS 7{J028
MANUAL NUMBER 69·20F·OM·B

GENERAL DESCRIPTION .......... SECTION •
SYSTEMS OPERATIONS ........... SECTION •
NOR.MAL PROCEDURES ........... SECTION •
EMERGENCY PROCEDURES ........ SECTION •
LIMITATIONS .................. SECTION •
PERFORMANCE ••.....•.••..•.. SECTION •
SERVICING ••...•..•........... SECTION •

• • • • • • • • • • • • •
This manual is issued as your operating guide for the
Mooney Executive 21. 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 Administration-Delegation Option Authority
APPROVED LIMITATIONS AND MUST BE CARRIED
IN THE AffiCRAFT 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 as a ready reference. Your
cooperation in reporting presentation and content recom-
mendations is solicited .
ii
• • • •
''Mooney Aircraft Corporation ("Mooney'~ warrants each new airplane
· manufactured and sold by Mooney against defects in material and
workmanshipunder normal use and service when operated lnaccord-
ance with Mooney's operating instructions . Mooney does not make
any warranties with respect to airplane equipment and accessories
not manufactured by Mooney, but Mooneydoesagree .to assign to ' the
Buyer, on request, any warranties Mooney has received from the
manufacturers of such airolane eauioment and accessories .
"This warranty and any other expr es~ 1;r i u. 1 111.le u warranties made by
Mooney (hereifter colle c tively ca.Jled ' 'Wa i' r ~ uties ")are only enforce-
able when and if (a) Mooney receiv es 1H '(11o; •l wr itten notice of the
breach within at least m1c (I) ye ar ~ ft e r ik i.1 .i ' " of the original air-
worthiness c ertificate for lhe new ai. plane, (h) ifr e quired byMooney, ·
the defective part is re moved from the airi :l;rne, p ro perly packed and
returned to Mo oney's Ke rrville , T <:J<. as \1i: w1. u ·;:msportation and in-
surance char ges prepa id, and ( c) M t: nn;,y .i .. i. •1 mines, Irr Its sole
judgment , that the part is defective a.ad th at nli lher the part nor the
airplane has b ee n subjected to any misus <·, negle ct, negligence, acci-
dent, or impr o per installation, rep ait Gr alte ration. Mooney's ex-
clusiv e obligati on under all Warranlies sh ;,.l! b€ limited to supplying,
free of charg e (L o. b. Moone y's planl), th .: material necessary to
repair or repl ace any defec tive part , a ll la!J or , ir.stallation and other
expenses to be born e by the Buy, · r. ·Mooney shall not be liable for
11peclal, consequential 01· incident ., 1 rlr .n iag bt>.
ANY IMPLIED WARRANTY OR MERCHANTABILITY OR FITNESS
· FORA PARTICULAR PURPOSEISHEREBYEXPRESSLYEXCLUDED . ''
•

SECTION I. GENERAL DESCRIPTION
DESIGN FEATURES
AIRFRAME . . • . . . . . . . . . . • • • . . • . . . . . . . . 1-2
POWER PLANT ·. . • . . . . • . . . . . • . . . . . . . ..• 1- 2
FLIGHT CONTROLS .••..•......•....•... 1-3
LANDING GEAR .••....•.•....•........ 1-3
SPECIFICATIONS OUTLINE
POWER PLANT . . • . • . . . . . . • . . . . . . • • . . . •1-3
PROPELLER ••...................•... 1-4
LANDING GEAR •..•..•....•..•...•.... 1-4
FUEL & OIL .••••..••....••..•...•...• 1-5
WEIGHT & LOADING .••..•••....•......• 1-5
BAGGAGE COMPARTMENT .•••..•........ 1-5
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MOONEY ~ ljWPffii>W OWNERS MANUAL
DESIGN FEATURES
The MOONEY EXECUTIVE 2lis alow-wingfour-place air-
craft with a retractable 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 Nor-
mal Category aircraft.
AIRFRAME
The airframe has a welded, tubular- steel cabin structure en-
closed 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
tail cone 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 a four-cylinder fuel-injected engine that
develops 200 horsepower. A 60-ampere 12-volt alternator
supplies ample electrical power for all standard and option-
al 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.
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MOONEY ~ ljffelbJi>.#1 OWNERS MANUAL
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 system
that provides a high degree of roll and yaw stability, 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 to navigation, traffic surveillance, and com-
mu' iications.
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 retracted. A gear warning
horn along with amber and green positfon lights help prevent
inadvertent gear-up landings. The retraction system in-
corporates an airspeed-actuated switch that prevents gear
retraction until a safe airspeed is attained. An emergency
gear extension system_ is provided.
SPECIFICATIONS OUTLINE
POWER PLANT
TYPE: Four-cylinder, air cooled, horizontally opposed,
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MOONEY ~ ljWihhi>..fl' OWNERS MANUAL
and fuel-injected engine with a wet-sump lubricating sys-
tem.
Model (Lycoming) .................. I0-36(}..AlA
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-ADl
Magnetos, Scintilla ............ S4LN-200 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 ...............•........... 14° ±o
0
High . . . . . . ... . . . . . . . . . . . . . . . . . . 290 ± 20
LANDING 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 .......................... 5.00x5
Main . . . . . . . . . . . . . . . . . . . . . . . . . . 6. 00 x 6
Tire Pressure:
Nose ..................... . ..... 49 PSI
Main ....................... . ... 30 PSI
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MOONEY ~ fiU@b'i*W OWNERS MANUAL
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
~ower Loading@ Gross Weight ......... 13. 7 PHP
BAGGAGE COMPARTMENT
Maximum Loading (unless limited by loading envelope):
Baggage Area .................... 120 LBS
Hat Rack . . . . . . . . . . . . . . . . . . . . . . . .10 LBS
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MOONEY ~ljWJUhi*W OWNERS MANUAL
T
8'4"
FIGURE 1-1.
DIMENSIONED THREE VIEW
1-6

SECTION 11. SYSTEMS OPERATIONS
POWER PLANT
ENGINE CONTR,OLS ............•....... 2-4
IGNITION SYSTEM . . . . . . . . . . . . . . . . . . . . . 2- 5
FUEL SYSTEM ..........•...•........ 2-6
OIL SYSTEM ......................... 2-6
ENGINE COOLING . . . . . . . . . . . . . . . . . . . . . 2:-7
VACUUM SYSTEM ..................... 2-7
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
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 ................ 2-18
BAGGAGE & CARGO AREAS . . . . . . . . . . . . . . 2-18
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MOONEY ®l@iW»J"*..W OWNERS MANUAL
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 seat and rehearsing
the systems operations and flight procedures portions of
this manual.
FIGURE 2-1. INSTRUMENT PANEL
2-2

lfllOONEY ~ lji&lffii>..fl OWNERS MANUAL
WINDSHIELD CENTER POST
1. Magnetic Compass
LEFT PANEL
2. Pilot Checklist
3. Rocker SWitches:
Landing Light
Navigation Lights
Pitot Heat
Anticollision Light
Boost Pump
4. Gear Switch & Upper
Annunciator Lights:
Power Boost On
Gear Up
5. Altimeter
6. Instrument Panel lliumi-
nation Control
7. Annunciator Lights Press-
To-Test Switch
8. Attitude Gyro (Artificial
Horizon)
9. Airspeed Indicator
10. Rate-of-Climb Indicator
11. Turn Coordinator &
Roll-Trim Knob
12. Head Phone & Microphone
Jacks
13. Parking Brake Control
14. Ignition-starter Switch
15. Master Switch
16. EGT Gage
17. Directional Gyro
18. Lower Annunciator Lights:
Gear Down
Hi Vacuum
Lo Vacuum
Overvoltage
Middle Marker
(optional)
Outer Marker (optional)
FM/Z Marker (optional)
RADIO PANEL
19. Radios/Autopilot (optional)
RIGHT PANEL
20. Engine & Fuel Gage Group:
Fuel Quantity Gage
(L Tank)
Fuel Quantity Gage
(R Tank)
Cylinder Head Tem-
perature Gage
Oil Pressure Gage
Oil Temperature Gage
Ammeter
21. Manifold Pressure/Fuel
Pressure Gage
22. Tachometer
23. Glove Box
24. Auxiliary Equipment
Circuit Breaker Panel
25. Main Circuit Breaker
Panel
26. Cigar Lighter
27. Cabin Vent Control
28. Cabin Heat Control
29. Cowl Flap Control
CONTROL PEDESTAL
30. Wing Flap Actuating
Switch
31. Engine Control Friction
Lock
32. Throttle Control
33. Propeller Control
34. Mixture Control
CENTER CONSOLE
35. Power Boost Control
36. Cabin Heat Inl et Control
37. Center Cabin Heat Inlet
38. Stabilizer Trim P os ition
Indicator
39. Wing Flap Position
Indicat or
CABIN FLOOR
40. Stabilizer Trim Control
Wheel
41. Fuel Selector Valve
Handle & Drain (Not
Illustrated)
LEFT CONTROL WHEEL
42. Clock (Not Illustrated)
2-3

MOONEY ~ ljMWJf>:t#' OWNERS MANUAL
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, with its round knob, regulates manifold pres-
- sure. 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 are established
by observing the EGT gage on the pilot's instrument panel
-
POWEi llOOST Off
ALTERNATE AIR
--·-
FIGURE 2-2. ENGINE
Am. INDUCTION SYSTEM
Z-4
while adjusting 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 power boost air control
lever, mounted in the cen-
ter console to the left ofthe
engine control pedestal
allows the selection of fil-
tered induction air or un-
filtered direct ram air. An

MOONEY ~ ljW2M2*.fl OWNERS MANUAL
annunciator light on the instrument panel illuminates when
the power boost air control lever is set for ram air and the
landing gear is down. . When operating at full throttle, us-
ing ram air will increase the manifold 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 power boost air control lever is down. The an-
nunciator light reminds the pilot to push the engine induc-
tion air control lever upward for filtered air before landing.
Should the induction air filter clog, a spring-loaded door
in the induction system will open by induction vacuum to
allow alternate air to enter the engine.
All engine instruments except the EGT gage are grouped in
the right instrument panel. Color arcs on instrument faces
mark operating ranges. Proper interpretation of engine in-
strument readings is essential for selecting optimum con-
trol settings and for maintaining maximu_m cruise fuel eco-
nomy. Engine limitations are given in Section V.
IGNITION SYSTEM
The left magneto has a set of fixed retard breaker points
that aid in smoother, easier starting. A battery- powered
starting vibrato-r 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.
2-5

MOONEY ~ fiW21Jh9>- OWNERS MANUAL
FUEL SYSTEM
Two integral sealed sections carry the fuel in the forward
inboard area of the wings. Full fuel capacity is 64 gallons.
There are sump drains at the lowest point in each tank for
takingfuel samples to check for sediment contamination and
condensed water accumulation. Section VII discusses the
fuel sampling procedure.
An illuminated 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 valve assembly contains a valve for draining con-
densed water and sediment from the lowest point in the fuel
lines before the first flightof the day and after each refuel-
ing. Section VIl discusses the selector valve flushing pro-
cedure.
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 fuel injector unit. Electric fuel-level trans-
mitters in the tanks operate fuel gages in the engine cluster.
The master switch actuates the fuel quantity indicator sys-
tem 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 are below 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.
2-6

MOONEY ~ ljWil)hf>. OWNERS MANUAL
ENGINE COOLING
The down-drait 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 allow proper air flow on the ground and
during low-speed high-power climb. Pulling the cowl flap
control below the instrument panel, to the left of the engine
control pedestal, opens the cowl flaps.
VACUUM SYSTEM
An engine-driven vacuum pump supplies suction for the vac-
uum-operated gyroscopic flight instruments and the Mooney
Positive Control system. Air entering the vacuum-powered
instruments is filtered; hence, sluggish or erratic opera-
tion of vacuum-driven instruments may indicate that a clog-
ged vacuum filter element is preventing adequate air in-
take. The HI or LO vacuum annunciator light will illumi-
nate if vacuum is above or below limits.
INSTRUMENTS
FLIGHT INSTRUMENTS
The basic flight instruments are grouped on the shock-
mounted flight panel directly in front of the pilot's seat.
Instrument arrangement is in the standard T-grouping with
the attitude gyro at top center and the directional gyro im-
mediately below. The airspeed indicator and the altimeter
cross the "T". The vertical speed indicator and the turn
coordinator at left ofthe directional gyro complete the stand-
ard flight instrumentation.
A standard eight-day clock is mounted in the pilot's control
wheel. The magnetic compass is mounted on the windshield
post above the instrument panel. The outside air temper-
ature gage is installed in the windshield.
2·7

. MOONEY ~ MJfU4hf>W OWNERS MANUAL
There is space and lighting for four optional radio indicators
on the right side of the flight panel. A back- lighted flight
checklist is on the extreme right of the flight panel. Space
for an optional remote indicating compa · ss is at top left of
the panel. The optional marker beacon indicator lights
mount between the radio indicators at right center below
the annunicator light group.
A pitot tube, mounted on the lower surface of the left wing,
picks up airspeed indicator ram air. An optional heated
pitotprevents pitot tube icing when flying in moisture-laden
air. A drain val ve is located on the forward bottom skin of
the left wing just outboard of the wing fillet. Static ports on
each side of the tail cone supply static air pressure for the
altimeter, the airspeed indicator, and the vertical speed
indicator. A drain valve is located on the fuselage bottom
skin below the tail cone access door. An optional alternate
static pressure source valve may be installed behind the
vertical speed indicator.
A stall warning horn, mounted in the cabin head liner and
triggered by a sensing vane on the left wing leading edge,
will sound when airspeed drops to near stall speed. The
sound becomes steady as the aircraft approaches a complete
stall.
A landing gear position light in the annunciator panel shows
amber when the gear is retracted. A green annunciator light
illuminates when the gear is down-and-locked. Retarding
the throttle setting below 12 inches manifold pressure when
the gear is not in the down-and-locked position causes the
gear warning horn in the cabin headliner to sound with a
regular, intermittent tone.
FLIGHT CONTROLS
PRIMARY FLIGHT CONTROLS
Push- pull tubes with self- aligning rod end bearings actuate
the primaryflight controlsurfaces. Beveled aileron trail-
ing edges help reduce pilot control forces required for flight
2- 8

MOONEY ~ ljilMh#W OWNERS MANUAL
maneuvering. A spring-
loaded interconnect device
indirectly joins the aileron
and rudder control systems
to assist in lateral stability
during flight maneuvers.
Control surface gap seals
minimize airflow through
the hinge slots and reduce
drag.
POSITIVE CONTROL
CUTOFF VALVE BUTTON
FIGURE 2-3. P.C.
SYSTEM CONTROLS
The Mooney Positive Control (P. C.) system provides a
high degree of roll and yaw stability, thereby enhancing the
inherent wings-level flight characteristics of the aircraft.
Positive Control will holda reasonable heading over a long
period of time when the 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 pneumatically operated, two-axis auto-
matic control superimposed on the primary flight control
systems. An electro-vacuum powered turn coordinator sup-
plies pneumatic inputs to servo units that link to the aileron
and rudder control systems. Since the engine-driven vac-
uum pump is the power source, P. C. is operative when-
ever the propeller is windmilling at more than 1000 RPM.
The thumb-operated cutoff button on the left hand grip of the
pilot's control wheel is shown in Figure 2-3. Depressing
this button any time during flight will render the Positive
Control system completely inoperative for flight maneuvers
or manual flying. Whenthe cutoff valve button is released,
2-9

MOONEY ~ ljWVJhi*.#1' OWNERS MANUAL
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 sys-
tem will not damage the aircraft or the P.C. components.
The roll-trim knob on the turn coordinator, as shown in
Figure 2- 3, provides an aileron trim function through the
P .C. system. Rotating the knob trims the aircraft about
its roll axis to compensate for asymmetrical fuel and pas-
seng-er 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 for proper [unctioning.
TRIM CONTROLS
For pitch trim control, the entire empennage pivots on the
tail cone attachment points to increase or decrease the hori-
zontal stabilizer angle. This design allows flight trim es-
tablishment with minimum control surface deflection; A
pointer in a slot located on the center console indicates
stabilizer trim position. Forward rotation of the trim whee1
lowers the nose; rearward rotation raises the nose in flight.
WING FLAP CONTROLS
The flap switch on the right of the engine control pedestal
operates the electrically-actuated wide-span wing flaps.
Holding the spring-loaded switch in the down position lowers
the flaps to the desired angle of deflection. A pointer in the
center console indicates flap position. The intermediate
mark in the pointer range is the flap TAKEOFF setting.
Holding the switch in the UP position, retracts the flaps.
Simply releasing the spring-loaded switch to return to the
OFF position stops the flaps at an intermediate position dur-
ing either extension or retraction.
2-10