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Mooney M20J 1978 Pilot Operating Handbook

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This Manual is NOT specific to your
aircraft. It is provided as a reference
tool only.
Refer to the Pilot's Operating
Handbook, provided with your
aircraft at delivery, for data specific
to your aircraft.
Copyright 2005 Mooney Airplane Company, Inc.
All Rights Reserved

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  • Page 1 This Manual is NOT specific to your aircraft. It is provided as a reference tool only. Refer to the Pilot's Operating Handbook, provided with your aircraft at delivery, for data specific to your aircraft. Copyright 2005 Mooney Airplane Company, Inc. All Rights Reserved...
  • Page 7 CONGRATULATIONS WELCOME T O MOBNEYvS NEW DIMENSION IN SPEED MOONEY HAS PLACED YOU IN A N ELITE AND DISTINC- TIVE CLASS OF AIRCRAFT OWNERS. WE HOPE YOU FIND YOUR NEW MOONEY A UNIQUE FLYING EXPERIENCE, WHETHER FOR BUSINESS OR P L E A S m E , Mooney 201, Model M20J.
  • Page 9 TABLE OF CONTENTS SECTION ........EMERGENCY PROCEDURES .
  • Page 11 SECTION I. TABLE OF CONTENTS TITLE PAGE STANDARD MRPLANE WEIGHTS DIMENSIONS, ME TEOROLWICAL TERMINO FLIGHT P U N N N G T E R m O WEIGHT & B A U N C E T E R m O ISSUED 11-15-77...
  • Page 12 THREE m E W ISSUED f 1- 15- 77...
  • Page 13 Mooney A i r c r d t Corporation, used in this Pilot's 9 e r a t i q andbook.
  • Page 14 5.3125 in. Bore 361.0 Compression Ratio Fuel Injector, Bend& Magnetos, Bendix PROPELLER Constant- speed, hy&aulically controlled pro- T Y P E peller with Diameter 73 in, miw. Number of Blades Blade Angle 30 In. Sa. Nigh Usable Fuel Capacity Minimum Fuel Octane Rali2x Blue Capacity (6 QTS MIN for f l g h t )
  • Page 15 STANDARD AIRPLANE WEIGIlTS (See page 6- 4) B a s i c Empty Weight BAGGAGE SPACE' AND ENTRY DIMENSIONS Baggage Area (Max.) Hal Rack (2.6 Baggage Door Opening Above Ground (Sill) 46" Entry Width 20.5" SPECIFIC LOADINGS 1 6 . 4 PSP Power Loading @ C .
  • Page 16 Maneuvering Speed i s the maximuin speed at which application of full available a e r odynamic control will not o v e r s t r e s s the a i r p l a n e . Maximum Flap Extended Speed i s t h e highest speed p e r m i s s i b l e with wing flaps in a p r e- s c r i b e d extended position.
  • Page 17 is the free a i r static temperature, obtained either from meteorological sources. It expressed 29.92 gradient from s e a level t o the aanfteads at which the temperature is -56.5oC is The number actually read from an alti- Indicated meter when barometric...
  • Page 18 R P M Manifold R e a e u r e is a presswe measured Demon- takeoff and landing wae actmlly is the acceleration due t o gravity. the altitude where the climbing a l l horizontal distances are measured l o r A location along the airplane fuselage the reference datum* The horizontal distance from the reference...
  • Page 19 C . G . The extreme center of gravity locations within L i m i t s which the airplane must be operated a t a given weight. Center of The point a t which a n airplane would balance if Gravity suspended.
  • Page 21 TABLE OF C O N T E W S TITLE INTRODUCTION AIRSPEED POWER P U N T LIMITATIONS POWER P L A N T INSTRUMENT MARmNGS WEIGHT UM%TS CENTER OF GRAmTU UMITS 2- 7 MANEUVER W M E S A TI O N LIMT~S 2- 9 2- 9...
  • Page 22 Calibration &ata shown in Section 5 with the normal being used, ample margins sllould be observed to tween the ~aormal and alternate static sources a.s shown in Section 5. a s Mooney M20J0 Mooney M20J F A A APPROVED Airplane Flight Manual...
  • Page 23 Airspeed limitations and their operatiom% significance a r e shown in Figure This calibration assumes z e r o instrument e r r o r . Do not exceed this speed Do not make full or Do not exceed FIGURE 2- 1 . AIRSPEED L%M%TATIONS Airplane Flight Manual 2 - 3...
  • Page 24 Airspeed indicat or mar kings, their color code and operational Green A r c and only- in _..---*- FIGURE 2- 2. A R S P E E D I m I G A T O R MARKINGS FAA APPROVED 2 - 4...
  • Page 25 POWER PLANT L i M l T A T l O N S Engine Manufacturer: Avco Lycoming. Engine Model Number: 10-360-A3B6D Engine Operating Limits for Takeoff and Continuous Operations : Maximum Engine Speed: 2700 R P M . Maximum Cylinder Head Temperature: ( 4 ~ 5 ' ~ ) . Maximum Oil Temperature: ( 2 4 ~ ~ ~ ) .
  • Page 26 Radial Wed Line (Maximum) 60 t o 90 PSI Green Arc (Operating range) Yellow Arc (Idling range) Arc (Starting warm- up range) Fuel Pressure 30 PSI Radial Red Llrae (Maxianurn) Radial Red Line (Maximum) Mooney M205 FAA APPROVED 9-29-82...
  • Page 27 Landing) 2740 LBS. Compartment 120 Lbs. M a x i m u m Weight i n Haln.aclc 10 Lbs. Fus. Sta. 119. C E N T E R OF G R A V I T Y L l M l T S ( G E A R DOWN) Most Forward 41.0 IN.
  • Page 28 48 Ibs. (8 gallons) of 290-foot above 190 M P H IAS (I64 K'TS). Above 190 M P H rapid throttle seduction may r e - sult in momentary propeller Mooney M20J F A A APPROVED REVISION A...
  • Page 29 Flaps m w n (33OI0 ....operate Do not in h o w n i c i ~ conditions, when quipped in accordance with FAR 91, F U E L LIMITATIONS 93.25 U.
  • Page 30 DECALS PLACARDS INTERIOR: The following placards must be installed inside the cabin the locations specified. OPERATIONAL LlMl"$T!$sONS S AIRPLANE MUST BE O P RA TED A S IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS. NO AEROBATIC MANEUVERS, INCLUDING SPINS, AWE APPRQVED.
  • Page 31 On Lower Left Instrument PULL FOR TURN OFF STROBE LTS ALTERNATE WHEN TAXIING NEAR OTHER OR WHEN N O T OPEN FLYING I N FOG OR IN CLOUDS S T 0 POSITION LTS MUST BE USED FOR A L L NIGHT OPERATIONS. 2 IN CASE OF FIRE TURN OFF CABIN HEAT.
  • Page 32 Valve Door mndle Baggage Door mndle FAA APPROVED...
  • Page 33 must The following placards on the be installed On mfn Gear Nose Gear Boor Fuel Tank BLUE) MIN, 86T. On Leading Edge of Horizontal and Trailing Edge Sides of Rudder...
  • Page 34 of Right Inboard End Flap of Wing Underside Airplane Flight Manual ISSUED 11-15-,7'%...
  • Page 36 This section provides t h e recommended procedures t o follow during a d v e r s e flight conditions. The infor ma- definite plan of action for coping with the most probable emergency situations which could occur in t h e operation A s it is not possible t o have a procedure for a l l types of is the pilot's resgonsi- emergencies that may occur,...
  • Page 37 ANNUNCIATOR PANEL WARNING LIGHTS Fault Remedy Warning Lf ght Gear Unsafe retracted position. Refer t o " Failure of landing g e a r t o extend electrically" page 3-8 or "Fail~are procedure of landing gear to retract after take- off"...
  • Page 38 Mixture F u e l Selector Valve Off Master Switch Extinguish with F i r e Extinguisher O F F Throttle C losed (Full Aft) Cabin Ventilation Heating Controls CLOSED (Control Forward) DOWN OR U P , depending on t e r r a i n . EXTEND.
  • Page 39 Braking- Maximum. Fuel Selector OFF. Master and Magneto/%art Switch-OFF. AND DURING CLIMB Select Other Tank. CHECK ON BOTH. If emgine does not $e8&2irt9 proceed t o POWER OFF landing. LOSS POWER I N Immediately upon noting any condition Chat could time and altitude permit.

  • Page 40: Power Off Landing

    Mixture Control Move slowly and smoothly Re-establish cruise power and R P M then lean indicated by the chart below, thew proceed to POWER OFF LA6dDING. MODEL POWER OFF LANDING Emergency Locator Transmitter Required, (if installed) Fuel Selector Valve PULL DOWN (33'3 Down or Up depewdilg on terrain.
  • Page 41 8%. MPH (7%. Master Switch OFF, P r i o r t o Landing. Up t o 2000 feet of altitude may be lost in one t u r n spin and recovery; t h e r e f o r e , s t a l l s a t low altitude a r e extremely The best spin recovery technique is t o avoid flight conditions Low speed flight n e a r s t a l l should be approached with caution and excessive flight control move--...
  • Page 42 T O EXTEND ELECTRICALLY 2. Landing Gear Actmtor GircGt Breaker PULL Gear Switch 4. lvfanm% Gear E&en&on Mechnisaaa LEVER BACK. Slowly u%l 5 . 1 c m f t o rotate clutch mechanism and allow it t s e w a g e drive e M t . 5.
  • Page 43 UNLATCHED D O O R I N FLIGHT the cabin door is not locked it may come unlatched i n flight. This may occur during or just after take- off. The door will t r a i l in a position approximately 3 inches open, but the flight c h a r a c t e r i s t i c s of the airplane will not be affected.
  • Page 44 ing t o r e s e t the breaker not m o r e than one t i m e . If t h i s f a i l s , pull the alternator field b r e a k e r , t u r n off a l l non-essential e l e c t r i c a l equipment and t e r m i n a t e the flight a s soon a s practical.
  • Page 45 FAILURE OF LANDING GEAR TO RETRACT TAKEOFF AFTER The following procedure applies t o all aircraft modified with the airspeed safety override system with the "BY PASS" switch (S/W 24-0238 and above) and all aircraft prior with the mechani- retraction "BY PASS" switch in accor- In the event that the gear fails t o retract when the landing gear control switch is placed i n the "UP"...
  • Page 47 SECTION TABLE OF CONTENTS PAGE P R E F L I G H T INSPECTION BEFORE STARTING CHECK STARTING ENGINE BEFORE T A K E O F F TAKEOFF .., e . 9 ~ 0 s 4 - 7 OBSTACLE CLEARANCE NORMAL 4- 9...
  • Page 48 FIGURE Gear Switch--NWN. Master Switch--ON t o check ot~tside lights, five seconds, Tail Tiedown- -REMOVE. points. Remove a%% ice, snow, o r f r o s t . Instrument Static Port--mOBSTR%TCTED.
  • Page 49 Wing Skins--CHECK. F l a p and Attach Points--CHECK. Aileron and Attach Points- -CHECK Wing Tip Strobe and Navigation Light--CHECK. Remove a l l i c e , snow, or f r o s t . Left Wing Ideading Edge--CHECK. Fuel Tank--CHECK QUANTITY: neck.
  • Page 50 OFF. CHECK. Alternate Static Air Control CHECK IN, When startiny engine using an approved external power source (Auw. Power Cable Adapter is available from Mooney Aircraft Corporation) no special starting procedure is necessary, Use normal starting procedures be low, 3-7-84...

  • Page 51: Before Takeoff

    Propeller Control Throttle Control FORWARD l/4, Master Switch Mixture Control Electric Fuel Boost Pump Switch ON TO ESTABLISH PRESSURE, THEN OFF. Mixture Control FULL AFT (IDLE CUT-OFF) Propeller Area CLEAR. TURN AND PUSH TO START, RELEASE TO BOTH WHEN ENGINE STARTS. Mixture MOVE SLOWLY AND SMOOTHLY TO RICH.
  • Page 52 Strobe Lights and Rotating Beacon--OW (if installed). Annunciator Lights CHECK WITH PRESS-TO- T E S T & THROTTLE RETARDED. T r i m TAKEOFF SETTING. If f o r w a r d CG s e t t r i m t o upper portion of band and t o lower portion when a t aft CG.
  • Page 53 TAKEOFF Move the codrolls slowly and smooth$y. In particular, avoid rapid opening the t k o t t l e the engine is e q u t p p d with a counterweighted cranlnsmt and there is a R o p e r full throttle e w i n e operatibn should be checked e a r l y in the takeoff roll.
  • Page 54 (Obstacle Clearance) TAKEOFF at start takeoff FULL TEHROTTLE AND 2700 RPM- Attitude Aircraft MPH (62 KTS. ) IAS. Speed IAS until 76 M P H Climb clear obstacle, then accelerate to 115 M P H (91. Gear RETRACT IN CLIMB AFTER RETRACT AFTER CLEARING OBSTACLE.
  • Page 55 CLIMB (Best Rate) Power FULL THROTTLE Mixture LEAN FOR SMOOTH OPERATION. FUEL OPEN. Airspeed a t %0,000 Ft. Ram Air -ON AFTER ENTERING CLEAR AIR. Manifold p r e s s u r e w i l l d r o p with increasing altitude a t any throttle setting.
  • Page 56 Upon reaching c r u i s e altitude, allow acceleration t o c r u i s e a i r s p e e d , then t r i m the a i r c r a f t for level flight, reduce manifold p r e s s u r e and R P M t o d e s i r e d c r u i s e power, and close t h e cowl flaps.
  • Page 57 When increasing power always r e t u r n m i d w e t o full rich, when decreasing power d e c r e a s e manifold p r e s s u e p e f o r e DESCENT Power A S DEWRED.
  • Page 58 ADJUST, a s n e c e s s a r y , Electric F u e l Boost Pump Ram Air Check Gear Down GEAR DOWN LIGHT ON MARKS ALIGNED IN VISUAL ImIGATOR I N F L W R . G O AROUND (BALKED LANDING 1 Power FULL THROTTLE AND...
  • Page 59 SHUTDOWN 1200 RPM ~11til cy- Radio Switch--OFF. Throttle--RETAR%) a s engine stops firing. Parking Brake-- Set (for short- term parking). seat belt. Parking Brake OFF. IDLE CUTOFF, CHOCKS. F o r Extended Parking or i n Gusty Wind Conditions BELT, TIE DOWN AIRCRAFT A T WING AND TAIL POINTS.

  • Page 61: Table Of Contents

    SECTION PERFORMANCE TABLE OF COBTENTS INTRODUCTION ......A &TI% UDE CQNVERSIQN .
  • Page 63 performance tables and graphs a r e grouped In t h i s A l l section of the manual for quick and easy reference. The information i s presented t o show performance that may be expected from the a i r c r a f t , and t o a s s i s t you in planning your flights with reasonable detail, and a c c u r - acy.
  • Page 64 = @AS...
  • Page 66 Given: 168 MPH...
  • Page 67 i 3 0 ISSUED X 1- 15-77...
  • Page 69 ALTERNATE S T A T I C SOURCE n u m b e r s from IAS t o obtain @AS assuming z e r o instrument e r r o r . CONDITIONS: Storm Window and Vents:@Iosed Defroster : M a i m u r n Power On...
  • Page 71 ISSUED 11-15-77...

  • Page 73: Flaps 33

    STALL SPEEDS ASSOCIATED CONDITIONS: Gross WeigM 2740 LBS. Forward CG Power airspeeds in MPH & mQT$ and assume zero instrument approximately 290 feet Flaps 1 5 ' Flaps 33' EXAMPLE: 2740 LBS. Landing Gear Down Flaps Angle Find: 65 M P H %AS 5-43...
  • Page 75 ISSUED 11-15-77...

  • Page 76: Climb Performance

    RATE OF CLIMB EXAMPLE GIVEN: D E N S T Y A L % % T m E - 9 0 0 0 FEET FMD: BEST RATE OF CWMB-590 FT./ BEST RATE OF CLIMB $PEED-$% KXdBTS %A8...
  • Page 77 TIME, FUEL AND DlSTANCE TO C L l M B Associated Conditions for the Time, Fuel and Distance t o Climb graph the following page: Power: Rich Ram A i r : On Cowl Flaps: Full Open Gear: Wing Flaps: Up Fuel Density 6.
  • Page 78 TIME, FUEL AND OlSTANCE...
  • Page 79 Data tables allow for: the best r a t e of climb speed (Vy) t o cruise altitude; a c r u i s e t o destination at the specified power and the s a m e altitude and power setting. The data is gallons of usable fuel, standard atmosphere, and no wind.
  • Page 81 2000...
  • Page 82 4000 FT, 5- 22...
  • Page 83 RANGE AT ECONOMY 6000 F t , 3 ' C 5- 23...
  • Page 84 CRUISE L RANGE AT ECONOMY 8000 FT,...
  • Page 85 RANGE AT...

  • Page 88: Best Power

    SEA LEVEL, 15°C MIXTURE SETTING: Use F U L L RICH mixture above 75% power. 2. Lean mixture in accordance with instructions in Section 75% power and below. 5- 28 11-15-77 ISSUED...
  • Page 89 RANGE 2000 FT, "ill°C MIXTURE SETTING: 1. U s e FUEL RICH mixture above ISSUED 11- 15- 77...
  • Page 92 AT BEST POWER 5-33 ISSUED 11-15-77...
  • Page 93 RANGE AT BEST POWER...
  • Page 95 CRUISE L RANGE AT BEST POWER...
  • Page 99 SECTION VI. TABLE O F CONTENTS PACE ....AIRPLANE WEIGHING PROCEDURE OWNERS WEIGHT & BALANCE RECORD ... . 6 - 6 6- 6 6- 7...
  • Page 100 Only those i t e m s checked (X) were in- s t a l l e d a t Mooney and a r e included i n the empty with the responsibility of properly loading your a i r...
  • Page 101 maximum g r o s s weight. The aircraft must be operated strictly within the limits of the Center-of -Gravity Moment Envelope shown on page 6-8. (A) LEVELING: Place a spirit %eve% on the skin line above the tailcone a c c e s s door when leveling the aircraft longitudinally.
  • Page 102 point t o main wheel axle center line, Measure horizontal distance from center line of nose wheel axle to center line of main wheel axles. 12. Record weights and measurements, and compute basic weight and CG a s follows: R E F POINT a .
  • Page 104 LOADING CALCULATION PROCEDURE Proper loading of the aircraft i s essential! for maximum flight performance and safety. This section will assist you in determining whether the aircraft loading schedule i s within the approved weight and center-of-gravity To figme a n actual loading problem for your a i r c r a f t , proceed a s follows: Step I.
  • Page 105 FAA REGISTRATION NO SERIAL NO of Grwity to Center Y SITUA~ON. Obtain the such aeot position [FWD, UID AFT) loading computation 3- 7- 84 11- 15- 77 ISSUED...
  • Page 106 AIRCRAFT CG LBCATION(Lyg) OF DATUM ISSUED 11-15-77...
  • Page 107 Mooney column and dated were installed a t Muoney. must be done in accordance with the r e f e r e n c e drawing o r a separate F A A approval.
  • Page 113 11-15-77...
  • Page 115 6- 1' s...
  • Page 116 15-77...
  • Page 118 3 - 7 - 8 4...

  • Page 119: Fuel System

    TABLE O F CONTENTS TITLE PAGE POWER B L A m ... . ENGINE CONTROLS ......FUEL SYSTEM .
  • Page 120 7-25 ELECTRIC GEAR RETRACTION SYSTEM 7-25 EXTENSION SYSTEM 7-26 EMERGENCY GEAR 7-26 ALTERNATOR & BATTERY 7-28 7-29 INSTRUMENT 7-29 7-29 CABIN UGHTMG 7-29 HEATING & V E N T I U T I N G S'SPSTEMS WINDSHIELD DEFROSTING SYSTEM CARGO BAGGAGE &...
  • Page 121 and equipment is one of your important first steps in de- veloping a fully efficient operatiw technique. This a i r and operation of systemss cona&rols and quipmewt, It is advimble for you, the pi%&, t o f a m i l k r i z e yourself with all controls and s y d e m s while sitting i n the pila$'s seat and r e h e a r s i q the sy&ems operations and The a i r f r a m e...
  • Page 122 POWER PLANT the pilot and co-pilot, on the ewg;ine control console, The t h o t t l e knob r e g u h t e s mangold p r e s s w e . the h o b aft decreases the settiwg;. The propeller e o d r o l , with i t s crowned blue o r black h o b , controls @ w i n e R P M t h o q h the propeller governor.
  • Page 123 Cylinder head temperature, oil pressme, fuel pressure and oil temperature gages are located above the flight instruments, tachometer, and mansold presstare the rigM of the radio panel. Golor arcs on are located mark aperatim ranges, selecting optimum control settings and for 113aintainiw magneto fires the lower right and upper left spark plugs, and the left magneto fires the lower %eft anad upper right spark plugs.
  • Page 124 t o f i r e the engine. After the engine s t a r t s , the impulse as a The coupling thenacts straight drive and the magneto f i r e s a t the normal firing position of the engine. The m a g START t o the BOTH position when released.
  • Page 125 and tharowh the electric fuel pump (boast pump) emoute t o the ewine-driven pump and the fuel injector unit, ficient p r e s s u r e and fuel %%ow for maximum engine performance should the engine driven pump fail, Electric fuel-level transmitters in the tanks operate the ENGINE DRIMN remaining in each tank.
  • Page 126 The engine h a s full- pressure wet-sump oil sy&em a n $-quart .capacity. An automatic bypass control valve routes oil flow around the oil cooler when operating temp- e r a t u r e s a r e below normal or when the cooling radiator is blocked, ENGINE COOLING and inflight power plant cooling.
  • Page 127 CONTROLS FAMILIARIZATION FLIGHT mSTRUMEN%S AND CONTROL$ radio bus. Energizing the s t a r t e r automatica%%y ener The master switch operates the battery relay which from main bus t o the alternator. This cuts off a l l ships power except the cabin Eight and electric clock.
  • Page 129 VERTICAL SPEED MDICATOR (if installed) The vertical speed indicator depicts airplane rate of climb or descent in feet per minute. The pointer is actuated by a m atmospheric p r e s s u r e change supplied by the static source. GEAR SAFETY OVERRIDE SWTCH The g e a r safety override switch is a mech- anical means of electrically bypassiw the...
  • Page 130 covers, No maix~temnce required on the compass except a n occasional check on a compass r o s e with adjustment of the compensation, necessary, and The flap switch in a r e c e s s on the rigM of the console, 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 deflec-...
  • Page 131 TRIM POSmION INDICATOR a cable attached to the t r i m wheel mechanism. Position the conso%e. circuit breaker t u r n s on the heating elements within the pitot tube. Should a short occur the combination OFF position. BREAKER circuit breaker will automatically t r i p t o the OFF landing light should not be operated...
  • Page 132 The fuel qraantitgr indicators a r e eased i n coeajunctio~2 in each fuel lank;. mitter float produces a maximtarn resistance through the fuel quantity indicator and maximum pointer def%ection. The cylinder head temperature indications a r e con- trolled by an electrical resistance type temperature probe installed in the number three cylinder, and receives power from the aircraft electrical system.
  • Page 133 indicating gage. The a m m e t e r indicates current flow, in a m p e r e s , from the alternator to the battery, or from the battery t o the electrical system. With the engine operating, and master switch "ON", the ammeter indicates the r a t e of charge being applied t o the battery.
  • Page 134 TACHOMETER T h e tachometer is a mechanical indicator driven a t half difficulties will be found in the driveshaft. To function properly, t h e shaft housing must be f r e e of kinlts, dents and s h a r p bends. MANIFOLD PRESSURE The manifold p r e s s u r e gage is of t h e d i r e c t reading type and is mounted above t h e engine...
  • Page 135 Pulling the control aft d e c r e a s e s the manifold p r e s s u r e thereby d e c r e a s i n g the engine power. C O W L FLAP C O N T R O L Pulling t h e cowl flap control full aft opens the cowl flap d o o r s allowing additional airflow t o p r o p e r l y cool the engine on the ground and during low speed high...
  • Page 136 MISCELLANEOUS INSTRUMENTS, CONTROLS AND INDICATORS RADIO LIGBT SWIIT.CEI AND DIMMER Turning the r a d i o light switch kxiob clockwise t u r n s ON the r a d i o and indicator lights. Continued turning clockwise i n c r e a s e s light intensity. RADIO PANELS Adequate s p a c e i s provided for installation of optional avionics.
  • Page 137 CIGAR LIGHTER (if installed) PARKING BRAKE CONTROL Pulling the parking bralce control and d e p r e s s i n g Pushing in the bralie pedals s e t s t h e parking bsalte. the parlting b r a k e control r e l e a s e s the parking brake. CABIN VENT CONTROL Pulling the cabin vent control aft opens the cabin vent, located on the r i g h t s i d e of t h e a i r p l a n e .
  • Page 138 ANNUNCIATOR AND SWITCH P A N E L PRESS-TO-TE ST SWL'GGH P r e s s i n g tlre r e d press-to-test switch with t h e annuncia- m a s t e r switch ON wl1.l illuminate a l l t o r light bu.lbs.
  • Page 139 V A C U U M The r e d o r improper acljustmcnt of a i r suction s y s t e m . Air and also the directionat% g y r o , and w i l l be shown The d e s i g m t e d snction range above 5 .
  • Page 140 PRIMARY FLIGHT CONTROLS Push-pull tubes with self-aligning rod end bearings actuate the p r i m a r y flight control surfaces. loaded interconnect device indirectly joins the a i l e r o n and rudder control s y s t e m s t o a s s i s t in l a t e r a l stability during flight maneuvers.
  • Page 141 supply static air- static tail SYSTEM STALL WARNflNO electrical stall w a r n i w system u s e s a mne-actmted switch, installed in the leB w i w Beadiq e k e , t o energize a stal% warning horn located in the cabin. The stall warn- ing switch is adjusted t o p r o d d e aura% wwning at t o 10...
  • Page 142 position whenever the unit position is proaTHded s o the unit a n be used a s a portable transmi#er o r i n the event the automatic fea- t u r e was not triggered by impact or to p s r i d i c a l l y test the function of the transmitter.
  • Page 143 ELECTRIC GEAR RETRACTIOH 8 The two-position electric gear control switch, identified by i t s wheel-sbped h o b , instrument p a m l above the t b o ~ l e . There a r e two ways t o check that the electrically-actated gear is down: The green gear-down annunciator light is ow, The indicator m a r k align a s seen on.
  • Page 144 The emergency g e a r edension pull cord located between and aft of the s e a t s is f o r t o extend the gear the electric system emergency gear extension ~p%.oeedure. BRAKE & STEERING S Y S T E m The main gear wheels incorporate seH-adjusting disc- The pilot's rudder pedals have typo hydraulic brakes.
  • Page 145 FIGURE 7- 3 ELECTRICAL SYSTEM SCHEMATIC REVISION A...
  • Page 146 Push- to- reset, push-pull, or rocker- switch circuit b r e a k e r s automatically r e n t flow if t h e s y s t e m s r e c e i v e a n overload, thus preventing damage t o e l e c t r i c a l wiring.
  • Page 147 exceeds limits, the r e d voltage warning light illuminates steadily. Turning off the r a d i o m a s t e r switch and then turning m a s t e r switch off and on, will r e s e t the voltage regulator.
  • Page 148 When high intensity wing tip strobe lights a r e in- stalled, they should be turned off when taxiing n e a r other aircraft,in fog or clouds. The conventional navigation lights must be used for a l l night operations. Three ventilating s y s t e m s provide cabin environmental control suited t o individual pilot and passenger prefer- ences.
  • Page 149 The cabin overhead ventilating s y s t e m works independently of the cabin heating and ventilating s y s t e m . F r e s h a i r e n t e r s an intake on the d o r s a l fin and controlled by individual eyeball outlets above each s e a t * The cabin heat control is marked CABIN HEAT,...
  • Page 150 SAFETY HARNESS T h e single diagonal type h a r n e s s i s designed s o the chest a n attachment point low on t h e inboard hip C a r e should be taken t o conform with t h i s location i n ad- justing the chest s t r a p and inboard belt length.
  • Page 151 TABLE OF CONTENTS TITLE PAGE ....TOWING ....ENGINE LUBRICATION GEAR ANDrrBRE 8-10...
  • Page 152 Keep in touch with y o u Mooney Service Center and take He b o w s you- advantage of h i s howledge and experience.

  • Page 153: Ground Handling

    Maintenance Manual or P a r t s W/lanleall. Service Maintenance and P a r t s Manuals may be obtained for y a w airplane f r o m your Mooney Marketing and Service Center. GROUND HANDLING aircraft in @Rose quarters, in the...
  • Page 154 As a precaution against wind damage, always t i e down the aircraft. when parked outside. Removable wing ttiedown eye- bolts, supplied with t h e loose equipment, s c r e w into wing r e c e p t a c l e s marked HOIST POINT just outboard of e a c h main g e a r .
  • Page 155 out r a i s i q the entire aircrafi. Wheels not being r a i s e d should be chocked fore and aft. Integral sealed tanks in the forward inboard sections of the wings c a r r y the fuel. With the aircraft standing on tanks have fuel level indicators t k t a r e visible t h o u g h the filler ports.
  • Page 156 25 taours of operation or until oil consump- tion has stabilized. The aircraft delivered from Mooney with straight mineral oil of the correct viscosity, The engine is equipped with an external oil filter and the...
  • Page 157 hours, a change t o additive oil should be undertaken with the e g i n e is in a n extremely dirty condition, engine has been overhauled. When c b n g i ~ from straight mineral oil t o additive o r compounded oil, after several the following precautiomry steps: a .
  • Page 158 Your Mooney Service Center bas a p v o v e d brands of t o service your airplane. A I R FILTER cannot be over-emphasized, A clean filter promotes fuel economy and longer engine life. The dry-type Donaldson filter can usually be washed...
  • Page 159 A Donaldson D-1400 Filter Cleaner i s water until rinse water i s clear. o r a i r heated above 1 8 0 ~ ~ damage is evi- dent, replace filter with a new one. GEAR S The aircraft i s equipped with 6-ply standard-brand t i r e s and tubes, Keep the main gear t i r e s inflated at 30 PSI and the nose t i r e at for maximum service life.
  • Page 160 gravity is 1.240 or lower. %art charging at four amperes and finish at two amperes; do not allow battery tempera- t u r e t o r i s e above 120°F during recharging. Keep the battery at full charge to prevent freezing in cold weather and to prolong service life.
  • Page 161 tolerances in the parts. This has no adverse affect on propeller performance o r operation and is no cause for con- c e r n if the total movement at the blade tip does not exceed seats the blades, rigidly and positively again& the r e t e d i o n bearing i n the propeller hub.
  • Page 162 on the leading edge of the wings, empenmge, and section will laelp reduce drag and abrasion in these w e a s , stance is found on the exterior paint, wash the a r e a at once t o prevent staining. Pmmediately flush away spilled battery acid, and t r e a t the a r e a with a baking so&-and-water solu- washing with a mild aircraft tion, followed by a...
  • Page 163 Certain miscellamous data, information and licenses a r e a p a r t sf the a b p h n e file. The followiw is a checklist documents that must either be carried in the airplane or available on request of the proper autlaority. (a) Aircraft Airworthiness Certificate (FAA F o r m 8100-2) (FAA F o r m 8050-3) installed (FCC F o r m 556).

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