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Mooney M20R - Ovation, Flight Manual

The Mooney M20R - Ovation Flight Manual is available for free download on our website. This comprehensive manual provides essential information for pilots operating the M20R, offering detailed instructions and procedures. Enhance your flying experience by accessing this invaluable resource at manualshive.com – your ultimate destination for aviation manuals.

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Summary of Contents for M20R - Ovation

Page 1: ...A APPROVED AIRPLANE FLIGHT MANUAL M20R OVATION ORIGINAL ISSUE 06 1994 REVISION G 03 2000 Copyright 2013 All Rights Reserved PIN POH 003600 MOONEY AVIATION COMPANY INC Louis Schreiner Field Kerrville Texas 78028 tel 830 896 6000 www mooney com ...

Page 2: ...29 0045 OE KGG Section VI page 6 5 Revised Weight and Balance sheet dated 10 4 12 inserted by Erik Rosdol on 15 Nov 2014 ...

Page 3: ... a clear and convenient manner to enable you to use the manual as a reference Your cooperation In reporting presentation and content recommendations is solicited REVISING THE MANUAL The i pages of this manual contain a list of Effective Pages containing a complete current listing of all pages i e Original or Revised Also in the lower right comer of the outlined portion is a box which denotes the m...

Page 4: ...v v vi 1 1 1 2 1 3 1 4 1 5 1 6 thru 1 8 1 9 1 10 2 1 2 2 2 3 2 4 2 5 2 6 2 7 2 8 2 9 2 10 2 11 2 12 2 13 2 14 2 15 2 16 2 17 2 18 3 1 thru 3 4 3 5 3 6 thru 3 7 3 8 3 9 3 10 3 11 3 12 3 13 3 14 3 15 3 16 4 1 4 2 thru 4 4 4 5 4 6 4 7 4 8 ISSUSED 6 94 G ORIGINAL G ORIGINAL ORIGINAL F c ORIGINAL G ORIGINAL G B G F ORIGINAL G E G D G A ORIGINAL ORIGINAL G E A E ORIGINAL E F E ORIGINAL F ORIGINAL F c E ...

Page 5: ... 1 8 2 8 3 thru 8 6 8 7 8 8 thru 8 10 I LIST OF EFFECTIVE PAGES con t l INTRODUCTION F E ORIGINAL c ORIGINAL A ORIGINAL G c E c ORIGINAL F ORIGINAL E ORIGINAL F ORIGINAL G ORIGINAL G ORIGINAL G F ORIGINAL G ORIGINAL G ORIGINAL G ORIGINAL G ORIGINAL A ORIGINAL 9 1 through 9 4 plus Applicable Supplements inserted ORIGINAL ii 10 1 10 2 thru 10 10 10 11 10 12 D ORIGINAL D ORIGINAL POH AFM NUMBER 3600 ...

Page 6: ... 4 5 13 6 15 6 16 6 17 6 20 6 21 6 22 6 25 thru 6 29 2 11thru 2 15 ILOG OF REVISIONS I DESCRIPTION FAA OF REVISIONS APPROVED I Revised Data Added Data Revised Chart Added Placard 1 1 MOONEY M20R DATE 1P The reVJsed portions of affected pages are and1 cated by vert1cal black lines 10 the margm POH AFM NUMBER 3600 G ISSUED 6 94 iii ...

Page 7: ...BER INTRODUCTION ILOG OF REVISIONS con tll REVISE DESCRIPTION FAA DATE PAGES OF REVISIONS I APPROVED The revised portions of affected pages are indicted by vertical black lines in he margin iv POH AFM NUMBER 3600 G ISSUED6 94 ...

Page 8: ...RAL LIMITATIONS EMERGENCY PROCEDURES NORMAL PROCEDURES PERFORMANCE WEIGHT BALANCE AIRPLANE SYSTEM DESCRIPTIONS HANDLING SERVICE MAINTENANCE SUPPLEMENTAL DATA SAFETY OPERATIONAL TIPS ISSUED 6 94 INTRODUCTION SECTION II Ill IV v VI VII VIII IX X v ...

Page 9: ...INTRODUCTION BLANK vi MOONEY M20R ISSUED 6 94 ...

Page 10: ...AGE SPACE AND ENTRY DIMENSIONS SPECIFIC LOADINGS IDENTIFICATION PLATE SYMBOLS ABBREVIATIONS TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY SYMBOLS ENGINE POWER TERMINOLOGY 1 3 1 3 1 3 1 4 1 4 1 4 1 4 1 4 1 5 1 5 1 5 1 5 1 5 1 5 Hi AIRPLANE PERFORMANCE FLIGHT PLANNING TERMINOLOGY 1 6 ENGINE CONTROLS INSTRUMENTS TERMINOLOGY 1 7 METEOROLOGICAL TERMINOLOGY 1 7 WEIGHT BALANCE TERMINOLOGY 1 8 MEASUREMENT CONV...

Page 11: ...SECTION I GENERAL MOONEY M20R 1099 8 Cl l I 36 1 1 FIGURE 1 1 THREE VIEW M20R 1 2 ISSU OD 6 94 ...

Page 12: ...tractable tricycle gear with rubber shock discs The main wheels have hydraulically operated disc brakes The nose wheel is fully steerable 11 left to 13 right of center Wleel Base Wleel Track lire Size Nose Main Trre Pressure Nose Main Minimum Turning Radius No brakes applied Right Left MAXIMUM CERTIACATED WEIGHTS Gross IM ight Maxim landing Weight Baggage Area Rear storage Area Cargo Rear Seats Fo...

Page 13: ...n this POHIAFM are considered mandatory for the Continued Airworthiness of this airplane in a condition equal to that of its original manufacture IDESCRIPTIVE DATA I ENGINE Number of engines Engine Manufacturer Molle Recommended lBO Type Number of cylinders Displacement Bore stroke Compression ratio Fuel System fk Fuel Aviation Gasoline Accessories Magnetos 9nition Harness ark Plugs OIICooler Alte...

Page 14: ...e tall cone below the horizontal stabilizer leading edge The aircraft Serial Number and type certif cate are shown ISYMBOLS ABBREVIATIONS TERMINOLOGY I GENERAL AIRSPEED TERMINOLOGY SYMBOLS GS GROUND SPEED Speed of an airplane relative to the ground KCAS KIAS KNOTS CAUBRATED AIRSPEED The indicated speed of an alrcraft corrected for position and instrument error Calibrated airspeed is equal to true ...

Page 15: ...th gear and flaps up ENGINE POWER TERMINOLOGY BHP CHT EGT MCP MP RPM BRAKE HORSEPOWER Power developed by the engine CYLINDER HEAD TEMPERATURE Operating temperature of engine cylinder s being monitored by sensor unit Expressed in F EXHAUST GAS TEMPERATURE The exhaust gas temperature measured in the exhaust pipe manifold Expressed in F MAXIMUM CONTINUOUS POWER The maximum power for takeoff normal ab...

Page 16: ...nsity altitude The altitude actually read from an altimeter when and only when barometric subscale Kollsman window has been set to Station Pressure INTERNATIONAL STANDARD ATMOSPHERE assumes that 1 The air is a dry perfect gas 2 The temperature at sea level is 15 degrees Celsius 59 F 3 The pressure at sea level is 29 92 inches Hg 1013 2 mb 4 The temperature gradient from sea level to the altitude a...

Page 17: ...n imaginary vertical plane from which all horizontal distances are are measured for balance purposes A location along the airplane fuselage usually given in terms of distance from the reference datum The weight of chocks blocks stands etc used when weighing an airplane and is included in the scale readings Tare is deducted from the scale reading to obtain the actual net airplane weight Fuel remain...

Page 18: ...erial u s Metric Liquid and Dry Measure Equivalents Equivalents 1 fluid ounce 0 961 u s 28 412 milliliters fluid ounce 1 734 cubic Inches 1 pint 1 032 u s 568 26 miiiUiters dry pints 1 201 u s liquid pts 34 678 cubic Inches 1 quart 1 032 u s 1 1361iters dry quarts 1 201 u s liquid qts 69 354 cubic Inches 1 gallon 1 201 u s 4 54611ters 277 420 cubic inches WEIGHT U S Customary Unit Avoirdupois Metr...

Page 19: ...SECTION I GENERAL 1 pound square foot 1 pound sq Inch 1 Pound HP 1 10 COMMON CONVERSIONS MOONEY M20R 0 488 kg meier square 2 036 Inch t Jg 0 4538 kg HP ISSUED 6 94 ...

Page 20: ... WEIGHT LIMITS CENTER OF GRAVITY GEAR DOWN MANEUVER LIMITS FLIGHT LOAD FACTOR LIMITS FLIGHT CREW OPERATING LIMITATIONS OXYGEN SYSTEM LIMITATIONS KINDS OF OPERATION LIMITS KINDS OF OPERATION EQUIPMENT LIST DECALS PLACARDS CABIN INTERIOR FUSELAGE INTF RIOR EXTERIOR FAA APPROVED ISSUED 6 94 REV G PAGE 2 2 2 2 2 3 2 4 2 5 2 6 2 7 2 7 2 7 2 8 2 8 2 8 2 8 2 8 2 8 2 8 2 11 2 11 2 15 2 16 AIRPLANE FLIGHT ...

Page 21: ... Markings chart Figure 2 2 are based on Airspeed Calibration data shown In SECTION V with the nonmal static source If the alternate static source Is being used ample margins should be observed to allow for the airspeed calibration variations between the normal and alternate static sources as shown In SECTION V Your Mooney Is certlfi ted under FAA Type Certificate No 2A3 as a Mooney M20R INOISE LIM...

Page 22: ...brupt control move 3300 1497 127 126 men above this 3368 1528 128 127 speed VFe MaximumAap 111 110 Do not exceed this Extended Speed speed with flaps in full down position VLE Maximum Landing 166 165 Maximum speed at Gear Extended which the aircraft Speed can be safely flown with the landing gear extended VLO Max Speed for 141 140 Max speed at which EXl Gear Extension the landing gear can be safel...

Page 23: ... Range Radial Red Line 59 110 KIAS 66 174 KIAS 174 195 KIAS 195 KIAS Lower limit is maximum weight Vso In landing con figuration Upper limit is maximum speed per mlssable with naps ex tended Lower limit is maximum weight Vs with flaps re tracted Upper limit is maximum structural cruising speed Operations must be con ducted with caution and only in smooth air Maximum speed for ali op erations FIGUR...

Page 24: ...F 24 C 170 F 200 F 76 C 93 C 30 60 PSI 10 PSI Oil Specification MHS 24 MHS 25 and TCM Approved oils Fuel Grade Color 1DOLL Blue or 100 octane Green Number of Propellers Propeller Manufacturer Propeller Blade Model Number Number of Blades Propeller Diameter McCauley Min Max McCauley Propeller Blade Angles 30 0 ln sta Low High Propeller Operating Limits McCauley McCauley I 3A32C418 G 82NRC 9 3 72 5 ...

Page 25: ...6 6 104 C 30 60 PSI 1400 1450 F 760 786 C BLUEARC 420 460 F 215 5 237 7 C 100 170 F 37 7 76 6 C 220 240 104 115 5 C 10 30PSI 60 100 PSI recommended climb MOONEY M20R RECLINE MAXIMUM LIMIT 2500 RPM 460 F 237 7 C 240 F 115 5 C 100 PSI 1650 F 899 C NOTE Refer to TCM Engine Maintenance and Operators Manual Section on Engine Specifications and Operating Limits for recommended cruise power and temperatu...

Page 26: ...rmissible to add ISO PROPYL alcohol to the fuel supply in quantities NOT TO EXCEED 3 of total fuel volume per tank DO NOT add other additives to fuel system due to potential deteriorating effects wllhln the fuel system IWEIGHT LIMITS Maximum Weight Takeoff 33681b 1528 Kg Maximum Weight Landing 3200 lb 1452 Kg Maximum Weight In Baggage Compartment 120 lb 54 4 Kg Fus Sta 101 5 253 7 em Maximum Weigh...

Page 27: ... accordance with AR 91 or FAR 135 ALTERNATOR OPERATING LIMITATIONS IS 94 AMPS KINDS OF OPERATION LIMITS This is a Normal Category airplane certified for VFRIIFR day or night operations when the re quired equipment is installed and operational as specified in the KINDS OF OPERATION EQUIPMENT LIST and the applicable operating rules Optional equipment installations may not be required to be operation...

Page 28: ...TURE INDICATOR AMMETER ALTERNATOR LANDING GEAR POSITION INDICATOR SEAT BELT SHOULDER HARNESS FOR EACH OCCUPANT UXVGI N MASK FOR EACH OCCUPANT POSITION LIGHTS STROBE LIGHTS ANTI COLLISION I l VFR DAY 2 1 VFR NIGHT IFR DAY i IFR NIGHT I 1 I 2 I 2 2 I I 1 I I 2 2 2 2 1 3 3 3 3 Equipment must be Installed and operable for all operations If inoperative for unoccupied seat s seat s must be placarded DO ...

Page 29: ...CATION SYSTEM NAVIGATION SYSTEM APPROPRIATE TO FACILITIES BEING USED BATIERY VACUUM SYSTEM INDICATOR FUEL BOOST PUMP PILOT S OPERATING HANDBOOK AIRPLANE FLIGHT MANUAL PITOT Heated OAT GAUGE VSI ALTERNATE STATIC SOURCE STAND BY VACUUM SYSTEM VFR DAY I2 i I I VFR NIGHT IFR DAY IFR NIGHT 1 I I i I I I I 2 I 2 I 2 i I I 1 i I 1 I I Equipment must be installed and operable for all operations When requi...

Page 30: ... 1 Se UB ftiO WI1I Ntl FWIIWIOl r 1 r sm l fJ2 o 1 8 T ru JOn PUUS IF CAUTION 1 TURN OfF S1ROOE U1ES WHEN TAXING N AR OlliER ACFT OR WHEN FLYING IN FOG OH IN CUlUDS S1D POSITION U1ES MUST BE FOR All NIGHT OPERATIONS 2 IN CASE OF FIRE TURN OFF CABIN HE AT 3 DO NOT SCR W IERNIER OONTROIS CUlS R THNt 1 lr FROM NUf FACE 40t t CONTROLS FUEL INSTRUMENTS TRIM CHECK LIST RUN UP PROP WING FLAPS SEAT LATCH ...

Page 31: ...SWTTCH FAIWRE A4018 FLOORBOARD BETWEEN SEATS 4045 ABOVE EACH IVIUUI It Y M20R FWD END OF REAR SEAT BOTTOM STRUCTURE 0 0 MIKE PHONE FUEL QTY 44 5 GAL B t S s __u_s_E _ A _ B _L_E J 213 BELOW INSTRUMENT PANEL EACH SIDE FUEL Fl OW loiEWORY ON E9 OFF II11CE ISOLATlON ON E9 OFF 0170 THRU 29 0199 INSTRUMENT RADIO PANEL VARIES W INSTALLED EQUIP DME WIY1 IND I IIEROOM DME WIV 1 YOR NORioW MJOIO ON E9 E9 E...

Page 32: ...TD 165 KIAS LWR INSTR PNL BELOW CONTROL WHEEL SHAFT PULL FOR ALT STATIC SOURCE A2001 GA I N ARB YElLijW AR8 BLUiQARC 0 250 420 420 490 1400 1450 30 60 PSI ABOVE ENGINE INSTRUMENT CLUSTER ON BEZEL 29 0170 29 0199 DO NOT OPEN ABOVE 132 KIAS AflltO AROUND EACH OXYGEN OUTLET ON OVERHEAD PANEL BELOW PILOT S STORM WINDOW ON MAGNETIC COMPASS ABOVE EACH CONTROL ONLWR CONSOLE ON CONTROL KNOB INSTR ALT AIR ...

Page 33: ...NSTRUMENT PANEL SPEEOBRAKE QUIPPED FOR OPERATING INSTRUCTIONS AND UMITATIONS SEE FAA APPROVED FM SUPPLEMENT OR PILOT S OPERATING HANDBOOK OPTIONAL 4057 ON UPPER INSTRUMENT PANEL NXXXXX FLOORBOARD BETWEEN SEATS BETWEEN SEATS ON EMERGENCY GEAR RELEASE EXTENSION HANDLE LIGHT SWITCH 6082 14 VOLTS 3AMPS MAX 5 A INTERMITIENT PUSH TO RELEASE 6012 BAGGAGE DOOR FRAME RT RADIO PNL ADJACENT TO AUX PVVR PLUG ...

Page 34: ...OLTS ONLY 6080 BACKSIDE OF AUX PWR RECEPTACLE DOOR USE AVIATORS OXYGEN ONLY SEE PILOT S OPERATING HANDBOOK FOR FILLING PRESSURES OPTIONAL 4050 INSIDE ENGINE OIL FILLER DOOR REMOVE OIL COOLER DOOR ON OIL FILLER DOOR IF KIT INSTALLED HYDRAULIC OIL RESERVOIR INSIDE OXYGEN FILLER DOOR BOTH BATIERIES MUSI 81 INSTALLED FOR FLIGHT 606 E N G IN E 0 IL 0 1l y OIL INSTALLED IN THIS ENGINE IS PANELS NEXT OIL...

Page 35: ...AD OF FLAPS UNDERSIDE OF WING 2 PLCS H0 IsT AFT OF 1 H COWL FLAP 1PLC POINT 6002 DO NOT PUSH HORIZ STAB L E RUDDER T E BOTH SIDES 6001 UNDER TAILCONE AFT OF WING T E STATIC DRAIN I 6024 PITOT DRAIN I 6026 GASCOLATOR DRAIN 6030 AIRPLANE FLIGHT MANUAL 2 16 UNDER LEFT WING L E NEAR FUSELAGE UNDER WING NEAR SUMP DRAINS FUEL DRAIN UNDER FUSELAGE AT SIDE AFT OF NOSE WHEEL WELL AEVA 7 94 6028 FAA APPROVE...

Page 36: ...Y 6035 ON NOSE LANDING GEAR SPINDLE ASSY WARNING DO NOT EXCEED TOWING LIMITS t 6036 MAGNETIC AZIMUTH TRANSMITTER O LWU BLIDHO f I OGISP f LOCATED INSIDE THIS INSPECTION COVER USE ONLY NON MAGNETIC SCREWS FOR COVER INSTALLATION FUEL 100 GREEN OR 1OOLL BLUE MIN OCT 44 5 U S GAL USABLE 168 5 LITERS USABLE FAA APPROVED ISSUED 6 94 6059 6050 ON BOTH FUEL FILLER CAPS REV A 7 94 AIRPLANE FLIGHT MANUAL 2 ...

Page 37: ...SECTION II LIMITATIONS AIRPLANE FLIGHT MANUAL 2 18 BLANK MOONEY M20R FAA APPROVED ISSUED 6 94 ...

Page 38: ...MPERATURE 3 8 HIGH OIL TEMPERATURE 3 8 LOW OIL PRESSURE 3 8 LOW FUEL PRESSURE 3 8 ENGINE DRIVEN FUEL PUMP FAILURE 3 8 FUEL VAPOR SUPPRESSION FLUCTUATING FUEL PRESSURE 3 9 FIRES ENGINE FIRE DURING START ON GROUND ENGINE FIRE IN FLIGHT ELECTRICAL FIRE IN FLIGHT SMOKE IN CABIN EMERGENCY DESCENT PROCEDURE GLIDE FORCED LANDING EMERGENCY GEAR RETRACTED OR EXTENDED OVERWEIGHT LANDING PROCEDURES SYSTEMS E...

Page 39: ...I 1111 EMERGENCY PROCEDURES I TABLE OF CONTENTS con t I TITLE UNIJ TCHED DOORS IN FLIGHT ICING EMERGENCY EXIT OF AIRCRAFT SPINS OTHER EMERGENCIES 3 2 IVIUUI It Y M20R PAGE 3 14 3 14 3 15 3 16 3 16 ISSUED 6 94 ...

Page 40: ...sible to haveaprocedure forall types ofemergencies that may occur It Isthe pilot s responsibility to use sound judgement based On experience and knowledge of the aircraft to determine the bestcourse ofaction Therefore ItIsconsidered mandatorythatthe pilot read the entire manual especially this section before night When applicable emergency procedures associated with optional equipment such as Auto...

Page 41: ...DING WITH ENGINE POWER Aaps DOWN PRECAUTIONARY LANDING ABOVE 3200 LBS AapsDOWN EMERGENCY DESCENT GEAR UP Smooth Air Turbulent Air 3368 lb 1528 kg 3300 lb 1497 kg 2430 lb 1102 kg 22321b 1012 kg EMERGENCY DESCENT GEAR DOWN Smooth Air Turbulent Air 3368 lb 1528 kg 3300 lb 1497 kg 2430 lb 1102 kg 22321b 1012 kg RECOMMENDED SPEED 85 KIAS 80 KIAS Q1 5 KIAS 89 0 KIAS 84 5 KIAS 80 0 KIAS 127 KIAS 126 KIAS...

Page 42: ...ndicates power Is applied to heater Some Foreign NC AMBER light indicates power is NOT applied to heater Suction is below 4 25 in Hg RED Turn Stand by Vacuum pump ON Suction is above 5 5 in Hg RED Turn Stand by Vacuum pump ON I NOTE I Attitude and Directional Gyros are unreliable when VAC light is Illuminated steady or flashing Vacuum system 1 hould be checked and or adjusted as soon as practicabl...

Page 43: ...ixture may require enrlchening POWER LOSS IN FLIGHT RE START PROCEDURES I Airspeed Fuel Selector LOW Boost Pump Switch Throttle Propeller I Mixture Magneto Starter Switch LOW Boost Pump Switch HIGH BOOST Pump guarded switch Alternate Air Door 85 KIAS minimum SELECT OTHER TANK Verify fullest tank ON to attempt re start FULL FORWARD FULL FORWARD AS REQUIRED to restore power VERIFY on BOTH OFF if eng...

Page 44: ...n system Is displayed In the cockpit by the illumination of the ALTAIR light In the main annunciator panel Wlen operating on the alternate air system ava ilable engine power will be less for a given propeller RPM compared to the primary Induction air system This Is due to loss ofram effect and Induction ofwarmer inlet air The following checklist should be used if a partial power loss due to primar...

Page 45: ...OIL TEMPERATURE tNOTEt Prolonged high oil temperature Indications will usually be accompanied by a drop in oil pressure If oil pressure remains normal then a high temperature indication may be caused by a faulty gauge or thermocouple Airspeed INCREASE Power REDUCE PREPARE FOR POSSIBLE ENGINE FAILURE IF TEMPERATURE CONTINUES HIGH LOW OIL PRESSURE 011 temperature and pressure gauges Monitor Pressure...

Page 46: ...to Starter SWitch Cabin Ventilation Heating Controls CONTINUE cranking or until fire is extinguished 1500 RPM for several minutes INOTEI SHUTD0 1 N inspect for damage CONTINUE CRANKING I IDLE CUTOFF OFF FULL FORWARD OFF OFF OFF EXTINGUISH with Fire Extinguisher OFF CLOSED IDLE CUTOFF OFF CLOSED If fire is not extinguished attempt to Increase airflow over engine by increasing glide speed Proceed wi...

Page 47: ...escent at 196 KIAS Additionally descent at 165 KIAS will provide a smoother ride and less pilot work load THEREFORE The following procedure is recommended for an emergency descent Power RETARD INITIALLY Airspeed 140 KIAS Landing Gear EXTEND Airspeed INCREASE TO 165 KIAS after landing gear is extended IMng Aaps UP Airspeed MAINTAIN 165 KIA during descent __ Spiteueddebrakes l f inst alled EXTEND Al...

Page 48: ...pproach Airspeed 80 KIAS Use a flatter approach angle than normal with power as necessary until a smooth touch down Is assured Expect landing distance over a50 feet obstacle Ref SECTION VIto Increase at least 600ft Conduct Gear and Tire Servicing Inspection as required Ret SECTION VIII lSVSTEMS EMERGENCIES PROPELLER PROPELLER OVERSPEED Throttle Oil Pressure Propeller Airspeed Throttle FUEL LOW FUE...

Page 49: ...ng Gear Actuator Circuit Breaker PULL Landing Gear Switch DOWN Gear Manual Emergency Extension Mechanism LATCH FORWARD LEVER BACK to engage manual extension mechanism I NOTE I Slowly pull T handle 1 to 2 inches 2 5 to 5 1 em to rotate clutch mechanism and allow it to engage drive shaft T Handle PULL 12 to 2d times and RETURN until gear is down and locked GEAR DOWN light ILLUMINATED STOP when resis...

Page 50: ...e unreliable Push sland by vacuum pump switch ON TheI flashing Hi LO VAC annunciator light should extinguish and the STBYVAC annunciatorwill illuminate The vacuum operated gyro Instruments will be operaUng on the stand by vac uum system The steady RED annunciator light may not extinguish when the stand by vacuum switch Is ON Continue Hight monitor non vacuum gauges Have vacuum system inspected pri...

Page 51: ...nnal manner tAND AS 699 AS POssiBLE and sec re I Jag ag doo Baggage Door latching mechanism VERIFY MECHANISM PROPERLY ENGAGED Qnside latching mechanism then shut from outside aircraft I P INGI flflllll 1111111111 WARNING I 1 11 11 11 11111 l DO NOT OPERATE IN KNOWN ICING CONDITIONS The Model M20R Is NOT APPROVED for flight Into known Icing conditions and operation In that environment Is prohibited...

Page 52: ...retracted to maintain better pitch control Ry approach speed at least 15 knots faster than normal expect a higher stall speed resulting In higher touchdown speed with longer landing roll Use normal flare and touchdo n technique Missed approaches SHOULD BE AVOIDED whentNer possible because of severty re duced climb performance If a go around Is mandatory apply full power retract landing gearwhen ob...

Page 53: ...rogreulng Into a apln If an unusual post atall attitude develops and reaulta rn a apln1 quick appllcallon or antlapln procedures ahoultf anorten the recovery INTENTIONAL SPINS ARE PROHIBITED In the event of an Inadvertent spin the following recovery procedure should be used Throttle ADerons Rudder Control Wheel RETARD to IDLE NElJTRAL Apply FUU RUDDER opposite direction of spin FORWARD of neutral ...

Page 54: ...FORE TAXI TAXI BEFORE TAKEOFF TAKEOFF CLIMB CLIMB CRUISE CLIMB CLIMB BEST RATE CLIMB BEST ANGLE CRUISE FUEL TANK SELECTION OXYGEN SYSTEM DESCENT GEAR UP GEAR DOWN APPROACH FOR LANDING GO AROUND BALKED LANDING LANDING TAXI AFTER LANDING SHUTDOWN SECURING AIRCRAFT ISSUED 6 94 REV F 9 96 PAGE 4 3 4 4 4 5 4 7 4 8 4 9 4 9 4 9 4 9 4 10 4 10 4 11 4 11 4 11 4 11 4 12 4 11 4 12 4 13 4 13 4 13 4 14 4 14 4 1...

Page 55: ...SECTION N NORMAL PROCEDURES lTABLE OF CONTENTS con l l 4 2 MOONEY M20R ISSUED 6 94 ...

Page 56: ...tures of the airplane are presented These procedures are provided to present asource of reference and review and to supply Information on procedures which are the same for all aircraft PRats should familiarize themselves with the procedures given In this section In order to become proficient In the normal operations of the airplane Normal procedures associated wHh those optional systems and equipm...

Page 57: ...UP Best Rate of Climb Best Angle of Climb LANDING APPROACH 3200 lbs Nanna Approach Flaps 1odegrees Nanna Approach Flaps 33 degl l95 Short Field Approach Flaps 33 degrees BALKED LANDING 3200 lbs Maximum Power Flaps 10 deg 80 90 KIAS 75 KIAS 105 KIAS EIOKIAS 80 KIAS 75 KIAS 70 KIAS 85 KIAS MAXIMUM RECOMMENDED TURBULENT AIR PENETRATION SPEED 3368 lbs 1528 Kgs 121 K1AS 3200 lbs 1452 Kgs 123 KIAS 2900 ...

Page 58: ...l1 1d OFF Oxygen Pressure Gauge CHECK Verify adequate oxygen supply for trip If use of oxygen is anticipated refer to oxygen duration chart Fig 7 13 Also check that face masks and hoses are accessible and in good condition 2 Right Fuselage Tallcone Oxygen Filler Access Uoor and F1ller Cap Bat1ery 2 Access Panel Instrument Statlc Pressure Port General Skin Condition Tailcone Empennage Access Panel ...

Page 59: ... chock REMOVE Left Main Landing Gear shock discs tire doors INSPECT Fuel Tank Sump Drain DRAIN Use sampler cup to VERIFY fuel is free of water sediment other contamination VERIFY proper fuel BLUE 1 OOLL GREEN 1 00 octane CAUTION Some diesel may be BLUE Verify by smell and feel that 100LL Is being used VERIFY drain closes and does not leak Pilot System Drain 6 Left Cowl Area Windshield Cabin Air In...

Page 60: ...Aileron and attach points Wing Flap and attach points Control linkages 10 Bag gage Door Area Baggage Door REMOVE UNOBSTRUCTED INSPECT Lens Bulbs INSPECT INSPECT INSPECT INSPECT VERIFY SECURED VERIFY inside handle is properly secured CHECK outside handle operation RETURN TO COCKPIT MASTER ROCKER SWITCHES OFF IBEFORE STARTING CHECK I Preflight Inspection Seats Seat Belts Shoulder Harness 1 occupant ...

Page 61: ...TING ENGINE Recharge dead batteries for at least one hour at 3 4 amps before starting engine Only No 1 battery left side of tailcone Is connected to the Auxiliary Power plug Before starting Checklist Throttle COMPLETED FULLOPEN FULL AM High RPM Full Forward RICH Propeller Mixture Master SWitch Alternator Field SWitch Annunciator Lights Low Fuel Boost Pump Switch ON ON PRESS TO TEST All lights shou...

Page 62: ... engine starts Throttle IDLE 600 700 RPM SEE ENGINE STARr PROCEDURES ABOVE FOR REMAINING SEQUENCES IWARM ENGINE START I Throtlle 1 2 to 1 Inch OPEN Mixture Full Forward RIC Low Fuel Boost Pump Switch ON TO CLEAR FUEL VAPORS 1 Low Fuel Boost Pump Switch 0 Magneto starter Switch WlliiN 1 2 SECONDS TURN PUSH to STARr release to BOTH when engine starts Throttle IDLE 600 700 RPM SEE ENGINE STARr PROCED...

Page 63: ...ery depletion in prolonged taxi or holding position before takeoff increase RPM until uAMMETER indicates positive charge jBEFORE TAKEOFF Taxi Checklist COMPLETED Parking Brake SET Fuel Selector FULLEST TANK Throttle 1000 RPM Propeller HIGH RPM Mixture FULL FORWARD Alternate Air Verify CLOSED Alternator Field SWitch Veriry ON Throttle 2000 RPM Magneto SWitch CHECK BOlH to L BOTH lo R BOTH Verirv en...

Page 64: ...ant that the throttle be applied SLOWLY This will allow the aircraft to s1art rolling before high RPM Is developed and gravel orloose material will be blown back from the propellerarealns1ead ofbeing pulled Into it TAKEOFF NORMAL Power Annunciator Engine Instruments Lift Off Climb Speed Landing Gear Wng Aaps FULL THROTILE 2500 RPM CHECK CHECK for proper Indications As specified in SECTION 5 ITakeo...

Page 65: ...charts published in SECTION 5 Engine instruments CHECK JNOTEJ Careful leaning of mixture control will result In best ruel efficiency This requires operating at proper EGT Failure to do so will result in excessive fuel bum After leveling off at cruise altitude set RPM for desired power setting per Cruise Power Chart In Section V Slowly lean Mixture until EGT reaches peak value Enrichen to 50 F rich...

Page 66: ...xygen This automatically stops flow of oxygen from that outlet oJ ygen su pply contror Knob OFF when oxygen Is no longer required 11 ll 111111111111111 II WARNING II I IIIII lllf7IIIll Proper oxygen flow is critical to pilot passenger safety especially at altitudes above 20 000 ft MSL It Is Important to closely monitor the face mask hose 1 flow Indicator to ensure oxygen Is constantly flowing to t...

Page 67: ... It will require a minimum of one hour ot flight before a permissable landing weight Is attained when takeoffs are made at maximum gross weight If landing at a weight exceeding maximum landing weight 3200 Lbs 1452 Kgs Is required see OVERWEIGHT LANDING PROCEDURE SECTION Ill Seats Seat Belts Shoulder Harness ADJUST AND SECURE Internal External lights Landing Gear Mixture Propeller Fuel Boost Pump S...

Page 68: ...Information for reduced flap settings Is not available See SECTION V for Landing Distance tables I NOTEI If maximum performance landings are desired use above procedures except reduce approach airspeed to 70 KIAS flaps full down and apply maximum braking wHhout skidding tires during rollout I NOTEI Crosswind landings should be accomplished by using above procedures except maintain approach speed a...

Page 69: ...ch Radio Master Switch Electrical Switches Interior Light Switches Parking Brake Extended parking 0 Cabin Windows and Doors sHUTDOWN SET IDLE RPM OFF OFF OFF GROUNDING CHECK IDLE CUT OFF OFF OFF OFF lSECURING AIRCRAfTl VERIFY OFF Key removed VERIFY OFF Verily OFF VerifY OFF VERIFY OFF RELEASE INSTALL WHEEL CHOCKS CONTROL WHEEL SECURED with seat belts cabin vents closed CLOSED AND LOCKED TIE DO N A...

Page 70: ...ALTERNATE STATIC SYSTEM GEAR DN FLAPS ON STALL SPEED VS ANGLE OF BANK TAKEOFF DISTANCE HARD SURFACE TAKEOFF DISTANCE GRASS SURFACE RATE OF CLIMB MAX CLIMB RATE OF CLIMB CRUISE CLIMB TIME FUEL DISTANCE TO CLIMB MAX CLIMB TIME FUEL DISTANCE TO CLIMB CRUISE CLIMB CRUISE POWER SETTINGS AND FUEL FLOWS SPEED POWER VS ALTITUDE RANGE ENDURANCE TIME FUEL DISTANCE TO DESCEND LANDING DISTANCE HARD SURFACE LA...

Page 71: ...SECTIONV PERFORMANCE 5 2 fTABLE OF CONTENTS can t MOONEY M20R ISSUED 6 94 ...

Page 72: ...ffect of altitude and OAT on aircraft performance 1 Set altimeter to 29 92 and read pressure altitude 2 Using the OAT grid for the applicable chart read the corresponding effect of OAT on performance CAUTION NNNNN Be sure to retum to focal altimeter setting In calculating aircraft elevation above sea level OPERATIONAL PROCEDURES FOR MAXIMUM FUE EFFICIENCY For maximum fuel efficiency on the M20R pr...

Page 73: ...y 5 KTAS An approximate adjustment to range data shown in this manual can be made based on flight time planned with landing gear doors removed from aircraft For example using the above cruise speed decrease for a 5 hour flight will result in a decrease in r lnge of approximately 25 N M 5 HR X 5 KTS 25 N M reduction in range IMISSION PROFILE CHARTS I The Mission Profile Charts are presented as a fl...

Page 74: ...MOONEY M20R TEMPERATURE CONVERSION SECTION V PERFORMANCE ...

Page 75: ... COMPONENT CHART 12 EXAMPLE WlND SPEED 20 KNOTS ANGLE BET o EEN WIND DIRECTION AND FLIGHT PATH 35 HEADWIND COMPONENT 16 4 KNOTS CROSSWIND COMPONENT 11 2 KNOTS 1100 il ts 20 es 3D 35 40 45 so ss e o CROSSIV ND COMPONENT IN KNOTS 5 6 DEMONSTRATED CROSS WIND IS 13 KNOTS THIS IS NOT A LIMITATION ISSUED 6 94 ...

Page 76: ...F GEAR UP FLAPS UP N ITEI v 200 INDICATED AIRSPEED ASSUMES I ZERD INS TRUMENT ERRDR L90 t7 LBO v L70 t7 f 0 z L60 I 1 w L50 w 1 l H 140 v w EXAMPLE f L30 I GIVEN AS 129 KNDTS FIND CAS L30 KN ITS Ill J L20 0 1 I LO v 0 100 v 90 I 80 v 70 v 60 60 70 80 90 1 00 llO 1 20 130 140 50 160 1 70 180 1 90 200 IAS IN DICATED AIRSPEED KNOTS ISSUED 6 94 5 7 ...

Page 77: ...SPEED CALIBRATIDN PRIMARY STATIC SYSTEM GEAR AND FLAPS DDVN EXAMPLE GIVEN lAS 80 KTS FLAPS 10 PDVER OFF FrND1 CAS 79 KTS NOTE INDICATED AIRSPEED ASSUMES ZERO INSTRUMENT ERROR 1 1 SPEED FOR SAFELY LE FLAPS FLAPS 10 PDVER OFF FLAPS 10 PO ER llN FLAPS 33 POWER OFF J FLAPS 33 PDVER ON I v I 50 60 70 80 90 100 110 120 130 140 IAS INDICATED AIRSPEED KNOTS ERlNG ISSUED 6 94 ...

Page 78: ...1 0 60 1 5 1 2 2 0 70 0 0 2 2 3 2 80 1 8 3 2 4 5 90 2 8 4 0 6 0 100 3 0 4 7 7 4 110 3 0 5 4 8 8 120 3 0 130 3 6 140 4 5 150 5 1 160 5 6 170 6 1 180 6 5 190 7 2 200 7 9 NOTE The minus sign indicates subtraction of the given numbers from KIAS to obtain the corrected airspeed CONDITIONS Power ON Storm Window Vents CLOSED Heater Defroster ON or OFF ISSUED 6 94 5 9 ...

Page 79: ... 6 12 20 9 17 30 90 8 11 19 12 17 28 18 25 43 100 6 11 22 9 16 33 13 24 50 110 2 5 23 2 7 33 4 11 51 120 9 13 20 130 21 31 47 140 23 33 51 150 15 22 33 160 12 17 26 170 9 13 26 180 8 12 18 190 10 14 22 200 12 18 27 NOTE The minus sign indicates subtraction of the given numbers from the indicated pressure altitude to obtain correct altitude assuming zero instrument error EXAMPLE KIAS 110 ALTIMETER ...

Page 80: ... 0 20 29 0 31 45 80 13 23 32 19 34 47 29 51 72 90 23 32 48 33 47 71 50 72 108 100 27 42 66 39 62 97 8 94 148 110 30 53 87 43 78 127 6 119 194 120 32 48 72 130 53 77 118 140 57 84 127 150 9 102 155 160 82 128 182 170 95 139 211 180 107 158 248 190 126 185 282 200 146 215 327 NOTE The minus sign Indicates subtraction of the given numberfrom the indicated altitude to obtain the corrected altitude CON...

Page 81: ...5 79 0 93 5 94 0 3368 LBS GEAR DD w N 5 0 1528 KGS FLAPS 10 64 5 6 4 5 69 5 69 5 76 5 77 5 91 0 92 0 GEAR DD w N FLAPS 33 59 0 59 0 63 5 63 5 70 0 70 0 83 5 84 5 GEAR UP t z s FLAPS o 62 5 67 0 67 5 74 5 75 0 88 5 89 5 3000 LBS GEAR DD w N t Z 1361 KGS FLAPS 10 61 0 65 5 65 5 72 5 73 0 86 5 87 5 GEAR DO w N FLAPS 33 55 5 55 5 59 5 59 5 66 0 66 0 78 5 79 5 GEAR UP 59 0 59 5 63 5 64 0 70 0 70 5 83 5...

Page 82: ...TACLE sa I I I I I I I 30 20 10 D 10 20 3D 40 OUTSIDE AIR TEMPERATURE C DISTANCE NOTE 1 MAXIMUM DEMONSTRATED CROSSWIND IS 1J KNOTS 2 CONDmONS OF HIGH HUMIDITY CAN RESULT IN AN INCREASE OF UP TO 10 TO THE TAKEOFF DISTANCE 80 HUMIDilY IS STD I Vl 4500 r HOO 1 I fH l 1200 j 1 fl J 1 ll 3500 1 ll t v ti 0 I b t l 1000 r JOOO 1 1 p vv 00 I l 800 w f r I II VV u 1 z I _l_ 20000 1 600 r I j_ l Cl _ 1500 ...

Page 83: ...RF SHORT DRY GRASS oSi LE VEL II I 11 ll_v I I I 71 1 I I rvY 3000 1 1 17 c If 1 2600 OAT PRESSURE 5000 FT ALTITUDE If WEIGHT 3 250 l 8S 1474 KGS 000 HE C MND 5 KTS lr r N COMPONENT GROUND ROLL 1745 FT 532 M J I 1 500 TOTAL TAKEOFF 3095 FT 943 M 1 i i r i 1 1 I v DISTANCE 50 FT OBSTACLE I r r 1000 I I r r _ 000 I 30 20 10 0 10 20 30 40 5 3365 3100 2900 2700 0 10 20 0 50 15 3 M OUTSIDE AIR TEMPERAT...

Page 84: ... v I __ v 1 2000 FT I I e 1 v 4000 FT K v v PRESSURE ALTITUDE 6 1oo FT1 v I v I I I _ 7 8000 FT I I I _ _ 7 1 10000 FT I I r fJ 1 12000 FT r lj r _ v I I I 1 14000 FT I I I N r t 1 v v 1 1 1 f 1yoo FT r fJ _ r r v L 18 00 IFT r r r 1 1 o 2f00f 7 r D 1 r u 1 1500 1400 1300 1200 1100z 1000 900 I 800 ID 700 600 LL 0 500 400 300 200 100 0 80 60 40 20 0 20 40 OUTSIDE AIR TEMPERATURE C 1 I I I I 3368 WE...

Page 85: ...CLIMB 92 3 FPM PRESSURE AnTUDE leo tevt _ 2000 FT r I I r 1 4000 FT I I i l I r 6000 7 I I 8000 FT rj I I I 1 100 0 FT _ 1 r 12000 FT f r 14000 FT H N I 40 2 40 60 OUTSIDE AIR TEMPERATURE C v v l v i v I I 1 _ _ r f r k _f f I kt f _ 1 I 3300 3200 3100 3000 QOO 2800 2700 2E 3368 WEIGHT LBS 1500 1450 1400 1350 1300 1250 1200 WEIGHT KGS 0 mm 0 Tl i 1500 o oO 1400 s Z z 1300 m 1200 1100z 0 I u 800 c ...

Page 86: ...KG 11 I 12600 l BS 1 179 KG li 11 7 1 I I A v I I EXAMPLE I I I I I I J l l v DEPARTURE PRESS ALT 1 000 FT I I I DEPARTURE OAT 30 C I I J I CRUISE PRESS ALT 12 000 FT CRUISE OAT 10 C I r J I WEIGHT 3200 LBS I I FUEL TO CLIMB 5 0 0 4 4 6 GAL I j ll i I TIME TO CLIMB 19 0 0 8 18 2 MIN I I DISTANCE TO CLIMB 37 2 1 7 35 5 NM I I f i I I I I I I II I I I I i I o s 1o 15 20 25 30 35 40 45 so ss 60 65 70...

Page 87: ... KG f c l 0 f I I I t j V _ OISTAI IC l 1 I IV v _ 1 I I v r I v v I EXAMPLE v r v DEPARTURE PRESS ALT 1 000 FT I DEPARTURE OAT 30 C CRUISE PRESS ALT 8 000 FT V ll CRUISE OAT 10 0 WEIGHT 3200 FUEL TO CUMB 4 3 o 4 3 9 GAL fi TlhlE TO CUMB 14 4 1 0 13 4 MIN DISTANCE TO CUMB 30 8 2 3 28 5 Nhl I 0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100 FUEL GALLONS TIME MINUTES DISTANCE NAUTICAL M...

Page 88: ...0 21000 11 C 52 F 27 0 25 7 24 8 23 8 22 6 22 0 21 1 20 0 19 1 18 2 17 3 16 2 15 4 14 6 41000 7 C 45 F 25 2 24 2 23 2 22 3 21 7 20 8 19 7 18 7 17 7 16 8 15 7 14 9 14 3 61000 3 C 38 F 24 7 23 6 22 8 22 0 21 2 20 3 19 2 18 2 17 2 16 3 15 3 14 6 14 0 81000 1 C 31 F 22 5 21 7 20 7 19 8 18 7 17 7 16 8 16 0 14 9 14 2 13 7 101000 5 C 23 F 20 2 19 3 18 2 17 2 16 4 15 8 14 6 13 9 13 4 121000 9 C 16 F 19 5 ...

Page 89: ...EXAMPLE PRESS ALT 6 000 FT OAT 25 oc POWER 75 AIRSPEED 178 KTAS v v t v 0 l x sCJ 1 r v f v I f I e I 80 60 40 20 0 20 40 60 120 140 v I I II _ I j_ _ v v v 7 7_ 2 I J v v I o lj lL l 1 0 1 f 160 180 OUTSIDE AIR TEMPERATURE C TRUE AIRSPEED KNOTS L 0 _ 0 0 I B e t I La 200 Ul tl m m c tl m a l c c m 0 mm oo IIz z m s 0 s O NZ 1 ...

Page 90: ...IJNliHY I I I J II I I I I 41 57 5 1 L liJivI J II 1 v EXAMPLE i J J j PRESS ALT 10000 FT I IJAT I C I I I 1 II 1ll Pll WE R 657 PWR 2400 RPM BEST Pll IE R l 111I J J j RANGE 97D N M 1795 oo J ssr 1 rss 1 1 I I I vI f v J v I I II J t l 4 rtf f 1 t j _ II I I I I I 1 I I I 65 IJ u z I 1 1 V1 I Jl I I I I I I I Y I I I I II 1 I j I f jr 1 1 jS I II I i l v 1 1l I I V 1 lllft_ ss J k5r j I I I I IRI...

Page 91: ... S to nao rd Do y 3200 LBS 1452 KGS 2400 RPM 75X thru 45X PDVER SETTINGS I I I 1 t I I I 2500 RPM 85X PO w ER SETTING 1 BEST POVER 45X 45X BEST ECONOMY I I I lL v v lJr v v t v __ _ 7 I I 7 t _l v EXAMPLE PRESS ALT 11000 FT PO w ER 65 2400 RPM 3EST POWER ENDURANCE 5 65 HOURS Sea 2 4 s w m Level PRESSURE ALTITUDE FEETxlOOO 3 I 65X ssx l I 657 l SSY I I 75Y I ll i II sx I I i s lf f asla I I ll I I ...

Page 92: ...T LANDING GEAR UP FLAPS UP MIXTURE LEAN TO BLUE ARC or ENRICHEN FOR SMOOTHNESS EXAMPLE INITIAL PRESSURE ALTo FINAL PRESSURE ALTo 18000 4000 TIME TD DESCEND 24 0 5 0 19 MINUTES FUEL TO DESCEND 3 6 0 7 2 9 GALLONS DISTANCE TO DESCEND 69 0 13 0 56 0 NAUTICAL MILES 30 35 I I I 0 1 0 2 0 3 0 4 0 5 0 6 0 FUEL GALLONS Liters Gal X 3 795 tt I I 1 0 20 40 60 BO 100 DISTANCE No utlco l Miles KM N M X 1 852 ...

Page 93: ...4000 f 1 1 r 1200 llAT C5 0 c L r i PRESSURE 6000 FT 1 11 r PL TlTUDE 1 DOD 1 P1 ll i L a W EIGHT 2 800 LBS LE 7D KG lj O i l 3000 5 HEAIJI ND S KTS L L 1 i COMPONENT BOO s ii1 1 1 GR JJND ROLL 350 FT 411 Ml L TOTAL LANDING 2800 FT C853 fC s 2000 600 IDSTANCE SO FT OBSTACLE 5 400 1 1000 200 0 0 30 EO 10 0 10 20 30 4 1 0 32oo rooo 211oo a oo 0 lO 20 50 152 M l 0 OUTSIDE AIR TE of ERATURE oc IIElGHT...

Page 94: ...IL polo 1 I 4000 1 I I I ll r l r r 1 IJ 1200 DAT 0 c r r u F z t f l PRESSURE 6000 FT 1 ooo t I ALTITUDE 1 1 r r c 1000 I EIGHT 2800 LBS 1270 KGS 1 r F 1 r 3000i l HEAD lND 5 KTS 1 r I SF r t k I soo8 COMPONENT I J GROUND ROLL 1650 F T 503 K 8 2000 TOTAL LANDO IIG 3100 FT C9 1 600 D1STAr E C O F T DBS TACLE J 400 i 1000 CEll 0 0 31 ro to 0 10 l ll 30 o so 3200 3noo esoo 26D I 0 II 2jJ 50 1 5 2 M ...

Page 95: ...Fuel _ n 1 tWil l nnun l UI UUIIIIU IUAJ IOKeOTT MCX t OWe r limO 0n0 Uescent 11 500 FT 1 45k 55 I 1 26 HRS 15 4 GAL 55 1 I I I 65 v I I lA r 1 t t 1 1 ll 1 I I 75 1 1 I I I I I It I I I I I I l I I I i I I I I I I I 4 I 55 I I I 65 75 _ 1 l l l I S L 2 4 6 8 10 12 14 16 18 20 PRESSURE ALTITUDE FT x 1 000 1 0 1 1 1 2 1 3 1 4 1 5 1 6 1 7 TOTAL MISSION TIME HOURS 1 8 12 14 16 18 20 22 TOTAL FUEL USE...

Page 96: ...l Missions Profiles Allow for W l lroUI I JYI IIO o V I t _ uA ruwcr vurr1u una uescent 5 I 11 500 FT 45 55 v I 2 47 HRS 29 6 GAL I li 55 55 v 65 1 65 t I v 1 Vt I I I I I _ I 75 1 ll 75 i 1 I I I f 1 il I I I I I I 1 1 I r I I I I 1 1 I S L 2 4 6 8 10 12 14 16 18 20 2 3 2 4 2 5 2 6 2 7 2 8 2 9 3 0 3 1 24 28 32 36 40 44 PRESSURE ALTITUDE FT x 1 000 TOTAL MISSION TIME HOURS TOTAL FUEL USED GALLONS ...

Page 97: ...ters 74 Imp Gol Usable Fuel n u oc u11 muA ruwe r limo_ ono uescent I l I I 11 500 FT 45 45 557 v I 3 68 HRS 43 9 GAL v 55 55 v I 1 65 v 1 1 1 l4 _ I 1 1 r I I 1 1 1 I I 75 I 1 1 1 I J I I I I I 1 I I I I I I I I il i I f I r 65 75 i I i S L 2 4 6 8 10 12 14 16 18 20 3 2 3 4 3 6 3 6 4 0 4 2 4 4 4 6 4 B 3B 42 46 50 54 56 PRESSURE ALTITUDE FT x 1 000 TOTAL MISSION TIME HOURS TOTAL FUEL USED GALLONS ...

Page 98: ...Profiles Allow for W I l r l VII IIIV o HIU lJ t Ot f H I I lsJ 11 500 FT I 457 55 I 4 89 HRS 1 58 3 GAL v 557 557 1 v 1 7 1 65 v 1 1 lA __ __ r I ll l 1 I 1 f 1 I I r I 75 I 75 I I r f f l I I I I I I 1 1 1 I _ I I j i r l lr I 1 tl 1 1 S L 2 4 6 8 10 12 14 16 18 20 4 5 4 7 4 9 5 1 5 3 5 5 5 7 5 9 6 1 48 56 64 72 80 88 PRESSURE ALTITUDE FT x 1 000 TOTAL MISSION TIME HOURS TOTAL FUEL USED GALLONS ...

Page 99: ...SECTION V PERFORMANCE 5 30 BLANK MOONEY M20R ISSUED 6 94 ...

Page 100: ...ITY UMITS 6 9 FIXED BALLAST 6 10 EQUIPMENT UST 6 10 NOTE The empty weight center or gravity and equipment list lor the airplane as delivered from MooneyAircraft Corporntlon Is contained In this section The use olthlssection Is valid for usa with the airplane ldentlfled below when ap proved by Mooney Aircraft Corporation MOONEY M20R AIRCRAFT SERIALNO ___ l _ Cf 00 f S ______ AIRCRAFT REGISTRATION N...

Page 101: ...nt weight and balaf1ce status or the airplane lor load scheduling The weight and balance data entered as your alrcraftlelt the factory plus the record you maintain on page 6 5 Is all of the data needed to compute loading schedules The maximum cenlncated ross weight forthe TCM powered M20R Is 336Bibs 1528 Kg for Takeofla nd 3200 pounds t452 Kgs for Landing Maximum useful load Is determlneo by subtr...

Page 102: ...ob from cantor ot nose gear trunlon retracting pivot axis to the fioor Mark the point of Intersection 10 Locate center line of nose wheel axle and main wheel axles In the same manner 11 Measure the horlzon a l distance from tho reference point to main wheel axle centerline Measure horizontal dlstilnoe from center line of nose wheel axle to center line of main wheel axles 12 Record weights and meas...

Page 103: ... twun To bJl wright CG F or ward ol Mo ln o nol Nos IJhe l o Alrcrolt Mn1n hw lc Axt Ctnter s Wr LH 9 b CG Af t oF Do tUPI Sta tlol l 0 1 ____Jn c l l l lM J3 ln 3 0 Cl l 330 ___ ln cM MI ln tM 1 11 1 Dlsto nc e FroM Center Dlstancf rol l N e Result ol CG crus STA Nose Gtor Trunlon 1o Gto r TDruNon to DatuM Co puta tbn DISto nce Aft ol DAtUM c nter of Mo ln IJhel l Abovr EMpty W Ight CG Axles CHar...

Page 104: ...X165 55179 5 70 K 14 40 82 08 GPS KLN90B 20518 6 30 X 14 40 90 72 Transponder KT76A 133066 3 10 X 14 40 44 64 GPS Ann 810435 501 0006 1 10 X 16 50 18 15 GPS Ant KA92 01727 0 60 X 117 96 70 78 TXP Ant Cl105 N A 0 40 X 41 50 16 60 Encoder AT3000 0018195 0 50 X 4 00 2 00 X X X X X INSTALLED ITEMS Com Nav GPS GTN750 1ZA010052 7 80 X 14 40 112 32 Transponder GTX33 89121556 3 60 X 128 00 460 80 GPSAnt G...

Page 105: ...IGHT YT ARM YT ARM H MOMENT ARM USEF UL CLBS CINCHES LBS INCHES LBS 1000 IN LOAD Kg c 1 1 CKg cr ro Kg Cr C I PI 15 q q BASIC EMPTY WEIGHT AS DELIVERED It Jnc lud s f ull oil Q ts Liters It ilon 1o 14 I 1 9i l 12 1 AvinAh TiiiiLLAT oiV 1 8 0 1 12 5 IBJ7 llno f Y i t 3h iln5 CHult lnChC s bV 25 T ar 1 1 CHult lnch s by 2 54 Fot Cr CMult pounds by 4 536 or Kg 0 j m II C i5 i z 0 m II m 0 0 II 0 1 JQ...

Page 106: ...or co pilot and enter these weights and moment 1000 values In the proper sub columns In the Problem Form on page 6 7 Step 3 Proceed asln Step2 to accountfortho passengers In seats 3and 4 Enterthe weight and value of moment 1000 In the proper columns Step 4 Again proceed as In Step 2to account for the amount offuel carried and enterthe weight and moment 1000 values In the proper columns Step 5 Once...

Page 107: ...3 20 59 17 87 9 011 120 Lbs 4 4 cm 0Sio I01 45 4 10 11 70 1015 S at Rock Mo l 10 Lbs 4 54 K9 0Sio 126 320 em 6 7 8 9 Loaded A C W lghl Tokeoll at Max Welghl 1526 A C will hov to burn oU 166 lbs h 1el 190 2 16 0 before normal landing is accomplished 3366 Required Fuel Burn Off 28 CQIS 105 9 li 0 6 lb Gol 76 2 9 5J 8 27 166 MAXIMUM LANDINC WEICHT al A C 1452 160 6 156 7 J200 e KJ gon Oro Ov c l lof2...

Page 108: ...0 r l 154 17 7 145 2 v II II 1452 3200 J 1400 II I I A C LOADED WITHIN THIS AREA 3000 L E ABOVE NORMAL APPROVED I ANOING WEIGHT fUEL t IUST BE 1 BliRNEO OFf PRIOR TO NQRI IAl J LANDING 0 ij 2900 1 300 IF I u 2800 I 1 0 0 I 2700 II I _J 1200 J 7 2600 I v 2500 9 6 J 1 1100 24301 1 2400 II I J 2300 1 I 1000 220 J II 2100 J J I I 907 2000 I I 70 90 110 130 150 170 190 LOAD AIRCRAFT MOMENT I 000 POUND ...

Page 109: ...2000 907 LOADED RCRAFT WEICHT 41 ISSUED 6 94 SECTION VI WEIGHT AND BALANCE M20R CENTER OF GRAVITY UMITS ENVELOPE I 1 1100 1150 1200 1250 I JlCR IfT CC UlOOOII Q IIY Ill a MI SIA 0 0 lli J l 1 I 3300 1 J AFT IMIT I J 1 j 1 2430 FORWARD UMI G G AIRCIWT CG LOCA lr fO INtHES NT a OAl 111 St 0 0 IJOO 50 61 MRCG UM JJ lis 6 9 ...

Page 110: ...ly those Items having an X In the Mark If Installed column and dated were Installed at Mooney Aircraft Corporation at the time of manufacture If addHional equipment Is to be Installed Hmust be done In accordance wfth the reference drawing or aseparate FAA approval INOTE Posi MI arms ara distances aft of the airplane datum Negative arms ara distances foiWIInS of the airplane datum Astertsks r after...

Page 111: ...ION DRA v ING Kg POUNDS A FIXED BALLAST VEIGHT 501 INSTU 350203 2 81 6 2 VEIGHT 503 INSTU 350203 6 08 13 4 VEIGHT 505 INSTU 350203 8 94 19 7 MO DAY YEAR ARM CM CINCHES li532 D 209 50 532 1 209 50 532 1 209 50 5 J 15 MARK IF NSTALLED X s s 0 oo xlz E m C5 I z ocn mm Q o zz C m ...

Page 112: ...TARTER ALT NR VAC PUMP EXH INDUCT SYST ALT AIR ENG MT FULL OIL PROP GOV 600270 249 3 549 5 PROPELLER CONSTANT SPEED McCAULEY HUB 3A32C418 680030 34 7 76 6 BLADES ot 82NRC 9 w SPINNER Refer to Section I II f r engine propeller f onfiguration MO DAY YEAR ARM CCM In 159 16 23 29 125 7 49 5 5 1 rr5 MARK IF INSTLD X X I ECil mm C l Cil J o lz z_ c lJl m s 0 0 z II ...

Page 113: ...m c J 2 J EQU f JMEN I LIST M EQ 82 ITEM ITEM REF WEIGHT NO DESCRIPTION DRAWING Kg POUNDS B POWERPLANT ACCESSORIES con t MO DAY YEAR ARM l cm INCHES 6 i CfS MARK IF INSTALLED s s gO JJO z G5 z ccn mm o zz 0 m ...

Page 114: ...STALL IJARNING INDICATOR 800311 45 1 0 GEAR w ARNING INDICATOR 800311 45 1 0 IJING TIP STROBE LIGHT INSTL 800311 2 27 5 0 TAIL STROBE LIGHT INSTL 800311 68 1 5 LANDING TAXI LIGHTS 2 SETS 210417 2 7 5 88 ACTUATOR FLAPS 750110 2 3 5 1 ACTUATOR LANDING GEAR 560260 5 08 11 2 MD DAY YEAR ARM CI INCHES 370 8 146 0 41 28 16 25 106 3 41 85 49 53 19 5 38 1 15 0 127 0 50 0 49 53 19 5 134 62 53 0 578 7 227 8...

Page 115: ...g CPOUNDS c ELECTRICAL SYSTEM CCON T E L T CD II M ELT 8 810152 1 63 3 59 E L T CARTEX ELT110 4 810150 2 26 4 98 E L T CARTEX ELS 10 810150 2 95 6 5 E L T CAMERI KIN 810436 1 41 3 1 tw __ MD 5 DAY q YEAR qs ARM MARK IF C M CINCHES NSTALLED 337 8 133 0 436 8 172 0 K 407 7 160 5 429 0 168 9 s s 1 lQ 00 Oz G5 I 1 zen om mo S o zz 0 m_ ...

Page 116: ... TIRES MAIN 2 E PLY RATING 520029 7 7 6 00 X 6 TYPE El WI TUBES NOSE v HEEL ASSE BL Y 540000 1 18 TIRE NOSE ll E PLY RATING 3 18 5 00 X 5 TYPE Ill W TUBE 540000 MASTER CYLINDER BRAKE 2 850109 1 36 VALVE PARKING BRAKE 850109 27 DUAL PUCK BRAKE ASSEMBLY 2 520029 35 POUNDS Ccro 163 57 13 72 ll O 162 51l 153 74 1 8 162 51 17 0 33 8 2 6 33 8 7 0 21 08 3 0 6 3 68 2 98 168 48 INCHES 64 4 63 98 60 53 63 9...

Page 117: ...0 m G M EQ 02 ITEM NO I I cUUif JMI _N I Ll I ITEM REF DESCRIPTION DRAWING Kg D WHEELS TIRES 6 BRAKES con t I l MO DAY YEAR WEIGHT ARM POUNDS em INCHES I I I MARK IF INSTALLED I I s s t IQ co oz I G5 I t zen em g zz m_ ...

Page 118: ...AT GAUGE 25 55 INDICATOR VERTICA_ SPEED 23 5 INDICATOR TURN So SLIP TURN COORD 83 1 84 ALTIMETER 2J 49 1 07 INDICATOR AIRSPEED 32 70 TACHOMETER 36 8 FUEL FLO W 63 1 39 ENGINE GAUGES DUAL CLUSTERS 820336 1 6 3 5 MO DAY YEAR ARM CI l INCHES 44 3 17 46 42 7 16 8 49 78 19 6 46 99 18 5 44 9 17 67 41 91 16 5 36 0 14 17 47 75 18 8 48 13 18 95 46 99 18 48 46 99 18 5 f iS MARK IF NSTALLED X X X X X X X E I...

Page 119: ...ING O g POUNDS E INSTR NTS CDN T ANNUNCIATOR PANEL 820336 58 1 3 MAGNETIC COMPASS 130323 23 5 HANIF DLD PRESSURE 820336 45 1 0 ALTERNATE STAT C AIR SOURCE 820336 14 31 MO DAY YEAR ARM Cf l INCHES 44 45 17 9 60 6 23 87 46 94 18 48 44 69 18 5 f 5 MARK IF NSTALLED X X X X I s s 0 oo Oz G I i ocn mm 0 s g zz 0 m_ ...

Page 120: ...D BY VACUUM PUMP CLUTCHl 860015 2 45 5 41 860063 5 44 12 0 STAND BY VACUUM PUMP TAlLCONEl OXYGEN SYSTEM 115 7 CCI ft 870029 20 2 44 55 DESCENT RATE CONTROL VACUUM 950155 5 59 12 32 DESCENT RATE CONTROL ELECTRIC 950271 5 8 2 8 PROPELLER DE ICE ELECTRIC 690003 2 69 5 93 MO DAY YEAR ARM cnl INCHESl 2 54 1 0 7 6 3 0 6 4 2 5 280 42 110 4 347 9 137 0 lf 70 0 l lf t 70 0 C 15 6 45 5 S q qs MARK IF NSTALL...

Page 121: ...Kgl POUNDSl G CABIN ACCOMODATIONS SUN VISORS 2l 130303 32 1 0 RESTRAINT ASSY REAR 2l 40318 227 5 0 IRESTRAINT ASSY F JD 2 140319 2 27l 5 0 SEAT BELT ASSY REAR 2 140262 1 36 3 0 f t MD 5 DAY f YEAR 1 I ARM MARK IF CI I NSTALLED INCHES 83 8 33 0 X 194 3 X 76 48 106 7 X 42 0 180 3 X 71 0 s s 1 JQ co Oz G5 c t z 0 CJm 0 zz m_ ...

Page 122: ...KING KCS 55A 810150 5 14 11 34 Cl68 8ll 66 46 KING KMA 24 810150 77 1 7 48 26 19 0 TERRA ENCODER 810150 C 23l 50 30 48 12 0 KING KLN 90B 1 S 810434 3 13 6 9 59 44 23 4 DAVID CLARK ISDCOM 810150 C 32l 70 43 18 17 0 KING KX 155 810150 2 3 5 1 36 65 14 43 KING KX 165 810150 2 6 5 7 36 53 14 38 KING KI 203 810150 73 1 6 38 1 15 0 KING KR 87 w KI 229 810150 3 6J 8 0 Cll2 4 44 25 KING KR 87 810150 2 4 5...

Page 123: ...50 13 4 29 5 KING KRB7 w KI227 810150 2 67 5 9 KING KLN89B 810434 1 43 3 15 INSIGHT STRIKE FINDE R 810430 2 0 4 35 INSIGHT GEM MJDE l 602 950248 1 20 2 6 GARMIN 155 GPS 810433 1 0 2 2 DRE SYMPHONY INTE RCOM 810202 55 1 22 INTE RCOM CtiUITE FUTD 810150 23 5 MO DAY YEAR ARM CM CINCHES 38 1 15 0 37 1 14 6 204 0 80 3 136 1 53 6 86 7 34 13 C220 D 86 6 7 6 3 0 36 5 14 38 81 28 32 0 C4B 3 19 0 5 t i5 MAR...

Page 124: ...1 3 2 8 45 7 18 0 AA80 INTER VOX 810202 32 43 2 17 0 J 7 AA83 INTER V JX CMUSID 810202 32 7 C43 2 17 0 w X10 10A 810413 5 6 12 3 C245 D 96 5 w X1000 1000 SERIES III 810197 J O 10 9 283 3 111 5 KAP 150 PA CKFC 150 830081 13 2 206 5 82 6 29 1 KAS297B ALT PRESELECT 830081 1 4 29 7 3 1 11 7 EHIS 40 810247 Cl J tD 34 9 C226 D 81 3 KRA 10 RADAR ALT 810150 j Cl f 3 8 14 7 4 58 8 FUEL FLO w SHAD N 820336 ...

Page 125: ...E 810150 1 81 4 0 38H KING KX155A 810150 1 59 39H KING KI 204 810150 77 1 7 40H KING KT 76C 810150 1 09 2 4 41H BOSE HEADSET w INTERFACD 810150 42H PMA 7000MS 810150 1 0 2 2 43H 44H 45H 46H 47H LOCATION WILL VARY MO DAY YEAR ARM CJY1 CINCHES 36 9 14 54 C36 9 14 54 38 1 15 0 38 1 15 0 I 73 7 29 0 15 MARK IF NSTALLEDi X s s NQ oo aJz Gi I t z om l tl I s o zz m_ ...

Page 126: ... SAMPLER Cl P CSTDIJED 04 05 BAGGAGE TIE DCIJNS C2 CSTCioiED 04 1 CARGO RESTRAINT BELTS C2 CSTDIJE 27 1 0 PITDT COVER CSTJIJED 03 3 POH AFH No HIJDNEY 84 1 5 ENGINE OPERATIJR S MANUAL t YCI Jioi N 35 5 ENGINE LOG BCCIC 07 2 AIRFRAME LCG BOOK 01003 0 3 2 1 S r t MO 5 DAY 9 YEAR 15 ARM MARK IF CPI INCHES NSTALLED C273J 107 5 X 332 7 131 0 X 332 7 131 0 X 332 7 131 0 X 332 7 131 0 X 332 7 131 0 X C33...

Page 127: ...ERENCE RECOGNITmN LIGHT INST C2 210413 60 1 32 134 6 53 0 1 RUDDER PEDAL EXTENSION INSTL or 2 720115 059 13 38 1 15 0 AUX POYER RECPT INSTL 800166 L48 3 27 332 7 131 D AUX PC WER CABLE ADAPTER 880042 3 43 7 57 DUAL BRAKE INSTL 95m12 L38 3 05 38J 15 0 STATIC DISCHARGE INST 950253 N GLIG1BL DIF F ERENCE STEP ASSY S INSTL 950256 L25 2 75 274 3 108 0 FIRE EXTINGUISHER INSTL 130328 1 20 2 65 153 7 60 5...

Page 128: ...140323 ICJ 3 47 HEADREST NSTL FRONT 140313 140323 1 57 3 47 SKYMAP 810218 Ctl D 19 2 DEFROSTER BLOVER 640314 39 87 3 PASSENGER REAR BENCH SEAT 140305 NO CHANGE TKS AIRFRAMEI WINGS 690007 Cl6 8 36 5 TKS PROPELLER CKNDI N ICING 690007 18 39 8 TKS FLUID C6 GAL 690007 25 0 55 2 I X 950 STORMSCOPE 810437 2 7 5 9 MD DAY YEAR ARM Cr CINCHES 457 2 180 0 457 2 180 0 62 67 24 75 203 20 80 0 114 3 45 0 159 2...

Page 129: ... JMlN I Ll I MR EQ J3 ITEM ITEM REF WEIGHT DESCR PTION DRA v ING Kg NO POUNDS J OPTIONAL EQUIPMENT CON T 25J 26J 27J 28J 29J 30J 31J 32J 33J 34J A MO DAY YEAR ARM MARK IF en NSTALLED INCHES i s s I Q co oz G5 t m zen om Ill I a zz m ...

Page 130: ... CIJ c m c M EQ J3 ITEM NO EQUIPMENT LIS T ITEM REF WEIGHT DESCRIPTION DRAW ING Kgl POUNDS __ J _ OPTIONAL EQUIPMENT CDN Tl MD DAY YEAR ARM eM INCHES MARK IF NSTALLED I I en Gl j to tz s 0 z m s 0 s O 1 z ...

Page 131: ...NG AND GROUND HANDLING LANDING GEAR CONSTRUCTION RETRACTION SYSTEM WHEEL BRAKES EMERGENCY EXTENSION SYSTEM WARNING SYSTEM STEERING CABIN BAGGAGE COMPARTMENT CARGO RESTRAINT SEATS SEAT BELTS SAFETY HARNESS DOORS WINDOWS EXITS CABIN DOOR PILOT S WINDOW EMERGENCY EXITS ENGINE GENERAL ENGINE CONTROLS ENGINE INSTRUMENTS ENGINE OPERATION AND CARE OILSYSTEM ISSUED6 94 REV G PAGE 7 3 7 3 7 3 7 3 7 3 7 4 7...

Page 132: ... FUEL SYSTEM ELECTRICAL SYSTEM ALTERNATOR BATTERY SCHEMATIC ANNUNCIATOR PANEL CIRCUIT BREAKER PANEL ELT PANEL LIGHTING SYSTEM CABIN ENVIRONMENT PITOT PRESSURE STATIC SYSTEM STALL WARNING SYSTEM OXYGEN SYSTEM VACUUM SYSTEM EMERGENCY LOCATOR TRANSMITTER E L T REMOTE SWITCH OPERATION 7 2 REV G MOONEY M20R PAGE 7 20 7 20 7 20 7 20 7 21 7 21 7 21 7 21 7 22 7 22 7 23 7 23 7 24 7 25 7 25 7 25 7 25 7 26 7...

Page 133: ...neuvering Hydraulic disc brakes and a steerable nose wheel aid In dlrectlcma control during taxiing and ground operations The landing gear Is electrically retracted and extended Awarning horn a gear position Indicator on the floorboard and a green GEAR DOWN light help prevent Inadver tent ge r up landings Amanual emergency gear extension system Is provfded In the event of electrical failure IF UGH...

Page 134: ...eri more leftof neutral poSition Wing Flaps The wing flaps are electrically operated and Interconnected through a torque tube and bellcranks Total flap area Is 17 98 square feet Nominal travel Is 0 to 33 Umlt switches prevent travel beyond these limits Wing flap position Is controlled by a pre select switch located on the lower center console Also located on the center console Is a flag position I...

Page 135: ...rmal time 1 CLOCK S N 29 0170 thru 29 0199 Refer to Figure 7 1Al The electric digital panel mountedDAVTRON Model BOO clock may be used and set by the following procedures The SEL button selects what is to be dlsP Iayed on the four digit window and the CTL button controls what Is being displayed Pressing select sequentially selects GMT Local Time Elapsed Time and back to GMT The confrol button star...

Page 136: ...OWN Select ETdisplay and enter set mode by pressing both buttons The countdown time can now be set Entering the time Is identical to GMT time selling Wlien the time is entered and the last digit is no tinge flashing the clock Is ready to start the countdown Momentarily_pressing the CTL button s1arts the countdown When lh ecount reaches zero the displays lash ana the external alarm is activated Pre...

Page 137: ...ld pressure gauge is of the direct reading type The gauge is calibrated in inches of mercury Hg and indicates the pressure in the induction air manifold 12 TACHOMETER 1 The tachometer is an electronic meter which counts ignition pulses The instrument is cali brated in engine revolutions per minute RPM 13 FUEL FLOW Fuel flow gauge an electric instrument operating from information provided by a fuel...

Page 138: ...dent the source system warning lilght on the annunciate then PUSH the MASTER WARN light contains a PUSH switch umfer the light MASTEn WARN light will extinguish for approx mately 2 minutes or until the next sysrem malfunction warninglight on the annunciator murr nates Repair Inoperable system prfor to next Hight ISWITCHES CONTROLS I 1 MAGNETO STARTER SWITCH Magneto Starter switch combines both ign...

Page 139: ...ed by circuit breakers in panel 11 GEAR SAFElY BY PASS SWITCH Gear Retraction Override Gear safety override switch is a manual means of electrically by passing the Airspeed Safety Switch In fhe event the landing gear switch Is placed In ge ll uv position a properly operating Airspeed Safety_Switch prevents gear from being retracted before takeoff speed of aQproxf mately 60 1 5 KTS Is reached To re...

Page 140: ...ents Pushing left side of spring loaded switch trims rudder left pushing right side of switch trims rudder right 16 RUDDER TRIM POSITION INDICATOR Rudder trim position is electrically indicated on an LED indicator located adjacent to switch Signal is transmitted to indicator thru a potentiometer attached to trim mectianism Position signal is transmitted to indicator by resistance readings 17 HIGH ...

Page 141: ...nob should not be turned IN any closer than 030 to 060 to panel nut face 24 MIXTURE CONTROL Mixture control allows pilot to adjust the fuel air ratio mixture of the engine Push control for ward to enrichen mixture Pull control full aftto close iille cutoff shutting down engine Control is a vernier type and fine adjustments of mixture can be obtained by turning knob clockwise to enrichen miXture an...

Page 142: ...instrument lights located in glareshield ON Continued turning clockwise increases light intensity 37 CIRCUIT BREAKER PANEL See details elsewhere in this Section 38 39 CO PILOT S HEADSET JACKS 40 41 PILOT S HEADSET JACKS 42 FUEL FLOW TOTALIZER INDICATOR FUEL MEMORY SWITCH Fuel Totall zer memory Is connected to the aircraft battery through a FUEL MEM ory switch Indicates fuel flow being used at give...

Page 143: ...iptions below Defective bulbs must be replaced prior to tnght Includes MASTER WARN light on S N 29 01 70 thru 29 0199 8 DIM SWITCH The DIM switch may be activated after the low fuel lights come on bright The switch will dim both low fuel lights but will not turn them off To restore display to bright press TEST swifch A 1 GEAR S AFETY INDI CATOR GEAR DOWN 2 GEAR SAFETY INDI CATOR GEAR UNSAFE A GEAR...

Page 144: ...or operation of attitude gyro and directional gyro Designated vacuum range is 4 25 I 25 to 5 5 2 0 0 inches of mercU YJHol The HI LOVAC llghlwlll BLINKWHEN VACUUM IS BELOW 4 25 ln Hg and Illuminate STEA DY WHEN VACUUM IS ABOVE 5 5 in Hg In either case gyros should not be considered reliable during this warning time Refer to Airborne Serv ice Lefler No 31 located in Section X 10 ALTVOLTS A RED ligh...

Page 145: ...sembly CAUTION Exceeding steering swivel angle limits may cause structura damage ILANDING GEAR I CONSTRUCTION Landing gear legs are constructed of chrome molybdenum tubular steel heat treated for greater strength and wear resistance Main gear leg attaching points pivot in bearing surfaces on forward and stub spars The nose gear mounts on cabin tubular steel frame and engine mount Rubber discs in a...

Page 146: ...een light shows conllnuously when landing gear Is fully extended The red light shows whenever landing gear is in transit or not locked down bul lsOFF when tanding gear Is fully retracted A visual gear position Indicator located on floorboard aft oflhe fuel selector shows that landing gearis down when indicatorma Ks align The geardown light is dimmed when navigation llghtr are turned on STEERING Ru...

Page 147: ...ESS Safety reslrainls if worn properly 1 occu pant per restraint keep occupants lirmly fn their seats during T 0 landfng1 turbulent air and during maneuvers The belts harnesses are mechanically simple and comfortable to wear The front seat inertia bells harnesses are attached to hardpofnts on side structure and seats The rear seal belts are attached to brackets firmly mounted to structural hard po...

Page 148: ...ngine Installed Is a Teledyne Continental Motors 10 550 G normally aspirated fuel injected engine The following designation describes engine I Denotes FUEL INJECTED 0 Denotes OPPOSED refers to the horizontally op_eosed cyJJnders 550 Denotes piston displacement In CUBIC INCHES G Denotes a specific equipment configuration Refer to TCDS for engine conflguratlon required The engine operates wUilthree ...

Page 149: ...llowed Poor maintenance re sults In faully engine performance and reduced service life Effictemt engine operation de mands careful attention to cleanliness of air fuel oil and maintaining operating temperatures within required limits Servicing of the engine should be accomplisned only by qualified per sonnel The minimum grade offuel for this engine Is 100LL or 100 octane avia ion gasoline If the g...

Page 150: ... left mag neto fires the upper P lugs on theleft and lower plugs on the rlght lhe magneto cases spark plugs harnesses anCl connections are shielded to prevent radFo Interference AIR INDUCTION SYSTEM The engine air Induction system conslst s of aNACA flush tYpe air r inletduct located on front oflower cowling The air inlet duct Incor porates the air filter housing This housing contains a throw away...

Page 151: ...el to the fuel manifold valve The assembly has three control units one fur alr ln the a lrth ottie assembly and two forthe fuel control unit The manifold valve receives fuel from the metering unit When fuel pressure reaches approxi mately 3 5 PSI a check valve opens and admits ftiel to six ports in lie manifold valve one port for each ftiel nozzle line The manifold valve also serves to provide a o...

Page 152: ... three blade metal constant speed unit Propeller rotational speed RPM Is maintained by a balance of air load oil pressure and engine rotational forces The propeller governor regulates aflow ofhigh pressure engine oil to a plston In the propellerdome The pis fen Is linked by a sliding rod and fork arrangement to proP eller blades Governor olt pressure acting on a piston and spring Increase propelle...

Page 153: ...plies electrical power for equipment operation The No 1 battery left side of lallcone is normally used asthe primary to sustain the electrical system and to start the aircraft The No 2 battery right side of tallcone Is normally considered as backup and Is kept in a fully charged condition by trickle charge through a diode system Should the No 1 battel be depletedtothe point of being unable to supp...

Page 154: ...AV 2 AUDIO PHONE 1JWISI Or O R EJ OO A N1f R c AV 51 UMin 1 lllT RCO vw r YAW OAAIPNER LOlW Hr ADstf lfFT tCADSCf RIGHT SPA SPAAt AFMR7 9 output voltage exceeds limits the overvoltage warning light illuminates steadily and the alter nator field circuit breaker trips Resetting the alternator field circuit breaker should reset alternator Ifthe circuit brea ker will not reset continueflightwith minim...

Page 155: ...ht control provides avionics _ 1 11 l and instrumenfl hling Rotating the knobs Ql Ql se turns N and Increases light ln L ___j MAP LIGHT FIGURE 7 10 CIRCUIT BREAKER PANEL TYPICAL The map light switch is located on the cen ter ofthe pirot s and co pilot s control wheel CABIN LIGHTING Two sets of overhead lights illuminate the cabin CAUTION The Cabin Light rocker switches are connected directly to ba...

Page 156: ...nt con trol s Ttiase controls mav be ad justed anywhere between full open and fuII closed OVERHEAD VENTILATION Cabin overhead ventilating system works Independently of cabin heat Ing and ventilating system Fresh air en1ers a NACA auot on dorsal fin and is controlled by Individual out lets above and between each seat A master air vent control regulates __ Klnon X1 T J flow of air through the indivi...

Page 157: ...vely a quanti Y gauge and a control kno below arm resf which is mechanically connected to he shutoff valve at the cylinder The suppi of oxygen can thus be shut off from the cockpit when not required When tlie control Is In the ON position sufficient o gen flow Is avallaole at the maximum airplane OP eratlng altitude see Section II Limitations wliffe at lower alt itudes the re ducing valve automati...

Page 158: ...ss the chart horizontallyto the right until Intersecting the diagonal line which represents the number of P er sons on board From thatIntersection drop vertically down to the heav yline marked 30LOOO ft 3 From this point on the heavy lin follow the trend of the curved lines down to the norizon tal line representing cruise altitude 1hen drop vertically down to the bottom of the chart and read the d...

Page 159: ...ON HOURS M 7 13 1 I U Ht 7 13 UXYliii N UUHAIIUN GHAHT 115 7 GU I t IVACUUM SYSTEM I The standard vacuum sysem on the M20R consist of a main vacuum pump regulator filters and a clutch activated engine driven stand by vacuum pump The matn vacuum pumR oper ates when engine Is running The standard stand by vacuum pump is coupled to the engine ac cessory drive but the elecrrically activated clutch mus...

Page 160: ... to OFF ARM position is selected when the transmitter is Installed at the factory and swltch should remain in that position whenever unit Is installed In the airplane The ON position Is provided so unit can be used as a portable transmitter or In the event the a tomatic feature was not triggered by impact or to periodically test the function ofthe trans mitter Select the OFF position when changing...

Page 161: ...VICING REFUELING jTABLE OF CONTENTSj ENGINE LUBRICATION INDUCTION AIR FILTER GEAR AND TIRES BATIERIES HYDRAULIC BRAKE RESERVOIR SYSTEM MAINTENANCE ENGINE PERFORMANCE CHECKS PROPELLER CARE EXTERIOR CARE INTERIOR CARE AIRPLANE FILE ISSUED 6 94 PAGE 8 2 8 3 8 3 8 3 8 3 8 4 8 4 8 4 8 5 8 6 8 6 8 7 8 7 8 7 8 7 8 7 8 8 8 8 8 1 ...

Page 162: ... service procedures which the op erator will normally perform or supervise Reference should be made to FAR Part 43 for infor mation regarding preventive maintenance which may be performed by a U S licensed pilot It is wise to follow a planned schedule of lubrication and preventive maintenance based on cli matic and flying conditions encountered in your locality Keep in touch with your Mooney Servi...

Page 163: ...Is necessary to lift the aircraft with jacks The tall tiedown point Is part otthe tall skid TO TIE DOWN AIRCRAFT a Part the airplane facing the wind b Fasten the co pilot S t t belt through the flight control wheel Pull seat belt snug so tlfght controls are Immobilized c Fasten strong ground anchored chain or rope to the Installed wing lledown eyebolts and place wheel chocks fore and aft of each w...

Page 164: ...l sample insert cup actuator prong Into sump drain receptacle Plfflh upward to open valve momentarily and drain fuel Intocup Ifwater Is in fuel a distinctline separating waterfrom gasolinewill be seen through transparent cup wall Water being heavier will settre to bottpm of cup while colored fuel will remain on top Continue taking fuel samplee until all water Is purged from tank Aircraft should be...

Page 165: ...esume normal oil drain periods after sludge conditions Improve Your Mooney Service Centerwill change engine oil in addition to performing all other service and inspection procedures needed when you bring your airplane Infor its50 hour 100 hour or annual inspections cAUTION Excessive oil sludge buildup indicates that the oil system needs servicing at less than 5D hour Intervals When changing or add...

Page 166: ...the cycle cAUTION NtvNr ltv After any landing other than a smooth touchdown and rollout when aircraft Is above 3200 Lbs 1 452 Kg the aircraft should undergo the Gear System Operational Inspection as outlined In M20R Service and Maintenance Manual No 180 Chapter 32 30 01 The gear warning horn may be checked In flight by retarding throttle with the gear up The gear horn should sound with an intermit...

Page 167: ...ing tolerances In the parts This has no adverse effect on propeller performance or operation With the first turn centrifugal force firmly seats the blades rigidly and positively against the retention bearing In the propeller hub Preflight Inspection of the propeller blades should Include In addition to the foregoing an occasional wiping with an cloth soeked In kerosene NEVER USE AN ALKALINE CLEANE...

Page 168: ...ercial cleaning and finishing compounds Foam type shampoos may be used for routine cleaning of carpets To mi lirnize carpet wet ting keep foam type cleaners as dry as possible and gently rub fn clrcles Use vacuum cleaner to remove foam and dry the materials Grease spots on carpet should be removed with jelly type spot lifter Do not saturate carpet with a solution which could damage backing materia...

Page 169: ...n request a AirplaneLog Book b Engine Log Book Since the Regulations of other nations may require other documents and data owners of airplanes not registered In the United States should check with their own aviation officials to determine their individual requirements ISSUED 6 94 8 9 ...

Page 170: ...SECTION VIII HANDUNG SERVICE AND MAINTENANCE BLANK 8 10 MOONEY M20R ISSUED 6 94 ...

Page 171: ...S PAGE INTRODUCTION 9 3 THE SUPPLEMENTS INSERTED INTO THIS SECTION ARE FAA APPROVED SUPPLEMENT INSERTED Elecdc c cec s Spucl ac c 5 K jo IS o 5v e fGg 0 n l l 4 AA 8o 1 ia t oa i1 h c O 5 t t 1 Pco j2r t r De he s Jet1 Kt 9 ue ISSUED 6 94 DATE Q f 94 sai 11 QilO l 14 a s 9 1 ...

Page 172: ...SECTION IX SUPPLEMENTAL DATA SUPPLEMENT INSERTED 9 2 MOONEY MODEL M20R DATE __ ISSUED 6 94 ...

Page 173: ...s on performance for certain optional equipment lnalalled In the alrp ane are contained In this soctlon Commonly Installed ltema 01 optional equipment whose function and operationdo not require detailed Instructions are deScribed by SECTION VII The Supplements are Approved by the FAA prior to Incorporation Into the Nrplane Flight Manual ISSUED 6 94 9 3 ...

Page 174: ...SECTION IX SUPPLEMENTAL DATA 9 4 BLANK MOONEY MODEL M20R ISSUED 6 94 ...

Page 175: ...ane Flight Manual when the Precise Flight Inc Electric Precise Speedbrake System SBS with control wheel switch operation Is Installed In accordance with Mooney Aircraft Corporation Drawing number 950271 The information contained herein supplements or supersedes the basic manual only In those areas listed For llmitallon procedures and performance information not contained In thls Supplement consult...

Page 176: ... I ...

Page 177: ...RATION P D BOX 72 Kerrville Texo s 78029 0072 LOG OF REVISIONS Revlslo Revision Description of FAA Dute NuMioer Puges Revisions Approved t l t i A ALL PAGES Added M20R to Heading of al Y i L i pages The revlsecl portions of o f f ectecl puges ore lndlcuted loy verticul blo ck lines In the Morgln FAA APPROVED PAGE2 of 4 ...

Page 178: ......

Page 179: ...rakes To retract push one additional time and release to OFF position lSECTION II OPERATING LIMITATIONSj AIRSPEEDS DESCENT IN ICING CONDITIONS PLACARDS SPEEDBRAKE Same limitations as basic airplane SPEEDBRAKES RETRACTED Located on the circuit breaker panel included on the aircraft C B panel placard when speedbrake system Is Installed SPEEDBRAKE Located In front of and In lull view of the pilot nea...

Page 180: ... retract speedbrakes as need l l during descent FINAL APPROACH Fly a high base leg and final approach Extend wing Haps as desired and place the SPEEDBRAKE SYSTEM switch ON to deploy speedbrakes NOTE The SPEEDBRAKE SYSTEM switch may be operated intermittently as required to modulate the glfdepath Maintain an 85 KIAS approach speed by establishing a moderately steep nose down attitude NOTE Increase ...

Page 181: ...he King 150 Series Automatic Aight Control System is Installed In accordance with Mooney drawing number 830081 The information contained herein supplements or supersedes the basic manual only In those areas listed herein For limitations procedures and performance information not contained In this supplement consult the basic Airplane Aight Manual FAAAPPROVED tMP Henry A Armstrong Mgr Alrcratt Cert...

Page 182: ... ...

Page 183: ...72 LOG OF REVISIONS Revislor Revision Description of FAA Dote NuMber Pages Revisions Approved A Title Page LO EP Log of Added M20R application j t l h _1_ t t y J y Revisions All Pages Added M20R to Heading of all pages The revised portions of affected pages are lnckated by vertical lolo cl lines In the Margin FAA APPROVED PAGE 2 of 16 ...

Page 184: ... ...

Page 185: ...m for the pilot The trim system Is designed to withstand any single lnflight malfunction Trim faults are visually and aurally annunciated A lockout device prevents autopilot engagement until the system has been successfully preflight tested The following conditions will cause the Autopilot to automatically disengage A Power failure B Internal Flight Control System failure C With the KCS 55A Compas...

Page 186: ...LIGHT TEST TEST BUTTON When momentarily pushed Initiates prenlght test sequence which automatically turns on all annunciator lights tests the roll and pitch rate monitors tests the autotrim fault monitor checks h manual trim drive voltage and tests all autopilot valid and dump logic If the preflight Is successfully passed the AP annunciator light will flash for approximately 6 seconds an aural ton...

Page 187: ...recouple 16 KAP 150 SYSTEM KC 191 AUTOPILOT COMPUTER Complete Autopilot computer Including system mode annunciators and system controls 17 thru 21 Not used FIGURE 3 AUTOPILOT CONTROL WHEEL SWITCH CAP 22 AUTOPILOT CONTROL WHEEL SWITCH CAP Switch assembly mounted on the pilot s control wheel associated with the autopilot and manual electric trim systems 23 AUTOPILOT DISCONNECT TRIM INTERRUPT AJP DIS...

Page 188: ... s optional radar altimeter 28 ROLL ATTITUDE INDEX Displays airplane roll attitude with respect to the roll attitude scale 29 ROLL ATTITUDE SCALE Scale marked at 0 10 20 30 60 and 90 30 PITCH ATTlTUDE SCALE Moves with respect to the symbolic airplane to present pitch attitude Scale graduated at 0 5 10 15 20 and 25 31 COMMAND BAR Displays computed steering commands referenced to the symbolic airpla...

Page 189: ...tracking valid navigation Information 38 LUBBER LINE Indicates aircraft magnetic heading on compass card 45 39 HEADING WARNING FLAG HOG When flag is in view the heading display is Invalid If a HOG flag appears and alateral mode HOG NAV APR or APR BC is selected the Autopilot will be disengaged The Autopilot may be re engaged in the basic wings level mode along with any vertical mode The CWS sw1tch...

Page 190: ...HEADING SELECTOR KNOB Positions heading bug 49 on compass card 45 by rotating the heading selector knob The Bug rotates with the compass card 45 COMPASS CARD Rotates to display heading of airplane with reference to lubber line 38 on HSI or DG FIGURE 7 KG 107 DG PAGE 8 of 16 REV A 7 94 FAA APPROVED ...

Page 191: ...G Provides a stable visual indication of aircraft heading to the pilot The gyro Is air driven 51 GYRO ADJUSTMENT KNOB PUSH When pushed In allows the pilot to manually rotate the gyro compass card 45 to correspond with the magnetic heading Indicated by the magnetic compass The unslaved compass card must be manually reset periodically to compensate for precessional errors In the gyro FIGURE 8 Kl 204...

Page 192: ... Breaker Switch circuit breaker supplies power to the avionics bus Switch circuit breaker supplies power to the autotrim and manual electric pitch trim systems Supplies power to the optional KCS 55A Compass System Supplies power to the KAA 15 Aural Alert Box sECTION II LIMITATIONS A During autopilot operation a pilot with seat belt fastened must be seated at the left pilot position B The autopilot...

Page 193: ...tely 5 seconds all annunciator lights off except AP which will flash approximately 12 times and then remain off c Note Aural Alert tone sounds with the flashing AP light NOTE IF TRIM WARNING LIGHT STAYS ON THEN THE AUTOTRIM DID NOT PASS PREFLIGHT TEST THE AUTOPILOT CIRCUIT BREAKER SHOULD BE PULLED THE AUTOPILOT AND MANUAL ELECTRIC TRIM WILL BE INOPERATIVE 5 MANUAL ELECTRIC TRIM TEST as follows a A...

Page 194: ...pitch limits or 15 or 1 o b Using Vertical Trim 1 VERTICAL TRIM Control PRESS either up or down to modify aircraft attitude at a rate of 7 deg sec up to the pitch limits or 15 or 1 o 2 VERTICAL TRIM Control RELEASE when desired aircraft attitude is reached The autopilot will maintain the desired pitch attitude 4 Altitude Hold a ALT Mode Selector Button PRESS Note ALT mode annunciator ON Autopilot ...

Page 195: ...1S SELECTED SET OBS TO THE DESIRED COURSE 2 HEADING Selector Knob SET BUG to provide desired Intercept angle 3 NAV Mode Selector Button PRESS a II the Course Deviation Bar Is greater than 2to 3dots the aircraft will conlinue In HOG mode or wings level if HOG not selected with the NAV annunciator flashing when the computed capture point is reached the HOG will disengage the NAV annunciator will ill...

Page 196: ...nunciator will illuminate steady and the selected course will be automatically captured and tracked b If the D Bar Is less than 2 to 3 dots the HOG mode will disengage upon selecting APR mode the APR annunciator will illuminate steady and the capture track sequence wiiJ automatically begin c When equipped with DG 1 OBS Knob SELECT desired approach course 2 APR Mode Selector Button PRESS 3 HEADING ...

Page 197: ... course inbound heading NOTE WHEN BC IS SELECTED THE LATERAL OPERATING MODE WILL CHANGE FROM HOG IF SELECTED TO WINGS LEVEL FOR 5 SECONDS A 45 INTERCEPT ANGLE WILL THEN BE ESTABLISHED BASED ON THE POSITION OF THE BUG a If the D Bar is greater than 2 to 3 dots the autopilot will annunciate HOG unless HDG not selected and BC modes with APR flashing when the computed capture point is reached the HOG ...

Page 198: ...D AS PART OF THE MISSED APPROACH PROCEDURE USE THE NAV MODE TO PREVENT INADVERTENT GS COUPLING 11 Before Landing NP DISC TRIM INTER switch PRESS to disengage AP C FLIGHT DIRECTOR OPERATION KFC 150 Systems Only NOTE THE FLIGHT DIRECTOR MODES OF OPERATION ARE THE SAME AS THOSE USED FOR AUTOPILOT OPERATIONS EXCEPT THE AUTOPILOT IS NOT ENGAGED AND THE PILOT MUST MANEUVER THE AIRCRAFT TO SATISFY THE FL...

Page 199: ...andbook and Airplane Flight Manual POH AFM when the AAOO lnterVOX Intercom System is installed in accordance with Mooney Drawl11g number 810417 M20J M20K 810202 M20L M20M M20R The information contained herein supplements or supersedes the basic manual only in those areas listed For limitations procedures and performance Information not contained in this supplement consult the basic Airplane Flight...

Page 200: ......

Page 201: ...OX 72 Kerrville Texas 78029 0072 Revision Revlslo n NuMber Po ges A ALL PAGES LOG OF REVISIONS Description of Revisions Added M20R to Heading of all pages FAA Approved Dute The revised portions of o ffected po ges nre Inellco ted by vertical blo ck Lines In the Mnrgln rAA At t HUVI U tage z ol 4 ...

Page 202: ......

Page 203: ...ncy procedures for the AABO intercom system EMERGENCY OPERATION II power Is lost to the AA80 for any reason It will drop Into the power fall mode and the pilot will be connected directly to the radios for emergency operation The external PTT switch will still function This mode Is similar to the PILOT ISOLATE mode except that all co pilot passenger functions are lost since they depend on external ...

Page 204: ...a separate level adjustment This line Is muted during transmit functions and when the Intercom Is active If the ISO function Is selected the pilot will be connected directly to the radios while the co pilot and rear seat passenger s remain on the ICS bus with the entertainment audio In the INTERVOX mode all stations hear the same audio ICS FUNCTION Intercom audio may be generated In two mOdes betw...

Page 205: ...ok and Airplane Flight Manual POH AFM when the Propeller De Ice System is Installed in accordance with Mooney Drawing 690003 The Information contained herein supplements or supersedes the basic manual only In those areas listed For limitations procedures and performance information not contained In this supplement consult the basic Airplane Flight Manual FAAAPPROVED a Henry A Armstrong Manager Air...

Page 206: ......

Page 207: ...rville Texo s 78029 0072 LOG OF REVISIONS Revlslor Revision Description of FAA Do te NuMber Po ges Revisions Approved c All Pages Added M20R to Heading of all pages The revised portions of o ffectecl po ges o re indlco ted loy vertico l blo ck lines in the Margin FAA APPROVED DATE 6 29 89 PAGE 2 of3 ...

Page 208: ......

Page 209: ...nd wilt cycle ON OFF with timer indicating when current Is being applied to heaHns elements ISECTION II LIMITATIONS I There is no change to the airplane limitations when the propeller de ice system in installed Flight into known Icing conditions is prohibited ISECTION Ill EMERGENCY PROCEDURES I No change ISECTION IV NORMAL PROCEDURES I If unexpected icing conditions are encountered the following p...

Page 210: ... ...

Page 211: ...s It provides limitations and other information for operation ofaircraft equipped with the GARMIN GTX 33 Mode S Transponder installed in accordance with DAO Aviation Minor Change DAO D0 0475 rev 02 This document serves as the EASA Approved Supplemental Flight Manual for the Garmin GTX 33 Mode S transponder The Information contained herein supplements or supersedes the basic Flight Manual only in t...

Page 212: ...r this AFMS and if necessary approved by the EASA Applicant EASA DOA EASA 21J 275 Name Address DAO Aviation NS Hangarvej HI 4000 Roskilde This Record ofRevisions shall remain in this document at all times Upon receipt of revisions insert page s into this document and enter the revision number revision date insertion date and signature ofthe person incorporating the revision into the document in th...

Page 213: ... 33 ATC Mode NCIS transponder with DENT capability Control ofthe transponder is done via the installed GTN series navigator system 2 The installed Mode S system satisfies the data requirements of ICAO Doc 7030 4 Regional Supplementary Procedures for Secondary Surveillance Radar SSR Mode S Elementary Surveillance in designated European airspace The capability to transmit data parameters complies wi...

Page 214: ...speed at which the GTN transitions from a ground state to an airborne state and vice versa it is set to 30 knots The GTX 33 will automatically switch to Ground Manual operation After Engine Start 1 Radio Master Switch ON The transponder will turn on together with the GTN series navigator system in the same mode of operation selected at the last power down and will display the last entered identifi...

Page 215: ...creen GND displays in the squawk code field Note Touch Ground to place transponder in Ground mode Mode S interrogations will be allowed GDN displays in the squawk code field SECTION V PERFORMANCE No change SECTION VI WEIGHT AND BALANCE See current weight and balance data SECTION VII AIRPLANE SYSTEM DESCRIPTIONS See GTX33 Pilot s Guide for a complete description ofthe GTX33 system ISSUEDDATE ot 2_ ...

Page 216: ...ENERAL TURBULENT WEATHER FLIGHT IN TURBULENT AIR MOUNTAIN FLYING VFR LOW CEILINGS VFR AT NIGHT VERTIGO DISORIENTATION STALLS SPINS AND SLOW FLIGHT STANDARD PROCEDURE SPIN RECOVERY VORTICES WAKE TURBULENCE TAKE OFF AND LANDING CONDITIONS MEDICAL FACTS FOR PILOTS GENERAL FATIGUE HYPOXIA HYPERVENTILATION ALCOHOL DRUGS SCUBA DIVING ADDITIONAL INFORMATION MANUFACTURER S INFORMATION ISSUED 6 94 REV D 1 ...

Page 217: ...e obtained from any Mooney Service Center as soon as possible For your added protection and safety we have added this special section to the Pilot s Operating Handbookto refresh your knowledge of anumber of safety subjects You should review these subjects periodically Topics Inthis section are mostly excerptsfrom FAA Documents and other articlespertaining to the subject of safe flying They are not...

Page 218: ...occurs 13 Practice engine out emergency landing gear extension and other emergency procedures at safe altitude preferably with a check pilot 14 Use caution In mountainous terrain 15 Keep your airplane In good mechanical condition 16 Stay Informed and alert fly In a sensible manner DON TS 1 Don t take off with frost ice or snow on the aircraft surfaces 2 Don t take off with less than minimum recomm...

Page 219: ...with the requirements of that airworthiness directive AIRMAN INFORMATION ADVISORIES AND NOTICES FAA AIRMAN S INFORMATION MANOA This documentcontains a wealth ofpilot Information for neartyall realms offlight navigation ground procedures and medical Information Among the subjects are Controlled Air Space Services Available to Pilots Radio Phraseology and Technique Airport Operations Clearances and ...

Page 220: ...f is aboard and suTflclentfortfle trip plus reserves Oil in the engines should be checke and filled as required INSPECTIONS MAINTENANCE In addition to maintenance inspections and preflight Information required by FAR Part 91 a complete pre flight inspection is imperative It is the responsibility oftlie owner and operatorto assure that the airplane is maintained in an airworthy conditlon and proper...

Page 221: ...nge quickly at times and treats weather forcastlng as profes slonal advice ratherthan as absolutefact He obtainsall theadvice hecan but still stays alert through knowledge of weather changes observations and conditions Plan the flight to avoid areas of severe turbulence and thunderstorms It is not always possible to detect Individual storm areas or find the In between clear areas Thunderstorms squ...

Page 222: ...exceed the climb capability of your airplane AVOID MOUNTAIN WAVE DOWNDRAFTS VFR LOW CEIUNGS If you are not Instrument rated avoid VFR On Top and Special VFR Beln caught above an undercast when an emergency descent Is required or at destination 1s an extremely hazardous position for the VFR pllot Accepting a clearance out of certain airport control zones with no minimum ceiling and one mile visibil...

Page 223: ...student pilot and Instructor pilot have a full set of operable controls 3 Conduct such practice at altitudes in excess of 6 000 ft above ground level Remember that an airplane at or near traffic pattern altitude probably will not recover from a pin b11forv Impact with the ground WhAn r Asr Anding to traffic pattern altitude and during operation In the traffic pattern and approach maintain a safe m...

Page 224: ... located near runway in a crosswind pattern MEDICAL FACTS FOR PilOTS GENERAL Modern Industry s record In rovldlng reliable equipment Isvery good When thapllol enl lrs theairplane he becomes an Integral part ofthe man machine system He IsJustas essential t9 a successful Rfght as the control surfaces To Ignore the pilot In pre flight planning would be as senseless as falling toInspectthe Integrityof...

Page 225: ...reathing rate until symptoms clear then resume normal breathing rate Normal breathing can be aided by talking aloud ALCOHOL Common senseand scientific evidencedictatethat you not flyasacrewmemberwhile under tile Influence ofalcohol Even small amounts of alcohol In the human system can adversely affect judgment and decision making abilities FAR 91 11 states a No person rna act as a crew member 1 wi...

Page 226: ...ons Right Service Stations or Airport Facilities These are very good sources of information and are highly recommended for study Some of these are titled Airman s Information Manual 12 Golden Rules for Pilots Weather or Not Disorientation Plane Sense Weather Info Guide for Pilots Wake Turbulence Don t Trust to Luck Trust to Safety Thunderstorm TRW IFR VFR Either Way Disorientation Can be Fatal MAN...

Page 227: ...SECTION X SAFETY INFORMATION 10 12 BLANK MOONEY MODEL M20R ISSUED 6 94 ...

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