Pilot's Operating Handbook and FAA Approved Airplane Flight Manual

This Pilot's Operating Handbook Is not designed as a substitute for edequate and compa ten! tl4aM insbuctian, knwledgeof cumnt eirwolthinessd h d b s , ap liceblefflenrl alr rquki- Uons or & W r y clrculsrs. lt is not intended to be a guide b r brrslc II&RinstNcPbn or a ban@ manual end should not be used b r m b n a l purposes unlasr kept in en up to dete stetus. All limitations, procedures, safety practices, seNicing and maintenance requirements pub- lished in thls POWAFM are constdered mandalory for the Continued Airworthiness of this airplane in a condllion equal to that of Rs original manufacture. THIS SECTION DOES NOT REQUIRE FAA APPROVAL 1 DESCRIPTIVE DATA 1 - - - - I ENGINE Number of engines . . . . . . . . . . . 1 Engine Manufacturer . . . . . . . iDCiROEI-L cornin? Model . . . . . . . . l O - d ~ 3 8 8 .... - .. f?ecommendedTBO : . . . . . . 2000 Hours . , . . . ~ e c i p k c a t i n ~ : aircooid, fuel injected. i\$ber otcyli"dek . , . , , . , , . . 4, Horizontally opposed . . . . . . . . Displacement . , 381 Cu. In. (5815.7 cc) Bore . . , . , . 5.125 In. (13.02 cm) . . . . . Stroke . , 4.375 In. (1 1.llcm) omp press ion r i i o . , . , . 8.7:l . . . . . . . . . . . . . . 2:; Fuel Injection flow . . . . . . . EJendix, RSA-5-AD1 Fuel - ~ v i k i o n%line . . . lbO dctane or l W U (min. ~rade) Accessories Magnetos (2) . . . Slick- UH - 4372, WH - 4370 ' Spark plugs . . . 18 MM x .75@mlhd. connection Memetor . . . . . . . Prestolite 28V, 70A Starter . . . . . . . . Restoliie 24 Volts lG38&A3B8D engines will be installed on SM 263375 and 243376, and will have Bendix MLN series magnetos installed. Ratings: Maximum Continuous Sea LeveCBHPM . . . . . PROPEUER . . . . . . . . . . . . . . . . . Number 1 Manufacturer . . . . . . . . . . . . ~ c ~ a u l e y * Model Number . . . . . . . ~ 2 ~ & ~ 2 1 4 / 9 0 ~ ~ ~ 1 6 ~ Number of Blades . . . . . . . . . . . . 2 Diameter Max. . . . . . . . . 74.0 in. (187.9 cm)' Min. . . . . . . . . . . . . . . . 73.0 in. (185.4 crn)' ISSUED 1 - gB 1 - 3 MOONEY M20J SECTION I GENERAL CABIN AND ENTRY DlMENStONS Cabin W t h (Maximum) . . . . . . . . 43.5 In. (110.5 cm) Cabin Length Maximum) . . . 114 In. (290 crn) . . . . . . . . . . Cabh Ha ht haximum) 44.5 In. (113 cm) fMry Wd% (Minimum) . . . . . . . 29.0 In. (73.8 cm) Entry Height (Minimum) . . . 35.0 In. (88.9 cm) BAGGAGE SPACE AND ENTRY DIMENSIONS Compartment W t h . . . . . 24 In. 80 9 cm Compartment Length . . . . . . 35 In. l88b c d Compartment Height . . . . . . . 35 In. (88.9 cm) Compartment Volume . . . . . . . . . 15.3 Cu. Ft. (.433 cubid meters) Cargo Area (with rear seats folded down) . . . . . . , 33.0 Cu. A. (.934cubic meters . . . . . . . . . . . Entry HeQht (Minimum) 20.5 In. (22.1 cm) Entry W t h . . . . . . . . . . 17.01n. (43.2cm) Ground to ~ott'omof siil . . . . 48.0 in. (118.8 cm) SPECIFIC LOADINGS Wng Loading @Meximum Gross Wight . . . . . 16.59 Lbs.lSq. Ft. is1 i<elsq, m) Power Loading @ Maximum Gross W i h t . . IDENTlFlCAllON PLATE All correswndence reaardina vour aimlane should include the Serial Number as deoicted on the ~entificationplGe. Thi bentific'ation plate k located on the lefl hand side, aft bnd of the tail cone, below the horizontalstabilizer leading edge. The aircrafl Serial Number and type certificate are shown. I SYMBOLS, ABBREVIATIONS & TERMINOLOGY 1 GENERAL AIRSPEED TERMINOLOGY a SYMBols GS GROUND SPED - Speed of an airplane relative to the ground. KCAS KNOTS CALIBRATED AIRSPEED - The indicated speed of an aircrafl, corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. KlAS KNOTS INDICATED AIRSPEED - The speed of an aircrafl as shown on its airspeed indicator. IAS values published in this handbook assume zero instrument error, M A S KNOTS TRUE AIRSPEED - The airspeed of an airplane relative to undisturbed air which is the KCAS corrected for akutude and tempereture. Va MANEUMRING SPEED - The maxlmum speed at which application of full available aerodynam~ccontrol will not overstress the airplane. vfe Y M U M FLAP MTENDy SPEED - The highest speed permissible wlth wlng Raps in a prescribed extended poslt~on. MAXIMUM LANDING GEAR EXENDED SPEED -The maxlmum speed at which an aircraft can be safely flown with the landing gear extended. ISSUED 1 - 98 1 - 5 SECTION I GENERAL MOONEY M20J GENERAL AIRSPEED TERMINOLOGY & SYMBOLS (con%.) \no MAXIMUM LANDING GEAR OPERATING SPEED -The maximum speed at which the landing gear can be safely extended or retracted. vne NEVER EXCEED SPEED - The speed limit that may not be exceeded at any time. Vno MAXIMUM STRUCTURAL CRUISING SPEED - The speed that should not be exceeded except in smooth air and then only with caulion. VS STALLING SPEED - The minimum steady flight speed at which the airplane is controllable. VW STALLING SPEED - The minimum steady flight speed at which the airplane is controllable in the landing configuration. VX BEST ANGLE-OF-CLIMB SPEED - The airspeed which delivers the greatest gain of aniude in the shortest possible horizontal distance. 4 BEST RATE-OF-CLIMBSPEED - The airspeed which delivers the reatest gain in aitiluda in the shortest possible time with gear and laps up. ENGINE POWER TERMINOLOGY BHP BRAKE HORSEPOWR - The power developed by the engine. CHT CYLINDER HEAD TEMPERATUE - Operating temperature of engine cylinder(s) being monitored by a sensor unit. Expressed in'^. EGT MHAUST GAS lEMPERATURE - Temperature of the exhaust gas fueUair mixture during engine operation. MCP MAXIMUM CONTINUOUS PO\IKR - The maximum power for takeoff, normal,abnorrnalor emergency operations. MP MANIFOLD PRESSURE - Pressure measured in the engine's induction system and is expressed in inches of mercury (Hg). RPM REVOLUTIONS PER MINUTE - Engine speed. AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demon- The velocity of the crosswind component for which adequate strated control of the airplane during takeoff and landing test was Crosswind actual demonstraled during certification. The value shown Velocty is NO?considered to be limiting. 9 Acceleration due to gravity. S e ~ c e The maximum anitude at which aircraft at gross weight has the Ceiling capability of climbing at the rate of 100 IVmin. 1 - 6 ISSUED 1 - 96 MOONEY M20J SECTION I GENERAL ENGINE CONTROLS & INSTRUMENTS ERMINOLOGY Propeller The control used to select engine speed. Contml Thmnle The control used to select engine power by controlling MP. control Mixture Provides a mechanicellink e to the fuel injector mixture Control conlml to control the she 2 t h e fuel feed aperture, and therefore the airtfuel mixture. It is the primary method to shut engine down. CHT Cylinder head temperature indicator used to determine that Gauae enaine o~eralinatem~eratureis within manufacturers EGT Exhaust gas temperature indicator used to Mentify correct lean Gauge fuel flow mixtures for verious power settings. Tachometer An instrument that indicates rotational speed of the engine. The speed is shown as propeller revolutions per minute (RPM). Propeller The device that regulates the RPM of the enginelpropeller by Govemor increasing or decreasing the propeller pitch, through a pitch change mechanism in the propeller hub. METEOROLOGICAL TERMINOLOGY AGL Above ground level. Density Altitude as determined by pressure atlitude and existing ambient Altitude temperature. In standard atmosphere (1%) density and pressure altitude are equal. For a given pressure altiiude, the higher the temperature, the higher the density altiiude. Indicated The altitude actually read from an altimeter when, and only Altitude when, the barnmetric subscale has been set to Station Pressure. INlEfWATIONAL STANDAW) ATMOSPHERE assumes that \lJ oThe air is a dory perfect gas; (2) The temperature at sea lewd is Celsius (59 F); (3) The pressure at sea level, is 29.92 inches Hg (1013.2 mb); (4) The temperature gradlent horn sea level to the anJude at which the tempernure k -56.S0 C (69.7 O F) is -0.00198 C (-0.003564~F) per foot. OAT OUTSIDE AIR TEMPERATURE - m e free air static temperature. obtained either tom inflight temperature indications or ground m~teOrolOgkalsources. lt is expressed in degrees Celsius. Pressure The altitude indicated when Kollsman Mndow is set to 29.92 Aniude In. Hg, or 1013.2 MB. In this handbook, altimeter instrument errors are assumed to be zero. Sation Actual atmospheric pressure at field elevetion. Pressure ISSUED 1 - % SECTION I GENERAL MOONEY M20J WEIGHT AND BALANCE TERMINOLOGY Arm The horizontal distance from the reference datum to the center of gra&y (C.G.) of an item. Basic The actual we' ht of the airplane and includes all operating equipment (iniuuding optional equipment) that has a tixed location and is actually installed in the aircrafl. It includes the weight of unusable hrel and full oil. Center of The point at which an airplane would balance if suspended. Gravity hs distance from the reference datum is found by dividing the (C.G.) total moment by the total weight of the airplane. C.G. Arm The arm obtained by add in^ the airplane's individual moments and dlvdlng the sum by the total weight. C.G. in Center of Gravity expressed in percent of mean aerodynamic percent MAC chord. C.G. The extreme center of gravity locations within which the airplane Limits must be operated at a given weight. MAC Mean Aerodynamic Chord. Maximum The maximum authorized weight of the aircraff and its Wight contents as listed in the aircrafl specificetins. Moment The product of the weight of an item multiplied by I s arm. (Moment divided by a constant is used to simplify balance calculations by reducing the number of digits.) Reference An imaginary vellical plane from which all horizontal distances Datum are measured for balance purposes. Station A localion alon the airplane fuselage usually given in terms of distance from tfe reference datum. Tare 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. Unusable Fuel remaining aner a runout test has been completed in Fuel accordance with governmental regulations. Usable Fuel available for airplane propulsion. Fuel Useful The basic empty weight subtracted from the maximum weight of Load the aircan. This load consists of the pilot, crew if applicable, fuel, passengers, and baggage. ISSUED I- W MOONEY M20J SECTION I GENERAL IM W U R E M E N T CONVERSION TABLES ] LENGTH U. S. Customary Unit . . . . . . . Metric Equivalents 1 inch . . . . . . . . . . . . . . . 2.54 centimeters 1 inch . . . . . . . . . . . . . . . 25.4 millimeters 1 foot . . . . . . . . . . . . 0.3048 meter 1 yard . . . . . . . 0.9144 meter 1 mile (staiute, land) . . . . . . 1,609 meters 1 mile (nautical, inlemaiional) . . . . . . . . . . . 1, 852 meters U. S. Customary Unit AREA . . . 1 square inch . . . . . . . . . 1 square foot . . . . . . . . . 1 square yard . . . . . . . . . Mebic Equivalents 6.4516 sq. centimeters centimeters .a9.030 . 0% sq. meter VOLUME OR CAPACITY . . . . . . . . . . U. S. Customary Unit Metric Equivalents 1 cubic inch . . . . . . . . . . . . 16.387 cubic centimeters 1 cubic foot . . . . . . 0.028 cubic meter 1 cubic yard . . . . . . . . . . . . . 0.765 cubic meter U.S. Customary . . . . . . . . . Metric Equivalents Liquid Measure . . . . . . . . . . . . . . . . . 1 fluid ounce . . . . . . . . . . . . . . 29.573 milliliiers 1 pint . . . . . . . . . . . . . . . . 0.473 liner 1 quart . . . . . . . . . . . . . . . . 0.948 liter 1 gallon . . . . . . . . . . . . . . . . 3.785 liiers U.S. Customary . . . . . . . . . Metric Equivalents Dry Measure . . . . . . . . . . . . . . . . . . . . . . . . . . lpint . . . . . . 0.551 liter 1 quati . . . . . . . . . . . . . . . . 1.lo1 liters British Imperial . . U.S. . . . . Metric Liquid and Dry ~easure' . Equivalents . ~ ~ u l v a l e n t s . . . 1 fluid ounce . . . . . 0.981 U.S. 28.412 millilllers fluid ounce, 1.734 cubic inches 1 pint . 1.032U.S. . 568.26 millillen dry pints, 1.201 U.S. tiquid pts. 34.678 cubic inches ISSUED 1 - 96 SECTION I GENERAL 1 quart 1 gallon U. S. Customary Unit (Avoirdupois) 1 grain . . . 1 dram . . . . . . 1 ounce 1 pound . . . U.S. Customary Unit 1 PSI0 . . . 1 lnch Hg . 1 lnch Hg . . VOLUME OR CAPACITY (cont) 1.032 U.S. dry quarts 1.201 U.S. liquid qts. 88.354 cubic inches 1.201 U.S,. 277.420 cubic inches WEIGHT MOONEY M20J 1.136 liters 4.548 liters . . . . . . . . 64.79891 milligrams . . . . . . . . . 1.772grams . . . . . . . . 28.350 grams 453.58237 grams . . . . . . . . . . . . PRESSURE . . . . . Metric Equivalents 8.885 KPA 3.388 KPA 25.40 mm Hg ISSUED 1 - 96 MOONEY M20J SECTION ll LIMITATIONS [ TABLE OF CONTENTS ] INTRODUCTION . . . . . . . . . . . . . . . . . . . 2-2 NOISE LIMITS . . . . . . . . . . . . . . . . . . . . 2-2 AIRSPEED LIMITATIONS . . . . . . . . . . . . . . . . 2-3 AIRSPEED INDICATOR M N G S . . . . . . . . . . . . . 2-4 POWER PLANT LlMlTATlONS . . . . . . . . . . . . . . 2-5 P O W R PLANT INS'IRUMENT MARKINGS . . . . . . . . . . 2-6 FUEL LIMITATIONS . . . . . . . . . . . . . . . . . . 2-6 WIGHT LIMITS . . . . . . . . . . . . . . . . . . . 2-7 CENTER OF GRAVlTY LIMITS (GEAR D O W ) . . . . . . . . . 2-7 MANEUMR LIMITS . . . . . . . . . . . . . . . . . . 2-7 FLIGHT LOAD FACTOR LIMITS . . . . . . . . . . . . . . 2-8 KINDS OF OPERATION LIMITS . . . . . . . . . . . . . . 2-8 KINDS OF OPERATION EQUIPMENTLIST . . . . . . . . . . 2-8 DECALS I PLACAFiDS . . . . . . . . . . . . . . . . . 2-11 CABIN INTERIOR . . . . . . . . . . . . . . . . . 2-11 FUSELAGE INTWOR . . . . . . . . . . . . . . . 2-16 EXTERIOR . . . . . . . . . . . . . . . . . . . 2-17 FAA APPROVED ISSUED 1 .W AIRPLANE RIGHT MANUAL 2- 1 SECTION II LIMITATIONS MOONEY M20J 1INTRODUCTION I SECTION I1includes operating limitations, instrument markings, and basic placards neces- sal)! for the Safe operation of the airplane, Is engine, standard systems and standard equipment. The limitations included in this section have been approved by the Federal Aviation Adminimtion. W e n applicable, limitations associated with optional systems or equipment such as autopilots are included in SECTION IX The airspeeds fisted in the Airspeed @itations chart (Figure 2-1.) and the Airspeed Indicator Markin s chart (Rqure 2-2) are based on k n p e e d Calibration data shown in SECTIONV mth the normal static source. If the abmate stat$ source iqbeing used, ample malgins should be obsewed to allow for the awpeed ~ l i b r s b o nvanstions behveen the normal and alternate stattc sources as shown in SECTION V. Your Mooney is celticated under FAA Type Certificate No. 2A3 as a Mooney M2W. The certificated noiselevel for the M20J at 2WX)Ibs. (1315 Kg.) maximum weight is 80.04 dB(A). No determinat~onhas been made by the Federal Awat~onAdmn~stratlonthat the noise levels of this airplane are or should be acceptable or unacceptable for operation at, into, or out of, any airport. AIIWLANE RIGHT MANUAL 2 - 2 FAA APPROVED ISSUED 1 - 98 MOONEY M20J SECTION II LIMITATIONS Airspeed limitations and their operational significance are shown in Fgure 2-1. This calibmtion assumes zero instrument error. SPEED KCASMIAS REMAfMS Never Exceed 1951lW Speed Maximum 1 741174 Structural Cruising Speed Maneuvering Speed at: 1b.N. 225W1021 103104 247011120 1W109 274W1243 1141115 2WWY1315 1171118 Do not exceed this speed in any operation. Do not exceed this speed ex- cept in smooth air, and then only with cau- tion. Do not make full or e b ~ p t control mow- ments above this speed. Maximum Rap 1091112 Do not exceed Extended Speed this speed with Raps in full down position. Maximum 13W132 Landing Gear Extended Speed Max. Speed for 1301132 Gear Extenston Maximum speed at which the aircraft can be safely Rown with the land- ing gear extended. Max. speed at which the land- ing gear can be safely ex- tended. Max. Speed for 1041107 Maximum Gear Retraction speed at which the landing gear can be safely retracted. Maximum Pilot 130/132 Mndow Open Speed Do not exceed this speed with pilot window open. FIGURE 2-1 AIRSPEED UMlTATlONS FAA m V E D AIWUNE FLIGHT MANUAL ISSUED 1 - gB 2-3 SECTION I1 LIMITATIONS MOONEY M20J AIRSPEED INDICATOR MARKINGS 1 Airspeed indicator markings, their color code and operational significance are shown in Figure 2-2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . - - - - - - - - - - - - - - - - - - - MARKING M i t e Arc (Full Flap Operating Renge) Green Arc (Normal Operating Range) Yellow Arc (Caution Range) Radial Red Line IAS VALUE or SIGNIFICANCE RANGE (KIAS) Lower limit is maximum weight Vso in landing configu- ration. Upper limit is maxi- mum speed permissible with naps ex- tended. Lower limit is maximum weight Vs with flaps retracted. Upper limit is maximum struc- tural cruising speed. Operations must be con- ducted with caution and only in smooth air. Maximum speed for all operations. FIGURE 2-2 AIRSPEED INDICATOR MARKINGS AIRPLANE FLIGHT MANUAL 2 - 4 FAA APPROVED ISSUED 1 - 06 MOONEY M20J SECTION ll LIMITATIONS LPOWER PLANT UMI~ATIONS1 Number of Engines . . . . . . . . . . . 1 Engine Manufacturer . . . . rrXTRON-Lycoming Engine Model Number . . . . . 10.360.A388' 1 0 ~ A 3 B B Dengines wlll be installed on SIN 24-3375 end 24-3376, and will have Bsnduc MLN series magnetos installed. Engine Operating Umils for Takeoff and Continuous Operations: Maximum Continous Power . 200 BHP Maximum Continous RPM . . . 2700 APM Transknt Continous RPM Urnl . . 2i70 fbr 3 seconds or less Max. Cylinder Head Temperature . . 475 'F (246'C) Maximum Oil Temperature . 2 4 5 ° ~ ( 1 1 8 0 ~ ) Oil Pressure Normal Operating . . . . 60-QO-FSI Minimum (IDLE ONLY) . . . . . . . . 25 PSI Maximum (cold oil) . . . . 100 PSI Oil Speciticetion . . . . . . . . . . MIL-L-22851 Fuel Pressure Minimum . . . . . . . . . . . 14 PSI Maximum . . . . . . . 30 PSI Fuel Grade. (Color) . 109 h a n e (~ieen)liOOL~ (Blue)^* Number of Ropellers . . . . . . . . . . 1 Propeller Manufacturer . . . . . . . ~ c d a u l e ~ " * Ropelbr Model Number . . . . . ~ 2 ~ 3 4 ~ 2 1 4 / 9 0 ~ ~ ~ 1 6 ~ * Propeller pameter: Mln. . . . . . . . . . . 73.0 In. (185.4 cm)*" Max. . . , . . , . 74.0 In. (187.9 cm)*** Ropeller t3lade'~n~les @ b In. sta.: Low . . . . . . . . . . 13.Q0+ I- . Z O * * . . . . . . . . . . Hklh 33.0' + I- .So*** Propeller Operating timils . . 2700 f?PM " 1 W U fuel is calibrated at 5.82 Ib/ga1.(.69 /liter) 100 octane fuel is calibraled at 0.0 Iblgal.I(P2 KgII'ier) "'OPIION: Hartzell HGC2n<-lBF/F76e$A-3Q . . . 73.0 In. (lB5.4 cp) (No Cutoff Allowed) . . . LOW:14.1 + 1- .l . . . Hih: 29.3' to 31.3' No cutoff allomd on propeller when de-ice boots are installed. FAAAPPROMD ISSUED 1 - 96 AIFBLANE FLIGHT MANUAL 2 - 5 SECTION II LIMITATIONS MOONEY M20J [POWER PLANT INSTRUM EN1 MARKINGS I C .-.- nNG) ( C A U ~ O N '--U M . , -- RANGE) Tachometer 1950 - 2700 1500 - 1950 2700 RPh4 Cylinder Head Temperature Oil Temperature 150 - 243' F 245' F (65 - 118 . C) (118' C) Oil Pressure 25 PSI so - 90 PSI (IDLE ONLY) 100 PSI 25-?PSI Fuel Pressure Radial 14- 30 PSI Red Llne Min. 14 PSI 'Yellow arc (starting and warm - up range) 90-100 PSI Refer to WTRON-Lycoming Engine M a i n t s ~ n c eand Operators Manual Section on Engine Specifications and Operating Limits for recommended - cnrisi p o w r and tempeiature ITmitations. FIGURE 2 3 POWERPLANT INSTRUMENT MARKINGS FUEL LIMITATIONS I A raduced fuel quantii indicator is installed in each tank filler neck. The bottom tip of these indicators shows the 26.U.S. gallon (94.7 liters) (20.8 IMP. Gal.) usable fuel level In each tank. An optional visual fuel quantity gauge may be installed on top of each tank and is to be used as a raference for refueling the tanks only. Total Fuel: . . . . Usable Fuel: . . . . Unusable Fuel: . . Fuel Grade (and Color): 100 Octane . . ioou . . . . . . . . . . AIRPLANE FLIGHT MANUAL 2 - 6 . . . . . . 33.25 U.S. Gal, each (126 be&)(27.7 Imp. Gal.) . . . . . . . 66.5 U.S. Gal (251.7 &ek)(55.4 Imp. Gal.) . . . . . . . 64.0 U.S. Gal (242.4 &e&)(5$3 Imp. Gal.) . . . . . . 2.5 U.S. Gal (9.5 ke&)(2.1 imp. Gal.) . , . . minimum grade aviation fuel (green). . , . . (low lead) aviation fuel (blue) with a l e d . content limited to 2 cc per gallon IS also approved. FAA APPROWED ISSUED 1 - 96 MOONEY M20J SECTION I1 LIMITATIONS - - - - - -- CAUTION -- - - - - -To mduce the pouiblltty of ice formation within the airctafl or engine fuel system it is rmissabk to add ISOPROPYL alcohol to tha hrsl supply i n q u n a * s NGTO EXCEED 1%of the total fuel volume per-tank. DO WT add other a d d i t i i s to the fuel system due to potential detenomting effects within tha fuel system. Maximum Wight (takeoff and landing) . . . . . . 2900 Ibs. (1315 Kg.) Maximum Wight in Beggage Compartment . , . 120 Ib. (5i.4 Kg.) @1 Fuse.'~ta.95.5 Maximum Wight in Hetrack . . . , . 10 Ib. (4.54 KQ.) @'fuse. da. 119.0 Maximum Wight in Ca o Area (Rear seats fokled dew$ . . . . . . . . 340 Ibs. (1G.2 kg) 6 ~ k e . &a. 70.7 ICENTER OF G M T Y UMITS (GEAR DOWN) I Most Forward . . . . . Fuse. Sta. 41.0 IN.(lW cm) @ 2250 Ibs. (1020 Kg). 13.3% MAC Intermediate Forward . . . . Fuse. Sa. 41.8 IN.(108 cm) @ 2470 Ibs. (1120 Kg) 14.7% MAC Forward Gross . . . . . Fuse. Sta. 45.0 lN.(114 cm) @ 2900 Ibs (1315 Kg) 20.1% MAC Afl Gross . . . . . . Fuse. Sta. 50.1 IN.(127 cm) @ 2800 Ibs. (1315 Kg.) 28.7% MAC MAC (at Wng Sta. 93.83)(238 cm) . . . . . . . 59.18 IN. (150 cm) Datum (station zem) is 5 inches (12.7 cm) afl of the center line of the nose gear attachin bob, and 33 inches (84 cm) forward of the wing leading edge at wing station 5825 (14 cm). IMANEUVER UMITS ( This airplane must be o erated as a Normal Category airplane. Aerobalic maneuvers, including spins, are pmhiiited. lllllllllllllll lMlARNlNGll I/IIIIIIIIIIII/ Takeoff manauvers, prolonged sideslips or steep descants when the selected fuel tank contains less than 8 gallons (48.0 Ibs., 30.3 liters, 8.7 IMP. Gal.) of fuel have not been demonstrated and may cause loss of pomtr. - I N O W . -Up to 400 foot altitude loss may occur during stalls at maximum wight. Use slow throttle movement. Rapid throttle movement may result in momentary propeller RPM overspeed. FAA APPROMD ISSUED 1 - Q6 AIRPIANE RIGHT MANUAL 2 - 7 SECTION il LIMITATIONS I FLIGHT LOAD FACTOR LIMITS I Maximum Positive Load Factor Flaps Up . . . . . . . Flaps Down (33 '1' . . . . . . . MOONEY M20J Maximum Negative Load Factor Flaps Up . . . . . . . . . . . . -1.5 0. naps Down . . . . . . . 0.0 g. Pilot . . . . . . . . . . . . . . 1 Maximum 6 k n g e r seating confiouratibn . . . . . 3 1 OPERATING U MITATIONS 1 If this airplane is not equipped wlh an approved oxygen system and ffight operations above 12,500 feet are desired, this airplane must be, (I) equipped with supplemental oxygen in accordance with FAR 23.1441, (2) o erated in accordance wlh FAR 91.32 and (3) equipped with aMonics in accordancewith &IR 91 or FAR 135. This is a Normal Category ai lane approved for W l F R day or night operations when equipped in accordance with PAR 91. DO NOT OPERATE IN KNOWN ICING CONDITIONS. TAKEOFFS WITH OPTIONAL ELECTRIC COWL FLAPS INOPERATIVEARE PROHIBITED. Autopilot Limitations- See SECmON IX I KINDS OF OPERATION EQUIPMENT LIST I The following equipment was approved during Type Certiftcalion and must be installed and operable for each kind of operation as specified. 7 lNOTE1 -The KINDS OF OPERATION EQUIPMENT list may not include all the equipment as mquimd by applicable operating rules. SEE NEXT PAGE FOR LISTINGS. AIRPLANE FLIGHT MANUAL FAA APPROVED 2 - 8 ISSUED 1 - 86 MOONEY M20J SECTION II LIMITATIONS SYSTEM or COMPONENT AIRSPEED INDICATOR . . . . . . . ALTIMETER, SENSlTIM . . . . . . . MAGNETIC DIECTION INDICATOR . . . . MANlFOLOPfESSUREGAUGE . . . . . TACHOMETER . . . . . . . . . NELQUANTiTY INDICATOR . . . . . . FUEL PRESSURE INDICATOR . . . . . OILPFiESSURElNDlCATOR . . . . . . OILTEMPERATURE INDICATOR . . . . . CYLINDER HEAD TEMPERANRE INDICATOR . ALTEIWATORLOADMEIER(AMMRER) . . . ALERNATOR , . . . . . , , . BATTEKY , . . . . . . , . . LANDING GEAR POSITION INDICATOR . . . SEAT BELTISHOULDER HARNESS FOREACH OCCUPANT '* . OXYGEN MASK FOR EACH OCCUPANT "' N E L BOOST WMP . . . . . . . . PILOTS OPER4TlNG HANDBOOK LAIRPLANE FLIGHTMANUAL . . POSITION LIGHTS . . . . . . . . STROBE LIGHTS (anti-collilon) . . . . . GYRO HORIZON . . . . . . . . . olwcnota GYRO . . . . . . . . TURN COOFKNNATOR or NRN 6 BANK INDICATOR LANDING LIGHT "" . . . . INSTRUMENT LIGHTS (INlEfWAL or GLA&SHIELD) CLOCK WTH SWEP SECOND HAND or DIGITAL) COMMUNICATIONSYSTEM . . . . . . NAVlGATlON SYSTEM . . . . . , . (APPROPRIATE TO FACILITIES BEING USED) VACUUM SYSTUlVlNDlCATOR . . , . . Equipment musf be installed and operable for all operations. .. If inoperative for unoccupied seat@),seat(s) must be placarded: **. "DO NOT OCCUPY" Only required when the operating rules require use of oxygen. .... W e n required by the appropriate regulations FAA APPROVED ISSUED 1- 98 A I W U N E FLIGHT MANUAL 2 - 9 SECTION II LIMITATIONS MOONEY M20J I KINDS OF OPERATION EQUIPMENT LIST (con't)J SYSTEM or COMPONENT (con't.) PITOT,HEATED "'* . . . . . . . OATGAUGE "" . . . . . . . . VSI "" . . . . . . . . . . ALTERNATE STATIC SOURCE *"' . . . . M R NIGHT I Equipment must be installed and operable for all operations. .*.. Men required by the appropriate regulations AIF@LANE RIGHT MANUAL 2 - 1 0 FAA APPROMD ISSUE0 1 - 98 IFR DAY IFR 1 1 1 1 1 1 1 1 NIGHT MOONEY M20J SECTION II LIMITATIONS [DECALS AND PLACARDSJ CABIN INTERIOR I ON LEFT SIDE PANEL The following placards must be installed inside the cabin at the bcetbns specified. DEFROSTER CABIN HEAT C A B I N V E N T PULL ON P U L L ON P U L L ON T CHECK L I S T A CONTROLS RUN-UP F U E L DOOR PROP WINDOW E INSTRUMENTS WING F L A P S MIXTURE TRIM SEAT L A T C H BOOST PUMP COWL F L A P S B E L T I H A R N E S S F CONDUCT TRIM CHECK PRIOR TO FLIGHT, F SEE PILOT'S OPERATING HANDBOOK. ( K3:IHARNESS MIXTURE GEAR WING F L A P S PROP G BOOST PUMP .I ON CONSOLE-BELOW CONTROLS II JSODEC-1 IFAA APPROMD AIRPLANE FLIGHT MANUAL ISSUED 1 - 96 2 - 11 4 OPERATIONAL LIMITATIONS T Y S N S T i -TED AS A IIR)(K CATEURY A l R M H t I N -1- VN TIC 5 E R A T l f f i L D Q T A T W STATED I N TIC flRW W PLUM= W N G S AND WULS 10 AEROUTIC mEWERS IwtLUMNG S P W RE&IMXMM SPEED VlTH L m O D l i GEAR m m ~ pI= nu. www SPEED m anrcr CZAR, I 0 7 K U S M X W I SPLtD TO MDm tWt 13L K U t mwtlW wswmm rum LMD rum-ru~sUP +a-w+t09 EMERGENCY MANUAL GEAR EXTENSION L PUL WDrW GUR ClRanT RCAYER. 0. M GEMssnrn IN c r n ~mm wsnm a ~ u s ~ ~ n c u ~ ~ u m w u ~ ~ w u r ~ t ~ m l ~ o r c 4. RU T-WU(DL~ STRAIGHT UP (12 m a w c s x 5. KUN T-I(LIIDLC TO RENRl TO mGlW. P D S l T l D I 6. MPCAT MIL GEAR @UWNL l M C O T S DI (PTO W FULS). ' IC T m K ELCCTR~UL TAILURE-SEE )(COWIIW IW~WTIR. CAUTION I. TUW OTF ST- LITES WY TAXIING )(w wr r~ Y N N FLYING I N TOG OP IN QOIIIS. STD W f l T m W LlTES W S T I USCD m ALL MW LPER~TIW. 2. Ell WE W rlRE TIRN OTf W I N M A T I m MYT ~CREVVERNIER ~ b m m sCL&R TWN mar m wl Fen. 9 w SECTION II LIMITATIONS MOONEY M20J AIRPLANE FLIGHT MANUAL 2 - 12 RAW SOURCE ON LOWER IBT I W R U $ ~ PANEL FAA APPROVED ISSUU) 1 - 9 6 WNOTOPEN ABOM 132 KW -lu ON PLm wmow O N c a W S O E A B Q Y E L ~ ON WHT IWSTRUUW PANEL ADUCWl TO TACHOUETER (UcCAULEY PRDPEU+R ONLY) ON LOWER CONSOLE BnOW COHlROLS * PUSH TO RELEASE -m E M E N WE ON RaRGDmGW(MmMONRO+ASE r (UNDER MomrRE CONIROL) LIKE PHONE 4 s LOWER LEFT irmRUUENl PANEL NAV 2 NAV 2 lND INTERCOM FUEL FLOW ISOLATE (LEGENDS MAY VARY WITH INSTALLED EQUIPMENT) ELT PUCARD - TW, RIGHT ~ U U E N TPANn MOONEY M20J SECTION I1 LIMITATIONS FLOOR BOARD AFT OF CONSOLE FLOOR BOARD F V D OF PILOT SEAT ON MAGNETIC COMPASS RED 1 PANEL LIGHTS E lRIGHT L O V E R RADIO PANEL -354 ON RETRACT TUBE WHITE (DISPLAYED THRU VINDOV ON FLODRBOARD VHEN LDG. GR. I S RETRACTED.) -137 ON L O V E R ENGINE CONTROL CONSOLE DO NOT SLAM DOOR / LOCKED \ ABOVE INSIDE CABIN ~ 0 0 ~ ; " ~ ~ -834 ABOVE INSIDE BAGGAGE DOOR HANDLE FAA APPROVED A I W E FLIGHT MANUAL ISSUED 1 - 96 2 - 1 3 SECTION II LIMITATIONS MOONEY M20J AIWLANE FLIGHT MANUAL 2 - 14 -379 RIGHT CONSOLE ABOVE AND BELOW FLAP SWITCH FAA APPFtOMD ISSUED 1 - 96 GEAR DOWN 0 0 -369 (DISPLAYED THRU WINDOW I N FLDORBDARD WHEN LDG, GR, IS EXTENDED) I] PUSH INCREASE WSH INCREASE 1 x 1 PUSH RICH -383 -385 -387 ABOVE EACH CONTROL ON LOWER INSTRUMENT PANEL W NOT EXCEED 10 LBS (4.5 Kg) IY 7H6 COUPARNENI USE FOR S T W E Of W;HT SMI ARllCLES OW WARNING: SEE ARCtW LWNG SCHEDULE MTA FOR BAM;AC;E COLlPUrmENT ALLOWABLE -155 ABOVE BAGGAGE COMPARTMENT IIN HATRACK SHELF MOONEY M20J SECTION 1 LIMITATIONS FAA APPROVED AIRPLANE FLIGHT MANUAL ISSUED 1 - 98 2 - 1 5 WWQIMCEFO120LBS IN THS WUPAmmn WARNING: g4& WNG SQ~LW~EMTA m a m M E CO- AUQMaE -153 ON TDP &AGCACE DOOR JAMB I- WARNING DO NOT EXCEED 170 LBS. (77.1 Kg) ON M S SEAT BACK. PEMClWT--mA F O R ~ ~ ~ U L Q M I L E : ON LOWER CONSOLE BnOW W SrmCH -378 ON FORWARD END OF REAR SEAT BOTTOU STRUCTURE C U R UP 107 KW CEAR ON 132 KIAS CEAR DmNDfD 132 KIAS PUSH G E M UP 0 3 Q C E A R S A F m GEAR DM BvPASS -393 UPPER CENTER INSTRUMENT PANEL GURE PANEL SHIELD -380 -384 UNDER RIGHT R9MO PANEL (FUSES) > SECTION II MOONEY LIMITATIONS M20J FUSELAGE INTERIOR (inside tailcone) The follow in^ placards must be installed inside the tailcone at the locations specfied. MAINTAIN LEVEL HERE -071 ON HYDRAULIC BRAKE RESERVOIR ENGINE OIL OIL INSTALLED I N THIS ENGINE I 8 NEXT OIL CHANGE IS DUE AT ,,,,,,,,,,-, HRS. (USE GREASE PENCIL) TACH TIHE -750 ON OIL ACCESS/FILLER DMR AIRPLANE FLIGHT MANUAL 2 - 1 6 FAA APPROMD ISSUED 1 - 96 MOONEY M20J SECTION I I LIMITATIONS EXTERIOR The following placards must be installed on the exterior of the aircran at the locations specified. TlRE PRESSURE 30 PSI (207 KPA) -761 ON MAIN GEAR DOORS TlRE PRESSURE 49 PSI (338 KPA) -7s9 ON NOSE GEAR DOOR FUEL-100 GREEN) or i w L L (w6 uw. on. 32 U.S. GAL STUJMRD ON FUEL TANK CAPS FUEL- 100 GREEN) or i w u (mu6 wH. om. 121.2 LITERS USEABLE FUEL-100 GREEN) or look 18Lu6 w. on. OPTIONAL ITOWING LIMITS - 700 tWARNING DO NOT EXCEED TOWING LIMITS -701 ON NOSE GEAR LEG DO NOT PUSH -009 ON LEADING EDGE OF HORIZONTAL STABILIZER AND TRNLING EDGE OF BOTH SIDES OF RUDDER NO STEP -007 ON INBOARD END OF FLAPS. WlNG LEADING EDGES AND WlNG AHEAD OF FLAPS FAA APPROVED AIRPLANE FLIGHT MANUAL ISSUED 1 - 86 2 - 17 SECTION II LIMITATIONS MOONEY M20J AIRPLANE FLIGHT MANUAL 2 - 1 8 HOIST POINT-01 1 ON UNDERSIDE OF WINGS (2 PLCS) FAAWROVED ISSUED 1-96 FUEL DRAIN UNDER EACH WING NEAR SUMP MUlNS GASCOLATOR DRAIN UNDER FUSELAGE AFT OF HOSE WHEEL mu PlTOT DRAIN UNDER LEFT HAND WING W C EDGE N M FUSEUCE STATIC DRAIN UNDER TULCONE m OF WING tRAlUNG EDGE m C - 8 MOONEY M20J SECTION Ill EMERGENCY PROCEDURES TITLE . . . . . * . . . . . . . . . . . . . . INTRODUCTION . . . . . . . . . . . . . . . . . . . AIRSPEEDS FOR EMERGENCY OPERATIONS . . . . . . . . . . . . . . . . . . ANNUNCIATOR PANEL W I N G LIGHTS . . . . . . . . . . . . . . . . . . . . . . ENGINE . . . . . . . . . PO= LOSSDURING TAKEOFF ROLL P O W LOSSAFfER LIFTOFF . . . . . . . . . . . . . . . . . P O W 3 LOSS IN RIGHT (RESTART PROCEDURES) ENGINE ROUGHNESS . . . . . . . . . . . . . . . ELECTRIC C O W FLAPS FAILURE .FULL CLOSED POSIRON . . HIGH CYLINDER HEAD TEMPERANRE . . . . . . . . . HIGH OIL TEMPERATURE . . . . . . . . . . . . . . LOW OIL PRESSUE . . . . . . . . . . . . . . . . . . . . . . . . ENGINE DRIVEN FUEL PUMP FAILURE FIRES . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGINE F I E .DUWNG STARTON GROUND ENGINE FIRE .IN FLIGHT . . . . . . . . . . . . . ELECTRICAL FIRE .IN FLIGHT . . . . . . . . . . . . . . . . . . . . . . EMEROENCYDESCENTPROCEDUS GLIDE . . . . . . . . . . . . . . . . . . . . FORCED LANDING EMERGENCY . . . . . . . . . . . . . GEAR REIRACTU) OR EXTENDED . . . . . . . . . . . SYSTEM EMERGENCIES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PROPULER . . . . . . . . . . . . . . . . . . . . . FUEL ELECTRICAL . . . . . . . . . . . . . . . . . . LANDING GEAR . . . . . . . . . . . . . . . . . OXYGEN . . . . . . . . . . . . . . . . . . . ALTERNATE STATIC SOURCE . . . . . . . . . . . . UNLATCHED DOORS IN FLIGHT . . . . . . . . . . . . ICING . . . . . . . . . . . . . . . . . SPINS . . . . . . . . . . . . . . . . . . . . . . EMERGENCY W T OF AIRCRAFT . . . . . . . . . . . . . OTHER EMERGENCIES . . . . . . . . . . . . . PAGE ISSUED 1.98 3 - 1 SECTION Ill EMERGENCY PROCEDURES MOONEY M20J ISSUED 1 - Q6