PILOT'S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL MOONEY

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 SECTION l GENERAL MOONEY M20J Type . . . . . . . . . . Constant Spe* GOWnIing . . . . . ~ydraulically'controlledby engine otl Blade Angles @ 30 in. Sta.(76.2 cm): Low . . . . . . 13.9 degrees + 1- .2 degrees' H$h . . . . . 33.0 degrees + I- .5 degrees" • OPTION: Hartzell HGC2YK-lBFIR668A-3Q 73.0" (185.42 cm) (No cutoff allowed) Blade An les: a30 in. sta. 5 cm) Low: ,PI d e g m s + 1- .rdegree High: 29.3 degrees to 31.1 degrees Spinner: Hartzell No. A2295 FUEL - Minimum Fuel Grade (Color) . I W Octane (Green)1100 LL (Blue) Total Capacity . . . . . . . . . 66.5 U.S. Gal. (251.7 iileri)(5i4 Imp. Gal.) Usable . . . . . . . . . . . 64.0 U.S. Gal. (242.3 iiteri)(5i3 Imp. Gal.) OIL - Total Oil Capacly . . 8 Qts. (7.57 Liten) Oil Capacity Minimum for ~ l i ~ h t. 5 Qts. (4.73 Liters) Oil Filter (Champion CH48103) . . . . . . . . . . Full Flow Oil grades, specifications and changing recommendations are contained in SECTION Vl11. LANDING GEAR PIPE: Electrically operated, fully retractable tricycle ear with rubber shock discs. The main wheels haw hydraulically operated disc brakes. 6 nose wheel is fully steerable 14' left or nght of center. M e e i Base . . . . . . . 71 9/16 in. (181.8 cm) M e e l Track . . . . . . . . 110 in. (279.4 cm) Tire Size: Nose . . . . . . . . . 5.00 x 5 (6 ply)Type Ill Main . . . . . . . . . . . . . 6.00 x 6 (6 ply)Type Ill Tire Pressure: Nose . . . . . . . . . . . . . . . . . 49 PSI Main . . . 30 PSI Min. Turning Redius (M&. by 2 for \iuni Tip'clearance distance)' (No brakes applied) . . . . . . . . . . 41 A. (12.5 m) MAXIMUM CERTIFICATED WEIGHTS Gross Wight . . . . . . . . . . . . 2900 Lbs. (1315 Kg) Ba~g~ag~; Area . . . . . . . . . . . . 1M Lbs. (54.4 Kg) . . . lOLbs.(4,54Kg) Cargo (Rear Seats FOI& down) . . . . 340 ~ b s .(154.2 KQ) STANDARD AIRPLANE WEIGHTS Basic Empt VUeig ht . . . . . . . . . . . See Page 1-10 Useful LO^ . . . . . . . Varies with'installed equipment See S ~ C ~ ~ O N ' V I for specific airplane weight. 1 - 4 ISSUED 1 - M 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 MOONEY M20J SECTION Ill EMERGENCY PROCEDURES 1INTRODUCTION I P I This section rovides the recommended procedures to follow during edverse flight condi- tions. The inkrmation is presented to enable you to form, in edvance, a definite plan of action for coping with the most probable emergency situations which could occur in the operation of your airplane. As it is not possible to haw a procedure for ell types of emergenciesthat may occur, it is the pilot's responsibility to use sound judgement based on experience and knowledge of the aircraft to determine the best course of adion. Therefore. it is considered mandetory that the pilot read the entire manual, especially this section beforenight. M e n applicable, emergenc procedures essocleted with optional equipment such as autopilots are inclu&d in SECTION IX I NOTE I - All aimpaeds in this section am indicated (IAS) and assume zero instrument error unless state+dothsrwirs. ISSUED 1 - 98 SECTION I l l EMERGENCY PROCEDURES MOONEY M20J IAIRSPEEDS FOR EMERGENCY OPERATIONS I CONDITION . . . RECOMMENDED SPEED ENGINE FAILURE AFTER TAKEOFF . . . . . . . . . . Wng flaps UP 85WAS . . . . . . . . . . Wng Raps COW' 75 WAS MAXIMUM GUDE SPEED MANEUVERING SPEED PRECAUTIONARY LANDING WlTH ENGINE POWER, Flaps D O W . . . . . . . . EMERGENCY DESCENT (GEAR UP) Smooth Air . . . . . Turbulent Air 2900 lb11315 Kg . 2740 lbl1243 kg . 2470 lb11120 kg . 2250 lbll021 kg . 03 KlAS 90 WAS 87 KlAS 84 KlAS 118 WAS 115 WAS 109 MAS 104 KlAS 75 KlAS 196 KlAS . 120 KlAS . 115KlAS . 109 WAS . 104 KlAS EMERGENCY DESCENT (GEAR DOWN) Smooth Air . . . . . . . . . . 132WAS Turbulent Air 2900lb11315Kg . ~ . . . . 2740 lb11243 kg . . . 2470 lb11120 kg . . . 2250 lbl1021 kg 120 KlAS 115 KlAS 109 WAS 104 KlAS 3 - 4 ISSUED 1 - 96 MOONEY M20J SECTION Ill EMERGENCY PROCEDURES I ANNUNCIATOR PANEL WARNING LIGHTS I WARNING UGHT GEAR UNSAFE LEFT or WGHT FUEL PROP DE-ICE (if installed) PlTOT HEAT SPEED BRAKE (if installed) HllLO VAC (Flashing) HlRO VAC (Steady) FAULT a REMEDY RED light indicates landing gear is not in iully extended or ret%cfed po- RED light indicates 2 112 to 3 allons (8.5 to 11.4 tilers) of usable &el re- main in the respective tank. &Itch to fuller tank. BLUE light Indicates power applled to De-ke boots. BLUE tiiht indicates power applied to heater. (On some foreign AM: - AMBER light indicates power is NOT applied to Fitot Heat). Speedbrakes are extended. Suction is below 4.25 In. Hg. (FED) Suction is above 5.5 In. Hg. (RED) -l NOTE1 -Attitude and dimctional g y m am unreliable when VAC light is illurninatad (steady or flashing). Vacuum system should bs checked andlor adjusted as soon as practicable. ALT WLTS (Flashing) ALT WLTS (Steady) START POMI? STBY VAC (if installed) EMOTE RNAV (if installed) BOOST PUMP ISSUED 1 - 96 FED light indicates alternator output is low. Refer to "ALTERNATOR OUT- PUT LOW' . FED light indicates overvoltage and Celd CIB tripped or Reid switch is OFF. Refer to "ALEWJATOR O W - VDLTAGE . R€D light indicates switch or relay is engaged and starter is energized. Flight should be terminated as soon as practicable. Engine & electrical system dam e may result. This is normal i n d i c z n during engine start. AMBER light indicates stand-by vac- uum system is ON. AMBER light indicates DME not slaved to RNAV. Fuel Boost Pump is ON. SECTION I l l EMERGENCY PROCEDURES MOONEY M20J pziiiq POWER LOSS - DURING TAKEOFF ROLL Throttle . . . . . . . . . . . CLOSED Brakes . . . . . . . . AS'REQUIRED Fuel ~ele&r . . . . . . . . . . . . . . . O R MagnelolSlarter &itch' . . . . . . . . . OFF Master . . . . . . . . . . . . O R POWER LOSS - AFTER TAKEOFF a IN FUGHT (RESTART PROCEDURES) Airs eed . . . . . . . . . . . . . 85 WAS ~uePSelecior . . . . . . . . S E ~ E ~ T O~HERTANK Fuel Pressure . . . . . . . . . Verify in GREEN ARC Fuel Boost Pump . . . . . . . . . . . ON (IF REQUIRED Throttle . . . . . . . . . Fuu F o 4 . -- . -. .- - - - Propeller . . . . . . . . NUFOR\IWW) M i u r e . . . . . . . . N L L F O ~ Magneto ~iarterl&ich' . . . . . . VERIFY on "BOTH'" If engine does not restatt after initial attempts: Mixture 1 . U CUTOFF (Initially) then i v a n c e siowly toward'Rld~until englne starts. If engine does not restart, extablish best glide speed and proceed to: FORCED LANDING EMERGENCY. After engine restam: Throttle . . . . . . . . ADJUST as required Propeller . . . . . . . . . . . . ADJUST as required Mixture . . . . . . . & - ~ as power is restored LAND AS SOON AS PRACTICABLE; COFWECT MALFUNCTION FfUOR TO NEXT FLIGHT. ENGINE ROUGHNESS Engine Instruments . . . . . . . . . . . . . CHECK Fuel Selector . . . . . . . . . . . OMER TANK Mixture . . . . &UST f i r smooth operation ~agnetol~iarter Select R or Lor BOTH. If ro~ghness'd&~~ears on sk@l; megneto, monitor pbwer and continue on selected magneto. 11111111111111111 11 WARNING /I 1111111/111111111 The engine may quit completely when one magneto is switched off if other magneto is faurn. H this happew, closa throttle to idle and mixture to idle cutoff before turning magnetos ON to prevent a severe afterfirs. When magnetos have been turned back on, proceed to POWER LOSS - IN FUGHT. Severe roughness may be sufficient to cause pmpelkr separation. Do not continw to operata a rough engine unless there is no other almative. Throttle . . . . . . . . . . . . . RU)UCE Check if a lesser throllle setting causes roughness to decrease. If severe engine roughness cannot be eliminated LAND AS SOON AS PRACTICABLE. ELECTRIC COWL FLAPS FAILURE - FULL CLOSED POSITION Acceptable engine operating temperatures can ahvays be maintained during Right with the cowl flaps failed in the hrll closed position using the following procedure: 3 - 6 ISSUED 1 - 06 MOONEY M20J SECTION Ill EMERGENCY PROCEDURES Power . . . . . . . . . . AS FZEQUIW Mixture . . . . . . . . . RICH Airspeed . . . . lb KlAS Cylinder ~ e i d0ii ~ e m p h u r e . . MONITOR - - N & & L O P E ~ A ~ N G RANGE HIGH CYLINDER HEAD TEMPERANRE Mixture . . . . . . . . . ENRICH As Required Cowl Flaps . . . . . . . . . OPEN as required Ainpeed . . . . . . . . INCREASE As Required Power . . . . . . . . . . . . . REDUCE . . . . . . if temperature cannot be'maikainedwithin limls. HIGH OIL TEMPERATURE - 1 N o w -Prolonged high oil tempfatun indicatbns will usually be accompanied by a drop in oil pressure. H oil pressure remains normal, then a high tern ratum indication may be caused by a faulty gauge or tempratun p&. Cowl Raps . . . . . Airspeed . . . . . . Power . . . . . . OPEN INCREASE EDUCE PREPARE FOR POSSIBLE ENGINE FAILURE IF TEMPERANRE CONTINUES HIGH. LOW OIL PRESSURE Oil temperature and pressure . . . . . . . Monitor Pressure below 25 PSI . . . . MPECT'ENGINE FAILURE, to FORCED LANDING EMERGENCY. ENGINE DRIVEN FUEL PUMP FAILURE An engine driven fuel pump failure is probable when the en$ine will only operate wlh the boost pump ON. Operation of the engine with a failed englne driven fuel pump and the BOOST ON will require smooth operalion of the engine controls and corresponding mix- ture chan e when the throllle is reposlioned or the engine speed is changed. W e n retardmg krottle or reducing engine speed lean the mlxture to prernml engine power loss from an ownich condlin. Enrich the mixture when openlng the throttle or increasing engine speed to prevent engine power loss from a lean condition. Always lean to obtain a smooth running engine. The following procedure should be followed when a failed engine driven fuel pump is suspected: M i u r e . . . . . . . . . . . . . . . IDLE CUT? Throttle . . . . . . . . CRUISE Posttion . . . . . . . . . . . . . . . Fuel Boost Pump ON Mixture . . . . INCREASE untiiengine &ark and adjust'for smooth engine operation. LAND AS SOON AS PRACTICABLE. ISSUED 1 - 98 3 - 7 SECTION Ill EMERGENCY PROCEDURES MOONEY M20J ENGINE FlREOURlNG START ON GROUND MegnetofStarterWitch . . . . . . . CONTINUE cranking If enaine stam Power . . . . . . . . . 1500 RPM for several minutes or until fire is extinguished. Engine . SH- -1nrp.ctforQmap ~fengine doe; NOT Art: MegnetofStarterSwitch . . . . . CONTINUE cranking Miiure . . . . . . . . . IDLE CUTOFF 'Ihmttle . . . . . . FULL F O R W Fuel se~ecior~aive' . . . . . . . . . . . . . . O F F . . . . . . . . . . . . . . MagnetolStarter %itch' OFF . . . . . . . . . Master Switch OFF Fire . . . . . . . . . . . E~TINGUISHwith ilre kinguisher ENGINE FIRE-IN FUGHT Fuel Selector Valve . . . . . . . . . . . OFF Throttle . . . . . . . . . . . . . CLOSED Mixlure . . . . . . . . . IDLE CUTOFF ~agnetol&arter&itch' . . . . . . . . . . OFF . . . . . . . . . . Cabin Ventilation L ~eating'~ontrok &OED Cowl Raps . . . . . . . . . . . CLOSEp Landin Gear . . or u ~ & ~ i n @ on tenam . . . . . . . . . . ~ n g d a p s : : D as necessary - l NOTE1 -If fim is not elinguished, attempt to increase aimow over the engine b increasing glide speed and open cowl Raps. Proceed mth FORCED LAND~NG EMERGENCY. DOnot attempt an engine nrtaft. ELECTRICAL FIRE- IN FUGHT (Smoke in Cabin) Master Switch . . . . . . . . . . . . OFF 111111111111111 IMIARNINOIl lll/lllllllllll Stall warning and gear warning am not available with Master Switch OFF. Alternator FieM Switch . . . . . . . . . . . . . . O f f All Electrical Witches . . . . . . . . . . . . . . OFF . . . . . . . . . . . . . . Cabin Ventilation OPEN Heating Controls . . . . . . . AS DESIRED Circuit Breakers . CHECK to identif; fau~ycircuit if possible. If electrical power is essential for the flight, attempt to identify and isolate faulty circuit as follows: Master Witch . . . . . . . . . . . . . . . ON Alternator FieM witc'h ON Select ESSENTIAL switches ON one at a time; permi a s h o i time to elapse before activating an additional circuit. LAND AS SOON AS POSSIBLE. 3 - 8 ISSUED 1 - gB MOONEY M20J SECTION Ill EMERGENCY PROCEDURES -- - In the event an emergency descent from hihaltiude is required, rates of descent of approximately 2,000 feet per minute or greater can be attained with the aircralt in two different configurations. \IUth the ear and flaps retracted and cowl flaps closed, an ainpeed of 198 knots will be required k r maximum rate of descent. W h the gear extended, flaps retractsd and cowl flaps closed, an airspeed of 132 knots will also give approximately the same maximum rate of descent. At 132 knots and the gear extended, the angle of descent will be reater, thus resulting in less horizontal distance trawled than a descent at 196 knots. A8ditionally, a descent at 132 knots will provide a smoother ride and a safer airspeed in the event air turbulence is encountered, resulting in less pilot workload. Therefore: The following procedureshould be used for an emergency descent: Power . . . . . . . . RETARD initiall Airspeed . . . . . . . . . . . . . . 132 J Z K I A ~ Landin G a r . . . . . . . . . . . DClEND \IUng +laps . . . . . . . . . . . . . . . . UP CowlRe~s . . . . . . . . . . . . . . . . &OSU) Power ~ u r i n gDescent AS WQUIRED to maintain'cylinde; lie& ~'empkrathe300''~(149' C) minimum. MAXIMUM GUDE DISTANCE MODEL MZOJ ISSUED I - W 3 - 9 SECTION Ill EMERGENCY PROCEDURES MOONEY M20J POWER OFF - GEAR RETRACTED OR EXTENDED Emergenc Locator Transmitter . . . . . . . . ARMED Seat ~ettd~houlder Harnesses . . . . . . . SECURE Cabin Door . . . . . . . . . . . . UNLATCHED . . . . . . . . . . . . . . . Fuel Selector O R MMure . . . . . . . . . . . . . IDLE CUTOR . . . . . . . . . . . ~a~netolSiarter OFF Wng Raps . . . . . . . . . . Full l h V k 4 . (33 &fees) Landing Gear . . . . . . . DOW or UP Depend~n on Terrain Approach Speed . . . . . . . . . . . AS SLOWA 8 POSSIBLE . . . . . . . . . . Master Switch OFF, prior to landin Landing . . . . . . . . . . . . kkl,TAIL LOWA~T~TUD! [ SYSTEMS EMERGENCIES 1 PROPEUER PROPEUER OVERSPEED Throttle . . . . . . . . . . . RETARD . . . . . . . . . Oil Ressure . CHECK Propeller . . . . . D E C R ~ & ,set if any control avaliable Airspeed . . . . . . . . RUlUCE Throttle . AS &QUI& td mintain RfjM delow 2700 RPM FUEL -LOW FUEL FLOW Mixture . . . . . . . . . . . . ENRICH Fuel ~elecior . O ~ S I ? E(hiliest TANK Ifcondition u60 h e 1 B ~ O & P U & ~ d.n;ce&ary .~~'UNMNG SHOULD dE M E AS SOON AS PRACTICABLE. ELECTRICAL ALTERNATOR OVERVOLTAGE IVoltaae wamina liaM illuminated steady and Anernator F i l d circuit - - breaker apped.) Avionics Master . . . . . . . . . . . OFF Master OFF, then ON r ihk&inL'9ht is i iilumhatsd, the f&o&g & i s are r i u i r h : Alternator Re C rcun Breaker . RESET If circuit breaker fill not.re&t, the foilov;ing prkedures am rsquirad: 1. Non-esential electrical equipment . . . . OFF to conserve battery power. 2.. Land, when practical, to correct matfunction. ALTERNATOR OUTPUT LOW (Voltage warning light flashing; ammeter showing discharge) 1. Nonesential electrical equipment . O R to consem battery power. 2. Land, when practical, to correct maifunction. Battery endurance will depend upon battery condition and electrical load on the battery. - I NOTE I-A tripped main altemator circuit breaker can only be caused by a shorted alternator circuit and cannot be comcted by msetting braaker. This should be verifiid by attemptin to mset breaker not mom than one time. If this fails, turn alternator f 1 1 1 8 ~ c h OFF. Tum OFF all n o n = ~ n t i a IeIe?ric?l equipment and termmate fl~ghtas soon as practical. Repa~rmalfunct~on~ng atternator prior to next flight. 3 - 10 ISSUED 1 - 96 MOONEY M20J SECTION Ill EMERGENCY PROCEDURES LANDING GEAR FAILURE OF LANDING GEAR TO EXTEND ELECTRICALLY Airspeed . . . . . 132 KIAS or less Landing Gear h u k o r circuit baker . . . . . . . . PUU Gear Swiich . . . . , . . DOW Manual Gear ~xtension'~edha&m . . L A ~ HFOR~M~DIL&ER BACK to engige manual extension mechansm. 7 I N O W - Stowly pull T handb 1 to 2 inches (2.6 t o 6.1 cm) t o rotate clutch rnechanim and allow it to engage drive shaft. T-Handle . . . . . . . W U (12 to 20 times and +nh'untii gear is down and locked, GE4R D O W light illuminaled; STOP when resistance is felt. Visual Gear Dawn Indicator . . . . CHECK ALIGNMENT by viewing ' h m dl&ly above the indicator. ......- CAUTION -- - - - - -Continuing t o pull on THandle after GEAR DOWN light ON will bind actuator; elscbiCal mtractlon MAY NOT be posribb until bindin0 is eliminafad. Return lever to normal position and recum latch. Reset landing gear actuator CIB. lNilNllllllll IMlARNlNON 111111111111111 Do not opereta landing gear ekctricalty with manuel extension system engaged. FORCED IANDING EMERGENCY GEARRETRACTEDORWTENDED Emergency Locator Transmitter . . . . . hWhlED Seat Belts and Shoulder Hamesses . . . SECURE Cabin Door . . . UNLATCHU) when sum of making landing ama: Fuel Selector . . . . . . . . . . . . . . O R Throttle . . . . . . . . . . . . . AS'REQUIRED M iure . . . . . . . . IDLECUTOFF ~ a g n e l o l ~ l a i e r . . . . . . . . . . . . OFF WngFlaps . . , , . . FliLdOhkl 3 3 ) LandingGear . : ~ ~ ~ D O ~ ~ ~ D ~ P E N D I N G O P J ~ E Master Switch . . . . . . . . . . . . OFF Approach Speed . . . . . . . . . & SLOW'& ~ossible Landing . . . . . . . . Lb&, TAIL LOW A l l l N D E FAILURE OF LANDING GEAR TO RETRACT AIRSPEED . . . . . . . . . . . . . . Below 107 MAS GEARSwiich . . . . . . . . . . . UP IF GEAR FAILS TO RETRACT, GEAR HORN - SOUNDING, GEAR ANNUNCIATOR LIGHTS and GEAR SAFElY BY-PASS LIGHT -ILLUMINATED: GR SAFETY BY PASS SWTCH . . DEPRESS and 'Hob until landing gear kllyretracted GEAR D O W and GEAR UNSFE Ughts . ECnNGUlSHED GEAR RUAYS Circuit Breaker PULL ( & m i n i h& and 6ear'By-~a&light wili g o ' ~ F F ISSUED 1 - 96 3 - 11 SECTION Ill EMERGENCY PROCEDURES MOONEY M20J IF GEAR FAILS TO RETRACT, GEAR HORN -DOES NOT SOUND, GEAR ANNUN- CIATOR LIGHTS and GEAR BY-PASS LIGHT - NOT ILLUMINATED: EMERGENCY GEAR EXTENSION LEER . . Verify LATCHED in proper position. GEAR RELAYS Circuit Breaker . . . . . . . RESET CONTINUE FLIGHT If desired. When ready to extend knding gear: . . . . . . . . . AIRSPEED Below 132 KlAS GEAR RELAYS'CIR~UIT 6 - . . . . . . . . . RESFT GEAR SWATCH . . . . . . . . DOWN position If gear will not eatend electrically, refer to FAILURE OF LANDING GEAR TO EXTEND ELECTAICALLY. OXYGEN Refer to SECTION IX, if aircrafl is equipped with oxygen. ALTERNATE STATIC SOURCE The alternate static air source should be used whenever it is suspected that normal static air sources are blocked. Selecting Alternate Static Air changes the source of static air for altimeter, ainpeed indicator and rate-of-climb from outside aircraft to cabin interior. M e n alemate static air source is in use, adjust indicated ainpeed and altimeter readings according to the appropriate alternate static source airspeed and altimeter calibration tables in SECTION V. The static air source valve is located on lower left portion of pilot's Riiht panel above pilot's lefl knee. When using the altomate static source th pilots window and a i ~ e n t s MUSTBEKEPTCLOSED Alternate Static Source . . . . W U ON Airspeed and Altimeter ~ e & i n & . . . ~ ~ ~ ~ ~ ~ a l i b r a t i o n s ' ~ a b l e s , 'SECTION V 1 UNLATCHED DOORS IN FUGHT I CABIN DOOR If cabin door is not properly closed it may come unlatched in lliight. This may occur during or just after take-off. The door will trail in a position a proximately 3 inches (7.6 cm) open, but flight characteristics of the airplane will not be aimed. Retum to the field in a normal manner. If practicable, secure door in some manner to prevent it from swinging open during landing. If it is deemed impractical to return and land, the door can be closed in tiight. afler reaching a safe altitude, by the following procedures: Airspeed . . . . . . . . . . . . . . . . QSKIAS Pilot's Storm findow . . . . . . . . . . OPEN Arcrafl . . . . . . . . RJGHT S ~ D E ~ I P ( w h t bank . . . . . . . . . . . . . . . with leR rudder) Ddor . . . . . . . . . piiuSHUT LATCH BAGGAGE DOOR If baggege door is not properly closed, it may come unlatched in flight. This may occur during or afler takeoff. The door may open to its full open position and then take an intermediate position d ending upon speed of the aircrafl. There will be considerable wind noise; loose, light gjects may exit aircrafl if in vicinity of open door. There is no way to shut and latch door from inside; fly aircrafl in normal manner; LAND AS SOON AS POSSIBLE and secure baggage door. 3 - 1 2 ISSUED 1 - 96 MOONEY M20J EMERGENCY SECTION Ill PROCEDURES Baggage Door latching mechanism MWN PROPERLY ENGAGED . (insidelat~hingme'chanism)thenshutfmmtheoutside. I ICING 1 111111111111111 IMIARNINGII IIIIIIIIIIIIII/ DO NOT OPERATE IN KNOWN ICING CONDITIONS. The Model M M I is NOT APPROVED for flight into known icing conditions and operation in that environment is prohibited. However, H those conditions are inadvertently encoun- tered or lfi ht into heavy snow is unavoidable, the following procedures are recom mended until%rther icing conditionscan be avoided: INADVERTENT ICING ENCOUNlER Pitot Heat . . . . . . . . . . . . . . ON Ropeller ~ e - l c e . . . . . . . ON '(F installed) Alternate Static Source . . . . . . . . . . . ON (rf required) Cabin Heat & Defroster . . . . . . . . . . . . . . ON Turn back or change attnude to obtain an outskie air temperature less conducive to icing. Move propeller control to maximum f?FW to minimire Ice build-up on propeller blades. If ice builds up or sheds uneventy on propelter, vibration will occur. M excessive vibration is noted, momentarily reduce e ine s eed with propeller control to bottom of GREEN ARC, then rapklily move control FdxF O ~ . -l N o w -Cycling RPM flexes propeller blades and high RPM increases centrHuga1 fone which improve8 propeikr capability to shed ice. As ice builds on the airframe, move elevator control fore and aR slightly to break any ice build-up that may have bridged gap between elevator horn and horizontalstabilizer. Wtch for signs of induction air finer blockage due to ice build-up; increase throttle setting to maintain manifold pressure. - IN o w -W ice blocks induction air filter, atternate air system will open automatically. VUth ice accumulation of 114 inch or more on the airframe, be prepared for a significant increase in aircmR weight and drag. This will result in SQnificantly reduced cruise and climb performance and higher stall speeds. Plan for higher approach speeds requiring higher power settings and longer landing rolls. -..---- - CAUTION -- - m e - . . Stall warning system may be inoperative. The defroster ma not clear ice from windshield. If necessary open pilot's storm window for visibility in lanAng approach and touchdown. VUth ice accumulations of any amount, use no more than 15' flaps for approach and landing. fly approach speeds at least 10 knots higher than normal, expect a higher stall speed resulting in higher touchdown speed with longer landing roll. Use normal flare and touchdown technique. Missed approaches SHOULD BE AVOIDED whenever possible because of severiy re- duced clmb performance. If a go-around is mandatory, apply FULL POWER, retract landing gear when obstacles are cleared; maintain 90 WAS and retract wing flaps. SECTION Ill EMERGENCY PROCEDURES MOONEY M20J 1//11111111/11/1 11 WARNING I1 11111/111/1!1111 Up to 2000 feet altitude ma be lost a a o m turn spin and recovery; STALLS AT LOW ALXTUDEARE EXTREMELY CRITICAL - l NOTE1 -The best spin lacowry mchnique is to avoid flight conditions conduchm t o spin entry. Low s m d flight near stall should be a roached with caution and excrssive flight control m m m r n r s in this fl& regime should be avoided. Should an unintentional stall occur the r i n n f t should not be atlowd to progress into a deep stall. Fast, but smooth stall mcovery will minimuze the risk of progressing into a spin. If an unusual post stall attitude develops and results in a spin, quick application d antispin procedures should shomn th lacowry. INTENTIONALSPlNS ARE PROHIBITED. In the event of an inadvertent spin, the following recovery procedure should be used: Throttle . . . . . . . . . . . RETARD lo IDLE Ailerons . . . . . . . NEUTRqL Rudder . Apply FUU RUD* opposite ;he direction of sptn Control k e e l . . FOR\IWW)of neutral in a brisk motton . Additional ~ d d e l e \ r n t o ;control may be required ifthe rotation does not stop HOLD ANTISPIN CONTROLS UNTIL ROTATION STOPS. Wng Flaps (If extended) . FEIWCT as soon as possible Rudder . . . . . . . . . NEUTRALIZE when spin stops ~ o n t r o l ~ e e l . . . . . . . SMOOTHLY MOM AFT . . . . . . to bri;lg the nose up to level flight altitude. I EMERGENCY EXIT OF AlRCAFf I CABIN DOOR WLL latch handle AFT. OPEN door and exit aircraft. BAGGAGE COMPARThlENT DOOR (AUXILIARY WIT) Release (PULL U rear seat back latches on Spar. Fold rear seat bazs forward. CLIMB OMR PULL off plastic cover. WLL latch pin. Lift red handle "UP. OPEN door and exit aircraft. To VERIFY RE-ENGAGEMENT of baggage door outside latch mechanism: Open outside handle fully Close inside RED handle to en age pin into cam slide of latch mechanism Place lalch pin in hole to hold !ED handle D O W Re lace cover. C&CK and operate outside hendie in normal manner. ISSUED 1- 96 MOONEY M20J SECTION Ill EMERGENCYPROCEDURES I OTHER EMERGENCIES] Refer to SECTION IX for EMERGENCY PROCEDURES of Optional Equipment. ISSUED 1 - 98 SECTION Ill EMERGENCY PROCEDURES BLANK MOONEY M20J ISSUED 1 - 96 MOONEY M20J SECTION IV NORMAL PROCEDURES TITLE . . . . . . . . . . . . . . . . . . . . PAGE INlRODUCTION . . . . . . . . . . . . . . . . . . . PREFLIGHT INSPECTION . . . . . . . . . . . . . . . . BEFOE STARTING CHECK . . . . . . . . . . . . ENGINE START . . . . . . . . . . . . . . . . . . FLOODED ENGINE START . . . . . . . . . . . . . . . \NRM ENGINE START . . . . . . . . . . . . . . . . . BEFORE TAXI . . . . . . . . . . . . . . . . . . . . TAXI . . . . . . . . . . . . . . . . . BEFORE TAKEOFF . . . . . . . . . . . . . . . . . TAKEOFF . . . . . . . . . . . . . . . . . . . . CLIMB . . . . . . . . . . . . . . . . . . . . . . CLIMB (CRUISE) . . . . . . . . . . . . . . . . . CLIMB (BEST RATE) . . . . . . . . . . . . . . . . CLIMB (BEST ANGLE) . . . . . . . . . . . . . . . CRUISE . . . . . . . . . . . . . . . . . . . . . . FUEL TANK SELECTlON . . . . . . . . . . . . . . . . DESCENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPROACH FOR LANDING GO AROUND (BAU<ED LANDING) . . . . . . . . . . . . . LANDING . . . . . . . . . . . . . . . . . . . . . TAXI AFTER IANDING . . . . . . . . . . . . . . . . . SHUTDOW . . . . . . . . . . . . . . . . . . . . SECURING AIRCRAFT . . . . . . . . . . . . . . . . . ISSUED 1 .96 4 SECTION IV NORMAL PROCEDURES MOONEY M20J IINTRODUCTION I This section describes the recommended procedures for the conduct of normal operations for the airplane. All of the required (FA4 regulations) pmcedures and those necessary for operation of the airplane as determined by the operating and des$n features of the airplane are presented. These procedures are provided to present a source of reference and review and to sup ly information on procedures which are the same for all aircraft. Pilots should farniliaRe themselves with the procedures given in this section in order to become proficient in the normal operations of the airplane. Normal procedures associated with those optional systems and uipment which require handbook supplements are provided by SECTION IX (~upplemenaData). ISSUED 1 - 88 MOONEY M20J SECTION IV NORMAL PROCEDURES PREFLIGHT INSPECTION 1 1. Cockpit - Gear Switch . MagnetoIStarter&itch' Master Switch . . Rocker Switches . . Circuit Breakers . . Battery Voltage IntemaUExtemalG h t s ' Fuel Gauges - Quantly Piot Heat Swiich . , Piot Heat Swiich . . Master Swiich . . Dow . . . . . . . . . . OFF . . . . . . . . . . . ON . . . . . . . . . . . O R . . . . . . . . . . . . . . . . . . IN . C I ~ E C K ~ ~ - ~ ~ ~ L T S ) CHLCK Operation . . . . . . . CHECK ' 0 ~ : ~ h e c kfjitot ' ~ e i~nnunciatorIUUMINATU) OFF . . . . . . . . . . . . O F F . . . . . . . . . . 2. W h t FuselqeKail Cone- Instrument.Sat~cPp? . . . . . . . UNOBS7RUC7ED General Skln Condi~on . . . . . . . . . . . . . INSPECT Access Panels . . . . . . . . . SECURED Tail Tiedown . . . . . . . . . m O b E 3. Empennage - Elevator and Rudder attach points and control linkage attachments . . INSPECT General Skin Condition . INSPECT-Remove ice, snow, or fmst. 4. Lefl Fuselageflail Cone- Fresh Air Vent (on Dorsal Fin) . . . . . . . . . . CLEAR Instrument ~ l a t ~ c port . . . . . . . . . . UNOBSTRVCTED General Skin Condition . . . . . . . . INSPECT TallconeIErnpennege~ c c e s iDoor . . . . . SECU- Static System Drain Valve . . . . . . . . . PUSH UP (Hold 3 5 k o n d s ) ISSUED 1 - 98 4 - 3 SECTION IV NORMAL PROCEDURES MOONEY M20J 5. Lefl VUng -General Skin Condlion . Rap and attach points . Aileron and attach points . Contml Linkeges . Wng Tips, Lights and iens ' Pitot Tube . . . Land, TTaxi lights . . Stall %ming Vane . . Fuel Tank . . . . INSPECT-Remove ice, snow, or frost. . . INSPECT . INSPECT . . . INSPECT . . . . . INSPECT . uN0ssTRUcTED . INSPECTkndbulbs UNOBSTRUCTED : CHECK QUANTITY-SECURE CAP - l N O W - A mduced fuel indicator is located in the filler neck. This indicator is used t o indicate useable fuel capacity of 26 U.S. gallons (94.7 Firs) (20.8 IMP. Gal.) - INOT4 -The optional v i s w l fuel uanUty gaugr is to be used for partial refueling purposes oAy; DO NOT uoe for p n ~ i p ~ check. Tiedown . . . . . . . . . . . . . . . REMOM Tank Vent . . . . . . . . . UNOBSTRUCTED M e e l Chock . WMOVE Lee Main Gear, shock biscs, Tire, doors (L &k&e . . . . INSPECT Fuel Tank Sump Dram . . . . . . . . D&IN Until Clear Pitot System Drain Valve . . . . . . . . . W S H UP ( H o i fo; 3-5.seconds) Gascolator Drain Valve . . . CLOSED (Check for drips) 6. Left Cowl Area -Wndshield . . . . . . . . . . . . . . . . CLEAN . . . . . . . . . . Cabin Air inlet Unobstructed Left Side Engine cowl Fasteners . . . . . . . . . SECURED . . . . . . . . . . . . . . . Len Cowl Flap INSPECT 7. PropellerJSpinner(L Front Cowl - . . . . . . . . . . . . Blades INSPECT for nicks, cracks, oil leaks, rotational, movement. INSPECT deice boots(8f mstalled). Spinner . . . , . , . . INSPECT for security, cracks Coolin Air and 1nd;ction lntake . . , . . UNOBSTRUCTED . . . . . . . Nose &ar, Shock D i s , Tire, D O O ~d iinkige INSPECT . . . . . . . . . . . . . . . . W e e l chock M O M 8. f?IQhtCowl Area - . . . . . . . . . . Right Side Engine Cowl Fasteners SECURED Engine Oil Level . . . . . . . CHECK (FULL for extended flighi.(~&. 8 qts.) (Minimum qty. 6 qts.) . . . . . . . . . . . . . . . Exhaust Pipe SECURED . . . . . . . . . . . . . . . Right Cowl Flap INSPECT Wndsh~ekl . . . . . . . . . . . . . . . CLEAN . . . . . . . . . . . . Cabin Air Inlet UNOBSTRUCTED 9. f?IQht bung - Fuel Tank Sump Drain . . . DRAIN until clear Right Main Gear, Shock D i i s , %re,'Do& B' ~ i n k a ~ e. . INSPECT M e e l Chock . . . . . . . . . . REMOVE . . . . . . . . . . . . . Tank Vent U ~ ~ ~ ~ ~ T R U C T U ) Tiedown . . . . . . . . . . . . . . . REMOM Landingmaxi lights . . . . . . . . IN&CT lendbulbs . . . . . . . . . . Fuel Tank CHECK QUANTITY-SECURE CAP 4 - 4 ISSUED 1 - 96 MOONEY M20J SECTION IV NORMAL PROCEDURES -lN o w -The mduced fuel Indicator Is located in the filler neck. This indicator is used to indicate usable fuel capacity of 25 U.S. gallons (94.7 liters) (20.6 IMP. gal.) The o p t i o ~ lvisual fuel quantity gauge is to be wad for pattial refueling purposes only; DO NOT uu, for pmflight check. Y n g Tip, L4hts 6 Lens . . . . . . . . . . . . . INSPECT kleron and attach points . . . . . . . . . . . . . INSPECT Flap and attach points . . . . . . . . . . . . . INSPECT Control Linkages . . . . . . . . INSPECT General Skin Condiiimn . INS~CT-WMO\~E ice, snow or frost 10. Baggage Door . . Verify SECURED \ieri$ inside iatch mechariisrn'is p~ope;ly secured. (Check outside handle operation) 11. Retum to Cockpl Fuel Selector . . . . . . . . . . R W U gascolator ring (5 seconds) Fuel Selector . . . . . . . L: W U gascolator ring (5 Gconds) Master Switch . . . . . . . . . . . ERIN OFF I BEFORE STARING CHECK 1 Preffight Inspection . . . . . . . COMPLmD Seats. Seat Beftsl~houherHamess ifoccuoant oer restraint) . JUST & SECURE . .MagnetolStarter Swiich . . . '. . . . O R Master Witch . . . . . . . . . . . . . . . O f f Alternator Fietd Swkch . . . . . . . . . . . O R Radio Mester M c h . . . . . . . . . . . . . O R . . . . . . . . . . . . . Fuel Boost Purno ~ . . . . . . . . . . . . 0% ~nernaieStatic Source , . Rocker Switches Directional Gyro (siaveliree'switch) ' Circuit Breakeffi . Emergency Locator ~ r a n s ~ n e r ':Throttle . . . . . . . Propeller . . . . . . . Mixture Cowl flaps (check'op&atick o f ' ~ ~ t i o ~ Parkin Brake. . . . . . ~ n g Aap switch . . . . Cabinvent . . . . . . CabinHeat . . . . . . Defrost . . . . . . . . . . . . Fuel seiecior Radios . . . . . Landing &ar &itch . . EllEmergency Gear ~andle . . Internal u h t s . . . . . Passengers . . . . . . elec . . . . . . . . . , Push off . . . . . O R . s ~ ~ k O ' ( i f installed) , CHECK . . . . . CLV: . HIGH l IDLECUl . . . . . . c cowl flaps) . . MRIFYO . . . . . . . . P l . Pt FULLEST TI sE? F~?~QUENCIES(Nondigital rad . . . . . . W . D O V U J ~ L A T C ~ A m 'SED RFM 'OR PW SET UP) IRED OFF O R VJK 10s) IYUJ +ED 3FF . Ernergency/General information briefing Refer to SECTION IX for Optional Equipment Checks. Obtain local information prior to engine Start. ISSUEDl-96 4 - 5 SECTION N NORMAL PROCEDURES MOONEY M20J \ENGINE START I - - - - - -- CAUTlON -- - - - - -When battery will not start engine, inspection should be conducted to determine reason. if determination is made that battery voltage is low, sewicing of the batteiy is essential and charging for at least one hour should be done before engim hi started. The batlory or other electrical circuits may be damaged if aircraft is operated with a low battery. INOm I -When starting engine using an approved external power wume no special starting rocedure is nacessary. Use normal starting rocedures below. ( ~ u x i & P o w r Cable Adapter Is available fmm doonly Aircraft ~orpomtiot!J. e m r y swouu, NOT BE c ~ M P L E ~ ~ ~ DEPLEE~)m n engine is to be started using an external power source. Before Starling Checklii Throttle . . . . Cowl Flaps . . . Propeller . . . . Mixture . . . Master Swiich Alternator Field Swkh ' Annunciator Lights . Fuel Boost Pump . . Mixture . . . Ropeller k e a MagnetolStarler G i c h ' . . . . . . . . COMPLETED 114 OPEN . . . . . . . . . . . . . . . . . . . . . . . OPEN . . . . . . FUUFORWAFZD . . . . . . . . FULLFOR\IWRD . . . . . . . . . . . . . . ON . . . . . . . . . . . ON +RE& TO TEST . . . . . . . . . . . . . . . . . . . ON to ~stabliihpressure, then OFF . . . . . . . . IDLE-CUTOFF . . . . . . . . . CLEAR . . . . . lUkN and ~ U S H to START release to both when engine starts. INOTE I "START POWERn warning light should illuminate whan magnetdstarter switch is in %TART" position and MUST extinguish when starter switch is released. I NOTE I - Cranking should be limited to 30 seconds and rewral minutes allowed betwen cranking periods to permit the starter to cool. Mixture . . . Move slowly and smoothly to RICH prottle . . . . . . Set at 1000 to 1200 RPM Enaine Oil Pressure . . CHECK G% -'if MINIMUM OIL FFESSUE - is not indicated wlhin 30 seconds, STOP ENGINE and determine problem. 'Ammeter . . . . . . . CHECK (Tum ~ d ~ . it. ON; dbseive neQiivemovement oi needle) IntemaVExtemai Lights . . . . . . . . . As Desired ' Engine Instruments . . . . . . . . . . CHECKED Fuel Flow Indicator . . . ~ S ~ ~ S E T (if desired) -----., - CAUTION -...... Do not operate engine at runvp speed unless the oil temperature is at least 75' F. (needle moves off White dot). Operation of the engine above 1200 RPM before reaching minimum oil temperature may cause engine damage due to insufficient oil flow for lubrication. 4 - 6 ISSUED I- 96 MOONEY M20J SECTION N NORMAL PROCEDURES I FLOODED ENGINE START 1 Fuel Boost Pump . . . . . . . . . . . . . OFF mrottle . . . . . . . . . . . . . . . FUU'FO~\N~RD M i u r e . . . . . . . . . IDLE CUTOFF ~agnetol&art&&itch' . . . fU6 and PUSH to start release to both when engine starts. M i u r e . . . . . . . . . . NUFORWWD Thm!le . ketard to 1200 PJJM WER to remaiAng ~ N ~ N E ' S T A ~ T proc;sduk above. 1WARM ENGINE START 1 Fuel Boost Pump . . . . . . . . . . . OFF mronle . . . . . . . Mixture . . . ~ m n e t o l ~ i a r t e i G i c h ' . . . Slight1 open . . . . . . . . . . . . FUI~~~~IDLE-CXOF. NRN and PUSH to start - release to both when engine starts. M i u r e . . . . . . . . . Move slowly and smoothly to RICH ThroFle . t o w t o l2OOFiPM REFER to remaining ENGINE'ST~pro&uks above. Engine Start Checklist . . Radio Master Switch . . . Elevator Trim Switch . . . Annunciator Panel , . . IntemaVExtemalLights . . Directional Gyro . . . . Instruments . . . . . R R d i o s . . . . . . Attimeter . . . . . . Fuel Selector . . . . . Cowl Flaps . . . . Equipment Checks . . . COMPLETED . . . . . . . . . . . . . . . . As desired & T O ~ S ~ A ~ S \ M T C H - O N . . . . . . . . . . . . . Normal indications . CHECK (Set Frequencies . . . . . . . . . . 4. . . . . . &ich tanks ve;ify engi;le i n s on other tank . . . . . CHECK OPEPATION (FULLOPEN or AS FEQUIRED) . Refer to SECTION IX -During cold weather, ground operations may be conducted with cowl flaps partially or fully closed to keep engine bmpemhtrns in normal operating ranges prior to takeon. Houuaver, if cowl Raps am fully closed, monitor engine tempemturns to avoid exceeding maximum allowable limits. Before Texi Checklist . . . . . . . . . COMPLETED Parking Brake . . . . . . . . . . . . . Release Brakes . . . . . . . . . . ~1;eck'duringTaxi Directional.~~ro . . . . &per indication during turns Turn Coordinator . . . Pmper indication during turns Artificial Horizon . . . . . . . . . . Erect during turns Throttle . . . . . . . . . . . . . . Minimum power Cowl Raps . . . . . . . . . . . . . OPEN or As Desired Propeller . . . . . . . . . . F U U W SECTION IV NORMAL PROCEDURES MOONEY M20J - - - - - -- CAUTION -- - - - - -To pmvent battery de letion in prolonged taxi or holding position befom takeoff, increase ~ P M until ULOW VOLTAGE" l i ~ Mext~nguishes. [ BEFORE TAKEOFF 1 Taxi Checklist . . . . . . . . . . . . . . COMPLFlED Parking Brake . . . . . . . . . . . . . . SET Fuel Selector . . . . . . . . . . . FUI~ESTTANK Ptopeller . . . . . . . . . . . HIGH RPM M i u r e . . . . . . . . . . . . Full Forward cowl naps . . . njuOPW0; AS REQUIRED Throttle . . . . . . . . . 1800-2000 RPM Magnetos . . . C H E C ~Bbth to L, 00th to R b t h (~ax/mu&175 ~lkl drop each magneto, 50 RPM Difference) An absence of RPM drop may be an indication of faulty magneto grounding or improper timing. If them is doubt concerning ignition system operation, RPM checks at a leaner mixture setting or higher engine s p e d will usually confirm whather a deficiency exifts. Propeller . . . . . . . . . CYCWretum to high RPM (3 times) Ammeter . . . . . . . . CHECK posnive charge indication ~onunciatorP & ~ I . CHECK'ALT VOLTS a HULO VAC I. M~OFF Throttle . . . . . . . . Retard to l8LE RPM Trim . . . . . . . . . . Takeoff setting wng Flaps . check' opiratiin-SiT TAKEOFF POSIT~ON (15 degrees) Right Controls . . . . . . . Check free and correct movement . . . . . . . . Cabin Door CHECK SECURED Seat Belts and hould& ~ & e & . . . . . . . . SECURED Avionics and Auto Pilot . . . . . . . . . CHECK (Refer to' SECTION 1x1 InternaVExtemal Light . . . . . . &Desired Rotating BeaconIStrobe ~ i ~ h t s . . . . . . . . . . . ON Pilots Wndow . . . . . . . & O E D Emergency Gear ~;ttension'(Reb)~andle . . . . DOV& and LATCHED Annunciator Liihts . . . . . . . CHECK PROPER INDICATION Parking Brake . . . . . . . . . . . Release Before Takeoff Checklist . . . . . . . . . . . . COMPLl?ED - l Now - Move the engine controls slowly and smoothly. In paiticular, avoid rapid opening and closing of the throttle as the engine is equipped ~h a countervce~ghtedcrank shaft and them IS a postibillty of detunlng the counter-wights with subsequent engine damage. Proper engine operation should be checked early in the takeoff roll. Any siginificant indicb tion of rough or sluggish engine response is reason to discontinue the takeoff. M e n takeoff must be made over a gravel surface, 1 is important that the throttle be applied slowly. This will al!ow the aircraft to start rolling before a high is developed, and gravel or loose matenal w~llbe blown back from the propeller area instead of being pulled Into 1. 4 - 8 ISSUED 1 - W MOONEY M20J SECTION IV NORMAL PROCEDURES TAKEOFF (NORMAL) Electric Fuel Boost Pump . . . . . . . . ON at start of takeoff roll Power . . . . . I%u THROTTLE (2700 M i u r e n j l ~ kcli ( i i a n for shooin operation at HIGH Engine lnsi~mentsi~nriunciatar Panel . . . CHECK for proper tndkatlons LtRofflClimb Speed . . . Ar specilied in SECTION V (Normal Takeoff Distance) Landing Gear . fmRACT in Climb afler clearing obstacles. Wng Fla s . . . . . . . . . . UP Electric !&el &ost.pump , . . . . . . . . 0Fk - ~ H E ~ K k s s u r e - l NOTE1 -If applicable, use noise abatement procedume as required. - l NOTE1 - See SECTION V for rate of climb graph. CUMB (CRUISEL Throttle . . . . . . 26" Hg Manifold Pressure Ropeller . . . . . . . 2800RPM Mixture . RICH (iean for'Srnooth'0peration 4 high elevation) Cowl Flaps . . . . FULL OFWd or As Required Airspeed . 90 to 100 KlAS Maintain these power skttings a;ld Allude to at i e a i 3060 fekt AGL o r cruise altttude. Manifold pressure will drop with increasing altlude et any throttle setting. Power can be restored by gradually opening the throttle. CUMB (BEST RATE)(Vy,I Power . . . . . FULL T H R O W and 2700 RPM . . . . . . . . . . . Mixture NURICH (Lean at higher attiiudes for smooth o eration) Cowl Flaps . . . . . . . . . . . . . . Airspeed ~ U UOPEN . . . . . . . . . . 88 KIAS at sea level decreasing l o 80 KlAS at 10,000 R. CUMB (BEST ANGLE)/Vx] Power . . . . . . FULL lHR0TT.E and 2700 RPM M i u r e . . . . . . . . F U U RICH (Lean at hiiher altlude for smooth operation) Cowl Raps . . . . . . . . . . . FULL OPEN ~irspeed . . . . . . W'KIAS at'sea'kvel increasing approximately 1.0 KlAS for each 5000 feet altlude ISSUED 1 -96 4 - 9 SECTION IV NORMAL PROCEDURES MOONEY M20J ICRUISE Upon reaching cruise altitude, accelerate to cruise airspeed; retrim aircraR as necessary for level fi' ht. Set manifold pressure and W M for desired power setting per Cruise Power Chart in &TION Vand close cowl naps. U s e recommended engine break-in procadurns as published by engine manufacturer. Electric cowl flaps may be openad slightly in order to keep engine temperatures within g m n arc. M e n electric cowl flaps are OPEN during cruise, the following effects on cruise speed will resuit: Cowl Flap's position indicator - 114 open (indicator positioned at 1st Index) Approximate,loss in TAS . 2KTAS Cowl Flap's position ~ndicator- 112 open (indicaior positioned at 2nd index) Approximate loss in TAS . . . . . . . . 4 KTAS - * - M e n cruising at 75 % power or less, lean the mixture afler cruise power is established in accordance with one of the following methods: A. Leaning with exhaust gas tern erature gauge (EGT) installed. 1. Lean the mixture until exflaust gas temperature peaks on the EGT indicator. ECONOMY CRUISE - Enach midure (push mixture control forward) until EGT indicator drops 14' C (25 F) below peak. BEST POWER MIXTURE - Enrich mixture until EGT indicator drops 55' C (100' F) below peak. I N O W -Compared to Economy Cruise, Bast P o w r mixture will result in an increase in fuel flow and a reduction in range. 2. Changes in altitude and power settings require peak EGT to be rechecked and mixture re-set. 6.Leaning without exhaust gas tern erature gaugt, EGT) installed: 1. Sowly m o w mixture controflenr afl from bULL RICH" position towad "LEAN position. 2. Continue leaning until slight loss of power is noted (loss of power may or may not be accompanied by bughnessj. 3. Enrich until engine runs smoothly and power is regained. W e n increasing p o w r always return mixture to full rich, then increase RPM before increasing manifold pressure; when decreasing p o w r decrease manifold pressure before reducing WM.Ahvays stay within the established operating limits, and always operate the controls slowly and smoothly. 4 - 10 ISSUED 1 - 96 MOONEY M20J SECTION IV NORMAL PROCEDURES Boost Pump Switch . . . . . . Fuel Selector . . . . . . . h o s t ~ u m p&kch . . . . . . . . . . ON . , . . ~ ~ ~ ~ S I T ~ T A . OFF (Observe fuel pressure gauge for proper pressure reading) Mixture . . . . . . LEAN to 14' C (25'~) rich of peak EGT as required for smooth engine o eratlon Power . , . . , . AS ~ Q U I R E D to keep CI~T in ~ A n ' A r c(30dO ~(148'C)minimum) - - - - .# -- CAUTION- ----.,-Avoid continuous operation betwen 1600 and 1950 RPM with power settings below 15"Hg. manifold pmssum. e r c i s e caution with power settings bslow 16"ti manifold p~?bsu-reat elnpeeds between TO - H S WlAS to pnclude co&uous operaeon In the 1600 - 1960 RPM mstricted range. - - - - - -- CAUTION- - - - - - -Avoid long high speed descents at low mantfold p s r u m as the engine can cool excessively. Cowl flaps . . . . . . . . . . . . . . CLOSED - l NOXI -Plan descents to arrive at pettern attitude on domwind lag for maximum fuel efficbmy and minimum aircmfl noise. IAPPROACH FOR LANDING I InternaVExternalLights . . . . . . . . . . . . As desired Seat BeHslShouMer Hamess . . . . . . . . FASTENED Landing Gear . . . . MD below 132 KIAS (dear down lGht on - check visual indicator on floor) Mixture . . . . . . . . . . . F U U RICH Propeller . . . . . . . . . . . . HIGH RPM Fuel Boost Pump . . . . . . . . . . . . . . ON Fuel Selector . . . . . . . . . . . . . F U I ~ E ~ TTANK Wng Flaps . . . . . . . . . . . T ~ E OFF POSITION NUdo^ below 112 KIAS - - - - - -- CAUTION- - - - - - -To minimize control wheel forces when antsring landing configuration, timely now-up tfimming is mcwnended to counteract nosedown pitching moment caused by reduction of powsr andlor Ihp extension. Trim . . . . . . . . . . . . As desired Parking Brake . . . . . . . . . . . MRlFY O R ISSUED 1 - gB 4-11 SECTION IV NORMAL PROCEDURES MOONEY M20J - l N o w -The parking brake should be mchecked to pnclude partially applied brakes during touchdown. GO AROUND (BALKED LANDING) 1 - - - - w e - CAUTION- - - - - - -To minimize control w h e l f m e s during goaround, timely nose-down trimming is mcomended to counteract noseup pitching moment as power is incnased andlor flap ratnction. Power , M i u r e . Airspeed . VUng Raps Trim . . Airspeed Landing G a r Mlng Flaps Cowl Flaps Airspeed . . . . . . NUM R O W 2 7 0 0 PF.4 . . . . . . . . . . . FULLRICH . . . . . . . . 85,KIAS . T&o!+ p&ition a ~ e rciimb'establshed . NOSE D O W (to reduce control force) Accelerate to 76 WAS . . . . . . . . . . . . . . . . . . . . . E l R 4 C T . . . . . . . . . . . . . . . FElR4CT . . . . . . . . . . . . . OPEN . . . . . . . . . . . . ~ccekrateto 86 KlAS ( LANDING I LANDING (NORMAL1 Approach for landing checklid COMPLETED Approach Airspeed . . As specified AIR SECTION ~ ( N k a i &ding Dstances) Touchdown . . . . . . . . . . . Main wheels first (aligned wkh runway) Landing Roll . . . . . . . Lower nose wheel gently Brakes . . . . . . . . . . . . . . As requi~ed Fuel B o o s t ' ~ u m ~. . . . . . . . . . . . OFF afler landlng Landing information for reduced ltap settings am not available. See SECTION V for landing Distance tables. - l N O T -- ONE SUGGESTED MEMOD -Crosswind landings may be accomplished by using above procedums except maintain approach speed approximately 10 KlAS above normal. Use 16' flaps for crooswinds below 10 Kts and flaps UP for crosswinds over 10 Kts. $low aircraft to crab until short final, then set up sideslip (low wing into the mnd). Accomplish touchdown in slight win low sideslip and alnraN aligned wtth runway. During landing roll, position wig^ controls to counteract crosswind. - - - - - -- CAUTION -...... The landing gear may retract during landing roll if landing gear switch is inadvertently placed in the UP position. 4 - 12 ISSUED I - gB MOONEY M20J SECTION IV NORMAL PROCEDURES I TAXI AFTER LANDING I Throttle . . . . . . . . 1000 to 1200 R?M Wng Flaps . . . . . . . . . . . . . . . RRRACT Cowl Flaps . . . . . . . . . . . . . . FULL OPEN Trim . . . . . . . . . . . . . . . . WSETto ~akeoff Radios . . . . . . . . . . . . . . . . As required Lighting . . . . . . . . . . . . As required [ - I Parking Brake . . . . . . . . . . . . . SET Throttle . . . . . . . . I& d i2bo WM (until cylinder head iemperature starts to drop) Radio Master . . . . . . . . . . . . . . . 0- InternaVExtemal ~ights . . . . . . . . . . . . OFF . . . . . . . . . . . MagnetoIStarIar Swiich ~ioundingCheck Mixture . . . . . . . . . IDLE CUTOFF . . . . . . . . . ~agnetol~iart&&itch' 0k when propeller sto s Afternator meld Swlch . . . . . . . . . . . . . . Master Witch OR. . . . . . . . . . . . . . off . . . . . . . . . . . . . Oxygen System (if equipped) O R MagnetolStarter . Master W i c h . Radio Master . Uectrical Switches Parking Brake . For extended parking 1SECURING AIRCRAFT I . . . . . . . OFFIKey removed . . . . . . . . . VERIFYOFF . . . . . . . M R l N O F F . MRIWOFF . . . . . . . . . . ~ S E and install wheel chocks . . . . . . . Control wheel - SECUEO wih Get belts; cabin vents CLOSED, TIE DOWN eircran at wing end tail points. ISSUED 1 - 98 SECTION IV NORMAL PROCEDURES BLANK MOONEY MZOJ ISSUED 1 - 86 MOONEY M20J SECTION V PERFORMANCE TABLE OF CONTENTS 1 TITLE . . . . . . . . . . . . . . . . . . . . PAGE INTRODUCTION . . . . . . . . . . . . . . . . . . . 5-3 VARIABLES . . . . . . . . . . . . . . . . . . . . 5-3 OPERATIONAL PROCEDURES FOR MAXMUM FUEL EFFECIWCY . . 5-3 P E R f O W C E CONSIDERATIONS . . . . . . . . . . . . 5-3 RANGE ASSUMPTIONS . . . . . . . . . . . . . . . 5.3 USEOFCOVKflAPS . . . . . . . . . . . . . . . 5-4 MAIN LOG GEAR LO= DOORS REMOVAL . . . . . . . 5-4 OPERATIONAL CONSlDERATlONS . . . . . . . . . . . . . 5-4 . TABLES AND CHARTS . lEMPEAATUfE C O N W I O N . . . . . . . . . . . . . . 5-5 CROSSWND COMPONENT . . . . . . . . . . . . . . . 5-6 AIRSPEED CAUBRATION P R I W STATIC SYSTEM(GEAR UP) . . . 5-7 AIRSPEED CALIBRATION PRlMARY STATIC SYSTEM(GEAR DOW) . 5-8 AlRSPEEOCALlSRATlON A L M A T E S T A l l C SYSTEM . . . . . 5 9 ALTlMElER CORRECTION PrUMARY STATIC SYSTEM (GEAR UP. FLAPSUP) . . . . . . . . . . . . . . . . . 5-10 ALTIMETER CORRECTION PRJMARY STATIC SYSTEM (GEAR DN. FLAPS DN) . . . . . . . . . . . . . . . . . 511 ALTIMETERCORRECTIONALTEF@hIlESTATICSYSTEM (1) . . . . 5-12 ALTIMEERCORIECTION ALTEF@hITESTATIC SYSTEM (2) . . . . 513 STALL SPEED VS ANGLE OF BANK . . . . . . . . . . . . 5-14 TAKEOFF DISTANCE .HARD SURFACE . . . . . . . . . . . 5-15 . TAKEOFF DISTANCE GRASS SUEACE . . . . . . . . . . 516 RATE OF CLIMB .TAKEOFF (klA)O . . . . . . . . . . . . . 5-17 RATE OF CLIMB .N O W (CRUISE) . . . . . . . . . . . . 518 BALKED LANDING CLIMB . . . . . . . . . . . . . . . . 519 TIME FUEL & DISTANCE TO CLIMB . . . . . . . . . . . . 5-20 CRUISE & RANGE DATA CONDITIONS . . . . . . . . . . . 5-22 CRUISE POWER SCHEDULE . . . . . . . . . . . . . . . 5.23 SPEED POWER VS ALTiTUDE . . . . . . . . . . . . . . 525 RANGE75% P O W . . RANGE65% POWR . . RANGE55% P O W R . . RANGE45% W W R . . ENDURANCE 75% P O W ENDURANCE 65% POWER ENDURANCE55% POW33 ENDURANCE 45% P O W SECTION V PERFORMANCE ITABLE OF CONTENTS (con't)] MOONEY M20J . . . . . . . . . . . . . . . . . . . . T I N PAGE -TABLES AND CHARTS (con%) -LANDING DISTANCE - HARD SURFACE . . . . . . . . . . . S34 LANDING DISTANCE - GRASS SUFIFACE . . . . . . . . . . 535 ISSUED 1 - Q6 MOONEY M20J ( INTRODUCTION 1 SECTION V PERFORMANCE The purpose of this section is to present the owner or o erator with information needed to facilitate planning of f i h t with resonabla accuracy. i(le Psrbrmance Data and Charts presented are calculated based upon actual flight tests with airplane and engine in good condition and the engine power controls stem properly adjusted. The flight test data has been corrected !o lnternational Standard Atmosphere conditions and then expanded analytically to cowr various alrplane gmss weights, operating altitudes and outside air temperatures. It is not possible to make allowances in the charls for varylng levels of pilot technique, proficiency or en!h'c)nmental conditions. Mechanical or aerodynamic changes are not authorized because they can affect performance or flight characteristics of the airplane. m e effect of such things as soft runways, slo ed runways, winds alolt or airplane configu- ration chan as must be evaluated by the plot. Howewr, the performance data on the charts can %eduplicsted, by following the dated procedures, in a property maintained, standard MZOJ. Examples are giwn to show how each chart is used. The only charts with no example are those where such an example of use wouM be repetiiiw. To obtain effect of altitude and OATon aircraft performance: 1. Set altimeter to 29.92 in.Hg. and read "Pressure Altitude". 2. Using the OATgrid forthe applicable chart, read corresponding effect of OATon performance. - " # - - - - - CAUTION -- - - - . . # - Be s u n to mtum to local alimeter setting i n calculating aircraft elevation above sea kvel. OPERAnONAL PROCEDURES FOR MAXIMUM FUE EFFICIENCY For maximuim fuel efficient in the M20J, m er mbdure leaning during cruise flighl must be accomnlished. The IO-&A~BB lor P ~ & ~ - A ~ B B D ~ enolne in the M2RI has been designed io attain maximum fuel eficknc , at desired ciuise"power, at 14OC rich of peak EGT. EGT is usual1 a more accurate inchation of engine operation and fuel bum than indicaled fuel b w . herefore it is recommended that the mixture be set using EGT as the primary reference instead of setting to a particular fuel flow. The foliowin procedure is recommended for setting cruise power and leaning to best economy at $596 power or less: 1. Alter leveling off, set the manifold pressure and RFM for the desired cruise power in accordance wiih the Cruise Power Schedule as shown In this SECTION. At this point, the mixture contml is at full rich from the climb. 2. Next, slowly move the mixture control toward lean while observing the EGT in- dicator. If leaning the mixlure causes the original manifold pressure setting to change, u,se the throttle to maintain that desired cruise manifold pressure and con- tinue leantng until best economy setting is obtained. 1 PERFORMANCE CONSIDERATIONS 1 RANGE ASSUMPTIONS Range data climb allowance is based on climbing at maximum continuous power to c ~ i s e altitude. Range reserves of 45 minutes at cruise power have been allowed on Range Data. Other conditions used in the Ranges shown are lisled on each chart. ISSUED 1 - 96 5 - 3 SECTION V PERFORMANCE MOONEY M20J USE OF COWL FLAPS M e n in level cruise fliiht w l h outside air temperatures well above standard or when cruising at very h$h alud