Mooney M20J Pilot Operating Handbook

AND FAA APPROVED AIRPLANE FLIGHT MANUAL MOONEY REGULATIONS, AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT MANUAL. THIS DOCUMENT MUST BE CARRIED IN THE AIRCRAFT AT ALL TIMES. MOONEY AIRCRAFT CORPORATION P.8. BOX 72, KERRVILLE, TEXAS 78029-0072 SERIAL NUMBER: REGISTRATION NUMBER: Don P. Watson, Manager Department of Transportation Southwest Region Fort Worth. Texas FAA APPROVED in Normal Category based on CAR PART 3; applicable to Model M20J SIN listed above only. REV. B 6-12-87 ISSUED 6-2-86 MANUAL NUMBER 1233

YOUR DECISION TO SELECT A MOONEY HAS PLACED YOU IN AN ELITE AND DISTINCTIVE CLASS OF AIRCRAFT OWNERS. WE HOPE THAT YOU FIND YOUR MOONEY A UNIQUE FLYING EXPERIENCE, WHETHER FOR BUSINESS OR PLEASURE. TI-IE MOST PROFITABLE EVER. This manual is provided as an operating guide for the Mooney Model M20J. It is important that you--regardless of your previous experience-- carefully read the handbook from cover to cover and review it frequently. All information and illustrations in the manual are based on the latest product information available at the time of publication approval and all sections in- cluding attached si~pplements are mandatory for proper operation of the aircraft. The right is reserved to make changes at any time without notice. Every effort has been made to present the material in a clear and convenient manner to enable you to use the manual as a reference. Your cooperation in reporting presentation and content recommendations is solicited. REVISING THE MANUAL The "i" pages of this manual contain a "List of Effective Pages" containing a complete current listing of all pages i.e., Original or Revised. Also, in the lower right corner of the outlined poflion, is a box which denotes the manual number and issue or revision of the manual. It will be advanced one letter, al- phabetically, per revision. With each revision to the manual a new List of Ef- fective Pages showing all applicable revisions with dates of approval and a "Log of Revisions" page(@ ,with only The latest revision shown, will be provided to replace the previous ones. This handbook will be kept current by Mooney Aircraft Corporation when the yellow information card in front of this handbook has been completed and mailed to Mooney Aircraft Corporation, P.O. Box 72, Kerrville, TX 78029-0072.

MODEL M20J ORIGINAL . . . . . . . . . . . . . . . . . . 6-2-86 REV. A . . . . . . . . . . . . . . . . 8-15-86 REV. B . . . . . . . . . . . . . . . . . . 6-12-87 Always destroy superseded pages when inserting revised pages. TITLE PAGE . . . . . . . . . . . . . . . . . "A" page . . . . . . . . . . . . . . . . . . I . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ii iii . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . iv . . . . . . . . . . . . . . . . . . . . v 1-lthrul-14 . . . . . . . . . . . . . . . . 2-1 thru 2-20 . . . . . . . . . . . . . . . . 3-1 thru 3-16 . . . . . . . . . . . . . . . . 4-1 thru 4-18 . . . . . . . . . . . . . . . . 5-1 thru 5-42 . . . . . . . . . . . . . . . . 6-1 thru 6-28 . . . . . . . . . . . . . . . . 7-1 thru 7-36 . . . . . . . . . . . . . . . . 8-1 thru 8-12 . . . . . . . . . . . . . . . . 9-1 thru 9-4 . . . . . . . . . . . . . . . . . 10-1 thru 10-14 . . . . . . . . . . . . . . . . . B Original . . B . . I 3 . B . B . B . B . B . B . B . B . B . B . B . B . . B POHIAFM NUMBER 1233 This POHIAFM effective beginning with SIN 24-3000 REV. B 6-12-87 ISSUED 6-2-86

POH/AFM NUMBER 1233 [REV. B] I REV. B 6-12-87 ISSUED 6-2-86

. . . . . . . . . . . . . . . . Vl AIRPLANE & SYSTEM DESCRIPTIONS . . . . . . . . . . VII HANDLING, SERVICE & MAINTENANCE . . . . . . . . . . Vlll SUPPLEMENTAL DATA . . . . . . . . . . . . . . . . IX SAFETY & QPERATIONAL TIPS . . . . . . . . . . . . . X REV. B 6-12-87 ISSUED 5-2-86

TITLE . . . . . . . . . . . . . . . . . . . . . PAGE THREE VlEW . . . . . . . . . . . . . . . . . . . 1-2 INTRODUCTION . . . . . . . . . . . . . . . . . 1-3 DESCRIPTIVE DATA . . . . . . . . . . . . . . . . . 1-3 ENGINE . . . . . . . . . . . . . . . . . . 1-3 PROPELLER . . . . . . . . . . . . . . . . . 1-4 FUEL . . . . . . . . . . . . . . . . . . . . 1-4 OIL . . . . . . . . . . . . . . . . . . . . 1-4 LANDING GEAR . . . . . . . . . . . . . . . 1-4 MAXIMUM CERTIFICATED WEIGHTS . . . . . . . 1-5 STANDARD AIRPLANE WEIGHTS . . . . . . . . . 1-5 CABIN & ENTRY DIMENSIONS . . . . . . . . . . 1-5 BAGGAGE SPACE AND ENTRY DIMENSIONS . . . 1-5 SPECIFIC LOADINGS . . . . . . . . . . . . . 1-6 IDENTIFICATION PLATE . . . . . . . . . . . . . 1-6 SYMBOLS, ABBREVIATIONS & TERMINOLOGY . . . . . . . .1-6 GENERAL AIRSPEED TERMINOLOGY & SYMBOLS . . 1-6 ENGINE POWER TERMINOLOGY . . . . . . . 1-7 ENGINE CONTROLS & INSTRUMENTS TERMINOLOGY . . 1-7 AIRPLANE PERFORMANCE & FLIGHT PLANNING TERMINOLOGY . . . . . . . . . . . . . . . 1-8 METEOROLOGICAL TERMINOLQGY . . . . . . . . 1-8 WEIGHT & BALANCE TERMINOLOGY . . . . . . . . 1-9 MEASUREMENT CONVERSION TABLES . . . . . . . . . 1-1 1

includes both Manufacturers and FAA APPROVED material required to be fur- nished to the pilot by the applicable Federal Aviation Regulation's. Section IX contains supplemental data supplied by Mooney Aircraft Corporation. Section I contains information of general interest lo the pilot. It also contains definitions of the terminology used in this Pilot's Operating Handbook. This handbook is not designed as a substitute for adequate and competent flight instruction, knowledge of current airworthiness directives, applicable federal air regulations or advisory circulars. It is not intended to be a guide for basic flight instruction or a training manual and should not be used for operational purposes unless kept in a current status. All limitations, procedures, safety practices, servicing and maintenance re- quirements published in this POHIAFM are considered mandatory for the Con- tinued Airworthiness of this airplane in a condition equal to that of its original manufacture. DESCRIPTIVE DATA ENGINE Number of engines . . . Engine Manufacturer . . . Model . . . . . . . Recommended TBO . . . Type . . . . . . . . . . . . . . . . . . Number of cyiinders . . . . . . . . Displacement . . . . . Bore . . . . . . . Stroke . . . . . . . Compression ratio . . , Fuel System Type . . . . . . Make . . . . . . Fuel . . . . . . . . . . . . . . Accessories Magnetos . . . . . Spark Plugs . . . . . . . . . Alternator . . . . . . . . . . . Starter Ratings: Maximum Continuous Sea Level BHP-RPM . . , REV. B 6-12-87 ISSUED 6-2-86 . . . . . . . . I . . . AVCB Lycoming 10-360-A3B6D . . . . . . . . .1800Hours . . Reciprocating, aircooled, fuel injected. . . . . . 4, Horizontally . . . . . opposed . . . . . . . . 361 Cu. In. (5915.7 cc) 5.125 In. (13.02 cm) . . . 4.375 In. (1 1.1 1 cm) . . . . . 8.7:l .F~~ellnjectionFlow . . . Bendix, RSA-5-AD1 . . . Aviation Gasoline100 or lOOLL . . . . min, grade . . .BendixD4LN2021 or D4LN3021 . . . . . . . 18MMX.750-20 . . Thd. Connection . . Prestolite 28 Volts, 70A . . . Prestolite 24 Volts

. . . . . . . . . . . Number of Blades 2 Diameter . . . . . . . . Max.74.0 in. (1 87.9 cm)" Min. . . . . . . 73.0 in. (185.4 cm)* Type . . . . . . . Constant Speed Governing . . . Hydraulically controlled by engine oil Blade Angles @ 30 in. Sta.: Low . . . .13.9 degrees +I- .2 degrees* High . . . . .33.0 degrees + 1- .5 degrees* *OPTION: Hartzell , . , . HC-C2YK-lBF/F7666A-3Q . . . 73.0" (1 85.42 cm) (No cutoff allowed) Blade Angles:@30 in. sta. L0~:14.1 degrees +I- .1 degree High: 29.3 degrees to 31.3 degrees Spinner:Hartzell No. A2295 Minimum Fuel Grade (Color) . , . , 100/130 (Green) . . . . . . . . . . . 100 LL (Blue) . . . . . . . . . Total Capacity 66.5 U.S. Gal. . . . . . . . . . . . . . (251.8 Liters) . . . . . . (55.4Imp.Gal.) . . . . . . . . . . . Usable 64.0 U.S. Gal. . , , . , , , . . , , , , (242.4 Liters) . . . . . . . . (53.3Imp.Gal.) Total Oil Capacity , . , . , . . 8 Qts. (7.57 Liters) . . . . . . . Oil Capacity Minimum for Flight 5 Qts. . . . . . . .(4.73 Liters) . . . . . . . . . . . . Oil Filter Full Flow Oil grades, specifications and changing recommendations are contained in Section VIII. LANDING GEAR TYPE: Electrically operated, fully retractable tricycle gear with rubber shock discs. The main wheels have hydraulically operated disc brakes. The nose wheel is fully steerable 14 degrees left or right of center. REV. B 6-12-87 1-4 ISSUED 6-2-86

. . . . . . . . Wheel Thread 108 314 in. (276.2 cm) Tire Size: . . . . . . . . . . Nose .5.00 x 5 (6 ply) Main . . . .6.00 x 6 (6 ply) Tire Pressure: Nose . . . . . . . . . . . . 49 PSI Main . . . . . . 30 PSI Min. Turning Radius . . . . . . . . (No brakes applied) 41 ft. (12.5 m) MMIMUM CERTIFICATED WEIGHTS Maximum Loading (unless limited by C.G. envelope) Gross Weight . . . 2740 Lbs. (1243 Kg) Baggage Area . . . 120 Lbs. (54.4 Kg) Hat Rack . . . . . . . . . 10 Lbs. (4.54 Kg) Cargo (Rear Seals Folded Down) . . . . 340 Lbs. (1 54.2 Kg) STANDARD AIRPMNE WEIGHTS . . . . . . . . Basic Empty Weight See Page 1-1 1 . . . . . . . . Useful Load Varies with installed . . , , . . equipment. See Section \/I for specific . . . airplane weight (pg. 6-5). CABIN AND ENTRY DlFWENSlONS Cabin Width (Maximum) . ,435 In. (110.5 cm) Cabin Length (Maximum) . 914 In. (290 cm) Cabin Height (Maximum) . . . 44.5 In. (1 13 cm) Entry Width (Minimum) . . . 29.0 In. (73.4 cm) Entry Height (Minimum) . . , . . 35.0 In. (88.9 cm) BAGGAGE SPACE AND ENTRY DlMENS16NS Compartment Width . Compartment Length Compartment Height . Compartment Volume . . . . . . Cargo Area (with rear seat folded down) . . . . . . . Entry Height (Minimum) . . . Entry Width Ground to Bottom of Sill . 24 In. (60.9 cm) . 35 In. (88.9 cm) . 35 In. (88.9 cm) . . . . 17.0Cu. Ft. (476 . cubic meters) . . . 33.0 Cu. Ft. (924 . cubicmeters) . . 20.5 In. (52.1 cm) . 17.0 In. (43.2 cm) . .46.0 In. (116.8 cm) REV. B 5-12-87 ISSUED 6-2-86

Weight . . . . . . 16.4 Lbs./Sq. Ft. . . . . . . (80.07 Kglsq. m) Power Loading @ Maximum Gross Weight . . . . . 13.7 Lbs.1H1 (6.21 KgIHP) . . . . . . . . . . . . . IDENTIFICATION PLATE All correspondence regarding your airplane should include the Serial Number as depicted on the identification plate. The identification plate is located on the left hand side, aft end of the tailcone, below the horizontal stabilizer lead- ing edge. The aircraft Serial Number and type certificate are shown. SYMBOLS, ABBREVIATIONS & TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY & SYMBOLS GS GROUND SPEED -. Speed of an airplane relative to the ground. KCAS KNOTS CALIBRATED AIRSPEED -The indicated speed of an aircraft, 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 aircraft as shown on its airspeed indicator. IAS values published in this handbook assume zero instrument error. KTAS KNOTS TRUE AIRSPEED - The airspeed of an airplane relative to undisturbed air which is KCAS corrected for altitude, temperature and compressibility. MANEUVERING SPEED -The maximum speed at which application of full available aerodynamic control will not overstress the airplane. MAXIMUM FLAP EXTENDED SPEED - The highest speed permissible with wing flaps in a prescribed extended posit' MAXIMUM LANDING GEAR EXTENDED SPEED - The maxi- mum speed at which an aircraft can be safely flown with the landing gear extended. REV. S 6-1 2-87 ISSUED 6-2-86

mum speed at which the landing gear can be safely extended or retracted. Vne NEVER EXCEED SPEED or MACH NUMBER - 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 caution. STALLING SPEED - The minimum steady flight speed at which the airplane is controllable. Vso 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 altitude in the shortest possible horizontal distance. VY BEST RATE-OF-CLIMB SPEED -The airspeed which delivers the greatest gain in altitude in the shortest possible time with gear and flaps up. ENGINE POWER TERMINOLOGY BHP BRAKE HORSEPOWER - The power developed by the engine. MCP MAXIMUM CONTINUOUS POWER - The maximum power for abnormal or emergency operations. MANIFOLD PRESSURE - Pressure measurecl in the engine's induction system and is expressed in inches of mercury (Hg). WPM REVOLUTIONS PER MINUTE - Engine speed. NRP NORMAL RATED POWER ENGlNE CONTROLS & INSTRUMENTS TERMINOLOGY Propeller Control used to select engine speed. Control Throttle Control used to select engine power, from the lowest Control through the highest power settings. REV. B 6-12-87 ISSUED 6-2-86

Control control to control size of fuel feed aperture, therefore the airifuel mixture. It is primary method to shut engine down. EGT A temperature measuring system that senses EXHAUST GAS TEMPERATURE (EGT) in the exhaust pipe. The EGT gauge is the primary indication for mixture leaning in cruise flight at 75% power or less. Tachometer Instrument that indicates engine rotational speed. Speed is shown as propeller revolutions per minute (RPM). Propeller Device that regulates RPM of enginelpropeller by Governor increasing or decreasing propeller pitch through a pitch change mechanism in propeller hub. AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demon- The ?lelocity of the crosswind component for which strated adequate control of the airplane during takeoff and Crosswind landing Velocity test was actually demonstrated during certification The value shown is not considered to ' limiting. g Acceleration due to gravity. Service The maximum altitude at which aircraft at gross weight Ceiling has the capability of climbing at the rate of 100 ftlmin. Unusable Fuel remaining after a runout test has been completed Fuel in accordance with governmental regulations. Usable Fuel available for airplane propulsion. Fuel METEOROLOGICAL TERMINOLOGY AGL Above ground level. Density Altitude as determined by pressure altitude and Al- titude existing ambient temperature. In standard atmosphere (ISA) density and presure altitude are equal. For a given pressure altitude, the higher the temperature, the higher the density altitude. REV. B 6-12-87 ISSUED 6-2-86

Pressure and only when, the barometric subscale has been set Altitude to 29.92 inches of mercury or 101 3.2 millibars. ISA OAT INTERNATIONAL STANDARD ATMOSPHERE assumes that (1) The air is a dry perfect gas; (2) The temperature at sea level is 15 degrees Celsius (59 degrees F); (3) The pressure at sea level is 29.92 inches Hg (1913.2 mb); (4) The temperature gradient from sea level to the altitude at which the temperature is -56.5 degrees C (-69.7 degrees F) is -0.00198 degrees C (-0.003564 degrees F) per foot. OUTSIDE AIR TEMPERATURE - The free air static tempera- ture, obtained either from inflight temperature indications or ground meteorological sources. It is expressed in degrees Celsius (previously Centigrade). Pressure The indicated pressure altitude corrected for position Altitude and instrument error. In this handbook, altimeter instrument errors are assumed to be zero. Station Actual atmospheric pressure at field elevation. Pressure Arm The horizontal distance from the reference datum to the center of gravity (C.G.) of an item. Basic The actual weight of the airplane and includes all Empty operating equipment including optional equipment) that Weight has a fixed location and is actually installed in the aircraft. It includes the weight of the unusable fuel and full oil. Center of The point at which an airplane would balance if Gravity suspended. Its distance (C.G.)from the reference datum is found by dividing the total moment by the total weight of the airplane. C.6. Arm The arm obtained by adding the airplane's individual moments and dividing the sum by the total weight. C.G. in Center of Gravity expressed in percent of mean percent aerodynamic chord. MAC C.G. The extreme center of gravity locations within which the Limits airplane must be operated at a given weight. REV. B 6-1 2-87 ISSUED 6-2-86 1-9

The maximum authorized weight of the aircraft and its contents as listed in the aircraft specifications. The product of the weight of an item multiplied by its arm. (Moment divided by a constant is used to simplify balance calculations by reducing the number of digits.) An imaginary vertical plane from which all horizontal distances are measured for balance purposes. A location along the airplane fuselage usually given in terms of distance from the reference datum. The weight of chocks, blocks, stands, etc. used when weighing an airplane, and is included in the scale readings. Tare is deducted from the scale reading to obtain the actual (net) airplane weight. The basic empty weight subtracted from the maximum weight of the aircaft. This load consists of the pilot, crew if applicable, fuel, passengers, and baggage. REV. B 6-12-87 ISSUED 6-2-86

LENGTH U. S. Customary Metric Equivalents Unit I inch 2.54 centimeters 1 foot 0.3048 meter 1 yard 0.91 44 meter 1 mile (statute, land) 1 mile (nautical, in- ternational) 1. 609 meters 1. 852 meters AREA U. S. Customary Unit Metric Equivalents 1 square inch 6.451 6 sq. centimeters I square foot 929.030 sq. centimeters 1 square yard 0.836 sq. meter REV. B 6-22-87 iSStlED 5.2-86

MOONEY MODEL M20J 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 Liquid Measure Metric Equivalents 1 fluid ounce 29.573 milliliters 1 pint 0.473 liter 1 quart 0.946 liter 1 gallon 3.785 liters U.S. Customary Dry Measure Metric Equivalents I pint 0.551 liter 1 quart 1,101 liters British Imperial U. S. Metric Equivalents Liquid and Dry Equivalents Measure 1 fluid ounce 0.961 28.412 milliliters U.S.fluid ounce, 1.734 cubic inches REV. B 6-12-87 ISSUED 6-2-86

MODEL M26J 1 pint 'r quart 1 gallon SECTION I GENERAL 1.032 568.26 milliliters U.S.dry pints, 1.201 liquid pts.,34.678 cubic inches 1.032 U.S. 1.136 liters dry quarts 1.201 U.S. liquid qts., 69.354 cubic inches 1.201 U.S. 4.546 liters 277.420 cubic inches WEIGHT II. S. Customary Unit (Avoirdupois) Metric Equivalents 1 grain 64.79894 milligrams I dram 4.772 grams 4 ounce 28.350 grams 4 pound 453.59237 grams REV. B 6-42-87 ISSUED 6-2-86

SECTION it LIMITATIONS TITLE . . . . . . . . . . . . . . . . . . . . PAGE INTRODUCT10N . . . . . . . . . . . . AIRSPEED LIMITATIONS AIRSPEED INDICATOR MARKINGS . . POWER PLANT LIMITATIONS . . . POWER PUNT INSTRUMENT MARKINGS WEIGHT LIMITS . . . . . . . CENTER OF GRAVITY (GEAR DQWII) . . . . . . . . . . NOISE LIMITS MANEUVER LIMITS . . . . . . . FLIGHT LOAD FACTOR LIMITS . . . KINDS OF OPERATION LIMITS . . . FUEL LIMITATIONS . . . . . . . OPERATING ALTITUDE LIMITATIONS . OTHER INSTRUMENTS 8( MARKINGS . BEC;ALS&PlACARDS . . . . . . . . . . . CABIN INTERIOR FUSELAGE INTERIQR . . . EXTERIOR . . . . . . . INFORMATIONAL . . . . . OPTIONAL . . . . . . . . FAA APPROVED RE\/ . 5 6-1 2-87 ISSUED 6-2-86 AIRPLANE FLIGI-19- MANUAL 2-1

and basic placards necessary for the safe operation of the airplane, its en- gine, standard systems and standard equipment. THE LIMITATIONS IN- CLUDED IN THIS SECTION WAVE BEEN APPROVED BY THE FEDERAL AVIATION ADMINISTRATION. When applicable, limitations as- sociated with optional systems or equipment such as autopilots are included in Section IX. -------- I NOTE I -------- The airspeeds listed in the Airspeed Limitations chart (Figure 2-1) and the Airspeed Indicator Markings chart (Figure 2-2) are based on Airspeed Calibration data shown in Section V with the normal static source. If the alternate static source is being used, ample margins should be observed to allow for the airspeed calibration variations between the normal and alternate static sources as shown in Section V. Your Mooney is certificated under FAA Type Certificate No. 2A3 as a Mooney M20J. AIRPLANE FLIGHT MANUAL 2-2 FAA APPROVED REV. B 6-12-87 ISSUED 6-2-86

1 .This dlbratlon assumes zero Instrument error. - - - - - - = = a = = = = = = = = = = = = = = = = = = = = = = = = = = = = = SPEED KCASMI AS REMARKS Never Exmd 7951198 sgeed Maxlrnum Struc- 1 7411 76 turat Cruising Speed Manewering Speed:lblKg i9411880 2250/1021 247011 120 274011 243 Maxmum Flap Ex- tended Speed 0-1 sdegrees 1 6 w l l dn +I 2611 32 -10911 15 Maxlmum Land- 1WY65 Iw GWT EX- tended Speed Max Speed for QR. OPS. GR.RePract. GR.Extend. Maximum Pilot 13011 32 Wlndow Open s m Do not exceed this speed. Do not exceed this speed except In smmth alr, and then with caution Do not make full or abrupt control m e ments a b e this speed. 50 not WC& t h ~ speeds wRh given flap settings. DO NOT exceed thk speed wlth LDG GR extended. DO NOT extend or rettact ux; GR above these speeds. Do not exceed this sped wlth pllot win- dow open. FiGURE 2-1 AIRSPEED LlMlTAflOPlS FAA APPROVED REV. 3 6-1 2-87 ISSUED 6-2-86 AIRPLANE FLIGHT MANUAL 2-3

Airspeed indicator markings, their color code and operational significance are shown in Figure 2-2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MARKING IAS VALUE SIGNIFICANCE OR RANGE (KI AS) White Arc 55-1 15 Lower limit is maximum Full Flap Operat- weight Vso at most FWD ing Range CG in landing configura- tion. Upper limit is maxi- mum speed permissible with full flaps extended. Green Arc- 63-1 76 Lower limit is max. weight (Normal Operat- Vs at most FWD CG with ing Range) flaps retracted. Upper limit is max, structural cruising speed. Yellow Arc 176-1 98 Operations must be con- (Caution Range) ducted with caution and only in smooth air. Radial Red Line 198 Maximum speed for all operations. FIGURE 2-2 AIRSPEED INDICATOR MARKINGS AIRPLANE FLIGHT MANUAL 2-4 FAA APPROVED REV. B 6-1 2-87 ISSUED 6-2-86

SECTION II LIMlTA.TI0NS Number of Engines . . . . . . . . . . . . . 1 Engine Manufacturer . . . . . . . Avco Lycoming Engine Model Number . . . . . IO-360-A3B6D Engine Operating Limits for Takeoff and Continuous Operations: Maximum Power . . . . 200 BWP . . . . . . . Maximum Engine Speed 2700 RPM TransientEngineRPMLimit . . . . 2970RPMfor . . . . . . . . . . . . 3 seconds or less Max. Cylinder Head Temperature . . . . 475 Degrees F . . . . . . . . . . . (246 Degrees C) Maximum Oil Temperature . . . 245 Degrees F (1 18 Degrees C) . . . . . . . . . . . . Oil Pressure Normal Operating . . . . . . . . . 30-80-PSI Minimum (IDLE ONI-Y) . . . . 25PSl Maximum (cold ail) . . . . . . . . 100 PSI Fuel Pressure Minimum . . . . . . . . . . . 14 PSI Maxirnum . . . . . . . . . . . . . 30 PSI Fuel Grade (Color) . . . . . . 10011 30 (Green) . . 100LL(Blue) Propeller Manufacturer . . . . . . . . . McCauley" Propeller Model No . 821934C214190DWB-16E or -16EP" Propeller Diameter: Min . . . . . . . . 73.0 In. (185.4 cm)" Max . . (No cutoff allowed)74.0 In. (1 87.9 cm)" Propelier Blade Angles @ 30 In. sfa.: Low . . . 13.9 Degrees -11- .2 Degrees" High . . . 33.3 Degrees +/- .5 Degrees* Propeller Operating Limits . . . . . . 2700 WPM * BPTIOI\1:Hartaell WC-C2YK-I BFIF7666A-3Q 73.0 In. (185.4 em) (No Cutoff Allowed) Low: 14.1 +/- .I Degree High:29.3 Degrees to 31.3 Degrees 100bl- fuel is calibrated a"l.82 l blgal, (.69 Kgll). 1001130 octane fuel is calibrated at 6.0 lb/ga1.(.72 Kgll) --=-""-- I NOTE I -------- No cutoff ailowed on propeller when de-ice boots are installed. FAA APPROVED REV. B 6-12-87 ISSUED 6-2-86 AIRPLANE FLIGHT MANUAL 2-5

INSTRUMENT YELLOW ARC- GREEN ARC- REDLINE (CAUTION NORMAL MAXIMUM RANGE) OPERATING LIMIT Tachometer 1500-1 950 1950-2700 2700 RPM Cylinder Head Temperature Oil 7.5' Min. 150-245'~ 245 O F Temperature Grnd.Run-up (65-1 1 8 ' ~ ) (1 1 8 ' ~ ) *** NO REDLINE Oil (IDLE ONLY) 60-90 PSI 100 PSI Pressure 25 - 60 * ** Fuel Pressure Radial Red Line 14-30 PSI 30 PSI Min. 14 PSI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . * Yellow arc (starting and warm-up range) . . . . . . 90-100 PSI ** Radial red line (minimum idling) . . . . . . . . 25 PSI *** Needle moves off White Dot. ----------- I NOTE I -- Refer to AVCO Lycoming Engine Maintenance and Operators Manual Section on Engine Specifications and Operating Limits for recommended cruise power and temperature limitations. AIRPLANE FLIGHT MANUAL 2-6 FAA APPROVED REV. €3 6-1 2-87 ISSUED 6-2-86

. . -2740 Ib. (I 243 Kg.) Maxlrnum Weight in Saggage Compartment , . . , 120 Ib. (54.4 Kg.) @Fus. Sta. 95.5 . . . . . . . . . . . . Maximum Weight in Hatrack . f 0 Ib. (4.54 Kg.) . . . . . . . . . . . . @Fus. Sta. 118.0 Maximum Welght In Cargo Area (Rear seats folded down) . . . . 340 lbs.(154.2Kg) . . . . . . . . . . . @ Fus. Sta, 70.7 CENTER OF GRAVlTV (GEAR DOWN) Most Forward-41.0 In. (Fus. Sta. In IN.)f 3.496 MAC . .2250 Ib. . . . . . . . . . . . . . .(102IlQ.) IntermedMe Fonrmrd-41.8 In. (Fuse. Sta. In In.) 1 4 . n MAC . . . . . . . . . . .2470 1b. . . . . . . . . . . . . . . (1120 Kg.) Fotward Gross-45.0 IN. (Fus. Sta. ln'l~.) 20.1% MAC . . . . . . . . . . . ,2740 Ib. . . . . . . . . . . . . (1243 Kg.) Aft GrossSO.1 IN. (Fus. Sta. In IN.) 38.7% MAC . . . . . . . . . . . . . . ,2740 Ib. . . . . . . . . . . . . . MAC (at Wlng Sta. 93.83) . . . . . . . . . Datum (station zero) Is 5 5n.(12.5 cm) aft of the center line of the nose gar at- Its, and 33 ln.{84 cm) forward of the wlng leading d g e at whg sta- E25Li cm). NOISE LIMITS The certikatd nolse lwei for the M2OJ at 2740 Ibs. (1243 Kg.) maximum welght b 74.0 dB (A). No deterrnlnatton has been made by the Faderal Avla- tlon Admlnlstratton that the nolse levels of this airplane are or should be ac- ceptable or unacceptable for operation at, Into, ar out of, any airport. MANEUVER LIMITS Thb alplane must be operated es a Normal Category alrphne. Aerotettc maneuversI including splns, are prohbited. Extreme sustained sideslips may result In fuel ventlng thereby musing fuel fumes In the csbln. FAA APPROVED REV. B 6-1 2-87 ISSUED 6-2-86 Al RPLANE FLIGHT MANUAL 2-7

when the selected fueI tank contains less than 8 gallons (48.0 Ik., 30.3 IRers, 8.6 IMP. Gal.) of fuel have not been demonstrated and may cause loss of pow& --- I NOTE I --- Up to 290 foot altitude loss may occur durfng stalls at maxlmum wetght. Slow throttle movement required at airspeed above 165 KIAS. Above 165 KIAS, rapid throffl~ movement may result momentary propeller RPM over- speed. FLIGHT LOAD FACTOR LIMITS Maximum Positive Load Factor . . . . . . . . . . . . . Flaps Up +3.8 g. Flaps Down (33 Degrees) . . . . . . . . + 2.0 g. Maxlmum Negative Load Factor . . . . . . . . . . . . . Flap Up -1.5 g. ' Flaps Down . . . . . . . . . . . . 0.0 g. KIMDS OF OPERATION LIMITS 7711s C a Normal Category airplane approved for VFRllFR day or night opera- tlons when quipped In accordance with FAR 91. I 00 NOT OPERATE IN KNOWN ICING CONDITIONS. TAKEOFFS WITH COWL FLAPS INOPERATIVE ARE PROHIBITED Autopilot Llmitatlons - See Section IX. FUEL LlMtTATlONS A reduced fuel quantity Indleator is I llrd in each tank. The bottom tlp of these lndieat ow the 25 U.S. gallon -4 (94.7 [Hers) (20.8 IMP. Gal.) usable fue level in each tank. AIRPLANE FLIGHT MANUAL 2-8 FAA APPROVED REV. B 6-1 2-87 ISSUED 6-2-86

-----"-- An optional visual fuel qu~nfity gauge may be instalied on top sf each tank and is lo be used 8s a refeket~~e for refueling tanks only. Standard Tanks (2) 33.25 U.S. Gal. each . . . . (126 Liters)(27.7 Imp. Gal.) Total Fuel: 66.5 U.S. Gal. . . . . . . (25f .8 Liters)(55.4 Imp. Gal.) Usable Fuel: 64.0 U.S. Gal. . . . . . . (247.4 Liters)(53.3 Imp. Gal.) Unirsable Fuel: 2.5 U.S. Gal, . . . . . . (9.5 Lilers)(2.1 Imp. Gal.) Fuel Grade (and Color): 10011 30 rninirnum grade aviation Fuel (green). 100LL (low lead) aviation fuel (blue) with a lead content limited to 2 cc per gallon is aiso approved. T s reduce the possibility sf ice formation within the aircreR or engine fuei system It is permissable to add !SO-PROPVL 2lcohsl to the fuel supply in quantities NOT TO EXCEED 1% 01 the total %%lei volume per tank. 00 NOT add other additives to the fue8 system due Ba potential deteriorating effects wil%liri the fuel system. OPERATING ALTi'TUDE klMITWTIQN8 ti' this airplane is not equipped with an approved axygen system and flight operations above 12,500 feet are desired this airplane !nust be, (1) equipped with supplemental oxygen in accordance with FAR 23 1441, (2) operated in accordance with FAR 9 1 or FAR 135 OTHER INSTRUMENTS AND MARKINGS The following standard eq~~ipmenn is norrnaliy vacuum operated. 4 . Artificial horizon. 2. Directional Gyro. FAA APPROVED REV. B 6-1 2-87 ISSUED 6-2-86 AIRPLANE FI-IGH-I' MP,NiJAl-

CABIN INTERIOR The following placards must be installed inside the cabin at the locations specified. - - IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS ND AEROBATIC MANEUVERS, I INCLUDING SPINS. ARE APPROVED MAXIMUM SPEED WITH LANDING I/ * - - - - - - - 4 T UP RED HANDLE OPERATIONAL LIMITATIONS THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE 111 NUT FACE. // ' INSTRUMENTS WING FLAPS RAM AIR SEAT LATCH MIXTURE COWL FLAPS BELT/ HARNESS BOOST PUMP On Left Side Panel DO NOT OPEN ABOVE 132 KIAS Console Below Corrlrolrs AIRPLANE FLIGHT MANUAL F M APPROVED 6-12-87 REV. B 2-1 0 ISSUED 6-2-86

LIMITATIONS O n R i g h t Instrument Pa-nel Adjacent to Ta-chometer (McCauLey ~rapeller only) a-----ma -- PARK BRAKE Betweena Seaks m E-mergency Gear Extension &lease - - - - - - , - < ELT Placard - 'Top Xght Ia~trument Panel (hgend Varies With Eqdpazaerki ImtaBled) . - - - - < - - - --

-- Floor Board Fwd 8f AIRPLANE FLIGHT MANUAL F M APPROVED 6-12-87 REV.B 2-1 2 ISSUED 6-2-86

lap SdIeh --~---- On Retract Tube (asplayed tlaru window ina floorboard when I n . GR,/ 1s extended,) Above Each Control. on Lower Isastrument Panel -- - - - - - - - - - - - - BQ HUT EXCEED 40 LB§ (4 L KQ) IM THIS COMPWR'IUFNT FOR STOWAQe OF Lwnr a e r T w m r u s Crmr SEE AWCWBFT LOAIPWO SCHEOULB: DATA FQR BAGGAGE CObBPAFITMEM'i ALbBW&t3bP: I8 Above Baggage Compartment On &track Shell. ------- - -. -. - . -- d ---- BO PBBY EXCEED $20 lB5 WARM,MQ: '54.4 K d iX TMS COWARWPdT SEE AETCRAF7 L O A M SCI(EWLE DATA P W tlAC-CdGE C W m W ALLQVALlbP: On Top Baggage Door Jamb. DO NOT EXCEED "870 bB8 OADING scneouee o c a ~ ~ FAA A$I"RFiBVED REV. B 6-1 2-07 ISSIJEB 6-2-86

& Below Cowl Flap (Under Mixture C o n t r o l ) On Lower Console Below -LOADID - A L T + Under c i r c u i t Above Flap Switch B r e a k e r P a n e l AIRPLANE FLIGHT MANUAL FAA APPROVED 6-12-87 REV. B 2-1 4 ISSUED 6-2-86

locations specified. ,-- - ----- L M O I W I 8BL OIL 1NSTALLED 1N THIS ENGINE BS: I I NEXT OBL CHANGE !S DUE A 4 (USE CREASE PENCIL] -- On O i l Access/Fill.eu. Iloor P

locations specified. TIRE PRESSURE 30 PSI (2.1 1 Kg/cr 1 On' Main Gear Doors f l R E PRESSURE 49 PSI (3.44Kg/cm2) On Nose Gear Door FUEL-100 (GREEN) FUEL-1 00 (GREEN) OR 100 U ( BLUE ) MIN, OCT- 606 LL (BLUE) MlN OCT 32 U.S. GM 12 6.2 LITERS USEABLE STANDARD OPTIONAL FUEL-"lo (GREEN) OR 100 LL (BLUE) MIN OCT TOWING LIMITS I DO NOT PUSH WARNING W MOT EXCttD TOWING LlMllS On Leading Edge of Mor izontal Stabilizes and Trailing Edge of Both Sides of Rudder NO STEP On Inboard End Of Flaps, Wing Leading Edges and Wing Ahead Of Flaps AIRPLANE FLIGHT MANUAL 2-1 6 6-12-67 REV. B ISSUED 6-2-86

LIMITATIONS POTBT D R A g N Under Left Hand Wing Leadfng Q A B C O L A T O R D R A I N Under Fuselage A f t o f Nose Wheel Well FAA APPROVED REV B 6- 1 2- 137 P,iRPlP,NE FLICI iT MAPJLIRI. ISSUED 6 2-86 3-1 ?

informational purposes or aesthetics. IMPORTANT INSTRUCTIONS ALWAYS ADD 1 1 T E R . "EYER ADO ACID. I ( E Y E ~ r t L L OVER BAFFLE NOR UORE THIN t!1-OYER THE TOPS OF SEPARATORS. F U L L l CHARGED SPECIFIC G R A V l l V - 1 . 2 7 5 R E C t l l R G l REOUfRED WHEN SP. OR REACHES 1.225 CMARGIHG RATES: START - I AUPERES FINISH - I AMPERES L 1 A I I U Y Y T T U I E R A T U R E OW CHARGE - 1 2 0 ' 6 169. C I KEEP CHARGED - PREVENT FREEZING CARE SHOULD BE TALE" MOT TO SPILL 8 A T T E R V ACID WHEW SERVICING OR REUOVIMG B A l T E R V Above Battery On Aft Side Baggage Compartment Bulkhead On Headlines By Interior Light. Switches ON Headliner near Overhead Shutoff Valve AIRPLANE FLIGHT MANUAL 2-1 8 FAA APPROVED 6-12-87 REV. B ISSUED 6-2-86

FAAAPPROVED F3EV.B 6-,12-87 ISSUED 6-2-86 AIRPLANE FilGHT MANUAL 2-19

LIMITATIONS OPTIONAL: See Section IX Supplements For Optional Placards Required. MOONEY MODEL M20J AIRPLANE FLIGHT MANUAL 2-20 FAA APPROVED REV. B 6-1 2-87 ISSUED 6-2-86

TITLE . . . . . . . . . . . INI~RODUCTION . . . . . . . . . . . . . . . . . AIRSPEEDS FOR EMERGENCY OPERATIONS ANNUNCIATOR PANEL WARNING LlGtITS . . . . ENGINE . . . . . . . . . . . . . . . . PO\NER LOSS-DLJRING 'TAKEOFF R0L.i . . . POWER LOSS-AFTER LIFTOFF R: DURING CLIMB POWER LOSS - IN $LIGHT . . . . . . . ENGINE RESTART PReSCEDhJRE-IN FLIGHT . . ENGINE F!RE - IN FLIGHT . . . . . . . . ENGINE ROUGHNESS . . . . . . . . COWI- FL4PS FAILIJRE-FUI-.I. CLOSED POSITION I-!IGH CYLINDER I-iEAD 'TEMPERTIIRE . . . E-i1Gi-i 01 L TEMPERATUI'IE . . . . . . . . LOVV OIL PRESSURE . . . . . . . . . Eb3G1NE DRIVEN FUEL PUMP IzAILURE . . . FIRES . . . . . . . . . . . . . . . . . ENGINE FiWE - GWOUhlD . . . . . . . . ENGINE FIRE .. IN FLIGI-IT . . . . . . . . ELECTRICAL FIRE - iN FI-IGHT . . . EMERGENCY DESCEN'T FSROCEDtJRE . . . . . GLIDE . . . . . . . . . . . . . . . . . LANDING EMERGENCY . . . . . . . . . . . POWER OFF - GEAR RETRACTED OR EXTENDED 130WER ON -GEAR RETWAC'TEB . . . . . SYSTEM EMERGENCIES . . . . . . . . . . . . . . . . . . . . . . . . PROPELLER . . . . . . . . . . . . . . . FUEL ELECTRICAI .. . . . . . . . . . . . u~~~~~~ GEAR . . . . . . . . . . . . . . . . . . . . . . . . OXYGEN ALTERNATE STATIC SOURCE . . . . . . . UNLATCHED DOOR IN FLIGHT . . . . . . . . . ICE PROTECTION . . . . . . . . . . . . . EMERGENCY EXIT OF AIRCRAFT . . . . . . . . SPIINS . . . . . . . . . . . . . . . . . OTHER EMERGENCIES . . . . . . . . . . PAGE REV . B 6-1 2-87 ISSUED 6-2-86

flight conditions. The information is presented to enable you to form, in ad- vance, 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 have a procedure for all types of emergencies that may occur, it is the pilot's responsibility to use sound judgement based on ex- perience and knowledge of the aircraft to determine the best course of ac- tion. Therefore, it is considered mandatory that the pilot read the entire manual, especially this section before flight. When applicable, emergency procedures associated with optional equipment such as autopilots are included in Section IX. 1 NOTE I ""-------- All airspeeds in this section are indicated (IAS) and assume zero instrument error unless stated otherwise. REV. B 6-12-87 ISSUED 6-2-86

Engine Failure after Takeoff . . . . . . . . . . Wing Flaps UP .85 KIAS . . . . . . . . . Wing Flaps DOWN .75 KIAS Maximum Glide Speed . . . . . . . . . . 2740 lb/1243 kg .91 KIAS . . . . . . . . . . 2500 lb/1134 kg .88 KlAS . . . . . . . . . . 2300 lbl1043 kg .85 KlAS Maneuvering Speed . . . . . . . . . . 2740 lb/1243 kg 1 16 MIAS . . . . . . . . . . 2470 lb/1120 kg 110 KlAS . . . . . . . . . . 2250 lb/1021 kg 105 KiAS . . . . . . . . . . 1941 Ib/880 kg .97 Kl AS Precautionary banding with Engine Power, Flaps DOWN . . . . 75 KIAS Emergency Descent (Gear UP) . . . . . . . . . . . Smooth Air 4 98 KlAS Tilrbulenl Air . . . . . . . 2740 lbll243 kg . 1 4 6 KlAS 2470 lb114 20 kg . , . . , . , . . 1 10 KlAS . . . . . . . . . 2250 lb/1021 kg 105 KlAS Emergency Descent (Gear DOWN) Smootti Air . . . . . . . . I65 KIA§ Turbulent Air . . . . . . . . . 2'740 lbl1243 kg 1 16 MIA5 2470 1b11120 kg . . , . . , . . 1 10 KlAS . . . . . . . . . 2250 lbl4024 kg 105 KlAS REV. B 6-12-87 ISSUED 6-2-86

WARNING LIGHT FAULT & REMEDY Gear Unsafe Left or Right Fuel Low LDG. GR. in transit or not fully ex- tended or retracted. Refer to "Failure of Landing Gear to Extend Electrical- lyl',pg. 3-12 or "failure of Landing Gear to RetractU,page 3-13. 2 112 to 3 gallons of usable fuel remain in the respective tanks. Switch to fuller tank. VAC (Flashing) Suction is below 4.25 In. Hg VAC (Steady) Suction is above 5.5 In. Hg. -------- I MOTE I Attitude and directional gyros are unreliable when VAC light is illuminated (steady or flashing). Vacuum system should be checked andlor adjusted as soon as practicable. Volts (Flashing) Volts (Steady) Ram Air Start Power ON Low voltage. Refer toUAlternator Low Voltage" on page 3-1 2. Overvoltage or tripped Voltage Relay. Refer to "Alternator Failure" on page 3-1 1. Ram Air light is ON when landing gear is extended. Close Ram Air before landing. Switch or relay has malfunctioned and starter is energized. Flight should be terminated as soon as practicable. Engine damage may result. %8 REV. B 6-12-87 ISSUED 6-2-86

Throttle . . . . . . . . . . . CLOSED Brakes . . . . . . . . . . .APPLY (Maximum) Fuel Selector . . . . . . . . . . . . . . . .OFF MagnetolStatTer Switch . . . . . . . .OFF Master . . . . . . . . . . . . . . . .OFF POWER LOSS - AFTER LIFTOFF AND DURiRsG CLIMB Airspeed . . . . . . . . '$5 MIAS Fuel selector . . . . OTHER TANK (fullest lank) . . . . . . . . . . . . Throttie .Full FORWARD Propeller . . . . . . . . . . Full Forward (High RPM) . . . . . . . . . . . . . . Mixture Full RICH Magneto switch . . . . . . . . . Verify on BOTH Fuel Boost Pump . . . . . . . . . . . . . . . ON If engine does not restat?, proceed to POWER OFF L~ANDING, page 3-'i0. POWER LOSS - IN FLIGHT lmrnediatsly upon ncting any cor7djtion that could eventually lead to an en- gine fai!ure (loss of oil or fuel system presure, or rough engine operation) per- form the following checks if time and altitude permit. bow Fuel Quantity . . . . . . . Firel selector To f~niiest tank Low Fuel Pressure . . . . . . . . . Aux. 'rue! pump on-off . . . . . . . . . . if no improvement noted Mixture Control . . . . . . . . . . . . . . Full RICH Magneto/Sta@erSwit@h . . . . . . SwilchtohEFTandRIGI-IT sir?gle magneto operation; if no improvement, switch Po BOTH If no improvement is noted, proceed to LAND as soon as practicable. ENGINE RESTART PROCEDURES - IN FLIGHT Airspeed . . . . . . . . .a5 KIAS Fuel Selector . . . . . . . . . Verify on FULLEST TANK . . . . . . . . . . . . Throttle OPEN 114 Travel Propeller . . . . . . . . . . . . 2700 WPM . . . . . . . . . . . . . . Mifiur@ FULL RICH Fuel Pressure . . . . . . . .Verify in Green Arc If no fuel presskrre is noted: . . . . . . . . . Fuel Boost Pump . . . . . . . . . . . . ON REV. B 6-12-87 ISSUED 6-2-86

If engine does not restart after initial attempts: Mixture . . . . . . . . IDLE CUTOFF (Initially) then advance slowly toward RlCH until engine starts ARer engine restarts: Throttle . . . . . . . . . . . . Adjust as required Propeller . . . . . . . . . . Adjust as required Mixture . . .RELEAN as power is restored If engine does not restart establish best glide speed and proceed to POWER OFF LANDING, page 3-10. ENGlNE ROUGHNESS Engine Instruments . . . . . . . . . . . . . CHECK . . . . . . . . . . . . . Fuel Selector OTHER TANK Mixture . . . . . READJUST for smooth operation MagnetoIStarter . . . . . . . . . Select R then L then BOTH. If roughness disappears on single magneto, adjust power and continue. llllllllllllllllllli// IIIWARNINGIII llllllllll/llllillll/ The engine may quit completely when one magneto is switched off, if the other magnets is faulty. If this happens, close throttle to idle and mixture to idle cutoff before turning magnetos ON to prevent a severe backfire. When magnetos have been turned back on, proceed to POWER LOSS - IN FLIGHT on page 3-5. Severe roughness may be sufficient to cause propeller separation. Do not continue to operate a rough engine unless there is no other alternative. -. i nrottle . . . . . . . . . . REDUCE check if a lesser throttle setting causes roughness to decrease. If severe engine roughness cannot be eliminated LAND as soon as prac- ticable. COWL FLAP FAILURE IN FULL CLOSED POSITION Acceptable engine operating temperatures can always be maintained during flight with the cowl flaps failed in the full closed position using the following procedure: Power . . . . . AS REQUIRED Mixture . . . . . . . . . . . . RICH Airspeed . . . . . . . . . . . 120 KlAS Cylinder Head Oil Temperature . . . MONITOR . . . . . . in NORMAL OPERATING RANGE REV. B 6-12-87 ISSUED 6-2-86

Midure . . . . . . . . . .READJUST to proper EGTlfuel flow for power being used Cowl Flap . . . . . . . . . . . OPEN as required Airspeed . . . . . . . . . . . . INCREASE Power . . . . . . . . . . REDUCE if temperature cannot be maintained within limits HlGH OIL TEMPERATURE -*-."--*--- Prolonged high oil temperature indications will usually be accompanied by a drop in oil pressiare. If oil pressrare remains nsr~na!, then B high temperature indication may be caused by a dauity gauge or tharmscgsuple. Cowl Flaps . . . . . . . . . . . OPEN as required Airspeed . . . . . . . .INCREASE Power . . . . . . . . . . . . W EDUCE Prepare for possibie engine failure if temperature continues high. LOW 68L PRESSURE Oil temperature and pressure . . . . . . Monitor Pressure below 25 PSI . . . . . . . . . Expect engine failure, . . . . . . proceed to POWER OFF ianding ENGINE DRIVEN FUEL PUMP FA%&URE An engine driven fuel puinp failure is probable when the engine will only operate with the boost pump on. Operation of the engine with a failed engine driven fuel pump and the BOOST ON will require smooth uperatiat? of the en- gine controls and corresponding mixture change when the throttle is reposi- tioned or the engine speed is changed. When retarding throttle or reducing engine speed lean the mixture lo prevent the engine frorn quitting from an overrich condition. Enrich the mixture when opening the throttle or increas- ing engine speed to prevent engine stoppage frorn 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: Mixture . . . . . . . . IDLE CUTOFF Throttle . . . . . . . . . . . CRUISE Position Boost Pump . . . . . . . . . . . . . . . . ON Mixture . . . . . . . . . . . . . Increase until engine starts and adjust for srrtooth engine operation. LAND as soon as practicable. REV. I3 6-12-87 ISSUED 6-2-86 3-7

EMERGENCY PROCEDURES MOONEY M20J FIRES ENGINE FIRE-GROUND . . . . . . . . . . Mixture IDLE CUTOFF (Full Aft) . . . . . . . . . . . . . . Fuel Selector Valve .OFF . . . . . . . . . . . . MagnetoIStarter Switch .OFF . . . . . . . . . . . . . . . Master Switch .OFF Fire , , . , . . , . Extinguish with Fire Extinguisher ENGINE FIRE-IN FLIGHT . . . . . . . . . Fuel Selector Valve . . . . . . . . . . Throttle . . . . . . . . . . Mixture Control MagnetolStarter Switch . . . . . . . Cabin Ventilation & Heating Controls . , . . . . . . . . . . . Cowl Flaps . . . . . . . . . . . . . . . . . . . banding Gear . . . . . . . . Wing Flaps . . . . . . . . -------- I NOTE I . .OFF . . CLOSED (Full Aft) IDLE CUTOFF (Full Aft) . .OFF . , . . CLOSED , . (Controls Forward) . , . . CLOSED , , .DOWN or UP, . depending on terrain . , , . EXTEND . . as necessary If fire is not extinguished, attempt l o increase airflow over the engine by increasing glide speed and open cowl flaps. Proceed with a POWER OFF landing as described on page 3-18. Do not attempt an engine restart. ELECTRICAL FIRE- IN FLIGHT (Smoke in Cabin) . . . . . . . . . . . . . . Master Switch .OFF llllll/l/llllllllllli/ ///WARNING/// ////////I///////////// Stall warning is not available with master switch OFF. Gear warning is not available with master switch OFF. . . . . . . . . . . . . . . Cabin Ventilation OPEh* . . . . . . . . Heating Controls CLOSED (Control Forward) . . . . . . . . . . Circuit Breakers CHECK to identify faulty . . . . . . . . . . . . circuit if possible. LAND as soon as practicable. REV. B 6-12-87 ISSUED 6-2-86

faulty circuit as follows: Master switch . . . . . . . . . . . . . . . . ON Select ESSENTIAL switches ON one at a time, and permit a short time to elapse before activating an additional circuit. EMERGENCYDESCENTPWBCEBURE In the event an emergency descent from high altitude is required, rates of de- scent of at least 3,000 feet per minute can be obtained with idle power, flaps UP & cowl flaps CLOSED with the aircraft in two different configurations: Configuration No. 1 : . . Gear DOWN, . . 165 KIAS Configuration No. 2: . . . Gear UP. . . . 198 KIA§ For an emergency descent from altitude, Configuration No. I is recom- mended. The angle of descent is greater and ar 165 KlAS the ride will be smoother, resulting in less pilot workload. Therefore: The following procedure should be used for an emergency descent: Power . , . Airspeed . . . Landing Gear . . . Airspeed . . . Wing Flaps . , . Cowl Flaps . . . Power During Descent REV. 5 6-12-87 ISSUED 6-2-86 . . . . . . . . . . IDLE . . . . . 140 KlAS EXTEND . . . . . . . . . . . . . . . . Increase to I65 KlAS . . . after landing gear is extended. . . . . . . . . . . . . UP CLOSED . . . . . . . . . . . . , . . AS REQUIRED to Maintain Cylinder Fiead Temperature . . . . . . . . . 300' F (149 ' C) minimum

MODEL M20J 11 10 8 0 9 X 8 tr: $ 7 3 6 W t. w i5 2 5 s! W x 2 1 ' 0 2 1 6 8 10 12 14 16 18 20 22 GROUND DISTANCE - NAUTICAL MILES UNBlNG EMERGENCY POWER OFF-GEAR RETRACTED OR EXTENDED Emergency Locator Transmitter Seat Belts and Shoulder Harnesses Cabin Door . . . . . Fuel Selector . . . . . Mixture . . . . . MagnetolStarter . . . . Flaps . . . . . Gear . . . . . Approach Speed . . . . Master . . . . . . . . . .ARMED . . . SECURE . . . UNLATCHED . . . .OFF . . . . IDLE CUTOFF . . . .OFF . . . Full DOWN (33 Degrees) . DOWN or UP Depending on Terrain . . . . . .71 KIA? . . . OFF, prior to landing " 6-12-87 REV. B ISSUED 6-2-86

Emergency Locator Transmitter , , , , , . , , , . ARMED Seal Belts and Shoulder Harnesses . . . SECURE Cabin Door IINMfGHED When sure of making landing area: . . . . . . . . . . . . Fuel Selector OFF . . . . . . . . . . . Throttle CLOSED . . . . . . . . . . Mixture IDLE CUTOFF . . . . . . . . . . . WlagnetolStader OFF . . . . . . . . Flaps Full DOWN (33 Degrees) Master . , . . , . , . , . , . .OFF Approach Speed . , . , . . As Slow As Possible Wings Keep , , , . , , , . , . . LEVEL SYSEMS EMERGENCIES PROPELLER PROPELLER OVERSPEED Throttle . . , . . , , , . , . . , . RETARD Oil Pressure . . . . . . . . . . . . . . . CHECK . . . . . . Propeller DECREASE, set if any control avaliable . . . . . . . . . . . . . . Airspeed REDUCE . . . . . . . Throttle . . . . . AS REQUIRED . . . . . . ro maintain RPM below 2700 RPM . . . . . . . . . . . . . . Chsck Mixture ENRICH . . . . . . . . . . . . . Fuel Selector Fullest TANK If condition persists, use Boost Pump if necessary and LANDING should be made as soon as practicabie. ALTERNATOR FAILURE (Voltage warning light illuminated steady) . . . . . . . . . . . . . . . Avionics Master .OFF . . . . . . . . . . . . . Master OFF, then ON if Warning bight is still illuminated, the following steps are required: . . . . . . . Alternator Field Circuit Breaker PULL . . . . . . Non-essentialElectricalEquiprnent .OFF LAND as soon as practicable.

Alternator Field Switch . . . . . . . . . . . OFF then ON If warning light still flashing, the following are required: AlternatorFieidCircuitBreaker . . . . . . . PULL Non-essentialelectricalEquipment . . .OFF LAND as soon as practicable. -----*-- I NOTE I A tripped main alternator circuit breaker can only be caused by a shorted alternator circuit and cannot be corrected by resetting the breaker. This should be verified by attempting do reset the breaker not more than one time. If this fails, turn the effected alternator field switch OFF. Turn off all non-essential eleelrieal equipment and terminate the flight as soon as practical. Repair the malfunctioning alternator prior to the next flight. LANDING GEAR FAILURE OF LANDING GEAR TO EXTEND ELECTRICALLY Airspeed . . . . . 140 KlAS or less . . . . . . . . Landing Gear Actuator Circuit Breaker PULL Gear Switch . . . . . . . . . . . . . . . DOWN Manual Gear Extension Mechanism . , . . LATCI-I FORWARD, LEVER BACK to engage manual extension mechanism -------- I NOTE I Slowly pull "T" handle 1 to 2 inches (2.5 to 5.1 cm) l o rotate clutch mechanism and allow it to engage elrive shaft. T-Handle . . . . . . . . . . . . . . . PULL (12 to 20 times and RETURN until gear is down and iocked, GEAR DOWN light illuminated; STOP when resistance is felt. . . -- SYSTEM MAY BECOME DAMAGED.-- . . . . . . . Visual Gear Down Indicator CHECK ALIGNMENT by viewing from directly above the indicator. a- N N N N N N N " CAUTION " N N N N N N N Continuing to pull on T-Handle after GEAR DOWN light ON will bind actuator,@leclrical retraction MAY NOT be possible until binding is eliminated. REV. 5 6-12-87 3-1 2 ISSUED 6-2-86

" CAUTION " N N N N N N N Malfunction of landing gear requires maintenance inspection and repair prior to activating electrical system. Return lever to normal position and secure with latch. Reset Landing Gear Ac- tuator Circuit Breaker. //////////////////I// ///WARNING/// l//lllllll/////ll/Il/ Do not operate landing gear electrically with manual extension system engaged. FAILURE OF LANDING GEAR TO RETRACT ("GR SAFETY BY PASS", both gear annunciator lights illuminated and gear warning horn activated.) "GR SAFETY BY PASS SWITCH" . . . . . . . . . DEPRESS . . . . . . . . until gear fully retracted "GEAR UNSAFE" and "GEAR DOWN" Lights . . . . . . .QUT "GEAR RELAYS" Circuit Breaker . . . PULL (Warning horn off) . . . . . . . . . . . . . . Gear Extension . . . . . . . . . RESET "GEAR RELAYS" . . . . . . Circuit Breaker Gear Switch . . . . . . . . . . . . . . . DOWN Check "Airspeed Safely Switch" as soon as practicable. Df above procedures do not initiate retraction process, check emergency manual extension lever on floor for proper position. Refer to Section IX if aircraft is equipped with oxygen. AL.TERNATE STATIC SOURCE The alternate static air source should be used whenever it is suspected that the normal static air sources are blocked. Selecting the alternate static source changes the source of static air for the altimeter, airspeed indicator and rate-of-climb from the outside of the aircraft to the cabin interior. REV. B 6-12-87 ISSUED 6-2-86

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 in the lower left portion of the pilot's flight panel above the pilot's left knee. --*----- I NOTE I When using the alternate static source the pilots window and airvents MUST BE KEPT CLOSED Alternate Static Source . . . . . . . . . . . . PULL ON Airspeed and Altimeter Readings . . . CHECK Calibrations Tables,SECTION V UNbBTCHED DOOR IN FLIGHT If the cabin door is not properly closed it may come unlatched in flight. This may occur during or just after take-off The door will trail in a position ap- proximtely 3 inches (7.6 cm) open, but the flight characteristics of the airplane will not be affected. Return to the field in a normal manner. If prac- ticable, during the landing flare have a passenger hold the door to prevent it from swinging open, If it is deemed impractical to return and land, the door can be closed in flight, after reaching a safe altitude, by the following procedures: Airspeed . . . . . . . . . . . . . . .96 KlAS Pilot's Storm Window . . . . . . . . . . . . OPEN Aircraft , , . . , . . , . RIGHT SIDESLIP (Right bank . . . . . . . with left rudder) Boor . . . . . . . . PULL SHUT & LA'PCH ICE PROTECTION llllllllllllllllllli/ IIIWARNINGIII lllllllllllllllllllll DQ NOT OPERATE IN KNOWN ICING CONDITIONS. The Model M20J is NOT APPROVED for flight into known icing conditions &- and operation in that environment is prohibited. However, if those conditions are inadvertently encountered or if flight into heavy snow is unavoidable, the following procedures are recommended until further icing conditions can be avoided: Ram Air . . . . . . . . . . . . . . . .OFF REV. B 6-12-87 ISSUED 6-2-86

in heavy snow may result In partial or total loss of engine power. Make sure the Ram Air Is OFF when flying In these condlflonr. Also, do not turn the Ram Air ON again when re-entering cleat air until all Ice and snow has metted from the alrcra ft . Pitot Heat . . . . . . . . . . . . . . . . ON Propeller Delce . . . . . . ON (it installed) Alternate Static Source . . . . . . . . . . ON (If required) Cabin Heat . . . . . . . . . . . . . . . .OFF . . . until englne operation is normal. I --- AVOID FURTHER ICING CONDITIONS --- I EMERGENCY EXIT OF AIRCAFT CABIN DOOR PULL latch Ilandle AFT. OPEN dour and exR aircraft. BAGGAGECOMPARTMENTDOOH Fold rear seat hcks forward, CLIMB OVER. PULL off p!astlc cover. PULL white button. Uft red handle "UP. OPEN door and extt aircraft. To verb re-engagement of outside latch mechanism, open outsMe tmndte fully, dose inside red handle to engage pln Into cam sllde of latch mechankm, push h on whb button until it snaps In place. Replace cover. Operate oublde handle In normal manner. SPINS ////////l///ll/////l IllWARNi NGlll //I/ //111//1/1/I/III/ Up to 2000 bet ol altitude may be lost In a one turn spln and mvery; tlwefam, stalls at low altitude are extremely crMlcal. REV. B 6-12-87 ISSUED 6-2-

conducive to spin entry. bow speed flight near stall should be approachgd with caution and excessive flight control movements in this flight regime should be avoided. Shou1d an unintentional stall occur the aircraff should not be allowed to progress into a d6ep stall. Fast, but smooth stall recovery will minimuze the risk of progressing into a spin. If an ur~usual post %tail attitude develops and results in a spin, quick application of antispin procedures should shorten the recovery. INTENTIONAL SPINS ARE PROH1BITED. In the event of an inadvertent spin, the following recovery, procedure should be used: Rudder . . . . Apply FULL RUDDER opposite . . . . . . the direction of spin Control Wheel . . ' , , -, , FORWARD of neutral in a brisk motion Additional FORWARD elevator control may be required if the rotation does not stop. Ailerons . . . . . . .NEUTRAL Throttle , . . . . . . . . . . . RETARD to IDLE I--lold anti-spin controls until rotation stops. Flaps(lf extended) . . . . . . . . . . . . . RETRACT . . . . as soon as possible Rudder . . NEUTRALIZE when spin stops Control Wheel . . . . . . . . . . SMOOTI-ILY MOVE AFT . . . . . . . . . . to bring the nose up to . . . . . . . a level flight attitude. OTHER EMERGENCIES Refer to Section IX for Emergency Procedures of Optional Equipment. REV. B 6-12-87 ISSUED 6-2-86

TITLE . . . . . . . . . . . . . . . . . . . . . PAGE INTRODUCTION . . . . . . . . . . . . . . . . . 4.2 PREFLIGHT INSPECTION . . . . . . . . . . . . . . . 4-3 BEFORE STARTING CHECK . . . . . . . . . . . . . . 4-6 STARTING ENGINE . . . . . . . . . . . . . . . 4-7 FLOODED ENGINE STARTING . . . . . . . . . . . 4-8 WARM ENGINE STARTING . . . . . . . . . . . . . . 4-8 BEFORE TAXI . . . . . . . . . . . . . . . . . . . 4-8 TAXI . . . . . . . . . . . . . . . . . . . . . 4-9 BEFORE TAKEOFF . . . . . . . . . . . . . . . . . 4-9 I'AKEOFF PROCEDURES . . . . . . . . . . . . . . 4-11 TAKEOFF . . . . . . . . . . . . . 4-41 I . . . . . . . . . . . . . . . . . . . 4-42 CL.lM\ns (NORMAL) . . . . . . . . . . . . . . . 4-12 CLIMB (BEST RATE) . . . . . . . . . . . . . . 4-12 CLIMB (BEST AIVGI-E) . . . . . . . . . . . . 4-12 CRUISE . . . . . . . . . . . . . . . . . . . . . 4-13 DESCENT . . . . . . . . . . . . . . . . . . . 4-14 APPROACH FOR LANDING . . . . . . . . . . . . . . 4-15 GO AROUND (BALKED LANDING) . . . . . . . . . . 4-16 LANDING . . . . . . . . . . . . . . . . . . . 4-16 TAXI AFTER LANDING . . . . . . . . . . . . . . . 4-17 . . . . . . . . . . . . . . . . . . . SI-IUTDQWN 4-47' SECURING THE AIRCRAFT . . . . . . . . . . . 4-18 REV . B 6-12-87 ISSUED 6-2-86

mal operations for the airplane.All of the required (FAA regulations) proce- dures and those necessary for operation of the airplane as determined by the operating and design features of the airplane are presented. These procedures are provided to present a source of reference and review and to supply information on procedures which are the same for all aircraft. Pilots should familiarize themselves with the procedures given in this section in order to become proficient in the normal operations of the airplane. Normal procedures associated with those optional systems and equipment which require handbook supplements are provided by Section IX (Supple- ments). REV. B 6-12-87 ISSUED 6-2-86

Gear Switch . . WiagrrelolS'tarzer Switch Master Switch . , InternallExternai Lights Fuel Gauges, Quantity Master Switch . . Fuel Selector . . Fuel Selector . . . . . . . . . . . . DOWN . . . . . . . . .OFF . . . . . . . . . . . . . . ON . . . . . . . . . CIIECK . . . . . . . . . . . . . CHECK . . . . . . .OFF . . . . . W:PULL gascolator ring . . . . . . . . (5 seconds) . . . . L: PULL gascolator ring . . . . . . . . (5 seconds) 2.Right Tail Cone Area - instrument Static Port . . . . . . . UNOBSTRUCTED Right Fuselage . . . . . . . . . . CHECK skin condition Tail tiedown . . . . . . . . . . . . . . REMOVE 3. Empennage .- Elevator and rudder attach points and control linkage attachments . . . . . . . . . . . . . . CHECK General skin condition . . . . . . . . . . . . . CHECK Remove ail ice, snow, or frost. REV. B 6-12-87 ISSUED 6-2-86

Fresh Air Vent (on Dorsal Fin) . . . . . . . . . . . CLEAR Instrument Static Port . . . . . . . . . . UNOBSTRUCTED Left Fuselage . . . . . . .CHECK Skin condition Tailcone Access Door . . . . . . . . . . . . SECURED Static System Drain Push Plunger . . . . . . . . . . . UP . . . . (Hold 3-5 Seconds) 5. Left wing - Skin condition . . . . . . . . Remove all ice, snow, or frost. Flap and attach points . . . . . . . . . . . . . CHECK Aileron and attach points . . . . . . . . . . . . CHECK Control linkages . . . . . . . . . . CHECK Wing tips and lights . . . . . . . . . . . CHECK Left wing leading edge . . . . . . . . . . . . . CHECK Pitot tube . . . . . . UNOBSTRUCTED (Heat element . . . . . . . . . . . . . OPERATIVE) Stall Switch Vane . . . . . UNOBSTRUCTED Fuel Tank . . . . . . CHECK QUANTITY.SECURE CAP ---------- I NOTE I A reduced fuel indicator is located in the filler neck. This indicator is used to indicate useable fuel capacity of 25 U.S. gallons (94.7 liters) (20.8 IMP. Gal.) I NOTE I The optional visual fuel quantity gauge is to be used for partial refueling purposes only; DO NOT use for preflight check. . . . . . . . . . . . . . . Tiedown REMOVE Tank Vent . . . . . . . . . . . UNOBSTRUCTED Wheel chock . . . . . . . . . . . . . . REMOVE . . . . . . . . Left main gear, shock discs and tire CHECK Left main gear doors . . . . . . . . . . . . CHECK Fuel tank sump drain . . . . . . DRAIN Until Clear Pitot System Drain . . . . . . . . Push plunger UP . . . .(Hold for 3-5 seconds) Gascolator Drain Valve . . CLOSED (Check for drips) G.Left Cowl Area - . . . . . . . . . . . . . . . Windshield CLEAN . . . . . . . . . Left Side Engine Cowl Fasteners SECURED REV. €3 6-12-87 ISSUED 6-2-86

. . . . . . . . . Blades CHECK for nicks, cracks, oil . . . leaks, rotationalmovement. . . . . . . . CHECK de-ice boots(if installed). Spinner . . . . . . CHECK for security, cracks . . . . . . . Cooling Air and Induction Intake UNOBSTRUCTED . . . . . . . . . . . Landing Light CHECK Lens & Bulb . . . . . . . . . . Nose Gear, shock discs and tire CHECK . . . . . . . . Nose Gear Door CHECK for Loose Linkage Wheel Chock . . . . . . . . . . . . . REMOVE 8. flight Cowl Area - Wight Side Engine Cowl Fasteners Engine Oil bevel . . . . . . . . . . . . . . . Exhaust Pipe . . . . . Cowl Flap . . . . . Windshield . . . . . . . . . Cabin Cooling Vent . . SECURED . . . . . . . . . . CHECK . (full for extended flight.(Max. 8 qts.) . (Minimum qty. 6 qts.) . . . . . . . . . SECURED . . . . . . . . . CHECK . . . . . . . . . CLEAN . . . UNOBSTRUCTED 9. Right Wing - Fuel Tank Sump Grain . . . . . . . . . . DRAIN until clear Right Main Gear, shock discs and tire . . . . . CHECK Right Main Gear Doors . . . . . . . . . . . . CHECK Wheel Chock . . . . . . . . . . . . . REMOVE . . . . . . . . . . . . Tank Vent IJNOBSTRUCTED . . . . . . . . . . . . . . Tiedown REMOVE Right Wing beading Edge . . . . . CHECK Fuel Tank . . . CHECK QUANTITY. SECURE CAP --"------- ( NOTE I --"------- The reduced fuel indlcatar is located In the Biller neck. This indicator is used to indicate kaaable fuel capacity of 25 U.S. gallons (94.7 liters) (20.8 IMP. gal.) 1 NOTE / "."-=.------ The optisrsal visual fuel quantity gauge is to be used for paP%iai refueiing purposes only; DO NOT use Isr preflight check. REV. B 6-12-87 ISSUED 6-2-86

CHECK . . . . . . . . . . . . Aileron and attach points CHECK . . . . . . . . . . . . . Flap and attach points CHECK . . . . . . . . . . . . . . . Control linkages CHECK . . . . . . . . . Skin condition REMOVE ice, snow or frost . . . . . . . . . . . . . 10. Baggage Door SECURED BEFORE STARTING CHECK . . . . . . . . . . . . Preflight Inspection COMPLETED . . . . Seats, seat belts and Shoulder Harness ADJUST & SECURE . . . . . . . . . . . . MagnetoIStarter Switch .OFF . . . . . . . . . . . . . . . . Master Switch OFF . . . . . . . . . . . . . Alternator Field Switch .OFF . . . . . . . . . . . . . Avionics Master Switch .OFF . . . . . . . . . . . . . . Fuel Boost Pump .OFF . . . . . . . . . . . . Alternate Static Source Push OFF . . . . . . . . . . . . . InternallExternal Lights .OFF . . . . . . . . . . . . . . . Pitot Heat .OFF . . . . . . . . . . . . . . Throttle CLOSED . . . . . . . . . . . . . . Propeller HIGH RPM . . . . . . . . . . . . . Mixture IDLE CUTOFF . . . . . . . . . . . . . Cowl Flaps VERIFY OPEN . . . . . . . . . . . . . . . . Parking Brakes SET . . . . . . . . . . . . . . Flap Switch FIapsL.JP Cabin Heat , . . , . , , . . , , , . . PUSH OFF . . . . . . . . . . . . . . Defrost PUSH OFF . . . . . . . . . . . . . Cabin Vent AS DESIRED . . . . . . . . . . . . Fuel Selector FULLEST TANK . . . . . . . . . . Compass Slave Switch ON (if installed) . . . . . . . . . . . . . . . Circuit Breakers CHECK . . . . . . . . . . Emergency Locator Transmitter ARM . . . . . . Radios SET FREQUENCIES (Non-digital radios) . . . . . . . . . Radio Blower .Master Sw. ON, then OFF . . . . . . . . . . . . . Landing Gear Switch DOWN . . . . . . . . . . . . . Internal/External Lights .OFF . . . . . . Passengers EmergencyIGeneral information briefing Refer to Section IX for Optional Equipment Checks. Obtain local information prior to engine start REV. B 6-12-87 ISSUED 6-2-86

-=-------- When sta~ing engine using an approved external power source no special star4ing procedure is necessary. Use normal staP-Zing procedures below. (Auxiliary Power Cable Adapter is available from Mooney Aircraft Corporation). The beBery SHOULD MOT be COMPLETELY depleted when dafllng the engin@ with an auxiliary power source. Throttle . . . . . . . . . . . . . . 1140PEN . . . . . . . . . . . . . . Propeller HIGH RPM Mixture . . . . Full Fornard (RICH) Master . . . . . . . . . . . . . . Switch ON Alternator Field Switch . . . . . . . . . . . . . . ON Annunciator Lights . . . . . . . . . . . PRESS TO TEST (All lights except "START POWER QNshould illuminate. Fuel Boost Pump . . . . . . . . ON . . . . to Establish Pressure, then OFF . . . . . . . . . . . . . Mixture IDLE-CUTOFF Propeller Area . . . . . . . . . . . CLEAR MagnetolStafler Switch . . . . . . TURN and PUSH to start, release to both when engine starts. I NOTE I --------..-- "START POWER QN" warning ligM should illuminate when magnetolstar4er switch is in "START' position. 1 NOTE I Cranking should be limited to 30 seconds, end serversrl minutes al!owed between cranking periods to permit the starler to cool. Mixture . . . . Move slowly and smoothly to RICH Throttle . . . . Set at 1000 to 1200 RPM Engine Oil Pressure . . . if MINIMUM OIL PRESSURE . . is not indicated within 30 seconds, STOP ENGINE and determine problem. Voltmeter . . . . Check for 27-28 Volts . . (To verify alternator is ON LINE) REV. 5 6-12-87 ISSUED 6-2-86

by engine manufacturer. FLOODED ENGINE STARTING Fuel Boost Pump . . . . . Throttle . . . . . . Iinixture . . . . . . MagnetoISta~er Switch . . . . . . . . . Throttle . . . . . . Mixture . . . . . . Engine Oil Pressure . ~ . . . . . . . . . . . . . . . . . . . . . . .OFF . . . FULLFORWARD IDLE CUTOFF . . . . . . . TUWN and PUSHto . . . . . start, release to both when engine starts. . . . . Retard to 1200 RPM . . Full forward (RICH) . . . IS MINIMUM Qlb PRESSURE is not indicated within 30 seconds, STOP ENGINE and determine problem WARM ENGINE STARTING Fuel Boost Pump . . . . . . . . . . .OFF TOii'~"ctle . . . . . . . . . . . . . Slightly open !Mixture . . . . . . Fu!l AR (IDLE-CUTOFF) Magneto/Staaer Switch . . . . . . TURN and PUSH to . start, reiease to both when engine starts. . . . . . . . . . . . . Tt~rottle 11000 to 1200 RPM Engine Oil Pfessure . . . ii PJINIMUIVI 011- PRESSURE is Frat indicated within 30 seconds, STOP ENGlME and determine problem. BEFORE TAX[ Avionics Master Switch . . . . . . . . . ON External Lights . . . . . . . . . As desired DfrecZionai Gyro . . . . SET or SLAVE SWI'TCH - ON Instruments . . . . . . . . . . . Normal Operation Radios . . . . .CHECK (See Frequencies) A12lmeter . . . . . . . . . . . . . . . .SET Fuel Selector . . . . . . . . $\tiitch tanks, verify . . . . .engine runs on other tank Cozvl Flaps . . . . . . . . CHECK OPERATION . . (T1-1en position OPEN or AS REQUIRED) REV. B 6-12-87 ISSUED 6-2-86

-------- In cold weather, ground operations mey be conducted with cowl flaps padiaQly or fuily ciosed to keep engine tempeeures in normal operating ranges prior to takeoR. However, if cowl flaps are fully closed, monitor engine temperatures to avoid exceeding maximum eliiowable limits. N N N A I N N N N " CAUTION " R I N N N N N N N To prevent battery depletion during prolonged taxi or holding position before takeoR, increase RPM until "LOW VOLTS" warning ligh% stops fleshing . . . . . . . . . . . . . . . Parltirtg Brake Release . . . . . . . . . . . . Brakes Checic during Taxi Directional Gyro . . . . Proper indication during turns Turn Coordinator , . , . . , . Proper indication during turns . . . . . . . . . . . Artificial Pforizon Erect during turns Taxi . . . . . . Minimum power BEFORE TAKEOFF I NOTE I A thorough pre-takeoff check is r@commandee8, however EXCESSIVE time spent conducting a pre-takeoff check list wiiQ effect fuel economy. Parking Brake Fuel Selector Throttle Propeller Mixture Cowl Flaps Alternate Air Warn Air Alternator . . . . . . . . . . . . . . . .SET . . . . . . . . . FULLEST TANK . . . . . . . . . . . . . 120ORPM . . . . . . . HIGH RPM . . . . . . . Full Forward (RICH) , . , . . , , . FULL OPEN or AS REQUIRED . . . . . . . . . . . VERIFY CLOSER . . . . . . . CLOSED CHECK . . . . . . . . . . . . . . . REV. B 6-4 2-87 ISSUED 6-2-86

Alternator Rocker Switch . . . . . . . OFF(Alt. outputlload 0%) Volts . . . . . . Approx. 24V(HIGH/LOW VOLT Annun. . . . . . . . flashes) . . . . . . . Alt. Rocker Switch ON(Alt. outputlload increases) Volts . . . Approx. 28V(HIGH/LOW VOLT Annun. . extinguishes) . . . . . . . . . . . . Alternator Field Switch Verify ON . . . . . . . (after above check) . . . . . . . . . . Oil Temperature 75 Degrees F Minimum . . . . . . . . (Needle moves off white dot) " CAUTION " N N N N N N N Do not operate the engine at run-up speed unless the oil temperature is 75 Degrees F. minimum (needle moves off White dot). Operation of the engine at too high a speed before reaching minimum oil temperature may cause loss of oil pressure. . . . . . . . . . . . . Throttle 1900-2000 RPM . . . . . . . . Magnetos .CHECK, Both to L, Both to R, Both, (Maximum 175 RPM drop each magneto, 50 RPM Difference) I NOTE I An absence sf RPM drop may be an indication sf faulty magneto grounding or improper timing. If there is doubt concerning ignition system operation, RPM checks at a leaner mixture setting or higher engine speed will usually confirm whether a deficiency exists. Propeller . . . . . . Throttle . . . . . . Trim . . . . . . Flaps . . . . . . Controls . . . . . . Cabin Door . . . . . . Seat Belts and Shoulder Harness . Avionics and Auto Pilot . . . . Annunciator Lights . . . . . I~ternalIExternal Light . . . . Rotating BeaconlStrobe Lights CYCLElreturn to high RPM (3 times) , . . , . Retard to IDLE RPM . . . Takeoff setting Check operation - TAKEOFF POSITION Check free and correct movement . . .CHECKSECURED . . . . SECURED . . . Check(Refert0 . . . Section IX) . . . . Press to Test . . . . . . As Desired . . . . . . . . . . ON REV. B 6-12-87 ISSUED 6-2-86

. . . . . . . . DOWN . . . . . . . . . . . . and LATCHED Parking Brake . . . . . . . . , . . . Release ,/' URES -----w-s NOTE ( ---*---- Move the engine controls slowly and smoothly. Bn particular, avoid rapid apenir~g end closing of the throttle as the engins is equipped with a counterweighted crank shaB and there is a possibility of detunlrag the counter-weights with subsequent engins damage. Proper engine operation should be checked early in the takeoff roll. Any siginificant indication of rough or sluggish engine response is reason to dis- continue the takeoff. When takeoff tnusa be made over a gravel surface, it is important that the throttle be applied slowly. This will allow the aircraft To start rolling before a high RPM is developed, and gravel or loose material will be blown back from the prop area instead of being pulled into it. TAKEOFF Electric Fuel Boost Pump . . . . . . . . . . ON at star* of takeoff roll . . . . . . . . . . . . . . P ovoer . . . FUb.lTIlROTTI-E and 2700 RPNI Aircraft Attitilde . . . . . . . . . . . biR Nose Wheel at . . . . . . . .63 C

. . . . . . . . . . . . . . .62 KlAS Climb Speed . . . 66 KlAS until clear of obstacle, . . . . . . then accelerate to 91 to 100 KlAS . . . . . . . . . . . Landing Gear Retract in Climb After . . . . . . . Clearing Obstacle Wing Flaps . . . . . . Retract After Clearing Obstacle . . . . . . . . Electric Fuel Boost Pump OFF, Check Pressure *--------- I NOTE I ---------- See Section V, page 5-13, for takeoff distances and aircran weight versus speed table. CLIMB ---------- I NOTE I Use noise abatement procedure as published by airport and/or this manual. CLIMB (NORMAL) . . . . . . . . . . Throttle 26" Wg Manifold Pressure . . . . . . . . . . . . . . Propeller 2600 RPM Mixture . . . RICH (Lean for Smooth Operation . . . . . . at high elevation) Cowl Flaps . . . . . . FULL OPEN or As Required . . . . . . . . . . . . Airspeed .91 to 100 KlAS Maintain these power settings and attitude to at least 3000 feet AGL or cruise altitude. CLIMB (BEST RATE) Power . . . . Full Throttle and 2700 RPM Mixture . . . . FULL RICH (Lean at higher . , . , . , . . ~ltitudes for smooth operation) . . . . . . . . . . . . . Cowl Flap FULLOPEN Airspeed , . , , . . , , . . , , . 88 KlAS at sea . . . . level decreasing to 82 KlAS . . . . . . . . . . . . .at 10,000 A. . - ---------- I NOTE I --------"- See Section V, page 5-17 for rate of climb graph. REV. B 6-12-87 ISSUED 6-2-86

Power . . . . FULL THROTTLE and 2700 RPM Mixture . . . . . . FULL RICH (Lean at higher . . . . .altitude for smooth operation) . . . . . . . . . . . . . Cowl Flap FULLOPEN Airspeed . , . , . , . . 69 KlAS at sea level increasing . . . . . . . . approxiinately 1.0 KlAS for each . . . . . . . . . . . 5000 feet altitude Ram Air . . . . . .ON after entering clear air =-----"- I MOTE / ------me $0 Increase performance at fu61 throttle pkrll the Ram Air control aft (Ram Air QN position) allowing induceion air to bypass air s'i!%er and irlcrease manifsid pressure. Manifold pressure will drop with increasing altitude at any throttle set- ring.Power can be restored by gradually opening the throttle. lllllllllllllllllll IIIWARNINGIII ll//llllll/l/ll/ll// -DO MOT FLY AIRCRAFT INTO KNOWN lCsNG CQNB1TIONS- CRUISE Upon reaching cruise altitude, accelerate to cruise airspeed; relrirn aircraft as necessary for level flight. Set rnariifold pressure and RPM for desired power setting per Cruise Power Chart in Section V. Position cowl flaps as required to maintain the oil and cylinder head temperature within their normal operat- ing ranges. -----"-., I NDTE I --""---" When cruising in conditions where %he OAT is well above starsdard, it may be necessary to OPEN cowl l!aps sllghtiy in order to keep engine temperatures in the green arc. When cowl fBape are OPEN during crteiae, tho following effects on cruise speed %strill resuit: Cowf Flaps 114 open (1st index) Approximate loss in TAS . . 2 KTAS Cowl FIaps 112 open (2nd Index) Approximate lass in $AS . 4 KTAS WE!'. B 6-12-87 ISSUED 6-2-06

established in accordance with one of the following methods: A.Leaning using exhaust gas temperature gauge (EGT) (if installed). 1. Lean the mixture exhaust gas temperature peaks on the EGT indicator. ECONOMY CRUISE - Enrich mixture (push mixture control forward) until the EGT indicator drops 14' C (25 degrees F.) below peak. BEST POWER MIXTURE - Enrich mixture until EGT indicator drops 55 ' C(lOoO F.) below peak. ---------- / NOTE I ---------- Compared to Economy Cruise, Best Power mixture will result in an increase in fuel flow and a reduction in rang@. 2. Changes in altitude and power settings require the peak EGT to be rechecked and the mixture re-set. B. Leaning without exhaust gas temperature gauge (EGT). 1. Slowly move mixture control lever aft from "FULL RICH" position toward "LEAN" position. 2. Continue leaning until slight loss of power is noted (loss of power may or may not be accompanied by roughness). 3. Enrich until engine runs smoothly and power is regained. When increasing power always return mixture to full rich, then increase RPM before increasing manifold pressure; when decreasing power decrease manifold pressure before reducing RPM.Always stay within the established operating limits, and always operate the controls slowly and smoothly. DESCENT Mixture . . . LEAN to 14' C rich of peak EGT as . . , . . required for smooth engine operation Power . . . . . . As Required to keep CHT in . . . . . . . . . Green Arc (300' F minimum), A N N N N N N N N b " CAUTION " ( *- 8 d & t 3 f ) N N N N N N N N Avoid continuous operation between 1500 and t950 WPM with power settings below 15" Hg. manifold pressure. REV. B 6-12-87 4-1 4 ISSUED 6-2-86

Exercise caretion with power setti~sgs below 15" Wg manifold pressure at airspeeds between 79 - 113 KlAS to preclude continuaus operation in the 1800 - 1956 WPM restricted range. Avoid song high speed descents at low svmsamifold pressure as the engine can coo[ excessively. . . . . . . . . . . . . cowl Flaps .FULLCLOSED . . . . . . Ram Air OFF before entering dusty air layers Plan deacetnts to arrive al pattern altittrde sra dow~nwirnd ieg for nlaximum fuel efficiency and mir~imunr aircraft noise. APPROACH FOR LANDSNG lnternnl/External Lights . . . . . . . . . . . . As desired Seat Belts, Shoc~lder Harness . . . . . FASTENED Landing Gear . . . . Extend below 140 KIA§ . . (Gear down light on - Cheekvisual . . . . . . . . . . . indicator on floor) . . . . . . . . . . . . . . Nlixtc~re FULL RICH . . . . . . . . . . . . . . Propeller HIGH RPM Fuel Boost Pump . . . . . . . . . . . . . . . ON . . . . . . . . . . . . Fuel Selector FULLEST TANK . . . . . . . . . . . . . Wing Flaps AS DESIRED TAKEOFF POSITION . . below 132 KlAS FULL DOWN . . . . . . . . below 1 15 Ki AS From a fDapo retracted trimmed condition, the force required for nose up pitch control wil! rapidly increase when power is reduced $0 idie and as flaps are fuisy extetsdeee". TimeBy trimming action should be accomplished $0 n~inimlze forces. Control force change with extending landing gear is minimal. Trim . . . . . . . . As desired . . . . . . . . Ram Air Verify OFF (warning light OFF) Parking Brake . . . . . . . . . . . . . . OFF REV. B 6-12-87 ISSUED 6-2-86 4-1 5

applied brakes during touchdown. GO AROUND (BALKED LANDING) N N N N N N N N " CAUTION " N N N N N N N N From a flaps extended and power at idle trimmed condition, the force required for nose down pitch control will rapidly increase when Maximum Continuous Power (MCP) is applied and as flaps are fully retracted. Little control force change will be experienced when retracting the landing gear. Power Mixture Airspeed Flaps Trim Airspeed Landing Gear Flaps Cowl Flaps Airspeed , FULL THROTTLE and 2700 RPM . . . FULL RICH . . . .65 UIAS , . , After climb established- . . . Takeoff position Reduce control force by trimming . . . . . NOSE DOWN . . Accelerate to 73 UlAS . . . . RETRACT . . . . RETRACT . . . . OPEN , , . . Accelerate to 91 KlAS LANDING LANDING (NORMAL) . . . . . . . . . . Airspeed on Final 71 KlAS (Full Flaps) . . . . . . . . . . . . Touchdown Main wheels first . . . . (aligned with runway) . . . . . . . . . . Landing Roll Lower nose wheel gently Brakes . . . . . . . . . . . . Minimum required . . . . . . . . . Wing Flaps Retract after clearing runway . . . . . . . . . . . . Boost Pump OFF after landing . . . . . . . . . . . . Trim Takeoff position -----*"--- ( NOTE ( -"-------- See Section V, pages 5-33 through 5-36 for Landing Distance Tables. REV. B 6-12-87 ISSUED 6-2-86

Airspeed on Final , , , , . , , , , , 65 MIAS (Full Flaps) . . . . . . . . . . . . Touchdown Main Wheels First Landing Roll . . . . Lower nose wheel quickly as . . . . . . . .possible Brakes . . . Maximum possibie without . . . . . . . . . . . . . locking wheels MNDiNG (CROSSWIND) Airspeed on Final . . . . . Above normal approach . . . airspeed with Full Flaps . , . . , , . , . . (if crosswind component is above 12 MTS use TAKEOFF Flaps position. Final Approach . . . . . . Allow Aircraft to crab . . . . . . . . . . . Prior to flare Slip aircraft into wirid . . . . . . . . . Touchdown Main wheels first (ALIGNED . . . . . . . \NlTH RUNWAY) Landing Roll . . . . . . . . Lower nose wheel as q~~ickly . . . . . . . . . . . . . as possib!e . . . . . . . . . Brakes As required to slow aircraR . . . . . . . as quickly as possible "CAUTION " M N < % . M N N N The Banding pear may retrac"luuring lassding roll if las~dirag gear obvitch is itsadvertently placed ial the UP position. TAXI AFTER L4NDING . . . . . . . . . . . . Throttle I000 to 1200 RPldl Flaps . . . . . . . . . . . . . RETRACT Cowl Flaps . . . . . . . . . . FUI-LOPEN Trim . . . . . . . . . . . . RESET to Takeoff Radios . . . . . . . . . .As required Lighting . . . . . . . . . .As required Parking brake . . . . . . . . . . SET . . . . . . . . - . Throttle 100C1 to '1200 WPM (cinlil cylinder . . . . . . . . head temperature staris to drop) Avionics Master . . . . . . . . . . . .OFF InternalIEflernal Lights . . . . . . . . . . . . . . QFF . . . . . . . . . MagnetoIStaRer Switch Grounding Check Mixture . . . . . . . . . . . . . IDLE CUTOFF REV. B 6-12-83 ISSUED 6-2-86

. . . . . . . . . . . . . Alternator Field Switch .OFF . . . . . . . . . . . . . . . Master Switch .OFF . . . . . . . . . . . Oxygen System (if equipped) .OFF SECURING THE AIRCRAFT MagnetolStarter . . . . . . . , . , . . BFFIKeyremoved . . . . . . . . . . . . . Master Switch VERIFY OFF . . . . . . . . . . . . . Avionics Master VERIFY OFF . . . . . . . . . . . . Electrical Switches VERIFY OFF Parking Brake , , , , , RELEASE and install wheel chocks For extended parking.Control wheel . , . , . , . SECURED with seat belts; cabin vents closed, tie down aircraft at wing and tail points. REV. I3 6-12-87 ISSUED 6-2-86

PAGE INTRODUCTION 5-2 USE OF PERFORMANCE CHARTS 5-2 PERFORMANCE CONSIDERATIONS 5-3 RANGE ASSUMPTIONS 5-3 USE OF COWl- FLAPS 5-3 ,p, MAIN GEAR $.qVV~WpOOR WEMQVAL T E M P ~ R A T U W ~ &NVERSI~T\I AIRSPEED CALIBRATION PRIMARY STATIC SYSTEM (GEAR UP) 5-6 AIRSPEED CALIBRATION PRIMARY STATIC SYSTEM (GEAR DOWN) 5-7 AIRSPEED CALIBRATION ALTERNATE STATIC SYSTEM 5-8 ALTIMETER CORRECTION PRIMARY STKTIC SYSTEM (GEAR UP, FLAPS 1JP) 5-9 ALTIMETER CORRECTION PRIMARY STATIC SYSTEM (GEAR BN, FLAPS BN) 5-10 ALTIMETER CORRECTION ALTERNATE STATIC SYSTEM 5-4 4 STALL SPEED VS ANGLE OF BANK 5-1 2 NORMAL TAKEOFF DISTANCE 5-13 eM&XIMUM PERFORMANCE T NORMAL TAKEOFF DISTANCE - GRA MM4MUM PERFORMANCE GRASS SURFACE r P RATE OF CLIMB TIME, FUEL & DISTANCE TO CLIMB CRUISE & RANGE DATA CONDITION CRUISE POWER SCI-1EDULE.I; SPEED POWER vs ALTITUD~ RANGE 75% POWER 5-24 RANGE 65% POWER 5-25 RANGE 55% POWER 5-26 RANGE 45% POWER 5-27 ENDURANCE 75% POWER 5-28 ENDURANCE 65% POWER 5-29 ENDURANCE 55% POWER 5-30 ENDURANCE 45% POWER TIME-FUEL-DISTANCE TO DESCEND NORMAL LANDING DISTANCE 5-33 : MAXIMUM PERFORMANCE LANISING Dl NORMAL M MbXlldlUM P - GRASS h4lSSIQN PR REV B 6-12-87 ISSUED 6-2-86 5- I

pilot can derive the information needed to plan flights with reasonable ac- curacy. The performance data and charts presented are calculated based upon actual flight tests , using average piloting techniques, the airplane and engine in good condition and the engine power control system properly ad- justed. The flight test data has been corrected to international standard at- mosphere conditions and then expanded analytically to cover various airplane gross weights, operating altitudes and outside air temperatures. It is not possible to make allowances in the charts for varying levels of pilot technique, proficiency or environmental conditions. The effect of soft run- ways, winds aloft or airplane configuration changes must be evaluated by the pilot. However, the performance data on the charts can be duplicated, by fol- lowing the stated procedures, in a properly maintained, standard M20J. Mechanical or aerodynamic modifications to the aircraft are not authorized since they can affect the performance or flight characteristics of the aircraft. USE OF PERFORMANCE CHARTS Performance data is presented in tabular or graphical form to illustrate the ef- fect of different variables. Example problems are shown on each chart to demonstrate how each chart is used. Only on those charts whose use is ob- vious is no example given. Generally, three items are required before entering each performance chart: (1) aircraft weight, (2) outside air temperature and (3) aircraft pressure al- titude. The aircraft weight can be calculated utilizing the information provided in Section VI of this handbook. Outside air temperature is obtained by read- ing the OAT gauge in the instrument cluster. Set the aircraft's altimeter to 29.92 in. Hg. and read the indicated (pressure) altitude. (BE SURE TO RETURN THE ALTIMETER TO THE LOCAL BAROMETRIC PRESSURE SET- TING AFTER OBTAINING PRESSURE ALTITUDE). Performance information derived by extrapolation beyond the limits shown on the charts should not be used for flight planning purposes. REMEMBER--To get chart performance, follow the chart procedures. OPERATIONAL PROCEDURES FOR MAXIMUM FUEL EFFICIENCY For maximuim fuel efficiency in the MZOJ, proper mixture leaning during cruise flight must be accomplished. The 10-360-A3B6D engine in the M20J has been designed to attain maximum fuel efficiency, at desired cruise power, at 1 4 ' ~ rich of peak EGT. E G Tis usually a more accurate indication of en- REV. B 6-12-87 j-2 ISSUED 6-2-86

mended that the mixture be set using EGT as the primary reference rt~slead of setting to a particular fuel flow. The Bollowing procedure is recornniended for setting cruise power and lean- ing to best economy at 75% power or less: I . AMer leveling off, set the manifold pressure and WPM for the desired cruise power in accordance with the cruise power schedule on page 5-)o(. At this point, the mixture control is at full rich from the climb. 6iv2 7 2. Next, slowly move the rnixtur rol toward lean while observing the EGT indicator. if leaning the mixtrr es the original manifold pressure sgt- ting to change, use the throttle to in that desired cruise manifold p b - sure and continue leaning until best economy setting is obtained. PERFORMANCE CONSIDERATIONS RANGE ASSUMPTiONS Range data ciimb allowance is based on climbing at maximum continuous power lo cruise altitude. Range reserves of 45 miriufes at cruise power have been allowed on Range Data. Other conditions rised in the Ranges shown are listed on each chart. Wh@!l in level cruise flight with outside air temperatures wgil above standard or when crc~ising at very high altitudes, it may be necessary to open the cowl Slaps to keep engine temperatures in the normal operating range. Since the cowi flaps in the M20J ;lare multi-position, numerous open settings are avail- abie to keep cylinder head and oil temperatures in the green arc under the snost adverse cunditiorss. Using the cowl flap's position indicator as a reference, the following cowl flap's open positions are given along with their effects on cruise speed: Cowl flaps closed to cowl flap's indicator- 414 open, (Indicator positioned at first index); (approximate loss in TAS) . . . . . . . . 2 Kts. Cowl flaps closed to cowl flap's indicator- 1/12 open, (Indicator positioned at second index); (approximate loss in TAS) . . . . . . . . 4 Kts. REV. B 6-4 2-87' ISSUED 6-2-86

condition can be made based on the flight time planned with the cowl flaps partially open. For example, using the above speed decrement for the cowl flaps 112 open for a 5 hour flight will result in the following decrease in range: 5 hr. x 4 Kts. = , . . . , 20 N.M. reduction in range MAIN GEAR LOWER DOOR REMOVAL If numerous takeoffs and landings are to be conducted on soft fields or in tall grass. or if ice and snow are likely to be present on runway and taxiway sur- faces for extended periods, it may be advantageous to remove the lower doors(extended position) installed on each main landing gear. These doors can be damaged during operations in soft field conditions, or a heavy ac- cumulation of packed snow or ice inside the doors could prevent proper land- ing gear operation. If these small gear doors are removed, a decrease in cruise speed and range can be expected and should be considered in preflight planning. To be con- servative, the following figures should be used: A. Decrease true airspeed at cruise by approximately 5 Kts B. Decrease range by as much as 50 N,M.(92 Km) for 64.0 gallon(243 liters) fuel capacity. REV. B 6-12-87 ISSUED 6-2-86

ISSUED 6-2-86

FLAPS AND GEAR UP, POWER ON 80 70 80 00 100 110 120 130 140 150 180 170 180 190 200 IAS - INDICATED AIRSPEED - KNOTS 6-12-87 REVB ISSUED 6-2-86

F U H AND GEAR mW REVB 6-12-87 ISSUED 6-2-86

CONDITIONS: S t o r m Window and Vents: CLOSED Defroster : ON POWER: ON 6-12-87 REVB ISSUED 6-2-86

ASSOCIATED CONDITIONS: Forward C.G. Power Idle NOTE: - U p to 290 feet altitude loss may occur during stalls at maximum weight. EXAMPLE : Weight 2500 LBS (1134 KGS) Landing Gear Down Flaps 150 Angle of Bank 45° Stall Speed 64.0 KCAS (68.0 KIAS)

ddoaxvd~~ g g g ~ ~ g g ~ g ~ g " " " " " " " " 0 0 0 0 ~ 0 ~ - C l m - , " n - ~ L I C l n - , - - _ " , . * _ - - - B) :: - c.* . " , -

Associated Conditions for the Time, Fuel and Distance to Clitnb graph on the following page: Cfimb Speed: Vy from Climb performance graph on preceeding page. Power: . . ,2700 WPM,Full Throttle . . . . . . . . . . . . Mixture: Fui! Rich Ram Air: . . . . . . . . . . . . ON Cow! Raps: . . . . . . . Full Ope$> banding Gear: . . . . . . . . . . . . UP Wing Flaps: . . . . . . . . . . . UP Fuel Density 6.0 Ibslgal 1.92 Kglliter) [VOTE: I. Distances showrr are based on zero wind. 2, Acid 9 ibs(4.1Kg) of fuei for start, taxi & T.Q. EXMGiPLE: See next page on Graph REV. B 6-12-87 !SSUED 6-2-86

MBONEY MODEL M20J I. Ali Cruise & Range Data tables allow for: warmup, taxi, takeoff, climb at max, power at best rate of climb speed (Vy) to cruise altitude, cruise to destination at the specified power and mixture setting, descent to pattern altitude and a 45 minute fuel reserve at the same altitude and power setting. The data is also based on 64 IJS. gals. of usuable fuel, standard atmosphere and no wind. 2. To ob%ain the performance shown by the Cruise and Range Data Tables on non-standard days, increase or decrease the matiifold pressure approximately .4 in. Wg. for each 10C variation in outside air temperature. INCREASE manifold pressure for air temperatures ABQ\IE standard and DECREASE manifold prss- sura for air a@rnperatures LOWER than standard. REV. B 6-12-87 ISSUED 6-2-86