Special Letter 92-1

3. If rudder balaaee falls within the above limits, re-install rudder on the aircraft per M20J S & M, Section 27-20-00, paragraph 2, B. Proceed to Step 8. If rudder does not fa!!within the above limits, proceed to Step 4. 4. Teinporarily add additional wei ht (washers or any other items) until static balance falls within limits. Remove temporary weights and weigh Iaem to see approximately how much additional weight was need& to baianr,a,\~lithinlimits. If 2.66 oz. or less is needed, the addition of washers described in Step 5 will provide the necessary added weight (ie. 16 each AN970-3 washers weigh 2.66 02.) 5. If balance just exceeds limit, one method is to remove the balance weight attach screws, one at a time and add washers under screw head (up to two under each screw) as required to balance rudder within the 2900 pound limits. If necessary, proceed to each attaching screw and add washers. It is recommended that the washers be distributed among all 8 attaching screws for a neater appearance. Either ANW-10 or AN970-3 washers may be used. However, for each washer added under screw head, the length of the NAS623-3 screw MUST BE increased by one dash number. (See Service Bulletin Kit for Part Numbers. You will need to request the quantity of washers and/or screws desired) 6. If greater than 2.66 oz. is required, remove the balance weight and weigh it together with the temporary weights. The total weight of these should be the specified weight of the new 46001 1-503 balance weight ordered. The maximum 460011-503 balance weight available is 2.88 pounds. 7. Re-check rudder after each change to the balance weight per S & M manual procedures until within limits. 8. Enter compliance statement in Airframe log book and return aircraft to service. WAR RANW: Mooney Aircraft Corporation will allow up to 2.5 hours labor to inspect the rudder balance. If the rudder is out of balance, up to an additional 2.0 hours will be approved to balance and repaint as . The necessary weights and hardware can be ordered throu h the nearest Mooney il Service necessal? enter. Warranty cred~twill be allowed for this Servie Bulletin e ort if necessary paperwork is received by Service Parts within 180 days of the date of this Service Bulletin. $5 M20-252 DATE: 4-6-92 REFERENCE DATA: N/A PARTS LIST: KIT PART NUMBER - SB M20-252-1 ITEM PIN . DESCRIPTION Q T Y 1. 46001 1-503 . WEIGHT, BALANCE . 1 * 2. AN960-10 . WASHER . .16 * * 3. AN970-3 . WASHER, LARGEOD . .16 ** 4. NAS623-3-2 . SCREW . . . 8 ** 5. MAS623-3-3 . SCREW . . 8 ** * Order weight as needed. 2.88 pounds is heaviest weight available from MAC. ** Use as required per Step 5 FIGURES1 TABLES: Refer to M20J Service and Maintenance Manual,No. 121, Chapter 27, FiGURE 27-18 and 27-19. CAUTION Use the limits depicted in this S&afor 2900 pound gross weight airera8 until S & M 6891 t38 reviad. MOQNEV AlRCRAFT 60RPOWAT!ON P.0. BOX 92 MEW RVILLE, TEmS 78829-8872 FAA APPROVED AIRPMNE FLIGHT MANUAL SUPPLEMENT M20J (SIN 243154 THRU 24-3208, 24-3282 TWRU 24-3217) WITH lNCREASEB GROSS WEIGHT MODIFICATIONS FOR 4988 POUND OPERATIONS REG. NO. SERIAL NO. -- This Supplelnent must be attached to the M20J F M Approved Pilot's Operating I-landbook and Airplane Flight Manual (POHIAFM) , No. 3201, basic issue or subsequent revisions, when aircraft (within Serial Numbers listed above) are operated at an increased gross weight of 2900 pounds. The information contained herein supplements or supersedes the basic rnanual only in those areas listed by a vertical black mark in the margin. For limitations, Erocedures and performance infortnation not contained in this supplement, corisult the asic Airplane Flight Manual. FAA APPROVED: Michele M. Owsley Mana er, Aircraft Certification Office F E D E ~ A LAVIATION ADM~NISTRATION Fort Worth, Texas. 761930150 Date: 11 - 91 M20J - 2900 POUND MOONEY AIRCRAFT CORPORATION GROSS WT. OPERATIONS AFM SUPPLEMENT MOUNEY A I R C R A F T C O R P O R A T I O N P, 0,BOX 72 K e r r v i l l e , Texas 78029-0072 LOG OF R E V I S I O N S The r e v i s e d p o r t i o n s o f a f f e c t e d pages a r e indicated by v e r t i c a l Mack Lines in t h e margin, Page 2 of 5 FAA APPROVED K e v i i i o r Number Revlslon Pages Description o f Revisions FAA Approved D a t e MOBNEY AlRCMAn COfaPBFiA1ION M%0,1 29i)k) PUklND AFW1 SUPPI-EMENT GROSS Y\d f O17ERATIONS This supplement is to provide operating procedures and performance data for the M20J aircraft, SIN 24-3153 thru 24-3200, 24-3202 thru 24-3217, when operating at the increased gross weight of 2900 pounds. 7'he pages of this AFM Supplement, will supercede the basic pages of Poi-(IAFWI, No. 3201, or subsequent revisions, in the areas marked with a vertical black line in the margin. The data on the entire page is provided for immediate reference even though some of it may be the same as the basic PBHIAFM. The following supplernental pages are to be used when operating at the increased gross weight of 2900 pounds: Page Number 1-3 THWU 1-6 The following supplemental pages are to be used when operating at the increased gross weight of 2900 pounds: Page Nurnbers 2-1 TI-IRU 2-4, 2-71 2-8 The following supplernental pages are to be used when operating at the increased gross weight of 2900 pounds: Page Number 3-3/34, 3-713-8 The following supplemental pages are to be used when operating at the increased gross weight of 2900 pounds: Page Nurnbers 4-414-2, 4-9 THRU 4-14 The following supplemental pages are to be used when operating at the increased gross weight of 2900 pounds: Page Numbers 5-1 TWWU 5-4, 5-1 4 TWRU 5-35 FAA APPROVED Page 3 of 5 M20J - 2900 POUND MOONEY AIRCRAFT CORPORATION GROSS W. OPERATIONS AFM SUPPLEMENT r...-.. .......... ...-.--.... ...........*...-...... ............-......... ..--< ...--..-.--....*.. ..........-.. SECTEONVI - WEIGHT AND BALP~NCE~ I......-..... - .-.-..-.. ........ --.".-.. The following supplemental pages are to be used when operating at the increased gross weight of 2900 pounds: Page Numbers 6-116-2, 6-5 thru 6-10 The following supplemental pages are to be used when operating at the increased gross weight of 2900 pounds: Page Number No pages changed for this SECTION. The following supplemental pages are to be used when operating at the increased gross weight of 2900 pounds Page Number No pages changed for this SECTION. The following supplemental pages are to be used when operating at the increased gross weight of 2900 pounds: Page Numbers Supplemental Pages for M20J 2900 # Gross Weight operations added to this Section. . ............. >...-........ ...... -.....-...................-.. ISECTION X - SAFEW hk OPERATIONAL TIPS\ The following supplemental pages are to be used when operating at the increased gross weight of 2900 pounds: Page Number No pages changed for this SECTION Page 4 of 5 FAA APPROVED M20,4 - ki9iiU P O U N[S GROSS Wl-. ClEJERA"1'16)NS I NOTE I ---------" ALL PAGES LISTED BINDER SECTION HEADINGS ABOVE UkdST BE INCLUDED IN THIS SUPPLEMENT AND BNSERTED INTO THE POHlAFM OF ANY MSQd AIRCRAFT (WITHIN SIN'S LISTED) WHICH IS OPERATING AT THE INCREASED GROSS WEIGHT OF 2900 POUNDS. ~ W N W , v , . , N " CAUTION " - w , " , - , N c " , " THE AIRCRAFT WEIGHT AND B A U N C E DATA AND EQUIPMENT LlSTlNGS (SECTION VI) FROM THE ORIGINAL POHIAFM MUST BE ENTERED &N TO ANY SUPPLEMENTAL PAGES INSERTED INTO THE POHIAFM WHEN THE AIRCRAFT IS TO BE OPERATED AT 2908 POUNDS GROSS WEIGHT. FAA APPROVED Page 5 of 5 AFBb'i 3201 SUPPLEBAENT 2900 POUND GROSS WEIGH9 C*.~,-3"- .akC IION I GENERAL This Pilot's Operating Handbook conforms to GAMA S ecification No. 1 and in- cludes both manufacturers rnaterial and FAA APPWOVAmaterial required to be furnished to the pilot by the applicable Federal Aviation Regulations. Section IX contains supplemental data supplied by Mooney Aircraft Corporation. Section I contains information of general interest to the pilot. It also contains defini- tions of the terminology used in this Operators Manual. This Pilot's Operating Handbook is not designed as a substitute for adequate and competent flight instruction, knowledge of current airworthiness directives, ap- glicable federal air regulations or advisory circulars. It is not intended to be a guide or basic flight instruction or a training manual and should not be used for opera- tional purposes unless kept in an up to date status. A11 limitations, procedures, safet practices, servicing and maintenance re uire menis published in this P ~ H l A ~ d a r e considered mandatory for the continue2 Air: worthiness of this airplane in a condition equal to that of its original manufacture. THIS SECTION DOES NOT REQUIRE FAA APPROVAL. I)ESCG3IP'I IVE DAT~,; ENGINE Number of engines . Engine IIAanufacturer Model . . ~ e e o m m e n d e d ' ~ ~ 8. . . . Type . . . Number of cylinders . . . . . Displacement . . Bore . . . Stroke . . . Compression ratio Fuel Systern . . . TY pe Make ~ue14viation'~asdline ' Accessories Magnetos . . . . . Spark +lugs , , . . . ~ ~ t e r n a t b r . . Starker . . , Ratings: Maximum Continuous Sea Level-BHPIRPM PROPELLER Number . . . Manufacturer . . Model Number . . Number of Blades Diameter Max. , , SUPPLEMENT ISSUED 14-91 . . . I . . AVCO iycomin . . I0-360-A3B68 1800 Hours . . . . Reciprocating, aircooled, . fuel injected. . .4, Horizontally . .opposed : 36; Cu. In. (5915.7 cc) . 5.125 In. (13.02 cm) . 4.375In.(lI.lIcrn) . 8.7:1 . . Fuel Injection Flow . . Bendix, RSA-5-AD1 . . . 400 or IOOLL min. grade . . . . . Bendix D4LN 2021 or D4LN3021 . . . . . 18 MM X ,750-20 . . Phd. Connection . . Prestolite 28V, 70A . . Prestolite 24 Volts SECTION I AFM 3201 SUPPLEMENT MOONEY GENERAL 2900 POUND GROSS WEIGHT MODEL M2QJ Min. . Type Governing Blade Angles . . . . .73.0 in. (185.4 cm)* Constant Speed . . . . . . . . , , , . . , . ~ ~ b r a u ~ i c a ~ ~ ~ controlled . . . . . . . by engine oil @ 30 in. Sta. (75 cm): . . . . , . bow .I3.9 degrees +/- .2 degrees* . . . High 33.0 degrees +/- .5 degrees* * OPTION: Hartzell HC-C2YK-1BFlF7666A-36 73.0" (185.42 cm) (No cutoff allowed) Blade Angles: @30 in. sta.(75 cm) Low: 14.1 degrees +I- . I degree High: 29.3 degrees to 31.3 degrees Spinner: Hartzell No. A2295 FUEL. . . . . . Minimum Fuel Grade (Color) 100/130 Green) . . . . . . . . . 100 LL ( ~ l u e j Total Capacity . . . . . . . 66.5 U.S. Gal. . . , , . . , . (251.7 iters)(55.4 Imp. Gal.) Usable . . . . . . . . 64.0 U.S. Gal. . . . . . . . (242.3 Gters)(53.3 Imp. Gal.) Total Oil Capacity . , , , . . 8 Qts. (7.57 Liters) Oil Capacity Min~mumfor Flight . . 5 Qts. . . . . . . (4.73 Liters) . . . . . . . . . . Oil Filter .Full Flow Oil grades, specifications and changing recommendations are contained in Section VIII. LWNBlNG 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. . . . . . . . Wheel Base 71 9/16 in. (181.0 cm) Wheel Tread , , , . . , . . 110 in. (279.4 cm) Tire Size: Nose . . . . Main . . . . 5.00 x 5 6 ply Type Ill 6.00 x 6 16 pldType Ill Tire Pressure: . . . . . . . . . . . Nose 49PSI . . . . . . . . . . Main 3OPSI Min. Turning ~ a d i u s . . . . . . . (No brakes applied) .41 R. (12.5 m) MAXIMUM CERTIFICATED WEIGHTS I Maximum Loading (unless limited by C.G. envelope) . . . . . . . Gross Weight 2900 Lbs. (4315 Kg) . . . . . . . . Baggage Area 120 bbs. (54.4 Kg) . . . . . . . . . Hat Rack 10 bbs. (4.54 Kg) Cargo (Rear Seats . . . . . . . Folded Down) .340 Lbs. (154.2 Kg) 1 - 4 SUPPLEMENT ISSUED 14 -91 emLC N"" ' 2 SECTION I GENERAL WFM 3201 SUPPLEMENT 2900 POUND GROSS WEIGHT MOONEY MODEL MSQd GENERAL AIRSPEED TERMINOLOGY & SYMBOLS 9 Acceleration due to gravity. G S 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 t o 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. M A S KNOTS TRUE AIRSPEED - The airspeed of an airplane relative t o undisturbed air. v a MANEUVERING SPEED - The maximum speed at which application of lull available aerodynamic control will not overstress the airplane. Vr e MAXIMUM FLAP EMENDED SPEED - The highest speed permissible with wing flaps in a prescribed extended position. Vie MAXIMUM LANDING GEAR EmENDED SPEED - The maximi~m speed at which an aircraR can be safely flown with the landing gear extended. ~ I O MAXIMUM UNDlNG GEAR OPERATING SPEED -The maximum 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. VS 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 takeoff, normal,abnormal or 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 1 - 6 SUPPLEMENT ISSUED 1 4 -99 TITLE . . . . . . . . . . . . . . . . PAGE INTRODUCTION . . . . . . . . . . . . . . . . . 2.2 AIRSPEED LIMITATIONS . . . . . . . . . . . . . . . 2.3 AIRSPEED INDICATOR MARKINGS . . . . . . . . . . . . 2.4 POWER PLANT LIMITATIONS . . . . . . . . . . . . . 2.5 POWER P U N T INSTRUMENT MARKINGS . . . . . . . . . 2.6 WEIGHT LIMITS . . . . . . . . . . . . . . . . .2.7 CENTER OF GRAVITY (GEAR DOWN) . . . . . . . . . . . 2.7 NOISE LIMITS . . . . . . . . . . . . . . . . . 2.7 MANEUVER LIMITS . . . . . . . . . . . . . . . . . 2.7 FLIGHT LOAD FACTOR LIMITS . . . . . . . . . . . . .2.8 . . . . . . . . . . . . . KINDS OF OPERATION LIMITS 2.8 FUEL LIMITATIONS . . . . . . . . . . . . . . . . 2.8 OPERATING ALTITUDE LIMITATIONS . . . . . . . . . . . 2.9 . . . . . . . . . . . OTHER INSTRUMENTS & MARKINGS 2.9 DECALS & PUCARDS . . . . . . . . . . . . . . . 2-10 CABIN INTERIOR . . . . . . . . . . . . . . 2-10 FUSELAGE INTERIOR . . . . . . . . . . . . 2-15 EXTERIOR . . . . . . . . . . . . . . . . 2-16 INFORMATIONAL . . . . . . . . . . . . . . 2-10 OPTIONAL . . . . . . . . . . . . . . . . 2-20 FAA APPROVED SUPPLEMENT ISSUED 11-91 AIRPLANE FLIGHT MANUAL 2 .1 SECTION II LIMITATIQNS AFM 3201 SUPPLEMENT 2900 POUND GROSS WEIGHT MOONEY MODEL M2OJ Section II includes operating limitations, instrument markings, and basic placards necessary for the safe operation of the airplane, its engine, standard systems and standard equipment. The limitations included in this section have been approved by the Federal Aviation Administration. When applicable, limitations associated 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) ere based on Airspeed calibration data shown in Section V with the normal static source. If the alternate static source is bein used, ample margins should be observed to allow for the airspeed calilration variations between the normal and alternate static sources as S h ~ w f lin Section V. Your Mooney is certificated under F M Type Certificate No. 2A3 as a Maoney M20J. ..*,,..,,. ,...,,,..,,,*..,,,.,..:..,.., :: NOISE LIMITS 1 r_..:.,:..: *...-- <.-........ *..-....,, The certificated noise level for the M20J at 2900 Ibs. (1315 Kg.) maximum weight is 80.64 dB (A). No determination has been made by the Federal Aviation Administra- tion that the noise levels of this airplane are or should be acceptable ar unaccep- table for operation at, into, or out of, any airport F M APPROVED SUPPLEMENT ISSUED 11-91 AkzM 3203 SUOPhkMEN 1 2900 POUND GROSS WklGPIE SECTION II I,.I!vILI:~T'ATIB~~S Airspeed limitations and their operational significance are shown in F i g ~ ~ r e 2.1. This calibration assumes zero instrument error. SPEED KCASIKlAS REMARKS VI-0 (EXT) VL.0 (RET) Never Exceed Speed Maximurn Str~lctural Cruising Speed Do not exceed this speed in any opera- tion. Do not exceed this speed except in smooth air, and then only with caution. Maneuvering Speed at: Ib./Kg. Do not ma.ke full or 225011021 -1031104 abrupt control move- 247011 120 1081109 ments above this 274011243 1141115 speed. 290011315 117/128 Maximum Flap 7091112 Do not exceed this Extended Speed speed with flaps in full down position. Maxirnum 1301132 Maximum speed at Landing Gear which the aircraft can Extended Speed be safely flown with the landing gear ex- tended. Max. Speed for 13014 32 Gear Esension Max. speed at which the landing gear can be safely extended Max. Speed for I041107 Maximum speed at Gear Retraction which the landing gear can be safely retracted. Maximum Pilot 1301132 Window Open Speed Do not exceed this speed with pilot win- dow open. FIGURE 2-1 AIRSPEED LIMITATIONS FAA APPROVED SUPPI-EMENT ISSUED 11-91 AIRPLANE FLIGHT MANUAL 2 - 3 SECTION II AFAR 3201 SUPPLEMENT MOONEY LIMITATIONS 2900 POUND GROSS WEIGHT MODEL M20J r.. , . . . .. .--.,,,,.,,,,,.,.,,.,,,,.,,,.,,.,A , ,.",,.,"~...~, ?IFISPEED INDICATOR ~ A F I K I N G S ~ ,,,,,,,.,,,,, v...,,.. ,,,*a,.,,- .,.,",..., ,..~ ,- a,,,,,.-,.. ,A,,,, ,. Airspeed indicator markings, their color code and operational significance are shown in Figure 2-2. MARKING White Arc (Full Flap Operating Range) 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 con- figuration. Upper limit is maximum speed permis- sible with flaps extended. Lower limit is maximum weight Vs with flaps retracted. Upper limit is maximum structural cruis- ing speed. 174-196 Operations must be con- ducted with caution and only in smooth air. Maximum speed for all operations. FIGURE 2-2 AIRSPEED INDICATOR MARKINGS AIRPMNE FLIGHT MANUAL 2 - 4 FAA APPROVED SUPPLEMENT ISSUED 11-91 MOOMEV Wi'bt4 3201 SUPPLEMENT SECTEON H I MODEL,. M20J 2900 POUND GROSS WEIGI-11. C..!Biki'i'A'TiONS Maximum Weight (takeoff and landing) . . . . . . . Maximum Weight in Baggage Compartment . . . . . . . 2900 Ib. (1315 Kg.) . 420 Ib. (54.4 Kg.) @ use. Sta. 95.5 Wlaximirm Weight in Hatrack . . . . 10 lb . . . . . . (4.5'4 ~ g . j@ iuse. Sta. 119.0 Maximum Weight in Cargo Area (Rear seats folded down) . . . . . 340 Ibs. . . . . (15'4.2 Kg) @ use. Sta. 70.7 $:EN I'ER QF GRAVI IY (GE:AR DCIWM) . . . . . Most Forward 41.0 IN. (Fuse. Sta. in IN )(TO4 cm) . . .l3.4% MAC 2250 Ib.(lO2l Kg.) Intermediate Forward . . , . 44 .8 IN. (Fuse. Sta. in IN.)(406 cm) . . . .l4.3% MAC 2470 lb. (4 120 Kg.) . . . . . Forward Gross 45.0 IN. (Fuse. Sta. in lN.)(114 cm) .20.1% MAC 2900 lb.(4315 Kg ) I!/ . . . . . . . . AR Gross . . . 50.1 IN. (Fuse. Sta. in lM.)(127 cm) .28.7% MAC 2900 lb.(1315 Kg.) I . . . . . . . . MAC (at Wing Sta. 93.83)(238 cm) . . . . . 59.40 IN.(150 cm) Datum (station zero) is 5 inches (12.7 cm) aft of the center line of the nose gear aRaching bolts, and 33 inches (84 cm) forward of the wing leading edge at wing sta- tion 59.25 (I50 cm). This airplane must be operated as a Normal Category airplane. Aerobatic maneuvers, including spins, are prohibited. . . . . . . . . . . . . . . . . . . . . IINARWINGIII . . . . . . . . . . . . . . . . . . . . Takeoff maneuvers, prolonged sideslips or steep descents when the selected fuel tank contains lass than 8 gallons (48.Qibs., 30.3 liters, 6.7 IMP. Gal.) of fuel have net been demonstrat& and may cause loss of power. - - - I NOTE I - - -. Up 10 400 foot tftititdde loss may occur during stalls at maximum weight. I Slow throttle movement required at airspeed above 165 KIAS. Above 165 KIAS, rapid throttle movement may result momentary propeller RPM overspeed. FAA APPROVED AIAPMNE FLIGI-11" MANUAL SLJPPLEMENT ISSUED 11-91 2 - 7 SECTION II AFM 3201 SUPPLEMENT MOONEY LIMITATIONS 2900 POUND GROSS WEIGHT MODEL M20J Maximum Positive Load Factor Flaps Up . . . . +3.8 g. Flaps Down (33 O) . . . . . . . . + 2.0 g. Maximum Negative Load Factor Flaps Up . . . . . . . . . . . -4.5 g. Flaps Down . . . . 0.0g. This is a Normal Category airplane approved for VFRIIFR day or night operations when equipped in accordance with FAR 91. DO NOT OPERATE IN KNOWN ICING CONDITIONS. TAKEOFFS WITH COWL FLAPS INOPERATIVE AWE PROHIBITED. Autopilot Limitations - See Section IX - - - I NOTE I - - - A reduced fuel quantity indicator is installed in each tank. The bsnom tip sf these indicators shows the 25 U.S. gallon (94.7 liters) (20.8 IMP. Gal.) usable fuel level in each tank. - - - I NOTE I - - - An optional visual fuel quantity gauge may be installed on top of each tank and is to be used as a reference for refueling the tanks only. Standard Tanks: (2) . 33.25 U.S. Gal. each . . (126 Liters)(27.7 Imp. Gal.) Total Fuel: . . . . . . . . 66.5 U.S. Gal . . . . . (252 L/ters)(55.4 Imp. Gal.) Usable Fuel: . . . . . . . 64.0 U.S. Gal . . . . (242 L/ters)(53.3 Imp. Gal.) Unusable Fuel: . . . . . . . 2.5 U.S. Gal . . . (9.5 iitersj(2.1 Imp. Gal.) Fuel ~ r a d e(anb Color): 1001130 . . . . minimum grade aviation fuel (green). 1OOLb . . . (low lead) aviation fuel (blue) with a lead . . . content limited to 2 cc per gallon is also approved. .. 42- N N W W N W W " CAUTION " W W W W W , . a N To reduce the possibility of ice formation within the aircraff or' engine fuel system it is pernliesable to add ISO-PROPYb a l c ~ h ~ i to the fuel supply in quantities NOT TO EXCEED 1% of the total fuel volume per tank. DO NOT add other additives to the fuel system due to potential deteriorating effects within the fuei system. AIRPMNE FLIGHT MANUAL FAA APPROVED 2 - 8 SUPPLEMENT ISSUED 4 1-94 MOOMEV wF&l 328 1 SUPPLEMEN S SEC9 ION IBI MODEL M2CB.I 2900 POUND WEIGHT EMP-RGkNCY 6'62QXk'EDURES . . . . . . . CBNDI'TION RECOMMENDED SPEED ENGINE FAILURE AFTER TAKEOFF . . . . . . . . . . Wing Flaps UP 85 KlAS . . . . . . . . . Wing Flaps DOWN 75 KlAS MAXIMUM GGDE SPEED MANEUVERING SPEED PRECAUTIONARY LANDING WITH ENGINE POWER Flaps DOWN . . . . . . EMERGENCY DESCENT (GEAR UP) . . . . . SmoothAir Turbulent Air 2900 1bll315 . . . . 2740 lbl1243 k g . . . 2470 lb/l120 kg . . . 2250 lb/1021 k g . . . EMERGENCY DESCENT (GEAR DOWN) . . . . . SmaothAir . 93 KlAS . 90 KIAS . 87 KlAS , 84 KlAS , . .118KIAS . .I 15 KlAS . . I 09 KlAS . . ,104 KlAS 75 KlAS 118 KlAS 115 KlAS 109 KlAS 104 MlAS 132 KlAS Turbulent Air - 2 x 0 lb11315 kg . . . . .I 18 KlAS . . . . . . . . 2740 lbI4 243 kg .I 15 KlAS . . . . . . . . 2470 lb/1120 kg .I09 KlAS . . . . . . . . 2250 lbl1021 k g . I 04 KlAS SUPPLEMENT ISSUED 11-91 SECTION Ill AFM 3201 SUPPLEMENT EMERGENCY PROCEDURES 2900 POUND WEIGHT MOONEY MODEL MVIPQJ WARNING LIGHT FAULT & REMEDY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - GEAR UNSAFE LDG. GR. in transit or not fully extended or retracted. Refer to "Failure of Landing Gear to Extend Electrically" or "Failure of Land- ing Gear to Retract". LEFT OR RIGHT FUEL PROP DE-ICE PITOT HEAT Hl/LO VAC (Flashing) Hl/LO VAC (Steady) 2 112 to 3 gallons of usable fuel remain in the respective tanks. Switch to fuller tank. Propeller De-Ice system has been turned ON. Pitot heat switch has been turned ON Suction is below 4.25 In. Hg. Suction is above 5.5 In. Hg. ---- I NOTE I ---- Attitude and directional gyros ere unreliable when VAC light is illuminated (steady sr flashing). Vacuum system should be checked and/or adjusted as soon as practicable. ALT. VOLTS (Flashing) bow voltage. Refer tol'Alternator Low Volt- age". ALT. VOLTS (Steady) Overvoltage or tripped Voltage Relay. Refer to "Alternator Failure". START POWER STBY VAC REMOTE RNAV LORAN CPLD Switch or relay has malfunctioned and starter is energized. Flight should be ter- minated as soon as practicable. Engine damage may result. Primary vacuum system has malfunctioned and stand-by vacuum system has been turned ON. &a- DME not slaved to WNAV. Loran is coupled to the NAV CBI or HSI SUPPLEMENT ISSUED 11-91 MOOPdEV AFM 330 % SUPPL-EPaENT 6E6: [ION i l l MODE!. M20J 2900 PQEBNB WEIGHT EME RGENCY ThTBOCI!DUWE9 ENGINE DRIVEN FUEL PUMP FAILk%C;BE An engine driven fuel pump failure is probable when the engine will only operate with the boost pump on. Operation of the engine with a fail& engine driven fuel pump and %heBOOST ON will require smooth operation of the engine controls and correspond- ing mixture change when the throttle is repositioned or the engine speed is changed. When retarding throttle or reducing engine speed lean the mixture to prevent the en- ine from quitting from an overrich condition. Enrich the mixture when openin the 8rotlle or increasing engine speed to prevent engine stoppage from a lean concftion. 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 . . . . . . . . . . Boost Pump . . . . . . . . . Mixture . . . . . . . . . . CRUISE Position . OM : I ~ C R E A S E . . until engine starts and adjust for smooth engine operation LAND as soon as practicable. ENGINE FIRE-GROUND Mixture . . . . . . . . . IDLE CU'TOFF (Full AR Fuel Selector Valve . . . oFll MagnetoIStarter Switch . . . . . . . . . QFF Master Switch . . . . . OFF Fire . . . . EXTINGUISH i i t h Fibe ~ A i n ~ u i s h e r ENGINE FIRE-IN FLIGHT Fuel Selector Valve . . . . . . . QFF Throttle . . . . . . . . C L ~ S E ~ ~ u l lAR Mixture Contiol . . . . I D ~ ECUTOFF [Full Aft1 MagnetoIStarter Switch . . . . . OFF . . . . . Cabin Ventilation & Heating dontrols .CLOSED . . . . . (Controls Forward) . . . . . . . . . . Cowl Flaps .CLOSED banding Gear . . . . . . . . DOWN or UP, . . . depending on terrain Wing Flaps . . . . EXTEND . . . . . . . . . . as necessary I NOTE I - - - If fire is not extinguished, al%emptto increase aifllow over the engine by increasing glide spe& and open cowl flaps. Proceed with a POWER OFF landing as described on page 3-10. Do not aHempt en engine r e s t a ~ . ELECTRICAL FIRE- IN FLIGHT (Smoke in Cabin) Master Switch . . . . llllllllllllllllllill IIIWARNIMGIII OFF /1/1ll1/1/llllll/ll/ Stall warning is not available with master switch OFF. Gear warning is not available with master switch OFF. Cabin Ventilation . . . Heating Controls . . . Circuit Breakers . . . . . OPEN c i o s i ~(Control Forward) . . . . CHECK - - . to identify faulty circuit if possible. . . . . . . . . LAND as soon as practicable. SUPPLEMENT ISSUED 11-94 3 - 7 SECTION Ill AFM 3209 SUPPLEMENT MOONEY EMERGENCY PROCEDURES 290Q POUND WEIGHT MODEL M20d If electrical power is essential for the flight, attempt to identify and isolate the faul- ty circuit as follows: . . Master switch . . . .ON Select ESSENTIAL switdhes 6 N one at a time, and' a short time to elapse before activating an additional circuit. In the event an emergency descent from high altitude is required, rates of descent of ap roximately 2,000 feet per minute or greater can be ailairled with the aircraft in two dtfPerent conf~gurations. With the gear and flaps retracted and cowl flaps closed, an airspeed of 196 knots will be required for maximum rate of descent. With the gear extended, flaps retracted 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 traveled than a descent at 196 knots. ldditionally, a descent at 132 knots will provide a smoother ride, resulting in less pilot workload. Therefore: The following procedure should be used for an emergency descent: Power Airspeed Landina Gear Wing FTaps . . . . . . . . . . . . U P Cowl Flaps . . . . . . . . .CLOSED Power During Descent . . AS R$QUI~EDto Maintain . Cylinder Head Temperature 300' F (149' C) minimum MAXIMUM GLIDE DISTANCE - MODEL M2OJ 3 - 8 SUPPLEMENT ISSUED 4 1-94 MOQNEV AC:M 3201 SUPPREMtMT S f CT&QMIIV MODEL M20J 2900 PQUND GROSS WEBGB B I NBL%WiAL I~~IBCEDURF-S TITLE . . . . . . . . . . . . . . . . PAGE INTRODUCTION . . . . . . . . . . . . . . . . .4.2 . . . . . . . . . . . . . . . PREFLIGHT INSPECTION 4.3 . . . . . . . . . . . . . . BEFORE STARTING CHECK 4.5 STARTING ENGINE . . . . . . . . . . . . . . . . .4.6 . . . . . . . . . . . . . FLOODED ENGINE STARTING 4.7 . . . . . . . . . . . . . . WARM ENGINE STARTING 4.7 BEFORE TAXI . . . . . . . . . . . . . . . . .4.8 TAXI . . . . . . . . . . . . . . . . . 4.8 BEFORE TAKEOFF . . . . . . . . . . . . . . . . . 4.8 TAKEOFF PROCEDURES . . . . . . . . . . . . . . . 4.8 TAKEOFF . . . . . . . . . . . . . . . . 4-9 CLIMB . . . . . . . . . CLIMB (NORMAL) . . . . . . . CLIMB (BESTRATE) . . . . . . CLIMB (BEST ANGLE) . . . . . CRUISE . . . . . . . . . . . . . . . . 4-10 DESCENT . . . . . . . . . . . . . . . . 4-11 . . . . . . . . . . . . . APPROACH FOR LANDING 4-41 GO AROUND (BALKED LANDING) . . . . . . . . . . . 4-12 TAXI AFTER LANDING . . . . . . . . . . . . . . . SHUTDOWN . . . . . . . . . . . . . . . . 4-13 . . . . . . . . . . . . . SECURING THE AIRCRAFT 4-13 SUPPLEMENT ISSUED 11-91 SECTION IV AFM 3201 SUPPLEMENT NORMAL PROCEDURES 2900 POUND GROSS WEIGHT MOONEY MODEL M20J This section describes the recommended procedures for the conduct of normal operations for the airplane. All of the requ~red(FAA regulations) procedures 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 (Supplements). SUPPLEMENT ISSUED 11-91 MOONEY AFM 320 1 SUPPLEMENT SE-:6T106\8 !'as' MODEL MSBJ 2900 POUND CROSS WEIGE.1T NORkeAB., IYWQCEBUWES Proper engine operation should be checked early in the takeoff roll. Ally siginificant indication of rough or sluggish engine response is reason to discontinue the takeoff. When takeoff must 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 (NORMAL) Electric Fuel Boost Pump . . . . . . . ON at star? of . . . . . . . . takeoff roll Power . . . . FULL~HROTTLEand 2700 RPM Engine Instruments . . . CHECK for proper indications LiRoff/Climb Speed . . . As specified in Section V (Normal Takeoff Distance) . . . . . . . banding dear . . . . . Retract in Climb . . . . . . Wing Flaps . . . Electric Fuel Boost $urnp . . . . . . . . after clearing obstacles . . . . . . . . .UP . . . . . OFF CHECK Pressure . . . . - - - I NOTE I --- If MMIMUM PERFORMANCE takeoffs ere desired, obtain full power before brake release and use lifisfflclimb speeds as specified in Section V (Maximarm PeP-formance Takeoff Distances). - - - I NOTE I --- Use noise abatement procedure as published by a i r ~ ~ @ or this man~ael. CLIMB (CRUISE) Throttle . . . 26" Hg Manifold Pressure Propeller . . . . . . . 2600 RYM Mixture . . . RICH (Lean for Smooth Operation . . . . . . . . . at high elevation) cowl Flaps . . . . FULL PEN or As Required Airspeed . . 90 to 100 KlAS Maintain these power settings and atiitude to at'least'3000'feet AGL or cruise altitude. Manifold pressure will drop with increasing altitude at any throttle setting. Power can be restored by gradually opening the throttle. CLIMB (BEST RATE)vy) Power . . FULLTHROTTLE and 2700 RPM Mixture . . . . . FULL RICH (Lean at higher altitudes for smooth operation) . . . . . . . Cowl Flaps . . . . FULL OPEN Airspeed . . . . . . . . 86 KlAS at sea level decreasing to 80 KIAS at 40,000 ft. . . . . . - - - - I NOTE I ---- See Section V, page 5-17 for rate of climb graph. SUPPLEMENT ISSUED 14 -94 SECTION 1V AFM 3201 SUPPLEMENT MOONEY NORMAL PROCEDURES 2900 POUND GROSS WEIGHT MODEL M20J Power . . , , . . FULLTHROTTLE and 2900 RPM Mixture . . , , , , . FULL RICH (Lean at higher . . . . altitude for smooth operation) Cowl Flaps . . . . . . FULL OPEN I Airspeed . . . . 66 KIAS a i sea ievel increasing . . approximately 1.0 KlAS for each . . . 5000 feet altitude Upon reachin cruise altitude, accelerate to cruise airspeed; retrim aircraft as necessary for ?eve1 flight. Set manifold 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 operating ranges. - - - I NOTE I- - - When cruising in conditions where the OAT is well above standard, it may be necessaq to OPEN cowl flaps sli htly in order to keep @ n g i ~ e temperatures in the green arc. When cowl ?laps are OPEN during crwse, the following effects an cruise speed will result: Cowl Flaps 114 open (I st Index) Approximate loss in TAS . . 2 K T A S Cowl Flaps 112 open (2nd Index) Approximate loss in PAS . . . 4 K T A S When cruising at 75 % power or less, lean the mixture aMer cruise power is 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 O C (100' F.) below peak. - - -- I NOTE I - - - Compared to Economy Cruise, Best Power mixture will result in an increase in fuel flow and a reduction in range. 2. Changes in altitude and power settings require the peak EGT to be rechecked and the mixture reset. B. Leaning without exhaust gas tem erature gauge,, EGT): L I. Siowlv move mixture controrlever aft from Ubb RICH" position toward "LEAN" position. 2. Continue leaning until slight loss of power is noted (loss of power may or may not be accompained 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 al- ways oerate the controls slowly and smoothly. 4 - 1 0 SUPPLEMENT ISSUED 11-91 AFM .320 1 SBJPPL.tME-.NT 46C i"iObd !V 7300 POUND GROSS WEICklT NQRhIAL 1>t40CEDUWES Mixture , . .LEAN to 14' C (25' F) rich of peak EGT as required . . . for smooth engine operation Power . . . . . AS REQUIRED to keep CHT . . in ~ i e e nkrc (300' F (149' C) min~rnurn) Avoid continuous operation between 150Q and 4950 RPM with power seHings below 18' manifold pressure. - - - - I NOTE I ---- Exercise caution with power seHings below 15" manifold pressure a$ airspeeds between 90 - 143 KlAS to preclude continuous operation in the 1500 - 1950 WPM restrid& range. " CAUTION " - N , - 4 W m N N Avoid Bong high speed descents at low manifold pressure as the engine can cool excessively. Cowl Flaps . . . . . . . F7ULLCL.OSED Ram Air . OFF before entering dusty air layers - - -- I NOTE I --- Plan descents to arrive at paHern altitude on downwind leg for maximum ttrel eRiciency and minimum aircraft noise. . . . . . . . InternalIExternal Lights As desired Seat Belts, Shoulder Harness . . . . FASTENED Landing Gear . .EXTEND below 140 KlAS . . . . . . . . (Gear down light - ON . . . check visual indicator on floor) . . . . . . . . . . Mixlure FULL RICH Propeller . . . HIGH RPM Fuel Boost Pump . . . . . . . . ON . . . . . . . . Fuel Selector FULLEST TANK Wing Flaps . . . . . . TAKEOFF ~ Q S I T ~ O N . . . . . FULL DOWN . . . . . . . AS DESIRED below 132 KlAS below I15 MlAS CAUTION " , . , W A , A , N N , " N To minimize control wheel forces during n~ane~avering,timely nose-up trimming is recommended to counteract nosa-down pilchirlg moment as power is reduced and/or flaps are extended. SUPPLEMENT ISSUED 11 91 4 - 1 1 SECTION 1M AFM 3201 SUPPLEMENT NORMAL PROCEDURES 2900 POUND GROSS WEIGHT Trim . . . . . . . . Parking Brake . . . . . . . MOONEY MODEL M20J As desired . OFF - - - I NOTE I --- The parking brake should be rechecked to preclude paPaially applied brakes during touchdown. W W , . , , . , W N M , " " CAUTION " W , " N W W W N , . , To minimize control wheel forces during maneuvering, timely nose-down trimming is recommend& to counteract nose-up pitching moment as power is reduced and/or flaps are retracted. Power . . . FULL THROTTLE1 2700 RPM . . . . . . . . . . Mixture FULL RICH Airspeed . . . . . . . 65 KlAS Wing Flaps . . . TAKEOFF position after climb established- Trim . . . . NOSE DOWN (to reduce control force) Airspeed . . . Accelerate to 76 KlAS Landing Gear . . . . . . RETRACT Wing Flaps . . . . RETRACT I Cowl Flaps . . . . . . . OPEN Airspeed . . Accelerate to 86 MIAS I MNBING (NORMAL) Approach for Landing Checklist . COMPLETED Approach Airspeed As specified in Section V (Mormai Landing Distances) Touchdown . . Main wheels first . . . . (aligned with runway) Landing Roll . . . .Lower nose wheel gently Brakes . . . Minimum required Fuel Boost Pump . . . OFF after landing --- I NOTE I - - - Landing information for reduced flap settings are not available. See Section V for Landing Distance Tables. - - - I NOTE ( - - - If maximum peflormence landings are desired, use above procedure except, reduce the approach airspeed to that specified in Section M (Maximum PerJormance Landing Distances). Apply maximum braking (without skidding tires) during rollout. SUPPLEMENT ISSUED 11-94 MOONf $B AFM 328 O SUPPLEMENT SkC110N IV MODEL M2OJ 2900 POUND GROSS WEIGHT kORMAL b~l48CEDUAES MPJDSNG (CROSSWIND) W W N N N N W " CAUTION " N N N N N N N Crosswind landings should be accomplished by using above procedures except maintain a proaeh speed a propriate for the wjnd condition$. AIIOWaircraft to crag until short final: then set up sidesrp (I?w wing into the wind). Accomplish touchdown in slight wing low sldesl~pand and aircraft slighed with runway. During landing roll, position flight controls to counteract crosswind. "CAUTION " N N N N N N N The landing gear may retract during landing roll if landing gear switch is inadvertently placed in the UP position. Throttle . . . . . . . . . 1000 to 1200 RPM . . . . . . . . . . Flaps RETRACT Cowl Flaps . . . . . . . . FULL OPEN Trim . . . . . RESETto Takeoff Radios . . . . . . . . As required Lighting . . . As required Parking brake' . . . . . . . SET Throttle , , . , , . 1000 to 4200 R P ~ (until cylinder . head temperature starts to dro Radio Master . . . . . . . . Internal/External Ligtits OFJ . . OFF MagnetolStarter Switch . , , . , . GroundingCheck Mixture , , , . . , . . IDLE CUTOFF ~ a ~ n e t o l ~ t a r t e ; Switch , , . . OFF when propeller stops Alternator Field Switch . . . . . . OFF . . . . . . . . . . Master Switch OFF Oxygen System (if equipped) . . . . . . OFF MagnetolStarter Master Switch QFF/Key removed VERIFY OFF Radio Master . . . VERIFY OFF Electrical Switches . . . . VERIFY OFF Parking Brake . . . RELEASE and'install wheel chocks For extended parking.~onirolwheel . . . SECURED , . , . , . . with seal 'belts; cabin vents closed, , , . , . . tie down aircraft at wing and tail points. SldPPLEMENT ISSUED 4 1-91 4 - 1 3 SECTION IV AFM 32011 SUPPLEMENT NQRMAL PROCEDURES 2900 POUND GROSS WEIGHT M00NEY MODEL M20J SUPPLEMENT ISSUED 11 -91 M06NEY AFM 3201 SUPPLEMENT SECTION V MODEL M20J 2900 POUND GROSS WElGHT PERFORMANCE TITLE . . . . . . . . . . . . . . . . PAGE INTRODUCTION . . . . . . . . . . . . . . . . . 5.2 VARIABLES . . . . . . . . . . . . . . . . .5.2 OPERATIONAL PROCEDURES FOR MAXIMUM FUEL EFFECIENCY . 5.2 PERFORMANCE CONSIDERATIONS . . . . . . . . . . .5.3 RANGE ASSUMPTIONS . . . . . . . . . . . . .5.3 USE OF COWL FLAPS . . . . . . . . . . . . . 5.3 MAIN GEAR LOWER DOOR REMOVAL . . . . . . . . 5.4 TEMPERATURE CONVERSION . . . . . . . . . . . . .5.5 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 STATIC SYSTEM (GEAR UP, FLAPS UP) . . . . . . . . . . . . . . . . 5.9 ALTIMETER CORRECTION PRIMARY STATIC SYSTEM (GEAR DN, FLAPS DN) . . . . . . . . . . . . . . . 5-10 . . . ALTIMETER CORRECTION ALTERNATE STATIC SYSTEM 5-11 STALL SPEED VS ANGLE OF BANK . . . . . . . . . . 5-12 NORMAL TAKEOFF DISTANCE . . . . . . . . . . . . 5-13 NORMAL TAKEOFF DISTANCE .GRASS SURFACE . . . . . 5-14 CLIMB .TAKEOFF . . . . . . . . . . . . . . . 5-15 CLIMB .NORMAL . . . . . . . . . . . . . . . . 5-16 CLIMB .BALKED LANDING . . . . . . . . . . . . . 5-17 TIME DISTANCE & FUEL TO CLIMB . . . . . . . . . . 5-18 CRUISE & RANGE DATA CONDITION . . . . . . . . . . 5-20 CRUISE POWER SCHEDULES . . . . . . . . . . . . 5-21 SPEED POWER VS ALTITUDE . . . . . . . . . . . . 5-23 RANGE 75% POWER . . . . . . . . . RANGE 65% POWER . . . . . . . . . RANGE 55% POWER . . . . . . . . . RANGE 45% POWER . . . . . . . . . ENDURANCE 75% POWER . . . . . . . ENDURANCE 65% POWER . . . . . . . ENDURANCE 55% POWER . . . . . . . ENDURANCE 45% POWER . . . . . . . NORMAL LANDING DISTANCE . . . . . . . . . . . . 5-32 NORMAL LANDING DISTANCE .GRASS SURFACE . . . . . 5-33 SUPPLEMENT ISSUED 11-91 SECTION V PERFORMANCE AFM 3201 SUPPLEMENT 2900 POUND GROSS WEIGHT MOONE'9 MODEL M20J The purpose of this section is to present the owner or operator with information needed to facilitate planning of flight with resonable accuracy. The Performance Data and Charts presented are calculated based upon actual flight tests with airplane and engine in good condition and the engine power control system proper- ly adjusted. The flight test data has been corrected to International Standard Atmosphere condi- tions 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 techni- que, proficiency or environmental conditions. Mechanical or aerodynamic changes are not authorized because they can affect performance or flight characteristics of the airplane. The effect of such things as soft runways, sloped runways, winds aloft or airplane configuration changes must be evaluated by the pilot. However, the performance data on the charts can be duplicated, by following the stated proce- dures, in a properly maintained, standard M20J. Examples are given to show how each chart is used. The only charts with no ex- ample are those where such an example of use would be repetitive. To obtain effect of altiutde and OAT on aircraft performance: 1. Set altimeter to 29.92 in.Hg. and read "Pressure Altitude". 2.Using the OAT grid for the applicable chart, read corresponding effect of OAT on performance. CAUTION Be sure 1s return to local altimeter setting in calculating aircraff elevation above sea level. For maximuim fuel efficiency in the M20J, proper mixture leaning during cruise flight must be accomplished. The IO-360-A3B6D engine in the M20J bas been designed to attain maximum fuel efficiency, at desired cruise power, at 14 C rich of peak EGT. EGT is usually a more accurate indication of engine operation and fuel burn than indicated fuel flow. Therefore it is recommended that the mixture be set using EGT as the primary reference instead of setting to a particular fuel flow. The following procedure is recommended for setting cruise power and leaning to best economy at 75% power or less: 1. After leveling off, set the manifold pressure and RPM for the desired cruise power in accordance with the cruise power schedule on page 5-21. At this point, the mix- ture control 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 mixture causes the original manifold pressure setting to change, use the throttle to maintain that desired cruise manifold pessure and con- tinue leaning until best economy setting is obtained. RANGE ASSUMPTIONS Range data climb allowance is based on climbing at maximum continuous power to cruise altitude. 5 - 2 SUPPLEMENT ISSUED 11-94 MOONEY AFM 3201 SUPPLEMENT SECTION V MODEL M2OJ 2900 POUND GROSS WEIGHT PERFORMANCE Range reserves of 45 minutes at cruise power have been allowed on Range Data Qther conditions used in the Ranges shown are listed on each chart. USE OF COWL F U P S When in level cruise flight with outside air temperatures well above standard or when cruising at very high altitudes, it may be necessary to open the cowl flaps to keep engine temperatures in the normal operating range. Since the cowl flaps in the M20J are multi-position, numerous open settings are available to keep cylirider head and oil temperatures in the green arc under the most adverse conditions. 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- 114 open, (Indicator positioned at first index); (approximate loss in TAS) . . . . . . . . 2 I<ts Cowl flaps closed to cowl flap's indicator- 112 open, (Indicator positioned at second index); (approximate loss in TAS) . . . . . . 4 Kts An appropriate adjustment to the range data shown for the cowl flaps closed condi- tion 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 REIVIWAL. If numerous takeoffs and land~ngsare to be conducted on soft fields or In tall grass or ~f Ice and snow are llkely to be present on runway and taxiway surfaces for extended periods, it may be advantageous to remove the lower doors(extended position) Installed on each main landlng gear These doors can be damaged during operations In soft f~eldconditions, or a heavy accumulat~onof packed snow or ice inside the doors could prevent proper landing 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. 'Po be conservative, 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. -----"-- I NOTE I Engine cooling ha$ beer3 satisfactorily demonstrated for an abrtside air tsmperatbsre 01 23 C (40' F) above standard. This is not an operating limitation. (See Powerplant Limitations in Section I I ) SUPPLEMENT ISSUED 11-94 5 - 3 SECTION V PERFORMANCE WFM 3204 SUPPLEMENT 2900 POUND GROSS WEIGHT MOONEV MODEL M20J SECTION V AFM 3201 SUPPLEMENT MOQNEY PERFORMANCE 2900 POUND GROSS WEIGHT MODEL MPQJ MOOHEY AFM 3201 SUPPLEMENT SECTION V MOBEL M20J 2900 POUND GROSS WEBGbIT PERFQRMAMGE S 8 3 1 3 W - 3 3 N V L S I C l A A 0 3 X V L ~ E E s ~ 8 ~ o ~ o o - 0 0 m~~msmn~ng~g~~$~~Ho ,-. - E = p s g & - 0 0 0 m"., m , s E -W SUPPLEMENT ISSUED 11-91 SECTION V AFM 3204 SUPPLEMENT MOONEY PERFORMANCE 2900 POUND GROSS WEIGHT MODEL M 5 - 4 4 SUPPLEMENT ISSUED 11-94