SERVICE BULLETIN M20-248

FIGURE SB M20-248-2A Page 4 of 4 SB M20-248 DATE 3 - 20 - 90 FIGURE SB M20-248-3 MOONEY AIRCRAFT CORPORATION P.O. BOX 72 KERRVILLE, TEXAS 78029 - 0072 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR Mooney Aircraft Model WITH - INCREASED TAKEOFF WEIGHT MODIFICATIONS - MOONEY SERVICE BULLETIN M20-248 REG. NO. SERIAL NO. This Supplement must be attached to the M20M FAA Approved Pilot's Operating Hand - book and Airplane Flight Manual (POHIAFM), No. 3500, when the Increased Takeoff W i g h t modifications have been installed in accordance with Mooney Service Bulletin M20-248, dated 3-20-90 or subsequent revisions. The information contained herein supple - ments or supersedes the basic manual only in those areas listed by a vertical black mark in the margin. For limitations, procedures and performance information not contained in this supplement, consult the basic Airplane Flight Manual. FAA APPROVED: d Henry A. Armstrong, Manager Aircraft Certification Service FEDERAL AVIATION ADMlN ISTRATION Fort Worth , Texas. 76193-0150 Date: 3 - 16 - 90 Revision A 4 - 96 PAGE 1 of 4 MOONEY S. B. M20- 248 MOONEY AIRCRAFT CORPORATION AFM SUPPLEMENT M20M M O O N E Y A I R C R A F T C U R P O R A T I O N P, 0 , BOX 7 2 Kerrville, T e x a s 78029 - 0072 L O G OF R E V I S I O N S - - The revised portions o f a f f e c t e d pages a r e indicated by vertical black lines in t h e margin. Revisior Number A PAGE 2 o f 4 FAA APPROVED Revision Pages Title Page, Log of Revisions, ii thru iv, 1-5, 2- 3, 2-4, 2-8, 5-13, 8-7 6-6, 6-7 Description o f Revisions Added Revision A to pages. Revised Data Revised Graphs FAA Approved D a t e Y MOONEY AIRCRAFT CORPORATION MOONEY S.'B. M20 -248 M20M AFM SUPPLEMENT This supplement is to provide the operating procedures and performance data for the M20M aircraft, SIN 27- 0001 thru 27- 0052 when modified according to Mooney Service Bulletin M20- 248 ,dated 3 - 20 - 90 or subsequent revisions. The pages of AFM Supplement, SB M20-248, will supercede the basic pages of POHIAFM, No. 3500, Revision B or later revisions in the areas marked with a verti - cal 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 POHIAFM. ............................................................ iSECTlON I - GENERAL: .................................................................. The following supplemental pages are to be used when SB M20- 248 has been com - plied with: Page Number 1-5 The following supplemental pages are to be used when SB M20- 248 has been com - plied with: Page Numbers 2-2, 2 - 3, 2 - 4, 2- 8, 2 - 12 The following supplemental pages are to be used when SB M20- 248 has been com - plied with: Page Number 3-1, 3 -5, 3 -15, 3 - 16 The following supplemental pages are to be used when SB M20- 248 has been com - plied with: Page Numbers 4-4, 4-14, 4 - 18, 4-19 The following supplemental pages are to be used when SB M20- 248 has been com - plied with: Page Numbers 5 -13 thru 5-19, 5-21 thru 5-30 The following supplemental pages are to be used when SB M20- 248 has been com - plied with: Page Numbers 6 - 2, 6 - 6 thru 6 - 8 FAA APPROVED PAGE 3 of 4 MOONEY S. B. M20 - 248 MOONEY AIRCRAFT CORPORATION AFM SUPPLEMENT M20M ............................................................................................................................................ iSECTlON VII - AIRPLANE AND SYSTEMS DE S CRIPT ION : ............................................................................................................................................ The following supplemental pages are to be used when SB M20 -248 has been com - plied with: Page Number No pages changed. The following supplemental pages are to be used when SB M20 -248 has been com - plied with: Page Number 8- 7 The following supplemental pages are to be used when SB M20- 248 has been com - plied with: Page Numbers All Supplemental Pages for SB M20- 248 added to this Section. iSECTlON X - SAFETY & OPERATIONAL TIPS: ................................................................................................................ The following supplemental pages are to be used when SB M20- 248 has been com - plied with: Page Number No pages changed. NOTE: ALL PAGES LISTED UNDER SECTION HEADINGS ABOVE MUST BE INCLUDED IN THIS SUPPLEMENT AND INSERTED INTO THE POHIAFM OF ANY AIRCRAFT WHICH HAS MOONEY SERVICE BULLETIN M20 -248, DATED 3 - 20 - 90 OR SUBSEQUENT REVISIONS COMPLIED WITH. PAGE 4 of 4 FAA APPROVED MOONEY AIRPLANE FLIGHT MANUAL SUPPLEMENT SECTION I M20M GENERAL MAXIMUM CERTIFICATED WEIGHTS . . . . . . . . . . . Gross Weight 3368 Lbs. (1528 Kg) Maximum Landing &ight . . . . . . . 3200 Lbs. (1452 Kg) Baggage Area . . . . . . . . . . . 120 Lbs. (54.4 Kg) Rear Storage Area . . . . . . . . . . IOLbs(4.5Kg) Cargo (Rear Seats ~ o l d e ddown) . . . . . . . . 340 Lbs. (154.2 Kg) STANDARD AIRPLANE WEIGHTS Basic Empty Wight . . . . . . See Definition, Page 1-8 UsefulLoad . . . . . . . Varies with installed equipment. See SECTION for specific airplane weight (pg. 6- 6). CABIN AND ENTRY DIMENSIONS Cabin Wdth (Maximum) . . . . . . 43.5 In. (110.5 cm) Cabin Length (Maximum) . . . . . . . . 126 In. (315 cm) Cabin Height (Maximum) . . . . . . 44.5 In. (113 cm) Entry Wdth (Minimum) . . . . . . 29.0 In. (73.4 cm) Entry Height (Minimum) . . . . . . . 35.0 In. (88.9 cm) BAGGAGE SPACE AND ENTRY DIMENSIONS Compartment Wdth . . . . . . . . . . . . . . . . . . . . . . Compartment Length . . . . . . . . . . . Compartment Height . . . . . . . . . . Compartment Volume Cargo Area (with rear seat folded down) . . . . . . . . . . . . . . . . Entry Height (Minimum) Entry Wdth . . . . . . . . . . . . . Ground to Bottom of Sill . . . . . . . . . . . 24 In. (60.9 cm) . 43 In. (109.2 cm) . 35 In. (88.9 cm) 20.9 Cu. Ft. i.592 cubic meters) 38.6 Cu. Ft. (1.09 cubic meters) . 20.5 In. (52.1 cm) . 17.0 In. (43.2 cm) I 46.0 In. (116.8 cm) SPECIFIC LOADINGS WIng Loading - @ Maximum Gross Wight . . . . . . 18.3 Lbs./Sq. Ft. (89.5 Kg/sq. m) Power Loading - @ Maximum Gross Wight . . . . . . 11.85 Lbs./HP (5.38 Kg/HP) I 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 tail cone, below the horizontal stabilizer leading edge. The aircraft Serial Number and type certificate are shown. ISSUED 6 - 89 SB M20-248 3 - 90 REV. A 4 - 96 SECTION I GENERAL MOONEY MODEL M20M SYMBOLS, ABBREVIATIONS & TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY & SYMBOLS g Acceleration due to gravity. 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. Vf e Vle Vlo Vne Vno vs vso vx 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 position. MAXIMUM LANDING GEAR EXTENDED SPEED -The maximum speed at which an aircraft can be safely flown with the landing gear extended. MAXIMUM LANDING GEAR OPERATING SPEED - The maximum speed at which the landing gear can be safely extended or retracted. NEVER EXCEED SPEED or MACH NUMBER - The speed limit that may not be exceeded at any time. MAXIMUM STRUCTURAL CRUISING SPEED - The speed that should not be exceeded except in smooth air and then only with caution. STALLING SPEED - The minimum steadyflight speed at which the airplane is controllable. STALLING SPEED - The minimum steady flight speed at which the airplane is controllable in the landing configuration. BEST ANGLE-OF-CLIMB SPEED - The airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance. ISSUED 6 - 89 MOONEY MODEL M20M SECTION II LIMITATIONS TITLE . . . . . . . . . . . . . . . . PAGE INTRODUCTION . . . . . . . . . . . . . . . . .2.2 NOISE LIMITS . . . . . . . . . . . . . . . . .2.2 . . . . . . . . . . . . . . AIRSPEED LIMITATIONS '2-3 AIRSPEED INDICATOR MARKINGS . . . . . . . . . . . . 2.4 . . . . . . . . . . . . . POWER PLANT LIMITATIONS 2.5 . . . . . . . . . POWER PLANT INSTRUMENT MARKINGS 2.6 FUEL LIMITATIONS . . . . . . . . . . . . .2.7 WEIGHT LIMITS . . . . . . . . . . . . . . . . .2.8 CENTER OF GRAVITY (GEAR DOWN) . . . . . . .2.8 MANEUVER LIMITS . . . . . . . . . . . . . . . . .2.8 FLIGHT LOAD FACTOR LIMITS . . . . . . . . . .2.8 FLIGHT CREW . . . . . . . . . . . . . . . . .2.8 . . . . . . . . . . . . . . OPERATING LIMITATIONS 2.9 OXYGEN SYSTEM LIMITATIONS . . . . . 2.9 KINDS OF OPERATION LIMITS . . . . . . . . . . . . .2.9 KINDS OF OPERATION EQUIPMENT LIST . . . . . . . . 2-10 DECALS & PLACARDS . . . . . . . . . 2-12 CABIN INTERIOR . . . . . . . . . . 2-12 FUSELAGE INTERIOR . . . . . . . 2 -16 EXTERIOR . . . . . . . . . . . . 2-17 INFORMATIONAL . . . . . . . . . . . . . . 2 - 18 OPTIONAL . . . . . . . . . . 2-20 FAA APPROVED ISSUED 6 . 89 REV . A 8 - 8 9 AIRPLANE FLIGHT MANUAL 2 - 1 SECTION II AIRPLANE FLIGHT MANUAL SUPPLEMENT MOONEY LIMITATIONS MODEL M20M Section II includes the mandatory 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) 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 M20M. The certificated noise level for the Mooney M20M at 3368 Ibs. (1528 Kg.) maximum weight is 74.03 dB(A). No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or unacceptable for operation at, into, or out of, any airport. AIRPLANE FLIGHT MANUAL SB M20-248 3 - 90 2 - 2 FAA APPROVED ISSUED 6 - 89 MOONEY AIRPLANE FLIGHT MANUAL SUPPLEMENT SECTION II M20M LIMITATIONS I AIRSPEED LIMITATIONS I Airspeed limitations and their operational significance are shown in Figure 2-1. This cali- bration assumes zero instrument error. V 1 SPEED KCASIKIAS REMARKS Never Exceed 1951195 Do not exceed Speed this speed in any operation. VNo Maximum 1741174 Do not exceed Structural this speed ex- Cruising cept in smooth Speed air, and then only with caution. Maneuvering Speed at: Ibs. /Kg. 260011179 1111111 Do not make full 290011315 1171117 or abrupt control 320011452 1231123 movement 336811528 1261127 above this speed. Maximum Flap 1091110 Do not exceed Extended Speed this speed with flaps in full down position. Maximum Land- 1651165 Maximum speed ing Gear Ex- at which the air- tended craft can be Speed safely flown with the landing gear extended. Max. Speed for 1391140 Max. speed at Gear Extension which the land- ing gear can be safely extended. Max. Speed for 1041106 Maximum speed Gear Retraction at which the land- ing gear can be safely retracted. Maximum Pilot 1331132 * Do not exceed Wndow Open *Some AIC may this speed with Speed show lower pilot window speeds open. FIGURE 2-1 AIRSPEED LIMITATIONS FAA APPROVED SB M20-248 3 - 90 AIRPLANE FLIGHT MANUAL ISSUED 6 - 89 REV. A 4 - 96 2 - 3 SECTION II AIRPLANE FLIGHT MANUAL SUPPLEMENT MOONEY LIMITATIONS M20M Airspeed indicator markings, their color code and operational significance are shown in Figure 2-2. MARKING IAS VALUE or RANGE (KIAS) SIGNIFICANCE M i t e Arc (Flap Operating Range) Green Arc (Normal Opera- ting Range) Yellow Arc (Caution Range) Radial Red Line 59-110 KlAS Lower limit is maximum weight Vso in landing configuration. Upper limit is maximum speed permissable with flaps extended. 66-174 KlAS 174-195 KlAS 195 KlAS Lower limit is maximum weight Vs with flaps re- tracted. Upper limit is maximum struc - tural cruising speed. Operations must be conducted with caution and only in smooth air. Maximum speed for all operations. FIGURE 2- 2 AIRSPEED INDICATOR MARKINGS AIRPLANE FLIGHT MANUAL SB M20-248 3 - 90 2 - 4 REV. A 4 - 96 FAA APPROVED ISSUED 6 - 89 MOONEY MODEL M20M SECTION II LIMITATIONS / / / / / / / / / / / / / / / / / / I / / / ///WARNING/// / / / / I / / / / / / / / / / / / / / / / Takeoff maneuvers when the selected fuel tank contains less than 12 gallons (45.4 liters) of fuel have not been demonstrated. I NOTE I Each fuel quantity gauge is calibrated to read zero (RED LINE) only in coordinated level flight when the quantity of fuel can no longer be safely used. ----- ------ I NOTE I ---- --- -- -- An optional visual fuel quantity gauge is installed on top of each tank and is to be used as a reference for refueling tanks only. Standard Tanks (2) . 47.5 U.S. Gal. each (179.8 liters) Total Fuel . . 95 U.S. Ga1.(359.6 liters) Usable Fuel: . .89 U.S. Gal. (336.8 liters) Unusable Fuel: . 6 U.S. Gal. (22.7 liters) Fuel Grade (and color): 100LL (low lead) (blue) or 100 (green) is approved. N N N N N N N " CAUTION " N N N N N N N To reduce the possibility of ice formation within the aircraft or engine fuel system it is permissible to add ISO-PROPYL alcohol 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 fuel system. FAA APPROVED ISSUED 6 - 89 AIRPLANE FLIGHT MANUAL 2 - 7 SECTION II AIRPLANE FLIGHT MANUAL SUPPLEMENT MOONEY LIMITATIONS M20M I WEIGHT LIMITS~ Maximum W i g h t - Takeoff . . . . . . . 3368 Ib. (1528 Kg.) Maximum W i g h t - Landing . . . . . . . . 3200 Ib. (1452 Kg) Maximum W i g h t in Baggage Compartment . . . 120 Ib. (54.4 Kg.) & FU's. i a . 101 S(257.8 cm) Maximum W i g h t in Rear Storage Area . . . . . . 10 Ib. (4.54 Kg.) @ Fus. ~ t a .131.0(332.7 cm) Maximum W i g h t in Cargo Area (Rear seats folded down) . . 340 Ibs. (154.2 KG) @ Fus. Sta. 70.7(179.5 cm) Most Forward . Fus. Sta. 41.0 IN. (104.1 cm) @ 2430 LB. (1102 Kg) . . . . . . . . . . . . . 16.79% MAC lntermediaie Forward . . . . Fus. Sta. 44 IN.(I 11.7 cm) @ 333b0 Ib. (1497 Kg) . . . . . . . . 21.7% MAC ~ o k a r dGross . Fus. ~ta.'46.01~.'(116.8dm) @ 3368 lb (1528 Kg) . . . . . . . . . . . . . 24.98% MAC Aft Gross . Fus. Sta. 51.0 IN(129.5 cm) @ 3368 Ib. (1528 Kg) . . . . . . . . . . 33.18% MAC I MAC (at K n g &a. 94.85)(241 cm) . . . . . . . 61 .OO ln.(154.9 cm) Datum (station zero) is 13 inches (32.5 cm) aft of the center line of the nose gear trunion attachlpivot bolts. I MANEUVER LIMITS I This airplane must be operated as a Normal Category airplane. Aerobatic maneuvers, including spins, are prohibited. 1 NOTE 1 i Up to 400 foot altitude loss may occur during stalls at maximum weight. Maximum Positive Load Factor Flaps Up . . . . . . . . . . . . + 3 . 8 g . Flaps Down (33 Degrees) . . . . . . . . . + 2.0 g. Maximum Negative Load Factor Flaps Up . . . . . . . . . . . . . . . -1.5 g. Flaps Down . . . . . . . . . . . . . . . .0.0 g. Pilot . . . . . . . . . . . . . . . . One Maximum passenger seating configuration . . . . . . . . . Three AIRPLANE FLIGHT MANUAL SB M20-248 3 - 90 FAA APPROVED 2 - 8 REV. A 4 - 96 ISSUED 6 - 89 SECTION II LIMITATIONS MOONEY MODEL M20M KINDS OF OPERATION EQUIPMENT LIST (con't.) SYSTEM or COMPONENT (con't.) - . / VFR DAY * GYRO-HORIZON DIRECTIONAL GYRO . i TURN COORDINATOR or TURN & BANK LANDING LIGHT **** INSTRUMENTS LIGHTS (INTERNAL or GLARESHIELD) CLOCK (WITH SWEEP SECOND HAND or DIGITAL) COMMUNICATION SYSTEM . NAVIGATION SYSTEM (APPROPRIATE TO FACILITIES BEING USED) BATTERY VACUUM SYSTEMIINDICATOR FUEL BOOST PUMP PILOT'S OPERATING HANDBOOK & AIRPLANE FLIGHT MANUAL . PITOT, Heated **** OAT GAUGE **** VSI **** ALTERNATE STATIC SOURCE **** STAND-BY VACUUM SYSTEM **** * Equipment must be installed and operable for all operations. **** When required by the apropriate regulations. I FAA APPROVED REV. A 8 - 89 AIRPLANE FLIGHT MANUAL ISSUED 6 - 89 2 - 1 1 SECTION II M O O N E Y LIMITATIONS AIRPLANE FLIGHT MANUAL SUPPLEMENT MODEL M20M ................................................................. !DECALS AND PLACARDSi CABIN INTERIOR The following placards are relevent to proper operation of the airplane and must be installed inside the cabin at the locations specified. OPERATII.1G LIMITATIONS M E MARKINGS AND P L 4 X T S INSTNLED IN THlS H R P L W E CDNTAlN OPEPATINC L M T A l l M I S WHCH MUST BE C C A R I E D WITH W E N DPERATINC TWlS ARPLrK t 4 T K NORMAL CATEGORY. TX1S W E tS CERTlfED FOR DAY W D t I F M KP/FR OPEPATION WHEN THE REQUIRED EQUIPLENT IS NSTALLEQ A t 0 OPER4TlONAL. RIGHT l N f O KNOWN ICNG CONMTKX(S E PROHIBITED. hW S R 0 8 4 T I C MANEWERS. INCLUDINC S P W ARE PPPROVED. OTHER O P C W n N C LMTATKINS WHICH NUST BE COMPUED WITN WHEN OPER4llIG THlS U R W l C IN M I S C1.TEOORY ARE CWT.4INEO IN THE A I P P M E F L W T M A N W . W W E R l N C SPEED (3368 LBS.).127 KIAS; (2600 LBS.).I 11 K I A S . EMERGENCY MANUAL GEAR EXTEblSION 1. PULL UNDING GEM a R C W B R W E R . 2. PUT C O R SWITCH IN E 4 R W W N POSITION. 3. PUSH RELEASE T M FORWARD AND UFT UP RED HANDLE. 4. PULL T-WDLE SWGHT UP (12 TO m INCHESI. 5. ALLOW T - W D L E TO RETIRN TO DR(CIN.4L POSlTlOII 6. REPEAT U N l l L C t r R MMN LGHT COMES LW (12 TO 2 0 PULLS). F TOTAL E L E C T R W FAILUPE-SEE MECnaNlCPL IVDIC4TOR. CAlJTlON 1. T W OFF STROBE LlTES W E N TAYlNG NL!R OTHER ACFT OP W E N F U l N C IN FOC OR W RWOS. ST0 P O S M W UTE: MUST BE USED FOR AIL MM mwnoNs. 2. N CAK O f FEE T W OFF M M HEAT. 3. DO NOT SCREW M R t i E R COHTROCS CLOSER TnaN 1/8" FROM I*n FLCE ON LEFT SlDE PANEL BELOW PILOT'S SlDE WINDOW BATTERIES MUST BE INSTALLED CHECK LIST ON BATTERY ACCESS PANELS T A O F UPPER L/H INSTR. CONTROLS RUN-UP DOOR FUEL PROP WINDOW INSTRUMENTS WING FLAPS ALT AIR TRIM SEAT LATCH PARK BRAKE COWLFLAPS BELTIHARNESS MIXTURE CONDUCT RUDDERIELEV TRIM CHECK PRIOR TO FLIGHT, SEE PILOT'S OPERATING HANDBOOK. PANEL BELTIHARNESS GEAR MIXTURE WING FLAPS PROP BOOST PUMP I PARK BRAKE ON CONSOLE COMPART -MENT COVER AIRPLANE FLIGHT MANUAL 2 - 12 SB M20-248 3 - 90 START S T W CLEAR HnDE FAA APPROVED ISSUED 6 - 89 MOONEY AIRPLANE FLIGHT MANUAL SUPPLEMENT SECTION Ill MODEL M20M EMERGENCY PROCEDURES TITLE . . . . . . . . . . . . . . . . PAGE INTRODUCTION . . . . . . . . . . . . . . . . .3 3 AIRSPEEDS FOR EMERGENCY OPERATIONS . . . . . . . . 3.4 ANNUNCIATOR PANEL WARNING LIGHTS . . . . 3.6 ENGINE . . . . . . . . . . . . . . . . .3.7 . . . . . . . POWER LOSS-DURING TAKEOFF ROLL 3.7 . . . . POWER LOSS-AFTER LIFTOFF & DURING CLIMB 3.7 POWER LOSS-DURING FLIGHT . . . . . . . . . . . . (RESTART PROCEDURE) 3.7 POWER LOSS-PRIMARY ENGINE INDUCTION AIR SYSTEM BLOCKAGE . . . . . . . . . . .3.8 TURBOCHARGER FAILURE . . . . . . . . . 3-10 COMPLETE LOSS OF ENGINE POWER . . 3-10 . . . . . . . PARTIAL LOSS OF ENGINE POWER 3- 10 ENGINE POWER OVERBOOST . . 3-10 . . . . . . . . . . . . ENGINE ROUGHNESS 3- 11 COWL FLAPS FAILURE . FULL CLOSED POSITION . . 3-11 HIGHCYLINDERHEADTEMPERATURE . . . . . . 3-11 HIGH OIL TEMPERATURE . . . . . . . . . . . 3- 12 LOW OIL PRESSURE . . . . . . . . . 3- 12 LOW FUEL PRESSURE . . . . . . . . 3- 12 ENGINE DRIVEN FUELPUMP FAILURE . 3-12 FUEL VAPOR SUPPRESSION (FLUCTUATING FUEL FLOW) 3- 13 FIRES . . . . . . . . . . . 3- 13 . . . . ENGINE FIRE . DURING START ON GROUND 3- 13 ENGINE FIRE . IN FLIGHT . . . . . 3- 13 . . . . . . . . . ELECTRICAL FIRE . IN FLIGHT 3- 13 EMERGENCY DESCENT PROCEDURE . . . . 3- 14 GLIDE . . . . . . . . . . . . . . 3-15 FORCED LANDING EMERGENCY . . . . 3-15 GEAR RETRACTED OR EXTENDED . . . . 3-15 OVERWEIGHT LANDING PROCEDURE . . . 3- 16 SYSTEMSEMERGENCIES . . . . . . PROPELLER . . . . . . . . FUEL . . . . . . . . . ELECTRICAL . . . . . . . . . . . . . . . LANDING GEAR OXYGEN . . . . . . . . . ALTERNATE STATIC SOURCE . . ISSUED 6 . 89 SB M20-248 3 SECTION Ill EMERGENCY PROCEDURES MOONEY MODEL M20M . . . . . . . . . . . I . . . . . . . . . . . . . . . . UNLATCHED DOORS IN FLIGHT 3 - 18 CABIN 3 - 18 BAGGAGE . . . . . . . . . . 3 - 19 . . . . . . . . . . . . . . . . ICE PROTECTION 3 - 19 EMERGENCY EXIT OF AIRCRAFT . . . . . . . . 3 - 20 SPINS . . . . . . . . . . . . . . . . 3- 21 OTHER EMERGENCIES . . . . . . . . . . . . . . 3 - 21 REV. A 8 . 89 ISSUED 6 . 89 MOONEY AIRPLANE FLIGHT MANUAL SUPPLEMENT SECTION I l l MODEL M20M EMERGENCY PROCEDURES .............................................................................................................. !AIRSPEEDS FOR EMERGENCY OPERATIONS: ................................................................................................................ Engine Failure after Takeoff Wing Flaps UP . 85 KlAS Wing Flaps DOWN . . 80 KlAS Best Glide Speed 3368 1bl1528 kg . 93.5 KlAS 3200 lbl1452 kg . 89.0 KlAS 2900 lbl1315 kg . 84.5 KlAS 2600 lbl1179 kg . 80.0 KlAS Maneuvering Speed 3368 Ib/1528 kg . ,127 KlAS 3200 lb/1452 kg . ,123 KlAS 2900 Ib/ 1315 kg .I17 KlAS 2600 lb/1179 kg . ,111 KlAS Precautionary Landing with Engine Power - Flaps DOWN a 75 KlAS Precautionary Landing above 3200 Lbs . 80 KlAS Emergency Descent (Gear UP) Smooth Air . 195 KlAS Turbulent Air 3368 lbl1528 kg . . ,127 KlAS 3200 1b11452 kg . . ,123 KlAS 2900lb/1315kg . .I17 KlAS 2600 lbl1179 kg . . I 11 KlAS Emergency Descent (Gear DOWN) Smooth Air Turbulent Air 3368 lbl1528 kg . 3200 lb/1452 kg . 2900 lb/1315 kg . 26001b/1179kg . ISSUED 6 - 89 SB M20-248 3 - 90 . 165 KlAS . .I27 KlAS . ,123 KlAS .I17 KlAS . .I11 KlAS 3 - 5 SECTION Ill EMERGENCY PROCEDURES MOONEY MODEL M20M WARNING LIGHT FAULT & REMEDY GEAR UNSAFE RED light indicates landing gear is not in fully extendedlor retracted position. Refer to "Failure of landing gear to extend electri- cally" procedure on page 3-17 or "Failure of Landing Gear to Retract" procedure on page 3-18. LEFT or RIGHT FUEL RED light indicates 2 112 to 3 gallons(9.5 to 11.4 liters) of usable fuel remain in the respective tanks. Switch to fuller tank. FUEL PRESSURE PROP DE-ICE PITOT HEAT STD BY VAC LOW VOLTS HIILO VAC RED light indicates fuel pressure has dropped below 24 PSI. Refer to "LOW FUEL PRESSURE" procedures on Page 3- 12 BLUE light indicates power applied to De- Ice boots BLUE light indicates power is applied to heater. (On French AIC ONLY-RED light in - dicates power is NOT applied to heater.) AMBER light indicates stand by vacuum pump is clutched to the engine & providing vacuum to system. RED light indicates voltage has dropped below 26.0 volts. Refer to "Alternator Low Voltage" procedure on page 3-16. RED flashing light indicates suction is below 4.25 inches of mercury. RED steady light indicates suction is above 5.2 inches of mercury. I NOTE I - --------- When either a steady (HI) or flashing (LO) VAC light is illuminated, the information obtained from the attitude and directional gyros is unreliable. Vacuum system should be checked and/or adjusted as soon as practicable. REV. B 11 - 89 ISSUED 6 - 89 MOONEY AIRPLANE FLIGHT MANUAL SUPPLEMENT SECTION 1 1 1 MODEL M20M EMERGENCY PROCEDURES I Note I ---- " --- - Greater glide distances can be attained by moving the propeller control FULL AFT (LOW RPM). GROUND DISTANCE - NAUllCAL MILES MAXIMUM GLIDE DISTANCE MODEL M20M GEAR RETRACTED OR EXTENDED Emergency Locator Transmitter . Seat Belts and Shoulder Harnesses Cabin Door Fuel Selector Mixture ~ a ~ n e t o l ~ t a r t e r switch ' Flaps Gear . Approach Speed Master Switch ISSUED 6 - 89 SB M20-248 3 - 90 , ARMED .SECURE . UNLATCHED OFF : I D L E CU T OFF . OFF . Full DOWN DOWN -lf conditions permit . 80 KlAS : O FF, prior to landing 3 - 1 5 SECTION Ill AIRPLANE FLIGHT MANUAL SUPPLEMENT MOONEY EMERGENCY PROCEDURES MODEL M20M ............................................................................................. :OVERWEIGHT LANDING PROCEDURESi ................................................................................................... In the event it is necessary to land with a weight exceeding 3200 Lbs. (max. landing weight) the following procedure is recommended in addition to normal Approach for Landing procedures: Approach Airspeed . 80 KlAS Use flatter approach angle than normal with pdwer as n e c e s ~ a ; ~ until a smooth touchdown is assured. Expect landing distance over a 50 feet obstacle (Ref Section V) to increase at least 600 feet. Conduct Gear & Tire Servicing inspection per Section VIII. ............................... .................................. !SYSTEMS EMERGENCIES: .................................................................. PROPELLER PROPELLER OVERSPEED Throttle . RETARD Oil Pressure . CHECK Propeller : D ECR EA SE set if any cbntro~available Airspeed . .REDUCE Throttle : AS R E Q U I R E D to maintain RPM below 2575 RPM FUEL LOW FUEL FLOW Check mixture Fuel Selector . ENRICH .Switch TANKS If condition persists, use Boost Pump Switch if necessary and LANDING should be made as soon as PRACTICABLE. ELECTRICAL ALTERNATOR OVERVOLTAGE (Voltage warning light illuminated steady and Alternator Field circuit breaker popped o n affected alternator.) Alternator Field Circuit Breaker . RESET If circuit breaker will not reset, the following procedures are required: 1. Monitor buss voltage and the output load of the remaining alternator. 2. Reduce electrical load, if needed, to maintain a buss voltage of 28 VDC and to operate within the load capacity of the remaining alternator. 3. Continue flight on the remaining alternator and land, when practical, to correct the malfunction. ALTERNATOR OUTPUT LOW (Output low or zero on one alternator) Affected Alternator Field Switch . . OFF then ON If output does not increase to near the same as the other alternator: Affected Alternator Field Switch . . OFF Electrical Load . MONITOR 1. Monitor buss voltage and the output load of the remaining alternator. 2. Reduce electrical load, if needed, to maintain a buss voltage of 28 VDC and to operate within the load capacity of the remaining alternator. 3. Continue flight on the remaining alternator and land, when practical, to correct the malfunction. 3 - 1 6 SB M20-248 3 - 90 ISSUED 6 - 89 MOONEY MODEL M20M SECTION IV NORMAL PROCEDURES This section describes the recommended procedures for the conduct of normal operations for the airplane. All of the required (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 (Supplemental Data). ISSUED 6 - 89 SECTION IV AIRPLANE FLIGHT MANUAL SUPPLEMENT MOONEY NORMAL PROCEDURES MODEL M20M ......................................................................................... ;SPEEDS ................................. FOR((_ NORMAL OPERATION! ........................................................ Unless otherwise noted, the following speeds are based on a maximum weight of 1 3368 pounds and may be used for any lesser weight. However, to achieve the performance specified in Section V for takeoff distance and climb performance, the speed appropriate to the particular weight must be used. TAKEOFF: Normal Climb Out . 80-90 KlAS Short Field Takeoff, Speed At 50 Ft. . 75 KlAS ENROUTE CLIMB, GEAR and FLAPS UP: Best Rate of Climb Best Angle of Climb . LANDING APPROACH (3200 Ibs.): Normal Approach, Flaps 10 degrees . Normal Approach, Flaps 33 degrees . Short Field Approach, Flaps 33 degrees ,105 KlAS . 85 KlAS 80 KlAS . 75 KlAS . 70 KlAS BALKED LANDING (3200 Ibs.): Maximum Power, Flaps 10 degrees . 85 KlAS MAXIMUM RECOMMENDED TURBULENT AIR PENETRATION SPEED: 3368 Ibs.11528 Kgs ,127 KlAS 3200 lbs.11452 Kgs . ,123 KlAS 2900 lbs.11315 Kgs .I17 KlAS 2600 lbs.11179 Kgs . ,111 KlAS 2400 lbs.11089 Kgs . ,106 KlAS MAXIMUM DEMONSTRATED CROSSWIND VELOCITY Takeoff or Landing 13 Knots ' ( ~ h i s ' i sNOT a Limitation) (See CROSSWIND COMPONENT CHART, Section V) 4 - 4 SB M20-248 3 - 90 ISSUED 6 - 89 MOONEY MODEL M20M SECTION IV NORMAL PROCEDURES Wing Flaps . CHECK operation. SET AT TAKEOFF position (10 Degrees) I - Flight Controls . . CHECK free and correct movement Avionics and Auto Pilot . . CHECK - (Refer to Section IX) Seats, Seat Belts and Shoulder Harness . SECURED Cabin Door . CHECK SECURED Pilots Window .CLOSED InternalIExternal Lights . AS DESIRED Parking Brake . RELEASE Strobe Lights . ON TAKEOFF . .. . PROCEDURES! . ... ... ........ ... .......... N N N N N N N N CAUTION " N N N N N N N N Proper engine operation should be checked early in the takeoff roll. Any significant 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 propeller area instead of being pulled into it. TAKEOFF If the turbocharger and its controlling system are properly rigged, manifold pressure will increase to 35 to 38 in. Hg. when the throttle is full open. However, engine operation with oil temperature below 100' F will result in an overboost (manifold pressure above 38 in. Hg.). If an overboost occurs, retard throttle to lower manifold pressure below 38 in. Hg, and continue flight. As the oil warms above 10oO F, throttle can be moved to full throttle position and controller will maintain proper manifold pressure for maximum continuous power. Full throttle operation during hot weather conditions may result in manifold pressure over 38 in. Hg. If this occurs retard the throttle below 38 in. Hg. and continue flight. Power . .FULL THROTTLE (2575 RPM) Annunciator . CHECK (BLUE Boost Pump Light - ON) Engine Instruments . CHECK for proper indications Lift OffIClimb Speed . . . As specified in Section V . (Takeoff Distance) Landing gear . .RETRACT IN CLIMB after clearing obstacles. Wing flaps . .UP Fuel Pressure . 24 PSI (minimum) I NOTE I -- ---- --- If maximum performance takeoffs are desired obtain full power before brake release and lift off at 65 KIAS and climb at 75 KIAS. ISSUED 6 - 89 REV. A 8 - 89 SECTION IV AIRPLANE FLIGHT MANUAL SUPPLEMENT NORMAL PROCEDURES MOONEY MODEL M20M --- ----- - I NOTE I -------- If applicable,use noise abatement procedures as required. CLIMB (CRUISE CLIMB) Power 34 In. Hg.12400 RPM) Mixture RICH Cowl Flaps : F U L ~OPE N or A S R E Q U I R E D Rudder Trim . As Desired Airspeed ,120 KlAS -- ----- - I NOTE / --- ---- -- See Section V, for rate of climb graph. CLIMB (BEST RATE) Power . FULL THROTTLE 12575 RPM Mixture RICH Cowl Flaps 1 FULL O P EN Rudder Trim . As Desired Airspeed . ,105 KlAS CLIMB (BEST ANGLE) Power . FULL THROTTLE12575 RPM Mixture RICH cowl flaps . : FULLOPEN I Rudder Trim . As Desired Airspeed . 85 KlAS Airspeed Throttle . ACCELERATE to cruise airspeed SELECTED SETTING (Ref. C R UIS E P E R F O R M A N C E C H A R T S in Section V) As the throttle is reduced, the BOOST PUMP annunciator light will extinguish.' Verify fuel pressure remains in GREEN arc. -------- - I NOTE I -- ------ Prolonged climbs to high cruise altitudes during hot weather operations may result i n some fuel pressure fluctuations(accompanied with possible fuel pressure annunciation)when the throttle is reduced. If fluctuations occur, turn Boost Pump Switch ON until cooling has alleviated fluctuations. 14 SB M20-248 3 - 90 ISSUED 6 - 89 MOONEY MODEL M20M SECTION IV NORMAL PROCEDURES ----- - I NOTE I Avoid extended descents at manifold pressure setting below 15 In.Hg. as the engine can cool excessively and may not accelerate satisfactorily when power is reapplied. Additionally, leaning the mixture to peak TIT during descent will save fuel and will eliminate any engine roughness associated with an overly rich mixture setting. During descent engine MP will tend to increase as the aircraft loses altitude. Occasional power reductions with the throttle may be required to maintain the original descent manifold pressure setting. NORMAL - GEAR UP Seats, Seat Belts, Shoulder Harness . ADJUST AND SECURE Wing Flaps . UP Landing Gear . UP Throttle : A ~ V E 15 in.' Hg. ( k e e p ' c ~ ~ ' i n Green) Propeller . 2400 RPM Mixture . Peak TIT Cowl Flaps . CLOSED CHT . : M O NIT O R (2500 F minimum) Airspeed . AS D E S I R E D ( ~ ~ ~ KIAS max.j Rudder Trim . AS DESIRED ------ -- I NOTE I -------- Plan descents to arrive at pattern altitude on downwind leg for maximum fuel effeciency and minumum aircraft noise. N N N N N N N N " CAUTION " N N N N N N N N DO NOT fly in the YELLOW ARC speed range unless the air is smooth. NORMAL - GEAR DOWN Seats, Seat Belts, Shoulder Harness . ADJUST AND SECURE Airspeed . DECELERATE to 140 KlAS Landing Gear . DOWN Throttle : A B O V E '15 ln.' Hg. ( ~ e e pC H T in Green Arc ) Propeller . 2400 RPM Mixture . Peak TIT Cowl Flaps Closed Cylinder Head ~ e m ~ i r a t u i e ' : ~ o n i t d r(250 O F min) Airspeed . 165 KlAS or LESS. ISSUED 6 - 89 4 - 1 7 SECTION IV AIRPLANE FLIGHT MANUAL. SUPPLEMENT MOONEY NORMAL PROCEDURES MODEL M20M Dm"------" I NOTE 1 ----------- Using the landing gear as a descent aid will result in a steeper descent rate (greater altitude loss per horizontal distance traveled). ........,...,,.,,.,................................................. IAPPROACH FOR LANDING; " CAUTION "N N N N N I U N The airplane must be within the ailswabie weight and balance envelope for landing (REF. Section VI). It will require a minimum of one hour of flight before a permissable landing weight is attained when takeoffs are made at maximum gross weight. If a landing at a weight exceeding maximum landing weight (3200 Lbs)(1452 Kgs.) is required, see OVERWEIGHT LANDING PRQCEDLIRE, Section Ill. Sears, Seat Belts, Shouider Harness . ADJUST AND SECURE InternalIExternallights . AS DESIRED Landing gear DB'WNbelow 140 KlAS '(check ear own light d ~ - c h e c kvisual indicator) Boost Pump . ON Fuel Selector : FULLE'ST T AN K Wing flaps : A S D E SIR E D (FULL down below 110 KIAS) ElevatorTrim . AS DESIRED Rudder Trim . AS DESIRED " CAUTION " N N N N -2 CV N To minimize esntrsi wheel forces during maneuvering, timely nose - up trimming is recommended to counteract the nose down pitching moment as power is reduced andlor the flaps are extended Parking Brake . VERIFY OFF Power , FULL FORWARD12575 RPM) Mixture Verify FULL RICH Boost Pump : Verify ON(BLUE light on Annunciator) ' (F& Throttle automaticaily turns Boost Pump ON) Wing Flaps TAKEOFF POSITION (10') ' ( ~ f t e rPOSITIVE clin-ll, eslablisltecl) Trim . , NOSE DOWN to reduce forces N N N N N N N N " CAUTION " N N N N N N N N To minimize control wheel forces during maneuvering, timely nose - down trimming is recommended to counteract the nose up pitching moment as power is increased and/or the flaps are retracted. Airspeed 85 KlAS Landing Gear : R E T R A C T Wing Flaps , RETRACT Airspeed ,105 KlAS 4 - 1 8 SB M20-248 3 - 90 ISSUED 6 - 89 MOONEY AIRPLANE FLIGHT MANUAL SUPPLEMENT SECTION IV MODEL M20M NORMAL PROCEDURES Approach for Landing Checklist . Wing Flaps Landing Gear Approach Airspeed Touchdown Landing Roll Brakes m---m---",= 1 NOTE [ . COMPLETED . FULL DOWN . DOWN and LOCKED . As specified In Section V . (Landing Distance) . MAIN WHEELS FIRST LOWER nose wheel gently . MINIMUM required Landing information for reduced flap settings are not available. See Section V for Landing Distance tables. ---- ------ I NOTE I --- =-- ---- - If maximum performarsce landings are desired, use the above procedures except, reduce the approach airspeed to "1KIAS (flaps full down) and apply maximum braking (without skidding tires) during rollout. ] NOTE I ..-----*---- Crosswind landings should be accomplished by using the above procedures except maintain approach speed appropriate for the wind conditions. Allow aircraft to crab until the landing flare. Accomplish the touchdown in a slight wing low sideslip (low wing into the wind) and the aircraft aligned with the runway. During the landing roll, position the flight controls to counteract the crosswind. N N N N N N N N " CAUTION " N N N N N N N N The landing gear may retract during landing roll if landing gear switch is placed in the UP position. TAXI AFTER LANDING' ....................................................................................... ............... Throttle . ASREQUIRED Boost Pump . OFF Cowl Flaps . OPEN Wing Flaps RETRACT Elevator Trim : T AKE OFF SETTING Avionics/Radios . . AS REQUIRED InteriorlExterior Lights . AS DESIRED ISSUED 6 - 89 SB M20-248 3 - 90 4 - 1 9 SECTION IV NORMAL PROCEDURES MOONEY MODEL M20M N N N N N N N " CAUTION " N N N N N N N Operate the engine at idle (below 1000 RPM) for 5 minutes to allow the TURBOCHARGER t o COOL. Taxi time after landing may be considered as part of the 5 minutes. Parking brake . SET Throttle . 700-750RPM Radio Master Switch . . OFF InteriorIExterior Lights . OFF Pitot Heat . . OFF Mixture . IDLE CUT - OFF Alternator Field Switches (LIR) . OFF Master Switch . OFF MagnetoIStarter Switch . OFF MagnetoIStarter Switch . VERIFY OFF/ Key removed Master Switch . VERIFY OFF Radio Master Switch . . Verify OFF Rocker Switches . Verify OFF Interior Light Switches . VERIFY OFF Parking Brake . RELEASE - INSTALL WHEEL CHOCKS Extended parking . CONTROL WHEEL SECURED with seat belts, cabin vents closed; Cabin Windows and Doors . CLOSED AND LOCKED TIE DOWN AIRCRAFT at wing and tail points. ISSUED 6 - 89 S T A L L SPEED v s , A N G L E O F B A N K A S S O C I A T E D C O N D I T I O N S : W E I G H T 3000 L B S (1361 K G S > F O R W A R D C.G. L A N D I N G GEAR E X A M P L E : F L A P S D O W N P O W E R I D L E 10 0 NOTE: U P T O 400 F E E T A L T I T U D E L O S S MAY A N G L E O F B A N K 4 S 0 OCCUR D U R I N G S T A L L S A T MAXIMUM W E I G H T S T A L L S P E E D 72.5 K C A S t73.0 K I A S > G E A R AND 3368 L B S CIS28 K G S ) 3 0 0 0 L B S (1361 K G S > 2 7 0 0 L B S < I 2 2 5 KGS) T A K E 0F F D I3 T A NC E SO FT, - KIAS 3368 LBS (1528 KGS) 1) MAXIMUM DEMONSTRATED CROSSWIND I S 13 KNOTS, 3100 LBS (1406 KGS) 6 4 70 2) CONDITIONS OF HIGH HUMIDITY CAN RESULT I N AN 2700 LBS (1225 KGS) 5 9 74 INCREASE OF UP TO 10% TO THE TAKEOFF DISTANCE, - 1400 ASSOCIATED CONDITIONSI POWER FULL THROTTLE/2575 RPM LANDING GEAR DOWN UNTIL OBSTACLE CLEARED WING FLAPS 10 O COWL FLAPS FULL OPEN RUNWAY SURFACE PAVED, LEVEL DRY EXAMPLE1 OAT 204 C PRESSURE 10000 FT, ALTITUDE WEIGHT 2900 LBS (1315 KGS) HEADWIND 5 KTS COMPONENT GROUND ROLL 900 FT, (if74 M) TOTAL TAKEOFF 1950 FT. (594 M) DISTANCE (50 FT, OBSTACLE) - I I I I I SO(15.2 M) OUTSIDE AIR TEMPERATURE - QC WEIGHT - POUNDS WIND COMPONENT OBSTACLE HEIGHT DOWN RUNWAY - KTS FEET m1500 1400 1300 WEIGHT - KGS MOONEY AIRPLANE FLIGHT MANUAL SUPPLEMENT SECTION V MODEL M20M PERFORMANCE ISSUED 6 - 89 SB M20-248 3 - 90 5 - 15 SECTION V AIRPLANE FLIGHT MANUAL SUPPLEMENT MOONEY PERFORMANCE MODEL M20M 0 0 0 s g " : i g g z g ; F l i g z ! Z s ! 2 z 4 w m - 8 W T a ~ 3 J . ~ 5 - 1 6 SB M20-248 3 - 90 ISSUED 6 - 89 MOONEY AIRPLANE FLIGHT MANUAL SUPPLEMENT SECTION V MODEL M20M PERFORMANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .^.:.. :...-................................................... :RATE ................OF ......,..CLIMB ...................-... CRUlSEj .......,...,......., MOONEY AIRPLANE FLIGHT MANUAL SUPPLEMENT SECTION V MODEL M20M PERFORMANCE I ISSUED 6 - 89 1 SB M20- 248 3 - 90 5 - 1 9 M20M CRUISE POWER SETTINGS AND FUEL FLOWS STANDARD D A Y CONDITIONS 24"/2200 RPM PEAK TIT 9,8 10,7 11,3 11,7 12,O 12s NOTE1 1) PEAK TIT INDICATES PEAK TIT OR 1750' F TIT 2) BEST POWER (AT 3 4 In, Hg,/2400 RPM) I S 1650' F TIT 3) WHEN OPERATING ABOVE 22000 FEET, AND AT MANIFOLD PRESSURES ABOVE 3 2 In,Hg,, ONLY BEST POWER MIXTURE (1650' F TIT) OR RICHER I S PERMITTED, 4) CRUISE FUEL FLOWS DECREASE APPROXIMATELY ,5 GPH FOR EACH 20' C ABOVE STANDARD TEMPERATURE, 5) CRUISE FUEL FLOWS INCREASE APPROXIMATELY ,5 GPH FOR EACH 20' C BELOW STANDARD TEMPERATURE, 27"/2200 RPM PEAK TIT 11,4 12,3 12,8 13,1 13,3 13,3 30"/2200 RPM PEAK TIT 12,9 13,7 14,3 14,5 14,7 14,6 32"/2400 RPM PEAK TIT 15,3 16,O 16,4 16,5 16,6 166 ALTITUDE 0 5000 10000 15000 20000 25000 OAT " 15 5 - 5 -15 - 25 - 35 34"/2400 RPM BEST POWER 196 20s 20,4 20,6 20,6 20,5 PEAK TIT 16,3 17,O 17,4 17,5 176 --- SECTION V AIRPLANE FLIGHT MANUAL SUPPLEMENT MOONEY PERFORMANCE MODEL M20M ............................................................................................. /TIME-FUEL-DISTANCE ........................ ...... .. TO DESCEND! .......................................................... IME - FUEL - DISTANCE TO DESCENI - 150 KIAS DESCENT SPEED ASSOCIATED CONDITIONSt POWER1 2000 RPM/MAP AS REQ'D TO MAINTAIN 750 FPM RATE OF DESCENT LANDING GEAR1 UP FLAPS1 UP COWL FLAPS1 CLOSED MIXTURE! PEAK TIT <DO NOT EXCEED 1 7 5 0 ~ ~ TIT) EXAMPLE] INITIAL PRESSURE ALTt 18000 FINAL PRESSURE ALTI 4000 TIME TO DESCENDt 24.0-5.0=19 MINUTES FUEL TO DESCEND1 3.8-0,8=3.0 GALLONS <14.39-3.03=11.36 Li> DISTANCE TR DESCEND1 69.0-13.0=56.0 NAUTICAL MILES C127.79-24.08=103.71 Km) . 10 15 20 30 35 O 3 TIME-MINUTES I I I I I I I I I I I I DISTANCE - Nautical Mile DISTANCE - Kilometers 5 - 24 SB M20- 248 3 - 90 ISSUED 6 - 89 MOONEY AIRPLANE FLIGHT MANUAL SUPPLEMENT SECTION V MODEL M20M PERFORMANCE L A N 1 NG D 1ST A NC E - G R A SS SUR FA CE 3200 (1452) 2900 11315) 2600 t1175) NOTE1 1) MAXIMUM DEMONSTRATED CROSSWIND I S 13 KNOTS, OUTSIDE AIR TEMPERATURE - OC WEIGHT - POUNDS WIND COMPUNENT OBSTACLE HEIGHT I DOWN RUNWAY - KTS FEET 1400 1300 1200 WEIGHT - KGS -80 -60 -40 -20 0 20 40 60 1.8 2,O 2.2 2.4 2.6 2.8 3.0 3,2 3,4 30 32 34 36 38 40 42 44 46 48 50 TOTAL MISSION TIME - HOURS TOTAL FUEL USED - GALLONS OUTSIDE AIR TEMPERATURE - C I I I I I II 110 li0 150 l j 0 190 TUTAL FUEL USED - LITERS 190 210 230 :SO 270 2s TOTAL FUEL USED LITERS SECTION V AIRPLANE FLIGHT MANUAL SUPPLEMENT MOONEY PERFORMANCE MODEL M20M I 5 - 30 SB M20 - 248 3 - 90 ISSUED 6 MOONEY MODEL M20M TABLE OF CONTENTS SECTION VI WEIGHT AND BALANCE TITLE . . . . . . . . . . . . . . . . PAGE INTRODUCTION . . . . . . . . . . . . . . . . .6 - 2 AIRPLANE WEIGHING PROCEDURE . . . . . . . . . . .6 - 2 WEIGHT & BALANCE CHART . . . . . . . .6 - 4 OWNERS WEIGHT & BALANCE RECORD . . . . .6 - 5 PROBLEM FORM . . . . . . . . . .6 - 6 LOADING COMPUTATION GRAPH . . . . .6 - 6 CENTER OF GRAVITY MOMENT ENVELOPE . .6 - 7 CENTER OF GRAVITY LIMITS . . . . . . . .6 - 8 FIXED BALLAST . . . . . . . . . . . . . . . . .6 - 9 PILOTS LOADING GUIDE . . . . . . . . . . . . . . 6- 10 EQUIPMENT LIST . . . . . . . . . . . 6 - 1 1 NOTE: The empty weight, center of gravity, and equipment list for the airplane as delivered from Mooney Aircraft Corporation is contained in this section. The use of this section is valid for use with the airplane identified below when approved by Mooney Aircraft Corporation. MOONEY - M20M AIRCRAFT SERIAL NO. AIRCRAFT REGISTRATION NO. Mooney Aircraft Corporation - Approval Signature & Date ISSUED 6 - 89 SECTION VI AIRPLANE FLIGHT MANUAL SUPPLEMENT MOONEY WEIGHT AND BALANCE MODEL M20M This section describes the procedure for calculating loaded aircraft weight and mo - ment for various flight operations. In addition, procedures are provided for calculat- ing the empty weight and moment of the aircraft when the removal or addition of equipment results in changes to the empty weight and center of gravity. A com - prehensive list of all Mooney equipment available for this airplane is included in this section. Only those items checked (X) were installed at Mooney and are included in the empty weight- and-balance data. The aircraft owner and/or pilot, has the responsibility of properly loading the aircraft for safe flight. Data presented in this section will enable you to carry out this responsibility and insure that your airplane is loaded to operate within the prescribed weight and center- of - gravity limitations. At the time of delivery, Mooney Aircraft Corporation provides the empty weight and center of gravity data for the computation of individual loadings. (The empty weight and C.G. (gear extended) as delivered from the factory is tabulated on page 6-5 when this manual is supplied with the aircraft from the factory.) FAA regulations also require that any change in the original equipment affecting the empty weight and center of gravity be recorded in the Aircraft Log Book. A con - venient form for maintaining a permanent record of all such changes is provided on page 6-5. This form, if properly maintained, will enable you to determine the current weight - and-balance status of the airplane for load scheduling. The weight- and- balance data entered as your aircraft left the factory, plus the record you maintain on page 6 -5, is all of the data needed to compute loading schedules. The maximum certificated gross weight for the Textron-Lycoming powered M20M is 1 3368 lbs (1528 Kg) for Takeoff and 3200 pounds (1452 Kgs) for Landing. Maximum useful load is determined by subtracting the corrected aircraft empty weight from its maximum gross weight. The aircraft must be operated strictly within the limits of the Center- of- Gravity Moment Envelope shown on page 6 - 7. AIRPLANE WEIGHING PROCEDURE (A) LEVELING: Place a spirit level on the leveling screws above the tailcone left access door when leveling the aircraft longitudinally. Level the aircraft by increas- ing or decreasing air pressure in the nose wheel tire. (B) WEIGHING: To weigh the aircraft, select a level work area and: 1. Check for installation of all equipment as listed in the Weight & Balance Record Equipment List. 2. Top off both wing tanks with full fuel. Subtract usable fuel, 89.0 U.S. gals. (337 liters) @ 5.82 ib/gal(100LL)(.69 Kg/l) =518 Ibs. (235 Kgs.), from total weight as weighed. OPTIONAL METHOD - Ground aircraft and defuel tanks as follows: a. Disconnect fuel line at fuel system union located forward of the firewall on the lower left hand side. b. Connect a flexible line to output fitting that will reach fuel receptacle. c. Turn fuel selector valve to tank to be drained; remove filler cap from fuel filler port. 6 - 2 SB M20- 248 3 - 90 ISSUED 6 - 89 OWNERS WEIGHT AND BALANCE RECORD CENTER BELOW A L L WEIGHT CHANGE DATA FROM AIRCRAFT LUG BUOK) AIRPLANE MODEL - M20M SERIAL NU, FAA REG, NU, 0 z rn n CI) ' d E 0 I -4 IZo m Ez % 3 m z 53 !I 0 C) I --I 9 z urn m m 9 2 6 0 m - DATE ( M u l t , DESCRIPTION OF MODIFICATION BASIC EMPTY WEIGHT AS DELIVERED ( W t ) ( I n c l u d e s full oll - 10 Q t s . (9,s l l t e r s ) i n c h e s by 25,4 m o r mm) < M u l t , ~ n c h e s WEIGHT RUNNING EMPTY WEIGHT ADDED WT, (LBS) (Kg) by 2,54 CHANGE WT8 (LBS) (Kg) p o u n d s (+) ARM (INCHES) t c m ) / t m m ) f o r Cm) WT, CLBS) (Kg) <-) ARM (INCHES) (cm>/lmm) ( M u l t , MOMENT /1000 by ,4536 ARM (IN) t c m > / t m m ) f o r USEFUL LOAD K g ) SECTION VI AIRPLANE FLIGHT MANUAL SUPPLEMENT MOONEY WEIGHT AND BALANCE M20M CAUTION Cargo loaded in rear seat area, with seat backs folded down, should have center of gravity over fuselage station 70.7. L O A D M O M E N T / 1 0 0 0 - K g - c m ( m m > 5 10 15 20 25 30 35 M O M E N T / 1 0 0 0 (THOUSANDS O F I N C H - P D U N D S / 1 0 0 0 ) SB M20-248 3 - 90 REV A 4 - 96 9. Refer to Center of Grovity Moment Envelope, to determine whether your A/C looding is acceptable. CAUTION-DO NOT LAND A/C WHEN OVER 3200 LBS EXCEPT IN AN EMERGENCY SITUATION. 3 Obtoin the moment/1000 volue for each seot position (FWD, MID or AFT) from loading computation gro ph. STEP YOUR ISSUED 6 - 89 ITEM WEIGHT (Kg) Lbs PROBLEM FORM SAMPLE PROBLEM (~g-cr!~~~YbT-in /1000) /100C WEIGHT (Kg) Lbs (1009) 2225 (77.1) 170 (77'1) 170 (77") 170 (77.1 ) 170 (164.7)363 (45.4) 00 (1528) 3368 (76.2) 168 (1 452 3)200 PROBLEM MOMENTlb-in (Kg-cm /1000) / I 0 0 0 (1 14.6) 99.46 (7.64) 6.63 (6.66) 5.78 13.85 12.02 13.85 12.02 20,59 17.87 .70 10.15 (190.2) 165.0 (- 9.53) - 8.27 (180.6) 156.7 1. 2. 3. 5. 6' 7. 8. A/C Basic Empt Wt.(W )(from poge 6 - 5) Full Oily 10 Bts.(9.5 Li) Q1.8751bs Kg/Li)(Sta. -20.19)(-51.3 cm) ossumed FULL for all flights) Pilot Seot ( # I ) * Co - Pilot Seat (#2) * Left Rear Seat (#3) or Corgo Area Right Rear Seat (#4) or Corgo Area Fuel (Max. Usoble - 89.0 Go1/534 Lbs) (337 Li/242Kg) 8 Sto 49.23(125 cm) Boggoge (Mox. 120 Lbs(54.4 cm)OSto.101.5 (257.8 cm) Hat Rock (Mox. 10 Lbs(4.54 Kg)QSta. 131.0 (332.7 cm) Loaded A/C Weight(Tokeoff at Mow. Weight) A/C will have to burn off 168 Ibs. fuel before normal londing is accomplished. Required Fuel Burn - Off 28 Gols (105.9 Li) @ 6 L~S./GOI. MAXIMUM LANDING WEIGHT of A/C MOONEY AIRPLANE FLIGHT MANUAL SUPPLEMENT SECTION VI M20M WEIGHT AND BALANCE M20M - CENTER OF GRAVITY MOMENT ENVELOPE CENTER of GRAVITY MOMENT ENVELOPE A/C WEIGHT 800 900 1000 1100 1200 1300 140015001600 1700 18001903 2000 ARE ABOVE NORMAL APPROVED LANDING WEIGHT. FUEL MUST B t- I BURNED -OFF PRIOR TO NORMA SB M20- 248 3 - 90 ISSUED 6 - 89 REV. A 4 - 96 SECTION VI AIRPLANE FLIGHT MANUAL SUPPLEMENT MOONEY WEIGHT AND BALANCE MODEL M20M 1lqc($% M20M CENIER OF GRAVITY LIMIT'S 6 - 8 SB M20- 248 3 - 90 ISSUED 6 - 89 I I I I 105 110 115 120 1 25 130 A R C W CG LOCATION (l+JCM PFI OF MTUM(STA 0.0) MOONEY AIRPLANE FLIGHT MANUAL SUPPLEMENT SECTION Vlll M20M HANDLING, SERVICE AND MAINTENANCE 1 NOTE1 A Donaldson D-1400 Filter Cleaner is also recommended. Do not use solvents. f. Rinse filter element with a stream of clear water until rinse water is clear. g. Dry filter thoroughly. Do not use a light bulb or air heated above 180' F. for filter drying. h. Inspect for damage and ruptures by holding light bulb inside filter. If damage is evident, replace filter with a new one. GEAR & TIRE SERVICING The aircraft is equipped with 6- ply Type Ill standard -brand tires and tubes. Keep the main gear tires inflated at 42 PSI and the nose tire at 49 PSI for maximum service life. Proper inflation will minimize tire wear and impact damage. Visually inspect the tires at preflight for cracks and ruptures, and avoid taxi speeds that require heavy braking or fast turns. Keep the gear and exposed gear retraction system components free of mud and ice to avert retraction interference and binding. It is recommended that retractionlextension cycles (5 minimum) be done any time any tire is replaced to assure that no interference exists during the cycle. * * * * * * - CAUTION- * * * * - * After any landing, other than a smooth touchdown and rollout, when aircraft is above 3200 Lbs (1452 Kg), the aircraft should undergo the Gear System Operational Inspection as outlined in M20M Service and Maintenance Manual, No. 150, Chapter 32-30-01. The gear warning horn may be checked in flight by retarding the throttle with the gear up. The gear horn should sound with an intermittent note when throttle is positioned 114 to 318 inch from idle, while the gear is up. BATTERY SERVICE The two 24-volt, 10 ampere-hour electrical storage batteries are located in the tailcone, aft sf baggage compartment bulkhead, accessible through left and right side tailcone access panels. Check battery fluid level every 25 FLIGHT HOURS or each 30 DAYS whichever comes first. To service the batteries, remove access cover and battery cover; check terminals and connectors for corrosion. Add distilled water to each battery cell as necessary; keep the fluid at one -quarter inch over the separator tops. Check the fluid specific gravity for a reading of 1.265 to 1.275. A recharge is necessary when the specific gravity is 1.240 or lower. Start charging at four amperes and finish at two amperes; do not allow battery temperature to rise above 120' F. during recharging. Keep battery at full charge to prevent freezing in cold weather and to prolong service life. * * * * - * - CAUTION- - - - - - -Alternators and voltage regulators operate only as a one-polarity system. Be sure the polarity is correct when connecting a charger or booster battery. ISSUED 6 - 89 SB M20-248 3 - 90 REV. A 4 - 96 SECTION Vlll MOONEY HANDLING, SERVICE AND MAINTENANCE MODEL M20M If corrosion is present, flush the battery, shelf and mounting area with a solution of baking soda and water. Do not allow soda to enter the battery cells. Keep cable connections clean and tightly fastened, and keep overflow line free of obstruction. HYDRAULIC BRAKE RESERVOIR SYSTEM The brake system hydraulic reservoir is located on the tailcone bulkhead, forward of the avionics. To service, remove the left side tailcone access panel and check fluid level every 50 HOURS of operation. Fluid level should be no higher than two (2) inches(5 cm) below the filler cap. Use only hydraulic fluid (Red) conforming to specification MIL- H-5606. DO NOT FILL reservoir while parking brake is set. ENGINE PERFORMANCE CHECKS When the aircraft leaves the factory the TEXTRON-Lycoming TIO-540-AF1A engine has been properly tuned and will perform at optimum efficiency. To insure that the engine is continuing to perform properly certain maintenance action should be per - formed during the 100 HOUR or ANNUAL inspection or whenever it is suspected that engine performance is not correct. Refer to SERVICE AND MAINTENANCE MANUAL for specific maintenance actions to adjust engine if necessary. PROPELLER CARE The high stresses to which propeller blades are subjected makes their careful in - spection and maintenance vitally important. Check the blades for nicks, cracks, or indications of other damage before each flight. Nicks tend to cause high stress concentrations in the blades which, if ignored, may result in cracks. It is very impor - tant that all nicks and scratches be repaired prior to next flight. It is not unusual for the propeller blades to have some end play or fore and aft movement as a result of manufacturing tolerances in the parts. This has no adverse effect on propeller per - formance or operation. With the first turn, centrifugal force firmly seats the blades, rigidly and positively against the retention bearing in the propeller hub. Preflight inspection of the propeller blades should include, in addition to the forego - ing, an occasional wiping with an cloth soaked in kerosene. NEVER USE AN ALKALINE CLEANER ON THE BLADES. Your Mooney Service Center will answer any questions you may have concerning blade repair and inspection. EXTERIOR CARE As with any paint applied to a metal surface, an initial curing period is necessary for developing the desired qualities of durability and appearance. Therefore, DO NOT APPLY WAX TO THE NEW AIRCRAFT EXTERIOR UNTIL TWO OR THREE MONTHS AFTER DELIVERY. Wax substances will seal paint from the air and prevent curing. Wash the exterior to prevent dirt from working into the curing paint. Hold buffing to a minimum until curing is complete and there is no danger of disturbing the under- coat. 8 - 8 ISSUED 6 - 89