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

SYMBOLS, ABBREVIATIONS &TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY & SYMBOLS ENGINE POWER TERMINOLOGY 1-3 1-3 1-3 1-4 1-4 1-4 1-4 1-4 1·5 • . 1-5 1-5 1-5 1-5 1-5 Hi AIRPLANE PERFORMANCE & FLIGHT PLANNING TERMINOLOGY 1-6 ENGINE CONTROLS & INSTRUMENTS TERMINOLOGY 1-7 METEOROLOGICAL TERMINOLOGY 1-7 WEIGHT & BALANCE TERMINOLOGY 1-8 MEASUREMENT CONVERSION TABLES . . . . . . . . . . . 1-8 ISSUED 6 - 94 1 - 1 SECTION I GENERAL MOONEY M20R (1099,8 ,Cl'l) I . -36'-1 ·~· 1 FIGURE 1 - 1 THREE VIEW - M20R 1 -2 ISSU:OD 6-94 SECTION I GENERAL FUEL Minimum Fuel Grade (Color) Total capacity . . . . Usable MOONEY M20R 100 LL (Blue) or 100 Octane (Green~ . . . 9S U.S. Gal.. (359.6 Liters . . . 89.0 U.S . Gal . (336.9 Liters Oil Specification . . . . • . . . . . . . . . . . MH5-24() an d as Approved by TCM . (Reference Engine Maintenance & Operators ManuaO All Tem peratures 0 • • • • • . • . • • • • • • . • 1511\50 or 20111.60 Above 30:F (- 1 0 C) Amb i ent Air (S .L) . . . . . . • . . . . SAE 50 Be low 50 F (1 0 C) Ambient Air (S L ) . . . . . . • . . SAE 30, 10\1\GO I Total 01 Capacity . • • . . . . . . . . . . . 8 Qts. (T.57 liters) Oil Filter . . . . . . . . . . . . . . . . . . . Full Row Oil grades, specifications and changing recommendations are contained in·SEcllON VIII. LANDING GEAR TYPE: Bectrically operated, fully retractable tricycle gear with rubber shock discs. The main wheels have hydraulically operated disc brakes. The nose wheel is fully steerable 11° left to 13° right of center. Wleel Base Wleel Track lire Size: Nose . Main . . Trre Pressure Nose . Main . Minimum Turning Radius (No brakes applied) Right . . . . . . . . • . • Left . . . . . . . . • . . MAXIMUM CERTIACATED WEIGHTS Gross IM!ight . . . . . . Maxim~ landing Weight . . Baggage Area • • . • • . Rear storage Area . . . . . Cargo (Rear Seats Folded Down) STANDARD AIRPLANE WEIGHTS 79 9116 in .. (198.91 em) . 110 in. (279.4 em) 5.00 X 5 (6 ply) 6.00 X 6 (6 ply) 49PSI 42PSI 40ft. (12.0 m) 48ft. (14.4 m) 3368 Lbs. (1528 Kg!3200 Lbs . (1452 Kg 120 Lbs . (54.4 Kg . 10 Lbs . (4.5 Kg 340 Lbs . (154 .2 Kg Basic Bnpty Weight Useful Load . . . . . . . . . . . . . . . . See Page 1-8 . . . . . . . . . Varies with installed equipment. See SECTION VI for specific airplane weight (pg. 6-5). 1-4 REV.C 9-94 ISSUED 6-94 MUUNt:Y M20R .:;J~VIIVI' I GENERAL IINTRODUCTION I This OperatoJS Manual confonns to GAMA Specification No. 1 and includes both Manufac- tureJS material and FAA APPROVED material required to be furnished to the Pilot by the appficable Federal Aviation Regu lations . section IX contains supplemental data supplied by Mooney Aircraft Corporation. section I contains information of general interest to the pilot. It also contains definitions of the tenninology used in this Operators Manual. This Pilot's Operating Handbook is not designed as a substitute for adequate and compe- tent flight instruction, knowledge of current airworthiness di rectives , applicable federal air regulations or advisory circulars. It is not Intended to be a guide for basic flight instruction or a training manual and should not be used for operaUonal purposes unless kept in an up to date status. · · All limitations, procedures, safety practices, servicing and maintenance requirements pub- lished in this POHIAFM are considered mandatory for the Continued Airworthiness of this airplane in a condition equal to that of its original manufacture. IDESCRIPTIVE DATA I ENGINE Number of engines Engine Manufacturer Molle! .... Recommended lBO Type . • . . Number of cylinders Displacement . . Bore . . . . stroke. . . . Compression ratio Fuel System ~fk~ ....Fuel-Aviation Gasoline Accessories Magnetos . . !9nition Harness ~ark Plugs . OIICooler . . Alternator . starter . Ratings: Maximum Takeoff Sea Level BHPIRPM PROPELLER Number . Manufacturer . Model Number . Number of Blades . . . . Diameter (112 in. cutoff allowed) Type . . . . . . . Governor (McCauley) . . . Blade Angles @ 30.0 in. sta.: Low .... . . . High . . . . . . . . . . 1 Teledyne Continental Motors (TC~ I. -. . • . . 10-550-G(S) . . . • • . . 2000 Hours Reciprocating, air cooled, fuel injected . . . . 6, Horizontally opposed . . . . 550 Cu. ln . ~9014 cc~ . . . . . 5.25 ln. 13.3 em : : : : . . 4~5 ~n . ~ o: 5c~ I . Fuellnjection .... TCM 100 octane - 1OOLL Bendix - S6RN -25 . . . . Shielded/Braided AC 273 (or equivalent) ( 18 m/m) • . . . . TCM Full Row 28 Volt DC, 100 AMPS 24vottDC . 280/2500 . . . . . . . 1 . . . . . McCauterl 3A32C418/(G)-82NRC-9 . . . . . . . . . . 3 . . . . . . 73 in . (185 .4 em) . . . . . . Constant Speed Hydraulically controlled by engine oil 16.1 degrees+ 1-0.2 degrees 40 degrees + 1- 0.5 degrees • Refer to TCOS for engine/propeller configuration required . ISSUED 6-94 REVF 9-96 1-3 MOONEY M20R CABIN AND ENTRY DIMENSIONS Cabin Width (Maximum) Cabin length (Maximum) Cabin Helght (Maximum) Entry Widlh (Minimum) Entry Height (Minimum) BAGGAGE SPACE AND ENTRY DIMENSIONS Compartment Width Compartrr.ent Length Compartment Height Compartment Volume Cargo Area (with rear seat folded down) Entry Height (Minimum) Entry Wldlh . . Ground to Bottom of SUI SPECIFIC LOADINGS Wing Loading - @ Maximum Gross Weight Power Loading - @ Maximum Gross Weight IDENTIFICATION PLATE SECTION I GENERAL . 43 .51n. (110.5 em 126 ln. (315 em 44.51n. (113 em 29.0 ln. (73.4 em 35.0 ln. (88.9 em 24 ln. (60.9 em~ 43ln. (109.2 em 35 ln. (88.9 em 20.9 cu . ft. (.592 cu. m) . . 38 .6 cu. ft. (1 .09 cu. m) • 20.5 ln. (52.1 em~ . 17.0 ln. (43.2 em . 46.0 ln. (116.8 em 19.26lbs./sq. ft . (94 kg/sq. m) . 12.02 lbs./HP (5.46 kg/HP) All correspondence r*rding 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 tall cone, below the horizontal stabilizer leading edge. The aircraft Serial Number and type certif.cate are shown. I SYMBOLS, ABBREVIATIONS & TERMINOLOGY I GENERAL AIRSPEED TERMINOLOGY & SYMBOLS GS GROUND SPEED - Speed of an airplane relative to the ground. KCAS KIAS KNOTS CAUBRATED AIRSPEED -The indicated speed of an alrcraft,corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. KNOTS INDICATED AIRSPEED - The sp eed of an aircraft as shown on its airspeed Indicator. lAS values published in this handbook assume zero instrument error. KTAS KNOTS TRUE AIRSPEED - The airspeed of an airplane relative to undisturbed air which Is the KCAS corrected for altitude and "temperature. Va Vte ISSUED 6-94 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. 1 -5 SECTION I GENERAL MOONEY M20R GENERAL AIRSPEED TERMINOLOGY & SYMBOLS (con't.) Vio Vne Vno Vs Vso Vx Vy MAXIMUM LANDING GEAR OPERATING SPEED- The maximum speed at which the landing gear can be safely extended or retracted. NEVER EXCEED SPEED - 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. 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 CHT EGT MCP MP RPM BRAKE HORSEPOWER - Power developed by the engine. CYLINDER HEAD TEMPERATURE- Operating temperature of engine cylinder(s) being monitored by sensor unit. Expressed in°F . EXHAUST GAS TEMPERATURE- The exhaust gas temperature measured in the exhaust pipe manifold: Expressed in °F. MAXIMUM CONTINUOUS POWER - The maximum power for takeoff, normal, abnonnal or emergency operations. MANIFOLD PRESSURE - Pressure measured in the engine's induction system and expressed in inches of mercury (Hg). REVOLUTIONS PER MINUTE - Engine speed. AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demon- strated Crosswind Velocity g Service Ceiling 1 -6 The velocity of the crosswind component for which adequate control of the airplane during takeoff and landing test was actually demonstrated during certification. The value shown is not considered to be limiting. Acceleration due to gravity. The maximum altitude at which aircraft at gross weight has the capability of climbing at the rate of 100 ft/min. REV.G ISSUED 6-94 MOONEY M20R SECTION I GENERAL ENGINE CONTROLS & INSTRUMENTS TERMINOLOGY Propeller Control Throttle Control Mixture Control CHTGauge Tachometer Propeller Governor The control used to select engine speed. The control used to select engine power by controlling MP. Provides a mechanical linkage to the fuel injector mixture control to control the size of the fuel feed aperture, and therefore the air/fuel mixture. It is the primary method to shut the engine down. Cylinder head temperature indicator used to detennine that engine operating temperature is within manufacturers specifications. An instrument that indicates rotational speed of the engine. The speed· is shown as propeller revolutions per minute (RPM). The device that regulates RPM of the engine/propeller by increasing or decreasing the propeller pitch, through a pitch change mechanism in the propeller hub. METEOROLOGICAL TERMINOLOGY AGL Density Altitude Indicated Altitude ISA OAT Pressure Altitude Station Pressure Above ground level. Altitude as detennined by pressure altitude and existing ambient temperature. In standard atmosphere (ISA) density and pressure altitude are equal. For a given pressure altitude, the higher the the temperature, the higher the density altitude. The altitude actually read from an altimeter when, and only when barometric subscale (Kollsman window) has been set to Station Pressure. INTERNATIONAL STANDARD ATMOSPHERE assumes that (1) The air is a dry perfect gas; (2) The temperature at sea level is 15 degrees Celsius (59°F); (3) The pressure at sea level is 29 .92 inches Hg (1013.2 mb); (4) The temperature gradient from sea level to the altitude at which the temperature is -56.5°C (-69.7°F) is -0.00198°C (-0.003564°F) per root. OUTSIDE AIR TEMPERATURE- The free air static temperature, obtained either from inflight temperature indications or ground meteorological sources. It is expressed in °C. The indicated altitude when Kollsman window is set to 29.92 ln. Hg. or 1 013.2 MB. In this handbook, altimeter instrument errors are assumed to be zero. Actual atmospheric pressure at field elevation. WEIGHT AND BALANCE TERMINOLOGY Ann Basic Empty Weight Center of Gravity (C.G.) ISSUED 6-94 The horizontal distance from the reference datum to the center of gravity (C.G.) of an item. The actual weight of the airplane and includes all operating equipment (including optional equipment) that has a fixed location and is actually installed in the aircraft. It includes the weight of unusable fuel and full oil. The point at which an airplane would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. REV . G 1 - 7 SECTION I GENERAL MOONEY M20R WEIGHT AND BALANCE TERMINOLOGY (can't.) C.G. Arm e.G. in %MAC C.G. Umits MAC Maximum Weight Maximum Landing Weight Moment lions Reference Datum Station Tare Unusable Fuel Usable Fuel Useful Load The arm obtained by adding the airplane's individual moments and dividing the sum by the total weight. Center of Gravity expressed in percent of mean aerodynamic chord (MAC). The extreme center of gravity locations within which the airplane must be operated at a given weight. Mean Aerodynamic Chord. The maximum authorized weight of the aircraft and its contents as listed in the aircraft specifications. The maximum authorized weight of the aircraft and its contents when a normal landing is to be made. The product of the weight of an item multiplied by its arm; (Moment divided by a constant is used to simplify balance calcula- by reducing the number of digits.) An imaginary vertical plane from which all horizontal distances are are measured for balance purposes. A location along the airplane fuselage usually given in terms of distance from the reference datum. The weight of chocks, blocks, stands, etc. used when weighing an airplane, and is included in the scale readings. Tare is deducted from the scale reading to obtain the actual (net) airplane weight. Fuel remaining after a runout test has been completed in accordance with governmental regulations. Fuel available for aircraft engine combustion . The basic empty weight subtracted from the maximum weight of the aircraft. This load consists of the pilot, crew Qf applicable), useable fuel, passengers, and baggage. IMEASUREMENT CONVERSION TABLES I LENGTH U. S. Customary Unit 1 inch Metric Equi•1alents 2.54 centimeters 0.3048 meter 0.9144 meter 1 , 609 meters 1, 852 meters 1 foot 1 yard . . 1 mile (statute, land) 1 mile (nautical, international) U. S. Customary Unit 1 square inch 1 square foot 1 square yard 1 -8 AREA REV.G Metric Equivalents 6.4516 sq. centimeters 929 sq. centimeters 0.836 sq. meter ISSUED 6-94 MOONEY SECTION I M20R GENERAL VOLUME OR CAPACITY U. S. Customary Unit Metric Equivalents 1 cubic Inch 16.39 cubic centimeters 1 cubic foot . 0.028 cubic meter 1 cubic yard . 0. 765 cubic meter U.S. Customary Liquid Measure Metric Equivalents 1 fluid ounce 29.573 miiiHiters 1 pint 0.4731iter 1 quart 0.946 liter 1 gallon 3.7851iters U.S. Customary Dry Measure Metric Equivalents 1 pint 0.551 liter 1 quart 1.101 liters British Imperial .u.s. Metric Liquid and Dry Measure • Equivalents Equivalents 1 fluid ounce .0.961 u.s. 28.412 milliliters fluid ounce, 1.734 cubic Inches 1 pint . 1.032 u.s. 568.26 miiiUiters dry pints. 1.201 u.s. liquid pts., 34.678 cubic Inches 1 quart . 1.032 u.s. 1.1361iters dry quarts 1. 201 u.s. liquid qts., 69.354 cubic Inches 1 gallon .1.201 u.s. 4.54611ters 277.420 cubic inches WEIGHT U. S. Customary Unit (Avoirdupois) Metric Equivalents 1 grain .64.79891 milligrams 1dram 1.772 grams 1 ounce . 28.350 grams 1 pound 453.6 grams PRESSURE U.S. Customary Unit Metric Equivalents 1 PSIG 6.895 KPA 1 Inch Hg 1 Inch Hg 3.388KPA : 25.40 mm Hg ISSUED 6-94 1 -9 SECTION I GENERAL 1 pound/square foot 1 pound /sq. Inch 1 Pound/HP 1 -10 COMMON CONVERSIONS MOONEY M20R 0.488 kg/ meier square . .2.036 Inch t:Jg . . • 0.4538 kg{HP ISSUED 6-94 MOONEY M20R SECTION II LIMITATIONS I TABLE OF CONTENTS I TITLE .. . • INTRODUCTION NOISE LIMITS . AIRSPEED LIMITATIONS . AIRSPEED INDICATOR MARKINGS . POWER PLANT LIMITATIONS POWER PLANT INSTRUMENT MARKINGS . FUEL LIMITATIONS WEIGHT LIMITS CENTER OF GRAVITY (GEAR DOWN) MANEUVER LIMITS FLIGHT LOAD FACTOR LIMITS FLIGHT CREW . OPERATING LIMITATIONS OXYGEN SYSTEM LIMITATIONS. KINDS OF OPERATION LIMITS KINDS OF OPERATION EQUIPMENT LIST . DECALS & PLACARDS CABIN INTERIOR FUSELAGE INTF,RIOR . EXTERIOR FAA APPROVED ISSUED 6-94 REV. G PAGE 2-2 2-2 2-3 2-4 2-5 2-6 2-7 2-7 2-7 2-8 2-8 2-8 2-8 2-8 2-8 2-8 2-11 2-11 2-15 2-16 AIRPLANE FLIGHT MANUAL 2-1 SECTION II LIMITATIONS IINTRODUCTION I MOONEY M20R 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. JNOTEJ The airspeeds listed In the Airspeed Umltallons 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 nonmal 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 certlfi~ted under FAA Type Certificate No. 2A3 as a Mooney M20R. INOISE LIMITS I IThe certificated noise level for the Mooney M20R at 3368 lbs. (1528 Kg.) maximum weight Is 72.6 dB(A). No determination has been made by the Federal Aviation Administration that the nois e levels of this airplane are or should be acceptable or unacceptable for operation at, Into, or out of, any airport. AIRPLANE FLIGHT MANUAL 2-2 REV . B 8-94 FAA APPROVED ISSUED 6-94 MOONEY M20R IAIRSPEED LIMITATIONS I SECTION II LIMITATIONS Airspeed limitations and their operational significance are shown in Figure 2-1. This cali- bration assumes zero instrument error. VI SPEED KCAS/KIAS REMARKS VNE Never Exceed 196/h95 Do not exceed this Speed speed in any opera- lion. VNo Maximum 175/174 Do not exceed this structural speed except in Cruising smooth air, and then Speed only with caution. VA Maneuvering Speed at: lbs ./Kg. 223211012 1041103 Do not make full or 2430/1102 109/108 abrupt control move- 3300/1497 127/126 men! above this 3368/1528 128/127 speed. VFe MaximumAap 111/110 Do not exceed this Extended Speed speed with flaps in full down position. VLE Maximum Landing 166/165 Maximum speed at Gear Extended which the aircraft Speed can be safely flown with the landing gear extended . VLO Max. Speed for 141/140 Max. speed at which (EXl) Gear Extension the landing gear can be safely extended . VLO Max. Speed for 107/106 Maximum speed at (RET) Gear Retraction which the landing gear can be safely retracted. Maximum Pilot 133/132 Do not exceed this Wndow Open speed with pilot win- Speed dow open. =======================;================ FAA APPROVED ISSUED 6-94 FIGURE 2-1 AIRSPEED UMITATIONS REV . G AIRPLANE FLIGHT MANUAL 2-3 SECTION II LIMITATIONS MOONEY M20R IAIRSPEED INDICATOR MARKINGS! Airspeed indicator markings, their color code and operational significance are shown In Figure 2- 2. . ' MARKING lAS VALUE or RANGE (KIAS) SIGNIFICANCE ==============-= ==================·========,=-=== White Arc (Flap Operating Range) Green Arc (Normal Operating Range) Yellow Arc (Caution Range) Radial Red Line 59-110 KIAS 66-174 KIAS 174-195 KIAS 195 KIAS Lower limit is maximum weight Vso In landing con- figuration. Upper limit is maximum speed per- mlssable with naps ex- tended. Lower limit is maximum weight Vs with flaps re- tracted. Upper limit is maximum structural cruising speed. Operations must be con- ducted with caution and only in smooth air. Maximum speed for ali op- erations. =-=-======·===========:=======-===-====== ============= FIGURE 2-2 AIRSPEED INDICATOR MARKINGS AIRPLANE FLIGHT MANUAL 2-4 REV. G FAA APPROVED ISSUED 6-94 MOONEY M20R SECTION II LIMITATIONS I POWER PLANT UMITATIONSI Number of Engines Engine Manufacturer Teledyne Continental Motors (TCM) Engine Model Number . . . . . . I0-550-G(5) * I Engine Operating Limits for Takeoff and Continuous Operations: Maximum Continuous Power Maximum Continuous RPM . . Transient RPM Limit . . . . . Maximum Cylinder Head Temperature Maximum Oil Temperature . . Minimum Oil Temperature-Takeoff . Recm'ded Cruising Temperature . Oil Pressure · Normal Operating . Minimum {IDLE ONLY) 280 BHP . . . • 2500 RPM • . . • 2600 RPM • . 460°. ~ C237 . ~ c~ . . . 240 F (115° c . . . . 75° F (24° C 170°F-200°F (76°C-93°C . . 30-60 PSI 10 PSI Oil Specification . MHS.24( ), MHS.25() and TCM Approved oils Fuel Grade (Color) 1DOLL (Blue)"* or 100 octane (Green) •• Number of Propellers Propeller Manufacturer . . Propeller/Blade Model Number Number of Blades . . Propeller Diameter: McCauley Min . Max . McCauley- Propeller Blade Angles @ 30.0 ln. sta.: Low ...... . ... . High Propeller Operating Limits (McCauley) . . . . McCauley I3A32C418/(G)-82NRC-9 • 3 72.5 ln. (184.2 em) . 73 ln. (185.4 em) 16.1 Degrees+ 1-0.2 Degrees 40.U Degrees + 1- 0.5 Degrees 2500 RPM " Refer to TCDS for engine/propeller configuration required . •• 100LL fuel is calibrated at 5.82 lb/gal(.69 KQ/Iiler) 100 octane fuel is calibrated at 6.0 lb.gal. (. 72 Kg/tiler) FAA APPROVED ISSUED 6-94 REVF9-96 AIRPLANE FLIGHT MANUAL 2-5 SECTION II LIMITATIONS INSTRUMENT !POWER PLANT INSTRUMENT MARKINGS! RECLINE MINIMUM LIMIT GREEN ARC NORMAL OPERATING YELLOW ARC === · ==========----- -== · =~==== Tachometer C~llnder ead Temperature Oil Temperature 0 11 Pressure Exhaust Gas Temperature 600 RPM No Redline No Redline 10.0 PSI (IDLE ONLY) 2200-2500 RPM 250-420° F (121 - 215.S0 C} 170 -220° F (76 .6 - 104°C) 30-60 PSI 1400-1450°F (760·786°C) (BLUEARC = 420- 460°F (215.5-237.7°C} 100- 170°F. (37 .7-76.6°C} 220°-240° (104°- 115.5°C) 10-30PSI 60- 100 PSI recommended climb) MOONEY M20R RECLINE MAXIMUM LIMIT 2500 RPM 460° F (237.7°C) 240° F (115.5°C) 100 PSI 1650°F (899°C} = -===-= ·===-=--===-==='!:::=====-----·===-::=== NOTE Refer to TCM Engine Maintenance and Operators Manual Section on Engine Specifications and Operating Limits for recommended cruise power and temperature limitations. FIGURE 2 - 3 POWER PLANT INSTRUMENT MARKINGS AIRPLANE FLIGHT MANUAL 2-6 REV.G FAA APPROVED ISSUED 6-94 MOONEY M20R IFUEL LIMITATIONS! IllIIIIIII!IIIII/II //WARNING// !1!1/l!l!l!llll/11/ SECTION If LIMITATIONS Takeoff maneuvers ,when the selected fuel tank contains less than 12 gallons (45.4 liters) of fuel, have not been demonstrated. INOTE I Each fuel quantity gauge is calibrated to read zero (RED LINE) only in coordinated level flight when remaining quantity of fuel can no longer be safely used. INOTE 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. Gal. (359.6llters) Usable Fuel: Unusable Fuel: . 89 U.S. Gal. (336.8llters) , 6 U.S. Gal. (22.7 liters) Fuel Grade (and color): 100Ll (low lead) (blue) or 100 octane (green) is approved. .. CAUTION .. To reduce possibility of Ice formation within the aircraft or engine fuel system it Ia permissible to add ISO-PROPYL alcohol to the fuel supply in quantities NOT TO EXCEED 3% of total fuel volume per tank. DO NOT add other additives to fuel system due to potential deteriorating effects wllhln the fuel system. IWEIGHT LIMITS! Maximum Weight- Takeoff • 33681b . (1528 Kg .) Maximum Weight- Landing . . . . . . . 3200 lb. (1452 Kg) Maximum Weight In Baggage Compartment . . . . . . 120 lb. (54.4 Kg .)@ Fus. Sta . 101.5 (253.7 em) Maximum Weight In Rear Storage Area . . . . . . • 10 lb. (4 .54 Kg.) @ Fus . Sta . 131.0 (297.5 em) Maximum Weight in Cargo Area (Rear seats folded down) . . . 340 lbs. {154.2 KG) @ Fus. Sta . 70.7 (176 .8 em) ICENTER OF GRAVITY LIMITS (GEAR oowfm Most Forward . Fus . Sta. 41 .0 IN . (1 04.1 em) @ 2430 LB . {11 02 Kg) . . . . . . . . . . . 16.79% MAC Intermediate Forward Fus . Sta . 441N .(111 .7 em)@ 3300 lb . (1497 Ka) . . . . . . . 21 .7% MA'C Forward Gross Fus . Sta. 46.0 IN . (116.6 em) @ 3368 lb (1526 Kol . . . . . • • 24.98% MAt: Aft Gross Fus. Sta. 51 .0 IN(129.5 em) @ 3366 lb. (1528 Kg) . . . . . . . . . . . . 33 . 18% MAC MAC (at Wing Sta . 94.85)(241 em) . 61 .00 ln. Datum (station zero) is 13 inches (32 .5 em) aft of the center line of the nose gear trunlon attach/pivot bolts. FAA APPROVED AIRPLANE FLIGHT MANUAL ISSUED 6- 94 2 - 7 SECTION II LIMITATIONS I MANEUVER LIMITS I MOONEY M20R This airplane must be operated as a Normal Category airplane. Aerobatic maneuvers, includ- ing spins, are prohibited. I NOTE I Up to 500 foot altitude loss may occur during stalls at maximum weight. I FLIGHT LOAD FACTOR LIMITS! Maximum Positive Load Factor Flaps Up . . . Flaps Down (33 Degrees) Maximum Negative Load Factor Flaps Up . Flaps Down I FLIGHT CREWI Pilot. . . . . . Maximum passenger seating configuration . I OPERATING LIMITATIONS! +3.8 g. +2.0 g. -1.5 g. .0.0 g. One Three V'Jhen aircraft Is not equipped with an agproved oxygen system and night operations above 1 12,000 fl. are desired1 this airplane must 15e, (1) eqwpped with supplemental oxygen In accor- dance with FAR 23.1 <J41, 12) OP-erate in accoraance w•th FAR 91 .32 and (3) eqwpped with avi- onics in accordance with ~AR 91 or FAR 135. ALTERNATOR OPERATING LIMITATIONS IS 94 AMPS. !KINDS OF OPERATION LIMITS! This is a Normal Category airplane certified for VFRIIFR day or night operations when the re- quired equipment is installed and operational as specified in the KINDS OF OPERATION EQUIPMENT LIST and the applicable operating rules. Optional equipment installations may not be required to be operational. The.pilot must determine that the applicabie operating rules requirements for each kind of op- eration are met. · OPERATIONS IN KNOWN ICING CONDITIONS ARE PROHIBITED. Autopilot Limitations - See SECTION IX. I KINDS OF OPERATION EQUIPMENTLiSTI The following equipment was approved during Type Certification and must be installed and op- erable for each kind of operation as specified. I NOTE I The KINDS OF OPERATION EQUIPMENT list may not include all the equipment as required by applicable operating rules. SEE NEXT PAGE FOR LISTINGS. AIRPLANE FLIGHT MANUAL 2-8 REV.G FAA APPROVED ISSUED 6-94 MODEL M20R LIMITATIONS KINDS OF OPERATION EQUIPMENT LIST SYSTEM or COMPONENT AIRSPEED INDICATOR ALTIMETER , SENSITIVE MAGNETIC DIRECTION INDICATOR MANIFOLD PRESSURE GAUGE . TACHOMETER FUEL QUANTITY INDICATOR FUEL PRESSURE INDICATOR OIL PRESSURE INDICATOR OIL TEMPERATURE INDICATOR . CYLINDER HEAD TEMPERATURE INDICATOR . EXHAUST GAS TEMPERATURE INDICATOR AMMETER . ALTERNATOR LANDING GEAR POSITION INDICATOR SEAT BELT & SHOULDER HARNESS FOR EACH OCCUPANT ** . UXVGI:N MASK FOR EACH OCCUPANT •*" POSITION LIGHTS STROBE LIGHTS (ANTI -COLLISION) , I . l . ' VFR DAY* 2 1 ' VFR NIGHT IFR DAY i IFR NIGHT ' I 1 ! - I 2 I 2 2 I- ! ! - 'I 1 II 2 2 2 2 ' 1 3 3 3 3 * Equipment must be Installed and opera ble for all operatio ns. ** If ino pe rative for unoccupied seat(s), se at(s) must be placarded: " DO NO T OCCUPY " *** Only required when the operating rules requite use of oxy gen. FAA APPROVED ISSUED 6-94 REV. E 9·95 AiRPLANE FLIGHT MANUAL 2-9 :St:t;IIUN II LIMITATIONS MUUNI::Y MODEL M20R KINDS OF OPERATION EQUIPMENT LIST (con't.) SYSTEM or COMPONENT (can't.) GYRO-HORIZON DIRECTIONAL GYRO TURN COORDINATOR or TURN & BANK INDICATOR _ LANDING LIGHT **** . INSTRUMENT LIGHTS (INTERNAL or GLARESHIELD) CLOCK (WITH SWEEP SECOND HAND or DIGITAL) COMMUNICATION SYSTEM . NAVIGATION SYSTEM . (APPROPRIATE TO FACILITIES BEING USED) BATIERY VACUUM SYSTEM/INDICATOR FUEL BOOST PUMP . PILOT'S OPERATING HANDBOOK & AIRPLANE FLIGHT MANUAL PITOT, Heated **** OAT GAUGE **** . VSI ****. ALTERNATE STATIC SOURCE**** STAND-BY VACUUM SYSTEM **** VFR DAY* I 2 !i I ! I VFR NIGHT IFR DAY IFR NIGHT 1 I I i , I II I 2 I 2 I 2 i I I 1 i I 1 I I\ * **** Equipment must be installed and operable for all operations. When required by the appropriate regulations. AIRPLANE FLIGHT MANUAL 2-10 FAA APPROVED ISSUED 6-94 M20R LIMITATIONS I DECALS AND PLACARDS! CABIN INTERIOR The following placards are relevent to proper operation of the airplane and must be installed in- side the cabin at the locations specified. T A K E 0 F F L D G OPERATING LIMITATIONS ~~NID P~~Jl.~~~!!!IIN O?IJIII1ll<C 1\ll~£ IN 1M£ H~ CQEGOIIY, 1liiS AAJ't.Nt£ IS CfJfflR£11 l1lR DAY NtJ> NXlffl' YF11 OP£l!AllOH WliOI 1HE REQU!llm EQUI'~OO IS 1/lSTIUID . D OPUI/iiiOHAL FllCIHf INTO ~~~f:l~p~o':Wlil ~lllilf~ ON LEFT SIDE PANEL IN PILOT'S VISION YtlST II£ CCIIPIJtD WIIH W!EN OPO!AliiG 1HIS AIIU'W!< IN 1liiS ~£~~..~~':::i=~11111AS. EMERGENCY MANUAL GEAR EXTENSION ~: ~U.~D~IH~oa.HcmaJn'IIREAI<DI. 3. PUSH ft£1.£\Se UB ftiO!WI1I Ntl> ~FWIIWIOl£ ~: r/1~,/r~~sm,l'& .fJ 2 o~1 ~ 8. ~T~:.':ru=~ £&JOn: PUUS). IF CAUTION 1. TURN OfF S1ROOE U1ES WHEN TAXING N!:AR OlliER ACFT OR WHEN FLYING IN FOG OH IN CUlUDS. S1D POSITION U1ES MUST BE FOR All. NIGHT OPERATIONS. 2. IN CASE OF FIRE TURN OFF CABIN HE'AT. 3. DO NOT SCR£W \IERNIER OONTROIS CUlS£R THNt 1/lr FROM NUf FACE. -40t)t> CONTROLS FUEL INSTRUMENTS TRIM CHECK LIST RUN-UP PROP WING FLAPS SEAT LATCH BELT HARNESS DOOR WINDOW ALTAIR PARK BRAKE MIXTURE CONDUCT RUDDER AND ELE.V TRIM CHECK PRIOR TO FLIGHT SEE PILOT'S OPERATING HANDBOOK BELT/HARNESS GEAR MIXTURE FUEL WING FLAPS PROP PARK BRAKE A4027 ON CONSOLE I/N285M /I UPPER INSTRUMENT PANEL-PILOT SIDE MIKE i®>0 ~ PHONE $@) ON LOWER CONSOLE -o!037 UPPER LIH INSTRUMENT PANEL START STOP CLEAR MODE I A4004 A4012 FAA APPROVED ISSUED 6-94 REV.G AIRPLANE FLIGHT MANUAL 2- 11 SECTION II LIMITATIONS I F LAPM~rJ (±) CONSOLE ABOVE & BELOW SWITCH PILOT'S L/H PANEL , FWD OF ARM REST WARNING: DO NOT EXCEED 170 LBS (77.1 Kg) ON THIS SEAT BACK. SEE AIRCRAFT LOADING SCHEDULE DATA FOR BAGGAGE COMPARTMENT ALLOWABLE ON RADIO PANEL, ADJACENT TO ELT SWITCH (OPTIONAL) CAUTION ABSEIICE: OF Ell UGHT DURING FIRST 3 SECONDS OF TEST INDICATES POSSIIIl£ G-SWTTCH FAIWRE A4018 FLOORBOARD BETWEEN SEATS -4045 ABOVE EACH IVIUUI\It:Y M20R FWD END OF REAR SEAT BOTTOM STRUCTURE 0 0MI KE PHONE FUEL QTY . 44.5 GAL B~t~S~~~s- .....__u_s_E_A_B_L_E-J -213 BELOW INSTRUMENT PANEL-EACH SIDE FUEL Fl.OW loiEWORY ON E9 OFF II11CE ISOLATlON ON E9 OFF 0170 THRU 29-0199} INSTRUMENT/RADIO PANEL (VARIES W/ INSTALLED EQUIP .) DME WIY1 IND I!IIEROOM DME WIV 1 YOR NORioW. MJOIO ON E9 E9 E9 E9 NAV 2 LDRAN PRIVATE OFF NAV 2 (TYPICAL-PLACARDS WILL VARY WITH AIRCRAFT CONFIGURATION) AIRPLANE FLIGHT MANUAL 2 - 12 REV . G FAA APPROVED ISSUED 6-94 M20R PUSH GR SAFETY BY PASS GEAR UP 106 KIAS UPPER CTR INSTR. PANEL ABOVE INSIDE BAGGAGE DOOR HANDLE LIMIIAIIUN::> AUXILIARY EXIT DO NOT OPEN IN FUGHT TO OPEN 1. PUll. OFF COVER 2. PUll. CABI.£ EXTRACTlNG LOCK PIN J . ACTUATE HANDLE TO CLOSE 1. STORE HANDLE 2. INSERT LOCK PIN 3. INSTALL COVER 4. CLOSE AND LATCH DOOR USING OUTSIDE HANOI.£ 5. LOCK DOOR 4041 GEAR DOWN 140 KIAS GEAR EXTD 165 KIAS LWR INSTR PNL.,BELOW CONTROL WHEEL SHAFT PULL FOR ALT STATIC SOURCE A200 1 GA'\I'N ARB YElLijW AR8 BLUiQARC 0 250 • 420 420 - 490 1400 - 1450 30 • 60 PS I ABOVE ENGINE INSTRUMENT CLUSTER ON BEZEL (29-0170- 29-0199) DO NOT OPEN ABOVE 132 KIAS . Afl ltO AROUND EACH OXYGEN OUTLET ON OVERHEAD PANEL BELOW PILOT'S STORM WINDOW ON MAGNETIC COMPASS ABOVE EACH CONTROL ONLWR CONSOLE ON CONTROL KNOB INSTR. ALT AIR PULL ON 9 17 0 33 - 11 FAA APPROVED ISSUED 6-94 PANEL REV . G A4001 THROTTLE PUSH INCREASE A4002 PROP PUSH INCREASE A4003 MIXTURE PUSH RICH A4005 AIRPLANE FLIGHT MANUAL 2-13 SECTION II LIMITATIONS DO NOT EXCEED 10 LBS~.l5 Ko) IN '!H IS COIIPAATIIENT WARNING ', USE FOR STOWAGE Of UC SOI'I' NITTC LES ONLY • SEE A! RCIWT t.OACING EDULE DATA FOR IJA.GGAGE COI.!PAATIIENI' ALLOWASI.E -6021 TOP OF BAGGAGE DOOR JAMB DO NOT EXCEED 120 LBS WARNING: (54.4 Kg) IN 'THIS COMPARTMENT SEE AIRCRAFT LOADING SCHEDULE DATA FOR BAGGAGE COMPARTMENT ALLOWABLE -6020 INSTRUMENT PANEL SP EEO BRAKE £QUIPPED: FOR OPE RATI NG INSTRUCTIONS AND UMITATIONS SEE FAA APPROVED />FM SUPPLEMENT OR PILOT'S OPERATING HANDBOOK . (OPTIONAL) -4057 ON UPPER INSTRUMENT PANEL NXXXXX FLOORBOARD - BETWEEN SEATS BETWEEN SEATS - ON EMERGENCY GEAR RELEASE EXTENSION HANDLE LIGHT SWITCH -6082 14 VOLTS 3AM PS MAX. 5 A INTERM ITIENT PUSH TO RELEASE -6012 BAGGAGE DOOR FRAME RT. RADIO PNL. ADJACENT TO AUX . <--·-P VVR . PLUG FLOORBOARD - FWD OF CO-PILOT SEAT-·-·> AIRPLANE FLIGHT MANUAL 2-14 REV. G MUUNt:Y M20R BAGGAGE COMPART- MENT ON HAT RACK SHELF @ GEAR DOW N @ -4009 FAA APPROVED ISSUED 6 • 94 M20R LIMITATIONS FUSELAGE INTERIOR The following placards must be installed inside the fuselage at the locations specified. CAUTION CAUTION WINTERIZATION KIT INSTALLED THIS DOOR SHALL BE REMOVED AND STOWED WHE~6~~~ ~~~~7-~6~RES TEMPE~.fu~~:~~;w~&l, (-1°C) ON KIT SLIDING DOOR AT OIL COOLER. IF KIT INSTALLED MAINTAIN tLEVEL HERE -6011 28 VOLT S ONLY -6080 BACKSIDE OF AUX. PWR. RECEPTACLE DOOR USE AVIATORS OXYGEN ONLY SEE PILOT'S OPERATING HANDBOOK FOR FILLING PRESSURES (OPTIONAL) -4050 INSIDE ENGINE OIL FILLER DOOR REMOVE OIL COOLER DOOR. ON OIL FILLER DOOR IF KIT INSTALLED HYDRAULIC OIL RESERVOIR INSIDE OXYGEN FILLER DOOR BOTH BATIERIES MUSI 81:. INSTALLED FOR FLIGHT - 606( .---------~E ~N ~G ~IN~E--0-IL----------, 0 ~~~1l::y OIL INSTALLED IN THIS ENGINE IS: PANELS NEXT OIL CHANGE IS DUE AT HRS. (USE GREASE PENCIL) TACH TIME FAA APPROVED ISSUED 6-94 -6041 REV.G UH & RIH AIRPLANE FLIGHT MANUAL 2-15 SECTION II LIMITATIONS EXTERIOR MOONEY M20R The following placards must be Installed on the exterior of the aircraft at the locations specified. NO STEP -6000 ON INBOARD END OF FLAP, WING LEADING EDGES AND WING AHEAD OF FLAPS UNDERSIDE OF WING (2 PLCS) H0 IsT& AFT OF 1../H COWL FLAP (1 PLC) POINT -6002 DO NOT PUSH HORIZ. STAB. L./E RUDDER T/E (BOTH SIDES) --'6001 UNDER TAILCONE AFT OF WING T/E STATIC DRAIN I -60 24 PITOT DRAIN I - 6026 GASCOLATOR DRAIN -6030 AIRPLANE FLIGHT MANUAL 2-16 UNDER LEFT WING L./E NEAR FUSELAGE UNDER WING NEAR SUMP DRAINS FUEL DRAIN UNDER FUSELAGE AT . SIDE AFT OF NOSE WHEEL WELL AEVA 7-94 -60 28 FAA APPROVED ISSUED 6-94 MOONEY M20R SECTION II LIMITATIONS ON MAIN LOG GEAR TIRE PRESSURE 42 PSI (2.95 Kg/em•) DOOR -6042 TIRE PRESSURE 49 PSI (3.44Kg/cm 2 ) -6044 ON NOSE LANDING GEAR DOOR TOWING LIMITS I ON NOSE LANDING GEAR LEGASSY -6035 ON NOSE LANDING GEAR SPINDLE ASSY. WARNING DO NOT EXCEED TOWING LIMITS t-6036 MAGNETIC AZIMUTH TRANSMITTER OLWU~/BLIDHO'f;'I~OGISP~~f~ LOCATED INSIDE THIS INSPECTION COVER . USE ONLY NON-MAGNETIC SCREWS FOR COVER INSTALLATION. FUEL-100(GREEN) OR 1OOLL(BLUE) MIN OCT 44 .5 U.S. GAL USABLE 168 .5 LITERS USABLE FAA APPROVED ISSUED 6-94 -6059 -6050 ON BOTH FUEL FILLER CAPS REV A 7-94 AIRPLANE FLIGHT MANUAL 2-17 SECTION II LIMITATIONS AIRPLANE FLIGHT MANUAL 2-18 BLANK MOONEY M20R FAA APPROVED ISSUED 6-94 MOONEY M20R SECTION Ill EMERGENCY PROCEDURES fTABLE OF CONTENTS! TITlE PAGE INTRODUCTION . 3-3 AIRSPEEDS FOR EMERGENCY OPERATIONS . 3-4 ANNUNCIATOR PANEl WARNING LIGHTS . 3-5 ENGINE . . . . . • . . . . . . . 3.{) POWER LOSS - DURING TAKEOFF ROLL . 3.{) POWER LOSS - AFTER LIFTOFF . . . . . . 3.{) POWER LOSS -IN FLIGHT (RE-START PROCEDURES) . 3.{) POWER LOSS - PRIMARY ENGINE INDUCTION AIR SYSTEM BLOCKAGE . 3-7 ENGINE ROUGHNESS . . . . . . . 3-8 HIGH CYLINDER HEAD TEMPERATURE . 3-8 HIGH OIL TEMPERATURE . . . . . 3-8 LOW OIL PRESSURE . . . . . . . 3-8 LOW FUEL PRESSURE . . . . . . . 3-8 ENGINE DRIVEN FUEL PUMP FAILURE . . 3-8 FUEL VAPOR SUPPRESSION (FLUCTUATING FUEL PRESSURE) . 3-9 FIRES ENGINE FIRE - DURING START ON GROUND ENGINE FIRE - IN FLIGHT • . . . . . . ELECTRICAL FIRE - IN FLIGHT (SMOKE IN CABIN) EMERGENCY DESCENT PROCEDURE GLIDE FORCED LANDING EMERGENCY GEAR RETRACTED OR EXTENDED OVERWEIGHT LANDING PROCEDURES SYSTEMS EMERGENCIES PROPELLER FUEL .... ELECTRICAL LANDING GEAR VACUUM OXYGEN ALTERNATE STATIC SOURCE ISSUED 6-94 . 3-9 . 3-9 . 3-9 . 3-9 .3-10 .3-10 . 3-11 . 3-11 . 3-11 . 3-11 .3-11 . 3-11 . 3-11 .3-12 .3-13 .3-13 .3-13 3 - 1 ;:,t:viiUI\1111 EMERGENCY PROCEDURES I TABLE OF CONTENTS (con't) I TITLE . ... UNIJ\TCHED DOORS IN FLIGHT . ICING........ . EMERGENCY EXIT OF AIRCRAFT. SPINS ..... OTHER EMERGENCIES 3-2 IVIUUI\It:Y M20R PAGE 3-14 3-14 3-15 3-16 3-16 ISSUED 6-94 MOONEY M20R SECTION Ill EMERGENCY PROCEDURES IINTRODUCTIONl This section provides the recommended procedures to follow during adverse flight condi- tions. The Information Is presented to enable you to form, In advance, a definite plan of action for coping with the most probable emergency situations which could occur In the operation of your arrplane. As It Is not possible to have a procedure for all types of emergencies that may occur, It Is the pilot's responsibility to use sound judgement based ·On experience and knowledge of the aircraft to determine the best course of action . Therefore, It Is considered mandatorythatthe pilot read the entire manual, especially this section before night. When applicable, emergency procedures associated with optional equipment such as Autopilots are Included In SECTION IX. JNOTEJ All airspeeds in this section are Indicated {lAS) and assume zero instrument error unless stated otherwise. · ISSUED 6-94 3-3 SECTION Ill EMERGENCY PROCEDURES MOONEY M20R IAIRSPEEDS FOR EMERGENCY OPERATIONS I CONDITION 3-4 ENGINE FAILURE AFTER TAKEOFF Wing Aaps UP Wing Aaps DOWN BEST GUDE SPEED 3368 lb/1528 kg 3200 lb/1452 kg 2900 lb/1315 kg 2600 lb/1179 kg MANEUVERING SPEED 3368 lb/1528 kg 3300 lb/1497 kg 2430 lb/1102 kg 2232 lb/1012 kg PRECAUTIONARY LANDING WITH ENGINE POWER Aaps DOWN PRECAUTIONARY LANDING ABOVE 3200 LBS AapsDOWN EMERGENCY DESCENT (GEAR UP) Smooth Air Turbulent Air 3368 lb/1528 kg 3300 lb/1497 kg 2430 lb/1102 kg 22321b/1012 kg EMERGENCY DESCENT (GEAR DOWN) Smooth Air Turbulent Air 3368 lb/1528 kg 3300 lb/1497 kg 2430 lb/1102 kg 22321b/1012 kg •RECOMMENDED SPEED . 85 KIAS . 80 KIAS Q1.5 KIAS 89.0 KIAS 84.5 KIAS 80.0 KIAS 127 KIAS 126 KIAS 108 KIAS 103 KIAS . 75 KIAS . 80 KIAS 196 KIAS 127 KIAS 126 KIAS 108 KIAS 103 KIAS 165 KIAS 127 KIAS 126 KIAS 108KIAS 103 KIAS ISSUED 6-94 MOONEY M20R SECTION Ill EMERGENCY PROCEDURES IANNUNCIATOR PANEL WARNING LIGHTS I WARNING LIGHT GEAR UNSAFE LEFT or RIGHT FUEL SPEED BRAKE ALTAIR PROP DE-ICE PITOT HEAT HI/LO VAC (Flashing) HI/LO VAC (Steady) FAULT & REMEDY RED light indicates landing gear is not in fully extended/or retracted position. Refer to "FAILURE OF LANDING GEAR TO EXTEND ELECTRICALLY " procedure or "FAILURE OF LANDING GEAR TO RETRACT " procedure. RED light Indicates 2 1/2 to 3 gals. (9.5 to 11.4 liters) SIN 29-00 01 thru 29-01 69) ; [ 6 to 8 gals. (23 to 30.3 liters) S/N 29-0170 thru 29-01 99) 1of usable fuel remain in the respective tanks . Switch to full er lank. AMBER light indicates Speed Brakes are acti- vated. AMBER light indicates alternate induction air door is open. BLUE light indicates power applied to De-Ice boots BLUE light indicates power Is applied to heater. (Some Foreign NC - AMBER light indicates power is NOT applied to heater.) Suction is below 4.25 in . Hg . (RED) Turn Stand-by Vacuum pump - ON Suction is above 5.5 in. Hg . (RED) Turn Stand-by Vacuum pump - ON I NOTE I Attitude and Directional Gyros are unreliable when VAC light is Illuminated (steady or flashing). Vacuum system 1;hould be checked and/or adjusted as soon as practicable. ALTVOLTS (Flashing) ALT VOLTS (Steady) START POWER STBY VAC REMOTE RNAV BOOST PUMP ISSUED 6 - 94 RED light indicates alternator output low. Refer to "ALTERNATOR OUTPUT LOW". RED light indicates overvoltage and Alt. field. C/B tripped. Refer to "ALTERNATOR OVER- VOLTAGE ". RED light Indicates switch or relay is en- gaged an d starter Is energized. Fli ght should be termin ated as soon as practica ble. Engine damage may result. This Is normal indication during engine start. AMBER light indicates stand-by vacuum pump is ON . NOT USED AT THIS TIME BLUE light indicates power to auxiliary fuel boost pump. REV . G 3-5 SECTION Ill EMERGENCY PROCEDURES MOONEY M20R IENGINE I POWER LOSS - DURING TAKEOFF ROLL Throttle . Brakes . Fuel Se lector . Magneto/Starter Switch Master Switch POWER LOSS - AFTER LIFTOFF . . . . CLOSED AS REQUIRED TO STOP AIRCRAFT OFF OFF OFF Airspeed . . . . . . . . 85 KIAS (Flaps UP) . . . . . 80 KIAS (Flaps TAKEOFF/DOWN) KEEP THE AIRCRAFT UNDER CONTROL - then: Fuel Selector . Throttle . Magneto switch Mixture . . . IPropeller . . . LOW Boost Pump Switch . . If Engine Quits then: SELECT OTHER TANK FULL FORWARD Verify on BOTH FULL FORWARD . FULL FORWARD ON - to attempt re-start HIGH BOOST Pump (g uarded switch) . ON - to attempt re-start ILAND AS SOON AS PRACTICABLE; CORRECT MALFUNCTION PRIOR TO NEXT FUGHT. If engine does not re-start, proceed to FORCED LANDING EMERGENCY. IIIII/III/IllII/IllII ///WARNING/// I/IIIII/II IIIll /Ill II Engine may run rough due to overrich mixture. Lean mixture until engine operates smoothly. I NOTE I If high power Is required, mixture may require enrlchening. POWER LOSS - IN FLIGHT (RE-START PROCEDURES) IAirspeed . . . Fuel Selector. . . LOW Boost Pump Switch . Throttle Propeller . . . IMixture . . . Magneto/Starter Switch . LOW Boost Pump Switch . . HIGH BOOST Pump (guarded switch) . Alternate Air Door . . . . . . 85 KIAS minimum SELECT OTHER TANK (Verify fullest tank) ON - to attempt re-start FULL FORWARD . . FULL FORWARD AS REQUIRED to restore power . . . VERIFY on BOTH OFF if engine does not start immediately ON - to attempt re-start Manually Open If engine does not start after initial attempts: Mixture . . . . . . . . IDLE CUT-OFF (l11ilii:dly) . . . . . then advance slowly toward RICH until engine starts. If engine does not re-start after several attempts establish best glide speed (Refer to Maxi- mum Glide Distance Chart) and proceed to FORCED LANDING EMERGENCY. After engine re-start: Throttle . . . IPropeller . . . Mixture . . . HIGH BOOST Pump Switch I NOTE! ADJUST as required . . ADJUST as required RELEAN as required for power setting OFF If eng i ne fails when HIGH BOOST pump Is turned OFF, suspect engine driven fuel pump failure. Proceed to ENGINE DRIVEN FUEL PUMP FAILURE. 3-6 Rev. E 9-95 ISSUED 6-94 MOONEY M20R SECTION Ill EMERGENCY PROCEDURES LAND AS SOON AS PRACllCABLE; CORRECTMALFUNCllON PRIOR TO NEXT FLIGHT. - CAUnON- Should engine excessively cool during engine out, care should be exercised during re-start to avoid excessive oil pressure. Allow engine to wann up. II OPERA11NG lHE ENGINEATTOO HIGH AN RPM BEFORE REACHING MINIMUM OIL TEMPERAlURES MAY CAUSE LOSS OF OIL PRESSURE. I POWER LOSS • PRIM.ARY ENGINE IN.DUCnON AIR SYSTEM BLOCKAGE Blockage of the primary engine Induction a r system may be exeerienced as a result of Hying in cloud or heavy snow with cold outside air temperatures (0°C or below) . At these temperatures, very small water droplets or solid Ice crystals In the air maY. enter the primary engine Induction inlet in cowl opening and lravellnslde Inlet duot to the Induction air filter. Ice particles or water droplets may collect and freeze on the air filter causing partial or total blockage of the primary engine induction system. If primary induction air system blockage occurs, the alternate engine Induction air system will automallcally open, supplying engine with an alternate air source drawn from inside the cowling rather than through the air filter. The alternate air system can also be manually opened at any time by pulling the control labeled ALTERNATE AIR Automatic or manual activation of the aile mate Induction system Is displayed In the cockpit by the illumination of the ALTAIR light In the main annunciator panel. Wlen operating on the alternate air system , ava.ilable engine power will be less for a given propeller RPM compared to the primary Induction air system. This Is due to loss of ram effect and Induction of warmer inlet air. The following checklist should be used if a partial power loss due to primary induction air system blockage is experienced : Alternate Air . . . . . Verify OPEN (annunciator light ON) Manifold Pressure 1 • 2 inches less than ilonnal, due to warm induction air IN01EI The alternate air door should open automatically when primary induction system is restricted. If alternate air door has not opened (Annunciator light-OFF) it can be opened manually by pulling alternate air control. Throttle Propeller Mixture Flight INCREASE as desired . . . . . . . . . INCREASE as required . to maintain desired cruise power setting (Ref.SECllON \1) . . . . . . . . . RELEAN to desired EGI CON11NUE • request altitude with warmer air, if able . In the unlikely event that a total power loss, due to primary engine induction air blockage, is experienced, the following checklist should be used: Airspeed . . Alternate Air . . . LOW Boost Pump SWitch Throttle . Propeller • Mixture . . • Magneto/starter SWitch After engine re-start: lhroHie . Propeller . Mixture . . . . . . LOW Boost Pump SWitch ISSUED 6-94 REVE 9 • 95 BEST GLIDE SPEED Manually OPEN I. .. ON Full FORWARD . . . . FULL FORWARD AS REQUIRED to restore power Verify on BOTH ADJUST as required . . . . ADJUST as required RELEAN as required for power setting (~efe_r to .pow_er c~art~ • s~c~o~~ I 3-7 SECTION Ill EMERGENCY PROCEDURES MOONEY M20R If engine does not re-start after several attempts, maintain best glide speed & proceed to FORCED LANDING EMERGENCY. ENGINE ROUGHNESS Engine Instruments . . CHECK Fuel Selector . . . . . . OTHER TANK Mixture . . . . . . . . . . . READJUST for smooth operation Magneto/Starter Switch . . . . . . . . . Select R or L or BOTH If roughness disappears on single magneto, monitor power and continue on selected magneto. IIIIIII///III/III/I //WARNING// //IIIII/1/1/J/IIIII The engine may quit completely when one magneto is switched off if the other magneto Is faulty. If this happens, close throttle to idle an~ mixture to Idle cutoff before tumlng magnetos ON to prevent a severe backfire. When magnetos have been turned back ON, proceed to POWER LOSS - IN FLIGHT. Severe roughness may be sufficient to cause propeller separation. Do not conllnue to operate a rough engine unless there Is no other atternative. Throttle . . . . . . . . . . , . . . . . REDUCE . . . . . check for a throttle setting that may cause roughness to decrease. If severe engine roughness cannot be eliminated, LAND AS SOON AS PRACTICABLE. HIGH CYLINDER HEAD TEMPERATURE Mixture Airspeed Power . ENRICH As Required . . . . . . . . . . INCREASE As Required . REDUCE - if temperature cannot be maintained within limits HIGH OIL TEMPERATURE tNOTEt Prolonged high oil temperature Indications will usually be accompanied by a drop in oil pressure. If oil pressure remains normal, then a high temperature indication may be caused by a faulty gauge or thermocouple. Airspeed • INCREASE Power REDUCE PREPARE FOR POSSIBLE ENGINE FAILURE IF TEMPERATURE CONTINUES HIGH. LOW OIL PRESSURE 011 temperature and pressure gauges . . . . . . Monitor Pressure below 10 PSI . . . . . . . . EXPECT ENGINE FAILURE, proceed to FORCED LANDING EMERGENCY. ENGINE DRIVEN FUEL PUMP FAILURE II/IIIII/lll/111/l/1/ II/WARNING/I/ ll/lllllllllllllll/11 When operating engine at moderate power with "HIGH BOOST" ON and engine driven fuel pump has failed, engine may quit or run rough when manifold pressure Is reduced, unless manually leaned. An engine driven fuel pump failure Is probable when engine will only operate with HIGH BOOST pump ON . Operation of engine with a failed engine driven fuel pump and auxilllary fuel pump HIGH BOOST ON will require smooth operation of engine controls and cor- responding mixture change when throttle Is repositioned or engine speed Is changed. When retarding throttle or reducing engine speed, adjust mixture to prevent engine power loss from an overrich cond~ion . Enrich mixture when opening throttle or increasing engine speed to prevent engine power loss from a le an condition. Always lean to obtain a smooth running engine. 3-8 REV A 7-94 ISSUED 6-94 MOONEY M20R SECTION Ill EMERGENCY PROCEDURES The following procedure should be followed when a failed engine driven fuel pump is suspected: HIGH BOOST Pump (guarded switch) . . . . . . . . . . . ON Throttle . . . . . . CRUISE Position or as required for engine operation Mixture . . . . . . • . . . ADJUST for smooth engine operation. LAND AS SOON AS PRACllCABLE & CORRECT MALFUNCTION. FUEL VAPOR SUPPRESSION (Fluctuating Fuel Flow) Engine operation • . . . . . . . . . . . . . . MONITOR Low Fuel Boost Pump SVotitch . . . . . . . . ON to clear vapors ILow Fuel Boost Pump SVotitch . OFF- (If condition still exists, REPEAT PROCEDURE). IFIRES! ENGINE FIRE - DURING START ON GROUND Magneto/Starter SVolitch If engine starts: Power Engine . . . . . . If engine does NOT start: Magneto/Starter SVotitch . . Mixture . . . . . Low Fuel Boost Pump SVotitch Throttle . . . Fuel Selector Valve . Magneto/Starter SVolitch Master SVolitch FIRE . ENGINE FIRE - IN FUGHT Fuel Selector Valve Throttle Mbdure . . . . Magneto/Starter SWitch . . . Cabin Ventilation & Heating Controls CONTINUE cranking or until fire is extinguished. 1500 RPM for several minutes INOTEI SHUTD0\1\.N; inspect for damage CONTINUE CRANKING I. . IDLE CUTOFF . . . . . OFF . . FULL FORWARD . OFF . OFF . . . . . . . OFF EXTINGUISH with Fire Extinguisher . OFF CLOSED IDLE CUTOFF . OFF CLOSED If fire is not extinguished, attempt to Increase airflow over engine by increasing glide speed. Proceed with FORCED LANDING EMERGENCY. DO NOT attempt an engine restart. If necessary, use fire extinguisher to keep fire out of cabin area. ELECTRICAL FIRE • IN FUGHT (Smoke in Cabin) Master SVolllch /IIlliIllJIII/II II //WARNING// IIIIIII11111/lllll . OFF Stall waming and landing gear waming, not available with Master Switch OFF. Alternator Field SVotitch . OFF Cabin Ventilation OPEN Healing Controls . . . . . . . CLOSED Circuit Breakers . . . . . CHECK to identify faulty circuit if possible LAND AS SOON AS POSSIBLE. If electrical power is essential for flight, attempt to identify and isolate faulty circuit as follows: Master SVolitch . ON Alternator Field SWitch ON ISSUED 6-94 REV. E 9-95 3-9 SECTION Ill MOONEY M20R EMERGENCY PROCEDURES Select ESSENTIAL switches ON one at a time; permit a short time to elapse before activating an additional circuit. !EMERGENCY DESCENT PROCEDUREl In the event an emergency descent from high altitude is required, rates of descent of . I !ea.st 3,000 feet per minute can be obtained in two different configurations: (1) IMth landing gear and flaps retracted, an airspeed of 196 KIAS will be required for maximum ra te of descent. (2) Wth the landing gear extended and Haps retracted an airspeed of 165 KIAS will also give approximately the same rate of descent. At 165 KIAS ·and the gear extended, the Iangle of descent will be greater, thus resulting In less horizontal distance traveled than a descent at 196 KIAS. Additionally, descent at 165 KIAS will provide a smoother ride and less pilot work load . 'THEREFORE; The following procedure is recommended for an emergency descent: Power . RETARD INITIALLY Airspeed . 140 KIAS Landing Gear . . • . • . . . . . . EXTEND Airspeed • INCREASE TO 165 KIAS after landing gear is extended. IMng Aaps . . . . . . . . UP Airspeed • . . . MAINTAIN 165 KIA$ during descent. __ Spiteueddeb rakes . (l.f inst. alled. ) . . . . . . . EXTEND All . . . • . . . AS DESIRED Power During Descent . . . . . . A§ REQUIRED to maintain CHT 250°F (121 C)mlnimum. MAXIMUM GUDE DISTANCE MODEL M20R 22000~~+-+-+-~~~~~~-r-r-+-+-+-+~~~-1~~~r-t-; 2oooor-~+-+-+-+-~~~~~-r-r-+-+~~~~~-i-i-1~~~r-t-; 1aooor-~~+-+-+-~;r,_~~~-r-+.ev~-t-t-i-i-;~~ r-r-t-; 1&ooor-+-+-+-~~~,_~-r-r-+~~~ ~~-t-+-i-1~~r-r-r-~t-1 ~ 1oooo W' I I I I !! eooo ~ I I I I A BEST GUDE SPEED i Weight lAS ,-1-- 60001--t-+-+-+7.6"+-+--+--+--+--+-+-+-+-1 LBS (Kg} (Kta) -I-- f' 3368 11 528 81.5 -~--- #" 3200 1452 89.0 40oor-~+A."'"JlfY-;-1~r-r-r-~~+-+--l i~gg m: =~ : ~ -I- 20oo~~~~~~r-r-+-+-+-r-r-r-r-r-~~1r-r-1~1~1r-~ ~ I I I I 3-10 !~ I I I I I I 10 0 10 20 30 40 50 60 70 80 GROUND DISTANCE - KILO!o.lETER!i REV. E 9-95 90 100 110 U-OUDE ISSUED 6-94 MOONEY M20A I NOTEI SECTION Ill EMERGENCY PROCEDURES Greater glide distances can be attained by moving the propeller control FULL AFT {LOW RPM). lFORCED LANDING EMERGENCYj GEAR RETRACTED OR EXTENDED Emergency Locator Transmitter Seat Belts/Shoulder Harnesses . ARMED • .SECURE UNLATCHED . . .OFF IDLE CUTOFF . . .OFF Cabin Door Fuel Selector Mixture . . . Magneto/Starter Switch Wing Flaps . • Landing Gear . Approach Speed . Master Switch . Wings . . . . Full DOWN DOWN-If conditions permit . . . . 80 KIAS . OFF, prior to landing . . LEVEL Attutude !OVERWEIGHT LANDING PROCEDURES! In the event It Is necessary to land with weight exceeding 3200 Lbs. (1452 Kg.) (max. landing weight) the following procedure Is recommended In addition to normal APPROACH FOR LANDING procedures: Approach Airspeed . 80 KIAS · Use a flatter approach angle than normal, with power as necessary until a smooth touch- down Is assured . Expect landing distance over a 50 feet obstacle (Ref. SECTION VIto Increase at least 600ft. Conduct Gear and Tire Servicing Inspection as required (Ret SECTION VIII) . · lSVSTEMS EMERGENCIES! PROPELLER PROPELLER OVERSPEED Throttle Oil Pressure Propeller Airspeed Throttle FUEL LOW FUEL FLOW Check mixture Fuel Selector . RETARD . . . . . . . . . . CHECK DECREASE RPM, re-set if any control available . . . . . . . . . . REDUCE . AS REQUIRED to maintain RPM below 2500 RPM . . .ENRICH . SWITCH TANKS If condition persists, use Fuel Boost Pump as necessary. LANDING should be made as soon as PRACTICABLE. ELECTRICAL ALTERNATOR OVERVOLTAGE (Alternator warning light Illuminated steady and Alternator Field circuit breaker tripped.) Alternator Field Circuit Breaker RESET If circuit breaker will not reset, the following procedures are required : ISSUED 6-94 3- 11 SECTION Ill EMERGENCY PROCEDURES 1. Reduce electricalload1 ,as required,.,. to maintain essential systems. 2. Continue flight and lAND, when Pt1ACTICABLE, to correct malfunction. MOONEY M20R I NOTE I The only source of electrical power is from the selected battery. Monitor battery voltage (min. 18V) and switch to other battery when necessary. ALTERNATOR OUTPUT LOW (Alternator warning light flashing) REDUCE ELECTRICAL LOAD If annunciator light still flashes: Alternator Field Switch 1. Reduce electrical load, as required, to maintain essential systems. 2. Continue flight and LAND, when PRACTICABLE, to correct malfunction. OFF I NOTE I The only source of electrical power is from the selected battery . Monitor battery voltage (min. 18V) and switch to other battery when necessary. Battery endurance will depend upon battery condition and electrical load on battery. If one battery becomes depleted, switch to other cattery. LANDING GEAR FAILURE OF LANDING GEAR TO EXTEND ELECTRICALLY Airspeed . . . . 140 KIAS or less Landing Gear Actuator Circuit Breaker PULL Landing Gear Switch . . . . . . . . . DOWN Gear Manual Emergency Extension Mechanism . LATCH FORWARD/LEVER BACK to engage manual extension mechanism I NOTE I Slowly pull "T" handle 1 to 2 inches (2.5 to 5.1 em) to rotate clutch mechanism and allow it to engage drive shaft. T-Handle . . . PULL (12 to 2d times) . . . and RETURN until gear is down and locked . . . GEAR DOWN light ILLUMINATED; STOP when resistance is felt. Visual Gear Down Indicator . . . . CHECK ALIGNMENT by viewing from directly above indicator -CAUTION- Continuing to pull on T-H~n<ll~ . after GEAR DOWN light ILLUMINATES, may bind actuator; electrical retraction MAY NOT be possible until binding is eliminated by ground maintenance. Return lever to normal position and secure with latch. Reset landing gear actuator circuit breaker. IIIIIIIIIIIllIIIII //WARNING// ///lll/l/l/l/1/1// Do not operate landing gear electrically with manual extension system engaged Do not fly craft until maintenance/Inspection is done on landing gear system. FAILURE OF LANDING GEAR TO RETRACT AIRSPEED Below 107 KIAS GEAR Switch . . . . . . . . UP Position GEAR FAILS TO RETRACT - GEAR HORN • SOUNDING; GEAR ANNUNCIATOR LIGHT & GEAR SAFETY BY-PASS LIGHT -ILLUMINATED 3-12 REV . E 9-95 ISSUED 6-94 MOONEY M20R SECTION Ill EMERGENCY PROCEDURES GEAR SAFETY BY-PASS SIMTCH . . . . . . . . . DEPRESS . . . . . HOLD until landing gear is fully retracted "GEAR UNSAFE" and " GEAR DO\MII" Lights . . . . . EXTINGUISHED "GEAR RELAY" Ckt . Bkr . . . . . . . . . . . . . . . . PULL . . . . . . . . . . (Warning Hom and Gear By Pass light will go OFF) Check "Airspeed sarety SWitch" or other malfunction as soon as practicable. "GEAR RELAY" Ckt . Bkr . . . . . . . . . . . . . . . PUSH IN WHEN READY TO EXTEND LANDING GEAR Airspeed . . . Gear Relay C/B . BELOW 140 KJAS RESET Landing Gear Switch Gear Down Light . . DOV\.N ILLUMINAlED JNOTEJ If above procedures do not initiate retraction process, check gear emergency manual extension lever (on floor) for proper position. GEAR FAILS TO RETRACT- GEAR HORN • DOES NOT SOUND GEAR ANNUNCIATOR LIGHTS & GEAR BY-PASS LIGHT- NOT ILLUMINATED GEAR EMERGENCY EXTENSION LEVER (on floor) Verify LATCHED in proper position GEAR ACTUATOR C/B . . . . . . . . . . . . . . . RESET . . . . . . . . . . Gear should retract if C/B was tripped FLIGHT . . . . . . . . . . . CONllNUE (if desired) When ready to extend landing gear at next landing: AIRSPEED . . . . . . . . . . . . . . . Below 140 KIAS GEAR SIMTCH . . . • . . . . . . . . . . . DOV\.N Position If gear .wlll not extend electrically at this time, refer to FAILURE OF LANDING GEAR TO EXTEND ELECTRICAL!.Y (previous page). VACUUM \Mlen " HVLO VAC " annunciator light illuminates (flashing or steady), vacuum operated Instruments are considered to be unreliable . Push sl and-by vacuum pump switch ON . The Iflashing Hi/LO VAC annunciator light should ext i ngui sh and the STBYVAC annunciator will illuminate . The vacuum operated gyro Instruments will be operaUng on the stand-by vac- uum system. The .steady RED annunciator light may not extinguish when the stand-by vacuum switch Is ON. Continue Hight , monitor non - vacuum gauges . Have vacuum system inspected prior to next flight. OXYGEN In the event of oxygen loss above 12,500 fL return to 12. 500 It as soon as feasib le. Refer to SECllON X for the phys iolog ical characte ristics of high altitude flight. ALTERNATE STATIC SOURCE The alternate static alr source should be used whenever It Is suspoolt:d lhatlhe nonnal stat ic ofr sources are blocked . Selecting the aHemate static source changes the source of static alr for the altimeter, airspeed indicator and rale-of4mb from outside of the aircrall to the cabin interior. lll.tlen aHemate staUc source Is In use, adjust indicated airspeed and altimeter readings according to the appropriate aHemale stallc source airspeed and altimeter calibration tables in SECllON V. lhe alternate static air source valve Is located on the Instrument panel below pil ot's control wheel shaft . JNOTEJ When using Alternate Static Source, pilot's window and air ventS MUST BE KEPT CLOSED. Alternate Static Source . . . Airspeed and Altimeter Readings . ISSUED 6-94 . . . . . . . . . . . PULLON CHECK Calibration Tables (Ref SECllON V) REV. F 9-96 3-13 SECTION Ill EMERGENCY PROCEDURES MOONEY M20R !uNLATCHED DOORS IN FUGHTI CABIN DOOR If cabin door Is not property closed it may come unlatched in flight. This may occur during or just after take-off. The door will trail In a position approximately 3 Inches (7 .6 em) open, but the flight characteristics of the airplane will not be affected . There will be considerable wind nofse; loose objects , In !he vicinity of the open door, may exit the aircraft . Return to the field In a nonnal manner. If practicable, secure the door In some manner to prevent It from swinging open during the landing . If it Is deemed impractical to return and land , the door can ' be closed in flight, after reaching a safe altitude, by the following procedures: Airspeed . . • Pilot's Stonn Wndow Aircraft . . . . Door . • • . BAGGAGE DOOR . . . . . . . . 95 KIAS . . . ..... .. . .. . OPEN RIGHT SIDESLIP (Right bank with left rudder) . . . . . . . PULL SHUT & LATCH If baggage door Is not property closed, it may come unlatched In flight. Th is may occur during or after takeoff. The door may open to its full open posHion and then take an lntennedlate position depending upon speed of aircraft. There will be consklerilble wind noise; toose objects, In the vic inity of the open door, may exit the alrcraR. There Is no way to shut and latch door rrom · the · ~nslde : Alttrall ftklht characteristics wUI not ·be affected; · fly aircraft in nonnal manner; tAND AS 699~ AS POssiBLE and sec~re I:Jag~ag'! doo ~. Baggage Door latching mechanism . . VERIFY MECHANISM PROPERLY ENGAGED Qnside latching mechanism) then shut from outside aircraft . .I!P.INGI . flflllll/1111111111 //WARNING/I 1//11/11/11/11111/l DO NOT OPERATE IN KNOWN ICING CONDITIONS. The Model M20R Is NOT APPROVED for flight Into known Icing conditions and operation In that environment Is prohibited . However, lf:ThOse coodilloi'is.are..lnadvertenlly en~u ii • tared or flight Into heavy snow is unavold.able, the following procedures are rec.ommended until further Icing conditions can be avoided: · INADVERTENT ICING ENCOUNTER Pilot Heat . . . Propelle r De-Ice . . Alternate Static Source Cabin Heat & Defroster Engine Gauges . . . ON ON 8if installed) .. . . ·- . ON !f required) .. . -~ -:- ... .. "' ;.-. . .. ·.. ··.. • . . .. ··:.. . :...... ON MONITOR tor any engine power reduction :rum back or change altHude to obtain an outs.~e ~r temperature less CQilducr.te to :ic- Ing . -- · ... · .,. · · ... · · Mow propeller control to maximum RPM to l)'linimlze Ice bu ild-up on propeller blades. If Ice builds up or sh~s unevenly on propeller,. }lib ~stfo n" wlll occur. If excessive vibration Is noted, momentanly reduce engine spee9 wll.ll propeller control to bottom of GREEN ARC , then rapidily move control FUU. FO~ . INOlEI Cycling RPM Hexes propeller blades aild high RPM increases centrifugal force which improves propeller capability to shed ice. As ice builds on the airframe, move elevator control fore and aft slightly to break any ice build-up that may have bridged gap between elevator hom and holizontal stablilizer. 3-14 REV.E 9-95 ISSUED 6-94 MOONEY M20R SECTION Ill EMERGENCY PROCEDURES V\Stch for signs of induction air filter blockage due to Ice build-up; increase throttle setting to maintain engine power. JNOTEI If Ice blocks induction air filler, alternate air sysem will open automatic~llly. wth ice accumulation of 1/4 Inch or more on the airframe, be prepared for a significant Increase in aircraft weight and dreg . lhls will result In slgnlflcanUy reduced cruise and climb performance and higher stall speeds. Plan for higher approach speeds requiring higher power settings and longer landing rolls. ------ • .. • • : .., .t • . . - CAUllON;, 1 • · :· ... :.. .. '.. • ,. -'<'.!'''-.... Stall waming ~m mly ~lriojJeriltive. INO~I . ·.. · · : · · · · The defroster may not clear Ice rrom ndahleld. If necessary open pilofs storm window for visibility in landing approach and touchdown. ~' .: .. Wth ice accumulations of·1 Inch or lessi use no more than 15° wing Raps for approach • and landing . For ice accum1,1lalion of 1 inch or more, fly approaches and tanding with flaps ,• • retracted to maintain better pitch control. Ry approach speed at least 15 knots faster than normal, expect a higher stall speed , resulting In higher touchdown speed with longer landing roll. Use normal flare and touchdo~ n technique. Missed approaches SHOULD BE AVOIDED whentNer possible because of severty re- duced climb performance. If a go-around Is mandatory, .apply full power, retract landing. · • gear when obstacles are cleared; maintain 90 KIAS and retract wing flaps . -AVOID FURTHER ICING CONDillONS - CABIN DOOR !EMERGENCY EXIT OF AIRCRAFTl PULL latch handle AFT. OPEN door and exit aircraft. BAGGAGE COMPARTMENT DOOR (Auxiliary Exit) Release (Pull UP) rear seat back latches on spar. Fold rear seat backS forward, CUMB OVI!R. PULL off plastic cover from over Inside latch. PULL latch pin. Pull red handle. OPEN door and exit aircraft . To VERIFY RE-ENGAGEMENT of baggage door, outside, latch mechanism: ISSUED 6-94 Open outside handle fully. Close inside RED handle to engage pin into cam slide of latch mechanism. Place latch pin in shaft hole to hold RED handle 00\MII. Replace cover. CHECK & operate outside handle in normal manner. REV.E 9-95 -· .;, : :·. . . 3-15 I I SECTION Ill EMERGENCY PROCEDURES MOONEY M20R ISPINSI II/IIIII/IIIIllIIII //WARNING// fllll/111/ll/lf/111 Up to 2,000 ft. aHitude may be lost In a one tum apln and recovery; STALLS AT LOW ALTITUDE ARE EXTREMELY CRITICAL INOTE I The best spin avoidance technique Ia to avoid flight conditions conducive to apln entry. Low speed Right near stall should b8 approached with caution and exceaalve flight control movements In this flight regime should be avoided. Should an unintentional ~II occur, the aircraft should not be allowed to progress Into a deep stall. Fast, but amooth stall recovery will minimize the rtak of progreulng Into a apln. If an unusual post atall attitude develops and reaulta rn a apln1 quick appllcallon or antlapln procedures ahoultf anorten the recovery. INTENTIONAL SPINS ARE PROHIBITED. In the event of an Inadvertent spin, the following recovery procedure should be used: Throttle ADerons Rudder Control Wheel . RETARD to IDLE . . . . . . . . NElJTRAL . . Apply FUU. RUDDER opposite direction of spin • FORWARD of neutral In a brisk motion ADDITIONAL FORWARD elevator control may be required If rotation does not stop. -- HOLD ANTI-SPIN CONTROLS UNTIL ROTATION STOPS -- Wing Flaps Of eldended) Rudifer . . . Control Wheel . RETRACT as soon as possible . NEUTRALIZE when spin stops . . . . SMOOTHLY MOVE AFT to bring the nose up to level ftlglit att~ude. I()THER .EMERGENCIES! Refer to SECTION IX for Emergency Procedures of Optional Equipment. 3-16 ISSUED 6-94 MOONEY M20R SECTION IV NORMAL PROCEDURES ITABLE OF CONTENTS I TITLE ..... INTRODUCTION . . . SPEEDS FOR NORMAL OPERATION . PREFLIGHT INSPECTION . BEFORE STARTING CHECK ENGINE START . . . . FLOODED ENGINE START . WARM ENGINE START . HOT ENGINE START BEFORE TAXI TAXI ... BEFORE TAKEOFF . TAKEOFF CLIMB . CLIMB (CRUISE CLIMB) . CLIMB (BEST RATE) . CLIMB (BEST ANGLE) CRUISE . . . . . FUEL TANK SELECTION OXYGEN SYSTEM DESCENT . . GEAR UP. GEAR DOWN. APPROACH FOR LANDING GO AROUND (BALKED LANDING) LANDING. . . . . TAXI AFTER LANDING . SHUTDOWN .... SECURING AIRCRAFT . ISSUED 6-94 REV. F 9-96 PAGE 4-3 4-4 4-5 4-7 4-8 4-9 4-9 4-9 4-9 4-10 4-10 4-11 4-11 4-11 4·11 4-12 4-11 4-12 4-13 4-13 4-13 4-14 4-14 4-15 4-15 4-15 4-16 4-16 4 - 1 SECTION N NORMAL PROCEDURES lTABLE OF CONTENTS (con'l)l 4-2 MOONEY M20R ISSUED 6-94 MOONEY M20R IINTRODUCTIONI SECTION IV NORMAL PROCEDURES This section describes thJ~ recommended procedures for the conduct of normal operations for the airplane. All of the required (fAA regulations) procedures arid those necessaJY -for operation of the airplane as determined by tfte 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. PRats 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 wHh those optional systems and equipment which require handbook supplements are provided by SECTION IX (Supplemental Data) . . · :.___,·· ISSUED 6-94 4-3 SECTION IV NORMAL PROCEDURES lSPEEDS ~OR NORMAL OPERATIONj MOONEY M20R Unless otherwise noted, the following speeds are based on a weight of 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 speEid appropriate to the particular weight must be used . · _ · TAKEOFF: Normal Climb Out Short Field Takeoff, Speed At 50 Ft. ENROUTE CUMB, GEAR and FLAPS UP: ' Best Rate of Climb Best Angle of Climb LANDING APPROACH (3200 lbs.): Nanna! Approach, Flaps 1o degrees Nanna! Approach, Flaps 33 degl'(l95 Short Field Approach, Flaps 33 degrees BALKED LANDING (3200 lbs.): Maximum Power, Flaps 10 deg~ 80-90 KIAS • 75 KIAS 105 KIAS · - ;...; , · · . ~ · . EIOKIAS . 80 KIAS . 75 KIAS . 70 KIAS . 85 KIAS . MAXIMUM RECOMMENDED TURBULENT AIR PENETRATION SPEED: 3368 lbs./1528 Kgs 121 K1AS 3200 lbs./1452 Kgs 123 KIAS 2900 lbs./1315 Kgs 117 KIAS 2600 lbs./1179 Kgs 111 KIAS 2400 lbs./1089 Kgs 106 KIAS DEMONSTRATED CROSSWIND VELOCITY: Takeoff or Landing . . . . . . . . . . . . 13 Knots . (This Is NOT A UMITATION, only a demonstrated number; (See CROSSWIND COMPONENT CHART, SECTION V) 4-4 ISSUED 6-94 -- MOONEY M20R 1. Cockpit- SECTION IV NORMAL PROCEDURES Gear Switch . . DOWN Magneto/Starter Switch OFF All Rocker Switches OFF Master Switch . ON All Circuit Breakers . . . . . . . . . . IN Battery Select Switch . . . . . SELECT from 1 to 2 or 2 to 1. CHECK Voltmeter after each selection. Leave on Battery w ith highest voltage. Internal/External Lights . • . . • . . CHECK operation . . . . (Check for ammeter fluctuations as each light Is checked) Pltot Heat Switch • . . . . . . . ON . . • . (Check Pilot Heat annunciator light Illuminated BLUE *) Fuel Quantity Gauges . . . . . . . CHECK QTY Fuel Selector It is recommended that wing tank sumps be drained prior to draining gascolator. . . . . . . At. Tank: Pull Gascolator ring (5 seconds! • . • . . . . U. Tank: Pull Gascolator ring (5 seconds Oxygen Supply Control Knob (if lnstall1:1d) OFF Oxygen Pressu re Gauge . . . • . . . . CHECK Verify adequate oxyg en supply for trip, (If use of oxygen is anticipated), refer to oxygen duration chart (Fig. 7-13) . Al so check that face masks and hoses are accessible and in good condition. 2. Right Fuselage/Tallcone Oxygen Filler Access Uoor and F1ller Cap Bat1ery # 2 Access Panel . Instrument Statlc Pressure Port. General Skin Condition . . Tailcone/Empennage Access Panel Tail tiedown rope/chain . . SECURED . SECURED UNOBSTRUCTED INSPECT SECURED REMOVE 3. Empennage Elevator and rudder attach points and control linkage attachments INSPECT INSPECT Empennage Freeplay-Verticai/Horizontal General skin condition . . INSPECT Remove ice, snow, or frost. * If TKS system is installed , pilot heat annunciator will illuminate AMBER when switch is ON and Pilot Heat has failed. Annunciator will not be illuminated when switch is ON and system is operating properly. ISSUED 6-94 REV . F 9-96 4-5 SECTION IV NORMAL PROCEDURES 4. Left Fuselage(Tailcone Cabin Fresh Air Vent (Dorsal Fi n) Tailcone/Empennage Access Panel Instrument Static Pressure Port. Avionics/Battery # 1 Access Panel Auxiliary Power Plug Access Door Static System Drain General Skin Condition 5. Left Wing General Skin Condition . Wing Flap & attach points . Aileron & attach points Control linkages . . Wing Tip, Lights and Lens . Fuel Tank Vent Pilot Tube . . . Landing/Taxi Lights Stall Switch Vane . Fuel Tank MOONEY M20R UNOBSTRUCTED . SECURED UNOBSTRUCTED SECURED . . . . SECURED PUSH Plunger UP, (Hold 3-5 Seconds) INSPECT I NOTE I INSPECT-Remove ice, snow, or frost. INSPECT INSPECT INSPECT . INSPECT . UNOBSTRUCTED UNOBSTRUCTED/SECURED (Heat element Operative) INSPECT Lens & Bulbs . . CHECK operation CHECK QUANTI'TY/SECURE CAP The optional visual fuel quantity gauge is to be use for partial refueling purposes only; DO NOT use for preflight quantity check . Tiedown rope/chain . REMOVE Wheel chock . . . . . . REMOVE Left Main Landing Gear, shock discs, tire & doors INSPECT Fuel Tank Sump Drain . . . . . . . . . DRAIN Use sampler cup to VERIFY fuel is free of water, sediment & other contamination; VERIFY proper fuel (BLUE/1 OOLL)(GREEN/1 00 octane) . -CAUTION- Some diesel may be BLUE, Verify by smell and feel that 100LL Is being used. VERIFY drain closes and does not leak. Pilot System Drain 6. Left Cowl Area Windshield Cabin Air Inlet . . . Left Side Engine Cowl Fasteners Exhaust Pipes . Engine Oil Filler Door PUSH plunger UP, (Hold for 3-5 seconds) I NOTE I . CLEAN UNOBSTRUCTED . SECURED INSPECT SECURED OPEN & INSPECT AREA The engine compartment must be free of fore i gn objects which could result in possible over healing and st!rious damage to the engine . Engine Oil • • • 0 Engine Oil Filler Door . Cooling Air Inlet . 7. Propeller/Spinner & Front Cowl Area Propeller/Spinner . . . . . . . Prop De-Ice Boots (if installed) Induction Air Inlet/Filter . . Nose gear, shock discs, tire & door s Wheel chock 4-6 REV. C 9-94 CHECK QUANTI'TY 8 Qts. (7 .57 I) CLOSE & SECURE Verify UNOBSTRUCTED INSPECT for nicks, cracks, oil leaks/rotational movement. INSPECT condition UNOBSTRUCTED INSPECT REMOVE ISSUED 6 - 94 MOONEY M20R 8. Right Cowl Area Right Side Engine Cowl Fasteners Cooling Air Inlet Windshield Cabin Air Inlet 9. Right Wing SECTION IV NORMAL PROCEDURES . . SECURED Verify UNOBSTRUCTED . CLEAN UNOBSTRUCTED Fuel Tank Sump Drain . . . . . . . . . DRAIN Use sampler cup to VERIFY fuel is free of water, sediment & other contamination. VERIFY proper fuel (BLUE/100LL) (GREEN/100 octane). . SEE: CAUTION on diesel fuel on previous page VERIFY drain closes and does not leak. Right main gear, shock discs, tire & doors Wheel chock . . . . . INSPECT . . . . REMOVE General Skin Condition. INSPECT Remove ice, snow and frost. Fuel Tank CHECK QUANTilY/SECURE CAP I NOTE I The optional visual fuel quantity gauge is to be use for partial refueling purposes only; DO NOT use for preflight quantity check. Tiedown rope/chain . Fuel Tank vent . . Landing/Taxi Lights Wing tip, lights and lens Aileron and attach points . Wing Flap and attach points Control linkages 10. Bag·gage Door Area Baggage Door . REMOVE UNOBSTRUCTED INSPECT Lens & Bulbs INSPECT INSPECT INSPECT INSPECT . . . VERIFY SECURED (VERIFY inside handle is properly secured) (CHECK outside handle operation) RETURN TO COCKPIT- MASTER/ROCKER SWITCHES OFF IBEFORE STARTING CHECK I Preflight Inspection . . . . . . Seats, Seat Belts/Shoulder Harness (1 occupant per restraint) Magneto/Starter Switch Master Switch . Alternator Field Switch Radio Master Switch . Fuel Boost Pump Switches . Directional Gyro (slave/free switch). Circuit Breakers ELT Switch . Rocker Switches . . COMPLETED ADJUST & SECURED OFF OFF OFF OFF . . OFF SLAVED (If instfliiAd) CHECK • ALL IN ARMED OFF Push OFF Alternate Static Source Throttle . . . CLOSED Propeller Mixture . Parking Brakes Wing Flap Switch Defrost . Cabin Heat . Cabin Vent Fuel Selector . All Rocker Switches Landing Gear Switch ISSUED 6-94 REV. E 9-95 FULL FORWARD (HIGH RPM) IDLE CUT-OFF . SET FLAPS UP PUSH OFF PUSH OFF AS DESIRED FULLEST TANK . . OFF DOWN POSITION 4-7 I SECTION IV MOONEY M20R NORMAL PROCEDURES RED Emergency Gear Extension Handle D0\1\.N AND LATCHED Internal Lights . • OFF Passenger Briefing . . . . . . . . . . . . COMPLETED . . . . . . . . . . (Emergency and general information briefing) Refer to SECTION 9 for Optional Equipment Procedures and Checks. I Obtain local information prior to engine start. IENGINE START I ~CAUTION~ When either battery voltage is low, Inspection. should be conducted to determine condition of battery and/or reason for battery being low. Replacement or servicing Of batteries Is essential and chargi ng for at least one hour should be done before engine Is started. Batteries must be serviceable and IT IS RECOMMENDED THAT BATTERIES BE FUU.Y CHARGED TO OPERATE AIRCRAFT. Electrical components may also be damaged if aircraft is operated when batteries are low. I NOTEI When starting engine usi ng the approved external power source, no special starting procedure is necessary. Use normal stalting procedures below. DO NOT START ENGINE IF BOTH BATlERIES ARE INCAPABLE OF STARTING ENGINE. Recharge dead batteries for at least one hour (at 3-4 amps) before starting engine. Only No. 1 battery (left side of tailcone) Is connected to the Auxiliary Power plug. Before starting Checklist ·Throttle . COMPLETED . . . FULLOPEN FULL AM> (High RPM) • Full Forward (RICH) Propeller . Mixture . Master SWitch . Alternator Field SWitch Annunciator Lights . . Low Fuel Boost Pump Switch ON . . . •. . . ... ON PRESS TO TEST (All lights should illuminate) ON during engine starting sequence ~CAUTION- For engine operation at outside air temperatures below -26° C ( -13°F), the engine and engine oil should be preheated to at least -26° c (-13°F) before the engine is started. Throttle . IDLE POSITlON rropellcr Area . . . . . CLEAR Magneto/starter Switch . . lURN & PUSH to START, release to BOlH when engine starts. . . . SELECT No.2 battery If No. 1battery 'wm 'not start' engine 4-6 I NOTE I COLD ENGINE START - Low fuel boost pump ON during 'Start" sequence. Tum low fuel boost pump OFF when engine obtains smooth operation. I NOTEI "START POWER" warning light should illuminate when Magneto/Starter switch is in ''STARl'' position. I NOTEI Cranking should be limited to 30 seconds, and several minutes allowed between cranking periods to permit the starter to cool. REV.E 9-95 ISSUED 6-94 MOONEY M20R SECTION IV NORMAL PROCEDURES Throttle . . . . . . . . • . . . . . . . IDLE 600 • 700 RPM • Engine Oil Pressure • . . • . . . . . • . . CHECK In GREEN ARC . . . . . If minimum oil pressure (10 PSI) Is not indicated within 30 seconds, . . . . . . • • . . . . . accompffsh engine shutdown procedures . Low Fuel Boost Pump SWitch . . . • . . . OFF • Ammeter . . • . . . . . . . . . . . . . . • . CHECK • intei1oriExteno'r Ughts • Engine Instruments . • Fuel Flow Indicator * Throttle • Mixture Tum LOG LT ON & observe Negative movement of needle . . . . . . .• ...... ASDESIREO . • . . . . . . . CHECKED . . . . . . TEST/RESET (If desired) . . . . . . . . 900{1000 RPM ADJUST FOR SMOOTH OPERAllON -CAUTION- Do not operate engine above 1000 RPM unless oil temperatun! is 75° F (24°C) minimum. Operation of engine above 1000 RPM at temperatun!s below 75° F (24°C) may damage engine. I FLOODED ENGINE START I Throttle . 1/ 2 OPEN Mixture . . . . . . . . . . . IDLE CUTOFF Low Fuel Boost Pump Switch ON- 8 ·10 SECONDS THEN OFF Magneto/starter Switch . . . . . . TURN & PUSH to START . . . • . . release to BOTH when engine starts. Mixture : Slowly advance toward RICH until engine starts Throttle . . . . . . . . . . . . . . . • . IDLE 600 - 700 RPM SEE ENGINE STARr PROCEDURES ABOVE • FOR REMAINING SEQUENCES. IWARM ENGINE START I Throtlle . . . . . . . . 1/2 to 1 Inch OPEN Mixture . . . . . • . . . . . . . . Full Forward (RIC~ Low Fuel Boost Pump Switch . . . ON • (TO CLEAR FUEL VAPORS 1Low Fuel Boost Pump Switch . . . . . . . . . . . . 0 Magneto/starter Switch WlliiN 1-2 SECONDS TURN & PUSH to STARr • . • . release to BOTH when engine starts . Throttle . . . . . . • . . • . • . . . . . IDLE 600- 700 RPM SEE ENGINE STARr PROCEDURES ABOVE • FOR REMAINING SEQUENCES. Th rottle . Mixture . Boost Pump Boost Pump Throt11e . Mixture . . . • . Magneto/starter Sw itch IHOT ENGINE START I FULL OPEN • • . . . IDLE CUT-OFF HIGH fo r 5 sec . or LOW for 15 sec . • . . . OFF . . . . . IDLE POSmON . . . . Full Forward (RICH) . . TURN & PUSH to START rel ease to BOTH when engine starts. Throttle . . . . . . . . . . . . . • . . • IDLE 600 • 700 RPM SEE ENGINE START PROCEDURES ABOVE ' FOR REMAINING SEQUENCES. I BEFORE TAXI I Engine start Checklist . COMPLETED Radio Master Switch . ON Elevator Trim Switch . . ON lntemai/Extemal Lights • . • As Desired Direct ional Gyro . . . . . . . . . . . . . SET or Slave switch ON stand-by Vacuum Pump Operational Check stand-by vacuum operalional l nd l cato r red button - VISIBLE SlBY VAC Switch . . . . . . . • . . . ON ISSUED 6-94 REV. F 9-96 4 - 9 SECTION IV NORMAL PROCEDURES MOONEY M20R l BEFORE TAXI (con't.)j Stand-by vacuum operational indicator red button - NOT VISIBLE STBY VAC SWitch . . . . . . . . . . . . . • . • OFF Instruments . . . . . . • . Nonnal Oper ation Radios . • . . . . • • . CHECKED and SET Altimeter . . . . . . • . . . . . . SET Fuel Selector S'MTCH TANKS verify engine runs on other tank Cilbln Heat . . . . . . . . . . . AS DESIRED Defroster . . • • AS DESIRED Cabin Vent . . . . . . . . AS DESIRED Optional Equipment Checks Reference SECTION IX. Before Taxi Checklist Rudder Trim -CAUTION- COMPLETED AS DESIRED With rudder trim in the full right position, the aircraft will tend to steer to the right during taxi. Parking brake . Brakes . . . Directional Gyro Tum Coordinator Artificial Horizon Throttle . Propeller· -CAUTION- . . . • • RELEASE . . CHECK during TAXI Proper ind loallon during turns Proper ind loall on during turns . . . ERECT during turns . . . . Minimum power . Full F01ward (HIGH RPM) To prevent battery depletion in prolonged taxi or holding position before takeoff, increase RPM until uAMMETER" indicates positive charge. jBEFORE TAKEOFF! Taxi Checklist . COMPLETED Parking Brake . . . SET Fuel Selector FULLEST TANK Throttle . 1000 RPM Propeller . HIGH RPM Mixture . FULL FORWARD Alternate Air . . Verify CLOSED Alternator Field SWitch . . Veriry ON Throttle . . . . . . . . . . . . . . . . • 2000 RPM Magneto SWitch . . . . . . • CHECK - BOlH to L, BOTH lo R, BOTH . Verirv eng ine operates smoothly on each magneto separately . (150 RPM MAX drop on each magneto, 50 RPM MAX di fference) I NOTE! An absence of RPM drop may be an indication of faulty magneto grounding or improper timing. If there is doubt concerning ignition system operation, RPM checks at a leaner mixture setting or higher engine speed will usually conrinn whether a deficiency exists. Propeller Ammeter Throttle . . . . . . Low Fuel Boost Pump SWitch Low Fuel Boost Pump SWitch 4-10 . . . CYCLEJRetum to high RPM . CHECK Positive Charge Indication . . . . . . . RETARD fo 1000 RPM ON-Verify annunciator light will Illuminate BLUE . . . . . . • . . . • . OFF REV. F 9-96 ISSUED 6 - 94 MOONEY M20R Elevator Trim . . . . RudderTrim . . . . . . . . . . Wng Flaps . . . . . . . . . . . SET AT TAKEOFF position (10 Degrees) Flight Controls . . . . . Cabin Door . . . . • . . . Seats! Seat Belts and Shoulder Harness . Avion cs and Auto Pilot . . . . . Annunciator Lights . . . • . . lntemai/Extemal Lights . . . . • strobe Lights/Rotating Beacon . . . Pilots Wndow . . . . . . . . Emergency Gear Extension (RED) Handle Oil Temperature CHT .. . Par1dng Brake . ITAKEOFFI SECTION IV NORMAL PROCEDURES TAKEOFF SETTING TAKEOFF SETTING CHECK operaUon. CHECK free and correct movement . . • . CHECK SECURED . . . . . . SECURED CHECK- (Refer to SECTION IX) . . . . . . • CHECK . . ASDESIRED . . . ON ... . CLOSED . 00\MII & LATCHED 7tF(24°C) minimum 250 F(121°C) minimum . • . . RELEASE Proper engine operation should be checked earty in the takeoff roll . Any sign ificant indication of rough or sluggish enQine response Is reason to discontinue takeoff. \Mlen takeoff must be made over a gravel surface, it is Importan t that the throttle be applied SLOWLY. This will allow the aircraft to s1art rolling before high RPM Is developed, and gravel or loose material will be blown back from the propeller arealns1ead of being pulled Into it . TAKEOFF (NORMAL) Power . Annunciator . . Engine Instruments Lift Off/Climb Speed Landing Gea r • . Wng Aaps . . . • . . . FULL THROTILE (2500 RPM) . . . . . • . . . . CHECK . . . . CHECK for proper Indications As specified in SECTION 5 ITakeoff Distance) RETRACT IN CUMB after clearing' obstacles . . . . . • . . . . . . UP I NOTEI If maximum performance takeoffs are desired obtain full power before brake release. Use lift off and climb speed as specified in SECTION 5. leu Mal I NOTEI If applicable,use noise abatement procedures as required. I NOTEI See SECTION 5, for rate of climb graph. CUMB (CRUISE) Power . . . Manifold Pressure Mixture . Rudder Trim Airspeed CUMB (BEST RATE)(Vvl Power . Mixture . Rudder Trim Airspeed ISSUED 6-94 REV . F 9-96 2500 RPM . . . . . • . 24lnches FULL RICH or BWE ARC on EGT . . . . . As Desired . . . • • . 120 KIAS . FULL THROffiE /2500 RPM FULL RICH or BLUE ARC on EGT As Desired 105KIAS 4-11 SECTION IV NORMAL PROCEDURES CUMB (BEST ANGL.E)(Vxl Power . . Mixture . . Rudder Trim Airspeed MOONEY M20R FULL lHROmE/2500 RPM FULL RICH . . . . As Desired 85 KIAS Leaning may be required during CUMB depending on abnospheric · conditions. jCRUISEj fNOTEI Use ~~~Commended engine break~n procedures as published by engine manufacturer. Airspeed Throttle . . . . . . . ACCELERATE to cruise airspeed . . . . . • . . . SElEClED SETTlNG (Ref. CRUISE PERFORMANCE CHARTS in SECTION 5) I NOTEI Prolonged climbs to high cruise attitudes during hot weather opemlions may result In some fuel flow fluctuations as lhrotue Is reduced. If fluctuations occur, tum Low Boost Pump SWitch ON until cooling has .alleviated fluctuations. Propeller . Mixture . . I NOTE! . . Set RPM to selected setting LEAN TO 50 F rich of PEAK EGT Cruise operation at BEST POWER will result in a substantial increase in fuel flow, greatly decreasing range and endurance; reference charts published in SECTION 5. Engine instruments CHECK JNOTEJ Careful leaning of mixture control will result In best ruel efficiency. This requires operating at proper EGT. Failure to do so will result in excessive fuel bum. After leveling off at cruise altitude, set RPM for desired power setting per Cruise Power Chart In Section V. Slowly lean Mixture until EGT reaches peak value. Enrichen to 50°F rich of peak EGT for best power (50°F lean of peak Is best economv.); careful adjustments are necessary for accurate setting. Changes in altitude or power MAY REQUIRE readjustment of EGT. Engine temperatures . . RuaderTrim . . . . . STABILIZE at cruise condition. . . . . . . As Desired Wlen Increasing power, always retum mixture to rull rich, then Increas e RPM berore Increasing manifold pressure; when decreasing power, decrease manifold pressure before reducing RPM. Always stay within the established operating limits, and always operate the controls slowly and smoothly . jFUEL TANK SELECTION! Low Fuel Boost Pump SWitch Fuel Selector . . . . . Low Fuel Boost Pump SWitch 4-12 REV.F 9-96 . . . ON OPPOSITE TANK OFF ISSUED 6-94 MOONEY M20R !OXYGEN SYSTEM! (OP110NAL EQUIPMENT} lllfllllll//11111111 II WARNING II 1/1/1111111/l/llllll SECTION IV NORMAL PROCEDURES Greasy lipsticks and waxed mustaches have been known to ignite · spontaneously inside OJWgen masks. Passengers should be suitably advised prior to flight. For safety reasons NO SMOKING should be allowed in the airplane while OJWgen is being used. \Mlen ready to use the OJWgen system, proceed as follows : Mask and Hose . . . . . . . . . . SELECT· either MIC or STD Adjust mask to face and adjust metallic nose strap for snug mask fit. Delivery Hose . . . . . PLUG INTO OUTlET assigned to that seat. I NOlEI When the oxygen system is turned ON, oxygen will flow continuously at the Iappropriate rate of flow for the altitude without any manual adjustments. Oxygen Supply Cont rol Knob . ON. Face Mask Hose Flow Indicator . . . . . . . . . • . CHECK . Oxygen is flow ing if the Indicator Is being forced toward the mask. Delivery Hose . . . UNPLUG from outlet when discontinuing use of oxygen. This automatically stops flow of oxygen from that outlet. oJ(ygen su.pply contror' Knob . . . . OFF- when oxygen Is no longer required . 11/ll/111111111111111 II WARNING II I///IIIII/lllf7IIIll Proper oxygen flow is critical to pilot/passenger safety, especially at altitudes above 20,000 ft. MSL It Is Important to closely monitor the face mask hose 1flow Indicator to ensure oxygen Is constantly flowing to the mask. A GREEN indication on the flow Indicator denotes proper oxygen flow. Always place the now indicator in a position where it is In the nonnal scan area of the cockpit. Refer to duration chart (Fig. 7-13) for safe operational quantities. IDESCENT! I NOlEI Avoid extended descents at low manifold pressure setting, as engine can cool excessively and may not accelerate satisfactorily when power is re-applied. NORMAL DESCENT· GEAR UP Seals, Seal Bells/Shoulder Harness Wing Flaps landing Gear Throttle . Propeller . Mixture . . . . . . Cylinder Head Temperature (CHl) Airspeed . . Rudder Trim . ADJUST AND SECURE UP . . UP CHT in Green) . . . . . . . . 2400RPM Peak EGT (Monitor as descent progresses) . . MONITOR £250° F(121°C) minimum.] . . . . AS 0ESIRE0(1S6 KlAS max .) AS DESIRED ISSUED 6-94 REV. E 9-95 4-13 SECTION IV NORMAL PROCEDURES I NOTE I MOONEY M20R Plan descents to arrive at pattern altitude on downwind leg for maximum fuel efficiency and minumum aircraft noise. -CAUTION- DO NOT fly in YELLOW ARC speed range unless the air is smooth. NORMAL DESCENT - GEAR DOWN I Seats, Seat Belts/Shoulder Harness Wing Flaps . . . . Airspeed. . . . . Landing Gear · Throttle Propeller Mixture . . . . Cylinder Head Temperature (CHT) Airspeed . ADJUST AND SECURE . . . UP DECELERATE to 140 KIAS . . DOWN Keep CHT in Green Arc . . . . . 2400 RPM Peak EGT (Monitor as descent progresses) . . Monitor {250° F (121 C) min) 165 KIAS or LESS . I NOTE I Using landing gear as a descent aid will result in a steeper descent rate (greater altitude loss per horizontal distance traveled). IAPPROACH FOR LANDING I -CAUTION- The airplane must be within allowable weight and balance envelope for landing (REF. SECTION VI) . It will require a minimum of one hour ot flight before a permissable landing weight Is attained when takeoffs are made at maximum gross weight. If landing at a weight exceeding maximum landing weight (3200 Lbs.)(1452 Kgs.) Is required , see OVERWEIGHT LANDING PROCEDURE, SECTION Ill . Seats, Seat Belts/Shoulder Harness . ADJUST AND SECURE Internal/External lights . Landing Gear Mixture . Propeller. . . Fuel Boost Pump Switches Fuel Selector . Wing Flaps . AS DESIRED . . • . EXTEND below 140 KIAS (Check Gear Down light ON-Check visual indicator) FULL RICH (on final) HIGH RPM (on final) . OFF FULLEST TANK . . T/0 POSITION (FULL DOWN below 110 KIAS) -CAUTION- To minimize control wheel forces when entering landing configuration, timely nose-up trimming is recommended to counteract nose down pitching moment caused by reduction of power and/or extension of flaps. Elevator Trim Rudder Trim Parking Brake AS DESIRED AS DESIRED VERIFY OFF I NOTE I The parking brake should be rechecked to preclude partially applied brakes during touchdown. 4- 14 REV . E 9-95 ISSUED 6-94 MOONEY M20R SECTION IV NORMAL PROCEDURES IGO AROUND (BALKED LANDING) I "'CAUTION"' To minimize control wheel forces during GO-AROUND, timely nose-down trimming is recommended to counteract nose up pitching moment as power is increased and/or flaps are retracted. Power Mixture . . . . Fuel Boost Pump Switches Wing Flaps . . . Trim . Airspeed . landing Gear Wing Flaps Airspeed LANDING (NORMAL) Approach for landing Checklist Approach Airspeed Touchdown . landing Roll Brakes . (LANDING! . . FULL FORWARD/2500 RPM) . . . . Verify FULL RICH : : TAKEOFF PosiTioN ·c?~~ (After POSITIVE climb established) NOSE DOWN to reduce forces .85 KIAS RETRACT RETRACT 105 KIAS • . • . . . . . COMPLETED As sl)eclfled In SECTION V (Landing Distance) . MAIN WHEELS FIRST (aligned w/ runway) . . . . . LOWER nose wheel gently . . . . • .