Mooney M20R - Ovation Manual

Mooney M20R - Ovation is a powerful, high-performance aircraft that's perfect for both private and business travel. With a maximum speed of 235 knots and a range of over 1,000 nautical miles, it can quickly and efficiently transport you to your destination. The Ovation is also equipped with a variety of advanced avionics and safety features, making it a great choice for pilots of all experience levels.

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MOONEY

M2OR

SECTION I

GENERAL

TITLE PAGE

THREE VIEW

INTRODUCTION

1-2

1-3

DESCRIPTIVE DATA

ENGINE

PROPELLER

FUEL

OIL

LANDING GEAR

MAXIMUM CERTIFICATED WEIGHTS

STANDARD AIRPLANE WEIGHTS

CABIN & ENTRY DIMENSIONS

BAGGAGE SPACE AND ENTRY DIMENSIONS

SPECIFIC LOADINGS

IDENTIFICATION PLATE

1-3

1-4

1-5

SYMBOLS, ABBREVIATIONS & TERMINOLOGY

METEOROLOGICAL TERMINOLOGY

WEIGHT & BALANCE TERMINOLOGY

1-5

GENERAL AIRSPEED TERMINOLOGY & SYMBOLS

ENGINE CONTROLS & INSTRUMENTS TERMINOLOGY . . .

1-5

ENGINE POWER TERMINOLOGY

AIRPLANE PERFORMANCE & FLIGHT PLANNING TERMINOLOGY .

1-6

1-7

1-8

MEASUREMENT CONVERSION TABLES 1-8

ISSUED 11 - 99 1 - 1

SECTION I

GENERAL

76'

(193.0 cn)

26' 9'

(815.3 cn)

6'-7 9/16'—i

(202.08

Cr,)

36' 1

(1099.8 cn)

(254 cm)

MOONEY

M2OR

•

1 - 2

9' 2

(279.4 cn)

FIGURE 1 - 1 THREE VIEW - M2OR

IS/N 29-0183, 29-0200 THRU 29-TBA]

ISSUED 11 - 99

MOONEY

M2OR

SECTION I

GENERAL

INTRODUCTION

This Operators Manual conforms to GAMA Specification No. 1 and includes both Manufacturers material and FAA APPROVED material required to be furnished to the Pilot by the applicable Federal Aviation Regulations. Section IX contains supplemental data supplied by Mooney

Aircraft Corporation.

Section I contains information of general interest to the pilot. It also contains definitions of the terminology used in this Operators Manual.

This Pilot's Operating Handbook is not designed as a substitute for adequate and competent flight instruction, knowledge of current airworthiness directives, applicable federal air regulations or advisory circulars. It is not intended to be a guide for basic flight instruction or a training manual and should not be used for operational purposes unless kept in an up to date status.

All limitations, procedures, safety practices, servicing and maintenance requirements published in this POH/AFM are considered mandatory for the Continued Airworthiness of this airplane in a condition equal to that of its original manufacture.

DESCRIPTIVE DATA

ENGINE

Number of engines .

Engine Manufacturer

Model .

Recommended TBO

Type

Number of cylinders

Displacement .

Bore .

Stroke

Compression ratio

Fuel System

Type

Make .

Fuel-Aviation Gasoline .

Accessories

Magnetos .

Ignition Harness .

Spark Plugs .

Oil Cooler

Alternator

Starter

Ratings:

Maximum Takeoff Sea Level BHP/RPM ,

• . . . . 1

Teledyne Continental Motors (TCM)

. .

. 10-550-G(6) *

2000 Hours

Reciprocating, air cooled, fuel injected

6, Horizontally opposed

550 Cu. In. (9014 cc)

. 5.25 In. (13.3 cm)

4.25 In. (10.8 cm)

. 8.5 : 1

. Fuel Injection

. TCM

10 0 octane - 100LL

Bendix - S6RN-25

Shielded/Braided

AC 273 (or equivalent) (18 m/m)

TCM Full Flow

28 Volt DC, 100 AMPS

. 24 volt DC

280/2500

PROPELLER

Number .

Manufacturer .

Model Number

Number of Blades

Diameter (MAX.)

(MIN.) .

Type . .

Governor (McCauley)

Blade Angles @ 30.0 in. Sta.:

Low.

High

* Refer to McCauley TCDS P3EA

. . 1

McCauley

2A34C241/82PGC-6 *

. 2

76 in. (193.0 cm)

75.5 in. (191.8 cm)

. . Constant Speed

Hydraulically controlled by engine oil

20.0 degrees +/- 0.5 degrees

37.5 degrees +/- 0.5 degrees or engine/propeller configuration required.

ISSUED 11 - 99

1 - 3

SECTION I

GENERAL

MOONEY

M2OR

FUEL

Minimum Fuel Grade (Color)

Total Capacity

Usable

100 LL (Blue) or 100 Octane (Green).

. 95 U.S. Gal. (359.6 Liters)

89.0 U.S. Gal. (336.9 Liters)

OIL

Oil Specification . . MHS-24( ) and as Approved by TCM. (Reference Engine Maintenance & Operators Manual)

15W50 or 20W50 All Temperatures .

Above 30 ° F (-1 ° C) Ambient Air (S.L.) .

Below 50 ° F (10 ° C) Ambient Air (S.L.)

Total Oil Capacity

Min. Oil .

Oil Filtr .

SAE 50

SAE 30, 10W30

8 Qts. (7.57 liters)

6 Qts. (5.68 liters)

Full Flow

Oil grades, specifications and changing recommendations are contained in SECTION VIII.

LANDING GEAR

TYPE:Electrically operated, fully retractable tricycle gear with rubber shock discs. The main wlwels have hydraulically operated disc brakes. The nose wheel is fully steerable 11 left to

13 right of center.

Wheel Base.

Wheel Track

79 9/16 in. (198.91 cm)

110 in (279.4 cm)

Tire Size:

Nose

Main.

Tire Pressure

Nose .

Main .

Minimum Turning Radius (No brakes applied)

Right .

Left .

5.00 x 5 (6 ply)

6.00 x 6 (6 ply)

49 PSI',

42 PSI

40 ft. (12.0 m)

48 ft. (14.4 m)

MAXIMUM CERTIFICATED WEIGHTS

Gross Weight .

Maximum Landing Weight

Baggage Area

Rear Storage Area .

Cargo (Rear Seats Folded Down)

3368 Lbs. (1528 Kg)

3200 Lbs. (1452 Kg)

120 Lbs. (54.4 Kg)

10 Lbs. (4.5 Kg)

340 Lbs. (154.2 Kg)

STANDARD AIRPLANE WEIGHTS

Basic Empty Weight .

Useful Load . .

See Page 1-8

. Varies with installed equipment.

See SECTION VI for specific airplane weight (pg. -6-5).

1 -4 REV. A 10- 03 ISSUED 11 - 99

MOONEY

M2OR

SECTION I

GENERAL

•

CABIN AND ENTRY DIMENSIONS

Cabin Width (Maximum)

Cabin Length (Maximum) .

Cabin Height (Maximum)

Entry Width (Minimum) .

Entry Height (Minimum) .

BAGGAGE SPACE AND ENTRY DIMENSIONS

Compartment Width.

Compartment Length

Compartment Height

Compartment Volume

Cargo Area (with rear seat folded down)

Entry Height (Minimum) .

Entry Width . . .

Ground to Bottom of Sill

43.5 In. (110.5 cm)

126 In. (315 cm)

44.5 In. (113 cm)

29.0 In. (73.4 cm)

35.0 In. (88.9 cm)

24 In. (60.9 cm)

43 In. (109.2 cm)

35 In. (88.9 cm)

20.9 cu. ft.

(.592 cu. m)

38.6 cu. ft.

(1.09 cu. m)

20.5 In. (52.1 cm)

17.0 In. (43.2 cm)

46.0 In. (116.8 cm)

SPECIFIC LOADINGS

Wing Loading - @ Maximum Gross Weight

Power Loading - @ Maximum Gross Weight

19.26 lbs./sq. ft.

(94 kg/sq. m)

12.03 lbs./HP

(5.46 kg/HP)

• IDENTIFICATION PLATE

All correspondence regarding your airplane should include the Serial Number as depicted on the identification plate. he 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.

SYMBOLS, ABBREVIATIONS & TERMINOLOGY

GENERAL AIRSPEED TERMINOLOGY & SYMBOLS

• V a

Vie

KCAS

KIAS

KTAS

GROUND SPEED - Speed of an airplane relative to the ground.

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.

KNOTS INDICATED AIRSPEED - The speed of an aircraft as shown on its airspeed indicator. IAS values published in this handbook assume zero instrument error.

KNOTS TRUE AIRSPEED - The airspeed of an airplane relative to undisturbed air which is the KCAS corrected for altitude and temperature.

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.

ISSUED 11 - 99 1 5

SECTION I

GENERAL

MOONEY

M2OR

GENERAL AIRSPEED TERMINOLOGY & SYMBOLS (con't.)

Vio MAXIMUM LANDING GEAR OPERATING SPEED - The maximum speed at which the landing gear can be safely extended or retracted.

Vne

Vno

VS0

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 steady-flight 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

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, abnormal 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

Demonstrated The velocity of the crosswind component for which adequate control of the airplane during takeoff and landing test was

Crosswind

Velocity actually demonstrated during certification. The value shown is not considered to be limiting. g

Service

Ceiling

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.

1 - 6 ISSUED 11 - 99

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M2OR

SECTION I

GENERAL

ENGINE CONTROLS & INSTRUMENTS TERMINOLOGY

The control used to select engine speed. Propeller

Control

Throttle

Control

Mixture

Control

The control used to select engine power by controlling MP.

CHT Gauge

Tachometer

Propeller

Governor

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 determine 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

Above ground level.

Attitude as determined 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 foot.

OUTSIDE AIR TEMPERATURE - The free air static temperature, obtained either from in-flight temperature indications or ground meteorological sources. It is expressed in °C.

The indicated attitude when Kollsman window is set to 29.92 In. Hg. or 1013.2 MB. In this handbook, altimeter instrument errors are assumed to be zero.

Actual atmospheric pressure at field elevation. Station

Pressure

WEIGHT AND BALANCE TERMINOLOGY

Arm

Basic

Empty

Weight

Center of

Gravity

(C.G.)

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.

ISSUED 11 - 99 1 - 7

SECTION I

GENERAL

MOONEY

M2OR

WEIGHT AND BALANCE TERMINOLOGY (con't.)

C.G. Arm

C.G. in

% MAC

C.G.

Limits

MAC

The extreme center of gravity locations within which the airplane must be operated at a given weight.

Mean Aerodynamic Chord.

Maximum

Weight

The maximum authorized weight of the aircraft and its contents as listed in the aircraft specifications.

Maximum The maximum authorized weight of the aircraft and its contents

Landing Weight when a normal landing is to be made.

Moment

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 product of the weight of an item multiplied by its arm.

(Moment divided by a constant is used to simplify balance calculations by reducing the number of digits.)

Reference

Datum

Station

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.

Tare

Unusable

Fuel

Usable

Fuel

Useful

Load

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 run-out test has been completed in accordance with Federal 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 (if applicable), useable fuel, passengers, and baggage.

MEASUREMENT CONVERSION TABLES

LENGTH

U. S. Customary Unit

1 inch .

1 foot

1 yard

1 mile (statute, land)

1 mile (nautical,. international)

Metric Equivalents

2.54 centimeters

0.3048 meter

0.9144 meter

1, 609 meters

1, 852 meters

AREA

U. S. Customary Unit

1 square inch

1 square foot

1 square yard.

Metric Equivalents

6.4516 sq. centimeters

929 sq. centimeters

0.836 sq. meter

1 - 8 ISSUED 11 - 99

MOONEY

M2OR

U. S. Customary Unit

1 cubic inch.

1 cubic foot

1 cubic yard

U.S. Customary

Liquid Measure

1 fluid ounce .

1 pint .

1 quart.

1 gallon

U.S. Customary

Dry Measure

1 pint .

1 quart

British imperial . .

Liquid and Dry Measure

1 fluid ounce ..

1 pint

1 quart

1 gallon

U. S. Customary Unit

(Avoirdupois)

1 grain .

1 dram .

1 ounce .

1 pound .

U.S. Customary Unit

1 PSIG

1 Inch Hg

VOLUME OR CAPACITY

SECTION I

GENERAL

Metric Equivalents

16.39 cubic centimeters

0.028 cubic meter

0.765 cubic meter

Metric Equivalents

29.573 milliliters

0.473 liter

0.946 liter

3.785 liters

Metric Equivalents

0.551 liter

1.101 liters

. Metric

Equivalents

28.412 milliliters

U. S.. .

Equivalents

0.961 U.S. . fluid ounce,

1.734 cubic inches

1.032 U.S. . dry pints,

1.201 U.S. liquid pts.,

34.678 cubic inches

1.032 U.S. . dry quarts

1201 U.S. liquid qts.,

69.354 cubic inches

1.201 U.S. .

277.420 cubic inches

WEIGHT

568.26 milliliters

1.136 liters

4.546 liters

Metric Equivalents

64.79891 milligrams

. 1.772 grams

. 28.350 grams

453.6 grams

PRESSURE

Metric Equivalents

. 6.895 KPA

3.388 KPA

25.40 mm Hg

ISSUED 11 - 99

1 - 9

SECTION I

GENERAL

1 pound/square foot

1 pound /sq. inch

1 Pound/HP .

MOONEY

M2OR

COMMON CONVERSIONS

0.488 kg/ meter square

. 2.036 inch Hg.

0.4538 kg/HP

1 - 10 ISSUED 11 - 99

MOONEY

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•

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 INTERIOR

EXTERIOR

SECTION II

LIMITATIONS

PAGE

2-2

2-3

2-4

2-5

2-6

2-7

2-8

2-11

2-15

2-16

FAA APPROVED

ISSUED 11 - 99

AIRPLANE FLIGHT MANUAL

2 - 1

SECTION II

LIMITATIONS

MOONEY

M2OR

INTRODUCTION

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.

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 M2OR.

•

NOISE LIMITS

The certificated noise level for the Mooney M2OR, S/N 29-0183, 29-0200 thru 29-TBA, at 3368 lbs. (1528 Kg.) maximum weight is 77.3 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

2 - 2

FAA APPROVED

ISSUED 11 - 99

SECTION II

LIMITATIONS

MOONEY

M2OR

Airspeed limitations and their operational sig nificance are shown in Figure 2-1. This calibration assumes zero instrument error.

AIRSPEED LIMITATIONS

•

V / SPEED KCAS/KIAS REMARKS

VNE Never Exceed

Speed

196/195 Do not exceed this speed in any operation.

VNO Maximum

Structural

Cruising

Speed

175/174 Do not exceed this speed except in smooth air, and then only with caution.

VA Maneuvering Speed at: lbs. /Kg.

2232/1012

2430/1102

3300/1497

3368/1528

104/103

109/108

127/126

128/127

Do not make full or abrupt control movement above this speed.

•

VFE

VLE

Maximum Flap

Extended Speed

111/110

Maximum Landing 166/165

Gear Extended

Speed

Do not exceed this speed with flaps in full down position.

Maximum speed at which the aircraft can be safely flown with the landing gear extended.

VLO Max. Speed for 141/140 Max. speed at

(EXT) Gear Extension which the landing gear can be safely extended.

Max. Speed for

Gear Retraction

107/106 Maximum speed at which the landing gear can be safely retracted.

RET)

133/132 Do not exceed this speed with pilot window open.

Maximum Pilot

Window Open

Speed

•

FAA APP ROVED

ISSUED 1 1-99

FIGURE 2-1 AIRSPEED LIMITATIONS

AIRPLANE FLIGHT MANUAL

2 - 3

SECTION II

LIMITATIONS

MOONEY

M2OR

AIRSPEED INDICATOR MARKINGS

Airspeed indicator markings, their color code and operational significance are shown in Figure

2-2.

MARKING IAS VALUE or RANGE

(KIAS)

SIGNIFICANCE

•

White Arc

(Flap

Operating Range)

59-110 KIAS Lower limit is maximum weight Vso in landing configuration. Upper limit is maximum speed permissable with flaps extended.

Green Arc

(Normal Operating Range)

66-174 KIAS

174-195 KIAS

Lower limit is maximum weight Vs with flaps retracted.

Upper limit is maximum structural cruising speed.

Operations must be conducted with caution and only in smooth air.

Yellow Arc

(Caution

Range)

195 KIAS Maximum speed for all operations.

Radial

Red Line

FIGURE 2-2 AIRSPEED INDICATOR MARKINGS

AIRPLANE FLIGHT MANUAL

2 - 4

FAA APPROVED

ISSUED 11 - 99

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SECTION II

LIMITATIONS

POWER PLANT LIMITATIONS

Number of Engines .

Engine Manufacturer

Engine Model Number

. 1

Teledyne Continental Motors (TCM)

10-550-G(6) *

Engine Operating Limits for Takeoff and Continuous

Maximum Continuous Power .

Maximum Continuous RPM .

Transient RPM Limit

Maximum Cylinder Head Temperature

Maximum Oil Temperature

Minimum Oil Temperature-Takeoff.

Recommended Cruising Temperature

Oil Pressure

Normal Operating

Minimum (IDLE ONLY) .

Operations:

. 280 BHP

2500 RPM

2600 RPM

460° F (237.7° C)

. 240° F (115° C)

. . 75° F (24° C)

170°F-200°F (76°C-93°C)

30-100 PSI

10 PSI

Oil Specification .

Fuel Grade (Color) .

Number of Propellers .

Propeller Manufacturer

Propeller Hub/Blade Model Number

MHS-24( ), MHS-25( ) and TCM Approved oils

100LL (Blue) ** or 100 octane (Green) **

. .

McCauley

2A34C241/82PGC-6 ***

2 Number of Blades

Propeller Diameter: McCauley

Min .

Max

75.5 In. (191.8 cm)

76 In. (193.0 cm)

McCauley

Propeller Blade Angles @ 30.0 In. sta.:

Low . . . .

High

20.0 Degrees +/- 0.5 Degrees

37.5 Degrees +/- 0.5 Degrees

Propeller Operating Limits (McCauley) 2500 RPM

* Refer to MAC TCDS 2A3 for engine configuration required.

** 100LL fuel is calibrated at 5.82 Ib/gal(.69 Kg/liter)

100 octane fuel is calibrated at 6.0 lb.gal. (.72 Kg/liter)

*** Refer to MAC TCDS 2A3 & McCauley TCDS P3EA for propeller configuration required.

FAA APPROVED

ISSUED 11 - 99

AIRPLANE FLIGHT MANUAL

2 - 5

SECTION II

LIMITATIONS

POWER PLANT INSTRUMENT MARKINGS

MOONEY

M2OR

INSTRUMENT REDLINE

MINIMUM

LIMIT

GREEN ARC

NORMAL

OPERATING

YELLOW

ARC

REDLINE

MAXIMUM

LIMIT

Tachometer 600 RPM

No Redline

Cylinder

Head

Temperature

2200-2500

RPM

250-460 ° F

(121 - 215.5

° C)

2500 RPM

460 °

(237.7

° C)

Oil

Temperature

No Redline 170 -240 ° F

(76.6 - 104 ° C)

100 - 170 ° F

(37.7-76.6

° C)

240 ° F

(115.5

° C)

Oil

Pressure

10.0 PSI

(IDLE ONLY)

30-100 PSI

Exhaust

Gas

Temperature

10 - 30 PSI 100 PSI

1400-1450 ° F

(760-788 ° C)

(BLUE ARC = recommended climb)

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.

AIRPLANE FLIGHT MANUAL

2 - 6

FIGURE 2 - 3 POWER PLANT INSTRUMENT MARKINGS

FM APPROVED

ISSUED 11 - 99

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SECTION II

LIMITATIONS

FUEL LIMITATIONS

111111111111111111I

// WARNING //

///////////////////

Takeoff maneuvers when the selected fuel tank contains less than

12 gallons (45.4 liters) of fuel have not been demonstrated.

NOTE

Each fuel quantity gauge is calibrated to read zero only in coordinated level flight when remaining 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)

Total Fuel .

47.5 U.S. Gal. each (179.8 liters)

95 U.S. Gal.(359.6 liters)

Usable Fuel:

Unusable Fuel:

89 U.S. Gal. (336.8 liters)

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 is 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 within the fuel system.

WEIGHT LIMITS

Maximum Weight - Takeoff .

Maximum Weight - Landing . .

Maximum Weight in Baggage Compartment

. .

3368 lb. (1528 Kg.)

3200 lb. (1452 Kg)

. . . . 120 lb.

(54.4 Kg.) @ Fus. Sta. 101.5(253.7 cm)

Maximum Weight in Rear Storage Area . . . . 10 lb.

(4.54 Kg.) @ Fus. Sta. 131.0(297.5 cm)

Maximum Weight in Cargo Area (Rear seats folded down) . . 340 lbs.

(154.2 KG) @ Fus. Sta. 767(176.8 cm)

CENTER OF GRAVITY LIMITS (GEAR DOWN)

Most Forward .

Intermediate ForWard

Forward Gross

Aft Gross

MAC (at Wing Sta. 94.85)(241 cm)

Fus. Sta. 41.0 IN. (104.1 cm) @ 2430 LB. (1102 Kg)

. . . 16.79% MAC

Fus. Sta. 44 IN.(111.7 cm) @ 3300 lb. (1497 Kg)

. . 21.7% MAC

Fus. Sta. 46.0 IN. (116.8 cm) @ 3368 lb (1528 Kg)

. . 24.98% MAC

Fus. Sta. 51.0 IN(129.5 cm) @ 3368 lb. (1528 Kg)

. 33.18% MAC

61.00 In.

Datum (station zero) is 13 inches (32.5 cm) aft of the center line of the nose gear trunion attach/pivot bolts.

FAA APPROVED

ISSUED 11 - 99

AIRPLANE FLIGHT MANUAL

2 - 7

SECTION II

LIMITATIONS

MOONEY

M2OR

MANEUVER LIMITS

This airplane must be operated as a Normal Category airplane. Aerobatic maneuvers, including spins, are prohibited.

I NOTE I

Up to 500 foot altitude loss may occur during stalls at maximum weight.

FLIGHT LOAD FACTOR LIMITS

Maximum Positive Load Factor

Flaps Up . . .

Flaps Down (33 Degrees)

Maximum Negative Load Factor

Flaps Up .

Flaps Down .

+3.8 g.

+2.0 g.

-1.5 g.

.0.0 g.

FLIGHT CREW

Pilot . . . .

Maximum passenger seating configuration

One

Three

OPERATING LIMITATIONS

When aircraft is not equipped with an approved oxygen system and flight operations above

12,000 ft. are desired, this airplane must be, (1) equipped with supplemental oxygen in accordance with FAR 23.1441, (2) operate in accordance avionics in accordance with FAR 91 or FAR 135. with FAR 91.211 and (3) equipped with

ALTERNATOR OPERATING LIMITATIONS IS 94 AMPS.

AVOID CONTINUOUS OPERATION BELOW 2100 RPM AT MANIFOLD PRESSURES

GREATER THAN 21 INCHES HG.

KINDS OF OPERATION LIMITS

This is a Normal Category airplane certified for VFR/IFR day or night operations when the required 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 applicable operating rules requirements for each kind of operation are met.

OPERATIONS IN KNOWN ICING CONDITIONS ARE PROHIBITED.

Autopilot Limitations

See SECTION IX.

KINDS OF OPERATION EQUIPMENT LIST

The following equipment was approved during Type Certification and must be installed and operable 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.

•

FAA APPROVED

ISSUED 11 - 99

AIRPLANE FLIGHT MANUAL

2 - 8

MOONEY

MODEL M2OR

•

NIGHT

SECTION II

LIMITATIONS

KINDS OF OPERATION EQUIPMENT LIST

VFR DAY *

VFR NIGHT

IFR DAY

IFR

SYSTEM or COMPONENT

1

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 **. .

OXYGEN MASK FOR EACH OCCUPANT **

POSITION LIGHTS

STROBE LIGHTS (ANTI-COLLISION) .

1 1 1 1

2

2 2 2

1 1 1

2 2 2 2

1

3

Equipment must be installed and operable for all operations.

** If inoperative for unoccupied seat(s), seat(s) must be placarded:

"DO NOT OCCUPY"

*** Only required when the operating rules require use of oxygen.

FAA APPROVED

ISSUED 11 - 99

AIRPLANE FLIGHT MANUAL

2 - 9

SECTION II

LIMITATIONS

KINDS OF OPERATION EQUIPMENT LIST (con't.)

SYSTEM or COMPONENT (con't.)

MOONEY

MODEL M2OR

NIGHT

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)

BATTERIES . .

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 ****

Equipment must be installed and operable for all operations

**** When required by the appropriate regulations.

AIRPLANE FLIGHT MANUAL

2 - 10

FM APPROVED

ISSUED 11 - 99

MOONEY

M2OR

SECTION II

LIMITATIONS

DECALS AND PLACARDS

CABIN INTERIOR

•

The following placards are relevant to proper operation of the airplane and must be installed inside the cabin at the locations specified.

OPERATING LIMITATIONS

THE MARKINGS AND PLACARDS INSTALLED IN THIS AIRPLANE CONTAIN

OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN

OPERATING THIS AIRPLANE IN THE NORMAL CATEGORY. THIS AIRPLANE

IS CERTIFIED FOR DAY AND NIGHT VFR/IFR OPERATION WHEN THE

REQUIRED EQUIPMENT IS INSTALLED AND OPERATIONAL. FLIGHT INTO

KNOWN ICING CONDITIONS IS PROHIBITED.NO AEROBATIC MANEUVERS,

INCLUDING SPINS ARE APPROVED. OTHER OPERATING LIMITATIONS WHICH

MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THIS

CATEGORY ARE CONTAINED IN THE FLIGHT MANUAL.

MANEUVERING SPEED (3368 LBS.). 127 KIAS: (2600 LBS.). 111 KIAS.

ON LEFT SIDE PANEL

IN PILOT'S VISION

EMERGENCY MANUAL GEAR EXTENSION

1. PULL LANDING GEAR ACTUATOR CIRCUIT BREAKER.

2. PUT GEAR SWITCH IN GEAR DOWN POSITION.

3. PUSH RELEASE TAB FORWARD AND LIFT UP RED HANDLE.

4. PULL 7-HANDLE STRAIGHT UP (12 TO 20 INCHES).

5. ALLOW 7-HANDLE TO RETURN TO ORIGINAL POSITION.

6. REPEAT UNTIL GEAR DOWN LIGHT COMES ON (12 TO 20 PULLS). IF

TOTAL ELECTRICAL FAILURE-SEE MECHANICAL INDICATOR.

CAUTION

1, TURN OFF STROBE LITES WHEN TAXIING NEAR OTHER ACFT OR

FLYING IN FOG OR IN CLOUDS. STD POSITION LITES MUST BE USED

FOR ALL NIGHT OPERATIONS.

2. IN CASE OF FIRE TURN OFF CABIN HEAT.

3. 00 NOT SCREW VERNIER CONTROLS CLOSER THAN

FACE.

1/8" FROM NUT

150056-103?

CHECK LIST

CONTROLS

FUEL

RUN-UP

PROP

INSTRUMENTS WING FLAPS

TRIM SEAT LATCH

BELT /1-IA RNESS

DOOR

WINDOW

ALT AIR

PARK BRAKE

MIXTURE

CONDUCT RUDDER AND ELEVATOR TRIM CHECK PRIOR

TO FLIGHT. SEE PILOT'S OPERATING HANDBOOK

FUEL WING FLAPS

MIXTURE

PROP

PARK BRAKE

150056

1030

INSTRUMENT LIGHTS

GLARE

SHIELD PANEL

LOWER LEFT

SIDE RADIO

PANEL

CONSOLE

150056-1011

FAA APPROVED

ISSUED 11 - 99

AIRPLANE FLIGHT MANUAL

2-11

SECTION II

LIMITATIONS

LL11 %\ F'

O O 1,

(-; /

CONSOLE

ABOVE &

BELOW

SWITCH

In NJ

1 U;2 ■ •,A

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.

FLOORBOARD

BETWEEN

SEATS

ON RADIO PANEL,

ADJACENT TO ELT

SWITCH

•.,

• I

• i( )N

.11.1

I WY' rs

I 1, i

WHEN APPLICABLE ELT

UNIT IS INSTALLED

MOONEY

M2OR

FWD END OF

REAR SEAT

BOTTOM

STRUCTURE

150085-037 [360 ° DECAL]

AIRPLANE FLIGHT MANUAL

2 - 12 REV. B 4 - 05

FAA APPROVED

ISSUED 11 - 99

SECTION II

LIMITATIONS

•

MOONEY

M2OR

PUSH

GR SAFETY

BY PASS

GEAR UP

106 KIAS

UPPER

CTR

INSTR.

PANEL

ABOVE

INSIDE

BAGGAGE

DOOR

HANDLE

AUXILIARY EXIT

DO NOT OPEN IN FLIGHT

TO OPEN

1. PULL OFF COVER

2. PULL CABLE EXTRACTING LOCK PIN

3. ACTUATE HANDLE

TO CLOSE

I. STORE HANDLE

2. INSERT LOCK PIN

3. INSTALL COVER

4. CLOSE AND LATCH DOOR USING

OUTSIDE HANDLE

5. LOCK DOOR

150056-1045

GEAR DOWN

140 KIAS

GEAR EXTD

165 KIAS

150056-1006

LWR INSTR PNL.,BELOW

CONTROL WHEEL SHAFT

PULL FOR

ALTERNATE

STATIC SOURCE

150055-1009

GO AROUND

150056-1019

LOWER FLT PANEL

NEXT TO THROTTLE

[OPTIONAL]

•

DO NOT OPEN

ABOVE 132 KIAS

BELOW

PILOT'S

STORM

WINDOW

Its

COMPASS

CALIBRATE WITH

150056-1031

ON MAGNETIC

CORRECTION

RADIO ON aa

150056-1016

AROUND EACH OXYGEN

COMPASS

OUTLET ON OVERHEAD

PANEL

T ROT T L E

PUSH INCREASE

ABOVE

150056— 100

EACH

CONTROL

ON LWR

PROP

PUSH INCREASE

150056-1007

INSTR.

PANEL

CONSOLE ON CONTROL KNOB

MIXTURE

PUS H FR' I C

1500 5 6 - 1 o 1 0

ALT AIR

PULL ON

FAA APPROVED

ISSUED 11 - 99

917033-11

AIRPLANE FLIGHT MANUAL

2-13

SECTION II

LIMITATIONS

MOONEY

M2OR

WARNING

DO NOT EXCEED 10 LBS (4.5 Kg) IN THIS COMPARTMENT

USE FOR STOWAGE OF LIGHT SOFT ARTICLES ONLY

SEE AIRCRAFT LOADING SCHEDULE DATA

FOR BAGGAGE COMPARTMENT ALLOWABLE

150056-1044

BAGGAGE COMPARTMENT

ON HAT RACK SHELF

TOP OF BAGGAGE DOOR JAMB

WARNING

DO NOT EXCEED 120 LBS

(54.4 Kg) IN THIS COMPARTMENT

SEE AIRCRAFT LOADING SCHEDULE DATA

FOR BAGGAGE COMPARTMENT ALLOWABLE

150056-1046

INSTRUMENT PANEL

SPEEDBRAKE EQUIPPED: FOR OPERATING INSTRUCTIONS

AND LIMITATIONS SEE FAA APPROVED AFM SUPPLEMENT

OR PILOT'S OPERATING HANDBOOK.

(OPTIONAL)

-4057

ON UPPER INSTRUMENT PANEL

N)0000(

FLOORBOARD-

BETWEEN

SEATS

BETWEEN SEATS - ON

EMERGENCY GEAR RELEASE

EXTENSION HANDLE

PUSH TO RELEASE

150056-1040

LIGHT

SWITCH

BAGGAGE DOOR

FRAME

GEAR

DOWN

150056-1015

150056-1043

14 VOLTS

3 AMPS MAX.

5 A INTERMITTENT

RT. RADIO PNL.

ADJACENT TO AUX.

<--PWR. PLUG

150056-1012

FLOORBOARD - FWD OF

CO-PILOT SEAT--->

AIRPLANE FLIGHT MANUAL

2-14

150056-1036

FAA APPROVED

ISSUED 11 - 99

•

MOONEY

M2OR

SECTION II

LIMITATIONS

"AVOID CONTINUOUS OPERATION BELOW 2100 RPM AT

MANIFOLD PRESSURES GREATER THAN 21 INCHES HG."

ON INSTRUMENT PANEL, ADJACENT TO TACHOMETER

NOTE: USED ONLY WHEN McCAULEY PROPELLERS INSTALLED

FUSELAGE INTERIOR

CAUTION

THIS DOOR SHALL BE

REMOVED AND STOWED

WHEN FIELD TEMPERATURES

EXCEED 30"F (-1'C)

The following placards must be installed inside the fuselage at the locations specified.

CAUTION

WINTERIZATION KIT INSTALLED

150056-2024

ON KIT SLIDING DOOR AT OIL

COOLER.

IF KIT INSTALLED

MAIN A N

WHEN OPERATING AT

TEMPERATURES ABOVE 30°F, (-1 °C),

REMOVE OIL COOLER DOOR.

150056-2002

ON OIL FILLER DOOR

IF KIT INSTALLED

HYDRAULIC

OIL

RESERVOIR

150056 - 20 1

6

8 - VC I_ I (3

C \I I Y

••.• •

• ■■

JSE /1\MA - Oi ∎ S

°N 1

SEE PILOT'S OPERATING

HANDBOOK I- OR

11 I 'NC; PIRTSSURF

)(i- 20"

BACKSIDE OF

AUX. PWR.

RECEPTACLE

DOOR

INSIDE OXYGEN

FILLER DOOR

INSIDE ENGINE OIL FILLER DOOR

ENGINE (X

NSTALL.13

IN THIS ENGINE IS

NEX

(

,L 1 S - CR715rl

PENC,I)

•

50056- 20C

FM APPROVED

ISSUED 11

- 99 REV. B 4 - 05

ON BATTERY

ACCESS

PANELS

L/H & R/H

I HON-.

BAT S

USI

ALI )

Cr:

:

; HI s:•;:f

5 )0 '

AIRPLANE FLIGHT MANUAL

2-15

SECTION II

LIMITATIONS

MOONEY

M2OR

EXTERIOR

The following placards must be installed on the exterior of the aircraft at the locations specified.

\O' STIP

150056-9006

ON INBOARD END OF FLAP,

WING LEADING EDGES AND

WING AHEAD OF FLAPS

UNDERSIDE OF WING (2 PLCS)

& AFT OF L/H COWL FLAP (1PLC)

HOIST POINT

150056-2012

DO \OT PAS

150056-2019

HORIZ. STAB. L/E

RUDDER T/E (BOTH SIDES)

UNDER TAILCONE

AFT OF WING T/E

PITOT DRAIN

150056-2011

UNDER LEFT WING

NEAR FUSELAGE

L/E

STATIC DRAIN

150056

2014

GASCOLATOR

DRAIN

150056-2010

UNDER WING NEAR

SUMP DRAINS

FUEL DRAIN

UNDER FUSELAGE RT. SIDE

AFT OF NOSE WHEEL WELL

150056-2013

AIRPLANE FLIGHT MANUAL

2-16

FAA APPROVED

ISSUED 11 - 99

MOONEY

M2OR

SECTION II

LIMITATIONS

ON MAIN LDG GEAR TIRE ;3 .3.7SSuRE L2

DOOR

(2.95 Ke/c,- , '

T , R; PRESSURE: 4

PS.

TONING

130056- 2022

Kq/cm

;

LANDING GEAR DOOR

:Nr,t6

,r,a.

ON NOSE

LANDING

GEAR

LEG ASSY

ON NOSE

LANDING

GEAR

SPINDLE

ASSY.

DO NOT [El

LI)

TOWING LMITS

is t

LWR UH WING PANEL

OUT/BD OF HOIST PT.

MAGNETIC AZIMUTH

TRANSMITTER

LOCATED INSIDE THIS INSPECTION

COVER. USE ONLY NON—MAGNETIC

SCREWS FOR COVER INSTALLATION.

—6050

USED WITH KING FLIGHT

CONTROL SYSTEMS ONLY uri

-100 (cRaN) OR

1 OOLL (IT ) MIN OCT

44.5 U.S. CAL. USABLE-

1 68.5 t I TERS LiSAI31 F

ON BOTH FUEL FILLER CAPS

150056 - 2008

FAA APPROVED

ISSUED 11 - 99 REV. B 4 - 05

AIRPLANE FLIGHT MANUAL

2 - 17

•

MOONEY

M2OR

TITLE

INTRODUCTION

AIRSPEEDS FOR EMERGENCY OPERATIONS

SECTION III

EMERGENCY PROCEDURES

PAGE

3-3

3-4

ANNUNCIATOR PANEL WARNING LIGHTS 3-5

ENGINE

POWER LOSS - DURING TAKEOFF ROLL

POWER LOSS - AFTER LIFTOFF

POWER LOSS - IN FLIGHT (RE-START PROCEDURES)

POWER LOSS - PRIMARY ENGINE INDUCTION AIR

SYSTEM BLOCKAGE

ENGINE ROUGHNESS

HIGH CYLINDER HEAD TEMPERATURE

HIGH OIL TEMPERATURE

LOW OIL PRESSURE

LOW FUEL PRESSURE

ENGINE DRIVEN FUEL PUMP FAILURE

FUEL VAPOR SUPPRESSION (FLUCTUATING FUEL PRESSURE)

•

FIRES

ENGINE FIRE - DURING START ON GROUND

ENGINE FIRE - IN FLIGHT

ELECTRICAL FIRE - IN FLIGHT (SMOKE IN CABIN)

EMERGENCY DESCENT PROCEDURE

GLIDE

3-10

3-6

. 3-6

3-7

3-8

3-9

FORCED LANDING EMERGENCY

GEAR RETRACTED OR EXTENDED

OVERWEIGHT LANDING PROCEDURES

•

SYSTEMS EMERGENCIES

PROPELLER

FUEL

ELECTRICAL

LANDING GEAR

VACUUM

OXYGEN

ALTERNATE STATIC SOURCE

3-11

3-12

3-13

1 ISSUED 11 99

SECTION III

EMERGENCY PROCEDURES

TABLE OF CONTENTS (con't)

TITLE

UNLATCHED DOORS IN FLIGHT

ICING

EMERGENCY EXIT OF AIRCRAFT

SPINS

OTHER EMERGENCIES

MOONEY

M2OR

PAGE

3-14

3-15

3-16

3 2

ISSUED 11 - 99

MOONEY

M2OR

SECTION III

EMERGENCY PROCEDURES

INTRODUCTION

This section provides the recommended procedures to follow during adverse flight conditions. 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 airplane.

As it is not possible to have a procedure for all types of emergencies that may occur, it is the pilot's responsibility to use sound judgement based on experience and knowledge of the aircraft to determine the best course of action. Therefore, it is considered mandatory that the pilot read the entire manual, especially this section before flight.

When applicable, emergency procedures associated with optional equipment such as Autopilots are included in SECTION IX.

NOTE I

All airspeeds in this section are indicated (IAS) and assume zero instrument error unless stated otherwise.

ISSUED 11 - 99 3 - 3

3 - 4

SECTION III

EMERGENCY PROCEDURES

AIRSPEEDS FOR EMERGENCY OPERATIONS

MOONEY

M2OR

CONDITION . RECOMMENDED SPEED

ENGINE FAILURE AFTER TAKEOFF

Wing Flaps UP

Wing Flaps DOWN

BEST GLIDE 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

Flaps DOWN

PRECAUTIONARY LANDING ABOVE 3200 LBS

Flaps DOWN . .

EMERGENCY DESCENT (GEAR UP)

Smooth Air .

Turbulent Air

3368 lb/1528 kg

3300 lb/1497 kg

2430 lb/1102 kg

2232 lb/1012 kg

EMERGENCY DESCENT (GEAR DOWN)

Smooth Air .

Turbulent Air

3368 lb/1528 kg

3300 lb/1497 kg

2430 lb/1102 kg

2232 lb/1012 kg

85 KIAS

80 KIAS

91.5 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

108 KIAS

103 KIAS

•

ISSUED 11 - 99

MOONEY

M2OR

SECTION III

EMERGENCY PROCEDURES

ANNUNCIATOR PANEL WARNING LIGHTS

WARNING LIGHT FAULT & REMEDY

GEAR UNSAFE 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.

LEFT or RIGHT FUEL RED light indicates 6 to 8 gals.(23 to 30.3 liters) of usable fuel remain in the respective tanks.

Switch to fuller tank.

SPEED BRAKE AMBER light indicates Speed Brakes are acti- vated.

ALT AIR

PROP DE-ICE

AMBER light indicates alternate induction air door is open.

BLUE light indicates power applied to De-Ice boots

PITOT HEAT BLUE light indicates power is applied to heater.

(Some Foreign NC - AMBER light indicates power is NOT applied to heater.)

HI/LO VAC (Flashing)

HI/LO VAC (Steady)

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 should be checked and/or adjusted as soon as practicable.

ALT VOLTS

(Flashing)

ALT VOLTS

(Steady)

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".

START POWER RED light indicates switch or relay is engaged and starter is energized. Flight should be terminated as soon as practicable. Engine damage may result. This is normal indication during engine start.

STBY VAC

REMOTE RNAV

BOOST PUMP

AMBER light indicates stand-by vacuum pump is ON.

OPTIONAL - "TRIM FAIL" LEGEND USED

WHEN KFC-225 IS INSTALLED. MAY BE

BLANK FOR OTHER SYSTEMS.

BLUE light indicates power to auxiliary fuel boost pump.

ISSUED 11 - 99 3 - 5

SECTION III

EMERGENCY PROCEDURES

MOONEY

M2OR

ENGINE

POWER LOSS - DURING TAKEOFF ROLL

Throttle .

Brakes

Fuel Selector .

Magneto/Starter Switch

Master Switch .

. . CLOSED

AS REQUIRED TO STOP AIRCRAFT

. OFF

OFF

POWER LOSS - AFTER LIFTOFF

Airspeed .

Throttle

Fuel Selector.

. .

. . 85 KIAS (Flaps UP)

80 KIAS (Flaps TAKEOFF/DOWN)

KEEP THE AIRCRAFT UNDER CONTROL - then:

Magneto switch

Mixture .

Propeller

LOW Boost Pump Switch

SELECT OTHER TANK

FULL FORWARD

. Verify on BOTH

FULL FORWARD

ON - to attempt re-start

If Engine Quits - then:

HIGH BOOST Pump (guarded switch) . ON - to attempt re-start

LAND AS SOON AS PRACTICABLE; CORRECT MALFUNCTION PRIOR TO NEXT FLIGHT.

If engine does not re-start, proceed to FORCED LANDING EMERGENCY.

/////////////////////

///WARNING///

/////////////////////

Engine may run rough due to overrlch mixture. Lean mixture until engine operates smoothly.

I NOTE

If high power is required, mixture may require enrichening.

POWER LOSS - IN FLIGHT (RE-START PROCEDURES)

Airspeed .

Fuel Selector.

LOW Boost Pump Switch .

Throttle

Propeller

Mixture .

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

A8 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 (Initially) then advance slowly toward RICH until engine starts.

If engine does not re-start after several attempts establish best glide speed (Refer to Maximum Glide Distance Chart) and proceed to FORCED LANDING EMERGENCY.

After engine re-start:

Throttle .

Propeller .

Mixture . .

ADJUST as required

RELEAN as required for power setting

. OFF

NOTE I

If engine fails when HIGH BOOST pump is turned OFF, suspect engine driven fuel pump failure. Proceed to ENGINE DRIVEN FUEL PUMP FAILURE.

3 6 ISSUED 11 - 99

MOONEY

M2OR

SECTION III

EMERGENCY PROCEDURES

LAND AS SOON AS PRACTICABLE; CORRECT MALFUNCTION PRIOR TO NEXT FLIGHT.

— CAUTION—.

Should engine excessively cool during engine out, care should be exercised during re-start to avoid excessive oil pressure. Allow engine to warm up.

OPERATING THE ENGINE AT TOO HIGH AN RPM BEFORE REACHING

MINIMUM OIL TEMPERATURES MAY CAUSE LOSS OF OIL PRESSURE.

POWER LOSS - PRIMARY ENGINE INDUCTION AIR SYSTEM BLOCKAGE

Blockage of the primary engine induction air system may Ige experienced as a result of flying 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 travel inside inlet duct 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 automatically 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 alternate induction system is displayed in the cockpit by the illumination of the ALT AIR light in the main annunciator panel. When operating on the alternate air system, available 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 .

Manifold Pressure .

Verify OPEN (annunciator light ON)

1 - 2 inches less than normal, due to warm induction air

I NOTE I

Mixture

Flight

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 . to maintain desired cruise power setting (Ref.SECTION V)

. .

. INCREASE as desired

INCREASE as required

RELEAN to desired EGT

CONTINUE - request altitude with warmer air, if able.

In the unlikely event that a total power loss, due toprimary 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 .

BEST GLIDE SPEED

Manually OPEN

. ON

Full FORWARD

FULL FORWARD

AS REQUIRED to restore power

. Verify on BOTH

After engine re-start:

Throttle . .

Propeller .

Mixture .

LOW Boost Pump Switch.

. . .

ADJUST as required

RELEAN as required for power setting

(Refer to power charts - SECTION V)

. OFF

ISSUED 11 - 99 3 - 7

SECTION III

EMERGENCY PROCEDURES

MOONEY

M2OR

If engine does not re-start after several attempts, maintain best glide speed & proceed to

FORCED LANDING EMERGENCY.

ENGINE ROUGHNESS

Engine instruments .

Fuel Selector .

Mixture . . .

Magneto/Starter Switch .

. . .

. .

. CHECK

OTHER TANK

READJUST for smooth operation

. Select R or L or BOTH

If roughness disappears on single magneto, monitor power and continue on selected magneto.

///////////////////

// WARNING //

///////////////////

The engine may quit completely when one magneto is switched off if the other magneto is faulty. If this happens, close throttle to idle and mixture to idle cutoff before turning magnetos ON to prevent a severe backfire. When magnetos have been turned back ON, proceed to POWER LOSS - IN FLIGHT.

Severe roughness may be sufficient to cause propeller separation. Do not continue to operate a rough engine unless there is no other alternative.

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

I NOTE I

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

Power

INCREASE

REDUCE

PREPARE FOR POSSIBLE ENGINE FAILURE IF TEMPERATURE CONTINUES HIGH.

LOW OIL PRESSURE

Oil temperature and pressure gauges

Pressure below 10 PSI .

Monitor

EXPECT ENGINE FAILURE, proceed to FORCED LANDING EMERGENCY.

ENGINE

DRIVEN FUEL PUMP FAILURE

///////////////0

// WARNING //

When operating engine

0/0/0/0 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 auxilliary fuel pump

HIGH BOOST ON will require smooth operation of engine controls and corresponding mixture change when throttle is repositioned or engine speed a changed. When retarding throttle or reducing engine speed, adjust mixture to prevent engine power loss from an overrich condition. Enrich mixture when opening throttle or increasing engine speed to prevent engine power loss from a lean condition. Always lean to obtain a smooth running engine.

3 8 ISSUED 11 - 99

MOONEY

M2OR

SECTION III

EMERGENCY PROCEDURES

The following procedure should be followed when a failed engine driven fuel pump is suspected:

HIGH BOOST Pump (guarded switch) .

Throttle . . . .

. . . . ON

CRUISE Position or as required for engine operation

Mixture ADJUST for smooth engine operation.

LAND AS SOON AS PRACTICABLE & CORRECT MALFUNCTION.

FUEL VAPOR SUPPRESSION (Fluctuating Fuel Flow)

Low Fuel Boost Pump Switch .

Engine operation ..

Low Fuel Boost Pump Switch

. . ON to clear vapors

. MONITOR

OFF - (If condition still exists, REPEAT PROCEDURE).

FIRES

ENGINE FIRE - DURING START ON GROUND

Magneto/Starter Switch

If engine starts:

Power.

Engine

If engine does NOT start:

Magneto/Starter Switch .

Mixture .

Low Fuel Boost Pump Switch .

Throttle

Fuel Selector Valve

Magneto/Starter Switch .

Master Switch

FIRE .

CONTINUE cranking or until fire is extinguished.

1500 RPM for several minutes

SHUTDOWN; inspect for damage

CONTINUE CRANKING

IDLE CUTOFF

OFF

FULL FORWARD

OFF

. . . . OFF

EXTINGUISH with Fire Extinguisher

ENGINE FIRE - IN FLIGHT

Fuel Selector Valve

Throttle .

Mixture

Magneto/Starter Switch . .

Cabin Ventilation & Heating Controls

. OFF

CLOSED

IDLE CUTOFF

. OFF

CLOSED

NOTE I

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 FLIGHT (Smoke in Cabin)

Master Switch . OFF

I11111111111111111

// WARNING //

//////////////////

Stall warning and landing gear warning, not available with Master Switch OFF.

Alternator Field Switch .

Cabin Ventilation .

Heating Controls

Circuit Breakers

OFF

OPEN

CLOSED

LAND

CHECK to identify faulty circuit if possible

AS

SOON AS POSSIBLE.

If electrical power is essential for flight, attempt to identify and isolate faulty circuit as follows:

Master Switch

Alternator Field Switch

ISSUED 11 - 99 3 - 9

SECTION

III

EMERGENCY PROCEDURES

MOONEY

M2OR

Select ESSENTIAL switches ON one at a time; permit a short time to elapse before activating an additional circuit.

EMERGENCY DESCENT PROCEDURE

In the event an emergency descent from high altitude is required, rates of descent of at least

3,000 feet per minute can be obtained in two different configurations:

(1) With landing gear and flaps retracted, an airspeed of 195 KIAS will be required for maximum rate of descent.

(2) With the landing gear extended and flaps retracted an airspeed of 165 KIAS will also give approximately the same rate of descent. At 165 KIAS and the gear extended, the angle 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

Airspeed

Landing Gear .

Airspeed .

Wing Flaps .

Airspeed . .

Speedbrakes (If installed)

Altitude . .

Power During Descent

. . .

RETARD INITIALLY

140 KIAS

. . . . . . EXTEND

INCREASE TO 165 KIAS after landing gear is extended.

MAINTAIN 165 KIAS during descent.

EXTEND

AS DESIRED

. . . AS REQUIRED to maintain CHT 250 ° F (121 ° C) minimum.

GLIDE

2400

)

2200

MAXIMUM GLIDE DISTANCE MODEL M2OR

(%.

/

2000 /

1800

1600

19

1400 g 1200 r

ASSOCIATED

Landing Gear

Wing Flaps

Cowl Flap

Propeller

Wi d

COND TIONS

Retracted

Zero Degrees

Closed

Windmilling

Zero Wind

1000

800

600

400

,...,

/

200 i

/

5 10

•'''''

10 20

BEST GLIDE SPEED

Weight IA S

LBS (Kg) (Kts )

3368 115281

3200

2900

2600

1452

1315

1179

91.5

89.0

84 5

80.0

15 20 25 30 35 40 45

GROUND DISTANCE — NAUTICAL MILES

30 40 50 60 70

GROUND DISTANCE — KILOMETERS

100

110

3-10 ISSUED 11 - 99

MOONEY

M2OR

SECTION III

EMERGENCY PROCEDURES

I NOTE

Greater glide distances can be attained by moving the propeller control FULL AFT

(LOW RPM).

FORCED LANDING EMERGENCY

GEAR RETRACTED OR EXTENDED

Emergency Locator Transmitter

Seat Belts/Shoulder Harnesses

Cabin Door

Fuel Selector

Mixture

Magneto/Starter Switch

Wing Flaps

Landing Gear .

Approach Speed

Master Switch .

Wings.

ARMED

. SECURE

UNLATCHED

OFF

IDLE CUTOFF

OFF

Full DOWN

DOWN-If conditions permit

. 80 KIAS

OFF, prior to landing

LEVEL Attitude

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 ap proach an glethan nor mal, with power as nec es sary un til a smooth touch dow• • assured.

Expectlanding distance over a 50 feet obstacle (Ref. SEC TION V) to in crease at least 600 ft.

Conduct Gear and Tire Servicing inspection as required (Ref. SECTION VIII).

SYSTEMS EMERGENCIES

PROPELLER

PROPELLER OVERSPEED

Throttle .

Oil Pressure .

Propeller

Airspeed

Throttle

FUEL

LOW FUEL FLOW

Check mixture

Fuel Selector

DECREASE RPM, re-set if any control available

AS REQUIRED to maintain RPM below 2500 RPM

ENRICH

SWITCFf TANKS

If condition persists, use Fuel Boost Pump as necessary. LANDING should be made as soon as PRACTICABLE.

ELECTRICAL

ALTERNATOR OVERVOLTAGE/FAILURE

(

((Alternator wam ing light illuminated steady. The Al ter na tor Field cir cuitbreaker maybe trippea

(overvoltage) or it may remain in its normal position (field fault).

Alternator Field Circuit Breaker . . . . RESET (If tripped)

If circuit breaker will not reset, the following procedures are required:

ISSUED 11 - 99 REV. A 10 - 03 3.11

SECTION III

EMERGENCY PROCEDURES

1. Reduce electrical load, as required, to maintain essential systems.

2. Continue flight and LAND, when PRACTICABLE, to correct malfunction.

The only source of electrical power is from the selected battery. Monitor battery voltage (min, 18V) and switch to other battery when necessary.

MOONEY

M2OR

•

I NOTE I

NOTE: (S/N 29-0297, 29-0300 THRU 27-TBA) Activating the EMERG BUS switch will automatically shed all systems outside the Yellow "ESSENTIAL" bands located on the Circuit

Breaker Panel. All systems lo cated within the Yel low"ES SEN TIAL" bands will re main pow erred by the remaining alternator, or in the case of Dual alternator failure, the selected battery.

ALTERNATOR OUTPUT LOW

(Altemator 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 en durance will de pend upon battery con di tion and electri cal load on battery. If one battery becomes depleted, switch to other battery.

LANDING GEAR

FAILURE OF LANDING GEAR TO EXTEND ELECTRICALLY

Airspeed . . . .

Landing Gear Actuator Circuit Breaker

Landing Gear Switch ..

Gear Manual Emergency Extension Mechanism

. .

140 KIAS or le

. PU1111.

DOWN

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 cm) to rotate clutch mechanism and allow it to engage drive shaft.

T-Handle

. . .

. . PULL (12 to 20 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-Handle, 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.

//////////////////

//WARNING//

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

GEAR Switch .

. . . . . .

Below 106 KIAS

UP Position

GEAR FAILS TO RETRACT — GEAR HORN - SOUNDING;

GEAR ANNUNCIATOR LIGHT & GEAR SAFETY BY-PASS LIGHT — ILLUMINATED

3 - 12 REV. A 10 - 03' ISSUED 11 - 99

MOONEY

M20C/E/F/J/K/L/M/R/S

SECTION VII

AIRPLANE AND SYSTEM DESCRIPTION

Addendum

to:

WARNING SYSTEM

LANDING GEAR

—CAUTION—

The absence of any of the above described indications in their

Normal sequence may represent a potential failure in the Landing

Gear or Indicator system. The floor mounted visual gear position

Indicator presents a mechanical indication of gear status. The

Visual gear position indicator shall be verified to be in the DOWN

Position (indicator marks aligned with the word DOWN fully visible) prior to ALL landings.

Issued 09-01

SERVICE

BULLETIN M20-279B

MOONEY SECTION III

. .

EMERGENCY PROCEDURES

•

M2OR

GEAR SAFETY BY-PASS SWITCH

"GEAR UNSAFE" and "GEAR DOWN" Lights .

"GEAR RELAY" Ckt. Bkr. . . .

Check "Airspeed Safety Switch" or other malfunction as soon as practicable.

"GEAR RELAY" Ckt. Bkr .

WHEN READY TO EXTEND LANDING GEAR

Airspeed .

Gear Relay C/B .

. .

HOLD until landing gear is fully retracted

. .

EXTINGUISHED

. PULL

(Warning Horn and Gear By Pass light will go OFF)

BELOW 140 KIAS

DEPRESS

PUSH IN

RESET

Landing Gear Switch . . DOWN

ILLUMINATED Gear Down Light

NOTE I

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 ACTUATOR C/B

FLIGHT

AIRSPEED

GEAR SWITCH

. . . . .

When ready to extend landing gear at next landing:

. .

•

GEAR EMERGENCY EXTENSION LEVER (on floor) Verify LATCHED in proper position

RESET

Gear should retract if C/B was tripped

. CONTINUE (if desired)

Below 140 KIAS

DOWN Position

If gear will not extend electrically at this time, refer to FAILURE OF . LANDING GEAR TO

EXTEND ELECTRICALLY (previous page).

VACUUM

When "HI/LO VAC" annunciator light illuminates (flashing or steady), vacuum operated instruments are considered to be unreliable. Push stand-by vacuum pump switch ON. The flashing

Hi/LO VAC annunciator light should extinguish and the STBY VAC annunciator will illuminate.

The vacuum operated gyro instruments will be operating on the stand-by vacuum system. The steady RED annunciator light may not extinguish when the stand-by vacuum switch is ON.

Continue flight, monitor non-vacuum gauges. Have vacuum system inspected prior to next flight.

OXYGEN

In the event of oxygen loss above 12,500 ft. return to 12.500 ft as soon as feasible.

Refer to SECTION X for the physiological characteristics of high altitude flight.

ALTERNATE STATIC SOURCE

•

shaft.

The alternate static air source should be used whenever it is suspected that the normal static air sources are blocked, Selecting the alternate static source changes the source of static air for the altimeter, airspeed indicator and rate-of-climb from outside of the aircraft to the cabin interior.

When alternate static source is in use, adjust indicated airspeed and altimeter readings according to the appropriate alternate static source airspeed and altimeter calibration tables in SECTION V.

The alternate static air source valve is located on the instrument panel below pilot's control wheel

When using Alternate Static Source, pilot's window and air vents

Alternate Static Source

Airspeed and Altimeter Readings

I NOTE I

MUST BE KEPT CLOSED.

. . . . . . PULL ON

CHECK Calibration Tables (Ref SECTION V)

3 - 13 ISSUED 11 - 99

SECTION III

EMERGENCY PROCEDURES

MOONEY

M2OR

UNLATCHED DOORS IN FLIGHT

CABIN DOOR

If cabin door is not properly closed it may come unlatched in flight. This may occur during or just after take-off. The door will trail in a position approximately 3 inches (7.6 cm) open, but the flight characteristics of the airplane will not be affected. There will be considerable wind noise; loose objects, in the vicinity of the open door, may exit the aircraft. Return to the field in a normal manner. Ifpracticable, 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 Storm Window .

Aircraft .

Door

. 95 KIAS

. . . OPEN

RIGHT 'SIDESLIP (Right bank with left rudder)

. PULL SHUT & LATCH

BAGGAGE DOOR

If baggage door is not properly closed, it may come unlatched in flight. This may occur during or after takeoff. The door may open to its full open position and then take an intermediate position depending upon speed of aircraft. There will be considerable wind noise; loose objects, in the vicinity of the open door, may exit the aircraft. There is no way to shut and latch door from the inside. Aircraft flight characteristics will not be affected; fly aircraft in normal manner;

LAND AS SOON AS POSSIBLE and secure baggage door.

Baggage Door latching mechanism . VERIFY MECHANISM PROPERLY ENGAGED

(inside latching mechanism) then shut from outside aircraft.

ICING

///////////////////

// WARNING //

///////////////////

DO NOT OPERATE IN KNOWN ICING CONDITIONS.

The Model M2OR is NOT APPROVED for flight into known icing conditions and operation in that environment is prohibited. However, if those conditions are inadvertently encountered or flight into heavy snow is unavoidable, the following procedures are recommended until further icing conditions can be avoided:

INADVERTENT ICING ENCOUNTER

Pitot Heat .

Propeller De-Ice

Alternate Static Source

Cabin Heat & Defroster

Engine Gauges .

. . ON

ON (if installed)

ON (if required)

MONITOR for any engine Power reduction

Turn back or change altitude to obtain an outside air temperature less conducive to icing.

Move propeller control to maximum RPM to minimize ice build-up on propeller blades. If ice builds up or sheds unevenly on propeller, vibration will occur. If excessive vibration is noted, momentarily reduce engine speed with propeller control to bottom of GREEN ARC, then rapidily move control FULL FORWARD.

I NOTE I

Cycling RPM flexes propeller blades and 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 buildup that may have bridged gap between elevator horn and horizontal stablilizer.

3 - 14 ISSUED 11 - 99

MOONEY

M2OR

SECTION III

EMERGENCY PROCEDURES

Watch for signs of induction air filter blockage due to ice build-up; increase throttle setting to maintain engine power.

I NOTE I

If ice blocks induction air filter, alternate air sysem will open automaticallly.

With ice accumulation of 1/4 inch or more on the airframe, be prepared for a significant increase in aircraft weight and drag. This will result in significantly reduced cruise and climb performance and higher stall speeds. Plan for higher approach speeds requiring higher power settings and longer landing rolls.

— CAUTION —

Stall warning system may be inoperative.

I NOTE I

The defroster may not clear ice from windshield. If necessary open pilot's storm window for visibility in landing approach and touchdown.

With ice accumulations of 1 inch or less, use no more than 15 ° landing. For ice accumulation of 1 inch or more, fly approaches and landing with flaps retracted to maintain better pitch control. Fly 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 touchdown technique.

Missed approaches SHOULD BE AVOIDED whenever possible because of severly reduced 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 CONDITIONS —

EMERGENCY EXIT OF AIRCRAFT

CABIN DOOR

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, CLIMB OVER.

PULL off plastic cover from over inside latch.

PULL lock pin.

Pull red handle.

OPEN door and exit aircraft.

To VERIFY RE-ENGAGEMENT of baggage door, outside, latch mechanism:

Open outside handle fully.

Close inside RED handle to engage pin into cam slide of latch mechanism.

Place lock pin

Replace cover. in shaft hole to hold RED handle DOWN.

CHECK & operate outside handle in normal manner.

ISSUED 11 - 99 3 - 15

3-16

SECTION III

EMERGENCY PROCEDURES

MOONEY

M2OR

SPINS

0/08////0

// WARNING //

0/0//////////

Up to 2,000 ft. altitude may be lost in a one turn spin and recovery;

STALLS AT LOW ALTITUDE ARE EXTREMELY CRITICAL.

NOTE

The best spin avoidance technique is to avoid flight conditions conducive to spin entry. Low speed flight near stall should be approached with caution and excessive flight control movements in this flight regime should be avoided.

Should an unintentional stall occur, the aircraft should not be allowed to progress into a deep stall. Fast, but smooth stall recovery will minimize the risk of progressing into a spin. If an unusual post stall attitude develops and results in a spin, quick application of antispin procedures should shorten the recovery.

INTENTIONAL SPINS ARE PROHIBITED.

In the event of an inadvertent spin, the following recovery procedure should be used:

Throttle

Ailerons

Rudder .

Apply FULL

. RETARD to IDLE

. . NEUTRAL opposite direction of spin

Control Wheel . 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 —

RETRACT as soon as pos ible

NEUTRALIZE when spin tops

. SMOOTHLY MOV AFT to bring the nose up to level flight attiti de.

Wing Flaps (If extended).

Rudder . .

Control Wheel

OTHER EMERGENCIES

Refer to SECTION IX for Emergency Procedures of Optional Equipment.

•

ISSUED 11 - 99

MOONEY

M2OR

SECTION IV

NORMAL PROCEDURES

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

4-12

4-13

4-14

4-15

4-16

4-9

4-10

4-11

4-12

PAGE

4-3

4-4

4-5

4-7

4-8

4-9

ISSUED 11 - 99 4 - 1

(7)

Z cn

53n

— Z

<

(7)

IJ m cr)

MOONEY

M2OR

INTRODUCTION

SECTION IV

NORMAL PROCEDURES

This section describes the recommended procedures for the conduct of normal operations for the airplane. All of the required (FAA or ICAO 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 11 - 99 4 - 3

SECTION IV

NORMAL PROCEDURES

SPEEDS FOR NORMAL OPERATION

MOONEY

M2OR

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 speed appropriate to the particular weight must be used.

TAKEOFF:

Normal Climb Out . 80-90 KIAS

Short Field Takeoff, Speed At 50 Ft. 75 KIAS

ENROUTE CLIMB, GEAR and FLAPS UP:

Best Rate of Climb .

Best Angle of Climb .

105 KIAS

85 KIAS

LANDING APPROACH (3200 lbs.):

Normal Approach, Flaps 10 degrees

Normal Approach, Flaps 33 degrees

Short Field Approach, Flaps 33 degrees .

BALKED LANDING (3200 lbs.):

Maximum Power, Flaps 10 degrees .

80 KIAS

75 KIAS

70 KIAS

85 KIAS

MAXIMUM RECOMMENDED TURBULENT AIR PENETRATION SPEED:

3368 lbs./1528 Kgs

3200 lbs./1452 Kgs .

127 KIAS

123 KIAS

2900 lbs./1315 Kgs

2600 lbs./1179 Kgs .

2400 lbs./1089 Kgs

117 KIAS

111 KIAS

106 KIAS

DEMONSTRATED CROSSWIND VELOCITY:

Takeoff or Landing 13 rnb e r)

(This is NOT A LIMITATION, only a demons. trated number)

(See CROSSWIND COMPONENT CHART, SECTION V)

4 - 4 ISSUED 11 - 99

MOONEY

M2OR

SECTION IV

NORMAL PROCEDURES

PREFLIGHT INSPECTION

1. Cockpit -

Gear Switch

Magneto/Starter Switch

All Rocker Switches

DOWN

OFF

Master Switch

All Circuit Breakers .

Battery Select Switch

CHECK Voltmeter

Internal/External Lights .

OFF

. . . . after each selection. Leave on Battery with highest voltage.

SELECT from 1 to 2 or 2 to 1.

. . . . CHECK operation

Pitot Heat Switch .

(Check for ammeter fluctuations as each light is checked)

. . . . . . . ON

(Check Pitot Heat annunciator light illuminated BLUE *)

Fuel Quantity Gauges

Fuel Selector

. . CHECK QTY

It is recommended that wing tank sumps be drained prior to draining gascolator.

. . . .

Oxygen Supply Control Knob (if installed)

Rt. Tank: Pull Gascolator ring (5 seconds)

Lt. Tank: Pull Gascolator ring (5 seconds)

. . . . . . OFF

Oxygen Pressure Gauge . . . . . . . . CHECK

Verify adequate oxygen supply for trip, (if use of oxygen is anticipated), refer to oxygen duration chart (Fig. 7-13, SECTION VII).

Also check that face masks and hoses are accessible and in good condition.

2. Right Fuselage/Tailcone

Oxygen Filler Access Door and Filler Cap

Battery # 2 Access Panel. . .

Instrument Static Pressure Port.

General Skin Condition . .

Tailcone/Empennage Access Panel

Tail tiedown rope/chain .

SECURED

UNOBSTRUCTED

. INSPECT

. SECURED

REMOVE

3. Empennage

Elevator and rudder attach points and control linkage attachments

Empennage Freeplay-Vertical/Horizontal

General skin condition .

INSPECT

. . INSPECT

Remove ice, snow, or frost.

* If TKS system is installed , pitot heat annunciator will illuminate AMBER when switch is

ON and Pitot Heat has failed. Annunciator will not be illuminated when switch is ON and system is operating properly.

ISSUED 11 99 4 - 5

SECTION IV

NORMAL PROCEDURES

4. Left Fuselage/Tailcone

Cabin Fresh Air Vent (Dorsal Fin)

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 .

Pitot Tube .

Landing/Taxi Lights

Stall Switch Vane .

Fuel Tank .

MOONEY

M2OR

UNOBSTRUCTED

SECURED

UNOBSTRUCTED

. SECURED

. . SECURED

PUSH Plunger UP, (Hold 3-5 Seconds)

. . . INSPECT

INSPECT-Remove ice, snow, or frost.

INSPECT

. INSPECT

UNOBSTRUCTED

UNOBSTRUCTED/SECURED

(Heat element Operative)

INSPECT Lens & Bulbs

CHECK operation

CHECK QUANTITY/SECURE CAP

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 .

Wheel chock . . . . . .

Left Main Landing Gear, shock discs, tire & doors .

Fuel Tank Sump Drain . . . . . . . .

REMOVE

INSPECT

DRAIN

Use sampler cup to VERIFY fuel is free of water, sediment & other contamination;

VERIFY proper fuel (BLUE/10OLL)(GREEN/100 octane).

—CAUTION —

Some diesel may be BLUE, Verify by smell and feel that 'I OOLL is being used.

Pitot System Drain .

VERIFY drain closes and does not leak.

PUSH plunger UP, (Hold for 3-5 seconds)

6. Left Cowl Area

Windshield .

Cabin Air Inlet

Left Side Engine Cowl Fasteners

Exhaust Pipes .

Engine Oil Filler Door .

. .

CLEAN

UNOBSTRUCTED

. SECURED

INSPECT SECURED

OPEN & INSPECT AREA

I NOTE I

The engine compartment must be free of foreign objects which could result in possible over heating and serious damage to the engine.

Engine Oil

Engine Oil Filler Door .

Cooling Air Inlet .

7. Propeller/Spinner & Front Cowl Area

Propeller/Spinner .

CHECK QUANTITY

8 Qts.(7.57 I)

. CLOSE & SECURE

Verify UNOBSTRUCTED

Prop De-Ice Boots (if installed)

Induction Air Inlet/Filter . .

Nose gear, shock discs, tire & doors .

Wheel chock .

INSPECT for nicks, cracks, oil leaks/rotational movement.

INSPECT condition

UNOBSTRUCTED

. INSPECT

REMOVE

4 - 6 ISSUED 11 - 99

MOONEY

M2OR

SECTION IV

NORMAL PROCEDURES

•

8. Right Cowl Area

Right Side Engine Cowl Fasteners

Cooling Air Inlet .

Windshield

Cabin Air Inlet

9. Right Wing

Fuel Tank Sump Drain . .

SECURED

Verify UNOBSTRUCTED

CLEAN

UNOBSTRUCTED

. . . . . . 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 . . .

General Skin Condition.

Fuel Tank .

. .

INSPECT

REMOVE

INSPECT 'Remove ice, snow and frost.

CHECK QUANTITY/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 .

. REMOVE

UNOBSTRUCTED

INSPECT Lens & Bulbs

INSPECT

10. Baggage Door Area

Baggage Door . . VERIFY SECURED

(VERIFY inside handle is properly secured)

. (CHECK outside handle operation)

RETURN TO COCKPIT — MASTER/ROCKER SWITCHES . . OFF

•

BEFORE STARTING CHECK

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 .

Alternate Static Source

Throttle

Propeller .

COMPLETED

ADJUST & SECURED

OFF

SLAVED (If installed)

CHECK - ALL IN

. ARMED

OFF

Push OFF

CLOSED

FULL FORWARD (HIGH RPM)

Mixture.

Parking Brakes

Wing Flap Switch

Defrost

Cabin Heat .

Cabin Vent

Fuel Selector .

All Rocker Switches

Landing Gear Switch

IDLE CUT-OFF

. SET

. FLAPS UP

PUSH OFF

AS DESIRED

FULLEST TANK

OFF

DOWN POSITION

4 - 7 ISSUED 11 - 99

4 - 8

SECTION IV

NORMAL PROCEDURES

MOONEY

M2OR

RED Emergency Gear Extension Handle

Internal Lights .

Passenger Briefing .

DOWN AND LATCHED

OFF

COMPLE.

(Emergency and general information bri

Refer to SECTION IX Supplements for Optional Equipment Procedures and Check

Obtain local airport information prior to engine start.

ENGINE START

- 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 charging for at least one hour should be done before engine is started. Batteries must be serviceable and IT IS RECOMMENDED THAT

BATTERIES BE FULLY CHARGED TO OPERATE AIRCRAFT. Electrical components may also be damaged if aircraft is operated when batteries are low

I NOTE I

When starting engine using the approved external power source, no special starting procedure is necessary. Use normal starting procedures below. DO NOT START ENGINE IF BOTH

BATTERIES 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

Propeller .

Mixture

Master Switch

Annunciator Lights

Low Fuel Boost Pump Switch

COMPLETED

FULL OPEN

FULL FWD (High RPM)

. Full Forward (RICH)

PRESS TO TEST (All lights should illuminate)

. ON during engine starting seq

CAUTION -

For engine operation at outside air temperatures Ielow -25° C (-13 °F), the engine and engine oil should be preheated to at least -25 C (-13 ° F) before the engine is started.

Throttle .

Propeller Area

Magneto/Starter Switch

If No 1 battery will not start engine

. IDLE POSITION

CLEAR

. TURN & PUSH to START, release to BOTH when engine starts.

. SELECT No 2 battery

I NOTE I

COLD ENGINE START - Low fuel boost pump ON during "Start" sequence. Turn low fuel boost pump OFF when engine obtains smooth operation.

I NOTE I

"START POWER" warning light should illuminate when Magneto/Starter switch is in

"START" position.

Cranking should be limited to 30 seconds, and several minutes allowed between

Throttle

I NOTE I cranking periods to permit the starter to cool.

. IDLE 600 - 700 RPM

•

ISSUED 11 - 99 REV. A 10 - Q3

MOONEY

M2OR

SECTION IV

NORMAL PROCEDURES

• Engine Oil Pressure .

. .

. . CHECK in GREEN ARC

If minimum oil pressure (10 PSI) is not indicated within 30 seconds,

Alternator Field Switch .

. . accomplish engine shutdown procedures.

Low Fuel Boost Pump Switch . OFF

• Ammeter .

. .

• Interior/Exterior Lights

• Engine Instruments

• Fuel Flow Indicator

• Throttle

• Mixture .

. . . . . CHECK

Turn LDG LT ON & observe Negative movement of needle.

. . . AS DESIRED

CHECKED

TEST/RESET (if desired)

900/1000 RPM

ADJUST FOR SMOOTH OPERATION

CAUTION -

Do not operate engine above 1000 RPM unless oil temperature is 75 ° F (24 ° C), minimum. Operation of engine above 1000 RPM at temperatures below 75 ° may damage engine.

FLOODED ENGINE START

Throttle

Mixture.

Low Fuel Boost Pump Switch

Magneto/Starter Switch

1/ 2 OPEN

IDLE CUTOFF

ON — 8 -10 SECONDS THEN OFF

. TURN & PUSH to START

Mixture.

Throttle.

SEE

. release to BOTH when engine starts.

Slowly advance toward RICH until engine starts

. . . . IDLE 600 - 700 RPM

ENGI NE START PROCEDURES ABOVE • FOR REMAINING SEQUENCES.

WARM ENGINE START

Throttle . . •lg to

Mixture . . .

Low Fuel Boost Pump Switch

Magneto/Starter Switch .

Throttle..

SEE ENGINE

' .

F Forward (RICH)

ON - (TO CLEAR FUEL VAPORS)

WITHIN . 1-2 SECONDS, TURN 84 • PUSH to START

. release to BOTH when engine starts.

- 700 RPM

PROCEDURES 'ABOVE • FOR REMAINING SEQUENCES.

HOT ENGINE START

Throttle .

Mixture . .

. FULL OPEN

IDLE CUT-OFF

Boost Pump .

Boost Pump

Throttle

Mixture . . .

Magneto/Starter Switch

. .

Throttle..

. .

HIGH for 5 sec. or LOW for 15 sec.

. . OFF

IDLE POSITION

Full Forward (RICH)

TURN & PUSH to START release to BOTH when engine starts.

. . IDLE 600 - 700 RPM

SEE ENGINE START PROCEDURES 'ABOVE • FOR REMAINING SEQUENCES.

BEFORE TAXI

Engine Start Checklist

Radio Master Switch .

Elevator Trim Switch

Internal/External Lights .

Directional Gyro . . .

Stand-by Vacuum Pump Operational Check

STBY VAC Switch .

COMPLETED

. ON

As Desired

SET or Slave switch ON

ISSUED 11 - 99 REV. A 10 - 03 4 - 9

SECTION IV

NORMAL PROCEDURES

MOONEY

M2OR

STBY VAC Switch .

Instruments .

. Radios .

Altimeter .

Fuel Selector

Cabin Heat

Defroster .

Cabin Vent

Optional Equipment Checks

BEFORE TAXI (con't.)

. . . OFF

Normal Operation

CHECKED and SET

. . SET

SWITCH TANKS verify engine runs on other tank

. AS DESIRED

AS DESIRED

Reference SECTION IX.

TAXI

Before Taxi Checklist .

Rudder Trim .

COMPLETED

AS DESIRED

— CAUTION —

With rudder trim in the full right position, the aircraft will tend to steer to the right during taxi.

Parking brake

Brakes . .

Directional Gyro

Turn Coordinator

Artificial Horizon

Throttle.

Propeller

. CHECK

RELEASE during TAXI

Proper indication during turns

. ERECT during turns

Minimum power

Full Forward (HIGH RPM)

— CAUTION —

prolonged takeoff, increase RPM until indicates positive charge.

BEFORE TAKEOFF

Taxi Checklist

Parking Brake

Fuel Selector,

Throttle

Propeller .

Mixture .

Alternate Air .

Alternator Field Switch

Throttle . .

Magneto Switch

COMPLETED

. SET

FULLEST TANK

1000 RPM

. HIGH RPM

FULL FORWARD

Verify CLOSED

Verify ON

2000 RPM .

. . CHECK - BOTH to L, BOTH to R, BOTH

Verify engine operates smoothly on each magneto separately.

(150 RPM MAX drop on each magneto, 50 RPM MAX difference)

I NOTE I

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 confirm whether a deficiency exists.

Propeller

Ammeter

Throttle. .

. .

Low Fuel Boost Pump Switch

CYCLE/Return to high RPM

CHECK Positive Charge Indication

. . . . RETARD to 1000 RPM

ON-Verify annunciator light will illuminate BLUE

. OFF

4 - 10 ISSUED 11 - 99

SECTION IV

NORMAL PROCEDURES

TAKEOFF SETTING

CHECK operation.

•

MOONEY

M2OR

Elevator Trim

Rudder Trim

Wing Flaps.

SET AT TAKEOFF position (10 Degrees)

Flight Controls

Cabin Door

. . .

Seats, Seat Belts and Shoulder Harness

Avionics and Auto Pilot .

Annunciator Lights

Internal/External Lights .

Strobe Lights/Rotating Beacon

Pilots Window. . .

. .

Emergency Gear Extension (RED) Handle.

Oil Temperature

CHT .

Parking Brake

CHECK free and correct movement

. CHECK SECURED

SECURED

CHECK - (Refer to SECTION IX)

CHECK

AS DESIRED

CLOSED

DOWN & LATCHED

75 ° F(24 ° C) minimum

250 ° F(121 ° C) minimum

. RELEASE

TAKEOFF

Proper engine operation should be checked early in the takeoff roll. Any significant indication of rough or sluggish engine response is reason to discontinue 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 high RPM is developed, and gravel or loose material will be blown back from the propeller area instead of being pulled into it.

TAKEOFF (NORMAL)

•

Power

Mixture .

Annunciator

Engine Instruments.

Lift Off/Climb Speed

Landing Gear .

Wing Flaps .

TAKEOFF (HIGH ALTITUDE)

. FULL THROTTLE (2500 RPM)

As specified in SECTION V (Takeoff

CHECK

. . CHECK for proper ind ications istance)

RETRACT IN CLIMB after clearing o bstacles.

. . UP

For maximum engine power, the mixture should be adjusted during the initi I takeoff roll to the top of the BLUE ARC on the EGT. The power increase is significant a bove 3000 ft. and this procedure should always be employed for field elevations greater than 5000 ft. above sea level.

I NOTE I

If maximum performance takeoffs are desired obtain full power release. Use lift off and climb speed as specified in SEC before brake

ION V.

CLIMB

I NOTE

If applicable,use noise abatement procedures as required.

See SECTION V, for rate of climb graph.

CLIMB (CRUISE)

Power .

Manifold Pressure .

Mixture

Rudder Trim.

Airspeed

. 2500 RPM

24 Inches

FULL RICH or BLUE ARC on EGT

. As Desired

120 KIAS

ISSUED 11 - 99 4-11

SECTION IV

NORMAL PROCEDURES

MOONEY

M2OR

CLIMB (BEST RATEN

Power .

Mixture .

Rudder Trim.

Airspeed .

. FULL THROTTLE /2500 RPM

FULL RICH or BLUE ARC on EGT

. As Desired

105 KIAS

CLIMB (BEST ANGLE)(1/.)

Power .

Mixture .

Rudder Trim.

Airspeed.

FULL THROTTLE/2500 RPM

. FULL RICH

As Desired

85 KIAS

Leaning may be required during CLIMB depending on atmospheric conditions.

CRUISE

I NOTE I

Use recommended engine break-in procedures as published by engine manufacturer.

Airspeed .

Throttle . . . .

ACCELERATE to cruise airspeed

. SELECTED SETTING

(Ref. CRUISE PERFORMANCE CHARTS in SECTION V)

I NOTE I

Prolonged climbs to high cruise altitudes during hot weather operations may result in some fuel flow fluctuations as throttle is reduced. If fluctuations occur, turn Low

Boost Pump Switch ON until cooling has alleviated fluctuations.

Propeller

Mixture .

Set RPM to selected setting

LEAN TO 50 ° F rich of PEAK EGT

I NOTE I

Cruise operation at BEST POWER will result in a substantial increase in fuel flow, greatly decreasing range and endurance; reference charts published in SECTION V.

Engine instruments

• • •

. . CHECK

I NOTE I

Careful leaning of mixture control will result in best fuel efficiency. This requires operating at proper EGT. Failure to do so will result in excessive fuel burn. 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 economy); careful adjustments are necessary for accurate setting. Changes in altitude or power MAY

REQUIRE readjustment of EGT.

Engine temperatures

Rudder Trim.

STABILIZE at cruise condition.

. As Desired

When increasing power, always return mixture to full rich, then increase RPM before increasing manifold pressure; when decreasing power, decrease manifold pressure before reducing

RPM. Always stay within the established operating limits, and always operate the controls slowly and smoothly.

FUEL TANK SELECTION

Low Fuel Boost Pump Switch .

Fuel Selector . . .

Low Fuel Boost Pump Switch .

. ON

OPPOSITE TANK

. OFF

4 12 ISSUED 11 - 99

MOONEY

M2OR

SECTION IV

NORMAL PROCEDURES

OXYGEN SYSTEM

(OPTIONAL EQUIPMENT)

////////////////////

// WARNING //

////////////////////

Greasy lipsticks and waxed mustaches have been known to ignite spontaneously inside oxygen masks. Passengers should be suitably advised prior to flight.

For safety reasons NO SMOKING should be allowed in the airplane while oxygen is being used.

When ready to use the oxygen system, proceed as follows:

Mask and Hose . . . . . . SELECT - either MIC or STD

. .

Delivery Hose .

Adjust mask to face and adjust metallic nose strap for snug mask fit.

. . . PLUG INTO OUTLET assigned to that seat.

I NOTE I

When the oxygen system is turned ON, oxygen will flow continuously at the appropriate rate of flow for the altitude without any manual adjustments.

Oxygen Supply Control Knob .

Face Mask Hose Flow Indicator

. .

Delivery Hose

. .

. . . . . . .

. ON.

CHECK

Oxygen is flowing if the indicator is being forced toward the mask.

UNPLUG from outlet when discontinuing use of oxygen.

. . . . This automatically stops flow of oxygen from that outlet.

Oxygen Supply Control Knob . . OFF - when oxygen is no longer required.

/////////////////////

// WARNING //

////////////////////

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 flow indicator to ensure oxygen is constantly flowing to the mask. A GREEN indication on the flow indicator denotes proper oxygen flow. Always place the flow indicator in a position where it is in the normal scan area of the cockpit.

Refer to duration chart (Fig. 7-13, SECTION VII) for safe operational quantities.

DESCENT

I NOTE I

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

Seats, Seat Belts/Shoulder Harness

Wing Flaps .

Landing Gear.

Throttle .

Propeller

Mixture

Cylinder Head Temperature (CHT)

Airspeed

Rudder Trim

ISSUED 11 - 99

ADJUST AND SECURE

. UP

CHT in Green)

. . . 2400 RPM

Peak EGT (Monitor as descent progresses)

MONITOR [250

° F(121 ° C) minimum]

AS DESIRED(196 KIAS max.)

. AS DESIRED

413

SECTION IV

NORMAL PROCEDURES

MOONEY

M2OR

I NOTE I

Plan descents to arrive at pattern altitude on downwind leg for maximum fuel efficiency and mlnumum aircraft noise.

— CAUTION —

DO NOT fly in YELLOW ARC speed range unless the air is smooth.

NORMAL DESCENT - GEAR DOWN

Seats, Seat Belts/Shoulder Harness .

Wing Flaps .

Airspeed.

Landing Gear

Throttle .

Propeller

Mixture

Cylinder Head Temperature (CHT)

Airspeed . .

ADJUST AND SECURE

DECELERATE

Monitor (250 ° F

. to 140 KIAS

Keep CHT in Green Arc

2400 RPM

Peak EGT (Monitor as descent progresses)

(121

DOWN

C)min)

165 KIAS or LESS.

I NOTE

Using landing gear as a descent aid will result in a steeper descent rate

(greater altitude loss per horizontal distance traveled).

APPROACH FOR LANDING

—

CAUTION

—

The airplane must be within allowable 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 landing at a weight exceeding maximum landing weight (3200

Lbs.)(1452 Kgs.) is required, see OVERWEIGHT LANDING PROCEDURE,

SECTION III.

Seats, Seat Belts/Shoulder Harness

Internal/External lights .

Landing Gear .

Mixture .

Propeller .

Fuel Boost Pump Switches

Fuel Selector .

Wing Flaps .

ADJUST AND SECURE

. AS DESIRED

E XTEND below

(Check Gear Down light ON -Check

. o indicator)

FULL RICH (on final)

HIGH RPM (on final)

OFF

FULLEST TANK

— 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

VERIFY OFF

I NOTE I

The parking brake should be rechecked to preclude partially applied brakes during touchdown.

4 - 14 ISSUED 11 - 99

MOONEY

M2OR

SECTION IV

NORMAL PROCEDURES

GO AROUND (BALKED LANDING)

— 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 .

FULL FORWARD/2500 RPM)

. Verify

FULL RICH

. OFF

TAKEOFF POSITION (10 °)

(After POSITIVE climb established)

NOSE DOWN to reduce forces

85 KIAS

RETRACT

105 KIAS

LANDING

LANDING (NORMAL)

Approach for Landing Checklist

Approach Airspeed .

Touchdown.

Landing Roll .

Brakes .

, . . . . COMPLETED

As specified in SECTION V (Landing Distance)

MAIN WHEELS FIRST (aligned w/ runway)

. LOWER nose wheel gently

. MINIMUM required

I NOTE

Landing information for reduced flap settings is not available.

See SECTION V for Landing Distance tables.

I NOTE I

If maximum performance landings are desired, use above procedures except, reduce approach airspeed to 70 KIAS (flaps full down) and apply maximum braking (without skidding tires) during rollout.

I NOTE I

Crosswind landings should be accomplished by using above procedures except maintain approach speed appropriate for wind conditions. Allow aircraft to crab until the landing flare. Accomplish touchdown in a slight wing low sideslip (low wing into wind) and aircraft aligned with runway. During landing roll, position flight controls to counteract crosswind.

CAUTION —

Landing gear may retract during landing roll if landing gear switch is placed in the UP position.

TAXI AFTER LANDING

Throttle . .

Fuel Boost Pump Switches

Wing Flaps .

Elevator Trim .

Avionics/Radios

Interior/Exterior Lights .

AS REQUIRED

OFF

RETRACT

TAKEOFF SETTING

AS REQUIRED

AS DESIRED

ISSUED 11 - 99 4 - 15

SECTION IV

NORMAL PROCEDURES

SHUTDOWN

MOONEY

M2OR

•

Parking Brake .

Throttle . .

Radio Master Switch

Interior/Exterior Lights .

Pitot Heat . . .

Alternator Field Switch .

Magneto/Starter Switch .

Mixture . .

Master Switch . .

Magneto/Starter Switch .

. SET

IDLE RPM

OFF

GROUNDING CHECK

. IDLE CUT-OFF

OFF

SECURING AIRCRAFT

Magneto/Starter Switch

Master Switch

Radio Master Switch

Electrical Switches

Interior Light Switches .

Parking Brake .

VERIFY OFF/ Key removed

VERIFY OFF

Verify OFF

VERIFY OFF

RELEASE - INSTALL WHEEL CHOCKS

CONTROL WHEEL SECURED Extended parking

. .

Cabin Windows and Doors with seat belts, cabin vents closed;

•

TIE DOWN AIRCRAFT at wing and tail points.

CLOSED AND LOCKED

4 16 REV. A 10 - 03 ISSUED 11 - 99

MOONEY

M2OR

SECTION V

PERFORMANCE

TITLE .

INTRODUCTION

VARIABLES

OPERATIONAL PROCEDURES FOR MAXIMUM FUEL EFFICIENCY

PERFORMANCE CONSIDERATIONS .

- TABLES AND CHARTS -

TEMPERATURE CONVERSION .

CROSSWIND COMPONENT CHART

AIRSPEED CALIBRATION - PRIMARY STATIC SYSTEM (GEAR UP)

AIRSPEED CALIBRATION - PRIMARY STATIC SYSTEM (GEAR DOWN).

AIRSPEED CALIBRATION - ALTERNATE STATIC SYSTEM .

ALTIMETER CORRECTION - PRIMARY STATIC SYSTEM .

ALTIMETER CORRECTION - ALTERNATE STATIC SYSTEM

STALL SPEED VS ANGLE OF BANK .

TAKEOFF DISTANCE - NORMAL

RATE OF CLIMB - MAX CLIMB .

RATE OF CLIMB - CRUISE CLIMB .

TIME-FUEL-DISTANCE TO CLIMB - MAX CLIMB .

TIME-FUEL-DISTANCE TO CLIMB - CRUISE CLIMB

CRUISE POWER SETTINGS AND FUEL FLOWS

- BEST POWER .

- BEST ECONOMY .

SPEED POWER VS ALTITUDE .

RANGE

BEST POWER

- BEST ECONOMY

ENDURANCE

- BEST POWER

- BEST ECONOMY

TIME-FUEL-DISTANCE TO DESCEND .

LANDING DISTANCE - NORMAL

5-18

5-19

5-20

5-21

5-22

5-5

5-6

5-7

5-8

5-9

5-10

5-11

5-12

5-13

5-14

5-15

5-16

5-17

5-23

5-24

5-25

5-26

PAGE

5-3

5-4

ISSUED 11 - 99 5 - 1

SECTION V

PERFORMANCE

TABLE OF CONTENTS (con't)

MOONEY

M2OR

5 - 2

ISSUED 11 - 99

MOONEY

M2OR

SECTION V

PERFORMANCE

INTRODUCTION

The purpose of this section is to present the owner or operator with information needed to facilitate planning of flights with reasonable accuracy.

The Performance Data and charts presented herein are calculated, based on actual flight tests with the airplane and engine in good condition and the engine power control system properly adjusted.

The flight test data has been corrected to International Standard Atmosphere conditions and then expanded analytically to cover various airplane gross weights, operating altitudes, and outside air temperatures.

VARIABLES

It is not possible to make allowances in the charts for varying levels of pilot technique, proficiency or environmental conditions. Mechanical or aerodynamic changes are not authorized because they can affect the performance or flight characteristics of the airplane. The effect of such things as soft runways, sloped runways, winds aloft or airplane configuration changes must be evaluated by the pilot. However, the performance on the charts can be duplicated by following the stated procedures in a properly maintained MOONEY M2OR.

Examples are given to show how each chart is used. The only charts with no example are those where such an example of use would be repetitive.

To obtain effect of altitude and OAT on aircraft performance:

1. Set altimeter to 29.92 and read "pressure altitude".

2. Using the OAT grid for the applicable chart read the corresponding effect of OAT on performance.

— CAUTION —

Be sure to return to local altimeter setting in calculating aircraft elevation above sea level.

OPERATIONAL PROCEDURES FOR MAXIMUM FUEL

EFFICIENCY

For maximum fuel efficiency on the M2OR, proper mixture leaning during cruise flight must be accomplished. The TCM 10-550-G(6) engine in the M2OR has been designed to attain maximum fuel efficiencX at desired cruise power. Best power mixture (at 2400 RPM) has been determined to be 50 F (10 °C) rich of peak EGT. EGT is usually a more accurate indication of engine operation and fuel burn than indicated fuel flow. Therefore, it is recommended that the mixture be set using EGT as the primary reference instead of setting to a particular fuel flow.

The following procedures is recommended for setting cruise power and leaning to best economy at 75% power or less.

1. After leveling off, set manifold pressure and RPM for the desired cruise power settings as shown in this SECTION. At this point, mixture is at full rich from the climb.

2. Slowly move mixture control toward lean while observing EGT indicator. If leaning mixture toward peak EGT causes the original manifold pressure setting to change, adjust throttle to maintain that desired cruise manifold pressure and continue leaning until best economy setting is obtained.

ISSUED 11 - 99 5 - 3

.1.1.•

■

•••• ••• ,"1.1••••••••• .."

SECTION V

PERFORMANCE

PERFORMANCE CONSIDERATIONS

MOONEY

M2OR

RANGE and ENDURANCE ASSUMPTIONS

Range and endurance allowance is based on climbing at maximum continuous power to cruise altitude.

Range and endurance reserves of 45 minutes at cruise power have been allowed for. Other conditions used for Range and Endurance are listed on each chart.

OPTIONAL PROPELLER DE-ICE BOOTS

With the optional propeller de-ice boots installed, expect climb performance to be degraded approximately 50 FPM from what is presented in the manual.

LANDING GEAR DOORS

When snow and ice are likely to be present on taxi and runway surfaces, inboard landing gear doors should be removed. Accumulation of ice and snow could prevent landing gear operation.

If inboard landing gear doors are removed, a decrease in cruise speed and range can be expected and should be considered in preflight planning. To be conservative the following figures should be used:

Decrease of true airspeed at normal cruise power setting by approximately 5 KTAS.

An approximate adjustment to range data shown in this manual can be made based on flight time planned with landing gear doors removed from aircraft. For example, using the above cruise speed decrease for a 5 hour flight will result in a decrease in range of approximately 25 N.M.:

5 HR X 5 KTS = . 25 N.M. reduction in range.

— CAUTION —

Zero wind conditions seldom occur. In addition, varying atmospheric conditions, aircraft weight, mechanical condition of the aircraft and piloting techniques all affect the actual flight time and fuel used during a flight.

It is the pilot's responsibility to determine the actual operating conditions and plan the flight accordingly.

5 - 4 ISSUED 11 99

MOONEY

M2OR

160

150

140

130

'PO

110

100

- 10

- PO

- 30

- 40

FAHRENHEIT

ISSUED 11 - 99

SECTION V

PERFORMANCE

40 CELSIUS

5 - 5

SECTION V

PERFORMANCE

MOONEY

M2OR

NOMMEN MMMMMMMM ONE

CROSSWIND COMPONENT CHART

Flight Nth

EXAMPLE ,

WIND SPEED

ANGLE BETWEEN WIND

20 KNOTS

DIRECTION AND FLIGHT PATH- 35'

HEADWIND COMPONENT

CROSSWIND COMPONENT

16A KNOTS

11.2 KNOTS

■

0• mm

■

I 10.

MMMM

a

20 I

AMMO

30'

• .1.."

1.4

MMM

•:.41

,Fd IN

114,

40'

MEMN71

AM.

■

AN.Z.POON rn z z

• • •

Mom.%

IMMLZ ,

MUM A. M

MINIMUM

MOM

WW1

ENNEAMMMU milorm o M 60,

NE11.Z.BM

, MIEMANNEU

EINEINIMZENEMENIr.

MgMINECMOO.4

...21T27= LNIP/6711!

MErZ!EMMUNO•••:.

ENUMN.Z.ANnINEL o

U ML.

, ",

111:71E/Errn:MIMPiV

.... r,

'Amur

va MMMMMM :

•

A.Aim

•

■■

••

!AIME

:MUM

/NUM mons

A MMMMMM 1110/.

N \11\\'11.`

AN4P.

MlUYEANordNPAIONEN4 sumw.. ,:mw:dimar:moml , ■ !...-;..

Ilt.72r, M A M ! M 1117 liliOAPAMP:;4411MUNIPI.

1 , ,e0:,PtillEI ■

■

11AINIMMIMMIlm!-•.r111

".11NN

,1 . I

MMM r..'esew

..dommw

4\,••

0 41 6 C‘

■

WEEP

UM,:

NUOMPie

...,

60' i MEW!

• • •

M A

OMMIIMMIMM.IIMOOMMNOME1

..4MNE1

MUM

!• ■

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80' a ,

SEM M

1MM•

70'

MMMM

UWE

T ca INL.i.

, -.! ila 7 .

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1111111010NOW.0

■

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Z.1=1A

■

••1, i,•-4. lim.=n.

11 11 movirma-mcome:

EERNVi

ELP.WAAELVEL

WIZ liamwm.m. ,

150' C IN n

C11 ■■■

■

.7:mu

Cllift.r. C mirmarmo mig..!1

180'

■

I

EL -

16 0 MA

•1

•

140.

■ WA

1•••mINMUM:

110°.WidIANN ENN,NENENN '.

: n .1

UM. i.e

‘r l

M n

11111 m m ra l i a l MMMMM

IN'AMMEMEENNENUNEE --.

1NNOEMMMMMM

► ‘,

5 10 15 20 25

CROSSWIND COMPONENT IN KNOTS

30 35 40 45 50 55 60

TEMPERATURE CONVERSION

CROSSWIND COMPONENT CHART

5-6 ISSUED 11 - 99

MOONEY

M2OR

SECTION V

PERFORMANCE

AIRSPEED CALIBRATION

PRIMARY STATIC SYSTEM

POWER ON & OFF, GEAR UP, FLAPS UP

200

NOTES

INDICATED AIRSPEED ASSUMES

ZERO INSTRUMENT ERROR

190

180

0 z

170

160

‘

A a

150

140 ca

a . 130 c 4 4

..1 a120 u

' •

(,) 110 a

100

• • •

/ i

EXAMPLE

GIVEN IAS 129 KNOTS

FINDS CAS 130 KNOTS

60 70 80 90 100 10 120 130 140 150 160 170

IAS

INDICATED AIRSPEED

KNOTS

180 190 200

ISSUED 11

99 5 - 7

SECTION V

PERFORMANCE

MOONEY

M2OR

AIRSPEED CALIBRATION

PRIMARY STATIC SYSTEM

GEAR AND FLAPS DOWN

EXAMPLE:

GIVEN: IAS 80 KTS

FLAPS 10

POWER OFF

FIND CAS 79 KTS

NOTE: INDICATED AIRSPEED ASSUMES

ZERO INSTRUMENT ERROR

140

130

120

110

100

FLAPS 10 ° POWER ON

FLAPS

10° POWER

33 ° POWER

OFF

SPEED FOR

SAFELY LO

FLAPS

ERING

FLAPS 33 ° POWER ON

.11--.11F 11

5-8

50 60 70 80 90 100 110 120 130 140

IAS - INDICATED AIRSPEED , KNOTS

ISSUED 11-99

MOONEY

M2OR

SECTION V

PERFORMANCE

100

110

120

130

140

150

160

170

180

190

200

KIAS

DEMONSTRATED CROSS WIND IS 13 KNOTS

(THIS IS NOT A LIMITATION)

AIRSPEED CALIBRATION - PRIMARY STATIC SYSTEM (GEAR UP)

AIRSPEED CALIBRATION - PRIMARY STATIC SYSTEM (GEAR DN)

AIRSPEED CALIBRATION - ALTERNATE STATIC SYSTEM

GEAR &

FLAPS UP

KIAS

GEAR &

FLAPS DN

(10°)

KIAS

GEAR &

FLAPS DN

(33 0)

KIAS

-3.0

-3.6

-4.5

3.0

1.5

0.0

-1.8

-2.8

-5.1

-5.6

-6.1

-6.5

-7.2

-7.9

0.0

-1.2

-2.2

-3.2

-4.0

-4.7

-5.4

-1.0

-2.0

-3.2

-4.5

-6.0

-7.4

-8.8

NOTE: The minus sign indicates subtraction of the given numbers from

KIAS to obtain the corrected airspeed.

CONDITIONS: Power-ON, Storm Window & Vents - CLOSED,

Heater & Defroster - ON or OFF

ISSUED 11 - 99 5 - 9

SECTION V

PERFORMANCE

MOONEY

M2OR

ALTIMETER CORRECTION - PRIMARY STATIC SYSTEM

SEA LEVEL 12,500 FT. 25,000 FT.

KIAS Gear &

Flaps UP

Gear

Dn/10 °

Flaps

Gear

Dn/33 °

Flaps

Gear & Gear Gear

Flaps UP Dn/10 ° Dn/33

Flaps Flaps

Gear & Gear laps UP Dn/10 °

Flaps

Gear

Dn/33 °

Flaps

50 4 -3 -4 7 10 -5

-2

-3 3 -5 -4 4

-5

-7 7 -10

70 -3 -2 -9 -5 -3 -13 -8 -4 -20

80 -4 -8 -14 -6 -12 -20 -9 -17 -30

90 8 -11 -19 -12 -17 -28 -18 -25 -43

100 -6 -11 -22 -9 -16 -33 -13 -24 -50

110 2 -5 -23 2 -7 -33 4 -11 -51

9 20 120

130 21

31 47

140

150

160 12 17 26

170 9 13 26

180 8 12 18

190 10 22

200 12

18 27

NOTE: The minus sign indicates subtraction of the given numbers from the indicated pressure altitude to obtain correct altitude, assuming zero instrument error.

EXAMPLE:

KIAS = 110 .

FLAPS = 10 ° . . .

ALTIMETER CORRECTION: -7 ft.

(Subtract from Indicated Altitude)

INDICATED PRESSURE ALTITUDE:12,500 ft. PRESSURE ALTITUDE; =12,493 ft.

5 - 10 ISSUED 11 - 99

MOONEY

M2OR

SECTION V

PERFORMANCE

ALTIMETER CORRECTION - ALTERNATE STATIC SYSTEM

SEA LEVEL 12,500 FT. 25,000 FT.

100

110

120

130

140

150

160

170

180

190

200

KIAS GEAR UP

FLAPS

GEAR

&FLAPS

10° 33°

-95

-107

-126

-146

-53

-57

-69

-82

-13

-23

-27

-30

-32

0 -4

-6 -11

-14 -20

-23 -32

-32 -48

-42 -66

-53 -87

GEAR UP

FLAPS UP

GEAR &

FLAPS

10° 33°

GEAR UP

FLAPS UP

GEAR

&FLAPS

10° 33°

20 0 -7 30 0 -10

-9 -16

-20 -29

-14 -24

-31 -45

-19

-33

-39

-43

-48

-77

-34 -47

-47 -71

-62 -97

-78 -127

-29

-50

-68

-66

-72

-118 -

-51 -72

-72 -108

-94 -148

-119 -194

-84

-102 -

-128

-139

-158

-185

-215

-127

-155

-182

-211

-248 -

-282 -

-327 -

NOTE: The minus sign indicates subtraction of the given number from the indicated altitude to obtain the corrected altitude.

CONDITIONS: Power -ON, Vents & Storm Window - CLOSED,

Heater & Defroster - ON or OFF.

ISSUED 11 - 99 5 - 11

z

><

Z

O0

I—

CC al al

CO O- o09

•

0'9L O'SL 0'C9 0'C9 O'LS O'Lg GCS GCS

0'C8 0'28 0'69 0'69 g'29 g'29 0 . 8S 0'8S

0 CC ScIV13

N/A

❑ CI el‘ooq

00T ScI V1A

` N/A ❑ G elV3 ❑

0 . 78 S . C8 S'OL 0'OL 0179 S'69 S'6S 0.6S

.0 ScIV -IJ

'dr) aV39

- -

S'6L g'8L 0'99 0'99 g'6S g'6g g'SS gss ° CC SciViA

Nfi\ ❑ CE NV=

S'L8 S'98 O'EL g'2L g'S9 g'g9 019 019

00T S cIV -IA

` Nr\cia ato39

S'68 g'88 O'SL S'17L S'L9 0'L9 0'C9 S'29

S'78 g'68 O'OL 0'OL g'69 S'E9 0 . 6S 0'6g

.0 ScIV -IJ

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() CC SdV1J

N/A ❑ C1 elV39

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0'26 0'16 S'LL g9L S'69 S'69 g'79 S'79

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SVIN SV3>I SVIN SV ❑ N SVIN SVON SVIN SV3)4

N ❑ LLIS ❑ d cIV -IJ

GNV NV39 oS17 00C

NNVE JD 31 ❑ NV

(SON g221)

SE( -1 00L2

(SON 19£1)

SEFI 000C

(S ❑ N 82ST)

Sgt 89CC

11-1 ❑ I3t1

SS ❑ ND

(stop' creL) sv3A S'2L

(SON I9CT) ost

..0i sal

NAM

owe

1:03dS 11V1S

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SdV1J .31.1WVX3

21'd39 DNICINV1

1H9I3A

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1:133aS -11VIS

UI cn

C rn

•

TAKEOFF WEIGHT-LBS (KGS) TAKEOFF SPEED

KIAS

3368 LBS (1528 KGS)

3100 LBS (1406 KGS)

2700 LBS (1225 )(CS)

SPEED AT

50 FT-KIAS

• TAKEOFF DISTANCE

NOTE: 1. CONDITIONS OF HIGH HUMIDITY CAN RESULT IN AN

INCREASE OF UP TO 10% TO THE TAKEOFF DISTANCE.

2. MAXIMUM DEMONSTRATED CROSSWIND IS 13 KNOTS.

-1600

5000

-1400

4500

ASSOCIATED CONDITIONS

POWER

MIXTURE

FULL THROTTLE/2500 RPM

SET EGT TO TOP OF

BLUE ARC AS REQUIRED

LDG GEAR DOWN UNTIL

OBSTACLE CLEARED

WING FLAPS 10'

RWY SURF. PAVED

HUMIDITY

LEVEL, DRY

80% IS STANDARD

EXAMPLE:

OAT

PRESSURE

ALTITUDE

WEIGHT

HEADWIND

COMPONENT

GROUND ROLL

3250 LBS (1474 KGS)

5 KTS

1600F7 (488 M)

NO°

Amillmmorris

AIMINIEHML.16/1

3500

3000 0

arimmommons

11111111111111•11MIN

_MMIERLINIMPA

• IMEMEHE

IF Pr

2500

2000

1500

1000

L' u_

500

1000 u

-800

-600

400

-200

TOTAL TAKEOFF

DISTANCE

(50 Ft OBSTACLE)

17'C

1000 FT

2560 FT (780 M)

-30 -20 -10 0 10 20 30 40

OUTSIDE AIR TEMPERATURE

50 3368 3100 2900 2700 0 10 20 0 50 (15.3 M

WEIGHT - LBS WIND COMPONENT OBSTACLE HEIGHT

I I I I I

1500 1400 1300

DOWN RUNWAY - KTS FEET

WEIGHT

KGS m

^.)0

7D Z

MAXIMUM RATE OF CLIMB

FULL THROTTLE, 2500 RPM, 105 KIAS, FULL RICH, GEAR UP, FLAPS UP

1500

300 _ 18000 FT

200-20000 FT

■

11

■

=11111

1500 mm

ElMil

In

EXA PLE:

PRESS ALT

OAT

WEIGHT

5,000 FT

15 .0

2,850 LBS

RATE OF CLIMB 1180 FRM

MIMIMPlIPM

1400 1400

1 800 m

1300

900

500

400

14000

Sea Level

I I

2000

8000 FT

10000

12000 Fr n

mamma. initimum

111.2111111

16000 FT MIAM-bil

IMEMPAIMFILIM

-Ai

.../11

1200

1100

•

1000 `

PRESSURE

000

6000 FT

ALTITUDE

111113111 "

EIMIIIVIIIIIIIIIIMIMIMMESNM

ENTIMMMOINIIII

IIIIMMOMIIPIPAIMI

EITINANIMIUMITE

ERIMENIIMIllaral

ENIMINIIIIIMINPLIE

1300

1200

1100 z

1000

1.1-1

900 E

.

800 I

700 -

L.)

600

.m

500 LA

PIMIPNIMP

I I

400 i g

• 1111

6.441

/%1111MMIIIIETAIII

300

1111111111111101

200

100 bga-

OUTSIDE

20 0

AIR TEMPERATURE

11111 111111 111

60 2600

3368

3300 3200 3100 3000

WEIGHT

2900

LBS

2800 2700

1500 14'50 14'00 1350 1300 1

WEIGHT - KGS

'50 12'00 • •

100 mm

-n

Z

<

0

)

•

CRUISE RATE OF CLIMB

FULL THROTTLE, 2500 RPM, 120 KIAS, FULL RICH, GEAR UP, FLAPS UP

1500

1400

1 300

1200

1 100

-"-

I-

LL'

1000

900

4000 FT ME 1111111 co

800

1- -

(x

700

600

6000

8000

FT 1111 11 11

ENIEM

10000

I

7 ra

RIMINI

L,_ o

300

200

12000 k.

500

400

1 4 000 FT

•

rim

100

-80 -60 -40 -20 0

OUTSIDE AIR TEMPERATURE

- C

40 60

1500

1 400

EXAMPLE:

■

PRESSURE

Sea Level

ALTITUDE zum

2000 FT

ii ii

■

PRESS ALT

OAT

5 350 FT

15°C

WE GHT 2 850 LBS

RATE OF CLIMB 923 FPM

"Tim

NOM

EllIIIIIIIIIP-

,M1/.

/111.M1111

/1111WIMMIll

_______ ..-

■ 1Slaggillian

....M

MIMI

1110...-

1 300

1200

3368

3300 3200 3100 3000

WEIGHT

2900

- LBS

Bin rif

1:11 ■ 11

111.11111 ill_

11111

2800 2700

1500 1450 1400 1350 1300 1250 1200

WEIGHT

KGS

300

2600

200

100

1 100

1000.,

900 it'

800

co

700 -

600 L, o

500

I- a

400

a

ix

m

-

DJ fl

K-1

Z z m <

TIME-FUEL-DISTANCE TO CLIMB (MAX RATE)

FULL THROTTLE,

2500

RPM,

105

KIAS, FULL RICH, GEAR

UP,

FLAPS

C., e

C.,

1,11111511 '

MIIII,

_ c)

03 rl, Cc

0(:) i

N6) /

1 .37/

-\- h-

<0 - ii,

1 111111

=1.

•

----h e

. - '

' ..----

11,211112.1

3368 LBS/1528 KG gol

LBS/1179 KG 111111111111M

"Ell

EXAMPLE:

2600

DEPARTURE PRESS ALT:

DEPARTURE OAT:

CRUISE PRESS ALT:

CRUISE OAT:

1,000 FT

12,000 FT

10 °C

WEIGHT:

FUEL

CLIMB:

TIME

CLIMB:

DISTANCE

3368 LBS

5.0-0.4=4.6 GAL

15.5-0.8=14.7 M N TO

CLIMB: 31.5-1.7=29

Era

30 "V c\

'''' II czP

0°

463°

1 --111

20C3o - f

NI 1

15 20 25 30 35 40 45 50 55 70 75 80 85 80

OUTSIDE AIR

40 60

TEMPERATURE C

FUEL-GALLONS,

(LITERS

GALLONS

TIME-MINUTES,

3.785

DISTANCE-NAUTICAL

KILOMETERS

NAUTICAL MILES

MILES

1.852)

•

90 95

100

-o rn m

-n n

0 0

Z

><

0 Z

0 m

Fri

C m

ID

• • •

TIME-FUEL--DISTANCE

TO CLIMB (CRUISE CLIMB)

FULL THROTTLE, 2500 RPM, 120 KIAS, FULL RICH, GEAR UP, FLAPS UP

33 0

3368 LBS/1528 KG

, 2600 LBS/1179 KG

DISTANCE

....,

PRESSURE

ALTITUDE

16000 FT

14000 FT

—

12000 Fl

_10000

FT

dm la

8000 F7

I

6000 FT

4000 FT I

2000 Fl

I 1

—80 —60 —40 —20 0 20 40 60

OUTSIDE AIR TEMPERATURE — C

FA

I 1

II

• IFP

1 11111p1/

1111 pi

iiAll

,..r

1111111

EXAMPLE:

DEPARTURE PRESS ALT:

DEPARTURE OAT:

CRUISE PRESS ALT:

CRUISE OAT:

WEIGHT:

FUEL TO CLIMB:

TIME

TOCLIMB:

DISTANCE TO CLIMB:

S

14C

"

1,000 FT

30 °C

3368 LBS

3.3-0.4=2.9 GAL

11.3-1.0=10.3 MIN

23.8-2.3=21.5 NM

1 1 1 I 1 1 1 1 1 1 1

—

8,000 FT

10 °C —

—

0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100

FUEL—GALLONS, TIME— MINUTES, DISTANCE—NAUTICAL MILES

(LITERS = GALLONS X 3.785 KILOMETERS = NAUTICAL MILES X 1.852)

0 m

(,)

O

(-)

m

CJ1

EXAMPLE:

M2OR CRUISE POWER SET - INGS AND FUEL FLOWS

Cruise Alt. 8000 ft.

OAT g° C (SEE NOTE)

Power Setting Desired 75%

BEST POWER 50'F Rich of Peck

/MP 2500/22.3

Fuel Flow 16.0

RPM

Max.

Recommended

75% Power

2400 2500 2300 2400 2500

65% Power

230012400 2500

55% Power

2300

45% Power

2400 12500 2300 2400 2500

Pressure

Altitude

(Feet)

Fuel

Flow

Std. Day

Best

POWER

Std. Temp.

17.8 17.9 15.8 15.9 16.0 13.9 14.0 14.1 11.9 12.0 H2.1 10.0 10.110.2

MANIFOLD PRESSURE - INCHES OF MERCURY

S. L. 15'C 59'F 27.0 26.2 25.5 24.5 23.2 22.9,21.9 20.8 20.5 19.4 18.3 18.0117.2 16.4

2,000 11t 52°F 26.5 25.7 25.0 24.0 22.8 22.521.6 20.5 20.1 19.0 17.9 17.5 16.8 16.0

4,000 7°C 45'F 25.2 24.4 23.4 22.5 22.1 21.3 20.2 19.7 18.7 17.6 16.9 16.3 15.7

23.8 23.0 22.2 21.6 20.8 19.7 19.3 18.3 17.3 16.6 16.0 15.4 6,000 3°C 387

8,000 - IC 31'F 21.9 21.1 20.3 19.2 18.9 17.9 16.9 16.3 15.7 15.1

20.7 19.8 18.7 18.5 17.6 16.6 15.9 15.4 14.8

19.2 18.4 18.1 17.2 16.3 15.6 15.114.5

10,000 -5t 23'F

12,000 -9'C 16'F

14,000 -13t 9'F

16,000 -17t 2°F

17.7 16.9 16.0 15.3 14.8 14.3

15.7 15.0 14.6 14.1

14.8 14.4 13.9 18,000 -21C -5°F

20,000 -25'C -12F

NOTE: Add .4" MP for each 10'C (18'F) OAT above standard day temperature. Subtract .4" MP for each

10'C (18'F) below standard day temperature. If OAT above standard precludes obtaining the desired MP, use the next higher RPM/MP With appropriate temperature correction to MP.

•

14.113.7 mm a) 0

0 m

Z om

33-<

co cl;

rn

m

•

EXAMPLE:

Cruise Alt. 8000 ft.

OAT 9° C (SEE NOTE)

M2OP CRUISE POWER SETTINGS AND =DEL (LOWS

Power Setting Desired 65%

BEST ECONOMY 50•F Lean of Peak

Max.

Recommended

RPM/MP 2300/22.7

Fuel Flow 12.2

RPM

75% Power 65% Power 55% Power

2400 250012300 2400 2500 2300 2400 2500 2300 2400 2500 2300 240012500

45% Power

,Pressure

Altitude

(Feet)

Fuel

Flow

Best

ECON.

16.3 16.4 14.3 14.4 14.5 12.2 12.3 12.4 10.2 10.3 10.4 8.2 8.3 8.4

Std. Doy Std. Temp. MANIFOLD PRESSURE - INCHES OF MERCURY

L. 15t 59°F 28.2 27.4 26.7 25.7 24.4 24.1 23.1 22.0 21.7 20.6 19.5 19.2 18.4 17.6

2,000 llt 52'F 26.9 26.2 25.2 24.0 23.7 22.8 21.7 21.3 20.2 19.1 18.7 18.0 17.2

4,000 7°C 45'F 25.6 24.6 23.7 23.3 22.5 21.4 20.9 19.9 18.8 18.1 17.5 16.9

6,000 3°C 38°F 23.4 22.8 22.0 20.9 20.5 19.5 18.5 17.8 17.2 16.6

8,000 -1°C 31'F

10,000 -5°C 23'F

12,000 -9°C 16'F

14,000 -13°C 9°F

16,000 -17°C 2T

18,000 -21°C -5°F

20,000 -25t -12'F

22.3 21.5 20.4 20.1 19.1 18.1 17.5 16.9 16.3

21.0 19.9 19.7 18.8 17.8 17.1 16.6 16.0

19.3 18.4 17.5 16.8 16.3 15.7

17.2 16.5 16.0 15.5

16.2 15.8 15.3

15.6 15.1

14.9

NOTE: Add .4" MP for eoch 10*C (18'F) OAT above standard day temperature. Subtract .4" MP for eoch

10'C (18'F) below standard day temperature. If OAT above standard precludes obtaining the desired MP, use the next higher RPM/MP with appropriate temperature correction to MP.

0 m

n

0 m

DJ 0 z 5 m <

Lu o o

2 cNi z 2 z

C.) ssi z z

>< z

00 u_

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Lu Lu w ocz

•

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•

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•

alt , 0 - 39111V3c1V431

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o

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Clean Configuration, B9.0 Gallons (337 Liters) (74 Imp. Gal.) Usable Fuel

Zero Wind, Range includes Wormup, Taxi, TokeoFf,

Max Power Climb Descent, Pius 45 Minutes Reserve at Cruise Power

CAUTION

IT IS RECOMMENDED THAT OPERATOR

CALCULATE RANGE FOR ACTUAL CONDITIONS. 3368 LBS (1528 KGS)

RANGE

•

N 0

?D O rn

F lA

i iil I

A I

!ft! i

,,,„,. roil BEST POWER EXAMPLE ,

PRESS ALT 10000 FT

OA T -1 ° C

POWER 65X

RANGE 970 N.M. (1795 KM)

Eii

•E# (5‘.C\'‘

55% r

757.

657.

-80 had

-60 -40 -20

0 20

OUTSIDE AIR TEMPERATURE -•C

40 60 800

900 1000 1100 1200

RANGE - NAUTICAL

(KILOMETERS = NAUTICAL

MILES

MILES X 1.852)

1300 rn

n o)

O m

K-1

> z z

m<

Clean Configuration, 89.0 Gallons (337 Liters) (74 Imp. Gal.) Usable Fuel

Zero Wind, Range includes Warnup, Taxi, Takeoff,

Max Power Climb Descent, Plus 45 Minutes Reserve at Cruise Power

ilirling

CAUTION

IT IS RECOMMENDED THAT OPERATOR

CALCULATE RANGE FOR ACTUAL CONDI IONS

11 Illiip

, /

RANGE

3368 LBS (1528 KGS)

,....

_411 vary

r

YIL

I c7)

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-80

cofra

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NAG

-60 -40 -20 0 20

OUTSIDE AIR TEMPERATURE -*C

4D 60

BEST ECONOMY EXAMPLE.

PRESS ALT 10000 FT

OAT -I ° C

P ° W ER"4 1250 NM (2315 KM)

900

A ii I

1 I

II II ll i

1000 1100 1200

RANGE

(KILOMETERS

1300

- NAUTICAL

= NAUTICAL

MILES

MILES X

1400

1.852)

•

1500

13(1)

M m

DD 0

— n

13 Z

0 n.) Z

0 m

•

Clean Configuration, 89.0 Gallons (337 Liters) (74 Imp. Gat) Usable Fuel

Zero Wind - Endurance Includes Warnup, Taxi, TakeoFF,

Max Pwr. Climb, Descent, Plus 45 Minutes Reserve at Cruise Power

CAUTION

Operator should compute endurance based on actual conditions.

ENDURANCE

<Standard Day)

3368 LBS (1528 KGS) t

— -O.

Al

BEST POWER EXAMPLE

PRESS ALT 11000 FT

POWER 65%

ENDURANCE

-. — — -....

5.60 HOURS

---1,... - — — ip..

75 / I

_ _

Sea

Level

2 4 6 8 1D 12 14 16

PRESSURE ALTITUDE - (FEETx1000)

18 20 4

1--

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65%

, i',.."' 55%

5 6

ENDURANCE - HOURS

45%

-a

rn

O m

Clean Configuration, 89.0 Gallons (337 Liters) (74 Imp. Gal) Usaloe Fuel

Zero W ∎ ncl - Endurance Includes Warmup, Taxi, Takeoff,

Max Pwr. Climb, Descent, Plus 45 Minutes Reserve at Cruise Power

CAUTION

Operator should compute endurance based on actual conditions.

ENDURANCE

(Standard Day)

3368 LBS (1528 KOS)

1T1

CO rfl

DJ 0

71 —I

45%

- -41.

BEST ECONOMY EXAMPLE

PRESS ALT 11000 FT

POWER 557.

ENDURANCE

- - -- -Bw-

7.55 HOURS

- -0. .- -

657

757;

N.-

<

4 -

55%

'0:.

., \N "

- -1

•

Sea

Level

2 4 6 8 10 12 14 16

PRESSURE ALTITUDE - (FEETx1000)

18 20 5 6 7 5

ENDURANCE - HOURS

N o m

MOONEY

M2OR

TIME-FUEL-DISTANCE TO DESCEND

SECTION V

PERFORMANCE

TIME-FUEL-DISTANCE TO DESCEND

150 KIAS DESCENT SPEED

ASSOCIATED CONDITIONS!

POWER , 2000 RPM/MAP AS REQ'D TO MAINTAIN

750 FPM RATE OF DESCENT

LANDING GEAR , UP

FLAPS , UP

MIXTURE ,

LEAN TO BLUE ARC or ENRICHEN FOR SMOOTHNESS

ISSUED 11 - 99

EXAMPLE'

INITIAL PRESSURE ALT'

FINAL PRESSURE ALT'

18000

4000

TIME TO DESCEND ,

FUEL TO DESCEND'

24.0-5.0=19 MINUTES

3.6 -0i= 2.9 GALLONS

DISTANCE TO DESCEND! 69.0-130 =56.0 NAUTICAL MILES

25000

20000

15000

10000

5000

•

1 25 30 35 10 15

TIME-MINUTES

,

I I

1.0

FUEL-GALLONS

,

I I I

2.0 3,0 4.0

(LI ters=al X 3.785)

, 1 1

1 i

5.0 6.0

40 60 80 100 20

DISTANCE-Nautical Miles (K m=NM. X L 852)

5-25

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Key features

Maximum speed of 235 knots
Range of over 1,000 nautical miles
Garmin G1000 NXi avionics suite
Electrically operated, fully retractable tricycle gear
Hydraulically operated disc brakes on main gear

Frequently asked questions

The maximum gross weight of the Mooney M20R - Ovation is 3368 Lbs. (1528 Kg).

The fuel capacity of the Mooney M20R - Ovation is 95 U.S. Gal. (359.6 Liters).

The range of the Mooney M20R - Ovation is over 1,000 nautical miles.