Mooney M20J 1978 Operating Manual

CONGRATULATIONS . . .

WELCOME TO MOBNEYvS NEW DIMENSION IN SPEED

MOONEY

AN

ELITE AND DISTINC

-

TIVE CLASS

OF

AIRCRAFT OWNERS.

WE HOPE
YOU FIND YOUR NEW MOONEY A UNIQUE FLYING
EXPERIENCE, WHETHER

EVER.

is

provided as an operating guide for the

Mooney

201,

Model

--

regardless of your previous experience--

carefully
read the handbook from cover to cover and review it
frequently.

on the latest

publication approval.

The

is

reserved to make

without notice*

Every effort has been

in

a

and conveniea2t

manner to enable you to

the

as

a

ready

reference,

in

and content recommendations

is

solicited.

THE

Page

of this manual

is

a "List

of Effective Pages

"

containing a complete etarent listing of aXB pages

,

Original or Revised. Also, in the lower

corner of the outlined portion,

a box which denotes

the issue or revision of the
revision to the manual a new List of Effective Pages

be received to replace the previous one*
This handbook will be kept current

by

Mooney Aircraft

handbook

has

been filled in and mailed to Mooney Aircraft

Corporation,

Box

72,

11-15-77

TABLE

OF

CONTENTS

SECTION

................

a

.............

......

EMERGENCY PROCEDURES

........

PROCEDURES

4

PERFORMANCE

5

..........

WEIGHT

BALANCE

SYSTEM

...........

7

SERVICE

.........

MAINTENANCE.

8

........

ISSUED

.

4

BLANK

SECTION

I.

TABLE

OF

CONTENTS

TITLE

PAGE

. .

.

.

.

.

DATA

.

WEIGHTS

STANDARD

WEIGHTS

1-5

DIMENSIONS,

.

.

.

AIRSPEED

ME

FLIGHT

WEIGHT

ISSUED

THREE

ISSUED

1-15-77

This Rlot

Operating hndbsok contaim

and includes the material rquired to be fwnished to

by

3.

data

by

I

used in this Pilot's 9eratiq andbook.

DATA

LANDING

GEAR

TYPE

operated

wheel,

brakes.

Base

11-9/16

Tread

9

Nose

Main

6

x

6

Tire Pressure:

Nose

49

Main

30

PSI

(No Brakes Applied)

TYPE

air

cooled,

and fuel

-

injected engine with a wet-sump

sys

-

tem.

Number

of

Engines

Recommended

RPM

200

BNP

Sea

Bore

5.3125 in.

361.0

Compression Ratio

Fuel Injector, Bend&

Magnetos, Bendix

PROPELLER

TYPE

Constant- speed, hy&aulically controlled pro

-

peller with

a

Diameter

73

Number

of

Blades

2

Blade Angle

30

Low

Nigh

Usable

Capacity

Gal.

Minimum

Fuel

Blue

Capacity

(6

QTS

MIN for

8

are

contained in Seetion

CERTIFICATED

WEIGHTS

Weight

Baggage

Area 120

ISSUED 11-15-77

STANDARD AIRPLANE WEIGIlTS

Basic Empty Weight

(See page

6-4)

BAGGAGE SPACE' AND ENTRY DIMENSIONS

Baggage Area
Hal Rack

x

(Max.)

(2.6

Baggage Door Opening

Above Ground

(Sill)

46

"

Entry Width

20.5

"

SPECIFIC LOADINGS

G.

16.4

Power Loading

PHP

ABBREVIATIONS

GENERAL

Calibrated Airspeed means the ia~dicated speed
of an aircraft, corrected

-

ment error. Calibrated airspeed is equal to

true airspeed in standard atmosphere at sea

GS

Ground Speed is the speed of an airplane

relative to the ground.

IAS

Indicated Airspeed

is

the speed of an aircraft

as shown on its airspeed indicator. IAS values

published

in

this handbook assume zero instru

-

ment error.

True Airspeed is the airspeed of an airplane
relative to undisturbed air.

REVISION

Maneuvering

Speed is the maximuin speed at
which application of full available
control will not overstress the airplane.

Maximum Flap Extended Speed is the highest
speed permissible with wing flaps in a pre

-

scribed extended position.

Maximum

is

the

maximum speed at which an aircraft can be

safely flown with the landing gear extended.

Maximum Landing

is

the

be safely extended or retracted.

Never Exceed Speed or Mach Number is the
speed
time.

Maximum

in

air

and thela only wit

caution.

speed at which tlae airplane is contm-obkable.

Stalling

Speed or the rni.nimum steady flight
speed at which the airplane is controllable in
the

Best Angle

-of-

Climb Speed

is the airspeed

which delivers the greatest

in

the shortest possible horizontal distance.

Best Rate

-of-

Climb Speed is the airspeed which
delivers the greatest gain in altitude in tlae
shortest possible time with gear and flaps

11-15-77

is

air

static temperature, obtained either from
meteorological sources. It

expressed

The

The pressure

at

sea level

is

29.92

(4)

The

temperature

gradient

sea

to the aanfteads at

which the temperature

is

per foot.

Indicated The number

read from

an

alti

-

meter when

when,

barometric

to

29.92

Pressure altitude

is

altitude corrected

position

and

In this handboolc, altimeter

assumed

to

be

zero.

Density Altitude

as

determined

by

Altitude and existing ambient temperature.

In

density and
pressure altitude are
pressure altitude,

the

tempera

-

ture, the

atmospheric

Pressure elevation.

ENGINE

POWER

BHP

is

the power developed

by the engine.

RPM

is

MP

Manifold Reaeure

is

a

ax

-

Demon

-

is

the

the crosswind component

for

takeoff and landing wae actmlly

certification tests.

The

shown

is

considered

to

is

the acceleration

to

gravity.

is

the

the capability

climbing

AWD

imaginary vertical plans from

all horizontal distances

are

measured

lor

purposes,

A

location along the airplane fuselage
the reference
The horizontal distance from the reference

datum to the center of gravity

of

an

The prduct of

the

weight of an item

arm.

(Moment divided

by

a

used

to simp%i$gv balance cal

-

culations

by

of

digits.

)

.

Arm

arm obtained

by

individual moments

sum

by

the total wsigkat.

C.G.

The

extreme center of gravity locations within

Limits which the airplane must

be

operated at a given

weight.

Center of

The point at which an airplane would balance if

Gravity suspended. Its distance from the reference

.

datum is found by dividing the total moment

by

the total weight of the airplane.

Usable

Fuel available for airplane pro;ulsion.

Unusable
Fuel

completed in accordance with governmental
regulations.

The maximum weight is the maximum authorized

Weight weight

of

the aircraft and its contents as listed

in the aircraft

The

basic empty weigh"c. of

is

and

includes all operating

has a fixed location and

is

actually installed

the airc-sa.ft. It includes the weight

the

is

the empty weight subtracted

fuel, passengers, and baggage,

Tare

Tare is the weight
etc. used when weighing an airplane, and is
included

in

the scale readings.

Tare is de

-

ducted from the scale reading to obtain the

(1-10

Blank)

.

TABLE

OF

TITLE

INTRODUCTION

2-2

AIRSPEED

2-3

ED

INDICATOR

2-4

.

POWER

LIMITATIONS

2-5

POWER

PLANT

INSTRUMENT

2-6

WEIGHT

CENTER

OF

2-7

MANEUVER

LOAD

FACTOR

2-9

O

PERATI

O

N

2-9

INSTRUMENTS

AND

.

.

2-9

...............

2-10

INTERIOR

2-10

2-13

FAA

APPROVED

-15-

77

Section

2
markings, and basic placards necessary
operation of the airplane, its engine, standard sy sterns

and standard equipment. The
this section have

Administration. When applicable, limitations associated

with
are included in Section

9.

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

with the normal

being

to

for

airspeed calibration variations be

-

tween the ~aormal and

alternate

shown

in

Section

5.

is

certificated under

FAA

Type

Certificate

as Mooney M20J0

Mooney

Airplane Flight Manual

FAA

APPROVED

ISSUED

Airspeed limitations and their operatiom% significance
are shown in Figure

This calibration assumes

zero

Do not exceed this speed

Do not make

or

Do

not

exceed

FIGURE

2

-

AIRSPEED

Airplane

Flight

2-3

Airspeed indicat or mar kings, their color code and operational

Green

Arc

be

conducted

with

and only-

_..---*

-

FIGURE

2-2.

2-4

FAA

APPROVED

11-15-77

POWER

PLANT

Engine Manufacturer: Avco Lycoming.
Engine
Engine Operating Limits for Takeoff and

Continuous Operations

Maximum Engine Speed: 2700
Maximum Cylinder Head Temperature: (4~5'~).
Maximum

Temperature: (24~~~).

Transient Engine RPM Limit - 2970 RPM for

3

Seconds or Less

Oil

Pressure, Minimum:

25

psi.

Maximum:

Fuel

Pressure, Minimum:

psi

Propeller Model Number: ~2%)3462%4/90~~~-16E

93

inches,

Propeller Operating Limits: Avoid contineeous operation

between 1500 and

RPM

power

settings

below

Angle

38

High

33.

POWER

Tachometer

Radial Red Line (Rated)
Green

Ar

--

(Rated

operating range)
Yellow Arc (Caution Range)

Cylinder Head Temperature

Radial Red Line
Green

Arc

(Operating range)

Pressure

Radial Red Line

idling)

Radial

Wed Line

Green

Arc

(Operating range)

Yellow

Arc (Idling range)

Arc

(Starting

warm-up range)

Fuel

Pressure

Red Line

(Minimum)

Radial

Red

(Operating range)

Radial

Red

Are

(Operating range)

Mooney M205

Flight

2-6

2700

RPM

25

PSI

aoo

60

to 90

to

14

30

PSI

to

30

PSI

FAA

APPROVED

REV

9-29-82

Landing)

2740 LBS.

in

Baggage

Compartment

120 Lbs.

Maximum

Weight

in

.

10 Lbs.

Fus. Sta. 119.

CENTER

OF

(GEAR

Most Forward 41.0

in

IN.

)

MAC

2250 LBS.

Intermediate Forward 41.

IN. (Fus, Wa.

)

MAC.

Forward Gross 45.0

.)

MAC

in IN.)

2740 LBS.

MAC

(IN.

at

Wing

Wa.

93-83)

59.18

Datum

is

5

of the center

of the nose

gear

attaching

33 inches

forward

of

the

'leading

edge

at

station

59.

FAA

APPROVED

ISSUED 11

-15-

77

Airplane

Manual.

MANEUVER LIMITS

This airplane must be operated as

a

airplane.

obatic maneuvers , including spins, are

not approved

.

Extreme sustained sideslips may result

in

fuel venting

thereby causing fuel fumes in the cabin.

Prolonged sideslips, steep descents,
or
of power if the selected fuel

tank

con

-

tains less than

48

(8

Up

290-foot

may

at

above 190

MPH

IAS

Above 190

(164

rapid throttle seduction may re

-

sult

in

momentary propeller

RPM

Mooney

FAA

REVISION

LOAD

LIMIT3

Flaps

...................

OPERATION

Do not

operate

in hown ici~ conditions,

is

a

when

quipped

accordance with

FAR

FUEL

2

93.25

Total Fuel:

8.

Gallons

Fuel

5

Gallons

A

reduced fuel qmntity indicator

is

installed

in

lank,

These

indicators show

25

usable

in each tank

fuel

(low lead) aviation fuel (blue) with

a lead

2

is

also

approved,

INSTRUMENTS

AND

operated:

Artificial horizon
Directional gyro

FAA

APPROVED

11-15-97

Airplane

DECALS

PLACARDS

INTERIOR:

The

following

placards

must

be

installed

inside

the

cabin

at

the

specified.

OPERATIONAL

T

H

I

S

O

PER

A

TED

A

S

IN COMPLIANCE WITH

THE

OPERATING LIMITATIONS STATED IN

THE

FORM

OF

PLACARDS,

MARKINGS AND MANUALS. NO AEROBATIC MANEUVERS,
INCLUDING SPINS, AWE
EXTENDED,

MPH.

MAX

SPEED TO EXTEND GEAR,

MAX

MANEUVERING

FLIGHT

LOAD

FLAPS I1P

EMERGENCY

GEAR

EXTENSION

I

2

PUT GEAR SWITCH IN

3

REL

E

A

S

E

F

O

RWA

R

D

L

IFT

U

P

R

E

D

UP

20 INCPIFS)

5

TO RETURN

TO

ORIGINAL POSITION

LIGHT

COMES

QN

20

IF

ELECTRICAL FAILURE

-

SEE

MECHANICAL INBlCA'rOR

CHECK

-

UP

SEAT

MIXTURE

FLAPS

RAM

AIR

SEAT BELT

WINDOW

RAM AIR
MIXTURE

GEAR

FAA

APPROVED

Airplane

ISSUED

11-15-77

On

Lower

Left

Instrument

TURN OFF STROBE LTS
WHEN TAXIING NEAR
OTHER

OR WHEN
FLYING IN FOG OR IN
CLOUDS
LTS MUST BE USED FOR
ALL NIGHT OPERATIONS.

2

IN CASE OF FIRE TURN
OFF CABIN HEAT.

3

DO NOT SCREW VERNIER
CONTROLS CLOSER THAN

FROM NUT FACE.

PULL

ALTERNATE

Pilots Window

DO

NOT

OPEN

M.P.H.

On

Right

Instrument

Panel

Below

Manifold

Gage

SGTT

On

Lower

Controls

On

Lower

Console Below Controls

FAA

APPROVED

ISSUED

15-77

Airplane Flight

Manual

Fuel

Valve

Baggage

MAXIMUM

Door

Inside

Baggage

Door

.

.

FAA

APPROVED

Manual

11-15-97

The

following

placards

must

be

installed

on

the

of

the

aircraft

locations

specified,

On

Gear

Nose

Gear

On

Fuel

Tank

,

---.-

(GREEN)

OR

BLUE)

3%

On

Leading

of

Horizontal

and

Trailing

Edge

Sides

Rudder

11-15-77

Plight

Inboard

End

of

Right

Flap

STEP

On

Underside

of

Wing

Airplane

Manual

ISSUED

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

-

a

definite plan of action for coping with the most probable
emergency situations which could occur in the operation

As

it

is

not possible to have a procedure for all types of

emergencies that may occur,

is

the pilot's resgonsi-

knowledge of
of action. Therefore, It is considered mandatory that
the pilot
before

When applicable, emergency procedures associated with
optional equipment

in

Section

indicated

and

zero

instrument

error

ANNUNCIATOR

PANEL

WARNING

LIGHTS

Warning

Fault

Remedy

Gear Unsafe

is

not in fully extended/

retracted position. Refer to

"

Failure

of

"

procedure

on

page

3-8

or "Fail~are

of landing gear to retract after take

-

off" procedure on page

3

-

%%.

Left or Right

2

to

3

the respective tanks.

Switch lo

Suction

is

(Steady)

Suction

5.5

inches of mesceary.

Attitude and dfrectioa~l gyros

reliable,

Vacuum

be

as

soon as

practicable.

Volts

"

Alternator Power

Loss

"

on page

3- 9.

Ram

air door

is

open (when landing

gear e%eended); close before landing.

REVISION

FIRE

-

GROUND

1.

Mixture

-

2.

Fuel Selector Valve Off

3.

Master Switch - Off

4.

Extinguish with Fire Extinguisher

FIRE

-

IN

-

OFF

2.

Throttle - C losed (Full Aft)

3.

-

Cabin Ventilation

Heating Controls - CLOSED

(Control Forward)

5.

-

DOWN OR

UP,

depending on terrain.

6.

Wing Flaps - EXTEND.

As

Necessary.

If

fire is not extinguished, attempt to iaacseaae

airflow over the engine

by

increasing

glide?

speed.

a power off landing as described

this

Do

not attempt

an

engine restart.

ELECTRICAL

IN

(Smoke in Cabin)

Master Switch - OFF.

Gear warning is not available with master switch

2.

Cabin Ventilation - Open

3.

Heating Controls

-

Circuit Breakers - CHECK. To identify faulty

circuit if possible.

Land as soon

as

to identify and isolate the faulty circuit as follows:

1.

Master Switch - ON.

2.

Select essential. switches

one at

a

and

permit a short time to elapse before activating an

additional circuit.

3-4

11-15-77

GROUND

ROLL

Braking

-

Fuel Selector

-

OFF.

Master and Magneto/%art Switch-OFF.

AFTER

LIFTOFF

AND

-

Select Other Tank.

2.

-

ON.

3.

-

RICH.

-

CHECK

ON

BOTH.

If
landing.

QR

LOSS

OF

POWER

IN

Immediately upon noting any condition

or

rough epxsgixae operation), perform

time

and altitude permit.

Fuel

-

FUEL

SELECTOR

TO

TANK.

Fuel Pressure

-

PUMP

ON

IMPROVE

3.

-

4.

-

Switch to left and right
single magneto operation; if no improvement,
switch to

noted, proceed to land as soon

as

practicable.

AIR

START

PROCEDURE

Propeller

-

(Full Forward).

Fuller Tank.

3.

Control

-

Cutoff (Full Aft).

-

Check.

no fuel pressme is

noted,

ON.

-

Both.

Mixture Control - Move slowly and smoothly

RICH (Forward).

8.

Re-establish cruise power and

RPM

then lean

engine fails to start establish best glide speed

indicated by the

POWER

OFF

MODEL

POWER

Emergency Locator Transmitter

-

ON

,

As

Required, (if installed)

2.

-

Fuel Selector Valve

-

5.

-

OFF.

6.

PULL

DOWN

7.

-

Down or

If-15-77

REV

9-29-82

8%.

MPH

Master Switch

-

OFF,

Up

to

2000

feet

of

altitude may be lost in

one turn spin and

recovery; therefore, stalls at low altitude are extremely

The best spin recovery technique

is

to avoid flight conditions

spin

entry.

Low speed flight near stall should

be approached with caution and excessive flight control

in

this RligM regime should be avoided,

an

to progress into a deep stall. Fast, brat smooth stall recovery

spin, If an

unusual post

a

quick

application of anti-spin procedures should shorten the

ARE

In

the event of

an

be used:

Rudder

-

FULL

RUDDER

opposite the direction
of spin,
Control Wheel - FORWARD of neutral in

a

be

required

if

the rotation does not stop.

3.

-

4.

TO

Hold anti-spin co&roRs until rotation stops:

-

as

possible.

6.

Rudder

-

Control Wheel - Smoothly move

to bring the nose

up to

a

level flight attitude,

ISSUED

15-77

9-29-82

OF

TO

EXTEND

Airspeed

2.

PULL

Gear Switch

-

4.

FORWARD,

LEVER

BACK.

Slowly u%l

1

to 2 inches (2.5 to

5.1

it

5.

-

to 20 inches) and

RETURN

gear 18 down and locked, GEAR

to 20 pulls).

6.

Down Indicator

-

Check

viewing from

activating

electrical

system.

Gear Adwtor

not operate kndiw gear electrically

GEAR-UP

a

normal

When

are

sure

of

Mixture

-

(Full

Aft).

3.

-

OFF.

4.

Fuel Selector Valve

OFF.

5.

Keep

level d~aring touchdown.

UNLATCHED

IN

the cabin door

is

not locked it may come unlatched
flight. This may occur during or just after take-off.
The door will trail in a position approximately

3

inches
open, but the flight characteristics of the airplane will
not be affected.

Return to the field

in

a

normal manner.

-

out have a passen

-

ger hold the door to prevent it from swinging open.
If it is deemed impractical to

can be closed in flight, after reaching a safe altitude,

by

the fo%%owing procedures:

Slowtoapproximately 1%0mph/96Mse

2.

Open the storm window to redrace cabin air pressure.

3.

4.

in

a right slip) and close the door,

LOSS

red

steadily,

the

radio

switch

off

and

oaa

to reset the voltage regralator. If the voltage

light comes on again

equipment not essential for
flight should be turned off and the flight terminated as
soon as practical to correct malfunction.

A

flashing

voltage

-

resetting the alternator field breaker does not restore the

alternator, turn off

as

soon as practical,

tripped main alternator circuit breaker can

only be caused

by

a

shorted alternator circuit

breaker. This should be verified by

ing to reset the breaker not more than one time.
If this fails, pull the alternator field breaker,
turn off all non

-

essential electrical equipment

and terminate

OPERATE

icing conditions are inadvertently encountered:

Turn

Do not turn ram air on again

when

air

until assured all ice and

snow

melted from tlae aircraft.

2.

Shut cabin heat off until. engine operation

is

normal.

3.

Push

(if

installed).

4.

air

source to

ALTERNATE

(if

installed).

Turn back or change altitude to obtain an outside

air

temperature less conducive to icing.

ALTERNATE

SOURCE

The

alternate static air source should

it

is

suspected that: the raoranal. static air sources are blocked.

Selecting

the

alternate position changes the source of static
air for the altimeter, airspeed indicator and
from the outside of the aircraft to the cabin interior.

air

source

is

use adjust the
indicated airspeed and altimeter readings according to the
appropriate alternate static source airspeed and altimeter
calibration tables in Section

5.

he static air source valve is located in the lower left

portion of the pilot's flight

left

knee.

FAILURE

OF

GEAR

TO

RETRACT

AFTER

TAKEOFF

The following procedure applies to all
aircraft modified with the airspeed
safety override system with the

PASS

"

switch

24-0238

and above)

and

aircraft prior with the mechani

-

retraction

"

BY

PASS

"

switch in accor

-

In the event that the gear fails to retract when the landing
gear control switch

is

placed

in

the

"UP"

position due to

the failure of the airspeed sensing or squat safety

lo activate after takeoff, the followtlag procedure should

be

as

an alternate means to

retraction:

fails

lo

actuate,

as

evidenced

by

sf

the

BY BASS

"

the

activation

the gear warning &zorn, depress

SAFETY

BY

PASS" switch and hold until gear is
This is evidenced

by

both the

gear unsafe and

gear

down

"

(2)

"

GEAR

circuit breaker to shut off gear
horn.
of the horn, but must be reset prior to

ex

-

tension of the landing gear).

(3)

"

GEAR

circuit

breaker

the

position.

Check "AESPEED" or

safety switch to

determine

11-15-'77

3

-

TIT

SECTION

TABLE

OF

PAGE

PREFLIGHT

INSPECTION

. a

BEFORE

STARTING

CHECK

STARTING

ENGINE

.

4-4

BEFORE

TAKEOFF

.

.

.

4-5

TAKEOFF

OBSTACLE

CLEARANCE

4-8

4

-

NORMAL

4-9

4-10

.

.

.

.

.

BEFORE

LANDING

.

.

4-11

GO

(BALKED

LANDING)

.

4

-

4-12

4-13

.

.

.

.

4-13

FIGURE

WALK

a.

Switch,--

OFF.

Gear Switch--NWN.

Master Switch--ON to

check

OFF.

and hold far

five

seconds,

on

2.

-- UNOBSTRUCTED.

Tail

-

REMOVE.

3.

rudder attach

points. Remove

snow, or frost.

Instrument Static Port--mOBSTR%TCTED.

5.

Wing Skins--

CHECK.

Flap and Attach Points

--

CHECK.

Aileron and Attach Points

--CHECK

.

Wing Tip Strobe and Navigation Light--CHECK.
Remove all ice, snow, or frost.

Wing

--

CHECK.

Fuel Tank--

CHECK QUANTITY:

reduced fuel indicator

is

neck. This indicator

is

used to indicate use-

able fuel capacity of

25

S. gallons,

Chock

--

REMOVE.

--CHECK,

--

CHECK.

Tank

--CLOSED.

LEAN.

Fasteners

-

for

Forward Engine Components--@BIEGK starter,

alternator

Door--CHECK

and

secure.

Landing Light

--

@HECK.

Nose Gear

--CHECK tire; cheek for towing damage.

--

CHECK.

Chocks

--REMOVE.

8.

Right Side Engine Cowl Fasteners--SECURE.
Engine

--

CHECK (Full for edended

flight).

Fuel

Drain--

SAMPLE.

Tank Vent

- - UNOBSTRUCTED.

-

REMOVE.

Main Gear, Shock Discs and Tire--

CHECK.

Right

--CHECK.

4-3

15.

Fuel. Tank--CHECK QUANTITY.

A

reduced fuel indicator is located in the filler

neck.

This

indicator

is

used to indicate useable

capacity of

25

gallons.

-

CHECK.
Wing Tip Strobe (if
Light

-

CHECK,

Aileron and Attach Points

-

CHECK.

Flap and Attach Points

-

CHECK.

Remove all ice, snow, or frost.
Baggage Door

-

SECURE,

BEFORE

Preflight Inspection - COMPLETE,
Emergency Locator Transmitter

-

Seats, Seat Belts and Shoulder Harness

(if

-

ADJUST AND SECURE,

Fuel Selector Handle

-

SET for fuller tank,

DEPRESS BRAKE PEDALS

PULL

ON.

and

Master

Switches .-

OFF,

Radio Waster

Switch

OFF.

Cowl Flaps

OPEN (Control FULL

Aft),

Ram Air Control

CLOSED,

Landing Gear

Switch - DOWN.

Mixture Control

-

IDLE

CUTOFF,

Propeller

FORWARD HIGH
Throttle - CLOSE (Full Aft),
Electric Fuel Boost Pump

-

OFF,
All External Lights - OFF,
Cabin Heat

-

OFF.

-

CHECK.

Alternate Static Air Control

-

CHECK IN,

ENGINE

When

external power source

Adapter is available from Mooney Aircraft
Corporation) no special starting procedure
is necessary, Use normal starting procedures
be low,

REV

3-7-84

11-15-77

PO.

Propeller Control
Throttle Control

-

FORWARD l/4,
Master Switch - ON.
Mixture Control

-

Electric Fuel Boost

Pump

Switch - ON TO ESTABLISH
PRESSURE, THEN OFF.
Mixture Control

-

FULL

AFT

(IDLE CUT

-

OFF) .

Propeller Area - CLEAR.

-

TURN

AND

PUSH TO START,
RELEASE TO BOTH WHEN ENGINE STARTS.
Mixture

-

MOVE SLOWLY AND SMOOTHLY TO RICH.

Oil Pressure Gage

-

If minimum oil pressure not

indicated within

30

seconds, STOP ENGINE, and

determine trouble,

Cranking should

be

limited to

30

seconds,

and

several minutes allowed between crank-

ing periods to permit the starter to

Throttle

Set for LOO0 to 1200

CLEARING

OPEN

FORWARD),

--IDLE

(FULL

Electric Fuel Boost Pump--OFF1,

--turn to "START'hnd

PUSH forward.

Throttle

-

when engine starts.

-

(FULL FORWARD).

Oil Pressure
not indicated within

30

seconds, STOP ENGINE,

and determine trouble.

BEFORE

TAKEOFF

Parking Brake--

SET.

Controls

--

@HECK

FREE

CORRECT

MOVEMENT.

Radio Master

--

ON

Instruments and Radios

-

-

CHECK

AND

DESIRED.

REV

3-7-84

ISSUED

11-15-77

5.

Strobe Lights and Rotating Beacon--

OW

(if

installed).

Annunciator Lights

-

-

CHECK WITH PRESS-TO

-

TEST

THROTTLE RETARDED.

Trim

--

TAKEOFF SETTING.

If

forward

CG

set
trim to upper portion of band and to
when at aft

CG.

THROTTLE

--

Magnetos

-

-

CHECK. Make magneto check at

1900

-

2000 RPM, as follows:

a.

BOTH to

-

Allow time

for plugs to clear.

-

Note

-

BOTH.

The

drop

should not

WPM

on either magneto

or

indicate greater than a 50

differen

-

tial between magnetos.

An absence of

RPM drop

be

indication of faulty magneto ground

-

ing

If

there

is
doubt concerning Ignition system
operation,

speed will usually confirm

a deficiency exists.

Propeller Control

-

Throttle

IDLE RPM.

Cabin Boor

-

LOCK.

Seat Belts

-

SECURE.

TAKEOFF

ISSUED

TAKEOFF

Move the codrolls slowly and smooth$y. In
particular, avoid rapid opening

the

as

the engine

is

counterweighted

is

a

of

Roper full throttle ewine operatibn should
be checked early in the takeoff roll. Any

significant indication of rough or sluggish

engine response

is

reason ta discontinue the

takeoff.

When takeoff must

be

made over a gravel

is

important that the throttle

be

applied s%ow%y. This

the

to start

before

a

high

RPM

is

sped,

and

gravel

or

be

from tlae

instead

into

Boost

-

QN

at

start

of

takeoff roll,

Power

FUEL

and

-

WFT

NOSE

AT

MPH

(62

-

MPN

(71

5.

-

RETRACT

IN

CLIMB

BEFORE

ATTAINING AN AIRSPEED

OF

(104

Wing

-

RETRACT

IN

CLIMB.

7.

Boost Pump

-

CHECK

PRESSURE.

TAKEOFF

(Obstacle Clearance)

-

ON

at start

takeoff

2.

FULL

AND

Aircraft

Attitude

NOSE

WHEEL

AT

MPH

(62

)

Climb

Speed

-

76

(66

IAS

clear

obstacle, then accelerate

to

105

to

115

MPH

IAS.

5.

Gear

-

RETRACT

IN

AFTER

.

-

RETRACT

AFTER

CLEARING

OBSTACLE.

Boost

-

,

CLIMB

(Nor

-

PRESSURE.

3

-

LEAN

SMOOTH

OPERATION.

-

OPEN.

5.

Airspeed

-

Air

-

OPEN

AFTER

ENTERING

CLEAR

AIR.

CLIMB

(Best Rate)

Power - FULL THROTTLE

2.

Mixture - LEAN FOR SMOOTH OPERATION.

-

FUEL

OPEN.

4.

Airspeed

-

MPM

(88

at Sea

94

(82

KTS) IAS

at %0,000 Ft.

5.

Ram Air

-

ON

AFTER

Manifold pressure

drop with increasing altitude at

any

be

restored by gradually

opening the

To

Increase ~ex?ormance<ak ftuli throttle,

Air

Air

ON position) allowing inducll.on

to

bypass the

air

filter

and

Turn ram air off

if

encountering icing conditions.

Do

­filtered induction air when flying in snow or other
conditions can be hazardous.

Snow can

in

the fuel injector impact tubes, or moisture can freeze
in the inlet passages under icing conditions to cause

-

countered

DO

RAM

ON AGAIN when
entering clear air until assured that all ice has melted
from the aircraft. Do not use ram air in visibly dusty

air.

After establishing
for
instruments are set and functioning properly.

Upon reaching cruise altitude, allow acceleration to
cruise airspeed, then trim the aircraft for level flight,
reduce manifold pressure and

RPM

to desired cruise
power, and close the cowl flaps. The cowl flaps should be
partially opened (control pulled aft
inches)

if

necessary, to maintain the oil and cylinder

head temperatures within the normal operating range.

When cruising at

percent power or less, lean the

mixture

after

is

established in accor

-

dance with one of the following methods:

A.

Leaning using exhaust gas temperature gage (EGT)
(if installed)

the

indicator.

-

Enrich mixture (push

mixture

indicator

r

more below peak.

M

I

X

TUR

E

Best power mixture will result in a
speed increase, an increase

a

reduction in range.

2.

Changes in altitude and power settings require

the

peak

to be rechecked and the mixture

re

-

set.

Leaning without exhaust gas temperature gage

Slowly move mixture control lever aft from
"

Full Richqs position toward lean position.

Continue leaning until slight lass of power

is

noted (loss of power

may

or may not be accom

-

panied by roughness).

When increasing power always return midwe to full rich,
when decreasing

RPM.

Always stay

within

the established operating

DESCENT

LEAN

OPERATION.

Power

-

AS

Avoid

and

RPM

manifold preseaare,

Exercise caution with

power

settings

below

15

"

manifold pressure at air

MPB

to preclude continuous operation

be 1508-1950'RPM restricted range.

-

CLOSED

(control

forward),

Seats, Seat Belts and Shoulder Harnesses - ADJUST

AND SECURE,

-

EXTEND

BELOW

155

MPN

(135

)

3.

-

Fuel

-

RIGHT

LEFT (Fullest

tank),

-

Wing

-

FULL

BE

132

(115

KTS)

REVISION

4-11

7.

-

ADJUST,

as necessary,

8.

Electric Fuel Boost

-

Ram

Air

-

LIGHT

OFF.

Check

Gear

-

GEAR

-

MARKS

ALIGNED IN VISUAL ImIGATOR

GO

AROUND

(BALKED

Power

-

FULL

AND

2700

AIRSPEED

-

(65

IAS.

Flaps

ESTABLISHED RE

-

TRACT

TO 0 DEGREES WHILE

ACCELER

-

TO

84

MPM

Gear - RETRACT

AFTER

CLIMB

ESTABLISHED,

-

Airspeed

on,

Final

-

8%

IAS

FLAPS,

Touchdown

WHEELS

FIRST.

LOWER

NOSE

GENTLY.

Brakes

-

Wing

RETRACT

AFTER

-

OPEN

Pump

-

OFF

AFTER

Trim

-

Throttle--1000

to

Lighting

-

required.

Trim- -

TAKEOFF.

SHUTDOWN

1200

RPM

cy

-

head

temperature starts to

3.

Radio

Switch--

OFF.

--OFF.

5.

CUTOFF.

6

Throttle--RETAR%)

as

engine stops

when

8.

Parking Brake--

Set (for short-term parking).

seat

belt.

AIRCRAFT

Parking Brake

-

-

-

OFF.

4.

Control - IDLE CUTOFF,

5.

-

AND

WHEEL,

CHOCKS.

6.

For

Extended

in

Gusty Wind Conditions

-

SEAT

BELT,

TIE

DOWN AIRCRAFT

AT

WING AND

POINTS.

ISSUED

SECTION

.

PERFORMANCE

TABLE

INTRODUCTION

5-3

.................

.............

A

............

AIRSPEEDCALIBRATION 5-7

NORMAL

STATIC

SYSTEM . Flaps

Up

NORMAL

STATIC

SYSTEM

.

Down

.

.

.

Gear

Up

STATIC

SYSTEM

.

Down

.

.

5-11

S

Y

S

TEM

.................

5-13

TAKEOFF

DISTANCES

MAXIMUM PERFORMANCE

.

5

-

TAKEOFF DISTANCES

5-15

PERFORMANCE

5-18

........

5-17

....

CRUISE.

RANGE

ENDURANCE

5-19

................

BEST ECONOMY

5-20

.................

BEST POWER

5-28

LANDING DISTANCES

5-30

....

.

.

5-36

MAXIMUM PERFORMANCE

5-37

5- 1/5-22

BLANK

All

performance tables and graphs are grouped In this

section of the manual for quick and easy reference. The

information is presented to show performance that may

be expected from the aircraft, and to assist you in
planning your flights with reasonable detail, and accur

-

acy. All data has been compiled from both calculations

and actual test flights with the aircraft and
good operating condition while using average piloting
techniques. The cruise performance data makes no

allowance for variables present

allowances must be made for actual conditions.

carefully detailed and analyzed flight plan will yield

maximum efficiency. After making a flight plan based

on estimates taken from the data

this section, you

should check your actual performance and note the

difference between your forecast conditions

and

your future estimates

be

The

at

pounds maimurn weight

No determim-tion

has been made

by

the Federal Aviation Administratioaa

be

acceptable or uceeptable for operation at, into, or od

any airpod,

REVISION

=

x

Given:

168

60 70 80 90 100 110 120 i30 140 150 160 170 180 190 200

ISSUED

1

-

-

AND

GEAR

50

-

AIRSPEED

-

ALTERNATE

SOURCE

-

-

numbers from

IAS

to obtain

@AS

assuming zero

instrument error.

CONDITIONS:

Storm

Window and Vents:@Iosed

Defroster

Power On

11-15-77

ISSUED

STALL

ASSOCIATED

CONDITIONS:

Gross

2740

Forward

CG

Power

airspeeds in
and assume zero instrument

during

is

approximately

feet

Flaps

Flaps

EXAMPLE:

2740

Landing Gear Down
Flaps
Angle

of

Find:

Knots

65

11-15-77

5-43

ISSUED 11-15-

77

PERFORMANCE

RATE

OF

-

-

EXAMPLE

GIVEN:

FEET

FMD:

BEST

BEST RATE

OF

TIME,

AND DlSTANCE

TO

Associated Conditions for

the

Fuel

and

Distance to Climb graph

on

the following page:

Speed

Performance graph

page.

Power:

Rich

Ram

Air:

Cowl Flaps:

Gear:

Up

Wing Flaps: Up

Fuel Density

NOTE:

Distances

shown

2.

Add

fuel

Given:

Weight

-

Find:

to

(

3.

Q)

13.5

Minutes

Distance to Climb

(23.

5

-

4.5)

19.

Q

Mi.

to

(24.5

-

5.0)

19.5

ISSUED

11-15-77

TIME,

AND

TO

RANGE

Cruise and -we Data tables allow for:

-

off, climb at ma. power at

the best rate of climb speed

a

cruise to destination at the specified power and

-

minute fuel reserve

at

the same altitude and power setting. The data

is

gallons of usable fuel,

standard atmosphere, and no wind.

and Range Data tables on non

-

standard days, in

-

crease or decrease the manifold presstare approxi

-

mately

for each 1Io0C variation in outside,

air

temper attare. Increase manifold pressure for

air

temperatures above standard and decrease

manifold pressure for air temperatures

standard.

3.

During winter operations when snow and

are

be

present on

and runway s%~sfaces

inboard landing gear doors shota%d be removed.

of

snow

Banding

gear operation.

a

decrease in cruise speed and

be

expected and sRaould be considered in

preflight planning. To be consermtive the following

a.

Decrease true airspeed at normal cruise power

setting by approximately

5

Decreased range may be as much

as

50

nautical

64

AT

ECONOMY

AT

ECONOMY

2000

11-15-77

RANGE

AT

ECONOMY

4000

5-22

11-15-77

RANGE

ECONOMY

6000

5-23

CRUISE

RANGE

AT

ECONOMY

8000

RANGE

AT

RANGE

AT

ECONOMY

RANGE

AT

BEST

POWER

MIXTURE SETTING:

SEA

LEVEL,

Use

FULL

mixture above

75% power.

2.

Lean mixture in

accordance

Section

at

75% power and below.

5-28

ISSUED

11-15-77

RANGE

AT

MIXTURE

SETTING:

2000

1.

Use

RICH

mixture

above

ISSUED

11-15-77

RANGE

AT

BEST

POWER

Use

FULL RICH

above

5-33

ISSUED

RANGE

AT

BEST

POWER

SETTING:

Use

FULL

RICH

above

CRUISE

RANGE

AT

BEST

POWER

DISTANCES

THROTTLE CLOSED

GEAR

-----

-

--

WING

FLAPS

------

-

-

-

--

FULL

PAVED.

SURFACE

APPROACH SPEED AT

50

FT

75

NOTE:

Maximum demonstrated crosswlnci velocliy

i2

MPH

Knots)

SECTION

BALANCE

TABLE

OF CONTENTS

PACE

...............

AIRPLANE WEIGHING PROCEDURE

OWNERS

BALANCE

6-5

............

LOADING

6-6

6-6

.

6-7

MOMENT

ENVELOPE

.

..............

empty

weight,

of gravity,

list

for

the airplane

as

delivered

Aircraft

Corporation

is

contained

in

this

section.

The

of

section

is

for rase

with

the

airplane identified beiow whela approved by Woonej;

Model.

-

This section describes tkae procedure for calcuiatix

loaded aircraft weight and moment for various

flight operations. In addition, procedures are

provided for

­ment of the aircraft when the removal or addition of
equipment results in changes to the empty weight

and

center

gravity.

comprehensive list of all Mooney

equipment available for this airplane

is

included in

this section, Only those items checked

were in

-

stalled at Mooney and are included in the empty

FAA

charges you, the aircraft owner and pilot,

with the responsibility of properly loading your air

-

craft for safe flight* Data presented in this section
insure that your airplane

is

loaded to operate within

-of-

gravity Xirnitatioe~s.

At the time

of

Aircraft

of

gravity data

for

of

individual loadings. (The

empty

weight and

G.

as

delivered

factory

tabulated

ow

page

the aircraft

factory.

FAA

regulations

require

any

center of gravity

be

Aircraft Log Book,

A

convenient form for maintaining a permanent record

of

such changes

is

provided on page

This form,

if properly maintained,

the

for

weight-and-balance data

entered

as

your aircraft 'left the factory, plus the

record

6-5,

is

needed

to

The

under

operating conditions

is

2740

pounds, mximum useful load

is

determined by

sub

-

tracting the corrected aircraft empty weight from its