Mooney M20J 1978 Operating Manual

CONGRATULATIONS . . .

WELCOME TO MOBNEYvS NEW DIMENSION IN SPEED

AND ECONOm. YOUR DECISION TO SELECT A NEW

MOONEY

HAS PLACED YOU IN

AN

ELITE AND DISTINC

-

TIVE CLASS

OF

AIRCRAFT OWNERS.

WE HOPE

THAT

YOU FIND YOUR NEW MOONEY A UNIQUE FLYING EXPERIENCE, WHETHER

FOR BUSINESS OR PLEASmE,

THE MOST PROFITABLE

EVER.

This manml

is

provided as an operating guide for the

Mooney

201,

Model

M20J.

It is important that you

--

regardless of your previous experience--

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

A11 information and i%%ustrations in the manual are based

on the latest

product information avaibble at the time of

publication approval.

The

right

is

reserved to make

changes at any

time

without notice*

Every effort has been

n2ade to present the

material

in a clear

and conveniea2t

manner to enable you to

use

the

manual

as

a

ready

reference,

Yobar cooperation

in

reporting presentation

and content recommendations

is

solicited.

IZEVISPNG

THE

MAWUA

%

Page i of this manual

is

a "List

of Effective Pages

"

containing a complete etarent listing of aXB pages

ie

e. , Original or Revised. Also, in the lower

corner of the outlined portion,

is

a box which denotes

the issue or revision of the

manual.

It

will be advanced one letter, a%phabetica%%y, per revision, With each

revision to the manual a new List of Effective Pages

will

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

by

Mooney Aircraft

Corporation when the revision card in the front of this

handbook

has

been filled in and mailed to Mooney Aircraft

Corporation,

P.O.

Box

72,

Kerrville,

TX 78028.

A

ISSUED

11-15-77

TABLE

OF

CONTENTS

SECTION

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

GENEGAL

a

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

LIN.w~ITATIONS.

2

......

EMERGENCY PROCEDURES

3

........

NORMAL

PROCEDURES

4

PERFORMANCE

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

5

..........

WEIGHT & BALANCE

6

AIRPLANE

(k

SYSTEM

...........

DESCRIPTIONS

7

WANE>L1.NG9

SERVICE

.........

&

MAINTENANCE.

8

........

SUPPLEMENTAX, DATA

9

ISSUED

1%-15-77

fsr

.

4

v/v6

BLANK

SECTION

I.

TABLE

OF

CONTENTS

TITLE

PAGE

%RREEwE&SP.

. .

o

a

.

a

el-2

mTRODUCT%ON

a

*

* *

01-3

DESCmPTIVE

DATA

*

a

*

*I-3

LANDmGGEAR

*

-

*

* *

*

a

-1-3

~N~~~~~~~~~~~~~~~~~~

01-3

PROPELLER*

a

0

o

e

*

e

o e

o

.

el-4

~~~~~~~~~~~~~~~oo~~

*I-4

OIL.

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

.I-4

MAXMUM CERTIFICATED

WEIGHTS

-1-4

STANDARD

MRPLANE

WEIGHTS

*

0

1-5

BAGGAGESPACE&

ENTRY

DIMENSIONS,

..........

-1-5

SPECIFIC

LOADINGS

.

0

.

0

a .

1-5

SYMBOM,

ABBREVUTPONS & TERMI-

NOLaP

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

.I-5

GENERA18

AIRSPEED

TERmNOLmV

&

BYMBOW.

....a.e....

1-5

ME

TEOROLWICAL TERMINO

AmPUNE PERFORMANCE

&

FLIGHT

PUNNNG

TERmO

WEIGHT

&

BAUNCE

TERmO

ISSUED

11-15-77

FIGmE

1-1

THREE

mEW

ISSUED

f

1-15-77

This Rlot

's

Operating hndbsok contaim 9 dscections and includes the material rquired to be fwnished to

the

pilot

by

CAR

Part

3.

It also con%ea%m supplemental

data

supplid

by

Mooney Aircrdt Corporation,

Section I contains informtian of general interest to the pi%&, It aalo contains &finitions of the terminol~

used in this Pilot's 9eratiq andbook.

DESCRIPTIVE

DATA

LANDING

GEAR

TYPE

:

Electri

ca%Q

operated

tricycle

gear

with

ri~bber

shock

discs,

steerable

nose

wheel,

and

hydraealfc

disc

brakes.

Wheel

Base

5

We

11-9/16

in.

Wheel

Tread

9

ft.

3/4

tn,

Tire

Size:

Nose

(8

Ply)

6.00~

5

Main

(6

Ply)

6

80

x

6

Tire Pressure:

Nose

49

PSI

Main

30

PSI

Mino Tuning mdius

41

ft*

(No Brakes Applied)

ENGWE

TYPE

:

Four- cylinder, horizontally opposed,

air

cooled,

and fuel

-

injected engine with a wet-sump

lubricatiw

sys

-

tem.

Number

of

Engines

1

Mode%

(Lycomiw)

IO-860-A3B6D

Recommended

TBO

1BOO

Hrs-

mted

HP

@

29106

RPM

200

BNP

@

Sea

Level

Bore

5.3125 in.

Sroke

4.375 in.

Msphcement

361.0

Cu.

In-

Compression Ratio

8.7:1

Fuel Injector, Bend&

RSA-5-AD1

Magnetos, Bendix

MLN

2021

PROPELLER

TYPE

:

Constant- speed, hy&aulically controlled pro

-

peller with a siwle-acting governor.

Mdel (McCauley) ~2~34@214/90~~~-

16E

Diameter

974

in.

mm,

73

in, miw.

Number

of

Blades

2

Blade Angle

@

30

In.

Sa.

:

Low

13.9~

-

+

,2"

Nigh

33"

-

-I-

.5"

'Total

Ftas%,

Capaci,ty

66-5

11.8.

Gal.

Usable

Fuel

Capacity

64

U.9.

Gal.

Minimum

Fuel

Octane

Rali2x

&

Color

Grade

P

1.08

100

LL

Blue

oil

Capacity

(6

QTS

MIN for

flght)

8

WS.

Oil grades, speciffeatioaas and changing recornmen&- tloaas

are

contained in Seetion

WE.

MAXMUM

CERTIFICATED

WEIGHTS

Maimurn Loading (mlsss limited by loading envelope):

Gr

sss

Weight

2'740

LBS.

Baggage

Area 120

LBS.

Hat

Rack

10

LBS.

ISSUED 11-15-77

STANDARD AIRPLANE WEIGIlTS

Basic Empty Weight

(See page

6-4)

Standard Useful Load

1100

LBS.

BAGGAGE SPACE' AND ENTRY DIMENSIONS

Baggage Area

24"x

35"x

35"M

(199

cu. ft.

)

Hal Rack

30"Wx

19"D

x

12H

(Max.)

(2.6

CU.

fe.)

Baggage Door Opening

Above Ground

(Sill)

46

"

Entry Width

1'9"

Elltry Height

20.5

"

SPECIFIC LOADINGS

Wing Loading @ G.

W.

16.4

PSP

Power Loading

@

C.

W.

13.

'7

PHP

SYMBOLS,

ABBREVIATIONS & TERMBNOLOGV

GENERAL

AIRSPEED

TERMINOLOGY

&

SYIMBOLS

CAS

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

for position and instru

-

ment error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea

Bevel.

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.

TAS

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

REVISION

A

'-

J

Maneuvering

--

Speed is the maximuin speed at

which application of full available

aer odynamic

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

b,andiiag Gear Extended Speed

is

the

maximum speed at which an aircraft can be

safely flown with the landing gear extended.

Maximum Landing

Gear Operating Speed

is

the

maximum speed at which the landing gea.r can

be safely extended or retracted. Never Exceed Speed or Mach Number is the

speed

linait that may not be exceeded at any

time.

Maximum

Striactriral Cruising Speed is the speed

Chat should not be exceeded except

in

smootla

air

and thela only wit

la

caution.

Stalling Speed or the 1aainirnu.m steady flight

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

landing configuration

Best Angle

-of-

Climb Speed

-.

is the airspeed

which delivers the greatest

gain of altitude

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

up.

ISSIJED

11-15-77

OAT

is

the

free

air static temperature, obtained either from

inflight temperature indications or ground

meteorological sources. It

is

expressed

in degrees Celcius krefiously Centigrade).

(2)

The

temperatwe atvsea levels

kQ

Celeius;

(3)

The pressure

at

sea level

is

29.92

inches

Hg;

(4)

The

temperature

gradient

from

sea

level

to the aanfteads at

which the temperature

is

-56.5oC

is

-0.00198~~

per foot.

Indicated The number

actually

read from

an

alti

-

Pressure

meter when

and

only

when,

the

barometric

ARLMuds

subscale

has

been

set

to

29.92

inches of

mer cusy.

Reasears

Pressure altitude

is

the

tx~dicated pressure

Altitude

altitude corrected

Pos

position

and

fnstru-

mealt

error,

In this handboolc, altimeter

instrument

errors are

assumed

to

be

zero.

Density Altitude

as

determined

by

pressme altitude

Altitude and existing ambient temperature.

In

stan&rd atmospiaere

(ISA)

density and

pressure altitude are

equal, For a given

pressure altitude,

the higher

the

tempera

-

ture, the

higher

the

density altitude.

&atio%%

Actual

atmospheric

presswe at

field

Pressure elevation.

ENGINE

POWER

TERMINOLaY

BHP

Brake Horsepower

is

the power developed

by the engine.

RPM

Revollutions Per Minute

is

@wine speed.

MP

Manifold Reaeure

is a presswe measured

&%on

syatem

awd

ts

ax

-

Demon

-

is

the

etratd velocftv d the crosswind component

for

Croeswiond which idqmte control

of

the itrplane

VelmiQ

dw%w

takeoff and landing wae actmlly

dem-

onadrated

desriw

certification tests.

The

mllue

shown

is

n&

considered

to

be lirnitim,

E!

g

is

the acceleration

due

to

gravity.

&tpdee

is

the

altitude where

the

Ceiligg

airera8

has

the capability

of

climbing

at

the

rats

d

100

lt/min.

WEHCBT

AWD

BALANCE

TERMINQImU

p7-.--p----p."p

Reference

An

imaginary vertical plans from

which

htum

all horizontal distances

are

measured

lor

balance

purposes,

Wation

A

location along the airplane fuselage

usw%%y given in terms of distance from

the reference

datum*

Ar

rn

The horizontal distance from the reference datum to the center of gravity

(C.

G.

)

of

an

item.

Moment

The prduct of

the

weight of an item

mu%-

tiplied by its

arm.

(Moment divided

by

a

constant

is

used

to simp%i$gv balance cal

-

culations

by

rdiacing the number

of

digits.

)

C . G.

Arm

The

arm obtained

by

addiw the airplane's

individual moments

and

di~ding

the

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

(C

.

G.

)

datum is found by dividing the total moment

by

the total weight of the airplane.

Usable

Fuel

Fuel available for airplane pro;ulsion.

Unusable

Fuel remaining after a runout test has been

Fuel

completed in accordance with governmental regulations.

Maximurn

The maximum weight is the maximum authorized

Weight weight

of

the aircraft and its contents as listed

in the aircraft

specificatio~as.

Basic

The

basic empty weigh"c. of

an

aircraft

is

the actual

Empty.

weightof the airplane

and

includes all operating

Weight

egurnpmclat (imcliading optional equipment) tkt

has a fixed location and

is

actually installed

in

the airc-sa.ft. It includes the weight

0%:

the

unusable fuel and full. oil,

Useful

'Fhe useful load

is

the empty weight subtracted

Load from the maximum weight of the aircraft. This

load consists of the pilot, crew if applicable,

fuel, passengers, and baggage,

Tare

Tare is the weight

of chocks, b%oclns, stands,

etc. used when weighing an airplane, and is included

in

the scale readings.

Tare is de

ducted from the scale reading to obtain the

actual (net) airplane weight.

1-9 (1-

10

Blank)

SECTION

II

.

TABLE

OF

CONTEWS

TITLE

PAGE

INTRODUCTION

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

2-2

AIRSPEED

WmATIIONS

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

2-3

AGRSPE

ED

INDICATOR

MARKmGS

.........

2-4

.

POWER

PUNT

LIMITATIONS

...........

2-5

POWER

PLANT

INSTRUMENT

MARmNGS

....

2-6

WEIGHT

UM%TS

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

2-7

CENTER

OF

GRAmTU

UMITS

...........

2-7

MANEUVER

WMES

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

278

FUGHT

LOAD

FACTOR

WMTS

.........

2-9

MIND$

OF

O

PERATI

O

N

LIMT~S

...........

2-9

FUEELIMmATTONS

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

2-9

OTHER

INSTRUMENTS

AND

MARKING8

.

0

2-9

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

DECAL,

9&

PMCARDS

2-10

INTERIOR

...

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

2-10

EXFERIQR*

=

..........

2-13

FAA

APPROVED

ISSUED 11-15-77

Section 2 includes operating limitations, instrument

markings, and basic placards necessary

for the safe

operation of the airplane, its engine, standard sy sterns

and standard equipment. The

%imitations 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

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

&ata shown in Section 5 with the normal

static source.

Kf

the alternate static source is

being

used, ample margins sllould be observed

to

allow

for

the

airspeed calibration variations be

-

tween the ~aormal and

alternate

static sources

a.s

shown

in

Section

5.

Your

Moaney

is

certificated under

FAA

Type

Certificate

No,

2A3

as Mooney M20J0

Mooney

M20J

Airplane Flight Manual

FAA

APPROVED

ISSUED

11-15-77

AIRSPEED

LlMITATION3

Airspeed limitations and their operatiom% significance are shown in Figure

2-1.

This calibration assumes

zero

instrument error.

Do not exceed this speed

Do not make

full

or

Do

not

exceed

these

FIGURE

2

-

1.

AIRSPEED

L%M%TATIONS

Mooney

M2OJ

Airplane

Flight

Manual

2-3

AIRSPEED

lNDlCATOR

MARKINGS

Airspeed indicat or mar kings, their color code and operational

significance are shown in Figwe

2-2,

white

Arc

Green

Arc

Full

Flap werating Raxe. Lower

Yellow

Arc

1

200

-

$25

1

@eratfons

nlust

be

conducted

with

caution

and only-

in

smooth

air,

-*--

..

wvm-m-

L--...,.i

------.

'

_..---*

-

FIGURE

2-2.

ARSPEED

ImIGATOR MARKINGS

Mooaaey

M20J

Airplane

F%igh%

Manawal

2-4

FAA

APPROVED

ISSWD

11-15-77

POWER

PLANT

LiMlTATlONS

Engine Manufacturer: Avco Lycoming. Engine

Model Number: 10-360-A3B6D

Engine Operating Limits for Takeoff and Continuous Operations

:

Maxinlum Power: 200 BHP

Maximum Engine Speed: 2700

RPM.

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

Oil

Temperature: (24~~~).

Transient Engine RPM Limit - 2970 RPM for

3

Seconds or Less

Oil

Pressure, Minimum:

25

psi.

Maximum:

100 psi

Fuel

Pressure, Minimum:

14

psi

Maximutn:30 psi

Propeller 1Vlariufacturer: McCataley Accessory Division.

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

Prn~elEer Diameter, Minimeam:

93

inches,

Maximum:

74

inches,

Propeller Operating Limits: Avoid contineeous operation

between 1500 and

71950

RPM

with

power

settings

below

15"

HG

manifold presswe.

Propeller Blade

Angle

3.t

38

Inch Station,

IJ~W

13.

go-+,

2"

High

33.

--

50

POWER

PLANnlNSTRUMENT

MARKINGS

Tachometer

Radial Red Line (Rated) Green

Ar

c

--

(Rated

operating range) Yellow Arc (Caution Range)

Cylinder Head Temperature

Radial Red Line

(Maximum)

Green

Arc

(Operating range)

Oil

Pressure

Radial Red Line

(Minimum

idling)

Radial

Wed Line

(Maximum)

Green

Arc

(Operating range)

Yellow

Arc (Idling range)

Yellow

Arc

(Starting

&

warm-up range)

Fuel

Pressure

Radia.1

Red Line

(Minimum)

Radial

Red

Llrae

(Maxianurn)

Green

Arc

(Operating range)

811

'Remperature

Radial

Red

Line (Maximum)

Green

Are

(Operating range)

Mooney M205

Airplane

Flight

Manml

2-6

2700

RPM

1950-2700 RPM 1500-1950 RPM

25

PSI

aoo

PSI

60

to 90

PSI

25

to

60

PSI

14

PSI

30

PSI

14

to

30

PSI

FAA

APPROVED

assmD

11-15-77

REV

C

9-29-82

Maximum Weight (Takeoff

RL

Landing)

....

2740 LBS.

Ma%irnurn Weight

in

Baggage

Compartment

......

120 Lbs. @ Fus. §&a. 95.5

Maximum

Weight

in

Haln.aclc .

.

10 Lbs. @ Fus. Sta. 119.

0

CENTER

OF

GRAVITY

LlMlTS

(GEAR

DOWN)

Most Forward 41.0

IN.

(Fus. %a.

in

IN.

)

13.4';

MAC

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

2250 LBS. Intermediate Forward 41. 8 IN. (Fus, Wa.

in

IN.

)

14,7?

MAC.

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

2470

EBS.

Forward Gross 45.0

%Ed.

(Fus.

Wa.

in IN

.)

20.15

MAC

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

2'540

LBS.

Rear Gross 50.1 IN. (Fus.

Ra.

in IN.)

28.97

MAC

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

2740 LBS.

MAC

(IN.

at

Wing

Wa.

93-83)

.......

59.18

Datum

(station zero)

is

5

inches

aft

of the center

line

of the nose

gear

attaching

bolts,

and

33 inches

forward

of

the

wing

'leading

edge

at

wing

station

59.

25.

FAA

APPROVED

ISSUED 11

-15-

77

Mooney

M209

Airplane

Flight

Manual.

MANEUVER LIMITS

This airplane must be operated as a Norma% Category airplane.

Aer

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

takeoff maneuvers may cause loss

of power if the selected fuel

tank

con

-

tains less than

48

Ibs.

(8

gallons) of

fuel.

Up

&a

290-foot

altitude

loss

may

occur

during

stalls

at

maximum

weight.

Slow throttle movement required at airspeeds

above 190

MPH

IAS

(I64

K'TS).

Above 190

MPH

%AS

(164

KTS),

rapid throttle seduction may re

-

sult

in

momentary propeller

RPM

overspeed.

Mooney

M20J

Airplane

Flight

Wlantaal

FAA

APPROVED

REVISION

A

PLlGHT

LOAD

FACTOR

LIMIT3

mimum Positive Load Factor,

Fbpsupa..

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

*3.8g

mimum Positive Load Factor,

Flaps

mwn

(33OI0

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

.2.%

Mmimum Negative Load Factorsk,

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

Flaps

Up

1.5g

KlNDS

OF

OPERATION

LIMITS

Do not

operate

in hown ici~ conditions,

This

is

a

Normal citegory aircrdt approved for

VFR/IFR/~~~

or night operations,

when

quipped

in

accordance with

FAR

91,

FUEL

LIMITATIONS

2

Wanbrd

Tanks:

93.25

U.

S,

Gal%o~~s Eacia

Total Fuel:

66-5

U.

8.

Galloss

Usable

Fuel

:

84

U.

S*

Gallons

Usamable

Fuel

:

2*

5

U.

S.

Gallons

A

reduced fuel qmntity indicator

is

installed

in

each

lank,

These

indicators show

the

25

U.

S.

gallon

usable

fuel

%eve%

in each tank

Fuel Grade (and Color): 100 minimum grade aviation

fuel

(green)%).

106LL

(low lead) aviation fuel (blue) with

a lead

eontent limited to 2 ec per gallon

is

also

approved,

OTHER

INSTRUMENTS

AND

MARKlNGS

The

liollowing equipment

is

mcuum

operated:

1,

Artificial horizon

2.

Directional gyro

FAA

APPROVED

PS$WD

11-15-97

Mooney

M20J

Airplane

FligM

Ed%anml

DECALS

PLACARDS

INTERIOR:

The

following

placards

must

be

installed

inside

the

cabin

at

the

locations

specified.

OPERATIONAL

LlMl"$T!$sONS

T

H

I

S

AIRPLANE

MUST

BE

O

PER

A

TED

A

S

n

saloaMae

Mooney M20J 1978 Operating Manual

Specifications and Main Features

Frequently Asked Questions

User Manual