Mooney Mustang M22 1967 Maintance Manual

MOOhfEY

M22

MUSTANG

SECTION SECTION SECTION

SECTION SECTION

SECTION

SECTION SECTION

APPENDIX

PRELIMINARY

I.

II.

III.

TV. V.

VI.

VII.

vm.

IX.

SERVICE

TABLE

GENERAL

GROUND

POWER

FUEL

LANDING

FLIGHT

INSTRUMENTS

OF

INFORMATION

HANDLING,

PLANT

SYSTEM

GEAR

CONTROLS

ENVIRONMENTAL

EZ~ECTRICAL

SERVICE

LUBRICATION

MAINTENANCE

CONTENTS

SERVICING,

CONTROLS

SYSTEM

MAMJAL~

GUIDE

AND

INSPECTION

,´•r

ISSUED

REVISED

JANUARY

31-6

05-

08-03-67(

11-15-87’

03-11,-68

04-22-68

1967

MOONEY

Box

12

Kerrville,

I

..I

AIRCRAFT,

Texas

INC

18028

LIST

OF

REVISED

PAGES

ISSUED

~fSER’r

LATEST

Title

Table

REVISED

PAGE

Page

of

Contents

PAGES

Section

DESTROY

I

1-2 1-4

1-5

1-8

Table

2-2

of

Cor,tents

Section

II

2-3

2-10

2-13

2-16

rs,

2-

19 2

3-

3-4

3-

13 14

3-

3-17 3-20´•; 3-35

1

5-

6-4

6-12 6-12A

Table

7-1 7-6 8-1

thru

of

2;18

2-

32

7A

5-

Contents

7-4

7-

15

Section

VII

8-2 8-5

8-8 8-9

Table

9-3

9-4

9-8

9-

10

of

thru

Contents

54

9-

Section

M

SUPERSEDED

.´•´•i:.;

PAGES.

LATEST

r´•

.t_:

DATE

OF

REVISION

04-

22-

04-22-68" 04-22-68*

11-

15-67

11-15-67

04-22-68" 11-

15-

04-22-68"

11-15-61

11-15-67

04-22-68" 04-22-68"

03-

081

’10~-’9-2-68"

l~´•.i-

11-’15-67--

’olii~2-

i)

E~8

11-15-67

04-22-68"

22-

04-

22-

04- 11-15-67

11-15-67 11-15-67 11-15-61

11-15-67 11-15-67

~1-

15-67

:ll-d5-S7

68"

67

7

6

7´•´•

6

s*

68"

6%´•~

´•e

;rt

83

3URCHASED

*THE

LETED

kSTE~ISK

BY

COP~S

TIiE

FRO1Vi

~IzATEs

0~3*

CI~RENT

YO’iiFC

R~VISION.

LOCAL

PXGES

REVISIONS

MOONEY

i.’´•

TKIS

OF

DISTRIBUTOR

’O~DE-.

PUBLICATION

OR

MAY

DEALER.

SECTION

GENERAL

INFORMATION

I

SECTION

GENEEEALINFQRMATION

I,

,´•u:

,t

.´•i

PAIZA

1-1,

1-2´•

1-5,

1-6,

1-7.

1-8,

1-9,

1-10,

1-11.

1-12,

1-14,

1-15,

1-16,

´•r

.1-171

1-General

Description

General

Engine,,,,,,,,,

Propeller

Airframa

Engine

Landine;

Nose

Brake

Flight

Positive

Electric

Fuel

Instruments....

Cabin

Systems....,

Emergency

TABZtE

Information

Specifications,

Coivling

Gear

System

Steering

System

Control

Power

System

System.,.,..,.~

Pressurization,

Exit

OF

System

Entrance

or

CONTENTS

Heating

,,.,~.,.1-1

,,,,,,,1-2

........~-8

Ventilating

i.

(I

.-t

I~i’

:PBGE

1-2

1-5

1-6

i~-6

~-6

,’1-?

~1-c7

1-9

REVISEI)

04-22-68

1-I.

-GENERAL

INFORhlATION.

1-2,

MT3STANG

DESCRIPTION.

high

Full

environmental

cabin

~ines

’struction

wing.

multi-rib

spars ional

which

ders,

brakes gear

ted.

The

trically

pressurization.

all-metal,

with

Control

construction

and

ribs.

with

duzl-cont~ol

lin~ed

are

supplying

each

on

is

fully

Air-oil

wide-span

actuated,

´•by

taching

points,

turbo-charged,

ing

engine

stant-speed

is

a

lo~y-wing,

a

surfaces

main

retractable

shock

trailing-edge

entire

Euelinjected,

driving

propeller.

The

four-to-five

single-en~ine

control

The

semi-monocoque

full

cantilever,

feature

with

Flight

to

pressure

Stablizer

´•Power

an

controls

wheels

individual

gear,

struts

empennage

is

80-inch,

to

and

support

provided

~ooney,

monoplane

is

achieved

aircraft

lamin‘ar

extruded

skins.

are

and

hydraulic

the

hydraulic

The

tricycle

electrically

wing

trim

around

air-cooled

all-metal,

M22,

place

through

design

airframe

flow

riveted

rudder

to

convent-

cylin-

landing

opera-

each

flaps

is

wheel..

are

accomplished’

its

a:310

by

Lycom-

com-

con-

spar,

the

pedals

disc

elec-

at-

BP,:

con-

1-3,

1-4.

1.

cylinder,

.bo

charged,

oil

jet

2.

3.

4.

5.

6.

GEjhTEItAL

ENGINE.

Type,,,,,...,,,.,

horizontc~lly

wet

piston

Model,..,.,

F,4A

Rated

Bore

Stroke

cooling.

Type

HP

~I.

Displacement

SPECIFICATIONS.

opposed,

sump,

Certificate.

and

air-cooled

RPM

(CU

.~coming

at

IN.

..Direct

fuel

,.,.....E10

000

15,

´•i:.

drive

injected,tur-

FT;

internal

310

at2575

with

TIO-541-AIA

i

:5,

six

EA

125

4.375-

541.

i

5

8.

Compression

Ratio

7,

3:1

I-1

9.

(LBS)

Standard

Dry

Weight,

wit’h

accessories

......570~

1-5

1-6,

PROPE

1.

Type..............

2.

Model

Diameter

3´•

4.

Low

5.

HighBladeAngle

Governor.

6.

7.

AIRFRAME

I.

st.

Clearance

Tip

Dimensions

Wing

LLER.

Blade

span

.Hartzell,’

~T.).,.........

Angle

to

(FT)

KC-CBPK-

~EG)

Ground

Constant

Single

(IN.

Speed

1B/8415-

c...80.

O-FOO

30’’20

acting

13.75

35.

4

0

b.

;c.

d,

2.

a.

b.

c.

d.

e.

f.

g.

Fuselage

Tail

Stabilizer

Areas:

´•Wing.

Ailerons

Flaps

Vertical

Rudder

Horizontal

Elevators

height

(SQ

length

(FT)...........21.

(FT)..........:.,..

(SQ

FT)

(SQ

(FT).

FT)...........

18.

FT)8´•

span

(SQ

fin

FT)

Stabilizer

FT)

(SQ

0

tVane

2

(SQ

r

Dorsal

FT)

0

9.0.

11.

7

93

166.

5

11.

25

4.

25

Ili´•

Y~CO

6.9

5

21.

0

12.

3.

a.

REVISED

Wsights

Weight

04-.22-68

and

empty

t~oadings:

(I;BS)

2425,

I~L

c

b,

Gross

Weight

(LBS)

,,,,,,,,,,3080,

STA

;i

Useful

c,

d,

Wing

Power

e,

4.

Wings:

Airfoil

a.

Airfoil

b,

Mean

c,

93,

83i,,

icO

d..

Center-of-Gravity

Geometric

e.

Load

Loading

(LBS),,,,.,,,,,,.

(LBS/SQ

(LBE/HP).......

atWin~Root

atWing

Aerodynamic

Tip

I~wist

.....NACA

Modified

Chord

Range.....

~EG)..

FT)

10,

,,,,,,22,

NACA

(IN,

2~

63~-215

at

wing

Llf´•

-to

31~0

,1255,

.11.87

641-

,59,18

1030’

t

05

MAC

Incidence

f.

DihedralAngle

g;

h,

Aspect

i.

Taper

5,

Fuselage:

Cabin

a,

(1)

(2)

(3)

(4)

(5)

Ratio

Dimensions

Keight

Width

Length

Cabin

An~;´•le

Ratio

(IN.

Door

(DEPJ)~’$

(DEG)........,.50

..,.....,........1.

Width

Keight

(IN,

(~N.

29

i""’

i"

17,

35,

30(

30’

338

935

89.

42,

118

34;

Q;

b,

.......5.

(1)

Maximum

Pass.

4

-Paas.

Compartment:

Loading-r;E~‘

´•,Co~figuration...

-Configura-tidn

i´•...

1’00,

270,

1-3

(2)

Baggage

Space

(CU

FT),,,,,,,,25,

c,

(3)

(bL)

(5)

Eandin~

(1)

(2)

(3)

(4)

0) (6)

Baggage

I:at

Racl~

Gear:

Type........

Operation

Wheel

Tire

Size-nose

Size-main

Pressure-nose

~oor

Door

Track

Base

VJicith

Heiirht

Capacity

.Tricycle

(FT),,,.,,,,,,,.

(FT)......,.,,,,8,

(6

(6-ply

(~N.

(I]i~.

(LFS)

ply

rating),,6,

(PSI).......45

Retractable

Electrical

21,

10,

II,

OOxB

00x6

4

25

Tire

(8)

Strut

(9)

Strut

(10)

the

center.

Fuel

FL:el

Strut

axle

(II)

(12)

´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•´•26´•40L1/8

6,

a.

Pressure-main

Pressur~-nose

Pressure-main

Extension,

Strut

(St’atic

and

Oil:

Capacity

extension

center

with

(r;sable

(PSI)

:ERtended

Extended

,,,,,,42

(PSI~

(PW)..

´•´•´•´•´•´•´•´•´•´•´•´•135.

measured

attaching

fuel.

U.S.

Static

43

Static

gallons).,

"1/8

from

Nose,

,,,,,25,

Main,

is

to

the

full

80´•

bar

92

b,

grade)

c,

d.

REVISED

r~el

Oil

Capacity

Minimum

11-15-67

Octane

(G~T)..............

Safe

Oil

Quantiijr

t~vel

aviation

(QT).,

.5~4.

4,

-1-4

I-?.

has

ENGINE

two

panel,

cam-locks

-ing

upward

maintenance.

tain-two

control

rods.

pull

fore

plete flaps

top

ring

skin,

cess

the

cowling

the

are

just

cowling

to

ring

through

baffles

Cooling

the

sf

the

lower

able

cowl

required

varying

full-open

cylinder

at

all

times.

engine

ly.

COWLJNG.

side

cowl

side

The

at.the

to

cowl

torque-arms

These

side

and

engine

installed

forward

can

the

top

cowl

cylinder

insure

air

also

engine

cowl

flaps

cylinder

fight

for

doors

cowl

doors

front,

provide

The

flaps

cowl

lower

cowling.

be

of

opening

cooling

access

side

connected

by

rods

doors

in.the of

the

removed

the

engine.

and

adequate

enters

compartrrieni,

flap

openings.

dllow

conditions.

ground

the

head

operations,

fiinged

bottom,

cowl

quick-disconnect,

must

can

nose

Two

lower

firewall.

is

fins.

cooling

the

pilot

temperatures

Open

head’temperatures´•closely~

must

shutdown

Cowl

flaps

to

dissipate

The

engine

to

fastened

are

and

to

the´•engine-for

doors

the

to

be

disconnected

be

raised.

section

additional

nose

in

one

Ram

forced

Tightly

for

accessory

and

is

’I’he

to

maintain

cowl

and

be

residu~il

cowling

the

top

rear,

each

cowl

skin

section

The

piece

air

enters

downward

sealed

the

engine.

section

exhausted

six

adjust-..

under

flaps

monitor

full-open

heat

cowl

with

open-

con-

flap

push-

be-

A

n~se-

com-

cowl

complete

for

ac-

through

the

at

even-

1-8.

cally

steerable

LAND7NG

operated

air-oilstruts,

nose

gear

nacelle,

into

the

wing.

spring-loaded

landing

down

traction

Safety

break

gear

by

switches,

the

cidental-gear

The

landing

position

retraction

cronized

extension:

REVISED

nose

retracts

while

control

bungee

mechanism

gear

retraction

gear

wheel

by

linkage.

r$close’the

to

Gear

11;-15-61

GEAR

tricycle

wheel,

and

hydraulic

aft

the

main

The

mechanical

springs

in

acGtauted

actuator

is

well

Nose

position

SYSTER~.

landing

a

shimmy

into

gear

lever.

which

an

circuit

on

doors,

nose

indicator

disc

the

retracts

gear

locks

The

overcenter

strut

by

the

enclosed

gear

~heel

.The

gear

dampener,

brakes.

lower

held

is

linked

gear

preload

compression,

to

prevent

ground.

in

actuated

door~

doors

lighas

electri-

has

engine

inboard

up

to

is

the

position.

the

by

are

a

the

held

up

gear

syn-

upon

re-

ac~

The

by

pro-

I-E

vided

warning

has

mit

15

on

3N.

manual

st

manual

horn

HOvith

electrical

dlectrically

not

Do

retract

the

instrument

sounds

override

lowering

malfunction,

while

the

landing

the

ge’ar

panel.

when

on

the

of

Do

manual

manually.

the

gear

not

A

throttle

up.

gear

in

operate

override

gear-throttle

is

reduced

The

systenl

actuator

the

event

the

is

engag~ed.

to

of

gear:

to

per-

an

1-9,

steerable

by

engaged

~pedals

cam

wheel

to

nose

limits.

1-10.

are are

rudder

pedals

provide

Shuttle

NOSE

a

push-pull.

centers

well.

right

gear

stalled

installed

individually

upon

for

and

A

BRAKE

pedals.

are

hydraulic

valves

automatically

brake

pedals

control,

panel,

tains

craft

´•-the

lated

The

operates

pressure

is

parked.

brakes.

slush

parking

parking;

and

overnight

servoir

of

the

is

firewall.

GEAR

nose

rudder

left

can

hydraulic

standard

as

linked

located

and

brake

use

located

linked

gear

tube

gear

the

The

is

which

retraction,

control

nose

of

center.

is

only

wheel

..-´•rIwhentowingthe

be

da!naged

if

shimmy

equipment.

SYSTEM.

on´•each

controlled

Both

switch

when

are

on

a

on

~Lse

water

wheel

parking.

to

hydraulic

pressure

either

depressed.

the

parking

the

Do

not

overheated,

is

chocks

in

the

Hydraulic

main

by

the

pilot

brake

the

pilot’s

brake

set

could

designed

for

The

nose

landing

SYSTEM.

to

the

rudder

automatically

freeing

during

upon

Observe

will

entry

easter

turn

aircrajPc,

turned

dampener‘l:s

toe

and

cylinders

to

operate

hydraulic

pilot

The

lower

discs

parking

freeze

for

mooring

hydraulic-fluid

wheel

beyond

gear.

pressure

co-pilot

or

parking

valve

while

when

or

the

short-duration

The

the

flight.

into

18

limits

in-

brakes

dise

which

the

pressure

co-pilot

instrument

which

the

brakes

brakes.

well

forward

pedals

dis-

rudder

The

the

degrees

asthe

its

Brakes

on

rudder

brakes.

brake

m~ain-

air-

when

accur~u-

re-

the

control

pilot

arril

control

flight

the

conventional

tubes

to

FLIG~‘IT

or

bell

CONTR~r)L

system

co-pilot

in

operation,

cranks

wheels

can

seat.

and

SYSTEM.

be.operated

All

utilizing

to

link

rudder

flight

the

from

controls

push-pull

control

pedals~

The

dual

either

are

surfaces

1-f;

rudder

i

inter’connectbtrngee

linked

are

mechanism

controlled

’~laps

panel,

are

m’nich

A~ongitudinal

-’~perated

rotating

wheel

POS~TnTE

Positive

two-~uris,

senses

the

meters

units.

and

control

element.

all

little

or

is

Control

P.Ci’system.

system

trim

differential

1-12.

Mooney

equipment.

erated,’

that

from

is

superimposed

consists

and

which

servo

rudder

and

Positive

landing

pilot’s

pneumatic

sense

lieves

inoperative.

with

craft

an

by

assist

to

operates

trim

the

set

to

appenna~rre

pneum~tically

androtary~valve

bei~veen

CONTROL

Control

The

system

both

roll

engine-driven

on

of

a

gyro

vacuum

The

bell

cra~s

operates

is

wheel.

relay,

which

Depressing

servo

effort

vacuum

The

~nd

P,ilerg~n

control

in

smitch

a

by

areversible

is

manually

stduilier

principal.

operated

rudder

system

is

automatic-control

and

y~ur.

vacuum

manual

the

sense

pressure

to

The

are

provide

from

servos

supplies

and

system

can

with

and

spring

coordination,

the

on

angle

The

instl-ument

electric

attach

of

directional

means

by

controling

trim

SYSTEM,

a

pneumatically-op-

element

a

button

the

renders

no

servo~.

standa-rd

is

Power

pump.

flight

to

cylinder-pis’ton

lirLited

dual

a

t~eoff

cutoff

operates

vacuum

cutoff

be

overpowerec~

damage

mechanism

is The

control

(rate

to

button

button.

the

to

systems

motor.

vacuum

der:ived

sSlstena

g3rro~

the

ai:l~ron

system.

throu6,rh

orr

a

the

to

sys’tcm

the

The

the

by

of

system

the.

~ro

re-

alr-

trim

a

1-13.

power

hour

storage

partment,

voltage

warning

panel

1-1~.

turns

sealed,

inboard

the

rear

vent

These

to

pump

downward

prevent

in

ELECTRXC

is

supplied

iLLLt=lllaLVJ.

The

re~ulator,

light.

power

FUEL

integral

section

out5oard

vents

freezing,

each

battery

system

A

Sk’STENI.

W:nba

of

through

designed

are

tanl;

POWER

a

by

d~lLI

located

z?

overvoltage

battery

and

on

tar;ks

each

corner

A

provides

SUPPLY.

12-volt,

o

/C)Tlnl´•C

IL1’

L~

in

a

switch off.

The

trarLsistorized

fuel

haS

located

wing.

of

lower

the

a

as

submerged

positive

?O-AMP,

YV

the

engine

relay,

on

system

Tznir

each

wing

Electric

35

ampere-

the

overhead.

the

in

vents

tanir,

electric

fue~flow

self-

com-

and,c;t

has

for´•´•c~rard,

in

arc~

an.d

surfa;:e.

boost

and

1-’

takeoff

of

Tank

fuel

the

tank;

lowest

on

fuel

the

selector

fuel

right

drains

ends

pumplic,

engine

boost

An

the

point

of

gages

The

the

emergency

right

rear

pump

electric

section

supplements

i

".landing.

the

.:i

bottom

compartment.

actuation

is

and

the

bjr

driven

the

engine

stalled

selector

fuel

system.

cated

tank,

fuel

console.

is

energized

emergency

fuel

pump

crankcase.

at

lowest

valve

the

at

and

are

controlled

by

point

drain

Fuel

inboard

wired

a

fuel

is

mounted

quantity

and

to

is

by

switch

pump

Fuel

in

at

outboard

fuel

the

in

switch.

on

sump

each

the

transmitters

quantity

pump

valve

panel

engine-

rear

are

fuel

in

are

each

on

and

in

and

of

in-

the

lo-

the.

1-15.

mounted

on

wires.

Engine

-pane’l

vides

The

each

winds.

sure

instrumentation

ment

manual

mental

pilot’s

valve

’panel´•for

1-16.

INSTRUMENTS.

tracks

The

instruments

as

air

static

side

This

for

panel

and

control

lower

is

CABTN

on

for

is

pressure

of

operation

located

’E~mergency

VENTILATING

Pressurization.

achieved

charging

by

system.

turbocharger

cabin

pressurization

exchanger,

components.

operational

an

rated

differential

airflow

have

percent

pressure

and

Pressurization

trols

pressure-dump

the

easy

flight

the

system

the

system

lighting

automatic

panel.

pilot’s

acceleroineter.

fuselage-to

using

instruments

panel,

access

panel

are

to

operate

uses

supplies

of

the

static

equipment

dimming

An,dlternate

behin~d’the

operation

PRESSURIZATION,

SYSTEMS.

land

air-flow

The

power

power,

of

is

set.

and

cp

bleed

The

its

system

five

entirely

shutoff

system

controls)

duct

settings

while

of

to

Pilot

using

and

with

been

All

to

is

fully

installed

two

altimeter

Cabin

air

system,

and

is

4.

1

Seven

automatic

operated

valves

shock

the

instruments

slides

the

on

The

yjitot

airspeed

buttons-one

mounted.

flight

which

instrument

static

compensate

atmospheric

and

other

pressure.

incorporates

systems.

located

are

static

pilot’s

instrument"e

’of’i6struments;´•´•i

HEATING,

pressurization

from

pressure

designed

maintaining

PSIup

the

turbo-

is

composed

the

on

as

pouirj~er

engine,

ram-air

a

control

to

low

to

24,

once

emergency

are

provided.

a.s

are

outward

lines

and

co-pilot’s

System

indicator.

on

for

cross-

pres-

The

instru-

both

Environ-

the

on

pre~sure‘?’

AND

is

of

the

heat

be

fully

25

cabin

a

000

feet

minGte.

the

con-

pro-

:i’

1-8

-WAR~TING

The

pressure

the

aft

defective

2.

Heating.

may

do

set;

A

obtained

tb´•

reduce

which

maximum

temperature

through

changer.

ation

the

ambient cabin. manifold

Hot

ing

ambient

heat

air

side

duct,

A

from

ventilating

circulates

tributing

heating

3.

head

is

airscoop

unpressurized.

4.

Defrosting.

frosting

duct

windshield.

When

system

dividual

1-11.

it

through

to

ring

to

open

cabin

throuph

(below

the

cabin

entry!

pressure

not

i;ari~per

valve

through

the

temperature

reach

engine

controlled

is

the

conditioning

A

shutoff

in

conSunction

exchanger

or

turbo-’charger-

heater

provides

the

to

heat

corltrol

of

air

blower

cabin

system

or

cooling

Ventilation.

provides

obtained

is

through

defrosting

EMERGENCY

is

impossible

the

baggage~compartment

release

the

door.

the

outer

the

door

regulating

bulkhead

with

must

Cabin

the

ram-air

a

temperature

loads

valve

duct,

muff

a

muff

source

surrounding

is

exchanger

cabin

in

the

air

through

to

provide

air.

A

Heated

from

a

nozzies

the

locking

Tb

baggage

handle)

nor

the.bagga=e

or

any

valves

c~8

these

be

replaced.

air

temperature

heat

the

of

20,

by

side

in

with

allows

bleed

sent

000

varying

of

the

a

of

au~ilary

through

and

at

temperature.

aft

end

the

even

manually

ventilation

air,

the

cabiii

control

at

EXIT

to

OR

open

pins

~gain

emergency’

do’or,.’i~ress

and

t;;rn

windoui’which

located

f~36t(lr’Y

valves.

control

exchanger

turbonbleed

200’F

of

feet.

the

cabin

free-

selection

airflow

of

overhead

distr8bution

operated

for

valve

the

ENTRANCE.

the

and

door

Cabin

air

heat

pressuriz-

air

the

right

cabin

the

mixed

the

cabin

when

windshield

pre~ssurization

~ind

~base

cabin

door.

turn

entranc’i~

handl’e‘.

the

can’be’opened

will

on

under

flow

ex-

valve

of

to

the

condition-

with

A

dis-

over-

the

ducts´•to

of

each

door,

Pull

the

provide

is

used

air,

air

in

either

exhaust

heat.

re-

of

cabin

de-

exit

the

handle

~o

thU~1Sd

If

in-

the

release

neither

break

exit

or

1~9

SECTION

GROUND

SERVICING,

INSPECTION

HANDLING,

AND

´•_.´•_

SECTION

.___

U,

GROUND

HANDI;~G,

._´•

_´•

_I

SERVIC~O,

r´•

AND

I

PARA

2-1. 22´•

2-3.

2-4,

2-5,

2-6,

2-7,

28,

2-9.

2-10,

2-11,

2-12,

2´•13´•

214´• 215; 2-16,’

2-17,

218.´•

2-19.

2-20..

221,

2-22,

2~23.

2T24,

2-25.

2-26,

2-27.

2;-28.

2-29,

2-30.

231. 2-32. 2-33,

2-34,

2-35,

Ground

Towing

Warmup

Parking Emergency

/General

Fuel

Fuel Fuel

Servicing

Sump

SeZector

Defueling

Engine Engine Battery

Tires

Hydraulic

Brake Nose

Nose

Main

Servicing

Gear Gear Gear

Oxygen

Cleaning

Windshields,

Engine

Interior

Jacking.

Leveling

Weight

_

Outdoor

Longtime

Returning

Inspection

Check

Aircraft

PolnLs

Engine

TABLE

OF

randling

and

Taxing

and

Mooring

Procedures

Air6raft

Drains

Oil

Induction

Brake

Shock

Servicing

Valve

Air

Reservoir

and

Strut.

Steering

Shock

Struts

System.

Fac"e

Masks

Windows,

Compartment.

and

Upholstery

and

Balance.

Storage

Plircraft

File

Inspection

Functional

CONTENTS

Drain

Filter

Bleeding

Shimmy

to

Service

Check

and

Damp

Boors.

I

..,.,.,,21

,..,...2-4

........21.

......,...28´•

........2-11

.........2-13,

.,......2-14~

.,.,...2-41.

..,,2-3

PAGI

21

..21?

2-1

2-2,

23

2-4.

25, 2-6,

28

29´• 29

210

210 2-11

~12

2-12

212

21L~

2-17.

Z1P.

2-

1’9

2-i9

2-t0.

~d-

z

rC

;TION

II.

GROUND

HANDLING,

TABLE

(Continued)

SERVICn;IG,

CONTENTQ

OF

AND

INSPECTIOW

PARA

i-36

2-37

2-38 2-39

2-40

2-41 2-42

2-43

2-44.

2-45

2-46

2-47

2-48

2-49 2-50

2-5~

2-52´•

25-Hour

fj0-Hour

100-Hour

Scope

Engine

Inspection........´•

Inspection.

lOeHour

of

Inspection.......´•´•

Propeller

Landing

Fuel

AircraftExterior

Internal

Special

AircraftInterior

Flight

Instrument

Cabin

Electrical

Post

Gear

Sjrstem

Aircraft

1000-Hour

Control

Pressurization

Inspection

periodic)

(or

Inspection.........´•´•´•´•´•´•

Retraction’System

Inspection

Inspection.......´•´•

Inspection......´•´•´•

Inspection.........

Ins9ection

Leakage

Functional

Flight

Test...........´•´•´•

Test

Inspection...

Inspection

Test

PAGE

21

2-

2-22

2-23

2’

2-25]

2-26)

2-20’;

2-27

2-28!

2-28

2-28~

2-20j

2-30

2-32

2-

24

32

.,I

REVISEI/

’-.´•:j-5

2-1.

C~OUhTD

KA~DLING.

2-2.

:ai~craft

iing

TOW~G.

in

.hangar.

taches

aircraft

t~he

~tLtively

When

iin

hand

wings,

board

peller equipment

CAUTION:

the

of

result

no

moving

is

aircraft

nose

180

portion

either

by

close

to

the

smooth

towbar

the

permited:

on

(2)

hub.

is

When

wheel

if

this

Use

hand

and

quarters

nose

providing

and

is

aircraft

the

of

propeller

Towing

not

recommended,

maneuvering

exercise

past

side

turning

a

for

on

wheel

the

available,

is

on

(1)

wing

tips,

by

caution

normal

its

of

center.

angle

towbar

ateerin~

the

axle.

ground

tires

r~quired,

the

blades

tractor

is

for

ramp

The

One

surface

are

properly

when

or

leading

and

(3)

or

not

to

swivel

Damage

exceeded.

moving

and

maneuver-

in

or

towbar

man

assistance

pushing

edges

on

adjacent

other

towing

turn

angle

will

the

a

at-

can

move

is

re-

inflated.

by

of

the

in-

to

pro-

powere~d’

2-3.

who

WARMUP

service

checked

personnel

aircraft.

Start

1.

Manual).

2.

Taxi

their

test

3,

While

nose

turn

reaction

sponse

2-4.

the

and

the

gear

4.

Check

coordinator

5.

Check

6.

Check

PtlRKL~G

aircraft,

aft

parking

out

by

before

and

forward

effectivness.

steering.

during

to

engine

of

main

brakes

AND

and

handle

qualified

attempting

warmup

taxing,

operation

during

operation

turns.

engine

control

AND

install

wheels.

TAXDI~G.

the

pilots

few

a

make

of

turns.

of

instruments

wheel

be´•

may

c~ircraft

or

to

engine

feet

and

shallow

gyro

PC

System

movements.

chocks

For

short-duration

used.

Ground

should

other

warmup

~2efer

check

turns

instruments

for

sluggish

When for

personnel

be

responsible

taxi

or

to

Owners

brakes

to

test

for

control

parking

the

to

and

re-

parking,

,-I

_:,´•

’wheel.

three

side

outboard

’tensil

.~hor

tiedown

ring

either

nose

belt

snug.

craft.

NOTE:

brakes

and

ing

when

i.

moor

a.

b.

c.

of

d.

to

e.

and

f.

gear

g.

2.

Do

&re

slush

cold

aircraft

MOORING.

the

Read

Place

Drive

feet

outboard

the

tailskid.

Install

of

strength

ground

rope.

Tie

the

anchor

side

For

and

Lock

through

For

not

overheated

acculuulation

weather.

airplane

aircraft

chocks

stakes

tiedown

each

rope

stake.

center

rope

of

tail.

additional

anchor

controls

the

maximum

set

tied

is

When

as

i~nto

fore

in’ground,

of

main

to

of

ends

control

protection,

parking

or

could

Do

not

down.

parking

follows:

the

anc!

each

rings

gear.

each

Allow

a

rope

to

security,

to

a

ground

by

looping

wheel

brakes

wl;en

freeze

set

parking

outof

wind.

aft

approximately

main

in

the

Tie

tiedown

little

a

to

ground

attach

right

when

moisture

doors,

of

each

gear

and

wing

a

GG~3-pound

ring

slack

tail

skid

stakes

a

stake.

seat´•

drawing

hangar

ciur-

brakes

ma;,n

to

either

receptacles

!min.)

and:

an-

in

each

tiedown

at

the

to

safety

the

air-

rope

the

belt

2-5.

of

EMERGENCY

i.

Engine

fire

a

starting,

take

ing,

Close

a.

Turn

b.

Set

c.

Turn

d.

Pull

e.

f.

Discharge

compartment

2.

Fuselage

fire

in

wheel

’immediateljr

controls

the

aircraft

REVISED

in

the

if

the

inixture

firewall

in

the

to

04-22-68

Fire

During

engine

the

fire

following

c’owl

.9ll~switches

’flaps.

control

fuel

well

place,a’il

selector

fire

through

or

(or

OFr"

extinguish

Wheel

PROCEDURES.

Starting.

compartment

is

not

.put

action:

´•off.

at

to

OFF

shutoff

valve

extinguisher

the

nose

Well

in

the

cabin

electrical,

position;.

the

flames.

IDLE

cowl

Fire.

then,

In

during

out

by

CUTOFF.

to

OFF.

into

openings.

In

fuselaEEe

or

fuel,

the

and

engine

cranlr-

case

event

engine

of

;ti-ea),

ig;lition

22

k

3.

(exccpt

ed

by

that

automatically

overload

an

df

an

the

aflit

Electrical

the

circuit

electrical

alternator

Make

for

Fire.

ignition-starter

breakers

interrupt

short

or

sure

electrical

fire,

circuit

turn

iield

that

electrical

All

circuits)

(orcircuit-breaker

of

flow

battery

extin,ruisher,

used.

off

switch

only

fires,

the

occurs.

the

immediately.

fire

a

is

circuits

are

In

protect-

power

the

switch

switches)

when

event

requirements

~ig

,´•~ubrication

r

$ervicing

meet

I~

conditions.

ing

environmental

perature

humidity

high

facilities,

shorten

27.

through

tank

has

capacity

filled

~half

lation

30-gallon

be

may

GENE,stAL

intervals

avera~e

ranges,

or

service

FUEL

filler

a

capacity

is

to

of

moisture

indicator

viewed

AIRCRAFT

are

Guide

requirements

When

conditions,

dusty

and

unusual

and

SERVICING.

ports

95’1J.S,

minimize

through

outl!:r?ed

Fi~ure

considered

are

operating

atmospheric

moisture,

operating

maintenance

on

top

of

47

gallons.

condensation

within

installed

is

the

SERVICING.

in

under

such

unimproved

Fuel

of

the

U.S.

gallons:

Keep

the

tartls.

filler

the

Service

These

adequate

normaJ.

under

as

abnormal

extreme

conditions,

airport

requirements,

intervals.

tanks

wings.

fuel

in

each

opening.

A

are

and

serviced

Each

total

tanks

accumu-

visual

tank

Servic-

and

to

operat-

tem-

fuel

at

and

least

vehicle

ing

WITHDI~

NOTE:

mosphere

vent

surface,.

each

Z-8.

valve

tank

to

Drain

’REVISED

nozzle

openings

flight.

FUEL

locared

is

provide

fuel

must

to

FEET

50

Each

at

C~heck

SUMP

for

sumps

11-15-61

The

be

wing

fuel

its

are

in

aircraft

grounded.

and

aircraft

of

tank

outboard

located

vents

GRAINS.

aft

the,

drainage

the

fuel

and

Ground

allow

is

for

inboard

NO

or

vented

rear

corner;

the

on

obsti´•uction~before

A

flush

corner

of

moisture

small

plastic

service

servic-

SMOKING

ve‘nicle.

the

to

lower

fuel-

~t-

wing

drain

of

and

cup

i

each

sediment.

23

furnished tank

the

first

service.

and

with

selector

flight

of

the

valve

each

loose

equipment.

sumps

and

day

before

after

Drain

each

wing

fuel

NOTE:

fuel,

and

checking

fuel

29.

fuel

selector

fuel

system,

control

a

drain

1.

fuel

pull

2. fuel

pull

3.

control

not

leaking

NOTE:

~requently

for

wait

sediment

selector

FUEL

the

Switch

drain

Switch

drain

After

knob

ice

After

at

both

SELECTOR

valve

and

the

on

fuel

draining,

is

outside

During

formation.

servicing

least

to

the

valve

has

fuel

selector

fuel

selector

valve

fuel

selector

control

full

cold

check’the

five

settle

fuel

drain.

at

is

a

console

control

for

be

forward

the

minutes

before

tank

VALVE

the

drain

valve:

sure

aircraft.

weather

fuel

the

lowest

valve

for

valve

10

and

a~rcraft

draining

sumps

DRAIN.

valve

fn

the

10

seconds.

fuel

that

operation,

selector

for

and

point

operated

cabin.

L

to

seconds,

R

to

drain

the

with

moisture

the

in

tank

valve

drain

i

and

The

the

by

To

and

valve

is

210.

ed

boost

through

rmARNING

container

Allow

WITTHIN

boost

electric

to

and

by

i.

a.

b.

reach

c.

remove

d.

DE

FUE

pumping

pumps

the

hTO

50

defuel

To

pumps:

Disconnect

boost

Connect

fuel

Turn

fle’peat’.lsteps

LING.

fuel

or

by

filler

Ground

during

SM~KING

FEET

pump.

recepticle.

fuel

filler

boost

on

and

c

The

out

of

siphoning~fuel

ports.

aircraft

the

all

defueling

OR

OPEN

of

the

aircraft

fuel

line

flexible

a

selector

from

cap

pumps

dto

drain

fuel

tanks

the

tanks

operations.

FLAME

defueline;

by

at

output

line

of

valve

filler

until

other

may

with

from

and

the

area.

operating

fitting

suitable

to

desired

port.

tank

tanhr

the

is

be

the

tanks

fuel

the

length

empty.

drain-

electric

of

tank

2-4

L~-

---I---

To

2.

sump

stops

2-11.

oils

drains

running,

ENGINE

that

straight

CAUTION:

mineral

or

specification

in

Lycoming

the

is

responsibility

ufacturer.

1014

Oatest

I.

Oil

operation.

engines

first

the

sumption

Recommendations

2.

PnainP

nn

II-

for

oil oil

engine

switch

several

should

is

to

afterthe

changing

compounded

steps:

Do

a.

oil.

clean

five

sludge

element

sume

ditions

Drain

b.

hours

c.

screen,

Do

or

normal

completely

and

fuel

OIL.

appear

mineral

Any

superior

oil

lubrication

compounded,

No,

engines.

Consult

revision)

Recommendations

Operate

on

straight

50

hours

has

stabilized,

hPPn

hnn

’’"U

UYY--

hundred

undertaken

be

in

an

extremely

additive

en~ine

from

not

oil,

the

has

straight

take

mur

straight

change

not

operate

before

Check

all

plugging.

every

10

oil

impi~ove.

and

301E

of

Lycoming

new~,

of

operation,

VrY-

oil

been

additive

the

oil

hours

drain

fuel

selector

There

in

their

oil,

must

to

be

Proof

the

lubricating

for

oil

or

For

LIIIILP

hours,

with

di~ty

should

overhauled.

mineral

the

following

oil

mineral

filtelaand

the

engine

first

screens

Change

oil

if

sludge

periods

system,

drain

are

performance

use

conform

acceptable

of

Service

recommendations.

aviation

either

such

until

is

recommended.

straight

with

for

conformity

oil

Instru~tion

Elor’P~w-engine

mineral

or

ctraiahf

YI-

a

change

overhauled

oil

until

Oil.

If

netjvly

Changing

nn

V1I

caution.

condition,

deferred

be

When

oil

ar~d

replace

change.

for

oil

ar~l2

after

oil

additive

to

precautionary

straight

from

longer

evidence

filter

oil

is

evident.

sludge

opel´•ate

fuel

additive

to

Lycoming

use

man-

uuring

oil

con-

When

minprnl

to

additive

the

until

mineral

the

oil.

than

of

con-

LSI

or

engine,

Re-

Zt

CILUTI~N:

"compounded"

to

Do.

to

which

refer

cylinder

which

not

Do

refer

to

oils

to

improve

not

do

"top

as

remover" oil.

engine.

cumstances.

The

a

them

use

used

class

certain

to

not

Such

terms

in

of

for

such

lubricanij’

are

such

use

oils

"detergent:’

manual

this

aviation

substances

aircraft

materials

cn&ine

use.

commonly

"dopes"

sonetimes

prnducts--they

automotive

can

oil

cause

"additive,

are

have

These

and

added

under

engine

intended

lubricating

"carbon

to

added

terms

known

fuel

been

damage-the

any

failure.

and

or

cir-

fJ.

engine

stopped

sump.

quarts..

door

the

4.

instdlled

is

refill

and

every

months

cumulated.

5.

-filterat

filter

-the

oil

suctioniscr’eenp,i31ean

;Examine

NOTE:

ation

when

with

and

,when.conditions

Checking

level

oil

long

Maintain

Access

the

in

Draining

in

sump

hours~of

50

if

50

Engine

the

right

cartridge

screeii’anrl

During

in

dusty

flights

prolonged

filter

~neine after

enough

the

to

top

Oil

the

hours

Oil

have

element

Oil

for

engine

filler

the

cowling.

Sump.

oil

sump,

with

operation,

of

flying

Filter.

rear

of

each

at

filter

periods

areas,

been

idling

each

warrant.

oil

the

in

time,

Level.

the

to

oil

cap

A

quick-drain

Drain

the

correct

or

time

Remove

engine

oil

inspect

for

of

prolonged

cold

of

short

25

engine

drain

level´•

is

once

have

chdnge.’

metal

climates,

~ange

hours

Check

back

at

gained

the

every

the

and

!?articles.

duration

or

the

has

into

~31

to

through

fitting

oil

sump

grade

been

not

engine

replace

Remove

reinstall.~

oper-

or

oil

the

more-often

been

1´•B

of

four

the

oil

I

ac-

the

d12.

ENCLNE

importaxlce

cannot

motes

be

fuel

dry-type

times

before

of

over

economy

filter

replacement

~NDUCTfON

f~eeping

the

emphasized.

and

can

usually

induction

longer

be

is

ATR

FILTER.

A

clean

engine

washed

necessary~

air

filter

life;

six

filter

to

The

clean´•.

pro-

The

eight

2-6

Replace

hours

first.

1.

2.

side

or

To

Remove

Direct

of

filter

the at

clean

one

induction

year

induction

the

filter

jet

of

a

(opposite

filter

air

interva3s,

against

to

aircraft.

normal

from

air

whichever

air

every

filter;

the

air

500

down

flow).

occurs

or

clean

NOTE:

nozzle

a

3.

filter

4.

for

dam~e.

gasket.

NOTE:

of

carbon,

ing

5.

minutes;

to-five

deposits

NOTE:

recommended.

is

Keep

element.

After

steps

Soak

then,

minutes

Do

not

pressure

air

nozzle

Cover

cleaning,

Discard

If

the

soot,

5

through

fi3ter

~1Cate

to

Donaldson

use

greater

filter

or

in

nonsudsing

filter

free

Do

a

compressor

at

Icast

entire

inspect

a

ruptured

shows

oil,

8.

the

11-1400

not

than

area

filter

an

continue

back

filter

Filter

use

?Init.

100

t7;vo

inches

with

and

filter

accumulation

with

detergent

and

forth

element

Cleaner

solvents.

PSZ.

air

gasket

or

with

from

jet.

broken

clean-

for

of

15

two-

6.

water

bulb

or

8.

filter

replace

9.

airvalve

10.

proper

2-13.

distilled

plates

weather,

and

water.

gravity

1.

2.

quired.

Rinse

until

Dry

air

Inspect

before

filter

Check

in

Reinstall

sealing

BATTERY.

water

at

all

charge

to

Remove Check

filter

rinse

filter

heated

for

a

light

with

flapper

wheel

and

times.

Keep

batter3r-box

electrolyte

element

water

is

thoroughly._

above

damage

bulb.

a.

new

vdlve

well

for

filter

in

security.

Service to

maintain

After

battery

freezirig.

with

cl~ar.

180~F

and

If

damage

one.

in

ram

proper

aircraft,

the

adding

long

above

cover.

and

service

stream

a

Do

not

for

ruptures

air

operation.

battery

electrolyte

water

enough

225

1.

use

drying

by

is

duct

making

using

to

specific

battery

of

clear

a

light

filter.

holding

evident,

and

sure

above

in

freezing

mix

electrolyte

as

of

only

re-

2´•7

3.

ed

electrolyte.

4.

st

use

water

Check

To

solution

to

neutralize

clean

battery

cables,

bicarbonate

of

box

terminals,

corrosion

for

corrosion;.

soda

of

and

spilled

and

Sattery

and

spill-

box,

clean

electrolyte.

CAUTION

bicarbonate

cells--permanent

Rinse

5.

6.

’S’i~i_ne

To

7.

petroleum

CAUTION:

ulator

system

when

Determine

load

214.

connecting

test

TIRES.

recommended

retard

jelly

are

only;

When

of

with

battery

after

The

designed

make

battery

least

~it

Keep

the

in

cleaning,

soda

to

damage

clean

water.

with

clear

corrosion,

cleaning

alternator

for

sure

a

charger

condition

twice

tires

the

Servicing´•and

enter

use

bf

each

coat

do

the

will

dry

terminals

and

tightening.

and

voltage

on

one-polarity

correct

booster

or

means

by

year.

at

the

Lubricatioa

allow

not

battery

result.

cloth.

polarity

airpressure

with

reg-

battery.

of

a

Guide,

2.

page

215.

Check

quently

a

hydraulic.

to

back~bleed

bleeder

cation

45

PSI.

CAUTION:

leased

servicing.

may

Check

or

pulling.

HYDRAULIC

the

hydraulic.

for

proper

pressure

valves.

MILrO-

prior

be

under

tires

valve

the

5806.

Be

The

fluid

system

Use

sure

to

starting

high

for

stem

BRAKE

brake

~service

hydraulic

Pressui´•ize

fluid

pressure

wear,

for

reservoir

level.

through

parking

hydraulic

in

the

cuts,

evidence

RESERVOIR.

best

For

unit

~3ressure

the

fluid

service

brakes

wheel

due

to

and

bruises.

of

tire

fre-

results

wheel

(red)

unit

are

system

cylinders

expansion.

slip-

use

pot)

cylinder

specifi-

~at:

re-

28

2-~6.

Remove

i.

and

plug

into

line

2.

Immerse

fluid

unit

vdlve.

bubbles

shuttlevalve.

wheel

line

5,

install

container.

3.

to

4.

5.

6.

7.

and

8.

Attach

Depress

When

cylinder

Remove

BRAKE

install filler

wheel

Depress

Feed

end

at

bleed

To

6.

filler

SERVIC~TG

hydraulic

suitable

hole.

open

pressurized

cylinder

the

fluid

of

into

flexible

co-pilot’s

Repeat

flow

is

bleeder

opposite

flexible

plug.

end

bleeder

pilot’s

system.

step

clear

fluid

fitting,

of

hydraulic

line

brake

of

valve

brake,

line

AND

flexible

brake

4.

air

from

BLEED~nTG.

reservoir

to

valve

pedal.

Check

immersed

pedal

bubbles,

and

remove

repeat

reservoir

attach

line

fluid

and

filler

flexible

in

service

open

for

air

in

to

reposition

close

service

steps

hydrai~lic

fluid.

4,

3,

and

re-

NOTE:

into

hole

9.

10.~

Resistance

are

depressed.

gear flation

ton

over

shock

will

rough

servicing

NOTE:

strut

grit

the

pressure.

the

Check

NOSE

and

not

piston

so

barrel

Hydraulic

system

brake

must

GEAR

strut

extension

bottom

surfaces.

details.

Keep

not

as

with

fluid

through

lining

pedals

solid

be

SHOCK

shouldbe’checked

to

when

the

cut

to

may

the

for

for when

insure

the

Refer

exposed

free

or

damage

resulting

be

reservoir

excessive

spongy

STRUT.

that

aircraft

to

paragraph

part

from

loss

gravity

brake

the

of

for

the

of

dust

fluid

feel.

pedals

The

proper

strut

is

the

seals

fed

filler

wear.

nose

taxied

shock

and

5-

pis-

~1

in

in-

for

i.

piston

Wipe

with

exposed

a

clean,

(polished)

cloth.

dry

area

of

shock

strut

29

tETdiii~TING:

Rsliova

ing

turns

~trut

2-18.

’DAMPER,.~

~iteering

through

Bhimmy

pydraulic

all

inch

3/4

counterclockwise

with

hydraulic~fluid.

NOSE

arm

the

damper

fluid

damping

Remove

pressure

(thin)

GEAR

The

are

hydraulic

level

action

~Lir

in

nut

on

before

STERRING

nose

connected

s~iimmy

should

checked

fails

to

valve

strut

air

gear

by

v-,ivo

to

removed

be

when

function

cap.

eurn-

2

servicing

SHIMMY

gr.

steering;

the

nose

damljer.

steering

properly.

1/4

bar

and

wheel

The

the

or

Check

inflation

landing

terrain. details.

the

or

2-17.

2-20.

when

and oxygen.

-the

the

bracket.

OXYGEN

fG.lly

1800

’Pn

snap-on.

co-pilot’s

Release

2.

Remove

3.

sembly

Refill

4.

oxygen

(Federdl

equivalent).

install

5.

mova!

procedure.

GEAR

main

and

when

Refer

(See

serviced

gear

extension

the

to

NOTE

SYSTEM.

PSIpressure,

refill

To

crain

LCVVVYY

~ULII

plastic

seat.

clamp

oxygen

cylinder

Specification

cylinder

SRUCK

shock

to

prevent

aircraft

paragraph

and

WAR~NING,

at

standard

contiains

the

oxygen

f~

nu~rapn

´•´•V

V1IJ

cover

securing

cylinder

with

in

STRUT~,

strut

taxied

is

5-11

The

oxygen

temperature

cylinder:

~vlinrlPr

VJ

bV1I

on

the-right

cylinder

and

aviator’s

BB-0-925,

reverse

piston

bottoming

over

for

servicing

paragraph

4.5cubic

just

re~ulator

breathing

sequence

_pbsition

un

rough

cylinder

(70bF)

feet

rpmn´•trp

J´•

UIIIV

forward

to

mounting

or

of

as-

re´•

for.

proper

of

of;

WAR~ING:

linder,

other

or

oxygen

hazard.

do

not

lubricants

system

in

contact,

i

’Ci:hen

allow

components.

servicing;

oil,

to

come

creates

the

grease,

in

a

Oil

fire

oxygen

solvents,

contact

v~ith

or

cy-

with

pure

explosion

2r

2-/0

2-21.

face

When

the

masks

servicing

face

OX"ITGEN

masks

dition.

i~22.

?fdequate

CLEAN~G.

inspection

components;.

the

appearance

it

reduces

Before

i.

brake

cool

2.

3.

discs,

Flush

Wash

water.

are

the

pitot

away

with

FACE

stowed

oxygen

and

hoses

and

Not

only

of

an

probability

washin~

head,

loose

mild

a

I\liASKS.

with

system

to

Cleanliness

ru~mtenance

does

aircraft

of

aircraft

and

dirt

aircraft

Disposable

the

oxygen

include

determine

is

cleanliness

but,

corrosion.

exterior,

static

and

cylinder.

an

their

a

inust

of

most

ports.

mud.

detergent

oxygen

inspei~tion

oon-

9or

aircraft

enhance

important,

cover

and

~f

~md

4.

5.

pre-wax

6.

for

the

7.

edges

reduce

NOTE:

fluid

surfaces,

ing.

NOTE:

flushed

be followed

aircraft

CAUTION:

household

exterior.

finish

skins

Use

To

remove

cleaner.

Apply

protection

Apply

of

wings,

drag

containing

treated

Do

detergents

Such

and

cause

soft

a

exterior-finish

an

a

heaty

empennage,

and

abrasion.

When

remove

Spilled

by

with

a

thorough

away

detergent

nait

detergents

corrosion

cleaning

heavy

of

acrylic

coating’of

fuel,

dye

at

battery

water,

bicarbonate

solution.

so

use

to

cloth

oxidation

enamel.

hydraulic

is

spilled

once

electrolyte

washing

wash

and

to

and

called

may

on

or

film,

wax

nose

fluid,

on

prevent

the

of

soda

"mild’’

aircraft

the

damage

aluminum

chamois.

use

recommended

the

to

section

or

paihted

stain-

must

area

solution

with

mild

a

leading

to

other

be

must

NOTE:

~:leaners

period.

and

clean,

90

days

Do

during

Use

after

not

only

cool

apply

the

mild

water

delivery

wax

initial

or

paint

aircraft

during

or

repainting.

use

detergent:

pre-wax

curing

the

first

2-23.

Pressurized

doors

than

require

those

I.

shields

kind.

2.

hear

depth

prior

saturated

the

3.

require

4.

to

5.

-W~INDSiIIEL;DS,

aircraft

of

Prior

for

scratches,

Pay

especidll~

outer

Scratches

Flush

wiping.

Remove

with

more

hon~ressurized;

to

flight,

edges

installation

windshield

grease

kerosene.

stringent

which

Never

windshields,

inspection

air~raft,.

check

windows

cracks,

pane~

exceed

and

wipe

or

~ttentioli.´•

of

a

windows

with

oil

while

close

of

-4NDI)OORS.

windows,

fissures

or

010

0.

new

pane.

a

with

dry.

soft

and

to

inches

and

wind-

water

cloth

and

care

of

defects

in

any

CAUTION:

carbontetrac

tin~uisher

household

or

windows

soften

6.

static

7.

leakage.

8.

silicone’

9.

proper

2-24.

of

dirt

fire

a

spection

fluid,

or

craze

Clean

windows

plexiglas

Check

If

Check

operation,

ENGINE

and

hazard

door

seals

stick-type

cabin

oil

requirements.

Never

use

hloride,

de-icer

window

windshields.

the

surface.

and

cleaner.

seals

are

dry,

lubricant.

’and

COMPARTMENT.

within

and

the

hampers

gasoline,

acetone,

fluid,

cleaning

Such

windshields

for

damage

lubricate

~baQ;gage

engine

completion

benezene,

fire

ex-

lacquer

sprays

solvents

lightly

ddor

compartment

on

with

that

mechanism

An

accumulation

of

could

with

thinner,

will

an

a

vital

anti-

cause

for

creates

in-

NOTE’:

cowl.

1.

Wash

’compartment

2.

Wipe

pal´•tq~nt

2-25.

Use

dry

INTERIOR

normal

Consult

´•.opening

down

engine

using

engine

after

household

paragraph

instructions.

non-flamabl~

a

cowling

washing?

AND

3-2

cowling

and

arid

eng´•lne~com-

UPHOLSTTE,Y

cleaning

practi~tes.

for

engine

solvent,

1

2-12

for

routine

i.

holstery

dust

and

2.

panels

a

With

~loth.

interior

Frequently

panels

dirt.

Clean

with

leather

mild

a

slightly

Remove

care.

vaccum-clean

headliners

and

aircraft

damp

grease

or

cloth

vinyl

and

spots

seats,

to

remove

upholstery

detergent.

with

dry

using’ajel~y

rugs,

surface

and

Wipe

a

soft

kick

spot

up-

clean

dry

lifter.

NOTE:

terior

solvents

NOTE:

for

vinyl;

be

can

dition

cleaners

NOTE:

ution

which

padding

of

carpets,

and

rub

to

remove

remain

CAUTION:

solvents

commercial

pounds,

tions

and

up

Never

furnishings.

which

Foam-type

leather,

used

the

to

entire

are

Never

could

materials.

keep

in

circles.

foam.

also

damp;

Do

interior

on

cleaning

follow

carefully.

the

area

apply

hai´•mful

are

shampoos

and

remove

interior.

recommended.

saturate

damage

foam

Do

dry

thoroughly,

not

use

manufacturer’s

the

Spillage

dried

furniture

IMost

plastic

stains

fabrics

To

minimize

as

dry

Use

a

not

allow

ali=ohol

plastics.

and

thoroughly.

polish

polishes

to

vinyl.

and

materidls

and

Sp;´•ay-on

with

the

backing

as

vacuum

carpets

or

When

finishing

should

to

contain

cleaners

to

con-

a

and

wetting

possible

cleaner

strong

using

com-

instruc-

be

cleaned

in-

sol-

to

L~

2-26.

aircraft

the

i.

holes

’the

nose

lage,

CAUTION:

be

on

to

jack

cinlrlp

the

structural

REVISED

~ACKTNG.

Install

outboard

jacir-pad

ten

inches

used

the

nose

install

point.

ia~lr

nose

0~-22-68

off

jack

of

The

to

obtain

jack

separate

nninf

or

using

damage.

the

aftof

Do

When

ground:

points

each

adapter

jack-pad

proper

points.

not

a

main

the

jacks

raise

~lcina

single

it

in

~zrewdll

is

necessary

the

gear,

adapter

weight

Do

under

tile

cPnarntP

YVr-I-U-V

jack

tie

beneath

not

nose

down

and

bulkhead.

must

distribution

s_ttelnpt

each

by

lacks

J

point

to

raise

mounting

i3osition

the

fuse-

nose

using

under

can

cause

a

21

2.

minimum

each

adapter.

to

contact

3.

j~evel

4.

liistzll

Raise

as

possible.

Secure

standard

42-inches

of

ack

j

Holdinl;

jack

aircraft,

safety

point

points

jack

aircraft

overall

and’

points

firmly.

keeping

locks

under

on

jacks,

extension,

the

nose

in

place,

wings

each

jack.

´•CX~7ith

5

raise

as

nearly

under

ack

a

pad

jacks

CAUTION:

out

of

10

I~IPI-I.

NOTE:

bleed

taneously

level

NOTE:

without not

being

and

aft.

2-21.

aircraft

on

250.

the

LEVELING.

upper

Adjust

decreasing

by

raising

aircraft

boards,

Adjust

in

jack.

the

tire

@efert9

doors

When

off

pressure

ar,ci

it

as

is

The

raising

raised

determined

is

aircraft

air

or

laterally,

~orward

aircraft

on

Do

not

when

lowering

evenly

lowered.

nose.

the

skin

pressure

lowering

~lace

and

level

the

high

Figure

raise

the

wind

the

all

on

to

keep

wheel;

entire

should

Longitudindl

by

placing

line

between

level

in

the

a

center

side

the

velocity

aircraft

jacks

may

aircraft.

be

checked

the

jacks.

spirit

the

of

by

decreasing

or

by

aircraft

simul-

the

be

leveling

a

Station

I

by

nose

To

level

front

lowering

on

is

over

on

jacks,

aircraft

raised

Wheels

fore

of

spirit

level

225

increasing

wheel

level

the

on

seat

pressure

the

jacks

the

tire

the

floor-

tracks.

and

or

~28.

aircraft,

1.

listed

2.

3.

4.

of

each

5.

craft

6.

2-21.

WEIGHTAND

select

Check

the

in

Weight:

Ground

Drain

Position

of

the

Place

scales.

on

up

Level.

a

for

installation

aircraft

engine

a

three

a

ramp

aircraft

level

oil

2000

wheels.

BALANCE.

work

Balance

and

sump.

L~B

capacity

each

on

described

as

of

drain

area

dll

Record,

scale

Toweighthe

and:

equipment

fuel

tanks.

scale

and

move

in

paragraph

as

in

front

air-

2-14

Mooney Mustang M22 1967 Maintance Manual

Specifications and Main Features

Frequently Asked Questions

User Manual

engine

AIRFRAME

instruments

Towing

defueling

battery

tires

leveling