Cessna 177 SERIES User manual

REPRINT

MODEL

177

SERIES

1968

thru

1978

SERVICE

MANUAL

4

OCTOBER

1995

D841-8-13

THIS

REPRINT

INCORPORATES

CHANGE

8,

DATED

2

OCTOBER

1995.

-

rCessna

A

Textron

Company

MODEL

177

SERIES

1968

thru

1978

SERVICE

MANUAL

I

Member

of

GAMA

FAA

APPROVAL

HAS

BEEN

OBTAINED

ON

TECHNICAL

DATA

IN

THIS

PUBLICATION

THAT

AFFECTS

AIRPLANE

TYPE

DESIGN.

THIS

REPRINT

INCORPORATES

CHANGE

8,

DATED

2

OCTOBER

1995.

CESSNA

AIJCRAFT

COMPANY

I

JULY

1

970

WICHITA,

KANSAS,

USA

D841-8-13

CHANGE

8

2

OCTOBER

1995

(RGI-50-12/00)

A

Textr

Company

TEMPORARY

REVISION

NUMBER

6

DATE

January

15,

2008

MANUAL

TITLE

MANUAL

NUMBER

-

PAPER

COPY

MANUAL

NUMBER

-

AEROFICHE

TEMPORARY

REVISION

NUMBER

Model

177

Series

1968

Thru

1978

Service

Manual

D841-8-13

D841-8-1

3AF

D84

1-8TR6

MANUAL

DATE

1

July

1970

REVISION

NUMBER

8

DATE

2

October

1995

This

Temporary

Revision

consists

of

the

following

pages,

which

affect

and

replace

existing

pages

in

the

paper

copy

manual

and

supersede

aerofiche

information.

AEROFICHE

SECTION

PAGE

FICHE/FRAME

2

22

26

27

28

AEROFICHE

SECTION

PAGE

FICHE/FRAME

1/B18

Added

REASON

FOR

TEMPORARY

REVISION

1

.

To

add

an

inspection

of

the

reel

type

secondary

seat

stop

installations.

2.

To

add

replacement

time

limits

for

the

landing

and

taxi

light switch.

FILING

INSTRUCTIONS

FOR

THIS

TEMPORARY

REVISION

1

.

For

Paper

Publications,

file

this

cover

sheet

behind

the

publication's

title

page

to

identify

the

inclusion

of

the

Temporary

Revision

into

the

manual.

Insert

the

new

pages

into

the

publication

at

the

appropriate

locations

and

remove

and

discard

the

superseded

pages.

2.

For

Aerofiche

Publications,

draw

a

line

with

permanent

red

ink

marker,

through

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(page)

affected

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Revision.

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visual

identifier

that

the

information

on

the

frame

(page)

is

no

longer

valid

and

the

Temporary

Revision

should

be

referenced.

For

"added"

pages

in a

Temporary

Revision,

draw

a

vertical

line

between

the

applicable

frames.

Line

should

be

wide

enough

to

show

on

the

edges

of

the pages.

Temporary

Revisions

should

be

collected

and

maintained

in a

notebook

or

binder

near

the

aerofiche

library

for

quick

reference.

3.

For

CD

publications,

mark

the

temporary

revision

part

number

on

the

CD

label

with

permanent

red

marker.

This

will be

a

visual

identifier

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the

temporary

revision

must

be

referenced

when

the

content

of the

CD

is

being

used.

Temporary

revisions

should

be

collected

and

maintained

in

a

notebook

or

binder

near

the

CD

library

for

quick reference.

©

Cessna

Aircraft

Company

A

Textro

Company

TEMPORARY

REVISION NUMBER

5

DATED

1 1

July, 2005

MANUAL

TITLE

Model

177

Series

1968

Thru

1978

Service

Manual

MANUAL

NUMBER

-

PAPER COPY

D841-8-13

MANUAL

NUMBER

-

AEROFICHE

D841-8-13AF

TEMPORARY

REVISION

NUMBER

D841-8TR5

MANUAL

DATE

1

July

1970

REVISION

NUMBER

8

DATE

2

October

1995.

This

Temporary

Revision

consists

of

the

following

pages,

which affect

and

replace existing

pages

in

the

paper

copy

manual

and

supersede

aerofiche

information.

AEROFICHE

SECTION

PAGE

FICHE/FRAME

SECTION

PAGE

FICHE/FRAME

13

13-7

1/L01

13

13-7A

Added

13

13-7B

Added

REASON

FOR

TEMPORARY

REVISION

1.

To

add

additional

information

to

install

gaskets

and

plate

between

the

propeller

governor

and

the

engine

accessory

case.

FILING

INSTRUCTIONS

FOR

THIS

TEMPORARY

REVISION

1

.

For

Paper Publications,

file

this

cover

sheet

behind

the

publication's

title

page

to

identify

the

inclusion

of

the

Temporary

Revision

into

the

manual.

Insert

the

new

pages

into

the

publication

at

the

appropriate

locations

and

remove

and

discard

the

superseded

pages.

2.

For

Aerofiche

Publications,

draw

a

line

with

permanent

red

ink

marker, through

any

aerofiche

frame

(page)

affected

by

the Temporary

Revision.

This

will

be

a

visual

identifier

that

the

information

on

the

frame

(page)

is

no

longer

valid

and

the

Temporary

Revision

should

be

referenced.

For

"added"

pages

in a

Temporary Revision,

draw

a

vertical

line

between

the

applicable

frames.

Line

should

be

wide

enough

to

show

on

the

edges

of

the

pages.

Temporary

Revisions

should

be

collected

and

maintained

in a

notebook

or

binder

near

the

aerofiche library

for

quick reference.

3.

For

CD

publications,

mark

the

temporary

revision

part

number

on

the

CD

label

with

permanent

red

marker. This

will

be

a

visual

identifier

that the

temporary

revision must

be

referenced

when

the

content

of

the

CD

is

being

used.

Temporary

revisions

should

be

collected

and

maintained

in

a

notebook

or

binder

near

the

CD

library

for

quick

reference.

©

Cessna

Aircraft

Company

Cessna

A

Textron

Company

TEMPORARY

REVISION

NUMBER

4

DATE

7

October

2002

MANUAL

TITLE

Model

177

Series

1968

Thru

1978

Service

Manual

MANUAL

NUMBER

-

PAPER

COPY

D841-8-13

MANUAL

NUMBER

-

AEROFICHE

D841-8-13AF

TEMPORARY REVISION

NUMBER

D841-8TR4

MANUAL

DATE

1

July

1970

REVISION

NUMBER

8

DATE

2

October

1995

This

Temporary

Revision

consists

of

the

following

pages, which

affect

and

replace

existing

pages

in

the

paper

copy

manual

and

supersede aerofiche

information.

AEROFICHE

SECTION

PAGE

FICHE/FRAME

SECTION

PAGE FICHE/FRAME

2

21

1/B17

2

22A/Deleted

NA

2

24A

Added

2

25

Added

2

26 Added

2

27

Added

15

22A

2/B7

15

22B

2/B8

15

22C

Added

REASON

FOR

TEMPORARY

REVISION

1.

To Add

A

Component

Time

Limits

Section

And

A

Fuel

Quantity

Indicating

System Operational

Test.

FILING

INSTRUCTIONS

FOR

THIS

TEMPORARY

REVISION

1.

For

Paper

Publications,

file

this

cover

sheet

behind

the

publication's

title

page

to

identify

the

inclusion

of

the

Temporary Revision

into

the

manual.

Insert

the

new pages

into

the

publication

at

the

appropriate

locations

and

remove

and

discard

the

superseded

pages.

2.

For

Aerofiche

Publications,

draw

a

line

with

permanent

red

ink

marker,

through

any

aerofiche

frame

(page)

affected

by

the

Temporary

Revision.

This

will

be

a

visual

identifier

that

the

information

on

the

frame

(page)

is

no

longer

valid

and

the

Temporary

Revision

should

be

referenced.

For

"added"

pages

in

a

Temporary

Revision,

draw

a

vertical

line

between

the

applicable

frames.

Line

should

be

wide

enough

to

show

on

the

edges

of

the

pages.

Temporary

Revisions

should

be

collected

and

maintained

in

a

notebook

or

binder

near

the

aerofiche

library

for

quick

reference.

COPYRIGHT

©

2002

CESSNA AIRCRAFT

COMPANY

WICHITA, KANSAS,

USA

TEMPORARY

REVISION

NUMBER

3

DATED

7

January

2000

MANUAL

TITLE

MODEL

177

SERIES

1968

THRU

1978

SERVICE

MANUAL

NUMBER

-

PAPER

COPY

D841-8-13

AEROFICHE

D841-8-13AF

TEMPORARY

REVISION

NUMBER

PAPER

COPY

D841-8TR3

AEROFICHE

N/A

MANUAL

DATE

1

JULY

1970

REVISION

NUMBER

8

DATE

2

OCTOBER

1995

This Temporary

Revision

consists

of

the

following

pages,

which

affect

existing

pages

in

the

paper

copy

manual

and

supersede

aerofiche

information.

AEROFICHE

SECTION

PAGE

FICHE/FRAME

SECTION

PAGE

FICHE/FRAME

2

22A

Added

2

24A

Added

REASON

FOR

TEMPORARY

REVISION

To

include

the

inspection

requirements

of

Cessna

Service

Bulletin

SEB99-18.

FILING

INSTRUCTIONS

FOR

THIS

TEMPORARY

REVISION

For

Paper

Publications:

File

this

cover

sheet

behind

the

publication's

title

page

to

identify

the

inclusion

of

the

Temporary

Revision

into the

manual.

Insert

the

new

pages

into

the

publication

at

the

appropriate

locations.

Draw

a

line,

with

a

permanent

red

ink

marker,

through

any

superceded

information.

For

Aerofiche

Publications:

Draw

a

line

through

any aerofiche

frame

(page)

affected

by

the

Temporary

Revision

with

a

permanent

red

ink

marker.

This

will

be

a

visual

identifier

that the

information

on

the

frame

(page)

is no

longer

valid

and

the

Temporary

Revision

should

be

referenced.

For

"added"

pages

in

a

Temporary

Revision,

draw

a

vertical

line

between

the

applicable

frames

which

is

wide

enough

to

show

on

the

edges

of the

pages.

Temporary

Revisions

should

be

collected

and

maintained

in

a

notebook

or

binder

near

the

aerofiche

library

for

quick

reference.

COPYRIGHT

2000

CESSNA

AIRCRAFT

COMPANY

WICHITA,

KANSAS,

USA

LIST

OF

EFFECTIVE

PA

P"m

INSERT

LATEST

CHANGED

PAGES.

DESTROY

SUPERSEDED.PAGES

OTE:

The

portion

of

the

text

affected

by

the

changes

is

indicated

by

a

vertical

line

in

the

outer

margine

of

the

page.

Changes

to

illustrations

are

indicated

by

miniture

pointing

hands.

Dates

of

issue

for

original

and

changed

pages

are:

Original

.

0...

1

July

1970

Change..

.5.....

15June

1975

Change

....

1

...

1

July

1971

Change

..

.6

...

1

July

1976

Change

....

2..

1

July

1972

Change

....

7...

1

July

1977

Change

....

3

1

July

1973

Change

....

8

..

2

October

1995

Change

....

4...

1

July

1974

TOTAL

NUMBER

OF

PAGES

IN

THIS

PUBLICATION

IS

434,

CONSISTING

OF

THE

FOLLOWING:

Page

Change

Page

Change

Page

Change

Page

Change

No.

N.

No.

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

8

5-13

thru

5-14

.

6

11-26

.......

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thru

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7

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....

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4-14A

thru

5-14C

....

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11-27

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

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16-2D

Blank

........

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iv.......

8

5-14D

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

6

11-28

...........

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16-3

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.......

7

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

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.......

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.....

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.....

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........

7

Upon

receipt

of

the

second

and

subsequent

changes

to

this

book.

personnel

responsible

for

maintaining

this

publication

in

current

status

should

ascertain

that

all

have

been

received

and

incorporated.

The

asteric

indicates

pages

changed,

added

o.

deleted

by

the

current

change.

A

Change

8

TABLE

OF

CONTENTS

PAGE

NO.

SECTION

Aerofiche/Manual

1.

GENERAL

DESCRIPTION

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

A................

1A8/1-1

2.

GROUND

HANDLING,

SERVICING,

CLEANING,

LUBRICATION

AND

INSPECTION

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

1A17/2-1

3.

FUSELAGE

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

1C2/3-1

4.

WINGS

AND

EMPENNAGE

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

1D4/4-1

5.

LANDING

GEAR,

WHEELS

AND

BRAKES

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

1D15/5-1

6.

AILERON

CONTROL

SYSTEM

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

1F4/6-1

7.

WING

FLAP

CONTROL

SYSTEM

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

1F18/7-1

8.

STABILATOR

CONTROL

SYSTEM

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

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

.

1G9/8-1

9.

STABILATOR

TRIM

CONTROL

SYSTEM

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

1G21/9-1

10.

RUDDER

CONTROL

SYSTEM

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

lHll/10-1

11.

EN

G

IN

E

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

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

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

112/11-1

12.

FUEL

SYSTEM

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

. . .

1

17/12-1

13.

PROPELLER

AND

GOVERNOR

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

1K19/13-1

14.

UTILITY

SYSTEMS

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

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

1L9/14-1

15.

INSTRUMENT

AND

INSTRUMENT

SYSTEMS

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

2A2/15-1

16.

ELECTRICAL

SYSTEMS

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

...

2B15/16-1

18.

STRUCTURAL

REPAIR

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

.

2E5/18-1

19.

PAINTING

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

.

....

2F17/19-1

20.

W

IRING

DIAGRAMS

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

2G1/20-1

Change

8

CROSS

REFERENCE

LISTING

OF

POPULAR

NAME

VS.

MODEL

NUMBERS

AND

SERIALS

All

aircraft,

regardless

of

manufacturer,

are

certificated

under

model

number

desiginations.

However,

popular

names

are

often

used

for

market-

ing

purposes.

To

provide

a

consistent

method

of

referring

to

these

air-

craft,

the

model

number

will

be

used

in

this

publication

unless

the

popular

name

is

necessary

to

differentiate

between

versions

of

the

same

basic

model.

The

following

table

provides

a

listing

of

popular

name,

model

number,

and serial

number.

MODEL

SERIALS

POPULAR

NAME

M

ODEL

POPULAR

NAME

YEAR

MODEL

BEGINNING

ENDING

177

or

CARDINAL

1968

177

17700001

17701164

177A

or CARDINAL

1969

177A

17701165

17701370

177B

or

CARDINAL

1970

177B

17701371

17701530

177B

or

CARDINAL

1971

177B

17701531

17701633

177B

or

CARDINAL

1972 177B

17701634

17701773

177B

or

CARDINAL

1973 177B

17701774

17701973

177B

or

CARDINAL

1974

177B

17701974

17702203

177B,

CARDINAL

1975

177B

17702204

17702313

and

CARDINAL

II

CARDINAL

or

1976

177B

17702314

17702522

CARDINAL

II

1977

177B

17702523

17702672

CARDINAL CLASSIC

1978

177B

17702673

17702752

Change

8

INTRODUCTION

This manual contains

factory-recommended

procedures

and

instructions

for

ground

handling,

servicing,

and

maintaining

Cessna

Model

177

-Series

aircraft.

Besides

serving

as

a

reference

for

the

experienced

mechanic,

this

book

also covers

step-by-step

procedures

for

the

less

experienced.

If

properly

used,

it

will

better

enable

the

mechanic

to

maintain

the aircraft

and

thereby

establish

a

reputation

for

reliable

service.

Information

for

Nav-O-Matic

Autopilots,

Electronic

Communications,

and

Navigation

Equipment

are

not

included

in

this

manual

These

manuals

are

available

from

Cessna

Parts

Distribution

(CPD

2)..

AEROFICHE

This

service

manual

is

designed

for

aerofiche

presentation.

To

facilitate

the

use

of

the

aerofiche,

refer

to

the

aerofiche

header

for

basic

information.

KEEPING

CESSNA PUBLICATIONS

CURRENT

The

information

in

this

publication

is

based

on

data

available

at

the

time

of

publication

and

is

updated, supplemented,

and

automatically

amended

by

all

information

issued

in

Service

News

Letters,

Service

Bulletins,

Supplier

Service

Notices,

Publication

Changes,

Revisions,

Reissues

and

Temporary

Revisions.

All

such

amendments

become

part

of

and

are

specifically

incorporated

within this

publication.

Users

are

urged

to

keep

abreast

of

the

latest

amendments

to

this

publication

through

information

available

at

Cessna

Authorized

Service

Stations

or

through

the

Cessna

Product Support

subscription

which

provide

disassembly,

overhaul, and

parts

breakdowns

for

some

of

the

various

suppliers

equipment

items.

Suppliers

publications

are

updated,

supplemented,

and

specifically

amended

by

supplier

issued

revisions and

service

information which

may

be

reissued

by

Cessna;

thereby

automatically

amending

this

publication

and

is

communicated

to

the

field

through

Cessna

Authorized

Service

Stations

and/or

Cessna

subscription

service.

WARNING

ALL

INSPECTION

INTERVALS,

REPLACEMENT

TIME

LIMITS,

OVERHAUL TIME LIMITS,

THE

METHOD

OF

INSPECTION,

LIFE

LIMITS,

CYCLE

LIMITS,

ETC.,

RECOMMENDED

BY

CESSNA

ARE

SOLELY

BASED

ON

THE

USE

OF

NEW,

REMANUFACTURED,

OR

OVERHAULED

CESSNA

APPROVED

PARTS.

IF PARTS

ARE

DESIGNED,

MANUFACTURED,

REMANUFACTURED,

OVERHAULED,PURCHASED,

AND/OR

APPROVED

BY

ENTITIES

OTHER

THAN

CESSNA,

THEN

THE

DATA

IN

CESSNAS

MAINTENANCE/SERVICE

MANUALS

NO

LONGER

APPLICABLE

AND

THE

PURCHASER

IS

WARNED

NOT

TO

RELY

ON

SUCH

DATA

FOR

NON-CESSNA

PARTS.

ALL

INSPECTION

INTERVALS

REPLACEMENT

TIME

LIMITS,

OVERHAUL

TIME

LIMITS, THE

METHOD

OF

INSPECTION,

LIFE

LIMITS,

CYCLE

LIMITS,

ETC.,

FOR

SUCH

NON-CESSNA

PARTS

MUST

BE

OBTAINED

FROM

THE

MANUFACTURER

AND/OR

SELLER OF

SUCH NON-CESSNA

PARTS.

REVISIONS/CHANGES

These

are

issued

to

the

dealers

by

Cessna

Aircraft

Company

for

this

publication

as

required,

and

include

only

pages

that

require

updating.

REISSUE.

Manual

is

reissued

to

dealers

as

required,

and is

a

complete

manual

incorporating

all

the

latest

information

and

outstanding

revisionsichanges.

It

supersedes

and

replaces

REVISIONS, CHANGES

and

REISSUES

can

be

purchased

from

your

Cessna

Dealer

or

directly

from

the

Cessna

Parts

Distribution,

(CPD

2)

Dept

701,

Cessna

Aircraft

Company,

5800

East

Pawnee,

Wichita,

Kansas

67201.

Change

8

iii

All

supplemental

service

information

concerning this

manual

is

supplied

to

all

Cessna

Dealers

so

that

they

have

the

latest authoritative

recommendations

for

servicing

these

Cessna

aircraft.

Therefore,

it

is

recommended

that

Cessna

owners

utilize

the

knowledge

and

experience

of

the

factory-trained

Dealer

Service

Organization.

CUSTOMER

CARE

SUPPLIES

AND

PUBLICATIONS

CATALOG

A

Customer

Care

Supplies

and

Publications

Catalog

is

available

from

your

Cessna

Dealer

or

directly

from

the

Cessna

Parts

Distribution,

(CPD

2),

Dept.

701,

Cessna

Aircraft

Company,

5800

East

Pawnee,

Wichita

Kansas

67201.

The

Supplies

and

Publications

catalog

lists

all

publications

and

Customer

Care

Supplies

available

from

Cessna

for

prior

year

models

as

well

as

new

products.

SUPPLEMENTAL

TYPE

CERTIFICATE

INSTALLATIONS

Inspection,

maintenance

and

parts

required

for (STC)

installations

are

not

included

in

this

manual.

When

an

STC

installation

is

incorporated

on

the

aircraft,those

portions

of

the

aircraft

affected

by

the

installation

must

be

inspected

in

accordance

with

the

inspection

program

published

by

the

owner

of

he

STC.

Since

STC

installations

may

change

systems

interface,

operating

characteristics

and

component

loads

or

stress

on

adjacent

structures.

Cessna

provided

inspection

criteria

may

not

be

valid

for

aircraft

with

STC

installations.

CUSTOMER COMMENTS

ON

MANUAL

Cessna

Aircraft

Company

has

endeavored

to

furnish

you

with

an

accurate,

useful,

up-to-date

manual.

This

manual

can

be

improved

with

your

help.

Please

use

the

return

card,

provided

with

your

manual,

to

report

any errors,

discrepancies,

and omissions

in this

manual

as

well

as

any

general

comments

you

wish

to

make.

iv

Change

8

SECTION

1

GENERAL DESCRIPTION

Page

No.

TABLE

OF

CONTENTS

Aerofiche/Manual

GENERAL

DESCRIPTION

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

1A8,1-1

Aircraft

Specifications

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

1A8/1-1

Model

177

and

"Cardinal"

Series

.......

1A8/1-1

Stations

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

1A8/1-1

Description

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

1A8/1-1

Torque

Values

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

1A8/1-1

1-1.

GENERAL

DESCRIPTION.

pitch

or

constant-speed

propellers.

1-2

MODEL

177

AND

"CARDINAL"

SERIES.

1-4.

AIRCRAFT

SPECIFICATIONS.

Leading

partic-

ulars

of

these

aircraft,

with

dimensions

based

on

1-3

DESCRIPTION.

The

Cessna

Models

177

and

gross

weight,

are

given

in

figure

1-1.

If

these

di-

"Cardinal"

Series

aircraft

described

in

this manual,

mensions

are

used

for

constructing

a

hangar

or

com-

are

single-engine,

high-wing

monoplanes

of

all-metal,

puting

clearances,

remember

that

such

factors

as

semimonocoque

construction.

Wings

are

full

canti-

nose

gear

strut

inflation,

tire

pressures,

tire

sizes,

lever,

with

a

sealed

section

which

forms

an

integral

and

load

distribution

may

result

in

some

dimensions

fuel

bay

area

in

each

wing.

The

fixed

tricycle

land-

that

are

considerably

different

from

those

listed.

ing

gear

consists

of

tubular

spring-steel

main

gear

struts

and

a

steerable

nose

gear

with

an

air/hydrau-

1-5.

STATIONS.

A

station

diagram

is

shown

in

fig-

lic

fluid

shock

strut.

Standard

four-place

seating

ure

1-2

to

assist

in

locating

equipment

when

a

written

consists

of

two

individual

front

seats

and

one

two/

description

is

inadequate

or

impractical.

place

rear

seat.

A

two-place

child's seat

may

be

in-

stalled,

aft

of

the

rear

seat

as

optional

equipment.

1-6.

TORQUE

VALUES.

A

chart

of

recommended

These

aircraft

feature

a

horizontal

stabilator,

swept-

nut

torque

values

is

shown

in

figure

1-3.

These

tor-

back

fin

and

rudder,

large

entry

doors,

and

rear

and

que values

are

recommended

for

all

installation

pro-

side

windows.

These

aircraft

are

powered

by

four-

cedures

contained

in

this

manual,

except

where

other

cylinder,

horizontally

opposed,

air-cooled,

"Blue

values

are

stipulated.

They

are

not

to

be

used

for

Streak"

(Lycoming)

engines,

driving

all-metal,

fixed-

checking

tightness

of

installed

parts

during

service.

Change

8

1-1

MODEL

177

&

CARDINAL

GROSS

WEIGHT

(1968

Model

177

&

Cardinal)

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

2350

lb

(1969

Model

177A

&

Cardinal

and on)

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

2500

lb

FUEL

CAPACITY

(thru

1969)

(Total)

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

.

49

gal.

(Usable)

..

. .

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

48

gal.

(1970

thru

1972)

(Total)

.

. . .

. .

. . .

. .

. . .

. .

. . .

..

50

gal.

(Usable)

. ...

.

. .

.

. .

.

. .

.

. .

.

. .

49

gal.

(beginning

with

1973)

STANDARD

FUEL

BAYS:

(Total)

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

50

gal.

(Usable).

. . . . . . .

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

. .

49

gal.

OPTIONAL

LONG/RANGE

FUEL

BAYS:

(Total)

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

....

61

gal.

(Usable).

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

60

gal.

NOTE

Fuel

bay

capacities

to

line

of

holes

inside

filler

neck

are

as

follows:

(thru

1969)

. . ..

.

........

. . .

. . . ..

21

gal.

(beginning

with

1970)

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

....

22

gal.

(Deduct

1

gallon

to

obtain

usable

fuel.)

OIL

CAPACITY

(Without

External

Filter).

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

8

qt

(With

External

Filter)

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

9

qt

ENGINE

MODEL

(Refer

to

Section

11

for

Engine

Data)

(1968

Model

177

&

Cardinal)

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

LYCOMING

0-320

Series

(1969

Model

177A

&

Cardinal

and

on)

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

LYCOMING

0-360

Series

PROPELLER

(1968

and

1969

Models

177, 177A

&

Cardinals).........

76"

McCauley

(Fixed

Pitch)

(1970

Model

177B

&

Cardinal

and

on)

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

76"

McCauley

(Constant

Speed)

MAIN

WHEEL

TIRES

(1968

Models)

..

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

.

6.00x6,

4-ply

rating

(1969

and

on)

.

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

6.00x6,

6-ply

rating

Pressure

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

30

psi

NOSE

WHEEL

TIRE

(Standard)

.........

5.00x5,

4-ply

rating

Pressure

(Serial

17700001

thru

1700854)

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

.

30

psi

(Serial

17700855

and

on)

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

35

psi

NOSE

WHEEL

TIRE

(Optional)

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

6.00x6,

4-ply

rating

Pressure

(Thru

Serial

17701164)

.......

.

30

psi

NOSE

GEAR

STRUT

PRESSURE

(Strut

Extended)

(Serial

17700001

thru

17700854)

.........

....

50

psi

(Serial

17700855

and

on)..

... . ...

... ... ...

40

psi

WHEEL

ALIGNMENT

(Measured

with

aircraft

empty)

Camber

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

3

°

to 5

°

Toe-in

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

0"

to

.06"

Figure

1-1.

Aircraft

Specifications

(Sheet

1

of

2)

1-2

Change

7

AILERON

TRAVEL

Up

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

20

°

±

2

°

Down

.

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

15

°

±

2

WING

FLAP

TRAVEL

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

0

°

to

30

°

, +2

°

-0

°

RUDDER

TRAVEL

(Measured

parallel

to

waterline)

Right

..

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

21 45'

1

Left

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

.

21

°

45'

±

1

°

RUDDER

TRAVEL

(Measured

perpendicular

to

hinge

line)

Right

..

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

24

±

1

Left

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

24°

±

1

°

STABILATOR

TRAVEL

Up

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

20

°

±

1

Down

.

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

. ... 5

°

±

1

°

STABILATOR

TRIM

TAB

TRAVEL

(Serial

17700001

thru

17701164)

Up

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

2

±

1

°

Down

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

7

°

±

1

°

(Serial

17701165

thru

17701370)

Up

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

. 6

°

,

+2

-0

°

Down

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

12,

+0

-2

(Serial

17701371

and

on)

Up

.......................... 5

±

1

°

Down

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

13

°

±

1

°

PRINCIPAL

DIMENSIONS

Wing

Span

(Conventional

Wing

Tip)

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

35'

7-1/2"

Wing

Span

(Conical-Camber

Wing

Tip)

...

.......

.

35'

6"

Wing

Span

(Conical-Camber

with

Strobe

Lights)

.......

35'

8"

Tail

Span

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

11'

10"

Length

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

.

27'

3"

Fin

Height

(Maximum

with

Nose

Gear

Depressed

and

Flashing

Beacon

Installed

on

Fin)

......

8'

7"

Track

Width

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

8'

3-1/2"

BATTERY

LOCATION

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

Aft

of

Baggage

Area

Figure

1-1.

Aircraft

Specifications

(Sheet

2

of

2)

Change

3

1-3

25.25

40.

00*

54.00

68.08

00

^^^82.

0017200

"^

^^^

1896.00

110.

00

124.

00*

136.

50

138.

00

e

155.

00

17

2.

00'

189.00

206.00'

*

The

asterisked

stations

are trailing

edge

stations,

THRU

1970

MODELS

which

are

canted

outboard.

The

remainder

of

the

stations,

as

well

as

the

stations

forward

of

the

main

spar

corresponding

to

the

asterisked

trailing

edge

stations,

are

perpendicular

to

the

leading

edge.

123.53

147.54

/

[\

59.00

123

|

164.53

/ /

,

t.~,

'

23so

263.00

-

r

\ 7

87.75

/

77

-

155.50

277.00

-54.00J

68.66

100.00

132.00

\

175.50

64.90

111.75

140.50

*BEGINNING

WITH

17701371

Figure

1-2.

Reference

Stations

1-4

Change

7

RECOMMENDED

NUT

TORQUES

THE

TORQUE

VALUES

STATED

ARE

POUND-INCHES,

TO

STEEL

NUTS

ON

OIL-FREE

CADMIUM

PLATED

THREADS.

FINE

THREAD

SERIES

TENSION

SHEAR

TAP

SIZE

TORQUE

STD

ALT STD

ALT

(NOTE

1)

(NOTE

2)

(NOTE

3)

(NOTE

2)

8-36

12-15

7-9

10-32

20-25

20-28

12-15

12-19

1/4-28

50-70

50-75

30-40

30-48

5/16-24

100-140

100-150

60-85

60-106

3/8-24

160-190

160-260

95-110 95-170

7/16-20

450-500

450-560

270-300

270-390

1/2-20

480-690

480-730

290-410

290-500

9/16-18

800-1000

800-1070

480-600

480-750

5/8-18

1100-1300

1100-1600

660-780

660-1060

3/4-16

2300-2500 2300-3350

1300-1500

1300-2200

7/8-14

2500-3000 2500-4650

1500-1800

1500-2900

1-14

3700-5500

3700-6650

2200-3300

2200-4400

1-1/8-12

5000-7000 5000-10000

3000-4200

3000-6300

1-1/4-12

9000-11000

9000-16700

5400-6600

5400-10000

COARSE

THREAD

SERIES

(NOTE

4)

(NOTE

5)

8-32

12-15

7-9

10-24

20-25

12-15

1/4-20

40-50

25-30

5/16-18

80-90

48-55

3/8-16

160-185

95-100

7/16-14

235-255

140-155

1/2-13

400-480

240-290

9/16-12

500-700

300-420

5/8-11

700-900

420-540

3/4-10

1150-1600

700-950

7/8-9

2200-3000

1300-1800

1-8

3700-5000

2200-3000

1-1/8-8

5500-6500

3300-4000

1-1/4-8

6500-8000

4000-5000

NOTES

1.

Covers

AN310,

AN315,

AN345, AN363,

MS20365,

MS21042,

MS21044,

MS21045

and

MS21046.

2.

When

using

AN310

or

AN320

castellated

nuts

where

alignment

between

the

bolt

and

cotter

slots

is

not

reached

using

normal

torque

values,

use

alternate

torque

values

or

replace

the

nut.

3.

Covers

AN316,

AN320,

MS20364

and

MS21245.

4.

Covers

AN363,

MS20365,

MS21042,

MS21043,

MS21044,

MS21045

and

MS21046.

5.

Covers

AN340.

CAUTION

DO

NOT

REUSE

SELF-LOCKING

NUTS.

The

above

values

are

recommended

for all

installation

procedures

contained

in

this

manual, except

where

other

values

are

stipulated.

They

are

not

to be

used for

checking

tightness

of

installed

parts

during

service.

Figure

1-3.

Torque

Values

Change

4

1-5/(1-6

blank)

SECTION

2

GROUND

HANDLING,

SERVICING,

CLEANING,

LUBRICATION

AND

INSPECTION

Page

No.

TABLE

OF

CONTENTS

Aerofiche/Manual

GROUND

HANDLING

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

A17/2-1

Tires

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

1B1/2-8

Towing

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

.....

1A17/2-1

Nose

GearShock

Strut

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

B1/2-8

Hoisting

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

1A20/2-3

Nose

GearShimmy

Dampener

.........

1B2/2-9

Jacking

...

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

1A20/2-3

Hydraulic

Brake

Systems

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

1B2/2-9

Leveling

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

1A20/2-3

CLEANIN

G

.........

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

...

1B2/2-9

Parking

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

1A20/2-3

W

indshield

and

Windows

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

1B2/2-9

Tie-Down

.....

........

.......

..

1A20/2-3

Required

Materials.

...........

1B2/2-9

Flyable

Storage

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

1A20/2-3

Cleaning

Instructions

..........

1B3/2-10

Returning

Aircraft

to

Storage

.........

1A20/2-3

Windshield

and

Window

Temporary

Storage

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

1A20/2-3

Preventive

Maintenance........

1B3/2-10

Inspection

During

Storage

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

1A21/2-4

Interior

Trim

.

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

1B4/2-10A

Returning

Aircraft

to

Service

.........

1A21/2-4

Painted

Surfaces.

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

1B4/2-10A

Indefinite

Storage

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

1A21/2-4

Aluminum

Surfaces

.

...........

1B4/2-10A

Inspection

During

Storage

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

1A22/2-5

Engine

and

Engine

Compartment

....

1B4/2-10A

Returning

Aircraft

to

Service

.........

1A22/2-5

Upholstery

and

Interior

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

1B5/2-10B

SERVICING

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

1A23/2-6

Propeller

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

1B5/2-10B

Fuel

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

..

1......

A23/2-6

Wheels

.

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

1B5/2-10B

Fuel

Drains

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

A23/2-6

LUBRICATION

.

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

1B5/2-10B

Carburetor

Drain

Plug

Inspection

....

1A23/2-6

Tachometer

Drive

Shaft

.

.........

B5/2-10B

Engine

Oil

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

1A23/2-6

W

heel

Bearings

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

1B5/2-10B

Induction

Air

Filter

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

1A24'2-7

Aileron

Rod

End

Bearings

...........

1B5/2-10B

Vacuum

System

Filter

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

1B1/2-8

Wing

Flap

Actuator

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

1B5/2-10B

Battery

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

B1/2-8

INSPECTION

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

1B13/2-17

2-1.

GROUND

HANDLING.

CAUTION

2-2.

TOWING.

Moving

the

aircraft

by

hand

is

ac-

When towing

the

aircraft,

do

NOT

turn

the

complished

by

pushing

on

the

landing

gear

struts.

A

nose

wheel

more

than

45

degrees

either

tow

bar,

illustrated

in

figure

2-1,

should

be

attached

side

of

center,

or

the

nose

gear

will

be

to

the

nose

gear

to

be

used

for

steering

and

maneuver-

damaged.

Do

not

push

on

control surfaces

ing

the

aircraft.

When

no

tow

bar

is

available,

press

or

outboard

empennage

surfaces.

When

down

the

tailcone

bulkhead,

just

forward

of

stabilizor,

puhing

on

tailcone, always

apply

pressure

to

raise

nose

wheel

off

the

ground.

With

the

nose

at

a

blkhead

to

avoid

buckling

the

skin.

wheel

clear

of

the ground,

the

aircraft

can

be

turned

by

pivoting

about

the

main

wheels.

Change

8

2-1

ITEM

NUMBER

TYPE

AND

PART-NUMBER

REMARKS

Block

(Jack

point

not

available)

1X4X4

padded

with

1/4"

rubber

Jack

Any

short

jack

of

capable

capacity

Cessna

#SE-767

Universal

tail

stand

(SEE

NOTE

1)

Cessna

#SE-576

(41-1/2"

high)

Universal

jack

stand

(FOR

USE

WITH

ITEM

2)

Cessna

#1700129-1

Jack

pad

(SEE

NOTE

2)

#2-170

Basic

jack

(includes

#2-71

Min.

closed

height:

34"

Slide

tube:

Liftstroke

22-1/2")

Max.

extension

height:

56-1/2"

#2-70

Slide

tube:

Liftstroke

Min.

closed

height:

57-1/2'

22-1/2"

Max.

extension

height:

80"

#2-64

Extension

cap

Adds

4"

#2-109

Leg

extension

Adds

12"

Figure

2-2.

Jacking

and

Leveling

(Sheet

1

of

2)

2-2

Change

6

NOTES

1

Weighted

adjustable

stand

attaches

to

tie-down ring.

Wing

jack

points

are

aft

of

the

aircraft

center-of-gravity.

This

causes

the

aircraft

to

be

nose-

heavy

when

on

jacks.

Place

additional

weights

(shot

bags

or

sand

bags)

on

the

weighted

tail

stand

to

hold

the

tail

down.

In

addition,

the

base

of

adjustable

stand

(SE-767)

is

to

be

filled

with

concrete

for

additional

weight

as

a

safety

factor.

2

On

tubular

gear

aircraft,

the

only

fairing

that

requires

removal

is

the

one

common

to

the

fuselage

and

the

tube

gear

fairing.

This

requires

the

removal

of

(7)

screws.

The

jack

pad

is

then

inserted

on

the

tube

in

the

area

between

the

fuselage

and

the

upper

end

of

the

tube

fairing,

then

jack

the

aircraft

as

re-

quired.

The

jack

pad

may

be

used

only

to

raise

one

main

wheel.

Do

not

use

brake

castings

as

jack

points.

3.

Items

(3), (4),

(5)

and

(6)

are

available

from

the

Cessna

Service

Parts

Center.

JACKING

INFORMATION

1.

Place

wing

jack under

main

spar

of

the

wing

just

outboard

of

main

wheel.

Pad

at top

of,

jack

should

be

placed

at

junction

of

main

wing

spar

and

wing

rib.

2.

Raise

aircraft

tail

and

attach

tail

stand

to

tie-down

fitting.

BE

SURE

the

tail

stand

weighs

enough to

keep

the

tail

down

under

all

conditions

and

that

it

is

strong

enough to

support

any

weight

that

may

be

placed

upon

it.

3.

Operate

jacks

evenly

until

desired

height

is

reached.

4.

The

individual

strut

jack

pad

may

be

used

to

raise

only

one

main

wheel

at

a

time.

Dis-

connect

strut-to-fuselage

fairing

to

attach

strut

jack

pad

to

strut.

DO NOT

use

brake

casting

as

a

jack

point.

5.

The

nose

may

be

raised

by

lowering

and

tying

down

the

tail.

6.

The

aircraft

may

be

hoisted

as

outlined

in

paragraph

2-3.

LEVELING

THE

AIRCRAFT

Longitudinal

leveling

of

the

aircraft

is

accomplished

by

removing

the

two

screws

in

the

tailcone

(shown

in

figure

2-2

at

"A")

and

installing bolts

in

the

jig-located

nutplates,

then

placing

a

level

across

the

bolts.

Also

refer

to

paragraph 2-5.

A

level

placed

across

the

front

seat

rails

at

corresponding

points

is

used

to

level

the

aircraft

laterally.

SHOP

NOTES:

Figure

2-2. Jacking

and

Leveling

(Sheet

2

of

2)

Change

6

2-2A/(2-2B blank)

2-3.

HOISTING.

The

aircraft

may

be

lifted

with

a

e.

These

aircraft

are

equipped

with

a

spring-loaded

hoist

of

two-ton

capacity

by

using

hoisting

rings

steering

bungee

which

affords

protection

against

nor-

which

are

optional

equipment,

or

by

means

of

suit-

mal wind

gusts.

However,

if

extremely

high

wind

able

slings.

The

front

sling

should

be

hooked

to

each

gusts

are

anticipated,

additional

external

locks

may

upper

engine

mount

at

the

firewall,

and

the

aft

sling

be

installed.

should

be

positioned

around

the

tailcone at

the

first

bulkhead

forward

of

the

leading

edge

of

the

stabilator.

2-8.

FLYABLE

STORAGE.

Flyable

storage

is

de-

If

the

hoisting

rings

are

used,

a

minimum

cable

lenght

fined

as

a

maximum

of

30

days

non-operational

stor-

of

60-inches

for

each

cable

is

required

to

prevent

age

and/or

the

first

25

hours

of

intermittent

engine

bending

of

the

eyebolt

type

hoisting

rings.

If

desired,

operation.

a

spreader

jig

may

be

fabricated

to apply

vertical

force

to

the

eyebolts.

NOTE

2-4.

JACKING.

Refer

to

figure

2-2

for

jacking

The

aircraft

is

delivered

from

Cessna

with

procedures.

a

corrosion

preventative

aircraft

engine oil

CAUTION

(MIL-C-6529,

Type

II).

This

engine

oil

is

a

blend

of

aviation

grade

straight

mineral

When

using

the

individual

jack

pad,

flexibility

oil

and

a

corrosion

preventative

compound.

of

the

gear

strut

will

cause

the

main

wheel

toThis

engine

oil

should

be

used

for

the

first

slide

inboard

as

the

wheel

is

raised,

tilting

25

hours

of

engine

operation.

In

the event

the

jack.

The

jack

must

then

be

lowered

for

it

is

necessary

to

add

oil

during

the

first

25

a

second

jacking

operation.

Jacking

both

hours

of

operation.

use

only

aviation

grade

wheels

simultaneously

with

individual

jack

straight

mineral

oil

of

the

correct

viscosity.

pads

is

not

recommended.

During

the

30

day

non-operational

storage

or

the

first

2-5.

LEVELING.

(Refer

to

figure

2-2.

)

Longitudinal

25

hours

of

intermittent

engine

operation,

every

sev-

leveling

of

the

aircraft

is

accomplished

by

removing

enth

day,

the

propeller

shall

be

rotated

through

five

screws

at

stations

213.0

and

238.0

(on

the

tailcone)

revolutions,

without

running

the

engine.

If

the

air-

and

installing

bolts

in

the

jig-located

nutplates;

then

craft

is

stored

outside,

tie

down

in

accordance

with

placing

a

level

across

the

bolts.

Raise,

or

lower,

paragraph

2-7.

In

addition,

the

pitot

tube,

static

air

the

nose

as required

to

center

the

bubble

in

the

level.

vents,

air

vents,

openings

in

the

engine

cowling

and

A

level placed

across

the

front

seat

rails

at

corres-

other

similar

openings

shall

have

protective

covers

ponding

points

is

used

to

level

the

aircraft

laterally.

installed

to

prevent

entry

of

foreign

material.

After

30

days,

aircraft

should

be

flown

for

30

minutes

or

2-6.

PARKING.

Parking

precautions

depend

prin-

ground

run-up

until

oil

has

re-ched operating

temper-

cipally

on

local

conditions.

As

a

general

precaution,

ature.

set

parking

brakes

or

chock

the

wheels

and

installthe

controls

lock.

In

severe

weather

and

high

wind

con-

CAUTION

ditions,

tie-down

the

aircraft

as

outlined

in

paragraph

2-7

if

a

hangar

is

not

available.

Excessive

ground

operation

shall

be

avoided.

2-9.

RETURNING

AIRCRAFT

TO

SERVICE.

After

2-7.

TIE-DOWN.

When

mooring

the

aircraft

in

the

flyable

storage,

returning

the

aircraft

to

service

is

open,

head

into

the

wind

if

possible.

Secure

control

accomplished

by

performing

a

thorough

pre-flight

in-

surfaces

with

the

internal

control

lock

and

set

brakes.

spection.

At

the

end

of

the

first

25

hours

of

engine.

operation,

drain

engine

oil

and

clean

oil

pressure

.C;AUTION

screen

(or

change

external

oil

filter

element).

Ser-

vice

engine

with

correct

grade

and

quantity

of

engine

Do

not

set

parking

brakes

during

cold

weather

oil.

Refer

to

figure

2-3

and

paragraph

2-21

for

cor-

when

accumulated

moisture

may

freeze

the

rect

grade

of

engine

oil.

brakes

or

when

the

brakes

are

overheated.

2-10.

TEMPORARY

STORAGE.

Temporary

storage

Moor

the

aircraft

in

accordance

with

the

following

is

defined

as

aircraft

in

a

non-operational

status

for

procedures.

a

maximum

of

90

days.

The

aircraft

is

constructed

a.

Tie

ropes,

cables,

or

chains

to

the

wing

tie-

of

corrosion

resistant

alclad

aluminum,

which

will

down

fittings

located

under

each

wing.

Secure

the

last

indefinitely

under

normal

conditions

if

kept

clean,

opposite

ends

of

ropes,

cables,

or

chains

to

ground

however,

these

alloys

are

subject

to oxidation.

The

anchors.

first

indication

of

corrosion

on

unpainted

surfaces

is

b.

Secure

a

tie-down

rope

(no

chains

or

cables)

to in

the

form

of

white

deposits

or

spots.

On

painted

the

exposed

portion

of

the

engine

mount

and

secure

surfaces,

the

paint

is

discolored

or

blistered.

Stor-

opposite

end

of

rope

to

a

ground

anchor.

age

in

a

dry

hangar

is

essential

to

good

preservation,

c.

Secure

the

middle

of

a

rope

to

the

tail

tie-down

and

should

be

procured

if

possible.

Varying

condi-

ring.

Pull

each

end

of

rope

away

at

a

45

degree

angle

tions

will

alter

the

measures

of

preservation,

but

and

secure

to

ground

anchors

at

each

side

of

tail.

under

normal

conditions

in a

dry

hangar,

and

for

stor-

d.

Secure

control

lock

on

pilot

control

column.

If

age

periods

not

to

exceed

90

days,

the

following

meth-

control

lock

is

not

available,

tie

pilot

control

wheel

ods

of

treatment

are

suggested.

back

with

the

front

seat

belt.

a.

Fill

fuel

bays

with

correct

grade

of

gasoline.

Change

6

2-3

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