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
2
2
2
22
26
27
28
AEROFICHE
SECTION
PAGE FICHE/FRAME
1/B18
Added
Added
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
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into the
publication
at
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2.
For Aerofiche Publications,
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Revision, draw
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Revisions should
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ina
notebook
or binder
near
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library
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3. For
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mark the
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revision
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© Cessna
Aircraft Company

A Textro Company
TEMPORARY
REVISION NUMBER
5
DATED 11 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
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
ina Temporary Revision,
draw a vertical
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frames. Line should
be wide enough to
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of the pages. Temporary
Revisions
should be collected
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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
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that the temporary
revision must
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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 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)
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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
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
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
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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
thetext
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.
No.
No.
No.
No.
No.
N.
No.
*Title
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6
11-26
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thru
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thru
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7
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.............. 6
16-2D
Blank
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*i
thru
iv.......
8
5-14D
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*1-1
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thru
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6
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.6
16-5
.. ru
167......
8
1-2
.
.7
5-17
................ 1
11-28B
Blank
....... 6
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..
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16-9thru
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thru5-20
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thru
16-12D
7
1-5
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4
5-21
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12-1.
....
7
16-13
.............
1-6 Blank
......
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thru
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8
12-2
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5
16-14.
.8
*2-1
........... 8
6-1
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12-3
thru
12-5
.......
7
16-15
..............
3
2-2thr
...............
.
6-
................
12-A
thru
4
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.
......
2-2B
Blank
..
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6
6-3
................
7
12-5
.............. 8 16-16A
. ............
2-
2
thru
2-6
....... 6 6- .............. 1
12-5Chru125
.........
7
16-16B
Ban
.7
2-7..........8 6-5......
.3
126thru
12-7
......
7
16-17
.
...........
6
2-8
..
.0
6-6 thru
6-8
......... 1
12-
thru2-9
....... 1
16-18.
.4
*2-9thru2-10
.......
8
7-1
.........
7
12-10thrul2-11
0 16-18A
.
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4
"2-10A
thru
2-10
...
8
7-2
..............
1
12-12
.
5
16-18B
Blank..
4
2-11
thru
2-12
.
.....
6
-
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1213
16-19
thru
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....
2-12A
.
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5
7-4
thru
7-5
.......
7
12-14
6
16-22...
.3
2-12B
Blank.......
5
7-6
.........
5
12-15tru12-16
....
16-22
thru
16-22B
::
7
2-13
..
7..
7-7
thru7-9
.........
3
13-17
16-23
..
2-14
.....
.4
7-10
Blank
.........
3
13-2
.
4 ............. 46
2-15
............
.
.................
13-3
..
............ 6
16-25
2-16
.
........
5
8-2
............... 2
13-4
thru
135
.......
2
16-26B
Bl.......
4
2-17
..
.....
6
-3 .................
7
13-6
.............. 6
16-26A.
.
5
2-18
.
.3
8-4
thru8-6..........
5
13-7
thru3-8
.......
7
16-26BBlank
.......
5
2-19
.
.............
7..... thru
-
......
... .
7
16-2
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.3...... 3
14-2thru4
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2
16-28thru..-29....
3
21
8
9-3
........
5 ........... 1
16-30
2-
..
2-22.
.4
9-4 .6
...............
7
16-31
..2
'*2-273
1-ru
224.... ....
7
*3-1
..
8
29-6
thru
9-8
............
-
B
n .... 3
16-33
thru
16-34
....
3-2
thru
3-3
.....
0
10-1
.........
7
15-2A
..
5
*1635.
.......
8
3-thru-6
......... 3
10-2
.............
5
1-2BBlnk....
5
16-36
.
.............
5
3-7
.........
5
10-3
thru10-4
......
7
15-3.
...........
4
16-37
thru
16-38
..
7
3-8
................
3
10-5
................
1-4thru
1-7
....
5
1639.
.. 8
3-9....
5
l0-Sthru10-7
.......
1
15-8...............
.
0
16-40
thru
16-44
7....
3-1
Lu
1
.......
2
10-8
.........
2
15-9
................
2
17-1
..........
Deleted
3-125
10-9
.........
*15-10
1..8-1
...........
7
3-13.2
10-10
Blank
.....
5
15-11.
.7
18-2................
0
3-14
..........
8-..
3
11-1
.........
7
15-12
.
......
6
18-3
Ba
.. .1
3-15...............
7
11-2
.........
6.......
15-13
.
..........
2
18-4
..0
3-16
thru
3-20
.......
4
11-3
thru114
.....
1
.
2-42 15-14......6
18-5
thru
18-6..
7
4-1
.................
7
11-5
.......
7 1
5-14A
thru1514D
18-7
.... 0
42-2
.
..........
.....
-
..............
8
18-8
.
............
4-3
.......
7
11-7
thru
11-8
.......
5
15-15A
thru
15-15B
.8
18-9
.............
7. 7
4
.5
11-9.2 15-16.
..
6
18-0thru
18-11
....
0
*51
........
8
11-10...6
15-17
.5
18-12
.
.............
1
5-2
thru5-2A
.....
..
11-11.5
.
-thrl.
2
18-12A
.
............
7
5-2B
Blank
.....
...
6
11-12thrull-13
.....
2
1
5-20
thru
15-22
.
8
18-12B
Blank..
7
5-3.7
11-14.
5
*15-22Athru
1S-22B
8
18-13
thru
18-24
0
5-4
5
11-15.2
15-23
thru
15-23
....
7
18-25.
1
5-5
................
6
11-16
thru
11-17
4....
15-24
.............. 6
18-26
thru
1-29
....
0
5-6
.......
..
7
11-18
..............
3
15-25.2
18-30
Blank
... 0
-6A
thru
5-iD....7 11-19........5 15-26.4
*19-1
thru
195...
8
5-7
thru
5-
.........
7
11-20
.2
27
7
19-6
Blank
........
5-9
thru
5-11
........
6
*11-21.
8
15-28
Blank.....
7
*20-1
thru
.202......
8
5-12.5
11-22
thru
11-25
.
2
*16-1
thru
16-2.
8
20-3thru20-87
.....
7
20-838
Blank
........
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
previous changes
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
previous issue(s).
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,
RELATED
ONLY TO STEEL NUTS ON OIL-FREE CADMIUM PLATED THREADS.
FINE
THREAD SERIES
TENSION
SHEAR
TAP
SIZE
TORQUE
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 pin
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