Cessna 150 Series User manual

MODEL
SERIES
1977
SERVICE
MANUAL
FAA
APPROVAL
HAS BEEN
OBTAINED ON
TECHNICAL
DATA IN
THIS
PUBLICATION
THAT
AFFECTS
AIRPLANE
DESIGN.
CHANGE 1
TO THE BASIC
MANUAL
IS BEING SUPPLIED
TO
PROVIDE
ADDITIONAL
INFORMATION
NECESSARY
TO MAINTAIN
THE
AIRPLANE
AND
INCORPORATES
TEMPORARY
CHANGE
1 AND
TEMPORARY
REVISION
1.
1
JULY
1976
COPYRIGHT
°
1995
CESSNA
AIRCRAFT
COMPANY
WICHITA.
KANSAS.
USA
CHANGE
1
AUGUST
1995
D2011-1-13
(RGI-50-5/01)

Cessna
A Textron
Company
TEMPORARY
REVISION
NUMBER
3
DATE
7 October
2002
MANUAL
TITLE
Model
150 Series
1977
Service
Manual
MANUAL NUMBER
- PAPER COPY D2011-1-13
MANUAL NUMBER
-
AEROFICHE
D2011-1-13AF
TEMPORARY
REVISION
NUMBER
D2011-1TR3
MANUAL
DATE
1 July
1976
REVISION
NUMBER
1
DATE
1 August
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
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PAGE
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PAGE FICHE/FRAME
2
22
1/B11
2
27
Added
2
22A/Deleted
NA
2
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2
23
1/B12
2
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2
25
1/B14
15
16A
1/112
2
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15
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Added
2
26A/Deleted
NA
REASON FOR TEMPORARY
REVISION
1.
To include
the requirement
to
inspect all
fluid carrying
lines and
hoses in
the cabin
and wing areas.
2.
Revise the
Special Inspection
Items
section,
add a Component Time
Limits
section, and
add a fuel
quantity indicating
system operational test.
FILING
INSTRUCTIONS
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THIS TEMPORARY
REVISION
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COPYRIGHT © 2002
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS,
USA

TEMPORARY
REVISION
NUMBER
2
DATED
7 January
2000
MANUAL
TITLE MODEL
150 SERIES
1977
SERVICE
MANUAL
MANUAL
NUMBER
- PAPER
COPY
D2011-1-13
AEROFICHE
D2011-1-13AF
TEMPORARY
REVISION
NUMBER PAPER
COPY
D2011-1TR2
AEROFICHE
N/A
MANUAL
DATE
1
JULY 1976
REVISION
NUMBER
1
DATE
1 AUGUST
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
26A
Added
18 4A
Added
REASON
FOR
TEMPORARY
REVISION
To
include
the inspection requirements
of
Cessna
Service
Bulletin
SEB99-18.
To provide
additional
information
for the stop
drilling
of cracks
that originate
at
the trailing edge
of control
surfaces
with
corrugated
skins.
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
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locations.
Draw a line,
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ink marker,
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For Aerofiche
Publications:
Draw
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Revision
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This will
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For "added"
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draw
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is
wide
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edges
of the pages.
Temporary
Revisions should
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collected
and maintained
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or binder near
the aerofiche
library
for
quick reference.
COPYRIGHT
© 2000
CESSNA
AIRCRAFT COMPANY
WICHITA,
KANSAS,
USA

INSERT
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DESTROY
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LIST
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NOTE:
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changes
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avertical
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Changes
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Illustrations
are
Indicated
by
miniature
pointing
hands.
Dates
of issue
for
original
and
changed pages
are:
Original.
.
July
1976
Change
.
1 ..
1 August
1995
* The
asterisk
indicates
pages changed,
added,
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deleted
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receipt
of
the
second and
subsequent
changes
to
this book,
personnel
responsible for
maintaining
this
publication
in
current
status
should
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that
all previous
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have
been
received
and
incorporated.
A
Change
1

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TABLE OF CONTENTS
SECTION
Page
1 GENERAL DESCRIPTION ........................ 1-1
2 GROUND HANDLING, SERVICING, LUBRICATION AND INSPECTION .... 2-1
3 FUSELAGE . ........................ .. 3-1
4 WINGS AND EMPENNAGE ....................... 4-1
5 LANDING GEAR AND BRAKES ...................... 5-1
6 AILERON
CONTROL SYSTEM ......................
6-1
7 WING FLAP CONTROL SYSTEM ..................... 7-1
8 ELEVATOR CONTROL SYSTEM ..................... 8-1
9 ELEVATOR TRIM TAB CONTROL SYSTEM ................ 9-1
10 RUDDER CONTROL SYSTEM ...................... 10-1
11 ENGINE
. .............................
. 11-1
12 FUEL SYSTEM. ............................ 12-1
13 PROPELLER. . ......................... . 13-1
14 UTILITY SYSTEMS
. ................ ........
. 14-1
15 INSTRUMENTS
AND INSTRUMENT SYSTEMS
. ................. 15-1
16 ELECTRICAL SYSTEMS. . ....................... 16-1
17 ELECTRONIC SYSTEMS (DELETED) (See page iii)
18 STRUCTURAL
REPAIR .......................
. 18-1
19 PAINTING ............................ . 19-1
20 WIRING DIAGRAMS ...........................
20-1

CROSS
REFERENCE
LISTING OF POPULAR
NAME VS. MODEL
NUMBERS AND
SERIALS
All aircraft, regardless
of manufacturer, are certificated under model
number designations. However,
popular names are often used for marketing purposes. To provide a consistent method of referring to the
various aircraft, model numbers will be used in this publication unless names are required to differentiate
between versions of the
same basic model. The following table provides
a cross reference listing of popular
name
vs. model
numbers.
MODEL
SERIALS
POPULAR NAME YEAR MODEL BEGINNING ENDING
150 COMMUTER
1977 150M
15078506
15079405
150 COMMUTER II
REIMS/CESSNA F150
1977 F150M F15001339
F15001428
REIMS/CESSNA
F150
COM-
MUTER
150 AEROBAT
1977 A150M A1500685
A1500734
REIMS/CESSNA F150 AEROBAT
1977 FA150M FA1500312
FA1500336
ii
Change
I

FOREWORD
This manual
contains
factory-recommended procedures
and
instructions for
ground handling, servicing,
and maintaining
Cessna
Model
150-Series aircraft. This
includes the Models 150,
Reims/
Cessna F150, 150 Aerobat,
and Reims/Cessna F150
Aerobat. The
Reims
version
of the model
150
is identical
to the
Model 150
except
that
it is powered by a 0-200-A
Rolls Royce engine. 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 Cessna 150-Series
aircraft
and thereby establish
a reputation for reliable
service.
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 the
Cessna Product
Support
subscription
services. Cessna Service Stations
have also been
supplied
with a group of supplier
publications which provide
disassembly,
overhaul,
and parts breakdowns
for some
of the various
supplier
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's Authorized
Service Stations and/or
through
Cessna's
subscription
services.
In addition
to the information
in this Service Manual, a group
of
vendor
publications
is available
from Cessna
Parts
Distribution
(CPD 2),
which describe complete
disassembly,
overhaul,
and
parts
breakdown
of some of the
various vendor
equipment items.
A listing
of the available
publications
is issued periodically
by
the Cessna
Propeller
Product
Support
Department.
Information
for Nav-o-Matic Autopilots,
Electronic Communi-
cations, and Navigation
Equipment are not
included in this manual.
These
manuals are
available
from Cessna
Parts Distribution.
WARNING
INSPECTION
INTERVALS,
REPLACEMENT
TIME
LIMIT'S
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
ALL
APPROVED
PARTS.
IF
PARTS
ARE
DESIGNED,
MANUFACTURED,
REMANUFACTURED,
OVERHAULED,
PURCHASED,
AND/OR
APPROVED
BY ENTITIES
OTHER
THAN
CESSNA,
THEN THE
DATA
IN CESSNA'S
MAINTENANCE/SERVICE
MANUALS
AND
PARTS
CATALOGS
ARE
NO LONGER
APPLICABLE
AND
THE
PURCHASER
IS WARNED
NOT
TO RELY
ON SUCH
DATA
FOR
NON-CESSNA
PARTS.
ALL
INSPECTION
INTEVALS,
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.
ChangE
I iii/(iv
Blank)

SECTION 1
GENERAL
DESCRIPTION
TABLE OF CONTENTS
GENERAL
DESCRIPTION
.... ......
1-1
Description
.............
1-1
Model
150 and F150-Series
.......
1-1
Aircraft Specifications
........
1-1
Description
.
...........
1-1
Stations
..............
1-1
Model
A150 and
FA150-Series
...... 1-1
Torque Values
............
1-1
1-1. GENERAL
DESCRIPTION.
ments
of the Acrobatic
Category,
FAR Part
23. In
addition
to the "beef-up",
quick-release cabin
doors,
1-2. MODEL
150 AND
F150-SERIES.
two-strap
shoulder
harnesses,
and aerobatic
paint
design are
standard. Removable
seat and back cush-
1-3. DESCRIPTION.
Cessna Model
150 and
F150-
ions are
provided to
allow occupants
to use
either a
Series aircraft,
described
in this
manual,
are high-
seat-pack
or back-pack
type parachute during
aero-
wing
monoplanes
of all-metal,
semimonocoque con-
batic
maneuvers.
struction.
Thes
aircraft
are equipped
with fixed
tu-
bular
spring-steel
main gear
struts
and a steerable
1-6.
AIRCRAFT
SPECIFICATIONS.
Leading partic-
nose
gear.
The steerable
nose
gear is
equipped
with
ulars of
these aircraft,
with
dimensions
based
on
an
air/hydraulic
fluid
shock
strut. Two-place
seat-
gross
weight, are
given
in figure
1-1. If these
di-
ing
is standard,
and
a double-width,
fold-up
auxiliary
mensions
are
used for
constructing
a
hangar
or com-
rear
seat
may be
installed
as optional
equipment.
puting
clearances,
remember
that
such factors
as
Each Model
150 and F150-Series
aircraft
is equipped
nose gear
strut inflation,
tire pressures,
tire
sizes
with a
four-cylinder,
horizontally
opposed,
air-cooled
and
load distribution
may
result
in some
dimensions
Continental
or Rolls
Royce
engine,
driving
an all-
that are
considerably
different
from
those listed.
metal,
fixed-pitch
propeller.
These
aircraft
feature
a "wrap
around"
rear window and
a swept-back
fin
1-7.
STATIONS.
Station diagrams
are
shown in
fig-
and rudder.
ures
1-2 and
1-3 to assist
in locating
equipment
when
a
written description
is
inadequate
or impractical
1-4. MODEL
A150 and FA150-SERIES. 1-8.
TORQUE VALUES. A chart of recommended
nut torque values is shown in figure 1-4. These tor-
1-5. DESCRIPTION.
Aerobatic Model A150 and que
values are recommended for all installation pro-
FA150-Series aircraft are a modification of the cur- cedures contained in this manual, except where other
rently produced Model 150. Structure has been values are stipulated. They are not to be used for
"beefed-up" in
some areas in order to meet require- checking
tightness of installed parts during service.
1-1

GROSS
WEIGHT
* .....................
.. .
1600 lb
FUEL CAPACITY
Standard Wing (Total) ................ .. . 26 gal.
Standard Wing (Usable) ................... 22.5 gal.
Long-Range Wing (Total) ..................
38 gal.
Long-Range Wing (Usable) .................. 35 gal.
OIL CAPACITY
Without External
Filter ................ .
6 qt
With External Filter ................ . . .7 qt
ENGINE MODEL (Refer
to Section 11 for Engine Data) .......
CONTINENTAL 0-200 Series
PROPELLER (Fixed Pitch) ................... . 69" McCAULEY
MAIN
WHEEL TIRES ......................
6.00x 6, 4-Ply
Rating
Pressure ........................ .21 psi
NOSE WHEEL TIRE (Standard) .................. 5.00x 5, 4-Ply Rating
Pressure
. .. . .. . . . . ... ...........
.30 psi
NOSE
WHEEL
TIRE
(Oversize)
.................
6.00x 6,
4-Ply Rating
TIRE (Stan ard) ... .... .. . ... . . . . .
NOSE GEAR STRUT PRESSURE
(Strut Extended) .........
20 psi
WHEEL ALIGNMENT (Tubular Gear)
Camber ... .................. ... 3* to 5-
Toe-In . . . ..................
00" to +.16"
AILERON TRAVEL
Up ............................ 20, +2" -0
°
Down
..........................
140,
+2
°
-0
°
WING FLAP
TRAVEL
.....................
0 to 40
° 2
RUDDER TRAVEL (Measured parallel to water line)
Right ............... . ........ . 20' 30', +0
°
-2
°
Left . . . . ................. . . . . ..
20
°
30', +0
°
-2
°
RUDDER TRAVEL (Measured
perpendicular to
hinge line)
Right .. ...................... 23', +0
°
-2
°
Left .. ......................
23', +00 -2
°
ELEVATOR TRAVEL
Up
... .. . . ... ......
. . . ... ... . . 23,
, +1" -0-
Down ................ ..........
15" 1°
ELEVATOR
TRIM TAB TRAVEL
Up ....................... .. 10°
±1
°
Down . . . . ..................... . .
20 +1
PRINCIPAL DIMENSIONS
Wing Span. ................... .....
33' 4"
Length ...
.....................
23' 11-1/2"
Fin Height (Maximum with Nose Gear Depressed and
Flashing Beacon Installed on Fin) ............. 8' 6"
Track Width
... ....................
7' 7-1/4"
Tail Span ....................... .
.10' 0"
BATTERY
LOCATION ...................
Firewall
Figure
1-1. Aircraft Specifications
1-2 Change I

0.00 18.50 56.69 70.69
8.37
36.00
76.44
71.44
49.69
Figure 1-2. Fuselage Stations
22.12
31.75
44.12
56.87
69.87
84.00
102.00
120. 00
138.00
156. 00
174. 00
192.00
Figure 1-3.
Wing Stations
1-3

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.
ICAUTIONI
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
1-4. Torque
Values
1-4

SECTION
2
GROUND HANDLING,
SERVICING,
CLEANING
LUBRICATION
AND
INSPECTION
TABLE
OF CONTENTS
Page
GROUND HANDLING
.
..............
2-1
Vacuum System
Filter .........
2-12
Towing .
......... .........
2-1
Battery ................
2-12
Hoisting.... ................
2-4
' Tires .................
2-12
Jacking .
......... .........
2-4
Nose Gear Shock
Strut .........
2-12
Leveling.
.............
. 2-4
Nose Gear
Shimmy Dampener
......
2-12
Parking
.
..........
... . 2-4
Hydraulic Brake
Systems
........
2-13
Tie-Down
...............
2-4
CLEANING
...............
. 2-13
Flyable Storage
...........
2-4
Windshield
and Windows. ........
2-13
Returning Aircraft to
Service .....
2-5 Plastic
Trim. ............
2-13
Temporary
Storage ...........
2-5
Painted Surfaces
............
2-13
Inspection
During Storage
. .......
2-5
Aluminum
Surfaces
.........
2-13
Returning
Aircraft to Service
......
2-5
Engine and
Engine Compartment
.....
2-13
I Indefinite Storage
..........
2-6 Upholstery
and Interior .........
2-13
Inspection During
Storage
......
.. 2-6
Propeller
.............
. 2-14
Returning
Aircraft
to Service ......
2-7
Wheels
..............
. 2-14
SERVICING
.
...............
2-7
LUBRICATION
.............
. 2-14
Fuel
. ...........
. 2-7
Tachometer
Drive Shaft
........
2-14
Fuel Drains ..............
2-7
Wheel Bearings
............
2-14
Carburetor
Drain
Plug Inspection
. 2-7
Nose
Gear Torque
Links ........
2-14
Engine
Oil. ..
2-7
Wing Flap Actuator
.........
.. 2-14
Engine Induction
Air Filter
.......
2-8 INSPECTION.
..
...... ....
2-18
2-1. GROUND HANDLING.
}CAUTION
2-2. TOWING. Moving the aircraft by hand is ac- When towing the aircraft, never turn the nose
complished by using the wingstruts
and landing gear wheel more
than 30 degrees either side of
struts as push points.
A tow bar attached to the nose center
or the nose gear will be damaged. Do
gear
should be used
for steering and
maneuvering
the not
push on control
surfaces or
outboard em-
aircraft
on the ground. When
no tow bar is available,
pennage
surfaces. When pushing
on the tail-
press down at the horizontal stabilizer front spar ad- cone, always apply pressure at a bulkhead to
jacent to the fuselage to raise
the nose wheel off the
avoid buckling the skin.
ground. With the nose wheel clear of the ground, the
aircraft can be turned by pivoting it about the main
wheels.
TOW BAR:
PART NUMBER
0501019-1 IS
AVAILABLE FROM CESSNA PARTS
DISTRIBUTION (CPD 2).
NOTE
Use tow
bar carefully
to
avoid scarring finish on
speed
fairing.
Figure
2-1. Tow
Bar
Change
1
2-1

REFER
TO SHEET
2
FOR
ITEM
NUMBERS
NOTE
Corresponding points
on
both
upper
door
sills
may
be
used
to
level
the
aircraft
laterally.
Reference
points
for
longitudinal
leveling
of
aircraft
are
two
screws
on
left
side
of
tailcone
at
zero
waterline.
These
are
indicated
in
illustration
by
A.
(Also
refer
to
paragraph 2-5)
Figure 2-2.
Jacking
and
Leveling
(Sheet
1
of
2)
2-2

JACKING
INFORMATION
ITEM
NUMBER
TYPE AND NUMBER
REMARKS
1
Block
(Jack point
not available)
1x4x4
padded
with 1/4" rubber
1 Jack
Any
short jack of capable
capacity
3
Universal tail stand
Any tail stand of capable capacity
4) Cessna
#SE-576 (41-1/2" high) Universal
jack stand (FOR USE WITH ITEM
2)
5 Built-in jack
pad Part of step
bracket (SEE CAUTION)
#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"
1. Wing jacks are
placed under front spar of wing just
outboard of wing strut, and must
extend far enough to raise
wheels off ground, and must be
of adequate strength.
2. Attach a
suitable stand
to the tie-down
ring. Be sure
tail stand weighs enough
to
keep tail down
and under all conditions
that it is
strong enough
to support any
weight
that might be placed on it (place
shot bags or sand bags on tail
stand. In
addition,
the base of adjustable
tail stand
is to be filled with
concrete for additional
weight as a safety factor.
3. Operate
jacks evenly until desired
height is reached.
ICAUTION
When
using built-in jack
pad, flexibility
of the gear strut
will cause the main
wheel to
slide inboard
as the
wheel is raised,
tilting
the jack. The
jack must
be lowered
for a
second
operation.
Jacking
both wheels
simultaneously
at built-in
jack pads
is not re-
commended.
Jack pad
may be used to raise
only one main wheel.
DO NOT USE
brake
casting as a jack point.
4. Items
(4) and
(6) are available
from
the Cessna
Parts Distribution
CPD 21
Figure
2-2. Jacking and
Leveling (Sheet 2
of 2)
Change 1 2-3

2-3.
HOISTING.
The
aircraft may
be lifted
with
a
NOTE
hoist of two-ton capacity by using hoisting rings,
which
are
optional
equipment,
or by
means
of suit-
The
aircraft
is delivered from
Cessna
with
a
able
slings.
The
front
sling should
be
hooked
to each
corrosion-preventive
aircraft
engine
oil
upper
engine
mount
at the'firewall.
and
the aft
sling
(MIL-C-6529,
Type
II).
This engine
oil
is a blend
should
be
positioned
around
the
fuselage
at the
first
of aviation
grade
straight
mineral
oil
and a
bulkhead
forward
of the
leading
edge
of the
stabilizer.
corrosion
preventive
compound.
This
engine
oil
If
the optional hoisting
rings
are
used,
a minimum
should
be
used
for the
first 25
hours
of engine
cable
length
of 60
inches
for
each cable
is
required
operation.
In the
event it
is necessary
to add
oil
to prevent
bending
of the
eyebolt-type
hoisting
rings.
during the
first
25 hours
of
operation,
use
only
If
desired,
a spreader
jig
may be
fabricated
to
apply
aviation
grade
straight
mineral
oil of
the
correct
vertical
force
to the eyebolts.
viscosity.
2-4.
JACKING.
Refer
to
figure
2-2
for
jacking
pro-
a.
Program
I. During
the
15 day non-operational
cedures.
storage
or the
first
50 hours
of
engine
or
cylinder
operation,
every
fifth day the
propeller
shall be
2-5.
LEVELING.
Corresponding
points
on
both
up-
rotated through
six
revolutions,
without
running
the
per
door
sills
may
be used
to
level
the aircraft
later-
engine,
stopping
the propeller
45
°to
90
°
from
the
ally.
The
reference
points
for
longitudinal
leveling
original
position.
of
the aircraft
are
the two
screws
on the
left side
of
the tailcone
at zero
waterline.
WARNING
2-6.
PARKING.
Parking
precautions
depend
prin-
cipally
on local conditions. As a general precaution,
For maximum safety, always take
the following
set parking brake
or chock the wheels and install the
precautions to ensure the engine cannot fire
or
controls lock. In severe
weather and high wind con- cause
injury when the propeller is moved:
ditions, tie
down
the aircraft
as
outlined
in paragraph
1.
Verify
magneto switches
are OFF
2-7
if a hangar
is not
available.
2. Set throttle CLOSED.
3. Set
mixture control
"IDLE CUT-OFF.
2-7. TIE-DOWN. When
mooring the aircraft in the
3 Set mixture Conttol IDLE CUT OFF
open, head into
the wind if possible. Secure control
5 Verify the cabin door latch is open.
surfaces
with
the internal
control
lock and set
brakes.
6. If the aircraft
is stored outside,
leave the
aircraft tie-downs
in place in accordance with
CAUTION
paragraph
2-7.
7. Do not
stand within
the
arc of the
propeller
Do not
set parking
brakes during
cold weather
blades while
rotating the
propeller.
when accumulated moisture may freeze the
brakes or
when
the
brakes
are
overheated.
In
addition,
the
pitot
tube
static
air
vents,
air vents,
openings in the engine
cowling, and other
similar
After
completing
the preceding,
proceed
to
moor
the
openings
shall
have
protective
covers
installed
to
aircraft
as
follows:
prevent
entry
of
foreign
material.
After
15
days,
the
a. Tie
ropes, cables,
or
chains
to the
wing
tie-
aircraft
should
be flown
for
30 minutes
reaching
but
down fittings
located
at the
upper
end
of each
wing
not
exceeding
normal
oil
and cylinder
operating
strut.
Secure
the
opposite
ends
of ropes,
cables, or
temperatures.
If
the aircraft cannot
be
flown,
it
chains
to
ground
anchors.
should
be represerved
in
accordance
with
paragraph
2-
b. Secure
a
tie-down
rope
(no
chains
or cables)
to
10.
Temporary
Storage
the
exposed portion
of the engine
mount and
secure
opposite
end of
rope to a ground
anchor.
c. Secure
the middle of
a rope to the tail tie-down
CAUTION
ring.
Pull each
end of
rope away
at a
45 degree
angle
and
secure
to ground
anchors
at
each side
of tail.
Excessive
ground
operations
shall be
avoided.
d.
Secure control
lock on
pilot control
column.
If
control
lock is
not available,
tie
pilot control
wheel
b. Program
II. After
engine
and cylinders
have
back
with front seat
belt.
operated
over 50 hours,
the aircraft
can be non-
e. These
aircraft are
equipped with a
spring-loaded
operationally
stored for up
to 30 days. Every
seventh
steering system
which affords
protection
against nor-
day the propeller
shall be
rotated through
six
mal wind
gusts. However, if extremely high wind
revolutions, without running the engine,
stopping at
gusts are anticipated, additional
external locks may 45
°to
90
°
from the
original position. The same
be installed. warnings and cautions apply as with Program I
flyable
storage
above.
2-8.
FLYABLE
STORAGE.
Flyable
storage
is
defined
as
a maximum
of 30 days
non-operational
Protective
covers
shall
be applied
as
with Program
storage.
Flyable
storage
has two
programs:
Program
I flyable
storage,
but
the aircraft
need
not be
flown
until
(aircraft
with
engines
or
cylinders
with
less than
50 30
days
non-operational storage
have elapsed.
If the
operating
hours)
and Program
II (aircraft
with
aircraft
cannot
be flown,
it should
be
put into
engines
or
cylinders
with
50
or more
operating
hours).
temporary
storage
in
accordance
with
paragraph
2-10.
2-4 Change 1

2-9.
RETURNING AIRCRAFT TO SERVICE.
After MIL-L-46002, Grade 1 or equivalent.
The
flyable
storage,
returning the
aircraft to service
is following
oils are approved
for spraying
accomplished
by performing
a thorough pre-flight operations
by Teledyne
Continental Motors:
inspection.
At the
end of the
first 25
hours of
engine
NOX RUST
VCI-105
- Daubert
Chemical
Co.,
operation,
drain
engine
oil and clean
oil pressure
4700 So.
Central
Ave., Chicago,
Illinois,
screen
(or change
external
oil
filter element).
Service
Petratect
VA - Pennsylvania
Refining
Co.,
engine with correct grade
and quantity
of engine
oil. Butler,
Pennsylvania.
Refer
to
figure
2-4
and
paragraph
2-21
for correct
grade
of engine oil.
h . Using
a portable pressure
sprayer,
atomize spray
preservative
oil through
the upper spark plug hole
of
2-10.
TEMPORARY
STORAGE.
Temporary storage
each
cylinder with
the piston in approximately
the
is defined as aircraft
in a non-operational
status for a bottom
dead center position.
A pressure pot or pump-
maximum of 90
days. The aircraft
is constructed
of up
type garden pressure
sprayer
may be used.
The
corrosion resistant
alclad aluminum,
which will last
spray head should have
ports around the
indefinitely
under normal
conditions
if kept clean, circumference
to allow complete
coverage
of cylinder
however, these
always are subject
to oxidation. The walls.
Rotate crankshaft
as each pair of cylinders
is
first
indication of corrosion on unpainted
surfaces is in
sprayed.
the form of white
deposits or spots. On
painted i.
After completing step
"h," rotate crankshaft
so
surfaces, the paint isdiscolored or
blistered.
Storage that no piston
is at top dead center.
If the aircraft is to
in a dry hangar
is essential to good
preservation and
be stored outside, stop
two-bladed propeller
so that
should
be procured if possible.
Varying conditions
will blades are as
near horizontal as possible
to provide
alter the
measures of preservation,
but under normal
maximum
clearance with passing
aircraft.
conditions a dry hangar,
and for storage periods
not to j. Again
spray each cylinder
without moving the
exceed
90 days, the following
methods of treatment
crankshaft to
thoroughly cover all interior
surfaces of
are suggested:
the cylinder above the piston.
a. Fill fuel tanks with
correct grade of gasoline.
k. Install
spark plugs and connect
spark plug leads.
b. Clean and
wax aircraft thoroughly.
1. Apply preservative
oil to the engine interior
by
c.
Clean any oil or grease
from tires and coat
tires spraying approximately
two
ounces of the
with a
tire preservative. Cover
tires to protect against
preservative
oil through the oil
filler tube.
grease and oil.
m. Seal all engine openings
exposed to the
d. Either
block up fuselage to relieve pressure on
atmosphere using suitable plugs or non-hygroscopic
tires or rotate
wheels every 30 days to change tape. Attach
a red streamer at each point that a
plug
supporting points and prevent flat spotting the tires, or tape is installed.
e. Lubricate all airframe
items and seal or cover all n. Ifthe aircraft
is to be stored outside, perform the
openings
which could allow
moisture and/or
dust to
procedures
outlined in paragraph
2-7. In addition,
the
enter.
pitot tube, static
source vents, air vents,
openings in
the engine cowling and
other similar openings
should
NOTE
have protective
covers installed
to prevent entry
of
foreign material.
The aircraft
battery
serial number
is recorded in
o. Attach
a warning placard
to the propeller
with the
the aircraft
equipment
list. To assure
accurate
following notation,
"DO NOT
TURN PROPELLER
--
warranty records,
the battery should
be re-
ENGINE PRESERVED
- preservation
date."
installed in the same aircraft from which it was
removed.
If the battery is
returned to service in
a 2-11. INSPECTION
DURING STORAGE.
different aircraft,
appropriate record
changes
a. Inspect airframe
for corrosion at least
once a
must
be made and notification
sent to the Cessna
month and remove
dust collections as
frequently as
Claims Department.
possible. Clean and wax as required.
b. Inspect the interior
of at least one cylinder
f. Remove battery
and store in a cool
dry place;
through the spark plug
hole for corrosion at least
once
service
the battery
periodically
and charge as
a month.
required.
NOTE
NOTE
Do not move crankshaft when inspecting
An engine treated in accordance with the
interior of cylinder
for corrosion.
following may
be considered
protected
against
normal
atmospheric corrosion
for a period not
to c. If the engine
is not returned to flyable
status at
exceed 90
days.
end of
the 90 day
temporary storage
period
and the
aircraft
is to
be continued
in
non-operational
storage,
g.
Disconnect
spark plug
leads and remove
upper
it
must be preserved
in accordance
with
Indefinite
and lower spark plugs from each cylinder. Storage, paragraph 2-13.
NOTE
2-12. RETURNINGAIRCRAFTTOSERVICE.
After
temporary storage,
use the following
procedures to
The
preservative oil
must be Lubricating
Oil-
return the aircraft
to service.
Contact
and Volatile, Corrosion
Inhibited,
a. Remove aircraft
from blocks and check
tires for
Change 1 2-5

proper inflation.
Check for proper nose gear strut
Accomplish temporary storage steps 2-10.g.
thru
inflation.
2-10.j..
b. Check
battery and install.
e. Apply preservative
oil to
the engine interior
by
c. Check that
oil sump has
proper grade and
spraying approximately
two ounces
of MIL-L-46002,
quantity of
engine oil.
Grade I oil or equivalent
through the oil filler
tube.
d. Service induction
air filter and remove warning
f. Do not
rotate propeller after
completing step "e."
placard
from propeller.
g. Install
lower spark
plug or install
solid plugs, and
e. Remove materials
used to cover openings.
install dehydrator
plugs in upper
spark plug holes. Be
f. Remove,
clean, and gap spark
plugs.
sure that dehydrator
plugs are blue in
color when
g.
While spark
plugs are removed,
rotate propeller
installed.
several revolutions
to clear excess
rust preventative
h. Cover spark
plug lead terminals
with shipping
oil from cylinders.
plugs (AN4060-1)
or other
suitable covers.
h. Install
sparkplugs. Torque
spark plugs to value
i. With throttle
in full open position, place
a bag of
specified in Section 11
and connect spark plug
leads. desiccant
in the carburetor intake
and seal opening
i. Check fuel strainer.
Remove and clean filter with
moisture resistant paper and tape.
screen if necessary. Check fuel tanks and fuel lines for j. Place a bag of desiccant in the exhaust tailpipe(s)
moisture
and sediment, and
drain enough fuel to
and seal openings
with moisture
resistant tape.
eliminate
moisture and sediment.
k. Seal cold air inlet to the heater muffwith
moisture
j. Perform a thorough pre-flight
inspection,
then resistant
tape.
start and warm up
engine.
i. Seal
engine breather by
inserting a dehydrator
k.
Give the airplane a thorough
cleaning and visual
MS27215-2 plug
in the breather hose
and clamping in
inspection.
A test
flight is recommended.
place.
m. Seal all other
engine openings exposed
to
2-13. INDEFINITE
STORAGE Indefinite storage
is atmosphere using
suitable
plugs or non-hygroscopic
defined as aircraft
in a non-operatonal status
for an tape.
indefinite
period
of time.
Engines
treated
in
accordance
with
the following
may be considered
NOTE
protected
against
normal
atmosphere
corrosion,
provided the
procedures outlined
in paragraph
2-14
Attach
a red streamer
to each place on
engine
are performed at the intervals specified.
where plugs or bags desiccant
are placed or
a.
Operate engine
until oil
temperature
reaches moisture
resistant
paper or tape
is installed.
normal operating range. Drain engine oil sump
and Either attach red streamers
outside of the sealed
reinstall drain plug.
area with tape or to the inside
of the sealed area
b. Fill oil
sump to normal operating
capacity
with with
safety wire
to prevent
wicking of
moisture
I MIL-C-6529
Type II corrosion-preventive
mixture into the sealed
area.
which
has been thoroughly
mixed
and pre-heated
to a
minimum of 221
°
F (105
°
C) at the time it is added
to n. Ifthe
aircraft is to be stored outside,
perform the
the
engine.
procedures
outlined in
paragraph 2-7.
In addition, the
pitot tube, static source vents, air vents, openings in
NOTE the engine cowling and other similar openings should
have protective covers installed to prevent entry of
MIL-C-6529, Type 11 corrosion-preventive
foreign
material.
mixture consists of one part compound MIL-C-
o. Attach a warning placard
on the throttle control
6529, Type
I (Cosmoline
No. 1223, supplied
by E.
knob, to the
effect that the
engine contains
no
F. Houghton
& Co., 305 W. LeHigh Avenue,
lubricating oil. Attach a warning placard
to the
Philadelphia, PA, or Esso Rus-ban 628,
or propeller with the following
notation, "DO NOT
equivalent) mixed with three parts new TURN PROPELLER - ENGINE PRESERVED -
lubricating
oil of the grade
recommended
for
preservation date."
service. Single grade
oil is recommended.
. p. Prepare
airframe for storage
a outlined in
During all spraying
operations corrosion
mixture
paragraph
2-10 thru step "f."
is
pre-heated
to 221
°to
250
°
F
(105
°
to 121
°
C).
NOTE
NOTE
As
an alternate
method
of indefinite
storage,
the
The corrosion-preventive
mixture is harmful
to
aircraft
may be serviced
in accordance
with
paint and should
be wiped from painted
surfaces paragraph
2-10 providing
the aircraft is run-up
immediately.
at maximum
intervals
of 90 days
and then
reserviced per
paragraph
2-10.
c. Immediately
after
filling the
oil sump
with MIL-
C-6529, Type II
corrosion-preventive
mixture,
fly the 2-14.
INSPECTION
DURING STORAGE.
Aircraft
aircraft for a period of time not to exceed
a maximum in indefinite storage
shall be inspected as follows:
of 30 minutes, reaching but not exceeding
normal oil a. Inspect cylinder dehydrator
plugs each seven
and cylinder
temperatures..
days.
s
d. Allow engine
to cool to
ambient temperature.
b. Change dehydrator
plugs
if their color indicates
an unsafe
condition.
2-6
Change
1

c. If the dehydrators
plugs have changed
color in capacities
are listed in Section
1. The recommended
one-half of
the cylinders, all desiccant
material in the
fuel grade to be
used is given in. figure
2-4.
engine shall
be replaced with
new material.
d. Every six months, respray the cylinder interiors IWARNING
with corrosion-preventive
mixture.
NOTE
Do not fly with contaminated or
unapproved fuel.
Before spraying,
inspect the interior of one 2-19.
FUEL DRAINS. Fuel quick-drains are located
cylinder for corrosion through the spark
plug in the fuel tanks, fuel line, fuel
strainer, carburetor,
hole and remove at least
one rocker box cover
and fuel line forward
of the ON-OFF valve
and carburetor.
inspect the
valve mechanism.
A
drain plug is
installed in the
carburetor. The
fuel
tanks and fuel strainer have drain valves. To activate
2-15. RETURNING
AIRCRAFT
TO SERVICE.
After quick-drain
valves
for fuel samplings,
place cup up
to
indefinite storage, use
the following procedure
to the valve
and depress valve with
rod protruding from
return
the aircraft to
service: cup.
See
Section 12 for
illustration of fuel
tank drain
a.
Remove aircraft
from blocks
and check tires
for valve.
The strainer drain
valve is an
integral part of
correct inflation.
Check for correct
nose gear strut
the fuel strainer assembly.
The strainer drain
is
inflation.
equipped with
a control which is
located adjacent to
b.
Check battery
and install.
the oil
dipstick. Access
to the control
is through the oil
c. Remove
all paper, tape,
desiccant bags, and
dipstick access
door. Open
drains and remove
drain
streamers
used to seal
and preserve
the engine.
plugs at
intervals specified
in figure 2-4.
Also, during
d. Remove
warning placards
posted at throttle
and
daily inspection of
the fuel strainer
and tanks,
if water
propeller.
is
found in the system,
all fuel drains
should be
e. Remove and clean
engine oil screen, then
reinstall temporarily
opened and all water
drained from the
and
safety. On aircraft
that are
equipped with
an system.
If the aircraft
has been
serviced with
external
oil filter,
install new filter
element.
improper
fuel grade, defuel
completely
and refuel with
f. Remove oil sump
drain plug and drain sump.
the correct
grade. Provided
weight and balance
Install
and safety drain plug.
considerations will
permit, fuel tanks should
be kept
full between flights.
NOTE
NOTE
The corrosion-preventive
mixture
will
mix with
the engine
lubricating
oil, so flushing
the oil
If fuel
tank quick-drains
are not installed,
at
system
is not necessary.
Draining
the oil sump
least
one quart of fuel
should be drained
from the
will remove enough of
the corrosion-preventive
fuel strainer
with the selector
valve in a position
mixture.
to assure each
tank is draining fuel.
NOTE
2-20. CARBURETOR
DRAIN PLUG INSPECTION.
In order to
prevent the possibility
of thread sealant
The corrosion-preventive mixture is harmful to contamination in the carburetor float chamber,
paint
and
should be
wiped from
painted
surfaces
cleaning and
inspection
of
the carburetor
should
be
immediately.
accomplished at
each 100-hour inspection
and
anytime water in the fuel is suspected.
g.
Service and install the
induction air filter.
a. With the fuel
valve OFF, remove carburetor
drain
h. Remove
dehydrator
plugs and spark
plugs or
plug and clean
off any sealant
present on
the end of
plugs
installed in spark plug
holes and rotate the
plug
or in the threads on
the plug.
propeller by hand several
revolutions to
clear b.
Inspect drain plug hole
in the carburetor and
corrosion-preventive
mixture
from cylinders.
remove any
sealant remaining
in the hole.
i. Clean,
gap, and install spark
plugs. Torque plugs
c. Turn fuel valve
to ON to flush float chamber
and
to the value listed
in Section 11.
ascertain
that all residue
of sealant material
is
j. Check fuel
strainer. Remove
and clean filter
dislodged
and washed
out of the
chamber. Flushing
screen. Check
fuel tanks
and fuel lines
for moisture
operation
should last
15 to 30 seconds.
and
sediment, and
drain enough
fuel to eliminate.
d.
A second flushing
should then
be accomplished
k.
Perform a thorough pre-flight
inspection, then
and the
drained fuel
retained for inspection
to insure
start and warm-up
engine.
that no sealant particles
are present.
1. Thoroughly
clean and visually
inspect
aircraft and
e. Install
drain plug
as follows:
flight
test aircraft.
1. Install drain
plug in carburetor
1-1/2 to 2
turns.
2-16. SERVICING.
2. Apply sealant
to drain plug
threads (use
NS-
40 [RAS-41 or equivalent).
2-17. Servicing
requirements
are shown
in figure 2-4.
3.
Tighten and
safety drain plug.
The
following
paragraphs
supplement
this figure
by
f. Turn
fuel valve
ON
and inspect
for evidence
of fuel
adding
details not
included in
the figure. leakage.
2-18. FUEL.
Fuel tanks should be
filled immediately
2-21. ENGINE OIL.
Checkengine lubricatingoil
after flight to lessen
moisture condensation. Tank
with
the oil dipstick five
to ten minutes after the
Change
1
2-7

engine
has been stopped. Engine
oil should be drained
while the engine is
still hot so that more
positive
draining is obtained. Refer to the inspection charts for
required intervals for oil and filter changes.
Change Valve shown open.
To close, twist
oil every six months even though less than the screwdriver until valve unlocks and
specified hours have accumulated.
Reduce these snaps down
to closed position.
periods
for prolonged operation
in dusty areas, in cold
climate where sludging conditions exist, or where
short flights and long idle periods are encountered,
which cause sludging conditions. Always change oil
and install a new filter element or clean screen
whenever oil on dipstick
appears dirty. Oil
capacity is
six
quarts total with a normal
operating capacity
of
five quarts for flights of less than three hours. For.
extended flight, fill to the six quart level on the
dipstick. DO
NOT operate with
less than the mini-
mum for flight quantity
of four quarts. If
the engine is
equipped
with an external
oil filter, an additional
quart of oil is required when the filer element is
changed.
When adding or changing
engine oil, use
aviation grade oil in accordance with figure
2-4. Figure 2-3.
Quick-Drain Valve
NOTE c. (Without Quick-Drain Valve.) Remove oil drain
plug from oil sump and allow oil to drain into a
The aircraft is delivered from Cessna with a container.
corrosion-preventive aircraft engine oil (MIL-C-
6259, Type II). If oil
must be added during the
NOTE
first
25
hours
of operation,
use
only
aviation
grade straight
mineral oil conforming to
To ensure complete draining of engine oil sumps,
Specification
MIL-L-6082 of
the correct grade.
the nose of the
aircraft should
be raised slightly
After the
first 25 hours of operation,
drain engine
and the
oil drained while
hot.
oil sump
and clean
the oil pressure
screen.
If an
optional oil filter is installed, change
filter d. After engine oil
has drained, close quick-drain
element at this time. Refill sump with correct valve as shown in figure 2-3 and remove hose, or
quantity and grade of aviation grade straight install and safety drain plug.
mineral oil and use until a total of 50 hours has
accumulated or oil consumption has stabilized, e. Remove and clean oil screen, or change external
then change to
ashless dispersant oil conforming
oil filter element.
to MILL-22851,
Continental Motors
f. On
aircraft equipped with
oil cooler, remove drain
Specification MHS-24, or current Continental plug in adapter (using Allen wrench) and drain oil
Aircraft Engine Service Bulletins. Newly cooler at each oil change. After oil cooler has drained,
overhauled engines
should also be operated on
reinstall plug in adapter.
aviation grade
straight mineral oil
conforming to
Specification MIL-L-6082
until a total of 50
NOTE
hours has accumulated or oil consumption has
stabilized. Multi-viscosity oils meeting When servicing aircraft equipped with an oil
Continental Motors Specification
MHS-24 are cooler,
refer to Continental Aircraft Engine
approved. Service Bulletin M76-5 and any revisions or
supplements thereto.
When changing engine oil, remove and clean oil
screen, or install a new filter element on aircraft g. Service engine with correct quantity of aviation
equipped with an external oil filter. An oil quick- grade engine oil as specified herein.
drain valve may be installed. This valve provides a
quicker and cleaner method of draining engine oil. NOTE
The valve is installed in the oil drain port of the oil
sump and allows oil to be drained by inserting a hose Check oil with dipstick after the first engine run-
over the fitting end and pushing up to lock the valve up when oil cooler is drained or external filter
open, allowing the oil to drain through the hose into a element is changed. Add oil as required to bring
container. To drain the engine oil, proceed as follows: oil in sump to correct level.
a. Operate engine until oil temperature is at normal
operating temperature.
2-22. ENGINE INDUCTION
AIR FILTER. The
b. (With Quick-Drain Valve.)
Attach a hose to the induction air
filter keeps dust and dirt from entering
quick-drain
valve in the oil sump. Push
up on quick-
the induction system.
The value of maintaining
the
drain valve until
it locks open, and allow oil to drain
air filter in a good clean condition can never
be
through hose into container. overstressed.
More engine wear
is caused through the
2-8 Change 1