Cessna SKYHAWK 1976 Pilot Operating Handbook
<"
PILOT'S
OPERATING
HANDBOOK
Ce~a.
1976<
...
......
~
. ,
Skyhawk
CESSNA MODEL 172M
'"
1
PERFORMANCE-
CESSNA
SPECIFlCA TIONS
MODEL 172M
PERFORMANCE -SPECIFICATIONS
SPEED:
Maximum
at
Sea
Level
. . . . . . . . . . . . . . . 125 KNOTS
Cruise,
75%
Power
at
8000
Ft
............
120
KNors
CRUISE:
Recommended
Lean
Mixture
with
fuel
allowance
for
engine
start,
taxi,
takeoff,
climb
and
45
minutes
reserve
at
45%
power.
75%
Power
at
8000
Ft.
. Range
450
NM
38
Gallons
Usable
Fuel
Time
3.9
HRS
75%
Power
at
8000
Ft.
. . . Range
595
NM
48
Gallons
Usable
Fuel
Time
5.1
HRS
Maximum Range
at
10,000
Ft
Range
480
NM
38
Gallons
Usable
Fuel
Time
4.8
HRS
Maximum Range at
10,000
Ft
Range
640
NM
48
Gallons
Usable
Fuel
Time
6.3
HRS
RATE
OF
CLIMB AT
SEA
LEVEL
645
FPM
SERVICE CEILING . . . . . . .
13,100
FT
TAKEOFF PERFORMANCE:
Ground
Roll
. . . . . . . •
865
FT
Total
Distance
Over
50-Ft
Obstacle
1525
FT
LANDING PERFORMANCE:
Ground Roll
.......•...
520
FT
Total
Distance
Over
50-Ft
Obstacle
1250
FT
STALL SPEED (CAS):
Flaps
Up,
Power
Off . . .
50
KNors
Flaps
Down,
Power
Off . .
44 KNOTS
MAXIMUM WEIGHT . . . . . 2300 LBS
STANDARD
EMPTY
WEIGHT:
Skyhawk
......
. 1387 LBS
Skyhawk
II
.....
.
1412 LBS
MAXIMUM
USEFUL LOAD:
Skyhawk
•......
913 LBS
Skyhawk
II
.....
. 888 LBS
BAGGAGE ALLOWANCE
..
.
120 LBS
WING
LOADING:
Pounds/Sq
Ft
13.2
POWER LOADING:
Pounds/HP
15.3
FUEL
CAPACITY:
Total
Standard
Tanks
• 42 GAL.
Long Range
Tanks
. .
52 GAL.
OIL
CAPACITY . . . . .
8 QTS
ENGINE: Avco
Lycoming.
0-320-E2D
150 BHP
at
2700 RPM
PROPELLER:
Fixed
Pitch,
Diameter
75 IN.
DI057-13-RGI-2000-4/95
PILOT'S
OPERATING
HANDBOOK
~
Cessna.
SKYHAWK
1976
MODEL
172M
Serial
No.
_~
____
_
Registration
No.
____
_
THIS
HANDBOOK
INCLUDES
THE
MATERIAL
REQUIRED TO
BE
FURNISHED
TO
THE
PILOT
BY
CAR
PART 3
COPYRIGHT @ 1989
CESSNA AIRCRAFT
COMPANY
WICHIT A, KANSAS, USA
CONGRA
TULA
TIONS
CESSNA
MODEL 172M
CONGRATULATIONS
..
..
Welcome
to
the ranks of Cessna owners! Your Cessna has been designed and constructed
to
give
you
the most
in
performance, economy, and comfort. It
is
our
desire
that
you will find
flying it, either for business
or
pleasure, a pleasant and profitable experience.
This handbook has been prepared as a guide
to
help you get the most pleasure and utility
from your airplane. It contains information about your Cessna's equipment, operating pro-
cedures, and performance; and suggestions for its servicing and care.
We
urge
you
to
read
it from cover
to
cover, and
to
refer
to
it frequently.
Our interest
in
your flying pleasure has
not
ceased with your purchase
of
a Cessna. World-
wide,
the
Cessna Dealer Organization backed by
the
Cessna Service Department stands ready
to
serve you. The following services are offered
by
most Cessna Dealers:
THE CESSNA WARRANTY - It
is
designed
to
provide you with the most compre-
hensive coverage possible:
a.
No
exclusions
b.
Coverage includes parts and labor
c. Available
at
Cessna Dealers world wide
d. Best
in
the
industry
Specific benefits and provisions
of
the
warranty plus other important benefits for
you are contained
in
your
Customer Care Program book supplied with your airplane.
Warranty service
is
available
to
you at any authorized Cessna Dealer throughout
the
world upon presentation
of
your Customer Care Card which establishes your eligibil-
ity under the warranty.
FACTORY TRAINED PERSONNEL
to
provide you with courteous expert service.
FACTORY APPROVED SERVICE EQUIPMENT
to
provide you with
the
most
efficient and accurate workmanship possible.
A STOCK OF GENUINE CESSNA SERVICE PARTS on hand when you need them.
THE LATEST AUTHORITATIVE INFORMATION FOR SERVICING CESSNA
AI
RPLANES, since Cessna Dealers have
all
of
the Service Manuals and Parts
Catalogs, kept current by Service Letters and Service News Letters, published by
Cessna Aircraft Company.
We
urge
all
Cessna owners
to
use the Cessna Dealer Organization
to
the fullest.
A current Cessna Dealer Directory accompanies your new airplane. The Directory
is
revised
frequently, and a current copy can be obtained from your Cessna Dealer. Make your
Directory one of your cross-country flight planning aids; a warm welcome awaits you
at
every Cessna Dealer.
CESSNA
TABLE
OF
CONTENTS
MODEL 172M
TABLE
OF
CONTENTS
SECTION
GENERAL
..
1
LIMITATIONS
2
EMERGENCY
PROCEDURES
3
NORMAL
PROCEDURES
• •
4
PERFORMANCE
•••.
5
WEIGHT
& BALANCE/
EQUIPMENT
LIST.
. • • • • • . • • • . . . 6
AIRPLANE & SYSTEMS
DESCRIPTIONS..
•••••••••••.
7
AIRPLANE
HANDLING,
SERVICE
& MAINTENANCE. • • • • • • . • 8
SUPPLEMENTS
(Optional
Systems
Description
& Operating
Procedures)
• • . • • • . • • • 9
This handbook
will
be
kept current by Service Letters published by Cessna Aircraft
Company. These are distributed
to
Cessna Dealers and
to
those who subscribe
through the Owner Follow-Up System. If you are not receiving subscription service,
you will want
to
keep in touch with your Cessna Dealer for information concerning
the change status of the handbook. Subsequent changes
will
be made
in
the form
of stickers. These should be examined and attached
to
the appropriate page
in
the
handbook immediately after receipt;
the
handbook should
not
be used for opera-
tional purposes until it has been updated
to
a current status.
m!(iv
blank)
\
CESSNA
SECTION 1
MODEL 172M GENERAL
SECTION
1
GENERAL
TABLE
OF
CONTENTS
Page
Three
View . . .
1-2
Introduction . . .
1-3
Descriptive
Data.
1-3
Engine .
1-3
Propeller
. .
1-3
Fuel
. . . •
1-3
enl . . . . . 1-4
Maximum
Certificated
Weights
1-5
Standard
Airplane
Weights
1-5
Cabin and
Entry
Dimensions.
.
1-5
Baggage Space and
Entry
Dimensions.
1-5
SpecifiC Loadings. . . . . . . . . .
1-5
Symbols, Abbreviations and
Terminology.
1-6
General
Airspeed
Terminology and
Symbols.
1-6
. . . . • . .
1-6
Meteorological
Terminology.
Engine Power Terminology . . . . . . . .
1-7
Airplane
Performance
and
Flight
Planning Terminology
1-7
Weight and Balance
Terminology.
. . . • . . . . . .
1-7
1-1
/
SECTION 1
CESSNA
GENERAL
MODEL 172M
NOTES;
t.
Wing
span
shown
with strobe lights
installed.
2.
Maximum height shown with nose
gear depressed,
all
tires and nose
strut
properly tnflated, and trashing
beacon installed,
3.
Wheel
'.ase length
is
65",
4.
Propeller ground clearance
is
11
314",
6.
Wing
area
is
174 square feet.
6. Minimum turning radius l*pivGt point
to
out.b09rd
wino
tip)
is
21'
5%".
PIVOT POINT PIVOT POINT
* *
36'
Figure
1-1.
Three
View
1-2
CESSNA
SECTION 1
MODEL 172M
GENERAL
INTRODUCTION
This
handbook
contains 9 sections,
and
includes
the
material
required
to
be
furnished
to
the
pilot
by
CAR
Part
3.
It
also
contains
supplemental
data
supplied
by
Cessna
Aircraft
Company.
Section 1
provides
basic
data
and
information
of
general
interest.
It
also
contains definitions
or
explanations
of
symbols,
abbreviations,
and
terminology
commonly
used.
DESCRIPTIVE
DATA
ENGINE
Number of
Engines:
1.
Engine
Manufacturer:
A vco Lycoming.
Engine Model
Number:
0-320-E20.
Engine Type:
Normally-aspirated,
direct-drive,
air-cooled,
horizontally-
opposed,
carburetor
equipped,
four-cylinder
engine with 320 cu. in.
displacement.
Horsepower
Rating and Engine Speed: 150
rated
BHP
at
2700 RPM.
PROPELLER
Propeller
Manufacturer:
McCauley
Accessory
Division.
Propeller
Model
Number:
lC160/0TM7553.
Number
of
Blades:
2.
Propeller
Diameter,
Maximum:
75
inches.
Minimum: 74
inches.
Propeller
Type:
Fixed
pitch.
FUEL
Fuel
Grade
(and Color): 80/87 Minimum
Grade
Aviation
Fuel
(red).
Alternate
fuels
which
are
also
approved
are:
100/130 Low Lead
AVGAS
(green). (Maximum
lead
content of 2
cc
per
gallon. )
100/130
Aviation
Grade
Fuel
(green). (Maximum
lead
content of
4.
6
cc
per
gallon. )
NOTE
When
substituting a higher
octane fuel, low
lead
AVGAS
100 should be
used
whenever
possible
since
it
will
result
in
less
lead
contamination of the engine.
1-3
1-4
SECTION 1
CESSNA
GENERAL
MODEL 172M
Fuel
Capacity:
Standard
Tanks:
Total
Capacity: 42
gallons.
Total
Capacity
Each
Tank:
21
gallons.
Total
Usable:
38
gallons.
Long Range
Tanks:
Total
Capacity:
52
gallons.
Total
Capacity
Each
Tank:
26
gallons.
Total
Usable:
48
gallons.
NOTE
To
ensure
maximum
fuel
capacity
when refueling, place
the fuel
selector
valve in
either
LEFT
or
RIGHT
posi-
tion to
prevent
cross-feeding.
OIL
Oil
Grade
(Specification):
:M1L-L-6082 Aviation
Grade
Straight
Mineral
Oil: Use to
replenish
supply during
first
25
hours
and
at
the
first
25-hour
oil
change.
Continue to
use
until a total
of
50
hours
has
accumulated
or
oil
consumption
has
stabilized.
NOTE
The
airplane
was
delivered
from
the
factory
with a
corro-
sion
preventive
aircraft
engine oil.
This
oil
should be
drained
after
the
first
25
hours
of
operation.
:M1L-L-22851
Ashless
Dispersant
Oil:
This
oil
must
be
used
after
first
50
hours
or
oil
consumption
has
stabilized.
Recommended
Viscosity
For
Temperature
Range:
SAE
50
aoove
t6°C
(60°F).
SAE
IOW30
or
SAE
30 between
-18°C
(O°F) and 21°C (70°F).
SAE
10W30
or
SAE
20 below -12°C(10°F).
NOTE
Multi-viscosity
oil
with a
range
of
SAE
10W30
is
recom-
mended
for
improved
starting
in cold
weather.
Oil Capacity:
Sump:
8
Quarts.
Total: 9 Quarts.
CESSNA
SECTION 1
MODEL 172M
GENERAL
MAXIMUM
CERTIFICATED
WEIGHTS
Takeoff,
Normal
Category:
2300
lbs.
Utility Category: 20001bs.
Landing, Normal Category: 23001bs.
utility
Category: 2000
lbs.
Weight
in
Baggage
Compartment,
Normal
Category:
Baggage
Area
1 (or
passenger
on
child's
seat)-Station
82 to 108:
120 lbs. See note below.
Baggage
Area
2 -Station 108 to 142:
50
lbs. See note below.
NOTE
The maximum combined weight capacity
for
baggage
areas
1 and 2
is
120 Ibs.
Weight in Baggage
Compartment,
Utility
Category:
In
this
category,
the
baggage
compartment
and
rear
seat
must
not be occupied.
STANDARD
AIRPLANE
WEIGHTS
Standard Empty Weight, Skyhawk: 1387 lbs.
Skyhawk
ll:
1412 lbs.
Maximum Useful Load:
Skyhawk:
Normal
Category
913
ths.
Utilit!
Category
6 3
lbS.
Skyhawk
II:
8881bs.
588
Ibs.
CABIN AND
ENTRY
DIMENSIONS
Detailed dimensions of the cabin
interior
and
entry
door openings
are
illustrated
in Section
6.
BAGGAGE SPACE AND
ENTRY
DIMENSIONS
Dimensions of the baggage
area
and baggage door opening
are
illus-
trated
in
detail
in Section
6.
SPECIFIC
LOADINGS
Wing Loading:
13.2
lbs.
/sq.
ft.
Power
Loading: 15. 3 Ibs.
/hp.
1-5
1-6
SECTION 1
CESSNA
GENERAL
MODEL
172M
SYMBOLS,
ABBREVIATIONS
AND
TERMINOLOGY
GENERAL
AIRSPEED
TERMINOLOGY AND SYMBOLS
KCAS
Knots
Calibrated
Airspeed
is
i!1dicated
airspeed
corrected
for
position and
instrument
error
and
expressed
in knots.
Knots
calibrated
airspeed
is
equal to KTAS in
standard
at-
mosphere
at
sea
level.
KIAS
Knots Indicated
Airspeed
is
the
speed
shown on the
airspeed
indicator
and
expressed
in knots.
KTAS
Knots
True
Airspeed
is
the
airspeed
expressed
in knots
rel-
ative
to undisturbed
air
which
is
KCAS
corrected
for
altitude
and
temperature.
Maneuvering Speed
is
the maximum
speed
at
which you
may
use
abrupt
control
travel.
Maximum
Flap
Extended Speed
is
the highest
speed
permis-
sible
with wing flaps in a
prescribed
extended position.
Maximum
Structural
Cruising
Speed
is
the
speed
that
should
not be exceeded except in smooth
air,
then only with caution.
Never Exceed Speed
is
the
speed
limit
that
may
not be
ex-
ceeded
at
any time.
stalling
Speed
or
the minimum
steady
flight
speed
at
which
the
airplane
is
controllable.
Stalling Speed
or
the minimum
steady
flight
speed
at
which
Vs
o
the
airplane
is
controllable
in the landing configuration
at
the
most
forward
center
of
gravity.
Best
Angle-oi-Climb
Speed
is
the
speed
wliich
results
in the
greatest
gain of
altitude
in a given
horizontal
distance.
Vy
Best
Rate-oi-Climb
Speed
is
the speed which
results
in the
greatest
gain in
altitude
in a given time.
METEOROLOGICAL TERMINOLOGY
OA
T Outside A
ir
Temperature
is
the
free
air
static
tempera~re.
It
is
expressed
in
either
degrees
Celsius
(formerly
CentI-
grade)
or
degrees
Fahrenheit.
CESSNA
SECTION 1
MODEL
172M
GENERAL
Standard
Temperature
Pressure
Altitude
Standard
Temperature
is
15°C
at
sea
level
pressure
altitude
and
decreases
by 2b C
for
each
1000
feet
of altitude.
Pressure
Altitude
is
the
altitude
read
from
an
altimeter
when the
barometric
subscale
has
been
set
to 29. 92
inches
of
mercury
(1013 mb).
ENGINE POWER TERMINOLOGY
BHP
Brake
Horsepower
is
the power developed by the engine.
RPM Revolutions
Per
Minute
is
engine speed.
Static
Static
RPM
is
engine
speed
attained
during a
full-throttle
en-
RPM
gine
runup
when the
airplane
is
on the ground
and
stationary.
AIRPLANE
PERFORMANCE AND
FLIGHT
PLANNING TERMINOLOGY
Demon- .Demonstrated
Crosswind
Velocity
is
the velocity
of
the
cross-
strated
wind component
for
which adequate
control
of the
airplane
Crosswind
during takeoff and landing
was
actually
demonstrated
during
Velocity
certification
tests.
The
value shown in not
considered
to be
limiting.
Usable
Fuel
Usable
Fuel
is
the fuel
available
for
flight planning.
Unusable
Fuel
GPH
NMPG
g
Unusable
Fuel
is
the quantity of
fuel
that can not be
safely
used
in flight.
Gallons
Per
Hour
is
the amount
of
fuel (in gallons)
consumed
per
hour.
Nautical
Miles
Per
Gallon
is
the
distance
(in
nautical
miles)
which can be
expected
per
gallon
of
fuel
consumed
at a spe-
cific engine
power
setting
and/or
flight configuration.
£
is
acceleration
due to
gravity.
WEIGHT
AND BALANCE TERMINOLOGY
Reference
Reference
Datum
is
an
imaginary
vertical
plane
from
which
Datum
all
horizontal
distances
are
measured
for
balance
purposes.
Station Station
is
a location along the
airplane
fuselage
given in
terms
of the
distance
from
the
reference
datum.
1-7
1-8
SECTION 1
GENERAL
Arm
Moment
Center
of
Gravity
(C.
G.)
C.G.
Arm
C.
G.
Limits
Standard
Empty
Weight
CESSNA
MODEL 172M
Arm
is
the
horizontal
distance
from
the
reference
datum to
theCenter
of
gravity
(C.
G.)
of
an
item.
Moment
is
the
product
of the weight of
an
item
multiplied
by
its
arm.
(Moment divided by
the
constant
1000
is
used
in
this
handbook to
simplify
balance
calculations
by reducing
the
number
of
digits.
)
Center
of
Gravity
is
the point
at
which an
airplane,
or
equip-
ment,
would
balance
if
suspended.
Its
distance
from
the
reference
datum
is
found by dividing the
total
moment
by the
total
weight of the
airplane.
Center
of
Gravity
Arm
is
the
arm
obtained
by adding the
airplane's
individual
moments
and
dividing the
sum
by the
total
weight.
Center
of
Gravity
Limits
are
the
extreme
center
of
gravity
locations
within which the
airplane
must
be
operated
at
a
given weight.
Standard
Empty
Weight
is
the
weight
of a standard
airplane,
including
unusable
fuel,
full
operating
fluids and full engine
oil.
Basic
Empty
Basic
Empty
Weight
is
the
standard
empty
weight
plus
the
Weight
Useful
Load
Gross
(Loaded)
Weight
Maximum
Takeoff
Weight
Maximum
Landing
Weight
Tare
weight of
optional
equipment.
Useful
Load
is
the
difference
between takeoff weight
and
the
basic
empty
weight.
Gross
(Loaded) Weight
is
the loaded weight of
the
airplane.
Maximum
Takeoff Weight
is
the
maximum
weight
approved
for
the
start
of
the
takeoff
run.
Maximum Landing Weight
is
the
maximum
weight
approved
for
the landing touchdown.
Tare
is
the weight
of
chocks,
blocks,
stands,
etc.
used
Wilen
weighing
an
airplane,
and
is
included
in the
scale
read-
ings.
Tare
is
deducted
from
the
scale
reading
to obtain
the
actual
(net)
airplane
weight.
CESSNA
SECTION 2
MODEL 172M
LIMITA TIONS
SECTION
2
LIMITATIONS
TABLE
OF
CONTENTS
Page
Introduction • • . . • . . •
2-3
Airspeed
Limitations
. . . .
2-4
Airspeed
Indicator
Markings
2-5
Power
Plant
Limitations
• .
2-5
Power
Plant
Instrument
Markings
2-6
Weight
Limits
• • . • .
2-6
Normal
Category.
.
2-6
utility
Category . • •
2-7
Center
of
Gravity
Limits
2-7
Normal
Category.
•
2-7
Utility Category •
2-7
Maneuver
Limits
2-7
Normal
Category •
2-7
Utility Category .
2-7
Flight
Load
Factor
Limits
2-8
Normal
Category
2-8
Utility Category • • •
2-8
Kinds of
Operation
Limits
•
2-9
Fuel
Limitations
2-9
Placards
•.•..•..
2-10
2-1/(2-2
blank)
CESSNA
SECTION 2
MODEL 172M
LIMITA TIONS
INTRODUCTION
Section 2 includes
operating
limitations,
instrument
markings,
and
basic
placards
necessary
for
the
safe
operation
of the
airplane,
its
engine,
standard
systems
and
standard
eqUipment. The
limitations
included in
this
section
have been
approved
by the
Federal
Aviation
Administration.
When
applicable,
limitations
associated
with optional
systems
or
eqUip-
ment
are
included in Section 9.
NOI'E
The
airspeeds
listed
in the
Airspeed
Limitations
chart
(figure 2-1) and the
Airspeed
Indicator
Markings
chart
(figure 2-2)
are
based
on
Airspeed
Calibration
data
shown
in Section
5 with the
normal
static
source.
If
the
alter-
nate
static
source
is
being
used,
ample
margins
should
be
observed
to allow
for
the
airspeed
calibration
varia-
tions between the
normal
and
alternate
static
sources
as
shown in Section
5.
Your
Cessna
is
certificated
under
FAA
Type
Certificate
No. 3A12
as
Cessna
Model No. 172M.
2-3
2-4
SECTION 2
CESSNA
LIMITATIONS
MODEL 172M
AIRSPEED
LIMITATIONS
Airspeed
limitations
and
their
operational
significance
are
shown
in
figure
2-1.
SPEED
KCAS
KIAS
REMARKS
VNE
Never Exceed Speed
158
160
Do
not
exceed this speed
in
any operation.
VNO
Maximum Structural
Cruising Speed
126 128
Do
not
exceed this speed
except
in
smooth air, and
then only with caution.
VA
Maneuvering Speed;
2300 Pounds
1950 Pounds
1600 Pounds
96
88
80
97
89
80
Do
not make full or abrupt
control movements above
this
speed.
VFE
Maximum Flap Extended
Speed
86
85
Do
not
exceed this speed
with flaps down.
Maximum Window Open
Speed
158
160
Do
not
exceed this speed
with windows open.
Figure
2-1.
Airspeed
Limitations
CESSNA
SECTION 2
MODEL 172M
LIMITATIONS
AIRSPEED
INDICATOR
MARKINGS
Airspeed
indicator
markings
and
their
color
code
significance
are
shown in
figure
2-2.
MARKING
KIAS VALUE
OR
RANGE
SIGNIFICANCE
White Arc
41 -85
Full Flap Operating
Range.
Lower
limit
is
maximum weight
VSo
in
landing configuration. Upper
limit
is
maximum
speed
permissible
with
flaps extended.
Green
Arc
47
128
Normal Operating
Range.
Lower
limit
is
maximum weight
Vs
with
flaps retracted. Upper
limit
is
maxi-
mum structural cruising
speed.
Yellow Arc
128 - 160 Operations must
be
\=onducted
with
caution
and
only in smooth air.
Red
Line
160
Maximum
speed
for
all operations.
Figure
2-2.
Airspeed
Indicator
Markings
POWER
PLANT
LI
MIT
AllONS
Engine
Manufacturer:
Avco Lycoming.
Engine Model Number:
0-320-E2D.
Engine Operating
lJ.mits
for
Takeoff and Continuous
Operations:
Maximum
Power:
150 BHP.
Maximum Engine Speed: 2700 RPM.
NOTE
The
static
RPM
range
at
full
throttle
(carburetor
heat
off)
is
2300 to 2420 RPM.
Maximum
Oil
Temperature:
l1SoC (245°F).
Oil
Pressure,
Minimum:
25
psi.
Maximum: 100
psi.
Propeller
Manufacturer:
McCauley
Accessory
Division.
Propeller
Model
Number:
1C160/DTM7553.
Propeller
Diameter,
Maximum: 75 inches.
Minimum:
74
inches.
2-5
2-6
SECTION 2
CESSNA
LIMITATIONS
MODEL
172M
POWER
PLANT
INSTRUMENT
MARKINGS
Power
plant
instrument
markings
and
their
color
code
significance
are
shown in
figure
2-3.
INSTRUMENT
RED
LINE GREEN ARC YELLOW ARC
RED
LINE
MINIMUM
LIMIT
NORMAL
OPERATING
CAUTION
RANGE
MAXIMUM
LIMIT
Tachometer
At
Sea
Level
At
5000 Ft.
At
10,000 Ft.
Oil Temperature
Oil
Pressure
Carburetor
Air
Temperature
- --
---
-
-
-
25
psi
- -
2200 -
2500
RPM
2200 -
2600
RPM
2200
2700
RPM
100°-245°F
60-90
psi
-- -
- -
--
- --
--
-
-
-15°
to
5°C
2700
RPM
2700
RPM
2700
RPM
245°F
100
psi
-- -
Figure
2-3.
Power
Plant
Instrument
Markings
WEIGHT
LIMITS
NORMAL
CATEGORY
Maximum
Takeoff
Weight: 2300
lbs.
Maximum
Landing Weight: 2300
lbs.
Maximum
Weight in Baggage
Compartment:
Baggage
Area 1 (or
passenger
on
child's
seat)-Station
82
to
108:
120
lbs.
See
note
below.
Baggage
Area 2 -Station
108 to 142: 50
lbs.
See
note
below.
NOTE
The
maximum
combined
weight
capacity
for
baggage
areas
1
and 2 is
120
lbs.
CESSNA
SECTION 2
MODEL 172M
LIMITATIONS
UTILITY CATEGORY
Maximum Takeoff Weight: 2000
lbs.
Maximum Landing Weight: 2000
lbs.
Maximum Weight
in
Baggage
Compartment:
In
the
utility
category.
the
baggage
compartment
and
rear
seat
must
not be occupied.
CENTER
OF
GRAVITY
LIMITS
NORMAL
CATEGORY
Center
of
Gravity
Range:
Forward:
35.0
inches aft of datum
at
1950 lbs.
or
less,
with
straight
line
variation
to 38. 5
inches
aft of datum
at
2300 Ibs.
Aft:
47.3
inches
aft
of datum
at
all
weights.
Reference
Datum:
Front
face of firewall.
UTILITY
CATEGORY
Center
of
Gravity
Range:
Forward:
35.0
inches
aft of datum
at
1950 lbs.
or
less,
with
straight
line
variation
to 35. 5
inches
aft
of datum at 2000 lbs.
Aft:
40.5
inches
aft of datum
at
all
weights.
Reference
Datum:
Front
face of
firewall.
MANEUVER
LIMITS
NORMAL
CATEGORY
This
airplane
is
certificated
in both the
normal
and
utility
category.
The
normal
category
is
applicable to
aircraft
intended
for
non-aerobatic
operations.
These
include any
maneuvers
incidental
to
normal
flying,
stalls
(except whip
stalls)
and
turns
in which the
angle
of bank
is
not
more
than
60
0
•
UTILITY
CATEGORY
This
airplane
is
not designed
for
purely
aerobatic
flight. However,
in the
acquisition
of
various
certificates
such
as
commercial
pilot,
instru-
ment
pilot and flight
instructor,
certain
maneuvers
are
required
by the
FAA.
All
of
these
maneuvers
are
permitted
in
this
airplane
when
oper-
ated
in the
utility
category.
In the
utility
category,
the baggage
compartment
and
rear
seat
must
2-7
2-8
SECTION 2
CESSNA
LIMITA TIONS
MODEL 172M
not be occupied.
No
aerobatic
maneuvers
are
approved except those
list-
ed
below:
MANEUVER
RECOMMENDED ENTRY SPEED*
Chandelles .
·
...
105 knots
Lazy
Eights
·
...
105 knots
Steep
Turns
· .
..
95
knots
Spins
...
Slow
Deceleration
Stalls (Except Whip
Stalls).
Slow
Deceleration
*Abrupt
use
of the
controls
is
prohibited above
97
knots.
Aerobatics
that
may
impose
high loads should not be attempted. The
important
thing to
bear
in mind in flight
maneuvers
is
that the
airplane
is
clean in aerodynamic design and will build
up
speed
quickly with the nose
down.
Proper
speed
control
is
an
essential
requirement
for
execution of
any maneuver, and
care
should always be
exercised
to avoid
excessive
speed
which in
turn
can impose
excessive
loads. In the execution of
all
maneuvers,
avoid
abrupt
use
of controls. Intentional spins with flaps
ex-
tended
are
prohibited.
FLIGHT
LOAD
FACTOR
LIMITS
NORMAL CATEGORY
Flight
Load
Factors
(Gross Weight - 2300
lbs.)
*Flaps
Up
..................
+3.
Sg, -1. 52g
*Flaps
Down
.................
+3.
Og
*The design load
factors
are
150%
of the above, and in
all
cases,
the
structure
meets
or
exceeds design loads.
UTILITY
CATEGORY
Flight Load
Factors
(Gross
Weight - 2000 lbs. )
*Flaps
Up
. . . • . . . . . . . . . . . . . . +4.4g, -1. 76g
*Flaps
Down
.................
+3.0g
*The design load
factors
are
150%
of the above, and in
all
cases,
the
structure
meets
or
exceeds design loads.
CESSNA
SECTION 2
MODEL 172M
LIMITA TIONS
KINDS
OF
OPERATION
LIMITS
The airpJane
is
equipped
for
day VFR and may be equipped
for
night
VFR
and/or
IFR
operations.
FAR
Part
91
establishes
the minimum
re-
quired
instrumentation
and equipment
for
these operations. The
refer-
ence to types of flight
operations
on the
operating
limitations
placard
re-
flects
equipment
installed
at
the
time
of
Airworthiness
Certificate
issuance.
Flight into known icing conditions
is
prohibited.
FUEL
LIMITATIONS
2 Standard Tanks:
21
U.
S.
gallons each.
Total
Fuel: 42
U.
S.
gallons.
Usable
Fuel
(all flight conditions):
38
U.
S.
gallons.
Unusable Fuel:
4.0
U.
S.
gallons.
2 Long Range
Tanks:
26
U.
S.
gallons each.
Total
Fuel:
52
U.
S. gallons.
Usable
Fuel
(all flight conditions): 48
U.
S.
gallons.
Unusable
Fuel:
4. 0
U.
S.
gallons.
NOTE
To
ensure
maximum fuel capacity when refueling, place
the fuel
selector
valve in
either
LEFT
or
RIGHT
posi-
tion to
prevent
cross-feeding.
NOTE
Takeoff and land with the fuel
selector
valve handle in
the BOTH position.
Fuel
Grade
(and Color): 80/87 Minimum
Grade
Aviation
Fuel
(red).
Alternate
fuels which
are
also
approved
are:
100/130 Low Lead
AVGAS
(green). (Maximum lead content of 2
cc
per
gallon. )
100/130 Aviation
Grade
Fuel
(green). (Maximum lead content of
4.
6 cc
per
gallon. )
NOTE
When substituting a
higher
octane fuel, low lead
AVGAS
100 should be
used
whenever
possible
since
it
will
result
in
less
lead
contamination of the engine.
2-9
2-10
SECTION 2
CESSNA
LIMITA TIONS
MODEL 172M
PLACARDS
The
following
information
is
displayed
in
the
form
of
composite
or
individual
placards.
(1) In
full
view
of
the
pilot:
(The
"DA
Y-NIGHT-VFR-IFR"
entry,
shown on the
example
below,
will
vary
as
the
airplane
is
equipped.)
This
airplane
must
be
operated
in
compliance
with the
operating
limitations
as
stated
in
the
form
of
placards,
markings,
and
manuals.
---------------MAXIMUMS--------------Normal
Category
Utility
Category
MANEUVERING
SPEED
(lAS) 97
knots.
97 knots
GROSS WEIGHT • • • . . 2300 Ibs.
20001bs.
FLIGHT LOAD FACTOR
Flaps
Up
+3,8,
-1.
52
+4.4,
-1.
76
Flaps
Down
+3,0 , •.
+3.0
Normal
Category -No
acrobatic
maneuvers
including
spins
approved.
Utility
Category
- Baggage
compartment
and
rear
seat
must
not
be
occupied.
--NO
ACROBATIC MANEUVERS
APPROVED-
EXCEPT
THOSE LISTED BELOW
Maneuver
Recm.
Entry
Speed
M~~
Recm.
Entry
Speed
Chandelles.
.105
knots
Spins
..
. Slow
Deceleration
Lazy
Eights
.105
knots
Stalls
(except
Steep
Turns
• 95
knots
whip
stalls)
Slow
Deceleration
Altitude
loss
in
stall
recovery --180 feet.
Abrupt
use
of
controls
prohibited
above
97 knots.
Spin
Recovery:
opposite
rudder -forward
elevator -neutralize
controls.
Intentional
spins
with
flaps
extended
are
prohibited.
Flight
into known icing
conditions
prohibited.
This
airplane
is
certified
for
the following flight
operations
as
of
date
of
original
airworthiness
certificate:
DA
Y - NIGHT -
VFR -IFR
CESSNA
SECTION 2
MODEL 172M LIMITATIONS
(2)
Forward
of
fuel
selector
valve:
BOTH TANKS
ON
FOR
TAKEOFF
& LANDING
(3)
On the fuel
selector
valve
(standard
tanks):
BOTH -
38
GAL.
ALL
FLIGHT ATTITUDES
LEFT
- 19 GAL.
LEVEL
FLIGHT ONLY
RIGHT - 19 GAL. LEVEL FLIGHT ONLY
OFF
On the
fuel
selector
valve (long
range
tanks):
BOTH - 48 GAL.
ALL
FLIGHT ATTITUDES
LEFT
- 24 GAL. LEVEL FLIGHT ONLY
RIGHT - 24 GAL.
LEVEL
FLIGHT ONLY
OFF
(4)
Near
fuel
tank
filler
cap
(standard
tanks):
FUEL
80/87 MIN. GRADE AVIATION GASOLINE
CAP.
21
U.
S. GAL.
Near
fuel
tank
filler
cap
(long
range
tanks):
FUEL
80/87
MIN. GRADE AVIATION GASOLINE
CAP.
26
U.
S. GAL.
2-11
2-12
SECTION 2
CESSNA
LIMITATIONS
MODEL
172M
(5)
Near
flap indicator:
Avom SLIPS WITH
FLAPS
EXTENDED
(6)
In
baggage compartment:
120 POUNDS MAXIMUM
BAGGAGE AND/OR AUXILIARY PASSENGER
FORWARD
OF
BAGGAGE DOOR LATCH
50 POUNDS MAXIMUM
BAGGAGE
AFT
OF
BAGGAGE DOOR LATCH
MAXIMUM 120 POUNDS COMBINED
FOR ADDITIONAL LOADING INSTRUCTIONS
SEE WEIGHT AND BALANCE DATA
(7)
On
the
instrument
panel
near
over-voltage
light:
HIGH VOLTAGE
CESSNA
SECTION 3
MODEL 172M
EMERGENCY PROCEDURES
SECTION
3
EMERGENCY
PROCEDURES
TABLE
OF
CONTENTS
Page
Introduction . . . . • . . . .
3-3
Airspeeds
For
Safe
Operation
.
3-3
OPERA TIONAL CHECKUSTS
Engine
Failures
• . . . . . . • • . • . . .
3-3
Engine
Failure
During Takeoff
Run.
• . .
3-3
Engine
Failure
Immediately
After
Takeoff .
3-3
Engine
Failure
During
Flight
. • . . . .
3-4
Forced
Landings.
. . . . • . . . . . . . .
3-4
Emergency
Landing Without Engine
Power
3-4
Precautionary
Landing With Engine
Power
3-4
Ditching.
. . . . . . . . • • . .
3-5
Fires
. . . . . . . . . . . . • . . .
3-5
Engine
Fire
During
Start
On Ground
3-5
Engine
Fire
In
Flight
. .
3-6
Electrical
Fire
In
Flight
3-6
Cabin
Fire
.....
.
3-6
Wing
Fire
•.•....
3-7
Icing . . . . . • . . . . .
3-7
Inadvertent
Icing
Encounter
. • . . • . . . . . . •
3-7
Static Source Blockage
(Erroneous
Instrument
Reading
Suspected).
. . . • . . . . . . . .
3-8
Landing With A
Flat
Main
Tire
......•
3-8
Electrical
Power
Supply System Malfunctions
3-8
Over-Voltage
Light
Illuminates
• . • .
3-8
Ammeter
Shows
Discharge
. . • . . .
3-8
AMPLIFIED PROCEDURES
Engine
Failure.
.
3-9
Forced
Landings .
3-10
3-1
3-2
SECTION 3
EMERGENCY PROCEDURES
TABLE
OF
CONTENTS
(Continued)
Landing Without
Elevator
Control
. . . . . . . . • . .
Fires
..•....................
Emergency
Operation
In
Clouds (Vacuum
System
Failure).
Executing A 1800 Turn
In Clouds
..
Emergency
Descent
Through Clouds
Recovery
From A Spiral
Dive
Flight
In
Icing Conditions . . . • . • .
Static
Source
Blocked
.....•
Spins
............•...
Rough Engine
Operation
Or
Loss
Of
Power
Carburetor
Icing • .
Spark
Plug Fouling
........
.
Magneto Malfunction . . . . . • • .
Low
Oil
Pressure
. . . . . . . . .
Electrical
Power
Supply
System
Malfunctions
Excessive
Rate
Of
Charge
.
insufficient
Rate
Of
Charge
. • . • . .
CESSNA
MODEL 172M
Page
3-10
3-10
3-11
3-11
3-11
3-12
3-12
3-12
3-13
3-13
3-13
3-14
3-14
3-14
3-15
3-15
3-15
CESSNA
SECTION 3
MODEL 172M
EMERGENCY PROCEDURES
INTRODUCTION
Section 3
provides
checklist
and
amplified
procedures
for
coping with
emergencies
that
may
occur.
Emergencies
caused
by
airplane
or
engine
maJiunctions
are
extremely
rare
if
proper
preflight
inspections
and
main-
tenance
are
practiced.
Enroute
weather
emergencies
can
be
minimized
or
eliminated
by
careful
flight planning
and
good judgement when
unexpect-
\
ed
weather
is
encountered.
However, should
an
emergency
arise
the
basic
guidelines
described
in
this
section
should
be
considered
and
applied
as
necessary
to
correct
the
problem.
Emergency
procedures
associated
with
the
ELT
and
other
optional
systems
can
be
found
in
Section
9.
AIRSPEEDS FOR
SAFE
OPERATION
Engine
Failure
After
Takeoff:
Wing
Flaps
Up
. . 65 KIAS
Wing
Flaps
Down • 60 KIAS
Maneuvering Speed:
2300
Lbs
.
97
KIAS
1950
Lbs
.
89 KIAS
1600
Lbs
...
80
KIAS
Maximum Glide:
2300
Lbs
...
65 KIAS
Precautionary
Landing With Engine
Power
60 KIAS
Landing Without Engine
Power:
Wing
Flaps
Up
. . . • • . .
65
KIAS
Wing
Flaps
Down.
. . . . .
60
KIAS
OPERATIONAL CHECKLI
STS
ENGINE FAILURES
ENGINE
fAILURE
DURING
TAKEOff
RUN
(1)
Throttle --IDLE.
(2)
Brakes --APPLY.
(3) Wing
Flaps --RETRACT.
(4)
Mixture --IDLE
CUT-OFF.
(5) Ignition Switch
--
OFF.
ENGINE
FAILURE
IMMEDIATELY
AFTER
TAKEOff
(1)
Airspeed --65
KIAS (flaps UP).
60
KIAS
(flaps
DOWN).
3-3
3-4
SECTION 3
CESSNA
EMERGENCY PROCEDURES
MODEL 172M
(2)
Mixture --IDLE
CUT-OFF.
(3)
Fuel
Selector
Valve --OFF.
(4) Ignition Switch --OFF.
(5) Wing
Flaps --AS
REQUIRED.
(6)
Master
Switch --OFF.
ENGINE
FAILURE
DURING
FLIGHT
(1)
Airspeed
--
65
KIAS.
(2)
Carruretor
Heat --ON.
(3)
Fuel
Selector
Valve --BOTH.
(4)
Mixture --RICH.
(5)
Ignition Switch --BOTH (or START
if
propeller
is
stopped).
(6)
Primer --IN and LOCKED.
FORCED
LANDINGS
EMERGENCY
LANDING
WITHOUT
ENGINE
POWER
(1)
Airspeed --65 KlAS (flaps UP).
60 KlAS (flaps DOWN).
(2)
Mixture --IDLE
CUT-OFF.
(3)
Fuel
Selector
Valve --OFF.
(4) Ignition Switch --OFF.
(5) Wing
Flaps --AS
REQUJRED (400 recommended).
(6)
Master
Switch --OFF.
(7)
Doors --UNLATCH PRIOR TO TOUCHDOWN.
(8) Touchdown
--
SLIGHTLY TAIL LOW.
(9)
Brakes --APPLY
HEAVILY.
PRECAUTIONARY
LANDING
WITH
ENGINE
POWER
(1) Wing
Flaps --20°.
(2)
Airspeed --60 KlAS.
(3)
Selected
Field --FLY
OVER, noting
terrain
and
obstructions,
then
retract
flaps
upon
reaching a safe
altitude
and
airspeed.
(4) Radio and
Electrical
Switches --OFF.
(5) Wing
Flaps --40° (on final
approach).
(6)
Airspeed --60 KlAS.
(7)
Master
Switch --OFF.
(8)
Doors --UNLATCH PRIOR TO TOUCHDOWN.
(9) Touchdown
--
SLIGHTLY TAIL LOW.
(10) Ignition Switch
--
OFF.
(11)
Brakes --APPLY
HEAVILY.
CESSNA
SECTION 3
MODEL 172M
EMERGENCY PROCEDURES
DITCHING
(1)
Radio --TRANSMIT
MAYDAY
on 121. 5 MHz, giving
location
and
intentions.
(2)
Heavy
Objects
(in baggage
area) --SECURE
or
JETTI&:>N.
(3)
Flaps --20
0
-
40
0
•
(4)
Power --ESTABLISH 300 FT/MIN DESCENT
at
55
KIAS.
(5)
Approach --High Winds, Heavy
Seas --INTO THE WIND.
Light Winds, Heavy Swells
--
PARALLEL
TO
SWELLS.
NOTE
If
no
power
is
available,
approach
at
65
KIAS
with
flaps
up
or
at
60
KIAS with
10°
flaps.
(6)
Cabin
Doors --UNLA
TCH.
(7)
Touchdown --LEVEL
ATTITUDE AT ESTABLISHED DESCENT.
(8)
Face --CUSHION
at
touchdown with folded
coat
or
seat
cushion.
(9)
Airplane --EVACUATE through cabin
doors.
If
necessary,
open window and flood cabin
to
equalize
pressure
so
doors
can
be
opened.
(10) Life
Vests
and
Raft
--
INFLATE.
FIRES
ENGINE
FIRE
DURING
START
ON
GROUND
(1)
Cranking --CONTINUE,
to
get a start
which
would
suck
the
flames
and
accumulated
fuel
through
the
carburetor
and
into
the
engine.
If
eng ine
starts:
(2)
Power --1700 RPM
for
a few
minutes.
(3) Engine --SHUTDOWN
and
inspect
for
damage.
If
engine
fails
to
start:
(4)
Throttle --FULL
OPEN.
(5)
Mixture --IDLE
CUT-OFF.
(6)
Cranking --CONTINUE
for
two
or
three
minutes.
(7)
Fire
Extinguisher --OBTAIN (have
ground
attendants
obtain
if
not
installed).
(8)
Engine --SECURE.
a.
Master
SWitch --OFF.
3-5
3-6
SECTION 3 CESSNA
EMERGENCY PROCEDURES MODEL 172M
b. Ignition Switch
--
OFF.
c.
Fuel
Shutoff Valve --OFF.
(9)
Fire --EXTINGUISH using
fire
extinguisher,
seat
cushion, wool
blanket,
or
dirt.
If
practical
try
to
remove
carburetor
air
filter
if
it
is
ablaze.
(10)
Fire
Damage --INSPECT,
repair
damage
or
replace
damaged
components
or
wiring
before
conducting
another
flight.
ENGINE
FIRE
IN
FLIGHT
(1) Mixture --IDLE
CUT-OFF.
(2)
Fuel
Selector
Valve --OFF.
(3)
Master
Switch --OFF.
(4) Cabin Heat
and
Air --OFF
(except
overhead
vents).
(5)
Airspeed --100
KIAS
(If
fire
is
not extinguished,
increase
glide
speed
to
find
an
airspeed
which
will
provide
an
incombustible
mixture).
(6)
Forced
Landing --EXECUTE
(as
described
in
Emergency
Land-
ing Without Engine
Power).
ElECTRICAL
FIRE
IN
FLIGHT
(1)
Master
Switch --OFF.
(2)
All
Other
Switches (except ignition switch) --OFF.
(3)
Vents/Cabin
Air/Heat --CLOSED.
(4)
Fire
Extinguisher --ACTIVATE
(if
available).
If
fire
appears
out
and
electrical
power
is
necessary
for
continuance
of flight:
(5)
Master
Switch --ON.
(6)
Circuit
Breakers --CHECK
for
faulty
circuit,
do
not
reset.
(7)
Radio/Electrical
Switches --ON
one
at a time,
with
delay
after
each
until
short
circuit
is
localized.
(8)
Vents/Cabin
Air/Heat --OPEN when
it
is
ascertained
that
fire
is
completely extinguished.
CABIN
FIRE
(1)
Master
Switch --OFF.
(2)
Vents/Cabin
Air/Heat --CLOSED (to avoid
drafts).
(3)
Fire
Extinguisher --ACTIVATE
(if
available).
IWARNING'
After
discharging
an
extinguisher
within a
closed
cabin,
ventilate
the
cabin.
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