Cessna 152 Quick setup guide

~
Cessna,.
152
CESSNA MODEL 152
INFORMATION
MANUAL
.....___~

NOTICE
AT
THE
TIME
OF
ISSUANCE,
THIS
INFOR-
MATION
MANUAL
WAS
AN
EXACT
DUPLI-
CATE OF THE
OFFICIAL
PILOT'S
OPERAT-
ING
HANDBOOK
AND
FAA
APPAOVED
AIRPLANE
FLIGHT
MANUAL
AND
IS
TO
BE
USED
FOR
GENERAL
PURPOSES
ONLY.
IT
WILL
NOT
BE KEPT
CURRENT
AND,
THEREFORE,
CANNOT
BE
USED
AS
A
SUBSTITUTE
FOR THE
OFFICIAL
PILOT'S
OPERATING
HANDBOOK
AND
FAA
APPROVED
AIRPLANE
FLIGHT
MANUAL
INTENDED
FOR
OPERATION
OF
THE
AIR-
PLANE.
CESSNA
AIRCRAFT
COMPANY
1
JULY
1978

PERFORMANCE-
SPECIFICATIONS
CESSNA
MODEL 152
PERFORMANCE SPECIFICATIONS
*SPEED:
Maximum
at
Sea
Level
. . . . . . . . . . . . . . . .
Cruise,
75%
Power
at
8000
Ft
. . . . . . . . . . . . .
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
. . .
24.5
Gallons
Usable
Fuel
75%
Power
at
8000
Ft
...
37.5
Gallons
Usable
Fuel
Maximum
Range
at
10,000
Ft
24.5
Gallons
Usable
Fuel
Maximum
Range
at
10,000
Ft
37.5
Gallons
Usable
Fuel
RATE
OF
CLIMB
AT
SEA
LEVEL
SERVICE
CEILING
. . . . . .
TAKEOFF
PERFORMANCE:
Ground
Roll
. . . . . . . .
Total
Distance
Over
50-Ft
Obstacle
LANDING
PERFORMANCE:
Ground
Roll
. . . . . . . . . . .
Total
Distance
Over
50-Ft
Obstacle
STALL
SPEED
(CAS):
Flaps
Up,
Power
Off
Flaps
Down,
Power
Off
MAXIMUM
WEIGHT:
Ramp
.......
.
Takeoff
or
Landing
. .
STANDARD
EMPTY
WEIGHT:
152
.........
.
152
II
. . . . . . . . .
MAXIMUM
USEFUL
LOAD:
152
........
· ·
152
II
. . . . . . . . .
BAGGAGE
ALLOWANCE
WING
LOADING:
Pounds/Sq
Ft
POWER
LOADING:
Pounds/HP
FUEL
CAP
ACITY:
Total
Standard
Tanks
Long
Range
Tanks
.
OIL
CAPACITY
ENGINE:
Avco
Lycoming
110
BHP
at
2550
RPM
PROPELLER:
Fixed
Pitch,
Diameter
Range
Time
Range
Time
Range
Time
Range
Time
110KNOTS
107
KNOTS
350NM
3.4
HRS
580NM
5.5
HRS
415NM
5.2
HRS
690NM
8.7HRS
715
FPM
14,700
FT
725
FT
1340
FT
475
FT
1200
FT
48
KNOTS
43KNOTS
1675
LBS
1670
LBS
1101
LBS
1133
LBS
574
LBS
542
LBS
120
LBS
10.5
15.2
26
GAL.
39
GAL.
6QTS
O-235-L2C
69
IN.
*Speed
performance
is
shown
for
an
airplane
equipped
with
optional
speed
fairings,
which
increase
the
speeds
by
approximately
2
knots.
There
is
a
corresponding
difference
in
range,
while
all
other
performance
figures
are
unchanged
when
speed
fairings
are
installed.
ii
1
July
1978

INFORMATION
MANUAL
I
CESSNA
AIRCRAFT
COMPANY I
1979 MODEL 152
COPYRIGHT
C 1993
CESSNA
AIRCRAFT
COMPANY
WICHITA,
KANSAS,
USA
Dll36-13-RGI-2500-4/97
Tl
1E
REPRINTING OF THIS
MANUAL
INCORPO-
RATES
INFORMATION
ISSUED
IN
REVISION 1
DATED
31
MARCH
1983 FROM
Tl!E
PILOT'S
OPERATING
HANDBOOK
AND
FAA APPROVED
AIRPLANE FLIGHT
MANUAL.
iii

TABLE OF CONTENTS
CESSNA
MODEL 152
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
iv
1 July 1978

CESSNA
MODEL
152
SECTION 1
GENERAL
TABLE OF
CONTENTS
SECTION
1
GENERAL
Page
Three
View
1-2
Introduction
1-3
Descriptive
Data
1-3
Engine
1-3
Propeller
1-3
Fuel
. . . 1-3
Oil
14
Maximum
Certificated
Weights
1-5
Standard
Airplane
Weights
. 1-5
Cabin
And
Entry
Dimensions
. 1-5
Baggage
Space
Dimensions
. . 1-5
Specific
Loadings
. . . . . . 1-5
Symbols,
Abbreviations
And
Terminology
1-5
General
Airspeed
Terminology
And
Symbols
1-5
Meteorological
Terminology
. . . . . . . 1-6
Engine
Power
Terminology
. . . . . . . . 1-7
Airplane
Performance
And
Flight
Planning
Terminology
1-7
Weight
And
Balance
Terminology
. . . . . . . . . . . 1-7
1
July
1978 1-1

SECTION
1
GENERAL
•------10'-0"----
NOTES:
CESSNA
MODEL 152
1.
Wing
span shown with conical camber wing
tips and strobe
lights
installed. If standard
wing tips without strobe lights are installed,
wing
span
is
32' • 8 1
/2".
Maximum height shown with nose gear
depressed, all tires and nose
strut
prop•
erly inflated and flashing beacon installed.
3.
Wheel
base
length
is
58".
4.
Propeller ground clearance
is
12".
5.
Wing
area
is
159 1/2 square feet.
------33'-4"------+-1•1
Figure
1-1.
Three
View
1-2 1
July
1978

CESSNA
MODEL
152
THIS DATA APPLICABLE ONLY TO AIRPLANES WITH LYCOMING
O-235-L2C ENGINE.
FOR
AIRPLANES WITH ENGINE MODIFIED TO
O-235-N2C,
REFER
TO DATA IN.SECTION 9 SUPPLEMENT.
INTRODUCTION
SECTION 1 I
GENERAL
I
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:
Avco
Lycoming.
Engine
Model
Number:
O-235-L2C.
Engine
Type:
Normally-aspirated,
direct-drive,
air-cooled,
horizontally-
opposed,
carburetor
equipped,
four-cylinder
engine
with
233.3
cu.
in.
displacement.
Horsepower
Rating
and
Engine
Speed:
110
rated
BHP
at
2550
RPM.
PROPELLER
Propeller
Manufacturer:
McCauley
Accessory
Division.
Propeller
Model
Number:
1A103/TCM6958.
Number
of
Blades:
2.
Propeller
Diameter,
Maximum:
69
inches.
Minimum:
67.5
inches.
Propeller
Type:
Fixed
pitch.
FUEL
Approved
Fuel
Grades
(and
Colors):
100LL
Grade
Aviation
Fuel
(Blue).
100
(Formerly
100/130)
Grade
Aviation
Fuel
(Green).
Fuel
Capacity:
Standard
Tanks:
Total
Capacity:
26
gallons.
Total
Capacity
Each
Tank:
13
gallons.
Total
Usable:
24.5
gallons.
1
July
1978
Revision
1 -
31
March
1983
1-3

I
SECTION
1
GENERAL
THIS DATA'APPUCABLE ONLY TO AIRPLANES WITH LYCOMING
0-235-UC
ENGINE.
FOR
AIRPLANES WITH ENGINE MODIFIED TO
O-Z35-N2C,
REFER
TO DATA IN SECTION 9 SUPPLEMENT.
CESSNA
MODEL
152
OIL
Long
Range
Tanks:
Total
Capacity:
39
gallons.
Total
Capacity
Each
Tank:
19.5
gallons.
Total
Usable:
37.5
gallons.
NOTE
Due
to
cross-feeding
between
fuel
tanks,
the
tanks
should
be
re-topped
after
each
refueling
to
assure
maximum
capacity.
Oil
Grade
(Specification):
MIL-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.
MIL-L-22851
Ashless
Dispersant
Oil:
This
oil
must
beused
after
first
50
hours
or
oil
consumption
has
stabilized.
Recommended
Viscosity
for
Temperature
Range:
MIL-L-6082
Aviation
Grade
Straight
Mineral
Oil:
SAE
50
above
16°C (60°F).
SAE
40
between
-1°C (30°F)
and
32°C (90°F).
SAE
30
between
-18°C (0°F)
and
21°c
(70°F).
SAE
20
below
-12°C (10°F).
MIL-L-22851
Ashless
Dispersant
Oil:
SAE
40
or
SAE
50
above
16°C (60°F).
SAE
40
between
-1°C (30°F)
and
32°C (90°F).
$AE
30
or
SAE
40
between
-18°C "(0°F)
and
21°c
(70°F).
SAE
30
below·
-12°c
(10°F).
Oil
Capacity:
Sump:
6
Quarts.
Total:
7
Quarts
(if
oil
filter
installed).
1-4 1
July
1978
Revision
1 -
31
March
1983

CESSNA
MODEL
152
SECTION
1
GENERAL
MAXIMUM
CERTIFICATED WEIGHTS
Ramp:
1675
lbs.
Takeoff:
1670
lbs.
Landing:
1670
lbs.
Weight
in
Baggage
Compartment:
Baggage
Area.
1
(or
passenger
on
child's
seat)
-
Station
50
to
76: 120
lbs.
See
note
below.
Baggage
Area.
2 -
Station
76
to
94:
40
lbs.
See
note
below.
NOTE
The
maximum
combined
weight
capacity
for
baggage
areas
1
and
2
is
120
lbs.
STANDARD
AIRPLANE WEIGHTS
Standard
Empty
Weight,
152: 1101
lbs.
152
II:
1133
lbs.
Maximum
Useful
Load,
152:
574
lbs.
152
II:
542
lbs.
CABIN
AND
ENTRY
DIMENSIONS
Detailed
dimensions
of
the
ca.bin
interior
and
entry
door
openings
are
illustrated
in
Section
6.
BAGGAGE SPACE
DIMENSIONS
Baggage
area.
dimensions
are
illustrated
in
detail
in
Section
6.
SPECIFIC
LOADINGS
Wing
Loading:
10.5
lbs./sq.
ft.
Power
Loa.ding:
15.2
lbs./hp.
SYMBOLS,
ABBREVIATIONS
AND
TERMINOLOGY
GENERAL AIRSPEED
TERMINOLOGY
AND
SYMBOLS
KCAS
Knots
Calibrated
Airspeed
is
indicated
airspeed
corrected
for
position
and
instrument
error
and
expressed
in
knots.
Knots
calibrated
airspeed
is
equal
to
KT
AS
in
standard
atmosphere
at
sea
level.
1
July
1978
1-5

SECTION
1
GENERAL
KIAS
KTAS
VNE
CESSNA
MODEL
152
Knots
Indicated
Airspeed
is
the
speed
shown
on
the
airspeed
indicator
and
expressed
in
knots.
Knots
True
Airspeed
is
the
airspeed
expressed
in
knots
relative
to
undisturbed
air
which
is
KCAS
corrected
for
altitude
and
temperature.
Manuevering
Speed
is
the
maximum
speed
at
which
you
may
use
abrupt
control
travel.
Maximum
Fla~
Extended
Speed
is
the
highest
speed
permissible
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
exceeded
at
any
time.
Stalling
Speed
or
the
minimum
steady
fiight
speed
at
which
the
airplane
is
controllable.
Stalling
Speed
or
the
minimum
steady
fiight
speed
at
which
the
airplane
is
controllable
in
the
landing
configu-
ration
at
the
most
forward
center
of
gravity.
Best
Angle-of-Climb
Speed
is
the
speed
which
results
in
the
greatest
gain
of
altitude
in
a
given
horizontal
distance.
Best
Rate-of-Climb
Speed
is
the
speed
which
results
in
the
greatest
gain
in
altitude
in
a
given
time.
METEOROLOGICAL
TERMINOLOGY
OAT
Standard
Tempera-
ture
Pressure
Altitude
1-6
Outside
Air
Temperature
is
the
free
air
static
temperature.
It
is
expressed
in
either
degrees
Celsius
or
degrees
Fah-
renheit.
Standard
Temperature
is
15°0
at
sea
level
pressure
alti-
tude
and
decreases
by
2°0
for
each
1000
feet
of
altitude.
Pressure
Altitude
is
the
altitude
read
from
an
altimeter
when
the
altimeter's
barometric
scale
has
been
set
to
29.92
inches
of
mercury
(1013
mb).
1
July
1978

CESSNA
MODEL
152
SECTION
1
GENERAL
ENGINE
POWER
TERMINOLOGY
BHP
RPM
Static
RPM
Brake
Horsepower
is
the
power
developed
by
the
engine.
Revolutions
Per
Minute
is
engine
speed.
Static
RPM
is
engine
speed
attained
during
a
full-throttle
engine
runup
when
the
airplane
is
on
the
ground
and
stationary.
AIRPLANE
PERFORMANCE
AND
FLIGHT
PLANNING
TERMINOLOGY
Demon-
strated
Crosswind
Velocity
Usable
Fuel
Unusable
Fuel
GPH
NMPG
Demonstrated'
Crosswind
Velocity
is
the
velocity
of
the
crosswind
component
for
which
adequate
control
of
the
airplane
during
takeoff
and
landing
was
actually
demon-
strated
during
certification
tests.
The
value
shown
is
not
considered
to
be
limiting.
Usable
Fuel
is
the
fuel
available
for
flight
planning.
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
specific
engine
power
setting
and/
or
flight
configura-
tion.
g g
is
acceleration
due
to
gravity.
WEIGHT
AND
BALANCE
TERMINOLOGY
Reference
Datum
Station
Arm
Moment
~.July
1978
Reference
Datum
is
an
imaginary
vertical
plane
from
which
all
horizontal
distances
are
measured
for
balance
purposes,
Station
is
a
location
along
the
airplane
fuselage
given
in
terms
of
the
distance
from
the
reference
datum.
Arm
is
the
horizontal
distance
from
the
reference
datum
to
the
center
of
gravity
(C.G.)
of
an
item.
Moment
is
the
product
of
the
weight
of
an
item
multiplied
1-7

SECTION
1
GENERAL
Center
of
Gravity
(C.G.)
C.G.
Ann
C.G.
Limits
Standard
Empty
Weight
Basic
Empty
Weight
Useful
Load
Maximum
Ra.mp
Weight
Maximum
Takeoff
Weight
Maximum
Landing
Weight
Tare
1-8
CESSNA
MODEL
152
by
its
ann.
(Moment
divided
by
the
constant
1000
is
used
in
this
handbook
to
simplify
balance
calculations
by
reduc-
ing
the
number
of
digits.)
Center
of
Gravity
is
the
point
at
which
an
airplane,
or
equipment,
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
individu.al
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
air-
plane,
including
unusable
fuel,
full
operating
fluids
and
full
engine
oil.
Basic
Empty
Weight
is
the
standard
empty
weight
pl
us
the
weight
of
optional
equipment.
Useful
Load
is
the
difference
between
ramp
weight
and
the
basic
empty
weight.
Maximum
Ramp
Weight
is
the
maximum
weight
approved
for
ground
maneuver.
(It
includes
the
weight
of
start,
taxi
and
runup
fuel.)
Maximum
Takeoff
Weight
is
the
maximum
weight
ap-
proved
for
the
start
of
the
takeoff
run.
Maximum
Landing
Weight
is
the
maximum
weight
ap-
proved
for
the
landing
touchdown.
Tare
is
the
weight
of
chocks,
blocks,
stands,
etc.
used
when
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.
1
July
1978

CESSNA
MODEL 152
SECTION 2
LIMITATIONS
SECTION 2
LIMITATIONS
THIS DATA APPLICABLE ONLY TO AIRPLANES WITH LYCOMING
O-235-L2C ENGINE.
FOR AIRPLANES WITH ENGINE MODIFIED TO
O-235-N2C, REFER TO DATA IN SECTION 9 SUPPLEMENT.
TABLE OF CONTENTS
Introduction . . . . . . . .
Airspeed Limitations
Airspeed Indicator Markings
Power Plant Limitations
Power Plant Instrument Markings
Weight Limits ..... .
Center Of Gravity Limits .
Maneuver Limits . . . .
Flight Load Factor Limits
Kinds Of Operation Limits
Fuel Limitations . .
Other Limitations
Flap Limitations
Placards .....
1 July 1978
Revision 1 - 31 March 1983
Page
2-3
2-3
2-4
2-4
2-5
2-5
2-5
2-6
2-6
2-6
2-7
2-7
2-7
2-8
2-1/(2-2 blank)
I

CESSNA
MODEL
152
SECTION2
LIMITATIONS
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
and
in
Section
9
have
been
approved
by
the
Federal
Aviation
Administration.
Observance
of
these
operating
limitations
is
required,py
Federal
Aviation
Regulations.
NOTE
Refer
to
Section
9
of
this
Pilot's
Operating
Handbook
for
amended
operating
limitations,
operating
procedures,
performance
data
and
other
necessary
information
for
airplanes
equipped
with
specific
options.
Your
Cessna
is
certificated
under
FAA
Type
Certificate
No.
3A19
as
Cessna
Model
No.
152.
AIRSPEED
LIMITATIONS
Airspeed
limitations
and
their
operational
significance
are
shown
in
figure
2-1.
I
>V
SPEED
KCAS KIAS REMARKS
VNE
Never
Exceed
Speed
145 149
Do
not
exceed
this
speed
in
any operation.
VNQ Maximum Structural 108
111
Do
not
exceed
this
speed
Cruising
Speed
except in smooth air,
and
then
only
with
caution.
VA
Maneuvering
Speed:
1670 Pounds
101
104 Do
not
make
full
or
abrupt
1500 Pounds
96 98
control movements
above
1350 Pounds
91
93
this
speed.
VFE Maximum Flap Extended Do not
exceed
this
speed
Speed
87 85
with
flaps down.
Maximum Window Open Do
not
exceed
this speed
with
Speed
145 149 windows open.
Figure
2-1.
Airspeed
Limitations
1
July
1978 2-3

SECTION2
LIMITATIONS
CESSNA
MODEL
152
AIRSPEED
INDICATOR
MARKINGS
Airspeed
indicator
markings
and
their
color
code
significance
are
shown
in
figure
2-2.
MARKING KIAS VALUE SIGNIFICANCE
OR
RANGE
White Arc
35 -85
Full Flap Operating Range. Lower
limit
is
maximum ·weight
Vs
0
in
landing configuration. Upper limit
is
maximum speed permissible with
flaps extended.
Green Arc
40-111
Normal Operating Range. Lower limit
is
maximum weight
Vs
at
most forward
C.G. with flaps retracted. Upper limit
is
maximum structural cruising speed.
Yellow Arc
111
-149
Operations must be conducted with
caution and only
in
smooth air.
Red Line
149
Maximum speed for all operations.
Figure
2-2.
Airspeed
Indicator
Markings
POWER PLANT LIMITATIONS
Engine
Manufacturer:
Avco
Lycoming.
Engine
Model
Number:
O-235-L2C.
Engine
Opera.ting
Limits
for
Takeoff
and
Continuous
Operations:
Maximum
Power:
110
BHP.
Maximum
Engine
Speed:
2550
RPM.
NOTE
The
static
RPM
range
at
full
throttle
(carburetor
heat
off
and
mixture
leaned
to
maximum
RPM)
is
2280to
2380
RPM.
Maximum
Oil
Temperature:
245°F (118°C).
Oil
Pressure,
Minimum:
25
psi.
Maximum:
100
psi.
Propeller
Manufacturer:
McCauley
Accessory
Division.
Propeller
Model
Number:
1A103/TCM6958.
Propeller
Dia.meter,
Maximum:
69
inches.
Minimum:
67.5
inches.
2-4
1
July
1978

CESSNA
MODEL 152
SECTION2
LIMITATIONS
POWER PLANT INSTRUMENT MARKINGS
Power plant instrument markings and their color code significance
are shown in figure 2-3.
RED LINE GREEN ARC
INSTRUMENT
MINIMUM
NORMAL
LIMIT OPERATING
Tachometer:
Sea Level
1900 -2350 RPM
4000 Feet ---1900 -2450
RPM
8000 Feet 1900 -2550 RPM
Oil Temperature --- 1oo<> - 245°F
Oil Pressure 25 psi 60 - 90 psi
Fuel Quantity E -- -
(0.75 Gal. Unusable
Each Tank)
Figure 2-3. Power Plant Instrument Markings
WEIGHT LIMITS
Maximum Ramp Weight: 1675 lbs.
Maximum Takeoff Weight: 1670 lbs.
Maximum Landing Weight: 1670 lbs.
Maximum Weight in Baggage Compartment:
RED LINE
MAXIMUM
LIMIT
2550 RPM
245°F
100
psi
---
Baggage Area 1 ( or passenger on child's seat) - Station 50 to 76: 120 lbs.
See note below.
Baggage Area 2 - Station 76 to 94: 40 lbs. See note below.
NOTE
The maximum combined weight capacity for baggage
areas 1 and 2 is 120 lbs.
CENTER OF GRAVITY LIMITS
Center of Gravity Range:
Forward: 31.0 inches aft of datum at 1350 lbs. or less,, 7ith straight line
variation to 32.65 inches aft of datum at 1670 lbs.
1 July 1978
2-5

SECTION
2
LIMITATIONS
CESSNA
MODEL
152
Aft: 36.5
inches
aft
of
datum
at
all
weights.
Reference
Datum:
Front
face
of
firewall.
MANEUVER
LIMITS
This
airplane
is
certificated
in
the
utility
category
and
is
designed
for
limited
aerobatic
flight.
In
the
acquisition
of
various
certificates
such
as
commercial
pilot
and
flight
instructor,
certain
maneuvers
are
required.
All
of
these
maneuvers
are
permitted
in
this
airplane.
No
aerobatic
maneuvers
are
approved
except
those
listed
below:
MANEUVER
Chandelles
.
Lazy
Eights
Steep
Turns
Spins
Stalls
(Except
Whip
Stalls)
RECOMMENDED
ENTRY
SPEED*
.95
knots
.95
knots
.95
knots
.
Use
Slow
Deceleration
.
Use
Slow
Deceleration
*Higher
speeds
can
be
used
if
abrupt
use
of
the
controls
is
avoided.
The
baggage
compartment
and/
or
child's
seat
must
not
be
occupied
during
aerobatics.
Aerobatics
that
may
impose
high
loads
should
not
be
attempted.
The
important
thing
to
bear
in
mind
in
flight
maneuvers
is
that
the
airpla:p.e
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.
FLIGHT LOAD FACTOR LIMITS
Flight
Load
Factors:
*Flaps
Up: +4.4g, -1.76g
*Flaps
Down:
+3.5g
*The
design
load
factors
are
150%
of
the
above,
and
in
all
cases,
the
structure
meets
or
exceeds
design
loads.
KINDS
OF OPERATION LIMITS
The
airplane
is
equipped
for
day
VFR
and
may
be
equipped
for
night
VFR
and/or
IFR
operations.
FAR
Part
91
establishes
the
minimum
required
instrumentation
and
equipment
for
'these
operations.
The
refer-
2-6 1
July
1978