Cessna 152 Quick setup guide

For Flight Training Reference Only

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 APPROVED
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 1979
For Flight Training Reference Only

INFORMATION MANUAL
CESSNA AIRCRAFT COMPANY
1980 MODEL 152
CESSNA AIRCRAFT COMPANY
M.mb.r of GAMA WICHITA, KANSAS, USA
1 July 1979
D1170-13-RPC-1OOOO-12/79
iii
For Flight Training Reference Only

PERFORMANCE- CESSNA
SPECIFICATIONS 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.
75% Power at 8000 Ft Range
24.5 Gallons Usable Fuel Time
75% Power at 8000 Ft . ' Range
37.5 Gallons Usable Fuel Time
Maximum Range at 10,000 Ft Range
24.5 Gallons Usable Fuel Time
Maximum Range at 10,000 Ft Range
37.5 Gallons Usable Fuel Time
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 CAPACITY: Total
Standard Tanks
Long Range Tanks
OIL CAPACITY
ENGINE: Avco Lycoming
110 BHP at 2550 RPM
PROPELLER: Fixed Pitch, Diameter
110 KNOTS
107 KNOTS
320 NM
3.1 HRS
545 NM
5.2 HRS
415 NM
5.2 HRS
690 NM
8.7 HRS
715 FPM
14,700 FT
725 FT
1340 FT
475 FT
1200 FT
48 KNOTS
43 KNOTS
1675 LBS
1670 LBS
1109 LBS
1142 LBS
566 LBS
533 LBS
120 LBS
10.5
15.2
26 GAL.
39 GAL.
6 QTS
O-235-L2C
69 IN.
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"Speed performance is shown for an airplane equipped with optional speed fairings,
which increas-3 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.
1 July 1979
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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
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CESSNA SECTION 1
MODEL 152 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
Oil 1-4
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 1979 1-1
For Flight Training Reference Only

SECTION 1
GENERAL
CESSNA
MODEL 152
3. Wheel base length is 58".
4. Propeller ground clearance is 12'
5. Wing area is 159 1/2 square feet.
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".
2. Maximum height shown with nose gear
depressed, all tires and nose strut prop
erly inflated and flashing beacon installed.
Minimum turning radius [sfcpivot point to
outboard wing tip) is 24' - 8".
Figure 1-1. Three View
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1 July 1979
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CESSNA SECTION i
MODEL 152 GENERAL
INTRODUCTION
This handbook contains 9 sections, and includes the material require!
to be furnished to the pilot by CAR Part 3. It also contains supplementa
data supplied by Cessna Aircraft Company.
Section 1 provides basic data and information of general interest. I
also contains definitions or explanations of symbols, abbreviations, am
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: HO rated BHP at 2550 RPM.
PROPELLER
Propeller Manufacturer: McCauley Accessory Division.
Propeller Model Number: 1A103/TCM6958.
Number of Biades: 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).
NOTE
Isopropyl alcohol or ethylene glycol monomethyl ether
may be added to the fuel supply. Additive concentrations
shall not exceed 1% for isopropyl alcohol or .15% for
ethylene glycol monomethyl ether. Refer to Section 8 for
additional information.
1 July 1979 1-E
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SECTION 1 CESSNA
GENERAL MODEL 152
Fuel Capacity:
Standard Tanks:
Total Capacity: 26 gallons.
Total Capacity Each Tank: 13 gallons.
Total Usable: 24.5 gallons.
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 _
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 be used 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).
SAE 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. i
Total: 7 Quarts (if oil filter installed).
1-4 1 July 1979
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CESSNA SECTION 1
MODEL 152 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: 1109 lbs.
152 II: 1142 lbs.
Maximum Useful Load, 152: 566 lbs.
152 II: 533 lbs.
CABIN AND ENTRY DIMENSIONS
Detailed dimensions of the cabin 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 Loading: 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 KTAS in standard
atmosphere at sea level.
1 July 1979 1-5
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SECTION 1 CESSNA
GENERAL MODEL 152
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
relative to undisturbed air which is KCAS corrected for
altitude and temperature.
VA Manuevering Speed is the maximum speed at which you
may use abrupt control travel.
Vpg Maximum Flap Extended Speed is the highest speed
permissible with wing flaps in a prescribed extended
position.
Vv Best Rate-of-Climb Speed is the speed which results in the
greatest gain in altitude in a given time.
METEOROLOGICAL TERMINOLOGY
~
Maximum Structural Cruising Speed is the speed that
should not be exceeded except in smooth air, then only with
caution.
VNE Never Exceed Speed is the speed limit that may not be
exceeded at any time.
Vg Stalling Speed or the minimum steady flight speed at
which the airplane is controllable.
V« Stalling Speed or the minimum steady flight speed at
which the airplane is controllable in the landing configu
ration at the most forward center of gravity.
V.. Best Angle-of-Climb Speed is the speed which results in
the greatest gain of altitude in a given horizontal distance.
"
OAT Outside Air Temperature is the free air static temperature.
It is expressed in either degrees Celsius or degrees Fah
renheit.
Standard Standard Temperature is 15°C at sea level pressure alti-
Tempera- tude and decreases by 2°C for each 1000 feet of altitude. _
ture
Pressure Pressure Altitude is the altitude read from an altimeter
Altitude when the altimeter's barometric scale has been set to 29.92
inches of mercury (1013 mb).
1-6 1 July 1979 _
For Flight Training Reference Only

CESSNA SECTION 1
MODEL 152 GENERAL
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
RPM engine 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
strated crosswind component for which adequate control of the
Crosswind airplane during takeoff and landing was actually demon-
Velocity strated during certification tests. The value shown is not
considered to be limiting.
Usable Fuel Usable Fuel is the fuel available for flight planning.
Unusable Unusable Fuel is the quantity of fuel that can not be safely
Fuel used in flight.
GPH Gallons Per Hour is the amount of fuel (in gallons)
consumed per hour.
NMPG 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 Reference Datum is an imaginary vertical plane from
Datum which 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.
Arm Arm is the horizontal distance from the reference datum to
the center of gravity (C.G.) of an item.
Moment Moment is the product of the weight of an item multiplied
1 July 1979 1.7
For Flight Training Reference Only

SECTION 1
GENERAL
CESSNA
MODEL 152
Center of
Gravity
(C.G.)
C.G.
Arm
C.G.
Limits
Standard
Empty
Weight
Basic Empty
Weight
Useful
Load
Maximum
Ramp
Weight
Maximum
Takeoff
Weight
Maximum
Landing
Weight
Tare
by its arm. (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 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 air
plane, including unusable i'uel, full operating fluids and
full engine oil.
Basic Empty Weight is the standard empty weight plus 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.
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CESSNA SECTIOi 3
MODEL 152 LIMITATIONS
SECTION 2
LIMITATIONS
TABLE OF CONTENTS
Page
Introduction 2-3
Airspeed Limitations 2-3
Airspeed Indicator Markings 2-4
Power Plant Limitations 2-4
Power Plant Instrument Markings 2-5
Weight Limits 2-5
Center Of Gravity Limits 2-5
Maneuver Limits 2-6
Flight Load Factor Limits 2-6
Kinds Of Operation Limits 2-6
Fuel Limitations 2-7
Other Limitations 2-7
Flap Limitations 2-7
Placards 2-8
1 July 1979 2-1/(2-2 blank)
For Flight Training Reference Only

CESSNA
MODEL 152
SECTION 2
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 by
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.
VNE
vN0
vA
VFE
SPEED
Never Exceed Speed
Maximum Structural
Cruising Speed
Maneuvering Speed:
1670 Pounds
1500 Pounds
1350 Pounds
Maximum Flap Extended
Speed
Maximum Window Open
Speed
KCAS
145
108
101
96
91
87
145
KIAS
149
111
104
98
93
85
149
REMARKS
Do not exceed this speed in
any operation.
Do not exceed this speed
except in smooth air, and
then only with caution.
Do not make full or abrupt
control movements above
this speed.
Do not exceed this speed
with flaps down.
Do not exceed this speed with
windows open.
Figure 2-1. Airspeed Limitations
1 July 1979
2-3
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SECTION 2
LIMITATIONS
CESSNA
MODEL 152
AIRSPEED INDICATOR MARKINGS
Airspeed indicator markings and their color code significance are
shown in figure 2-2.
MARKING
White Arc
Green Arc
Yellow Arc
Red Line
KIAS VALUE
OR RANGE
35 - 85
40 - 111
111 - 149
149
SIGNIFICANCE
Full Flap Operating Range. Lower
limit is maximum weight Vg in
landing configuration. Upper limit
is maximum speed permissible with
flaps extended.
Normal Operating Range. Lower limit
is maximum weight Vg at most forward
C.G. with flaps retracted. Upper limit
is maximum structural cruising speed.
Operations must be conducted with
caution and only in smooth air.
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 Operating Limits for Takeoff and Continuous Operations:
Maximum Power: 110 BHP rating.
Maximum Engine Speed: 2550 RPM.
NOTE
The static RPM range at full throttle (carburetor heat off
and mixture leaned to maximum RPM) is 2280 to 2380 RPM.
Maximum Oil Temperature: 245°F (118°C).
Oil Pressure, Minimum: 25 psi.
Maximum: 115 psi.
Propeller Manufacturer: McCauley Accessory Division.
Propeller Model Number: 1A103/TCM6958.
Propeller Diameter, Maximum: 69 inches.
Minimum: 67.5 inches.
2-4
1 July 1979
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CESSNA
MODEL 152
SECTION 2
LIMITATIONS
POWER PLANT INSTRUMENT MARKINGS
Power plant instrument markings and their color code significance
are shown in figure 2-3.
INSTRUMENT
Tachometer:
Sea Level
4000 Feet
8000 Feet
Oil Temperature
Oil Pressure
Fuel Quantity
Suction
RED LINE
MINIMUM
LIMIT
25 psi
E
(0.75 Gal. Unusable
Each Tank)
GREEN ARC
NORMAL
OPERATING
1900 - 2350 RPM
1900 - 2450 RPM
1900 - 2550 RPM
100° - 245°F
60 - 90 psi
4.5 - 5.4 in. Hg
RED LINE
MAXIMUM
LIMIT
2550 RPM
245° F
115 psi
- —
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:
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, with straight line
variation to 32.65 inches aft of datum at 1670 lbs.
1 July 1979 2-5
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SECTION 2 CESSNA
LIMITATIONS MODEL 152
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 1979
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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 RECOMMENDED ENTRY SPEED*
Chandelles 95 knots
Lazy Eights 95 knots
Steep Turns 95 knots
Spins Use Slow Deceleration
Stalls (Except Whip Stalls) 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 airplane is
clean in aerodynamic design and will build up speed quickly with me 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.
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For Flight Training Reference Only

CESSNA SECTION 2
MODEL 152 LIMITATIONS
ence to types of flight operations on the operating limitations placard
reflects equipment installed at the time of Airworthiness Certificate
issuance.
Flight into known icing conditions is prohibited.
FUEL LIMITATIONS
2 Standard Tanks: 13 U.S. gallons each.
Total Fuel: 26 U.S. gallons.
Usable Fuel (all flight conditions): 24.5 U.S. gallons.
Unusable Fuel: 1.5 U.S. gallons.
2 Long Range Tanks: 19.5 U.S. gallons each.
Total Fuel: 39 U.S. gallons.
Usable Fuel (all flight conditions): 37.5 U.S. gallons.
Unusable Fuel: 1.5 U.S. gallons.
NOTE
Due to cross-feeding between fuel tanks, the tanks should
be re-topped after each refueling to assure maximum
capacity.
Takeoffs have not been demonstrated with less than 2 gallons of total fuel
(1 gallon per tank).
Fuel remaining in the tank after the fuel quantity indicator reads empty
(red line) cannot be safely used in flight.
Approved Fuel Grades (and Colors):
100LL Grade Aviation Fuel (Blue).
100 (Formerly 100/130) Grade Aviation Fuel (Green).
OTHER LIMITATIONS
FLAP LIMITATIONS
Approved Takeoff Range: 0° to 10°.
Approved Landing Range: 0° to 30°.
1 July 1979 2-7
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SECTION 2
LIMITATIONS
CESSNA
MODEL 152
"
PLACARDS
The following information must be displayed in the form of composite
or individual placards.
1. In full view of the pilot: (The "DAY-NIGHT-VFR-IFR" entry,
shown on the example below, will vary as the airplane is
equipped).
The markings and placards installed in this airplane contain
operating limitations which must be complied with when operat
ing this airplane in the Utility Category. Other operating limita
tions which must be complied with when operating this airplane
in this category are contained in the Pilot's Operating Handbook
and FAA Approved Airplane Flight Manual.
NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE
LISTED BELOW
Maneuver
Rec. Entry
Speed
Maneuver
Rec. Entry
Speed
Chandelles 95 KIAS
Lazy 8's 95 KIAS
Steep Turns 95 KIAS
Spins Slow Decel.
Stalls (Ex
cept Whip
Stalls) Slow Decel.
Intentional spins prohibited with flaps extended.
Flight into known icing conditions prohibited.
This airplane is certified for the following flight operations as of
date of original airworthiness certificate:
DAY—NIGHT—VFR—IFR
2. In the baggage compartment:
120 LBS. MAXIMUM BAGGAGE AND/OR AUXILIARY SEAT PAS
SENGER. FOR ADDITIONAL LOADING INSTRUCTIONS SEE
WEIGHT AND BALANCE DATA.
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