DEPARTMENT OF TRANSPORTATION

FEDERAL AVIATION ADMINISTRATION

3A19
Revision 51
Textron Aviation
150 150J
150A 150K
150B A150K
150C 150L
150D A150L
150E 150M
150F A150M
150G 152
150H A152
August 1, 2024

WARNING: Use of alcohol-based fuels can cause serious performance degradation and fuel
system component damage and is therefore prohibited on Cessna airplanes.

TYPE CERTIFICATE DATA SHEET NO. 3A19

This data sheet, which is a part of type certificate No. 3A19, prescribes conditions and limitations under which the product for
which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations.

Type Certificate Holder: Textron Aviation Inc.

One Cessna Boulevard
Wichita, Kansas 67215

Type Certificate Holder Record: Cessna Aircraft Company transferred to

Textron Aviation Inc. on July 29, 2015

I. Model 150, 2 PCLM (Utility Category), Approved July 10, 1958

Model 150A, 2 PCLM (Utility Category), Approved June 14, 1960
Model 150B, 2 PCLM (Utility Category), Approved June 20, 1961
Model 150C, 2 PCLM (Utility Category), Approved June 15, 1962

Engine Continental O-200-A

*Fuel 80/87 min. grade aviation gasoline

*Engine Limits For all operations, 2750 r.p.m. (100 hp.)

Propeller and 1. Propeller

Propeller Limits (a) Sensenich Hub 69CK 24 lb. (-32)
Static r.p.m. at maximum permissible throttle setting:
Not over 2470, not under 2320
No additional tolerance permitted
Diameter: not over 69 in., not under 67.5 in.
2. Propeller
(a) McCauley Hub 1A100/MCM 21 lb. (-32)
Static r.p.m. at maximum permissible throttle setting:
Not over 2475, not under 2375
No additional tolerance permitted
Diameter: not over 69 in., not under 67.5 in.
3. Propeller
(a) McCauley Hub 1A101/DCM 21 lb. (-32)
Static r.p.m. at maximum permissible throttle setting:
Not over 2600, not under 2500
No additional tolerance permitted
Diameter: not over 69 in., not under 67.5 in.

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19
Rev No. 51 43 43 41 42 41 41 41 51 51 41 38 50 30 50 32 32 37 50
3A19 2 Rev. 51

I. Models 150, 150A, 150B, 150C (cont’d)

*Airspeed Limits (CAS) Never exceed 157 m.p.h. (136 knots)

Maximum structural cruising 120 m.p.h. (104 knots)
Maneuvering 106 m.p.h. ( 92 knots)
Flaps extended 85 m.p.h. ( 74 knots)

C.G. Range (+33.4) to (+36.0) at 1500 lb.

(+32.2) to (+36.0) at 1250 lb. or less
Straight line variation between points given.

Empty Weight C.G. Range None

Leveling Means Top edge of fuselage splice plate.

*Maximum Weight 1500 lb.

No. of Seats 2 at (+39); for child's optional jump seat, refer to Equipment List.

Maximum Baggage 80 lb. at (+65)

Fuel Capacity 26 gal. (22.5 gal. usable, two 13 gal. tanks in wings at +42)
See NOTE 1 for data on system fuel.

Oil Capacity 6 qt. (-13.5; unusable 2 qt.)

See NOTE 1 for data on system oil.

Control Surface Wing flaps Retracted 0°

Movements 1st notch 10°
2nd notch 20°
3rd notch 30°
4th notch 40°
Ailerons Up 20° Down 15°
Elevator Up 25° Down 15°
Elevator tab Up 10° Down 20°
Rudder Right 16° Left 16°

Serial Nos. Eligible Model 150: 617, 17001 thru 17999, 59001 thru 59018
Model 150A: 628, 15059019 thru 15059350
Model 150B: 15059351 thru 15059700
Model 150C: 15059701 thru 15060087

II. Model 150D, 2 PCLM (Utility Category), Approved July 19, 1963
Model 150E, 2 PCLM (Utility Category), Approved June 18, 1964
Model 150F, 2 PCLM (Utility Category), Approved May 27, 1965

Engine Continental O-200-A

*Fuel 80/87 min. grade aviation gasoline

*Engine Limits For all operations, 2750 r.p.m. (100 hp.)

Propeller and 1. Propeller

Propeller Limits (a) Sensenich Hub 69CK 24 lb. (-32)
Static r.p.m. at maximum permissible throttle setting:
Not over 2470, not under 2320
No additional tolerance permitted
Diameter: not over 69 in., not under 67.5 in.
2. Propeller
(a) McCauley 1A100/MCM 21 lb. (-32)
Static r.p.m. at maximum permissible throttle setting:
Not over 2475, not under 2375
No additional tolerance permitted
Diameter: not over 69 in., not under 67.5 in.
Rev. 51 3 3A19

II. Models 150D, 150E, 150F (cont’d)

Propeller and 3. Propeller

Propeller Limits (cont’d) (a) McCauley 1A101/DCM 21 lb. (-32)
Static r.p.m. at maximum permissible throttle setting:
Not over 2600, not under 2500
No additional tolerance permitted
Diameter: not over 69 in., not under 67.5 in.

*Airspeed Limits (CAS) Never exceed 162 m.p.h. (141 knots)

Maximum structural cruising 120 m.p.h. (104 knots)
Maneuvering 109 m.p.h. ( 95 knots)
Flaps extended 100 m.p.h. ( 87 knots)

C.G. Range (+32.9) to (+37.5) at 1600 lb.

(+31.5) to (+37.5) at 1280 lb. or less
Straight line variation between points given.

Empty Weight C.G. Range None

Leveling Means Top of tailcone

*Maximum Weight 1600 lb.

No. of Seats 2 at (+39); for child's optional jump seat, refer to Equipment List.

Maximum Baggage Models 150D, 150E: 120 lb. at (+65)

Model 150F: 120 lb. - Reference weight and balance data

Fuel Capacity 26 gal. (22.5 gal. usable, two 13 gal. tanks in wings at +42)
See NOTE 1 for data on system fuel.

Oil Capacity 6 qt. (-13.5; unusable 2 qt.) See NOTE 1 for data on system oil

Control Surface Wing flaps (150D, 150E) Retracted 0°

Movements 1st Notch 10°
2nd Notch 20°
3rd Notch 30°
4th Notch 40°
Wing flaps (150F) Down 0° -40° ±2°
Ailerons Up 20° Down 15°
Elevator Up 25° Down 15°
Elevator tab Up 10° Down 20°
Rudder (150D, 150E) Right 16° Left 16°
(150F) Right 23° Left 23°
(measured parallel to chord)

Serial Nos. Eligible Model 150D: 15060088 thru 15060772

Model 150E: 644, 15060773 thru 15061532
Model 150F: 15061533 thru 15064532
3A19 4 Rev. 51

III. Model 150G, 2 PCLM (Utility Category), Approved May 5, 1966,

2 PCSM (Utility Category), Approved August 12, 1966
Model 150H, 2 PCL-SM (Utility Category), Approved August 10, 1967
Model 150J, 2 PCL-SM (Utility Category), Approved May 2, 1968
Model 150K, 2 PCL-SM (Utility Category), Approved June 5, 1969

Engine Continental O-200-A

*Fuel 80/87 min. grade aviation gasoline

*Engine Limits For all operations, 2750 r.p.m. (100 hp.)

Propeller and 1. Propeller

Propeller Limits (a) Sensenich Hub 69CK 24 lb. (-32)
Static r.p.m. at maximum permissible throttle setting:
Not over 2470, not under 2320
No additional tolerance permitted
Diameter: not over 69 in., not under 67.5 in.
2. Propeller
(a) McCauley Hub 1A100/MCM 21 lb. (-32)
Static r.p.m. at maximum permissible throttle setting:
Not over 2475, not under 2375
No additional tolerance permitted
Diameter: not over 69 in., not under 67.5 in.
3. Propeller (seaplane only)
(a) McCauley Hub 1A90/CF 24 lb. (-32)
Static r.p.m. at maximum permissible throttle setting:
Not over 2600, not under 2500
No additional tolerance permitted
Diameter: not over 75 in., not under 73.5 in.
4. Propeller
(a) McCauley Hub 1A101/DCM 21 lb. (-32)
Static r.p.m. at maximum permissible throttle setting:
not over 2600, not under 2500
No additional tolerance permitted
Diameter: not over 69 in., not under 67 in.

*Airspeed Limits (CAS) Never exceed 162 m.p.h. (141 knots)

Maximum structural cruising 120 m.p.h. (104 knots)
Maneuvering 109 m.p.h. ( 95 knots)
Flaps extended 100 m.p.h. ( 87 knots)

C.G. Range Landplane

(+32.9) to (+37.5) at 1600 lb.
(+31.5) to (+37.5) at 1280 lb. or less
Seaplane
(+33.8) to (+36.5) at 1650 lb.
(+33.0) to (+36.5) at 1400 lb. or less
Straight line variation between points given

Empty Weight C.G. Range None

Leveling Means Top of tailcone

*Maximum Weight Landplane 1600 lb.

Seaplane 1650 lb. (Edo 88A-1650 floats)

No. of Seats 2 at (+39); for child's optional jump seat, refer to Equipment List.

Maximum Baggage 120 lb.; Reference weight and balance data

Rev. 51 5 3A19

III. Models 150G, 150H, 150J, 150K (cont’d)

Fuel Capacity Landplane

26 gal. (22.5 gal. usable, two 13 gal. tanks in wings at +42.0)
Seaplane
26 gal. (21.5 gal. usable, two 13 gal. tanks in wings at +42.0)
See NOTE 1 for data on system fuel.

Oil Capacity 6 qt. (-1.5; unusable 2 qt.)

See NOTE 1 for data on system oil.

Control Surface Wing flaps Down 0° -40° ±2°

Movements Ailerons Up 20° +2°, -0° Down 14° +2°, -0°
Elevator Up 25° ±1° Down 15° ±1°
Elevator tab Up 10° ±1° Down 20° ±1°
Rudder Right 23° +0°, -2° Left 23° +0°, -2°
(measured perpendicularly to hinge line)

Serial Nos. Eligible Model 150G: 15064533 thru 15067198 (except 15064970)
Model 150H: 649, 15067199 thru 15069308
Model 150J: 15069309 thru 15071128
Model 150K: 15071129 thru 15072003

IV. Model A150K, Aerobat, 2 PCLM (Acrobatic Category), Approved June 5, 1969

Engine Continental O-200-A

*Fuel 80/87 min. grade aviation gasoline

*Engine Limits For all operations, 2750 r.p.m. (100 hp.)

Propeller and 1. Propeller

Propeller Limits (a) McCauley Hub 1A101/DCM 21 lb. (-32)
Static r.p.m. at maximum permissible throttle setting:
Not over 2600, not under 2500
No additional tolerance permitted
Diameter: not over 69 in., not under 67 in.

*Airspeed Limits (CAS) Never exceed 193 m.p.h. (168 knots)

Maximum structural cruising 140 m.p.h. (122 knots)
Maneuvering 118 m.p.h. (103 knots)
Flaps extended 100 m.p.h. ( 87 knots)

C.G. Range (+32.9) to (+37.5) at 1600 lb.

(+31.5) to (+37.5) at 1280 lb. or less

Empty Weight C.G. Range None

Leveling Means Top of tailcone

*Maximum Weight 1600 lb.

No. of Seats 2 at (+39); for child's optional jump seat, refer to Equipment List.

Maximum Baggage 120 lb.; Reference weight and balance data.

Fuel Capacity 26 gal. (22.5 gal. usable, two 13 gal. tanks in wings at +42.0)
3A19 6 Rev. 51

IV. Model A150K (cont’d)

Oil Capacity 6 qt. (-13.5; unusable 2 qt.)

See NOTE 1 for data on system oil.

Control Surface Wing flaps Down 0° -40° ±2°

Movements Ailerons Up 20° +2°, -0° Down 14° +2°, -0°
Elevator Up 25° ±1° Down 15° ±1°
Elevator tab Up 10° ±1° Down 20° ±1°
Rudder Right 23° +0°, -2° Left 23° +0°, -2°
(measured perpendicularly to hinge line)

Serial Nos. Eligible Model A150K: A1500001 thru A1500226

V. Model 150L, 2 PCLM (Utility Category), Approved June 8, 1970

Engine Continental O-200-A

*Fuel 80/87 min. grade aviation gasoline

*Engine Limits For all operations, 2750 r.p.m. (100 hp.)

Propeller and 1. Propeller

Propeller Limits (a) McCauley Hub 1A101/GCM 27.7 lb. (-34.5)
(1971, 1972, 1973 models)
Static r.p.m. at maximum permissible throttle setting:
Not over 2600, not under 2500
No additional tolerance permitted
Diameter: not over 69 in., not under 67 in.

2. Propeller
(a) McCauley Hub 1A101/HCM 27.7 lb. (-34.5)
(1972, 1973, 1974 models)
Static r.p.m. at maximum permissible throttle setting:
Not over 2600, not under 2500
No additional tolerance permitted
Diameter: not over 69 in., not under 67 in.

3. Propeller
(a) McCauley Hub 1A101/PCM 27.0 lb. (-34.5)
(1974 model)
Static r.p.m. at maximum permissible throttle setting:
Not over 2600, not under 2500
No additional tolerance permitted
Diameter: not over 69 in., not under 67 in.

4. Propeller
(a) McCauley Hub 1A102/OCM 27.0 lb. (-34.5)
(1971 thru 1974 models)
Static r.p.m. at maximum permissible throttle setting:
Not over 2560, not under 2460
No additional tolerance permitted
Diameter: not over 69 in., not under 67.5 in.

*Airspeed Limits (CAS) Never exceed 162 m.p.h. (141 knots)

Maximum structural cruising 120 m.p.h. (104 knots)
Maneuvering 109 m.p.h. ( 95 knots)
Flaps extended 100 m.p.h. ( 87 knots)

C.G. Range (+32.9) to (+37.5) at 1600 lb.

(+31.5) to (+37.5) at 1280 lb. or less
Straight line variation between points given.
Rev. 51 7 3A19

V. Model 150L (cont’d)

Empty Weight C.G. Range None

Leveling Means Jig located nut plates and screws at Stations +94.63 and
+132.94 on left side of tailcone.

*Maximum Weight 1600 lb.

No. of Seats 2 at (+39); for child's optional jump seat, refer to Equipment List.

Maximum Baggage 120 lb.; Reference weight and balance data.

Fuel Capacity 26 gal. (22.5 gal. usable, two 13 gal. tanks in wings at +42.0)
See NOTE 1 for data on system fuel.

Oil Capacity 6 qt. (-13.5; unusable 2 qt.)

See NOTE 1 for data on undrainable oil.

Control Surface Wing flaps Down 0° -40° ±2°

Movements Ailerons Up 20° +2°, -0° Down 14° +2°, -0°
Elevator Up 25° ±1° Down 15° ±1°
Elevator tab Up 10° ±1° Down 20° ±1°
Rudder Right 23° +0°, -2° Left 23° +0°, -2°
(measured perpendicularly to hinge line)

Serial Nos. Eligible 15072004 thru 15072628 (1971 Model)

15072629 thru 15073658 (1972 Model)
15073659 thru 15074850 (1973 Model)
15074851 thru 15075781 (1974 Model)

VI. Model A150L, Aerobat, 2 PCLM (Acrobatic Category), Approved June 8, 1970

Engine Continental O-200-A

*Fuel 80/87 min. grade aviation gasoline

*Engine Limits For all operations, 2750 r.p.m. (100 hp.)

Propeller and 1. Propeller

Propeller Limits (a) McCauley Hub 1A101/GCM 27.7 lb. (-34.5)
(1971, 1972, 1973 models)
Static r.p.m. at maximum permissible throttle setting:
Not over 2600, not under 2500
No additional tolerance permitted
Diameter: not over 69 in., not under 67 in.

2. Propeller
(a) McCauley Hub 1A101/HCM 27.7 lb. (-34.5)
(1971, 1972, 1973 models)
Static r.p.m. at maximum permissible throttle setting:
Not over 2600, not under 2500
No additional tolerance permitted
Diameter: not over 69 in., not under 67 in.

3. Propeller
(a) McCauley Hub 1A102/OCM 27.0 lb. (-34.5)
(1971 thru 1974 model)
Static r.p.m. at maximum permissible throttle setting:
Not over 2560, not under 2460
No additional tolerance permitted
Diameter: not over 69 in., not under 67.5 in.
3A19 8 Rev. 51

VI. Model A150L (cont’d)

*Airspeed Limits (CAS) Never exceed 193 m.p.h. (168 knots)

Maximum structural cruising 140 m.p.h. (122 knots)
Maneuvering 118 m.p.h. (103 knots)
Flaps extended 100 m.p.h. ( 87 knots)

C.G. Range (+32.9) to (+37.5) at 1600 lb.

(+31.5) to (+37.5) at 1280 lb. or less

Empty Weight C.G. Range None

Leveling Means Jig located nut plates and screws at Stations +94.63 and +132.94 on
left side of tailcone.

*Maximum Weight 1600 lb.

No. of Seats 2 at (+39); for child's optional jump seat, refer to Equipment List.

Maximum Baggage 120 lb.; Reference weight and balance data.

Fuel Capacity 26 gal. (22.5 gal. usable, two 13 gal. tanks in wings at +42.0)
See NOTE 1 for data on unusable fuel.

Oil Capacity 6 qt. (-13.5; unusable 2 qt.)

See NOTE 1 for data on undrainable oil.

Control Surface Wing flaps Down 0° -40° ±2°

Movements Ailerons Up 20° +2°, -0° Down 14° +2°, -0°
Elevator Up 25° ±1° Down 15° ±1°
Elevator tab Up 10° ±1° Down 20° ±1°
Rudder Right 23° +0°, -2° Left 23° +0°, -2°
(measured perpendicularly to hinge line)

Serial Nos. Eligible A1500227 thru A1500276 (1971 Model)

A1500277 thru A1500342 (1972 Model)
A1500343 thru A1500429 (1973 Model)
A1500430 thru A1500523 (1974 Model, except A1500433)

VII. Model 150M, 2 PCLM (Utility Category), Approved May 6, 1974

Engine Continental O-200-A

*Fuel 80/87 min. grade aviation gasoline

*Engine Limits For all operations, 2750 r.p.m. (100 hp.)

Propeller and 1. Propeller

Propeller Limits (a) McCauley Hub 1A102/OCM 27.7 lb. (-34.5)
Static rpm at maximum permissible throttle setting:
Not over 2560, not under 2460
No additional tolerance permitted
Diameter: not over 69 in., not under 67 in.

*Airspeed Limits (CAS) (S/N 15075782 thru 15077005)

Never exceed 162 m.p.h. (141 knots)
Maximum structural cruising 120 m.p.h. (104 knots)
Maneuvering 109 m.p.h. ( 95 knots)
Flaps extended 100 m.p.h. ( 87 knots)
Rev. 51 9 3A19

VII. Model 150M (cont’d)

*Airspeed Limits (IAS) (S/N 15077006 thru 15079405)

(See NOTE 4 on Never exceed 141 knots
use of IAS) Maximum structural cruising 107 knots
Maneuvering 97 knots
Flaps extended 85 knots

C.G. Range (+32.9) to (+37.5) at 1600 lb.

(+31.5) to (+37.5) at 1280 lb. or less
Straight line variation between points given.

Empty Weight C.G. Range None

Leveling Means Jig located nut plates and screws at Stations +94.63 and +132.94 on left side of tailcone

*Maximum Weight 1600 lb.

No. of Seats 2 at (+39); for child's optional jump seat, refer to Equipment List,

Maximum Baggage 120 lb.; Reference weight and balance data.

Fuel Capacity 26 gal. (22.5 gal. usable, two 13 gal. tanks in wings at +42.0)
See NOTE 1 for data on unusable fuel.

Oil Capacity 6 qt. (-13.5; unusable 2 qt.)

See NOTE 1 for data on undrainable oil.

Control Surface Wing flaps Down 0° -40° ±2°

Movements Ailerons Up 20° +2°, -0° Down 14° +2°, -0°
Elevator Up 23° +1°, -0° Down 15° ±1°
Elevator tab Up 10° ±1° Down 20° ±1°
Rudder Right 23° +0°, -2° Left 23° +0°, -2°
(measured perpendicularly to hinge line)

Serial Nos. Eligible 15075782 thru 15077005 (1975 Model)

15077006 thru 15078505 (1976 Model)
15078506 thru 15079405 (1977 Model)

VIII. Model A150M, Aerobat, 2 PCLM (Acrobatic Category), Approved May 6, 1974

Engine Continental O-200-A

*Fuel 80/87 min. grade aviation gasoline

*Engine Limits For all operations, 2750 r.p.m. (100 hp.)

Propeller and 1. Propeller

Propeller Limits (a) McCauley Hub 1A102/OCM 27.0 lb. (-34.5)
Static r.p.m. at maximum permissible throttle setting:
Not over 2560, not under 2460
No additional tolerance permitted
Diameter: not over 69 in., not under 67.5 in.

*Airspeed Limits (CAS) (S/N 15064970, A1500524 thru A1500609)

Never exceed 193 m.p.h. (168 knots)
Maximum structural cruising 140 m.p.h. (122 knots)
Maneuvering 118 m.p.h. (103 knots)
Flaps extended 100 m.p.h. ( 87 knots)
3A19 10 Rev. 51

VIII. Model A150M (cont’d)

*Airspeed Limits (IAS) A1500610 thru A1500734

(See NOTE 4 on Never exceed 164 knots
use of IAS) Maximum structural cruising 123 knots
Maneuvering 105 knots
Flaps extended 85 knots

C.G. Range (+32.9) to (+37.5) at 1600 lb.

(+31.5) to (+37.5) at 1280 lb. or less
Straight line variation between points given

Empty Weight C.G. Range None

Leveling Means Jig located nut plates and screws at Stations +94.63 and +132.94 on left side of tailcone.

*Maximum Weight 1600 lb.

No. of Seats 2 at (+39); for child's optional jump seat, refer to Equipment List.

Maximum Baggage 120 lb.; Reference weight and balance data.

Fuel Capacity 26 gal. (22.5 gal. usable, two 13 gal. tanks in wings at +42.0)
See NOTE 1 for data on unusable fuel.

Oil Capacity 6 qt. (-13.5; unusable 2 qt.)

See NOTE 1 for data on undrainable oil.

Control Surface Wing flaps Down 0° -40° ±2°

Movements Ailerons Up 20° +2°, -0° Down 14° +2°, -0°
Elevator Up 23° +1°, -0° Down 15° ±1°
Elevator tab Up 10° ±1° Down 20° ±1°
Rudder Right 23° +0°, -2° Left 23° +0°, -2°
(measured perpendicularly to hinge line)

Serial Nos. Eligible 15064970, A1500524 thru A1500609 (1975 Model)

A1500610 thru A1500684 (1976 Model)
A1500685 thru A1500734 (1977 Model)

IX. Model 152, 2 PCLM (Utility Category), Approved March 16, 1977

Engine S/N 15279406 thru 15285594

Lycoming O-235-L2C

S/N 15285595 and On, aircraft reworked per SK152-15 or SK152-16

Lycoming O-235-N2C

*Fuel 100LL/100 min. grade aviation gasoline

*Engine Limits S/N 15279406 thru 15285594

For all operations, 2550 r.p.m. (110 hp.)

S/N 15285595 and On

For all operations 2550 r.p.m. (108 hp.)
Rev. 51 11 3A19

IX. Model 152 (cont'd)

Propeller and 1. Propeller

Propeller Limits (a) McCauley Hub 1A103/TCM 23.2 lb. (-36.5)
Static rpm at full throttle
(carburetor heat off and mixture leaned to
maximum r.p.m.) is 2280 to 2380 r.p.m.
For allowable variations in static r.p.m. at
non-standard temperatures, refer to the
Service Manual.
Diameter: not over 69 in., not under 67.5 in.
(b) Spinner: Dwg. 0450073

*Airspeed Limits (IAS) Never exceed 149 knots

(See NOTE 4 on Maximum structural cruising 111 knots
use of IAS) Maneuvering 104 knots
Flaps extended 85 knots

C.G. Range (+32.65) to (+36.5) at 1670 lb.

(+31.0) to (+36.5) at 1350 lb. or less
Straight line variation between points given.

Empty Weight C.G. Range None

Leveling Means Jig located nut plates and screws at Stations +94.63 and +132.94 on left side of tailcone.

*Maximum Weight 1670 lb.

1675 lb. ramp weight (S/N 15282032 and On)

No. of Seats 2 at (+39); for child's optional jump seat, refer to Equipment List.

Maximum Baggage 120 lb.; Reference weight and balance data.

Fuel Capacity 26 gal. (24.5 gal. usable, two 13 gal. tanks in wings at +42.0)
See NOTE 1 for data on unusable fuel.

Oil Capacity 6 qt. (-14.7; unusable 2 qt.)

See NOTE 1 for data on undrainable oil.

Control Surface s Wing flaps Down 0° -30° ±2°

Movements Ailerons Up 20°  2° Down 15°  1°
(aileron travel measured from 1° ±.5° droop)
Elevator Up 25° ±1° Down 18° ±1°
Elevator tab Up 10° ±1° Down 20° ±1°
Rudder Right 23° +0°, -2° Left 23° +0°, -2°
(measured perpendicularly to hinge line)

Serial Nos. Eligible 15279406 thru 15282031 (1978 Model)

15282032 thru 15283591 (1979 Model)
15283592 thru 15284541 (1980 Model)
15284542 thru 15285161 (1981 Model)
15285162 thru 18285594 (1982 Model)
15285595 thru 15285833 (1983 Model)
15285834 thru 15285939 (1984 Model)
15285940 thru 15286033 (1985 Model)
3A19 12 Rev. 51

X. Model A152, Aerobat, 2 PCLM (Acrobatic Category), Approved March 16, 1977

Engine S/N A1500433, A1520735, 681 thru A521014

Lycoming O-235-L2C

S/N A1521015 and On, aircraft reworked per SK152-15 or SK152-16

Lycoming O-235-N2C

*Fuel 100LL/100 min. grade aviation gasoline

*Engine Limits S/N A1500433, A1520735, 681 thru A1521014

For all operations, 2550 r.p.m. (110 hp.)

S/N A1521015 and on

For all operations, 2550 r.p.m. (108 hp.)

Propeller and 1. Propeller

Propeller Limits (a) McCauley Hub 1A103/TCM 23.2 lb. (-36.5)
Static rpm at full throttle
(carburetor heat off and mixture leaned to
maximum r.p.m.) is 2280 to 2380 r.p.m.
For allowable variations in static r.p.m. at
non-standard temperatures, refer to the
Service Manual.
Diameter: not over 69 in., not under 67.5 in.
(b) Spinner: Dwg. 0450073

*Airspeed Limits (IAS) Never exceed 172 knots

(See NOTE 4 on Maximum structural cruising 125 knots
use of IAS) Maneuvering 108 knots
Flaps extended 85 knots

C.G. Range (+32.65) to (+36.5) at 1670 lb.

(+31.0) to (+36.5) at 1350 lb. or less

Empty Weight C.G. Range None

Leveling Means Jig located nut plates and screws at Stations +94.63 and +132.94 on left side of tailcone.

*Maximum Weight 1670 lb.

1675 lb. ramp weight (S/N 681, A1520809 and On)

No. of Seats 2 at (+39); for child's optional jump seat, refer to Equipment List.

Maximum Baggage 120 lb.; Reference weight and balance data.

Fuel Capacity 26 gal. (24.5 gal. usable, two 13 gal. tanks in wings at +42.0)
See NOTE 1 for data on unusable fuel.

Oil Capacity 6 qt. (-14.7; unusable 2 qt.)

See NOTE 1 for data on undrainable oil.

Control Surface Wing flaps Down 0° -30° ±2°

Movements Ailerons Up 20°  1° Down 15°  1°
(aileron travel measured from 1° ±.5° droop)
Elevator Up 25° ±1° Down 18° ±1°
Elevator tab Up 10° ±1° Down 20° ±1°
Rudder Right 23° +0°, -2° Left 23° +0°, -2°
(measured perpendicularly to hinge line)
Rev. 51 13 3A19

X. Model A152 (cont’d)

Serial Nos. Eligible A1500433, A1520735 thru A1520808 (1978 Model)

681, A1520809 thru A1520878 (1979 Model)
A1520879 thru A1520943 (1980 Model)
A1520944 thru A1520983 (1981 Model)
A1520984 thru A1521014 (1982 Model)
A1521015 thru A1521025 (1983 Model)
A1521026 thru A1521027 (1984 Model)
A1521028 thru A1521049 (1985 Model)

Data Pertinent to All Models

Datum Fuselage station 0.0 front face of firewall

Certification Basis:
Part 3 of the Civil Air Regulations dated May 15, 1956, as amended by 3-4. In addition, effective S/N 15282032 and On for
Model 152, and S/N 681, A1520809 and On for Model A152, FAR 23.1559 effective March 1, 1978. FAR 36 dated December 1,
1969, plus Amendments 36-1 through 36-5 for Models 152 and A152 only. In addition, effective S/N 15285940 and On, and S/N
A1521028 and On, FAR 23.1545(a), Amendment 23-23 dated December 1, 1978.

Application for Type Certificate dated August 13, 1956.

Type Certificate No. 3A19 issued July 10, 1958, obtained by the manufacturer under delegation option procedures.

Equivalent Safety Items S/N 15077006 thru 15079405

S/N 15279406 and On
S/N A1500610 thru A1500734
S/N 681, A1500433, A1520735 and On

Airspeed Indicator CAR 3.757 (See NOTE 4)

(S/N 15279406 thru 15285939 and 681, A1500433, A1520735 thru A1521027)

Operating Limitations CAR 3.778(a)

Production Basis:
Production Certificate No. 4. Delegation Option Manufacturer No. CE-1 authorized to issue airworthiness certificates under
delegation option provisions of Part 21 of the Federal Aviation Regulations.

Equipment:
The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed
in the aircraft for certification. This equipment must include a current Airplane Flight Manual (AFM), effective at S/N 681,
15282032 and On, and A1520809 and On. In addition, the following item of equipment is required:

1. Stall warning indicator, audible, Cessna Dwg. 0511062

(Model 150 thru 150E)

2. Stall warning indicator, audible, Cessna Dwg. 0413029

(Model 150F thru 150M) (1977 Model)
(Model A150K thru A150M) (1977 Model)
(Model 152 and A152)
3A19 14 Rev. 51

NOTE 1. Current weight and balance report together with list of equipment included in certificated empty weight, and
loading instructions, when necessary, must be provided for each aircraft at the time of original certification.

S/N 17001 thru 17999, 59001 thru 59018, 15059019 thru 15077005 and A1500001 thru A1500609
The certificated empty weight and corresponding center of gravity location must include unusable fuel of 21 lb.
at (+40) for landplanes or 27 lb. at (+40) for seaplanes and an undrainable oil of (0) lb. at (-13.5) for both
landplane and seaplane.

S/N 15077006 thru 15079405 and A1500610 thru A1500734

The certificated empty weight and corresponding center of gravity location must include unusable fuel of 21 lb.
at (+40) and full oil of 11.3 lb. at (-13.5) for landplane.

S/N 681, A1500433, 15279406 and On, and A1520735 and On

The certificated empty weight and corresponding center of gravity location must include unusable fuel of 9 lb.
at (+40) and full oil of 11.3 lb. at (-14.7) for landplane.

NOTE 2. The following information must be displayed in the form of composite or individual placards.

A. In full view of the pilot:

(1) "This airplane must be operated in compliance with the operating limitations stated in the form of
placards, markings and manuals."

(2) Models 150, 150A, 150B, 150C

"Acrobatic maneuvers are limited to the following:

Maneuver Entry Speed

Chandelle 106 m.p.h. ( 92 knots)
Steep turns 106 m.p.h. ( 92 knots)
Lazy eights 106 m.p.h. ( 92 knots)
Design maneuvering speed 106 m.p.h. ( 92 knots)
Stalls (except whip) Use slow deceleration
Spins Use slow deceleration
Spin recovery - opposite rudder-neutral elevator.
Intentional spins with flaps extended prohibited.”

(3) Models 150D, 150E, 150F, 150G, 150H, 150J, 150K

"Acrobatic maneuvers are limited to the following:

Maneuver Entry Speed

Chandelle 109 m.p.h. ( 95 knots)
Steep turns 109 m.p.h. ( 95 knots)
Lazy eights 109 m.p.h. ( 95 knots)
Stalls (except whip) Use slow deceleration
Spins Use slow deceleration
Intentional spins with flaps extended prohibited.
Spin recovery - opposite rudder-forward elevator.

Maximum design weight: Landplane 1600 lb.

Seaplane 1650 lb.
Maximum maneuvering speed: 109 m.p.h. ( 95 knots)
Maximum flight maneuvering load factors:
Flaps Up: +4.4 -1.76
Flaps Down: +3.5"
Rev. 51 15 3A19

NOTE 2 (cont’d)

(4) Model A150K

"This airplane must be operated as an Acrobatic Category airplane in compliance with the
operating limitations stated in the form of placards, markings, and manuals.

Acrobatic Category
Maximum design weight: 1600 lb.
Maximum maneuvering speed: 118 m.p.h. (103 knots)
(Refer to weight and balance data for loading instructions)
Flight maneuvering load factors:
Flaps up: +6.0 -3.0
Flaps down: +3.5
Aerobatic maneuvers with flaps extended are prohibited. Inverted flight is prohibited.

Child's seat and/or baggage compartment must not be occupied during aerobatic maneuvering.
Spin recovery: Apply opposite rudder, followed by forward elevator for normal recovery.

The following aerobatic maneuvers are approved:

Maneuver Entry Speed

Chandelle 120 m.p.h. (104 knots)
Steep turns 110 m.p.h. ( 96 knots)
Barrel rolls 130 m.p.h. (113 knots)
Snap rolls .90 m.p.h. ( 78 knots)
Lazy eights 120 m.p.h. 104 knots)
Aileron rolls 130 m.p.h (113 knots
Immelmann’s 145 m.p.h (126 knots)
Cuban eights 145 m.p.h. (126 knots)
Loops 130 m.p.h (113 knots)
Vertical reversements 90 m.p.h. ( 78 knots)
Stalls (except whip) Use slow deceleration
Spins Use slow deceleration”

(5) Model 150L and 150M (1971 thru 1975 Model)

"This airplane is approved in the utility category and must be operated in compliance with the
operating limitations as stated in the form of placards, markings, and manuals.

Maximums
Maneuvering speed (IAS): 109 m.p.h. CAS (95 knots)
Gross weight: 1600 lb.
Flight load factor:
Flaps Up: +4.4, -1.76
Flaps Down: +3.5
No acrobatic maneuvers approved except those listed below:

Maneuver Entry Speed

Chandelle 109 m.p.h. ( 95 knots)
Lazy eights 109 m.p.h. ( 95 knots)
Steep turns 109 m.p.h. ( 95 knots)
Stalls (except whip) Use slow deceleration
Spins Use slow deceleration

In full view of the pilot:

Spin Recovery: opposite rudder - forward elevator - neutralize controls.
Intentional spins with flaps extended are prohibited. Known icing conditions to be avoided.
This airplane is certified for the following flight operations as of date of original airworthiness
certificate:
(DAY - NIGHT - VFR - IFR)" (As Applicable)
3A19 16 Rev. 51

NOTE 2 (cont’d)

(6) Model A150L and A150M (1971 thru 1975 Model)

"This airplane is approved in the acrobatic category and must be operated in compliance with the
operating limitations as stated in the form of placards, markings, and manuals.

Maximums
Maneuvering speed (IAS) 118 m.p.h. CAS (103 knots)
Gross weight 1600 lb.
Flight load factor Flaps Up +6.0, -3.0
Flaps Down +3.5

Aerobatic maneuvers with flaps extended are prohibited. Inverted flight is prohibited.
Child's seat and/or baggage compartment must not be occupied during aerobatics.

Maneuver Entry Speed

Chandelle 120 m.p.h. (104 knots)
Steep turns 110 m.p.h. ( 96 knots)
Barrel rolls 130 m.p.h. (113 knots)
Snap rolls 90 m.p.h. ( 78 knots)
Lazy eights 120 m.p.h. (104 knots)
Aileron rolls 130 m.p.h (113 knots)
Immelmann’s 145 m.p.h (126 knots)
Cuban eights 145 m.p.h. (126 knots)
Loops 130 m.p.h (113 knots)
Vertical reversements 90 m.p.h. ( 78 knots)
Stalls (except whip) Use slow deceleration
Spins Use slow deceleration

In full view of the pilot:

Spin Recovery: opposite rudder - forward elevator - neutralize controls.
Intentional spins with flaps extended are prohibited. Known icing conditions to be avoided.
This airplane is certified for the following flight operations as of date of original airworthiness
certificate:
(DAY - NIGHT - VFR - IFR)" (As Applicable)

(7) Model 150M (1976 and 1977 Model)

"This airplane is approved in the acrobatic category and must be operated in compliance with the
operating limitations as stated in the form of placards, markings, and manuals.

Maximums
Maneuvering speed (IAS): 97 knots
Gross weight: 1600 lb.
Flight load factor: Flaps Up: +4.4, -1.76
Flaps Down: +3.5

No acrobatic maneuvers approved except those listed below:

Maneuver Max Entry Speed

Chandelle 95 knots
Lazy eights 95 knots
Steep turns 95 knots
Stalls (except whip) Use slow deceleration
Spins Use slow deceleration

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:
(DAY - NIGHT - VFR - IFR)" (As applicable)
Rev. 51 17 3A19

NOTE 2 (cont’d)

(8) A150M (1976 and 1977 Model)

"This airplane is approved in the acrobatic category and must be operated in compliance with the
operating limitations as stated in the form of placards, markings, and manuals.

Maximums
Maneuvering speed (IAS): 105 knots
Gross weight: 1600 lb.
Flight load factor: Flaps Up: +6.0, -3.0
Flaps Down: +3.5

Aerobatic maneuvers with flaps extended are prohibited. Inverted flight is prohibited.
Baggage compartment and/or child's seat must not be occupied during aerobatics.

The following aerobatic maneuvers are approved:

Maneuver Recommended Entry Speed

Chandelle 105 knots
Steep turns 100 knots
Barrel rolls 115 knots
Snap rolls 80 knots
Lazy eights 105 knots
Aileron rolls 115 knots
Immelmann’s 130 knots
Cuban eights 130 knots
Loops 115 knots
Vertical reversements 80 knots
Stalls (except whip) Use slow deceleration
Spins Use slow deceleration

Abrupt use of controls prohibited above 105 knots.

Spin Recovery: opposite rudder - forward elevator - neutralize controls.
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)" (As Applicable)

(9) Model 152 (1978 Model)

"This airplane is approved in the utility category and must be operated in compliance with
the operating limitations as stated in the form of placards, markings, and manuals.

Maximums
Maneuvering speed (IAS): 104 knots
Gross weight: 1670 lb.
Flight load factor: Flaps Up: +4.4, -1.76
Flaps Down: +3.5

No acrobatic maneuvers approved except those listed below:

Maneuver Recommended Entry Speed

Chandelle 95 knots
Steep turns 95 knots
Lazy eights 95 knots
Stalls (except whip) Use slow deceleration
Spins Use slow deceleration

Abrupt use of controls prohibited above 104 knots.

Intentional spins with flaps extended are prohibited. Altitude loss in a stall recovery: 160 ft.
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)" (As applicable)
3A19 18 Rev. 51

NOTE 2 (cont’d)

(10) Model A152 (1978 Model and S/N A1500433)

"This airplane is approved in the acrobatic category and must be operated in compliance with the
operating limitations as stated in the form of placards, markings, and manuals.

Maximums
Maneuvering speed (IAS): 108 knots
Gross weight: 1670 lb.
Flight load factor: Flaps Up: +6.0, -3.0
Flaps Down: +3.5

Aerobatic maneuvers with flaps extended are prohibited. Inverted flight is prohibited.
Baggage compartment and/or child's seat must not be occupied during aerobatics.

The following aerobatic maneuvers are approved:

Maneuver Recommended Entry Speed

Chandelle 105 knots
Steep turns 100 knots
Barrel rolls 115 knots
Snap rolls 80 knots
Lazy eights 105 knots
Aileron rolls 115 knots
Immelmann’s 130 knots
Cuban eights 130 knots
Loops 115 knots
Vertical reversements 80 knots
Stalls (except whip) Use slow deceleration
Spins Use slow deceleration

Abrupt use of controls prohibited above 108 knots.

Altitude loss in a stall recovery: 160 ft. 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)" (As Applicable)

B. On the flap handle:

(1) Model 150, 150A, 150B, 150C
"Flaps: Pull to extend
Retracted 0°
Takeoff: 1st Notch 10°
2nd Notch 20°
3rd Notch 30°
Landing: 4th Notch 40°"

(2) Model 150D, 150E

"Flaps - Pull to extend
Takeoff: Retracted 0°
Landing: 0°-40°"

C. In the baggage compartment:

(1) Model 150, 150A, 150B, 150C
"Baggage - 80 lb. maximum."

(2) Model 150D, 150E

"Baggage - 120 lb. maximum."

(3) S/N A1500433, 15279406 through 15282031, and A15200735 through A1520808
"120 lb. maximum baggage and/or auxiliary seat passenger. For additional loading
instructions see Weight and Balance Data."
Rev. 51 19 3A19

NOTE 2 (cont’d)

D. On the instrument panel:

Models 150K, A150K, 150L (1971 Model), A150L (1971 Model)
"Do not turn off alternator in flight except in emergency."

E. Near fuel shut-off valve:

(1) Models 150 thru 150M (1977 Model) and A150K thru A150M (1977 Model)
"Fuel 22.5 gals. ON-OFF"

(2) S/N A1500433, 15279406 thru 15282031, and A15200735 thru A1520808
"Fuel 24.5 gals. ON-OFF"

F. On front door posts:

S/N A1500433, A15200735 thru A1520808
"Emergency door release
1. Unlatch door.
2. Pull 'D' ring."

G. On door near window latch:

(1) Models A150K thru A150M (1975 Model)
"Do not open window above 165 m.p.h."

(2) Models A150M (1976 and 1977 Models) and A152 (1978 Model)
"Do not open window above 143 knots IAS."

H. On the instrument panel near over voltage light:

Models 150L, 150M, A150L, A150M, 152 (1978 Model), A152 (1978 Model) and S/N A1500433
"High Voltage"

I. On left hand instrument panel:

S/N A1500433, 15279406 thru 15282031, A1520735 thru A1520808
“Spin Recovery
1. Verify ailerons are neutral and throttle is closed.
2. Apply full opposite rudder.
3. Move control wheel briskly forward to break stall."

J. S/N 681, 15282032 and On, and A1520809 and On

All placards required in the Pilot's Operating Handbook (POH) and FAA Approved Airplane Flight
Manual (AFMS) must be installed in the appropriate locations.

K. Near fuel tank filler:

(1) Model 150 series thru S/N 15079405, A150 series thru S/N A1500734, except S/N A1500433:
"FUEL
80/87 min. grade aviation gasoline
Cap. 13.0 U.S. Gal."

(2) S/N A1500433, 15279406 thru 15282031, and A1520735 thru A1520808:
"FUEL
100LL/100 min. grade aviation gasoline
Cap. 13.0 U.S. Gal."
3A19 20 Rev. 51

NOTE 3. Reserved

NOTE 4. The markings of the airspeed indicator with IAS provides an equivalent level of safety to CAR 3.757 when the
approved airspeed calibration data presented in Section V of the Pilot's Operating Handbooks listed below is
available to the pilot:

Model Cessna P/N Serial Number

150M D1055-13 15077006 thru 15078505)
A150M D1056-13 A1500610 thru A1500684)
150M D1080-13 15078506 thru 15079405)
A150M D1081-13 A1500685 thru A1500734)
152 D1107-13 15279406 thru 15282031)
A152 D1108-13 A1500433and A1520735 thru A1520808)
152 D1136-13PH 15282032 thru 15283591)
A152 D1137-13PH 681, A1520809 thru A1520878)
152 D1170-13PH 15283592 thru 15284541)
A152 D1171-13PH A1520879 thru A1520943)
152 D1190-13PH 15284542 thru 15285161)
A152 D1191-13PH A1520944 thru A1520983)
152 D1210-13PH 15285162 thru 15285594)
A152 D1211-13PH A1520984 thru A1521014)
152 D1229-13PH 15285595 thru 15285833)
A152 D1230-13PH A1521015 thru A1521025)
152 D1249-13PH 15285834 thru 15285939)
A152 D1250-13PH A1521026 thru A1521027)

NOTE 5. 14-volt electrical system

(Models 150 series thru S/N 15079405, and A150 series thru S/N A1500734, except A1500433)

28-volt electrical system

(S/N 681, A1500433, 15279406 and On, A1520735 and On)

In addition to the placards specified above, the prescribed operating limitations indicated by an asterisk (*)
under Sections I through X of this data sheet must also be displayed by permanent markings.

NOTE 6. DELETED.

---------- END ---------