DEPARTMENT OF TRANSPORTATION

FEDERAL AVIATION ADMINISTRATION

A13EU
Revision 16
Textron Aviation
F150F F152
F150G FA150K
F150H FA150L
F150J FA150M
F150K FA152
F150L FRA150L
F150M FRA150M
April 1, 2019

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. A13EU

This data sheet, which is part of Type Certificate No. A13EU, prescribes conditions and limitations under which the product for
which the Type Certificate was issued meets the airworthiness requirements of the Civil Air 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

Type Certificate A13EU was transferred from Reims Aviation S.A., 51 Aerodrome de Reims-Prunay, Reims, France, to Cessna
Aircraft Company on December 11, 2006. Coincident with this transfer, the Federal Aviation Administration (FAA) has
accepted the status of State of Design and State of Manufacture as defined by Annex 8 to the Convention of International Civil
Aviation. Prior to December 11, 2006, products identified under Type Certificate A13EU were approved by the FAA in
accordance with the Federal Aviation Regulation appropriate to Imported Products (FAR 21.29). Effective December 11, 2006,
and after, these products are to be considered domestic products for the purpose of certification, and Federal Aviation
Regulations 21.21 becomes appropriate.

I. Model F150F, 2 PCLM (Utility Category), Approved February 17, 1966

Engine Continental O-200-A

* Fuel 80/87 min. grade aviation gasoline

* Engine Limits For all operations, 2750 rpm. (100 hp)

Propeller and 1. Sensenich 69CK 24 lb (-32)

Propeller Limits Diameter: not over 69 in., not under 67.5 in.
Static r.p.m. at maximum permissible throttle setting:
Not over 2470, not under 2320
No additional tolerance permitted

2. McCauley 1A101/MCM 21 lb (-32)

Diameter: not over 69 in., not under 67.5 in.
Static r.p.m. at maximum permissible throttle setting:
Not over 2475, not under 2375
No additional tolerance permitted
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18
Rev. No. 16 14 16 16 14 16 16 16 16 16 14 16 11 11 14 11 11 11
A13EU 2 Rev. 16

I. Model F150F (cont’d)

Propeller and 3. McCauley 1A101/DCM 21 lb (-32)

Propeller Limits Diameter: not over 69 in., not under 67.5 in.
(cont’d) Static r.p.m. at maximum permissible throttle setting:
Not over 2600, not under 2500
No additional tolerance permitted

Airspeed Limits (CAS) *Never exceed 162 mph (141 knots)

*Maximum structural cruising 120 mph (104 knots)
*Maneuvering 109 mph (95 knots)
*Flaps extended 100 mph (87 knots)

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

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

Empty Wt. 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)
See NOTE 1 for system fuel.

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

Control Surface Movements Wing Flaps Down 0° - 40° ± 2°

Ailerons Up 20° Down 15°
Elevator Up 25° Down 15°
Elevator Tab Up 10° Down 20°
Rudder Right 23° Left 23°
(measured parallel to chord)

Serial Numbers Eligible F150-0001 thru F150-0067

II. Model F150G, 2 PCLM (Utility Category), Approved September 16, 1966
Model F150H, 2 PCLM (Utility Category), Approved September 5, 1967
Model F150J, 2 PCLM (Utility Category), Approved August 13, 1968
Model F150K, 2 PCLM (Utility Category), Approved August 20, 1969

Engine Rolls Royce Continental O-200-A

* Fuel 80/87 min. grade aviation gasoline

* Engine Limits For all operations, 2750 rpm. (100 hp)

Propeller and 1. McCauley 1A100/MCM 21 lb (-32)

Propeller Limits Diameter: not over 69 in., not under 67.5 in.
Static rpm. at maximum permissible throttle setting:
Not over 2475, not under 2375
No additional tolerance permitted

2. McCauley 1A101/DCM 21 lb (-32)

Diameter: not over 69 in., not under 67 in.
Not over 2600, not under 2500
Rev. 16 3 A13EU

No additional tolerance permitted

II. Model F150G, Model F150H, Model F150J, Model F150K (cont’d)

Airspeed Limits (CAS) *Never exceed 162 mph (141 knots)

*Maximum structural cruising 120 mph (104 knots)
*Maneuvering 109 mph (95 knots)
*Flaps extended 100 mph (87 knots)

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

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

Empty Wt. C.G. Range None

Leveling Means Top surface at 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)
See NOTE 1 for system fuel and oil.

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

See NOTE 1 for data on system fuel and oil.

Control Surface Movements Wing Flaps Down 0° - 40° ± 2°

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 Numbers Eligible F150G: F150-0068 thru F150-0219

F150H: F150-0220 thru F150-0389
F150J: F150-0390 thru F150-0529
F150K: F15000530 thru F15000658

III. Model FA150K, 2 PCLM (Acrobatic Category), Approved November 5, 1969

Engine Rolls-Royce Continental O-200-A

* Fuel 80/87 min. grade aviation gasoline

* Engine Limits For all operations, 2750 rpm. (100 hp)

Propeller and McCauley 1A101/DCM 21 lb (-32)

Propeller Limits Diameter: not over 69 in., not under 67 in.
Static rpm. at maximum permissible throttle setting:
Not over 2600, not under 2500
No additional tolerance permitted

Airspeed Limits (CAS) *Never exceed 193 mph (168 knots)

*Maximum structural cruising 140 mph (122 knots)
*Maneuvering 118 mph (103 knots)
*Flaps extended 100 mph (87 knots)

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

(+31.5) to (+37.5) at 1280 lbs. or less
Straight line variation between points given.
A13EU 4 Rev. 16

III. Model FA150K (cont’d)

Empty Wt. C.G. Range None

Leveling Means Top surface at 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)
See NOTE 1 for system fuel and oil.

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

See NOTE 1 for data on system fuel and oil.

Control Surface Movements Wing Flaps Down 0° - 40° ± 2°

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 Numbers Eligible FA1500001 through FA1500081

IV. Model F150L, 2PCLM (Utility Category), Approved October 9, 1970

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

2. McCauley 1A101/HCM (1973, 1974 models) 27.7 lb (-34.5)

Diameter: not over 69 in., not under 67 in.
Static r.p.m. at maximum permissible throttle setting:
Not over 2600, not under 2500
No additional tolerance permitted

3. McCauley 1A101/PCM (1974 models) 27.0 lb (-34.5)

Diameter: not over 69 in., not under 67 in.
Static r.p.m. at maximum permissible throttle setting:
Not over 2600, not under 2500
No additional tolerance permitted
(See Note 4 for Data on serial number eligibility)

4. McCauley 1A102/OCM (1971 through 1974 models) 27.0 lb (-34.5)

Diameter: not over 69 in., not under 67.5 in.
Static r.p.m. at maximum permissible throttle setting:
Not over 2560, not under 2460
No additional tolerance permitted
Rev. 16 5 A13EU

IV. Model F150L (cont’d)

Airspeed Limits (CAS) *Never exceed 162 mph (141 knots)

*Maximum structural cruising 120 mph (104 knots)
*Maneuvering 109 mph (95 knots)
*Flaps extended 100 mph (87 knots)

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

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

Empty Wt. C.G. Range None

Leveling Means Jig located nut plates and screws at Station +94.63 and Station 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. total, (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 Movements Wing Flaps Down 0° - 40° ± 2°

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 Numbers Eligible F15000659 through F15001143

V. Model FA150L, 2PCLM (Acrobatic Category), Approved October 9, 1970

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

2. McCauley 1A101/HCM (1971, 1972, 1973 models) 27.7 lb (-34.5)

Diameter: not over 69 in., not under 67 in.
Static r.p.m. at maximum permissible throttle setting:
Not over 2600, not under 2500
No additional tolerance permitted

3. McCauley 1A102/OCM (1971 through 1974 models) 27.0 lb (-34.5)

Diameter: not over 69 in., not under 67.5 in.
Static r.p.m. at maximum permissible throttle setting:
Not over 2560, not under 2460
A13EU 6 Rev. 16

No additional tolerance permitted

V. Model FA150L (cont’d)

Airspeed Limits (CAS) *Never exceed 193 mph (168 knots)

*Maximum structural cruising 140 mph (122 knots)
*Maneuvering 118 mph (103 knots)
*Flaps extended 100 mph (87 knots)

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

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

Empty Wt. C.G. Range None

Leveling Means Jig located nut plates and screws at Station +94.63 and Station 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. total, (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 Movements Wing Flaps Down 0° - 40° ± 2°

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 Numbers Eligible FA1500082 through FA1500120

VI. Model FRA150L or FA150L (when equipped with FKA150-2311 and FKA-2316), 2PCLM (Acrobatic Category),
Approved December 3, 1971

Engine Rolls-Royce Continental O-240-A

* Fuel 100/130 min. grade aviation gasoline

* Engine Limits For all operations, 2800 rpm. (130 hp)

Propeller and McCauley 1A135/BRM 24.8 lb (-34.5)

Propeller Limits Diameter: not over 71 in., not under 70 in.
Static rpm. at maximum permissible throttle setting:
Not over 2500, not under 2400
No additional tolerance permitted

Airspeed Limits (CAS) *Never exceed 193 mph (168 knots)

*Maximum structural cruising 140 mph (122 knots)
*Maneuvering 118 mph (103 knots)
*Flaps extended 100 mph (87 knots)

C.G. Range (+33.0) to (+37.5) at 1650 lbs.

(+31.5) to (+37.5) at 1350 lbs. or less
Straight line variation between points given.
Rev. 16 7 A13EU

VI. Model FRA150L or FA150L (when equipped with FKA150-2311 and FKA-2316) (cont’d)

Empty Wt. C.G. Range None

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

* Maximum Weight 1650 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. total, (22.5 gal. usable, two 13 gal. tanks in wings at +42.0)
See NOTE 1 for system fuel and oil.

Oil Capacity 6 qt. (-18, unusable 2 qt.).

See NOTE 1 for data on undrainable oil.

Control Surface Movements Wing Flaps Down 0° - 40° ± 2°

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 Numbers Eligible FRA1500121 through FRA1500261

FA1500121 through FA1500261 (when equipped with FKA150-2311 and FKA-2316)

VII. Model F150M, 2PCLM (Utility Category), Approved October 8, 1974

Engine Continental O-200-A

* Fuel 80/87 min. grade aviation gasoline

* Engine Limits For all operations, 2750 rpm (100 hp)

Propeller and McCauley 1A102/OCM 27.7 lb (-34.5)

Propeller Limits Diameter: not over 69 in., not under 67.5 in.
Static rpm. at maximum permissible throttle setting:
Not over 2560, not under 2460
No additional tolerance permitted

Airspeed Limits (CAS) F150M (1975 Model)

*Never exceed 162 mph (141 knots)
*Maximum structural cruising 120 mph (104 knots)
*Maneuvering 109 mph (95 knots)
*Flaps extended 100 mph (87 knots)

Airspeed Limits (IAS) F150M (1976 Model and on)

(See NOTE 3 on use of IAS) *Never exceed 141 knots
*Maximum structural cruising 107 knots
*Maneuvering 97 knots
*Flaps extended 85 knots

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

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

Empty Wt. C.G. Range None

A13EU 8 Rev. 16

VII. Model F150M (cont’d)

Leveling Means Jig located nut plates and screws at Station +94.63 and Station 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. total, (22.5 gal. usable, two 13 gal. tanks in wings at +42.0)
See NOTE 1 for system fuel and oil.

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

See NOTE 1 for data on undrainable oil.

Control Surface Movements Wing Flaps Down 0° - 40° ± 2°

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 Numbers Eligible F15001144 through F15001428

VIII. Model FRA150M or FA150M (when equipped with FKA150-2311 and FKA150-2316) 2PCLM (Acrobatic
Category), Approved October 8, 1974

Engine Rolls Royce O-240-A or O-240-E (S/N FA00262 and on)

* Fuel 100/130 min. grade aviation gasoline

* Engine Limits (O-240-A) For all operations, 2800 rpm. (130 hp)
(O-240-E) - Takeoff (5 min.) 2800 rpm. (130 hp)
For all other operations 2650 rpm. (123 hp)

Propeller and McCauley 1A135/BRM 24.8 lb (-34.5)

Propeller Limits Diameter: not over 71 in., not under 70 in.
Static rpm. at maximum permissible throttle setting:
Not over 2500, not under 2400
No additional tolerance permitted

Airspeed Limits (CAS) FRA150M (1975 Model)

*Never exceed 193 mph (168 knots)
*Maximum structural cruising 140 mph (122 knots)
*Maneuvering 118 mph (103 knots)
*Flaps extended 100 mph (87 knots)

Airspeed Limits (IAS) FRA150M (1976 Model and up)

(See NOTE 3 on use of IAS) *Never exceed 164 knots
*Maximum structural cruising 123 knots
*Maneuvering 105 knots
*Flaps extended 85 knots

C.G. Range (+32.9) to (+37.5) at 1650 lbs.

(+31.5) to (+37.5) at 1350 lbs. or less

Empty Wt. C.G. Range None

Rev. 16 9 A13EU

VIII. Model FRA150M or FA150M (when equipped with FKA150-2311 and FKA150-2316) (cont’d)

Leveling Means Jig located nut plates and screws at Station +94.63 and Station 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 +142.0)
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 Movements Wing Flaps Down 0° - 40° ± 2°

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

Serial Numbers Eligible FRA1500262 through FRA1500336

FA1500262 through FA1500336 (when equipped with FKA150-2311 and
FKA150-2316)

IX. Model F152, 2PCLM (Utility Category), Approved June 2, 1977

Engine Lycoming O-235-L2C (1978 through 1982 model)

Lycoming O-235-N2C (1983 model and on and aircraft reworked per SK152-15 or
SK152-16)

* Fuel 100LL/100 min. grade aviation gasoline

* Engine Limits For all operations, 2550 rpm. (110 hp) (1978 through 1982 model)
For all operations, 2550 rpm. (108 hp) (1983 model and on)

Propeller and (a) McCauley 1A103/TCM6958 23.2 lb (-36.5)

Propeller Limits Diameter: not over 69 in., not under 67.5 in.
Static rpm. at full throttle (carburetor heat off and
mixture leaned to maximum rpm. is 2280 to 2380 rpm.
No additional tolerance permitted
(b) Spinner: Dwg. 0450073

Airspeed Limits (IAS) *Never exceed 149 knots

(See NOTE 3 on use of IAS) *Maximum structural cruising 111 knots
*Maneuvering 104 knots
*Flaps extended 85 knots

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

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

Empty Wt. C.G. Range None

Leveling Means Jig located nut plates and screws at Station +94.63 and Station 132.9 on
left side of tailcone.
A13EU 10 Rev. 16

IX. Model F152 (cont’d)

* Maximum Weight 1670 lb.

1675 lb. ramp weight (1979 model 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. total, (24.5 gal. usable, two 13 gal. tanks in wings at +42.0)
See NOTE 1 for data on unusable oil.

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

See NOTE 1 for data on undrainable oil.

Control Surface Movements Wing Flaps Down 0° - 30° ± 2°

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)

Serial Numbers Eligible F15201429 through F15201980

X. Model FA152, 2PCLM (Acrobatic Category), Approved June 2, 1977

Engine Lycoming O-235-L2C (1978 through 1982 model)

Lycoming O-235-N2C (1983 model and on and aircraft reworked per SK152-15 or
SK152-16)

* Fuel 100LL/100 min. grade aviation gasoline

* Engine Limits For all operations, 2550 rpm. (110 hp) (1978 through 1982 model)
For all operations, 2550 rpm. (108 hp) (1983 model and on)

Propeller and (a) McCauley 1A103/TCM6958 23.2 lb (-36.5)

Propeller Limits Diameter: not over 69 in., not under 67.5 in.
Static rpm. at full throttle (carburetor heat off and
mixture leaned to maximum rpm.) is 2280 to 2380 rpm.
For allowable variations in static rpm. at non-standard
temperatures, refer to the Service manual.
(b) Spinner: Dwg. 0450073

Airspeed Limits (IAS) *Never exceed 172 knots

(See NOTE 3 on use of IAS) *Maximum structural cruising 125 knots
*Maneuvering 108 knots
*Flaps extended 85 knots

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

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

Empty Wt. C.G. Range None

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

* Maximum Weight 1670 lb.

1675 lb. ramp weight (1979 model and on)
Rev. 16 11 A13EU

X. Model FA152 (cont’d)

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. total, (24.5 gal. usable, two 13 gal. tanks in wings at +42.0)
See NOTE 1 for data on unusable oil.

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

See NOTE 1 for data on undrainable oil.

Control Surface Movements Wing Flaps Down 0° - 30° ± 2°

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)

Serial Numbers Eligible FA1520337 through FA1520425

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.

F152/FA152 comply with FAR 36 dated December 1, 1969 plus

Amendments 36-1 through 36-5.

Date of Application for Type Certificate: 27 September 1966.

Type Certificate No. A13EU issued 17 February 1966.

Equivalent Safety Items Airspeed indicator CAR 3.757 (See NOTE 3)

Operating Limitations CAR 3.778 (a)

Equipment The basic required equipment as prescribed in the applicable airworthiness regulations
(see Certification Basis) must be installed in the aircraft for certification. In addition
the following item of equipment is required:

Stall warning indicator, Audible, Cessna Dwg. 0413029.

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.

FRA150M (1976 Model): F150G thru F150M (1976 Model), FA150K, FA150L, FRA150L, FRA150M:
The certificated empty weight and corresponding center of gravity location must include unusable fuel of 21
lb. at +40 and undrainable oil of (0) lb at -13.5.

F150M (1977 Model), FRA150M (1977 Model):

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.

F152, FA152:
The certificated empty weight and corresponding center of gravity locations must include unusable fuel of 9
lb. at (+40) and full oil of 11.3 lb. at (-14.7) for landplane.
A13EU 12 Rev. 16

Data Pertinent To All Models (cont’d)

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 F150G, F150H, F150J and F150K:

“Acrobatic maneuvers are limited to the following:

Maneuver Entry Speed

Chandelle 109 mph (95 knots)
Steep Turns 109 mph (95 knots)
Lazy Eights 109 mph (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 1600 lb.
Maximum maneuvering speed 109 mph (95 knots)

Maximum flight maneuvering load factors

Flaps up +4.4, -1.76
Flaps down +3.5°”

(3) Model FA150K

“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 mph (103 knots)
Refer to weight and balance data for landing instructions
Flight maneuvering load factors
Flaps up +6.0, -3.0
Flaps down +3.5°
Acrobatic maneuvers with flaps extended are prohibited.
Inverted flight is prohibited.
Child’s seat and/or baggage compartment must not be occupied during acrobatic maneuvering.
Spin recovery: apply opposite rudder, followed by forward elevator for normal recovery.

THE FOLLOWING ACROBATIC MANEUVERS ARE APPROVED:

Maneuver Entry Speed Maneuver Entry Speed

Chandelles 120 mph (104 knots) Lazy Eights 120 mph (104 knots)
Steep Turns 110 mph (96 knots) Spins Slow deceleration
Barrel Rolls 130 mph (113 knots) Aileron Rolls 130 mph (113 knots)
Snap Rolls 90 mph (78 knots) Immelmans 145 mph (126 knots)
Loops 130 mph (113 knots) Cuban Eights 145 mph (126 knots)
Vertical Stalls (except
Reversements 90 mph (78 knots) Whip Stalls) Slow deceleration”
Rev. 16 13 A13EU

Data Pertinent To All Models (cont’d)

NOTE 2. (cont’d)

(4) Model F150L and F150M (1971 Model through 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 109 mph CAS (95 knots)
Gross Weight 1600 lb.
Flight Load Factor Flaps Up +4.4, -1.76
Flaps Down +3.5

Maneuver Max. Entry Speed Maneuver Max. Entry Speed

Chandelles 109 mph (95 knots) Spins Slow Deceleration
Lazy Eights 109 mph (95 knots) Stalls (except
Steep Turns 109 mph (95 knots) whip stalls) Slow Deceleration

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)

(5) Model FA150L, FRA150L and FRA150M(1971 Model through 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 118 mph (CAS) (103 knots)
Gross Weight 1650 lb (FRA150L and M)
1600 lb (FA150L)
Flight load factor Flaps up +6.0, -3.0
Flaps down +3.5

Acrobatic maneuvers with flaps extended are prohibited.

Inverted flight is prohibited.
Child’s seat and/or baggage compartment must not be occupied during acrobatics.

Maneuver Recom. Entry Speed Maneuver Recom. Entry Speed

Chandelles 120 mph (104 knots) Lazy Eights 120 mph (104 knots)
Steep Turns 110 mph (96 knots) Spins Slow Deceleration
Barrel Rolls 130 mph (113 knots) Aileron Rolls 130 mph (113 knots)
Snap Rolls 90 mph (78 knots) Immelmans 145 mph (126 knots)
Loops 130 mph (113 knots) Cuban Eights 145 mph (126 knots)
Vertical Stalls (except
Reversements 90 mph (78 knots) Whip Stalls) Slow Deceleration

Spin Recovery: opposite rudder - forward elevator - neutralize controls.

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)

A13EU 14 Rev. 16

Data Pertinent To All Models (cont’d)

NOTE 2. (cont’d)

(6) Model F150M (1976 and 1977)

“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) 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 Recom. Entry Speed Maneuver Recom. Entry speed

Chandelles 95 knots Spins Slow Deceleration
Lazy Eights 95 knots Stalls(except
Steep Turns 95 knots whip Stalls) Slow Deceleration

Abrupt use of the controls prohibited above 97 knots.

Spin recovery: opposite rudder - forward elevator - neutralize controls.
Intentional spins with flaps extended are prohibited.
Flight into known icing condition prohibited.
This airplane is certified for the following flight operations as of date of original airworthiness
certificate:

(DAY - NIGHT - VFR - IFR)” (As applicable)

(7) Model FRA150M (1976 and 1977)

“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 1650 lb.
Flight load factor Flaps up +6.0, -3.0
Flaps down +3.5

Acrobatic maneuver with flaps extended are prohibited.

Inverted flight is prohibited.
Baggage compartment and/or child’s seat must not be occupied during acrobatics.

Maneuver Recom. Entry Speed Maneuver Recom. Entry Speed

Chandelles 105 knots Lazy Eights 105 knots
Steep Turns 100 knots Spins Slow Deceleration
Barrel Rolls 115 knots Aileron Rolls 115 knots
Snap Rolls 80 knots Immelmans 130 knots
Loops 115 knots Cuban Eights 130 knots
Vertical Stalls (except
Reversements 80 knots Whip Stalls) Slow
Deceleration

Abrupt use of the controls prohibited above 105 knots.

Spin recovery: opposite rudder - forward elevator - neutralize controls.
Flight into known icing condition prohibited.
This airplane is certified for the following flight operations as of date of original airworthiness
certificate:

(DAY - NIGHT - VFR - IFR)” (As applicable)

Rev. 16 15 A13EU

Data Pertinent To All Models (cont’d)

NOTE 2. (cont’d)

(8) Model F152 (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 Recom. Entry Speed Maneuver Recom. Entry speed

Chandelles 95 knots Spins Slow Deceleration
Lazy Eights 95 knots Stalls(except
Steep Turns 95 knots whip Stalls) Slow Deceleration

Abrupt use of the controls prohibited above 104 knots.

Intentional spins with flaps extended are prohibited.
Flight into known icing condition 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 FA152 (1978 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) 108 knots
Gross Weight 1670 lb.
Flight load factor Flaps up +6.0, -3.0
Flaps down +3.5

Acrobatic maneuver with flaps extended are prohibited.

Inverted flight is prohibited.
Baggage compartment and/or child’s seat must not be occupied during acrobatics.

THE FOLLOWING ACROBATIC MANEUVERS ARE APPROVED:

Maneuver Recom. Entry Speed Maneuver Recom. Entry Speed

Chandelles 105 knots Lazy Eights 105 knots
Steep Turns 100 knots Spins Slow Deceleration
Barrel Rolls 115 knots Aileron Rolls 115 knots
Snap Rolls 80 knots Immelmans 130 knots
Loops 115 knots Cuban Eights 130 knots
Vertical Stalls (except
Reversements 80 knots Whip Stalls) Slow Deceleration

Abrupt use of the controls prohibited above 108 knots.

Altitude loss in a stall recovery - 160 ft.
Flight into known icing condition prohibited.
This airplane is certified for the following flight operations as of date of original airworthiness
certificate:

(DAY - NIGHT - VFR - IFR)” (As applicable)

A13EU 16 Rev. 16

Data Pertinent To All Models (cont’d)

NOTE 2. (cont’d)

B. In the baggage compartment: (F152, FA152) (1978 Model):

“120 lb. maximum baggage and/or auxiliary seat passenger. For additional loading instructions see
Weight and Balance Data”.

C. On the instrument panel:

(1) Models F150K, FA150K
Models F150L, FA150L and FRA150L (1971):
“Do not turn off alternator in flight except in emergency”

D. Near fuel shutoff valve:

(1) Model F150G through F150N, FA150K through FA150L, FRA150L and
FRA150M (1977 Model):
“Fuel 22.5 gals. ON-OFF”

(2) Model F152 and FA152 (1978 Model):

“Fuel 24.5 gals. ON-OFF”

E. On front door post:

(1) Model FA150K, FA150L, FRA150L, FRA150M, F152 and FA152:
“Emergency door release
a. Unlatch door
b. Pull ‘D’ ring”

F. On door near window latch:

(1) Model FA150K, FA150L, FRA150L and FRA150M (1975 Model):
“Do not open window above 165 mph.”

(2) On FRA150M (1976 and 1977 Model), and FA152 (1978 Model):
“Do not open window above 143 knots IAS”.

G. On the instrument panel near overvoltage light (Model F150L, F150M, FA150L,
FRA150L, FRA150M, F152 (1978 Model) and FA152 (1978 Model):
(1) “High voltage”.

H. On left hand instrument panel:

(1) Model F152 and FA152 (1978 Model):
“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.
4. Neutralize rudder and recover from dive.”

I. Model F152 and FA152 (1979 Model and on):

All placards required in the pilot’s operating handbook and FAA approved airplane
flight manual must be installed in the appropriate locations.
Rev. 16 17 A13EU

Data Pertinent To All Models (cont’d)

NOTE 3. The marking of the airspeed indicator with I.A.S. 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 MODEL YEAR

F150M D1055-13 1976 Model
FRA150M D1056-13 1976 Model
F150M D1080-13 1977 Model
FRA150M D1081-13 1977 Model
F152 D1107-13 1978 Model
FA152 D1108-13 1978 Model
F152 D1136-13 PH 1979 Model
FA152 D1137-13 PH 1979 Model
F152 D1170-13 PH 1980 Model
FA152 D1171-13 PH 1980 Model
F152 D1190-13 PH 1981 Model
FA152 D1191-13 PH 1981 Model
F152 D1210-13 PH 1982 Model
FA152 D1211-13 PH 1982 Model
F152 D1229-13 PH 1983 Model
FA152 D1230-13 PH 1983 Model
F152 D1249-13 PH 1984 Model
FA152 D1250-13 PH 1984 Model
F152 D1270-13 PH 1985 Model
FA152 D1271-13 PH 1985 Model

NOTE 4. RESERVED

NOTE 5. Near fuel tank filler:

A. F150 series through 1977 Model and FA150 series through 1977 Model:
“Fuel
80/87 min. grade aviation gasoline
Cap. 13.0 U.S. Gal.”

B. F152 and FA152 (1978 Model):

“Fuel
100LL/100 min. grade aviation gasoline
Cap. 13.0 U.S. Gal.”

NOTE 6. 14-volt electrical system

(F150 series through 1977 Model and FA150 series through 1977 Model)

28-volt electrical system

(F152 and FA152) (1978 Model and on)

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

NOTE 7. Aircraft manufactured in France prior to December 11, 2006 and subsequently placed on the U.S. Registry,
may be granted a U.S. Airworthiness Certificate on the basis of 14 CFR Part 21, Section 21.183(d). This
will be a recurrent airworthiness certification and requires a statement or attestation of conformity to the
applicable type design at the time of original manufacture be obtained from the DGAC France. (e.g., the
French TC / U.S. 21.29) This “baseline” conformity determination can then be used as a starting point for
which to evaluate the aircraft’s present conformity of type design and condition for safe operation as
required by 21.183(d).(e.g., Review of all modifications and repairs, AD compliance, appropriate
maintenance, etc., depending upon the current exporting authority and any applicable bilateral agreement.)
A13EU 18 Rev. 16

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