# TCDS A13EU: Textron Aviation Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Textron Aviation Inc.
- Revision: 16
- Revised: April 1, 2019
- Product: Aircraft, Small Airplane
- Certification basis: Part 3, Part 21, Part 36, CAR 3
- Registered aircraft: 4, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/b3/80/b380614663737f56cd9b62bb0d8b6b1442260fcb2be23666c421910b227ac1e8
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/8AA0E9DA4F591F1F862583EE0072A22C.0001
- Page: https://openairdocs.org/tcds/A13EU

## Models (14)

As the data sheet lists them.

- FRA150M
- F150G
- FA152
- F150H
- F152
- F150L
- F150K
- F150M
- F150J
- FA150M
- F150F
- FA150L
- FA150K
- FRA150L

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
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 
 
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

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 t hrough 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 of f 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 Equi pment 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 prohibi ted.  
 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 h andbook 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 
 
---- END ----
```

## ADs (22, in force first)

- [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023
- [AD 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022
- [AD 2009-10-09 R2](https://openairdocs.org/ad/2009-10-09-R2): Rudder Control System · Cessna 150F, 150G, 150H and 23 more. Effective Sep 12, 2011
- [AD 2011-10-09](https://openairdocs.org/ad/2011-10-09): Seat Rails and Roller Housing Inspections · Cessna 150A, 150B, 150C and 221 more. Effective Jun 17, 2011
- [AD 2004-19-01](https://openairdocs.org/ad/2004-19-01): Upper shoulder harness adjusters · Cessna F150G, F150H, F150J and 129 more. Effective Nov 1, 2004
- [AD 2000-06-01](https://openairdocs.org/ad/2000-06-01): Fuel Strainer Assembly · Cessna 150F, 150G, 150H and 163 more. Effective May 5, 2000
- [AD 97-01-13](https://openairdocs.org/ad/97-01-13): Fuel, Oil and Hydraulic Hoses · Cessna 150, 150A, 150B and 232 more. Effective Feb 3, 1997
- [AD 96-09-06](https://openairdocs.org/ad/96-09-06): Air Filter Assemblies · Maule Aerospace Technology 7ACA, 7ECA, 7FC and 180 more. Effective Jun 7, 1996
- [AD 93-24-15](https://openairdocs.org/ad/93-24-15): Instrument Panel Light Rheostat · Cessna F150F, F150G, F150H and 26 more. Effective Feb 11, 1994
- [AD 88-15-06](https://openairdocs.org/ad/88-15-06): Battery Location · Cessna 150, 150A, 150B and 23 more. Effective Aug 3, 1988
- [AD 86-24-07](https://openairdocs.org/ad/86-24-07): Engine Controls Installation · Cessna 150C, 150D, 150E and 142 more. Effective Jan 7, 1987
- [AD 72-03-03 R3](https://openairdocs.org/ad/72-03-03-R3): Wing Flap Actuators Jack Screw · Cessna F150F, F150G, F150H and 83 more. Effective Oct 15, 1984
- [AD 83-22-06](https://openairdocs.org/ad/83-22-06): Aileron Hinge Pin · Cessna 152, 172N, 172P and 18 more. Effective Nov 8, 1983
- [AD 80-25-07 R1](https://openairdocs.org/ad/80-25-07-R1): Oil Coolers · American Champion 7ECA, 7GCAA, 7GCBC and 39 more. Effective Sep 24, 1981
- [AD 80-11-04](https://openairdocs.org/ad/80-11-04): Cracked Nutplates · Cessna 150F, 150G, 150H and 22 more. Effective Jun 2, 1980
- [AD 80-01-06](https://openairdocs.org/ad/80-01-06): Flap Actuator Assembly · Cessna 152, 172RG, A152 and 2 more. Effective Jan 7, 1980
- [AD 76-01-01](https://openairdocs.org/ad/76-01-01): High Speed Flutter · One twelve-gallon auxiliary fuel tank in each outboard wing… (Flint Aero STC SA1809WE). Effective Jan 9, 1976
- [AD 68-17-04](https://openairdocs.org/ad/68-17-04): Stall Warning System · Cessna 150, 150A, 150B and 63 more. Effective Sep 7, 1968
- [AD 2009-10-09 R1](https://openairdocs.org/ad/2009-10-09-R1) (historical): Rudder stop · Cessna 150F, 150G, 150H and 23 more. Effective Dec 11, 2009
- [AD 2009-10-09](https://openairdocs.org/ad/2009-10-09) (historical): Rudder stop · Cessna 150F, 150G, 150H and 21 more. Effective Jun 17, 2009
- [AD 87-20-03 R2](https://openairdocs.org/ad/87-20-03-R2) (historical): Seat Tracks · Cessna 150A, 150B, 150C and 212 more. Effective Sep 24, 1990
- [AD 86-26-04](https://openairdocs.org/ad/86-26-04) (historical): Shoulder Harness Adjuster · Cessna Aircraft Company, The 120, 140, 140A and 134 more. Effective Jan 6, 1987

## Registered aircraft by registry model (OpenAirDocs)

- [Cessna F150H](https://openairdocs.org/model/cessna-f150h): 1 aircraft (registry code 2072540)
- [Cessna F150M](https://openairdocs.org/model/cessna-f150m): 1 aircraft (registry code 2072535)
- [Reims F150M](https://openairdocs.org/model/reims-f150m): 1 aircraft (registry code 7530114)
- [Reims F152](https://openairdocs.org/model/reims-f152): 1 aircraft (registry code 7530113)

## STCs approved under this data sheet (88, first 50)

- [STC SA12428CH](https://openairdocs.org/stc/SA12428CH): Installation of the Lycoming Engines Electronic Ignition System (EIS). Lycoming Engines, An Operating Division of AVCO Corporation
- [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC
- [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC
- [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA01330LA](https://openairdocs.org/stc/SA01330LA): Installation of alternate avionics support assembly.. Radiorax Aviation Systems LLC
- [STC SA00622DE](https://openairdocs.org/stc/SA00622DE): Installation of John Deere AGRI Services, Inc. JD3 Aerial Imaging System,. Aeroptic LLC
- [STC SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation
- [STC SA00871SE](https://openairdocs.org/stc/SA00871SE): Installation of cockpit sunvisors. Rosen Sunvisor Systems LLC
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc.
- [STC SA1219EA](https://openairdocs.org/stc/SA1219EA): Installation of a Sensenich Model 72CKS6-0-56 -54 or -52 metal propeller and a S72CK spinner assembly. Sensenich Propeller Company
- [STC SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC
- [STC SA02987CH](https://openairdocs.org/stc/SA02987CH): Installation of the Electroair Electronic Ignition System. Electroair Acquisition Corporation
- [STC SA2780CE](https://openairdocs.org/stc/SA2780CE): Installation of wing leading edge cuffs, drooped wing tips, stall fences and aileron gap seals.. Curry Aviation LLC
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc.
- [STC SA220SO](https://openairdocs.org/stc/SA220SO): Tow bar, release mechanism, and safety tow link.. Fliegen Works Inc. 
      d/b/a Pacific Aerial Tow Hooks
- [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation
- [STC SA00410BO](https://openairdocs.org/stc/SA00410BO): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation
- [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation
- [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc
- [STC SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation
- [STC SA00344BO PAGE 1](https://openairdocs.org/stc/SA00344BO%20PAGE%201): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies
- [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation
- [STC SA01435SE](https://openairdocs.org/stc/SA01435SE): Installation of J.P. Instruments (JPI) Primary Engine Data Management System. J. P. Instruments
- [STC SA02013CH](https://openairdocs.org/stc/SA02013CH): Installation of Avidyne Corporation Traffic Advisory System (TAS). Avidyne Corporation
- [STC SA00024NY](https://openairdocs.org/stc/SA00024NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K007 on single or multi-engine fixed wing light aircraft incorporating Lycoming reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation
- [STC SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC
- [STC SA00382BO](https://openairdocs.org/stc/SA00382BO): Installation of Globalstar Antenna and Cradle provisions to support a Globalstar GPS-1700 in non-composite airplanes. Avidyne Corporation
- [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley
- [STC SA00343BO](https://openairdocs.org/stc/SA00343BO): Installation of a single configuration or a dual configuration Avidyne Corporation Integrated Flight Display, Model IFD540 loaded with Release 10.0 software (or later FAA approved release). Avidyne Corporation
- [STC SA10077SC](https://openairdocs.org/stc/SA10077SC): Installation of push-button starter system.. Hartzell Engine Technologies, LLC
- [STC SA00352BO PAGE 1](https://openairdocs.org/stc/SA00352BO%20PAGE%201): Installation of an Avidyne Corporation Mode A/C/S Transponder with ADS-B Out capability, Model AXP340 loaded with Version 3.13 software (or later FAA approved version),. Avidyne Corporation
- [STC SA00780SE](https://openairdocs.org/stc/SA00780SE): Installation of the True Lock Safety Retention Axle Lock Nut System. True Lock LLC
- [STC SA02333AK](https://openairdocs.org/stc/SA02333AK): Fabrication and installation of F. Atlee Dodge p/n 8008 Firewall Battery Box. F. Atlee Dodge Aircraft Services, LLC
- [STC SA02119SE PAGE 1](https://openairdocs.org/stc/SA02119SE%20PAGE%201): Installation of Garmin GDL 88 ADS-B UAT Transceiver System. Garmin International Inc
- [STC SA01582SE](https://openairdocs.org/stc/SA01582SE): Fabrication and installation of battery box. Bogert Aviation
- [STC SA484CH](https://openairdocs.org/stc/SA484CH): Installation of instrument light dimmer system.. Tanis Aircraft Products
- [STC SA02442AK PAGE 1](https://openairdocs.org/stc/SA02442AK%20PAGE%201): Approval of the L-3 Communications NGT 2000/2500 ADS-B system. ADS-B Technologies, LLC
- [STC SA01669CH](https://openairdocs.org/stc/SA01669CH): Installation of Challenger Reusable Air Filter. Challenger Aviation Products Inc.
- [STC SA02283SE PAGE 1](https://openairdocs.org/stc/SA02283SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In Flight Data) CGR-30P. Electronics International Inc.
- [STC SA02402SE PAGE 1](https://openairdocs.org/stc/SA02402SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) CGR-30C. Electronics International Inc.
- [STC SA02248LA](https://openairdocs.org/stc/SA02248LA): Installation of Sensor Pod and wiring for a passenger operated monitoring system. Sky IMD Inc
- [STC SA02825NY PAGE 1](https://openairdocs.org/stc/SA02825NY%20PAGE%201): Installation of Aerospace Logic Aircraft Instruments. Aerospace Logic Inc.
- [STC SA03148NY](https://openairdocs.org/stc/SA03148NY): The installation of the Latitude Technologies Corporation S100 Tracking System. Latitude Technologies Corporation
- [STC SA2693NM](https://openairdocs.org/stc/SA2693NM): Installation of Electronics International digital volt/amp gauges and accessories.. Electronics International Inc.

All 88: https://openairdocs.org/tcds/A13EU/stcs.md

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