# TCDS 3A19: Textron Aviation Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Textron Aviation Inc.
- Revision: 51
- Revised: August 1, 2024
- Product: Aircraft, Small Airplane
- Certification basis: Part 23, CAR 3
- Registered aircraft: 9,914, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/69/88/6988f6a0346a0573e6cc0f3de9a66d7629e1a7f5ae07484b2c10338aceb4996a
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID193681345220240924134511.0001
- Page: https://openairdocs.org/tcds/3A19

## Models (18)

As the data sheet lists them.

- 150L
- 150B
- 150D
- A150L
- A150K
- 150E
- A150M
- A152
- 150M
- 150K
- 150C
- 150G
- 150J
- 150A
- 150H
- 150
- 150F
- 152

## 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 19 
Rev No. 51 43 43 41 42 41 41 41 51 51 41 38 50 30 50 32 32 37 50 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
 3A19  
 Revision 51  
 Textron Aviation   
150 150J 
150A 150 K 
150B A150 K 
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 ty pe certificate No. 3A19, prescribes conditio ns and limitations under which the product fo r 
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.

3A19 2 Rev. 51 
I. Models 150, 150A, 150B, 150C  (cont’d) 
 
 *Airspeed Limits (CAS) Neve r 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. usab le, 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  Win g flaps Retracte d 0° 
  Movements  1st notch 10° 
  2nd notch 20° 
  3rd notch 30° 
  4th notch 40° 
 Ailerons Up  20° Down  15° 
 Elevato r U p  25° Down  15° 
 Elevator tab Up  10° Down  20° 
 Rudde r Ri ght  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 ex ceed 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) Retracte d 0°  
  Movements  1st Notch 10°  
  2nd Notch 20°  
  3rd Notch 30°  
  4th Notch 40°  
 Win g flaps (150F)  Down  0° -40° ±2° 
 Ailerons Up 20° Down 15°  
 Elevato r U p 25° Down 15°  
 Elevator tab Up 10° Down 20°  
 Rudder (150D, 150E) Ri ght 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 ex ceed 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.; Refere nce 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 U p 20° +2°, -0° Down 14° +2°, -0° 
 Elevato r Up 25° ±1° Down 15° ±1° 
 Elevator tab U p 10° ±1° Down 20° ±1° 
 Rudde r Right 23° +0°, -2° Left 23° +0°, -2° 
   (measured perpendicularly to hinge line) 
 
 Serial Nos. Eligible Mode l 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 (Acrob atic 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) Neve r 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  Win g flaps   Down   0° -40° ±2° 
  Movements Ailerons Up 20° +2°, -0° Down 14° +2°, -0° 
 Elevato r U p 25° ±1° Down 15° ±1° 
 Elevator tab Up 10° ±1° Down 20° ±1° 
 Rudde r Ri ght 23° +0°, -2° Left 23° +0°, -2° 
    (measured perpendicularly to hinge line) 
 
 Serial Nos. Eligible M odel 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) Neve r 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  Win g flaps   Down   0° -40° ±2° 
  Movements Ailerons Up 20° +2°, -0° Down 14° +2°, -0° 
 Elevato r U p 25° ±1° Down 15° ±1° 
 Elevator tab Up 10° ±1° Down 20° ±1° 
 Rudde r Ri ght 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 (Acrob atic 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) Neve r 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  Win g flaps   Down   0° -40° ±2° 
  Movements Ailerons Up 20° +2°, -0° Down 14° +2°, -0° 
 Elevato r U p 25° ±1° Down 15° ±1° 
 Elevator tab Up 10° ±1° Down 20° ±1° 
 Rudde r Ri ght 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 U p 20° +2°, -0° Down 14° +2°, -0° 
 Elevato r Up 23° +1°, -0° Down 15° ±1° 
 Elevator tab U p 10° ±1° Down 20° ±1° 
 Rudde r 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 (Acr obatic 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 U p 20° +2°, -0° Down 14° +2°, -0° 
 Elevato r Up 23° +1°, -0° Down 15° ±1° 
 Elevator tab U p 10° ±1° Down 20° ±1° 
 Rudde r 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 variati ons 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) 
 Elevato r Up 25° ±1° Down 18° ±1° 
 Elevator tab U p 10° ±1° Down 20° ±1° 
 Rudde r 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 (Acrob atic 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 variati ons 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  Win g flaps   Down   0° -30° ±2° 
Movements Ailerons Up 20°  1° Down 15°  1° 
   (aileron travel measured from 1° ±.5° droop) 
 Elevato r Up 25° ±1° Down 18° ±1° 
 Elevator tab U p 10° ±1° Down 20° ±1° 
 Rudde r 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 ba lance 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 co rresponding 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 co rresponding 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 co rresponding 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 fo rm 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, follo wed 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 th e 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 appr oved 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 th e 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 ar e prohibited.  Inverted flight is prohibited. 
   Child's seat and/or baggage compartmen t 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 appr oved 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 th e 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 pr ohibited.  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 th e 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 approve d 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 (197 8 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 br iskly 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 in dicator 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 A 150 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 ---------
```

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- [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 81-15-03](https://openairdocs.org/ad/81-15-03): Engine Inlet Air Filters · Replace existing engine induction air filter (Brackett Aero Filters STC SA693CE or SA71GL). Effective Jul 20, 1981
- [AD 81-05-01](https://openairdocs.org/ad/81-05-01): Fuel Tank Capacity · Cessna 152, 172N, 172P and 3 more. Effective Mar 2, 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 80-06-03](https://openairdocs.org/ad/80-06-03): Wing Flap Cable Clamp · Cessna 150M, 152, 172N and 3 more. Effective Apr 21, 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 79-08-03](https://openairdocs.org/ad/79-08-03): Electrical System · Cessna 120, 140, 140A and 152 more. Effective Jun 6, 1979
- [AD 79-02-06](https://openairdocs.org/ad/79-02-06): Exhaust System · Cessna 152 and A152. Effective Jan 25, 1979
- [AD 78-25-07](https://openairdocs.org/ad/78-25-07): Vertical Fin Attachment Brackets · Cessna A150M and A152. Effective Dec 22, 1978
- [AD 77-02-09](https://openairdocs.org/ad/77-02-09): Wing Flap System · Cessna 150, 150A, 150B and 61 more. Effective Feb 3, 1977
- [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 75-15-08](https://openairdocs.org/ad/75-15-08): Engine Lubrication · Filtrator Company Engine Crankcase Breather and Vacuum Pump… (D'Shannon Products STC SA2219WE). Effective Sep 10, 1975
- [AD 74-06-02](https://openairdocs.org/ad/74-06-02): AVCON Mufflers · Lycoming 150 and160 hp Model O-320-( ) engine (Williams Robert or Barbara STC SA750CE or 3 others). Effective Mar 18, 1974
- [AD 73-23-07](https://openairdocs.org/ad/73-23-07): Defective Spar Attachment Fittings · Cessna 150, 150A, 150B and 68 more. Effective Nov 19, 1973
- [AD 71-22-02](https://openairdocs.org/ad/71-22-02): Cracks In Nose Gear Fork · Cessna 150, 150A, 150B and 52 more. Effective Nov 9, 1971
- [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 67-31-04](https://openairdocs.org/ad/67-31-04): Removal Of Glove Compartment · Cessna 150G and 150H. Effective Nov 29, 1967
- [AD 67-26-04](https://openairdocs.org/ad/67-26-04): Altimeters · Bell Helicopter Textron Canada 206A, 150G, 172H (USAF T-41A) and 36 more
- [AD 67-03-01](https://openairdocs.org/ad/67-03-01): Exhaust Gas Heat Exchangers · Cessna 150, 150A, 150B and 10 more. Effective Jan 14, 1967
- [AD 62-22-01](https://openairdocs.org/ad/62-22-01): Vacuum Pump Modification · Wet-to-dry vacuum pump conversion kit 300-2 (Parker Hannifin STC SA1-610 or SA1-630). Effective Oct 31, 1962
- [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 152](https://openairdocs.org/model/cessna-152): 1,637 aircraft (registry code 2071835)
- [Cessna 150L](https://openairdocs.org/model/cessna-150l): 1,447 aircraft (registry code 2071826)
- [Cessna 150M](https://openairdocs.org/model/cessna-150m): 1,439 aircraft (registry code 2071830)
- [Cessna 150F](https://openairdocs.org/model/cessna-150f): 1,063 aircraft (registry code 2071814)
- [Cessna 150G](https://openairdocs.org/model/cessna-150g): 977 aircraft (registry code 2071816)
- [Cessna 150H](https://openairdocs.org/model/cessna-150h): 756 aircraft (registry code 2071818)
- [Cessna 150J](https://openairdocs.org/model/cessna-150j): 659 aircraft (registry code 2071820)
- [Cessna 150](https://openairdocs.org/model/cessna-150): 387 aircraft (registry code 2071802)
- [Cessna 150E](https://openairdocs.org/model/cessna-150e): 303 aircraft (registry code 2071812)
- [Cessna 150K](https://openairdocs.org/model/cessna-150k): 303 aircraft (registry code 2071822)
- [Cessna 150D](https://openairdocs.org/model/cessna-150d): 260 aircraft (registry code 2071810)
- [Cessna 150C](https://openairdocs.org/model/cessna-150c): 166 aircraft (registry code 2071808)
- [Cessna 150A](https://openairdocs.org/model/cessna-150a): 122 aircraft (registry code 2071804)
- [Cessna 150B](https://openairdocs.org/model/cessna-150b): 111 aircraft (registry code 2071806)
- [Cessna A150L](https://openairdocs.org/model/cessna-a150l): 80 aircraft (registry code 2071828)
- [Cessna A150M](https://openairdocs.org/model/cessna-a150m): 80 aircraft (registry code 2071831)
- [Cessna A150K](https://openairdocs.org/model/cessna-a150k): 72 aircraft (registry code 2071824)
- [Cessna A152](https://openairdocs.org/model/cessna-a152): 48 aircraft (registry code 2071836)
- [P Z L Koliber 150A](https://openairdocs.org/model/p-z-l-koliber-150a): 4 aircraft (registry code 05626C1)
- [Cessna / De Canio A150K](https://openairdocs.org/model/cessna-de-canio-a150k): 0 aircraft (registry code 2071825)
- [Cessna/Camacho CESSNA 150L](https://openairdocs.org/model/cessna-camacho-cessna-150l): 0 aircraft (registry code 2071827)

## STCs approved under this data sheet (448, first 50)

- [STC SA01233SE](https://openairdocs.org/stc/SA01233SE): Fabrication and installation of Alaskan Bushwheel LLC tail wheel and fork assembly. ABI, LLC
- [STC SA00709CH](https://openairdocs.org/stc/SA00709CH): Installation of replacement wing root vent described by Dwg Nos. 8-30-96-1& 8-30-96-2, no rev, both dtd 8/30/96, or later FAA app rev.. Gallagher Aviation, LLC
- [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 SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of  existing instrument panel lights dimmer control.. TCW Technologies, LLC
- [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC
- [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 SA02069AK](https://openairdocs.org/stc/SA02069AK): Fabrication and installation of the Airglas, Inc., Landes PA32-206LA Nose Fork equipped with up to a 8.50 x 6 tire. Airglas Inc.
- [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 SA01134DE](https://openairdocs.org/stc/SA01134DE): Installation of EarthX ETX680-24-TSO Lithium Battery. EarthX Inc.
- [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC
- [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc.
- [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 SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position  Light System, and applicable associated power supplies. Whelen Aerospace Technologies
- [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 SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc.
- [STC SA04075CH](https://openairdocs.org/stc/SA04075CH): Installation of Dynon EFIS-D10A EAA sales kit part number 102778-000. Dynon Avionics Inc.
- [STC SA01005DE](https://openairdocs.org/stc/SA01005DE): Installation of a EarthX ETX900-TSO Lithium battery. EarthX Inc.
- [STC SA00081NY](https://openairdocs.org/stc/SA00081NY): Installation of Iceman Aviation Supplies, Inc. Carburetor Ice Detector.. Alcor LLC
- [STC SA270SO](https://openairdocs.org/stc/SA270SO): Water and ice detector in fuel gascolator and carburetor.. LegacySTC.com
- [STC SA316SO](https://openairdocs.org/stc/SA316SO): Carburetor ice detector.. LegacySTC.com
- [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 SA00037WI](https://openairdocs.org/stc/SA00037WI): Installation of B & C Specialty Products BC100-1 battery.. B & C Specialty Products Inc
- [STC SA01330LA](https://openairdocs.org/stc/SA01330LA): Installation of alternate avionics support assembly.. Radiorax Aviation Systems LLC
- [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd.
- [STC SA02594SE](https://openairdocs.org/stc/SA02594SE): SkyView HDX Instrumentation and Autopilot System manufactured. Dynon Avionics
- [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding 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 SA00088WI](https://openairdocs.org/stc/SA00088WI): Installation of replacement stabilizer and elevator tips.. Curry Aviation LLC
- [STC SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. 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 SA616NE](https://openairdocs.org/stc/SA616NE): Installation of a Sensenich Model69CKS12 or M69CKS12 fixed-pitch- metal propeller.. Sensenich Propeller Company
- [STC SA02575AK](https://openairdocs.org/stc/SA02575AK): Installation of the nose tire scraper P/N TSL-100. Aero Twin Inc.
- [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine
- [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine
- [STC SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC
- [STC SA00897WI](https://openairdocs.org/stc/SA00897WI): Installation of Concorde Battery Corporation (VRSLA) Valve regulated sealed lead acid battery.. Aero-Mach Wilco LLC
- [STC SA403CE](https://openairdocs.org/stc/SA403CE): Installation of Wipaire Skis Inc. Model A-2000A (Aircraft Skis) (FluiDyne) (Federal) Main and NA-800
Nose Skis. F.Atlee Dodge Aircraft Services
- [STC SA00406WI](https://openairdocs.org/stc/SA00406WI): Installation of replacement flap trailing edge bulbs with AOG Drawing. Athena Aircraft, LLC
- [STC SA00709SE](https://openairdocs.org/stc/SA00709SE): Installation of replacement control surface skin panels.. Athena Aircraft, LLC
- [STC SA02987CH](https://openairdocs.org/stc/SA02987CH): Installation of the Electroair Electronic Ignition System. Electroair Acquisition Corporation
- [STC SA2433CE](https://openairdocs.org/stc/SA2433CE): Installation of aileron and/or flap gap seals.. Curry Aviation LLC
- [STC SA2515CE](https://openairdocs.org/stc/SA2515CE): Installation of replacement wing tips.. Curry Aviation LLC
- [STC SA2662CE](https://openairdocs.org/stc/SA2662CE): Installation of wing leading edge cuffs, drooped tips, stall fences and aileron gap seals.. Curry Aviation LLC
- [STC SA2851CE](https://openairdocs.org/stc/SA2851CE): Installation of wheel fairings.. Curry Aviation LLC
- [STC SA909CE](https://openairdocs.org/stc/SA909CE): Install STOL kit (wing leading edge cuffs, drooped tips, stall fences and aileron gap seals). (152 LANDPLANE). Curry Aviation LLC
- [STC SA01827WI](https://openairdocs.org/stc/SA01827WI): Installation of LED Position Lights.. Aero-Mach Wilco LLC

All 448: https://openairdocs.org/tcds/3A19/stcs.md

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OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.