# TCDS 3A12: Textron Aviation Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Textron Aviation Inc.
- Revision: 89
- Revised: September 15, 2026
- Product: Aircraft, Small Airplane
- Certification basis: Part 23, CAR 3
- Registered aircraft: 20,230, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/17/1a/171a9fab6d65b93d47341832030d40ab719af9dd2eb05cc1870e4fbccc7d8141
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID175852420220260916212847.0001
- Page: https://openairdocs.org/tcds/3A12

## Models (18)

As the data sheet lists them.

- 172F (USAF T-41A)
- 172M
- 172Q
- 172R
- 172K
- 172G
- 172A
- 172L
- 172
- 172H (USAF T-41A)
- 172P
- 172D
- 172C
- 172E
- 172N
- 172S
- 172B
- 172I

## 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 20 
Rev. No. 89 60 60 60 60 57 64 60 82 60 51 60 67 81 78 85 50 50 55 55 
Page No. 21 22 23 24 25 26 27 28 29 30 31 32 33        
Rev. No. 50 72 59 83 81 80 76 86 77 80 87 89 89        
 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
 3A12  
 Revision 89  
 Textron Aviation   
172 172I   
172A 172K   
172B 172L   
172C 172M   
172D 172N   
172E 172P   
172F (USAF T-41A) 172Q   
172G 172R   
172H (USAF T-41A) 172S  
 September 15, 2026  
 
 
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. 3A12 
 
This data sheet which is part of Type Certificate No. 3A12 prescribes conditions and limitations under which the product for 
which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations.   
 
Type Certificate Holder Textron Aviation Inc. 
One Cessna Boulevard 
Wichita, Kansas 67215 
 
Type Certificate Holder Record Cessna Aircraft Company transferred to  
Textron Aviation Inc. on July 29, 2015 
 
 
I. Model 172, 4 PCLM (Normal Category), approved November 4, 1955; 2 PCLM (Utility Category),  
 approved December 14, 1956 
 
Engine Continental O-300-A or O-300-B 
 
*Fuel 80/87 minimum grade aviation gasoline 
 
*Engine Limits For all operations, 2700 rpm (145 hp)

3A12 2 Rev. 89 
I. Model 172 (cont’d) 
 
 Propeller and  1. McCauley Propeller 
Propeller Limits  Hub:  1A170/DM 
Static r.p.m. at maximum permissible throttle setting: 
 Not over 2360, not under 2230. 
 No additional tolerance permitted. 
Diameter: Not over 76 in., not under 74.5 in. 
Spinner: Dwg. 0550162 
2. Sensenich Propeller  
Hub: M74DR or 74DR 
Static r.p.m. at maximum permissible throttle setting: 
  Not over 2430, not under 2300 
  No additional tolerance permitted 
Diameter: Not over 74 in., not under 72.0 in. 
Spinner:  Dwg. 0550162 
3. McCauley Propeller 
Hub: 1C172/MDM 7652, 53, or 55 30 lb. (-39.0) 
Static r.p.m. at maximum permissible throttle setting: 
  Not over 2350, not under 2250. 
  No additional tolerance permitted. 
Diameter: Not over 76 in., not under 74.5 in. 
Spinner: Dwg. 0550216 
 
 *Airspeed Limits Maneuvering  115 mph (100 knots) 
(CAS) Maximum structural cruising 140 mph (122 knots) 
Never exceed  160 mph (139 knots) 
Flaps extended 100 mph (  87 knots) 
 
C.G. Range Normal   (+40.8)  to  (+46.4)  at 2200 lb. 
   (+36.4)  to  (+46.4)  at 1733 lb. 
Utility category (+38.4)  to  (+40.3)  at 1950 lb. 
   (+36.4)  to  (+40.3)  at 1733 lb. or less 
Straight line variation between points given. 
 
Empty Weight C.G. Range None 
 
*Maximum Weight Normal category 2200 lb. 
 Utility category 1950 lb. 
 
Number of Seats 4 (2 at +36, 2 at +70).  For child's optional jump seat, refer to Equipment List. 
 
Maximum Baggage 120 lb. (+95) 
 
Fuel Capacity 42 gal. total, 37 gal. usable (two 21 gal. tanks in wings at +48).   
 (See NOTE 1 for weight of unusable fuel and oil). 
 
Oil capacity 2 gal. (-20), includes 1 gal. unusable 
 
 Control Surface Movements Wing Flaps Takeoff  Retracted   0° 
   1st notch 10° 
Landing  2nd notch 20° 
  3rd notch 30° 
  4th notch 40° 
Ailerons Up 20° Down 14° 
Elevator tab Up 28° Down 13° 
Elevator Up 28° Down 26° 
Rudder Right 16° Left 16° 
 
 Serial Numbers Eligible 610, 612, 615, 28000 thru 29999,  
36000 thru 36999, 46001 thru 46754.

Rev. 89 3 3A12 
II. Model 172A, 4 PCL-SM (Normal Category), 2 PCLM (Utility Category), approved July 16, 1959;  
Model 172B, Skyhawk, 4 PCL-SM (Normal Category), 2 PCLM (Utility Category), approved June 14, 1960 
 
 Engine Continental O-300-C or O-300-D 
 
 *Fuel 80/87 minimum grade aviation gasoline 
 
 *Engine Limits For all operations, 2700 rpm (145 hp) 
 
 Propeller and 1. McCauley Propeller 
Propeller Limits  Hub: 1C172/EM  7652, 53, or 55 
Static rpm at maximum permissible throttle setting: 
  Not over 2350, not under 2230. 
  No additional tolerance permitted. 
Diameter: Not over 76 in., not under 74.5 in. 
Spinner:  Dwg. 0550216, or 0550221 or 0550228 
2. McCauley Propeller (seaplane) 
Hub: 1A175/SFC 8040 
Static rpm at maximum permissible throttle setting: 
  Not over 2480, not under 2380. 
  No additional tolerance permitted. 
Diameter: Not over 80 in., not under 78.4 in. 
Spinner:  Dwg. 0550216 or 0550221 
3. Sensenich Propeller 
Hub: 74DC-0-56 
Static rpm at maximum permissible throttle setting: 
  Not over 2420, not under 2300. 
  No additional tolerance permitted. 
Diameter: Not over 74 in., not under 72.5 in. 
 
 *Airspeed Limits Maneuvering   115 mph (100 knots) 
(CAS) Maximum structural cruising 140 mph (122 knots) 
Never exceed   160 mph (139 knots) 
Flaps extended  100 mph (  87 knots) 
 
 C.G. Range Landplane (Model 172A): 
Normal category (+40.8)  to  (+46.4)  at 2200 lb. 
  (+36.4)  to  (+46.4)  at 1733 lb. or less 
Utility category (+38.4)  to  (+40.3)  at 1950 lb. 
  (+36.4)  to  (+40.3)  at 1733 lb. or less 
Straight line variation between points given. 
 
Landplane (Model 172B): 
Normal category (+40.4)  to  (+46.4)  at 2200 lb. 
  (+36.4)  to  (+46.4)  at 1850 lb. or less 
Utility category (+37.4)  to  (+40.3)  at 1950 lb. 
  (+36.4)  to  (+40.3)  at 1850 lb. or less 
Seaplane (Models 172A, 172B): 
Normal category (+39.8)  to  (+45.5)  at 2220 lb. 
   (+36.4)  to  (+45.5)  at 1825 lb. or less 
Straight line variation between points given. 
 
 Empty Weight C.G. Range None 
 
 *Maximum Weight Landplane: 
Normal category 2200 lb. 
Utility category 1950 lb. 
Seaplane: 
Normal category 2220 lb.

3A12 4 Rev. 89 
II. Model 172A (cont’d) 
 
 Number of Seats 4 (2 at +36, 2 at +70).  For child's optional jump seat, refer to Equipment List. 
 
 Maximum Baggage 120 lb.  (+95) 
 
 Fuel Capacity Model 172A:  42 gal. total, 37 gal. usable   
Model 172B:  39 gal. usable (two 21 gal. tanks in wings at +48)   
(See NOTE 1 for weight of unusable fuel and oil). 
 
 Oil Capacity 2 gal.  (-20), 1 gal. usable 
 
 Control Surface Movements Wing Flaps Takeoff  Retracted   0° 
   1st notch 10° 
 Landing  2nd notch 20° 
   3rd notch 30° 
   4th notch 40° 
Ailerons Up 20° Down 15° 
Elevator tab Up 28° Down 13° 
Elevator Up 28° Down 26° 
Rudder (landplane) Right 16° Left 16° 
 (seaplane) Right 19° Left 15° 
(Measured parallel to W.L.) 
 
 Serial Numbers Eligible Model 172A: 622, 625, 46755 thru 47746 
Model 172B: 630, 17247747 thru 17248734 
 
III. Model 172C, 4 PCL-SM (Normal Category), 2 PCLM (Utility Category), approved July 18, 1961 
 
 Engine Continental O-300-C or O-300-D 
 
 *Fuel 80/87 minimum grade aviation gasoline 
 
 *Engine Limits For all operations, 2700 rpm (145 hp) 
 
 Propeller and 1. McCauley Propeller 
Propeller Limits  Hub: 1C172/EM 7652, 53, or 55 
Static rpm, at maximum permissible throttle setting: 
  Not over 2350, not under 2230. 
  No additional tolerance permitted. 
Diameter: Not over 76 in., not under 74.5 in. 
Spinner: Dwg. 0550216, 0550221 or 0550228 
2. McCauley Propeller (seaplane) 
Hub: 1A175/SFC 8040 
Static rpm, at maximum permissible throttle setting: 
  Not over 2480, not under 2380. 
  No additional tolerance permitted. 
Diameter: Not over 80 in., not under 78.4 in. 
Spinner: Dwg. 0550216 or 0550221 
3. Sensenich Propeller 
Hub: 74DC-0-56 
Static rpm at maximum permissible throttle setting: 
  Not over 2420, not under 2300. 
  No additional tolerance permitted. 
Diameter: Not over 74 in., not under 72.5 in. 
 
 *Airspeed Limits Maneuvering  115 mph (100 knots) 
(CAS) Maximum structural cruising 140 mph (122 knots) 
Never exceed  160 mph (139 knots) 
Flaps extended 100 mph (  87 knots)

Rev. 89 5 3A12 
III.  Model 172C (cont’d) 
 
 C.G. Range Landplane: 
Normal category (+40.5)  to  (+46.4)  at 2250 lb. 
   (+36.4)  to  (+46.4)  at 1850 lb. or less 
Utility category (+37.4)  to  (+40.3)  at 1950 lb. 
   (+36.4)  to  (+40.3)  at 1850 lb. or less 
Seaplane: 
Normal category (+39.8)  to  (+45.5)  at 2220 lb. 
   (+36.4)  to  (+45.5)  at 1825 lb. or less 
Straight line variation between points given. 
 
 Empty Weight C.G. Range None 
 
 *Maximum Weight Landplane: 
Normal category 2250 lb. 
Utility category 1950 lb. 
Seaplane: 
 Normal category 2220 lb. 
 
 Number of Seats 4 (2 at +36, 2 at +70).  For child's optional jump seat, refer to Equipment List. 
 
 Maximum Baggage 120 lb.  (+95) 
 
 Fuel Capacity 39 gal. total, 36 gal. usable (two 19.5 gal. tanks in wings at +48). 
  (See NOTE 1 for weight of unusable fuel and oil). 
 
 Oil Capacity 2 gal. (-20), includes 1 gal. unusable 
 
 Control Surface Movements Wing Flaps Takeoff  Retracted   0° 
  1st notch 10° 
Landing  2nd notch 20° 
  3rd notch 30° 
  4th notch 40° 
Ailerons Up 20° Down 15° 
Elevator tab Up 28° Down 13° 
Elevator Up 28° Down 26° 
Rudder (Landplane) Right 16° Left 16° 
 (Seaplane) Right 19° Left 15° 
(Measured parallel to W.L.) 
 
 Serial Numbers Eligible 17248735 thru 17249544 
 
IV. Model 172D, 4 PCL-SM (Normal Category), 2 PCLM (Utility Category), approved June 19, 1962 
 Model 172E, 4 PCL-SM (Normal Category), 2 PCLM (Utility Category), approved June 27, 1963 
Model 172F (USAF T-41A), 4 PCL-SM (Normal Category), 2 PCLM (Utility Category), approved April 21, 1964 
 Model 172G, 4 PCL-SM (Normal Category), 2 PCLM (Utility Category), approved June 15, 1965 
Model 172H (USAF) T-41A), 4 PCL-SM (Normal Category), 2 PCLM (Utility Category), approved June7, 1966 
 
Engine Continental O-300-C or O-300-D 
 
*Fuel 80/87 minimum octane aviation gasoline 
 
*Engine Limits For all operations, 2700 rpm (145 hp)

3A12 6 Rev. 89 
IV.  Models 172D, 172E, 172F, 172G, 172H (cont’d) 
 
 Propeller and 1. McCauley Propeller 
 Propeller Limits  Hub: 1C172/EM 7652, 53 
Static rpm at maximum permissible throttle setting: 
  Not over 2420, not under 2230. 
  No additional tolerance permitted. 
Diameter: Not over 76 in., not under 74.5 in. 
Spinner: Model 172D/E/F:  Dwg. 0550216, 0550221 or 0550228 
  Model 172G/H:  Dwg. 0550236 
2. McCauley Propeller (seaplane) 
Hub: 1A175/SFC 8040 
Static rpm at maximum permissible throttle setting: 
  Not over 2480, not under 2380. 
  No additional tolerance permitted. 
Diameter: Not over 80 in., not under 78.4 in. 
Spinner: Model 172D/E/F: Dwg. 0550216, 0550221 
  Model 172G/H:  Dwg. 0550236 
 
 *Airspeed Limits Maneuvering   122 mph (106 knots) 
 (CAS) Maximum structural cruising 142 mph (122 knots) 
Never exceed   174 mph (151 knots) 
Flaps extended  100 mph (  87 knots) 
 
 C.G. Range Landplane 
Normal category (+38.5)  to  (+47.3)  at 2300 lb. 
  (+35.0)  to  (+47.3)  at 1950 lb. or less 
Utility category (+35.5)  to  (+40.5)  at 2000 lb. 
 (+35.0)  to  (+40.5)  at 1950 lb. or less 
Seaplane 
Normal category (+39.8)  to  (+45.5)  at 2220 lb. 
  (+36.4)  to  (+45.5)  at 1825 lb. or less 
Straight line variation between points given. 
 
 Empty Weight C.G. Range None 
 
 *Maximum Weight Landplane: 
Normal category  2300 lb. 
Utility category  2000 lb. 
  Seaplane: 
Normal category  2220 lb. 
 
 Number of Seats 4 (2 at +36, 2 at +70).  For child's optional jump seat, refer to Equipment List. 
 
 Maximum Baggage 120 lb. (+95) 
 
 Fuel Capacity 39 gal. total, 36 gal. usable (two 19.5 gal. tanks in wings at +48) 
  (See NOTE 1 for weight of unusable fuel and oil). 
 
 Oil Capacity 2 gal.  (-20), 1 gal. usable 
 
 Control Surface Movements Wing Flaps Takeoff  Retracted   0° 
     1st notch 10° 
   Landing  0° 40° 
Ailerons Up 20° Down 15° 
Elevator tab Up 28° Down 13° 
Elevator Up 28° Down 23° 
(Neutral position is with bottom of balance area flush with bottom of stabilizer) 
Rudder  (landplane) Right 16° Left 16° 
 (seaplane) Right 19° Left 15°

Rev. 89 7 3A12 
IV.  Models 172D, 172E, 172F, 172G, 172H (cont’d) 
 
 Serial Numbers Eligible Model 172D: 17249545 thru 17250572 
Model 172E: 639, 17250573 thru 17251822 
Model 172F: 17251823 thru 17253392 
Model 172G: 17253393 thru 17254892 
Model 172H: 638, 17254893 thru 17256512 (except 17256493) 
 
 
V. Model 172I, 4 PCL-SM (Normal Category), 2 PCLM (Utility Category), approved December 15, 1967 
 Model 172K, 4 PCL-SM (Normal Category), 2 PCLM (Utility Category), approved May 9, 1968 
 
 Engine Lycoming O-320-E2D 
 
 *Fuel 80/87 minimum grade aviation gasoline 
 
 *Engine Limits For all operations, 2700 rpm (150 hp) 
 
 Propeller and 1. McCauley Propeller 
 Propeller Limits  Hub: 1C172/MTM 7653 
Static rpm at maximum permissible throttle setting: 
 Not over 2360, not under 2260. 
 No additional tolerance permitted (see NOTE 3). 
Diameter: Not over 76 in., not under 74 in. 
Spinner: Dwg. 0550320 
2. McCauley Propeller (seaplane) 
Hub: 1A175/ATM 8042 
Static rpm at maximum permissible throttle setting: 
 Not over 2480, not under 2380. 
 No additional tolerance permitted (see NOTE 3). 
Diameter: Not over 80 in., not under 78.4 in. 
Spinner: Dwg. 0550320 
3. McCauley Propeller 
Hub:  1C160/CTM 7553 
Static rpm at maximum permissible throttle setting: 
 Not over 2370, not under 2270. 
 No additional tolerance permitted (see NOTE 3). 
Diameter:  not over 75 in., not under 74 in. 
Spinner: Dwg. 0550320 
4. McCauley Propeller (seaplane) 
Hub:  1A175/ETM 8042 
Static rpm at maximum permissible throttle setting: 
 Not over 2480, not under 2380. 
 No additional tolerance permitted (see NOTE 3). 
Diameter: Not over 80 in., not under 78.4 in. 
Spinner: Dwg. 0550321 
5. McCauley Propeller 
Hub:  1C160/DTM 7553 
Static rpm at maximum permissible throttle setting: 
  Not over 2370, not under 2270. 
  No additional tolerance permitted (see NOTE 3). 
Diameter: Not over 75 in., not under 74 in. 
Spinner: Dwg. 0550320 
 
 *Airspeed Limits Maneuvering  122 mph (106 knots) 
 (CAS) Maximum structural cruising 140 mph (122 knots) 
Never exceed  174 mph (151 knots) 
Flaps extended 100 mph (  87 knots)

3A12 8 Rev. 89 
V. Model 172I, Model 172K (cont'd) 
 
 C.G. Range Landplane: 
Normal category (+38.5)  to  (+47.3)  at 2300 lb. 
  (+35.0)  to  (+47.3)  at 1950 lb. or less 
Utility category (+35.5)  to  (+40.5)  at 2000 lb. 
  (+35.0)  to  (+40.5)  at 1950 lb. or less 
Seaplane (Edo 89-2000 or 89A2000 floats): 
Normal category (+39.8)  to  (+45.5)  at 2220 lb. 
  (+36.4)  to  (+45.5)  at 1825 lb. or less 
Straight line variation between points given. 
 
 Empty Weight C.G. Range None 
 
 *Maximum Weight Landplane: 
Normal category  2300 lb. 
Utility category  2000 lb. 
Seaplane: 
Normal category  2220 lb. 
 
 Number of Seats 4 (2 at +34 to +46, 2 at +73).  Occupant on child's optional jump seat at +93. 
 
 Maximum Baggage 120 lb. at +95 
 
 Fuel Capacity 42 gal. total, 38 gal. usable (two 21 gal. tanks in wings at +48) 
  (See NOTE 1 for weight of unusable fuel and oil). 
 
 Oil Capacity 2 gal.  (-14.0), 1-1/2 gal. usable 
 
 Control Surface Movements Wing Flaps Takeoff   0°  -  10° 
   Landing   0°  -  40°  ±2° 
Ailerons Up 20° ±1° Down 15°  ±1° 
Elevator tab Up 28° +1°, -0° Down 13°  +1°, -0° 
Elevator Up 28° +1°, -0° Down 23°  +1°, -0° 
(Neutral position is with bottom of balance area flush with bottom of stabilizer.) 
Rudder  (landplane) Right 16° ±1° Left 16°  ±1° 
 (seaplane) Right 19° ±1° Left 15°  ±1° 
(Measured parallel to W.L.) 
 
 Serial Numbers Eligible Model 172I: 17256513 thru 17257161 
Model 172K  
  1969 model: 17257162 thru 17258486 
  1970 model: 17258487 thru 17259223 
 
VI. Model 172L, 4 PCL-SM (Normal Category), 2 PCLM (Utility Category), approved May 13, 1970 
 
Engine Lycoming O-320-E2D 
 
*Fuel 80/87 minimum grade aviation gasoline 
 
*Engine Limits For all operations, 2700 rpm (150 hp)

Rev. 89 9 3A12 
VI. Model 172L (cont'd) 
 
 Propeller and 1. McCauley Propeller 
Propeller Limits  Hub: 1C172/MTM 7653 
Static rpm at maximum permissible throttle setting: 
  Not over 2360, not under 2260. 
  No additional tolerance permitted (see NOTE 3). 
Diameter: Not over 76 in., not under 74 in. 
Spinner: Dwg. 0550320 
2. McCauley Propeller (seaplane) 
Hub: 1A175/ATM 8042 
Static rpm at maximum permissible throttle setting: 
  Not over 2480, not under 2380. 
  No additional tolerance permitted (see NOTE 3). 
Diameter: Not over 80 in., not under 78.4 in. 
Spinner: Dwg. 0550320 
3. McCauley Propeller 
Hub: 1C160/CTM 7553 
Static rpm at maximum permissible throttle setting: 
  Not over 2370, not under 2270. 
  No additional tolerance permitted (see NOTE 3). 
Diameter: Not over 75 in., not under 74 in. 
Spinner: Dwg. 0550320 
4. McCauley Propeller 
Hub: 1C160/DTM 7553 
Static rpm at maximum permissible throttle setting: 
  Not over 2370, not under 2270. 
  No additional tolerance permitted (see NOTE 3). 
Diameter: Not over 75 in., not under 74 in. 
Spinner: Dwg. 0550320 
5. McCauley Propeller (Seaplane only) 
Hub: 1A175/ETM 8042 
Static rpm at maximum permissible throttle setting: 
  Not over 2480, not under 2380. 
  No additional tolerance permitted (see NOTE 3). 
Diameter: Not over 80 in., not under 78.4 in. 
Spinner: Dwg. 0550321 
 
 *Airspeed Limits Maneuvering  122 mph  (106 knots) 
(CAS) Maximum structural cruising  140 mph  (122 knots) 
Never exceed   174 mph  (151 knots) 
Flaps extended  100 mph  (  87 knots) 
 
 C.G. Range Landplane 
Normal category (+38.5)  to  (+47.3)  at 2300 lb. 
   (+35.0)  to  (+47.3)  at 1950 lb. or less 
Utility category (+35.5)  to  (+40.5)  at 2000 lb. 
   (+35.0)  to  (+40.5)  at 1950 lb. or less 
Straight line variation between points given. 
 
Seaplane (Edo 89-2000 or 89A2000 floats): 
Normal category (+39.8)  to  (+45.5)  at 2220 lb. 
  (+36.4)  to  (+45.5)  at 1825 lb. or less 
  Straight line variation between points given. 
 
 Empty Weight C.G. Range None 
 
 *Maximum Weight Landplane: 
Normal category  2300 lb. 
Utility category  2000 lb. 
Seaplane: 
Normal category  2220 lb.

3A12 10 Rev. 89 
VI. Model 172L (cont'd) 
 
 Number of Seats 4 (2 at +34  to  +46, 2 at +73).  Occupant on child's optional jump seat at +96. 
 
 Maximum Baggage 120 lb. at +95 
 
 Fuel Capacity 42 gal. total, 38 gal. usable (two 21 gal. tanks in wings at +48). 
(See NOTE 1 for weight of unusable fuel). 
 
 Oil Capacity 2 gal.  (-14.0), 1-1/2 gal. usable. 
(See NOTE 1 for data on undrainable oil). 
 
 Control Surface Movements Wing Flaps  Takeoff   0°  -  10° 
  Landing   0°  -  40°  ±2° 
Ailerons Up 20° ±1° Down 15°  ±1° 
Elevator tab Up 28° +1°, -0° Down 13°  +1°, -0° 
Elevator Up 28° +1°, -0° Down 23°  +1°, -0° 
(Neutral position is with bottom of balance area flush with bottom of stabilizer) 
Rudder (landplane) Right 16° ±1° Left 16°  ±1° 
 (seaplane) Right 19° ±1° Left 15°  ±1° 
(Measured parallel to W.L.) 
 
 Serial Numbers Eligible 1971 model: 17259224 thru 17259903  
1972 model: 17259904 thru 17260758  
 
VII. Model 172M, Skyhawk, 4 PCL-SM (Normal Category), 2 PCLM (Utility Category, approved May 12, 1972 
 
Engine Lycoming O-320-E2D 
 
*Fuel 80/87 minimum grade aviation gasoline 
 
*Engine Limits For all operations, 2700 rpm (150 hp) 
 
Propeller and 1. McCauley Propeller 
Propeller Limits  Hub: 1C160/CTM 7553 
Static rpm at maximum permissible throttle setting: 
  Not over 2370, not under 2270. 
  No additional tolerance permitted (see NOTE 3). 
Diameter: Not over 75 in., not under 74 in. 
Spinner: Dwg. 0550320 
2. McCauley Propeller 
Hub: 1C160/DTM 7553 
Static rpm at maximum permissible throttle setting: 
  Not over 2370, not under 2270. 
  No additional tolerance permitted (see NOTE 3). 
Diameter: Not over 75 in., not under 74 in. 
Spinner: Dwg. 0550320 
3. McCauley Propeller (seaplane) 
Hub: 1A175/ATM 8042 
Static rpm at maximum permissible throttle setting: 
  Not over 2545, not under 2445. 
  No additional tolerance permitted (see NOTE 3). 
Diameter: Not over 80 in., not under 78.4 in. 
Spinner: Dwg. 0550320 
4. McCauley Propeller (seaplane) 
Hub: 1A175/ETM 8042 
Static rpm at maximum permissible throttle setting: 
  Not over 2545, not under 2445. 
  No additional tolerance permitted (see NOTE 3). 
Diameter: Not over 80 in., not under 78.4 in. 
Spinner: Dwg. 0550320

Rev. 89 11 3A12 
VII. Model 172M  (cont'd) 
 
 *Airspeed Limits S/N 17256493, 17260759 thru 17265684: 
(CAS) Maneuvering   112 mph  (  97 knots) 
Maximum structural cruising 145 mph  (126 knots) 
Never exceed   182 mph  (158 knots) 
Flaps extended  100 mph  (  87 knots) 
S/N 17265685 thru 17267584: 
Maneuvering   97 knots 
(See NOTE 4 on use of CAS) Maximum structural cruising 128 knots 
Never exceed   160 knots 
Flaps extended    85 knots 
 
 C.G. Range Landplane: 
Normal category  (+38.5)  to  (+47.3)  at  2300 lb. 
  (+35.0)  to  (+47.3)  at  1950 lb. or less 
Utility category  (+35.5)  to  (+40.5)  at  2000 lb. 
  (+35.0)  to  (+40.5)  at  1950 lb. or less 
 
Seaplane (Edo 89-2000 or 89A2000 floats): 
Normal category  (+39.8)  to  (+45.5)  at  2220 lb. 
   (+36.4)  to  (+45.5)  at  1825 lb. or less 
Straight line variation between points given. 
 
 Empty Weight C.G. Range None 
 
 *Maximum Weight Normal category: 2300 lb. (landplane); 2220 lb. (seaplane) 
Utility category: 2000 lb. (landplane) 
 
 Number of Seats 4 (2 at +34 to +46, 2 at +73).  Occupant on child's optional jump seat at +96. 
 
 Maximum Baggage 120 lb. at +95 
 
 Fuel Capacity 42 gal. total, 38 gal. usable (two 21 gal. tanks in wings at +48) 
(See NOTE 1 for data on unusable fuel). 
 
 Oil Capacity 2 gal.  (-14.0), 1-1/2 gal. usable 
(See NOTE 1 for data on undrainable oil). 
 
 Control Surface Movements Wing Flaps Takeoff   0°  -  10°  (landplane/seaplane) 
 Landing   0°  -  40°  +0°  -2° (landplane) 
    0°  -  30°  ±2° (seaplane) 
Ailerons Up 20° ±1° Down 15°  ±1° 
Elevator tab Up 28° +1°, -0° Down 13°  +1°, -0° 
Elevator Up 28° +1°, -0° Down 23°  +1°, -0° 
(Neutral position is with bottom of balance area flush with bottom of stabilizer.) 
Rudder  (landplane) Right 16° ±1° Left 16°  ±1°  
 (seaplane) Right 19° ±1° Left 15°  ±1°  
(Measured parallel to W.L.) 
 
 Serial Numbers Eligible 1973 model: 17256493, 17260759 thru 17261898 (except 17261445 & 17261578) 
1974 model: 17261899 thru 17263458  
1975 model: 17263459 thru 17265684  
1976 model: 17265685 thru 17267584

3A12 12 Rev. 89 
VIII. Model 172N, Skyhawk, 4 PCL-SM (Normal Category), 2 PCLM (Utility Category), approved May 17, 1976 
 
 Engine Lycoming O-320-H2AD 
 
 *Fuel 100/130 minimum grade aviation gasoline 
(S/N 17261445, 17267585 thru 17269309) 
 
100LL/100 minimum grade aviation gasoline 
(S/N 17261578, 17269310 thru 17274009) 
 
 *Engine Limits For all operations, 2700 rpm (160 hp) 
 
 Propeller and  1. McCauley Propeller 
Propeller Limits  Hub:  1C160/DTM 7557 
Static rpm at maximum permissible throttle setting: 
 Not over 2400, not under 2280. 
 No additional tolerance permitted. 
Diameter: Not over 75 in., not under 74 in. 
Spinner: Dwg. 0550320 
2. McCauley Propeller (seaplane) 
Hub: 1A175/ETM 8042 
Static rpm at maximum permissible throttle setting: 
 Not over 2570, not under 2470. 
 No additional tolerance permitted. 
Diameter: Not over 80 in., not under 78.5 in. 
Spinner: Dwg. 0550320 
 
 *Airspeed Limits Models: 1977, 1978, 1979 
(CAS)  Maneuvering    97 knots 
(see NOTE 4 on use of CAS)  Maximum structural cruising  128 knots  
Never exceed  160 knots 
Flaps extended    85 knots 
 
Model: 1980  
Maneuvering    97 knots 
Maximum structural cruising  127 knots 
Never exceed  158 knots 
Flaps extended    85 knots 
 
 C.G. Range Landplane: 
Normal category (+38.5)  to  (+47.3)  at 2300 lb. 
   (+35.0)  to  (+47.3)  at 1950 lb. or less 
Utility category (+35.5)  to  (+40.5)  at 2000 lb. 
   (+35.0)  to  (+40.5)  at 1950 lb. or less 
 
Seaplane (Edo 89-2000 or 89A2000 floats): 
 Normal category (+39.8)  to  (+45.5)  at 2220 lb. 
   (+36.4)  to  (+45.5)  at 1825 lb. or less 
Straight line variation between points given. 
 
 Empty Weight C.G. Range None 
 
 *Maximum Weight Normal category: 2300 lb. (landplane); 2220 lb. (seaplane) 
  Utility category: 2000 lb. (landplane) 
 
 Number of Seats 4 (2 at +34 to +46, 2 at +73).  Occupant on child's optional jump seat at +96.

Rev. 89 13 3A12 
VIII. Model 172N (cont’d) 
 
 Maximum Baggage 120 lb. at +95 
 
 Fuel Capacity 42 gal. total, 40 gal. usable (two 21.5 gal. tanks in wings at +48) 
  (See NOTE 1 for data on unusable fuel). 
 
 Oil Capacity 1.5 gal.  (-14.0), 1.0 gal. usable 
 
 Control Surface Movements Wing Flaps Takeoff   0°  -  10°  (landplane/seaplane) 
 Landing   0°  -  40°  +0°  -2° (landplane) 
    0°  -  30°  ±2° (seaplane) 
Ailerons Up 20° ±1° Down 15°  ±1° 
Elevator tab Up 28° +1°, -0° Down 13°  +1°, -0° 
Elevator Up 28° +1°, -0° Down 23°  +1°, -0° 
(Neutral position is with bottom of balance area flush with bottom of stabilizer) 
Rudder (landplane) Right 16° ±1° Left 16°  ±1°   
 (seaplane) Right 19° ±1° Left 15°  ±1°   
(Measured parallel to W.L.) 
 
 Serial Numbers Eligible 1977 model: 17261445, 17267585 thru 17269309  
1978 model: 17261578, 17269310 thru 17271034 (except 17270050) 
1979 model: 17271035 thru 17272884  
1980 model: 17270050, 17272885 thru 17274009  
 
IX. Model 172P, Skyhawk, 4 PCL-SM (Normal Category), 2 PCLM (Utility Category), approved May 13, 1980 
 
 Engine Lycoming O-320-D2J 
 
 *Fuel 100LL/100 minimum grade aviation gasoline 
 
 *Engine Limits For all operations, 2700 rpm (160 hp) 
 
 Propeller and 1. McCauley Propeller 
 Propeller Limits  Hub: 1C160/DTM 7557 
Static rpm at maximum permissible throttle setting: 
  Not over 2420, not under 2300 
  No additional tolerance permitted 
Diameter: Not over 75 in., not under 74 in. 
Spinner: Dwg. 0550320 
2. McCauley Propeller (floatplane only) 
Hub: 1A175/ETM 8043 
Static rpm at maximum permissible throttle setting: 
  Not over 2570, not under 2470 
  No additional tolerance permitted 
Diameter: Not over 80 in., not under 78.5 in. 
Spinner:  Dwg. 0550320 
 
 *Airspeed Limits Maneuvering    99 knots (landplane) 
(CAS)     96 knots (floatplane) 
(See NOTE 4 on use of CAS) Maximum structural cruising 127 knots 
Never exceed   158 knots 
Flaps extended    85 knots

3A12 14 Rev. 89 
IX. Model 172P (cont’d) 
 
 C.G. Range Landplane: 
Normal category (+39.5)  to  (+47.3)  at 2400 lb. 
    (+35.0)  to  (+47.3)  at 1950 lb. or less 
Utility category (+36.5)  to  (+40.5)  at 2100 lb. 
    (+35.0)  to  (+40.5)  at 1950 lb. or less 
 
Seaplane (Edo 89-2000 or 89A2000 floats): 
 Normal category (+39.8)  to  (+45.5)  at 2220 lb. 
    (+36.4)  to  (+45.5)  at 1825 lb. or less 
Straight line variation between points given. 
 
 Empty Weight C.G. Range None 
 
 *Maximum Weight Normal category: 2400 lb. (landplane); 2220 lb. (seaplane) 
  Utility category: 2100 lb. (landplane) 
 
 Number of Seats 4 (2 at +34 to +46, 2 at +73).  Occupant on child's optional jump seat at +96. 
 
 Maximum Baggage 120 lb. at +95 
 
 Fuel Capacity 42 gal. total, 40 gal. usable (two 21.5 gal. tanks in wings at +48) 
  (See NOTE 1 for data on unusable fuel). 
 
 Oil Capacity 2 gal.  (-13.1), 1.5 gal. usable 
 
 Control Surface Movements Wing Flaps Takeoff   0°  -  10° 
 Landing   0°  -  30°  +0°,  -2° 
Ailerons Up 20° ±1° Down 15°  ±1° 
Elevator tab (floatplane) Up 28° +1°, -0° Down 13°  +1°, -0°  
 (landplane) Up 22° +1°, -0° Down 19°  +1°, -0°  
Elevator Up 28° +1°, -0° Down 23°  +1°, -0° 
(Neutral position is with bottom of balance area flush with bottom of stabilizer) 
Rudder (landplane) Right 16° ±1° Left 16°  ±1°  
 (seaplane) Right 19° ±1° Left 15°  ±1°  
(Measured parallel to W.L.) 
 
 Serial Numbers Eligible 1981 model: 17274010 thru 17275034 
1982 model: 17275035 thru 17275759 
1983 model: 17275760 thru 17276079 
1984 model: 17276080 thru 17276259 
1985 model: 17276260 thru 17276516 
1986 model: 17276517 thru 17276654

Rev. 89 15 3A12 
X. Model 172Q, Cutlass, 4 PCLM (Normal Category), approved October 15, 1982 
 
 Engine Lycoming O-360-A4N 
 
 *Fuel 100LL/100 minimum grade aviation gasoline 
 
 *Engine Limits For all operations, 2700 rpm (180 hp) 
 
 Propeller and 1. McCauley Propeller 
 Propeller Limits  Hub   1A170E/JFA 7658 
Static rpm at maximum permissible throttle setting: 
  Not over 2450, not under 2350. 
  No additional tolerance permitted. 
Diameter: Not over 76 in., not under 74.5 in. 
Spinner: Dwg. 0509077 
 
 *Airspeed Limits Maneuvering   105 knots 
Maximum structural cruising 127 knots 
Never exceed   158 knots 
Flaps extended    85 knots 
 
 C.G. Range Normal category (+41.0) to (+47.3) at 2550 lb. 
  (+35.0) to (+47.3) at 1950 lb. or less 
Straight line variation between points given. 
 
 Empty Weight C.G. Range None 
 
 *Maximum Weight Normal category:  2550 lb. 
 
 Number of Seats 4 (2 at +34 to +46, 2 at +73)  
(Occupant on optional child's seat at +96) 
 
 Maximum Baggage 120 lbs. at +95 
 
 Fuel Capacity 54 gal. total, 50 gal. usable (two 27 gal. tanks in wings at +48) 
(See NOTE 1 for data on unusable fuel). 
 
 Oil Capacity 9 qt. at -15.5, 2 qt. unusable 
 
 Control Surface Movements Wing Flaps Takeoff 0°  -  10° 
 Landing 0°  -  30°  +0°,  -2° 
Ailerons Up 20° ±1° Down 15°  ±1° 
Elevator tab Up 22° +1°, -0° Down 19°  +1°, -0° 
Elevator Up 28° +1°, -0° Down 23°  +1°, -0° 
(Neutral position is with bottom of balance area flush with bottom of stabilizer) 
Rudder  Right 16° ±1° Left 16°  ±1° 
(Measured parallel to W.L.) 
 
 Serial Numbers Eligible 1983 model: 17275869 thru 17276054 
1984 model: 17276101 thru 17276211

3A12 16 Rev. 89 
Data Pertinent to Models 172 thru 172Q  
 
Datum Front face of firewall (S/N 28000 thru 47746) 
Lower front face of firewall (S/N 17247747 thru 17276654) 
 
Leveling Means Upper doorsill 
 
Certification Basis: 
 
Models 172 thru 172P 
Civil Air Regulations (CAR) Part 3 effective November 1, 1949, as amended by 3-1 through 3-12.  In addition, effective at S/N 
17271035 and On, 23.1559 effective March 1, 1978.   
FAR 36 dated December 1, 1969, plus Amendments 36-1 through 36-5 for Model 172N.   
FAR Part 36 dated December 1, 1969, plus Amendments 36-1 through 36-12 for Models 172P thru 172Q.  In addition, effective 
at S/N 17276260 and On, 23.1545(a), Amendment 23-23 dated December 1, 1978. 
 
Equivalent Safety Items 17261445, 17261578, 17265685 
 
Airspeed Indicator CAR 3.757 (see NOTE 4 on use of CAS) 
(S/N 17261445, 17261578, 17265685 thru 17276259) 
 
Operating Limitations CAR 3.778(a) 
 
Model 172Q 
Part 3 of CAR dated November 1, 1949, as amended by 3-1 through 3-12.  In addition, 23.1559 effective March 1, 1978; 
23.951(b)(2), Amendment 23-15 effective October 31, 1974; and 23.1545(a), Amendment 23-23 effective December 1, 1978.  
FAR 36 dated December 1, 1969, plus amendments 36-1through 36-12. 
 
Application for Type Certificate dated July 11, 1955.  Type Certificate No. 3A12 issued November 4, 1955, obtained by the 
manufacturer under Delegation Option Procedures. 
 
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 FAR. 
 
Equipment: 
The basic required equipment as prescribed in the applicable airworthiness requirements (see Certification Basis) must be 
installed in the aircraft for certification.  This equipment must include a current Airplane Flight Manual (AFM) effective S/N 
17271035 and On. 
 
1. Models 172 thru 172G:  Stall warning indicator, Dwg. 0511062. 
2. Model 172H and On: Stall warning indictor, Dwg. 0523112. 
 
Cessna Publication TS1000-13 should be used for equipment references on all aircraft prior to the Model 
172E.  Refer to applicable equipment list for the Model 172E and subsequent models. 
 
NOTE 1: Current weight and balance report including 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 28000 thru 29999, 36000 thru 36999, 46001 thru 47746, 17247747 thru 17265684 
The certificated empty weight and corresponding center of gravity location must include: 
 Unusable fuel of 30 lb. at (+46) on Models 172 and 172A, or  
 18 lb. at (+46) for Models 172B thru 172H, or 
 24 lb. at (+46) for Models 172I thru 172M (17265684), and  
 Undrainable oil of (0) lb. at -20) for Models 172 thru 172H, and  
 (0) lb. at (-14) for Models 172I thru 172M (17265684). 
 
S/N 17261578, 17261445, 17265685 thru 17274009 
The certificated empty weight and corresponding center of gravity location must include: 
 Unusable fuel of 24 lbs. at (+46) through Model 172M (17267584), or  
 18 lbs. at (+46) 17267585 and On, and  
 full oil of 11.3 lb. at (-14).

Rev. 89 17 3A12 
Data Pertinent to Models 172 thru 172Q (cont'd) 
NOTE 1 (cont’d) 
 
Model 172P, S/N 17274010 thru 17276654: 
The certificated empty weight and corresponding center of gravity location must include:  
Unusable fuel of 18 lb. at (+46) and full oil of 15 lb. at (-13.1). 
 
Model 172Q, S/N 17275869 thru 17276211: 
The certificated empty weight and corresponding center of gravity location must include:  
Unusable fuel of 24 lb. at (+46) and full oil of 16.88 lb. at (-15.5). 
 
NOTE 2. The following placards must be displayed as indicated: 
 
A. In full view of the pilot: 
(1) Models 172, 172A, 172B 
"This airplane must be operated in compliance with the operating limitations stated in the form of 
placards, markings, and manuals. 
 
NORMAL CATEGORY 
Maximum design weight 2200 lb. 
Refer to weight and balance data for loading instructions. 
Flight maneuvering load factors Flaps up +3.8 -1.52 
  Flaps down +3.5 
No acrobatic maneuvers including spins approved. 
 
UTILITY CATEGORY 
Maximum design weight 1950 lb. 
Baggage compartment and rear seat must not be occupied 
Flight maneuvering load factors Flaps up +4.4 -1.76 
  Flaps down +3.5 
 
No acrobatic maneuvers approved except those listed below. 
Maneuver Entry speed 
Chandelles 115 mph (100 knots) 
Lazy eights 115 mph (100 knots) 
Steep turns 115 mph (100 knots) 
Spins  Slow deceleration 
Stalls (except whip stalls) Slow deceleration" 
 
(2) Model 172C 
"This airplane must be operated in compliance with the operating limitations stated in the form of 
placards, markings, and manuals. 
 
NORMAL CATEGORY 
Maximum design weight 2250 lb. 
Refer to weight and balance data for loading instructions. 
Flight maneuvering load factors Flaps up +3.8 -1.52 
  Flaps down +3.5 
No acrobatic maneuvers including spins approved. 
 
UTILITY CATEGORY 
Maximum design weight 1950 lb. 
Baggage compartment and rear seat must not be occupied. 
Flight maneuvering load factors Flaps up +4.4 -1.76 
  Flaps down +3.5 
 
No acrobatic maneuvers approved except those listed below. 
Maneuver Entry speed 
Chandelles 115 mph (100 knots) 
Lazy eights 115 mph (100 knots) 
Steep turns 115 mph (100 knots) 
Spins  Slow deceleration 
Stalls (except whip stalls) Slow deceleration"

3A12 18 Rev. 89 
Data Pertinent to Models 172 thru 172Q (cont'd) 
NOTE 2 (cont’d) 
 
(3) Models 172D, 172E, 172F, 172G, 172H, 172I, 172K 
"This airplane must be operated in compliance with the operating limitations stated in the form of 
placards, markings, and manuals. 
 
 NORMAL CATEGORY 
Maximum design weight 2300 lb. 
Refer to weight and balance data for loading instructions. 
Flight maneuvering load factors: 
  Flaps up +3.8 -1.52 
  Flaps down +3.5 
No acrobatic maneuvers including spins approved. 
 
UTILITY CATEGORY 
Maximum design weight 2000 lb. 
Baggage compartment and rear seat must not be occupied. 
Flight maneuvering load factors Flaps up +4.4 -1.76 
  Flaps down +3.5 
No acrobatic maneuvers except those listed below. 
Maneuver Max. Entry speed 
Chandelles 122 mph (106 knots) 
Lazy eights 122 mph (106 knots) 
Steep turns 122 mph (106 knots) 
Spins  Slow deceleration 
Stalls (except whip stalls) Slow deceleration" 
 
(4) Model 172L (1971 model) 
"This airplane must be operated in compliance with the operating limitations stated in the form of 
placards, markings, and manuals. 
 
   MAXIMUMS 
   Normal Category Utility Category 
Maneuvering speed (CAS) 122 mph (106 knots) 122 mph (106 knots) 
Gross weight 2300 lb. 2000 lb. 
Flight load factor 
 Flaps up +3.8 -1.52 +4.4 -1.76 
 Flaps down +3.5  +3.5 
Normal category: No acrobatic maneuvers including spins approved. 
Utility category: Baggage compartment and rear seat must not be occupied. 
 
No acrobatic maneuvers approved except those listed below. 
Maneuver Entry speed 
Chandelles 122 mph (106 knots) 
Lazy eights 122 mph (106 knots) 
Steep turns 122 mph (106 knots) 
Spins  Slow deceleration 
Stalls (except 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)

Rev. 89 19 3A12 
Data Pertinent to Models 172 thru 172Q (cont'd) 
NOTE 2 (cont’d) 
 
(5) Model 172L (1972 model) 
"This airplane must be operated in compliance with the operating limitations as stated in the form 
of placards, markings, and manuals: 
 
MAXIMUMS 
Normal Category Utility Category 
Maneuvering speed (CAS) 122 mph (106 knots) 122 mph (106 knots) 
Gross weight 2300 lb. 2000 lb. 
Flight load factor 
 Flaps up +3.8 -1.52 +4.4 -1.76 
 Flaps down +3.5  +3.5 
 
Normal category: No acrobatic maneuvers including spins approved 
Utility category: Baggage compartment and rear seat must not be occupied. 
 
No acrobatic maneuvers approved except those listed below. 
Maneuver Max. Entry speed 
Chandelles 122 mph (106 knots) 
Lazy eights 122 mph (106 knots) 
Steep turns 122 mph (106 knots) 
Spins  Slow deceleration 
Stalls (except 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) 
 
(6) Model 172M (Landplane):  
(S/N 17256493, 17260759 thru 17265684, except 17261445 and 17261578) 
"This airplane must be operated in compliance with the operating limitations as stated in the form 
of placards, markings, and manuals. 
 
MAXIMUMS 
Normal Category Utility Category 
Maneuvering speed (CAS) 112 mph (97 knots) 112 mph (97 knots) 
Gross weight 2300 lb. 2000 lb. 
Flight load factor 
 Flaps up +3.8 -1.52 +4.4 -1.76 
 Flaps down +3.0  +3.0 
 
Normal category: No acrobatic maneuvers including spins approved. 
Utility category: Baggage compartment and rear seat must not be occupied. 
 
No acrobatic maneuvers approved except those listed below. 
 
Recommended Recommended 
Maneuver Entry speed  Maneuver Entry Speed 
Chandelles 120 mph (104 knots) Spins Slow deceleration 
Lazy eights 120 mph (104 knots) Stalls (except Slow deceleration 
Steep turns 112 mph (  97 knots)   whip stalls) 
 
Altitude loss in stall recovery: 180 feet. 
Abrupt use of the controls prohibited above 112 mph.

3A12 20 Rev. 89 
Data Pertinent to Models 172 thru 172Q  (cont'd) 
NOTE 2 (cont’d) 
 
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) 
 
Model 172M (Floatplane): 
(S/N 17256493, 17260759 thru 17265684, except 17261445 and 17261578) 
"This airplane must be operated as a normal category airplane in compliance with the operating 
limitations as stated in the form of placards, markings, and manuals. 
 
MAXIMUMS 
Maneuvering speed   110 mph (96 knots) (CAS) 
Gross weight   2220 lbs. 
Flight load factor   Flaps up +3.8, -1.52 
    Flaps down +3.0 
 
WATER RUDDER:  Extend for taxi; retract for takeoff, flight, and landing. 
No acrobatic maneuvers, including spins approved.   
Altitude loss in a stall recovery:  200 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) 
 
(7) Models 172M, 172N (Landplane)   
(S/N 17261445, 17261578, 17265685 thru 17271034, except 17270050) 
"This airplane must be operated in compliance with the operating limitations stated in the form of 
placards, markings, and manuals. 
 
MAXIMUMS 
Normal Category Utility Category 
Maneuvering speed (CAS) 97 knots 97 knots 
Gross weight 2300 lb. 2000 lb. 
Flight load factor 
 Flaps up +3.8 -1.52 +4.4 -1.76 
 Flaps down +3.0  +3.0 
 
Normal category:   No acrobatic maneuvers including spins approved. 
Utility category:  Baggage compartment and rear seat must not be occupied. 
 
NO ACROBATIC MANEUVERS EXCEPT THOSE LISTED BELOW: 
 
Recommended  Recommended 
Maneuver Entry speed  Maneuver Entry Speed 
Chandelles 105 knots  Spins Slow deceleration 
Lazy eights 105 knots  Stalls (except Slow deceleration 
Steep turns   95 knots)    whip stalls) 
 
Altitude loss in stall recovery:   180 feet. 
Abrupt use of the controls prohibited above 97 knots

Rev. 89 21 3A12 
Data Pertinent to Models 172 thru 172Q (cont'd) 
NOTE 2 (cont’d) 
 
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) 
 
Models 172M, 172N (Floatplane):  
(S/N 17265685 thru 17271034) 
 
FLOATPLANE 
"This airplane must be operated as a normal category airplane in compliance with the operating 
limitations as stated in the form of placards, markings, and manuals. 
 
MAXIMUMS 
Maneuvering speed (CAS)  96 knots 
Gross weight   2220 lb. 
Flight load factor Flaps up  +3.8, -1.52 
   Flaps down  +3.0 
 
Water Rudder:  Extend for taxi; retract for takeoff, flight, and landing. 
 
No acrobatic maneuvers, including spins approved.   
Altitude loss in a stall recovery:  200 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. Forward of fuel selector valve (all models through S/N 17265684, except 17261445 and 17261578): 
"Both tanks on for takeoff and landing." 
 
C. On the fuel selector valve (at appropriate location): 
 
(1) Models 172, 172A 
"Both:  37 gal. 
 Left:  18.5 gal. 
 Right:  18.5 gal. 
 Off" 
 
(2) Model 172B 
"Both:  39 gal. 
 Left:  19.5 gal. 
 Right:  19.5 gal. 
 Off" 
 
(3) Models 172C, 172D, 172E, 172F, 172G, 172H 
"Both:  36 gal. 
 Left:  18 gal. 
 Right:  18 gal. 
 Off" 
 
(4) Models 172I thru 172M (except S/N 17261445 and 17261578) 
"Both:  38 gal. (all flight attitudes) 
 Left:  19 gal. (level flight only) 
 Right:  19 gal. (level flight only) 
 Off"

3A12 22 Rev. 89 
Data pertinent to Models 172 thru 172Q  (cont'd) 
NOTE 2 (cont’d) 
 
(5) Model 172N (S/N 17261445, 17261578, 17267585 thru 17271034, excluding 17270050) 
"Both:  40 gal.  (all flight altitudes) (takeoff - landing) 
 Left:  20 gal.  (level flight only) 
 Right:  20 gal.  (level flight only) 
 Off" 
 
D. Models 172 thru 172E 
On flap handle  
(1) "Flaps  -  Pull to extend 
Takeoff Retract   0° 
  1st notch 10° 
Landing 0°  -  40° 
(2) "Avoid slips with flaps down." 
 
E. Model 172F (electric flaps) thru S/N 17271034, excluding 17270050 
Near flap indicator:  "Avoid slips with flaps extended." 
 
F. In baggage compartment: 
(1) Models 172 thru 172B 
 "Maximum baggage 120 lb.  For additional loading instructions, see weight and balance data." 
(2) Models 172C thru 172M (1973 model) 
 "120 lb. maximum baggage and/or auxiliary seat passenger.   
 For additional loading instructions see weight and balance data." 
(3) S/N 17261899 thru 17271034, excluding 17270050 
"120 lb. maximum baggage and/or auxiliary passenger forward of baggage door latch." 
"50 lb. maximum baggage aft of baggage door latch maximum 120 lb. combined. 
For additional loading instructions see weight and balance data." 
 
G. S/N 17258487 thru 17259903. 
Near ammeter:  "Do not turn off alternator in flight except in emergency." 
 
H. Additional placards required in seaplane. 
(1) Models 172A thru 172I, in full view of the pilot: 
"Operate as normal category airplane except: 
Maximum weight 2220 lb. 
Maximum altitude loss in stall recovery 120 ft. 
Flaps  -  takeoff  -  1st notch -10° 
Water rudder  -  pull to extract 
Retract  -  takeoff, flight and landing 
Extend   -  taxi." 
 
(2) Model 172K, in full view of the pilot: 
″THIS AIRPLANE MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING 
LIMITATIONS AS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUALS 
 
NORMAL CATEGORY; FLOATPLANE 
Maximum weight  2220 lb. 
Refer to weight and balance data for loading instructions. 
 
Flight maneuvering load factors  Flaps up +3.8,  -1.52 
     Flaps down +3.5 
 
No acrobatic maneuvers including spins approved. 
Maximum altitude loss in stall recovery: 120 ft. 
 Flaps:  Takeoff  -  10° . . .  Water rudder:  Pull to retract . . . 
 Retract:  Takeoff, flight and landing . . . . Extend:  Taxi."

Rev. 89 23 3A12 
Data Pertinent to Models 172 thru 172Q (cont'd) 
NOTE 2 (cont’d) 
 
(3) Model 172F thru S/N 17271034, excluding 17270050, in full view of the pilot. 
"Floatplane Max. Flaps  -  30°." 
 
(4) Model 172L, in full view of the pilot: 
 
"FLOATPLANE 
THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN 
COMPLIANCE WITH THE OPERATING LIMITATIONS AS STATED IN THE FORM OF 
PLACARDS, MARKINGS, AND MANUALS. 
 
"MAXIMUMS 
Maneuvering speed  122 mph CAS (106 knots) 
Gross weight   2220 lb. 
Flight load factor   Flaps up  +3.8,  -1.52 
    Flaps down  +3.5 
 
WATER RUDDER:  Extend for taxi; retract for takeoff, flight, and landing. 
 
FLAPS:  10° for takeoff 
 
No acrobatic maneuvers, including spins, approved.   
Altitude loss in stall recovery:  120 ft. 
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) 
 
I. Models 172I, 172K, 172L (with IC172/MTM propeller) 
Near tachometer: "Avoid continuous operation 
1. Above 75 percent power in cruise 
2. Above 2500 rpm in full throttle climb." 
 
J. Model 172L (1972 model) thru Model 172N (1978 model) 
Near ammeter and adjacent to overvoltage light:  "High Voltage" 
 
K. Models with S/N 28000 thru 17258855, except those with Cessna Kit No. SK-172-31B  
or SK-172-32 installed near fuel selector valve:  
 
"SWITCH TO SINGLE TANK OPERATION IMMEDIATELY UPON REACHING CRUISE 
ALTITUDES ABOVE 5000 FEET." 
 
L. Near fuel tank filler 
(1) Models 172, 172A, 172B 
 "FUEL 
 80/87 min. grade aviation gasoline 
 Cap. 21 U.S. gal." 
 
(2) Models 172C, 172D, 172E, 172F, 172G, 172H 
 "FUEL 
 80/87 min. grade aviation gasoline 
 Cap. 19.5 U.S. gal." 
 
(3) Models 172I thru 172M (except S/N 17261445 and 17261578) 
 "FUEL 
 80/87 min. grade aviation gasoline 
 Cap. 21 US. gal."

3A12 24 Rev. 89 
Data pertinent to Models 172 thru 172Q (cont'd) 
NOTE 2 (cont’d) 
 
(4) Model 172N (S/N 17261445, 17267585 thru 17269309) 
 "FUEL 
 100/130 min. grade aviation gasoline 
 Cap. 21.5 US. gal." 
 
(5) Model 172N (S/N 17261578, 17269310 thru 17271034, excluding 17270050) 
 "FUEL 
 100LL/100 min. grade aviation gasoline 
 Cap. 21.5 US. gal." 
 
M. Effective at S/N 17270050, 17271035 thru 17276654 
All placards required in the Pilot's Operating Handbook (POH) and FAA Approved AFM must be 
installed in the appropriate locations. 
 
NOTE 3. Compliance with Service Letter SE74-16 (Carburetor Nozzle Replacement) allows rpm's as follows: 
Landplane: not over 2420, not under 2300 
Seaplane: not over 2570, not under 2445 
 
NOTE 4. The marking of the airspeed indicator in CAS provides an Equivalent Level of Safety (ELOS) to CAR 3.757 
when approved airspeed calibration data presented in Section V of the POH below is available to the pilot 
(TIAS is exactly equal to CAS): 
 
MODELS    S/N’s 
172M, Cessna P/N D1057-13 17265685 thru 17267584 
172N, Cessna P/N D1082-13 17261445, 17267585 thru 17269309 
172N, Cessna P/N D1109-13 17261578, 17269310 thru 17271034, except 17270050 
172N, Cessna P/N D1138-13PH 17271035 thru 17272884 
172N, Cessna P/N D1172-13PH 17270050, 17272885 thru 17274009 
172P, Cessna P/N D1192-13PH 17274010 thru 17275034 
172P, Cessna P/N D1212-13PH 17275035 thru 17275759 
172P, Cessna P/N D1231-13PH 17275760 thru 17276079 
172P, Cessna P/N D1251-13PH 17276080 thru 17276259 
 
NOTE 5. 14-volt electrical system 
(Model 172 series thru S/N 17269309, except 17258105 thru 17258112, and 17261578) 
 
28-volt electrical system 
(S/N 17258105 thru 17258112, 17261578 and 17269310 thru 17276654) 
 
NOTE 6. Special Ferry Flight Authorization.  Flight Standards District Offices (FSDO) is authorized to issue Special 
overweight ferry flight authorizations.  These airplanes are structurally satisfactory for ferry flight if 
maintained within the following limits:   
1.  Takeoff weight must not exceed 130% of the maximum weight for Normal Category.  
2.  The Never Exceed Airspeed (VNE) and Maximum Structural Cruising Speed (VC) must be reduced  
 by 30%.  
3. Forward and aft center of gravity limits may not be exceeded.  
4.  Structural load factors of +2.5 g. to -1.0 g. may not be exceeded.   
Requirements for any additional oil should established in accordance with AC 23.1011-1.  Increased stall 
speeds and reduced climb performance should be expected for the increased weights.  Flight characteristics 
and performance at the increased weights have not been evaluated.  Flight Permit for operations of 
overweight aircraft may be found in AC 21-4B.  
 
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.

Rev. 89 25 3A12 
XI. Model 172R, Skyhawk, 4 PCLM (Normal Category), 2 PCLM (Utility Category), Approved June 21, 1996 
 
 Engine Lycoming IO-360-L2A, Rated 160 Horsepower 
 
When modified by Cessna Modification Kit MK172-72-01 (See NOTE 4) 
Lycoming IO-360-L2A, Rated 180 Horsepower 
 
 Fuel 100/100LL minimum grade aviation gasoline 
 
 Engine Limits For all operations, 2,400 RPM 
 
When modified by Cessna Modification Kit MK172-72-01 (See NOTE 4) 
For all operations, 2,700 RPM 
 
 Propeller and 1. McCauley Propeller 
 Propeller Limits  Hub   1C235/LFA7570 
Static rpm at full throttle setting: 
  Not over 2,165; not under 2,065. 
  No additional tolerance permitted. 
Diameter: Not over 75 in., not under 74 in. 
Spinner: Dwg. 0550236 
 
When modified by Cessna Modification Kit MK172-72-01 (See NOTE 4) 
2. McCauley Propeller 
Hub   1A170E/JHA7660 
Static rpm at full throttle setting: 
  Not over 2,400; not under 2,300. 
  No additional tolerance permitted. 
Diameter: Not over 76 in., not under 75 in. 
Spinner: Dwg. 0550236 
 
 Airspeed Limits Maneuvering 99 Knots IAS (  97 Knots CAS) 
Max Structural Cruising 129 Knots IAS (126 Knots CAS) 
Never Exceed 163 Knots IAS (160 Knots CAS) 
Flaps Extended 85 Knots IAS (  84 Knots CAS) 
 
When modified by Cessna Modification Kit MK172-72-01 (See NOTE 4) 
Maneuvering 105 Knots IAS (102 Knots CAS) 
Max Structural Cruising 129 Knots IAS (126 Knots CAS) 
Never Exceed 163 Knots IAS (160 Knots CAS) 
Flaps Extended 85 Knots IAS (  84 Knots CAS) 
 
 C.G. Range When using POH/AFM 172RPHUS-00, or later FAA approved revision,  
or POH/AFM 172RPHAUS-00 thru -03, or later FAA approved revision 
Normal Category 
(1) Aft Limits 47.3 inches aft of datum at 2,450 pounds or less. 
 
(2) Forward Limits Linear variation from 40.0 inches aft of datum at 2,450 lb. 
to 35.0 inches aft of datum at 1,950 lb.; 
35.0 inches aft of datum at 1,950 lb. or less. 
 
Utility Category 
(1) Aft Limits 40.5 inches aft of datum at 2,100 lb. or less. 
 
(2) Forward Limits Linear variation from 36.5 inches aft of datum at 2,100 lb. 
to 35.0 inches aft of datum at 1,950 lb.; 
35.0 inches aft of datum at 1,950 lb. or less.

3A12 26 Rev. 89 
XI. Model 172R (cont’d) 
 
 C.G. Range (cont’d) When Using POH/AFM 172RPHAUS-04, or later FAA approved revision,   
  or POH/AFM 172RPHBUS-00, or later FAA approved revision  
Normal Category 
(1) Aft Limits 47.3 inches aft of datum at 2,450 pounds or less. 
(2) Forward Limits Linear variation from 40.0 inches aft of datum at 2,450 lb. 
to 35.0 inches aft of datum at 1,950 lb.;  
35.0 inches aft of datum at 1,950 lb. or less. 
 
Utility Category 
(1) Aft Limits 40.5 inches aft of datum at 2,200 pounds or less. 
(2) Forward Limits Linear variation from 37.5 inches aft of datum at 2,200 lb. 
to 35.0 inches aft of datum at 1,950 lb.; 
35.0 inches aft of datum at 1,950 lb. or less. 
 
When modified by Cessna Modification Kit MK172-72-01 (See NOTE 4) 
Normal Category 
(1) Aft Limits 47.3 inches aft of datum at 2,550 pounds or less. 
 
(2) Forward Limits Linear variation from 41.0 inches aft of datum at 2,550 lb. 
to 35.0 inches aft of datum at 1,950 lb.; 
35.0 inches aft of datum at 1,950 lb. or less. 
 
Utility Category 
(1) Aft Limits 40.5 inches aft of datum at 2,200 pounds or less. 
 
(2) Forward Limits Linear variation from 37.5 inches aft of datum at 2,200 lb. 
to 35.0 inches aft of datum at 1,950 lb.;  
35.0 inches aft of datum at 1,950 lb. or less. 
 
 Empty Wt. C.G. Range None 
 
 Reference Datum Lower portion of front face of firewall 
 
 MAC 58.8 inches; Leading edge of MAC 25.9 inches aft of datum 
 
 Leveling Means Left side of Tailcone at 108.0 inches and 142.0 inches aft of datum  
 
 Maximum Weights When using POH/AFM 172RPHUS-00, or later FAA approved revision,  
or POH/AFM 172RPHAUS-00 thru -03 or later FAA approved revision 
Normal Category 
Maximum Ramp 2,457 lb.  
Maximum Takeoff and Landing 2,450 lb.  
 
Utility Category 
Maximum Ramp   2,107 lb.  
Maximum Takeoff and Landing 2,100 lb.  
 
When using POH/AFM 172RPHAUS-04, or later FAA approved revision,  
or POH/AFM 172RPHBUS-00, or later FAA approved revision  
Normal Category 
Maximum Ramp 2,457 lb.   
Maximum Takeoff and Landing 2,450 lb.  
 
Utility Category 
Maximum Ramp   2,207 lb.  
Maximum Takeoff and Landing 2,200 lb.

Rev. 89 27 3A12 
XI. Model 172R (cont’d) 
 
 Maximum Weights (cont’d) When modified by Cessna Modification Kit MK172-72-01 (See NOTE 4) 
Normal Category  
Maximum Ramp 2,558 lb.  
Maximum Takeoff and Landing 2,550 lb.  
 
Utility Category 
Maximum Ramp   2,208 lb.  
Maximum Takeoff and Landing 2,200 lb.  
 
 No. of Seats 4 (2 at 34.0 to 46.0 inches aft of datum; 2 at 73.0 inches aft of datum) 
 
 Maximum Baggage 120 lb. at 95.0 inches aft of datum 
 
When modified by Cessna Modification Kit MK172-72-01 (See NOTE 4) 
120 lb. at 82.0 to 108.0 inches aft of datum 
50 lb. at 108.0 to 142.0 inches aft of datum 
(Maximum combined weight capacity for baggage areas is 120 lb.)  
 
 Fuel Capacity (Gal.) 56 gallons total; 53 gallons usable 
(Two 28-gallon tanks in wings at 48.0 inches aft of datum) 
(See NOTE 1 for data on unusable fuel) 
 
 Oil Capacity (Gal.) 2.0 gallons at 13.1 inches forward of datum 
3.5 quarts usable 
 
When modified by Cessna Modification Kit MK172-72-01 (See NOTE 4) 
2.0 gallons at 13.1 inches forward of datum 
3.0 quarts usable 
 
 Control Surface Movements Wing Flaps Takeoff 0º - 10º 
  Landing 0º - 30º  + 0°/-2° 
Ailerons Up 20° ± 1° Down 15° ± 1° 
Elevator tab Up 22° + 1°/-0° Down 19° + 1°/-0° 
Elevator Up 28° + 1°/-0° Down 23° + 1°/-0° 
(Neutral position is with bottom of balance area flush with bottom of stabilizer) 
Rudder (Measured parallel to W.L.):  Right 16° 10’± 1°  Left 16° 10’ ± 1° 
Rudder (Measured perpendicular to Hinge):  Right 17° 44’ ± 1° Left 17° 44’ ± 1° 
 
 Serial Numbers Eligible 17280001 and On 
 
Data Pertinent to Model 172R: 
 
Certification Basis: 
FAR Part 23 effective February 1, 1965, as amended by 23-1 through 23-6, except as follows:   
23.423, 23.611, 23.619, 23.623, 23.689, 23.775, 23.871, 23.1323, 23.1563 as amended by Amendment 23-7.  23.807, 23.1524 as 
amended by Amendment 23-10.  23.507, 23.771, 23.853(a)(b)(c), 23.1365 as amended by Amendment 23-14.  23.951 as 
amended by Amendment 23-15.  23.607, 23.675, 23.685, 23.733, 23.787, 23.1309, 23.1322 as amended by Amendment 23-17.  
23.1301 as amended by Amendment 23-20.  23.1353, 23.1559 as amended by Amendment 23-21.  23.603, 23.605, 23.613, 
23.1329, 23.1545 as amended by Amendment 23-23.  23.441, 23.1549 as amended by Amendment 23-28.  23.779, 23.781 as 
amended by Amendment 23-33.  23.1, 23.51, 23.561 as amended by Amendment 23-34.  23.301, 23.331, 23.351, 23.427, 23.677, 
23.701, 23.735, 23.831 as amended by Amendment 23-42.  23.961, 23.1093; 23.1143(g), 23.1147(b), 23.1303, 23.1357, 23.1361, 
23.1385 as amended by Amendment 23-43.  23.562(a), 23.562(b)(2), 23.562(c)(1), 23.562(c)(2), 23.562(c)(3), 23.562(c)(4) as 
amended by Amendment 23-44.  23.33, 23.53, 23.305, 23.321, 23.485, 23.621, 23.655, 23.731 as amended by Amendment  
23-45. 
 
FAR 36 dated December 1, 1969, as amended by Amendments 36-1 through 36-21.

3A12 28 Rev. 89 
Data Pertinent to Model 172R (cont'd) 
 
Certification Basis (cont'd): 
 
Additions for the Garmin G1000 Integrated Cockpit System (ICS) Only: 
14 CFR 23.303, 23.307, 23.601, 23.1163(a), 23.1367, 23.1381 as amended by Amendment 23- N/C.  23.1589 as amended by 
Amendment 23-13.  23.771(a) as amended by Amendment 23-14.  23.607 and (Electrical System) 23.1309(a)(1)(2)(c) as 
amended by Amendment 23-17.  23.1301, 23.1327, 23.1547(e) as amended by Amendment 23-20.  23.1501, 
23.1541(a)(1)(2)(b)(1)(2) as amended by Amendment 23-21.  23.603, 23.605 as amended by Amendment 23-23.  23.1529 as 
amended by Amendment 23-26.  23.561(e), 23.1523, 23.1581(a)(2), 23.1583(a)(c)(d)(f), 23.1585(a)(b)(d) as amended by 
Amendment 23-34.  23.301 as amended by Amendment 23-42.  23.1322, 23.1331, 23.1357(a)(b)(c)(d) as amended by 
Amendment 23-43.  23.305, 23.773(a)(1)(2), 23.1525, 23.1549 as amended by Amendment 23-45.  23.1303(a)(b)(c)(f), 
23.1309(a)(1)(i)(ii)(2)(b)(1)(2)(i)(ii)(3)(4)(i)(ii)(iii)(iv)(c)(1)(2)(iii)(3)(d)(e)(f)(1), 23.1311, 23.1321(a)(c)(d)(e), 
23.1323(a)(b)(1)(2)(c); 23.1329(g)(h), 23.1351(a)(1)(2)(i)(b)(1)(iii)(2)(3)(c)(4)(d)(1), 23.1353(a)(b)(c)(d)(e), 23.1359(c), 
23.1361; 23.1365(a)(b)(d)(e)(f), 23.1431(a)(b)(d)(e) as amended by Amendment 23-49.  23.1325(a)(b)(1)(2)(i)(3)(c)(d)(e), 
23.1543(b)(c), 23.1545(a)(b)(1)(2)(3)(4), 23.1553, 23.1555(a)(b), 23.1563(a), 23.1567(a) as amended by Amendment 23-50.  
23.777(a)(b), 23.955(a)(2), 23.1337(a)(1)(2)(b)(1)(c) as amended by Amendment 23-51.  23.1305(a)(1)(2)(3)(b)(2)(3)(i) 
(4)(i)(5)(6)(i) as amended by Amendment 23-52.  23.901(a)(b) as amended by Amendment 23-53. 
 
Additions for the Garmin GFC-700 Automatic Flight Control System (AFCS) only: 
14 CFR 23.1335 as amended by Amendment 23-20, 23.1329(a)(c)(d)(e)(f) as amended by Amendment 23-49. 
 
Equivalent Safety Items  
1. Induction System Icing Protection  23.1093, refer to FAA letter dated 5/3/1996 
2. Throttle Control  23.1143(g), refer to FAA letter dated 3/22/1996 
3. Mixture Control  23.1147(b), refer to FAA letter dated 3/22/1996 
4. Anti-Collision Light System  23.1401(d), refer to ACE-07-09, FAA letter dated 10/12/2007  
5. Aviation White Color Requirement 23.1397(c), refer to ACE-07-10, FAA letter dated 11/29/2007 
 
Date of Application for Amended Type Certificate was September 25, 1995. 
Type Certificate No. 3A12 was amended June 21, 1996. 
 
Special Conditions as follows: 
No. 23-159-SC, “Cessna Aircraft Company, Cessna Model 172R; Installation of Electronic Flight Instrument System and the 
Protection of the System from High Intensity Radiated Fields (HIRF)”. 
 
Production Basis  
Production Certificate No. PC-4 issued March 28, 1997.  Applies to S/N 17280014, 17280015, 17280017, 17280021 thru 
17280029, 17280031 and On.  Airplane serial numbers not listed were produced under Type Certificate only.  Cessna is 
authorized to issue airworthiness certificates under the delegation provisions of Delegation Option Authorization No. CE-1 in 
accordance with Part 21 of the FAR. 
 
Equipment 
The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed 
in the airplane for certification. 
 
NOTE 1: Weight and Balance:  
 
S/N 17280001 and On  
The certificated empty weight and corresponding center of gravity location must include unusable fuel of  
18 lb. at 46.0 inches aft of datum, and full oil of 15.0 lb. at 13.1 inches forward of datum.

Rev. 89 29 3A12 
Data Pertinent to Model 172R (cont'd) 
 
NOTE 2: The airplane must be operated according to the appropriate Pilot’s Operating Handbook and FAA Approved 
Airplane Flight Manual (POH/AFM).  POH/AFM P/N 172RPHUS00, or later FAA approved revision, is 
applicable to Production Model 172R.  POH/AFM P/N 172R180PH00, or later FAA approved revision, is 
applicable to Production Model 172R airplanes when modified by Cessna Modification Kit MK172-72-01.  
All POH/AFM Supplements approved for P/N number 172RPHUS00, are also applicable to P/N 
172R180PH00, unless specifically noted otherwise in the Supplement.  All FAA required placards are 
included in Section 2 of the applicable POH/AFM, the applicable operating rules, or the certification basis 
must be installed as specified via the parts list for 0500530, Airplane Assembly (useful placarding reference 
is the Textron Aviation Illustrated Parts Catalogue (IPC).  Any discrepancies identified between the IPC and 
an aircraft under inspection need to be reconciled using the previously stated parts list). 
 
FAA Approved AFM:  P/N 172RPHAUS-00, or later FAA approved revision, is applicable to the Model 
172R equipped with Garmin G1000 Integrated Cockpit System.  The airplane must be operated according to 
the appropriate AFM.  Required placards are included in the AFM, the applicable operating rules, or the 
certification basis must be installed as specified via the parts list for 0500530, Airplane Assembly (useful 
placarding reference is the Textron Aviation IPC.  Any discrepancies identified between the IPC and an 
aircraft under inspection need to be reconciled using the previously stated parts list). 
 
FAA Approved AFM: P/N 172RPHBUS-00, or later FAA approved revision, are applicable to the Model 
172R equipped with Garmin G1000 Integrated Cockpit System and Garmin GFC-700 AFCS.  The airplane 
must be operated according to the appropriate AFM.  Required placards are included in the AFM, the 
applicable operating rules, or the certification basis must be installed as specified via the parts list for 
0500530, Airplane Assembly (useful placarding reference is the Textron Aviation IPC.  Any discrepancies 
identified between the IPC and an aircraft under inspection need to be reconciled using the previously stated 
parts list). 
 
NOTE 3: Special Ferry Flight Authorization.  FSDO is authorized to issue special overweight ferry flight 
authorizations.  This airplane is structurally satisfactory for ferry flight if maintained within the following 
limits:   
1. Takeoff weight must not exceed 130% of the maximum weight for Normal Category.  
2. The Never Exceed Airspeed (VNE) and Maximum Structural Cruising Speed (VC) must be reduced  
 by 30%.  
3. Forward and aft center of gravity limits may not be exceeded.  
4. Structural load factors of +2.5 g. to -1.0 g. may not be exceeded.   
Requirements for any additional oil should be established in accordance with AC 23.1011-1.  Increased stall 
speeds and reduced climb performance should be expected for the increased weights.  Flight characteristics 
and performance at the increased weights have not been evaluated.  Flight Permit for operations of 
overweight aircraft may be found in AC 21-4B. 
 
NOTE 4: Only certain Model 172R airplane serial numbers are eligible for modification by Cessna Modification Kit 
MK172-72-01.   Applicable serial numbers are as follows: 
 
17280159 17280242 17280251 17280253 17280257 
17280262 17280281 17280292 17280301 17280305 
17280426 17280488 17280606 17280607 17280608 
17280609 17280610 17280613 17280614 17280616 
17280621 17280622 17280623 17280624 17280631 
17280632 17280633 17280634 17280638 17280639 
17280640 17280646 17280647 17280648 17280652 
17280653 17280659 17280660 17280661 17280662 
17280664 17280667 17280668 17280669 17280670 
17280672 17280673 17280674 17280675 17280701 
17280707     
 
NOTE 5: The following serial numbers are manufactured under the name Cessna Aircraft Company:  
17280001 thru 17281622. 
 
NOTE 6: Company name change effective 7/29/2015. The following serial numbers are manufactured under the name 
Textron Aviation Inc.: 17281623 and On.

3A12 30 Rev. 89 
 
XII. Model 172S, Skyhawk SP, 4 PCLM (Normal Category), 2 PCLM (Utility Category), Approved May 1, 1998 
 
 Engine Lycoming IO-360-L2A, Rated 180 Horsepower 
 
 Fuel 100/100LL minimum grade aviation gasoline 
 
 Engine Limits For all operations, 2,700 RPM 
 
 Propeller and 1. McCauley Propeller 
Propeller Limits  Hub   1A170E/JHA7660 
Static rpm at full throttle setting: 
  Not over 2400; not under 2300. 
  No additional tolerance permitted. 
Diameter: Not over 76 in., not under 75 in. 
Spinner: Dwg. 0550236 
 
 Airspeed Limits Maneuvering 105 Knots IAS (102 Knots CAS) 
Max Structural Cruising 129 Knots IAS (126 Knots CAS) 
Never Exceed 163 Knots IAS (160 Knots CAS) 
Flaps Extended   85 Knots IAS (  85 Knots CAS) 
 
 C.G. Range Normal Category 
(1) Aft Limits 47.3 inches aft of datum at 2,550 pounds or less. 
(2) Forward Limits Linear variation from 41.0 inches aft of datum at 2,550 
pounds to 35.0 inches aft of datum at 1,950 pounds.  35.0 
inches aft of datum at 1,950 pounds or less. 
Utility Category 
(1) Aft Limits 40.5 inches aft of datum at 2,200 pounds or less. 
(2) Forward Limits Linear variation from 37.5 inches aft of datum at 2,200 
pounds to 35.0 inches aft of datum at 1,950 pounds.  35.0 
inches aft of datum at 1,950 pounds or less. 
 
 Empty Wt. C.G. Range None 
 
 Reference Datum Lower portion of front face of firewall  
 
 MAC 58.8 inches; Leading edge of MAC 25.9 inches aft of datum  
 
 Leveling Means Left side of Tailcone at 108.0 inches and 142.0 inches aft of datum  
 
 Maximum Weights Normal Category 
Maximum Ramp 2,558 lb.  
Maximum Takeoff and Landing 2,550 lb.  
 
Utility Category 
Maximum Ramp   2,208 lb.  
Maximum Takeoff and Landing 2,200 lb. 
 
 No. of Seats 4 (2 at 34.0 to 46.0 inches aft of datum; 2 at 73.0 inches aft of datum) 
 
 Maximum Baggage 120 lb. at 82.0 to 108.0 inches aft of datum 
50 lb. at 108.0 to 142.0 inches aft of datum 
(Max. combined weight capacity for baggage areas is 120 pounds) 
 
 Fuel Capacity (Gal.) 56 gallons total; 53 gallons usable  
(two 28-gallon tanks in wings at 48.0 inches aft of datum). 
(See NOTE 1 for data on unusable fuel). 
 
 Oil Capacity (Gal.) 8.0 quarts at 13.1 inches forward of datum 
3.0 quarts usable

Rev. 89 31 3A12 
XII. Model 172S (cont’d) 
 
 Control Surface Movements Wing Flaps Takeoff 0º - 10º 
  Landing 0º - 30º  + 0°/-2° 
Ailerons Up 20° ± 1° Down 15° ± 1° 
Elevator tab Up 22° + 1°/-0° Down 19° + 1°/-0° 
Elevator Up 28° + 1°/-0° Down 23° + 1°/-0° 
(Neutral position is with bottom of balance area flush with bottom of stabilizer) 
Rudder (Measured parallel to W.L.):  Right 16° 10’± 1°   Left 16° 10’ ± 1° 
Rudder (Measured perpendicular to Hinge:  Right 17° 44’ ± 1° Left 17° 44’ ± 1° 
 
 Serial Numbers Eligible 172S8001 and On 
 
Data Pertinent to Model 172S: 
 
Certification Basis:  
FAR Part 23 effective February 1, 1965, as amended by 23-1 through 23-6, except as follows:   
23.423, 23.611, 23.619, 23.623, 23.689, 23.775, 23.871, 23.1323, 23.1563 as amended by Amendment 23-7.  23.807, 23.1524 as 
amended by Amendment 23-10.  23.507, 23.771, 23.853(a)(b)(c), 23.1365 as amended by Amendment 23-14.  23.951 as 
amended by Amendment 23-15.  23.607, 23.675, 23.685, 23.733, 23.787, 23.1309, 23.1322 as amended by Amendment 23-17.  
23.1301 as amended by Amendment 23-20.  23.1353, 23.1559 as amended by Amendment 23-21.  23.603, 23.605, 23.613, 
23.1329, 23.1545 as amended by Amendment 23-23.  23.441, 23.1549 as amended by Amendment 23-28.  23.779, 23.781 as 
amended by Amendment 23-33.  23.1, 23.51, 23.561 as amended by Amendment 23-34.  23.301, 23.331, 23.351, 23.427, 23.677; 
23.701, 23.735, 23.831 as amended by Amendment 23-42.  23.961, 23.1093, 23.1143(g), 23.1147(b), 23.1303, 23.1357; 23.1361, 
23.1385 as amended by Amendment 23-43.  23.562(a), 23.562(b)(2), 23.562(c)(1), 23.562(c)(2), 23.562(c)(3), 23.562(c)(4) as 
amended by Amendment 23-44.  23.33, 23.53, 23.305, 23.321; 23.485, 23.621, 23.655, 23.731 as amended by  
Amendment 23-45. 
 
FAR 36 dated December 1, 1969, as amended by Amendments 36-1 through 36-21. 
 
Additions for the Garmin G1000 Integrated Cockpit System (ICS) Only:  
14 CFR 23.303, 23.307, 23.601, 23.1163(a), 23.1367, 23.1381 as amended by Amendment 23- N/C.  23.1589 as amended by 
Amendment 23-13.  23.771(a) as amended by Amendment 23-14.  23.607 and (Electrical System) 23.1309(a)(1)(2)(c) as 
amended by Amendment 23-17.  23.1301, 23.1327, 23.1547(e) as amended by Amendment 23-20.  23.1501, 
23.1541(a)(1)(2)(b)(1)(2) as amended by Amendment 23-21.  23.603, 23.605 as amended by Amendment 23-23.  23.1529 as 
amended by Amendment 23-26.  23.561(e), 23.1523, 23.1581(a)(2), 23.1583(a)(c)(d)(f) and 23.1585(a)(b)(d) as amended by 
Amendment 23-34.  23.301 as amended by Amendment 23-42.  23.1322, 23.1331, 23.1357(a)(b)(c)(d) as amended by 
Amendment 23-43.  23.305, 23.773(a)(1)(2), 23.1525, 23.1549 as amended by Amendment 23-45.  23.1303(a)(b)(c)(f), 
23.1309(a)(1)(i)(ii)(2)(b)(1)(2)(i)(ii)(3)(4)(i)(ii)(iii)(iv)(c)(1)(2)(iii)(c)(3)(d)(e)(f)(1), 23.1311, 23.1321(a)(c)(d)(e), 23.1323(a) 
(b)(1)(2)(c), 23.1329(g)(h), 23.1351(a)(1)(2)(i)(b)(1)(iii)(2)(3)(c)(4)(d)(1), 23.1353(a)(b)(c)(d)(e), 23.1359(c), 23.1361, 
23.1365(a)(b)(d)(e)(f), 23.1431(a)(b)(d)(e) as amended by Amendment 23-49.  23.1325(a)(b)(1)(2)(i)(3)(c)(d)(e), 23.1543(b)(c), 
23.1545(a)(b)(1)(2)(3)(4), 23.1553, 23.1555(a)(b), 23.1563(a), 23.1567(a) as amended by Amendment 23-50.  23.777(a)(b), 
23.955(a)(2), 23.1337(a)(1)(2)(b)(1)(c) as amended by Amendment 23-51.  23.1305(a)(1)(2)(3)(b)(2)(3)(i)(b)(4)(i)(5)(6)(i) as 
amended by Amendment 23-52.  23.901(a)(b) as amended by Amendment 23-53. 
 
Additions for the Garmin GFC-700 Automatic Flight Control System (AFCS) only: 
14 CFR 23.1335 as amended by Amendment 23-20. 23.1329(a)(c)(d)(e)(f) as amended by Amendment 23-49. 
 
Additions for the Garmin GI 275 Electronic Flight Instrument Only: 
14 CFR 23.1327 as amended by Amendment 23-20. 23.1501 as amended by Amendment 23-21. 23.1529 as amended by 
Amendment 23-26. 23.1523(b), 23.1581(a)(1)(2) as amended by Amendment 23-34. 23.1322, 23.1331 as amended by 
Amendment 23-43. 23.1525 as amended by Amendment 23-45. 23.1303(a)(b)(f), 23.1309(a)(1)(2)(b)(c)(1)(2)(iii)(3)(d)(e)(f), 
23.1311(a)(b), 23.1321(a)(c)(d)(e), 23.1323(a)(c), 23.1351(a)(1)(2)(i), 23.1359(c), 23.1365(a)(d)(e), 23.1431 (a)(b) as amended 
by Amendment 23-49. 23.1325(a)(b)(1)(i)(ii)(iii)(2)(i), 23.1543(b)(c), 23.1545(a)(b)(1)(2)(3)(4), 23.1555(a)(b) as amended by 
Amendment 23-50. 23.777(a)(b) as amended by Amendment 23-51. 23.1308(a)(b)(c) as amended by Amendment 23-57. 
23.1306(a)(b) as amended by Amendment 23-61. 23.2010 and 23.2510 as amended by Amendment 23-64 (see NOTE 6).  
Effective at S/N 172S12701 and On. 
 
Additions for 14 CFR Part 23 Amendment 64: 
14 CFR 23.2000, 23.2005, 23.2010 as amended by Amendment 23-64 (see NOTE 7).  Effective at S/N 172S12701 and On.

3A12 32 Rev. 89 
Data Pertinent to Model 172S: (cont’d) 
 
Certification Basis (cont'd): 
 
Additions for the Garmin G1000 NXi Integrated Cockpit System Only: 
14 CFR 23.683, 23.867 as amended by Amendment 23-7.  23.613(a)(b) as amended by Amendment 23-45.  23.301(a), 23.337, 
23.561(a)(b)(3)(e), 23.607(a)(b), 23.611 as amended by Amendment 23-48.  23.1329(b), 23.1351(g), 23.1353(h), 23.1359(a)(b), 
as amended by Amendment 23-49.  23.143(c), 23.1555(e)(2), 23.1581(a)(b)(1)(3)(c)(d)(f), 23.1583(h)(m), 23.1585(j) as amended 
by Amendment 23-50.  23.1337(b)(c) as amended by Amendment 23-51. 23.2515, 23.2520 as amended by Amendment 23-64 
(see NOTE 8).  Effective at S/N 172S13231 and On. 
 
Additions for the Dual Electronic Ignition System Only: 
14 CFR 23.1309(a)(1)(2), 23.1353(h), 23.1431(b) as amended by Amendment 23-49.  23.1581(a)(2) as amended by Amendment 
23-50.  23.901(a)(1)(2)(b)(1)(2) as amended by Amendment 23-53.  Effective at S/N 172S13375 and On. 
 
Additions for new or changed non-rechargeable lithium battery installations: 
14 CFR Part 23 regulations as amended by Amendment 23-64 (see NOTE 9):  14 CFR 23.2010 and 23.2325(g).  Effective at S/N 
172S13689 and On. 
 
Additions for new or changed installations affecting aeronautical security (cybersecurity): 
14 CFR Part 23 regulations as amended by Amendment 23-64 (see NOTE 10):  14 CFR 23.2010, 23.2500, 23.2505 and 23.2510.  
Effective at S/N 172S13689 and On. 
 
Equivalent Safety Items 
1.  Induction System Icing Protection 23.1093, refer to FAA letter dated 5/1/1998 
2. Throttle Control 23.1143(g), refer to FAA letter dated 5/1/1998 
3. Mixture Control 23.1147(b), refer to FAA letter dated 5/1/1998 
4. Anti-Collision Light System  23.1401(d), refer to ACE-07-09, FAA letter dated 10/12/2007 
5. Aviation White Color Requirement  23.1397(c), refer to ACE-07-10, FAA letter dated 11/29/2007 
 
Date of Application for Amended Type Certificate for Model 172S was November 13, 1997. 
Type Certificate No. 3A12 was amended May 1, 1998, for Model 172S. 
 
Special Conditions as follows: 
No. 23-159-SC, “Cessna Aircraft Company, Cessna Model 172S. Installation of Electronic Flight Instrument System and the 
Protection of the System from High Intensity Radiated Fields (HIRF)." 
 
Production Basis  
Production Certificate No. PC-4 issued August 27, 1998.  Applies to S/N 172S8003 and On.  Airplane serial numbers not listed 
were produced under Type Certificate only.  Cessna is authorized to issue airworthiness certificates under the delegation 
provisions of Delegation Option Authorization No. CE-1 in accordance with Part 21 of the FAR. 
 
Equipment 
The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed 
in the airplane for certification. 
 
NOTE 1. Weight and Balance:  
 S/N 172S8001 and On 
The certificated empty weight and corresponding center of gravity location must include unusable fuel of 18 
pounds at 46.0 inches aft of datum, and full oil of 15.0 pounds at 13.1 inches forward of datum. 
 
NOTE 2. POH/AFM:  P/N 172SPHUS-00 (or later FAA approved revision) is applicable to the Model 172S.  The 
airplane must be operated according to the appropriate POH/AFM.  All FAA required placards are included 
in Section 2 of the POH/AFM, the applicable operating rules, or the certification basis must be installed as 
specified via the parts list for 0500531, Airplane Assembly (useful placarding reference is the Textron 
Aviation IPC.  Any discrepancies identified between the IPC and an aircraft under inspection need to be 
reconciled using the previously stated parts list). 
 
FAA Approved AFM:  P/N 172SPHAUS-00, or later FAA approved revision, is applicable to Model 172S 
equipped with Garmin G1000 Integrated Cockpit System.  The airplane must be operated according to the 
appropriate AFM.  Required placards are included in the AFM, the applicable operating rules, or the 
certification basis must be installed as specified via the parts list for 0500531, Airplane Assembly (A useful 
placarding reference is the Textron Aviation IPC.  Any discrepancies identified between the IPC and an 
aircraft under inspection need to be reconciled using the previously stated parts list).

Rev. 89 33 3A12 
Data Pertinent to Model 172S: (cont’d) 
NOTE 2. (cont’d) 
 
FAA Approved AFM:  P/N 172SPHBUS-00, or later FAA approved revision, are applicable to the Model 
172S equipped with Garmin G1000 Integrated Cockpit System and Garmin GFC-700 AFCS.  The airplane 
must be operated according to the appropriate AFM.  Required placards are included in the AFM, the 
applicable operating rules, or the certification basis must be installed as specified via the parts list for 
0500531, Airplane Assembly (useful placarding reference is the Textron Aviation IPC.  Any discrepancies 
identified between the IPC and an aircraft under inspection need to be reconciled using the previously stated 
parts list). 
 
FAA Approved AFM:  P/N 172SPHCUS-00, or later FAA approved revision, are applicable to the Model 
172S equipped with Garmin G1000 NXi Integrated Cockpit System.  The airplane must be operated 
according to the appropriate AFM.  Required placards are included in the AFM, the applicable operating 
rules, or the certification basis must be installed as specified via the parts list for 0500531, Airplane 
Assembly (useful placarding reference is the Textron Aviation IPC.  Any discrepancies identified between 
the IPC and an aircraft under inspection need to be reconciled using the previously stated parts list). 
 
NOTE 3. Special Ferry Flight Authorization.  FSDO is authorized to issue Special overweight ferry flight 
authorizations.  This airplane is structurally satisfactory for ferry flight if maintained within the following 
limits:   
1. Takeoff weight must not exceed 130% of the maximum weight for Normal Category.  
2. The Never Exceed Airspeed (VNE) and Maximum Structural Cruising Speed (VC) must be reduced  
by 30%.  
3.  Forward and aft center of gravity limits may not be exceeded.  
4.  Structural load factors of +2.5 g. to -1.0 g. may not be exceeded.   
Requirements for any additional oil should be established in accordance with AC 23.1011-1.  Increased stall 
speeds and reduced climb performance should be expected for the increased weights.  Flight characteristics 
and performance at the increased weights have not been evaluated.  Flight Permit for operations of 
overweight aircraft may be found in AC 21-4B.  
 
NOTE 4. The following serials numbers are manufactured under the name Cessna Aircraft Company:  
172S8001 thru 172S11614. 
 
NOTE 5. Company name change effective 7/29/15. The following serials numbers are manufactured under the name 
Textron Aviation: 172S11615 and On. 
 
NOTE 6. Means of Compliance for 23.2510 [23-64] is draft AC 20-184A. 
 
NOTE 7. 14 CFR 23.2005 Certification Level and Performance Level: Level 2, Low Speed. 
 
NOTE 8. Means of Compliance for 23.2515 [23-64] and 23.2520 [23-64] is FAA Policy PS-ACE-23-10. 
 
NOTE 9. Means of Compliance for 23.2010 [23-64] and 23.2325(g) [23-64] is CPP-23.2525-1 (signed 2023.10.19). 
 
NOTE 10. Means of Compliance for 23.2010, 23.2500, 23.2505, and 23.2510 as amended by Amendment 23-64 is 
ASTM F3532-22. 
 
 
 
------- END ------
```

## ADs (85, first 50, in force first)

- [AD 2024-14-03](https://openairdocs.org/ad/2024-14-03): Autopilot System · Garmin GFC 500 Autopilot (STC SA01866WI). Effective Aug 20, 2024
- [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 2020-18-01](https://openairdocs.org/ad/2020-18-01): Fuselage · Textron 172N, 172P, 172Q and 62 more. Effective Nov 12, 2020
- [AD 2018-02-04](https://openairdocs.org/ad/2018-02-04): Exhaust Noise Suppressor · Aerospace Welding Minneapolis A1754001-23, A1754001-25, 172 and 3 more. Effective Feb 21, 2018
- [AD 2013-11-11](https://openairdocs.org/ad/2013-11-11): Engine Oil Pressure · Cessna 172R, 172S, 182S and 4 more. Effective Aug 1, 2013
- [AD 2013-03-15](https://openairdocs.org/ad/2013-03-15): Aircraft Fuel Distribution System · Cessna 172R and 172S. Effective Mar 19, 2013
- [AD 2012-22-01](https://openairdocs.org/ad/2012-22-01): Aircraft Fuel Distribution System · Cessna 172R and 172S. Effective Dec 28, 2012
- [AD 2012-02-02](https://openairdocs.org/ad/2012-02-02): Fuel · Cessna 172R and 172S. Effective Mar 13, 2012
- [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 2011-06-02](https://openairdocs.org/ad/2011-06-02): Engine · TAE 125-01 Engine Installation (Technify Motors STC SA01303WI). Effective May 26, 2011
- [AD 2008-26-10](https://openairdocs.org/ad/2008-26-10): Alternate static air source selector valve · Cessna 172, 172A, 172B and 179 more. Effective Jan 5, 2009
- [AD 2008-10-02](https://openairdocs.org/ad/2008-10-02): Part number identification placard · Cessna 172, 172R, 172RG and 64 more. Effective May 12, 2008
- [AD 2008-05-09](https://openairdocs.org/ad/2008-05-09): Crew seats · Cessna 172R, 172S, 182T and 3 more. Effective Apr 8, 2008
- [AD 2008-02-18](https://openairdocs.org/ad/2008-02-18): Pick-up collar support and nylon screws · BRS-172 parachute recovery system (Ballistic Recovery Systems STC SA01679CH or SA01999CH). Effective Feb 28, 2008
- [AD 2007-08-03](https://openairdocs.org/ad/2007-08-03): Flexible fuel hoses · Cessna 172R, 172S, 182T and 3 more. Effective May 2, 2007
- [AD 2007-05-10](https://openairdocs.org/ad/2007-05-10): Steel lock rod/bar on both crew seat back cylinder lock assemblies · Cessna 172R, 172S, 182S and 4 more. Effective Apr 11, 2007
- [AD 2006-17-04](https://openairdocs.org/ad/2006-17-04): Flexible fuel hoses located in the engine compartment · Cessna 172R, 172S, 182T and 3 more. Effective Sep 1, 2006
- [AD 2006-12-07](https://openairdocs.org/ad/2006-12-07): ECi cylinder assemblies · Aerostar AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 386 more. Effective Jul 11, 2006
- [AD 2006-03-08](https://openairdocs.org/ad/2006-03-08): Vacuum pumps · Aero Advantage 14-19, 14-19-2, 14-19-3 and 299 more. Effective Mar 10, 2006
- [AD 2005-25-08](https://openairdocs.org/ad/2005-25-08): Electronic Flight Information System (EFIS) · B-N Group BN-2A, 172, 180 and 22 more. Effective Jan 23, 2006
- [AD 2005-13-10](https://openairdocs.org/ad/2005-13-10): Main electrical power junction box circuit breakers · Cessna 172R, 172S, 182T and 3 more. Effective Aug 9, 2005
- [AD 2005-05-53 R1](https://openairdocs.org/ad/2005-05-53-R1): Flight control system · Cessna 172R, 172S, 182T and 1 more. Effective Mar 21, 2005
- [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005
- [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 2004-15-18](https://openairdocs.org/ad/2004-15-18): Honeywell KAP 140 Autopilot Computer System · Cessna 172R, 172S, 182S and 4 more. Effective Sep 12, 2004
- [AD 2001-23-17](https://openairdocs.org/ad/2001-23-17): GNS 430 units · Cessna 172, 182, 206 and 209 more. Effective Dec 28, 2001
- [AD 2001-23-03](https://openairdocs.org/ad/2001-23-03): Forward Door Post · Cessna 172N, 172P, 172RG and 5 more. Effective Dec 27, 2001
- [AD 2001-06-17](https://openairdocs.org/ad/2001-06-17): Engine Idle Speed and Fuel Control Mixture Setting · Cessna 172R and 172S. Effective Apr 20, 2001
- [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 98-21-21 R1](https://openairdocs.org/ad/98-21-21-R1): Electric Inflatable Door Seals · Cessna 17-30, 17-30A, 17-31 and 267 more. Effective May 1, 2000
- [AD 99-27-02](https://openairdocs.org/ad/99-27-02): Fuel Selector Valves · Cessna 170B, 172, 172A and 36 more. Effective Jan 21, 2000
- [AD 99-18-14](https://openairdocs.org/ad/99-18-14): Control Yoke Pivot Bolt · Cessna 172R. Effective Sep 27, 1999
- [AD 98-25-02](https://openairdocs.org/ad/98-25-02): Top-mounted Antenna · Bell Helicopter Textron Canada 407, 172, 172A and 243 more. Effective Dec 22, 1998
- [AD 98-25-03](https://openairdocs.org/ad/98-25-03): Aileron Control Cable · Cessna 172R. Effective Dec 18, 1998
- [AD 98-14-03](https://openairdocs.org/ad/98-14-03): Transponders · Cessna 172, 172A, 172B and 230 more. Effective Aug 16, 1998
- [AD 98-14-07](https://openairdocs.org/ad/98-14-07): Lower Forward Doorpost · Cessna 172R. Effective Aug 16, 1998
- [AD 98-13-41](https://openairdocs.org/ad/98-13-41): Aileron Control Cables · Cessna 172R. Effective Jul 20, 1998
- [AD 98-02-05](https://openairdocs.org/ad/98-02-05): Engine Exhaust Muffler · Cessna 172R. Effective Feb 23, 1998
- [AD 98-01-01](https://openairdocs.org/ad/98-01-01): Placard in Cockpit · Cessna 172R and 182S. Effective Feb 2, 1998
- [AD 97-12-06](https://openairdocs.org/ad/97-12-06): Check Clearance Between Cowling and Gascolator and Cowling and Tailpipe · Cessna 172R. Effective Jul 15, 1997
- [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 96-12-22](https://openairdocs.org/ad/96-12-22): Full Flow Engine Oil Adapter · Bellanca CH-300 Pacemaker, 120, 140 and 361 more. Effective Jul 31, 1996
- [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 90-06-03 R1](https://openairdocs.org/ad/90-06-03-R1): Exhaust Heater/Muffler Assembly · Cessna 172, 172A, 172B and 16 more. Effective Mar 27, 1991
- [AD 79-10-14 R1](https://openairdocs.org/ad/79-10-14-R1): Fuel Tank Venting · Cessna 140A, 150, 150A and 172 more. Effective May 30, 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 85-23-07](https://openairdocs.org/ad/85-23-07): Autopilot Systems · Aerostar PA-60-700P (Aerostar 700P), 172L, 172P and 37 more. Effective Jan 27, 1986
- [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

All 85: https://openairdocs.org/tcds/3A12/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Cessna 172M](https://openairdocs.org/model/cessna-172m): 3,573 aircraft (registry code 2072418)
- [Cessna 172N](https://openairdocs.org/model/cessna-172n): 3,138 aircraft (registry code 2072434)
- [Cessna 172S](https://openairdocs.org/model/cessna-172s): 1,915 aircraft (registry codes 2072439, 2072442)
- [Cessna 172](https://openairdocs.org/model/cessna-172): 1,805 aircraft (registry code 2072402)
- [Textron 172S](https://openairdocs.org/model/textron-172s): 1,239 aircraft (registry code 2072449)
- [Cessna 172P](https://openairdocs.org/model/cessna-172p): 1,111 aircraft (registry code 2072436)
- [Cessna 172K](https://openairdocs.org/model/cessna-172k): 1,026 aircraft (registry code 2072430)
- [Cessna 172L](https://openairdocs.org/model/cessna-172l): 857 aircraft (registry code 2072432)
- [Cessna 172H](https://openairdocs.org/model/cessna-172h): 780 aircraft (registry code 2072424)
- [Cessna 172G](https://openairdocs.org/model/cessna-172g): 722 aircraft (registry code 2072420)
- [Cessna 172F](https://openairdocs.org/model/cessna-172f): 717 aircraft (registry code 2072414)
- [Cessna 172R](https://openairdocs.org/model/cessna-172r): 683 aircraft (registry code 2072401)
- [Cessna 172E](https://openairdocs.org/model/cessna-172e): 617 aircraft (registry code 2072412)
- [Cessna 172D](https://openairdocs.org/model/cessna-172d): 471 aircraft (registry code 2072410)
- [Cessna 172A](https://openairdocs.org/model/cessna-172a): 435 aircraft (registry code 2072404)
- [Cessna 172B](https://openairdocs.org/model/cessna-172b): 413 aircraft (registry code 2072406)
- [Cessna 172C](https://openairdocs.org/model/cessna-172c): 362 aircraft (registry code 2072408)
- [Cessna 172I](https://openairdocs.org/model/cessna-172i): 353 aircraft (registry code 2072426)
- [Cessna 172Q](https://openairdocs.org/model/cessna-172q): 13 aircraft (registry code 2072437)
- [Cessna/Walker 172F](https://openairdocs.org/model/cessna-walker-172f): 0 aircraft (registry code 2072415)

## STCs approved under this data sheet (821, 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 SA02539AK](https://openairdocs.org/stc/SA02539AK): Installation of a Continental Aerospace Technologies IO-370CLC1U8 and Hartzell Model HC-C2YR-1N/NG8301,-3, -7 Propeller. David A. Stoots
- [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 SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies
- [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 SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International 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 SA03932NY](https://openairdocs.org/stc/SA03932NY): Installation and maintenance of XCAM Pod on port or starboard wing strut. J&C Engineering Services LTD
- [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 SA2714CE](https://openairdocs.org/stc/SA2714CE): Installation of Lycoming O-320-D2G or -D2J engine and McCauley1C160/DTM or Sensenich 74 DMS14-0 propeller.. Air Plains Services Corporation
- [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 SA01866WI](https://openairdocs.org/stc/SA01866WI): Installation of Garmin GFC 500 Autopilot with Electronic Stability and Protection. Garmin International Inc.
- [STC SA12276IB](https://openairdocs.org/stc/SA12276IB): Payload System Installation. Icarus Aero Inc.
- [STC SA04075CH](https://openairdocs.org/stc/SA04075CH): Installation of Dynon EFIS-D10A EAA sales kit part number 102778-000. Dynon Avionics Inc.
- [STC SA02595AK](https://openairdocs.org/stc/SA02595AK): Fabrication and installation of Airglas Inc. cargo pod kit model LC172. Airglas 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 SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC
- [STC SA01801AT](https://openairdocs.org/stc/SA01801AT): For the Cessna 172 airplane models incorporating Lycoming O-320 engines: Modification of the standard exhaust system as documented in Laminar Flow Systems Installation Instructions Document, "Laminar Flow System Extractor Exhaust System" Revision A, dated, November 20, 1998 and Technical Drawing List, Book No. PFS-B-800, dated, November 16, 1998 or per Power Flow Systems, Inc. Installation Instructions Document PFS-0058-00, Rev. A, dated October 5, 2001 and Master Drawing List, Report No. PFS-0032-00, Rev. IR, dated August 10, 2000, or later FAA approved revisions.
For the Cessna 172 airplane models incorporating Lycoming O-320 ,O-360 0r IO-360 engines:
Modify the standard exhaust system as document in Power Flow Systems, Inc. Installation Instructions Document PFS-13250-00, Rev B, dated, December 9, 2002 and Master Drawing list PFS-13240-00, Rev, IR, dated October 3, 2002.. Power Flow Systems Inc
- [STC SA02228AT](https://openairdocs.org/stc/SA02228AT): For model 172 airplanes with Lycoming O-360 engines per STC SA332GL or STC SA4428SW, modification of standard exhaust system. For model 172 with Lycoming O-360 engines per STC SA647CE or STC SA1324CE, modification of standard exhaust system.. Power Flow Systems Inc
- [STC SA1945CE](https://openairdocs.org/stc/SA1945CE): Increase normal category maximum gross weight from 2300 to 2400 lbs. and increase utility category maximum grow weight from 2000 to 2100 lbs. per Installation Instructions, STC SA1945CE, Gross Weight Increase for the C172N with an FAA approval date of January 3, 1989, or later.. Power Flow Systems Inc.
- [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 SA02588AK](https://openairdocs.org/stc/SA02588AK): Installation of Ground Adjustable Sensenich Composite 2G0M8S14/C76PGF Propeller. Sensenich Propeller Company
- [STC SA553GL](https://openairdocs.org/stc/SA553GL): Remove tricycle landing gear and install conventional landing gear. (172C S/N 28000 THRU17249544 FOR ALL MODELS). Jorden Alexander Grieff
- [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 SA01120SE](https://openairdocs.org/stc/SA01120SE): Installation of Door Steward.. Mountain View Aviation LLC
- [STC SA860SO](https://openairdocs.org/stc/SA860SO): Installation of portable hand control. Union Aviation LLC
- [STC SA39CH](https://openairdocs.org/stc/SA39CH): Installation of an Amphibian Landing Gear Position Advisory System/Laser Gear Advisory System. Wipaire Inc.
- [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 SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC
- [STC SA00622DE](https://openairdocs.org/stc/SA00622DE): Installation of John Deere AGRI Services, Inc. JD3 Aerial Imaging System,. Aeroptic LLC
- [STC SA02751SE](https://openairdocs.org/stc/SA02751SE): Replacement instrument panel as structural provisions. Jansma Design, 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 SA02006CH](https://openairdocs.org/stc/SA02006CH): Installation of air conditioning system.. Kelly Aerospace Thermal Systems LLC
- [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.

All 821: https://openairdocs.org/tcds/3A12/stcs.md

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