# TCDS 3A17: Textron Aviation Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Textron Aviation Inc.
- Revision: 47
- Revised: July 29, 2015
- Product: Aircraft, Small Airplane
- Certification basis: Part 23, CAR 3
- Registered aircraft: 2,151, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/6f/96/6f96ad72c39d8aa1ff1130191f4a999f015ab8d4bad96b49c7005b1f8c558128
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/CB2BFE3BB96650FF86257ED2006AA7B5.0001
- Page: https://openairdocs.org/tcds/3A17

## Models (12)

As the data sheet lists them.

- R172H ((USAF T-41D))
- R172G ((USAF T-41C or D))
- R172K
- R172F ((USAF T-41D))
- 172RG
- R172J
- 175
- 175B
- P172D
- R172E ((USAF T-41B, 
USAF T-41C and D))
- 175C
- 175A

## 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. 47 44 39 44 44 44 39 39 43 43 43 42 41 41 41 38 38 41 42 45 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
3A17 
Revision 47 
Textron Aviation Inc. 
 175 175A 
 175B 175C 
 P172D 
 R172E (USAF T-41B) 
  (USAF T-41C or D) 
 R172F (USAF T-41D) 
 R172G (USAF T-41C or D) 
 R172H (USAF T-41D) 
 R172J R172K 
 172RG 
July 29, 2015 
 
TYPE CERTIFICATE DATA SHEET NO. 3A17 
 
This data sheet which is part of Type Certificate No. 3A17 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 Avaiation Inc. on July 29, 2015 
 
I. Model 175, Skylark, 4 PCL-SM (Normal Category), approved January 14, 1958 
 
 Engine Continental GO-300A or GO-300C 
 
 *Fuel 80/87 minimum grade aviation gaosline 
 
 *Engine limits For all operations,  GO-300A, 3200 rpm (175 hp) 
     GO-300C, 3200 rpm (175 hp) 
 
 Propeller and  1. McCauley 1A175/FC 8455 or 8467 
   propeller limits  (a) Diameter:  not over 84 in., not under 82.5 in. 
    Static rpm at maximum permissible throttle setting: 
     Landplane: not over 2740, not under 2640 
     Seaplane: not over 3000, not under 2900 
    No additional tolerance permitted 
   (b) Spinner, Cessna Dwg. 0552004 
  2. McCauley 1B175/MFC 8455 or 8467 
   (a) Diameter:  not over 84 in., not under 82.5 in. 
    Static rpm at maximum permissible throttle setting: 
     Landplane: not over 2645, not under 2545 
     Seaplane: not over 2970, not under 2870 
    No additional tolerance permitted 
   (b) Spinner, Cessna Dwg. 0550212 or 0550221 
 
 *Airspeed limits Maneuering   123 mph (107 knots) 
    (TIAS) Maximum structural cruising 140 mph (122 knots) 
  Never exceed   176 mph (153 knots) 
  Flaps extended  100 mph (  87 knots)

3A17 2 Rev. 47 
 
I. Model 175  (cont'd) 
 
 C.G. range Landplane: 
  (+41.5) to (+46.4) at 2350 lbs. 
  (+36.5) to (+46.4) at 1850 lbs. or les 
 
  Seaplane: 
  (+39.5) to (+45.5) at 2350 lbs. 
  (+36.5) to (+45.5) at 2020 lbs. or less 
  Straight line variation between points given. 
 
 Empty weight C.G. range None 
 
 *Maximum weight 2350 lbs. (landplane) 
  2350 lbs. (seaplane) 
 
 Number of seats 4  (2 at +36, 2 at +70) 
 Maximum baggage 120 lbs. (+95) 
 
 Fuel capacity 52 gal. (two 26 gal. tanks in wing (+48); 43 gal. usable). 
  See NOTE 1 for weight of unusable fuel. 
 
 Oil capacity 10 qt. (-18.5) (3 qt. unusable) 
 
 Control surface movements Wing flaps   Retracted   0° 
     1st notch 10° 
     2nd notch 20° 
     3rd notch 30° 
     4th notch 40° 
  Ailerons Up 20° Down 15° 
  Elevator tab Up 28° Down 12° 
  Elevator Up 27.5° Down 26° 
  Rudder Landplane:  Right 16° Left 16° 
   Seaplane:  Right 12° Left 12° 
 
 Serial numbers eligible 28700A, 55001 through 56238 
 
 
II. Model 175A, Skylark, 4 PCL-SM (Normal Category), approved August 28, 1959 
 Model 175B, Skylark, 4 PCL-SM (Normal Category), approved June 14, 1960 
 
 Engine Continental GO-300C or GO-300D 
 
 *Fuel 80/87 minimum grade aviation gasoline 
 
 *Engine limits For all operations, 3200 rpm  (175 hp) 
  See NOTE 4. 
 
 Propeller and 1. McCauley 1B175/ MFC 8467 
   propeller limits  (a) Diameter:  not over 84 in., not under 82.5 in. 
    Static rpm at maximum permissible throttle setting: 
    Landplane:  not over 2645, not under 2545 
    See NOTE 4. 
    No additional tolerance permitted 
   (b) Spinner, Cessna Dwg. 0550221 
  2. McCauley 1D200/OM  9044 (seaplane only) 
   (a) Diameter:  not over 90 in., not under 88 in. 
    Static rpm at maximum permissible throttle setting: 
     not over 2810, not under 2710 
     No additional tolerance permitted 
   (b) Spinner, Cessna Dwg. 0552004

Rev. 46 3 3A17 
 
II. Models 175A, 175B   (cont'd) 
  
 *Airspeed Limits Landplane and Seaplane 
   (TIAS) Maneuvering   123 mph  (107 knots) 
  Maximum structural cruising 140 mph  (122 knots) 
  Never exceed   176 mph  (153 knots) 
  Flaps extended  100 mph  (  87 knots) 
 
 C.G. Range Landplane 
  (+41.5) to (+46.4) at 2350 lbs. 
  (+36.0) to (+46.4) at 1850 lbs. or less 
  Seaplane 
  (+39.5) to (+45.5) at 2450 lbs. 
  (+36.5) to (+45.5) at 2020 lbs. or less 
  Straight line variation between points given. 
 
 Empty weight C.G. range None 
 
 *Maximum weight 2350 lbs.  (landplane) 
  2450 lbs.  (seaplane) 
 
 Number of seats 4  (2 at +36, 2 at +70) 
 
 Maximum baggage 120 lbs.  (+95) 
 
 Fuel capacity 52 gal. (two 26 gal. tanks in wings at +48; 42 gal. usable) 
  See NOTE 1 for weight of unusable fuel. 
 
 Oil capacity 10 qt. at -18.5  (3 qt. 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 19° 
 
 Serial numbers eligible Model 175A:  619, 56239 through 56777 
  Model 175B:  17556778 through 17557002 
 
 
III. Model 175C, Skyhawk, 4 PCLM (Normal Category), approved September 18, 1961 
 Model P172D, Skyhawk Powermatic, 4 PCLM (Normal Category), approved June 25, 1962 
 
 Engine Continental GO-300E 
 
 *Fuel 80/87 minimum grade aviation gasoline 
 *Engine limits For all operations, 3200 rpm (175 hp) 
 
 Propeller and 1. McCauley constant speed propeller 
   propeller limits  (a) McCauley, 2A31C21 hub with 84S blades 
    Diameter:  not over 84 in., not under 82 in. 
    Pitch settings at 30 in. sta.: 
     Low 13°, high 26.5° 
   (b) Garwin hydraulic governor, 34-827 
    Cessna spinner, 0552016

3A17 4 Rev. 47 
 
III. Models 175C, P172D (cont'd) 
  
 *Airspeed limits Model 175C: 
    (TIAS) Maneuvering   125 mph  (109 knots) 
  Maximum structural cruising 140 mph  (122 knots) 
  Never exceed   176 mph  (153 knots) 
  Flaps extended  100 mph  (  87 knots) 
 
  Model P172D: 
  Maneuvering   127 mph  (110 knots) 
  Maximum structural cruising 145 mph  (126 knots) 
  Never exceed   182 mph  (158 knots) 
  Flaps extended  100 mph  (  87 knots) 
 
 C.G. range Model 175C: 
  (+39.5)  to  +46.4)  at  2450 lbs. 
  (+36.0)  to  (+46.4)  at  2050 lbs. or less 
 
  Model P172D: 
  (+40.5) to (+47.3) at 2500 lbs. 
  (+35.0) to (+47.3) at 1950 lbs. or less 
  Straight line variation between points given. 
 
 Empty weight C.G. range None 
 
 *Maximum weight Model 175C:  2450 lbs. 
  Model P172D:  2500 lbs. 
 
 Number of seats 4  (2 at +36, 2 at +70) 
 
 Maximum baggage 120 lbs.  (+95) 
 
 Fuel capacity 52 gal. (two 26 gal. tanks in wings at +48; 41.5 gal. usable) 
  See Note 1 for weight of unusable fuel. 
 
 Oil capacity 10 qt. at -18.5 (3 qt. unusable). 
 
 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 
    (Model 175C) Up 28° Down 26° 
    (Model P172D) Up  28° Down 23° 
    Neutral position measured 
    with the bottom of the balance 
    area flush with the bottom of 
    the stabilizer) 
  Rudder  (measured Right 16° Left 16° 
    parallel to O.O.W.L.) 
 
 Serial numbers eligible Model 175C:  17557003 through 17557119 
  Model P172D:  P17257120 through P17257188

Rev. 46 5 3A17 
 
IV. Model R172E (USAF T-41B), (USAF T-41C or D), 4 PCLM (Normal Category), 2 PCLM (Utility Category),  
 approved April 21, 1964 
 Model R172F (USAF T-41D), 4 PCLM (Normal Category), 2 PCLM (Utility Category), approved May 14, 1968 
 
 Engine Continental IO-360-D or IO-360-DB 
 
 *Fuel 100/130 minimum grade aviation gasoline 
 
 *Engine limits For all operations, 2800 rpm (210 hp) 
 
 Propeller and 1. McCauley constant speed propeller 
   propeller limits  (a) D2A34C67 hub with 76C blades 
    Diameter:  not over 76 in., not under 74.5 in. 
    Pitch settings at 30 in. sta.: 
     Low 11.7°, high 22.5° 
   (b) Governor 
    (1) Woodward F210452 or 
    (2) McCauley C290-D2/T6 or 
    (3) McCauley C290-D3/T6 
   (c) 2A34C209 hub with 78CCA-2 blades (T-41B) 
    Diameter: not over 76 in., not under 74.5 in. 
    Pitch settings at 30 in. sta.: 
     Low 11.3°, high 22.0° 
  2. McCauley fixed pitch, 1B235/DFC 7850 (T-41C) 
   (a) Diameter: not over 78 in., not under 76.5 in. 
    Static rpm at max. permissible throttle setting 
     not over 2370, not under 2270 
    No additional tolerance permitted. 
 
 *Airspeed limits Maneuvering   127 mph  (110 knots) 
   (TIAS) Maximum structural cruising 145 mph  (126 knots) 
  Never exceed   182 mph  (158 knots) 
  Flaps extended  100 mph  (  87 knots) 
 
 C.G. range Normal category 
  (+40.5)  to  (+47.3) at 2500 lbs. 
  (+35.0)  to  (+47.3) at 1950 lbs. 
 
  Utility category 
  (+37.5) to (+40.5) at 2200 lbs. 
  (+35.0) to (+40.5) at 1950 lbs. 
 
 Empty weight C.G. range None 
 
 *Maximum weight 2500 lbs.  (normal category) 
  2200 lbs.  (utility category) 
 
 Number of seats 4  (2 at +36, 2 at +70) 
 
 Maximum baggage 200 lbs.  (+95) 
 
 Fuel capacity 52 gal. (two 26 gal. tanks in wings at +48; 46 gal. usable) 
  See Note 1 for weight of unusable fuel. 
 
 Oil capacity 10 qt.  - 21.5  (7 qt. usable) 
  See Note 5 for optional oil capacity. 
  See Note 1 for weight of undrainable oil.

3A17 6 Rev. 47 
 
IV. Models R172E, R172F  (cont’d) 
  
 Control surface movements Wing flaps Takeoff  0°  - 10° 
   Landing  0°  - 40° 
  Ailerons Up 20° Down 15° 
  Elevator tab Up 28° Down 13° 
  Elevator Up 28° Down 23° 
    (Neutral position measured 
    with the bottom of the balance 
    area flush with the bottom of 
    the stabilizer) 
  Rudder Right 16° Left 16° 
 
 Serial numbers eligible Model R172E:  R172-0001 through R172-0335 
  Model R172F:  R172-0336 through R172-0409 
 
 
V. Model R172G (USAF T-41C or T-41D), 4 PCLM (Normal Category), 2 PCLM (Utility Category), 
 approved July 18, 1969 
 
 Engine Continental IO-360-D, IO-360-C, IO-360DB or IO-360-CB 
 
 *Fuel 100/130 minimum grade aviation gasoline 
 
 *Engine limits For all operations, 2800 rpm  (210 hp) 
 
 Propeller and 1. McCauley constant speed propeller 
   propeller limits  (a) D2A34C67 hub with 76C blades 
    Diameter: not over 76 in., not under 74.5 in. 
    Pitch settings at 30 in. sta.: 
     Low 11.7°, high 22.5° 
   (b) Governor 
    (1) Woodward F210452 or 
    (2) McCauley C290-D2/T6 or 
    (3) McCauley C290-D3/T6 
  2. McCauley fixed pitch propeller, 1B235/DFC 7850 (T-41C) 
   (a) Diameter:  not over 78 in., not under 76.5 in. 
    Static rpm at maximum permissible throttle setting 
    not over 2370, not under 2270 
    No additional tolerance permitted. 
 
 *Airspeed Limits Maneuvering   125 mph  (109 knots) 
   (TIAS) Maximum structural cruising 146 mph  (126 knots) 
  Never exceed   185 mph  (160 knots) 
  Flaps extended  100 mph  (  87 knots) 
 
 C.G. range Normal Category 
  (+41.0) to (+47.3) at 2550 lbs. 
  (+35.0) to (+47.3) at 1950 lbs. 
 
  Utility Category 
  (+37.5) to (+40.5) at 2200 lbs. 
  (+35.0) to (+40.5) at 1950 lbs. 
 
 Empty weight C.G. range None 
 
 *Maximum weight 2550 lbs.  (normal category) 
  2200 lbs.  (utility category) 
 
 Number of seats 4  (2 at +36, 2 at +70)

Rev. 46 7 3A17 
 
V. Model R172G  (cont'd) 
 
 Maximum baggage 200 lb.  (+95) 
 
 Fuel capacity 52 gal. (two 26 gal. tanks in wings at +48; 46 gal. usable) 
  See Note 1 for weight of unusable fuel. 
 
 Oil capacity 10 qt.  - 21.5  (7 qt. usable) 
  See Note 1 for weight of undrainable oil. 
  See Note 5 for optional oil capacity. 
 
 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 measured with  
    the bottom of the balance area flush  
    with the bottom of the stabilizer) 
  Rudder Right 16° ± 1° Left 16° ± 1° 
    (Measured parallel to W.L.) 
 
 Serial numbers eligible Model R172G: R1720410 through R1720444 
 
 
VI. Model R172H (USAF T-41D), 4 PCLM (Normal Category), 2 PCLM (Utility Category), approved July 2, 1970 
 
 Engine Continental IO-360-D, IO-360-C,  IO-360-H, IO-360-DB, IO-360-CB or IO-360-HB 
 
 *Fuel 100/130 minimum grade aviation gasoline 
 
 *Engine limits For all operations, 2800 rpm (210 hp) 
 
 Propeller and propeller 1. McCauley constant speed propeller 
   limits  (a) D2A34C67 hub with 76C blades 
    Diameter:  not over 76 in., not under 74.5 in. 
    Pitch settings at 30 in. sta.: 
     Low 11.7°, high 22.5° 
   (b) Governor 
    (1) Woodward F210452 or 
    (2) McCauley C290-D2/T6 
   (c) 2A34C209 hub with 78CCA blades 
    Diameter:  not over 78 in., not under 76.5 in. 
    Pitch settings at 30 in. sta.: 
     Low 10.6°, high 22.0° 
   (d) Governor 
    (1) Woodward F210452 or 
    (2) McCauley C290-D2/T6 
   (e) 2A34C209 hub with 78CCA-2 blades 
    Diameter:  not over 76 in., not under 74.5 in. 
    Pitch settings at 30 in. sta.: 
     Low 11.3°, high 22.0° 
   (f) Governor 
    (1) Woodward F210452 or 
    (2) McCauley C290-D2/T6 or 
    (3) McCauley C290-D3/T6 
  2. McCauley fixed pitch propeller, 1B235/DFC 7850 
   (a) Diameter:  not over 78 in., not under 76.5 in. 
    Static rpm at max. permissible throttle setting, 
      not over 2370, not under 2270 
    No additional tolerance permitted.

3A17 8 Rev. 47 
 
VI. Model R172H  (cont'd) 
 
 *Airspeed Limits Maneuvering   125 mph  (109 knots) 
   (TIAS) Max. structural cruising 146 mph  (126 knots) 
  Never exceed   185 mph  (160 knots) 
  Flaps extended  100 mph  (  87 knots) 
 
 C.G. range Normal Category 
  (+41.0) to (+47.3) at 2550 lbs. 
  (+35.0) to (+47.3) at 1950 lbs. 
 
  Utility Category 
  (+37.5) to (+40.5) at 2200 lbs. 
  (+35.0) to (+40.5) at 1950 lbs. 
 
 Empty weight C.G. range None 
 
 *Maximum weight 2550 lbs.  (normal category) 
  2200 lbs.  (utility category) 
 
 Number of seats 4  (2 at +36, 2 at +70) 
 
 Maximum baggage 200 lbs.  (+95) 
 
 Fuel capacity 52 gal. (two 26 gal. tanks in wings at +48)  (46 gal. usable) 
  See NOTE 1 for weight of unusable fuel. 
 
 Oil capacity 10 qt. -21.5  (7 qt. usable) 
  See Note 1 for weight of undrainable oil. 
  See Note 5 for optional oil capacity. 
 
 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 measured 
    with the bottom of the balance 
    area flush with the bottom of 
    the stabilizer) 
  Rudder Right 16° ± 1° Left 16° ± 1° 
    (Measured parallel to W.L.) 
 
 Serial numbers eligible Model R172H: R1720445 through R1720494  (1971 year model) 
      R1720495 through R1720546  (1972 year model) 
      R1720547 through R1720620  (1973 through 1976) 
 
 
VII. Model R172J, 4 PCLM (Normal Category), 2PCLM (Utility Category), approved September 19, 1972 
 
 Engine Continental IO-360-H or IO-360-HB 
 
 *Fuel 100/130 minimum grade aviation gasoline 
 
 *Engine limits For all operations, 2800 rpm  (210 hp)

Rev. 46 9 3A17 
 
VII. Model R172J    (cont'd) 
 
 Propeller and propeller 1. McCauley constant speed propeller 
   limits  (a) D2A34C209 hub with 78CCA blades 
    Diameter:  not over 78 in., not under 76.5 in. 
    Pitch settings at 30 in. sta.: 
     Low 10.6°, high 22.0° 
   (b) 2A34C209 hub with 78CCA-2 blades 
    Diameter:  not over 76 in., not under 74.5 in. 
    Pitch settings at 30 in. sta.: 
     Low 11.3°, high 22.0° 
   (c) Governor 
    (1) Woodward F210452 or 
    (2) McCauley C290-D2/T6 or  
    (3) McCauley C290-D3/T6 
   (d) Spinner, Cessna Dwg. 0550328 
 
 *Airspeed limits Maneuvering   118 mph  (104 knots) 
     (TIAS) Maximum structural cruising 146 mph  (126 knots) 
  Never exceed   185 mph  (160 knots) 
  Flaps extended  100 mph  (  87 knots) 
 
 C.G. range Normal Category 
  (+41.0)  to (+47.3)  at  2550 lbs. 
  (+35.0)  to (+47.3)  at  1950 lbs. 
 
  Utility Category 
  (+37.5)  to  (+40.5)  at  2200 lbs. 
  (+35.0)  to  (+40.5)  at  1950 lbs. 
 
 Empty weight C.G. range None 
 
 *Maximum weight 2550 lbs.  (normal category) 
  2200 lbs.  (utility category) 
 
 Number of seats 4  (2 at +36, 2 at +70) 
 
 Maximu baggage 200 lbs.  (+95) 
 
 Fuel capacity 52 gal. (two 26 gal. tanks in wings at +48)  (46 gal. usable) 
  See Note 1 for weight of unusable fuel. 
 
 Oil capacity 10 qt.  -21.5  (7 qt. usable) 
  See Note 1 for weight of undrainable oil. 
  See Note 5 for optional oil capacity. 
 
 Control surface movements Wing flaps Takeoff  0°  - 10° 
   Landing  0°  - 40° ± 0° -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 measured 
    with the bottom of the balance 
    area flush with the bottom of 
    the stabilizer) 
  Rudder Right 16° ± 1° Left 16° ± 1° 
    (Measured parallel to W.L.) 
 
 Serial numbers eligible Model R172J:  P17257189  (1974 model)

3A17 10 Rev. 47 
 
VIII.  Model R172K, Hawk XP, 4 PCL-SM (Normal Category), 2 PCLM (Utility Category), approved 
    May 28, 1976 
 
 Engine Continental IO-360-K or IO-360-KB (S/N R1722000 through R1722929) 
     IO-360-KB (S/N 680, R1722930 and on) 
 
 *Fuel 100/130 minimum grade aviation gasoline 
  (S/N R1722000 through R1722724) 
 
  100LL/100 minimum grade aviation gasoline 
  (S/N R1722725 and on) 
 
 *Engine limits For all operations, 2600 rpm (195 hp) 
 
 Propeller and propeller Landplane 
   limits 1. McCauley constant speed propeller 
   (a) 2A34C203 hub with 90DCA- 14 blades 
    Diameter:  not over 76 in., not under 74.5 in. 
    Pitch settings at 30 in. sta.: 
     Low 12.0°, high 25.1° 
   (b) Governor 
    (1) McCauley C290D3/T15 
   (c) Spinner, Cessna Dwg. 0550328 
 
  Floatplane 
  1. McCauley constant speed propeller 
   (a) 2A34C203 hub with 90DCA- 10 blades 
    Diameter:  not over 80 in., not under 78.5 in. 
    Pitch settings at 30 in. sta.: 
     Low 11.3°, high 24.8° 
   (b) Governor 
    (1) McCauley C290D3/T15 
   (c) Spinner, Cessna Dwg. 0550328 
 
 *Airspeed Limits S/N 680, R1722000 through R1723199 
     (IAS) Maneuvering   105 knots 
    (See Note 7 on Use of IAS) Maximum structural cruising 129 knots 
  Never exceed   163 knots 
  Flaps extended    85 knots 
 
  S/N R1723200 and on 
  Maneuvering   104 knots 
  Maximum structural cruising 129 knots 
  Never exceed   163 knots 
  Flaps extended    85 knots 
 
 C.G. range Landplane 
  Normal Category 
  (+41.0) to (+47.3) at 2550 lbs. 
  (+35.0) to (+47.3) at 1950 lbs. 
 
  Utility Category 
  (+37.5) to (+40.5) at 2200 lbs. 
  (+35.0) to (+40.5) at 1950 lbs. 
  Straight line variation between points given. 
 
 
  Floatplane:  (Edo 248B-2440) 
  Normal Category 
  (+39.5) to (+45.5) at 2550 lbs. 
  (+37.0) to (+45.5) at 2100 lbs.

Rev. 46 11 3A17 
 
VIII.  Model R172K  (cont'd) 
 
 Empty weight C.G. range None 
 
 *Maximum weight 2550 lbs  (Normal Category) Landplane and Floatplane 
  2200 lbs. (Utility Category) Landplane 
  2558 lbs. Ramp weight (S/N R1722930 and on) 
 
 Number of seats 4  (2 at +36, 2 at +70) 
 
 Maximum baggage 200 lb.  (+95) 
 
 Fuel capacity 52 gal. (two 26 gal. tanks in wings at +48)  (49 gal. usable) 
  See Note 1 for weight of unusable fuel. 
 
 Oil capacity 8 qt. -21.5 (5 qt. usable) 
 
 Control surface movements Wing flaps Takeoff  0°  - 10° (landplane) 
     0°  - 20° (floatplane) 
   Landing  0°  - 40° +0° -2° 
     (R1722000 through 
     R1723399, and 680) 
     0°  - 30° +0° -2° 
     (R1723400 and on) 
  Ailerons Up 20° ± 1° Down 15° ± 1° 
  Elevator tab Up 28° + 1° -0° Down 13° + 1° -0° 
     (R1722000 through 
     R1723399, and 680) 
     (All R172K floatplanes) 
   Up 22° +1° -0° Down 19° +1° -0° 
     (R1723400 and on) 
  Elevator Up 28° + 1° -0° Down 23° + 1° -0° 
    (Neutral position measured 
    with the bottom of the balance 
    area flush with the bottom of 
    the stabilizer) 
  Rudder Right 16° ± 1° Left 16° ± 1° 
    (Measured parallel to W.L.) 
 
 Serial numbers eligible Model R172K: R1722000 through R1722724 (1977 model) 
      R1722725 through R1722929 (1978 model) 
      680, R1722930 through R1723199 (1979 model) 
      R1723200 through R1723399 (1980 model) 
      R1723400 through R1723454 (1981 model) 
 
 
IX. Model 172RG, Skyhawk RG, 4 PCLM (Normal Category), approved June 1, 1979 
 
 Engine Lycoming O-360-F1A6 
 
 *Fuel 100LL/100 minimum grade aviation gasoline 
 
 *Engine limits For all operations, 2700 rpm  (180 hp) 
 
 Propeller and propeller 1. McCauley constant speed propeller 
   limits  (a) B2D34C220 hub with 80VHA - 3.5 blades 
    Diameter:  not over 76.5 in., not under 75.5 in. 
    Pitch settings at 30 in. sta.: 
     Low 12.0°, high 26.5° 
   (b) Governor 
    (1) McCauley C290D3/T18 
   (c) Spinner, Cessna Dwg. 2450002

3A17 12 Rev. 47 
 
IX. Model 172RG  (cont’d) 
 
 *Airspeed limits Maneuvering   106 knots 
   (IAS) Maximum structural cruising 145 knots 
 (See Note 7 on use of IAS) Never exceed   164 knots 
  Flaps extended  100 knots 
  Landing gear extension 164 knots 
 
 C.G. range Normal Category 
  (+39.5) to (+46.5) at 2650 lbs. 
  (+36.0) to (+46.5) at 1950 lbs. 
  Straight line variation between points given. 
  Moment change due to retracting landing gear +2424 in.-lbs. 
 
 Empty weight C.G. range None 
 
 *Maximum weight 2650 lbs. 
  Ramp weight  2658 lbs. 
 
 Number of seats 4  (2 at +34 to +46, 2 at +73) 
 
 Maximum baggage 200 lb.  (+95) 
 
 Fuel capacity 66 gal. (two 33 gal. tanks in wings at +48.0)  (62 gal. usable) 
  See Note 1 for weight of unusable fuel. 
 
 Oil capacity 8 qt.  (-17.4)  (5 qts. usable) 
 
 Control surface movements Wing flaps Up 0° Down 30° +0°, -2° 
  Ailerons Up 20° ± 1° Down 15° ± 1° 
  Elevator tab Up 28° + 1° -0° Down 23° + 1° -0° 
  Elevator Up 28° + 1°, -0° Down 23° + 1°, -0° 
    (Neutral position measured 
    with the bottom of the balance 
    area flush with the bottom of 
    the stabilizer) 
  Elevator tab Up 22° + 1°, -0° Down 19° + 1°, -0° 
  Rudder Right 16° ± 1° Left 16° ± 1° 
    (Measured parallel to W.L.) 
 
 Serial numbers eligible Model 172RG: 172RG0001 through 172RG0570 (1980 Model) 
      691, 172RG0571 through 172RG0890 (1981 Model) 
      172RG0891 through 172RG1099 (1982 Model) 
      172RG1100 through 172RG1144 (1983 Model) 
      172RG1145 through 172RG1177 (1984 Model) 
      172RG1178 through 172RG1191 (1985 Model)

Rev. 46 13 3A17 
 
Data Pertinent to All Models 
 
Datum Lower front face of firewall 
 
Leveling means Upper door sill 
  
Certification Basis:  
175 Series, P172D and R172 Series 
Part 3 of the Civil Air Regulations dated May 15, 1956.  In addition, effective S/N R1722930 and on, FAR 23.1559 effcti ve 
March 1, 1978.  FAR 36 dated December 1, 1969, plus amendments 36-1 through 36-6 for Model R172K and on. 
 
172RG 
Part 3 of the Civil Air Regulations dated May 15, 1956, plus paragraphs 23.729, 23.777(e), 23.781, 23.1555(e)(1) and (2), and 
23.1563 of the Federal Aviation Regulations dated February 1, 1965, as amended effective September 1, 1977; FAR 23.1559 
effective March 1, 1978; FAR 36 dated December 1, 1969, plus amendments 36-1 through 36-10.  In addition, effective S/N 
172RG1178 and on, FAR 23.1545(a), Amendment 23-23 dated December 1, 1978. 
 
R172H (USAF T-41D) 
Part 3 of the Civil Air Regulations dated May 15, 1956.  In addition, effective S/N R1720621 and on, FAR 36 dated Decembe r 1, 
1969, plus amendments 36-1 through 36-12. 
 
Application for Type Certificate dated August 13, 1956.  Type Certificate No. 3A17 issued January 14, 1958, obtained by the 
manufacturer under delegation option procedures. 
 
Equivalent Safety Items S/N 680, R1722000 and up 
Airspeed Indicator CAR 3.757 (see Note 7 on use of IAS) 
Operating Limitations CAR 3.778(a) 
 
Equivalent Safety Items 172RG0001 and up 
Fuel system CAR 3.430 
Airspeed Indicator CAR 3.757 (see Note 7 on use of IAS) (S/N 172RG0001 through 172RG1177) 
Operating Limitations CAR 3.778(a) 
Landing Gear Indication System FAR 23.729(e) (S/N 172RG0001 through 172RG0890) 
 
Production Basis:  
Production Certificate No. 4.  Delegation Option Manufacturer No. CE-1 authorized to issue airworthiness certificates under 
delegation option provisions of Part 21 of the Federal Aviation Regulations. 
 
Equipment: The basic required equipment as prescribed in the applicable airworthiness requirements (see 
  Certification Basis) must be installed in the aircraft for certification.  This equipment must 
  include a current Airplane Flight Manual effective S/N R1722930 and on, S/N 172RG0001 and on. 
  In addition, the following items of equipment are required: 
 
  1. Model 175 through P172D, Stall Warning Indicator, Dwg. 0511062. 
  2. Model R172E and on, Stall Warning System, Dwg. 0523112. 
  3. Model R172, S/N R1720001 through R1720546, Fuel Boost Pump Switch, Dwg. 0509027. 
  4. Model 172RG, S/N 172RG0001 and on, Stall Warning Indicator, S1672-5.   
 
  The equipment portion of Aircraft Specification 3A17, Revision 10, or Cessna Service News 
  dated November 5, 1963, which contains the Revision 10 edition, should be used for equipment 
  references on all aircraft prior to the Model P172D.  Refer to applicable equipment list for the  
  Model P172D and subsequent models.

3A17 14 Rev. 47 
 
Data Pertinent to All Models (cont’d) 
 
NOTE 1: Model 175, 175A, 175B, 175C, P172D, R172E through R172J 
 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.  
The certificated empty weight and corresponding center of gravity location must include unusable fuel of 54 
lbs. at (+46) for Model 175, 60 lb. at (+46) for Models 175A and 175B, 63 lbs. at (+46) for Models 175C and 
P172D, 36 lbs. at (+46) for R17E through R172J; and unusable oil of 5.5 lbs. at (-18.5) for Models 175, 
175A, 175B, 175C, and P172D, and undrainable oil of 0.0 lbs. at (-21.5) for Models R172E through R172J. 
 
 Model R172K and on 
 The certificated empty weight and corresponding center of gravity locations must include unusable fuel of 18 
lbs. at (+46) and full oil of 15 lbs. at (-21.5). 
 
  Model 172RG and on 
 The certificated empty weight and corresponding center of gravity location must include unusable fuel of 24 
lb. at (+46) and full oil of 17 lbs. at (-16.1). 
 
NOTE 2:   (A) The following placards must be displayed in full view of the pilot: 
     (1) "This airplane must be operated in compliance with the operating limitations stated in 
     the form of placards, markings and manuals." 
 
     (2) "Normal category 
     Maximum design weight ( )** 
     Reference weight and balance data for loading instructions. 
     **Use 2350 lbs. for Models 172, 175A and 175B; 2450 lbs. for Model 175C; 2500 lbs. 
     for Models P172D, R172E, and R172F and 2550 lbs. for Model R172G. 
     Flight Maneuvering Load Factors 
    Flaps up +3.8  -1.52 
    Flaps down +3.5 
    No acrobatic maneuvers including spins approved." 
 
     (3) (a) "Utility Category (R172E and R172F only) 
     Maximum design weight 2200 lbs. 
     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  127 mph (110 knots) 
    Lazy Eights  127 mph (110 knots) 
    Steep turns  127 mph (110 knots) 
    Spins   Slow deceleration 
    Stalls    (except whip stalls) Slow deceleration" 
 
    (b) "Utility Category (R172G only) 
     Maximum design weight 2200 lbs. 
    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  125 mph (109 knots) 
     Lazy Eights  125 mph (109 knots) 
     Steep turns  125 mph (109 knots) 
     Spins   Slow deceleration 
     Stalls    (except whip stalls) Slow deceleration"

Rev. 46 15 3A17 
 
Data Pertinent to All Models (cont’d) 
 
NOTE 2  (cont'd)  
  (A) (4) (a) Model R172H, S/N R1720445 through R1720494 
     "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  125 mph CAS (109 knots) 125 mph CAS (109 knots) 
    Gross weight   2550 lb.  2200 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 Maneuver Max. Entry Speed 
    Chandelles  125 mph (109 knots) Spins  Slow deceleration 
    Lazy Eights  125 mph (109 knots) Stalls  Slow deceleration 
    Steep turns  125 mph (109 knots)   (except whip stalls) 
 
    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) 
 
    (b) Model R172H, S/N R1720495 through R1720620 
     "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  125 mph CAS (109 knots) 125 mph CAS (109 knots) 
    Gross weight   2550 lb.  2200 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 Maneuver Max. Entry Speed 
    Chandelles  125 mph (109 knots) Spins  Slow deceleration 
    Lazy Eights  125 mph (109 knots) Stalls  Slow deceleration 
    Steep turns  125 mph (109 knots)   (except whip stalls) 
 
    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)

3A17 16 Rev. 47 
 
Data Pertinent to All Models (cont’d) 
 
NOTE 2  (cont'd)  
  (A)  (c) Model R172J 
     "This airplane must be operated in compliance with the operating limitations 
     as stated in the forms of placards, markings, and manuals. 
 
             MAXIMUMS 
        Normal Category Utility Category 
     Maneuvering speed  118 mph CAS (104 knots) 118 mph CAS (104 knots) 
     Gross weight   2550 lb.  2200 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: 
     Maneuver  Max. Entry Speed Maneuver Max. Entry Speed 
     Chandelles  125 mph (109 knots) Spins  Slow deceleration 
     Lazy Eights  125 mph (109 knots) Stalls  Slow deceleration 
     Steep turns  118 mph (104 knots)   (except whip stalls) 
 
     Altitude loss in stall recovery  -  160 ft. 
     Abrupt use of controls prohibited above 118 mph. 
     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) 
 
    (d) Model R172K (R1722000 through R1722929) (landplane) 
     "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  105 knots  105 knots 
     Gross weight    2550 lb.  2200 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   110 knots   Spins  Slow deceleration 
     Lazy Eights   110 knots   Stalls  Slow deceleration 
     Steep turns   105 knots   (except whip stalls) 
 
     Altitude loss in stall recovery  -  160 ft. 
     Abrupt use of the controls prohibited above 105 knots. 
 
     Spin recovery:  Opposite rudder  -  Forward elevator  -  Neutralize controls 
     Intentional spins with flaps extended are prohibited.  Flight into known icing 
     conditions prohibited.  This airplane is certified for the following flight 
     operations as of date of original airworthiness certificate. 
 
      DAY  -  NIGHT  -  VFR  -  IFR"  (as applicable)

Rev. 46 17 3A17 
 
 
Data Pertinent to All Models (cont’d) 
 
NOTE 2  (cont'd) 
   (A) (e) Model R172K (R1722000 through R1722929)  (Floatplane with Edo 248B-2440 floats) 
     "This airplane must be operated as a normal category airplane in compliance wih the 
     operating limitations as stated in the form of placards, markings and manuals. 
 
MAXIMUMS 
     Maneuvering speed (IAS) 105 knots 
     Gross weight    2550 lbs. 
     Flight load factor   Flaps up +3.8, -1.52 
           Flaps down +2.0 
 
     No acrobatic maneuvers, including spins, approved.  Altitude loss in a stall 
     recovery - 250 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) 
 
    (f) Model R172K  (S/N 680, R1722930 and on)  (Landplane) 
      
     "The markings and placards installed in this airplane contain operating 
     limitations which must be complied with when operating this airplane in 
     the Normal Category.  Other operating limitations which must be complied 
     with when operating this airplane in this category or in the Utility 
     Category are contained in the Pilot's Operating Handbook and FAA Approved 
     Airplane Flight Manual. 
 
     Normal Category  No acrobatic maneuvers, including spins, approved. 
 
     Utility Category  No acrobatic maneuvers approved except those listed 
          in the Pilot's Operating Handbook. 
 
          Baggage compartment and rear seat must not be occupied. 
 
     Spin Recovery   Opposite rudder, forward elevator, neutralize controls. 
 
     Flight into known icing conditions prohibited. 
 
     This airplane is certified for the following flight operations as of date of original 
     airworthiness certificate. 
 
      DAY  -  NIGHT  -  VFR  -  IFR"  (as applicable) 
 
    (g) Model R172K  (R1722930 and on)  (Floatplane with Edo 248B-2440 floats) 
     "The markings and placards installed in this airplane contain operating 
     limitations which must be complied with when operating this airplane in 
     the Normal Category.  Other operating limitations which must be complied 
     with when operating this airplane in this category are contained in the 
     Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. 
 
     No acrobatic maneuvers, including spins, approved. 
 
     Flight into known icing conditions prohibited. 
 
     This airplane is certificated for the following flight operations as of date of 
     original airworthiness certificate: 
 
      DAY  -  NIGHT  -  VFR  -  IFR"  (as applicable)

3A17 18 Rev. 47 
 
Data Pertinent to All Models (cont’d) 
 
NOTE 2  (cont'd) 
  (A) (5) Near fuel selector: 
    (a) Model 175 through P172D 
     "Both tanks on for takeoff and landing." 
    (b) Model R172 and on 
     "When switching from dry tank, turn pump on 'High' momentarily." 
 
   (6) Near flap handle or switch: 
    (a) Model 175 though P172D 
     "Flaps  -  Pull to extend 
     Takeoff  Retract 0° 
        1st Notch 10° 
        0°  -  40° 
    (b) Model R172E through R172J 
     "Avoid slips with flaps extended." 
    (c) R172K (R1722000 through R1723399, and 680) 
        "W   0° 
        I  
       N 10° 
       G  
        20° 
       F 
       L 
       A 
       P 40° 
       S 
       AVOID SLIPS WITH  
       FLAPS EXTENDED." 
 
    (d) R172K (R1723400 and on) 
        "W   0° 
        I  
       N 10° 
       G  
        20° 
       F 
       L 
       A 
       P 40° 
       S 
       AVOID SLIPS WITH  
       FLAPS EXTENDED." 
 
   (7) Model 175A, 175B floatplane: 
    "Operate as a Normal Category airplane except: 
     Maximum design weight 2450 lbs. 
     Maximum altitude in stall recovery   120 ft. 
     Water rudder  -  Pull to retract; retract for normal takeoff, flight and landing 
     Extend - taxi and cross wind takeoff"

Rev. 46 19 3A17 
 
Data Pertinent to All Models (cont’d) 
 
NOTE 2  (cont'd) 
  (A) (8) With fixed pitch propeller (T-41C) 
    (a) "A fuel flow placard placed near the fuel flow meter will read: 
 
CLIMB FUEL FLOW  -  G.P.H. 
     Altitude    2400  2600 
         S.L.    14.5  16.0 
       4,000    12.5  14.0 
       8,000    11.0  12.0 
     12,000      9.5  10.5" 
 
    (b) On panel adjacent to mixture stop: 
     (1) "Engage for student training above 5000 ft." 
     (2) "Mixture stop" 
     (3) "Engage" 
 
   (9) Model R172G and R172H 
    (a) On instrument panel: 
     "Do not turn off alternator in flight except in emergency." 
    (b) The following placard must be displayed in the baggage compartment: 
     (1) Model 175 through P172D 
      "Maximum baggage 120 lb.  For additional loading instructions, see 
      weight and balance data." 
     (2) Model R172E through R172H 
      "200 pounds maximum baggage or 120 lbs. aux. seat passenger.  For 
      additional loading instructions, see weight and balance data." 
     (3) Model R172J and on 
      "200 pounds maximum baggage or 120 lbs. aux. seat passenger forward 
      of baggage door latch.  50 pounds maximum baggage aft of baggage door 
      latch.  Maximum 200 pounds combined.  For additional loading 
      instructions, see weight and balance data." 
 
   (10) On control lock:  (R172K and on) 
    "Control lock  -  Remove before starting engine." 
 
   (11) Near fuel selector valve handle:  (R172K and on) 
     "BOTH   -  49 gal. 
       LEFT   -  24.5 gal. 
       RIGHT -  24.5 gal." 
 
   (12) Near fuel tank filler: 
    (a) R1722000 through R1722724 
       "Fuel 
      100/130 min. grade aviation gasoline 
       Cap. 26 U.S. Gal." 
    (b) S/N 680, R1722725 and on 
       "Fuel 
      100LL or 100 min. grade aviation gasoline 
       Cap. 26 U.S. gal." 
 
   (13) On instrument panel near manifold pressure/fuel flow gauge:  (R172K and on) 
      "FUEL FLOW 
        AT FULL THROTTLE 
         2600 rpm 
      S.L.   16 GPH 
        4000 ft  14 GPH 
        8000 ft  12 GPH 
      12000 ft  10 GPH"

3A17 20 Rev. 47 
 
Data Pertinent to All Models (cont’d) 
 
NOTE 2  (cont'd) 
  (A) (14) R172K, S/N R1722000 through R1723199, S/N R1723400 and on 
    (Floatplane with Edo 2488-2440 floats) 
    (a) Near airspeed indicator 
      "Floatplane 
     Stall speeds are approximately 5 KIAS lower than indicator markings." 
 
   (15) 172RG and on 
    All placards required in the Pilot's Operating Handbook and FAA Approved 
    Airplane Flight Manual must be installed in the appropriate locations. 
 
   (16) R172H, S/N R1720621 and on 
    All placards required in the Pilot's Operating Handbook and FAA Approved 
    Airplane Flight Manual must be installed in the appropriate locations. 
 
NOTE 3: RESERVED 
 
NOTE 4: The Models 175A and 175B fuel system does not comply with CAR 3.433 and 3.434 for horsepower greater 
than 167 at the best angle of climb which is the most critical attitude. 
 
NOTE 5: Compliance with Cessna Service Letter SE74-18, dated August 23, 1974, Supplement No. 1, allows a 2 quart 
reduction in oil capacities (10 quarts to 8 quarts on IO-360 series engines). Usable oil is 5 quarts. 
 
NOTE 6: Model R172J and on 
 Cylinder head temperature probe to be installed in No. 2 cylinder head.  
 
 Model 172RG and on 
 Cylinder head temperature probe to be installed in No. 4 cylinder head.  
 
NOTE 7: The marking of the airspeed indicator with IAS provides an equivalent level of safety to CAR 3.757 when 
the approved airspeed calibration data presented in Section V of the Pilot's Operating Handbooks listed 
below is available to the pilot: 
 
   R172K, Cessna P/N D1083-13 (S/N R1722000 through R1722724) (Landplane) 
   R172K, Cessna P/N D1110-13 (S/N R1722725 through R1722929) (Landplane) 
   R172K, Cessna P/N D1098-13 (S/N R1722725 through R1722929) (Floatplane) 
   R172K, Cessna P/N D1139-13PH (S/N 680, R1722930 through R1723199) 
   R172K, Cessna P/N D1173-13PH (S/N R1723200 through R1723399) 
   R172K, Cessna P/N D1193-13PH (S/N R1723400 through R1723454) 
   172RG, Cessna P/N D1174-13PH (S/N 172RG0001 through 172RG0570) 
   172RG, Cessna P/N D1194-13PH (S/N 172RG0571 through 172RG0890) 
   172RG, Cessna P/N D1213-13PH (S/N 172RG0891 through 172RG1099) 
   172RG, Cessna P/N D1232-13PH (S/N 172RG1100 through 172RG1144) 
   172RG, Cessna P/N D1253-13PH (S/N 172RG1145 through 172RG1177) 
 
NOTE 8: 14-volt electrical system 
 (S/N R1722000 through R1722724) 
 
 28-volt electrical system 
 (S/N 680, R1722725 and on; S/N 172RG0001 and on) 
 
 In addition to the placards specified above, the prescribed operating limitations indicated by an asterisk (*) 
under Sections I through IX of this data sheet must also be displayed by permanent markings. 
 
NOTE 9: For Models 172RG, P172, R172, and 175: 
 
WARNING:  Use of alcohol-based fuels can cause serious performance degradation and fuel 
system component damage, and is therefore prohibited on Cessna airplanes. 
 
--- END ---
```

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- [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 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 86-19-11](https://openairdocs.org/ad/86-19-11): Contaminated Fuel · Cessna 177, 177A, 177B and 83 more. Effective Oct 4, 1986
- [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 85-20-01](https://openairdocs.org/ad/85-20-01): Cabin Heat Deactivated · Cessna 172RG. Effective Dec 5, 1985
- [AD 72-03-03 R3](https://openairdocs.org/ad/72-03-03-R3): Wing Flap Actuators Jack Screw · Cessna F150F, F150G, F150H and 83 more. Effective Oct 15, 1984
- [AD 83-22-06](https://openairdocs.org/ad/83-22-06): Aileron Hinge Pin · Cessna 152, 172N, 172P and 18 more. Effective Nov 8, 1983
- [AD 83-14-04](https://openairdocs.org/ad/83-14-04): Cabin Heater Shroud Modification · Cessna 172RG. Effective Jul 20, 1983
- [AD 83-10-03](https://openairdocs.org/ad/83-10-03): Control Wheel Yoke Guide Modification · Cessna 172M, 172N, 172P and 17 more. Effective Jun 30, 1983
- [AD 82-07-02](https://openairdocs.org/ad/82-07-02): Engine Crankcase Breather · Lycoming O-360-A1A engine and Hartzell HC-C2YK-1B/7666A-2… (Avcon Industries STC SA1324CE or 14 others). Effective Apr 8, 1982
- [AD 80-25-07 R1](https://openairdocs.org/ad/80-25-07-R1): Oil Coolers · American Champion 7ECA, 7GCAA, 7GCBC and 39 more. Effective Sep 24, 1981
- [AD 81-16-09](https://openairdocs.org/ad/81-16-09): Elevator Control System · Cessna 172N, 172P, 172RG and 17 more. Effective Aug 13, 1981
- [AD 81-14-06](https://openairdocs.org/ad/81-14-06): Rudder Trim/Nose Gear Steering Bungee · Cessna 172RG. Effective Jul 13, 1981
- [AD 81-05-01](https://openairdocs.org/ad/81-05-01): Fuel Tank Capacity · Cessna 152, 172N, 172P and 3 more. Effective Mar 2, 1981
- [AD 80-19-08](https://openairdocs.org/ad/80-19-08): Fuel/Air Mixture · Cessna 172RG. Effective Sep 15, 1980
- [AD 80-06-03](https://openairdocs.org/ad/80-06-03): Wing Flap Cable Clamp · Cessna 150M, 152, 172N and 3 more. Effective Apr 21, 1980
- [AD 80-07-03](https://openairdocs.org/ad/80-07-03): Oil Pressure · Cessna R172K. Effective Mar 31, 1980
- [AD 80-01-06](https://openairdocs.org/ad/80-01-06): Flap Actuator Assembly · Cessna 152, 172RG, A152 and 2 more. Effective Jan 7, 1980
- [AD 79-08-03](https://openairdocs.org/ad/79-08-03): Electrical System · Cessna 120, 140, 140A and 152 more. Effective Jun 6, 1979
- [AD 77-12-08](https://openairdocs.org/ad/77-12-08): External Electrical Ground Power Receptacle · Cessna 172M, 172N, 177B and 19 more. Effective Jun 27, 1977
- [AD 77-02-09](https://openairdocs.org/ad/77-02-09): Wing Flap System · Cessna 150, 150A, 150B and 61 more. Effective Feb 3, 1977
- [AD 74-06-02](https://openairdocs.org/ad/74-06-02): AVCON Mufflers · Lycoming 150 and160 hp Model O-320-( ) engine (Williams Robert or Barbara STC SA750CE or 3 others). Effective Mar 18, 1974
- [AD 74-04-01](https://openairdocs.org/ad/74-04-01): Aft Fuselage Bulkhead Assembly · Cessna 172, 172A, 172B and 16 more. Effective Feb 12, 1974
- [AD 73-23-07](https://openairdocs.org/ad/73-23-07): Defective Spar Attachment Fittings · Cessna 150, 150A, 150B and 68 more. Effective Nov 19, 1973
- [AD 73-20-04](https://openairdocs.org/ad/73-20-04): Fuel Pump Boost Electrical Circuit · Cessna R172E. Effective Oct 3, 1973
- [AD 73-17-01](https://openairdocs.org/ad/73-17-01): Fuel Transfer Pump Placard · Cessna 170, 170A, 170B and 53 more. Effective Aug 16, 1973

All 59: https://openairdocs.org/tcds/3A17/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Cessna R172K](https://openairdocs.org/model/cessna-r172k): 653 aircraft (registry code 2072431)
- [Cessna 175](https://openairdocs.org/model/cessna-175): 536 aircraft (registry code 2072502)
- [Cessna 172RG](https://openairdocs.org/model/cessna-172rg): 445 aircraft (registry code 2072438)
- [Cessna 175A](https://openairdocs.org/model/cessna-175a): 245 aircraft (registry code 2072504)
- [Cessna 175B](https://openairdocs.org/model/cessna-175b): 100 aircraft (registry code 2072506)
- [Cessna R172E](https://openairdocs.org/model/cessna-r172e): 98 aircraft (registry code 2072413)
- [Cessna 175C](https://openairdocs.org/model/cessna-175c): 44 aircraft (registry code 2072508)
- [Cessna P172D](https://openairdocs.org/model/cessna-p172d): 23 aircraft (registry code 2072202)
- [Cessna R172G](https://openairdocs.org/model/cessna-r172g): 6 aircraft (registry code 2072421)
- [Cessna R172J](https://openairdocs.org/model/cessna-r172j): 1 aircraft (registry code 2072429)
- [Cessna R172H](https://openairdocs.org/model/cessna-r172h): 0 aircraft (registry code 2072425)

## STCs approved under this data sheet (541, 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 SA12446AK](https://openairdocs.org/stc/SA12446AK): Installation of Sensenich Propeller Company 2G0M8SXX/C76PGF Composite, Ground Adjustable Propeller. Sensenich Propeller Company
- [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 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 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 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 SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA01330LA](https://openairdocs.org/stc/SA01330LA): Installation of alternate avionics support assembly.. Radiorax Aviation Systems LLC
- [STC 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 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 SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation
- [STC SA00871SE](https://openairdocs.org/stc/SA00871SE): Installation of cockpit sunvisors. Rosen Sunvisor Systems LLC
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA1168SO](https://openairdocs.org/stc/SA1168SO): Installation of Aqua Model 2200 floats.. Outpost X Aviation Inc.
- [STC SA665CE](https://openairdocs.org/stc/SA665CE): Installation of Model 2400 Aqua floats. (175 FLOATPLANE CONFIGURATION). Outpost X Aviation Inc
- [STC SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc.
- [STC SA02575AK](https://openairdocs.org/stc/SA02575AK): Installation of the nose tire scraper P/N TSL-100. Aero Twin Inc.
- [STC SA02576AK](https://openairdocs.org/stc/SA02576AK): Installation of Cleveland and ABI, LLC Wheel and Brake Kits. ABI LLC
- [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine
- [STC SA04400NY](https://openairdocs.org/stc/SA04400NY): Installation of the Integrated Back-up Battery System (IBBS). TCW Technologies LLC
- [STC SA04192NY](https://openairdocs.org/stc/SA04192NY): KFD 900 Primary Flight Display System Additional Functions. Honeywell International Inc
- [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine
- [STC SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC
- [STC SA00897WI](https://openairdocs.org/stc/SA00897WI): Installation of Concorde Battery Corporation (VRSLA) Valve regulated sealed lead acid battery.. Aero-Mach Wilco LLC
- [STC SA3-611](https://openairdocs.org/stc/SA3-611): Installation of Wipaire Skis Inc. Model 3000 (Aircraft Skis) (FluiDyne) (Fli-Lite) Main and Model 2000
Nose skis. F.Atlee Dodge Aircraft Services

All 541: https://openairdocs.org/tcds/3A17/stcs.md

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