# TCDS A18EU: Textron Aviation Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Textron Aviation Inc.
- Revision: 10
- Revised: January 16, 2025
- Product: Aircraft, Small Airplane
- Certification basis: Part 21, CAR 3
- Registered aircraft: 2, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/ac/55/ac55344c318f0789b4a70d8471fab132b4cfd1440e05e805e0f92f784e314cac
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID189199282620250117143432.0001
- Page: https://openairdocs.org/tcds/A18EU

## Models (6)

As the data sheet lists them.

- FR172G
- FR172J
- FR172K
- FR172E
- FR172H
- FR172F

## 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 
Rev. No. 10 9 8 10 10 7 10 7 7 9 8 7 7 10 
 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A18EU 
Revision 10 
Textron Aviation 
 FR172E 
 FR172F 
 FR172G 
 FR172H 
 FR172J 
 FR172K 
January 16, 2025 
 
 
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. A18EU 
 
This data sheet, which is part of Type Certificate No. A18EU, prescribes conditions and limitations under which the product for 
which the Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations.   
 
Type Certificate Holder Textron Aviation Inc. 
 One Cessna Boulevard   
 Wichita, Kansas 67215 
 
Type Certificate Holder Record Cessna Aircraft Company transferred to  
 Textron Aviation Inc. on July 29, 2015 
 
 
Type Certificate (TC) A18EU was transferred from Reims Aviation S.A., 51 Aerodrome de Reims-Prunay, Reims, France, to 
Cessna Aircraft Company, Wichita, Kansas, USA, on December 11, 2006. Coincident with this transfer, the Federal Aviation 
Administration (FAA) has accepted the status of State of Design and State of Manufacture as defined by Annex 8 to the 
Convention of International Civil Aviation. Prior to December 11, 2006, products identified under TC A18EU were approved by 
the FAA in accordance with the Federal Aviation Regulation (FAR) appropriate to Imported Products (FAR §21.29). Effective 
December 11, 2006, and after, these products are to be considered domestic products for the purpose of design certification, 
continued airworthiness, and administration under FAR §21.21 becomes appropriate.  
 
 
I. Model FR172E, 4 PCLM (Normal category), 2 PCLM  (Utility category) approved September 19, 1967 
 Model FR172F, 4 PCLM (Normal category), 2 PCLM  (Utility category) approved October 10, 1968 
 
 Engine Rolls Royce Continental IO-360-D 
 
 *Fuel 100/130 minimum grade aviation gasoline 
 
 *Engine Limits For all operations, 2800 rpm (210 hp.)

A18EU 2 Rev. 10 
I. Model FR172E, FR172F  (cont’d) 
 
 Propeller and  1. McCauley propeller 
  Propeller Limits  Hub: D2A34C67 
Blades: 76C 
Diameter: Not over 76 in., not under 74.5 in. 
Pitch at 30-inch station: 
 Low pitch:  11.7   
 High pitch: 22.5  
a. Hydraulic governor: 
 (1)  Woodward J210452 
 (2) McCauley C290-D2/T6 
2. McCauley propeller 
Hub: 1B235/DFC (T-41C) 
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) True Ind. 
 (KIAS) Maximum structural cruising 145 mph  (126 knots) True Ind. 
Never exceed 182 mph  (158 knots) True Ind. 
Flaps extended 100 mph  (  87 knots) True Ind. 
 
 C.G. Range Normal Category  (+40.5)  to  (+47.3)  at 2500 lb. 
    (+35.0)  to  (+47.3)  at 1950 lb.  
Utility Category (+37.5)  to  (+40.5)  at 2200 lb. 
    (+35.0)  to  (+40.5)  at 1950 lb. 
Straight line variation between points given. 
 
 Empty Weight C.G. Range None 
 
 *Maximum Weight 2500 lb. (Normal Category) 
  2200 lb. (Utility Category) 
 
 Number of Seats Four (two at +36, two at +70)  
 
 Maximum Baggage 120 lb.  (+95) 
 
 Fuel Capacity 52 gal. (two 26 gal. ta nks in wings at +48; 46 gal. usable) 
  See NOTE 1 for weight of unusable fuel. 
 
 Oil capacity 10 qt. at -21.5 (1 qt. unusable) 
  See NOTE 5 for optional oil capacity.  Se e NOTE 1 for weight of undrainable oil.  
 
 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 No’s Eligible FR172E: FR17200001 thru FR17200060 
  FR172F:  FR17200061 thru FR17200145

Rev. 10 3 A18EU 
II. Model FR172G, 4 PCLM (Normal category), 2 PC LM (Utility category), Approved August 20, 1969 
 
 Engine Rolls Royce Continental IO- 360-D, IO-360-C, IO-360-DB, or IO-360-CB 
 
 *Fuel  100/130 minimum grade aviation gasoline. 
 
 *Engine limits For all operations, 2800 r.p.m. (210 hp.) 
 
 Propeller and  1. McCauley propeller 52 lb. (-42) 
  Propeller Limits  Hub: D2A34C67 
Blades: 76C 
Diameter: Not over 76 in., not under 74.5 in. 
Pitch at 30-inch station: 
 Low pitch:  11.7   
 High pitch: 22.5  
a. Hydraulic governor: 
 (1)  Woodward J210452, or 4 lb. (-34) 
 (2) McCauley C290-D2/T6 
 (3) McCauley C290-D3/T6 
2. McCauley propeller 
Hub: 1B235/DFC (T-41C) 
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 125 mph (109 knots) True Ind. 
Maximum structural cruising 145 mph (126 knots) True Ind. 
Never exceed 185 mph (160 knots) True Ind. 
Flaps extended 100 mph (  87 knots) True Ind. 
 
 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. 
Straight line variation between points given.  
 
 Empty weight C.G. Range None 
 
 *Maximum weight 2550 lb. (Normal Category) 
  2200 lb. (Utility Category) 
 
 Number of seats Four (two at +36, two at +70) 
 
 Maximum baggage 120 lb. (+95) 
 
 Fuel capacity  52 gals. (two 26 gal. tanks in wings at +48; 46 gals. usable). 
  See NOTE 1 for weight of unusable fuel. 
 
 Oil capacity 10 qts. at -21.5 (7 qt. unusable) 
  See NOTE 1 for weight of undrainable oi l.  See NOTE 5 for optional oil capacity. 
 
 Control Surface Wing flaps Takeoff   0   10 
 Movements  Landing    0   40 
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 No’s Eligible FR17200146 thru FR17200205 
  FR17200207 thru FR17200225

A18EU 4 Rev. 10 
III. Model FR172H, 4 PCLSM (Normal Category), 2 PC LM (Utility Category), Approved October 9, 1970 
 
 Engine Rolls Royce Continental, IO-360-D, IO-360-C, IO-360-DB, IO-360-CB, or IO-360-HB 
 *Fuel 100/130 minimum grade aviation gasoline. 
 
 *Engine Limits For all operations, 2800 r.p.m. (210 hp.) 
 
 Propeller and  1. McCauley propeller 
  Propeller Limits  Hub: D2A34C67 
Blades: 76C 
Diameter: Not over 76 in., not under 74.5 in. 
Pitch at 30-inch station: 
 Low pitch:  11.7   
 High pitch: 22.5  
a. Hydraulic governor: 
 (1)  Woodward F210452, or 
 (2) McCauley C290-D2/T6 
2. McCauley propeller 
Hub: 2A34C209 
Blades: 78CCA 
Diameter: Not over 78 in., not under 76.5 in. 
Pitch at 30-inch station: 
 Low pitch:  10.6   
 High pitch: 22.0  
a. Hydraulic governor: 
 (1)  Woodward F210452, or 
 (2) McCauley C290-D2/T6 
3. McCauley propeller 
Hub: 2A34C209 
Blades: 78CCA-2 
Diameter: Not over 76 in., not under 74.5 in. 
Pitch at 30-inch station: 
 Low pitch:  11.3   
 High pitch: 22.0  
a. Hydraulic governor: 
 (1)  Woodward F210452 
 (2) McCauley C290-D2/T6 
 (3) McCauley C290-D3/T6 
4. McCauley propeller 
Hub: 1B235/DFC 
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  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 lb. 
(+35.0) to (+47.3) at 1950 lb. 
 
Utility Category 
(+37.5) to (+40.5) at 2200 lb. 
(+35.0) to (+40.5) at 1950 lb.

Rev. 10 5 A18EU 
III. Model FR172H (cont’d) 
 
 Empty Weight C.G. Range None 
 
 *Maximum Weight 2550 lb. (Normal Category) 
2200 lb. (Utility Category) 
 
 Number of Seats Four (two  at +36; two at +70)   
 
 Maximum Baggage 200 lb. (+95)  
 
 Fuel Capacity 52 gals. (two 26 gal. ta nks in wings at +48; 46 gal. usable)  
See NOTE 1 for weight of unusable fuel. 
 
 Oil Capacity 10 qt. at -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 is with 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 No’s Eligible FR17200226 thru FR17200308 
FR17200310 thru FR17200350 
 
IV. Model FR172J, 4 PCLM (Normal Category), 2 PCLM  (Utility Category) Approved October 27, 1972 
 FR172J (thru 1975 Model)  
 
 Engine Rolls Royce Continental IO-360-H or IO-360-HB 
 
 *Fuel 100/130 minimum grade aviation gasoline. 
 
 *Engine Limits For all operations, 2800 r.p.m. (210 hp.) 
 
 Propeller and  1. McCauley propeller 
  Propeller Limits  Hub: 2A34C209  
Blades: 78CCA-2 
Diameter: Not over 76 in., not under 74.5 in. 
Pitch at 30-inch station: 
 Low pitch:  11.3   
 High pitch: 22.0  
a. Hydraulic governor: 
 (1)  Woodward F210452 
 (2) McCauley C290-D2/T6 
 (3) McCauley C290-D3/T6 
b. Spinner: Dwg 0550328 
 
 *Airspeed Limits (CAS) Maneuvering  118 mph  (104 knots) 
Maximum structural cruising 146 mph  (126 knots) 
Never exceed  185 mph  (160 knots) 
Flaps extended 100 mph  (  87 knots)

A18EU 6 Rev. 10 
IV. Model FR172J (1976 Model)  (cont’d) 
 
 Engine Rolls Royce Continental IO-360J 
 
 *Fuel 100/130 minimum grade aviation gasoline. 
 
 *Engine limits Takeoff (5 min) at 2800 r.p.m. (210 hp) 
  Max. continuous 2600 r.p.m. (195 hp) 
 
 Propeller and  1. McCauley propeller 
  Propeller Limits  Hub: 2A34C209  
Blades: 78CCA-2 
Diameter: Not over 76 in., not under 74.5 in. 
Pitch at 30-inch station: 
 Low pitch:  11.3   
 High pitch: 22.0  
a. Hydraulic governor: 
 (1)  Woodward F210452 
 (2) McCauley C290-D2/T6 
 (3) McCauley C290-D3/T6 
b. Spinner:  Dwg 0550328 
 
 *Airspeed limits (IAS) Maneuve ring    118 m.p.h. (104 knots) 
  Maximum structural cruising  146 m.p.h. (126 knots) 
  Never exceed   185 m.p.h. (160 knots) 
  Flaps extended  100 m.p.h. ( 87 knots) 
 
 C.G. Range Normal category 
  (+41.0)  to  (+47.3) at 2550 lb. 
  (+35.0)  to  (+47.3) at 1950 lb.  
  Utility category 
  (+37.5)  to  (+40.5)  at 2200 lb. 
  (+35.0)  to  (+40.5)  at 1950 lb.  
 
 Empty Weight C.G. Range None 
 
 Maximum Weight 2550 lb. (Normal Category) 
  2200 lb. (Utility Category)  
 
 Number of Seats Four (two at +36, two at +70) 
 
 Maximum Baggage 200 lb. (+95) 
 
 Fuel Capacity 52 gals. (two 26 gal. tanks in wings at +48; 46 gals. usable) 
  See NOTE 1 for weight of unusable fuel. 
 
 Oil Capacity 10 qts. at -21.5 (7 qt. unusable) 
  See NOTE 1 for weight of undrainable oi l.  See NOTE 5 for optional oil capacity. 
 
 Control Surface Wing Flaps  Takeoff  0  - 10 
 Movements     Landing  0  – 40 
  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 No’s Eligible FR17200351 thru FR17200559 
  FR17200562 thru FR17200590

Rev. 10 7 A18EU 
V. Model FR172K, 4 PCLM (Normal category), 2 PC LM (Utility category) Approved October 27, 1976 
 
 Engine Rolls Royce Continental IO-360-K or  
  IO-360-KB (1977 and 1978 model, 1979 model and On)  
 
 *Fuel  100/130 minimum grade aviation gasoline (1977 model) 
  100LL/100 minimum grade aviati on gasoline (1978 model and On) 
 
 *Engine Limits For all operations, 2600 r.p.m. (195 hp.) 
 
 Propeller and  1. McCauley propeller 
  Propeller Limits  Hub: 2A34C203  
Blades: 90DCA-14 
Diameter: Not over 76 in., not under 74 in. 
Pitch settings at 30-inch station: 
 Low pitch:  12.0   
 High pitch: 25.1  
a. Hydraulic governor: McCauley C290D3/T15 
b. Spinner:  Dwg 0550328 
2. McCauley propeller (floatplane only) 
Hub: 2A34C203  
Blades: 90DCA-10 
Diameter: Not over 80 in., not under 78.5 in. 
Pitch settings at 30-inch station: 
 Low pitch:  11.3   
 High pitch: 25.1  
a. Hydraulic governor: McCauley C290D3/T15 
b. Spinner:  Dwg 0550328 
 
 *Airspeed Limits (1977 Model thru 1979 Model) 
 (IAS, see NOTE 7)  Maneuvering   105 knots 
   Maximum structural cruising 129 knots 
   Never exceed  153 knots 
   Flaps extended    87 knots 
 
  (1980 Model 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 lb.  
  (+35.0) to (+47.3) at 1950 lb.  
  Utility Category 
  (+37.5) to (+40.5) at 2200 lb. 
  (+35.0) to (+40.5) at 1950 lb.  
 
  Floatplane: (Edo 248B-2400) 
  Normal Category 
  (+39.5) to (+45.5) at 2550 lb. 
  (+37.0) to (+45.5) at 2110 lb. 
 
 Empty Wt. C.G. Range None 
 
 Maximum Weight  2550 lb. (Normal Category) 
  2200 lb. (Utility Category) 
  2558 lb. Ramp weight (1979 model and on) 
 
 No. of Seats Four (two  at +36, two at +70)

A18EU 8 Rev. 10 
V. Model FR172K  (cont’d) 
 
 Maximum Baggage 200 lb. (+95) 
 
 Fuel Capacity 52 gals. (two 36 gal. ta nks in wings at +48) (49 gals. usable). 
  See NOTE 1 for weight of unusable fuel. 
 
 Oil Capacity 8 qts. at -21.5 (5 qt. usable) 
 
 Control Surface Movements Wing Flaps Takeoff 0  - 10 (Landplane) 
    Landing 0  - 20 (Floatplane) 
      0  - 40 + 0, - 2 
      (1977 model thru 1980 model) 
  Ailerons  Up  20    1 Down 15    1 
  Elevator Tab Up 28    1, -0 Down 13    1, -0 
      (1977 model thru 1980 model) 
      (All FR172K floatplanes) 
    Up 28  + 1, -0 Down 19  + 1, - 0 
      (1981 model and On) 
  Elevator  Up 28  + 1, -0 Down 23  + 1, -0 
  (Neutral position measured with the bot tom of the balance area flush with the 
   bottom of the stabilizer.) 
  Rudder   Right    16    1 Left 16    1  
  (Measured parallel to W. L.) 
 
 Serial No’s Eligible FR17200591 thru FR17200675 
 
Data Pertinent to All Models 
 
Datum Front face of firewall 
 
Leveling means Upper door sill 
 
Certification basis FAR 21.29 CAR 3 effec tive May 15, 1956, with no amendments. 
  TC A18EU issued:  September 19, 1967. 
  Date of Application for TC:  August 8, 1967. 
 
Equipment The basic required as prescribed in the applicable airworthiness requirements (see 
Certification Basis) must be installed in the aircraft for certification. In addition, the 
following item of equipment is required: 
 
  Stall Warning System, Cessna dwg. 0523112 
 
NOTE 1. 1. Model FR172E thru FR172J 
  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 the corresponding center of gravity location must 
include unusable fuel of 36 lb. at (+46) and undrainable oil of 0.0 lb. at (-21.5) for Models FR172E 
through FR172J.  
 
 2. Model FR172K and On  
  The certificated empty weight and corresponding center of gravity location must include ususable fuel of 
18 lb. at (+46) and full oil of 15 lb. at (-21.5).

Rev. 10 9 A18EU 
NOTE 2. The following placards must be displayed in full view of the pilot: 
 
 1. Models FR172E, FR172F, and FR172G: 
  “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 (___)** 
Reference weight and balance data for loading instructions. 
**Use 2500 lb. for Models FR172E and FR172F, and 2550 lb. for Model FR172G.  
 
Flight Maneuvering Load Factors 
Flaps Up  +3.8 -1.52 
Flaps Down +3.5’ 
 
 2. Models FR172E and FR172F only: 
“Utility category 
Maximum design weight2200 lb. 
Baggage compartment and rear 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” 
 
 3. Model FR172G only: 
 “Utility category 
Maximum design weight  2200 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  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” 
 
 4. Model FR172H only: 
“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

A18EU 10 Rev. 10 
NOTE 2 (cont’d) 
 
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  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 
 
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)” 
 
 5. Model FR172J only 
“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  118 mph CAS (104 knots)  118 mph. (104 knots)  
  Gross Weight 2550 lb.   2200 lb. 
  Flight Load Factor  
   Flaps Up +3.8 -1.52   +4.4 -1.76 
   Flaps Down +3.5    +3.50 
 
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  Recommended Entry Speed 
Chandelles  125 mph (109 knots) 
Lazy eights  125 mph (109 knots) 
Steep turns  118 mph (104 knots) 
Spins  Slow deceleration 
Stalls (except whip stalls) Slow deceleration 
 
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)”

Rev. 10 11 A18EU 
NOTE 2 (cont’d) 
 
 6. Model FR172K (1977 & 1978 models) (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 
 Crosswind 20 knots at 90  
 
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  Recommended Entry Speed 
Chandelles   110 knots 
Lazy eights  110 knots 
Steep turns  105 knots 
Spins  low deceleration 
Stalls (except whip stalls) low deceleration 
 
Altitude loss in stall recovery – 160 ft. 
Abrupt use of 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 or original airworthiness 
certificate. 
 
  (DAY NIGHT VFR IFR) (As applicable)” 
 
 7. Model FR172K (1977 and 1978 model) 
(Floatplane with Edo 248B-2440floats) 
“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.  
 
Maneuvering speed (IAS) 105 knots 
Gross Weight  2550 lb. 
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 feet.  
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)” 
 
“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 (POH) and FAA Approved Airplane Flight Manual 
(AFM).  
 
Normal Category – No acrobatic maneuvers, including spins, approved. 
Utility Category – No acrobatic maneuvers approved except those listed in the POH.

A18EU 12 Rev. 10 
NOTE 2 (cont’d) 
 
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)” 
 
 8. Model FR172K (1979 model 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 POH and FAA 
Approved AFM.  
 
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)” 
 
 9. Near fuel selector (all models) 
“When switching from dry tank, turn pump on ‘HIGH’ momentarily” 
 
 10. Near flap handle or switch: 
a. Model FR172E thru FR172J 
 “Avoid slips with extended” 
 
b. Model FR172K (1977 model thru 1980 model) 
 
W 0  
I 10  
N 20  
G  
 
F 
L 40  
A 
P 
S 
 
  AVOID SLIPS WITH FLAPS EXTENDED

Rev. 10 13 A18EU 
NOTE 2 (cont’d) 
 
c. FR172K (1981 model and On) 
 
W 0  
I 10  
N 20  
G 
 
F 
L 30  
A 
P 
S 
 
 AVOID SLIPS WITH FLAPS EXTENDED 
 
 11. The following placard must be displayed on the instrument panel:  
 
a. Models FR172G and FR172H 
 “Do not turn off alternator in flight except in emergency.” 
 The following placard must be displayed in the baggage compartment.  
 
b. Model FR172E thru FR172H 
 “200 pounds maximum baggage or 120 lb. aux. seat passenger. For additional loading instructions 
see weight and balance data. 
 
c. Model FR172J and On  
 “200 lb. baggage or 120 lb. aux. seat passenger forward of baggage door latch. 50 lb. maximum 
baggage aft of baggage door latch. Maximum 200 lb. combined.  For additional loading 
instructions, see weight and balance data.” 
 
d. On control lock: (FR172K and On) 
 “Control lock – Remove before starting engine” 
 
e. Near fuel selector va lve handle: (FR172K and On) 
 “BOTH – 49 gal. 
 LEFT – 24.5 gal. 
 RIGHT – 24.5 gal.  
 
f. Near fuel tank filter:   
 FR172K (1977 model) 
 “Fuel 
 100/130 min. grade aviation gasoline 
 Cap. 26 U.S. gal.” 
 
 FR172K (1978 model and On) 
 “Fuel 
 100LL or 100 min. grade aviation gasoline 
 Cap. 26 U.S. gal.” 
 
g. On instrument panel near manifold pressure/fuel flow gauge: (FR172K and On) 
 
“FUEL FLOW 
AT FULL THROTTLE 
  2600 RPM 
S.L.  16 GHP 
4000 ft. 14 GHP 
8000 ft. 12 GHP 
12000 ft. 10 GHP”

A18EU 14 Rev. 10 
NOTE 3. RESERVED. 
 
NOTE 4. RESERVED. 
 
NOTE 5. Compliance with Cessna Service Letter No. SE74- 18, dated August 23, 1974, Supplemental No. 1, allows a 
two quart reduction in oil capacities (10 quarts to 8 quarts on IO-360 series engines). Usable oil is 5 quarts. 
 
NOTE 6. Model FR172J and On 
  Cylinder head temperature probe to be installed in No. 2 cylinder head. 
 
NOTE 7. 14-volt electrical system 
  (Model FR172K, 1977 model) 
 
  28-volt electrical system 
  (Model FR172K, 1978 model and On) 
 
In addition to the placards specified above, the prescribed operating limitations indicated by an asterisk (*) under Section I 
through IX of this data sheets must also be displayed by permanent markings.  
 
 
---- END ----
```

## ADs (25, 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 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 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 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 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 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 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 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 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 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 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 83-10-03](https://openairdocs.org/ad/83-10-03): Control Wheel Yoke Guide Modification · Cessna 172M, 172N, 172P and 17 more. Effective Jun 30, 1983
- [AD 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 76-04-03](https://openairdocs.org/ad/76-04-03): ARC PA-500A Actuators · Cessna 172L, 172M, 177B and 43 more. Effective Feb 26, 1976
- [AD 74-08-01](https://openairdocs.org/ad/74-08-01): Autopilot Servo Actuators · Aircraft Radio Autopilot Servo Actuators, 172L, 172M and 29 more. Effective Apr 9, 1974
- [AD 68-17-04](https://openairdocs.org/ad/68-17-04): Stall Warning System · Cessna 150, 150A, 150B and 63 more. Effective Sep 7, 1968
- [AD 87-20-03 R2](https://openairdocs.org/ad/87-20-03-R2) (historical): Seat Tracks · Cessna 150A, 150B, 150C and 212 more. Effective Sep 24, 1990
- [AD 86-26-04](https://openairdocs.org/ad/86-26-04) (historical): Shoulder Harness Adjuster · Cessna Aircraft Company, The 120, 140, 140A and 134 more. Effective Jan 6, 1987
- [AD 80-04-08](https://openairdocs.org/ad/80-04-08) (historical): Fuel Lines · Cessna 172N, R172K, F172N and 1 more. Effective Feb 16, 1980

## Registered aircraft by registry model (OpenAirDocs)

- [Cessna FR 172 J](https://openairdocs.org/model/cessna-fr-172-j): 1 aircraft (registry code 2075735)
- [Cessna FR 172 K](https://openairdocs.org/model/cessna-fr-172-k): 1 aircraft (registry code 2075739)

## STCs approved under this data sheet (113, first 50)

- [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 SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc.
- [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 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 SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC
- [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 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 SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation
- [STC SA00871SE](https://openairdocs.org/stc/SA00871SE): Installation of cockpit sunvisors. Rosen Sunvisor Systems LLC
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc.
- [STC SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc.
- [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine
- [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 SA2213CE](https://openairdocs.org/stc/SA2213CE): Installation of STOL Kit (wing leading edge cuffs, droop tips, stall fences and aileron gap seals). Curry Aviation LLC
- [STC SA02734LA](https://openairdocs.org/stc/SA02734LA): Installation of Airfilm Wing Strut Utility Mount. Airfilm Camera Systems
- [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc.
- [STC SA09902AC](https://openairdocs.org/stc/SA09902AC): Installation of BendixKing KFD 900 Flight Display System. Honeywell International Inc. (Bendix King)
- [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King)
- [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation
- [STC SA00410BO](https://openairdocs.org/stc/SA00410BO): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation
- [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc
- [STC SA01869WI](https://openairdocs.org/stc/SA01869WI): Installation of a Tail Tie-Down Assembly. Middle Forks Mod LLC
- [STC SA03286CH](https://openairdocs.org/stc/SA03286CH): Install an electronic engine ignition system. Electroair Acquisition Corporation
- [STC SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation
- [STC SA00344BO PAGE 1](https://openairdocs.org/stc/SA00344BO%20PAGE%201): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies
- [STC SA00744DE](https://openairdocs.org/stc/SA00744DE): Installation of the Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT31 Transponder and an approved position sensor. Peregrine
- [STC SA00765DE](https://openairdocs.org/stc/SA00765DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine
- [STC SA00900CH](https://openairdocs.org/stc/SA00900CH): Installation of Wipaire Model 2350 Amphibian/Seaplane Floats and McCauley Model 1A200/WFA propeller.. Wipaire Inc
- [STC SA01435SE](https://openairdocs.org/stc/SA01435SE): Installation of J.P. Instruments (JPI) Primary Engine Data Management System. J. P. Instruments
- [STC SA02153LA-D PAGE 1](https://openairdocs.org/stc/SA02153LA-D%20PAGE%201): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc.
- [STC SA01835WI](https://openairdocs.org/stc/SA01835WI): Installation of Trig Avionics TY-96 or TY-97 VHF Communications Radio. Peregrine
- [STC SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC
- [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley
- [STC SA00353BO](https://openairdocs.org/stc/SA00353BO): Installation of an auto lean system. Flight Enhancements LLC
- [STC SA00780SE](https://openairdocs.org/stc/SA00780SE): Installation of the True Lock Safety Retention Axle Lock Nut System. True Lock LLC
- [STC SA09857AC](https://openairdocs.org/stc/SA09857AC): Installation of an ISTART Starting Enhancement System. IStart Partners, Ltd.
- [STC SA02119SE PAGE 1](https://openairdocs.org/stc/SA02119SE%20PAGE%201): Installation of Garmin GDL 88 ADS-B UAT Transceiver System. Garmin International Inc
- [STC SA484CH](https://openairdocs.org/stc/SA484CH): Installation of instrument light dimmer system.. Tanis Aircraft Products
- [STC SA02442AK PAGE 1](https://openairdocs.org/stc/SA02442AK%20PAGE%201): Approval of the L-3 Communications NGT 2000/2500 ADS-B system. ADS-B Technologies, LLC
- [STC SA4305WE](https://openairdocs.org/stc/SA4305WE): Installation of GAR-AERO wheel adapters and tundra type tires on the main landing gear. Seaplanes North LLC

All 113: https://openairdocs.org/tcds/A18EU/stcs.md

---
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