# TCDS A23EU: Textron Aviation Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Textron Aviation Inc.
- Revision: 8
- Revised: April 1, 2019
- Product: Aircraft, Small Airplane
- Certification basis: Part 21, Part 23
- Registered aircraft: 3, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/49/b5/49b5a837da403f015723d58015d1a177f92b05a96c165da2fe101f1081bca3c3
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/E85B2AA04105D1F2862583EE0072A0D1.0001
- Page: https://openairdocs.org/tcds/A23EU

## Models (8)

As the data sheet lists them.

- F337G
- FT337GP
- F337E
- FT337F
- FT337E
- F337F
- FT337HP
- F337H

## What the data sheet says

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

```text
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 
Rev. No. 8 3 8 8 3 8 3 8 7 8 6 8 6 3 3 3 3 3 3 
Page No. 20 21 22 23 24 
Rev. No. 3 3 3 3 6 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A23EU 
Revision 8 
Textron Aviation 
F337E 
F337G 
FT337E 
FT337GP 
F337F 
F337H 
FT337F 
FT337HP 
 April 1, 2019   
 
TYPE CERTIFICATE DATA SHEET NO. A23EU 
 
This data sheet, which is a part of Type Certificate No. A23EU, prescribes conditions and limitations under which the product for 
which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. 
 
Type Certificate Holder Textron Aviation Inc. 
  One Cessna Boulevard 
  Wichita, Kansas  67215 
 
Type Certificate Holder Record Cessna Aircraft Company transferred to  
  Textron Aviation Inc. on July 29, 2015 
 
Type Certificate A23EU was transferred from Reims Aviation S.A., 51 Aerodrome de Reims-Prunay, Reims, France, To Cessna 
Aircraft Company on December 11, 2006. Coincident with this transfer, the Federal Aviation Administration (FAA) has accepted 
responsibilities of State of Design for all airplanes, and State of Manufacture for airplanes manufactured after December 11, 2006 
as defined by Annex 8 to the Convention on International Civil Aviation. Prior to December 11, 2006, products identified under 
Type Certificate A23EU were approved by the FAA in accordance with the Federal Aviation Regulation appropriate to Imported 
Products (FAR 21.29). Effective December 11, 2006, and after, these products are to be considered domestic products for the 
purpose of design certification, continued airworthiness, and administered under Federal Aviation Regulations §21.21. 
 
I. Model F337E, 4-6 PCLM (Normal Category), Approved February 23, 1970 
 
 Engine (Front) Continental IO-360-C 
  (Rear)  Continental IO-360-C 
 
* Fuel 100/130 minimum grade aviation gasoline 
 
* Engine Limits For all operations, 2800 rpm (210 b.hp.) 
 
 Propeller and 1. McCauley constant speed full-feathering propeller installation 
   Propeller Limits  a. (Front) McCauley D2AF34C59/76C 
    Diameter:  not over 76 in., not under 74.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station: 
    11.7°  low, 79.0° feathered. 
 
   b. (Rear) McCauley D2AF34C61/L76C 
    Diameter:  not over 76 in., not under 74.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station: 
    10.8°  low, 79.0° feathered.

Rev. 8  Page 2 of 24 A23EU 
I. Model F337E (cont’d) 
    c. (Front) McCauley D2AF34C301/76CTA-0 
    Diameter:  not over 76 in., not under 75 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  11.7°  low, 79.0° feathered. 
 
   d. (Rear) McCauley D2AF34C302/L76CTA-0 
    Diameter:  not over 76 in., not under 75 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  10.8°  low, 79.0° feathered. 
 
   e. (Front) McCauley D2AF34C306/78 CAA-0 
    Diameter:  not over 78 in., not under 76.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  11°  low, 82° feathered. 
 
   f. (Rear) McCauley D2AF34C307/L78CBA-2 
    Diameter:  not over 76 in., not under 74.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  11°  low, 80° feathered. 
 
   g. (Front) Woodward hydraulic governor 210443 
 
   h. (Rear) Woodward hydraulic governor 210443 
 
   j. (Front) McCauley hydraulic governor CF 310D1/T1 or CF 310D2/T1 
 
   k. (Rear) McCauley hydraulic governor CF 310D1/T1 or CF 310D2/T1 
 
   l. (Front) Cessna spinner 1557303 (includes support and bulkhead assembly) 
 
   m. (Rear) Cessna spinner 1457306 (includes support and bulkhead assembly). 
 
* Airspeed Limits Never exceed  225 mph.  (195 knots) 
   (CAS) Maximum structural cruising  190 mph.  (165 knots) 
  Flaps extended  120 mph.  (104 knots) 
  Maneuvering  155 mph.  (135 knots) 
  Landing gear extension  160 mph.  (139 knots) 
 
 C.G. Range (+137.4) to (+143.0) at 4440 lb. 
   (landing gear extended) (+134.5) to (+143.0) at 3837 lb. or less. 
  Straight line variation between points given. 
  Landing gear retraction moment is +3318 in.-lb. 
 
 Empty Weight C.G. Range None 
 
* Maximum Weight 4440 lb. takeoff and flight: 4400 lb. landing 
 
 Number of Seats 4 - 6 (2 at +98.0 to +109.0); (2 at +133.0 to +142.0); 
  1 or 2 at +162.0 to +168.0) 
 Maximum Baggage 365 lb. (reference weight and balance for additional information) 
 
 Fuel Capacity 92.8 gal. (92 gal. usable) (2 tanks 46.4 gal. ea. at +150) 
  See NOTE 1 for data on undrainable fuel 
 
 Oil Capacity 10 qt. - front (+43.0) (7 qt. usable) (See NOTE 6) 
  10 qt. - rear (+207.5) (7 qt. usable) 
  See NOTE 1 for data on undrainable oil.

Rev. 8  Page 3 of 24 A23EU 
I. Model F337E  (cont'd) 
 
 Control Surface Movements Wing Flaps 
   Inboard   Down 25° +1, -2° 
   Outboard   Down 25° +1, -2° 
  Ailerons  Up 21° + 2° Down 14° 30' + 2° 
  Elevator  Up 26° + 1° Down 15°+ 1° 
  Elevator tab Up 15° + 1° Down 15° + 1° 
  Rudder 
   Measured parallel to  
   O.O.W.L. Inboard 15° + 0°, -2° Outboard 22° + 2° 
 
   Measured perpendicularly 
   to hinge line Inboard 17° + 0°, -2° Outboard 25° + 2° 
 
 Serial Nos. Eligible Model F337E: F3370001 thru F3370024 
 
II. Model FT337E, 4 - 6 PCLM (Normal Category), Approved February 23, 1970 
 Model FT337F, 4 - 6 PCLM (Normal Category), Approved January 4, 1971 
 
 Engines (Front) Continental TSIO-360-A 
  (Rear)  Continental TSIO-360-A 
 
* Fuel 100/130 minimum grade aviation gasoline 
 
* Engine Limits For all operations, 2800 rpm (210 b.hp.) 32 in. Hg MP 
  (Critical altitude to 20,000 ft. in standard atmosphere) 
 
 Propeller and 1. McCauley constant speed full-feathering propeller installation 
   Propeller Limits  a. (Front) McCauley D2AF34C91/76C-0 
    Diameter:  not over 76 in., not under 74.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  12.7°  low, 79.0° feathered.   
 
   b. (Rear) McCauley D2AF34C61/L76C 
    Diameter:  not over 76 in., not under 74.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  11.8°  low, 79.0° feathered. 
 
   c. (Front) McCauley D2AF34C304/76CTA-0 
    Diameter:  not over 76 in., not under 75 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  12.7°  low, 79.0° feathered. 
 
   d. (Rear) McCauley D2AF34C302/L76CTA-0 
    Diameter:  not over 76 in., not under 75 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  11.8°  low, 79.0° feathered. 
 
   e. (Front) Woodward hydraulic governor 210443 
 
   f. (Rear) Woodward hydraulic governor 210443 
 
   g. (Front) McCauley hydraulic governor CF310D1-T1 or CF 310 D2/T1 
 
   h. (Rear) McCauley hydraulic governor CF310D1-T1 or CF 310 D2/T1 
 
   j. (Front) Cessna spinner 1557303 (includes support and bulkhead assembly) 
 
   k. (Rear) Cessna spinner 1457306 (includes support and bulkhead assembly).

Rev. 8  Page 4 of 24 A23EU 
II. Models FT337E, FT337F (cont'd) 
 
* Airspeed Limits Never exceed 228 mph.  (198 knots) 
   (CAS) Maximum structural cruising 190 mph.  (165 knots) 
  Flaps extended 120 mph.  (104 knots) 
  Maneuvering 155 mph.  (135 knots) 
  Landing gear extension 160 mph.  (139 knots) 
 
 C.G. Range (+134.5) to (+142.0) at 3837 lb. or less. 
   (landing gear extended) (+138.3) to (+142.0) at 4630 lb.  
  Straight line variation between points given. 
  Landing gear retraction moment is +3318 in.-lb. 
 
 Empty Weight C.G. Range None 
 
* Maximum Weight 4630 lb. takeoff and flight 
  4400 lb. landing 
 
 Number of Seats 4 - 6 (2 at +98.0 to +109.0); (2 at +133.0 to +142.0); 
   1 or 2 at +162.0 to +168.0) 
 
 Maximum Baggage 365 lb. (reference weight and balance for additional information) 
 
 Fuel Capacity 92.8 gal. (92 gal. usable) (2 tanks 46.4 gal. ea. at +150) 
  See NOTE 1 for data on undrainable fuel 
 
 Oil Capacity 11 qt. - front (+43.0) (7 qt. usable) (See NOTE 6) 
  11 qt. - rear (+207.5) (7 qt. usable) 
  See NOTE 1 for data on undrainable oil. 
 
 Control Surface Movements Wing Flaps 
   Inboard   Down 25° +1°, -2° 
   Outboard   Down 25° +1°, -2° 
  Ailerons  Up 21° + 2° Down 14° 30' + 2° 
  Elevator  Up 26° + 1° Down 15°+ 1° 
  Elevator tab Up 15° + 1° Down 15° + 1° 
  Rudder 
   Measured parallel to  
   O.O.W.L. Inboard 15° + 0°, -2° Outboard 22° + 2° 
   Measured perpendicular 
   to hinge line Inboard 17° + 0°, -2° Outboard 25° + 2°  
 
 Serial Nos. Eligible Model FT337E:  F3370001 through F3370024 
  Model FT337F:  F3370025 through F3370055 
 
III. Model F337F, 4 - 6 PCLM (Normal Category), Approved January 4, 1971 
 
 Engines (Front) Continental IO-360-C 
  (Rear)  Continental IO-360-C 
 
* Fuel 100/130 minimum grade aviation gasoline (See NOTE 5) 
 
* Engine Limits For all operations, 2800 r.p.m. (210 b.hp.)

Rev. 8  Page 5 of 24 A23EU 
III. Model F337F (cont'd) 
 
 Propeller and 1. McCauley constant speed full-feathering propeller installation 
   Propeller Limits  a. (Front) McCauley D2AF34C59/76C 
    Diameter:  not over 76 in., not under 74.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  11.7°  low, 79.0° feathered. 
 
   b. (Rear) McCauley D2AF34C61/L76C 
    Diameter:  not over 76 in., not under 74.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  10.8°  low, 79.0° feathered. 
 
   c. (Front) McCauley D2AF34C301/76CTA-0 
    Diameter:  not over 76 in., not under 75 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  11.7°  low, 79.0° feathered. 
 
   d. (Rear) McCauley D2AF34C302/L76CTA-0 
    Diameter:  not over 76 in., not under 75 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  10.8°  low, 79.0° feathered. 
 
   e. (Front) McCauley D2AF34C306/78 CAA-0 
    Diameter:  not over 78 in., not under 76.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  11°  low, 82° feathered. 
 
   f. (Rear) McCauley D2AF34C307/L78CBA-2 
    Diameter:  not over 76 in., not under 74.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  11°  low, 80° feathered. 
 
   g. (Front) Woodward hydraulic governor 210443 
 
   h. (Rear) Woodward hydraulic governor 210443 
 
   j. (Front) McCauley hydraulic governor CF310D1-T1  
 
   k. (Rear) McCauley hydraulic governor CF310D1-T1   
 
   l. (Front) Cessna spinner 557303 (includes support and bulkhead assembly) 
 
   m. (Rear) Cessna spinner 1457306 (includes support and bulkhead assembly) 
 
* Airspeed Limits Never exceed  228 mph  (198 knots) 
   (CAS) Maximum structural cruising  190 mph  (165 knots) 
  Flaps extended  120 mph  (104 knots) 
  Maneuvering  155 mph  (135 knots) 
  Landing gear extension  160 mph  (139 knots) 
 
 C.G. Range (+140.0) to (+143.0) at 4630 lb. 
   (landing gear extended) (+137.3) to (+143.0) at 4400 lb. 
  (+134.5) to (+143.0) at 3837 lb. or less. 
  Straight line variation between points given. 
  Landing gear retraction moment is +3318 in.-lb.

Rev. 8  Page 6 of 24 A23EU 
III. Model F337F (cont'd) 
 
 Empty Weight C.G. Range None 
 
* Maximum Weight 4630 lb. takeoff and flight: 4400 lb. landing 
 
 Number of Seats 4-6 (2 at +98.0 to +109.0); (2 at +133.0 to +142.0); 
   (1 or 2 at +162.0 to +168.0) 
 
 Maximum Baggage 365 lb. (reference weight and balance for additional information) 
 
 Fuel Capacity 92.8 gal. (92 gal. usable) (2 tanks 46.4 gal. ea. at +150) 
  See NOTE 1 for data on unusable fuel 
 
 Oil Capacity 10 qt. - front (+43.0) (7 qt. usable) (See NOTE 6) 
  10 qt. - rear (+207.5) (7 qt. usable) 
  See NOTE 1 for data on undrainable oil. 
 
 Control Surface Movements Wing Flaps 
   Inboard   Down 25° +1°, -2° 
   Outboard   Down 25° +1°, -2° 
  Ailerons  Up 21° + 2° Down 14° 30' + 2° 
  Elevator  Up 26° + 1° Down 15° + 1° 
  Elevator tab Up 15° + 1° Down 15° + 1° 
  Rudder 
   Measured parallel to  
   O.O.W.L. Inboard 15° + 0°, -2° Outboard 22° + 2° 
 
  Measured perpendicularly 
   to hinge line Inboard 17° + 0°, -2° Outboard 25° + 2° 
 
 Serial Nos. Eligible Model F337F: F3370025 thru F3370045 (1971 Model) 
    F3370046 thru F3370055 (1972 Model) 
 
IV. Model F337G, 4 - 6 PCLM (Normal Category), Approved April 5, 1973 
 
 Engine (Front) Continental IO-360-G 
  (Rear)  Continental IO-360-G 
 
* Fuel 100/130 minimum grade aviation gasoline (See NOTE 5) 
 
* Engine Limits For all operations, 2800 rpm (210 b.hp.) 
 
 Propeller and 1.  McCauley constant speed, full-feathering propeller installations 
   Propeller Limits  a. S/NF3370056 thru F3370080 
    (Front) McCauley D2AF34C306/78 CAA-0 
    Diameter:  not over 78 in., not under 76.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  11°  low, 82° feathered. 
 
   b. S/N F3370080 and on 
    (Front) McCauley D2AF34C310/90DEA-12 
    Diameter:  not over 78.0 in., not under 76.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  9.9°  low, 82.0° feathered. 
 
   c. (Rear) McCauley D2AF34C307/L78 CBA-2 
    Diameter:  not over 76.0 in., not under 74.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  11°  low, 80° feathered.

Rev. 8  Page 7 of 24 A23EU 
IV. Model F337G (cont'd) 
   d. (Front) McCauley hydraulic governor CF310 D1/T1 or CF310 D2/T1 
 
   e. (Rear) McCauley hydraulic governor CF310 D1/T1 or CF310 D2/T1 
 
   f. (Front) Cessna spinner 1557303 (includes support and bulkhead assembly) 
 
   g. (Rear) Cessna spinner 1457306 (includes support and bulkhead assembly). 
 
* Airspeed Limits S/N F3370056 thru F3370076 
   (CAS) 
  Never exceed  228 m.p.h.  (198 knots) 
  Maximum structural cruising  190 m.p.h.  (165 knots) 
  Flaps extended  125 m.p.h.  (108 knots) 
  Maneuvering  155 m.p.h.  (135 knots) 
  Landing gear extension  160 m.p.h.  (139 knots) 
 
 Airspeed Limits S/N F3370077 and on 
   (IAS) (See NOTE 7) 
  Never exceed  200 KIAS 
  Maximum structural cruising  168 KIAS 
  Flaps extended  110 KIAS 
  Maneuvering  137 KIAS 
  Landing gear extension  140 KIAS 
 
 C.G. Range (+140.0) to (+143.0) at 4630 lb. 
   (landing gear extended) (+137.3) to (+143.0) at 4400 lb. 
    (+134.5) to (+143.0) at 3837 lb. or less. 
  Straight line variation between points given. 
  Landing gear retraction moment is +3318 in.-lb. 
 
 Empty Weight C.G. Range None 
 
* Maximum Weight 4630 lb. takeoff and flight: 4400 lb. landing 
 
 Number of Seats 4-6 (2 at +98.0 to +109.0); (2 at +140.0); 
   (1 or 2 at +170.0) 
 
 Maximum Baggage 365 lb. (See weight and balance for landing instructions) 
  Maximum baggage with restraining net - 160 lb. 
 
 Fuel Capacity S/N F3370056 thru F3370076 
  92.8 gal. (92 gal. usable) (2 tanks 46.4 gal. ea. at +150.0) 
  See NOTE 1 for data on unusable fuel. 
 
  S/N F3370077 and on: 
  90.6 gal. (88 gal. usable) (2 tanks 45.3 gal. ea. at +149.0) 
  See NOTE 1 for data on unusable fuel. 
 
 Oil Capacity S/N F3370056 thru F3370063: 
  10 qt. - Front (+43.0) (7 qt. usable)  
  10 qt. - Rear (+207.5) (7 qt. usable) 
  See NOTE 1 for data on undrainable oil. 
 
  S/N F3370064 and on: 
  8 qt.-Front (+43.0) (5 qt. usable) 
  8 qt.-Rear  (+207.5) (5 qt. usable) 
  See NOTE 1 for data on undrainable oil.

Rev. 8  Page 8 of 24 A23EU 
IV. Model F337G (cont'd) 
 
 Control Surface Movements Wing Flaps 
   Inboard   Down 25° +1°, -2° 
   Outboard   Down 25° +1°, -2° 
  Ailerons  Up 21° + 2° Down 14° 30' + 2° 
  Elevator  Up 26° + 1° Down 15°+ 1° 
  Elevator tab Up 15° + 1° Down 15° + 1° 
  Rudder 
   Measured parallel to  
   O.O.W.L. Inboard 15° + 0°, -2° Outboard 22° + 2° 
  Measured perpendicularly 
   to hinge line Inboard 17° + 0°, -2° Outboard 25° + 2° 
 
 Serial Nos. Eligible 1973 Model:  F3370056 thru F3370063 
  1974 Model:  F3370064 thru F3370071 
  1975 Model:  F3370072 thru F3370076 
  1976 Model:  F3370077 thru F3370079 
  1977 Model:  F3370080 thru F3370084 
 
V. Model FT337GP, 4 - 5 PCLM (Normal Category), Approved May 22, 1973 
 
 Engine (Front) Continental TSIO-360-C 
  (Rear)  Continental TSIO-360-C 
 
* Fuel 100/130 minimum grade aviation gasoline (See NOTE 5) 
 
* Engine Limits For all operations, 2800 rpm. (225 b.hp.) 37 in. Hg.MP 
 
 Propeller and 1. McCauley constant speed, full feathering propeller installation 
   Propeller Limits  a. S/N FP33700001 through FP33700017 
    (Front) McCauley D2AF34C303/78CAA-0 
    Diameter:  not over 78 in., not under 76 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  12.5° low, 82.0 feathered. 
 
   b. S/N FP33700018 and up 
    (Front) McCauley D2AF34 C308/90 DEA-12 
    Diameter:  not over 78.0 in., not under 76.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  11.3° low, 82.3° feathered. 
 
   c. (Rear) McCauley D2AF34C305/L78CBA-2 
    Diameter:  not over 76 in., not under 74 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  12.5° low, 80.0° feathered. 
 
   d. S/N FP33700001 thru FP33700008 
    (Front) McCauley hydraulic governor CF310 D1/T1 or CF310 D2/T1 
 
    S/N FP33700009 thru FP33700017 
    (Front) McCauley hydraulic governor CFS310 D3/T1 
 
    S/N FP33700018 and on 
    (Front) McCauley hydraulic governor DCFS310 D4/T5

Rev. 8  Page 9 of 24 A23EU 
V. Model FT337GP  (cont'd) 
 
   e. S/N FP33700001 thru FP33700008 
    (Rear) McCauley hydraulic governor CF310D1/T1 or CF310D2/T1 
 
    S/N FP33700009 thru FP33700022 
    (Rear) McCauley hydraulic governor DCFS310 D3/T1 
 
    S/N FP33700023 and on 
    (Rear) McCauley hydraulic governor DCFS 310 D8/T1 
 
   f. (Front) Cessna spinner 1557303 (includes support and bulkhead assembly) 
 
   g. (Rear) Cessna spinner 1457306 (includes support and bulkhead assembly) 
 
* Airspeed Limits S/N FP33700001 through FP33700015 
 (CAS)  
  Never exceed  230 mph.  (200 knots) 
  Maximum structural cruising  190 mph.  (165 knots) 
  Flaps extended  125 mph.  (108 knots) 
  Maneuvering  155 mph.  (135 knots) 
  Landing gear extension  160 mph.  (139 knots) 
 
 Airspeed Limits (IAS) S/N FP33700016 and up 
 (See NOTE 7 on use of IAS) 
  Never exceed  205 KIAS 
  Maximum structural cruising  169 KIAS 
  Flaps extended  110 KIAS 
  Maneuvering  139 KIAS 
  Landing gear extension  140 KIAS 
 
 C.G. Range S/N FP33700001 thru FP33700015 
   (landing gear extended) 
  (+138.6) to (+142.0) at 4700 lb. 
    (+134.5) to (+142.0) at 3837 lb. or less. 
  Straight line variation between points given. 
  Landing gear retraction moment is +3318 in.-lb. 
 
  S/N FP33700016 and on 
 
  (+137.7) to (+142.0) at 4700 lb. 
  (+134.5) to (+142.0) at 3837 lb. or less 
  Straight line variation between points given. 
  Landing gear retraction moment is 3318 in. lb. 
 
 Empty Weight C.G. Range None 
 
 Maximum Weight 4700 lb. takeoff and flight: 4465 lb. landing 
 
 Number of Seats S/N FP33700001 thru FP33700015 
  4-5 (2 at +98.0 to +109.0); (2 at +140.0); 
   (1 optional at +170.0) 
 
  S/N FP33700016 thru FP337000022 
  4-5  (2 at +98.0 to +109.0); (2 at +140.0 to +158.0);  
   (1 optional at +170.0) 
 
 Maximum Baggage 365 lb. (reference weight and balance for additional information)

Rev. 8  Page 10 of 24 A23EU 
V. Model FT337GP  (cont'd) 
 
 Fuel Capacity S/N FP33700001 thru FP33700013 
  125 gal. (123 gal. usable) (2 tanks 62.5 gal. ea. at +150.0) 
  See NOTE 1 for data on unusable fuel 
 
  S/N FP33700014 and on 
  150.6 gal. (148 gal. usable) (2 tanks, 75.3 gal. ea. at +150.0) 
  See NOTE 1 for data on unusable fuel 
 
 Oil Capacity S/N FP33700001 thru FP33700008 
  11 qt. - front (+44.5) (7 qt. usable) (See NOTE 6) 
  11 qt. - rear (+205.9) (7 qt. usable) (See NOTE 6) 
  See NOTE 1 for data on undrainable oil. 
 
  S/N FP33700009 and on 
  9 qt. Front (+44.5) (5 qt. usable) 
  9 qt. Rear (+205.9) (5 qt. usable) 
  See NOTE 1 for data on undrainable oil 
 
 Control Surface Movements Wing Flaps 
   Inboard   Down 25° +1°, -2° 
   Outboard   Down  25° +1°, -2° 
  Ailerons  Up 21° + 2° Down 14° 30' + 2° 
  Elevator  Up 26° + 1° Down 15°+ 1° 
  Elevator tab Up 15° + 1° Down 15° + 1° 
  Rudder 
   Measured parallel to  
   O.O.W.L. Inboard 15° + 0°, -2° Outboard 22° + 2° 
 
  Measured perpendicularly 
   to hinge line Inboard  17° + 0°, -2° Outboard 25° + 2° 
 
 Serial Nos. eligible 1973 FT337GP Model:  FP33700001 thru FP33700008 
  1974 FT337GP Model:  FP33700009 thru FP33700013 
  1975 FT337GP Model:  FP33700014 thru FP33700015 
  1976 FT337GP Model:  FP33700016 thru FP33700017 
  1977 FT337GP Model:  FP33700018 thru FP33700022 
 
VI. Model F337H, 4-6 PCLM (Normal Category), Approved March 2, 1978 
 
 Engine (Front) Continental IO-360-G 
  (Rear)  Continental IO-360-G 
 
* Fuel 100LL/100 minimum grade aviation gasoline 
  See NOTE 5 
 
* Engine Limits For all operations, 2800 rpm (210 b.hp.) 
 
 Propeller and 1. McCauley constant speed full-feathering propeller installations 
   Propeller Limits  a. (Front) McCauley D2AF34C310/90DEA-12 
    Diameter:  not over 78.0 in., not under 76.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station: 
    9.9°  low, 82.0° feathered. 
 
   b. (Rear) McCauley D2AF34C307/L78CBA-2 
    Diameter:  not over 76 in., not under 74.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station: 
    11.0°  low, 80.0° feathered.

Rev. 8  Page 11 of 24 A23EU 
VI. Model F337H (cont'd) 
   c. (Front) McCauley hydraulic governor DCF310D7/T1 
 
   d. (Rear) McCauley hydraulic governor DCF310D7/T1 
 
   e. (Front) Cessna spinner 1557303 (includes support and bulkhead assembly) 
 
   f. (Rear) Cessna spinner 1457306 (includes support and bulkhead assembly). 
 
* Airspeed Limits (IAS) Never exceed  200 KIAS 
 (See NOTE 7 on use of IAS) Maximum structural cruising  168 KIAS 
  Flaps extended  110 KIAS 
  Maneuvering  137 KIAS 
  Landing gear extension  200 KIAS 
  Landing gear operating speed  140 KIAS 
 
 C.G. Range (+140.0) to (+143.0) at 4630 lb. 
   (landing gear extended) (+137.3) to (+143.0) at 4400 lb. 
  (+134.5) to (+143.0) at 3837 lb. or less. 
  Straight line variation between points given. 
  Landing gear retraction moment is +3318 in.-lb. 
 
 Empty Weight C.G. Range None 
 
* Maximum Weights 4630 lb. takeoff and flight 
  4400 lb. landing 
 
 Number of Seats 4-6 (2 at +98.0 to +109.0); (2 at +135.0 to +141.0); 
   (1 or 2 at +161.0 to +167.0) 
 
 Maximum Baggage 365 lb. (See weight and balance for loading instructions) 
  Maximum baggage with restraining net - 160 lb. 
 
 Fuel Capacity 90.6 gal. (88 gal. usable) (2 tanks 45.3 gal. ea. at +149.0) 
  See NOTE 1 for data on unusable fuel 
 
 Oil Capacity 8 qt. - front (+43.0) (5 qt. usable) 
  8 qt. - rear (+207.5) (5 qt. usable) 
 
 Control Surface Movements Wing Flaps 
   Inboard   Down 25° +1°, -2° 
   Outboard   Down 25° +1°, -2° 
  Ailerons  Up 21° + 2° Down 14° 30' + 2° 
  Elevator  Up 26° + 1° Down 15°+ 1° 
  Elevator tab Up 15° + 1° Down 15° + 1° 
  Rudder          
   Measured parallel to  
   O.O.W.L. Inboard 15° + 0°, -2° Outboard 22° + 2° 
 
   Measured perpendicularly 
   to hinge line Inboard 17° + 0°, -2° Outboard 25° + 2° 
 
 Serial Nos. Eligible 1978 Model:  F3370085 through F3370086

Rev. 8  Page 12 of 24 A23EU 
VII. Model FT337HP, 4-5 PCLM (Normal Category), Approved March 2, 1978 
 
 Engine (Front) Continental TSIO-360-C 
  (Rear)  Continental TSIO-360-C 
 
* Fuel 100LL/100 minimum grade aviation gasoline 
  See NOTE 5 
 
*  Engine Limits For all operations, 2800 rpm (225 b.hp.) 37 in. Hg. MP 
 
  Propeller and 1. McCauley constant speed full feathering propeller installation 
    Propeller Limits  a. (Front) McCauley D2AF34C308/90DEA-12 
    Diameter:  not over 78.0 in., not under 76.5 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  11.3°  low, 82.3° feathered. 
 
   b. (Rear) McCauley D2AF34C305/L78CBA-2 
    Diameter:  not over 76.0 in., not under 74.0 in. 
    No further reduction permitted 
    Pitch setting at 30 in. station:  12.5°  low, 80.0° feathered. 
 
   c. (Front) McCauley hydraulic governor DCFS310D7/T5 
 
   d. (Rear) McCauley hydraulic governor DCFS310D8/T1 
 
   e. (Front) Cessna spinner 1557303 (includes support and bulkhead assembly) 
 
   f. (Rear) Cessna spinner 1457306 (includes support and bulkhead assembly). 
 
*  Airspeed Limits (IAS) Never exceed  205 KIAS 
  (See NOTE 7 on use of IAS) Maximum structural cruising  169 KIAS 
  Flaps extended  110 KIAS 
  Maneuvering  139 KIAS 
  Landing gear extended  205 KIAS 
  Landing gear operating speed  140 KIAS 
 
  C.G. Range (+137.7) to (+142.0) at 4700 lb. 
    (landing gear extended) (+134.5) To (+142.0) at 3837 lb. or less. 
  Straight line variation between points given. 
  Landing gear retraction moment is +3318 in.-lb. 
 
  Empty Weight C.G. Range None 
 
*  Maximum Weight 4700 lb. takeoff and flight:  
  4465 lb. landing 
 
  Number of Seats 4-5 (2 at +98.0 to +109.0); (2 at +140.0 to +158.0); 
   (1 optional at +170) 
 
  Maximum Baggage 365 lb. (reference weight and balance for additional information) 
 
  Fuel Capacity 150.6 gal. (148 gal. usable) (2 tanks 75.3 gal. ea. at +150.0) 
  See NOTE 1 for data on unusable fuel 
 
  Oil Capacity 9 qt. - front (+44.5) (5 qt. usable)  
  9 qt. - rear (+205.9) (5 qt. usable) 
  See NOTE 1 for data on undrainable oil.

Rev. 8  Page 13 of 24 A23EU 
VII. Model FT337HP  (cont'd) 
 
 Control Surface Movements Wing Flaps 
   Inboard   Down 25° +1°, -2° 
   Outboard   Down 25° +1°, -2° 
  Ailerons  Up 21° + 2° Down 14° 30' + 2° 
  Elevator  Up 26° + 1° Down 15°+ 1° 
  Elevator tab Up 15° + 1° Down 15° + 1° 
  Rudder 
   Measured parallel to  
   O.O.W.L. Inboard  15° + 0°, -2° Outboard 22° + 2° 
  Measured perpendicularly 
   to hinge line Inboard 17° + 0°, -2° Outboard 25° + 2° 
 
 Serial Nos. Eligible 1978 Model:  FP3370023  
 
DATA PERTINENT TO ALL MODELS 
 
 Datum 65.0 in. forward of front face of firewall 
 
 Leveling Means Two jig located nutplates and screws installed on left side of fuselage immediately below  
  pilot's window. 
 
 Certification Basis Models F337E, FT337E, F337F, FT337F, F337G, FT337GP, F337H and FT337HP 
  Part 23 of the Federal Aviation Regulations dated February 1, 1965, as amended by 23-1  
   through 23-6. 
  Type Certificate No. A23EU, issued February 23, 1970 
  Date of Application for Type Certificate:  February 19, 1970. 
  Equivalent Safety Items S/N FP3370016 and on 
     S/N F3370077 and on 
  Airspeed Indicator FAR 23.1545 (See NOTE 7 on use of IAS) 
  Operation Limitations FAR 23.1583(a)(1) 
 
 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations  
  (see Certification Basis) must be installed in the aircraft for certification.  In addition, the  
  following items of equipment are required: 
 
  Stall Warning Indicator, Cessna Dwg. 0511062 
 
NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and 
loading instructions when necessary, must be provided for each aircraft at the time of original certification.  
The certificated empty weight and corresponding center of gravity locations must include the following: 
 
   Unusable Fuel 
  Serial Numbers   Weight (lb) Arm 
  F3370001 through F3370076     5 +159.5 
  F3370077 and up    15 +159.0 
  FP3370001 through FP3370013   12 +157.8 
  FP3370014 and up    15 +159.0 
 
   Undrainable Oil 
  Serial Numbers   Weight  Arm 
  F3370001 through F3370076   0.0 +125.5 
  FP3370001 through FP3370015 
 
   Full Oil 
  Serial Numbers   Weight  Arm 
  F3370077 and up  30.0 (Std. F337) 
    33.8 (FT337) +125.5 
  F3370016 and up  33.8 +125.5

Rev. 8  Page 14 of 24 A23EU 
DATA PERTINENT TO ALL MODELS 
 
NOTE 2. The following placards must be displayed as indicated: 
 
  A. Applicable to Model F337E and FT337E 
 
   1) In full view of the pilot: 
 
    "This airplane must be operated as a Normal Category Airplane in compliance with the  
    operating limitations as stated in the form of placards, markings and manuals. 
 
    Maximums 
    Maneuvering speed  55 mph. - CAS. 
    Design weight:  (F337E only) Takeoff 4440 lb.; Landing 4400 lb. 
    Design weight: (FT337E only) Takeoff 4630 lb.; Landing 4400 lb. 
    Flight maneuvering load factors: Flaps Up   +3.8   -1.52 
       Flaps Down  +2.0. 
    Altitude loss in stall recovery  300 feet. (F337E only) 
    Altitude loss in stall recovery  400 feet. (FT337E only) 
    Flap extension speed: 1/3 - 160 mph CAS 
       1/3 to full down flap - 120 mph CAS. 
 
    No acrobatic maneuvers, including spins approved. 
    Gear extension speed:  160 mph CAS. 
    Airplane is controllable in 20-knot cross wind. 
    Known icing conditions to be avoided".  (If applicable) 
    This airplane is certificated for the following flight operations as of date of original airworthiness  
    certificate: 
 
VFR - IFR - DAY - NIGHT".  (As applicable) 
 
   2) On the control lock:  "Control lock - remove before starting engines". 
 
   3) On the baggage door: "Maximum capacity 365 lb.  For additional loading instructions 
        see weight and balance data". 
 
   4) On the fuel selector cover: 
    "Front engine     Rear engine 
    Off     Off 
    Left Main 46.0 gal.   Left Main 46.0 gal. 
    Right Main 46.0 Gal.   Right Main 46.0 gal. 
 
   5) Near fuel selector: 
    "Takeoff and Landing - 
    Front engine  - Left Main 
     Rear engine   - Right Main" 
 
   6) Near propeller control:  "To feather propeller, lift propeller control up and pull back." 
 
   7) On upper portion of quadrant cover:  "With inoperative engine, feather propeller." 
 
   8) Adjacent to the fuel filler caps:  "Tank capacity 46.4 U.S. gallons, 100/130 minimum grade." 
 
   9) On the gear emergency pump cover:  
     "To extend gear manually, place gear handle in full down position, pull emergency handle out and  
    pump vertically."

Rev. 8  Page 15 of 24 A23EU 
DATA PERTINENT TO AL MODELS 
 
NOTE 2. (cont’d) 
   10) The following check list shall be placed in the map compartment: 
 
     "BEFORE TAKEOFF   BEFORE LANDING 
    1. Set trim controls 1. Gear down 
    2. Fuel selector main tanks 2. Fuel selector main tanks 
    3. Cowl flaps open 3. Cowl flaps closed 
    4. Mixtures rich  4. Mixtures rich 
    5. Propellers forward 5. Propellers forward 
    6. Flaps 0 - 1/3  6. Flaps down". 
 
   11) The following placard must be installed near the manifold pressure instrument :  
    (applicable to Model FT337E only) 
    
Altitude in Feet 
Sea Level to 
Manifold 
Pressure 
In. Hg. 
 
Fuel Flow 
Gal/Hr. 
20,000 32 21 
22,000 30 19 
24,000 28 17 
26,000 26 15 
28,000 24 13 
30,000 22 11 
 
  Normal Power Climb - 2600 rpm. - 28 manifold pressure - 14.5 gph" 
 
  B. Applicable to Models F337F and FT337F 
 
   1) In full view of the pilot: 
 
    (a) "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." 
 
    (b) "No acrobatic maneuvers, including spins approved". 
 
    (c) "Maximum maneuvering speed 155 m.p.h. - CAS". 
 
    (d) "Maximum design weight:  Takeoff 4630 lb.; Landing 4400 lb." 
 
    (e) "Maximum flight maneuvering load factors:  Flaps Up    +3.8   -1.52 
          Flaps Down  +2.0" 
 
    (f) "Maximum altitude loss in stall recovery 400 feet". 
 
    (g) "Maximum flap extension speed: 1/3 - 160 mph. CAS 
          1/3 to full down flap - 120 mph. CAS". 
 
    (h) "Gear extension speed:  160 mph. CAS". 
 
    (i) "Airplane is controllable in 20-knot cross wind". 
 
    (j) "Known icing conditions to be avoided".  (If applicable) 
 
    (k) "This airplane is certificated for the following flight operations as of date of original 
     airworthiness certificate: 
   
 (DAY NIGHT VFR IFR) (As applicable)” 
 
   2) On the control lock:  "Control lock - remove before starting engines".

Rev. 8  Page 16 of 24 A23EU 
DATA PERTINENT TO ALL MODELS 
 
NOTE 2. (cont’d) 
   3) On the baggage door:  "Maximum capacity 365 lb.  For additional loading instructions 
    see weight and balance data". 
 
   4) On the fuel selector cover: 
    “Front engine     Rear engine 
    Off      Off 
    Left Main     46.0 gal.  Left Main     46.0 gal. 
    Right Main   46.0 gal.  Right Main   46.0 gal.” 
 
   5) Near fuel selector: 
    (a) "Takeoff and landing -  Front engine  - Left Main 
           Rear engine   - Right Main" 
 
    (b) "When switching from dry tank turn pump on "HI" momentarily". 
 
   6) Near propeller control:  "To feather propeller, lift propeller control up and pull back". 
 
   7) On upper portion of quadrant cover:  "With inoperative engine, feather propeller". 
 
   8) Adjacent to the fuel filler caps:   "Tank capacity 46.4 U.S. gallons, 
          100/130 minimum grade." 
 
   9) On the gear emergency pump cover:  
    "To extend gear manually, place gear handle in full down position, pull emergency handle out  
    and pump vertically". 
 
   10) The following check list shall be placed in the map compartment: 
 
    "BEFORE TAKEOFF   BEFORE LANDING 
    1. Set trim controls 1. Gear down 
    2. Fuel selector main tanks 2. Fuel selector main tanks 
    3. Cowl flaps open 3. Cowl flaps closed 
    4. Mixtures rich  4. Mixtures rich 
    5. Propellers forward 5. Propellers forward 
    6. Flaps 0 - 1/3  6. Flaps down". 
 
   11) The following placards must be installed near the fuel flow indicators: 
 
    Model F337F 
    "Maximum Power Mixture Settings 
     S.L.   102 lb./hr. 
     4,000 ft.    90 lb./hr. 
     8,000 ft.    78 lb./hr. 
      12,000 ft.    66 lb./hr. 
 
    Model FT337F: 
    "Maximum allowable to manifold pressure and climb fuel flow 
    
 
Altitude in Feet 
Sea Level to 
Manifold 
Pressure 
In. Hg. 
 
Fuel Flow 
lb./hr. 
20,000 32 126 
22,000 30 114 
24,000 28 102 
26,000 26 90 
28,000 24 78 
30,000 22 66 
 
    Normal Power Climb - 2600 r.p.m. - 28 manifold pressure - 87 lb/hr."

Rev. 8  Page 17 of 24 A23EU 
DATA PERTINENT TO ALL MODELS 
 
NOTE 2. (cont’d) 
 
   12) On the left side of the pedestal adjacent to the alternate static source valve when installed: 
    "Alternate Static Source Correction 
    Airspeed:  Fly 3 mph. faster than normal 
    Altitude:  Cruise - Fly 270 feet higher than normal 
       Approach - Fly 100 feet higher than normal". 
 
   13) Below instrument cluster and adjacent to the tachometer: 
    "TAXI & TAKEOFF 
    Lead with rear engine power 
    Check rpm. and fuel flow". 
 
  C. Applicable to Model F337H 
 
   1) In full view of the pilot: 
 
    (a) "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."  
 
    (b) "No acrobatic maneuvers, including spins approved." 
 
    (c) "Maximum Gross Weight: Takeoff 4630 lb. 
          Landing 4400 lb. 
 
    (d) "Maximum flight maneuvering load factors: Flaps Up +3.8   -1.52 
           Flaps Down +2.0" 
 
    (e) "Flight into known icing conditions prohibited." 
 
    (f) "Maximum altitude loss in stall recovery - 400 feet." 
 
    (g) "This airplane is certificated for the following flight operations as of date of original  
     airworthiness certificate: 
 
 (DAY NIGHT VFR IFR) (As applicable)” 
 
   2) Located near the Airspeed Indicator: 
    (a) Model F337G 
     S/N F3370056 thru F3370076 
      "Maximum Speeds      CAS 
      Gear Operation 160 mph 
      Gear Extended  228 mph 
      Maneuvering  155 mph" 
 
    (b) Model F337G/ F337H 
     S/N F3370077 and on 
      "Maximum Speeds        IAS 
      Gear Operation 140 knots 
      Gear Extended  200 knots 
      Maneuvering  137 knots" 
 
   3) On the control lock:  "Control lock - remove before starting engines." 
 
   4) On the rear firewall in the baggage area:  "Maximum capacity 365 lb., Maximum  
    baggage with restraining net 160 lb.  For additional loading instruction see weight  
    and balance data."

Rev. 8  Page 18 of 24 A23EU 
DATA PERTINENT TO ALL MODELS 
 
NOTE 2. (cont’d) 
   5) On the fuel selector covers: 
 
S/N F3370056 thru F3370076 S/N F3370077 and on 
Fuel Off 
Rear Engine 
 Fuel Off 
Rear Engine 
Left On Right On  Left On Right On 
     
276 lb. 276 lb.  240 lb. 266 lb. 
  46 gal.   46 gal.    40 gal.   44 gal. 
  Takeoff and landing - Right Tank Takeoff and landing - Right Tank 
  When switching from dry tank - When switching from dry tank - 
  turn pump on 'HI' momentarily. turn pump on 'HI' momentarily. 
 
Fuel Off 
Front Engine 
 Fuel Off 
Front Engine 
Left On Right On  Left On Right On 
     
276 lb. 276 lb.  264 lb. 240 lb. 
  46 gal.   46 gal.    44 gal.   40 gal. 
  Takeoff and landing - Left Tank Takeoff and landing - Left Tank 
 
   6) Near propeller control:   
    "To feather propeller, lift propeller control up and pull back." 
 
   7) On upper portion of quadrant cover:  "With inoperative engine, feather propeller." 
 
   8) Adjacent to the fuel filler caps:   
    S/N F3370056 thru F3370076 
    "Tank capacity 46.4 U.S. Gallons, 100/130 minimum grade". 
 
    S/N F3370057 thru F3370084 
    "Tank capacity 45.3 U.S. Gallons, 100/130 minimum grade" 
 
    S/N F3370085 and on 
    "Tank capacity 45.3 U.S. Gallons, 100LL/100 minimum grade" 
 
   9) On the inside of the fuel cap covers:  "To ensure complete filling of tanks: 
    (1) Fill slowly 
    (2) Retop after filling opposite wing" 
 
    10) Near the landing gear emergency hydraulic hand pump: 
    (a) S/N F3370056 thru F3370084 
     "Manual Gear Extension 
     (1) Select gear down 
     (2) Pull handle forward 
     (3) Pump vertically" 
 
    (b) S/N F3370085 and on 
     "Manual Gear Extension 
     (1) Select gear down 
     (2) Pull handle forward 
     (3) Pump vertically 
     Caution:  Do not pump with gear up selected"

Rev. 8  Page 19 of 24 A23EU 
DATA PERTINENT TO ALL MODELS 
 
NOTE 2. (cont’d) 
   11) Located beneath engine instrument cluster: 
    "Taxi and Takeoff 
    Lead with rear engine power 
    Check RPM and fuel flow" 
 
    12) Located near wing flap indicator: 
    (a) S/N F3370056 thru F3370076 
     "Maximum flap extension speeds: 
      1/3 160 mph CAS 
      1/3 - 2/3 140 mph CAS 
      2/3 - full 125 mph CAS" 
 
    (b) S/N F3370077 and on: 
     "Maximum flap extension speeds: 
      1/3 165 KIAS 
      1/3 - 2/3 135 KIAS 
      2/3 - full 110 KIAS" 
 
  13) Pilot's checklist: 
    (a) S/N F3370056 thru F3370071 
     A separate checklist as described by Cessna Dwg. 1400019 is installed in the map 
     compartment. 
 
    (b) S/N F3370072 thru F3370076 
     A separate checklist as described by Cessna Dwg. 1505050 is installed in the map 
     compartment. 
 
    (c) S/N F3370077 thru F3370079 
     A separate checklist as described by Cessna Dwg. 1505066 is installed in the map 
     compartment. 
 
    (d) S/N F3370080 thru F3370084 
     A separate checklist as described by Cessna Dwg. 1505074 is installed in the map  
     compartment. 
 
    (e) S/N F3370085 and on: 
     A separate checklist as described by Cessna Dwg. 1505095 is installed in the map 
     compartment. 
 
   14) The following placard must be installed near the fuel flow indicator: 
    "Maximum power mixture settings 
     S.L.   102 lb./hr. 
     4,000 ft.    90 lb./hr. 
     8,000 ft.    78 lb./hr. 
     12,000 ft.    66 lb./hr. 
 
   15) S/N F3370064 and on: 
    Forward of parking brake control: 
     "OFF 
      PARKING 
      BRAKE 
      ON" 
 
   16) S/N F3370064 and on: 
    Upper cabin door pin lock around cutout for pin:  "PUSH TO LOCK"

Rev. 8  Page 20 of 24 A23EU 
DATA PERTINENT TO ALL MODELS 
 
NOTE 2. (cont’d) 
   (17) S/N F3370064 and on: 
    Near the over-voltage test button: 
     "HIGH 
     VOLT 
     TEST  
     NOTE - CYCLE MASTER SWS AFTER TEST" 
 
    18) The following placard must be installed to the right of the tachometer and in the vicinity 
    of the engine gage cluster:   "Do not initiate single engine takeoff" 
 
  D. Applicable to Model FT337GP/FT337HP 
 
   1) In full view of the pilot: 
 
    (a) "This airplane must be operated as a normal category airplane in compliance with  
     the operations limitations stated in the form of placards, markings and manuals." 
 
    (b) "No acrobatic maneuvers, including spins, approved:. 
 
    (c) "Maximum Gross Weight: Takeoff 4700 lb. 
          Landing 4465 lb. 
 
    (d) "Maximum flight maneuvering load factors: Flaps Up +3.8   -1.52 
          Flaps Down +2.0" 
 
    (e) "Maximum operating altitude 20,000 feet" 
 
    (f) "Landing with cabin pressurized is prohibited" 
 
    (g) "Flight into known icing conditions prohibited" 
 
    (h) S/N FP3370001 through FP3370015 
     "Altitude loss in stall recovery - 400 feet". 
 
     S/N FP3370016 and up 
     "Altitude loss in a stall recovery - 450 feet" 
 
    (i) "This airplane is certified for the following flight operations as of date of original  
     airworthiness certificate: 
 
 (DAY NIGHT VFR IFR) (As applicable)” 
 
   2) Located near the Airspeed Indicator: 
    S/N FP3370001 thru FP3370015 
    "Maximum Speeds  - CAS 
    Gear Operation  160 mph 
    Gear Extended   230 mph 
    Maneuvering   155 mph" 
 
    S/N FP3370016 and on 
    "Maximum Speeds - IAS 
    Gear Operation  140 knots 
    Gear Extended   205 knots 
    Maneuvering   139 knots" 
 
   3) On control lock:  "Control lock - Remove before starting engines". 
 
   4) On the right rear firewall in the baggage area:   
    "Maximum baggage capacity 365 lb. Maximum baggage with restraining net 160 lb.    
    For additional loading instruction see weight and balance data".

Rev. 8  Page 21 of 24 A23EU 
DATA PERTINENT TO ALL MODELS 
 
NOTE 2. (cont’d) 
   5) On the fuel selector covers: 
 
      S/N FP3370001 thru FP3370013  
Fuel Off 
Rear Engine 
Left On Right On 
  
369 lb. 369 lb. 
(61.5 gal.) (61.5 gal.) 
      Takeoff and landing - Right Tank 
      Operation of both engines from one tank prohibited. 
 
"Fuel Off 
Front Engine 
Left On Right On 
  
369 lb. 369 lb. 
(61.5 gal.) (61.5 gal.) 
      Takeoff and landing - Left Tank 
 
   S/N FP3370014 and on 
Fuel Off 
Rear Engine 
 
Level Flight Only 
Left on 
Takeoff and Landing 
Right On 
  
420 lb.  444 lb. 
(70 gal.) (74 gal.) 
      When switching from dry tank - turn pump on 'HI' momentarily. 
      See Checklist for crossfeed limitations. 
 
Fuel Off 
Rear Engine 
Takeoff and Landing 
Left on 
Level Flight Only 
Right On 
  
444 lb.  420 lb. 
(74 gal.) (70 gal.) 
 
   6) Near propeller control:  "To feather propeller, lift propeller control up and pull back". 
 
   7) On upper portion of quadrant cover:  "With inoperative engine, feather propeller". 
 
   8) Adjacent to the fuel filler caps:   
    S/N FP3370001 thru FP3370013 
    "Tank capacity 62.5 U.S. Gallons, 100/130 minimum grade". 
 
    S/N FP3370014 thru FP3370022 
    "Tank capacity 75.3 U.S. Gallons, 100/130 minimum grade" 
 
    S/N FP3370023 and on 
    "Tank capacity 75.3 U.S. Gallons, 100LL/100 minimum grade"

Rev. 8  Page 22 of 24 A23EU 
DATA PERTINENT TO ALL MODELS 
 
NOTE 2. (cont’d) 
   9) On the inside of the fuel can covers:   
    S/N FP3370001 thru FP337008 
    "To obtain maximum capacity, fill slowly" 
 
    S/N FP3370009 and on 
    "To ensure complete filling of tanks: 
    (1) Fill slowly 
    (2) Retop after filling opposite wing" 
 
   10) Near the landing gear emergency hydraulic hand pump: 
    S/N FP3370001 thru FP3370022 
    "Manual Gear Extension 
    (1) Select gear down 
    (2) Pull handle forward 
    (3) Pump vertically" 
 
    S/N FP3370023 and on 
    "Manual Gear Extension 
    (1) Select gear down 
    (2) Pull handle forward 
    (3) Pump vertically 
     Caution:  Do not pump with gear up selected" 
 
    11) On the left side of the pedestal adjacent to the alternate static source valve: 
    S/N FP3370001 thru FP3370015 
    "Alternate static source correction 
    Airspeed:  Fly climbs and approaches 10 mph. faster than normal 
    Altitude:  Cruise: Fly 270 feet higher than normal 
       Approach: Fly 100 feet higher than normal" 
 
    S/N FP3370016 and on 
    "Alternate static source correction 
    Airspeed:  Fly climbs and approaches 10 KIAS faster than normal 
    Altitude:   Cruise: Fly 270 feet higher than normal 
       Approach: Fly 100 feet higher than normal" 
    
    12) Near pressurization air controls - right of pedestal: 
    "Cabin pressurization 
     Dump-Pull 
     Front 
     Rear" 
 
   13) Located beneath engine instrument cluster: 
     "Taxi and Takeoff 
     Lead with rear engine power 
     Check RPM and fuel flow" 
 
   14) Located near wing flap indicator: 
    S/N FP3370001 thru FP3370015 
     "Maximum flap extension speeds: 1/3 160 mph CAS 
          1/3 - 2/3 140 mph CAS 
          2/3 - full 125 mph CAS" 
    S/N FP3370016 and on: 
    "Maximum flap extension speeds: 1/3 165 KIAS 
          1/3 - 2/3 135 KIAS 
          2/3 - full 110 KIAS"

Rev. 8  Page 23 of 24 A23EU 
DATA PERTINENT TO ALL MODELS 
 
NOTE 2. (cont’d) 
   15) S/N FP3370001 thru FP3370013 
    A separate checklist as described by Cessna Dwg. 1505032 is installed in the map compartment. 
 
    S/N FP3370014 thru FP3370015 
    A separate checklist as described by Cessna Dwg. 1505051 is installed in the map compartment. 
 
    S/N FP3370016 thru FP3370017 
    A separate checklist as described by Cessna Dwg. 1505065 is installed in the map compartment. 
 
    S/N FP3370018 thru FP3370022 
    A separate checklist as described by Cessna Dwg. 1505075 is installed in the map compartment. 
 
    S/N FP3370023 and on 
    A separate checklist as described by Cessna Dwg. 1505093 is installed in the map compartment. 
 
   16) S/N FP3370001 thru FP3370013 
    Above the fuel gauges: 
    "Takeoff with less than 60 lb. (10 Gal.) fuel per tank is prohibited". 
 
   17) Near the fore and aft cabin door lock pins through the ABS trim: 
    "PUSH TO LOCK" 
 
   18) S/N FP3370014 and on 
    Forward of the parking brake control: 
     "OFF 
      PARKING 
      BRAKE 
      ON" 
 
   19) S/N FP3370014 and on 
    Near the over-voltage test button: 
     "HIGH 
      VOLT 
      TEST  
     NOTE - CYCLE MASTER SWS AFTER TEST" 
 
   20) S/N FP3370009 and on 
    Below the fuel flow indicator 
    "MAX. POWER MIXTURE SETTING - 140 lb/hr" 
 
   21) The following placard must be installed to the right of the tachometer and in the vicinity 
    of the engine gage cluster:  "Do not initiate single engine takeoff"   
 
NOTE 3. The cylinder head temperature thermistors must be installed as follows: 
 
 Cylinder Head No. 
Model Front Engine Rear Engine 
F337E 3 2 
FT337E and FT337F 1 1 
F337F 6 6 
F337G and F337H 4 6 
FT337GP and FT337HP 6 1

Rev. 8  Page 24 of 24 A23EU 
DATA PERTINENT TO ALL MODELS 
 
NOTE 4. Service information applicable to Model FT337GP/FT337HP 
 
  Components subject to the establishment of a retirement life as shown below with the corresponding  
  retirement life hours: 
 
   Component Name    Retirement Hours 
   Windshield, side windows 15,000 
   and ice detector light lens 
  
NOTE 5. 1%, by volume, isopropyl alcohol approved for use as fuel anti-icing additive when used as outlined in 
  Cessna Service Letter ME73-25 dated November 2, 1973, or subsequent revisions. 
 
NOTE 6. All Skymaster series aircraft 1964 through 1973 (Models 336, 337, and P337) complying with Cessna 
  Service Letter ME74-2 have the maximum oil level reduced two quarts from 10 quarts to 8 quarts.  Do not  
  operate at less than 6 quarts dipstick level reading. 
   
NOTE 7. The marking of the airspeed indicator with IAS provides an equivalent level of safety to FAR 23.1545 when  
  the approved airspeed calibration data presented in Section V of the Pilot's Operating Handbooks listed  
  below is available to the pilot: 
 
Model Cessna P/N  Serial Number 
F337G D1534-13  F3370077 through F3370079 
FT337GP D1535-13  FP3370016 though FP3370017 
F337G D1538-13  F3370080 through F3370084 
FT337GP D1539-13  FP3370018 through FP3370022 
F337H D1554-13  F3370085 and on 
FT337HP D1556-13  FP3370023 and on 
 
  In addition to the placards above, the prescribed operating limitations indicated by an asterisk (*) under  
  Sections I through VII of this data sheet must also be displayed by permanent markings. 
 
 
 
 --- END ---
```

## ADs (12, in force first)

- [AD 2023-09-09](https://openairdocs.org/ad/2023-09-09): Exhaust Turbine System (Recip) · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 292 more. Effective Jul 17, 2023
- [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 2011-15-11](https://openairdocs.org/ad/2011-15-11): Wings · Nineteen and a half(19.5 U.S.) gallons wing tip fuel tank (Flint Aero STC SA5090NM). Effective Sep 6, 2011
- [AD 2011-10-09](https://openairdocs.org/ad/2011-10-09): Seat Rails and Roller Housing Inspections · Cessna 150A, 150B, 150C and 221 more. Effective Jun 17, 2011
- [AD 2010-21-18](https://openairdocs.org/ad/2010-21-18): Wings · Wing tip extension fuel tanks (Aviation Enterprises STC SA02055AT or 3 others). Effective Nov 3, 2010
- [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 2000-06-01](https://openairdocs.org/ad/2000-06-01): Fuel Strainer Assembly · Cessna 150F, 150G, 150H and 163 more. Effective May 5, 2000
- [AD 97-01-13](https://openairdocs.org/ad/97-01-13): Fuel, Oil and Hydraulic Hoses · Cessna 150, 150A, 150B and 232 more. Effective Feb 3, 1997
- [AD 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 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

## Registered aircraft by registry model (OpenAirDocs)

- [Cessna FT337GP](https://openairdocs.org/model/cessna-ft337gp): 1 aircraft (registry code 2073711)
- [Reims F337G](https://openairdocs.org/model/reims-f337g): 1 aircraft (registry code 7535728)
- [Reims FT337GP](https://openairdocs.org/model/reims-ft337gp): 1 aircraft (registry code 7535709)

## STCs approved under this data sheet (68, 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 SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation
- [STC 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 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 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 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 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 SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation
- [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation
- [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc
- [STC 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 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 SA02013CH](https://openairdocs.org/stc/SA02013CH): Installation of Avidyne Corporation Traffic Advisory System (TAS). Avidyne Corporation
- [STC SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC
- [STC SA1627WE](https://openairdocs.org/stc/SA1627WE): Installation of drooped ailerons in flaps down mode, recontoured wing leading edge, stall fences, aileron centering springs, conical cambered wing tips and flap actuated elevator trim spring.. Sierra Industries Ltd.
- [STC SA00382BO](https://openairdocs.org/stc/SA00382BO): Installation of Globalstar Antenna and Cradle provisions to support a Globalstar GPS-1700 in non-composite airplanes. Avidyne Corporation
- [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley
- [STC SA00343BO](https://openairdocs.org/stc/SA00343BO): Installation of a single configuration or a dual configuration Avidyne Corporation Integrated Flight Display, Model IFD540 loaded with Release 10.0 software (or later FAA approved release). Avidyne Corporation
- [STC SA00352BO PAGE 1](https://openairdocs.org/stc/SA00352BO%20PAGE%201): Installation of an Avidyne Corporation Mode A/C/S Transponder with ADS-B Out capability, Model AXP340 loaded with Version 3.13 software (or later FAA approved version),. Avidyne Corporation
- [STC SA00780SE](https://openairdocs.org/stc/SA00780SE): Installation of the True Lock Safety Retention Axle Lock Nut System. True Lock LLC
- [STC SA02119SE PAGE 1](https://openairdocs.org/stc/SA02119SE%20PAGE%201): Installation of Garmin GDL 88 ADS-B UAT Transceiver System. Garmin International Inc
- [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 SA02121SE](https://openairdocs.org/stc/SA02121SE): Installation of Garmin GTS 825 (TAS) or GTS 855 (TCAS I) Traffic System. Garmin International Inc
- [STC SA02825NY PAGE 1](https://openairdocs.org/stc/SA02825NY%20PAGE%201): Installation of Aerospace Logic Aircraft Instruments. Aerospace Logic Inc.
- [STC SA453CE](https://openairdocs.org/stc/SA453CE): Install Hoskins Twilighter Mk.III supplementary lighting system.. BF Goodrich Aerospace
- [STC ST00961LA](https://openairdocs.org/stc/ST00961LA): Installation of MASS Systems fire extinguisher cartridges as replacements for Walter Kidde Aerospace fire extinguisher cartridges in fire extinguisher bottles installed in the airplane models noted on the FAA Approved Model List dated June 29, 2000, or later FAA approved revisions.  These fire extinguisher cartridges are in accordance with the MASS Systems Master Drawing List No. 30980-1, "Slug Thrower Cartridges Master Drawing List", Revision N/C, dated
June 26, 2000, or later FAA approved revisions.. AMETEK AMERON LLC d/b/a MASS Systems
- [STC SA2693NM](https://openairdocs.org/stc/SA2693NM): Installation of Electronics International digital volt/amp gauges and accessories.. Electronics International Inc.
- [STC SA01988SE](https://openairdocs.org/stc/SA01988SE): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) MVP-50P.. Electronics International Inc.
- [STC SA01834CH](https://openairdocs.org/stc/SA01834CH): Installation of the High Intensity Discharge Light Assembly Kit.. Knots 2U Ltd.
- [STC SA02033AT](https://openairdocs.org/stc/SA02033AT): Modification to install an air-oil separator to prevent oil from being aspirated from the engine breather line.. M-20 Oil Separators LLC
- [STC SA4005NM](https://openairdocs.org/stc/SA4005NM): Precise Flight Inc. Pulselite Control System. Precise Flight Inc
- [STC SA00271WI](https://openairdocs.org/stc/SA00271WI): Replacement of the hydraulic system pressure switch with a new switch. APPH Wichita Inc.
- [STC SA02446CH](https://openairdocs.org/stc/SA02446CH): Installation of the Courtesy Light Kit.. Knots 2U Ltd.
- [STC SA20GL](https://openairdocs.org/stc/SA20GL): Installation of Woodward Type II electronic propeller synchronizer or synchrophaser system. (G-44A MODIFIED COLEMILL - STC 2-13) (500-A modified - Colemill STC SA340SO). Ontic Engineering and Manufacturing Inc.
- [STC SA00680SE](https://openairdocs.org/stc/SA00680SE): Installation of Electronics International model UBG-16 or UBG-16T bar graph engine analyzer.. Electronics International
- [STC SA03100AT](https://openairdocs.org/stc/SA03100AT): Installation of Wing Auxiliary Fuel Tanks.. Aviation Enterprises
- [STC SA02700AT](https://openairdocs.org/stc/SA02700AT): Installation of Air Conditioner System. Aviation Enterprises
- [STC SA01215SE](https://openairdocs.org/stc/SA01215SE): Installation of vortex generators on the leading edge of the upper side of the wing on the underside of the horizontal stabilizer, and on both vertical stabilizers.. Micro AeroDynamics Inc
- [STC SA09121AC-D](https://openairdocs.org/stc/SA09121AC-D): Installation of S-TEC System 55 Two Axis Automatic Flight Guidance System, Model ST-603. S-TEC Corporation
- [STC SA02168AK](https://openairdocs.org/stc/SA02168AK): Installation of hourmeter airspeed switch. For unpressurized aircraft only. Pressurized aircraft must have pressurization system deactivated.. Avalaska Inc

All 68: https://openairdocs.org/tcds/A23EU/stcs.md

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