# TCDS E1NM: Honeywell Aerospace US LLC - Type: Type certificate data sheet - Status: Current - Holder: Honeywell Aerospace US LLC - Revision: 13 - Revised: March 27, 2026 - Product: Engine - Certification basis: Part 34, Part 33 - Registered aircraft: 465, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/78/ae/78ae356ebd4576f5a993967e4126bb81ead7c0536ec273507d61189bb022918d - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID142173243720260605173736.0001 - Page: https://openairdocs.org/tcds/E1NM ## Models (10) As the data sheet lists them. - TFE731-60 - TFE731-40 - TFE731-20 - TFE731-20R - TFE731-20AR - TFE731-40AR - TFE731-20BR - TFE731-50R - TFE731-40R - TFE731-40BR ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E1NM Revision 13 Honeywell Aerospace US LLC (AlliedSignal) TFE731-20 TFE731-20AR TFE731-20BR TFE731-20R TFE731-40 TFE731-40R TFE731-40AR TFE731-40BR TFE731-50R TFE731-60 March 27, 2026 TYPE CERTIFICATE DATA SHEET NO. E1NM Engine models described herein conforming with this data sheet (which is part of Type Certificate No. E1NM) and other approved data on file with the Federal Aviation Administration, meet pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. TYPE CERTIFICATE HOLDER: Honeywell Aerospace US LLC 111 South 34th Street Phoenix, AZ 85034 TYPE CERTIFICATE HOLDER RECORD: Honeywell International Inc. 111 South 34th Street Phoenix, AZ 85034 TYPE CERTIFICATE HOLDER RECORD: AlliedSignal Inc. transferred 111 South 34th Street Phoenix, AZ 85034 Model: TFE731-20, -20AR, -20BR, -20R, -40, -40R, -40AR, -40BR, -50R, and -60 Type: Turbofan: One stage geared fan, four stage axial flow low pressure compressor, one stage centrifugal high-pressure compressor, annular combustor, one stage high pressure turbine, and three stage low pressure turbine. Page No. 1 2 3 4 5 6 7 Rev. No. 13 13 13 13 13 13 12 E1NM 2 of 7 Static Thrust Ratings: (See Notes 4 and 12) TFE731 Models Max. Continuous at Sea Level, lbs. Takeoff at Sea Level, lbs. (see NOTE 15) -20 3500 3500 -20AR 3500 3650 -20BR 3500 3650 -20R 3500 3650 -40 4250 4250 -40R 4250 4462 -40AR 4250 4420 -40BR 3500 3850 -50R 5000 5000 -60 4525 5000 Controls. Fuel controls and power management are controlled by Digital Electronic Engine Control (DEEC) with a backup hydromechanical control. The hardware and software configurations of this system and the associated engine fuel pump and hydromechanical unit are controlled by an approved engine equipment list for each specific engine model and aircraft application. Principal Dimensions Refer to the installation drawing for each specific engine model configuration for dimensions and center of gravity location. Weight, Dry, Pounds (maximum): TFE731 Models Lbs. -20 895 -20AR 895 -20BR 895 -20R 895 -40 885 -40R 885 -40AR 885 -40BR 895 -50R 978 -60 993 The engine weights shown herein are that of the power section and all components coded "E" in the Engine Equipment List. The total engine weight, including the weight of items coded "A" in the Engine Equipment list, is included on the engine installation drawing for each specific aircraft configuration. Fuel Fuels conforming to Honeywell Aerospace US LLC. Specifications EMS 53111 (Jet A Type), EMS 53112 (Jet A-1 and JP-8 Types), EMS 53113 (Jet B and JP-4 Types), and EMS 53116 (JP-5 Type). Refer to engine installation manual for approved fuel types (see NOTE 12). Refer to engine installation manual for approved fuel additives (see NOTE 12). Aviation Gasoline, ASTM D 910 Grades 80 or 100LL, not in excess of 500 gallons per 100 hours of operation, may be used in emergencies. Oil Oil conforming to Honeywell Aerospace US LLC Specification EMS53110. E1NM 3 of 7 Ce rtification Basis *14 CFR part 33, effective February 1, 1965, as amended by 33-1 through 33-15, effective August 16, 1993. * *14 CFR part 34 effective September 10, 1990, as amended by 34-1 through 34-3, effective February 3, 1999. Model Part 33 Certification Basis Part 34 Certification Basis Date of Application Date of Issuance/Amended -60 * as stated above Original effective 9/10/90 02/08/94 05/01/95 -40, -40R * as stated above Original effective 9/10/90 02/08/94 07/13/95 -20, -20R * as stated above Original effective 9/10/90 01/19/93 04/04/97 -20AR * as stated above ** 03/24/99 05/14/99 -20BR * as stated above ** 01/22/01 08/25/03 -40AR * as stated above ** 02/07/05 10/31/05 -50R * as stated above ** 09/24/04 10/13/06 -40BR * as stated above ** 02/16/12 01/15/13 Production Basis Production Certificate No. 413, issued March 4, 1965. Reissued Production Certificate No. 413NM to Honeywell Aerospace US LLC on March 29, 2026. N OTE 1. Maximum permissible operating speeds for the low and high pressure rotors for all engine models excluding TFE731-50R and TFE731-40BR are as follows: Low Pressure Rotor (N1) RPM High Pressure Rotor (N2) RPM Takeoff/Maximum Continuous 21,000 31,485 Maximum Transient (control overshoot) 21,105 31,957 N OTE 1A. Maximum permissible operating speeds for the low and high pressure rotors for the TFE731-50R and TFE731-40BR engine models are as follows: Low Pressure Rotor (N1) RPM High Pressure Rotor (N2) RPM Takeoff 21,000 31,800 Maximum Continuous 21,000 31,485 Maximum Transient (control overshoot) 21,105 32,277 N OTE 2. Temperature Limits: M aximum Interstage Turbine Temperature (ITT) Limits: oF (oC) TFE731 Models Max. Continuous Takeoff (see NOTE 15) Starting (Ground/Air) -20 1,726 (941) 1,766 (963) 1,726 (941) -20AR 1,726 (941) 1,766 (963) 1,726 (941) -20BR 1,816 (991) 1,871 (1022) 1,822 (994) -20R 1,726 (941) 1,766 (963) 1,726 (941) -40 1,816 (991) 1,871 (1022) 1,822 (994) -40R 1,816 (991) 1,871 (1022) 1,822 (994) -40AR 1,816 (991) 1,871 (1022) 1,822 (994) -40BR 1,816 (991) 1,871 (1022) 1,822 (994) -50R 1,816 (991) 1,871 (1022) 1,822 (994) -60 1,816 (991) 1,871 (1022) 1,822 (994) E1NM 4 of 7 Maximum Oil Inlet Temperature Range, oF (oC) for all engine models: Sea Level to 30,000 Feet Above 30,000 Feet Fan Gearbox Inlet Maximum 260 (127) 284 (140) Accessory Gearbox Inlet Maximum 300 (149) 315 (157) Fan gearbox oil inlet temperature transient of 300oF (149oC) for a maximum of 2 minutes is permitted for all operational altitudes. External engine components, maximum temperature (limiting temperature of specific components) are as specified in the applicable engine installation manual, see NOTE 12. Operation at an engine fuel inlet temperature as high as 135°F (57°C) with a vapor volume to liquid volume ratio (V/L) equal to 0.45, and as low as -65°F (-54°C) with fuel at a viscosity of 12 centistokes or less during starting is approved. NOTE 3. Fuel and Oil Pressure Limits: Fuel pump inlet pressure minimum 5 psi above true vapor pressure maximum 50 psig Oil pressure minimum 50 psig normal operating range 65 to 80 psig NOTE 4. The ratings are based on static test stand operation and under the following conditions: (a) No loading of aircraft accessory drives. (b) No compressor bleed airflow. (c) Bellmouth inlet conforming to Honeywell Aerospace US LLC Drawing 5837113 for the TFE731-60 and SKP17308 for the TFE731-20, -20AR, -20BR, -20R, -40, -40R, -40AR, -40BR, and SKP23600 for the TFE731-50R. (d) Fan exhaust and turbine exhaust nozzles conforming to Honeywell Aerospace US LLC Drawing SKP23202 for the TFE731-60 and SKP23199 for the TFE731-40, -40R, -40AR and SKP23196 for the TFE731-20, -20AR, -20BR, -20R, -40BR, and SKP24973 for the TFE731-50R. (e) No anti-icing airflow. (f) Interstage Turbine Gas Temperature (ITT) and rotor speed limits not exceeded. (g) Dry inlet air. NOTE 5. Accessory Drive Provisions: Accessory Drive Type Internal Spline RPM and Rotation Facing Drive Note: (e) Accessory Max. Torque (lb-in) Weight (pounds, maximum) Overhung Moment Drive (one each) Config. End Tc To Ts Note (b) (lb-in) Starter or Starter Generator D2* Note (c) AND20002 Type XII-D modified as follows: RPM, torques, accessory weight, and moment as shown AND20002 12,602 Note (a) CW 12,728 Note (f) CW 200 300 1600 45 400 Aircraft Accessory D3* AND20002 Type XII-D modified as follows: RPM, torques, accessory weight, and moment as shown AND20002 12,602 Note (a) CW 12,728 Note (f) CW 200 300 1000 40 400 E1NM 5 of 7 Aircraft Accessory D1* (for engines without motive flow fuel pump) AND20001 Type XI-B modified as follows: RPM, torques, accessory weight, and moment as shown AND20001 6,300 Note (a) CW 6,364 Note (f) CW 240 360 1650 15 100 Aircraft Accessory D1* (for engines with motive flow fuel pump) Note (d) AND20001 Type XI-B modified as follows: RPM, torques, accessory weight, and moment as shown AND20001 6,300 Note (a) CW 6,364 Note (f) CW 100 165 1000 7 18 CW= clockwise (looking aft) To = torque overload (5 min. per 4 hr. period) Tc = continuous torque Ts = static torque *Accessory pads are identified by these symbols on the applicable installation drawings. Notes: (a) Drive speeds are based on a maximum steady state HP rotor speed of 31,485 rpm for all models excluding TFE731-50R and TFE731-40BR. (b) Total weight of the aircraft accessories shall not exceed 95 pounds for engines without motive flow fuel pump: 87 pounds with motive flow fuel pump. (c) The estimated torsional spring constant for the starter generator drive is 7,000 pound inches per radian. (d) Drive is located on engine auxiliary motive flow fuel pump. (e) Total combined accessory power extraction limits are specified in the applicable engine installation manual (see NOTE 12). (f) Drive speeds are based on a maximum steady state HP rotor speed of 31,800 rpm for models TFE731-50R and TFE731-40BR. NOTE 6. For compressor bleed airflow limits, refer to the applicable engine installation manual (see NOTE 12). NOTE 7. These engines meet FAA requirements for turbine disk integrity and rotor blade containment. NOTE 8. These engines meet FAA requirements for operation in icing conditions within the envelope defined in 14 CFR part 25, Appendix C. NOTE 9. Certain engine parts are life-limited. These limits are published in the FAA Approved Airworthiness Limitations Section of the Instructions for Continued Airworthiness contained in the Light Maintenance Manuals, Chapter 5. NOTE 10. Variations in engine configuration and installation components are identified by a suffix to the basic model number on the engine nameplate; i.e. TFE731-60-XY (“X” denotes Honeywell Aerospace US LLC installed configuration rating code number(s) and “Y” denotes Honeywell Aerospace equipment code letter(s) of aircraft manufacturer), and an Engine Equipment List number. Certain features of these components are influenced by aircraft design considerations. In the Engine Equipment List, those items coded “E” are basic engine items and are controlled by Part 33. Items coded “A” have been demonstrated as compatible with the basic engine during engine certification testing. However, operation, functioning, and performance of these in a specific aircraft installation must be demonstrated during aircraft certification. Subsequent design control associated with these factors is the responsibility of the aircraft manufacturer. E1NM 6 of 7 NOTE 11 Power setting, power checks and control of engine thrust output in all operations is to be based on Honeywell Aerospace US LLC engine charts referring to low pressure rotor speed (N1). Speed sensors are included in the engine assembly for this purpose. NOTE 12. For additional authorized operation and installation detailed information, refer to FAA approved engine installation manuals as follows: IM-8300: TFE731-20, -20AR, -20BR, -20R IM-8010: TFE731-40, -40R, -40AR IM-8009: TFE731-60 IM-8024: TFE731-50R IM-8033: TFE731-40BR NOTE 13. Model description – similarities, differences and special characteristics: TFE731-60 Basic Model One stage geared fan (damperless low-aspect-ratio rotor blade), four- stage axial flow low pressure compressor, one-stage centrifugal high pressure compressor, annular combustor, one-stage high pressure turbine, and three-stage low pressure turbine. TFE731-40 Same as TFE731-60 basic model except one-stage geared fan (midspan dampered rotor blade), different external assembly (plumbing, electrical, etc.). TFE731-40R Same as TFE731-40 except different external assembly (plumbing, electrical, etc.). The -40R incorporates the Automatic Performance Reserve (APR) system and/or the Manual Performance Reserve (MPR) system. TFE731-20 Same as TFE731-60 basic model except one-stage geared fan (midspan dampered rotor blade), modification to the tangential onboard inducer (TOBI), DS material for first-stage LP turbine blade, different HP turbine nozzle area, different combustor and fuel atomizer shroud cooling scheme, different external assembly (plumbing, electrical, etc.). TFE731-20R Same as TFE731-20 except the -20R incorporates the APR and/or MPR system. TFE731-20AR Same as TFE731-40R except different external assembly (plumbing, electrical, etc.). TFE731-20BR Same as TFE731-20AR except operates at the higher ITT ratings of the -40R engine. TFE731-40AR Same as TFE731-40R except operates at lower takeoff thrust rating. TFE731-50R Same as TFE731-60 basic model except a reduced-diameter fan rotor assembly and associated surrounding outer structure, incorporates the APR system, increased N2 speed at takeoff. E1NM 7 of 7 TFE731-40BR Same as TFE731-20BR with increased takeoff flat-rated thrust and increased N2 limit. Incorporates improved durability hot-section hardware already used on TFE731-60. NOTE 14. The engine type design does not include a thrust reverser. Considerations for the installation of a thrust reverser are contained in the engine installation manuals (see NOTE 12). The engines have demonstrated compatibility with the following thrust reversers: Engine Model T/R Manufacturer Right Hand Left Hand Center -20/-20R/-20AR/ -20BR/-40BR Nordam TR5045 TR5045 N/A -40R/-40AR Nordam TR5040AS TR5040AS N/A -40 Dassault (Alenia) N/A N/A F50B-583-D3 -60 Dassault (Alenia) N/A N/A FGFB-583-D1 -50R Nordam TR5050 TR5050 N/A NOTE 15. The normal 5-minute takeoff time limit may be extended to 10 minutes for engine out contingency. NOTE 16. DELETED -------------------------END----------------------- ``` ## ADs (7, in force first) - [AD 2019-05-07](https://openairdocs.org/ad/2019-05-07): Turbine Engine Compressor Section · Honeywell International TFE731-20AR, TFE731-20BR, TFE731-20R and 4 more. Effective Apr 25, 2019 - [AD 2014-12-52](https://openairdocs.org/ad/2014-12-52): Engines · Honeywell International TFE731-20AR, TFE731-20BR, TFE731-20R and 11 more. Effective Jul 28, 2014 - [AD 2012-16-14](https://openairdocs.org/ad/2012-16-14): LPT2 rotor blades · Honeywell International TFE731-20AR, TFE731-20BR, TFE731-20R and 5 more. Effective Oct 1, 2012 - [AD 2008-02-19](https://openairdocs.org/ad/2008-02-19): High pressure (HP) turbine rotor assemblies · Honeywell International TFE731-20AR, TFE731-20BR, TFE731-20R and 15 more. Effective Mar 6, 2008 - [AD 99-07-19](https://openairdocs.org/ad/99-07-19): Tube and Fuel Flow Meter Mounting Bracket · Honeywell International TFE731-40R. Effective Apr 21, 1999 - [AD 98-10-15](https://openairdocs.org/ad/98-10-15): Fuel Line · Honeywell International TFE731-40R. Effective May 19, 1998 - [AD 2017-20-01](https://openairdocs.org/ad/2017-20-01) (historical): Turbine Engine Compressor Section · Honeywell International TFE731-20 and TFE731-40. Effective Nov 2, 2017 ## Registered aircraft by registry model (OpenAirDocs) - [Honeywell TFE731-50R](https://openairdocs.org/engine/honeywell-tfe731-50r): 123 aircraft (registry code 33940) - [Honeywell TFE731-20BR](https://openairdocs.org/engine/honeywell-tfe731-20br): 105 aircraft (registry code 33919) - [Honeywell TFE731-20AR](https://openairdocs.org/engine/honeywell-tfe731-20ar): 51 aircraft (registry code 33918) - [Honeywell TFE731-40AR](https://openairdocs.org/engine/honeywell-tfe731-40ar): 50 aircraft (registry code 33923) - [Alliedsign TFE731-60](https://openairdocs.org/engine/alliedsign-tfe731-60): 45 aircraft (registry code 02504) - [Honeywell TFE731-60](https://openairdocs.org/engine/honeywell-tfe731-60): 39 aircraft (registry code 33924) - [Honeywell TFE731-40R](https://openairdocs.org/engine/honeywell-tfe731-40r): 18 aircraft (registry code 33922) - [Honeywell TFE731-40](https://openairdocs.org/engine/honeywell-tfe731-40): 17 aircraft (registry code 33921) - [Alliedsign TFE731-40](https://openairdocs.org/engine/alliedsign-tfe731-40): 6 aircraft (registry code 02519) - [Alliedsign TFE731-20AR](https://openairdocs.org/engine/alliedsign-tfe731-20ar): 3 aircraft (registry code 02516) - [Alliedsign TFE731-20BR](https://openairdocs.org/engine/alliedsign-tfe731-20br): 3 aircraft (registry code 02517) - [Alliedsign TFE731-40R](https://openairdocs.org/engine/alliedsign-tfe731-40r): 2 aircraft (registry code 02520) - [Alliedsign TFE731-20](https://openairdocs.org/engine/alliedsign-tfe731-20): 1 aircraft (registry code 02515) - [Alliedsign TFE731-40AR](https://openairdocs.org/engine/alliedsign-tfe731-40ar): 1 aircraft (registry code 02521) - [Honeywell TFE731-20](https://openairdocs.org/engine/honeywell-tfe731-20): 1 aircraft (registry code 33917) - [Alliedsign TFE731-20R](https://openairdocs.org/engine/alliedsign-tfe731-20r): 0 aircraft (registry code 02518) - [Honeywell TFE731-20R](https://openairdocs.org/engine/honeywell-tfe731-20r): 0 aircraft (registry code 33920) --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.