TCDS E6WE

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E6WE Revision 18 Honeywell Aerospace US LLC (AlliedSignal, Garrett, AiResearch) TFE731-2, -2A, -2B, -2BR, -2C, -3R, -3A, -3AR, -3B, -3BR, -3C, -3CR, -3D, -3DR, -4R, -5, -5A, - 5AR, -5B, -5BR, -5R March 27, 2026 TYPE CERTIFICATE DATA SHEET NO. E6WE Engine models described herein conforming with this data sheet (which is part of Type Certificate No. E6WE) 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. 111 South 34th Street Phoenix, AZ 85034 TYPE CERTIFICATE HOLDER RECORD: Garrett Turbine Engine Co. 111 South 34th Street Phoenix, AZ 85034 TYPE CERTIFICATE HOLDER RECORD: AiResearch Manufacturing Co. 111 South 34th Street Phoenix, AZ 85034 Model TFE731-2, -2A, -2B, -2BR, -2C, -3, -3R, -3A, -3AR, -3B, -3BR, -3C, -3CR, -3D, -3DR, -4, -4R, -5, -5A, -5AR, -5B, -5BR, -5R 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. 18 18 18 17 18 18 18 E6WE 2 of 7 Static Thrust Ratings: TFE731 Models Maximum Continuous at Sea Level, lbs. Takeoff at Sea Level, lbs. (5 mins.) -2, -2B, -2C 3500 3500 -2A 3600 3600 -2BR 3500 3650 -3, -3A, -3C, -3D 3700 3700 -3R, -3AR, -3CR, -3DR 3700 3880 -3B 3650 3650 3BR 3650 3850 -4 4080 4080 -4R 4080 4080 -5 4304 4304 -5R 4304 4304 -5A 4500 4500 -5AR 4500 4500 -5B 4634 4750 -5BR 4634 4750 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. TFE731 Models Lbs. -2 743 -4, -4R 822 -2A 772 -2B, -2BR 773 -5, -5R 852 -2C 753 -5A, -5AR 884 -3, -3R 754 -5B, -5BR 899 -3A, -3AR 775 3B, -BR 769 -3C, 3CR 777 -3D, -3DR 767 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 JB-8 Types), EMS 53113 (Jet B and JP-4 Types), and EMS 53116 (JP-5 Type). BIOBAR JF biocide additive is approved for use in the fuel at a concentration not to exceed 20 ppm of elemental boron. KATHON FP 1.5 biocide additive is approved for use in the fuel at a concentration not to exceed 100 ppm. E6WE 3 of 7 Shell ASA-3 Anti-Static Additive, or equivalent, in amounts to bring the fuel up to a range of 50 to 450 conductivity units for JET A, JET A-1, and JET B, or up to a range of 200 to 600 conductivity units for JP4, 5, and 8, is permissible as long as the quantity added does not exceed one part per million. MIL-DTL-85470 "D" and "E" inhibitor, icing, fuel system, or equivalent, are approved for use in amounts up to 0.15 percent by volume. Aviation Gasoline, MIL-G-5572D, Grade 80/87, 100/130, and 115/145, not in excess of 500 gallons per 100 hours of operation, may be used in emergencies in TFE731-2/3 series engines which do not incorporate a fuel heater. Oil Oil conforming to Honeywell Aerospace US LLC Specification EMS 53110, Type 2. Certification Basis: 14 CFR part 33 dated April 3, 1967, and Amendments 1, 2, and 3, and Special Condition No. 33-44-WE-13. Type Certificate No. E6WE, issued August 31, 1972, for -2; September 12, 1974, for -3; January 13, 1978, for -3R; January 22, 1981, for -3A and -3AR; March 3, 1981, for -3B and -3BR; November 22, 1983, for -5 and -5R; December 10, 1984, for the -5A; July 7, 1986, for -5AR; September 16, 1988, for -2A, -2B, and -2BR; February 7, 1991, for -5B and -5BR; November 7, 1991, for -4 and -4R; January 22, 1993, for -3C and -3CR; and October 28, 1994, for -3D and -3DR; and March 23, 1998, for -2C. Date of application for type certificate June 25, 1969. Production Basis: Production Certificate No. 413 issued March 4, 1965, and reissued as Production Certificate No. 413NM to Honeywell Aerospace US LLC, dated March 29, 2026. NOTE 1: Maximum permissible continuous engine operating speeds for the engine rotors are as follows: TFE731 Models Low Pressure Rotor (N1) RPM High Pressure Rotor (N2) RPM -2 20,688 29,692 -2A, -2B, -3, -3A, -3B, -3C, - 3D, -5, -5A 21,000 29,692 -2BR, -3R, -3AR, -3BR, - 3CR, -3DR, -4, -5R, -5AR 21,000 29,989 -2C 20,688 30,100 -4R, -5B 21,000 30,300 -5BR 21,000 30,540 E6WE 4 of 7 NOTE 2: Temperature Limits: Maximum Interstage Turbine Temperature (ITT) Limits: °F (°C) Maximum Oil Inlet Temperature Range, °F (°C) for all engine models: Fan gearbox oil temperature transient of 300°F (149°C) 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 16). Operation at an engine fuel inlet temperature as high as 135°F (57°C) and as low as -65°F (-54°C) is approved with fuel at or above the pour point during starting. If fuel that does not contain an approved anti-icing additive is used, an approved engine fuel heater, or an alternate system capable of maintaining a fuel filter inlet temperature of 35°F, must be used. In installations that do not use an approved fuel heater and may extract motive flow for aircraft injector systems, engine operation with inoperative electronic fuel control is limited to a minimum inlet fuel temperature of 12°F (- 11°C) with 1000 pounds per hour (maximum) motive flow extraction and -31°F (-35°C) without motive flow extraction. Installations which are equipped with the hydromechanical fuel control heater are approved for operation with fuel inlet temperature as low as -65°F (-54°C) provided fuel is at or above pour point. Max. Takeoff Starting TFE731 Models Continuous (5-Minutes) (Ground/Air) -2 1530 (832) 1580 (860) 1580 (860) -2C 1590 (865) 1615 (880) 1615 (880) -3, -3A 1625 (885) 1665 (907) 1665 (907) -3R, -3AR 1625 (885) 1705 (929) 1665 (907) -2A, -2B 1625 (885) 1635 (890) 1665 (907) -2BR 1625 (885) 1680 (916) 1665 (907) -3B 1635 (890) 1635 (890) 1635 (890) -3BR 1635 (890) 1680 (916) 1635 (890) -3C, -3D 1670 (910) 1670 (910) 1670 (910) -3CR, -3DR 1670 (910) 1705 (929) 1670 (910) -4, -5, - 5A 1693 (924) 1746 (952) 1746 (952) -4R, -5R, -5AR 1696 (924) 1786 (974) 1746 (952) -5B 1775 (968) 1793 (978) 1793 (978) -5BR 1775 (968) 1824 (996) 1793 (978) 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) E6WE 5 of 7 NOTE 3: Pressure Limits: NOTE 4: The ratings are based on static test stand operation and under the following conditions: (a) No loading of accessory drives (b) No compressor bleed airflow (c) Bellmouth inlet conforming to Honeywell Aerospace US LLC SKP17308 (TFE731-2, -2A, -2B, -2BR, -2C, -3, -3A, -3AR, -3R, -3B, -3BR, -3C, -3CR, - 3D, -3DR, -4 and -4R models) and SKP23600 (TFE731-5, -5R, -5A, -5AR, - 5B, and -5BR models). (d) Fan exhaust and turbine exhaust nozzles conforming to Honeywell Aerospace US LLC Drawing SKP17303 Drawing SKP1730 (TFE731-2 and -2C models), SKP17402 (TFE731-2A, -2B, -2BR, -3, -3R, -3A, -3AR, -3B, -3BR, -3C, -3CR, -3D, and -3DR models), SKP24628 (TFE731-4 and -4R models), SKP17829 (TFE731-5 and -5R models), SKP23873 and SKP23640 (TFE731-5A and - 5AR models), and SKP24301 and SKP23640 (TFE731-5B and -5BR models). The aerodynamic flow path of this fan duct includes Honeywell Aerospace US LLC operational air-oil coolers (P/Ns 158600, 159900, and 159910 with oil flowing). (e) No anti-icing airflow. (f) Interstage Turbine Gas Temperature (ITT) and rotor speed limits do not exceed. Fuel pump inlet pressure, minimum (Refer to applicable engine installation manual (See Note 16). maximum 50 psig Oil pressure at inlet connection to engine, minimum 4.0 psia Oil normal operating pressure 38 to 46 psig At idle, minimum (Refer to applicable engine installation, manual (See Note 16). 25 psig E6WE 6 of 7 NOTE 5: Accessor Drive Provisions: Accessory Drive Drive Type Drive Modification Rotation Facing Drive End and RPM at N2 of 29,024 RPM Maximum Torque (lb.-in.) Accessory Weight Pounds Maximum Maximum Overhung Moment (lb.-in.) Tc To Ts Starter or Starter Generator AND2002 Type XII- D (Modified) Pad rotated, RPM, Torques, accessory weight and moment CW 12000 210 315 1600 45 400 Aircraft Accessory AND20002 Type XII- D (Modified) Pad rotated, RPM, Torques, accessory weight and moment CW 12000 210 315 1000 40 400 Aircraft Accessory AND20001 Type XI-B (Modified) Pad rotated, RPM, Torques, accessory weight and moment CW 6000 250 375 1650 15 100 CW = Clockwise Tc = Continuous Torque To = Torque Overload Ts = Static Torque NOTE: Total weight of the accessories is not to exceed 95 pounds. Refer to the applicable engine installation manual (See Note 16). NOTE 6. Custom Bleed Airflow Limits. Refer to the applicable engine installation manual (See Note 16). 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 listed in the FAA approved Honeywell Aerospace US LLC Service Bulletins TFE731-72-3001 and TFE731-72-3501. NOTE 10: These engine models meet the requirements of Special Condition No. 33-44-WE-13. NOTE 11: Variation in engine configuration and installation components are identified by a suffix to the basic model on the engine nameplate, i.e. TFE734 -2-XY, (“X” denotes Honeywell Aerospace installed configurations rating code number(s) and “Y” denotes Honeywell Aerospace equipment code letter(s) E6WE 7 of 7 of aircraft manufacture), and an Engine Equipment List, those items code letter (s) of aircraft manufacture), 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 of the Federal Aviation Regulations. Items coded “A” have been demonstrated as compatible with the basic engine during engine certification testing. However, the 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. NOTE 12: 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 13: The TFE731-2BR, -3R, -3AR, -3BR, -3CR, -3DR, -4R, -5AR, -5BR, and -5R turbofan engines with their electronic fuel control systems are adjusted for the limits noted herein. NOTE 14: For additional authorized operation and installation detailed information, see FAA-approved sections of the applicable engine installation manual (See Note 16). NOTE 15: These engines meet the requirements of §§ 33.68, 33.71(c), 33.75, 33.77 and 33.90 effective with Amendment 33-6. NOTE 16: The engine installation manual numbers are applicable to the respective engine models as follows: IM-8001: TFE731-2, -2C, -3, -3R, -3A, -3AR, -3B, -3BR, -3C, -3CR, -3D, -3DR IM-7440: TFE731-4, -4R IM-4200: TFE731-5, -5R, -5AR, -5B, -5BR NOTE 17: These engines are in compliance with Part 34 of the Federal Aviation Regulations. ---------------------------END-----------------------