TCDS E7WE

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E7WE Revision 6 Honeywell Aerospace US LLC (AlliedSignal, Garrett) ATF3-6 ATF3-6A March 27, 2026 TYPE CERTIFICATE DATA SHEET NO. E7WE Engine models described herein conforming with this data sheet (which is part of Type Certificate No. E7WE) 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 (TC) 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 Model Number: ATF3-6, ATF3-6A Type Turbofan, three-rotor, single-stage fan, 5-stage axial low-pressure compressor, single-stage centrifugal high-pressure compressor, reverse- flow annular combustor, single-/3-/2- stage high-/low pressure turbine, mixed-flow exhaust, electronic hydromechanical fuel control Page No. 1 2 3 4 5 6 7 Revision No. 6 6 6 6 2 6 2 E7WE 2 of 7 Rating (see Note 5) ATF3-6 ATF3-6A Maximum continuous at sea level and 59°F Static thrust, lbs. 5101 5101 Takeoff at sea level and 59°F (5 minutes): Static thrust, lbs. 5440 5440 Flight idle at sea level (minimum) Static thrust, lbs. 740 740 Controls and Accessories Certain engine controls and accessories are approved for use on the engine. These (see Note 13) controls and accessories are listed in the FAA approved Honeywell Aerospace Service Bulletin ATF3-72-6003. Center of Gravity Refer to Installation Manual, IM-2800, Section 3, for center of gravity with standard equipment as well as optional accessories. Principle Dimensions: length (including spinner) 102.8 inches (-6) 101.97 inches (-6A) width 33.7 inches The undrainable fuel and oil weight shall not exceed 13.4 pounds. This includes 18.25 pounds for the remotely mounted electronic fuel control. The engine weight shown herein is that of the power section and all components coded "E" in the Engine Parts List. The total engine weight, including the weight of items coded "A" in the Engine Parts List, is included on the engine installation drawing for each specific aircraft configuration. Fuel Fuels conforming to the following Honeywell Aerospace Specifications: EMS 53111 (Jet A type) EMS 53112 (Jet A-1 and JP-8 type) EMS 53113 (Jet B and JP-4 types) EMS 53116 (JP-5 type) Fuel Additives SOHIO Biobar JF biocide additive is approved for use in the fuel at a concentration not to exceed 20 ppm of elemental boron. Model Number ATF3-6 ATF3-6A-3 ATF3-6A-4 Total dry weight 1165.2 1186.4 1165.3 Total wet weight 1194.6 1215.8 1194.7 E7WE 3 of 7 Shell ASA-3 anti-static additive, in amounts to bring fuel up to 300 conductivity units is permissible except that in no event shall the additive exceed 1ppm. MIL-DTL-85470 "D" or "E" inhibitor, icing, fuel system is approved for use in the fuel in amounts up to 0.15 percent by volume. Oil Oil must conform to Honeywell Aerospace Specification EMS 53110, Type II (MIL-PRF-23699). The ATF3-6 engine has a self-contained oil system and does not require an aircraft installed oil tank. Certification Basis: 14 CFR Part 33, dated April 3, 1967, and amendments 33-1 through 33- 8, and Exemption Number 2566, dated June 8, 1978, which provided an exemption to §§33.27 and 33.88. Dated of application for type certificate was October 28, 1974. Type Certificate Number E7WE issued dated May 15, 1981, for the ATF3-6 and March 8, 1982, for the ATF3-6A. Production basis: Production Certificate Number 413NM, issued to Honeywell Aerospace US LLC on March 29, 2026. NOTE 1: Maximum permissible engine rotor speeds are: Maximum permissible three-hour engine windmilling speeds (rpm) are: ATF3-6 ATF3-6A Fan rotor (N1) (-6) 2835 (27.3%) (26.5%) Low pressure rotor (N2) 1516 (8.8%) (8.8%) High pressure rotor (N3) 4768 (12.9%) (12.9%) NOTE 2: Maximum permissible temperatures: Continuous RPM (percent) 30-Second Transient RPM (percent) 5- Second Transient RPM (percent) Fan Rotor (N₁) (-6A) 10,700 (100.0) 10,700 (100.0) 10,700 (100.0) Fan Rotor (N₁) (-6) 10,400 (100.0) 10,400 (100.0) 10,400 (100.0) Lower pressure rotor (N2) 17, 200 (100.0) 17,286 (100.5) 17,544 (102.0) High pressure rotor (N3) 36,900 (100.0) 37,269 (101.0) 38,008 (103.0) Interstage Turbine Temperature (ITT): Takeoff (5 minute) 1850°F (1010°C) Takeoff (5 second transient) Maximum continuous Starting Starting (5 second transient) 1868°F 1778°F 1850°F 1868°F (1020°C) (970°C) (1010°C) (1020°C) E7WE 4 of 7 NOTE 2: (continued) Engine external components, maximum temperature (limiting temperature of specific components are as specified in the Engine Installation Manual IM-2800, Section 12.) NOTE 3: Pressure Limits (psig): Oil Pressure Takeoff, climb, flight idle and cruise 55 to 83 Ground idle 30 to 83 Transient (3 minutes maximum) 90 (maximum) (Refer to IM-2800) Fuel Pressure Maximum 50 Minimum 5 psi above true vapor pressure Note: An 8-mesh or finer screen must be provided upstream of the engine fuel inlet. NOTE 4: Maximum fuel vapor/liquid ration is 0.45. (Refer to IM-2800). NOTE 5: Engine ratings are based on calibrated test stand performance under the following conditions: a) No load on accessory drives. b) No compressor or fan bleed airflow. c) Bellmouth inlet conforming to Honeywell Aerospace Drawing SKP22514, included in the drawing section, with inlet ram recovery of 100 percent. d) Fan duct and exhaust nozzle conforming to Honeywell Aerospace Drawing 3001120, included in the drawing section. Nominal physical exhaust nozzle throat area is 405 square inches. e) No anti-icing airflow. f) 0.2 percent cooling air extracted from the fan discharge bypass flow to maintain specified component temperatures in Zone II (tailcone). (Refer to IM-2800.) g) Interstage Turbine Gas Temperature (ITT) and rotor speed limits not exceeded. h) Test stand data corrected to reflect any deviation from U.S. Standard Atmosphere of 59°F and 29.92 in.Hg. sea level, static conditions. i) At sea level static conditions below 46°F the ATF3-6 engine has a flat rated Oil temperature °F (°C) Takeoff (maximum) 360 (182) Takeoff (minimum) 122 (50) Continuous operation (maximum) 360 (182) Continuous operation (minimum) 122 (50) Starting (minimum) -40 (-40) Transient (3 minutes) 370 (188) Engine fuel inlet temperature °F (°C) Maximum (refer to IM-2800) 135 (57) Minimum (refer to IM-2800) 65 (-54) E7WE 5 of 7 maximum continuous thrust of 5440 lbs. and above 46°F is rated at a constant ITT of 1778°F. j) At sea level static conditions below 71°F the ATF3-6 engine has a flat rated takeoff thrust of 5440 lbs. and above 71°F is rated at a constant ITT of 1850°F. k) At sea level static conditions below 46°F the ATF3-6A engine has a flat rated maximum continuous thrust of 5440 lbs. and above 46°F is rated at a constant ITT of 1778°F. l) At sea level static conditions below 70°F the ATF3-6A engine has a flat rated takeoff thrust of 5440 lbs. and above 70°F is rated at a constant ITT of 1850°F. NOTE: Refer to Installation Manual, IM-2800, Section 14, for uninstalled takeoff, and maximum continuous, and maximum climb power setting curves. NOTE 6: Maximum engine oil consumption rate is 0.07 gallon per hour measured over a 10-hour period. N OTE 7: A ccessory Drive AS Standard Drive Type (1 each) AS Mating Flanage Rotation Direction (facing drive pad) Drive to Rotor Ratio with N3 at 36,900 Maximum Torque (lb.- in.) Accessory Weight Pounds Maximum Tc To Ts Aircraft Accessory - D1 468-A6C-1, Rev B (modified) 471 CW 0.340 355 500 1690 60 Starter Generator - D2 468-A6C-1, Rev B (modified) 471 CW 0.207 500 750 2530 65 Hydraulic Pump - D3 961, Rev. A (modified) 962-1P CCW 0.214 250 375 1650 12 Hydraulic Pump - D4 961, Rev. A (modified) 962-1P CCW 0.166 320 480 1622 40 CW = Clockwise CCW =Counterclockwise Tc = Continuous Torque To =Torque Overhead Ts = Static Torque R efer to IM-2800, Section 9, Figure 9-1 for total accessory shaft horsepower available for extraction from accessory drives. P ads D3 and D4 are modified for 0.343-inch groove depth and 0.264- inch minimum groove width. E7WE 6 of 7 A speed-reducing gearbox suitable for mounting on the Permanent Magnet Generator (PMG) is available as an option. With this gearbox installed on Pad D1, the accessory drive pad is identified as D4. The estimated torsional spring constant for the starter-generator drive is 126,000 lb.-in per radian. Maximum windmilling accessory power extraction and aerodynamic drag are provided n Section 9 of IM-2800. NOTE 8: A total bleed airflow equal to a maximum of 8.5 percent of the engine core airflow may be extracted from the four bleed ports, provided not more than 5 percent of the gas generator airflow is extracted from the high-pressure bleed ports. NOTE 9: These engines meet FAA requirements for operation in icing conditions within the envelope defined in 14 CFR Part 25, Appendix C, in effect on the date on which the original engine type certificate was issued. NOTE 10: Certain engine parts are life limited. These limits are listed in the FAA- approved Honeywell Aerospace Service Bulletin ATF3-72-6001. NOTE 11: Power setting, power checks and control of engine thrust output in all operations is based on Honeywell Aerospace engine charts which refer to fan rotor speed (N1) and are contained in Section 14 of the Installation Manual, IM-2800. Speed sensors are included in the engine assembly for this purpose. NOTE 12: These engines are certified for use with electronic/hydromechanical fuel control. The electronic computer is essential for takeoff operations and must be installed in accordance with instructions provided in Section 12 of IM-2800. NOTE 13. Variations in engine configuration, installation components, and derated thrust are identified by a suffix in the basic model number on the engine nameplate;, i.e., ATF3-6-XY, (“X” denotes Honeywell Aerospace installed configurations rating code number(s) and “Y” denotes Honeywell Aerospace equipment code letter(s) of aircraft manufacturer), Engine Parts List number. These variations are influenced by aircraft design n considerations. In the Engine Parts List, those items coded "E" are basic engine items and are controlled by 14 CFR Part 33. 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 associated with these factors is the responsibility of the aircraft manufacturer. NOTE 14: Maximum allowable steady-state engine air inlet distortion limits for stall-free operation are provided in Section 8 of IM-2800. NOTE 15: Time for first overhaul: These engines are of modular construction, as described in IM-2800. Inspection intervals for each of these modules is provided in FAA- approved Honeywell Aerospace Service Bulletin ATF3-72-6002. E7WE 7 of 7 NOTE 16: These engines are in compliance with the fuel venting emission requirements of Special Federal Aviation Regulations No. 27, Section 15(a)(3). NOTE 17: For additional authorized operation and installation detailed information, see FAA-approved sections of the Engine Installation Manual, IM-2800. ----------------------------------END----------------------------------