TCDS E00010LA

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E00010 LA Revision 13 Honeywell Aerospace US LLC AS907-1-1A AS907-2-1A AS907-2-1G AS907-2-1S AS907-3-1E September 10, 2026 TYPE CERTIFICATE DATA SHEET NO. E00010LA Engi nes of models described herein conforming with this data sheet (which is part of Type Certificate No. E00010LA) and other approved data on file with the Federal Aviation Administration (FAA), meet the minimum standards for use in certificated aircraft in accordance with 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 RECORD HOLDER: Honeywell International Inc. 111 South 34th Street Phoenix, AZ 85034 Models: AS907-1-1A, AS907-2-1A, AS907-2-1G, AS907-2-1S, AS907-3-1E Type: Turbofan: One stage fan, four stage axial flow high pressure compressor, one stage centrifugal high pressure compressor, annular combustor, two stage high pressure turbine, and three stage low pressure turbine. Static Thrust Ratings: (see NOTE 4 and NOTE 12) Max Continuous, Takeoff, at Ambient at Ambient Temperature, Temperature, at Sea Level, lbs. Model at Sea Level, lbs. (see NOTE 10) AS90 7-1-1A 6,929 at ISA + 15ºC 6,944 at ISA + 20ºC AS907-2-1A 7,530 at ISA + 14ºC 7,530 at ISA + 20ºC AS907-2-1G 7,337 at ISA + 17ºC 7,765 at ISA + 17ºC AS907-2-1S 7,428 at ISA + 15ºC 7,665 at ISA +18.9ºC AS907-3-1E 7,335 at ISA + 22.5ºC 7,638 at ISA + 18ºC Cont rols: Fuel control and power management are controlled by a Full Authority Digital Electronic Control (FADEC) system which features a dual-channel electronic control in the form of two electronic control units (ECUs). The hardware and software configurations of this system and the associated engine hydromechanical unit with integral fuel pump are controlled by the approved Engine Equipment List (see NOTE 13). Page No. 1 2 3 4 5 6 Rev. No. 13 13 13 13 13 13 E00010LA 2 Principal Dimensions: Refer to the engine installation drawing for dimensions and center of gravity location. We ight, Dry, Pounds (maximum): Mode l Lbs. AS9 07-1-1A 1,534 AS907-2-1A 1,534 AS907-2-1G 1,534 AS907-2-1S 1,534 AS907-3-1E 1,514 The engine weight includes all components of the basic engine as defined by the approved Engine Equipment List. Components that are certified as part of the aircraft under Title 14 CFR part 25, which are mounted on the engine, are not included in the basic weight. Fu el: Fuels conforming to Honeywell Aerospace US LLC Specifications EMS53111 (Jet A Type), EMS53112 (Jet A-1 and JP-8 Types), EMS53113 (Jet B and JP-4 Types), and EMS53116 (JP-5 Type). No fuel control adjustment is required when changing from primary to alternate fuels. Re fer to engine installation manual for approved fuel types and fuel additives (see NOTE 12). Oi l: Oil conforming to Honeywell Aerospace US LLC Specification EMS53110, Type II. Refer to engine installation manual for approved engine oils (see NOTE 12). Cer tification Basis: AS9 07-1-1A and AS907-2-1G • 14 CFR part 33, effective February 1, 1965, as amended by 33-1 through 33-20, effective December 13, 2000. • 14 CFR part 34, effective September 10, 1990, as amended by 34-1 through 34-7A, effective May 24, 2024. Fuel Venting and Exhaust Emissions Standards; See NOTE 15. AS9 07-2-1A • 14 CFR part 33, effective February 1, 1965, as amended by 33-1 through 33-33, effective September 20, 2012, excluding Amendments 33-22 and 33-31. • 14 CFR part 34, effective September 10, 1990, as amended by 34-1 through 34-7A, effective May 24, 2024. Fuel Venting and Exhaust Emissions Standards; See NOTE 15. AS9 07-2-1S and AS907-3-1E • 14 CFR part 33, effective February 1, 1965, as amended by 33-1 through 33-33, effective September 20, 2012, excluding Amendment 33-22. • 14 CFR part 34, effective September 10, 1990, as amended by 34-1 through 34-7A, effective May 24, 2024. Fuel Venting and Exhaust Emissions Standards; See NOTE 15. En gine Table of Models Model Date of Application Type Certificate Issued 1st Production Date AS907-1-1A November 4, 1998 June 25, 2002 May 29, 2003 AS907-2-1G April 20, 2006 March 18, 2011 March 25, 2011 AS907-2-1A August 31, 2012 May 13, 2014 May 14, 2014 AS907-3-1E February 26, 2009 July 7, 2014 July 12, 2014 AS907-2-1S September 7, 2015 August 25, 2017 September 28, 2017 E00010LA 3 Production Basis: Production Certificate No. 413, issued March 4, 1965. Reissued Production Certificate No. 413NM to Honeywell Aerospace US LLC on March 29, 2026. NOTE 1. Maximum permissible operating speeds for the low and high-pressure rotors of the engine are as follows: Model Low-Pressure Rotor Speed (N1), RPM High-Pressure Rotor Speed (N2), RPM Maximum Continuous Takeoff (see NOTE 10) Maximum Transient (20 Seconds Maximum) Maximum Continuous Takeoff (see NOTE 10) Maximum Transient (20 Seconds Maximum) AS907-1-1A 9,723 9,812 9,957 27,319 27,568 28,075 AS907-2-1A 9,800 9,830 9,957 27,530 27,714 28,075 AS907-2-1G 9,800 9,830 9,957 27,599 27,714 28,075 AS907-2-1S 9,800 9,830 9,957 27,599 27,714 28,075 AS907-3-1E 9,830 9,830 9,957 27,599 27,714 28,075 NOTE 2. Temperature Limits: Maximum indicated Interturbine Temperature (ITT) Limits: ºF (ºC) Max. Takeoff Starting Model Continuous (See NOTE 10) (Ground/Air) Transient AS907-1-1A 1,702 (928) 1 ,735 (946) * 1,764 (962)** AS907-2-1A 1,742 (950) 1,751 (955) * 1,778 (970)** AS907-2-1G 1,742 (950) 1,751 (955) * 1,778 (970)** AS907-2-1S 1,742 (950) 1,751 (955) * 1,778 (970)** AS907-3-1E 1,742 (950) 1,751 (955) * 1,778 (970)*** * Varies with N2, refer to engine installation manual (see NOTE 12) ** 20 seconds maximum *** 2 minutes maximum Maximum Oil Inlet Temperature Limits: Continuous, Transient °F (°C) (2 Minutes Max.), °F (°C) 280 (138) 310 (154) External engine components maximum temperature (limiting temperature of specific components) is approved as specified in the engine installation manual (see NOTE 12). Operation at an engine fuel inlet temperature as high as 185ºF (85ºC) for the AS907-1-1A, AS907- 2-1A, AS907-2-1G and AS907-2-1S engines and 131ºF (55ºC) for the AS907-3-1E engine with a vapor volume to liquid volume ratio (V/L) equal to 0.45, and as low as -65ºF (-54ºC) with fuel at a viscosity of 12.0 centistokes or less during starting is approved as specified in the engine installation manual (see NOTE 12). NOTE 3. Fuel and Oil Pressure Limits: Fuel pump inlet pressure: Minimum - Whichever is highest of the following: (a) 5 psi above the true vapor pressure of the fuel; E00010LA 4 (b) Pressure corresponding to a V/L ratio of 0.45; (c) 35% of atmospheric pressure; (d) 2 psia. Maximum: (a) 35 psig. Oil Pressure: Oil pressure is not regulated and pressure limits vary with N2. Refer to engine installation manual (see NOTE 12). NOT E 4. The ratings are based on static test stand operation and under the following conditions: (a) No loading of aircraft accessory drives; (b) No aircraft bleed air extraction; (c) Fan exhaust and turbine exhaust nozzles conforming to Honeywell Aerospace US LLC Drawings N10780-1 and N10781-1; (d) Bellmouth inlet conforming to Honeywell Aerospace US LLC Drawing 5837800-1; (e) Dry inlet air; (f) No exhaust nozzle back pressure; (g) Static Thrust Ratings ambient temperature at breakpoint. NOT E 5. Accessory Drive Provisions: Accessory Drive Drive Type (One Each) Internal Spline Configuration RPM and Rotation Facing Drive End Note (b) Accessory Maximum Torque (lb-in) Maximum Weight (Pounds) Maximum Overhung Moment (lb-in)** Tc To Ts Generator/ Alternator D30* (AS907-1-1A, AS907-2-1A, and AS907-2-1G) AS468B-AV1 modified as follows: RPM, torques, accessory weight, and moment as shown. AS468B 13,665 Note (a) CW 242 363 1,600 34.7 128.5 Generator/Alternator D30* (AS907-2-1S and AS907-3-1E) AS468B-AV1 modified as follows: RPM, torques, accessory weight, and moment as shown. AS468B 13,665 Note (a) CW 242 363 1,600 40.7 190 Hydraulic Pump D10* (AS907-1-1A, AS907-2-1A, AS907-2-1G, and AS907-2-1S) AS468B-AV1 modified as follows: RPM, torques, accessory weight, and moment as shown. AS468B 5,974 Note (a) CW 250 375 1,544 22.3 103.9 Hydraulic Pump D10* (AS907-3-1E) AS468B-AV1 modified as follows: RPM, torques, accessory weight, and moment as shown. AS468B 5,974 Note (a) CW 250 388 1,544 22.3 103.9 CW = Clockwise Tc = Continuous Torque To = Torque Overload (5 minutes per 4 hour period) Ts = Static Torque * Accessory pads are identified by these symbols on the engine installation drawing. ** At quick attach/detach (QAD) interface. Notes: (a) Drive speeds are based on a 100% design N2 of 28,100 rpm. (b) Total combined accessory power extraction limits are specified in the engine installation manual (see NOTE 12). NOTE 6. For aircraft bleed airflow limits, refer to the engine installation manual (see NOTE 12). E00010LA 5 NOTE 7 . For the AS907-1-1A, AS907-2-1A, AS907-2-1G, and AS907-2-1S engine aircraft installations, fuel from the engine pump is extracted to drive jet or turbine pumps in the aircraft fuel system (motive flow). Refer to the engine installation manual (see NOTE 12). The AS907-3-1E engine fuel pump does not drive aircraft system motive flow. NOTE 8 . The engine meets FAA requirements for operation in icing conditions within the envelope defined in Title 14 CFR part 25, Appendix C. NOTE 9 . Certain engine parts are life-limited. These limits are included in the engine Light Maintenance Manual, Airworthiness Limitations Section. NOTE 1 0. The normal 5-minute takeoff time limit may be extended to 10 minutes for engine out contingency. NOTE 1 1. Power setting, power checks, and control of engine thrust output in all operations are based on N1. Speed sensors are included in the engine assembly for this purpose. NOTE 1 2. For additional performance, authorized operation, and installation detailed information, refer to FAA-approved sections of the engine installation manual as follows: Model A S907-1-1A: 24-IM-8014 Model AS907-2-1A: 24-IM-8014 Model AS907-2-1G: 24-IM-8029 Model AS907-2-1S: 24-IM-8034 Model AS907-3-1E: 24-IM-8030 NOTE 1 3. The engine control systems has been approved for Time Limited Dispatch (TLD) operations, and the airworthiness limitations pertaining to the maximum approved dispatch intervals and maintenance requirements of the engine control system are specified in the engine Light Maintenance Manual, Airworthiness Limitations Section. NOTE 1 4. Recommended engine inspection intervals are included in the engine Light Maintenance Manual, Chapter 5. NOTE 1 5. The following emissions standards promulgated in 14 CFR part 34, Amendment 34-7A, effective May 24, 2024, and 40 CFR part 1031, effective December 23, 2022, have been complied with for all models listed in Engine Table of Models. • Fuel V enting Emission Standards: 14 CFR §§ 34.10(b) and 34.11; in addition, 40 CFR § 1031.30(b). • Smoke Number (SN) Emission Standards: 14 CFR § 34.21(e)(2); in addition, 40 CFR § 1031.60(a)(5). • Carbon Monoxide (CO) Emission Standards: 14 CFR § 34.21(d)(1)(ii); in addition, 40 CFR § 1031.60(d). • Hydrocarbons (HC) Emission Standards: 14 CFR § 34.21(d)(1)(i); in addition, 40 CFR § 1031.60(c). • Oxides of Nitrogen (NOx) Emission Standards: 14 CFR § 34.23(b)(1); in addition, 40 CFR § 1031.60(e)(5) • Non-volatile Particulate Matter (nvPM) Mass Concentration Standards: 14 CFR § 34.25(a)(1); in addition, 14 CFR § 1031.60(a)(6). • nvPM Mass and Number Emission Standards: 14 CFR § 34.25(a)(2); in addition, 14 CFR § 1031.60(b)(2). E00010LA 6 In addition to the FAA’s finding of compliance based on the certification requirements defined in this TCDS, the engine manufacturer has declared that the ICAO emissions standards identified in Annex 16, Volume II, Fifth Edition, Part III, Chapter 2, Section 2.2.2 for SN, Section 2.3.2 for CO and HC, Section 2.3.2.e for NOx (also known as CAEP/8), Chapter 4, Section 4.2.2.1 for nvPM Mass concentration (also known as CAEP/10), Section 4.2.2.2.a.1 for nvPM LTO Mass (also known as CAEP/11), Section 4.2.2.2.b.1 for nvPM LTO Number (also known as CAEP/11), and Part II Chapter 2 for fuel venting have also been demonstrated. NOT E 16. Model description – similarities, differences, and special characteristics: Model Model Description AS907-1-1A One stage fan, four stage axial flow high-pressure compressor, one stage centrifugal high-pressure compressor, annular combustor, two stage high-pressure turbine, and three stage low-pressure turbine. AS907-2-1G Same as AS907-1-1A except increased thrust ratings and ITT and rotor speed limits, modified centrifugal compressor and high- and low-pressure turbine nozzles, improved combustion system, provisions for customer fan bleed, a new exhaust mixer nozzle system, and modified FADEC system software. AS907-2-1A Same as AS907-2-1G except modified thrust ratings and maximum continuous N2 rotor speed limit, select installation interface parts, and updated ECUs and software. AS907-3-1E Same as AS907-2-1A except modified thrust ratings and ITT transient time and maximum continuous rotor speed limits, modified fan inlet housing, modified fan outer bypass duct and aft mounting system, non-variable stage 1 compressor vanes, modified compressor and combustor cases, increased accessory drive limits, modified generator quick attach-detach (QAD), modified air turbine starter, and modified FADEC system software. AS907-2-1S Same as AS907-2-1A except modified thrust ratings and maximum continuous N2 rotor speed limit, air turbine starter, select installation interface parts, and modified FADEC system software. NOT E 17. The engine type design does not include a thrust reverser (T/R). Considerations for the installation of a thrust reverser are contained in the engine installation manual (see NOTE 12). The engines have demonstrated compatibility with the following thrust reversers: Mode l T/R Manufacturer T/R Part Numbers Left Hand Right Hand AS907-1-1A Safran Nacelles (formerly Aircelle and Hurel- Hispano) Per T/R installation drawing 13A025-03-0G Per T/R installation drawing 13A026-02-0G Per T/R installation drawing 13A016-00-0G Per T/R installation drawing 13A017-00-0G AS907-2-1G Safran Nacelles (formerly Aircelle) Per T/R installation drawing31A516-01-0G Per T/R installation drawing 31A517-01-0G AS907-2-1A Safran Nacelles (formerly Aircelle) Per T/R installation drawing 33A016-01-0G Per T/R installation drawing 33A017-01-0G AS907-3-1E Safran Nacelles (formerly Aircelle) Per T/R installation drawing 32A716-02-0G Per T/R installation drawing 32A717-02-0G AS907-2-1S Safran Nacelles (formerly Aircelle) Per T/R installation drawing 35L0016-00-0 Per T/R installation drawing 35L0017-00-0 …END …