TCDS E00085EN

* PAGE 1 2 3 4 5 6 7 REV. 2 3 2 2 3 2 2 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET TCDS NUMBER E00085EN REVISION: 3 GE Honda Aero Engines MODELS: HF120 DATE: October 7, 2024 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00085EN) and other approved data on file with the Federal Aviation Administration, 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 (TC) HOLDER: GE Honda Aero Engines 2987 Tucker Street Burlington, NC 27215 MODELS: HF120 TYPE The HF120 engine is a dual rotor, medium bypass ratio turbofan with a single stage fan, 2-stage low pressure compressor, single stage radial flow high pressure compressor, single annular reverse flow combustor, single stage high pressure turbine, 2-stage low pressure turbine, lobed exhaust mixer, and a full authority digital engine control (FADEC). RATINGS (see NOTE 1) Maximum Continuous at sea level, static thrust, lb -H1A configuration 2057 1922 Takeoff 5-minute (see NOTE 13) at sea level, static thrust, lb -H1A configuration 2095 2037 Flat rating ambient temperature for Takeoff and Maximum Continuous 77°F/25°C COMPONENTS / CONFIGURATIONS For information regarding components and engine configuration, refer to the approved parts list: Fuel Pump Metering Unit Motive Flow 24100-Q0A Full Authority Digital Engine Control (FADEC) Hardware 34100-Q0A FADEC Software OS 34211-Q0A FADEC Software AS 34221-Q0A Ignition System One ignition unit Two igniter plugs 31311-Q0A 31111-Q0A TCDS E00085EN PAGE 2 PRINCIPAL DIMENSIONS (in) Length (fan duct front flange to aft end of rear fan duct) 59.5 in Width (maximum envelope) 25.8 in Height (maximum envelope) 30.5 in WEIGHT (DRY) (lbs) Includes basic engine, basic engine accessories, and optional equipment as listed in the manufacturer’s engine specifications. 466 lbs CENTER OF GRAVITY LOCATIONS (in) (Engine only) Station (axial) 207.6 in Waterline 99.9 in Buttline 97.5 in FUEL Refer to HF120 Service Bulletin 73-0001 and its latest revision for detailed information pertaining to fuels and additives. This Service Bulletin lists the eligible fuels and additives conforming to GE Aviation Specification D50TF2 (Class A and C only). OIL Refer to HF120 Service Bulletin 79-0001 and its latest revision for detailed information pertaining to Type 2 oils. This Service Bulletin lists the approved oils conforming to GE Aviation Specification D50TF1. CERTIFICATION BASIS HF120 • 14 CFR Part 33, effective February 1, 1965, as amended by 33-1 through 33-30. • 14 CFR Part 34,effective September 10, 1990, as amended by 34-1 through 34-7A. See NOTE 11 for detailed summary of the certification basis for fuel venting and exhaust emissions. • Equivalent Level of Safety (ELOS) Findings: ELOS No. TC2596EN-E-P-1 to 14 CFR § 21.21 and 33.68(b) TYPE CERTIFICATE E00085EN MODELS APPLICATION DATE ISSUED/AMENDED HF120 February 27, 2007 December 13, 2013 PRODUCTION BASIS HF120 Production Certificate numbers 347CE and 108 TCDS E00085EN PAGE 3 NOTES NOTE 1. ENGINE RATINGS Guaranteed performance is based on sea level static (SLS) standard day conditions with a referee cowl system and with the items listed below. • Specified fuel that has an average lower heating value of 18,576 BTU/lb • No loading of the accessory drive pads • No high pressure (HP) extraction for motive flow • No air bleed from customer ports • No anti-icing bleed • No inlet distortion • No inlet screen losses • 100 percent ram recovery • No humidity NOTE 2. MAXIMUM PERMISSIBLE TEMPERATURES Indicated Interstage Turbine Temperature (ITT) Takeoff 5-minute (see NOTE 13) 1580°F (860°C) Transient 2-minute 1625°F (885°C) Maximum Continuous 1569°F (854°C) Ground starts (manual or auto) 1033°F (556°C) Inflight starts (manual or auto) 1033°F (556°C) Indicated plane 4.5 ITT is synthesized by the ECU from sensed plane 4.9 gas temperature. Indicated Oil Temperature Continuous 290°F (143°C) Transient (15 minutes) 330°F (165°C) NOTE 3. FUEL AND OIL PRESSURE LIMITS Fuel Pressure at the engine pump inlet Minimum: True vapor pressure plus 5.0 psi or ambient plus 5.0 psi, whichever is greater Maximum: 50 psig with aircraft boost operative Indicated Oil Pressure Varies as a function of core rotor speed (N2), see Operating Instructions GEK 112116. NOTE 4. ACCESSORY DRIVE CHARACTERISTICS Accessory Rotation Facing Gearbox Pad Gear Ratio to Core Rotor Maximum Steady State Drive Shaft RPM Maximum Weight LB Maximum Overhung Moment IN-LB Shear Torque IN-LB Maximum Continuous Torque IN-LB See Comments B,C Starter/Generator CW 0.2511 12,354 45 265 1600 222 Comments: A. Maximum core engine speed is 49,200 rpm. B. Maximum continuous overload torque for the SG pad is 302.5 in-lb at 6001 rpm for 5 minutes (28.8 hp). C. Maximum transient overload torque for the SG pad is 360.3 in-lb at 6001 rpm for 5 seconds (34.3 hp). D. Maximum horsepower extraction at the SG pad is 24.2 hp. TCDS E00085EN PAGE 4 NOTE 5. MODEL DESCRIPTION The HF120 is the certified baseline engine model and is limited to installation on the HA-420 aircraft. The HF120-H1A configuration is a fully capable baseline HF120 that is derated for service by the FADEC software in order to accommodate HA-420 aircraft power management. The data in this TCDS applies to the baseline HF120 and all configurations unless stated otherwise. NOTE 6. ENGINE TYPE DESIGN ACCESSORIES, COMPONENTS, SYSTEM ASSEMBLIES WITH AIRCRAFT- LEVEL REQUIREMENTS PROVIDED AS PART OF ENGINE TYPE DESIGN: Not applicable. NOTE 7. AIRCRAFT ACCESSORIES, COMPONENTS OR SYSTEM ASSEMBLIES INSTALLED ON THE ENGINE BUT ARE NOT PROVIDED AS PART OF THE ENGINE TYPE DESIGN: The following aircraft type design accessories are engine-mounted or engine-interfacing: Starter-Generator Fuel inlet fitting Fire detection sensor Bleed air ducting (ECS and anti-ice, see NOTE 21) Nacelle inlet ECU electrical harnesses Mount system components (see NOTE 9) NOTE 8. SPECIAL ANTI-ICING OR DE-ICING REQUIREMENTS None. NOTE. 9. ENGINE MOUNT SYSTEM Three aft mount lugs on the Aft Mount Ring installed between the Combustor Case and the Rear Fan Duct flanges. Four forward mount pads on the intermediate case. Attachment hardware is provided by the installer and must meet the engine specifications in engine Installation Manual GEK 112115. NOTE 10. POWER BOOST, INJECTION AND AUGMENTATION SYSTEMS None. TCDS E00085EN PAGE 5 NOTE 11. SPECIAL INSTALLATION REQUIREMENTS (1) The HF120 does not support ETOPS, reverse thrust or hydraulic fluid systems. There are no special installation requirements for FOD protection, EMI/lightning protection, induction system icing protection, EGT shunting or aircraft software criticality level. (2) Time Limited Dispatch (TLD) Criteria pertaining to the dispatch and maintenance requirements for the engine control systems are specified in the HF120-H1A FADEC Control System TLD Summary for Honda Aircraft HA-420, GEK 112118-H1 and the Airworthiness Limitations Section of the engine Line Maintenance Manual, GEK 112112-H1, which defines the various configurations and maximum operating intervals. (3) Emissions and Fuel Venting The following emissions standards promulgated in 14 CFR Part 34, Amendment 7A, effective May 24, 2024, and 40 CFR Part 1031, effective December 23, 2022, have been complied with for the HF120 and the –H1A configuration: • Fuel Venting emission standards: 14 CFR 34.11; in addition, 40 CFR 1031.30(b) • Smoke Number (SN) emission standards: 14 CFR 34.21(e); in addition, 40 CFR 1031.50(a) 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, Fourth Edition, Amendment 10, effective July 20, 2022, have also been demonstrated for the following: • Part II, Chapter 2 for Fuel Venting • Part III, Chapter 2, Section 2.2.2 for Smoke number NOTE 12. MANUFACTURER’S SERVICE BULLETINS AND OTHER SPECIAL INSTRUCTIONS SB 71-0000 Recommended Engine Maintenance and Inspection Program SB 73-0001 Requirements for and Approval of Fuel and Additives SB 79-0001 Approved Oils NOTE 13. SPECIAL OPERATING PROCEDURES AND LIMITATIONS It is permissible to operate below minimum oil pressure for a maximum of 15 seconds during negative G operations, see engine Operating Instructions GEK 112116. 5-minute Takeoff conditions may be extended to 10 minutes for engine failure contingency, see engine Operating Instructions GEK 112116. Operation in icing conditions, see engine Operating Instructions GEK 112116. NOTE 14. SPECIAL REPAIR AND OVERHAUL LIMITATIONS None. NOTE 15. PRIMARY ENGINE MANUALS Installation Manual GEK 112115 Operating Instructions GEK 112116 Line Maintenance Manual GEK 112112-H1 Overhaul Manual GEK 112114-H1 Time Limited Dispatch Summary GEK 112118-H1 The “-H1” titled manuals are not specific to the HF120-H1A configuration. NOTE 16. FOREIGN MANUFACTURED ENGINE IMPORTS None. TCDS E00085EN PAGE 6 NOTE 17. LIFE LIMITED PARTS Life limited engine parts are addressed in Line Maintenance Manual GEK 112114-H1 Airworthiness Limitations Sections 05-11 and 05-21. NOTE 18. MILITARY MODEL INFORMATION Not applicable. NOTE 19. MAXIMUM PERMISSIBLE ROTOR SPEEDS Low pressure rotor (N1) 19,055 RPM (100.0%) High pressure rotor (N2) 49,200 RPM (100.9%) Note: 100 percent N2 is 48,777 RPM NOTE 20. OUTPUT SHAFT TORQUE LIMIT Not applicable. TCDS E00085EN PAGE 7 NOTE 21. BLEED AIR EXTRACTION Engine Bleed Air Extraction Limits (See Comment A) Pressure Altitude feet CDP Bleed Flow lbm/min (% of W25) HP Bleed -1000 41.0 (17.0%) -1000 to 46,000 Linear Transition between -1000 feet and 46,000 feet altitude 46,000 22.2 (15.0%) Pressure Altitude feet Fan Bleed Flow % of W2 Fan Bleed All altitudes 1.0% HP Bleed Air Extraction Limits Above 26,000 feet (See Comment A) Pressure Altitude feet CDP Bleed Flow lbm/min HP Bleed 26,000 17.1 (10.0%) 26,000 to 46,000 Linear Transition between 26,000 feet and 46,000 feet altitude 46,000 12.8 (12.0%) HP Bleed Air Extraction Limits Below 26,700 RPM Core Speed (See Comments A, B) Core Speed RPM CDP Bleed Flow lbm/min (% of W25) HP Bleed 23,900 36.0 (19.0%) 23,900 to 26,700 Linear Transition between 23,900 RPM and 26,700 RPM Core Speed 26,700 41.0 (19.0%) Comments A. Bleed extraction limit details are described in engine Installation Manual GEK 112115. B. Bleed extraction below 26,700 RPM applies to all regions of the environmental operating envelope at ground idle. NOTE 22. ROTOR DISK INTEGRITY AND BLADE CONTAINMENT (where special requirements apply) No special requirements. ….. END …..