TCDS E00095EN

PAGE 1 2 3 4 5 6 7 8 9 REV. 4 0 4 3 3 0 4 3 0 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" INDICATES “NOT APPLICABLE” NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00095EN TCDS NUMBER E00095EN REVISION: REVISION 4 DATE: 18 December 2024 GENERAL ELECTRIC COMPANY MODELS: GE9X-105B1A GE9X-105B1A1 GE9X-105B1A2 GE9X-105B1A3 Engines of model described herein conforming with this data sheet (which is part of Type Certificate Number E00095EN) 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: General Electric Company GE Aerospace 1 Neumann Way Cincinnati, OH 45215-6310 I. MODELS GE9X-105B1A GE9X-105B1A1 GE9X-105B1A2 GE9X-105B1A3 TYPE The GE9X engine is a high bypass dual -rotor, axial-flow turbofan. The bypass ratio of the engine is 9.9:1 with an overall pressure ratio of 60:1. The single stage fan contains 16 wide chord composite blades. The high- pressure compressor (HPC) pressure ratio is 27:1. The eleven-stage high pressure compressor (HPC) is driven by a two- stage high pressure turbine (HPT). The fan and three-stage low-pressure compressor (LPC) are driven by a six- stage low- pressure turbine (LPT). A single annular Twin Annulus Premixing Swirler combustor converts fuel and compressor discharge air into energy to drive the turbines. The accessory drive system extracts energy from the high pressure, high speed rotor to drive the engine accessories and the engine-mounted aircraft accessories. The engine is equipped with a dual channel FADEC control system. RATINGS 110,000 (48,930) 103,500 (46,039) 86 (30) 77 (25) - - - - - - - - - - - - - - - - - - - - - - - - (See Note 1.) Static Thrust at Sea Level: lb (daN) • Takeoff (5 min.) • Maximum continuous Flat Rating Ambient Temperature at Sea Level: °F (°C) • Takeoff • Maximum continuous COMPONENTS Part Number Electronic Engine Control Pressure Subsystem Main Fuel Pump Fuel Metering Unit Ignition Exciter Ignitor Data Entry Plug (Rating) Core Configuration Plug EEC Software 2635M32 2635M34 2638M00 2665M23 2635M36 1754M84 2531M61P38 2665M54 2761M48 - - - - - - - - - - - - 2531M61P42 - - - - - - - - - - - - - - - - 2531M61P46 - - - - - - - - - - - - - - - - 2531M61P50 - - - - E00095EN 2 of 9 I. MODELS (Cont.) GE9X-105B1A GE9X-105B1A1 GE9X-105B1A2 GE9X-105B1A3 FUEL • Approved fuels and additives are defined in the Installation Manual and Operating Instructions Manual. Additional information can be found in GE9X Service Bulletin 73- 0001. (See Notes 12 & 15) OIL • Refer to GE9X Service Bulletin SB 79-0001 for detailed information pertaining to Type 2 oils. The Service Bulletin covers the approved oils conforming to General Electric Specification D50TF1 or the latest revisions that are authorized. (See Note 12) PHYSICAL CHARACTERISTICS PRINCIPLE DIMENSIONS Length: in (mm) Fan Spinner to TRF aft most flange Width: in (mm) Nominal Height: in (mm) Nominal 224.0 (5689.6) 161.3 (4097.0) 163.7 (4158.0) - - - - - - - - - - - - - - - - - - WEIGHT (DRY): lb (kg) Includes dry weight Not to Exceed: 21,230 (9630) - - - - - - CENTER OF GRAVITY LOCATION Nominal, Dry Engine Only Station (axial): in (mm) HPC case fwd flange = 200.2 in (5085 mm) Waterline: in (mm) Butt line: in (mm) 223.9 (5687.1) 98.7 (2507.0) 99.8 (2534.9) - - - - - - - - - - - - - - - - - - THIS SPACE INTENTIONALLY LEFT BLANK E00095EN 3 of 9 CERTIFICATION BASIS • 14 CFR part 33, effective February 1, 1965, as amended by 33-1 through 33-34, inclusive • 14 CFR part 34, amendment 7A effective May 24, 2024 • ELOS: None • Special Conditions: • Fan Blade §33.94 – SC No. 33-018-SC, dated 14-April-2017 • Endurance Test §33.87 – SC No. 33-17-02-SC, dated 18-December-2017 • Exemptions: • HPT Aft Shaft Loss of Load §33.27(c) – Exemption No. 17511, dated 29-August-2017 MODEL APPLICATION DATE TC ISSUED / AMENDED GE9X-105B1A 29 January 2016 25 September 2020 GE9X-105B1A1 29 January 2016 25 September 2020 GE9X-105B1A2 29 January 2016 25 September 2020 GE9X-105B1A3 29 January 2016 25 September 2020 PRODUCTION BASIS 1. Production Certificate No. 108 2. Production Limitation Record No. 3 THIS SPACE INTENTIONALLY LEFT BLANK E00095EN 4 of 9 NOTE 1. ENGINE RATING Engine rating is based on calibrated stand performance under the following conditions: Takeoff thrust is nominally independent of ambient temperature (flat rated) up to ambient temperature of: Std + 15°C (30°C, 86°F), except as noted above. Maximum continuous thrust is nominally independent of ambient temperature (flat rated) up to ambient temperature of Std. + 10°C (25°C, 77°F). Assumptions: 1. Sea level static, standard day: 101.325 kPA Pressure (14.696 psia); 15°C temperature (59°F) 2. Zero customer bleed or customer horsepower extraction 3. Ideal inlet, 100% ram recovery 4. Production aircraft flight cowling 5. Production instrumentation 6. Fuel lower heating value of 18,400 BTU/lb (42,798 kJ/kg) Thrust Setting Parameter Power setting, power checks and control of engine thrust output in all operations is to be based on GE Aviation engine charts referring to fan speed. Fan speed sensors are included in the engine assembly for this purpose. NOTE 2. TEMPERATURE LIMITS Indicated Turbine Exhaust Gas Temperature Takeoff, 5 min Maximum Continuous Max Transient (30 sec.) Ground Starts Inflight Starts • Starter Assist or Steady State Windmill • Quick Windmill Relight • High Power Fuel Cut 1087°C (1989°F) 1052°C (1926°F) 1092°C (1998°F) 750°C (1382°F) 875°C (1607°F) 925°C (1697°F) 975°C (1787°F) Fuel Pump Inlet Temperature Maximum Minimum (Cold Start) 65°C (150°F) -40°C (-40°F) Or the relevant fuel freezing point, whichever is higher Oil Temperature Continuous operation Transient (15 minutes) 160°C (320°F) 177°C (350°F) As measured in the oil tank NOTES E00095EN 5 of 9 NOTE 3. FUEL AND OIL PRESSURE LIMITS Fuel Pressure Limits at The Engine Pump Inlet The engine fuel system provides the fuel flows and pressures required for starting and operating the engine throughout the operating envelope with the following fuel pressure provided at the engine pump inlet: • With aircraft boost pumps operative, the fuel pressure at the engine pump inlet ranges from a maximum of 70 psig down to the greater of the true vapor pressure plus 7.0 psi (48.3 kPa) or ambient pressure plus 7.0 psi (48.3 kPa) for engine fuel flow rates less than 5000 lbm/hr (2268 kg/hr), and the greater of the true vapor pressure plus 7.0 psi (48.3 kPa) or ambient pressure plus 5.0 psi (34.5 kPa) for engine fuel flow rates greater than or equal to 5000 lbm/hr (2268kg/hr). • With aircraft boost pumps inoperative (suction feed), the minimum fuel pressure at the engine pump inlet is extended to 3.5 psia (24.1 kPa) during takeoff and climb (maximum vapor-to-liquid ratio (v/l) of 0.45) for up to 60 minutes followed by up to 600 minutes for all other flight phases with minimum fuel pressure of 3.5 psia (24.1 kPa) (maximum vapor-to-liquid ratio (v/l) of 0.28). Oil Pressure Limits • The minimum pressure limit at idle is 10.0 psid (68.9 kPa) and varies up to 32 psid (220.6 kPa) at redline. • The maximum pressure is limited during cold starts by a 425 psid (2930.3 kPa differential) pressure-relief valve. • The oil pressure limits are defined as outlined in the GE9X Installation Manual and Operating Instructions (See Note 12). NOTE 4. GE9X ACCESSORY DRIVE CHARACTERISTICS ACCESSORY DEFINITION ROTATION (NOTE #4a) GEAR RATIO TO CORE ROTOR DRIVE SHAFT at 100% N2 (RPM) (NOTE #4b) MAXIMUM WET WEIGHT LB (KG) MAXIMUM OVERHUNG MOMENT IN-LB (N·m) CONTINUOUS PAD RATING HP (KW) OVERLOAD HP (KW) ACCESSORY SHEAR TORQUE IN-LB (N·m) IDG Installation Drawing 2615M99 CCW 0.805 7698 225 (102.1) (QAD INCL.) 1830 (206.8) 271 (202.1) at GI 298 (222.2) at TO 280 (208.8) at CR SEE NOTE 4c. 15332-17296 (1723-1954) BUG (VSCF) CW 2.415 23093 93.7 (42.5) 635.3 (71.8) 0 kVA Nominal 50 kVA MaxCont 4 (3) at GI 89 (66.4) at GI 17 (12.7) at TO 101 (75.3) at TO 12 (8.9) at CR 98 (73.1) at CR SEE NOTE 4d. 2900-3226 (328-364) HYDRAULIC PUMP 47% Loaded CCW 0.369 3532 43.6 (19.8) 250.7 (28.3) 30 (22.4) at GI 37 (27.6) at TO 42 (31.3) at CR (NOTE #4e) SEE NOTE 4f. 4250-4850 (480-548) HYDRAULIC PUMP 53% Loaded CCW 0.369 3532 43.6 (19.8) 250.7 (28.3) 33 (24.6) at GI 40 (29.8) at TO 46 (34.3) at CR (NOTE #4e) SEE NOTE 4f. 4250-4850 (480-548) CORE TURN (CRANK PORT) 0.5 SQUARE DRIVE CW 0.369 3532 N/A N/A N/A N/A N/A ACCESSORY DRIVE NOTES: a. Rotation is defined facing the pad. b. 100 percent core engine speed is 9561 rpm c. 329 HP at TO for 5 minutes, freq: 1.5 / flight hour 445 Hp for 5 sec, freq: 2,2x10^-2 /flight hour 493 Hp for 5 sec, freq: 1x10^-8 / flight hour (max fault power) d. SINGLE MAIN GENERATOR COND. (at TO SPEED): • 65 Hp for 5 minutes, 0.5x10^-5 / flight hour • 83 Hp for 5 sec, 0.5x10^-5 / flight hour ETOPS CONDITION (at TO SPEED): • 122 Hp for 5 minutes, 0.5x10^-6 / flight hour • 169 Hp for 5 sec, 0.5x10^-6 / flight hour MAX FAULT CONDITION: • 180 Hp for 50 ms max fault power 1x10^-6/ flight hour e. For cruise condition, only one of the two engine driven hydraulic pumps is pressurized f. NORMAL FLIGHT CONDITION (at CR SPEED): • 65 Hp at 47% loaded EDP up to 5 sec Power peaks • 72 Hp at 53% loaded EDP up to 5 sec Power peaks SINGLE ENGINE OPERATION FOLLOWING ENGINE IFSD COND. (at CR SPEED): • 71 Hp at 47% loaded EDP up to 5 sec Power peaks • 78 Hp at 53% loaded EDP up to 5 sec Power peaks DUAL E NGINE OPERATION WITH SINGLE EDP FAILED COND. (at CR SPEED): • 77 Hp up to 5 sec Power peaks EDP OVER PRESSURE FAILURE COND.: • Single EDP at 2000 in-lb for max 5 sec, 3.18x10^-8 /pump hour E00095EN 6 of 9 NOTE 5. ENGINE MODEL DESCRIPTION The models shown on this TCDS have the following general characteristics Model/Rating Description GE9X-105B1A Base Rating GE9X-105B1A1 Low alt, hot day bump GE9X-105B1A2 High alt, hot day bump GE9X-105B1A3 Composite A1+A2 The parts list for each engine model contains a configuration group number to identify the engine configuration. The engine model configuration is identified as GE9X-xxG0y, where xx is the model rating and y is the applicable configuration as described below. Group Description G01 Baseline G02 Reserved for future use G03 Reserved for future use NOTE 6. TYPICAL AIRCRAFT ACCESSORIES, COMPONENTS, OR 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 ENGINE TYPE DESIGN • Flight Inlet - The GE9X engine is approved for use with the Boeing Flight Inlet P/N: 314W2100 • Thrust Reverser - The GE9X engine is approved for use with the Boeing Thrust Reverser System P/N: 315W2295 • Primary Exhaust - The GE9X engine is approved for use with the Boeing Primary Exhaust P/N: 333W2000 • Sump Eductor System - The GE9X engine is approved for use with the Boeing Sump Eductor P/N: 314W2541 • Forward Mount - The GE9X engine is approved for use with the Boeing Forward Mount P/N: 310W2020 • Thrust Links Module - The GE9X engine is approved for use with the Boeing Thrust Links Module P/N: 310W2040 • Aft Mount - The GE9X engine is approved for use with the Boeing Aft Mount P/N: 310W2030 • Hydraulic Pump - The GE9X engine is approved for use with the Boeing Hydraulic Pump P/N: 332W2110 • Integrated Drive Generator - The GE9X engine is approved for use with the Boeing Integrated Drive Generator P/N: 332W2210-10 • Variable Speed Constant Frequency / Back-up Generator - The GE9X engine is approved for use with the Boeing Variable Speed Constant Frequency / Back-up Generator P/N: 332W2210-20 NOTE 8. SPECIAL ANTI-ICING OR DE-ICING REQUIREMENTS • NOT APPLICABLE NOTE 9. ENGINE MOUNT SYSTEM PROVISIONS • Forward Mount Fan Case Yoke • Thrust Link Fan Hub Frame Mount Lugs • Aft Mount Turbine Rear Frame Mount Lugs • Forward Mount, Thrust Links and Aft Mount are the responsibility of the Airframer (See Note 7) NOTE 10. POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS AND LIMITS • NOT APPLICABLE E00095EN 7 of 9 NOTE 11. SPECIAL INSTALLATION REQUIREMENTS • ETOPS The GE9X Engine has not demonstrated compliance to 33.201 and therefore is not ETOPS eligible at this time. • Time Limited Dispatch Criteria The GE9X Engine Control has been approved for Time Limited Dispatch. Criteria pertaining to the dispatch and maintenance requirements for the engine control systems are specified in the airworthiness limitation section of the GE9X Engine Manual (05-11-07), which defines the various configurations and maximum operating intervals. A control system reliability monitoring program has been established with GE9X, as a contingency of the dispatch criteria approval, to ensure that overall engine control system and specific component failure rates do not exceed the maximum values permitted by the reliability analysis. • Induction System Icing Demonstration of compliance to 14 CFR Part 33.68, Induction System Icing, is installation specific to the Boeing B777X model aircraft for the GE9X engines model series. Installation of these engine models on different airplane models or types will require a separate evaluation and finding of compliance to 14 CFR Part 33.68. • Exhaust 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 engine models GE9X‐105B1A, GE9X‐105B1A1, GE9X‐105B1A2, GE9X-105B1A3: • 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 1031.60(a)(5) • Hydrocarbons (HC) emission standards: 14 CFR 34.21(d)(1)(i); in addition, 40 CFR 1031.60(c) • Carbon Monoxide (CO) emission standards: 14 CFR 34.21(d)(1)(ii); in addition, 40 CFR 1031.60(d) • Oxides of Nitrogen (NOx) emission standards: 14 CFR 34.23(b)(1); in addition, 40 CFR 1031.60(e)(5) (also known as Tier 8 new type) • non-volatile Particulate Matter (nvPM) Mass Concentration Emission Standards: 14 CFR 34.25(a)(1); in addition, 40 CFR 1031.60(a)(6) (also known as Tier 10) • nvPM Mass and Number Emission Standards: 14 CFR 34.25(a)(2); in addition, 40 CFR 1031.60(b)(2) (also known as Tier 11 in-production) 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, 2020, 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, • Part III, Chapter 2, Section 2.3.2 for Carbon monoxide and Hydrocarbons, • Part III, Chapter 2, Section 2.3.2.e for Oxides of Nitrogen (also known as CAEP/8), • Part III, Chapter 4, Section 4.2.2.1 for nvPM Mass Concentration (also known as CAEP/10), and • Part III, Chapter 4, Section 4.2.2.2 for nvPM Mass and Number (also known as CAEP/11) NOTE 12. MANUFACTURER’S SERVICE BULLETINS OF SPECIAL INTEREST • 71-0001 – Recommended Tasks for Servicing and Inspection • 71-0003 – Engine Event Data Collection • 72-0003 – Hardware Exposed to Abnormal Operating Events • 72-0005 – Fan Blade Fleet Leader Program • 72-0006 – R65 Immersion Ultrasonic Inspection Documentation • 73-0001 – Requirements for Approved Fuel and Additives • 79-0001 – Requirements for Approved Oil and Additives E00095EN 8 of 9 NOTE 14. SPECIAL REPAIR OR OVERHAUL LIMITATION • FAN BLADE REPAIR Substantiation of repairs of the fan blade structural composite material in the root section up to the inner annulus flow path must show that compliance to GE9X Special Condition No. 33-018-SC is maintained. NOTE 15. APPLICABLE INSTALLATION, MAINTENANCE AND OVERHAUL MANUALS Instructions for Continued Airworthiness (ICA) are incomplete. ICA must be complete and accepted prior to delivery of the first aircraft with GE9X engines installed, or upon issuance of a standard certificate of airworthiness for the aircraft with GE9X engines installed, whichever occurs later. The applicable installation and operating manuals are: 1. Installation Manual (IM): GEK 131800 2. Operating Instructions (OI): GEK 131801 The applicable engine shop and overhaul (ICA) manuals are: 1. Engine Shop Manual (ESM): GEK 131802 2. System Description Manual (SDS): GEK 131809 3. Standard Practices Manual (SPM): GEK 9250 4. Time Limited Dispatch Summary (TLD): GEK 131804 5. Components Maintenance Manuals (CMM): Various GEK as published by GE 6. Service Bulletins (SB): Various as published by GE (see Note 12) The applicable on-wing maintenance (ICA) manuals are: 1. System Description Manual: see Boeing Systems Description Manual (SDS) 2. Aircraft Maintenance Manual: see Boeing Aircraft Maintenance Manual (AMM) 3. Fault Isolation Manual: see Boeing Fault Isolation Manual (FIM) NOTE 16. IMPORT REQUIREMENTS FOR FOREIGN MANUFACTURED ENGINES • NOT APPLICABLE NOTE 17. LIFE LIMITED AND CRITICAL ENGINE PARTS Life limits established for critical engine parts are published in the ALS of Chapter 05 of the GE9X Engine Shop Manual (ESM): GEK 131802 (See Note 15). NOTE 18. MILITARY MODEL INFORMATION (differences from civil aviation model) • NOT APPLICABLE NOTE 13. SPECIAL OPERATING PROCEDURES OR LIMITATIONS • Negative G Operation During negative g operation only, it is permissible to operate below minimum oil pressure (17.4 psid) for a maximum of 15 seconds as outlined in the GE9X Installation Manual and Operating Instructions (See Note 15). • Minimum Flight Idle The minimum permissible idle in flight is a non-adjustable limit, preset into the EEC Control schedule. Flight idle is engaged based on thrust lever position and operating conditions as outlined in the GE9X Installation Manual and Operating Instructions (See Note 15). • Takeoff Time Limit The normal 5-minute takeoff rating may be extended to 10 minutes for engine out contingency, as outlined in the GE9X Installation Manual and Operating Instructions (See Note 15). • Icing Operation For operation in icing conditions: requirements, limitations, and notes are outlined in the GE9X Installation Manual and Operating Instructions (See Note 15). E00095EN 9 of 9 NOTE 19. MAXIMUM PERMISSIBLE MAIN ROTOR SPEEDS AND OUTPUT SHAFT SPEED SPOOL RPM % Low pressure rotor (N1) High pressure rotor (N2) 2,510 11,119 106.6 116.3 NOTE 20. MAXIMUM ALLOWABLE OUTPUT/PROPELLER SHAFT TORQUE LIMIT • NOT APPLICABLE NOTE 21. MAXIMUM PERMISSIBLE BLEED AIR EXTRACTION LOCATION TEMPERATURE CORRECTED FAN SPEED FLOW LIMIT HPC Stage 4 All speeds above minimum idle. 7.5% of primary airflow* HPC Stage 11 (CDP) All speeds above minimum idle. 15% of primary airflow* * Absolute maximum. Refer to the GE9X Installation Manual for detailed bleed schedules (See Note 15). NOTE 22. ROTOR DISK INTEGRITY AND ROTOR BLADE CONTAINMENT • Fan Blade Special Condition §33.94 - No. 33-018-SC NOTE 23. INITIAL MAINTENANCE INSPECTION Completion of the GE9X ETOPS engine test, in accordance with §33.201(c) through (f), is necessary to meet §33.90(b) requirements, and must occur prior to EIS for aircraft with GE9X engines installed. ----END----