TCDS E00091EN

1 U.S. DEPARTMENT OF TRANSPORTATION TCDS NUMBER E00091EN REVISION: 6 FEDERAL AVIATION ADMINISTRATION DATE: November 26, 2025 GENERAL ELECTRIC COMPANY MODELS: TYPE CERTIFICATE DATA SHEET GE Passport 20-17BB1A, GE Passport 20-18BB1A, GE Passport 20-19BB1A, GE Passport 20-19BB1B. Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00091EN) 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 GE Aerospace GE Passport 20–17BB1A GE Passport 20–18BB1A GE Passport 20–19BB1A GE Passport 20–19BB1B TYPE The GE Passport 20 engine is a high bypass dual-rotor, axial-flow turbofan. The bypass ratio of the engine is 5.6:1 with an overall pressure ratio of 45:1. The high pressure compressor (HPC) pressure ratio is 23:1. The High pressure compressor (HPC) is driven by a two stage High pressure turbine (HPT). The 10-stage high-pressure (HP) compressor includes five blisk stages for weight reduction. The integrated front fan and three stage Low pressure compressor (LPC) is driven by a four stage Low pressure turbine (LPT). A Low Emission combustor (LEC) is used for weight and emissions advantage. Combustor case has integrated OGV diffuser for weight reduction. 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 Next Gen Full- Authority Digital Engine Control (FADEC) control system which provides enhanced fault isolation and capability for engine functionality and diagnostics. RATINGS (See Note 15) Maximum Continuous at Sea Level Static Thrust (lb) 16,815 17,565 17,565 17,565 Fan Speed (rpm) 5,517 5,611 5,611 5,611 Take Off – 5 minutes at Sea Level (See Note 13.3) Static Thrust (lb) 17,745 18,435 18,920 18,920 Fan Speed (rpm) 5,633 5,706 5,761 5,761 Flat Rating – Ambient Temperature Takeoff 95oF / 35oC 95oF / 35oC 86oF / 30oC 86oF / 30oC Maximum Continuous 77oF / 25oC 77oF / 25oC 77oF / 25oC 77oF / 25oC PAGE 1 2 3 4 5 6 7 8 9 REV. 6 5 5 5 1 1 4 6 0 NOTE: CHANGES ARE BLACK- LINED IN THE LEFT MARGIN. 2 I. MODELS (cont.) GE Passport 20- 17BB1A GE Passport 20- 18BB1A GE Passport 20- 19BB1A GE Passport 20- 19BB1B MODEL LIST (Engine Configuration) GE Passport 20– 17BB1AG01/G02 GE Passport 20- 18BB1AG01/G02 GE Passport 20- 19BB1AG01/G02 GE Passport 20- 19BB1BG01/G02 GE Passport 20– 17BB1AG03/G04 GE Passport 20- 18BB1AG03/G04 GE Passport 20- 19BB1AG03/G04 GE Passport 20– 17BB1AG05/G06 GE Passport 20- 18BB1AG05/G06 GE Passport 20- 19BB1AG05/G06 COMPONENTS (GE P/Ns) Fuel Metering Unit 2496M14 2496M14 2496M14 2496M14 Electronic Engine Control 2500M36 2500M36 2500M36 2500M36 Pressure Sub-system 2474M65 2474M65 2474M65 2474M65 FADEC Software (earliest part number shown) 2575M73 2575M73 2575M73 2575M73 Data Entry Plug 2531M61P06 2531M61P22 2531M61P30 2531M61P31 Fuel Pump 2496M12 2496M12 2496M12 2496M12 IGNITION SYSTEM Two ignition exciters GE P/N 2488M61 2488M61 2488M61 2488M61 Two igniter plugs GE P/N 2519M29 2519M29 2519M29 2519M29 PRINCIPAL DIMENSIONS (in) Length (Fan spinner to aft centerbody flange) 132.50 in 132.50 in 132.50 in 132.50 in Width (maximum envelope) 54.32 in 54.32 in 54.32 in 54.32 in Height (maximum envelope) 51.90 in 51.90 in 51.90 in 51.90 in WEIGHT (DRY) Includes basic engine, basic engine accessories, and optional equipment as listed in the manufacturer’s engine specifications. 4554 lbs. 4554 lbs. 4554 lbs. 4554 lbs. CENTER OF GRAVITY LOCATIONS (in); Engine only Station (axial) – LH Engine 217.5 217.5 217.5 217.5 Waterline – LH Engine 97.1 97.1 97.1 97.1 Buttline – LH Engine 100.8 100.8 100.8 100.8 Station (axial) – RH Engine 217.8 217.8 217.8 217.8 Waterline – RH Engine 97.1 97.1 97.1 97.1 Buttline – RH Engine 98.8 98.8 98.8 98.8 FUEL See NOTE 12.1 for approved fuels. OIL See NOTE 12.2 for approved lubricants. CERTIFICATION BASIS • 14 CFR Part 33, effective February 1, 1965, as amended by 33-1 through 33-33 • 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. 3 TYPE CERTIFICATE MODELS APPLICATION DATE ISSUE/AMMENDED GE Passport 20-17BB1A May 22, 2012 April 29, 2016 GE Passport 20-18BB1A May 22, 2012 April 29, 2016 GE Passport 20-19BB1A April 15, 2014 April 29, 2016 GE Passport 20-19BB1B March 19, 2025 July 31, 2025 PRODUCTION BASIS Production Certification No. 108 • Equivalent Levels of Safety (ELOS) Findings: • ELOS No. TC3323EN-E-P-10 for 14 CFR 33.76 • ELOS No. TC3323EN-E-P-9 for 14 CFR 33.83 • ELOS No. TC3323EN-E-P-13 for 14 CFR 33.89 4 NOTES NOTE 1. ENGINE RATINGS (Engine ratings are based on a calibrated test stand, under the conditions specified below) 1. Sea level static, standard pressure (14.696 psia), 59 °F. 2. No customer bleed or customer power extraction. 3. Ideal engine Inlet, 100 % ram recovery 4. Production aircraft cowling. 5. Production instrumentation. 6. Fuel lower heating value of 18,400 BTU/lb. NOTE 2. TEMPERATURE LIMITS 1. Indicated Turbine exhaust gas temperature (T49) 1.1. Takeoff 5 minutes (see NOTE 13.3) 1,895 °F (1,035 °C) 1.2. Maximum Continuous 1,823 °F (995 °C) 1.3. Ground starts (manual or auto) 1,382 °F (750°C) Pre S/B 73-0025 1,472 °F (800°C) Post S/B 73-0025 1.4. Inflight starts (manual or auto) 1,607 °F (875°C) 1.5. Inflight starts (high power fuel cut) 1,787 °F (975°C) 2. Twenty (20) Exhaust Gas Temperature excursions of up to 1970.6 °F (1077 °C) for up to 15 seconds permitted before maintenance action required. Operator needs to maintain the count of excursions. 3. Oil temperature limits 3.1 Continuous 320°F (160°C) 3.2 Transient (15 minutes) 329°F (165°C) NOTE 3. FUEL AND OIL PRESSURE LIMITS FUEL PRESSURE LIMITS AT THE ENGINE PUMP INLET 1. Aircraft Boost Pump Operative The minimum pressure at the engine fuel pump inlet with aircraft boost pumps operative is true vapor pressure plus 5 psia (32.4 kPa) with aircraft boost pump operative to a maximum of 50 pisa. The maximum vapor to liquid ratio at the engine fuel pump inlet with aircraft boost pumps operative is zero. 2. Aircraft Boost Pump Inoperative The engine fuel system operation is restricted with the aircraft boost pumps inoperative as outlined in the GE Passport 20 Installation Manual GEK 112054. OIL PRESSURE LIMITS See Figure 8.2.6 of the GE Passport 20 Specific Operating Instructions GEK 112053 for definition of minimum and maximum oil pressures. NOTE 4. ACCESSORY DRIVE See the following Table. 5 ACCESSORY DEFINED BY ROTATION (NOTE #1) GEAR RATIO TO CORE ROTOR DRIVE SHAFT (RPM) MAX WEIGHT LB (KG) MAX OVERHUNG MOMENT IN-LB (N-m) SHEAR TORQUE IN- LB (N-m) CONTINUOUS PAD RATING HP OVER-LOAD [HP] VFG CW 0.8523 16773 91.20 (41.27) WET 529 (59.77) WET 4200.0 (474.54) 95102.1 120 for 2 min (See Note 3) AIR TURBINE STARTER CW 0.5714 11246 21 (9.50) DRY 56.7 (6.40) DRY 7500 (847.38) N. A. N.A. FUEL PUMP CW 0.3844 7565 28.90 (13.08) DRY 118.5 (13.39) DRY 3030 (342.34) 84.5 98 N.A. PMA CW 0.9143 17993 6.01 (2.73) DRY 5.5 (0.62) N.A. 0.70 N.A. PMG CCW 0.9143 17993 3.3 (1.49) DRY 6.6 (0.75) DRY N.A. 1.1 N.A. LUBE UNIT CW 0.2406 4734 26.71 (12.08) WET 119.9 (13.55) 1704 (192.52) 4.8 N.A. HYDRAULIC PUMP CCW 0.2406 4734 20.4 (9.23 ) DRY 93.23 (10.53) DRY 2700 (305.06) 25.8 at idle speed. 45 at max. speed 39.8 at idle speed. 69.4 at max speed. CORE TURN CRANKING PAD 0.5 SQUARE DRIVE CW 0.3466 6821 N.A. N.A. N.A. N.A. N.A NOTES: 1. Rotation is defined facing the pad. 2. 100 percent core engine speed is 19680 rpm. 3. VFG Overload ratings: 172 HP at flight idle, 5 sec and 81.5 HP at flight idle, for up to 5 minutes 6 NOTE 5. MODEL DESCRIPTION (List differences, similarities and special characteristics for each model, relative to the base model). The GE Passport 20 engine models are limited to installation on the Bombardier Aerospace Global-7500 and Global-8000 model aircrafts only with respect to the installed power response characteristics. Any bill-of-material changes that could significantly and adversely affect power response will have to be reassessed. NOTE 6. ENGINE TYPE DESIGN ACCESSORIES, COMPONENTS, SYSTEM ASSEMBLIES WITH AIRCRAFT LEVEL REQUIREMENTS (List accessories, similarities and system assemblies that are provided as part of the engine type design, but have traditionally been approved at the installation level and that may have specific aircraft level requirements to meet.) The following are installed on the GE Passport 20 engine and have Aircraft Level requirements: 1. Fire Detector, Fan Cowl - GE part no. 2580M13P01 / 2580M13P02 2. Fire Detector, Accessory Gear Box - GE part no. 2516M97P01 3. Fire Detector, Low Pressure Turbine Sensor – GE part no. 2516M98P01 NOTE 7. COMPATIBLE ACCESSORIES, COMPONENTS, SYSTEM ASSEMBLIES UNDER CURRENT ENGINE CERTIFICATION (List accessories, similarities and system assemblies that are not part of the engine type design, but have been shown to the compatible with the engine model under its certification basis). The GE Passport 20 engine models have the following installation: 1. Thrust Reverser, LH – 2. Thrust Reverser, RH – 3. Precooler System 4. Engine Driven Hydraulic Pump 5. Variable Frequency Generator 6. Permanent Magnetic Generator 7. Air Management System a. Bleed Pressure Sensor b. Bleed Monitoring Pressure Sensor c. Pressure Regulating Shut off valve d. Fan Air Valve NOTE 8. SPECIAL ANTI-ICING OR DE-ICING REQUIREMENTS (List accessories, similarities and system assemblies that are provided as part of the engine type design, but have traditionally been approved at the installation level and that may have specific aircraft level requirements to meet.) Reserved. NOTE 9. ENGINE MOUNT SYSTEM PROVISIONS (List accessories, similarities and system assemblies that are provided as part of the engine type design, but have traditionally been approved at the installation level and that may have specific aircraft level requirements to meet.) The GE Passport 20 engine models contains the following engine mount system parts that need to meet Aircraft level requirements: 1. Yoke - Forward and Aft 2. Link - Forward and Aft 3. Pin, Pylon 4. Bolt, Shoulder Link – Forward and Aft 5. Thrust Link 6. Bolt, Shoulder Thrust Link 7. Pin, Pylon Thrust Link NOTE 10. POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS.. Not Applicable 7 NOTE 11. SPECIAL INSTALLATION REQUIREMENTS 1. Inlet Foreign object protection Not Applicable. 2. Electromagnetic Interference (EMI) : none 3. Thrust Reverser Installation: None 4. Icing Protection: None 5. Criticality level of software : NA 6. Part 34 Emission standards: The following emission 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 GE Passport 20 engine models. • 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) • Non-Volatile Particulate Matter (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). 7. ETOPS eligibility: GE Passport 20 models have not been certified to ETOPS requirement and are therefore not eligible for ETOPS operations. 8. Time Limited dispatch limitations: Criteria pertaining to the engine control systems’ dispatch and maintenance requirements have been specified in GEK 119289 FADEC Control System Time Limited Dispatch Summary Document and Chapter 5 Airworthiness Limitations section of the GEK 112062 Line Maintenance Manual. These documents define the various configurations and maximum operating intervals. 9. Exhaust Gas Temperature shunting: The GE Passport 20-17BB1A model incorporates an EGT shunt of 31°C at fan speeds above idle. Thus, for an indicated EGT of 1895°F (1035°C), the measured EGT is 1839.2°F (1004°C). 10. Specific Aircraft Installation eligibility: None NOTE 12. MANUFACTURER’S SERVICE BULLETINS 1. Refer to GE Passport 20 Service Bulletin SB73-0001 for detailed information pertaining to fuels and additives. This Service Bulletin covers the eligible fuels listed per GE Aerospace Specification D50TF2. Eligible fuel classifications are: Class A – Aviation Kerosene Class C – Low Freeze Kerosene Class D – High Flash Kerosene Class E – Low Flash Kerosene NOTE: Class B – (Jet B, JP4) is prohibited 2. Refer to GE Passport 20 Service Bulletin SB79-0001 and its latest revision for detailed information pertaining to Lubricant brands and additives. This Service Bulletin covers the approved oils listed per latest authorized revision of GE Aerospace Specification D50TF1. Eligible oil classifications are: Class A, Class B, Class C, Class E, Class F and Class G 3. Refer to GE Passport 20 Service Bulletin SB73-0002 and its latest revision for the detailed information pertaining to the minimum approved FADEC software version that needs to be installed. 8 NOTE 13. SPECIAL OPERATING PROCEDURE OR LIMITATIONS 1. For operating in Icing conditions, requirements, limitation and notes are specified in the latest version of the FAA approved GEK 112053 GE Passport Specific Operating Instructions. 2. It is permissible to operate below minimum oil pressure for a maximum of 20 seconds during negative G operations. Refer GEK 112053 GE Passport 20 Operating Instructions for a definition of minimum oil pressure. 3. Takeoff Limit: The normal 5-minute take off limit may be extended to 10 minutes for one engine out contingency. NOTE 14. SPECIAL REPAIR AND OVERHAUL INSTRUCTIONS Reserved NOTE 15. APPLICABLE MANUALS 1. Applicable Installation information and Limitations have been provided in the latest FAA approved GEK 112054 GE Passport 20 Installation Manual. 2. Refer to the latest version of the FAA approved GEK 112063 Engine Shop Manual and GEK 112062 Line Maintenance Manual for maintenance criteria and requirements. NOTE 16. IMPORT REQUIREMENTS FOR FOREIGN MANUFACTURED ENGINES. Not Applicable NOTE 17. LIFE LIMITS Life Limits for critical rotating components for the GE Passport 20 engine models have been published in the Chapter 5 of the latest FAA approved GEK 112062 Line Maintenance Manual. NOTE 18. MILITARY MODEL INFORMATION (difference from civil aviation model). Reserved. NOTE 19. MAXIMUM PERMISSIBLE MAIN ROTOR AND OUTPUT SHAFT SPEEDS. 100 % N1 speed is 6,032.4 rpm. 100 % N2 speed is 19,680.1 rpm. Maximum permitted Fan Shaft Speed is 6,260 rpm, i.e. 103.7% of N1 Maximum permitted Core Shaft Speed is 22,625 rpm., i.e. 114.9% of N2. NOTE 20. MAXIMUM ALLOWABLE OUTPUT/PROPELLER SHAFT TORQUE LIMIT AT TORQUE METER/SENSOR Not Applicable. 9 NOTE 21. MAXIMUM PERMISSIBLE BLEED AIR EXTRACTION NOTE 22. ROTOR DISK INTEGRITY AND ROTOR BLADE CONTAINMENT (where special requirements apply) Reserved. ….. END ….. Stage 4 PS3 (psig) Percent W25 0 5.00 60 5.00 60 10.00 248 10.00 282 9.60 282 8.20 336 8.20 490 6.10 583 5.50 > 583 5.50 Stage 7 PS3 (psig) Percent W25 0 2.40 70 2.40 90 2.30 118 1.70 225 1.05 365 0.75 600 0.50 > 600 0.50 Stage 10 PS3 (psig) Percent W25 0 10.00 60 10.00 60 15.00 170 15.00 257 11.60 454 8.00 454 4.60 > 454 4.60