# TCDS E00078NE: General Electric Company GE Aerospace - Type: Type certificate data sheet - Status: Current - Holder: General Electric Company GE Aerospace - Revision: 19 - Revised: April 17, 2025 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 232, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/15/b2/15b2afb730ffb2c95d4d73751f6836afffabb7a58e1c98e849ad3f2cabdd5c31 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID171961763820250418150923.0001 - Page: https://openairdocs.org/tcds/E00078NE ## Models (31) As the data sheet lists them. - GEnx-1B67/P1 - GEnx-1B58/P1 - GEnx-1B64 - GEnx-1B54/P1 - GEnx-1B67 - GEnx-1B70 - GEnx-1B70/72/P1 - GEnx-1B70/P1 - GEnx-1B70/75/P1 - GEnx-1B64/P1 - GEnx-1B54 - GEnx-2B67B - GEnx-1B74/75/P1 - GEnx-2B67 - GEnx-1B58 - GEnx-1B78/P2 - GEnx-1B70/72/P2 - GEnx-1B67/P2 - GEnx-1B75/P2 - GEnx-1B70/75/P2 - GEnx-1B70/P2 - GEnx-1B75/P1 - GEnx-1B64/P2 - GEnx-1B58/P2 - GEnx-1B54/P2 - GEnx-1B74/75/P2 - GEnx-2B67/P - GEnx-1B70C/P1 - GEnx-1B70C/P2 - GEnx-1B76/P2 - Genx-1B76A/P2 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00078NE) 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 Aviation GEnx-1B54 GEnx-1B58 GEnx-1B64 GEnx-1B67 GEnx-1B70 TYPE The GEnx-1B engine is a dual rotor, axial flow, high bypass ratio turbofan. The 10-stage high pressure compressor is driven clockwise (Aft Looking Forward) by a 2-stage high pressure turbine. The single stage fan and 4-stage low pressure compressor are driven counterclockwise (Aft Looking Forward) by a 7-stage low pressure turbine. The engine control system includes a Full Authority Digital Engine Control (FADEC), which has an aircraft connection for digital communication. An engine monitoring unit (EMU) provides vibration level signals to the aircraft. The GEnx-2B engine is a dual rotor, axial flow, high bypass ratio turbofan. The 10-stage high pressure compressor is driven clockwise (Aft Looking Forward) by a 2-stage high pressure turbine. The single stage fan and 3-stage low pressure compressor are driven counterclockwise (Aft Looking Forward) by a 6-stage low pressure turbine. The engine control system includes a Full Authority Digital Engine Control (FADEC), which has an aircraft connection for digital communication. An engine monitoring unit (EMU) provides vibration level signals to the aircraft. RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb 56,300 - - 61,500 - - 66,500 fan speed, rpm 2,166 - - 2,247 - - 2,319 Takeoff - 5 min. at sea level, (see NOTE 12) static thrust, lb 57,400 61,000 67,000 69,400 72,300 fan speed, rpm 2,184 2,239 2,326 2,360 2,401 Flat rating ambient temperature Takeoff 86°F / 30°C - - - - - - - - Maximum Continuous 77°F / 25°C - - - - - - - - PAGE 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 REV. 19 12 12 12 15 15 15 19 18 18 14 14 14 12 11 11 14 19 19 19 19 19 19 19 LEGEND: “- -“ INDICATES “SAME AS PRECEDING MODEL” / “-“ NOT APPLICABLE U.S. DEPARTMENT OF TRANSPORTATION TCDS NUMBER E00078NE REVISION: 19 DATE: April 17, 2025 FEDERAL AVIATION ADMINISTRATION GENERAL ELECTRIC COMPANY MODELS: TYPE CERTIFICATE DATA SHEET E00078NE GEnx-1B54 GEnx-1B54/P1 GEnx-1B54/P2 GEnx-1B58 GEnx-1B58/P1 GEnx-1B58/P2 GEnx-1B64 GEnx-1B64/P1 GEnx-1B64/P2 GEnx-1B67 GEnx-1B67/P1 GEnx-1B67/P2 GEnx-1B70 GEnx-1B70/P1 GEnx-1B70/P2 GEnx-1B70C/P1 GEnx -1B70C/P2 GEnx-1B70/72/P1 GEnx -1B70/72/P2 GEnx-2B67 GEnx-1B70/75/P1 GEnx- 1B70/75/P2 GEnx-2B67B GEnx-1B74/75/P1 GEnx- 1B74/75/P2 GEnx-2B67/P GEnx-1B75/P1 GEnx-1B75/P2 GEnx-1B76/P2 Genx-1B76A/P2 GEnx-1B78/P2 E00078NE Page 2 of 24 I. MODELS (cont.) GEnx-1B54 GEnx-1B58 GEnx-1B64 GEnx-1B67 GEnx-1B70 MODEL LIST (Engine Configuration) (see NOTE 16) COMPONENTS (GE P/Ns) Fuel Metering Unit FADEC Hardware FADEC Software (earliest part number shown) Configuration Box Engine Configuration FADEC Rating Plug Fuel Pump IGNITION SYSTEM Two ignition exciters GE P/N Two igniter plugs GE P/N PRINCIPAL DIMENSIONS (in) Length (Fan spinner to aft centerbody flange) Width (maximum envelope) Height (maximum envelope) WEIGHT (DRY) Includes basic engine, basic engine accessories, and optional equipment as listed in the manufacturer’s engine specifications. CENTER OF GRAVITY LOCATIONS (in); Engine only Station (axial) Waterline Buttline GEnx-1B54G01 GEnx-1B54G02 GEnx-1B54G03 GEnx-1B54G04 GEnx-1B54G05 2122M20 2121M82 2447M85 2124M23P09 (G03-G05 Model List) 787-8 2400M60P03 787-9 2400M60P11 (G03 Model List) 787-8 2400M60P06 787-9 2400M60P12 (G04/G05 Model List) 2125M31P62 2122M22 2121M94 1754M84 GEnx-1B58G01 GEnx-1B58G02 GEnx-1B58G03 GEnx-1B58G04 GEnx-1B58G05 - - - - - - - - - - - - - - - - 2125M31P08 - - - - - - GEnx-1B64G01 GEnx-1B64G02 GEnx-1B64G03 GEnx-1B64G04 GEnx-1B64G05 - - - - - - - - - - - - - - - - 2125M31P68 - - - - - - GEnx-1B67G01 GEnx-1B67G02 GEnx-1B67G03 GEnx-1B67G04 GEnx-1B67G05 - - - - - - - - - - - - - - - - 2125M31P20 - - - - - - GEnx-1B70G01 GEnx-1B70G02 GEnx-1B70G03 GEnx-1B70G04 GEnx-1B70G05 - - - - - - - - - - - - - - - - 2125M31P74 - - - - - - 194.9 in 139.1 in 137.2 in - - - - - - - - - - - - - - - - - - - - - - - - 13,505 lbs (G01-G03 Model List) 13,552 lbs (G04/G05 Model List) - - - - - - - - - - - - - - - - 216.1 in. (G01-G03 Model List) 216.6 in (G04/G05 Model List) 99.9 in. 100.7 in. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - E00078NE Page 3 of 24 I. MODELS (cont.) GEnx-1B54/P1 GEnx-1B58/P1 GEnx-1B64/P1 GEnx-1B67/P1 GEnx-1B70/P1 RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb fan speed, rpm Takeoff - 5 min. at sea level, (see NOTE 12) static thrust, lb fan speed, rpm Flat rating ambient temperature Takeoff Maximum Continuous MODEL LIST (Engine Configuration) (see NOTE 16) COMPONENTS (GE P/Ns) Fuel Metering Unit FADEC Hardware FADEC Software (earliest part number shown) Configuration Box Engine Configuration FADEC Rating Plug Fuel Pump IGNITION SYSTEM Two ignition exciters GE P/N Two igniter plugs GE P/N PRINCIPAL DIMENSIONS (in) Length (Fan spinner to aft centerbody flange) Width (maximum envelope) Height (maximum envelope) WEIGHT (DRY) Includes basic engine, basic engine accessories, and optional equipment as listed in the manufacturer’s engine specifications. CENTER OF GRAVITY LOCATIONS (in); Engine only Station (axial) Waterline Buttline 56,300 2,166 57,400 2,184 86°F / 30°C 77°F / 25°C - - - - 61,000 2,239 - - - - 61,500 2,247 67,000 2,326 - - - - - - - - 69,400 2,360 - - - - 66,500 2,319 72,300 2,401 - - - - GEnx-1B54/P1G01 2122M20 2121M82 2447M85 2124M23P13 787-8 2400M60P10 787-9 2400M60P13 2125M31P62 2122M22 2121M94 1754M84 GEnx-1B58/P1G01 - - - - - - - - - - - - 2125M31P08 - - - - - - GEnx-1B64/P1G01 - - - - - - - - - - - - 2125M31P68 - - - - - - GEnx-1B67/P1G01 - - - - - - - - - - - - 2125M31P20 - - - - - - GEnx-1B70/P1G01 - - - - - - - - - - - - 2125M31P74 - - - - - - 194.9 in 139.1 in 137.2 in - - - - - - - - - - - - - - - - - - - - - - - - 13,552 lbs - - - - - - - - 216.6 in 99.9 in. 100.7 in. - - - - - - - - - - - - - - - - - - - - - - - - E00078NE Page 4 of 24 I. MODELS (cont.) GEnx-1B70/72/P1 GEnx-1B70/75/P1 GEnx-1B74/75/P1 GEnx-1B75/P1 RATINGS (see NOTE 5) Maximum continuous at sea level, static thrust, lb fan speed, rpm Takeoff - 5 min. at sea level, (see NOTE 12) static thrust, lb fan speed, rpm Flat rating ambient temperature Takeoff Maximum Continuous MODEL LIST (Engine Configuration) (see NOTE 16) COMPONENTS (GE P/Ns) Fuel Metering Unit FADEC Hardware FADEC Software (earliest part number shown) Configuration Box Engine Configuration FADEC Rating Plug Fuel Pump IGNITION SYSTEM Two ignition exciters GE P/N Two igniter plugs GE P/N PRINCIPAL DIMENSIONS (in) Length (Fan spinner to aft centerbody flange) Width (maximum envelope) Height (maximum envelope) WEIGHT (DRY) Includes basic engine, basic engine accessories, and optional equipment as listed in the manufacturer’s engine specifications. CENTER OF GRAVITY LOCATIONS (in); Engine only Station (axial) Waterline Buttline 66,500 2,319 72,300 2,401 93.4°F / 34.1°C 77°F / 25°C - - - - - - - - 101.8°F / 38.8°C - - 68,600 2,375 76,700 2,496 89°F / 31.7°C - - 68,800 2,378 77,600 2,510 86°F / 30°C - - GEnx-1B70/72/P1G01 2122M20 2121M82 2447M85 2124M23P13 787-8 2400M60P10 787-9 2400M60P13 2125M31P32 2122M22 2121M94 1754M84 GEnx-1B70/75/P1G01 - - - - - - - - - - - - 2125M31P80 - - - - - - GEnx-1B74/75/P1G01 - - - - - - - - - - - - 2125M31P44 - - - - - - GEnx-1B75/P1G01 - - - - - - - - - - - - 2125M31P50 - - - - - - 194.9 in 139.1 in 137.2 in - - - - - - - - - - - - - - - - - - 13,552 lbs - - - - - - 216.6 in 99.9 in. 100.7 in. - - - - - - - - - - - - - - - - - - E00078NE Page 5 of 24 I. MODELS (cont.) GEnx-1B54/P2 GEnx-1B58/P2 GEnx-1B64/P2 GEnx-1B67/P2 GEnx-1B70/P2 RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb fan speed, rpm Takeoff - 5 min. at sea level, (see NOTE 12) static thrust, lb fan speed, rpm Flat rating ambient temperature Takeoff Maximum Continuous MODEL LIST (Engine Configuration) (see NOTE 16) COMPONENTS (GE P/Ns) Fuel Metering Unit FADEC Hardware FADEC Software (earliest part number shown) Configuration Box Engine Configuration FADEC Rating Plug Fuel Pump IGNITION SYSTEM Two ignition exciters GE P/N Two igniter plugs GE P/N PRINCIPAL DIMENSIONS (in) Length (Fan spinner to aft centerbody flange) Width (maximum envelope) Height (maximum envelope) WEIGHT (DRY) Includes basic engine, basic engine accessories, and optional equipment as listed in the manufacturer’s engine specifications. CENTER OF GRAVITY LOCATIONS (in); Engine only Station (axial) Waterline Buttline 56,300 2,166 57,400 2,184 86°F / 30°C 77°F / 25°C - - - - 61,000 2,239 - - - - 61,500 2,247 67,000 2,326 - - - - - - - - 69,400 2,360 - - - - 66,500 2,319 72,300 2,401 - - - - GEnx-1B54/P2G01 GEnx-1B54/P2G02 2459M17 2122M20 2447M85 2124M23P15 2400M60P07 2125M31P62 2122M22 2121M94 1754M84 GEnx-1B58/P2G01 GEnx-1B58/P2G02 - - - - - - - - - - 2125M31P08 - - - - - - GEnx-1B64/P2G01 GEnx-1B64/P2G02 - - - - - - - - - - 2125M31P68 - - - - - - GEnx-1B67/P2G01 GEnx-1B67/P2G02 - - - - - - - - - - 2125M31P20 - - - - - - GEnx-1B70/P2G01 GEnx-1B70/P2G02 - - - - - - - - - - 2125M31P74 - - - - - - 194.9 in 139.1 in 137.2 in - - - - - - - - - - - - - - - - - - - - - - - - 13,552 lbs - - - - - - - - 216.6 in 99.9 in. 100.7 in. - - - - - - - - - - - - - - - - - - - - - - - - E00078NE Page 6 of 24 I. MODELS (cont.) GEnx-1B70/72/P2 GEnx-1B70/75/P2 GEnx-1B74/75/P2 GEnx-1B75/P2 GEnx-1B78/P2 RATINGS (see NOTE 5) Maximum continuous at sea level, static thrust, lb fan speed, rpm Takeoff - 5 min. at sea level, (see NOTE 12) static thrust, lb fan speed, rpm Flat rating ambient temperature Takeoff Maximum Continuous MODEL LIST (Engine Configuration) (see NOTE 16) COMPONENTS (GE P/Ns) Fuel Metering Unit FADEC Hardware FADEC Software (earliest part number shown) Configuration Box Engine Configuration FADEC Rating Plug Fuel Pump IGNITION SYSTEM Two ignition exciters GE P/N Two igniter plugs GE P/N PRINCIPAL DIMENSIONS (in) Length (Fan spinner to aft centerbody flange) Width (maximum envelope) Height (maximum envelope) WEIGHT (DRY) Includes basic engine, basic engine accessories, and optional equipment as listed in the manufacturer’s engine specifications. CENTER OF GRAVITY LOCATIONS (in); Engine only Station (axial) Waterline Buttline 66,500 2,319 72,300 2,401 93.4°F / 34.1°C 77°F / 25°C - - - - - - - - 101.8°F / 38.8°C - - 68,600 2,375 76,700 2,496 89°F / 31.7°C - - 68,800 2,378 77,600 2,510 86°F / 30°C - - 68,600 2,375 80,400 2,586 86°F / 30°C - - GEnx-1B70/72/P2G01 GEnx-1B70/72/P2G02 2459M17 2122M20 2447M85 2124M23P15 2400M60P07 2125M31P32 2122M22 2121M94 1754M84 GEnx-1B70/75/P2G01 GEnx-1B70/75/P2G02 - - - - - - - - - - 2125M31P80 - - - - - - GEnx-1B74/75/P2G01 GEnx-1B74/75/P2G02 - - - - - - - - - - 2125M31P44 - - - - - - GEnx-1B75/P2G01 GEnx-1B75/P2G02 - - - - - - - - - - 2125M31P50 - - - - - - GEnx-1B78/P2G01 GEnx-1B78/P2G02 - - - - - - - - - - 2125M31P86 - - - - - - 194.9 in 139.1 in 137.2 in - - - - - - - - - - - - - - - - - - - - - - - - 13,552 lbs - - - - - - - - 216.6 in 99.9 in. 100.7 in. - - - - - - - - - - - - - - - - - - - - - - - - E00078NE Page 7 of 24 I. MODELS (cont.) GEnx-1B70C/P1 GEnx-1B70C/P2 GEnx-1B76/P2 GEnx-1B76A/P2 RATINGS (see NOTE 5) Maximum continuous at sea level, static thrust, lb fan speed, rpm Takeoff - 5 min. at sea level, (see NOTE 12) static thrust, lb fan speed, rpm Flat rating ambient temperature Takeoff Maximum Continuous MODEL LIST (Engine Configuration) (see NOTE 16) COMPONENTS (GE P/Ns) Fuel Metering Unit FADEC Hardware FADEC Software (earliest part number shown) Configuration Box Engine Configuration FADEC Rating Plug Fuel Pump IGNITION SYSTEM Two ignition exciters GE P/N Two igniter plugs GE P/N PRINCIPAL DIMENSIONS (in) Length (Fan spinner to aft centerbody flange) Width (maximum envelope) Height (maximum envelope) WEIGHT (DRY) Includes basic engine, basic engine accessories, and optional equipment as listed in the manufacturer’s engine specifications. CENTER OF GRAVITY LOCATIONS (in); Engine only Station (axial) Waterline Buttline 66,500 2,319 72,300 2,401 101.8 °F / 38.8 °C 77°F / 25°C - - - - - - - - - - - - 68,600 2,375 78,500 2,521 86°F / 30°C - - - - - - - - - - 91°F / 32.8°C - - GEnx-1B70C/P1G01 2122M20 2121M82 2447M85 2124M23P18 787-8 2400M60P10 787-9 2400M60P13 2125M31P98 2122M22 2121M94 1754M84 GEnx-1B70C/P2G01 GEnx-1B70C/P2G02 2459M17 2122M20 2447M85 2124M23P18 2400M60P07 2125M31P98 - - - - - - GEnx-1B76/P2G01 GEnx-1B76/P2G02 - - - - - - 2124M23P22 - - 2125M31P56 - - - - - - GEnx-1B76A/P2G01 GEnx-1B76A/P2G02 - - - - - - - - - - 2125M31P92 - - - - - - 194.9 in 139.1 in 137.2 in - - - - - - - - - - - - - - - - - - 13,552 lbs - - - - - - 216.6 in 99.9 in. 100.7 in. - - - - - - - - - - - - - - - - - - E00078NE Page 8 of 24 I. MODELS (cont.) GEnx-2B67 GEnx-2B67B GEnx-2B67/P RATINGS (see NOTE 5) Maximum continuous at sea level, static thrust, lb fan speed, rpm Takeoff - 5 min. at sea level, (see NOTE 12) static thrust, lb fan speed, rpm Flat rating ambient temperature Takeoff Maximum Continuous MODEL LIST (Engine Configuration) (see NOTE 16) COMPONENTS (GE P/Ns) Fuel Metering Unit FADEC Hardware FADEC Software (earliest part number shown) Configuration Box Engine Configuration FADEC Rating Plug Fuel Pump IGNITION SYSTEM Two ignition exciters GE P/N Two igniter plugs GE P/N PRINCIPAL DIMENSIONS (in) Length (Fan spinner to aft centerbody flange) Width (maximum envelope) Height (maximum envelope) WEIGHT (DRY) Includes basic engine, basic engine accessories, and optional equipment as listed in the manufacturer’s engine specifications. CENTER OF GRAVITY LOCATIONS (in); Engine only Station (axial) Waterline Buttline 58,500 2,604 67,400 2,806 86°F / 30°C 77°F / 25°C - - - - - - - - - - - - - - - - - - - - - - - - GEnx-2B67G01 GEnx-2B67G02 2122M20 2124M70 2124M22P02 2400M60P04 2125M31P20 2122M22 2139M52 1754M84 GEnx-2B67BG01 GEnx-2B67BG02 - - - - 2124M22P06 2400M60P08 - - - - - - - - GEnx-2B67/PG01 GEnx-2B67/PG02 GEnx-2B67/PG03 2459M17 2122M20 - - 2124M22P10 2400M60P09 - - - - - - - - 185.0 in 126.0 in 127.3 in - - - - - - - - - - - - 12,397 lbs - - - - 218.7 in. 98.4 in. 99.9 in. - - - - - - - - - - - - E00078NE Page 9 of 24 I. MODELS (cont.) ALL FUEL OIL See NOTE 7 for approved fuels. Refer to GEnx-1B Service Bulletin 79-0001 and GEnx-2B Service Bulletin 79-0001 and its latest revision for detailed information pertaining to Type 2 oils. These Service Bulletins cover the approved oils conforming to General Electric Specification D50TF1 or the latest revisions that are authorized. CERTIFICATION BASIS GEnx-1B54, -1B58, -1B64, -1B67, -1B70 • 14 CFR part 33, effective February 1, 1965, as amended by 33-1 through 33-21 and amendment 33-23 section 33.76. • 14 CFR part 34, amendment 5, effective December 31, 2012. (14 CFR part 34, amendment 5A, effective October 23, 2013 for the GEnx-1B70) See NOTE 16 for detailed summary of the certification basis for fuel venting and exhaust emissions. • GEnx-1B Fan Blade Special Condition (33-006-SC) • Equivalent Level of Safety (ELOS) Findings: o ELOS No. 8040-ELOS-08-NE02 to 14 CFR 33.87(a) and (b) − Applicable to engines with high pressure turbine stage 1 blade part number 2305M26P03 and/or combustor fuel nozzle part numbers 2255M88P09, 2255M88P10, and 2256M66P10 o ELOS No. 8040-ELOS-08-NE03 to 14 CFR 33.27(c) o ELOS No. 8040-ELOS-08-NE04 to 14 CFR 33.90 − Applicable to engines with combustor chamber part numbers 2257M40G03/G04 o ELOS No. 8040-ELOS-08-NE05 to 14 CFR 33.77 o ELOS No. 8040-ELOS-10-NE03 to 14 CFR 33.68(a) o ELOS No. AT03359EN-E-P-1 to 14 CFR 33.83(d) o ELOS No. TC2191EN-E-P1 to 14 CFR 33.27(c)(2)(v) GEnx-1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, -1B70/P1, -1B70C/P1 -1B70/72/P1, - 1B70/75/P1, -1B74/75/P1, -1B75/P1 • 14 CFR part 33, effective February 1, 1965, as amended by 33-1 through 33-21 and amendment 33-23 section 33.76. • 14 CFR part 34, amendment 5, effective December 31, 2012 (14 CFR part 34, amendment 5A, effective October 23, 2013 for the GEnx-1B70/P1, -1B70C/P1 -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, -1B75/P1) See NOTE 16 for detailed summary of the certification basis for fuel venting and exhaust emissions. • GEnx-1B Fan Blade Special Condition (33-006-SC) • Equivalent Level of Safety (ELOS) Findings: o ELOS No. 8040-ELOS-08-NE05 to 14 CFR 33.77 o ELOS No. 8040-ELOS-12-NE01 Rev. 1 to 14 CFR 33.27(c) o ELOS No. 8040-ELOS-12-NE02 to 14 CFR 33.68(a) o ELOS No. 8040-ELOS-12-NE03 to 14 CFR 33.87(a) and (b), and §33.93(a) o ELOS No. AT03359EN-E-P-1 to 14 CFR 33.83(d) o ELOS No. TC2191EN-E-P1 to 14 CFR 33.27(c)(2)(v) GEnx-1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, -1B70C/P2, -1B70/72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2, -1B78/P2 • 14 CFR part 33, effective February 1, 1965, as amended by 33-1 through 33-21 and amendment 33-23 section 33.76. • 14 CFR part 34, amendment 7A, effective May 24, 2024. See NOTE 16 for detailed summary of the certification basis for fuel venting and exhaust emissions. • GEnx-1B Fan Blade Special Condition (33-006-SC) • Equivalent Level of Safety (ELOS) Findings: o ELOS No. AT3129EN-E-P-1 Rev. 1 to 14 CFR 33.27(c) o ELOS No. 8040-ELOS-08-NE05 to 14 CFR 33.77 o ELOS No. TC2191EN-E-P1 to 14 CFR 33.27(c)(2)(v) E00078NE Page 10 of 24 GEnx-2B67, -2B67B • 14 CFR part 33, effective February 1, 1965, as amended by 33-1 through 33-21, and amendment 33-23 section 33.76. • 14 CFR part 34, amendment 5, effective December 31, 2012. See NOTE 16 for detailed summary of the certification basis for fuel venting and exhaust emissions. • GEnx-2B Fan Blade Special Condition (33-007-SC) • Equivalent Level of Safety (ELOS) Findings: o ELOS No. 8040-ELOS-09-NE01 to 14 CFR 33.27(c) o ELOS No. 8040-ELOS-09-NE02 to 14 CFR 33.77(c) and (e) o ELOS No. AT2432EN-E8040 o ELOS-10-NE02 to 14 CFR 33.78 o ELOS No. AT03382EN-E-P-1 to 14 CFR 33.83(d) o ELOS No. TC2191EN-E-P1 to 14 CFR 33.27(c)(2)(v) GEnx-2B67/P • 14 CFR part 33, effective February 1, 1965, as amended by 33-1 through 33-21, and amendment 33-23 section 33.76. • 14 CFR part 34, amendment 7A, effective May 24, 2024. See NOTE 16 for detailed summary of the certification basis for fuel venting and exhaust emissions. • GEnx-2B Fan Blade Special Condition (33-007-SC) • Equivalent Level of Safety (ELOS) Findings: o ELOS No. AT3138EN-E-P-1 to 14 CFR 33.27(c) o ELOS No. AT3138EN-E-P-2 to 14 CFR 33.87(a) and (b), and 33.93 o ELOS No. AT3138EN-E-P-3 to 14 CFR 33.77(c) and (e) o ELOS No. AT3138EN-E-P-5 to 14 CFR 33.78 o ELOS No. AT03382EN-E-P-1 to 14 CFR 33.83(d) o ELOS No. TC2191EN-E-P1 to 14 CFR 33.27(c)(2)(v) E00078NE Page 11 of 24 CERTIFICATION BASIS TYPE CERTIFICATE E00078NE (cont.) MODELS APPLICATION DATE ISSUE/AMMENDED GEnx-1B54 GEnx-1B58 December 13, 2004 May 24, 2005 March 31, 2008 March 31, 2008 GEnx-1B64 December 13, 2004 March 31, 2008 GEnx-1B67 May 24, 2005 March 31, 2008 GEnx-1B70 December 13, 2004 March 31, 2008 GEnx-1B54/P1 September 21, 2010 June 14, 2012 GEnx-1B58/P1 September 21, 2010 June 14, 2012 GEnx-1B64/P1 September 21, 2010 June 14, 2012 GEnx-1B67/P1 September 21, 2010 June 14, 2012 GEnx-1B70/P1 September 21, 2010 June 14, 2012 GEnx-1B70/72/P1 September 21, 2010 June 14, 2012 GEnx-1B70/75/P1 September 21, 2010 June 14, 2012 GEnx-1B74/75/P1 September 21, 2010 June 14, 2012 GEnx-1B75/P1 September 21, 2010 June 14, 2012 GEnx-1B54/P2 October 6, 2010 April 12, 2013 GEnx-1B58/P2 October 6, 2010 April 12, 2013 GEnx-1B64/P2 October 6, 2010 April 12, 2013 GEnx-1B67/P2 October 6, 2010 April 12, 2013 GEnx-1B70/P2 October 6, 2010 April 12, 2013 GEnx-1B70/72/P2 October 6, 2010 April 12, 2013 GEnx-1B70/75/P2 October 6, 2010 April 12, 2013 GEnx-1B74/75/P2 October 6, 2010 April 12, 2013 GEnx-1B75/P2 October 6, 2010 April 12, 2013 GEnx-1B78/P2 October 6, 2010 April 12, 2013 GEnx-2B67 February 28, 2006 July 22, 2010 GEnx-2B67B October 15, 2010 September 12, 2011 GEnx-2B67/P October 15, 2010 November 22, 2013 GEnx-1B70C/P1 December 10, 2013 February 6, 2015 GEnx-1B70C/P2 December 10, 2013 February 6, 2015 GEnx-1B76/P2 March 24, 2016 June 20, 2016 GEnx-1B76A/P2 March 24, 2016 June 20, 2016 PRODUCTION BASIS Production Certificate No. 108 E00078NE Page 12 of 24 NOTE 1. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS GEnx-1B54, -1B58, -1B64, -1B67, -1B70 Low pressure rotor (N1) 2,726 RPM High pressure rotor (N2) 13,425 RPM NOTES: A) 100 percent N1 is 2,560 RPM B) 100 percent N2 is 11,377 RPM GEnx-1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, -1B70/P1, -1B70C/P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, -1B75/P1 Low pressure rotor (N1) 2,778 RPM High pressure rotor (N2) 13,539 RPM NOTES: A) 100 percent N1 is 2,560 RPM B) 100 percent N2 is 11,377 RPM GEnx-1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, -1B70C/P2, -1B70/72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2, -1B78/P2 Low pressure rotor (N1) 2,778 RPM High pressure rotor (N2 13,368 RPM NOTES: A) 100 percent N1 is 2,560 RPM B) 100 percent N2 is 11,377 RPM GEnx-2B67, -2B67B Low pressure rotor (N1) 3,026 RPM High pressure rotor (N2) 13,425 RPM NOTES: A) 100 percent N1 is 2,835 RPM B) 100 percent N2 is 11,377 RPM GEnx-2B67/P Low pressure rotor (N1) 3,026 RPM High pressure rotor (N2) 13,368 RPM NOTES: A) 100 percent N1 is 2,835 RPM B) 100 percent N2 is 11,377 RPM NOTES E00078NE Page 13 of 24 NOTE 2. MAXIMUM PERMISSIBLE TEMPERATURES GEnx-1B54, -1B58, -1B64 , -1B67, -1B70 Indicated turbine exhaust gas temperature (T49) [see NOTE 5] Takeoff 5 minutes (see NOTE 12) 1,895°F (1,035°C) 30 seconds Maximum Transient 1,904°F (1,040°C) Maximum Continuous 1,841°F (1,005°C) Ground starts (manual or auto) 1,382°F (750°C) Inflight starts (manual or auto) 1,607°F (875°C) Inflight starts (high power fuel cut) 1,787°F (975°C) Oil temperature limits Continuous 320°F (160°C) Transient (15 minutes) 350°F (177°C) GEnx-1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, -1B70/P1, -1B70C/P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, -1B75/P1 Indicated turbine exhaust gas temperature (T49) [see NOTE 5] Takeoff 5 minute (see NOTE 12) 1,940°F (1,060°C) 30 seconds Maximum Transient 1,949°F (1,065°C) Maximum Continuous 1,886°F (1,030°C) Ground starts (manual or auto) 1,382°F (750°C) Inflight starts (manual or auto) 1,607°F (875°C) Inflight starts (high power fuel cut) 1,787°F (975°C) Oil temperature limits Continuous 320°F (160°C) Transient (15 minutes) 350°F (177°C) GEnx-1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, 1B70C/P2, -1B70/72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2, -1B78/P2 Indicated turbine exhaust gas temperature (T49) [see NOTE 5] Takeoff 5 minute (see NOTE 12) 1,949°F (1,065°C) 30 seconds Maximum Transient 1,958°F (1,070°C) Maximum Continuous 1,886°F (1,030°C) Ground starts (manual or auto) 1,382°F (750°C) Inflight starts (manual or auto) 1,607°F (875°C) Inflight starts (high power fuel cut) 1,787°F (975°C) Oil temperature limits Continuous 320°F (160°C) Transient (15 minutes) 350°F (177°C) E00078NE Page 14 of 24 NOTE 2. GEnx-2B67, -2B67B, -2B67/P (cont.) Indicated turbine exhaust gas temperature (T49) [see NOTE 5] Takeoff 5 minute (see NOTE 12) 1,940°F (1,060°C) 30 seconds Maximum Transient 1,949°F (1,065°C) Maximum Continuous 1,886°F (1,030°C) Ground starts (manual or auto) 1,382°F (750°C) Inflight starts (manual or auto) 1,607°F (875°C) Inflight starts (high power fuel cut) 1,787°F (975°C) Oil temperature limits Continuous 320°F (160°C) Transient (15 minutes) 350°F (177°C) NOTE 3. FUEL AND OIL PRESSURE LIMITS FUEL PRESSURE LIMITS AT THE ENGINE PUMP INLET The limit is from minimum fuel pressures of not less than the greater of true vapor pressure plus 5.0 psi or ambient plus 5.0 psi to a maximum of 70 psig. For the GEnx-1B, on the Boeing B787 aircraft, the minimum fuel pressure limit is extended down to minimum fuel pressure of 3.5 psia and maximum vapor-to-liquid ratio (v/l) of 0.45 for up to 60 minutes followed by up to 600 minutes with minimum fuel pressure of 3.5 psia and a maximum vapor-to-liquid ratio (v/l) of 0.28. OIL PRESSURE LIMITS See Figure 8-1 of GEnx-1B Operating Instructions GEK 112857 and GEnx-2B Operating Instructions GEK 114113 for definition of minimum and maximum oil pressures. E00078NE Page 15 of 24 NOTE 4. GEnx ACCESSORY DRIVE CHARACTERISTICS GEnx-1B54, -1B58, -1B64, -1B67, and -1B70 Accessory Defined By Rotation (See Comment A) Gear Ratio to Core Rotor Drive Shaft (RPM) Maximum Weight LB (KG) Maximum Overhung Moment IN-LB (Nꞏm) Shear Torque IN-LB (Nꞏm) Continuous Pad Rating HP (Inflight -total for both VFSG’s) Overload [HP] 692 VFSG 1 ICNR -GE- CCW 1.1331 12,891.30 234.4 (106.3) 1,718 (194.4) 19,596-20,220 (Dual Engine) See BE059 WET (2,214-2,285) 790 Comment (Single Engine) C 692 VFSG 2 ICNR-GE- CCW 1.1331 12,891.30 234.4 (106.3) 1,718 (194.4) 19,596-20,220 (Dual Engine) See BE060 WET (2,214-2,285) 790 Comment (Single Engine) C Hydraulic ICNR-GE- CCW 0.4438 5,049.10 30.3 (13.74) 140 (15.81) 2,625-3,715 62 85 Pump BE057 WET WET (297-420) [5 sec] Core Turn 0.5 Square Drive/ Dwg- 2305M71 CCW 0.6773 7,705.60 N. A. N. A. N. A. N. A. N. A. Comments: A. Rotation is defined facing the pad. B. 100 percent engine core speed is 11,377rpm. C. 1,021 HP total both drive pads at flight idle, with no more than 528 HP on any one drive pad for up to 1 second [single engine]. 866 HP total both drive pads at flight idle, with no more than 471 HP on any one drive pad for up to 5 minutes [dual engine]. E00078NE NOTE 4. (cont.) Page 16 of 24 GEnx ACCESSORY DRIVE CHARACTERISTICS (continued) GEnx-1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, -1B70/P1, -1B70C/P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, and -1B75/P1 Accessory Defined By Rotation (See Comment A) Gear Ratio to Core Rotor Drive Shaft (RPM) Maximum Weight LB (KG) Maximum Overhung Moment IN-LB (Nꞏm) Shear Torque IN-LB (Nꞏm) Continuous Pad Rating HP (Inflight -total for both VFSG’s) Overload [HP] 676 VFSG 1 ICNR -GE- CCW 1.1331 12,891.30 234.4 (106.3) 1,718 (194.4) 19,596-20,220 (Dual Engine) See BE059 WET (2,214-2,285) 720 Comment C (Single Engine) 676 VFSG 2 ICNR-GE- CCW 1.1331 12,891.30 234.4 (106.3) 1,718 (194.4) 19,596-20,220 (Dual Engine) See BE060 WET (2,214-2,285) 720 Comment C (Single Engine) Hydraulic ICNR-GE- CCW 0.4438 5,049.10 30.3 (13.74) 140 (15.81) 2,625-3,715 62 85 Pump BE057 WET WET (297-420) [5 sec] Core Turn 0.5 Square Drive/ Dwg- 2305M71 CCW 0.6773 7,705.60 N. A. N. A. N. A. N. A. N. A. Comments: A. Rotation is defined facing the pad. B. 100 percent engine core speed is 11,377rpm. C. 1,021 HP total both drive pads at flight idle, with no more than 528 HP on any one drive pad for up to 1 second [single engine]. 866 HP total both drive pads at flight idle, with no more than 471 HP on any one drive pad for up to 5 minutes [dual engine]. E00078NE NOTE 4. (cont.) Page 17 of 24 GEnx ACCESSORY DRIVE CHARACTERISTICS (continued) GEnx-1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, -1B70C/P2, -1B70/72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2 and -1B78/P2 Accessory Defined By Rotation (See Comment A) Gear Ratio to Core Rotor Drive Shaft (RPM) Maximum Weight LB (KG) Maximum Overhung Moment IN-LB (Nꞏm) Shear Torque IN-LB (Nꞏm) Continuous Pad Rating HP (Inflight -total for both VFSG’s) Overload [HP] 676 VFSG 1 ICNR -GE- CCW 1.1331 12,891.30 234.4 (106.3) 1,718 (194.4) 19,596-20,220 (Dual Engine) See BE059 WET (2,214-2,285) 720 Comment C (Single Engine) 676 VFSG 2 ICNR-GE- CCW 1.1331 12,891.30 234.4 (106.3) 1,718 (194.4) 19,596-20,220 (Dual Engine) See BE060 WET (2,214-2,285) 720 Comment C (Single Engine) Hydraulic ICNR-GE- CCW 0.4438 5,049.10 30.3 (13.74) 140 (15.81) 2,625-3,715 59 85 Pump BE057 WET WET (297-420) [5 sec] Core Turn 0.5 Square Drive/ Dwg- 2305M71 CCW 0.6773 7,705.60 N. A. N. A. N. A. N. A. N. A. Comments: A. Rotation is defined facing the pad. B. 100 percent engine core speed is 11,377rpm. C. 1,021 HP total both drive pads at flight idle, with no more than 528 HP on any one drive pad for up to 1 second [single engine]. 866 HP total both drive pads at flight idle, with no more than 471 HP on any one drive pad for up to 5 minutes [dual engine]. E00078NE Page 18 of 24 NOTE 4. (cont.) GEnx ACCESSORY DRIVE CHARACTERISTICS (continued) GEnx-2B67, -2B67B, -2B67/PG01 and -2B67/PG02 Accessory Defined by Rotation (See Comment A) Gear Ratio to Core Rotor Drive Shaft (RPM) Static Weight LB Maximum Overhang Moment IN-LB Shear Torque Torque IDG 747-8 Boeing engine specification CCW 0.6696 4654 to 8989 (See Comment C) IDG 126.8 QAD 5.6 900 9000 + 400 in-lb (in-lb) 2245 -CONTINUOUS 3575 –TRANSIENT (See Comment D) 5250 –MOMENTARY (See Comment E) HYDRAULIC PUMP 747-8 Boeing engine specification CCW 0.3157 2194 to 4238 40.1 DRY 261 WET 4550 + 300 in-lb (in-lb) 1103 - CONTINUOUS 1790 – TRANSIENT (See Comment F) 4250 – FAILURE (See Comment G) AIR TURBINE STARTER M50TF4062 CCW 1.1331 58.4 % N2 (5863 RPM) MAX CUT OUT 49.38 300 1685 ft-lb (ft-lb) Cold Day APU Start 617 XBL Start 820 CORE TURN 0.5 SQUARE DRIVE CCW 0.6012 6839.9 N.A. N.A. N.A. N.A. Comments: A. Rotation is defined facing the pad B. 100 percent engine core speed is11,377rpm. C. IDG online speed: 4,600 rpm. Load is removed when input remains 4,450 RPM or less for 150 + 50 ms. D. Once every 1,000 engine operating hours. E. Once every 5,000 engine operating hours. F. Peak running torque at engine start and at maximum flow for simultaneous flap and gear operation (takeoff condition). G. Torque experienced during an input shaft shear event. E00078NE Page 19 of 24 NOTE 4. (cont.) GEnx ACCESSORY DRIVE CHARACTERISTICS (continued) GEnx-2B67/PG03 Accessory Defined by Rotation (See Comment A) Gear Ratio to Core Rotor Drive Shaft (RPM) Static Weight LB Maximum Overhang Moment IN-LB Shear Torque Torque IDG VC-25B Boeing engine specification CCW 0.6696 4500 to 9250 IDG 145 (Dry) QAD 6.0 (Dry) 1088 10,050 + 450 in-lb (in-lb) 3033 -CONTINUOUS 5687 –TRANSIENT (See Comment D) 7003 –MOMENTARY (See Comment E) HYDRAULIC PUMP 747-8 Boeing engine specification CCW 0.3157 2194 to 4238 40.1 DRY 261 WET 4550 + 300 in-lb (in-lb) 1103 - CONTINUOUS 1790 – TRANSIENT (See Comment F) 4250 – FAILURE (See Comment G) AIR TURBINE STARTER M50TF4062 CCW 1.1331 58.4 % N2 (5863 RPM) MAX CUT OUT 49.38 300 1685 ft-lb (ft-lb) Cold Day APU Start 617 XBL Start 820 CORE TURN 0.5 SQUARE DRIVE CCW 0.6012 6839.9 N.A. N.A. N.A. N.A. Comments: A. Rotation is defined facing the pad B. 100 percent engine core speed is11,377rpm. C. IDG online speed: 4,600 rpm. Load is removed when input remains 4,450 RPM or less for 150 ± 50 ms. D. Once every 1,000 engine operating hours. E. Once every 5,000 engine operating hours. F. Peak running torque at engine start and at maximum flow for simultaneous flap and gear operation (takeoff condition). G. Torque experienced during an input shaft shear event. NOTE 5. ENGINE RATINGS Engine ratings are based on calibrated test stand performance under the following conditions: 1. Sea level static, standard pressure (14.696 psia), 59 °F 2. No 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 E00078NE Page 20 of 24 NOTE 6. MAXIMUM PERMISSABLE BLEED AIR EXTRACTION GEnx-1B54, -1B58, -1B64, -1B67, and -1B70 (applicable to engines not equipped with a booster anti-ice system) Stage 7 - Percent W25 Any Power Setting 3.3% GEnx-1B54, -1B58, -1B64, -1B67, -1B70, -1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, -1B70/P1, -1B70C/P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, -1B75/P1, - 1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, -1B70C/P2, -1B70/72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2 and -1B78/P2 (applicable to engines equipped with a booster anti-ice system) Percent Corrected Fan Speed (%N1K) Stage 7 - Percent W25 0 to 31.3 5.0% 31.3 to 66.4 4.7% > 66.4 3.3% Comments: A. 100% engine fan speed is 2,560 RPM B. 3.3% W25 is the maximum flow delivered to the engine inlet anti-ice system at any power setting. GEnx-2B67, -2B67B %N1K CDP Bleed Percent W25 T2 > 67ºF T2 < 67ºF 0 13 13 81.1 13 13 81.1 8 10 88.2 8 10 88.2 8 8.5 91.7 8 8.5 91.7 8 8 120.0 8 8 NOTE: 100% engine fan speed is 2,835 RPM GEnx-2B67/P %N1K CDP Bleed Percent W25 T2 > 67ºF T2 < 67ºF 0 13 13 81.1 13 13 81.1 8 10 88.2 8 10 88.2 8 8.5 91.7 8 8.5 91.7 8 8 120.0 8 8 NOTE: 100% engine fan speed is 2,835 RPM %N1K S4 Bleed Percent W25 0 7.28% 15.9 7.28% 21.2 7.28% 50.0 7.28% 50.0 7.85% 75.8 7.85% 75.8 7.65% 81.1 7.65% 84.7 7.85% 91.7 7.85% 108.6 6.00% 108.6 5.00% 120.0 5.00% %N1K S4 Bleed Percent W25 0 7.28% 15.9 7.28% 21.2 7.28% 50.0 7.28% 50.0 7.85% 64.6 7.85% 64.6 7.60% 77.8 7.60% 77.8 7.39% 95.9 7.39% 108.6 6.00% 108.6 5.00% 120.0 5.00% E00078NE Page 21 of 24 NOTE 7. FUEL Refer to GEnx-1B Service Bulletin 73-0001 and Installation Manual GEK 112856, GEnx-2B Service Bulletin 73-0001 and Installation Manual GEK 114114 for detailed information pertaining to fuels and additives. These Service Bulletins cover the eligible fuels listed per GE Aviation 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 Kathon TM fp 1.5 Fuel Biocide is prohibited NOTE 8. LIFE LIMITS Life limits for critical rotating components for the GEnx-1B54, -1B58, -1B64, -1B67, -1B70, -1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, -1B70/P1, -1B70C/P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, -1B75/P1, -1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, -1B70C/P2, -1B70/72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2 and -1B78/P2 are published in Chapter 5 of the GEnx Engine Manual, GEK 112851. The GEnx-2B67, -2B67B, and -2B67/P cyclic life limits are published in Chapter 5 of the GEnx Engine Manual GEK 114119. The GEnx-1B and GEnx-2B cyclic life limits are based on a commercial mission cycle, which consists of a start, takeoff, climb, cruise, descent, and landing. Use (or non-use) of a fan reverser for braking during landing does not affect cycle counts. Each of the following constitutes one cycle: (1) a flight consisting of a takeoff and landing, (2) a touch-and-go landing or simulated touch-and-go landing (no weight on wheels) for pilot training. NOTE 9. THRUST SETTING PARAMETER Power setting, power checks, and control of engine thrust output in all operations are based on Fan Speed (N1). Speed sensors are included in the engine assembly for this purpose. NOTE 10. ICING CONDITIONS Requirements and limitations for ground operation in icing conditions are specified in: Operating Instructions GEK 112857 for the GEnx-1B54, -1B58, -1B64, -1B67, -1B70, -1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, -1B70/P1, -1B70C/P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, -1B75/P1,-1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, -1B70C/P2, -1B70/72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2 and -1B78/P2 Operating Instructions GEK 114113 for the GEnx-2B67, -2B67B, and -2B67/P. NOTE 11. NEGATIVE G OPERATION During "negative-G" operation only, it is permissible to operate below minimum oil pressure for a maximum of 15 seconds, as specified in: GEnx Operating Instructions, GEK 112857, Section 8, for the GEnx-1B54, -1B58, -1B64, -1B67, -1B70, -1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, -1B70/P1, -1B70C/P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, -1B75/P1, -1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, -1B70C/P2, -1B70/72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2 and -1B78/P2 minimum oil pressure definition. GEnx Operating Instructions, GEK 114113, Section 8, for the GEnx-2B67, -2B67B, and -2B67/P minimum oil pressure definition. NOTE 12. TAKEOFF TIME LIMIT The normal 5-minute takeoff time limit may be extended to 10 minutes for engine out contingency. E00078NE Page 22 of 24 NOTE 13. TIME LIMITED DISPATCH CRITERIA Criteria pertaining to the engine control systems’ dispatch and maintenance requirements are specified in: For the GEnx-1B54, -1B58, -1B64, -1B67, -1B70, -1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, -1B70/P1, -1B70C/P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, -1B75/P1, -1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, -1B70C/P2, -1B70/72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2 and -1B78/P2 engine models: General Electric FADEC Control System Time Limited Dispatch Summary Document, GEK 112858, and the Airworthiness Limitations Section of the GEnx Engine Manual, GEK 112851, which define the various configurations and maximum operating intervals. For the GEnx-2B67, -2B67B, and -2B67/P engine models: General Electric FADEC Control System Time Limited Dispatch Summary Document, GEK 114112, and the Airworthiness Limitations Section of the GEnx Engine Manual, GEK 114119, which define the various configurations and maximum operating intervals. NOTE 14. Deleted. NOTE 15. FAN BLADE REPAIR Approval of repairs of the fan blade composite material in the root section of the fan blade up to the inner annulus flow path line must be coordinated with the FAA Engine Certification Office. Substantiation of the repairs must show that compliance to GEnx-1B Special Condition No. 33-006-SC or GEnx-2B Special Condition No. 33-007-SC is maintained. NOTE 16. EXHAUST EMISSIONS AND FUEL VENTING The following emissions standards promulgated in 14 CFR part 34, amendment 5, effective December 31, 2012, and 40 CFR part 87, effective July 18, 2012, have been complied with for: GEnx-1B54, -1B58, -1B64, -1B67, -1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1 as well as GEnx-2B67 and -2B67B. Fuel Venting Emission Standards: 14 CFR 34.10(a) and 34.11; in addition, 40 CFR 87.10(a) and 87.11. Smoke Number (SN) Emission Standards: 14 CFR 34.21(e)(2); in addition, 40 CFR 87.23(c)(l). Carbon Monoxide (CO) Emission Standards: 14 CFR 34.21(d)(l)(ii); in addition, 40 CFR 87.23(c)(l). Hydrocarbons (HC) Emission Standards: 14 CFR 34.21(d)(1)(i); in addition, 40 CFR 87.23(c)(l). Oxides of Nitrogen (NOx) Emission Standards: 14 CFR 34.23(b)(l); in addition, 40 CFR 87.23(c)(3). The following emissions standards promulgated in 14 CFR part 34, amendment 5A, effective October 23, 2013, and 40 CFR part 87, effective July 18, 2012, have been complied with for: GEnx-1B70, -1B70/P1, 1B70C/P1, -B70/72/P1, -1B70/75/P1, -1B74/75/P1, and -1B75/P1. Fuel Venting Emission Standards: 14 CFR 34.10(a) and 34.11; in addition, 40 CFR 87.10(a) and 87.11. Smoke Number (SN) Emission Standards: 14 CFR 34.21(e)(2); in addition, 40 CFR 87.23(c)(l). Carbon Monoxide (CO) Emission Standards: 14 CFR 34.21(d)(l)(ii); in addition, 40 CFR 87.23(c)(l). Hydrocarbons (HC) Emission Standards: 14 CFR 34.21(d)(1)(i); in addition, 40 CFR 87.23(c)(l). Oxides of Nitrogen (NOx) Emission Standards: 14 CFR 34.23(b)(l); in addition, 40 CFR 87.23(c)(3). 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 , Third Edition, Part Ill, Chapter 2, Section 2.2.2 for SN, Section 2.3 .2 for CO and HC, Section 2.3.2.e.3 for NOx (also known as CAEP/8), and Part II Chapter 2 for fuel venting have also been demonstrated. The GEnx-1B54, -1B58, -1B64, -1B67, and -1B70 engine models (defined by the G01 and G02 model lists) for the B787- 8 aircraft, and the GEnx-2B67 (defined by the GEnx-2B67G01 and GEnx-2B67G02 model lists) for the B747-8 aircraft will not support the installation of the flow split valve fuel accumulator system. Fuel accumulator system installation is required in order to eliminate post-engine shutdown intermittent fuel releases and observed vapors. E00078NE Page 23 of 24 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: GEnx-1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, - 1B70/P2, -1B70C/P2, -1B70/72/P2, - 1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2, -1B78/P2, and - 2B67/P. 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 17. INDUCTION SYSTEM ICING Demonstration of compliance to 14 CFR part 33, section 33.68, Induction System Icing, is installation specific to the Boeing B787 model aircraft for the GEnx-1B54, -1B58, -1B64, -1B67, -1B70, -1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, -1B70/P1, -1B70C/P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, -1B75/P1, -1B54/P2, -1B58/P2, -1B64/P2, - 1B67/P2, -1B70/P2, -1B70C/P2, -1B70/72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2 and -1B78/P2 engine models, and B747-8 and B747-8F for the GEnx-2B67, -2B67B, and -2B67/P engine models. Installation of these engine models on different airplane models or type will require a separate evaluation and finding of compliance to section 33.68. NOTE 18. Deleted. NOTE 19. Deleted NOTE 20. Deleted. NOTE 21. EXTENDED TWIN ENGINE OPERATIONS (ETOPS) The GEnx-1B54, -1B58, -1B64, -1B67, and -1B70 engine models (defined by the G03, G04 and G05 model lists), the GEnx-1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, -1B70/P1, -1B70C/P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, -1B75/P1, -1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, -1B70C/P2, -1B70/72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2 and -1B78/P2 engine models comply with the requirements of 14 CFR part 33, sections 33.4, Appendix A, A33.3(c), 33.71(c)(4), and 33.201, and are therefore eligible for installation on ETOPS and Early ETOPS approved airplanes. The demonstrated diversion time is 330 minutes at maximum continuous power plus 15 minutes at hold and go-around power. ETOPS eligibility does not constitute airplane or operational level approvals necessary to conduct ETOPS flights. For the GEnx-1B54, -1B58, -1B64, -1B67, -1B70, -1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, -1B70/P1, 1B70C/P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, and -1B75/P1, -1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, - 1B70C/P2, -1B70/72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2 and -1B78/P2 engine models installed on B787 aircraft, the engine fuel pump must be replaced prior to the next ETOPS flight after any single suction feed operation event of duration greater than 30 minutes. Suction feed operation is defined by engine pump inlet fuel pressure less than the greater of true vapor pressure plus 5.0 psi or ambient plus 5.0 psi. NOTE 22. Deleted. E00078NE Page 24 of 24 NOTE 23. The engine Instructions for Continued Airworthiness (ICA’s) are incomplete for the GEnx-2B67/PG03 engine models. Aircraft with GEnx-2B67/PG03 engines models installed are not eligible for an airworthiness certificate until ICA’s are accepted by the FAA AIR-575 Certification Office. ….. END ….. ``` ## ADs (33, in force first) - [AD 2026-14-03](https://openairdocs.org/ad/2026-14-03): Engine Fuel Distribution · General Electric Company GE Aerospace GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2 and 17 more. Effective Aug 21, 2026 - [AD 2026-04-09](https://openairdocs.org/ad/2026-04-09): Turbine Engine Compressor Section · General Electric GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2 and 17 more. Effective Mar 11, 2026 - [AD 2025-11-03](https://openairdocs.org/ad/2025-11-03): Turbine Section · General Electric GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2 and 15 more. Effective Jul 8, 2025 - [AD 2024-25-07](https://openairdocs.org/ad/2024-25-07): Turbine Engine Compressor Section · General Electric GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2 and 17 more. Effective Feb 12, 2025 - [AD 2023-17-08](https://openairdocs.org/ad/2023-17-08): Turbine Section · General Electric GEnx-1B64/P2, GEnx-1B67/P2, GEnx-1B70/75/P2 and 6 more. Effective Oct 23, 2023 - [AD 2022-25-20](https://openairdocs.org/ad/2022-25-20): Turbine Engine Compressor Section, Turbine Section · General Electric GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2 and 17 more. Effective Jan 26, 2023 - [AD 2022-20-12](https://openairdocs.org/ad/2022-20-12): Turbine Engine Compressor Section, Turbine Section · General Electric GEnx-1B54/P2, GEnx-1B58/P2, GEnx-1B64/P2 and 13 more. Effective Nov 16, 2022 - [AD 2022-19-01](https://openairdocs.org/ad/2022-19-01): Turbine Section · General Electric GEnx-2B67/P. Effective Oct 25, 2022 - [AD 2022-18-04](https://openairdocs.org/ad/2022-18-04): Engine Fuel Distribution · General Electric GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2 and 14 more. Effective Oct 12, 2022 - [AD 2022-03-16](https://openairdocs.org/ad/2022-03-16): Turbine Section · General Electric GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2 and 17 more. Effective Mar 21, 2022 - [AD 2022-04-07](https://openairdocs.org/ad/2022-04-07): Fuel Controlling System · General Electric GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2 and 17 more. Effective Mar 9, 2022 - [AD 2021-21-05](https://openairdocs.org/ad/2021-21-05): Engine Controls · General Electric GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2 and 17 more. Effective Dec 28, 2021 - [AD 2021-13-16](https://openairdocs.org/ad/2021-13-16): Engine Fuel Distribution · General Electric GEnx-2B67, GEnx-2B67/P and GEnx-2B67B. Effective Aug 25, 2021 - [AD 2021-11-07](https://openairdocs.org/ad/2021-11-07): Turbine Engine Compressor Section · General Electric Genx-1B76A/P2, GEnx-1B64, GEnx-1B64/P1 and 17 more. Effective Jul 30, 2021 - [AD 2021-02-07](https://openairdocs.org/ad/2021-02-07): Engine Fuel Distribution · General Electric Genx-1B76A/P2, GEnx-1B64, GEnx-1B64/P1 and 14 more. Effective Mar 30, 2021 - [AD 2020-25-10](https://openairdocs.org/ad/2020-25-10): Turbine Section · General Electric Genx-1B76A/P2, GEnx-1B64/P2, GEnx-1B67/P2 and 6 more. Effective Jan 21, 2021 - [AD 2020-20-12](https://openairdocs.org/ad/2020-20-12): Turbine Engine Combustion Section · General Electric Genx-1B76A/P2, GEnx-1B64, GEnx-1B64/P1 and 14 more. Effective Nov 5, 2020 - [AD 2020-20-11](https://openairdocs.org/ad/2020-20-11): Turbine Section · General Electric Genx-1B76A/P2, GEnx-1B64/P2, GEnx-1B67/P2 and 6 more. Effective Nov 3, 2020 - [AD 2020-13-04](https://openairdocs.org/ad/2020-13-04): Engine Controls · General Electric Genx-1B76A/P2, GEnx-1B54, GEnx-1B54/P1 and 28 more. Effective Jul 24, 2020 - [AD 2019-02-01](https://openairdocs.org/ad/2019-02-01): Turbine section · General Electric Genx-1B76A/P2, GEnx-1B54, GEnx-1B54/P1 and 28 more. Effective Feb 25, 2019 - [AD 2018-21-12](https://openairdocs.org/ad/2018-21-12): Engine Fuel Distribution · General Electric GEnx-2B67, GEnx-2B67/P and GEnx-2B67B. Effective Jan 4, 2019 - [AD 2018-14-12](https://openairdocs.org/ad/2018-14-12): Turbine Section · General Electric GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2 and 12 more. Effective Aug 30, 2018 - [AD 2017-26-01](https://openairdocs.org/ad/2017-26-01): Turbine Section · General Electric GEnx-1B64/P2, GEnx-1B67/P2, GEnx-1B70/75/P2 and 3 more. Effective Jan 23, 2018 - [AD 2017-12-02](https://openairdocs.org/ad/2017-12-02): Fuel Injector Nozzle · General Electric Genx-1B76A/P2, GEnx-1B64, GEnx-1B64/P1 and 13 more. Effective Jul 13, 2017 - [AD 2016-20-15](https://openairdocs.org/ad/2016-20-15): Engine fan stator module assembly · General Electric GEnx-1B64/P2, GEnx-1B67/P2, GEnx-1B70/75/P2 and 3 more. Effective Nov 18, 2016 - [AD 2016-04-11](https://openairdocs.org/ad/2016-04-11): high-pressure turbine (HPT) rotor stage 1 blade · General Electric GEnx-1B54, GEnx-1B58, GEnx-1B64 and 2 more. Effective Apr 1, 2016 - [AD 2015-23-04](https://openairdocs.org/ad/2015-23-04): Non-conforming ball valve in the oil filler cap · General Electric GEnx-1B54, GEnx-1B54/P1, GEnx-1B54/P2 and 22 more. Effective Dec 17, 2015 - [AD 2013-23-14](https://openairdocs.org/ad/2013-23-14): Critical rotating life-limited parts (LLPs) · General Electric GEnx-2B67 and GEnx-2B67B. Effective Jan 7, 2014 - [AD 2013-16-15](https://openairdocs.org/ad/2013-16-15): Booster anti-ice (BAI) air duct · General Electric GEnx-2B67B. Effective Sep 23, 2013 - [AD 2012-19-08](https://openairdocs.org/ad/2012-19-08): Fan mid shafts (FMS) · General Electric GEnx-1B54, GEnx-1B54/P1, GEnx-1B58 and 13 more. Effective Sep 21, 2012 - [AD 2018-16-07](https://openairdocs.org/ad/2018-16-07) (historical): Turbine Section · General Electric Genx-1B76A/P2, GEnx-1B54, GEnx-1B54/P1 and 28 more. Effective Aug 15, 2018 - [AD 2017-09-06](https://openairdocs.org/ad/2017-09-06) (historical): Engine · General Electric Genx-1B76A/P2, GEnx-1B54, GEnx-1B54/P1 and 28 more. Effective Jun 9, 2017 - [AD 2015-15-03](https://openairdocs.org/ad/2015-15-03) (historical): Power loss in ice crystal icing (ICI) conditions · General Electric GEnx-1B54, GEnx-1B54/P1, GEnx-1B54/P2 and 26 more. Effective Aug 24, 2015 ## Registered aircraft by registry model (OpenAirDocs) - [GE GENX-1B74/75/](https://openairdocs.org/engine/ge-genx-1b74-75-series): 60 aircraft (registry code 30222) - [GE GENX-1B70/P2](https://openairdocs.org/engine/ge-genx-1b70-p2): 44 aircraft (registry code 30228) - [GE GENX-2B67/P](https://openairdocs.org/engine/ge-genx-2b67-p): 35 aircraft (registry code 30235) - [GE GENX-1B76A/P2](https://openairdocs.org/engine/ge-genx-1b76a-p2): 29 aircraft (registry code 30231) - [GE GENX-1B76/P2](https://openairdocs.org/engine/ge-genx-1b76-p2): 18 aircraft (registry code 30238) - [GE GENX series](https://openairdocs.org/engine/ge-genx-series): 17 aircraft (registry code 30163) - [GE GENX-2B67B](https://openairdocs.org/engine/ge-genx-2b67b): 10 aircraft (registry code 30165) - [GE GENX-2B67](https://openairdocs.org/engine/ge-genx-2b67): 6 aircraft (registry code 30234) - [GE GENX-1B75/P2](https://openairdocs.org/engine/ge-genx-1b75-p2): 5 aircraft (registry code 30232) - [GE GENX-1B70/P1](https://openairdocs.org/engine/ge-genx-1b70-p1): 3 aircraft (registry code 30219) - [GE GENX-1B70](https://openairdocs.org/engine/ge-genx-1b70): 2 aircraft (registry code 30214) - [GE GENX-1B70/75/](https://openairdocs.org/engine/ge-genx-1b70-75-series): 2 aircraft (registry code 30221) - [GE GENX-1B67/P2](https://openairdocs.org/engine/ge-genx-1b67-p2): 1 aircraft (registry code 30227) - [GE GENX-1B54](https://openairdocs.org/engine/ge-genx-1b54): 0 aircraft (registry code 30210) - [GE GENX-1B54/P1](https://openairdocs.org/engine/ge-genx-1b54-p1): 0 aircraft (registry code 30215) - [GE GENX-1B54/P2](https://openairdocs.org/engine/ge-genx-1b54-p2): 0 aircraft (registry code 30224) - [GE GENX-1B58](https://openairdocs.org/engine/ge-genx-1b58): 0 aircraft (registry code 30211) - [GE GENX-1B58/P1](https://openairdocs.org/engine/ge-genx-1b58-p1): 0 aircraft (registry code 30216) - [GE GENX-1B58/P2](https://openairdocs.org/engine/ge-genx-1b58-p2): 0 aircraft (registry code 30225) - [GE GENX-1B64](https://openairdocs.org/engine/ge-genx-1b64): 0 aircraft (registry code 30212) - [GE GENX-1B64/P1](https://openairdocs.org/engine/ge-genx-1b64-p1): 0 aircraft (registry code 30217) - [GE GENX-1B64/P2](https://openairdocs.org/engine/ge-genx-1b64-p2): 0 aircraft (registry code 30226) - [GE GENX-1B67](https://openairdocs.org/engine/ge-genx-1b67): 0 aircraft (registry code 30213) - [GE GENX-1B67/P1](https://openairdocs.org/engine/ge-genx-1b67-p1): 0 aircraft (registry code 30218) - [GE GENX-1B70/72/](https://openairdocs.org/engine/ge-genx-1b70-72-series): 0 aircraft (registry code 30220) - [GE GENX-1B75/P1](https://openairdocs.org/engine/ge-genx-1b75-p1): 0 aircraft (registry code 30223) - [GE GENX-1B78/P2](https://openairdocs.org/engine/ge-genx-1b78-p2): 0 aircraft (registry code 30233) --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). 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