TCDS E00049EN

Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00049EN) 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 Aviation 1 Neumann Way Cincinnati, OH 45215-6310 I. MODELS GE90-76B GE90-77B GE90-85B GE90-90B TYPE Dual rotor, axial flow, high bypass ratio turbofan. The 10-stage high pressure compressor is driven by a 2-stage high pressure turbine. The single stage fan and 3-stage low pressure compressor are driven by a 6-stage low pressure turbine. RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb Takeoff (5 min. see NOTE 16) at sea level, static thrust, lb Flat rating ambient temperature Takeoff Maximum continuous 75,430 81,070 91ºF/32.8ºC 77ºF/25ºC 75,430 81,700 - - - - 81,230 88,870 86ºF/30ºC - - 90,580 94,000 - - - - COMPONENTS (GE P/Ns) Hydromechanical Control Unit Full Authority Digital Engine Control (FADEC) Hardware (H/W) & Software (S/W) H/W (See NOTE 21) S/W (See NOTE 21) 1693M75 1851M65 1838M16 1959M87 1838M16 1853M99 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - * PAGE 1 2 3 4 5 6 7 8 9 10 11 12 REV. 21 9 18 19 21 18 18 18 18 18 18 21 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "- - -" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00049EN TCDS NUMBER E00049EN REVISION 21 DATE: June 11, 2024 GENERAL ELECTRIC COMPANY MODELS: GE90-76B GE90-90B GE90 -113B GE90-77B GE90-94B GE90 -115B GE90-85B GE90-110B1 TCDS E00049EN Page 2 of 12 I. MODELS (cont.) GE90-76B GE90-77B GE90-85B GE90-90B Configuration Type Box (See NOTE 10) FADEC Rating Plug Main Fuel Pump IGNITION SYSTEM Two ignition units GE P/N Two ignitor plugs GE P/N 320-837-701-0 320-839-501-0 320-892-101-0 320-892-201-0 320-846-701-0 320-892-601-0 320-915-201-0 320-921-501-0 320-833-701-0 1689M10 9238M66 1754M84 - - - - - - - - - - - - - - - - - - 320-833-901-0 - - - - - - - - - - - - - - - - - - - - - - - - 320-833-801-0 320-834-201-0 - - - - - - - - - - - - - - - - - - - - - - - - 320-834-001-0 - - - - - - PRINCIPAL DIMENSIONS (in) Length (Fan spinner to nozzle centerbody) Width (maximum envelope) Height (maximum envelope) 286.9 152.4 155.6 - - - - - - - - - - - - - - - - - - WEIGHT (DRY) Includes basic engine, basic engine accessories, and optional equipment as listed in the manufacturer's engine specifications. 17,400 - - - - - - CENTER OF GRAVITY LOCATIONS (in) (Engine only) Station (axial) Waterline Buttline 227.5+1.5 99.9+0.5 100.4+0.5 - - - - - - - - - - - - - - - - - - TCDS E00049EN Page 3 of 12 II. MODELS GE90-94B TYPE Dual rotor, axial flow, high bypass ratio turbofan. The 10-stage high pressure compressor is driven by a 2-stage high pressure turbine. The single stage fan and 3-stage low pressure compressor are driven by a 6-stage low pressure turbine. RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb Takeoff (5 min. see NOTE 16) at sea level, static thrust, lb Flat rating ambient temperature Takeoff Maximum continuous 90,580 97,300 86oF/30ºC 77oF/25ºC COMPONENTS (GE P/Ns) Hydro-mechanical Control Unit Full Authority Digital Engine Control (FADEC) Hardware (H/W) & Software (S/W) Hardware (H/W) (See NOTE 21) Software (S/W) (See NOTE 21) Configuration Type Box (See NOTE 10) FADEC Rating Plug Main Fuel Pump IGNITION SYSTEM Two ignition units GE P/N Two ignitor plugs GE P/N 1851M65 1959M87 1838M16 1853M99 320-921-501-0 320-834-301-0 1689M10 9238M66 1754M84 PRINCIPAL DIMENSIONS (in) Length (Fan spinner to nozzle centerbody) Width (maximum envelope) Height (maximum envelope) 286.9 152.4 155.6 WEIGHT (DRY) Includes basic engine, basic engine accessories, and optional equipment as listed in the manufacturer's engine specifications. 17,400 CENTER OF GRAVITY LOCATIONS (in) (Engine only) Station (axial) Waterline Buttline 227.5+1.5 99.9+0.5 100.4+0.5 TCDS E00049EN Page 4 of 12 III MODELS GE90-110B1 GE90-113B GE90-115B TYPE RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb Takeoff (5 min. see NOTE 16) at sea level, static thrust, lb Flat rating ambient temperature Takeoff Maximum continuous COMPONENTS (GE P/Ns) Hydro-mechanical Control Unit Full Authority Digital Engine Control (FADEC) Hardware (H/W) (See NOTE 21) Software (S/W) (See NOTE 21 Configuration Type Box FADEC Rating Plug G01 G02 G03 G04 Main Fuel Pump IGNITION SYSTEM Two ignition units GE P/N Two ignitor plugs GE P/N 110,000 110,760 92ºF/33ºC 77ºF/25ºC 110,000 113,530 86ºF/30ºC 77ºF/25ºC 110,000 115,540 86ºF/30ºC 77ºF/25ºC 1962M80 1962M67 2041M27 390-850-001-0 390-851-001-0 390-850-002-0 390-851-002-0 390-801-011-0 390-803-001-0 390-803-011-0 390-803-021-0 2042M69 9238M66 1754M84 - - - - - - - - - - - - - - 390-802-001-0 390-804-001-0 - - - - - - - - - - - - - - - - - - - - - - - - 390-800-001-0 390-805-001-0 390-805-011-0 390-805-021-0 - - - - - - PRINCIPAL DIMENSION (in) Length (Fan spinner to nozzle centerbody) Width (maximum envelope) Height (maximum envelope) 286.67 148.38 154.56 - - - - - - - - - - - - WEIGHT (DRY) Includes basic engine, basic engine accessories, and optional equipment as listed in the manufacturer’s engine specifications. 19316 - - - - CENTER OF GRAVITY LOCATIONS (in) (Engine only) Station (axial) Waterline Buttline 219.2+1.5 100.14+0.5 100.28+0.5 - - - - - - - - - - - - TCDS E00049EN Page 5 of 12 IV. MODELS ALL FUEL See NOTE 7 for approved fuels. OIL Type 2 oils conforming to GE90 Specification D50TF1 or the latest revisions are authorized. For approved brand of oils refer to GE90 Service Bulletin 79-001. CERTIFICATION BASIS (-76B/-77B/-85B/-90B) CERTIFICATION BASIS (-94B) CERTIFICATION BASIS (-113B) CERTIFICATION BASIS (-110B1, -115B) Title 14, Code of Federal Regulations (14 CFR) part 33, effective February 1, 1965, amendments 33-1 through 33-15, inclusive; 14 CFR part 34, amendment 4, effective June 29, 2009; and Special Condition Number SC-33-ANE-08-NE; and para. 33.71(c)(4), amendment 33-27, effective November 24, 2008. 14 CFR part 33, effective February 1, 1965, including amendments 33-1 through 33-15, and amendment 33-19; 14 CFR part 34, amendment 5, effective December 31, 2012; Special Condition SC-33-ANE-08-NE, and Equivalent Level of Safety Finding for §33.68(b) Number 8040-ELOS-00-NE-01; and para. 33.71(c)(4), amendment 33-27, effective November 24, 2008. See NOTE 25 for detailed summary of the certification basis for fuel venting and exhaust emissions for GE90-94B model. 14 CFR part 33, effective February 1, 1965, including Amendments 33-1 through 33-20; 14 CFR part 34, amendment 5, effective December 31, 2012; Special Condition SC-33-ANE-08-NE, and Exemption to §33.73(b), No. 7953 dated January 15, 2003; and para. 33.71(c)(4), amendment 33-27, effective November 24, 2008, Part 33.27(c)(2)(v) ELOS # GE90-2015-MT-07-P-1 dated July 6, 2016, Part 33.27(c) ELOS # GE90-2016-MT-03-P2 dated November 30, 2016. See NOTE 25 for detailed summary of the certification basis for fuel venting and exhaust emissions for GE90-113B model. 14 CFR part 33, effective February 1, 1965, including Amendments 33-1 through 33-20; 14 CFR part 34, amendment 7A, effective May 24, 2024; Special Condition SC-33-ANE-08-NE, and Exemption to §33.73(b), No. 7953 dated January 15, 2003; and para. 33.71(c)(4), amendment 33-27, effective November 24, 2008, Part 33.27(c)(2)(v) ELOS # GE90-2015-MT-07-P-1 dated July 6, 2016, Part 33.27(c) ELOS # GE90-2016-MT-03-P2 dated November 30, 2016. See NOTE 25 for detailed summary of the certification basis for fuel venting and exhaust emissions for GE90-110B1 and GE90-115B models. TYPE CERTIFICATE E00049EN MODELS APPLICATION DATE ISSUED/AMENDED GE90-76B DEC 16, 1991 FEB 2, 1995 GE90-85B DEC 16, 1991 FEB 2, 1995 GE90-90B AUG 10, 1994 JUL 2, 1996 GE90-77B NOV 20, 1995 JUL 2, 1996 GE90-94B MAR 5, 1999 JUN 9, 2000 GE90-113B JUN 27, 2000 JUL 30, 2003 GE90-115B JUN 27, 2000 JUL 30, 2003 GE90-110B1 JAN 9, 2002 JUL 30, 2003 GE90-75B DEC 16, 1991 FEB 2, 1995 (Deleted JUL 24, 1995) GE90-92B AUG 10, 1994 JUL 2, 1996 (Deleted June 26, 2000) PRODUCTION BASIS GE90-76B/-77B/-85B/-90B/-94B/-110B1/-113B/-115B Production Certificate No. 108 TCDS E00049EN Page 6 of 12 NOTES NOTE 1. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS GE90-76B GE90-77B/-85B/-90B/-94B GE90-110B1/-113B/-115B Low pressure rotor (N1) 2,465 RPM 2,465 RPM 2,602 RPM (109.0%)* (109.0%)* (110.5%)*** High pressure rotor (N2) 10,705 RPM 10,918 RPM 11,292 RPM (114.7%)** (117%)** (121%)** * 100% N1 is 2,261.5 RPM ** 100% N2 is 9,332.0 RPM *** 100% N1 is 2,355.0 RPM NOTE 2. MAXIMUM PERMISSIBLE TEMPERATURES Indicated turbine exhaust gas temperature (T49) GE90-76B GE90-77B/-85B/-90B/-94B (see NOTE 10) Takeoff (5 minute; see NOTE 16) 1,787ºF (975ºC)* 1,885ºF (1030ºC) Maximum Continuous 1,697ºF (925ºC) 1,859ºF (1015ºC) Ground starts (manual or auto) 1,382ºF (750ºC) 1,382ºF (750ºC)** Inflight starts (manual or auto) 1,517ºF (825ºC) - - * 60 seconds maximum transient 1,796ºF (980ºC) - - - ** 40 seconds start EGT exceedance 1,517ºF (825ºC) limit for –94B only Oil temperature limits Continuous 255ºF (124ºC) - - Transient 275ºF (135ºC) - - Indicated turbine exhaust gas temperature (T49) GE90-110B1/ -113B/ -115B Takeoff (5 minute; see NOTE 16) 1,994ºF (1,090ºC)*** Maximum Continuous 1,922ºF (1,050ºC) Ground starts (manual or auto) 1,382ºF (750ºC) Inflight starts (manual or auto) 1,517ºF (825ºC) ***30 seconds maximum transient 2,003ºF (1,095ºC) Oil temperature limits Continuous 270ºF (132ºC) Transient 290ºF (143ºC) TCDS E00049EN Page 7 of 12 NOTE 3. FUEL AND OIL PRESSURE LIMITS FUEL PRESSURE LIMITS AT THE ENGINE PUMP INLET Maximum allowable fuel pressure is 70 psig. Minimum allowable fuel pressure under normal operating conditions (fully operational aircraft fuel system) is 5.0 psia. At altitudes of 38,000 feet and below, transitory excursions of 15 seconds or less to a minimum fuel pressure of 3.5 psia are allowable provided the average fuel pressure remains above 4.5 psia. OIL PRESSURE LIMITS LOW PRESSURE The limit is 10.0 psid (69 kPa diff.). (See NOTE 14) NOTE 4. ACCESSORY DRIVE PROVISIONS GE90-76B/-77B/-85B/-90B/-94B DRIVE PAD Rotation Facing Gearbox Pad Gear Ratio To Core Speed Horsepower Continuous Pad Rating HP (kW) Shear Torque in-lb (N-m) Maximum Overhung Moment in-lb (N-m) IDG (120 kVA) CCW (*) 0.7947 243 (181.3) 10,000 – 10,500 2,000 (226.0) (1,130 – 1,187) Hydraulic Pump CCW 0.3783 85 (63.5) 4,250 – 4,850 230 (26.0) (480 - 548) VSCF/PMG CCW 2.4126 58 (43.3) 3,500; 4,500** 400 (45.2) Generator (395, 508)** (20/30 kVA) IDG Overload Limits 304 HP (226.8 kVA) for 5 minutes per 1,000 hours of operation 406 HP (302.9 kVA) for 5 seconds per 1,000 hours of operation 500 HP (373.0 kVA) electrical fault VSCF/PMG Overload limits 87 HP (64.9 kVA) for 5 minutes per 1,000 hours of operation 116 HP (86.5 kVA) for 5 seconds per 1,000 hours of operation 128 HP (95.5 kVA) electrical fault 100% core speed is 9,332 RPM (*) Counter Clockwise (**) Shear torque capability is a function of operator requirements. Consult GE Aviation for installed capability. TCDS E00049EN Page 8 of 12 NOTE 4. Cont. GE90-110B1/-113B/-115B DRIVE PAD Rotation Facing Gearbox Pad Gear Ratio To Core Speed Horsepower Continuous Pad Rating HP (kW) Shear Torque in-lb (N-m) Maximum Overhung Moment in-lb (N-m) IDG (120 kVA) CCW (*) 0.7947 243 (181.3) 10,500 max 2,000 (226.0) (1,187 max) Hydraulic Pump CCW 0.3783 85 (63.5) 4,250 – 4,850 230 (26.0) (480 - 548) VSCF/PMG CCW 2.4126 58 (43.3) 1,250 max 400 (45.2) Generator (141.2 max) (20/30 kVA) IDG Overload Limits 304 HP (226.8 kVA) for 5 minutes per 1,000 hours of operation 406 HP (302.9 kVA) for 5 seconds per 1,000 hours of operation 500 HP (373.0 kVA) electrical fault VSCF/PMG Overload limits 87 HP (64.9 kVA) for 5 minutes per 1,000 hours of operation 116 HP (86.5 kVA) for 5 seconds per 1,000 hours of operation 128 HP (95.5 kVA) electrical fault 100% core speed is 9,332 RPM (*) Counter Clockwise NOTE 5. 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# NOTE 6. MAXIMUM PERMISSIBLE AIR BLEED EXTRACTION Allowable Bleed Limits (%) GE90-76B/-77B/-85B/-90B/-94B Below 23% N1K 23 to 31% N1K 31 to 57.4% N1K 57.4 to 80% N1K 80 to 96.8% N1K Above 96.8% N1K Stage 4 S tage 7 Stage 10 Maximum Allowable 7.8 1.8 13.6 15.4 7.6 1.6 12.8 14.4 7.4 1.3 12.6 13.9 7.2 1.3 12.6 13.9 7.0 1.3 6.5 8.3 6.5 1.3 6.5 7.8 TCDS E00049EN Page 9 of 12 NOTE 6. Cont. GE90-110B1/-113B/-115B Stage 4 Stage 7 Stage 9 Maximum Allowable Below 27% N1K At 51% N1K At 80% N1K At 88% N1K At 93% N1K today Above 93% N1K 7.6 7.6 7.6 7.6 7.6 7.6 1.5 1.5 1.5 1.5 1.5 1.5 11.2 11.5 12.0 11.0 8.0 7.3 12.7 13.0 13.5 12.5 9.1 9.1 NOTE 7. FUEL Approved fuels must conform to GE Specification D50TF2. Certain fuels such as those produced to PRC Specification RP3 meet the requirements of D50TF2 by means of the Specification. The engine will operate with a mixture of fuels or additives conforming to GE Specification D50TF2. NOTE 8. Life limits established for critical rotating components for: GE90-76B/-77B/-85B/-90B/-94B are published in Chapter 5 of the GE90 Engine Manual, GEK 100700 GE90-110B1/-113B/-115B are published in Chapter 5 of the GE90-100 Engine Manual, GEK 109993 NOTE 9. 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. GE90-76B engines with configuration type box number 320-839-501-0 must incorporate the HP/LP turbine hardware and associated changes per General Electric GE90 Service Bulletin 72-169. The FADEC incorporates a 30ºC shunt. The corresponding indicated EGT limits are 975ºC (take-off), 980ºC (take-off with 60 second max. transient), and 965ºC (max. continuous). NOTE 11. For ground operation in icing conditions the following procedures must be observed: GE90-76B/-77B/-85B/-90B/-94B During ground operations (including taxi-in and taxi-out) in icing conditions, the pilot must perform one of the following shed procedures: (a) Run up the engines momentarily to a minimum of 50% N1 at intervals not to exceed 15 minutes, or (b) For operation at ambient conditions of -6 ºC (23 ºF) and above, and at airport altitudes up to 3,048 meters (10,000 ft), perform the following at intervals not to exceed 60 minutes: 1) Increase throttle to a minimum of 55% N1 2) Dwell at the specified N1 for 20 seconds minimum 3) Decelerate to idle or proceed with normal takeoff procedure. See GE90 Operating Instructions Manual GEK 100703. GE90-110B1/-113B/-115B During ground operations (including taxi-in and taxi-out) in icing conditions, the engine must be run up momentarily to a minimum of 50% N1 at intervals not to exceed 60 minutes. See GE90-100 Operating Instructions Manual GEK109994. Note: For possible variations in engine acceleration times in icing conditions see the GE90-100 Installation Manual GEK 109995. TCDS E00049EN Page 10 of 12 NOTE 12. All GE90 engines with configuration type box part numbers 320-892-101-0 or 320-892-201-0 must incorporate the PT25 extended wedge ice shield per GE90 Service Bulletin 77-008 and must incorporate FADEC software P/N 1853M99P06 (version 9.1.9.7 or later) per GE90 Service Bulletin 73-040. All GE90 engines with configuration type box part numbers 320-837-701-0, 320-839-501-0, 320-892-101-0, 320-892- 201-0, 320-846-701-0, 320-892-601-0 and 320-915-201-0, have a minimum permissible N2 of 6,066 RPM for in- flight operation during icing conditions. All GE90 engines with configuration type box part numbers 320-921-501-0 have a minimum permissible N2 of 6,310 RPM for in-flight operation during icing conditions. All GE90 engines with configuration type box part numbers 390-850-001-0 and 390-851-001-0 have a minimum permissible N1 of 730 RPM for in-flight operation during icing conditions. NOTE 13. Demonstration of compliance to §33.68, Induction System Icing is installation specific to the B777-200LR/300ER and B777 Freighter airplanes for the GE90-110B1/-113B/-115B model engines. Installation of these model engines on different airplane models or types will require a separate evaluation and finding of compliance to §33.68. NOTE 14. During "negative-G" operation only, it is permissible to operate below minimum oil pressure of 10 psid (69.0 kPa diff) for a maximum of 15 seconds. See GE90 Operating Instructions Manual, GEK 100703, for GE90-76B/-77B/-85B/-90B/-94B See GE90-100 Operating Instructions Manual, GEK 109994, for GE90-110B1/-113B/-115B. NOTE 15. THESE MODELS INCORPORATE THE FOLLOWING GENERAL CHARACTERISTICS ENGINE MODEL CHARACTERISTICS GE90-76B Basic Model GE90-77B Same as GE90-76B except improved HPT/LPT flowpath and higher thrust ratings. Corresponding Rating Plug changes. GE90-85B Same as GE90-76B except higher thrust ratings. Corresponding Rating Plug changes. GE90-90B Same as GE90-77B except higher thrust ratings. Corresponding Rating Plug changes. GE90-94B Same as GE90-90B except 3D aero HPC and higher thrust ratings. Corresponding rating plug changes. GE90-110B1 Differs primarily from basic model in FAN, LPC, HPC, HPT and LPT hardware, higher takeoff thrust rating with increased speed, and temperature limitations. Corresponding rating plug changes. See NOTE 22. GE90-113B Same as GE90-110B1 except higher thrust ratings. Corresponding Rating Plug changes. GE90-115B Same as GE90-113B except higher thrust ratings. Corresponding Rating Plug changes. TCDS E00049EN Page 11 of 12 NOTE 16. The normal 5 minute takeoff time limit may be extended to 10 minutes for engine out contingency. NOTE 17. TIME LIMITED DISPATCH CRITERIA Criteria pertaining to the dispatch and maintenance requirements for the engine control systems are specified in: For the GE90-76B/-77B/-85B/-90B/-94B see General Electric Document GEK 103084 and the Airworthiness Limitations Section of the GE90 Engine Manual GEK 100700, which defines the various configurations and maximum operating intervals. For the GE90-110B1/-113B/-115B the requirements are defined in the Airworthiness Limitations section of the GE90- 100 Engine Manual GEK 109993 NOTE 18. For approval of repairs of fan blade composite material in the root section of the fan blade up to the inner annulus flow path line see the Airworthiness Limitations Section of GE90 Engine Manual GEK 100700 for the GE90-76B/-77B/- 85B/-90B/-94B and GE90-100 Engine Manual GEK 109993 for the GE90-110B1/-113B/-115B. NOTE 19. Note deleted. NOTE 20. Reserved. NOTE 21. The FADEC unit P/N originally defined both hardware and software. The hardware and software are now defined by separate P/Ns. The engine should be equipped with a FADEC defined either by the combined P/N or by the hardware and the software P/Ns. NOTE 22. NOTE 23. An exemption to §21.19(a) was granted and issued in Washington, DC, on August 26, 2002, for the GE90-110B1/- 113B/-115B engine models. This exemption allowed GEAE to amend Type Certificate No. E00049EN to add these models rather than apply for a new type certificate for those engines, subject to the following conditions and limitations: 1. GEAE must comply with §21.17 as if it was a new type certificate. 2. GEAE must conduct a large flocking bird test as part of compliance with §33.76, Bird Ingestion. 3. GEAE must include an engine test to demonstrate compliance to §33.90, Initial Maintenance Inspection. 4. An applicant installing the GE90-110B1/-113B/-115B engine models into an aircraft must comply with all of the applicable airworthiness standards for a new type certificated engine, including applicable aircraft special conditions. Demonstration of compliance to §33.73(b) Power or Thrust Response is installation specific to the B777- 200LR/300ER and B777 Freighter airplanes for the GE90-110B1/-113B/-115B model engines. Installation of these model engines on different airplane models or types will require a separate evaluation and finding of compliance to §33.73(b). NOTE 24. The engine oil tank filler cap of GE90-76B/-77B/-85B/-90B/-94B and GE90-110B1/-113B/-115B engine model meet the requirement of §33.71(c)(4). TCDS E00049EN Page 12 of 12 NOTE 25. 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: GE90-94B and GE90-113B. 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)(1). Carbon Monoxide (CO) Emission Standards: 14 CFR 34.21(d)(1)(ii); in addition, 40 CFR 87.23(c)(l). Hydrocarbons (HC) Emission Standards: 14 CFR 34.21(d)(l)(i); in addition, 40 CFR 87.23(c)(l). Oxides of Nitrogen (NOx) Emission Standards: 14 CFR 34.23(a)(2); in addition, 40 CFR 87.23(c)(2). 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 III, Chapter 2, Section 2.2.2 for SN, Section 2.3.2 for CO and HC, Section 2.3.2 .d.3 for NOx (also known as CAEP/6), and Part II Chapter 2 for fuel venting have also been demonstrated. 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: GE90-110B1 and GE90-115B. 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(a)(2); in addition, 40 CFR 1031.60(e)(4) (also known as Tier 6 in-production) 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.d for Oxides of Nitrogen (also known as CAEP/6), • Part III, Chapter 4, Section 4.2.2.1 for nvPM Mass Concentration (also known as CAEP/10), and