TCDS E00088EN

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00088EN TCDS NUMBER E00088EN REVISION: REVISION 7 DATE: April 1, 2026 CFM INTERNATIONAL, S.A. MODEL: LEAP-1B28 LEAP-1B28B2 LEAP-1B28B1 LEAP-1B28B3 LEAP-1B27 LEAP-1B25 LEAP-1B21 LEAP-1B23 LEAP-1B28B2C LEAP-1B28BBJ1 LEAP-1B28BBJ2 E ngines of model described herein conforming with this data sheet (which is part of Type Certificate Number E00088EN) 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. TY PE CERTIFICATE (TC) HOLDER: CFM International, S.A. 2 Boulevard du Général Martial Valin 75724 Paris Cedex 15 France I. MODELS LEAP-1B28 LEAP-1B28B2 LEAP-1B28B1 LEAP-1B28B3 TYPE High bypass turbofan engine, with: coaxial front fan/booster driven by a multi-stage low pressure turbine; a multi-stage compressor; two-stage high pressure turbine; twin annular pre swirl combustors; and a full authority digital engine control (FADEC). RATINGS See Note 1. Static Thrust at Sea Level lb (daN) • Takeoff (5 min.) • Maximum continuous Flat Rating Ambient Temperature at Sea Level °F (°C) • Takeoff • Maximum continuous 29,317 (13,041) 28,690 (12,762) 86 (30) 77 (25) - - - - - - - - - - - - - - - - - - - - - - - - COMPONENTS Part Number Full Authority Digital Control (FADEC) • Electronic control unit • PSS • Software 2474M64 2474M65 2628M86, 2628M87, 2628M88, 2697M83 - - - - - - - - - - - - - - - - - - - - - - - - • Identification plug Refer to the latest revision of CFM Service Bulletin LEAP-1B SB 72-0018 for a list of Data Entry Plug part numbers. PAGE 1 2 3 4 5 6 7 8 9 10 11 12 REV. 7 7 7 7 3 6 5 4 3 4 6 4 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. E00088EN 2 of 11 I. MODELS (Cont.) LEAP-1B28 LEAP-1B28B2 LEAP-1B28B1 LEAP-1B28B3 FUEL • Approved fuel conforming to GE Specification D50TF2, Classes A, C, D, and E. Primary fuel is D50TF2 Class-A (Jet A) with other fuels listed being acceptable alternates. No fuel control adjustment is required when changing from primary to alternate fuels. Use of aviation gasoline and D50TF2 Class-B, Wide-Cut Distillate (Jet B or JP-4) is not authorized. • Refer to the latest revision of CFM Service Bulletin LEAP-1B S/B 73-0001 for a list of fuels specifically approved for LEAP-1B engine. OIL • Synthetic type conforming to GE Specification D50TF1, Type I and Type II. • Refer to the latest revision of CFM Service Bulletin LEAP-1B S/B 79-0001 for a list of oil specifically approved for the LEAP-1B engine. PHYSICAL CHARACTERISTICS PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRV aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 123.9 (3147) 95.31 (2421) 88.82 (2256) - - - - - - - - - - - - - - - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, including basic engine accessories lb (kg) 6128 (2780) - - - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 211.8 (5380.0) 98.2 (2494) 98.2 (2494) - - - - - - - - - - - - - - - - - - II. MODELS LEAP-1B27 LEAP-1B25 TYPE High bypass turbofan engine, with: coaxial front fan/booster driven by a multi-stage low pressure turbine; a multi-stage compressor; two-stage high pressure turbine; twin annular pre swirl combustors; and a full authority digital engine control (FADEC). RATINGS See Note 1. Static Thrust at Sea Level lb (daN) • Takeoff (5 min.) 28,037 (12,471) 26,786 (11,915) • Maximum continuous 27,272 (12,131) 25,958 (11,547) Flat Rating Ambient Temperature at Sea Level °F (°C) • Takeoff • Maximum continuous 86 (30) 77 (25) 86 (30) 77 (25) COMPONENTS Part Number Full Authority Digital Control - - - - - - - - (FADEC) • Electronic control unit 2474M64 • PSS • Software 2474M65 2628M86, 2628M87, 2628M88, 2697M83 • Identification Plug Refer to the latest revision of CFM Service Bulletin LEAP-1B SB 72-0018 for a list of Data Entry Plug part numbers. E00088EN 3 of 11 II. MODELS (Cont.) LEAP-1B27 LEAP-1B25 FUEL • Approved fuel conforming to GE Specification D50TF2, Classes A, C, D, and E. Primary fuel is D50TF2 Class-A (Jet A) with other fuels listed being acceptable alternates. No fuel control adjustment is required when changing from primary to alternate fuels. Use of aviation gasoline and D50TF2 Class-B, Wide-Cut Distillate (Jet B or JP-4) is not authorized. • Refer to the latest revision of CFM Service Bulletin LEAP-1B S/B 73-0001 for a list of fuels specifically approved for LEAP-1B engine. OIL • Synthetic type conforming to GE Specification D50TF1, Type I and Type II. • Refer to the latest revision of CFM Service Bulletin LEAP-1B S/B 79-0001 for a list of oil specifically approved for the LEAP-1B engine. PHYSICAL CHARACTERISTICS PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRV aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 123.9 (3147) - - 95.31 (2421) - - 88.82 (2256) - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, including basic engine accessories lb (kg) 6128 (2780) - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 211.8 (5380.0) - - 98.2 (2494) - - 98.2 (2494) - - III. MODELS LEAP-1B21 LEAP-1B23 LEAP-1B28B2C TYPE High bypass turbofan engine, with: coaxial front fan/booster driven by a multi-stage low pressure turbine; a multi-stage compressor; two-stage high pressure turbine; twin annular pre swirl combustors; and a full authority digital engine control (FADEC). RATINGS See Note 1. Static Thrust at Sea Level lb (daN) • Takeoff (5 min.) 25,014 (11,127) 25,907 (11,524) 28,037 (12,471) • Maximum continuous 24,054 (10,700) 25,012 (11,126) 27,272 (12,131) Flat Rating Ambient Temperature at Sea Level °F (°C) • Takeoff • Maximum continuous 86 (30) 77 (25) 86 (30) 77 (25) 86 (30) 77 (25) Full Authority Digital Control (FADEC) • Electronic control unit • PSS • Software 2474M64 2474M65 2628M86, 2628M87, 2628M88, 2697M83 - - - - - - - - - - - - - - - - • Identification plug Refer to the latest revision of CFM Service Bulletin LEAP-1B SB 72-0018 for a list of Data Entry Plug part numbers. E00088EN 4 of 11 III. MODELS (Cont.) LEAP-1B21 LEAP-1B23 LEAP-1B28B2C FUEL • Approved fuel conforming to GE Specification D50TF2, Classes A, C, D, and E. Primary fuel is D50TF2 Class-A (Jet A) with other fuels listed being acceptable alternates. No fuel control adjustment is required when changing from primary to alternate fuels. Use of aviation gasoline and D50TF2 Class-B, Wide-Cut Distillate (Jet B or JP-4) is not authorized. Refer to the latest revision of CFM Service Bulletin LEAP-1B S/B 73-0001 for a list of fuels specifically approved for LEAP-1B engine. OIL • Synthetic type conforming to GE Specification D50TF1, Type I and Type II. Refer to the latest revision of CFM Service Bulletin LEAP-1B S/B 79-0001 for a list of oil specifically approved for the LEAP-1B engine. PHYSICAL CHARACTERISTICS PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRV aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 123.9 (3147) - - - - 95.31 (2421) - - - - 88.82 (2256) - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, including basic engine accessories lb (kg) 6128 (2780) - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 211.8 (5380.0) - - - - 98.2 (2494) - - - - 98.2 (2494) - - - - IV. MODELS LEAP-1B28BBJ1 LEAP-1B28BBJ2 TYPE High bypass turbofan engine, with: coaxial front fan/booster driven by a multi-stage low pressure turbine; a multi-stage compressor; two-stage high pressure turbine; twin annular pre swirl combustors; and a full authority digital engine control (FADEC). RATINGS See Note 1. Static Thrust at Sea Level lb (daN) • Takeoff (5 min.) 29,317 (13,041) 28,037 (12,471) • Maximum continuous 28,690 (12,762) 27,272 (12,131) Flat Rating Ambient Temperature at Sea Level °F (°C) • Takeoff • Maximum continuous 86 (30) 77 (25) 86 (30) 77 (25) COMPONENTS Part Number Full Authority Digital Control - - - - - - - - (FADEC) • Electronic control unit 2474M64 • PSS 2474M65 • Software 2628M86, 2628M87, 2628M88, 2697M83 • Identification plug Refer to the latest revision of CFM Service Bulletin LEAP-1B SB 72-0018 for a list of Data Entry Plug part numbers. E00088EN 5 of 11 IV. MODELS (Cont.) LEAP-1B28BBJ1 LEAP-1B28BBJ2 FUEL • Approved fuel conforming to GE Specification D50TF2, Classes A, C, D, and E. Primary fuel is D50TF2 Class-A (Jet A) with other fuels listed being acceptable alternates. No fuel control adjustment is required when changing from primary to alternate fuels. Use of aviation gasoline and D50TF2 Class-B, Wide-Cut Distillate (Jet B or JP-4) is not authorized. • Refer to the latest revision of CFM Service Bulletin LEAP-1B S/B 73-0001 for a list of fuels specifically approved for LEAP-1B engine. OIL • Synthetic type conforming to GE Specification D50TF1, Type I and Type II. • Refer to the latest revision of CFM Service Bulletin LEAP-1B S/B 79-0001 for a list of oil specifically approved for the LEAP-1B engine. PHYSICAL CHARACTERISTICS PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRV aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 123.9 (3147) - - 95.31 (2421) - - 88.82 (2256) - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, including basic engine accessories lb (kg) 6128 (2780) - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 211.8 (5380.0) - - 98.2 (2494) - - 98.2 (2494) - - THIS SPACE INTENTIONALLY LEFT BLANK E00088EN 6 of 11 CERTIFICATION BASIS 1. 14 CFR part 33, effective February 1, 1965, with Amendments 33-1 through 33-33 thereto. 2. 14 CFR part 34, Amendment 7A, effective May 24, 2024. 3. Equivalent Level of Safety (ELOS) Findings: • LEAP1B-2014-TC-01-P-1 to 14 CFR 33.27(c): High Pressure Shaft Loss-of-Load • LEAP1B-2014-TC-01-P-2 to 14 CFR 33.77: Foreign object Ingestion – Ice • LEAP1B-2014-TC-01-P-3 to 14 CFR 33.83: Vibration Test 4. Special Conditions: • Fan Blade Special Condition No. 33-017-SC 5. Exemptions: None MODEL APPLICATION DATE TC ISSUED/ AMENDED LEAP-1B28 09 May 2013 04 May 2016 LEAP-1B28B2 09 May 2013 04 May 2016 LEAP-1B28B1 27 October 2016 17 February 2017 LEAP-1B28B3 27 October 2016 17 February 2017 LEAP-1B27 27 October 2016 17 February 2017 LEAP-1B25 27 October 2016 17 February 2017 LEAP-1B21 27 February 2018 30 May 2018 LEAP-1B23 27 February 2018 30 May 2018 LEAP-1B28B2C 27 February 2018 30 May 2018 LEAP-1B28BBJ1 27 February 2018 30 May 2018 LEAP-1B28BBJ2 27 February 2018 30 May 2018 PRODUCTION BASIS Production Certificate No. 108 for engines produced in the United States by General Electric under license from CFM International, S.A. (See NOTE 16). Production Certification No. FR.21G.0007 dated December 17th, 2009 for engines produced in France by Safran under license from CFM International, S.A (See NOTE 16). THIS SPACE INTENTIONALLY LEFT BLANK. E00088EN 7 of 11 NOTES NOTE 1. ENGINE RATING Engine rating is based on calibrated stand performance under the following conditions: Takeoff thrust is nominally independent of ambient temperature (flat rated) up to ambient temperature of: Std + 15°C (30°C, 86°F), except as noted above. Maximum continuous thrust is nominally independent of ambient temperature (flat rated) up to ambient temperature of Std. + 10°C (25°C, 77°F). Assumptions: 1. Sea level static, standard day: 101.325 kPA Pressure (14.696 psia); 15°C temperature (59°F) 2. Zero customer bleed or customer horsepower extraction 3. Ideal inlet, 100% ram recovery 4. Production aircraft flight cowling 5. Production instrumentation 6. Fuel lower heating value of 18,400 BTU/lb Thrust Setting Parameter Power setting, power checks and control of engine thrust output in all operations is to be based on CFM International engine charts referring to fan speed. Fan speed sensors are included in the engine assembly for this purpose. NOTE 2. TEMPERATURE LIMITS Indicated Turbine Exhaust Gas Temperature 1 Takeoff, 5 min Maximum Continuous Max Transient (30 sec.) Ground Starts Inflight Starts • Starter Assist or Steady State Windmill • Quick Windmill Relight • High Power Fuel Cut 1038°C (1900°F) 1013°C (1855°F) 1048°C (1918°F) 753°C (1387°F) 883°C (1621°F) 920°C (1688°F) 981°C (1798°F) Fuel Pump Inlet Temperature Maximum Minimum (Cold Start) 54.5°C (130°F) -43°C (-45°F) Or the relevant fuel freezing point, whichever is higher. 1 EXHAUST GAS TEMPERATURE INDICATION The Exhaust Gas Temperature (EGT = T48) is measured at low pressure turbine inlet Model Ratings Indicated Turbine Exhaust Gas Temperature Maximum Exhaust Gas Temperature Limit Pre-Service Bulletin LEAP-1B 72-0169 Post-Service Bulletin LEAP- 1B 72-0169 LEAP-1B28, LEAP-1B28B2, LEAP-1B25, LEAP-1B27, LEAP-1B28B1, LEAP-1B28B3 Takeoff, 5 min 1038°C (1900°F) 1038°C (1900°F) 1060°C (1940°F) Maximum Continuous 1013°C (1855°F) 1013°C (1855°F) 1040°C (1904°F) LEAP-1B21, LEAP-1B23, LEAP-1B28B2C LEAP-1B28BBJ1, LEAP- 1B28BBJ2 Takeoff, 5 min 1038°C (1900°F) N/A 1060°C (1940°F) Maximum Continuous 1013°C (1855°F) N/A 1040°C (1904°F) LEAP-1B28, LEAP-1B28B2, LEAP-1B25, LEAP-1B27, LEAP-1B28B1, LEAP-1B28B3, LEAP-1B21, LEAP-1B23, LEAP-1B28B2C, LEAP- 1B28BBJ1, LEAP-1B28BBJ2 Pre-Service Bulletin LEAP-1B 73-0025 Post-Service Bulletin LEAP- 1B 73-0025 Ground Starts 753°C (1387°F) 753°C (1387°F) 800°C (1472°F) All models are certified for a max transient exhaust gas temperature (EGT) exceedance at take-off of 10°C for 30 seconds maximum. E00088EN 8 of 11 TEMPERATURE LIMITS (Cont.) Oil Temperature Maximum • Continuous operation • Transient (15 minutes) Minimum (Cold Start) • Engines Not Compliant with LEAP-1B S/B 72-0011 • Engines Compliant with LEAP-1B S/B 72-0011 140°C (284°F) 155°C (311°F) -19°C (-2°F) -40°C (-40°F) NOTE 3. FUEL AND OIL PRESSURE LIMITS Fuel Pressure Limits At The Engine Pump Inlet • 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 (34.5 kPa). The maximum vapor to liquid ratio at the engine fuel pump inlet with aircraft boost pumps operative is zero. • Aircraft Boost Pump Inoperative The engine fuel system operation is restricted with the aircraft boost pumps inoperative as outlined in the LEAP-1B Installation Manual. Oil Pressure Limits • The minimum pressure limit at idle is 17.4 psid (120.0 kPa) and varies up to 29 psid (200.0 kPa) at redline. • The maximum pressure is limited during cold starts by a 420.5 psid (2900 kPa differential) pressure- relief valve. NOTE 4. ACCESSORY DRIVE CHARACTERISTICS Electrical (IDG)* Rotation Direction+ CCW Pad Rating HP (kW) 0.418 168 (125) Shear Torque in.lb (N.m) 9408 (1063) Maximum overhung moment in.lb (N.m) 956 (108) (wet) Hydraulic Pump* Rotation Direction+ CCW Pad Rating in.lb (N.m) 0.191 1407 (159) Shear Torque in.lb (N.m) 3602 (407) Maximum overhung moment in.lb (N.m) 166 (18.8) (wet) * - Airframer Supplied Hardware + - CW = CLOCKWISE (looking at the Pad) ** - 100% core speed = 17,167 RPM NOTE 5. ENGINE MODEL CHARACTERISTICS The model shown on this TCDS has the following general characteristics LEAP-1B28 737MAX 8 Configuration LEAP-1B28B2 Same as LEAP-1B28 with additional takeoff thrust at high altitude conditions. LEAP-1B28B1 Same as LEAP-1B28B2 with revised takeoff thrust schedule at high altitude conditions. LEAP-1B28B3 Same as LEAP-1B28B2 with revised takeoff thrust schedule at low altitude conditions. LEAP-1B27 Same as LEAP-1B28 except for lower thrust rating. LEAP-1B25 Same as LEAP-1B28 except for lower thrust rating. LEAP-1B21 Same as LEAP-1B28 except for lower thrust rating. LEAP-1B23 Same as LEAP-1B28 except for lower thrust rating. LEAP-1B28B2C Same as LEAP-1B28B2 except thrust is capped by LEAP-1B27 below 1,000 ft and fairs to equivalent of LEAP-1B28B2 thrust by 7,000 ft LEAP-1B28BBJ1 Same as LEAP-1B28B1, but customized for Boeing Business Jet application LEAP-1B28BBJ2 Same as LEAP-1B282C, but customized for Boeing Business Jet application E00088EN 9 of 11 LEAP-1B engine series includes: LEAP-1B28, LEAP-1B28B2, LEAP-1B28B1, LEAP-1B28B3, LEAP-1B27, LEAP-1B25, LEAP-1B21, LEAP-1B23, LEAP-1B28B2C, LEAP-1B28BBJ1, LEAP-1B28BBJ2. The parts list for each engine model contains a configuration group number to identify the engine configuration. The engine model configuration is identified as LEAP-1BxxG0y where xx is the model and y is the applicable configuration as described in LEAP-1B Service Bulletin 72-0187. NOTE 6. NOT APPLICABLE NOTE 7. COMPATIBLE SYSTEM ASSEMBLIES Thrust Reverser The LEAP-1B engine is approved for use with the Boeing thrust reverser system P/N 315A6295 NOTE 8. NOT APPLICABLE NOTE 9. NOT APPLICABLE NOTE 10. NOT APPLICABLE NOTE 11. SPECIAL REQUIREMENTS ETOPS LEAP-1B series engines have complied with the requirements of §§ 33.4 (A33.3(c)), 33.71(c) (4) and 33.201, and are therefore eligible for installation on Extended Operations (ETOPS) and Early ETOPS approved airplanes. The demonstrated diversion time is 180 minutes at maximum continuous thrust plus 15 minutes at hold power. Note that ETOPS eligibility does not constitute airplane or operational level approvals necessary to conduct ETOPS flights. LEAP-1B S/B 71-0002 defines the requirements for conducting ETOPS operation. Time Limited Dispatch Criteria Criteria pertaining to the dispatch and maintenance requirements for the engine control systems are specified in the airworthiness limitation section of the LEAP-1B Engine Shop Manual (LEAP- 1B-05-17-00), which defines the various configurations and maximum operating intervals. A control system reliability monitoring program has been established with LEAP, as a contingency of the dispatch criteria approval, to ensure that overall engine control system and specific component failure rates do not exceed the maximum values permitted by the reliability analysis. Induction System Icing Demonstration of compliance to 14 CFR 33.68, Induction System Icing, is installation specific to the Boeing B737 MAX model aircraft for the LEAP-1B series engines Installation of these engine models on different airplane models or types will require a separate evaluation and finding of compliance to 14 CFR 33.68. NOTE 12. NOT APPLICABLE E00088EN 10 of 11 NOTE 13. SPECIAL OPERATING PROCEDURES Negative G Operation During negative g operation only, it is permissible to operate below minimum oil pressure (17.4 psid) for a maximum of 10 seconds. See LEAP-1B Specific Operating Instruction Manual, GEK 113769 Minimum Flight Idle The minimum permissible idle in flight is a non-adjustable limit, preset into the EEC Control schedule. Flight idle is engaged based on thrust lever position and operating conditions as specified in the LEAP-1B Specific Operating Instructions Manual, GEK 113769 Takeoff Time Limit The normal 5 minute takeoff rating may be extended to 10 minutes for engine out contingency, as specified in the LEAP-1B Specific Operating Instructions Manual, GEK 113769 Icing Operation For operation in icing conditions; requirements, limitations, and notes are specified in the LEAP- 1B Specific Operating Instructions Manual, GEK 113769 NOTE 14. NOT APPLICABLE NOTE 15. APPLICABLE INSTALLATION, MAINTENANCE AND OVERHAUL MANUALS The applicable installation and operating manuals are: 1) Turbofan Engine Installation Manual (EIM): CRL-2106b_1 2) Specific Operating Instructions (SOI): CRL-2105b (GEK 113769) Instructions for Continued Airworthiness (ICA): Engine Shop Manuals, Service Bulletins, Overhaul and Maintenance Manuals, Repair Manuals, Vendor Manuals, and Design Changes which contain a statement that the document is EASA approved or approved under authority of DOA No. EASA.21J.086 are accepted by the FAA and considered FAA approved. Repair data and related instructions are considered FAA approved or accepted as applicable. These approvals pertain to the type design only. The ICA includes: 1) Engine Shop Manual (ESM): ESM.21 2) Standard Practices Manual (SPM): SPM.25 3) Consumable Product Manual (CPM): CPM.25 4) Non Destructive Test Manual (NDTM): NDTM.25 5) Components Maintenance Manuals (CMM): as published by CFM 6) Service Bulletins (SB): as published by CFM 7) Maintenance Manual: see Aircraft Maintenance Manual (AMM) 8) Fault Isolation Manual: see Aircraft Fault Isolation Manual (FIM) NOTE 16. IMPORT REQUIREMENTS The type certificate holder, CFM International, S.A., is a company established and jointly owned by Safran of France and the General Electric Company for the certification, sale, and support of CFM56 & LEAP series engines. The LEAP-1B engine series is a product line designed to power the Boeing 737MAX series of aircraft models. With respect to the benefits of type certification for production, General Electric and Safran function as licensees of CFM International, S.A. The location of final assembly can be inferred from the engine manufacturer, which will be identified on the engine nameplate, along with the date of production. Engines produced in the United States by GE are identical to and fully interchangeable with engines produced in France by Safran. Modules, assemblies, or parts produced in France are eligible for use in engines produced to this type certificate provided an airworthiness approval certificate (EASA Form 1 – Authorized Release Certificate or JAA Form 1) issued by Safran under authority of European Aviation Safety Agency (EASA) Production Certificate No. FR.21G.0007 is attached to the item or invoice covering shipment of items (Ref. 14 CFR 21.502). NOTE 17. CRITICAL ENGINE PARTS Life limits established for critical engine parts are published in the ALS section of Chapter 05 of the LEAP-1B Engine Shop Manual, ESM.21. NOTE 18. NOT APPLICABLE E00088EN 11 of 11 NOTE 19. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS Low pressure rotor (N1): 4586 rpm (104.3 % - 100 % N1 is defined as 4397 rpm) High pressure rotor (N2): Pre-SB LEAP-1B 72-0169: 20171 rpm (117.5 % - 100 % N2 is defined as 17167 rpm) Post-SB LEAP-1B 72-0169: 19828 rpm (indicated 117.5%) NOTE 20. NOT APPLICABLE NOTE 21. MAXIMUM PERMISSIBLE BLEED AIR EXTRACTION LOCATION TEMPERATURE CORRECTED FAN SPEED FLOW LIMIT HPC Stage 4 All speeds above minimum idle. 10% of primary airflow* HPC Stage10 All speeds above minimum idle. 15% of primary airflow* Bypass Duct All speeds above minimum idle. 1% of primary airflow * - Absolute maximum. Refer to the LEAP-1B Installation Manual, for detailed bleed schedules. NOTE 22. NOT APPLICABLE NOTE 23. EXHAUST EMISSIONS AND FUEL VENTING The following emissions standards promulgated in 14 CFR part 34, amendment 7A, effective May 24, 2024, and 40 CFR part 1031, effective December 23, 2022, have been complied with for the LEAP-1B series engines 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) Carbon Monoxide (CO) Emission Standards: 14 CFR 34.21(d)(1)(ii); in addition, 40 CFR 1031.60(d) Hydrocarbons (HC) Emission Standards: 14 CFR 34.21(d)(1)(i); in addition, 40 CFR 1031.60(c) 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