# TCDS E00089EN: CFM International S.A. - Type: Type certificate data sheet - Status: Current - Holder: CFM International S.A. - Revision: 11 - Revised: May 12, 2026 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 208, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/c0/d1/c0d1bfd4720e243098bf96160a32f5d66167d6646cc1c48b1b46c6ef59188c8b - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID176784880320260511172448.0001 - Page: https://openairdocs.org/tcds/E00089EN ## Models (34) As the data sheet lists them. - LEAP-1A33 - LEAP-1A24E1 - LEAP-1C28 - LEAP-1C30B1 - LEAP-1A30 - LEAP-1A26E1 - LEAP-1A33B2 - LEAP-1C30 - LEAP-1A26 - LEAP-1A29CJ - LEAP-1A24 - LEAP-1A23 - LEAP-1A32 - LEAP-1A35A - LEAP-1A26CJ - LEAP-1A29 - LEAP-1A33S - LEAP-1A32S - LEAP-1A30S - LEAP-1A26S - LEAP-1A26E1S - LEAP-1A35AR - LEAP-1A33R - LEAP-1A33B2R - LEAP-1A32R - LEAP-1A30R - LEAP-1A33RS - LEAP-1A32RS - LEAP-1A30RS - LEAP-1A26E2 - LEAP-1A35AX - LEAP-1A33X - LEAP-1A33B2X - LEAP-1A32X ## 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 E00089EN) and ot her 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: CFM International, S.A. 2 Boulevard du Général Martial Valin 75724 Paris Cedex 15 France I. MODELS LEAP-1A35AX LEAP-1A33X LEAP-1A33B2X LEAP-1A32X 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; annular pre swirl combustor, 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 °F (°C) • Takeoff • Maximum continuous 32,160 (14,305) 24,850 (11,054) 86 (30) 77 (25) - - - - - - - - - - - - - - - - - - - - - - - - COMPONENTS Part Number Full Authority Digital Control (FADEC) • Electronic control unit • Software • Identification plug 2500M34 2590M00 and 2590M01 - - - - - - - - - - - - - - - - - - Refer to the latest revision of CFM Service Bulletin LEAP-1A SB 72-0136 for a list of Data Entry Plug part numbers 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 25 26 27 28 REV. 11 10 10 10 11 10 11 10 11 10 11 11 11 11 11 11 11 11 11 11 11 11 11 11 11 11 11 11 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00089EN TCDS NUMBER E00089EN REVISION: Revision 11 DATE: May 12, 2026 CFM INTERNATIONAL, S.A. MODELS: LEAP-1A35A LEAP-1C30 LEAP-1A33S LEAP-1A33RS LEAP-1A33 LEAP-1C30B1 LEAP-1A32S LEAP-1A32RS LEAP-1A33B2 LEAP-1C28 LEAP-1A30S LEAP-1A30RS LEAP-1A32 LEAP-1A29 LEAP-1A26S LEAP-1A26E2 LEAP-1A30 LEAP-1A29CJ LEAP-1A26E1S LEAP-1A26 LEAP-1A26CJ LEAP-1A35AR LEAP-1A26E1 LEAP-1A35AX LEAP-1A33R LEAP-1A24 LEAP-1A33X LEAP-1A33B2R LEAP-1A24E1 LEAP-1A33B2X LEAP-1A32R LEAP-1A23 LEAP-1A32X LEAP-1A30R LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. E00089EN 2 of 28 I. MODELS (Cont.) LEAP-1A35AX LEAP-1A33X LEAP-1A33B2X LEAP-1A32X 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-1A S/B 73-0001 for a list of fuels specifically approved for LEAP-1A engine. OIL • Approved oils are synthetic type conforming to SAE AS5780 specification, grade SPC (Standard Performance Capability) or HPC (High performance Capability). • Refer to the latest revision of CFM Service Bulletin LEAP-1A S/B 79-0001 for a list of oil specifically approved for the LEAP-1A engine. PHYSICAL CHARACTERISTICS LEAP-1A G01 PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRF aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 131.0 (3328) 100.1 (2543) 93.2 (2368) - - - - - - - - - - - - - - - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, Including basic engine accessories and fluids weight (oil and fuel). lb (kg) 6591 (2990) - - - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 212.6 (5400.0) 99.0 (2514.6) 97.8 (2484.1) - - - - - - - - - - - - - - - - - - PHYSICAL CHARACTERISTICS LEAP-1A All other Gyy (see Note 5) PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRF aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 131.0 (3328) 99.7 (2533) 93.0 (2362) - - - - - - - - - - - - - - - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, including basic engine accessories and fluids weight (oil and fuel). lb (kg) 6632 (3008) - - - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 212.6 (5400) 99.0 (2514.6) 97.8 (2484.1) - - - - - - - - - - - - - - - - - - E00089EN 3 of 28 II. MODELS LEAP-1A35A LEAP-1A33 LEAP-1A33B2 LEAP-1A32 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; annular pre swirl combustor, 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 °F (°C) • Takeoff • Maximum continuous 32,160 (14,305) 31,690 (14,096) 86 (30) 77 (25) - - - - - - - - - - - - - - - - - - - - - - - - COMPONENTS Part Number Full Authority Digital Control (FADEC) • Electronic control unit • Software • Identification plug 2500M34 2590M00 and 2590M01 - - - - - - - - - - - - - - - - - - Refer to the latest revision of CFM Service Bulletin LEAP-1A SB 72-0136 for a list of Data Entry Plug part numbers 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-1A S/B 73-0001 for a list of fuels specifically approved for LEAP-1A engine. OIL • Approved oils are synthetic type conforming to SAE AS5780 specification, grade SPC (Standard Performance Capability) or HPC (High performance Capability). • Refer to the latest revision of CFM Service Bulletin LEAP-1A S/B 79-0001 for a list of oil specifically approved for the LEAP-1A engine. PHYSICAL CHARACTERISTICS LEAP-1A G01 PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRF aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 131.0 (3328) 100.1 (2543) 93.2 (2368) - - - - - - - - - - - - - - - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, Including basic engine accessories and fluids weight (oil and fuel). lb (kg) 6591 (2990) - - - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 212.6 (5400.0) 99.0 (2514.6) 97.8 (2484.1) - - - - - - - - - - - - - - - - - - E00089EN 4 of 28 II. MODELS (Cont.) LEAP-1A35A LEAP-1A33 LEAP-1A33B2 LEAP-1A32 PHYSICAL CHARACTERISTICS LEAP-1A All other Gyy (see Note 5) PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRF aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 131.0 (3328) 99.7 (2533) 93.0 (2362) - - - - - - - - - - - - - - - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, including basic engine accessories and fluids weight (oil and fuel). lb (kg) 6632 (3008) - - - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 212.6 (5400) 99.0 (2514.6) 97.8 (2484.1) - - - - - - - - - - - - - - - - - - THIS SPACE INTENTIALLY LEFT BLANK E00089EN 5 of 28 III. MODELS LEAP-1A30 LEAP-1A29 LEAP-1A29CJ 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.) 32,160 (14,305) 29,290 (13,029) - - • Maximum continuous 31,690 (14,096) 26,680 (11,868) - - Flat Rating Ambient Temperature °F (°C) • Takeoff • Maximum continuous 86 (30) 77 (25) 97 (36) - - - - - - COMPONENTS Part Number Full Authority Digital Control (FADEC) • Electronic control unit • Software • Identification plug 2500M34 2590M00 and 2590M01 - - - - and - - - - - - and - - Refer to the latest revision of CFM Service Bulletin LEAP-1A SB 72-0136 for a list of Data Entry Plug part numbers 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-1A S/B 73-0001 for a list of fuels specifically approved for LEAP-1A engine. OIL • Approved oils are synthetic type conforming to SAE AS5780 specification, grade SPC (Standard Performance Capability) or HPC (High performance Capability). • Refer to the latest revision of CFM Service Bulletin LEAP-1A S/B 79-0001 for a list of oil specifically approved for the LEAP-1A engine. PHYSICAL CHARACTERISTICS LEAP-1A G01 PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRF aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 131.0 (3328) - - - - 100.1 (2543) - - - - 93.2 (2368) - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, including basic engine accessories and fluids weight (oil and fuel). lb (kg) 6591 (2990) - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 212.6 (5400) - - - - 99.0 (2514.6) - - - - 97.8 (2484.1) - - - - E00089EN 6 of 28 III. MODELS LEAP-1A30 LEAP-1A29 LEAP-1A29CJ PHYSICAL CHARACTERISTICS LEAP-1A All other Gyy (see Note 5) PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRF aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 131.0 (3328) - - - - 99.7 (2533) - - - - 93.0 (2362) - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, including basic engine accessories and fluids weight (oil and fuel). lb (kg) 6632 (3008) - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 212.6 (5400) - - - - 99.0 (2514.6) - - - - 97.8 (2484.1) - - - - THIS SPACE INTENTIONALLY LEFT BLANK E00089EN 7 of 28 IV. MODELS LEAP-1A26 LEAP-1A26CJ LEAP-1A26E1 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.) 27,120 (12,064) - - - - • Maximum continuous 26,680 (11,868) - - - - Flat Rating Ambient Temperature °F (°C) • Takeoff • Maximum continuous 111 (44) 77 (25) - - - - 120 (49) - - COMPONENTS Part Number Full Authority Digital Control (FADEC) • Electronic control unit • Software • Identification plug 2500M34 2590M00 and 2590M01 - - - - and - - - - - - and - - Refer to the latest revision of CFM Service Bulletin LEAP-1A SB 72-0136 for a list of Data Entry Plug part numbers 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-1A S/B 73-0001 for a list of fuels specifically approved for LEAP-1A engine. OIL • Approved oils are synthetic type conforming to SAE AS5780 specification, grade SPC (Standard Performance Capability) or HPC (High performance Capability). • Refer to the latest revision of CFM Service Bulletin LEAP-1A S/B 79-0001 for a list of oil specifically approved for the LEAP-1A engine. PHYSICAL CHARACTERISTICS LEAP-1A G01 PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRF aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 131.0 (3328) - - - - 100.1 (2543) - - - - 93.2 (2368) - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, including basic engine accessories and fluids weight (oil and fuel). lb (kg) 6591 (2990) - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 212.6 (5400) - - - - 99.0 (2514.6) - - - - 97.8 (2484.1) - - - - E00089EN 8 of 28 IV. MODELS LEAP-1A26 LEAP-1A26CJ LEAP-1A26E1 PHYSICAL CHARACTERISTICS LEAP-1A All other Gyy (see Note 5) PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRF aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 131.0 (3328) - - - - 99.7 (2533) - - - - 93.0 (2362) - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, including basic engine accessories and fluids weight (oil and fuel). lb (kg) 6632 (3008) - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 212.6 (5400) - - - - 99.0 (2514.6) - - - - 97.8 (2484.1) - - - - THIS SPACE INTENTIONALLY LEFT BLANK E00089EN 9 of 28 V. MODELS LEAP-1A24 LEAP-1A24E1 LEAP-1A23 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.) 24,010 (10,680) - - - - • Maximum continuous 24,000 (10,676) - - 23,510 (10,458) Flat Rating Ambient Temperature °F (°C) • Takeoff (5 min.) • Maximum continuous 113 (45) 77 (25) 130 (55) - - 113 (45) - - COMPONENTS Part Number Full Authority Digital Control (FADEC) • Electronic control unit • Software • Identification plug 2500M34 2590M00 and 2590M01 - - - - and - - - - - - and - - Refer to the latest revision of CFM Service Bulletin LEAP-1A SB 72-0136 for a list of Data Entry Plug part numbers 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-1A S/B 73-0001 for a list of fuels specifically approved for LEAP-1A engine. OIL • Approved oils are synthetic type conforming to SAE AS5780 specification, grade SPC (Standard Performance Capability) or HPC (High performance Capability). • Refer to the latest revision of CFM Service Bulletin LEAP-1A S/B 79-0001 for a list of oil specifically approved for the LEAP-1A engine. PHYSICAL CHARACTERISTICS LEAP-1A G01 PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRF aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 131.0 (3328) - - - - 100.1 (2543) - - - - 93.2 (2368) - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, including basic engine accessories and fluids weight (oil and fuel). lb (kg) 6591 (2990) - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 212.6 (5400) - - - - 99.0 (2514.6) - - - - 97.8 (2484.1) - - - - E00089EN 10 of 28 V. MODELS (Cont.) LEAP-1A24 LEAP-1A24E1 LEAP-1A23 PHYSICAL CHARACTERISTICS LEAP-1A All other Gyy (see Note 5) PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRF aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 131.0 (3328) - - - - 99.7 (2533) - - - - 93.0 (2362) - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, including basic engine accessories and fluids weight (oil and fuel). lb (kg) 6632 (3008) - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 212.6 (5400) - - - - 99.0 (2514.6) - - - - 97.8 (2484.1) - - - - THIS SPACE INTENTIONALLY LEFT BLANK E00089EN 11 of 28 VII. MODELS LEAP-1A35AR LEAP-1A33R LEAP-1A33B2R LEAP-1A32R LEAP-1A30R 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; annular pre swirl combustor, 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 °F (°C) • Takeoff • Maximum continuous 32,160 (14,305) 24,850 (11,054) 86 (30) 77 (25) - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - COMPONENTS Full Authority Digital Control (FADEC) • Electronic control unit • Software • Identification plug Part Number 2500M34 2590M00 and 2590M01 - - - - - - - - - - - - - - - - - - - - - - - - Refer to the latest revision of CFM Service Bulletin LEAP-1A SB 72-0136 for a list of Data Entry Plug part numbers 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-1A S/B 73-0001 for a list of fuels specifically approved for LEAP-1A engine. OIL • Approved oils are synthetic type conforming to SAE AS5780 specification, grade SPC (Standard Performance Capability) or HPC (High performance Capability). • Refer to the latest revision of CFM Service Bulletin LEAP-1A S/B 79-0001 for a list of oil specifically approved for the LEAP-1A engine. PHYSICAL CHARACTERISTICS LEAP-1A G01 PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRF aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 131.0 (3328) 100.1 (2543) 93.2 (2368) - - - - - - - - - - - - - - - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, Including basic engine accessories and fluids weight (oil and fuel). lb (kg) 6591 (2990) - - - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 212.6 (5400.0) 99.0 (2514.6) 97.8 (2484.1) - - - - - - - - - - - - - - - - - - E00089EN 12 of 28 VII. MODELS (Cont.) LEAP-1A35AR LEAP-1A33R LEAP-1A33B2R LEAP-1A32R LEAP-1A30R PHYSICAL CHARACTERISTICS LEAP-1A All other Gyy (see Note 5) PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRF aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 131.0 (3328) 99.7 (2533) 93.0 (2362) - - - - - - - - - - - - - - - - - - - - - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, including basic engine accessories and fluids weight (oil and fuel). lb (kg) 6632 (3008) - - - - - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 212.6 (5400) 99.0 (2514.6) 97.8 (2484.1) - - - - - - - - - - - - - - - - - - - - - - - - THIS SPACE INTENTIONALLY LEFT BLANK E00089EN 13 of 28 VII. MODELS LEAP-1A33S LEAP-1A32S LEAP-1A30S LEAP-1A26S LEAP-1A26E1S 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; annular pre swirl combustor, 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 °F (°C) • Takeoff • Maximum continuous 32,160 (14,305) 24,850 (11,054) 86 (30) 77 (25) - - - - - - - - - - - - - - - - 27,120 (12,064) 26,680 (11,868) 111 (44) 77 (25) - - - - - - - - COMPONENTS Part Number Full Authority Digital Control (FADEC) • Electronic control unit • Software • Identification plug 2500M34 2590M00 and 2590M01 - - - - - - - - - - - - - - - - - - - - - - - - Refer to the latest revision of CFM Service Bulletin LEAP-1A SB 72-0136 for a list of Data Entry Plug part numbers 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-1A S/B 73-0001 for a list of fuels specifically approved for LEAP-1A engine. OIL • Approved oils are synthetic type conforming to SAE AS5780 specification, grade SPC (Standard Performance Capability) or HPC (High performance Capability). • Refer to the latest revision of CFM Service Bulletin LEAP-1A S/B 79-0001 for a list of oil specifically approved for the LEAP-1A engine. PHYSICAL CHARACTERISTICS LEAP-1A G01 PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRF aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 131.0 (3328) 100.1 (2543) 93.2 (2368) - - - - - - - - - - - - - - - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, Including basic engine accessories and fluids weight (oil and fuel). lb (kg) 6591 (2990) - - - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 212.6 (5400.0) 99.0 (2514.6) 97.8 (2484.1) - - - - - - - - - - - - - - - - - - E00089EN 14 of 28 VII. MODELS (Cont.) LEAP-1A33S LEAP-1A32S LEAP-1A30S LEAP-1A26S LEAP-1A26E1S PHYSICAL CHARACTERISTICS LEAP-1A All other Gyy (see Note 5) PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRF aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 131.0 (3328) 99.7 (2533) 93.0 (2362) - - - - - - - - - - - - - - - - - - - - - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, including basic engine accessories and fluids weight (oil and fuel). lb (kg) 6632 (3008) - - - - - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 212.6 (5400) 99.0 (2514.6) 97.8 (2484.1) - - - - - - - - - - - - - - - - - - - - - - - - THIS SPACE INTENTIONALLY LEFT BLANK E00089EN 15 of 28 IX. MODELS LEAP-1A33RS LEAP-1A32RS LEAP-1A30RS LEAP-1A26E2 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; annular pre swirl combustor, 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 °F (°C) • Takeoff • Maximum continuous 32,160 (14,305) 24,850 (11,054 86 (30) 77 (25) - - - - - - - - - - - - - - - - 27,120 (12,064) 26,040 (11,583) - - - - COMPONENTS Part Number Full Authority Digital Control (FADEC) • Electronic control unit • Software • Identification plug 2500M34 2590M00 and 2590M01 - - - - - - - - - - - - - - - - - - Refer to the latest revision of CFM Service Bulletin LEAP-1A SB 72-0136 for a list of Data Entry Plug part numbers 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-1A S/B 73-0001 for a list of fuels specifically approved for LEAP-1A engine. OIL • Approved oils are synthetic type conforming to SAE AS5780 specification, grade SPC (Standard Performance Capability) or HPC (High performance Capability). • Refer to the latest revision of CFM Service Bulletin LEAP-1A S/B 79-0001 for a list of oil specifically approved for the LEAP-1A engine. PHYSICAL CHARACTERISTICS LEAP-1A G01 PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRF aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 131.0 (3328) 100.1 (2543) 93.2 (2368) - - - - - - - - - - - - - - - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, Including basic engine accessories and fluids weight (oil and fuel). lb (kg) 6591 (2990) - - - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 212.6 (5400.0) 99.0 (2514.6) 97.8 (2484.1) - - - - - - - - - - - - - - - - - - E00089EN 16 of 28 IX. MODELS (Cont.) LEAP-1A33RS LEAP-1A32RS LEAP-1A30RS LEAP-1A26E2 PHYSICAL CHARACTERISTICS LEAP-1A All other Gyy (see Note 5) PRINCIPLE DIMENSIONS Length Fwd. fan case flange to TRF aft flange Width Maximum Envelope Height Maximum Envelope in (mm) 131.0 (3328) 99.7 (2533) 93.0 (2362) - - - - - - - - - - - - - - - - - - WEIGHT Not to Exceed The engine weight is defined as the weight of the basic engine, including basic engine accessories and fluids weight (oil and fuel). lb (kg) 6632 (3008) - - - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 212.6 (5400) 99.0 (2514.6) 97.8 (2484.1) - - - - - - - - - - - - - - - - - - THIS SPACE INTENTIONALLY LEFT BLANK E00089EN 17 of 28 VI. MODELS LEAP-1C28 LEAP-1C30 LEAP-1C30B1 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). Other hardware includes accessories and EBU, an exhaust nozzle and plug, an engine mounting system and a thrust reverser unit including a digital Thrust Reverser Control Unit (TRCU). RATINGS See NOTE 1. Static Thrust at Sea Level lb (daN) • Takeoff (5 min.) 29220 (12998) 30830 (13714) 30830 (13714) • Maximum continuous 28760 (12793) 29950 (13322) 29950 (13322) Flat Rating Ambient Temperature °F (°C) • Takeoff (5 min.) • Maximum continuous 86 (30) 77 (25) - - - - - - - - COMPONENTS Part Number Full Authority Digital Control (FADEC) • Electronic control unit • Software • Identification plug 2500M35 2590M02 and 2590M03 - - - - - - - - - - - - Refer to the latest revision of CFM Service Bulletin LEAP-1C SB 72-0062 for a list of Data Entry Plug part numbers 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-1C S/B 73-0001 for a list of fuels specifically approved for LEAP-1C engine. OIL • Approved oils are synthetic type conforming to SAE AS5780 specification, grade SPC (Standard Performance Capability) or HPC (High performance Capability). • Refer to the latest revision of CFM Service Bulletin LEAP-1C S/B 79-0001 for a list of oil specifically approved for the LEAP-1C engine. PHYSICAL CHARACTERISTICS LEAP-1C G01 PRINCIPLE DIMENSIONS Length Fan cowl hinge beam front to end of center vent tube Width Maximum Envelope (including TR Unit) Height Maximum Envelope (including TR Unit) in (mm) 177.35 (4505) - - - - 104.65 (2659) - - - - 106.81 (2714) - - - - WEIGHT Not to Exceed The engine weight is defined as the dry weight of the basic engine, accessories and EBU, an exhaust nozzle and plug, an engine mounting system and a thrust reverser unit. lb (kg) 8675 (3935) - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 215.0 (5464) - - - - 99.2 (2520) - - - - 98.1 (2492) - - - - E00089EN 18 of 28 VI. MODELS (Cont.) LEAP-1C28 LEAP-1C30 LEAP-1C30B1 PHYSICAL CHARACTERISTICS LEAP-1C All other Gyy (see Note 5) PRINCIPLE DIMENSIONS Length Fan cowl hinge beam front to end of center vent tube Width Maximum Envelope (including TR Unit) Height Maximum Envelope (including TR Unit) in (mm) 177.35 (4505) 104.65 (2659) 106.81 (2714) - - - - - - - - - - - - WEIGHT Not to Exceed The engine weight is defined as the dry weight of the basic engine, accessories and EBU, an exhaust nozzle and plug, an engine mounting system and a thrust reverser unit. lb (kg) 8661 (3929) - - - - CENTER OF GRAVITY LOCATION Engine Only, Nominal Weight Station (axial) HPC case fwd flange = 200 in (5080 mm) Waterline Buttline in (mm) 215.0 (5464) 99.2 (2520) 98.1 (2492) - - - - - - - - - - - - THIS SPACE INTENTIONALLY LEFT BLANK E00089EN 19 of 28 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: • ELOS No. LEAP1A1C-2014-TC-01-P-11 to 14 CFR 33.27(c): High Pressure Shaft Loss-of-Load • ELOS No. LEAP1A1C-2014-TC-01-P-8 to 14 CFR 33.97(a): Thrust Reverser (applicable for 1C models only) 4. Special Conditions: • Fan Blade Special Condition No. 33-015-SC 5. Exemptions: None MODEL APPLICATION DATE TC ISSUED/ AMENDED LEAP-1A35A June 23, 2014 November 20, 2015 LEAP-1A33 May 21, 2012 March 11, 2016 LEAP-1A33B2 August 27, 2013 March 11, 2016 LEAP-1A32 May 21, 2012 March 11, 2016 LEAP-1A30 June 23, 2014 March 11, 2016 LEAP-1A26 May 21, 2012 March 11, 2016 LEAP-1A26E1 May 21, 2012 March 11, 2016 LEAP-1A24 May 21, 2012 March 11, 2016 LEAP-1A24E1 May 21, 2012 March 11, 2016 LEAP-1A23 June 23, 2014 March 11, 2016 LEAP-1C28 June 27, 2012 December 21, 2016 LEAP-1C30 June 27, 2012 December 21, 2016 LEAP-1C30B1 August 27, 2013 December 21, 2016 LEAP-1A29 February 16, 2018 May 30, 2018 LEAP-1A29CJ February 16, 2018 May 30, 2018 LEAP-1A26CJ February 16, 2018 May 30, 2018 LEAP-1A35AX November 14, 2023 July 10, 2024 LEAP-1A33X November 14, 2023 July 10, 2024 LEAP-1A33B2X November 14, 2023 July 10, 2024 LEAP-1A32X November 14, 2023 July 10, 2024 LEAP-1A35AR September 15, 2025 May 6, 2026 LEAP-1A33R September 15, 2025 May 6, 2026 LEAP-1A33B2R September 15, 2025 May 6, 2026 LEAP-1A32R September 15, 2025 May 6, 2026 LEAP-1A30R September 15, 2025 May 6, 2026 LEAP-1A33S September 15, 2025 May 6, 2026 LEAP-1A32S September 15, 2025 May 6, 2026 LEAP-1A30S September 15, 2025 May 6, 2026 LEAP-1A26S September 15, 2025 May 6, 2026 LEAP-1A26E1S September 15, 2025 May 6, 2026 LEAP-1A33RS September 15, 2025 May 6, 2026 LEAP-1A32RS September 15, 2025 May 6, 2026 LEAP-1A30RS September 15, 2025 May 6, 2026 LEAP-1A26E2 September 15, 2025 May 6, 2026 PRODUCTION BASIS Production Certificate No. 108 for LEAP-1A engines produced in the United States by General Electric under license from CFM International, S.A. (See NOTE 16). Production Organization Approval No. FR.21G.0007 dated December 17th, 2009 for engines produced in France by SAFRAN Aircraft Engines under license from CFM International, S.A (See NOTE 16). THIS SPACE INTENTIONALLY LEFT BLANK. E00089EN 20 of 28 NOTES NOTE 1. ENGINE RATINGS Engine ratings are 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) for all models, 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) for all models. For the models LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1 (for A319 aircraft only), LEAP-1A29, LEAP-1A26E2 (for A320 aircraft only), LEAP-1A30R, LEAP-1A32R, LEAP-1A33B2R, LEAP- 1A35AR, LEAP-1A30RS, LEAP-1A32RS, LEAP-33RS (for A321 aircraft only) and LEAP-1A32X, LEAP-1A33X, LEAP-1A33B2X, LEAP-1A35AX (for A321XLR aircraft only), when the Go-Around thrust logic is active, the available Go-Around thrust is less than or equal to rated Take-Off thrust, as defined and agreed with aircraft type certificate holder. 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 Takeoff, 5 min Maximum Continuous Max Transient (30 sec.) 1060°C (1940°F) 1025°C (1877°F) 1065°C (1949°F) Ground Starts Inflight Starts 750°C (1382°F) (Measured 750°C (1382°F) Pre LEAP-1A S/B 73-0034 and Pre LEAP-1C S/B 73-0003) 750°C (1382°F) (Measured 800°C (1472°F) Post LEAP-1A S/B 73-0034 and Post LEAP-1C S/B 73-0003) 875°C (1607°F) FUEL PUMP INLET TEMPERATURE Maximum Minimum (Cold Start) 55°C (131°F) -54°C (-65.2°F) Or the relevant fuel freezing point, whichever is higher. OIL TEMPERATURE Maximum • Continuous operation • Transient (15 minutes) 140°C (284°F) 155°C (311°F) Minimum (Cold Start) • Engines Not Compliant with LEAP-1A S/B 72-0034, 72-0035, & 72-0036; and LEAP-1C..G01 • Engines Compliant with LEAP-1A S/B 72-0034, 72-0035, & 72-0036; and all other LEAP-1C.. Gyy (see Note 5) -29°C (-20°F) -40°C (-40°F) Minimum for Acceleration to Take-Off Power 19°C (66°F) E00089EN 21 of 28 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 (32.4 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-1A and LEAP-1C Installation Manuals. 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 (All LEAP-1A Models) ELECTRICAL (IDG)* Rotation Direction+ Speed ratio to core** Pad Rating HP (kW) Shear Torque in.lb (N.m) Maximum overhung moment in.lb (N.m) (wet) CCW 0.462 173 (129) 9400 (1062) 1000 (113) HYDRAULIC PUMP* Rotation Direction+ Speed ratio to core** Pad Rating in.lb (N.m) Shear Torque in.lb (N.m) Maximum overhung moment in.lb (N.m) (wet) CCW 0.211 1301 (147) 4249 (480) 204 (23) * Airframer Supplied Hardware + CCW = COUNTERCLOCKWISE (looking at the Pad) ** 100% core speed = 16,645 RPM ACCESSORY DRIVE CHARACTERISTICS (All LEAP-1C Models) ELECTRICAL (VFG)* Rotation Direction+ Speed ratio to core** Pad Rating HP (kW) Shear Torque in.lb (N.m) Maximum overhung moment in.lb (N.m) (wet) CCW 1.066 205 (151) 7665 (866) 1230 (139) HYDRAULIC PUMP* Rotation Direction+ Speed ratio to core** Pad Rating in.lb (N.m) Shear Torque in.lb (N.m) Maximum overhung moment in.lb (N.m) (wet) CCW 0.203 1239 (140) 3602 (407) 175 (19.8) * Airframer Supplied Hardware + CCW = COUNTERCLOCKWISE (looking at the Pad) ** 100% core speed = 16,645 RPM E00089EN 22 of 28 NOTE 5. MODEL DESCRIPTION The models shown on this TCDS have the following general characteristics LEAP-1A LEAP-1A35AX A321XLR optional model, with additional takeoff thrust at high altitude conditions. LEAP-1A33X A321XLR optional model, with higher thrust rating. LEAP-1A33B2X Same as LEAP-1A33X, with additional pilot-selected takeoff thrust capability. LEAP-1A32X A321XLR basic model. LEAP-1A35A A321neo optional model, with additional takeoff thrust at high altitude conditions. LEAP-1A33 A321neo optional model, with higher thrust rating. LEAP-1A33B2 Same as LEAP-1A33, with additional pilot-selected takeoff thrust capability. LEAP-1A32 A321neo basic model. LEAP-1A30 A321neo optional model, with lower thrust rating. LEAP-1A29 A320neo optional model. LEAP-1A29CJ A320neo or A319neo Airbus Corporate Jet (ACJ) optional model. Same as LEAP-1A29. LEAP-1A26 A320neo basic model. A319neo optional model. LEAP-1A26CJ A320neo or A319neo Airbus Corporate Jet (ACJ) basic model. Same as LEAP-1A26. LEAP-1A26E1 Same as LEAP-1A26, with extended ambient temperature takeoff thrust capability. LEAP-1A24 A319neo basic model. A320neo optional model. LEAP-1A24E1 Same as LEAP-1A24, with extended ambient temperature takeoff thrust capability. LEAP-1A23 A319neo optional model. LEAP-1A35AR Same as LEAP-1A35, with reduced go around thrust LEAP-1A33R Same as LEAP-1A33 with reduced go around thrust LEAP-1A33B2R Same as LEAP-1A33B2 with reduced go around thrust LEAP-1A32R Same as LEAP-1A32 with reduced go around thrust LEAP-1A30R Same as LEAP-1A30 with reduced go around thrust LEAP-1A33S Same as LEAP-1A33 with optimized climb thrust LEAP-1A32S Same as LEAP-1A32 with optimized climb thrust LEAP-1A30S Same as LEAP-1A30 with optimized climb thrust LEAP-1A26S Same as LEAP-1A26 with optimized climb thrust LEAP-1A26E1S Same as LEAP-1A26E1 with optimized climb thrust LEAP-1A33RS Same as LEAP-1A33 with optimized climb thrust and reduced go around LEAP-1A32RS Same as LEAP-1A32 with optimized climb thrust and reduced go around LEAP-1A30RS Same as LEAP-1A30 with optimized climb thrust and reduced go around LEAP-1A26E2 Same as LEAP-1A26S with higher ambient condition and reduced go around LEAP-1A engine series includes: LEAP-1A35A, LEAP-1A33, LEAP-1A33B2, LEAP-1A32, LEAP-1A30, LEAP-1A26, LEAP-1A26E1, LEAP-1A24, LEAP-1A24E1, LEAP-1A23, LEAP- 1A29, LEAP-1A29CJ, LEAP-1A26CJ, LEAP-1A35AX, LEAP-1A33X, LEAP-1A33B2X, LEAP- 1A32X, LEAP-1A30R, LEAP-1A32R, LEAP-1A33B2R, LEAP-1A33R, LEAP-1A35AR, LEAP- 1A26S, LEAP-1A26E1S, LEAP-1A30S, LEAP-1A32S, LEAP-1A33S, LEAP-1A30RS, LEAP- 1A32RS, LEAP-33RS, and LEAP-1A26E2. The parts list for each LEAP-1A engine model contains a configuration group number to identify the engine configuration. The engine model configuration is identified as LEAP-1AxxGyy where xx is the model and yy is the applicable configuration as described in LEAP-1A Service Bulletin 72-0220. The models shown on this TCDS have the following general characteristics LEAP-1C LEAP-1C28 C919 Standard Range Configuration LEAP-1C30 C919 Extended Range Configuration LEAP-1C30B1 Same as LEAP-1C30, except for pilot-selected extended takeoff thrust capability LEAP-1C engine series includes LEAP-1C28, LEAP-1C30, and LEAP-1C30B1 The parts list for each LEAP-1C engine model contains a configuration group number to identify the engine configuration. The engine model configuration is identified as LEAP-1CxxGyy where xx is the model and yy is the applicable configuration as described in LEAP-1C Service Bulletin 72-0007. E00089EN 23 of 28 NOTE 6. ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES PROVIDED AS PART OF ENGINE TYPE DESIGN: For LEAP-1C, all models. Engine mounting system and thrust reverser unit including a digital Thrust Reverser Control Unit (TRCU) are part of engine type design, with aircraft level requirements. NOTE 7. ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES NOT PROVIDED AS PART OF ENGINE TYPE DESIGN: COMPATIBLE SYSTEM ASSEMBLIES Thrust Reverser The LEAP-1A engine is approved for use with the Aircelle thrust reverser system: P/N BDL0011-12-0 for the left hand thrust reverser half; and P/N BDL0051-12-0 for the right hand thrust reverser half. The LEAP-1C engine Type Certificate includes the thrust reverser. NOTE 8. SPECIAL ANTI-ICING OR DE-ICING REQUIREMENTS: NOT APPLICABLE E00089EN 24 of 28 NOTE 9. ENGINE MOUNT SYSTEM PROVISIONS: For all models, For information regarding Engine Mount provisions refer to the Engine Installation Manuals of the respective models. See Note 15 for applicable Engine Installation Manuals. NOTE 10. POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS: NOT APPLICABLE E00089EN 25 of 28 NOTE 11. SPECIAL INSTALLATION REQUIREMENTS: ETOPS The LEAP-1A series engines models comply 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. ETOPS eligibility does not constitute airplane or operational level approvals necessary to conduct ETOPS flights. LEAP-1A S/B 71-0006 defines the requirements for conducting ETOPS operation. LEAP-1C engine models are not eligible for Early Extended Twin Operations (ETOPS) at this time. 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 Engine Shop Manual (05-17-01 LEAP- 1A ESM.20, LEAP-1C ESM.22), 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: Limited to the Airbus A319neo/A320neo/A321neo model aircraft for the LEAP-1A series engines. Limited to the CO MAC C919 model aircraft for the LEAP-1C 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. Emissions Standards 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-1A engine series and LEAP-1C engine series. 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 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) E00089EN 26 of 28 NOTE 12. MANUFACTURER’S SERVICE BULLETINS OR OTHER INSTRUCTIONS COVERING MATTERS OF INTEREST: NOT APPLICABLE 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 14 seconds. See LEAP-1A Specific Operating Instruction Manual, GEK 131717, and the LEAP-1C Specific Operating Instructions Manual, GEK 131718. 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-1A Specific Operating Instructions Manual, GEK 131717, and the LEAP- 1C Specific Operating Instructions Manual, GEK 131718. Takeoff Time Limit The normal 5 minute takeoff rating may be extended to 10 minutes for engine out contingency, as specified in the LEAP-1A Specific Operating Instructions Manual, GEK 131717, and the LEAP- 1C Specific Operating Instructions Manual, GEK 131718. Icing Operation For operation in icing conditions; requirements, limitations, and notes are specified in the LEAP- 1A Specific Operating Instructions Manual, GEK 131717, and the LEAP-1C Specific Operating Instructions Manual, GEK 131718. NOTE 14. SPECIAL REPAIR OR OVERHAUL LIMITATIONS: NOT APPLICABLE E00089EN 27 of 28 NOTE 15. APPLICABLE INSTALLATION, MAINTENANCE AND OVERHAUL MANUALS LEAP-1A: The applicable installation and operating manuals are referenced in the latest revision of CFM Service Bulletin LEAP-1A 72-0220. 1) Turbofan Engine Installation Manual (EIM – IM.20): LEAP-1A G01 CRL 2106a LEAP-1A All other Gyy CRL 2106a_3 2) Specific Operating Instructions (SOI): CRL 2105a (GEK 131717) 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 LEAP-1A ICA includes: 1) Engine Shop Manual (ESM): SM.20 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) Troubleshooting Manual: see Aircraft Troubleshooting Manual (TSM) LEAP-1C: The applicable installation and operating manuals are referenced in the latest revision of CFM Service Bulletin LEAP-1C 72-0007. 1) Turbofan Engine Installation Manual (EIM – IM.22) LEAP-1C G01 CRL 2106c LEAP-1C G02 CRL 2106c_1 LEAP-1C G03 CRL 2106c_2 LEAP-1C All other Gyy CRL 2106c_3 2) Specific Operating Instructions (SOI): CRL 2105c (GEK131718) 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 LEAP-1C ICA includes: 1) Engine Shop Manual (ESM): SM.22 2) Standard Practices Manual (SPM): SPM.25 3) Consumable Product Manual (CPM): CPM.25 4) Non Destructive Test Manual (NDTM): NDTM.25 5) Power Plant Build-up Manual (PPBM): PP.22 6) Components Maintenance Manuals (CMM): as published by CFM 7) Service Bulletins (SB): as published by CFM 8) Maintenance Manual: see Aircraft Maintenance Manual (AMM) 9) Troubleshooting Manual: see Aircraft Troubleshooting Manual (TSM) NOTE 16. IMPORT REQUIREMENTS The type certificate holder, CFM International, S.A., is a company established and jointly owned by SAFRAN Aircraft Engines of France and the General Electric Company for the certification, sale, and support of CFM56 & LEAP series engines. The LEAP-1A engine series is a product line designed to power the Airbus A319neo/320neo/321neo/321XLR aircraft. The LEAP-1C engine series is a product line designed to power the COMAC C919 aircraft. With respect to the benefits of type certification for production, General Electric and SAFRAN Aircraft Engines 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 Aircraft Engines. E00089EN 28 of 28 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 Aircraft Engines 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. LIFE LIMITED PART INFORMATION: Life limits established for critical engine parts are published in the ALS section of Chapter 05 of the LEAP-1A Engine Shop Manual, ESM.20, and the LEAP-1C Engine Shop Manual, ESM.22. NOTE 18. MILITARY MODEL INFORMATION: NOT APPLICABLE NOTE 19. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS SPOOL RPM % Low pressure rotor (N1) High pressure rotor (N2) 3894 19,391 101.0 116.5 NOTE 20. OUTPUT/PROPELLER SHAFT TORQUE LIMITS NOT APPLICABLE NOTE 21. BLEED AIR EXTRACTION PROVISIONS: MAXIMUM PERMISSIBLE BLEED AIR EXTRACTION LOCATION TEMPERATURE CORRECTED FAN SPEED FLOW LIMIT HPC Stage 4 All speeds above minimum idle. 9.97% core airflow* HPC Stage7 Above 2314 RPM 2.45% core airflow Below 2314 RPM 2.9% core airflow HPC Stage10 All speeds above minimum idle. 15.0% of core airflow. Bypass Duct All speeds above minimum idle. 2 % of secondary airflow * - Absolute maximum. Refer to the LEAP-1A or LEAP-1C Installation Manual, for detailed Stage 4 bleed schedule. NOTE 22. ROTOR DISK INTEGRITY AND ROTOR BLADE CONTAINMENT (where special requirements apply): NOT APPLICABLE ----END---- ``` ## ADs (19, in force first) - [AD 2026-14-06](https://openairdocs.org/ad/2026-14-06): Turbine Section · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 10 more. Effective Jul 27, 2026 - [AD 2026-02-04](https://openairdocs.org/ad/2026-02-04): Turbine Engine Compressor Section · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 10 more. Effective Feb 26, 2026 - [AD 2026-02-08](https://openairdocs.org/ad/2026-02-08): Engine Controls · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 10 more. Effective Feb 25, 2026 - [AD 2025-21-03](https://openairdocs.org/ad/2025-21-03): Turbine section · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 10 more. Effective Dec 29, 2025 - [AD 2025-12-03](https://openairdocs.org/ad/2025-12-03): Turbine Engine Compressor Section; Turbine Section · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 10 more. Effective Jul 25, 2025 - [AD 2025-04-12](https://openairdocs.org/ad/2025-04-12): Turbine Section · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 24 more. Effective Apr 8, 2025 - [AD 2025-01-03](https://openairdocs.org/ad/2025-01-03): Turbine Section · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 13 more. Effective Mar 11, 2025 - [AD 2024-19-07](https://openairdocs.org/ad/2024-19-07): Engine Fuel and Control · CFM International LEAP-1A32 and A321-251NX. Effective Oct 7, 2024 - [AD 2024-07-02](https://openairdocs.org/ad/2024-07-02): Turbine Section · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 10 more. Effective Jun 10, 2024 - [AD 2024-07-06](https://openairdocs.org/ad/2024-07-06): Turbine Engine Compressor Section · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 10 more. Effective Jun 3, 2024 - [AD 2022-17-12](https://openairdocs.org/ad/2022-17-12): Turbine Section · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 10 more. Effective Oct 6, 2022 - [AD 2022-15-04](https://openairdocs.org/ad/2022-15-04): Turbine Section · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 10 more. Effective Aug 4, 2022 - [AD 2022-14-02](https://openairdocs.org/ad/2022-14-02): Turbine Engine Compressor Section, Turbine Section · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 10 more. Effective Jul 18, 2022 - [AD 2022-09-09](https://openairdocs.org/ad/2022-09-09): Turbine Engine Compressor Section, Turbine Section · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 10 more. Effective Jun 21, 2022 - [AD 2021-11-21](https://openairdocs.org/ad/2021-11-21): Turbine Section · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 10 more. Effective Jul 15, 2021 - [AD 2020-25-13](https://openairdocs.org/ad/2020-25-13): Turbine Section · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 10 more. Effective Jan 25, 2021 - [AD 2017-24-06](https://openairdocs.org/ad/2017-24-06): Turbine Section · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 7 more. Effective Dec 15, 2017 - [AD 2023-09-06](https://openairdocs.org/ad/2023-09-06) (historical): Turbine Section · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 10 more. Effective Jun 23, 2023 - [AD 2018-19-16](https://openairdocs.org/ad/2018-19-16) (historical): Engine Controls · CFM International LEAP-1A23, LEAP-1A24, LEAP-1A24E1 and 10 more. Effective Oct 25, 2018 ## Registered aircraft by registry model (OpenAirDocs) - [CFM International LEAP-1A26](https://openairdocs.org/engine/cfm-international-leap-1a26): 115 aircraft (registry code 13110) - [CFM International LEAP-1A33](https://openairdocs.org/engine/cfm-international-leap-1a33): 93 aircraft (registry code 13115) - [CFM International LEAP-1A35A](https://openairdocs.org/engine/cfm-international-leap-1a35a): 0 aircraft (registry code 13135) --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. 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