# TCDS E00056EN: CFM International S.A. - Type: Type certificate data sheet - Status: Current - Holder: CFM International S.A. - Revision: 11 - Revised: August 19, 2024 - Product: Engine - Certification basis: Part 33 - Data sheet PDF: https://openairdocs.org/files/sha256/e3/c0/e3c0f15a59cc66f157971d1c208fcfe5bcb49f37470a8d9cb7aefc5b19af9866 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID156756785620240821160812.0001 - Page: https://openairdocs.org/tcds/E00056EN ## Models (49) As the data sheet lists them. - CFM56-7B27E/F - CFM56-7B26/B1 - CFM56-7B20/2 - CFM56-7B27 - CFM56-7B27E/B1 - CFM56-7B27/3 - CFM56-7B26/3B2F - CFM56-7B22E - CFM56-7B24E - CFM56-7B27/B3 - CFM56-7B22/2 - CFM56-7B27A/3 - CFM56-7B27/3B1F - CFM56-7B24/3B1 - CFM56-7B26/3 - CFM56-7B27/B1 - CFM56-7B20E - CFM56-7B27/3B3 - CFM56-7B26/B2 - CFM56-7B26/2 - CFM56-7B24/B1 - CFM56-7B26E/B1 - CFM56-7B27/2 - CFM56-7B27A - CFM56-7B26/3B2 - CFM56-7B22E/B1 - CFM56-7B24 - CFM56-7B26E - CFM56-7B26E/F - CFM56-7B22/B1 - CFM56-7B26E/B2 - CFM56-7B26/3B1 - CFM56-7B24/2 - CFM56-7B20/3 - CFM56-7B26E/B2F - CFM56-7B20 - CFM56-7B22/3 - CFM56-7B22 - CFM56-7B26/3F - CFM56-7B27/3B1 - CFM56-7B24E/B1 - CFM56-7B27/3F - CFM56-7B27AE - CFM56-7B24/3 - CFM56-7B22/3B1 - CFM56-7B26 - CFM56-7B27E - CFM56-7B27E/B1F - CFM56-7B27E/B3 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00056EN TCDS NUMBER E00056EN REVISION: 11* DATE: August 19, 2024 CFM INTERNATIONAL, S.A. MODELS: CFM56-7B20 CFM56-7B20/2 CFM56-7B20/3 CFM56-7B20E CFM56-7B22 CFM56-7B22/2 CFM56-7B22/B1 CFM56-7B22/3 CFM56-7B22/3B1 CFM56-7B22E CFM56-7B22E/B1 CFM56-7B24 CFM56-7B24/2 CFM56-7B24/B1 CFM56-7B24/3 CFM56-7B24/3B1 CFM56-7B24E CFM56-7B24E/B1 CFM56-7B26/3 CFM56-7B26 CFM56-7B26/2 CFM56-7B26/B1 CFM56-7B26/3B1 CFM56-7B26/3B2F CFM56-7B26/3F CFM56-7B26/B2 CFM56-7B26E CFM56-7B26E/B1 CFM56-7B26E/B2 CFM56-7B26E/B2F CFM56-7B26E/F CFM56-7B27 CFM56-7B27A CFM56-7B27AE CFM56-7B27/3 CFM56-7B27/3F CFM56-7B26/3B2 CFM56-7B27/B1 CFM56-7B27/B3 CFM56-7B27/2 CFM56-7B27/3B1 CFM56-7B27/3B3 CFM56-7B27A/3 CFM56-7B27E/B1 CFM56-7B27/3B1F CFM56-7B27E/B3 CFM56-7B27E CFM56-7B27E/F CFM56-7B27E/B1F Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00056EN) 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: CFM International, S.A. 2 Boulevard du General Martial Valin 75015 Paris, France I. MODELS CFM56-7B20 CFM56-7B22 CFM56-7B24 TYPE High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, multi-stage compressor with one-stage high pressure turbine CFM56-7B series: single annular combustor CFM56-7B/2 series: double annular combustor CFM56-7B/3 series: improved emissions single annular combustor CFM56-7B/3F series: improved emissions single annular combustor and increased EGT CFM56-7BE and 7BE/F series: improved HPC diffuser, HPT and LPT performance RATINGS (See NOTE 4) Takeoff (5 min. see NOTE 13), sea level, static thrust, lb. Maximum continuous, sea level static thrust, lb. 20,600/ 9,163 daN 19,400/ 8,630 daN 22,700/ 10,097 daN 22,300/ 9,920 daN 24,200/ 10,765 daN 22,800/ 10,142 daN Flat rating AMBIENT TEMPERATURE Takeoff Maximum continuous 86oF / 30oC 77oF / 25oC - - - - - - - - * 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 REV. 11 8 8 8 8 8 8 8 8 8 8 8 8 8 8 8 8 11 10 10 10 10 10 10 10 11 11 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. E00056EN 2 of 27 I. MODELS (CONT.) CFM56-7B20 CFM56-7B22 CFM56-7B24 FUEL SYSTEM See NOTE 7 for approved fuels. Fuel pump / SNECMA part 340-402-104 - - - - number (P/N) 340-402-105 - - - - (Combined boost and single element gear-type pump) Hydromechanical unit / GE P/N 1853M56 - - - - Electronic control unit / GE P/N - Hardware - Software Identification plugs / SNECMA P/N 1851M50 - - - - 1853M33 - - - - 2042M67 - - - - 2044M16 - - - - 1853M78 - - - - 2044M25 - - - - 340-131-712 340-131-721 340-131-732 340-131-717 340-131-726 340-131-737 340-203-201 340-203-301 340-203-401 340-198-850 340-199-250 340-200-050 340-198-950 340-199-350 340-200-150 OIL Synthetic type conforming to GE Specification D50TF1, Type I and Type II. CFM Service Bulletin CFM56-7B 79-001 list approved brand oils. IGNITION SYSTEM GE P/N Two ignition units Unison 9238M66 - - - - Simmonds 1538M69 - - - - Two igniter plugs Unison 1374M12 - - - - Champion 1374M13 - - - - PRINCIPAL DIMENSIONS INCHES / MILLIMETERS Length (fan case forward 98.7/2507.5 - - - - flange to LPT frame aft flange) Width (maximum envelope) 83.4/2118.0 - - - - Height (fan case forward 72.0/1829.0 - - - - flange outer diameter) WEIGHT (dry) Includes basic engine accessories and optional equipment as listed in manufacturer’s engine specification, including engine mounted portions of the condition monitoring instrumentation. Pounds 5260.0 - - - - Kilograms 2385.9 - - - - CENTER OF GRAVITY LOCATIONS STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) Inches 207.4+ 1.0 - - - - Millimeters 5269+ 25 - - - - E00056EN 3 of 27 II. MODELS CFM56-7B26 CFM56-7B27 CFM56-7B27A CFM56-7B20/2 CFM56-7B22/2 TYPE High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, multi- stage compressor with one-stage high pressure turbine CFM56-7B series: single annular combustor CFM56-7B/2 series: double annular combustor CFM56-7B/3 series: improved emissions single annular combustor CFM56-7B/3F series: improved emissions single annular combustor and increased EGT CFM56-7BE and 7BE/F series: improved HPC diffuser, HPT and LPT performance RATINGS (See NOTE 4) Takeoff (5 min. see NOTE 13), sea level, static thrust, lb. Maximum continuous, sea level static thrust, lb. 26,300/ 11,699 daN 25,900/ 11,521 daN 27,300/ 12,143 daN 25,900/ 11,521 daN - - - - - - - - 20,600/ 9,163 daN 19,400/ 8,630 daN 22,700/ 10,097 daN 22,300/ 9,920 daN Flat rating AMBIENT TEMPERATURE Takeoff Maximum continuous 86oF / 30oC 77oF / 25oC - - - - - - - - - - - - - - - - FUEL SYSTEM See NOTE 7 for approved fuels. Fuel pump / SNECMA P/N (Combined boost and single element gear-type pump) Hydromechanical unit / GE P/N 340-402-104 340-402-105 1853M56 - - - - - - - - - - - - - - - - - - - - - - - - Electronic control unit / GE P/N - Hardware - Software Identification plugs / SNECMA P/N 1851M50 1853M33 2042M67 2044M16 1853M78 2044M25 340-131-742 340-131-747 340-203-501 340-200-850 340-200-950 - - - - - - - - - - - - 340-131-752 340-131-757 340-203-601 340-201-450 340-201-550 --- - - - - - - - - - - 340-203-701 --- --- --- --- 1851M50 - - - - - - - - - - 340-138-710 340-138-715 340-203-201 --- --- - - - - - - - - - - - - 340-138-720 340-138-725 340-203-301 --- --- OIL Synthetic type conforming to GE Specification D50TF1, Type I and Type II. CFM Service Bulletin CFM56-7B 79-001 list approved brand oils. IGNITION SYSTEM GE P/N Two ignition units Unison Simmonds Two igniter plugs Unison Champion 9238M66 1538M69 1374M12 1374M13 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - PRINCIPAL DIMENSIONS INCHES / MILLIMETERS Length (fan case forward flange to LPT frame aft flange) Width (maximum envelope) Height (fan case forward flange outer diameter) 98.7/2507.5 83.4/2118.0 72.0/1829.0 - - - - - - - - - - - - - - - - - - - - - - - - E00056EN 4 of 27 II. MODELS (CONT.) CFM56-7B26 CFM56-7B27 CFM56-7B27A CFM56-7B20/2 CFM56-7B22/2 WEIGHT (dry) Includes basic engine accessories and optional equipment as listed in manufacturer’s engine specification, including engine mounted portions of the condition monitoring instrumentation. Pounds Kilograms 5260 2385.9 - - - - 5282 2395.9 5360 2431.3 - - - - CENTER OF GRAVITY LOCATIONS STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) Inches Millimeters 207.4 + 1.0 5269 + 25 - - - - - - - - - - - - - - - - III. MODELS CFM56-7B24/2 CFM56-7B26/2 CFM56-7B27/2 CFM56-7B26/B1 TYPE High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, multi-stage compressor with one-stage high pressure turbine CFM56-7B series: single annular combustor CFM56-7B/2 series: double annular combustor CFM56-7B/3 series: improved emissions single annular combustor CFM56-7B/3F series: improved emissions single annular combustor and increased EGT CFM56-7BE and 7BE/F series: improved HPC diffuser, HPT and LPT performance RATINGS (See NOTE 4) Takeoff (5 min. see NOTE 13), sea level, static thrust, lb. Maximum continuous, sea level static thrust, lb. 24,200/ 10,765 daN 22,800/ 10,142 daN 26,300/ 11,699 daN 25,900/ 11,521 daN 27,300/ 12,143 daN 25,900/ 11,521 daN 26,300/ 11,699 daN 25,900/ 11,521 daN Flat rating AMBIENT TEMPERATURE Takeoff Maximum continuous 86oF / 30oC 77oF / 25oC - - - - - - - - - - - - FUEL SYSTEM See NOTE 7 for approved fuels Fuel pump / SNECMA P/N (Combined boost and single element gear-type pump) Hydromechanical unit / GE P/N 340-402-104 340-402-105 1853M56 - - - - - - - - - - - - - - - - - - Electronic control unit / GE P/N - Hardware - Software Identification plugs / SNECMA P/N 1851M50 1853M33 2042M67 2044M16 1853M78 2044M25 340-138-730 340-138-735 340-203-401 - - - - - - - - - - - - 340-138-740 340-138-745 340-203-501 - - - - - - - - - - - - 340-138-750 340-138-755 340-203-601 - - - - - - - - - - - - 340-203-511 340-143-201 340-143-301 340-201-050 340-201-150 E00056EN 5 of 27 III. MODELS (CONT.) CFM56-7B24/2 CFM56-7B26/2 CFM56-7B27/2 CFM56-7B26/B1 OIL Synthetic type conforming to GE Specification D50TF1, Type I and Type II. CFM Service Bulletin CFM56-7B 79-001 list approved brand oils. IGNITION SYSTEM GE P/N Two ignition units Unison Simmonds Two igniter plugs Unison Champion 9238M66 1538M69 1374M12 1374M13 - - - - - - - - - - - - - - - - - - - - - - - - PRINCIPAL DIMENSIONS INCHES / MILLIMETERS Length (fan case forward flange to LPT frame aft flange) Width (maximum envelope) Height (fan case forward flange outer diameter) 98.7/2507.5 83.4/2118.0 72.0/1829.0 - - - - - - - - - - - - - - - - - - WEIGHT (dry) Includes basic engine accessories and optional equipment as listed in manufacturer’s engine specification, including engine mounted portions of the condition monitoring instrumentation. Pounds Kilograms 5360 2431.3 - - - - - - - - 5260 2385.9 CENTER OF GRAVITY LOCATIONS STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) Inches Millimeters 207.4 + 1.0 5269 + 25 - - - - - - - - - - - - IV. MODELS CFM56-7B27/B1 CFM56-7B27/B3 CFM56-7B22/B1 CFM56-7B24/B1 TYPE High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, multi- stage compressor with one-stage high pressure turbine CFM56-7B series: single annular combustor CFM56-7B/2 series: double annular combustor CFM56-7B/3 series: improved emissions single annular combustor CFM56-7B/3F series: improved emissions single annular combustor and increased EGT CFM56-7BE and 7BE/F series: improved HPC diffuser, HPT and LPT performance RATINGS (See NOTE 4) Takeoff (5 min. see NOTE 13), sea level, static thrust, lb. 27,300/ 12,143 daN - - 22,700/ 10,097 daN 24,200/ 10,765 daN Maximum continuous, sea level static thrust, lb. 25,900/ 11,521 daN - - 22,300/ 9,920 daN 22,800/ 10,142 daN Flat rating AMBIENT TEMPERATURE Takeoff Maximum continuous 86oF / 30oC 77oF / 25oC - - - - 96.8oF / 36oC - - 105.8oF / 41oC - - FUEL SYSTEM See NOTE 7 for approved fuels. Fuel pump / SNECMA P/N (Combined boost and single element gear-type pump) Hydromechanical unit / GE P/N 340-402-104 340-402-105 1853M56 - - - - - - - - - - - - - - - - - - E00056EN 6 of 27 IV. MODELS (CONT.) CFM56-7B27/B1 CFM56-7B27/B3 CFM56-7B22/B1 CFM56-7B24/B1 Electronic control unit / GE P/N - Hardware - Software Identification plugs / SNECMA P/N 1851M50 1853M33 2042M67 2044M16 1853M78 2044M25 340-142-801 340-142-901 340-203-611 340-201-650 340-201-750 - - - - - - - - - - - - 340-143-441 340-143-451 340-203-631 340-202-050 340-202-150 - - - - - - - - - - - - 340-142-001 340-142-101 340-203-311 340-199-450 340-199-550 - - - - - - - - - - - - 340-142-201 340-142-301 340-203-411 340-200-250 340-200-350 OIL Synthetic type conforming to GE Specification D50TF1, Type I and Type II. CFM Service Bulletin CFM56-7B 79-001 list approved brand oils. IGNITION SYSTEM GE P/N Two ignition units Unison Simmonds Two igniter plugs Unison Champion 9238M66 1538M69 1374M12 1374M13 - - - - - - - - - - - - - - - - - - - - - - - - PRINCIPAL DIMENSIONS INCHES / MILLIMETERS Length (fan case forward flange to LPT frame aft flange) Width (maximum envelope) Height (fan case forward flange outer diameter) 98.7/2507.5 83.4/2118.0 72.0/1829.0 - - - - - - - - - - - - - - - - - - WEIGHT (dry) Includes basic engine accessories and optional equipment as listed in manufacturer’s engine specification, including engine mounted portions of the condition monitoring instrumentation. Pounds Kilograms 5260 2385.9 - - - - - - - - - - - - CENTER OF GRAVITY LOCATIONS STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) Inches Millimeters 207.4 + 1.0 5269 + 25 - - - - - - - - - - - - E00056EN 7 of 27 V. MODELS CFM56-7B26/B2 CFM56-7B26/3B2 TYPE High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, multi- stage compressor with one-stage high pressure turbine CFM56-7B series: single annular combustor CFM56-7B/2 series: double annular combustor CFM56-7B/3 series: improved emissions single annular combustor CFM56-7B/3F series: improved emissions single annular combustor and increased EGT CFM56-7BE and 7BE/F series: improved HPC diffuser, HPT and LPT performance RATINGS (See NOTE 4) Takeoff (5 min. See NOTE 13), sea level, static thrust, lb. 26,300/ 11,699 daN 26,300/ 11,699 daN Maximum continuous, sea level static thrust, lb. 22,800/ 10,142 daN 22,800/ 10,142 daN Flat rating AMBIENT TEMPERATURE Takeoff Maximum continuous 95°F / 35°C 77°F / 25°C - - - - FUEL SYSTEM See NOTE 7 for approved fuels. Fuel pump / SNECMA P/N 340-402-104 340-402-105 (Combined boost and single 340-402-105 element gear-type pump) Hydromechanical unit / GE P/N 1853M56 - - Electronic control unit / GE P/N - Hardware 1851M50 - - 1853M33 - - 2042M67 - - 2044M16 - - - Software 1853M78 - - 2044M25 - - Identification plugs / 340-203-521 340-203-521 SNECMA P/N OIL Synthetic type conforming to GE Specification D50TFI, Type I and Type II. CFM Service Bulletin CFM56-7B 79-001 list approved brand oils. IGNITION SYSTEM GE P/N Two ignition units Unison 9238M66 - - Simmonds 1538M69 - - Two igniter plugs Unison 1374M12 - - Champion 1374M13 - - PRINCIPLE DIMENSIONS INCHES / MILLIMETERS Length (fan case forward 98.7 / 2507.5 - - flange to LPT frame aft flange) Width (maximum envelope) 83.4 / 2118.0 - - Height (fan case forward 72.0 / 1829.0 - - flange outer diameter E00056EN 8 of 27 V. MODELS (CONT.) CFM56-7B26/B2 CFM56-7B26/3B2 WEIGHT (dry) Includes basic engine accessories and optional equipment as listed in manufacturer’s engine specification, including engine mounted portions of the condition monitoring instrumentation. Pounds 5260 2385.9 - - - - Kilograms CENTER OF GRAVITY LOCATIONS STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) Inches Millimeters 207.4 + 1.0 5269 + 25 - - - - VI. MODELS CFM56-7B20/3 CFM56-7B22/3 CFM56-7B24/3 TYPE High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, multi-stage compressor with one-stage high pressure turbine CFM56-7B series: single annular combustor CFM56-7B/2 series: double annular combustor CFM56-7B/3 series: improved emissions single annular combustor CFM56-7B/3F series: improved emissions single annular combustor and increased EGT CFM56-7BE and 7BE/F series: improved HPC diffuser, HPT and LPT performance RATINGS (See NOTE 4) Takeoff (5 min. see NOTE 13), sea level, static thrust, lb. Maximum continuous, sea level static thrust, lb. 20,600/ 9,163 daN 19,400/ 8,630 daN 22,700/ 10,097 daN 22,300/ 9,920 daN 24,200/ 10,765 daN 22,800/ 10,142 daN Flat rating AMBIENT TEMPERATURE Takeoff Maximum continuous 86oF / 30oC 77oF / 25oC - - - - - - - - FUEL SYSTEM See NOTE 7 for approved fuels. Fuel pump / SNECMA P/N (Combined boost and single element gear-type pump) Hydromechanical unit / GE P/N 340-402-105 1853M56 - - - - - - - - Electronic control unit / GE P/N - Hardware - Software Identification plugs / SNECMA P/N 1851M50 1853M33 2042M67 2044M16 1853M78 2044M25 340-203-201 - - - - - - - - - - - - 340-203-301 - - - - - - - - - - - - 340-203-401 E00056EN 9 of 27 VI. MODELS (CONT.) CFM56-7B20/3 CFM56-7B22/3 CFM56-7B24/3 OIL Synthetic type conforming to GE Specification D50TF1, Type I and Type II. CFM Service Bulletin CFM56-7B 79-001 list approved brand oils. IGNITION SYSTEM GE P/N Two ignition units Unison 9238M66 - - - - Simmonds 1538M69 - - - - Two igniter plugs Unison 1374M12 - - - - Champion 1374M13 - - - - PRINCIPAL DIMENSIONS INCHES / MILLIMETERS Length (fan case forward 98.7/2507.5 - - - - flange to LPT frame aft flange) Width (maximum envelope) 83.4/2118.0 - - - - Height (fan case forward 72.0/1829.0 - - - - flange outer diameter) WEIGHT (dry) Includes basic engine accessories and optional equipment as listed in manufacturer’s engine specification, including engine mounted portions of the condition monitoring instrumentation. Pounds 5260.0 - - - - Kilograms 2385.9 - - - - CENTER OF GRAVITY LOCATIONS STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) Inches 207.4+ 1.0 - - - - Millimeters 5269+ 25 - - - - VII. MODELS CFM56-7B26/3 CFM56-7B27/3 CFM56-7B26/3B1 CFM56-7B27A/3 TYPE High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, multi-stage compressor with one-stage high pressure turbine CFM56-7B series: single annular combustor CFM56-7B/2 series: double annular combustor CFM56-7B/3 series: improved emissions single annular combustor CFM56-7B/3F series: improved emissions single annular combustor and increased EGT CFM56-7BE and 7BE/F series: improved HPC diffuser, HPT and LPT performance RATINGS (See NOTE 4) Takeoff (5 min. see NOTE 13), sea level, static thrust, lb. 26,300/ 11,699 daN 27,300/ 12,143 daN 26,300/ 11,699 daN 27,300/ 12,143 daN Maximum continuous, sea level static thrust, lb. 25,900/ 11,521 daN 25,900/ 11,521 daN 25,900/ 11,521 daN 25,900/ 11,521 daN Flat rating AMBIENT TEMPERATURE Takeoff Maximum continuous 86oF / 30oC 77oF / 25oC - - - - - - - - - - - - E00056EN 10 of 27 VII. MODELS (CONT.) CFM56-7B26/3 CFM56-7B27/3 CFM56-7B26/3B1 CFM56-7B27A/3 FUEL SYSTEM See NOTE 7 for approved fuels. Fuel pump / SNECMA P/N (Combined boost and single element gear-type pump) Hydromechanical unit / GE P/N 340-402-105 1853M56 - - - - - - - - - - - - Electronic control unit / GE P/N - Hardware - Software Identification plugs / SNECMA P/N 1851M50 1853M33 2042M67 2044M16 1853M78 2044M25 340-203-501 - - - - - - - - - - - - 340-203-601 - - - - - - - - - - - - 340-203-511 - - - - - - - - - - - - 340-203-701 OIL Synthetic type conforming to GE Specification D50TF1, Type I and Type II. CFM Service Bulletin CFM56-7B 79-001 list approved brand oils. IGNITION SYSTEM GE P/N Two ignition units Unison Simmonds Two igniter plugs Unison Champion 9238M66 1538M69 1374M12 1374M13 - - - - - - - - - - - - - - - - - - - - - - - - PRINCIPAL DIMENSIONS INCHES / MILLIMETERS Length (fan case forward flange to LPT frame aft flange) Width (maximum envelope) Height (fan case forward flange outer diameter) 98.7/2507.5 83.4/2118.0 72.0/1829.0 - - - - - - - - - - - - - - - - - - WEIGHT (dry) Includes basic engine accessories and optional equipment as listed in manufacturer’s engine specification, including engine mounted portions of the condition monitoring instrumentation. Pounds Kilograms 5260 2385.9 - - - - - - - - 5282 2395.9 CENTER OF GRAVITY LOCATIONS STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) Inches Millimeters 207.4 + 1.0 5269 + 25 - - - - - - - - - - - - E00056EN 11 of 27 VIII. MODELS CFM56-7B27/3F CFM56-7B27/3B1F CFM56-7B26/3F CFM56-7B26/3B2F TYPE High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, multi-stage compressor with one-stage high pressure turbine CFM56-7B series: single annular combustor CFM56-7B/2 series: double annular combustor CFM56-7B/3 series: improved emissions single annular combustor CFM56-7B/3F series: improved emissions single annular combustor and increased EGT CFM56-7BE and 7BE/F series: improved HPC diffuser, HPT and LPT performance RATINGS (See NOTE 4) Takeoff (5 min. see NOTE 13), sea level, static thrust, lb. 27,300/ 12,143 daN - - - - 26,300/ 11,699 daN - - - - Maximum continuous, sea level static thrust, lb. 25,900/ 11,521 daN - - - - 25,900/ 11,521 daN 22,800/ 10,142 daN Flat rating AMBIENT TEMPERATURE Takeoff Maximum continuous 86oF / 30oC 77oF / 25oC - - - - - - - - - - - - FUEL SYSTEM See NOTE 7 for approved fuels. Fuel pump / SNECMA P/N (Combined boost and single element gear-type pump) 340-402-105 - - - - - - Hydromechanical unit / GE P/N 1853M56 - - - - - - Electronic control unit / GE P/N - Hardware - Software Identification plugs / SNECMA P/N 1851M50 1853M33 2042M67 2044M16 1853M78 2044M25 340-205-001 - - - - - - - - - - - - 340-205-111 - - - - - - - - - - - - 340-205-101 - - - - - - - - - - - - 340-205-021 OIL Synthetic type conforming to GE Specification D50TF1, Type I and Type II. CFM Service Bulletin CFM56-7B 79-001 list approved brand oils. IGNITION SYSTEM GE P/N Two ignition units Unison Simmonds Two igniter plugs Unison Champion 9238M66 1538M69 1374M12 1374M13 - - - - - - - - - - - - - - - - - - - - - - - - PRINCIPAL DIMENSIONS INCHES / MILLIMETERS Length (fan case forward flange to LPT frame aft flange) Width (maximum envelope) Height (fan case forward flange outer diameter) 98.7/2507.5 83.4/2118.0 72.0/1829.0 - - - - - - - - - - - - - - - - - - E00056EN 12 of 27 VIII. MODELS (CONT.) CFM56-7B27/3F CFM56-7B27/3B1F CFM56-7B26/3F CFM56-7B26/3B1F WEIGHT (dry) Includes basic engine accessories and optional equipment as listed in manufacturer’s engine specification, including engine mounted portions of the condition monitoring instrumentation. Pounds Kilograms 5260 2385.9 - - - - - - - - - - - - CENTER OF GRAVITY LOCATIONS STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) Inches Millimeters 207.4 + 1.0 5269 + 25 - - - - - - - - - - - - IX. MODELS CFM56-7B27/3B1 CFM56-7B27/3B3 CFM56-7B22/3B1 CFM56-7B24/3B1 TYPE High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, multi- stage compressor with one-stage high pressure turbine CFM56-7B series: single annular combustor CFM56-7B/2 series: double annular combustor CFM56-7B/3 series: improved emissions single annular combustor CFM56-7B/3F series: improved emissions single annular combustor and increased EGT CFM56-7BE and 7BE/F series: improved HPC diffuser, HPT and LPT performance RATINGS (See NOTE 4) Takeoff (5 min. see NOTE 13), sea level, static thrust, lb. 27,300/ 12,143 daN - - 22,700/ 10,097 daN 24,200/ 10,765 daN Maximum continuous, sea level static thrust, lb. 25,900/ 11,521 daN - - 22,300/ 9,920 daN 22,800/ 10,142 daN Flat rating AMBIENT TEMPERATURE Takeoff Maximum continuous 86oF / 30oC 77oF / 25oC - - - - 96.8oF / 36oC - - 105.8oF / 41oC - - FUEL SYSTEM See NOTE 7 for approved fuels. Fuel pump / SNECMA P/N (Combined boost and single element gear-type pump) 340-402-105 - - - - - - Hydromechanical unit / GE P/N 1853M56 - - - - - - Electronic control unit / GE P/N - Hardware - Software Identification plugs / SNECMA P/N 1851M50 1853M33 2042M67 2044M16 1853M78 2044M25 340-203-611 - - - - - - - - - - - - 340-203-631 - - - - - - - - - - - - 340-203-311 - - - - - - - - - - - - 340-203-411 OIL Synthetic type conforming to GE Specification D50TF1, Type I and Type II. CFM Service Bulletin CFM56-7B 79-001 list approved brand oils. IGNITION SYSTEM GE P/N Two ignition units Unison Simmonds Two igniter plugs Unison Champion 9238M66 1538M69 1374M12 1374M13 - - - - - - - - - - - - - - - - - - - - - - - - E00056EN 13 of 27 IX. MODELS (CONT.) CFM56-7B27/3B1 CFM56-7B27/3B3 CFM56-7B22/3B1 CFM56-7B24/3B1 PRINCIPAL DIMENSIONS INCHES / MILLIMETERS Length (fan case forward flange to LPT frame aft flange) Width (maximum envelope) Height (fan case forward flange outer diameter) 98.7/2507.5 83.4/2118.0 72.0/1829.0 - - - - - - - - - - - - - - - - - - WEIGHT (dry) Includes basic engine accessories and optional equipment as listed in manufacturer’s engine specification, including engine mounted portions of the condition monitoring instrumentation. Pounds Kilograms 5260 2385.9 - - - - - - - - - - - - CENTER OF GRAVITY LOCATIONS STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) Inches Millimeters 207.4 + 1.0 5269 + 25 - - - - - - - - - - - - X. MODELS CFM56-7B20E CFM56-7B22E CFM56-7B24E CFM56-7B24E/B1 TYPE High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, multi-stage compressor with one-stage high pressure turbine CFM56-7B series: single annular combustor CFM56-7B/2 series: double annular combustor CFM56-7B/3 series: improved emissions single annular combustor CFM56-7B/3F series: improved emissions single annular combustor and increased EGT CFM56-7BE series: improved HPC diffuser, HPT and LPT performance RATINGS (See NOTE 4) Takeoff (5 min. see NOTE 13), sea level, static thrust, lb. Maximum continuous, sea level static thrust, lb. 20,600/ 9,163 daN 19,400/ 8,630 daN 22,700/ 10,097 daN 22,300/ 9,920 daN 24,200/ 10,765 daN 22,800/ 10,142 daN 24,200/ 10,765 daN 22,800/ 10,142 daN Flat rating AMBIENT TEMPERATURE Takeoff Maximum continuous 86 oF / 30oC 77oF / 25oC - - - - - - - - 105.8 oF / 41oC - - FUEL SYSTEM See NOTE 7 for approved fuels. Fuel pump / SNECMA part number (P/N) (Combined boost and single element gear-type pump) Hydromechanical unit / GE P/N 340-402-105 1853M56 - - - - - - - - - - - - - - - - Electronic control unit / GE P/N - Hardware - Software Identification plugs / SNECMA P/N 1851M50 1853M33 2042M67 2044M16 1853M78 2044M25 340-203-201 - - - - - - - - - - - - 340-203-301 - - - - - - - - - - - - 340-203-401 - - - - - - - - - - - - 340-203-411 E00056EN 14 of 27 X. MODELS(CONT) CFM56-7B20E CFM56-7B22E CFM56-7B24E CFM56-7B24E/B1 OIL Synthetic type conforming to GE Specification D50TF1, Type I and Type II. CFM Service Bulletin CFM56-7B 79-001 list approved brand oils. IGNITION SYSTEM GE P/N Two ignition units Unison Simmonds Two igniter plugs Unison Champion 9238M66 1538M69 1374M12 1374M13 - - - - - - - - - - - - - - - - - - - - - - - - PRINCIPAL DIMENSIONS INCHES / MILLIMETERS Length (fan case forward flange to LPT frame aft flange) Width (maximum envelope) Height (fan case forward flange outer diameter) 98.7/2507.5 83.4/2118.0 72.0/1829.0 - - - - - - - - - - - - - - - - - - WEIGHT (dry) Includes basic engine accessories and optional equipment as listed in manufacturer’s engine specification, including engine mounted portions of the condition monitoring instrumentation. Pounds Kilograms 5280 2395 - - - - - - - - - - - - CENTER OF GRAVITY LOCATIONS STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) Inches Millimeters 207.4+ 1.0 5269+ 25 - - - - - - - - - - - - XI. MODELS CFM56-7B26E CFM56-7B27E CFM56-7B26E/B1 CFM56-7B27AE TYPE High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, multi-stage compressor with one-stage high pressure turbine CFM56-7B series: single annular combustor CFM56-7B/2 series: double annular combustor CFM56-7B/3 series: improved emissions single annular combustor CFM56-7B/3F series: improved emissions single annular combustor and increased EGT CFM56-7BE series: improved HPC diffuser, HPT and LPT performance RATINGS (See NOTE 4) Takeoff (5 min. see NOTE 13), sea level, static thrust, lb. 26,300/ 11,699 daN 27,300/ 12,143 daN 26,300/ 11,699 daN 27,300/ 12,143 daN Maximum continuous, sea level static thrust, lb. 25,900/ 11,521 daN 25,900/ 11,521 daN 25,900/ 11,521 daN 25,900/ 11,521 daN Flat rating AMBIENT TEMPERATURE Takeoff Maximum continuous 86oF / 30oC 77oF / 25oC - - - - - - - - - - - - E00056EN 15 of 27 XI. MODELS (CONT.) CFM56-7B26E CFM56-7B27E CFM56-7B26E/B1 CFM56-7B27AE FUEL SYSTEM See NOTE 7 for approved fuels. Fuel pump / SNECMA P/N (Combined boost and single element gear-type pump) 340-402-105 - - - - - - Hydromechanical unit / GE P/N 1853M56 - - - - - - Electronic control unit / GE P/N - Hardware - Software Identification plugs / SNECMA P/N 1851M50 1853M33 2042M67 2044M16 1853M78 2044M25 340-203-501 - - - - - - - - - - - - 340-203-601 - - - - - - - - - - - - 340-203-511 - - - - - - - - - - - - 340-203-701 OIL Synthetic type conforming to GE Specification D50TF1, Type I and Type II. CFM Service Bulletin CFM56-7B 79-001 list approved brand oils. IGNITION SYSTEM GE P/N Two ignition units Unison Simmonds Two igniter plugs Unison Champion 9238M66 1538M69 1374M12 1374M13 - - - - - - - - - - - - - - - - - - - - - - - - PRINCIPAL DIMENSIONS INCHES / MILLIMETERS Length (fan case forward flange to LPT frame aft flange) Width (maximum envelope) Height (fan case forward flange outer diameter) 98.7/2507.5 83.4/2118.0 72.0/1829.0 - - - - - - - - - - - - - - - - - - WEIGHT (dry) Includes basic engine accessories and optional equipment as listed in manufacturer’s engine specification, including engine mounted portions of the condition monitoring instrumentation. Pounds 5280 - - - - 5302 Kilograms 2395 - - - - 2405 CENTER OF GRAVITY LOCATIONS STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) Inches 207.4 + 1.0 - - - - - - Millimeters 5269 + 25 - - - - - - E00056EN 16 of 27 XII. MODELS CFM56-7B27E/F CFM56-7B27E/B1F CFM56-7B26E/F CFM56-7B26E/B2F TYPE High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, multi-stage compressor with one-stage high pressure turbine CFM56-7B series: single annular combustor CFM56-7B/2 series: double annular combustor CFM56-7B/3 series: improved emissions single annular combustor CFM56-7B/3F series: improved emissions single annular combustor and increased EGT CFM56-7BE series: improved HPC diffuser, HPT and LPT performance RATINGS (See NOTE 4) Takeoff (5 min. see NOTE 13), sea level, static thrust, lb. 27,300/ 12,143 daN - - - - 26,300/ 11,699 daN - - - - Maximum continuous, sea level static thrust, lb. 25,900/ 11,521 daN - - - - 25,900/ 11,521 daN 22,800/ 10,142 daN Flat rating AMBIENT TEMPERATURE Takeoff Maximum continuous 86oF / 30oC 77oF / 25oC - - - - - - - - 95.oF / 35oC - - FUEL SYSTEM See NOTE 7 for approved fuels. Fuel pump / SNECMA P/N (Combined boost and single element gear-type pump) 340-402-105 - - - - - - Hydromechanical unit / GE P/N 1853M56 - - - - - - Electronic control unit / GE P/N - Hardware - Software Identification plugs / SNECMA P/N 1851M50 1853M33 2042M67 2044M16 1853M78 2044M25 340-205-001 - - - - - - - - - - - - 340--111 - - - - - - - - - - - - 340-205-101 - - - - - - - - - - - - 340-205-021 OIL Synthetic type conforming to GE Specification D50TF1, Type I and Type II. CFM Service Bulletin CFM56-7B 79-001 list approved brand oils. IGNITION SYSTEM GE P/N Two ignition units Unison Simmonds Two igniter plugs Unison Champion 9238M66 1538M69 1374M12 1374M13 - - - - - - - - - - - - - - - - - - - - - - - - PRINCIPAL DIMENSIONS INCHES / MILLIMETERS Length (fan case forward flange to LPT frame aft flange) Width (maximum envelope) Height (fan case forward flange outer diameter) 98.7/2507.5 83.4/2118.0 72.0/1829.0 - - - - - - - - - - - - - - - - - - E00056EN 17 of 27 XII. MODELS (CONT.) CFM56-7B27E/F CFM56-7B27E/B1F CFM56-7B26E/F CFM56-7B26E/B2F WEIGHT (dry) Includes basic engine accessories and optional equipment as listed in manufacturer’s engine specification, including engine mounted portions of the condition monitoring instrumentation. Pounds Kilograms 5280 2395 - - - - - - - - - - - - CENTER OF GRAVITY LOCATIONS STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) Inches Millimeters 207.4 + 1.0 5269 + 25 - - - - - - - - - - - - XIII. MODELS CFM56-7B27E/B1 CFM56-7B27E/B3 CFM56-7B22E/B1 CFM56-7B26E/B2 TYPE High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, multi- stage compressor with one-stage high pressure turbine CFM56-7B series: single annular combustor CFM56-7B/2 series: double annular combustor CFM56-7B/3 series: improved emissions single annular combustor CFM56-7B/3F series: improved emissions single annular combustor and increased EGT CFM56-7BE series: improved HPC diffuser, HPT and LPT performance RATINGS (See NOTE 4) Takeoff (5 min. see NOTE 13), sea level, static thrust, lb. 27,300/ 12,143 daN - - 22,700/ 10,097 daN 26,300/ 10,699 daN Maximum continuous, sea level static thrust, lb. 25,900/ 11,521 daN - - 22,300/ 9,920 daN 22,800/ 10,142 daN Flat rating AMBIENT TEMPERATURE Takeoff Maximum continuous 86oF / 30oC 77oF / 25oC - - - - 96.8oF / 36oC - - 95.oF / 35oC - - FUEL SYSTEM See NOTE 7 for approved fuels. Fuel pump / SNECMA P/N (Combined boost and single element gear-type pump) 340-402-105 - - - - - - Hydromechanical unit / GE P/N 1853M56 - - - - - - Electronic control unit / GE P/N - Hardware - Software Identification plugs / SNECMA P/N 1851M50 1853M33 2042M67 2044M16 1853M78 2044M25 340-203-611 - - - - - - - - - - - - 340-203-631 - - - - - - - - - - - - 340-203-311 - - - - - - - - - - - - 340-203-521 E00056EN 18 of 27 XIII. MODELS (CONT) CFM56-7B27E/B1 CFM56-7B27E/B3 CFM56-7B22E/B1 CFM56-7B26E/B2 OIL Synthetic type conforming to GE Specification D50TF1, Type I and Type II. CFM Service Bulletin CFM56-7B 79-001 list approved brand oils. IGNITION SYSTEM GE P/N Two ignition units Unison Simmonds Two igniter plugs Unison Champion 9238M66 1538M69 1374M12 1374M13 - - - - - - - - - - - - - - - - - - - - - - - - PRINCIPAL DIMENSIONS INCHES / MILLIMETERS Length (fan case forward flange to LPT frame aft flange) Width (maximum envelope) Height (fan case forward flange outer diameter) 98.7/2507.5 83.4/2118.0 72.0/1829.0 - - - - - - - - - - - - - - - - - - WEIGHT (dry) Includes basic engine accessories and optional equipment as listed in manufacturer’s engine specification, including engine mounted portions of the condition monitoring instrumentation. Pounds Kilograms 5280 2395 - - - - - - - - - - - - CENTER OF GRAVITY LOCATIONS STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) Inches Millimeters 207.4 + 1.0 5269 + 25 - - - - - - - - - - - - CERTIFICATION BASIS 1. 14 CFR Part 33 effective February 1, 1965, with Amendments 33-1 through 33-15 thereto. 2. The following models comply with 14 CFR part 34, amendment 5, effective December 31, 2012: CFM56-7B20/3 CFM56-7B22/3 CFM56-7B24/3 CFM56-7B24/3B1 CFM56-7B26/3 CFM56-7B26/3B1 CFM56-7B26/3B2 CFM56-7B26/3F CFM56-7B26/3B2F CFM56-7B27/3 CFM56-7B27/3B1 CFM56-7B27/3B3 CFM56-7B27/3F CFM56-7B27/3B1F CFM56-7B27A/3 The following models comply with 14 CFR part 34, amendment 7A, effective May 24, 2024: CFM56-7B20E CFM56-7B22E CFM56-7B22E/B1 CFM56-7B24E CFM56-7B24E/B1 CFM56-7B26E CFM56-7B26E/B1 CFM56-7B26E/B2 CFM56-7B26E/F CFM56-7B26E/B2F CFM56-7B27E CFM56-7B27E/B1 CFM56-7B27E/B3 CFM56-7B27E/F CFM56-7B27E/B1F CFM56-7B27AE See NOTE 22 for detailed summary of the certification basis for fuel venting and exhaust emissions. MODEL APPLICATION DATE TYPE CERTIFICATE ISSUED/AMENDED TYPE CERTIFICATE WITHDRAWN CFM56-7B18 CFM56-7B20 CFM56-7B22 CFM56-7B24 CFM56-7B26 CFM56-7B27 CFM56-7B20/2 CFM56-7B22/2 CFM56-7B24/2 CFM56-7B26/2 CFM56-7B27/2 CFM56-7B26/B1 CFM56-7B27/B1 CFM56-7B27/B3 NOV 28, 1995 NOV 28, 1995 NOV 28, 1995 NOV 28, 1995 NOV 28, 1995 NOV 28, 1995 NOV 28, 1995 NOV 28, 1995 NOV 28, 1995 NOV 28, 1995 NOV 28, 1995 MAR 4, 1998 MAR 4, 1998 JUL 30, 1998 DEC 17, 1996 DEC 17, 1996 DEC 17, 1996 DEC 17, 1996 DEC 17, 1996 DEC 17, 1996 NOV 14, 1997 NOV 14, 1997 NOV 14, 1997 NOV 14, 1997 NOV 14, 1997 OCT 30, 1998 OCT 30, 1998 OCT 30, 1998 OCT 17, 2008 (*) CERTIFICATION BASIS (cont) E00056EN 19 of 27 CFM56-7B22/B1 CFM56-7B24/B1 CFM56-7B27A CFM56-7B22/B2 CFM56-7B26/B2 CFM56-7B18/3 CFM56-7B20/3 CFM56-7B22/3 CFM56-7B22/3B1 CFM56-7B22/3B2 CFM56-7B24/3 CFM56-7B24/3B1 CFM56-7B26/3 CFM56-7B26/3B1 CFM56-7B26/3B2 CFM56-7B26/3F CFM56-7B26/3B2F CFM56-7B27/3 CFM56-7B27/3B1 CFM56-7B27/3B3 CFM56-7B27/3F CFM56-7B27/3B1F CFM56-7B27A/3 CFM56-7B20E CFM56-7B22E CFM56-7B22E/B1 CFM56-7B24E CFM56-7B24E/B1 CFM56-7B26E CFM56-7B26E/B1 CFM56-7B26E/B2 CFM56-7B26E/F CFM56-7B26E/B2F CFM56-7B27E CFM56-7B27E/B1 CFM56-7B27E/B3 CFM56-7B27E/F CFM56-7B27E/B1F CFM56-7B27AE JUN 11, 1997 JUN 11, 1997 SEPT 8, 1999 AUG 20, 2001 AUG 20, 2001 APR 23, 2004 APR 23, 2004 APR 23, 2004 APR 23, 2004 APR 23, 2004 APR 23, 2004 APR 23, 2004 APR 23, 2004 APR 23, 2004 APR 23, 2004 DEC 15, 2005 DEC 15, 2005 APR 23, 2004 APR 23, 2004 APR 23, 2004 APR 23, 2004 APR 23, 2004 APR 23, 2004 AUG 28, 2008 AUG 28, 2008 AUG 28, 2008 AUG 28, 2008 AUG 28, 2008 AUG 28, 2008 AUG 28, 2008 AUG 28, 2008 AUG 28, 2008 AUG 28, 2008 AUG 28, 2008 AUG 28, 2008 AUG 28, 2008 AUG 28, 2008 AUG 28, 2008 AUG 28, 2008 MAY 9, 2000 MAY 9, 2000 APR 27, 2001 APR 25, 2003 APR 25, 2003 JUN 14, 2006 JUN 14, 2006 JUN 14, 2006 JUN 14, 2006 JUN 14, 2006 JUN 14, 2006 JUN 14, 2006 JUN 14, 2006 JUN 14, 2006 JUN 14, 2006 JUN 14, 2006 JUN 14, 2006 JUN 14, 2006 JUN 14, 2006 JUN 14, 2006 JUN 14, 2006 JUN 14, 2006 OCT 17, 2008 JUL 30, 2010 JUL 30, 2010 JUL 30, 2010 JUL 30, 2010 JUL 30, 2010 JUL 30, 2010 JUL 30, 2010 JUL 30, 2010 JUL 30, 2010 JUL 30, 2010 JUL 30, 2010 JUL 30, 2010 JUL 30, 2010 JUL 30, 2010 JUL 30, 2010 JUL 30, 2010 OCT 17, 2008(*) OCT 17, 2008(*) OCT 17, 2008(*) (*) Effective October 17, 2008 the models designation CFM56-7B18, CFM56-7B22/B2, CFM56-7B18/3, CFM56-7B22/3B2 were withdrawn at the request of the manufacturer. None of these models were released to revenue service. The Direction Generale de L'Aviation Civile (DGAC) originally type certificated these engine models under DGAC Certificate de Type Moteur M21. The FAA validated these products under Type Certificate Number E00056EN. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of these products on behalf of France. EASA Type Certificate Number EASA.E.004 was issued June 14, 2006. E00056EN 20 of 27 The original production basis was French “Agreement de Production” No. F.G.007 or P03 issued by Direction Generale de L’Aviation Civile (DGAC) for engines produced in France by SNECMA under license from CFM International, S.A. Effective September 28, 2004, these engine models were produced under European Aviation Safety Agency (EASA) Production Certificate FR.21G.0007. (See NOTE 10). IMPORT REQUIREMENTS To be considered for installation on aircraft registered in the United States, each individually imported engine must be accompanied by an EASA airworthiness approval certificate (EASA Form 1 – Authorized Release Certificate) or JAA Form 1 issued by SNECMA on behalf of EASA under EASA Production Certificate FR.21G.0007. The EASA Form 1 – Authorized Release Certificate, or JAA Form 1, should contain the following statement: ‘The engine covered by this certificate has been examined, tested, and found to conform to U.S. Type Certificate E00056EN and is in a condition for safe operation.’ NOTES NOTE 1. MAXIMUM PERMISSIBLE TEMPERATURES (ALL MODELS) TURBINE EXHAUST GAS (T495) (See NOTE 14) As measured by a harness of eight thermocouples located at the second stage low pressure turbine vane: Takeoff (5 min.) Maximum continuous Starting 950oC 925oC 725oC Time temperature envelope Refer to model’s S.O.I. CFMI-TP.01.14 FUEL PUMP INLET REFER TO THE APPROPRIATE INSTALLATION MANUAL. OIL SUPPLY (See NOTE 18) Continuous operation Transient (45 minutes) 140oC/284oF 155oC/311oF NOTE 2. FUEL AND OIL PRESSURE LIMITS Fuel limits Oil limits Fuel system pressure limits required to meet all engine operating conditions extend from a minimum fuel pressure of not less than 5 psia (0.35 bar absolute) above the true fuel vapor pressure to a maximum fuel pressure of 148 psia (10.2 bar absolute) with a fuel vapor/liquid ratio < 0.45 at all conditions. For specific installation limits, see Installation Manual, CFM7B01, Part A, Section 5, Figures A2 and A3. The minimum pressure limit is 13 psid (90 kPa differential). The maximum pressure limit during cold starts is 305 psid (2102 kPa differential), limited by a pressure-relief valve. See NOTE 12. NOTE 3. ACCESSORY DRIVE PROVISIONS ALL MODELS EXCEPT -7B27A, -7B27A/3 & -7B27AE -7B27A,-7B27A/3 & -7B27AE *(3) ELECTRICAL Rotation (1) Speed ratio to core (2) Pad Rating (kW) Shear Torque (in-lb) Maximum overhung moment (in-lb) CW CW 0.565 .565 135 239.4*(3) 9,000 17,500 950 1,540 E00056EN 21 of 27 HYDRAULIC PUMP Rotation (1) Speed ratio to core (2) Pad Rating (in-lb) Shear Torque (in-lb) Maximum overhung moment (in-lb) CW 0.256 1,550 4,400 166 CW 0.256 1,550 4,400 166 (1) CW = CLOCKWISE FACING PAD / CCW = COUNTERCLOCKWISE FACING PAD (2) 100% CORE ENGINE SPEED = 14,460 RPM *(3) FOR 7B27A, 7B27A/3 & 7B27AE, UNDER CERTAIN BLEED CONDITIONS, MAXMUM PAD RATING IS NOT AVAILABLE. REFER TO INSTALLATION MANUAL CFM-7B01 FOR MAX PERMISSIBLE EXTRACTION LOADS UNDER THESE CONDITIONS. NOTE 4. Engine ratings are based on calibrated stand performance (sea level static) under the following conditions: Takeoff thrust is nominally independent of ambient temperature (flat rated) up to ambient temperature of: o o o • Std + 15 C (30 C, 86 F) for all models except as noted below o o o • Std + 21 C (36 C, 96.8 F) for 7B22/B1, 7B22/3B1 and 7B22/B1 o o o • Std + 26 C (41 C, 105.8 F) for 7B24/B1, 7B24/3B1 and 7B24E/B1 o o o • Std + 20 C (35 C, 95 F) for 7B26/B2, 7B26/3B2, 7B26/3B2F, 7B26E/B2 and 7B26E/B2F Maximum continuous is nominally independent of ambient temperature (flat rated) up to o o o ambient temperature of Std. + 10 C (25 C, 77 F) for all models. Zero customer bleed and horsepower extraction. 100% inlet recovery. Based on the production flight exhaust system. NOTE 5. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS (ALL MODELS) RPM % Low pressure rotor (N1) 5,382 104 High pressure rotor (N2) 15,183 105 100% N1 = 5,175 RPM, 100% N2= 14,460 RPM NOTE 6. MAXIMUM PERMISSIBLE AIR BLEED EXTRACTION (ALL MODELS)* LOCATION FAN CORRECTED SPEED FLOW LIMIT Fan Discharge All speeds above minimum idle 2% fan airflow HPC Stage 5 only All speeds above minimum idle 10% core airflow Compressor discharge only Minimum idle to 61% N1K 61% to 82.5% N1K Above 82.5% N1K 12% core airflow Linear variation from 12% to 7% core airflow 7% core airflow HPC Stage 5 and compressor discharge combined Minimum idle to 61% N1K 61% to 82.5% N1K Above 82.5% N1K 13% core airflow Linear variation from 13% to 10% core airflow 10% core airflow * FOR THE 7B27A, 7B27A/3 & 7B27AE ENGINES, UNDER CERTAIN GEARBOX LOAD CONDITIONS, THIS BLEED SCHEDULE WILL NOT BE AVAILABLE. FOR PERMITTED BLEED SCHEDULES UNDER THESE CONDITIONS, REFER TO CFM56-7B INSTALLATION MANUAL CFM7B01. E00056EN 22 of 27 NOTE 7. Approved fuel conforming to GE Specification D50TF2. MIL-T-5624, Grades JP-4 or JP-5, ASTM D 1655, Jet A, A1 and B are consistent with this GE Specification. Primary fuel is 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 is not authorized. Consult Specific Operating Instructions, CFMI-TP.01.14, Section 3, for additive usage. NOTE 8. Life limits established for critical rotating components are published in Chapter 5 of the CFM56-7B Engine Shop Manual, CFM-TP.SM.10. NOTE 9. Power setting, power checks and control of engine thrust output in all operations is to be based on CFM engine charts referring to fan speed. Fan speed sensors are included in the engine assembly for this purpose. NOTE 10. The type certificate holder, CFM International, S.A., is a company established and jointly owned by Societe Nationale l’Etude et de Construction de Moteurs d’Aviation (SNECMA) of France and the General Electric Company for the certification, sale, and support of CFM56 series engines. With respect to the benefits of type certification for production, General Electric and SNECMA function as licensees of CFM International, S.A. This type certificate applies only to engines produced in France under EASA Type Certificate E.004. Engines of the same model designation produced in the United States under Type Certificate No. E00055EN are identical to and fully interchangeable with engines produced under this type certificate. Similarly, modules, assemblies, or parts produced in the United States under Production Certificate No. 108 are eligible for use in engines produced under this type certificate These engines, when produced by General Electric under Production Certificate No.108, are identified by an even numbered serial number prefix ( Reference CFM56-7B Service Bulletin 72-0747 for a list of approved prefixes). All engines identified by an odd numbered prefix () will be produced by SNECMA under Production Certificate No.F.G.007. (Reference CFM56-7B Service Bulletin 72-0747 for a list of approved prefixes) Effective September 28, 2004, engines produced by SNECMA were produced under EASA Production Certificate FR.21G.0007. Engine serial number 893-133 was the first engine produced by SNECMA under the EASA Production Certificate NOTE 11. The minimum permissible idle in flight corresponds to N2=64.7% (9,350 rpm) below 25oF. Between 25oF (-3.8oC) and 40oF (4.4oC), the idle speed varies from 64.7% (9,350 rpm) to 58.8% (8,500 rpm). Above 40oF (4.4oC), the minimum permissible idle speed is 58.8% (8,500 rpm). Other EEC schedule limitations, such as minimum fuel flow and minimum PS3 (including Mach No. bias for 7B27A,7B27A/3 & -7B27AE), may result in minimum N2 speed limitations in flight that are higher than the N2 limits listed above. All limits are non- adjustable and are preset into the EEC schedules. NOTE 12. During negative-g operation only, it is permissible to operate below minimum oil pressure (13 psid) for a maximum of 10 seconds. See Specific Operating Instructions, CFMI-TP.01.14, Section 6. NOTE 13. The normal 5 minute takeoff rating may be extended to 10 minutes for engine out contingency. NOTE 14 (a). The indicated maximum permissible takeoff exhaust gas temperature (EGT) is 950oC. These indicated takeoff EGT redlines are accomplished via an EGT shunt and an EGT trim in the ECU software as noted below. The effect on EGT (units oC) with respect to the indicated takeoff EGT redline value of 950oC for each of the models is summarized below: Model Actual Measured Takeoff Redline Value Authorized Indicated Takeoff EGT level with 30oC Shunt Only* Maximum EGT Trim Level** Indicated Takeoff EGT Redline 7B20, 7B20/3 884 914 36 950 7B22, 7B22/3 886 916 34 950 7B22/B1, 7B22/3B1 907 937 13 950 7B24, 7B24/3 908 938 12 950 E00056EN 23 of 27 7B24/B1, 7B24/3B1 920 950 0 950 7B26, 7B26/B1, 7B26/B2, 7B26/2, 7B26/3B1, 7B26/3B2, 7B26/3 920 950 0 950 7B27, 7B27A, 7B27/B1, 7B27/B3, 7B27/3, 7B27/3B1, 7B27/3B3, 7B27A/3 920 950 0 950 7B20/2 894 914 36 950 7B22/2 896 916 34 950 7B24/2 918 938 12 950 7B26/2 930 950 0 950 7B27/2 930 950 0 950 7B26/3F, 7B26/3B2F, 7B27/3F, 7B27/3B1F 940 950 0 950 7B20E 904 914 36 950 7B22E 906 916 34 950 7B22E/B1 927 937 13 950 7B24E 928 938 12 950 7B24E/B1 940 950 0 950 7B26E/B1, 7B26E/B2, 7B26E 940 950 0 950 7B27E, 7B27E/B1, 7B27E/B3, 940 950 0 950 7B27AE 928 938 12 950 7B26E/F, 7B26E/B2F, 7B27E/F, 7B27E/B1F 960 950 0 950 * EGT shunt adds 30oC to actual measured engine EGT on CFM56-7B, 7B/3 and 7BE series engines, 10oC to actual measured engine EGT on CFM56-7B/3F and –7BE/F series engines, and 20oC to the actual measured engine EGT on CFM56-7B/2 series engines to provide an indicated EGT level. This EGT shunt is triggered above 8,500 RPM core speed for all CFM56 series engines. For E series only, there is a 20oC profile EGT shunt (cooler) in addition to the present +30oC or +10oC (E/F series) shunt. This profile shunt (-20oC) will be active above 10400 rpm Physical Core speed (N2) and –10oC Shunt at ground idle conditions. This profile shunt will be active for all flight conditions. ** The EGT trim function adds the values noted above to the indicated EGT levels. This EGT trim is only triggered at mach numbers from 0 to 0.40 and when the core speed is greater than 11,200 RPM. This function is only applicable for the engine models indicated. NOTE 14 (b). The indicated maximum permissible maximum continuous EGT is 925oC. The same trims and shunts described in Note 14(a) for takeoff EGT are applicable to maximum continuous EGT. NOTE 14 (c). All CFM56-7B engines are certified with an indicated maximum permissible takeoff EGT transient allowance of 960oC for 20 seconds. This equates to a 10oC increase above the maximum permissible indicated value of 950oC. NOTE 15. The CFM56-7B27A, CFM56-7B27A/3 and CFM56-7B27AE variants are designed for military application only. The engine serial number of these variants includes 654, 655, 362 or 363 depending on final assembly location. FAA certified engines used in military service are not necessarily operated or maintained in accordance with FAA regulations. Commercial service uses of the CFM56-7B27A, CFM56-7B27A/3 or CFM56-7B27AE variants, and the installation of used CFM56-7B27A, CFM57-7B27A/3 and CFM56-7B27AE parts in another CFM56-7B variant, are subject to prior approval of the FAA (Engine Certification Office, ANE-140). . NOTE 16. Note deleted. NOTE 17. Criteria pertaining to the dispatch and maintenance requirements for the engine control systems are specified in the airworthiness limitation section of the CFM56-7B Engine Shop Manual (CFM-TP.SM.10), which defines the various configurations and maximum operating intervals. E00056EN 24 of 27 NOTE 18. NOTE 19. NOTE 20. The actual maximum permissible oil temperature for starting and idle conditions is 10oC higher for continuous operation and 5oC higher for transient operation than the corresponding indicated oil temperatures. An indicated oil temperature for continuous operation of 140oC (284oF) corresponds to an actual oil temperature of 150oC (302oF). An indicated oil temperature for transient operation of 155oC (311oF) corresponds to an actual oil temperature of 160oC (320oF). CFM56-7B series includes: CFM56-7B20, -7B22, -7B22/B1, -7B24, -7B24/B1, -7B26, - 7B26/B2, -7B27, -7B27A, -7B26/B1, -7B27/B1 and -7B27/B3 CFM56-7B/2 series includes: CFM56-7B20/2, -7B22/2, -7B24/2, -7B26/2, and -7B27/2 CFM56-7B/3 series includes: CFM56-7B20/3, -7B22/3, -7B22/3B1, -7B22/3B2, -7B24/3, - 7B24/3B1, -7B26/3, -7B26/3B1, -7B26/3B2, -7B27/3, -7B27/3B1, -7B27/3B3, and –7B27A/3 CFM56-7B/3F series includes: CFM56-7B26/3F, -7B26/3B2F, -7B27/3F, and -7B27/3B1F. CFM56-7BE series includes: CFM56-7B20E, -7B22E, -7B22E/B1, -7B22E/B2, -7B24E, - 7B24E/B1, -7B26E, -7B26E/B1, -7B26E/B2, -7B27E, -7B27E/B1, and -7B27E/B3 CFM56-7BE/F series includes: CFM56-7B26E/F, -7B26E/B2F, -7B27E/F, and -7B27E/B1F. The models shown on this TCDS have the following general characteristics: MODEL CHARACTERISTICS CFM56-7B18 Base model. (No longer available) CFM56-7B20 Same as CFM56-7B18 except for increased thrust ratings. CFM56-7B22 Same as CFM56-7B18 except for increased thrust ratings. CFM56-7B24 Same as CFM56-7B18 except for increased thrust ratings. CFM56-7B26 Same as CFM56-7B18 except for increased thrust ratings. CFM56-7B27 Same as CFM56-7B18 except for increased thrust ratings. CFM56-7B20/2 Same as CFM56-7B20 except CFM56-7B20/2 has a double annular combustor. CFM56-7B22/2 Same as CFM56-7B22 except CFM56-7B22/2 has a double annular combustor. CFM56-7B24/2 Same as CFM56-7B24 except CFM56-7B24/2 has a double annular combustor. CFM56-7B26/2 Same as CFM56-7B26 except CFM56-7B26/2 has a double annular combustor. CFM56-7B27/2 Same as CFM56-7B27 except CFM56-7B27/2 has a double annular combustor. CFM56-7B27/B1 Same as CFM56-7B27 except CFM56-7B27/B1 has optimized power management at takeoff. CFM56-7B26/B1 Same as CFM56-7B26 except CFM56-7B26/B1 is intended for a business jet application (different mission). CFM56-7B27/B3 Same as CFM56-7B27 except CFM56-7B27/B3 is intended for a business jet application (different mission). CFM56-7B22/B1 Same as CFM56-7B22 except CFM56-7B22/B1 has an extended flat rated temperature for takeoff. CFM56-7B24/B1 Same as CFM56-7B24 except CFM56-7B24/B1 has an extended flat rated temperature for takeoff. CFM56-7B27A Same as CFM56-7B27, except CFM56-7B27A has increased capability for gearbox power extraction. CFM56-7B26/B2 Same as CFM56-7B26, except CFM56-7B26/B2 has an extended high altitude and temperature rating above corner point takeoff. CFM56-7B20/3 Same as CFM56-7B20 except forlow emissions combustor and redesigned compressor and HPT rotor. CFM56-7B22/3 Same as CFM56-7B20 except for increased thrust, low emissions combustor and redesigned compressor and HPT rotor. CFM56-7B24/3 Same as CFM56-7B20 except for increased thrust, low emissions combustor and redesigned compressor and HPT rotor. CFM56-7B26/3 Same as CFM56-7B20 except for increased thrust, low emissions combustor and redesigned compressor and HPT rotor. CFM56-7B27/3 Same as CFM56-7B20xcept for increased thrust, low emissions combustor and redesigned compressor and HPT rotor. CFM56-7B22/3B1 Same as CFM56-7B22/B1 except for low emissions combustor and redesigned compressor and HPT rotor. E00056EN 25 of 27 NOTE 21. CFM56-7B24/3B1 Same as CFM56-7B24/B1 except for low emissions combustor and redesigned compressor and HPT rotor. CFM56-7B26/3B1 Same as CFM56-7B26/B1 except for low emissions combustor and redesigned compressor and HPT rotor. CFM56-7B26/3B2 Same as CFM56-7B26/B2 except for low emissions combustor and redesigned compressor and HPT rotor. CFM56-7B27/3B1 Same as CFM56-7B27/B1 except for low emissions combustor and redesigned compressor and HPT rotor. CFM56-7B27/3B3 Same as CFM56-7B27/B3 except for low emissions combustor and redesigned compressor and HPT rotor. CFM56-7B26/3F Same as CFM56-7B26/3 except for increased EGT limits CFM56-7B26/3B2F Same as CFM56-7B26/3B2 except for increased EGT limits. CFM56-7B27/3F Same as CFM56-7B27/3 except for increased EGT limits. CFM56-7B27/3B1F Same as CFM56-7B27/3B3 except for increased EGT limits. CFM56-7B27A/3 Same as CFM56-7B27A except for low emissions combustor and redesigned compressor and HPT rotor. CFM56-7BE series The E models incorporate, with respect to /3 models, improved HPC diffuser, new HPT , new LPT and new exhaust diffuser (Boeing Part). CFM56-7BE/F series The E/F models incorporate, with respect to /3F models, improved HPC diffuser, new HPT , new LPT and new exhaust diffuser (Boeing Part). Installation Manuals, Specific Operating Instructions, 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 or for approvals made before September 28, 2003 by DGAC 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. E00056EN 26 of 27 NOTE 22. All engine models are in compliance with the emissions requirements in 14 CFR part 34, effective September 10, 1990, as amended by 34-1 through 34-4, except as follows: 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: CFM56-7B20/3 CFM56-7B22/3 CFM56-7B24/3 CFM56-7B24/3B1 CFM56-7B26/3 CFM56-7B26/3B1 CFM56-7B26/3B2 CFM56-7B26/3F CFM56-7B26/3B2F CFM56-7B27/3 CFM56-7B27/3B1 CFM56-7B27/3B3 CFM56-7B27/3F CFM56-7B27/3B1F CFM56-7B27A/3 Fuel Venting Emission Standards: 14 CFR §34.11; in addition, 40 CFR §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)(1). Hydrocarbons (HC) Emission Standards: 14 CFR § 34.21(d)(1)(i); in addition, 40 CFR §87.23(c)(1). Oxides of Nitrogen (NOx) Emission Standards: 14 CFR §§ 34.23(a)(2) and 34.23(b)(1); in addition, 40 CFR §§ 87.23(c)(2) and 87.23(c)(3). In addition to the FAA's finding of compliance based on the certification requirements defined in this TCDS, the engine manufacturer has declared that the ICAO emissions standards identified in Annex 16, Volume II, Third Edition, Part III, Chapter 2, Section 2.2.2 for SN, Section 2.3.2 for CO and HC, Sections 2.3.2.d.2.i and 2.3.2.e.2.i for NOx (also known as CAEP/6 and CAEP/8, respectively), 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: CFM56-7B20E CFM56-7B22E CFM56-7B22E/B1 CFM56-7B24E CFM56-7B24E/B1 CFM56-7B26E CFM56-7B26E/B1 CFM56-7B26E/B2 CFM56-7B26E/F CFM56-7B26E/B2F CFM56-7B27E CFM56-7B27E/B1 CFM56-7B27E/B3 CFM56-7B27E/F CFM56-7B27E/B1F CFM56-7B27AE 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) E00056EN 27 of 27 NOTE 23 NOTE DELETED. ----END---- ``` ## ADs None name its models. ## STCs approved under this data sheet (1) - [STC SE04840NY](https://openairdocs.org/stc/SE04840NY): Installation of HarcoSemco Exhaust Gas Temperature (EGT) Electrical Harnesses in CFM56-7 engine. 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