TCDS E21EU

I TCDS NUMBER E21EU U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E21EU REVISION: 13* DATE: February 17, 2022 CFM INTERNATIONAL, S.A. MODELS: CFM56-2 CFM56-3 CFM56-2A CFM56-3B CFM56-2B CFM56-3C Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E21EU) 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 (See NOTE 12) CFM56-2 CFM56-2B CFM56-2A CFM56-3 CFM56-3B TYPE RATINGS (See NOTE 4) High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, multi-stage compressor with one stage turbine and annular combustor. Takeoff (5 min., see NOTE 16), sea level, static thrust, lb./daN. Maximum continuous, sea level static thrust, lb. Flat rating Takeoff Maximum continuous FUEL SYSTEM Fuel Control, Woodward 24,000/10,676 23,000/10,230 22,000/9,786 21,580/9,599 24,000/10,676 23,405/10,411 20,100/8,941 18,900/8,407 22,100/9,830 20,500/9,118 AMBIENT TEMPERATURE 86oF / 30oC 77oF / 25oC 90oF/32.2oC - - 95oF / 35oC - - 86oF / 30oC - - - -- - See NOTE 8 for approved fuels GE PART NO. 9378M47 9278M96 1323M36 9368M57 9387M15 9275M73 CIT Sensor, Woodward 9178M37 - - - - 9334M96 - - Power Management Control, GE 7076M20 7084M61 7129M23 7090M98 7125M15 7157M60 7157M61 7157M64 7139M84 7139M91 7045M91 --- --- 7157M62 7157M63 7157M66 7157M67 * PAGE 1 2 3 4 5 6 7 8 REV. 13 12 12 12 11 12 12 11 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. I I TCDS E21EU PAGE 2 II. MODELS (See NOTE 12) CFM56-3C TYPE RATINGS (See NOTE 4) High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, multi-stage compressor with one stage turbine and annular combustor. Takeoff (5 min., see NOTE 16), sea level, static thrust, lb./daN Maximum continuous, sea level static thrust, lb. Flat rating Takeoff Maximum continuous FUEL SYSTEM Fuel Control, Woodward 23,515/10,460 21,850/9,719 AMBIENT TEMPERATURE 86oF / 30oC 77oF / 25oC See NOTE 8 for approved fuels GE PART NO. 1459M27 9387M15 CIT Sensor, Woodward 9334M96 Power Management Control, GE 7147M10 7157M68 I. MODELS (Continued) CFM56-2 CFM56-2B CFM56-2A CFM56-3 CFM56-3B FUEL SYSTEM (Cont.) Fuel Pump, TRW SAFRAN PART NUMBER 301-776-101-0 301-776-101-0 301-779-101-0 301-778-801-0 - - Combined boost and single 301-776-102-0 301-776-102-0 301-779-102-0 301-778-802-0 - - element gear type pump 301-776-103-0 301-776-104-0 301-779-103-0 301-778-804-0 - - 301-776-104-0 301-776-105-0 --- 301-778-805-0 - - 301-776-105-0 301-776-106-0 --- 301-778-806-0 - - 301-776-106-0 301-776-109-0 --- 301-779-001-0 - - 301-776-108-0 301-776-111-0 --- 301-779-002-0 - - 301-776-109-0 301-776-112-0 --- 301-779-005-0 - - 301-776-110-0 301-776-113-0 --- 301-779-006-0 - - 301-776-111-0 301-776-114-0 --- 301-779-007-0 - - 301-776-112-0 301-776-115-0 --- --- --- 301-776-113-0 301-779-001-0 --- --- --- 301-776-114-0 301-779-005-0 --- --- --- 301-776-115-0 301-779-007-0 --- --- --- 301-778-801-0 301-779-101-0 --- --- --- 301-778-802-0 301-779-102-0 --- --- --- 301-778-804-0 301-779-103-0 --- --- --- 301-778-805-0 --- --- --- --- 301-778-806-0 --- --- --- --- 301-779-001-0 --- --- --- --- 301-779-002-0 --- --- --- --- 301-779-005-0 --- --- --- --- 301-779-006-0 --- --- --- --- 301-779-007-0 --- --- --- --- Fuel/Oil Heat Exchanger 301-771-402-0 301-771-402-0 301-779-401-0 301-776-401-0 - - 301-771-403-0 301-779-401-0 301-779-402-0 301-776-402-0 - - 301-771-404-0 301-779-402-0 --- 301-776-403-0 - - 301-780-501-0 - - Servo Fuel Heater 301-772-901-0 301-772-901-0 301-779-501-0 301-776-501-0 - - 301-779-501-0 301-779-502-0 301-776-502-0 - - 301-779-502-0 --- --- --- I TCDS E21EU PAGE 3 I. MODELS (Continued) CFM56-2 CFM56-2B CFM56-2A CFM56-3 CFM56-3B OIL Models CFM56-2/-2B/-2A Models CFM56-3/-3B/-3C IGNITION SYSTEM Two ignition units Synthetic type conforming to GE Specification D50TF1, Type 1 or 2. CFM Service Bulletin (CFM56-2) 79-0001 lists approved oil brands. Synthetic type conforming to GE Specification D50TF1, Type 1 or 2. CFM Service Bulletin (CFM56-3/-3B/-3C) 79-0001 lists approved oil brands. GE PART NO. 9238M66 - - - - - - - - 1538M69 - - - - - - - - 9101M52 Two igniter plugs 1153M38 9275M71 - - - - - - 1374M12 - - - - - - - - 1153M38 9276M36 - - - - - - PRINCIPAL DIMENSIONS Length, (fan case forward flange to LPT rear frame aft flange) 1374M13 - - - - - - - - INCHES / MILLIMETERS 95.7/2430 - - - - 93.1/2364 - - Width, (fan casing forward flange diameter) 72.04/1830 - - - - 63.39/1610 - - Height, (bottom of accessory gearbox to top of fan casing forward flange) WEIGHT (dry) Pounds / Kilograms CENTER OF GRAVITY LOCATIONS Inches Millimeters 84.25/2140 - - - - 66.61/1692 - - Includes basic engine accessories and optional equipment as listed in manufacturers engine specification, including engine mounted portions of the condition monitoring instrumentation. 4711/2139 - - 4850/2200 4309/1954 4334/1966 STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) 206+1 - - 205+1 209+1 - - 5233+25 - - 5220+25 5319+25 - - II. MODELS (Continued) CFM56-3C FUEL SYSTEM (Cont.) Fuel Pump, TRW SAFRAN PART NUMBER 301-778-802-0 Combined boost and single 301-779-001-0 element gear type pump 301-779-002-0 Fuel/Oil Heat Exchanger 301-776-401-0 301-776-402-0 301-776-403-0 301-780-501-0 Servo Fuel Heater 301-776-501-0 OIL Models CFM56-2/-2B/-2A Models CFM56-3/-3B/-3C IGNITION SYSTEM Two ignition units 301-776-502-0 Synthetic type conforming to GE Specification D50TF1, Type 1 or 2. CFM Service Bulletin (CFM56-2) 79-0001 lists approved oil brands. Synthetic type conforming to GE Specification D50TF1, Type 1 or 2. CFM Service Bulletin (CFM56-3/-3B/-3C) 79-0001 lists approved oil brands. GE PART NO. 9238M66 1538M69 Two igniter plugs 9275M71 1374M12 9276M36 1374M13 I - - TCDS E21EU PAGE 4 II. MODELS (Continued) CFM56-3C PRINCIPAL DIMENSIONS Length, (fan case forward flange to LPT rear frame aft flange) INCHES / MILLIMETERS 93.1/2364 Width, (fan casing forward flange diameter) 63.39/1610 Height, (bottom of accessory gearbox to top of fan casing forward flange) WEIGHT (dry) Pounds / Kilograms CENTER OF GRAVITY LOCATIONS Inches Millimeters 66.61/1692 Includes basic engine accessories and optional equipment as listed in manufacturers engine specification, including engine mounted portions of the condition monitoring instrumentation. 4334/1966 STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) 209+1 5319+25 CERTIFICATION BASIS Code of Federal Regulations Part 33 effective February 1, 1965, with Amendments 33-1 through 33-6 thereto. In addition, the engines are in compliance with the emissions requirements of Special Federal Aviation Regulation No. 27-5. Exemption No. 2641 from compliance with 14 CFR §33.88 issued Nov. 20, 1978, Exemption No. 2850 from compliance with 14 CFR §33.7 issued October 31, 1979, and Exemption No. 83-ANE-001E from compliance with 14 CFR §33.14 issued July 27, 1983. APPLICATION TYPE CERTIFICATE TYPE CERT. MODEL DATE ISSUED/AMENDED WITHDRAWN CFM56-2 AUG 07, 1975 NOV 08, 1979 CFM56-2B JUL 28, 1981 JUN 25, 1982 CFM56-3 SEP 17, 1980 JAN 12, 1984 CFM56-3B MAR 05, 1984 JUN 19, 1984 CFM56-2A DEC 15, 1983 JUN 06, 1985 CFM56-3C APR 07, 1986 DEC 18, 1986 The Direction Generale de L'Aviation Civile (DGAC) originally type certificated these engine models under DGAC Certificate de Type Moteur M9. The FAA validated these products under US Type Certificate Number E21EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of these products on behalf of France. PRODUCTION BASIS 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 (now SAFRAN) 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 11). IMPORT REQUIREMENTS To be considered for installation on aircraft registered in the United States, each individually imported engine must be accompanied by EASA airworthiness approval certificate (EASA Form 1 – Authorized Release Certificate) or JAA Form 1 issued by SAFRAN 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 Number E21EU and to be in a condition for safe operation.’ See NOTE 11. For further information. I TCDS E21EU PAGE 5 NOTES MODELS CFM56-2 CFM56-2B CFM56-2A CFM56-3 CFM56-3B CFM56-3C NOTE 1. TURBINE EXHAUST GAS (T495) Takeoff (5 min., see NOTE 16) Takeoff Transient (20 sec.) Maximum continuous Starting Time temperature envelope Refer to model's S.O.I. OIL (See NOTE 15) Continuous operation Transient (15 minutes) NOTE 2. Fuel limits Oil limits Refer to model's S.O.I. NOTE 3. STARTER Rotation (1) Speed ratio to core Maximum torque (in-lbs) Continuous Static Maximum overhung moment (in-lbs) ELECTRICAL Rotation (1) Speed ratio to core Maximum torque (in-lbs) Continuous Static Maximum overhung moment (in-lbs) FORWARD HYDRAULIC PUMP Rotation (1) Speed ratio to core Maximum torque (in-lbs) Continuous Static Maximum overhung moment (in-lbs) AFT HYDRAULIC PUMP Rotation (1) Speed ratio to core Maximum torque (in-lbs) Continuous Static Maximum overhung moment (in-lbs) MAXIMUM PERMISSIBLE TEMPERATURES For engine configurations designated by a suffix for specific installation (see NOTE 12), refer to the appropriate S.O.I. for maximum operating temperatures. As measured by a harness of six or nine thermocouples located at the second stage low pressure turbine vanes. 905oC --- 870oC TP.O1.6 - - --- - - TP.01.7 930oC --- 895oC TP.01.10 - - 940oC - - TP.01.9 - - - - - - - - - - - - - - - - Refer to the appropriate installation manual and S.O.I. 140oC 155oC 160oC 175oC 140oC 155oC 160oC 165oC - - - - - - - - FUEL AND OIL PRESSURE LIMITS Refer to the appropriate installation manual TP.01.6 TP.01.7 TP.01.10 TP.01.9 - - - - ACCESSORY DRIVE PROVISIONS (see also next page) CW 1.343:1 4,150 10,444 300 CW 1.343:1 4,150 10,444 300 CW 1.343:1 4,900 9,700 340 CCW 0.996:1 5,400 13,370 300 - - - - - - - - - - - - - - - - - - - - CW 0.561:1 (125 kw) 10,900 2,100 CW 0.561:1 (125 kw) 10,900 2,100 CW 0.5823:1 165 hp 7,000 1,600 CW 0.562:1 2,500/135 kw 8,800 2,500 - - - - - - - - - - - - - - - - - - - - CCW 0.254:1 1,500 6,398 (2) 500 --- --- --- --- --- CW 0.255:1 1,000 4,400 400 CW 0.255:1 1,500 4,400 500 - - - - - - - - - - - - - - - - - - - - CW 0.254:1 1,000 6,398 (2) 400 CW 0.254:1 2,390 6,398 400 --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- --- (1) CW = CLOCKWISE / CCW = COUNTERCLOCKWISE (2) Total torque for forward and aft hydraulic pump drives must not exceed 6,398 in- pounds static. TCDS E21EU PAGE 6 NOTE 4. Engine ratings are based on calibrated stand performance under the following conditions: For the CFM56-2/-3/-3B/-3C, takeoff thrust is nominally independent of ambient temperature (flat rated) up to ambient temperature of Std + 15oC; for the CFM56-2B, Std +17.2oC; and for the CFM56-2A, Std +20oC; Maximum continuous is nominally independent of ambient temperature (flat rated) to Std +10oC; Zero customer bleed and horsepower extraction; No scrubbing drags; 100% inlet recovery; and Based on CFM International referee separate flow exhaust system. NOTE 5. Fan exhaust/reverser system models CFM56-FR02B and CFM56-FR03B are approved for incorporation on CFM56-2 and CFM56-2A engine models, respectively, in accordance with 14 CFR Part 33. NOTE 6. MODELS CFM56-2 CFM56 -2B CFM56- 2A CFM56-3 CFM56- 3B CFM56-3C MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS Low Pressure Rotor (N1), rpm High Pressure Rotor (N2), rpm 5,280 (102%) 15,183 (105%) - - - - - - - - 5,490 (106%) - - - - - - - - - - NOTE 7. Maximum permissible air bleed extraction: Refer to the appropriate Installation Manual. NOTE 8. Approved fuel conforming to GE Specification D50TF2. MIL-T-5624, Grades JP-4 or JP-5, ASTM D1655, Jet A, A1, and B are consistent with this GE specification. PRIMARY FUEL For the CFM56-2/-3/-3B/-3C, the primary fuel is Jet A. For the CFM56-2A/-2B, the primary fuel is JP4. AVIATION GASOLINE, MOTOR GASOLINE, EMERGENCY FUELS, AND FUEL ADDITIVES For the CFM56-2/-3/-3B/-3C use of aviation gasoline is not authorized. Consult appropriate Operating Manual for additive usage. For the CFM56-2B and -2A use of aviation gasoline and motor gasoline is authorized for periods not to exceed six hours. Consult appropriate Operating Manual for action following use of emergency fuels and for additive usage. For limitations on use of emergency fuels with the CFM56-2B and -2A, consult the appropriate Installation Manual. NOTE 9. Life limits established for critical rotating components are published in each model's Shop Manual. NOTE 10. 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. TCDS E21EU PAGE 7 NOTE 11. The type certificate holder, CFM International, S.A., is a company established and jointly owned by SAFRAN Aircraft Engines, formerly 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, SAFRAN and General Electricfunction as licensees of CFM International, S.A. This type certificate applies only to engines produced in France under DGAC Certificate de Type Moteur M9. Engines of the same model designation produced in the United States under Type Certificate No. E2GL 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. Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document ), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. For a list of the applicable engine serial numbers refer to the latest revisions of following Service Bulletins: CFM56-2A Service Bulletin 72-0649 "CFM56-2A Engine Serialization Manufacturing Sequence" or CFM56-2B Service Bulletin 72-0801 "CFM56-2B Engine Serialization Manufacturing Sequence" or CFM56-2C Service Bulletin 72-1040 "CFM56-2C Engine Serialization Manufacturing Sequence" or CFM56-3 Service Bulletin 72-1175 "CFM56-3 Engine Serialization Manufacturing Sequence" Effective September 28, 2004, engines produced by SAFRAN were produced under EASA Production Certificate FR.21G.0007. NOTE 12. A suffix may be added to the basic engine model number on the engine nameplate to identify minor variations in engine configuration, installation components or reduced ratings peculiar to aircraft installation requirements. For example: CFM56-2-xx. Engines that have a suffix added to the basic model number are identified in CFM International Service Bulletins, and are summarized below: Engine Model Service Bulletin No. Application CFM56-2-C1/-C5 72-0001 (CFM56-2) DC8-71/-72/-72F/-73 CFM56-2-C2 72-0001 (CFM56-2) None CFM56-2-C3/-C6 72-0001 (CFM56-2) DC8-72F CFM56-2A-2/-3 72-0001 (CFM56-2A) No Commercial Application CFM56-2B-1/-2 72-0001 (CFM56-2B) No Commercial Application CFM56-3-B1 72-0001(CFM56-3/-3B/-3C) 737-300/-500 CFM56-3B-2 72-0001 (CFM56-3/-3B/-3C) 737-300/-400 CFM56-3C-1 72-0001 (CFM56-3/-3B/-3C) 737-300/-400/-500 NOTE 13. For the CFM56-3/-3B/-3C models, the throat area of the inlet installed on the engine shall not exceed 2700 sq. in. (1.742 sq. meters) of area. TCDS E21EU PAGE 8 NOTE 14. For inflight operation during icing conditions: For the CFM56-2 series engines, the minimum permissible N1 RPM is 37 percent. However, momentary N1 excursions below 37 percent, not to exceed 60 seconds duration, are permissible for approach and landing operation below 10,000 feet pressure altitude. For CFM56-2 series engines which are equipped with 43 percent rich pilot fuel nozzles, in accordance with CFM56-2 Service Bulletin Number 73-0047, the minimum permissible N1 RPM for inflight operation is 29 percent. For CFM56-3/-3B/-3C engines, the minimum permissible N1 RPM for inflight operation during icing conditions is 21.8 percent. NOTE 15. The oil temperature for the CFM56-2B, CFM56-3, CFM56-3B, and CFM56-3C is measured at the scavenge pump discharge. The oil temperature for the CFM56 -2A and CFM56-2-C series engines is measured at the supply pump discharge. The transient limit is defined as 15 minutes for all models except for the CFM56-2B. The transient limit is defined as 10 minutes for the CFM56-2B. The continuous operation and transient oil temperature limits for the CFM56-2-C1, -2-C3, -2-C5, and -2-C6 is 140oC and 155oC respectively. The continuous operation and transient oil temperature limits for the CFM56-2-C2 is 150oC and 155oC respectively. Refer to S.O.I. TO.01.6. NOTE 16. The normal 5 minute takeoff rating may be extended to 10 minutes for engine out contingency for the CFM56-3/-3B/-3C. NOTE 17. 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. ----END----