TCDS E29NE

* PAGE 1 2 3 4 5 6 7 REV. 7 7 7 7 3 7 7 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTICE: ALL SIGNIFICANT CHANGES, IF ANY, ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E29NE TCDS NUMBER E29NE REVISION: 7* DATE: May 17, 2013 CFM INTERNATIONAL, S.A. MODELS: CFM56-5 CFM56-5-A1/F CFM56-5A3 CFM56-5A4 CFM56-5A4/F CFM56-5A5 CFM56-5A5/F Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E29NE) 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 CFM56-5 CFM56-5-A1/F CFM56-5A3 TYPE High bypass turbofan; coaxia l front fan/booster driven by multi-stage low pressure turbine, multi-stage compressor with one-stage high pressure turbine and annular combustor. RATINGS (See NOTE 4) Takeoff (5 min., see NOTE 17), sea level, static thrust, lb. Maximum continuous, sea level static thrust, lb. 25,000/ (11,120 daN) 23,700/ (10,540 daN) - - - - 26,500/ (11,787 daN) - - Flat rating AMBIENT TEMPERATURE Takeoff Maximum continuous 86øF / 30øC 77øF / 25øC - - - - - - - - TCDS E29NE PAGE 2 I. MODELS (Continued) CFM56-5 CFM56-5-A1/F CFM56-5A3 FUEL SYSTEMS See NOTE 8 for approved fuels Fuel pump / SNECMA P/N (Combined boost and single element gear-type pump) Hydromechanical unit GE Part Numbers 301-785-501-0 301-785-502-0 1348M79 - - - - - - - - - - - - ELECTRONIC ENGINE CONTROL Electronic control unit GE Part Numbers Identification plugs SNECMA Part Numbers 1459M55 1519M83 1820M27 320-586-001-0 320-586-201-0 320-586-301-0 - - - - - - 320-586-021-0 320-586-221-0 - - - - - - 320-586-031-0 320-586-231-0 OIL Synthetic type conforming to GE Specification D50TF1, Type 1 and Type 2. CFM Service Bulletin / CFM56-5 79- 001 lists approved oil brands. IGNITION SYSTEM GE PART NUMBER Two ignition units Unison and Simmons Two igniter plugs Unison and Champion 1538M69 9238M66 1374M12 1374M13 --- - - - - - - --- - - - - - - PRINCIPAL DIMENSIONS INCHES / MILLIMETERS Length, (fan case forward flange to LPT rear frame aft flange) Width, (fan casing forward flange diameter) Height, (bottom of accessory gearbox to top of fan casing forward flange) 95.3/2422 75.12/1908 82.73/2101 - - - - - - - - - - - - WEIGHT (Dry) Includes basic engine accessories and optional equipment as listed in manufacturers engine specification, including engine mounted portions of the condition monitoring instrumentation) Pounds / Kilograms 5139/2331 - - - - CENTER OF GRAVITY LOCATIONS STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) Inches Millimeters 206.9+1 5255+25 - - TCDS E29NE PAGE 3 II. MODELS CFM56-5A4 CFM56-5A4/F CFM56-5A5 CFM56-5A5/F TYPE High bypass turbofan; coaxial front fan/booster driven by multi-stage low pressure turbine, multi-stage compressor with one-stage high pressure turbine and annular combustor. RATINGS (See NOTE 4) Takeoff (5 min., see NOTE 17), sea level, static thrust, lb. Maximum continuous, sea level static thrust, lb. 22,000/ (9786 daN) 20,670/ (9195 daN) - - - - 23,500/ (10,453 daN) - - - - - - Flat rating AMBIENT TEMPERATURE Takeoff Maximum continuous 113øF / 45øC 77øF / 25øC - - - - 98.6øF / 37øC - - - - - - FUEL SYSTEMS See NOTE 8 for approved fuels Fuel pump / SNECMA P/N (Combined boost and single element gear-type pump) Hydromechanical unit GE Part Numbers 301-785-501-0 301-785-502-0 1348M79 - - - - - - - - - - - - - - - - - - ELECTRONIC ENGINE CONTROL Electronic control unit GE Part Numbers Identification plugs SNECMA Part Numbers 1519M83 1820M27 336-414-201-0 336-414-205-0 - - - - 336-414-210-0 336-414-215-0 - - - - 336-414-220-0 336-414-225-0 - - - - 336-414-230-0 336-414-235-0 OIL Synthetic type conforming to GE Specification D50TF1, Type 1 and Type 2. CFM Service Bulletin / CFM56-5 79-001 lists approved oil brands. IGNITION SYSTEM GE PART NUMBER Two ignition units Unison and Simmons Two igniter plugs Unison and Champion 1538M69 9238M66 1374M12 1374M13 --- - - - - - - --- - - - - - - --- - - - - - - PRINCIPAL DIMENSIONS INCHES / MILLIMETERS Length, (fan case forward flange to LPT rear frame aft flange) Width, (fan casing forward flange diameter) Height, (bottom of accessory gearbox to top of fan casing forward flange) 95.3/2422 75.12/1908 82.73/2101 - - - - - - - - - - - - - - - - - - WEIGHT (Dry) Includes basic engine accessori es and optional equipment as listed in manufacturers engine specification, including engine mounted portions of the condition monitoring instrumentation) Pounds / Kilograms 5139/2331 - - - - - - CENTER OF GRAVITY LOCATIONS STATION, ENGINE ONLY (REFER TO INSTALLATION DRAWING) Inches Millimeters 206.9+1 5255+25 - - - - - - - - - - - - TCDS E29NE PAGE 4 CERTIFICATION BASIS Federal Aviation Regulations Part 33 effective February 1, 1965, with Amendments 33-1 through 33-10 thereto. In addition, the engines are in compliance with the emissions requirements of Special Federal Aviation Regulation No. 27-5. APPLICATION TYPE CERTIFICATE TYPE CERTIFICATE MODEL DATE ISSUED/AMENDED WITHDRAWN CFM56-5 09/06/84 08/27/87 CFM56-5A2 12/15/88 02/ 05/90 10/15/92 (*) CFM56-5A3 12/15/88 02/05/90 CFM56-5-A1/F 12/15/88 10/15/92 CFM56-5A4 02/03/94 02/27/96 CFM56-5A4/F 02/03/94 02/27/96 CFM56-5A5 02/03/94 02/27/96 CFM56-5A5/F 02/03/94 02/27/96 (*) Effective October 15, 1992, the model designation (CFM56-5A2" was changed to "CFM56-5-A1/F", at the r equest of the manufacturer. No CFM56-5A2 models were released to revenue service. PRODUCTION BASIS The original production basis was "Agreement de Production" Numbers F.G.007 or P03 issued by the 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 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 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 No. E29NE and is in a condition for safe operation. See Note 11. ’ NOTES NOTE 1. MAXIMUM PERMISSIBL E TEMPERATURES (All Models) For engine configurations designated by a suffix for specific installations (see NOTE 12), refer to the appropriate S.O.I. for maximum operating temperatures TURBINE EXHAUST GAS (T495) (INDICATED / SEE NOTE 5) As measured by a harness of nine thermocouples located at the second stage low pressure turbine vane: Takeoff (5 min.) Maximum continuous Starting Time temperature envelope Refer to model's S.O.I. 890øC 855øC 725øC TP.01.11 FUEL PUMP INLET REFER TO THE APPROPRIATE INSTALLATION MANUAL OIL SUPPLY Continuous operation Transient (15 minutes) 140øC/284øF 155øC/311øF NOTE 2. FUEL AND OIL PRESSURE LIMITS TCDS E29NE PAGE 5 Fuel limits Oil limits Operation and air/ground starting pressure limits extend from a minimum fuel pressure of not less than 5.5 psia (37.9 kPa absolute) above the true fuel vapor pressure to a maximum of 60 psig (413.7 kPa gauge), relative to atmosphere, with vapor/liquid ratio of zero at all conditions. For limits, see Installation Manual, Part A, Section 5, Figures A2 through A5. The minimum pressure limit at idle is 13 psid (89.6 kPa differential) and varies up to 45 psid (310.2 kPa differential) at cruise thrust. The maximum pressure limit during cold starts is 300 psid (2069 kPa differential), limited by a pressure-relief valve. See NOTE 14. NOTE 3. ACCESSORY DRIVE PROVISIONS (All Models) ELECTRICAL Rotation (1) Speed ratio to core Maximum torque (inch-pounds) Continuous Static Maximum overhung moment (inch-pounds) CCW .5947:1 135 KW 9,492 1,000 HYDRAULIC PUMP Rotation (1) Speed ratio to core Maximum torque (inch-pounds) Continuous Static Maximum overhung moment (inch-pounds) CCW .256:1 1,500 4,400 160 1. FACING DRIVE PAD: CW = CLOCKWISE / CCW = COUNTERCLOCKWISE NOTE 4. 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: - Std + 15 oC (30oC, 86oF) for -5, -5A3, & -5-A1/F - Std + 30 oC (45oC, 113oF) for -5A4 & -5A4/F - Std + 22 oC (37oC, 98.6oF) for -5A5 & -5A5/F Maximum continuous is nominally independent of ambient temperature (flat rated) to Std +10øC (25øC, 77øF); Zero customer bleed and horsepower extraction; No scrubbing drags; 100% inlet recovery; and Based on CFM International referee separate flow exhaust system with primary exhaust nozzle (core) P/N 15-25200-2014 and fan nozzle P/N 4013356-302. NOTE 5. CFM56-5, -5A4, -5A5 Indi cated 890øC EGT redline corresponds to actual of 890øC. CFM56-5A3, -5-A1/F, Indicated 890øC EGT redline corresponds to -5A4/F, -5A5/F actual of 915øC, and indicated 855øC EGT redline corresponds to actual of 880øC. NOTE 6. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS (All Models) Low pressure rotor (N1), rpm High pressure rotor (N2), rpm 5,100 (102%) 15,183 (105%) TCDS E29NE PAGE 6 NOTE 7. MAXIMUM PERMISSIBLE AIR BLEED EXTRACTION (All Models) LOCATION FAN CORRECTED SPEED FLOW LIMIT Fan discharge HPC Stage 5 only Compressor discharge only HPC Stage 5 and compressor discharge combined 20% - 100% N1K 20% - 100% N1K 20% - 61.0% N1K 61% - 82.5% N1K 82.5% - 100% N1K 20% - 61.0% N1K 61% - 82.5% N1K 82.5% - 100% N1K 2% fan airflow 10% core airflow 14% core airflow Linear variation from 14%-7% core airflow 7% core airflow 14% core airflow Linear variation from 14%-10% core airflow 10% core airflow NOTE 8. 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 for additive usage. NOTE 9. Life limits established for crit ical rotating components are published in the CFM56-5 Shop Manual, Chapter 5. NOTE 10. Power setting, power checks and control of engine thrust output in all operations is to be based on CFMI engine charts referring to fan speed. Fan speed sensors are included in the engine assembly for this purpose. NOTE 11. The type certificate holder, CF M 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 certification applies only to engines produced in France under EASA Certificate E.067.. Engines of the same model designation produced in the United States under Type Certificate No. E28NE 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 Certification No. 108 are eligible for use in engines produced under this type certificate. These engines, when produced by General Electric, are identified by the serial number prefix "730 and 732"; when produced by SNECMA, they are identified by the prefix "731 and 733". 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: CFM56-5xx. Engines that have a suffix to the basic model number are identified in CFM International Service Bulletin No. CFM56-5 72-001, and are summarized below: (1) CFM56-5-A1, basic model for Airbus A320 NOTE 13. The minimum permissible idle in flight corresponds to N2=58.8% (8,500 rpm), which is a non-adjustable limit, preset into the ECU control schedule. TCDS E29NE PAGE 7 NOTE 14. 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 , Section 6. NOTE 15. The models shown on this TCDS have the following general characteristics: MODEL CHARACTERISTICS CFM56-5 Basic model. CFM56-5-A1/F Same as CFM56- 5 except EGT limits increased through introduction of hot section modifications. This model was originally certified as CFM56-5A2, but that designation was changed at the request of the manufacturer. CFM56-5A3 Same as CFM56-5-A1/F except for increased takeoff thrust rating. CFM56-5A4 Same as CFM56-5A3 except for reduced thrust takeoff rating and lower EGT limits. CFM56-5A4/F Same as CFM56-5A3 except for reduced thrust takeoff rating CFM56-5A5 Same as CFM56-5A3 except for reduced thrust takeoff rating and lower EGT limits. CFM56-5A5/F Same as CFM56-5A3 except for reduced thrust takeoff rating. NOTE 16. The CFM56-5, -5-A1/F, -5A3, -5 A4, -5A4/F, -5A5, -5A5/F FADEC series engines have been approved to operate with certain faults present in the control system, based on satisfaction of 14 CFR Part 33 requirements and appropriate engine control system reliability requirements. FAA approved criteria pertaining to dispatch and maintenance requirements for the engine control system are specified in GE Document No. GEK 98455, which defines the dispatchable configurations and maximum operating intervals. A control system reliability monitoring program has been established with CFMI, 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. NOTE 17. The normal 5 minute takeoff rating may be extended to 10 minutes for engine out contingency. ----END----