TCDS E41NE

Page No 1 2 3 4 5 6 7 LEGEND: "- -" indicates "Same as Preceding Model" Rev No 11 11 6 11 11 11 11 "- - -" indicates Not applicable U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E41NE TCDS NUMBER E41NE REVISION: 11 GENERAL ELECTRIC COMPANY MODELS: CF6-80E1A1 CF6-80E1A4 CF6-80E1A4/B CF6-80E1A2 CF6-80E1A3 June 10, 2013 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E41NE) 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: GENERAL ELECTRIC COMPANY AIRCRAFT ENGINE GROUP 1 NEUMANN WAY CINCINNATI, OH 45215-6301 I. MODELS CF6-80E1A1 CF6-80E1A2 CF6-80E1A4 CF6-80E1A3 CF6-80E1A4/B TYPE Dual rotor, axial flow, annular combustor, high bypass turbofan. The 14-stage high pressure compressor is driven by a 2-stage high pressure turbine and the integrated fan and low pressure compressor are driven by a 5-stage low pressure turbine. RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb Takeoff (5 min) at sea level, static thrust, lb (See NOTE 18) Flat rating ambient temperature Takeoff Maximum continuous COMPONENTS (GE P/N) Hydromechanical Control Unit Electronic Control Unit (ECU) GE P/N (See NOTE 17) ECU Rating Plug, GE P/N Main Fuel Pump, GE P/N 58,020 63,290 86°F(30°C) 77°F(25°C) 1521M74 1799M99 1851M74 1851M80 1960M84 2043M29 1753M83P35 1752M18 60,400 64,530 - - - - - - - - - - - - - - - - 1753M83P44 - - - - 66,870 - - - - - - - - - - - - - - - - 1753M83P25 - - - - 68,530 - - - - - - - - - - - - - - - - 1753M83P60 - - - - 68,530 - - - - - - - - - - - - - - - - 1753M83P54 - - PRINCIPAL DIMENSIONS (in) Length (Fan spinner to outer LPT flange face) Width (maximum envelope) Height (maximum envelope) 168.41 114.13 113.13 - - - - - - - - - - - - - - - - - - - - - - - - WEIGHT (DRY) (lb) Includes all basic engine accessories, and optional equipment as listed in the manufacturer's engine specifications. 11,225 - - - - - - - - CENTER OF GRAVITY (in) (Engine only) Station Waterline Buttline 218.80±2.0 98.70±1.0 99.80±1.0 - - - - - - - - - - - - - - - - - - - - - - - - E41NE Page 2 of 7 FUEL See NOTE 7 OIL See NOTE 14 CERTIFICATION BASIS CF6-80E1A1/A2 CF6-80E1A4; A3; A4/B Title 14, Code of Federal Regulations (14 CFR) part 33, effective February 1, 1965, Amendments 33-1 through 33-12, inclusive. 14 CFR part 33, effective February 1, 1965, Amendments 33-1 through 33-12, inclusive and Section 33.28, Amendment 33-15. All CF6 engines approved under TYPE CERTIFICATE NO. E41NE comply with the fuel venting emissions and exhaust emissions requirements of Special FAR No. 27-5. The following models comply with 14 CFR part 34, amendment 5, effective December 31, 2012. See NOTE 21 for detailed summary of the certification basis for fuel venting and exhaust emissions: CF6-80E1A1, CF6-80E1A2, CF6-80E1A3, CF6-80E1A4 and CF6-80E1A4/B. TYPE CERTIFICATE E41NE MODELS APPLICATION DATE ISSUED/AMENDED CF6-80E1A1 September 7, 1989 May 25, 1993 CF6-80E1A2 September 7, 1989 May 25, 1993 CF6-80E1A4 May 18, 1994 July 18, 1997 CF6-80E1A3 July 26, 1999 June, 27, 2001 CF6-80E1A4/B November 20, 2003 April 29, 2004 PRODUCTION BASIS Production Certificate No. 108 for engines produced by the General Electric Company in the United States. In addition, CF6-80E1 series engines and parts thereof produced in Europe are eligible in accordance with the following: Societe National d'Etude et de Construction de Moteurs d'Aviation (SNECMA) • Production agreement No. 6.3592 between General Electric and SNECMA dated April19, 1983, for complete engines and modules. • Identification plates for CF6-80E1A1, CF6-80E1A2, CF6-80E1A3, CF6-80E1A4, and CF6-80E1A4/B engines manufactured by SNECMA shall contain the following information: 1. Manufacturer (SNECMA, France) 2. Model 3. Serial number (Numbers 811-XXX are assigned to engines manufactured by SNECMA) 4. Type Certificate Number E41NE 5. Import Type Certificate No. M-IM. Each individually imported engine must be accompanied by an airworthiness approval tag, JAA Form F1, issued by SNECMA on behalf of Direction Generale de l'Aviation Civile (DGAC) under production certificate number P03 or a "Certificate de Navigabilite pour Exportation" delivered by the DGAC. Note, effective September 28, 2004, any of these engine models and parts thereof would be produced under European Aviation Safety Agency (EASA) Production Certificate FR.21G.0007. To be considered for installation on aircraft registered in the United States, each individually imported engine or parts thereof produced under EASA Production Certificate FR.21G.0007 must be accompanied by an EASA airworthiness approval certificate (EASA Form 1 – Authorized Release Certificate) issued by SNECMA under authority of the EASA Production Certificate and attached to each item or invoice covering a shipment of similar items (Ref. 14 CFR 21.502). E41NE Page 3 of 7 NOTE 4. ACCESSORY DRIVE PROVISIONS CF6-80E1A1;A2;A4;A3;A4/B DRIVE PAD Rotation Facing Gearbox Pad Gear Ratio To Core Speed Horsepower Continuous Pad Rating Shear Torque Static Overhung Moment Starter CCW1 0.9564 8,4002 16,800 2 400 2 949.073 1898.1 3 45.2 3 IDG CCW 0.8026 215 hp 10,5942 2,000 2 (160.3 kw) 11973 226.0 3 Hydraulic Pump (Two) CCW 0.378 42 hp 5,0002 400 2 (31.3 kw) 565.03 45.2 3 IDG Overload Limits a. 135 KVA electr ical load (234.9 hp) 3750 lb-in. (424 N-m) for 5 minutes in the accessory gearbox life. b. 180KVA electrical load (313.2 hp) 5000 lb-in. (565 N-m) for 5 seconds in the accessory gearbox life. 1. Counterclockwise 2. Torque, lb-in 3. Torque, N-m NOTES NOTE 1. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS CF6-80E1 (all Models) Low pressure rotor (N1) 3,835 (115.5%) High pressure rotor (N2) 11,105 (113.0%) NOTE 2. MAXIMUM PERMISSIBLE TEMPERATURES Turbine exhaust gas temperature (T49) Indicated Takeoff (5 min.) 1787 °F (975°C) (See NOTE 10) Maximum Continuous 1724 °F (940°C) (See NOTE 10) Starting (max. transient for 40 sec.) 1598 °F (870°C) Starting (ground)(max. - no time limit) 1382 °F (750°C) Refer to CF6-80E1 Operating Instruction GEK 99382 for time temperature envelope. Oil (all models) Continuous operation 320 °F (160°C) Transient (15 minutes max) 347 °F (175°C) NOTE 3. FUEL AND OIL PRESSURE LIMITS FUEL PRESSURE LIMITS AT ENGINE PUMP INLET GROUND STARTING, AIR STARTING, AND OPERATION Extends from a minimum fuel pressure of greater than or equal to 5.0 psi (34.5 kPa, absolute) above the true vapor fuel pressure to a maximum of 68 psig (468 kPa gage) (relative to the atmosphere) with vapor/liquid ratio of zero at all conditions. OIL PRESSURE LIMITS LOW PRESSURE 10.0 psid (69 kPa) minimum 15.0 psid (103.4 kPa diff.) at 55% N2 35.0 psid (241.5 kPa diff.) at 110% N2 During negative-g operation only, it is permissible to operate below minimum oil pressure (10 psid indicated) for a maximum of 30 seconds. See CF6-80E1 Operating Instruction, GEK 99382, Section 6. E41NE Page 4 of 7 NOTE 5. Engine Ratings are defined under the following conditions: CF6-80E1 (all models) a. Fan inlet air at 59°F and 29.92 in HG abs., zero humidity. b. Ideal engine inlet (100% bellmouth recovery). c. No external bleed or accessory drive power for aircraft accessories. d. Turbine temperature and engine rotor speed limits not exceeded. Along with the following flight exhaust system definition: CF6-80E1A1;A2;A4;A3;A4/B ES-CF6-4GXX NOTE 6. MAXIMUM PERMISSIBLE AIR BLEED EXTRACTION BLEED LOCATION CF6-80E1 ALL MODELS (Percent) Stage 8, Compressor airflow, normal Stage 11 Compressor Discharge Steady State at Takeoff Rating Steady State at or below maximum continuous Acceleration above 80% N2 Steady State or Acceleration Operation at 80% N2 or below 7.2 1.5 5.0 10.0 7.0 10.0 NOTE 7. FUEL Eligible fuels must conform to GE Specification D50TF2. The latest revision of the specification will apply. NOTE 8. Engine Part Life Limits and Mandatory Inspections are published in the Airworthiness Limitations section of CF6-80E1 Engine Manual, GEK 99376. NOTE 9. Power setting, power checks and control of engi ne thrust output in all operations is to be based on GE charts referring to Fan Speed (N1). Speed sensors are included in the engine assembly for this purpose. NOTE 10. The indicated (cockpit) Takeoff and Ma ximum Continuous EGT Redline values for CF6-80E1 engine models correspond to actual (measured) gas path temperature based on correction (shunt) values established for each engine model. These corrections, shown in the table below, are made in the Electronic Control Unit (ECU) and controlled by the installed Rating Plug. The engine configuration input to the ECU is controlled by the installed Identification Plug. E41NE Page 5 of 7 MODELS CF6-80E1A1/A2 CF6-80E1A2 Post SB 72- 1861, 73-00422, and 73-00433 CF6-80E1A4 CF6-80E1A4 Post SB 73- 00422 and SB 73-00433 CF6-80E1A4 SB 73-00734 CF6-80E1A3 CF6-80E1A4/B Takeoff EGT Correction (Shunt) Values: 60°C 75 °C 70 °C 75 °C 85 °C 85 °C 85 °C EGT Redline Values Takeoff Indicated 1787°F (975°C) - - - - - - - - - - - - Actual 1895°F (1035°C) 1922°F (1050°C) 1913°F (1045°C) 1922°F (1050°C) 1940°F (1060°C) 1940°F (1060°C) 1940°F (1060°C) Max, Continuous Indicated 1724°F (940°C) - - - - - - - - - - - - Actual 1828°F (998°C) - - - - - - 1855°F (1013°C) 1855°F (1013°C) 1855°F (1013°C) 1. SB 72-0186 introduced the R88DT HPTR to the CF6-80E1A2 engine model. The R88DT HPTR configuration includes enhanced blades (Stage 1 HPT blades with TBC and Stage 2 HPT blades of DSR 142 material). 2. SB 73-0042 introduced ECU software E.1.L to the CF6-80E1A2 and CF6-80E1A4 engine models. 3. SB 73-0043 introduced Identification Plugs associated with ECU software version E.1.L to the CF6-80E1A2 and CF6-80E1A4 engine models. 4. SB 73-0073 identifies appropriate CF6-80E1A3 capable hardware and the Identification Plugs associated with ECU software version E.1.O for the CF6-80E1A4 engine model. NOTE 11. For inflight operation during ic ing conditions, the minimum idle permissible corresponds to N2 (core) = 6,555 rpm. NOTE 12. The engine manufacturer supplies the engine assembled EBU, the exhaust system, and engine attach fittings for the CF6-80E1A1, A2, A4, A3, and A4/B engines. The components, approved for installation on CF6-80E1 (all models) in accordance with 14 CFR part 33, are defined in the engine model lists for the CF6-80E1A1, A2, A4, A3, and A4/B. Major components included are: SYSTEM KIT NUMBER Exhaust ES-CF6-4GXX Pneumatic 277-1475 Starter 277-1650 Fuel supply 277-1450 Aft mount 683L241G01 (upper beam) 683L239G01 (lower beam) NOTE 13. Overhaul of CF6-80E1 (all models) engine components is not authorized until component manuals become available. In the interim, components utilizing new part tolerances may be provided by the manufacturer. NOTE 14. OIL: Oil synthetic type conforming to GE Specification D50FT1. GE Service Bulletin 79-0001 lists approved oils and applicable restrictions. NOTE 15. Deleted. E41NE Page 6 of 7 NOTE 16. Criteria pertaining to the dispatch and maint enance requirements for engine control systems are specified in Airworthiness Limitations Section of the Engine Manual GE Document No. GEK 99376, which define the various configurations and maximum operating intervals. NOTE 17. THESE MODELS INCORPORATE THE FOLLOWING GENERAL CHARACTERISTICS SERIES CF6-80E1 CF6-80E1A1 CF6-80E1A2 CF6-80E1A4 CF6-80E1A3 CF6-80E1A4/B CHARACTERISTICS Basic Model Same as CF6-80E1A1except higher takeoff thrust rating. Corresponding Rating Plug change. For CF6-80E1A2 engine with the R88DT HPTR (Post SB 72-0186), actual EGT redline is 1050°C (See Note 10). Corresponding Electronic Control Unit (ECU) software (Post SB 73-0042) and Identification Plug (Post SB 73-0043) changes. Same as CF6-80E1A1/A2 baseline except higher takeoff thrust rating and actual EGT redline increased 1045 o C (See Note 10). Includes forged mount. Corresponding Rating Plug and Identification Plug changes. For CF6-80E1A4 engines ECU Software Version E.1.L or later (Post SB 73-0042), actual EGT redline is increased to 1050 o C (See Note 10). Corresponding Identification Plug (Post SB 73-0043) changes. For CF6-80E1A4 engines with ECU Software Version E.1.O or later (Post SB 73-0091) and specific hardware identified in SB 73-0073, actual takeoff EGT redline is increased to 1060 o C (See Note 10). Includes the R88DT HPT, R80 Stage 1 low pressure turbine nozzle, and other minor engine changes. Corresponding Identification Plug (Post SB 73-0073) changes. Same as CF6-80E1A4 except higher takeoff thrust rating and actual EGT redline increased to 1060°C (See Note 10). Includes the R88DT HPT and new Stage 1 low pressure turbine nozzle. Corresponding ECU software version, Rating Plug, and Identification Plug changes per SB 72-0134. Same as CF6-80E1A3 with same takeoff thrust rating and actual EGT redline of 1060°C (See Note 10). Corresponding ECU software version, Rating Plug, and Identification Plug changes per SB 72-0134. NOTE 18. The normal 5 minute takeoff rating may be extended to 10 minutes for engine out contingency. NOTE 19. Engine Instructions for Continued Airworthiness (ICA’s) are not complete. Aircraft with the CF6-80E1A1 engine model installed are not eligible for an airworthiness certificate until the ICA’s are complete and accepted by the FAA Engine Certification Office. NOTE 20. Removed. E41NE Page 7 of 7 NOTE 21. 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: CF6-80E1A1, CF6-80E1A2, CF6-80E1A3, CF6-80E1A4 and CF6-80E1A4/B. Fuel Venting Emission Standards: 14 CFR 34.10(a) and 34.11; in addition, 40 CFR 87.10(a) and 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); in addition, 40 CFR 87.23(c)(2). 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, Section 2.3.2.d.3 for NOx (also known as CAEP/6), and Part II Chapter 2 for fuel venting have also been demonstrated. …..END….. ANE-140:Kasra Sharifi:K,S:781-238-777 G:\Usr\ANE-100\ANE140\GE_CMT\CF6 General\_CF6 Cross-Product Projects\Certification\TCDS\E41NE (CF6- 80E1) 8110.1a(1)