TCDS E13NE

PAGE 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 REV 27 25 25 25 25 25 26 27 23 25 25 24 24 25 25 25 25 25 25 27 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E13NE TCDS NUMBER E13NE REVISION: Revision 27 Date: August 6, 2024 GENERAL ELECTRIC COMPANY MODELS: CF6-80A CF6-80C2B1 CF6-80C2B1F1 CF6-80A1 CF6-80C2B2 CF6-80C2D1F CF6-80A2 CF6-80C2B4 CF6-80C2A5F CF6-80A3 CF6-80C2B6 CF6-80C2B7F CF6-80C2A1 CF6-80C2B1F CF6-80C2B1F2 CF6-80C2A2 CF6-80C2B2F CF6-80C2B6FA CF6-80C2A3 CF6-80C2B3F CF6-80C2B5F CF6-80C2A5 CF6-80C2B4F CF6-80C2B8F CF6-80C2A8 CF6-80C2B6F CF6-80C2L1F CF6-80C2K1F Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E13NE) 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 GE AEROSPACE 1 NEUMANN WAY CINCINNATI, OH 45215-6301 I. MODELS CF6-80A CF6-80A1 CF6-80A2 CF6-80A3 TYPE Dual rotor, axial flow, high bypass turbofan. The 14-stage high pressure compressor is driven by a 2-stage high pressure turbine and the integrated front fan and low pressure compressor are driven by a 4-stage low pressure turbine. RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb 43,660 43,610 45,720 45,800 Takeoff (5 min.) at sea level, static thrust, lb (See NOTE 23) 46,930 46,990 48,670 48,970 Flat rating ambient temperature Takeoff 92oF/33.3oC - - - - - - Maximum continuous 77oF/25.0oC - - - - - - MAIN ENGINE CONTROL, WOODWARD GE P/N 9238M79 9363M11 9238M79 9363M11 POWER MANAGEMENT CONTROL GE P/N 7076M98 7084M12 7076M98 7084M12 1305M68 --- 1305M69 1305M70 PAGE 21 REV 27 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. TCDS E13NE 2 I. MODELS (Continued) CF6-80A CF6-80A1 CF6-80A2 CF6-80A3 EGT SHUNT JUNCTION BOX (See NOTE 15) GE P/N FUEL PUMP GE P/N IGNITION SYSTEM Two ignition units GE P/N Or GE P/N Two ignitor plugs GE P/N Or GE P/N PRINCIPAL DIMENSIONS Length (in) (fan spinner to LPT aft flange face) Width (in) (maximum envelope) Height (in) (maximum envelope) WEIGHT (DRY) (lb) 9230M48P02 9304M23 9101M52 9238M66 9101M37 1305M52 166.9 97.9 95.1 8,776 - - 9039M45 - - - - - - - - - - 94.5 105.6 8,760 - - 9304M23 - - - - - - - - - - 97.9 95.1 8,776 - - 9039M45 - - - - - - - - - - 94.5 105.6 8,760 NOTE: Weight includes basic engine accessories & optional equipment as listed in the manufacturer's engine specifications, including condition monitoring instrumentation sensors. CENTER OF GRAVITY LOCATIONS Station (in) (engine only) Waterline (in) (engine only) Buttline (in) (engine only) 222.8+2.0 98.2+1.0 99.8+0.5 219.4+2.0 95.8+1.0 98.7+0.5 222.8+2.0 98.2+1.0 99.8+0.5 219.4+2.0 95.8+1.0 98.7+0.5 II. MODELS CF6-80C2A1 CF6-80C2A2 CF6-80C2B1 CF6-80C2B4 TYPE Dual rotor, axial flow high bypass turbofan. The 14-stage compressor is driven by a 2-stage high pressure turbine and the integrated front 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 53,390 48,080 49,550 52,370 Takeoff (5 min.) at sea level, static thrust, lb (See NOTE 23) 57,860 52,460 55,980 57,180 Flat rating ambient temperature Takeoff 86oF/30oC 111oF/44oC 86oF/30oC 90oF/32.2oC Maximum continuous 77oF/25.0oC - - - - - - MAIN ENGINE CONTROL, WOODWARD GE P/N 1332M18 - - --- --- 1332M19 - - - - - - 1459M60 - - --- --- 1459M77 - - --- --- POWER MANAGEMENT CONTROL GE P/N 1339M18 1339M19 1339M21 1339M20 TCDS E13NE 3 II. MODELS (Continued) CF6-80C2A1 CF6-80C2A2 CF6-80C2B1 CF6-80C2B4 EGT SHUNT JUNCTION BOX (See NOTE 15) GE P/N FUEL PUMP GE P/N IGNITION SYSTEM Two ignition units GE P/N Or GE P/N Two ignitor plugs GE P/N Or GE P/N PRINCIPAL DIMENSIONS Length (in) (fan spinner to LPT aft flange face) Width (in) (maximum envelope) Height (in) (maximum envelope) WEIGHT (DRY) (lb) 1325M15P05 1325M15P07 1383M97P03 1383M97P07 9355M33 9238M66 --- 9392M95 9387M23 168.26 105.10 105.97 9,480 - - - - - - - - - - - - --- - - - - - - - - - - - - - - - - - - - - - - - - --- --- - - - - - - - - 9,670 --- - - - - - - - - - - --- --- - - - - - - - - - - NOTE: Weight includes basic engine accessories & optional equipment as listed in the manufacturer's engine specifications, including condition monitoring instrumentation sensors. CENTER OF GRAVITY LOCATIONS Station (in) (engine only) Waterline (in) (engine only) Buttline (in) (engine only) 223.93+2.0 98.90+0.5 100.00+0.5 - - - - - - - - - - - - 223.86+2.0 98.86+0.5 99.97+0.5 III. MODELS CF6-80C2A3 CF6-80C2B2 CF6-80C2B6 CF6-80C2A5 CF6-80C2A8 TYPE Dual rotor, axial flow high bypass turbofan. The 14-stage compressor is driven by a 2- stage high pressure turbine and the integrated front 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 54,790 49,020 56,100 56,210 48,080 Takeoff (5 min.) at sea level, static thrust, lb (See NOTE 23) 58,950 51,950 60,070 60,100 57,860 Flat rating ambient temperature Takeoff 86oF/30oC 90oF/32.2oC 86oF/30oC - - 95oF/35oC Maximum continuous 77oF/25oC 86oF/30oC 77oF/25oC - - - - MAIN ENGINE CONTROL, WOODWARD 1459M60 1453M12 1538M66 1459M60 - - GE P/N 1459M77 POWER MANAGEMENT CONTROL GE P/N 1374M93 1374M94 1457M16 1459M13 1672M13 TCDS E13NE 4 III. MODELS (Continued) CF6-80C2A3 CF6-80C2B2 CF6-80C2B6 CF6-80C2A5 CF6-80C2A8 EGT SHUNT JUNCTION BOX (See NOTES 1 & 19) GE P/N FUEL PUMP GE P/N 1325M15P07 1383M97P03 1383M97P07 9355M33 - - - - - - - - --- - - - - - - --- - - - - - - --- - - - - - - IGNITION SYSTEM Two ignition units / GE P/N Two ignitor plugs / GE P/N PRINCIPAL DIMENSIONS Length (in) (fan spinner to LPT aft flange face) Width (in) (maximum envelope) Height (in) (maximum envelope) WEIGHT (DRY) (lb) 9238M66 9387M23 168.26 105.10 105.97 9,480 - - - - - - - - - - 9,670 - - - - - - - - - - - - - - - - - - - - - - 9,480 - - - - - - - - - - - - NOTE: Weight includes basic engine accessories & optional equipment as listed in the manufacturer's engine specifications, including condition monitoring instrumentation sensors. CENTER OF GRAVITY LOCATIONS Station (in) (engine only) Waterline (in) (engine only) Buttline (in) (engine only) 223.86+2.0 98.86+0.5 99.97+0.5 - - - - - - - - - - - - - - - - - - - - - - - - IV. MODELS CF6-80C2B1F CF6-80C2B2F CF6-80C2B4F CF6-80C2B6F CF6-80C2D1F TYPE Dual rotor, axial flow high bypass turbofan. The 14-stage compressor is driven by a 2-stage high pressure turbine and the integrated front 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 23) Flat rating ambient temperature Takeoff Maximum continuous HYDROMECHANICAL UNIT GE P/N ELECTRONIC CONTROL UNIT, GE P/N 49,810 57,160 90oF/32.2oC 77oF/25oC 1383M68 1471M63 1519M89 1820M33 2121M25 2121M26 49,140 52,010 - - 86oF/30oC - - - - - - - - - - - - 52,470 57,280 - - 77oF/25oC - - - - - - - - - - - - 56,170 60,030 86oF/30oC - - - - - - - - - - - - - - 56,730 60,690 - - - - 1471M24 1519M91 1820M34 --- --- --- TCDS E13NE 5 IV. MODELS (CONTINUED) CF6-80C2B1F CF6-80C2B2F CF6-80C2B4F CF6-80C2B6F CF6-80C2D1F ELECTRONIC CONTROL UNIT, (cont.) GE P/N IDENTIFICATION PLUG (See NOTE 21) GE P/N EGT SHUNT JUNCTION BOX (See NOTES 15, 19, & 20) GE P/N FUEL PUMP GE P/N 2121M29 2121M37 2121M38 2121M41 1851M56 7161M98 7157M87 1325M15P07 1383M97P03 1383M97P07 1519M97P01 9355M33 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - --- - - - - --- --- --- --- - - - - - - --- --- --- - - - - IGNITION SYSTEM Two ignition units, GE P/N Two ignitor plugs, GE P/N RATING PLUG GE P/N PRINCIPAL DIMENSIONS Length (in) (fan spinner to LPT aft flange face) Width (in) (maximum envelope) Height (in) (maximum envelope) WEIGHT (DRY) (lb) 9238M66 9387M23 7156M94G01 168.26 111.42 105.97 9,790 - - - - 7156M94G02 - - - - - - - - - - - - 7156M94G03 - - - - - - - - - - - - 7156M94G04 - - - - - - - - - - - - 7156M94G01 - - - - - - 9,850 NOTE: Weight includes basic engine accessories & optional equipment as listed in the manufacturer's engine specifications, including condition monitoring instrumentation sensors. CENTER OF GRAVITY LOCATIONS Station (in) (engine only) Waterline (in) (engine only) Buttline (in) (engine only) 223.86+2.0 98.86+0.5 99.97+0.5 - - - - - - - - - - - - - - - - - - - - - - - - TCDS E13NE 6 V. MODELS CF6-80C2B1F1 CF6-80C2B3F CF6-80C2A5F CF6-80C2B7F (See NOTE 24) CF6-80C2B1F2 TYPE RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb Takeoff (5 min.) at sea level, static thrust, lb (See NOTE 23) Flat rating ambient temperature Takeoff Maximum continuous HYDROMECHANICAL UNIT GE P/N ELECTRONIC CONTROL UNIT, GE P/N Dual rotor, axial flow high bypass turbofan. The 14-stage compressor is driven by a 2-stage high pressure turbine and the integrated front fan and low pressure compressor are driven by a 5-stage low pressure turbine. 49,810 60,030 86oF/30oC 77oF/25oC 1383M68 1820M33 39,850 52,010 90oF/32.2oC - - - - 1471M63 1519M89 1820M33 56,210 60,100 86oF/30oC - - - - 1820M99 1797M63 --- 56,170 60,030 - - - - - - 1471M63 1519M89 1820M33 2121M25 2121M26 2121M29 2121M37 2121M38 2121M41 49,810 - - - - - - - - - - - - - - --- --- --- --- --- --- IDENTIFICATION PLUG (See NOTE 21) GE P/N EGT SHUNT JUNCTION BOX (See NOTES 15, 19, & 20) GE P/N FUEL PUMP GE P/N 1851M56 7161M98 1383M97P03 1383M97P07 1519M97P01 9355M33 - - - - - - - - - - - - - - - - --- --- - - - - - - - - 1383M97P03 1383M97P07 - - - - - - - - - - - - - - - - IGNITION SYSTEM Two ignition units, GE P/N Two ignitor plugs, GE P/N RATING PLUG GE P/N PRINCIPAL DIMENSIONS Length (in) (fan spinner to LPT aft flange face) Width (in) (maximum envelope) Height (in) (maximum envelope) WEIGHT (DRY) (lb) 9238M66 9387M23 7156M94G05 168.26 111.42 105.97 9,790 - - - - 7156M94G06 - - - - - - 9,499 - - - - 7156M94G01 - - - - - - 9,860 - - - - 7156M94G07 - - - - - - 9,790 - - - - 7156M94G08 - - - - - - 9,499 NOTE: Weight includes basic engine accessories & optional equipment as listed in the manufacturer's engine specifications, including condition monitoring instrumentation sensors. CENTER OF GRAVITY LOCATIONS Station (in) (engine only) Waterline (in) (engine only) Buttline (in) (engine only) 223.86+2.0 98.86+0.5 99.97+0.5 - - - - - - - - - - - - - - - - - - - - - - - - TCDS E13NE 7 VI. MODELS CF6-80C2B6FA CF6-80C2B5F CF6-80C2B8F CF6-80C2L1F CF6-80C2K1F TYPE Dual rotor, axial flow high bypass turbofan. The 14-stage compressor is driven by a 2-stage high pressure turbine and the integrated front fan and low pressure compressor are driven by a 5-stage low pressure turbine. RATINGS (See NOTE 5) 44,100 51,250 95oF/35oC 95oF/35oC 2042M93 --- --- --- --- --- --- --- --- --- 43,400 59,740 86oF/30oC 77oF/25oC - - --- --- --- --- --- --- --- --- --- Maximum continuous at sea level, static thrust, lb 56,170 49,810 56,170 Takeoff (5 min.) at sea level, static thrust, lb (See NOTE 23) 60,030 60,030 60,030 Flat rating ambient temperature Takeoff Maximum continuous 86oF/30oC 77oF/25oC - - - - - - - - HYDROMECHANICAL UNIT GE P/N 1383M68 - - - - ELECTRONIC CONTROL UNIT, GE P/N's 1820M33 2121M29 2121M41 1471M63 1519M89 1820M33 2121M25 - - - - - - - - 2121M26 - - 2121M29 - - 2121M37 - - 2121M38 - - 2121M41 - - ELECTRONIC ENGINE CONTROL (EEC) GE P/N Hardware (H/W) Software (S/W) IDENTIFICATION PLUG (See NOTE 21) GE P/N EGT SHUNT JUNCTION BOX (See NOTES 15, 19, & 20) GE P/N FUEL PUMP GE P/N IGNITION SYSTEM Two ignition units, GE P/N Two ignitor plugs, GE P/N RATING PLUG, GE P/N PRINCIPAL DIMENSIONS Length (in) (fan spinner to LPT aft flange face) Width (in) (maximum envelope) Height (in) (maximum envelope) WEIGHT (DRY) (lb) --- --- 1851M56 7161M98 1519M97P01 9355M33 9238M66 9387M23 7156M94G10 168.26 111.42 105.97 9,768 --- --- - - - - - - - - - - - - 7156M94G09 - - - - - - 9,790 --- --- - - - - - - - - - - - - 7156M94G12 - - - - - - 9,790 2042M67 2044M12 1754M25 --- --- - - - - - - 1753M83P35 - - - - - - 9,843 - - 2123M53 - - --- --- - - - - - - - - - - - - - - - - NOTE: Weight includes basic engine accessories & optional equipment as listed in the manufacturer's engine specifications, including condition monitoring instrumentation sensors. CENTER OF GRAVITY LOCATIONS Station (in) (engine only) Waterline (in) (engine only) Buttline (in) (engine only) 223.86+2. 0 98.86+1.0 99.97+1.0 - - - - - - - - - - - - 223.9+2 .0 98.9+1.0 100.0+1.0 - - - - - - TCDS E13NE 8 CERTIFICATION BASIS CF6-80A SERIES Title 14, Code of Federal Regulations (14 CFR) part 33, effective February 1, 1965, Amendments 33-1 through- 33-8 inclusive as revised by Grant of Exemption No. 3372 from Paragraphs 33.7(c)(17), 33.14, 33.23, 33.27, and 33.88 of Amendment 8. TYPE CERTIFICATE E13NE MODELS APPLICATION DATE ISSUED/AMENDED CF6-80A DEC 01, 1978 OCT 06, 1981 CF6-80A1 JUL 29, 1980 OCT 06, 1981 CF6-80A2 JUN 16, 1981 OCT 06, 1981 CF6-80A3 JUN 16, 1981 OCT 06, 1981 CF6-80C2 SERIES 14 CFR part 33 effective February 1, 1965, Amendments 33-1 through 33-8 inclusive except for (Except CF6-80C2L1F the approved substitute compliance procedures, which are in accordance with Amendment 10. and CF6-80C2K1F) The specific requirements of Amendment 10 met are those defined in Paragraphs 33.7, 33.14, 33.23, 33.27, 33.88, and 33.92. All CF6 engines approved under Type Certificate No. E13NE 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: CF6-80C2A5F, CF6-80C2A8, CF6-80C2B2, CF6-80C2B2F, CF6-80C2B4, CF6-80C2B4F, CF6-80C2B6, CF6-80C2B6FA, CF6-80C2D1F, CF6- 80C2B8F. The following models comply with 14 CFR part 34, amendment 7A, effective May 24, 2024: CF6- 80C2B1F, CF6-80C2B5F, CF6-80C2B6F, CF6-80C2B7F. See NOTE 29 for detailed summary of the certification basis for fuel venting and exhaust emissions. CF6-80C2L1F (only) 14 CFR part 33, effective February 1, 1965, Amendments 33-1 through 33-8 inclusive. Amendment 10 sections 33.7, 33.14, 33.23, 33.27, 33.88 and 33.92, Amendment 15 section 33.28 and Equivalent Level of Safety finding, 8040-ELOS-04-NE-02 for §33.89(a)(3)(ii) and (iii). CF6-80C2L1F model complies with 14 CFR part 34, amendment 5, effective December 31, 2012. See NOTE 29 for detailed summary of the certification basis for fuel venting and exhaust emissions. CF6-80C2K1F (only) 14 CFR part 33 effective February 1, 1965, Amendments 33-1 through 33-8 inclusive except for the approved substitute compliance procedures, which are in accordance with Amendments 9 and 10. The specific requirements of Amendment 9 met are those defined in Sections 33.4 and 33.5. The specific requirements of Amendment 10 met are those defined in Sections 33.7, 33.14, 33.23, 33.27, 33.88, and 33.92. Amendment 15 Section 33.28. Equivalent Level of Safety (ELOS) finding, 8040-ELOS-05-NE-03 for Section 33.89(a)(3)(ii) and (iii). CF6-80C2K1F model complies with 14 CFR part 34, amendment 7A, effective May 24, 2024. See NOTE 29 for detailed summary of the certification basis for fuel venting and exhaust emissions. TCDS E13NE 9 TYPE CERTIFICATE E13NE CF6-80C2 SERIES (continued) MODELS APPLICATION DATE ISSUED/AMENDED CF6-80C2A1 SEP 11, 1984 JUN 28, 1985 CF6-80C2B1 SEP 11, 1984 JUN 28, 1985 CF6-80C2A2 SEP 11, 1984 DEC 30, 1985 CF6-80C2B4 MAR 05, 1986 OCT 31, 1986 CF6-80C2A3 MAR 05, 1986 DEC 09, 1986 CF6-80C2B2 NOV 20, 1986 APR 06, 1987 CF6-80C2B6 FEB 20, 1987 SEP 30, 1987 CF6-80C2A5 MAY 12, 1987 OCT 26, 1987 CF6-80C2B1F MAR 26, 1987 MAR 31, 1988 CF6-80C2B2F MAY 18, 1988 SEP 23, 1988 CF6-80C2B4F MAY 18, 1988 SEP 23, 1988 CF6-80C2B6F MAY 18, 1988 SEP 23, 1988 CF6-80C2D1F MAY 18, 1988 DEC 20, 1988 CF6-80C2B1F1 OCT 23, 1989 JUN 15, 1990 CF6-80C2A8 JUN 22, 1990 FEB 26, 1991 CF6-80C2B3F APR 11, 1990 NOV 23, 1992 CF6-80C2A5F APR 02, 1993 OCT 13, 1993 CF6-80C2B7F JAN 27, 1993 OCT 13, 1993 CF6-80C2B1F2 SEP 17, 1993 NOV 18, 1993 CF6-80C2B6FA JAN 31, 1994 SEP 21, 1995 CF6-80C2B5F AUG 11, 1994 MAY 22, 1997 CF6-80C2B8F SEP 02, 1997 MAR 18, 1999 CF6-80C2L1F JAN 30, 2002 AUG 30, 2004 CF6-80C2K1F JUL 14, 2004 FEB 22, 2006 PRODUCTION BASIS Production Certificate No. 108 for engines produced by General Electric in the United States. In addition, CF6-80A series engines and parts thereof produced in Europe are eligible in accordance with the following: Société National d'Etude et de Construction de Moteurs d'Aviation (SNECMA): Production agreement No. 6-3032 between General Electric and SNECMA dated February 20, 1981, for complete engines and modules. Identification plates for CF6-80A1/A3 engines manufactured by SNECMA shall contain the following information: 1. Manufacturer (SNECMA, France) 2. Model 3. Serial Number (Numbers 585- are assigned to CF6-80A1/A3 engines manufactured by SNECMA) 4. Type Certificate Number E13NE 5. Import TC No. M-IM13 6. Established ratings Each individually imported engine and parts thereof must be accompanied by an airworthiness approval tag, JAA Form F1, issued by SNECMA on behalf of Director Generale de l'Aviation Civile 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. TCDS E13NE 10 PRODUCTION BASIS (continued) SNECMA: In addition, CF6-80C2 series engines (except for CF6-80C2L1F and CF6-80C2K1F models) and parts thereof produced in Europe are eligible in accordance with the following: Production agreement No. 6.3592 between the General Electric Company and SNECMA dated April 19, 1983, for complete engines and modules. Identification plates for CF6-80C2 engines manufactured by SNECMA shall contain the following information: 1. Manufacturer (SNECMA, France) 2. Model 3. Serial Number (Numbers 695- are assigned to CF6-80C2 PMC engines manufactured by SNECMA and Numbers 703- and 705-204 and up are assigned to CF6-80C2 FADEC engines manufactured by SNECMA) 4. Type Certificate Number E13NE 5. Import TC No. M-IM13 6. Established ratings Each individually imported engine and parts thereof must be accompanied by an airworthiness approval tag, JAA Form F1, issued by SNECMA on behalf of Director Generale de l'Aviation Civile 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. NOTES NOTE 1. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS Low pressure rotor (N1). High pressure rotor (N2). CF6-80A (ALL MODELS) 4016 rpm (117.0%) 10859 rpm (110.5%) (*) CF6-80C2 (ALL MODELS) 3854 rpm (117.5%) 11055 rpm (112.5%) NOTE 2. MAXIMUM PERMISSIBLE TEMPERATURES Turbine exhaust gas temperature (T49): Takeoff (5 min.) Maximum continuous 120 second maximum transient 1724oF (940oC) (*) 1643oF (895oC) (*) 1760oF (960oC) (**) 1697oF (925oC) 1769oF (965oC) for B8F only Starting (max transient 40 secs) Starting (max no time limit) 1598oF (870oC) 1382oF (750oC) - - - - NOTES: Refer to CF6-80A Operating Instruction GEK 72506, or CF6-80C2 (except CF6-80C2L1F and CF6-80C2K1F), Operating Instruction GEK 92462 or GEK 112651 for CF6-80C2L1F (only) or GEK 112724 for CF6-80C2K1F (only) for time temperature envelope. (*) See NOTE 28 for further information regarding maximum permissible parameters on CF6-80A engines. (**) See NOTES 15 and 20 for further information regarding EGT Redline and EGT Junction Box. TCDS E13NE 11 NOTE 2. MAXIMUM PERMISSIBLE TEMPERATURES (continued) Fuel Pump Inlet CF6-80A / CF6-80A2 Refer to CF6-80A Installation Manual GEK 50460 CF6-80A1 / CF6-80A3 Refer to CF6-80A Installation Manual GEK 50490 CF6-80C2A1 / A2 / A3 / A5 / A8 / B1 / B2 / B4 / B6 Refer to CF6-80C2 Installation Manual GEK 50492 CF6-80C2B1F / B2F / B3F / B4F / B6F / D1F / B1F1 / A5F / B7F / B1F2 / B6FA / B5F / B8F Refer to CF6-80C2 FADEC Installation Manual GEK 97284 CF6-80C2L1F Refer to CF6-80C2L1F Installation Manual GEK 112655 CF6-80C2K1F Refer to CF6-80C2K1F Installation Manual GEK 112723 Oil Outlet / All Models Continuous operation 320oF (160oC) Transient operation (15 mins limit) 347oF (175oC) NOTE 3. FUEL AND OIL PRESSURE LIMITS FUEL PRESSURE LIMITS AT ENGINE PUMP INLET CF6-80A / A2 GROUND STARTING This limit is from minimum fuel pressure of not less than 12 psia (82.7 kPa, absolute) to a maximum of 64 psig (441.3 kPa gage) (relative to atmosphere) with vapor/liquid ratio of zero at all conditions. OPERATION AND AIR STARTING Operation and air starting pressure limit extends from a minimum fuel pressure of more than 5.0 psi (34.5 kPa) above the true vapor fuel pressure to a normal maximum fuel pressure of 64 psig (441.3 kPa gage) with transient pressure (2 minute maximum) up to 71 psig (489.5 kPa gage) permitted (relative to the atmosphere) at all conditions. CF6-80A1 / A3 GROUND STARTING This limit is from a minimum fuel pressure of not less than 12 psia (82.7 kPa, absolute) to a maximum of 50 psig (344.8 kPa gage) (relative to atmosphere) with vapor/liquid ratio of zero at all conditions. OPERATION AND AIR STARTING The engine fuel system will provide fuel flow and pressure required for starting and operating the engine throughout the defined operational envelope when the fuel pressure at the fuel pump inlet connections to the engine ranges from a minimum of true vapor pressure of the fuel plus 5.0 psi (34.5 kPa) to a maximum of 50 psig