TCDS E23EA

* PAGE 1 2 3 4 5 6 7 8 9 10 11 REV. 21 21 21 21 21 21 21 20 20 21 21 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTICE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E23EA TCDS NUMBER E23EA REVISION: 21 DATE: June 10, 2013 GENERAL ELECTRIC COMPANY MODELS: CF6-6D CF6-50C CF6-50E CF6-6D1 CF6-50CA CF6-50E1 CF6-6D1A CF6-50C1 CF6-50E2 CF6-50C2 CF6-50E2B CF6-6K CF6-50C2B CF6-6K2 CF6-50C2D CF6-45A CF6-45A2 CF6-50A Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E23EA) 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 One Neumann Way Cincinnati, OH 45215 I. MODELS CF6-6D CF6-6D1 CF6-6D 1A CF6-6K CF6-6K2 TYPE High bypass turbofan: coaxial front fan driven by multi-stage low pressure turbine, multi-stage compressor with two stage turbine and annular combustor. RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb. Takeoff (5 min.) at sea level, static thrust, lb. (See NOTE 14) Alternate takeoff (5 min.) at sea level, static thrust, lb. Flat rating ambient temperature Takeoff Alternate takeoff Maximum continuous 37,500 39,300 --- 88°F/31°C --- 77°F/25°C - - 40,300 --- 84°F/29°C --- - - - - 40,900 --- - - --- - - - - 39,300 --- 88°F/31°C --- - - - - 40,900 --- 84°F/29°C --- - - TCDS E23EA PAGE 2 I. MODELS (CONT.) CF6-6D CF6-6D1 CF6-6D 1A CF6-6K CF6-6K2 FUEL CONTROL, WOODWARD GE P/N CIT SENSOR, WOODWARD GE P/N FUEL PUMP GE P/N Single element gear type pump FUEL (See NOTE 7) Conforming to GE Specification 9033M11 or 9221M56 7003M94 9015M46 or 9039M45 D50TF2 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - OIL Synthetic type conforming to GE Specification D50TF1. GE Service Bulletin 79-0001 lists approved oils and applicable restrictions. IGNITION SYSTEM Two ignition units GE P/N Two ignitor plugs GE P/N STARTING Starter GE P/N Starter Valve 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) 9101M52 9101M37 9014M18 or 9281M79 9033M46 188 94 105 8,176 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - NOTE: Weight includes basic engine accesso ries & optional equipment as listed in the manufacturer's engine specification, including condition monitoring instrumentation sensors per GE Specification GEK 9251. CENTER OF GRAVITY LOCATIONS Station (in) (engine only) Waterline (in) (engine only) 227.0+2.0 98.1+1.0 - - - - - - - - - - - - - - - - TCDS E23EA PAGE 3 II. MODELS CF6-50A CF6-50C CF6-50CA CF6-50C1 CF6-50C2 TYPE High bypass turbofan: coaxial front fan driven by multi-stage low pressure turbine, multi-stage compressor with two stage turbine and annular combustor. RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb. Takeoff (5 min.) at sea level, static thrust, lb. (See NOTE 14) Alternate takeoff (5 min) at sea level, static thrust, lb. Flat rating ambient temperature Takeoff Alternate takeoff Maximum continuous 46,300 48,400 --- 87°F/31°C --- 86°F/30°C - - 50,400 --- 86°F/30°C --- - - - - - - --- - - --- - - - - 51,800 46,600 - - 86°F/30°C - - - - - - --- - - --- - - FUEL CONTROL, WOODWARD GE P/N CIT SENSOR, WOODWARD GE P/N FUEL PUMP GE P/N Single element gear type pump FUEL (See NOTE 7) Conforming to GE Specification 9070M55 9261M73 or 9261M74 9015M46 or 9039M45 D50TF2 - - - - - - - - - - - - - - - - - - - - - - - - 9070M55 or 9187M29 - - - - - - - - - - 9070M55 - - - - - - - - - - OIL Synthetic type conforming to GE Specification D50TF1. GE Service Bulletin 79-0001 lists approved oils and applicable restrictions. IGNITION SYSTEM Two ignition units GE P/N Two ignitor plugs GE P/N STARTING Starter GE P/N Starter Valve 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) 9101M52 or 9238M66 9101M37 or 1305M52 9014M18 or 9281M79 9033M46 183 94 105 8,825 - - - - 9101M37 or 9387M23 - - - - - - - - - - - - 8,966 - - - - 1305M52 or 9101M37 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - NOTE: Weight includes basic engine accesso ries & optional equipment as listed in the manufacturer's engine specification, including condition monitoring instrumentation sensors per GE Specification GEK 9251. TCDS E23EA PAGE 4 II. MODELS (CONT.) CF6-50A CF6-50C CF6-50CA CF6-50C1 CF6-50C2 CENTER OF GRAVITY LOCATIONS Station (in) (engine only) Waterline (in) (engine only) 224.0+2.0 96.8+1.0 - - - - - - - - - - - - - - - - III. MODELS CF6-50C2D CF6-50E CF6-50E1 CF6-50E2 CF6-50C2B TYPE High bypass turbofan: coaxial front fan driven by multi-stage low pressure turbine, multi-stage compressor with two stage turbine and annular combustor. RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb. Takeoff (5 min.) at sea level, static thrust, lb. (See NOTE 14) Alternate takeoff (5 min) at sea level, static thrust, lb. Flat rating ambient temperature Takeoff Alternate takeoff Maximum continuous 46,300 51,800 --- 79°F/26°C --- 86°F/30°C - - - - 46,600 78°F/26°C 86°F/30°C - - - - - - --- 86°F/30°C --- - - - - - - --- - - --- - - - - 53,200 --- 79°F/26°C --- 86°F/30°C FUEL CONTROL, WOODWARD GE P/N CIT SENSOR, WOODWARD GE P/N FUEL PUMP GE P/N Single element gear type pump FUEL (See NOTE 7) Conforming to GE Specification 9070M55 9261M73 or 9261M74 9015M46 or 9039M45 D50TF2 9187M29 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 9070M55 - - - - - - - - - - OIL Synthetic type conforming to GE Specification D50TF1. GE Service Bulletin 79-0001 lists approved oils and applicable restrictions. IGNITION SYSTEM Two ignition units GE P/N Two ignitor plugs GE P/N STARTING Starter GE P/N Starter Valve 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) 9101M52 or 9238M66 1305M52 or 9101M37 9014M18 or 9281M79 9033M46 183 94 105 8,966 - - - - - - - - 9014M18 - - - - - - - - 9,047 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 9014M18 or 9281M79 - - - - - - - - 8,966 TCDS E23EA PAGE 5 III. MODELS (CONT.) CF6-50C2D CF6-50E CF6-50E1 CF6-50E2 CF6-50C2B WEIGHT (DRY) (lb) 8,966 9,047 - - - - 8,966 NOTE: Weight includes basic engine accesso ries & optional equipment as listed in the manufacturer's engine specification, including condition monitoring instrumentation sensors per GE Specification GEK 9251. CENTER OF GRAVITY LOCATIONS Station (in) (engine only) Waterline (in) (engine only) 224.0+2.0 96.8+1.0 - - - - - - - - - - - - - - - - IV. MODELS CF6-50E2B CF6-45A CF6-45A2 TYPE High bypass turbofan: coaxial front fan driven by multi-stage low pressure turbine, multi-stage compressor with two stage turbine and annular combustor. RATINGS (See NOTE 5) Maximum continuous at sea level, static thrust, lb. Takeoff (5 min.) at sea level, static thrust, lb. (See NOTE 14) Alternate takeoff (5 min) at sea level, static thrust, lb. Flat rating ambient temperature Takeoff Alternate takeoff Maximum continuous 46,300 53,200 --- 86°F/30°C --- 86°F/30°C 43,250 45,600 --- 97°F/36°C --- - - - - - - --- - - --- - - FUEL CONTROL, WOODWARD GE P/N CIT SENSOR, WOODWARD GE P/N FUEL PUMP GE P/N Single element gear type pump FUEL (See NOTE 7) Conforming to GE Specification 9187M29 9261M73 or 9261M74 9015M46 or 9039M45 D50TF2 - - - - - - 9039M45 - - - - - - - - - - - - OIL Synthetic type conforming to GE Specification D50TF1. GE Service Bulletin 79-0001 lists approved oils and applicable restrictions. TCDS E23EA PAGE 6 IV. MODELS (CONT.) CF6-50E2B CF6-45A CF6-45A2 IGNITION SYSTEM Two ignition units GE P/N Two ignitor plugs GE P/N STARTING Starter GE P/N Starter Valve 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) 9101M52 or 9238M66 1305M52 or 9101M37 9014M18 9033M46 183 94 105 9,047 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - NOTE: Weight includes basic engine accesso ries & optional equipment as listed in the manufacturer's engine specification, including condition monitoring instrumentation sensors per GE Specification GEK 9251. CENTER OF GRAVITY LOCATIONS Station (in) (engine only) Waterline (in) (engine only) 224.0+2.0 96.8+1.0 - - - - - - - - CERTIFICATION BASIS Title 14, Code of Federal Regulations (14 CFR) part 33 effective February 1, 1965, with Amendments 33-1 through 33-3 thereto, and Special Conditions 33-9-EA-4 for CF6-6 and CF6-50 series and 33-36-EA-9 for CF6-50 series. All CF6 series engines approved under Type Certificate No. E23EA comply with the February 1, 1974, fuel venting emissions and January 1, 1976, exhaust emissions requirements of Special Federal Aviation Regulation No. 27 effective February 1, 1974, Section 15. CF6-50/-45 engines delivered after January 1, 1988, comply with Special Federal Aviation Regulation 27-5. DATE OF APPLICATION/ MODELS AMENDED APPLICATION DATE TC E23EA ISSUED/AMENDED CF6-6D JUL 03, 1968 SEPT 16, 1970 CF6-50A SEPT 05, 1969 MAR 23, 1972 CF6-6D1 JUN 02, 1971 AUG 02, 1971 CF6-50D JUL 9, 1971 NOV 27, 1972* CF6-50C JUL 9, 1971 NOV 20, 1973 CF6-50E APR 02, 1973 NOV 20, 1973 CF6-6H JUL 18, 1973 NOV 07, 1973* CF6-50H AUG 21, 1973 SEPT 07, 1973* CF6-50E1 MAY 21, 1975 AUG 12, 1975 CF6-50C1 JUN 03, 1976 JUL 22, 1976 CF6-50CA JUN 03, 1977 JUN 08, 1977 TCDS E23EA PAGE 7 CERTIFICATION BASIS DATE OF APPLICATION/ MODELS AMENDED APPLICATION DATE TC E23EA ISSUED/AMENDED CF6-45A FEB 13, 1976 JUL 12, 1977 CF6-45B MAY 03, 1977 JUL 12, 1977* CF6-6D1A JUL 24, 1978 AUG 01, 1978 CF6-50C2 JAN 05, 1978 AUG 11, 1978 CF6-50E2 JAN 05, 1978 DEC 07, 1978 CF6-45A2 DEC 04, 1978 DEC 07, 1978 CF6-45B2 DEC 04, 1978 DEC 07, 1978* CF6-50C2B JUL 20, 1979 AUG 08, 1979 CF6-50E2B JUL 20, 1979/JUL 28, 1982 AUG 08, 1979/MAR 18, 1983 CF6-50C2D AUG 11, 1988 SEPT 22, 1988 CF6-6K JAN 08, 1980 OCT 06, 1981 CF6-6K2 NOV 27, 1984 DEC 31, 1984 * Engine models CF6-45B, CF6-45B2, and CF6-50D were deleted from Type Certificate E23EA on April 9, 1981. Engine model CF6-6H was deleted from Type Certificate E23EA on August 12, 1975. Engine model CF6-50H was deleted from Type Certificate E23EA on November 9, 1977. The above were deleted at the request of the type certificate holder. No engines of these models are in existence, nor is there intent to manufacture or convert to these models. PRODUCTION BASIS Production Cer tificate No. 108 for engines produced by General Electric in the United States. In addition, CF6-50 series engines and parts thereof produced in Europe are eligible in accordance with the following: 1. License agreement between General Electric and Societe National d'Etude et de Construction de Monteurs d'Aviation effective March 12, 1971, for complete engine and parts thereof. 2. License agreement between General Electric and Motoren and Turbinen Union, Munich GmbH effective February 9, 1971, for engine parts only. Identification plates for engines manufactured by SNECMA shall contain the following information: 1. Manufacturer (SNECMA, France) 2. Model 3. Serial Number (Numbers 455-701through 455-999 and 528-101 through 528-999 are assigned to -50 engines manufactured by SNECMA) 4. Type Certificate Number E23EA 5. Established ratings 6. French certificate IM7 Each individually imported engine must be accompanied by an airworthiness approval tag, JAA Form 1, issued by SNECMA on behalf of the French Direction Generale de l'Aviation Civile (DGAC) under Production Certificate No. P03 or a "Certificat de Navigabilite pour Exportation" delivered by the DGAC (Ref. 14 CFR 21.502). For imported modules, assemblies or parts produced by SNECMA in France, an airworthiness approval tag, JAA Form 1, issued by SNECMA on behalf of the French DGAC under Production Certificate No. P03 or a Certificat de Navigabilite pour Exportation" delivered by the DGAC (Ref. §21.502) shall be attached to each item or invoice covering a shipment of similar items. For imported modules, assemblies or parts produced by MTU in the Federal Republic of Germany, a Luftfahrt-Bundersamt tag Muster Nr. 13/1 shall be attached to each item or invoice covering a shipment of similar items. TCDS E23EA PAGE 8 NOTES NOTE 1. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS CF6-45A, CF6-45A2 CF6-50C1, CF6-50E CF6-6D, CF6-6D1 CF6-50A CF6-50E1, CF6-50C2 CF6-6D1A, CF6-6K CF6-50C CF6-50E2, CF6-50C2B CF6-6K2 CF6-50CA CF6-50E2B, CF6-50C2D Low pressure rotor (N1). 3,810 (111 %) 4,102 (119.5%) 4,102 (119.5%) High pressure rotor (N2). 9,925 ( 101%) 10,761 (109.5%) 10,761 (109.5%) NOTE 2. MAXIMUM PERMISSIB LE INDICATED TEMPERATURES Turbine exhaust gas temperature (T5.4): Takeoff (5 min.) 1670°F (910°C) (CF6-6D, CF6-6D1, CF6-6D1A, CF6-6K, CF6-6K2) 1679°F (915°C) (CF6-50A) 1733°F (945°C) (CF6-50C, CF6-50C A, CF6-50C1, CF6-50C2, CF6-50E, CF6-50E1, CF6-50E2, *CF6-50A, CF6-45A, CF6-45A2, CF6-50C2B, CF6-50E2B, CF6-50C2D) Maximum continuous 1616°F (880°C) (CF6-6D, CF6-6D1, CF6-6D1A, CF6-6K, CF6-6K2) 1607°F (875°C) (CF6-50A) 1670°F (910°C) (*CF6-50A, CF6- 50C, CF6-50CA, CF6-50C1, CF6-50E, CF6-50E1, CF6-50E2, CF6-50C2, CF6-50C2B, CF6-50E2B, CF6-50C2D, CF6-45A, CF6-45A2) Maximum for acceleration 1697°F (925°C) (CF6-6 D, CF6-6D1, CF6-6D1A, CF6-6K, CF6-6K2) (2 min.) 1706°F (930°C) (CF6-50A) 1760°F (960°C) (CF6-50C, CF6-50C A, CF6-50C1, CF6-50C2, CF6-50E, CF6-50E1, CF6-50E2, *CF6-50A, CF6-45A, CF6-45A2, CF6-50C2B, CF6-50E2B, CF6-50C2D) Starting (max transient 40 secs) 1652°F (900°C) Starting (max no time limit) 1382°F (750°C) NOTE: Refer to CF6 Operating Instruction GEK 9267, for CF6-6 series and GEK 28467 for CF6-50/-45 series for time temperature envelope. *CF6-50A engines must comply with GE Service Bulletin 72-471 to be eligible for these higher temperature limits. GE Service Bulletin 77-25 is available to increase CF6-50/-45 series EGT margin by 10°C. This is accomplished by reducing indicated EGT by 10°C using a shunt device. SB 77-25 also defines required hot section hardware. Operating procedures and maintenance requirements shall be conducted per indicated EGT. Fuel Pump Inlet Refer to CF6 Installation Manual GEK 9286 Oil outlet / All models: Continuous operation 320°F (160°C) Transient operation 347°F (175°C) (Transient operation is limited to 15 minutes) TCDS E23EA PAGE 9 NOTE 3. FUEL AND OIL PRESSURE LIMITS Fuel: Minimum at engine pump inlet; 3.5 p.s.i. above absolute fuel vapor pressure, with maximum of 50 p.s.i. above absolute ambient atmospheric pressure. Oil: Limits vary - refer to Specific Operating In struction GEK 9267 for CF6-6 series, and GEK 28467 for CF6-50/-45 series. NOTE 4. ACCESSORY DRIVE PROVISIONS MODELS: DRIVE PAD ROTATION CF6-6 GEAR RATIO TO CORE SPEED CF6-45/-50 GEAR RATIO TO CORE SPEED TORQUE (in. - lb.) CONT. STATIC STATIC OVERHUNG MOMENT (in. - lb.) Starter CSD Alternator* Tachometer (core)** Hydraulic pump*** CC CC C C CC 1.000 0.870 ----- 0.427 0.366 0.956 0.832 ------- 0.409 0.350 10,800 19,200 (250 H.P.) 17,400 ------------ -------- 7 540 (85 H.P.) 7,400 400 900 1,000 3 500 C = Clockwise; CC = Counter-clockwise * = Alternator Driven by CSD ** = Tachometer Mounted on and Driven through Main Lube & Scavenge Pump *** = Either or both of two hydraulic pump drives NOTE 5. ENGINE RATINGS ARE BASED ON CALIBRATED STAND PERFORMANCE UNDER THE FOLLOWING CONDITIONS: Fan inlet air at 59°F and 29.92 in. hg. GE bellmouth air inlet per GE Drawing 4013106-124, or 4013070-409 (light weight) No external air bleed or accessory drive power for aircraft accessories. Fan nozzle configuration defined by GE drawing 4013124-051, for CF6-6 series and 4013157-495 for CF6-45 series and CF6- 50 series. Jet nozzle configuration defined by GE Drawing 4013124-012 for CF6-6 series and 4013156-186 for CF6-45 series and CF6- 50 series. Turbine temperature and engine rotor speed limits not exceeded. Core engine acceptance test cowling defined by GE Drawing 4013124-021. Pylon configuration acceptance test cowling defined by GE Drawing 4013070-716 and/or 4013124-091. Stand thrust adjusted for scrubbing drag per Figure A-11 of CF6 Installation Manual GEK 9286. Engine performance deck R70AEG214 for CF6-6 series or R71AEG135 for CF6-45 series and CF6-50 series is the prime source of engine performance data throughout the flight envelope. NOTE 6. MAXIMUM PERMISSIBLE AIR BLEED EXTRACTION BLEED LOCATION CF6-6 CF6-45/ CF6-50 Stage 8, compressor airflow, normal Stage 8, compressor airflow, intermittent* Compressor discharge Steady state at takeoff rating Steady state between 80% N2 and maximum continuous During acceleration above 80% N2 Operating at 80% N2 or below Stage 10 Stage 13 5.00% N/A 5.00% 10.00% 7.00% 5.00% N/A 2.00% 5.00% 5.75% 5.00% 10.00% 7.00% 12.50% 2.00% N/A *The engine manufacturer is to be consulted regarding c onditions, number of occurrences and duration of each occurrence within the limitations of: average of 2 x 10(-3) occurrences per engine operating hour and a maximum of 0.5 hour duration per occurrence (cumulative total of 50 hours). Intermittent operation is defined as "dispatch with a bleed system inoperative, or bleed system or engine failure in flight" and should be confined to the physical core speed (N2) range of 81.5 to 98.5 r.p.m. TCDS E23EA PAGE 10 NOTE 7. FUEL Approved fuel conforming to GE Specification D50TF2 . The latest revision of specification will apply. NOTE 8. Cyclic life limits for CF6-6 critical rotating components ar e published in the Life Limits Section of the CF6-6 Engine Manual GEK 9266. Cyclic life limits for CF6-50/-45 critical rotating and static components are published in the Life Limits Section of CF6-50/-45 Engine Manual GEK 50481. NOTE 9. Power setting, power checks and control of engine thrust output in all operations is to be based on GE engine charts referring to Fan Speed (N1). Speed sensors are included in the engine assembly for this purpose. NOTE 10. The following thrust reverser models are approved in accordance with 14 CFR 33.97 for incorporation on CF6 engine models: CF6-6D, -6D1, -6D1A, CF6-50A, -50C, -50CA, -50C1, CF6-45A, -45A2, -50E, -6K, -6K2 -50C2, -50C2B, -50C2D -50E1, -50E2, -50E2B Fan Reverser FR-CF6G01 FR-CF6G02 FR-CF6G04 Model No. FR-CF6G07 FR-CF6G03 FR-CF6G06 TR-CF6-F4 FR-CF6G05 TR-CF6-F6 F R - C F 6 G 0 8 F R - C F 6 G 0 9 F R - C F 6 G 1 0 T R - C F 6 - F 3 Turbine Reverser Model No. TR-CF6-4** TR-CF6-5* TR-CF6-7* *A fixed core exhaust nozzle , N-CF6-1, is eligible for use in lieu of the TR-CF6-5 or TR-CF6-7 turbine reverser. A short fixed core exhaust nozzle, N-CF6-3, is also eligible for use in lieu of the TR-CF6-5 turbine reverser. **Fixed core nozzle Rohr P/N 217-0001-501, 503, or 505. NOTE 11. Refer to FAA New England Region or cognizant foreign airworthiness authority regarding foreign validation of FAA certification of CF6 series engines. NOTE 12. The following models incorporate the following general characteristics: CF6-6D Basic model. CF6-6D1 Same as CF6-6D except takeoff rating extende d to 40,300 lbs. at 84°F ambient temperature sea level static with improved engines parts as defined in SB (CF6-6) 72-263 and SB 73-42. CF6-6D1A Same as CF6-6D1 except for takeoff rating extended to 40,900 lbs at 84°F ambient temperature. CF6-45A Same as CF6-50E except for reduced ratings sp ecified at increased flat rating ambient temperature. CF6-45A2 Same as CF6-50E2 except for reduced ratings speci fied at increased flat rating ambient temperature. CF6-50A Basic CF6-50 series model. Differs primarily from CF6-6 series in the number of low pressure and high pressure compressor stages, number of low pressu re turbine stages, rotor speeds and temperature limits. TCDS E23EA PAGE 11 NOTE 12 (Cont.) CF6-50C Same as CF6-50A except takeoff rating increased to 50,400 lbs, flat rated to 86°F ambient temperature sea level static and with improved engine parts. CF6-50CA Same as CF6-50C except for variable stator vane reset actuator as used on CF6-50C1 for improved exhaust gas temperature operational characteristics. CF6-50C1 Same as CF6-50C except the engine is operated at an increased takeoff thrust of 51,800 lbs. flat rated to 86°F ambient temperature SLS with an altern ate takeoff rating of 46,600 lbs. flat rated ambient temperature SLS. CF6-50E Same as CF6-50C except the engine is operated to increased takeoff thrust of 51,800 lbs at a lower flat rated ambient temperature of 78°F SLS with an a lternate takeoff rating of 46,600 lbs flat rated to 86°F ambient temperature SLS. CF6-50E1 Same as CF6-50E except the takeoff flat rating am bient temperature is increased to 86°F sea level static with improved engine parts. CF6-50C2 Same as CF6-50C1 except for new fan blade, Main Engine Control, and fan case stiffening ring. CF6-50C2B Same as CF6-50C2 except for increased takeo ff thrust of 53,200 lbs at lower flat rated ambient temperature of 79°F. CF6-50C2D Same as CF6-50C2 except for lower fl at rated ambient temperature of 79°F, SLS. CF6-50E2 Same as CF6-50E1 except for new fan blade, Main Engine Control, and fan case stiffening ring.