TCDS E00063EN

TCDS NUMBER E00063EN REVISION: 11 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET DATE: November 22, 2024 GENERAL ELECTRIC COMPANY MODELS: CF34-8C1; CF34-8C5; CF34-8C5A1; CF34-8C5B1; CF34-8C5A2; CF34-8C5A3; CF34-8E2; CF34-8E2A1; CF34-8E5; CF34-8E5A1; CF34-8E5A2; CF34-8E5A2HA; CF34-8E6; CF34-8E6A1 Engi nes of models described herein conforming with this data sheet 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 manufacturers manuals and other FAA approved instructions. TY PE CERTIFICATE (TC) HOLDER: General Electric Company GE Aerospace 1000 Western Avenue Lynn, Massachusetts 01910 I. MODELS CF34-8C1 CF34-8C5 CF34-8C5A1 CF34-8C5B1 CF34-8C5A2 CF34-8C5A3 TYPE Dual rotor, axial flow, high bypass ratio turbofan; single stage fan, ten stage axial compressor, annular combustion chamber, two stage high pressure turbine, four stage low pressure turbine, a thrust reverser (CF34 –8E models only), aft core cowl (CF34 –8E models only), exhaust nozzle, exhaust centerbody, starter, and a Full Authority Digital Engine Control (FADEC). RATINGS (See NOTE 5) Sea level static thrust, lb Maximum takeoff (5 min.) (See NOTES 13,15 and 18) 13790 14510 - - 13790 14510 - - Normal takeoff (5 min.) (See NOTES 13 and 15) 12670 13360 13630 12670 14050 14510 Maximum continuous (See NOTE 13) 13277 13680 - - 13280 13680 - - CONTROL SYSTEM COMPONENT Fuel Control, Woodward Governor 4120T01 - - - - - - - - - - Full Authority Digital Engine Control (FADEC), Lockheed/Martin Ignition System 2 Ignition Exciters, Unison 2 Ignition Plugs, Federal Mogul / Champion Fuel Pump, Argotech 4120T00 9238M66 4096T33 4120T04 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - PAGE 1 2 3 4 5 6 7 8 9 10 11 12 REV. 11 2 10 10 10 7 10 8 10 10 10 11 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. TCDS E00063EN Page 2 of 12 I. MODELS (continued) CF34-8C1 CF34-8C5 CF34-8C5A1 CF34-8C5B1 CF34-8C5A2 CF34-8C5A3 FUEL Fuel conforming to GE Jet Fuel Specification No. D50TF2, current revision, is applicable for all models. See GEK 105094 (CF34-8C1/8C5 models), GEK 112034 (CF34-8E models), Operating Instructions, for specific fuels approved per the subject specifications. OIL Oil conforming to GE Specification No. D50TF1, current revision, is applicable for all models. See GEK 105094 (CF34-8C1/8C5 models), GEK 112034 (CF34-8E models), Operating Instructions, for specific oils approved per the subject specifications. PRINCIPAL DIMENSIONS AND MEASUREMENTS Length, inches Maximum diameter, inches Weight, pounds (includes residual fuel and oil) Center of Gravity Location, inches Engine Station Butt Line Water Line (Demountable Assembly less fluids to fill; see Installation Manual GEK 105093) 152.28 60.66 2704 173.2 99.6 99.1 - - 151.57 60.66 2780 173.9 99.78 99.35 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - II. MODELS CF34-8E2 TYPE Dual rotor, axial flow, high bypass ratio turbofan; single stage fan, ten stage axial compressor, annular combustion chamber, two stage high pressure turbine, four stage low pressure turbine, a thrust reverser (CF34 –8E models only), aft core cowl (CF34 –8E models only), exhaust nozzle, exhaust centerbody, starter, and a Full Authority Digital Engine Control (FADEC). RATINGS (See NOTE 5) Sea level static thrust, lb Maximum takeoff (5 min.) (See NOTES 13,15 and 18) 13300 Normal takeoff (5 min.) (See NOTES 13 and 15) 12410 Maximum continuous (See NOTE 13) 12540 CONTROL SYSTEM COMPONENT 4120T01 4120T00 9238M66 4096T33 4120T04 Fuel Control, Woodward Governor Full Authority Digital Engine Control (FADEC), Lockheed/Martin Ignition System 2 Ignition Exciters, Unison 2 Ignition Plugs, Federal Mogul / Champion Fuel Pump, Argotech TCDS E00063EN Page 3 of 12 II. MODELS (continued) CF34-8E2 FUEL Fuel conforming to GE Jet Fuel Specification No. D50TF2, current revision, is applicable for all models. See GEK 105094 (CF34- 8C1/8C5 models), GEK 112034 (CF34- 8E models), Operating Instructions, for specific fuels approved per the subject specifications. OIL Oil conforming to GE Specification No. D50TF1, current revision, is applicable for all models. See GEK 105094 (CF34-8C1/8C5 models), GEK 112034 (CF34-8E models), Operating Instructions, for specific oils approved per the subject specifications. PRINCIPAL DIMENSIONS AND MEASUREMENTS Length, inches Maximum diameter, inches Weight, pounds (includes residual fuel and oil) Center of Gravity Location, inches Engine Station Butt Line Water Line (14 CR Part 33 Propulsion System; see Installation Manual GEK 112033) 121.18 62.65 3147.6 175.01 99.43 100.07 III. MODELS CF34-8E2A1 CF34-8E5 CF34-8E5A1 CF34-8E5A2 CF34-8E5A2HA CF34-8E6 CF34-8E6A1 TYPE Dual rotor, axial flow, high bypass ratio turbofan single stage fan, ten stage axial compressor, annular combustion chamber, two stage high pressure turbine, four stage low pressure turbine, a thrust reverser (CF34-–8E models only), aft core cowl (CF34 –8E models only), exhaust nozzle, exhaust centerbody, starter, and a Full Authority Digital Engine Control (FADEC). RATINGS (See NOTE 5) Sea level static thrust, lb Maximum takeoff (5 min.) (See NOTES 13,15 and 18) 13300 14510 - - - - - - 14050 - - Normal takeoff (5 min.) (See NOTES 13 and 15) 13300 13420 14050 14510 - - 13420 14050 Maximum continuous (See NOTE 13) 12540 13520 - - - - - - - - - - TCDS E00063EN Page 4 of 12 III. MODELS (cont) CF34-8E2A1 CF34-8E5 CF34-8E5A1 CF34-8E5A2 CF34-8E5A2HA CF34-8E6 CF34-8E6A1 CONTROL SYSTEM COMPONENTS 4120T01 4120T00 9238M66 4096T33 4120T04 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Fuel Control, Woodward Governor Full Authority Digital Engine Control (FADEC), Lockheed/Martin Ignition System 2 Ignition Exciters, Unison 2 Ignition Plugs, Federal Mogul / Champion Fuel Pump, Argotech FUEL Fuel conforming to GE Jet Fuel Specification No. D50TF2, current revision, is applicable for all models. See GEK 112034 (CF34-8E models), Operating Instructions, for specific fuels approved per the subject specifications OIL Oil conforming to GE Specification No. D50TF1, current revision, is applicable for all models. See GEK 112034 (CF34-8E models), Operating Instructions, for specific oils approved per the subject specifications. PRINCIPAL DIMENSIONS AND MEASUREMENTS Length, inches (14 CFR Part 33 Propulsion System; see Installation Manual GEK 112033) 121.18 62.65 3147.6 175.01 99.43 100.07 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Maximum diameter, inches Weight, pounds (includes residual fuel and oil) Center of Gravity Location, inches Engine Station Butt Line Water Line TCDS E00063EN Page 5 of 12 CERTIFICATION BASIS . 1) CF34-8C1 14 CFR Part 33, effective February 1, 1965, as amended by amendments 33-1 through 33-19, and Equivalent Level of Safety 8040-ELOS-97-NE- 01. 2) CF34-8C5 (All Models) and CF34-8E (All Models) - 14 CFR Part 33, effective February 1, 1965, including Amendments 33-1 through 33-20 3) All Engine models- 14 CFR Part 34, Amendment 7A, effective May 24, 2024. See NOTE 26 for detailed summary of the certification basis for fuel venting and exhaust emissions. MODEL APPLICATION DATE TYPE CERTIFICATE ISSUED/AMENDED CF34-8C1 May 1, 1997 Nov 30, 1999 CF34-8C5 May 31, 2000 Apr 12, 2002 CF34-8C5A1 May 31, 2000 Apr 12, 2002 CF34-8C5B1 May 31, 2000 Apr 12, 2002 CF34-8C5A2 May 31, 2000 Apr 12, 2002 CF34-8C5A3 May 31, 2000 Apr 12, 2002 CF34-8E2 May 31, 2000 Apr 12, 2002 CF34-8E2A1 May 31, 2000 Apr 12, 2002 CF34-8E5 May 31, 2000 Apr 12, 2002 CF34-8E5A1 May 31, 2000 Apr 12, 2002 CF34-8E5A2 May 31, 2000 Apr 12, 2002 CF34-8E6 May 31, 2000 Apr 12, 2002 CF34-8E6A1 May 31, 2000 Apr 12, 2002 CF34-8E5A2HA Dec 21, 2023 Sep 23, 2024 TCDS E00063EN Page 6 of 12 NOTES Notes 1 through 28 applicable to models as specified NOTE 1. Maximum permissible engine operating speeds for the engine rotors are as follows: Low pressure rotor (N1), rpm CF34-8C 1 CF34-8C5 (all models) CF34-8E (all models) Maximum takeoff 7360 7360 7360 Normal takeoff 7247 7360 7360 Maximum continuous 7360 7360 7360 High pressure rotor (N2), rpm Maximum takeoff 17710 17710 17710 Normal takeoff 17515 17710 17710 Maximum continuous 17437 17470 17470 Refer to GE Engine Manual GEK 105091 (CF34-8C1/8C5 models), GEK 112031 (CF34-8E models) and other manual or inspection requirements when limits are exceeded. 100 percent N1 rotor speed is 7,400 rpm, 100 percent N2 rotor speed is 17,820 rpm. NOTE 2. Maximum permissible temperatures are as follows: Interturbine temperature (T45)*, °F(°C) CF34-8C1 CF34-8C5 CF34-8C5A1 CF34-8C5B1 CF34-8C5A2 Maximum takeoff (5 min) See Note 18 1760 (960)** 1814 (990) - - - - - - Maximum takeoff (2 min. out of a total of 5 minutes) *** 1794 (979)** 1843 (1006) - - - - - - Normal takeoff (5 min) 1689 (920)** 1736 (947) 1754 (957) 1738 (948) 1783 (973) Normal takeoff (2 min. out of a total of 5 minutes)*** 1723 (939)** 1765 (963) 1783 (973) 1767 (964) 1812 (989) Maximum continuous 1701 (927)** 1760 (960) - - - - - - CF34-8C5A3 Maximum takeoff (5 min) See Note 18 1814 (990) Maximum takeoff (2 min. .out of a total of 5 minutes)*** 1843 (1006) Normal takeoff (5 min) 1814 (990) Normal takeoff (2 min. . out of a total of 5 minutes)*** 1843 (1006) Maximum continuous 1760 (960) NOTE 2. (continued) Maximum permissible temperatures are as follows: Interturbine temperature (T45)*, °F(°C) TCDS E00063EN Page 7 of 12 CF34-8E2 CF34-8E2A1 CF34-8E5 CF34-8E5A1 CF34-8E5A2 Maximum takeoff (5 min) See Note 18 1814 (990) - - - - - - - - Maximum takeoff (2 min. out of a total of 5 minutes)*** 1843 (1006) - - - - - - - - Normal takeoff (5 min) 1755 (957) 1814 (990) 1740( 949) 1783 (973) 1814 (990) Normal takeoff (2 min. out of a total of 5 minutes)*** 1784 (973) 1843 (1006) 1769 (965) 1812 (989) 1843 (1006) Maximum continuous 1760 (960) - - - - - - - - CF34-8E5A2HA CF34-8E6 CF34-8E6A1 Maximum takeoff (5 min) See Note 18 1814 (990) - - - - Maximum takeoff (2 min. out of a total of 5 minutes)*** 1843 (1006) - - - - Normal takeoff (5 min) 1814 (990) 1771 (966) 1814 (990) Normal takeoff (2 min. out of a total of 5 minutes)*** 1843 (1006) 1800 (982) 1843 (1006) Maximum continuous 1760 (960) - - - - *The interturbine temperature is measured by either 5 probes (5 thermocouples) or 10 probes (20 thermocouples) mounted in the low pressure turbine casing. ** For the CF34-8C1 engine model, maximum takeoff, normal takeoff and maximum continuous T45 limits may be exceeded transiently as a result of OBV activation provided T45 does not exceed 1869°F (1021°C) for 30 seconds, and does not exceed a temperature limit that ramps from 1869°F (1021°C) to 1794°F (979°C) over the next 30 seconds, as defined in GE Operating Instructions GEK 105094. The total number of transient occurrences as a result of OBV activation above a T45 of 1794°F (979°C) is limited to a maximum of 10 occurrences as defined in GE Engine Manual GEK 105091. *** The 2-minute interturbine temperature (T4.5) limits (2 minutes out of 5 minutes takeoff time) are intended to cover engine T4.5 overshoot characteristics which occur during engine stabilization at constant Takeoff thrust. For the CF34-8C1 engine model, additional transient temperature and time limits for starting are defined in GE Operating Instructions GEK 105094. Refer to GE Engine Manual GEK 105091 (CF34-8C1/8C5 models), GEK 112031 (CF34-8E models) for inspection requirements when limits are exceeded. Oil tank temperatures****, °F (°C) ALL MODELS Continuous operation 311 (155) Transient operation 325 (163) ****Transient operation above 311° F (155º C) is limited to 15 minutes. Fuel inlet temperature (at engine fuel filter inlet), °F (°C) ALL MODELS Continuous operation Jet A, Jet A1, Jet B 250 (121) JP8 250 (121) JP5 250 (121) JP4, JP4/JP5 mixture 250 (121) Ground Operation 250 (121) TCDS E00063EN Page 8 of 12 NOTE 3. FUEL AND OIL PRESSURE LIMITS Fuel: At engine pump inlet: minimum pressure of 5 PSID above the true vapor pressure of the fuel with a vapor/liquid ratio of zero with aircraft boost operative. Operating range 5 PSIG to 50 PSIG. At engine motive flow discharge: minimum pressure of 150 PSIG at idle or above. Operating range is 150 PSIG to 800 PSIG. See GE Installation Manual GEK 105093 (CF34- 8C1/8C5 models) and GEK 112033 (CF34-8E models) for additional limits. Oil: At idle on the ground the oil pressure limit is 25 PSID minimum . At takeoff, 45 PSID minimum.. Normal operating range, 25 PSID to 95 PSID. See GE Installation Manual GEK 105093 (CF34-8C1/8C5 models) and GEK 112033 (CF34-8E models) for additional limits. NOTE 4. ACCESSORY DRIVE PROVISIONS (ALL MODELS) Accessory Location on AGB Axis Speed (rpm) HP (Rated) Direction Of Rotation facing AGB Torque (lb-in) Static / Cont / Overload Max. Acc. Wt. (lb) Overhung Moment (lb-in) Shear Torque (lb-in) Lube/Scav Oil Pump Axis-C Fwd 7898 6 CCW 300 /48/ NA (1) 10.3 33 750-850 IDG Axis-C Aft 7898 74.8 (2) CW 675 (1) /597/ 1129 (5 min)(4) 1605 (5 sec)(4) 81.2 (6) 720 Maximum 3144- 3648 Air Turbine Starter Axis-D Aft 12234 N/A CW 2112, 4200 (3) / NA / NA 27.7 113 6300- 7500 Hydraulic Pump Axis-G Fwd 4825 30 CW 573 (1) (5) / 392 / 670 14.7 Dry 43.5 2004 max Alternator Axis-E Aft 8103 4 CCW NA / NA / NA 3.0 2.6 N/A Fuel Pump Axis-F Aft 8319 40 CW 180 (1) /303/NA 23 113 1255- 1380 CW - Clockwise CCW - Counter Clockwise Accessory Speeds are based on Core Speed: 17000 rpm (1) -40° F SLS (2) HP is constant over the operating range with slight variations due to changes in efficiency. HP extraction is 74.8 HP at 7898 rpm (pad speed) and 73.5 HP at 4618 rpm (pad speed). The 5 minute overload rating is 82.7 HP and the 5 second overload rating is 117.6 HP. (3) 2112 in-lbs at 59° F SLS, 4200 in-lbs at –40° F SLS (4) Overload at 4618 rpm (pad speed) (5) 573 in-lbs at 626 rpm (pad speed) (6) Includes oil and V band coupling NOTE 5. Engine ratings are based on calibrated test stand performance under the following conditions: 1. Static sea level standard conditions of 59° F and 29.92 inches Hg. 2. No aircraft accessory loads or air extraction. 3. No anti-icing; no inlet distortion; no inlet screen losses; and 100% ram recovery. 4. Inlet bellmouth and cowl system as described in GE Installation Manual GEK 105093 (CF34-8C1/8C5 models) and GEK 112033 (CF34-8E models). 5. Specified fuel having an average lower heating value of 18,500 BTU/lb (CF34-8C1/-8C5 models); 18,550 BTU/lb (CF34 –8E models); specified lube oil. NOTE 6. Air Bleed Extraction - maximum customer air bleed extraction is as follows: Customer bleed air is available from either stages 6 or 10 (compressor discharge) of the compressor at all operating conditions at or above idle. (No compressor bleed is permitted below idle.). Customer bleed is scheduled to switch from stage 10 bleed at low power operation to stage 6 TCDS E00063EN Page 9 of 12 bleed at high power operation as described in GE Installation Manual GEK 105093 (CF34-8C1/8C5 models), and GEK 112033 (CF34-8E models). Location Maximum Demonstrated Bleed Air (% of Total Compressor Airflow) CF34-8C1 CF34-8C5 CF34-8E (all models) (all models) Compressor Stage 6 8 8 8 Compressor Stage 10 (Compressor Discharge) 12.75 12.75 12.0 Maximum Allowable Bleed --- 12.75 12.0 NOTE 7. A minimum core speed (N2) must be maintained to ensure engine operation in icing conditions. The FADEC Power Management controls ground and flight idle core speeds above the minimum speed demonstrated for 14 CFR 33.68, Induction System Icing. At low ambient temperatures, the minimum permissible ground and flight idle speeds correspond to N2=58.47% (9,940 rpm) which is a non-adjustable limit, preset in the FADEC Power Management schedules. As ambient temperatures increase, the minimum permissible core speed increases as scheduled by the FADEC Power Management based upon N2 or PS3 control schedules. NOTE 8. The maximum permissible inlet distortion for these engines is specified in GE Installation Manual GEK 105093 (CF34- 8C1/8C5 models) and GEK 112033 (CF34-8E models). NOTE 9. For the CF34-8E model series, the engine manufacturer supplies the Nacelle System. The following Aft Core Cowl and Thrust Reverser systems, which are a part of this Nacelle system, have been certified for the listed engine models under this type certificate in accordance with Federal Aviation Regulation (FAR), Part 33. The FAR 33 engine type design definition is provided by: ENGINE MODEL LIST AFT CORE COWL PARTS LIST THRUST REVERSER PARTS LIST CF34-8E2 15F0001 15G0001 CF34-8E2A1 15F0001 15G0001 CF34-8E5 15F0001 15G0001 CF34-8E5A1 15F0001 15G0001 CF34-8E5A2 15F0001 15G0001 CF34-8E5A2HA 15F0001 15G0001 CF34-8E6 15F0001 15G0001 CF34-8E6A1 15F0001 15G0001 NOTE 10. Life limits, established for critical components, are published in FAA approved GE Engine Manual GEK 105091 (CF34- 8C1/8C5 models) and GEK 112031 (CF34-8E models). NOTE 11. Recommended maintenance inspection intervals are published in GE Engine Manual GEK 105091 (CF34-8C1/8C5 models) and GEK 112031 (CF34-8E models). NOTE 12. The operating temperature limit for specific components and accessories specified in GE Installation Manual GEK 105093 (CF34-8C1/8C5 models) and GEK 112033 (CF34-8E models) must be observed when installing the engine. TCDS E00063EN Page 10 of 12 NOTE 13. For CF34-8C1, CF34-8C5 (all models) and CF34-8E (all models), static thrusts at sea level are rated at 86ºF ambient temperature and below for normal takeoff and maximum takeoff. Maximum Continuous thrust is rated at 77ºF and below at cruise altitudes. The computer performance decks for calculating engine performance are as follows: Engine Model Computer Deck No. CF34-8C1 L0073A CF34-8C5 G0175C CF34-8C5A1 G0175C CF34-8C5B1 L0073A CF34-8C5A2 G0175C CF34-8C5A3 G0175C CF34-8E2 G0175D CF34-8E2A1 G0175D CF34-8E5 G0175D CF34-8E5A1 G0175D CF34-8E5A2 G0175D CF34-8E5A2HA G0175D CF34-8E6 G0175D CF34-8E6A1 G0175D NOTE 14. CF34-8C1, CF34-8C5 (all models) and CF34-8E (all models), engines comply with the applicable fuel venting and exhaust emission requirements of Part 34, Amendment 7A, effective May 24, 2024. NOTE 15. The time limit at the normal takeoff rating is five minutes and shall include any time accumulated above the normal takeoff rating. NOTE 16. TIME LIMITED DISPATCH CRITERIA Criteria pertaining to the dispatch and maintenance requirements for the engine control systems are specified in the airworthiness section of the Engine Manuals, GEK 105091 (CF34-8C1/8C5 models) and GEK 112041 (CF34-8E models), which define the various configurations and maximum operating intervals. NOTE 17. Overhaul of the CF34-8C1, CF34-8C5 (all models) and CF34-8E (all models), components is only authorized via approved component manuals. NOTE 18. The 5 minute maximum takeoff time limit may be extended to 10 minutes for one engine inoperative operation in multi-engine aircraft. NOTE 19. Refer to Operating Instructions GEK 105094 (CF34-8C1/8C5 models) and GEK 112034 (CF34-8E models) for engine warm-up procedure. NOTE 20. Refer to Operating Instructions GEK 105094 (CF34-8C1/8C5 models) and GEK 112034 (CF34-8E models) for thrust reverser operation. NOTE 21. The CF34-8C1, CF34-8C5 (all models), and CF34-8E (all models), engine normal takeoff interturbine temperature (T45) limit has been established to assure that a fully degraded engine at the normal takeoff rating will achieve the maximum takeoff rated thrust without exceeding the maximum takeoff T45 limit. NOTE 22. The above models incorporate the following characteristics: Model Characteristics CF34-8C1 Basic Model CF34-8C5 Derivative of CF34-8C1; side mounted; increased T45 and thrust rating CF34-8C5A1 Derivative of CF34-8C1; side mounted; increased T45 and thrust rating CF34-8C5B1 Derivative of CF34-8C1; side mounted; increased T45 CF34-8C5A2 Derivative of CF34-8C1; side mounted; increased T45 and thrust rating CF34-8C5A3 Derivative of CF34-8C1; side mounted; increased T45 and thrust rating CF34-8E2 Derivative of CF34-8C1; top mounted; increased T45; includes thrust reverser and aft core TCDS E00063EN Page 11 of 12 cowl CF34-8E2A1 Derivative of CF34-8C1; top mounted; increased T45; includes thrust reverser and aft core cowl CF34-8E5 Derivative of CF34-8C1; top mounted; increased T45 and thrust rating; includes thrust reverser and aft core cowl CF34-8E5A1 Derivative of CF34-8C1; top mounted; increased T45 and thrust rating; includes thrust reverser and aft core cowl CF34-8E5A2 Derivative of CF34-8C1; top mounted; increased T45 and thrust rating; includes thrust reverser and aft core cowl CF34-8E5A2HA Derivative of CF34-8C1; top mounted; increased T45 and thrust rating; includes thrust reverser and aft core cowl CF34-8E6 Derivative of CF34-8C1; top mounted; increased T45 and thrust rating; includes thrust reverser and aft core cowl CF34-8E6A1 Derivative of CF34-8C1; top mounted; increased T45 and thrust rating; includes thrust reverser and aft core cowl NOTE 23. The engine is equipped with an Automatic Power Reserve (APR) function for takeoff operation with one engine inoperative. During normal takeoff (NTO), when the automatic power reserve function is activated, the engine control of the inoperative engine sends an input signal to the engine control of the operating engine. Upon receiving this signal, the engine thrust of the operating engine automatically increases from normal takeoff or lower thrust to the corresponding, pre-determined maximum takeoff (MTO) thrust. If one engine is inoperable full MTO thrust is available to the pilot at any time by throttle selection. The engine control system also incorporates schedules that assure a fully degraded engine, during operation, at the NTO or lower thrust, will achieve the specified MTO thrust without exceeding the engine operating limits when the automatic power reserve function is activated. NOTE 24. A suffix may be added to CF34-8 basic engine model numbers on the engine nameplate to identify minor variations in the engine configuration, installation components, or differences specific to aircraft requirements, for example, CF34-8C5/M. Service Bulletin (SB) 72-0235 describes the conversion of the base model to a minor model (with /M designation) and Service Bulletin (SB) 72-0244 describes the conversion from the minor model back to the base model. Only those designations and purposes listed below may be used. The SB number must be appended to the engine nameplate. Life limits for the /M minor model designation, established for critical components, are published in FAA approved GE Engine Manual GEK 105091 (CF34-8C1/8C5 models). Allowable suffix designations: Designation: Purpose: