# TCDS E8NE: General Electric Company GE Aviation - Type: Type certificate data sheet - Status: Current - Holder: General Electric Company GE Aviation - Revision: 42 - Revised: July 3, 2025 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 84, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/a4/51/a451d48fbfe19995649e77f579a6bf8b0ce85f5856925a081eaab16ad26187f2 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID131722953820250702203956.0001 - Page: https://openairdocs.org/tcds/E8NE ## Models (30) As the data sheet lists them. - CT7-6A - CT7-9C - CT7-7A - CT7-2A - CT7-7A1 - CT7-8A7 - CT7-8E - CT7-9D2 - CT7-9B - CT7-9C3 - CT7-2D - CT7-2D1 - CT7-8A - CT7-8F5 - CT7-8 - CT7-5A3 - CT7-2E1 - CT7-8A6 - CT7-9B2 - CT7-9D - CT7-8E5 - CT7-8F - CT7-8B5 - CT7-8B - CT7-8A1 - CT7-9B1 - CT7-6 - CT7-2F1 - CT7-5A2 - CT7-8A5 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text MODELS: CT7- 2A/2D/ 2E1 2F1 6/6A 8 5A2 5A3 7A/ 9B/9C/ 9B1/ 9D/ 2D1 7A1 9C3 9B2 9D2 Maximum Continuous (SL) Equivalent Shaft hp --- --- --- --- --- 1,660 --- 1,764 --- --- --- Shaft hp 1,595 1871 1,712 1,718 2,043 1,600 1,600 1,700 1,750 1,750 1,750 Thrust, lb --- --- --- --- --- 150 --- 160 --- --- --- Output, rpm 21,000 21,000 21,000 20,463 21,945 1,384 (1) 1,384 (1) 1,384 (1) 1,384 (1) 1,384 (1) 1,384 (1) Normal Takeoff (5 min) (SL) Equivalent Shaft hp --- --- --- --- --- 1,800 --- 1,764 --- --- --- Shaft hp 1,625 1985 1,979 2,000 2,520 1,735 1,665 1,700 1,750 1,750 1,750 Thrust, lb --- --- --- --- --- 164 --- 160 --- --- --- Output, rpm 21,000 21,000 21,630 20,463 21,945 1,384 (1) 1,384 (1) 1,384 (1) 1,384 (1) 1,384 (1) 1,384 (1) Maximum Takeoff (5 min) (SL) Shaft hp --- --- --- --- --- --- 1,785 --- 1,870 1,950 1,940 Output, rpm --- --- --- --- --- --- 1,384 (1) --- 1,384 (1) 1,384 (1) 1,384 (1) 30 Minute (SL) --- --- Shaft hp --- --- 2,336 --- --- --- --- --- --- Output, rpm --- --- 21,945 --- --- --- --- --- --- (1) Output for these turboprop models is specified as nominal propeller speed (gear-reduced Np). 1,384 rpm is not a rating or limitation and is presented for reference only. The limit for c ontinuous operation is 1,396 rpm. See NOTE 7. TCDS NUMBER E8NE REVISION: 42 General Electric Company U.S. DEPARTMENT OF TRANSPORTATION MODELS: CT7-2A CT7-7A CT7-8B CT7-9B FEDERAL AVIATION ADMINISTRATION CT7-2D CT7-7A1 CT7-8B5 CT7-9B1 TYPE CERTIFICATE DATA SHEET NO. E8NE CT7-2D1 CT7-2E1 CT7-8 CT7-8A CT7-8E CT7-8E5 CT7-9B2 CT7-9C CT7-2F1 CT7-5A2 CT7-8A1 CT7-8A5 CT7-8F CT7-8F5 CT7-9C3 CT7-9D CT7-5A3 CT7-6 CT7-8A6 CT7-8A7 CT7-9D2 CT7-6A July 3, 2025 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E8NE) and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certified 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 Aviation 1000 Western Avenue Lynn, MA 0191 0 (USA) TYPE CT7- Axial flow, free-turbine turboshaft. Five-stage axial / single-stage centrifugal compressor; annular combustion chamber; two-stage gas generator turbine; two-stage power turbine. Full Authority Digital Engine Control (FADEC) only for the CT7-2E1/2F1/8/8A/8A1/8A5/8A6/8A7/8B/8B5/8E/8E5/8F/8F5 models. 2A/2D/2D1/2E1/2F1/6/6A/8/8A /8A1/8A5/8A6/8A7/8B/8B5/ 8E/8E5/8F/8F5 CT7-5A2/5A3/7A/7A1/9B/ Axial flow, free-turbine turboprop. Five-stage axial / single-stage centrifugal compressor; annular combustion chamber; two-stage gas generator turbine; two-stage power turbine; integral propeller gearbox. 9B1/9B2/9C/9C3/9D/9D2 Ratings are AEO unless labeled OEI. RATINGS (See NOTES 5 and 11) SL: Sea level PAGE 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 42 39 42 35 41 39 37 41 41 42 39 39 40 41 37 41 37 40 LEGEND: "---" NOT APPLICABLE TCDS E8NE Page 2 of 18 MODELS: CT7- 2A/2D/ 2E1 2F1 6/6A 8 5A2 5A3 7A/ 9B/9C/ 9B1/ 9D/ 2D1 7A1 9C3 9B2 9D2 Continuous OEI (SL) Shaft hp --- 1985 1,979 2,000 --- --- --- --- --- --- --- Output, rpm --- 21,000 21,630 20,463 --- --- --- --- --- --- --- 30-minute OEI (SL) Shaft hp 1,625 --- --- --- 2,498 --- --- --- --- --- --- Output, rpm 21,000 --- --- --- 21,945 --- --- --- --- --- --- 2½-minute OEI (SL) Shaft hp 1,725 --- --- 2,000 --- --- --- --- --- --- --- Output, rpm 21,000 --- --- 20,463 --- --- --- --- --- --- --- 2-minute OEI (SL) Shaft hp --- --- 2,054 --- 2,520 --- --- --- --- --- --- Output, rpm --- --- 21,630 --- 20,848 --- --- --- --- --- --- 30-second OEI (SL) Shaft hp --- --- 2,129 --- 2,600 --- --- --- --- --- --- Output, rpm --- --- 21,630 --- 20,848 --- --- --- --- --- --- Flat 30-sec/2-min OEI (SL) Shaft hp --- 2214 --- --- --- --- --- --- --- --- --- Output, rpm --- 21,000 --- --- --- --- --- --- --- --- --- MODELS: CT7- 8A 8A1 8A5 8A6 8A7 8B 8B5 8E 8E5 8F 8F5 Maximum Continuous (SL) Shaft hp 2,043 2,041 2,157 2,329 2,323 2,041 2,154 2,041 2,154 1,960 2,151 Output, rpm 21,945 21,527 21,945 21,945 21,527 20,900 20,900 20,872 20,872 20,841 20,841 Normal Takeoff (5 min) (SL) Shaft hp 2,520 2,538 2,634 2,695 2,685 2,529 2,609 2,527 2,608 2,474 2,603 Output, rpm 21,945 21,527 21,945 21,945 21,527 20,900 20,900 20,872 20,872 20,841 20,841 30 Minute (SL) Shaft hp 2,336 2,334 2,544 2,637 2,627 2,489 2,529 2,488 2,528 2,383 2,524 Output, rpm 21,945 21,527 21,945 21,945 21,527 20,900 20,900 20,872 20,872 20,841 20,841 Continuous OEI (SL) Shaft hp 2,498 2,495 2,544 2,637 2,627 2,489 2,529 2,488 2,528 2,383 2,524 Output, rpm 21,945 21,527 21,945 21,945 21,527 20,900 20,900 20,872 20,872 20,841 20,841 2-minute OEI (SL) Shaft hp 2,520 2,502 2,606 2,684 2,667 2,523 2,606 2,522 2,604 2,430 2,599 Output, rpm 20,900 20,482 20,900 20,900 20,482 20,900 20,900 20,872 20,872 19,800 20,841 30-second OEI (SL) Shaft hp 2,740 2,712 2,769 2,845 2,788 2,740 2,769 2,739 2,767 2,624 2,762 Output, rpm 20,900 20,482 20,900 20,900 20,482 20,900 20,900 20,872 20,872 19,800 20,841 MODELS: CT7- 2A/2D 2D1 2E1 2F1 6/6A 8/8A/8A1/ 8E/8E5 8F5 9B/9B1/ 8B5/8F Fuel Control Hamilton Standard (P/N) JFC78-4 JFC78-4 --- --- JFC78-4 819700-9 819700-9 819700-9 JFC78-5 JFC78-5 (1) Woodward Governor (Model) --- 3470 --- --- --- --- --- --- --- 3470 FADEC (P/N) --- --- 5158T32 5158T32 --- 4110T55 4110T55 4110T55 --- --- FADEC (P/N) 5183T35(2) Fuel Boost pump Lear Siegler-Romec (P/N) RR53150 RR53150 RR53150 RR53150 RR53150 RR53150 RR53150 RR53150 RR53150 RR53150 Fuel (See NOTE 12) GE Jet Fuel Specification D50TF2 D50TF2 D50TF2 D50TF2 D50TF2 D50TF2 D50TF2 D50TF2 D50TF2 D50TF2 For specific approved fuels see Operating SEI- SEI- GEK GEK SEI- GEK GEK GEK SEI- SEI- Instructions: 569 569 112766 112102 694 105157 112153 114117 575 575 (1) Some CT7-9B/9C engines were shipped with Hamilton Standard JFC 78-5 Fuel Controls, which remain an alternate to the Woodward Governor unit on the CT7-9B/9B1/9B2/9C/9C3/9D/9D2. (2) 5183T35 on CT7-8A6 only RATINGS - Continued (See NOTES 5 and 11) RATINGS - Continued (See NOTES 5 and 11) FUEL SYSTEM 8A5/8A6/ 8A7/8B/ 5A2/5A3/ 7A/7A1 9B2/9C/9C3 /9D/9D2 TCDS E8NE Page 3 of 18 MODELS: CT7- 2E1 2F1 6/6A 8E/8E5 8F5 5A2/5A3/7A/ 8B/8B5/8F 9D/9D2 GE Oil Specification D50TF1 D50TF1 D50TF1 D50TF1 D50TF1 D50TF1 D50TF1 D50TF1 For specific approved oils, SEI- GEK GEK SEI- GEK GEK GEK SEI- see Operating Instructions: 569 112766 112102 694 105157 112153 114117 575 MODELS: CT7- 2A 2D 2D1 2E1 2F1 6/ 6A 8 8A/8A1/8A5/ 8A6/8A7/8B/ 8B5/8E/ 8E5/8F 8F5 5A2/5A3/ 7A/7A1 9B/9B1/ 9B2/9C/ 9D 9C3/ 9D2 Length (in) 47 47 47 47 47 48.2 48.8 48.8 42.3 96 96 96 Maximum diameter (in) --- --- --- --- --- --- --- --- --- --- --- --- Width (in) 26 26 26 26 26 26 26 26 26 26 26 26 Height (in) 25 25 25 26 26 25 25 25 25 29 29 29 Weight, dry (lb) 429 442 466 491 482 493 537 (1) 542 (1) 528 (1) 783 805 807 (1) Does not include cables from engine to FADEC. MODELS: CT7- 2A 2D 2D1 2E1 2F1 6/6A 8/8A/8A1/ 8F5 9B/9B1/9B2/ 8E/8E5/8F Aft of front mount centerline (in) 13.22 13.19 13.29 13.42 13.41 13.76 13.58 23.64 31.08 31.45 Above engine horizontal centerline (in) 1.38 1.39 1.40 1.19 1.17 1.25 1.98 1.10 2.75 2.73 Left of vertical centerline (in) 0.42 0.45 0.47 0.64 0.64 0.49 1.02 0.46 0.28 0.26 EXCITER UNIT IGNITER PLUG Supplier Part Number GE Part Number GE Part Number MODELS: CT7- 2A 48987 4040T18 4053T22 2D/2D1 44525 4068T11 5044T67 2E1/2F1 --- 5157T09 5044T67 5A2/5A3/6/6A/7A/7A1/9B/9B1/9B2/9C/9C3/9D/9D2 44525 4068T11 5044T67 8/8A/8A5/8A1/8A6/8A7/8B/8B5/8E/8E5/8F/8F5 9049950-1 3060T07 5044T67 OIL 2A/2D /2D1 8/8A/8A1/ 8A5/8A6/8A7/ 7A1/9B/9B1/ 9B2/9C/9C3/ PRINCIPAL DIMENSIONS (See NOTE 34) CENTER OF GRAVITY LOCATION 8A5/8A6/ 8A7/8B/8B5/ 5A2/5A3/ 7A/7A1 9C/9C3/ 9D/9D2 IGNITION SYSTEM, DUAL (Includes exciter unit and two igniter plugs) NOTES MODELS: CT7- 2A/2D/2D1 2E1 2F1 5A2/7A 5A3 6/6A 7A1 8 8A/8A1 8A6 8A7 8A5/8B/8B5/8E5/8F 8E 8F5 9B/9B1/9B2/9D 9C 9C3/9D2 See NOTES 1 through 18, 24, 34 and 44. See NOTES 1 through 17, 24, 29, 34 through 38 and 48. See NOTES 1 through 17, 24, 29, 34 through 37, 40, 48 and 50. See NOTES 1 through 17, 21 through 25, 33 and 34. See NOTES 1 through 17, 21 through 25, 30, 32 and 34. See NOTES 1 through 17, 24 and 34. See NOTES 1 through 17, 21 through 25 and 34. See NOTES 1 through 17, 24, 29, 34 through 38 and 40. See NOTES 1 through 17, 24, 29, 34 through 40. See NOTES 1 through 17, 24, 29, 34 through 38 and 40 See NOTES 1 through 17, 24, 29, and 34 through 40. See NOTES 1 through 17, 24, 29, 34 through 38 and 42. See NOTES 1 through 17, 24, 29, 34 through 38 and 49. See NOTES 1 through 17, 21, 24, 29, 34 through 38 and 43. See NOTES 1 through 17, 21 through 25, 29, 30, 33 and 34. See NOTES 1 through 17, 21 through 25, 28, 29, 30, 33 and 34. See NOTES 1 through 17, 21 through 25, 29, 30 and 34. TCDS E8NE Page 4 of 18 CERTIFICATION BASIS MODELS: CT7- 2A/2D/2D1 2E1 2F1 6/6A 8 8A/8A1/8A5/8B/8B5/8E/ 8E5/8F/8F5 8A6/8A7 5A2/5A3/7A/7A1/9B/9B1/ 9B2/9C/9C3/9D/9D2 14 CFR 33, effective February 1, 1965, as amended by amendments 33-1 through 33-5; Special Condition 33-76-NE-2. 14 CFR 33, effective February 1, 1965, as amended by amendments 33-1 through 33-20; Special Condition 33-012-SC; Equivalent Level of Safety memo AT3011EN-E-P-4. 14 CFR 33, effective February 1, 1965, as amended by amendments 33-1 through 33-20; Special Condition 33-002-SC; Equivalent Level of Safety memo AT3011EN-E-P-4. 14 CFR 33, effective February 1, 1965, as amended by amendments 33-1 through 33-5; 14 CFR 33.87, Amendment 12; Special Condition number 33-76-NE-2. 14 CFR 33, effective February 1, 1965, as amended by amendments 33-1 through 33-19; Special Conditions 33-002-SC and 33-003-SC. The inlet particle separator blower rotor was certified to 14 CF R 29.1461 as amended by amendment 29-3, instead of 14 CFR 33.27. 14 CFR 33, effective February 1, 1965, as amended by amendments 33-1 through 33-20; Special Conditions 33-002-SC and 33-005-SC. 14 CFR 33, effective February 1, 1965, as amended by amendments 33-1 through 33-20; Special Conditions 33-002-SC and 33-005-SC; Equivalent Level of Safety memo 8040-ELOS-12-NE04. 14 CFR 33, effective February 1, 1965, as amended by amendments 33-1 through 33-5; 14 CFR 33.17 an d 14 CFR 33.77 as amended by amendments 33-1 through 33-6; Special Condition 33-NE-1. TYPE CERTIFICATE NUMBER E8NE MODEL APPLIED FOR ISSUED/REVISED DELETED CT7-1 JUL 02 1974 JUN 29 1977 MAY 28 1981 CT7-2 FEB 02 1978 SEP 06 1978 JAN 15 1982 T700/T1C AUG 01 1977 SEP 06 1978 MAY 18 1983 T700/T2C OCT 10 1980 MAY 28 1981 JUL 30 1992 CT7-2A MAY 30 1980 MAY 28 1981 CT7-2B MAR 17 1982 MAY 18 1983 JUL 30 1992 CT7-5A AUG 06 1981 AUG 29 1983 OCT 02 1986 CT7-7 AUG 14 1981 AUG 29 1983 NOV 26 1985 CT7-7E JUL 08 1983 AUG 29 1983 NOV 26 1985 CT7-5A1/7A/7E1 APR 17 1984 MAY 15 1984 OCT 02 1986 CT7-7A APR 17 1984 MAY 15 1984 CT7-7E1 APR 17 1984 MAY 15 1984 NOV 26 1985 CT7-5A2 DEC 18 1984 MAR 25 1985 CT7-2D JUL 15 1985 AUG 22 1985 CT7-9B MAR 16 1987 JUN 17 1988 CT7-9C AUG 15 1985 JUN 17 1988 CT7-6/6A MAR 17 1987 JUN 30 1988 CT7-5A3/7A1 AUG 29 1988 MAR 16 1989 CT7-2D1 DEC 07 1988 JUN 30 1989 CT7-9B1/9B2/9D JUN 03 1991 JUN 24 1992 CT7-9C3/9D2 SEP 26 1997 JUN 25 1998 CT7-8 OCT 2 1996 SEP 29 2000 CT7-8A/8A5/8B/8B5/8E/8E5/8F/8F5 SEP 15 2003 APR 08 2004 CT7-8A1 JUN 12 2007 JUN 21 2010 CT7-8A6/8A7 MAY 20 2010 MAY 21, 2012 CT7-2E1 SEP 10, 2009 JUNE 12, 2013 CT7-2F1 JUN 29 2015 March 13, 2019 TCDS E8NE Page 5 of 18 MAXIMUM PERMISSIBLE GAS GENERATOR OPERATING SPEEDS (rpm) MODELS: CT7- 2A/2D/2D1 2E1 2F1 6/6A 8 8A/8A1/8A5/8B 8F5 8A6/8A7 / 8B5/8E/8E5/8F 30-second OEI --- --- 46,935 --- 46,340 46,340 46,340 46,340 2-minute OEI --- --- 46,935 --- 46,010 46,010 46,010 46,010 2½-minute OEI 46,070 --- --- 46,060 --- --- --- --- Flat 30-second/2-minute OEI --- 46,935 --- --- --- --- --- --- 30-minute OEI 45,430 --- --- --- 45,760 --- --- --- Continuous OEI --- 45,907 45,907 45,900 --- 45,760 46,010 46,010 Normal takeoff (5 min) 45,430 45,907 45,907 45,900 46,010 46,010 46,010 46,010 30-minute --- --- --- --- 45,350 45,760 46,010 46,010 Maximum continuous 45,240 45,907 45,907 45,420 44,660 44,660 44,660 44,950 Transient (12 sec) 47,000 46,137 46,137 47,440 46,120 46,120 46,120 46,120 Transient OEI (12 sec) 47,000 --- --- 47,440 --- --- --- --- MAXIMUM PERMISSIBLE GAS GENERATOR OPERATING SPEEDS (rpm) MODELS: CT7- 5A2 5A3 7A/7A1 9B/9C/9C3 9B1/9B2/ 9D/9D2 Normal takeoff (5 min) 45,000 44,650 45,000 45,288 (1) 45,100 Maximum takeoff --- 45,000 --- 45,600 45,600 Maximum continuous 44,720 44,720 44,720 45,600 45,600 Transient (12 sec) 47,000 47,000 47,000 47,000 47,000 APU (prop brake on) (2) (2) (2) (3) (3) (1) (2) (3) CT7-9C: See NOTE 28. Refer to Figure 6-5, SEI-575 Refer to Figure 6-6, SEI-575 IMPORT REQUIREMENTS: To be considered eligible for installation on United States (U.S.) registered aircraft, each engine to be exported to the U.S. shall be accompanied by a certificate of airworthiness for export or by a certifying statement, endorsed by the exporting cognizant civil airworthiness authority and containing the following language: 1. This engine conforms to its Type Certificate Number E8NE and is in a condition for safe operation. 2. This engine has been subjected by the manufacturer to a final operational check and is in a proper state of airworthiness. Reference 14 CFR Section 21.500, which provides for the airworthiness acceptance of aircraft engines manufactured outside of the U.S. and for which a U.S. type certificate has been issued. Additional guidance is contained in FAA Advisory Circular 21-23, “Airworthiness Certification of Civil Aircraft, Engine, Propellers and Related Products Imported into the United States.” PRODUCTION BASIS: FAA Production Certificate number 108. Transport Canada Manufacturing Approval Certificate number 231-91 for CT7-8A1/8A7 engine Serial Numbers 530001 to 530099 (See NOTE 39). EASA Production Organization Approval ES.21G.0016 for CT7-8F5 engine Serial Numbers 731004 to 731099 and 733001 to 733100 (See NOTE 43). EASA Production Organization Approval IT.21G.0008 for CT7-8E engine Serial Numbers 087001 to 087050 (See NOTE 49). NOTES Limitations are AEO unless labeled OEI. NOTE 1. NOTE 1. - Continued Overspe ed inspection, see NOTE 10. TCDS E8NE Page 6 of 18 MAXIMUM PERMISSIBLE TEMPERATURES MODELS: CT7- 2A 2D 2D1 2E1 2F1 6/6A 8 POWER TURBINE INLET (T4.5/ITT) (1) °C/°F °C/°F °C/°F °C/°F °C/°F °C/°F °C/°F 30-second OEI --- --- --- --- 1,078/1,972 --- 1010/1,851 2-minute OEI --- --- --- --- 991/1,815 --- 990/1,814 2½-minute OEI 915/1,680 911/1,671 858/1,577 --- --- 968/1,774 --- Flat 30-second/2-minute OEI --- --- --- 1101/2013 --- --- --- 30-minute OEI 878/1,613 873/1,603 858/1,577 --- --- --- 979/1,794 Continuous OEI --- --- --- 983/1802 963/1,765 948/1,738 --- Normal takeoff 878/1,613 873/1,603 858/1,577 983/1802 963/1,765 948/1,738 986/1,807 30-minute --- --- --- --- --- --- 957/1,755 Maximum continuous 863/1,585 858/1,576 841/1,546 957/1755 897/1,647 899/1,650 920/1,688 Transient (12 sec) 950/1,742 945/1,733 903/1,657 991/1816 974/1,785 1011/1,852 987/1,809 Transient OEI (12 sec) 950/1,742 945/1,733 903/1,657 --- --- 1011/1,852 --- Starting 950/1,742 945/1,733 903/1,657 963/1,766 963/1,765 948/1,738 1000/1,832 Oil inlet 150/302 150/302 150/302 150/302 150/302 150/302 149/300 (1) The power turbine inlet gas temperature is measured by 7 thermocouples mounted in the power turbine casing. For inspection requirements when limits are exceeded, refer to Maintenance Manual SEI-570 for CT7-2A/2D/ 2D1, GEK112043-02 for CT7-2E1, GEK112043-03 for CT7- 2F1, SEI-695 for CT7-6/6A, and GEK105159 for CT7-8. MAXIMUM PERMISSIBLE TEMPERATURES MODELS: CT7- (other models next page) 8A/8A1 8A5 8A6/8A7 8B 8B5/8E/8E5 /8F/8F5 POWER TURBINE INLET (T4.5/ITT) (2) °C/°F °C/°F °C/°F °C/°F °C/°F 30-second OEI 1,049/1,921 1,049/1,921 1,097/2,006 1,049/1,921 1,049/1,921 2-minute OEI 1,006/1,843 1,006/1,843 1,013/1,855 1,006/1,843 1,006/1,843 Continuous OEI 988/1,811 988/1,811 996/1,824 988/1,811 988/1,811 Normal takeoff 995/1,823 1,002/1,835 1,007/1,844 995/1,823 1,002/1,835 30-minute 988/1,811 988/1,811 996/1,824 988/1,811 988/1,811 Maximum continuous 935/1,715 935/1,715 946/1,734 935/1,715 935/1,715 Transient (12 sec) 1,003/1,838 1,003/1,838 1,008/1,847 1,003/1,838 1,003/1,838 Starting 1,000/1,832 1,000/1,832 1,000/1,832 1,000/1,832 1,000/1,832 Oil inlet 149/300 149/300 149/300 149/300 149/300 (2) The power turbine inlet gas temperature is measured by 7 thermocouples mounted in the power turbine casing . For inspection requirements when limits are exceeded, refer to Maintenance Manual GEK105159. MAXIMUM PERMISSIBLE TEMPERATURES MODELS: CT7- 5A2/7A/7A1 5A3 9B/9C3 9B1/9B2 9C 9D/9D2 POWER TURBINE INLET (T4.5/ITT) (3) °C/°F °C/°F °C/°F °C/°F °C/°F °C/°F Normal takeoff (5 min) Normal takeoff (2 min) (4) Maximum takeoff (5 min) (5) Maximum takeoff (2 min) (4) (5) Maximum continuous Transient (12 sec) Starting Oil inlet Propeller gearbox, continuous Transient (15 min) Power unit, continuous Transient (15 min) 930/1,705 919/1,687 917/1,683 907/1655 921/1,690 (6) 909/1,668 --- --- 927/1,701 917/1683 --- 919/1,686 --- 943/1,730 940/1,724 940/1,724 950/1,742 940/1,724 --- --- 950/1,742 950/1,742 --- 950/1,742 917/1,682 921/1,690 944/1,731 944/1,731 944/1,731 944/1,731 960/1,760 960/1,760 965/1,769 965/1,769 975/1,787 965/1,769 960/1,760 960/1,760 965/1,769 965/1,769 970/1,778 965/1,769 77/171 77/171 77/171 77/171 77/171 77/171 93/199 93/199 93/199 93/199 93/199 93/199 122/252 122/252 122/252 122/252 122/252 122/252 132/270 132/270 132/270 132/270 132/270 132/270 (3) The power turbine casing. For inspect Manual SEI-576 for CT7-5A2/5A3/7A/7A1/9B/9B1/9B2/ 9C/9C3/9D/9D2. (4) 2-minute tra nsient maximum during a 5-minute takeoff. (5) Automatic power reserve (APR). See NOTE 30. (6) See NOT E 28. NOTE 2. NOTE 2. - Continued NOTE 2. - Continued TCDS E8NE Page 7 of 18 FUEL PRESSURE LIMITS MODELS: All CT7 Models At engine boost pump inlet: For all operation, including starts, the minimum pressure shall be 1.0 psi above true vapor pressure of the fuel, with a vapor/liquid ratio less than or equal to 1.0. Maximum fuel pressure shall be 50 psi above absolute ambient atmospheric pressure. In addition, minimum fuel pressure during starting shall be no lower than atmospheric pressure (or tank pressure, whichever is higher) minus 2.8 psi. OIL PRESSURE LIMITS MODELS: CT7- 2A 2D/2D1/2E1/2F1/6/6A/8/8A/8A1/ 8F/8F5 9C/9C3/9D/9D2 Ground idle, minimum 20 psig 20 psid --- Operating range 40-100 psig 30-100 psid --- Power unit Ground idle, minimum --- --- 20 psid Operating range --- --- 30-100 psid Propeller gearbox Ground idle, minimum --- --- 5-25 psig Operating range --- --- 25-140 psig ACCESSORY DRIVE PROVISIONS Drive Type Rotation* Speed Maximum Torque (in-lb) Continuous Static MODELS CT7-2A/2D/2D1/6/6A/8/8A/ 8A1/8A5/8A6/8A7/8B/ 8B5/8E/8E5/8F Starter MS3326-2 (1) CW 0.64979 (2) 336 900(3)/1000 (4) CT7-8F5 Starter Clutch V-Band Pad (13) CW 0.64979 (2) 336 900(3)/1000 (4) CT7-2E1 Starter-Generator AS963-1 CCW 0.29736 730 (5) 1320 (3)/1470 (7) /1700 (10) CT7-2F1 Starter MS3326-2 (1) CW 0.64979 (2) 336 900(3)/550 (4) CT7-5A2/5A3/7A/7A1/9B/9B1 9B1/9B2/9C/9C3/9D/9D2 Starter-Generator AS963A-12V (8) CCW 0.26630 (2) 820 (5)/192 (6) 1530 (3)/1900 (10)/ 1645 (7) Propeller Gearbox Propeller shaft AS1414(8) CCW 0.06291 (9) (8) (8) Hydraulic pump MS3326(AS)-2 (8) CW 0.27932 (9) 123 (11) AC generator AS963A-12V (8) CW 0.54650 (9) 370(12) (12) Propeller overspeed governor MS3325(AS)-2 (8) CW 0.38091 (9) (11) Propeller control unit (13) CW 0.06291 (9) (11) (1) Modified (2) (3) (4) (5) (6) (7) (8) (9) (10) (11) (12) (13) Ratio to gas generator speed 3 seconds maximum duration Maximum axial impact force, pounds Starter Generator mode for 3 minutes restricted at gr Unrestricted maximum is 112 in-lb 0.05 seconds maximum duration Modified For CT7-5A2/5A3/7A/7A1 see Installation Manual SEI-585 For CT7-9B/9B1/9B2/9C/9C3/9D/9D2 see Installation Manual SEI-726 Ratio to power turbine speed Shear torque for starter/generator shaft shear section Overtorque allowance minimum of 1.5 x maximum normal rated torque for 10 8 cycles and minimum of 5 x maximum normal rated torque as a limit load. Maximum overload up to 415 in-lb for 5 minutes For CT7-8F5 see Installation Manual GEK 114116 For CT7-5A2/5A3/7A/7A1 see Installation Manual SEI-585 For CT7-9B/9B1/9B2/9C/9C3/9D/9D2 see Installation Manual SEI-726 NOTE 3. 8A5/8A6/8A7/8B/8B/ 8E/8E5/ 5A2/5A3/7A/7A1/9B/9B1/9B2/ NOTE 4. * Facing engine pad, CW = CLOCKWISE CCW = COUNTERCLOCKWISE TCDS E8NE Page 8 of 18 NOTE 5. Engine ratings are based on calibrated test stand performance under the following conditions: CT7-2A/2D/2D1/6/6A/ 8/8A/8A5/8A6/8A7/8B/ 8B5/8E/8E5/8F/8F5/8A1 Static sea level standard conditions of 59oF and 29.92 inches Hg. GE Aviation air inlet, GE Aviation P/N 1076662-542 (CT7-2A/2D/2D1) or P/N 17A132-505 (CT7-8/8A/8A1/ 8A5/8A6/8A7-8B/8B5/8E/8E5/8F/8F5), and shaft shield, P/N 17A132-506 or GE Aviation P/N 1076662-486 (CT7-6/6A), and shaft shield, GE Aviation P/N 1076662-592. CT7-8F5 outer bellmouth adapter, P/N 17A210-005, and inner bellmouth adapter, P/N 17A210-004. No external air bleed for aircraft accessories. Exhaust configuration as defined by GE Aviation P/N 1076662-524 or P/N 1076662-554 (CT7-8/8A/8A1/8A5/8A6/8A7/8B/8B5/8E/8E5/8F/8F5). No anti-icing airflow. For additional performance data, refer to the engine specifications and customer decks included with the specific GE/airframe contract. Power ratings for the CT7-8A/8A1/8A6/8A7/8E/8F5 are based on operating in test cell mode (engine capabilities), which disables the EECU torque limiting corresponding to the rotorcraft capabilities. In their respective rotorcraft installations, the EECU applies torque limits of: CT7-8A/8A1/8A6/8A7 8A 8A1 8A6 8A7 30-Second OEI 703.3 701.8 698.4 698.4 ft-lb 2-Minute OEI 598.6 603.6 598.6 698.4 ft-lb Continuous OEI 598.6 603.6 598.6 653.5 ft-lb Normal Takeoff 548.7 553.2 548.7 568.2 ft-lb CT7-8E/8F5 8E 112% MGB Config (SW v5.20) 8E 117% MGB Config (2) (SW v5.31) 8F5 30-Second OEI 568.2 568.2 N/A ft-lb 2-Minute OEI 568.2 522.3 602.0 ft-lb Continuous OEI 568.2 467.9 N/A ft-lb AEO 467.9 488.8 602 ft-lb Notes: 1. Both SW v5.20 and SW v5.31 ramps to 30 sec OEI limits as needed in rotor droop conditions for OEI and AEO. 2. Compliance to SB # 74-0026 required for MGB torque increase. MGB: Main Gearbox CT7-5A2/7A Static sea level standard conditions of 59°F and 29.92 inches Hg. No inlet system loss, no anti-icing, no customer bleed or power extraction. Exhaust system specified per Note 36 on the installation drawing. For additional performance data, refer to the engine specifications and customer decks included with the specific GE/airframe contract. CT7-5A2 takeoff flat rated to 93°F, maximum continuous flat rated to 95°F. CT7-7A takeoff flat rated to 91°F, maximum continuous flat rated to 86°F. CT7-5A3/7A1 Static sea level standard conditions of 59°F and 29.92 inches Hg. No inlet system loss, no anti-icing, no customer bleed or power extraction. Exhaust system specified per Note 36 on the installation drawing. TCDS E8NE Page 9 of 18 For additional performance data, refer to the engine specifications and customer decks included with the specific GE/airframe contract. CT7-5A3 maximum takeoff flat rated to 93°F, normal takeoff flat rated to 93°F, maximum continuous flat rated to 95°F. CT7-7A1 takeoff flat rated to 97°F, maximum continuous flat rated to 86°F. CT7-9B/9B1/9B2/9C/ Static sea level standard conditions of 59ºF and 29.92 inches Hg. 9C3/9D/9D2 No inlet system loss, no anti-icing, no customer bleed or power extraction. Exhaust system specified per Note 36 on the installation drawing. For additional performance data, refer to the engine specifications and customer decks included with the specific GE/airframe contract. CT7-9B maximum takeoff flat rated to 93°F, normal takeoff flat rated to 93°F, maximum continuous flat rated to 91°F. CT7-9B1 maximum takeoff flat rated to 84°F, normal takeoff flat rated to 93°F, maximum continuous flat rated to 91°F. CT7-9B2 maximum takeoff flat rated to 93°F, normal takeoff flat rated to 93°F, maximum continuous flat rated to 91°F. CT7-9C maximum takeoff flat rated to 95°F, normal takeoff flat rated to 106°F, maximum continuous flat rated to 106°F. CT7-9C3 maximum takeoff flat rated to 101°F, normal takeoff flat rated to 101°F, maximum continuous flat rated to 106°F. CT7-9D maximum takeoff flat rated to 86°F, normal takeoff flat rated to 91°F, maximum continuous flat rated to 97°F. CT7-9D2 maximum takeoff flat rated to 93°F 34ºC, normal takeoff flat rated to 93°F, maximum continuous flat rated to 97°F. CT7-2E1 Static sea level standard conditions of 59°F and 29.92 inches Hg. GE Aviation P/N 1076662-542 air inlet, and P/N 1076662-592 shaft shield. No inlet system loss, anti-icing airflow, customer bleed airflow or power extraction. Exhaust configuration as defined by GE Aviation P/N 1076662-524 or P/N 1076662-554. Power ratings for the CT7-2E1 are based on operating in test cell mode (engine capabilities), which disables the EECU torque limiting corresponding to the rotorcraft capabilities. In its rotorcraft installation, the EECU applies torque limits of: 30-minute 355.5 ft-lb 30-Second OEI 527.2 ft-lb 2-Minute OEI 499.6 ft-lb Continuous OEI 435.2 ft-lb TCDS E8NE Page 10 of 18 POWER TURBINE OPERATING RANGE (rpm) MODELS: CT7- 2A/2D/2D1 2E1 2F1 6/6A 8/8A/8A5 8A1 8A6 8A7 8B/8B5 8E/8E5 8F/8F5 Transient (12 sec) 22,500 23,100 23,100 25,300 24,350 24,350 24,350 24,350 24,350 24,350 24,350 Maximum permissible 21,000 22,000 22,000 22,200 22,200 22,200 22,200 22,200 22,200 22,200 22,200 Maximum governing 21,000 22,000 22,000 21,000 21,945 21,542 21,945 21,542 20,900 20,872 20,841/21,675* Nominal 21,000 21,420 21,630 20,463 21,945 21,542 21,945 21,542 20,900 20,872 20,841 Minimum governing 19,000 --- --- 18,200 --- --- --- --- --- --- --- *Higher speed is only available for the 8F5 aircraft configured for the higher maximum governing speeds. For additional performance data, refer to the engine specifications and customer decks included with the specific GE/airframe contract. CT7-2F1 Static sea level standard conditions of 59°F and 29.92 inches Hg. GE Aviation P/N 1076662-542 air inlet, and GE Aviation P/N 1076662-592 shaft shield. No inlet system loss, anti-icing airflow, customer bleed airflow or power extraction. Exhaust configuration as defined by GE Aviation P/N 1076662-524 or P/N 1076662-554. Power ratings for the CT7-2F1 are based on operating in test cell mode (engine capabilities), which disables the EECU torque limiting corresponding to the rotorcraft capabilities. In its rotorcraft installation, the EECU applies torque limits of: Torque Limit (per engine) ft-lbs * Total Torque Limit (two engines) ft-lbs Contingency/OEI 30 second 530 963* 2 minute 530+ 963* Continuous 456+ 963* AEO 30 second OEI 530 963** 5 minute take off 515+ 770+ Max continuous 490+ 688+ *Note that, because an engine may determine that it is in an OEI situation when, in fact the other engine is producting power, Two engine limits are applied in OEI. **AEO limits are set at the 30 sec OEI limits nominally. +Limits are based on bits sent to engine by aircraft. The aircraft may or may not choose to use these bits. For additional performance data, refer to the engine specifications and customer decks included with the specific GE/airframe contract. NOTE 6. CT7-2A/2D/2D1/2E1/2F1/ Maximum permissible customer air bleed extraction is 6.5 percent. 6/6A/8/8A/8A1/8A5/ 8A6/8A7/8B/8B5/ 8E/8E5/8F CT7-8F5 Maximum permissible customer air bleed extraction is 4.0 percent. CT7-5A2/5A3/7A/7A1 Customer bleed air is provided through two bleed ports (mid-compressor and compressor discharge). At the mid-compressor port, maximum allowable bleed (no engine anti-icing airflow) is 6.5 percent. Maximum allowable bleed airflow at the compressor discharge bleed port is approximately 8 percent in flight and 12 percent while in APU mode. See CT7-5A2/5A3/7A/7A1 Installation Manual SEI-585. CT7-9B/9B1/9B2/9C/ Customer bleed air is provided through two bleed ports (mid-compressor and compressor discharge). At the 9C3/9D/9D2 mid-compressor bleed port, maximum allowable bleed (no engine anti-ice airflow) is 6.5 percent. Maximum allowable bleed airflow at the compressor discharge bleed port is approximately 8 percent in flight and 12 percent while in APU mode. See CT7-9B/9B1/9B2/9C/9C3/9D/9D2 Installation Manual SEI-726. NOTE 7. TCDS E8NE Page 11 of 18 POWER TURBINE OPERATING RANGE (rpm) MODELS: CT7- 5A2/5A3/7A/7A1 9B/9B1/9B2/9C/9C3/9D/9D2 Transient (12 sec) 25,240 25,240 Maximum permissible 1,396 (1) 22,200 Maximum governing --- --- Nominal rating 1,384 (1) 22,000 Minimum governing 970 19,855 (1) Output for these turboprop models is specified as propeller speed (gear reduced Np). POWER TURBINE SHAFT TORQUE LIMITS (ft-lb) MODELS: CT7- 2E1 2F1 6/6A 8 8A/8A1/ 8A6/8A7 8F5 5A2 5A3 7A/7A1 9B/9B1/ 2A/2D/ 8A5/8B/ 9B2/9C/ 2D1 8B5/8E/ 9C3/9D/ 8E5/8F 9D2 30-second OEI --- --- 575 --- 676 702 734 734 --- --- --- --- 2-minute OEI --- --- 575 --- 636 660 702 660 --- --- --- --- Flat 30-second/2-minute OEI --- 575 --- --- --- --- --- --- --- --- --- --- 2½-minute OEI --- --- --- 560 --- --- --- --- --- --- --- --- 30-minute OEI 500 --- --- --- 604 --- --- --- --- --- --- --- Continuous OEI --- 515 515 547 --- 640 660 640 --- --- --- --- Normal takeoff (5 min) 500 515 515 547 603 660 676 660 420 404 413 510 Maximum takeoff (5 min) --- --- --- --- --- --- --- --- --- 433 433 510 30-minute --- --- --- --- 574 640 660 640 --- --- --- --- Maximum continuous 450 490 490 488 525 610 610 610 389 389 389 460 Transient (12 sec) 700 545 545 700 638 777 777 777 500 500 500 600 NOTE 7. - Continued Overspeed inspection, see NOTE 10 NOTE 8. TCDS E8NE Page 12 of 18 SEA LEVEL STATIC POWER LIMITS BELOW 59°F These ratings and the limitations on the usage of them are defined in Title 14, Code of Federal Regulations (14 CFR). MODELS: CT7- 2A/2D/2D1 2E1 2F1 6/6A 5A2/5A3/7A/7A1/ 9B/9B1/9B2/9C/ 9C3/9D/9D2 30-second OEI Decreases linearly to 1940 shp at -58°F 2-minute OEI Decreases linearly to 1940 shp at -58°F Flat 30-second/ --- Decreases linearly to --- --- --- 2-minute OEI 2033 shp at -58°F 2½-minute OEI Increases linearly to 1,748 shp at 32oF. For characteristics below 32oF, refer to Performance Bulletin, SEI-601. --- --- Increase Linearly to 2,173 shp at -65oF. --- Normal takeoff, Increases linearly to 1,722 shp Flat rated to -58 F Flat rated to -31°F, Increase linearly to Flat rated to -65oF. Maximum takeoff, at 32oF; increases linearly to decreases linearly to 2,131 shp at -36oF, 30-minute OEI and Continuous OEI (1) 1,738 shp at 23oF. For characteristics below 23oF, refer to Performance Bulletin, SEI-601. 1940 shp at -58°F then flat rated to -65oF Flat rated to -58°F Maximum Increases linearly to 1,724 shp Flat rated to -58°F Increase linearly to Flat rated to -65oF. continuous at 23oF, increase linearly to 1,730 shp at 18oF. For characteristics below 18oF, refer to Performance Bulletin, SEI-601. 1,901 shp at -43oF, then flat rated to - 65oF. (1) CT7-2E1 has normal takeoff and continuous OEI ratings only. NOTE 9. All engine models meet FAA requirements for operation in icing conditions. At temperature minus 4oF and below engine gas generator speed must be maintained at or above the physical speed defined on Figure A-5 SEI-520 Installation Manual (CT7-2A), SEI-692 Installation Manual (CT7-2D/2D1), SEI-693 Installation Manual (CT7-6/6A). The CT7- 2E1/2F1/5A2/5A3/7A/7A1/8/8A/8A1/8A5/8A6/8A7/8B/8B5/8E/8E5/8F/8F5/9B/9B1/9B2/ 9C/ 9C3/9D/9D2 engine models have no anti-icing operational restrictions in their normal operating ranges. NOTE 10. If an Ng (NOTE 1), T4.5/ITT (NOTE 2), Np (NOTE 7), or Torque (NOTE 8) limit for the engine has been exceeded, or if an associated time-limitation has been exceeded, e.g. 12 seconds, 5 minutes, etc., the engine must be inspected per GE Aviation Maintenance Manual: SEI-570 (CT7-2A/2D/2D1) GEK 112043-02 (CT7-2E1) GEK 112043-03 (CT7-2F1) SEI-695 (CT7-6/6A) SEI-576 (CT7-5A2/5A3/7A/7A1/9B/9B1/9B2/9C/9C3/9D/9D2) GEK 105159 (CT7-8/8A/8A1/8A5/8A6/8A7/8B/8B5/8E/8E5/8F/8F5). In addition, if propeller shaft speed has exceeded 1,588 rpm for more than 12 seconds, the CT7-5A2/5A3/7A/7A1/9B/9B1/9B2/9C/9C3/9D/9D2 turboprop engine must be inspected per SEI-576. NOTE 11. TCDS E8NE Page 13 of 18 SEA LEVEL STATIC POWER LIMITS BELOW 59°F These ratings and the limitations on the usage of them are defined in 14 CFR. MODELS: CT7- 8 8A 8A1 8A5 8A6/8A7 30-second OEI Increase linearly to 2675 shp at 47°F, then flat to -57°F, decreasing linearly to 2644 shp at -65°F. Increase linearly to 2750 shp at 51°F, then flat to -36°F, decreasing linearly to 2645 shp at -65°F. Flat to -46°F, then decreasing to 2636 shp at -65°F. Flat to -56°F, then decreasing to 2662 shp at -65°F. Flat rated to -65oF. 2-minute OEI Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. Continuous OEI --- Flat rated to -65oF. Flat rated to -65oF. Flat rated to –65oF. Flat rated to -65oF. 30-minute OEI Flat rated to -65oF. --- --- --- --- Normal takeoff Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. 30-minute Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. Maximum Increase linearly to Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. Flat rated to –65oF. continuous 2110 shp at 53°F, then flat rated to -65°F NOTE 11. – SEA LEVEL STATIC POWER LIMITS BELOW 59°F These ratings and the limitations on the usage of them are defined in 14 CFR. Continued MODELS: CT7- 8B 8B5/8E5 8E 8F 8F5 30-second OEI Flat to -39°F, then decreasing to 2645 shp at -65°F. Flat to -36°F, then decreasing to 2662 shp at -65°F. Flat to -44°F, then decreasing to 2656 shp at -65°F. Flat rated to -65°F. Flat rated to -40°F. Flat rated to -40oF. Flat rated to -40oF. --- Flat rated to -40oF. Flat rated to -40oF. Flat rated to -40oF. 2-minute OEI Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. Continuous OEI Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. 30-minute OEI --- --- --- --- Normal takeoff Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. 30-minute Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. Maximum Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. Flat rated to -65oF. continuous NOTE 11. – Continued NOTE 12. Approved fuels and additives are specified in GE Specification D50TF2 revision 21or later. NOTE 13. Life limits, established for critical rotating components, are published in the following GE Aviation Maintenance Manuals Chapter 5: SEI-570 (CT7-2A/2D/2D1) GEK 112043-02 (CT7-2E1) GEK 112043-03 (CT7-2F1) SEI-695 (CT7-6/6A) GEK 105159 (CT7-8/8A/8A1/8A5/8A6/8A7/8B/8B5/8E/8E5/8F/8F5) SEI-576 (CT7-5A2/5A3/7A/7A1/9B/9B1/9B2/9C/9C3/9D /9D2) TCDS E8NE Page 14 of 18 The following engine components provide means to satisfy the indicated requirements of the 14 CFR Part shown. 2A/2D/2D1/6/6A 2E1/2F1/8/8A/8A1/8A5/ 5A2/5A3/7A/7A1/9B/9B (Part 29 Amendment 46) (1) Fuel filter 29.997(a),(b),(c),(d) 29.997(a),(b),(c),(d) 25.997(a)(b)(c)(d) 29.1305(a)(17) * 29.1305(a)(18) * 25.1305(c)(6) * (2) Oil tank 29.1011(a) 29.1011(a) 25.1011(a) 29.1013(a) 29.1013(a) 25.1013(a) 29.1013 (b)(1)(3) 29.1013(b)(1)(3) 25.1013(b)(1)(3) 29.1013(c)(1)(2)(3) 29.1013(c)(1)(2)(3) 25.1013(c)(1)(2) 29.1013(d)(1)(2) 29.1013(d)(1)(2) 25.1013(d)(1)(2) 29.1013(e) 29.1013(e) 25.1013(e) 29.1015(a)(b) 29.1015(a)(b) 25.1015(a)(b) 29.1189(a)(2) 29.1189(a)(2) 25.1189(a)(2) 29.1305(a)(7) * 29.1305(a)(8) * 25.1305(a)(3) * (3) Oil filter 29.1019(a)(1)(2)(4) 29.1019(a)(1)(2)(4) 25.1019(a)(1)(2)(4) 29.1019(a)(3)(5) * 29.1019(a)(3)(5) * 25.1019(a)(3) * 29.1305(a)(18) * 29.1305(a)(19) * 25.1305(c)(7) * (4) Inlet particle 29.1461(c) 29.1461(c) --- separator blower (5) Ventilation 29.831(b) 29.831(b) 25.831(b) * Means to satisfy the requirement are provided by the engine. NOTE 14. Recommended maintenance inspection intervals are published in the following GE Aviation publications: Service Bulletin No. (CT7-TS) 72-0001 (CT7-2A/2D/2D1) Service Bulletin No. (CT7-TS) 72-0009 (CT7-6/6A) Service Bulletin No. (CT7-TP) 72-0002 (CT7-5A2/5A3/7A/7A1/9B/9B1/9B2/9C/9C3/9D/9D2) Service Bulletin No. 71-0000 (CT7-8/8A/8A1/8A5/8A6/8A7/8B/8B5/8E/8E5/8F/8F5) Service Bulletin No. 71-0000 (CT7-2E1) Service Bulletin No. 71-0000 (CT7-2F1) NOTE 15. 14 CFR 29 (Part 29 Amendment 13) 8A6/8A7/8B/8B5/8E/8E 5/8F/8F5, 1/9B2/9C/9C3/9D/9D2, (Part 25 Amendment 43) NOTE 16. a. The temperature value and/or nacelle airflow requirements specified in Paragraph A-8 (A-7 for the CT7- 2F1) and A-9 (A-8 for the CT7-2F1), or Section B-7 (CT7-2E1 and CT7-2F1), of the Installation Manual must be met when installing the engine: SEI-520 (CT7-2A) SEI-692 (CT7-2D/2D1) GEK 112765 (CT7-2E1) GEK 112103 (CT7-2F1) SEI-693 (CT7-6/6A) SEI-866 (CT7-8/8A/8A1/8A5/8A6/8A7/8B/8B5/8E/8E5/8F) GEK 114116 (CT7-8F5) b. The requirements specified in the Installation Manual must be met when installing the turboprop engine: SEI-585 Paragraph A-9 (CT7-5A2/5A3/7A/7A1). SEI-726 Paragraph A-7 (CT7-9B/9B1/9B2/9C/9C3/9D/9D2) Compliance with 14 CFR 33.17 Amendment 6 concerning ignition of leaking oil is obtained only when the above requirements are met. TCDS E8NE Page 15 of 18 NOTE 17. The following models incorporate the following general characteristics: CT7-2A: Basic Model. CT7-2D: Similar to CT7-2A but incorporates higher flow compressor and surface coatings to improve resistance to wear and corrosion. CT7-2D1: Similar to CT7-2D but incorporates CT7-6/6A hot section. CT7-2E1: Similar to CT7-2D1 but incorporates CT7-8 growth models improved durability hot section, CT7-9 (Accessory Gear Box) AGB and combustor, and FADEC control system CT7-2F1: Similar to CT7-2E1 but incorporates CT7-2D1 and CT7-8 AGB CT7-6/6A: Similar to CT7-9B/9C except for turboshaft CT7-2 family inlet and exhaust frames. CT7-8: Similar to CT7-6 except for increased airflow compressor, improved durability turbine and FADEC based control. CT7-8A/8A1/8A5/8A6/8A7/8B/8B5/8E/8E5/8F/8F5: Similar to CT7-8 except for increased durability turbine. CT7-5A2/5A3/7A/7A1/9B/9B1/9B2/9C/9C3/9D/9D2: Turboprop power units are similar to turboshaft engines with slightly increased airflows, a one-inch increase in power turbine rotor shaft length and associated hardware changes. Turboprop engines incorporate a propeller gearbox coupled to the power unit by a drive shaft housing and two interconnecting struts. The turboprop models’ propeller gearbox has the capability of being equipped with an optional propeller brake assembly. The propeller brake when engaged stops propeller rotation while allowing the gas generator portion of the engine to remain in operation as an auxiliary power unit (APU mode). NOTE 18. The CT7-2A engine control system incorporates total torque limiting capability which limits total torque of a twin engine installation to a combined output of approximately 615 ft-lb at rated output speed. NOTE 19. The CT7-1/2, T700/T1C, CT7-2B and T700/T2C engines were removed from Type Certificate No. E8NE on May 28, 1981, January 15, 1982, May 18, 1983, and July 30, 1992, respectively, at the request of the type certificate holder. NOTE 20. This note has been deleted. NOTE 21. FOREIGN OBJECT INGESTION PROTECTION The CT7 turboprop engine models (CT7-5A2/5A3/7A/7A1/9B/9B1/9B2/9C/9C3/9D/9D2) have substantiated the ingestion requirements of 14 CFR 33.77 fitted with the following GE Aviation inlet duct reference drawings: 17A133-912 and SK585500-121 Sheets 1, 2 and 3 (CT7-5A2/5A3/7A/7A1) 17A151-828 and 17A151-837 (CT7-9B/9B1/9B2/9C/9C3/9D/9D2) GE Aviation should be consulted regarding the aerodynamics and structural requirements of this feature. The CT7-8F5 Engine shall be limited to aircraft installation in which it is shown that a bird cannot strike the engine, be ingested into the engine, or adversely restrict airflow into the engine. NOTE 22. CT7-5A2/5A3/7A/7A1/9B/9B1/9B2/9C/9C3/9D/9D2 propeller steady state avoidance ranges are 375-500 rpm and 625-950 rpm. NOTE 23. CT7-5A2/5A3/7A/7A1/9B/9B1/9B2/9C/9C3/9D/9D2 engines can incorporate a propeller brake assembly as optional equipment. Refer to CT7-5A2/5A3/7A/7A1 Installation Manual SEI-585 or CT7-9B/9B1/9B2/9C/ 9C3/9D/9D2 Installation Manual SEI-726 for aircraft installation considerations. The aircraft propeller brake system must preclude inadvertent brake applications. TCDS E8NE Page 16 of 18 NOTE 24. All models meet the fuel venting requirements of 14 CFR part 34, 34.11. All CT7 Turbo Prop models (CT7-5/ -7/ -9 models) comply with the smoke exhaust emissions requirements of 14 CFR part 34, 34.21(e)(3) amendment 34-5. NOTE 25. Turboprop models (CT7-5A2/5A3/7A/7A1/9B/9B1/9B2/9C/9C3/9D/9D2) incorporate a constant torque governing system including overtorque and overtemperature limiting features. NOTE 26. The CT7-7/7E/7E1 engines were removed from Type Certificate No. E8NE on November 26, 1985, at the request of the type certificate holder. No CT7-7/7E/7E1 models are in existence. NOTE 27. The CT7-5A and the CT7-5A1 engines were removed from Type Certificate No. E8NE on October 2, 1986, at the request of the type certificate holder. No CT7-5A/5A1 models are in existence. NOTE 28. For the CT7-9C model, the limits for gas generator speed (Ng, rpm) and power turbine inlet temperature (T4.5/ITT) at normal takeoff power rating are further defined as follows: The Ng limit is 45,288 rpm when outside air temperature (OAT) is less than 95°F. When OAT is between 95°F and 106°F, the Ng limit varies linearly with OAT. When OAT is greater than 106°F the Ng is 45,600 rpm. The T4.5/ITT limit is 1690ºF when OAT is less than 95°F. When OAT is between 95°F and 106°F, the T4.5/ITT limit varies linearly with OAT from 1690°F to 1731ºF. When OAT is greater than 106°F the T4.5/ITT limit is 1742ºF. NOTE 29. Limits have been established for certain models with regard to Electromagnetic Interference (EMI) and lightning. Refer to the Installation Manual for more detailed descriptions of EMI and lightning capabilities and limits: SEI-726 (CT7-9B/9B1/9B2/9C/9C3/9D/9D2) SEI-866 (CT7-8/8A/8A1/8A5/8A6/8A7/8B/8B5/8E/8E5/8F) GEK 114116 (CT7-8F5) GEK112765 (CT7-2E1) GEK 112103 (CT7-2F1) NOTE 30. For the CT7-5A3/9B/9B1/9B2/9C/9C3/9D/9D2 models, the Normal Takeoff power, T4.5/ITT and Ng limits are presented for the purpose of defining the maximum T4.5/ITT and Ng at which Normal Takeoff power can be set to ensure that: 1. Maximum takeoff power will be achieved if demanded by the automatic power reserve (APR) mechanism, and 2. No maximum limits will be exceeded. NOTE 31. This note has been deleted. NOTE 32. For the CT7-5A3 model, the pilot may elect to operate the engine to CT7-5A2 normal takeoff limits provided the APR mechanism is not activated and provided that the climb-cruise power settings are restricted to CT7-5A2 levels. NOTE 33. The CT7-5A2/7A/9B/9B1/9B2/9C/9D engines, may be operated under the Derivative Engine Takeoff Rating program as outlined in GE Aviation CT7 Operations Engineering Bulletins 1 and 11, latest Revisions. The Derivative Engine Takeoff Rating program reduces the NOTE 5 flat rated temperatures for maximum takeoff, normal takeoff and maximum continuous by 5ºC. TCDS E8NE Page 17 of 18 NOTE 34. The Principal Dimensions are nominal values for reference only. More exact dimensions are defined in the Installation Drawing found in: SEI-520 (CT7-2A) SEI-692 (CT7-2D/2D1) GEK 112765 (CT7-2E1) GEK 112103 (CT7-2F1) SEI-693 (CT7-6/6A) SEI-585 (CT7-5A2/5A3/7A/7A1) SEI-726 (CT7-9B/9B1/9B2/9C/9C3/9D /9D2) SEI-866 (CT7-8/8A/8A1/8A5/8A6/8A7/8B/8B5/8E/8E5/8F) GEK 114116 (CT7-8F5) NOTE 35. For the CT7-8/8A/8A1/8A5/8A6/8A7/8B/8B5/8E/8E5/8F/8F5 models, the FADEC system isochronously governs engine output shaft speed (Np) and therefore aircraft main rotor speed (Nr), and incorporates torque matching between engines. Automatic operational limiters are provided for torque, speed and power turbine inlet temperature (T4.5/ITT). For the CT7-2E1/2F1 the FADEC system isochronously governs engine output shaft speed (Np) and therefore aircraft main rotor speed (Nr), and incorporates either torque or power turbine inlet temperature matching between engines (pilot selectable). The FADEC also provides automatic operational limiters for torque, rotor speeds and power turbine inlet temperature (T4.5/ITT) as defined in the Installation Manual GEK 112765 (CT7-2E1) and GEK 112103 (CT7-2F1). NOTE 36. For the CT7-8/8A/8A1/8A5/8A6/8A7/8B/8B5/8E/8E5/8F/8F5 models, the power turbine inlet gas temperature (T4.5/ITT) and torque data are required for the aircraft system to alert the pilot and track the time when the engine is at the 30-second and 2-minute OEI ratings; see Installation Manual SEI-866 (CT7-8/8A/8A1/8A5/ 8A6/8A7/8B/8B5/8E/8E5/8F) or GEK 114116 (CT7-8F5). The FADEC system provides the T4.5/ITT and Torque signals to the aircraft system to track the time at those ratings. For the CT7-2E1 model, the power turbine inlet gas temperature (T4.5/ITT), gas generator speed (Ng) and torque data are required for the aircraft system to alert the pilot and track the time when the engine is at the flat rated 30-second/2-minute OEI rating; see Operating Instructions GEK 112766. The FADEC system provides the T4.5/ITT, Ng, and Torque signals to the aircraft system to track the time at those ratings. For the CT7-2F1 model, the power turbine inlet gas temperature (T4.5/ITT), gas generator speed (Ng) and torque data are required for the aircraft system to alert the pilot and track the time when the engine is at the 30- second and 2-minute OEI ratings; see Installation Manual GEK 112103. The FADEC system provides the T4.5/ITT, Ng, and Torque signals to the aircraft system to track the time at those ratings. NOTE 37. For the CT7-2E1/2F1/8/8A/8A1/8A5/8A6/8A7/8B/8B5/8E/8E5/8F/8F5 models, engine maintenance logic is provided by the FADEC system, which transmits maintenance information over an ARINC data bus. This information includes system fault event indications and power assurance calculation results. NOTE 38. For the CT7-2E1 model, in an all engines operating (AEO) condition, the T4.5 limit will be automatically set to the flat 30-second/2-minute OEI limit when the engine senses a PT rotor speed (Np) droop to 95% of the reference speed, or to 99.5% of the reference speed with a rate of decrease faster than 3% per second. The T4.5 limit will reset to the Takeoff (AEO) limit when Np is greater than 99.5% of the reference speed and T4.5 is at least 5.5°C below the AEO T4.5 reference temperature for 3 seconds. For the CT7-8, 8A, 8A1, 8A5, 8A6, 8A7, 8E, 8E5, 8F and 8F5 models, in an AEO condition, the FADEC provides torque, speed and T4.5 Limiting at takeoff power. For specific models, CT7-8/8A/8A1/8A5/8A6/8A7: The T4.5 limit will be automatically set to 30-second OEI limit when the engine senses an Np droop of more than 5%. The T4.5 limit will reset to the Takeoff (AEO) limit when Np is at or above 99% of the reference Np speed. CT7-8E/8E5: The T4.5 limit will be automatically set to 30-second OEI limit when the engine senses an Np droop to 96% or less. The T4.5 limit will reset to the Takeoff (AEO) limit when Np is at or above 99% of the reference Np speed. CT7-8F/8F5: The T4.5 limit will be automatically set to 30-second OEI limits when the engine senses an Np droop to 93% or less. The T4.5 limit will reset to the Takeoff (AEO) limit when Np is at or above 99% of the reference Np speed. TCDS E8NE Page 18 of 18 Any such event will trigger a 30-second OEI rating cockpit annunciation and post-flight maintenance action in accordance with the Maintenance Manual. NOTE 39. CT7-8A1/8A7 engines and parts thereof manufactured by StandardAero, 20699 Westminster Highway, Richmond, British Columbia, Canada, under Licensing Agreement Number 10.0062 with the General Electric Company, are identified by engine Serial Numbers 530001 to 530099. NOTE 40. The CT7-8/8A/8A1/8A6/8A7 models are approved to operate with certain faults present in the control system. This is based on satisfaction of 14 CFR Part 33 requirements and appropriate engine control system reliability requirements. Criteria pertaining to the time limited dispatch and maintenance requirements for engine control systems are contained in Chapter 5 of the Engine Maintenance Manual GEK 105159. Details of the fault codes, various configurations and maximum operating intervals are in GE Report No. GEK 112652, Control System Time Limited Dispatch Summary for the Sikorsky S92 Helicopter. The CT7-2F1 model is approved to operate with certain faults present in the control system. This is based on satisfaction of 14 CFR Part 33 requirements and appropriate engine control system reliability requirements. Criteria pertaining to the time limited dispatch and maintenance requirements for engine control systems are contained in Chapter 5 of the Engine Maintenance Manual GEK 112043-03. Details of the fault codes, various configurations and maximum operating intervals are in GEK 134615, Control System Time Limited Dispatch Summary for the Bell 525 Helicopter. The CT7-2E1 model is approved to operate with certain faults present in the control system. This is based on satisfaction of 14 CFR Part 33 requirements and appropriate engine control system reliability requirements. Criteria pertaining to the time limited dispatch and maintenance requirements for engine control systems are contained in Chapter 5 of the Engine Maintenance Manual GEK 112043-02. Details of the fault codes, various configurations and maximum operating intervals are in GEK 112055, Control System Time Limited Dispatch Summary for the AW189 Helicopter. NOTE 41. This note has been deleted. NOTE 42. The Component Maintenance Manual (CMM) for the CT7-8A5/8B/-8B5/-8E5/-8F FADEC has not been issued. Any FADEC removed from service on a CT7-8A5/8B/-8B5/-8E5/-8F engine may not be repaired until the CMM is issued. NOTE 43. CT7-8F5 engines and parts thereof manufactured by Industria de Turbo Propulsores S. A. (ITP)/Industria de Turbinas Helicoptero S.A. (ITH) Edificio 300, Parque Tecnologico, 48170 Zamudio, Vizcaya, Spain under Appendix of Business Agreement Number 79.0056 with GE Aviation are identified by engine Serial Numbers 731004 to 731099 and 733001 to 733100. NOTE 44. The Component Maintenance Manual (CMM) for the CT7-2A/2D/2D1 Anti-Icing/Start Bleed Valve manufactured by Garrett/Allied Signal/Honeywell identified by GE part number 5066T38 has not been issued. Any AISBV of this part number removed from service may not be repaired until the CMM is issued. NOTE 45. This note has been deleted. NOTE 46. This note has been deleted. NOTE 47. This note has been deleted. NOTE 48. For the CT7-2E1/2F1, GE voluntarily elected to show compliance to 14 CFR 33.28, Amendment 28 (CT7- 2E1) and Amendment 26 (CT7-2F1) for the Electronic Engine Control, Fuel Metering Unit, and Anti- Icing/Start Bleed Valve. 14 CFR 33.28 at Amendment 28 is unchanged since Amendment 26. NOTE 49. CT7-8E engines and parts thereof manufactured by AVIO S.r.l., Via I Maggio 99, Rivalta di Torino, Italy, under Business Agreement Number 42.0174 with the General Electric Company, are identified by engine Serial Numbers 087001 to 087050. NOTE 50: This note has been deleted. …..END….. ``` ## ADs (26, in force first) - [AD 2025-05-15](https://openairdocs.org/ad/2025-05-15): Engine (Turbine/Turboprop) · General Electric Company GE CT7-2E1. Effective Apr 17, 2025 - [AD 2025-05-02](https://openairdocs.org/ad/2025-05-02): Engine (Turbine/Turboprop) · General Electric CT7-5A2, CT7-5A3, CT7-7A and 8 more. Effective Apr 8, 2025 - [AD 2024-06-51](https://openairdocs.org/ad/2024-06-51): Engine (Turbine/Turboprop); Turbine Section · General Electric CT7-2E1, CT7-2F1, CT7-8A and 2 more. Effective Apr 23, 2024 - [AD 2023-21-07](https://openairdocs.org/ad/2023-21-07): Turbine Engine Reduction Gear · General Electric CT7-5A2, CT7-5A3, CT7-7A and 6 more. Effective Dec 11, 2023 - [AD 2022-18-16](https://openairdocs.org/ad/2022-18-16): Turbine Engine Combustion Section, Turbine Section · General Electric CT7-8A. Effective Oct 7, 2022 - [AD 2017-19-20](https://openairdocs.org/ad/2017-19-20): Turbine Engine Compressor Section · General Electric CT7-8A and CT7-9B. Effective Oct 27, 2017 - [AD 2011-21-17](https://openairdocs.org/ad/2011-21-17): Fuel filter differential pressure switch. · General Electric CT7-8A, CT7-8A1, CT7-8E and 1 more. Effective Nov 17, 2011 - [AD 2011-19-03](https://openairdocs.org/ad/2011-19-03): Accessory gearbox (AGB) · General Electric CT7-8, CT7-8A, CT7-8A1 and 2 more. Effective Nov 9, 2011 - [AD 2010-23-20](https://openairdocs.org/ad/2010-23-20): Gas generator turbine (GGT) shafts · General Electric CT7-9C and CT7-9C3. Effective Dec 22, 2010 - [AD 2008-26-02](https://openairdocs.org/ad/2008-26-02): Electrical chip detectors · General Electric CT7-8A. Effective Jan 26, 2009 - [AD 2007-08-01](https://openairdocs.org/ad/2007-08-01): Eddy current inspection (ECI) of boltholes · General Electric CT7-5A2, CT7-5A3, CT7-7A and 8 more. Effective May 14, 2007 - [AD 2004-16-07](https://openairdocs.org/ad/2004-16-07): Turbine Stage 2 Aft Cooling Plates · General Electric CT7-2D1. Effective Aug 23, 2004 - [AD 2004-07-09](https://openairdocs.org/ad/2004-07-09): PGB oil filter impending bypass button (IBB) · General Electric CT7-2A, CT7-2D, CT7-2D1 and 14 more. Effective May 11, 2004 - [AD 2003-08-52](https://openairdocs.org/ad/2003-08-52): Compressor variable geometry (VG) · General Electric CT7-9B. Effective Jun 2, 2003 - [AD 2002-01-03](https://openairdocs.org/ad/2002-01-03): Stage 2 Turbine Aft Cooling Plates · General Electric CT7-5A2, CT7-5A3, CT7-7A and 1 more. Effective Feb 12, 2002 - [AD 97-25-07](https://openairdocs.org/ad/97-25-07): Stage 1 or 2 Gas Generator Turbine (GGT) Disk · General Electric CT7-5A2, CT7-7A, CT7-9B and 1 more. Effective Jan 28, 1998 - [AD 96-26-01](https://openairdocs.org/ad/96-26-01): GGT Stage 2 Forward Cooling Plate · General Electric CT7-5A2, CT7-7A, CT7-9B and 1 more. Effective Mar 10, 1997 - [AD 94-17-16](https://openairdocs.org/ad/94-17-16): Propeller Gearboxes · General Electric CT7-5A2, CT7-5A3, CT7-7A and 6 more. Effective Sep 15, 1994 - [AD 93-25-17](https://openairdocs.org/ad/93-25-17): Gas Generator Turbine (GGT) Disks and Cooling Plates · General Electric CT7-2A, CT7-5A2, CT7-6 and 2 more. Effective Feb 2, 1994 - [AD 93-23-05](https://openairdocs.org/ad/93-23-05): Gas Generator Turbine (GGT) Rotor Assembly Parts and Power Turbine (PT) Disks · General Electric CT7-5A2 and CT7-7A. Effective Jan 10, 1994 - [AD 88-07-08](https://openairdocs.org/ad/88-07-08): Power Turbine Overspeed · General Electric CT7-5A2. Effective May 9, 1988 - [AD 2024-05-51](https://openairdocs.org/ad/2024-05-51) (historical): Turbine Section · General Electric CT7-2E1, CT7-2F1, CT7-8A and 11 more. Effective Apr 1, 2024 - [AD 2018-03-13](https://openairdocs.org/ad/2018-03-13) (historical): Turbine Engine Reduction Gear · General Electric CT7-5A2, CT7-5A3, CT7-7A and 6 more. Effective Feb 28, 2018 - [AD 2006-06-51](https://openairdocs.org/ad/2006-06-51) (historical): Electrical chip detectors for the No. 3 bearing · General Electric CT7-8A. Effective May 2, 2006 - [AD 2005-18-01](https://openairdocs.org/ad/2005-18-01) (historical): Turbine aft cooling plate boltholes · General Electric Aircraft Engines CT7-5A2, CT7-5A3, CT7-7A and 4 more. Effective Oct 24, 2005 - [AD 2003-06-03](https://openairdocs.org/ad/2003-06-03) (historical): Propeller gearbox (PGB) oil filter · General Electric Aircraft Engines CT7-2A, CT7-2D, CT7-2D1 and 14 more. Effective Apr 24, 2003 ## Registered aircraft by registry model (OpenAirDocs) - [GE CT7-8A](https://openairdocs.org/engine/ge-ct7-8a): 43 aircraft (registry code 30136) - [GE CT7-9B](https://openairdocs.org/engine/ge-ct7-9b): 23 aircraft (registry code 30148) - [GE CT7-5A2](https://openairdocs.org/engine/ge-ct7-5a2): 7 aircraft (registry code 30144) - [GE CT7-9C3](https://openairdocs.org/engine/ge-ct7-9c3): 6 aircraft (registry code 30150) - [GE CT7-2A](https://openairdocs.org/engine/ge-ct7-2a): 3 aircraft (registry code 30184) - [GE CT7-8A7](https://openairdocs.org/engine/ge-ct7-8a7): 2 aircraft (registry code 30183) - [GE CT7-2D](https://openairdocs.org/engine/ge-ct7-2d): 0 aircraft (registry code 30131) - [GE CT7-2D1](https://openairdocs.org/engine/ge-ct7-2d1): 0 aircraft (registry code 30132) - [GE CT7-5A3](https://openairdocs.org/engine/ge-ct7-5a3): 0 aircraft (registry code 30145) - [GE CT7-6](https://openairdocs.org/engine/ge-ct7-6): 0 aircraft (registry code 30133) - [GE CT7-6A](https://openairdocs.org/engine/ge-ct7-6a): 0 aircraft (registry code 30134) - [GE CT7-7A](https://openairdocs.org/engine/ge-ct7-7a): 0 aircraft (registry code 30146) - [GE CT7-7A1](https://openairdocs.org/engine/ge-ct7-7a1): 0 aircraft (registry code 30147) - [GE CT7-8](https://openairdocs.org/engine/ge-ct7-8): 0 aircraft (registry code 30135) - [GE CT7-8A5](https://openairdocs.org/engine/ge-ct7-8a5): 0 aircraft (registry code 30137) - [GE CT7-8B](https://openairdocs.org/engine/ge-ct7-8b): 0 aircraft (registry code 30138) - [GE CT7-8B5](https://openairdocs.org/engine/ge-ct7-8b5): 0 aircraft (registry code 30139) - [GE CT7-8E](https://openairdocs.org/engine/ge-ct7-8e): 0 aircraft (registry code 30140) - [GE CT7-8E5](https://openairdocs.org/engine/ge-ct7-8e5): 0 aircraft (registry code 30141) - [GE CT7-8F](https://openairdocs.org/engine/ge-ct7-8f): 0 aircraft (registry code 30142) - [GE CT7-8F5](https://openairdocs.org/engine/ge-ct7-8f5): 0 aircraft (registry code 30143) - [GE CT7-9B1](https://openairdocs.org/engine/ge-ct7-9b1): 0 aircraft (registry code 30151) - [GE CT7-9B2](https://openairdocs.org/engine/ge-ct7-9b2): 0 aircraft (registry code 30152) - [GE CT7-9C](https://openairdocs.org/engine/ge-ct7-9c): 0 aircraft (registry code 30149) - [GE CT7-9D](https://openairdocs.org/engine/ge-ct7-9d): 0 aircraft (registry code 30153) - [GE CT7-9D2](https://openairdocs.org/engine/ge-ct7-9d2): 0 aircraft (registry code 30154) --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). 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