# TCDS E23EA: General Electric Company

- Type: Type certificate data sheet
- Status: Current
- Holder: General Electric Company
- Revision: 21
- Revised: June 10, 2013
- Product: Engine
- Certification basis: Part 21, Part 33
- Registered aircraft: 32, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/2e/91/2e9125c552fcfafabdfc154ee39c7acc09d03f53b65eaf7c23ac3f38eae350c9
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/2C339DD53360180C86257B9B004942CA.0001
- Page: https://openairdocs.org/tcds/E23EA

## Models (18)

As the data sheet lists them.

- CF6-50E1
- CF6-50CA
- CF6-50A
- CF6-6D1A
- CF6-50E
- CF6-50C2D
- CF6-6D
- CF6-6D1
- CF6-50C1
- CF6-50E2B
- CF6-50C2
- CF6-50C
- CF6-45A2
- CF6-50C2B
- CF6-6K
- CF6-45A
- CF6-50E2
- CF6-6K2

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
* 
 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. 
 
CF6-50E2B Same as CF6-50E2 except for increased takeoff thrust of 53,200 lbs with the incorporation of either 
  GE Service Bulletin 78-190 or 78-192. 
 
CF6-6K  Same as CF6-6D except for new fan blades and fan case stiffening ring. 
 
CF6-6K2  Same as CF6-6K except engine is operated to in creased takeoff thrust of 40,900 lbs at a lower flat rated 
  ambient temperature of 84°F, SLS. 
 
General Electric Service Bulletin (CF6-50) 72-350 outlines the conversions from one CF6-50/-45 series model to another 
CF6-50/-45 series model that have been FAA approved.  A suffix may be added to the basic engine model number on the 
engine name plate to identify minor variations in the engine configuration, installation components or derated thrust peculiar to 
aircraft installation requirements.  For example:  CF6-50C2-XX.  Engines that have suffix to the basic model number are 
identified in General Electric Service Bulletin No. (CF6-50/-45) 72-350, and are summarized below: 
 
1. CF6-50C2-R - Same as -50C2 except reduced takeoff thrust rating (50,400 lbs. SLS). 
      All hardware, limitations and other ratings are identical. 
 
2. CF6-50C2-F - Same as -50C2 except reduced ra tings (T.O. 45,600 lbs. SLS; MCT 43,250 lbs. SLS). 
      All hardware, limitations and other ratings identical. 
 
NOTE 13. Overhaul of CF6-6K2 engines is not authorized until th e engine manual becomes available.  Meanwhile, rebuilt engine 
utilizing new engine tolerances may be provided by the manufacturer. 
 
NOTE 14. The normal 5 minute takeoff time limit may be extended to 10 minutes for engine out contingency. 
 
NOTE 15. Removed. 
----END----

TCDS  E23EA            PAGE 12 
 
 ASE CMT PM Branch 
Manager 
Office Manager 
Routing-Symbol ANE-141  ANE-141 ANE-141 ANE-140 
Name Kasra Sharifi Tomasz Rakowski Christopher Spinney Thomas Boudreau 
Initials     
Date     
 
ANE-140:Kasra Sharifi:K,S:781-238-777 
G:\Usr\ANE-100\ANE140\GE_CMT\CF6 General\_CF6 Cross-Product 
Projects\Certification\TCDS\E23EA (CF6-6, CF6-45, CF6-50)\Rev21 8110.1a(1)
```

## ADs (70, first 50, in force first)

- [AD 2023-04-11](https://openairdocs.org/ad/2023-04-11): Turbine Section · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Apr 28, 2023
- [AD 2011-23-04](https://openairdocs.org/ad/2011-23-04): Forward engine mount assembly side links · General Electric CF6-45A, CF6-45A2, CF6-50A and 14 more. Effective Dec 12, 2011
- [AD 2011-07-01](https://openairdocs.org/ad/2011-07-01): Forward and aft centerbodies · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Apr 22, 2011
- [AD 2007-11-18 R1](https://openairdocs.org/ad/2007-11-18-R1): Forward fan stator cases · General Electric CF6-50C, CF6-50C1 and CF6-50C2. Effective Jan 4, 2010
- [AD 2008-02-17](https://openairdocs.org/ad/2008-02-17): Thrust reverser actuation systems · General Electric CF6-50A, CF6-50C, CF6-50C1 and 16 more. Effective Feb 28, 2008
- [AD 2007-19-06](https://openairdocs.org/ad/2007-19-06): Compressor discharge pressure (CDP) · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Oct 23, 2007
- [AD 2005-26-06](https://openairdocs.org/ad/2005-26-06): Low pressure turbine (LPT) stage 2 interstage seal assemblies · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Jan 26, 2006
- [AD 2005-07-05](https://openairdocs.org/ad/2005-07-05): Low pressure turbine (LPT) · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective May 4, 2005
- [AD 2005-08-04](https://openairdocs.org/ad/2005-08-04): Low-cycle-fatigue (LCF) · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Apr 28, 2005
- [AD 2003-10-01](https://openairdocs.org/ad/2003-10-01): High pressure turbine rotor (HPTR) rear shafts · General Electric CF6-6D, CF6-6D1, CF6-6D1A and 2 more. Effective Jun 17, 2003
- [AD 2003-09-06](https://openairdocs.org/ad/2003-09-06): Low pressure turbine (LPT) · General Electric CF6-50A, CF6-50C, CF6-50C1 and 8 more. Effective Jun 3, 2003
- [AD 2003-02-07](https://openairdocs.org/ad/2003-02-07): Low pressure turbine (LPT) shrouds · General Electric CF6-50A, CF6-50C, CF6-50C1 and 30 more. Effective Mar 3, 2003
- [AD 2002-25-08](https://openairdocs.org/ad/2002-25-08): High pressure compressor rotor · General Electric CF6-45A, CF6-45A2, CF6-50A and 40 more. Effective Jan 23, 2003
- [AD 2002-05-03](https://openairdocs.org/ad/2002-05-03): Life-Limited Rotating Parts · General Electric CF6-45A, CF6-45A2, CF6-50A and 15 more. Effective Apr 12, 2002
- [AD 2002-02-09](https://openairdocs.org/ad/2002-02-09): Low Pressure Turbine Rotor (LPTR) Stage 2 Disks · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Mar 15, 2002
- [AD 2001-12-20](https://openairdocs.org/ad/2001-12-20): Air Ducts and Reworked Mating Hardware · General Electric CF6-50A, CF6-50C, CF6-50C1 and 8 more. Effective Jul 26, 2001
- [AD 2001-04-16](https://openairdocs.org/ad/2001-04-16): Low Pressure Turbine (LPT) Nozzle Lock Assembly Studs · General Electric CF6-50A, CF6-50C, CF6-50C1 and 8 more. Effective Mar 21, 2001
- [AD 2000-11-12](https://openairdocs.org/ad/2000-11-12): High Pressure Compressor Disk Lock Slots · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Aug 14, 2000
- [AD 98-22-06](https://openairdocs.org/ad/98-22-06): Fan Disks · General Electric CF6-45A, CF6-45A2, CF6-50A and 41 more. Effective Nov 23, 1998
- [AD 98-18-10](https://openairdocs.org/ad/98-18-10): Low Pressure Turbine Disks · General Electric CF6-6D, CF6-6D1, CF6-6D1A and 2 more. Effective Sep 30, 1998
- [AD 97-22-14](https://openairdocs.org/ad/97-22-14): (HPCR) 3-9 Spool · General Electric CF6-50A, CF6-50C, CF6-50C1 and 29 more. Effective Nov 17, 1997
- [AD 95-08-03](https://openairdocs.org/ad/95-08-03): High Pressure Turbine Rotor Stage 2 Disks · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Jun 12, 1995
- [AD 91-10-03 R1](https://openairdocs.org/ad/91-10-03-R1): High Pressure Compressor · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Apr 28, 1995
- [AD 94-08-05](https://openairdocs.org/ad/94-08-05): Fan Stator Case · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Jul 5, 1994
- [AD 94-09-18](https://openairdocs.org/ad/94-09-18): High Pressure Turbine Disk · General Electric CF6-45A, CF6-45A2, CF6-50A and 15 more. Effective Jun 6, 1994
- [AD 93-14-18](https://openairdocs.org/ad/93-14-18): High pressure turbine (HPT) thermal shields · General Electric CF6-45A, CF6-45A2, CF6-50A and 40 more. Effective Oct 4, 1993
- [AD 93-13-10](https://openairdocs.org/ad/93-13-10): Compressor Spools · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Sep 21, 1993
- [AD 91-24-01](https://openairdocs.org/ad/91-24-01): Compressor Rear Frame Casing · General Electric CF6-6D, CF6-6D1, CF6-6D1A and 2 more. Effective May 26, 1992
- [AD 91-23-13](https://openairdocs.org/ad/91-23-13): Fan Disks · General Electric CF6-50A, CF6-50C, CF6-50C1 and 12 more. Effective Nov 22, 1991
- [AD 91-15-16](https://openairdocs.org/ad/91-15-16): High Pressure Turbine Thermal Shields · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Sep 4, 1991
- [AD 91-15-03](https://openairdocs.org/ad/91-15-03): Fan Disks · General Electric CF6-6D, CF6-6D1, CF6-6D1A and 2 more. Effective Aug 5, 1991
- [AD 91-12-09](https://openairdocs.org/ad/91-12-09): Fan Disks · General Electric CF6-6D, CF6-6D1, CF6-6D1A and 2 more. Effective Jun 27, 1991
- [AD 91-01-04](https://openairdocs.org/ad/91-01-04): Fan Disk · General Electric CF6-45A, CF6-45A2, CF6-50A and 19 more. Effective Jan 22, 1991
- [AD 90-23-15](https://openairdocs.org/ad/90-23-15): Turbine Mid-frame · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Dec 6, 1990
- [AD 90-19-08](https://openairdocs.org/ad/90-19-08): Low Pressure Turbine Rotor Stage One Disk · General Electric CF6-6D, CF6-6D1, CF6-6D1A and 2 more. Effective Oct 15, 1990
- [AD 90-19-09](https://openairdocs.org/ad/90-19-09): High Pressure Turbine Stage One Disks · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Oct 1, 1990
- [AD 90-12-06](https://openairdocs.org/ad/90-12-06): Low Pressure Turbine · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Jun 25, 1990
- [AD 89-20-01 R1](https://openairdocs.org/ad/89-20-01-R1): Fan Disks · General Electric CF6-6D, CF6-6D1, CF6-6D1A and 2 more. Effective Dec 12, 1989
- [AD 89-01-02](https://openairdocs.org/ad/89-01-02): High Pressure Turbine Stage 2 Disks · General Electric CF6-50A, CF6-50C, CF6-50C1 and 8 more. Effective Dec 29, 1988
- [AD 88-12-01](https://openairdocs.org/ad/88-12-01): High Pressure Compressor Rear Shafts · General Electric CF6-6D, CF6-6D1, CF6-6D1A and 2 more. Effective Jun 6, 1988
- [AD 87-23-06](https://openairdocs.org/ad/87-23-06): High Pressure Turbine Impeller Spacer · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Nov 5, 1987
- [AD 86-12-03](https://openairdocs.org/ad/86-12-03): High Pressure Turbine Rotor (HPTR) Stage 1 Disk · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Jun 29, 1986
- [AD 84-01-01](https://openairdocs.org/ad/84-01-01): Compressor Assemblies · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Feb 10, 1984
- [AD 82-25-08](https://openairdocs.org/ad/82-25-08): HPT Spacer/Impeller · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Dec 30, 1982
- [AD 82-20-03](https://openairdocs.org/ad/82-20-03): Inspect First Stage HPT Disks · General Electric CF6-45A, CF6-45A2, CF6-50A and 10 more. Effective Oct 31, 1982
- [AD 81-19-08](https://openairdocs.org/ad/81-19-08): Low Pressure Turbine Rotor Stage 2 Disks · General Electric CF6-6D, CF6-6D1, CF6-6D1A and 2 more. Effective Sep 21, 1981
- [AD 77-08-08](https://openairdocs.org/ad/77-08-08): Compressor · General Electric CF6-50A, CF6-50C, CF6-50C1 and 2 more. Effective Feb 14, 1980
- [AD 80-03-06](https://openairdocs.org/ad/80-03-06): Stage 2 HPT Disks · General Electric CF6-6D, CF6-6D1, CF6-6D1A and 2 more. Effective Feb 8, 1980
- [AD 78-07-03](https://openairdocs.org/ad/78-07-03): Compressor Spool · General Electric CF6-6D and CF6-6D1. Effective May 22, 1978
- [AD 76-21-04](https://openairdocs.org/ad/76-21-04): High Pressure Compressor · General Electric CF6-6D and CF6-6D1. Effective Nov 30, 1977

All 70: https://openairdocs.org/tcds/E23EA/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [GE CF6-50C2](https://openairdocs.org/engine/ge-cf6-50c2): 10 aircraft (registry code 30085)
- [GE CF6-50 series](https://openairdocs.org/engine/ge-cf6-50-series): 9 aircraft (registry code 30018)
- [GE CF6-6](https://openairdocs.org/engine/ge-cf6-6-series): 9 aircraft (registry code 30020)
- [GE CF6-6D](https://openairdocs.org/engine/ge-cf6-6d): 2 aircraft (registry code 30076)
- [GE CF6-45A2](https://openairdocs.org/engine/ge-cf6-45a2): 1 aircraft (registry code 30017)
- [GE CF6-50C](https://openairdocs.org/engine/ge-cf6-50c): 1 aircraft (registry code 30082)
- [GE CF6-45A](https://openairdocs.org/engine/ge-cf6-45a): 0 aircraft (registry code 30092)
- [GE CF6-50A](https://openairdocs.org/engine/ge-cf6-50a): 0 aircraft (registry code 30081)
- [GE CF6-50C1](https://openairdocs.org/engine/ge-cf6-50c1): 0 aircraft (registry code 30084)
- [GE CF6-50C2B](https://openairdocs.org/engine/ge-cf6-50c2b): 0 aircraft (registry code 30090)
- [GE CF6-50C2D](https://openairdocs.org/engine/ge-cf6-50c2d): 0 aircraft (registry code 30086)
- [GE CF6-50CA](https://openairdocs.org/engine/ge-cf6-50ca): 0 aircraft (registry code 30083)
- [GE CF6-50E](https://openairdocs.org/engine/ge-cf6-50e): 0 aircraft (registry code 30087)
- [GE CF6-50E1](https://openairdocs.org/engine/ge-cf6-50e1): 0 aircraft (registry code 30088)
- [GE CF6-50E2](https://openairdocs.org/engine/ge-cf6-50e2): 0 aircraft (registry code 30089)
- [GE CF6-50E2B](https://openairdocs.org/engine/ge-cf6-50e2b): 0 aircraft (registry code 30091)
- [GE CF6-6D1](https://openairdocs.org/engine/ge-cf6-6d1): 0 aircraft (registry code 30077)
- [GE CF6-6D1A](https://openairdocs.org/engine/ge-cf6-6d1a): 0 aircraft (registry code 30078)
- [GE CF6-6K](https://openairdocs.org/engine/ge-cf6-6k): 0 aircraft (registry code 30079)
- [GE CF6-6K2](https://openairdocs.org/engine/ge-cf6-6k2): 0 aircraft (registry code 30080)

## STCs approved under this data sheet (5)

- [STC SE00025EN](https://openairdocs.org/stc/SE00025EN): Installation of International Aerospace Tubes, LLC, Master Drawing List TPC Stage 7 Cooling System ,
revision NR, dated December 15, 2011, or later FAA-Approved Revisions. United Technologies Corporation, Pratt & Whitney Division
- [STC SA1139NW-D](https://openairdocs.org/stc/SA1139NW-D): Install fireproof blankets on Engine Fan Reverser Intermediate Fireseal in lieu of Fireproof Intumescent Coating.. United Airlines Inc
- [STC SE91WE](https://openairdocs.org/stc/SE91WE): Removal of General Electric 'EGT cable and conduit assembly,' P/N9037M17P03 or 9037M17P04, and replacement with Co-Operative Industries P/N 66615.. Boeing Company
- [STC SE00969CH](https://openairdocs.org/stc/SE00969CH): Install AeroControlex P/N 2605290-001 variable stator feedback control cable.. AeroControlex Group TransDigm Inc
- [STC SE00461LA](https://openairdocs.org/stc/SE00461LA): Install fireproof blankets on the engine fan reverser intermediate fireseal, in lieu of fireproof intumescent coating.. Hi Temp Insulation Inc

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.