# TCDS E13NE: General Electric Company GE Aerospace

- Type: Type certificate data sheet
- Status: Current
- Holder: General Electric Company GE Aerospace
- Revision: 27
- Revised: August 6, 2024
- Product: Engine
- Certification basis: Part 33
- Registered aircraft: 629, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/b3/ef/b3ef364c6acb5465a559b8913589c35a7ea60e69cce68df3aeb52e3cd58543ed
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID102644680020240807131204.0001
- Page: https://openairdocs.org/tcds/E13NE

## Models (28)

As the data sheet lists them.

- CF6-80C2A8
- CF6-80C2B4
- CF6-80A2
- CF6-80C2B4F
- CF6-80C2B5F
- CF6-80C2B7F
- CF6-80C2B1F2
- CF6-80C2A1
- CF6-80C2D1F
- CF6-80C2B6FA
- CF6-80A1
- CF6-80C2K1F
- CF6-80C2B8F
- CF6-80C2B6
- CF6-80C2B1F
- CF6-80C2A3
- CF6-80C2L1F
- CF6-80C2B1
- CF6-80A
- CF6-80C2A5
- CF6-80C2A2
- CF6-80C2B2F
- CF6-80C2B6F
- CF6-80A3
- CF6-80C2B2
- CF6-80C2A5F
- CF6-80C2B1F1
- CF6-80C2B3F

## 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 12 13 14 15 16 17 18 19 20 
REV 27 25 25 25 25 25 26 27 23 25 25 24 24 25 25 25 25 25 25 27 
 
 
U.S. DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
TYPE CERTIFICATE DATA SHEET E13NE 
TCDS NUMBER E13NE 
REVISION: Revision 27 
Date: August 6, 2024 
GENERAL ELECTRIC COMPANY 
MODELS: 
CF6-80A  CF6-80C2B1  CF6-80C2B1F1 
CF6-80A1 CF6-80C2B2 CF6-80C2D1F 
CF6-80A2 CF6-80C2B4 CF6-80C2A5F 
CF6-80A3 CF6-80C2B6 CF6-80C2B7F 
 
CF6-80C2A1  CF6-80C2B1F  CF6-80C2B1F2 
CF6-80C2A2 CF6-80C2B2F CF6-80C2B6FA 
CF6-80C2A3 CF6-80C2B3F CF6-80C2B5F 
CF6-80C2A5 CF6-80C2B4F CF6-80C2B8F 
CF6-80C2A8 CF6-80C2B6F 
CF6-80C2L1F CF6-80C2K1F 
 
Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E13NE) and other approved data on 
file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data 
sheets and applicable portions of the Federal Aviation Regulations, provided they are installed, operated, and maintained as prescribed by the 
approved manufacturer's manuals and other approved instructions. 
TYPE CERTIFICATE (TC) HOLDER:  GENERAL ELECTRIC COMPANY 
GE AEROSPACE 
1 NEUMANN WAY 
CINCINNATI, OH 45215-6301 
 
I. MODELS CF6-80A CF6-80A1 CF6-80A2 CF6-80A3 
TYPE Dual rotor, axial flow, high bypass turbofan. The 14-stage high pressure 
compressor is driven by a 2-stage high pressure turbine and the integrated front 
fan and low pressure compressor are driven by a 4-stage low pressure turbine. 
RATINGS (See NOTE 5)     
Maximum continuous at sea     
level, static thrust, lb 43,660 43,610 45,720 45,800 
Takeoff (5 min.) at sea level, static thrust, lb     
(See NOTE 23) 46,930 46,990 48,670 48,970 
Flat rating ambient temperature     
Takeoff 92oF/33.3oC - - - - - - 
Maximum continuous 77oF/25.0oC - - - - - - 
MAIN ENGINE CONTROL, WOODWARD     
GE P/N 9238M79 9363M11 9238M79 9363M11 
POWER MANAGEMENT CONTROL     
GE P/N 7076M98 7084M12 7076M98 7084M12 
 1305M68 --- 1305M69 1305M70 
 
 
 
 
 
 
 
PAGE 21 
REV 27 
 
LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" 
"---" NOT APPLICABLE 
NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN.

TCDS E13NE 2 
 
 
I. MODELS (Continued) CF6-80A CF6-80A1 CF6-80A2 CF6-80A3 
EGT SHUNT JUNCTION BOX 
(See NOTE 15) 
GE P/N 
FUEL PUMP 
GE P/N 
 
IGNITION SYSTEM 
Two ignition units 
GE P/N 
Or GE P/N 
Two ignitor plugs 
GE P/N 
Or GE P/N 
 
PRINCIPAL DIMENSIONS 
Length (in) (fan spinner to LPT aft 
flange face) 
Width (in) (maximum envelope) 
Height (in) (maximum envelope) 
WEIGHT (DRY) (lb) 
 
9230M48P02 
 
 
9304M23 
 
 
 
9101M52 
9238M66 
 
9101M37 
1305M52 
 
 
 
166.9 
97.9 
95.1 
 
8,776 
 
- - 
9039M45 
- - 
- - 
 
- - 
- - 
 
 
 
- - 
94.5 
105.6 
8,760 
 
- - 
9304M23 
- - 
- - 
 
- - 
- - 
 
 
 
- - 
97.9 
95.1 
8,776 
 
- - 
9039M45 
- - 
- - 
 
- - 
- - 
 
 
 
- - 
94.5 
105.6 
8,760 
 NOTE: Weight includes basic engine accessories & optional equipment as 
listed in the manufacturer's engine specifications, including condition 
monitoring instrumentation sensors. 
CENTER OF GRAVITY LOCATIONS 
Station (in) (engine only) 
Waterline (in) (engine only) 
Buttline  (in) (engine only) 
222.8+2.0 
98.2+1.0 
99.8+0.5 
219.4+2.0 
95.8+1.0 
98.7+0.5 
222.8+2.0 
98.2+1.0 
99.8+0.5 
219.4+2.0 
95.8+1.0 
98.7+0.5 
 
II. MODELS CF6-80C2A1 CF6-80C2A2 CF6-80C2B1 CF6-80C2B4 
TYPE Dual rotor, axial flow high bypass turbofan. The 14-stage compressor is driven 
by a 2-stage high pressure turbine and the integrated front fan and low pressure 
compressor are driven by a 
5-stage low pressure turbine. 
RATINGS (See NOTE 5)     
Maximum continuous at sea     
level, static thrust, lb 53,390 48,080 49,550 52,370 
Takeoff (5 min.) at sea level, static thrust, lb     
(See NOTE 23) 57,860 52,460 55,980 57,180 
Flat rating ambient temperature     
Takeoff 86oF/30oC 111oF/44oC 86oF/30oC 90oF/32.2oC 
Maximum continuous 77oF/25.0oC - - - - - - 
MAIN ENGINE CONTROL, WOODWARD     
GE P/N 1332M18 - - --- --- 
 1332M19 - - - - - - 
 1459M60 - - --- --- 
 1459M77 - - --- --- 
POWER MANAGEMENT CONTROL     
GE P/N 1339M18 1339M19 1339M21 1339M20

TCDS E13NE 3 
 
 
II. MODELS (Continued) CF6-80C2A1 CF6-80C2A2 CF6-80C2B1 CF6-80C2B4 
EGT SHUNT JUNCTION BOX 
(See NOTE 15) 
GE P/N 
 
 
 
FUEL PUMP 
GE P/N 
IGNITION SYSTEM 
Two ignition units 
GE P/N 
Or GE P/N 
Two ignitor plugs 
GE P/N 
Or GE P/N 
 
PRINCIPAL DIMENSIONS 
Length (in) (fan spinner to LPT aft 
flange face) 
Width (in) (maximum envelope) 
Height (in) (maximum envelope) 
WEIGHT (DRY) (lb) 
 
1325M15P05 
1325M15P07 
1383M97P03 
1383M97P07 
 
9355M33 
 
 
 
9238M66 
--- 
 
9392M95 
9387M23 
 
 
168.26 
105.10 
105.97 
 
9,480 
 
- - 
- - 
- - 
- - 
 
- - 
 
 
 
- - 
--- 
 
- - 
- - 
 
 
- - 
- - 
- - 
 
- - 
 
- - 
- - 
- - 
- - 
 
- - 
 
 
 
- - 
--- 
 
--- 
- - 
 
 
- - 
- - 
- - 
 
9,670 
 
--- 
- - 
- - 
- - 
 
- - 
 
 
 
- - 
--- 
 
--- 
- - 
 
 
- - 
- - 
- - 
 
- - 
 NOTE: Weight includes basic engine accessories & optional equipment as 
listed in the manufacturer's engine specifications, including condition 
monitoring instrumentation sensors. 
CENTER OF GRAVITY LOCATIONS 
Station (in) (engine only) 
Waterline (in) (engine only) 
Buttline  (in) (engine only) 
223.93+2.0 
98.90+0.5 
100.00+0.5 
- - 
- - 
- - 
- - 
- - 
- - 
223.86+2.0 
98.86+0.5 
99.97+0.5 
 
III. MODELS CF6-80C2A3 CF6-80C2B2 CF6-80C2B6 CF6-80C2A5 CF6-80C2A8 
TYPE Dual rotor, axial flow high bypass turbofan. The 14-stage compressor is driven by a 2- 
stage high pressure turbine and the integrated front fan and low pressure compressor are 
driven by a 5-stage low pressure turbine. 
RATINGS (See NOTE 5)      
Maximum continuous at sea      
level, static thrust, lb 54,790 49,020 56,100 56,210 48,080 
Takeoff (5 min.) at sea level, static thrust,      
lb (See NOTE 23) 58,950 51,950 60,070 60,100 57,860 
Flat rating ambient temperature      
Takeoff 86oF/30oC 90oF/32.2oC 86oF/30oC - - 95oF/35oC 
Maximum continuous 77oF/25oC 86oF/30oC 77oF/25oC - - - - 
MAIN ENGINE CONTROL,      
WOODWARD 1459M60 1453M12 1538M66 1459M60 - - 
GE P/N 1459M77     
POWER MANAGEMENT CONTROL 
     
GE P/N 1374M93 1374M94 1457M16 1459M13 1672M13

TCDS E13NE 4 
 
 
III. MODELS (Continued) CF6-80C2A3 CF6-80C2B2 CF6-80C2B6 CF6-80C2A5 CF6-80C2A8 
EGT SHUNT JUNCTION BOX 
(See NOTES 1 & 19) 
GE P/N 
 
 
FUEL PUMP 
GE P/N 
 
1325M15P07 
1383M97P03 
1383M97P07 
 
 
9355M33 
 
- - 
- - 
- - 
 
 
- - 
 
--- 
- - 
- - 
 
 
- - 
 
--- 
- - 
- - 
 
 
- - 
 
--- 
- - 
- - 
 
 
- - 
IGNITION SYSTEM 
Two ignition units / GE P/N 
Two ignitor plugs / GE P/N 
PRINCIPAL DIMENSIONS 
Length (in) (fan spinner to LPT aft 
flange face) 
Width (in) (maximum envelope) 
Height (in) (maximum envelope) 
 
WEIGHT (DRY) (lb) 
 
9238M66 
9387M23 
 
 
 
168.26 
105.10 
105.97 
9,480 
 
- - 
- - 
 
 
 
- - 
- - 
- - 
9,670 
 
- - 
- - 
 
 
 
- - 
- - 
- - 
- - 
 
- - 
- - 
 
 
 
- - 
- - 
- - 
9,480 
 
- - 
- - 
 
 
 
- - 
- - 
- - 
- - 
 NOTE: Weight includes basic engine accessories & optional equipment as listed in the 
manufacturer's engine specifications, including condition monitoring instrumentation sensors. 
CENTER OF GRAVITY LOCATIONS 
Station (in) (engine only) 
Waterline (in) (engine only) 
Buttline (in) (engine only) 
223.86+2.0 
98.86+0.5 
99.97+0.5 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
 
IV. MODELS CF6-80C2B1F CF6-80C2B2F CF6-80C2B4F CF6-80C2B6F CF6-80C2D1F 
TYPE Dual rotor, axial flow high bypass turbofan. The 14-stage compressor is driven by a 2-stage high 
pressure turbine and the integrated front fan and low pressure compressor are driven by a 5-stage 
low pressure turbine. 
RATINGS (See NOTE 5) 
Maximum continuous at sea 
level, static thrust, lb 
Takeoff (5 min.) at sea level, static 
thrust, lb (See NOTE 23) 
 
Flat rating ambient temperature 
Takeoff 
Maximum continuous 
HYDROMECHANICAL UNIT 
GE P/N 
 
ELECTRONIC CONTROL UNIT, 
GE P/N 
 
49,810 
 
 
57,160 
 
 
90oF/32.2oC 
77oF/25oC 
 
 
1383M68 
 
 
1471M63 
1519M89 
1820M33 
2121M25 
2121M26 
 
49,140 
 
 
52,010 
 
 
- - 
86oF/30oC 
 
 
- - 
 
 
- - 
- - 
- - 
- - 
- - 
 
52,470 
 
 
57,280 
 
 
- - 
77oF/25oC 
 
 
- - 
 
 
- - 
- - 
- - 
- - 
- - 
 
56,170 
 
 
60,030 
 
 
86oF/30oC 
- - 
 
 
- - 
 
 
- - 
- - 
- - 
- - 
- - 
 
56,730 
 
 
60,690 
 
 
- - 
- - 
1471M24 
1519M91 
1820M34 
--- 
--- 
---

TCDS E13NE 5 
 
 
IV. MODELS (CONTINUED) CF6-80C2B1F CF6-80C2B2F CF6-80C2B4F CF6-80C2B6F CF6-80C2D1F 
ELECTRONIC CONTROL UNIT, 
(cont.) 
GE P/N 
 
 
 
IDENTIFICATION PLUG 
(See NOTE 21) GE P/N 
 
 
EGT SHUNT JUNCTION BOX 
(See NOTES 15, 19, & 20) GE P/N 
 
 
 
FUEL PUMP GE P/N 
 
2121M29 
2121M37 
2121M38 
2121M41 
 
 
1851M56 
7161M98 
7157M87 
 
1325M15P07 
1383M97P03 
1383M97P07 
1519M97P01 
9355M33 
 
- - 
- - 
- - 
- - 
 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
- - 
- - 
 
- - 
- - 
- - 
- - 
 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
- - 
- - 
 
- - 
- - 
- - 
- - 
 
 
- - 
- - 
- - 
 
- - 
- - 
--- 
- - 
- - 
 
--- 
--- 
--- 
--- 
 
 
- - 
- - 
- - 
 
--- 
--- 
--- 
- - 
- - 
 
IGNITION SYSTEM 
Two ignition units, GE P/N 
Two ignitor plugs, GE P/N 
RATING PLUG GE P/N 
PRINCIPAL DIMENSIONS 
Length (in) (fan spinner to LPT aft 
flange face) 
Width (in) (maximum envelope) 
Height (in) (maximum envelope) 
 
WEIGHT (DRY) (lb) 
 
 
9238M66 
9387M23 
7156M94G01 
 
 
 
168.26 
111.42 
105.97 
 
9,790 
 
 
- - 
- - 
7156M94G02 
 
- - 
- - 
- - 
 
- - 
 
 
- - 
- - 
7156M94G03 
 
- - 
- - 
- - 
 
- - 
 
 
- - 
- - 
7156M94G04 
 
- - 
- - 
- - 
 
- - 
 
 
- - 
- - 
7156M94G01 
 
- - 
- - 
- - 
 
9,850 
 NOTE: Weight includes basic engine accessories & optional equipment as listed in the 
manufacturer's engine specifications, including condition monitoring instrumentation sensors. 
CENTER OF GRAVITY 
LOCATIONS 
Station (in) (engine only) 
Waterline (in) (engine only) 
Buttline (in) (engine only) 
 
223.86+2.0 
98.86+0.5 
99.97+0.5 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
 
- - 
- - 
- -

TCDS E13NE 6 
 
 
V. MODELS CF6-80C2B1F1 CF6-80C2B3F CF6-80C2A5F CF6-80C2B7F 
(See NOTE 24) 
CF6-80C2B1F2 
TYPE 
 
 
 
RATINGS (See NOTE 5) 
Maximum continuous at sea 
level, static thrust, lb 
 
Takeoff (5 min.) at sea level, static 
thrust, lb (See NOTE 23) 
 
Flat rating ambient temperature 
Takeoff 
Maximum continuous 
HYDROMECHANICAL UNIT 
GE P/N 
 
ELECTRONIC CONTROL UNIT, 
GE P/N 
Dual rotor, axial flow high bypass turbofan. The 14-stage compressor is driven by a 2-stage high 
pressure turbine and the integrated front fan and low pressure compressor are driven by a 5-stage 
low pressure turbine. 
 
49,810 
 
 
60,030 
 
 
86oF/30oC 
77oF/25oC 
 
1383M68 
 
 
1820M33 
 
39,850 
 
 
52,010 
 
 
90oF/32.2oC 
- - 
- - 
1471M63 
1519M89 
1820M33 
 
56,210 
 
 
60,100 
 
 
86oF/30oC 
- - 
- - 
1820M99 
1797M63 
--- 
 
56,170 
 
 
60,030 
 
 
- - 
- - 
- - 
1471M63 
1519M89 
1820M33 
2121M25 
2121M26 
2121M29 
2121M37 
2121M38 
2121M41 
 
49,810 
 
 
- - 
 
 
- - 
- - 
 
 
- - 
 
 
- - 
- - 
- - 
--- 
--- 
--- 
--- 
--- 
--- 
IDENTIFICATION PLUG 
(See NOTE 21) GE P/N 
 
EGT SHUNT JUNCTION BOX 
(See NOTES 15, 19, & 20) GE P/N 
 
 
FUEL PUMP 
GE P/N 
1851M56 
7161M98 
 
 
1383M97P03 
1383M97P07 
1519M97P01 
 
9355M33 
- - 
- - 
 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
 
 
--- 
--- 
- - 
 
- - 
- - 
- - 
 
 
1383M97P03 
1383M97P07 
- - 
 
- - 
- - 
- - 
 
 
- - 
- - 
- - 
 
- - 
 
IGNITION SYSTEM 
Two ignition units, GE P/N 
Two ignitor plugs, GE P/N 
RATING PLUG GE P/N 
PRINCIPAL DIMENSIONS 
Length (in) (fan spinner to LPT 
aft flange face) 
Width (in) (maximum envelope) 
Height (in) (maximum envelope) 
 
WEIGHT (DRY) (lb) 
 
9238M66 
9387M23 
7156M94G05 
 
 
 
168.26 
111.42 
105.97 
 
9,790 
- - 
- - 
7156M94G06 
 
 
- - 
- - 
- - 
 
9,499 
- - 
- - 
7156M94G01 
 
 
- - 
- - 
- - 
 
9,860 
- - 
- - 
7156M94G07 
 
 
- - 
- - 
- - 
 
9,790 
- - 
- - 
7156M94G08 
 
 
- - 
- - 
- - 
 
9,499 
  NOTE: Weight includes basic engine accessories & optional equipment as listed in the 
manufacturer's engine specifications, including condition monitoring instrumentation sensors. 
CENTER OF GRAVITY 
LOCATIONS 
Station (in) (engine only) 
Waterline (in) (engine only) 
Buttline  (in) (engine only) 
 
 
223.86+2.0 
98.86+0.5 
99.97+0.5 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
 
- - 
- - 
- - 
 
- - 
- - 
- -

TCDS E13NE 7 
 
 
 
 
VI. MODELS CF6-80C2B6FA CF6-80C2B5F CF6-80C2B8F CF6-80C2L1F CF6-80C2K1F 
TYPE Dual rotor, axial flow high bypass turbofan. The 14-stage compressor is driven by a 2-stage high 
pressure turbine and the integrated front fan and low pressure compressor are driven by a 5-stage low 
pressure turbine. 
RATINGS (See NOTE 5)    
 
44,100 
 
 
51,250 
 
 
95oF/35oC 
95oF/35oC 
 
2042M93 
--- 
--- 
--- 
--- 
--- 
--- 
--- 
--- 
--- 
 
43,400 
 
 
59,740 
 
 
86oF/30oC 
77oF/25oC 
 
- - 
--- 
--- 
--- 
--- 
--- 
--- 
--- 
--- 
--- 
Maximum continuous at sea    
level, static thrust, lb 56,170 49,810 56,170 
Takeoff (5 min.) at sea level, static    
thrust, lb (See NOTE 23) 60,030 60,030 60,030 
Flat rating ambient temperature    
Takeoff 
Maximum continuous 
86oF/30oC 
77oF/25oC 
- - 
- - 
- - 
- - 
HYDROMECHANICAL UNIT    
GE P/N 1383M68 - - - - 
ELECTRONIC CONTROL UNIT, 
GE P/N's 1820M33 2121M29 
2121M41 
1471M63 
1519M89 
1820M33 
2121M25 
- - 
- - 
- - 
- - 
  2121M26 - - 
  2121M29 - - 
  2121M37 - - 
  2121M38 - - 
  2121M41 - - 
ELECTRONIC ENGINE CONTROL 
(EEC) GE P/N 
Hardware (H/W) 
Software (S/W) 
IDENTIFICATION PLUG 
(See NOTE 21) GE P/N 
 
EGT SHUNT JUNCTION BOX 
(See NOTES 15, 19, & 20) GE P/N 
FUEL PUMP GE P/N 
IGNITION SYSTEM 
Two ignition units, GE P/N 
Two ignitor plugs, GE P/N 
RATING PLUG, GE P/N 
PRINCIPAL DIMENSIONS 
Length (in) (fan spinner to LPT 
aft flange face) 
Width (in) (maximum envelope) 
Height (in) (maximum envelope) 
 
WEIGHT (DRY) (lb) 
 
--- 
--- 
 
1851M56 
7161M98 
1519M97P01 
 
 
9355M33 
 
 
9238M66 
9387M23 
7156M94G10 
 
 
 
168.26 
111.42 
105.97 
 
9,768 
 
--- 
--- 
 
- - 
- - 
- - 
 
 
- - 
 
 
- - 
- - 
7156M94G09 
 
 
- - 
- - 
- - 
 
9,790 
 
--- 
--- 
 
- - 
- - 
- - 
 
 
- - 
 
 
- - 
- - 
7156M94G12 
 
 
- - 
- - 
- - 
 
9,790 
 
2042M67 
2044M12 
 
1754M25 
--- 
 
--- 
 
 
- - 
 
- - 
- - 
1753M83P35 
 
 
 
- - 
- - 
- - 
9,843 
 
- - 
2123M53 
- - 
--- 
--- 
 
 
- - 
 
 
- - 
- - 
- - 
 
 
 
- - 
- - 
- - 
 
- - 
 NOTE: Weight includes basic engine accessories & optional equipment as listed in the manufacturer's 
engine specifications, including condition monitoring instrumentation sensors. 
CENTER OF GRAVITY LOCATIONS 
Station (in) (engine only) 
Waterline (in) (engine only) 
Buttline (in) (engine only) 
223.86+2. 0 
98.86+1.0 
99.97+1.0 
- - 
- - 
- - 
- - 
- - 
- - 
223.9+2 .0  
98.9+1.0 
100.0+1.0 
- - 
- - 
- -

TCDS E13NE 8 
 
CERTIFICATION BASIS 
 
CF6-80A SERIES Title 14, Code of Federal Regulations (14 CFR) part 33, effective February 1, 1965, Amendments 33-1 through- 33-8 
inclusive as revised by Grant of Exemption No. 3372 from Paragraphs 33.7(c)(17), 33.14, 33.23, 33.27, and 33.88 of 
Amendment 8. 
 
TYPE CERTIFICATE E13NE 
MODELS APPLICATION DATE ISSUED/AMENDED 
 
CF6-80A DEC 01, 1978 OCT 06, 1981 
CF6-80A1 JUL 29, 1980 OCT 06, 1981 
CF6-80A2 JUN 16, 1981 OCT 06, 1981 
CF6-80A3 JUN 16, 1981 OCT 06, 1981 
 
CF6-80C2 SERIES  14 CFR part 33 effective February 1, 1965, Amendments 33-1 through 33-8 inclusive except for 
(Except CF6-80C2L1F the approved substitute compliance procedures, which are in accordance with Amendment 10. 
and CF6-80C2K1F) 
The specific requirements of Amendment 10 met are those defined in Paragraphs 33.7, 33.14, 33.23, 
33.27, 33.88, and 33.92. 
All CF6 engines approved under Type Certificate No. E13NE comply with the fuel venting emissions 
and exhaust emissions requirements of Special FAR No. 27-5. The following models comply with 14 
CFR part 34, amendment 5, effective December 31, 2012: CF6-80C2A5F, CF6-80C2A8, CF6-80C2B2, 
CF6-80C2B2F, CF6-80C2B4, CF6-80C2B4F, CF6-80C2B6, CF6-80C2B6FA, CF6-80C2D1F, CF6-
80C2B8F. 
The following models comply with 14 CFR part 34, amendment 7A, effective May 24, 2024: CF6-
80C2B1F, CF6-80C2B5F, CF6-80C2B6F, CF6-80C2B7F. 
 
See NOTE 29 for detailed summary of the certification basis for fuel venting and exhaust emissions. 
 
CF6-80C2L1F (only) 14 CFR part 33, effective February 1, 1965, Amendments 33-1 through 33-8 inclusive. 
Amendment 10 sections 33.7, 33.14, 33.23, 33.27, 33.88 and 33.92, Amendment 15 section 33.28 and 
Equivalent Level of Safety finding, 8040-ELOS-04-NE-02 for §33.89(a)(3)(ii) and (iii). 
CF6-80C2L1F model complies with 14 CFR part 34, amendment 5, effective December 31, 2012. 
See NOTE 29 for detailed summary of the certification basis for fuel venting and exhaust emissions. 
 
CF6-80C2K1F (only) 14 CFR part 33 effective February 1, 1965, Amendments 33-1 through 33-8 inclusive except for 
the approved substitute compliance procedures, which are in accordance with Amendments 9 and 10. The specific 
requirements of Amendment 9 met are those defined in Sections 33.4 and 33.5. The specific requirements of 
Amendment 10 met are those defined in Sections 33.7, 33.14, 33.23, 33.27, 33.88, and 33.92. Amendment 15 Section 
33.28. Equivalent Level of Safety (ELOS) finding, 8040-ELOS-05-NE-03 for Section 33.89(a)(3)(ii) and (iii). 
 
CF6-80C2K1F model complies with 14 CFR part 34, amendment 7A, effective May 24, 2024. See 
NOTE 29 for detailed summary of the certification basis for fuel venting and exhaust emissions.

TCDS E13NE 9 
 
 
  TYPE CERTIFICATE E13NE  
CF6-80C2 SERIES 
(continued) 
MODELS APPLICATION DATE ISSUED/AMENDED 
 CF6-80C2A1 SEP 11, 1984 JUN 28, 1985 
 CF6-80C2B1 SEP 11, 1984 JUN 28, 1985 
 CF6-80C2A2 SEP 11, 1984 DEC 30, 1985 
 CF6-80C2B4 MAR 05, 1986 OCT 31, 1986 
 CF6-80C2A3 MAR 05, 1986 DEC 09, 1986 
 CF6-80C2B2 NOV 20, 1986 APR 06, 1987 
 CF6-80C2B6 FEB 20, 1987 SEP 30, 1987 
 CF6-80C2A5 MAY 12, 1987 OCT 26, 1987 
 CF6-80C2B1F MAR 26, 1987 MAR 31, 1988 
 CF6-80C2B2F MAY 18, 1988 SEP 23, 1988 
 CF6-80C2B4F MAY 18, 1988 SEP 23, 1988 
 CF6-80C2B6F MAY 18, 1988 SEP 23, 1988 
 CF6-80C2D1F MAY 18, 1988 DEC 20, 1988 
 CF6-80C2B1F1 OCT 23, 1989 JUN 15, 1990 
 CF6-80C2A8 JUN 22, 1990 FEB 26, 1991 
 CF6-80C2B3F APR 11, 1990 NOV 23, 1992 
 CF6-80C2A5F APR 02, 1993 OCT 13, 1993 
 CF6-80C2B7F JAN 27, 1993 OCT 13, 1993 
 CF6-80C2B1F2 SEP 17, 1993 NOV 18, 1993 
 CF6-80C2B6FA JAN 31, 1994 SEP 21, 1995 
 CF6-80C2B5F AUG 11, 1994 MAY 22, 1997 
 CF6-80C2B8F SEP 02, 1997 MAR 18, 1999 
 CF6-80C2L1F JAN 30, 2002 AUG 30, 2004 
 CF6-80C2K1F JUL 14, 2004 FEB 22, 2006 
 
 
 
 
PRODUCTION BASIS Production Certificate No. 108 for engines produced by General Electric in the United States. 
 
In addition, CF6-80A series engines and parts thereof produced in Europe are eligible in accordance with the 
following: 
Société National d'Etude et de Construction de Moteurs d'Aviation (SNECMA): 
Production agreement No. 6-3032 between General Electric and SNECMA dated February 20, 1981, for complete 
engines and modules. 
Identification plates for CF6-80A1/A3 engines manufactured by SNECMA shall contain the following information: 
1. Manufacturer (SNECMA, France) 
2. Model 
3. Serial Number (Numbers 585- are assigned to CF6-80A1/A3 engines 
manufactured by SNECMA) 
4. Type Certificate Number E13NE 
5. Import TC No. M-IM13 
6. Established ratings 
 
Each individually imported engine and parts thereof must be accompanied by an airworthiness approval tag, 
JAA Form F1, issued by SNECMA on behalf of Director Generale de l'Aviation Civile under production certificate 
number P03 or a "Certificate de Navigabilite pour Exportation" delivered by the DGAC. 
Note, effective September 28, 2004, any of these engine models and parts thereof would be produced under European 
Aviation Safety Agency (EASA) Production Certificate FR.21G.0007. To be considered for installation on aircraft 
registered in the United States, each individually imported engine or parts thereof produced under EASA Production 
Certificate FR.21G.0007 must be accompanied by an EASA airworthiness approval certificate (EASA Form 1 – 
Authorized Release Certificate) issued by SNECMA under authority of the EASA Production Certificate.

TCDS E13NE 10 
 
 
PRODUCTION BASIS 
(continued) 
SNECMA: 
 
In addition, CF6-80C2 series engines (except for CF6-80C2L1F and CF6-80C2K1F models) and 
parts thereof produced in Europe are eligible in accordance with the following: 
Production agreement No. 6.3592 between the General Electric Company and SNECMA dated 
April 19, 1983, for complete engines and modules. 
 
Identification plates for CF6-80C2 engines manufactured by SNECMA shall contain the following 
information: 
1. Manufacturer (SNECMA, France) 
2. Model 
3. Serial Number (Numbers 695- are assigned to CF6-80C2 PMC engines 
manufactured by SNECMA and Numbers 703- and 705-204 and up are 
assigned to CF6-80C2 FADEC engines manufactured by SNECMA) 
4. Type Certificate Number E13NE 
5. Import TC No. M-IM13 
6. Established ratings 
 Each individually imported engine and parts thereof must be accompanied by an airworthiness 
approval tag, JAA Form F1, issued by SNECMA on behalf of Director Generale de l'Aviation 
Civile under production certificate number P03 or a "Certificate de Navigabilite pour Exportation" 
delivered by the DGAC. 
Note, effective September 28, 2004, any of these engine models and parts thereof would be 
produced under European Aviation Safety Agency (EASA) Production Certificate FR.21G.0007. 
To be considered for installation on aircraft registered in the United States, each individually 
imported engine or parts thereof produced under EASA Production Certificate FR.21G.0007 must 
be accompanied by an EASA airworthiness approval certificate (EASA Form 1 – Authorized 
Release Certificate) issued by SNECMA under authority of the EASA Production Certificate. 
 
 
 
 NOTES 
NOTE 1. MAXIMUM PERMISSIBLE ENGINE ROTOR SPEEDS 
 
Low pressure rotor (N1). 
High pressure rotor (N2). 
CF6-80A (ALL MODELS) 
4016 rpm (117.0%) 
10859 rpm (110.5%) (*) 
CF6-80C2 (ALL MODELS) 
3854 rpm (117.5%) 
11055 rpm (112.5%) 
NOTE 2. MAXIMUM PERMISSIBLE TEMPERATURES 
Turbine exhaust gas temperature (T49):   
Takeoff (5 min.) 
Maximum continuous 
120 second maximum transient 
1724oF (940oC) (*) 
1643oF (895oC) (*) 1760oF (960oC) (**) 1697oF (925oC) 
1769oF (965oC) for B8F only 
Starting 
(max transient 40 secs) 
Starting 
(max no time limit) 
 
1598oF (870oC) 
 
1382oF (750oC) 
 
- - 
 
- - 
NOTES: Refer to CF6-80A Operating Instruction GEK 72506, or CF6-80C2 (except CF6-80C2L1F and CF6-80C2K1F), Operating Instruction 
GEK 92462 or GEK 112651 for CF6-80C2L1F (only) or GEK 112724 for CF6-80C2K1F (only) for time temperature envelope. 
(*) See NOTE 28 for further information regarding maximum permissible parameters on CF6-80A engines. 
(**) See NOTES 15 and 20 for further information regarding EGT Redline and EGT Junction Box.

TCDS E13NE 11 
 
 
NOTE 2. MAXIMUM PERMISSIBLE TEMPERATURES (continued) 
Fuel Pump Inlet  
CF6-80A / CF6-80A2 Refer to CF6-80A Installation Manual GEK 50460 
CF6-80A1 / CF6-80A3 Refer to CF6-80A Installation Manual GEK 50490 
CF6-80C2A1 / A2 / A3 / A5 / A8 / B1 / B2 / B4 / B6 Refer to CF6-80C2 Installation Manual GEK 50492 
CF6-80C2B1F / B2F / B3F / B4F / B6F / D1F / B1F1 / A5F / B7F / 
B1F2 / B6FA / B5F / B8F 
Refer to CF6-80C2 FADEC 
Installation Manual GEK 97284 
CF6-80C2L1F Refer to CF6-80C2L1F Installation Manual 
GEK 112655 
CF6-80C2K1F Refer to CF6-80C2K1F Installation Manual 
GEK 112723 
Oil Outlet / All Models  
Continuous operation 320oF (160oC) 
Transient operation (15 mins limit) 347oF (175oC) 
 
NOTE 3. FUEL AND OIL PRESSURE LIMITS 
FUEL PRESSURE LIMITS AT ENGINE PUMP INLET 
CF6-80A / A2 
 
GROUND STARTING 
This limit is from minimum fuel pressure of not less than 12 psia (82.7 kPa, absolute) to a maximum of 64 psig 
(441.3 kPa gage) (relative to atmosphere) with vapor/liquid ratio of zero at all conditions. 
OPERATION AND AIR STARTING 
Operation and air starting pressure limit extends from a minimum fuel pressure of more than 5.0 psi (34.5 kPa) 
above the true vapor fuel pressure to a normal maximum fuel pressure of 64 psig (441.3 kPa gage) with transient 
pressure (2 minute maximum) up to 71 psig (489.5 kPa gage) permitted (relative to the atmosphere) at all 
conditions. 
 
CF6-80A1 / A3 
 
GROUND STARTING 
This limit is from a minimum fuel pressure of not less than 12 psia (82.7 kPa, absolute) to a maximum of 50 psig 
(344.8 kPa gage) (relative to atmosphere) with vapor/liquid ratio of zero at all conditions. 
OPERATION AND AIR STARTING 
The engine fuel system will provide fuel flow and pressure required for starting and operating the engine 
throughout the defined operational envelope when the fuel pressure at the fuel pump inlet connections to the 
engine ranges from a minimum of true vapor pressure of the fuel plus 5.0 psi (34.5 kPa) to a maximum of 50 psig 
(344.8 kPa gage) supplied with vapor-free fuel for all normal operating conditions except idle power at altitudes 
greater than 10,000 feet (3.048 km). For altitudes greater than 10,000 feet (3.048 km) at least 15 psig (103.4 
kPa gage) pressure is required at the main fuel pump inlet at metered fuel flow levels of 2500 pph (1134 kg/hr) or 
less. 
 
CF6-80C2 (ALL MODELS) 
GROUND STARTING, AIR STARTING, AND OPERATION 
This limit is from a minimum fuel pressure of not less than 5.0 psia (34.34 kPa, absolute) above the true vapor 
pressure to a maximum of 70 psig (482.6 kPa gage) (relative to atmosphere) with vapor/liquid ratio of zero at all 
conditions. 
OIL PRESSURE LIMITS AT IDLE 
CF6-80A / A1 / A2 / A3 
The pressure limit at idle is 10 psid (69.0 kPa diff) minimum; varying from 26 to 120 psid (179.4 to 827.6 kPa 
diff) in the normal operating range. 
 
CF6-80C2 (ALL MODELS) 
The pressure limit at idle is 9.5 psid (65.5 kPa diff) minimum; varying from 26 to 120 psid (179.4 to 827.6 kPa 
diff) in the normal operating range. See NOTE 16.

TCDS E13NE 12 
 
 
NOTE 4. ACCESSORY DRIVE PROVISIONS 
 
CF6-80A / A2 
DRIVE PAD 
Starter 
IDG 
Hydraulic Pump (1) 
Rotation 
Facing 
Gearbox Pad 
Gear Ratio 
To 
Core Speed 
 
Horsepower 
Continuous 
Shear 
Torque 
(lb - in) 
Static 
Overhung 
Moment 
(lb - in) 
CCW (*) 
CCW 
CCW 
0.956 
0.832 
0.344 
8,400 (torque lb-in) 
175 hp 
85 hp 
16,800 
9,492 
4,260 
400 
2,000 
400 
IDG Overload Limits 225 hp "kw" equivalent for 5 minutes per 1,000 hours of operation 
225 hp "kw" equivalent for 5 seconds per hour of operation 
450 hp "kw" equivalent for 5 seconds per 1,000 hours of operation 
 (*) Counterclockwise 
CF6-80A1 / A3 
DRIVE PAD 
Rotation 
Facing 
Gearbox Pad 
Gear Ratio 
To 
Core Speed 
 
Horsepower 
Continuous 
Shear 
Torque 
(lb - in) 
Static 
Overhung 
Moment 
(lb - in) 
Starter 
IDG 
Hydraulic Pumps (2) 
CCW (*) 
CCW 
CCW 
0.956 
0.832 
0.350 
10,800 (torque lb-in) 
175 hp 
85 hp 
19,200 
9,492 
7,400 
400 
2,000 
500 
 (*) Counterclockwise 
CF6-80C2A1 / A2/ A3 / A5 / A8 / 
D1F / A5F 
DRIVE PAD 
Rotation 
Facing 
Gearbox Pad 
Gear Ratio 
To 
Core Speed 
Horsepower 
Continuous (For 
Qualification 
Testing) 
Shear 
Torque 
(lb - in) 
Static 
Overhung 
Moment 
(lb - in) 
Starter 
IDG 
Hydraulic Pumps (2) 
CCW (*) 
CCW 
CCW 
0.956 
0.832 
0.344 
8,400 (torque lb-in) 
(949.07 N-m) 
215 hp 
(160.3 kw) 
42 hp 
(31.3 kw) each pump 
16,800 
(1898.1 N-m) 
10,500 
(1186.4 N-m) 
4,260 
(481.1 N-m) 
400 
(45.2 N-m) 
2,000 
(226.0 N-m) 
400 
(45.2 N-m) 
IDG Overload Limits 225 hp (167.8 kw) for 5 minutes per 1,000 hours of operation 
225 hp (167.8 kw) for 5 seconds per hour of operation 
450 hp (335.6 kw) for 5 seconds per 1,000 hours of operation 
 (*) Counterclockwise 
CF6-80C2B1 / B2 / B4 / B6 / 
B1F/ B2F / B3F / B4F / B6F / 
B1F1 / B7F / B1F2 / B5F / B8F 
 
DRIVE PAD 
Rotation 
Facing 
Gearbox Pad 
Gear Ratio 
To 
Core Speed 
Horsepower 
Continuous (For 
Qualification 
Testing) 
Shear 
Torque 
(lb - in) 
Static 
Overhung 
Moment 
(lb - in) 
Starter 
IDG 
Hydraulic Pump (1) 
CCW (*) 
CCW 
CCW 
0.956 
0.832 
 
0.344 
8,400 (torque lb-in) 
(949.07 N-m) 
220 hp 
(164.1 kw) 
85 hp 
(63.4 kw) 
16,800 
(1898.1 N-m) 
10,500 
(1186.4 N-m) 
4,260 
(481.1 N-m) 
400 
(45.2 N-m) 
2,000 
(226.0 N-m) 
400 
(45.2 N-m) 
IDG Overload Limits 270 hp (201.3 kw) for 5 minutes per 1,000 hours of operation 
360 hp (268.5 kw) for 10 seconds per hour of operation 
450 hp (335.6 kw) for 5 seconds per 1,000 hours of operation 
 (*) Counterclockwise

TCDS E13NE 13 
 
 
 
NOTE 4. ACCESSORY DRIVE PROVISIONS (Cont.) 
 
CF6-80C2B6FA 
DRIVE PAD 
Rotation 
Facing 
Gearbox Pad 
Gear Ratio 
To 
Core Speed 
Horsepower 
Continuous (For 
Qualification 
Testing) 
Shear 
Torque 
(lb - in) 
Static 
Overhung 
Moment 
(lb - in) 
Starter CCW(*) 0.956 8,400 (torque, lb-in) 16,800 400 
   (949.07N-m) (1898.1N-m) (45.2 N-m) 
IDG No. 1 (Aft) CCW 0.832 270 hp 14,000 2,300 
   (201.3 kw) (1581.9N-m) (260.0 N-m) 
IDG No. 2 (Forward) CCW 0.817 270 hp 14,000 2,300 
   (201.3 kw) (1581.9N-m) (260.0 N-m) 
Hydraulic Pump (1) CCW 0.344 85.0 hp 4,260 400 
   (63.4 kw) (481.1N-m) (45.2 N-m) 
IDG Overload Limits a. 325 hp (242.3 kw) for 5 minutes per 1,000 hours of operation. 
b. 435 hp (324.4 kw) for 10 seconds per 1,000 hours of operation. 
c. 525 hp (391.5 kw) for 1 second per 5,000 hours of operation. 
 * Counterclockwise 
See CF6-80C2 FADEC Installation Manual GEK 97284 for limits on allowable combinations of power extraction and compressor bleed 
for CF6-80C2B6FA. 
 
CF6-80C2L1F / CF6- 
80C2K1F 
DRIVE PAD 
Rotation 
Facing 
Gearbox Pad 
Gear Ratio 
To 
Core Speed 
Horsepower 
Continuous (For 
Qualification 
Testing) 
Shear 
Torque 
(lb - in) 
Static 
Overhung 
Moment 
(lb - in) 
Starter CCW(*) 0.956 8,400 (torque, lb-in) 16,800 400 
   (949.1N-m) (1898.1N-m) (45.2 N-m) 
IDG CCW 0.832 139 hp 9450 2,000 
   (103.7 kw) (1067.7 N-m) (226.0 N-m) 
Hydraulic Pump (2) CCW 0.344 80 hp 8150 400 
   (59.7 kw) (920.8 N-m) (45.2 N-m) 
IDG Overload Limits 225 hp (167.86 kw) for 5 minutes and 5 seconds per fight . 
375 hp (279.77 kw) for 5.5 seconds per flight. 
 (*) Counterclockwise 
 
NOTE 5. ENGINE RATINGS ARE DEFINED UNDER THE FOLLOWING CONDITIONS: 
CF6-80 (ALL MODELS) 
Fan inlet air at 59oF and 29.92 in. hg. abs. zero humidity. 
Ideal engine inlet (100% bellmouth recovery). 
No external air bleed or accessory drive power for aircraft accessories. 
Turbine temperature and engine rotor speed limits not exceeded. 
Also with the following flight exhaust system definition. 
 
CF6-80A CF6-80C2 A1 / CF6-80C2 
A1/A2/A3 A2/A3/A5/A8 CF6-80C2B1 B2/B4/B6 
 
NS-CF6-1 ES-CF6-1G01 TR-CF6-F23G03 TR-CF6-F23G01 
NS-CF6-1G01 ES-CF6-1G02 TR-CF6-F23G04 TR-CF6-F23G02 
NS-CF6-1G02 ES-CF6-1G03 TR-CF6-F23G07 TR-CF6-F23G05 
NS-CF6-1G03 ES-CF6-1G04 TR-CF6-F23G08 TR-CF6-F23G06 
NS-CF6-1G04   TR-CF6-F23G11 TR-CF6-F23G09 
TR-CF6-F23G12  TR-CF6-F23G10 
TR-CF6-F23G13 
TR-CF6-F23G14

TCDS E13NE 14 
 
 
NOTE 5. ENGINE RATINGS ARE DEFINED UNDER THE FOLLOWING CONDITIONS (Cont.) : 
 
 
CF6-80C2B1F/ CF6-80C2 
B1F1/B3F/B1F2/B5F B2F/B4F/B6F/B7F/B8F CF6-80C2D1F CF6-80C2A5F 
 
TR-CF6-F23FG03  TR-CF6-F23FG01  ES-CF6-2G01  ES-CF6-5G01 
TR-CF6-F23FG04 TR-CF6-F23FG02 ES-CF6-2G02 ES-CF6-5G02 
TR-CF6-F23FG07 TR-CF6-F23FG05 ES-CF6-2G03 ES-CF6-5G03 
TR-CF6-F23FG08 TR-CF6-F23FG06 ES-CF6-2G04 ES-CF6-5G04 
TR-CF6-F23FG11 TR-CF6-F23FG09 ES-CF6-2G05 
TR-CF6-F23FG12 TR-CF6-F23FG10 ES-CF6-2G06 CF6-80C2L1F (See NOTE 26)  
TR-CF6-F23FG13  ES-CF6-2G07 491F5000000-501 (TR Position 1) 
TR-CF6-F23FG14 ES-CF6-2G08  491F5000000-502 (TR Position 2) 
ES-CF6-2G09 491F5000000-503 (TR Position 3) 
CF6-80C2B6FA ES-CF6-2G10 491F5000000-504 (TR Position 4) 
TR-CF6-F23FAG01 ES-CF6-2G11 737L827G01 (Primary Exhaust) 
TR-CF6-F23FAG02 ES-CF6-2G12 
CF6-80C2K1F (See NOTE 26) 
491J2000100-501 (TR Position 1) 
491J2000200-501 (TR Position 2) 
737L827G01 (Primary Exhaust) 
 
 
NOTE 6. MAXIMUM PERMISSIBLE AIR BLEED EXTRACTION 
 
 
 
(*) Intermittent operation is defined as "dispatch with a system inoperative, or bleed system, or engine failure inflight" and 
should be confined to the physical core speed (N2) range of 8009 (81.5%) to 9680 (98.5%) rpm as shown in the above 
tabulation. At all normal flight conditions, maximum bleed will remain 5% of core engine physical airflow. The 
manufacturer is to be consulted regarding conditions, number of occurrences, and duration of each occurrence within the 
limitations of: 
 
The 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). 
(**) 5.75 maximum allowable stage 8 bleed when 10th stage customer bleed is also used. 
BLEED LOCATION CF6-80A/A2 CF6-80A1/A3 
Stage 8, compressor airflow, normal 5.00% 5.00% 
Stage 8, compressor airflow, intermittent (*)   
N2 RPM 8009-8600 5.75% 5.75% 
N2 RPM 8600-8850 6.25% (**) --- 
N2 RPM 8850-9680 5.75% --- 
Compressor discharge   
Steady state at takeoff rating 5.00% 5.00% 
Steady state between 80% N2 and maximum continuous 10.00% 10.00% 
During acceleration above 80% N2 7.00% 7.00% 
Operating at 80% N2 or below 12.50% 12.50% 
Stage 10 2.00% 2.00% 
Stage 11 --- ---

TCDS E13NE 15 
 
 
NOTE 6. MAXIMUM PERMISSIBLE AIR BLEED EXTRACTION (Cont.) 
 
BLEED LOCATION 
CF6-80C2 
FADEC (*) 
(Percent) 
CF6-80C2 
PMC 
(Percent) 
Stage 8, compressor airflow, normal 8.8 8.8 
Stage 11 1.5 1.5 
Compressor discharge   
Steady state at takeoff rating 5.0 5.0 
Steady state at maximum continuous or below 10.0  
Transient operation above maximum continuous rating 7.0  
Steady state between 80% N2 and maximum continuous  10.0 
During acceleration above 80% N2  7.0 
Operating at 80% N2 or below  12.0 
 
(*) See CF6-80C2 FADEC Installation Manual for limits on allowable combinations of power extraction and compressor 
bleed for CF6-80C2B6FA. 
 
NOTE 7. FUEL 
Eligible fuels must conform to GE Specification D50TF2. The latest specification revision will apply. 
NOTE 8. Cyclic life limits for critical rotating and static components are published in the Airworthiness 
Limitations Sections of CF6-80A Engine Manual GEK 72501, CF6-80C2 Engine Manual GEK 92451, 
CF6-80C2L1F Engine Manual GEK112213 and CF6-80C2K1F Engine Manual GEK112721. 
 
 
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. RESERVED 
NOTE 11. For CF6-80A inflight operation during icing conditions, the minimum permissible N1 rpm is 40% for 
CF6-80 series engines. However, momentary N1 excursions below 40%, not to exceed 60 seconds 
duration, are permissible for approach and landing operation below 10,000 feet pressure altitude. For 
CF6-80C2 operation, the minimum idle permissible inflight corresponds to N2 (core) = 6050 rpm, which 
is a preset limit within the Main Engine Control, (PMC engines) or Electronic Control Unit (FADEC 
engines) and is not field adjustable. 
NOTE 12. CF6-80A1/A3 Models 
The engine manufacturer supplies Nacelle System NS-CF6-1. The following kits listed, which are part 
of this Nacelle system, have been approved for installation on CF6-80A1/A3 engines in accordance with 
14 CFR part 33. 
 
SYSTEM KIT NUMBER 
Nozzle & Centerbody 
 
Engine Attach Fittings 
Lower Aft Mount 
Upper Aft Mount 
Engine Assembled EBU 
 
Fan Reverser TR-CF6-F23G02 
Position #1 
Position #2 
 
Fan Reverser Actuation System 
Supply Air - Pylon Mounted 
Supply Air - Engine Mounted 
Compartment Cooling Air System 
Fuel Flowmeter 
681L287 
 
681L288 
681L294 
681L185 
 
 
681L292 
681L293 
 
 
681L188 
681L189 
 
681L244 
681L250

TCDS E13NE 16 
 
 
NOTE 12. 
(cont.) 
CF6-80C2 Models 
The engine manufacturer supplies the engine assembled EBU for CF6-80C2A1 / A2 / A3 / A5 / A8 / 
A5F; CF6-80C2B1 / B2 / B4 / B6; CF6-80C2B1F / B2F / B3F / B4F / B5F / B6F / B7F / B1F1/B1F2; 
and CF6-80C2D1F , CF6-80C2L1F and CF6-80C2K1F engines. The components, which had been 
approved for installation on CF6-80C2 engines in accordance with 14 CFR part 33, are defined in the 
model lists CF6-80C2A1 / A2 / A3 / A5/ A8; CF6-80C2B1 / B2 /B4 / B6; CF6-80C2B1F / B2F / B3F / 
B4F / B5F / B6F / B7F / B1F1 / B1F2 / B6FA / B8F; CF6-80C2D1F; CF6-80C2A5F; CF6-80C2L1F; 
and CF6-80C2K1F. 
 
The engine manufacturer also supplies total exhaust system and engine attach fittings for the CF6- 
80C2A1 / A2 / A3 / A5 / A8; the CF6-80C2A5F, the CF6-80C2L1F, the CF6-80C2K1F and CF6- 
80C2D1F (except D1F upper aft mount beam), but supplies only the Fan Reverser System for the CF6- 
80C2B1 / B2 / B4 / B6 and CF6-80C2B1F / B2F / B3F / B4F / B5F / B6F / B7F / B1F1 / B1F2 / B6FA / 
B8F engines. 
The exhaust system (ES) and Fan Reverser (TR) Kit numbers approved for installation under 14 CFR 
part 33 are listed in NOTE 5 of this TCDS. 
 
NOTE 13. Overhaul of CF6-80C2L1F and CF6-80C2K1F engine components is not authorized until Instructions for 
Continued Airworthiness (ICA) become available. In the interim, components utilizing new part 
tolerance may be provided by the manufacturer. 
NOTE 14. Oil synthetic type conforming to GE Specification D50TF1. GE Service Bulletin 79-0001 lists approved 
oils and applicable restrictions. 
NOTE 15. The indicated 960oC EGT Redline for the CF6-80C2 engines using EGT Shunt Junction Box P/N 
1325M15P05 or 1325M15P07 corresponds to an actual 1005oC EGT. The indicated 960oC EGT Redline 
for CF6-80C2 engines using EGT Shunt Junction Box P/N 1383M97P03 or 1383M97P07 corresponds to 
an actual 1020oC EGT. CF6-80C2A1/A2/A3/B1/B2/B4 and CF6-80C2B1F/B2F/B3F/B4F models 
equipped with EGT Shunt Junction Box P/N 1383M97P03/P07 must also incorporate the HP/LP turbine 
hardware and associated changes per General Electric CF6-80C2 Service Bulletins 72-201, 72-222, 
72-240, 72-241, 72-248, 72-255, 72-268, 77-005, and 77-006. Refer to previous pages for EGT Shunt 
Junction Box applications to the various engine models. 
NOTE 16. CF6-80C2 models only: During negative-g operation only, it is permissible to operate below minimum 
oil pressure (10 psid indicated) for a maximum of 30 seconds. See Sections 6 of CF6-80C2 Specific 
Operating Instructions, GEK 92462, CF6-80C2L1F GEK 112651, and CF6-80C2K1F GEK 112724. 
NOTE 17. THESE MODELS INCORPORATE THE FOLLOWING GENERAL CHARACTERISTICS 
SERIES CF6-80A CHARACTERISTICS 
CF6-80A  Basic model. 
CF6-80A1  Same as CF6-80A, except the engine incorporates a fan case mounted gearbox. 
CF6-80A2  Same as CF6-80A, except increased takeoff thrust rating. Corresponding PMC and MEC 
changes. 
CF6-80A3  Same as CF6-80A1, except increased takeoff thrust rating. Corresponding PMC and 
MEC changes. 
SERIES CF6-80C2 
CF6-80C2A1 Basic model (takeoff ideal thrust rating: 59,000 pounds). 
CF6-80C2A2 Same as 80C2A1, except lower takeoff thrust rating (53,500 ideal). Corresponding PMC 
and MEC changes. 
CF6-80C2A3 Same as 80C2A1, except higher takeoff thrust rating (60,200 ideal). Corresponding PMC 
and MEC changes.

TCDS E13NE 17 
 
 
 
NOTE 17. 
(cont.) 
THESE MODELS INCORPORATE THE FOLLOWING GENERAL CHARACTERISTICS (Cont.) 
CF6-80C2B1  Same as 80C2A1, except lower takeoff thrust rating (56,700 ideal). Corresponding PMC 
and MEC changes. Minor airframe related hardware changes, and added servo fuel 
heater. 
CF6-80C2B2  Same as 80C2A1, except lower takeoff thrust rating (52,500 ideal). Corresponding PMC 
and MEC changes. Minor airframe related hardware changes, and added servo fuel 
heater. 
CF6-80C2B4  Same as 80C2A1, except lower takeoff thrust rating (57,900 ideal). Corresponding PMC 
and MEC changes. Minor airframe related hardware changes, and added servo fuel 
heater. 
CF6-80C2B6 
 
Same as 80C2A1, except higher takeoff thrust rating (60,800 ideal). Corresponding PMC 
and MEC changes. Minor HPT and LPT hardware changes, minor airframe related 
hardware changes, and added servo fuel heater. 
CF6-80C2A5  Same as 80C2A1, except higher takeoff thrust rating (61,300 ideal). Corresponding PMC 
and MEC changes. Minor HPT and LPT hardware changes. 
CF6-80C2A8  Same as 80C2A1, except takeoff thrust is flat rated to 95ºF. Corresponding PMC and 
MEC changes. Minor HPT and LPT hardware changes. 
CF6-80C2B1F Same as 80C2A1, except lower takeoff thrust rating (58,000 ideal). Incorporates Full 
Authority Digital Engine Control (FADEC), modulated active clearance control for the 
HPT and LPT, modulated bore cooling, two levels of 11th stage cooling to the HPT and 
redesigned accessory gearbox. Minor airframe related hardware changes, and added servo 
fuel heater. 
CF6-80C2B1F1 Same as 80C2A1, except higher takeoff thrust rating (60,800 ideal) and maximum 
continuous rating same as 80C2B1F. Minor HPT and LPT hardware changes. 
Incorporates Full Authority Digital Engine Control (FADEC), modulated active clearance 
control for the HPT and LPT, modulated bore cooling, two levels of the 11th stage cooling 
to the HPT and redesigned accessory gearbox. Minor airframe related hardware changes, 
and added servo fuel heater. Only ECU P/N 1820M33P04 incorporating 8.2.N software 
can be used on the CF6-80C2B1F1. See NOTE 27. 
CF6-80C2B2F Same as 80C2A1, except lower takeoff thrust rating (52,700 ideal). Incorporates Full 
Authority Digital Engine Control (FADEC), modulated active clearance control for the 
HPT and LPT, modulated bore cooling, two levels of 11th stage cooling to the HPT and 
redesigned accessory gearbox. Minor airframe related hardware changes, and added servo 
fuel heater. 
CF6-80C2B3F Same as 80C2A1, except lower takeoff thrust rating (52,700 ideal). Incorporates Full 
Authority Digital Engine Control (FADEC), modulated active clearance control for the 
HPT and LPT, modulated bore cooling, two levels of 11th stage cooling to the HPT and 
redesigned accessory gearbox. Minor airframe related hardware changes, and added servo 
fuel heater. Only ECU P/Ns 1471M63P31, 1519M89P21, or 1820M33P04 incorporating 
8.2.N software can be used on the CF6-80C2B3F. See NOTE 27. 
CF6-80C2B4F Same as 80C2A1, except lower takeoff thrust rating (58,100 ideal). Incorporates Full 
Authority Digital Engine Control (FADEC), modulated active clearance control for the 
HPT and LPT, modulated bore cooling, two levels of 11th stage cooling to the HPT and 
redesigned accessory gearbox. Minor airframe related hardware changes, and added servo 
fuel heater. 
CF6-80C2B6F Same as 80C2A1, except higher takeoff thrust rating (60,800 ideal). Minor HPT and LPT 
hardware changes. Incorporates Full Authority Digital Engine Control (FADEC), 
modulated active clearance control for the HPT and LPT, modulated bore cooling, two 
levels of 11th stage cooling to the HPT and redesigned accessory gearbox. Minor 
airframe related hardware changes, and added servo fuel heater.

TCDS E13NE 18 
 
 
NOTE 17 
(cont.) 
THESE MODELS INCORPORATE THE FOLLOWING GENERAL CHARACTERISTICS (cont.) 
CF6-80C2D1F Same as CF6-80C2A1, except higher takeoff rating (61,960 ideal). Minor HPT and LPT 
hardware changes. Incorporates Full Authority Digital Engine Control (FADEC), 
modulated active clearance control for the HPT and LPT, modulated bore cooling, and 
two levels of 11th stage cooling to the HPT. Minor airframe related changes. 
CF6-80C2A5F Same as 80C2A1, except higher takeoff thrust rating (61,300 ideal). Minor HPT and LPT 
hardware changes. Incorporates Full Authority Digital Engine Control (FADEC), 
modulated active clearance control for the HPT and LPT, modulated bore cooling. Minor 
airframe related hardware changes, and added servo fuel heating system. 
CF6-80C2B7F Same as 80C2A1, except higher takeoff thrust rating (60,800 ideal). Minor HPT and LPT 
hardware changes. Incorporates Full Authority Digital Engine Control (FADEC), 
modulating active clearance control for the HPT and LPT, modulated bore cooling, two 
levels of 11th stage cooling to the HPT and redesigned accessory gearbox. Minor 
airframe related hardware changes, and added servo fuel heater. 
CF6-80C2B1F2 Same as 80C2A1, except higher takeoff thrust rating (60,800 ideal). Incorporates Full 
Authority Digital Engine Control (FADEC), modulated active clearance control for the 
HPT and LPT, modulated bore cooling, two levels of 11th stage cooling to the HPT and 
redesigned accessory gearbox. Minor airframe related hardware changes, and added servo 
fuel heater. Only ECU P/Ns 1471M63P31, 1519M89P21, or 1820M33P04 incorporating 
8.2.N software can be used on the CF6-80C2B1F2. See NOTE 27. 
CF6-80C2B6FA Same as 80C2A1 except higher takeoff thrust rating (60,800 ideal). Minor HPT and LPT 
hardware changes. Redesigned accessory gearbox incorporating two IDG units. Second 
IDG cooler added. Incorporates Full Authority Digital Engine Control (FADEC), 
modulated active clearance control for the HPT, and a constant level of 11th stage cooling 
to HPT. Minor airframe related changes, and added servo fuel heater. 
 
Beginning with the 1995 Block 2 FADEC engine shipments (April 1995), the two levels 
of 11th stage cooling to the HPT were changed to a single level of cooling for all 
CF6-80C2 applications (Airbus, Boeing and Douglas) and the modulated bore cooling 
was changed to a single level of cooling for CF6-80C2 Boeing applications only. 
Beginning with the 1995 Block 3 engine shipments (July, 1995), the modulated active 
clearance control for the LPT was changed to a constant flow clearance control for CF6- 
80C2 Boeing applications only. 
CF6-80C2B5F Same as 80C2A1 except higher takeoff thrust rating (60,800 ideal). Minor HPT and LPT 
hardware changes. Incorporates Full Authority Digital Engine Control (FADEC), 
modulated active clearance control for the HPT, and a constant level of 11th stage cooling 
to HPT. Minor airframe related changes, and added servo fuel heater. 
CF6-80C2B8F Same as CF6-80C2B7F except for increased thrust during takeoff. In addition, the 
CF6-80C2B8F incorporates a 965oC transient EGT redline for a maximum of two 
minutes. Incorporates improved HPT and LPT rotors. 
CF6-80C2L1F Same as 80C2A1 except lower takeoff thrust rating (52,500 ideal). Minor HPT and LPT 
hardware changes. Redesigned accessory gearbox incorporating two Hydraulic Pump 
units. Redesigned gearbox to handle higher hydraulic loads. Incorporates new generation 
Full Authority Digital Engine Control (FADEC 3), Modulated active clearance control for 
the HPT, and a constant level of 11th stage cooling to HPT. Minor airframe related 
changes, and added servo fuel heater. A constant flow clearance control for the LPT. 
Bore cooling is un-modulated single level of cooling. 
The CF6-80C2L1F will only be installed on non-FAA certified, USAF C-5M aircraft. 
CF6-80C2K1F Same as CF6-80C2L1F except higher takeoff thrust rating (59,740 ideal). In addition, the 
Thrust Reverser Actuation System (TRAS) is same as CF6-80C2A5F. 
The CF6-80C2K1F will only be installed on non-FAA certified, Japanese C-X military 
aircraft. The C-X aircraft designation will change to C-2 in the year 2011.

TCDS E13NE 19 
 
 
NOTE 18. Criteria pertaining to the dispatch and maintenance requirements for CF6-80C2 FADEC engines are 
specified in the Airworthiness Limitations Section of CF6-80C2 Engine Manual GEK 92451, which define 
the various configurations and maximum operating intervals. 
For CF6-80C2L1F, the criteria pertaining to the dispatch and maintenance requirements for engine 
control systems are defined in the Airworthiness Limitation Section of the CF6-80C2L1F Engine Manual 
GEK 112213. 
 
For CF6-80C2K1F, the criteria pertaining to the dispatch and maintenance requirements for engine 
control systems are defined in the Airworthiness Limitation Section of the CF6-80C2K1F Engine Manual 
GEK 112721. 
NOTE 19. The CF6-80C2A5/A8/B5F/B6/B6F/B6FA/B7F/B1F1/B1F2/D1F/A5F engine models require the 
incorporation of General Electric CF6-80C2 Service Bulletins 72-201, 72-222, 72-240, 72-241, 72-248, 
72-255, 72-268, 77-005 and 77-006. 
NOTE 20. Incorporation of EGT Junction Box P/N 1519M97P01 (direct readout) in lieu of EGT Shunt Junction box 
P/N 1325M15P07 or 1383M97P03/P07 is applicable to CF6-80C2 FADEC engine models only and 
requires the simultaneous introduction of ECU P/N's 1471M63P16 (or later) or 1519M89P08 (or later) or 
1820M33P01 (or later) for CF6-80C2B1F/B2F/B3F/B4F/ B5F/ B6F/ B6FA/ B1F1/ B7F/ B1F2/ B8F engine 
models as listed on the data sheet. EGT Junction Box P/N 1519M97P01 is used on all CF6-80C2DF and 
CF6-80C2AF models. 
 
The CF6-80C2L1F and CF6-80C2K1F engines do not have an EGT Junction Box. EGT system is made up 
of four sectors with two EGT probes in each sector. Output from each sector goes to both channels of the 
FADEC. FADEC software processes the EGT and calculates the indicated (shunted) EGT. Indicated 
960ºC EGT is the redline value and corresponds to actual 1020°C EGT. 
NOTE 21. The incorporation of the Engine Identification Plug is applicable to the CF6-80C2 FADEC engine models 
only. The applicable part numbers are as follows: 
CF6-80C2BF Engine Models 
 
Engine Identification Plug P/N 7157M87 must be used with ECU P/N's 1471M63P07/P08/P11/ P12 and 
with 1519M89P05/P06. 
Engine Identification Plug P/N 7161M98 must be used with ECU P/N's 1471M63P16 (or later) or 
1519M89P08 (or later) or 1820M33P01 (or later). Engine Identification Plug P/N 7161M98 or 1851M56 
must be used with ECU P/N’s 1471M63P31 (or later) or 1519M89P21 (or later) or 1820M33P04 (or later) 
or 2121M25P01 (or later), or 2121M26P01 (or later), or 2121M29P01 (or later), or 2121M37P01 (or later), 
or 2121M38P01 (or later), or 2121M41P01 (or later). The exact Engine Identification Plug P/N is 
determined by engine hardware options and engine test results. 
CF6-80C2DF Models 
 
Engine Identification Plug P/N's 7161M98 must be used with ECU P/N 1519M91P04 (or later) or 
1820M34P01 (or later). Engine Identification Plug P/N 7161M98 or 1851M56 must be used with ECU 
P/N’s 1519M91P07 (or later) or 1820M34P02(or later) or 1851M51P01(or later) or 1851M52P01(or later) 
or 1851M53P01(or later). The exact Engine Identification Plug P/N is determined by engine hardware 
options and engine test results. 
 
CF6-80C2AF Models 
Engine Identification Plug P/N 7161M98 or 1851M56 must be used for all ECU P/N's. The exact 
Identification Plug P/N is determined by engine hardware options and engine test results.

TCDS E13NE 20 
 
 
NOTE 21. 
(cont.). 
CF6-80C2 FADEC ENGINE MODEL IDENTIFICATION PLUG PART NUMBERS (cont.) 
CF6-80C2L1F and CF6-80C2K1F Models 
Engine Identification Plug P/N 1754M25 must be used for all Electronic Engine Control (EEC) P/N’s. 
P/N 1754M25 is an un-programmed, programmable identification Plug. When programmed, this part 
makes identification Plug P/Ns 1962M81P01 through 1962M81P08. The exact identification Plug P/N is 
determined by engine hardware options and engine test results. 
NOTE 22. The CF6-80C2B3F does not require the incorporation of General Electric CF6-80C2 Service Bulletins 
72-201, 72-222, 72-240, 72-241, 72-248, 72-255, 72-268, 77-005 and 77-006. If these bulletins are not 
incorporated, the engine must use one of the Identification Plug P/N's 7161M98G26 through G49 or 
P/N's 7161M98G74 through G97. See NOTE 21. 
NOTE 23. The normal 5 minute takeoff time limit may be extended to 10 minutes for engine out contingency. 
NOTE 24. A suffix may be added to the CF6-80C2B7F basic engine model number on the engine nameplate to 
identify minor variations in the engine configuration, installation components, or differences peculiar to 
aircraft requirements. For example: CF6-80C2B7FX. 
 
CF6-80C2B7F1 – Same as CF6-80C2B7F except for a minor variation in the installation 
components and engine control software to interface with aircraft requirements for higher 
bleed demand. All hardware, limitations, and other ratings are identical. Only ECU P/N 
1820M33P04 incorporating 8.2.N software can be used on the CF6-80C2B7F1. See 
NOTE 27. 
NOTE 25. Removed. 
NOTE 26. The Fan Reverser Systems for the CF6-80C2L1F and CF6-80C2K1F are certified for use only as a braking 
means on the ground. 
NOTE 27. The engine Instructions for Continued Airworthiness (ICA’s) are incomplete and do not include the 
CF6-80C2B1F1 / B1F2 / B3F / B7F1 engine models. Aircraft with CF6-80C2B1F1 / B1F2 / B3F / B7F1 
engine models installed are not eligible for an airworthiness certificate until the ICA’s are revised and 
accepted by the FAA Engine Certification Office. 
NOTE 28. The maximum high pressure rotor speed and maximum turbine exhaust gas temperatures permissible for all 
CF6-80A models, determined in NOTES 1 and 2, have been increased from originally certified operating 
limits. This limit increase was approved by the FAA in Service Bulletin No. CF6-80 S/B 72-260, 
Revision 2, dated January 31, 1984. The life limits, dependent on the operating limits, applicable to certain 
rotating components are listed in Chapter 5 of the Engine Manual GEK 72501. 
NOTE 29. The following emissions standards promulgated in 14 CFR part 34, amendment 5, effective December 31, 
2012, and 40 CFR part 87, effective July 18, 2012, have been complied with for: CF6-80C2A5F, 
CF6-80C2A8, CF6-80C2B2, CF6-80C2B2F, CF6-80C2B4, CF6-80C2B4F, CF6-80C2B6, CF6-80C2B6FA, 
CF6-80C2B8F, CF6-80C2D1F, and CF6-80C2L1F. 
 
Fuel Venting Emission Standards: 14 CFR 34.10(a) and 34.11; in addition, 40 CFR 87.10(a) and 87.11. 
Smoke Number (SN) Emission Standards: 14 CFR 34.21(e)(2); in addition, 40 CFR 87.23(c)(1). 
Carbon Monoxide (CO) Emission Standards: 14 CFR 34.21(d)(1)(ii); in addition, 40 CFR 87.23(c)(1). 
Hydrocarbons (HC) Emission Standards: 14 CFR 34.21(d)(1)(i); in addition, 40 CFR 87.23(c)(1). 
Oxides of Nitrogen (NOx) Emission Standards: 14 CFR 34.23(b)(1); in addition, 40 CFR 87.23(c)(3). 
In addition to the FAA’s finding of compliance based on the certification requirements defined in this 
TCDS, the engine manufacturer has declared that the ICAO emissions standards identified in Annex 16, 
Volume II, Third Edition, Part III, Chapter 2, Section 2.2.2 for SN, Section 2.3.2 for CO and HC, Section 
2.3.2.e.3 for NOx (also known as CAEP/8), and Part II Chapter 2 for fuel venting have also been 
demonstrated.

TCDS E13NE 21 
 
The following emissions standards promulgated in 14 CFR part 34, amendment 7A, effective May 24, 
2024, and 40 CFR part 1031, effective December 23, 2022, have been complied with for: CF6-80C2B1F, 
CF6-80C2B5F, CF6-80C2B6F, CF6-80C2B7F, and CF6-80C2K1F. 
 
Fuel Venting Emission Standards: 14 CFR 34.11; in addition, 40 CFR 1031.30(b) 
 
Smoke Number (SN) Emission Standards: 14 CFR 34.21(e); in addition, 40 CFR 1031.60(a)(5) 
 
Hydrocarbons (HC) Emission Standards: 14 CFR 34.21(d)(1)(i); in addition, 40 CFR 1031.60(c) 
 
Carbon Monoxide (CO) Emission Standards: 14 CFR 34.21(d)(1)(ii); in addition, 40 CFR 1031.60(d) 
 
Oxides of Nitrogen (NOx) Emission Standards: 14 CFR 34.23(b)(1); in addition, 40 CFR 1031.60(e)(5) 
(also known as Tier 8 new type) 
 
non-volatile Particulate Matter (nvPM) Mass Concentration Emission Standards: 14 CFR 34.25(a)(1); in 
addition, 40 CFR 1031.60(a)(6) (also known as Tier 10) 
 
nvPM Mass and Number Emission Standards: 14 CFR 34.25(a)(2); in addition, 40 CFR 1031.60(b)(2) 
(also known as Tier 11 in-production) 
 
In addition to the FAA's finding of compliance based on the certification requirements defined in this 
TCDS, the engine manufacturer has declared that the ICAO emissions standards identified in Annex 16, 
Volume II, Fourth Edition, Amendment 10, effective July 20, 2020, have also been demonstrated for the 
following: 
• Part II, Chapter 2 for Fuel Venting 
• Part III, Chapter 2, Section 2.2.2 for Smoke number, 
• Part III, Chapter 2, Section 2.3.2 for Carbon monoxide and Hydrocarbons, 
• Part III, Chapter 2, Section 2.3.2.e for Oxides of Nitrogen (also known as CAEP/8), 
• Part III, Chapter 4, Section 4.2.2.1 for nvPM Mass Concentration (also known as CAEP/10), and  
• Part III, Chapter 4, Section 4.2.2.2 for nvPM Mass and Number (also known as CAEP/11) 
 
-- End of TCDS –
```

## ADs (80, first 50, in force first)

- [AD 2024-24-03](https://openairdocs.org/ad/2024-24-03): Engine Exhaust · Boeing MD-11, MD-11F and CF6-80C2D1F. Effective Jan 13, 2025
- [AD 2023-20-08](https://openairdocs.org/ad/2023-20-08): Engine (Turbine/Turboprop) · General Electric CF6-80C2B1F, CF6-80C2B2F, CF6-80C2B4F and 4 more. Effective Oct 19, 2023
- [AD 2021-26-22](https://openairdocs.org/ad/2021-26-22): Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Mar 14, 2022
- [AD 2022-02-18](https://openairdocs.org/ad/2022-02-18): Engine Mount Section · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 3 more. Effective Feb 25, 2022
- [AD 2021-14-11](https://openairdocs.org/ad/2021-14-11): Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 25 more. Effective Aug 27, 2021
- [AD 2021-03-02](https://openairdocs.org/ad/2021-03-02): Fuel Control/Turbine Engines · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Mar 31, 2021
- [AD 2020-22-02](https://openairdocs.org/ad/2020-22-02): Engine Fuel and Control · General Electric CF6-80C2A5F, CF6-80C2B1F, CF6-80C2B2F and 13 more. Effective Dec 3, 2020
- [AD 2018-07-05](https://openairdocs.org/ad/2018-07-05): Turbine Section · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective May 11, 2018
- [AD 2017-11-15](https://openairdocs.org/ad/2017-11-15): Turbine/ Turboprop Engine--Turbine Section · General Electric CF6-80C2L1F. Effective Jul 13, 2017
- [AD 2016-08-10](https://openairdocs.org/ad/2016-08-10): Accessory heat shield · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 26 more. Effective Jun 1, 2016
- [AD 2014-21-01](https://openairdocs.org/ad/2014-21-01): Fuel manifold · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 26 more. Effective Nov 28, 2014
- [AD 2013-08-20](https://openairdocs.org/ad/2013-08-20): Fuel tube · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 14 more. Effective May 31, 2013
- [AD 2012-03-12](https://openairdocs.org/ad/2012-03-12): No. 3 bearing packing · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 21 more. Effective Apr 5, 2012
- [AD 2012-04-05](https://openairdocs.org/ad/2012-04-05): Electronic control unit (ECU) · General Electric CF6-80C2B1F, CF6-80C2B1F1, CF6-80C2B1F2 and 8 more. Effective Mar 30, 2012
- [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 2009-21-07](https://openairdocs.org/ad/2009-21-07): Thrust and thrust control · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 21 more. Effective Dec 1, 2009
- [AD 2009-14-08](https://openairdocs.org/ad/2009-14-08): High-pressure compressor rotor (HPCR) stages 11-14 spool/ shafts · General Electric CF6-80C2B5F. Effective Aug 5, 2009
- [AD 2009-08-06](https://openairdocs.org/ad/2009-08-06): Stage 1 high-pressure turbine (HPT) rotor  
 disks · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective May 18, 2009
- [AD 2009-07-10](https://openairdocs.org/ad/2009-07-10): High-pressure turbine rotor (HPTR) · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective May 6, 2009
- [AD 2009-07-03](https://openairdocs.org/ad/2009-07-03): Eddy current inspection (ECI) · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 26 more. Effective Apr 30, 2009
- [AD 2009-04-10](https://openairdocs.org/ad/2009-04-10): Critical life-limited parts · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 30 more. Effective Mar 30, 2009
- [AD 2008-21-11](https://openairdocs.org/ad/2008-21-11): Low-pressure turbine (LPT) cases · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 25 more. Effective Nov 28, 2008
- [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 2007-24-07](https://openairdocs.org/ad/2007-24-07): Thermal spray coating on certain stage 1 fan disks · General Electric CF6-80C2B1. Effective Jan 2, 2008
- [AD 2007-22-07](https://openairdocs.org/ad/2007-22-07): Electronic control unit (ECU) · General Electric CF6-80C2D1F. Effective Nov 28, 2007
- [AD 2007-21-06](https://openairdocs.org/ad/2007-21-06): Electronic control unit (ECU) · General Electric CF6-80C2A5F. Effective Nov 15, 2007
- [AD 2007-11-20](https://openairdocs.org/ad/2007-11-20): Fuel shroud retaining rings · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 22 more. Effective Jul 10, 2007
- [AD 2007-05-14](https://openairdocs.org/ad/2007-05-14): Cast titanium weld- repaired forward engine mount platforms · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Apr 9, 2007
- [AD 2006-16-06](https://openairdocs.org/ad/2006-16-06): Certain stage 1 high- pressure turbine (HPT) rotor disks · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 21 more. Effective Sep 5, 2006
- [AD 2006-06-08](https://openairdocs.org/ad/2006-06-08): Latching system of the fan reverser · General Electric CF6-80C2D1F. Effective Apr 25, 2006
- [AD 2005-17-05](https://openairdocs.org/ad/2005-17-05): High pressure compressor rotor (HPCR) · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 25 more. Effective Sep 27, 2005
- [AD 2005-06-07](https://openairdocs.org/ad/2005-06-07): Directional pilot valve (DPV) assembly · General Electric CF6-80A1, CF6-80A3, CF6-80C2A1 and 5 more. Effective Apr 25, 2005
- [AD 2004-22-07](https://openairdocs.org/ad/2004-22-07): Stage 2 nozzle guide vanes (HPT S2 NGVs) · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Dec 1, 2004
- [AD 2004-07-13](https://openairdocs.org/ad/2004-07-13): High pressure turbine (HPT) stage 1 disks · General Electric CF6-80C2A5F, CF6-80C2B5F, CF6-80C2B7F and 1 more. Effective May 6, 2004
- [AD 2003-12-08](https://openairdocs.org/ad/2003-12-08): Directional pilot valve · General Electric CF6-80A1, CF6-80A3, CF6-80C2A1 and 5 more. Effective Jul 23, 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 2002-22-12](https://openairdocs.org/ad/2002-22-12): Titeflex hoses · BAE Systems ATP, Avro 146-RJ100A, Avro 146-RJ70A and 122 more. Effective Dec 13, 2002
- [AD 2001-06-09](https://openairdocs.org/ad/2001-06-09): Aft Engine Mount Link Assemblies · General Electric CF6-80A3. Effective May 1, 2001
- [AD 2000-12-08](https://openairdocs.org/ad/2000-12-08): Mount Link Assemblies · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 4 more. Effective Aug 28, 2000
- [AD 2000-03-04](https://openairdocs.org/ad/2000-03-04): General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 19 more. Effective Apr 10, 2000
- [AD 99-01-01](https://openairdocs.org/ad/99-01-01): Accessory Gearbox (AGB) idler adapters · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 19 more. Effective Jan 21, 1999
- [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 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 96-16-07](https://openairdocs.org/ad/96-16-07): Rear Right Hand Mount Link · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 17 more. Effective Aug 28, 1996
- [AD 95-17-16](https://openairdocs.org/ad/95-17-16): Compressor Rear Frame · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective Nov 7, 1995
- [AD 95-10-11](https://openairdocs.org/ad/95-10-11): Fan Reversers · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 17 more. Effective May 31, 1995
- [AD 94-20-06](https://openairdocs.org/ad/94-20-06): Oil System · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Dec 27, 1994
- [AD 94-07-04](https://openairdocs.org/ad/94-07-04): High Pressure Turbine Disk · General Electric CF6-80A, CF6-80A1, CF6-80A2 and 1 more. Effective May 23, 1994
- [AD 94-06-03](https://openairdocs.org/ad/94-06-03): High Pressure Turbine Disk · General Electric CF6-80C2A1, CF6-80C2A2, CF6-80C2A3 and 16 more. Effective Apr 29, 1994

All 80: https://openairdocs.org/tcds/E13NE/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [GE CF6-80C2B6F](https://openairdocs.org/engine/ge-cf6-80c2b6f): 258 aircraft (registry code 30109)
- [GE CF6-80 series](https://openairdocs.org/engine/ge-cf6-80-series): 237 aircraft (registry code 30025)
- [GE CF6-80C2B1F](https://openairdocs.org/engine/ge-cf6-80c2b1f): 37 aircraft (registry code 30106)
- [GE CF6-80C2B6](https://openairdocs.org/engine/ge-cf6-80c2b6): 25 aircraft (registry code 30103)
- [GE CF6-80C2D1F](https://openairdocs.org/engine/ge-cf6-80c2d1f): 24 aircraft (registry code 30110)
- [GE CF6-80C2B7F](https://openairdocs.org/engine/ge-cf6-80c2b7f): 10 aircraft (registry code 30114)
- [GE CF6-80A](https://openairdocs.org/engine/ge-cf6-80a): 9 aircraft (registry code 30093)
- [GE CF6-80C2A5F](https://openairdocs.org/engine/ge-cf6-80c2a5f): 6 aircraft (registry code 30113)
- [GE CF6-80A2](https://openairdocs.org/engine/ge-cf6-80a2): 5 aircraft (registry code 30095)
- [GE CF6-80C2B5F](https://openairdocs.org/engine/ge-cf6-80c2b5f): 4 aircraft (registry code 30117)
- [GE CF6-80C2A5](https://openairdocs.org/engine/ge-cf6-80c2a5): 3 aircraft (registry code 30104)
- [GE CF6-80C2A1](https://openairdocs.org/engine/ge-cf6-80c2a1): 2 aircraft (registry code 30097)
- [GE CF6-80C2B2](https://openairdocs.org/engine/ge-cf6-80c2b2): 2 aircraft (registry code 30102)
- [GE CF6-80C2B8F](https://openairdocs.org/engine/ge-cf6-80c2b8f): 2 aircraft (registry code 30118)
- [GE CF6-80C2B1](https://openairdocs.org/engine/ge-cf6-80c2b1): 1 aircraft (registry code 30099)
- [GE CF6-80C2B1F1](https://openairdocs.org/engine/ge-cf6-80c2b1f1): 1 aircraft (registry code 30111)
- [GE CF6-80C2B4](https://openairdocs.org/engine/ge-cf6-80c2b4): 1 aircraft (registry code 30100)
- [GE CF6-80C2B4F](https://openairdocs.org/engine/ge-cf6-80c2b4f): 1 aircraft (registry code 30108)
- [GE CF6-80C2B6FA](https://openairdocs.org/engine/ge-cf6-80c2b6fa): 1 aircraft (registry code 30116)
- [GE CF6-80A1](https://openairdocs.org/engine/ge-cf6-80a1): 0 aircraft (registry code 30094)
- [GE CF6-80A3](https://openairdocs.org/engine/ge-cf6-80a3): 0 aircraft (registry code 30096)
- [GE CF6-80C2A2](https://openairdocs.org/engine/ge-cf6-80c2a2): 0 aircraft (registry code 30098)
- [GE CF6-80C2A3](https://openairdocs.org/engine/ge-cf6-80c2a3): 0 aircraft (registry code 30101)
- [GE CF6-80C2A8](https://openairdocs.org/engine/ge-cf6-80c2a8): 0 aircraft (registry code 30105)
- [GE CF6-80C2B1F2](https://openairdocs.org/engine/ge-cf6-80c2b1f2): 0 aircraft (registry code 30115)
- [GE CF6-80C2B2F](https://openairdocs.org/engine/ge-cf6-80c2b2f): 0 aircraft (registry code 30107)
- [GE CF6-80C2B3F](https://openairdocs.org/engine/ge-cf6-80c2b3f): 0 aircraft (registry code 30112)
- [GE CF6-80C2L1F](https://openairdocs.org/engine/ge-cf6-80c2l1f): 0 aircraft (registry code 30119)

## STCs approved under this data sheet (6)

- [STC SE01543CH](https://openairdocs.org/stc/SE01543CH): Replace Hamilton Sundstrand P/N 778839-13, 778839-14, 778839-19, 778839-20, 778839-37, 778839-38, 816682-1, 840618-2, 880724 carbon bushings with Cook Airtomic P/N AIR22947 Slotted Entry Busing in the High Pressure Shutoff Valve.. Cook Airtomic
- [STC SE01478CH](https://openairdocs.org/stc/SE01478CH): Installation of Cook Airtomic alignment joint p/n AIR 22912.. Cook Airtomic
- [STC SE00969CH](https://openairdocs.org/stc/SE00969CH): Install AeroControlex P/N 2605290-001 variable stator feedback control cable.. AeroControlex Group TransDigm Inc
- [STC SE01471AT](https://openairdocs.org/stc/SE01471AT): Replace right and left side Rohr, Inc. fire detection harness on GE CF6-80C2 engine.. Unison Industries
- [STC SE00463LA](https://openairdocs.org/stc/SE00463LA): Install fireproof blankets on the engine fan reverser intermediate fireseal, in lieu of fireproof intumescent coating.  This STC is jointly by owned by Hi Temp Insulation and MRA Systems acting through Middle River Aircraft Systems, 103 Chesapeake Park Plaza, Baltimore, MD 21220. Hi Temp Insulation Inc
- [STC SA2227SO](https://openairdocs.org/stc/SA2227SO): Installation of wiring and associated components for utilization of the Rolls Royce, Inc., ARINC, interface/readers UT1317 or UT1317/1, for the purpose of acquisition, recording, and analysis in real time of engine/aircraft/ systems. (767 SERIES POWERED BY RR RB-11-524 SERIES. Rolls Royce, Inc

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