# TCDS E00063EN: General Electric Company GE Aerospace

- Type: Type certificate data sheet
- Status: Current
- Holder: General Electric Company GE Aerospace
- Revision: 11
- Revised: November 22, 2024
- Product: Engine
- Certification basis: Part 33
- Registered aircraft: 1,117, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/3f/0c/3f0cf3d883d1d0deebf488037f3787ca642e4361531fd0eddc30c821a0f48f61
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID144229774320241122193331.0001
- Page: https://openairdocs.org/tcds/E00063EN

## Models (14)

As the data sheet lists them.

- CF34-8C5B1
- CF34-8E5A1
- CF34-8C5A2
- CF34-8C5
- CF34-8E2A1
- CF34-8E6A1
- CF34-8C5A3
- CF34-8E5A2
- CF34-8C1
- CF34-8C5A1
- CF34-8E5
- CF34-8E2
- CF34-8E6
- CF34-8E5A2HA

## What the data sheet says

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

```text
TCDS NUMBER E00063EN 
REVISION: 11 
U.S. DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
TYPE CERTIFICATE DATA SHEET 
DATE: November 22, 2024 
GENERAL ELECTRIC COMPANY 
MODELS: 
CF34-8C1; CF34-8C5; CF34-8C5A1; CF34-8C5B1; 
CF34-8C5A2; CF34-8C5A3; 
CF34-8E2; CF34-8E2A1; CF34-8E5; CF34-8E5A1; 
CF34-8E5A2; CF34-8E5A2HA; CF34-8E6; CF34-8E6A1 
Engi
nes of models described herein conforming with this data sheet and other approved data on file with the Federal Aviation 
Administration, meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and 
applicable portions of the Federal Aviation Regulations, provided they are installed, operated, and maintained as prescribed by the 
approved manufacturers manuals and other FAA approved instructions. 
TY
PE CERTIFICATE (TC) HOLDER: General Electric Company 
GE Aerospace 
1000 Western Avenue 
Lynn, Massachusetts 01910 
I. MODELS CF34-8C1 CF34-8C5 CF34-8C5A1 CF34-8C5B1 CF34-8C5A2 CF34-8C5A3 
TYPE 
Dual rotor, axial flow, high bypass ratio turbofan; single stage fan, ten stage axial compressor, annular 
combustion chamber, two stage high pressure turbine, four stage low pressure turbine, a thrust reverser 
(CF34 –8E models only), aft core cowl (CF34 –8E models only), exhaust nozzle, exhaust centerbody, 
starter, and a Full Authority Digital Engine Control (FADEC). 
RATINGS (See NOTE 5) 
Sea level static thrust, lb 
Maximum takeoff (5 min.) 
(See NOTES 13,15 and 
18) 
13790 14510 - - 13790 14510 - - 
Normal takeoff (5 min.) 
(See NOTES 13 and 15) 
12670 13360 13630 12670 14050 14510 
Maximum continuous 
(See NOTE 13) 
13277 13680 - - 13280 13680 - - 
CONTROL SYSTEM 
COMPONENT 
Fuel Control, Woodward 
Governor 
4120T01 - - - - - - - - - - 
Full Authority Digital 
Engine 
Control (FADEC), 
Lockheed/Martin 
Ignition System 
2 Ignition Exciters, 
Unison 
2 Ignition Plugs, 
Federal Mogul / 
Champion 
Fuel Pump, Argotech 
4120T00 
9238M66 
4096T33 
4120T04 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
- - 
PAGE 1 2 3 4 5 6 7 8 9 10 11 12 
REV. 11 2 10 10 10 7 10 8 10 10 10 11 
LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" 
"---" NOT APPLICABLE 
NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN.

TCDS E00063EN Page 2 of 12 
 
 
 
 
I. MODELS (continued) CF34-8C1 CF34-8C5 CF34-8C5A1 CF34-8C5B1 CF34-8C5A2 CF34-8C5A3 
FUEL Fuel conforming to GE Jet Fuel Specification No. D50TF2, current revision, is applicable for all 
models. See GEK 105094 (CF34-8C1/8C5 models), GEK 112034 (CF34-8E models), Operating 
Instructions, for specific fuels approved per the subject specifications. 
OIL Oil conforming to GE Specification No. D50TF1, current revision, is applicable for all models. 
See GEK 105094 (CF34-8C1/8C5 models), GEK 112034 (CF34-8E models), Operating 
Instructions, for specific oils approved per the subject specifications. 
PRINCIPAL DIMENSIONS 
AND MEASUREMENTS 
 
 
 
 
 
 
Length, inches 
 
Maximum diameter, inches 
Weight, pounds 
(includes residual fuel and 
oil) 
Center of Gravity Location, 
inches 
Engine Station 
Butt Line 
Water Line 
(Demountable 
Assembly less 
fluids to fill; 
see Installation 
Manual GEK 
105093) 
 
 
152.28 
 
60.66 
2704 
 
 
 
 
173.2 
99.6 
99.1 
- - 
 
 
 
 
 
 
 
151.57 
 
60.66 
2780 
 
 
 
 
173.9 
99.78 
99.35 
- - 
 
 
 
 
 
 
 
- - 
 
- - 
- - 
 
 
 
 
- - 
- - 
- - 
- - 
 
 
 
 
 
 
 
- - 
 
- - 
- - 
 
 
 
 
- - 
- - 
- - 
- - 
 
 
 
 
 
 
- - 
 
- - 
- - 
 
 
 
 
- - 
- - 
- - 
- - 
 
 
 
 
 
 
- - 
 
- - 
- - 
 
 
 
 
- - 
- - 
- - 
II. MODELS     CF34-8E2  
TYPE 
Dual rotor, axial flow, high bypass ratio turbofan; single stage fan, ten stage axial 
compressor, annular combustion chamber, two stage high pressure turbine, four 
stage low pressure turbine, a thrust reverser (CF34 –8E models only), aft core 
cowl (CF34 –8E models only), exhaust nozzle, exhaust centerbody, starter, and 
a Full Authority Digital Engine Control (FADEC). 
RATINGS 
(See NOTE 5) 
Sea level static thrust, lb 
 
 
    
Maximum takeoff (5 min.) 
(See NOTES 13,15 and 18) 
13300 
Normal takeoff (5 min.) 
(See NOTES 13 and 15) 
12410 
Maximum continuous 
(See NOTE 13) 
12540 
CONTROL SYSTEM 
COMPONENT 
  
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
4120T01 
 
4120T00 
 
 
 
 
9238M66 
 
4096T33 
 
4120T04 
Fuel Control, Woodward 
Governor 
Full Authority Digital Engine 
Control (FADEC), 
Lockheed/Martin 
 
Ignition System 
2 Ignition Exciters, 
Unison 
2 Ignition Plugs, Federal 
Mogul 
/ Champion 
Fuel Pump, Argotech

TCDS E00063EN Page 3 of 12 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
II. MODELS (continued)     CF34-8E2 
FUEL Fuel conforming to GE Jet Fuel Specification No. D50TF2, current revision, is applicable for all models. 
See GEK 105094 (CF34- 8C1/8C5 models), GEK 112034 (CF34- 8E models), Operating Instructions, for 
specific fuels approved per the subject specifications. 
OIL Oil conforming to GE Specification No. D50TF1, current revision, is applicable for all models. See GEK 
105094 (CF34-8C1/8C5 models), GEK 112034 (CF34-8E models), Operating Instructions, for specific oils 
approved per the subject specifications. 
PRINCIPAL DIMENSIONS AND 
MEASUREMENTS 
 
 
 
 
 
Length, inches 
 
Maximum diameter, inches 
 
Weight, pounds 
      (includes residual fuel and oil) 
 
Center of Gravity Location, inches 
      Engine Station 
      Butt Line 
      Water Line 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
  
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
(14 CR Part 33 
Propulsion 
System; see 
Installation 
Manual GEK 
112033) 
 
 
121.18 
62.65 
 
3147.6 
 
 
 
175.01 
99.43 
100.07 
III. MODELS CF34-8E2A1 CF34-8E5 CF34-8E5A1 CF34-8E5A2 CF34-8E5A2HA CF34-8E6 CF34-8E6A1 
TYPE 
Dual rotor, axial flow, high bypass ratio turbofan single stage fan, ten stage axial compressor, annular 
combustion chamber, two stage high pressure turbine, four stage low pressure turbine, a thrust reverser 
(CF34-–8E models only), aft core cowl (CF34 –8E models only), exhaust nozzle, exhaust centerbody, 
starter, and a Full Authority Digital Engine Control (FADEC). 
RATINGS (See NOTE 5) 
Sea level static thrust, lb 
       
Maximum takeoff (5 min.) 
(See NOTES 13,15 and 18) 13300 14510 - - - - - - 14050 - - 
Normal takeoff (5 min.) 
(See NOTES 13 and 15) 13300 13420 14050 14510 - - 13420 14050 
Maximum 
continuous (See 
NOTE 13) 
12540 13520 - - - - - - - - - -

TCDS E00063EN Page 4 of 12 
 
 
 
III. MODELS (cont) CF34-8E2A1 CF34-8E5 CF34-8E5A1 CF34-8E5A2 CF34-8E5A2HA CF34-8E6 CF34-8E6A1 
CONTROL SYSTEM 
COMPONENTS 
 
 
 
4120T01 
 
4120T00 
 
 
 
 
9238M66 
 
4096T33 
 
 
4120T04 
 
 
 
- - 
- 
- - 
 
 
 
 
- - 
 
- - 
 
 
- - 
 
 
 
- - 
 
- - 
 
 
 
 
- - 
 
- - 
 
 
- - 
 
 
 
- - 
 
- - 
 
 
 
 
- - 
 
- - 
 
 
- - 
 
 
 
- - 
 
- - 
 
 
 
 
- - 
 
- - 
 
 
- - 
 
 
 
- - 
 
- - 
 
 
 
 
- - 
 
- - 
 
 
- - 
 
 
 
- - 
 
- - 
 
 
 
 
- - 
 
- - 
 
 
- - 
Fuel Control, 
Woodward Governor 
Full Authority Digital Engine 
Control (FADEC), 
Lockheed/Martin 
 
Ignition System 
2 Ignition Exciters, 
Unison 
2 Ignition Plugs, 
Federal Mogul / 
Champion 
Fuel Pump, 
Argotech 
FUEL Fuel conforming to GE Jet Fuel Specification No. D50TF2, current revision, is applicable for all 
models. See GEK 112034 (CF34-8E models), Operating Instructions, for specific fuels approved 
per the subject specifications 
OIL Oil conforming to GE Specification No. D50TF1, current revision, is applicable for all models.  
See GEK 112034 (CF34-8E models), Operating Instructions, for specific oils approved per the 
subject specifications. 
PRINCIPAL DIMENSIONS 
AND MEASUREMENTS 
 
 
 
 
Length, inches 
(14 CFR Part 
33 Propulsion 
System; see 
Installation 
Manual GEK 
112033) 
121.18 
 
62.65 
 
3147.6 
 
 
 
 
175.01 
99.43 
100.07 
- - 
 
 
 
 
 
- - 
 
- - 
 
- - 
 
 
 
 
- - 
- - 
- - 
- - 
 
 
 
 
 
- - 
 
- - 
 
- - 
 
 
 
 
- - 
- - 
- - 
- - 
 
 
 
 
 
- - 
 
- - 
 
- - 
 
 
 
 
- - 
- - 
- - 
- - 
 
 
 
 
 
- - 
 
- - 
 
- - 
 
 
 
 
- - 
- - 
- - 
- - 
 
 
 
 
 
- - 
 
- - 
 
- - 
 
 
 
 
- - 
- - 
- - 
- - 
 
 
 
 
 
- - 
 
- - 
 
- - 
 
 
 
 
- - 
- - 
- - 
Maximum diameter, inches 
Weight, pounds 
(includes residual fuel and 
oil) 
Center of Gravity Location, 
inches 
Engine Station 
Butt Line 
Water Line

TCDS E00063EN Page 5 of 12 
 
 
CERTIFICATION BASIS . 1) CF34-8C1 14 CFR Part 33, effective February 1, 1965, as 
amended by amendments 33-1 through 33-19, and Equivalent Level of Safety 8040-ELOS-97-NE- 
01. 
2) CF34-8C5 (All Models) and CF34-8E (All Models) - 
14 CFR Part 33, effective February 1, 1965, including 
Amendments 33-1 through 33-20 
3) All Engine models- 14 CFR Part 34, Amendment 7A, effective May 24, 2024. 
See NOTE 26 for detailed summary of the certification basis for fuel venting and exhaust emissions. 
 
 
MODEL 
APPLICATION 
DATE 
TYPE CERTIFICATE 
ISSUED/AMENDED 
 
 
CF34-8C1 May 1, 1997 Nov 30, 1999 
 
CF34-8C5 May 31, 2000 Apr 12, 2002  
CF34-8C5A1 May 31, 2000 Apr 12, 2002  
CF34-8C5B1 May 31, 2000 Apr 12, 2002  
CF34-8C5A2 May 31, 2000 Apr 12, 2002  
CF34-8C5A3 May 31, 2000 Apr 12, 2002  
CF34-8E2 May 31, 2000 Apr 12, 2002  
CF34-8E2A1 May 31, 2000 Apr 12, 2002  
CF34-8E5 May 31, 2000 Apr 12, 2002  
CF34-8E5A1 May 31, 2000 Apr 12, 2002  
CF34-8E5A2 May 31, 2000 Apr 12, 2002  
CF34-8E6 May 31, 2000 Apr 12, 2002  
CF34-8E6A1 May 31, 2000 Apr 12, 2002  
 
CF34-8E5A2HA Dec 21, 2023 Sep 23, 2024

TCDS E00063EN Page 6 of 12 
 
NOTES 
 
Notes 1 through 28 applicable to models as specified 
 
NOTE 1. Maximum permissible engine operating speeds for the engine rotors are as follows: 
 
 
 
 
 
 
Low pressure rotor (N1), rpm 
CF34-8C 1  CF34-8C5 
(all models) 
CF34-8E 
 (all models) 
Maximum takeoff 7360 7360 7360 
Normal takeoff 7247 7360 7360 
Maximum continuous 7360 7360 7360 
High pressure rotor (N2), rpm    
Maximum takeoff 17710 17710 17710 
Normal takeoff 17515 17710 17710 
Maximum continuous 17437 17470 17470 
Refer to GE Engine Manual GEK 105091 (CF34-8C1/8C5 models), GEK 112031 (CF34-8E models) and other manual or inspection 
requirements when limits are exceeded. 
100 percent N1 rotor speed is 7,400 rpm, 100 percent N2 rotor speed is 17,820 rpm. 
NOTE 2. Maximum permissible temperatures are as follows: 
Interturbine temperature (T45)*, °F(°C) 
 
 CF34-8C1 CF34-8C5 CF34-8C5A1 CF34-8C5B1 CF34-8C5A2 
Maximum takeoff (5 min) See Note 18 1760 (960)** 1814 (990) - - - - - - 
Maximum takeoff (2 min. out of a total of 5 
minutes) *** 
1794 (979)** 1843 (1006) - - - - - - 
Normal takeoff (5 min) 1689 (920)** 1736 (947) 1754 (957) 1738 (948) 1783 (973) 
Normal takeoff (2 min. out of a total of 5 
minutes)*** 
1723 (939)** 1765 (963) 1783 (973) 1767 (964) 1812 (989) 
Maximum continuous 1701 (927)** 1760 (960) - - - - - - 
 
CF34-8C5A3 
    
Maximum takeoff (5 min) See Note 18 1814 (990)     
Maximum takeoff (2 min. .out of a total of 
5 minutes)*** 
1843 (1006)     
Normal takeoff (5 min) 1814 (990)     
Normal takeoff (2 min. . out of a total of 5 
minutes)*** 
1843 (1006)     
Maximum continuous 1760 (960)     
 
 
 
NOTE 2. (continued)   Maximum permissible temperatures are as follows: 
Interturbine temperature (T45)*, °F(°C)

TCDS E00063EN Page 7 of 12 
 
 
CF34-8E2 CF34-8E2A1 CF34-8E5 CF34-8E5A1 CF34-8E5A2 
Maximum takeoff (5 min) See Note 18 1814 (990) - - - - - - - - 
Maximum takeoff (2 min. out of a total of 5 
minutes)*** 
1843 (1006) - - - - - - - - 
Normal takeoff (5 min) 1755 (957) 1814 (990) 1740( 949) 1783 (973) 1814 (990) 
Normal takeoff (2 min. out of a total of 5 
minutes)*** 
1784 (973) 1843 (1006) 1769 (965) 1812 (989) 1843 (1006) 
Maximum continuous 1760 (960) - - - - - - - - 
 
CF34-8E5A2HA CF34-8E6 CF34-8E6A1 
   
Maximum takeoff (5 min) See Note 18    1814 (990) - - - -    
Maximum takeoff (2 min. out of a total of 5 
minutes)*** 
1843 (1006) - - - -    
Normal takeoff (5 min) 1814 (990) 1771 (966) 1814 (990)    
Normal takeoff (2 min. out of a total of 5 
minutes)*** 
1843 (1006) 1800 (982) 1843 (1006)    
Maximum continuous 1760 (960) - - - -    
 
*The interturbine temperature is measured by either 5 probes (5 thermocouples) or 10 probes (20 thermocouples) mounted in the low 
pressure turbine casing. 
 
** For the CF34-8C1 engine model, maximum takeoff, normal takeoff and maximum continuous T45 limits may be exceeded transiently 
as a result of OBV activation provided T45 does not exceed 1869°F (1021°C) for 30 seconds, and does not exceed a temperature limit 
that ramps from 1869°F (1021°C) to 1794°F (979°C) over the next 30 seconds, as defined in GE Operating Instructions GEK 105094. 
The total number of transient occurrences as a result of OBV activation above a T45 of 1794°F (979°C) is limited to a maximum of 10 
occurrences as defined in GE Engine Manual GEK 105091. 
*** The 2-minute interturbine temperature (T4.5) limits (2 minutes out of 5 minutes takeoff time) are intended to cover engine T4.5 
overshoot characteristics which occur during engine stabilization at constant Takeoff thrust. 
 
For the CF34-8C1 engine model, additional transient temperature and time limits for starting are defined in GE Operating Instructions 
GEK 105094. 
 
Refer to GE Engine Manual GEK 105091 (CF34-8C1/8C5 models), GEK 112031 (CF34-8E models) for inspection requirements when 
limits are exceeded. 
 
Oil tank temperatures****, °F (°C) 
 
ALL MODELS  
Continuous operation 311 (155) 
Transient operation 325 (163) 
****Transient operation above 311° F (155º C) is limited to 15 minutes. 
 
Fuel inlet temperature (at engine fuel filter inlet), °F (°C) 
 
ALL MODELS  
Continuous operation  
Jet A, Jet A1, Jet B 250 (121) 
JP8 250 (121) 
JP5 250 (121) 
JP4, JP4/JP5 mixture 250 (121) 
Ground Operation 250 (121)

TCDS E00063EN Page 8 of 12 
 
 
NOTE 3. FUEL AND OIL PRESSURE LIMITS 
 
Fuel: At engine pump inlet: minimum pressure of 5 PSID above the true vapor pressure of the fuel with a vapor/liquid ratio of zero 
with aircraft boost operative. Operating range 5 PSIG to 50 PSIG. At engine motive flow discharge: minimum pressure of 
150 PSIG at idle or above. Operating range is 150 PSIG to 800 PSIG. See GE Installation Manual GEK 105093 (CF34- 
8C1/8C5 models) and GEK 112033 (CF34-8E models) for additional limits. 
 
Oil: At idle on the ground the oil pressure limit is 25 PSID minimum . At takeoff, 45 PSID minimum.. Normal operating range, 
25 PSID to 95 PSID. See GE Installation Manual GEK 105093 (CF34-8C1/8C5 models) and GEK 112033 (CF34-8E models) 
for additional limits. 
 
NOTE 4. ACCESSORY DRIVE PROVISIONS (ALL MODELS) 
 
Accessory Location on 
AGB Axis 
Speed 
(rpm) 
HP 
(Rated) 
Direction Of 
Rotation 
facing AGB 
Torque (lb-in) 
Static / Cont / 
Overload 
Max. 
Acc. 
Wt. 
(lb) 
Overhung 
Moment 
(lb-in) 
Shear 
Torque 
(lb-in) 
Lube/Scav Oil 
Pump 
Axis-C Fwd 7898 6 CCW 300 /48/ NA (1) 10.3 33 750-850 
IDG Axis-C Aft 7898 74.8 (2) CW 675 (1) /597/ 
1129 (5 min)(4) 
1605 (5 sec)(4) 
81.2 
(6) 
720 
Maximum 
3144- 
3648 
Air Turbine 
Starter 
Axis-D Aft 12234 N/A CW 2112, 4200 (3) 
/ NA / NA 
27.7 113 6300- 
7500 
Hydraulic 
Pump 
Axis-G Fwd 4825 30 CW 573 (1) (5) / 
392 / 670 
14.7 
Dry 
43.5 2004 max 
Alternator Axis-E Aft 8103 4 CCW NA / NA / NA 3.0 2.6 N/A 
Fuel Pump Axis-F Aft 8319 40 CW 180 (1) 
/303/NA 
23 113 1255- 
1380 
CW - Clockwise CCW - Counter Clockwise 
 
 
Accessory Speeds are based on Core Speed: 17000 rpm 
(1) -40° F SLS 
(2) HP is constant over the operating range with slight variations due to changes in efficiency. HP extraction is 74.8 HP at 7898 
rpm (pad speed) and 73.5 HP at 4618 rpm (pad speed). The 5 minute overload rating is 82.7 HP and the 5 second overload 
rating is 117.6 HP. 
(3) 2112 in-lbs at 59° F SLS, 4200 in-lbs at –40° F SLS 
(4) Overload at 4618 rpm (pad speed) 
(5) 573 in-lbs at 626 rpm (pad speed) 
(6) Includes oil and V band coupling 
 
 
NOTE 5. Engine ratings are based on calibrated test stand performance under the following conditions: 
 
1. Static sea level standard conditions of 59° F and 29.92 inches Hg. 
2. No aircraft accessory loads or air extraction. 
3. No anti-icing; no inlet distortion; no inlet screen losses; and 100% ram recovery. 
4. Inlet bellmouth and cowl system as described in GE Installation Manual GEK 105093 (CF34-8C1/8C5 models) 
and GEK 112033 (CF34-8E models). 
5. Specified fuel having an average lower heating value of 18,500 BTU/lb (CF34-8C1/-8C5 models); 18,550 
BTU/lb (CF34 –8E models); specified lube oil. 
 
NOTE 6. Air Bleed Extraction - maximum customer air bleed extraction is as follows: Customer bleed air is available from either 
stages 6 or 10 (compressor discharge) of the compressor at all operating conditions at or above idle. (No compressor bleed 
is permitted below idle.). Customer bleed is scheduled to switch from stage 10 bleed at low power operation to stage 6

TCDS E00063EN Page 9 of 12 
 
bleed at high power operation as described in GE Installation Manual GEK 105093 (CF34-8C1/8C5 models), and GEK 
112033 (CF34-8E models). 
 
Location Maximum Demonstrated Bleed Air (% of Total Compressor Airflow) 
 
 CF34-8C1 CF34-8C5 CF34-8E 
 (all models) (all models) 
Compressor Stage 6 8 8 8 
Compressor Stage 10 (Compressor Discharge) 12.75 12.75 12.0 
Maximum Allowable Bleed --- 12.75 12.0 
 
 
NOTE 7. A minimum core speed (N2) must be maintained to ensure engine operation in icing conditions. The FADEC Power 
Management controls ground and flight idle core speeds above the minimum speed demonstrated for 14 CFR 33.68, 
Induction System Icing. At low ambient temperatures, the minimum permissible ground and flight idle speeds 
correspond to N2=58.47% (9,940 rpm) which is a non-adjustable limit, preset in the FADEC Power Management 
schedules. As ambient temperatures increase, the minimum permissible core speed increases as scheduled by the FADEC 
Power Management based upon N2 or PS3 control schedules. 
 
 
NOTE 8. The maximum permissible inlet distortion for these engines is specified in GE Installation Manual GEK 105093 (CF34- 
8C1/8C5 models) and GEK 112033 (CF34-8E models). 
 
NOTE 9.  
For the CF34-8E model series, the engine manufacturer supplies the Nacelle System. The following Aft Core Cowl and 
Thrust Reverser systems, which are a part of this Nacelle system, have been certified for the listed engine models under 
this type certificate in accordance with Federal Aviation Regulation (FAR), Part 33. The FAR 33 engine type design 
definition is provided by: 
ENGINE MODEL 
LIST 
AFT CORE COWL 
PARTS LIST 
THRUST REVERSER 
PARTS LIST 
CF34-8E2 15F0001 15G0001 
CF34-8E2A1 15F0001 15G0001 
CF34-8E5 15F0001 15G0001 
CF34-8E5A1 15F0001 15G0001 
CF34-8E5A2 15F0001 15G0001 
CF34-8E5A2HA 15F0001 15G0001 
CF34-8E6 15F0001 15G0001 
CF34-8E6A1 15F0001 15G0001 
 
NOTE 10. Life limits, established for critical components, are published in FAA approved GE Engine Manual GEK 105091 (CF34- 
8C1/8C5 models) and GEK 112031 (CF34-8E models). 
 
 
NOTE 11. Recommended maintenance inspection intervals are published in GE Engine Manual GEK 105091 (CF34-8C1/8C5 
models) and GEK 112031 (CF34-8E models). 
 
 
NOTE 12. The operating temperature limit for specific components and accessories specified in GE Installation Manual GEK 105093 
(CF34-8C1/8C5 models) and GEK 112033 (CF34-8E models) must be observed when installing the engine.

TCDS E00063EN Page 10 of 12 
 
NOTE 13. For CF34-8C1, CF34-8C5 (all models) and CF34-8E (all models), static thrusts at sea level are rated at 86ºF ambient 
temperature and below for normal takeoff and maximum takeoff. Maximum Continuous thrust is rated at 77ºF and below 
at cruise altitudes. The computer performance decks for calculating engine performance are as follows: 
Engine Model Computer Deck No. 
CF34-8C1 L0073A 
CF34-8C5 G0175C 
CF34-8C5A1 G0175C 
CF34-8C5B1 L0073A 
CF34-8C5A2 G0175C 
CF34-8C5A3 G0175C 
CF34-8E2 G0175D 
CF34-8E2A1 G0175D 
CF34-8E5 G0175D 
CF34-8E5A1 G0175D 
CF34-8E5A2 G0175D 
CF34-8E5A2HA G0175D 
CF34-8E6 G0175D 
CF34-8E6A1 G0175D 
 
 
NOTE 14. CF34-8C1, CF34-8C5 (all models) and CF34-8E (all models), engines comply with the applicable fuel venting and 
exhaust emission requirements of Part 34, Amendment 7A, effective May 24, 2024. 
 
 
NOTE 15. The time limit at the normal takeoff rating is five minutes and shall include any time accumulated above the normal 
takeoff rating. 
 
NOTE 16. TIME LIMITED DISPATCH CRITERIA 
 
Criteria pertaining to the dispatch and maintenance requirements for the engine control systems are specified in the 
airworthiness section of the Engine Manuals, GEK 105091 (CF34-8C1/8C5 models) and GEK 112041 (CF34-8E models), 
which define the various configurations and maximum operating intervals. 
 
 
NOTE 17. Overhaul of the CF34-8C1, CF34-8C5 (all models) and CF34-8E (all models), 
components is only authorized via approved component manuals. 
 
NOTE 18. The 5 minute maximum takeoff time limit may be extended to 10 minutes for one engine 
inoperative operation in multi-engine aircraft. 
 
 
NOTE 19.  Refer to Operating Instructions GEK 105094 (CF34-8C1/8C5 models) and GEK 112034 
(CF34-8E models) for engine warm-up procedure. 
 
 
NOTE 20.  Refer to Operating Instructions GEK 105094 (CF34-8C1/8C5 models) and GEK 112034 
(CF34-8E models) for thrust reverser operation. 
 
 
NOTE 21. The CF34-8C1, CF34-8C5 (all models), and CF34-8E (all models), engine normal 
takeoff interturbine temperature (T45) limit has been established to assure that a fully degraded engine at the 
normal takeoff rating will achieve the maximum takeoff rated thrust without exceeding the maximum 
takeoff T45 limit. 
 
NOTE 22. The above models incorporate the following characteristics: 
Model Characteristics 
CF34-8C1 Basic Model 
CF34-8C5 Derivative of CF34-8C1; side mounted; increased T45 and thrust rating 
CF34-8C5A1 Derivative of CF34-8C1; side mounted; increased T45 and thrust rating 
CF34-8C5B1 Derivative of CF34-8C1; side mounted; increased T45 
CF34-8C5A2 Derivative of CF34-8C1; side mounted; increased T45 and thrust rating 
CF34-8C5A3 Derivative of CF34-8C1; side mounted; increased T45 and thrust rating 
CF34-8E2 Derivative of CF34-8C1; top mounted; increased T45; includes thrust reverser and aft core

TCDS E00063EN Page 11 of 12 
 
cowl 
CF34-8E2A1 Derivative of CF34-8C1; top mounted; increased T45; includes thrust reverser and aft core 
cowl 
CF34-8E5 Derivative of CF34-8C1; top mounted; increased T45 and thrust rating; includes thrust 
reverser and aft core cowl 
CF34-8E5A1 Derivative of CF34-8C1; top mounted; increased T45 and thrust rating; includes thrust 
reverser and aft core cowl 
CF34-8E5A2 Derivative of CF34-8C1; top mounted; increased T45 and thrust rating; includes thrust 
reverser and aft core cowl 
CF34-8E5A2HA Derivative of CF34-8C1; top mounted; increased T45 and thrust rating; includes thrust 
reverser and aft core cowl 
CF34-8E6 Derivative of CF34-8C1; top mounted; increased T45 and thrust rating; includes thrust 
reverser and aft core cowl 
CF34-8E6A1 Derivative of CF34-8C1; top mounted; increased T45 and thrust rating; includes thrust 
reverser and aft core cowl 
 
NOTE 23. The engine is equipped with an Automatic Power Reserve (APR) function for takeoff operation with one engine 
inoperative. During normal takeoff (NTO), when the automatic power reserve function is activated, the engine 
control of the inoperative engine sends an input signal to the engine control of the operating engine. Upon receiving 
this signal, the engine thrust of the operating engine automatically increases from normal takeoff or lower thrust to 
the corresponding, pre-determined maximum takeoff (MTO) thrust. If one engine is inoperable full MTO thrust is 
available to the pilot at any time by throttle selection. 
The engine control system also incorporates schedules that assure a fully degraded engine, during operation, at 
the NTO or lower thrust, will achieve the specified MTO thrust without exceeding the engine operating limits 
when the automatic power reserve function is activated. 
 
NOTE 24. A suffix may be added to CF34-8 basic engine model numbers on the engine nameplate to identify minor variations 
in the engine configuration, installation components, or differences specific to aircraft requirements, for example, 
CF34-8C5/M. 
Service Bulletin (SB) 72-0235 describes the conversion of the base model to a minor model (with /M designation) 
and Service Bulletin (SB) 72-0244 describes the conversion from the minor model back to the base model. Only 
those designations and purposes listed below may be used. The SB number must be appended to the engine 
nameplate. 
Life limits for the /M minor model designation, established for critical components, are published in FAA approved 
GE Engine Manual GEK 105091 (CF34-8C1/8C5 models). 
 
Allowable suffix designations: 
 
Designation: Purpose: 
CF34-8C5/M Indicates the capability for frequent or repetitive use of the max takeoff (MTO) rating 
with associated airworthiness limitations section life limits. 
 
CF34-8C5A1/M Indicates the capability for frequent or repetitive use of the max takeoff (MTO) rating 
with associated airworthiness limitations section life limits. 
 
CF34-8C5A2/M Indicates the capability for frequent or repetitive use of the max takeoff (MTO) rating 
with associated airworthiness limitations section life limits. 
NOTE 25. A suffix may be added to CF34-8 basic engine model numbers on the engine nameplate to identify minor variations 
in the engine configuration, installation components, or differences specific to aircraft requirements, for example, 
CF34-8C5/B. 
Service Bulletin (SB) 72-A0237 describes the conversion of the base model to a minor model (with /B designation) 
and Service Bulletin (SB) 72-A0243 describes the conversion from the minor model back to the base model. Only 
those designations and purposes listed below may be used. The SB number must be appended to the engine 
nameplate. 
Life limits for the /B minor model designation, established for critical components, are published in FAA approved 
GE Engine Manual GEK 105091 (CF34-8C1/8C5 models). 
 
Allowable suffix designations: 
 
Designation: Purpose: 
 
CF34-8C5/B Indicates use of the engine in an Alternate Mission application, with associated 
Airworthiness limitations section life limits 
 
CF34-8C5B1/B Indicates use of the engine in an Alternate Mission application, with associated 
Airworthiness limitations section life limits

TCDS E00063EN Page 12 of 12 
 
 
CF34-8C5A1/B Indicates use of the engine in an Alternate Mission application, with associated 
Airworthiness limitations section life limits 
 
CF34-8C5A2/B Indicates use of the engine in an Alternate Mission application, with associated 
Airworthiness limitations section life limits 
NOTE 26. 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: CF34-8C1, CF34-8C5, 
CF34-8C5A1, CF34-8C5B1, CF34-8C5A2, CF34-8C5A3, CF34-8E2, CF34-8E2A1, CF34-8E5, CF34-8E5A1, 
CF34-8E5A2, CF34-8E5A2HA, CF34-8E6, CF34-8E6A1. 
 
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) 
NOTE 27. The CF34-8D1, -8D3, -8D5 and -8D6 were deleted from the Type Certificate on September 10, 2010, at the request 
 of the Type Certificate holder. 
 
 
 
 
 
 
-- END--
```

## ADs (24, in force first)

- [AD 2026-21-11](https://openairdocs.org/ad/2026-21-11): Turbine Engine Compressor Section · General Electric Company GE Aerospace CF34-8C1, CF34-8C5, CF34-8C5A1 and 10 more. Effective Nov 27, 2026
- [AD 2025-12-08](https://openairdocs.org/ad/2025-12-08): Turbine Engine Combustion Section · General Electric CF34-8C1, CF34-8C5, CF34-8C5A1 and 10 more. Effective Jul 23, 2025
- [AD 2023-02-05](https://openairdocs.org/ad/2023-02-05): Turbine Engine Combustion Section · General Electric CF34-8C1, CF34-8C5, CF34-8C5A1 and 9 more. Effective Mar 14, 2023
- [AD 2022-21-06](https://openairdocs.org/ad/2022-21-06): Turbine Section · General Electric CF34-8C1, CF34-8C5, CF34-8C5A1 and 10 more. Effective Nov 15, 2022
- [AD 2022-09-14](https://openairdocs.org/ad/2022-09-14): Compressor Bleed Valve · General Electric CF34-8C1, CF34-8C5, CF34-8C5A1 and 10 more. Effective Jun 24, 2022
- [AD 2022-08-06](https://openairdocs.org/ad/2022-08-06): Turbine Engine Compression Section · General Electric CF34-8C1, CF34-8C5, CF34-8C5A1 and 10 more. Effective Apr 29, 2022
- [AD 2021-26-19](https://openairdocs.org/ad/2021-26-19): Turbine Section · General Electric CF34-8C5, CF34-8C5B1, CF34-8E2 and 6 more. Effective Jan 25, 2022
- [AD 2021-23-51](https://openairdocs.org/ad/2021-23-51): Turbine Engine Compression Section · General Electric CF34-8C1, CF34-8C5, CF34-8C5A1 and 10 more. Effective Dec 29, 2021
- [AD 2021-18-13](https://openairdocs.org/ad/2021-18-13): Turbine Engine Combustion Section · General Electric CF34-8C1, CF34-8C5, CF34-8C5A1 and 10 more. Effective Oct 22, 2021
- [AD 2018-17-14](https://openairdocs.org/ad/2018-17-14): Thrust Reverser · General Electric CF34-8E2, CF34-8E2A1, CF34-8E5 and 4 more. Effective Nov 7, 2018
- [AD 2017-20-09](https://openairdocs.org/ad/2017-20-09): Turbine Engine Bypass Section · General Electric CF34-8E2, CF34-8E2A1, CF34-8E5 and 4 more. Effective Nov 13, 2017
- [AD 2017-17-18](https://openairdocs.org/ad/2017-17-18): Turbine Engine Compressor Section · General Electric CF34-8C1, CF34-8C5, CF34-8C5A1 and 10 more. Effective Oct 6, 2017
- [AD 2013-06-06](https://openairdocs.org/ad/2013-06-06): Operability bleed valves (OBV) · General Electric CF34-8C1, CF34-8C5, CF34-8C5A1 and 10 more. Effective May 8, 2013
- [AD 2009-24-06](https://openairdocs.org/ad/2009-24-06): Full authority digital electronic controls · General Electric CF34-8E2, CF34-8E2A1, CF34-8E5 and 4 more. Effective Dec 28, 2009
- [AD 2008-05-01](https://openairdocs.org/ad/2008-05-01): Fuel metering units (FMU) · General Electric CF34-10E2A1, CF34-10E5, CF34-10E5A1 and 8 more. Effective Apr 3, 2008
- [AD 2005-07-09](https://openairdocs.org/ad/2005-07-09): Master variable geometry (VG) actuators · General Electric CF34-8E2, CF34-8E2A1, CF34-8E5 and 4 more. Effective Apr 20, 2005
- [AD 2005-07-06](https://openairdocs.org/ad/2005-07-06): Master variable geometry (VG) actuators · General Electric CF34-8C1 and CF34-8C5. Effective Apr 15, 2005
- [AD 2003-09-14](https://openairdocs.org/ad/2003-09-14): Combustion chamber assemblies · General Electric CF34-8C1. Effective Jun 12, 2003
- [AD 2002-23-02](https://openairdocs.org/ad/2002-23-02): Airworthiness Limitations Section (ALS) - Critical Life-Limited Parts · General Electric CF34-8C1. Effective Dec 26, 2002
- [AD 2019-22-05](https://openairdocs.org/ad/2019-22-05) (historical): Compressor bleed governor · General Electric CF34-8C1, CF34-8C5, CF34-8C5A1 and 3 more. Effective Dec 23, 2019
- [AD 2017-23-06](https://openairdocs.org/ad/2017-23-06) (historical): Compressor bleed governor · General Electric CF34-8C1, CF34-8C5, CF34-8C5A1 and 1 more. Effective Nov 30, 2017
- [AD 2008-16-01](https://openairdocs.org/ad/2008-16-01) (historical): Full authority digital engine controls (FADECs) · General Electric CF34-8E2, CF34-8E2A1, CF34-8E5 and 4 more. Effective Aug 15, 2008
- [AD 2004-04-04](https://openairdocs.org/ad/2004-04-04) (historical): Master Variable geometry (VG) actuators · General Electric CF34-8E2, CF34-8E2A1, CF34-8E5 and 4 more. Effective Mar 9, 2004
- [AD 2003-26-05](https://openairdocs.org/ad/2003-26-05) (historical): Master Variable Geometry (VG) Actuators · General Electric CF34-8C1, CF34-8C5, CF34-8C5A1 and 3 more. Effective Jan 20, 2004

## Registered aircraft by registry model (OpenAirDocs)

- [GE CF34-8E5](https://openairdocs.org/engine/ge-cf34-8e5): 698 aircraft (registry code 30061)
- [GE CF34-8C5](https://openairdocs.org/engine/ge-cf34-8c5): 271 aircraft (registry code 30050)
- [GE CF34-8C5B1](https://openairdocs.org/engine/ge-cf34-8c5b1): 134 aircraft (registry code 30052)
- [GE CF34-8C5A1](https://openairdocs.org/engine/ge-cf34-8c5a1): 10 aircraft (registry code 30051)
- [GE CF34-8E5A2](https://openairdocs.org/engine/ge-cf34-8e5a2): 3 aircraft (registry code 30063)
- [GE CF34-8C1](https://openairdocs.org/engine/ge-cf34-8c1): 1 aircraft (registry code 30049)
- [GE CF34-8C5A2](https://openairdocs.org/engine/ge-cf34-8c5a2): 0 aircraft (registry code 30053)
- [GE CF34-8C5A3](https://openairdocs.org/engine/ge-cf34-8c5a3): 0 aircraft (registry code 30054)
- [GE CF34-8E2](https://openairdocs.org/engine/ge-cf34-8e2): 0 aircraft (registry code 30059)
- [GE CF34-8E2A1](https://openairdocs.org/engine/ge-cf34-8e2a1): 0 aircraft (registry code 30060)
- [GE CF34-8E5A1](https://openairdocs.org/engine/ge-cf34-8e5a1): 0 aircraft (registry code 30062)
- [GE CF34-8E6](https://openairdocs.org/engine/ge-cf34-8e6): 0 aircraft (registry code 30064)
- [GE CF34-8E6A1](https://openairdocs.org/engine/ge-cf34-8e6a1): 0 aircraft (registry code 30065)

---
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.