# TCDS TE6CH: Rolls-Royce Corporation

- Type: Type certificate data sheet
- Status: Current
- Holder: Rolls-Royce Corporation
- Revision: 29
- Revised: December 30, 2016
- Product: Engine
- Certification basis: Part 33, Part 34
- Registered aircraft: 702, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/f4/8f/f48f0e40a130dbde01178980a8029325854a756966b0760176221b77def8a721
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/EC513C57C0969BE5862580980053A0AA.0001
- Page: https://openairdocs.org/tcds/TE6CH

## Models (12)

As the data sheet lists them.

- AE 3007A1E
- AE 3007A
- AE 3007A1/3
- AE 3007A1/2
- AE 3007A3
- AE 3007A2
- AE 3007A1
- AE 3007A1/1
- AE 3007C1
- AE 3007C
- AE 3007A1P
- AE 3007C2

## 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 No. 1 2 3 4 5 6 7 8 Legend: “- -“ indicates “same as previous model” 
Rev No. 27 27 27 28 28 27 27 27                               “—“ indicates “not applicable”     
 
U.S. DEPARTMENT OF TRANSPORTATION 
 
FEDERAL AVIATION ADMINISTRATION 
 
TYPE CERTIFICATE DATA SHEET NO. TE6CH 
 TE6CH 
 Revision 29 
 Rolls-Royce Corporation 
  30 December 2016 
AE 3007C 
AE 3007A 
AE 3007A1/1 
AE 3007A1/2 
AE 3007A1 
AE 3007A1/3 
AE 3007A1P 
AE 3007A3 
AE 3007C1 
AE 3007A1E 
AE 3007A2 
AE 3007C2 
Engine models described herein conforming  with this data sheet (which is part of Type Certificate No. TE6CH) and other 
approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certified aircraft 
in accordance with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations provided 
they are installed, operated, and maintained as prescribed by the manufacturer's FAA approved manuals and other  FAA 
approved instructions. 
 
Type certificate holder: Rolls-Royce Corporation 
 P.O. Box 420 
 Indianapolis, Indiana 46206-0420 
 
Type certificate holder record:  TE6CH originally issued to Allison Engine Company on 28 Feb 95.  
 TE6CH reissued to Rolls-Royce Corporation on 1 Sep 2000. 
Model type description (see Note 12) 
Ratings (see Notes 1&2) AE 3007C2 AE 3007A1 AE 3007A1/11 AE 3007A1/21 AE 3007A11 AE 3007A1/31 
Takeoff, 5 min:  
Static thrust (lbf) 6442 7580 - - - - - - - -  
Fan shaft speed (rpm) 7376 7750 7716 7823 7903 - - 
Gas generator speed (rpm) 15388 15452 15603 15842 16013 - - 
Maximum continuous:   
Static thrust (lbf) 6442 6820 - - - - - - - - 
Fan shaft speed (rpm) 7376 7441 7404 7548 7613 - -  
Gas generator speed (rpm) 15388 15204 15366 15619 15778 - - 
Fan shaft rotation (ALF) CCW - - - - - - - - - - 
Dimensions of basic engine:  
Length (overall), in 115.08 - - - - - - - - - - 
Width (max), in 46.14 - - - - - - - - - - 
Height (max), in 55.70 - - - - - - - - - - 
C.G. location  
(dry, no aircraft accessories)*  
Engine station, in 93.58 93.9 - - - - - - - - 
Butt line, in 99.87 99.9 - - - - - - - - 
Water line, in 97.71 97.7 - - - - - - - - 
Weight, dry, lb 1614 1657 - - - - - - - - 
* C.G. references – STA 100.00 (engine axial station) = Compressor case aft splitline 
 WL 100.00 = Engine horizontal centerline (+ upward) 
 BL 100.00 = Engine vertical centerline (+ to the right, ALF)

2 of 9 TE6CH 
 
Ratings (see Notes 1&2) AE 3007A1P1 AE 3007A31 AE 3007C12 AE 3007A1E1 AE 3007A21 AE 3007C22 
Takeoff, 5 min:  
Static thrust (lbf) 8338 7201 6764 8917 9440 7042 
Fan shaft speed (rpm) 8059 7600 7518 8248 8146 7344 
Gas generator speed 
(rpm) 15953 15329 15452 16128 16245 15196 
Maximum continuous:  
Static thrust (lbf) 6820 - - 6764 7339 8097 7042 
Fan shaft speed (rpm) 7613 7430 7518 7801 7756 7344 
Gas generator speed 
(rpm) 15778 15191 15452 15926 15975 15196 
Fan shaft rotation (ALF) CCW - - - - - - - - - -  
Dimensions of basic engine:  
Length (overall), in 115.08 - - - - - - - - - - 
Width (max), in 46.14 - - - - - - - - - - 
Height (max), in 55.70 - - - - - - - - - - 
C.G. location  
(dry, no aircraft accessories)*  
Engine station, in 93.9 - - 93.58 93.82 93.85 93.52 
Butt line, in 99.9 - - 99.87 99.87 99.87 99.88 
Water line, in 97.7 - - 99.71 97.65 97.70 97.59 
Weight, dry, lb 1657 - - 1617 1657 1681 1641 
 
 AE 3007A Series and AE 3007C Series 
Engine control system (see 
Note 10) 
Goodrich Full Authority Digital Electronic Control (FADEC) – Qty 2. Goodrich Fuel Pump & 
Metering Unit (FPMU) – Qty 1. Goodrich Compressor Variable Geometry (CVG) actuator – 
Qty 1. 
Fuels 
Kerosene, commercial turbine fuel conforming to MIL-DTL-5624, NATO F-40 (JP-4) and 
NATO F-44 (JP-5); MIL-DTL-83133, NATO F-34 (JP-8) and NATO F-35; ASTM-D-1655, 
Jet A and A1; ASTM-D-6615, Jet B; GOST 10227-2013, TS-1 and RT; GOST 10227-86, TS-
1 and RT; GB6537-94, RP-3; GB 6537-2006 No. 3 Jet Fuel; GSTU 32.00149943.011-99, TC-
1; GSTU 320.00149943.007-97, PT 
Lubrication oil Synthetic oil conforming to MIL-PRF-23699F and subsequent or MIL-PRF-7808L         [below –40F, (–40C)] and subsequent. 
Ignition system BF Goodrich Aerospace, Engine Electrical Systems Division dual capacitance discharge, high energy type exciters, dual igniter plugs.

3 of 9 TE6CH 
 
 
 AE 3007A Series 
(excluding AE 3007A2) AE 3007 A2 AE 3007C Series AE 3007C2 
Certification 
basis 
14 CFR Part 33  
effective 1 Feb 65, including 
Amendments 33-1 through 33-15 
  
 
14 CFR Part 33  
effective 1 Feb 65, 
including 
Amendments 33-1 
through 33-15, 
plus 
 
   14 CFR §33.76 
Amendment 20 
   (Bird ingestion) 
 
   14 CFR §33.78 
(a) (2)       
Amendment 19   
   (Rain and hail 
ingestion)  
14 CFR Part 33  
effective 1 Feb 65, including 
Amendments 33-1 through 
33-14 
14 CFR Part 33  
effective 1 Feb 65, 
including Amendments 
33-1 through 33-14 
 
14 CFR 33.28 
Amendment 15 
(Electrical and 
electronic control 
systems) 
 
14 CFR §33.76 
Amendment 20 (Bird 
ingestion) 
 
14 CFR §33.78 (a) (2) 
Amendment 19   
(Rain and hail 
ingestion)  
14 CFR Part 34, Amendment 5, 
effective 31 Dec 2012. See Note 
14 for detailed summary of the 
certification basis for fuel venting 
and exhaust emissions by engine 
model. 
- - - - - - 
Production 
basis 
Production Certificate No. 310 - - - - - - 
 
Application for Type Certificate dated 24 May 90, amended 22 Dec 92.  
Original Type Certificate No. TE6CH issued 28 Feb 95. 
 
Model Added to TC  Model Added to TC  Model Added to TC 
AE 3007C 
AE 3007A 
AE 3007A1/1 
AE 3007A1/2 
 
28 Feb 95 
27 Nov 96 
15 Apr 98 
15 Jun 98 
 
 AE 3007A1 
AE 3007A1/3 
AE 3007A1P 
AE 3007A3 
 
6 Nov 98 
27 May 99 
6 Aug 99 
7 Sep 99 
 
 AE 3007C1 
AE 3007A1E 
AE 3007A2 
AE 3007C2 
29 Oct 2001 
2 Aug 2002 
15 April 2010 
24 July 2013

4 of 9 TE6CH 
 
NOTE 1 The following criteria apply to the AE 3007A 
Series engine ratings:  
1. Sea level static, 29.92 in Hg 
2. 100% inlet pressure recovery 
3. Exhaust nozzle area (A9) of 670.1 in2 
4. Zero percent relative humidity 
5. No inlet air distortion 
6. No customer bleed extraction 
7. No anti-ice airflow 
8. No external power extraction 
9. ISA ambient conditions for thrust  
10. Flat rated temperatures for rotor speeds 
NOTE 2  The following criteria apply to the AE 3007C 
Series engine ratings: 
1. Sea level static, 29.92 in Hg 
2. Typical inlet pressure recovery 
3. Exhaust nozzle area (A9) of 650 in2 
4. Zero percent relative humidity 
5. No inlet air distortion 
6. No customer bleed extraction 
7. No anti-ice airflow 
8. No external power extraction 
9. ISA ambient conditions for thrust  
10. Flat rated temperatures for rotor speeds

5 of 9 TE6CH 
 
Flat Rated Temperatures 
 
NOTE 3 Temperature limits, °F (°C) 
To ensure operation of the engine at the correct Measured ITT temperature limits allowable ITT Trim Plug ranges are published in the 
Maintenance Manual   
 
 AE 3007C AE 3007C1 AE 3007C2 
Measured interstage turbine 
temperature (T4.5/ITT):    
Takeoff, 5 min 1630 (888) 1665 (907) 1650 (899) 
Maximum continuous 1562 (850) 1575 (857) 1593 (867) 
Starting 1472 (800) 1472 (800) 1472 (800) 
Transient Starting (5 Seconds) 1562 (850) 1562 (850) 1562 (850) 
 
For AE 3007C and AE 3007C1 model engines Pre SB AE 3007C-73-053, or SB AE 3007C-73-054, or SB AE 3007C-73-055 (engine 
control software version C9.2), the following alternate Takeoff and Maximum continuous temperature limits are available.  
 AE 3007C AE 3007C1 
Measured interstage turbine 
temperature (T4.5/ITT):   
Takeoff, 5 min 1639 (893) 1650 (899) 
Maximum continuous 1582 (861) 1593 (867) 
 
 AE 3007A AE 3007A1/2 
Measured interstage turbine 
temperature (T4.5/ITT): 
 
Takeoff, 5 min 1690 (921) 1738 (948) 
Maximum continuous 1600 (871) 1653 (901) 
Starting 1472 (800) 1472 (800) 
 
 AE 3007A1/1 AE 3007A1 AE 3007A1P AE 3007A1/3 AE 3007A3 
Measured interstage turbine 
temperature (T4.5/ITT): 
  
Takeoff, 5 min  1690 (921) 1738 (948) 1738 (948) 1738 (948) 1738 (948) 
Maximum continuous 1605 (874) 1653 (901) 1653 (901) 1653 (901) 1653 (901) 
Starting 1472 (800) 1472 (800) 1472 (800) 1472 (800) 1472 (800) 
Transient Starting (5 Seconds) 1562 (850) 1562 (850) 1562 (850) 1562 (850) 1562 (850) 
 
 AE 3007A1E AE 3007A2 
Measured interstage turbine 
temperature (T4.5/ITT): 
 
Takeoff, 5 min  1778 (970) 1778 (970) 
Transient Takeoff Acceleration 
(90 Seconds) 1821 (994) 1821 (994) 
Starting 1472 (800) 1472 (800) 
Transient Starting (5 Seconds) 1562 (850) 1562 (850) 
   
 Takeoff Max Continuous 
AE 3007C, AE 3007A, AE 3007A1/1, AE 
3007A3, AE 3007C1, AE 3007C2 
ISA + 15°C 
ISA + 27°F 
ISA + 15°C 
ISA + 27°F 
AE 3007A1/2 ISA + 23°C 
ISA + 41°F 
ISA + 23°C 
ISA + 41°F 
AE 3007A1, AE 3007A1/3 ISA + 30°C 
ISA + 54°F 
ISA + 30°C 
ISA + 54°F 
AE 3007A1P ISA + 19°C 
ISA + 34°F 
ISA + 19°C 
ISA + 34°F 
AE 3007A1E ISA + 19°C 
ISA + 34°F 
ISA + 30°C 
ISA + 54°F 
AE 3007A2 ISA + 15°C 
ISA + 27°F 
ISA + 20°C 
ISA + 36°F

6 of 9 TE6CH 
 
NOTE 4  Maximum allowable rotor speeds, rpm (%) 
 AE 3007C, AE 3007C1 AE 3007A, AE 3007A1/2, AE 3007A3 AE 3007A1, AE 3007A1/1, AE 3007A1/3, AE 3007A1P AE 3007A1E AE 3007A2 AE 3007C2 
Low pressure 
turbine (N1) 8700 8700 8700 8700 8500 8105 
High pressure 
turbine (N2) 16123 16270 (102.5) 
16,270 (102.5) 
or 
16440 (102.5)  
or  
16667 (102.5) 
16667 
(105.0) 
16667 
(105.0) 16300 
 
The following statements apply to this Note 4: 
 (1)   For all AE 3007 A Series models, the installed trim plug shall be within the allowable ITT Trim Plug ranges published in the 
Airworthiness   Limitations Section of the Maintenance Manual, reference CSP34012 or CSP34022.  
(2)   The AE 3007A1, AE 3007A1/1, AE 3007A1/3, and AE 3007A1P models that comply with Service Bulletin AE 3007A-73-090 or 
equivalent, are cleared to 16440 or 16667 rpm. Otherwise, maximum allowable N2 speed is 16270 rpm for these models. See Maintenance 
Manual Task Number 77-21-25-400-801 to select the correct ITT Trim Plug for these configurations. 
 
NOTE 5  Accessory drive provisions 
 
Direction of 
rotation 
(FLA) 
Speed 
ratio 
Normal 
load 
(HP)**** 
Cyclic 
overload load 
(HP)**** 
Failure 
overload load 
(HP)****  
Max shear  
torque  
(in lb) 
Max overhung 
moment  
(in lb) 
Generator 1 CW 0.745 23.5 43.5 - - 1600 300 
Generator 2 CW 0.745 23.5 43.5 - - 1600 300 
Hydraulic pump CW 0.473 13.0 37.3 42 1840 160 
****The maximum total accessory horsepower extraction for all thrust settings and flight conditions is 60 HP. An overload 
limit of 80 HP is permitted for a period of five minutes at all thrust settings and all fligh t conditions below 45,000 feet.  
Cyclic overload is defined as five minutes per one hour of operation.  Failure overload is defined as one minute per 
10,000 hours of operation. 
 
NOTE 6  Oil and fuel inlet pressure limits, psig 
 AE 3007C, AE 3007C1 AE 3007A Series AE 3007C2 
Oil pressure limits:   
Minimum below 88% N2  
(N2 < 14000 rpm) 
34 - - - - 
Minimum above 88% N2  
(N2  14000 rpm) 
48 - - - - 
Maximum, no time limit (1)  95(2)(4)  (105) (2)(4)(5) 110 105 
Maximum, up to 5 minutes — 115(4) — 
Maximum, up to 2 minutes 155(2)(4) 155(3)(4) 155 
Fuel pump inlet pressure limits for 
Jet A, Jet A-1/JP-5 and Jet B/JP-4: 
  
Minimum –  Refer to Section 1 of the Installation Design Manual (Note 3)  
Maximum 55 - - - - 
(1)  With oil temperature > 70F  
(2)  Compliance with Service Bulletin AE 3007C-79-029 or equivalent is required. 
(3)  Compliance with Service Bulletin AE 3007A-79-025 or equivalent is required. 
(4)  Refer to the Abnormal Operation Section of the following Operations Manuals (Note 3)  
(5)  Compliance with Service Bulletin AE 3007C-79-042 or equivalent is required. On engines complying 
with Service Bulletin AE 3007C-79-042 the maximum allowable oil pressure of 105 PSIG will be indicated  
as 95 PSIG.  All operating procedures and limitations are applied using the indicated oil pressure.   
 
NOTE 7  Maximum engines bleed flow, percent of core airflow 
 AE 3007C,  
AE 3007C1, 
AE 3007C2 AE 3007A 
AE 3007A1/1, AE 3007A1/2, AE 3007A1, 
AE 3007A1/3, AE 3007A1P, AE 3007A3 
AE 3007A1E, 
AE 3007A2

7 of 9 TE6CH 
 
8th stage 7.0% — — — 
9th stage — 8.5% 7.9% 6.9% 
14th stage 12.0% 10.5% 9.3% 9.6% 
8th + 14th stages 17.5% — — — 
9th + 14th stages — 18.0% 16.5% 16.0% 
Fan bypass — 90 lbm/min - - - - 
 
 
NOTE 8 Mandatory replacement times (life limits) established for critical components and mandatory airworthiness 
inspections are published in the Airworthiness Limitations Section of the Maintenance Manual  (Note 3). 
 
NOTE 9 The accessory gearbox mounted accessories provided as part of the engine include Permanent Magnet Alternator 
(PMA), Fuel Pump & Metering Unit (FPMU) and Oil Pump. Additional accessory gearbox mounting pads are 
also provided on the engine for the engine starter, two aircraft electrical generators and one aircraft system 
hydraulic pump.

8 of 9 TE6CH 
 
 
NOTE 10 Aircraft mounted engine control equipment consists of two FADEC assembly units, associated sensors and 
equipment as defined in the following Turbofan Engine Assembly Drawings: 
 
 AE 3007C 
AE 3007A 
AE 3007A1/1 
AE 3007A1/2 
AE 3007A1 
AE 3007A1/3 
AE 3007A1P 
AE 3007A3 
AE 3007C1 
AE 3007A1E 
AE 3007A2 
AE 3007C2 
23057202 revision CW and later 
23054002 revision DM and later 
23070002 revision AD and later 
23070443 revision H and later 
23070991 revision E and later 
23070402 revision A and later 
23070401 revision F and later 
23070412 revision J and later 
23074408 revision A and later 
23074862 revision D and later 
23087636 initial release and later 
23090589 revision M and later 
 
 
For AE 3007A1E with two P/N 23076287 FADECs (B7.4 Software) the following restriction applies:  
(a)  Verify N2 speed is less than 9,000 rpm (56%) prior to initiating any restart attempt.  
 
NOTE 11 The FAA-approved time limits that AE 3007C Series and AE 3007A Series engines may operate with control 
system faults present are defined by the Mandatory Inspections, Systems Description Section (05 -13-00) and the 
Time Limits, System Description Section (05-14-00) of the Maintenance Manual (Note 3). Installation 
requirements are in the Installation Design Manual (Note 3), while normal and abnormal operational procedures 
are in the Operations Manual (Note 3). 
 
NOTE 12 AE 3007A Series and AE 3007C Series engines are direct drive turbofan engines of modular 
design which incorporate  
 A single stage fan connected to a three-stage low pressure turbine.   
 A 14-stage axial compressor with variable vanes (including inlet guide vanes) for the 
first six stages, an    annular combustor, and a two-stage high pressure turbine.   
 A full-length composite outer duct.   
 Fore and aft mounting provisions, which allow either underwing pylon or aft 
fuselage mounting installation.  
 
The following table highlights differences between the models: 
 
 AE 3007C Series 
AE 3007A Series 
excluding AE 
3007A2 
AE 3007A2 AE 3007C2 
Fan blades P/N 23060567 (Type III) P/N 23061623 (Type IV) P/N 23089091 (Type X) P/N 23089091 (Type X) 
High pressure compressor bleed 8th stage 9th stage 9th stage 8th stage 
Fan bypass bleed No Yes Yes No 
Rear mount support ring Rotatable position Fixed position Fixed position Fixed position 
Fuel flow meter, Rolls-Royce supplied No Yes Yes No

9 of 9 TE6CH 
 
 
 
NOTE 13  
 
NOTE 14 
Compliance with Service Bulletin AE 3007A-72-384 or equivalent is required for the AE 3007A2 Model. 
 
The following emissions standards promulgated under 14 CFR Part 34, Amendment 5, effective 31 Dec 2012, 
and 40 CFR Part 87, effective 18 July 2012, have been complied with for engine models listed. 
Engine Model(s) Emissions Standards 
AE 3007C 
AE 3007A 
AE 3007A1/1 
AE 3007A1 
AE 3007A1/3 
AE 3007A1P 
AE 3007A3 
AE 3007C1 
AE 3007A1E 
AE 3007A2 
AE 3007C2 
 
Fuel Venting 14 CFR §§ 34.10(b) and 34.11; in addition, 40 CFR §§ 
87.10(b) and 87.11, as amended. 
 Smoke Number (SN) 14 CFR §34.21(e)(2); in addition, 40 CFR § 87.23(c)(1). 
Carbon Monoxide (CO) 14 CFR § 34.21(d)(1)(ii); in addition, 40 CFR § 
87.23(c)(1). 
Hydrocarbons (HC) 14 CFR § 34.21(d)(1)(i); in addition, 40 CFR § 
87.23(c)(1). 
Oxides of Nitrogen (NOx) 14 CFR § 34.23(b)(1); in addition, 40 CFR § 87.23(c)(3) 
(Tier 8). 
In addition to the FAA’s findings 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 for NOx 
(also known as CAEP/8), and Part II Chapter 2 for fuel venting have also been 
demonstrated. 
AE 3007A1/2† 14 CFR Part 34 and 40 CFR Part 87 as above except Oxides of Nitrogen (NOx) per 14 
CFR Part 34.21(d)(1)(iv) (Tier 2). 
† No longer in production 
 
     
...END...
```

## ADs (27, in force first)

- [AD 2020-16-13](https://openairdocs.org/ad/2020-16-13): Turbine Engine Compressor Section · Rolls-Royce AE 3007A, AE 3007A1, AE 3007A1/1 and 5 more. Effective Aug 14, 2020
- [AD 2018-17-04](https://openairdocs.org/ad/2018-17-04): Turbine section · Rolls-Royce AE 2100D2A, AE 2100D3 and AE 3007A2. Effective Sep 21, 2018
- [AD 2017-26-06](https://openairdocs.org/ad/2017-26-06): Turbine/turboprop Engine, Turbine · Rolls-Royce AE 3007A, AE 3007A1, AE 3007A1/1 and 7 more. Effective Jan 31, 2018
- [AD 2017-11-05](https://openairdocs.org/ad/2017-11-05): Turbine/ turboprop Engine, Turbine Section · Rolls-Royce AE 3007C and AE 3007C1. Effective Jul 18, 2017
- [AD 2015-02-08](https://openairdocs.org/ad/2015-02-08): Turbine wheels · Rolls-Royce AE 2100D2, AE 2100D2A, AE 2100D3 and 11 more. Effective Mar 11, 2015
- [AD 2013-26-06](https://openairdocs.org/ad/2013-26-06): High-pressure turbine (HPT) stage 2 wheels · Rolls-Royce AE 3007A, AE 3007A1, AE 3007A1/1 and 5 more. Effective Feb 7, 2014
- [AD 2011-22-03](https://openairdocs.org/ad/2011-22-03): Low-cycle fatigue cracks · Rolls-Royce AE 3007A, AE 3007A1, AE 3007A1/1 and 4 more. Effective Nov 17, 2011
- [AD 2009-24-04](https://openairdocs.org/ad/2009-24-04): Fan spinner · Rolls-Royce AE 3007A1, AE 3007A1E, AE 3007A1P and 5 more. Effective Dec 28, 2009
- [AD 2009-04-03](https://openairdocs.org/ad/2009-04-03): 2nd stage, 3rd stage, and 4th stage compressor wheels · Rolls-Royce AE 1107C and AE 3007A1E. Effective Mar 24, 2009
- [AD 2007-24-05](https://openairdocs.org/ad/2007-24-05): Engine oil temperature · Rolls-Royce AE 3007A, AE 3007A1, AE 3007A1/1 and 8 more. Effective Jan 2, 2008
- [AD 2004-04-05](https://openairdocs.org/ad/2004-04-05): Engine oil system · Rolls-Royce AE 3007A, AE 3007A1, AE 3007A1P and 4 more. Effective Mar 9, 2004
- [AD 2003-25-08](https://openairdocs.org/ad/2003-25-08): 1st and 2nd stage turbine spacers · Rolls-Royce AE 3007A1, AE 3007A1E, AE 3007A1P and 3 more. Effective Jan 21, 2004
- [AD 2001-25-05](https://openairdocs.org/ad/2001-25-05): Compressor Cone Shafts · Rolls-Royce AE 3007A, AE 3007A1, AE 3007A1P and 4 more. Effective Jan 23, 2002
- [AD 2001-19-03](https://openairdocs.org/ad/2001-19-03): High Pressure Turbine 1st to 2nd Stage Turbine Spacer · Rolls-Royce AE 3007A and AE 3007C. Effective Oct 29, 2001
- [AD 2001-17-31](https://openairdocs.org/ad/2001-17-31): Second Stage High Pressure Turbine Wheel · Rolls-Royce AE 2100A, AE 2100C, AE 2100D3 and 2 more. Effective Oct 5, 2001
- [AD 2000-18-06](https://openairdocs.org/ad/2000-18-06): Digital Electronic Controls · Rolls-Royce AE 3007A, AE 3007A1, AE 3007A1P and 5 more. Effective Sep 22, 2000
- [AD 2000-13-01](https://openairdocs.org/ad/2000-13-01): Turbine Wheels · Rolls-Royce AE 3007A, AE 3007A1, AE 3007A1P and 5 more. Effective Sep 1, 2000
- [AD 2000-11-22](https://openairdocs.org/ad/2000-11-22): Critical Life-Limited Parts · Rolls-Royce AE 3007A, AE 3007A1, AE 3007A1P and 5 more. Effective Aug 7, 2000
- [AD 99-03-03](https://openairdocs.org/ad/99-03-03): Full Authority Digital Engine Control (FADEC) · Rolls-Royce AE 3007A and AE 3007A1/1. Effective Feb 16, 1999
- [AD 98-11-32](https://openairdocs.org/ad/98-11-32): Sump Magnetic Chip Collector Plug · Rolls-Royce AE 3007A, AE 3007A1, AE 3007A1P and 5 more. Effective Jun 18, 1998
- [AD 2010-19-01](https://openairdocs.org/ad/2010-19-01) (historical): High pressure turbine · Rolls-Royce AE 3007A. Effective Oct 27, 2010
- [AD 2009-08-51](https://openairdocs.org/ad/2009-08-51) (historical): High-pressure turbine · Rolls-Royce AE 3007A, AE 3007A1, AE 3007A1/1 and 6 more. Effective May 27, 2009
- [AD 2008-26-06](https://openairdocs.org/ad/2008-26-06) (historical): High-pressure turbine (HPT) · AE 3007A. Effective Jan 8, 2009
- [AD 2001-08-15](https://openairdocs.org/ad/2001-08-15) (historical): Oil System · AE 3007A, AE 3007A1, AE 3007A1P and 4 more. Effective May 14, 2001
- [AD 2000-09-05](https://openairdocs.org/ad/2000-09-05) (historical): Cone Shafts · AE 3007A, AE 3007A1, AE 3007A1P and 4 more. Effective Jul 5, 2000
- [AD 99-02-51](https://openairdocs.org/ad/99-02-51) (historical): Starter Shaft Seal · AE 3007A, AE 3007A1, AE 3007A1P and 5 more. Effective Apr 20, 1999
- [AD 2008-19-51](https://openairdocs.org/ad/2008-19-51) (historical): AE 3007A, AE 3007A1, AE 3007A1E and 5 more

## Registered aircraft by registry model (OpenAirDocs)

- [Allison AE3007C series](https://openairdocs.org/engine/allison-ae3007c-series): 204 aircraft (registry code 03028)
- [Rolls-Royce AE3007 series](https://openairdocs.org/engine/rolls-royce-ae3007-series): 185 aircraft (registry code 54582)
- [Allison AE-3007A](https://openairdocs.org/engine/allison-ae-3007a): 83 aircraft (registry code 03030)
- [Rolls-Royce AE-3007A1P](https://openairdocs.org/engine/rolls-royce-ae-3007a1p): 59 aircraft (registry code 54571)
- [Allison AE-3007C1](https://openairdocs.org/engine/allison-ae-3007c1): 37 aircraft (registry code 03053)
- [Rolls-Royce AE-3007A1E](https://openairdocs.org/engine/rolls-royce-ae-3007a1e): 37 aircraft (registry code 54169)
- [Rolls-Royce AE-3007C2](https://openairdocs.org/engine/rolls-royce-ae-3007c2): 31 aircraft (registry code 54234)
- [Rolls-Royce AE-3007C1](https://openairdocs.org/engine/rolls-royce-ae-3007c1): 20 aircraft (registry code 54168)
- [Rolls-Royce AE-3007C](https://openairdocs.org/engine/rolls-royce-ae-3007c): 16 aircraft (registry code 54572)
- [Allison AE-3007A1/3](https://openairdocs.org/engine/allison-ae-3007a1-3): 9 aircraft (registry code 03036)
- [Rolls-Royce AE-3007A1/3](https://openairdocs.org/engine/rolls-royce-ae-3007a1-3): 7 aircraft (registry code 54166)
- [Rolls-Royce AE-3007A2](https://openairdocs.org/engine/rolls-royce-ae-3007a2): 6 aircraft (registry code 54594)
- [Rolls-Royce AE-3007A1](https://openairdocs.org/engine/rolls-royce-ae-3007a1): 4 aircraft (registry code 54165)
- [Allison AE-3007C](https://openairdocs.org/engine/allison-ae-3007c): 2 aircraft (registry code 03047)
- [Allison AE-3007A1/1](https://openairdocs.org/engine/allison-ae-3007a1-1): 1 aircraft (registry code 03048)
- [Rolls-Royce AE-3007A](https://openairdocs.org/engine/rolls-royce-ae-3007a): 1 aircraft (registry code 54162)
- [Allison AE-3007A1](https://openairdocs.org/engine/allison-ae-3007a1): 0 aircraft (registry code 03050)
- [Allison AE-3007A1/2](https://openairdocs.org/engine/allison-ae-3007a1-2): 0 aircraft (registry code 03049)
- [Allison AE-3007A1E](https://openairdocs.org/engine/allison-ae-3007a1e): 0 aircraft (registry code 03054)
- [Allison AE-3007A1P](https://openairdocs.org/engine/allison-ae-3007a1p): 0 aircraft (registry code 03051)
- [Allison AE-3007A3](https://openairdocs.org/engine/allison-ae-3007a3): 0 aircraft (registry code 03052)
- [Rolls-Royce AE-3007A1/1](https://openairdocs.org/engine/rolls-royce-ae-3007a1-1): 0 aircraft (registry code 54163)
- [Rolls-Royce AE-3007A1/2](https://openairdocs.org/engine/rolls-royce-ae-3007a1-2): 0 aircraft (registry code 54164)
- [Rolls-Royce AE-3007A3](https://openairdocs.org/engine/rolls-royce-ae-3007a3): 0 aircraft (registry code 54167)

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