# TCDS TE1CH: Rolls-Royce Corporation

- Type: Type certificate data sheet
- Status: Current
- Holder: Rolls-Royce Corporation
- Revision: 32
- Revised: December 29, 2017
- Product: Engine
- Certification basis: Part 33, Part 34
- Registered aircraft: 17, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/d7/fc/d7fc70cb64d77fb72f7a9248e5c68019f30211abdd219f8aa61eab2b6b786e54
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/958B10612FCD574F86258211006D4706.0001
- Page: https://openairdocs.org/tcds/TE1CH

## Models (7)

As the data sheet lists them.

- AE 2100P
- AE 2100D2A
- AE 2100D3
- AE 2100C
- AE 2100J
- AE 2100D2
- AE 2100A

## What the data sheet says

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

```text
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
TYPE CERTIFICATE DATA SHEET NO. TE1CH 
Rolls-Royce Corporation  TE1CH 
Revision 32                                         December 29, 2017 
AE 2100A AE 2100D3 
AE 2100C  AE 2100J 
AE 2100D2  AE 2100P 
AE 2100D2A 
 
 
Engine models described herein conforming with this data sheet (which is part of Type Certificate No. TE1CH) 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 
450 South Meridian Street 
Indianapolis, Indiana 46255-1103 
 
Type Certificate Holder Record: TE1CH originally issued to Allison Division, General Motors Corporation - 23 Apr 1993 
TE1CH reissued to Allison Engine Company - 1 Dec 1993 
TE1CH reissued to Rolls-Royce Corporation - 1 Sept 2000 
 
 
Models AE 2100A, AE 2100C, AE 2100D2, AE 2100D2A, AE 2100D3, AE 2100J and AE 2100P. 
 
Type:  Free turbine turboprop engine, modular design, 14 stage axial compressor, annular combustor, 2 stage gas 
generator turbine, 2 stage power turbine, front mounted propeller reduction gearbox, bottom mounted power 
section accessory gearbox, two single channel full authority digital electronic controls. 
 
Model AE 2100A AE 2100C 
Ratings (see Note 1) P/N 23053610 P/N 23060202 P/N 23057466 P/N 23060302 
Takeoff (5 min,):     
Shaft Horsepower, SHP 4,152 - - 3,271 - - 
Gas Generator Speed, rpm 15,030 - - 14,847 - - 
Output Shaft Speed, rpm 1,100 - - 1,100 - - 
Measured Gas Temperature °F 1,417 - - 1,365 - - 
     
Maximum Continuous:     
Shaft Horsepower, SHP 3,738 - - 3,271 - - 
Gas Generator Speed, rpm 14,873 - - 14,847 - - 
Output Shaft Speed, rpm 1,100 - - 1,100 - - 
Measured Gas Temperature, °F 1,371 - - 1,365 - - 
     
Output Shaft Gear Ratio: 13.98:1 - - 13.98:1 - - 
     
Propeller Mount: Flange type - - - - - - 
     
Principal Dimensions of Basic Engine:     
Length (overall), in. 115.68 118.14 115.68 - - 
Width (max), in. 31.40 32.84 31.40 31.92 
Height (max), in. 49.62 52.92 49.62 52.72 
C. G. location, dry     
•  aft of prop flange, in. 52.36 54.04 52.36 51.92 
•  above engine center line, in. 2.15 2.50 2.15 2.40 
     
Weight (dry), lb: 1,578 1,627 1,578 - - 
"- -" indicates "same as previous model" 
Page 1 2 3 4 5 6 7 8 9 10 11 
Rev 32 32 32 29 29 30 31 28 29 29 32

2 of 11 TE1CH 
 
Model (continued) AE 2100A AE 2100C 
 P/N 23053610 P/N 23060202 P/N 23057466 P/N 23060302 
     
Engine Control System: 
(major components) 
Full Authority 
Digital Electronic 
Control (FADEC), qty. 2 
(Aircraft mounted) 
- - - - - - 
 Fuel Pump & 
Metering Unit (FPMU) 
- - - - - - 
 Compressor 
Variable Geometry 
(CVG) Actuator 
- - - - - - 
     
Fuels: Allowed Fuels are provided in the Operations Manual for each engine model. 
 
See Note 10 for applicable Operations Manual publication. 
     
Lubrication Oil: Allowed Oils are provided in the Operations Manual for each engine model. 
 
See Note 10 for applicable Operations Manual publication. 
     
Certification Basis: 14 CFR Part 33 dated 
February 1, 1965, 
including Amendments 
33-1 through 33-14 
 
14 CFR Part 34, effective 
September 10,1990, 
including Amendments 
34-1 through 34-3 
- - 
 
 
 
 
- - 
- - 
 
 
 
 
- - 
- - 
 
 
 
 
- - 
     
 Original application for 
Type Certificate dated 
February 15, 1990 
amended July 20, 1992; 
Type certificate No. 
TE1CH, issued April 23, 
1993 
Major design change 
approved April 15, 
1994 (See Note 9) 
Original application for 
Type Certificate dated 
June 15, 1992, amended 
July 20, 1992 and 
December 17, 1993; 
Type certification No. 
TE1CH amended 
December 20, 1993 
Major design 
change 
approved 
August 11, 
1994 (See Note 9) 
     
Production Basis: Production Certificate No. 
310, dated June 24, 1993 
- - - - - - 
     
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
"- -" indicates "same as previous model"

3 of 11 TE1CH 
 
Model AE 2100D2 AE 2100D2A AE 2100D3 AE 2100J AE 2100P 
         
Ratings (see Note 1) P/N 
23070302 
P/N 
23085027 
P/N 
23054062 
P/N 
23090635 
P/N 
23091820 
P/N 
23091822 
P/N 
23070202 
P/N 
23086499 
Takeoff (5 min, see Note 1):         
Shaft Horsepower, SHP 4,637 - - - - - - - - - - 4,591 4,152 
Gas Generator Speed, 
rpm 
15,284 - - - - - - - - - - 15,176 15,030 
Output Shaft Speed, rpm 1,020.7 - - - - - - - - - - 1,020.7 1,100 
Measured Gas 
Temperature °F 
1,488 - - - - - - - - - - 1,493 1,417 
         
Maximum Continuous:         
Shaft Horsepower, SHP 4,637 - - - - - - - - - - 4,591 3,738 
Gas Generator Speed, 
 
15,042 - - - - - - - - - - 14,937 14,873 
Output Shaft Speed, rpm 1,020.7 - - - - - - - - - - 1,020.7 1,100 
Measured Gas 
Temperature, °F 
1,431 - - - - - - - - - - 1,432 1,371 
         
Output Shaft Gear Ratio: 13.98:1 - - - - - - - - - - - - - - 
         
Propeller Mount: - - - - - - - - - - - - - - - - 
         
Principal Dimensions of 
Basic Engine: 
        
Length (overall), in. 116.99 - - 124.12 - - - - - - 118.14 - - 
Width (max), in. 31.80 - - 28.71 - - - - - - 32.84 - - 
Height (max), in. 52.53 - - 46.33 - - - - - - 52.92 - - 
C. G. location, dry         
•  aft of prop flange, in. 53.72 - - 59.66 - - - - - - 54.04 - - 
•  above engine center 
line, in. 
2.48 - - 2.97 - - - - - - 2.50 - - 
         
Weight (dry), lb: 1,776 - - 1,740 - - - - - - 1,666 1,627 
 
Model (continued) AE 2100D2 AE 2100D2A AE 2100D3 AE 2100J AE 2100P 
         
 P/N 23070302 P/N 23085027 P/N 
23054062 
P/N 
23090635 
P/N 
23091820 
P/N 
23091822 
P/N 
23070202 
P/N 
23086499 
Engine Control 
System: (major 
components) 
Full Authority 
Digital Electronic 
Control (FADEC), qty. 
2 (Aircraft mounted) 
- - - - - - - - - - - - - - 
 Fuel Pump & 
Metering Unit (FPMU) 
- - - - - - - - - - - - - - 
 Compressor 
Variable Geometry 
(CVG) Actuator 
- - - - - - - - - - - - - - 
         
Fuels: Allowed Oils are provided in the Operations Manual for each engine model. 
See Note 10 for applicable Operations Manual publication. 
         
Lubrication Oil: Allowed Oils are provided in the Operations Manual for each engine model. 
See Note 10 for applicable Operations Manual publication. 
         
 
 
 
 
 
 
"- -" indicates "same as previous model"

4 of 11 TE1CH 
 
Model 
(continued) 
AE 2100D2 AE 2100D2A AE 2100D3 AE 2100J AE 2100P 
 P/N 23070302 P/N 23085027 P/N 23054062 P/N 23090635 P/N 23091820 P/N 23091822 P/N 23070202 P/N 23086499 
Certification 
Basis: 
14 CFR Part 33, 
Effective February 
1,1965, including 
Amendments 33- 
1 through 33-15 
 
14 CFR Part 34, 
effective 
September 10, 
1990 including 
Amendments 34- 
1 through 34-3. 
- - 
 
 
 
 
 
 
- - 
- - 
 
 
 
 
 
 
- - 
- - 
 
 
 
 
 
 
- - 
- - 
 
 
 
 
 
 
- - 
- - 
 
 
 
 
 
 
- - 
- - 
 
 
 
 
 
 
- - 
14 CFR Part 33 
dated February 1, 
1965, including 
Amendments 33-
1 through 33-14 
 
 
- - 
         
 Original 
application for 
type Certificate 
dated May 22, 
1998;   
Type certificate 
No. TE1CH 
amended March 
31, 2001 
Original 
application for 
Type Certificate 
dated August 22, 
2006; 
Type Certificate 
No. TE1CH 
amended 
December 15, 
2006 
Original 
application for 
type Certificate 
dated September 
15, 1994, 
amended under 
Allison letter 96- 
AY-094; 
Type certificate 
No. TE1CH 
amended March 
31, 1997 
 
 
 
 
- - 
 
 
 
 
 
- - 
 
 
 
 
 
- - 
 
Original 
application for type 
Certificate dated 
May 22, 
1998; 
Type certificate 
No. TE1CH 
amended July 12, 
2000 
Original 
application 
for Type 
Certificate dated 
August 22, 
2006; 
Type Certificate 
No. TE1CH 
amended May 1, 
2007 
Production 
Basis: 
Production 
Certificate No. 
310, dated June 
24, 1993 
- - - - - - - - - - - - - - 
         
 
NOTE 1 - Ratings Basis 
Engine ratings are based on: 
 
- Sea level static, 29.92" Hg, (ISA +39ºF for AE 2100A and AE 2100P), (ISA +54°F for AE 2100C), (ISA +44°F for AE 2100D2, 
AE 2100D2A, AE 2100D3 and AE 2100J) 
- Flat rated to 98°F (AE 2100A and AE 2100P), 113°F (AE 2100C), 103°F (AE 2100D2, AE 2100D2A, AE 2100D3 and AE 
2100J), compressor inlet temperature 
- 100% inlet pressure recovery 
- Exhaust nozzle area (A9) of: AE 2100A and AE 2100P = 220 in2, AE 2100C = 220 in2, AE 2100D2, AE 2100D2A, AE 2100D3 
and AE 2100J = 235 in2 
- Zero relative humidity 
- No inlet air distortion 
- No customer bleed extraction 
- No external power extraction 
- Fuel having an LHV of 18400 Btu/lb (AE 2100A and AE 2100P), 18550 Btu/lb (AE 2100C), 18300 Btu/lb (AE 
2100D3), and 18400 Btu/lb (AE 2100D2, AE 2100D2A, and AE 2100J) otherwise conforming to fuels specified for 
use with this engine 
- Oil conforming to MIL-PRF-23699 
- Minimum Specification Engine (100%) 
 
 
 
 
 
 
 
 
 
 
"- -" indicates "same as previous model"

5 of 11 TE1CH 
 
NOTE 2 – Temperature Limits 
 
Model: AE 2100A AE 2100C 
 P/N 23053610 P/N 23060202 P/N 23057466 P/N 23060302 
Temperature Limits:     
Measured Gas Temp. 
(same as T4.5 and ITT)     
Takeoff (5 minutes) 1566°F - - 1528°F - - 
Max. Continuous 1532°F - - 1528°F - - 
Starting 1500°F - - - - - - 
     
Oil Inlet Temperature:     
Max. Steady State 185°F 190°F 185°F - - 
Max. Transient (5 min.) 200°F - - - - - - 
Minimum -40°F or -65°F - Set by oil selection.  See Note 10 for the applicable Operations Manual and approved oils. 
Maximum External 
Component Temperatures 
The maximum component operating temperatures are listed in the engine Installation Design Manuals. 
See Note 10 for applicable Installation Design Manual publication. 
  
Fuel Pump Inlet Temp:  
Minimum -65°F or that temperature corresponding to 12 centistokes (Cs) fuel viscosity, whichever is higher. 
Maximum steady state 135°F - - - - - - 
 
 
Model AE 2100D2 AE 2100D2A AE 2100D3 AE 2100J AE 2100P 
 P/N 23070302 P/N 23085027 P/N 23054062 P/N 23090635 P/N 23091820 P/N 23091822 P/N 23070202 P/N 23086499 
Temperature Limits:         
Measured Gas Temp. 
(same as T4.5 and ITT) 
        
Takeoff (5 minutes) 1566°F - - - - - - - - - - - - - - 
Max. Continuous 1532°F - - - - - - - - - - - - - - 
Starting - - - - - - - - - - - - - - - - 
         
Oil Inlet Temperature:         
Max. Steady State 185°F - - - - - - - - - - - - 190°F 
Max. Transient (5 
minutes) 
200°F - - - - - - - - - - - - - - 
Minimum -40°F or -65°F - Set by oil selection.  See Note 10 for the applicable Operations Manual and approved oils. 
Maximum External 
Component 
Temperatures 
The maximum component operating temperatures are listed in the engine Installation Design Manuals. 
See Note 10 for applicable Installation Design Manual publication. 
  
Fuel Pump Inlet Temp:  
Minimum -65°F or that temperature corresponding to 12 centistokes (Cs) fuel viscosity, whichever is higher. 
Maximum steady state 135°F - - - - - - - - - - - - - - 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
"- -" indicates "same as previous model"

6 of 11 TE1CH 
 
NOTE 3 – Speed Limits 
Model AE 2100A AE 2100C 
 P/N 23053610 P/N 23060202 P/N 23057466 P/N 23060302 
Max Permissible Speeds:     
Gas Generator:     
Steady State, rpm 15,715 - - 15,404 - - 
Transient, rpm 15,872 - - 15,558 - - 
Power Turbine:     
Steady State, rpm 15,375 - - - - - - 
Transient, rpm 16,298 - - - - - - 
Prop Shaft:     
Steady State, rpm 1,100 - - - - - - 
Transient, rpm 1,166 - - - - - - 
 
Model AE 2100D2 AE 2100D2A AE 2100D3 AE 2100J AE 2100P 
          P/N 23070302 P/N 23085027 P/N 23054062 P/N 23090635 P/N 23091820 P/N 23091822 P/N 23070202 P/N 23086499 
Max Permissible Speeds:         
Gas Generator:         
Steady State, rpm 15,715 - - - - - - - - - - - - - - 
Transient, rpm 15,872 - - - - - - - - - - - - - - 
Power Turbine:         
Steady State, rpm 14,267 - - - - - - - - - - - - 15,375 
Transient, rpm 16,298 - - - - - - - - - - - - - - 
Prop Shaft:         
Steady State, rpm 1,020.7 - - - - - - - - - - - - 1,100 
Transient, rpm 1,166 - - - - - - - - - - - - - - 
 
 
NOTE 4 – Torque Limits 
Model AE 2100A AE 2100C 
 P/N 23053610 P/N 23060202 P/N 23057466 P/N 23060302 
Maximum Permissible 
Engine Shaft Torque:     
Transient, ft lb 1,710 - - - - - - 
Takeoff (5 min), ft lb 1,470 - - 1,168 - - 
Max. Continuous, ft lb 1,328 - - 1,168 - - 
 
Model AE 2100D2 AE 2100D2A AE 2100D3 AE 2100J AE 2100P 
          P/N 23070302 P/N 23085027 P/N 23054062 P/N 23090635 P/N 23091820 P/N 23091822 P/N 23070202 P/N 23086499 
Maximum Permissible 
Engine Shaft Torque: 
        
Transient, ft lb 1,933 - - - - - - - - - - - - 1,710 
Takeoff (5 min), ft lb 1,732 - - - - - - - - - - - - 1,470 
Max. Continuous, ft lb 1,732 - - - - - - - - - - - - 1,328 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
"- -" indicates "same as previous model"

7 of 11 TE1CH 
 
NOTE 5 – Oil/Fuel Limits 
Model AE 2100A AE 2100C 
 P/N 23053610 P/N 23060202 P/N 23057466 P/N 23060302 
Pressure Limits:     
     Oil Pressure Limits:     
Power Section (max), psig 80 90(a) 80 - - 
Power Section (min), psig 40 - - - - - - 
Prop gearbox (max), psig 210(b) - - - - - - 
Prop gearbox (min), psig 25 20 25 - - 
Fuel Pump Inlet Pressure:     
Minimum Fuel true vapor pressure 
(TVP) plus 3 psi 
For Jet-A fuel true vapor 
pressure (TVP) plus 3 psi; 
For Jet-B fuel true vapor 
pressure (TVP) plus 11.4 
psi 
Fuel true vapor pressure 
(TVP) plus 3 psi 
- - 
Maximum, psig 52 - - - - - - 
 
Note (a)   Power section oil pressure is 90 psig if Service Bulletin AE 2100A-79-045 has been complied with, otherwise limit 
remains at 80 psig. 
Note (b)   Power section and gearbox pressures may reach 250 psig for up to 2.5 minutes during initial starting and warm-up. 
 
Model AE 2100D2 AE 2100D2A AE 2100D3 AE 2100J AE 2100P 
 P/N 23070302 P/N 23085027 P/N 23054062 P/N 23090635 P/N 23091820 P/N 23091822 P/N 23070202 P/N 23086499 
Pressure Limits:         
         
Oil Pressure Limits:         
Power Section (max), psig 90 - - - - - - - - - - - - - - 
Power Section (min), psig 40 - - - - - - - - - - - - - - 
Prop gearbox (max), psig 210(b) - - - - - - - - - - - - - - 
Prop gearbox (min), psig 10 - - - - - - - - - - - - 20 
Fuel Pump Inlet Pressure:         
Minimum For Jet-A fuel 
true vapor 
pressure 
(TVP) plus 3 
psi; For Jet-B 
fuel true vapor 
pressure 
(TVP) plus 
11.4 psi 
- - - - - - - - - - - - - - 
Maximum, psig 55 - - 52 - - - - - - - - - - 
 
 
 
NOTE 6 - Accessory Drive Provisions 
Model AE 2100A and AE 2100C (All) 
Accessory Direction of 
Rotation 
Speed ratio Max torque cont. 
(in. lb.) 
Max torque static 
(in. lb.) 
Max overhung 
moment (in. lb.) 
 
Power Section Accessory Gearbox 
Starter CW 1.0000 1080 3240 80 
 
Gearbox Mounted Accessory Drive Gearbox 
Generator CW 1.1258 373 2100 250 
Pitch Control Unit No drive provided 
(mounted pad only) 
N/A N/A N/A 100 
Prop oil pump CCW 0.3506 120 500 40 
Hydraulic pump CW 0.5942 125 450 100 
 
 
 
 
"- -" indicates "same as previous model"

8 of 11 TE1CH 
 
NOTE 6 - Accessory Drive Provisions (continued) 
 
Oil Tank 
 
Feather pump 
(Aircraft supplied) 
No drive provided 
(mount pad only) 
N/A N/A N/A 19 
 
Model AE 2100D2 and AE 2100D2A 
      
Accessory Direction of 
rotation 
Speed ratio Max torque cont. 
(in. lb.) 
Max torque static 
(in. lb.) 
Max overhung 
moment (in. lb.) 
 
Power Section Accessory Gearbox 
Starter CW 1.0000 1080 3240 101 
 
Gearbox Mounted Accessory Drive Gearbox 
Generator CW 0.8432 815 3000 600 
Pitch Control Unit No drive provided 
(mounted pad only) 
N/A N/A N/A 138 
Prop oil pump CCW 0.3833 83 1000 40 
Hydraulic pump CW 0.2571 1500 4400 43 
 
 
Model AE 2100D3 (All) 
      
Accessory Direction of 
rotation 
Speed ratio Max torque cont. 
(in. lb.) 
Max torque static 
(in. lb.) 
Max overhung 
moment (in. lb.) 
 
Power Section Accessory Gearbox 
Starter CW 1.0000 1080 3240 101 
 
Gearbox Mounted Accessory Drive Gearbox 
Generator CW 0.8432 815 3000 600 
Pitch Control Unit No drive provided 
(mounted pad only) 
N/A N/A N/A 138 
Prop oil pump CCW 0.3833 83 1000 40 
Hydraulic pump CW 0.2571 1500 4400 43 
 
 
Model AE 2100J 
      
Accessory Direction of 
rotation 
Speed ratio Max torque cont. 
(in. lb.) 
Max torque static 
(in. lb.) 
Max overhung 
moment (in. lb.) 
 
Power Section Accessory Gearbox 
Starter CW 1.0000 1080 3240 101 
 
Gearbox Mounted Accessory Drive Gearbox 
Generator CW 0.8432 529 3000 600 
Pitch Control Unit No drive provided 
(mounted pad only) 
N/A N/A N/A 138 
Prop oil pump CCW 0.3833 83 1000 40 
Hydraulic pump CW 0.2571 344 4400 40 
 
 
 
 
 
 
 
 
 
"- -" indicates "same as previous model"

9 of 11 TE1CH 
 
 
 
NOTE 6 - Accessory Drive Provisions (continued) 
 
Model AE 2100P 
      
Accessory Direction of 
rotation 
Speed ratio Max torque cont. 
(in. lb.) 
Max torque static 
(in. lb.) 
Max overhung 
moment (in. lb.) 
 
Power Section Accessory Gearbox 
Starter CW 1.0000 1080 3240 80 
 
Gearbox Mounted Accessory Drive Gearbox 
Generator CW 1.1258 373 2100 250 
Pitch Control Unit No drive provided 
(mounted pad only) 
N/A N/A N/A 100 
Prop oil pump CCW 0.3506 120 500 40 
Hydraulic pump CW 0.5942 125 450 100 
 
Oil Tank 
Feather pump 
(Aircraft supplied) 
No drive provided 
(mount pad only) 
N/A N/A N/A 19 
 
 
NOTE 7 – Customer Bleed (maximum as a percentage of the total engine inlet airflow) 
Model AE 2100A AE 2100C 
 P/N 23053610 P/N 23060202 P/N 23057466 P/N 23060302 
     
8th stage, % 3.7 N/A 3.7 N/A 
     
10th stage, % N/A 4.75 N/A 4.75 
     
14th stage, % 8.0 9.2 8.0 9.2 
     
 
 
Model AE 2100D2 AE 2100D2A AE 2100D3 AE 2100J AE 2100P 
 P/N 23070302 P/N 23085027 P/N 23054062 P/N 23090635 P/N 23091820 P/N 23091822 P/N 23070202 P/N 23086499 
         
8th stage, % N/A N/A N/A N/A N/A N/A N/A N/A 
         
10th stage, % 8.0 - - - - - - - - - - - - 4.75 
         
14th stage, % 15.0 - - - - - - - - - - - - 9.2 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
"- -" indicates "same as previous model"

10 of 11 TE1CH 
 
NOTE 8 - Approved Propellers 
 
Propellers to be used with this engine must have mounting provisions and functioning characteristics which are compatible with 
the engine and its control system.  The AE 2100A, AE 2100C, AE 2100D2, AE 2100D2A, AE 2100D3, AE 2100J and AE 
2100P engines and control systems have been designed and tested to be compatible with the propellers models as noted: 
 
Model AE 2100A AE 2100C 
 P/N 23053610 P/N 23060202 P/N 23057466 P/N 23060302 
     
 Dowty R381 - - Dowty R384 - - 
 
Model AE 2100D2 AE 2100D2A AE 2100D3 AE 2100J AE 2100P 
 P/N 23070302 P/N 23085027 P/N 23054062 P/N 23090635 P/N 23091820 P/N 23091822 P/N 23070202 P/N 23086499 
         
 Dowty R391 - - - - - - - - - - Dowty R414 Dowty R381 
 
The propeller models noted above are controlled by an integrated control system which is a part of the corresponding engine 
type design. The propeller models noted, comply with the propeller airworthiness requirements when used with the 
corresponding engine only. Any change to the engine, including its control system, which affects, or may affect, the propeller 
approval must be substantiated to demonstrate that the propeller as integrated with the changed engine, including its control 
system, still complies with the propeller certification basis. Also, any change to the engine, resulting from a change to the 
propeller, must be substantiated to demonstrate that the changed engine still complies with the engine certification basis. 
 
The engine-propeller installation must be approved as a part of aircraft type certification. 
 
 
NOTE 9 – Engine Model Description 
 
 
AE 2100A, P/N 23053610 (Base Model): Basic model; has bleed air off-take from the 8th and 14th stages. 
 
AE 2100A, P/N 23060202:   Same as AE 2100A, P/N 23053610, except for having bleed air off-take from the 10th and 
14th compressor stages, different engine control software.  AE 2100A engines P/N 23053610, are eligible to be converted to 
engine P/N 23060202, via Service Bulletin No. AE 2100A-72-037. 
 
AE 2100C, P/N 23057466: Similar to the AE 2100A engine (P/N 23053610); rated at a maximum power of 3,271 shp. 
 
AE 2100C, P/N 23060302: Similar to the AE 2100A engine (P/N 23060202); incorporates bleed air off-take from the 10th 
and 14th compressor stages.  The AE 2100C engine P/N 23060302 is a variant of engine P/N 23057466 and is also rated at 
a maximum power of 3271 shp. 
 
AE 2100D3, P/N 23054062: Similar to the AE 2100A engine (P/N 23060202); rated at a maximum power of 4637 shp.  Oil 
Tank is aircraft supplied. 
 
AE 2100D3, P/N 23090635: Same as the AE 2100D3 engine P/N 23054062, except the engine is configured with a 60/90 
kVA generator. 
 
AE 2100D3, P/N 23091820: Same as the AE 2100D3 engine P/N 23054062, except the engine is configured with a 
propeller Wind Gust Brake unit on the GMAD. 
 
AE 2100D3, P/N 23091822: Same as the AE 2100D3 engine P/N 23054062, except the engine is configured with a 60/90 
kVA generator  and a propeller Wind Gust Brake unit on the GMAD. 
 
AE 2100D2, P/N 23070302: Similar to the AE 2100D3 (P/N 23054062) with the exception of a shorter torquemeter, 
propeller gearbox connecting struts and the addition of the AE 2100A oil tank.  The AE 2100D2 also includes a gearbox 
mounted oil accumulator.  The AE 2100D2 has similar ratings and limitations as the AE 2100D3 engine. 
 
AE 2100D2A, P/N 23085027: Same as the AE 2100D2 (P/N 23070302) with the exception incorporating Service bulletins 
AE 2100D2-72-070 and -071.  The AE 2100D2A has identical ratings and limitations as the AE 2100D2 engine. 
 
AE 2100J, P/N 23070202: Similar to the AE 2100D3 (P/N 23054062) with the exception of a shorter torquemeter and 
propeller gearbox connecting struts.  The AE 2100J has similar ratings and limitations as the AE 2100D3 engine.  Oil Tank 
is aircraft supplied. 
 
"- -" indicates "same as previous model"

11 of 11 TE1CH 
 
 
NOTE 9 – Engine Model Description (Con’t) 
 
 
AE 2100P, P/N 23086499: Same as the AE 2100A engine (P/N 23060202).  The AE 2100P model, at the time of 
certification (May 1, 2007), is the exact equivalent of the AE 2100A model.  Any AE 2100A Service Bulletins prior to May 
1, 2007 can be applied to the AE 2100P model.  Any Service Bulletin created after this date for the AE 2100P will be 
identified as an AE 2100P Service Bulletin.  Any ‘pre’ May 1, 2007 original issue AE 2100A Service bulletins that are 
revised after May 1, 2007 and are intended for use on the AE 2100P, will be identified as a ‘stand-alone’ AE 2100P Service 
Bulletin. 
 
Initial production AE 2100A engines S/Ns CAE 510001 through CAE 510034, and AE 2100C engines S/Ns CAE 530001 and 
CAE 530002,  are identified as GMA 2100A and GMA 2100C respectively and are different in model prefix only.  The 
manufacturer of initial production AE 2100A engines CAE 510001 through CAE 510038, and AE 2100C engines CAE 530001 
and CAE 530002, as identified on the engine data plates, is Allison Gas Turbine Division of General Motors.  Subsequent 
engines have been manufactured by Allison Engine Company or Rolls-Royce Corporation.  The three manufacturers are 
different in name only. 
 
 
NOTE 10 - Approved Manuals 
 
These documents, in combination with the limits declared by this TCDS, constitute the only approved method of installing 
and operating the engine. 
 
Mandatory replacement times (life limits) established for critical components and mandatory airworthiness inspections for the 
AE 2100A, AE 2100C, AE 2100D2, AE 2100D2A, AE 2100D3, and AE 2100J engines are published in the listed 
Maintenance Manuals: 
 
 
 
 
 
 
 
...END... 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
 
"- -" indicates "same as previous model" 
 AE 2100A AE 2100C AE 2100D2 AE 2100D2A AE 2100D3 AE 2100D3 (60/90 kVA) AE 2100D3 (WGB) AE 2100D3 (60/90 kVA, 
WGB) 
AE 2100J AE 2100P 
Installation 
Design Manual CSP34006 CSP34031 CSP34069 CSP34069 CSP34040 CSP34040 CSP34040 CSP34040 CSP34068 CSP 34110 
Operations 
Manual CSP30000 CSP30006 CSP30014 CSP30014 CSP30004 CSP30004 CSP30004 CSP30004 CSP30009 CSP 30018 
Maintenance 
Manual 
 
CSP31005 
 
CSP31003 
 
CSP34081 
 
CSP34081 
 
CSP34042 
 
CSP34042 
 
CSP34042 
 
CSP34042 
 
CSP34082 
 
CSP31015 
Parts List PL 3667 PL 3666 PL 3695 PL 10006 PL 3670 PL 10055 PL 10068 PL 10069 PL 3693 PL 10014
```

## ADs (10, in force first)

- [AD 2022-01-04](https://openairdocs.org/ad/2022-01-04): Turbine Engine Compressor Section · Rolls-Royce Deutschland AE 2100D3. Effective Feb 2, 2022
- [AD 2020-22-18](https://openairdocs.org/ad/2020-22-18): Turbine Engine Reduction Gear · Rolls-Royce AE 2100A, AE 2100D2, AE 2100D2A and 1 more. Effective Dec 15, 2020
- [AD 2020-20-04](https://openairdocs.org/ad/2020-20-04): Turbine Engine Reduction Gear · Rolls-Royce AE 2100D3. Effective Oct 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 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 2009-11-04](https://openairdocs.org/ad/2009-11-04): Propeller gearbox (PGB) · Rolls-Royce AE 2100D2, AE 2100D2A, AE 2100D3 and 1 more. Effective Jun 26, 2009
- [AD 2006-25-13](https://openairdocs.org/ad/2006-25-13): Compressor cone shaft assemblies · Rolls-Royce AE 2100D3. Effective Dec 29, 2006
- [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 99-17-09](https://openairdocs.org/ad/99-17-09): Propeller Gearbox (PGB) and Power Section (P/S) Strut Fittings · Rolls-Royce AE 2100A and AE 2100C. Effective Sep 7, 1999
- [AD 99-03-09](https://openairdocs.org/ad/99-03-09): Turbine wheel failure · Rolls-Royce AE 2100A, AE 2100C and AE 2100D3. Effective Feb 19, 1999

## Registered aircraft by registry model (OpenAirDocs)

- [Rolls-Royce AE-2100A](https://openairdocs.org/engine/rolls-royce-ae-2100a): 7 aircraft (registry code 54140)
- [Allison AE-2100A](https://openairdocs.org/engine/allison-ae-2100a): 5 aircraft (registry code 03042)
- [Rolls-Royce AE-2100D3](https://openairdocs.org/engine/rolls-royce-ae-2100d3): 5 aircraft (registry code 54143)
- [Allison AE-2100C](https://openairdocs.org/engine/allison-ae-2100c): 0 aircraft (registry code 03043)
- [Allison AE-2100D2](https://openairdocs.org/engine/allison-ae-2100d2): 0 aircraft (registry code 03044)
- [Allison AE-2100D3](https://openairdocs.org/engine/allison-ae-2100d3): 0 aircraft (registry code 03045)
- [Allison AE-2100J](https://openairdocs.org/engine/allison-ae-2100j): 0 aircraft (registry code 03046)
- [Rolls-Royce AE-2100C](https://openairdocs.org/engine/rolls-royce-ae-2100c): 0 aircraft (registry code 54141)
- [Rolls-Royce AE-2100D2](https://openairdocs.org/engine/rolls-royce-ae-2100d2): 0 aircraft (registry code 54142)
- [Rolls-Royce AE-2100J](https://openairdocs.org/engine/rolls-royce-ae-2100j): 0 aircraft (registry code 54144)

## STCs approved under this data sheet (1)

- [STC SE00888CH](https://openairdocs.org/stc/SE00888CH): Install a Wind Gust Brake Kit. Rolls-Royce Corporation

---
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