TCDS TE1CH

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