# TCDS E00008CH: Rolls-Royce Corporation - Type: Type certificate data sheet - Status: Current - Holder: Rolls-Royce Corporation - Revision: 5 - Revised: August 31, 2018 - Product: Engine - Certification basis: Part 33, Part 34 - Data sheet PDF: https://openairdocs.org/files/sha256/67/20/6720fcfba4b45ab803385bb06876b5bac6e3a52baa20990d1f8c62419bc922e3 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/E77AE2CC98A93164862582F200734610.0001 - Page: https://openairdocs.org/tcds/E00008CH ## Models (1) As the data sheet lists them. - AE 1107C ## 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 Rev No. 5 4 4 4 4 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E00008CH Revision 5 Rolls-Royce Corporation AE 1107C August 31, 2018 TYPE CERTIFICATE DATA SHEET NO. E00008CH Engine models described herein conforming with this data sheet (which is part of Type Certificate No. E00008CH) 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 Model: AE 1107C Type: Free turbine turboshaft engine, modular design, 14 stage axial compressor, annular combustor, 2 stage gas generator turbine, 2 stage power turbine, bottom mounted power section accessory gearbox, two single channel full authority digital electronic controls. Model AE 1107C (P/N 23060102) Ratings (see Note 1) Takeoff (5 min, see Note 1): Shaft Horsepower, SHP 6,456 Gas Generator Speed, rpm (estimated) 15,817 Power Turbine Speed, rpm 15,750 Measured Gas Temperature °F 1,565 Maximum Continuous: Shaft Horsepower, SHP 4,633 Gas Generator Speed, rpm (estimated) 15,268 Power Turbine Speed, rpm 15,000 Measured Gas Temperature, °F 1,392 Principal Dimensions of Basic Engine: Length (overall), in. 77.94 Diameter, Nominal, in. 24.50 Maximum Radial Projection, in. 21.10 C. G. location, dry (refer to Installation Drawings) Engine Axial Station, in. 98.985 Engine Buttock Line, in. 99.59 Engine Water Line, in. 97.98 Weight (dry), lb: 998.4 2 E00008CH AE 1107C (P/N 23060102) Engine Control System: (major components) Full Authority Digital Electronic Control (FADEC), qty 2. Fuel Pump & Metering Unit (FPMU) Compressor Variable Geometry (CVG) actuator. Fuels: MIL-DTL-5624 grades JP-4 and JP-5. MIL-DTL-83133 grade JP-8. Additional fuels are identified in Engine Manual (CSP 31006), and Operations Manual (CSP 30007) Lubrication Oil: Oils conforming to MIL-PRF-23699 or MIL-PRF-7808, except MIL-PRF-23699 only for oil temperatures above those corresponding to an oil kinematic viscosity of 13,000 centistokes. Additional oils are identified in Engine Manual (31006), and Operation Manual (CSP 30007). Ignition System: Dual capacitance discharge, high energy type exciters, dual igniter plugs Certification Basis: 14 CFR Part 33 dated February 1, 1965, with Amendments 1 through 15 inclusive, plus 14 CFR §33.74 amendment 17 (Continued Rotation) Original application for type Certificate dated April 3, 1995; Revised October 6, 1997 to include amendment 15. Type Certificate No. E00008CH issued November 6, 1998. Production Basis: Production Certificate No. 310, dated November 6, 1998. NOTE 1. Model AE 1107C (P/N 23060102) Engine ratings are based on: - Sea level static, ISA+44°F. - 100% inlet pressure recovery - Exhaust nozzle area of: 318.7 in2 - Zero relative humidity - No inlet air distortion - No customer bleed extraction - No external power extraction - No anti-ice airflow - Fuel having an LHV of 18300 Btu/lb otherwise conforming to fuels specified for use with this engine - Oil conforming to MIL-PRF-23699 - Minimum Specification Engine (100%) 3 E00008CH NOTE 2. Model AE 1107C (P/N 23060102) Temperature Limits: Measured Gas Temp. (same as T4.5 and ITT) Takeoff (5 minutes) 1616°F(A) Max. Continuous 1532°F Starting 1435° F(A) Oil Inlet Temperature: Max. Steady State 275°F Max. Transient (1 min.) 285°F Minimum -40°F (MIL-PRF-23699) -65°F (MIL-PRF- 7808) 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 (A) For AE 1107C production engines that have incorporated FADEC software version G14 or higher. For in- service engines that comply with SB AE 1107C-73-033. For all other engines the following temperature limits apply: Takeoff 1566°F, Starting 1500°F. NOTE 3. Model AE 1107C (P/N 23060102) Maximum Permissible Speeds: Gas Generator: Steady State, rpm 15,970 Transient, rpm 16,129 Power Turbine: Steady State, rpm 15,750 Transient, rpm 16,350 NOTE 4. Model AE 1107C (P/N 23060102) Maximum Permissible Engine Shaft Torque: Transient, ft lb 2,500 Takeoff (5 min), ft lb 2,153 Max. Continuous, ft lb 1,622 4 E00008CH NOTE 5. Model AE 1107C (P/N 23060102) Pressure Limits: Oil Pressure Limits: Power Section (max), psid 60 Power Section (min), psid 35 @ 100% Ng 30 @ Idle Ng Fuel Pump Inlet Pressure: Minimum, psig 11.1 Maximum, psig 50 NOTE 6. Model AE 1107C (P/N 23060102) Accessory Drive Provisions: Direction of Max torque cont. Max torque static Max overhung Accessory rotation Speed ratio (lb-in) (lb-in) moment (in. lb) Starter CW 1.0000 1080 3240 80 NOTE 7. Model AE 1107C (P/N 23060102) The maximum permissible customer compressor bleed air quantity for the AE 1107C engine as a percentage of the total engine inlet airflow is: 14th stage, % 8.0% NOTE 8. Mandatory replacement times (life limits) established for critical components and mandatory airworthiness inspections for the AE 1107C engine are published in the Tim e Limits Manual, CSP 34027. NOTE 9. The AE 1107C engine meets the applicable requirements of 14 CFR part 34 Amendments 1-5A. NOTE 10. The AE 1107C model is intended for a US military application. Current US law does not require that public use or milita ry aircraft/engines be operated or maintained in accordance with the FAA approved type design. Deliberate or planned operation of this model outside of the Type Design, to include but not limited to ratings, limitations, and instructions for continued airw orthiness, is considered a violation of the Type Design and 14 CFR Part 33. NOTE 11. The AE 1107C model is intended for use only in a dual engine application. NOTE 12. The AE 1107C model is restricted to fixed engine attitude until tilt -rotor engine requirements are defined by the Federal Aviation Administration and subsequent compliance to these requirements has been demonstrated. 5 E00008CH NOTE 13. The AE 1107C model is intended for installation in a U.S. military aircraft which does not have an FAA type certificate or FAA standard certificate of airworthiness. The AE 1107C Instructions for Continued Airworthiness (ICA) are captured in the following published documents: AE 1107C Engine Manual (CSP 31006), AE 1107C Time Limits Manual (CSP 34027), and applicable service bulletins. ...END... ``` ## ADs (1, in force first) - [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 ## Registered aircraft by registry model (OpenAirDocs) - [Allison AE-1107C](https://openairdocs.org/engine/allison-ae-1107c): 0 aircraft (registry code 03041) - [Rolls-Royce AE-1107C](https://openairdocs.org/engine/rolls-royce-ae-1107c): 0 aircraft (registry code 54002) --- 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.