TCDS TE6CH

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...