TCDS E25NE

* PAGE 1 2 3 4 5 6 7 8 9 10 REV. 12 12 12 12 12 12 11 12 12 11 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTICE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES, IF ANY, ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E25NE TCDS NUMBER E25NE REVISION: 12* DATE: December 17, 2014 ROLLS-ROYCE DEUTSCHLAND Ltd & Co KG MODELS: TAY 611-8 TAY 620-15 TAY 651-54 TAY 650-15 TAY 611-8C Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E25NE) and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated 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 approved manufacturer's manuals and other approved instructions. TYPE CERTIFICATE (TC) HOLDER: Rolls-Royce Deutschland Ltd & Co KG Eschenweg 11, Dahlewitz 15827 Blankenfelde-Mahlow Germany (Formerly Rolls-Royce plc, Derby, England) I. MODELS (TAY) 620-15 611-8 650-15 651-54 611-8C TYPE Dual rotor, axial flow high bypass turbofan, single-stage fan, three-stage low pressure compressor, 12-stage high pressure compressor, 10 cannular combustion chambers, two-stage high pressure turbine, and three-stage low pressure turbine. RATINGS Maximum continuous at sea level, static thrust, lb Takeoff (5 min.) at sea level, static thrust, lb Takeoff (10 min. OEI) at sea level, static thrust, lb 13,475 13,850 13,850 12,420 - - - - 14,000 15,100 15,100 - - 15,400 15,400 12,420 13,850 13,850 TCDS E25NE PAGE 2 I. MODELS (CONT.) (TAY) 620-15 611-8 650-15 651-54 611-8C COMPONENTS* FADEC: EEC Goodrich (1)P/N Fuel control: Goodrich (1) or: Goodrich (1) P/N or: Goodrich (1) P/N or: Goodrich (1)P/N Fuel pump (LP): FR-HiTemp (2) P/N Fuel pump (HP): Goodrich P/N Ignitor Plugs: Smiths P/N or: Smiths P/N or: Champion (3) P/N or: Champion (3) P/N N/A CASC501 CASC512 BP230/6 MK5 GD500 1401/RIG 1 1401/RIG 2 Y183-5 N/A CASC504 CASC514 CASC515 CASC516 BP230/6 MK5 GD501 1401/RIG 1 1401/RIG 2 Y183-5 N/A CASC506 CASC508 CASC509 BP230/6 MK5 GD501 1401/RIG 1 1401/RIG 2 Y183-5 Y183-6 N/A CASC510 CASC506 CASC508 BP230/6 MK5 GD501 1401/RIG 2 Y183-5 Y183-6 TEEC2000-04-AE FMU1101 & TMB101 BP230-6 MK5 GD502 Y183-5 * or later approved standards (1) formerly TRW and Lucas (2) formerly Bae Systems & Plessey (3) formerly Auburn PRINCIPAL DIMENSIONS, IN. Length, front flange to rear flange Maximum diameter, encircling diameter 94.75 70.72 - - - - - - - - - - - - - - - - WEIGHT (dry) (lbs.) 3,310 3,255 3,516 3,590 3,390 Basic engine with all essential accessories necessary for engine operation, but excludes intake, jet pipe, and nozzle assembly and hydraulic pumps. Starter is included for models TAY 620-15, 650- 14, 650-15, and 651-54. CENTER OF GRAVITY, IN. Aft front suspension centerline Below engine centerline Starboard from engine centerline 13.8 3.4 0.6 - - 2.9 0.4 14.2 3.3 0.6 14.5 3.5 - - 14.3 2.1 -0.8 FUEL See NOTE 10 OIL See NOTE 11 Oil Capacity 13.6 Liters/5.1 Liters usable TCDS E25NE PAGE 3 CERTIFICATION BASIS Tay 611-8, Tay 620-15, Tay 650-15 and Tay 651-54: 14 CFR 21.29 and part 33 effective Feb. 1, 1965, amended by 14 CFR 33-1 through 14 CFR 33- 9 and 14 CFR part 34, amendment 5, effective 12/31/2012 Pursuant to 14 CFR 21.29(a)(1)(ii), Type Certificate E25NE was issued in validation of the British Civil Aviation Authority's certification of compliance with BCAR standards, which were found to provide a level of safety equivalent to the above "Certification Basis", as follows: Airworthiness and Environmental Protection Requirements: JAR-E, Change 6, dated August 28, 1981 (BCAR Section C, Issue 13) Emissions: ICAO Annex 16, Volume II, First Edition, 1981 Special Conditions: Blue Paper C798, C3-4, 6.6.4 – “Endurance Tests, Temperatures (Hot Oil Running)” TAY 611-8C: 14 CFR 21.29 and part 33, effective Feb. 1, 1965, amended by 14 CFR 33-1 through 14 CFR 33- 9, § 33.28, Amendment 15, § 33.76, Amendment 20, § 33.78, Amendment 19, § 33.88, Amendment 18 and 14 CFR part 34, amendment 5, effective 12/31/2012. See note 13 for detailed summary of the certification basis for fuel venting and exhaust emissions. Pursuant to 14 CFR 21.29(a)(1)(ii), Type Certificate E25NE was issued in validation of the British Civil Aviation Authority's certification of compliance with BCAR standards, which were found to provide a level of safety equivalent to the above "Certification Basis", as follows: Airworthiness and Environmental Protection Requirements: JAR-E, Change 6 JAR-E, Change 10, E20 and E25 JAR-E, Change 10 for all new parts of the engine control system and its associated accessories ICAO Annex 16, Volume II, Second Edition, July 1993 – Emissions and venting Later compliance has been shown with CS-34 in accordance with ICAO Annex 16, Volume II, Third Edition 2008 incl. Amendment 6 –Aircraft Engine Emissions (approved 29/06/2011) Special Conditions: JAR-E790 at Change 10, Ingestion of Rain and Hail JAR-E540 and E800 at Amendment 11, Bird Strike / Ingestion JAR-E530(f) at Change 10 and AMJ 20X- 1, EEC Fire & Overheat Protection Equivalent Safety Findings: JAR-E, Change 6, C3-4, Paragraph 6, 150 hour endurance test JAR-E, Change 6, C3-4, Paragraph 2.2.1 and JAR-E, Change 10, E640(b)(1), static pressure tests JAR-E, Change 6, C3-4, Paragraph 22, Compressor and turbine rotor integrity tests DATE OF DATE TC ISSUED DATE TC MODEL APPLICATION OR REVISED CANCELLED TAY 610-8 MAR 06, 1984 OCT 30, 1986 OCT 21, 2002 TAY 620-15 MAR 06, 1984 OCT 30, 1986 TAY 611-8 SEP 09, 1987 OCT 15, 1987 TAY 611-8B MAY 02, 1989 JUN 30, 1989 OCT 21, 2002 TAY 650-14 JAN 26, 1988 MAR 16, 1990 OCT 21, 2002 TAY 650-15 JUN 02, 1987 OCT 05, 1988 TAY 651-54 MAR 20, 1991 MAY 20, 1992 TAY 611-8C DEC 12, 2001 MAR 5, 2003 The aviation authority for Germany, Luftfahrt-Bundesamt, type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E25NE. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Germany. TCDS E25NE PAGE 4 IMPORT REQUIREMENTS To be considered eligible for installation on U.S. registered aircraft, each new engine to be exported to the United States with Luftfahrt-Bundesamt (Germany) or EASA airworthiness approval shall have a Joint Aviation Authorities (JAA) or EASA Form 1, Authorized Release Certificate. The JAA or EASA Form 1 should state that the engine conforms to the type design approved under the U.S. Type Certificate E25NE, is in a condition for safe operation and has undergone a final operational check. Additional guidance is contained in FAA Advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, Engines, Propellers, and Related Products, Imported into the United States. NOTES I. MODELS (TAY) 620-15 611-8 650-15 651-54 611-8C NOTE 1. MAXIMUM PERMISSIBLE ENGINE OPERATING SPEEDS (See NOTES 8, 14, and 18) Models 611-8, 611-8C 100% HP=12,484 rpm, 100% LP=8,393 rpm Models 620-15, 650-15, 651-54 100% HP=12,136 rpm, 100% LP=8,393 rpm LOW PRESSURE ROTOR (N1) Takeoff (5 min.) Takeoff (10 min. OEI) Maximum continuous Transient (20 sec.) Maximum for reverse thrust 8,100 8,100 8,100 8,343 8,015 8,015 8,015 8,250 - - - - - - - - - - - - - - - - - - - - - - 8,100 5,457 HIGH PRESSURE ROTOR (N2) Takeoff (5 min.) Takeoff (10 min. OEI) Maximum continuous Transient (20 sec.) Minimum idle, ground and flight Maximum for reverse thrust 12,560 12,560 12,197 12,937 5,813 11,602 12,446 12,446 12,172 12,809 5,818 11,485 12,560 12,560 12,197 12,937 5,813 11,310 12,670 12,670 - - - - - - 11,650 12,560 12,560 12,172 12,684 6,130 N/A Operational Limitations: Tay 611-8 Tay 620-15 Tay 650-15 Tay 651-54 Tay 611-8C Static Ground Running and Taxiing Stabilized operation is not permitted in the Low Pressure rotor speed (N1) range 57% to 75% LP during all static ground running operations in forward thrust, and during taxiing. It is permitted to pass through this range whilst increasing or decreasing thrust. During static ground running the park brake must be used. For ground checks with the aircraft stationary and during taxiing the use of reverse thrust is limited to idle. TCDS E25NE PAGE 5 Reverse Thrust Stabilized operation is not permitted in the Low Pressure rotor speed (N1) range 54% to 72% Stabilized operation is not permitted in the Low Pressure rotor speed (N1) range 57% to 75% Stabilized operation at any intermediate position between idle and maximum reverse thrust is prohibited Take-off For take-off, the thrust levers must be initially being set to 1.15 Engine Pressure Ratio (EPR) or below, then set the required take- off EPR between 40 and 80 kts forward speed Powerback The use of powerback is prohibited. See applicable Operating Instructions identified in note 12 for a complete list of operating limitations NOTE 2. MAXIMUM PERMISSIBLE TEMPERATURES (See NOTE 14) TURBINE GAS TEMP. Measured at first stage low pressure turbine nozzle guide vane oC/oF oC/oF oC/oF oC/oF °C/°F Takeoff (5 min.) Takeoff (10 min. OEI) Maximum continuous Overtemperature (20 sec.) Starting, ground (2 sec.) Starting, inflight (2 sec.) 800/1472 800/1472 735/1355 820/1508 700/1292 780/1436 - - - - 715/1319 - - - - - - 850/1562 850/1562 795/1463 870/1598 740/1364 780/1436 865/1589 865/1589 - - 885/1625 - - - - 800/1472 800/1472 715/1319 820/1508 700/1292 - - FUEL TEMPERATURE Measured at inlet to high pressure stage of fuel pump (See NOTE 10) oC/oF oC/oF oC/oF oC/oF °C/°F Continuous operation Transient operation (15 min.) 90/194 120/248 - - - - 95/203 130/266 - - - - - - - - OIL INLET TEMPERATURE Measured at oil pump exit (See NOTE 11) oC/oF oC/oF oC/oF oC/oF °C/°F Continuous operation Transient operation (15 min.) 105/221 120/248 - - - - - - - - - - - - - - 120/248 NOTE 3. FUEL AND OIL PRESSURE LIMITS / ALL MODELS FUEL Measured at inlet to low pressure stage of fuel pump Minimum operation Minimum starting Maximum 12 psia or 6 psi above tank pressure, which ever is lower, but not less than 2 psig 10 psia 40 psig OIL Measured at oil pump exit. Minimum for takeoff Maximum continuous Idle to 9500 rpm (1) 30 psig 25 psig 16 psig (1) Oil pressure increase follows a straight line relationship between 9500 rpm N2 and maximum continuous condition. TCDS E25NE PAGE 6 I. MODELS (TAY) 620-15 611-8 650-15 651-54 611-8C NOTE 4. MAXIMUM PERMISSIBLE AIR BLEED EXTRACTIONS Compressor air bleed may be used in accordance with Rolls-Royce instructions such that the operating limitations are not exceeded, up to either the individual or combined non-dimensional bleed extraction defined. Bleed air for nose cowl anti-icing is included. T1 = total temperature at engine intake (K) P1 = total pressure at engine intake (psia) M7 = HP stage 7 offtake mass flow (lb/sec) M12 = HP stage 12 offtake mass flow (lb/sec) MT = M7+M12 offtake mass flow (lb/sec) MF = LP (fan) offtake mass flow (lb/sec) 7th-Stage HPC Bleed ((M7)(T1**.5))/P1 Maximum takeoff Maximum continuous and below 12th-Stage HPC Bleed ((M12)(T1**.5))/P1 Maximum takeoff Maximum continuous and below HPC Total Bleed ((MT)(T1**.5))/P1 Maximum takeoff (a) Maximum continuous and below (b) Fan Bleed ((MF)(T1**.5))/P1 Maximum takeoff Maximum continuous and below 7.0 7.0 --- 10.0 7.0 10.0 10.5 10.5 - - - - - - - - - - - - -- -- - - - - - - - - - - - - 6.5 6.5 9.69 9.10 - - 12.9 9.69 12.9 14.51 13.94 7.0 7.0 - - 6.9 7.0 10.0 10.5 10.5 (a) For maximum takeoff, the bleed air may be extracted from 7th stage only. (b) For maximum continuous, the bleed air may be extracted either from 12th stage or from combination of 7th and 12th stages. NOTE 5. BASIS OF RATINGS Use of the 10-minute one engine inoperative (OEI) takeoff rating is approved for use only in the event of an inoperative engine(s) due to shutdown or failure, and is limited to periods of not more than 10-minutes. Takeoff thrust under normal conditions, i.e. when all engines are operative, is limited to periods of not more than 5-minutes. Ratings are based on static test stand operation under the following conditions: (a) compressor inlet air at 15°C (59°F) and 29.92 in-Hg (b) Rolls-Royce test bed flaremeter TA1, TA2 or TA3 (ATF9476) for the TAY 611-8 and 620-15 and TA10 or TA11 (ATF10173) for the TAY 650-15, 651-54 and 611-8C. (c) Rolls-Royce Jet Pipe/Final Nozzle Assembly JP2 or JP3 (ATF9786) for the TAY 611-8 and 620-15, 650-15 and 651-54 and JP4 or JP5 (ATF9786) for the TAY 611-8C. (d) turbine gas temperature measured by 9 pairs of thermocouples mounted in the first stage low pressure turbine nozzle guide vane (NGV) with ballast resistor, specified in the applicable engine manual (e) no aircraft accessory loads or bleed air extraction (f) turbine gas temperature limits and engine rotor speed limits are not exceeded (g) 100% air intake recovery TCDS E25NE PAGE 7 NOTE 6. ACCESSORY DRIVE PROVISIONS DRIVE Rotation Speed Ratio To HP Rotor Speed TORQUE (lb - in) Maximum Continuous Instantaneous Overhang (lb - in) Starter All models Main Hydraulic pump 611-8 /611-8C 620-15 / 650-15 651-54 Auxiliary hydraulic pump 620-15 / 650-15 IDG 620-15 / 650-15 611-8C AC generator 611-8 CSD and alternator 651-54 CW CCW CCW CW CW CW CW CCW CW 1.0398 0.2615 0.3397 0.2880 0.3176 0.5088 0.5088 0.8821 0.6846 2592 732 461 732 176 659 659 500 1230 2981 3000 1455 3000 500 4286 7140 2310 5900 153 140 36 140 11 743 743 250 2154 NOTES: CW = clockwise, looking into the appropriate gearbox face CCW = counter-clockwise NOTE 7. Thrust setting, thrust check and control of engine output in all operations are to be based on Rolls- Royce engine charts included in the relevant operating instructions. On the hydromechanically controlled engines, pressure ratio (EPR) indication is not reliable as the primary thrust setting parameter due to the EPR probe's susceptibility to icing. N1 thrust setting procedures must be used for the TAY 620-15 model unless the EPR probes are modified in accordance with Rolls-Royce Service Bulletins 75-1036 and 75-1055 or the equivalent and with appropriate EPR thrust setting charts. NOTE 8. For inflight operation during icing conditions, the minimum allowable fan speed (N1) for the TAY 611-8C is 21.1% (1770rpm) and for the other variants is 21% (1760 rpm). NOTE 9. Certain engine parts are life-limited. These parts are listed in time limit section of the relevant Engine Manuals. Maintenance is to be carried out in accordance with the manual (See NOTE 12). NOTE 10. Approved fuels and fuel additives are listed in the appropriate Rolls-Royce Operating Instructions (See NOTE 12.) For the TAY 611-8 and 651-54 and 611-8C, minimum fuel temperature measured at inlet to low pressure stage of fuel pump is -40°C (-40°F). For the TAY 620-15 and 650-15, minimum fuel temperature measured at inlet to low pressure stage of fuel pump is -50°C (-58°F). NOTE 11. Approved oils are listed in the appropriate Rolls-Royce Operating Instructions (See NOTE 12). Oils of the approved types when reclaimed to the approved Rolls-Royce standards are approved for use. Minimum oil temperatures, measured at oil pump exit, are as follows: MINIMUM OIL TEMPERATURE ACCELERATION STARTING FROM IDLE TAY MODEL oC oF oC oF 611-8 / 611-8C 620-15 / 650-15 651-54 -40 -50 -40 -40 -58 -40 -30 -30 -30 -22 -22 -22 TCDS E25NE PAGE 8 NOTE 12. TAY MODEL OPERATING INSTRUCTIONS MAINTENANCE MANUAL ENGINE MANUAL INSTALLATION MANUAL 611-8 620-15 650-15 651-54 611-8C F-TAY-1RR F-TAY-2RR F-TAY-3RR F-TAY-5RR F-TAY-6RR M-TAY-1RR M-TAY-2RR M-TAY-3RR M-TAY-5RR M-TAY-6RR E-TAY-1RR E-TAY-2RR E-TAY-3RR E-TAY-5RR E-TAY-6RR EL2825 EL1716 EL2823 EL2834 O-TR0817/03 NOTE 13. The following emissions standards promulgated in 14 CFR part 34, Amendment 5, effective December 31, 2012 and 40 CFR part 87, effective July 18, 2012 have been complied with for the Tay 611-8C engine model. Fuel Venting Emission Standards: 14 CFR 34.10(a) and § 34.11; in addition, 40 CFR 87.10(a) and § 87.11. Smoke Number (SN) Emission Standards: 14 CFR 34.21(e)(2); in addition, 40 CFR 87.23(c)(1). Carbon Monoxide (CO) Emission Standards: 14 CFR 34.21(d)(1)(ii); in addition, 40 CFR 87.23(c)(1). Hydrocarbons (HC) Emission Standards: 14 CFR 34.21(d)(1)(i); in addition, 40 CFR 87.23(c)(1). Oxides of Nitrogen (NOx) Emission Standards: 14 CFR 34.23(a)(2); in addition, 40 CFR 87.23(c)(2). In addition to the FAA’s finding 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.d for NOx (also known as CAEP/6), and Part II Chapter 2 for fuel venting have also been demonstrated. NOTE 14. Limits regarding transient rotor shaft overspeed and transient gas temperature and number of occurrences are specified in the appropriate Rolls-Royce Maintenance Manual (See NOTE 12). NOTE 15. The engines are approved for use to the following ambient temperatures in Column 1 and 2 and are flat rated to the values in column 3 and 4. MAXIMUM AMBIENT FLAT TAKEOFF TAY MODEL oC oF oC oF 611-8 620-15 55 55 131 131 30 30 86 86 650-15 651-54 611-8C 55 50 52 131 122 131 30 30 30 86 86 86 NOTE 16. The maximum inlet throat area of the engines including aircraft air intake is limited to 1405 square inches for the TAY 611-8C and 1500 square inches for all other variants. NOTE 17. The maximum engine inlet distortion limit is specified in the appropriate Rolls-Royce Installation Manual (See NOTE 12). TCDS E25NE PAGE 9 NOTE 18. The limits quoted are relative to the engines equipped with one of the following thrust reverser types. TAY 611-8: Grumman Aerospace type 1159P41460-1 / -2 TAY 620-15: Grumman Aerospace type 1159P41530-1 / -2 / -9 /-10 and 1159RDP41530-51 / -52. TAY 650-15: Grumman Aerospace type 1159RDP41530-7 / -8 / -9 / -10. TAY 651-54: Dee Howard thrust reverser type TR6510 with the engine side mount configuration, and Dee Howard jet pipe P/N Qf 781.1000 for center engine mount configuration. TAY 611-8C: Nordam thrust reverser P/N 08ND78006-1 for left hand installation and P/N 08ND78006-2 for right hand installation. Approval for operation in reverse thrust does not imply approval of the thrust reversers themselves. NOTE 19. These engine models incorporate the following general characteristics: 610-8: Base Engine with Installation features to suit Gulfstream IV series aircraft. No longer in service. TAY 620-15: Same as 610-8, except takeoff and maximum continuous static thrust increase at sea level flat rated to 86°F ambient temperature. Installation features to suit Fokker 70 and Fokker 100 series aircraft. TAY 611-8: Same as 610-8, except takeoff static thrust increase at sea level flat rated to 86°F ambient temperature. Installation features to suit Gulfstream IV and IV-SP series aircraft. TAY 650-15: Same as 620-15, except with increased diameter fan, improved combustors, new high pressure turbine blades and vanes, and other minor hardware changes to accommodate higher thrust. Installation features to suit Fokker 100 series aircraft. TAY 651-54: Same as 650-15, except with installation features and gearbox to suit the Boeing 727-100 series aircraft and either a Dee Howard thrust reverser (side- mounted engines) or a Dee Howard jet pipe P/N Qf 781.1000 (center engine). TAY 611-8C: Same as 611-8, except with Fan system from TAY 650-15 and the introduction Of a FADEC control system. TCDS E25NE PAGE 10 NOTE 20. Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or, for approvals made before September 28, 2003 by Luftfahrt-Bundesamt (Germany) or CAA (UK). Any such documents including those approved under a delegated authority, are accepted by the FAA and are considered FAA approved, as appropriate. • Service bulletins, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. • Technical Variances These approvals pertain to the type design only ----END----