TCDS E20EU

Page No. 1 2 3 4 Rev. No. 4 4 4 4 Revised 12/94 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E20EU Revision 4 ROLLS-ROYCE Ltd., Aero Division-Bristol/ S.N.E.C.M.A. Olympus 593 Mk. 610-14-28 January 15, 1981 TYPE CERTIFICATE DATA SHEET NO. E20EU Engines and models described herein conforming with this data sheet (which is part of Type Certificate No. E20EU), and other approved data on file with the Federal Aviation Administration (FAA), meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of the FAA regulations provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approval instructions. Type Certificate Holder Rolls-Royce Limited, Aero Division-Bristol P.O. Box 3, Filton, Bristol, England S.N.E.C.M.A. 2 Bd. Victor, Paris 75015, France Model Olympus 593 Mk. 610-14-28 Type Turbojet - 2 spool turbojet (type 610) with exhaust assembly incorporating primary nozzle with reheat (type 14) and secondary nozzle reverser (type 28). 7 stage low pressure compressor driven by a single stage axial turbine. 7 stage high pressure compressor driven by a single stage axial turbine. Annular combustion system incorporating vaporizers. Rating Static thrust at sea level, lb. I.S.A. I.S.A. + 15°C Without Reheat Maximum Continuous 28,800 27,190 Takeoff (5 min.) 31,350 29,920 With Reheat Takeoff (5 min.) 37,080 35,220 Max. Contingency (2.5 min.) 38,130 36,650 (See NOTE 7B) Intermediate Contingency 32,800 30,760 (15 min.) Transonic (15 min.) 32,800 30,760 Approved Types (See NOTE 7) Fuel Components Fuel Control Units Lucas Aerospace Ltd. Type FCU117 or 117M Reheat Fuel Controller SNECMA Type 301.244/014/015/016/017/019 Fuel Pump - 1st Stage Lucas Aerospace Ltd. FSP117 or FSP117M - 2nd Stage Lucas Aerospace Ltd. SSP105 or SSP105M or SSP106 or SSP106M. Starter Pump Lucas Aerospace Ltd. ESP102 or ESP102M L.P. Governor Overspeed Amplifier Lucas Aerospace Ltd. LSG 103/3/E Engine Control Amplifier Ultra Electronics Ltd. A6A16/24CA, A6A16/24CC, and A6A16/24DC. Reheat Control Amplifier Blecma 620-357-017, -018, -081, -082. Reheat Flame Detector SNECMA 525-700-562, -745. E20EU 2 Model (cont'd) Olympus 593 Mk. 610-14-28 Oil Approved Types (See NOTE 7) Mobil RM.193A-3; Snell ASTO 555; Esso ETO 25; B.P. Energet 523. Total Capacity 26 (U.S. Quarts) Integral Oil Tank, Max. 16 Capacity (U.S. Quarts) Usable oil (U.S. Quarts) Min. 12.5 Principal Dimensions, Inches Length (Flange to Flange) 148.4 (3.77m) Diameter (At Intake Flange) 47.8 (1.220m) Weight (dry) Pounds Dry weight of flange engine with all required equipment including air starter but excluding reheat components and no residual fuel or oil. 6510 Weight of optional external equipment - fuel flowmeter. 5 Estimated weight of residual fuel & oil 39 Center of Gravity (dry) Inches Forward of main engine mounting trunnion center line. 13.4 Below engine horizontal center line 2.0 Ignition Ignition Unit Lucas Aerospace Ltd. NB 10705 Igniters (2) Champion Sparking Plug Co. Ltd. CBS 112-3 & 112-4 Certification Basis FAR 21.29 and FAR 33 effective February 1, 1965, as amended by Amendment 33-1 through 33-3, plus Special Conditions No. 33-40-EU-10 and Amendment No. 1 thereto, dated December 6, 1974. Type Certificate No. E20EU issued March 17, 1978. Effective date of application for type certification: January 19, 1967. Pursuant to FAR 21.29(a)(ii) type certificate was issued in validation of the Anglo/French certification of compliance with Special Conditions No. 33-40-EU-10 including Amendment No. 1; and Anglo/French TSS Standards which were found to provide a level of safety equivalent to the above FAR 33 regulations as follows: The Anglo/French Supersonic Transport TSS Standards as defined in Contents List No. 29, dated March 26, 1976, Part 0, Number 0-0, 0-1, and Appendix; Part 6 Number 6-5, 6-6, 6-8, 6-9, and Appendices to each and 6-7. Import Requirements Each individually imported engine unit must be accompanied by a Rolls-Royce Limited, Aero Division-Bristol/Societe Nationale d'Etudes et de Construction de Moteurs d'Aviation, CAA or Bureau Veritas approved "Inspection and Test Certificate" signed by a person authorized by CAA or B.V. as appropriate and containing the following statement: "The engine unit covered by this certificate conforms to the type certificate and is in condition for safe operation, and has been subjected by the manufacturer to a final operational check". Additional Requirements SFAR 27 as amended by Amendments 1 and 2 thereto. 3 E20EU NOTE 1. Rotor Speed Limitations N1 % N2% Takeoff (5 min.), with or without reheat 102.0 105.7 Maximum Continuous 102.0 105.3 Maximum Contingency (2.5 min.) 102.0 106.8 Intermediate Contingency and Transonic (15 min.) 102.0 105.1 Maximum for Reverser Ground (45 sec.) - - 98.0 in flight (4 min.) As obtained at reverse idle Maximum Overspeed (20 sec.) 108.5 110.0 Minimum Ground Idle - - 60.0 (100% N1 = 6,500 rpm; 100% N2 = 8,530 rpm) NOTE 2. Temperature Limitations (°C) Maximum Exhaust Gas Takeoff (5 min.) with or without reheat 806 Maximum Continuous 739 Maximum Contingency (2.5 min.) 833 Intermediate Contingency and Transonic Acceleration (15 min.) 755 Momentary during Starts and Relight (2 sec.) 550 Oil Temperature at Pressure Pump Inlet Maximum during Takeoff 125 Maximum Continuous 190 Maximum Transient (5 min.) 195 Minimum for Starting -35 Minimum for Motoring Cycle -40 Minimum for Opening Up -20 Fuel Temperature at Burner Manifold Inlet (See NOTE 7B Minimum for Starting and Relighting -40 Minimum for Opening Up 20 Maximum for Maximum Continuous 150 Maximum Transient (2 min.) 170 NOTE 3. Fuel and Oil Pressure Limits p.s.i. Fuel - Minimum at Engine Inlet (See NOTE 7B) 12.5 absolute Fuel Filter Differential - Maximum 7 Oil - Differential relative to Intermediate Without Mod. With Mod. Casing Oil Space 8562 installed 8562 installed Normal Range 18 to 30 10 to 20 Minimum for Flight at Ground Idle 18 10 Minimum to Complete Flight 13 5 NOTE 4. The ratings are based on static test stand operation under the following conditions: - Compressor inlet air at 59°F and 29.92"Hg. No aircraft accessory loads or optional air extraction. Intake venturi to Rolls-Royce drawing No. RL83649. Variable primary nozzle assembly type 14 installed but secondary nozzle not installed. Exhaust gas temperature measured by 8 thermocouples as defined in D.I.S. 843, issue 7, or subsequent approved issues. Static ratings corrected in accordance with RT.1040. E20EU 4 NOTE 5. Accessory drive provisions: Speed Ratio Torque Overhang to HP (in. -lb.) Moment Drive *Rotation Turbine Shaft Cont. Static (in. -lb) Starter cc .805:1 7800(stall) 22700 (shear neck) 216 I.D.G. c .805:1 1547 8905 203 Hydraulic Pump (Main) cc .4355:1 1690 3617 127 Hydraulic Pump (Standby) c .4355:1 900 2179 82 First Stage Fuel Pump cc 1.414:1 425 2751 141 Fuel Control c .526:1 40 230 349 Unit with Second Stage Pump (air driven) c *Clockwise (c) or counterclockwise (cc) looking on the drive face of the accessory. NOTE 6. Maximum permissible air bleed extraction: Maximum RPM for air bleed extraction - unrestricted. Max Bleed for Eng. Air Mass % Total No-Bleed & Airplane Services Flow Lb/Sec. Mass Flow Cabin Conditioning - Normal Max. 1.2 - - Emergency Max. 2.4 - - Engine Anti-icing, Max. - - 0.52 Fuel Heating (below 5°C fuel temp) Max. - - 0.52 NOTE 7. A. Approved fuels & fuel additives, approved lubricating oils and limitations appropriate to each are listed in Technical Publication No. TP.178/B.E.D., Olympus 593 Mk. 610-14-28 Operating Instructions, Ch. 2 and Appendix 3, dated May 28, 1975 or later approved revision. B. For wide-cut type (AVTAG JP.4) or mixture of wide-cut and Kerosene type (AVTUR JP.1) fuels the following limitations apply: 1. Minimum fuel inlet pressure - 20 psia. 2. Maximum fuel temperature 50°C. Refer to Engine Operating Instructions for techniques to avoid exceeding this limit. 3. Use of Maximum Contingency Power is prohibited. NOTE 8. Life limited parts are identified in Chapter 5 of the Olympus 593 Mk. 610-14-28 Engine Maintenance Manual, TP 181/1/R/SN. NOTE 9. Olympus 593 Mk. 610-14-28 manuals approved by the Anglo/French Authorities accepted as equivalent to FAR 33.5 requirements are as follows: - Operating Instructions TP.178/B.E.D. - Maintenance Manual TP.181/1/RR/SN - Installation Manual See NOTE 10. - Overhaul Manual TP.187/1/RR/SN and TP.187/1/RR/SN NOTE 10. The Olympus 593 Mk. 610-14-28 is limited to installation on the French/British Concorde airplane. NOTE 11. This engine approval includes the engine unit, primary and secondary nozzle with reverser as defined on RR DIS 843, issue 1, or later, for the Mk 610-14-28 as approved by the CAA. .....END.....