TCDS E9EU

Page No. 1 2 3 Rev. No. 2 1 1 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E9EU Rolls-Royce ORPHEUS 810D Rev. 2 July 8, 2011 NOTE 16. This type certificate is cancelled effective July 8, 2011 and is not valid for aircraft manufactured after this date. This cancellation also invalidates, and precludes issuance of, any U.S. Certificates of Airworthiness. TYPE CERTIFICATE DATA SHEET NO. E9EU Engines of models described herein conforming with this specification and approved data on file with the Federal Aviation Administration are rated as airworthy for use in certificated aircraft in accordance with pertinent aircraft specifications 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 Holder Rolls-Royce, Limited Bristol, England Model Bristol Orpheus Mark 810D Type Turbo-jet Seven stage axial compressor, can-annular combustion system with seven separate flame tubes, single stage turbine. Rating (Static thrust at sea level, lb.) (See Note 5.) Takeoff 4850 Maximum continuous 4130 Fuel controls Fuel pump Lucas type SCH.51754 Combined control unit Lucas type SCH.51755 Air fuel ratio control Lucas type SCH.50458 Hunter (sprayer) Lucas type SCH. 76 Fuel See Note 8. Oil capacity Oil tank capacity total 23 Imp. pints (27.7 U.S. pints) "Full" 20.8 Imp. pi nts (25.0 U.S. pints) usable capacity 16.5 Imp. pints (19.8 U.S. pints) Oil Castrol 98 Esso Turbo Oil 35 ENCO.35 Esso Extra Turbo Oil 274 ENCO.Extra 274 Aeroshell Turbine Oil 750 Principal Dimensions, ins. Le ngth (air intake to exhaust cone flange) 93.47 (overall) 100.52 Height 36.95 Width 32.4 Weight (dry) lb. Basic engine - including ignition 975 lb. units, igniters and anti-icing control valve, but not including starter generator, hydraulic pump, tachometer generator and jet pipe. E9EU 2 Center of Gravity, ins. Forward of mounting trunnion centre line 0.5 (± 0.25) Ignition (High Energy System) Tw o Igniters, Smiths/K.L.G. type RH.375/1. Two H.E. Ignition Units, Rotax/B.T.H. type C28TS Certification basis FAR 21.29 FAR 33 effective February 1, 1965, including amendments 33-1 through 33-3 and exemption No. 959, issued March 13, 1969. Date of Application for Type Certificate: April 30, 1969 Type Certificate No E9EU issued: June 16, 1969. The aviation authority for the United Kingdom, the UK Civil Aviation Authority (CAA), originally type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E9EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the UK. Special Numbers Eligible OR130001, OR130002, OR130003, and OR130004, in accordance with exemption No. 959, issued March 13, 1969. Import Requirements To be considered eligible for installation on U.S. registered aircraft, each new engine to be exported to the United States with UK CAA or EASA airw orthiness approval shall have a Joint Aviation Authorities (JAA) or EASA Form 1, Authorized Re lease Certificate. The JAA or EASA Form 1 should state that the engine conforms to the ty pe design approved under the U.S. Type Certificate E9EU, is in a condition for safe operation and has undergone a final operational check. NOTE 1. Maximum permissible engi ne operating rotor speeds are: Takeoff, RPM 10,000 (100.5%) (5 min. limit) Maximum continuous, RPM 9,500 (95.5%) Momentary overspeed, RPM 10,300 (103.5%) (20 sec. limit) NOTE 2. Maximum permissible temperatures are: Jet pipe temperatures (Measured mean of 4 thermocouples located in the jet pipe in a plane 29" downstream of the exha ust cone rear flange) Takeoff 725°C (5 min. limit) Maximum continuous 640°C Ground idling 675°C (15 min. limit) 640°C (Unlimited) Starting 800°C Oil inlet temperature 115°C Fuel inlet temperature 50°C NOTE 3. Fuel and oil pressure limits: Fuel pressure: Maximum inlet pressure 40 psi Minimum inlet pressure 5 psi (warning switch not fitted) Oil pressure: Maximum 65 psi Normal 45-60 psi (95.5% RPM) Minimum 25 psi NOTE 4. Maximum permissibl e air bleed extraction: Bleed for engine deicing and aircraft services (compressor delivery casing): Range of RPM at which bleed may be used - unlimited Maximum air delivery (1% of no bleed mass flow) - 2% 3 E9EU NOTE 5. The ratings are based on static test stand operation under the following conditions: International Standard Atmo spheric Conditions at Sea Level All optional air bleeds closed Aircraft service accessory drives unloaded Test bed venturi intake to RR/BED drawing XP.5007/8/9/10 Test bed 20" diameter straight jet pipe having nozzle suitability trimmed Jet pipe temperature measured by 4 thermocouples 100.5% indicated speed corresponding to 10,000 RPM NOTE 6. These engines meet FAA require ments for operation in icing conditions. NOTE 7. The following accessory drive provisions are incorporated: * Speed Ratio to Turbine Torque (in. lb.) Overhang Drive Rotation Shaft Continuous Static (in. lb.) Starter/generator A.C. 0.871/1 550 6050 750 Hydraulic pump C. 0.397/1 270 2600 100 Generator (tachometer) C. 0.422/1 (Drive Shear 35/40) 3 *Clockwise or anti-clockwise looki ng on the drive face of the accessory. NOTE 8. The following fuels are eligible for this engine: Aviation Turbine Fuel Specifications: British D. Eng. R.D. 2494 or 2453 American ASTM.D.1655-66T. Jet A-1 British D. Eng. R.D. 2486 or 2454 or 2498 American ASTM.D.1655-66T. Jet B MIL-J-5624G. Grades JP.4 and JP.5 NOTE 9. This engine has not been dem onstrated to comply with FAA requirements for rotor disc integrity, blade containment, and bird and hail ingestion. NOTE 10. Service life limited parts are shown in A RB approved Rolls-Royce Document PFG/JPLG/79603 with interpretation of cyclic life as defined in ARB letter reference BTL/ORP of March 7, 1969. NOTE 11. Engines shall continue to be overhauled peri odically by the Bristol Engine Division of Rolls-Royce in accordance with the Maintena nce program that has been utilized for the engines since 1957. NOTE 12. The only optional additives that may be used in approval fuels are as follows: 1. Anti-icing additives to Specification D. Eng. R.D. 2451 or MIL-I-27686D (including Phillips Anti-icing Additive PFA 55 MB, type 99.6/0. 4) may be used in concentrations not exceeding 0.15% by volume in approved kerosene or wide cut fuels. 2. Anti-static additive Shell ASA.3 may be used in approved kerosene or wide cut fuels in concentration not exceeding 0.75 grammes per cubic metre in kerosene or 0.60 grammes per cubic metre in wide cut fuels. NOTE 13. These engines are approved only for insta llation on the Lockheed Jetstar Model 329 airplane serial no. 1001 when that aircraft is certificat ed under Exemption No. 909, issued December 9, 1968. E9EU 4 NOTE 14. Manuals Operating Instructions and Maintenance - Orpheus 803 Engine Operating and Servicing Instructions T.O. 2J-J80302-2 endorsed by Special Notice ref: TP.134/B.E.D. relating to Orpheus 810D applicability. Overhaul - Orpheus 803 Engine Overhaul Instructions R.O. 2J-J80302-3 Orpheus Component Salvage Manual Orpheus Repair Notes Orpheus Test Manual - Section 3, Note 50, Issue 2, and Section 5, Note 10, Issue 3. Performance - Orpheus 810 Engine Performance Brochure TC 344. Parts List - Orpheus 810D, Schedule D.I.S. B.181480. NOTE 15. Each of the documents lis ted below must state that it is approved by the European Aviation Safety Agency (EASA) or, for approvals made before September 28, 2003 by the United Kingdom Civil Aviation Authority. Any such documents including those approved under a delegated authority, are accepted by the FAA and are considered FAA approved. • 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.....