TCDS E-308

Page No. 1 2 3 Rev. No. 12 11 11 FEDERAL AVIATION AGENCY E-308 Revision 12 ROLLS-ROYCE Conway 505 508, 508A 509, 509A July 8, 2011 NOTE 13. 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. E-308 Engines of models described herein conforming with this data sheet (which is a part of engine type certificate No. E-308) and other approved data on file with the Federal Aviation Agency, meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets and applicable portions of the Civil Air Regulations provided they are installed, operated and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. Manufacturer Rolls-Royce Ltd. Derby, England Model Conway 505 508, 509 508A, 509A Type Turbojet (By-Pass) Axial Compressor Twin Spool 3 stage Turbine Turbo Annular Combustion with 10 Flame Tubes - - - - - - - - - - - - - - - - Ratings Max. cont. static thrust, and 14,625 lb . at 9600 14,625 lb. at 9675 14,625 lb. at 9650 r.p.m. at sea level hp. r.p.m. hp. r.p.m. hp. r.p.m. Takeoff static thrust and r.p.m. at sea level (5 min.) 16,500 lb. at 10060 hp. r.p.m. 17,500 lb. at 10127 hp. r.p.m. 18,000 lb. at 10140 hp. r.p.m. Max. with reverse thrust selected (1 min.) 9825 hp. r.p.m. 10127 hp. r. p.m. 10140 hp. r.p.m. Fuel control Lucas RTC 29/31 AP control - - - - - - - - Lucas MGTD 25/16 P pump - - (508) - - (508A) 26/17 P pump (509) - - (509A) Fuel See NOTE 11 - - - - - - - - Oil (29 U.S. pints integral tank) Esso Turbo Oil 15 Aviation Turbo Oil 35 Esso Turbo Oil 35 Aeroshell 300, Castrol 3C - - - - - - - - Principal dimensions Length (From front of nose to rear exhaust cone bullet) 134.210" - - - - - - - - Diameter (Max.) including auxiliaries Approx. 50" (see installation drawing) - - - - - - - - Weight (dry) - including fuel system, oil tank, anti-icing system, accessory drives igniters, igniter boxes and harnesses, Sundstrand oil system and fuel backing pump. 4690 lb. (Max.) - - - - - - - - Center of Gravity Aft of front suspension 15.1" - - - - - - - - Ignition system Igniters, Lodge 432/2 with Rotax boxes NB.38. - - - - - - - - NOTES 1,2,3,4,5,6,7,8,9,10,11 - - - - - - - - "- -" indicates "same as preceding model" E-308 2 Certification basis CAR Part 10, British Civil Airworthiness Requirements Section C equivalent to CAR Part 13 including Amendments 13-1 and 13-2. Type Certificate No. E-308 issued January 19, 1959; models 508 and 509 added September 1, 1959; 508A and 509A added July 12, 1963. Date of Application for Type Certificate: March 29, 1956. 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 E-308. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the UK. Import Requirements To be considered eligible for installa tion on U.S. registered aircraft, each new engine to be exported to the United States with UK CAA or EA SA airworthiness approval shall have a Joint Aviation Authorities (JAA) or EASA Form 1, Author ized 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 E-308, is in a condition for safe operation and has undergone a final operational check. NOTE 1. Maximum LP speed for takeoff, Max. Continuous cond itions and for reverse thrust, is 7335 LP r.p.m. (505, 508A, 509A) and 7356 LP r.p.m. (508, 509) NOTE 2. Maximum permissible temperatures: Turbine gas temperature (Mean of 6 thermocouples in exhaust cone): Takeoff 1247°F. (675°C.) Maximum continuous 1112°F. (600°C.) Max. transient in starting 1247°F. (675°C.) Max. with reverse thrust selected 1247°F. (675°C.) Oil inlet temperature -67°F. to +221°F. (-55 to +105°C.) NOTE 3. Fuel and oil pressure limits: Minimum fuel inlet pressure measured at inlet to engi ne main pump = 0 lb. p.s.i. for 5 minutes, and 7 p.s.i.g. unrestricted. Oil pressure normal 30-45 p.s.i. gauge (minimum in flight at 9650 HP r.p.m. = 28). NOTE 4. The ratings are based upon standard conditions with no ai r bleed or power takeoff, 60°F. and 29.92" hg. barometer, pw/po = .01, and with turbine gas temperature within limits. Engine to be fitted with straight jet pipe Part No. DES.51690, Issue 3, and 25.75" diameter final nozzle R-R Part No. CU.26100 and test bed intake flare J.59408, and using fuel of calorific volume 18,550 BThU/lb. The thrust values quoted are minimum. Thrust reverser unit Conway T.R. 501 for Conway 505, 508 and 508A NOTE 5. The following accessory drive provisions are incorporated: Drive Rotation Speed Ratio to turbine Cont. Torque Inst. Torque Maximum Overhang Starter CW .72 x H.P. 615 lb. ft. 1230 lb. ft. 470 lb. in. H.P. Tacho CC .423 x H.P. 7 lb. in. 50 lb. in. Negligible L.P. Tacho CW .6066 x L.P. 7 lb. in. 50 lb. in. Negligible Sundstrand CW .683 x H.P. 1000 lb. in. 4400 lb. in. Not overhung (Stressed to 625 lb. in.) Hydraulic pump CC .352 x H.P. 1000 lb. in. 4400 lb. in. 104 lb. in. NOTE 6. These engines meet FAA requirement s for vibration, icing protection, for adequate turbine disc integrity, for rotor blade containment and do no require external armoring. NOTE 7. Under all conditions compressor bleed air may be used for aircraft and engine services up to the maximum delivery permitted by the engine air bleed ports, provided that the r.p.m. or turbine gas temperature operating limitations are not exceeded. NOTE 8. The maximum allowable thrust for below standard inlet air temperatures and/or ram conditions is 20,000 lb. for five minutes at takeoff conditions. 3 E-308 NOTE 9. Maximum permissible overspeed limit for the engine rotors are as follows: Low Pressure Compressor - 7560 r.p. m. for 20 seconds (505, 508A, 509A), 7576 r.p.m. for 20 seconds (508, 509) High Pressure Compressor - 10,500 r.p.m. for 20 seconds If these limits are exceeded, the engine shall be overhauled. NOTE 10. For aircraft using percentage type tachomet ers, the following conversion factors shall be used: L.P. - 9938 H.P. r.p.m. = 100% L.P. - 6924 L.P. r.p.m. = 100% NOTE 11. The following fuels are eligible for these engines: Aviation Kerosene Specifications British D Eng. R.D. 2482 or 2494 Canadian 3-GP-23C Type 1 American A.S.T.M. D.1655-59T Type A or Type A-1 I.A.T.A. Kerosene Type Fuel Aviation Wide-cut Specifications British D Eng. R.D. 2486 Canadian 3-GP-22C Type 11 American MIL-J-5624F Grade JP4 A.S.T.M.D. 1655-59T Type B I.A.T.A. Wide-cut fuel. Fuels conforming to the approved specifications and late r revisions may be used separately or mixed in any proportions without adversely affecting the engine operation or power output. No fuel control adjustment is required when changing fuel types. NOTE 12 Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or, for approvals made before Sept ember 28, 2003 by the United Kingdom Civil Aviation Authority. Any such documents including those approved under a delegated aut hority, 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.....