TCDS E-299

Page No. 1 2 3 4 5 Rev.No. 6 5 5 6 6 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E-299 Revision 6 ALVIS LIMITED Leonides 502/5A, 6A, 7A, 8 503/5A, 6A, 7A, 8 504/5A, 6A, 7A, 8 514/5A, 5, 6A, 6 7A, 7, 8A, 8 531/8, 8B March 26, 2007 TYPE CERTIFICATE DATA SHEET NO. E-299 Engines of models described herein conforming with this data sheet (which is part of type certificate No. 299) and other approval 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 Civil Air Regulations provided they are installed, operated and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. Manufacturer Alvis Limited Holyhead Road Coventry CV5 8JH England Model Leonides 504/5A, 504/6A 504/7A, 504/8 503/5A, 503/6A 503/7A, 503/8 502/5A, 502/6A 502/7A, 502/8 Type 9RA Reduction Gears 0.625:1 (5A) - - (6A) - - (7A) 0.5:1 (8) 0.625:1 (5A) - - (6A) - - (7A) 0.5:1 (8) 0.625:1 (5A) - - (6A) - - (7A) 0.5:1 (8) Rating Max. continuous, hp, r.p.m., boost psi, at rated press. alt 490-2900-+6.0-3750 460-2900-+4.5-6000 440-2900-+3.5-7250 (ft.) sea level press. alt. 475-2900-+6 .0-S.L. 435-2900-+4.5-S.L. 410-2900-+3.5-S.L. Takeoff (5 min.), hp, r.p.m., boost psi, at rated press. alt. 545-3000-+8.0-1750 - - - - (ft.) sea level press. alt. 540-3000-+8.0-S.L. - - - - Fuel (minimum grade aviation gasoline) 100/130 - - - - "- -" indicates "same as preceding model." "⎯" indicate "does not apply." TCDS E-299 2 Model Leonides 504/5A, 504/6A 504/7A, 504/8 503/5A, 503/6A 503/7A, 503/8 502/5A, 502/6A 502/7A,502/8 Lubricating Oil D. Eng. R.D. 2472B/2 Aeroshell W80, W100, W120 BP Aero 120 HD, Esso E100 - - - - Bore and stroke, in. 4.80 x 4.41 - - - - Supercharger ratio 6.5:1 - - - - Displacement, cu.in. 718.6 - - - - Compression ratio 6.5:1 - - - - Weight (dry), lb. 830 ± 1¼% (5A) 835 ± 1¼% (6A) 835 ± 1¼% (7A) 815 ± 1¼% (8) - - - - - - - - - - - - - - - - C.J. Location (basic engine) 2.2" behind C/L of cyls. - - - - Propeller Shaft No: 3 S.B.A.C. - - - - Fuel Injection Hobson Type 269A (5A) Hobson Mk. 144A (6A) Hobson Mk. 153A (7A) Hobson Mk. 153 (8) - - - - - - - - - - - - - - - - Ignition, Dual Magneto B.T-H. C9.B/2 - - - - Timing. °BTC Rt. 40° Left 36° - - - - Spark Plugs Lodge LA2, LA2/1 KLG. KA2, KA3 - - - - Oil sump capacity, qt Dry Sump - - - - NOTES 1, 2, 3, 4, - - - - Model Leonides 514/5, 514/5A, 514/6 514/6A, 514/7,514/7A 514/8, 514/8A 531/8 531/8B Type 9RA Reduction Gears 0.625:1 - - - - - - - - - - 0.5:1 - - (5) (5A) (6) (6A) (7) (7A) (8) (8A) 0.5:1 0.5:1 "- -" indicates "same as preceding model." "⎯" indicate "does not apply." TCDS E-299 3 Model Leonides 514/5, 514/5A, 514/6 514/6A, 514/7,514/7A 514/8, 514/8A 531/8 531/8B Rating Max. continuous, hp, r.p.m., boost psi, at rated press. alt 495-2900-+6.0-3750 590-3000-+6.5-2750 585-3000-+6.5-2750 (ft.) sea level press. alt. 480-2900-+6 .0-S.L. 575-3000-+6.5-S.L. 570-3000-+6.5-S.L. Takeoff (5 min.), hp, r.p.m., boost psi, at rated press. alt. 560-3000-+8.0-1750 650-3200-+8.0-2000 635-3200-+8.0-2000 (ft.) sea level press. alt. 550-3000-+8 .0-S.L. 640-3200-+8.0-S.L. 625-3200-+8.0-S.L. Fuel (minimum grade aviation gasoline) 100/130 - - - - Lubricating Oil D. Eng.R.D. 2472B/2 Aeroshell W80, W100, W120 BP Aero 120HD, Esso E100 Bore and stroke, in. 4.80 X 4.41 4.80 X 4.80 - - Supercharger ratio 6.5:1 - - - - Displacement, cu.in. 718.6 783 - - Compression ratio 6.5:1 - - - - Weight (dry), lb. 830 ± 1¼% (5 & 5A) 835 ± 1¼% (6 & 6A) 835 ± 1¼% (7 & 7A) 835 ± 1¼% (8 & 8A) 860 ± 1¼% 865 ± 1¼% C.G. Location (basic engine) 2.2" behind C/L of cyls.- 1.60 - - Propeller Shaft No: 3 S.B.A.C. - - - - Fuel Injection Hobson AL.16 (8) Hobson AL. 17. (8A) Hobson Type 382 Mk. 1 Hobson Type 382 Mk. 1A. Ignition, Dual Magneto B.T-H. C9.B/2 - - - - Timing. °BTC Rt. 40° Left 36° Rt. 33° Left 33° - - Spark Plugs Lodge LA2, LA2/1 KLG. KA2 & KA3 - - - - Oil sump capacity, qt Dry sump - - - - NOTES 1, 2, 3, 4 - - - - "- -" indicates "same as preceding model." "⎯" indicate "does not apply." TCDS E-299 4 Certification Basis CAR 10. Type Certificate No. 299, issued March 21, 1958; Models 514/8 and 514/8A added June 23, 1969; Model 531/8 and 531/8B added October 3, 1960; Models 504/5A, 504/6A, 504/7A, 503/5A 503/6A, 503/7A, 502/5A, 502/6A, and 502/7A added February 4, 1963; Models 514/5, 514/5A, 514/6, 514/6A, 514/7, 514/7A, added March 4, 1976. Date of Application for Type Certificate: August 22, 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-299. 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 eligib le for installation on U.S. registered airc raft, each new engine to be exported to the United States with UK CAA or EASA airworthin ess 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 E-299, is in a condition for safe operation and has undergone a final operational check. NOTE 1. The ratings of 502, 503, and 504 e ngines are based on standard conditions of temperature and barometric pressure 59°F and 29.92 in.Hg. at sea level and .012 absolute humidity. (.57 in.Hg. vapor pressure). If corrected to dry standard air conditions the maximum continuous powers at sea level would be increased by approximately 3.5% and 2.0%, respectively. The power output of different engines is based on a possible variation of ± 4% in accordance with British standards. NOTE 2. All but 531/8 and 531/8B 531/8 and 531/8B Maximum permissible temperature, °F Cylinder head, thimble type thermocouple 445 482 455 with Aeroshell W80 Oil inlet 212 212 194 with Aeroshell W80 NOTE 3. Fuel pressure limits, p.s.i. min. 25 max. 29 Oil pressure limits, p.s.i. (at maximum continuous conditions) 70/80 75/85 (models 531/b and 531/8B) NOTE 4. The following accessory drive or mounting provisions are available: Original Direction Speed Ratio Maxi mum Torque (in.-lb.) Max. Overhang Accessory or Rotation to Crankshaft Continuous Static Moment (in.-lb.) C.S.U. C .848:1 *51 **665 37.7 35 (5, 6, 7, 5A, 6A, 7A) Tachometer C 1:1 1.9 500 2.7 Generator CC 2:1 112.8 1,320 322 Fuel Injector CC .889:1 23 240 44.8 Vacuum Pump CC 1:1 16.8 240 16.8 Hydraulic Pump CC .831:1 121 240 16.1 Air Compressor C .416:1 69.2 240 6.2 Electric Starter C 1:1 4,800+ 5,400 73.4 Cartridge Starter C 1:1 8,400+ 51.6 "C" - clockwise viewing accessory drive face. "CC" - counterclockwise. * - continuous torque values base d on take-off r.p.m. at sea level. ** - maximum torque of weak link without pe rmanent set, or clutch setting of starter. + - maximum starter torque. TCDS E-299 5 NOTE 5 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. 1 • Service bulletins, 2 • Structural repair manuals, 3 • Vendor manuals, 4 • Aircraft flight manuals, and 5 • Overhaul and maintenance manuals. 6 7 • Technical Variances These approvals pertain to the type design only. ....END....