TCDS E-283

Page No. 1 2 3 4 Rev. No. 19 19 17 19 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E 283 TCDS: E 283 REVISION: 19 DATE: March 23, 2007 Rolls-Royce Duetschland Ltd & Co KG MODELS: DART 511 511-7E 514 514-7 Engines of models described herein conforming with this data sheet (which is a part of type certificate No. E 283) and 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 Deutschland Ltd & Co KG Postfach 1536 D-15827 Dahlewitz Germany (formerly, Rolls-Royce Limited Derby, England) Model Dart 511 511-7E 514, 514-7 Type Turboprop 2-stage centrifugal compressor - - - - 2-stage turbine - - - - 7 combustion chambers - - - - .086 reduction gearing - - - - Maximum continuous at sea level, equivalent shaft hp., shaft hp., jet thrust, r.p.m. 1677-1535-355-14500 - - - - Takeoff (5 min.) at sea level, equivalent shaft hp., shaft hp., jet thrust, r.p.m. 1677-1535-355-14500 (dry) 1716-1570-365-14500 (with W/A injection) - - - - - - 1824-1670-385-14500 (with W/A injection) Propeller shaft type SRAC Standard No. 4 - - - - Fuel control Lucas 36/29AC - - Lucas CCU.36/27AC Water/alcohol control R.K. 23194 - - R.K. 20833 Fuel See NOTE 6 - - - - Oil (4 gal. integral oil tank) Esso Aviation Turbo Oil 35 Esso Turbo Oil 35 Castrol 96 Aseroshell Turbine Oil 750 Texaco Synthetic Turbo Oil 35 Esso Extra Turbine Oil 274 - - - - Principal dimensions: Length, overall, in. 97.6 - - - - Diameter, in. 37.9 - - - - C.G. location: Aft of mounting feet, in. .6 - - 0 TCDS E-283 2 Model Dart (cont'd) 511 511-7E 514, 514-7 Weight (dry), lb. (includes all controls, exhaust unit, ignition system, torque-meter, thermocouples, oil tank, fuel pump and water injection unit) 1182 - - 1163 Ignition system Igniters Lodge LR.104, KLG KR.104 or Champion FHE-19-6H, AC YA-20 (Rolls-Royce P/N CR.104) with igniter boxes, Rotax N.B. 25/3, N.B. 34 or B.T.N. 063TS - - - - NOTES 1,2,3,4,5,6,7,8,9 1,2,3,4,5,6,7,8,9 1,2,3,4,5,7,8,9 "- -" indicates "same as preceding model" Certification basis CAR 10. Engine Type Certificate No. 283 issued June 13, 1955. Date of Application for Type Certificate April 20, 1955. Each individually imported engine and replacement parts must be accompanied by the pertinent Rolls-Royce Engine Inspection and Test Certificate and be clearly identified as imported. The Dart 506 and Dart 510 engine models, cancelled, December 9, 2002. The aviation authority for Germany, Luftfahrt-Bundesamt, originally type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E-283. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Germany. 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 E-283, 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 NOTE 1. Maximum permissible temperatures: Turbine gas temperatures: Actual operating exhaust gas temper atures will vary to meet environmental operating conditions in accordance with the approved manufacturer's instructions. 511 511-7E 514, 514-7 Takeoff (wet) 1103°F (595°C) - - 1112°F (600°C) Takeoff (dry) 1076° (580°C) 1076°F to 1157°F (580°C to 625°C) 1103°F (595°C) Maximum continuous 1076°F (580°C) 1076°F to 1157°F (580°C to 625°C) 1094°F to 1202°F (590° to 650°C) Maximum transient start 1184°F (640°C) - - Oil inlet temperature. +5°F to 230°F (-15°C to 110°C) - - NOTE 2. Fuel and oil pressure limits: Fuel supply pressure at engine fuel inlet, varying with flow per RR curve HK 23634, issue 3. Oil pressure, 15 to 30 p.s.i.g., minimum to complete flight 12 p.s.i.g. (p.s.i.g = pounds per sq. in. gage) NOTE 3. The engine ratings are based on standard conditions with no ai r bleed or accessory power drive, 60°F, 29.92 in.Hg., and Pw/Po = .01 at sea level with limiting exhaust gas temperatures. TCDS E 283 3 On dry air, T.O. power is increased by less than 1/2% and MC power by 1-1/3%. Jet thrust is converted to equivalent shaft hp by dividing the thrust value by a factor of 2.5. For 511, 511-7E, 514, 514-7 engi nes, the power output values are the minimum acceptance values and with the temperature limits are based on the use of Rolls-Royce RK. 13196 exhaust system. NOTE 4. Water/alcohol injection is optional and is utilized through automa tically varied flow to provide a constant level of power output for takeoffs. The w/a fluid should be a 63/37 mixture of water and methyl alcohol (Rolls-Royce AEP-1-W/M Issue 5) or equivalent. The water used is distilled, demineralized, or contains a maximum of 10.PPM solids, and the methyl alcohol is British D.Eng. R.D. 2481 or equivalent. The w/a flow for the 511 and 511-7E engines begins at temperatures over 60°F and increases to 582 gph (U.S. maximum). The maximum w/a flow for the 514 and 514-7 is 655 gph (U.S.). NOTE 5. Accessory provisions on engine: (Oil c ooler and air inlet are engine-mounted) Drive Rotation (facing drive) (C - clockwise) (CC - counter-clockwise) Speed Ratio to Turbine Continuous Torque* (in. -lb.) Static Torque** (in. -lb.) Maximum Overhang (in. -lb.) Power takeoff 120 hp. for 511, 511-7E 514 and 514-7 CC 345 1510 4960 185.0 Propeller governor 511 and 511-7E CU86E CC .195 138 1380 93.5 514 and 514-7 CU 98 CC .195 138 1380 93.5 Starter, Rotax C5102 or C5104 CC 2.000 272 1000 86.7 Fuel pump, Lucas CB222/3AU 511, 511-7E, 514, and 514-7 CC .195 85 780 34.0 *Continuous torque values are based on takeoff power at sea level. **Maximum torque of weak link without permanent set, or the clutch setting for the starter. NOTE 6. The mixing of approved fuels is permitted w ithout restriction. No adjustment of the engine controls is necessary and no loss of performance occurs. The following fuels are approved for these engines (Fuels shall conform to the specifications as listed or to subsequent revisions thereof): British D.Eng. R.D.2482 or 2494 Canadian 3-GP-23 f type 1 American A.S.T.M. D. 1655- 68 type A or A-1 I.A.T.A. Kerosene Type Fuel British D.Eng.R.D.2486 Canadian 3-GP-22 f type II American MIL-T-5624G Grade J.P.4 A.S.T.M. D.1655-68 type B I.A.T.A. Wide-cut Fuel NOTE 7. These engines meet FAA requirements for icing protection, ade quate turbine disc integrity and rotor blade containment and do not require external armoring. NOTE 8. Maximum permissible air bleed extraction for aircraft pur poses is 1.88% for engine models 511, 511-7E, 514 and 514-7. TCDS E-283 4 NOTE 9. Maximum overspeed limit is 17,000 r.p.m. for 20 sec. If this limit is exceeded the engine will be overhauled. Note 10. 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. • Service bulletins, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. • Techinical Variances These approvals pertain to the type design only. END