TCDS E-311

Page No. 1 2 3 4 Rev. No. 10 11 10 11 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" INDICATES "DOES NOT APPLY" NOTICE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E-311 Revision 11 ROLLS-ROYCE Tyne 506 512 515 March 23, 2007 TYPE CERTIFICATE DATA SHEET NO. E-311 Engines of models described herein conforming with this data sheet (which is a part of engine type certificate No. 311) 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. Type Certificate Holder Rolls-Royce Limited Derby, England Model Tyne 506 512 515 Type Turboprop Two Spool Axial Compressor -- -- 4-stage turbine Turbo Annular combustion chamber with 10 flame tubes .064 to 1 reduction gear Ratings Max. continuous, at sea level, equivalent shaft hp 4207 4684 5061 Actual shaft hp., 3835 4270 4685 Jet Thrust 930 1035 940 LP rpm (Max.) 13500 14100 14500 HP rpm (Max) 17900 17900 17950 Takeoff (5 min.) at sea 4804 5344 5521 level, equivalent shaft hp Actual shaft hp 4320 4850 5095 Jet Thrust 1210 1235 1065 LP r.p.m. (Max.) 15250 15250 15250 HP r.p.m. (Max) 18150 18150 18150 Max. reverse pitch; braking (1 min.) 13250 LP r.p.m., -- -- maneuvering (5 min.) 16600 HP r.p.m. -- -- Propeller shaft type SBAC No. 6 Fuel control Lucas BCU. 100 Lucas Sch. 6623 Lucas Sch. 5199 with Lucas Pump MGBB, 101 Fuel See Note 10 -- -- Oil Capacity 57.6 U.S. pints integral oil tank -- -- Oil Type See relevant RR Operating Instruction Manual Castrol 98 or Aeroshell Turbine oil 750 or Texaco Synthetic Turbine Oil 35 TCDS E-311 2 Model Tyne 506 512 515 Principal dimensions: Length, overall, in. 108.74 -- -- Diameter (see Installation Dwg.), in. Approx. 3.5 -- -- C.G. location: Aft of propeller curve fitting line, in. 41.0 -- -- Weight (dry), lb. (includes all controls, exhaust unit, igniter plugs, thermocouples, oil tank and fuel pump & control unit) 2248 2285 2193 Ignition system -- -- High energy type with two Rotax NB38 or BTH.C34TS/1 boxes and igniters LODGE LR 109 or 109/1 "- -" Indicates "same as preceding model" "—" Indicates "does not apply" Certification basis CAR 10. Type Certificate No. 311 issued March 8, 1960. Date of Application for Type Certificate October 17, 1959. Each individually imported engine must be accompanied by a Rolls-Royce Limited/ARB approved "Inspection and Test Certificate" signed by a person authorized by the Air Registration Board. The United Kingdom Civil Aviation Authority originally type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E-311. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of UK. Import Requirements: To be considered eligible for installation on U.S. registered aircraft, each new engine to be exported to the United States with Civil Aviation Authority of United Kingdom 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-311, is in a condition for safe operation and has undergone a final operational check. NOTE 1. Maximum permissible temperatures: Turbine gas temperatures (at inlet to 2nd stage turbine) 506 512 515 Takeoff 1175°F (635°C)* 1229°F (665°C)* 1229°F (665°C)* Maximum continuous 1139°F (615°C)* 1184°F (640°C)* 1199°F (645°C)* Maximum transient not to exceed 5 seconds 1328°F (720° C) 1337°F (725°C) 1337°F (725°C) Maximum in reverse pitch 1139°F (615°C) 1148°F (620°C) 1148°F (620°C) * If the Rolls Royce recommended procedure of fuel trimmer control is used for take-off, climb and cruise, these temperature limits are applicable to sea level only. Above sea level the lim its increase by 4-1/2°F (2-1/2°C) per 1000 ft. altitude. Oil inlet temperatures: Unrestricted 15 Minute Limit With Castrol 98 or Aeroshell 750: +5°F to 221°F(-15°C to 105°C) +5°F to 230°F(-15°C to 110°C) With any other approved oil: +5°F to 212°F(-15°C to 100°C) +5°F to 221°F(-15°C to 105°C) TCDS E-311 3 NOTE 2. Fuel and oil pressure limits: Fuel supply pressure at engine fuel inlet, varying with flow per R-R curve H.K.23909 Issue 5 - Max. Fuel Temp. 176°F (80°C). Oil pressure, varies inversely with oil temperature, normal, 40 to 65 p.s.i.g. with 38 p.s.i.g. min. in flight. (p.s.i.g. = pounds per sq. in. gauge) NOTE 3. The engine ratings are based on standard conditions with no air bleed or aircraft accessory power extraction 59°F and 14.7 p.s.i. (29.92" Hg.), and pw/Po=.01 at sea level with gas temperatures within limits. On dry air the change in power is negligible. Jet thrust is converted to equivalent shaft hp. by dividing the thrust value by a factor of 2.5. Thrust output values are the minimum acceptable and are based on the use of Rolls-Royce exhaust cone J.65340 or 73422 and Nozzle J.64341 (506 and 512) or J.64383 (515) with 18 or 20 thermocouples located in the intermediate turbine guide vanes. NOTE 4. Accessory provisions on engines (Air inlet is engine-mounted) Continuous Static Maximum Speed Ratio Torque** Torque*** Overhang Drive Rotation* to Turbine (in. -lb.) (in. -lb.) (in. -lb.) Power takeoff CC .4898 LP 2725 10400-13600 _______ P.C.U. De Havilland CC .174 LP 660 at takeoff 1020 450.00 Type PAY 85002, 85200, 85400 377 at cruise Starter: ) C12503 (506) .621 HP at 414 (for 1 min.) 1800 max. 420.00 Electric) C 12505 (506 & 512) C engine pad 492 (for 1 min.) 270.00 Air CT.1006/1(515) (Not applicable with Air 41.86 Starter) Tachometer HP) C .249 HP Negligible 174 2.25 Direct Bdg. LP) CC .250 LP Negligible 174 2.25 HP) CC .238 HP) Conforms to AND 20005 % reading XV B. LP) CC .275 LP) Fuel Pump CC .2598 HP 87.3 (506) 500 79.25 Lucas MCRS 101 92.5 (512 & 515) Backing Pump Plessey BP34 C .181 HP 5.18 190 10.75 * "C" - Clockwise, "CC" - counter clockwise, facing engine drive. ** 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 tarter.. NOTE 5. Both JP-1 and JP-4 type fuels are acceptable but whenever a change is made between these type of fuels, readjustment of the fuel control must be made. NOTE 6. These engines meet FAA requirements for icing protection, for adequate turbine disc integrity, for rotor blade containment, and do not require external armoring. NOTE 7. Propellers used with this engine must have functioning characteristics which are compatible with the engine and its control system. NOTE 8. No air bleed is provided for aircraft services. NOTE 9. Maximum overspeed limits are 18,700 HP r.p.m. and 16,800 LP r.p.m. for 20 seconds. If these limits are exceeded the engine shall be overhauled. TCDS E-311 4 NOTE 10. The following fuels are eligible for these engines: Aviation Kerosene Specifications British D.Eng. R.D. 2453, 2482, 2494, or 2498 Canadian 3-GP-23f Kerosene type or 3-GP-24e American ASTM D 1655-68 Jet A or Jet A-1 MIL-T-5624G jp5 Grade I.A.T.A. Kerosene Type (1969) Note: The following departures from Spec. D. Eng. R.D. 2494 are acceptable. Flash Point °F - minimum 70°, Mercaptan Sulphur %age weight max. .016 Aviation Wide-cut Specifications British D.Eng R.D. 2454 or 2486 Canadian 3-GP-22f wide-cut type American ASTM D. 1655-68 Jet B MIL-T-5624G I.A.T.A. Wide-cut type (1969) Fuels conforming with the approved specifications and later 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. The only optional additives which may be used in approved fuels are as follows: 1. Anti-static additive Shell ASA3 in concentrations not exceeding 0.75 ppm. (gm.per cu. metre) 2. Phillips anti-icing additive PFA 55MB (Type 99.6/0.4) or anti-icing additives to specification D. Eng. R.D. 2451 or MIL/I/27686D in concentrations not exceeding 0.15% by volume. 3. Santolene "C" corrosion inhibitor in concentrations such that the total phosphorous content does not exceed 0.06 ppm. 4. Biobor J.F. biocide additive as an intermittent or non-continuous treatment may be used in accordance with the appropriate Rolls-Royce instructions in concentrations not exceeding 270 ppm., and such that the total Boron content does not exceed 20 ppm. NOTE 11. Service Information 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 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. • Technical Variances These approvals pertain to the type design only. ...END....