TCDS E16EU

PAGE 1 2 3 4 REV. 1 1 1 1 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTICE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES, IF ANY ARE BLACK-LINED IN THE LEFT MARGIN. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E16EU Rev. 2 ROLLS-ROYCE (1971) BRISTOL M.45H Mk.501 March 31, 2011 NOTE 12. This type certificate is cancelled effective March 31, 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. E16EU Engines of models described herein conforming with this data sheet (which is part of Type Certificate No. E16EU), and other approved 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 F.A.A. 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 (1971) LIMITED Bristol Engine Division P.O. Box 3, Filton, Bristol ENGLAND Model M.45H Mk.501 Type Turbofan 2 spool short by-pass. Fan a nd 5 stage I.P. Compressor driven by a 3 Stage Turbine and a 7 Stage H.P. Compressor driven by a single Stage Turbine. An annular combustion system incorporating vaporizers. Rating (see NOTE 4) Static thrust at sea level, lb. Take-off (5 min.) 7260 Maximum Continuous 7090 Fuel (see NOTE 8) Fuel system (including Dowty Type 1140 Mk.1 acceleration control, fuel pumps and steady state control L.P. Governor Dowty Type 1144 Mk.1 Pressurizing & check valve Dowty Type 1145 Mk.1 Oil Total oil capacity (US pints) 18 Usable oil (US pints) 9.6 Type Shell ASTO 390 Esso ETO 2380 Shell ASTO 500 Principal Dimensions, ins. Mobil Jet II Shell ASTO 555 Castrol 580 Length (including nose bullet 110 (2799 mm) to tail bullet) Diameter (at by-pass) 41.8 (1060 mm) Overall length (intake fairing 122 (3103 mm) to tail bullet) Weight (dry) lb. Basic engine, including fuel 1560 and oil system, anti-icing E16EU - 2 - system, igniter plugs, accessory drive gearbox, blow-off valves, hot pro- pelling nozzle, and fuel heater. Installation items supplied by 245 R.R. (1971) including electrical harness, engine mounting attachment fittings, firewall and supports, firewire (compressor section), tacho generator, transmitters, slinging attachments. Vibration transducers, starter flameshields and by-pass ducts. Powerplant items supplied by RR to complete power unit assembly. Nacelle (including accessory 395 cowls) top fixed panel, rear cowl) and nacelle associated equipment (including constant speed drive, alternator, hydraulic pump, pipes, cooling and ventilation). Centre of Gravity, in. (For total weight of 2200 lb.) Forward of rear mounting 18 trunnion center line Below engine horizontal center 0.25 line. Ignition (High energy system) Two igniters Smiths SB8113 Igniter Unit Rotax C 146/TS/3 NOTES. (1 through 11) Certification Basis: FAR 21.29 and FAR 33 effective February 1, 1965 as amended by amendments 33-1 through 33-4. Type Certificate No. E16EU, issued May 9, 1975. Effective date of application for type certificate: April 30, 1972. Pursuant to FAR 21.29(a)(1)(ii), Ty pe Certificate E16EU was issued in validation of the Civil Aviation Authority's certification of compliance with BCAR standards, which were found to provide a level of safety equivalent to th e above "Certification Basis," as follows: BCAR Section C, Issue 6, dated June 15, 1966 plus Blue Papers: 415, 435, 436, 468, 474, 476, 480, 481, 482, 499, 506, 544, 551 (Para. 3.2.2 only) and 554. Import Requirements Each individually imported engine mu st be accompanied by an R.R. (1971) Ltd./CAA approved "Inspection and Test Certificate" signed by a person authorized by the CAA, and containing the follo wing statement: "The engine covered by this certificate conforms to Type Certificate and is in condition for safe operation; and has been subjected by the manufacturer to a final operational check." E16EU - 3 - NOTE 1: Maximum permissible temperature are as follows (°C) Uncompensated Jet pipe Temperature: Take-off (5 min. limit) 577 to 614 * Maximum Continuous 559 to 608 * Starting (5 sec. limit) - Oil temperature at pressure pump inlet -5°C and above 477 - Oil temperature at pressure pump inlet below -5°C 525 *Limit depends on ambient conditions. See RR Operating Instructions TP.176. Take-off (5 min. limit) 601 Maximum Continuous - Below 160 KIAS : - anti-icing auto 595 - anti-icing on 600 - Above 160 KIAS : - anti-icing auto 580 - anti-icing on 585 Starting (5 sec. limit) - Oil temperature at pressure pump inlet -5°C and above 500 - Oil temperature at pressure inlet below -5°C 565 **Defined by RR Mod.M45-0047. See RR Operating Inst ructions TP.176 for aircraft inst.modification standard. - Oil inlet (unrestricted time) 130 - Oil inlet (10 sec.) 160 - Fuel heater outlet 65 NOTE 2: Fuel and Oil Pressure Limits: Fuel Pressure Minimum (measured at inlet 10 p.s.i. above true fuel vapor to L.P. fuel filter) pressure or 3 p.s.i. (gauge) whichever is greater with a Maximum (measured at inlet 50 p.s.i.g. to L.P. fuel filter) Oil Pressure Normal 30 - 50 p.s.i.g. at 95% r.p.m. and oil temperature of 60°C and above). Minimum to complete flight 7.5 p.s.i.g. (at max.oil temp.) Maximum 50 p. s.i.g. (at 100% r.p.m.) NOTE 3. The following accessory drive provisions are incorporated: Speed Ratio to Torque Overhang Drive Rotations Turbine shaft (in.lb.) (in.lb.) Continuous Static Starter AC .632 590 4320 21 Constant Speed Drive AC .423 384 3550 396 Hydraulic Pump AC .387 200 2292 33 L.P. Tachometer AC .420 7.5 45 1 H.P. Tachometer AC .234 7.5 45 1 *Clockwise or anti-clockwise looking on the drive face of the accessory NOTE 4. The ratings are based on string test stand operation under the following conditions: International standard atmos pheric conditions at sea level. All optional air bleeds closed. Aircraft service accessory drives unleashed. Test bed venturi intake to R.R. (1971) Drg.HL. 112951. Hot and cold nozzles as defined in P.I. 81837. Jet pipe temperature measured by ther mocouple harness as defined in P.I.S.837. NOTE 5. M45H models have the following applications: Mark 501 Basic Model for VFW Fokker 614 aircraft. NOTE 6. (a) Maximum permi ssible engine operating rotor speeds are as follows: N1 N2 E16EU - 4 - Take-off, rpm (5 min.limit) 10150 (101.4%) 17890: (99.7%) Maximum continuous rpm. 10050 (100.4%) 17660: (98.4%) Transient overspeed, rpm. (20 s ec. limit) 10190 (101.8%) 17960: (100.1%) (b) Ground idle/flight idle, minimum 10588 (59.0%) NOTE 7. Air bleed extraction limitations: Range of R.P.M. at which air bleed may be used. Unrestricted Maximum air delivery for aircraft services and engine de-icing (% of no bleed mass flow) 5% NOTE 8. The following fuels may be used for this engine: Aviation Kerosene Specifications Aviation Wide-cut Specifications British D.Eng.R.D.2494, D.Eng.R.D.2453 D.Eng.R.D. 2486 Canadian 3-GP-23 3-GP-22 American ASTM D 1655 Jet A or A-1 ASTM D 1655 Jet B 1ATA 1973 Kerosene Type Wide-Cut Type NOTE 9. The only optional additives which may be used in approved fuels are as follows: 1. Anti-static additive Shell ASA 3 in concentrations not exceeding 1.0 mg. per liter. (378.5 mg, or 0.013 oz., per 100 U.S. Gals.) 2. Fuel System Icing Inhibitor (F.S .I.I.) to specification D.Eng.R.D. 2451 or MIL-I-27686E in concentrations not exceeding 0.15% by volume. 3. Anti-corrosion additive Hitec E.515 in c oncentrations not exceeding 14.3 mg per liter. (5.4 grams, or 0.191 oz., per 100 U.S. Gals.) NOTE 10. Life limited components are listed in Chapter 5 of the M45H Mk.501 Engine Maintenance Manual, together with their approved lives. NOTE 11. M45H Series Manuals approved under BCAR accepted as equivalent to FAR 33.5 are: 1. Engine Flight Operating In structions. Reference TP.176/BED. 2. M45H-501 Engine & Powerplant Ma intenance Manual. Reference TP.182/BED. 3. M45H-501 Engine I llustrated Parts Catalog. M45H engines not eligible for im port into U.S. under FAR 21.29 until CAA approved Installation and Overhaul Manuals are provided by Rolls Royce. ---END---