TCDS E14EU

Page No. 1 2 3 4 5 Rev No. 3 3 3 3 3 Revised 4/95 FEDERAL AVIATION ADMINISTRATION U.S. DEPARTMENT OF TRANSPORTATION E14EU TURBOMECA Revision Number: 3* Model: ASTAZOU III A May 29, 1975 TYPE CERTIFICATE DATA SHEET E14EU Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E14EU) 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 Federal Aviation Regulations, provided they are installed, operated, and maintained as prescribed by the approved manufacturer’s manuals and other approved instructions. Type Certificate Holder: TURBOMECA 64 - Bordes - France I. Model: ASTAZOU III A TYPE Single spool (fixed shaft) turbine-shaft engine for single engined helicopter. - single stage axial compressor - single stage centrifugal compressor - annular combustion chamber with central fuel injection - three stage axial turbine - 7.039 : 1 reduction gearing RATING (See NOTE 7) At nominal engine speed of 43,500 r.p.m. - Maximum continuous and Takeoff (5 min) 592 s.hp. FUEL CONTROL Turbomeca integral constant speed governor with phase advance correction: 0.064.87.807.0 (includes fuel pump, idle fuel control and hp., fuel shut-off cock). FUEL See NOTE 13, for approved fuels and additives. OIL See NOTE 12, for approved oils. PRINCIPAL DIMENSIONS Length, in. 56.40 Width, in. 19.00 Height, in. 20.00 CENTER OF GRAVITY C.G. location, aft of accessory drive plate, in. 6.06 below engine center line, in. .24 left of engine center line (looking forward), in. .24 WEIGHT Dry weight of fully equipped engine (exhaust pipe excluded Maximum lb. 325 DRIVE SHAFT TYPE (special) 24 internal involute splines, according to AND 20006, Type XVI D Spec. Pitch circle diameter, 1,20 in. IGNITION High tension, low energy system, comprising: E14EU 2 - Double ignition coil : Air Equipment Type 81268 - Two torch igniters : Turbomeca 0.237.30.755.0 - Two high tension cables : Turbomeca 0.043.07.703.0 - Ignition fuel micropump : Turbomeca 0.044.63.509.0 STARTING Electric starter-generator : S.E.B. Type 505 Compressor acceleration bleed-off valve : Turbomeca 0.210.09.519.0 Starter cut-out pressure switch : Turbomeca 0.076.48.500.0 CERTIFICATION BASIS FAR 21.29 and FAR 33, effective February 1, 1965, and Amendments 33-1, 33-2, 33-3, and 33-4. Date of application for Type Certificate : May 6, 1971. Type Certificate No. E14EU issued : September 7, 1972. IMPORT REQUIREMENTS The “Certificat de Controle” must contain the following statement: “The engine covered by this certificate conforms to Type Certificate E14EU; is in condition for safe operation; and has been subjected by the manufacturer to a final operational check.” NOTE 1. Maximum permissible engine speeds, r.p.m.* Takeoff, maximum continuous, and normal flight conditions: 43,500 +400 Transients (under sharp loading or unloading): 43,500 - 0 æ1,500 Overspeed (10 sec. limit): 45,600 *Refer to Turbomeca Operation Manual 268.08.931 for required action if limits are exceeded. NOTE 2. Maximum permissible temperatures A. Exhaust gas (T4, °C)* (measured with two thermocouples on turbine exhaust diffuser) Takeoff (5 min.) and Maximum Continuous 550 Transient (10 sec.) 600 *Refer to Turbomeca Operation Manual 268.08.931 for required action if limits are exceeded. B. Oil (measured on oil return from cooler to tank union on the engine, °C) (See NOTE 12) Minimum and maximum during operation : -15 and +85 (NATO 0.148 and equivalent oils) : -10 and +85 (NATO 0.135 and equivalent oils) : 0 and +85 (NATO 0.156 and equivalent oils) : + 5 and +85 (NATO 0.149 and equivalent oils) C. Fuel (°C not measured on engine) Minimum and maximum during operation: -40 and +50 NOTE 3. Fuel and oil pressure limits (p.s.i.g.) A. Fuel : at engine inlet for starting: 4.3 to 8.7 at engine inlet for operation: - 4.3 to 13.1 B. Oil : (measured at engine pump outlet, after filter) Normal : 21.7 to 72.6 Minimum : 11.6 Maximum : 72.6 NOTE 4. Maximum permissible air bleed (from centrifugal compressor plenum) (Orifice limited at engine pick-up union) : 0.220 lb/sec. Power loss due to air bleed-off : 304 hp/lb/sec. NOTE 5. Air intake anti-icing limits This engine meets the ice protection requirements when either TURBOMECA anti-icing shield No. 0 235 20 753 0 or 0 235 21 768 0, air intake grid TURBOMECA No. 0 235 21 762 0 or AEROSPATIALE silencer No. 341 A 54 0110 or 341 A 54 1004 is installed; and the following limitations are observed: 3 E14EU OAT = -40°C minimum Oil temperature (measured as per note 2B) : +30°C minimum NOTE 6. Accessory drive provisions The following driven accessories are provided on the engine and included in engine weight (with exception of the A.C. generator, which is an optional item). Accessory Manufacturer, Type Rotation sense of engine drive pad Reduction ratio (Nominal r.p.m.) Maximum continuous available power (hp) Maximum static torque (in. lb.) Static overhang (in. lb.) Principal power output drive shaft Turbomeca - CCW 7.039591 (6179.3) 523 13,000 800 Starter- Generator S.E.B. 505 CW 5.571294 (7807.8) 10 885 221 Tachometer Transmitter Kollsman L827.80-00-010 CW 10.38481 (4188.8) .1 4.5 9 (A.C. Generator optional) Not part of normal delivery CW 3.63468 (11968) 16 300 133 CCW = counterclockwise, looking forward CW = clockwise, looking at accessory drive pad NOTE 7. Engine ratings : are based on calibrated rig with the performance under the following conditions: - Static, sea level standard conditions (59°F, 29.92 Hg.) - No air bleed, no power off-takes The indicated ratings are minimum acceptable final test performance of series and overhauled engines, measured with: - Calibrated test bed air intake, straight, short exhaust pipe, 10.25 in. dia. (For complete performance diagram, see Turbomeca Operation Manual 268.08.931). NOTE 8. The engine has no provision for principal fuel supply filtering. Fuel supply from aircraft (helicopter) system must therefore be delivered to engine with a 15 microns filtration grade. Maximum fuel flow: 63.4 U.S. gallons/hour. NOTE 9. The Astazou III A has integral oil system, including oil tank, oil pumps, filter, all necessary piping and fittings, (except oil cooler, which is helicopter delivery). - Oil pump assembly (lubricating and scavenging pumps): Turbomeca 0.269.16.513.0 or 0.268.16.518.0 - Oil filter (part of the accessory drive casing) including cleanable metallic filter-element with a 30 microns filtration grade: Sofrance, Type P5315A - Oil tank volume, including air expansion space: 3.86 U.S. gal - Oil volume at top of show-glass (filled): 2.43 U.S. gal - Oil volume at lowest show-glass (minimum indication): 1.64 U.S. gal - Demonstrated usable oil volume: 1.32 U.S. gal - Undrainable oil volume (approx.) .40 U.S. gal - Oil consumption, normally negligible, but less than: .21 U.S. pint/hour maximum allowable: 1.05 U.S. pint/hour - Maximum acceptable fuel dilution in oil: 10 percent in volume NOTE 10. Engine monitoring transmitters: The engine is equipped with the following transmitter instruments: (a) Tachometer transmitter (turbine speed): KOLLSMAN Type L827.80-00-010 (b) Low oil pressure alarm pressure switch: TURBOMECA 0.076.46.506.0 or 507.0 E14EU 4 (c) Oil temperature bulb: JAEGER Type 1982-03 (d) Thermocouple harness including 2 thermocouples: TURBOMECA 0.025.83.000.0 (e) Fuel flow limit pressure switch (included in fuel TURBOMECA 0.076.47.500.0 control unit). (f) Oil pressure transmitter: LABEM Type 5116-6 NOTE 11. Engine fire detection: The following unit detectors are installed: - Three L’HOTELLIER B232 (front zone) - One L’HOTELLIER B332 (rear zone) NOTE 12. Oils shall conform to the specifications as listed in table below or to subsequent revisions thereof. Do not mix different oils, flush the system when changing from one type to the other. SPECIFICATION REMARKS NATO France U.S.A. U.K. Description 0.148 0.150 AIR 3513 AIR 3514 MIL-L-7808 - - - Synthetic Oil 3 c St Normal oil. 0.156 - MIL-L-23699 - Synthetic Oil 5 c St Alternate oil. 0.149 0.159 - AIR 3517 - - D.ENG.RD2487 - Synthetic Oil 7.5 c St 0.135 AIR 3515 Aeroshell Turbine Oil 3 D.ENG.RD2490 Mineral oil 3 c St Esso Aviation Utility Oil Caltex Jet Engine oil Medium Heavy NOTE 13. Fuels shall conform to the specifications as listed in table below or to subsequent versions thereof. The mixing of approved fuels is permitted, subject to the limitations specified under “Remarks”. No adjustment of engine control is necessary and no loss of performance occurs. - Normal fuels, unrestricted SPECIFICATIONS REMARKS FRENCH U.S. BRITISH NATO Aviation Fuels - D.ENG.RD2453 AVTUR FS II F34 AIR 3405 ASTM Jet A - - (TRO) ASTM Jet A1 D.ENG.RD2494 AVTUR F35 Aviation Fuels MIL-T-5624 (JP.4) D.ENG.RD2454 AVTAG FS II F40 AIR 3407 (TR4) ASTM Jet B D.ENG.RD2486 AVTAG F45 Aviation Fuels - - F42 AIR 3403 (TR5) MIL-T-5624 (JP.5) D.ENG.RD2498 AVCAT F44 5 E14EU - Fuels subjected to restrictions on use SPECIFICATION Restrictions FRENCH U.S. BRITISH NATO Gasoline MIL-G-5572 (Grade 80/87) - F12 Maximum operating time on gasoline during any period between (Grade 100/130) D.ENG.RD2485 F18 overhauls: 25 hours AIR 3401 (Grade 115/145) F22 Automotive Gasoline DCEA/2D MT80 MIL-G-3056 DEF 2401 F46 Add 1 to 2% of lubricating oil by volume (mineral if possible) Automotive Diesel oil DCEA/21C VVF 800 DF2 TS.10.003 F54 Not to be used at OAT below -5°C VVF 800 DF1 - - Not to be used as OAT below -15°C - VVF 800 DFA F56 Gasoil 0 7120 STM MIL-F-16884 DEF 2402 (47/0 DIESO) F75 Not to be used as OAT below -5°C Gasoil 20 7120 STM - DEF 2402 (47/20 DIESO) F76 Not to be used at OAT below 0°C Illuminating Oil DCEA/11C VV-K 211 DEF 2403 F58 Not to be used at OAT below -15°C The following fuel additives are approved for use: - Anti-icing additive: AIR 3652, MIL-I-27686, D.ENG.RD.2451, Phillips PFA-55-MB, each is eligible up to 0.15 percent by volume, with or without glycerine. - Anti-static additive: SHELL ASA-3, up to 0.0001 percent by volume. NOTE 14. See SGAC approved Chapter 5 of Turbomeca Maintenance Manual 268.08.933 for life limited parts. .....END.....