TCDS E17EU

Page No. 1 2 3 4 Rev. No. 2 2 1 2 FEDERAL AVIATION ADMINISTRATION U.S. DEPARTMENT OF TRANSPORTATION E17EU TURBOMECA Revision 2 ASTAZOU XVIII A March 21, 2007 TYPE CERTIFICATE DATA SHEET E17EU Engines of models described conforming with this data sheet (which is part of Type Certificate Number E17EU) 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, and maintained as prescribed by the approved manufacturer’s manuals and other approved instructions. Type Certificate (TC) Holder: Turbomeca S.A. 64 511 Bordes Cedex, France I. Models Astazou XVIII A TYPE Single spool (fixed shaft turbine)/Turbo-shaft engine for single engined helicopters -Two stage axial compressor -Single stage centrifugal compressor -Annular combustion chamber -Three stage axial turbine (43,000 rpm) -Reduction gear box with output rotating at 5,830 rpm (1/7.375643 reduction ratio) RATING (See NOTE 7) -At nominal turbine speed of 43,000 rpm -Maximum continuous 804 s.hp. -Take-off (5 minutes) 871 s.hp. FUEL (See NOTE 14) FUEL CONTROL Turbomeca integral cons tant speed governor with phase advance correction (includes fuel pump, fuel clock, starting and idling unit and fuel flow limiter). Oil See NOTE 13 PRINCIPAL -Length in. 55.86 DIMENSIONS -Width in. 21 -Height in. 28 CENTER OF GRAVITY C.G. location, af t of engine front attachment plane, 22.1 in., on engine centre line. WEIGHT Dry weight of fully equipped engine (exha ust pipe excluded) : Maximum 375 lb. Refer to Turbomeca Installation Manual No. 275.01.932 Ch. 3 for definition of engine dry weight. DRIVE SHAFT TYPE Shaft with 24 external involute splines 40 x 14 x 2.5 according to French Standard E 22 141. IGNITION Low tension high energy system including: -Two high energy gene rators ABG or EYQUEM -Two igniters SMITHS or EYQUEM STARTING (See NOTE 6) St arter generator SEB Starting unit TURBOMECA with servo-valv e TURBOMECA and electro-valve INDUSTRIA. EGT and idling RPM electronic unit TURBOMECA. E17EU 2 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: October 12, 1973. Type Certificate No. E17EU issued: January 22, 1976. The aviation authority for France, the Direction Generale de L'Aviation Civile (DGAC), originally type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E17EU . Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of France. IMPORT REQUIREMENTS To be considered eligible for installation on U.S. registered aircraft, each new engine to be exported to the United States with the DGAC 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 E17EU, is in a condition for safe operation and has undergone a final operational check. NOTE 1 Permissible engine speeds, rpm: Maximum: -Takeoff & Maximum continuous 44,500 -Transient overspeed (10 sec. limit) 45,600 Minimum for continuous operation 41,500 Refer to Operation Manual 275.01.934 for required action if limits are exceeded. NOTE 2. Maximum perm issible temperature: A. Exhaust gas (t4 °C) (measured with two thermocoupl es on turbine exhaust diffuser). -Takeoff (5 minutes) 620 -Maximum continuous 580 *Starting maximum (5 sec.) 700 to 750 *Refer to Operation Manual 275.01.934 fo r required action if limits are reached. B. Oil (°C) (measured on the suction line from tank to pressure pump) -Maximum operating : +95 -Minimum for starting : - 40 (with normal fu el and oil types, and ground power supply Refer to Operation Manual 275.01.934 for further details). -Minimum for power application : 0 C. Fuel (°C) (at engine inlet) -Minimum for starting : - 40 -Maximum operating : +55 NOTE 3. Fuel and oil pressure limits (psig) A. Fuel : at engine for starting 2.9 to 11.6 at engine inlet for operation - 4.3 to +17.4 B. Oil : (measured at engine pum p outlet, after filter) normal 15.95 to 72.6 minimum 15.95 maximum 72.6 E17EU 3 NOTE 4. Maximum permissible air bleed - P2 air bleed (from centrifugal compressor plenum) max. air mass flow : 0.26 lb/sec. - P1 air bleed (between axial and centrifuga l compressor) max. air mass flow : 0.44 lb/sec. - Power loss due to P2 bleed air : 335 s.hp/lb/sec. - Power loss due to P1 bleed air : 213 s.hp/lb/sec. NOTE 5. Air intake requirements - The engine complies with the ice protection requirem ents of FAR 33.67(c) when fitted with S.N.I.A.S. air intake. SNIAS grid no. 360A.58.1001.08 and 09 and sound suppressor no. 360A.58.1001.05 and 06 or SGAC approved equivalent intake are required. NOTE 6. Accessory drive provisions The following drive accessories are provided as part of en gine and are included in engine dry weight (except A.C. generator which is an optional item) and are as defined in Turbomeca Installation Manual No. 275.01.932. Accessory Manufacturer Type Direction of rotation of drive Reduction ratio Nominal rpm Maximum continuous available power s.hp. Maximum static torque in. lb. Static overhang in. lb. Main output shaft TURBOMECA CCW* 7.375643 5830 ÄÄ ÄÄ ÄÄ Starter generator SEB CCW 4.291417 10,020 10 885 221 Tachometer transmitter JAEGER CCW 5.095994 8,438 .1 4.5 9 A.C. generator (optional) ÄÄ CW 3.620748 11,876 16 300 133 Fuel pump and governor TURBOMECA CCW 10.886075 3,950 ÄÄ ÄÄ ÄÄ Oil pump TURBOMECA CW 10.886075 3.950 ÄÄ ÄÄ ÄÄ *CCW : Counter clockwise, looking from rear of the engine. CW : Clockwise or CCW: Counter clockwise, looking at accessory drive. NOTE 7. Engine ratings : Based on calibrated test rig with performance under the following conditions: - Static, sea level standard conditions (59°F, 29.92 in Hg) - No air bleed, no accessory power off-take. The indicated ratings are mi nimum final test performance of production and overhaul engines measured with engine acceptance test specification No. 275.02.940 (calibrated test bed air intake, straight, short exhaust pipe, 10.23 in.dia.) NOTE 8. Fuel supply requirements : - The engine has no provision for principal fuel filteri ng. Fuel supply from aircraft (helicopter) system must therefore be delivered to engine with a 10 micron filtration grade. - Filter ice protection not provided with engine. NOTE 9. The Astazou XVIII A has an integral oil system , including oil tank, cooler, pumps, filter and piping. - Oil pumps (pressure an d scavenge) - TURBOMECA - Oil filter - TURBOMECA with me tallic filter element SOFRANGE - Oil tank volume, including expa nsion volume : 3.57 U.S. gal. - Oil volume, at top of show glass (filled) : 2.38 U.S. gal. - Oil volume, at lowest show glass (minimum indicated) : 1.85 U.S. gal. - Oil consumption, normally negligib le, but less than : .13 U.S. gal. - Maximum acceptable fuel dilution in oil : 10% in volume. E17EU 4 NOTE 10. Engine mon itoring transmitters The engine is equipped with the following transmitter instruments: - Tachometer transmitter (turbine speed) JAEGER - Oil pressure transmitter LABEM - Minimum oil pressure switch TURBOMECA - Oil temperature bulb “JAEGER” - Thermocouple harness including 2 thermocouples MOVIE-SONICS - Fuel flow limit pressure switch TURBOMECA NOTE 11. Electrical equipment - Electronic starting control box TURBOME CA (actuated by E.G.T. and R.P.M.) - Refer to Turbomeca Operation Manua l No. 275.01.934 for electrical limits. NOTE 12. Engine fire and overheat sensors: - The following fire detector s are provided : 4 L’HOTELLIER - Complementary rear zone overh eat temperature sensors : 2 ELMWOOD NOTE 13. Refer to Turbomeca Operation Manual No . 275.01.934 for approved oil specifications. NOTE 14. Refer to Turbomeca Operatio n Manual No. 275.01.934 for approved fuel and additive specifications. NOTE 15. A list of life limited parts is given in SGAC approved Chapter V of Turbomeca Maintenance Manual No. 275.01.935. NOTE 16. Manuals required by FAR 33.5: - OPERATION MANUAL 275.01.934 - INSTALLATION MANUAL 275.01.932 - MAINTENANCE MANUAL 275.01.935 - OVERHAUL MANUAL 275.01.936 NOTE 17. 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 Direction Generale de L'Aviation Civile (DGAC). 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. These approvals pertain to the type design only. .....END.....