# TCDS E13EU: Turbomeca S.A. - Type: Type certificate data sheet - Status: Current - Holder: Turbomeca S.A. - Revision: 5 - Revised: November 11, 2018 - Product: Engine - Certification basis: Part 21, Part 33 - Registered aircraft: 5, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/83/78/8378f8bb562ae4447b28465e822363ce4d2bd85a102db232acca7ca4b07e32f7 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/2F661B2AF357F5F08625835900576693.0001 - Page: https://openairdocs.org/tcds/E13EU ## Models (2) As the data sheet lists them. - Astazou XIV H - Astazou XIV B ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 Rev. No. 5 5 5 5 5 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E13EU Revision Number: 5 Safran Helicopter Engines Models: Astazou XIV B Astazou XIV H November 11, 2018 TYPE CERTIFICATE DATA SHEET E13EU Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E13EU) 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 (TC) Holder: Safran Helicopter Engines (formerly Turbomeca) 64 511 Bordes Cedex France I. Models Astazou XIV B Astazou XIV H TYPE Single spool turbo-shaft engine for single engined helicopters: - Two stage axial compressor - Annular combustion chamber with central fuel injection - Three stage axial turbine (43,000 rpm) - 7.34528:1 reduction gearing (5824 rpm) - 6.78857:1 reduction gearing (6334 rpm) RATING (See NOTE 7) At nominal engine speed of 43,000 rpm - Maximum continuous: 542 shp. - Maximum continuous and Takeoff (5 min.): 592 shp. - Takeoff (5 min.) : 592 shp. FUEL CONTROL Safran Helicopter Engines integral constant speed governor with phase advance correction: includes fuel pump, idle Fuel control and hp. fuel shut-off cock, fuel flow limiter (Astazou XIV H only). FUEL See Note 13. OIL See Note 12. PRINCIPAL DIMENSIONS Length, in.: 56.42 57.90 Width, in.: 20.47 19.68 Height, in.: 24.55 22.20 CENTER OF GRAVITY C.G. location, aft of accessory drive plate, on engine C.L., in.: 7.30 C.G. location, aft of rear engine attachment phase: in engine C.L., in.: 8.15 WEIGHT (dry, completely equipped, exhaust pipe excluded): 353 lb. (maximum) E13EU 2 DRIVE SHAFT TYPE. Special 24 internal involute splines, according to AND 20006, Type XVI Spec., pitch circle: 1.20 inches diameter. IGNITION. High tension, low energy, comprising: - Double ignition coil : Air Equipment - Two torch igniters : Safran Helicopter Engines - Two high tension cables : Safran Helicopter Engines - Ignition fuel micropump : Safran Helicopter Engines CERTIFICATION BASIS FAR 21.29 and FAR 33, effective 1 February 1965 and Amendments 33-1, 33-2, 33-3 and 33-4. Date of application for Type Certificate : 7 May 1971 (Astazou XIV B). Type Certificate No. E13EU issued : 12 September 1972. Date of application for Type Certificate extension to Astazou XIV H : 25 November 1975. Amended Type Certificate E13EU issued May 25, 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 E13EU. 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 E13EU, is in a condition for safe operation and has undergone a final operational check. NOTE 1. Permissible engine speeds, rpm Maximum: - Takeoff maximum continuous, and all normal flight conditions: 43,200 - Transients: 44,500 - Overspeed (10 sec. limit): 45,600 Minimum for transient operation 41,500 Refer to Safran Helicopter Engines Operation Manual for required action if limits are exceeded. NOTE 2. Maximum and minimum permissible temperatures. A. - Exhaust gas (°C) (Measured with two thermocouples on turbine exhaust diffuser) ASTAZOU XIV B ASTAZOU XIV H - Take-off (5 min.) 550 550 * Maximum continuous 470* 500 **Starting 700 to 750 700 to 750 **Refer to Operation Manual for required action if limits exceeded. * When modification AB60/No. 40 is installed the permitted maximum is 500. B. - Oil (°C) (Measured on oil return from cooler to tank) - Minimum for starting -30 - Minimum for engine loading -15 - Maximum in operation +85 - Minimum for anti-icing +30 C. - Fuel (°C) (not measured on the engine) - Minimum for starting -30 - Maximum in operating +55 Refer to Safran Helicopter Engines Operation Manual for required actions if limits are exceeded. 3 E13EU 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. B. - Oil : (at engine oil pump outlet) - Normal : 20 to 70 - Minimum : 16 - Maximum : 70 NOTE 4. Maximum permissible air bleed (from centrifugal compressor plenum) (Orifice limited at engine pick-up union) : 0.420 lb/sec. Power loss due to air bleed off : 335 hp/lb/sec. NOTE 5. Air intake anti-icing limits. This engine complies with the ice protection requirements of FAR 33.67(c) when Safran Helicopter Engines P/N 0.235.28.751.0 or grid no. 0 235 21 762 0 or SNIAS sound suppressors SNIAS no. 341 A 54 0110 or no. 341 A 54 1004 is fitted or SGAC-approved equivalent intake are required. Oil temperature (refer to NOTE 2(B)). 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). Refer to Safran Helicopter Engines Installation Manual. Accessory Engine Type Manufacturer Rotation direction of engine drive pad* Reduction ratio (nominal rpm). Maximum continuous available power (shp) Maximum static torque (in. lb.) Static overhang (in. lb.) Principal power out put drive XIV B XIV H Safran Helicopter Engines CCW 7.34528 (5854) 6.78857 (6334) 542 592 8 680 8 680 780 780 Starter Generator XIV B XIV H S E B CW 5.5713 (7,718) 4.18166 (10,283) 10 868 221 A.C. Generator XIV B XIV H - CW 3.63468 (11,830) 3.57173 (12,039) 12 18.1 300 133 Tachometer Transmitter XIV B XIV H JAEGER CW 10.3481 (4,141) 10.2049 (4,214) 0.1 4.5 9 E13EU 4 Accessory Engine Type Manufacturer Rotation direction of engine drive pad* Reduction ratio (nominal rpm). Maximum continuous available power (shp) Maximum static torque (in. lb.) Static overhang (in. lb.) Fuel pump and control unit Generator XIV B Safran Helicopter Engines CCW 10.9417 (3,390) 10,750 (4,000) - - - Fuel Pump XIV B Safran Helicopter Engines CW 11.4513 (3,755) 11.250654 (3,822) - - - *Direction of rotation: looking at accessory drive pad except principal power output drive from the rear of the engine. NOTE 7. Engine ratings: are based on calibrated test rig with the performance under the following conditions: - Static sea level standard conditions (59°F, 29.92 in. Hg.) - No air bleed, no power off-takes The ratings are minimum acceptable final test performance of production series and overhauled engines, measured according to Acceptance Test Specification No. 283 00 940. NOTE 8. Fuel supply requirements: The engine has no provision for principal fuel supply filtering. Fuel supply from aircraft (helicopter) system must therefore be delivered to engine with a 10 microns filtration grade. Maximum fuel flow: - 61 U.S. gal./h. (ASTAZOU XIV B) - 65.5 U.S. gal./h. (ASTAZOU XIV H) - Filter ice protection not provided with engine. NOTE 9. The ASTAZOU XIV has integral oil system, including oil tank, oil pumps, oil filter, all necessary piping and fitting, except oil cooler, which is aircraft (helicopter) delivery. - Oil pump assembly (lubricating and scavenging pumps) : Safran Helicopter Engines - Oil filter (part of accessory drive casing) including cleanable metallic filter-element with 30 microns filtration grade : SOFRANCE - Oil tank volume : including 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) : 1.64 U.S. gal - Demonstrated usable oil volume : 1.11 U.S. gal - Undrainable oil volume (approx) : .40 U.S. gal - Oil consumption, normal, 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) : JAEGER b - Low oil pressure alarm pressure switch : Safran Helicopter Engines c - Oil pressure transmitter : LABEM d - Oil temperature bulb : JAEGER e - Thermocouple harness including 2 thermocouples : Safran Helicopter Engines f - Fuel flow limit pressure switch, (including in fuel control unit) : Safran Helicopter Engines 5 E13EU NOTE 11. Electrical requirements Refer to Safran Helicopter Engines Operation Manuals for electrical limits. NOTE 12. Refer to Safran Helicopter Engines Operation Manuals for approved oil specifications. NOTE 13. Refer to Safran Helicopter Engines Operation Manuals for approved and additive specifications. NOTE 14. Engine fire sensors: - The following fire detectors are provided: 4 l’Hotellier NOTE 15. See DGAC approved Chapter 5 of Maintenance Manual for life limited parts. NOTE 16. Manuals required by FAR 33.5: ASTAZOU XIV B ASTAZOU XIV H - OPERATION MANUAL 283 00 931 283 02 938 - INSTALLATION MANUAL 283 00 939 283 02 937 - MAINTENANCE MANUAL 283 00 936 283 02 933 - OVERHAUL MANUAL 283 00 938 283 00 938 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..... ``` ## ADs (7, in force first) - [AD 2021-05-22](https://openairdocs.org/ad/2021-05-22): Turbine Section · Turbomeca Arriel 1B, Arriel 1C, Arriel 1C2 and 3 more. Effective Mar 22, 2021 - [AD 2018-22-11](https://openairdocs.org/ad/2018-22-11): Turbine Section · Turbomeca Astazou XIV B and Astazou XIV H. Effective Mar 18, 2019 - [AD 2016-12-07](https://openairdocs.org/ad/2016-12-07): Third stage turbine wheel · Turbomeca Astazou XIV B and Astazou XIV H. Effective Jul 26, 2016 - [AD 2016-09-02](https://openairdocs.org/ad/2016-09-02): 3rd stage turbine wheel · Turbomeca Astazou XIV B and Astazou XIV H. Effective Jun 8, 2016 - [AD 2013-26-09](https://openairdocs.org/ad/2013-26-09): 2nd-stage turbine disk · Turbomeca Astazou XIV B and Astazou XIV H. Effective Feb 14, 2014 - [AD 2005-25-12](https://openairdocs.org/ad/2005-25-12): Air intake noise suppressors · Turbomeca Astazou XIV B and Astazou XIV H. Effective Dec 28, 2005 - [AD 2010-11-10](https://openairdocs.org/ad/2010-11-10) (historical): In-flight shutdown · Turbomeca Astazou XIV B and Astazou XIV H. Effective Jul 6, 2010 ## Registered aircraft by registry model (OpenAirDocs) - [Turbomeca ASTAZOU XIV H](https://openairdocs.org/engine/turbomeca-astazou-xiv-h): 5 aircraft (registry code 60018) - [Turbomeca ASTAZOU XIV B](https://openairdocs.org/engine/turbomeca-astazou-xiv-b): 0 aircraft (registry code 60017) --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.