# TCDS E10EU: Turbomeca S.A. - Type: Type certificate data sheet - Status: Current - Holder: Turbomeca S.A. - Revision: 6 - Revised: January 9, 2012 - Product: Engine - Certification basis: Part 21, Part 33 - Registered aircraft: 6, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/8e/90/8e9089c1728ca5f5b4f4b2c318a56062681e63a6ac3e9bb5e016e71c8fd2fab6 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/8FF3A89E5FFE79FF862579900069100E.0001 - Page: https://openairdocs.org/tcds/E10EU ## Models (2) As the data sheet lists them. - Turmo IVA - Turmo IVC ## 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. 6 5 5 4 5 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E10EU Revision No. 6 TURBOMECA TURMO IVA TURMO IVC January 9, 2012 TYPE CERTIFICATE DATA SHEET E10EU Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E10EU) 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 S.A. 64 511 Bordes Cedex, France Models TURMO IVA TURMO IVC Type Twin spool (free turbine) turbos haft engine for multiengined helicopter. - Single stage axial compressor - Single stage centrifugal compressor - Annular combustion chamber with central fuel injection - Two stage axial turbine for gas generator - Single stage axial free power turbine - Direct drive output Ratings (See NOTE 5 & 8) At nominal power turbine speed of 22,840 r.p.m. SHAFT HORSEPOWER (SHP) TORQUE (ft. lb) IVA IVC IVA IVC Maximum continuous 1170 1287 273 300 T.O. (5 min.) 1274 1495 298 350 30 min. power rating 1274 1475 298 345 2 1/2 min. power rating 1415 1555 332 365 Fuel Control Constant speed fuel flow for free turbine spool 0.064.63.809. 0 (IVA); 0.064.63.810.0 (IVC) Speed limiter for gas generator spool. Idling fuel flow control unit 0.064.63.809.0 (IVA); 0.064.63.810.0 (IVC) High pressure fuel cock. (included in governor) Fuels. SPECIFICATION French NATO U.S.A. U.K. Russian AIR 3405 (TRO) F.34 D.ENG.RD.2453 AVTUR FS.II ASTM-D-1655 Jet A F.35 ASTM-D-1655 Jet A1 D.ENG.RD.2494 AVTUR AIR 3407 (TR4) F.40 MIL-T-5624 (JP4) D.E NG.RD.2454 AVTAG FS.II F.45 ASTM-B-1655 Jet B D.ENG.RD.2486 AVTAG AIR 3404 (TR5) F.42 F.44 MIL-T-5624 (JP5) D.ENG.RD.2498 AVCAT TS-1 for TURMOIVC only TCDS E10EU 2 Anti-icing additive must be used in accordance with the SGAC-approved SNIAS SA 330F (TURMO IVA) or SA 330G (TURMO IVC) Rotorcraft Flight Manuals (ref. Type Certificate No. H4EU.) The following fuel additives are approved for use: - Phillips PFA 55 MB, MIL-I-27686 (as revised), or French Air 3652 (as revised) anti-icing additive in quantity up to 0.15 percent in volume (with or without glycerin). - Shell ASA-3 antistatic additive in qua ntity up to 0.0001 percent in volume. Oils ENGINE OIL SPECIFICATION (Latest Amendment) REMARKS FRENCH NATO U.S.A. U.K. AIR 3513 0.148 MIL-L-7808 3 cst (98,9F) Synthetic AIR 3514 0.150 0.156 MIL-L-23699 5 cst (98,9F) 0.149 D.ENG.RD 2487 7.5 cst (98,9C) AIR 3517 0.159 MINERAL AIR 3515 0.134 and 0.135 AERO-SHELL Turbine oil 3 ESSO Aviation Utility oil F CALTEX JET Engine Oil Medium heavy D.ENG.RD 2490 CAUTION: The mixing of mineral and synthetic oils is not recommended. The system should be flushed when changing from one type to the other. PRINCIPAL DIMENSIONS Length: 85.98 in. Width: 25.08 in. Height 28.31 in. WEIGHT Dry completely equipped, including exhaust pipe : 499.4 lb. Tolerance on weight = 0 to +11 lb. CENTER OF GRAVITY Forward of rear engine mount plane: 35.3 in. In the horizontal plane of the engine centerline and output drive shaft, from centerline on drive shaft side: 3.15 in. Reward of front engine mounting bolt in plane of the fixation struts: 19.66 in. IGNITION High tension, low energy, comprising: - Double ignition coil : Air-Equipment Type 81268/21 - Two torch igniters : Turbomeca 0.237.30.755.0 - Two high tension cables : Turbomeca 0.043.07.709.0 and 710.0 - Ignition fuel micropump : Turbomeca 0.044.63.504.0 STARTING Electric Starter: SEB Type 1028 CERTIFICATION BASIS FAR 21.29 and FAR 33, effective February 1, 1965 and Amendments 33-1, 33-2, and 33-3. Date of Application for Type Cer tificate: March 10, 1970 (TURMO IVA) Type Certificate No. E10EU issued June 23, 1971. Date of Application for amended Type Certificate: December 14, 1972 (TURMO IVC) Type Certificate amended May 15, 1974, to include TURMO IVC. 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 E10EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of France. TCDS E10EU 3 IMPORT REQUIREMENTS: To be considered eligible for inst allation 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 E10EU, is in a condition for safe operation and has undergone a final operational check. Additional guidance is contained in F AA Advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, Engines, Propellers and Related Products, Imported into the United States. This engine is eligible only in S.N.I. A.S. SA330F model helicopter when fitted with TURMO IVA, and SA330G model helicopter when fitted with TURMO IVC, reference Type Certificate H4EU; and must be maintained in accordance with SA330F Maintenance Manuals, chapters 71, 72, 73, 75, 76, 77, 78, and 80. NOTE 1. Maximum permissibl e rotor speeds, r.p.m.* - Gas generator turbine IVA IVC 2 1/2 min. power rating 33,950 33,800 30 min. power rating 33,300 33,350 Takeoff (5 min.) 33,300 33,450 Maximum continuous 32,800 32,500 Transient (30 sec. max.) 34,100 34,100 *Refer to Turbomeca Operation Manual for required action if limits are exceeded. Also refer to this Manual for other r.p.m. limits versus OAT and engine bleed configuration. - Free Turbine (expressed as output shaft r.p.m.) Nominal speed 22,840 Maximum speed 23,750 NOTE 2. Maximum permissible temperatures. A. Gas generator turbine exhaust (T4), C* (measured with two thermocouples on gas generator turbine exhaust diffuser). IVA IVC 2 1/2 min. power rating 790 790 ** 30 min. power rating 780 770 Takeoff (5 min.) 780 780 Maximum continuous 750 710 Starting (30 sec. max.) 750 750 Transient, for operation 820 (30 sec. max.) 830 (12 sec. max.) Maximum residual before starting 150 150 * Refer to Turbomeca Operation Manual for required action if limits are exceeded. **Maximum limit for Turmo IVC with bleed air on for anti-icing = 820C (refer to Turbomeca Operation Manual for engine disposition). B. Oil temperature limits (measured in oil tank), C - Maximum operating 100 - Minimum for starting -35 with AIR 3513, 3514; -26 with AIR 3517, MIL-L-23699, D.ENG.RD 2487; -20 with AIR 3515 (D.ENG.RD.2490) - Minimum for power higher than idle 0 TCDS E10EU 4 C. Fuel temperature limits, C - Minimum for starting -30 with TR0 and TR4 (JP4); -20 with TR5 (JP5) - Maximum for operating +50 NOTE 3. Fuel and Oil Pressure Limits, psig. Fuel: At engine inlet for starting 4.3 to 11.6 At engine inlet for operation -5.8 to 17.4 Oil: (At engine oil pump outlet) At ground idle, minimum 10.0 Normal operating range 51.0  3.0 Maximum pressure 65.0 Minimum at 32,000 r.p.m. 29.0 NOTE 4. Accessory Drive Provisions The following driven accessories are provided on the engine and are included in engine weight. Accessory Part No. Directi on of Reduction Max. Torque Overhang of Rotation (facing pad) Ratio (referenced to turbine speed) Continuous in. lb. Static in. lb. in. lb. - On gas generator turbine. Starter Tachometer Transmitter SEB Type 1028 JAEGER Type 545 359 CW (Clockwise) CCW (Counter clockwise) 1:1.24188 1:7.94482 1 150 5 49 18 - On free turbine (output turbine) Tachometer Transmitter drive (Not fitted) CCW 1:3.81419 2 9 27 NOTE 5. Engine ratings are based on calibrated te st stand performance under the following conditions: - Static sea level ISA conditions, (59 F, 29.92 in.Hg.) - No air bleed - No power off-takes by the accessories. The ratings are minimum acceptable final test performan ce of series and overhauled engines, measured with: - Calibrated test bed air intake, according to Turbomeca dwg. No. 6202 66 701 0. - Flight exhaust pipe, Turbomeca Part No. 0.249. 76.000.0 (which is part of engine delivery). - Air intake anti-icing protection shield installed, but not supplied with hot air. NOTE 6. Maximum permissible air bleed (from centrifugal compressor plenum). (Orifice limited at engine ou tlet with 0.598 in. orifice). - For aircraft services (including inlet duct anti-icing when required) 0.397 pounds per second. - See Turbomeca Operation Manual for limitations on bleed flow vs engine power and r.p.m. NOTE 7. Air intake anti-icing limits: - If OAT is between +5 C and -20C, Gas Generator r.p.m. must be equal to or higher than 26,000 - If OAT is between -20 C and -30C, Gas Generator r.p.m. must be equal to or higher than 26,500 - Also engine oil temperature must be equal or higher than 30 C. The engine meets FAR 33 requirement s for operation in icing conditions when above limitations are observed. TCDS E10EU 5 NOTE 8. Engine Mechanical Lim its: Not limited on engine side. Maximum torque: 400 ft. lb. on free turbine output shaft. Operation of gas generator turbine with free turbine stopped is prohibited. NOTE 9. The TURMO IVA and IVC integral oil system including pum ps, oil tank, oil filter, oil cooler with its mechanical driven cooling fan, all necessary pipes and fittings. - Oil pump assembly (lubricating and scavenging pumps) : Turbomeca 0.249.17.747.0 - Oil cooler with thermostat (heat rejecti on approx. 7.0 BTU/sec.): Jaeger Type 2.2598A - Oil filter (part of intake casing) (including cleanable metallic filter-element with 30 microns filtration grade): Sofrance Type P.5315 A NOTE 10. The engine has no provision for fuel filtering. Fuel supply from aircraft system must therefore be delivered to engine with a 10 microns filtration grade. Maximum fuel flow: Approx. 142.5 U.S. gal/hr (IVA) and 155.8 U.S. gal/hr (IVC) NOTE 11. Engine monitoring transmitters: The engine is equipped with following transmitte r instruments, which are part of delivery: (a) Tachometer transmitter (gas gene rator turbine speed) JAEGER Type 545359 (b) Oil pressure transmitter JAEGER-AMA Type 1879 SB (c) Oil temperature bulb JAEGER-AMA 1982 ZC (d) Thermocouple harness including two chromel-alumel thermocouples. TURBOMECA 0.177.40.000.0 (IVA) 0.177.40.501.0. (IVC) NOTE 12. Engine fire detection: The following spot detectors are installed: -Two l'Ho tellier Type B 232 and one Type B 332 (front engine zone). -Three l'Hotellier Type B 332 (rear engine zone). NOTE 13. Electrical Equipment: 27 volts DC system with all n ecessary harnesses and wiring, including connection box : Turbomeca 0.249.92.950.0 Automatic starting sequence block : Turbomeca 0.177.10.754.0 is approved for use on the engine. NOTE 14. Information on service life limited parts in cont ained in Chapter 5, TURBOMECA Maintenance Manual NO. 279 02 932. NOTE 15. Turbomeca TURMO IVA and IVC engine manuals approve d by SGAC and accepted by FAA as equivalent to FAR 33.5 requirements are: OPERATION MANUAL - No. 279 00 931 MAINTENANCE MANUAL - No. 279 02 932 INSTALLATION MANUAL - No. 249 92 932 OVERHAUL MANUALS - NOTE 15 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 (6, in force first) - [AD 2016-05-08](https://openairdocs.org/ad/2016-05-08): Centrifugal compressor inducer blade loss · Turbomeca Turmo IVA and Turmo IVC. Effective Apr 21, 2016 - [AD 2010-02-08](https://openairdocs.org/ad/2010-02-08): Pipe union crack · Turbomeca Turmo IVA and Turmo IVC. Effective Feb 3, 2010 - [AD 2009-02-08](https://openairdocs.org/ad/2009-02-08): Oil-tank-to-oil-cooler flexible lubrication pipes · Turbomeca Turmo IVA and Turmo IVC. Effective Mar 4, 2009 - [AD 2006-23-17](https://openairdocs.org/ad/2006-23-17) (historical): Centrifugal compressor intake wheel blades · Turbomeca Turmo IVA and Turmo IVC. Effective Dec 21, 2006 - [AD 2006-21-11](https://openairdocs.org/ad/2006-21-11) (historical): Flexible lubrication pipes · Turbomeca Turmo IVA and Turmo IVC. Effective Nov 3, 2006 - [AD 2003-11-09](https://openairdocs.org/ad/2003-11-09) (historical): Centrifugal Compressor Intake Wheel Blades · Turbomeca Turmo IVA and Turmo IVC. Effective Jul 3, 2003 ## Registered aircraft by registry model (OpenAirDocs) - [Turbomeca TURMO IVC](https://openairdocs.org/engine/turbomeca-turmo-ivc): 5 aircraft (registry code 60077) - [Turbomeca TURMO IV series](https://openairdocs.org/engine/turbomeca-turmo-iv-series): 1 aircraft (registry code 60008) - [Turbomeca TURMO IVA](https://openairdocs.org/engine/turbomeca-turmo-iva): 0 aircraft (registry code 60076) --- 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.