# TCDS E1IN: Turbomeca S.A. - Type: Type certificate data sheet - Status: Current - Holder: Turbomeca S.A. - Revision: 7 - Revised: March 20, 2007 - Product: Engine - Certification basis: Part 21, CAR 10 - Registered aircraft: 15, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/79/10/791060441d9ccb68fe863ceb8308029c9e1732dc76203b5b1082e2e0edabfe2b - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/E0D83FA7786B93DE862572A50073268A.0001 - Page: https://openairdocs.org/tcds/E1IN ## Models (3) As the data sheet lists them. - Artouste IIIB1 - Artouste IIIB - Artouste IIID ## 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. 7 7 6 6 7 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E1IN Revision 7 TURBOMECA Artouste 111B Artouste 111B1 Artouste 111D March 20, 2007 TYPE CERTIFICATE DATA SHEET E1IN Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E1IN) 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: Turbomeca S.A. 64 511 Bordes Cedex France I. MODELS Artouste IIIB Artouste IIIB1 Artouste IIID TYPE Turboshaft for single stage axial compressor - - - -(see NOTE 11) helicopters single stage centrifugal compressor - - - - annular combustion chamber - - - - three stage turbine - - - - 5.802:1 reduction gearing - - 5.7131:1 reduction gearing RATING (See NOTE 3) - - - - Maximum continuous at sea 690 - 33,500 (+1000 rpm transients permitted - - - - level, shaft hp., r.p.m. (Limited to 543 HP by engine gear box)(405kw) - - - - Takeoff at sea level, 858 - 33,500 (+1000 rpm transients permitted) - - - - Shaft hp., r.p.m. (T.O. power limited to 5 min.) )limited to 563 HP by engine gear box)(420kw) (limited to 590 HP by engine gear box) (440kw) - - Drive shaft type Special, 24 internal involute splines according to and 20006 type XVID specification, pitch circle diameter, in : 1.20 - - - - Fuel Control Turbomeca governor, 0.64.39.000.0 or 0.064.39.500.0 - - 0.64.39.501.0 Turbomeca fuel pump, 0.044.49.000.0 or 0.044.49.501.0 - - 0.044.49.502.0 Semca fuel cock, 0.100.85.725.0 or 0.202.12.788.0 - - 0.202.12.788.0 Turbomeca automatic starting box, 0.077.47.000.0 or 0. 077.51.502.0 - - 0.077.98.524.0 Turbomeca micropump (for starting) 0.044.56.000.0 or 0.044. 61.501.0 - - 0.044.61.501.0 FUEL See NOTE 9 LEGEND: “ - -” INDICATES “SAME AS PRECEDING MODEL” “ - - -” INDICATES “DOES NOT APPLY” 2 E1IN I. MODELS: Artouste IIIB, IIIB1 Artouste 111D OIL See NOTE 10 Principal dimensions Length, in. 71.4 - - Width, in. 20.5 21.85 Height, in. 26.25 24.70 C. G. Locations: Aft of front mounts, in. 18.1 - - Weight (dry) lb. 393 - - (includes all controls, fuel pump) starter-generator. Excludes tailpipe and oil tank). Ignition System Low energy type (27-vole supply) with two Turbomeca 0.206.30.773 or 0.237.30.775.0 torch igniters - - Dual ignition coil, Air-Equipment 81.264 or 81.268/10 - - Certification basis CAR 10 (FAR 21.29)Engine Type Certificate No. E1IN issued 27 March 1962. Date of Application for Type Certificate 18 February 1960. 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 E1IN. 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 E1IN, is in a condition for safe operation and has undergone a final operational check. NOTE 1. Maximum permissible te mperatures: Artouste IIIB, IIIB1 Artouste IIID Gas temperature at turbine outlet: Maximum takeoff (5 min.)550°C(1020°F) - - - - Maximum continuous 500°C (930°F) - - - - (The turbine exhaust gas te mperature is measured by 2 thermocouples.) Oil inlet temperatures for engine operation: 32° to 185°F (0° to 85°C) - - - - NOTE 2. Fuel and oil pressure limits: Fuel, at engine inlet:(4.3 to 11. 6 p.s.i.g. for starting) - - - - (-4.3 to 17.4 p.s.i.g. when operating) - - - - Oil (pressure at engine oil pump ou tlet) Normal: 20 to 70 psig - - - - Minimal:16 psig - - - - Minimum ground idle:10 psig - - - - NOTE 3. The engine ratings are the minimu m guaranteed and are based on the following: Static sea level standard conditions of 59°F, 29.92 in. Hg. No external air bleed or aircraft accessory power. A typical jet pipe, although the engine is not sensitive to small differences in tailpipes. Exhaust gas temperature is measured by the 2 Turbomeca thermocouples installed on each engine. 3 E1IN NOTE 4. The following drive provisions are provided on the engines: Rotation Speed Continuous Torque Static Torque Overhang Drive (facing drive) Ratio (in.-lb.) (in.-lb.) (in.-lb.) Acrouste IIIB Starter-generator, Counter-clockwise 1:5.1080 135 650 170 IIIB1 Labinal 2687 A or 1:5.0295 - - - - - - - - - IIID Artouste IIIB Tachometer,AMA C ounter-clockwise 1:10.00016 .02 10 6 IIIB1 Type 10 IIID NOTE 5. Production engines are normally provided with a sonic orifice limiting engine bleed air to 65 grams per second. When DGAC approved Turbomeca Mod. TU 1 is incorpor ated, bleed flow is orifice limited to 170 grams per second. Horsepower loss is 0.4 kilowatts pe r gram per second (243.5 HP/Lb/sec.) NOTE 6. The engine is for use on helicopters and includes the following special equipment: Isochronous speed governing system. Automatic sequence device for starting. NOTE 7. This engine meets FAA requireme nts for adequate turbine disk integrity and rotor blade containment and does not require external armoring. NOTE 8. This engine has no provision for anti-icing the inlet and has not been substantiated for use in icing weather. NOTE 9. Fuels shall conform to the speci fications as listed in the table below or to subsequent revisions thereof. The mixing of approved fuels is permitted subject to th e limitations specified under “Remarks: No adjustment of engine controls is necessary and no loss of performance occurs.” Normal fuels, unrestricted SPECIFICATIONS NATO FREEZING POINT ANTI- ICING FUEL TYPE SYMBOL USA UK FRANCE (Approximately) ADDITIVE Kerosene - 50 (AVTUR-FS-11) JP 8 F 34 MIL-T-83133 (JP 8) D.ENG.RD 2453 AIR 3405 F34 -50°C With Kerosene - 50 (AVTUR) JP 1 F 35 ASTM-D-1665 Jet A1 D.ENG.RD 2494 AIR 3405 F-35 -50°C Without Kerosene - - - ASTM-D-1655 Jet A - - - - - - -40°C Without Wide cut fuel (AVTAC FS 11) JP 4 F 40 MIL-T-5624 JP 4 D.ENG.RD 2454 AIR 3407 -58°C With Wide cut fuel (AVTAC) JP-4 - - - - - - D.ENG.RD 2486 - - - -58°C Without Wide cut fuel - - - ASTM-D-1655 Jet B - - - - - - -50°C Without High flash point Kerosene JP 5 (AVCAT) F 43 - - - D.Eng.RD 2498 AIR 3404 F-43 -46°C Without High flash point Kerosene JP 5 (AVCAT FS 11) F 44 MIL-T 5624 JP 5 D.ENG.RD\2 452 AIR 3404 F-44 -46° C With 4 E1IN SPECIFICATIONS FUEL TYPE NATO SYMBOL USA UK FRANCE RESTRICTIONS ON USE Aviation Type Gasoline (AVCAS) F 12 MIL-G-5527 Grade 80/87 - - - AIR 3401 80/87 -Maximum operating time on gasoline during any period between overhauls total 25 hours. F-18 MIL-G-5572 Grade 100/130 D.ENG.RD 2485 AIR 3401 100/130 Operating altitude range: row 0 to 4000 m OAT from -50°C to +30°C F 22 MIL-G-5572 - - - AIR 3401 115/145 - Add approx.2% of lubricating oil by volume (mineral based oil if possible). Automotive Gasoline F 46 MIL-G-3056 DEF 2402 DCEA/2MT80 -Use preferably the lowest possible lead content type of gasoline Automotive Diesel oil 1 - - - VVF 800 DF1 - - - - - - Not to be used at O.A.T.below- 15°C Automotive Diesel oil 2 F 54 VVF 800 DF2 TS 10 003 DCEA/21C Not to be used at O.A.T. below -5°C The extended use of those fuels is not recommended. The restrictions Artic Diesel Fuel F 56 VVF 800 DFA - - - - Not to be used at O.A.T. below -20°C connected with such a use and the associated maintenance Gasoil O F 75 MIL-F-16884 DEF 2 402 7 120 STM 47/0 Dieso Not to be used at O.A.T. below -5°C instructions should be assessed on a case by case basis. Gasoil 20 F 76 - - DEF 2 402 7 120 STM 47/20 Dieso Not to be used at O.A.T. below +0°C Illuminating Oil F 58 VVK 221 DEF 2 403 DCEA/11 C Not to be used at O.A.T. below -15°C Gasoline F 12 MIL-G-5572 (Grade 80/87) - - - AIR 3401 Maximum operating time on gasoline F 18 (Grade 100/130) D.ENG.RD 2485 AIR 3401 during any period between overhauls: 25 hours. F 22 (Grade 115/145) D.ENG.RD 2401 AIR 3401 Automotive Gasoline F 46 MIL-G-3056 DEF 2401 DCEA/ 2DMT80 Add 1 to 2% of lubricating oil by volume (mineral if possible) Automotive Diesel Oil F 54 VVF 800 DF2 TS.10.003 DCEA/21C Not to be used at OAT below -5°C - - - - - - VVF 800 DF1 - - - - - - Not to be used at OAT below -15°C F 56 VVF 800 DFA - - - - - - Gasoil O F 75 MIL-F-16684 DEF 2402 (47/0 DIESO) 7120 STM Not to be used at OAT below -5°C Gasoil 20 F 76 - - - DEF 2402 (47/20 DIESO) 7120 SIM Not to be used at OAT below -5°C Illuminating Oil F 58 VVK 211 DEF 2403 DCEA/11C Not to be used at OAT below -15°C 5 E1IN C - The following fuel additives are approved for use: - Anti-icing additive: AIR 3652, NATO S748, MIL-I-27686, D.ENG.RD 2451, PHILLIPS PFA-55 MB each is eligible up to .15% in volume, with or without glycerine. - Anti-static additive: SHELL ASR-3, up to 0.0001% in volume. NOTE 10. 4.2 APPROVED OILS SPECIFICATIONS FUEL TYPE NATO SYMBOL USA UK FRANCE RESTRICTIONS ON USE Mineral: Fluid 3 to 3.5 cSt at 98.9°C 0.135 - - - D.ENG.RD 2490 AIR 3515 Aeroshell oil 3 BP turbine oil 3 Esso aviation utility oil f EFF JET ENGINE OIL 15 CASTROLAERO CT 11 Synthetic fluid 3 to 3.9 cST at 98.9°C 0.148 MIL-L-7808 - - - - - - BP turbine oil 15 Castrol 3C CASTROL 325 Esso turbo oil 2389 Mobil oil Avrex 256 STAUFFER Jet oil 1 0.150 - - - - - - AIR 3514 ELF jet synthetic oil 15 Turbonycoil 13 B - - - - - - - - - - - - Aeroshell turbine oil 390 Synthetic Medium 5 cSt at 98.9°C OAT= -20°C 0.156 MIL-L- 23669 - - - - Elf Jet Synthetic oil 25 Esso Turbo oil 2380 Mobil Jet Oil 11 TURBONYCOIL 525 CASTROL 5 000 Aeroshell 500 Synthetic 7.5 cSt at 98.9°C 0.149 DER D 2487 CASTROL 98 AEROSHELL 750 ESSO TURBO OIL 274 OA = 10°C 0..159 - - - - AIR 3517 TURBONYCOIL 35 m TURBONYCOIL 35 A NOTE: 1. The oil brands are indicated in alphabetical order. 2. the specification should be at the latest amendment. 3. The use of different oil spec. or brands must be submitted to TURBOMECA for approval. 4. In case of change of oil brand or specification, flush through the oil system according to Maintenance Manual Instructions. NATO USA UK FRANCE` NOTES GREASES S 740 S 720 MIL-T 5544 MIL-M-7866 DTD 392 AIR 4247 AIR 4223 Storage Oils C 624 MIL-C-6529 Type III DTD 900/4426 DED 2490 DEF 2001 AIR 1504 AIR 3515 Fuel system and external spray NOTE 11 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 (8, in force first) - [AD 2007-19-11](https://openairdocs.org/ad/2007-19-11): Fuel pumps · Turbomeca Artouste IIIB, Artouste IIIB1 and Artouste IIID. Effective Oct 9, 2007 - [AD 2007-01-04](https://openairdocs.org/ad/2007-01-04): Lower union of the flexible fuel pipe · Turbomeca Artouste IIIB and Artouste IIIB1. Effective Jan 25, 2007 - [AD 2005-26-13](https://openairdocs.org/ad/2005-26-13): In-flight engine shutdown · Turbomeca Artouste IIIB, Artouste IIIB1 and Artouste IIID. Effective Feb 3, 2006 - [AD 2005-17-06](https://openairdocs.org/ad/2005-17-06): Engine air intake assembly · Turbomeca Artouste IIIB, Artouste IIIB1 and Artouste IIID. Effective Sep 27, 2005 - [AD 2001-12-19](https://openairdocs.org/ad/2001-12-19): Electrical Fuel Cock, · Turbomeca Artouste IIB1, Artouste IIC, Artouste IIC1 and 6 more. Effective Jul 26, 2001 - [AD 2006-04-15](https://openairdocs.org/ad/2006-04-15) (historical): Fuel pumps · Turbomeca Artouste IIIB, Artouste IIIB1 and Artouste IIID. Effective Mar 14, 2006 - [AD 2002-22-11](https://openairdocs.org/ad/2002-22-11) (historical): Injection wheel · Turbomeca Artouste IIIB, Artouste IIIB1 and Artouste IIID. Effective Dec 13, 2002 - [AD 2000-06-12](https://openairdocs.org/ad/2000-06-12) (historical): Smoke Emissions Checks · Turbomeca Artouste IIIB, Artouste IIIB1 and Artouste IIID. Effective Jun 12, 2000 ## Registered aircraft by registry model (OpenAirDocs) - [Turbomeca ARTOUSTEIIIB](https://openairdocs.org/engine/turbomeca-artousteiiib): 10 aircraft (registry code 60003) - [Turbomeca ARTOUSTEIIIB1](https://openairdocs.org/engine/turbomeca-artousteiiib1): 5 aircraft (registry code 60066) - [Turbomeca ARTOUSTE IIID](https://openairdocs.org/engine/turbomeca-artouste-iiid): 0 aircraft (registry code 60067) --- 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.