# TCDS E-300: Turbomeca S.A. - Type: Type certificate data sheet - Status: Current - Holder: Turbomeca S.A. - Revision: 7 - Revised: March 20, 2007 - Product: Engine - Certification basis: CAR 10 - Registered aircraft: 5, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/44/6e/446ebf3ab8063add29ea377749315897d3f58de93f5cc3d72fefbc34439bbdb1 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/9F4B467066E6E233862572A500750384.0001 - Page: https://openairdocs.org/tcds/E-300 ## Models (6) As the data sheet lists them. - Artouste IIB1 - Artouste IIC - Artouste IIC2 - Artouste IIC1 - Artouste IIC6 - Artouste IIC5 ## 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 Rev. No. 7 7 6 7 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E-300 Revision 7 TURBOMECA ARTOUSTE IIB1 IIC, IIC1, IIC2, IIC5, IIC6 March 20, 2007 TYPE CERTIFICATE DATA SHEET NO E-300 Engines of models described herein conforming with this data sheet (which is a part of engine type certificate No. 300) 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 Civil Air 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 Model Artouste IIB1 IIC, IIC1, IIC2, IIC5, I I C 6 Type Turboshaft for Single stage centrifugal compressor - - helicopters Annular combustion chamber Two stage turbine 5.803:1 reduction gearing Rating Maximum continuous at sea level, Shaft hp., r.p.m. 330-34000 - - Takeoff (5 min.) at sea level), Shaft hp, r.p.m. 400-34000 - - Drive shaft type Fuel control,Turbomeca Governor 064.14.000 064.28.000 or 064.37000 or 064.37.000 Turbomeca Automatic 077.13.000 077.28.000 Starting Box or 077.37.000 or 077.37.000 Turbomeca Micropump 044.38.000 - - (for starting) or 044.56.000 - - Fuel (See NOTE 9) Approved Specification (latest amendment): JP.1 (MIL.F.5616) or JP-4 (MIL-T-5624) British D.Eng. R.D. 2482 or R.D. 2486 France TRO (AIR 3405) or TR4 (AIR 3407) JP.5 (MIL-J-5624) French TR5 (AIR 3404) British D.Eng. R.D. 2488 or R.D. 2498 Aviation Gasoline (MIL-G-5572 or MIL-G-3056) British D.Eng. R.D. 2485 or DEF 2401 French MT 80 (AIR 3401) Diesel Fuel (MIL-F-16884 Type I and Type II French 47.0 Dieso Illuminating Oil (Kerosene) Automotive Diesel Oil 2 E-300 Oil (See NOTE 1) (F or ambient air above 14°) Shell Turbine Oil 9 Esso Turbine Oil 57 Caltex Jet Engine Oil Heavy British DED 2479 French AIR 3512 (For ambient air lower then 14 °F) Shell Turbine Oil 3 Esso Aviation Utility Oil F Caltex Jet Engine Oil Medium Heavy British DED 2490 or DEF 2001 French AIR 3515 Caltex Aircraft Instrument Oil (For ambient air between 5 °F and 41°F) British DED 2480 I I B 1 IIC, IIC1, IIC2, IIC5, IIC6 Principal Dimensions: Length, in. 54.4 58.13 Width, in. 29.9 29.9 Height, in. 27.0 26.65 C. G. Location: Aft of front mounts, in. 8.56 9.61 Weight (dry), lbs. (Includes weight of clutch, 44 lb.) 342 360 Ignition system Low energy type (24 volt supply) with 2 Turbomeca 056.31.750 or .751 or 223.30.750 torch igniters Dual ignition coil RB Ducellier AV type A or air equipment 81264 NOTES 1, 2, 3, 4, 5, 6, 7, 8, 9, 10 - - “- -” indicates “same as preceding model.” Certification basis CAR 10. Engine Type Cer tificate No. 300 issued January 13, 1958, amended January 20, 1960 to include IIC, am ended August 28, 1968, to include IIC1, IIC2, IIC5, and IIC6. Date of application for Type Certificate: November 22, 1955 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 E-300 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 E-300 is in a condition for safe operation and has undergone a final operational check. NOTES: Note 1. Maximum perm issible temperatures: Turbine exhaust gas temperatures: IIB1 IIC, IIC1, IIC2, IIC5, IIC6 Takeoff 1125°F (607°C) 1035°F (557°C) Maximum continuous 950°F (510°C) 950°F (510°C) Maximum transient 1040°F (560°C) 1022°F (550°C) The turbine exhaust gas temperat ure is measured by 4 thermocouples. Oil inlet temperature: 68° to 175°F (20° to 80°C) For ambient air te mperatures 14°F and above with appropriate grade of oil per manual. 32° to 86°F (0° to 30°C) For ambient ai r temperatures below 14°F with appropriate grade of oil per manual. 3 E-300 NOTE 2. Fuel and oil pressure limits: Fuel, at engine inlet, 4.0 to 4.5 p.s.i.g. Oil, normal pressures are 30 to 60 p.s.i.g., ex cept minimum of 10 p.s.i.g. is permitted for idling. 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. At the exhaust gas temperatures stamped on each engine. This temperature will vary somewhat but will be no higher than 1100°F (593°C) for IIB1, 1010°F (543°C) for IIC, IIC1, IIC2, IIC5, IIC6 for all engines at takeoff power, which corres ponds to a turbine inlet temperature of 1480°F (804°C) for IIB1, 1385°F (752°C) for IIC, IIC1, IIC2, IIC5, IIC6. Exhaust gas temperatures are measured by the 4 Turbomeca thermocouples installed on each engine. A typical jet pipe, although the engine is not sensitive to small differences in tailpipes. NOTE 4. The following aircraft accessories provisions are provided on the engine: Drive Rotation (facing drive) Speed Ratio Continued Torque (in. lb.) Static Torque (in. lb.) Starter-generator (Labavia DD 2501A) Counter clockwise 1:5.108 85 520 Tachometer (AMA/G32/type 110) Clockwise 1:10 - 10 NOTE 5. Maximum air bleed for aircraft se rvices is .067 lb/sec. at sea level. NOTE 6. This engine is for use on helic opters and includes the following equipment: Drive clutch assembly for main drive Overload signaling device Isochronous speed govering system Automatic sequency device for starting NOTE 7. This engine meets FAA require ments for adequate turbine disc 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. (a) Use of any of the specified alternate fu els does not require readjustment of fuel controls Use of leaded Aviation Gasoline as an altern ate fuel is limited to no more than 25 hours between overhauls as engine power output will decrease significantly with its extended use. (b) When Marine Diesel Fuel is used, the out side air temperature must be above +5°F (-15°C). (c) When JP5 is used, its speci fic gravity must be below 0.8. (d) When gasoline is used, it is recommended to add 1% oil. (e) Illuminating oil (kerosene) to be us ed must have the following characteristics: Sulphur: Less than 0.2% flash point Not less than 100°F (38°C), freezing point Not greater than -40°F (-40°C) (f) Automotive diesel oil must not be used when th e outside air temperature is below 32°F (0°C). Its characteristics must be: Sulpnur: Less than 1% , kinematic viscosity at 68°F (20°C) Less than 9 centistokes NOTE 10. (a) The models IIC and IIC 1 are similar to the IIB1 except for improved design for the turbine section and stators. (b) The model IIC2 is similar to the IIC and IIC 1 except for improvement in the intake and reduction gear casing design. (c) The model IIC5 is similar to the IIC1 except for steel inducer instead of aluminum alloy and new combustion chamber outer liner. (d) The model IIC6 is similar to the IIC5 except for the improvement in the intake and reduction gear casing design. 4 E-300 NOTE 11 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 (1, in force first) - [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 ## Registered aircraft by registry model (OpenAirDocs) - [Turbomeca ARTOUSTE IIC6](https://openairdocs.org/engine/turbomeca-artouste-iic6): 3 aircraft (registry code 60065) - [Turbomeca ARTOUSTE IIB1](https://openairdocs.org/engine/turbomeca-artouste-iib1): 2 aircraft (registry code 60060) - [Turbomeca ARTOUSTE IIC](https://openairdocs.org/engine/turbomeca-artouste-iic): 0 aircraft (registry code 60061) - [Turbomeca ARTOUSTE IIC1](https://openairdocs.org/engine/turbomeca-artouste-iic1): 0 aircraft (registry code 60062) - [Turbomeca ARTOUSTE IIC2](https://openairdocs.org/engine/turbomeca-artouste-iic2): 0 aircraft (registry code 60063) - [Turbomeca ARTOUSTE IIC5](https://openairdocs.org/engine/turbomeca-artouste-iic5): 0 aircraft (registry code 60064) --- 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.