TCDS E00077EN

PAGE 1 2 3 4 5 REV. 1 1 1 1 0 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00077EN TCDS NUMBER E00077EN REVISION: Rev. 1 DATE: September 22, 2010 TURBOMECA MODEL: MAKILA 2A MAKILA 2A1 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00077EN) 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. 64511 Bordes Cedex France I. MODELS MAKILA 2A MAKILA 2A1 TYPE Twin spool (free turbine engine); turbosha ft engine for twin-engined helicopters; three stage axial compressor; single-stage centrifugal compressor; annular combustion chamber with centrifugal fuel injection; two-stage gas generator turbine; two-stage power turbine. RATINGS (See NOTE 7) 30-second OEI 2-minute OEI Continuous OEI 30-minute AEO Takeoff (5 minutes) Maximum continuous SHP (kw) 2358 (1758) 2226 (1660) 2109 (1573) 1747 (1303) 1747 (1303) 1747 (1303) SHP (kw) 2381 (1776) 2336 (1668) 2156 (1608) -.- -.- -.- FUEL Refer to the Installation and Operating Manual for a list of approved fuels and additives. OIL Refer to the Installation and Operating Manual for a list of approved oils. CERTIFICATION BASIS Makila 2A: FAR 21.29 a nd FAR 33 effective February 1, 1965, as amended by FAR 33-1 through 20. Pursuant to FAR 21.29(a)(1)(ii), this Type Certificate was issued in validation of the European Aviation Safety Agency (EASA) Certification Basis which was found to provide a level of safety equivalent to that provided by FAR 33, Amendment 33-20. EASA Certification Basis: Airworthiness Requirements: JAR-E Amendment 11 dated 1st November, 2001 Special Conditions: SC1: Special Conditions for approval of the 30-Second, 2-Minute OEI ratings SC2: Special Conditions for approval of a 30 Minutes AEO rating SC3: Special Condition for approval of th e software and programmed Logic Devices Exemptions: None Equivalent Safety Finding: JAR-E 570(a)(4)(ii) and (a)(5)(ii)- Indica tion to the flight crew of impending blockage for oil filter with a by-pass SC1 – Availability of 30 Second OEI rati ng during transition from the OEI training mode Environmental Standards: Compliance with the fuel venting provisions of ICAO Annex 16 (Amendment 5, November, 2005), Volume II, Part 2, Chapter 2 has been demonstrated on 01 June, 2007 TCDS E00077EN Page 2 of 5 MODEL APPLICATION DATE TYPE CERTIFICATE ISSUED / AMENDED TYPE CERTIFICATE SURRENDERED MAKILA 2A 9/21/2006 1/25/08 MAKILA2A1 3/23/2009 9/21/2010` 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 E00077EN is in a condition for safe operation and has undergone a final operational check. NOTES NOTE 1. MAXIMUM PERMISSIBLE OPERATING SPEEDS. For variation of these limits with outside air temperature, or if these limits are exceeded, refer to the Installation and Operating Manual. I. MODELS: MAKILA 2A MAKILA 2A1 A. GAS GENERATOR (N1) 30-second OEI 2-minute OEI Continuous OEI 30-minute AEO Takeoff (5 minutes) Maximum continuous Transient overspeed (20 seconds) % (RPM) 102.24% (33,943) 100.68% (33,425) 99.33% (32,977) 99.18% (32,927) 99.18% (32,927) 96.85% (32,155) 100.68% (33,425) %.............(RPM) 102.09% (33,895) 100.30% (33,302) 99.42% (33,008) 98.75% (32,786) 98.75% (32,786) 96.45% (32,022) 100.30% (33,302) 100% gas generator speed equals 33,200 rpm B. POWER TURBINE (N2) IDLE Mode Min stabilized Max stabilized FLIGHT Mode Min stabilized Max stabilized, 30 sec. OEI Max stabilized, other ratings Min Transient (20 secs.) Max Transient (20 secs.) % (RPM) 45% (10,333) 106% (24,340) 93% (21,355) 104.5% (23995) 106% (24,340) 80% (18,370) 111% (25,488) %..............(RPM) -.- -.- -.- - - -.- -.- -.- 100% power turbine speed equals 22,962 rpm NOTE 2. A. EXHAUST GAS (T45) MAXIMUM PERMISSIBLE TEMPERATURES. Refer to the Installation andOperating Manual for required action if limits are exceeded. Start-up: Unlimited duration Max overtemp (<5 secs) Max overtemp (<2 secs) In Flight: Continuous OEI 30 minute AEO Take-off Max Continuous 780 oC 830 oC 840oC 799oC 796oC 796oC 749oC -.- -.- -.- 814oC 801oC 801oC 754oC B. OIL Min for Starting Min for power-up Maximum MEASURED AT OIL-FUEL EXCHANGER OUTLET -30oC for 5 cSt oils (having a 5x10-6 m2/s kinematic viscosity) -45oC for 3 cSt or 4 cSt oils (having a 3x10-6 or 4x10-6 m2/s kinematic viscosity) 10oC for 5 cSt oils (having a 5x10-6 m2/s kinematic viscosity) -30oC for 3 cSt or 4 cSt oils (having a 3x10-6 or 4x10-6 m2/s kinematic viscosity) 120oC C. Fuel (See NOTE 8) Maximum MEASURED AT ENGINE INLET 50oC TCDS E00077EN Page 3 of 5 NOTE 3. NOTE 4. Fuel Oil POWER TURBINE OUTPUT SHAFT TORQUE LIMITS Maximum torque on engine output shaft is 406 ft-lb (551Nm) at the maximum continuous, takeoff and 30 minute all engine operative ratings. Maximum torque on engine output shaft at all One Engine Inoperative ratings is 688 ft-lb (933Nm). These torque values correspond to the engine torque limit. An engine electronic control limit may be implemented to protect the main gearbox of the helicopter. FUEL AND OIL PRESSURE LIMITS Normal operation minimum absolute fuel pressure at engine inlet - psia (kPa) Altitude From Idle (included) to T/O power (not included) From T/O power (included) to 30 second OEI power (included -2000 ft 9.3 (64) 6.1 (42) 0 ft 7.4 (51) 4.9 (34) 5,000 ft 6.8 (47) 4.5 (31) 10,000 5.1 (35) 3.2 (22) Starting or relight operation minimum relative fuel pressure at engine inlet: 3.6 psig (25 kPa) Maximum relative fuel pressure at engine inlet: 21.8 psig (150 kPa. Refer to the Installation and Operating Manual for additional information. Minimum relative oil pressure: 23.2 psig (160 kPa) Maximum relative oil pressure: 87.0 psig (600 kPa) NOTE 5. Max P3 air for A/C use: Max P24 air for A/C use: MAXIMUM PERMISSIBLE AIR BLEED - Standard day sea level condition. 0.485 lbm/sec (220 g/sec) at OEI Continuous 0.463 lbm/sec (210 g/sec) at Max Continuous 0.044 lbm/sec (20 g/sec) at Max Continuous Only in case of failure of the helic opter main gearbox lubricating system. For further information refer to the Installation manual. NOTE 6. AIR INTAKE REQUIREMENTS These engines have not been tested to evaluate the effects of foreign object ingestion in accordance with FAR 33.76 and FAR 33.77. Protection against foreign object ingestion must be provided by the installation. Refer to The Installation Manual The Makila 2A engine has been shown to comply with the induction system icing requirements of FAR 33.68 when tested with an air intake per Eurocopter France drawing numbers 332.A58.0013 (air intake with screen) or 332.A58.0041 (multi-purpose air intake). Refer to the Installation and Operating Manual for additional information. TCDS E00077EN Page 4 of 5 NOTE 7. ACCESSORY DRIVE PROVISIONS / ALL MODELS COMPONENT (*) ROTATIO N RPM REDUCTION RATIO Maximum Over- Torque mda.N (in-lb) Maximum Static Overhang Moment mda.N (in-lb) Shear Shaft Breaking- Torque mda.N (in-lb) Starter CW (1) 23,355 0.70350 2.8 (247.82) 0.4 (35.40) 6.1 (539.90) (*) CW = Clockwise (1) Direction of rotation of accessory drives is indicated with the off-take flange seen from outside; i.e., the direction of rotation of the accessory drive shaft on the engine. NOTE 8. Engine ratings are the minimum values defined under the following conditions: Static sea level standard conditions at 59 oF and 29.92 in/Hg. No airbleed, no accessory power offtake other th an that necessary for the engine operation. Engine equipped with test bed air intake and primary exhaust pipe. Mean swirl angle at the compressor air intake plane is less than or equal to 0.5 degrees. OEI Mode selected Output shaft rotational speed: 22962 rpm Lower fuel heating value: 18545 BTU/lbm (43,136 kJ/kg) NOTE 9. FUEL SUPPLY REQUIREMENTS Fuel supply from helicopter system must be delivered to the engine through a 10-micron filter provided by the aircraft manufacturer. NOTE 10. OIL SYSTEM: Refer to Installation and Operating Manual NOTE 11. ENGINE MONITORING TRANS MITTERS: Refer to the Installation and Operating Manual NOTE 12. ELECTRICAL EQUIPMENT: Refer to the Installation and Operating Manual NOTE 13. OIL BRANDS: Refer to the Installation and Operating Manual for approved oil brands. Mixing oils of different brands or specifications is prohibited. NOTE 14. FUEL AND FUEL ADDITIVES: Refer to the Installation and Operating Manual for specifications. NOTE 15. ENGINE AIRWORTHINESS LIMITATIONS: Li sted in the EASA-approved Maintenance Manual. NOTE 16. APPROVED MANUALS MAKILA 2A MAKILA 2A1 Installation Dwg and Manual X 298 N7 001 2 X298 N7 001 2 Operating Instructions X 298 N7 001 2 X298 N7 001 2 Performance Brochure X 298 N7 002 9 X298 U3 001 9 Maintenance Manual X 298 N7 450 1 X298 N7 450 1 Overhaul Manual X 298 N7 500 2 X298 N7 500 2 NOTE 17. TIME LIMITED DISPATCH: These engines have not been approved for time limited dispatch with any engine systems and equipment inoperative. NOTE 18. During normal operation the engine electronic cont rol receives electrical power from a dedicated engine driven alternator. A backup electrical power source must be provide by the aircraft. NOTE 19. The effects of an inoperative electronic control on aircraft operational characteristics must be evaluated prior to installation approval. TCDS E00077EN Page 5 of 5 NOTE 20 . SERVICE INFORMATION: Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA). 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…..