TCDS E12NE

U.S. DEPARTMENT OF TRANSPORTATION TCDS NUMBER E12NE REVISION: 6* DATE: January 11, 2023 FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E12NE SAFRAN HELICOPTER ENGINES MODELS: MAKILA 1A MAKILA 1A1 MAKILA 1A2 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E12NE) 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 Safran Helicopter Engines 64510 Bordes Cedex France TYPE CERTIFICATE (TC) RECORD Turbomeca S.A., until July 18, 2016. TYPE RATINGS (See NOTE 7) 30-second OEI 2-minute OEI 2-1/2 minute OEI 30-minute or continuous OEI Takeoff (5 minutes) Maximum continuous FUEL (See NOTE 14) OIL (See NOTE 13) MIL-L-7808 / MIL-L-23699 / AIR 3514 CERTIFICATION BASIS Makila 1A/1A1: FAR 21.29 and FAR 33 effective February 1, 1965, as amended by FAR 33-1 / -2 / -3 / -4 / -5 / -6 / -7 / -8. Makila 1A2: FAR 21.29 and FAR 33 effective February 1, 1965, as amended by FAR 33-1 / -2 / -3 / -4 / -5 / -6 / -7 / -8 and Special Condition No. SC-92-01-NE. MODEL APPLICATION DATE TYPE CERTIFICATE ISSUED / AMENDED TYPE CERTIFICATE SURRENDERED MAKILA 1A 03/07/78 04/13/81 MAKILA 1A1 03/28/85 MAKILA 1A2 07/07/89 03/17/92 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 E12NE. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of France. IMPORT REQUIREMENTS Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document) , and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. * LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" NOTICE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. PAGE 1 2 3 4 5 REV. 6 6 3 6 5 I. MODELS MAKILA 1A MAKILA 1A1 MAKILA 1A2 Twin spool (free turbine engine); turboshaft engine for twin-engine 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. SHP (kw) SHP (kw) SHP (kw) --- --- 2108(1573) --- --- 1966(1467) 1756(1310) 1877(1400) --- 1662(1240) 1783(1330) 1903(1420) 1662(1240) 1819(1357) 1844(1376) 1515(1130) 1589(1185) 1657(1236) TCDS E12NE Page 2 of 5 NOTE 1. MAXIMUM PERMISSIBLE OPERATING SPEEDS. For variation of these limits with OAT, refer to Operation Manual. If these limits are exceeded, refer to Operation Manual. I. MODELS: A. GAS GENERATOR (Ng) RPM 30-second OEI 2-minute OEI 2-1/2 minute OEI 30-minute or continuous OEI Takeoff (5 minutes) Maximum continuous Transient overspeed (20 seconds) B. POWER TURBINE SPEED (Np) RPM Maximum stabilized Maximum Transient (20 seconds) 100% power turbine speed equals NOTE 2. A. EXHAUST GAS (T4) 2-1/2 minute OEI 30-minute or continuous `OEI Takeoff (5 minutes) Maximum continuous Starting Transient (5 seconds) Transient (2 seconds) Transient (5 seconds) Transient (2 seconds) NOTE 2. (Continued) B. OIL Maximum operating Minimum for starting MAXIMUM PERMISSIBLE TEMPERATURES. Refer to Operation Manual for required action if limits are exceeded. MEASURED WITH FOUR THERMOCOUPLES ON GAS GENERATOR EXHAUST DIFFUSER 810oC 775oC 830oC 785oC --- 840oC 785oC 735oC 750oC 800oC 810oC --- --- 795oC - - - - 800oC (1) 810oC (1) 820oC (2) 850oC (2) 825oC 770 oC - - - -800oC (3) - -810oC (3) - -820oC (4) - -850oC (4) (1) Altitude less than 6,000 meters (2) Altitude equal to or greater than 6,000 meters (3) Altitude less than 6,100 meters (4) Altitude equal to or greater than 6,100 meters MEASURED AT OIL-FUEL EXCHANGER OUTLET +120oC Between -50oC and -30oC, according to oil specifications. Refer to Operation Manual. C. Fuel (See NOTE 8) Maximum operating MEASURED AT ENGINE INLET +50oC NOTES MAKILA 1A MAKILA 1A1 MAKILA 1A2 --- --- 34,650 --- --- 33,815 34,000 - - --- 33,200 - - 33,450 33,200 33,350 33,270 32,500 32,300 32,335 34,900 - - 33,625 100% gas generator speed equals 33,200 rpm 23,764 - - 23,880 26,735 - - 27,072 22,850 - - 22,962 TCDS E12NE Page 3 of 5 NOTE 3. Fuel Oil FUEL AND OIL PRESSURE LIMITS (psig) Refer to Operation Manual Minimum 24.7 psig, measured at engine pump outlet, after filter NOTE 4. Maximum air mass flow MAXIMUM PERMISSIBLE AIR BLEED (P2 air bleed from centrifugal compressor plenum). Standard day sea level condition. 0.035 lb/second at maximum continuous rating NOTE 5. AIR INTAKE REQUIREMENTS These engines have not been tested in icing conditions in accordance with FAR 33.68. These engines have not been tested to evaluate the effects of foreign object ingestion in accordance with FAR 33.77. Operation under icing conditions and protection against foreign object ingestion should be evaluated before installation approval and suitable protection devices should be provided as required. Protection grid as defined by SNIAS drawing numbers 332 A58 0050 / 332 A58 0054 - 06 / -07 / -08 / and -09 meet the requirements of FAR 33.77. NOTE 6. ACCESSORY DRIVE PROVISIONS / ALL MODELS COMPONENT (*) ROTATION RPM REDUCTION RATIO Maximum Permanent Power (kw/shp) Maximum Over- Torque m.da.N (in-lb) Maximum Static Overhang Moment Shear Shaft Breaking- Torque m.da.N (in-lb) Generator rotor CCW (1) 33,200 0.70350 Starter CW (2) 23,355 1.7 (148) 0.5 (43.5) 6.6 to 7.4 (547- 643) Oil pump unit (3) CCW (2) 4,184 0.12602 Fuel pump & governor CW (2) 4,184 0.12602 Free turbine rotor MAKILA 1A CCW (1) 22,850 1240 / 1662 MAKILA 1A1 CCW (1) 22,850 1357 / 1818 MAKILA 1A2 CCW (1) 22,962 1292 / 1732 (*) CCW = Counterclockwise / CW = Clockwise (1) Direction of rotation of engine rotors and main drives is indicated according to French standard MF-L-85010: i.e., engine observed aft looking forward. (2) 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. (3) Integrated accessories (engine internal accessories); otherwise data not given. TCDS E12NE Page 4 of 5 NOTE 7. Engine ratings are based on calibrated static test stand performance under the following conditions: Static sea level standard conditions at 59oF and 29.92 in/Hg. No airbleed, no accessory power offtake other than that necessary for the engine running. For the Makila 1A and 1A1: 22,850-rpm power shaft speed. For the Makila 1A2: 22,962-rpm power shaft speed. FOR THE MAKILA 1A AND 1A1, the indicated ratings are minimum final test performance of production and overhaul engines measured with engine acceptance test specification Number 0.298.00.940.9, calibrated test bed air intake Number 6.202.88.704.0, and Turbomeca exhaust duct Number 0.301.51.755.0. FOR THE MAKILA 1A2, the indicated ratings are minimum final test performance of production and overhaul engines measured with engine acceptance test specification Number 0.298.00.950.0, calibrated test bed air intake Number 6.202.88.704.0, and Turbomeca exhaust duct Number 0.301.53.731.0. NOTE 8. FUEL SUPPLY REQUIREMENTS Fuel supply from helicopter system must be delivered to the engine through a 10-microm filter provided by the aircraft manufacturer. NOTE 9. OIL SYSTEM: Refer to Operation Manual NOTE 10. ENGINE MONITORING TRANSMITTERS: Refer to Operation Manual NOTE 11. ELECTRICAL EQUIPMENT: Refer to Operation Manual NOTE 12. ENGINE FIRE DETECTORS Six fire detectors are provided on the engine. The characteristics of the fire detectors are to be evaluated prior to approval of the engine installation. NOTE 13. OIL BRANDS: Refer to Operation Manual for approved oil brands. Mixing of different oil brands or specifications is prohibited. NOTE 14. FUEL AND FUEL ADDITIVES: Refer to Operation Manual for specifications. NOTE 15. Certain engine parts are life-limited. These limits are listed in the DGAC-approved Maintenance Manual, Chapter 5. NOTE 16. MANUALS REQUIRED BY far 33.5 MODELS MAKILA 1A MAKILA 1A1 MAKILA 1A2 Operation manual 298 01 930 / 298 01 933 298 01 930 / 298 01 933 X 298 H2 101 1 / X 298 H2 101 2 Installation manual 298 00 930 / 298 00 931 X 298 EO 001 1 / X 298 EO 001 2 X 298 H2 001 1 / X 298 H2 001 2 Performance brochure N/A X 298 EO 001 9 X 298 H2 202 9 Maintenance manual X 298 76 460 1 X 298 EO 460 1 X 298 H2 400 2 Overhaul manual 298 01 935 298 01 935 298 01 935 NOTE 17. Engine maintenance program requirements are defined in the approved Maintenance Manual. NOTE 18. The electronic section of the fuel control will be located in the airframe in accordance with applicable Installation Manual requirements and Turbomeca Drawing Number 0 177 69 9000. TCDS E12NE Page 5 of 5 NOTE 19. The electronic control must receive electrical power from two separate and independent buses, either one of which is capable of supplying the full electrical needs of the control, or to be switched to an independent secondary bus in the event of a failure of the primary bus. NOTE 20. The effects of an inoperative electronic control on aircraft operational characteristics must be evaluated prior to installation approval. NOTE 21 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…..