TCDS E00096EN

Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00096EN) 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: Safran Helicopter Engines, S. A. 64510 Bordes France TYPE The ARRANO 1 series turboshaft engines have an annular air inlet integrating inlet guide vanes, a two-stage centrifugal compressor driven by a single-stage high pressure turbine, a reverse flow combustion chamber and a single-stage low pressure turbine (power turbine) driving a reduction gearbox located at the front of the engine and an exhaust pipe. The high pressure (gas generator) shaft drives the accessory gearbox. The engine is controlled by a Full Authority Digital Electronic Control (FADEC). I. MODELS ARRANO 1A RATINGS (See NOTE 1), shaft hp (kW) Maximum continuous 990 (738) Takeoff (5 minutes) 1141 (851) 30-minute All Engines Operating (AEO ) 1141 (851) Continuous One Engine Inoperative (OEI) 1239 (924) 2 min OEI 1394 (1040) 30 sec OEI 1467 (1094) PRINCIPAL DIMENSIONS, inches (mm) Length 48 (1219) Width 24.5 (623.2) Height 32.2 (817) CENTER OF GRAVITY Refer to Installation and Operating Manual WEIGHT - Completely equipped with EECU, pounds (kg) 381.4 (173.5) LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" INDICATES “NOT APPLICABLE" U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET TCDS NUMBER E00096EN REVISION: 2 DATE: October 30, 2025 SAFRAN HELICOPTER ENGINES, S. A. MODELS: ARRANO 1A PAGE 1 2 3 4 5 6 7 8 REV. 2 2 0 0 2 1 0 1 TCDS E00096EN Page 2 of 8 CONTROL SYSTEM Dual channel electronic engine control system FUEL CONTROL Refer to Installation and Operating Manual DRIVE SHAFT TYPE Refer to Installation and Operating Manual IGNITION High energy ignition generator with dual output, 2 Igniter plugs and cables STARTING The automatic starting sequence is ensured by the Engine Electronic Control Unit using the aircraft starter generator. APPROVED FUELS Refer to Installation and Operating Manual for approved fuel and additive specifications. APPROVED OILS Refer to Installation and Operating Manual for approved oil specifications. EQUIPMENT The equipment necessary to operate the engine and that is not included in the Engine Type Design Definition is defined in the applicable Installation and Operating Manual. CERTIFICATION BASIS ARRANO 1A Airworthiness Standards: 14 CFR, Part 33, effective February 1, 1965, as amended by 33-1 through 33-34 Special condition: • 33-20-01-SC, 30 min AEO power rating An Equivalent Level of Safety Finding has been made for the following regulation: • 14 CFR 33.27(c) and 33.27(f), Partial Shaft Excursion for Overspeed Evaluation (documented in ELOS Memo TC04141EN-E-P-4) The European Aviation Safety Agency (EASA) originally type certificated this engine on June 18, 2019. The FAA validated this product under U.S. Type Certificate Number E00096EN, on December 23, 2020. APPLICATION MODEL DATE ISSUED DELETED ARRANO 1A August 29, 2019 December 23, 2020 TCDS E00096EN Page 3 of 8 NOTES NOTE 1. ENGINE RATINGS The performance values specified are defined in the Installation and Operating Manual and correspond to minimum values at 109% N2 under the following conditions: - Uninstalled performance ; - Worst aged engine ; - No temperature, pressure or flow angle distortion at air inlet ; - Power measured on engine test bed with reference exhaust ; - Sea Level Static, ISA condition ; - No back pressure downstream of the exhaust pipe ; - No air bleed ; - No electrical power off-take ; - No power drawn by any accessories other than those required for engine operation; - Fuel heating value at 43 136 kJ/kg ; - Humidity considered is the reference value of 0.0069 kg/kg dry air humidity mixing ratio, which corresponds to 65% relative humidity at sea level ISA condition ; - Torque limits presented in NOTE 20. NOTE 2. TEMPERATURE LIMITS MAXIMUM EXHAUST GAS TEMPERATURE (T45 °C) Measured with thermocouples at the gas generator turbine outlet ARRANO 1A Takeoff 912 Maximum continuous 886 30-minute AEO 912 Continuous OEI 914 2 min OEI 957 30 sec OEI 991 AEO Transient (20 second limit) 934 Starting (unlimited) 800 Starting (maximum over-temperature): 850 APU mode 665 FUEL TEMPERATURE (°C) Measured at engine inlet ARRANO 1A Maximum operating temperature: +57°C Minimum fuel temperature for operating, starting and restart envelope: The highest temperature between -45°C and Freezing point temperature defined for the applicable fuel standard. Refer to the Installation and Operating Manual for detailed definition and limitations of normal fuels usage. The minimum fuel temperature is subject, for certain fuels, to mandatory use of anti-icing additive for temperatures below -30°C. Refer to the Installation and Operating Manual for further details. TCDS E00096EN Page 4 of 8 NOTE 2. continued OIL TEMPERATURE (°C) Measured at the oil filter outlet. ARRANO 1A Maximum operating temperature: 115°C Minimum oil temperature for starting: -36°C for oils with viscosity rating of 5 cSt -45°C for oils with viscosity rating of 3 cSt Minimum oil temperature before applying power: • Without anti-icing additives in fuel, the minimum oil temperature before applying power is +20 °C. The authorization of applying power is given by the flag “powering up not allowed” set to 0 ; • With anti-icing additives in fuel, the minimum oil temperature before applying power is 0 °C. During the oil warm-up period, the engine shall be run in APU mode or in IDLE mode, or in FLIGHT mode with the minimum collective pitch position. Refer to Installation and Operating Manual for detailed oil temperature limitations NOTE 3. PRESSURE LIMITS FUEL ARRANO 1A Detailed information about fuel pressures depending on atmospheric conditions and fuel specifications are provided in the Installation and Operating Manual. OIL ARRANO 1A Normal oil pressure during operation: between 58 PSI (400 kPa) (relative pressure) and 130.5 PSI (900 kPa) (relative pressure). Minimum and Maximum level warnings are functions of N1 and oil temperature NOTE 4. ACCESSORY DRIVE PROVISIONS NOTE 5. MODEL DESCRIPTION ARRANO 1A: Base model NOTE 6. ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES, WITH AIRCRAFT LEVEL REQUIREMENTS, PROVIDED AS PART OF ENGINE TYPE DESIGN Refer to Installation and Operating Manual NOTE 7. AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES INSTALLED ON THE ENGINE BUT ARE NOT PROVIDED AS PART OF ENGINE TYPE DESIGN Refer to Installation and Operating Manual NOTE 8. SPECIAL ANTI-ICING OR DE-ICING REQUIREMENTS Refer to NOTE 2 and the Installation and Operating Manual for requirements for the use of fuel anti-icing additives. ARRANO 1A ACCESSORY / Direction* of Nominal RPM Maximum Steady Maximum Torque at Maximum Static Overhung Moment DRIVE Rotation State Power Overload (in-lb) Allowable for HP Accessories (in-lb) Starter-Generator CW 11,727 (100% N1) 17.4 708.1 221.3 * CW = REFERENCE FACING ENGINE ACCESSORY PAD CLOCKWISE TCDS E00096EN Page 5 of 8 NOTE 9. ENGINE MOUNT SYSTEM PROVISIONS Refer to Installation and Operating Manual NOTE 10. POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS Not Applicable NOTE 11. SPECIAL INSTALLATION REQUIREMENTS AIR INTAKE REQUIREMENTS The engine was certified for ingestion of birds, hail, rain and snow based on the capability of the aircraft inlet design as defined in the Installation and Operating Manual. The following inlets have been approved for use with this engine: ECP H160.001893 and ECP H160.000900 INSTALLATION CONDITIONS ARRANO 1A EECU shall be installed outside of a designated fire zone and outside of a zone that might lead to overheat conditions. Corresponding installation assumptions are defined in the Installation and Operating Manual. Fire detection is not part of the Engine design and is under Helicopter manufacturer responsibility. LIGHTNING AND ELECTROMAGNETIC INTERFERENCES PROTECTION Qualified environmental conditions of the ARRANO 1A control system components, including EMI and HIRF, are detailed in the Installation and Operating Manual. TIME LIMITED DISPATCH ARRANO 1A has been approved for Time Limited Dispatch. The maximum rectification period for each dispatchable state is specified in the Airworthiness Limitations Section of the Maintenance Manual. The TLD dispatchable fault configurations are defined in the Installation and Operating Manual. (See NOTE 15) EMISSIONS STANDARDS The following emissions standards promulgated in 14 CFR Part 34, Amendment 5A, effective October 23, 2013 have been complied with for the ARRANO 1A: • Fuel Venting Emission Standards: 14 CFR 34.11 OVERSPEED PROTECTION ARRANO 1A is equipped with a power turbine overspeed shutdown device. Refer to the Installation and Operating Manual for additional details. NOTE 12. MANUFACTURER’S SERVICE BULLETINS OR OTHER INSTRUCTIONS COVERING MATTERS OF INTEREST Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or approved under EASA.21J.070. 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, • Design changes. These approvals pertain to the type design only. NOTE 13. SPECIAL OPERATING PROCEDURES OEI TRAINING MODE ARRANO 1A EECU features an OEI TRAINING mode for training crews in the event of engine failure. Refer to the applicable Installation and Operating Manual for additional details. APU MODE ARRANO 1A engine has APU mode capability. Use conditions of APU mode are defined in Installation and Operating Manual. TCDS E00096EN Page 6 of 8 NOTE 14. SPECIAL REPAIR OR OVERHAUL LIMITATIONS Not Applicable NOTE 15. APPLICABLE INSTALLATION, MAINTENANCE AND OVERHAUL MANUALS MANUALS REQUIRED BY 14 CFR PART 33.5: ARRANO 1A Installation and Performance Manual Operating Manual X3561A0022 X3561A0012 Installation and Operating Manual includes System Description and Time Limited Dispatch Summary. The manuals listed above have been accepted or approved per 14 CFR 33.5 MANUALS REQUIRED BY 14 CFR PART 33.4: ARRANO 1A Maintenance Manual Overhaul Manual Maintenance Manual Time Limited Dispatch Trouble Shooting Book Summary X3561A4602 X3561A5002 X3561A4612 X3561A4602 Component Service Letters and Maintenance Manuals Service Bulletins Various Refer to the SL and SB directory The manuals listed above have been accepted or approved per 14 CFR 33.4 NOTE 16. IMPORT REQUIREMENTS: To be considered eligible for installation on U.S. registered aircraft, each new engine to be exported to the United States with EASA airworthiness approval shall have EASA Form 1, Authorized Release Certificate. The EASA Form 1 should state that the engine conforms to the type design approved under the U.S. Type Certificate E00096EN, is in a condition for safe operation and has undergone a final operational check. Additional guidance is contained in FAA Advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, Engines, Propellers and Related Products Imported into the United States. NOTE 17. LIFE LIMITED PART INFORMATION: Life-limited components are listed in Chapter 05 of the engine Maintenance Manual. NOTE 18. MILITARY MODEL INFORMATION: Not applicable. TCDS E00096EN Page 7 of 8 NOTE 19. PERMISSIBLE ENGINE ROTOR AND OUTPUT SHAFT SPEEDS: GAS GENERATOR SPEED (PERCENT N1) ARRANO 1A 100% N1 = 44,139 rpm In-flight and APU mode Minimum speeds: Idle Mode (1) Idle with PT locked APU Mode Flight Mode (2) 57% 57% 59.8% 69.8 (1) This speed corresponds to the minimum stabilized N1 speed in IDLE mode with N2=80% (2) This speed corresponds to the minimum stabilized N1 speed in FLIGHT mode with N2=100% In-flight maximum speeds, All Engine Operative (*): Take-off (5 minutes) 30-minute AEO Maximum Continuous AEO transient (20 seconds) 104% 104% 103% 105.5% In-flight maximum speeds, One Engine Inoperative: 30-second OEI 2-minute OEI Continuous OEI 107.8% 105.6% 104.5% POWER TURBINE SPEED (PERCENT N2) ARRANO 1A 100% N2 = 34,767 rpm (power turbine) 100% N2 = 7,939 rpm on the power drive. In flight Minimum Speeds: Stabilized Transient (20 seconds) 90% 70% Operation with turbine locked is only authorized in APU mode and for engine starting In flight Maximum Speeds: Stabilized 109% A Maximum Inadvertent Overspeed of 115% has been certified for the ARRANO 1A model. This corresponds to the maximum N2 speed for which inadvertent occurrence of up to 20 seconds has been demonstrated not to require rejection of the engine from service or maintenance action (other than to correct the cause). TCDS E00096EN Page 8 of 8 ----END---- NOTE 20. MAXIMUM OUTPUT/SHAFT TORQUE LIMITS (N.m) Maximum torque, All Engines Operative (1): Take-off 30-minute Maximum AEO transient (5 minutes) AEO Continuous (20 seconds) (2) 940 940 816 940 Maximum torque, One Engine Inoperative (2): 30 second OEI 2 minute OEI Continuous OEI 1327 1176 1033 (1) For AEO ratings, torque values presented above correspond to the maximum torque validated for the engine. (2) For OEI ratings and AEO transient 20s, engine torque values are limited by torque toppings sent by the helicopter on ARINC frame to the EECU in order to protect the helicopter main gearbox. Values presented above correspond to the maximum value of the torque topping range authorized by the EECU for each power rating. For further details refer to Installation and Operating Manual. NOTE 21. MAXIMUM PERMISSIBLE P3 AIR BLEED FROM THE OUTLET OF THE 2ND STAGE CENTRIFUGAL COMPRESSOR Maximum air mass flow: P3 air bleed extraction for helicopter use is limited by the section of the P3 extraction restrictor. The maximum possible extraction is 205 g/s and corresponds to Take-Off power at ISA Sea Level conditions. For any other operating point, refer to Installation and Operating Manual Power loss due to air bleed: Refer to Installation and Operating Manual. NOTE 22. ROTOR DISK INTEGRITY AND ROTOR BLADE CONTAINMENT (WHERE SPECIAL REQUIREMENTS APPLY) Not applicable. NOTE 23. SOFTWARE: The ARRANO 1A EECU software has been validated in accordance with the requirements of DO-178B guidelines for a level A software.