TCDS E00013LA

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E00013LA Revision 2 Honeywell Aerospace US LLC HTS900-2-1D March 27, 2026 TYPE CERTIFICATE DATA SHEET NO. E00013LA Engines of models described herein conforming with this data sheet (which is part of Type Certification No. E00013LA) 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 FAA approved manufacturer's manual and other FAA approved instructions. TYPE CERTIFICATE HOLDER: Honeywell Aerospace US LLC 111 South 34th Street Phoenix, AZ 85034 TYPE CERTIFICATE RECORD HOLDER: Honeywell International Inc. 111 South 34th Street Phoenix, AZ 85034 Page No. 1 2 3 4 5 Rev. No. 2 2 -- 1 1 I. MODELS HTS900-21D TYPE Free turbine turboshaft engine; two-stage centrifugal compressor; reverse-flow annular combustor; single-stage gas producer turbine; single-stage power turbine; front- mounted accessory/reduction gearbox. RATINGS (See NOTE 1) Maximum Continuous Output shaft horsepower, SHP Output shaft speed, rpm Takeoff (5 minute) Output shaft horsepower, SHP Output shaft speed, rpm 757 6,317 820 6317 REDUCTION GEAR RATIO (Output shaft speed to power turbine speed) 0.1654 LEGEND: “- -“ INDICATES “SAME AS PRECEDING MODEL” “---“ INDICATES “DOES NOT APPLY” NOTICE: SIGNIFICANT CHANGES ARE BLACK LINED IN THE LEFT MARGIN E00013LA 2 CONTROL SYSTEM The full-authority digital engine control (FADEC) system features a dual-channel electronic control unit (ECU) with an electromechanical manual mode backup, a fuel metering unit (FMU), harnesses, and sensors. Engine operation and condition are monitored through speed sensors mounted on the accessory/reduction gearbox, twelve measured gas temperature (MGT) thermocouples located between the gas producer turbine and the power turbine, and a hydromechanical torquemeter internal to the gearbox. FUEL Refer to the engine installation manual for approved fuel types, limitations on their use and approved fuel additives. (see NOTE 11) OIL Refer to the engine installation manual for approved oil types and brands. Installation of the engine must include a full flow scavenge oil strainer and chip detector. (see NOTE 11) PRINCIPAL DIMENSIONS & C.G. LOCATION Refer to engine installation manual. (see NOTE 11) WEIGHT (Dry), lb. (Includes standard equipment listed in the engine installation manual) 338 CERTIFICATION BASIS: Title 14 Code of Federal Regulations (CFR) part 33 effective February 1, 1965, as amended by 33-1 through 33-20, effective December 13, 2000. MODEL APPLICATION DATE TYPE CERTIFICATE ISSUED / AMENDED HTS900-2-1D November 17, 2005 December 23, 2008 PRODUCTION BASIS: Production Certificate No. 413NM, reissued on March 29, 2026, to Honeywell Aerospace US LLC NOTE 1: Engine ratings are based on calibrated stand performance under the following conditions: Static sea level conditions at 59 °F and 29.92 in. Hg. No inlet loss, bleed air extraction or customer power extraction. Reference exhaust duct as specified in the engine installation manual E00013LA 3 NOTE 2: Temperature Limits: HTS900-2-1D MEASURED GAS TEMPERATURE, °F (°C) as transmitted by the FADEC for display in the cockpit. Maximum Continuous 1,652 (900) Takeoff (5 minute) 1,757 (958) Transient (15 seconds) 1,790 (977) Starting 1,790 (977) OIL TEMPERATURE, °F (°C) measured at oil temperature bulb. Minimum for engine starting Refer to engine installation manual Minimum for operation above ground idle 50 (10) Minimum for operation above flight idle 150 (66) Maximum 230 (110) FUEL TEMPERATURE Refer to engine installation manual for starting and operating fuel inlet temperature limitations. (see NOTE 11) COMPONENT TEMPERATURE Refer to the installation manual for external component temperature limits. (see NOTE 11) NOTE 3: Operating Speed Limits: HTS900-2-1D GAS PRODUCER SPEED, rpm as transmitted by the FADEC for display in the cockpit (100% = 47,870 rpm) Maximum Continuous 48,410 Takeoff (5 minute) 49,570 Transient (15 seconds) 49,980 OUTPUT SHAFT SPEED, rpm as transmitted by the FADEC for display in the cockpit (100% = 6,317 rpm) Minimum governed speed 6,000 Maximum Continuous 6,633 Takeoff (5 minute) 6,633 Transient (15 seconds) 7,265 E00013LA 4 NOTE 4: Torque Limits: NOTE 5: Fuel and Oil Pressure Limits: NOTE 6: Drive Pad Drive Type Speed Ratio Rotating (Facing Pad) Maximum Continuous Extraction (7,000 rpm to maximum pad speed) Maximum Transient Extraction (7,000 rpm to maximum pad speed) Maximum Torque During Starts Maximu m Shear Torque of Mounted Accessory Starter/ generator AND20001 XIA (modified) * 0.2512 NG, 12,025 rpm at 100% CW 10.9 hp, except above 20,000 ft. altitude per operating limits in the engine installation manual 16.5 hp (2-min.)** 21.8 hp (5-sec.)** 500 in-lbf 1,100 in- lbf Auxiliary generator / alternator AND20002 XIIA (modified)* 0.3265 NP, 12,472 rpm at 100% CW 10.9 hp 16.5 hp (2-min.) 21.8 hp (5-sec.) N/A 1,100 in- lbf HTS900-2-1D OUTPUT SHAFT TORQUE, lb-ft as transmitted by the FADEC for display in the cockpit (100% = 629 lb-ft) Maximum Continuous 629 Takeoff (5 minute) 682 Transient (15 seconds) 760 HTS900-2-1D FUEL INLET PRESSURE Minimum fuel inlet pressure limits vary with fuel type, temperature and ambient conditions. Refer to the engine installation manual (see NOTE 11). Maximum (psig) 50 OIL PRESSURE Oil pressure limits vary with gas producer speed (NG) and oil temperature. Refer to the engine installation manual (see NOTE 11). E00013LA 5 CW = Clockwise NG = Gas producer speed NP = Power turbine speed * Limit pad speed and maximum loads modified. Refer to specification AND20001 Rev. 2, Drive – Type XI Engine Accessory, controlled by Army – Aviation Missile Command, and specification AND20002 Rev. 3, Drive – Type XII Engine Accessory, controlled by Air Force Material Command Logistics Support. Engine installation manual includes drive pad mounting limits and pad definition. (see NOTE 11) ** Engine operation with starter/generator pad power extraction in excess of the maximum continuous value has not been verified to be surge free. NOTE 7: Maximum permissible bleed air extraction at the customer bleed port is 5% of inlet airflow. NOTE 8: The engine complies with induction system icing and the ice ingestion requirements of 14 CFR §§ 33.68 and 33.77, provided that the applicable airframe inlet screens, filters, particle separators, and bypass systems are sized to prevent the passage of objects greater than 0.50 inch diameter. Details of the ice ingestion limits based on engine type certification testing are defined in the engine installation manual. (see NOTE 11) NOTE 9: Certain engine parts are life-limited, and the limits are included in the engine Light Maintenance Manual, Airworthiness Limitations Section. NOTE 10: Recommended engine inspection intervals are included in the engine Light Maintenance Manual. NOTE 11: For additional performance, authorized operation and detailed installation information, refer to the FAA approved sections of the engine installation manual as follows: Models Engine Installation Manual HTS900-2-1D IM-8028 NOTE 12: Deleted (Rev 1) NOTE 13: As provided for 14 CFR §§ 33.76, 33.78, the engine has not been tested to evaluate the effects of bird and hailstone ingestion. The bird and hailstone ingestion characteristics of the airframe air inlet and engine combination are to be evaluated prior to approval of the engine installation. -----------------------END----------------------