TCDS E2WE

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E2WE Revision 9 H oneywell Aerospace US LLC (AlliedSignal Garrett AirResearch) TPE331-25A, -25AA, -25AB, -25B, -25C, -25D, -25DA, -25DB, -25E, -25F, -25FA, - 25FB29A TPE33l-43, -43-A, -43-B, -45, - 47, -47-A, -47-B, -49, -51, -55, -55-A, -55-B, -57, - 57A, -57-B, -61, 61-A, -61-B, -71 March 27, 2026 TY PE CERTIFICATE DATA SHEET NO. E2WE E ngines of models described herein conforming with this data sheet (which is pa1t of Type Ce1tificate No. E2WE) and other approved data on file with the Federal Aviation Administration (FAA) meet the minimum standards for use in certified aircraft in accordance with pe1tinent 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. TY PE CERTIFICATE HOLDER: Honeywell Aerospace US LLC 111 South 34th Street Phoenix, AZ 85034 TY PE CERTIFICATE HOLDER RECORD: Honeywell International Inc. 111 South 34th Street Phoenix, AZ 85034 Mo del: TPE331-25A, -25AA, -25AB, TPE331-43, -43-A, -43-B, -45, -47, - 25B, -25C, -25D, -25DA, -25DB, -47-A, -47-B, -49, -51, -55, -55-A, -25E, -25F, -25FA, -25FB, -29A -55B, -57, -57-A, -57-B, -61, -61-A, -61-B, -71 Ra tings (see Note 3) Maximum continuous SHP 500 ESHP 529 (see Note 4) Output Shaft speed RPM 2000 Exhaust gas temperature ºF (ºC) 995 (535) Takeoff (5 minutes) SHP 575 Page No. 1 2 3 4 5 Rev. No. 9 9 9 9 9 E2WE 2 of 5 Exhaust gas temperature °F (0C) 1060 (571) 1070 (577) Gearbox power limit while not exceeding exhaust gas temperature limits: Continuous operation Ram takeoff conditions (5 minutes) 1313lb-ft 1707 lb-ft 1392 lb-ft Model (See Note 5) TPE331-25A, -25AA, -25AB, -25B, -25C, -25D, -25DA, -25DB, TPE33l-43, -43-A, -43-B, -45, -47, -47-A, -47-B, -49, -51, -55, -55-A, -25E, -25F, -25FA, -25FB, -29A -55-B, -57, -57-A, -57-B, -61, -61-A, -61-B, -71 Principal dimensions of basic engine Length, Inches 46.01 46.01 Width, Inches 20.18 - 21.32 20.79 - 21.02 Height, Inches 24.71 - 26.6 26.6 C.G. location, inches aft of gearbox rear face 7.1 7.1 C.G. location, inches above engine rotor center line 2.66 - 2.78 2.66 - 3.04 C.G. location, inches to the right of vertical center line when looking into exhaust 0.36 - 0.44 0.25 - 0.36 Weight, d1y, lbs. 335 335 Basic engine includes fuel pumps And filters, fuel control unit; fuel shutoff Valve; ignition system excluding power Source; propeller flange; propeller-tube oil transfer; exhaust thermocouples and harness; lubrication system exclusive of optional oil tank with integral oil-to-fuel heat exchanger and lines shrouding; torque sensor; and engine inlet anti-icing system, valve, electrical harness and plumbing lines. Propeller-shaft to engine-rotor ratio 1:20.865 Fuel Aviation turbine fuels conforming to ASTM D1655 grades Jet A and Jet A- 1; ASTM D6615 grade Jet B; Military Fuels MIL-DTL-5624 grades JP-4 and JP-5; MIL-F-5616-1 grade JP-1; MIL-G-5572 Aviation Gasoline Grade 80/87 not in excess of 1,000 gallons per 100 hours of engine operation may be used for emergency fuel operation. Oil Oils conforming to Honeywell Aerospace US LLC, Specification EMS53110 (Type I and Type II) are approved. Ignition System Honeywell Aerospace US, LLC (Scintilla or General Laboratory Associates) 369913 high-voltage capacitor-discharge type and two and two ignitor plugs, Honeywell Aerospace (Champion Spark Plug Co. or A.C. Spark Plug Co.) 369812 or (AC Spark Plug Co.) 369949. Certification Basis CAR 13 in effect on August 30, 1963, the date of application for Type Certificate. Type Certificate Number E2WE issued February 25, 1965. E2WE 3 of 5 P roduction Basis Control System Production Certificate Number 413 issued March 4, 1965. Reissued as Production Certificate Number 413NM to Honeywell Aerospace US LLC on March 29, 2026. The following basic control accessories are selected for combability with the propeller choice. The propeller selected for use with the engine must have functional characteristics that are compatible with the engine and with the control-system accessories. F uel Control 865420 or 893000 Fuel Pump Assembly 868531 Propeller Governor 865423 or 867374 or 869132 Propeller Pitch Control 867330 or 867390 Propeller Tube 866533 or 866678 N OTE 1: Maximum permissible temperature: TPE331-25A, -25AA, -25AB, TPE331-43, -43-A, -43-B, -45, -47, - 25B, -25C, -25D, -25DA, -25DB, -47-A, -47-B, -49, -51, -55, -55-A, -25E, -25F, -25FA, -25FB, -29A -55B, -57, -57-A, -57-B, -61, -61-A, -61-B, -71 E xhaust gas temperature Maximum continuous 995ºF (535ºC) 1026ºF (ºC) Takeoff (5 minutes) 1060ºF (571ºC) 1070ºF (ºC) The above takeoff and maximum continuous exhaust gas temperatures are for ARDC Model Atmosphere, Standard sea-level day static conditions. To maintain constant turbine inlet temperature, exhaust gas temperature will vary as a function of ambient conditions. Consult the manufacture’s operation manual for other than standard sea-level day operations. Starting Not to exceed 1500ºF (815ºC) for one second Oil inlet temperature Minus 40ºF (minus 40ºC) to 260ºF (127ºC) MIL-PRF-23699 Minus 40ºF (minus 40ºC) to 200ºF (93ºC) MIL-PRF-7808 Ambient air temperature Minus 65ºF (minus 54ºC) to 125ºF (52ºC) External engine component Ignition lead 500ºF (260ºC) Igniter Plugs 550ºF (288ºC) Thermocouple harness 850ºF (454ºC) Fuel Shutoff Valve 250ºF (121ºC) Fuel Control Assembly 265ºF (130ºC) Engine zones Zone 1 (forward of the fire-shield adapter) 200ºF (93ºC) Zone 2 (Aft of the fire-shield adapter up to the turbine exhaust-diffuser split line) 450ºF (232ºC) N OTE 2: Pressure limits: Inlet air pressure Sea level to 30,000 feet altitude With fuel conforming to Minus 3.0 PSIG at altitudes up to 15,000 feet; and 5 PSIG above true Those specified above, vapor pressure, or that which will maintain the vapor-liquid ratio fuel pressure at inlet between 0 and 0.45 for altitudes of 15,000 feet and above. The inlet connection to the engine. fuel pressure at all altitudes shall not exceed 50 PSIG maximum. E2WE 4 of 5 O il pressure at inlet Not to exceed a 12-inch negative head. connection to the engine O il operating pressure 70 to 120 PSIG N OTE 3: The engine ratings are based on: Dynamometer operation at ARDC Model Atmosphere, sea level static conditions. Compressor Inlet Air (Dry) 59ºF (15ºC), 29.92 in Hg. MIL- DTL-5624, Grade JP-4, fuel with lower heating value of 18,400 Btu per pound and MIL-PRF-23699 (WEP)-2 type oil, Mobil Oil Jet II. No bleed -air extraction, no anti-icing airflow, and no external accessory loads. Zero inlet duct loss. Exhaust gas discharging to ambient static pressure through the turbine exhaust diffuser furnished with the engine. Measured exhaust-gas temperature as indicated by average of the exhaust gas temperature thermocouples. N OTE 4: Equivalent shaft horsepower (ESHP) is based on ESHP = Jet Thrust lb. 2.5 +SHP N OTE 5: Accessory Drive Provisions: Nominal Use Type of Drive (one each) Speed Ratio to Engin e Rotor R otation⁴ Facing Drive Pad Maximum Torque Continuous (lb -in.) Maximum Torque Overload (lb -in.) Maximum Torque Static (lb -in.) Overhung Moment (lb -in.) Drive5 Speed ( rpm) Tachometer - Generator AND200051 Type XV-B 0.100 CW per AND 7 per AND - - 50 per AND 25 4,187 per AND Starter or starter generator AND200022 Type XII-D (modified) 0.261 CW per AND 300 600 2,200 per AND 500 per AND 10,886 Aircraft Accessory AND200013 Type XI-B (modified) 0.096 CCW 250 per AND 375 Per AND 1,650 per AND 125 per AND 3,959 Propeller governor AND200104 Type XX-A (modified) 0.090 CW per AND 125 per AD 188 Per AND 825 per AND 125 3,754 Propeller Pitch Control Mounting pad provided. 30 NONE 1Same as AND except as shown in the table and except for stud length 2 Same as AND except as shown in the table and except that studs are rotated 30º from standard pad configuration. 3 Same as AND except as shown in the table. 4 CW = Clockwise; CCW = Counterclockwise. 5 Drive speed at takeoff engine-rotor speed of 100 percent. N OTE 6: Bleed-air extraction above ground idle is permissible up to 5 percent of compressor non-bleed airflow when the anti-icing system is not in use and up to 3 percent of compressor non-bleed airflow when the anti-icing system is in use. N OTE 7: The maximum allowable propeller shaft speed is 2,100 RPM for a transient period not to exceed 5 seconds. N OTE 8: MIL-DTL-85470 jet fuel anti-icing additive is approved for use in fuels in amounts not to exceed 0.15 percent volume. E2WE 5 of 5 NOTE 9: These engines meet FAA requirements for adequate turbine disc integrity and rotor blade containment and do not require external armoring. N OTE 10: These engines meet FAA requirements for operation in icing conditions. N OTE 11: Propeller shaft is bolted-flange type with clockwise rotation when looking into turbine exhaust. N OTE 12: Shell ASA-3 anti-static additive, or equivalent, in amounts to bring the fuel up to 300 conductivity units is permissible except that in no event shall the additive exceed l PPM. N OTE 13: Engine with an "L" stamped after the Model Number (25AL) have the 75 percent low ground idle kit installed. This increased the weight of the engine 11oz. and does not change the C.G. Low ground idle kits should be installed on engine models as shown in the following chart: -- -----------------------END--------------------------- Engine Model Low Ground Idle Kit TPE331-25A, -25AA, -25AB 869063-1 TPE-331-25D, -25DA, -25DB 869362-1 TPE331-25F, -25FA, 25FB 869363-1 TPE331-43, -43-A, 43-B 869361-1 TPE331-47, -47-A, -47-B 869360-1 TPE331-55, -55-A, -55-B 869743-1 TPE331-57, -57-A, -57-B 869744-1 TPE331-61, -61-A, -61-B 893152-1