TCDS E3WE

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E3WE Revision 9 Honeywell Aerospace US LLC AlliedSignal, Garrett, AiResearch) TPE331-1 TPE331-1U TPE331-1UA TPE331-2 TPE331-2U TPE331-2UA March 27, 2026 TYPE CERTIFICATE DATA SHEET NO. E3WE Engine models described herein conforming with this data sheet (which is part of Type Certificate No. E3WE) and other approved data on file with the Federal Aviation Administration, meet 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: Honeywell Aerospace US LLC 111 South 34th Street Phoenix, AZ 85034 TYPE CERTIFICATE HOLDER RECORD: Honeywell International Inc. 111 South 34th Street Phoenix, AZ 85034 TYPE CERTIFICATE HOLDER RECORD: AlliedSignal Inc. 111 South 34th Street Phoenix, AZ 85034 TYPE CERTIFICATE HOLDER RECORD: Garrett Turbine Engine Co. 111 South 34th Street Phoenix, AZ 85034 TYPE CERTIFICATE HOLDER RECORD: AiResearch Manufacturing Co. 111 South 34th Street Phoenix, AZ 85034 Type Single-Shaft Turboprop with two-stage centrifugal compressor, three- stage axial turbine, and single annular combustion chamber. Model Number (The letter “U” after the model dash number indicates that the engine air inlet is located above the propeller shaft centerline. Omission of the letter “U” after the model dash number indicates that the engine air inlet is located below the propeller shaft centerline.) Page No. 1 2 3 4 5 Rev. No. 9 9 9 9 9 E3WE 2 of 5 Ratings (see Note 3) TPE331-1, -1U, -1UA TPE331-2, -2U, -2UA Max. continuous SHP 665 715 ESHP (see Note 4) 705 755 Output shaft speed, RPM 2000 2000 Exhaust gas temperature °F (°C) 1047 (564) 1072 (578) Interstage turbine temperature °F (°C) 1638 (890) 1693 (923) Takeoff (5 mins) SHP 665 715 ESHP (see Note 4) 705 755 Output shaft speed, RPM 2000 2000 Exhaust gas temperature °F (°C) 1047 (564) 1072 (578) Interstage turbine temperature °F (°C) 1638 (890) 1693 (923) Principal dimensions of basic engine Refer to the Installation Drawing for each specific engine model configuration for dimensions and center of gravity location. Weight, Dry, Pounds (see Note 14) 335 335 The engine weight shown herein is that of the power section and all components coded “E” in the Engine Equipment List. Unit weights for items coded “A” in the Engine Equipment List are contained in the Engine Installation Manual IM-5111. Propeller-shaft to Engine-Rotor ratio 1:20.865 1:20.865 Fuels Engine operation is approved with the following aviation turbine fuels: Honeywell Aerospace US LLC EMS 53111 (Type A) Honeywell Aerospace US LLC EMS 53112 (Type A-1) Honeywell Aerospace US LLC EMS 53113 (Class A-JP4 and Class B Type B) Honeywell Aerospace US LLC EMS 53114 (Type JP-5) British D. Eng. R.D. 2486, Issue 2 British D. Eng. R.D. 2494, Issue 4 ASTM D975 Grade 2-D, dated 1977 (No. 2 Diesel Fuel) Diesel Fuel approval limited to TPE331-1-101Z engine only and usage at ambient temperatures above +15ºF. Aviation gasoline MIL-G-5572, Grade 80/87, not in excess of 1000 gallons per 100 hours of operation, may be used for emergency fuel operation. Fuel Additives MIL-DTL-85470 Fuel system Icing Inhibitor, or an equivalent inhibitor, may be added in a quantity not in excess of 0.15 percent by volume, to fuels not containing anti-icing inhibitors. Shell ASA-3 anti-static additives or equivalent, may be used in amounts to bring the fuel up to 300 conductivity units, but in no event shall be additive exceed 1PPM. E1NM 3 of 5 S ohio Biodor JF Biocide Additive, or equivalent, is approved for use in the fuel at a concentration not to exceed 20 PPM of elemental Boron. O il Oils conforming to Honeywell Aerospace US LLC Specification EMS 53110 (Type 1 and Type 2). Co ntrols: (See NOTE 15) Ce rtification Basis: 14 CFR Part 33 dated February 1, 1965, and Amendments 1, 2, and 3. Type Certificate Number E3WE, issued Dated December 14, 1967. Production Basis: Production Certificate Number 413, issued dated March 4, 1965, Reissued as Production Certificate Number 413NM to Honeywell Aero space US LLC on March 29, 2026. N OTE 1: Maximum permissible temperature TPE331-1, 1U, -1UA TPE331-2, -2U, -2UA Exhaust gas temperature, EGT Maximum continuous °F (°C) 1,047 (564) 1,072 (578) Takeoff (5 minutes) °F (°C) 1,072 (578) 1,072 (578) Inlet turbine temperature, ITT Maximum continuous °F (°C) 1,638 (892) 1,693 (923) Takeoff (5 minutes) °F (°C) 1,693 (923) 1,693 (923) The above takeoff and maximum continuous exhaust gas temperatures are for U.S. Standard Atmosphere sea-level static conditions, except when noted in the manual for Model TPE331-1, -1U, and -1UA versions at 80°F (27°C) ambient temperature, sea-level altitude, static condition. To maintain constant turbine inlet temperature, exhaust gas temperature will vary as a function of ambient conditions. Consult the manufacturer's operating manual for other than s tandard sea-level day conditions. The maximum exhaust gas temperature for engines equipped with EGT thermocouples for operation at 65 percent speed is 1400°F (760°C). During starting, the maximum exhaust gas temperature (EGT) is not to exceed 1500°F (815°C) or interstage turbine temperature (ITT) is not to exceed 2100°F (1149°C) for more than one second. Oil inlet temperature: Minus 40°F (-40°C) to 260°F (127°C) for MIL-PRF-23699 type, and Minus 40°F (-40°C) to 200°F (93°C) for MIL-PRF-7808 type. A mbient air temperature: Minus 65°F (-54°C) to 125°F (52°C) External engine components, surface temperature °F (°C): TPE331-1, -1U, -1UA TPE331-2, -2U, -2UA Ignition leads 450 (232) 450 (232) Igniter plugs 450 (232) 450 (232) Thermocouple harness (EGT) 850 (454) 850 (454) Thermocouple lead (ITT) 450 (232) 450 (232) Fuel manifold 450 (232) 450 (232) Start fuel manifold 450 (232) 450 (232) Fuel shutoff valve 250 (121) 250 (121) Fuel control assembly 265 (129) 265 (129) Anti-icing valve, bleed air 610 (321) 610 (321) E3WE 4 of 5 NOTE 2: Pressure limits Inlet air pressure Sea level to 30,000 feet altitude except when noted in the manual for certain model TPE331-1, -1U, and -1UA versions at 35,000 feet. Fuel pump inlet pressure, 5 psig plus true vapor pressure of fuel. Refer to IM-5111 for Operational minimum normal operation limitations. Oil pressure at inlet 2.45 psia connection to the engine, minimum Oil operating pressure 70 to 120 psig at 100% speed 50 to 120 psig at 100% speed (above 23,000 feet altitude) 40 psig (minimum) at 64% speed (ground idle) NOTE 3: The engine ratings are based on: Dynamometer operation at U.S. Standard Atmosphere, sea-level static conditions or when noted in the manual at 80°F (27°C) ambient temperature, sea-level altitude, static conditions. Compressor inlet air dry 59°F (15°C) or 80°F (27°C) whichever is applicable, 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 type oil, Mobil Oil Jet II. No bleed-air extraction, no anti-icing airflow, and no external accessory loads. Zero inlet loss. Exhaust gas discharging to ambient-static pressure through the turbine exhaust diffuser furnished with the engine. Measured exhaust gas temperature is indicated by the average of the exhaust gas temperature thermocouples (EGT) or measured interstage turbine temperature (ITT). NOTE 4: Equivalent shaft horsepower (ESHP) for static conditions is based on: ESHP= Net thrust, pounds + SHP 2.5 NOTE 5: Accessory Drive provisions: Type Drive AND Drive Rotation Facing Drive Speed Ratio Drive to Maximum Torque (lb.-in) Overhung Nominal Use (one each) Modifications Pad and RPM Engine Rotor ¹c ¹o ¹s Moment (lb.- in) Aircraft accessory AND20001 Type XI-B (Modified) Rotation, and RPM CCW 3,959 RPM 0.09487 250 375 1650 125 Starter or starter- generated AND20002 Type XIII-D (Modified) RPM, Tc, To, And stud pattern rotation 30º CW 10,887 RPM 0.26089 300 600 2200 500 Tachometer Generator AND20005 Type XV-B (Modified) Shorter studs and threads length CW4,187 RPM 0.10033 7 -1 50 25¹ Propeller governor Mounting pad provided RPM CW 3,754 RPM 0.08995 125 188 -- 125¹ Propeller pitch control Mounting pad provided - - - - - - - - - - 3 E1NM 5 of 5 CW – Clockwise Tc - continuous torque RPM at 100 percent engine speed CCW – Counterclockwise To - torque overload -1 - Unspecified in AND Standard Ts - static torque NOTE 6: Up to 6 percent of the compressor non bleed airflow is available for aircraft use during engine anti-icing operation and up to 8 percent is available without engine anti-icing operation. NOTE 7: The maximum allowable power, as sensed by the torque sensor, in pound-feet is: NOTE 8: The maximum allowable propeller shaft speed is 2,100 RPM for a transient period not to exceed 5 seconds, and 2,020 RPM for 5 minutes. The normal output shaft speed is 2,000 RPM. NOTE 9: MIL-DTL-85470 Fuel System Icing Inhibitor, or equivalent, is approved for use in fuels in amounts not to exceed 0.15 percent by volume. NOTE 10: These engines meet FAA requirements for adequate turbine disc integrity and rotor blade containment and do not require external armoring. NOTE 11: These engines meet FAA requirements for operation in icing conditions. NOTE 12: Propeller shaft is bolted-flange type with clockwise rotation when viewed forward from the turbine exhaust. NOTE 13: 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 1 PPM. NOTE 14: The TPE331-1UA and -2UA are identical to the TPE331-1U and -2U, respectively, except they have an aluminum gear box. This increases the weight of the engine 15 pounds but does not affect the C.G. NOTE 15: Variations in engine configuration and installation components are identified by a suffix to the basic model number on the engine nameplate; i.e., TPE331-1-XY (“X” denotes Honeywell Aerospace installed configuration rating code number(s) and “Y” denotes Honeywell Aerospace equipment code letter(s) of aircraft manufacturer), and an Engine Equipment List Number. Certain features of these components are influenced by aircraft design considerations. In the Engine Equipment List, those items coded "E" are basic engine items and are controlled by 14 CFR Part 33. Items coded "A" have been demonstrated as compatible with the basic engine during engine certification testing. However, the operation, functioning, and rigging of these in a specific aircraft installation must be demonstrated during aircraft certification. Subsequent design change control associated with these factors is the responsibility of the aircraft manufacturer. N OTE 16: Certain engine parts are life limited. These limits are listed in the FAA-approved Honeywell Aerospace US LLC Service Bulletin TPE-72-0019, dated December 4, 1972, or later FAA-approved revisions. -------------------------END-------------------- TPE331-1, -1U, -1UA TPE331-2, -2U, -2UA 5 Minute Torque Limit 1,890 2,040 Maximum Continuous Torque Limit 1,746 1,878