# TCDS E5WE: Honeywell Aerospace US LLC - Type: Type certificate data sheet - Status: Current - Holder: Honeywell Aerospace US LLC - Revision: 3 - Revised: March 27, 2026 - Product: Engine - Certification basis: Part 33 - Data sheet PDF: https://openairdocs.org/files/sha256/af/1e/af1e4deaa07eacc6ad150b414ef4874bc8fa9a9f17b9835ce04cd4973572919d - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID184889346420260605175659.0001 - Page: https://openairdocs.org/tcds/E5WE ## Models (1) As the data sheet lists them. - TSE36-1 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E5WE Revision 3 Honeywell Aerospace US LLC AlliedSignal, Garrett, AiResearch) TSE36-1 March 27, 2026 TYPE CERTIFICATE DATA SHEET NO. E5WE Engine models described herein conforming with this data sheet (which is part of Type Certificate No. E5WE) 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 turboshaft engine with wet-sump gearbox, single-stage centrifugal compressor, single-stage radial inward-flow turbine, single- can combustor with torus transition chamber, and flanged exhaust duct. Model Number: TSE36-1 Page No. 1 2 3 4 5 Rev. No. 3 3 3 3 3 E5WE 2 of 5 Ratings (see Note 3) TSE36-1 Max. continuous shaft horsepower, hp 220 Output shaft speed, rpm 2929 Exhaust gas temperature (EGT), °F (°C) 1080 (582) Takeoff (5 mins) shaft horsepower, hp 240 Output shaft speed, rpm 2929 Exhaust gas temperature (EGT), °F (°C) 1167 (630) Fuel control and fuel pump assembly Honeywell Aerospace P/N 894451 Overspeed Governor Honeywell Aerospace P/N 1095843 EGT Temperature Compensating Resistor (see Note 15) Honeywell Aerospace P/N 866157 Principal dimensions of basic engine Length, inches 35.90 Width, inches 27.87 Height, inches 21.79 C.G. location, inches aft of gearbox mount centerline 5.96 C.G. location, inches above engine rotor centerline 0.84 C.G. location, inches to the left of vertical centerline when looking into exhaust 0.04 Weight (dry), pounds (see Note 4) 178 The basic engine comprises a wet-sump gearbox with an associated lubrication system; a compressor, a combustor-turbine section with exhaust duct and EGT thermocouple, and the following control components: a) Fuel-control unit and high-pressure pump b) Fuel-shutoff valve c) Fuel-flow-divider valve d) Fuel atomizer e) Overspeed governor f) Ignition coil, igniter lead, and igniter plug Ratio of output shaft to engine rotor 1:19.801 Fuel ASTM D 1655-68, Types Jet A, *Jet B, and Jet A-1. *MIL-DTL-5624, Grades JP-4 and JP-5* NATO equivalents of the above fuels are also approved. For emergency use only, use the following fuels: ASTM D4814, MIL-G-5572D, Grades 80/87, 100/130, and 115/145. *Minimum fuel temperature corresponding to a kinematic viscosity of not more than 12 centistrokes. Oil MIL-PRF-23699A: Aeroshell Turbine Oil 500, Enco/Esso 2380 T urbo Oil, Mobile Jet Oil II; MIL-PRF-7808D: Brayco 880 Conojet, British Petroleum Aero Turbine Oil 15, Caltex SATO 15, Continental Conojet, Sinclair Turbo S Oil 15, Texaco SATO 15; MIL-PRF-7808: Hancock Airturb Syn Lube, Stauffer Jet I. E5WE 3 of 5 Certifi cate Basis Production Basis 14 CFR part 33 dated February 1, 1965, and A mendments 1, 2, and 3 Type Certificate Number E5WE, is sued date d April 30, 1970. Date of application for Type Certificate, dated February 8, 1968 Production Certificate No. 413. Reissued Production Certificate Number 413NM to Honeywell Aerospace US LLC on March 29, 2026. NOTE 1: Maximum Permissible Temperature Exhaust gas temperature: Maximum continuous, °F (°C) 1080 (582) Takeoff (5 minutes), °F (°C) 1167 (630) The above t akeoff and maximum continuous exhaust gas temperatures are for U.S. Standard Atmosphere sea-level static conditions. To maintain constant turbine inlet temperature, exhaust gas temperature will vary as a function of ambient conditions. Consult the Honeywell Aerospace US LLC Operating Instructions, IM-5118, for other than standard sea-level day conditions. During starting, the maximum exhaust gas temperature is not to exceed 1400°F (760°C) for more than one second. Oil in let temperature: -40°F (-40°C) to 205°F (95°C) for MIL-PRF-23699 type. -40°F (-40°C) to 175°F (79°C) for MIL-PRF-7808 type. Ambien t temperature: Operating: -65°F (-54°C) to 130°F (54°C) Starting: -40°F (-40°C) to 130°F (54°C) External engine components, surface temperature °F (°C): Overspeed governor 160 (71) Ignition lead 450 (232) Ignition plug 450 (232) Ignition coil 160 (71) Thermocouple lead 450 (232) Monopole pickup 400 (205) Fuel atomizer 275 (135) Fuel-shutoff valve 250 (121) Fuel-control 200 (93) Fuel lines 250 (121) Tachometer cable drive Engine zones , air temperature: 160 (71) Zone 1 (gear case and components) 250°F (121°C) Zone 2 (inlet) Ambient inlet air Zone 3 (diffuser housing section) 400°F (205°C) Zone 4 (turbine section) 450°F (232°C) E5WE 4 of 5 NOTE 2: Pressure Limits NOTE 3: The engine ratings are based on: Dynamometer operation at U.S. Standard Atmosphere, Sea level static conditions Compressor inlet air (dry), 59°F (15°C) 29.92 in. Hg MIL- DTL-5624, Grade JP-4 fuel with lower heating value of 18,400 btu per pound MIL- PRF-23699 type oil, MIL- PRF-7808 type oil No bleed-air extraction 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 exhaust gas temperature thermocouple. NOTE 4: Engine accessories are: Output shaft adapter (15 lbs) (see NOTE 12) Torque sensor (3 lbs) Engine speed cable-drive assembly (1.5 lbs) An EGT compensating system (0.5 lbs) These accessories increase engine weight to 198 lbs. NOTE 5: Accessory drive provisions: Type of Drive AND Drive Rotation Facing Drive Speed Ratio, Drive to Maximum Torque (lb.-in.) Gear Case Housing Overhung Normal Use (One each) Modification Pad and RPM Engine Rotor T c T o T s Moment (lb.- in.) Engine Main Internal Not AND CCW 0.05050 4,72 5,91 5,50 0 Output Shaft Spline Standard 2,292 RPM 8 6 0 Tachometer* Generator AND20005 Type XV-B -- CW 4,193 RPM 0.07229 7 -- 50 25 Tachometer* SAEAS54 Type 1 -- CW 1,481 RPM 0.02553 2 3 7 5 Inlet air pressure Sea level to 20,000 feet altitude Inlet fuel pressure (at the engine-driven pump) 30 psig max. at 100% speed. Min. engine-pump inlet pressure is 5 psi above true vapor pressure of the fuel in use. Oil operating pressure 90 to 110 psig at 100% speed 50 psig min. at 30,000 rpm E5WE 5 of 5 Customer Accessory Pad AND20001 Type XI-C Rotation, RPM, and Torque CCW 12,021 RPM 0.20689 80 120 320 150 CW - clockwise Tc - continuous torque CCW - counterclockwise To - torque overload Ts - static torque • If either optional tachometer-generator speed-sensing unit or tachometer cable-drive adapter speed-sensing unit is used, it will be mounted directly to the AND pad and the overspeed governor will be mounted to the aft side and be driven by the through-drive shaft of the speed sensing unit. if neither type speed-sensing units are used the overspeed governor will be mounted directly to the AND pad. NOTE 6: Up to 4 percent of the compressor nonbleed airflow is available for aircraft use and is available from an MS33649 type boss. NOTE 7: The maximum allowable power, as sensed by the torque sensor, in pound-feet is: NOTE 8: The maximum allowable output shaft speed is 3075 rpm. The normal output shaft speed is 2929 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: This engine meets FAA requirements for adequate turbine-disc integrity and rotor-blade containment and does not require external armoring. NOTE 11: This engine meets FAA requirements for operation in icing conditions within the envelope defined in 14 CFR P art 25, Appendix C. NOTE 12: Output 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 basic engine does not include a fuel filter or filter deicing system. NOTE 15: EGT compensating resistor values are identified by specific dash numbers and are matched to each engine during production or overhaul acceptance test. Field replacement must be a part with the original dash number. ---------------------------END------------------------ Maximum torque overload 493 Normal rateoff 430 Maximum continuous torque 394 ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [AiResearch TSE36-1](https://openairdocs.org/engine/airesearch-tse36-1): 0 aircraft (registry code 01598) - [Garrett TSE36-1](https://openairdocs.org/engine/garrett-tse36-1): 0 aircraft (registry code 29083) - [Honeywell TSE36-1](https://openairdocs.org/engine/honeywell-tse36-1): 0 aircraft (registry code 33813) --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.