# TCDS E00080EN: Pratt & Whitney Canada Corp. - Type: Type certificate data sheet - Status: Current - Holder: Pratt & Whitney Canada Corp. - Revision: 3 - Revised: September 16, 2025 - Product: Engine - Certification basis: Part 21, Part 33 - Registered aircraft: 215, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/f9/77/f977ac5b0a11542cae1f8e0c43dcec63fa6a5343446c9bcc6c70436fadab324c - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID145296207220250923200648.0001 - Page: https://openairdocs.org/tcds/E00080EN ## Models (2) As the data sheet lists them. - PW617F-E - PW617F1-E ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text TCDS E00080EN PAGE 1 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00080EN TCDS NUMBER E00080EN REVISION: 3 DATE: September 16, 2025 PRATT & WHITNEY CANADA, CORP. MODEL: PW617F-E PW617F1-E Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00080EN) 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: Pratt & Whitney Canada, Corp. (Formerly Pratt & Whitney Canada, Inc.) 1000 Marie-Victorin Longueuil, Québec Canada J4G 1A1 MODELS PW617F-E PW617F1-E TYPE Twin spool controlled by Full Authority Digital Electronic Control (FADEC). Turbomachinery is comprised of a single stage fan driven by a single stage low pressure turbine, a high pressure compressor consisting of one mixed flow compressor stage and one centrifugal compressor stage, one stage high pressure turbine, annular reverse-flow fully effusion cooled combustor with internally mounted fuel manifold, and an integrated mono case. Twin spool controlled by Full Authority Digital Electronic Control (FADEC). Turbomachinery is comprised of a single stage fan driven by a single stage low pressure turbine, a high pressure compressor consisting of one mixed flow compressor stage and one centrifugal compressor stage, one stage high pressure turbine, annular reverse-flow fully effusion cooled combustor with internally mounted fuel manifold, and an integrated mono case. PW617F-E PW617F1-E RATING (See Note 1, 2) Thrust DaN lb. Ambient Limit C F Indicated Turbine Temperature C F Thrust DaN lb. Ambient Limit C F Indicated Turbine Temperature C F Maximum Takeoff Max Continuous 809.6 1820 749.5 1695 710.8 1598 15 59 25 77 20 68 845 1553 830 1526 830 1526 841.1 1891 768.6 1728 756.6 1701 17 62 23 74 24 76 - - - - - - - - - - - - PAGE 1 2 3 4 5 6 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "- - -" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. REV. 3 2 3 2 2 2 TCDS E00080EN PAGE 2 ENGINE OPERATING LIMITS PW617F-E PW617F1-E Operating Condition Operating Limits Thrust Time Limits (min.) Max. ITT (C) N2 RPM (%) N1 RPM (%) Max. ITT (C) N2 RPM (%) N1 RPM (%) Maximum 10 845 40,200 (100.4) 19,845 (100) - - 40,676 (101.6) - - Takeoff 5 830 40,200 (100.4) 19,845 (100) - - 40,676 (101.6) - - Max. Continuous - 830 40,200 (100.4) 19,845 (100) - - 40,676 (101.6) - - Starting - 950 --- --- - - --- --- Transient 20 sec. 90 sec. 862 --- 40,840 (102) --- 20,043 (101) --- - - --- 41,316 (103.2) --- - - --- ENGINE OPERATING LIMITS (cont’d.) PW617F-E PW617F1-E Operating Condition Operating Limits Thrust Time Limits (min.) Oil Pressure psig Oil Temperature (C) Min to Max Oil Pressure psig Oil Temperature (C) Min to Max Maximum 10 --- --- --- --- Takeoff 5 See Note 5 14 to 130 - - - - Max. Continuous - See Note 5 14 to 130 - - - - Starting - 0 to 275 -40 min. - - - - Transient 20 sec. 90 sec. See Note 5 See Note 5 --- 130 to 141 - - - - --- - - ACCESSORY POWER EXTRACTION LIMITATIONS Maximum limitations are defined in the Installation Manual. - - AIR BLEED PW617F-E PW617F1-E A. Maximum bleed air available Up to 9.1% of core flow at all altitudes - - B. During Starting Bleed air not permitted - - C. Bleed air contaminat ion meets Para 3.1.2.11.3 of MIL-E-5007E - - TCDS E00080EN PAGE 3 FUEL PW617F-E PW617F1-E Fuel Bleed A motive flow output is provided from the Fuel Metering Unit (FMU) motive flow port. Refer to Installation Manual. - - Fuel Pressure Refer to applicable Installation Manual. - - Fuel Temperature (a) The minimum allowable fuel tank temperature is -40F (-40C) when operating without fuel anti-icing additive. (b) Maximum fuel pump inlet temperature for starting and operating is 90OF (32OC) for typical wide cut fuels and 221OF (105OC) for kerosene type fuels. at sea level; minimum inlet temperature is -31OF (-35OC), Refer to Installation Manual for additional information. - - Fuel Type Fuels and additives conforming to the specifications listed in applicable P&WC Maintenance Manual are approved for use. - - OIL PW617F-E PW617F1-E Refer to Installation Manual for oil pressure and temperature. - - Refer to Maintenance manual for approved oil type and brand. - - Oil Capacity Litres Imp. Gallons U.S. gallon Total: 3.79 0.83 1.00 Usable: 0.89 0.20 0.24 - - ACCESSORY DRIVES The following apply to the accessory drive, which is provided by the engine: SPEED RATIO TO N2 MAXIMUM TORQUE (in.-lb.) MAXIMUM OVERHANG DRIVE ROTATION SHAFT CONTINUOUS STATIC (in.-lb.) PW617F-E DRIVEN BY HIGH ROTOR Starter Generator CW 0.3 200 1600 210 PW617F1-E - - - - - - - - - - - - CW - Clockwise facing accessory pad. The power extraction from the starter generator pad under continuous operation is limited to a maximum of 20 hp. The power extraction from the starter generator pad under overload conditions occurring for periods of 5 minutes maximum at the frequency of once per 4 hrs. is limited to 30 hp. The power extraction from the starter generator pad under overload conditions occurring for periods of 5 seconds maximum at the frequency of once per 4 hrs. is limited to 40 hp. IGNITION PW617F-E PW617F1-E Exciter P/N Igniter Plug P/N Refer to Assembly Parts List Refer to Assembly Parts List - - - - PW617F-E PW617F1-E PRINCIPAL DIMENSIONS Refer to Installation Drawing referenced in approved Installation Manual. - - C.G. LOCATION Refer to Installation Drawing referenced in approved Installation Manual. - - TCDS E00080EN PAGE 4 MAXIMUM ENGINE DRY WEIGHT PW617F-E PW617F1-E Includes basic bill of material components and sensors required for engine operation and monitoring. - - 380 lbs. - - CERTIFICATION BASIS PW617F-E 14 CFR 21.29, 14 CFR Part 33, effective February 1, 1965, as amended by 33-1 through 33-20 and 14 CFR Part 34, Amendment 5A, effective October 23, 2013. See NOTE 16 for a detailed summary of the certification basis for fuel venting and exhaust emissions. PW617F1-E - - MODEL APPLIED FOR TYPE CERTIFICATE ISSUED/REVISED DELETED PW617F-E January 10, 2006 July 15, 2009 - PW617F1-E March 4, 2016 October 31, 2016 - IMPORT REQUIREMENTS: To be considered eligible for installation on United States (U.S.) registered aircraft, each engine to be exported to the U.S. shall be accompanied by a certificate of airworthiness for export or by a certifying statement, endorsed by the exporting cognizant civil airworthiness authority which contains the following language: (1) This engine conforms to its Type Certificate Number and is in a condition for safe operation. (2) This engine has been subjected by the manufacturer to a final operational check and is in a proper state of airworthiness. Reference 14 CFR Section 21.500, which provides for the airworthiness acceptance of aircraft engines manufactured outside of the U.S. and for which a U.S. type certificate has been issued. 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." NOTES NOTE 1. The engine ratings for PW617F-E and PW617F1-E engine models are based on dry sea level static ICAO standard atmospheric conditions. No accessory loads or air bleed. The quoted ratings are obtainable on a test stand with specified fuel and oil, and using the exhaust duct and intake bell mouth specified in the Installation Manual. NOTE 2. Take-off ratings that are limited to 5 minutes duration may be used for up to 10 minutes for OEI operations without adverse effects upon engine airworthiness. Such operations are anticipated on an infrequent basis (as engine failure at take-off events is uncommon) and no limits or special inspections have been imposed. NOTE 3. Minimum permissible flight idle N2 for PW617F-E is: 23,623 RPM (59%) Minimum permissible flight idle N2 for PW617F1-E is: 23,623 RPM (59%) TCDS E00080EN PAGE 5 NOTE 4. Instructions for Continued Airworthiness (ICA) are listed in: PW617F-E PW617F1-E Maintenance Manual P/N 3072162 - - Line Maintenance Manual P/N 3072696 - - Overhaul Manual P/N 3072163 - - Airworthiness Limitations Manual P/N 3072699 - - NOTE 5. Refer to Installation Manual ER6331 for PW617F-E and for PW617F1-E. NOTE 6. Rotor component parts are life limited. Life limits are listed in Airworthiness Limitation Manual: P/N 3072699 for PW617F-E and for PW617F1-E. NOTE 7. Approved Publications: PW617F-E PW617F1-E Installation Manual P/N ER6331 - - Airworthiness Limitation Manual P/N 3072699 - - NOTE 8. Other Publications: PW617F-E PW617F1-E FADEC Interface Control Document P/N ER6370 - - Assembly Parts List for Production Engines P/N 35C3100 Revision J and subsequent revisions 35C6500 Rev A and subsequent revisions Refer to Installation Manual, ER6331 for PW617F-E and PW617F1-E for accessory drives specifications; principle dimensions; weights, inertias and centre of gravity locations; and additional information on provisions and connections to airframe provided vibration, Oil pressure and temperature and fuel flow sensor NOTE 9. NOTE 10. (deleted) These engines are approved for multiple engine installations only. NOTE 11. These engines are not approved for use with a thrust reverser. NOTE 12. The software contained in the Electronic Engine Control has been designed, developed, tested and documented in accordance with the provision of the critical Category, Level A of RTCA/DO178B. NOTE 13. The Electronic Engine Control Unit has not been fire tested and therefore must not be installed in a designated fire zone. NOTE 14. The PW617F-E and PW617F1-E engines are approved with Time Limited Dispatch (TLD) limitations. Aircraft considerations are contained in the Installation Manual. The dispatch criteria are contained in the Airworthiness Limitation Manual P/N 3072699 for PW617F-E and for PW617F1-E. TCDS E00080EN PAGE 6 NOTE 15. NOTE 16. Service bulletins, structural repair manuals, vendor manual, aircraft flight manuals, and overhaul and maintenance manuals, which contain a statement that the document is Transport Canada-approved, are acceptable by the FAA and are considered FAA-approved unless otherwise noted. These approvals pertain to the type design only. The following emissions standards promulgated in 14 CFR Part 34, Amendment 5A, effective October 23, 2013, and 40 CFR Part 87, effective October 31, 2012, have been complied with for the PW617F-E and PW617F1-E engines. Fuel Venting Emission Standards: 14 CFR §§ 34.10(b) and 34.11; in addition, 40 CFR §§ 87.10(b) and 87.11 as amended. Smoke Number (SN) Emission Standards: 14 CFR § 34.23(a)(1); in addition , 40 CFR § 87.23(c)(1). In addition to the FAA’s finding of compliance based on the certification requirements defined in this TCDS, the engine manufacturer has declared that the ICAO emissions standards identified in Annex 16, Volume II, Third Edition, Part III, Chapter 2, Section 2.2.2 for SN, and Part II, Chapter 2 for fuel venting have also been demonstrated. ----END---- ``` ## ADs (1, in force first) - [AD 2010-17-01](https://openairdocs.org/ad/2010-17-01): Fuel Filter Bypass Valve poppet · Pratt & Whitney Canada PW617F-E. 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