TCDS E00059EN

PAGE 1 2 3 4 5 6 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" REV. 6 6 6 6 6 6 "---" NOT APPLICABLE NOTE: ALL PAGES ARE RE-FORMATTED. SIGNIFICANT CHANGES, IF ANY, ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00059EN TCDS NUMBER E00059EN REVISION: 6 DATE: July 10, 2024 PRATT & WHITNEY CANADA.CORP. MODELS: PW545A, PW545B, PW545C, PW545D Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00083EN) 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. 1000 Marie Victorin Longueuil, Quebec Canada J4G 1A1 TYPE CERTIFICATE (TC) RECORD Pratt & Whitney Canada, Inc. (Name change of TC Holder) TYPE Twin spool with a low pressure compressor consisting of a single stage integrally bladed fan and one axial boost stage, a high pressure compressor consisting of two axial stages and one centrifugal compressor stage, one stage high pressure turbine, three stage low pressure turbine, annular reverse-flow combustor and full length annular bypass duct. MODELS: PW545A PW545B PW545C PW545D THRUST RATINGS POUNDS (See Note 1) Takeoff (5 minutes) (See NOTE 13) Maximum Continuous 3952 3,372 4,119 - - - - - - 4,218 - - COMPONENTS/ CONFIGURATION Refer to Assembly Parts List in Note 5.. For Principal Dimensions and C.G. Location refer to the Installation Drawing in the approved Installation Manual FUEL TYPE Fuel types and additives conforming to the specifications are listed in Approved Fuels and Oil List P/N 3137840 and the P&WC Maintenance Manual are approved for use. OIL TYPE Oils conforming to the specifications listed in Approved Fuels and Oil List P/N 3137840 and the applicable P&WC Maintenance Manual are approved for use. TCDS E00059EN PAGE 2 CERTIFICATION BASIS: PW545A PW545B PW545C and PW545D 14 CFR Section 21.29; 14 CFR Part 33, Amendments 1 through 15, effective August 16, 1993; and 14 CFR Part 34, effective September 10, 1990. 14 CFR Section 21.29; 14 CFR Part 33, Amendments 1 through 20, effective December 13, 2000; and 14 CFR Part 34, Amendment 3, effective February 3, 1999. 14 CFR Section 21.29; 14 CFR Part 33, Amendments 1 through 20, effective December 13, 2000; and Federal Aviation Administration Equivalent Level of Safety (ELOS) finding: 33.76, Bird Ingestion, para. (c), Amendment 20, ELOS No. 8040- ELOS-08-NE-07. The PW545C and PW545D complied with 14 CFR part 34, amendment 5A, effective October 23, 2013. See Note 23 for a detailed summary of the certification basis for fuel venting and exhaust emissions. All Models comply with 14 CFR part 34, amendment 7A, effective May 24, 2024 MODEL TYPE CERTIFICATE NUMBER E00059EN APPLIED FOR ISSUED/ REVISED DELETED PW545A PW545B PW545C PW545D 08/25/95 02/10/03 01/05/07 04/28/22 07/18/97 01/16/04 05/05/08 07/10/24 NOTES NOTE 1 ENGINE RATINGS . The engine ratings for the PW545A, PW545B, PW545C and PW545D engine models are based on static sea level conditions: Compressor inlet air (dry) 77ºF, at takeoff and 95ºF at max. continuous 29.92 in. Hg Engine intake and exhaust as described in the Department of Transport Canada approved Installation Manual. NOTE 2. TEMPERATURES INTERTURBINE TEMPERATURE ºF/ºC ºF/ºC ºF/ºC ºF/ºC MODELS: PW545A PW545B PW545C PW545D Takeoff (5 min.) Maximum continuous Starting ( 5 sec.) Transient (20 sec.) (Also see Installation Manual) 1328/720 1328/720 1328/720 1400/760 1364/740 - - 1364/740 1436/780 - - - - - - - - - - - - - - - - TCDS E00059EN PAGE 3 NOTE 2 (continued) OIL INLET TEMPERATURE ºF/ºC ºF/ºC ºF/ºC ºF/ºC MODELS: PW545A PW545B PW545C PW545D Maximum Minimum Transient maximum 545A: (120 sec.) Transient maximum 545B: (400 sec.) Transient maximum 545C: (ins. man.) (Also see Installation Manual) 250/121 -40/-40 275/135 --- - - - - --- 275/135 - - - - --- - - - - - - --- - - Fuel temperature Maximum fuel pump inlet temperature for starting and operating for the PW545A and PW545B is 135 degF(57 degC) at sea level and for the PW545C and PW545D it is 127 degF (53 degC); minimum inlet temperature for the PW545A and PW545B is -48 degF(-44 degC) and for the PW545C and PW545D it is -43 degF (-41 degC), for typical kerosene type fuels. Refer to Installation Manual/NOTE 7 for additional information. Max Accessory Temperature The engine compartment shall be ventilated as necessary to keep the air temperature surrounding accessory components from exceeding he limits defined in the Installation Manual NOTE 3. PRESSURES FUEL Refer to the Installation Manual. OIL MODELS PW545A PW545B PW545C PW545D Min. at Ground Idle up to 60% N2 Min. at 60% N2 and above Max Transient (20 seconds) Transient (120 seconds) Transient (400 seconds) psig psig psig psig 25 45 140 0 20-250 --- - - - - 160 - - --- 20-250 - - - - - - - - --- - - - - - - - - - - --- - - NOTE 4 ACCESSORY DRIVE PROVISIONS The following apply to the accessory drives, which are provided by the engine and included in the basic engine weight: SPEED RATIO TO TURBINE MAXIMUM TORQUE (in. - lb.) MAXIMUM OVERHANG DRIVE ROTATION * SHAFT CONTINUOUS STATIC (in.-lb.) DRIVEN BY HIGH ROTOR Hydraulic pump Starter generator Alternator** CW CW CW . 1280:1 .3633:1 0.3363:1 225 240 110/ 83 1600 1600 1600 40 210 250 *CW - Clockwise facing accessory pad. ** -Alternator Max torque (Continuous) for the PW545A and PW545B is 110 and for the PW545C and PW545D is 83. Total accessory power limit is 22.5 hp. at Flight Idle N2, increasing linearly to 34.5 hp. at 100% N2. Refer to Installation Manual for restrictions above 20,000 ft. altitude and allowable 5 minute emergency accessory power extraction. Also see NOTE13. TCDS E00059EN PAGE 4 NOTE 5 MODEL DESCRIPTION Production Engine Configuration at the time of certification is defined for each engine model as follows: PW545A - EAPL A31J1900-01 PW545B - Engine Assembly Drawing No. 30J2622, Revision B PW545C - EAPL A30J2934 PW545D - EAPL A30J4255 NOTE 6 TYPICAL AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES WITH AIRCRAFT LEVEL REQUIREMENTS PROVIDED AS PART OF ENGINE TYPE DESIGN Not Applicable NOTE 7 AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES INSTALLED ON THE ENGINE BUT ARE NOT PROVIDED AS PART OF ENGINE TYPE DESIGN Not Applicable NOTE 8 SPECIAL ANTI-ICING OR DE-ICING REQUIREMENTS Not applicable. NOTE 9 ENGINE MOUNT SYSTEM REQUIREMENTS Refer to Installation Manual NOTE 10 POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS Not applicable. NOTE 11 SPECIAL INSTALLATION REQUIREMENTS Fuel Bleed- Fuel from pump delivery may be extracted to drive jet or turbine pumps in the airplane fuel system. Refer to Installation Manual. Oil Tank Capacity – Refer to Installation Manual. The PW545A, PW545B, PW545C and PW545D engine definition does not include a thrust reverser. Considerations for the installation of a thrust reverser are contained in the Installation Manual. Model PW545C and PW545D For HIRF and lightning conformance, and installation requirements, Refer to the Installation Manual. The software contained in the Electronic Engine Control for the PW545C engine has been designed, developed, tested and documented in accordance with the provisions of Critical Category Level A of RTCA/DO178B and with portions of the PW545D software as Critical Category, Level A of RTCA/DO178C. The engine is equipped with a FADEC which is approved for Time Limited Dispatch (TLD). The dispatch criteria are defined in the Airworthiness Limitations Section of the Maintenance Manual P/N 30J2302 for the PW545C and P/N 30J3292 for the PW545D. The TLD dispatchable fault configuration is defined in ER 6612-01 Part A Interface Control Document for the PW545C and ER 11051-01 Part A Interface Control Document for the PW545D. NOTE 12 MANUFACTURERS SERVICE BULLETINS OR OTHER INSTRUCTIONS COVERING MATTERS OF INTEREST 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 accepted by the FAA and are considered FAA-approved. These approvals pertain to the type design only. TCDS E00059EN PAGE 5 NOTE 13 SPECIAL OPERATING PROCEDURES 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. Flight Idle is a function of Ambient Pressure for PW545C and PW545D Models. The starter/generator pad for the PW545A, PW545B, PW545C and PW545D engine models may be overloaded in an emergency to a torque of 340 in.-lb. for periods up to 5 minutes, subject to total accessory power not exceeding 40 hp. This can recur at 4 hour intervals. Refer to Installation Manuals (see NOTE 7) for restrictions above 10,000 feet altitude. NOTE 14 SPECIAL REPAIR OR OVERHAUL LIMITATIONS Not applicable. NOTE 15 APPLICABLE INSTALLATION, MAINTENANCE & OVERHAUL MANUALS PW545A Installation Manual P&WC Engineering Report 3159 PW545B Installation Manual P&WC Engineering Report 5715 PW545C and PW545D Installation Manual P&WC Engineering Report 6725 PW545A: Maintenance Manual P/N 30J1272 Overhaul Manual P/N 30J1273 PW545B: Maintenance Manual P/N 30J2242 Overhaul Manual P/N 30J2243 PW545C: Maintenance Manual P/N 30J2302 Overhaul Manual P/N 30J2303 PW545D: Maintenance Manual P/N 30J3292 Overhaul Manual P/N 30J3293 Recommended overhaul and inspection intervals are listed in P&WC Maintenance Manuals. PW545C FADEC interface Control Document ER6612. PW545D FADEC interface Control Document ER11051. NOTE 16 IMPORT REQIREMENTS Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document) and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. NOTE 17 LIFE LIMITED PART INFORARMATION Certain engine parts are life limited. Life limits are listed in Airworthiness Limitation Section of Maintenance Manual. NOTE 18 MILITARY MODEL INFORMATION Not applicable. TCDS E00059EN PAGE 6 NOTE 19. ROTOR SPEEDS ENGINE SPEED LIMITATIONS (RPM)) MODELS PW545A PW545B PW545C PW545D ENGINE SPEED LIMITATIONS RPM Max Steady State Low Rotor (N1) Max Steady State High Rotor (N2) 13,084 33,289 - - 33,622 - - - - - - - - Minimum permissible flight idle N2 is: PW545A: 16,841 RPM (51.5%) PW545B: 17,396 RPM (53.2%) PW545C and PW545D: 17,723 RPM (54.2%) NOTE 20. OUTPUT SHAFT TORQUE LIMITS Not applicable NOTE 21 BLEED AIR EXTRACTION PROVISIONS AIR BLEED, ALL MODELS: A. High compressor bleed. Maximum external bleed air available is: B. During starting: C. Bleed air contamination meets: 63 pounds per minute (ppm) at sea level, decreasing linearly to 39 ppm at 40,000 ft, then decreasing linearly to 38 ppm at 45,000 ft. Bleed air not permitted. Para 3.1.2.11.3 of MIL-E-5007E NOTE 22 ROTOR DISK INTEGRITY AND ROTOR BLADE CONTAINMENT (where special requirements apply) No special requirements. NOTE 23 FUEL VENTING AND EXHAUST EMISSIONS 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 PW545C engine model. Fuel Venting Emission Standards: 14 CFR §§34.10(b) and 34.11; in addition 40 CFR §§87.10(b) and 87.11. 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 for the PW545C and the ICAO emissions standards identified in Annex 16, Volume II, Fourth Edition, Part III, Chapter 2, Section 2.2.2 for SN, and Part II Chapter 2 for fuel venting have also been demonstrated for the PW545D. ----END----