TCDS E00071EN

* PAGE 1 2 3 4 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" REV. 5 5 4 3 "---" NOT APPLICABLE NOTICE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00071EN TCDS NUMBER E00071EN Revision 5 DATE: August 9, 2024 PRATT & WHITNEY CANADA CORP. MODELS: PW307A PW307D Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00071EN) and other approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificate 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, Quebec Canada J4G 1A1 I. MODELS PW307A PW307D TYPE Twin-spool axial flow turbofan propulsion engine incorporating a single-stage fan, multi-stage axial-centrifugal compressor, annular combustor, two-stage high pressure turbine, and three-stage low pressure turbine. RATINGS POUNDS THRUST / SEE NOTE 4 Normal takeoff (5 minutes) Maximum takeoff (5 minutes) Maximum continuous 6,405 --- 6,405 6,725 --- 6,725 FUEL TYPE For PW307A: Refer to Maintenance Manual P/N 30P0422. For PW307D: Refer to Maintenance Manual P/N 30P3242. OIL TYPE For PW307A: Refer to Maintenance Manual P/N 30P0422. For PW307D: Refer to Maintenance Manual P/N 30P3242. EQUIPMENT/COMPONENTS For PW307A: Fuel pump; fuel filter, oil cooled oil cooler, electrical fuel impending bypass and bypass indicator; control system-dual channel FADEC with dedicated power source; oil pressure sensor, oil temperature sensor, electrical oil impending bypass and bypass indicator, vibration sensor, N1 speed sensor, N2 speed sensor, P3 pressure transducer, BOV solenoid, variable vane actuator, fire detector, P1/T1 probes, fuel temperature sensor, fuel pressure switch and provision for fuel flowmeter are standard equipment as shown in the Approved Parts List. Required equipment also includes a chip detector or other metallic debris-detecting device. For output drive specification, accessory drives, principal dimensions, weights, inertias, and center of gravity (CG) locations, refer to the Installation Manual. For additional information, refer to the Installation Manual or to the Parts List. For PW307D: As per PW307A, with the exception of the fuel temperature sensor which is deleted. TCDS E00071NE PAGE 2 CERTIFICATION BASIS 14 CFR Part 33 effective February 1, 1965, and Amendments 33-1 to 33-20. The following models comply with 14 CFR Part 34, Amendment 7A, effective May 24, 2024. See note 23 for the certification basis for the fuel venting and exhaust emissions: PW307A and PW307D. Type Certificate E00071EN Issued/Revised DATE OF DATE TC ISSUED MODEL APPLICATION OR REVISED PW307A 4/21/2005 8/10/2005 PW307D 10/30/2014 11/20/2015 IMPORT REQUIREMENTS To be considered eligible for installation on U.S. - registered aircraft, each engine to be exported to the United States shall be accompanied by a certificate of airworthiness for export or certifying statement endorsed by the exporting cognizant civil airworthiness authority and containing the following language: (1) This engine conforms to its United States type design (Type Certificate Number E00071EN) 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 or propellers 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 I. MODELS PW307A PW307D NOTE 1. ENGINE ROTOR SPEED LIMITS (RPM) Low rotor speed (N1) maximum High rotor speed (N2) maximum 11,110 101% 28,500 100% 11,110 101% 28,500 100% NOTE 2. ENGINE INTERTURBINE TEMPERATURES LIMITS (oC/oF) Normal takeoff (5 minutes) Maximum takeoff (5 minutes) Maximum continuous Starting transient (5 seconds) 920/1688 --- 920/1688 950/1742 920/1688 --- 920/1688 950/1742 NOTE 3. Reserved NOTE 4. The engine ratings are based on dry sea level static ICAO standard atmospheric conditions. No external accessory loads and no air bleed. The quoted ratings are obtained on a test stand with the specified fuel and oil, without intake ducting and utilizing the exhaust duct and intake defined in the approved Installation Manual. NOTE 5. ENGINE AIRBLEED LIMITS Refer to the Installation Manual, Section 2 TCDS E00071NE PAGE 3 NOTE 6. ENGINE OIL TEMPERATURE/PRESSURE LIMITS AND CAPACITY Refer to the Installation Manual, Table 2-1 Total capacity: PW307A and PW307D; 7.10 liters; 1.56 imperial gallons; 1.88 U.S. gallons NOTE 7. Pressure Temperature ENGINE FUEL LIMITS Refer to the Installation Manual, Section 6. Refer to the Installation Manual, Section 6. NOTE 8. Reserved NOTE 9. The PW307 series engines are approved for multiple-engine installations only. NOTE 10. The PW307 series engines meet Transport Canada and FAA requirements for operation in icing conditions. These engines also meet the requirements of Canadian Airworthiness Manual 533.27 and do not require external armoring. NOTE 11. Life limits for critical rotating components are published in the airworthiness limitations section of each maintenance manual. NOTE 12. The recommended engine operating time between overhauls and hot section inspection intervals are published in Chapter 5 of each Maintenance Manual. NOTE 13. The PW307 series engines meet fuel venting requirements of 14 CFR Part 34, effective September 10, 1990, including amendments 1 through 3 inclusive. NOTE 14. Reserved NOTE 15. For HIRF and lightning conformance, and installation requirements, refer to the Installation Manual. NOTE 16. The software contained in the Electronic Engine Control system for the PW307 series engines has been designed, developed, tested, and documented in accordance with the provisions of Critical Category Level A of RTCA/DO178B. NOTE 17. Reserved NOTE 18. The PW307 series engines are approved for operation with Time Limited Dispatch (TLD) limitations. The dispatch criteria are contained in the Airworthiness Limitations section of each Maintenance Manual. NOTE 19. The PW307 series engines’ bill of materials does not include a thrust reverser. Considerations for the installation of a thrust reverser are contained in the Installation Manual. . NOTE 20. Minimum permissible flight idle N2 is 17,100 RPM (60%). It is corrected above 60% (A 60% mechanical stop is built into the software.) TCDS E00071NE PAGE 4 NOTE 21. NOTE 22. Approved Publications PW307A PW307D Installation Manual ER5598 P/N 30P3400 FADEC Interface Control Doc. ER5520 ER8652 Engine Assy. Parts List – 1st A 30P0100-01 A30P3300-01 Production engine Airworthiness Limitation P/N 30P0422 P/N 30P3242 Section of Maintenance Manual Maintenance Manual P/N 30P0422 P/N 30P3242 Overhaul Manual P/N 30P0423 P/N 30P3243 Service Bulletins, Structural Repair Manuals, Vendor Manuals, Aircraft Flight Manuals and Maintenance Manuals, which contain a statement that the document is Transport Canada approved, is accepted by the FAA and is considered FAA approved. These approvals pertain to the type design only. NOTE 23. The following emissions standards promulgated in 14 CFR Part 34, Amendment 5A, effective October 23, 2013, and 40 CFR Part 87, effective July 18, 2012, have been complied with for the PW307A and PW307D. For the PW307A and PW307D: 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 § 34.21(e)(2); in addition, 40 CFR § 87.23(c)(1). Carbon Monoxide (CO) Emission Standards: 14 CFR § 34.21(d)(1)(ii); in addition, 40 CFR § 87.23(c)(1). Hydrocarbons (HC) Emission Standards: 14 CFR § 34.21(d)(1)(i); in addition, 40 CFR § 87.23(c)(1). Oxides of Nitrogen (NOx) Emission Standards: 14 CFR § 34.23(b)(1); in addition, 40 CFR § 87.23(c)(3). 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, Section 2.3.2 for CO and HC, Section 2.3.2.e for NOx (also known as CAEP/8), and Part II Chapter 2 for fuel venting have also been demonstrated. ----END---