TCDS E35NE

* PAGE 1 2 3 4 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" REV. 9 9 9 9 "---" 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 E35NE TCDS NUMBER E35NE REVISION: 10* DATE: February 5, 2015 PRATT & WHITNEY CANADA MODELS: PW305 PW306A PW306D PW305A PW306B PW306D1 PW305B PW306C Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E35NE) 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 PW305 PW305A PW305B PW306A PW306B PW306C PW306D PW306D1 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 NOTES 4 AND 14 Normal takeoff (5 minutes) Maximum takeoff (5 minutes) Maximum continuous (See Note 8) 5,225 5,225 4,750 4,679 4,679 4,679 5,204 5,266 4,483 6,040 6,040 6,040 6,050 --- 6,050 5,770 --- 5,770 5,907 --- 5,907 5,907 --- 5,907 FUEL TYPE For PW305, PW305A, and PW305B: Refer to Pratt & Whitney Canada (PWC) Service Bulletin 24004 or Maintenance Manual 30B1401. For PW306A: Refer to Maintenance Manual 30B1412. For PW306B: Refer to Maintenance Manual 30B4132. For PW306C: Refer to Maintenance Manual 30B4422. For PW306D/D1: Refer to Maintenance Manual 30B7302. OIL TYPE For PW305, PW305A, and PW305B: Refer to PWC Service Bulletin 24001 or Maintenance Manual 30B1401. For PW306A: Refer to Maintenance Manual 30B1412. For PW306B: Refer to Maintenance Manual 30B4132. For PW306C: Refer to Maintenance Manual 30B4422. For PW306D/D1: Refer to Maintenance Manual 30B7302. EQUIPMENT/COMPONENTS Fuel pump; fuel filter and electrical impending bypass indicator; control system-dual channel FADEC with dedicated power source; 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. TCDS E35NE PAGE 2 CERTIFICATION BASIS For the PW305, PW305A, and PW305B, Title 14 of the Code of Federal Regulations (14 CFR Part 33) effective February 1, 1965, including Amendments 33-1 through 33-11 and 14 CFR Part 34, Amendment 5a, effective October 23, 2013 (See Note 19). For the PW306A, PW306B, PW306C, PW306D, and PW306D1, 14 CFR Part 33, effective February 1, 1965, including Amendments 33-1 through 33-11 plus §§ 33.28 Amendment 15, 33.76 Amendment 20, 33.77 Amendment 19 and 33.78 Amendment 19 and 14 CFR Part 34, Amendment 5a, effective October 23, 2013 (See Note 19). Type Certificate E35NE Issued/Revised DATE OF DATE TC ISSUED MODEL APPLICATION OR REVISED PW305 06/26/90 04/11/91 PW305A 10/15/92 01/14/93 PW305B 12/22/92 02/17/93 PW306A 08/07/98 12/04/98 PW306B 08/07/98 12/04/98 PW306C 04/10/01 07/12/02 PW306D 12/02/11 09/24/13 PW306D1 09/12/14 02/05/15 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 E35NE) 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 FAR 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 PW305 PW305A PW305B PW306A PW306B PW306C PW306D PW306D1 NOTE 1. ENGINE ROTOR SPEED LIMITS (RPM) Low rotor speed (N1)* maximum High rotor speed (N2)** maximum 10,820 102% 27,469 102% - - - - - - - - - - - - - - - - 11,138 105% 28,277 105% - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - * 100% N1 = 10,608 ** 100% N2 = 26,930 NOTE 2. ENGINE INTERTURBINE TEMPERATURES LIMITS (oC/oF) Normal takeoff Maximum takeoff Maximum continuous Starting transient (20 seconds) 760/1445 785/1445 785/1445 680/1256 - - - - - - 950/1742 - - - - - - 680/1256 890/1634 920/1688 920/1688 950/1742 920/1688 --- - - - - - - --- - - - - - - --- - - - - - - --- - - - - TCDS E35NE PAGE 3 NOTE 3. AMBIENT TEMPERATURE LIMITS (oC/oF) Normal takeoff Maximum takeoff Maximum continuous 15.0/59.0 22.0/71.6 19.4/66.9 26.6/79.8 33.9/93.0 20.8/69.4 15.0/59.0 23.5/74.3 27.5/81.5 26.7/80 31.7/89 26.7/80 35/96 --- 35/96 33/91.4 --- 32/89.6 32/89.6 --- 30/86.0 32/89.6 --- 30/86.0 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. NOTE 6. ENGINE OIL TEMPERATURE/PRESSURE LIMITS AND CAPACITY Refer to the Installation Manual. Useable capacity: PW305, PW305A, PW305B: 4.73 liters; 1.04 imperial gallons; 1.25 U.S. gallons PW306A, PW306B, PW306C, PW306D, PW306D1: 5.0 liters; 1.10 Imperial gallons; 1.32 U.S. gallons NOTE 7. Pressure Temperature Viscosity ENGINE FUEL LIMITS Refer to the Installation Manual. Refer to the Installation Manual. Maximum for operation equals 12 centistroke. NOTE 8. The take-off ratings that are nominally limited to 5 minutes duration may be used for up to 10 minutes for one engine inoperative operations during takeoff. Refer to the Engine Maintenance Manual Chapter 05-10-00 for any subsequent required maintenance actions. NOTE 9. The PW305 and PW306 series engines are approved for multiple-engine installations only. NOTE 10. The PW305 and PW306 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. The airworthiness limitations manual P/N 30B2978 for the PW306B has been superseded by data in the airworthiness limitations section of the 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. Fuel venting and exhaust emissions requirements revised. See Note 19. NOTE 14. The PW305, PW305A, PW305B and PW306A engines include provisions for automatic power increase to Maximum Takeoff. For these engine models the limitations stated for Normal Takeoff are to ensure that the Maximum Takeoff limitations are not exceeded in the event of an automatic power increase to Maximum Takeoff Power. Refer to Table 2-1 in the Installation Manual. For the PW305, PW305A, PW305B, and PW306A engine models, the Maximum Takeoff rating is the maximum approved takeoff power. For the PW306B, PW306C, PW306D, and PW306D1 the Normal Takeoff rating is the maximum approved takeoff power. NOTE 15. For PW305 series engines: The Electronic Engine Control system conforms to the lightning test defined by the SAE AE4L committee report, AE4L-87-3, using level 4 Waveforms. For installation requirements, refer to the Installation Manual. Models PW306 series engines: For HIRF and lightning conformance, and installation requirements, refer to the Installation Manual. TCDS E35NE PAGE 4 NOTE 16. The software contained in the Electronic Engine Control system for the PW305 series engines has been designed, developed, tested, and documented in accordance with the provisions of Critical Category Level 1 of RTCA/DO178A. The software contained in the Electronic Engine Control system for the PW306 series engines has been designed, developed, tested, and documented in accordance with the provisions of Critical Category Level A of RTCA/DO178B. NOTE 17. MODEL DESCRIPTION PW305 Basic model PW305A Similar to PW305 but with reduced thrust ratings and configuration changes to suit the aircraft installation. PW305B Similar to PW305 but with increased thrust ratings and configuration changes to suit the aircraft installation. PW306A Similar to PW305 but with increased thrust ratings, redesigned fan and first stage high pressure compressor, and hot section modifications to accommodate increased gas path temperatures. PW306B Similar to PW305 but with increased thrust ratings, redesigned fan and first stage high pressure compressor, and hot section modifications to accommodate increased gas path temperatures. PW306C Similar to PW306A but with reduced thrust ratings and configuration changes to suit the aircraft installation. PW306D/D1 Similar to PW306C with increased thrust ratings and a canted bypass duct to revector thrust inboard. NOTE 18. The PW306B, PW306C, PW306D, and PW306D1 engines are approved for operation with certain detected FADEC faults in accordance with time limited dispatch policy. The operating time limits are contained in the Airworthiness Limitations Section of the Maintenance Manuals. Aircraft considerations are contained in the Installation Manuals. NOTE 19. 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 PW305, PW305A, PW305B, PW306A, PW306B, PW306C, PW306D, and PW306D1: For the PW305, PW305A, PW305B, PW306A, PW306B, PW306C, PW306D, and PW306D1: Fuel Venting Emissions Standards: 14 CFR §§ 34.10(b) and 34.11; in addition, 40 CFR §§ 87.10(b) and 87.11. For the PW305, PW305A, PW305B, PW306C, PW306D, and PW306D1: 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, PWC 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 PW306A and PW306B: Smoke Number (SN) emission Standards: 14 CFR § 34.21(e)(2); and 40 CFR § 87.23(c)(1). Carbon Monoxide (CO) Emissions Standards: 14 CFR § 34.21(d)(1)(ii); and 40 CFR § 87.23(c)(1). Hydrocarbons (HC) Emissions Standards: 14 CFR § 34.21(d)(1)(i); and 40 CFR § 87.23(c)(1). Oxides of Nitrogen (NOx) Emissions Standards: 14 CFR § 34.23(b)(1); and 40 CFR § 87.23(c)(3). In addition to the FAA’s finding of compliance based on the certification requirements defined in this TCDS, PWC 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 and Part II Chapter 2 for fuel venting have also been demonstrated. NOTE 20. Deleted. ----END----