# TCDS E00053EN: Pratt & Whitney Canada Inc. - Type: Type certificate data sheet - Status: Current - Holder: Pratt & Whitney Canada Inc. - Revision: 8 - Revised: September 5, 2019 - Product: Engine - Certification basis: Part 21, Part 33, Part 34 - Registered aircraft: 869, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/86/0c/860cdc16e50d9255e2d370c043322baeafc1f61474b8053efdb02f4ff9cf9f35 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/98CE39D51C4F6AEC86258473005976DB.0001 - Page: https://openairdocs.org/tcds/E00053EN ## Models (5) As the data sheet lists them. - PW535B - PW535E - PW530A - PW535A - PW535E1 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text PAGE 1 2 3 4 5 6 7 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" REV. 8 8 8 8 8 8 8 "---" NOT APPLICABLE NOTICE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00053EN 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 TYPE Twin spool turbofan with single stage integrally bladed fan, one axial low compressor stage (PW535A, PW535B, PW535E and PW535E1), two axial high compressor stages and one centrifugal compressor stage, one stage high pressure turbine, two stage low pressure turbine, annular reverse-flow combustor and full length annular bypass duct. The PW535B, PW535E and PW535E1 models have a dual channel Full Authority Digital Electronic Control. MODELS PW530A PW535A PW535B PW535E PW535E1 Thrust rating pounds (See note 1) Maximum continuous at sea level 2,843 3400 - - 3360 3478 Maximum Take-off --- --- --- 3360 3478 Takeoff (5 min.) at sea level 2,887 3400 - - 3360 3478 See Note 13 and the Installation Manual FUEL Fuels conforming to specification CPW204. Approved fuels and additives are listed in P&WC Maintenance Manual. OIL Synthetic type conforming to the current PWA 521 (Type II) Specification. Approved Oil brands are listed in P&WC Maintenance Manual. COMPONENTS/ CONFIGURATION For information regarding components and engine configuration refer to the Installation Manual. PRINCIPAL DIMENSIONS Refer to Installation Drawing in approved Installation Manual. WEIGHT & C. G. LOCATION Refer to Installation Drawing in approved Installation Manual. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00053EN TCDS NUMBER E00053EN REVISION: 8 DATE: September 5, 2019 PRATT & WHITNEY CANADA CORP. MODELS: PW530A PW535E PW535A PW535E1 PW535B E00053EN Page 2 of 7 NOTES NOTE 1. ENGINE RATINGS: The engine ratings are based on static sea level conditions: PW530A: Compressor inlet air (dry) 73°F, at takeoff and 59°F at max. continuous. PW535A: Compressor inlet air (dry) 81°F at takeoff , and 67.3°F at max. continuous. PW535B: Compressor inlet air (dry) 81°F at takeoff , and 67.3°F at max. continuous. PW535E: Available to 33°C/91.4°F at takeoff and 24°C/75.2°F at max continuous. PW535E1: Available to 33°C/91.4°F at takeoff and 24°C/75.2°F at max continuous 29.92 in. Hg. No accessory loads or air bleed. Engine intake and exhaust as described in the Department of Transport, Canada, approved Installation Manual. CERTIFICATION BASIS Models: PW530A 14 CFR Part 33, Amendments 1 through 15 inclusive, effective August 16, 1993, and FAR 34 effective September 10, 1990. PW535A 14 CFR Part 33, Amendments 1 through 17 inclusive, effective July 5, 1996, including Federal Aviation Administration Exemption Number 7074 and FAR 34 effective September 10, 1990. PW535B 14 CFR Part 33, effective February 1, 1965, and Amendments 33-1 through 33-20 inclusive, FAR 34-3 and Federal Aviation Administration Equivalent Level of Safety (ELOS) finding: 33.76, Bird Ingestion, para. (c), Amendment 20, ELOS No. 8040-ELOS-06-NE-01. PW535E PW535E1 14 CFR Part 33, effective February 1, 1965, Amendments 33-1 through 33-24, except Amendment 33-21. This model complies with 14 CFR part 34, amendment 5A, effective October 23, 2013. See Note 11 for a detailed summary of the certification basis for fuel venting and exhaust emissions. 14 CFR Part 33, effective February 1, 1965, Amendments 33-1 through 33-24, except Amendment 33-21. This model complies with 14 CFR part 34, amendment 5A, effective October 23, 2013. See Note 11 for a detailed summary of the certification basis for fuel venting and exhaust emissions. TYPE CERTIFICATE NUMBER E00053EN MODEL APPLICATION DATE ISSUED/REVISED PW530A August 25, 1995 APRIL 17, 1996 PW535A March 11, 1997 November 18, 1999 PW535B June 20, 2005 December 20 2006 PW535E February 19, 2007 December 11, 2009 PW535E1 October 3 2018 September 5, 2019 E00053EN Page 3 of 7 NOTE 2. TEMPERATURE LIMITS: TURBINE MODELS PW530A PW535A PW535B PW535E PW535E1 Interturbine temperature (ITT) ℃/℉ Maximum Take-off Takeoff (5 min.) Maximum continuous Starting (5 sec.) Transient (20 sec.) --- 700/1292 700/1292 740/1364 740/1364 --- - - - - - - - - --- - - - - - - - - 725/1337 -- 680/1256 -- 765/1409 - - - - - - - - - - FUEL MODELS PW530A PW535A PW535B PW535E PW535E1 Fuel Pump Inlet Temperature ℃/℉ Maximum starting and operating at sea level Minimum 57/135 -44/-48 - - -41/-43 - - - - 99/210 - - - - - - For typical kerosene type fuels. Refer to Installation Manual for additional information OIL MODELS PW530A PW535A PW535B PW535E PW535E1 Oil Inlet Temperature ℃/℉ Maximum Minimum Transient Maximum 121/250 -40/-40 135/275 (120 seconds) 132.2/270 - - 140.5/285 (200 seconds) - - - - - - - - - - - - - - - - - - NOTE 3. PRESSURES: Fuel Refer to Installation Manual. OIL (psid) PW530A PW535A PW535B PW535E PW535E1 Min. at ground idle & above (to 60% N2) 25 - - - - - - Min at 60% N2 and above 45 - - - - - - Max. 160 - - - - - - Transient Minimum (20 seconds) 0 - - - - - - Transient (400 seconds) 20 - 250 20 - 270 - - - - OIL TANK CAPACITY See Installation Manual Total Capacity Imperial quarts 4.19 See Installation See Installation U.S. quarts 5.03 Manual Manual Usable Capacity Imperial quarts 1.55 U.S. quarts 1.86 E00053EN Page 4 of 7 NOTE 4. ACCESSORY DRIVES: The following apply to the accessory drives, which are provided by the engine and included in the basic engine weight DRIVE ROTATION SPEED RATIO TO TURBINE SHAFT MAXIMUM TORQUE (in-lb) MAXIMUM OVERHANG DRIVEN BY HIGH ROTOR CONTINUOUS STATIC (in-lb) Hydraulic pump Clockwise facing pad .1353:1 (PW530A) .1279:1 (PW535A) .1279:1 (PW535B) .1279:1 (PW535E) .1279:1 (PW535E1) 125 220 220 220 220 1600 40 Starter generator Clockwise facing pad .3843:1 (PW530A) .3634:1 (PW535A) .3634:1 (PW535B) .3634:1 (PW535E) .3634:1 (PW535E1) 240 195 195 200 200 1600 210 210 210 241 241 Total accessory power limit is 22.5 hp. at 50% N2, increasing linearly to 30 hp. at 100% N2 (PW530A, PW535A, PW535B). Total accessory power limit is 24hp. at 52.9% N2, increasing linearly to 34.5 hp. at 100% N2 (PW535E, PW535E1). Refer to Installation Manual for restrictions above 20,000 ft. altitude (PW530A) and allowable 5 minute emergency accessory power extraction. The starter/generator pad 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 Manual for restrictions above 10,000 feet altitude. Refer to the Installation manual for specific details on the PW535E and PW535E1. NOTE 5. MODEL DESCRIPTION: The PW530 series engines incorporate the following characteristics: PW530A Basic model PW535A Similar to PW530A but with increased thrust ratings, redesigned fan, added low compressor axial booster stage, and redesigned low pressure turbine. PW535B Similar to PW535A but with a dual channel Full Authority Digital Electronic Control. PW535E Similar to the PW535B but with improvements to the performance (thrust and SFC) through increased turbine inlet temperatures and an increase in the N2 limit. The modification does not change the N1, MOT, MOP limits of the PW535B. PW535E1 Similar to the PW535E but with increased thrust ratings. The modification does not change the N1, N2, MOT, MOP limits of the PW535E. NOTE 6. ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES PROVIDED AS PART OF ENGINE TYPE DESIGN: Not Applicable NOTE 7. ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES 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 PROVISIONS: Refer to Installation Manual for the engine mount system. NOTE 10. POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS: Not Applicable E00053EN Page 5 of 7 NOTE 11. SPECIAL INSTALLATION REQUIREMENTS: EXHAUST EMISSIONS AND FUEL VENTING 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 PW535E and PW535E1: Fuel Venting Emissions Standards: 14 CFR §§ 34.10(b) and 34.11; in addition, 40 CFR §§ 87.10(b) and 87.11. Smoke number (SN) Emissions 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. FADEC The model PW535E and, PW535E1 electronic engine control has not been fire tested and therefore must not be installed in a designated fire zone. FUEL BLEED Fuel from pump delivery may be extracted to drive jet or turbine pumps in the airplane fuel system. Refer to appropriate Installation Manual. HIRF and LIGHTENING For HIRF and lightning conformance, and installation requirements, refer to the Installation manual. THRUST REVERSERS The engine definition does not include a thrust reverser. All models except the PW535E & PW535E1 have considerations for the installation of a thrust reverser that are contained in the Installation Manual. TIME LIMITED DISPATCH The PW535B engines incorporating SB 30341 are equipped with a FADEC which is approved for Time Limited Dispatch (TLD). The dispatch criteria are defined in the Airworthiness Limitation Section of the Maintenance Manual P/N 3071822. The TLD dispatchable fault configuration is defined in ER 6338-05 Part A Interface Control Document. The PW535B engines not incorporating SB 30341 are not approved for Time Limited Dispatch (TLD). The model PW535E and PW535E1 engines are 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 3072702 and references report number ER 10555 that lists the TLD dispatchable fault catergories. MAXIMUM ACCESSORY TEMPERATURE The engine compartment shall be ventilated as necessary to keep the air temperature surrounding accessory components from exceeding the limits defined in the applicable Installation Manual SOFTWARE The software contained in the Electronic Engine Control for the PW535B, PW535E and PW535E1 engines has been designed, developed, tested and documented in accordance with the provisions of Critical Category Level A of RTCA/DO178B, with portions of the PW535E1 software as Critical Category Level A of RTCA/DO178C. E00053EN Page 6 of 7 NOTE 12. MANUFACTURER’S SERVICE BULLETINS OR OTHER INSTRUCTIONS COVERING MATTERS OF INTEREST: Service bulletins, structural repair manuals, vendor manuals, 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 unless otherwise noted. These approvals pertain to the type design only. NOTE 13. SPECIAL OPERATING PROCEDURES: Model PW530A, PW535A and PW535B The take-off rating and its associated operating limitations may be used for up to 10 minutes in the event of engine out contingency without adverse effects upon the engine airworthiness. Their use is otherwise limited to not more than 5 minutes. Such operations are anticipated on an infrequent basis (as engine failures at take-off events are uncommon) and no limits or special inspections have been imposed. Model PW535E, PW535E1 Normal take-off ratings are nominally limited to 5 minutes duration. Maximum take-off is intended for emergency situations with one engine inoperative with wing anti-ice on, or other aircraft emergencies requiring a single engine to provide air for all wing anti-ice requirements. A total of 10 minutes is allowed for any combination of Maximum take-off and Normal take-off. (Also see Installation Manual) NOTE 14. SPECIAL REPAIR OR OVERHAUL LIMITATIONS: Not Applicable NOTE 15. APPLICABLE INSTALLATION, MAINTENANCE & OVERHAUL MANUALS: MODELS PW530A PW535A PW535B PW535E PW535E1 Installation Manual Maintenance Manual Overhaul Manual Assembly Parts Listing FADEC Interface Control Document ER3562 30J1112 30J1113 A31J1400-01 --- ER3660 3044952 3044953 A3041960-01 --- ER6336 3071822 3071823 A3071463-01 ER6338 ER6639 3072702 3072703 A3072913-01 ER6677 ER6639 3072702 3072703 A3135603 ER10106 NOTE 16. 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 FAR 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." NOTE 17. LIFE LIMITED PART INFORMATION: Certain engine parts are life limited. These life limits are listed in P&WC Maintenance Manual P/N 30J1112 (PW530A) and P/N 3044952 (PW535A) and P/N 3071822 (PW535B) and P/N 3072702 (PW535E, PW535E1). E00053EN Page 7 of 7 NOTE 18. MILITARY MODEL INFORMATION: Not Applicable NOTE 19. ROTOR SPEEDS MODELS PW530A PW535A PW535B PW535E PW535E1 Engine Speed Limitations, RPM / % Maximum steady state low rotor (N1) Maximum steady state high rotor (N2) 15,750 (100%) 32,150 (100%) 15,850 (100%) 33,970 (100%) -- -- -- -- -- -- Refer to Installation Manual for transients Flight Idle Minimum N2 15,880 (49.4%) 17,975 (52.9%) 18,140 (53.4%) 18,717 (55.1%) -- -- The PW535B, PW535E and PW535E1 Flight Idle is a function of ambient pressure. NOTE 20. OUTPUT/PROPELLER SHAFT TORQUE LIMITS: Not Applicable NOTE 21. MAXIMUM PERMISSIBLE COMPRESSOR AIR BLEEDS: AIR BLEED, MODELS: PW530A PW535A PW535B PW535E PW535E1 A. High compressor bleed. Maximum external bleed air available is: 45 pounds per hour (pph) at sea level, decreasing linearly to 36 pph at 20,000 ft altitude, then decreasing linearly to 28 pph at 40,000 ft, then decreasing linearly to 27 pph at 45,000 ft. 71 pph at sea level, decreasing linearly to 54 pph at 32,000ft altitude, then decreasing linearly to 28 pph at 45,000 ft altitude. See Installation Manual See Installation Manual See Installation Manual B. During starting, bleed shall not exceed that taken by a: 0.3 - inch diameter orifice throat - - - - See Installation Manual See Installation Manual C. Bleed air contamination meets: Para 3.18 of MIL-E-5007C Para 3.1.2.11.3 of MIL-E-5007E - - See Installation Manual See Installation Manual NOTE 22. ROTOR DISK INTEGRITY AND ROTOR BLADE CONTAINMENT: (where special requirements apply) Not applicable ----END---- ``` ## ADs (6, in force first) - [AD 2025-05-13](https://openairdocs.org/ad/2025-05-13): Turbine Section · Pratt & Whitney Canada PW535E and PW535E1. Effective Apr 23, 2025 - [AD 2010-18-09](https://openairdocs.org/ad/2010-18-09): Bleed valve/servo valve · Pratt & Whitney Canada PW545A, PW545B and PW530A. Effective Sep 10, 2010 - [AD 2006-24-08](https://openairdocs.org/ad/2006-24-08): Fuel manifold leakage · Pratt & Whitney Canada PW535A. Effective Dec 19, 2006 - [AD 2006-08-13](https://openairdocs.org/ad/2006-08-13): Hydromechanical fuel control (HFC) · Pratt & Whitney Canada PW535A. Effective May 8, 2006 - [AD 2003-03-21](https://openairdocs.org/ad/2003-03-21): Flexible Fuel Tubes · Pratt & Whitney Canada PW530A, PW535A and PW545A. Effective Feb 20, 2003 - [AD 98-17-10](https://openairdocs.org/ad/98-17-10): Compressor Rotor · Pratt & Whitney Canada PW530A. Effective Oct 21, 1998 ## Registered aircraft by registry model (OpenAirDocs) - [Pratt & Whitney Canada PW535E](https://openairdocs.org/engine/pratt-whitney-canada-pw535e): 413 aircraft (registry code 52297) - [Pratt & Whitney Canada PW535E1](https://openairdocs.org/engine/pratt-whitney-canada-pw535e1): 214 aircraft (registry code 52312) - [Pratt & Whitney Canada PW535A](https://openairdocs.org/engine/pratt-whitney-canada-pw535a): 124 aircraft (registry code 52134) - [Pratt & Whitney Canada PW530A](https://openairdocs.org/engine/pratt-whitney-canada-pw530a): 64 aircraft (registry code 52065) - [Pratt & Whitney Canada PW535B](https://openairdocs.org/engine/pratt-whitney-canada-pw535b): 54 aircraft (registry code 52184) --- 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.