# TCDS E00083EN: Pratt & Whitney Canada Corp. - Type: Type certificate data sheet - Status: Current - Holder: Pratt & Whitney Canada Corp. - Revision: 4 - Revised: March 24, 2021 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 43, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/24/e4/24e45ab6c75fb6a6002544426028aae7f76147e571eb3f86e90fff02e98e28d9 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/A0D6AEA6E49C4CDB862586B50063AECB.0001 - Page: https://openairdocs.org/tcds/E00083EN ## Models (3) As the data sheet lists them. - PW210S - PW210A - PW210A1 ## 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 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" REV. 4 4 4 4 4 4 "---" 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 E00083EN TCDS NUMBER E00083EN REVISION: 4 PRATT & WHITNEY CANADA.CORP. MODELS: PW210S, PW210A, PW210A1 DATE : March 24, 2021 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 Twin spool free turbine turboshaft engine controlled by a Full Authority Digital Electronic Control (FADEC), with one mixed flow and one centrifugal flow compressor driven by a single Turbine, annular reverse-flow combustor and a reduction gearbox driven by a Power Turbines. MODELS PW210S PW210A PW210A1 RATINGS (See Note 1) SHAFT HORSEPOWER RATINGS [kW] 30 sec. OEI 2 min. OEI Flat 30 sec. and 2 min. OEI Continuous. OEI 1123.4 [837] 1091.3 [814] 1027.1 [766] 802.5 [599] 802.5 [599] 802.5 [599] 1214.3 (905.5) --- 1030.8 (768.6) 875.4 (652.8) 875.4 (652.8) 824.6 (614.9) 1286.6 (946.1) --- - - - - - - - - Maximum Take-Off 30 min. Hover Maximum continuous TCDS E00083EN PAGE 2 COMPONENTS/ CONFIGURATION Electronic Engine Control, Fuel Control Unit (includes fuel pumps, filter and Permanent Magnet Alternator), Air Cooled Oil Cooler, Fuel Oil Heat Exchanger, oil filter, IGV actuator, ignition system (airframe powered) and sensors are included as per approved Parts List. Required equipment includes Chip Detector or other metallic debris detecting device. For additional information including dimensions, weight and CG, optional and aircraft provided equipment drive specifications, refer to Installation Manual The ECS sensors provide signals for cockpit display of Rotor Speed, Torque, ITT, Oil Pressure, Temperature and Impending Bypass; Fuel Low Pressure and Impending Blockage; Exceedances; Cautions; OEI Use and Timer; Engine Out and ECS Faults, refer to FADEC Interface Control Document for details. Refer to Section 8 of the Installation Manual for HIRF and Lightning qualification and conformance. Refer to Electrical drawing appended to Installation Manual and FADEC Interface Control Document for functional and electrical descriptions. FUEL Fuel types and additives conforming to the specifications listed in applicable P&WC Maintenance Manual are approved for use. LUBRICATING OILS Refer to the Installation Manual Table 2-1 for oil pressure and temperature limits. Oil types, brand and additives conforming to the specifications listed in applicable P&WC Maintenance Manual are approved for use. CERTIFICATION BASIS: For PW210S: Title 14 of the Code of Federal Regulations (14 CFR Part 33) effective February 1, 1965, Amendments 33-1 through 33-30 and 2 Special conditions: 33-008-SC: for on ground engine operation in auxiliary power unit (APU) mode 33-009-SC: for 30-minutes all engines operating (AEO) hovering power engine rating For PW210A and PW210A1 Title 14 of the Code of Federal Regulations (14 CFR Part 33) effective February 1, 1965, Amendments 33-1 through 33-30 and 2 Special Conditions: 33-009-SC: for 30-minutes all engines operating (AEO) hovering power engine rating 33-016-SC: for Flat 30-second and 2-minute One Engine Inoperative (OEI) Rating MODEL APPLICATION ISSUED/ REVISED DELETED PW210S PW210A PW210A1 September 27, 2005 February 13, 2013 October 7, 2020 December 5, 2011 August 14, 2015 March 24, 2021 TCDS E00083EN PAGE 3 NOTES NOTE 1 ENGINE RATINGS The engine ratings are based on dry sea level static ICAO standard atmospheric conditions with no accessory loads and no airbleed. 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. TEMPERATURES ENGINE INDICATED TURBINE TEMPERATURE LIMITS (ºC/°F) MODELS PW210S PW210A PW210A1 30 sec. OEI 2 min. OEI Flat 30 sec. and 2 min. OEI OEI Overshoot (5 seconds) Continuous. OEI Maximum Take-Off 30 min. Hover Maximum continuous Transient (20 seconds) Starting 1006/1843 980/1796 --- + 9/16 924/1695 924/1695 (*) 924/1695 886/1627 980/1796 825/1517 --- --- 1020/1868 + 11/20 941/1726 930/1706 930/1706 886/1594 941/1726 825/1517 --- --- - - - - 937/1719 937/1719 937/1719 - - - - - - (*) Refer to Installation Manual for Initial Take-off limit setting FUEL Refer to Section 5 of the Installation Manual. OIL Refer to Installation Manual NOTE 3. PRESSURES FUEL Refer to Section 5 of the Installation Manual. OIL Refer to Installation Manual NOTE 4 ACCESSORY DRIVE PROVISIONS Refer to Installation Manual NOTE 5 MODEL DESCRIPTION PW210S- Installed in the Sikorsky S76D PW210A- Installed in the Leonardo Helicopters AW-169 helicopter. PW210A1- Installed in the Leonardo Helicopters AW-169 helicopter. 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 TCDS E00083EN PAGE 4 NOTE 10 POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS Not applicable. NOTE 11 SPECIAL INSTALLATION REQUIREMENTS The engines meet the requirements of 14 CFR §§ 33.68, 33.76, 33.77 and 33.78 when installed in accordance with the Pratt & Whitney Canada Installation Manual Instructions The Electronic Engine Control Unit has not been fire tested and therefore must not be installed in a designated fire zone. HIRF/Lightning protection and Electromagnetic Interference (EMI) emitted by the EEC System including, cables, are specified in the Installation Manual, Section 8. 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 and the CPLD meet Level A of RTCA/DO254. The engines can be operated with certain detected FADEC faults in accordance with Time Limited Dispatch (TLD) policy. Aircraft considerations are contained in the Installation Manual, and time limits are contained in the Airworthiness Limitations Section of the Maintenance Manual The conditions for starting, running or stopping the engine with the output shaft locked by an aircraft provided rotor brake are specified in the Installation Manual . Configuration of the PW210S engine is defined by Engine Assembly Drawing 30L0022 Configuration of the PW210A and PW210A1 engine is defined by Engine Assembly Drawing 30L1860 Oil Capacity Liters Imperial Gallons U.S. Gallons PW210S: Total: 4.85 1.067 1.281 Useable: 1.05 0.231 0.277 PW210A and PW210A1: Total; 5.78 1.271 1.527 Useable: 1.53 0.336 0.404 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. NOTE 13 SPECIAL OPERATING PROCEDURES Not Applicable NOTE 14 SPECIAL REPAIR OR OVERHAUL LIMITATIONS Required inspections after any use of 30 seconds or 2 minutes OEI power rating, or Flat Rated 30 second and 2 minute OEI Rating, are contained in the Airworthiness Limitation Section of Maintenance Manual. TCDS E00083EN PAGE 5 NOTE 15 APPLICABLE INSTALLATION , MAINTENANCE & OVERHAUL MANUALS Approved Publications: PW210S: Installation Manual P/N 30L2170 (ER6421) FADEC Interface Control Document ER 6368 Airworthiness Limitation Section of Maintenance Manual P/N 30L0892 PW210A and PW210A1: Installation Manual P/N 30L2274 (ER7434) FADEC Interface Control Document P/N 30L2141 (ER7436) Airworthiness Limitation Section of Maintenance Manual P/N 30L2392 ICA PW210S: Maintenance Manual P/N 30L0892 Overhaul Manual P/N 30L0893 PW210A and PW210A1: Maintenance Manual P/N 30L2392 Overhaul Manual P/N 30L2393 NOTE 16 IMPORT REQIREMENTS 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 United States Type Design (Type Certificate Number E00083EN) 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 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 E00083EN PAGE 6 NOTE 19. ROTOR SPEEDS ENGINE ROTOR SPEED LIMITS (RPM)) MODELS PW210S PW210A PW210A1 Gas Generator Speed NG Maximum 30 sec. OEI 2 min. OEI Flat 30 sec. and 2 min. OEI OEI Overshoot (5 seconds) Continuous OEI Maximum Take-Off 30 min. Hover Maximum continuous Transient (20 seconds) Minimum Idle APU mode Power Turbine Speed NP Maximum Transient (20 seconds) Output shaft Speed Maximum Continuous Transient (20 seconds) 52,400 51,900 --- +255 51,000 51,000 51,000 50,400 51,900 29,063 29,063 28,692(**) 31,211 6,514 7,085 --- --- 51,360 - - 50,430 50,100 50,100 49,200 50,430 - - --- 28,120(***) 30,293 15,372 16,560 --- --- - - - - - - - - - - - - - - - - --- - - - - - - - - ** Refer to Installation Manual for NPT limit when Torque is less than 65.8 ft*lbs (89.2 N*m) *** Refer to Installation Manual for NPT limit when Torque is less than 24.6 ft*lbs (33.4 N*m) NOTE 20. OUTPUT SHAFT TORQUE LIMITS ENGINE OUTPUT SHAFT TORQUE LIMITS (ft*lb) [N*m] MODELS PW210S PW210A PW210A1 30 sec. OEI 2 min. OEI Flat 30 sec. and 2 min. OEI OEI Overshoot (5 seconds) Continuous. OEI Take-Off (5-min) 30 min. Hover Maximum continuous Transient (20 seconds) 920.6 [1248] 894.3 [1212] --- +33 [+44.6] 841.7 [1142] 657.6 [ 892] 657.6 [ 892] 657.6 [ 892] 894.3 [1212] --- --- 430 (583) --- 365 (494.9) 310 (420.3) 310 (420.3) 292 (395.9) 473 (641.3) --- --- 455.5 (617.6) - - - - - - - - 480.1 (650.9) NOTE 21 BLEED AIR EXTRACTION PROVISIONS Refer to Section 2 of the Installation Manual NOTE 22 ROTOR DISK INTEGRITY AND ROTOR BLADE CONTAINMENT (where special requirements apply) No special requirements. ----END---- ``` ## ADs (3, in force first) - [AD 2026-16-13](https://openairdocs.org/ad/2026-16-13): Turbine Section · Pratt & Whitney Canada PW210A, PW210A1 and PW210S. Effective Aug 31, 2026 - [AD 2021-15-12](https://openairdocs.org/ad/2021-15-12): Turbine Engine Compressor Section · Pratt & Whitney Canada PW210A and PW210S. Effective Sep 9, 2021 - [AD 2026-13-09](https://openairdocs.org/ad/2026-13-09) (historical): Turbine Section · Pratt & Whitney Canada PW210A, PW210A1 and PW210S. Effective Jul 14, 2026 ## Registered aircraft by registry model (OpenAirDocs) - [Pratt & Whitney Canada PW210S](https://openairdocs.org/engine/pratt-whitney-canada-pw210s): 26 aircraft (registry code 52294) - [Pratt & Whitney Canada PW210A](https://openairdocs.org/engine/pratt-whitney-canada-pw210a): 17 aircraft (registry code 51950) --- 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.