# TCDS E21NE: Pratt & Whitney Canada Corp. - Type: Type certificate data sheet - Status: Current - Holder: Pratt & Whitney Canada Corp. - Revision: 5 - Revised: June 4, 2007 - Product: Engine - Certification basis: Part 21, Part 27, Part 33 - Registered aircraft: 193, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/a6/a6/a6a69dc4857417cf5ed964df15e59f3939455e9d19c070342e268bef65e89e3f - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/1D9D41AD13FD117C86257547006E6309.0001 - Page: https://openairdocs.org/tcds/E21NE ## Models (5) As the data sheet lists them. - PT6B-37A - PT6B-37 - PT6B-36 - PT6B-36B - PT6B-36A ## 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 REV. 5 5 5 4 4 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES IF ANY, ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E21NE TCDS NUMBER E21NE REVISION: 5* DATE: June 4, 2007 PRATT & WHITNEY CANADA MODELS: PT6B-36 PT6B-37 PT6B-36A PT6B-37A PT6B-36B Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E21NE) 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, Inc. 1000 Marie Victorin Longueuil, Quebec Canada J4G 1A1 I. MODELS PT6B-36 PT6B-36A PT6B-36B PT6B-37 PT6B-37A TYPE A free-turbine turboshaft engine incorporating a multistage compressor with 3 axial and 1 centrifugal stage, a single stage compressor turbine, and a single stage power turbine. RATINGS (SEE NOTE 4) Shaft Horsepower (hp) Maximum continuous Takeoff (5 min.) 30 min. OEI 2.5 min. OEI 870 960 960 1,020 887 981 1,033 1,033 - - - - - - - - 830 900 --- --- 847 917 --- --- FUEL CONTROL Electronic Control Un it: Hamilton Standard Model JFC 132 Hamilton Standard Model 3050087 (PT6B-37A) Hydromechanical Unit: Hamilton Standard Model JFC 132 AlliedSignal Model DP-F2 (PT6B-37) FUEL PUMP Part of Hydromechanical Unit assembly Sundstrand Model 025323-700 (PT6B-37) FUEL Fuel conforming to P&WC Specifica tion No. CPW204 or approved revision. Refer to P&WC Service Bulletin No. 11044 and current revisions for further details. Refer to Maintenance Manual P/N 3053102 for PT6B-37A approved fuels. OIL Oil conforming to P&WC Specificati on No. PWA521 or approved revision Types I or II. Refer to P&WC Service Bulletin No. 11001 and current revisions for acceptable lubricants. Refer to Maintenance Manual P/N 3053102 for PT6B-37A approved oils. TCDS E21NE PAGE 2 PRINCIPAL DIMENSIONS Length, in. nominal Height, in. nominal Width, in. nominal 59.15 (65.89, PT6B-37) 32.5 (35.2, PT6B-37) (35.6, PT6B-37A) 19 (22.6, PT6B-37) I. MODELS (Continued) PT6B-36 PT6B-36A PT6B-36B PT6B-37 PT6B-37A WEIGHT Engine - dry, lbs. (includes external engine accessories) 384 396 400 402.5 407.5 C.G. LOCATION (DRY WEIGHT), IN. Belo w engine horizontal centerline 2.40 (2.78, PT6B-37) (2.75, PT6B-37A) / Aft of engine reference plane 20.93 (25.62, PT6B-37) (25.597, PT6B-37A) / Left of engine vertical centerline 0.39 (with port mounted exhaust duct) and 0.31 (with starboard mounted exhaust duct) (0.23, PT6B-37) (0.21, with dual port exhaust, PT6B-37A). IGNITION SYSTEM Exciter: P& WC P/N 3014365, Bendix Type TGLN-28, P/N 10-381550-1; Plug: P&WC P/N 3031213 or 3027280, Bendix P/N 10-390667-1 or Champion P/N CH30455. CERTIFICATION BASIS: FAR Part 33, effective Februa ry 1, 1965, as amended by 33-1 to 33-9, inclusive, including Canadian Special Requirements as contained in Transport Canada letter to Pratt & Whitney Canada, dated March 5, 1984, which is equivalent to FAR 33, Amendment 10 for the following paragraphs: 33.7, 33.14, 33.17, 33.19, 33.23, 33.27, 33.77, 33.87, 33.88, 33.90, and 33.94. For the PT6B-37A, the basis also includes FAR Part 33, paragraph 33.28 of Amendment 15 for the Digital Electronic Control. TYPE CERTIFICATE E21NE ISSUED/REVISED DATE OF DATE TC ISSUED MODEL APPLICATION OR REVISED PT6B-36 AUG 20, 1984 SEPT 3, 1985 PT6B-36A JUN 9, 1986 AUG 19, 1986 PT6B-36B MAR 12, 1992 SEPT 14, 1992 PT6B-37 DEC 5, 1997 NOV. 23, 1998 PT6B-37A MAR 23, 1999 AUG 23, 1999 IMPORT REQUIREMENTS To be considered for installati on on United States 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, which contains the following language: 1. This engine conforms to its Unite d States type design (Type Certificate Number E21NE) 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 United States for which a United States 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. TCDS E21NE PAGE 3 NOTES I. MODELS PT6B-36 PT6B-36A PT6B-36B PT6B-37 PT6B-37A NOTE 1 MAXIMUM PERMISSIBLE ENGINE OPERATING SPEEDS (RPM) Output Shaft Maximum continuous Takeoff (5 min.) 30 min. OEI 2.5 min. OEI No load* Transient (10 sec.) Gas Generator Maximum continuous Takeoff (5 min.) 30 min. OEI 2.5 min. OEI No load Transient (30 sec.) Power Turbine Maximum continuous Takeoff (5 min.) 30 min. OEI 2.5 min. OEI No load* Transient (10 sec.) 6,469 6,469 6,469 6,469 6,589 6,918 38,400 38,400 38,400 39,000 --- 39,100 33,945 33,945 33,945 33,945 34,575 36,300 - - - - - - - - - - - - - - - - 39,000 - - --- - - - - - - - - - - - - - - - - - - - - - - - - - - 39,400 39,400 40,000 40,000 --- 40,200 - - - - - - - - - - - - 4,373 4,373 --- --- 4,569 4,810 38,100 39,300 --- --- --- 39,500 33,036 33,036 --- --- 34,523 36,337 4,504 4,504 --- --- 4,723 - - - - - - --- --- --- - - 34,027 34,027 --- --- 35,678 36,339 *This speed is permitted to output torques not exceeding 175.0 lb-ft. NOTE 2 MAXIMUM PERMISSIBLE INTERTURBINE TEMPERATURES (oC / oF) Maximum Continuous Takeoff (5 min.) 30 min. OEI 2.5 min. OEI Starting (5 sec.) Transient (5 sec.) 776/1429 816/1501 816/1501 850/1562 940/1724 850/1562 - - - - 844/1551 844/1551 - - 870/1598 - - - - - - - - - - - - 755/1391 810/1490 --- --- - - 860/1580 - - - - --- --- - - - - NOTE 3 MAXIMUM PERMISSIBLE OUTPUT TORQUE, FOOT-POUNDS Maximum continuous Takeoff (5 min.) 30 min. OEI 2.5 min. OEI No load Transient (10 sec.) 795 877 877 932 0 1,000 - - - - 932 - - - - - - - - - - - - - - - - - - 997 1080 --- --- - - 1150 - - - - --- --- - - - - NOTE 4. Engine ratings are based on static sea level standard conditions of (dry) inlet air at 59oF and 29.92 in. Hg with no external accessory loads and no airbleed. The quoted ratings are obtainable on a test stand with the specified fuel and oil, without intake ducting and using the exhaust port defined in the Installation Manual. TCDS E21NE PAGE 4 NOTE 5. FUEL AND OIL PRESSURE AND TEMPERATURE LIMITS: Fuel Pressure Inlet head boost pump is required. Minimum pressure at the inlet to the engine driven fuel pump must be such that the vapor/liquid ratio of the fuel does not exceed 0.2. Maximum wet lift: 72 inches; maximum dry lift: 72 inches. Oil Pressure The following limits apply at gas generator speed above 30,000 rpm (27,000 rpm for PT6B-37, -37A), below 30,000 rpm (27,000 rpm for PT6B-37, -37A) gas generator speed, the minimum oil pressure is 40 psig. Normal Range: 70-105 psig maximum (PT6B-36, -36A, -36B) 80-110 psig maximum (PT6B-37, -37A) No Load: 40 psig minimum Starting: 300 psig maximum Oil Temperature Normal Range: 0-115oC (PT6B-36, -36A, -36B) 10-115 oC (PT6B-37, -37A) Starting minimum: -54oC (PT6B-36, -36A, -36B) -40 oC (PT6B-37, -37A) NOTE 6. ACCESSORY DRIVE PROVISIONS PT6B-36/36A/36B MAXIMUM TORQUE (lb-in) MAXIMUM OVERHUNG ROTATION SPEED RATIO CONTINUOUS STATIC MOMENT (lb-in) Driven by gas generator turbine: Oil cooler blower (optional) Starter generator Driven by gas generator turbine: AC generator C C CC .3153* .2879* .3776** 60 140 300 800 1,600 1,500 150 250 250 C = Clockwise, CC = Counterclockwise * Gas Generator Speed (Ng) 100% = 38,400 rpm ** Power Turbine Speed (Np) 100% = 31,432 rpm NOTE 6. ACCESSORY DRIVE PROVISIONS PT6B-37/-37A MAXIMUM TORQUE (lb-in) MAXIMUM OVERHUNG ROTATION SPEED RATIO CONTINUOUS STATIC MOMENT (lb-in) Starter-generator Hydraulic pump AGB tachometer Optional accessory drive Aircraft accessory drive RGB tachometer C CC CC CC C CC 0.2931* 0.20412* 0.1121* 0.1019* 0.32075* 0.1269** 170 150 7 60 135 7 1600 800 100 800 800 100 250 25 10 25 25 10 C = Clockwise, CC = Counterclockwise * Gas Generator Speed (Ng) 100% = 38,060 rpm ** Power Turbine Speed (Np) 100% = 33,036 rpm NOTE 7. The engines meet the requirements of FAR 33. 68 for operation in icing conditions as defined in FAR 25, Appendix C, provided that the intake system conforms with the P&WC Installation Manual Instructions for inertial separation of snow and icing particles. TCDS E21NE PAGE 5 NOTE 8. Overhaul Manual P/N 3034443 (PT6B-36, -36A, -36B), P/N 3043603 (PT6B-37), P/N 3053103 (PT6B-37A). Until the Overhaul Manual is available, all overhauls must be performed by P&WC to new engine standards. NOTE 9. Maintenance Manual P/N 3034442 (PT6B-36, -36A, -36B), P/N 3043602 (PT6B-37), P/N 3053102 (PT6B-37A). NOTE 10. External airbleed shall not exceed 5.25% of inlet airflow. No airbleed is permissible during the starting cycle. NOTE 11. The lightning protection requi rement and the maximum allowable electromagnetic interference for the Electronic Engine Control System are specified in the P&WC Installation Manual, (Chapter 6 PT6B-36, -36A, -36B and Chapter 7 PT6B-37, -37A). NOTE 12. The engine electronic control software meets "Flight Critical" standard of RTCA/DO178. For PT6B-37A, the engine electronic control software meets "Flight Critical" category level A of RTCA/DO-178B. NOTE 13. Life limits for critical rotating components are published in P&WC Service Bulletin No. 11002 (PT6B-36, -36A, -36B) or 32002 (PT6B-37), Maintenance Manual P/N 3053102 (PT6B-37A) or approved revisions. NOTE 14. Engine and accessory time between overhaul (TBO) and engine time between inspections (TBI) are published in P&WC Service Bulletin No. 11003 (PT6B-36, -36A, -36B) or 32003 (PT6B-37), Maintenance Manual P/N 3053102 (PT6B-37A) or approved revisions. NOTE 15. Foreign object ingestion prot ection. The engine has demonstrated the ingestion requirements of FAR 33.77 provided that the intake system conforms with the P&WC Installation Manual Instructions. NOTE 16. The PT6B-36 and PT6B-36A engines meet the fuel venting requirements of SFAR 27. Effective February 1, 1974, as amended by Amendments SFAR 27-1 through 27-4. The PT6B-36B, PT6B-37 and PT6B-37A engines meet the fuel venting requirements of FAR 34, effective September 10, 1990. NOTE 17. Maximum permissible operating temperatures of engine and airframe mounted components are specified in the P&WC Installation Manual. NOTE 18. The oil tank is not provided with the engine (PT6B-36, -36A, -36B). The airframe manufacturer is required to supply an oil cooler, oil tank, and connecting tubes. The PT6B-37 and PT6B-37A includes an integral oil tank. NOTE 19. Service bulletins, structural repair manuals , vendor manuals, aircraft flight manuals, and overhaul and maintenance manauals, 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. ----END---- ``` ## ADs (5, in force first) - [AD 2020-18-05](https://openairdocs.org/ad/2020-18-05): Fuel Control/Turbine Engines · Pratt & Whitney Canada PT6B-37A. Effective Oct 7, 2020 - [AD 2019-22-03](https://openairdocs.org/ad/2019-22-03): Turbine Engine Reduction Gear · Pratt & Whitney Canada PT6B-37A. Effective Dec 24, 2019 - [AD 2004-20-04](https://openairdocs.org/ad/2004-20-04): Compressor rear hubs · Pratt & Whitney Canada PT6B-36A and PT6B-36B. Effective Oct 18, 2004 - [AD 88-03-01](https://openairdocs.org/ad/88-03-01): Compressor Stator Assembly · Pratt & Whitney Canada PT6B-36A. Effective Nov 29, 1988 - [AD 2015-20-04](https://openairdocs.org/ad/2015-20-04) (historical): Reduction gearbox (RGB) assembly · Pratt & Whitney Canada PT6B-37A. Effective Nov 18, 2015 ## Registered aircraft by registry model (OpenAirDocs) - [Pratt & Whitney Canada PT6B-37A](https://openairdocs.org/engine/pratt-whitney-canada-pt6b-37a): 186 aircraft (registry code 52179) - [Pratt & Whitney Canada PT6B-36B](https://openairdocs.org/engine/pratt-whitney-canada-pt6b-36b): 4 aircraft (registry code 52177) - [Pratt & Whitney Canada PT6B-36A](https://openairdocs.org/engine/pratt-whitney-canada-pt6b-36a): 3 aircraft (registry code 52176) - [Pratt & Whitney Canada PT6B-36](https://openairdocs.org/engine/pratt-whitney-canada-pt6b-36): 0 aircraft (registry code 52175) - [Pratt & Whitney Canada PT6B-37](https://openairdocs.org/engine/pratt-whitney-canada-pt6b-37): 0 aircraft (registry code 52178) ## STCs approved under this data sheet (2) - [STC SE00022EN](https://openairdocs.org/stc/SE00022EN): Installation of Oil Tank Filler Neck Check Valve.. Helicopter Support Inc Services Div - [STC SE659NE](https://openairdocs.org/stc/SE659NE): Installation of oil tank filler neck check valve, P/N TSA-76A.. Aviation Components Support --- 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.