# TCDS E20NE: Pratt & Whitney Canada Corp. - Type: Type certificate data sheet - Status: Current - Holder: Pratt & Whitney Canada Corp. - Revision: 16 - Revised: September 22, 2025 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 173, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/42/d2/42d20ca88e9048583fdd7ed8b1a8b45516673468949ebf9597822b0484acb3eb - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID136526835320250923202928.0001 - Page: https://openairdocs.org/tcds/E20NE ## Models (26) As the data sheet lists them. - PW118A - PW118 - PW123B - PW124B - PW127F - PW121A - PW123 - PW119C - PW123E - PW127G - PW123D - PW120 - PW126A - PW121 - PW119B - PW123AF - PW127E - PW123C - PW125B - PW118B - PW120A - PW127M - PW127 - PW127N - PW127XT-M - PW127XT-N ## 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 8 9 10 11 12 REV. 16 14 16 16 16 16 16 16 16 14 16 16 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTICE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E20NE TCDS NUMBER E20NE REVISION: 16 DATE: September 22, 2025 PRATT & WHITNEY CANADA CORP. MODELS: PW118 PW123 PW127 PW118A PW123AF PW127E PW118B PW123B PW127F PW119B PW123C PW127G PW119C PW123D PW127M PW120 PW123E PW127N PW120A PW124B PW127XT-M PW121 PW125B PW127XT-N PW121A PW126A Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E20NE) 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 CERTIFICATE (TC) RECORD Pratt & Whitney Canada, Inc. Pratt & Whitney Aircraft of Canada, Ltd. (Name change of TC Holder) MODELS PW118 PW118A PW118B PW119B PW119C PW120 PW120A PW121 TYPE A three spool free-turbine turboprop propulsion engine incorporating two centrifugal compressors, each driven by independent axial turbines, a reverse flow annular combustor, and a two-stage power turbine that drives a gearbox. RATINGS (See NOTE 13(1)) Maximum takeoff (5 min.), at sea level Equivalent shaft horsepower Shaft horsepower Thrust, pounds Output, RPM Normal takeoff at sea level Equivalent shaft horsepower Shaft horsepower Thrust, pounds Output, RPM Maximum continuous at sea level Equivalent shaft horsepower Shaft horsepower Thrust, pounds Output, RPM --- --- --- --- 1,892 1,800 230 1,300 1,892 1,800 230 1,300 --- --- --- --- 1,893 - - 231 - - 1,893 - - 231 - - --- --- --- --- 1,892 - - 230 - - 1,892 - - 230 - - 2,282 2,180 256 1,339 1,941 1,851 225 1,339 1,941 1,851 225 1,339 - - - - - - - - - - - - - - - - - - - - - - - - 2,100 2,000 250 1,212 1,892 1,800 230 1,212 1,787 1,700 217 1,212 - - - - - - - - - - - - - - - - 1,892 1,800 230 - - 2,252 2,150 255 - - 2,044 1,950 235 - - 2,044 1,950 235 - - E 2 0 N E P a g e 2 MODELS (Continued) PW121A PW123 PW124B PW125B PW126A PW127 PW127E RATINGS (See NOTE 13(1)) Maximum takeoff (5 min.), at sea level Equivalent shaft horsepower Shaft horsepower Thrust, pounds Output, RPM Normal takeoff at sea level Equivalent shaft horsepower Shaft horsepower Thrust, pounds Output, RPM Maximum continuous at sea Level Equivalent shaft horsepower Shaft horsepower Thrust, pounds Output, RPM 2,304 2,200 260 1,212 2,075 1,980 238 1,212 1,992 1,900 230 1,212 2,502 2,380 304 - - 2,253 2,142 279 - - 2,261 2,150 280 - - 2,522 2,400 305 - - 2,272 2,160 - - - - 2,522 2,400 305 - - 2,626 2,500 314 - - 2,367 2,250 290 - - 2,261 2,150 280 - - 2,795 2,662 333 - - 2,518 2,396 306 - - 2,493 2,372 303 - - 2,880 2,750 325 - - 2,594 2,475 297 - - 2,619 2,500 299 - - 2,516 2,400 289 - - 2,266 2,160 265 - - 2,516 2,400 289 - - MODELS (Continued) PW123B PW123C PW123D PW123E PW127F PW123AF PW127G RATINGS (See NOTE 13(1)) Maximum takeoff (5 min.), at sea level Equivalent shaft horsepower Shaft horsepower Thrust, pounds Output, RPM Normal takeoff at sea level Equivalent shaft horsepower Shaft horsepower Thrust, pounds Output, RPM Maximum continuous at sea Level Equivalent shaft horsepower Shaft horsepower Thrust, pounds Output, RPM 2,626 2,500 315 1,212 2,378 2,261 291 1,212 2,262 2,150 280 1,212 2,262 2,150 280 1,212 2,054 1,950 258 - - 2,054 1,950 258 - - - - - - - - - - - - - - - - - - - - - - - - - - 2,502 2,380 304 - - 2,253 2,142 279 - - 2,261 2,150 280 - - 2,880 2,750 325 - - 2,593 2,475 297 - - 2,619 2,500 299 - - --- --- --- --- 2,502 2,380 304 - - 2,261 2,150 280 - - 3,058 2,920 344 1,212 2,771 2,645 315 - - 3,058 2,920 344 - - E 2 0 N E P a g e 3 MODELS (Continued) PW127M PW127N PW127XT-M PW127XT-N RATINGS (See NOTE 13(1)) Maximum takeoff (5 min.), at sea level Equivalent shaft horsepower Shaft horsepower Thrust, pounds Output, RPM Normal takeoff at sea level Equivalent shaft horsepower Shaft horsepower Thrust, pounds Output, RPM Maximum continuous at sea Level Equivalent shaft horsepower Shaft horsepower Thrust, pounds Output, RPM 2,880 2,750 325 1,212 2,593 2,475 297 1,212 2,619 2,500 299 1,212 - - - - - - - - - - - - - - - - - - - - - - - - 2,882 - - 330 - - 2,595 - - 300 - - 2,621 - - 302 - - - - - - - - - - - - - - - - - - - - - - - - - - COMPONENTS/ CONFIGURATION Standard equipment included with the engine are shown in the Parts List. For additional information, refer to Installation Manual. For output drive specifications and C.G. location, refer to Installation Manual. FUEL Approved fuel types are those conforming to current PWC specification CPW 204 and later revisions. For all models (except PW127XT-M and PW127XT-N), refer to the Maintenance Manual (chapter 72-00-00) for approved fuel types and additives. For the PW127XT-M and PW127XT-N, refer to the Maintenance Manual (chapter 73.00.00) or the Installation Manual (Appendix A) for approved fuel types and additives OIL Refer to Installation Drawing in approved Installation Manual For all models (except PW127XT-M and PW127XT-N), refer to the Maintenance Manual (chapter 72-00-00) for approved oil types and brands. For the PW127XT-M and PW127XT-N, refer to the Maintenance Manual (chapter 73.00.00) or the Installation Manual (Appendix B) for approved oil types and brands. PRINCIPAL DIMENSIONS Refer to Installation Drawing in approved Installation Manual DRY WEIGHT, POUNDS INCLUDING ESSENTIAL ENGINE ACCESSORIES PW118 / PW118A / PW118B PW119B / PW119C PW120 / PW120A / PW121 / PW121A PW123 / PW123B / PW123C / PW123D PW123AF PW124B / PW125B / PW126A / PW127 / PW127E / PW127F / PW127G PW127M / PW127N PW127XT-M / PW127XT-N 885 887 957 1,000 1,030 1,060 1,062 1,090 CG LOCATION Refer to Installation Drawing in approved Installation Manual E 2 0 N E P a g e 4 CERTIFICATION BASIS 14 CFR Part 33, effective February 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 September 20, 1983, 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 all models except for PW127N and PW127XT-M. For PW127N FAR Part 33 effective February 1, 1965 and Amendments 33-1 to 33-9 inclusive, and Special Condition SCA 2014-02 (Transport Canada Letter to Pratt and Whitney Canada dated September 20, 1983), Pratt & Whitney Canada Corp, Canadian Special Requirements dated April 25, 2014. PW127XT-M and PW127XT-N 14 CFR Part 33 up to and including Amendment 33-24, except for paragraph 533.27; 14 CFR Part 33 up to and including Amendment 33-32; Exemption 19763 for 33.27(f)(6) Compliance with 14 CFR 34 up to amendment 34-6, dated March 6, 2018. See NOTE 11(1) for detailed summary of the certification basis for fuel venting and exhaust emissions. See NOTE 11(2) for additional emissions information. Type Certificate E20NE issued/revised DATE OF DATE TC ISSUED MODEL APPLICATION OR REVISED PW115 07/17/81 11/21/84* PW118 11/13/86 08/06/86 PW118A 08/14/87 11/13/87 PW118B 03/05/96 03/08/96 PW119B 05/17/93 06/03/93 PW119C 02/08/96 03/08/96 PW120 07/17/81 11/21/84 PW120A 07/17/81 11/21/84 PW121 08/14/87 03/31/88 PW121A 06/05/95 09/08/95 PW123 08/14/87 04/29/88 PW123B 05/19/95 05/24/95 PW123C 05/19/95 05/24/95 PW123D 05/19/95 05/24/95 PW123E 05/19/95 05/24/95 PW124 08/21/84 04/29/88* PW124A 08/14/87 04/29/88* PW124B 10/02/89 02/15/90 PW125B 08/14/87 04/29/88 PW126A 07/07/89 11/27/89 PW127 09/16/92 11/25/92 PW127E 07/20/95 09/08/95 PW127F 09/18/96 10/25/96 PW123AF 04/18/97 05/17/99 PW127G 08/10/99 12/16/99 PW127M 03/07/07 01/09/08 PW127N 02/15/23 06/13/23 PW127XT-M 06/22/20 08/18/23 PW127XT-N 08/27/24 09/04/25 *Engine models PW115, PW124, and PW124A were deleted from Type Certificate E20NE on June 23, 1992. The above were deleted at the request of the type certificate holder. No engines of these models are in existence, nor is there intent to manufacture or convert to these models. E 2 0 N E P a g e 5 NOTES NOTE 1. ENGINE RATINGS: 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 obtainable on a test stand with the specified fuel and oil, without intake ducting and utilizing the exhaust port and intake defined in the approved Installation Manual. NOTE 2. TEMPERATURES MAXIMUM PERMISSIBLE TEMPERATURES (DEGREES FARENHEIT)(See NOTE 13(4)) MODELS PW118 PW118A PW118B PW119B PW119C PW120 PW120A PW121 Interturbine temperature (ITT) Maximum takeoff Normal takeoff Maximum continuous Starting (5 sec.) Transient (20 sec.) --- 1,500 1,472 1,742 1,562 --- - - - - - - - - --- - - - - - - - - 1,472 1,472 1,472 1,742 1,562 - - - - - - - - - - 1501 1,445 - - - - - - - - - - - - - - - - - - - - - - - - - - Air inlet temperature for rated power Maximum takeoff Normal takeoff Maximum continuous --- 91 91 --- 108 108 --- 113 - - 88 118 118 97 - - 127 82 82 91 - - - - - - 78 78 82 MODELS (Continued) PW121A PW123 PW124B PW125B PW126A PW127 PW127E Interturbine temperature (ITT) Maximum takeoff Normal takeoff Maximum continuous Starting (5 sec.) Transient (20 sec.) 1,501 1,456 1,472 1,742 1,562 1,472 1,409 - - - - 1,544 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Air inlet temperature for rated power Maximum takeoff Normal takeoff Maximum continuous 77 77 86 95 95 113 94 94 94 86 86 113 84 84 105 89 89 106 113 113 113 I. MODELS (Continued) PW123B PW123C PW123D PW123E PW127F PW123AF PW127G Interturbine temperature (ITT) Maximum takeoff Normal takeoff Maximum continuous Starting (5 sec.) Transient (20 sec.) 1,472 1,409 1,472 1,742 1,544 - - 1,418 - - - - - - - - - - - - - - - - - - 1,409 - - - - - - - - - - - - - - - - --- 1,472 - - - - - - 1,472 1,409 - - - - - - Air inlet temperature for rated power Maximum takeoff Normal takeoff Maximum continuous 86 86 113 78 78 94 113 113 127 105 105 113 95 95 112 --- - - 113 95 - - 95 I. MODELS (Continued) PW127M PW127N PW127XT-M PW127XT-N Interturbine temperature (ITT) Maximum takeoff Normal takeoff Maximum continuous Starting (5 sec.) Transient (20 sec.) 1,472 1,409 1,472 1,742 1,544 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Air inlet temperature for rated power Maximum takeoff Normal takeoff Maximum continuous 103 103 118 110 110 - - 103 103 - - 110 110 - - Fuel and oil temperature limitations are defined in the applicable Installation Manual. E 2 0 N E P a g e 6 NOTE 3. PRESSURES Fuel and oil pressure limitations are defined in the applicable Installation Manual. NOTE 4. ACCESSORY DRIVE PROVISIONS DRIVE MAXIMUM TORQUE (IN-LB) CONTINUOUS STATIC OVERLOAD SPEED RATIO ROTATION FOR MODELS PW118/118A/118B/ 119B/119C: Starter/Generator: Starting Mode Generating Mode AC Generator Hydraulic Pump O/S Governor FOR MODELS: PW120/120A/121/ 121A/123/123AF/123B/123C/123D/123E: Starter/Generator: Starting Mode Generating Mode AC Generator Hydraulic Pump O/S Governor FOR MODELS PW124B/125B/126A/127/127E/127F, 127G/127M/127N/127XT-M/127XT-N Starter/Generator: Starting Mode Generating Mode AC Generator (11): Integral Drive Generator (IDG) (9/12) 100% Speed 55.3% Speed Hydraulic Pump (10): PW125B Model PW126A Model O/S Governor 407 (4) 210 (7) 132 180 37 407 (4) 210 (7) 250 (8) 180 37 407 (4) 210 380 550 958 180 180 37 1,600 1,600 1,470 1,380 --- 1,600 1,600 2,000 1,300 --- 1,800 1,800 2,500 3,650 3,650 1,500 1,500 --- 800 340 320 200 56.7 800 340 440 200 56.7 800 (6) 340 550 (6) 619 (5) 878 (6) 1,078 (5) 1,450 (6) 400 400 56.7 .36017 (1) .36017 (1) 10.275 (2) 5.8714 (2) 4.1515 (2) .36017 (1) .36017 (1) 12.1949 (3) 6.2623 (3) 4.5333 (3) .36017 (1) .36017 (1) 12.212 (3) 7.073 (3) 3.911 (3) 5.017 (3) 3.504 (3) 4.500 (3) CW CW CW CW CCW CW CW CW CW CCW CW CW CW CW CW CW CW CCW NOTES: (1) Gas generator speed (Ng) 100% = 33,300 RPM (2) Output Shaft Speed (Np) 100% = 1,300 RPM (3) Output Shaft Speed (Np) 100% = 1,200 RPM (4) Not to exceed 60 seconds (5) Not to exceed 5 minutes (6) Not to exceed 5 seconds (7) Not to exceed 24 shp (8) Not to exceed 50.8 shp (9) IDG must be used with hydraulic pump (10) Not used on PW124B/127 models (11) Not used on PW125B model (12) Used on PW125B model only NOTE 5. MODEL DESCRIPTION A three spool free-turbine turboprop propulsion engine incorporating two centrifugal compressors, each driven by independent axial turbines, a reverse flow annular combustor, and a two-stage power turbine that drives a gearbox. E 2 0 N E P a g e 7 NOTE 6. TYPICAL AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES, WITH AIRCRAFT LEVEL REQUIREMENTS, PROVIDED AS PART OF ENGINE TYPE DESIGN: Not Applicable NOTE 7. AIRCRAFTACCESSORIES, 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: The PW100 series engines meet the requirements of FAR 33.68 for operation in icing conditions as defined in FAR 25, Appendix C, when the intake system conforms with the Pratt & Whitney Canada Installation Manual instructions for inertial separation of snow and icing particles. NOTE 9. ENGINE MOUNT SYSTEM PROVISIONS: Refer to Installation Manuals for the engine mount system. NOTE 10. POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS: Not Applicable NOTE 11. SPECIAL INSTALLATION REQUIREMENTS: (1)-All models meet the fuel venting requirements of SFAR 27, effective February 1, 1974, as amended by Amendments SFAR 27-1 through 27-5, and FAR 34. (2)-In addition to FAA finding of compliance based on the certification requirement defined in this TCDS the engine manufacturer h(as declared that the PW127XT-M engine model has shown to comply to AWM Chapter 516, Subchapter B for prevention of Fuel Venting at Change 516-15, which refers to ICAO Annex 16 Volume II, “Aircraft Engine Emissions”, Fourth Edition, July 2017, as amended by and including Amendment 10. (3)-The electronic engine control system (automatic feather control system on PW123AF) meets the lightning protection requirements specified in the SAE AE4L committee report. For specific capabilities and installation requirements refer to Installation Manual. (4)-For PW118, PW120, PW120A, and PW121 models the software contained in the Electronic Control Unit has been developed, documented and tested in accordance with the provisions of the critical category of RTCA/DO-178A November 1981. (5)-For the PW118A, PW118B, PW119B, PW119C, PW121A, PW123, PW123B, PW123C, PW123D, PW123E, PW124B, PW125B, PW126A, PW127, PW127E, PW127F and PW127G models, the software contained in the Electronic Control Unit has been designed, developed, documented and tested in accordance with the provisions of Critical Category Level 1 of RTCA/DO-178A, March 1985. (6)- The PW127M and PW127XT-M software are identical and are modifications of the PW127F software. The PW127N and PW127XT-N software are identical and are a modification of the PW127M software. The modifications have been designed, developed, documented and tested in accordance with the provision of the Level A of RTCA/DO-178B, December 1992. (7)-For PW124B, PW127, PW127E, PW127F, PW127M, PW127N, PW127XT-M and PW127XT-N engine models equipped with a software based Auto-Feather Unit {AFU}, the hardware has been designed, developed, and tested in accordance with RTCA/DO-254 for DAL A equipment, and the software has been designed, developed, and tested in accordance with RTCA/DO-178C, DO-331, and DO-330 for Level A software, except for the Boot Loader (BL) software which was developed to DO-178B on a previous certified program and is re-used in accordance with the guidance of FAA AC 20-115D. (8)-Engines acceptable with both 6 blade and 4 blade propeller installations are: PW118, PW118A, PW118B, PW119B, PW119C, PW120, PW120A, PW121, PW121A, PW123, PW123AF, PW123B, PW123C, PW123D, PW123E, PW124B, PW127, PW127E (BS850) and PW127F (BS 918). Engines acceptable with 6 blade propeller installation only are: PW125B, PW126A, PW127E (BS 1034), PW127F (BS1033), PW127G, PW127M, PW127N, PW127XT-M, and PW127XT-N. E 2 0 N E P a g e 8 (9)-All PW100 series models have been approved with a propeller overspeed capability to cater to propeller control malfunctions. The Engine Installation Manual operating limits define the overspeed limit. NOTE 11. SPECIAL INSTALLATION REQUIREMENTS: (Continued) (10)Oil Tank Capacity PW118, PW118A, PW118B, PW119B, PW119C, PW120, PW120A, PW121 and PW121A Liters Imperial gallons US gallons Usable 3.8 0.83 1.0 Total 17.7 3.9 4.7 PW123, PW123AF, PW123B, PW123C, PW123D, PW123E, PW124B, PW125B, PW126A, PW127, PW127E, PW127F, PW127G, PW127M, PW127NPW127XT-M and PW127XT-N Liters Imperial gallons US gallons Usable 8.0 1.76 2.11 Total 19.3 4.25 5.10 NOTE 12. MANUFACTURER’S SERVICE BULLETINS OR OTHER INSTRUCTIONS COVERING MATTERS OF INTEREST: Service Bulletins, vendor manuals 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: (1)-The PW120, PW120A, PW121, PW121A, PW123, PW123B, PW123C, PW123D, PW123E, PW124B, PW125B, PW126A, PW127, PW127E, PW127F,PW126G, PW127M, PW127N, PW127XT-M and PW127XT-N models include provisions for automatic power increase from Normal Takeoff Power to Maximum Takeoff Power. 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. (2)-For all engine models takeoff ratings that are nominally limited to 5 minutes duration may be used for up to 10 minutes for OEI operations without adverse effects upon engine airworthiness. Such operations are anticipated on an infrequent basis (as engine failure at take-off events are uncommon) and no limits or special inspections have been imposed. (3)-For the PW120, PW120A, PW121, and 123E models, the normal takeoff high pressure rotor speed limitation is variable with ambient temperature to ensure the maximum spool speed is not exceeded in the event of an automatic power increase to maximum takeoff. Refer to the Installation Manual for the normal takeoff limit. (4)-Normal Takeoff ITT limitation is variable with ambient temperature for the following models: PW121A, PW123, PW123B, PW123C, PW123D, PW123E, PW124B, PW125B, PW126A, PW127, PW127E, PW127F, PW127G, PW127M PW127N, PW127XT-M and PW127XT-N. Refer to the applicable engine installation manual for the variable ITT limit. (5)-The speed relationship between the low compressor spool and the high compressor spool is controlled by new engine acceptance procedures and the Overhaul Manual for the PW120, PW120A, and PW121 and PW121A. NOTE 14. SPECIAL REPAIR OR OVERHAUL LIMITATIONS: Recommended maintenance intervals are published in the scheduled inspection section of the engine manual or maintenance manual, as applicable. E 2 0 N E P a g e 9 NOTE 15. APPLICABLE INSTALLATION, MAINTENANCE & OVERHAUL MANUALS: INSTALLATION MANUALS PW118 PW121A PW125B PW127E PW118A PW123 PW126 PW127F PW118B PW123B PW126A PW127G (ER4004) PW119A PW123AF PW127 PW127J (ER4633) PW119B/PW119C PW123C PW127M (ER6830) PW120 PW123D PW127N (3079820) PW120A PW123E PW127XT-M (3136239) PW121 PW124B PW127XT-N (3136239) MAINTENANCE MANUALS PW118, PW118A, PW118B 3034622 PW119B, PW119C 3072152 PW120A, PW121 3034632 PW120, PW121, PW121A 3034642 PW123,PW123B, PW123C, PW123D, PW123E 3036432 PW123AF 3034538 PW124B, PW127, PW127E, PW127F, PW127M, PW127N 3037332 PW125B 3032932 PW126A 3034922 PW127G 3044822 PW127XT-M and PW127XT-N 3136182 OVERHAUL MANUALS PW118, PW118A, PW118B 3034623 PW119B 3038533 PW119C 3038532 PW120, PW121, PW121A 3034643 PW120A, PW121 3034633 PW123,PW123B, PW123C, PW123D, PW123E 3036433 PW123AF 3034539 PW124B, PW127, PW127E, PW127F, PW127M, PW127N 3037333 PW125 3034944 PW126A 3034923 PW127G 3044823 PW127XT-M and PW127XT-N 3136183 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. These approvals pertain to the type design only. NOTE 16. IMPORT REQUIREMENTS: Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document) , and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. NOTE 17. LIFE LIMITED PART INFORMATION: Life limits for critical rotating components are published in the airworthiness limitations section of the engine manual or airworthiness limitations manual, as applicable. E 2 0 N E P a g e 10 NOTE 18. MILITARY MODEL INFORMATION: Not applicable NOTE 19. ROTOR SPEEDS MAXIMUM PERMISSIBLE ENGINE OPERATING SPEEDS (RPM) MODELS PW118 PW118A PW118B PW119B PW119C PW120 PW120A PW121 LIMITATIONS (See NOTES 13(5) & 13(9)) MAXIMUM PERMISSIBLE ENGINE OPERATION SPEEDS (RPM) Output shaft Maximum takeoff Normal takeoff Maximum continuous Transient (20 sec.) Transient (5 sec.) High pressure rotor Maximum takeoff Normal takeoff Maximum continuous Transient (20 sec.) Low pressure rotor Maximum takeoff Normal takeoff Maximum continuous Transient (20 sec.) --- 1,300 1,300 1,430 --- --- 33,300 33,300 33,966 --- 27,700 27,700 28,531 --- - - - - - - --- --- 33,966 33,966 - - --- 28,808 28,808 28,808 --- - - - - - - --- --- - - - - - - --- - - - - - - 1,339 1,339 1,339 1,430 --- 34,200 34,200 34,200 34,700 28,900 28,900 28,900 29,340 - - - - - - - - --- - - - - - - - - - - - - - - - - 1,212 1,212 1,212 1,320 1,440 34,350 * 34,150 34,675 ---** --- --- --- - - - - - - - - - - - - * - - - - ---** --- --- --- - - - - - - - - - - - - * - - - - ---** --- --- --- * See NOTE 13(3); ** See NOTE 13(5) MODELS (Continued) PW121A PW123 PW124B PW125B PW126A PW127 PW127E LIMITATIONS (See NOTES 13(5) & 13(9)) MAXIMUM PERMISSIBLE ENGINE OPERATION SPEEDS (RPM) Output shaft Maximum takeoff Normal takeoff Maximum continuous Transient (20 sec.) Transient (5 sec.) High pressure rotor Maximum takeoff Normal takeoff Maximum continuous Transient (20 sec.) Low pressure rotor Maximum takeoff Normal takeoff Maximum continuous Transient (20 sec.) 1,212 1,212 1,212 1,320 1,440 34,380 33,975 34,160 34,675 ---** --- --- --- - - - - - - - - --- 34,200 33,633 34,200 34,550 28,800 28,170 28,800 28,900 - - - - - - 1,380 --- - - - - - - - - - - - - - - - - - - - - - - - - --- - - 33,750 - - - - - - 28,140 - - - - 1,212 1,212 1,212 - - --- 34,190 33,670 34,190 34,500 28,900 28,280 28,900 28,900 - - - - - - 1,296 1,440 34,360 33,930 34,360 35,440 28,870 28,090 28,870 29,575 1,212 1,212 1,212 - - - - 34,360 33,930 34,360 34,730 - - - - - - - - E 2 0 N E P a g e 11 MODELS (Continued) PW123B PW123C PW123D PW123E PW127F PW123AF PW127G LIMITATIONS (See NOTES 13(5) & 13(9)) MAXIMUM PERMISSIBLE ENGINE OPERATION SPEEDS (RPM) Output shaft Maximum takeoff Normal takeoff Maximum continuous Transient (20 sec.) Transient (5 sec.) High pressure rotor Maximum takeoff Normal takeoff Maximum continuous Transient (20 sec.) Low pressure rotor Maximum takeoff Normal takeoff Maximum continuous Transient (20 sec.) 1,212 1,212 1,212 1,320 --- 34,200 33,633 34,200 34,550 28,800 28,270 28,800 28,900 - - - - - - - - --- - - - - - - - - - - - - - - - - - - - - - - - - --- - - - - - - - - - - - - - - - - - - - - - - - - --- - - * - - - - - - 28,170 - - - - - - - - - - 1,296 1,440 34,360 33,930 34,360 35,440 28,870 28,090 28,870 29,575 --- - - - - 1,320 --- --- 34,200 34,200 34,550 --- 28,800 28,800 28,900 1,212 - - - - --- 1,440 34,530 34,050 34,530 35,440 28,990 28,500 28,990 29,575 *See NOTE 13(3) MODELS (Continued) PW127M PW127N PW127XT-M PW127XT-N LIMITATIONS (See NOTES 13(5) & 13(9)) MAXIMUM PERMISSIBLE ENGINE OPERATION SPEEDS (RPM) Output shaft Maximum takeoff Normal takeoff Maximum continuous Transient (20 sec.) Transient (5 sec.) High pressure rotor Maximum takeoff Normal takeoff Maximum continuous Transient (20 sec.) Low pressure rotor Maximum takeoff Normal takeoff Maximum continuous Transient (20 sec.) 1,212 1,212 1,212 1,296 1,440 34,360 34,930 34,360 33,440 28,870 28,090 28,870 29,575 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - --- - - - - - - - - - - - - - - - - - - - - - - - - --- - - - - - - - - - - - - - - - - E 2 0 N E P a g e 12 NOTE 20. OUTPUT/PROPELLER SHAFT TORQUE LIMITS: (See NOTE 13(1)) MODELS PW118 PW118A PW118B PW119B PW119C PW120 PW120A PW121 MAXIMUM PERMISSIBLE OUTPUT TORQUE (FOOT-POUNDS) Maximum continuous Maximum takeoff Normal takeoff Transient (20 sec.) 7,272 --- 8,000 9,270 - - --- - - - - - - --- - - - - 9,090 9,090 --- 10,570 - - - - --- - - 8,535* 9,850* 8,535* 11,000* - -* - -* - -* - -* - -* - -* - -* - -* *For PW120, PW120A and PW121 engines incorporating either SB 20316 or SB 20380 the transient limit is 12,750 ft-lbs., the maximum takeoff limit is 11,000 ft-lbs., the maximum continuous and normal takeoff limit is 10,000 ft-lbs. MODELS (Continued) PW121A PW123 PW124B PW125B PW126A PW127 PW127E MAXIMUM PERMISSIBLE OUTPUT TORQUE (FOOT-POUNDS) Maximum continuous Maximum takeoff Normal takeoff Transient (20 sec.) 10,000 11,000 10,000 12,750 - - - - - - - - 10,766 11,170 9,454 13,080 9,410 10,965 9,890 14,300 11,650 11,650 11,650 13,080 12,800 12,800 12,800 13,200 12,800 12,800 - - 14,440 MODELS (Continued) PW123B PW123C PW123D PW123E PW127F PW123AF PW127G MAXIMUM PERMISSIBLE OUTPUT TORQUE (FOOT-POUNDS) Maximum continuous Maximum takeoff Normal takeoff Transient (20 sec.) 10,000 11,197 10,000 12,750 10,040 10,040 --- - - - - - - --- - - 10,000 11,000 10,000 - - 12,800 12,800 12,800 14,440 10,000 --- 11,000 12,750 13,000 13,000 13,000 14,440 MODELS (Continued) PW127M PW127N PW127XT-M PW127XT-N MAXIMUM PERMISSIBLE OUTPUT TORQUE (FOOT-POUNDS) Maximum continuous Maximum takeoff Normal takeoff Transient (20 sec.) 12,800 12,800 12,800 14,440 - - - - - - - - - - - - - - - - - - - - - - - - NOTE 21. MAXIMUM PERMISSIBLE COMPRESSOR AIR BLEEDS: Maximum external (HP): Maximum external (LP) PW118 / 118A / 118B / 120 / 120A / 121 / 121A: PW119B/ 119C / 123 / 123AF / 123B / 123C / 123D / 123E / 124B / 125B / 126A / 127 / 127E / 127F / 127G / 127M:/ 127N / PW127XT-M/ PW127XT-N Maximum during start: 10% of inlet airflow up to a maximum of 33 lb/min (15 kg/min) 8% of inlet airflow 10% of inlet airflow Bleed flow equivalent to that obtained from 0.2" (0.5 cm) diameter orifice at the engine bleed port. NOTE 22. ROTOR DISK INTEGRITY AND ROTOR BLADE CONTAINMENT: (where special requirements apply) Not applicable ----END---- ``` ## ADs (19, in force first) - [AD 2015-20-03](https://openairdocs.org/ad/2015-20-03): Fuel nozzle and the fuel manifold flow adapter · Pratt & Whitney Canada PW120, PW121, PW121A and 6 more. Effective Nov 18, 2015 - [AD 2013-15-08](https://openairdocs.org/ad/2013-15-08): First-stage PT blades · Pratt & Whitney Canada PW118A, PW118B, PW119B and 15 more. Effective Sep 17, 2013 - [AD 2012-26-08](https://openairdocs.org/ad/2012-26-08): Propeller shafts · Pratt & Whitney Canada PW118, PW118A, PW118B and 20 more. Effective Feb 15, 2013 - [AD 2006-19-06](https://openairdocs.org/ad/2006-19-06): Propeller shaft · Pratt & Whitney Canada PW118, PW118A, PW118B and 14 more. Effective Sep 29, 2006 - [AD 2004-20-01](https://openairdocs.org/ad/2004-20-01): Bypass valve cover · Pratt & Whitney Canada PW123, PW123AF, PW123B and 10 more. Effective Nov 5, 2004 - [AD 2003-21-03](https://openairdocs.org/ad/2003-21-03): Low pressure rotor speed (NL) sensor · Pratt & Whitney Canada PW118, PW120, PW120A and 1 more. Effective Nov 20, 2003 - [AD 2003-16-04](https://openairdocs.org/ad/2003-16-04): Fuel heaters · Pratt & Whitney Canada PW118, PW118A, PW118B and 19 more. Effective Sep 10, 2003 - [AD 98-14-02](https://openairdocs.org/ad/98-14-02): Fuel Manifold Transfer Tubes · Pratt & Whitney Canada PW118, PW118A, PW118B and 17 more. Effective Aug 31, 1998 - [AD 97-17-05](https://openairdocs.org/ad/97-17-05): Gas Generator Case Drain Ports · Pratt & Whitney Canada PW118, PW118A, PW118B and 17 more. Effective Sep 9, 1997 - [AD 94-11-11](https://openairdocs.org/ad/94-11-11): Intercompressor Case · Pratt & Whitney Canada PW118A, PW123, PW124B and 2 more. Effective Jul 25, 1994 - [AD 94-03-02](https://openairdocs.org/ad/94-03-02): High Pressure Turbine Disks · Pratt & Whitney Canada PW118, PW118A, PW120 and 5 more. Effective Feb 16, 1994 - [AD 92-17-14](https://openairdocs.org/ad/92-17-14): Fuel Pump · Pratt & Whitney Canada PW123, PW124B, PW125B and 1 more. Effective Nov 18, 1992 - [AD 92-01-08](https://openairdocs.org/ad/92-01-08): High Pressure Rotor · Pratt & Whitney Canada PW118, PW118A, PW120 and 5 more. Effective Jul 27, 1992 - [AD 91-24-03](https://openairdocs.org/ad/91-24-03): Turbomachinery Magnetic Chip Detector · Pratt & Whitney Canada PW123, PW124B, PW125B and 1 more. Effective May 26, 1992 - [AD 91-06-02](https://openairdocs.org/ad/91-06-02): Turbomachinery Magnetic Chip Detector · Pratt & Whitney Canada PW118, PW118A, PW120 and 6 more. Effective Mar 29, 1991 - [AD 91-01-03](https://openairdocs.org/ad/91-01-03): Hydromechanical Fuel Control Units · Pratt & Whitney Canada JT15D-5, PW118, PW118A and 3 more. Effective Jan 7, 1991 - [AD 88-26-51](https://openairdocs.org/ad/88-26-51): High Pressure Turbine Components · Pratt & Whitney Canada PW118, PW118A, PW120 and 2 more. Effective Sep 22, 1989 - [AD 2014-14-02](https://openairdocs.org/ad/2014-14-02) (historical): O-ring seal · Pratt & Whitney Canada PW120, PW121, PW121A and 6 more. Effective Aug 15, 2014 - [AD 2012-11-14](https://openairdocs.org/ad/2012-11-14) (historical): Propeller shafts · Pratt & Whitney Canada PW118, PW118A, PW118B and 20 more. Effective Jul 20, 2012 ## Registered aircraft by registry model (OpenAirDocs) - [Pratt & Whitney Canada PW118](https://openairdocs.org/engine/pratt-whitney-canada-pw118): 37 aircraft (registry code 52116) - [Pratt & Whitney Canada PW119C](https://openairdocs.org/engine/pratt-whitney-canada-pw119c): 20 aircraft (registry code 52163) - [Pratt & Whitney Canada PW127M](https://openairdocs.org/engine/pratt-whitney-canada-pw127m): 18 aircraft (registry code 51498) - [Pratt & Whitney Canada PW120](https://openairdocs.org/engine/pratt-whitney-canada-pw120): 17 aircraft (registry code 52114) - [Pratt & Whitney Canada PW123D](https://openairdocs.org/engine/pratt-whitney-canada-pw123d): 15 aircraft (registry code 52199) - [Pratt & Whitney Canada PW121](https://openairdocs.org/engine/pratt-whitney-canada-pw121): 14 aircraft (registry code 52124) - [Pratt & Whitney Canada PW123](https://openairdocs.org/engine/pratt-whitney-canada-pw123): 14 aircraft (registry code 52129) - [Pratt & Whitney Canada PW123AF](https://openairdocs.org/engine/pratt-whitney-canada-pw123af): 10 aircraft (registry code 52224) - [Pratt & Whitney Canada PW119B](https://openairdocs.org/engine/pratt-whitney-canada-pw119b): 7 aircraft (registry code 52133) - [Pratt & Whitney Canada PW123E](https://openairdocs.org/engine/pratt-whitney-canada-pw123e): 5 aircraft (registry code 52222) - [Pratt & Whitney Canada PW118B](https://openairdocs.org/engine/pratt-whitney-canada-pw118b): 3 aircraft (registry code 52131) - [Pratt & Whitney Canada PW123C](https://openairdocs.org/engine/pratt-whitney-canada-pw123c): 3 aircraft (registry code 52152) - [Pratt & Whitney Canada PW120A](https://openairdocs.org/engine/pratt-whitney-canada-pw120a): 2 aircraft (registry code 52215) - [Pratt & Whitney Canada PW124](https://openairdocs.org/engine/pratt-whitney-canada-pw124-series): 2 aircraft (registry code 52130) - [Pratt & Whitney Canada PW127F](https://openairdocs.org/engine/pratt-whitney-canada-pw127f): 2 aircraft (registry code 52223) - [Pratt & Whitney Canada PW127G](https://openairdocs.org/engine/pratt-whitney-canada-pw127g): 2 aircraft (registry code 52225) - [Pratt & Whitney Canada PW118A](https://openairdocs.org/engine/pratt-whitney-canada-pw118a): 1 aircraft (registry code 52214) - [Pratt & Whitney Canada PW127E](https://openairdocs.org/engine/pratt-whitney-canada-pw127e): 1 aircraft (registry code 52220) - [Pratt & Whitney Canada PW121A](https://openairdocs.org/engine/pratt-whitney-canada-pw121a): 0 aircraft (registry code 52216) - [Pratt & Whitney Canada PW123B](https://openairdocs.org/engine/pratt-whitney-canada-pw123b): 0 aircraft (registry code 52221) - [Pratt & Whitney Canada PW124B](https://openairdocs.org/engine/pratt-whitney-canada-pw124b): 0 aircraft (registry code 52217) - [Pratt & Whitney Canada PW125B](https://openairdocs.org/engine/pratt-whitney-canada-pw125b): 0 aircraft (registry code 52218) - [Pratt & Whitney Canada PW126A](https://openairdocs.org/engine/pratt-whitney-canada-pw126a): 0 aircraft (registry code 52125) - [Pratt & Whitney Canada PW127](https://openairdocs.org/engine/pratt-whitney-canada-pw127): 0 aircraft (registry code 52219) ## STCs approved under this data sheet (13) - [STC SE2805SO](https://openairdocs.org/stc/SE2805SO): Installation of an oil tank safety cap adapter which is intended to prevent loss of oil in the event of loss or damage to the oil filler cap.. Jet Avion Corporation - [STC SE00023EN](https://openairdocs.org/stc/SE00023EN): Installation of Oil Tank Filler Neck Check Valve, Part Number TSA100Sa, Parts List Rev A dated 7/3/1997.. Helicopter Support Inc Services Div - [STC SE01638NY](https://openairdocs.org/stc/SE01638NY): Installation of HP Turbine vanes with improved cooling.. Atlantic Turbines International Inc. - [STC SE00344LA](https://openairdocs.org/stc/SE00344LA): Installation of Western Filter Corp. oil filter element, P/N WF334638, as a replacement for the P&W Canada filter element, P/N 3112895-01, in the lubrication system.. Western Filter Corporation - [STC SE792NE](https://openairdocs.org/stc/SE792NE): Installation of oil tank filler neck check valve P/N TSA-100 SA.. Aviation Components Support - [STC SE00097LA](https://openairdocs.org/stc/SE00097LA): Installation of strainer element, P/N 90220, as a replacement for strainer element, P/N 3106403-01, in the oil pressure transfer tube assembly.. Ejay Filtration, Inc - [STC SE01045AT](https://openairdocs.org/stc/SE01045AT): Installation of engine ignition lead. Unison Industries - [STC SE00074LA](https://openairdocs.org/stc/SE00074LA): Installation of Puroflow filter element, P/N 11-11064, as a replacement for P&W Canada filter element, P/N3029315 (and optional numbers) in the reduction gearbox scavenge oil filtering system.. Puroflow Corporation - [STC SE00075LA](https://openairdocs.org/stc/SE00075LA): Installation of Puroflow filter element, P/N 11-11065, as a replacement for P&W Canada filter element, P/N3112895-01, in the reduction gearbox scavenge oil filtering system.. Puroflow Corporation - [STC SE00076LA](https://openairdocs.org/stc/SE00076LA): Installation of Puroflow filter element, P/N 11-11084, as a replacement for P&W Canada filter element, P/N3035681 (and optional part numbers) in the engine fuel filtering system.. Puroflow Corporation - [STC SE00079LA](https://openairdocs.org/stc/SE00079LA): Installation of Puroflow filter element, P/N 11-11085, as a replacement for P&W Canada filter element, P/N3035728 (and optional part numbers) in the engine fuel filtering system.. Puroflow Corporation - [STC SE00082LA](https://openairdocs.org/stc/SE00082LA): Installation of Puroflow filter element, P/N 11-11102, as a replacement for P&W Canada filter element, P/N3038454, in the engine fuel filtering system.. Puroflow Corporation - [STC SE00083LA](https://openairdocs.org/stc/SE00083LA): Installation of Puroflow filter element, P/N 70-106, as a replacement for P&W Canada filter element, P/N3034190, in the reduction gearbox scavenge oil filtering system.. Puroflow Corporation --- 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.