TCDS E25EA

PAGE 1 2 3 4 5 6 7 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" REV. 11 10 10 10 9 10 11 "---" 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 E25EA TCDS NUMBER E25EA REVISION: 11 DATE: November 16, 2022 PRATT & WHITNEY CANADA CORP. MODELS: JT15D-1 JT15D-4 JT15D-5 JT15D-1A JT15D-4B JT15D-5A JT15D-1B JT15D-4C JT15D-5B JT15D-4D JT15D-5C JT15D-5F JT15D-5R Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E25EA) 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, QC Canada J4G 1A1 TYPE CERTIFICATE (TC) RECORD : Pratt & Whitney Canada, Inc. Pratt & Whitney Aircraft of Canada, Ltd.. United Aircraft of Canada Ltd. (Name changes of TC Holder) TYPE JT15D-1 / -1A / -1B: Twin spool with a single stage fan and centrifugal compressor, three stage turbine, annular reverse- flow combustor and full-length annular bypass duct. JT15D-4 / -4B / -4C / -4D / -5 / -5A / -5B / -5C / -5F/-5R: Twin spool with single stage fan, one axial compressor stage and one centrifugal compressor stage, three stage turbine, annular reverse-flow combustor and full length annular bypass duct. THRUST RATING, POUNDS (See NOTE 15) JT15D-1 JT15D-1A JT15D-1B JT15D-4 JT15D-4B JT15D-4C JT15D-4D Maximum continuous at sea level Takeoff (5 min.) at sea level 2,090 2,200 - - - - - - - - 2,375 2,500 - - - - - - - - - - - - JT15D-5 JT15D-5A JT15D-5B JT15D-5C JT15D-5F JT15D-5R Maximum continuous at sea level Takeoff (5 min.) at sea level 2,900 2,965 - - 2,900 - - 2,900 3,190 3,190 2,900 2,900 - - 2,965 ENGINE SPEED LIMITATIONS (rpm) JT15D-1 JT15D-1A JT15D-1B JT15D-4 JT15D-4B JT15D-4C JT15D-4D Max steady state low rotor (N1) Max steady state high rotor (N2) 15,840 31,120 16,540 - - - - - - 16,540 31,450 16,860 31,800 - - - - 16,540 - - JT15D-5 JT15D-5A JT15D-5B JT15D-5C JT15D-5F JT15D-5R Max steady state low rotor (N1) Max steady state high rotor (N2) 16,540 31,450 - - - - - - - - - - - - - - - - - - - - TCDS E25EA Page 2 of 7 INTERTURBINE TEMPERATURE øF/øC øF/øC øF/øC øF/øC øF/øC øF/øC øF/øC MODELS: JT15D-1 JT15D-1A JT15D-1B JT15D-4 JT15D-4B JT15D-4C JT15D-4D Takeoff (5 min.) (See NOTE 15) Maximum continuous Maximum for acceleration Starting Transient (2 sec.) 1292/700 1256/680 1292/700 932/500 1328/720 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 1310/710 1274/690 1310/710 - - 1346/730 1292/700 1256/680 1292/700 932/500 1328/720 1328/720 - - 1328/720 - - 1364/740 MODELS: JT15D-5 JT15D-5A JT15D-5B JT15D-5C JT15D-5F JT15D-5R Takeoff (5 min.) (See NOTE 15) Maximum continuous Maximum for acceleration Starting Transient (2 sec.) 1292/700 1256/680 1292/700 1022/550 1328/720 - - - - - - - - - - - - - - - - - - - - - - 1292/700 - - - - - - - - 1256/680 - - - - - - - - - - - - - - - - OIL INLET TEMPERATURE øF/øC øF/øC øF/øC øF/øC øF/øC øF/øC øF/øC MODELS: JT15D-1 JT15D-1A JT15D-1B JT15D-4 JT15D-4B JT15D-4C JT15D-4D Maximum Minimum Transient maximum (90 sec.) 250/121 -40/-40 280/138 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - MODELS: JT15D-5 JT15D-5A JT15D-5B JT15D-5C JT15D-5F JT15D-5R Maximum Minimum Transient maximum (15 min.) 250/121 -40/-40 275/135 - - - - - - - - - - - - - - - - 265/129 - - - - 275/135 - - - - - - MAXIMUM ACCESSORY TEMP. 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. AIR BLEED, MODELS: JT15D-1 JT15D-1A JT15D-1B JT15D-4 JT15D-4B JT15D-4C JT15D-4D A. High compressor bleed. Maximum external bleed air available is: 10% of high compressor flow 10% of high compressor flow to 22,000 feet, decreasing linearly to 7% at 43,000 feet. No more than 5% may be taken from either of the bleed ports B. Bypass bleed. Maximum external bleed air available is: N/A 2% of the bypass flow throughout the flight envelope C. During starting, bleed shall not exceed that taken by a: 0.3 - inch diameter orifice throat - - D. Bleed air contamination meets: Para 3.18 of MIL-E-5007c - - AIR BLEED, MODELS: JT15D-5 JT15D-5A JT15D-5B JT15D-5F JT15D-5R JT15D-5C A. High compressor bleed. Maximum external bleed air available is: 10% of high compressor flow to 22,000 feet, decreasing linearly to 5% at 45,000 feet. No more than 5% may be taken from either of the bleed ports. - - B. Bypass bleed. Maximum external bleed air available is: N/A --- --- --- 2% of the bypass flow throughout the flight envelope C. During starting, bleed shall not exceed that taken by a: 0.3 - inch diameter orifice throat - - D. Bleed air contamination meets: Para 3.18 of MIL-E-5007C - - FUEL / ALL MODELS 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. Fuel Pressure Refer to appropriate Installation Manual. Fuel temperature Maximum fuel pump inlet temperature for starting and operating is 135øF(57øC); minimum inlet temperature is - 65øF(-54øC), subject to a viscosity limit of 12 centistokes. (for the JT15D-4, 7 centistokes for cold-soaked starting.).See Note 14 for JT15D-5R operation at temperatures above -40øC TCDS E25EA Page 3 of 7 Fuel type (Also see NOTE 4) JP-1, JP-4, and JP-5 type fuels conforming to PWA Specification No. CPW 204 and later revisions, plus Icing Inhibitor - Fuel System - to CGSB Specification 3-GP-526a in the absence of an approved fuel heater. Wide cut fuels and Avgas are not permitted for the JT15D-5R (See SB7144). FUEL CONTROL ECU = ELECTRICAL CONTROL UNIT HMU = HYDROMECHANICAL UNIT FUEL FLOW DIVIDER FUEL PUMP JT15D-1 JT15D-1A JT15D-1B JT15D-4 JT15D-4B JT15D-4C JT15D-4D JT15D-5 JT15D-5A JT15D-5B JT15D-5C JT15D-5F JT15D-5R Aviation Electric DPL-1 & DPL-2 - - - - Aviation Electric DPL-2 - - - - - - ECU: Hamilton Standard EEC 118-31 HMU: Hamilton Standard JFC 118-31 Bendix Avelex DPL-2 ECU: Hamilton Standard EEC 118-31 HMU: Hamilton Standard JFC 118-31 ECU: Hamilton Standard EEC 118-31 HMU: Hamilton Standard JFC 118-31 ECU: Hamilton Standard 780933-3 HMU: Hamilton Standard 790155-1 ECU: Hamilton Standard EEC 118-31 HMU: Hamilton Standard JFC 118-31 Lucas SCH 1210/13, FD206 - - - - Lucas FD206 - - - - - - Goodrich 25950-2 Lucas 26060 or 26280 Lucas ES480 Lucas ES480 Lucas 25950 Goodrich 25950-2 Sundstrand 025493/Vickers PF40094-2B - - - - Sundstrand 025493/TRW 398600 - - - - - - TRW 706600 Argo Tech 710500 Argo Tech 717100 TRW 706600 TRW 706600 TRW 710501-02 Argo Tech 845400 OIL MODELS: JT15D: -1 -1A -1B -4 -4B -4C -4D -5 -5A -5B -5C -5F -5R OIL PRESSURE psig psig psig psig psig psig psig psig psig psig psig psig psig Min. at 20000 rpm N2 & above Min. below 20000 rpm N2 Min. for aerobatic maneuvers Max. Max. transient (90 seconds) 65 35 N/A 95 N/A - - - - - - - - - - - - - - - - - - - - 70 35 N/A 95 N/A - - - - - - - - - - - - - - 25 - - - - - - - - N/A - - - - 60 40 N/A 83 95 - - - - N/A - - - - - - - - - - - - - - - - 35 40 90 100 - - 40 N/A 83 95 - - - - - - - - - - OIL TYPE (Also see NOTE 8) Synthetic type conforming with the current PWA 521 (Type II) Specifications (See Department of Transport Canada approved Installation Manual). OIL TANK CAPACITY Total capacity Imperial gallons U.S. gallons Usable capacity Imperial gallons U.S. gallons 1.78 2.14 1.04 1.25 - - - - - - - - - - - - - - - - 1.73 2.08 1.01 1.21 - - - - - - - - 1.31 1.58 0.59 0.71 1.73 2.08 1.01 1.21 1.69 2.03 1.00 1.20 - - - - - - - - - - - - - - - - 1.98 2.39 0.42 0.50 1.69 2.03 1.00 1.20 1.81 2.17 - - - - TCDS E25EA Page 4 of 7 ACCESSORY DRIVES The following apply to the accessory drives, which are provided by the engine and included in the basic engine weight: SPEED RATIO TO TURBINE MAXIMUM TORQUE (in. - lb.) MAXIMUM OVERHANG DRIVE ROTATION SHAFT CONTINUOUS STATIC (in.-lb.) DRIVEN BY HIGH ROTOR High rotor tachometer Hydraulic pump Starter generator DRIVEN BY LOW ROTOR Low rotor tachometer CW CW CW CCW .1282:1 .1282:1 .3640:1 .2642:1 7 225 210 7 50 1600 1600 50 10 125 180 0 *CW - Clockwise; CCW - Counterclockwise Total accessory power extraction is limited to 22.5 hp at 52% N2 and increases linearly to 30 hp at maximum permissible N2 at altitudes up to and including 20,000 ft. Refer to the applicable Installation Manual for restrictions over altitudes of 20,000 ft. Also see NOTE 3. IGNITION MODELS JT15D -1 -1A -1B -4 -4B -4C -4D -5 -5R -5A -5C -5B -5F Exciter Unison Lucas Igniter plug Unison AC Champion 9049770-3 NB01201 9044810-4 YB-15 FHE 246-4 9060660-2 --- 9044810-4 --- FHE 246-4 9049770-3 - - --- - - 9060660-1 SL20009-02 9044810-4 PRINCIPAL DIMENSIONS Refer to Installation Drawing in approved Installation Manual. C. G. LOCATION Refer to Installation Drawing in approved Installation Manual. CERTIFICATION BASIS JT15D-1, except serial numbers 076364 through 076672 JT15D-1A, all serial numbers JT15D-1B, all serial numbers FAR 21.29, FAR 33 dated February 1, 1965, Amendments 33-1, 33-2, 33-3, inclusive. JT15D-4, -4B, -4C, and -4D, except serial numbers 070011 through 070059 less 070038 FAR 21.29, FAR 33 dated February 1, 1965, Amendments 33-1 through 33-4, inclusive, and FAR 33.68 of Amendment 33.6. (Excepted serial numbers were certified under FAR 21.21 See NOTE 10.) Models JT15D-5, -5A, -5B, -5C, -5F and - 5R FAR 21.29, FAR 33, Amendments 1 through 9 inclusive, effective October 14, 1980, with the exception of 33.77, 33.88, and 33.92 which are to FAR Part 33 Amendments 1 through 4 inclusive, effective April 22, 1971; and Advisory Circulars AC 33-1B and 33.3. NOTE: The JT15D-5A incorporates a dual idle solenoid P/N 3242737. The use of low idle speed is approved for ground operation only. When operating at the low idle speed, the engine is not approved for operation in icing conditions as defined by FAR Part 33, paragraph 33.68(b). TCDS E25EA Page 5 of 7 TYPE CERTIFICATE NUMBER E25EA TYPE CERTIFICATE NUMBER E25EA MODEL APPLIED FOR ISSUED/ REVISED DELETED MODEL APPLIED FOR ISSUED/ REVISED DELETED JT15D-1 JT15D-4 JT15D-1A JT15D-1B JT15D-4B JT15D-4D JT15D-5 JT15D-5A JT15D-5B JT15D-4C JT15D-5C JT15D-5F 06/02/69 11/23/73 09/07/76 07/16/82 12/15/83 12/15/83 04/24/84 03/08/88 11/06/90 01/28/91 02/05/92 03/01/93 05/13/71 01/28/74 10/05/76 09/17/82 12/22/83 12/22/83 06/13/84 12/01/88 11/15/90 08/21/92 08/21/92 10/05/93 JT15D-5R 02/09/06 09/07/06 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 and containing the following language: (1) This engine conforms to its Type Certificate Number E25EA 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." NOTES NOTE 1. The engine ratings are based on static sea level conditions: Compressor inlet air (dry) 59øF (JT15D-4D is rated at 69øF, JT15D-5/-5A/-5B/-5F and -5R are rated at 80øF, at takeoff and 59øF 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. NOTE 2. Emergency operation on gasoline (MIL-G-5572, all grades) is limited to a total of 50 hours in any engine overhaul period. NOTE 3. 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 up to an altitude of 9,000 ft for all engine models except the -5, -5B, -5F and –5R which extend to 10,000 ft. Above 9,000 ft allowable emergency horsepower extraction decreases linearly to 30 hp at an altitude of 20,000 ft and then reverts to normal horsepower extraction limits for all engine models except the -5, -5B, -5F and -5R. For these engine models the emergency horsepower extraction decreases linearly from 40 hp at 10,000 ft to 29 hp at an altitude of 45,000 ft. NOTE 4. For alternate fuels, see Department of Transport, Canada, approved Installation Manual. NOTE 5. This NOTE deleted June 13, 1977. TCDS E25EA Page 6 of 7 NOTE 6. These engines meet FAA requirements for adequate turbine disk integrity and rotor blade containment and do not require external armoring. NOTE 7. Certain engine parts are life limited. For JT15D-1, -1A, -1B, JT15D-4, -4B, -4D and JT15D-5, -5A, -5F, -5R engines, these life limits are listed in P&WC Engine Service Bulletin Number 7002. For JT15D-4C and JT15D-5C life limits are listed in PW&C Engine Service Bulletin Number 7302. For JT15D-5B life limits are listed in P&WC Engine Service Bulletin Number 7402. Permissible overhaul and inspection intervals are listed in P&WC Engine Service Bulletin Number 7003 (Number 7403 for JT15D-5B engines). NOTE 8. P&WC Engine Service Bulletin Number 7001 lists approved oil brands (7401 for JT15D-5B and - 5F). NOTE 9. The JT15D models incorporate the following characteristics: JT15D-1 Basic model. JT15D-1A Similar to JT15D-1 except for increased low rotor speed limit and improved altitude performance. JT15D-1B Identical to JT15D-1A with higher recommended cruise rating and decreased Time Before Overhaul (TBO). JT15D-4 Similar to JT15D-1 except for additional single stage axial compressor and increased ratings. JT15D-4B Similar to JT15D-4 except for increased rotor speed and gas path temperature limitations. JT15D-4C Similar to JT15D-4 except approved for aerobatic maneuvers. JT15D-4D Similar to JT15D-4 except for increased rotor speed and gas path temperature limitations. JT15D-5 Similar to JT15D-4 except for increased thrust ratings and electronic fuel control. JT15D-5A Similar to JT15D-5 except for hydromechanical fuel control unit and the ignition system (2 separate exciters replaces the single input/dual output JT15D-5 unit) and the dual idle solenoid. JT15D-5B Similar to JT15D-5 except that life limited rotating components have new part numbers to satisfy the requirements of the specific aircraft application. JT15D-5C Similar to JT15D-5 except thrust ratings are increased and approved for aerobatic maneuvers. JT15D-5F Similar to JT15D-5 except for installation specific modifications. JT15D-5R Similar to the JT15D-5 except for the addition of a fuel heater and filter with appropriate externals and accessory changes. The fuel filter is transferred to the engine (previously A/C mounted) downstream of the fuel heater. TCDS E25EA Page 7 of 7 NOTE 10. This Type Certificate Data Sheet reflects the certification basis and approval for those serial- numbered JT15D series engines listed under "Certification Basis." Two Type Certificates have been issued for administrative purposes: E25EA under FAR 21.29, for engines produced in Canada, and E1NE under FAR 21.21, for engines produced in the United States. The type design for each model engine, regardless of where produced, is identical. The information on this Type Certificate Data Sheet applies to all Pratt & Whitney Canada Model JT15D series engines, including: (a) Those serial-numbered engines listed on and certificated under FAA Type Certificate E1NE, originally issued to Pratt & Whitney Aircraft Division of United Technologies Corporation, East Hartford, Connecticut, U.S.A., and reissued to Pratt & Whitney Canada Ltd., (formerly United Aircraft of Canada, Ltd.) Longueuil, Quebec, Canada. (b) Those serial numbered engines listed above, certificated under this Type Certificate E25EA, issued to Pratt & Whitney Aircraft of Canada, Ltd.. (formerly United Aircraft of Canada Ltd.), Longueuil, Quebec, Canada. NOTE 11. This NOTE deleted. NOTE 12. NOTE 13 NOTE 14 NOTE 15 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. Certain JT15D engines carry an additional designation in the form of a build specification number shown on the Supplementary data plate. Designation and users are listed in P&WC Service Bulletin No. 7151 JT15D-5R may be used at temperatures above -40°C (-40°F) without the use of fuel system icing inhibitor. The take-off 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 events during take-off are uncommon) and no limits or special inspections have been imposed. ----END----