TCDS E45NE

PAGE 1 2 3 4 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" REV. "---" NOT APPLICABLE U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E45NE TCDS NUMBER E45NE REVISION: Original* DATE: DECEMBER 16, 1993 PRATT & WHITNEY CANADA, INC MODELS: JT15D-5D Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E45NE) 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 MODELS I. JT15D-5D TYPE Twin spool with single stage integrally bladed 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 1) Maximum continuous at sea level Takeoff (5 min.) at sea level 3,045 3,045 ENGINE SPEED LIMITATIONS, RPM (See NOTE 4 and also refer to Installation Manual for transients) Max steady state low rotor (N1) Max steady state high rotor (N2) 16,860 31,777 INTERTURBINE TEMPERATURE łF/łC MODELS: JT15D-5D Takeoff (5 min.) Maximum continuous Starting Transient (2 sec.) 1328/720 1292/700 1022/550 1364/740 (Also see Installation Manual) OIL INLET TEMPERATURE łF/łC MODELS: JT15D-5D Maximum Minimum Transient maximum (15 min.) 250/121 -40/-40 275/135 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. TCDS E45NE PAGE 2 AIR BLEED, MODELS: JT15D-5D 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. During starting, bleed shall not exceed that taken by a: 0.3 - inch diameter orifice throat - - C. 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 Installation Manual. Fuel temperature Maximum fuel pump inlet temperature for starting and operating is 135 łF(57łC); minimum inlet temperature is -65łF(-54łC), subject to a viscosity limit of 12 centistokes. Fuel type (Also see NOTE 2) Fuels conforming with PWC, Service Bulletin 7144, plus Icing Inhibitor (Fuel System to C.G.S.B. Specification 3-GP-526a or MIL-I-27686) in the absence of an approved fuel heater. FUEL COMPONENTS FUEL CONTROL FUEL FLOW DIVIDER FUEL PUMP JT15D-5D Bendix Avelex DP-L2 PWC P/N 3118402-01 Lucas 26280 PWC P/N 3118375-01 Argo Tech 717100 PWC P/N 3037078 OIL MODELS: JT15D: -5D OIL PRESSURE psig Min. at 20000 rpm N2 & above Min. below 20000 rpm N2 Max. Max. transient (90 seconds) 60 40 90 100 OIL TYPE (Also see NOTE 7) 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 1.74 2.09 0.97 1.17 TCDS E45NE PAGE 3 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 limit is 22.5 hp. at 52% N2, increasing linearly to 30 hp. at 97% N2. Refer to Installation Manual for restrictions above 20,000 ft. altitude. Also see NOTE 3. IGNITION MODELS JT15D -5D Exciter Lucas Igniter plug Unison PWC P/N 3118172-01 PWC P/N 3117464-01 PRINCIPAL DIMENSIONS Refer to Installation Drawing in approved Installation Manual. C. G. LOCATION Refer to Installation Drawing in approved Installation Manual. CERTIFICATION BASIS Models JT15D-5D FAR 21.29, FAR 33, Amendments 1 through 14 inclusive, effective September 10, 1990, and FAR 34 effective September 10, 1990. TYPE CERTIFICATE NUMBER E45NE MODEL APPLIED FOR ISSUED/ REVISED DELETED JT15D-5D 12/10/93 12/16/93 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 E45NE 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." TCDS E45NE PAGE 4 NOTES NOTE 1. The engine ratings are based on static sea level conditions: Compressor inlet air (dry) 80łF, at takeoff and 59łF 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 emergency to a torque of 340 in.-lb. for periods up to 5 minutes, subject to total accessory power not exceeding 40 hp. NOTE 4. Minimum permissible flight idle N2 is 17035 RPM (52%). NOTE 5. Certain engine parts are life limited. For JT15D-5D engines, these life limits are listed in P&WC Engine Service Bulletin Number 7002. NOTE 6. Permissible overhaul and inspection intervals are listed in P&WC Engine Service Bulletin Number 7003. NOTE 7. P&WC Engine Service Bulletin Number 7001 lists approved oil brands. NOTE 8. Prior to issue of the DOT-approved Maintenance Manual, JT15D-5D engines must be maintained in accordance with temporary instructions issued by Pratt & Whitney personnel. Overhauls are not permitted until issuance of the DOT-approved Overhaul Manual. Engines may be returned to Pratt & Whitney Canada for re-manufacture to new production standard. NOTE 9. 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. ----END----