TCDS E00073EN

TCDS E00073EN PAGE 1 2 3 4 5 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "- - -" NOT APPLICABLE NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. REV. 2 2 2 2 2 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00073EN TCDS NUMBER E00073EN REVISION: 2 DATE: January 16 , 2007 PRATT & WHITNEY CANADA, CORP. MODELS: PW615F-A Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00073EN) 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. (Formerly Pratt & Whitney Canada, Inc.) 1000 Marie-Victorin Longueuil, Quebec Canada J4G 1A1 MODELS I. TYPE PW615F-A Twin spool controlled by Full Authorit y Digital Electronic Control (FADEC), a single stage fan driven by a single stage Low pressure Turbine, a high pressure compressor consisting of one mixed flow compressor stage and one centrifugal compressor stage, one stage high pressure turbine, annular reverse-flow fully effusion cooled combustor with internally mounted fuel manifold and a integrated mono case and a Air Cooled Oil Cooler. THRUST RATING, POUNDS (See NOTE 1) Maximum continuous at sea level Takeoff (5 min.) at sea level (See Note 2) 1460 1460 ENGINE SPEED LIMITATIONS, RPM Max steady state low rotor (N1) Max steady state high rotor (N2) Transient (20 sec.) low rotor (N1) Transient (20 sec.) high rotor (N2) 21,830 (100%) 44,040 (100%) 22048 (101%) 44921 (102%) INTERTURBINE TEMPERATURE (ºF/ºC) Takeoff (5 min.) Maximum continuous Starting ( 5 sec.) Transient (20 sec.) (Also see Installation Manual/NOTE 7) 1526/830 1526/830 1584/862 1584/862 OIL INLET TEMPERATURE (ºF/ºC) Maximum Minimum Transient maximum (90 sec) (Also see Installation Manual/NOTE 7) 275/135 -40/-40 286/141 TCDS E00073EN PAGE 2 MAXIMUM ACCESSORY TEMP. The engine compartment s hall be ventilated as necessary to keep the air temperature surrounding accessory components from exceeding the limits defined in the Installation Manual. AIR BLEED, A Maximum external bleed air available is: 17 pounds per minute (ppm) at sea level, decreasing linearly to 13.4 ppm at 43,000 ft. B. During starting: Bleed air not permitted C. Bleed air contamination meets: Para 3.1.2.11.3 of MIL-E-5007E FUEL Fuel Bleed A motive flow output is provided from the Fuel Metering Unit (FMU) motive flow port. Refer to Installation Manual. Fuel Pressure Refer to applicable Installation Manual/ NOTE 7. Fuel temperature Maximum fuel pump inlet temperature for starting and operating is 135 O F(57 O C) for typical wide cut fuels and 190 O F(88 O C) for kerosene type fuels. at sea level; minimum inlet temperature is -31 O F(-35 O C), Refer to Installation Manual for additional information. Fuel type Fuels and additives conforming to the specifications listed in applicable P&WC Maintenance Manual are approved for use. OIL PRESSURE (psig) Min. at ground idle & flight idle Maximum, Steady State Maximum, Transient See also Installation Manual 20 170 250 OIL TYPE Oils conforming to the Specificat ions listed in the applicable P&WC Maintenance Manual are approved for use. OIL TANK CAPACITY Total capacity Liters Imperial gallons U.S. gallons Usable capacity Liters Imperial gallons U.S. gallons See also Installation Manual 4.85 1.067 1.281 0.74 0.163 0.195 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 Hydraulic pump Starter generator CW* CW* 0.0952:1 0.2705:1 40 200 1600 1600 20 210 TCDS E00073EN PAGE 3 *CW - Clockwise facing accessory pad. Total accessory power limit is 9.67 hp. at 48.6% N2, increasing linearly to 17.3 hp. at 100% N2. The starter/generator pad for the PW615F-A engine model may be overloaded in an emergency to a torque of 300 in.-lb. for periods up to 5 minutes, subject to total accessory power not exceeding 20.5 hp at 48.6% N2 increasing linearly to 33 hp at Max N2. This shall be considered as recurring at every 100 hours interval. Refer to Installation Manual. IGNITION MODELS PW615F-A Exciter Igniter plug Refer to Assembly Parts List Refer to Assembly Parts List (see Note 7) PRINCIPAL DIMENSIONS Refer to applicable Installati on Drawing referenced in approved Installation Manual. C.G. LOCATION Refer to Insta llation Drawing referenced in applicable approved Installation Manual. MAXIMUM ENGINE DRY WEIGHT Includes basic bill of material components and sensors required for engine operation and monitoring. MODEL PW615F-A 308.7lb. CERTIFICATION BASIS: Models PW615F-A FAR 21.29, FAR 33, Amendments 1 through 20 inclusive effective December 13, 2000 and FAR 34, Amendment 3, effective February 3, 1999. MODEL TYPE CERTIFICATE NUMBER E00073EN APPLIED FOR ISSUED/ REVISED DELETED PW615F-A 5/7/2003 7/21/2006 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 ce rtifying statement, endorsed by the exporting cognizant civil airworthiness aut hority which contains the following language: (1) This engine conforms to its Type Certificate Number 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 pr ovides for the airworthiness acceptance of aircraft engines manufactured outsi de of the U.S. and for which a U.S. type certificate has been issued. Additi onal guidance is contained in FAA Advisory Circular 21-23, "Airworthiness Certific ation of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States." TCDS E00073EN PAGE 4 NOTES NOTE 1. The engine ratings for PW615F-A engine m odel are based on dry sea level static ICAO standard atmospheric conditions. No accessory loads or air bleed. 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. Take-off ratings that are 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. NOTE 3. Minimum permissible flight idle N2 for PW615F-A is: 25,000 RPM (56.8%) NOTE 4. Instructions for Continued Airworthiness are listed in: Maintenance Manuals - P/N 3059712 Line Maintenance Manual – P/N 3072691 Overhaul Manual P/N 3059713 NOTE 5. Certain engine parts are lif e limited. Life limits are listed in Airworthiness Limitation Manuals: P/N 3072698 NOTE 6. Removed NOTE 7. Approved Publications: Installation Manual ER5829 FADEC Interface Control Document ER6004-02 Airworthiness Limitation Manual P/N 3072698 Assembly Parts List for production engines 35C0510 Revision K and subsequent revision NOTE 8. Refer to Installation Manual, ER5829 for accessory drives specifications; principle dimensions; weights, inertias and centre pf gravity locations; and additional information on provisions and connections to airframe provided vibration, Oil pressure and temperature and fuel flow sensor NOTE 9. 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 acceptable by the FAA and are considered FAA-approved unless otherwise noted. These approves pertain to the type design only. NOTE 10. The engine is approved for multiple engine installations only. NOTE 11. The installation require an airframe mounted Fuel Shut Off Valve NOTE 12. The engine is not approved for use with a thrust reverser. NOTE 13. The software contained in the Elec tronic Engine Control has been designed, developed, tested and documented in accordance with the provision of the critical Category, Level A of RTCA/DO178B. Each Electronic Engine Control channel also includes a simple PLD that meets Level A of RTCA/DO254 NOTE 14. The Electronic Engine Control Unit has not been fire tested and therefore must not be installed in a designated fire zone. NOTE 15. The PW615F-A engine is approved with Ti me Limited Dispatch (TLD) limitations. The dispatch criteria are contained in the Airworthiness Limitation Manual P/N 3072968. ----END----