TCDS E31NE

* PAGE 1 2 3 4 5 REV. 7 3 4 5 9 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" NOT APPLICABLE NOTE: ALL PAGES HAVE BEEN REFORMATTED. SIGNIFICANT CHANGES ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE SHEET E31NE TCDS NUMBER E31NE REVISION: 9* DATE: March 22, 1995 INTERNATIONAL AERO ENGINES MODELS: V2500-A1 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E31NE) 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: International Aero Engines AG (IAE) Corporate Center II 628 Hebron Avenue Glastonbury, CT 06033-2595 I. MODELS V2500-A1 TYPE Dual rotor, axial flow, high bypass turbofan, single-stage fan, three-stage, low pressure compressor, 10-stage high pressure compressor, annular combustor, two-stage, high- pressure turbine, five-stage, low pressure turbine. RATINGS (NOTE 5) Maximum continuous at sea level, static thrust, lb Takeoff (5 min.) at sea level, static thrust, lb 22,240 24,800 COMPONENTS For information refer to the Installation and Operating Manual (IOM), Installation Handbook; Illustrated Parts Catalogue or Approved Parts List. PRINCIPAL DIMENSIONS (in) Length Normal diameter Maximum radial projection 126.0205 66.4 43.7 TCDS E31NE PAGE 2 I. MODELS (cont.) V2500-A1 WEIGHT (DRY) (Includes all essential accessories, but excludes starter, exhaust nozzle, and power source for the ignition system) 2,404 kg / 5,300 lb CENTER OF GRAVITY (in) Aft of front mount area centerline Below engine centerline Starboard of engine vertical centerline 14.30+1.0 2.20+0.5 0.3+0.5 FUEL (See NOTE 10) OIL (See NOTE 11) CERTIFICATION BASIS FAR 33, effective February 1, 1965, as amended by 33-1 through 33-10 inclusive. Date of Type Certificate Model Date of Application No. E31NE Issued/Revised V2500-A1 April 1, 1985 June 24, 1988 PRODUCTION BASIS Production Certificate No. 114NE TCDS E31NE PAGE 3 NOTES NOTE 1. Maximum permissible engine operating speeds for the engine rotors as follows: Low Pressure rotor (N1), RPM 5,465 (100%) High Pressure rotor (N2), RPM 14,915 (100%) NOTE 2. Maximum permissible temperatures are as follows: Turbine Exhaust Gas Temperature (See NOTE 18) Take off (5 minutes) 650łC/1202łF actual; 635łC/1175łF indicated Maximum Continuous 625łC/1157łF actual; 610łC/1130łF indicated Start Ground 635łC/1175łF Inflight 635łC/1175łF Oil Outlet Temperature Continuous operation 155łC/311łF Transient operation (15 minutes) 165łC/329łF maximum External engine component maximum limiting temperatures are specified in the Installation and Operating Manual, Section 4.3. NOTE 3. Fuel Pressure Oil Pressure Fuel and oil pressure limits At inlet to engine system pump, not less than 5 psig above the true vapor pressure of the fuel and not greater then 70 psig with a vapor/liquid ratio of zero 60 psig minimum. NOTE 4. Maximum Permissible Air Bleed Extraction is as Follows: Airflow Maximum Bleed Limit** Station % of Inlet Core Flow (WA26) 7th Stage Bleed At or Below 91% corrected high rotor speed 7.7% Above 91% corrected high rotor speed Less than 7.7%* 10th Stage Bleed At or below 60% corrected high rotor speed 12% Above 60% corrected high rotor speed Less than 12%* * Permissible air bleeds limits are provided in the Installation and Operating Manual, Section 4.1, Figure 4. ** Simultaneous use of 7th and 10th stage bleed at limiting conditions is allowed only when required by a malfunction and only until the next landing. TCDS E31NE PAGE 4 NOTE 5. The ratings are based on Sea Level Static test stand operation under the following condition: Engine inlet air at 59łF and 29.92 in.Hg. Specified fuel and oil. No fan or compressor air bleed or load on accessory drives. Ideal inlet pressure recovery. A mixed exhaust system having no internal pressure losses and a mixed primary nozzle velocity coefficient equal to 1.0. Takeoff rating is a maximum thrust certified for takeoff operation. The specified takeoff thrust is available at and below ISA +27łF (15łC) ambient temperature. Maximum Continuous rating is the maximum thrust certified for continuous operation. The specified thrust is available at and below ISA +18łF (10łC) ambient temperature. NOTE 6. The following accessory drive provisions are incorporated: Drive Speed Ratio Starter (ccw) .941 N2 Hydraulic Pump (ccw) .267 N2 Integrated Drive Generator System (ccw) .064 N2 Fuel Pump (ccw) .427 N2 ccw - counter clockwise Torque (lb-in) Continuous Static Overload (A) (A) (A) 1300 6500(B) 1950 (C) 1,100 (C) 650 3500 975(B) A - Strength of starter drive shall be adequate for a starter delivering maximum torque of 470 lb. ft. at zero RPM and 1175 lb. ft. maximum impact torque. The engine starter drive shear section is designed to fail at a static torque of 940-1081 lb.ft. B - Maximum allowable for 5-minutes duration recurring at 4 hour intervals. C - Maximum allowable continuous torque values are equivalent to 175 horsepower at an engine speed at or above sea level ground idle. The drive is designed to accommodate the following overload conditions: Horsepower Duration Time Recurring Time 225 5 minutes 1,000 hours 225 5 seconds 1 hour 450 5 seconds 1,000 hours NOTE 7. Power setting, power checks, and control of engine output in all operations is to be based upon International Aero Engines AG engine charts referring to either turbine discharge section gas pressure or low rotor speed. Pressure probes and a low rotor speed sensor are included in the engine assembly for this reason. TCDS E31NE PAGE 5 NOTE 8. For inflight operation during icing conditions, the minimum allowable fan speed is 25.6% (1,400 RPM). NOTE 9. Lightning protection requirements and electromagnetic interference emitted by the electronic engine control system including cables are specified in the V2500 Installation and Operating Manual, Section 4.12. NOTE 10. Fuel and fuel additives conforming to the specifications specified in V2500 Installation and Operation Manual, Section 4.5 may be used separately or mixed in any proportions without adversely affecting the engine operation or power output. NOTE 11. Specific oil brands approved for use are identified in the V2500 Installation and Operating Manual, Section 4.9. NOTE 12. Certain engine parts are life limited. These limits are listed in the FAA-approved International Aero Engines AG V2500 turbofan Engine Manual, Chapter 5, Time Limit Section. NOTE 13. The engines meet the January 1, 1984, smoke and gaseous emission requirements of FAR 34. NOTE 14. The engines meet the January 1, 1975, fuel venting emissions requirements of FAR 34. NOTE 15. The maximum permissible V2500 engine inlet distortion limit is specified in the V2500 Installation and Operating Manual, Section 4.4. NOTE 16. Limits regarding transient rotor shaft overspeed rpm, and transient gas temperature and the number of overtemperature occurrences, are specified in the Maintenance Manual. NOTE 17. Time limited dispatch (TLD) limits for the V2500-A1 FADEC control system are listed in the V2500 Installation and Operating Manual (IOM) (IAE-0043), Section 4.13. The technical data substantiating the IOM TLD limits are contained in IAE V2500 Reports IAE-0184, PWA-6189, and PWA-6243. NOTE 18. Electronic Engine Control (EEC) software version SCN11G and earlier versions have maximum permissible exhaust gas temperatures 635łC (actual and indicated) for takeoff (5 minutes) and 610łC for maximum continuous. To provide adequate margin for consolidated bump rating operation, EEC software version SCN11H to SCN12B/N can provide maximum permissible EGT of 640łC actual (635 łC indicated) for non-bump takeoff, 650łC actual (635łC indicated) for consolidated bump takeoff, and 615łC actual (610łC indicated) for maximum continuous. EEC software version SCN12C provides a maximum permissible EGT of 650oC actual (635oC indicated) for takeoff and 625oC actual (610oC indicated) for maximum continuous with or without consolidated bump usage. The noted engine ratings and limits are controlled by EEC P/N and Data Entry Plug (DEP) P/N, and are implemented by specific Service Bulletin instructions only. The engine data plate also reflects the engine ratings and limits configuration. The indicated vs. actual EGT values are controlled by EEC software. NOTE 19. Supplemental Type Certificate SE636NE approves installation of a fan thrust reverser and exhaust system (P/N 740D8018) on the V2500-A1 series models. The thrust reverser/exhaust system consists of the thrust reverser, common nozzle assembly, tail plug, and pylon installation kit, and consists of parts listed in IAE Thrust Reverser Type Design Bill-of-Material, Serial No. N0009. NOTE 20. Model Description: V2500-A1 Basic Model ----END----