TCDS E22NE

Page No. 1 2 3 Rev No. 2 1 2 Reformatted 8/94. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E22NE Revision - 2 ALFA ROMEO AR318-02 March 26, 2007 TYPE CERTIFICATE DATA SHEET NO. E22NE Engines of models described herein conforming with this data sheet (which is part of Type Certificate No. E22NE) 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 Civil Air Regulations provided they are installed, operated and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. Type Certificate Holder: Alfa Romeo Avio S.p.A. Pomigliano d'Arco (Napoli) Italia Model: AR318-02 Type: The AR318-02 is a single-shaft turboprop engine comprising a single stage centrifugal compressor, a reverse flow annular combustion chamber, and a two stage axial turbine. An integral main reduction and accessory gearbox is driven by a forward extension of the compressor shaft and has provisions for a starter-generator unit, fuel pump and control system, propeller governor, oil pump and aircraft accessories. One aircraft bleed air port is provided. Ratings: (see Note 1) SHP (KW) Maximum Continuous, sea level static 563 (420) Takeoff (5 minutes), sea level static 607 (453) Limitations: (see Note 2) Gas Generating operating speed RPM Takeoff (5 minutes) rating (maximum) 38,095 (100%) Maximum continuous rating (maximum) 37,523 (98.5%) Flight idle (minimum) 36,190 (95%) Temperature Limitations: (see Note 3) Max. permissible interstage turbine temp. ITT Takeoff (5 minutes) rating 1313°F (712°C) Maximum continuous rating 1284°F (696°C) Maximum transient starts 1382°F (750°C) Fuel Temperature: Measured at engine pump inlet Minimum at start - 31°F (- 35°C) Maximum 104°F (40°C) Oil Temperature: Measured at supply oil pump inlet Minimum at start - 4°F (- 20°C) Maximum 131°F (55°C) Output Shaft Torque Limitations: Takeoff (5 minutes) 1589 (lb.-ft.) Maximum continuous 1496 (lb.-ft.) Fuel and Oil Pressure Limitations: Fuel (measured at engine FCU pump inlet) Minimum 7 psig Maximum 50 psig The engine will operate satisfactorily with fuel pressure at the fuel control inlet 5 psi above the vapor pressure of the fuel inlet temperature. Oil (measured at oil filter outlet) E22NE 2 Minimum 60 psig Maximum 70 psig Ambient Temperature Limitation: Permissible ambient temperature range for engine start: Sea Level - 4°F to 104°F (- 20°C to 40°C) 10,000 ft. - 4°F to 86°F (- 20°C to 30°C) NOTE: Additional data on engine start are specified in Alfa Romeo Avio AR318-02 Operating and Installation Instructions Manual. Fuel Control System: (a) Fuel control unit (FCU), Lucas Ltd. type PGC 302 (b) Speed and temperature amplif ier (ECU), Lucas Ltd. type STA-550 Accessory Provisions: Drive Type Rotation *Speed Maximum Torque Maximum Overhang Moment (N.m) (lb.-in.) (N.m) (lb.-in.) Starter/Generator Lear Si egler CW 0.256 9.10 80.52 13.78 122 Fuel Pump Lucas PGC 302 CW 0.162 1.96 17.36 6.21 55 Propeller Governor Woodward 82010-080 CW 0.102 1.63 14.44 1.29 11.45 Oil Pump CW 0.262 1.64 14.52 1.80 15.9 *Speed = ratio to engine Torque Measurement System: (a) Torque signal conditioning unit (S CU), Simmonds Precision, type 473265-001. (b) Torque and speed sensor, Simmonds Precision, type 473216. Propeller Governor: Woodward, type 8210-080 Interstage Temperature Sensor: Smiths Industries, type 3101-RTH-1 Low Oil Pressure Switch: Smiths Industries, type 4502/KPS/6/35 Ignition System: Three torch ignitors, Lucas, type 08107 Two ignitor plugs, Auburn, type YB63-1 Ignition box, Simmons Precision, type 49930 Starter Generator: Lear Siegler, type 23046-028 Fuel: (See NOTE 4) Type: JP-1 (Aviation Kerosene), JP-4 Oil: (See NOTE 5) Type (synthetic, confor ming to MIL-L-23699C): Shell ASTO 500 Principal Dimensions: Length 41.3 in. (1049 mm) Width 21.57 in. (548 mm) Center of Gravity Locations: Complete engine with accessories except spinner and propeller. Forward of engine gearbox/front mount pad: 7.32 in. (186 mm) On the left side of propeller shaft cen ter line, rear view: 0.27 in. (6.8 mm) Weight: Basic engine weight: 356 lbs. (161.5 kg.) Dry (includes FCU, oil pump, le vers, oil/fuel pipes; excludes propeller, spinner, propeller governor, starter generator, unfeathering pump): 388 lbs. (176 kg.) Propeller, spinner, propeller governor, starter generator, unfeathering pump: 150 lbs. (68 kg.) Certification Basis: Federal Aviation Regulations (FAR's) 21.29 and 33 through Amendment 9, inclusive. Pursuant to FAR 21.29 (a) (1) (ii) the type certificate was issued in validation of Registro Aeronautico Italiano (RAI) certification to RAI requirements, Part 233 (Amendment 9). Date of type certification application: April 21, 1982. E22NE 3 The aviation authority for Italy, Ente Nazioonale per l’Aviazione Civile (ENAC) (formerly Registro Aeronautico Italiano), originally type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E22NE. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Italy. Import Requirements: To be considered eligible for installation on U.S. re gistered aircraft, each new engine to be exported to the United States with ENAC or EASA airworthiness approval shall have a Joint Aviation Authorities (JAA) or EASA Form 1, Authorized Release Certificate. The JAA or EASA Form 1 should state that the engine conforms to the type design approved under the U.S. Type Certificate E22NE is in a condition for safe operation and has undergone a final operational check. NOTE 1. Engine ratings are based on calibrated te st stand performance under the following conditions: - Nominal output shaft speed of 2,006 rpm. - Static sea level standard conditions of 59°F (15°C) and 29.92 in. Hg (1 atm). - Air intake: air intake box and mounting shroud, P/ N 180.30.72.100 E02, intake flare, P/N L22091 (DLF 10311). - Exhaust configuration, P/N LF 133203. - No external air bleed or accessory drive power for aircraft accessories. - Additional performance parameters are contained in Alfa Romeo Avio AR318-02 Operating and Installation Instructions Manual. NOTE 2. 100% output shaft speed equals 2, 006 rpm, corresponding to 38,095 turbine rpm. NOTE 3. The interstage inlet gas temperatur e (ITT) is measured by eight (8) thermocouples mounted in a radial plane at the second stage turbine nozzle. NOTE 4. Approved fuels and additives are listed in Alfa Ro meo Avio AR318-02 Operating and Installation Instructions Manual. NOTE 5. Any derogation from oil type specified herein must be declared in approved Alfa Romeo Service Instructions. NOTE 6. The installation of engine must be su ch that ingestion of birds is prevented. NOTE 7. Life limited parts and accountability methods ar e identified in Alfa Romeo Avio AR318-02 Continued Airworthiness Instructions, RAI approved. The time of first overhaul is equal to 750 hours. NOTE 8. AR318-02 manual approved under RA I requirements as equivalent to FAR 33.4 and 33.5 (Amendment 9) requirements are as follows: - Installation Instructions AR318- 02 Installation Instruction Manual - Operation Instructions AR318- 02 Operating Instructions Manual - Maintenance AR318-02 Maintenance Manual - Overhaul AR318-02 Overhaul Manual - Performance AR318-02 Technical specification document NOTE 9. Overhaul of engine must comp ly with the AR318-02 Overhaul Manual. NOTE 10. The air inlet pressure distortion limits are defined in AR318-02 Operating and Installation Manual. NOTE 11. Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or, for approvals made before September 28, 2003 by Ente Nazionale per l’Aviazione Civile (ENAC) or Registro Aeronautico Italiano (RAI). Any such documents including those approved under a delegated authority, are accepted by the FAA and are considered FAA approved. • Service bulletins, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. These approvals pertain to the type design only. ...END...