TCDS A12EU

Page No. 1 2 3 4 5 Rev. No. 3 1 1 2 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A12EU Revision 3 Rinaldo. Piaggio PD 808/526 March 2, 2010 TYPE CERTIFICATE DATA SHEET NO. A12EU This data sheet, which is a part of type certificate No. A12EU, prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder Industr ie Aeronautiche e Meccaniche Rinaldo Piaggio S.P.A. (formerly Piaggio & Co.) Genoa, Italy I. Piaggio-Douglas Model PD 808/526 (Transport Aircraft), Approved November 27, 1968 Engines 2 Bristol Siddeley Viper 526 turbine engines Fuel Aviation Kerosene Specification: American A.S.T.M. D1655/64T Jet A or A-1 British D.Eng. R.D. 2482 or 2494 Aviation Wide-Cut Specification: American A.S.T.M. D1655/64T Jet B British D. Eng. R.D. 2486 Oil ESSO TJ.15 and ESSO Extra 274 ENCO TJ.15 and ENCO Extra 274 Mobil Jet II, Castrol 98, Aero Shell 390 Engine Limits Take-off static thrust, st andard day sea level (100%) 3330 lb Maximum continuous thrust, standard day sea level (98.5%) 3100 lb Maximum permissible engine roto r operating speed 100% 13760 RPM Maximum overspeed (20 second limit) 103% Ground Idling 40 - 41% Maximum permissible turbin e outlet gas temperature: Take-off (5 minute limit) 740 °C Maximum continuous 715 °C Starting (5 second limit) 800 °C Ground idling 645 °C Maximum permissible oil inlet temperature: Continuous operation 125 °C Maximum permissible air bleed extraction of primary engine airflow 7.5% A12EU 2 Airspeed Limits (IAS) V MO (Maximum operating) Sea level 340 kts 19500 feet 352 kts M MO (Maximum operating) 19500 feet and above M = 0.75 (IMN) V A (Maneuvering) 18300 lb gross weight 280 kts 15500 lb gross weight 250 kts 13000 lb gross weight 230 kts V FE (Flap Speed) 20 ° down 220 kts 40 ° down 185 kts V LE (Landing gear extended speed) 220 kts V LO (Landing gear operating speed) 200 kts V MCG (Minimum control speed, ground) sea level ISA - 50 °C 89 kts V MCA (Minimum control speed air) is below the stall speed Tire limit ground speed (Nose landing gear) (Take-off) 157 kts Datum Fuselage station “0”, 38 inches forward of cut for sliding nose. Mean Aerodynamic Chord (MAC) 74.6 inches. Leading edge of MAC is located at fuselage station 216.5 inches. C.G. Range (gear extended) WEIGHT FORWARD AFT (Pounds) % MAC Inches % MAC Inches 18,300 21.0 +232.16 24.5 +234.78 16,000 22.0 +232.91 - - 14,500 - - 27.5 +237.00 13,000 - - 27.5 +237.00 12,500 17.5 +229.55 - - 11,000 17.5 +229.55 - - 10,000 19.4 +231.00 24.8 +235.00 Straight line variation between points given Leveling Means Longitudinally - Fuselage right si de between station 336.50 inches to 351.0 inches. Laterally - Fuselage station 321.4 inches. Maximum Weight Ramp 18,300 lb Take-off (brake release) 18,000 lb Landing 16,000 lb Zero Fuel 13,000 lb Minimum Crew Two Pilot and Co-pilot Maximum Passengers Nine Maximum Baggage Weight lb . Arm Inches (5 passengers version) Forward compartment: 140 128.74 Rear compartment: 100 274.31 Maximum Baggage (9 passengers version) Forward compartment: 140 143.31 3 A12EU Fuel Capacity Usable fuel (See NOTE 1 for unusable fuel) Location Volume U.S. Gals. Arm Inches Right or left tank (wing plus tip ) (each) 485 Wing (right or left) (each) 248 245.78 Tip (right or left) (each) 237 226.56 Oil Capacity Maximum oil system cap acity (See NOTE 1 for unusable oil) Location Volume U.S. Gals. Arm Inches No. 1 1.94 308.14 No. 2 1.94 308.14 Maximum operating altitude 40,000 feet Other operating limitations Aircraft sha ll be operated in compliance with the operating limitations specified on the R.A.I. Approved Airp lane Flight Manual. Control Surface Movements Surface Travel Tolerance Aileron Up 16 ° ± 1° Down 16 ° Aileron tabs (trim on left side only) Left side Up 32 ° ± 2° Down 36 ° Right side Up 20 ° ± 2° Down 20 ° Rudder Left 27 ° ± 1° Right 27 ° Rudder trim tabs Left 25 ° ± 1° Right 25 ° Elevator Up 20 ° ± 1° Down 10 ° Elevator trim tab Up 22 ° ± 2° (Electrical) Down 27 ° Elevator trim tab Up 8 ° ± 2° (Mechanical) Down 12 ° Flaps Down 40 ° ± 2° Speed brakes Down 45 ° ± 2° Spoilers Up 60 ° ± 2° Serial Numbers Eligible A Registro Aeronautico Italiano (R.A.I.) Certificate of Airworthiness for Export, endorsed as noted below under Import Requi rements, must be submitted for each individual aircraft for which app lication for certification is made. Certification Basis FAR 21.29 a nd CAR 4b dated December 1953; Amendments 4b-1 through 4b-11 thereto; the provisions of Special Civil Ai r Regulation SR-422B; the Special Conditions listed in Attachment A to FAA letter to the Registro Aeronautico Italiano (R.A.I.) dated May 11, 1966. Type Certificate (Import) No. A12EU issued November 27, 1968. (See NOTE 3) Date of Application December 7, 1961 Compliance with the following additional requirements has been established: Amendment 4b-12 Sections 4b.1 thru 4b. 191, 4b.334 (e), 4b.413 thru 4b.447 (except 4b.437), 4b.450 thru 4b.454, 4b.603 thru 4b. 612, 4b.622 thru 4b.634, 4b.642, 4b.643, A12EU 4 4b.711, 4b.718, 4b.738 and 4b.740. Amendment 4b.14; FAR 25 - Amendment 25 - 15 FAA exemption No. 769 (Grant exemption from CAR 4b.437). The R.A.I originally type certificated th is aircraft under its type certificate. The FAA validated this product under U.S. Type Certificate Number A12EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the R.A.I. Import Requirements A U.S. Certificate of Airworthiness may be issued on the basis of an Italian Certificate of Airworthiness for Export signed by a represen tative of the Registro Aeronautico Italiano containing the following statement: “The airp lane covered by this certificate has been examined and found to comply with U.S. Ci vil Air Regulations Part 4b issued December 31, 1953, including Amendments 4b-1 thru 4b-11, additional requirements as stated under Certification Basis of Type Certificat e Data Sheet A12EU, and conforms to Type Certificate A12EU.” The FAA can issue a U.S. airworthiness certif icate based on an R.A.I. Export Certificate of Airworthiness (Export C of A) signed by a representative of the R.A.I. on behalf of the European Community. The Export C of A should contain the following statement: ‘The aircraft covered by this certificate has been examined, tested, and found to conform to the type design approved under U.S. Type Certificate No A12EU and to be in a condition for safe operation.’ Required Equipment The basic required e quipment as prescribed in the applicable airworthiness regulations must be installed in the aircraft for certification. A required Equipment List is provided in the R. Piaggio Report No. 9008 dated November 16, 1966, and is availa ble upon request from the manufacturer. A current R.A.I. - Approved Airplane Fli ght Manual for the Model PD 808/526 must be carried on the aircraft at all times. Service Information All Service Bulletins are approved by R.A.I. and carry a statement to that effect. NOTE 1 (a) A current Weight and Balance Report including lis t of equipment included in certificated empty weight, and loading instructions, must be in each aircraft at the time of original certification and at all times thereafter. (b) The airplane must be loaded so that the C.G. is within the specified limits at all times. (c) The weight of system fuel and oil as defined be low and hydraulic fluid must be included in the empty weight of the airplane. System Fuel U.S. Gals . Arm inches Unusable fuel 16 260.00 Undrainable fuel (trapped in tanks & lines) 4 260.00 System Oil U.S. Gals . Arm inches Unusable oil (both engines) 1.8 308.14 Undrainable oil Negligible NOTE 2 The service life limits for aircraft structural part s which are fatigue critical are listed in the Approved Airplane Flight Manual. NOTE 3 Piaggio Model PD 808, Approved November 29, 1966 withdrawn November 27, 1968, since Bristol Siddeley Viper 525 engines are not installed on any PD 808 airplanes. 5 A12EU NOTE 4 SERVICE INFORMATION: Each of the documents listed below that contain a st atement that it is approved by the European Aviation Safety Agency (EASA) - or for approvals made before September 28, 2003 - by the R.A.I., are accepted by the FAA and are considered FAA approved. These approvals pertain to the type design only. • Industrie Aeronautiche e Meccaniche Se rvice Bulletins, except as noted below, • Structural repair manuals, • Vendor manuals referenced in Industrie Aeronautiche e Meccaniche ]service bulletins • Aircraft flight manuals, • Repair Instructions. Design changes that are contained in Service Bulletins and are classified as level 1 major in accordance with the US Bilateral Aviation Safety Agreement Implementation Procedures for Airworthiness must be approved by the FAA. ......END......