TCDS A61EU

Page No. 1 2 3 4 5 6 7 Rev. No. 4 - 1 1 3 4 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A61EU Revision 4 Vulcan Air S.p.A. SF600 SF600A July 7, 2021 TYPE CERTIFICATE DATA SHEET No. A61EU This data sheet which is part of Provisional Type Certificate No. A61EU prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder. Vulcan Air S.p.A. Via Giovanni Pascoli, 7 80026 Casoria-Napoli Italy I. Model SF600 (Normal Category), approved October 4, 1990. Engine. 2 Detroit Diesel Allison 250-B17C turboprops Fuel. Commercial Kerosene Jet A-1 conforming to ASTM D1655 specification. When ambient temperature is lower than +5ºC (105.8ºF) the fuel must contain anti-icing additive conforming to MIL-I-27686E in amount of not less than 0.060 and no more than 0.15 by volume. Oil. According to Airplane Flight Manual. Engine Ratings. Take off and Max continuous 420 SHP Engine Limits. Percent Torque Meter Pressure Torque Takeoff and Max continuous 100 107 Propeller Speed (N2) Percent RPM Take off, O.E.I. climb and Max continuous 100 2030 Transient (15 seconds) 110 2233 Turbine Outlet Temperature Takeoff and Max Continuous 810ºC Transient (6 seconds) 843ºC Starting (10 seconds) 810-927ºC 2 A61EU Propeller and Propeller Model Hartzell HC-B3T Limits. Hub HC-B3TF-7A Blade T10173-11R Diameter 90 3/8 inches (no reduction permitted) Blade angle at 30 inch station low pitch + 9.5º ± 0.5º feathering 80º (only for reference) reverse - 11 ± 0.5º Governor Woodward model 8210-018 Overspeed governor Woodward model 8210-011 Spinner Hartzell P/N 835-39 Airspeed Limits. IAS (Knots) Max operating speed - VMO 166 Maneuvering - VA 146 Max Flap Extended - VFE 125 Min Control Speed - VMC with critical (left) engine inoperative 77 Max speed with cargo door open 111 Max speed with windows open 131 Center of Gravity Range. 5.320 m (209.45 in.) to 5.560 m (218.9 in.) at 3400 kg (7495 lbs.) 5.208 m (205.04 in.) to 5.560 m (218.9 in.) at 2600 kg (5732 lbs.) or less Straight line variation between points given. Reference Datum. 5.00 m (196.85 in.) forward of wing leading edge. Mean Aerodynamic Chord . 1.6 m (62.99 in.) (L.E. at STA 196.85) (MAC) Leveling Means. Seat rails in cargo compartment Maximum Weights. Take-off weight: 3400 kg. (7495 lbs.) Landing weight: 3180 kg. (7010 lbs.) Zero Fuel Weight: 3275 kg. (7220 lbs.) Minimum Crew. One pilot required in left seat. Number of Seats. 11 (2 pilots, 9 passengers) 2 at 2.950 m (116.14 in.), 2 at 3.921 m (154.37 in.) 2 at 4.734 m (186.38 in.), 2 at 5.572 m (219.37 in.) 2 at 6.410 m (252.36 in.), 1 at 7.706 m (303.385 in.) Maximum Baggage. 250 kg. (550 lbs.) at 8.322 m (327.638 in.) Fuel Capacity. Four wing tanks total 1024 l. (270.6 U.S. Gal.) usable 998 l. (263.7 U.S. Gal.) See Note 1 for data on unusable fuel. 3 A61EU Oil Capacity. Total capacity 14 l., (3.7 U.S. Gal.) 7 l. (1.85 U.S. Gal.) for each engine at 4.480 m (176.4 in.) Maximum Operating Altitude. 20,000 ft. Control Surface Movements. Wings flaps Down 30º ± 1º Aileron Up 25º ± 1º Down 15º ± 1º Aileron tab (with respect Up 20º ± 1º Down 20º ± 1º to aileron chord) Elevator Up 24º ± 1º Down 15º ± 1º Elevator tab (with respect Up 26º30' ± 1º Down 27º30' ± 1º to elevator chord) Rudder Left 23º ± 1º Right 23º ± 1º Rudder tab (with rudder Left 14º ± 1º Right 14º ± 1º in neutral position) II. Model SF600A (Normal Category), approved May 8, 1996. (Same as Model SF600 except: Increased take-off weight; increased maximum landing weight; increased zero fuel weight, new powerplant system; wing aerodynamic modifications; main landing gear supporting structure modifications). Engine. 2 Detroit Diesel Allison 250-B17F/1 turboprops. Fuel. Commercial Kerosene Jet A-1 conforming to ASTM D1655 specification. When ambient temperature is lower than +5ºC (105.8ºF) the fuel must contain anti-icing additive conforming to MIL-I-27586E in amount of not less than 0.060 and no more than 0.15 by volume. Oil. According to Airplane Flight Manual. Engine Ratings. Takeoff and Max. Continuous 450 SHP Engine Limits. Torque Meter Pressure Torque Take off and Max continuous 111 P.S.I. Propeller Speed (N2) Percent RPM Take off, O.E.I. climb and Max continuous 105 2132 Transient (15 seconds) 110 2233 Turbine Outlet Temperature Take off and Max Continuous 810ºC Transient (6 seconds) 899ºC Starting (10 seconds) 810-927ºC 4 A61EU Propeller and Propeller Model Hartzell HC-B3T Limits. Hub HC-B3TF-7A Blade T10173-11R Diameter 90 3/8 inches (no reduction permitted) Blade angle at 30 inch station low pitch + 9.5º ± 0.5º feathering 80º (only for reference) reverse - 11 ± 0.5º Governor Woodward model 8210-018 Overspeed governor Woodward model 8210-011 Spinner Hartzell P/N 835-39 Airspeed Limits. IAS (Knots) Max operating speed - VMO 162 Maneuvering - VA 150 See A.F.M. for variations with weight Max with Flap Ext. - VFE 121 Min Control Speed - VMC with critical (left) engine inoperative 88 Max speed with cargo door open (Flaps up) 109 Max speed with windows open 129 Center of Gravity Range. 5.349 m (210.59 in.) to 5.560 m (218.9 in.) at 3605 kg (7947 lbs.) 5.208 m (205.04 in.) to 5.560 m (218.9 in.) at 2600 kg (5732 lbs.) or less Straight line variation between points given. Reference Datum. 5.00 m (196.85 in.) forward of wing leading edge. Mean Aerodynamic Chord 1.6 m (62.99 in.) (L.E. at STA 196.85) (MAC) Leveling Means. Seat rails in cargo compartment. Maximum Weights. Ramp weight 3625 Kg. (7991 lbs.) Take-off weight 3605 Kg. (7947 lbs.) Landing weight 3400 Kg. (7495 lbs.) Zero Fuel weight 3350 Kg. (7385 lbs.) Minimum Crew. One pilot required in left seat. Number of Seats. 11 (2 pilots, 9 passengers) 2 at 2.950 m (116.14 in.), 2 at 3.921 m (154.37 in.) 2 at 4.734 m (186.38 in.), 2 at 5.572 m (219.37 in.) 2 at 6.410 m (252.36 in.), 1 at 7.706 m (303.385 in.) Maximum Baggage. 250 kg. (550 lbs.) at 8.322 m (327.638 in.) 5 A61EU Fuel Capacity. Four wing tanks total 1024 l. (270.6 U.S. Gal.) usable 998 l. (263.7 U.S. Gal.) See Note 1 for data on unusable fuel. Oil Capacity. Total capacity (tank + engine) 18.5 l. (4.9 U.S. Gal.) 9.25 l. (2.45 U.S. Gal.) for each engine at 4.480 m (176.4 in.) Maximum Operating Altitude. 20,000 ft. Control Surface Movements. Wings flaps Down 30º ± 1º Aileron Up 25º ± 1º Down 15º ± 1º Aileron tab (with respect Up 20º ± 1º Down 20º ± 1º to aileron chord) Elevator Up 24º ± 1º Down 15º ± 1º Elevator tab (with respect Up 26º30' ± 1º Down 27º30' ± 1º to elevator chord) Rudder Left 19º ± 1º Right 19º ± 1º Rudder tab (with rudder Left 24º ± 1º Right 24º ± 1º in neutral position) DATA PERTINENT TO ALL MODELS. Serial Number Eligible. The Registro Aeronautico Italiano (R.A.I.) Certificate of Airworthiness endorsed as noted below under "Import Requirements" must be submitted for each individual aircraft for which application for certification is made. Vulcan Air SF600 airplane models have the following serial numbers No. 005 thru 009. Vulcan Air SF600A airplane models have the following serial numbers No. 010 thru 999. Additional numbers may be added by petition submitted by the Type Certificate holder. Certification Basis. (a) SF600 Federal Aviation Regulations - 14 CFR Section 21.29 and 14 CFR FAR 23 effective 1 February 1965, including amendments 23-1 through 23-32. 14 CFR SFAR 27 amendments 27-1 through 27-5. 14 CFR Part 36 effective 1 December 1969 including amendments 36-1 through 36-15. Equivalent safety finding exist with respect to the following regulation: - 14 CFR Section 23.1545(b)(5): Marking of airspeed indicator for Vyse Date of initial application for Type Certificate July 31, 1986 with re-application August 1, 1989. 6 A61EU (b) SF600A 14 CFR Part 23, dated February 1, 1965, including amendments 23-1 through 23-35, amendment 23-36 for para. 23.2, 23.1413, amendment 23-40 for the paragraph 23.951, amendments 23-42 for the paragraphs 23.67, 23.75, 23.161, 23.331, 23.351, 23.421, 23.423, 23.425, 23.427, 23.441, 23.443, 23.455, 23.677, 23.701, 23.939, 23.1323, 23.1325. Equivalent safety finding exist with respect to the following regulation: - 14CFR Section 23.1545(b)(5): Marking of airspeed indicator for Vyse - 14 CFR Part 34 effective September 10, 1990. - 14 CFR Part 36 dated December 1, 1969, as amended through amendments 36-20 effective September 16, 1992. Date of initial application for Type Certificate October 24, 1990. Import Requirements. To be considered eligible for operation in the United States, each aircraft manufactured under this type certificate must be accompanied by a certificate of airworthiness for export or certifying statement endorsed by the exporting foreign civil airworthiness authority which states (in the English language): This aircraft conforms to its U.S. type design (Type Certificate No. A61EU) and is in a condition for safe operation. The U.S. airworthiness certification basis for aircraft for aircraft type certificated under FAR Section 21.29 and exported by the country of manufacture is FAR Sections 21.183(c) or 21.185(c). Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 exported from countries other than the country of manufacture (e.g., third party country) is FAR Sections 21.183(d) or 21.183(b). Equipment. The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis) must be installed in the aircraft for certification. In addition, the following items are required: SF600 a) Pre-stall warning indicator, Safe Flight Instrument Corp., Type 164. b) Agusta SF600 Flight Manual, R.A.I. approved dated June 5, 1987 (Approval No. 231.129/T) or later R.A.I. approved revision. c) Engine Armoring Kit installed in accordance with Drawing 7 A61EU Equipment (cont.) FI-504046. SF600A SF600A R.A.I. approved Airplane Flight Manual (600-00-38-03) dated September 27, 1993 and subsequent approved revisions. NOTES NOTE 1. Current weight and balance report including list of equipment in certificated empty weight, and loading instructions, must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity location must include: Unusable Fuel in internal tanks: 18 kg. (38.5 lbs.) at 5.650 m. (222.4 in.) Unusable Fuel in external tanks: 3 kg. (6 lbs.) at 5.650 m. (222.4 in.) Engine Oil (total): for SF600 12 kg. (27 lbs.) at 4.480 m. (176.4 in.) for SF600A 15.85 kg. (35 lbs.) at 4.48 m. (176.4 in.) NOTE 2. All placards required in the AFM must be installed in the appropriate location. NOTE 3. Instructions for Continued Airworthiness and Service Life Limits of components are contained in the SF600A Maintenance Manual (SIAI Marchetti Report 600-00-39-01). Revisions to Airworthiness Limitations must be FAA approved. All manufacturer’s service bulletins (and other manual material) which contain a statement that the document is approved by the exporting airworthiness authority (RAI) may be interpreted as FAA approved. These approvals pertain to the type design only. All service bulletins classified as Mandatory by the Italian Civil Aviation Authority are identified to that effect and are subject to an Airworthiness Directive issued by the FAA. Aircraft eligible for a standard airworthiness certificate must not be issued an airworthiness certificate unless the FAA has approved the Instructions for Continued Airworthiness. .....END.....