TCDS A58EU

Page No. 1 2 3 4 Rev. No. 5 5 4 3 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A58EU Revision 5 FFT-GmbH SC01 B-160 Gyroflug Speed Canard March 1, 2012 TYPE CERTIFICATE DATA SHEET NO. A58EU This data sheet which is part of Type Certificate No. A58EU 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 FFT Gesellschaft für Flugzeug - & Faserverbund-Technologie mbH P.O. Box 85 Flugplatz D-7947 Mengen West Germany Type Certificate Ownership Record The FAA was notified by letter on June 23, 1998 that this firm is defunct. See NOTE 8. Type Certificate Ownership Record (1) This TC was considered not valid by the state of design on January 24, 2008, and has been replaced by European Aviation Safety Agency (EASA) Specific Airworthiness Specification (SAS) number EASA.SAS.A.050, issued January 24, 2008. Only standard airworthiness certificates issued prior to March 1, 2012 are valid. (2) Future unsafe conditions existing in the aircraft may result in the revocation of the airworthiness certificates of the aircraft if there is no entity to comply with 14 CFR § 21.99(a), “Required design changes.” (3) Replacement parts may not be available in the future. I. Model SC 01 B-160 (Normal Category), approved April 12, 1990 Engine Lycoming O-320-D1A Fuel Avgas 100 or 100LL Engine Limits Maximum takeoff power 160 hp (119 kw) Maximum takeoff rpm 2700 rpm Maximum continuous rpm 2500 rpm Propeller and Propeller Limits MT-Propeller MTV-6-C/LD 152-07 Diameter : 59.84 in (152 cm) No additional tolerance permitted Maximum rpm : 2700 Airspeed Limits (IAS) Never exceed : 197 kts (365 km/h) Max. structural cruising : 154 kts (285 km/h) Maneuvering : 114 kts (212 km/h) Landing gear lowering: : 109 kts (202 km/h) Landing gear extended: : 109 kts (202 km/h) 2 A58EU C.G. Range Forward C.G.: (aft of datum) 119.3 in (303.0 cm) at 1146 lbs. (520 kg) 119.3 in (303.0 cm) at 1500 lbs. (680 kg) 120.5 in (306.0 cm) at 1576 lbs. (715 kg) Rear C.G. 125.2 in (318.0 cm) at 1102 lbs. (500 kg) 123.8 in (314.4 cm) at 1576 lbs. (715 kg) Straight line variation between points given. Empty Weight C.G. Range Forward C.G.: 131.1 in (333.0 cm) at 926 lbs. (420 kg) 129.5 in (329.0 cm) at 1102 lbs. (500 kg) Rear C.G.: 134.6 in (342.0 cm) at 926 lbs. (420 kg) 133.1 in (338.0 cm) at 1102 lbs. (500 kg) Straight line variation between points given. Datum Fuselage station 0.0 126.4 in (321 cm) in front of main wi ng root leading edge and wing strake kink Leveling Means Rear left canopy frame 8° nose down Maximum Takeoff Weight 1576 lbs. (715 kg) Maximum Landing Weight 1500 lbs. (680 kg) Number of Seats 2: 1 at 79.0 in (193 cm) (front cockpit) 1 at 118.0 in (302 cm) (rear cockpit) Minimum Crew 1 in the front cockpit Maximum Baggage 33 lbs. (15 kg) at 108.3 in (275 cm) Fuel Capacity 42.26 US Gal (160 l) Two inter-connected 21.13 US gal tanks in wing strakes at 122.8 in (312 cm) 40.95 US Gal (155 l) usable Oil Capacity 8 qts. minimum 2 qts Control Surface Movements Ailerons Up 20° Down 8.5° Elevator Up 10° Down 29° Elevator trim Down 11° Down 29° Rudder (both): in 0° Out 27.5° Serial Nos. Eligible S 60 and subsequent. Only those aircraft serials holding a standard airworthiness certificate issued prior to March 1, 2012 are eligible. Import Requirements None elig ible after March 1, 2012. Previous to this date: The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of the Luftfahrt Bundesamt 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 comply with U.S. airworthiness regulations 14 CFR Part 23 approved under U.S. Type Certificate No. A58EU and to be in a condition for safe operation.’ 3 A58EU Certification Basis 1) 14 CFR Sections 21.29, 21.183(c), and 14 CFR 23, effective January 9, 1965, including Amendments 23-1 through 23.28, and 2) 14 CFR Part 36, effective December 1, 1969, including 36-1 through amendment 36-17, and 3) Special Conditions; Gyroflug Speed Canard published in Federal Register 53FR49851 December 12, 1988, and 4) Section 611(b) of the FAA Act of 1958 Application for Type Certificate dated February 2, 1987. The Luftfahrt Bundesamt originally type certificated this aircraft under its type certificate Number 1066. The FAA validated this product under U.S. Type Certificate Number A58EU. Effective September 28, 2003, th e European Aviation Safety Agency (EASA) began oversight of this product on behalf of Germany. Equipment The basic required equipment as pr escribed in the applicable airworthiness regulation (see Certification Basis) must be installed in the aircraft. This equipment must include a current Pilot's Operating Manual. Service Information 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 the Luftfahrt Bundesamt. • Service bulletins, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. The FAA accepts such documents and considers them FAA-approved unless one of the following conditions exists: • The documents change the limitations, performance, or procedures of the FAA approved manuals; or •The documents make an acoustical or emissions changes to this product’s U.S. type certificate as defined in 14 CFR § 21.93. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case-by-case to EASA to approve on behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. NOTE 1. A current weight and balance report together with a list of included equipment must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity locations must include the following: a) Unusable fuel of 8 lbs. (3 .6 kg) 122.8 in (312 cm) aft of datum b) engine oil of 8 quarts NOTE 2. The placards listed in Section 2 of the LBA-a pproved Airplane Flight Manual must be displayed. NOTE 3. Every 3,000 flight hours the "Significant Structur al Items Inspection" and prior to 12,000 flight hours the "Airframe Major Inspection" contained in th e FAA approved airworthiness limitation section of the Gyroflug-FFT maintenance manual must be performed. NOTE 4. Structural composite components exposed direc tly to sunlight must have a white surface (except for registration markings). Changing the color and the thickness of the coat is only permissible after prior approval by the manufacturer. NOTE 5. Major structural repairs must be accomplished at FAA certified repair stations rated for composite 4 A58EU aircraft structure work, in accordance with Gyroflug repair methods approved by FAA. NOTE 6. The airplane is approved for IFR day/night flights. NOTE 7. Acrobatic maneuvers, incl uding spins, are not approved. NOTE 8. The FAA was informed by the Luftfahrt-Bundesamt (LBA) of Germany on June 23, 1998, that this firm is defunct. For issues concerning con tinued airworthiness, contact: the aviation authority of Germany, or the Small Airplane Directorate: Luftfahrt-Bundesamt (LBA) Federal Aviation Administration Hermann-Blenk-Str. 26 Sma ll Airplane Directorate, ACE-112 38108 Braunschweig 901 Locust, Room 301 Germany Kansas City, MO 64106 NOTE 9. For issuance of an airworthiness certificate in accord ance with 14 CFR Part 21.182(c), the Luftfahrt Bundesamt of Germany must certify that the airplane conforms to the type design and is in a condition for safe operation. In that regard, the Luftfahrt Bundesamt of Germany will certify that the airplane complies with all applicable mandatory continuing airworthiness information (MCAI) it has issued. For issuance of an airworthiness certificate in accordance with 14 CFR Part 21.182(d) the certificating insp ector, or other authorized person, must find, among other things, that the product is in a condition for safe ope ration. In order to make that finding, the certificating inspector or other authorized person should contact AC E-112, Federal Aviation Admini stration, Small Airplane Directorate, prior to issuance to determine whether show ing airplane compliance with certain MCAI is necessary to support a finding that the airplane is in a condition for safe operation. .....END.....