TCDS G17EU

Page No. 1 2 Rev. No. 2 2 DEPARTMENT OF TRANSPORATION FEDERAL AVIATION ADMINISTRATION G17EU Revision 2 SLINGSBY Type T.53.B March 1, 2012 TYPE CERTIFICATE DATA SHEET NO. G17EU This data sheet which is a part of type certificate No. G17EU 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 Slingsby Aircraft Co. Ltd. Kirkbymoorside Yorkshire, England Type Certificate Ownership Record (1) This TC was considered not valid by the state of design on July 5, 2007, and has been replaced by European Aviation Safety Agency (EASA) Specific Airworthiness Specification (SAS) number EASA.SAS.A.088, issued July 5, 2007. 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. Model T.53.B., approved September 3, 1968 Airspeed limits (IAS) Glid e or dive 123 knots (143 mph) Airplane tow 80 knots (93 mph) Auto-winch tow 70 knots (81 mph) C.G. range (-5.0) to (+4.64) Datum The C. of G. horizontal datum is the wi ng root leading edge 11.62" from the center line of aircraft. Leveling means The fuselage horizontal datum is leve l when the top of the rear fuselage slopes nose down at 8°12' Maximum weight 1160 lbs (A crobatic and Cloud Flying) 1285 lbs (Non-Cloud Flying) No. of seats 2 Baggage None Control surface Movements Elevator Up 25° Down 25° Rudder Right 30° Left 30° Aileron Up 30° Down 15° Dive brakes 6.90" out (upper) 7.20" down (lower) G17EU 2 Serial Nos. eligible Only those ai rcraft serials holding a standard airworthiness certificate issued prior to March 1, 2012 are eligible. The United Kingdom Certificate of Airwor thiness for Export endorsed as noted under "Import Requirements" must be submitted for each individual glider for which Application for Certification is made. Certification Basis FAR 21.23, eff ective June 6, 1968. British Civil Airworthiness Requirements, Section E, Gliders, Issue 2, dated May 16, 1960, was found to provide a level of safety equivalent to FAR 21.23, effective June 6, 1968, to enable certification under the provisions of FAR 21.29 (a) (ii). Type Certificate No. G17EU issued September 3, 1968. Date of Application for Type Certificate: June 27, 1968 Import requirements None elig ible after March 1, 2012. Previous to this date: A U.S. Airworthiness Certificate may be issued on the basis of a U.K. Certificate of Airworthiness for Export signed by a repres entative of the Civil Aviation Department, Board of Trade containing the following statement: "The glider covered by this certificate has been examined and found to comply with the British Civil Airworthiness Requirements, S ection E, Gliders, Issue 2, dated May 16, 1960 and conforms to Type Certificate No. G17EU. Equipment: The basic required equipm ent as prescribed in the applicable airworthiness regulations (see Certification basis) must be installed in the glider for certification. NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions when necessary, must be provided for each glider at the time of original certification. NOTE 2. The following placards must be installed in full view of the pilot: (a) "Flight in cloud is permitted providing the following instruments of an approved type are installed" - "Altimeter and Turn and Bank." (b) "The following acrobatic manoeuvers are permitted - l oops, stall turns, tight turns (3 1/2g) spins and chandelles." (c) "Night flying" is prohibited. (d) The following I.A.S. must not be exceeded. Glide or dive 123 knots (143 mph) Airplane tow 80 knots (93 mph) Auto-winch tow 70 knots (81 mph) Spins must not be continue d above 70 knots I.A.S. (81 mph). When flying in rough air, max. speed 80 knots I.A.S. (93 mph) (e) The breaking load of the weak link in the towing cable is not to exceed 1400 lb. ...END...