TCDS G27EU

Page No. 1 2 3 Rev. No. 1 2 - DEPARTMENT OF TRANSPORATION FEDERAL AVIATION ADMINISTRATION G27EU Revision 1 SLINGSBY T.59.D March 1, 2012 TYPE CERTIFICATE DATA SHEET NO. G27EU This data sheet which is a part of type certificate No. G27EU 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 Sailplanes 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Type Certificate Ownership Record (1) This TC was considered not valid by the state of design on July 5, 2007, and has been replaced by European Aviation Safety Agency (EASA) Specific Airworthiness Specification (SAS) number EASA.SAS.A.089, issued July 5, 2007.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. I. Model Glasflugel T.59.D "KESTREL" Glider, approved 15 December 1972. Airspeed limits (I.A.S.) Max. speed variable with Flap positions - 2 up 135 knots (155 m.p.h.) 1 up 135 knots (155 m.p.h.) 0 108 knots (124 m.p.h.) 1 down 108 knots (124 m.p.h.) 2 down 81 knots (93 m.p.h.) Landing 65 knots (75 m.p.h.) Max. rough air 105 knots (121 m.p.h.) Airplane Tow 81 knots (93 m.p.h.) Auto-Winch Tow 70 knots (90 m.p.h.) Air Brakes Max. Oper ating 135 knots (155 m.p.h.) C.G. range (+11.5 in.) to (+14.76 in.) at all weights. Empty Weight C.G. Range None Datum Wing leading edge nose root Leveling means Slope of rear top surface of fuselage: 2.5° tail down Maximum weight Ma x. take-off without water ballast 960 lb. Max. take-off with water ballast* 1040 lb. Max. landing 960 lb. (*Total weight of sailplane must not ex ceed 960 lb before water ballast is added.) G27EU 2 No. of seats 1 (at 17.2 in. forward of datum) Baggage None Control surface Movements Elevator Up 16.5° + 1.5° Down 16.5° + 1.5° Rudder Right 25° + 2.0° Left 25° + 2.0° Aileron Up 20° + 2.0° Down 10° + 1.0° (Measured with flaps in position 0, See NOTE 6). Flaps Up 8° + 1.0° (See NOTE 6) Down 35° + 2.0° Air Brakes 4.45 in. + 0.20 in. above upper surface of wing. Weak Links for Towing 1000 lb. Max. Serial Nos. eligible Only those ai rcraft serials holding a standard airworthiness certificate issued prior to March 1, 2012 are eligible. A (United Kingdom) Civil Aviation Authority Certificate of Airworthiness for Export endorsed as noted below under "Import Re quirements" must be submitted for each individual glider for which Application for Standard Airworthiness Certification is made. Import requirements None elig ible after March 1, 2012. Previous to this date: A U.S. Standard Airworthiness Certificate may be issued on the basis of a Certificate of Airworthiness for Export signed by a representative of the Civil Aviation Authority, Airworthiness Division, cont aining the following statement: "The glider covered by this certificate ha s been examined, tested, and found to conform to the type design approved under FAA Type Certificate G27EU and is in a condition for safe operation". Certification Basis FAR 21.29 and FA R 21.23, effective 1 February 1965. Type Certificate No. G27EU, issued 15 December 1972. Date of Application for Type Certificate: 12 June 1972. Validation Basis Type Certificate G27EU was pursuan t to FAR 21.29 (a)(1)(ii) in validation of Civil Aviation Authority certification of complia nce with BCAR Section E, Issue 2, except paragraph 3.1 of Chapter E3-2 and 3-1 of Chapter E3-7 which was found to provide a level of safety equivalent to th e aforementioned FAA certification basis. Equipment: The basic required equipm ent as prescribed in the applicable airworthiness regulations (see Certification basis) must be installe d in the glider for standard airworthiness certification. In addition the following equipment must be installed: 1. Instruments (non-cloud flying): (a) Airspeed Indicator (b) Altimeters (c) Magnetic Compass 2. Additional Instruments for cloud flying: (a) Turn and Bank indicator (b) Variometer NOTES G27EU 3 NOTE 1. Current weight and balance report including list of equipment in certificated empty weight, and loading instructions when necessary, must be provided for each glider at the time of original airworthiness certification. NOTE 2. The following placards must be installed in full view of the pilot: (a) "This glider must be operated in compliance with the Operating Limitations stated in the form of placards, markings, and manuals". (b) "Cloud flying: Permitted only when th e following instruments are installed: (1) Airspeed Indicator (2) Altimeter (3) Magnetic Compass (4) Turn and Bank (5) Variometer" (c) "No acrobatic maneuvers, including spins, approved". (d) When night flying equipment is not installed: "Night flying is prohibited". (e) "Max. Rough Air 105 knots Max. Aero Tow 81 knots Max. Winch/Auto Tow 70 knots Max. Airbrakes Open 135 knots Flap Setting Speed Vne +2 & Landing Flap Down 65 knots +2 Down 81 knots +1 Down 108 knots 0 108 knots -1 Up 135 knots -2 Up 135 knots" (g) "Weak Link - 1000 lb. max." (h) "Max. T.O. Weight without water ballast 960 lb Max. T.O. Weight w ith water ballast 1040 lb Max. landing weight 960 lb Jettison water ballast before landing". NOTE 3. (Reserved) NOTE 4. All external portions of the g lider exposed to sunlight must be painted white. Registration and competition numbers must be painted blue-gra y or in any other light colors. NOTE 5. Information essential for the proper repair of the g lider is contained in the Slingsby Sailplanes "Glass Fiber Glider Repair Manual", dated March 1972. NOTE 6. Control surfaces should be rigge d in accordance with Slingsby Drawing No. 59D-00-2 "Rigging Diagram - 19 Meter Kestral", Issue 4, or later approved issue. ...END...