# TCDS G42EU: Vickers-Slingsby - Type: Type certificate data sheet - Status: Current - Holder: Vickers-Slingsby - Revision: 0 - Revised: January 18, 1979 - Product: Aircraft, Glider - Certification basis: Part 1, Part 21 - Data sheet PDF: https://openairdocs.org/files/sha256/a3/02/a302c871a8bb9fc92311c76f432a3427fd84eefe1e74b93f2f59db4c07d6993c - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/C0B70A3E2455498F85256720005988B3.0001 - Page: https://openairdocs.org/tcds/G42EU ## Models (1) As the data sheet lists them. - T.65A Vega ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 Rev. No. - - - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION G42EU SLINGSBY T65A Vega January 18, 1979 TYPE CERTIFICATE DATA SHEET NO. G42EU This data sheet which is a part of type certificate No. G42EU 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 Vickers-Slingsby Kirkbymoorside York YO6 6EZ England I. Model T.65A Vega Glider, approved January 18, 1979 Airspeed limits (I.A.S.) Vne - Max. speed (all flap positions) 135 knots (155 m.p.h.) Vb - Max. rough air 106 knots (122 m.p.h.) Vt - Airplane tow 100 knots (115 m.p.h.) Ww - Auto-winch tow 70 knots (90 m.p.h.) Air brakes max. operating 135 knots (155 m.p.h.) C.G. range 9.25 in. to 13.26 in. aft of datum at all weights. Empty Weight C.G. Range None. Datum Wing leading edge at wing root (350 mm from a/c centreline) Leveling means Fuselage datum points horizontal. Maximum weight Max. take-off without water ballast 775 lb. Max. take-off with water ballast* 970 lb. Max. landing 970 lb. (*Total weight of sailplane must not exceed 775 lb. before water ballast is added). Water Ballast one 9.75 gal. (97.5 lbs) capacity water ballast bag in each wing - no significant effect on CG. No. of seats One (at 18.0 in. Forward of datum) Maximum Baggage None Control surface movements Elevator Up 24° + 1.5° Down 16° + 1.5° Rudder Right 25° + 2.0° Left 25° + 2.0° Aileron Up 23° + 1.0° Down 10° + 1.0° (Measured with flaps in position 0, see NOTE 6) Flaps Up 8° +1.0° (See NOTE 6) Down 8° + 1.0° Air Brakes Angle with wing upper surface 48° min. G42EU 2 Wink Links for Towing 1100 lb. Max. Serial Nos. eligible See Import Requirements. Import Requirements 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 United Kingdom, Civil Aviation Authority, Airworthiness Division, containing the following statement: "The glider covered by this certificate has been examined, tested, and found to conform to the type design approved under FAA Type Certificate no. G42EU and is in condition for safe operation". Certification Basis FAR 21.23 and FAR 21.29 effective February 1, 1965. Type Certificate No. G42EU issued January 18, 1979. Date of Application for Type Certificate: March 30, 1977. Validation Basis Type Certificate G42EU was issued pursuant to FAR 21.29 (a) in validation of Civil Aviation Authority, Certification of Compliance with the Ostiv Airworthiness Requirements for sailplanes September 1971 - Category U and LFSM airworthiness requirements for sailplanes translated May 1967 - Category U, either of which was found to provide a level of safety equivalent to the aforementioned FAA certification basis. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification basis) must be installed in the glider for standard airworthiness certification. In addition the following equipment must be installed: 1. Instruments (Non-Cloud flying): (a) Airspeed indicator (marked per Flight Manual Section 1.5.2.) (b) Altimeter. (c) Magnetic Compass 2. Additional Instruments for Cloud flying: (a) Turn and Bank Indicator (b) Variometer 3. Additional Instruments for limited approved aerobatics (a) Accelerometer 4. T.65A VEGA Flight Manual approved by the CAA through amendment 5, dated July 1978 or later approved amendments. NOTES: 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 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 the following instruments are installed: (1) Airspeed indicator (2) Altimeter (3) Magnetic Compass (4) Turn and Bank (5) Variometer (c) Non-aerobatic The following aerobatic maneuvers only are permitted: Loops, spins, stall turns, chandelles, lazy eights and tight turns up to 3.5'g. NOTE: See Flight Manual Section 1.4.12 for recommended entry airspeeds. 3 G42EU NOTE 2. (Cont'd) (d) When night flying equipment is not installed: "Night flying is prohibited". (e) "Max. Rough Air 106 knots Max. Aero Tow 100 knots Max. Winch/Auto Tow 70 knots Max Air Brakes Open 135 knots Max. Speed Vne 135 knots (f) "Weak link - 1000 lb. max." (g) "Max. T.O. weight without water ballast 775 lb. Max. T.O. weight with water ballast 970 lb. Max. landing weight 970 lb. (h) "Max. cockpit load lb. Min. cockpit load lb. NOTE: Determined per weighing schedule Flight Manual, page 32. NOTE 3. (Reserved). NOTE 4. All external portions of the glider exposed to sunlight must be painted white. Registration and Competition numbers must be painted blue-gray or in any other light colours. NOTE 5. Information essential to the proper Maintenance and repair of the glider is contained in the Vega Service and Repair Manual, February 1978. NOTE 6. Control surfaces should be rigged in accordance with Flight Manual pages 33, 34 and 35. NOTE 7. Major repairs must be accomplished at FAA certificated repair stations rated for Fiberglass Reinforced Plastic (FRP) work, in accordance with repair methods approved by Vickers-Slingsby. ...END... ``` ## ADs (3, in force first) - [AD 84-22-01](https://openairdocs.org/ad/84-22-01): Elevator Malfunction · Vickers-Slingsby T.65A Vega. Effective Nov 7, 1984 - [AD 82-07-01](https://openairdocs.org/ad/82-07-01): Placard/Flap Airbrake System · Vickers-Slingsby T.65A Vega. Effective Mar 25, 1982 - [AD 80-15-08](https://openairdocs.org/ad/80-15-08): Main Wing Shear Web · Vickers-Slingsby T.65A Vega. Effective Jul 17, 1980 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.