The Thor T/A is a Canadian ultralight aircraft that was designed by Thorsten B. Strenger (or possibly Gunter Webster) and produced by Thor Air of Weston, Ontario. The aircraft was supplied as a kit for amateur construction.Cliche, Andre: Ultralight Aircraft Shopper's Guide 8th Edition, page E-41. Cybair Limited Publishing, 2001.
Design and development The aircraft was designed to comply with the US FAR 103 Ultralight Vehicles rules, including the category's maximum empty weight of . The aircraft has a standard empty weight of . It features a strut-braced high-wing, a single-seat, open cockpit, conventional landing gear and a single engine in tractor configuration.
The aircraft is made from bolted-together aluminum tubing, with its flying surfaces covered in Dacron sailcloth. Its 80% double-surface span wing is braced with "V" lift struts. The pilot is accommodated on an open seat, protected by a simple windshield. The landing gear has suspension on the main wheels and features a steerable tailwheel. The three axis control system is unusual. Pitch and roll are conventionally controlled with elevator and rudder, while roll is controlled with tip rudders.
Variants T/A Initial design, powered by a Rotax 277 single cylinder, two-stroke powerplant. 1-A Up-engined model, powered by a Rotax 447 twin cylinder, two-stroke powerplant.
Two-seater Similar to the single-seat models but with a second seat for dual instruction.
Specifications (T/A)
References