Thor T/A Explained

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.^[1] ^[2]

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 2540NaN0. The aircraft has a standard empty weight of 2380NaN0. 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 32.31NaN1 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 280NaN0 Rotax 277 single cylinder, two-stroke powerplant.

1-A

Up-engined model, powered by a 400NaN0 Rotax 447 twin cylinder, two-stroke powerplant.

Two-seater

Similar to the single-seat models but with a second seat for dual instruction.

Notes and References

Cliche, Andre: Ultralight Aircraft Shopper's Guide 8th Edition, page E-41. Cybair Limited Publishing, 2001.
Web site: Thor T/A . 2 January 2012. Virtual Ultralight Museum. https://web.archive.org/web/20150507191309/http://virtualultralightmuseum.com/t.htm. 7 May 2015.