Thor T/A

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title: "Thor T/A" type: doc version: 1 created: 2026-02-28 author: "Wikipedia contributors" status: active scope: public tags: ["1980s-canadian-ultralight-aircraft", "homebuilt-aircraft", "single-engined-tractor-aircraft"] description: "Canadian ultralight aircraft" topic_path: "geography/canada" source: "https://en.wikipedia.org/wiki/Thor_T/A" license: "CC BY-SA 4.0" wikipedia_page_id: 0 wikipedia_revision_id: 0

::summary Canadian ultralight aircraft ::

::data[format=table title="Infobox aircraft"]

Field	Value
name	T/A
aircraft_type	Ultralight aircraft
national_origin	Canada
manufacturer	Thor Air
designer	Thorsten B. Strenger (or possibly Gunter Webster)
status	Production completed
introduction	1985
::

| name = T/A | logo = | logo_size = | image = | alt = | caption = | long_caption = | other_names = | aircraft_type = Ultralight aircraft | aim = | outcome = | related = | national_origin = Canada | manufacturer = Thor Air | design_group = | designer = Thorsten B. Strenger (or possibly Gunter Webster) | builder = | issuer = | status = Production completed | owners = | primary_user = | more_users = | service = | major_applications = | proposals = | prototypes = | number_built = | construction_number = | civil_registration = | military_serial = | radio_code = | requirement = | aircraft_carried = | flights = | total_hours = | total_distance = | construction_date = | introduction = 1985 | retired = | first_flight = | initiated = | in_service = | last_flight = | expected = | developed_from = | variants = | developed_into = | preservation = | fate = | predecessors = | successors = | concluded = 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.

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 254 lb. The aircraft has a standard empty weight of 238 lb. 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 32.3 ft 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 28 hp Rotax 277 single cylinder, two-stroke powerplant. ;1-A1-A :Up-engined model, powered by a 40 hp 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)

|ref=Cliche and the Virtual Ultralight Museum |prime units?=imp General characteristics

|genhide=

|crew=one |capacity= |length m= |length ft=13.8 |length in= |length note= |span m= |span ft=32 |span in=4 |span note= |height m= |height ft=7 |height in=8 |height note= |wing area sqm= |wing area sqft=167 |wing area note= |aspect ratio= |airfoil= |empty weight kg= |empty weight lb=238 |empty weight note= |gross weight kg= |gross weight lb=500 |gross weight note= |fuel capacity=5 u.s.gal |more general= Powerplant

|eng1 number=1 |eng1 name=Rotax 277 |eng1 type=single cylinder, two-stroke aircraft engine |eng1 kw= |eng1 hp=28

|prop blade number= |prop name= |prop dia m= |prop dia ft= |prop dia in= |prop note=

Performance

|perfhide=

|max speed kmh= |max speed mph=63 |max speed kts= |max speed note= |cruise speed kmh= |cruise speed mph=55 |cruise speed kts= |cruise speed note= |stall speed kmh= |stall speed mph=22 |stall speed kts= |stall speed note= |never exceed speed kmh= |never exceed speed mph= |never exceed speed kts= |never exceed speed note= |range km= |range miles= |range nmi= |range note= |endurance= |ceiling m= |ceiling ft=10000 |ceiling note= |g limits=+3/-2 |roll rate= |glide ratio=9:1 |climb rate ms= |climb rate ftmin=700 |climb rate note= |time to altitude= |sink rate ms= |sink rate ftmin= |sink rate note= |lift to drag= |wing loading kg/m2= |wing loading lb/sqft= |wing loading note= |power/mass= |thrust/weight= |more performance= |avionics=

|see also= |related= |similar aircraft= |lists=

References

References

1. Cliche, Andre: ''Ultralight Aircraft Shopper's Guide'' 8th Edition, page E-41. Cybair Limited Publishing, 2001. {{ISBN. 0-9680628-1-4
2. Virtual Ultralight Museum. "Thor T/A".

::callout[type=info title="Wikipedia Source"] This article was imported from Wikipedia and is available under the Creative Commons Attribution-ShareAlike 4.0 License. Content has been adapted to SurfDoc format. Original contributors can be found on the article history page. ::