The T-2 was produced starting in 1995 as a trainer for western markets under subcontract, but is now sold under the General Aviation Design Bureau's own name.
The T-2 Maverick was designed to comply with the Fédération Aéronautique Internationale microlight category, including the category's maximum gross weight of 4500NaN0. The aircraft has a maximum gross weight of 450to depending on the version. It features a cable-braced hang glider-style high-wing, weight-shift controls, a two-seats-in-side-by-side configuration open cockpit with two separate cockpit fairings, tricycle landing gear and a single engine in pusher configuration.
The aircraft's structure is made from tubing, with its double surface wing covered in Dacron sailcloth. Its 10.21NaN1 span wing is supported by a single tube-type kingpost and uses an "A" frame weight-shift control bar. Powerplants available are the twin cylinder, air-cooled, two-stroke, dual-ignition 500NaN0 Rotax 503 engine, the liquid-cooled 640NaN0 Rotax 582 engine or the four cylinder, air and liquid-cooled, four-stroke, dual-ignition 800NaN0 Rotax 912UL engine.
The aircraft has an empty weight of 1900NaN0 and a gross weight of 450to depending on the version, giving a useful load of 260to. With full fuel of the payload is 238to.
Two different wings have been supplied as standard, initially the Maverick 14.7 and, since 2000, the larger Maverick II with a wing area of 16.5m2.