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.[1]
The T-2 Maverick was designed to comply with the Fédération Aéronautique Internationale microlight category, including the category's maximum gross weight of 450 kg (992 lb). The aircraft has a maximum gross weight of 450 to 540 kg (992 to 1,190 lb) 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.[1]
The aircraft's structure is made from tubing, with its double surface wing covered in Dacron sailcloth. Its 10.2 m (33.5 ft) 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 50 hp (37 kW) Rotax 503 engine, the liquid-cooled 64 hp (48 kW) Rotax 582 engine or the four cylinder, air and liquid-cooled, four-stroke, dual-ignition 80 hp (60 kW) Rotax 912UL engine.[1]
The aircraft has an empty weight of 190 kg (419 lb) and a gross weight of 450 to 540 kg (992 to 1,190 lb) depending on the version, giving a useful load of 260 to 350 kg (573 to 772 lb). With full fuel of 30 litres (6.6 imp gal; 7.9 US gal) the payload is 238 to 328 kg (525 to 723 lb).[1]
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 16.5 m2 (178 sq ft).[1]