The two seat Tundra was later developed into a conventional landing gear single seat ultralight for the US FAR 103 Ultralight Vehicles category, including meeting the category's stringent 254 lb (115 kg) empty weight limit. The resulting aircraft was introduced in 1997 and was designated the 1/2 Tun indicating it was "half a Tundra". This version had the wingspan reduced from the two-seater's 32 ft (9.8 m) to 26 ft (7.9 m). The cockpit steel tube structure was also reduced, along with the cockpit fairing and the fuel tank was changed to 5 US gal (19 l) capacity, from the two seater's 10 US gal (38 l) tank. Reported construction time for the 1/2 Tun is also 250 hours. The 1/2 Tun's standard engine is the 40 hp (30 kW) Rotax 447 twin-cylinder, two-stroke aircraft engine.
Manufactured / designed by the same producer / designer: