The initial model of the Tundra family was the two-seats-in-tandemtricycle gear Tundra for the US ultralight trainer, homebuilt and European FAI microlight categories. The aircraft features a semi-enclosed cockpit with optional doors and can be fitted with skis or floats.[1][2][3]
The Tundra is built from a welded steel cockpit cage with a fibreglass fairing. The tailboom, tail group and wings are of aluminium construction, with the wings and tail surfaces covered in doped aircraft fabric. The wing incorporates a D-cell, Junkers-style ailerons and a single strut layout.[1][2]
The standard engine is the 50 hp (37 kW) Rotax 503 twin-cylinder, two-stroke aircraft engine, with the liquid-cooled 74 hp (55 kW) Rotax 618, 64 hp (48 kW) Rotax 582, 65 hp (48 kW) Hirth 2706 or the 64 hp (48 kW) SuziAir three-cylinder engines optional. Reported construction time for the two-seater is 250 hours.[1][2][3]
The two-seater 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.[1]
Media related to Joplin Tundra at Wikimedia Commons
