ALTO 912 TG
Ultralight/ light sport all-metal aircraft produced by Direct Fly till 2022. In total more than a hundred pieces of this model has been sold and is still flying in many countries of the world, beside the Czech Republic it has been for example France, Australia, Italy, USA or Turkey.
ALTO 912 TG has been popular in all three of its versions, as a ready to fly, quick kit and basic kit.
In 2016 a technology transfer agreement was signed between Direct Fly and Wanfeng Aviation. The agreement allowed Wafeng to produce and sell ALTO 912 TG on Chinese market.
Production of ALTO 912 TG has been terminated with the arrival of new ALTO NG model in 2022.
The advantages of ALTO lie in its simple and comfortable piloting, which is guaranteed by the design of the wing. The rectangular wing plan and the profile with a blunt leading edge provide predictable stall characteristics and behaviour. The wing is a semi-monocoque structure and is equipped with built-in tanks with a capacity of 92 litres of fuel.
The rear of the fuselage is designed with a rectangular cross section with an oval upper surface. The stiffness of the structure is secured by diagonal webs. The wing-fuse link is conceived as the interconnection of the wing beams with the center plane of the airplane by means of flanged bolts.
The horizontal and vertical tail surfaces are of a traditional arrangement. They are made as a riveted structure with composite end arcs.
Flight control transmission from the "stick" is realized by means of rods and cables. Directional steering of the front landing gear leg is coupled with pedals for changing the aircraft direction. The brakes are hydraulically controlled by a lever located on the center panel.
The landing gear is designed as three-wheel, with front steering wheel. The main wheels are fixed to the fuselage on flexible laminate legs.
Access to the cockpit is secured by means of footpaths located at the trailing edge of the wing. The spacious, 110 cm wide cockpit provides plenty of room for comfortable control of the aircraft. The cockpit roof slides forward and it is mounted on rails.
Specifications
| Length | 6,15 m |
| Wingspan | 8,20 m |
| Wing area | 10,6 m2 |
| Height | 2,25 m |
| Cockpit width | 1,10 m |
| Number of seats | 2 |
| Fuel tank capacity | 92 l |
| Engine | Rotax 912ULS |
| Take-off distance to 50ft (UL/LSA) | 250/410 m |
| Landing distance from 50ft (UL/LSA) | 200/295 m |
| Empty weight | 288 kg |
| Maximum takeoff weight (UL/LSA) | 472,5/600 kg |
| VNE (never-exceeded speed) (UL/LSA) | 250/243 km/h |
| Cruising speed | 180 km/h |
| Stalling speed, landing configuration (UL/LSA) | 65/76 km/h |
| Stalling speed, clean configuration (UL/LSA) | 74/87 km/h |
| Load factor | +4 / -2 |
| Maximum climbing speed (UL/LSA) | 6,3/5,1 m/s |
