| Dimensions | |
| Length | 6.22 m |
| Wingspan | 8.13 m |
| Wing Area | 10.6 m2 |
| Height | 2.32 m |
| Cockpit Width | 1.10 m |
| Weights | |
| Empty Weight | from 315 kg |
| Maximum Takeoff Weight | 600 kg |
| Performance | |
| VNE (Never-Exceeded Speed) | 165 mph |
| Cruising Speed | 125 mph / 136 mph |
| Maximum Climbing Speed | 1000 ft/min |
| Stalling Speed (Landing) * | 42 mph |
| Stalling Speed (Clean) * | 55 mph |
| Take-off distance to 15 m (50ft) * | 400 m / 330 m |
| Landing distance from 15 m (50ft) * | 340 m |
| Range | 625 miles |
| Other | |
| Fuel Tank Capacity | 92 L |
| Engine (standard) | Rotax 912 ULS / Rotax 912 iS / Zonsen C100 / Edge Performance EP915ECI |
| Load Factor | +4 / -2 g |
| Number of Seats | 2 |
Note: Performance figures marked with an asterisk are typically calculated at maximum takeoff weight and under standard atmospheric conditions.
Cockpit with Panoramic Screen
The spacious, 43″ wide cockpit provides plenty of room for comfortable control of the aircraft. The one-piece panoramic screen provides unrivalled all-round views for increased safety. The entire cockpit screen/roof slides forward for easy access.
Wing
The advantages of the ALTO NG 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 fuel tanks with a capacity of 92 L.
Fuselage
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.
Tail Surfaces
The horizontal and vertical tail surfaces are of a traditional arrangement. They are made as a riveted structure with composite end arcs.
Flight Controls
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 centre panel.
Landing Gear
The landing gear is designed as three-wheel, with front steering wheel. The main wheels are fixed to the fuselage on flexible laminate legs.