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1.3. Description of the Aeroplane
ATEC 212 SOLO is an ultralight single-seater cantilever low-wing aircraft of an all carbon
composite construction. It is equipped with a tail landing gear with the steerable tail wheel.
The power plant is a pull arrangement and consists of a ROTAX 912 UL 80 HP engine and a
two-blade or three-blade fix or ground adjustable propeller FITI.
1.4. Specification
Dimensions
Wing span ……………………………………. 7,48 m
Length of fuselage ……………………………. 5,2 m
Total height ……………………………………. 1,4 m
Wing area ……………………………………. 7,27 m
2
Depth of mean aerodynamic chord …………….. 1,032 m
Span of horizontal tail surface …………….. 2,18 m
Flap position ……………………………………. I 10°
II 20°
III 35°
Airfoil Section
Root section …………………………………….. SM 701
End section …………………………………….. SM 701
Tail Wheel Landing Gear
Wheel spacing…………………………………….. 1,56 m
Wheel base …………………………………….. 3,66 m
Tyre dimensions …………………………….. 350 * 120
Tyre pressure …………………………………….. 0,16 MPa / 1,6 atp
Springing system
Main wheels …………………………….. composite spring
Tail wheel …………………………….. composite spring
Brakes ……………………………………. Main wheels hydraulic disc brakes
Rescue System installed / not installed………. GRS 6/360
Weights
Empty weight …………………………………………………. kg
Maximum take-off weight …………………………………. 300 kg
Maximum take-off weight including rescue system installed … 315 kg
Maximum weight of luggage in luggage space … 5 kg