B612
The final assembly of B612 was moved to HORN ULM
For more detail about B612 please contact Aviatec - Horn ULM
Single seat european ultralight with fully retractable landing gear.
Fuselage is welded steel spaceframe construction covered by ceconite. Between the firewall and instrument panel is allmost 8 U.S. gal. composite fuel tank. The central section contains gear reinforcement areas for main landing gear and all retractable mechanism that is placed uder the seat.
The wing is of single spar contruction build of glass-epoxy composite with carbon fibre main spars, wing skins molded in negative molds. Wing enploys split flap that increase speed range. Wings can be easy removed by one person.
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Tail section: Centilever tail is constructed with tube aluminium spars and styrofoam ribs covered by ceconite. Horizontal tail section is easy removable.
New model of B612 is delivered with all composite tail section only.
Lending gear: Welded steel udercarriage legs with hydraulic-shock-absorber are manually retractable. The tricycle gear configuration, steerable nosewhel and diferential braking all combine to make the aircraft easy handle on the ground.
Engine: accetable hp range is 28- 80 hp.B-612 is originaly designed for Rotax 503 [50hp].
| Dimensions | Weights | Performance |
| Wing area: 6,8m2 / 70,7sq.ft. | Empty: 175 kg / 375 lb. | Stall: 65 km h-1 / 40 mph |
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Length: 4,8m / 15,5 ft.
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Gross: 300 kg / 662 lb. | Vne: 270 km h -1 / 166 mph |
| Wing span: 6,9 m / 22,3 ft. | Useful load: 130 kg / 286 lb. | Cruise: 200 - 250 km h-1 / 123 - 151 mph |
| Cocpit width: 0,6m / 24 in. | Fuel capacity 30 l / aprox. 7,9 U.S.gal. | Rate of climb: 2 - 9 m s-1 / 387 -1935 fpm |
All performace numbers depend on used engine.
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