TYPE: Single-seat ultralight/kitbuilt.
PROGRAMME: First flight April 1996; development continuing towards FAA FAR Pt 103 certification. Had undergone fundamental redesign by 2000, changing from tractor to pusher propeller and relocating tailboom to low position, complete with tailwheel; by 2003, certification still continuing.
CURRENT VERSIONS: S-17: As described.
S-18: Two-seat; described separately.
CUSTOMERS: 43 sold and 35 completed by July 2003.
COSTS: Kit, with engine: Rotax 447, US$11,200; Rotax 503 DC, US$12,193 (all 2003). Flyaway US$3,000 to US$4,000 extra.
DESIGN FEATURES: Pod and boom fuselage; V-strut-braced wings; quoted building time 150 hours.
FLYING CONTROLS: Conventional and manual.
STRUCTURE: Light alloy fuselage, pre-assembled with all controls in situ; wing has tubular spar. Fuselage is 12.7 cm (5 in) aluminium tube with 4130 welded steel cockpit cage; optional composites nosecone. Dacron skin; spring steel landing gear.
LANDING GEAR: Fixed tailwheel type; tapered spring steel main legs; hand-lever operated brakes on mainwheels.
POWER PLANT: Prototype has one 34.0 kW (45.6 hp) Rotax 503 two-cylinder piston engine driving a three-blade IVO propeller via 2.58:1 reduction gearing. Alternatives include 31.0 kW (41.6 hp) Rotax 447 UL-2V. Fuel capacity 19 litres (5.0 US gallons; 4.2 Imp gallons) standard; 34 litres (9.0 US gallons; 7.5 Imp gallons) optional.
ACCOMMODATION: One person in open cockpit with Lexan windscreen/nosecone; four-point Hooker harness.