| AeroKuhlmann | |
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HW100 - 45000
UAW55 - 105000 RRW100 - 175000 PKRR - 7500 |
AeroKuhlmann Scub Scub Role - 2-seat light aircraft National origin - France Manufacturer - AeroKuhlmann First flight - 5 May 1996 Number built - 17 by mid-1999 The AeroKuhlmann Scub is a single engine, high wing utility aircraft built in France in the 1990s. Design and development The Scub is a high wing light utility aircraft, capable of cargo, medical, mapping, agricultural and surveillance work. It is powered by a single 62.5 kW (83.3 hp) JPX 4TX75A flat four engine and seats two in tandem with dual control. It has a conventional layout, with a straight edged wings carrying 2° of dihedral. The short span ailerons extend to the squared-off tips. The wings are of mixed construction, based on a single 3-ply birch spar with a carbon fibre cap combined with glass fibre ribs. The leading edge is plywood, the rest covered with Dacron. The wings fold for storage. The fuselage of the Scub is a chrome-molybdenum steel tube structure, Dacron covered and flat sided. The tapered, square topped vertical stabilizer has a horn balanced rudder. The starboard elevator carries a trim tab. The Scub has a conventional, fixed undercarriage without wheel fairings. Floats or skis may be fitted instead; the conversion takes about 2 hours. Floats add 50 kg (110 lb) to the empty weight. For agricultural work, Micronair 7000 atomisers are fitted on underwing bars, fed from a bulbous ventral tank. Surveillance cameras can be mounted underwing. The Scub first flew on 5 May 1996. It was certified to JAR-VLA standard in France. In 2000, it was available either as an Ultralight, with maximum take-off weights (MTOW) of 450 kg (992 lb) in Europe or 544 kg (1.200 lb) in USA, or with a MTOW of 598 kg (1,320 lb). Operational history The Scub had its first public outing at the 1997 Paris Airshow and by mid-1999 17 had been built. Several have been used in Madagascar for crop spraying. In mid-2010, 8 were on the European civil registers. Specifications (MTOW, landplane) Data from Jane's All the World's Aircraft 2000/01 General characteristics Capacity: 2 Length: 7.01 m (23 ft 0 in) Wingspan: 10.06 m (33 ft 0 in) Height: 1.83 m (6 ft 0 in) Wing area: 14.77 m2 (159.0 sq ft) Airfoil: NASA L51 0417 modified, supercritical Empty weight: 304 kg (670 lb) Max takeoff weight: 598 kg (1,318 lb) Powerplant: 1 × JPX 4TX75A flat four, 62.5 kW (83.8 hp) Propellers: 2-bladed UTX, wooden Performance Maximum speed: 124 km/h (77 mph, 67 kn) Stall speed: 60 km/h (37 mph, 32 kn) Never exceed speed: 169 km/h (105 mph, 91 kn) Range: 1,005 km (624 mi, 543 nmi) Endurance: 7.0 h Service ceiling: 4,570 m (14,990 ft) Maximum glide ratio: 15:1, unpowered Rate of climb: 4.2 m/s (830 ft/min) |