The AeroKuhlmann Scub is a single engine, high wing utility aircraft built in France in the 1990s.

Scub
Role 2-seat light aircraft
National origin France
Manufacturer AeroKuhlmann
First flight 5 May 1996
Number built 17 by mid-1999.

Design and development edit

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.[1]

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.[1]

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).[1]

Operational history edit

The Scub had its first public outing at the 1997 Paris Airshow[2] and by mid-1999 17 had been built.[1] Several have been used in Madagascar for crop spraying.[2] In mid-2010, 8 were on the European civil registers.[3]

Specifications (MTOW, landplane) edit

Data from Jane's All the World's Aircraft 2000/01[1]

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)

References edit

  1. ^ a b c d e Jackson, Paul (2000). Jane's All the World's Aircraft 2000-01. London: Jane's Information Group. p. 111. ISBN 0-7106-2011-X.
  2. ^ a b Simpson, Rod (2001). Airlife's World Aircraft. Shrewsbury: Airlife Publishing Ltd. p. 14. ISBN 1-84037-115-3.
  3. ^ Partington, Dave (2010). European registers handbook 2010. Air Britain (Historians) Ltd. ISBN 978-0-85130-425-0.