NOIN CHOUCAS

English name: Jackdaw

TYPE: Side-by-side ultralight kitbuilt.

PROGRAMME: Design started 1994 by Claude Noin; construction of prototype started 1995; first flight February 1996; construction of production prototype started 1996. Marketed as basic kit for advanced builders, quoted build time 1,200 hours. A special version for physically handicapped pilots is to be launched, if there is sufficient demand.

CUSTOMERS: One flying and one under construction by January 2003.

COSTS: Kit (glass fibre) €7,738, (carbon fibre) €8,756 (2003).

DESIGN FEATURES: Tail-less design, stated to be stallproof and spinproof; design aimed at meeting ultralight category certification requirements while matching performance of modern gliders and conventional three-axis ultralight aircraft. Dihedral 4°; zero twist.

FLYING CONTROLS: Unconventional flying wing; pitch control by elevators in inboard wing trailing-edge; ailerons outboard; large rudder. Trim tabs on elevators; spoilers/airbrakes on upper surface of wing.

STRUCTURE: Standard fuselage moulded in half-shells of carbon fibre/epoxy; glass fibre/epoxy fuselage available at lower cost for advanced builders, but with weight penalty; composites wing structure with carbon fibre main spar, glass fibre/epoxy-stiffened Styrofoam ribs and birch plywood D-section leading-edge, covered with heat-shrink Dacron; moulded carbon fibre/epoxy ailerons; Lexan/polycarbonate canopy with carbon fibre frame.

LANDING GEAR: Tailwheel type, fixed; streamline fairings on main legs and wheels; drum brakes.

POWER PLANT: One 37.0 kW (49.6 hp) Rotax 503 UL-2V with 2.58:1 reduction gear driving a two-blade ground-adjustable DUC 20 carbon fibre propeller. Fuel capacity 36 litres (9.5 US gallons; 7.9 Imp gallons), of which 35 litres (9.25 US gallons; 7.7 Imp gallons) are usable.

ACCOMMODATION: Two, side by side beneath one-piece upward-hinging canopy; baggage shelf to rear of seats.

SYSTEMS: 14 V DC alternator provides electrical power.

AVIONICS (factory-built aircraft): Comms: VHF comm and intercom.
Instrumentation: ASI, altimeter, variometer, slip indicator, compass, tachometer, fuel gauge, chronometer, CHT and EGT gauges and voltmeter.

EQUIPMENT: BRS 5 ballistic parachute recovery system optional.

DIMENSIONS, EXTERNAL:

  • Wing span: 14.35 m (47 ft 1 in)
  • Length overall: 5.35 m (17 ft 6½ in)
  • Height overall: 1.95 m (6 ft 4¾ in)
  • Propeller diameter: 1.60 m (5 ft 3 in)

DIMENSIONS, INTERNAL:

  • Cabin max width: 0.97 m (3 ft 2 in)

AREAS:

  • Wings, gross: 21.30 m² (229.3 sq ft)

WEIGHTS AND LOADINGS:

  • Weight empty: 260-290 kg (573-639 lb)
  • Max T-O weight:
    • FAI ultralight certification: 450 kg (992 lb)
    • motor glider certification: 510 kg (1,124 lb)

PERFORMANCE, POWERED:

  • Max level speed: 97 kt (180 km/h; 111 mph)
  • Cruising speed at 75% power: 70 kt (130 km/h; 81 mph)
  • Stalling speed: 33 kt (60 km/h; 38 mph)
  • Max rate of climb at S/L: 180 m (590 ft)/min
  • T-O run: 100 m (330 ft)
  • Landing run: 150 m (495 ft)
  • Range at 75% power, no reserves: 175 n miles (325 km; 201 miles)

PERFORMANCE, UNPOWERED:

  • Best glide ratio: 23
  • Min rate of sink: less than 1.00 m (3.28 ft)/s

The article appears in the following publication:
Jane's All the World's Aircraft 2004-2005. Jane's Information Group Ltd. 2004. ISBN: 0-7106-2614-2

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