As well as being slightly larger overall than the Rutan VariEze, the Speed Canard differs in a number of important details, as noted in the 1987-88 Jane's. Wings and other GFRP/CFRP components, manufactured initially by Glaser-Dirks, are now produced by FFT.
Construction of the first prototype (D-EEEX, c/n A-1) began in late 1978, and this aircraft first flew on 2 December 1980. Initial test flights revealed the need for a number of design changes before it could be approved for series production. Of these, the principal one was the adoption of a new Eppler aerofoil section and 5.9° anhedral on the outer wing sections. A new 'first' flight with this modified wing was made by D-EEEX on 10 July 1981. A second airframe was completed for static testing, followed by a second flying prototype (D-EEEW, c/n A-3), which made its initial flight on 17 April 1983 and enabled the Speed Canard to receive German LBA type certification on 30 September that year.
Series production began with the fourth aircraft (D-EELZ, c/n S-4), and 20 examples of this initial version were built by September 1985 for customers in Germany (17), Switzerland (2), and Belgium (1). As built with the standard O-235 engine, they are designated SC-01; some examples have been retrofitted with the more powerful O-320 engine, in which form they are known as the SC 01-160 and were described in Jane's 1987-88.
Beginning with c/n S-24, current production models are designated SC 01 B (O-235 engine) and SC 01 B-160 (O-320 engine). These versions, which first flew in the Summer of 1985 and received LBA certification on 26 March 1986, have winglets of increased area, plus other minor improvements. A number of earlier Speed Canards have also been modified to the current B/B-160 standard. A GT version of the SC 01 B-160 was introduced in 1987; this has VFR avionics as standard.
The Speed Canard is certificated in France, Germany, Japan, Switzerland, Scandinavia, UK, USA and the Benelux countries. More than 50 B/B-160s have been ordered.

TYPE: Two-seat sporting and surveillance aircraft.

WINGS: Cantilever mid-wing monoplane. Short-span centre-section strakes, sweptback approx 60° on leading-edges, without anhedral or dihedral. Main wings have an Eppler E793 aerofoil section, with 15.6 per cent thickness/chord ratio, anhedral angle of 5° 54', and 22° sweepback at quarter-chord. Single-spar structure of GFRP and CFRP, without ribs. Each wingtip is upswept at nearly 90° to form a slightly outward canted NASA type winglet with inset rudder. Centrally located aileron in each wing trailing-edge. No flaps. No aileron or rudder tabs. Main wings are detachable for transportation and storage. Narrow-chord cantilever foreplane, of Eppler E1231 aerofoil section, is mounted high on nose and has a balanced elevator, with fixed tab near inboard end, on each trailing-edge. Construction (GFRP and CFRP) similar to that of wings.

FUSELAGE: Non-pressurised oval-section nacelle type, of GFRP composites construction.

LANDING GEAR: Tricycle type, with fixed main units and electrically retractable nosewheel which is carried on a carbon/Kevlar strut moulded to conform to the outside contour of the fuselage, eliminating need for a fairing door. Main units, carried on cantilever self-sprung carbon/Kevlar struts, are fitted with Cleveland wheels (tyre size 5.00-5), Cleveland disc brakes, and speed fairings. The Scott nosewheel, which retracts rearward, is fitted with a size 10 x 3.5-4 tyre. Nosewheel strut is hinged to allow aircraft to be parked in a kneeling position with only the wheel exposed.

POWER PLANT (SC 01 B): One 86.5 kW (116 hp) Textron Lycoming O-235-P2A flat-four engine, mounted in the rear fuselage and driving a Hoffmann HO-V113B-L/LD150+2A three (composites)-blade constant-speed pusher propeller. Fuel in two integral tanks (one in each wing centre-section strake) with combined capacity of 160 litres (42.3 US gallons; 35.2 Imp gallons). Oil capacity 6 litres (1.58 US gallons; 1.32 Imp gallons).

POWER PLANT (SC 01 B-160): One 119 kW (160 hp) Textron Lycoming O-320-D1A flat-four engine, driving an MT-Propeller (Mühlbauer) MTV-6-C/LD 152-07 three-blade constant-speed propeller. Fuel capacity as for lower powered version. Oil capacity 8 litres (2.11 US gallons; 1.76 Imp gallons).

ACCOMMODATION: Pilot and passenger in tandem, on semi-reclining seats in individual cockpits. Side-stick controls. Separate one-piece moulded canopies, both opening sideways to starboard. Space for 15 kg (33 lb) of baggage aft of rear seat. Both cockpits heated and ventilated.

SYSTEMS: Alternator to provide power for nosewheel extension/retraction.

AVIONICS: To customer's requirements except for GT, which has VFR instrumentation as standard. Can be equipped to full IFR standard, including autopilot, two com/nav, ILS, ADF, artificial horizon, turn and bank indicator and heading gyro.

DIMENSIONS, EXTERNAL:

  • Wing span: 7.77 m (25 ft 6 in)
  • Foreplane span: 3.60 m (11 ft 9¾ in)
  • Foreplane chord, constant: 0.34 m (1 ft 1¾ in)
  • Wing aspect ratio: 7.7
  • Foreplane aspect ratio: 10.6
  • Length overall: 4.70 m (15 ft 5 in)
  • Fuselage: Length: 4.40 m (14 ft 5¼ in)
    • Max width: 0.74 m (2 ft 5 in)
    • Max depth: 1.06 m (3 ft 5¾ in)
  • Height overall: 1.81 m (5 ft 11¼ in)
  • Wheel track: 1.66 m (5 ft 5¼ in)
  • Wheelbase: 2.47 m (8 ft 1¼ in)
  • Propeller diameter: 1.52 m (5 ft 0 in)
  • Propeller ground clearance: 0.31 m (1 ft 0¼ in)

DIMENSIONS, INTERNAL:

  • Cockpits:
    • Max combined length: 2.80 m (9 ft 2¼ in)
    • Max width: 0.64 m (2 ft 1¼ in)
    • Max height: 0.99 m (3 ft 3 in)

AREAS:

  • Wings, gross: 7.84 m² (84.39 sq ft)
  • Foreplane, gross: 1.22 m² (13.13 sq ft)
  • Ailerons (total): 0.376 m² (4.05 sq ft)
  • Winglets (total): 2.20 m² (23.68 sq ft)
  • Rudders (total): 0.168 m² (1.81 sq ft)
  • Elevators (total, incl tabs): 0.33 m² (3.55 sq ft)

WEIGHTS AND LOADINGS (A: with O-235, B: with O-320 engine):

  • Weight empty: A: 420 kg (926 lb)
    • B: 440 kg (970 lb)
  • Max fuel: A, B: 115 kg (253 lb)
  • Max payload with 100 litres (26.4 US gallons; 22 Imp gallons) fuel: A: 188 kg (414,5 lb)
    • B: 204 kg (450 lb)
  • Max T-O weight: A: 680 kg (1,499 lb)
    • B: 715 kg (1,576 lb)
  • Max landing weight: A, B: 680 kg (1,499 lb)
  • Max wing loading: A: 75.05 kg/m² (15.38 lb/sq ft)
    • B: 75.98 kg/m² (15.5 lb/sq ft)
  • Max power loading: A: 7.86 kg/kW (12.92 lb/hp)
    • B: 6.01 kg/kW (9.85 lb/hp)

PERFORMAMCE (at max T-O weight, A and B as above):

  • Never-exceed speed (VNE): A, B: 197 knots (365 km/h; 226 mph) IAS
  • Max level speed at S/L:
    • A: 146 knots (270 km/h; 168 mph)
    • B: 159 knots (295 km/h; 183 mph)
  • Max cruising speed, 75% power:
    • A at 1,830 m (6,000 ft) 143 knots (265 km/h; 165 mph)
    • B at 2,135 m (7,000 ft) 154 knots (285 km/h; 177 mph) IAS
  • Econ cruising speed, 65% power:
    • A at 3,050 m (10,000 ft) 138 knots (257 km/h; 160 mph)
    • B at 3,350 m (11,000 ft) 148 knots (275 km/h; 171 mph)
  • Stalling speed: A, B: 57 knots (105 km/h; 66 mph) IAS
  • Max rate of climb at S/L: A: 300 m (985 ft)/min
    • B: 396 m (1,300 ft)/min
  • Service ceiling: A: 4,420 m (14,500 ft)
    • B: 5.640 m (18.500 ft)
  • T-O run: A: 450 m (1,475 ft)
    • B: 350 m (1,150 ft)
  • T-O to 15 m (50 ft): A: 700 m (2,300 ft)
    • B: 540 m (1,770 ft)
  • Landing from 15 m (50 ft): A, B: 700 m (2,300 ft)
  • Landing run: A, B: 300 m (985 ft)
  • Range with max fuel, no reserves:
    • 55% power: A: 1,025 nm (1,900 km; 1,180 miles)
    • B: 890 nm (1,650 km; 1,025 miles)
  • Range at S/L with max fuel, 45 min reserves:
    • 75% power: A: 728 nm (1,350 km; 839 miles)
    • B: 553 nm (1,025 km; 637 miles)
    • 45% power: A: 1,011 nm (l,875 km; 1,165 miles)
    • B: 715 nm (1,325 km; 823 miles)
  • g limits: A: +4.4/-2.2
    • B: +3.8/-2.2