On 25 April 1988 FFA of Switzerland announced the receipt of a contract from Swissair for eight trainers of advanced design, designated FFA-2000 (now Eurotrainer 2000), to replace the Piaggio P.149s of the airline's flying school, which had been in service for 25 years. The airline has an option on a further four of these trainers. Development began in 1987, with design assistance from the Swiss ALR group (see 1987-88 Jane's). Development has been taken over by FFT, and the first flight was scheduled for April 1991. Certification is expected in March 1992 and delivery of the first aircraft to Swissair shortly afterwards.
Following discontinuation of the Porsche engines, the prototypes and the eight aircraft for Swissair's civil aviation flying school (SLS) will be powered by the Textron Lycoming AEIO-540 flat rated to 200 kW (268 hp) to meet German noise regulations. The aircraft will sustain +6/-3 g and high-stress parts of the glassfibre airframe are reinforced with carbonfibre. A Christen-type fuel and oil system will permit negative-g manoeuvres.

TYPE: Two/four-seat training and touring aircraft, capable of limited aerobatics.

WINGS: Cantilever low-wing monoplane. Horstmann-Quast advanced laminar wing section, with thickness/chord ratio of 16 per cent. Dihedral 6° 30' from roots. Fail-safe structure of composites (mainly glassfibre), including ailerons and Fowler trailing-edge flaps. No tabs.

FUSELAGE: Conventional structure, of same materials as wings.

TAIL UNIT: Conventional structure, built in same way as wings. Fixed incidence tailplane. Trim tab in rudder and each elevator.

LANDING GEAR: Hydraulically retractable tricycle type, with single wheel on each unit. Mainwheels retract inward, nosewheel rearward.

POWER PLANT: One Textron Lycoming AEIO-540-L1B5 flat-six engine, flat rated at 200 kW (268 hp). Christen kit for inverted flying. Fuel capacity 260 litres (68.7 US gallons; 57.2 Imp gallons).

ACCOMMODATION: Seats for two or four persons, in pairs under one-piece forward-hinged canopy. Dual controls and pedal brakes standard. Baggage space aft of seats. Cockpit heated and ventilated.

AVIONICS: From simple VFR to dual control IFR, according to customer's requirements.


  • Wing span: 10.38 m (34 ft 0¾ in)
  • Wing aspect ratio: 7.7
  • Length overall: 8.14 m (26 ft 8½ in)
  • Height overall: 3.20 m (10 ft 6 in)
  • Elevator span: 3.87 m (12 ft 8½ in)
  • Propeller diameter: 2.10 m (6 ft 10¾ in)


  • Wings, gross: 14.00 m² (150.7 sq ft)


  • Basic weight empty: 920 kg (2,028 lb)
  • Max T-O weight: 1,480 kg (3,262 lb)
  • Max aeobatic T-O weight: 1,300 kg (2,866 lb)
  • Max wing loading: 105.7 kg/m² (21,6 lb/sq ft)
  • Max power loading: 7.4 kg/kW (12.17 lb/hp)

PERFORMAMCE (estimated at two-seat trainer T-O weight):

  • Never-exceed speed (VNE): 224 knots (416 km/h; 258 mph)
  • Max level speed at S/L: more than 175 knots (324 km/h; 201 mph)
  • Econ cruising speed (65% power) at S/L: 157 knots (291 km/h; 181 mph)
  • Stalling speed, flaps down: 52 knots (96 km/h; 60 mph)
  • Max rate of climb at S/L: 408 m (1,340 ft)/min
  • Service ceiling: 6,100 m (20,000 ft)
  • T-O to 15 m (50 ft) at 600 m (1,970 ft): 500 m (1,640 ft)
  • Landing from 15 m (50 ft): 490 m (1,610 ft)
  • Endurance, 45 min reserves: 4h
  • g limits: +5/-3 (utility) and +6/-3,5 (aerobatic)