AMS CARAT A

TYPE: Single-seat motor glider ultralight.

PROGRAMME: First flown 16 December 1997: flight testing carried out during 1998. Initial production aircraft displayed at Aero '99, Friedrichshafen, in April 1999 under name of Technoflug TFK-2 Carat. Folding propeller certified 7 November 2000; certified by LBA 15 July 2001. Promotion and marketing transferred to AMS, which displayed fourth aircraft at Aero '03, Friedrichshafen, April 2003.

CUSTOMERS: Six built by 1 January 2004, including exports to Germany, Switzerland and US (13 aircraft by 19 September 2006). Total 28 built by April 2005.

COSTS: USD69,635 (2001) without avionics.

DESIGN FEATURES: Low wing of 21.3 aspect ratio; optional winglets; T tail. Uses wings and horizontal tail (but not water tank) of Schempp-Hirth Discus sailplane, with main spar passing under pilot's knees; wings and tailplane can be detached for storage and aircraft will fit into sailplane trailer. Optional winglets.

FLYING CONTROLS: Conventional and manual. Schempp-Hirth airbrakes on upper wing surfaces and ‘turbulators’ below.

STRUCTURE: Generally of glass fibre and carbon fibre composites. Wings have PVC foam cores.

LANDING GEAR: Tailwheel type; retractable. Mainwheels, size 4.00-4 in, retract inwards and forwards electrohydraulically with manual override; fixed steerable 210x65 mm tailwheel. Hydraulic disc brakes. Parking brake.

POWER PLANT: One 1,800 cc (109.8 cu in) Sauer E1S conversion of Volkswagen four-stroke, air-cooled motorcar engine, producing 40 kW (53.6 hp) at max continuous power, driving a 1.40 m (4 ft 7 in) Technoflug KS-F3-1A/140-1 fixed-pitch propeller, blades of which are held forward by gas damping springs located under the spinner when not turning. Other planned engines include 59.6 kW (79.9 hp) Rotax 912. Fuel capacity 53 litres (14.0 US gallons; 11.7 Imp gallons) in single fuel tank situated between cockpit and engine.

SYSTEMS: Electric starter and generator; 12 V 16 Ah battery. Electric fuel pump.

AVIONICS: Suggested package includes ATR720A radio, Honeywell transponder and Filser DX50FAI GPS.

DIMENSIONS, EXTERNAL:

  • Wing span: 15.00 m (49 ft 2½ in)
  • Length overall: 6.21 m (20 ft 4½ in)

DIMENSIONS, INTERNAL:

  • Baggage compartment volume: 0.1 m³ (3.53 cu ft)

AREAS:

  • Wings, gross: 10.58 m² (113.9 sq ft)

WEIGHTS AND LOADINGS:

  • Weight empty: 325 kg (717 lb)
  • Max baggage weight: 145 kg (320 lb)
  • Max T-O weight: 470 kg (1,036 lb)

PERFORMANCE, POWERED:

  • Never-exceed speed (VNE): 135 kt (250 km/h; 155 mph)
  • Normal cruising speed at 75% power: 116 kt (214 km/h; 133 mph)
  • Stalling speed: 44 kt (80 km/h; 50 mph)
  • Max rate of climb at S/L: 210 m (689 ft)/min
  • T-O run: 226 m (741 ft)
  • Landing run: 137 m (450 ft)
  • Range with max fuel, 30 min reserves: 554 n miles (1,026 km; 637 miles)
  • g limits: +5.3/-2.65

PERFORMANCE, UNPOWERED:

  • Stalling speed: 44 kt (80 km/h; 50 mph)
  • Best glide ratio: 35
  • Min rate of sink: 0.75 m (2.46 ft)/s