US marketing name: Spectrum SA-20 Vista

TYPE: Tandem-seat ultralight/kitbuilt.

PROGRAMME: Design started September 1990; construction of prototype began November 1990; first flight 5 August 1991; construction of first production aircraft started September 1991, first flown 15 August 1993; prototype appeared abroad for first time in Hodkovice, Czech Republic, at European Microlight Championship, August 1993, gaining ninth place; fourth production A-20 won third place at World Microlight Championship, Poznan, Poland, August 1994; seventh production A-20 gained second place at EMC '95, Little Rissington, UK; initial production aircraft was placed first at EMC, Hungary, 2002.

CURRENT VERSIONS: A-20 Vista: Basic aircraft, as described in detail.
A-20R912 Sky Cruiser: Described separately.
A-20S: Variant under development by 1997, with large multichannel radiometer built into its nose for a wide range of ecological survey work. No known manufacture.
A-20SKh: Agricultural (selskokhozyaistvennyi: agricultural) with 59.6 kW (79.9 hp) Rotax 912 UL, three-blade ground-adjustable pitch Ivoprop propeller, sweptback (1° 30') wing, two chemical tanks, each 90 litres (23.8 US gallons; 19.8 Imp gallons) scabbed to fuselage sides, and streamlined spraybar with four or six atomisers. Prototype construction began July 1997; first flight September 1997; no subsequent production reported. A fuller description has been published.
A-20 Vista STOL: With 47.8 kW (64.1 hp) Rotax 582 UL; cruising speed 76 kt (140 km/h; 87 mph).
A-20 Vista SS: Rotax 582 and wing span of 10.02 m (33 ft 4 in); empty weight 222 kg (490 lb); cruising speed 87 kt (185 km/h; 100 mph); range 205 n miles (379 km; 236 miles) or 399 n miles (740 km; 460 miles) with auxiliary fuel.
A-30 Vista Speedster Prototype under test at Sebring, Florida, by early 2002.

CUSTOMERS: First customer delivery August 1993; exports to Czech Republic, Germany, Hungary, Jordan, Poland, Russia, Singapore and United Arab Emirates; last-mentioned acquired seven for Umm-al Qaiwain Flying Club. Total of 36 A-20s of all types produced by mid-2002.

COSTS: US$35,000 complete (2000).

DESIGN FEATURES: High-wing, T-tail configuration, optimised for rapid disassembly for transport by trailer. Tail surfaces mounted on aluminium tube which detaches at joint with the nacelle.
Unswept wing; P-IIIa-15 wing section, thickness/chord ratio 15 per cent; chamfered tips; dihedral 1° 30'; incidence at roots 3° 30', twist 3°.

FLYING CONTROLS: Manual. Single-piece, rod-operated flaperons extend full length of wing trailing-edge; no tabs. Single-piece elevator with protruding, in-flight adjustable tab. Full-height rudder with no tab.

STRUCTURE: Riveted aluminium wing structure; leading-edge D box closed by I-section main spar; stamped wing ribs; bent sheet rear false spar; partially fabric covered. Control surfaces similar to wings. All-composites honeycomb sandwich fuselage pod.

LANDING GEAR: Mainwheels, with speed fairings, on single leaf-spring; steerable tailwheel linked to rudder.

POWER PLANT: One 37.0 kW (49.6 hp) Rotax 503 UL-2V two-stroke piston engine driving a KievProp three-blade, ground-adjustable pitch pusher propeller via 3:1 reduction gearbox. Rotax 462,582 (47.8 kW; 64.1 hp), 618 and 912 engines optional. Fuelling point on starboard side of nacelle. Standard capacity 38 litres (10.0 US gallons; 8.4 Imp gallons); optional 90 litres (23.8 US gallons; 19.8 Imp gallons).

EQUIPMENT: Ballistic recovery parachute.