TYPE: Side-by-side lightplane/kitbuilt.

PROGRAMME: Prototype (FLARF-02647) first flew (in floatplane configuration) 22 June 1998; public debut at Gelendzhik 98 seaplane show, and in landplane version at MAKS, Moscow, August 1999; evaluated during 1999 and 2000 by AvtoZavod Flying Club in Togliatti. Seventh production airframe, under construction in mid-2001, is first with Rotax 914 engine.

CURRENT VERSIONS: A-27: Baseline version with Hirth engine.
A-27M Advantage: Version with 73.5 kW (98.6 hp) Rotax 912 ULS engine driving a Kiev ground-adjustable pitch propeller or 84.6 kW (113.4 hp) Rotax 914 ULS, driving a variable-pitch propeller. Several minor design changes, including more rounded forward lower fuselage surfaces, but description generally as for A-27, except where indicated.

COSTS: Kit US$14,000 excluding instruments (US$700), landing gear and Rotax 912 engine (US$14,000). Ex-works, complete, with wheels, US$35,500 (1999). Wheel landing gear US$1,000; skis US$250 to US$350; floats US$1,200 and US$1,650.

DESIGN FEATURES: Braced, high-wing monoplane with single main and two jury struts each side. Sweptback fin and rudder; unswept wings and horizontal tail. Meets JAR-VLA certification requirements.

FLYING CONTROLS: Manual. Ailerons, rudder and all-moving tailplane with anti-balance tab. Flaps. A-27M has fixed tailplane with elevators, and ailerons with external mass balances.

STRUCTURE: Tube metal fuselage with composites skin.

LANDING GEAR: Tricycle type; fixed. Cantilever, metal mainwheel legs; telescopic, leaf-sprung nosewheel leg. Mainwheel size 400x150; nosewheel size 300x125. Optional floats or skis.

POWER PLANT (A-27): One 70.8 kW (95 hp) Hirth F30 flat-four driving a four-blade, ground-adjustable pitch propeller. Fuel capacity: 80 litres (21.1 US gallons; 17.6 Imp gallons); (A-27M) 100 litres (26.4 US gallons; 22.0 Imp gallons).

ACCOMMODATION: Two persons, side by side; forward-hinged door each side. Luggage space behind seats.