TYPE: Side-by-side kitbuilt.

PROGRAMME: Design started by Aeroplastika June 1988; construction of prototype LAK-XE (LY-XMH) begun by Avia Baltika in January 1990; first flight 2 August 1992 with 50.7 kW (68 hp) Limbach L 1700 engine; prototype displayed at Moscow Air Show 1993; later uprated with 65 kW (87 hp) Limbach L 2400; horn balance added to rudder; three (one XE, two XA) completed by January 1996; first customer delivery (second XA prototype) May 1995; Avia Baltika pursued ground and flight test programme for JAR-VLA certification, and intended to produce kits and/or complete aircraft. Programme lapsed in late 1990s; revived in 2004 but as low priority.

CURRENT VERSIONS: LAK-XA (American): Continental IO-240 engine, although second LAK-X fitted with PZL-Franklin 4A-235B3 engine to US order.
LAK-XE (European): With choice of three engines, each of less than 74.6 kW (100 hp).

CUSTOMERS: Six reportedly built by Avia Baltika, of which two to USA (currently N8023J and N17EJ).

DESIGN FEATURES: Objectives were short field capability, high L/D range, good fuel economy and cabin comfort. Mid-mounted high-aspect ratio wing; laminar flow NACA 64 series aerofoil, thickness 15 per cent at root, 12 per cent at tip, with 6° dihedral, 4° incidence and 2° twist; fuselage of oval cross-section. Wings detachable for storage.

FLYING CONTROLS: Conventional and manual. Elevators and ailerons actuated by rods/levers, rudder by cables; electrically actuated flaps, maximum deflection 3° up at high cruising speed, 40° down for landing; aileron/flap mixer deflects ailerons 10° down with maximum flap deflection; electrically actuated elevator trim.

STRUCTURE: Wet layup epoxy/glass fibre/foam core composites basic airframe; fuselage moulded in left/right halves with six composites bulkheads and vertical fin webs and ribs; wing moulded in upper/lower shells with root rib. I-beam spar and rear shearweb; tailplane similar.

LANDING GEAR: Tricycle type; fixed. Fuselage-mounted, cantilever self-sprung legs of high-temperature prepreg epoxy/unidirectional glass fibre composites construction; single wheel, with fairing, on each unit; size 115 mm on mainwheels, 100 mm on nosewheel; tyre size 5.00-5 on mainwheels, 300 x 125 mm on steerable nosewheel (±180°); pressures 3.43 bars (50 lb/sq in) on mainwheels, 2.94 bars (43 lb/sq in) on nosewheel; hydraulic disc brakes.

POWER PLANT: LAK-XA: One 93.2 kW (125 hp) Teledyne Continental IO-240-B engine driving a Warp Drive ground-adjustable pitch propeller. Fuel capacity 85 litres (22.4 US gallons; 18.7 Imp gallons).
LAK-XE: One 69.4 kW (93 hp) Limbach L 2400 engine driving a Mühlbauer MTV-1 two-blade constant-speed (electric) composites propeller. Fuel in two integral wing tanks each with filter port; combined capacity 110 litres (29 US gallons; 24.2 Imp gallons) of which 100 litres (26.4 US gallons; 22 Imp gallons) are usable.

ACCOMMODATION: Two seats side by side under single-piece forward-hinged bubble canopy; baggage compartment behind seats, capacity 30 kg (66 lb); accommodation is heated and ventilated.

SYSTEMS: Electrical system powered by 12 V engine-driven alternator; 12 V 45 Ah battery.

Data below apply to both versions except where noted:

DIMENSIONS, EXTERNAL:

• Wing span: 10.68 m (35 ft 0½ in)
• Wing chord: at root: 1.50 m (4 ft 11 in)
• at tip: 0.80 m (2 ft 7½ in)
• Wing aspect ratio: 11.3
• Length overall: XA: 7.00 m (22 ft 11½ in)
• XE: 6.95 m (22 ft 9½ in)
• Height overall: 2.20 m (7 ft 2½ in)
• Tailplane span: 3.30 m (10 ft 10 in)
• Wheel track: 2.10 m (6 ft 10¾ in)
• Wheelbase: 1.55 m (5 ft 1 in)

DIMENSIONS, INTERNAL:

• Cabin: Length: 1.40 m (4 ft 7 in)
• Max width (incl wingroot armrests): 1.10 m (3 ft 7¼ in)
• Max height: 1.10 m (3 ft 7¼ in)
• Baggage compartment volume: approx 0.50 m³ (17.7 cu ft)

AREAS:

• Wings, gross: 12.05 m² (129.71 sq ft)
• Ailerons (total): 1.10 m² (11.84 sq ft)
• Trailing-edge flaps (total): 1.04 m² (11.19 sq ft)
• Fin: 1.48 m² (15.93 sq ft)
• Rudder: 0.71 m² (7.64 sq ft)
• Tailplane: 2.40 m² (25.83 sq ft)
• Elevators (total): 0.86 m² (9.26 sq ft)

WEIGHTS AND LOADINGS:

• Weight empty, equipped: XA: 460 kg (1,014 lb)
• XE: 400 kg (882 lb)
• Max T-O weight: XA: 750 kg (1,653 lb)
• XE: 630 kg (1,433 lb)
• Max wing loading: XA: 62.2 kg/m² (12.75 lb/sq ft)
• XE: 53.9 kg/m² (11.05 lb/sq ft)
• Max power loading: XA: 8.05 kg/kW (13.22 lb/hp)
• XE: 9.38 kg/kW (15.41 lb/hp)

PERFORMANCE:

• Max level speed at S/L:
• XA: 135 kt (250 km/h; 155 mph)
• XE: 108 kt (200 km/h; 124 mph)
• Max cruising speed: XA: 118 kt (220 km/h; 136 mph)
• XE: 97 kt (180 km/h; 111 mph)
• Econ cruising speed: XA: 108 kt (200 km/h; 124 mph)
• XE: 86 kt (160 km/h; 99 mph)
• Stalling speed:
• flaps up: XA: 51 kt (95 km/h; 59 mph)
•   XE: 46 kt (85 km/h; 53 mph)
• flaps down: XA: 44 kt (82 km/h; 51 mph)
•   XE: 40 kt (75 km/h; 47 mph)
• Max rate of climb at S/L: XA: 300 m (984 ft)/min
• XE: 240 m (787 ft)/min
• Service ceiling: XA, XE: 2,000 m (6,560 ft)
• T-O run: XA, XE: 150 m (495 ft)
• Landing run: XA: 150 m (495 ft)
• XE: 100 m (330 ft)
• Range with max payload and max fuel: XA, XE: 459 n miles (850 km; 528 miles)
• g limits: XA: +4/-2

The article appears in the following publication:
Jane's All the World's Aircraft 2007-2008. Jane's Information Group Ltd. 2007. ISBN: 0-7106-2792-0