AVIAPROM M-12

TYPE: Three-seat lightplane; three-seat kitbuilt.

PROGRAMME: Kasatik M-12 designed by Feniks OKB (Phoenix Design Bureau; a division of Promax) and built by Aviacor plant at Samara; exhibited at Moscow in 1995, powered by two 25.7 kW (34.5 hp) Vikhr 30 piston engines. Intermittent promotion (interrupted by flight test crash on 14 October 1997) continued for further decade within CIS until Western launch at Paris Air Show in June 2005. Certification under way to FAR/EASA 23, day VFR.

CUSTOMERS: Several sales in CIS and one in Germany prior to 2005. US marketing began in July 2006, with exhibition at AirVenture, Oshkosh.

COSTS: USD96,280 flyaway with Jabiru engine; kit USD53,380, less engines and instruments (2006).

DESIGN FEATURES: High, constant-chord wing with single bracing strut each side and two pusher piston engines close inboard; cockpit pod with narrow rear fuselage and low-mounted tailplane braced to sweptback fin by single strut each side. Rudder trailing-edge sweptback from base to tip; earlier versions had trapezoidal vertical tail. Wings foldable for storage and transport. Service life 4,000 landings, 2,000 hours or 10 years. Mainplane dihedral 1° 30'; no sweepback. Tailplane: no incidence or dihedral. Fin leading-edge sweepback 35°.

FLYING CONTROLS: Conventional and manual. Mass-balanced ailerons. Balanced rudder and elevator, latter with flight-adjustable trim tab, port. Slotted flaps.

STRUCTURE: Riveted aluminium monocoque with bolted joints; composites for some non-load-bearing items; welded steel engine mounting.

LANDING GEAR: Tricycle type; fixed. Fuselage-mounted spring aluminum cantilever mainwheel legs with 6.00-6 tyres and cable brakes (alternatively 360x135 or 400x150 tyres). Steerable nosewheel 300x12.5. Composites speed fairings on all wheels. Optional floats or skis. Turning circle 3.1 m (11 ft) about nosewheel; 2.9 m (10 ft) about mainwheel; taxiway width for U-turn 10 m (33 ft).

POWER PLANT: Two four-stroke, flat-four piston engines driving two-blade, variable-pitch pusher propellers; 59.6 kW (79.9 hp) Rotax 914 or 59.7 kW (80 hp) Jabiru 2200. Optionally, two-stroke 48.0 kW (64.4 hp) two-cylinder Rotax 582 driving three-blade, fixed-pitch propellers. Fuel capacity 150 litres (39.6 US gallons; 33.0 Imp gallons). Two pneumatic fuel pumps.

ACCOMMODATION: Pilot (front) and two passengers (rear). Baggage compartment behind seats. Forward-hinged door each side. Optional second set of controls for port rear seat. Cockpit heated and ventilated.

SYSTEMS: Electric system 12 V and 24 V provided by engine-mounted generators and 55 Ah motorcar battery, plus 9 Ah auxiliary battery.

AVIONICS: Comms: Garmin GNS 400 nav/com and GTX 320 transponder.

EQUIPMENT: Optional ballistic recovery parachute occupying part of baggage compartment.

DIMENSIONS, EXTERNAL:

  • Wing span: 10.20 m (33 ft 5½ in)
  • Wing chord, constant: 1.20 m (3 ft 11¼ in)
  • Wing aspect ratio: 8.5
  • Width, wings folded: 1.95 m (6 ft 4¾ in)
  • Length overall: 6.80 m (22 ft 3¾ in)
  • Height overall: 2.30 m (7 ft 6½ in)
  • Tailplane span: 3.00 m (9 ft 10 in)
  • Wheel track: 1.60 m (5 ft 3 in)
  • Wheelbase: 2.05 m (6 ft 8¾ in)
  • Propeller diameter: Rotax 582: 1.60 m (5 ft 3 in)
    • Jabiru 2200, Rotax 912: 1.55 m (5 ft 1 in)

DIMENSIONS, INTERNAL:

  • Cockpit: Length: 2.76 m (9 ft 0½ in)
    • Max width: 1.15 m (3 ft 9¼ in)
    • Max height: 1.14 m (3 ft 9 in)

AREAS:

  • Wings, gross: 12.20 m² (131.3 sq ft)

WEIGHTS AND LOADINGS:

  • Weight empty: Rotax 912: 474 kg (1,045 lb)
    • Jabiru 2200: 448 kg (988 lb)
  • Max baggage weight: normal: 40 kg (88 lb)
    • with BRS parachute: 24 kg (53 lb)
  • Max payload: 280 kg (617 lb)
  • Max fuel weight: 108 kg (238 lb)
  • Max T-O weight: Rotax 912: 860 kg (1,895 lb)
    • Jabiru 2200: 848 kg (1,869 lb)
  • Max zero-fuel weight, Jabiru 2200: 750 kg (1,653 lb)
  • Max wing loading: Rotax 912: 70.5 kg/m² (14,44 lb/sq ft)
    • Jabiru 2200: 69.5 kg/m² (14,24 lb/sq ft)
  • Max power loading: Rotax 912: 7.22 kg/kW (11.86 lb/hp)
    • Jabiru 2200: 7.11 kg/kW (11.68 lb/hp)

PERFORMANCE:

  • Max level speed: Rotax 912: 127 kt (235 km/h; 146 mph)
    • Jabiru 2200: 124 kt (230 km/h; 143 mph)
  • Normal cruising speed: Rotax 912: 103 kt (190 km/h; 118 mph)
    • Jabiru 2200: 97 kt (180 km/h; 112 mph)
  • Max rate of climb at S/L: 480 m (1,575 ft)/min
  • Service ceiling: 4,000 m (13,120 ft)
  • Range with max payload: Rotax 912: 637 n miles (1,180 km; 733 miles)
    • Jabiru 2200: 518 n miles (960 km; 596 miles)
  • Endurance: Rotax 912: 6 h 20 min

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

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