TYPE: Four-seat lightplane.
PROGRAMME: Prototype first flew mid-1967 as extensively redesigned cabin version of veteran Yak-18 trainer; over 700 built at Smolensk Aircraft Plant (SmAZ), including trainer, ambulance, communications and light freight versions; production resumed by Smolensk in 1993 to meet new contracts and one converted to Technoavia SM-94 prototype. Second production run ended in 1996 due to bankruptcy of SmAZ. In 1998, work recommenced on 15 stored, part-built airframes, which being completed with two-piece windscreen, designed for Technoavia SM-94. New aircraft delivered as either SM-94 or distributed in Western Europe (eight reserved) by Richard Goode Aerobatics of White Waltham, UK. Further production now appears to be in hand.
CUSTOMERS: First resumed (1993) deliveries to Luxembourg, Philippines, Russia, Switzerland, Turkey, UAE, UK and USA. Recent deliveries include three to Ulyanovsk Aviation School in June 2001. Production in 2001 reportedly 10 to 12 per year; total of 80 built between 1993 and mid-2001.
COSTS: US$95,000 (1999, Goode-sourced).
DESIGN FEATURES: Adaptation of aerobatic trainer. Conventional cantilever low-wing monoplane; three-section two-spar wings; semi-monocoque fuselage of basically square section; strut- and wire-braced tail surfaces. Airframe life 5,000 hours or 20 years.
Wing section Clark YH, thickness/chord ratio 14.5 per cent at root, 9.3 per cent at tip; dihedral 70 20' on outer panels only.
FLYING CONTROLS: Conventional and manual. Plain flaps and elevator trim.
STRUCTURE: All-metal construction, except for fabric covering on parts of outer wing panels, ailerons and tail surfaces.
LANDING GEAR: Retractable tricycle type; single wheel on each unit; pneumatic retraction, K-141/T-141 mainwheels inward into centre-section, Type 44-1 nosewheel rearward; Hydromash oleo-nitrogen shock-absorbers; castoring nosewheel is non-steerable; Yaroslavl tyres size 500x150 on mainwheels, 400x150 on nosewheel; tyre pressure (all) 2.95 bar (43 lb/sq in); pneumatic plate-type brakes on mainwheels. Minimum ground turning radius 2.52 m (8 ft 3¼ in).
POWER PLANT: One 265 kW (355 hp) VOKBM M-14P air-cooled radial piston engine; optional 294 kW (394 hp) M-14PF in 1999 version; V-530TA-D35 two-blade variable-pitch metal propeller; wingroot fuel tanks, combined capacity 190 litres (50.2 US gallons; 41.8 Imp gallons); gravity fuelling points on wing upper surface. Optional usable fuel capacities of 321 litres (84.7 US gallons; 70.6 Imp gallons), 360 litres (95.3 US gallons; 74.9 Imp gallons) or 614 litres (162 US gallons; 135 Imp gallons) available in 1999 version. Oil capacity 20 litres (5.3 US gallons; 4.4 Imp gallons). Inverted fuel and oil systems optional.
ACCOMMODATION: Cabin of main production version seats four persons in pairs, with forward-hinged jettisonable door each side; rear bench seat removable for freight carrying; ambulance configuration accommodates pilot, stretcher patient and medical attendant; baggage compartment aft of rear seat. Option to increase seating to six has not been pursued. Cabin heated and ventilated.
SYSTEMS: Pneumatic system for landing gear and flaps, operating pressure 49 bar (711 lb/sq in); 36/115 V AC electrical system at 400 Hz, 28.5 V DC and 20NKBN-25 battery for red panel lighting, nav and landing lights, and fintip anti-collision beacon.
AVIONICS: Comms: Baklan-5 UHF radio, intercom.
Instrumentation: ARK-15M radio compass, radio altimeter and flight recorder standard.
Customised avionics available in 1999 version.
EQUIPMENT: Optional smoke system for 1999 version.