English name: Stork

TYPE: Utility kitbuilt.

PROGRAMME: Programme started in 1994 when licence acquired from Aeroprogress/ROKS-Aero to produce the T-411 Aist-2; Aist-2 design started November 1992; construction of prototype began April 1993; first flight (marked only 'T-411') 10 November 1993 in standard form; 15 March 1994 with ski landing gear. Khrunichev prototype (RA-01585), with several detail changes, first exhibited at Moscow Air Show 1997. Second prototype reported nearing first flight in January 2002. Initially designated T-411 Wolverine, which name now transferred to T-421. North American promotion (in kit form) taken over by Sherpa Aircraft in 2001 and first two (unassembled) kits for US market were displayed at AirVenture, Oshkosh, in July 2003.
Manufacture intended by RSK 'MiG', whose Voronin plant contracted in March 2000 to build 15 for delivery in 2001, but delivery target slipped to first quarter 2002, with all 15 to be handed over during following six months. However, by June 2002, talks between Khrunichev and RSK 'MiG' still had not reached a satisfactory conclusion, although first aircraft then nearing completion. Manufacture of kits is envisaged. By March 2003, deliveries were stated to be due for completion by end 2003.

CURRENT VERSIONS: T-411: As described.
T-411A: Agricultural version.
T-411P: Floatplane version with twin floats, for operations in seas with wave height up to 0.35 m (1 ft 1¾ in); length overall 10.00 m (32 ft 9¾ in); maximum take-off weight 1,650 kg (3,637 lb); payload 440 kg (970 lb); cruising speed 113 kt (210 km/h; 130 mph); T-O run 315 m (1,033 ft); T-0 to 15 m (50 ft) 475 m (1,558 ft); landing from 15 m (50 ft) 305 m (1,000 ft); landing run 195 m (640 ft); maximum range 607 n miles (1,125 km; 699 miles).
T-411F: As T-411P, but with amphibious floats.
T-411L: Ski-equipped version.
T-411LY: Textron Lycoming TIO-540 powered version.
T-411 Turbo: Walter M 610B turboprop. Incomplete prototype shown in Moscow, August 2001.
T-421: No description.

CUSTOMERS: Orders received from Russian forestry, fisheries and national emergency ministries, Australia, Malaysia and USA from which approximately 70 orders received, including aircraft supplied in kit form.

COSTS: US$130,000 with M-14 engine; US$20,000 more with Lycoming engine (2002).

DESIGN FEATURES: Conventional strut-braced high-wing monoplane. Constant-chord unswept wings with fixed leading-edge slat, slotted ailerons and single-slotted, three-position (0, 20, 40o) trailing-edge flaps; V bracing struts. Rectangular-section fuselage. Unswept tail unit with dorsal fin; constant-chord horizontal tail surfaces. Compared with the Aeroprogress Aist-2, the Khrunichev version has slightly stretched airframe and more roomy cabin; different landing gear and power plant.
Wing section NACA 23011; dihedral 2o from root; incidence 3o 30'.

FLYING CONTROLS: Conventional and manual. Actuation by pushrods and cables; electrically controlled trim tab in each elevator; fixed full-span leading-edge slats; slotted flaps.

STRUCTURE: Fuselage structure of 4130 steel tube covered with Dacron synthetic fabric and aluminium alloys. Two-spar, constant-chord wings; metal skin on leading-edge and over fuel tanks at root, Dacron covered between spars. Metal tail surfaces, Dacron covered.

LANDING GEAR: Non-retractable tailwheel type; single wheel on each unit, with fairings on mainwheels. Arched cantilever tubular spring main legs. Self-centring castoring tailwheel. Mainwheel tyres 600x180; tailwheel 310x135. Brakes on mainwheels.

POWER PLANT: One 268 kW (360 hp) VOKBM M-14X nine-cylinder radial with Muhlbauer MTV-9 three-blade variable-pitch propeller, or 261 kW (350 hp) Textron Lycoming TIO-540 flat-six with Hartzell three-blade variable-pitch propeller. Two main and two auxiliary fuel tanks in wingroots, total capacity 340 litres (89.8 US gallons; 74.8 Imp gallons); gravity fuelling. Oil capacity 22.0 litres (5.8 US gallons; 4.8 Imp gallons).

ACCOMMODATION: Pilot and three or four passengers, on side-by-side front seats and rear bench seat; starboard front seat and rear bench removable, or bench seat foldable, for carrying equivalent freight; convertible into ambulance for one stretcher patient, one seated casualty and medical attendant in addition to pilot. Dual controls standard. Baggage/cargo compartment aft of rear seats, with large upward-opening door on port side, used also for loading freight or stretcher. Forward-hinged jettisonable door each side of cabin. Ventilation and heating standard.

SYSTEMS: Pneumatic system for starting engine and operating mainwheel brakes; pressure 50 bar (725 lb/sq in). Electrical system includes GSR-3000M engine-driven 27 V DC generator and 28 Ah 12CAM-28 battery.

AVIONICS: Russian or Western (Honeywell) avionics available, including GPS. Optional autopilot.


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