KHRUNICHEV T-415 SNEGIR

English name: Bullfinch

TYPE: Six-seat utility transport.

PROGRAMME: Design started (by Aeroprogress/ROKS-Aero) in 1993; prototype construction began 1994; design revised 1998; first flight (RA-01522) 15 May 1999. No further information received; production status unclear.

DESIGN FEATURES: Conventional strut-braced high-wing monoplane. Constant-chord unswept wings; V bracing struts. Rectangular section fuselage. Unswept tail unit with long dorsal fin and horn-balanced elevators and rudder.

FLYING CONTROLS: Conventional and manual, by pushrods and cables; slotted ailerons; electrically actuated single-slotted flaps; electrically actuated trim tab in each elevator. Dual controls standard.

STRUCTURE: Two-spar wing metal skinning around wingroot fuel tanks, remainder covered with Stits Poly-Fiber synthetic fabric. Welded tube truss fuselage, covered with metal sheet and synthetic fabric. Metal tail surfaces, fabric covered.

LANDING GEAR: Tailwheel type; fixed. Single wheel on each unit, with fairings optional on mainwheels. Spring-type tailwheel unit with castoring tailwheel. Mainwheel tyre size 700x260; tailwheel 300x135. Brakes on mainwheels. Ski- and float-equipped versions under development in 2001.

POWER PLANT: One 265 kW (355 hp) VOKBM M-14P nine-cylinder radial driving an MT-Propeller MTV-9 three-blade, variable-pitch (hydraulic) propeller. Detailed description applies to this variant. Version with 559.3 kW (750 shp) Walter M 601 turboprop under development in 2001; future provision for versions with 224 kW (300 hp) Textron Lycoming IO-340 flat-six or 336 kW (450 shp) Rolls-Royce 250-B17F turboprop, each driving a Hartzell three-blade, constant-speed propeller. Fuel contained in four tanks in wingroots, each with filler port.

ACCOMMODATION: Pilot and up to five passengers; four passenger seats in two rows with provision for fifth passenger alongside pilot. Forward-hinged fully glazed door on each side, with large passenger/cargo door on port side of cabin at rear.

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 12SAM-28 battery.

AVIONICS: VFR avionics standard, IFR optional.
Flight: Includes ARK-25 ADF, AGB-96B gyro horizon and GPS.

DIMENSIONS, EXTERNAL:

  • Wing span: 12.94 m (42 ft 5½ in)
  • Wing chord, constant: 2.00 m (6 ft 6¾ in)
  • Wing aspect ratio: 6.5
  • Length overall: 8.84 m (29 ft 0 in)
  • Height overall: 2.74 m (8 ft 11¾ in)
  • Propeller diameter: 2.49 m (8 ft 2 in)

DIMENSIONS, INTERNAL:

  • Cabin max width: 1.40 m (4 ft 7 in)

AREAS:

  • Wings, gross: 25.88 m² (278.6 sq ft)
  • Horizontal tail surfaces: 5.70 m² (61.35 sq ft)
  • Vertical tail surfaces: 2.60 m² (27.9 sq ft)

WEIGHTS AND LOADINGS:

  • Weight empty: 1,150 kg (2,535 lb)
  • Max fuel: 306 kg (675 lb)
  • Max T-O weight: 1,750 kg (3,858 lb)
  • Max wing loading: 67.62 kg/m² (13.85 lb/sq ft)
  • Max power loading: 6.61 kg/kW (10.87 lb/hp)

PERFORMANCE:

  • Max level speed: 124 kt (230 km/h; 143 mph)
  • Service ceiling: 7,600 m (24,930 ft)
  • T-O run: 220 m (725 ft)
  • Landing run: 300 m (985 ft)
  • Range with max fuel: 842 n miles (1,560 km; 969 miles)
  • g limits: +3.8/-1.5

The article appears in the following publication:
Jane's All the World's Aircraft 2004-2005. Jane's Information Group Ltd. 2004. ISBN: 0-7106-2614-2

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