English name: Rook

TYPE: Light utility turboprop.

PROGRAMME: Design started by Utility Aircraft Division in September 1991, as monoplane successor to Antonov An-2/3 biplane; construction of prototype started April 1992; first flight (FLARF-01466) 7 December 1994; no evidence of reported four additional prototypes, all of which are presumed to have been used for static testing.
Series manufacture by Moscow Aviation Production Organisation (MAPO) initiated January 1993; initial production aircraft shown unpainted at Lukhovitsy factory, August 1999; further seven then substantially complete. One T-101 delivered to Chukotka region in July 2000 on six-month lease, representing initial revenue-earning use; second supplied to undisclosed operator in early 2001 and third being prepared for delivery by late 2001. A Westernised version, developed via the Aeroprogress ROKS/Aero T-201, was unsuccessfully marketed as the Khrunichev T-201. In March 2002 the company suggested it was looking for certification by 2004.

CURRENT VERSIONS: T-101: Basic passenger/cargo transport. Detailed description applies specifically to T-101.
Several other variants have been proposed, but none has yet appeared.

CUSTOMERS: Two delivered by mid-2001. Third on order; Asian customer negotiating for four in late 2001. In March 2002 production of parts for 50 aircraft was under way, with 25 sets ready for assembly.

COSTS: Approximately US$700,000 (2002).

DESIGN FEATURES: Single-turboprop aircraft for Normal category passenger/cargo transportation and utility applications; suitable to replace Antonov An-2. High-mounted, unswept, constant-chord, braced wing; non-retractable landing gear and unpressurised cabin; STOL capable, with wide CG range; large passenger/freight door; sweptback fin and rudder with dorsal fin; braced constant chord tailplane and elevators.
Wing section CAHI (TsAGI) P-11-14; dihedral 3o; incidence 3o constant.

FLYING CONTROLS: Conventional and manual. Actuation by pushrods and cables. Slotted ailerons, deflection 30o up, 14o down; elevator deflection 42o up, 22.5o down; rudder deflection ±28o. Trim tabs in each aileron, each elevator and rudder. Electrically actuated single-section slotted trailing-edge flap and two-section automatic leading-edge slats on each wing; flap deflection 25o take-off, 40o for landing.

STRUCTURE: All-metal (aluminium alloy and high-tensile steel) structure; two-spar wings. metal skinned with integral, and ribs; two-spar fin and tailplane; semi-monocoque fuselage, with frames, stringers and stressed skin.

LANDING GEAR: Non-retractable tailwheel type with single wheel on each unit. Main legs of tripod type, with oleo-pneumatic shock-absorption; KT-135D mainwheels, with 720x320 tyres, pressure 3.43 bar (50 lb/sq in); K-392 tailwheel, with 380x200 tyres, pressure 3.43 bar (50 lb/sq in); hydraulic brakes and anti-skid units on mainwheels. Skis and floats optional.

POWER PLANT: One 706 kW (947 shp) Mars (Omsk) TVD-10B turboprop, driving AV-24AN three-blade constant-speed propeller with reverse pitch and full feathering. Three fuel tanks in each wing, each 200 litres (52.8 US gallons; 44.0 Imp gallons); total fuel capacity 1,200 litres (317 US gallons; 264 Imp gallons). Oil tank capacity 30 litres (7.9 US gallons; 6.6 Imp gallons).

ACCOMMODATION: Crew of one or two; up to nine passengers or equivalent freight. Forward-opening door each side of flight deck; large upward-opening freight door aft of wing on port side, with integral inward-opening passenger door; door between flight deck and cabin; starboard emergency exit. Cabin ventilated and heated by engine bleed air.

SYSTEMS: Hydraulic system for brakes; maximum flow 4 litres (1.05 US gallons; 0.88 Imp gallon)/min, at 147 bar (2,135 lb/sq in). Three-phase 120/208 V 400 Hz AC electrical system, supplied by 6 kVA 200 A BU6BK brushless alternator, with emergency DC power supply and 24 V 40 ah Ni/Cd battery. Electric de-icing of propeller blades and spinner; engine air intake de-iced by heated oil.

AVIONICS: Comms: R-855A emergency locator beacon and ARB-NK emergency radio buoy.
Radar: Weather radar pod under starboard wing.
Flight: Com/nav equipment for VFR and IFR operations by day and night over all terrain; PNP-72-14 nav; A-723 long-range radio nav; ARK-M ADF; GRAN low-altitude radio altimeter; GROM satellite nav; A-611 marker beacon receiver; AP-93 autopilot.
Instrumentation: Air data system with digital airspeed and altitude indication; VBM-1PB standby altimeter; KC-MC compact compass system; AGB-96 gyro horizon.


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