TYPE: Twin-turboprop light transport.

PROGRAMME: Original Be-30 first flown in prototype form on 3 March 1967; eight Be-30s built, but programme terminated when Aeroflot ordered Let L-410As from Czechoslovakia. Hard currency shortage revived programme 1993, with modestly upgraded version known as Be-32; one of original Be-30s (RA-67205) exhibited at 1993 Paris Air Show, as Be-32 demonstrator with original Russian TVD-10B engines; re-engined with PT6A-65B turboprops, RA-67205 first flew as Be-32K on 15 August 1995. Launch of Be-32K production continued to be discussed in 2001, although initial investment of Rb1,060 million required, plus Rb1,460 million in medium term; no announced orders.
Be-132 emerged from agreement between Motor-Sich of Ukraine, IAPO, Klimov and Beriev, signed at Paris Air Show in June 2001. Initial details released at MAKS, Moscow, August 2001. Completion of business plan and start of marketing were due for early 2002, but little evidence of progress 12 months later. Certification planned to AP-25.

CURRENT VERSIONS: Be-132MK: Initial version. Compared with Be-32, has more circular fuselage cross-section and increased length.

DESIGN FEATURES: General purpose light transport, optimised for operation from remote airfields. Conventional cantilever high-wing monoplane; three-section wings, with anhedral on outer panels; 42° sweptback vertical tail surfaces; engines at tip of centre-section each side. Ventral underfin.

FLYING CONTROLS: Conventional and manual. Trim tabs in both ailerons, both elevators and rudder. Double-slotted flaps in two sections each side, inboard and outboard of engines.

STRUCTURE: All-metal; semi-monocoque fuselage of rectangular section; spars and skin panels of wing torsion box are mechanically and chemically milled profile pressings; detachable bonded leading-edge; half of wings and most of tail unit covered with thin honeycomb panels stiffened with stringers; majority of fuselage made of adhesive-bonded panels; tips of wings and tail surfaces and wing/fuselage fillets of GFRP.

LANDING GEAR: Tricycle type; single wheel on each unot; nosewheel retracts forward, mainwheels rearward into engine nacelles; tyres size 720x320 on mainwheels, 500x150 on nosewheel; mainwheel brakes.

POWER PLANT: Two 1,103kW (1,479 shp) Klimov VK-1500 turboprops; six-blade Aerosila AV-36 propellers; integral wing fuel tanks.

ACCOMMODATION: Basic seating for two crew and 26 passengers in two-plus-one configuration at 78 cm (30½ in) pitch. Carry-on baggage compartment on starboard side, aft of cabin seating, opposite forward-hinged door and airstairs; lavatory to rear.


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