Antonov An-2

COMMENT : Found at Jane's All the World Aircraft Demo...
NATO reporting name: Colt

The prototype of the An-2, designed to a specification of the Ministry of Agriculture and Forestry of the USSR, made its first flight on 31 August 1947. In 1948 the aircraft went into production in the USSR as the An-2, with a 746 kW (1000hp) ASh-62 engine.

By 1960, more than 5000 An-2s had been built in the Soviet Union, as fully described in previous editions of Jane's. Licence rights were granted to China, where the first locally produced An-2 was completed in December 1957, as the Yunshuji-5 or Y-5. Limited production continues in China, as described under the SAP heading in that section.

Since 1960, apart from a few dozen Soviet built An-2Ms (1971-72 Jane's), continued production of the An-2 has been primarily the responsibility of PZL Mielec, the original licence arrangement providing for two basic versions: the An-2T transport and An-2R agricultural version. The first Polish built An-2 was flown on 23 October 1960. Mielec has since built more than 11950 An-2s for domestic use and for export to the USSR (10427), Bulgaria, Czechoslovakia, Egypt, France, the then German Democratic Republic, Hungary, Iraq, North Korea, Mongolia, Netherlands, Nicaragua, Romania, Sudan, Tunisia, Turkey, the UK, Venezuela and Yugoslavia. They include 7777 An-2Rs. In 1989 AICSA of Colombia (which see) assembled two An-2s from kits supplied from PZL Mielec via Pezetel.

Polish built versions have different designations from those built in the USSR. They include the An-2 Geofiz; An-2LW; An-2P, PK, P-Photo and PR; An-2R; An-2S; An-2T, TD and TP. Further details of these can be found in the 1983-84 and earlier editions of Jane's.

The following details apply to the PZL Mielec An-2P:
TYPE : Single-engined general purpose biplane.
WINGS: Unequal span single-bay biplane. Wing section RPS 14 per cent (constant). Dihedral, both wings, approx 2~ 48'. All-metal two-spar structure, fabric covered aft of front spar. I- type inter-plane struts. Differential ailerons and full span automatic leading-edge slots on upper wings, slotted trailing-edge flaps on both upper and lower wings. Flaps operated electrically, ailerons mechanically by cables and push/pull rods. Electrically operated trim tab in port aileron.
FUSELAGE : All-metal stressed skin semi-monocoque structure of circular section forward of cabin, rectangular in the cabin section and oval in the tail section.
TAIL UNIT : Braced metal structure. Fin integral with rear fuselage. Fabric covered tailplane. Elevators and rudder operated mechanically by cables and push/pull rods. Electrically operated trim tab in rudder and port elevator. LANDING GEAR: Non-retractable split axle type, with long stroke oleo shock absorbers. Main tires size 800x260mm, pressure 2.25 bars (32.7 lb/sq in). Pneumatic shoe brakes on main units. Fully castoring and self-centering PZL Krosno tailwheel, size 470x210, with electro-pneumatic lock. For rough field operation the oleo-pneumatic shock absorbers can be charged from a compressed air cylinder installed in the rear fuselage. Interchangeable ski landing gear available optionally.
POWER PLANT : One 746 kW (1000hp) PZL Kalisz ASz-62IR nine-cylinder radial aircooled engine, driving an AW-2 four-blade variable-pitch metal propeller. Six fuel tanks in upper wings, with total capacity of 1200 litres (317 US gallons; 264 Imp gallons). Oil capacity 120 litres (31.7 US gallons; 26.4 Imp gallons).
ACCOMMODATION : Crew of two on flight deck, with access via passenger cabin. Standard accommodation for 12 passengers, in four rows of three with centre aisle. Two foldable seats for children in aisle between first and second rows, and infant's cradle at front of cabin on starboard side. Toilet at rear of cabin on starboard side. Overhead racks for up to 160kg (352 lb) of baggage, with space for coats and additional 40kg (88 lb) of baggage between rear pair of seats and toilet. Emergency exit on starboard side at rear. Walls of cabin are lined with glass-wool mats and inner facing of plywood to reduce internal noise level. Cabin floor is carpeted. Cabin heating and starboard windscreen de-icing by engine bleed air; port and centre windscreen are electrically de-iced. Cabin ventilation by ram air intakes on underside of top wings.
SYSTEMS: Compressed air cylinder, of 8 litres (0.28 cu ft) capacity, for pneumatic charging of shock absorbers and operation of tailwheel lock at 49 bars (711 lb/sq in) pressure and operation of main brakes at 9.80 bars (142 lb/sq in). Contents of cylinder are maintained by AK-50 P engine driven compressor, with AD-50 automatic relief device to prevent overpressure. DC electrical system is supplied with basic 27V power (and 36V or 115V where required) by an engine driven generator and a storage battery. CO_2 fire extinguishing system with automatic fire detector.
AVIONICS : Dual controls and blind-flying instrumentation standard. R-842 HF and RS-6102 or Baklan-5 VHF lightweight radio transceivers, RW-UM radio altimeter (A-037 from 1 April 1989), ARK-9 radio compass, MRP-56P marker beacon receiver, GIK-1 gyro compass, GPK-48 gyroscopic direction indicator and SPU-7 intercom.
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Created January 25, 1996 Back to
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