Wing span upper, lower 18.18m, 14.24m
Length Overall (tail up), (tail down) 12.71m, 12.40m
Height overall (tail up), (tail down) 6.10m, 4.00m
Wheel track 3.45m
Propeller diameter 3.60m
Propeller ground clearance 0.69m
Wing area 71.6m
Cargo door (port) mean height, mean width 1.55m, 1.39m
Cargo compartment length, Max height, Max width
4.10m, 1.80m, 1.60m
Weight empty 3450kg
Max T-O weight 5500kg
Useful load 2050kg
Maximum fuel weight 900kg
Max wing loading 78.82kg/m
Max power loading 5.5kg/hp
Performance (at AUW of 5250 kg)
Max level speed at 1500 m 253km/h
Econ. cruising speed 185km/h
Stalling speed 90km/h
Max rate of climb at S/L 3m/s
Service ceiling 4400m
T-O run. (grass) 170m
T-O to 10.7, m (grass) 320m
Landing run (grass) (hard runway) 185m, 170m
Range at 1000m altitude with 700 kg payload 1370 km
Cabin area 360′ picture, zoom in and look around. Use you mouse to around the cabin.
An-2 (Passenger) can be characterized by the following: wings – unequal-span single-bay biplane. Wing section RIIS 14o/o (constant). Dihedral, both wings, approx 2’48. All-metal two-spar structure, fabric covered aft of front spar. Differential ailerons and full-span automatic leading-edge slats on upper wings, slotted trailing-edge flaps on both upper and lower wings. Flaps operated electrically, ailerons mechanically. Fuselage – all-metal stressed-skin semi-monocoque structure. Crew of two on flight deck, with access via passenger cabin. Standard accommodation for 12 passengers, in four of three rows with center aisle. Two folding seats for children on the aisle between the 1st and 2nd rows. Toilet at rear cabin on starboard side. Overhead racks for baggage of up to 160 kg, with space for coats and additional 40 kg of baggage between the rear pair of seats and toilet. Emergency exit on starboard side at rear. Walls of cabin are lined with glass-wool mats to reduce internal noise level. Cabin heating and starboard windscreen de-icing by engine bleed air; port and center windscreen are de-iced electrically. Cabin ventilation by. ram-air intakes. Air-conditioning system in An-2R. Tail unit – braced metal structure. Fabric-covered tailplane. Elevators and rudder operated mechanically. Electrically-operated trim tab in rudder and elevator. Landing gear – non-retractable split-axle type, with long-stroke oleo shock-absorbers. Main wheel tyres size 800 X 260 mm, pressure 230 kPa (2.3 kg/cm2). Pneumatic brakes on main units. Fully-castoring and self-centering tailwheel with electro-pneumatic lock. Interchangeable ski landing gear available optionally. Power plant – one 736 kW (1000 hp) PZL ASz-62IR nine-cylinder radial air-cooled engine, driving an AW-2 four-blade variable pitch metal propeller. Six fuel tanks in upper wing, with total capacity of 1200 litters. Oil capacity – 120 litters. Systems: Compressed air cylinder of 8 litters capacity for pneumatic charging of shock-absorbers and operation of tailwheel lock at 5000 kPa (50 kg/cm2) pressure and operation of main-wheel brakes at 1000 kPa (10 kg/cm2). DC electrical system is supplied with basic 27 V power by an engine-driven generator and a storage battery. CO2 fire extinguishing system with automatic fire detector. Equipment: Dual controls and blind-flying instrumentation standard. R-860. HF and R-842 VHF radio transceivers (or R56102A or Becker AR400 or Narco KX-170), RW-UM radio altimeter, ARK-9 radio compass, MRP-5EP marker beacon receiver, GB-1 gyro compass, GPK-48 gyroscopic direction indicator, and SPU-7 intercom.
DESIGN DEVELOPMENT: The prototype of this large biplane was designed according to the specification of the Ministry of Agriculture and Forestry of the USSR and its first flight was made on 31 August 1947. It was powered by a 560 kW (7B0 hp) ASh-21 engine and was known as the SKh-1. In 1948 design went into production in the USSR as the An-2 with a 736 kW (987 hp) ASh-62 engine. License rights were granted to China where the first locally-produced An-2 was completed in December of 1957. Since 1960, apart from a small Soviet-built quantity of a developed version known as An-2M, , the continued production of the An-2 has been taken over by the Polish PZL factory at Mielec, the origin license arrangement providing for two basic versions: the An-2T transport and An-2R agricultural version. The first Polish-built An-2 made its first flight on 23 October 1961. Since the very beginning of An-2 production, PZL-Mielec has made numerous improvements to the airframe of An-2R resulting in extension of TBO from 900 hr in 1961 to 1500 hr in 1970 and 2000 hr in 1973. The service life was extended to 15 900 hr. More than 90 per cent of the aircraft made up export deliveries, mainly to the former USSR. Since 1960 – 10 000 An-2s were built including 5500 agricultural versions.
The AN2 represents a bargain for what was the former Soviet union airliner along with the Lisunov Li2 (DC3 copy), we have the facilities to overhaul these aircraft and to supply with a normal certificate of airworthiness. Fuel costs are high at 120 lts/ hour economic cruise however with up to 12 passengers the miles/ pax/ lt fuel is very reasonable. The aircraft makes a good club machine for outings to France for example.