Aircraft was designed by Oleg Konstantinovich Antonov at Kiev for utility transport
use requiring short field performance.

HA-MKF was manufactured in 1980 by PZL-Mielec in Poland.

WSK-PZL-Kalisz (Wytwornia Sprzetu Komunikacyjnego-PZL-Kalisz)
Shvetsov ASz-62 IR Geared 9 Cylinder 1823 Cu. In. Radial Engine, rated at 1000 HP max, driving a 4 blade AW-2 Propeller.
 

Take-Off Power             1000 HP at 2200 RPM = 110 gallons/hr = 500 litres/hr   5 minutes max.

Rated Power                  820 HP at 2100 RPM

Max. Continuous            738 HP at 2030 RPM

75% Power                    615 HP at 1910 RPM

 Propeller Gear Ratio    0.637 to 1        11:16
 

Normal Operation:

1800 RPM and 800 mm Hg manifold pressure for typical climb.
1600 RPM and 700 mm Hg for typical cruise.
Use 100 Octane Aviation Grade minimum.

Airframe Construction:

The wings are of an unequal span single bay biplane design, all metal construction, with fabric covering. The wing area is 770 square feet total. Note: wings have full length leading edge slats and ailerons droop with flap actuation to provide great STOL performance. The fuselage is of all-metal stressed skin semi-monocoque construction.  The tail is a braced all metal structure with fabric covering.

Controls:
Ailerons, rudder, and elevators are all manually controlled with pushrods and cables. Flaps and trim electrically operated. Automatic leading edge slats provide excellent slow speed safety and high lift.

Landing Gear:
Conventional configuration (tail wheel design) with split axle, long stroke oleo shock absorbers on the main mounts and a fully castoring and self centring tail wheel. Brakes are pneumatically operated.

Crew: Normally two pilots, may be flown single pilot when no passengers are aboard.

Dimensions:
Length = 41 feet, 9 inches;  Wing Span = 59 feet, 8 inches;  Height = 13 feet, 2 inches (tail down).  Total Wing Lift Area = 256.6 sq. ft. (156.2 upper, 100.4 lower).  Cargo compartment = 13.5 feet long by 5 feet wide by 5.9 feet tall (398.25 cubic feet).  Cargo door opening - 4.5 feet wide by 5 feet tall.

Weights:
Empty = 7,600 lbs.; Max Take Off = 12,125 lbs.; Max Landing = 11,574 lbs.;
Max fuel = 2,000 lbs. (312 USG);
Oil Qty.= 22 Gallons / 100 litres Max.   (13 Gallons minimum to 18 Gallons normal.)
Useful load with max fuel= 2,525 lbs. (3500 lbs with half fuel carried).

Compressed Air System: 8 litre (490 Cu.In.) Air Cylinder at 49 bars (711 PSI) maintained by engine driven AK-50M compressor and AD-50 relief valve. Pressure gauge is on pilot's left hand console. A pressure reducer supplies 10 bars (145 PSI) for the main brakes.

The Air Pressure is required for the pneumatic main wheel brakes, but can be used to charge the landing gear shock absorbing oleo-pneumatic struts when dry nitrogen is not available. A fitting is also available to fill the tires from this system. The 8 litre
air cylinder can also be charged from appropriate ground support equipment.

Electrical System: 24v DC battery  with engine driven generator to maintain charge.
Voltmeter and Ammeter on Instrument Panel.  The 28v DC generator requires at least 900-1000 RPM to kick in.  36v 3 phase 400hz AC power, supplied by two converters, is used to power the Russian Gyroscopic compass, Artificial Horizon and ADF.

CO2 Fire Extinguishing System with automatic fire detector: Nine fire detectors are located throughout the engine compartment. If the Fire Warning Lamp light, the CO2 system can be activated by breaking the safety seal and pushing the button. The CO2 bottle has an electrically activated pyrotechnic cartridge to release the CO2 into the collector.  Portable CO2 Fire Extinguishers are normally installed in the cockpit and cabin as well.

Oil Cooling System: The Oil System consists of a 125 litre (33 gal) Max. permitted
22 gal. tank, suction pump and an external Oil Cooler with electrically controlled shutters.
Use Aeroshell 100 Oil.

The following data applies to all An-2s except float versions which have reduced performance and load capacities. Data is based on a typical weight of 11,600lbs.

        Red Line Speed: V-NE  162 kts = 300 Kph
        White Line Flaps: V-FE  70 kts =  130 Kph
        Best Glide:    65 kts = 120 Kph

        Maximum Speed: 139kts or 160mph or 257Kph (120kts / 220Kph more typical)
        Economy Cruise Speed: 100kts or 115mph or 185Km (95kts / 175Kph more typical)
        Minimum Speed: 49kts or 56mph or 90Kph
        Take-Off Speed: 43kts or 50mph or 79Kph (15 degrees of flap).
        Landing Speed: 46kts or 53mph or 85Kph (30 degrees of flap).
        Stall Speed: 35-40kts or 65Kph but controlled descents are possible at 25kts/30mph/46Kph

         Typical SL Take-Off distance to clear 50 foot obstacle: 1600 feet.
         Minimum SL Take-Off Run: 560 feet.
         Typical SL Landing distance over 50 foot obstacle: 1400 feet.

         Normal Range: 485nm with 45 min. reserve.
         (550nm max with approx. 6 hours endurance).
         Max SL Rate of Climb: 680 fpm, 30 minutes to 14,425 feet.
         Ceiling: 14,425 feet with 1,100lbs. of cargo.
         Note 1: Tolerable Cross wind component is only 8 kts with full flaps.

         Note 2: Aircraft cannot be taxied with wind in excess of 20 kts.