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Purpose:
Convertible cargo/passenger aircraft
Description:
The aircraft is intended for cargo carrying of total weight up to 10 t or 52 passengers. Possibility of cabin conversion from cargo version to passenger or mixed and vice versa is available.
It is operable both from paved runways and from unpaved ones.
The aircraft cabin conversion provides the following:
passengers transportation with possible cabin capability conversion up to 52 persons or 10 t of cargo;
mixed transportation versions (cargo + passengers): 20 passengers + 4.5 tones of cargo or 12 passengers + 6 tones of cargo.
Also the aircraft can be supplied in administratively-staff version. Equipment and layout of cabin are to be agreed with the Customer.
FUNCTIONAL FEATURES
The aircraft is an all-metal cantilever high-wing monoplane with single-finned T-tailed empennage. The aircraft is intended for operation in all-weather conditions.
Arrangement of engines over the wing provides the air flow passing along the upper wing surface which results in additional lifting force formation. Availability of high lift wing and engine thrust reverse allows to operate the aircraft on short runways, and the aircraft landing gear and high engines location allows to operate the aircraft on runways with artificial, soil, sandy, pebbled and icy coatings.
In fuselage tail section the cargo door is located which is used for cargo loading/unloading. Cargo hatch opening is closed with the ramp that can be used as a stairs or moved under the fuselage to facilitate aircraft loading directly from the truck.
The door is used for cargo loading/unloading and paratroops/cargo dropping. Cargo hatch opening is closed with the ramp that can be used as a stairs or moved under the fuselage to facilitate aircraft loading directly from the truck.
Technical details:
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Maximum payload weight, t
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10
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Engines:
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type
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D-36 ser.3 A double-flow turbojet engine
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number x thrust, tf
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2x6.5
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Maximum cruissng flight speed, km/h
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650
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Maximum flight altitude, m
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10100
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Fuselage length, m
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25.735
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Maximum diameter, m
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3.10
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Flight range at 9 000 m -10100 m pressure altitude and 560-580 km/h airspeed with engine thrust not exceeding maximum cruise power condition thrust, for take off weight 36 500 kg and 1-hour fuel reserve, km:
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with maximum payload 10 000 kg and fuel reserve 4834 kg before taking-off
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800
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with maximum fuel reserve 9 634 kg before taking-off and payload 5 200 kg
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2600
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2–3
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