DESIGN. The helicopter is executed under the one-screw circuit with a wing two GDT and the three-basic chassis.
Fuselage all-metal, frame design. In nose of a part the cabins of crew, forward for the navigator, average for two pilots and back for the radio operator and borttehnic are placed. In the central part Fuselage the cargo cabin by the sizes 12 õ 2.65 õ 2.5ì and volume about 80ì3, cargo hatch by the sizes 2.65 õ 2.7ì with shutters, opening in the party, and cargo gangway designed for transportation of cargoes in weight up to 12ò is placed or up to 65 passengers on folding seats (in extreme situations in a cabin up to 150 passengers), or 41 injured on a stretcher with two hospital attendants on folding seats were transported; on the right to a board of a cabin are located a door and nine windows, on left two doors and seven windows. In a floor of a cargo cabin there is a cargo hatch closed by shutters.
The tail beam of a design separated, fastens to Fuselage by bolts, comes to an end by a trailer beam. On a tail beam the controlled stabilizer, and on a trailer beam the fixed rudder of a direction is established.
The wing parts, has a beam and consoles with of a type, nose and tail parts and end. The wing is designed for the maximal loading equal 25 % flight of weight, has a structure ÖÀÃÈ Ï35 with relative thickness at a root 15 % and on the end 12 %. The left console has a corner çàêëèíåíèÿ14¨15 ', and right 15¨45 '.
The chassis three-basic, not cleaned(not removed), with æèäêîñòíî-gas shock-absorbers; a forward support with two by wheels by the sizes 720 õ 310ìì; the main support of a type have on one brake wheel by the sizes 1320 õ 480ìì and pressure of 7 kg / ñì2; on a tail beam there is a tail support; the chassis allows to make rise and landing(planting) vertically and for a plane type.
The bearing(carrying) screw , with by fastening of blades and hydraulic dempfers is inclined forward on 5 ¨. Blades of an all-metal design, rectangular form in the plan, with structures NACA 230Ì and CAGI with relative thickness 17.5 % at the end and 11 % on the end and corner 6 ¨. Horda of the blade 1ì. The blades have steel from integral of a pipe from steel 40ÕÍÌÀ in length 15.61ì with various thickness of a wall and form of cross section. To joins 20 part, consisting from of a part with a counterbalance and by a package and tail part with cellular , and trailer. Blade have electrical system, district speed of the ends of blades 220ì/with.
The power(force) installation consists of two turbo GDT-25Â Perm NPO "Airengine" with the free turbine established by a number(line) from above Fuselage in , the engine has the nine-step compressor and two-step turbine. Length of the engine 2.74ì, width 1.09ì, height 1.16ì, dry weight with all units of 1344 kg, take-off capacity of the engine of 4045 kw.
The fuel system is executed under the two-wire circuit, the fuel contains in 11 soft tanks of general(common) capacity 3250ë, for increase of range of flight the installation of two pendant tanks on 2250ë and additional tanks of capacity 4500ë in a cargo cabin is stipulated.
The equipment: two hydraulic systems with pressure 12.8 15.3ÌÏà provide a drive of hydroamplifiers and units of management, the auxiliary system provides a drive of cargo shutters and gangways and ò. ä.
Arms. On some military helicopters in nose part is established machine gun And 12.7 calibre 12.7ìì on is limited mobile installation ÍÓÂ-1Â with sight To - 10ò.
Crew: 5, passengers: 65, power(force) installation: 2 x GDT Ä-25À of the Perm factory by capacity on 4045êÂò, diameter of the bearing(carrying) screw: 35.0ì, length with rotating screws: 41.74ì, height: 9.16ì, width Fuselage : 3.2ì, take-off weight: 42500êã, weight empty: 27240êã, maximal speed: 300êì/÷, main speed: 250êì/÷, seedweight: 6.5ì/with, dynamic ceiling: 4500ì, static ceiling: 1000ì, range of flight with loading 8ò: 620êì, range: 1450êì, useful loading: 12000êã
