Kraków 2010-07-09.
Construction
270b Section 22.07.1984 year.
PZL M-28 / An-28.
Construction PZL M-28.
Serially produced at WSK PZL-Mielec under a license from the CCCP. A communication plane for transporting passengers and goods in extreme climatic conditions. It has SLOT properties (short take-off and landing). A two-engine turboprop high-strut wing with a metal structure.
Classic double-spar wings. Divided technologically into three parts. Center wing and external attachments. The outline of the central part is rectangular and the outer parts trapezoidal. The construction of the airfoil of the caisson type. The caisson is made up of girders, ribs and a working cover. The caissons, both inside and in attachments, are integral fuel tanks. The outer parts have a rich mechanization. There are two-section gills on the leading edge. Two-section interrupters (slots) on the upper surface. Flaps and ailerons on the trailing edge. The left aileron has a balancing flap. Initially, the shuttlecocks were covered with linen. This is not the end. Two flaps, left and right, and slots are attached to the center wing. All dampers of double-slot type. The wingspan is 22.073 m, and the largest chord is 1,886 m.
The fuselage of the metal structure aircraft consists of a load-bearing covering, longitudinal members, beams and frames. Frames of sight glasses and crew compartment windows are integral parts of the structure. In terms of technology, the hull is divided into three parts. A center wing is attached to the middle part of up to two frames in the upper zone. On the other hand, a residual airfoil was attached to the lower part, and the main landing gear legs and main wings shot down to its ends. The cargo cabin floor is adapted to increased pressure. At the rear of the fuselage there are cargo doors and steps. Double-leaf doors open to the outside. The cargo hold measures 5.26 mx 1.74 mx 1.72 m. In the passenger version there are 19 seats in a 1 + 2 arrangement with a spacing of 0.72 m. The passage is 0.354 m wide. In the rear part of the fuselage, the horizontal tail structure is attached to two frames.
Tail in the shape of the letter "H", with a relatively large surface. This large surface provides excellent maneuverability at low and high speeds. The horizontal strut is structurally one-piece, two-spar, fastened with four fittings to the fuselage frames. They are equipped with a two-piece elevator with balancing flaps. Doubled vertical tail with division into rudder and fins. Structurally single-girder. Each rudder has a trim tab. Initially, all rudders were covered with linen.
The adopted landing gear system of the aircraft allows it to be used at small airports and landing sites with a boggy, snow-covered, gravel or sand surface. The plane was equipped with a fixed landing gear with a front wheel. All wheels are single. Low pressure tires. The leg of the front undercarriage is attached to two floor members. Left-right hydraulic front wheel 50 degrees, unbraked. When lifting off the ground, the front wheel automatically returns to the neutral position with minimal resistance. Size 595 x 320 mm. The main landing gear legs are attached to the residual blades, which ensure its sufficient spacing. Size 720 x 320 mm. The distance of the main undercarriage is 3.405 mm, and the base of the undercarriage is 4.40 m. Braking system of the main undercarriage wheels is hydraulic with anti-skid system (ABS). It is possible to brake each wheel separately.
Written by Karol Placha Hetman