METHOD OF ON CONDITION REPAIR AND MODERNIZATION UP DATING OF AN AIRCRAFT CENTER WING SECTION

摘要

The utility model relates to the sphere of aviation and aircraft repair technology, namely to the Method of on-condition repair and modernization up-dating of an aircraft center wing section, in particular, of Antonov-32 (An-32) type aircraft, and its modifications. Method of aircraft on-condition repair and modernization up-dating is performed sequentially in time at several stages, according to which at the 1st stage the accepting of aviation engineering (AE for repair is carried out, at the 2nd stage the extensional fault detection of the AE received for repair is provided, while there are used data on individual resource of the elements, failures and malfunctions of the products that were revealed during their operation and repairs, as well as statistical data collected in the database of the aircraft repair plant to determine the feasibility of one or another method of the AE components maintenance and repair, appropriate updating of the repair technological cycle is carried out, and the properly systematized data obtained during the AE inspecting are transmitted to the database of the aircraft repair plant, at the 3rd stage the AE disassembly is carried out pursuant to approved list of works in accordance with the repair technology, and when conducting the AE disassembling and inspection of removable and non- removable equipment the dismantle is performed of only those elements that need additional diagnostics or maintenance, scheduled repair or overhaul, at the 4th stage cleaning and washing of dismounted parts, assemblies, units and the whole object are performed, at the 5th stage the items are completed in groups for further delivery for repair, considering the equipment that need repair on-condition or overhaul is transferred to the appropriate areas for implementation of the 7th stage of the repair operations, while the equipment that does not need additional operations is transferred, either directly or via an intermediate keeping in store, for further reassembly, installation and testing at the 8th stage of the repair, at the 6th stage the technical diagnosis is carried out, which is aimed to determine the technical condition of the items delivered for repair and remedial procedures for detected faults and defects, at the 7th stage the repair is performed with simultaneous structural modification, at the 8th stage there are carried out sequential operations on reassembly, installation and testing with subsequent transfer of the repaired AE to the flight test station for acceptance tests, at the 9th stage the ground and flight tests are carried out, which represent together check and acceptance tests, recent data on faults and defects revealed after the 6th - 9th stages of the repair are systematized and transmitted to the database of the aircraft repair plant, at the 10th stage there are performed operations of the AE processing, painting, storage, packaging and delivery to the customer, which is characterized in that at the 7th stage the structural modification of the center wing section is performed by modification of the rear end of the center wing section, spars, and strengthening of lower panels of the center wing section, replacement of the upper ledge of load-carrying part of the wing-root fillet of the center wing section and the fuselage, wherein the removable panels are mounted on the rear end of the center wing section, while the lower panels of the center wing section are provided with at least three endurance reinforcing plates of corresponding thickness: length - 6200 mm, width - 380 mm, 520 mm, 390 mm, which are mounted and fixed from No.4 rib of a half-wing to No.4 rib of another half-wing through the openings in the upper part of the fuselage, total thickness of the plates and web is 7 mm, the plates are made of aluminum alloy D16ATV (?16ATB) sheets, and their configuration takes in account the existing corrosion damages of the lower panels of the center wing section, bushings and bolts are mounted at fixing straps and fuselage bows with account of results of eddy currents test on faults detecting, and at that the ledge of load-carrying part of the wing-root fillet of the center wing section and the fuselage is made of D16T extruded profile of 2410 mm length, which configuration takes in account a thickness of the reinforcing plates, and one more point - spacer plates are installed in the ledges setting area between the plates on No.3 and No.7 stringers