Patent ID: 8636107

Claim:
A method for repairing at least a portion of an acoustic panel for a nacelle of an aircraft turbojet engine, said panel comprising an acoustic skin in which a plurality of acoustic holes are drilled, a solid skin, and a cellular acoustic structure comprising a plurality of cells, each of which has one or more drainage openings arranged in one or more of walls forming each cell, said acoustic structure being arranged between the acoustic skin and the solid skin, said method comprising: A—a part of the acoustic panel to be cut is defined; B—said part is cut with the exception of the acoustic skin; C—the cut part is removed, thereby forming a cut in the cut acoustic panel forming a cutting area that is closed by the acoustic skin; D—a resin, which is capable of hardening at ambient temperature, is injected through the acoustic holes of the acoustic skin, said holes terminating in complete cells adjacent to junction cells belonging to the cut acoustic panel so as to block the drainage openings of said junction cells, said junction cells being in contact with the cutting area; E—a replacement cellular acoustic structure is positioned in the cutting area and on the acoustic skin, said replacement cellular acoustic structure having a size substantially equal to the cutting area; and F—a solid replacement skin is formed on the replacement cellular acoustic structure.