Process for repairing airplane panels
AssigneeAirbus Operations S.L.
InventorsAlberto Balsa Gonzalez, Francisco de Paula Burgos Gallego
Life of this patent
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Abstract
A repair process for a composite material panel that forms part of a fuselage, wings, or stabilizers of an aircraft, with the panel having large dimensions and including irregular contours in some areas and edges prone to damages occurring from handling and assembly of the panel. The process a) locates the damage in the element of the composite material panel; b) sands the area that includes the damage in an area larger than the damage, makes a cut in the panel, having the cut of a same form as a piece that will serve to repair panel; c) places the piece in the cut, so that it is perfectly flush with the panel to be repaired; and d) attaches the piece to the composite material panel.
Claims6
A repair process for a composite material panel that forms part of a fuselage, wings, or stabilizers of an aircraft, with the panel having large dimensions and including irregular contours and edges prone to damages occurring from handling and assembly of the panel, the process comprising:
- a) locating a damaged area in an element of the composite material panel;
- b) sanding an area including the damaged area, the area being larger than the damaged area, and making a cut in the panel, the cut being in a same shape as a shape of a predefined piece that will serve to repair the panel;
- c) placing the predefined piece in the cut such that the predefined piece is perfectly flush with the panel to be repaired;
- and
- d) attaching the predefined piece to the composite material panel.
Dependencies are inferred from the claim text.