Patent ID: 8784589

Claim:
A method for reworking a reduced impedance of an electrically conductive layer contained on an aircraft composite skin, the method comprising: revealing a section of the electrically conductive layer; removing a portion of the electrically conductive layer to reveal an underlying composite skin; introducing a section of replacement electrically conductive material and a film adhesive layer over the underlying composite skin such that an outer portion patch overlaps an overlapping region of an unremoved portion of the electrically conductive layer, and such that the film adhesive layer is sandwiched between and in contact with the overlapping region of the unremoved portion of the electrically conductive layer and the section of replacement electrically conductive material, forming an overlap splice joint between the replacement electrically conductive section and the overlapping region of the unremoved portion of the electrically conductive layer, the single lap joint providing an electrically conductive path between the replacement electrically conductive material and the unremoved portion of the electrically conductive layer; removing one or more fasteners within the section of the electrically conductive layer, wherein removing each of the one or more fasteners leaves one or more fastener holes; and plugging the one or more holes with one or more plugs, wherein the one or more plugs substantially consist of polytetrafluoroethylene.