# US 8,784,589 B2 · Copper grid repair technique for lightning strike protection > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,784,589 B2 - Document ID: US8784589B2 - Status: Granted - Kind: B2 - Application number: 13/449,083 - Filed: 2012-04-17 - Published: 2012-08-16 - Granted: 2014-07-22 - Earliest claimed: 2005-09-06 - Assignees: The Boeing Company - Applicants: Patrice K. Ackerman; Steven D. Blanchard; Daniel J. Kovach - Inventors: Patrice K. Ackerman; Steven D. Blanchard; Daniel J. Kovach - Web page: https://patentgrep.com/patent/US8784589B2 ## CPC - B32B 38/10: Removing layers, or parts of layers, mechanically or chemically - B29C 73/10: using patches sealing on the surface of the article (B29C73/14 takes precedence) - B32B 43/00: Operations specially adapted for layered products and not otherwise provided for, e.g. repairing; Apparatus therefor - B64F 5/40: Maintaining or repairing aircraft - B29L 2031/3076: {Aircrafts (blades, propellers B29L2031/08)} - Y10T 156/109: Embedding of laminae within face of additional laminae - Y10T 428/20: Patched hole or depression - B32B: LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM - B29C: SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING (making preforms B29B11/00; making laminated products by combining previously unconnected layers which become one product whose layers will remain together B32B37/00 - B32B41/00) - B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR - B29L: INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract A method for reworking an electrically conductive layer of a composite skin is disclosed in which a patch replaces the altered section of the electrically conductive layer. The method is performed by removing a portion of the electrically conductive layer to reveal the underlying composite skin. A patch is formed, having an electrically conductive section coupled to an adhesive having a low dielectric breakdown strength, and is then introduced over the underlying composite skin such that the adhesive layer covers the underlying composite skin and overlaps an unremoved portion of the electrically conductive layer. The patch is applied such that the electrically conductive section within the patch covers the adhesive layer and overlaps the unremoved section of the electrically conductive layer. The adhesive layer preferably has a low dielectric breakdown strength, so that electricity from lightning which strikes the composite skin may be conducted through the adhesive. ## Claims ### Claim 1 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. ### Claim 2 (depends on 1) The method of claim 1, wherein: revealing a section of the electrically conductive layer comprises removing any paint, primers, or other layers on the aircraft composite skin. ### Claim 3 (depends on 1) The method of claim 1, further comprising: wet-laying a resin-impregnated fabric over the section of replacement electrically conductive material; and curing the resin-impregnated fabric. ### Claim 4 (depends on 3) The method of claim 3, further comprising: curing the film adhesive layer; and curing the resin impregnated fabric. ### Claim 5 (depends on 4) The method of claim 4 wherein the film adhesive layer is cured simultaneously with curing the resin impregnated fabric. ### Claim 6 (depends on 1) The method of claim 1, wherein: the electrically conductive layer is a copper foil grid; and the replacement electrically conductive section is made from copper foil. ### Claim 7 (depends on 3) The method of claim 3, wherein the film adhesive layer comprises an unsupported thermosetting modified epoxy film adhesive. ### Claim 8 A method for reworking an electrically conductive layer on a composite skin, comprising: revealing a section of the electrically conductive layer; removing a portion of the electrically conductive layer to reveal an underlying composite skin, leaving an unremoved section of the electrically conductive layer; removing a fastener within the section of the electrically conductive layer, revealing a hole; plugging the hole with a plug, wherein the plug substantially consists of polytetrafluoroethylene; introducing a patch having a replacement electrically conductive section and a film adhesive layer over the underlying composite skin such that an outer portion of the 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 replacement electrically conductive section; wet-laying a resin-impregnated fabric onto the patch, and curing the resin-impregnated fabric; and curing the film adhesive layer and the resin impregnated fabric simultaneously. ### Claim 9 (depends on 8) The method of claim 8, wherein the replacement electrically conductive section within the patch overlaps the unremoved section of the electrically conductive layer by between approximately one half inch and approximately one inch. ### Claim 10 (depends on 8) The method of claim 8, wherein the film adhesive layer is approximately 0.005 inches thick. ### Claim 11 (depends on 8) The method of claim 8, wherein the film adhesive layer is a 250 Fahrenheit cure unsupported thermosetting epoxy film adhesive and has a nominal weight of about 0.030 pounds per square foot. ### Claim 12 (depends on 8) The method of claim 8, wherein the resin-impregnated fabric overlaps the patch by approximately one half inch. ### Claim 13 (depends on 8) The method of claim 8, wherein revealing a section of the electrically conductive layer comprises: removing any paint, primer or other layers over an area to be reworked. ### Claim 14 (depends on 8) The method of claim 8, wherein the film adhesive layer comprises an unsupported thermosetting modified epoxy film adhesive. ### Claim 15 A method for reworking an electrically conductive layer on a composite skin, comprising: revealing a section of the electrically conductive layer; removing a portion of the electrically conductive layer to reveal an underlying composite skin, leaving an unremoved section of the electrically conductive layer; removing a fastener within said section of the electrically conductive layer, revealing a hole; plugging the hole with a plug substantially consisting of polytetrafluoroethylene; introducing a patch having a replacement electrically conductive section and a film adhesive layer over the underlying composite skin, such that an outer portion of the replacement electrically conductive section of said patch substantially overlaps an overlap 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 overlap region of said unremoved portion of the electrically conductive layer and the replacement electrically conductive section; forming an overlap splice joint between the replacement electrically conductive section and the overlap region of the unremoved portion of the electrically conductive layer, the overlap splice joint providing an electrically conductive path between the replacement electrically conductive section and the unremoved portion of the electrically conductive layer, the film adhesive layer being a 0.005 inches thick layer of an unsupported thermosetting epoxy film adhesive; and curing the film adhesive layer; the film adhesive layer covering the underlying composite skin and overlapping the unremoved section of the electrically conductive layer; the replacement electrically conductive section within the patch covering the film adhesive layer; and the replacement electrically conductive section within the patch overlapping the unremoved section of the electrically conductive layer by between approximately one half inch and approximately one inch. ### Claim 16 (depends on 15) The method of claim 15, wherein: the electrically conductive layer is a copper foil grid; and the patch is a copper patch and the electrically conductive section of the patch is made from copper foil. ### Claim 17 (depends on 15) The method of claim 15, further comprising: introducing milled glass and a thermosetting epoxy resin around the plug.