# US 9,040,821 B2 · Aircraft cable routing harness > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,040,821 B2 - Document ID: US9040821B2 - Status: Granted - Kind: B2 - Application number: 13/284,135 - Filed: 2011-10-28 - Published: 2012-05-03 - Granted: 2015-05-26 - Earliest claimed: 2010-10-29 - Assignees: Airbus Operations GmbH - Applicants: Jack Blanchard; Anthony Bryant - Inventors: Jack Blanchard; Anthony Bryant - Web page: https://patentgrep.com/patent/US9040821B2 ## CPC - B64C 3/18: Spars; Ribs; Stringers - H02G 3/0431: {Wall trunking} - B64C: AEROPLANES; HELICOPTERS - H02G: INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES ## Abstract A harness is provided comprising a body having a series of electrical conductors embedded therein and substantially running along the length thereof. The body may be part of a structural component such as stringer. ## Claims ### Claim 1 An aircraft fuel tank assembly, comprising: an aircraft wing having an upper skin and a lower skin defining a fuel tank; and, a fuel quantity installation cable routing harness within the fuel tank, the fuel quantity installation cable routing harness comprising: an elongate body having an embedded conductor extending along its length; and, at least one connector extending from a base attached to one of upper or lower skins to the elongate body to provide an air gap between the elongate body and the base. ### Claim 2 (depends on 1) An aircraft fuel tank assembly according to claim 1 in which the elongate body is substantially inflexible. ### Claim 3 (depends on 1) An aircraft fuel tank assembly according to claim 1, in which the embedded conductor is electromagnetically shielded. ### Claim 4 (depends on 3) An aircraft fuel tank assembly according to claim 3, in which the embedded conductor is surrounded by a conducting sheath. ### Claim 5 (depends on 4) An aircraft fuel tank assembly according to claim 4, in which the sheath is constructed from a metal foil. ### Claim 6 (depends on 5) An aircraft fuel tank assembly according to claim 5, in which the conducting sheath is in electrical contact with the at least one connector. ### Claim 7 (depends on 1) An aircraft fuel tank assembly according to claim 1 in which the at least one connector is conductive for conducting static charge from the elongate body to a fuel tank wall. ### Claim 8 (depends on 7) An aircraft fuel tank assembly according to claim 7 in which the at least one connector is a clip configured to at least partially surround the elongate body. ### Claim 9 (depends on 8) An aircraft fuel tank assembly according to claim 8 in which the clip is constructed from a carbon doped composite. ### Claim 10 (depends on 8) An aircraft fuel tank assembly according to claim 8 in which the at least one connector defines a snap fit formation to receive the elongate body. ### Claim 11 (depends on 1) An aircraft fuel tank assembly according to claim 1, in which the elongate body is at least partially constructed from a laminar composite, and the embedded conductor is embedded within a matrix material of the composite and positioned between adjacent layers of the laminate. ### Claim 12 (depends on 1) An aircraft fuel tank assembly according to claim 1, in which the embedded conductor is a wire. ### Claim 13 (depends on 1) An aircraft fuel tank assembly according to claim 1, further comprising a printed circuit board embedded within the body. ### Claim 14 (depends on 13) An aircraft fuel tank assembly according to claim 13, in which the elongate body is at least partially constructed from a laminar composite and the printed circuit board comprises a planer substrate oriented substantially parallel with the composite laminate. ### Claim 15 (depends on 1) An aircraft fuel tank assembly according to claim 1, defining at least one raceway channel configured to receive a cable. ### Claim 16 (depends on 15) An aircraft fuel tank assembly according to claim 15, defining a plurality of raceway channels. ### Claim 17 An aircraft fuel tank assembly, comprising: an aircraft wing having a wing skin defining a fuel tank; and, a fuel quantity installation cable routing harness within the fuel tank, the fuel quantity installation cable routing harness comprising: an elongate body having an embedded conductor extending along its length; at least one resilient arm extending from a base attached to the wing skin to the elongate body to provide an air gap between the elongate body and the base. ### Claim 18 (depends on 17) An aircraft fuel tank assembly according to claim 17, wherein the at least one resilient arm is a pair of resilient arms holding said elongate body therebetween. ### Claim 19 An aircraft fuel tank assembly, comprising: an aircraft wing having a wing skin defining a fuel tank; and, a fuel quantity installation cable routing harness within the fuel tank, the fuel quantity installation cable routing harness comprising: an elongate body having an embedded conductor extending along its length; a base attached to a lower surface of said wing skin, and a pair of resilient arms extending from said base to the elongate body to provide an air gap between the elongate body and the base.