# US 2015/0147136 A1 · Fixing element for components of an assembly > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2015/0147136 A1 - Document ID: US20150147136A1 - Status: Published application - Kind: A1 - Application number: 14/547,802 - Filed: 2014-11-19 - Published: 2015-05-28 - Earliest claimed: 2013-11-25 - Assignees: Airbus Operations GmbH - Applicants: Airbus Operations S.A.S. - Inventors: Jean-Philippe MAUREL; Frederic LABAL; Jean-Luc MARTRES - Web page: https://patentgrep.com/patent/US20150147136A1 ## CPC - F16B 33/008: {Corrosion preventing means} - F16B 33/06: Surface treatment of parts furnished with screw-thread, e.g. for preventing seizure {or fretting (corrosion preventing means F16B33/008; settable coatings for locking threaded members F16B39/225; deformable coatings for locking threaded members F16B39/34)} - F16B 35/00: Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws ({F16B33/008 takes precedence; joining sheets or plates using screws with two separate threads F16B5/0275; using screws with adjustment sleeves F16B5/0283}; thread cutting screws F16B25/00) - F16B: DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING (couplings for transmitting rotation F16D) ## Abstract A fixing element for components of an assembly, comprising a rod which is formed by a cylindrical shaft and an end, the rod being a metal component which is at least partially surface-treated by means of anode oxidation and coated over at least a portion of the cylindrical shaft with a lubricating coating. Such a fixing element enables the electrical continuity to be ensured with the components during mounting with moderate interference in the assembly. ## Claims ### Claim 1 The fixing element for securing components of an assembly, comprising: a metal rod comprising a cylindrical shaft and an end, the metal rod comprising: a first region that is at least partially surface-treated by means of anode oxidation; and a second region coated over at least a portion with a lubricating coating. ### Claim 2 (depends on 1) The fixing element of claim 1, wherein the cylindrical shaft comprises: at least a first strip that extends in the length of the cylindrical shaft and which is surface-treated by means of anode oxidation; and at least a second strip that extends in the length of the cylindrical shaft and which is coated with the lubricating coating. ### Claim 3 (depends on 2) The fixing element of claim 2, wherein the cylindrical shaft comprises: a plurality of first strips that are surface-treated by means of anode oxidation; and a plurality of second strips that are coated with a lubricating coating, the first and second strips extending over angular sectors that are distributed around the periphery of the cylindrical shaft. ### Claim 4 (depends on 3) The fixing element of claim 3, wherein the first and second strips are distributed in a substantially uniform manner around the periphery of the cylindrical shaft. ### Claim 5 (depends on 3) The fixing element of claim 3 wherein the cylindrical shaft comprises three first strips that are surface-treated by means of anode oxidation and each over three angular sectors of substantially 45°, respectively, and that are separated in pairs by means of a second strip that is covered with the lubricating coating and extends over an angular sector of substantially 75°. ### Claim 6 (depends on 3) The fixing element of claim 3, wherein the cylindrical shaft comprises two first strips that are surface-treated by means of anode oxidation and that extend over two angular sectors between substantially 90 and 150°, respectively, and two second strips which are covered with a lubricating coating that extends over two angular sectors between substantially 30 and 90°, respectively. ### Claim 7 (depends on 3) The fixing element of claim 3, wherein the rod is at least partially surface-treated by means of sulphuric anode oxidation. ### Claim 8 (depends on 7) The fixing element of claim 7, wherein lubricating coating (R) is a coating comprising phenolic resin. ### Claim 9 An aircraft assembly, comprising: a first component; a second component; and a metal rod comprising a cylindrical shaft and an end for securing the first and second components, the metal rod comprising: a first region that is at least partially surface-treated by means of anode oxidation; and a second region coated over at least a portion thereof with a lubricating coating. ### Claim 10 (canceled) ### Claim 11 (depends on 9) The aircraft assembly of claim 9, wherein the cylindrical shaft comprises: at least a first strip that extends in the length of the cylindrical shaft and which is surface-treated by means of anode oxidation; and at least a second strip that extends in the length of the cylindrical shaft and which is coated with the lubricating coating. ### Claim 12 (depends on 11) The aircraft assembly of claim 11 wherein the cylindrical shaft comprises; a plurality of first strips that are surface-treated by means of anode oxidation; and a plurality of second strips that are coated with a lubricating coating, the first and second strips extending over angular sectors that are distributed around the periphery of the cylindrical shaft. ### Claim 12 (depends on 12) The aircraft assembly of claim 12, wherein the oxidation is a sulfur anode oxidation. ### Claim 14 (depends on 13) The aircraft assembly of claim 13, wherein the metal rod comprises a cylindrical shaft and an end, and wherein a section between the cylindrical shaft and the end is frustroconical. ### Claim 15 (depends on 14) The aircraft assembly of claim 14 wherein the frustoconical section is threaded. ### Claim 16 (depends on 13) The aircraft assembly of claim 13 wherein the anode oxidation is substantially 0.5 microns thick. ### Claim 17 (depends on 13) The aircraft assembly of claim 13 wherein the lubricant coating is substantially 5 microns thick. ### Claim 18 (depends on 13) The aircraft assembly of claim 13 wherein the metal rod is titanium. ### Claim 19 A method for treating a fixing element that secures an aircraft assembly, the fixing assembly including a rod comprised of a cylindrical shaft, an end section, and an intermediate connecting section, the method comprising: coating at least a first portion of the cylindrical shaft with a lubricant. ### Claim 20 (depends on 19) The method of claim 19 further comprising anode oxidizing at least a second portion of the cylindrical shaft.