Fixing element for components of an assembly

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.

What is claimed is: 
     
         1 . 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. 
   
     
     
         2 . The aircraft assembly of  claim 1 , wherein the cylindrical shaft comprises:
 at least a first strip that extends a length of the cylindrical shaft and which is surface-treated by means of anode oxidation; and   at least a second strip that extends the length of the cylindrical shaft and which is coated with the lubricating coating.   
     
     
         3 . The aircraft assembly 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. 
 
     
     
         4 . The aircraft assembly of  claim 3 , wherein the oxidation is a sulfur anode oxidation. 
     
     
         5 . The aircraft assembly of  claim 4 , wherein the metal rod comprises a cylindrical shaft and an end, and wherein a section between the cylindrical shaft and the end is frustroconical. 
     
     
         6 . The aircraft assembly of  claim 5  wherein the frustoconical section is threaded. 
     
     
         7 . The aircraft assembly of  claim 4  wherein the anode oxidation is substantially 0.5 microns thick. 
     
     
         8 . The aircraft assembly of  claim 4  wherein the lubricant coating is substantially 5 microns thick. 
     
     
         9 . The aircraft assembly of  claim 4  wherein the metal rod is titanium. 
     
     
         10 . 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.   
     
     
         11 . The method of  claim 10  further comprising anode oxidizing at least a second portion of the cylindrical shaft.