Fastener assembly

Patent metadata

Field	Value
Publication number	US-9140287-B2
Application number	US-201313754471-A
Country	US
Kind code	B2
Filing date	Jan 30, 2013
Priority date	Jan 30, 2013
Publication date	Sep 22, 2015
Grant date	Sep 22, 2015

Abstract

A fastener assembly is disclosed for mounting a component to a bracket attached to an inner surface of the skin of an aircraft wing such that the component is thermally and electrically isolated from the bracket is disclosed. The component and bracket each have mounting holes and the fastener assembly includes a fastening element having a shaft to extend through the holes, first and second isolating members mountable on the shaft on either side of the bracket such that the bracket is sandwiched between the first and second isolating members.

First claim

The invention claimed is:

1. A fastener assembly for mounting a component to a bracket attached to an inner surface of a skin of an aircraft wing such that the component is thermally and electrically isolated from the bracket, the component and bracket each having mounting holes, wherein the fastener assembly comprises a fastening element having a shaft to extend through said holes, first and second isolating members mountable on the shaft on either side of the bracket such that the bracket is sandwiched between said first and second isolating members and, a retaining element threadingly engageable with the shaft protruding through the second isolating member to clamp said first and second isolating members together against said bracket, wherein one of said isolating members has a central portion that protrudes through said mounting hole in the bracket and the other isolating member comprises a recess to receive said central portion.

2. A fastener assembly according to claim 1 , wherein the first isolating member is located between the component and the bracket and has said central portion to extend through the hole in the bracket.

3. A fastener assembly according to claim 2 , wherein the first isolating member comprises a mounting surface to receive and mount a component thereon.

4. A fastener assembly according to claim 2 , wherein the second isolating member is located between the bracket and the retaining element.

5. A fastener assembly according to claim 1 , wherein the first and second isolating members are slideably received on the shaft.

6. A fastener assembly according to claim 1 , wherein the central portion is an interference fit in the recess.

7. A fastener assembly according to claim 1 , wherein the central portion is smaller than the hole in the bracket through which it extends to provide a clearance gap between said central portion and the bracket.

8. A fastener assembly according to claim 7 , comprising a bracket member attachable to said bracket coupled to said inner surface of an aircraft wing, said bracket member having a hole therein through which the shaft of the retaining member extends.

9. A fastener assembly according to claim 1 wherein the first and second isolating members are formed from insulating or highly resistive material.

10. A fastener assembly according to claim 1 , wherein the fastener element is a bolt and the retaining element is a nut.

11. An aircraft wing including a bracket mounted to an inner surface thereof and a component mounted to said bracket using a fastener assembly according to claim 1 .

12. A method of thermally and electrically isolating a component mounted to a bracket attached to an inner surface of the skin of an aircraft wing using a fastener assembly according to claim 1 , the method including the steps of inserting the shaft of a fastening member through a hole in said component, placing a first isolating member on the shaft against said component and inserting the shaft through a hole in said bracket such that the first isolating member is located between the component and the bracket with a central portion of said first isolating member extending through said hole, placing a second isolating member on the shaft so that the bracket is sandwiched between said first and second isolating members and so that said central portion of the first isolating member is received in a recess in said second isolating member and, threadingly engaging a retaining member with the shaft protruding through the second isolating member to clamp said first and second isolating members together against said bracket.

Assignees

• Airbus Operations Ltd

Inventors

• Warren Martin

Classifications

• Y10T29/49947

  by applying separate fastener · CPC title

• F16B33/004 Primary

  Sealing; Insulation (by means of washers F16B43/001) · CPC title

• F16B5/0241

  with the possibility for the connection to absorb deformation, e.g. thermal or vibrational · CPC title

• Y10T29/49948

  Multipart cooperating fastener [e.g., bolt and nut] · CPC title

• B64D45/02

  Lightning protectors; Static dischargers · CPC title