Aircraft fuel tank isolator

Patent metadata

Field	Value
Publication number	US-11435013-B2
Application number	US-202117362952-A
Country	US
Kind code	B2
Filing date	Jun 29, 2021
Priority date	Mar 29, 2018
Publication date	Sep 6, 2022
Grant date	Sep 6, 2022

Abstract

An isolator for an aircraft fuel tank configured to separate an electrically conductive internal panel of the fuel tank from an electrically conductive pipe that passes through the panel. The isolator includes: a plurality of first attachment points for attaching the isolator to the panel, a plurality of second attachment points for attaching the isolator to the pipe, and an aperture defined by an outer wall and extending from a first side of the isolator to a second side of the isolator. The aperture is configured to receive the pipe in use, wherein the isolator is formed of a non-electrically conductive material.

First claim

The invention claimed is:

1. An isolator for an aircraft fuel tank, the isolator configured to separate an electrically conductive internal panel of the fuel tank from an electrically conductive pipe that passes through the panel, the isolator comprising:
a plurality of first attachment points configured to attach the isolator to the panel,
a plurality of second attachment points configured to attach the isolator to the pipe, and
an aperture defined by an outer wall and extending from a first side of the isolator to a second side of the isolator, the aperture configured to receive the pipe,
wherein the isolator comprises a non-electrically conductive material, and
wherein each of the plurality of first attachment points is configured to receive a fastener for fastening the isolator to the panel and each of the plurality of second attachment points is configured to receive a fastener for fastening the isolator to the pipe.

2. The isolator according to claim 1 , wherein the plurality of first attachment points are oriented in an opposite direction to the plurality of second attachment points.

3. The isolator according to claim 1 , wherein the plurality of first attachment points and the plurality of second attachment points are positioned on a flange extending from the outer wall of the aperture.

4. The isolator according to claim 3 , wherein the flange is chamfered around the first and second attachment points.

5. The isolator according to claim 1 , wherein each of the first attachment points are positioned at substantially the same radial distance from the aperture.

6. The isolator according to claim 1 , wherein each of the second attachment points are positioned at substantially the same radial distance from the aperture.

7. The isolator according to claim 1 , wherein each of the first and second attachment points are positioned at substantially the same radial distance from the aperture.

8. The isolator according to claim 1 , wherein the first and second attachment points are alternately spaced around the aperture.

9. The isolator according to claim 1 , wherein the first and second attachment points are equally spaced around the aperture.

10. The isolator according to claim 1 , wherein the isolator is formed from only the non-electrically conducting material.

11. An isolation system comprising:
the isolator according to claim 1 ,
a plurality of first bolts each received by a respective first attachment point, and
a plurality of second bolts each received by a respective second attachment point.

12. The isolation system according to claim 11 , wherein at least one of the plurality of first and second bolts are electrically-conductive,
the isolation system comprising a non-electrically conductive sealant covering the head of the at least one of the plurality of first and second bolts.

13. An aircraft comprising the isolator according to claim 1 .

14. An aircraft according to claim 13 , further comprising wings formed from a non-electrically conductive material.

15. An apparatus comprising:
the isolator according to claim 1 , and
an electrically conductive pipe.

16. A method of isolating an electrically conductive internal panel of an aircraft fuel tank from an electrically conductive pipe that passes through the panel, the method comprising:
passing the pipe through a tube of a non-electrically conductive material isolator,
passing the tube through an aperture in the panel,
rigidly attaching the isolator to a pipe fitting fixed to the pipe with a first fastener, the first fastener received by a first attachment point of the isolator, and
rigidly attaching the isolator to the panel with a second fastener, the second fastener received by a second attachment point of the isolator.

17. The method according to claim 16 , wherein the first and second fasteners are electrically conductive, and wherein the method comprises:
electrically insulating the first fastener from the panel, and
electrically insulating the second fastener from the pipe.

Assignees

• Airbus Operations Ltd

Inventors

• West Nicholas

Classifications

• F16L5/10

  by using sealing rings or sleeves only · CPC title

• F16L5/00

  Devices for use where pipes, cables or protective tubing pass through walls or partitions (installations of electric cables or lines through walls, floors or ceilings H02G3/22) · CPC title

• B64D37/04

  Arrangement thereof in or on aircraft · CPC title

• B64D37/32 Primary

  Safety measures not otherwise provided for, e.g. preventing explosive conditions · CPC title

• B64D37/00 Primary

  Arrangements in connection with fuel supply for power plant (refuelling during flight B64D39/00) · CPC title