Transport element support assembly

Patent metadata

Field	Value
Publication number	US-11168839-B2
Application number	US-201715628018-A
Country	US
Kind code	B2
Filing date	Jun 20, 2017
Priority date	Jun 20, 2017
Publication date	Nov 9, 2021
Grant date	Nov 9, 2021

Abstract

A transport element support assembly comprises a front plate, a back plate, and a grommet. The front plate has a first opening and a first set of holes. The back plate has a second opening and a second set of holes. A chamber is formed by the first opening and the second opening and is configured to hold a transport element. The grommet is positioned within the chamber. The transport element support assembly formed by the front plate, the back plate, and the grommet is configured to provide electrical isolation between the transport element and an aircraft structure.

First claim

What is claimed is:

1. A transport element support assembly comprising:
a front plate having a first opening and a first set of holes;
a back plate having a second opening and a second set of holes;
a chamber formed by the front plate and the back plate, the chamber interposed between the front plate and the back plate and configured to hold a transport element; and
a grommet positioned within the chamber, wherein the transport element support assembly formed by the front plate, the back plate, and the grommet is configured to provide electrical isolation between the transport element and an aircraft structure;
wherein a hole pattern formed by an axial alignment of the first set of holes with the second set of holes is split into a plurality of hole pattern sets, wherein each hole pattern set is configured to match a hole pattern in the aircraft structure and each hole pattern set is configured to provide a different centerline position of the transport element.

2. The transport element support assembly of claim 1 further comprising:
alignment features configured to align the front plate to the back plate such that the first set of holes remains aligned to the second set of holes.

3. The transport element support assembly of claim 2 , wherein the back plate has a flange with a circular shape and an angle configured to hold the grommet in place.

4. The transport element support assembly of claim 3 , wherein the front plate has a recess with an angle configured to hold the grommet in place.

5. The transport element support assembly of claim 1 further comprising:
a key representing a configuration of the transport element support assembly when a centerline of the transport element is in a nominal position.

6. The transport element support assembly of claim 1 , wherein the front plate and the back plate abut each other.

7. The transport element support assembly of claim 1 , wherein a rotation of the transport element support assembly adjusts a centerline of the transport element in at least one of a lateral direction or a vertical direction.

8. The transport element support assembly of claim 7 , wherein the rotation of the transport element support assembly adjusts the centerline of the transport element in at least one of the lateral direction or the vertical direction within selected tolerances.

9. The transport element support assembly of claim 8 , wherein the rotation creates a desired fit between the transport element support assembly and the aircraft structure, and further comprising:
a fastener system configured to secure the transport element support assembly to the aircraft structure after the rotation is completed.

10. A fluid system for an aircraft, the fluid system comprising:
a tube; and
a tube support assembly comprising:
a front plate having a first opening and a first set of holes;
a back plate having a second opening and a second set of holes;
a chamber formed by interfacing the front plate and the back plate, wherein the chamber is interposed between the front plate and the back plate and is configured to hold the tube; and
a grommet positioned within the chamber, wherein the tube support assembly formed by the front plate, the back plate, and the grommet is configured to provide electrical isolation between the tube and an aircraft structure;
wherein a hole pattern formed by an axial alignment of the first set of holes with the second set of holes is split into a plurality of hole pattern sets, wherein each hole pattern set is configured to match a hole pattern in the aircraft structure and each hole pattern set is configured to provide a different centerline position of the tube.

11. The fluid system of claim 10 , wherein the tube support assembly further comprises:
alignment features configured to align the front plate to the back plate such that the first set of holes remains aligned to the second set of holes.

12. The fluid system of claim 11 , wherein the tube support assembly further comprises:
a key representing a configuration of the tube support assembly when a centerline of the tube is in a nominal position.

13. The fluid system of claim 10 , wherein the front plate and the back plate are positioned on a same side of the aircraft structure.

14. The fluid system of claim 13 , wherein a rotation of the tube support assembly adjusts a centerline of the tube in at least one of a lateral direction or a vertical direction within selected tolerances to create a desired fit between the tube support assembly and the aircraft structure.

15. The fluid system of claim 10 , wherein the aircraft structure is a rib and the tube support assembly is configured to provide electrical isolation between the tube and the rib during an electromagnetic event.

16. The fluid system of claim 10 , wherein the back plate has a flange with a circular shape and an angle configured to hold the grommet in place.

17. The fluid system of claim 15 , wherein the front plate has a recess with an angle configured to hold the grommet in place.

18. The fluid system of claim 10 , wherein the front plate and the back plate abut each other.

19. The fluid system of claim 14 , wherein the rotation of the tube support assembly adjusts the centerline of the tube in at least one of the lateral direction or the vertical direction.

20. The fluid system of claim 14 , further comprising:
a fastener system configured to secure the tube support assembly to the aircraft structure after the rotation is completed.

Assignees

• Boeing Co

Inventors

• Cheatham Benjamin Curtis
• Gilbertson Michael Leslie

Classifications

• F16L5/08 Primary

  by means of axial screws compressing a ring or sleeve · CPC title

• F16L5/027

  by means of a joint of the quick-acting type · CPC title

• F17C2205/0184

  Attachments to the ground, e.g. mooring or anchoring · CPC title

• B64D45/02

  Lightning protectors; Static dischargers · CPC title

• F17C5/06 Primary

  for filling with compressed gases · CPC title