Decompression panel for use in an aircraft

Patent metadata

Field	Value
Publication number	US-9751609-B2
Application number	US-201615336397-A
Country	US
Kind code	B2
Filing date	Oct 27, 2016
Priority date	Oct 25, 2013
Publication date	Sep 5, 2017
Grant date	Sep 5, 2017

Abstract

A method of installing and replacing a plurality of decompression panels into a sidewall assembly of an aircraft includes coupling a first decompression panel to at least one of a sidewall and a floor panel of the sidewall assembly. The method also includes inserting a tab of the first decompression panel into a slot of a second decompression panel. The slot is defined by a flange extending along a surface of the second decompression panel. The method further includes coupling the second decompression panel to at least one of a sidewall and a floor panel of the sidewall assembly.

First claim

What is claimed is:

1. A method of installing and replacing a plurality of decompression panels into a sidewall assembly of an aircraft, said method comprising:
coupling a first decompression panel to at least one of a sidewall and a floor panel of the sidewall assembly;
inserting a tab of the first decompression panel into a slot of a second decompression panel, wherein the tab is arcuate to facilitate installation of the first decompression panel, wherein the slot is defined by a flange extending along a surface of the second decompression panel; and
coupling the second decompression panel to at least one of a sidewall and a floor panel of the sidewall assembly.

2. The method in accordance with claim 1 , wherein inserting the tab comprises deforming the flange to enable the slot to receive the tab.

3. The method in accordance with claim 2 , wherein deforming the flange comprises deforming the flange along a channel formed through the flange, wherein the channel facilitates deformation of the flange.

4. The method in accordance with claim 3 , further comprising returning the flange to a pre-deformed configuration to secure the tab within the slot.

5. The method in accordance with claim 1 , further comprising coupling a clamping device to the first decompression panel to secure the first decompression panel to the second decompression panel.

6. The method in accordance with claim 5 , wherein coupling the clamping device comprises coupling the clamping device to the first decompression panel and the floor panel.

7. The method in accordance with claim 1 , further comprising removing the first decompression panel from the second decompression panel.

8. The method in accordance with claim 7 , wherein removing the first decompression panel from the second decompression panel comprises removing the tab from within the slot.

9. The method in accordance with claim 8 , wherein removing the tab from within the slot comprises rotating the tab of the first decompression panel.

10. The method in accordance with claim 8 , wherein removing the tab from within the slot comprises deforming the flange to enlarge the slot.

11. The method in accordance with claim 1 , wherein the first decompression panel and the second decompression panel are coupled such that that a cabin-facing surface of the first decompression panel is flush with a cabin-facing surface of the second decompression panel.

12. A method of securing and separating a first decompression panel of an aircraft sidewall assembly and a second decompression panel of the sidewall assembly, said method comprising:
deforming a flange on the second decompression panel, wherein deforming the flange comprises deforming the flange along a channel formed through the flange, wherein the channel facilitates deformation of the flange;
inserting a tab of the first decompression panel into a slot of the second decompression panel, wherein the slot is defined by the flange extending along a surface of the second decompression panel; and
releasing the flange to secure the tab within the slot.

13. The method in accordance with claim 12 further comprising coupling a clamping device to the first decompression panel to secure the first decompression panel to the second decompression panel.

14. The method in accordance with claim 12 , wherein said body portion further comprises an upper edge and an opposing lower edge, said flange being evenly spaced between said upper and said lower edges.

15. The method in accordance with claim 12 , further comprising removing the first decompression panel from the second decompression panel.

16. The method in accordance with claim 15 , wherein removing the first decompression panel from the second decompression panel comprises removing the tab from within the slot.

17. The method in accordance with claim 16 , wherein removing the tab from within the slot comprises rotating the tab of the first decompression panel.

18. The method in accordance with claim 16 , wherein removing the tab from within the slot comprises rotating the flange to enlarge the slot.

19. An aircraft comprising:
a side wall;
a floor panel;
a decompression panel coupled between said side wall and said floor panel, said decompression panel comprising:
a body portion comprising a first end and a second end opposing said first end;
a tab extending along said first end, wherein said tab is arcuate to facilitate installation of said decompression panel; and
a flange extending from said body portion along said second end, at least a portion of said flange extending along a surface of said body portion such that a slot is defined between said portion of said flange and said surface of said body portion at said second end; and

a clamping device coupled to said decompression panel and at least one of said side wall and said floor panel, said clamping device configured to secure said decompression panel.

Assignees

• Boeing Co

Inventors

• Perkins Thomas
• Olliges Michael J
• Loken Allan A
• Arm Hannah Rebecca
• Glaze Tatum Jeremy Ryan

Classifications

• B64C1/18 Primary

  Floors · CPC title

• B32B3/06

  for securing layers together; for attaching the product to another member, e.g. to a support {, or to another product, e.g. groove/tongue, interlocking} · CPC title

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B64C1/069 Primary

  Joining arrangements therefor · CPC title

• B64C2001/009

  comprising decompression panels or valves for pressure equalisation in fuselages or floors · CPC title