Decompression panel assembly and methods of installation

Patent metadata

Field	Value
Publication number	US-10899428-B2
Application number	US-201916674727-A
Country	US
Kind code	B2
Filing date	Nov 5, 2019
Priority date	Mar 30, 2016
Publication date	Jan 26, 2021
Grant date	Jan 26, 2021

Abstract

A method of installing a decompression panel assembly in an aircraft. The decompression panel assembly includes a body portion, a baffle member, and a panel member. The method includes coupling the body portion to the panel member, wherein the body portion includes a plurality of frame members defining a plurality of openings in the body portion. The method also includes coupling the baffle member to the plurality of frame members such that the baffle member removably obstructs at least one opening of the plurality of openings. The baffle member is integrally formed with the plurality of frame members and is configured for at least partial displacement from the at least one opening during a decompression event. The decompression panel assembly is then coupled between a sidewall and a floor panel of the aircraft.

First claim

What is claimed is:

1. A method of installing a decompression panel assembly in an aircraft, the decompression panel assembly including a body portion, a baffle member, and a panel member, said method comprising:
coupling the body portion to the panel member, wherein the body portion includes a plurality of frame members defining a plurality of openings in the body portion;
coupling the baffle member to the plurality of frame members such that the baffle member removably obstructs at least one opening of the plurality of openings, wherein the baffle member is integrally formed with the plurality of frame members and is configured for at least partial displacement from the at least one opening during a decompression event, wherein the baffle member includes a plurality of frangible seams configured to yield during the decompression event; and
coupling the decompression panel assembly between a sidewall and a floor panel of the aircraft.

2. The method in accordance with claim 1 , wherein the frangible seams form an entire perimeter of each detachable section such that each detachable section is detached from the plurality of frame members during a decompression event to enable air flow through the plurality of openings.

3. The method in accordance with claim 1 , wherein the frangible seams form at least a portion of a perimeter of each detachable section such that each detachable section is at least partially detached from the plurality of frame members during a decompression event to enable air flow through the plurality of openings.

4. The method in accordance with claim 3 , wherein each detachable section is hingedly coupled to the plurality of frame members.

5. The method in accordance with claim 1 , wherein the plurality of frame members comprise an inboard edge and an outboard edge, wherein the baffle member is integrally formed with the plurality of frame members proximate the outboard edge.

6. The method in accordance with claim 1 , wherein the baffle member obstructs each opening of the plurality of openings.

7. The method in accordance with claim 1 , wherein the baffle member obstructs fewer than all of the plurality of openings.

8. The method in accordance with claim 1 , wherein the baffle member and the plurality of frame members are formed from the same material.

9. A method of installing a decompression panel assembly in an aircraft, the decompression panel assembly including a body portion, a baffle member, and a panel member, said method comprising:
integrally forming the body portion with a plurality of frame members that define a plurality of openings in the body portion;
releasably coupling the baffle member to the plurality of frame members such that the baffle member removably obstructs at least one opening of the plurality of openings, wherein the baffle member is integrally formed with the plurality of frame members and is configured for at least partial displacement from the at least one opening during a decompression event, wherein the baffle member includes a plurality of frangible seams configured to yield during the decompression event; and
coupling the decompression panel assembly between a sidewall and a floor panel of the aircraft.

10. The method in accordance with claim 9 , wherein the frangible seams form an entire perimeter of each detachable section such that each detachable section is detached from the plurality of frame members during a decompression event to enable air flow through the plurality of openings.

11. The method in accordance with claim 9 , wherein the frangible seams form at least a portion of a perimeter of each detachable section such that each detachable section is at least partially detached from the plurality of frame members during a decompression event to enable air flow through the plurality of openings.

12. The method in accordance with claim 11 , wherein each detachable section is hingedly coupled to the plurality of frame members.

13. The method in accordance with claim 9 , wherein the plurality of frame members comprise an inboard edge and an outboard edge, wherein the baffle member is integrally formed with the plurality of frame members proximate the outboard edge.

14. The method in accordance with claim 9 , wherein the baffle member obstructs each opening of the plurality of openings.

15. The method in accordance with claim 9 , wherein the baffle member obstructs fewer than all of the plurality of openings.

16. The method in accordance with claim 9 , wherein the baffle member and the plurality of frame members are formed from the same material.

17. A method of installing a decompression panel assembly in an aircraft, the decompression panel assembly including a body portion, a baffle member, and a panel member, said method comprising:
coupling the body portion to the panel member, wherein the body portion includes a plurality of frame members defining a plurality of openings in the body portion;
coupling the baffle member to the plurality of frame members such that the baffle member removably obstructs at least one opening of the plurality of openings, wherein the baffle member is integrally formed with the plurality of frame members and is configured for at least partial displacement from the at least one opening during a decompression event, wherein the baffle member includes a plurality of frangible seams that define a plurality of detachable sections each associated with an opening of the plurality of openings; and
coupling the decompression panel assembly between a sidewall and a floor panel of the aircraft.

18. A method of installing a decompression panel assembly in an aircraft, the decompression panel assembly including a body portion, a baffle member, and a panel member, said method comprising:
integrally forming the body portion with a plurality of frame members that define a plurality of openings in the body portion;
releasably coupling the baffle member to the plurality of frame members such that the baffle member removably obstructs at least one opening of the plurality of openings, wherein the baffle member is integrally formed with the plurality of frame members and is configured for at least partial displacement from the at least one opening during a decompression event, wherein the baffle member includes a plurality of frangible seams that define a plurality of detachable sections each associated with an opening of the plurality of openings; and
coupling the decompression panel assembly between a sidewall and a floor panel of the aircraft.

Assignees

• Boeing Co

Inventors

• Sterling David E
• Griffing James Scott
• Perkins Thomas Seth
• Beck Hannah Katherine
• Weston Adam Robert
• Walter Sara Lynn

Classifications

• B64C2001/009

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

• B64F5/10

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

• B64C1/18 Primary

  Floors · CPC title