Patent ID: 8959872
Filing Date: 2015-02-24
Classification: B29D,B64C,E04F,Y10T

Abstract:
1. A method of constructing a raised panel assembly, the method comprising: locating a first raised panel and a second raised panel within an aircraft to produce a gap between a first edge of the first raised panel and a second edge of the second raised panel, wherein at least one of the first raised panel and the second raised panel is a composite panel, wherein the composite panel includes a first surface material that comprises a first surface of the composite panel, a second surface material that comprises a second, opposed, surface of the composite panel, and a core material that extends between the first surface material and the second surface material; placing a flow-limiting structure within the raised panel assembly to form a boundary of a channel that is configured to receive a sealant material, wherein the channel includes a portion of the gap; placing an elongate disassembly aid within the gap, wherein the elongate disassembly aid is configured to decrease a time needed to disassemble the first raised panel from the second raised panel by at least one of slicing, cutting, severing, tearing, and splitting at least a portion of the sealant material that extends between the first raised panel and the second raised panel; and applying the sealant material to the channel, wherein the flow-limiting structure limits a flow of the sealant material therepast, wherein the sealant material forms an adhesive bond with the first raised panel and the second raised panel, and further wherein the applying is performed after the placing.