Patent ID: 9022321
Filing Date: 2015-05-05
Classification: B64C,B64D

Abstract:
1. A decompression arrangement for an aircraft, comprising: a first cabin lining element that extends, in at least some sections, substantially parallel with an aircraft outer skin and includes a lower edge region provided at a distance from a floor of the aircraft, wherein the first cabin lining element extends from the lower edge region generally upwardly in a direction of a ceiling of the aircraft; a second cabin lining element positioned between the first cabin lining element and the aircraft outer skin, wherein the second cabin lining element includes an upper edge region positioned between the lower edge region of the first cabin lining element and the aircraft outer skin, and wherein the second cabin lining element extends downwardly from the upper edge region in a direction of the floor of the aircraft, wherein the first and second cabin lining elements delimit an inner region of a cabin of the aircraft; an air discharge opening, which is arranged between the lower edge region of the first cabin lining element and the upper edge region of the second cabin lining element and which is adapted, in the normal operation of the aircraft, to discharge air from the inner region of the cabin into a region of the aircraft lying between the first and second cabin lining elements and the aircraft outer skin; and a decompression element, which is integrated in the second cabin lining element and has a flap which, in a closed position, closes a pressure equalizing opening formed in the decompression element, wherein the flap is configured to, if a first predetermined differential pressure acts on the decompression element, pivot about an axis in a first direction from the closed position into a first open position, wherein in the first open position the flap opens the pressure equalizing opening formed in the decompression element, wherein the flap is configured to, if a second predetermined differential pressure acts on the decompression element, pivot about the axis in a second direction opposite the first direction into a second open position, wherein in the second open position the flap opens the pressure equalizing opening formed in the decompression element, and wherein the decompression element is positioned relative to the first and the second cabin lining elements in such a manner that the flap in its second open position keeps clear a through-flow cross-section of the air discharge opening.