Patent ID: 8955803
Filing Date: 2015-02-17
Classification: B64C

Abstract:
1. Decompression assembly for an aircraft, comprising: a first cabin lining element extending downwardly toward a floor of a cabin of the aircraft and having a lower boundary, a second cabin lining element extending upwardly from the floor in the direction of the first cabin lining element and having an upper boundary, wherein the upper boundary of the second cabin lining element is disposed at a smaller distance from an aircraft outer skin than the lower boundary of the first cabin lining element so that, viewed from the cabin, the upper boundary of the second cabin lining element is positioned behind the lower boundary of the first cabin lining element, an air discharge opening disposed between the lower boundary of the first cabin lining element and the upper boundary of the second cabin lining element for discharging air from a cabin of the aircraft into an area of the aircraft located between the cabin lining elements and the aircraft outer skin, and a decompression element, which is adapted to release a pressure compensation opening between the cabin of the aircraft and the area of the aircraft located between the cabin lining elements and the aircraft outer skin in the event of decompression, wherein the air decompression element is disposed in an area of the aircraft that is shielded from an interior of the cabin of the aircraft by the first and/or the second cabin lining element.