Airbus Operations Gmbh

Airbus (sas)

Patrique Doemeland

Florian Schuephaus

Silvan Fiedler

Michael Auburger

Thomas Bock

Jens Voss

Brigitte Gerner

Ingo Roth

Markus Horst

An aircraft interior component system includes an aircraft interior component, a first structure holder fastened to an element of the aircraft structure, and a first component holder fastened to the aircraft interior component. The first component holder is fastened to the aircraft interior component in a first region thereof which faces an aircraft cabin ceiling when the aircraft interior component is mounted in an aircraft. The first structure holder and the first component holder attach the aircraft interior component in a suspended manner to the element, such that a mounting gap is present, at least in a second region of the aircraft interior component facing an aircraft cabin floor when the aircraft interior component is mounted in an aircraft, between a rear side of the aircraft interior component and an aircraft component opposite the rear side of the aircraft interior component.

Aircraft interior component system and method for mounting an interior component system in an aircraft

A decompression assembly (') for an aircraft comprises a first cabin lining element (&#x2032;) having a boundary area (&#x2032;) and a second cabin lining element (&#x2032;) having a boundary area (&#x2032;), wherein the boundary area (&#x2032;) of the second cabin lining element (&#x2032;) is disposed at a smaller distance from an aircraft outer skin (&#x2032;) than the boundary area (&#x2032;) of the first cabin lining element (&#x2032;). An air discharge opening (&#x2032;) is disposed between the boundary area (&#x2032;) of the first cabin lining element (&#x2032;) and the boundary area (&#x2032;) of the second cabin lining element (&#x2032;) for discharging air from a cabin (&#x2032;) of the aircraft into an area (&#x2032;) of the aircraft located between the cabin lining elements (&#x2032;) and the aircraft outer skin (&#x2032;). A decompression element (&#x2032;) is adapted to release a pressure compensation opening (&#x2032;) between the cabin (&#x2032;) of the aircraft and the area (&#x2032;) of the aircraft located between the cabin lining elements (&#x2032;) and the aircraft outer skin (&#x2032;) in the event of decompression and is disposed in an area of the aircraft that is shielded from an interior of the cabin (&#x2032;) of the aircraft by the first and/or the second cabin lining element (&#x2032;).

Decompression assembly for an aircraft

A gap covering device for covering a gap between two mutually adjacent first aircraft interior panels includes a visible portion as well as a retaining portion connected to the visible portion and extending opposite the visible portion. A receiving structure is fastened to an inner surface of the visible portion and/or of the retaining portion and has a receiving contour adapted to an edge contour of the first aircraft interior panels.

Gap covering device

Gap covering device for aircraft wall panels

Growing community of inventors

Hamburg, Germany

Patrique Doemeland