Abstract: A clamping block in an aircraft that is used as a stop for passenger supply units and oxygen containers, in a passenger supply channel in flight direction. The clamping block is made of plastic and features a single piece design. Installation can be done without the use of a tool by clicking the clamping block onto the passenger supply channel in an intended position. Also a system comprising the clamping block and methods for assembling and disassembling such a system.

Abstract: A system for an aircraft cabin, comprising a supply channel extending in a longitudinal direction of the aircraft cabin and including a recess along the longitudinal direction for installing supply modules, a camera module arranged at a first position of the recess of the supply channel, the camera module includes a camera to capture images in the visible spectral range and infrared spectral range, wherein the camera is directed towards passenger seats, a lighting module arranged at a second position of the recess of the supply channel, the lighting module including an infrared light source configured to emit light in the infrared spectral range, and a control device connected to the camera module and the lighting module, wherein the control device is configured to control the camera and the infrared light source. Further a method for monitoring an aircraft cabin as well as an aircraft cabin comprising such system.

Abstract: A cable guide arrangement for use in a luggage bin, in particular an aircraft luggage bin, comprises a shaft bearing element and a shaft element rotatably mounted in the shaft bearing element and through which there passes an opening extending along a central axis of the shaft element. The cable guide arrangement further comprises at least one cable guide element connected to the shaft bearing element or to the shaft element and comprising a first and a second guide portion. The first guide portion is configured to deflect a cable, extending in the radial direction with respect to the central axis of the shaft element, with a defined bending radius in the direction of the central axis of the shaft element. The second guide portion is configured to guide the cable parallel to the central axis of the shaft element through the opening extending through the shaft element.

Abstract: 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.

Abstract: A cable guide arrangement for use in a luggage bin, in particular an aircraft luggage bin, comprises a shaft bearing element and a shaft element rotatably mounted in the shaft bearing element and through which there passes an opening extending along a central axis of the shaft element. The cable guide arrangement further comprises at least one cable guide element connected to the shaft bearing element or to the shaft element and comprising a first and a second guide portion. The first guide portion is configured to deflect a cable, extending in the radial direction with respect to the central axis of the shaft element, with a defined bending radius in the direction of the central axis of the shaft element. The second guide portion is configured to guide the cable parallel to the central axis of the shaft element through the opening extending through the shaft element.

Abstract: A decompression assembly (10; 10?) for an aircraft comprises a first cabin lining element (12; 12?) having a boundary area (14; 14?) and a second cabin lining element (20; 20?) having a boundary area (22; 22?), wherein the boundary area (22; 22?) of the second cabin lining element (20; 20?) is disposed at a smaller distance from an aircraft outer skin (24; 24?) than the boundary area (14; 14?) of the first cabin lining element (12; 12?). An air discharge opening (28; 28?) is disposed between the boundary area (14; 14?) of the first cabin lining element (12; 12?) and the boundary area (22; 22?) of the second cabin lining element (20; 20?) for discharging air from a cabin (18; 18?) of the aircraft into an area (30; 30?) of the aircraft located between the cabin lining elements (12, 20; 12?, 20?) and the aircraft outer skin (24; 24?).

Abstract: 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.

Abstract: The invention relates to a cover panel for an aircraft, comprising a decompression opening that can be closed by a decompression flap that comprises a membrane, and a ventilation opening that is provided separately in the cover panel and that is permanently open. Furthermore, the invention relates to an aircraft fuselage comprising such a cover panel.

Abstract: A decompression assembly (10; 10?) for an aircraft comprises a first cabin lining element (12; 12?) having a boundary area (14; 14?) and a second cabin lining element (20; 20?) having a boundary area (22; 22?), wherein the boundary area (22; 22?) of the second cabin lining element (20; 20?) is disposed at a smaller distance from an aircraft outer skin (24; 24?) than the boundary area (14; 14?) of the first cabin lining element (12; 12?). An air discharge opening (28; 28?) is disposed between the boundary area (14; 14?) of the first cabin lining element (12; 12?) and the boundary area (22; 22?) of the second cabin lining element (20; 20?) for discharging air from a cabin (18; 18?) of the aircraft into an area (30; 30?) of the aircraft located between the cabin lining elements (12, 20; 12?, 20?) and the aircraft outer skin (24; 24?).

Abstract: The invention relates to a cover panel for an aircraft, comprising a decompression opening that can be closed by a decompression flap that comprises a membrane, and a ventilation opening that is provided separately in the cover panel and that is permanently open. Furthermore, the invention relates to an aircraft fuselage comprising such a cover panel.