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: 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 supply channel is provided with an air distribution system for vehicles, in particular for aircraft. The supply channel includes, but is not limited to an elongated housing, a hollow profile extending in longitudinal direction of the housing, and at least one air shower that includes, but is not limited to an air inlet and at least one air outlet. A generated surface of the hollow profile includes, but is not limited to a multitude of perforation openings. The at least one is designed such that in a region of the air inlet it rests tightly against the generated surface of the hollow profile. Perforation openings that do not lead to an air inlet of an air shower can be sealed off by an adhesive film or foil that has been applied. The supply channel makes possible variable positioning of air showers along the longitudinal direction of the supply channel.

Abstract: The invention relates to a fastening device for installing a hatrack on a substructure of a means of locomotion, wherein the fastening device comprises a pre-locking device and a main locking device. In this arrangement the pre-locking device is designed for automatic provisional affixation of the hatrack to the fastening device when the hatrack during an installation movement of the hatrack is moved in the direction to the fastening device. The main locking device is designed for final affixation of the hatrack to the fastening device.

Abstract: An equipment holder is provided with an optional grid function for positioning a first cabin component of an aircraft relative to a second cabin component of the aircraft and for attaching the two cabin components to each other. The equipment holder includes, but is not limited to an attachment element, a fixing element, and a position determination device. In this arrangement the attachment element is designed to attach the equipment holder to the first cabin component. The fixing element is designed to fix a position of the equipment holder relative to the second cabin component. Furthermore, the position determination device is designed to discontinuously indicate the position of the equipment holder relative to the second cabin component with a position signal.

Abstract: A universal bracket for fastening different panel elements and/or additional devices in aircraft, comprises a base plate for fastening to a substructure, a support plate connected to the base plate and a plurality of spring clips received in the support plate to provide a releasable and vibration-damping connection to the panel elements. The base plate has at least one bore screen for fastening at least one device carrier for fastening at least one additional device, in particular emergency lighting, an emergency exit sign or the like, in different positions, wherein the fastening of the device carriers is provided with a fastening device such as fastening rivets, screws or the like.

Abstract: An equipment holder is provided with an optional grid function for positioning a first cabin component of an aircraft relative to a second cabin component of the aircraft and for attaching the two cabin components to each other. The equipment holder includes, but is not limited to an attachment element, a fixing element, and a position determination device. In this arrangement the attachment element is designed to attach the equipment holder to the first cabin component. The fixing element is designed to fix a position of the equipment holder relative to the second cabin component. Furthermore, the position determination device is designed to discontinuously indicate the position of the equipment holder relative to the second cabin component with a position signal.

Abstract: A mounting fixture for detachably fastening cover plates in an aircraft. For fixing, a retaining bracket fixed on the cover plate is snap-fitted onto a retaining pin fixed on a substructure of the fuselage cell. A first holder is fixed on the retaining pin for receiving at least one connecting element, and a second holder is displaceably fitted in a forked holder on the retaining bracket. The forked holder has a roughly U-shaped form with two upright arms each connected at their lower ends by a base plate. Two connecting elements are preferably each fixed in the holders. The connecting elements are formed as electrical and/or optical sockets and plugs each with cabling attached. By swiveling a contacting lever the second holder can be moved linearly to and fro in relation to the first holder and can be introduced and pushed at least in part into the first holder whereby the final electrical and/or optical contact is produced by means of the sockets and the plugs.

Abstract: The invention relates to a holding element for fastening equipment elements to a supporting rail with a rail head having an essentially elliptical cross-sectional outer contour which is fastened to an inner supporting structure of a fuselage cell of an aircraft. The holding element has, inter alia, two resilient and pivotable clamping arms which, when “clamped on”, bear against the rail head and thereby bring about an initial fixing of the holding element on the supporting rail. The holding element can still be displaced longitudinally in this state. If the holding element is pressed further upward onto the supporting rail counter to the resilient action of two silicone buffers, a plug-in pin latches together with a spring clip and, by means of an upwardly moving locking frame, the locking of the clamping arms takes place at the same time, and therefore the clamping arms are secured against an intentional expansion in this “locked state”.

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 holding device for attaching a ceiling sign to a ceiling structure contains a base for attaching the ceiling elements and an adapter part for attaching the ceiling sign, the adapter part can be folded down from the base together with the ceiling sign in order to remove the ceiling elements.

Abstract: A supply channel is provided with an air distribution system for vehicles, in particular for aircraft. The supply channel includes, but is not limited to an elongated housing, a hollow profile extending in longitudinal direction of the housing, and at least one air shower that includes, but is not limited to an air inlet and at least one air outlet. A generated surface of the hollow profile includes, but is not limited to a multitude of perforation openings. The at least one is designed such that in a region of the air inlet it rests tightly against the generated surface of the hollow profile. Perforation openings that do not lead to an air inlet of an air shower can be sealed off by an adhesive film or foil that has been applied. The supply channel makes possible variable positioning of air showers along the longitudinal direction of the supply channel.

Abstract: The invention relates to a fastening device for installing a hatrack on a substructure of a means of locomotion, wherein the fastening device comprises a pre-locking device and a main locking device. In this arrangement the pre-locking device is designed for automatic provisional affixation of the hatrack to the fastening device when the hatrack during an installation movement of the hatrack is moved in the direction to the fastening device. The main locking device is designed for final affixation of the hatrack to the fastening device.

Abstract: A universal bracket for fastening different panel elements and/or additional devices in aircraft, comprises a base plate for fastening to a substructure, a support plate connected to the base plate and a plurality of spring clips received in the support plate to provide a releasable and vibration-damping connection to the panel elements. The base plate has at least one bore screen for fastening at least one device carrier for fastening at least one additional device, in particular emergency lighting, an emergency exit sign. or the like, in different positions, wherein the fastening of the device carriers is provided with a fastening device such as fastening rivets, screws or the like.

Abstract: A mounting fixture for detachably fastening cover plates in an aircraft. For fixing, a retaining bracket fixed on the cover plate is snap-fitted onto a retaining pin fixed on a substructure of the fuselage cell. A first holder is fixed on the retaining pin for receiving at least one connecting element, and a second holder is displaceably fitted in a forked holder on the retaining bracket. The forked holder has a roughly U-shaped form with two upright arms each connected at their lower ends by a base plate. Two connecting elements are preferably each fixed in the holders. The connecting elements are formed as electrical and/or optical sockets and plugs each with cabling attached. By swiveling a contacting lever the second holder can be moved linearly to and fro in relation to the first holder and can be introduced and pushed at least in part into the first holder whereby the final electrical and/or optical contact is produced by means of the sockets and the plugs.

Abstract: A connecting element for separably connecting a first component to a second component in a vibration damping fashion and, optionally, for compensating tolerances between the first and the second component in a compensation direction, wherein the connecting element comprises a damping ring with an inner sleeve that can be fixed in the first component, as well as a spring element with an oblong hole arranged therein, and wherein a retaining bolt can be snapped between two spring surfaces of the spring element essentially parallel to a snap-in direction. The inner sleeve comprises an insert which comprises either a cylindrical bore or an oblong hole. Alternatively, the connecting element can be respectively realized for producing connections between the components with or without tolerance compensation by selecting the appropriate insert that comprises either a cylindrical bore or an oblong hole.

Abstract: The invention relates to a holding element for fastening equipment elements to a supporting rail with a rail head having an essentially elliptical cross-sectional outer contour which is fastened to an inner supporting structure of a fuselage cell of an aircraft. The holding element has, inter alia, two resilient and pivotable clamping arms which, when “clamped on”, bear against the rail head and thereby bring about an initial fixing of the holding element on the supporting rail. The holding element can still be displaced longitudinally in this state. If the holding element is pressed further upward onto the supporting rail counter to the resilient action of two silicone buffers, a plug-in pin latches together with a spring clip and, by means of an upwardly moving locking frame, the locking of the clamping arms takes place at the same time, and therefore the clamping arms are secured against an intentional expansion in this “locked state”.

Abstract: A holding device for attaching a ceiling sign to a ceiling structure contains a base for attaching the ceiling elements and an adapter part for attaching the ceiling sign, the adapter part can be folded down from the base together with the ceiling sign in order to remove the ceiling elements.

Abstract: A connecting element for separably connecting a first component to a second component in a vibration damping fashion and, optionally, for compensating tolerances between the first and the second component in a compensation direction, wherein the connecting element comprises a damping ring with an inner sleeve that can be fixed in the first component, as well as a spring element with an oblong hole arranged therein, and wherein a retaining bolt can be snapped between two spring surfaces of the spring element essentially parallel to a snap-in direction. The inner sleeve comprises an insert which comprises either a cylindrical bore or an oblong hole. Alternatively, the connecting element can be respectively realized for producing connections between the components with or without tolerance compensation by selecting the appropriate insert that comprises either a cylindrical bore or an oblong hole.