Abstract: A fastening system for overhead storage bins on a supporting structure, having at least one pair of suspension eye lugs attached to a supporting structure or the overhead storage bins. The suspension eye lugs are detachably interconnected by a main pin, with receivers for the main pin being in alignment in a mounting position of the overhead storage bin. The main pin is spring-loaded in a main pin guide toward the other suspension eye lug and has, with the overhead storage bin not yet mounted, an end position in which the main pin is deployed from the main pin guide. A portion of the suspension eye lugs has a sloping ramp that allows the main pin to be deployed in the receiver of the other suspension eye lug by action of preload during upward movement of the overhead storage bin and its suspension eye lug into the mounting position.

Abstract: A locking mechanism (100) and a lock (110) are provided. The locking mechanism (100) comprises a push-button (148) connected to a freewheel (154) via a traction cable, with the freewheel being connected to a drive device (160) of the lock (110). A baggage compartment in the cabin of an airplane usually comprises two locks (110) of this type which can be unlocked by the push-button (148). A freewheel (154) arranged between the push-button (148) and the lock (110) ensures that the push-button (148) remains in a pushed position as long as each lock (110) allocated to the baggage compartment is not in a correctly locked position. It can be identified from the position of the push-button of the baggage compartment whether both locks of the baggage compartment are correctly snapped in.

Abstract: A hinge for a packaging or cargo box or the like, having a first and a second hinge leaf, the second hinge leaf has a first bushing and a second bushing located at a distance therefrom, between which a bushing of the first hinge leaf can be rotated about a mutual hinge axis. An axial tube is rotationally fixed to the bushing of the first hinge leaf and is pivot-supported in the bushings of the second hinge leaf. A torsion spring is disposed in the axial tube and attached to one end of the axial tube. A torque support connects the other end of the torsion spring to the second hinge leaf in a rotationally fixed manner. A damper for the hinge movement is connected to the second hinge leaf and the axial tube.

Abstract: A lock for a luggage box installed overhead in the cabin of an aircraft, including a stationary housing and a cover that can move about a rotary axis. The lock includes a locking pin device that can be mounted on the housing, having two locking pins (32, 32b) disposed in parallel, a catch (20) that can be mounted on the cover and that has two locking hooks (55, 55b) that can be pivoted about a pivot axis (22, 22b) for receiving the locking pins (32, 32b) for locking the lock (10), and a manually actuatable drive device (60) for jointly pivoting the locking hooks (51, 51b) away from the locking pins (32, 32b) for unlocking the lock (10). The drive device (60) has a gear rack (62) and a sliding element (64) that can be linearly displaced against the pressure of a spring element (70).

Abstract: A connecting device (10) is provided for releasably connecting a fitting piece, such as an interior lining, to a supporting structure, such as a fuselage. The connecting device (10) includes a plug-in holding mechanism (50) including a bushing piece (52) and a connecting pin (75) that can be releasably locked therein. A bent connecting arm (60), to which the connecting pin is fastened, is releasably fastened to a structural holder (40) mounted on the supporting structure. In one position, the connecting arm (60) is plugged into the structural holder (40) and is releasably locked therein. In a second position (125), in which the connecting arm (60) is rotated 180° about the longitudinal axis thereof, an electrical contact device (90) is additionally inserted between the connecting arm (60) and the bushing piece (52).

Abstract: A holding device (10) is provided for use during the installation of a component (60) to be fastened vertically to a support structure (50) such as that of an aircraft, for example a cabin sidewall lining part. The holding device (10) includes a hook (12) and an eyelet (14) receiving the hook, the hook and eyelet being designed so that they can be fastened to the support structure (50) or the component (60). The eyelet (14) has at least one elastically resilient element for the movable mutual support of the eyelet (14) and hook (12). The holding device (10) facilitates the fastening of a perpendicularly installed component (60). The elastically resilient element allows the component (60) to be pre-positioned in a nominal position.

Abstract: A hinge for a packaging or cargo box or the like, having a first and a second hinge leaf, the second hinge leaf has a first bushing and a second bushing located at a distance therefrom, between which a bushing of the first hinge leaf can be rotated about a mutual hinge axis. An axial tube is rotationally fixed to the bushing of the first hinge leaf and is pivot-supported in the bushings of the second hinge leaf. A torsion spring is disposed in the axial tube and attached to one end of the axial tube. A torque support connects the other end of the torsion spring to the second hinge leaf in a rotationally fixed manner. A damper for the hinge movement is connected to the second hinge leaf and the axial tube.

Abstract: A plug-type mount is provided for releasably holding an equipment part such as a panel or an interior trim part on a sub-frame such as a fuselage. The plug-type mount (5) includes a first holder (30) and a second holder (35) which can be fastened to one another with the aid of a holding pin (11) and a housing (20), in which the holding pin (11) can be releasably locked. The holders (30, 35) carry in each case at least one electrical contact (33, 34) and are configured in such a way that, in the case of the holding pin (11) being locked in the housing (20), the holders (30, 35) are fastened to one another and the electrical contacts (33, 34) are connected electrically. Excessive cable lengths can be avoided by the preferable use of the plug-type mount (5) in an airplane because the electrical connection is also produced and disconnected as the mechanical connection is produced and disconnected.

Abstract: A plug-type mount is provided for releasably holding an equipment part such as a panel or an interior trim part on a sub-frame such as a fuselage. The plug-type mount (5) includes a first holder (30) and a second holder (35) which can be fastened to one another with the aid of a holding pin (11) and a housing (20), in which the holding pin (11) can be releasably locked. The holders (30, 35) carry in each case at least one electrical contact (33, 34) and are configured in such a way that, in the case of the holding pin (11) being locked in the housing (20), the holders (30, 35) are fastened to one another and the electrical contacts (33, 34) are connected electrically. Excessive cable lengths can be avoided by the preferable use of the plug-type mount (5) in an airplane because the electrical connection is also produced and disconnected as the mechanical connection is produced and disconnected.

Abstract: A plug mounting (50) is provided as a combination of a plug (10) and a mount (30), for the detachable mounting of an equipment part, such as an inner panel, to a supporting frame, such as an aircraft fuselage. The plug (10) has a mounting pin (12), which has an annular groove (25) on one end, which can be engaged with a slide (34) of the mount (30), which is under spring pretension. The mounting pin (12) can be connected to the foundation by a damping element. The mount (30) is fastened to the housing (32) on the equipment part. The mount (30) has an eccentric lever (42) for unlocking the plug (10) by displacing the slide (34) against the spring pretension. The arrangement is made so that only the mounting pin (12) of the plug (10) needs to be inserted into the opening of the housing of the mount (30).

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 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: Fastening arrangement for a lightweight structural component (1) is provided, including a housing (2) which is incorporated in the lightweight structural component (1), with the housing having a bore (3) with an internal thread (4), and a screw element (5). The housing (2) is formed in one piece. A threaded insert (6) formed as a helically wound spring is introduced into the bore (3) with a force fit and/or form fit, the internal boundary of which forms the internal thread (4) to allow the screw element (5) provided with an external thread (7) to be threadingly engaged.