Abstract: A device (100) for securing a support structure such as solar module-carrier (12) to a flat roof (16) which is provided with a non-bearing insulation layer (24) covered by a sealing strip (22). The device (100) has an upper connection element (150) for the support structure and a spacer member (120) which can be guided through an opening (26) in the insulation layer (24) in order to support the connection element (150) on a roof substructure (17). The spacer member (120) is anchored by a plurality of anchoring parts (28) on the roof substructure (17). The connection element (150) comprises an upper and a lower connection flange (152, 154) between which the sealing strip (22) is clamped. The spacer member (120) is designed as a profile or hollow-profile part which can be cut to length as required and is produced as an extrusion part from a thermal insulation material.

Abstract: A self-boring screw (2) having a boring section (6) attached to the free end of the screw shaft (4), two vanes (12) radially protruding from the boring section, the edges of the vanes facing toward the boring tip (8) of the boring section (6) being configured as boring blades (13). The boring section (6) includes a chip discharge zone (14) that is configured such that the edges of the vanes (12) facing toward the boring tip (8) forms a cutting point (S) with a boring radius (16), the cutting point having a distance (A) to the screw shaft (4) that is at least ? of the cutting edge length of the bore tip (8). The chip discharge zone (14) makes it possible that the chips produced by the boring blade (10) at the boring tip (8) can be discharged freely and without buildup.

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 fastening system (10) for hanging mountable overhead containers (12) such as baggage compartments in an airplane. The system includes at least one pair of support lugs (20, 22) mounted on a support structure (14) or on an overhead container (12). The support lugs (20, 22) can be detachably connected to each other by a pin (30) that can be drawn back in a pin guide (40) and thereby spring-loaded in the exit direction. When the support lug (22) attached to the overhead container (12) is inserted into the support lug (20) having the pin guide (40) when installing the container, the pin (30) is unlatched in the pin guide (40) and automatically moves out into the support eye (22) attached to the overhead container (12). Using a lever joined (60) to the pin guide (40) by a hinge, the pin (30) can be moved out completely into an end position, and locked in said position. In order to remove the overhead container (12), the lever (60) must simply be pivoted back.

Abstract: A device for processing a belt strap for storing screws, in which the belt strap has a flat, U-shaped cross section that has a periphery that has a ratio of no more than 11:10 relative to the non-flanged belt. A guide device for the belt strap guides and holds the belt strap. The screws can be pressed out from the upper side of the belt strap. The guide device (3) has two guide slits (10) receiving the belt strap (2) in at least the region of the flanges (4), each slit being L-shaped in cross section and each having a contact surface (5) for the underside (6) of the belt (20) and a guide rib (11) extending across the flange (4).

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 self-tapping screw having a boring part and a threaded shaft for fixing a panel-type object to a preferably metallic substructure is provided. The screw is configured in such a way that it produces a through hole in the panel type object, said hole accommodating the shaft with a degree of play and so that it produces a bore in the substructure into which the thread on the shaft cuts a counter-thread. The boring part includes a boring tip that is located eccentrically in relation to the longitudinal axis of the screw. The tip centers the screw during the positioning operation in such a way that the boring part executes a circular displacement about the boring tip, which expands the through hole to the desired size, whereas the bore in the substructure is produced with the diameter of the boring part.

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 screw (60) is provided, having a shaft (32) and a head (66), for fastening a component onto a substructure utilizing a tightly pressing conical sealing disk (50) against the component. The screw head (66) is configured at the bottom (64) thereof around the shaft (32) as a cone that is tapered in the direction of the top (68) of the screw head (66). The cone angle of the conical sealing disk (50) measured against a perpendicular line to the disk axis is equal to, or larger than the cone angle (alpha) of the screw head (66), which is measured against a perpendicular line to the screw axis. When the screw (60) is tightened, the conical bottom (64) of the screw head (66) and the conical top (58) of the sealing disk (50) are in mutual surface contact with each other. This maintains a sealing connection. Through the conical configuration of the bottom (64) of the screw head (66) the so-called “cupping” of the sealing disk (50) is prevented when the screw (60) is tightened.

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 washer (14) and a threaded assembly (22) between a screw (30) and a workpiece (42) are provided. The washer (14) is offset up to an angle (?) with respect to a flat initial state, such that the washer has an insert thickness (De) that is substantially greater than the initial thickness (Da) thereof. The washer (14) is made of a malleable material. The length (Lg) of an unthreaded shank section (40) of the screw (30) is smaller than the sum of the thickness (Dw) of the workpiece (42) and the insert thickness (De) of the washer (14), and essentially not smaller than the sum of the thickness (Dw) of the workpiece (14) and the insert thickness (Da) of the washer (14). When the last thread of the screw (30) leaves the workpiece (42) on being screwed in, the force previously exerted on the washer (14) by the feed of the screw is zero.

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 torsion bar is provided, for application in belt winders for safety belts, provided on the end sections thereof with embodiments of drive and/or locking elements, for positive connection to corresponding devices. The torsion bar and the drive and/or locking elements provided on the ends thereof is produced in one piece from a non-ferrous metal, using varying impact extrusions in order to achieve different torques with constant dimensions or the drive and/or locking elements with various diameters for the torsion bar.

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: 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 threaded element (1) is provided having at least two slots (3), notches, grooves or the like that intersect the thread (2). The slots (3), notches, grooves or the like are configured in relation to the thread (2) so that they intersect the thread (2) to form a sharp cutting edge on the thread flanks (4), thus preventing reverse rotation. The slots, notches or grooves have no more than 25-times the pitch and the same rotational direction as the thread.

Abstract: A self-boring screw (2) having a boring section (6) attached to the free end of the screw shaft (4), two vanes (12) radially protruding from the boring section, the edges of the vanes facing toward the boring tip (8) of the boring section (6) being configured as boring blades (13). The boring section (6) includes a chip discharge zone (14) that is configured such that the edges of the vanes (12) facing toward the boring tip (8) forms a cutting point (S) with a boring radius (16), the cutting point having a distance (A) to the screw shaft (4) that is at least ? of the cutting edge length of the bore tip (8). The chip discharge zone (14) makes it possible that the chips produced by the boring blade (10) at the boring tip (8) can be discharged freely and without buildup.

Abstract: A retaining cam (20) for a rotatable fastener for connecting components (16, 17) is provided. The retaining cam (20) has a housing (22) pivotally supported on a base plate (24), by which the retaining cam (20) can be fixedly connected to one (17) of the components (16, 17). A screw (30) is secured rotationally fixed in the housing (22). A fastener bolt (40) rotatably connected to another (16) of the components (16, 17) can be screwed onto the screw (30). Spring elements are associated with the screw (30) for generating an elastic pretension for securing the fastener bolt (40) against rotation. The housing (22) is pivotally supported on the base plate (24) by a spherical washer (50). An angle deviation between the center axes of the retaining cam (20) and the fastener bolt (40) can be compensated for by pivoting the retaining cam on the spherical washer (50) while maintaining full-surface contact of the retaining cam (20).