Abstract: A door hinge comprises a first hinge element fastenable to a door frame and a second hinge element fastenable to a door leaf and includes first and second hinge blade. A first pivot axis is connected, when the door hinge is in a first operating condition, to first and second hinge elements such that the second hinge blade is pivotable relative to the first hinge element, in a first pivot direction, for unblocking a door aperture. The first pivot axis is decoupled from the first or the second hinge element when the door hinge is in a second operating condition. A second pivot axis is connected to the first and second hinge elements such that said first and second hinge elements are pivotable relative to one another, in a second pivot direction which is opposed to the first pivot direction, for unblocking the door aperture.

Abstract: A device (10) for the detachable connection of structural parts (80, 84) in an aircraft, comprising a clamping lever arrangement (12) associated with a first structural part (80) and a clamping pin (14) associated with a second structural part (84), wherein the clamping lever arrangement (12) comprises an eccentric shaft (20) rotatably mounted about a rotation axis (A) on the first structural part (80), a clamping lever (16) mounted eccentrically and swivellably with respect to the eccentric shaft (20) and a driving bushing (18) rotatably mounted relative to the eccentric shaft (20) about the rotation axis (A) and coupled in a geared manner to the clamping lever (16), wherein the clamping lever arrangement (12) can furthermore be displaced between a release position, a readiness position and a locking position.

Abstract: A door hinge (10) according to the invention comprises a first hinge element (12) which is fastenable to a door frame (24) and a second hinge element (14) which is fastenable to a door leaf (28) and has a first hinge blade (20) and a second hinge blade (22). A first pivot axis (32) is connected, when the door hinge (10) is in a first operating condition, to the first and second hinge elements (12, 14) in such a way that the second hinge blade (22) of the second hinge element (14) is pivotable, when the door hinge (10) is in said first operating condition, about said first pivot axis (32), relative to the first hinge element (12), in a first pivot direction (Px), for the purpose of unblocking a door aperture which is bounded by the door frame (24). The first pivot axis (32) is decoupled from the first or the second hinge element (12, 14) when the door hinge (10) is in a second operating condition.

Abstract: The invention relates to a device (10) for the detachable connection of structural parts (80, 84) in an aircraft, comprising a clamping lever arrangement (12) associated with a first structural part (80) and a clamping pin (14) associated with a second structural part (84), wherein the clamping lever arrangement (12) comprises an eccentric shaft (20) rotatably mounted about a rotation axis (A) on the first structural part (80), a clamping lever (16) mounted eccentrically and swivellably with respect to the eccentric shaft (20), and a driving bushing (18) rotatably mounted relative to the eccentric shaft (20) about the rotation axis (A) and coupled in a geared manner to the clamping lever (16), wherein the clamping lever arrangement (12) can furthermore be displaced between a release position, a readiness position and a locking position, wherein the clamping lever (16) in the release position releases the clamping pin (14) and wherein the clamping lever (16) in the locking position engages the locking pin (14)