Patent ID: 8776353

Claim:
An attachment system for attaching an aircraft interior fitting element to an aircraft structure, wherein the attachment system comprises: an aircraft interior fitting element; a first latching device rigidly coupled with one of the aircraft interior fitting element or the aircraft structure, the first latching device comprising: a first latching element configured for attaching the first latching device to a first fixation device; a first trigger element; and a first retaining element; wherein the first latching element comprises a groove corresponding to the first trigger element and the first retaining element; wherein the first trigger element is configured to releasably secure the first latching element in an unlatched first state by engaging into the groove of the first latching element; wherein the first retaining element is configured to releasably secure the first latching element in a latched second state by engaging into the groove of the first latching element; wherein the first latching element is movable from the unlatched first state to the latched second state by activating the first trigger element; and wherein the first latching element is movable from the latched second state to the unlatched first state by activating the first retaining element; a second latching device rigidly coupled with one of the aircraft interior fitting element or the aircraft structure; the first fixation device corresponding to the first latching device and rigidly coupled with other of the aircraft structure or aircraft interior fitting element; and a second fixation device corresponding to the second latching device and rigidly coupled with other of the aircraft structure or aircraft interior fitting element; wherein the first latching device and the first fixation device are rigidly detachably couplable to one another; wherein the second latching device and the second fixation device are rigidly detachably couplable to one another; wherein at least one of the first and second latching devices has a first portion couplable with the first or second fixation device, and a second portion rigidly connectable to the aircraft interior fitting element; and wherein the at least one of the first and second latching devices, comprising the first and second portions, is adapted to pivot the aircraft interior fitting element relative to the first and second fixation device.