Patent ID: 8397352
Filing Date: 2013-03-19
Classification: B64C,B64D,F16B,H02P,Y02T,Y10T

Abstract:
1. A decompression-element fastening system for releasably fastening a trim component serving as a decompression element to a supporting structure in an aircraft internal region, comprising: a bolt which has a bolt axis, at least one detent recess on a first end, and a first thread on a second end, a screw including a second thread and connected by the second thread to the bolt, the screw also including a screw head at an end portion opposite to the second thread, the screw head positioned to press the trim component towards the supporting structure when the screw is moved to a screwed-in position relative to the bolt, and at least one detent element coupled to the supporting structure for resilient support, the detent element positioned such that when the bolt approaches the detent element during fastening of the trim component to the supporting structure, the detent element slides over the first end of the bolt and engages with the associated detent recess, wherein the detent element is sufficiently resilient to disengage from the detent recess by sliding over the first end of the bolt if a predetermined tensile force acting in the direction of the bolt axis is exceeded, thereby unfastening the trim component from the supporting structure.