Link bar assemblies are provided to connect adjacent structural components (e.g., components of an aircraft such as connecting an underwing engine to the wing structure) having respective connection lugs. The link bar assemblies will include a link bar having opposed terminal ends which include circular bearings, bushings operatively received by the circular bearings of the link bar, and a bolt and pin assembly inserted through the bushings to connect the terminal ends of the link bar to the respective connection lugs of the adjacent structural components. At least one of the bushings includes a multi-faceted flange and defines an eccentric aperture (e.g., an elliptical aperture having major and minor axes) such that rotation of the bushing allows the eccentric aperture to become aligned with the mounting opening of a respective connection lug.
QUICKLY ADJUSTABLE FAIL-SAFE LINK BAR ASSEMBLIES ESPECIALLY USEFUL FOR CONNECTING STRUCTURAL COMPONENTS OF AN AIRCRAFT
2020-10-01
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge / F16M Rahmen, Gehäuse oder Grundplatten von Kraftmaschinen oder anderen Maschinen oder von Apparaten, nicht auf eine besondere Art von Maschine oder Apparat eingeschränkt, die anderweitig vorgesehen ist , FRAMES, CASINGS, OR BEDS, OF ENGINES OR OTHER MACHINES OR APPARATUS, NOT SPECIFIC TO AN ENGINE, MACHINE, OR APPARATUS PROVIDED FOR ELSEWHERE |
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