Rotation fitting for the empennage of an aircraft
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United States of America Patent
Stats
-
Jul 28, 2009
Grant Date -
Jun 28, 2007
app pub date -
Aug 4, 2006
filing date -
Dec 26, 2005
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
Rotation fitting secured to a frame (6) of the fuselage of an aircraft and linked to a receiving element secured to the empennage (5) which comprises a central fitting (1) and two side fittings (2,3), the central fitting (1) presenting two lugs (1d,1k) with an opening (1e,1j) each and four side wings (1g,1f,1i,1h), and each one of the side fittings (2,3) presenting a lug (2d,3d) with an opening (2e,3e) each and two side wings (2g,2f,3g,3f), the central fitting (1) being secured to a surface of the frame (6) and the side fittings (2,3) in an opposite surface of the frame (6), such that the frame (6) is arranged between the central fitting (1) and the two side fittings (2,3), such that the lugs (1d,1k) of the central fitting (1) make contact with the lugs (2d,3d) of the side fittings, with all the openings (1e,1j,2e,3e) being aligned in order to house a pin (4) associated with the receiving element secured to the empennage (5).
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