jamesgrieco(at)yahoo.com Guest
 
 
 
 
 
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				 Posted: Fri Apr 14, 2006 4:35 am    Post subject: Cracks in aft fuselage stiffeners: My 2cents | 
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				Gary, I would reconsider doing much to stiffen that panel. From
 what I have read on GG, the cause(s) are all speculation. The
 basic description some gave of the purpose of those stiffeners
 as a frame was completely wrong. They are nothing more than
 panel breakers designed to stop the walls of the torque box from
 buckling.
 
 That area is bounded by the forward and aft vertical fin
 attachment bulkheads and the upper web and lower skin. The ratio
 of length to width is roughly 2.5:1 which is fairly typical of
 beam webs. As our grummans are made as light weight as possible,
 the webs probably fail in shear buckling when subjected to
 ultimate loading (presumably torsion from the horizontal and
 vertical). The simple and most weight efficient fix is to put
 'panel breakers' at mid bay to stiffen the webs and prevent
 buckling.
 
  	  | Quote: | 	 		  From all the pictures that I have seen the cracks occur where
 the stiffeners overlap each other. This might have been done to
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 provide some stability to the vertical flange of the stiffeners,
 but I suspect it was done simply to allow manufacturing to put
 glue on all the surfaces, and it probably aids in fixturing the
 stiffeners in place. That the crack would initiate there is not
 a real surprise, but they do last many years.
 
 In any event, it does not make those stiffeners act as any real
 frame in my opinion, as a frame would require an inner cap. I
 would bet that once the crack releases the ends of the two
 stiffeners from each other, that is the end of the problem. This
 would could be proven if the a/c that have had this problem have
 had the condition for a long time (very probable) and they had
 no further crack growth. The function of the stiffener as a
 panel breaker is not at risk. From my experience on our
 Grumman's very big brothers, this is not unusual.
 
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