Patent ID: 8424806

Claim:
Aircraft component that comprises at least one panel ( 11 ) of composite material, the panel ( 11 ) being formed by a skin ( 13 ) and a plurality of stiffening stringers ( 15 ) configured with a central section ( 17 ) and feet ( 19 ), as well as spars ( 25 ) and ribs ( 27 ) connected to said panel ( 11 ), an arrangement of said stringers ( 15 ) and said spars ( 25 ) and ribs ( 27 ) including zones of one intersection and potential interference between said stringers ( 15 ) and said spars ( 25 ) and ribs ( 27 ), characterised in that the configuration of an end of a stringer ( 15 ) in one of said zones, includes a first section ( 41 ) in which the height of the central section ( 17 ) of the stringer ( 15 ) tapers down toward extended feet ( 23 ) to a tapered end and the width of the feet ( 19 ) increases until the width reaches a predetermined width (A) and a second section ( 43 ) with the extended feet ( 23 ) of said predetermined width (A) and no central section ( 17 ), including in said first section ( 41 ) mechanical means ( 31 ) to bind the end of the stringer ( 15 ) to the skin ( 13 ).