Patent ID: 8800917
Filing Date: 2014-08-12
Classification: B64C,B64D

Abstract:
1. Aft aerodynamic fairing ( 5 ) for an aircraft engine ( 4 ) attachment pylon ( 1 ) comprising upper spars (L 1 ), transverse stiffening ribs ( 50 ), lower spars (L 3 ) and a trailing edge ( 55 ) where the upper spars (L 1 ) and lower spars (L 3 ) join together in a V configuration at the trailing edge side ( 55 ) characterized in that a structural structure ( 59 ) is formed in the trailing edge according to a profile open to the outside of the fairing ( 5 ), and in that the structure ( 59 ) in a first end (E 5 ) comes to be enclosed between a corresponding end portion (P 3 ) of the lower spars (L 3 ) and the ends ( 5 e ) of at least one transverse stiffening rib ( 50 ) flush longitudinally with lower spars (L 3 ), extends between the lower spars (L 3 ) and the aft upper spars (L 1 ) over a straight central portion ( 29 ) inclined relative to the end (E 5 ) thereof and the spars, where this central portion ( 29 ) is suitable for receiving the trailing edge ( 55 ), and comes at a second end portion (E 4 ) flush against a portion (P 1 ) of the upper spars (L 1 ), parallel to said first end (E 5 ).