Patent ID: 8814092

Claim:
An aircraft fuselage primary structure comprising: a skin ( 11 ), at least one reinforcing fuselage frame ( 13 ), at least one crossmember ( 14 ) attached to said at least one reinforcing fuselage frame ( 13 ), and at least one structural element ( 2 ) of elongate shape, comprising a compression beam ( 21 ) of longitudinal axis Z made of composite material, said material comprising plies of continuous fibers held in place by a resin, said compression beam, the axis of which is directed substantially in a direction of compressive forces that are to be absorbed in the event of an impact, being attached at a first end ( 213 ) to the crossmember ( 14 ), and at a second end ( 214 ) to the reinforcing fuselage frame ( 13 ), wherein the compression beam ( 21 ) is attached, at least at one of the first and second ends ( 213 , 214 ), by a gusset plate ( 22 ), said gusset plate comprising: guide means ( 223 ) for guiding the beam ( 21 ) substantially along its longitudinal axis Z, a cutting element ( 224 ) for cutting the compression beam ( 21 ) into at least two strips, in the direction of the longitudinal axis Z, and a clearance groove ( 225 ) for each of said at least two strips.