Assembly comprising a continuous structural element for aircraft and a fitting

An assembly comprising:

• a continuous structural element for an aircraft;
• and,
• a fitting,
• wherein the continuous structural element for the aircraft comprises:
• an outer flange,
• an inner flange, and
• a web between the outer flange and the inner flange,
• wherein the inner flange has at least one portion with a wavy shape such that a smallest thickness of the web occurs at a center of the wavy shape, and a thickness of the web on either side of the center of the wavy shape increases continuously along the inner flange until reaching apexes of the wavy shape on either side of the center of the wavy shape, such that a largest thickness of the wavy shape occurs at the apexes of the wavy shape, and
• wherein the fitting comprises at least one through hole and is configured to fit a portion of the web at the at least one portion of the inner flange with the wavy shape such that in an assembled state the fitting is joined to the portion of the web by connecting means so that the at least one through hole of the fitting is not covered by the web.