an aircraft fuselage structure is disclosed herein and includes an outer skin , with circumferential ribs , such that a recess is provided for receiving a wing torsion box in the outer skin , and the ribs are interrupted in the region of the recess . an object of the disclosure includes providing an aircraft fuselage structure designed such that the wing torsion box is able to extend at least partially through the upper region of the fuselage , without the stability of the fuselage being significantly reduced . this can include providing first longitudinal members which are adjacent to the recess and which extend along the longitudinal edges beyond the entire length thereof . end regions of the first longitudinal members are connected to ribs which extend circumferentially at intervals from the transverse edges of the recess along the outer skin over the vertical longitudinal central plane .