Structural element of an aircraft fuselage

1. A structural element of an aircraft fuselage, comprising:

stringers extending in a longitudinal direction of the aircraft fuselage; and

ribs extending transversely to the stringers in a circumferential direction of the fuselage,

wherein at least one of the stringers includes at least a one-piece stringer portion formed as a fastening rail for elements to be installed in the aircraft fuselage, the one-piece stringer portion comprising:

a head region that extends in the longitudinal direction, the head region being interrupted by receiving recesses that receive said ribs and are open on a side facing towards an interior of the fuselage, the head region being continuous between the receiving recesses; and

a foot region opposite the head region that extends in the longitudinal direction continuously between ends of the one-piece stringer portion and is uninterrupted by the receiving recesses,

wherein the one-piece stringer portion is perforated with a plurality of holes configured for fastening components.

2. The structural element according to claim 1 , wherein the structural element comprises an outer skin of the aircraft fuselage, wherein the stringers and ribs are connected to the outer skin.

3. The structural element according to claim 2 , wherein the foot region is fastened to the outer skin; and

wherein the head region faces towards the interior of the fuselage.

4. The structural element according to claim 3 , wherein the head region has a profile cross-section provided for positive installation of fastening elements.

5. The structural element according to claim 4 , wherein the profile cross-section of the head region is L-shaped.

6. The structural element according to claim 4 , wherein the profile cross-section of the head region is T-shaped.

7. The structural element according to claim 4 , wherein the profile of the head region has a C-shaped profile cross-section.

8. The structural element according to claim 7 , wherein an open segment of the C-shaped profile cross-section faces towards the interior of the fuselage.

9. The structural element according to claim 3 , wherein the one-piece stringer portion is fastened in a thermally insulating manner to the outer skin.

10. The structural element according to claim 9 , wherein the foot region is fastened by means of angle profiles to the outer skin, wherein a thermal insulation is provided between the angle profiles and the foot region.

11. The structural element according to claim 1 wherein bridging sealing elements are inserted into the recesses of the head region, wherein the bridging sealing elements enclose the ribs on a side of the ribs facing towards the interior of the fuselage.

12. The structural element according to claim 1 , wherein the one-piece stringer portion formed as a fastening rail has a profile cross-section which is used for positive installation of fastening elements.

13. The structural element according to claim 12 , wherein the one-piece stringer has a C-shaped profile cross-section whose open segment faces towards the interior of the fuselage.

14. The structural element according to claim 1 , wherein the plurality of holes are located in a region of the one-piece stringer portion between the head region and the foot region.