Production method for producing a load-bearing fuselage panel for a fuselage portion of an aircraft fuselage in a region of a cabin of an aircraft, comprising: producing the fuselage panel in a sandwich-type construction with an inner panel and an outer skin in the form of shells (18, 20), and a filler panel, which is embedded between the shells (18, 20), in the form of a core, such that the outer skin is configured as part of a fuselage structure and the outer boundary of the aircraft fuselage, configuring the inner panel for an interior space boundary of the cabin, integrating functional elements of the fuselage structure, and integrating functional elements of the cabin and/or of the aircraft, into the filler panel, wherein the method comprises the following steps: a) designing and separately manufacturing the filler panel in such a way that it is configured to accommodate functional elements of the fuselage structure and to accommodate functional elements of the cabin and/or of the aircraft, b) providing the filler panel with functional elements of the cabin and/or of the aircraft, providing the filler panel, during the manufacturing operation according to step a), with webs, frames and/or ribs in the form of functional elements for the load-bearing construction of the fuselage structure, c) manufacturing the outer skin in the form of a shell (18, 20) of the fuselage panel, d) manufacturing the inner panel in the form of a shell (18, 20) of the fuselage panel, e) fastening the filler panel to one of the shells (18, 20), and f) fastening the other shell (18, 20) to the filler panel, wherein, during the manufacturing operation according to step c) and/or step d), at least one of the shells (18, 20) is provided with a positioning aid for positioning the filler panel, wherein step b) comprises the following step: b1) pre-assembling the webs, frames and/or ribs in the form of functional elements of the fuselage structure into the filler panel prior to steps e) and f). producing the fuselage panel in a sandwich-type construction with an inner panel and an outer skin in the form of shells (18, 20), and a filler panel, which is embedded between the shells (18, 20), in the form of a core, such that the outer skin is configured as part of a fuselage structure and the outer boundary of the aircraft fuselage, configuring the inner panel for an interior space boundary of the cabin, integrating functional elements of the fuselage structure, and integrating functional elements of the cabin and/or of the aircraft, into the filler panel, wherein the method comprises the following steps: a) designing and separately manufacturing the filler panel in such a way that it is configured to accommodate functional elements of the fuselage structure and to accommodate functional elements of the cabin and/or of the aircraft, b) providing the filler panel with functional elements of the cabin and/or of the aircraft, providing the filler panel, during the manufacturing operation according to step a), with webs, frames and/or ribs in the form of functional elements for the load-bearing construction of the fuselage structure, c) manufacturing the outer skin in the form of a shell (18, 20) of the fuselage panel, d) manufacturing the inner panel in the form of a shell (18, 20) of the fuselage panel, e) fastening the filler panel to one of the shells (18, 20), and f) fastening the other shell (18, 20) to the filler panel, a) designing and separately manufacturing the filler panel in such a way that it is configured to accommodate functional elements of the fuselage structure and to accommodate functional elements of the cabin and/or of the aircraft, b) providing the filler panel with functional elements of the cabin and/or of the aircraft, providing the filler panel, during the manufacturing operation according to step a), with webs, frames and/or ribs in the form of functional elements for the load-bearing construction of the fuselage structure, c) manufacturing the outer skin in the form of a shell (18, 20) of the fuselage panel, d) manufacturing the inner panel in the form of a shell (18, 20) of the fuselage panel, e) fastening the filler panel to one of the shells (18, 20), and f) fastening the other shell (18, 20) to the filler panel, wherein, during the manufacturing operation according to step c) and/or step d), at least one of the shells (18, 20) is provided with a positioning aid for positioning the filler panel, wherein step b) comprises the following step: b1) pre-assembling the webs, frames and/or ribs in the form of functional elements of the fuselage structure into the filler panel prior to steps e) and f).