Aircraft or spacecraft fuselage comprising a fuselage skin and divided in at least a first and a second fuselage sections (2a, 2b) which, when assembled, form the fuselage, the fuselage including a structural junction which comprises a first fitting attached to a portion of the fuselage skin in the first fuselage section, a second fitting attached to a portion of the fuselage skin in the second fuselage section, and a pressure bulkhead skin attached to an inner flange of the first fitting, the inner flange being spaced apart from the fuselage skin towards an inner space enclosed by the fuselage skin when the fuselage is assembled; wherein the pressure bulkhead skin is, in use, a skin of a rear pressure bulkhead of the aircraft or spacecraft, wherein with respect to the rear pressure bulkhead, the first fuselage section is a forward section and the second fuselage section is a rearward section; wherein the first fitting and the second fitting are connected, during assembling of the fuselage, at least using a plurality of tension bolts, wherein the tension bolts each are arranged and adapted to transfer at least tensile loads, in a direction across adjacent edges (12a, 12b) of the first and second fuselage sections (2a, 2b) in a region where the first and second fuselage sections (2a, 2b) are joined, between the first and second fittings (13, 23); and wherein the first fitting further comprises a first outer flange for joining the first fitting to the portion of the fuselage skin in the first fuselage section and a first web connecting the inner flange and the first outer flange, and wherein the second fitting comprises a second outer flange for joining the second fitting to the portion of the fuselage skin in the second fuselage section and a second web connected to the second outer flange. a first fitting attached to a portion of the fuselage skin in the first fuselage section, a second fitting attached to a portion of the fuselage skin in the second fuselage section, and a pressure bulkhead skin attached to an inner flange of the first fitting, the inner flange being spaced apart from the fuselage skin towards an inner space enclosed by the fuselage skin when the fuselage is assembled; wherein the pressure bulkhead skin is, in use, a skin of a rear pressure bulkhead of the aircraft or spacecraft, wherein with respect to the rear pressure bulkhead, the first fuselage section is a forward section and the second fuselage section is a rearward section; wherein the first fitting and the second fitting are connected, during assembling of the fuselage, at least using a plurality of tension bolts, wherein the tension bolts each are arranged and adapted to transfer at least tensile loads, in a direction across adjacent edges (12a, 12b) of the first and second fuselage sections (2a, 2b) in a region where the first and second fuselage sections (2a, 2b) are joined, between the first and second fittings (13, 23); and wherein the first fitting further comprises a first outer flange for joining the first fitting to the portion of the fuselage skin in the first fuselage section and a first web connecting the inner flange and the first outer flange, and wherein the second fitting comprises a second outer flange for joining the second fitting to the portion of the fuselage skin in the second fuselage section and a second web connected to the second outer flange.