Aircraft or spacecraft fuselage comprising a fuselage skin and divided in at least a first and a second fuselage sections 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 of the first and second fuselage sections in a region where the first and second fuselage sections are joined, between the first and second fittings ; 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 of the first and second fuselage sections in a region where the first and second fuselage sections are joined, between the first and second fittings ; 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 . <EOS>