Abstract: For aircraft without pre-designed vertical-tail hoisting devices, the disassembly, transportation and hoisting processes involve complicated operations and potential safety hazards. This paper designs a simple lifting-lug structure, which makes use of the through-holes of vertical-tail joint lugs, the through-holes of fuselage frame flange joint lugs and original assembly nuts. It can not only serve as temporary bolted connections, but also realize safe hoisting of the vertical tail. To verify whether the strength and deformation of the lifting-lug structure meet application requirements, simulation analysis of the vertical-tail lifting-lug system is carried out using ABAQUS software. The results show that under static-load conditions, the peak stress of the lifting-lug structure is 179.7 MPa, which is lower than the allowable material stress of 417.5 MPa (only 43.1% of the allowable value), the maximum displacement is 0.251 4 mm. All indices satisfy the safety-margin requirements. The analysis verifies that the designed lifting-lug structure possesses sufficient strength reserve and can guarantee the safety of vertical-tail hoisting operations.