Abstract: Fastening holes are important locations for fatigue crack initiation in aircraft structures. The fatigue life of fastening hole can be remarkably improved by cold extrusion process. The traditional cold extrusion strengthening process has the problem of non-uniform distribution of residual stress along the thickness direction, which seriously weakens the fatigue strengthening effect. In order to address above problems, the residual stress distributions between the new inclined split sleeve and the traditional counterpart after cold extrusion were compared by finite element simulation, and the fatigue life under far-field alternating loads was predicted. The results show that the circumferential compressive residual stress produced by traditional split sleeve cold extrusion varies greatly along the thickness direction, and the compressive stress zone is smaller along the radial direction. On the contrary, the circumferential residual compressive stress generated by the new split sleeve is more uniform along the thickness direction, and the compressive stress zone is wider along the radial direction. The anti-fatigue performance of cold squeezed hole processed by the new split sleeve is significantly better than that processed by the traditional split sleeve.