Abstract: Cold extrusion reinforcement for crack-filling sleeve is an effective strengthening technique in Anti-fatigue and longevity technology. It is widely used in the reinforcement of aircraft critical parts’ connecting holes. In actual engineering application scenarios, the end face of the reinforced hole are mostly non-mating surface. The protruding material at the reinforced hole’s outlet can be removed by polishing or milling, which is not difficult. However, The core part’s intersecting hole at the rotating beam cylindrical axis of an aircraft’s all-moving winglet is difficult to implement hole extrusion strengthening, the rotary beam’s material is titanium-alloy, its outer circle need high precision and it has corrosion-resistant spray coating. Threrfore, how to remove the material raised around the orifice on a circular shaft and guarantee the high precision cylindrical dimensions after the hole’s strengthening, how to ensure that hole extrusion reinforcement with not to damage the spray layer after the hole’s strengthening, all that are technical difficulties in engineering practice, which caused the hole extrusion technology can not be applied in such scenarios This paper focuses on the above issues, An experiment which is from the perspective of engineering application was designed and had been verified. A feasible technical solution is finally obtained, which is successfully solving the hole extrusion technology’s application difficulties of Titanium alloy rotary beam cylindrical intersecting hole.