Abstract: As a frequently-used aeronautical material, aluminium alloy 6082T6 has the excellent mechanical properties. The fatigue non-propagating crack in the metal was studied. The SENT specimens were used in the fatigue tests. The 1 mm radii stop-holes were carefully centered and drilled at the fatigue crack tips with the help of a milling machine. After the researches it was found that the non-propagating crack length can be achieved through the reasonable specimens design. The non-propagating crack tolerance can be pre-setted at the dangerous place where the crack tends to be initiated and the reliability life of component can be significantly improved. The method can improve the impact resistance of component and reduce the risk of crack propagation during the maintenance interval.