Abstract: Many papers have been presented to introduce the deleterious effects of fretting damage on fatigue strength: reductions of over 50% are reported for simple coupon type specimens. In the aircraft failure investigating, the presence of fretting damage on the failure areas is also frequently noticed, especially the high chance of fretting damage occurrence appears in the aircraft structure where two pieces of material are connected by rivets,bolts, pins and interference fit. To what extent this damage effects on airframe structural life has not been determined, but is certainly a serious and noticeable problem.The microcosmic characters of fretting damage of high strength aluminum-alloy riveted fasteners and the effects of different type of treatments applied to the faying surfaces on the fatigue strength are analysed in details. The results of tests show that the fatigue life of riveted fasteners can be generally increased with different degree if an appropriate type of treatment is employed for the faying surfaces. The method of bonded and riveted joint studied in the paper is the effectively protective measure to prevent fretting damage occurred in riveted fasteners.When the axial interchangeable stress σmax is less than 125MPa the fatigue life of the bonded and rivetted joint specimen is over 60% higher than that of the interference riveted joint specimen.