In this paper, flap peening treated of 2024 T3 aluminum alloy sheets with 2.5 mm thickness were investigated and presented. The specimens used for the studies were taken from an Airbus A330-200 aircraft fuselage scrap plate near the waste vent hole area. There are 5 specimens were investigated with different surface treatments. The sheets were blended out to simulate the damaged areas and sharp edge removal. Furthermore, the flap peening was applied to improve the characteristics of the damaged material surface at various rotational speeds (1500, 2500, and 3500 rpm). For investigation, the tensile strength, roughness, and hardness of the specimens were measured to study the effects of the repair process. Afterward, the specimen’s macrostructure was investigated for observing the effect of corrosion removal and shot peening on the metal surface to the inner side microstructure and the occurrence of crack propagation. The measurements show there was a significant improvement in strength and hardness after flap peening was applied. Although flap peening application at 3500 rpm resulting better material properties, the difference is not significant compared to the 2500 rpm rotational speed. The result of microstructure and crack propagation observation using optical microscopy proved that shot peening on the outer surface of the material with rotations of 1500 rpm, 2500 rpm, and 3500 rpm compared to the original specimen does not have an impact on the internal microstructure of the material, and no crack propagation occurred. However, excessive flap peening intensity may potentially affect lower fatigue life, as reported by the previous research. Further study is needed to know how far the effect of the treatment on the fatigue life of the material and the optimum parameter for the flap peening process.