Among a few candidates of 7XXX aluminum alloys that demonstrate high static mechanical properties along with high fatigue endurance, the 7050 alloy has been a leading alloy in the aerospace industry due to its resistance to stress corrosion cracking in all directions. One of the primary issues in design against fatigue with structural material is the effect of applied surface treatment. Previous studies of the 7050 alloy have concentrated on the effect of chromic acid anodizing treatment on low-cycle, transition, and high-cycle fatigue regions without giving special attention to the effect on the “estimated” fatigue limit. Understandably, it is not simple to conduct an exhaustive testing campaign at a very high-cycle region with a great number of specimens. The authors of this study have conducted an extensive fatigue test campaign to characterize the long-life fatigue of 7050 material excised from plate and forgings. Their primary intention was to reveal the degree of reduction in fatigue and accordingly to characterize how different micromechanisms play an active role in the altered fatigue behavior of specimens when subjected to anodizing. For the long-life fatigue tests, the staircase method with a runout criterion of 5E + 7 cycles was employed. Specimens were excised from different orientations and from different thicknesses. The results reveal that the effect of chromic acid anodizing on the fatigue behavior of the 7050 alloy varies in different regions of the S-N curve. In low-cycle and high-cycle regimes up to 106 cycles, a slight decrease in fatigue life exists, as described in the literature. The results of the long-life regime, however, show that anodizing has an unusual effect on fatigue. Efforts were made to understand the responsible mechanism through fractography focused on the crack initiation sites, microstructural characterization, and comparative through-thickness residual stress measurements.