Fiber metal laminates (FMLs) are structural materials that play a vital role in the aviation sector, in which they are exposed to cyclic long-term loading. This article investigates creep response and rupture mechanisms of glass laminate aluminum reinforced epoxy (GLARE) FMLs based on microindentation creep testing. Specimens were manufactured by compression molding, and experiments were conducted under different test parameters, namely, aluminum surface treatment (in terms of surface roughness), creep chamber temperature, indentation load, and run time. In addition, rupture mechanisms were analyzed using scanning electron microscopy. The individual interaction of control parameters on creep strain and mass loss response was studied using Taguchi method. Among the studied factors, specimen condition and creep chamber temperature predominantly control creep rupture, whereas load and time were less important, as confirmed by statistical predictions using linear regression.