In recent years, studies for a new kind of fiber metal laminates, Ti/CFRP, sometimes called TiGr have been increasing for the application to advanced supersonic aircrafts. In these studies, however, sufficient observations of damages, especially internal ones, were not exhibited. In the present paper, the fatigue damage behaviour and impact responses and damages of fiber metal laminates based on a titanium alloy and GFRP as Ti/FRP system was investigated in detail. At first, fatigue tests for open-hole specimens of Ti/GFRP were conducted. From the experimental evidence, the dominant fatigue damage modes were identified as cracks and delaminations of the Ti layer, transverse cracks of the 90° layer and 0790° interlaminar delaminations in the GFRP layer near the open-hole. A finite element model based on these fatigue damage modes was developed, and this model was confirmed to predict the changes in mechanical properties of the laminates. Low-velocity impact tests were also conducted for the laminates with single Ti layer. From the experimental results, it was found that laminates with single Ti layer at non-impacted side showed good impact resistance, and in this case, the extent of interlaminar delaminations in GFRP was dependent on damages of Ti layer presented during the impact event. Numerical analyses of impact events were also carried out in order to verify the relationship between the internal/external damages and the impact responses. The numerical results showed that the impact responses of the laminates could be represented by the FE analysis.