Abstract: Using Acoustic Emission (AE )to monitor riveted Panel Fatigue test of Aircraft. Parameter filter and location filter were utilized to obtain the available AE signals. Trend analysis, location analysis and combined filter analysis of the characteristic parameters of available AE signals were further used to obtain the data of fatigue crack initiation and extension. These results have proven that the technique of AE can exactly predict the time of fatigue crack initiation and extension, and it can provide reference to fatigue and damage tolerable design of panel structures of aircraft.