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All aircraft structures are exposed to both fatigue and static loads. Damage caused by fatigue loads is much more dangerous because it can cause damage at a level lower than the ad hoc strength. Fatigue testing requires both a large number of samples and machine time, which generates considerable costs. In the case of tests performed on prototypes, it is sometimes impossible to make a large number of samples. In such a situation, as well as in a situation when results are sufficient, the accelerated methods described by the co-author in [3] may be used to study with some approximation. In the standard tests, only the number of cycles measured under a predetermined regime is used. Many signals can be used in accelerated studies: e.g. piston displacement, force, strain gauge, thermographic measurement [4].
