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A running crack has the potential to cause new cracks to grow and spread throughout the structure. These new cracks are not continuous. They form and grow in random places due to the discontinuities in the crack. Successive cracks appearing in the same place is called fatigue machining. This phenomenon can be reduced or eliminated by cyclic or sinusoidal stress loading and reduces the defects induced in the structure by the original fatigue crack(s). The bodies of the structure are allowed to vibrate due to the applied cyclic or sinusoidal stress, which may be transferred either mechanically or elastically to the existing fatigue crack(s). This stress wave propagation is called stress corrosion.

In 1973, at the request of the National Academy of Engineering, Robert S. Gelinas (then with the U.S. Department of Energy) proposed the crack growth theory, in which the following stress intensity criteria were relaxed: (1) crack closure through cyclic load; (2) plasticity-based stress magnification; (3) crack size dependency of stress-intensity factors; (4) crack size dependency of crack growth rates; (5) crack size dependency of circumferential stress tensor elements; and (6) stress-corrosion cracking. The theory was given the philosophical name of ``Why not'' and was not widely adopted at that time. It is now slowly becoming adopted by the structural engineering industry as an acceptable life prediction theory.

An alternate approach to fatigue prediction is the analytic life prediction approach, or AIPA, theory. The AIPA method derives the fatigue life by analytically deriving the stress intensity factors at the crack tip and conducting a series of numerical simulations to predict the crack growth rates. The theory is widely adopted by the engineering community and is used as the industry-standard life prediction method. The assumption is that this approach simulates the evolution of the crack in a semi-analytical way. It appears that the industry has accepted this approach in the desire to obtain best-achieved life. d2c66b5586