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This study proposes a method for the fast simulation of the distribution of alternating magnetic fields around internal cracks as well as cracks on the inner and outer diameter surfaces of a pipe. This method, which uses a bobbin‐type magnetic camera to inspect cracks in small‐bore piping systems, is based on a dipole model, allowing for the rapid calculation and storage of data on the distribution of alternating magnetic fields around cracks from a sensor moving inside a pipe. Copyright © 2014 John Wiley & Sons, Ltd.

Aircraft MLG and wing structures have been recognized as fatigue critical structures and exposed to the risk of fatigue crack initiation and propagation. Furthermore, these structures are frequently subjected to serious dynamic loading condition during a Hard Landing which may lead to their failure. Especially, structural integrity of MLG and wing components is decreased as the flight time increased because of the fatigue damage accumulated on the aircraft.In this study, the effects of Hard Landing on the MLG and wing components of aging aircraft were evaluated by using numerical approach. To achieve the aim, a finite element model has been developed and simulations were conducted by varying the landing conditions. As a result, it was revealed that the high stress concentration phenomenon was occurred at the lower Side Brace of MLG. Thereby, the intensified inspection for the lower Side Brace should be considered to prevent unexpected aircraft mishap.

Recently, there were significantly increased cracks failure for external fuel tank horizontal fin of F-5 aircraft. In this paper, the dynamic behavior of horizontal fin was to quantitate by using Finite Element Method. To achieve this goal, the fatigue analysis for time and frequeucy domain has been performed by using the dynamic load spectrum of speed brake. In conclusion, it was proved that fatigue life of the horizontal fin was reduced by the influence of dynamic behavior.

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