Abstract
Various nondestructive evaluation (NDE) methods are frequently employed to inspect the adhesive bonds of aircraft structures in service. The literature on the capability of various NDE techniques reveals a deficiency in linking NDE test parameter characteristics of the frequency or size of defects to critical failure properties such as the lifetime and the strength of adhesive bonds. In this study an attempt has been made to develop such correlations. A specimen geometry was employed so as to permit cleavage-type debonding under fatigue loading. This geometry and loading configuration provide for a simple fatigue testing program and simple analytical methods. Damage by flexural fatigue aging of these adhesively bonded specimens was induced at different intervals of their fatigue lifetime. The specimens were composed of materials that were commonly used in actual aircraft production during the 1970s. Pulse-echo ultrasonic C-scanning and thermal wave imaging were performed to inspect the adhesive joints at ...
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