This chapter describes how ultrasonic testing came to be a viable method for evaluating intergranular stress-corrosion cracking (SCC) in large-diameter stainless steel pipe welds in boiling water reactor service. Intergranular SCC can be difficult to detect using nondestructive evaluation (NDE) techniques because of its treelike branching pattern and its location in the heat-affected zone within the weld. As the chapter explains, by optimizing excitation and reflected waveforms, switching to dual-element sensing, properly orienting the scanning path, and using crack-tip diffraction and amplitude-drop techniques, the height, length, and location of intergranular cracks can be accurately determined anywhere along the walls of the pipe as well as in weld areas.

An aircraft crashed following the loss of yaw control in full airborne flight. The subsequent discovery of broken shutter bolts in the rear pitch reaction control valve led to an inspection campaign that found bolt failures of a similar nature in valves on several other aircraft. The bolts were removed and analyzed to determine the mode and cause of failure. Based on the results of macroscopy, scanning electron fractography, metallographic examination, and chemical analysis, the failures were caused by stress corrosion cracking, and in one case, overtightening.

This chapter provides an overview of the tools and techniques used to examine failure specimens and the wealth of information that can be obtained from fracture surfaces, cracks, wear patterns, and other such features. It discusses the use of metallography, fractography, and optical and electron microscopy. It presents a number of images recorded using these methods and explains what they reveal about the mode of fracture and the state of the component prior to failure.

An aircraft was heavily damaged when it was forced to land due to a throttle malfunction. Investigators determined that one of the studs linking the throttle to the engine fractured from fatigue, initiated by cracks formed during a riveting procedure. This chapter provides a summary of the investigation, which included the use of scanning electron fractography, along with recommendations on acceptable hole patterns for rivets.

This chapter describes an investigation following an aircraft accident in which the main undercarriage struts had failed. Visual examination revealed that the starboard strut fractured about 13 cm from the end nearest the underside of the wing. A close-up view of the fracture surface indicated that cracking initiated at the outer periphery of the strut and propagated inward until overload fracture occurred. SEM imaging revealed fatigue striations along the outer periphery and dimples elsewhere, indicative of tensile overload. Based on these observations, investigators concluded that the starboard strut failed by fatigue, which overloaded the port side strut as evidenced by its slant type fracture pattern.

This article depicts typical fractographic features for a number of different composite materials, covering interlaminar and translaminar fracture characteristics in composite materials.