This thesis reviews the application of non-destructive testing techniques to Boeing 737-800 nose landing gear torsion links, current inspection techniques, failure mechanisms, and technical procedures. Examinations of Boeing NDT Manual D6-37239 procedures are identified here which cover ultrasonic tests using Reference Standard 350 and eddy current inspection methods and baseline capabilities and limitations in the methodologies. By investigating known performance failures such as the ASL Airlines torsion link fracture at 27,000 flight cycles and the Delta Flight 1092 nose landing gear collapse, the research identifies a key unmet need for detection by which conventional detection for crack detection achieves 0.040 inches, and from 0.025 inches to 0.030 inches. The analysis includes real operational data from the Enter Air Services (Part 145 AMO) including five Boeing 737-800 High-Frequency Eddy Current inspection reports, which provide real evidence of the application of Boeing practices on the job and a comparison with theoretical concepts using real-life maintenance practices. Advanced technologies (Phased Array Ultrasonic Testing and Eddy Current Array) and risk-based inspection techniques such as those that address operational severity differences between the Boeing 737 fleet will be analyzed, in the future. The review aims to connect concepts from previous research on NDT with practical aviation maintenance with a view to understanding the limits and potential improvement in the inspection practice in landing gear structural integrity assessment.