The aim of this study was to identify non-destructive testing methods for crack detection in spars, which are structural components of light wooden aircraft. The term compression crack refers to a structural anomaly that occurs as a fine fracture perpendicular to wood fibres. A crack results from significant deformation followed by compression failure of the wood cells. Crack formation is accompanied by several transverse fissures in the material. Monitoring the spars helped to determine the inspection problem. The cracks were located on both the upper and lower surfaces of the wing. Cracks formed close to the wing/fuselage joint and extended to the landing gear attachments. The selected methods used in this study are: thermal imaging (surface inspection with direct access), X-ray analysis (deep inspection without direct access), ultrasound (deep inspection with direct access) and acoustic emission (passive detection without direct access - In-service monitoring). (Texte intégral)