A structural component such as a wing skin for an aircraft is formed generally of a first composite fiber and matrix material exhibiting a first tensile modulus in respect of tensile stress and a first tolerance of strain resulting from such stress. One or more openings are provided in the component and the material of a portion of the component bounding the opening(s) is a second composite fiber and matrix material. The second material exhibits a second tensile modulus in respect of tensile stress that is smaller than the first tensile modulus of the first material and a second tolerance of strain resulting from such stress that is greater than the first tolerance of strain of the first material.