Aerodynamical and structural outlet guide vanes for jet engine intermediate cases can be made out of titanium, multi-axial or variable-axial CFRP. The absolute and density specific stiffnesses of the material approaches and the engine structures are compared. The lightweight potential for different 1- to 3-directional load scenarios are shown. Application-oriented boundary conditions of the aerodynamical and structural component are developed and defined. Furthermore, design and simulation methods (e.g. for variable-axial CFRP) are presented in order to elaborate suitable fiber architectures for different composite design methods in a given design space. The relative density specific stiffnesses of the component using the three different lightweight material approaches are compared and evaluated under both 1- to 3-dimensional idealized load scenarios and with a real engine reference load case.