Abstract: An automated repair structural analysis processing system for aircraft composite parts is disclosed, combining a method for digitally describing damage on composite components with a system that evaluates composite aircraft repair options for a given part design, damage set, and repair history, and provides automatic calculation of the residual strength of damaged metal and composite parts. In addition, this invention provides a system that automatically informs maintenance specialists when they will not be allowed to repair a part based on an automatic structural analysis of that part, and automatically generates an assessment of conformity with engineering acceptance standards that can be used to generate a request for engineering disposition automatically sent to the appropriate engineering or executive authority.