A method for qualifying a gas turbine engine component comprising: creating a set of substantially identical gas turbine engine components via a uniform manufacturing procedure; determining a set of as-manufactured parameters of each gas turbine engine component in the set of substantially identical gas turbine engine components; determining a variance model of the set of substantially identical gas turbine engine components, wherein the variance model is a mathematical representation of a plurality of characteristics of the substantially identical gas turbine engine components in the set of substantially identical gas turbine engine components, the characteristics describing variations between the substantially identical gas turbine engine components within the set of substantially identical gas turbine engine components; determining a plurality of predicted response models based at least in part on the variance model, each of the predicted response models corresponding to one of an engine type and an engine assembly, and each of the predicted response models being configured to determine a predicted response of including a gas turbine engine component from the set of substantially identical gas turbine engine components in the corresponding one of the engine type and the engine assembly; identifying as-manufactured parameters of a gas turbine engine component, the gas turbine engine component being substantially identical to components in the set of substantially identical gas turbine engine components and being constructed via the uniform manufacturing procedure, and applying the as-manufactured parameters of the gas turbine engine component to each of the predicted response models, thereby generating a predicted response output from each of the predicted response models; and identifying an optimum predicted response from each of the generated predicted response models and associating the engine type or engine assembly that corresponds with the optimum predicted response with a unique part identifier of the gas turbine engine component. creating a set of substantially identical gas turbine engine components via a uniform manufacturing procedure; determining a set of as-manufactured parameters of each gas turbine engine component in the set of substantially identical gas turbine engine components; determining a variance model of the set of substantially identical gas turbine engine components, wherein the variance model is a mathematical representation of a plurality of characteristics of the substantially identical gas turbine engine components in the set of substantially identical gas turbine engine components, the characteristics describing variations between the substantially identical gas turbine engine components within the set of substantially identical gas turbine engine components; determining a plurality of predicted response models based at least in part on the variance model, each of the predicted response models corresponding to one of an engine type and an engine assembly, and each of the predicted response models being configured to determine a predicted response of including a gas turbine engine component from the set of substantially identical gas turbine engine components in the corresponding one of the engine type and the engine assembly; identifying as-manufactured parameters of a gas turbine engine component, the gas turbine engine component being substantially identical to components in the set of substantially identical gas turbine engine components and being constructed via the uniform manufacturing procedure, and applying the as-manufactured parameters of the gas turbine engine component to each of the predicted response models, thereby generating a predicted response output from each of the predicted response models; and identifying an optimum predicted response from each of the generated predicted response models and associating the engine type or engine assembly that corresponds with the optimum predicted response with a unique part identifier of the gas turbine engine component.