A method for maintaining a gas turbine engine component comprising: training, by a computer system, a maintenance schedule module via: receiving a set of measured parameters for each gas turbine engine component in a set of single route gas turbine engine components, wherein each single gas turbine engine component has been exposed to a substantially identical route for a substantially identical duration and was manufactured using one of a single manufacturing process and a uniform combination of processes, generating a variation model of the set of single route gas turbine engine components, wherein the variation model models variations of single route gas turbine engine components for the specific manufacturing process or processes and a specific wear case of the single route for the set of substantially identical gas turbine engine components, based on the measured set of substantially identical gas turbine engine components, iteratively running a simulation where each of the single route components is incorporated into a simulated engine, and a computer simulation is run to determine how each single route gas turbine engine component is expected to operate within a mathematical model of the simulated engine, and correlating variations in the set of parameters between each of the single route gas turbine engine components and each other single route component with variations in the operation of the corresponding simulation results, generating a predictive model based on the variations where the correlated variations from the simulation results are applied to the variation model, wherein the predictive model provides a prediction of an expected wear pattern of a component if the component is used along the single route; and wherein the method further comprises: generating a maintenance schedule, by the computer system, for a second gas turbine engine component, substantially identical to each gas turbine engine component in the set of single route gas turbine engine components by the predictive model applying the expected wear pattern to the as-manufactured second gas turbine engine component and determining an expected amount of flight hours that the component can be operated before a repair operation is required, provided the component is utilized in the single route. receiving a set of measured parameters for each gas turbine engine component in a set of single route gas turbine engine components, wherein each single gas turbine engine component has been exposed to a substantially identical route for a substantially identical duration and was manufactured using one of a single manufacturing process and a uniform combination of processes, generating a variation model of the set of single route gas turbine engine components, wherein the variation model models variations of single route gas turbine engine components for the specific manufacturing process or processes and a specific wear case of the single route for the set of substantially identical gas turbine engine components, based on the measured set of substantially identical gas turbine engine components, iteratively running a simulation where each of the single route components is incorporated into a simulated engine, and a computer simulation is run to determine how each single route gas turbine engine component is expected to operate within a mathematical model of the simulated engine, and correlating variations in the set of parameters between each of the single route gas turbine engine components and each other single route component with variations in the operation of the corresponding simulation results, generating a predictive model based on the variations where the correlated variations from the simulation results are applied to the variation model, wherein the predictive model provides a prediction of an expected wear pattern of a component if the component is used along the single route; and wherein the method further comprises: generating a maintenance schedule, by the computer system, for a second gas turbine engine component, substantially identical to each gas turbine engine component in the set of single route gas turbine engine components by the predictive model applying the expected wear pattern to the as-manufactured second gas turbine engine component and determining an expected amount of flight hours that the component can be operated before a repair operation is required, provided the component is utilized in the single route.