A computer-implemented method of modeling and integrating aircraft engine installation deltas (EIDs) using a computing environment comprising a data terminal connected to a data server and to one or more aircraft sensors that indicate one or more operational conditions, the data server collecting data for aggregation and analysis and including a modeling integration system that periodically receives condition indicator data and other data, models EIDs and integrates such modeling with systems that profile engines, the modeling integration system including an EID modeler and an engine performance profiler, the method comprising: receiving by the EID modeler flight data related to an aircraft comprising an engine installed therein, the flight data comprising values for engine parameters, flight parameters, power parameters and measured EIDs; determining by the EID modeler values of the measured EIDs for the engine based, at least in part, on the flight data; determining by the EID modeler values of measured power parameters for the engine based, at least in part, on the flight data; receiving by the EID modeler specification data for the engine in its uninstalled state; establishing by the EID modeler values of unmeasured EIDs, an unmeasured EID being an EID for which no values are included in the flight data; generating by the EID modeler a mathematical model of a plurality of EIDs for the engine as a function of one or more of the engine parameters, wherein the plurality of EIDs comprise the measured EIDs and the unmeasured EIDs; validating by the EID modeler the mathematical model based, at least in part, on the values of the measured installation delta; determining by the EID modeler whether the validation was successful; if the validation was successful, integrating by the EID modeler the validated mathematical model with an engine performance profiling program; and generating by the EID modeler and engine performance profiler a performance profile of the engine in its installed state using the validated mathematical model based, at least in part, on one or more input values for the engine parameter. receiving by the EID modeler flight data related to an aircraft comprising an engine installed therein, the flight data comprising values for engine parameters, flight parameters, power parameters and measured EIDs; determining by the EID modeler values of the measured EIDs for the engine based, at least in part, on the flight data; determining by the EID modeler values of measured power parameters for the engine based, at least in part, on the flight data; receiving by the EID modeler specification data for the engine in its uninstalled state; establishing by the EID modeler values of unmeasured EIDs, an unmeasured EID being an EID for which no values are included in the flight data; generating by the EID modeler a mathematical model of a plurality of EIDs for the engine as a function of one or more of the engine parameters, wherein the plurality of EIDs comprise the measured EIDs and the unmeasured EIDs; validating by the EID modeler the mathematical model based, at least in part, on the values of the measured installation delta; determining by the EID modeler whether the validation was successful; if the validation was successful, integrating by the EID modeler the validated mathematical model with an engine performance profiling program; and generating by the EID modeler and engine performance profiler a performance profile of the engine in its installed state using the validated mathematical model based, at least in part, on one or more input values for the engine parameter.