System and method for maintaining an aircraft engine

1. A system, comprising:

an aircraft engine that includes high pressure turbine blades, low pressure turbine blades, and a plurality of bearings;

a data logging device associated with the aircraft engine and configured to acquire engine data of the aircraft engine; and

an external device that is external to the data logging device, the external device including processing circuitry configured to

calculate a risk of domestic object damage for the aircraft engine based on the engine data of the aircraft engine acquired from the data logging device via a communication network, wherein the engine data include a record of past failures, a record of repairs of the aircraft engine, a record of operating environment of the aircraft engine, and a record of operating hours of the aircraft engine,

identify a scope and period of a failure coverage cycle based on the calculated risk of domestic object damage for the aircraft engine, wherein the scope of the failure coverage cycle is limited to domestic object damage occurring in the aircraft engine, and the period of the failure coverage cycle corresponds to initiation and termination of the failure coverage cycle,

determine eligibility of the aircraft engine for the scope and the period of the failure coverage cycle based on the calculated risk of domestic object damage for the aircraft engine,

calculate an economic basis for the failure coverage cycle based on the engine data of the aircraft engine acquired from the data logging device, the scope of the failure coverage cycle, and the period of the failure coverage cycle, and

assign the failure coverage cycle to the aircraft engine based on the calculated risk of the domestic object damage for the aircraft engine and the economic basis for the failure coverage cycle.

2. The system according to claim 1 , wherein the processing circuitry is further configured to generate an agreement for the failure coverage cycle, wherein the generated agreement includes the assigned failure coverage cycle, the economic basis for the failure coverage cycle, and a serial number of the aircraft engine.

3. The system according to claim 1 , further comprising:

a display device, wherein

the processing circuitry is further configured to

generate, before assigning the failure coverage cycle, a recommendation indicating the calculated economic basis for the failure coverage and the scope and the period of the failure coverage cycle, and

display the generated recommendation via a graphical user interface on the display device.