FIELD: machine building.
SUBSTANCE: system contains module of identification of base address of gas turbine of the aircraft engine, module of generation of relative address of the gas turbine rotor, module of generation of relative address if rotor disk of the gas turbine, module of generation of signals for the parameters reading of the disk blades, module of parameters registration of the disk blades, module of generation of call signals of subroutine calculating blade exhaust according to running hours, module of registration of blades exhaust based on running hours, module of identification of base address of exhaust ratio of the disk blades, module of generation of reading signals for ratio of running hours exhaust and limit exhaust, module of registration of ratios between blades running exhaust and limit exhaust, module of recognition of category of degree of spent blade service life, module of monitoring of diagnostic monitoring of the disk blades.
EFFECT: increased response by means of exclusion of data search through full data base of the server, and by search localisation as per only reference addresses of data base corresponding to identifiers of the aircraft engine elements.
2 cl, 14 dwg, 3 tbl
