Patent ID: 8467913

Claim:
A fault diagnosis apparatus for at least one system of an aircraft, the fault diagnosis system comprising: a number N 1 , n 1 ε[ 1 , . . . , N 1 ], of systems, wherein the n 1 -th system, in each case, is configured to provide a number N 2 , n 2 ε[ 1 , . . . , N 2 ], of instances of a main function of a number N 3 , n 3 ε[ 1 , . . . , N 3 ] of main functions of the aircraft; a number N 4 , n 4 ε[ 1 , . . . , N 4 ], of IMA modules, wherein the n 4 -th IMA module, in each case, is configured to provide resources at least to the respective n 2 -th instances of the main functions; a generic diagnostic unit comprising a predetermined number N 5 , n 5 ε[ 1 , . . . , N 5 ], of instances of the generic diagnostic unit; and wherein, the n 5 -th instance, in each case, of the generic diagnostic unit is configured for adaption of the corresponding n 5 -th diagnostic unit to at least one system.