Process for digital diagnosis of a system of actuators in an aircraft undergoing maintenance

An electronic device for diagnosing a condition of a system of actuators of an aircraft turbine engine when the aircraft is on a ground, the device being configured to be coupled, during a diagnosis, to an electrical wiring harness of said turbine engine connecting a computer of said turbine engine to the system of actuators of said turbine engine, the device comprising a power supply block to power said device, a connection block configured to enable the connection of said device to the electrical wiring harness of the turbine engine to be diagnosed, a communication block configured to send information to a user and to receive instructions from the user, and a control block comprising a test signal transmission module and modules for measuring the signals received by the device in response to the test signals over a work cycle of the system of actuators of the turbine engine, the power supply block being configured for self-powering the electronic device by a battery or a power generator, independently of any other system and independently of the turbine engine to diagnose.