Patent ID: 8000844

Claim:
A test system for an aircraft for testing a flight control system of the aircraft, said test system comprising: said flight control system which comprises at least one flight control computer which comprises: a first processor that implements a functional mode; a second processor that implements a test mode, in which the flight control computer can be subjected to commands received from the exterior; a switch that switches between said first and second processors; and an interface that transmits, in the test mode, to the exterior information available in said flight control computer and receives commands from the exterior; and a test device which comprises a connector that connects, in a detachable manner, to a communication bus of said flight control computer, and which cooperates with said second processor in a test phase, wherein: said interface transmits, in the functional mode, to the exterior the information available in said flight control computer; and said test device operates in one of the following two operational phases: a test phase, in which said test device cooperates with said second processor of the flight control computer which is then in the test mode so as to allow the taking over of said flight control computer, said taking over comprising sending commands to the flight control computer and having access to information generated by such taking over; and a data reception phase, in which said test device cooperates with said first processor of the flight control computer which is then in the functional mode so as to have access in real time to the information, including fault indications, which is available on said flight control computer, without affecting its behavior.