Diagnosis of an aircraft engine control unit
A device and a method for diagnosing an engine control unit of an aircraft, the device including an autonomous and mobile electronic diagnostic unit and connecting means for connecting the unit to an engine control unit of an aircraft, the connecting means advantageously including a single connection cable.
1. A device for diagnosing an aircraft engine control unit comprising:
an electronic diagnosis unit, said electronic diagnosis unit being autonomous and mobile and being configured to carry out:
automatic continuity and/or electrical insulation tests of electrical connectors, and determining a health status of these connectors based on the results of the tests, and/or
automatic tests for verifying the internal electrical integrity of the aircraft engine control unit without simulating the flight conditions of the engine to which the aircraft engine control unit is to be connected, and
connecting means configured to connect the electronic diagnosis unit to the aircraft engine control unit of an aircraft engine,
wherein the connecting means comprise a single connection cable which comprises:
a first cable portion including at a free end a first connecting plug for connection to the electronic diagnosis unit, and
a second cable portion connected to the first cable portion and including at second free ends a plurality of second connecting plugs for connection to the aircraft engine control unit and/or to elements of the aircraft engine intended to be connected to the aircraft engine unit.
2. The device according to claim 1 , wherein the cable is constituted by a first stretch with a single branch and by a second stretch with a plurality of parallel branches, the branch of the first stretch being equipped with the first connecting plug at its end opposite the second stretch, and the branches of the second stretch being equipped with the second connecting plugs at their ends opposite the first stretch.
3. The device according to claim 2 , wherein the first stretch has a length L1 and the second stretch has a maximum length L2, L1 being equal to L1 or greater than L2.
4. The device according to claim 2 , wherein at least some of the branches of the second stretch have different lengths.
5. The device according to claim 1 , wherein said device further comprises a portable computer system, the electronic diagnosis unit and and said computer system is configured to communicate by a wireless link.
6. The device according to claim 1 , wherein the second plugs of the cable comprise plugs that are configured to be connected to ports of the aircraft engine control unit, and other plugs that are configured to be connected to complementary plugs of harnesses or items of equipment of the aircraft engine.
7. The device according to claim 1 , wherein the electronic diagnosis unit is configured to measure electrical impedance values, to compare measured values with theoretical values pre-stored in the electronic diagnosis unit, and to emit a signal in accordance with the results of the comparison.
8. The device according to claim 1 , wherein the electronic diagnosis unit comprises a signal and/or data generation module, a signal and/or data acquisition module, at least one signal and/or data storage memory, a signal and/or data processing module and a signal and/or data communication module.
9. The device according to claim 1 , wherein the electronic diagnosis unit is in the form of a suitcase with a closing lid and at least one carrying handle.
10. A method for diagnosing an aircraft engine control unit by means of a device according to claim 1 , wherein said method comprises a step of connecting the single connection cable to the electronic diagnosis unit, to the aircraft engine control unit and/or to the elements of the aircraft engine which is hooked to an aircraft.
11. The method according to claim 10 , wherein the step of connecting to the aircraft engine control unit is performed in a nacelle of the aircraft engine where the aircraft engine control unit is located.
12. The method according to claim 10 , wherein the aircraft engine control unit is an electronic control unit.
13. The device according to claim 3 , wherein L1>k*L2 with a scaling factor k which is at least equal to 2.