Patent ID: 9395274
Filing Date: 2016-07-19
CPC Classification: B64D,G01M,G07C

Claim Text:
1. A method for testing an equipment of an aircraft engine, said equipment having variable geometries and being controlled hydraulically by a fuel system comprising a low-pressure circuit, a high-pressure circuit, an aircraft shut-off valve capable of being closed to isolate said circuits from at least one fuel tank, an injection shut-off valve capable of being closed to isolate the high-pressure circuit from an injection chamber of the aircraft engine, and a doser to regulate a rate of fuel sent into the injection chamber, the method comprising: in a first phase, testing, using a computer, the doser while the aircraft shut-off valve is either open or closed; and in a second phase, testing jacks of equipments having variable geometries using said computer while the aircraft shut-off valve is open and during rod extension of said jacks, wherein the second phase comprises controlling the injection shut-off valve so as to eject fuel into the injection chamber during rod retraction of said jacks.