AIRCRAFT BLEED AIR SYSTEM AND METHOD FOR ITS MONITORING

The aircraft bleed air system comprises an engine (13) comprising a first pressure port (3) and a second pressure port (4); a pressure valve (11) placed downstream of the second pressure port (4); and a pressure regulating valve (2) placed downstream of the first pressure port (3) and the pressure valve (11). [0002] The method comprises detecting a bleed pressure evolution in a transient from a moment when a pressure regulating valve (2) is fully open and a moment in which a pressure valve (11) is opened; determining that the pressure regulating valve (2) functions correctly if the detected pressure transient is higher than a preset value; or determining that the pressure regulating valve (2) is damaged if the detected pressure transient is lower than a preset value, identifying an event. [0003] They permit a predictive maintenance of the valves of the bleed air system.