| 摘要 |
<p>The device i.e. aircraft condition monitoring system (ACMS) (5), has a monitoring unit (23) for monitoring parameters relating to a transitory phenomenon of an engine (3) of an aircraft. A processing unit (21) triggers the acquisition of values of the parameters at relevant moments depending on the evolution of one of the parameters and generates a report having the parameter values describing a sequence of the transitory phenomenon. An input interface receives data relating to physical parameters obtained from sensors (9a, 9b) located in the engine. An independent claim is also included for a method for monitoring an aircraft engine.</p> |
