| 摘要 |
The system (1) has control units (2A, 2B) e.g. electronic engine control units, associated with respective engines of an aircraft. A data transmission unit (4) connects the control units to a monitoring unit (5). The monitoring unit automatically receives configuration information from the control units. A warning unit (7) is connected to the monitoring unit. The warning unit automatically emits a warning signal to inform an operator i.e. pilot, about an incompatibility between the configuration information during receiving incompatibility information from the monitoring unit. |
