| 摘要 |
The aircraft power margin indicator is of the type which includes the following: - sensors (2,3,4) designed to provide data relative to different monitoring parameters of the engine; - a device (5) which processes the signals from the sensors, and; - a display unit (6) presenting on a screen (7), data relative to the processed parameters, from the engine monitored parameters, whose actual value is the closest to the limit value for the particular parameter. The system has a device (12) for testing the analytical coherence between at least one of the parameters and at least another of the parameters. The device effects a coherence test for the gas ejection temperature (T4) and the motor couple (Cm) with regard to the respective gas generator regime (Ng). These tests are carried out in a stable flight phase. The coherence tests are carried out taking into account the pressure and the ambient temperature and by taking all power samples at the engine.
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