| 摘要 |
A turbine engine monitoring and recording system includes an engine mounted unit which contains at least a non-volatile memory and a data-processor, and a remote unit suitable for either cockpit mounting or for accessing by a ground portable unit including an additional data-processor and a display unit. Thermocouples and other sensors mounted on the engine supply raw data to the engine mounted electronics unit, and this input information includes temperature data. Elevated over-temperature levels are segregated and the time during which the engine is within each of the over-temperature bands is measured, and is recorded in a non-volatile, electronically alterable memory which is periodically updated during operation of the aircraft. The number of starts is also counted and stored, and the total running time of the engine is also recorded. Upon command from the remote unit, information is transferred from the non-volatile memory to the remote display unit, so that the time at which the turbine has been operated at specific over-temperature levels may be readily accessed.
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