| Summary: | 碩士 === 大同大學 === 機械工程學系(所) === 94 === Today’s commercial aircraft mainly uses FADEC engine to provide thrust power for aircraft operation. The main function of FADEC is to control the engine thrust power and maintains optimal performance via EEC. The EEC, which is installed on engine, receives signals from engine or airframe system to control engine and to prevent engine from stalling or surging. Moreover, the monitor system of EEC is also capable of detecting malfunction or failure condition during engine operation.
In operating experience of PW4158 FADEC engine, it is shown that 2.5 bleed system, stator vane actuator system and turbine case cooling system, which are designed to control compressor and turbine section, could cause EEC unable to identify the mechanical failure due to lack of correct feedback. Because the feedback sensor is installed at the actuator, the EEC is unable to detect failure of downstream mechanism of actuator if the related components are damaged. The undetectable situation of EEC will lead to non-cockpit warning effect and cause difficulties for maintenance personnel in determining the root causes of failure in trouble shooting procedure.
This thesis aims to focus on the undetectable failure of A300-600R PW4000 FADEC engine in the cockpit, and to carry out 2.5 bleed, SVA and TCC system experiment by mean of FADEC ground test of the engine control system actuators. Subsequently, use the test result of engine actuator test to figure out the undetectable failure related to above-mentioned systems. Finally, the proposals of R.I.I (required inspection item), D.V.I (detail visual inspection) and PTR (practical training record) are built into the maintenance system to provide duplicate inspection procedure 、detail inspection procedure and thorough training course to improve current maintenance plan and reduce risk of engine surge or malfunction due to undetectable mechanical failure.
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