The ECU safety system is such that all internal and external fault monitoring circuit outputs are consolidated and passed through a short time‐constant filter to eliminate transient effects. Once this signal appears a 500mS time‐out is started. At the end of this period a lane changeover is initiated together with a cockpit fault warning. If the fault condition is removed during the time‐out period, it is reset.
de Gaye, R. (1986), "Experience of One UK Electronic Equipment Supplier With Bite on Engine/Flight Control Systems Over the Past Ten Years — Part 2", Aircraft Engineering and Aerospace Technology, Vol. 58 No. 10, pp. 10-14. https://doi.org/10.1108/eb036345Download as .RIS
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