Flight control system redundancy and hardovers
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Flight control system redundancy and hardovers
I wonder how on earth could be the 737 designed with no redundancy on the rudder system leaving such a risky scenario uncovered in a fail-safe way? (I know they were retrofitted after years.)
Are there other flight control systems which can still show this kind of problem? I think it has to be mandatory to assure a fail-safe system which is critical to flight safety e.g. flight controls, engines and other plausible out of control scenarios due to a single component failure.
I see there are still incident reports (rare, but not to be ignored) over years regarding uncomanded pitch, roll or surface deflection (either FBW or classic hyd systems). Fortunately, most of them, I think even all of them, are nothing comparing to the deadly hardover faced in the 737 rudder PCU problem, but even so, they might be a big threat event in some not very lucky circumstances.
What about nowadays modern airliners flight control redundancy? What do you think guys? How was that possible? Is it still possible, not happened yet and no concern claiming this?
Are there other flight control systems which can still show this kind of problem? I think it has to be mandatory to assure a fail-safe system which is critical to flight safety e.g. flight controls, engines and other plausible out of control scenarios due to a single component failure.
I see there are still incident reports (rare, but not to be ignored) over years regarding uncomanded pitch, roll or surface deflection (either FBW or classic hyd systems). Fortunately, most of them, I think even all of them, are nothing comparing to the deadly hardover faced in the 737 rudder PCU problem, but even so, they might be a big threat event in some not very lucky circumstances.
What about nowadays modern airliners flight control redundancy? What do you think guys? How was that possible? Is it still possible, not happened yet and no concern claiming this?
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Redundancy in a broader view
