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experienced an uncontained failure of its No. 2 engine stage 1 fan rotor disk assembly. The engine fragments severed the No. 1 and No. 3 hydraulic system lines. Forces from the engine failure fractured the No. 2 hydraulic system line. With the loss of all three hydraulic-powered flight control systems, safe landing was impossible. The lack of independence of the three hydraulic systems, although physically isolated,

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