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24 Cards in this Set
- Front
- Back
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The primary flight controls are
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Hydraulically powered and controlled by separate cable runs
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Each aileron is deflected by
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A pair of hydraulically powered controll units
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If both PCUs fail on the same aileron, high speed flutter is prevented by
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A flutter damper
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Aileron position is indicated on the FLIGHT CONTROL synoptic pahe by a
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Transmitter attached to each aileron
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The autopilot servo for aileron control is located in
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The right cable run
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If the ROLL DISC handle is pulled
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The autopilot can still control the bank angle if the jam is on the left side
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The AILERON MON OK advisory EICAS message indicates
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The aileron computer passed its self test
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The AILERON PCU caution EICAS message indicates
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Low pressure in either PCU servo valve for the aileron shown on the FLIGHT CONTROLS synoptic page
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Automatic centering and artificial feel for each elevator is accomplished by
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The related pitch feel unit
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The autopilot elevator servo is located in the
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Left control cable run
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The ELEVATOR SPLIT caution EICAS message indicates
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Elevator positions disagree by 5 degrees or more
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The horizontal stabilizer trim system recieves control signals from
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Manual trim swithches, Mach Trim System and autopilot trim systems
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When pressed, the STAB TRIM DISC swithches disconnect
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Both horizontal stabilizer trim channels
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Mach trim is operative
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While above 0.4 mach when the autopilot is not engaged
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Mach trim signals are generated by the
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Air Data Computers
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If the copilot rudder cable run jams
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Either set of rudder pedals are opperational
Pedal resistance is doubled |
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During high speed flight flight, which YD is available
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YD 1
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The flight spoiler detent mechanism
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Limits asymmetrical spoiler retraction to 20 degrees if the spoiler control linkage fails
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Operation of the ground spoilers
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Is controlled by the PSEU
Requires pressure from hydraulic system No. 1 |
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The flaps are
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Electrically operated by tow motors powered from the main AC buses
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Flap operation and protection against asymmetrical extension is monitored by the
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Flap control unit via signals from the brake/detection units located on each outboard flap panel
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Stickpusher operation
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Requires both stall channels agree to critical AOA
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The stall protection system includes
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A stickpusher in the right elevator control run and a stickshaker on each control column
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The SPS INDICATOR on each side panel
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Must only be used for stall protection system testing
Indicates ignition activation, stickshaker activation and stickpusher activation while airborne when the pointer enters the color coded arc |
