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Questions and Answers
The pitch trim stabilizer moves at a rate of 0.4 degrees per second in the direction commanded.
The pitch trim stabilizer moves at a rate of 0.4 degrees per second in the direction commanded.
True
In the Cruise sub-mode, the FCS will be in Cruise sub-mode when the On-ground sub-mode logic is satisfied.
In the Cruise sub-mode, the FCS will be in Cruise sub-mode when the On-ground sub-mode logic is satisfied.
False
Pitch response is designed to be conventional without any additional damping.
Pitch response is designed to be conventional without any additional damping.
False
Elevator movement is augmented with sensor feedback to provide a more inconsistent response to column input.
Elevator movement is augmented with sensor feedback to provide a more inconsistent response to column input.
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The aircraft provides protection against exceeding the maximum mach number.
The aircraft provides protection against exceeding the maximum mach number.
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Wheel deflection commands aileron and roll-spoiler deflection in Roll Control.
Wheel deflection commands aileron and roll-spoiler deflection in Roll Control.
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The aircraft can only enter Maintenance mode if the aircraft is moving on the ground with the landing gear up.
The aircraft can only enter Maintenance mode if the aircraft is moving on the ground with the landing gear up.
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Pitch trim at nose down limit is a cautionary advisory in the operating manual.
Pitch trim at nose down limit is a cautionary advisory in the operating manual.
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In the event of pitch control miscompare, the pilot and copilot control column positions are different.
In the event of pitch control miscompare, the pilot and copilot control column positions are different.
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Approaching maximum displacement of pitch axis flight control surfaces is a cause for caution according to the operating manual.
Approaching maximum displacement of pitch axis flight control surfaces is a cause for caution according to the operating manual.
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There are limitations established for the elevator control system according to the provided data.
There are limitations established for the elevator control system according to the provided data.
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Both MLG WOW must be false for the FCC to enter Maintenance mode.
Both MLG WOW must be false for the FCC to enter Maintenance mode.
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During normal maneuvering, the entry threshold for AOA limiting sub-mode is approximately 0.88-0.93 normalized AOA regardless of airspeed deceleration rate.
During normal maneuvering, the entry threshold for AOA limiting sub-mode is approximately 0.88-0.93 normalized AOA regardless of airspeed deceleration rate.
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An abrupt nose up control input can trigger the entry into the AOA limiting sub-mode at any normalized angle of attack.
An abrupt nose up control input can trigger the entry into the AOA limiting sub-mode at any normalized angle of attack.
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If the aircraft touches down while in AOA limiting mode, it will transition to takeoff sub-mode.
If the aircraft touches down while in AOA limiting mode, it will transition to takeoff sub-mode.
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Full aft column input results in the aircraft reaching a maximum allowed angle of attack of approximately 0.96 normalized AOA.
Full aft column input results in the aircraft reaching a maximum allowed angle of attack of approximately 0.96 normalized AOA.
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Reducing the angle of attack will keep the aircraft in the AOA limiting mode.
Reducing the angle of attack will keep the aircraft in the AOA limiting mode.
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The FCC AOA Limiting advisory CAS message will be displayed along with Stall Protection Active caution CAS message when the AOA is near its limit value of 0.96.
The FCC AOA Limiting advisory CAS message will be displayed along with Stall Protection Active caution CAS message when the AOA is near its limit value of 0.96.
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