Flight Controls Flashcards
In the event of a mechanical failure of the slats/flaps control lever:
(A). The slats/flaps will operate at half speed
(B). The slats/flaps will fail in their present position
(C). The slats/flaps will retract to 0°
(D). An emergency flap switch will allow limited slat and flap selection
An emergency flap switch will allow limited slat and flap selection
Operation of the rudder trim will cause rudder pedal deflection in the direction trim was applied.
t
f
False
Pulling the ROLL DISC handle separates the control wheel interconnect and:
(A). Establishes a cross-side aileron/spoileron relationship
(B). Illuminates a Master Warning ROLL SEL
(C). Gives the pilots control of both spoilerons
(D). Automatically disables spoileron control on jammed side
Establishes a cross-side aileron/spoileron relationship
In the event of a dual engine failure with the APU off, how are the primary flight controls powered?
(A). Hydraulic system 2 via ACMP 2B
(B). Hydraulic system 3 via ACMP 3B
(C). Hydraulic systems 1 and 3
(D). Hydraulic systems 2 and 3
Hydraulic system 3 via ACMP 3B
Both STALL PTCT PUSHER switches must be in the “ON” position for stick pusher activation.
t
f
True
Movement of the primary flight controls is through:
(A). Cable and/or pushrods to the PCUs which hydraulically move the flight controls
(B). Exclusively through fly-by-wire technology
(C). Hydraulic lines running from the control column to the control surface
(D). Electric signals sent by the FEC
Cable and/or pushrods to the PCUs which hydraulically move the flight controls
If the pitch disconnect is pulled, the captain’s control wheel controls:
the left elevator
right elevator
both elevators
neither elevaotrs
The left elevator
Which primary flight controls are powered by all three hydraulic systems?
ailerons
rudder
elevators
a and b
b and c
Rudder
Elevators
Movement of the primary flight controls is transmitted electronically (fly-by-wire) to the aileron, rudder and elevator PCUs that hydraulically move the control surfaces.
t
f
False
Yaw dampening improves an aircrafts stability by damping out oscillations that if not corrected can result in:
uncoordinated flight
mach tuck
dutch roll
reverse sensing
Dutch roll
If both channels of the yaw damper fail, a yaw damper caution message is displayed and
A). If engaged, the autopilot disconnects
B). Rudder trim becomes inoperative
C). Illuminates both yaw damper switchlight
D). Illuminates the yaw disconnect switchlight
If engaged, the autopilot disconnects
Activation of the aileron trim will cause deflection of the control wheels
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f
True
On the ground, with the rudder trim in the neutral position, the trim indication is:
white
green
amber
cyan
Green
The stabilizer (pitch) trim varies from:
+13 degrees (nose down) to -2 degrees (nose up)
+5 degrees (nose down) to -15 degrees (nose up)
+15 degrees (nose down) to -5 degrees (nose up)
+2 degrees (nose down) to -13 degrees (nose up)
+2 degrees (nose down) to -13 degrees (nose up)
The type of horizontal trim that has the highest priority
autopilot
mach trim
captain manual trim
first officer manual trim
Captain manual trim
