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CAE Q 2 > Flight controls > Flashcards

Flight controls Flashcards

1
Q

The number of flight spoilers located on each wing is:

a) 2.
b) 3.
c) 4.
d) 6.

A

4.

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2
Q

The Flap/Slat Electronic Unit (FSEU) does not provide:
a) LE skew detection for slats 2 through 7, except during autoslat operation.
b) TE asymmetry protection by removing hydraulic pressure to the TE flaps if an
asymmetry is detected.
c) Overspeed protection for LE devices.
d) Protection from uncommanded motion by LE devices or TE flaps.

A

c) Overspeed protection for LE devices.

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3
Q

The flap load relief system is operational at the:

a) Flaps 10, 15, 25, 30 and 40 positions.
b) Flaps 25, 30 and 40 positions.
c) Flaps 30 and 40 positions.
d) Flaps 40 position only.

A

a) Flaps 10, 15, 25, 30 and 40 positions.

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4
Q

When the speedbrakes are deployed in flight, the SPEEDBRAKES EXTENDED
light:
a) Always illuminates.
b) Illuminates only when the speedbrakes are deployed uncommanded.
c) Illuminates only when the radio altitude is less than 800 feet.
d) Illuminates when the radio altitude is less than 800 feet, or the TE flaps are extended
beyond flaps 10.

A

Illuminates when the radio altitude is less than 800 feet, or the TE flaps are extended
beyond flaps 10.

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5
Q

Hydraulic system B is lost. Which statement is correct:
a) The main yaw damper is inoperative. The YAW DAMPER light will illuminate when
the system Flight Control Switch is selected to STBY RUD. The Yaw Damper switch
cannot be reset.
b) The main yaw damper is inoperative. The standby yaw damper will start to operate
when the system B Flight Control Switch is selected to STBY RUD and the Yaw
Damper Switch is reset.
c) Operation of the main yaw damper is not affected by a loss of hydraulic system B.
d) None of the above.

A

a) The main yaw damper is inoperative. The YAW DAMPER light will illuminate when
the system Flight Control Switch is selected to STBY RUD. The Yaw Damper switch
cannot be reset.

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6
Q

lf wheel spin-up is not detected on landing with the SPEED BRAKE lever in the
armed position, the flight spoilers will deploy automatically:
a) When any gear strut compresses.
b) Only when the right main landing gear strut compresses.
c) Only when the left main landing gear strut compresses.
d) When reverse thrust is selected.

A

a) When any gear strut compresses.

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7
Q

To operate the Feel system, the Elevator Feel Computer uses:

a) Either hydraulics system A or B pressure.
b) Either hydraulics system A or B pressure (whichever is higher).
c) Hydraulics system A.
d) Hydraulics system B.

A

b) Either hydraulics system A or B pressure (whichever is higher).

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8
Q

A Mach Trim system provides speed stability at the higher Mach numbers…Mach
trim is automatically accomplished above:
a) Mach 0.50.
b) Mach 0.615.
c) Mach 0.655.
d) Mach 0.70.

A

b) Mach 0.615.

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9
Q

The trailing edge flaps are at 15 units. The correct indication on the aft overhead
panel for the leading edge devices is:
a) All amber TRANSIT lights illuminated.
b) All LE devices EXT lights illuminated.
c) All LE devices FULL EXT lights illuminated.
d) LE slats EXT lights and LE flaps FULL EXT lights illuminated.

A

d) LE slats EXT lights and LE flaps FULL EXT lights illuminated.

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10
Q

The amber LE FLAPS TRANSIT light:

a) Indicates all LE Devices are fully extended.
b) Indicates LE Slats are fully extended.
c) Is inhibited during Autoslat operation inflight.
d) Provides TE Flaps asymmetry protection.

A

c) Is inhibited during Autoslat operation inflight.

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11
Q

What is the maximum flap extension altitude?

a) 10 000 feet.
b) 17 000 feet.
c) 20 000 feet.
d) 23 000 feet.

A

c) 20 000 feet.

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12
Q

.The flight spoilers rise on the wing with up aileron and remain faired on the wing
with down aileron. When the control wheel is displaced more than approximately
____ degrees, spoiler deflection is initiated.
a) 6°.
b) 8°.
c) 10°.
d) 12°.

A

c) 10°.

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13
Q

The Speed Trim System (STS) operates most frequently during takeoff & goaround.
Conditions for speed trim operation are…
a) Airspeed between 100 KIAS and Mach 0.60, 10 seconds after takeoff, 5 seconds
following release of trim switches, autopilot not engaged, sensing of
trim requirement.
b) Airspeed between 100 KIAS and Mach 0.60, 10 seconds after takeoff, 10 seconds
following release of trim switches, sensing of trim requirement.
c) Airspeed between 100 KIAS and Mach 0.60, 15 seconds after takeoff, 10 seconds
following release of trim switches,, sensing of trim requirement.
d) Airspeed between 100 KIAS and Mach 0.60, 15 seconds after takeoff, 5 seconds
following release of trim switches, autopilot engaged, sensing of trim
requirement.

A

a) Airspeed between 100 KIAS and Mach 0.60, 10 seconds after takeoff, 5 seconds
following release of trim switches, , autopilot not engaged, sensing of
trim requirement.

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14
Q

The amber FEEL DIFF PRESS light illuminates when the:
a) Flaps are up and a pressure-imbalance between hydraulic systems A & B is detected
or if one of the elevator feel pitot systems fails.
b) Flaps are not up and a hydraulic pressure imbalance is detected or one of the
elevator feel pitot systems fails.
c) Flaps are up or down and a hydraulic pressure imbalance is detected or if one of the
elevator pitot systems fails.
d) No correct answer is provided.

A

Flaps are up or down and a hydraulic pressure imbalance is detected or if one of the
elevator pitot systems fails.

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15
Q

.In the event of an elevator jam, transfer mechanisms allow:
a) For lighter than normal forces to be used on the control column for take-off and
landing.
b) The control columns to be physically separated.
c) Applying force against the jam will breakout only the Captain’s control column.
d) The elevator feel and centring unit to transfer proper aerodynamic forces to the
control columns.

A

b) The control columns to be physically separated.

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16
Q

Main electric trim authority limit is:

a) Flaps retracted 3.95 to 14.5 units.
b) Flaps retracted 3.95 to 12.5 units.
c) Flaps retracted 0.20 to 16.9 units.
d) Flaps retracted 0.5 to 14.5 units.

A

a) Flaps retracted 3.95 to 14.5 units.

17
Q

Conditions for speed trim operation include:

a) 5 seconds after take-off.
b) Ten seconds after release of trim switches.
c) 100 KIAS – M 0.60.
d) N1 above 50%.

A

c) 100 KIAS – M 0.60.

18
Q

When hydraulic system B is lost: (System A operating):
a) Main yaw damper functions are available as long as hydraulic system A is providing
normal pressure and the yaw damper switch is ON.
b) Standby yaw damper functions are available as long as hydraulic system A is
providing normal pressure and the yaw damper switch is ON.
c) Main and standby yaw damper functions are inoperative.
d) Standby yaw damper functions are available if the FLT CONTROL B switch is placed
to STBY RUD and the YAW DAMPER switch is reset to ON.

A

c) Main and standby yaw damper functions are inoperative.

19
Q

Yaw damper inputs (main or standby) can be overridden:

a) Only when the yaw damper switch is OFF.
b) By trim inputs but not rudder pedal inputs.
c) By rudder pedal inputs but not trim inputs.
d) By either trim or rudder pedal inputs.

A

d) By either trim or rudder pedal inputs.

20
Q

The number of ground spoilers located on each wing is:

a) 2.
b) 3.
c) 4.
d) 6.

A

a) 2.

21
Q

The number of slats located on each wing is:

a) 2.
b) 3.
c) 4.
d) 6.

A

c) 4.

22
Q

Decreasing airspeed during descent from altitude by using speedbrakes. The
correct position of the SPEEDBRAKE LEVER is:
a) ARMED.
b) FLIGHT DETENT.
c) UP.
d) Any intermediate position.

A

b) FLIGHT DETENT.

23
Q

The ALTERNATE FLAPS master switch:
a) Fully extends the LE devices using standby hydraulic pressure and electrically
extends the TE flaps.
b) Closes the flight spoiler shutoff valve.
c) Activates the standby hydraulic pump and pressurizes the standby rudder power
control unit.
d) Arms the ALTERNATE FLAPS position switch, activates the standby hydraulic pump
and closes the trailing edge flaps bypass valve.

A

d) Arms the ALTERNATE FLAPS position switch, activates the standby hydraulic pump
and closes the trailing edge flaps bypass valve.

24
Q

The autoslat system:
a) Provides for slat deployment above Vmo/Mmo.
b) Drives the slats to the full-extended position when the TE flaps 1 through 25 are
selected and the airplane approaches a stall.
c) Is normally powered by hydraulic system A.
d) Is normally powered by the Power Transfer Unit (PTU).

A

b) Drives the slats to the full-extended position when the TE flaps 1 through 25 are
selected and the airplane approaches a stall.

25
Q

The Power Transfer Unit (PTU) provides an alternate source of power for the
autoslat system if:
a) A loss of hydraulic system A pressure is sensed.
b) The hydraulic system A engine driven pump is inoperative.
c) The alternate flaps position switch is momentarily held down.
d) Pressure from the Hydraulic system B engine driven pump drops below limits.

A

d) Pressure from the Hydraulic system B engine driven pump drops below limits.

26
Q

In addition to hydraulic system A and B, the rudder can also be powered by the
standby hydraulic system through the:
a) System A standby rudder power control unit.
b) System B standby rudder power control unit.
c) Standby rudder power control unit
d) Main rudder power control unit

A

c) Standby rudder power control unit

27
Q 
The elevator feel computer provides elevator system feel. This computer receives
inputs from:
a) Altitude and elevator position.
b) Elevator balance tabs position.
c) Only system A hydraulic pressure.
d) Airspeed and stabilizer position.
A

d) Airspeed and stabilizer position.

28
Q

Select the correct statement:
a) The primary flight controls are powered by hydraulic system A and B, with backup
from the standby hydraulic system for the rudder and manual reversion for the aileron
and elevator.
b) Flight spoilers are used both for roll control, descent and deceleration.
c) The trailing edge flaps can be both extended and retracted using the alternate flap
drive system.
d) All statements are correct

A

d) All statements are correct.

CAE Q 2 (15 decks)

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