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TKE-P > FLIGHT CONTROLS > Flashcards

FLIGHT CONTROLS Flashcards

1
Q
  1. The pitch direct law is:
    a. a load factor demand with no protection
    b. a direct side stick to elevator relationship

c. a direct side stick to elevator relationship with
AUTOTRIM operation

d. achieved through the THS using manual trim control

A

b. a direct side stick to elevator relationship

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2
Q
  1. When is the THS not available?
    a. after blue hydraulic system failure
    b. after yellow and green failure
    c. never lost, always available manually
    d. after loss of FAC 1 and 2
A

b. after yellow and green failure

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3
Q
  1. The PFD displays in amber the message “USE MAN PITCH TRIM” in
    a. Normal Law
    b. Alternate Law
    c. Direct Law
A

c. Direct Law

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4
Q
  1. Which surfaces are used for lift dumping?
    a. all spoilers
    b. spoilers 1 to 3
    c. spoilers 1 to 4
A

a. all spoilers

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5
Q
  1. Which signals cause rudder pedal movement?
    a. yaw damping signals
    b. rudder trim signals
    c. turn coordination signals
A

b. rudder trim signals

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6
Q
  1. If ELAC 1 and 2 have failed:
    a. pitch control is provided by the FAC’s
    b. pitch control can only be achieved from the trim wheel
    c. the elevator and pitch trim are controlled by SEC 1 or 2
A

c. the elevator and pitch trim are controlled by SEC 1 or 2

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7
Q
  1. If FAC 1 and 2 have failed:
    a. the rudder can always be controlled from the pedals
    b. the rudder control is lost
    c. the rudder control is provided by SEC 3
A

a. the rudder can always be controlled from the pedals

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8
Q
  1. When both sticks are moved in the same or opposite direction:
    a. the surface movement is proportional to the algebraic sum of the deflections of both sticks
    b. the surface movement is proportional to the last stick deflected
    c. the surface movement is proportional to the first stick deflected
    d. the left stick has a priority
A

a. the surface movement is proportional to the algebraic sum of the deflections of both sticks

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9
Q
  1. The elevator, ailerons, spoilers are:
    a. hydraulically activated and mechanically controlled
    b. electrically activated and hydraulically controlled
    c. hydraulically activated and electrically controlled
A

c. hydraulically activated and electrically controlled

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10
Q
  1. Rudder control is electrical for yaw damping and trim:
    a. yes
    b. no
A

a. yes

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11
Q
  1. What statement is correct:
    a. ground spoiler function: all spoilers deploy
    b. speed brake function: spoilers 1, 2, 3 deploy
    c. roll function: ailerons + spoilers 4 and 5 deploy
A

a. ground spoiler function: all spoilers deploy

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12
Q
  1. How many control modes are there on the elevators servo jacks?
    a. 2 - active and damping
    b. 3 - active, damping and centering
    c. 4 - active, semi-active, damping and centering
A

b. 3 - active, damping and centering

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13
Q
  1. What are the limits for maneuvre protection:
    a. +2.5 G, -1 G clean
    b. +2.0 G, -0 G when Flaps extended
    c. a and b are correct
A

c. a and b are correct

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14
Q
  1. Which ELAC normally controls the elevators and the stabilizer:
    a. ELAC 1
    b. ELAC 2
A

b. ELAC 2

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15
Q
  1. How many hydraulic motors drive the screw jack of the stabilizer:
    a. 2
    b. 3
A

a. 2

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16
Q
  1. How many electric motors can control the hydraulic motor of the stabilizer:
    a. 1
    b. 2
    c. 3
A

c. 3

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17
Q
  1. If neither ELAC 1 nor ELAC 2 are available, pitch control is automatically transferred to:
    a. SEC 1 or SEC 2
    b. SEC 1 or SEC3
    c. Sec 3
A

a. SEC 1 or SEC 2

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18
Q
  1. In normal law, the flight mode changes to the landing mode when passing:
    a. 50 ft
    b. 100 ft
A

a. 50 ft

19
Q
  1. At landing when passing 30 ft:
    a. the altitude is memorized
    b. the altitude is progressively reduced to 2º nose down over a period of 8 secs.
A

b. the altitude is progressively reduced to 2º nose down over a period of 8 secs.

20
Q
  1. How can a deactivated stick be reactivated:
    a. by momentary action on take over push button of the active stick
    b. by momentary action on either stick take over push buttons
    c. by momentary action on take over push button of deactivated stick
A

b. by momentary action on either stick take over push buttons

21
Q
  1. In roll normal law, the bank angle protection is active when bank angle is:
    a. > 45 degrees
    b. > 33 degrees
    c. > 67 degrees
A

c. > 67 degrees

22
Q
  1. The roll normal law provides combined control of the:
    a. ailerons + spoilers 2 to 5 + rudder
    b. ailerons + spoilers 2 to 5
A

a. ailerons + spoilers 2 to 5 + rudder

23
Q
  1. If ELAC 1 and ELAC 2 have failed:
    a. roll control is provided by ailerons only
    b. roll control is provided by ailerons and spoilers
    c. roll control is provided by spoilers only
A

c. roll control is provided by spoilers only

24
Q
  1. In flight, if a WTB (wing tip brake) is activated, can you release it:
    a. yes
    b. no
A

b. no

25
Q
  1. What happens when SFCC 1 fails:
    a. nothing
    b. flaps and slats operate at half speed
    c. flaps system lost
A

b. flaps and slats operate at half speed

26
Q
  1. If one Flap power control unit fails, what happens:
    a. nothing
    b. flaps at half speed
    c. flaps are lost
A

b. flaps at half speed

27
Q
  1. If CONF. 0 is not selected after take-off, the flaps automatically retract at:
    a. >180 kts
    b. 210 kts
    c. V2
A

b. 210 kts

28
Q
  1. After an automatic retraction of the flaps with CONF. 1, the flaps will automatically re-extend when speed decreases:
    a. yes
    b. no
A

b. no

29
Q
  1. Is it possible to select an intermediate position with the flaps and slats selector:
    a. yes
    b. no
A

b. no

30
Q
  1. If you are flying at an angle of attack more than Alpha Prot, what happens when you release the stick:
    a. speed returns to VLS
    b. speed returns to Alpha Prot
A

b. speed returns to Alpha Prot

31
Q
  1. When ALT LAW is active, the High Speed and High Angle of Attack protections are:
    a. degraded
    b. lost
A

b. lost

32
Q
  1. When ALT LAW is active, the Yaw Damping is:
    a. available (damper authority is limited to ±5 degrees of rudder deflection)
    b. lost
A

a. available (damper authority is limited to ±5 degrees of rudder deflection)

33
Q
  1. When in CONF 1+F, the flaps retract to 0º automatically at 210 kts:
    a. Alpha/Speed Lock function
    b. Automatic Retraction function
    c. Flap Load Relief function
A

b. Automatic Retraction function

34
Q
  1. How many hydraulic systems activate the rudder:
    a. 1
    b. 2
    c. 3
A

c. 3

35
Q
  1. Slat retraction from 1 to 0 is inhibited if angle of attack exceeds 8.5º or speed goes down below 148 KTS, this function is called:
    a. Alpha/Speed Lock
    b. Automatic Retraction System (ARS)
    c. Flap Load Relief System (FLRS)
A

a. Alpha/Speed Lock

36
Q
  1. In alternate law, the change to direct law occurs when:
    a. landing gear down or at the selection of flaps 2 (LGCIU 1 + 2 fault)
    b. landing gear down
    c. passing 50 ft
A

a. landing gear down or at the selection of flaps 2 (LGCIU 1 + 2 fault)

37
Q
  1. Slats SYS 1 fault on the ECAM warning display means:
    a. SFCC 1 has failed
    b. the slat channel in one SFCC has failed
A

b. the slat channel in one SFCC has failed

38
Q
  1. With hydraulic blue system remaining and before landing gear extension, the flight control law is:
    a. alternate
    b. normal
    c. direct
A

a. alternate

39
Q
  1. In flight control normal law, the stall warning is activated:
    a. if slats are not extended when reaching a speed of 148 knots
    b. when Alpha Max is reached
    c. when Alpha Prot is reached

d. angle of attack corresponding to stall warning cannot
be reached in normal law

A

d. angle of attack corresponding to stall warning cannot

be reached in normal law

40
Q
  1. The pitch normal law provides:
    a. manoeuvre protection + pitch attitude protection + high speed protection
    b. manoeuvre protection + high angle of attack protection + high speed protection
    c. manoeuvre + high angle of attack + high speed + pitch attitude protection
    d. manoeuvre protection + pitch attitude protection + low speed stability
A

c. manoeuvre + high angle of attack + high speed + pitch attitude protection

41
Q
  1. When is the THS not available?
    a. after yellow and green hydraulic system failure
    b. never lost, always available manually
    c. after blue hydraulic system failure
    d. after loss of FAC 1 and 2
A

a. after yellow and green hydraulic system failure

42
Q
  1. Flight control computers are:
    a. 2 ELACs - 2 SECs - 3 FACs
    b. 2 ELACs - 3 SECs - 2 FACs
    c. 3 ELACs - 2 SECs - 2 FACs
A

b. 2 ELACs - 3 SECs - 2 FACs

43
Q
  1. When bank angle protection is active, is auto trim is inoperative?
    a. Yes
    b. No
A

a. Yes

TKE-P (17 decks)

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