FLIGHT CONTROLS

Question 1

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

Answer 1

b. a direct side stick to elevator relationship

Question 2

2. 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

Answer 2

b. after yellow and green failure

Question 3

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

Answer 3

c. Direct Law

Question 4

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

Answer 4

a. all spoilers

Question 5

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

Answer 5

b. rudder trim signals

Question 6

6. 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

Answer 6

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

Question 7

7. 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

Answer 7

a. the rudder can always be controlled from the pedals

Question 8

8. 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

Answer 8

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

Question 9

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

Answer 9

c. hydraulically activated and electrically controlled

Question 10

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

Answer 10

a. yes

Question 11

11. 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

Answer 11

a. ground spoiler function: all spoilers deploy

Question 12

12. 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

Answer 12

b. 3 - active, damping and centering

Question 13

13. 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

Answer 13

c. a and b are correct

Question 14

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

Answer 14

b. ELAC 2

Question 15

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

Answer 15

a. 2

Question 16

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

Answer 16

c. 3

Question 17

17. 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

Answer 17

a. SEC 1 or SEC 2

Question 18

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

Answer 18

a. 50 ft

Question 19

19. 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.

Answer 19

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

Question 20

20. 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

Answer 20

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

Question 21

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

Answer 21

c. > 67 degrees

Question 22

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

Answer 22

a. ailerons + spoilers 2 to 5 + rudder

Question 23

23. 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

Answer 23

c. roll control is provided by spoilers only

Question 24

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

Answer 24

b. no

Question 25

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

Answer 25

b. flaps and slats operate at half speed

Question 26

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

Answer 26

b. flaps at half speed

Question 27

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

Answer 27

b. 210 kts

Question 28

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

Answer 28

b. no

Question 29

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

Answer 29

b. no

Question 30

30. 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

Answer 30

b. speed returns to Alpha Prot

Question 31

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

Answer 31

b. lost

Question 32

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

Answer 32

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

Question 33

33. 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

Answer 33

b. Automatic Retraction function

Question 34

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

Answer 34

c. 3

Question 35

36. 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)

Answer 35

a. Alpha/Speed Lock

Question 36

37. 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

Answer 36

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

Question 37

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

Answer 37

b. the slat channel in one SFCC has failed

Question 38

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

Answer 38

a. alternate

Question 39

40. 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

Answer 39

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

Question 40

41. 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

Answer 40

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

Question 41

42. 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

Answer 41

a. after yellow and green hydraulic system failure

Question 42

43. 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

Answer 42

b. 2 ELACs - 3 SECs - 2 FACs

Question 43

44. When bank angle protection is active, is auto trim is inoperative? a. Yes b. No

Answer 43

a. Yes