問題一覧
1
After an automatic retraction of the flaps with CONF. 1, the flaps will automatically re-extend when speed decreases:
No
2
At landing when passing 30 ft:
The attitude is progressively reduced to 2° nose down, to force the pilot to make a nose up input
3
Elevators, ailerons and spoilers are:
Hydraulically activated and electrically controlled
4
Flight control computers are:
2 ELACs - 3 SECs - 2 FACs
5
How can a deactivated stick be reactivated:
By momentary action on either stick take over push buttons
6
How many control modes are there on the elevator's servo jacks?
3
7
How many electric motors can control the hydraulic motor of the stabilizer:
3
8
How many hydraulic motors drive the screw jack of the stabilizer:
2
9
How many hydraulic systems activate the rudder:
3
10
If ELAC 1 and 2 have failed:
The elevator and pitch trim are controlled by SEC 1 or 2
11
If ELAC 1 and ELAC 2 have failed:
Roll control is provided by spoilers only
12
If FAC 1 and 2 have failed:
The rudder can always be controlled from the pedals
13
If configuration 0 is not selected after take-off, the flaps automatically retract at:
210 kts
14
If neither ELAC 1 nor ELAC 2 are available, pitch control is automatically transferred to:
SEC 1 or SEC 2
15
If one Flap power control unit fails, what happens:
Flaps at half speed
16
If you are flying at an angle of attack more than Alpha Prot, what happens when you release the stick?
Speed returns to Alpha Prot
17
In alternate law, the change to direct law occurs when:
Landing gear down or at the selection of flaps 2 (LGCIU 1 + 2 fault)
18
In flight, if a WTB (wing tip brake) is activated, can you release it?
No
19
In normal law, the flight mode changes to the flare mode when passing:
50 ft
20
In normal law, the stall warning is activated:
Angle of attack corresponding to stall warning can’t be reached in normal law
21
In roll normal law, the bank angle protection is active when bank angle is:
> 67°
22
Is it possible to select an intermediate position with the flaps and slats selector?
No
23
Rudder control is electrical for yaw damping and trim:
Yes
24
Lift augmentation is achieved on each wing by:
2 flap surfaces + 5 slat surfaces
25
SLATS SYS 1 FAULT on the ECAM warning display means:
The slat channel in one SFCC has failed
26
Slat retraction from 1 to 0 is inhibited if angle of attack exceeds 8.5 degrees or speed < 148 knots:
Alpha/Speed Lock
27
The PFD displays in amber the message "USE MAN PITCH TRIM" in
Direct Law
28
The pitch direct law is:
A direct side stick to elevator relationship
29
The pitch normal law provides:
Manoeuvre + high angle of attack + high speed + pitch attitude protection
30
The roll normal law provides combined control of the:
Ailerons + spoilers 2 to 5 + rudder
31
What are the limits for maneuver protection:
Both (+2.5 G - 1 G clean) and (+2 G - 0 flaps extended) are correct
32
What happens when SFCC 1 fails:
Flaps and slats operate at half speed
33
What statement is correct:
Ground spoiler function: all spoilers deploy
34
When ALT LAW is active, the High Speed and High Angle of Attack protections are:
Lost
35
When ALT LAW is active, the Yaw Damping is:
Available (damper authority is limited to ±5 degrees of rudder deflection)
36
When bank angle protection is active, is auto trim inoperative?
Yes
37
When both sticks are moved in the same or opposite direction:
The surface movement is proportional to the algebraic sum of the deflections of both sticks
38
When in CONF 1+F, the flaps retract to 0o automatically at 210 kts:
Automatic Retraction function
39
When is the THS not available?
After yellow and green hydraulic system failure
40
Which ELAC normally controls the elevators and the stabilizer:
ELAC 2
41
Which signals cause rudder pedal movement?
Rudder trim signals
42
Which surfaces are used for lift dumping on ground?
All spoilers, 1 to 5
43
With blue hydraulic system remaining and before landing gear extension, the flight control law is:
Alternate