7. Flight Controls

Question 1

The pitch direct law is:

Accepted Answer

a direct sidestick to elevator relationship

Answer

a load factor demand with no protection

Answer

a direct sidestick to elevator relationship with automatic pitch trim

Answer

achieved through the THS using manual pitch trim control

Question 2

When is the Trimmable Horizontal Stabilizer (THS) not available?

Accepted Answer

if green and yellow hydraulic systems have failed

Answer

if blue hydraulic system has failed

Answer

it is always available manually

Answer

after loss of Flight Augmentation Computer (FAC) 1 and 2

Question 3

below what bank angle will the selected bank angle be maintained with the stick neutral

Accepted Answer

33 deg

Answer

67 deg

Answer

45 deg

Answer

90 deg

Question 4

Which surfaces are used as ground spoilers for lift dumping?

Accepted Answer

all spoilers

Answer

spoilers 1 to 3

Answer

spoilers 2,3,4

Answer

spoilers 1 to 4

Question 5

Which signals cause rudder pedal movement?

Accepted Answer

rudder trim only

Answer

yaw damping

Answer

rudder trim and yaw damping

Answer

turn co-ordination

Question 6

If ELAC (Elevator Aileron Computer) 1 and 2 have failed:?

Accepted Answer

pitch control is automatically transferred to SEC 1 or SEC 2

Answer

pitch control is automatically transferred to SEC 1 or SEC 3

Answer

pitch control is automatically transferred to SEC 3

Answer

pitch control is automatically transferred to ELAC 3

Question 7

If FAC 1 and 2 have failed:?

Accepted Answer

the rudder can still be controlled by the rudder pedals

Answer

rudder control is lost

Answer

rudder control is provided by SEC 3

Answer

rudder control is provided by FMGC 1

Question 8

When both sticks are moved in the same or opposite direction:

Accepted Answer

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

Answer

control surface movement is proportional to the last stick deflected

Answer

control surface movement is proportional to the first stick deflected

Answer

the left stick has priority

Question 9

Elevators, ailerons and spoilers are:

Accepted Answer

electrically controlled and hydraulically actuated

Answer

mechanically controlled and hydraulically actuated

Answer

hydraulically controlled and electrically actuated

Answer

electrically controlled and electrically actuated

Question 10

For yaw damping and trim, rudder control is:

Accepted Answer

electrical

Answer

mechanical

Answer

hydraulic

Answer

pneumatic

Question 11

Which statment is correct?:

Accepted Answer

Ground spoiler function: all spoilers deploy

Answer

Speedbrake function: spoilers 1,2 and 3 deploy

Answer

Roll function: ailerons and spoilers 4 & 5 deploy

Answer

Speedbrake function: all spoilers deploy

Question 12

How many control modes are there on the elevator servo jacks?:

Accepted Answer

3 - active, damping and centering

Answer

2 - active and damping

Answer

1 - active

Answer

3 - active, standby and damping

Question 13

What are the load factor limits?

Accepted Answer

+2.5g and -1g clean; +2.0g and 0g in other configurations

Answer

+2.5g and -1g in all configurations

Answer

+2.0g and 0g in all configurations

Answer

+2.5g and -1g : limits apply only in clean configuration

Question 14

Which Flight Control Computer (FCC) normally controls the elevator and stabilizer:

Accepted Answer

ELAC 2

Answer

ELAC 1

Answer

SEC 1

Answer

SEC 2

Question 15

How many hydraulic motors drive the stabilizer screw jack?

Accepted Answer

2

Answer

0

Answer

1

Answer

3

Question 16

The hydraulic motors for the stabilizer are driven by:

Accepted Answer

one of three electric motors for auto trim and a mechanical trim wheel

Answer

one of two electric motors for auto trim

Answer

an electrical trim wheel

Answer

one of two electric motors

Question 17

In normal law, the flight mode changes to flare mode for landing:

Accepted Answer

when the aircraft passes 50’ RA

Answer

passing 30’ RA

Answer

passing 20’ RA

Answer

passing 350’ RA

Question 18

At landing, as the aircraft descends through 30’:

Accepted Answer

the pitch attitude is reduced to 2° nose down over 8 seconds

Answer

the pitch attitude is memorized

Answer

the attitude is set as an initial reference for pitch attitude control

Answer

the pitch attitude is increased by 2°

Question 19

How can a deactivated stick be reactivated?

Accepted Answer

by momentarily pressing the takeover PB on either stick

Answer

by momentarily pressing the takeover PB on the active stick

Answer

by simultaneously pressing the takeover PB on both sticks

Answer

by momentarily pressing the takeover PB on the deactivated stick

Question 20

In roll normal law, the bank angle protection maintains:

Accepted Answer

roll attitude constant when stick is neutral, up to 33° bank

Answer

roll attitude constant when stick is neutral, up to 45° bank

Answer

maximum bank angle of 45°, provided no other protections are active

Answer

maximum bank angle of 45° with full lateral sidestick deflection

Question 21

Roll normal law combines control of:

Accepted Answer

ailerons, spoilers 2-5 and rudder in the sidestick

Answer

ailerons and all spoilers in the sidestick

Answer

ailerons and speedbrakes in the sidestick

Answer

ailerons and spoilers 2 & 4 in the sidestick

Question 22

If ELAC 1 and 2 are inoperative, roll control is provided by:

Accepted Answer

spoilers 2-5 through the SECs

Answer

ailerons only through the SECs

Answer

ailerons and spoilers 2-5 through the SECs

Answer

spoilers 2 4 only

Question 23

In flight, if a Wing Tip Brake (WTB) is activated

Accepted Answer

it cannot be released and the corresponding surface cannot be operated

Answer

it can be released after applying the ECAM procedure

Answer

it can be released if hydraulic system pressure is available

Answer

it can be released provided there is no asymmetry

Question 24

What happens when SFCC1 fails?

Accepted Answer

flaps and slats operate at half speed

Answer

slat and flap operation remains normal

Answer

flaps are lost

Answer

slats are lost

Question 25

After take-off in CONF 1, if the pilot does not select configuration 0:

Accepted Answer

flaps automatically retract at 210kts

Answer

flaps automatically retract at 180 kts

Answer

flaps and slats automatically retract at 210kts

Answer

there is no automatic retraction feature for slats or flap

Question 26

After an automatic retraction of the flaps:

Accepted Answer

flaps do not automatically re-extend

Answer

flaps automatically re-extend when speed decreases

Answer

flaps do not re-extend unless speed decreased below VLS

Answer

flaps automatically re-extend when speed decreases below green dot

Question 27

Is it possible to select an intermediate flap setting?

Accepted Answer

no, only positions 0,1,2,3 and Full can be selected

Answer

yes, the flap lever can be placed in any position

Answer

yes, but only for certain failure situations

Answer

no, only slats can be selected to an intermediate position

Question 28

If the angle of attack is greater than alpha prot, when the sidestick is released

Accepted Answer

angle of attack reduces to alpha prot

Answer

speed returns to Vls

Answer

cannot fly at an angle greater than alpha prot

Answer

angle of attack remains the same

Question 29

When alternate law is active:

Accepted Answer

high speed and high angle of attack protections are lost

Answer

high speed protection is available

Answer

high angle of attack protection is available

Answer

protections are degraded

Question 30

when the aircraft is in direct law;

Accepted Answer

The pilot controls yaw with the rudder pedals, while the yaw damping and turn coordination functions are lost

Answer

The pilot controls yaw with the rudder pedals, while the yaw damping and turn coordination functions remain

Answer

The autopilot controls yaw with the rudder pedals, while the yaw damping and turn coordination functions remain

Answer

The autopilot controls yaw with the rudder pedals, while the yaw damping and turn coordination functions are lost

Question 31

The slats alpha lock function accomplishes which of the following

Accepted Answer

Prevents slats retracting when the airspeed is too low or angle of attack is too high

Answer

Prevents runaway slats

Answer

Allows you to fly at any angle of attack

Answer

Extends the slats when slats or flaps are 0 and speed<200kts

Question 32

Which hydraulic systems actuate the rudder:

Accepted Answer

Green, Blue and Yellow

Answer

Blue

Answer

Blue and Green

Answer

Blue and Yellow

Question 33

Lift augmentation is achieved on each wing by:

Accepted Answer

2 flap surfaces and 5 slat surfaces

Answer

3 flap surfaces and 4 slat surfaces

Answer

5 spoiler panels

Answer

LAF, using ailerons and spoilers 4 & 5

Question 34

Slat retraction from 1 to 0 is inhibited on A320 if

Accepted Answer

angle of attack > 8.60 or speed < 148

Answer

not inhibited

Answer

speed > 210kts

Answer

angle of attack is greater than alpha prot

Question 35

In alternate law, the change to direct law occurs when:

Accepted Answer

landing gear down (or when Flap 2 selected if LGCIU 1+2 fault)

Answer

landing gear down

Answer

passing 50’ RA

Answer

flap 3 selected

Question 36

Slat SYS 1 Fault on ECAM means:

Accepted Answer

the slat channel in SFCC 1 has failed

Answer

SFCC 1 has failed

Answer

the slat channel in one SFCC has failed

Answer

both slat channels have failed

Question 37

With Hydraulic G+Y failure (Blue system only remaining) the flight control law is

Accepted Answer

direct, after landing gear extension

Answer

alternate, after landing gear extension

Answer

direct, before landing gear extension

Answer

normal, before landing gear extension

Question 38

In flight control normal law, the stall warning is activated:

Accepted Answer

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

Answer

at 148kts if slats are not extended

Answer

when alpha max is reached

Answer

when alpha prot is reached

Question 39

The pitch normal law provides

Accepted Answer

load factor limitation, high angle of attack, and high speed and pitch attitude protection

Answer

load factor limitation, pitch attitude protection and high speed protection

Answer

load factor limitation, high angle of attack and high speed protection

Answer

load factor limitation, pitch attitude protection and low speed stability

7. Flight Controls

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