FLIGHT CONTROLS

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After an automatic retraction of the flaps with CONF. 1, the flaps will automatically re-extend when speed decreases:

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

Elevators, ailerons and spoilers are:

Hydraulically activated and electrically controlled

Flight control computers are:

2 ELACs - 3 SECs - 2 FACs

How can a deactivated stick be reactivated:

By momentary action on either stick take over push buttons

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

How many electric motors can control the hydraulic motor of the stabilizer:

How many hydraulic motors drive the screw jack of the stabilizer:

How many hydraulic systems activate the rudder:

If ELAC 1 and 2 have failed:

The elevator and pitch trim are controlled by SEC 1 or 2

If ELAC 1 and ELAC 2 have failed:

Roll control is provided by spoilers only

If FAC 1 and 2 have failed:

The rudder can always be controlled from the pedals

If configuration 0 is not selected after take-off, the flaps automatically retract at:

210 kts

If neither ELAC 1 nor ELAC 2 are available, pitch control is automatically transferred to:

SEC 1 or SEC 2

If one Flap power control unit fails, what happens:

Flaps at half speed

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

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

Landing gear down or at the selection of flaps 2 (LGCIU 1 + 2 fault)

In flight, if a WTB (wing tip brake) is activated, can you release it?

In normal law, the flight mode changes to the flare mode when passing:

50 ft

In normal law, the stall warning is activated:

Angle of attack corresponding to stall warning can’t be reached in normal law

In roll normal law, the bank angle protection is active when bank angle is:

> 67°

Is it possible to select an intermediate position with the flaps and slats selector?

Rudder control is electrical for yaw damping and trim:

Yes

Lift augmentation is achieved on each wing by:

2 flap surfaces + 5 slat surfaces

SLATS SYS 1 FAULT on the ECAM warning display means:

The slat channel in one SFCC has failed

Slat retraction from 1 to 0 is inhibited if angle of attack exceeds 8.5 degrees or speed < 148 knots:

Alpha/Speed Lock

The PFD displays in amber the message "USE MAN PITCH TRIM" in

Direct Law

The pitch direct law is:

A direct side stick to elevator relationship

The pitch normal law provides:

Manoeuvre + high angle of attack + high speed + pitch attitude protection

The roll normal law provides combined control of the:

Ailerons + spoilers 2 to 5 + rudder

What are the limits for maneuver protection:

Both (+2.5 G - 1 G clean) and (+2 G - 0 flaps extended) are correct

What happens when SFCC 1 fails:

Flaps and slats operate at half speed

What statement is correct:

Ground spoiler function: all spoilers deploy

When ALT LAW is active, the High Speed and High Angle of Attack protections are:

Lost

When ALT LAW is active, the Yaw Damping is:

Available (damper authority is limited to ±5 degrees of rudder deflection)

When bank angle protection is active, is auto trim inoperative?

Yes

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

When in CONF 1+F, the flaps retract to 0o automatically at 210 kts:

Automatic Retraction function

When is the THS not available?

After yellow and green hydraulic system failure

Which ELAC normally controls the elevators and the stabilizer:

ELAC 2

Which signals cause rudder pedal movement?

Rudder trim signals

Which surfaces are used for lift dumping on ground?

All spoilers, 1 to 5

With blue hydraulic system remaining and before landing gear extension, the flight control law is:

Alternate

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