Flight Control

51問 • 1年前

Angelo Ortiz

通報

問題一覧

The pitch direct law is:

A direct side stick to elevator relationship

How many degrees down do the ailerons extend (aileron drop)?

They extend 5 degree down when the flaps are extended

Which surfaces are used for lift dumping on ground?

All spoilers, 1 to 5

Which signals cause rudder pedal movement?

Rudder trim signals

If ELAC 1 and 2 have failed:

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

If FAC 1 and 2 have failed:

The rudder can always be controlled from the pedals

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

Elevators, ailerons and spoilers are:

Hydraulically activated and electrically controlled

Rudder control is electrical for yaw damping and trim:

Yes

What statement is correct:

Ground spoiler function: all spoilers deploy

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

What are the limits for maneuver protection:

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

Which ELAC normally controls the elevators and the stabilizer:

ELAC 2

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

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

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

50 ft

How can a deactivated stick be reactivated:

By momentary action on either stick take over push buttons

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

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

> 67°

The roll normal law provides combined control of the:

Ailerons + spoilers 2 to 5 + rudder

If ELAC 1 and ELAC 2 have failed:

Roll control is provided by spoilers only

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

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

210 kts

What happens when SFCC 1 fails:

Flaps and slats operate at half speed

After FLAP retraction, when is CONF 1+F available again?

At 100 kt or less

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

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

When roll direct law is active, the yaw damping is:

Lost

Sideslip target:

To indicate how much rudder to use to get the best climb performance in case of engine failure

How many hydraulic systems activate the rudder:

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

Alpha/Speed Lock

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

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

SLATS SYS 1 FAULT on the ECAM warning display means:

The slat channel in one SFCC has failed

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

Alternate

In normal law, the stall warning is activated:

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

The pitch normal law provides:

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

When is the THS not available?

After yellow and green hydraulic system failure

Flight control computers are:

2 ELACs - 3 SECs - 2 FACs

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

Yes

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

Direct Law

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

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

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

Automatic Retraction function

Lift augmentation is achieved on each wing by:

2 flap surfaces + 5 slat surfaces

Which flight control computer normally operates the ailerons?

Elevator and aileron computer (ELAC) 1

In normal law, what happens if the pilot holds full lateral side stick deflection?

The bank angle goes to 67° and no further

What is true regarding the flight controls on an A320?

They are all electrically controlled and hydraulically activated

Which spoilers are ground spoilers?

Spoilers 1-5

ドローン

ドローン

パート15

パート15

パート8

パート8

パート7

パート7

パート19

パート19

パート18

パート18

パート9

パート9

パート5

パート5

航空機性能

航空機性能

飛行計画

飛行計画

航空管制

航空管制

航法

航法

航空機一般

航空機一般

特例/事前照会/検査・証明

ユーザ名非公開 · 15問 · 11ヶ月前

特例/事前照会/検査・証明

気象支援（上田）

気象支援（上田）

原告適格の肯否

原告適格の肯否

キャリアコード

キャリアコード

航空会社 2レターコード

航空会社 2レターコード

航空用語

航空用語

問題一覧

The pitch direct law is:

A direct side stick to elevator relationship

How many degrees down do the ailerons extend (aileron drop)?

They extend 5 degree down when the flaps are extended

Which surfaces are used for lift dumping on ground?

All spoilers, 1 to 5

Which signals cause rudder pedal movement?

Rudder trim signals

If ELAC 1 and 2 have failed:

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

If FAC 1 and 2 have failed:

The rudder can always be controlled from the pedals

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

Elevators, ailerons and spoilers are:

Hydraulically activated and electrically controlled

Rudder control is electrical for yaw damping and trim:

Yes

What statement is correct:

Ground spoiler function: all spoilers deploy

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

What are the limits for maneuver protection:

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

Which ELAC normally controls the elevators and the stabilizer:

ELAC 2

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

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

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

50 ft

How can a deactivated stick be reactivated:

By momentary action on either stick take over push buttons

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

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

> 67°

The roll normal law provides combined control of the:

Ailerons + spoilers 2 to 5 + rudder

If ELAC 1 and ELAC 2 have failed:

Roll control is provided by spoilers only

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

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

210 kts

What happens when SFCC 1 fails:

Flaps and slats operate at half speed

After FLAP retraction, when is CONF 1+F available again?

At 100 kt or less

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

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

When roll direct law is active, the yaw damping is:

Lost

Sideslip target:

To indicate how much rudder to use to get the best climb performance in case of engine failure

How many hydraulic systems activate the rudder:

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

Alpha/Speed Lock

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

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

SLATS SYS 1 FAULT on the ECAM warning display means:

The slat channel in one SFCC has failed

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

Alternate

In normal law, the stall warning is activated:

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

The pitch normal law provides:

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

When is the THS not available?

After yellow and green hydraulic system failure

Flight control computers are:

2 ELACs - 3 SECs - 2 FACs

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

Yes

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

Direct Law

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

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

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

Automatic Retraction function

Lift augmentation is achieved on each wing by:

2 flap surfaces + 5 slat surfaces

Which flight control computer normally operates the ailerons?

Elevator and aileron computer (ELAC) 1

In normal law, what happens if the pilot holds full lateral side stick deflection?

The bank angle goes to 67° and no further

What is true regarding the flight controls on an A320?

They are all electrically controlled and hydraulically activated

Which spoilers are ground spoilers?

Spoilers 1-5