Flight Controls

Question 1

The stabilizer and rudder can also be

Answer 1

mechanically-controlled

Question 2

regardless of the pilot’s input, the computers will prevent excessive maneuvers and exceedance of the safe envelope in pitch and roll axis. However, as on conventional aircraft, the _______ has no such protection

Answer 2

rudder

Question 3

Stabilizer = Electrical for ________or ______ control ________ for manual trim control

Answer 3

normal / alternate / Mechanical

Question 4

Rudder = _______, however control for yaw damping, turn coordination and trim is _________.

Answer 4

Mechanical / electrical

Question 5

_______flight control computers process pilot and autopilot inputs according to normal, alternate, or direct flight control laws

Answer 5

Seven / 2 ELACs (Elevator Aileron Computer) For : Normal elevator and stabilizer control. Aileron control. 3 SECs (Spoilers Elevator Computer) For : Spoilers control. Standby elevator and stabilizer control. 2 FACs (Flight Augmentation Computer) For : Electrical rudder control.

Question 6

Two elevators and the Trimmable Horizontal Stabilizer (THS) control the aircraft in pitch. The maximum elevator deflection is ____ ° nose up, and _____° nose down. The maximum THS deflection is ____° nose up, and _____° nose down.

Answer 6

30 / 17 / 13.5 / 4

Question 7

One aileron and four spoilers on each wing control the aircraft about the roll axis. The maximum deflection of the ailerons is ___ °. The ailerons extend ____ ° down when the flaps are extended (aileron droop). The maximum deflection of the spoilers is ____°.

Answer 7

25 / 5 / 35

Question 8

Speedbrake extension is inhibited, if:

Answer 8

‐ SEC 1 and SEC 3 both have faults, or ‐ An elevator (L or R) has a fault, or ‐ Angle-of-attack protection is active, or ‐ Flaps are in configuration FULL, Thrust levers above MCT position, or ‐ Alpha Floor activation.

Question 9

The maximum speedbrake deflection in manual flight is:

Answer 9

40 ° for spoilers 3 and 4 20 ° for spoiler 2.

Question 10

The maximum speedbrake deflection with the autopilot engaged is:

Answer 10

25 ° for spoilers 3 and 4 12.5 ° for spoiler 2.

Question 11

ground spoilers retract:

Answer 11

• After landing, • After a rejected takeoff, when the ground spoilers are disarmed. • During a touch and go, when at least one thrust lever is advanced above 20 °

Question 12

SHARP (Short Airfield Package) is a set of aircraft modifications allowing operations on short runway:

Answer 12

• An improved leading edge root fillet • A Vortex Generators on trailing edge panels

Question 13

The normal flight control laws provides:

Answer 13

‐ Aircraft control on the 3 axis ‐ Flight envelope protection ‐ Alleviation of maneuver loads.

Question 14

Protections are intended to:

Answer 14

• Provide maximum authority to the PF to consistently achieve the best possible aircraft performance in extreme conditions • Reduce the risks of overcontrolling, or overstressing the aircraft • Provide PF with an instinctive and immediate procedure to ensure that the PF achieves the best possible result

Question 15

Flight Controls - normal law- pitch- Ground mode is a direct relationship between:

Answer 15

sidestick deflection and elevator deflection, without auto trim.

Question 16

When the aircraft reaches ___ kt during the takeoff roll, the system reduces the maximum up elevator deflection from ___ ° to ____ °

Answer 16

75 / 30 / 20

Question 17

The Rotation Mode depends on:

Answer 17

• The pitch rate • The tail clearance • The sidestick position

Question 18

The objective of the Rotation Mode is

Answer 18

to provide a homogeneous rotation for all possible weight, CG and configurations, while minimizing the risk of a tail strike.

Question 19

The Rotation Mode is active from

Answer 19

70 kt during takeoff roll until 10 s after lift-off

Question 20

Flight control surfaces are all : ‐ Electrically-controlled, and ‐ Hydraulically-actuated. The stabilizer and rudder can also be

Answer 20

mechanically-controlled

Question 21

computers will prevent excessive maneuvers and exceedance of the safe envelope. No protection for

Answer 21

Rudder

Question 22

The maximum elevator deflection is ___ ° nose up, and ____ ° nose down

Answer 22

30 / 17

Question 23

The maximum THS deflection is ____ ° nose up, and ___ ° nose down.

Answer 23

13.5 / 4

Question 24

Two electrically-controlled hydraulic servojacks drive each elevator. Each servojack has three control modes :

Answer 24

Active : The jack position is electrically-controlled. • Damping : The jack follows surface movement. • Centering : The jack is hydraulically retained in the neutral position

Question 25

One aileron and four spoilers on each wing control the aircraft about the roll axis. The maximum deflection of the ailerons is ____°. The ailerons extend ___ ° down when the flaps are extended (aileron droop).

Answer 25

25 / 10

Question 26

A321=The maximum deflection of the spoilers is: ‐ ___ ° for spoilers 2, 4, and 5 ‐ ___º for spoilers 3.

Answer 26

35 / 7

Question 27

Speedbrake extension is inhibited, if one of the following occurs:

Answer 27

‐ SEC1 and SEC3 both are faulty, or ‐ An elevator (L or R) is faulty, or ‐ Angle-of-attack protection is active, or ‐ Flaps are in configuration FULL, or -Thrust levers are above MCT position, or ‐ Alpha Floor is activated.

Question 28

The maximum speedbrake deflection in manual flight is:

Answer 28

• 40 ° for spoilers 3 and 4 • 20 ° for spoiler 2.

Question 29

The maximum speedbrake deflection with the autopilot engaged is:

Answer 29

• 25 ° for spoilers 3 and 4 • 12.5 ° for spoiler 2.

Question 30

The ground spoilers retract:

Answer 30

During a touch and go, when at least one thrust lever is advanced above 20 °

Question 31

The normal flight control laws provides:

Answer 31

‐ Aircraft control on the 3 axis ‐ Flight envelope protection ‐ Alleviation of maneuver loads.

Question 32

Automatic pitch trim freezes in the following situations:

Answer 32

‐ The flight crew enters a manual trim order ‐ The radio height is below 50 ft (100 ft with autopilot engaged) ‐ The load factor goes below 0.5 g ‐ The aircraft is in high-speed or high-Mach protection.

Question 33

The normal law protects the aircraft throughout the flight envelope, as follows :

Answer 33

‐ load factor limitation ‐ pitch attitude protection ‐ high-angle-of-attack (AOA) protection ‐ high-speed protection.

Question 34

The flight director bars disappear from the PFD when the pitch attitude exceeds ___ ° up or ____ ° down. They return to the display when the pitch angle returns to the region between 22 ° up and 10 ° down.

Answer 34

25 / 13

Question 35

When the aircraft is : ‐ In normal cruise range (around M .77), ‐ In straight flight, ‐ With the autopilot engaged, ‐ With symmetrical engine thrust, and ‐ With fuel in the wing tanks distributed symmetrically, the rudder trim should stay between

Answer 35

1 ° right and 2.3 ° left.