Flight Controls

Question 1

Power Control Units (PCUs) are

Answer 1

Hydraulic actuators that control the respective flight control surface

Question 2

The primary flight control electronics include two complementary parts:

Answer 2

– The Primary Actuator Control Electronics (P-ACE).

– The Flight Control Module (FCM

Question 3

PITCH TRIM SWITCH: actuation of only half of the switch does not command the horizontal stabilizer. When this half actuation persists for more than

Answer 3

7 s, the switch is automatically deactivated

Question 4

Manual PITCH TRIM Switch commands are limited to

Answer 4

3 s

Question 5

AP/TRIM DISC BUTTOM: The PITCH TRIM FAIL Caution EICAS message is displayed when the AP/TRIM DISC Button is pressed for more than

Answer 5

11 s

Question 6

When any of the Pitch Trim SYS CUTOUT Button is pushed in, the respective

Answer 6

AP/TRIM DISC Button PITCH TRIM DISC function is unavailable

Question 7

Flaps: Position 4 is gated for normal

Answer 7

Go Around and Takeoff. Position 5 is used for landing

Question 8

If the value of the PBIT remaining time readout is higher or equal to

Answer 8

5, the numbers will be displayed in green, otherwise will be cyan. Invalid data will be represented by 2 dashes (“- -“) in amber

Question 9

If SLAT/FLAP surface stops in an intermediate position, the SLAT/FLAP READOUT will display the more retracted surface position. As an example, if flap fails between positions 2 and 3, the EICAS will indicate position

Answer 9

2

Question 10

ROLL/PITCH/YAW TRIM SCALE: There is a green takeoff band on the scale extending from 2°

Answer 10

DOWN to 4° UP, corresponding to the allowable pitch trim position for takeoff.

Question 11

The Power Up Built in Test (PBIT) reduces the flight control system exposition to

Answer 11

latent faults, ensuring that the system components remain capable of executing their functions

Question 12

if the PBIT expires in-flight,

Answer 12

No action is required, as the EICAS CAUTION message will only be displayed after landing

Question 13

The Electrical PBIT is automatically performed during power up after the airplane is powered by any AC source and takes approximately

Answer 13

3 min to complete

Question 14

The Hydraulic PBIT is performed automatically, only on the ground when all three hydraulic systems are pressurized. The test takes

Answer 14

1 minute to complete and will be interrupted if any flight control surface is moved while the test is in progress.

Question 15

TAIL STRIKE AVOIDANCE (TSA): The TSA function will be ENABLED for takeoff at estimated altitudes less than

Answer 15

20 ft

Question 16

TSA: The function maximum pitch down elevator deflection in order to correct airplane attitude by reducing its pitch rate is limited to

Answer 16

8°. In case of a negative pitch rate, the maximum pitch up elevator deflection is limited to 0°.

Question 17

The TSA function will be ENABLED for landing at estimated altitudes less than

Answer 17

70 ft.

Question 18

For landings and GO AROUND with flap 5, it is not possible to engage TSA function before

Answer 18

5 min have elapsed from takeoff

Question 19

Stabilizer Trim priority Logic:

Answer 19

1. Backup switches.
2. LH PITCH TRIM Switch (Captain).
3. RH PITCH TRIM Switch (First Officer).
4. FCM (auto-trim) commands

Question 20

Automatic Mach Trim compensates pitch down tendency caused by

Answer 20

changes on the aerodynamic center position, which moves backwards as Mach number increase

Question 21

There are seven slat/flap control lever positions. Slat and flap motion is sequenced such that slats extend

Answer 21

first and flaps retract first when the motion command requires both surfaces to move. The system uses electrical power to move the surfaces

Question 22

After touchdown the FCM will command all multifunction spoiler surfaces to the 40° extended position and the ground spoiler surfaces to 60° when the following conditions are simultaneously met:

Answer 22

– Weight on wheels on ground.

– Wheel speed is above 45 kt or airspeed is above 60 KIAS.

– Thrust Lever Angle (TLA) below 26°.

Question 23

If extended during approach, the speed brakes will automatically retract upon selection of slat/flap

Answer 23

2 or above. Speed brakes will not be deployed if airspeed is below 180 KIAS, and will also automatically retract if airspeed decreases below this threshold