Flight Controls

Question 1

On the ground, above 60 knots groundspeed, the flight control system attempts to maintain a yaw rate near zero by applying rudder input. This function is only available in: [8.90.10]

Answer 1

The NORMAL flight control mode.

Question 2

With a complete loss of flight control signaling, the alternate pitch trim switches must be used to move the stabilizer. [8.90.10]

True or False?

Answer 2

True.

Question 3

Both the flaps and slats are driven hydraulically in which mode(s): [8.90.10]

Answer 3

PRIMARY mode only.

Question 4

With the flaps and slats in the SECONDARY mode, if airspeed exceeds 225 knots for the 787-8 or 240 knots for the 787-9 with slats fully extended, they retract to the — position. [8.90.10]

Answer 4

Middle

Question 5

On the ground, all spoiler panels extend if both reverse thrust levers are raised to the reverse idle detent. [8.90.10]

True or False?

Answer 5

True.

Question 6

Which of the following is true when the flight control system is operating in secondary mode? [8.90.10]

Answer 6

Autopilots and envelope protections are not available.

Question 7

With flight control system operating in the direct mode, the primary flight computers are operative. [8.90.10]

True or False?

Answer 7

False.

Question 8

The spoilers will automatically extend and the speed brake lever is driven to UP for a rejected takeoff. [8.90.10]
True or False?

Answer 8

True.

Question 9

In the NORMAL flight control mode, the autopilot system sends control surface commands: [8.90.10]

Answer 9

• Directly to the PFCs.
• To the backdrive actuators.

Question 10

The autopilot is only available in the: [8.90.10]

Answer 10

NORMAL flight control mode only.

Question 11

With the flaps and slats in the PRIMARY mode, uncommanded motion will: [8.90.10]

Answer 11

Cause the flaps or slats to transfer to the SECONDARY mode.

Question 12

When operating with the slats in the SECONDARY mode and positioned to the full extended position, if the airspeed exceeds 225 knots for the 787-8, or 240 knots for the 787-9: [8.90.10]

Answer 12

• LOAD RELIEF will be displayed on the EICAS.
• The slats will retract to the middle position.

Question 13

The primary flight control computers (PFCs) will override a pilot command. [8.90.10]

True or False?

Answer 13

False.

Question 14

The flaps and slats in the SECONDARY mode are controlled separately and can be positioned by hydraulic pumps or electric motors. [8.90.10]

True or false?

Answer 14

True.

Question 15

Can the Primary Flight Computers be selected to the SECONDARY flight control mode? [8.90.10]

Answer 15

No, SECONDARY selection occurs automatically.

Question 16

In the NORMAL flight control mode, yaw control attempts to maintain zero yaw rate due to engine failure when above: [8.90.10]

Answer 16

60 knots groundspeed and airplane on the ground.

Question 17

Disconnecting the primary flight control computers (PFCs) places the airplane: [8.90.10]

Answer 17

In the DIRECT mode.

Question 18

Wheel to rudder cross-tie is available in which mode(s)? [8.90.10]

Answer 18

Secondary and Direct Modes.

Question 19

The three flight control modes are: [8.90.10]

Answer 19

NORMAL, SECONDARY, DIRECT.

Question 20

With a total hydraulic failure, how are the Pitch and Roll modes controlled? [8.90.10]

Answer 20

A. Electrically using the control wheel.
B. Primary pitch trim switches.
C. Alternate pitch trim switches.
D. All of the above.

Question 21

After landing, the flight control system automatically self-tests: [8.90.10]

Answer 21

When the flaps and speed brakes are retracted and groundspeed less than 30 knots.

Question 22

Why is the 787 provided with an electrical flight control backup system? [8.90.10]

Answer 22

• In case of a dual AC bus failure.
• In case both FMCs are lost.

Question 23

During takeoff, the rudder becomes aerodynamically effective at approximately 40 knots. [8.90.10]

True or False?

Answer 23

False.

Question 24

With the autopilot disengaged, when is manual trimming necessary? [8.90.10]

Answer 24

For airspeed changes.

Question 25

In the NORMAL mode, pitch trim operates differently on the ground than it does in flight. [8.90.10] True or False?

Answer 25

True.

Question 26

Both primary and alternate pitch trim switches may be used with the autopilot engaged. [8.90.10] True or False?

Answer 26

False.

Question 27

The stabilizer green band is calculated by: [8.90.10]

Answer 27

- FMC inputs of CG. - FMC Gross weight

Question 28

The EICAS advisory message STAB GREENBAND is displayed when: [8.90.10]

Answer 28

- The nose gear pressure transducer and greenband data disagree. - Either nose gear transducer fails.

Question 29

Pitch trim is not available if BOTH the L2 and R2 stabilizer control switches are placed to CUTOUT while in the NORMAL flight control mode. [8.90.10] True or False?

Answer 29

False.

Question 30

Stall protection limits the speed to which the airplane can be trimmed. [8.90.10] True or False?

Answer 30

True.

Question 31

The ailerons are during high-speed flight. [8.90.10]

Answer 31

Locked out

Question 32

Each hydraulic system is dedicated to a different set of spoiler pairs; therefore, symmetric operation is maintained in the event of hydraulic system failure. [8.90.10] True or False?

Answer 32

True.

Question 33

Some of the benefits of an electronically controlled flight control system (fly-by-wire) are: [8.90.10]

Answer 33

A. Increased fuel economy. B. Enhanced handling qualities. C. Reduced pilot workload. **D. All of the above.**

Question 34

When is the slat auto gap function available? [8.90.10]

Answer 34

A. Flaps are in the primary mode with the slats in the middle position. B. Airspeed below 225 KIAS for the 787-8. C. Airspeed below 240 KIAS for the 787-9. **D. All of the above.**

Question 35

Which of the following are limitations on the use of speed brakes? [1.30]

Answer 35

Do not use the speed brakes inflight below 1000 feet.

Question 36

The 787 has a single rudder having a hinged section that deflects twice as far to provide additional yaw authority. [8.90.10] True or False?

Answer 36

False.

Question 37

The Wheel to Rudder Cross-Tie system operates in conjunction with the Thrust Asymmetry Protection function and is effective both on the ground and in the air. [8.90.10] True or False?

Answer 37

False.

Question 38

If the flap placard speed is exceeded with flaps in the position ---- for the 787-8/-9/-10, LOAD RELIEF is displayed and the flaps automatically retract to a position appropriate for the airspeed. [8.90.10]

Answer 38

15 through 30

Question 39

The --- are locked out during high-speed flight. [8.90.10]

Answer 39

Ailerons

Question 40

The yaw control function for asymmetry compensation is inoperative in the Secondary and Direct flight control modes. [8.90.10] True or False?

Answer 40

True.

Question 41

Which of the following functions are not available in the Secondary Mode? [8.90.10]

Answer 41

- Envelope protection. - Auto speed brakes.

Question 42

Roll control wheel input beyond 35 degrees of bank causes: [8.90.10]

Answer 42

The PFD bank indicator turns amber.

Question 43

Automated yaw and roll control for engine failure, crosswind, or turbulence is an integral part of the flight control system. [8.90.10] True or False?

Answer 43

True.

Question 44

Tail strike protection cannot be overridden by pilot input. [8.90.10]

Answer 44

False.

Question 45

Auto drag operates only when on an electronic glideslope or FMC generated glidepath is captured. [8.90.10] True or False?

Answer 45

False

Question 46

Wheel to rudder cross tie is not provided in the ----flight control mode because the flight control system automatically controls sideslip and fin loads. [8.90.10]

Answer 46

Normal

Question 47

Rudder trim is automatic in all flight phases in the ----flight control mode, including during engine failure. [8.90.10]

Answer 47

Normal

Question 48

On landing automatic or manual trim inputs are zeroed after landing. [8.90.10] True or False?

Answer 48

True.

Question 49

In the air, the spoilers automatically retract and the speed brake lever is driven forward to the DOWN position when either thrust lever is approximately 70% of full travel. [8.90.10] True or False?

Answer 49

True.

Question 50

Pre-Gap functions when: [8.90.10]

Answer 50

A. The flaps are operating in secondary mode B. Airspeed is below 225 on the -8 and below 240 on the -9/-10 C. The flap lever is out of up **D. All of the above conditions exist**

Question 51

FLAP LOAD RELIEF protects flaps from excessive airload by: [8.90.10]

Answer 51

- Retracting flaps back to a setting based on current speed, not to exceed flaps 5 - When speed is reduced, the flaps will return to the flap handle setting

Question 52

Land Attitude Modifier (LAM) is an automatic function used to increase: [8.90.10]

Answer 52

- Pitch attitude. - Nose gear height.

Question 53

With Autopilot engaged, moving any pitch trim switches will disengage the autopilot [8.90.10] True or False?

Answer 53

False

Question 54

Stall Protection reduces the likelihood of inadvertently exceeding the stall angle of attack by: [8.90.10]

Answer 54

- Providing enhanced pilot awareness of the approach to a stall. - Limited the speed to which the airplane can be trimmed.

Question 55

The EICAS advisory message STAB GREENBAND is displayed if the following occurs: [8.90.10]

Answer 55

A. Computed green band disagrees with pressure transducer data. B. The 2 transducer values are not within the set tolerance. C. Either transducer has failed. **D. Any of the above.**

Question 56

Autodrag function operates by deflecting the ailerons downward in conjunction while stowing the outboard spoilers. [8.90.10] True or False?

Answer 56

False