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]

A. The NORMAL flight control mode.

Answer 1

A. 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]

A. True.

Answer 2

A. True.

Question 3

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]

C. Middle

Answer 3

C. Middle

Question 4

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

A. True.

Answer 4

A. True.

Question 5

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

B. False.

Answer 5

B. False.

Question 6

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

A. True.

Answer 6

A. True.

Question 7

The autopilot is only available in the: [8.90.10]

D. NORMAL flight control mode only.

Answer 7

D. NORMAL flight control mode only.

Question 8

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

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

Answer 8

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

Question 9

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]

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

D. Both B and C.

Answer 9

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

D. Both B and C.

Question 10

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

B. False.

Answer 10

B. False.

Question 11

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

A. True.

Answer 11

A. True.

Question 12

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

B. 60 knots groundspeed and airplane on the ground.

Answer 12

B. 60 knots groundspeed and airplane on the ground.

Question 13

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

C. In the DIRECT mode.

Answer 13

C. In the DIRECT mode.

Question 14

The three flight control modes are: [8.90.10]

A. NORMAL, SECONDARY, DIRECT.

Answer 14

A. NORMAL, SECONDARY, DIRECT.

Question 15

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

A. Electrically using the control wheel.
B. Primary pitch trim switches.
C. Alternate pitch trim switches.

D. All of the above.

Answer 15

A. Electrically using the control wheel.
B. Primary pitch trim switches.
C. Alternate pitch trim switches.

D. All of the above.

Question 16

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

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

Answer 16

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

Question 17

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

B. In case of a complete hydraulic loss.

Answer 17

B. In case of a complete hydraulic loss.

Question 18

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

B. False.

Answer 18

B. False

Question 19

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

B. For airspeed changes.

Answer 19

B. For airspeed changes.

Question 20

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

A. True.

Answer 20

A. True

Question 21

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

B. False.

Answer 21

B. False.

Question 22

The stabilizer green band is calculated by: [8.90.10]

B. FMC inputs of CG.
C. FMC Gross weight

D. Both B and C

Answer 22

B. FMC inputs of CG.
C. FMC Gross weight

D. Both B and C

Question 23

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

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

D. A and C are correct.

Answer 23

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

D. A and C are correct.

Question 24

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]

B. False

Answer 24

B. False.

Question 25

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

Answer 25

A. True.

Question 26

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] A. True.

Answer 26

A. True.

Question 27

Some of the benefits of an electronically controlled flight control system (fly-by-wire) are: [8.90.10] A. Increased fuel economy. B. Enhanced handling qualities. C. Reduced pilot workload. D. All of the above.

Answer 27

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

Question 28

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

Answer 28

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 29

Which of the following are limitations on the use of speed brakes? [1.30] D. Do not use the speed brakes inflight below 1000 feet.

Answer 29

Do not use the speed brakes inflight below 1000 feet.

Question 30

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

Answer 30

B. False.

Question 31

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] B. False.

Answer 31

B. False

Question 32

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] A. 15 through 30

Answer 32

A. 15 through 30

Question 33

The ______are locked out during high-speed flight. [8.90.10] A. Ailerons

Answer 33

A. Ailerons

Question 34

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

Answer 34

A. True.

Question 35

Which of the following functions are not available in the Secondary Mode? [8.90.10] B. Envelope protection. C. Auto speed brakes. D. B and C.

Answer 35

B. Envelope protection. C. Auto speed brakes. D. B and C.

Question 36

Roll control wheel input beyond 35 degrees of bank causes: [8.90.10] B. The PFD bank indicator turns amber.

Answer 36

B. The PFD bank indicator turns amber.

Question 37

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

Answer 37

A. True.

Question 38

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

Answer 38

B. False.

Question 39

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

Answer 39

B. False

Question 40

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] C. Normal

Answer 40

C. Normal

Question 41

Rudder trim is automatic in all_______ flight phases in the flight control mode, including during engine failure. [8.90.10] D. Normal

Answer 41

D. Normal

Question 42

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

Answer 42

A. True.

Question 43

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] A. True.

Answer 43

A. True

Question 44

Pre-Gap functions when: [8.90.10] 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

Answer 44

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 45

FLAP LOAD RELIEF protects flaps from excessive airload by: [8.90.10] A. Retracting flaps back to a setting based on current speed, not to exceed flaps 5 B. When speed is reduced, the flaps will return to the flap handle setting D. Both A and B

Answer 45

A. Retracting flaps back to a setting based on current speed, not to exceed flaps 5 B. When speed is reduced, the flaps will return to the flap handle setting D. Both A and B

Question 46

Land Attitude Modifier (LAM) is an automatic function used to increase: [8.90.10] A. Pitch attitude. C. Nose gear height. D. both A and C.

Answer 46

A. Pitch attitude. C. Nose gear height. D. both A and C.

Question 47

With Autopilot engaged, moving any pitch trim switches will disengage the autopilot [8.90.10] B. False

Answer 47

B. False

Question 48

Stall Protection reduces the likelihood of inadvertently exceeding the stall angle of attack by: [8.90.10] A. Providing enhanced pilot awareness of the approach to a stall. B. Limited the speed to which the airplane can be trimmed. D. Both A and B.

Answer 48

A. Providing enhanced pilot awareness of the approach to a stall. B. Limited the speed to which the airplane can be trimmed. D. Both A and B.

Question 49

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

Answer 49

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 50

Autodrag function operates by deflecting the ailerons downward in conjunction while stowing the outboard spoilers. [8.90.10] B. false

Answer 50

B. False

Question 51

The ailerons are ______during high-speed flight. [8.90.10] A. Locked out

Answer 51

A. Locked out

Question 52

Wheel to rudder cross-tie is available in which mode(s)? [8.90.10] A. Secondary and Direct Modes.

Answer 52

A. Secondary and Direct Modes.

Question 53

Can the Primary Flight Computers be selected to the SECONDARY flight control mode? [8.90.10] C. No, SECONDARY selection occurs automatically.

Answer 53

C. No, SECONDARY selection occurs automatically.

Question 54

In the NORMAL flight control mode, the autopilot system sends control surface commands: [8.90.10] B. Directly to the PFCs. C. To the backdrive actuators. D. Both B and C.

Answer 54

B. Directly to the PFCs. C. To the backdrive actuators. D. Both B and C.

Question 55

Which of the following is true when the flight control system is operating in secondary mode? [8.90.10] D. Autopilots and envelope protections are not available.

Answer 55

D. Autopilots and envelope protections are not available.

Question 56

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

Answer 56

C. PRIMARY mode only.

Question 57

The autopilot is only available in the: [8.90.10] D. NORMAL flight control mode only

Answer 57

D. NORMAL flight control mode only

Question 58

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] A. True

Answer 58

A. True