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:

A. The NORMAL flight control mode.
B. The SECONDARY flight control mode.
C. The DIRECT flight control mode.
D. All modes.

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.

A. True.
B. False.

Answer 2

A. True.

Question 3

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

A. ALTERNATE mode only.
B. SECONDARY MODE only.
C. PRIMARY mode only.
D. In all modes.

Answer 3

C. 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.

A. Retracted
B. 5 degree
C. Middle
D. Slat load relief not available in secondary mode

Answer 4

C. Middle

Question 5

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

A. True.
B. False.

Answer 5

A. True.

Question 6

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

A. Autopilot is available.
B. Envelope protection is available.
C. The PFCs are not available.
D. Autopilots and envelope protections are not available.

Answer 6

D. Autopilots and envelope protections are not available.

Question 7

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

A. True.
B. False.

Answer 7

B. False.

Question 8

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

A. True.
B. False.

Answer 8

A. True.

Question 9

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

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

Answer 9

D. Both B and C.

Question 10

The autopilot is only available in the:

A. NORMAL and SECONDARY flight control modes.
B. ALTERNATE flight control mode.
C. Only if normal stab trim is available.
D. NORMAL flight control mode only.

Answer 10

D. NORMAL flight control mode only.

Question 11

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

A. Cause the flaps or slats to transfer to the SECONDARY mode.
B. Cause the flap or slat system to transfer to the ALTERNATE mode.
C. Drive the slats to the mid sealed position.
D. Lock out the outboard flaps.

Answer 11

A. 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:

A. The slats will transfer to the ALTERNATE mode.
B. LOAD RELIEF will be displayed on the EICAS.
C. The slats will retract to the middle position.
D. Both B and C.

Answer 12

D. Both B and C.

Question 13

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

A. True.
B. False.

Answer 13

B. False.

Question 14

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

A. True.
B. False.

Answer 14

A. True.

Question 15

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

A. Yes, by disconnecting the PFCs.
B. Yes, by disconnecting the autopilot.
C. No, SECONDARY selection occurs automatically.
D. Yes, by disconnecting the Stabilizer Trim.

Answer 15

C. 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:

A. V1.
B. 60 knots groundspeed and airplane on the ground.
C. 150 knots IAS, with a thrust differential greater than 10%.
D. E/O acceleration height.

Answer 16

B. 60 knots groundspeed and airplane on the ground.

Question 17

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

A. In the SECONDARY and DIRECT modes.
B. In the ALTERNATE mode.
C. In the DIRECT mode.
D. Out of control.

Answer 17

C. In the DIRECT mode.

Question 18

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

A. Secondary and Direct Modes.
B. All modes.
C. Direct mode.
D. Normal mode

Answer 18

A. Secondary and Direct Modes.

Question 19

The three flight control modes are:

A. NORMAL, SECONDARY, DIRECT.
B. PRIMARY, SECONDARY, ALTERNATE.
C. NORMAL, SECONDARY, STANDBY.
D. There are only two modes of operation for the Primary Flight Control System.

Answer 19

A. NORMAL, SECONDARY, DIRECT.

Question 20

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

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

Answer 20

D. All of the above.

Question 21

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

A. When the left and right hydraulic systems are depressurized.
B. During engine shutdown, before external power can be connected.
C. When the flaps and speed brakes are retracted and groundspeed less than 30 knots.
D. When the PFCs are disconnected.

Answer 21

C. 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?

A. In case of a dual AC bus failure.
B. In case of a complete hydraulic loss.
C. In case both FMCs are lost.
D. A and C.

Answer 22

B. In case of a complete hydraulic loss.

Question 23

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

A. True.
B. False.

Answer 23

B. False.

Question 24

With the autopilot disengaged, when is manual trimming necessary?

A. For configuration changes.
B. For airspeed changes.
C. Never, the autopilot trims the airplane.
D. A and B are correct.

Answer 24

B. For airspeed changes.

Question 25

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

A. True.
B. False.

Answer 25

A. True.

Question 26

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

A. True.
B. False.

Answer 26

B. False.

Question 27

The stabilizer green band is calculated by:

A. The nose gear pressure switch.
B. FMC inputs of CG.
C. FMC Gross weight
D. Both B and C

Answer 27

D. Both B and C

Question 28

The EICAS advisory message STAB GREENBAND is displayed when:

A. The nose gear pressure transducer and greenband data disagree.
B. The FMC determines the stabilizer is in takeoff low mode.
C. Either nose gear transducer fails.
D. A and C are correct.

Answer 28

D. A and C are correct.

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.

A. True.
B. False.

Answer 29

B. False.

Question 30

Stall protection limits the speed to which the airplane can be trimmed.

A. True.
B. False.

Answer 30

A. True.

Question 31

The ailerons are during high-speed flight.

A. Locked out
B. Fully deflected position
C. Locked out in low-speed flight
D. Are never locked out

Answer 31

A. 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.

A. True.
B. False.

Answer 32

A. True.

Question 33

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

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

Answer 33

D. All of the above.

Question 34

When is the slat auto gap function available?

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 34

D. All of the above.

Question 35

Which of the following are limitations on the use of speed brakes?

A. Do not use the speed brakes with flaps 25 or 30.
B. Do not use speed brakes with the gear down.
C. Speed brakes can be used at any altitude.
D. Do not use the speed brakes inflight below 1000 feet.

Answer 35

D. 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.

A. True.
B. False.

Answer 36

B. 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.

A. True.
B. False.

Answer 37

B. 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.

A. 15 through 30
B. 1 through 30
C. 5 through 30
D. A and B are correct.

Answer 38

A. 15 through 30

Question 39

The _______ are locked out during high-speed flight.

A. Ailerons
B. Ailerons and spoilers 5 and 10
C. Ailerons and spoilers 4, 5, 10, and 11
D. Spoilers 5 and 10

Answer 39

A. Ailerons

Question 40

The yaw control function for asymmetry compensation is inoperative in the Secondary and Direct flight control modes.

A. True.
B. False.

Answer 40

A. True.

Question 41

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

A. Wheel to rudder cross-tie.
B. Envelope protection.
C. Auto speed brakes.
D. B and C.

Answer 41

D. B and C.

Question 42

Roll control wheel input beyond 35 degrees of bank causes:

A. The control wheel force rolls the airplane back to level flight.
B. The PFD bank indicator turns amber.
C. The control wheel force will not allow the pilot to override its inputs.
D. Both A and B are correct.

Answer 42

B. 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.

A. True.
B. False.

Answer 43

A. True.

Question 44

Tail strike protection cannot be overridden by pilot input.

A. True.
B. False.

Answer 44

B. False.

Question 45

Auto drag operates only when on an electronic glideslope or FMC generated glidepath is captured.

A. True
B. False

Answer 45

B. 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.

A. Secondary
B. Direct
C. Normal
D. Alternate

Answer 46

C. Normal

Question 47

Rudder trim is automatic in all flight phases in the _______ flight control mode, including during engine failure.

A. Secondary and Direct
B. Secondary
C. Direct
D. Normal

Answer 47

D. Normal

Question 48

On landing automatic or manual trim inputs are zeroed after landing.

A. True.
B. False.

Answer 48

A. 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.

A. True.
B. False.

Answer 49

A. True.

Question 50

Pre-Gap functions when:

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 50

D. All of the above conditions exist

Question 51

FLAP LOAD RELIEF protects flaps from excessive airload by:

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
C. Only when operating in the Secondary and Direct flight control modes
D. Both A and B

Answer 51

D. Both A and B

Question 52

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

A. Pitch attitude.
B. Air speed.
C. Nose gear height.
D. both A and C.

Answer 52

D. both A and C.

Question 53

With Autopilot engaged, moving any pitch trim switches will disengage the autopilot.

A. True
B. False

Answer 53

B. False

Question 54

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

A. Providing enhanced pilot awareness of the approach to a stall.
B. Limited the speed to which the airplane can be trimmed.
C. Allowing the airplane to be trimmed in a nose up attitude.
D. Both A and B.

Answer 54

D. Both A and B.

Question 55

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

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 55

D. Any of the above.

Question 56

Autodrag function operates by deflecting the ailerons downward in conjunction while stowing the outboard spoilers.

A. True
B. false

Answer 56

B. False