Brainscape's Knowledge GenomeTM

Browse over 1 million classes created by top students, professors, publishers, and experts.


See full index

Boeing 787 RR > Flight Controls > Flashcards

Flight Controls Flashcards

1
Q

There are 2 outboard and 2 inboard trailing edge flap position sensors the measure the flap position. Which of these functions make it necessary to have 2 sensors for the trailing edge flap system?

A. To supply position feedback to the flight control electronics (FCE) to find flap skew conditions

B. To monitor the inboard flap position independently of outboard flap position because of the variable camber trim system

C. To supply position feedback to the flight control electronics (FCE) to find uncommanded motion

A

B. To monitor the inboard flap position independently of outboard flap position because of the variable camber trim system

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
2
Q

Which high lift mode has different displays for slats and flaps and no magenta or green commands bars?

A. Primary mode

B. Secondary mode

C. Alternate mode

A

C. Alternate mode

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
3
Q

To operate the high lift system on the ground, with one power cart connected, which of these must you do before you operate the flap lever?

A. Make sure the primary flight control function (PFCF) is in secondary mode

B. Operate each hydraulic system and put the speed brake lever to the full UP position

C. Manually lift the electro-mechanical actuators

A

B. Operate each hydraulic system and put the speed brake lever to the full UP position

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
4
Q

Which flaperon component operates mechanically as an spoiler panel?

A. Flaperon tab

B. Flaperon manifold

C. Fixed hinge panel

A

C. Fixed hinge panel

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
5
Q

Spoiler 4 electrical actuator has a failure, and you must change it. The AMM shows that you must lift the spoiler to the raised position, how do you this?

A. Use the manual release on the actuator

B. Remove the motor cap and use a tool to turn the actuator

C. Apply a load to the rod end

A

B. Remove the motor cap and use a tool to turn the actuator

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
6
Q

Which conditions occur when the primary flight control function (PFCF) operates in the normal mode?

A. Protective functions do not operate

B. All protective functions and the autopilot operate

C. The autopilot cannot operate

A

B. All protective functions and the autopilot operate

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
7
Q

The primary flight controls function (PFCF) changes from the normal mode to the secondary mode for wich condition?

A. PFC system senses a loss of air data

B. Pilot disconnects the autopilot system

C. PFC disconnect switch is in the DISC position

A

A. PFC system senses a loss of air data

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
8
Q

Which is true for the surface lock function?

A. It can be in operation in flight or in ground

B. It operates when the primary flight control function (PFCF) is in direct mode

C. It can not operate if the primary flight control (PFC) disconnect switch is in DISC

A

C. It can not operate if the primary flight control (PFC) disconnect switch is in DISC

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
9
Q

There is a loss of control data from the flight control electronics (FCE). How can the flight crew control movement of the horizontal stabilizer trim actuator (HSTA)?

A. Move the alternate pitch switches (arm and control) in opposite directions

B. Use the alternate pitch trim switches

C. Put the primary flight controls switch in the DISC position

A

B. Use the alternate pitch trim switches

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
10
Q

Wich component gives a signal to the flight control electronics (FCE) unit to measure elevator position and monitor for faults?

A. Column position transducers

B. Power control unit (PCU) rotary variable differential transformer (RVDT)

C. Power control unit (PCU) linear variable differential transformer (LVDT)

A

C. Power control unit (PCU) linear variable differential transformer (LVDT)

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
11
Q

When you try to adjust the captain rudder pedals, they do not move. Which component can cause this?

A. Rudder pedal flexible jackshaft assembly failure

B. Rudder pedal breakout mechanism failure

C. Rudder pedal damper is over serviced

A

A. Rudder pedal flexible jackshaft assembly failure

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
12
Q

Which of these occurs if there is a difference between the spoiler position command transmitted from the external resolvers and the spoiler position command transmitted from the internal actuator linear variable differential transformer (LVDT)

A. The electromechanical actuators (EMA) shut down

B. The flight control electronic (FCE) units remove power to the spoiler

C. A NO AUTOLAND EICAS message shows

A

B. The flight control electronic (FCE) units remove power to the spoiler

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
13
Q

During electronic rig you see FLIGHT CONTROL SYS message. What should you do?

A. Complete the test and then troubleshoot the fault

B. Stop the test and troubleshoot the fault

C. Nothing. This is normal during the rig test

A

B. Stop the test and troubleshoot the fault

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
14
Q

The magenta number above the current stab trim position, on the flight control synoptic page shows which data?

A. The recommended elevator position for landing

B. The pressure output of the nose gear pressure transducer

C. The recommended take off position of the stabilizer

A

C. The recommended take off position of the stabilizer

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
15
Q

You must do a test of rudder movement with the rudder pedals while the airplane is parked. How can prevent nose wheel movement during the test?

A. Push and hold the rudder pedals disconnect switch

B. Lock closed the nose wheel steering isolation valve

C. Disable nose wheel steering through the central maintenance computer

A

A. Push and hold the rudder pedals disconnect switch

How well did you know this?
1
Not at all
2
3
4
5
Perfectly
16
Q

What ground test must you do after installation of any electric flight controls component?

A. Central maintenance computing function (CMCF)- ground test-operational test.

B. Central maintenance computing function (CMCF)-ground test-LRU replacement test

C. Central maintenance computing function (CMCF)-ground test-system test

A

B. Central maintenance computing function (CMCF)-ground test-LRU replacement test

17
Q

Which of these are the control modes for the primary flight control function (PFCF)?

A. On and OFF

B. Normal, secondary and direct

C. Primary, secondary and alternate

A

B. Normal, secondary and direct

18
Q

Which statement is NOT true of the surface lock function?

A. Ground speed less than 40 knots

B. Primary flight computer (PFC) disconnect switch must be in the DISC position

C. Airplane on ground

A

B. Primary flight computer (PFC) disconnect switch must be in the DISC position

19
Q

What energy source moves the flaps and leading adage devices in the high lift primary mode?

A. Electric power

B. Hydraulic power

C. Hydraulic or electric power

A

B. Hydraulic power

20
Q

Which component causes the control wheel to move to the neutral position when a control wheel input is removed?

A. Feel and centering unit

B. Aileron trim mechanism

C. Force limiter-override mechanism (POGO)

A

A. Feel and centering unit

21
Q

During initial power on, you see on the flight control synoptic page that amber X replaces the scale for all flight controls. Which of these is the most probable cause?

A. Failure of 2 flight control modules (FCM)

B. Hydraulic system failure or not in operation

C. Rigging of flight controls is necessary

A

B. Hydraulic system failure or not in operation

22
Q

Which flight controls surfaces operates only at low speeds in flight?

A. Ailerons

B. Flaperon

C. Elevators

A

A. Ailerons

23
Q

Where is the door position indication shown for the empennage door actuation system (EDAS)?

A. Flight controls synoptic page

B. High lift maintenance page

C. Page 4 of the flight controls maintenance

A

C. Page 4 of the flight controls maintenance

24
Q

A logbook report showed that there was a jam of the captain pedals, but with more force the first officer pedals operated. What component will let the first officer move pedals during this condition?

A. Rudder pedals damper

B. Rudder pedal breakout mechanism

C. Rudder feel and centering unit

A

B. Rudder pedal breakout mechanism

25
Q

When the captain control column is released, there is unwanted oscillation. Which of these is the probable cause?

A. Column damper low of fluid or has a failure

B. Elevator feel and centering mechanism has a jam

C. Column breakout mechanism has a failure

A

A. Column damper low of fluid or has a failure

26
Q

When the spoilers are full extended, the flight controls synoptic page shows which indication?

A. A box with black fill

B. A box filled with by a amber X

C. A box with white fill

A

C. A box with white fill

27
Q

Which flight control surface (s) give short-term pitch control?

A. Elevators

B. Ailerons

C. Horizontal stabilizer

A

A. Elevators

Boeing 787 RR (5 decks)

Brainscape helps you reach your goals faster, through stronger study habits.
© 2025 Bold Learning Solutions. Terms and Conditions