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Boeing (AS) > Ch.9 > Flashcards

Ch.9 Flashcards

Flight Controls

1
Q

Which Hydraulic System(s) normally power the primary flight controls?

A

System A and B. Either can operate all of the Primary Flight Controls

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2
Q

The loss of Hydraulic Systems A and B will render which spoiler panels inoperative?

A

All spoiler panels

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3
Q

How do ailerons and elevators operate with the loss of both Hydraulic systems A and B?

A

Manually through manual reversion. Mechanical throughput is provided through the PCU

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4
Q

What happens when the FLT CONTROL A switch is positioned to STBY RUD?

A

This activates the standby hydraulic system and opens the Standby rudder shutoff valve allowing standby hyd pressure to power the standby rudder PCU

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5
Q

What powers the rudder during manual reversion?

A

The standby hydraulic system. No manual reversion is available

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6
Q

Which are the roll control surfaces and how are they powered?

A
  • Ailerons: HYD systems A & B through the Aileron Feel/Centering unit
  • Flight spoilers: Connected by cables between the FO control wheel and spoiler PCU’s through the Spoiler Mixer. HYD Sys A & B are each connected to different spoiler pair to provide isolation
  • Aileron Trim
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7
Q

*What happens when a single aileron trim switch is pushed?

A

Nothing?

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8
Q

Why is aileron trim prohibited with the autopilot engaged?

A

To prevent abrupt movements when the autopilot is disconnected

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9
Q

How many degrees of control wheel displacement initiates spoiler deflection?

A

Approx. 10*

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10
Q

Which flight control Switch (es) are used for maintenance purposes only?

A

Spoiler switches

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11
Q

With a jammed or restricted Spoiler system how is roll controlled?

A

Moving the captains control wheel will activate the Aileron transfer mechanism and roll will be provided by ailerons

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12
Q

With a jammed or restricted aileron system how is roll controlled?

A

Moving the F/O’s control wheel will activate the Aileron transfer mechanism and roll will
be provided by the spoilers

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13
Q

What does an illuminated FEEL DIFF PRESS light (amber) indicate?

A

Excessive differential pressure within the Elevator feel computer

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14
Q

How does actuating the Stabilizer trim switch on the control wheel affect autoflight?

A

Automatically disengages auto pilot

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15
Q

What is the purpose of the stab trim switch on the aft electronic panel?

A

To bypass the stabilizer trim cutout switches and restore power if both trim cutout switches have failed internally

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16
Q

What does the green band of the STAB TRIM indicator on the control stand indicate?

A

The take off trim range

17
Q

What does an illuminated SPEED TRIM FAIL light (amber) during master caution recall
indicate?

A

Failure of a single FCC channel failure

18
Q

Describe the functions of the Stall Management Yaw Damper (SMYD) computers.

A

Determine when stall warning is required based on: AOA sensors, ADIRU outputs, anti- ice controls, configuration, thrust, FMC outputs, and mach compensation. The SMYD computes a stick shaker AOA and compares it with actual AOA. When actual AOA exceeds computed AOA, the stick shaker fires

19
Q

Which light is armed by selecting FLT CONTROL A or B switch to STBY RUD?

A

The standby hydraulic system Low Pressure light

20
Q

When does the main rudder Power Control Unit (PCU) limit full rudder authority?

A

At speeds above approx. 135 KTS, pressures in both A & B are reduced by around 25% to limit full rudder authority in flight after takeoff and before landing

21
Q

What does the rudder trim control switch do?

A

Electrically repositions the Rudder Feel/Centering unit which adjusts the rudder neutral position

22
Q

How do you activate the standby yaw damper?

A

During manual reversion (loss of both HYD SYS A & B), both Flight Control switches are placed in STBY RUD, the yaw damper can then be reset to on and will be powered by the Standby hydraulic system

23
Q

What are the positions of the speed brake lever and what are the limitations?

A

Down, armed, flight detent, up. Do not move the speedbrake past the flight detent in flight (Should be restricted by a lever stop when the flaps are fully retracted)

24
Q

What does the SPEED BRAKE DO NOT ARM light (amber) indicate?

A

Abnormal condition or abnormal test inputs to the Automatic Speed Brake System

25
Q

During landing, when do the ground spoilers deploy?

A

When these conditions occur:

  • Speed brake lever in the ARMED position
  • Speed brake armed light is illuminated
  • RA less than 10’
  • Both thrust levers in IDLE
  • Main landing gear wheels spin up (60+KTS)
  • Landing gear strut compressed
26
Q

What would cause the LE FLAPS TRANSIT light (amber) to illuminate?

A
  • Any LE device transit
  • Any LE device not in programmed position when compared to TE flaps
  • A LE uncommanded motion
  • During alternate flap extension until LE devices are fully extended and TE flaps 15
27
Q

What is the normal position of the LE flaps for each Flap lever position?

A

Stowed for UP, full extended position for positions 1-40

28
Q

When do the LE slats deploy to full extend?

A

When lever is moved beyond the 25 position

29
Q

Which flap settings have load relief?

A

Flaps 10, 15,25 and 40

30
Q

What does an AUTO SLAT FAIL light (amber) illumination during master caution recall indicate?

A

A single SMYD (Stall management Yaw damper) computer failure

31
Q

What does an AUTO SLAT FAIL light (amber) illumination during master caution recall indicate?

A

A single SMYD (Stall management Yaw damper) computer failure

32
Q

Which devices move when the Alternate Flaps switch is placed in the DOWN position? Up Position? Which systems move these devices?

A
  • Down: Fully extends all LE devices using the Standby HYD sys, and a mechanical
    drive motor moves the TE flaps
  • UP: Retracts the flaps. LE device cannot be retracted using the Standby HYD sys

Boeing (AS) (15 decks)

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