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UAL 787 SKV > Flight Controls > Flashcards

Flight Controls Flashcards

1
Q

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.

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2
Q

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?

A

True.

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3
Q

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

A

PRIMARY mode only.

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4
Q

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]

A

Middle

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5
Q

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?

A

True.

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6
Q

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

A

Autopilots and envelope protections are not available.

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7
Q

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

True or False?

A

False.

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8
Q

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

A

True.

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9
Q

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

A
  • Directly to the PFCs.
  • To the backdrive actuators.
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10
Q

The autopilot is only available in the: [8.90.10]

A

NORMAL flight control mode only.

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11
Q

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.

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12
Q

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]

A
  • LOAD RELIEF will be displayed on the EICAS.
  • The slats will retract to the middle position.
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13
Q

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

True or False?

A

False.

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14
Q

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?

A

True.

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15
Q

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

A

No, SECONDARY selection occurs automatically.

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16
Q

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

A

60 knots groundspeed and airplane on the ground.

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17
Q

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

A

In the DIRECT mode.

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18
Q

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

A

Secondary and Direct Modes.

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19
Q

The three flight control modes are: [8.90.10]

A

NORMAL, SECONDARY, DIRECT.

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20
Q

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

A

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

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21
Q

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

A

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

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22
Q

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

A
  • In case of a dual AC bus failure.
  • In case both FMCs are lost.
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23
Q

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

True or False?

A

False.

24
Q

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

A

For airspeed changes.

25
Q

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

True or False?

A

True.

26
Q

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

True or False?

A

False.

27
Q

The stabilizer green band is calculated by: [8.90.10]

A
  • FMC inputs of CG.
  • FMC Gross weight
28
Q

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

A
  • The nose gear pressure transducer and greenband data disagree.
  • Either nose gear transducer fails.
29
Q

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?

A

False.

30
Q

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

True or False?

A

True.

31
Q

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

A

Locked out

32
Q

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?

A

True.

33
Q

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

A

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

34
Q

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

A

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.

35
Q

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

A

Do not use the speed brakes inflight below 1000 feet.

36
Q

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?

A

False.

37
Q

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?

A

False.

38
Q

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

39
Q

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

A

Ailerons

40
Q

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

True or False?

A

True.

41
Q

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

A
  • Envelope protection.
  • Auto speed brakes.
42
Q

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

A

The PFD bank indicator turns amber.

43
Q

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?

A

True.

44
Q

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

A

False.

45
Q

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

True or False?

A

False

46
Q

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]

A

Normal

47
Q

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

A

Normal

48
Q

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

True or False?

A

True.

49
Q

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?

A

True.

50
Q

Pre-Gap functions when: [8.90.10]

A

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

51
Q

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
  • When speed is reduced, the flaps will return to the flap handle setting
52
Q

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

A
  • Pitch attitude.
  • Nose gear height.
53
Q

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

True or False?

A

False

54
Q

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.
  • Limited the speed to which the airplane can be trimmed.
55
Q

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

A

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.

56
Q

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

True or False?

A

False

UAL 787 SKV (15 decks)

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