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B787 > Fltct > Flashcards

Fltct Flashcards

1
Q

On the ground above 60kts groundspeed, the flight control system attempts to maintain a yaw rate near zeo by appyling rudder input. This function is only available in ____.

A

The NORMAL flight control mode.

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2
Q

With a coplete loss of flight control signaling, the ____ must be used to move the stabilizer.

A

Alternate pitch trim switches

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3
Q

The flaps and slats are driven:

A

Hydraulically in the PRIMARY mode only

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4
Q

With the flaps and slats in the SECONDARY mode, if airspeed exceeds 225 knots with the slats fully extended, they retract to the ____ position.

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.

A

A. True

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6
Q

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

A

Autopilots and envelope protections are not available.

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7
Q

With flight controls operating in the direct mode, which of te following components of the primary flight control system are inoperative?

A

Primary flight computer (PFCs).

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8
Q

Automatic speedbrake extension is provided for a rejected takeoff.

A

A. True

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9
Q

Thw autopilot sends signals:

A

Directly to the PFCs.

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10
Q

The autopilot is available in:

A

NORMAL flight control mode only.

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11
Q

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

A

Cause the flap or slats to transfer to the SECONDARY mode.

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12
Q

When operating with th slats in the SECONDARY mode and positioned to the fully extended position, if the airspeed exceeds 225 knots:

A

B. LOAD RELIEF will be displayed on the EICAS.

C. The slats will retract to the middle position.

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13
Q

The primary f;ight control computers (PFCs) cannot override a pilot command.

A

A. True

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14
Q

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

A

A. True

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15
Q

How can the pilot place the aircraft into the SECONDARY flight control mode?

A

You cannot, 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 _____?

A

60kts groundspeed and aircraft on the ground

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17
Q

Disconnecting the primary flight control computers (PFC’s) places the aircraft _____.

A

In the DIRECT mode.

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18
Q

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

A

A. Secondary

C. Direct

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19
Q

The three modes of the Primary Flight Control System are:

A

NORMAL, SECONDARY, DIRECT

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20
Q

With a total hydraulic failure, Pitch and Roll control is still available:

A

electrically using the control wheel and either primary or alternate pitch trim.

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21
Q

After landing, tje flight control system automatically self test:

A

with flaps and speedbrakes retracted and groundspeed less than 30kts

22
Q

Why is the B787 provided with an elctrical flight control backup system?

A

B. In case of a complete hydraulic loss.

23
Q

During takeoff, the rudder becomes aerodynatically effective at:

A

approximately 60 knots.

24
Q

When autopilot is not engaged, when is manual trimming necessary?

A

B. For airspeed changes.

25
Q

In the NORMAL mode, pitch trim operates the in same manner on the ground as it does in flight.

A

B. False

26
Q

The alternate pitch trim switches may be used with the autopilot engaged to correct for minor airspeed changes.

A

B. False

27
Q

The stabilizer green band is calculated by:

A

B. FMC inputs of CG, and gross weight.

28
Q

The EICAS message STAB GREENBAND is displayed when:

A

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

29
Q

If BOTH the L2 and R2 stabilizer control switches are placed to CUTOUT while in the NORMAL flight control mode:

A

Pitch trim is still available through the trim switches.

30
Q

The autothrottles must be ____ to support stall protection.

A

Armed

31
Q

When the pitch mode is FLCH or TOGA the autothrottles will not automatically engage to support stall protection.

A

A. True

32
Q

The ailerons are:

A

Locked out during high speed flight.

33
Q

Each spoiler pair is dedicated to the same hydraulic system, therefore, symmetric operation is maintained in the event of hydraulic system failure.

A

A. True

34
Q

Some of the benefits of the fly-by-wire design are:

A

A. Increased fuel economy.
B. Enhanced handling quantities.
C. Reduced pilot workload.

35
Q

When is the slat auto gap function available?

A

B. Only in the primary mode and at flaps 1, 5, 15, and 20..

36
Q

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

A

D. Do not use the speed brakes inflight below 1000 feet.

37
Q

The B787 has a single rudder with the lower portion having a hinged section that deflects twice as far to provide additional yaw authority.

A

B. False

38
Q

The Wheel to Rudder Cross-Tie system operates in conjunction with TAP and is effective both on the ground and in the air

A

B. False

39
Q

If the flap placard speed is exceeded with flaps in the ____ position, LOAD RELIEF is displayed and the flaps automatically retract to a position appropriate for the airspeed.

A

B. 15 through 30

40
Q

Which flight control surfaces are locked out during high- speed flight?

A

Ailerons

41
Q

The yaw control function for thrust asymmetry :

A

Is only available in the Normal flight control mode.

42
Q

Which of the following functions are available in the Secondary Mode?

A

A. Wheel to rudder cross-tie

43
Q

What happens when a a roll control wheel input causes the bank angle to exceed 35 degrees?

A

B. The PFD bank indicator turns amber.

44
Q

Automated yaw and roll control for engine failure, crosswind, or turbulance is an integral part of the flight control system.

A

A. True

45
Q

Tailstrike protection can be overriden by pilot input.

A

A. True

46
Q

Auto drag operates only on an electric or FMC generated glidepath.

A

B. False

47
Q

Wheel to rudder cross tie is not provided in hte Normal flight control ode because the flight control system automatically controls sideslip and fin loads.

A

A. True

48
Q

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

A

A. True

49
Q

After landing during a single engine approach, an applied automatic or manual trim inputs are zeroed after landing.

A

A. True

50
Q

The speedbrakes automatically retract in the air when either throttle is advanced 90% full travel.

A

A. True

B787 (21 decks)

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