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B787 > Flight Controls > Flashcards

Flight Controls Flashcards

1
Q

ACEs?

A

Actuator Control Electronics (4)

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2
Q

PFCs?

A

Primary Flight Computers (3)

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3
Q

Roll control is provided by what surfaces?

A

Ailerons, flaperons and assymetric spoilers

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4
Q

Ailerons?

A

Outboard of the flaps

Assist with roll control only in low speed flight

Locked out during high speed flight

Droop with flaps

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5
Q

How many PCUs on the rudder?

A

3

Each is powered by a different hydraulic system

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6
Q

How many slats are there?

A

12

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7
Q

Control Input path for manual flight?

A

Pilot inputs to ACEs

ACEs sends electronic signals to PFCs

PFCs calculate inputs and send them back to ACEs

ACEs then convert back to analog and send signals to PCUs

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8
Q

What are the inputs to the PFCs?

A

Air data

Inertial data

Flap and slat position

Engine thrust

Radio altitude

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9
Q

Control path for auto flight?

A

Pilot inputs to MCP

MCP signals to PFCs

PFC signals to ACEs

ACEs mechanical signals to PCUs

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10
Q

Why should the flight controls not be moved after landing?

A

After landing with the flaps retracted and speed below 30 knots, a series of flight control self-tests are run, and take approx. 90 seconds to complete

Moving the flight controls interrupt these tests

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11
Q

When are flight control self-tests performed?

A

After landing with speed less than 30 knots and flaps retracted

After shutdown with external power connected

Hydraulics should not be shut off
Controls should not be moved
Flaps and speed brake lever should not e moved

If two consecutive flights pass without uninterrupted self-tests, error message

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12
Q

What causes PFCs to revert to secondary mode?

A

Inertial or air data is insufficient

OR

All slat and flap position data is unavailable

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13
Q

FLIGHT CONTROL MODE EICAS?

A

Primary flight control system is in secondary mode

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14
Q

In which flight control modes is the autopilot available?

A

Only normal mode

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15
Q

How is secondary mode different from manual normal mode?

A

The PFCs use simplified computations to generate the flight control commands

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16
Q

What functions are not available in secondary mode, (nor in direct mode, for that matter)

A 
Autopilot
Auto speed brakes
Pitch compensation
Gust suppression
Roll / yaw asymmetry compensation
Tail strike protection
Envelope protection
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17
Q

When do the ACEs automatically transition to direct mode?

A

ACEs detect failure of all three PFCs or lose communication with them

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18
Q

How do you manually select direct mode?

A

Move the PRIMARY FLIGHT COMPUTERS disconnect switch to disconnect

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19
Q

PRI FLIGHT COMPUTERS EICAS?

A

Flight control system is in direct mode

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20
Q

Flight control input path in direct mode?

A

Pilot inputs received by the ACEs are sent directly to the PCUs

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21
Q

For turns with bank angle less than ________ degrees, no back pressure on the column is required

A

30 degrees

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22
Q

When does the stab trim indication on the EICAS blank?

A

Gear is up for 10 seconds

OR

60 seconds after liftoff

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23
Q

When does stab trim pointer, box and digital readout display in white?

A

When outside of the green band

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24
Q

The stab trim pointer, the box and digital readout are all in amber (readout indicates “x”)

A

Stab trim is inoperative

The pointer will remain on the scale at the last known position

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25
Q

What is the magenta figure above the stab trim digital readout?

A

The FMC calculated units of trim

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26
Q

What is the function of the nose gear oleo transducers?

A

Provide actual gross weight and CG information

Compared to FMC calculated stab green band

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27
Q

STAB GREENBAND EICAS

A

Computed green band disagrees with transducer data

The transducers disagree

Either transducer has failed

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28
Q

Do the alternate pitch trim switches have priority over the primary trim?

A

Yes

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29
Q

What is Overspeed Protection?

A

As airspeed approaches Vmo or Mmo, the pilot must apply continuous forward column pressures twice the normal force to exceed the limit

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30
Q

Stall trim protection?

A

Lowest speed to which the aircraft can be trimmed is the minimum maneuvering speed

The pilot must apply continuous aft column pressure at twice the normal rate, to maintain airspeed below minimum maneuvering speed

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31
Q

If A/T armed but not engaged, and speed decreases near stick shaker….?

A

A/T automatically activates in speed mode and advances thrust to maintain minimum maneuvering speed

AIRSPEED LOW will be displayed

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32
Q

When will the A/T not automatically engage in autothrottle stall protection? (3)

A

Pitch mode in FLCH or TOGA

Airplane below 400 ft after takeoff

Airplane below 100 ft on approach

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33
Q

How does tail strike protection work?

A

The PFCs calculate if a tail strike is imminent

Elevator deflection is then automatically decreased

Pilot can override by increasing back force

Tail strike protection is not registered by the control column

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34
Q

What is LAM?

A

Landing Attitude Modifier

Improved approach attitudes

Increases nose wheel contact margin at overspeed approaches with FLAPS 20, 25 and 30

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35
Q

How does LAM work?

A

Undrooping the flaperons and extending inboard spoilers increases pitch attitude

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36
Q

When is LAM available?

A

In normal mode during both auto flight and manual flight

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37
Q

What calculates feel commands?

A

The PFCs, based on airspeed

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38
Q

What is the difference in pitch command between normal mode and both secondary and direct mode?

A

Normal pitch mode commands a rate of pitch change

Secondary and direct mode command a proportional elevator deflection

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39
Q

Secondary and direct modes do not provide pitch compensation for:

A

Flap and speed brake configuration

Gear configuration

Thrust changes

Turns at 30 degrees of bank

Turbulence

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40
Q

STABILIZER L2 or STABILIZER R2

EICAS?

A

Uncommanded stabilizer motion sensed, and the stabilizer channel that caused the motion is shut down

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41
Q

STABILIZER warning message?

A

Both stabilizer channels automatically shut down or fail

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42
Q

STABILIZER CUTOUT warning message?

A

All power to the stabilizer switches has been removed by placing both STAB TRIM CUTOUT switches to CUTOUT

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43
Q

If control column force opposes pitch trim for more than two seconds?

A

Control cutout function will disable the trim commands until switch input indicates no trim input

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44
Q

If control column force opposes pitch trim input for more than 20 seconds?

A

STABILIZER L2/R2 EICAS

Flight controls revert to direct mode

System shutdown

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45
Q

What flight control modes is Control Column cutout function available in?

A

Normal and secondary

46
Q

Describe roll control in normal flight control mode

A

PFCs position the ailerons, flaperons and spoilers to command a roll rate in proportion to wheel displacement

47
Q

Flight control response to turbulence?

A

Aircraft roll response to turbulence is minimized by automatic control surface commands

48
Q

Why is there no aileron trim?

A

Aileron trim is incorporated into the flight control laws

No pilot input required

49
Q

Bank angle protection?

A

Reduces chance of exceeding bank angle boundaries due to:

External disturbances

System failures

Inappropriate pilot action

If 35 degrees exceeded, control wheel force rolls aircraft back to 30 degrees.

Can be overridden

50
Q

What device disables bank angle protection?

A

The A/P DISENGAGE bar

51
Q

When does bank angle indicator change to amber?

A

At bank angles exceeding 35 degrees

52
Q

Is bank angle protection available in secondary or direct modes?

A

No, only in normal mode

53
Q

If all hydraulic power lost, can pilot control pitch and roll?

A

Yes, using:

Primary pitch trim (stab)

Alternate pitch trim (stab)

Control Wheel (2 spoiler pairs)

Via direct wiring from flight deck to control surfaces

54
Q

In normal mode, rudder pedals command what?

A

They command a sideslip maneuver depending on pedal displacement

55
Q

Vertical gust suppression?

A

Enhances ride quality in vertical gusts and turbulence

Symmetric deflection of flaperons and elevators

Only with autopilot engaged in altitude hold or VNAV level flight

56
Q

Lateral gust suppression?

A

Automatic application of discrete yaw commands

57
Q

Manual rudder trim:

When is it zeroed?

When is it inhibited? (List 2 instances)

A

It is zeroes at 30 kts on takeoff
Also zeroes on landing

Further manual inputs are inhibited until airborne

Also inhibited on approach with autopilot yaw engaged (LAND3)

58
Q

When is automatic rudder trim provided?

A

During normal flight mode

59
Q

Does the automatic rudder trim displace the rudder pedals?

A

Yes, providing pilot awareness of the rudder commands

60
Q

When does the rudder trim position blank on the EICAS?

A

Gear is up plus 10 seconds

OR

60 seconds after takeoff

61
Q

When does EICAS RUDDER TRIM display automatically?

A

After landing, ground speed less than 40 kts

In the air with following EICAS messages:

PRI FLT COMPUTERS

FLIGHT CONTROL MODE

ENG SHUTDOWN

ENG FAIL

ENG THRUST

62
Q

Describe rudder ratio operation

What is it based on?

A

The rudder ratio changer is based on flap position

When flaps are up, the rudder response to pedal deflection is less than when the flaps are extended

63
Q

How many sets of spoilers are there?

A

There are seven sets of spoilers

Four outside of the flaperons

Three inside of the flaperons

64
Q

How are the spoilers powered and controlled?

A

All three hydraulic systems supply five sets of spoilers

Each pair is controlled by the same ACE and hydraulic system

Two spoiler pairs (4+11 and 5+10) are individually powered by two electrical buses

65
Q

SPOILERS EICAS?

A

Failure of one or two spoiler panels in the air

OR

Failure of one not down and locked spoiler panel on the ground

66
Q

SPOILER PAIRS EICAS?

A

Failure of three or more spoiler panels

67
Q

What is Autodrag?

A

Deflects the ailerons upward and raising the two most outboard spoilers, to assist in glideslope capture when above the glidepath

68
Q

When is the Autodrag feature available?

A

Only in the landing configuration

Flaps 25 or 30

Thrust levers in idle

Only in normal mode

69
Q

When is the Autodrag deflection removed?

A

At 500 feet AGL

70
Q

PRIMARY FLIGHT CONTROLS switch to DISC?

A

Disconnects the PFCs and puts the flight control system in the direct mode

Putting back in AUTO may restore secondary of normal mode

71
Q

PRIMARY FLIGHT COMPUTERS switch in AUTO?

A

Flight control system will operate in the normal mode

System faults will automatically cause the system to revert to secondary or direct mode

72
Q

PRIMARY FLIGHT COMPUTERS DISC light?

A

PFCs are disconnected either automatically or manually, and the system is in the direct mode

73
Q

What are the three modes of flap/slat operation?

A

Primary - hydraulic

Secondary - hydraulic or electric

Alternate - electric

74
Q

Primary flap/slat mode

A

Flaps and slats are controlled together using center hydraulic system motors

Autogap and flap load relief available

75
Q

How many flap positions on 787-8?

How many on 787-9?

Where are the gates?

A

7

10

Gates at 1 and 20 positions

76
Q

When does the flap/slat indicator display?

A

When slats begin to extend

77
Q

What is magenta figure on the flap/slat position indicator?

A

Flap lever position

78
Q

When does flap lever position indication on indicator turn green?

A

When flaps reach commanded position

79
Q

When is the flap/slat indicator removed from the EICAS?

A

10 seconds after flaps and slats reach the UP position

80
Q

When does the secondary flap/slat mode engage?

A

Center hydraulic system has failed

Flap or slat primary control failure

Primary mode fails to move flaps/slats to commanded position

Control surfaces move at less than 50% rate

Uncommanded motion detected

Flap or slat disagree detected

81
Q

Describe flap and slat secondary mode

A

Slats and flaps are controlled separately

Positioned by hydraulic or electric motors

Pilot control is through flap lever, but procedures limit flap extension to flaps 20

82
Q

What failures lead to the alternate flaps switch?

A

All 3 flight control modes in the Flight Control Electronics (FCE)

Primary and secondary modes

FLAP lever

83
Q

What features are not available in the flap and slat alternate mode?

A

Asymmetry and uncommanded motion protection

Slat autogap and pregap

Flaps and slat load relief

84
Q

What occurs when the ALTN FLAPS ARM switch is pressed?

A

ALTN appears in the switch

Each flap and slat position appears on EICAS

Alternate flap control is armed

Alternate flap selector is armed

Primary and secondary operation is disabled

Asymmetry, skew and uncommanded motion is disabled

Slat autogap disabled

Flap and slat load relief not available

Flap lever is inoperative

85
Q

Three-position ALTN Flaps selector to EXT?

A

Flaps and slats extend simultaneously

Slats are limited to middle position

Flaps are limited to flaps 20

86
Q

ALTN FLAPS selector to RET?

A

Slat retraction is inhibited until the FLAPS are UP

87
Q

When is the expanded flap indication displayed automatically?

A

Flap/slat control in secondary or alternate mode

Any non-normal condition is detected

88
Q

What colors are the outline and fill when in secondary mode?

A

White

89
Q

When the outline and fill colors of the flap indication are amber, what EICAS message(s) will you see?

A

FLAPS DRIVE

OR

SLATS DRIVE

90
Q

What does the magenta indication on the flap indicator signify?

A

Flaps or slats are in transit to the commanded position

91
Q

What does the green color on the flaps indicator signify?

A

The flaps and slats are in the commanded position

92
Q

Flap load relief?

A

Only available in the primary mode

Load relief prevents extension beyond 5-25

EICAS indication indicates in-transit condition, shows actual flap position

Flap lever does not move

93
Q

Slat load relief?

A

Available in secondary mode
(Not required in primary or alt)

If slats fully extended and airspeed > 240 knots (B787-9) or 225 knots (B787-8),
the slats will retract to the middle position

LOAD RELIEF is displayed

94
Q

What is Slat Autogap?

A

Primary mode only

If slats in middle position and high AOA, slats are fully extended to avoid stall condition

95
Q

What is slat pregap?

A

Available only in secondary mode

Slats automatically move to full extend when flaps not UP and airspeed is less than 240 knots (787-9) or 225 knots (787-8)

96
Q

Cruise flaps?

A

Automated function that improves aircraft performance by symmetrically moving the flaps, ailerons, flaperons and spoilers

Changes camber of the wing

Available above 25,000 feet between Mach .54 and .87

97
Q

CRUISE FLAPS SYS EICAS?

A

The cruise flaps system has failed with the flaps in an increased drag condition

98
Q

When are skew condition and asymmetric protection provided?

A

In primary and secondary modes

99
Q

FLAPS PRIMARY FAIL or

SLATS PRIMARY FAIL EICAS

A

Uncommanded motion, system placed in secondary mode

If motion persists, the system will shut down and FLAPS DRIVE or SLATS DRIVE will be displayed

100
Q

FLIGHT CONTROL SURFACES FAIL light?

A

Any of the control surfaces failed to lock

101
Q

If the flight controls are LOCKED, when will they automatically lock?

A

When groundspeed exceeds 40 knots

102
Q

What happens when you move the flap lever in the primary mode?

A

Sends a signal to the ACEs

ACEs send a signal to the Flight Control Module (FCM)

The FCM sends a position command back to ACEs

The position command is relayed to the PCUs

103
Q

When do the flaps fully extend (both aircraft)?

A

At flaps 25

104
Q

What are the flap and slat inhibit parameters?

A

Above 260 knots and above 20,000 feet

105
Q

When does the aircraft attempt to maintain zero yaw rate?

A

During asymmetrical reverse thrust

Takeoff in gusty conditions

Takeoff in crosswind

106
Q

What is the aircraft yaw response to an engine failure?

A

Above 60 knots groundspeed

The flight control system will command the rudder to counteract most of the yawing moment due to engine failure

Pilot will still recognize the engine failure as not all of the yaw will be counteracted

Rudder pedals will move with system

107
Q

Moving speedbrake lever to UP positions which spoilers to which positions?

A

1, 2, 13, 14 - 60 degrees

3, 12 - 45 degrees

4, 11 - 35 degrees

All inboard spoilers - 10 degrees

108
Q

With speedbrake lever in armed position, when will the spoilers extend?

A

Speedbrake lever is driven to UP position when the main gear trucks untilt and both thrust levers are not in the takeoff range

109
Q

When will the speed brakes extend if the lever is not in the ARMED position?

A

On the ground with groundspeed above 85 knots if either thrust lever was in takeoff range then subsequently both thrust levers moved to idle

On the ground and both thrust levers are moved to reverse idle

110
Q

When will speedbrakes automatically retract?

A

On ground, either thrust lever moved to takeoff range

On ground, if transition to the air

In the air, if either thrust lever is beyond 90% travel

B787 (22 decks)

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