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Airbus A330 > Flight Controls > Flashcards

Flight Controls Flashcards

1
Q

Flight Controls subjects are

A

Fly by wire, Flight Control surfaces, slats and flaps, controls and indications, flight control computers FCC

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2
Q

Flt controls are ______________ controlled and ________________ actuated

A

Electrically / hydraulically

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3
Q

The THS Trimmable Horizontal Stabilizer is mechanically linked to

A

Cockpit controls should a temporary, complete loss of electrical power occur

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4
Q

The two hand wheels mechanically control

A

THS

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5
Q

There is no _________trim

A

Aileron

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6
Q

A/P , sidestick input F/CTL computes flight control surface actuators

A

________ FCC . 1 is capable of controlling the aircraft.

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7
Q

3 PRIM (Flight Control Primary Computers) actuate:

A

Normal, Alternate and Direct control laws; speedbrake and ground spoiler control; protection speed computation; rudder travel limit

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8
Q

2 SEC computers; flight control secondary computer (FCSC) actuate:

A

Direct control laws including yaw damper function; Rudder trim and rudder travel limit

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9
Q

3 PRIM / 2 SEC = 2 FCDC (Flight Control Data Concentrators) = acquire data signal = CMC

A

Central Maintenance Computer

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10
Q

If 1 computer is unable, another executes, except

A

Spoiler control

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11
Q

If all PRIM fail, each SEC becomes

A

Its master and controls its surfaces

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12
Q

Sidesticks become active when ________ power is available

A

Hydraulic

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13
Q

Simultaneous inputs by Captain and F/O are

A

Algebraically summed

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14
Q

After first engine is running, sidestick position

A

Indicator is on PFD

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15
Q

PFD = + combined sidestick order and > Max sidestick deflection

A

PFD = + combined sidestick order and > Max sidestick deflection

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16
Q

Two sidestick pb handgrip:

A

A/P disconnect/ sidestick priority pb ; ptt pb

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17
Q

If held for at least ____ seconds, the other sidestick is latched out and takeover pb can be released without losing priority

A

40

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18
Q

To reactivate sidestick,

A

Press takeover pb

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19
Q

Max elevator deflection

A

30º up 15 ºdown

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20
Q

Max THS deflection 14º up

A

2ºdown

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21
Q

Two electrically controlled hydraulic servojacks are fitted on each

A

Elevator

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22
Q

Servojacks 3 modes are

A

Active = electrically controlled; damping = follows surface; centering = hydraulica maintained in neutral position

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23
Q

Normal – 1 active and 1

A

Damping (some maneuvers can cause it active)

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24
Q

If active servojack fails, damped becomes

A

Active and dialed damping

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25
Q

If servojacks are not ___________/__________ controlled, switched to damping

A

Electrically / hydraulic

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26
Q

If ____ elevator servojacks not electrically controlled , automatically centering mode

A

4

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27
Q

Elevators by PRIM 1 – left and right elevators driven by

A

Green hydraulic jacks

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28
Q

If PRIM 1 fails, PRIM 2 assumes through

A

blue and yellow hydraulic jacks.

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29
Q

If PRIM 1 / PRIM 2 unavailable

A

Pitch control SEC 1 / PRIM 3 THS control

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30
Q

PRIM 1/2/3 fail

A

SEC elevator THS 0 (lost control)

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31
Q

Elevator indicator partially boxed amber if electrical failure detected by

A

PRIM

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32
Q

Blue or yellow hydraulic power available – mechanical control by

A

Cable of THS

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33
Q

If three PRIM fails, electrical control of

A

THS is lost

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34
Q

Ailerons max deflection

A

25º. Spoiler max deflection 35º.

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35
Q

Aileron droop =

A

Ailerons deflected when flaps extended

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36
Q

Each aileron servojack has two control modes

A

Active / damping

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37
Q

The system automatically selects Damping mode if _______ and _______ or ______ and _______ low pressure, or if respective computer fails

A

Green / yellow or blue and green

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38
Q

At high speed more than ____ kt in Conf 0 – outboard ailerons = 0 deflection

A

190

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39
Q

In A/P or in some failures, outboard ailerons up to ____ kt

A

300

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40
Q

If RAT only – outboard ailerons in

A

Damping – reduce hydraulic power consumption

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41
Q

Spoilers automatically retracted to

A

Zero if fault or loss of electrical control

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42
Q

Spoiler retains deflection at time of loss, or lesser deflection if aerodynamic forces push it if system

A

Loses hydraulic pressure

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43
Q

Roll control is achieved by ____ ailerons and ____ spoilers on each wing

A

Two / five

44
Q

Yaw control on a single rudder surface, actuated by

A

3 independent hydraulic jacks (each by different hydraulic system)

45
Q

Max rudder deflection is

A

+- 35º

46
Q

PFTU

A

Pedal feel and trim unit

47
Q

PRIM 1 = yaw damping and

A

Turn coordinator

48
Q

No feedback to rudder pedals from

A

Yaw damping / turn coordination

49
Q

In case of total electrical failure or loss of rudder control, flight control computers failure, Backup Control Module (BCM) controls

A

Yellow hydraulic jack or Blue (if yellow not available)

50
Q

Rudder trim is

A

Manual flight

51
Q

Rudder trim is ___/second in clean configuration

A

1º

52
Q

Manual flight ____ authority of max rudder deflection ___ degrees

A

85% / 29

53
Q

The BCM provides this amount of control of the rudder in case of total electrical failure:

A

Direct rudder command and yaw damping

54
Q

The pilot can in manual flight apply rudder trim from the

A

RUD TRIM rotary sw on the pedestal: authority 85% of max rudder deflection limited to 29º

55
Q

Spoiler max deflection 1 = 25º and 2 to 6=

A

30º

56
Q

Speedbrakes inhibited if active

A

Maneuver load alleviation MLA; angle of attack protection; low speed stability; at least one thrust lever more than MCT; A.FLOOR

57
Q

Speed brakes can be reset again___ sec after lever reset

A

5

58
Q

Message SPEED BRK when speed brakes are extended

A

From 1,500 ft after takeoff until landing

59
Q

Message SPEED BRK green / flashes amber

A

At least 1 engine idle; speed brakes extended during takeoff roll until reaching 1,500ft after takeoff

60
Q

RTO > 72 kt spoilers armed – extend – idle / not armed

A

Extend at least 1 reverse other idle

61
Q

GND SPLRS partially extend when reverse on at least

A

1 engine (other at idle) and 1 main gear compressed

62
Q

The ground spoilers automatically extend during RTO >

A

72 kt

63
Q

When speed brakes are selected, spoilers

A

1 to 6 are activated

64
Q

Within_______________, which determine how aircraft flight control surfaces should be positioned

A

FCCs – control laws

65
Q

Active Normal Law = all flight control surfaces function even after certain

A

FCC, hydraulic, electrical faults

66
Q

Normal law protections:

A

Load factor limitation, pitch attitude, angle of attack, high speed, bank angle protections, and low energy warning, and also maneuver load alleviation

67
Q

THS automatically set at ____degrees up until reset for required takeoff

A

4

68
Q

Rotation maneuver in Direct Law with full

A

elevator authority

69
Q

5 seconds blend ground mode in normal law – 5 seconds -

A

Flight mode

70
Q

Normal law flight mode is a load factor demand law with

A

autotrim and full flight envelope protection.

71
Q

Pitch normal law – sidestick neutral and wings level -

A

1 G

72
Q

Sidestick forward – load factor – increases / aft – load factor -

A

Decreases

73
Q

Pitch trim automatic

A

Manual / A/P

74
Q

Frozen automatic pitch trim:

A

Manual trim order; radio altitude < 100ft for flare; load factor < 0.5 g; high speed protection

75
Q

Normal turns – up to ___ degrees bank, don’t hold back for keeping altitude

A

33

76
Q

Establish a turn ,

A

release to neutral

77
Q

Flare mode =

A

Direct stick to elevator relationship, with some damping by load factor and pitch rate feedbacks

78
Q

At 50 ft – slight pitch

A

Down – pilot moves sidestick rearwards to maintain constant path = reproduce conventional aircraft aerodynamic characteristics

79
Q

Once the aircraft is flying the required trajectory, or flight path, the sidestick can e release to

A

Its neutral position, and the aircraft will maintain 1g

80
Q

The flight mode changes to flare mode at

A

Landing when passing 100ft. Flare mode is a direct stick to elevator relationship

81
Q

Pitch normal law protections:

A

Load factor limitations, pitch attitude, angle of attack, high speed, low energy warning

82
Q

Pitch normal law – sidestick – load factor limitation-

A

F/CTL computes – slats + 2.5g to -1 g / extended +2.0g to 0g

83
Q

ECAM – G LOAD - > 1.4g or

A

< 0.7g

84
Q

Pitch attitude ___ up / ____ up low speed / ______ down

A

30º / 25º / 15º

85
Q

Pitch limits on PFD =

A

Green – PFD declutter > 25º up < 13º down

86
Q

PFD V(red) >

A

30ºup – PFD normal between 22ºup and 10ºdown

87
Q

Low end of speed = alpha -

A

Max lift attained

88
Q

Conventional aircraft = stick shaker / A330 normal law – alpha= alpha protection -

A

System switches the elevator control from normal mode to protective

89
Q

Protection mode =

A

Angle of attack proportional to sidestick deflection

90
Q

Alpha max =

A

Maximum angle of attack available normal law < theoretical maximum

91
Q

In the range between alpha protection and alpha max, sidestick

A

Commands alpha directly. A/P disconnects if Alpha Protection is active

92
Q

Alpha protection, alpha max and A.FLOOR vary according to

A

Weight and configuration

93
Q

Alpha prot and alpha max = flight computer =

A

PRIM

94
Q

A.FLOOR – PRIM – activated through

A

A/Thrust system

95
Q

Fly lower alpha protection-

A

Sidestick rearwards (protection)

96
Q

If sidestick released angle returns

A

To alpha protection and stays there

97
Q

Critical angle – A.FLOOR by A/Thrust system. A/Thrust commands

A

TOGA regardeless of lever position

98
Q

A/Thrust armed or off engages TOGA when

A

Angle> threashould in acceleration config; ground speed variation; difference G/S and IAS; sidestick > 14º pitch ; attitude >25º; AOA is active

99
Q

Exit AOA protection if

A

Pushed > 8º fwd; pushed > 0º fwd at least 1 sec (alpha < angle max); neutral or pushed fwd (angle

100
Q

Exit A.FLOOR

A

Message TOGA LK on FMA

101
Q

To cancel TOGA LOCK, thrust lever

A

reduced to thrust required to press A/THR instinctive disconnect pb

102
Q

PFD VLS , Vangle Prot

A

Top of amber and black; V angle max top of red

103
Q

VMAX – automatic – AP off,

A

Pitch trim frozen and positive spiral static stability, so release sidestick, aircraft wings level

104
Q

Vmax prot =

A

Bank limit from 67º to 45º

105
Q

High speed protection symbol =

A

Green at VMO + 4kt

106
Q

Between 2,000ft and 100ft SPEED,SPEED,SPEED computed by PRIM’s with inputs

A

Aircraft config, airspeed deceleration rate, flight path angle

Airbus A330 (33 decks)

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