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A320 Systems > Flight Controls. FCTRL > Flashcards

Flight Controls. FCTRL Flashcards

1
Q

What are the roles of the Elevator Aileron Computers(ELAC1 and ELAC2)?

A
  1. Control of elevators, ailerons, trimmable horizontal stabilizer(THS)
  2. Determines requirement for and activated spoiler assist during rolls, and rudder input for yaw
  3. Both are normally active. If one fails the remaining one assumes control automatically for the other one
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2
Q

What are the roles of the Flight Augmentation Computers(FAC 1 and FAC2)

A 
1 Control of rudder including 
     Turn coordination
     Yaw damping
     High/low speed rudder Limiting
     Rudder Trim
2. Only one FAC is active at a time with the other one a backup
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3
Q

What are the roles of the Spoiler Elevator Computers?(SEC1, SEC 2, SEC3)

A
  1. All SECs are active with each responsible for a specific pair, or pairs, of spoiler panels
  2. SEC1 and SEC2 can provide backup of the elevators and THS in the event of a dual ELAC failure
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4
Q

Describe normal law

A
  1. FCCs logic of the aircrafts pitch roll and yaw limits during normal ops
  2. ALL protections are available to keep aircraft in design envelope.
  3. Active when all or nearly all systems are functioning properly
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5
Q

Describe alternate law

A
  1. FCCs logic for pitch, roll, and yaw limits in response to system failures involving the FCC, hydraulic, or NAV systems(ADIRS)
  2. Some flight control characteristics change
  3. Some flight envelope protections are lost
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6
Q

Describe Direct Law

A

1 typically as a result of the landing gear being lowered while in Alternate Law but can be the result of more significant failures

  1. Flight control feel, and response is like a conventional aircraft
  2. All protections are lost
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7
Q

Describe Mechanical Backup Law

A
  1. Occurs when all FCCs have failed or total loss of electrical power
  2. Inoperative side sticks
  3. Only controlled by manual pitch trim, rudder pedals, engine thrust
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8
Q

Describe Abnormal Law

A
  1. Provides sufficient controls for unusual attitudes

2. A subset of Alternate Law

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9
Q

Describe Load Factor Demand

What’s Law/s is it available?

A
  1. Available in Normal and Alternate Law
  2. FCCs interpret pitch change command as G loading
    A. Climb commands(stick aft) result in a
    Positive G load change
    B. Descent commands(stick forward)
    Result in negative G load
    C. Neutral Stick result in 0 G loading
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10
Q

Describe automatic Pitch Trim during a roll

Which law/s is it available

A
  1. Automatic pitch trim is provided by the ELACs in Normal AND Alternate mode
  2. Automatically provided for pitch trim up to 33 degrees
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11
Q

Describe Maneuver Protection

Available in which Law/s

A
  1. Available in Normal and Alternate modes
  2. Restricts flight control movement that exceed its designed structural G loading
    A. Clean = -1.0g to 2.5g
    B. Slats extended/flaps retract = -1g to 2.5g
    C. Slats and flaps extended = 0g to 2.0g
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12
Q

Describe pitch Protection

Available in which Law/s?

A
  1. Available ONLY in Normal Law
  2. Prevents excessive nose up or nose down attitudes
  3. ELACs will allow attitudes no greater than 30* nose up and 15* nose down
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13
Q

Describe high speed protection

Available in which Law/s?

A
  1. Only in Normal Law
  2. Attempts to prevent aircraft from exceeding VMO/MMO
  3. Autopilot automatically disengaged
  4. ELACs auto pitch the aircraft up to limit acceleration regardless of stick position
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14
Q

Describe Alpha Protection (Alpha Prot.)

Available in which Law/s?

A
  1. Normal Law only
  2. FCCs prevent AOA from exceeding predetermined threshold at low speed
  3. Auto pilot disengages and speed brakes auto retract
  4. FCC Load Factor Demand to direct side stick pitch control.
  5. Pilot side stick input CAN override the FCC and further degrade AOA
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15
Q

Describe Roll Rate Demand

Available in which Law/s?

A
  1. Only in Normal Law
  2. Full sidestick give max roll rate if 15* per second regardless of airspeed or configuration
  3. Half stick deflection yield half max roll rate
  4. Neutral side stick commands a zero change in rate
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16
Q

Describe Bank Angle Hold and Positive Spiral Stability

A

Both roll characteristics are only available in Normal Law

Bank Angle Hold = at bank angles of less than or equal to 33* the bank is maintained with automatic pitch trim when side stick is released

Positive Spiral Stability- at bank angles greater than 33* if sidestick is released the aircraft will auto roll back to 33*
1. Continuous pressure on sidestick to hold bank angles exceeding 33* as well as pitch adjustments

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17
Q

Describe the roll of Automatic Pitch Trim during turns

Available in which Law/s?

A
  1. Available in Normal Law and Alternate Law
  2. At bank angles of 33* or less, the ELACs auto introduce necessary back pressure through auto pitch trim
  3. At bank angles over 33* the feature is inhibited and aft sidestick will be necessary to maintain a level turn
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18
Q

Describe bank angle protection

Available in which Law/s?

A
  1. Only inNormal Law

2. ELACs restrict bank angle to max 67* even if full left or right sidestick is maintained

19
Q

What are the indications of Normal Law on the PFD?

Pic

A

Green equal signs at:

  1. 67* bank angle limit
  2. +30* and -15* pitch attitude limits
  3. High speed protection limit
20
Q

Describe the Ground Mode, Flight Mode, and Landing Modes of Normal Law

A

Ground Mode:

  1. Active on ground
  2. Direct relationship between sidestick and flight control surfaces
  3. Allows flight control check and rotation

Flight Mode:

  1. Active shortly after takeoff
  2. All FCCs protections and flight characteristics take effect

Landing Mode:

  1. On descent through 50’ AGL at which point the ELACs memorize pitch attitude
  2. At 30’ AGL, ELACs add gentle down pitch commands
  3. Pilot instinctively counters nose down moment resulting in Normal flare
  4. Shortly after landing it returns to ground mode and the THS resets to 0.
21
Q

How is roll control maintained while in Alternate Law

A
  1. Direct relationship between sidestick deflection and aileron/elevator deflection
  2. All roll control flight characteristics and protections are lost
22
Q

Describe high and Low speed stabilities in Alternate Law

A

High Speed Stability:
1. Active below VMO/MMO
2. ELACs command elevators to increase pitch, attempting to prevent an increase in speed
3 High SpeedStability CAN be overridden by sidestick input

Low Speed Stability:

  1. Active at airspeeds slightly higher than stall
  2. FCCs command elevators to decrease aircrafts pitch, attempting to increase speed
  3. Low Speed Stability can be overridden by sidestick
23
Q

What is the Stall Speed indication on the PFD when in Normal or Alternate Law?

A

By the top of the red and black “barber pole” of the airspeed indicator

24
Q

What are the indications of Alternate Law?

Pic

A
  1. Normal Law indications are replaced with Amber Xs
  2. F/CTL ALTN LAW (PROT LOST) message in the E/WD memo section
  3. Contrary to the ECAM message, SOME GCC protections remain active.
25
Q

What are the indications of Direct Law?

A
  1. Alternate Law Amber Xs remain
  2. USE MAN PITCH TRIM (Amber) appears above the artificial horizon on the PFD
  3. F/CTL DIRECT LAW (PROT LOST) message on E/WD memo section
  4. ECAM message is correct. aLL protections are lost
26
Q

Describe Mechanical Backup Law

A
  1. Provides mechanical control in the event all FCCs fail or a total loss of electrical power
  2. Intended to be used only until restoration of FCC or electrical power
27
Q

Which flight control surfaces are operational when in Mechanical Backup Law

A
  1. Rudder
  2. Trimmable Horizontal Stabilizer (THS)
  3. Only available if there is hydraulic power to the respective servos
28
Q

PFD indications of Mechanical Backup Law

Pic

A
  1. Alternate Law Amber Xs remain
  2. MAN PITCH TRIM ONLY (red) appears above artificial horizon.

PFD displays are predicated on electrical power

29
Q

What are the indications of Alpha Prot on the airspeed indicator
(Pic)

A
  1. Alpha Prot is represented by the position of the top of the Amber and black band
  2. Available only in Normal Law
  3. It can be overridden with aft side stick movement
30
Q

What is Alpha Max and how is it indicated on the airspeed indicator?
(Pic)

A
  1. Alpha Max is the highest AOA that the flight control computers will allow:
    A. ONLY in Normal Law
    B. It cannot be overridden by the pilot
    Even with full aft sidestick pressure
  2. Represented by the top of the red band on the airspeed indicator
31
Q

Describe Abnormal Law

A
  1. Ensures flight characteristics and protections associated with Normal Law do not interfere with recovery from an abnormal flight attitude.
  2. Essentially it’s Alternate Law with no auto pitch trim or yaw dampening. After the recovery has been made, the aircraft remains in Alternate Law for the remaining of the flight
  3. Law will not degrade to Direct Law once the landing gear is extended
32
Q

How is the rudder and rudder Trim displays on the ECAM F/CTL page.
(Pic)

A
  1. Rudder is depicted in green and represents actual rudder position
  2. Commanded rudder Trim is represented by the cyan (blue) tick mark
33
Q

What’s the meaning of a pulsing A-LOCK (blue) on the E/WD?

Pic

A
  1. A-LOCK is displayed as an indication that leading edge slat retraction has been inhibited due to excessively low airspeed or high angle of attack
  2. Once airspeed and/or AOA corrections have been made, the slats will respond to flap lever commands and retract, and A-LOCK indications disappears
34
Q

What is the sidestick priority system.

Pic

A

The sidestick priority system allows either pilots sidestick to have sole control of the aircraft in the event
1. Pressing and holding the Autopilot Disconnect/Priority pb:
A. Disengages the AP/s I’d engaged
B. Temporarily deactivates the opposite
Sidestick
C. Generated respective “Priority Left or
Priority Right” voice message
D. A Red Arrow illuminates only on the SIDE
STICK PRIORITY indicator of the pilot
Whose sidestick has been deactivated
E. If the deactivated sidestick is sensed NOT
To be in the neutral position, CAPT or F/O
(Both green) illuminates ONLY on the
SIDE STICK PRIORITY indicator of the
Pilot who has taken priority
2. After 40 sec. of pressing the sidestick Autopilot Disconnect/Priority pb, it may be released and the opposing sidestick will remain temporarily deactivated
3. A deactivated sidestick may be deactivated at any time by pressing its Autopilot Disconnect/Priority pb

35
Q

What occurs when both side sticks are simultaneously moved?

A

1 “Dual Input” is heard from loudspeakers
A. If moved in the same
Direction:
1. ELACs will “sum their inputs” up to a
Max of one sidesticks full deflection
B. If moved in the opposite directions:
1. ELACs cancel both inputs

36
Q

What are the indications on the ECAM F/CTL page of hydraulic system power sources?
(Pic)

A
  1. G - indicates controls powered by the Green hydraulic system
  2. Y - by the Yellow hydraulic system
  3. B - by the blue system
  4. If the system is functioning normally, the letter is displayed in green, it changes to Amber if the respective hydraulic system has failed
37
Q

What are the indications of the Flight Control Computers on the ECAM F/CTL page
(Pic)

A
  1. The two ELACs and the three SECs are depicted
  2. The respective computers number is shown in green when functioning normally
  3. If a FCC fails or has been selected OFF, the computers number and the half-box surrounding it both turn Amber
  4. The two FACs are not depicted on the ECAM F/CTL page
38
Q

What are the indications of Pitch Trim on the ECAM F/CTL page?
(Pic)

A
  1. A digital readout for Pitch Trim on the ECAM F/CTL page
    A. It displays the angle of the
    THS for nose UP or nose DN trimming
    For example:
    -0.6* UP indicates the THS is set at
    -0.6* for aircraft nose up trimming
    (Opposite for DN)
  2. Pitch trim must manually be set for takeoff. Once airborne pitch trim is auto positioned per FCC logic
39
Q

What are the two references on the ECAM F/CTL page which represents the neutral aileron positions?
(Pic)

A
  1. The two white tick marks represents the ailerons neutral position when the flaps are retracted
  2. The white square represents the ailerons neutral position when the flaps are extended. This is referred to as “Aileron Droop” and provides additional aerodynamic lift when the flaps are extended
40
Q

What are the indications on the E/WD memo section of Speed Brake deployment?
(Pic)

A
  1. SPEED BRAKE - in green when deployed and the engines at idle
  2. SPEED BRAKE - in Amber when deployed and the engines above idle
41
Q

What are the speed brake deployment limits with Autopilot engagement?

A
  1. With AP engaged the range of speed brake deployment is limited to half the max range. Placing speed brake lever beyond the 1/2 position will yield NO further deployment
  2. Should AP failure occur with the speed brake lever beyond 1/2 position the speed brakes will immediately deploy further to meet the levers commanded position
42
Q

What are the method/s of monitoring Speed Brake and Ground Spoiler deployment?
(Pic)

A
  1. Vertical pointing arrows (green) appear on both ECAM F/CTL and WHEEL pages
  2. On landing the ground spoilers are monitored on the WHEEL page, which is auto displayed with landing gear extension
43
Q

What are the conditions that will cause Speed Brakes to automatically retract if deployed in-flight?
(Pic)

A
  1. FLAPS FULL selected
  2. Airspeed decreases to Alpha Prot.
  3. Thrust Levers placed to TOGA
44
Q

What are the requirements for automatic Ground Spoilers deployment during landing or rejected takeoff?
(Pic)

A
  1. MAin gear - Weight on Wheels
  2. Main gear wheel - 72 knots or greater
    A. When ARMED: they deploy
    When both thrust levers at IDLE
    B. When NOT ARMED: they
    Deploy when at least one thrust lever
    Is in the REV and the other is at IDLE

A320 Systems (15 decks)

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