CH11 A330 FLT CTR Flashcards
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD.
- *F/CTL PAGE**
1. Spoiler and Speed Brake Indications
Spoiler status is depicted as:
- Green Line - Spoiler ______ and ______
- Green Triangle - Spoiler ____ and ______.
- Amber Triangle - Spoiler ______ and ______
- Amber Number - Spoiler ______ and ______.
- The ________ of the affected spoiler is displayed in amber.
- Amber XXs - The flight control computer cannot determine the ________ of the spoiler surface
- or the corresponding _______ ______ _______ is inoperative.
VOL. II, 27.4.2 F/CTL Page
- *F/CTL PAGE**
1. Spoiler and Speed Brake Indications
Spoiler status is depicted as:
- Green Line - Spoiler operational and retracted
- Green Triangle - Spoiler operational and extended.
- Amber Triangle - Spoiler faulted and extended
- Amber Number - Spoiler faulted and retracted.
- The number of the affected spoiler is displayed in amber.
- Amber XXs - The flight control computer cannot determine the position of the spoiler surface
- or the corresponding flight control computer is inoperative.
VOL. II, 27.4.2 F/CTL Page
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
F/CTL PAGE
2. Aileron Position Indication
The aileron position indicator consists of
- a white scale showing the ________ of aileron deflection
- and a ________ position indicator for each aileron.
Aileron position indicators depicted:
• Green - ________ operation
• Amber - Both ________ for the aileron are inoperative
• Amber XXs - The flight control computers cannot determine the ________ of the aileron.
VOL. II, 27.4.2
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
F/CTL PAGE
2. Aileron Position Indication
The aileron position indicator consists of
- a white scale showing the range of aileron deflection
- and a green position indicator for each aileron.
Aileron position indicators depicted:
• Green - Normal operation
• Amber - Both servos for the aileron are inoperative
• Amber XXs - The flight control computers cannot determine the position of the aileron.
VOL. II, 27.4.2
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
- *F/CTL PAGE**
- *2. Aileron Position Indication**
Droop Positions
- A ________ box on the position indicator scale depicts the current drooped aileron neutral position.
- A box only appears when the following configurations are selected:
- First droop level - Flaps __ + ___
- Second droop level - Flaps __, __, or ____
Note: Ailerons do not droop in the flaps ___ position (slats only).
VOL. II, 27.4.2
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
- *F/CTL PAGE**
- *2. Aileron Position Indication**
Droop Positions
- A white box on the position indicator scale depicts the current drooped aileron neutral position.
- A box only appears when the following configurations are selected:
- First droop level - Flaps 1 + F
- Second droop level - Flaps 2, 3, or FULL
Note: Ailerons do not droop in the flaps 1 position (slats only).
VOL. II, 27.4.2
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
F/CTL PAGE
3. Hydraulic System Pressure Indications
The hydraulic system letters positioned adjacent to the flight control symbols indicate the hydraulic systems powering each of the flight control surfaces.
- • G - ________ system
- • B - ________ system
- • Y - ________ system
The letters are displayed in either:
- • Green - ________ hydraulic system pressure
- • Amber - ________ hydraulic system pressure
Note: Amber half box -
- The flight control computer controlling that servo has ________ or is ______ ______.
- The ________ is inoperative.
VOL. II, 27.4.2
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
F/CTL PAGE
3. Hydraulic System Pressure Indications
The hydraulic system letters positioned adjacent to the flight control symbols indicate the hydraulic systems powering each of the flight control surfaces.
- • G - Green system
- • B - Blue system
- • Y - Yellow system
The letters are displayed in either:
- • Green - Normal hydraulic system pressure
- • Amber - Low hydraulic system pressure
Note: Amber half box -
- The flight control computer controlling that servo has failed or is selected off.
- The servo is inoperative.
VOL. II, 27.4.2
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
F/CTL PAGE
4. Pitch Trim Position Indication
- • PITCH TRIM label - Normally ________
- • Amber - THS _____________ control lost. THS - Trimable Horizontal Stabilizer
Pitch Trim Position Indication - Normally green:
- • The numeric value indicates the ______ ______ setting.
- • UP or DN - The selected setting produces aircraft ______ ____ or ______ ______ trim.
- • Amber - B + Y hydraulic low pressure. Pitch trim is ______ ______.
VOL. II, 27.4.2
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
F/CTL PAGE
4. Pitch Trim Position Indication
- • PITCH TRIM label - Normally white
- • Amber - THS electrical control lost. THS - Trimable Horizontal Stabilizer
Pitch Trim Position Indication - Normally green:
- • The numeric value indicates the pitch trim setting.
- • UP or DN - The selected setting produces aircraft nose up or nose down trim.
- • Amber - B + Y hydraulic low pressure. Pitch trim is not available.
VOL. II, 27.4.2
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
F/CTL PAGE
5. Elevator Position Indication
The elevator position indicators depicted:
- • Green - ________ operation
- • Amber - Both the ________ and ________ hydraulic system pressures are low.
- • Amber XX - The flight control computers cannot determine the ________ of that elevator.
VOL. II, 27.4.2
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
F/CTL PAGE
5. Elevator Position Indication
The elevator position indicators depicted:
- • Green - Normal operation
- • Amber - Both the green and blue hydraulic system pressures are low.
- • Amber XX - The flight control computers cannot determine the position of that elevator.
VOL. II, 27.4.2
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
F/CTL PAGE
6. Rudder Indications
The scale shows the full range of rudder travel. Rudder position indicator depicted:
- • Green – ________
- • Amber rudder symbol and scale -
- All ________ hydraulic systems have low pressure.
Rudder travel limiter indicator
- Shows the rudder ________ limits.
- Green – ________
- Amber - Rudder travel limit ________ is unavailable
Rudder trim position indicator depicted
- • Blue – ________
- • Amber - Rudder trim systems __ and __ are inoperative.
NORM CTL - Not normally displayed.
- Appears in amber when normal rudder control is ________ and the ______ ______ ______ (______) is in operation.
VOL. II, 27.4.2
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
F/CTL PAGE
6. Rudder Indications
The scale shows the full range of rudder travel. Rudder position indicator depicted:
- • Green – Normal
- • Amber rudder symbol and scale -
- All three hydraulic systems have low pressure.
Rudder travel limiter indicator
- Shows the rudder deflection limits.
- Green – Normal
- Amber - Rudder travel limit function is unavailable
Rudder trim position indicator depicted
- • Blue – Normal
- • Amber - Rudder trim systems 1 and 2 are inoperative.
NORM CTL - Not normally displayed.
- Appears in amber when normal rudder control is lost and the Backup Control Module (BCM) is in operation.
VOL. II, 27.4.2
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
- *PFD**
- *1. Protection Limit Symbols**
- Green equal signs symbolize ______ and ______ limits.
- Limit indications are replaced by amber XXs when in ______ or ______ law.
Limit symbols are placed at:
- • ___°_ bank
- • ____° nose up
- • ____° nose down
- •___+___
VOL. II, 27.4.3
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
- *PFD**
- *1. Protection Limit Symbols**
- Green equal signs symbolize attitude and speed limits.
- Limit indications are replaced by amber XXs when in alternate or direct law.
Limit symbols are placed at:
- • 67° bank
- • 30° nose up
- • 15° nose down
- •VMO+4
VOL. II, 27.4.3
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
2. Sidestick Position Indicator
- The sidestick position indicator is displayed on both PFDs while on the ________ with __ ______ running.
- It indicates the ________ captain/first officer sidestick positions.
Note: Sidestick position is not an indication of ______ ______ ______ positions.
VOL. II, 27.4.3
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
2. Sidestick Position Indicator
- The sidestick position indicator is displayed on both PFDs while on the ground with an engine running.
- It indicates the summed captain/first officer sidestick positions.
Note: Sidestick position is not an indication of flight control surface positions.
VOL. II, 27.4.3
_FLTCTR_01_
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
E/WD
Flap Position Display
1. S and F
The S indicates the ________ side of the display and the F indicates the ________ side.
The letter and slat/flap symbol display are depicted:
- • White - _____\_ operation (S and F not displayed in ________ configuration)
- • Amber - Respective surface is ________, either due to a loss of ______ ______or ________ control.
VOL. II, 27.4.4 E/WD Flap Position Display
_FLTCTR_01_
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
E/WD
Flap Position Display
1 S and F
The S indicates the slat side of the display and the F indicates the flap side.
The letter and slat/flap symbol display are depicted:
- • White - Normal operation (S and F not displayed in clean configuration)
- • Amber - Respective surface is inoperative, either due to a loss of hydraulic pressure or computer control.
VOL. II, 27.4.4 E/WD Flap Position Display
_FLTCTR_01_
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
E/WD
- A LOCK (replaces S) - Pulses _________, ______/______ lock function is active
- (_______ at 1 but selected _______).
VOL. II, 27.4.4
_FLTCTR_01_
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
E/WD
- A LOCK (replaces S) - Pulses green, alpha/speed lock function is active
- (slats at 1 but selected up).
VOL. II, 27.4.4
_FLTCTR_01_
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
E/WD
1. F RELIEF (replaces F) - Pulses ________, flap ______ ______ function is active.
- Flap load relief is only available in position __, __, or ______.
- The flap load relief system commands a flap position of ________ position ________ than selected.
VOL. II, 27.4.4
_FLTCTR_01_
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
E/WD
1. F RELIEF (replaces F) - Pulses green, flap load relief function is active.
- Flap load relief is only available in position 2, 3, or FULL.
- The flap load relief system commands a flap position of one position less than selected.
VOL. II, 27.4.4
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
E/WD
2. Selected Slat/Flap Position
Selected slat and flap position symbols appear in _____ until the respective surface is in the _____ position.
3. Actual and Selected Position Indications
The slat and flap symbols depicted:
- • Green - ________ slat or flap positions in ________ operation.
- • Amber - A ________ has occurred causing the respective slats or flaps to be ______________.
VOL. II, 27.4.4
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
E/WD
2. Selected Slat/Flap Position
Selected slat and flap position symbols appear in blue until the respective surface is in the commanded position.
3. Actual and Selected Position Indications
The slat and flap symbols depicted:
- • Green - Actual slat or flap positions in normal operation.
- • Amber - A failure has occurred causing the respective slats or flaps to be inoperative.
VOL. II, 27.4.4
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
E/WD
When a clean configuration is reached, only a ‘________ view’ of the wing is displayed.
The ________ symbols are not displayed.
VOL. II, 27.4.4
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
E/WD
When a clean configuration is reached, only a ‘side view’ of the wing is displayed.
The position symbols are not displayed.
VOL. II, 27.4.4
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
4. FLAPS Lever Selection
- Indicates the ________ flap configuration.
- The indications are depicted in ________ when the commanded slat/flap position has been reached and ________ while in transit.
- Blank - Position 0 is selected (slats and flaps up).
- 1 + F - Slats and flaps are selected to __. _(_______ only)
- 1 - ________ only (position 1 selected from ___ ______).
- 2 - _____ and _____ selected to 2.
- 3 - ________ set to 3 (_______ _______) and flaps selected to _.
- FULL - _____ and _____ fully extended.
VOL. II, 27.4.4
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
4. FLAPS Lever Selection
- Indicates the commanded flap configuration.
- The indications are depicted in green when the commanded slat/flap position has been reached and blue while in transit.
- Blank - Position 0 is selected (slats and flaps up).
- • 1 + F - Slats and flaps are selected to 1. (Take off Position only)
- • 1 - Slats only (position 1 selected from 0 inflight).
- • 2 - Slats and flaps selected to 2.
- • 3 - Slats set to 3 (fully extended) and flaps selected to 3.
- • FULL - Slats and flaps fully extended.
VOL. II, 27.4.4
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
FLAPS Lever Selection
5. Selectable Position Indications
- The small white squares indicate a ________ slat or flap position.
- They are not shown when the airplane is in the ________ configuration.
VOL. II, 27.4.4
FLTCTR_01
Discuss normal and abnormal indications on the F/CTL page, PFD, and E/WD
FLAPS Lever Selection
5. Selectable Position Indications
- The small white squares indicate a selectable slat or flap position.
- They are not shown when the airplane is in the clean configuration.
VOL. II, 27.4.4
FLTCTR_02
Discuss the meaning of the ECAM memos as they relate to flight control system.
SPEED BRK
- If the speed brakes are extended, the message is displayed in ________.
- The message becomes amber in flight if one or both engines are not at idle thrust for more than [_____] seconds.
VOL. II, 27.2.13
FLTCTR_02
Discuss the meaning of the ECAM memos as they relate to flight control system.
SPEED BRK
- If the speed brakes are extended, the message is displayed in green.
- The message becomes amber in flight if one or both engines are not at idle thrust for more than [50] seconds.
VOL. II, 27.2.13
FLTCTR_02
Discuss the meaning of the ECAM memos as they relate to flight control system.
GND SPLRS ARMED
If the ground spoilers are armed the message is displayed in _________.
TURB DAMP OFF
TURB DAMP pb is selected ________
VOL. II, 27.2.13
FLTCTR_02
Discuss the meaning of the ECAM memos as they relate to flight control system.
GND SPLRS ARMED
If the ground spoilers are armed the message is displayed in green.
TURB DAMP OFF
TURB DAMP pb is selected OFF
VOL. II, 27.2.13
FLTCTR_03
Describe the indications on the PFD when in normal, alternate, & direct law as well as backup flight control.
NORMAL LAW
On the PFD, green equal signs are present at [_____°] of bank, at [____°_ & _-____°] of pitch, and a few knots above _____/____. The range where alpha protection is active is displayed on the airspeed indicator as a _____ and _____ band.
VOL. II, 27.3.4.1-5
FLTCTR_03
Describe the indications on the PFD when in normal, alternate, & direct law as well as backup flight control.
NORMAL LAW
On the PFD, green equal signs are present at [67°] of bank, at [30° & -15°] of pitch, and a few knots above VMO/MMO. The range where alpha protection is active is displayed on the airspeed indicator as a black and amber band.
VOL. II, 27.3.4.1-5
FLTCTR_03
Describe the indications on the PFD when in normal, alternate, & direct law as well as backup flight control.
ALTERNATE LAW
To indicate the loss of protections,
- amber _____s_ replace the green equal signs on the PFD.
- Alpha prot and alpha max are replaced by a ____ and _____ striped stall warning indication (VSW).
VOL. II, 27.3.5.2
FLTCTR_03
Describe the indications on the PFD when in normal, alternate, & direct law as well as backup flight control.
ALTERNATE LAW
To indicate the loss of protections,
- amber XXs replace the green equal signs on the PFD.
- Alpha prot and alpha max are replaced by a red and black striped stall warning indication (VSW).
VOL. II, 27.3.5.2
FLTCTR_03
Describe the indications on the PFD when in normal, alternate, & direct law as well as backup flight control.
DIRECT
- If direct law is active, an amber ______ ______ ______ ______ message is displayed on the PFD.
- This is a reminder of the loss of ________ pitch trim.
VOL. II, 27.3.6.2
FLTCTR_03
Describe the indications on the PFD when in normal, alternate, & direct law as well as backup flight control.
DIRECT
- If direct law is active, an amber USE MAN PITCH TRIM message is displayed on the PFD.
- This is a reminder of the loss of automatic pitch trim.
VOL. II, 27.3.6.2
FLTCTR_03
Describe the indications on the PFD when in normal, alternate, & direct law as well as backup flight control.
BACKUP FLIGHT CONTROL
If a loss of control of both elevators is detected,
- a red ______ ______ ______ ______ message is displayed on the PFD.
- This is a warning that the ________ is the only flight control surface available for pitch control.
VOL. II, 27.3.8.2
FLTCTR_03
Describe the indications on the PFD when in normal, alternate, & direct law as well as backup flight control.
BACKUP FLIGHT CONTROL
If a loss of control of both elevators is detected,
- a red MAN PITCH TRIM ONLY message is displayed on the PFD.
- This is a warning that the THS is the only flight control surface available for pitch control.
VOL. II, 27.3.8.2
FLTCTR_04
Describe the flight characteristics provided in normal law.
Normal law is the flight control law in use during normal conditions when all, or nearly all aircraft systems are operational.
Normal law provides the ________
- level of ________
- flight ________ protection,
- and ________ enhanced handling characteristics, including automatic ______ ______
- The ________ is almost always available in normal law.
VOL. II, 27.3.1.2
FLTCTR_04
Describe the flight characteristics provided in normal law.
Normal law is the flight control law in use during normal conditions when all, or nearly all aircraft systems are operational.
Normal law provides the highest
- level of automation,
- flight envelope protection,
- and computer enhanced handling characteristics, including automatic pitch trim.
- The autopilot is almost always available in normal law.
VOL. II, 27.3.1.2
FLTCTR_04
Describe the flight characteristics provided in normal law.
Pitch Control
In flight, pitch is controlled by demanding changes in __ ______ (______ ______ demand).
- Normal law provides automatic ________ trimming and flight ________ protections.
- Forward or aft sidestick displacement controls pitch by demanding a change in ___ ______.
- The___ ______ demanded determines the rate of pitch change.
- Returning the sidestick to neutral ________ the current pitch attitude.
VOL. II, 27.3.2.1
FLTCTR_04
Describe the flight characteristics provided in normal law.
Pitch Control
In flight, pitch is controlled by demanding changes in g load (load factor demand).
- Normal law provides automatic pitch trimming and flight envelope protections.
- Forward or aft sidestick displacement controls pitch by demanding a change in g load.
- The g load demanded determines the rate of pitch change.
- Returning the sidestick to neutral maintains the current pitch attitude.
VOL. II, 27.3.2.1
Pitch Control
Pitch demands are routed to the flight control computers, which then command elevator ________ movement.
At the same time, commands are also sent to the ________ to begin trim movement.
- The ______ automatically trims until the elevators are ________ behind the THS.
- Traditional aircraft are trimmed to maintain a speed; therefore, if thrust is changed the aircraft changes pitch to stay close to the trimmed speed.
- However, the A-330 maintains its current pitch even if ______or ______ is changed.
- For bank angles up to ____°, normal changes in g load during turns are compensated for ________.
- Beyond ____°, _____ sidestick must be held in order to maintain altitude.
VOL. II, 27.3.2.1
FLTCTR_04
Describe the flight characteristics provided in normal law.
Pitch Control
Pitch demands are routed to the flight control computers, which then command elevator servo movement.
At the same time, commands are also sent to the THS to begin trim movement.
- The THS automatically trims until the elevators are streamlined behind the THS.
- Traditional aircraft are trimmed to maintain a speed; therefore, if thrust is changed the aircraft changes pitch to stay close to the trimmed speed.
- However, the A-330 maintains its current pitch even if thrust or speed is changed.
- For bank angles up to 33°, normal changes in g load during turns are compensated for automatically.
- Beyond 33°, aft sidestick must be held in order to maintain altitude.
VOL. II, 27.3.2.1
FLTCTR_04
Describe the flight characteristics provided in normal law.
Roll Control
In normal law, roll control is roll rate ________.
- Left and right sidestick displacement demands a roll rate ________ to the sidestick displacement, ________ of speed, with a maximum value of [___°_]/ second.
- When the sidestick is neutral, a zero roll rate is commanded and the current bank angle (up to ____°) is maintained.
- At bank angles greater than ____°, normal law has ______ ______ stability and sidestick deflection must be held to maintain bank angles greater than ____°.
- If the bank angle is greater than ____°, releasing the sidestick to neutral will result in the bank angle reducing to ____°.
VOL. II, 27.3.2.2
FLTCTR_04
Describe the flight characteristics provided in normal law.
Roll Control
In normal law, roll control is roll rate demand.
- Left and right sidestick displacement demands a roll rate proportional to the sidestick displacement, independent of speed, with a maximum value of [15°]/ second.
- When the sidestick is neutral, a zero roll rate is commanded and the current bank angle (up to 33°) is maintained.
- At bank angles greater than 33°, normal law has positive spiral stability and sidestick deflection must be held to maintain bank angles greater than 33°.
- If the bank angle is greater than 33°, releasing the sidestick to neutral will result in the bank angle reducing to 33°.
VOL. II, 27.3.2.2
FLTCTR_04
Describe the flight characteristics provided in normal law.
Yaw Control
In normal law ________ turn coordination and ______ ______ are provided.
When an autopilot is on, ________ trim is automatic.
________rudder trim and the trim ________ pb are inhibited.
VOL. II, 27.3.2.3
FLTCTR_04
Describe the flight characteristics provided in normal law.
Yaw Control
In normal law full turn coordination and yaw damping are provided.
When an autopilot is on, rudder trim is automatic.
manual rudder trim and the trim RESET pb are inhibited.
VOL. II, 27.3.2.3
FLTCTR_04
Describe the flight characteristics provided in normal law.
Ground Mode
Ground mode is active when the aircraft is sensed on the ground. In ground mode:
- The sidestick commands control surface deflection (elevators, ailerons, spoilers) directly ________ to sidestick deflection.
- Maximum elevator, aileron, and spoiler deflection is limited depending on aircraft ________.
- Pitch trim is automatically set to _______ units up after landing.
VOL. II, 27.3.3.2 Ground Mode
FLTCTR_04
Describe the flight characteristics provided in normal law.
Ground Mode
Ground mode is active when the aircraft is sensed on the ground. In ground mode:
- The sidestick commands control surface deflection (elevators, ailerons, spoilers) directly proportional to sidestick deflection.
- Maximum elevator, aileron, and spoiler deflection is limited depending on aircraft speed.
- Pitch trim is automatically set to 4 units up after landing.
VOL. II, 27.3.3.2 Ground Mode
FLTCTR_04
Describe the flight characteristics provided in normal law.
Flight Mode
Flight mode is progressively blended in over a period of [____] seconds after takeoff.
Flight mode provides the ________ law pitch, roll, and yaw characteristics previously discussed.
VOL. II, 27.3.3.3 Flight Mode
FLTCTR_04
Describe the flight characteristics provided in normal law.
Flight Mode
Flight mode is progressively blended in over a period of [5] seconds after takeoff.
Flight mode provides the normal law pitch, roll, and yaw characteristics previously discussed.
VOL. II, 27.3.3.3 Flight Mode
FLTCTR_04
Describe the flight characteristics provided in normal law.
Landing Mode
Landing mode gives the flare and touchdown a ________ feel.
- It becomes active when descending below _____ feet RA, and only affects ________ handling characteristics.
- In landing mode, the sidestick commands a ________ sidestick to elevator relationship.
- Additionally, at _____ feet RA a slight pitch down elevator input is applied so that an _____ stick movement is required to maintain the same pitch.
- If both radio altimeters fail, landing mode becomes active when the landing gear is down and both autopilots are disconnected. (not LOD)
- Shortly after touchdown the flight controls transition to ________ mode.
VOL. II, 27.3.3.4 Landing Mode
FLTCTR_04
Describe the flight characteristics provided in normal law.
Landing Mode
Landing mode gives the flare and touchdown a conventional feel.
- It becomes active when descending below 100 feet RA, and only affects pitch handling characteristics.
- In landing mode, the sidestick commands a direct sidestick to elevator relationship.
- Additionally, at 50 feet RA a slight pitch down elevator input is applied so that an aft stick movement is required to maintain the same pitch.
- If both radio altimeters fail, landing mode becomes active when the landing gear is down and both autopilots are disconnected. (not LOD)
- Shortly after touchdown the flight controls transition to ground mode.
VOL. II, 27.3.3.4 Landing Mode
FLTCTR_05
Describe the protections provided in normal law.
Pitch Attitude Protection
Pitch attitude protection prevents excessive aircraft ________.
These attitude limits are displayed on the PFDs as green equal signs at
- ___° nose up
- and ___° nose down.
- If a limit is reached, further sidestick displacement in that direction produces ___ ______.
VOL. II, 27.3.4.2
FLTCTR_05
Describe the protections provided in normal law.
Pitch Attitude Protection
Pitch attitude protection prevents excessive aircraft pitch.
These attitude limits are displayed on the PFDs as green equal signs at
- 30° nose up
- and 15° nose down.
- If a limit is reached, further sidestick displacement in that direction produces no effect.
VOL. II, 27.3.4.2
FLTCTR_05
Describe the protections provided in normal law.
High Speed Protection
- High speed protection prevents aircraft ________ due to excessive speed.
- High speed protection activates ______ ______ VMO/MMO, at the speed depicted by a ______ ______ sign.
VOL. II, 27.3.4.2
FLTCTR_05
Describe the protections provided in normal law.
High Speed Protection
- High speed protection prevents aircraft damage due to excessive speed.
- High speed protection activates slightly above VMO/MMO, at the speed depicted by a green equal sign.
VOL. II, 27.3.4.2
FLTCTR_05
Describe the protections provided in normal law.
High Speed Protection
When high speed protection activates:
- The autopilot(s) ________.
- Nose down pitch trim is ________.
- The flight control computers attempt to limit further acceleration by commanding a gentle ______ ____.
- This protection limits maximum airspeed by automatically________ the aircraft’s pitch attitude even if the sidestick is held full _______._
- The bank angle limit is reduced from 67° to ____°_ (limit marks do not move).
-
______ ______ stability becomes active at all bank angles (instead of the usual ____° in normal law).
- Therefore, the sidestick must be ________ to maintain any bank angle.
- If the sidestick is released the aircraft returns to a bank angle of _____°.
- The ________ and ______ ______ lights activate and an __/______ (________) warning is displayed on the E/WD.
- The ________ can only be silenced by slowing down or pushing the ______ ______ pb.
High speed protection is deactivated when the aircraft decreases below _______/______._
VOL. II, 27.3.4.4
FLTCTR_05
Describe the protections provided in normal law.
High Speed Protection
When high speed protection activates:
- The autopilot(s) disconnect.
- Nose down pitch trim is inhibited.
- The flight control computers attempt to limit further acceleration by commanding a gentle pitch up.
- This protection limits maximum airspeed by automatically increasing the aircraft’s pitch attitude even if the sidestick is held full forward.
- The bank angle limit is reduced from 67° to 45° (limit marks do not move).
-
Positive spiral stability becomes active at all bank angles (instead of the usual 33° in normal law).
- Therefore, the sidestick must be held to maintain any bank angle.
- If the sidestick is released the aircraft returns to a bank angle of 0°.
- The CRC and MASTER WARN lights activate and an O/SPEED (overspeed) warning is displayed on the E/WD.
- The CRC can only be silenced by slowing down or pushing the EMER CANC pb.
High speed protection is deactivated when the aircraft decreases below VMO/MMO.
VOL. II, 27.3.4.4
FLTCTR_05
Describe the protections provided in normal law.
Alpha Protection
Alpha protection limits the aircraft’s ______ of ______ (alpha).
- This allows the pilot to safely command a ________ angle of attack for critical maneuvers such as windshear recovery and GPWS “pull up” maneuvers without the danger of ________ the aircraft.
- The range where alpha protection is active is displayed on the airspeed indicator as a ______ and ______ band.
- The top of the band is referred to as ______ ______ (______ ______),
- and the base of the band as _______ _______ (_______ _______).
Alpha max is an angle of attack slightly _______ _______ the stall angle of attack.
- At alpha max, the aircraft will not ________ but will have nearly the ________ allowable lift for the current ________ and ________
If the angle of attack exceeds alpha prot:
- the _______(s)_ disconnect,
- the speedbrakes ________ (the handle does not move),
- and the sidestick control switches from __- ______ demand to ______ of ______ demand.
Between alpha prot and alpha max, sidestick pitch displacement ______ and ______ commands angle of attack.
- If the sidestick is held full aft, the aircraft will vary pitch to maintain ______ ______.
- If the sidestick is released to neutral the aircraft will vary pitch to maintain ______ ______.
- Sidestick movement ________ of neutral is required to leave alpha protection mode and return back to the normal g load demand mode.
VOL. II, 27.3.4.5 Alpha Protection
FLTCTR_05
Describe the protections provided in normal law.
Alpha Protection
Alpha protection limits the aircraft’s angle of attack (alpha).
- This allows the pilot to safely command a maximum angle of attack for critical maneuvers such as windshear recovery and GPWS “pull up” maneuvers without the danger of stalling the aircraft.
- The range where alpha protection is active is displayed on the airspeed indicator as a black and amber band.
- The top of the band is referred to as alpha prot (alpha protection),
- and the base of the band as alpha max (alpha maximum).
Alpha max is an angle of attack slightly less than the stall angle of attack.
- At alpha max, the aircraft will not stall but will have nearly the maximum allowable lift for the current weight and configuration.
If the angle of attack exceeds alpha prot:
- the autopilot(s) disconnect,
- the speedbrakes retract (the handle does not move),
- and the sidestick control switches from g load demand to angle of attack demand.
Between alpha prot and alpha max, sidestick pitch displacement directly and proportionally commands angle of attack.
- If the sidestick is held full aft, the aircraft will vary pitch to maintain alpha max.
- If the sidestick is released to neutral the aircraft will vary pitch to maintain alpha prot.
- Sidestick movement forward of neutral is required to leave alpha protection mode and return back to the normal g load demand mode.
VOL. II, 27.3.4.5 Alpha Protection
FLTCTR_05
Describe the protections provided in normal law.
Bank Angle Protection
- Bank angle protection prevents pilot or autopilot demands from producing _________ bank angles.
- Bank angle protection limits bank angles to____°_ or less.
VOL. II, 27.3.4.7
FLTCTR_05
Describe the protections provided in normal law.
Bank Angle Protection
- Bank angle protection prevents pilot or autopilot demands from producing excessive bank angles.
- Bank angle protection limits bank angles to 67° or less.
VOL. II, 27.3.4.7
FLTCTR_05
Describe the protections provided in normal law.
Low Energy Warning
Normal law also provides an aural low energy warning of “______ ______ ______.”
- The warning is repeated every [______] seconds and indicates that the aircraft’s energy state would require additional thrust to attain a ______ ______ of ______.
- The PRIMs (FLIGHT CONTROL PRIMARY COMPUTER) compute the low energy warning according to the aircraft ______, ______ ______ rate, and______ ______angle.
- The warning is normally generated before ______ ______ activates.
- However, in some cases of ________ aft sidestick movement, alpha floor may activate without first triggering the low energy warning.
VOL. II, 27.3.4.8
FLTCTR_05
Describe the protections provided in normal law.
Low Energy Warning
Normal law also provides an aural low energy warning of “SPEED SPEED SPEED.”
- The warning is repeated every [5] seconds and indicates that the aircraft’s energy state would require additional thrust to attain a positive rate of climb.
- The PRIMs (FLIGHT CONTROL PRIMARY COMPUTER) compute the low energy warning according to the aircraft configuration, speed deceleration rate, and flight path angle.
- The warning is normally generated before alpha floor activates.
- However, in some cases of rapid aft sidestick movement, alpha floor may activate without first triggering the low energy warning.
VOL. II, 27.3.4.8
FLTCTR_06
Describe the flight characteristics provided in ALTERNATE LAW.
Alternate law is the flight control law in use following ________ or combinations of ________ that do not permit the ______ ______ ______ to maintain normal law.
Alternate law provides reduced:
- ______________,
- ______________,
- and ________ characteristics.
Depending on the degree of failure, the ________ may or may not be available.
VOL. II, 27.3.5.1
FLTCTR_06
Describe the flight characteristics provided in alternate law.
Alternate law is the flight control law in use following failures or combinations of failures that do not permit the flight control computers to maintain normal law.
Alternate law provides reduced:
- automation,
- protections,
- and handling characteristics.
Depending on the degree of failure, the autopilot may or may not be available.
VOL. II, 27.3.5.1
FLTCTR_06
Describe the flight characteristics provided in alternate law.
Pitch Control
Alternate law pitch control is similar to normal law.
Alternate law has:
- ________ protection,
- ________ pitch trim,
- and______ and ______ modes identical to normal law.
Low and High speed stabilities replace
- ______ speed protection
- ______ protection,
- ______ attitude protection,
VOL. II, 27.3.5.3
FLTCTR_06
Describe the flight characteristics provided in alternate law.
Pitch Control
Alternate law pitch control is similar to normal law.
Alternate law has:
- maneuver protection,
- automatic pitch trim,
- and ground and landing modes identical to normal law.
low and high speed stabilities replace
- HIGH speed protection
- ALPHA protection,
- PITCH attitude protection,
VOL. II, 27.3.5.3
FLTCTR_06
Describe the flight characteristics provided in alternate law.
Low Speed Stability
In alternate law, low speed stability replaces ______ ______ and is activated by ________ instead of ______ of ______.
- At [_\_- __] knots above stall speed, a ______ ______ command is produced to avoid a further decrease in airspeed.
- Low speed stability can be ________ by the pilot.
- If sufficient aft sidestick is applied, the aircraft can be ________.
If a stall is approached,
- audio stall warning “________”
- and a synthesized voice “______ ______” are activated.
VOL. II, 27.3.5.3
FLTCTR_06
Describe the flight characteristics provided in alternate law.
Low Speed Stability
In alternate law, low speed stability replaces alpha protection and is activated by speed instead of angle of attack.
- At [5-10] knots above stall speed, a nose down command is produced to avoid a further decrease in airspeed.
- Low speed stability can be overridden by the pilot.
- If sufficient aft sidestick is applied, the aircraft can be stalled.
If a stall is approached,
- audio stall warning “crickets”
- and a synthesized voice “STALL STALL” are activated.
VOL. II, 27.3.5.3
FLTCTR_06
Describe the flight characteristics provided in alternate law.
Yaw Control
When roll alternate law ALT 1 is in effect, yaw control is identical to______ law.
- Turn coordination and yaw damping are ________
When roll alternate law ALT 2 is in effect:
- ______ ______ is lost when slats and flaps are up.
- Pilot rudder application is ________ for turn coordination.
- Yaw damping remains ________.
VOL. II, 27.3.5.5
FLTCTR_06
Describe the flight characteristics provided in alternate law.
Yaw Control
When roll alternate law ALT 1 is in effect, yaw control is identical to normal law.
- Turn coordination and yaw damping are functional.
When roll alternate law ALT 2 is in effect:
- turn coordination is lost when slats and flaps are up.
- Pilot rudder application is required for turn coordination.
- Yaw damping remains functional.
VOL. II, 27.3.5.5
FLTCTR_07
Describe the flight characteristics and protections provided in direct law.
- Automatic ______ ______ is inoperative
- ________ must be trimmed manually using the pitch trim wheels.
- ______ and ______ warnings are still available.
- If direct law is active, an amber ______ ______ ______ ______ message is displayed on the PFD.
- This is a reminder of the loss of automatic pitch trim.
VOL. II, 27.3.6.1
FLTCTR_07
Describe the flight characteristics and protections provided in direct law.
- Automatic pitch trim is inoperative
- THS must be trimmed manually using the pitch trim wheels.
- Overspeed and stall warnings are still available.
- If direct law is active, an amber USE MAN PITCH TRIM message is displayed on the PFD. This is a reminder of the loss of automatic pitch trim.
VOL. II, 27.3.6.1
FLTCTR_08
Describe the flight characteristics provided in Backup flight control.
Backup flight control allows control of the aircraft during a
- complete loss of ________ power or all ______ ______ ______.
Pitch
In backup control,
- sidestick pitch demands are ____________
- Pitch is controlled using the pitch ______ ______ through a______ connection to the THS hydraulic ________.
27.3.8.2 Indications not LOD
If a loss of control of both elevators is detected:
- a red MAN PITCH TRIM ONLY message is displayed on the PFD.
- This is a warning that the THS is the only flight control surface available for pitch control.
VOL. II, 27.3.8.1
VOL. II, 27.3.8.3
FLTCTR_08
Describe the flight characteristics provided in backup flight control.
Backup flight control allows control of the aircraft during a
- complete loss of electrical power or all flight control computers.
Pitch
In backup control,
- sidestick pitch demands are inoperative.
- Pitch is controlled using the pitch trim wheels through a mechanical connection to the THS hydraulic jackscrew.
27.3.8.2 Indications not LOD
If a loss of control of both elevators is detected:
- a red MAN PITCH TRIM ONLY message is displayed on the PFD.
- This is a warning that the THS is the only flight control surface available for pitch control.
VOL. II, 27.3.8.1
VOL. II, 27.3.8.3
FLTCTR_08
Describe the flight characteristics provided in backup flight control.
Yaw & Roll
In almost all cases, if ______ ______ ______ ______ is displayed on the PFD:
- sidestick roll control is ________.
- However, in some limited scenarios, sidestick roll control may be possible (e.g., only _______ 3_ operational).
If sidestick roll control is not possible:
- yaw and roll are controlled using the ______ ______.
- Rudder demands are sent to the ______ ______ module which commands the rudder’s hydraulic ________.
- When the g load increases due to bank the pilot must add ______ ___ _____ control to hold altitude.
Note: Asymmetric or differential engine thrust changes can result in significant yaw/roll rates.
VOL. II, 27.3.8.4
FLTCTR_08
Describe the flight characteristics provided in backup flight control.
Yaw & Roll
In almost all cases, if MAN PITCH TRIM ONLY is displayed on the PFD:
- sidestick roll control is inoperative.
- However, in some limited scenarios, sidestick roll control may be possible (e.g., only PRIM 3 operational).
If sidestick roll control is not possible:
- yaw and roll are controlled using the rudder pedals.
- Rudder demands are sent to the backup control module which commands the rudder’s hydraulic servos.
- When the g load increases due to bank the pilot must add nose up pitch control to hold altitude.
Note: Asymmetric or differential engine thrust changes can result in significant yaw/roll rates.
VOL. II, 27.3.8.4
FLTCTR_9
Discuss the flap and slat protections.
Flap Load Relief System (FLRS) (2, 3, and FULL)
- The Flap Load Relief System (FLRS) is an automatic protection that moves the flaps to one position ________ than the selected configuration.
- The FLRS is only available with selected positions of __, __ and ______.
- Slat position is not affected.
- When the FLRS is activated, the F on the flap position indicator is replaced by __ ______ pulsing in ________.
VOL. II, 27.2.12.7
FLTCTR_9
Discuss the flap and slat protections.
Flap Load Relief System (FLRS) (2, 3, and FULL)
- The Flap Load Relief System (FLRS) is an automatic protection that moves the flaps to one position less than the selected configuration.
- The FLRS is only available with selected positions of 2, 3 and FULL.
- Slat position is not affected.
- When the FLRS is activated, the F on the flap position indicator is replaced by F RELIEF pulsing in green.
VOL. II, 27.2.12.7
FLTCTR_9
Discuss the flap and slat protections. Flap Load Relief System (FLRS) (2, 3, and FULL)
Slats Alpha/Speed Lock
The Slat Alpha/Speed lock function inhibits slat retraction at ______ ______of ______ (______) and/or ________ speed.
If the flaps lever is selected to ______ when in excess of a certain angle of attack or below a certain speed:
- the ________ remain at position 1.
When the angle of attack is no longer excessive and speed exceeds a certain speed:
- the ________ will automatically retract to 0 as previously selected.
VOL. II, 27.2.12.9
FLTCTR_9
Discuss the flap and slat protections. Flap Load Relief System (FLRS) (2, 3, and FULL)
Slats Alpha/Speed Lock
The Slat Alpha/Speed lock function inhibits slat retraction at high angles of attack (alpha) and/or low speed.
If the flaps lever is selected to 0 when in excess of a certain angle of attack or below a certain speed:
- the slats remain at position 1.
When the angle of attack is no longer excessive and speed exceeds a certain speed:
- the slats will automatically retract to 0 as previously selected.
VOL. II, 27.2.12.9
FLTCTR_9
Discuss the flap and slat protections. Flap Load Relief System (FLRS) (2, 3, and FULL)
Slats Alpha/Speed Lock
When activated, the S on the slat position indicator is replaced by _ ______ pulsing in green.
This function only inhibits retraction if
- the excessive ______
- or ____ airspeed values are already present at selection of CONF 0.
- It does not automatically extend the ______.
VOL. II, 27.2.12.9
FLTCTR_9
Discuss the flap and slat protections. Flap Load Relief System (FLRS) (2, 3, and FULL)
Slats Alpha/Speed Lock
When activated, the S on the slat position indicator is replaced by A LOCK pulsing in green.
This function only inhibits retraction if
- the excessive alpha
- or low airspeed values are already present at selection of CONF 0.
- It does not automatically extend the slats.
VOL. II, 27.2.12.9
FLTCTR_11
Describe the sidestick priority design logic.
When a takeover pb is pushed:
- A synthesized voice states “PRIORITY LEFT” or “PRIORITY RIGHT”, as appropriate.
- A ________ arrow, pointing towards the pilot with control, is illuminated in front of the pilot ________ control.
- The red arrow indicates that the sidestick is currently ________
- A green CAPT or F/O light illuminates in front of the pilot in ________ if the deactivated sidestick is not sensed in neutral.
Both green CAPT and F/O lights will ________ when both sidesticks are displaced from the neutral position.
- Additionally, on some aircraft, a synthesized voice stating “______ ______” will be announced.
VOL. II, 27.2.3.3-4
FLTCTR_11
Describe the sidestick priority design logic.
When a takeover pb is pushed:
- A synthesized voice states “PRIORITY LEFT” or “PRIORITY RIGHT”, as appropriate.
- A red arrow, pointing towards the pilot with control, is illuminated in front of the pilot losing control.
- The red arrow indicates that the sidestick is currently deactivated.
- A green CAPT or F/O light illuminates in front of the pilot in control if the deactivated sidestick is not sensed in neutral.
Both green CAPT and F/O lights will flash when both sidesticks are displaced from the neutral position.
- Additionally, on some aircraft, a synthesized voice stating “Dual Inputs” will be announced.
VOL. II, 27.2.3.3-4
FLTCTR_13
Discuss trim capabilities for all three axes.
Pitch Trim
- In flight, pitch trim is normally ________.
- Manual control of the THS is available at any time (provided ______ or ____ system pressure is available) by using the pitch ______ ______.
- Shortly after landing the PRIMs automatically set the THS to ___° UP_.
VOL. II, 27.2.6.3-5
FLTCTR_13
Discuss trim capabilities for all three axes.
Pitch Trim
- In flight, pitch trim is normally automatic.
- Manual control of the THS is available at any time (provided blue or yellow system pressure is available) by using the pitch trim wheels.
- Shortly after landing the PRIMs automatically set the THS to 4° UP.
VOL. II, 27.2.6.3-5
FLTCTR_13
Discuss trim capabilities for all three axes.
Rudder Trim
Rudder trim is achieved by repositioning a______ spring.
- Two trim motors commanded by the _______s_ (S______ ______ ______) position the centering spring to provide rudder trim. The spring also provides ________ feel.
- There is no feedback to the rudder pedals from ______ ______ and ________ coordination.
- In manual flight (autopilot off) the trim is adjusted with the ______ ______ knob on the center pedestal.
- Rudder trim may be reset to zero by momentarily pushing the ________ pb next to the trim knob.
VOL. II, 27.2.8.2
FLTCTR_13
Discuss trim capabilities for all three axes.
Rudder Trim
Rudder trim is achieved by repositioning a centering spring.
- Two trim motors commanded by the SECs (_Spoiler Elevator Computer_) position the centering spring to provide rudder trim. The spring also provides artificial feel.
- There is no feedback to the rudder pedals from yaw damping and turn coordination.
- In manual flight (autopilot off) the trim is adjusted with the RUD TRIM knob on the center pedestal.
- Rudder trim may be reset to zero by momentarily pushing the RESET pb next to the trim knob.
VOL. II, 27.2.8.2
FLTCTR_13
Discuss trim capabilities for all three axes.
Rudder Trim
When an autopilot is on:
- the trim knob and RESET button are ________
- and the FMGEC (FLIGHT MANAGEMENT GUIDANCE ENVELOPE COMPUTER) computes the ____ ____ orders.
- ________ pedal inputs can override autopilot inputs and ________ the autopilot(s).
Rudder trim position is displayed on the indicator next to the ______ ______ knob. Trim is indicated in degrees left or right. Dashes are displayed for ________ data or a failure of ______-__ test.
VOL. II, 27.2.8.2
FLTCTR_13
Discuss trim capabilities for all three axes.
Rudder Trim
When an autopilot is on:
- the trim knob and RESET button are deactivated
- and the FMGEC (FLIGHT MANAGEMENT GUIDANCE ENVELOPE COMPUTER) computes the rudder trim orders.
- Manual pedal inputs can override autopilot inputs and disconnect the autopilot(s).
Rudder trim position is displayed on the indicator next to the RUD TRIM knob. Trim is indicated in degrees left or right. Dashes are displayed for invalid data or a failure of power-up test.
VOL. II, 27.2.8.2
