Oral Questions Flashcards
CALLS PANEL
What happens when a pilot presses and holds the MECH pb on the CALLS panel?
It illuminates a blue light on the EXT PWR PANEL (in the nose L/G bay) and sounds an external horn
(AOM Vol 1 23.20.21)
CALLS PANEL
How should a pilot call the forward flight attendant?
Press the FWD button on the Calls Panel
CALLS PANEL
When would a pilot push the EMER pushbutton on the CALLS panel?
When there is an emergency and the Pilot would like to speak with the Flight Attendant A
OXYGEN Panel
What happens when a pilot pushes the CREW SUPPLY PUSHBUTTON?
Valve opens to supply low pressure oxygen to the masks
OXYGEN Panel
How does the passenger fixed oxygen system work and how long does it last?
Chemical oxygen generators last for approximately 15 minutes
OXYGEN Panel
What does the illumination of the SYS ON light mean? Does this mean that all the masks have deployed?
The signal has been sent to release the oxygen mask doors, but some masks may have to be deployed manually.
OXYGEN Panel
What causes automatic deployment of the masks?
Cabin altitude reaching approximately 14,000 feet
OXYGEN Panel
How is the crew oxygen mask microphone deactivated when the mask is stowed?
The RESET control slide with accomplish this - it does not happen automatically
OXYGEN Panel
What indication would a pilot have of a crew oxygen cylinder thermal discharge?
The green disk on the lower left side of the forward fuselage would be missing
OXYGEN Panel
Could the passenger oxygen mask provide oxygen for anything other than depressurization?
No
OXYGEN Panel
On the ground, if there is an amber half frame around the CKPT OXY PSI box, where would you look to see if you have enough oxygen for the flight?
COM Book 1 Performance - Limitations - Oxygen
INDICATING/RECORDING Systems
Why is the GND CTL pushbutton selected to ON during the preflight?
To record preflight activities in the cockpit
INDICATING/RECORDING Systems
If the GND CTL pushbutton was not selected ON, how would the system work in automatic mode?
On the ground:
- during the first 5 minutes after the aircraft electrical network is energized
- after the first engine start
- it is stopped automatically 5 minutes after the last engine shutdown provided the CVR jack is not used
In flight (whether the engines are running or not)
INDICATING/RECORDING Systems
What allows the cabin PAs to be recorded?
ACP 3 PA volume knob out and set at or above the medium range
GPWS Panel
What does pressing the SYS pushbutton do?
All basic GPWS alerts (mode 1 to 5) are inhibited
GPWS Panel
What does an amber FAULT light in the SYS pushbutton indicate on the GPWS panel?
Any failure of the GPWS mode 1 through 5
(AOM Vol 1 34.70.12)
GPWS Panel
What effect, if any, does an amber FAULT light in the SYS pushbutton have on the TERR mode
No effect at all
GPWS Panel
Describe a situation when a pilot might press LDG FLAP 3
What would LDG MEMO display?
To avoid nuisance warning in case of landing in CONF 3
- In this case, LDG MEMO displays FLAPS…CONF 3 instead of CONF FULL
GPWS Panel
Describe a situation when a pilot might press the FLAP MODE pushbutton
- To avoid a nuisance warning in case of landing with flaps setting reduced
- FLAP SYS 1 (2) FAULT would require the selector of FLAP MODE off
GPWS Panel
What effect, if any, does the failure of TERR mode have on basic GPWS?
No effect whatsoever
EMER ELEC PWR Panel
What is the significance of the red FAULT illuminating on the RAT & EMER GEN light?
AC BUS1 and AC BUS2 are lost and the emergency generator is not supplying electrical power
EMER ELEC PWR Panel
When would the red FAULT light on the RAT & EMER GEN light normally illuminate?
The fault light will illuminate once the RAT is deployed and electrical power is not being supplied (approx. 8 seconds)
EMER ELEC PWR Panel
How can the RAT be deployed?
- Manually by pushing MAN ON (EMER ELEC PWR panel) or RAT MAN ON (HYDRAULIC Panel)
- Automatically by the loss of both AC BUS 1 and AC BUS 2
EMER ELEC PWR Panel
What is the difference between the automatic RAT deployment and manual RAT deployment by pressing the RAT MAN ON on the HYD panel?
RAT MAN ON supplies Blue Hydraulic pressure only, no electrical generation
EMER ELEC PWR Panel
After deploying the RAT by pressing the RAT MAN ON pushbutton on the HYD panel it becomes necessary to also extract electrical power. How can this be accomplished?
By pressing the MAN ON pushbutton on the EMER ELEC PWR
EMER ELEC PWR Panel
What does the RAT supply?
Blue Hydraulic System pressure and the emergency electrical generator
EMER ELEC PWR Panel
What would cause the GEN 1 LINE SMOKE light to illuminate?
Smoke detectors (particle detectors) in the avionics ventilation ducting
EMER ELEC PWR Panel
Aside from GEN 1 LINE SMOKE light, what would be other indications of avionics smoke?
- ECAM warning
- Amber FAULT lights in the EXTRACT and BLOWER pushbuttons on the VENTILATION panel
EMER ELEC PWR Panel
If the ECAM directs the pilot to select GEN 1 LINE pb sw to OFF, what will be accomplished?
- Gen 1 line contactor opens (white OFF light illuminates)
- AC BUS 1 powered by GEN 2 through the Bus Tie Contactors
- Gen 1 powers one fuel pump directly in each wing tank
EVAC Panel
Why do we select the CAPT position using the CAPT/PURS sw?
What would happen in cockpit if cabin CMD pushbutton is pressed?
- The alert may only be activated from the cockpit
- If one of the cabin CMD pushbuttons is pressed, on the cockpit horn sounds for 3 seconds
EVAC Panel
While conducting the Emergency Evacuation Checklist, the pilots determine that evacuation is required. How should the pilots command the evacuation?
- Make a PA announcement
- Press the EVAC COMMAND pushbutton
Flight Controls & Flight Control Laws
What type of flight control system does the A320 family aircraft utilize?
Fly-By-Wire system
Flight Controls & Flight Control Laws
Describe how the flight controls are controlled and activated?
Electrically controlled and Hydraulically Activated
Flight Controls & Flight Control Laws
How is NORMAL LAW indicated on the PFD?
Green “=” for pitch, bank, and overspeed limits
Amber/black (ALPHA PROT) airspeed tape
Flight Controls & Flight Control Laws
How is ALTERNATE LAW indicated on the PFD?
Amber Xs (indicating lack of NORMAL LAW protections)
Flight Controls & Flight Control Laws
How is DIRECT LAW indicated on the PFD?
- Amber “USE MANUAL PITCH TRIM”
- Amber Xs (indicating lack of NORMAL LAW protections)
Flight Controls & Flight Control Laws
How is MECHANICAL BACKUP indicated on the PFD?
- Red “MAN PITCH TRIM ONLY”
- Amber Xs (indicating lack of NORMAL LAW protections)
Flight Controls & Flight Control Laws
When operating in NORMAL LAW in flight mode, what does the side stick command for pitch and roll?
Pitch ….. G load
Bank ….. Roll rate
Flight Controls & Flight Control Laws
What is the significance of the Side Stick Priority (Red Arrow) Light?
The other pilot has gained side stick authority
Flight Controls & Flight Control Laws
Name the Flight Control Computers and the number of each
ELAC - Elevator Aileron Computer (2)
SEC - Spoiler Elevator Computer (3)
FAC - Flight Augmentation Computer (2)
Flight Controls & Flight Control Laws
What does SEC 3 control?
Spoiler Control - one flight spoiler and one ground spoiler on each wing
- controls #2 Spoiler in each wing (used for roll control, speed brakes and ground spoilers)
Flight Controls & Flight Control Laws
What should happen to the THS after landing?
Reset to zero
Flight Controls & Flight Control Laws
Describe some of the protections a pilot will have in NORMAL LAW?
- High Speed
- High Angle of Attack (AOA) Protection
- Load Factor Limitation +2.5G / -1.0G (+2.0G / 0.0G with Flaps/Slats)
- Pitch Attitude Protections (30° UP / 15° DOWN)
- Bank Angle Protection (67°)
Flight Controls & Flight Control Laws
Describe High Speed Protection
What happens if no sidestick input applied?
How does positive spiral static stability and bank angle limits change?
If VMO/MMO plus a predetermined factor is exceeded, the system induces a pitch-up to limit aircraft speed
If no sidestick input, the aircraft will slightly overshoot VMO/MMO and
Positive spiral static stability is introduced at 0º (instead of 33º in normal law), so that with sidestick released, the aircraft always returns to bank angle of 0º.
Bank angle limit is reduced from 67º to 40º
Flight Controls & Flight Control Laws
What, if anything, can a pilot do to override high-speed protection pitch up?
It is not possible to override a protection while still in NORMAL LAW. In this case, the aircraft would need to be forced into ALTERNATE LAW (by turning 2 ADRs off, for example).
Flight Controls & Flight Control Laws
What is ALPHA MAX?
How is it indicated?
The maximum angle of attack allowed in NORMAL LAW
indicated by the top of the red stripe on the airspeed scale.
Flight Controls & Flight Control Laws
How does the High Angle of Attack Protection operate?
When the angle of attack exceeds ALPHA PROT:
- nose up pitch trim ceases and
- angle of attack is now proportional to side stick deflection, not to exceed ALPHA MAX even with full aft side stick deflection
Flight Controls & Flight Control Laws
What protections and stabilities, if any, does a pilot have in ALTERNATE LAW?
- Load Factor
- High-speed stability
- Low speed stability
Flight Controls & Flight Control Laws
What protections, if any, does a pilot have in DIRECT LAW?
None
Flight Controls & Flight Control Laws
When, if at all, does flare mode activate in ALTERNATE LAW? Describe the whole process?
There is no flare mode if operating in ALTERNATE LAW. The aircraft proceeds directly from ALTERNATE LAW to DIRECT LAW when the gear is selected down, and flare mode will not be available.
Flight Controls & Flight Control Laws
If in ALTERNATE LAW, when will the aircraft revert to DIRECT LAW?
If the controls degrade to ALTERNATE LAW for any reason other than recovery from abnormal attitude, DIRECT LAW automatically becomes active with:
- gear extension and
- autopilots not engaged.
In this case, full use of autopilot is recommended until they must be disconnected.
Flight Controls & Flight Control Laws
When is there a direct relationship between side stick and flight control surface deflection?
- When in DIRECT LAW
- On the ground (Ground Mode)
Flight Controls & Flight Control Laws
It’s common Airbus philosophy that the Airbus *cannot* stall in NORMAL LAW. However, there are condition in which it can. Describe how this can happen.
- A good pilot will operate under the philosophy that anything can happen.
- Preventative systems such as ALPHA PROT, ALPHA MAX, etc, could interpret bad data as valid data and subsequently fail to recognize the actual AOA or flight path of the airplane
- Therefore, hard to pinpoint exact scenarios when Airbus can stall in NORMAL LAW, but we need to understand anything is possible and we should recognize stall indications and recover regardless of the active control law
Flight Controls & Flight Control Laws
How would the aircraft enter ABNORMAL ATTITUDE LAW?
What is the purpose of ABNORMAL ATTITUDE LAW?
By exceeding approximately double the NORMAL LAW limits.
Purpose is to allow the aircraft to be recovered from an unusual attitude
Flight Controls & Flight Control Laws
If the flight crew is flying at 300 knots and they happen to pull full back on the side stick, how high can they pitch up?
30° up
Flight Controls & Flight Control Laws
If the pilot selects 100 knots on the speed knob, how slow would the aircraft fly if the autopilot and auto thrust are engaged?
VLS
It is the lowest selectable speed for the autopilot and the autothrust. Even if the
selected target speed is below VLS, the A/THR will maintain VLS as a minimum. VLS
is indicated by the top of the amber strip on the PFD airspeed scale
Flight Controls & Flight Control Laws
Describe, in detail, what would happen if the pilot slowly pulled the thrust to idle in NORMAL LAW.
Continuing the scenario above, describe what would happen if the flight crew continued to pull back on the side stick. How slow would the aircraft go?
At some point, during this demonstration the AUTOTHRUST automatically applies TOGA power. What is this protection, and how does it work?
- As airspeed decays, the THS adjusts the pitch attitude to maintain altitude.
- If the AOA increases to a threshold value, known as ALPA PROT, the pitch function of the side stick changes. Stick movement commands a specific AOA instead of G load change
- Since nose up pitch trim ceases, the pilot must hold continuous back pressure in order to flow slower than the speed for ALPHA PROT
- The aircraft would go the speed corresponding to ALPHA MAX
- With the stick full aft, the elevators will adjust the pitch attitude to maina a maximum safe AOA (ALPHA MAX). This maximum AOA , induced by the pilot, is slightly lower than the stall AOA; therefore the aircraft theoretically cannot be stalled in NORMAL LAW
- ALPHA FLOOR is a function of AUTOTHRUST. It will activate at any airspeed based on AOA and automatically apply TOGA thrust regardless of thrust lever position.
- ALPHA FLOOR is available if: - the AUTOTHRUST is functional (it does not need to be active)
- an engine is running (not both), and
- the aircraft is in NORMAL LAW
- AOA protection does not depend on ALPHA FLOOR to function
- On NEO aircraft, ALPHA FLOOR is inhibited above M0.6
Flight Controls & Flight Control Laws
Describe what would happen if a flight crew attempted to overstress the aircraft while in NORMAL LAW.
What happens if G Loads become greater that normal?
What happens when side stick pushed forward
What happens to pitch when side stick returned to neutral?
- Maneuver protection prevents a pilot from over stressing the aircraft by limiting flight control inputs
- If G loads become greater than normal, they are displayed in amber on the lower ECAM above the digital clock (> 1.4g or less than .7g for > 2 sec - displays for 5 secs - AOM 1 p.727)
- When the side stick is pushed forward, less than 1G is commanded. A given pitch input always results in the same pitch response regardless of airspeed.
- When the stick is returned to neutral, the new pitch is held constant regardless of airspeed changes
Flight Controls & Flight Control Laws
What will happen if the pilot over speeds the aircraft? Are there any protections that are available to the pilots
How is the speed at which the protection activates shown on the the airspeed indicator?
What type of warning is generated? Can it be silenced?
How do bank protections change in high speed protection?
- An over speed causes the flight control computers to provide a nose up input to reduce aircraft damage due to excess speed. This protection limits the max airspeed by increasing the pitch attitude even if full forward stick is held
- The speed at which this protection activates is show on the airspeed indicator as a green “=” sign
- An overspeed warning is generated as VMO is exceeded (specifically at VMO +4). This warning can only be silenced by the EMER CANCEL pushbutton
- If the stick is released, the speed will return to VMO/MMO. The protection will allow a momentary increase in airspeed up to VMO+16/MMO+0.04 permit any necessary maneuvering but then the speed will again slow to the limit
- Positive spiral static stability is introduced to 0 degrees bank angle (instead of 33 deg in normal law) so that with the side stick released the aircraft always returns to bank angle of 0 degrees. The bank angle limit is reduced from 67 deg to 40.
- If high-speed protective is active, positive spiral stability occurs at all bank angles, and control pressure is required to hold any bank angle greater than zero.
- It is possible to over speed the aircraft. The computers merely limit the max attainable speed.
Flight Controls & Flight Control Laws
When a pilot rolls into a bank, what is provided by the Flight Control Laws?
What flight controls does sidestick command?
What is the roll rate at full deflection?
Up to what bank angle is pitch trim automatic?
What do you need to do to maintain bank angle above this?
What is positive spiral static stability
- In “flight” mode of NORMAL LAW, roll control is a roll rate demand.
- Side stick inputs command the
1. ailerons,
2. spoilers 2-5, and the
3. rudder to achieve the commanded roll rate with bank angle protection, turn coordination, and Dutch roll damping - The roll rate demanded by the pilot is proportional to side stick deflection. When the side stick is neutral the ailerons and spoilers are positioned to maintain the roll rate at 0° per second. This results in a constant bank angle.
- When the side stick is displaced laterally, increasing roll rates are commanded. At full deflection, a roll rate of 15° per second is commanded in NORMAL LAW. The ailerons and spoilers are positioned as necessary to achieve the commanded roll rate.
- The side stick position cannot be used as a reference to determine the actual positions of flight control surfaces
- In normal turns (up to 33°) pitch trim is automatic and assists the pilot in maintaining altitude
- If the bank is increased beyond 33° and the side stick is released, the aircraft would return to 33° of bank. This is known as positive spiral stability
- Positive spiral stability is a characteristic programmed into the flight control computers, which returns the aircraft to a more stable condition (0° if high speed or AOA protection is active)
- Beyond 33° of bank, positive spiral stability is active and automatic pitch trim is inhibited. To maintain a bank angle greater than 33°, continuous side stick pressure must be used. Also, continuous back pressure will be needed to maintain altitude since automatic pitch trim is inhibited
Flight Controls & Flight Control Laws
The pilots find themselves in ALTERNATE LAW. Describe the indications and available protections, and flight control logic.
- In most cases, a single system component failure will not cause a flight control degradation (jammed stabilizer causes a degradation).
Indications:
- Amber X’s and EW/D message
- ECAM states PROT LOST, but maneuver protection is still available
Available protections and flight control logic:
- Autopilot availability in ALTERNATE LAW depends on the failures that caused the degradation. Generally speaking, if the failures do not affect a primary flight control surface, the autopilot should be available
- Pitch is the same as NORMAL LAW
- Roll is direct (not roll rate demand) - instead of commanding a specific roll rate, there is a direct relationship between side stick position and control surface position. As a result, roll sensitivity now changes with aircraft speed and amount of side stick deflection. Depending on the failure combination, the maximum roll rate may be as much as twice what it was in NORMAL LAW.
- Bank angle protection is not available in ALTERNATE LAW. Roll commands are carried out directly without modification
- Yaw loses coordination
- Attitude, high speed, and AOA protections are lost. Replaced by high speed stability and low speed stability, respectively.
- High speed stability activates just prior to the over speed warning. Nose down trim is inhibited
- Low speed stability activates just prior to the stall warning. Nose up trim is inhibited.
- The pilot can override the stabilities and over speed or stall the aircraft
- Attitude protection is lost and the green “=” signs on the PFD are replaced with amber Xs. There are now no limits on how far a pilot can pitch or roll the aircraft. The aircraft can roll beyond the amber Xs. Positive spiral stability is also lost.
- In ALTERNATE LAW, turn coordination is always lost regardless of FAC status. Yaw damping, rudder trim and rudder limiting is available if a FAC is operational.
Flight Controls & Flight Control Laws
The pilot finds themselves in DIRECT LAW. Describe the indications, protections, and flight control logic.
In what condition / phase of flight would you mostly likely find yourself in DIRECT LAW?
- When in ALTERNATE LAW, there is no landing mode that would provide consistent control during landing for all possible failure combinations. Consequently, the flight controls transition to DIRECT LAW when the landing gear is extended and autopilot is off.
- DIRECT LAW is very unlikely in flight. It usually results from lowering the gear while in ALTERNATE LAW.
- Pitch control is direct. Load factor demand is lost. Pitch sensitivity or control is a factor of airspeed and the amount flight control deflection. Roll control is the same as ALTERNATE LAW (direct relationship with no protections).
Indications:
- An ECAM message is generated and says “PROT LOST”. Unlike in ALTERNATE LAW, this is now true. There are no protections and stabilities available in DIRECT LAW.
- Message “USE MAN PITCH TRIM” in amber is displayed on the FMA because automatic pitch trim is lost
Flight Controls & Flight Control Laws
- The pilots find themselves in MECHANICAL BACKUP. What functions are available?
- What would cause the airplane to revert to mechanical backup?
- control is provided for the rudder and THS (as long as hydr press avail)
- complete loss of flight control computers or electrical power, provided that there is hydraulic pressure
———————————————————————————————-
- MECHCANICAL BACKUP control is provided for the rudder and THS in the event of a complete loss of flight control computers or electrical power, provided that there is hydraulic pressure.
- Although the airplane can be flown indefinitely in this condition, it is intended to be used only as long as it takes to restore the computers.
- Note: the EW/D warning message and red “MAN PITCH TRIM ONLY” indication on the FMA. There isn’t a specific mechanical backup ECAM message.
** The side sticks are inoperative.
- Pitch is controlled with the trim wheel via the mechanical connection to the pitch system
- Roll and yaw are controlled through the rudder pedals and the mechanical connection to the rudder.
- In reality, the failure of only four flight control computers may result in mechanical backup: both ELACs and SEC 1 and 2 fail, all computerized pitch control is lost. In this case, because SEC 3 is still available, the side sticks can control roll using one spoiler on each wing, but pitch control is mechanical
ADIRS Panel
What is the ADIRS?
Air Data and Inertial Reference System
ADIRS Panel
What type of information does the Air Data Reference System provide?
- Airspeed
- Temperature
- AOA
- Mach
- Barometric altitude
- Over speed warnings
ADIRS Panel
What type of information does the IR provide?
- Aircraft position
- Attitude
- Acceleration
- Angular rates
- Flight Path Vector (FPV)
- Track
- Heading
- Groundspeed
ADIRS Panel
If there was an IR1 FAULT, what should be done with the switching panel to display backup data appropriately?
ATT/HDG to Capt 3
ADIRS Panel
If there was an ADR1 FAULT, what should be done with the switching panel to display backup data appropriately?
AIR DATA to Capt 3
ADIRS Panel
Explain the ADIRS Power-up and Initialization
- Switch from OFF to NAV
- ON BAT light illuminates and then extinguishes
- White ALIGN light illuminates for the duration of alignment (only on 319; 502-534)
- In 319 535-536, 320s and 321s, the E/WD memo section displays “IRS IN ALIGN” during alignment and replaces the ALIGN lights on the overhead panel.
ADIRS Panel
What are some indications of an ADIR having reverted to battery power on the ground?
- An external horn sounds
- The ON BAT light comes on
- An ADIRU & AVNCS light illuminates in amber on the external power panel
ADIRS Panel
What is the significance of a steady FAULT light on the IR?
IR has failed and cannot be recovered
ADIRS Panel
What is the significance of a flashing FAULT light on the IR?
Navigation function is lost. Attitude and Heading may be recovered in ATT mode.
ADIRS Panel
Describe what would happen if an ADR was selected OFF?
How could you recover the functions?
- The pilot would lose from that one ADR:
1. barometric altitude
2. airspeed
3. Mach
4. AOA
5. temperature
6. over speed warnings - The ECAM would instruct the pilot to select the AIR DATA SWTG to CAPT 3 or F/O 3 as appropriate
- At that point the affected pilot’s side would return to normal
ADIRS Panel
What functions are lost when an IR is turned OFF?
How can the functions be recovered?
- There are two ADIRS control panels installed on the fleet. On the older panel with keypad and digital display, the pilot would lose the IR (Inertial Reference) part which supplies:
1. aircraft position
2. attitude
3. accelerations
4. angular rates
5. flight path vector
6. track
7. heading
8. groundspeed
along with all the ADR information
The ECAM instructs the pilot to select the ATT HDG SWTG to CAPT 3 or F/O 3 as appropriate. At that point the affected pilot’s side returns to normal - The newer panel with no keypad and digital display allows the pilot to turn off only the IR, and in this case, only the IR information would be lost and the ADR information would still be available.
ADIRS Panel
When would a pilot perform a full alignment versus a quick alignment
Full Alignment:
- If the IR mode selectors are currently off
- First flight of the day
- If there is a change of flight crew
- If GPS is not available and the Flight Crew expects long segments in poor NAVAID coverage
Quick alignment:
1. For all other flights, if the deviation of the IRS position from the FMGC is greater than 5nm
ADIRS Panel
What could cause the flashing white ALIGN light to illuminate on the ground?
- PPOS not entered within 10 minutes of alignment or within 3 minutes of fast-alignment
- Large difference in LAT/LONG between shutdown position and entered position
- Aircraft movement during alignment
Note: no align light on A320 - the E/WD memo section displays “IRS IN ALIGN” during alignment and replaces ALIGN lights on the overhead panel. This memo flashes in green for the same reasons as the ALIGN lights flash on the other aircraft
EXT LTS Panel
If the RWY TURN OFF, LAND and NOSE switches are all in the ON position, which lights automatically extinguish after takeoff?
The NOSE and RWY TURN OFF lights extinguish when the landing gear is retracted
EXT LTS Panel
What is the difference between position 1 and 2 on the NAV & LOGO Toggle Switch?
Separate bulbs
EXT LTS Panel
When do the strobes flash in AUTO?
When the main landing gear is not compressed.
APU Panel
What does the illumination APU MASTER SW FAULT indicate?
Automatic APU shutdown has occurred
APU Panel
What is the significance of the APU AVAIL light illuminating?
APU is running above 99.5% or 2 seconds after N speed reaching 95%. In practical terms it is ready to accept and support ELEC and/or AIR load.
APU Panel
What condition in the APU system would cause an external horn to sound on the ground?
APU fire
APU Panel
With the APU green AVAIL light ON and the EXT PWR green AVAIL light on, which system is powering the aircraft?
2 Avails = APU powering the aircraft
APU Panel
If possible, how would the APU be used if it has already started the cool-down cycle?
Pressing the APU MASTER SW pushbutton
APU Panel
When running the securing checklist why is it important to wait 2 minutes after the APU avail light goes out before switching off the batteries?
Switching the batteries off before the APU flap is closed may cause smoke in the cabin during the next flight.
SIGNS Panel
What occurs when the EMER EXIT LT switch is placed to OFF?
- All lights OFF
- Amber EMER EXIT LT OFF light illuminates
SIGNS Panel
Why do we place the NO SMOKING SIGN to AUTO instead of ON?
It allows the EMER EXT LT to charge their batteries
INT LTS Panel
What flight deck lighting is available if normal electrical power is lost?
- Captain’s instrument panel
- Right dome light (provided DOME switch set in DIM or BRT)
- Standby compass
CABIN PRESS Panel
How is the landing field elevation entered into the pressurization system in automatic, semi-automatic and manual modes?
Automatic - FMGC (LDG ELEV must be in AUTO)
Semi-automatic - by LDG ELEV selector button
Manual - by selecting the MODE SEL to MAN and then using the MAN V/S CTL toggle switch
CABIN PRESS Panel
What does selecting the DITCHING pushbutton ON accomplish?
Closes all openings below the waterline
Note: If you lose both cabin pressure systems 1 +2, you have to manually close the outflow valve
CABIN PRESS Panel
When would a pilot push the ditching pushbutton?
What does it do?
Which valves?
- When ditching
- When directed by the deicing checklist
1SP Answer:
- closes 5 valves below the waterline
1SP Answer:
(right to left on ovrhd panel)
1. EXTRACT valve
2. Inlet (BLOWER) valve
3. RAM AIR valve
4. PACK flow control valves
5. Main outflow valve
AOM 1 p.120/22
CABIN PRESS Panel
How many controllers are in the pressurization system?
Two, only one is used at a time and they swap roles after each landing
CABIN PRESS Panel
How can a pilot manually switch controllers?
Switch MODE SEL to MAN for 10 seconds, then back to AUTO
CABIN PRESS Panel
What does an amber FAULT light in the MODE SEL pushbutton indicate?
Both automatic pressure controllers are faulty
CABIN PRESS Panel
What protects the airframe from excessive cabin differential pressure?
Two pressure relief valves
ANTI ICE Panel
What is accomplished if the WING anti-ice pushbutton is selected ON while the aircraft is on the ground?
The system will self-test for 30 seconds, and then the valves will close until the aircraft is airborne
ANTI ICE Panel
What does the WING FAULT light illumination on the ANTI ICE panel indicate?
- Valve disagreement (comes on momentarily when valve in transit)
- Low pressure
ANTI ICE Panel
What does the ENG 1(2) FAULT light illumination on the ANTI ICE panel indicate?
Valve disagreement (comes on momentarily when valve in transit)
ANTI ICE Panel
After selecting the probe/window heat pb on the ground to remove ice or fog on the window, would the pilot need to select it off before T/O?
Yes, so it can happen in the automatic mode
ANTI ICE Panel
What part of the wing is heated?
Outboard 3 slats
ANTI ICE Panel
In what position do the WING and ENGINE anti ice valves fail if electrical power is lost?
Wing - valves CLOSE
Engine - valves OPEN
ANTI ICE Panel
What is the significance of high swept wings versus less swept wings in ice accumulation?
The more swept the wing, the less time for the moisture to attach
ANTI ICE Panel
A flight crew is arriving to the aircraft in DTW early in the morning and notice that the cockpit windows are frosted over. What should the flight crew do?
Select the PROBE/WINDOW HEAT on. This must be selected off prior to takeoff in order to regain normal system logic
ANTI ICE Panel
The temperature outside is 2C with visible moisture. What should the flight crew turn on?
ENG anti-ice after engine start.
Icing conditions may be expected when the OAT (on ground
and for takeoff), or the TAT (in flight), is 10°C or below, and there is visible moisture in any form (such as clouds, fog with low visibility, rain, snow, sleet, ice crystals), or when standing water, slush, ice, or snow is present on the taxiways or runway
ANTI ICE Panel
After takeoff, when should the flight crew turn on the WING anti-ice.
WING anti ice can be used after the aircraft is in a clean wing and when conditions warrant use
ANTI ICE Panel
Climbing through FL240 in visible moisture, the crew notices the TAT is -22C and the SAT is -45C. What would be appropriate use of the ENG anti ice.
Engine anti ice may be turned OFF in this scenario. Engine anti ice is required when icing conditions exist or are expected except during climb or cruise when the SAT is below -40C.
ANTI ICE Panel
Starting a descent out of FL350 with visible moisture, the TAT is -32C and SAT is -53C. What would be appropriate use of the ENG anti ice?
Engine anti-ice must be ON during the descent in icing conditions even if SAT is below -40C.
ANTI ICE Panel
Descending through 10,000ft, the pilots notice ice accumulation on the cockpit windshield blades. What should they do?
When can Wing Anti-ice be used?
Turn on the WING anti-ice. WING anti-ice may either be used to prevent or remove ice accumulation from the wing leading edges. After takeoff, WING anti-ice can be used after the aircraft is in a clean wing configuration. Ice accumulation can be detected by observing the ice indicator located between the two cockpit windshields or by observing the windshield wiper blades.
ANTI ICE Panel
Can the WING anti-ice be used on the approach and landing?
Yes, but it should only be considered in severe icing because second segment climb performance could be affected if a go-around is performed.
ANTI ICE Panel
What is TAT?
Total air temperature
- it is also called Indicated Air Temperature (IAT) or Ram Air Temperature (RAT)
ANTI ICE Panel
What is SAT?
Static Air Temperature
- is also called Outside Air Temperature (OAT) or True Air Temperature
ANTI ICE Panel
Should a flight crew use TAT or SAT when determining whether to turn anti-ice systems on?
TAT indicates when to turn anti-ice ON. SAT indicated when it may be able to be turned OFF
AIR COND Panel
If PACK FLOW is selected to LO, NORM or HIGH and only the APU is providing BLEED AIR or one pack is selected OFF, what will the pack provide?
HIGH flow rate, since the flow rate function is automatic
AIR COND Panel
If the HOT AIR valve faults, what will happen to the temperature control system?
All trim air valves close and PACK 1 controls the cockpit temperature to the selected valve. PACK 2 controls the cabin to the averages selected by the FWD and AFT CABIN temperature selector knobs
AIR COND Panel
How are the PACKS controlled and operated?
Electrically controlled and pneumatically operated
AIR COND Panel
What are some potential causes from a PACK FAULT light?
PCS
- Valve position disagrees with selected
- Compressor outlet overheat
- Pack outlet overheat
AIR COND Panel
What are some potential causes for ENG BLEED FAULT light?
- Bleed overpressure
- Bleed overheat
- Wing or engine leak on the related side
- Bleed valve NOT closed during engine start
- Bleed valve NOT closed with the APU BLEED ON
1 SP Answer:
E - Excessive Pneumatic Temp or Pressure
W - Wing or Engine Leak
D - Disagreement between ENG and APU bleed valves (failure of auto logic)
AIR COND Panel
What is the logic for the X-BLEED rotary selector?
SHUT = the valve is closed AUTO = open if the APU bleed valve is open; closed if APU bleed valve is closed or there is a wing, pylon or APU leak (except during engine start) OPEN = the valve is OPEN
AIR COND Panel
What does APU BLEED FAULT illumination indicate?
APU bleed leak
AIR COND Panel
What does selecting RAM AIR pushbutton accomplish?
Ram air inlet opens if the differential pressure is less than 1 PSI
AIR COND Panel
What is the RAM AIR pushbutton used for?
- Smoke/fumes removal in the cabin
- Ventilation of cabin with a dual pack failure
1SP Answer:
RAM AIR utilized for
- unpressurized flight below 10,000ft
- when both PACKs inop and
- ventilation needed (i.e. smoke removal)
AIR COND Panel
How is the Bleed leak detection different on CEO and NEO aircraft?
If Bleed Air Monitoring Computer (BMC) fails on NEO airplane, over temperature protection is lost on the affected side. Has no effect on the CEO.
AIR COND Panel
When should you select LO pack flow?
319: when number of passengers < 138
320: when number of passengers < 141
321: select ON ECON FLOW when the number of passengers is below 168
ELEC Panel
What is the minimum battery voltage?
25.6v
ELEC Panel
What would a pilot do if BAT voltage is 25.5 or below on originating preflight?
How long should the batteries be charged?
Charge the batteries with external power by selecting BAT pushbuttons to AUTO
20 minutes, then recheck the voltage
ELEC Panel
Explain how to conduct the BAT check. What if it fails the test?
- Select ELEC on ECAM
- Turn BAT 1 & 2 OFF then ON
- Check BAT charge current is < 60 amps and decreasing within 10 seconds
- If it fails the test, wait until the end of the charging cycle, and repeat the test
ELEC Panel
Describe the electrical power system
- The electrical power system consists of a three-phase 115/200-volt 400-hertz constant frequency AC system and 28-volt DC
- Normally, the system produces alternating current, some of which is then transformed into direct current for certain applications
- Each of the aircrafts 3 generators can supply the whole network
- If all normal AC generation is lost, an emergency generator can supply AC power
- If all AC generation is lost, the system can transform DC power from the batteries to AC power
ELEC Panel
If all AC power is lost, what happens?
DC power from the batteries converted into AC
ELEC Panel
What would be an expected indication in the GEN pushbuttons prior to engine start?
FAULT indication
ELEC Panel
Define and describe an IDG
- Integrated Driver Generator
- Takes variable engine output and gives a constant output
ELEC Panel
How would a pilot disconnect an IDG?
How would an IDG be reconnected?
Lift the red guard and push the IDG pushbutton, being careful not to hold the pushbutton for longer than 3 seconds
This cannot be done by the flight crew - it is a maintenance function
ELEC Panel
Describe the function of the BUS TIE in AUTO
- Allows a single source to power AC BUS 1 and 2
- Allows connection of the APU GEN or EXT power to the system
- Inhibits multiple sources connected simultaneously
ELEC Panel
If GEN 1 fails to supply AC Bus 1, what happens?
GEN 2 (or APU GEN if available) powers the system through the bus tie
ELEC Panel
How is the AC ESS bus normally powered?
From AC Bus 1
ELEC Panel
If AC BUS 1 fails, how is the AC ESS bus powered?
AC Bus 2 automatically feeds the AC ESS bus
ELEC Panel
What indication will be present on the ELEC panel that the AC BUS 2 is feeding the AC ESS bus?
AC ESS FEED ALTN light illuminated only if the switch is manually selected
ELEC Panel
What does a GALLEY fault light indicate?
At least one generator load is above 100% output
ELEC Panel
Explain the AUTO function of the GALLEY pushbutton
Sheds main galley if only 1 GEN is available
ELEC Panel
How is the BATTERY BUS normally powered?
DC BUS 1 through the DC tie contactor
ELEC Panel
What buses are powered by the EMER GEN?
AC ESS BUS
AC ESS SHED
DC ESS BUS by the ESS TR
DC ESS SHED
ELEC Panel
What does a BAT FAULT light indicate?
- Battery charging current outside limits
- BAT contactor open
ELEC Panel
When are the batteries connected to the battery bus?
- APU start
- Battery charging
- AC BUS 1 & 2 not powered and airspeed below 100kts
FUEL Panel
Generally, what is the total fuel capacity?
42,000 lbs (41,285)
FUEL Panel
Why is it possible for there to be a value higher than 42,000lbs on the ECAM FOB?
The fuel can expand by 2% without venting overboard
FUEL Panel
How many fuel pumps are on the aircraft and where are they located?
There are 7 total fuel pumps:
- 2 center tank pumps
- 4 wing tank pumps (2 in each wing)
- 1 APU fuel pump
FUEL Panel
Explain the flow of fuel from before engine start to climb (assume full tanks)
- At engine start, the fuel is fed from the wing tanks
- After an engine is started, the center tank pumps turn on and continue to run for 2 minutes
- If slats are selected within those 2 minutes, the center tank pumps will continue to run until the time has elapsed, then they will stop.
- If the slats are extended at any other time, the center pumps will shut off - At takeoff, the engines feed fuel from their respective wing tanks
- When slats are retracted to zero, the fuel is fed from the center tank
- When the center tank runs low, the pumps continue to run for 5 minutes
FUEL Panel
What is the difference between the CTR TK Pump on an A319 and some older A320s (601-628) versus CTR TK XFR (transfer) on the A321 and newer A320s (629-656, 690-696, 901-915)?
CTR TK Pumps are identical to the main tank fuel pumps. The CTR TK XFR are jet pumps that transfer center tank fuel to the main L (R) pumps
FUEL Panel
What does a fault light in one of the L(R) TK PUMPS pushbuttons indicate?
Low delivery pressure
FUEL Panel
What does a fault light in the MODE selector indicate?
- Failure of the AUTO mode
- Center tank has more than 550lbs and either wing tank has less than 11,000lbs
FUEL Panel
How would a pilot know that fueling is in progress?
REFUELG message appears on the ECAM. This does not mean the fuel is entering the tanks, merely that the refueling door is open
FUEL Panel
Describe IDG cooling and how it relates to the FADEC
- Some of the fuel supplied to each engine goes from the high-pressure fuel line in that engine, through the integrated drive generator (IDG) heat exchanger (where it absorbs heat), to the fuel return valve, and back to either the wing tank or outer tank, depending on the aircraft.
- This operation ensures IDG cooling when the oil temperature is high or when at low engine power
- The FADEC controls the fuel return depending on the temperature of the IDG - the higher the temperature, the higher the flow.
FUEL Panel
What happens if returned IDG cooling fuel fills the wing tanks while the center tanks are feeding?
The center tank pumps will cut off until the wing tank quantity is reduced by 1100lbs in the inner tank.
