Oral Study Questions Flashcards
How should a pilot call the forward flight attendant?
Press the FWD button.
How should a pilot call a mechanic?
Press and hold the MECH button. It illuminates a blue light on the EXT PWR PANEL and sounds an external horn.
What happens when a pilot presses the EMER pb?
- Pink light flashes at all area Call Panels.
- EMERGENCY CALL appears on all attendant indication panels.
- High-low chime (repeated 3 times) sounds throughout the cabin loud speakers.
What happens when the F/As initiate an emergency call?
- The white EMER ON light and amber CALL lights flash.
- The amber ATT lights flash on the ACPs.
- 3 long buzzers sound in the cockpit.
- System resets when the attendant hangs up the relevant systems.
What does the illumination of the SYS ON light mean?
The signal has been sent to release the oxygen mask doors.
What causes automatic deployment of the masks?
Cabin altitude reaching approximately 14,000’.
How does the passenger oxygen system work?
Chemical oxygen generators for approximately 13 to 15 minutes.
What happens when a pilot pushes the CREW SUPPLY pb?
Valve opens to supply low pressure oxygen to the pilots.
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
Will the crew oxygen mask microphone automatically be deactivated when the mask is stowed?
No, you must press the RESET control slide.
Why is the GND CTL pb selected to ON during preflight?
To record preflight activities in the cockpit
If the PB was not selected ON, how would the system work in automatic mode?
- ON for 5 minutes after electrical power is supplied to the aircraft.
- At least one engine is operating, stops 5 min after last engine shut down.
What allows the cabin PAs to be recorded?
ACP 3 PA Volume knob out and in the 12 to 3 o’clock position.
Pressing the GPWS SYS pb does what?
All Basic GPWS alerts (Modes 1 to 5) are inhibited.
What does an amber FAULT light in the SYS pb indicate on the GPWS panel? What effect if any does it have on the TERRAIN mode?
- Any failure of GPWS mode 1 through 5.
- No effect.
Describe a situation when a pilot might press LDG FLAP 3?
- To avoid nuisance warning in case of landing in CONF 3.
- In this case, LDG MEMO displays FLAPS…CONF 3 instead of FLAPS …FULL.
Describe a situation when a pilot might press the FLAP MODE pb?
- To avoid nuisance warning in case of landing with flaps setting reduced.
- FLAP SYS 1 (2) Fault would cause you to select FLAP MODE off.
What effect if any does the TERR mode failed have on basic GPWS?
No effect.
What is the significance of the red FAULT illuminating on the RAT & EMER GEN light?
AC BUS1 and AC BUS 2 are lost and the RAT is not supplying electrical power.
When would it normally illuminate?
The fault light will illuminate once the RAT is deployed and electrical power is not being supplied (approximately 8 seconds).
How can the RAT be deployed?
Manually by pushing MAN ON or RAT MAN ON, or automatically by the loss of both AC BUS 1 and AC BUS 2.
What does the RAT supply?
Blue Hydraulic system and the emergency electrical generator.
What buses are powered by the emergency electrical generator?
- AC ESS and AC ESS Shed.
- DC ESS and DC ESS Shed.
What is the difference between the Automatic RAT deployment and RAT deployed by pressing the RAT MAN ON on the HYD panel?
RAT MAN ON supplies Blue Hydraulic PSI only, no electrical generation.
After deploying the RAT by pressing the RAT MAN ON pushbutton on the HYD panel and it became necessary to also extract electrical power, how can it be accomplished?
By pressing the MAN ON pushbutton on the EMER ELEC PWR.
What would cause the GEN 1 LINE SMOKE light to illuminate?
Smoke detected in the avionics ventilation ducting.
If the ECAM directs a pilot to select GEN 1 LINE PB 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 Contactor.
- GEN 1 powers one fuel pump directly in each wing tank.
Will there be any other indications of avionics smoke?
ECAM warning and amber FAULT lights in the EXTRACT and BLOWER pbs on the VENTILATION panel.
What is checked on the EVAC panel during the Preliminary cockpit preparation?
CAPT & PURS switch in CAPT position.
How should the pilot command an evacuation?
- Make a PA announcement.
- Press the EVAC COMMAND pb.
What type of flight control system does the A320 family aircraft utilize?
Fly-By-Wire System.
How are flight controls controlled and activated?
Electrically Controlled and Hydraulically Activated.
How is NORMAL LAW indicated on the PFD?
Green double markers.
How is ALTERNATE LAW indicated on the PFD?
Amber Xs (indicating lack of NORMAL LAW protections).
How is DIRECT LAW indicated on the PFD?
- AMBER “USE MANUAL PITCH TRIM”.
- Amber Xs (indicating lack of NORMAL LAW protections).
How is MECHANICAL BACKUP indicated on the PFD?
- RED “MAN PITCH TRIM ONLY”.
- Amber Xs (indicating lack of NORMAL LAW protections).
When operating in NORMAL LAW in FLIGHT mode, what does the side stick command for pitch and roll?
- Pitch – G load.
- Bank – Roll Rate.
What is the significance of the Side Stick Priority (Red Arrow) Light?
The other pilot has gained side stick authority.
Name the Flight Control Computers.
- ELAC – Elevator Aileron Computer (2).
- SEC – Spoiler Elevator Computer (3).
- FAC – Flight Augmentation Computer (2).
What are the some of the ELAC functions? QRM should be referenced.
- Normal elevator.
- Normal aileron.
- Normal pitch and roll.
- Alternate pitch.
- Direct pitch and roll.
- Abnormal attitude.
- Aileron droop.
- Autopilot orders.
What are some of the SEC functions? QRM should be referenced.
- Normal roll.
- Speed brakes.
- Alternate pitch.
- Direct pitch.
- Direct roll.
- Abnormal attitude.
What does the SEC 3 control?
Spoiler Control – one flight spoiler and one ground spoiler on each wing.
What are some of the FAC functions?
- Rudder Trim.
- Rudder travel limit.
- Yaw control.
- Flight Envelope Protection – vertical.
- Windshear Protection.
- Low Energy Warning Protection.
- Alpha Floor Protection.
- PFD speed scale.
What should happen to the THS after landing?
Reset to zero.
Describe some of protections a pilot will have in Normal Law?
- High Speed.
- High Angle of Attack (AOA/alpha).
- Load Factor Limitation (+2.5g / -1.0g).
- Pitch Attitude (30° up/15° down).
- Bank Angle (67°).
Describe High Speed Protection.
If VMO/MMO plus a predetermined factor is exceeded, the system induces a pitch-up input to limit aircraft speed.
What would a pilot have to do to override the high speed protection pitch-up?
Turn 2 ADRs off to force the aircraft into Alternate law.
What is alpha max?
The maximum angle of attack allowed in Normal Law, indicated by the top of the red strip on the airspeed scale.
How does High Angle of Attack Protection operate?
When the angle of attack exceeds alpha prot, 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.
What protections does a pilot have in Alternate Law?
- Load Factor.
- High speed stability.
- Low speed stability.
What protections does a pilot have in Direct Law?
None.
When do you get Flare Mode in Alternate Law? Describe the whole process
You don’t. You go directly from Alternate Law to Direct Law when the gear is selected
down.
If in Alternate Law, when will the aircraft revert to Direct Law? What might be a wise thing to do?
If the controls degrade to alternate law for any reason other than recovery from abnormal attitude, Direct Law automatically becomes active with gear extension with autopilots not engaged. In other words, let the autopilots work for you until you must disconnect them.
When is there a direct relationship between side stick and flight control surface deflection?
- When in Direct Law.
- When below 100’.
It’s common Airbus philosophy that the Airbus can’t stall in Normal Law. However, there are conditions in which it can.
- Faulty Radio Altimeter.
- A competent 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 angle of attack or flight path of the aircraft. Therefore, it is hard to point to exact scenarios when the Airbus can stall in normal law. We need to understand anything is possible and we should recognize stall indications and recover regardless of the active control law.
How would you get into Abnormal Attitude Law?
By exceeding approximately double the Normal Law limits.
What is the purpose of Abnormal Attitude Law?
Allows the aircraft to be recovered from an unusual attitude.
After recovery from an unusual attitude, what law are you in?
Abnormal Attitude Law
What PFD indications indicate Normal Law?
- Green = for pitch, bank, and overspeed limits.
- Amber/black (alpha prot) airspeed tape.
If the pilot is flying along at 300 knots and they happen to pull full back on the side stick, how high can they pitch up to?
30° up.
With an AP ON and A/THR ON, if the pilot selected 100 knots on the speed knob, how slow would the aircraft fly?
VLS.
Describe what would happen if the pilot slowly pulled the power to idle?
- As airspeed decays, the THS adjusts the pitch attitude to maintain altitude.
If the angle of attack increases to a threshold value, known as ALPHA PROT, the pitch function of the side stick changes. Stick movement commands a specific AOA instead of a G change. - Since auto trimming is inoperative, the pilot must hold continuous back pressure in order to fly slower than ALPHA PROT.
Describe what would happen if the pilot continued to pull back on the side stick. How slow would the aircraft go?
- Alpha Max.
- With the stick full aft, the elevators will adjust the pitch attitude to maintain, a maximum safe angle of attack (Alpha Max). This maximum angle of attack, induced by the pilot, is slightly less than the stall angle of attack; therefore, the aircraft theoretically can’t be stalled in normal law.
At some point during this demonstration the Auto thrust automatically applies TOGA power. What is this protection name and how does it work?
- ALPHA FLOOR is a function of auto thrust. It will activate at any airspeed based on angle of attack and automatically apply TOGA thrust regardless of thrust lever position.
- ALPHA FLOOR is available if the auto thrust is functional (it does not need to be active), an engine is running (not both), and the aircraft is in normal law.
- Angle of attack protection does not depend on ALPHA FLOOR to function.
Can the pilot over stress the aircraft by pulling back too hard on the side stick in Normal Law?
- No.
- 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.
- 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.
What will happen if the pilot over speeds the aircraft? Are there any protections that are available to the pilot?
- 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 maximum airspeed by increasing the pitch attitude even if full forward stick is held.
- The speed at which this protection activates is shown on the airspeed indicator as a green “=” sign.
- An over speed warning is generated as VMO is exceeded (Vmo+4). This warning can only be silenced by the EMER CANCEL pb.
- If the stick is released, the speed will return to VMO/MMO. The protection will allow a momentary increase in airspeed to permit any necessary maneuvering but then the speed will again slow to the limit.
- If high-speed protection is active, bank angle is limited to 45°. Bank angle is also limited to 45° if angle of attack protection is active, in either case the limit marks do not move.
- If high-speed protection 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 maximum attainable speed.
When a pilot rolls into a bank, what is provided by the Flight Control Laws?
- The flight mode roll control is a roll rate demand law. Side stick inputs commands the ailerons, spoilers 2-5, and the rudder to achieve the commanded roll rate with bank angle protection, turn coordination, and Dutch roll damping.
- The roll rate demanded inflight, 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.
- The side stick position cannot be used to establish where flight control surfaces are.
- 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.
- In normal turns (up to 33°) pitch trim is automatic and assists the pilot in maintaining altitude.
- If the pilot would increase the bank to 45 degrees and then let go of the stick the altitude (pitch inputs may still be needed to maintain altitude), the aircraft returns 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 angle-of-attack 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.
The pilots find themselves in Alternate Law. Describe the protections.
- Amber Xs and EW/D message. In most cases, a single failure will not cause a flight control degradation (jammed stab causes a degradation).
- 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.
- The ECAM states PROT LOST, but maneuver protection is still available.
- Pitch is the same as normal law, roll is direct, and yaw loses turn coordination.
- Attitude, high speed, and angle of attack protections are lost. They are replaced by high speed stability and low speed stability respectively.
- High speed stability activates just prior to the over speed warning at which time nose down trim is inhibited.
- Low speed stability activates just prior to the stall warning at which time nose up trim is inhibited.
- The pilot can override the stabilities and over speed or stall the aircraft.
- 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 as it was in normal law.
- 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. Positive spiral stability is 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.
- Aircraft can roll beyond the amber Xs.
- Bank angle protection is not available in alternate law. Roll commands are carried out directly without modification.
The pilots find themselves in Direct Law. Describe the protections.
- 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 gear is extended.
- Direct law is very unlikely in flight. It usually results from lowering the gear while in alternate law.
- ECAM message generated - PROT LOST is true. There are no protections or stabilities available in direct law.
- USE MAN PITCH TRIM in amber is displayed on FMA because automatic pitch trim is lost.
- 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).
The pilots find themselves in Mechanical Backup. What functions are available?
- Mechanical back up control is provided for the rudder and THS in the event of a complete loss of flight control computers or electrical power.
- Although the aircraft can be flown indefinitely in this condition, it is intended to be only as long as it takes to restore the computers.
- Note the EW/D warning message and MAN PITCH TRIM ONLY indication on the FMA.
- The side sticks are inoperative. Pitch is controlled with the trim wheel via the mechanical connection to the pitch system.
- Roll and yaw is controlled through the rudder pedals and the mechanical connection to the rudder.
- In reality, the failure of only four flight control computers results in mechanical backup. If 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.
What is the ADIRS?
Air Data and Inertial Reference System.
What are some of the parameters that the Air Data Reference System provides?
Barometric altitude, Airspeed, Over Speed Warnings, Temperature, AOA, MACH.
What are some of the parameters the IR provides?
Attitude, FPV, Track, Heading, Acceleration, Angular Rates, GS and Aircraft Position.
With an IR 1/ADR 1 FAULT which switching panel switch would you move to display backup data?
ATT HDG to CAPT 3.
If the AIR DATA portion of ADIRU 1 has failed, which switching panel would you move to display backup data?
AIR DATA to CAPT 3.
Explain the ADIRS Power-up and Initialization.
- Switch OFF to NAV.
- ON BAT light illuminates and then extinguishes.
- White ALIGN light illuminates for the duration of alignment (only on an A-319/ A-321).
- In a 320 the E/WD memo section displays IRS IN ALIGN during alignment and replaces ALIGN lights on the overhead panel.
What is the importance of observing the ON BAT light?
It confirms the ADIRS ability to revert to aircraft battery power.
What are some indications of an ADIRU having reverted to battery power on the ground?
- An external horn sounds.
- An ADIRU and the blue AVNCS light illuminates on the External Power Panel.
What is the significance of a steady FAULT light on the IR?
IR has failed and cannot be recovered.
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.
What could cause the flashing white ALIGN light to illuminate on the ground?
- Position - PPOS not entered within 10 min. of alignment or within 3 minutes of fast-alignment.
- Place - Large difference in LAT/LONG between shutdown position and entered position -1°.
- Push - Aircraft movement during alignment.
- 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.
Describe what will happen if an ADR is selected OFF?
- The pilots would lose barometric altitude, airspeed, mach, angle of attack, temperature and over speed warnings from that one ADR.
- 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 pilot’s affected side would return to normal.
What functions are lost when an IR is turned OFF?
- The pilot would lose the IR part (Inertial Reference) which supplies attitude, flight path vector, track, heading, accelerations, angular rates, ground speed, and aircraft position.
- Along with all the ADR information.
- The ECAM would instruct the pilot to select the ATT HDG SWTG to CAPT 3 or F/O 3 as appropriate.
- At that point the pilot’s affected side would return to normal.
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.
What is the difference between position 1 and 2 on the NAV & LOGO Toggle Switch?
Separate bulbs.
What position should the STROBE switch be in during preflight?
AUTO.
When do the strobes flash in AUTO?
When the computer logic considers the aircraft airborne.
What does the illumination APU MASTER SW FAULT indicate?
Automatic APU shutdown has occurred.
What is the significance of the APU AVAIL light illumination?
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).
What condition in the APU system would cause an external horn to sound?
APU fire
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.
During the cool down cycle can you still use the APU?
Yes, press the APU MASTER SW pb.
When will the EXIT signs automatically illuminate?
- With the EMER EXIT LT switch in ARM, and Normal AC power is lost.
- DC SHED ESS BUS not powered.
- Cabin altitude is excessive (above 11,300‘), NO SMOKING, FASTEN SEAT BELT and EXIT signs illuminated.
What lights illuminate when normal aircraft electrical power fails?
- Floor proximity emergency escape path-marking system.
- Overhead emergency lighting.
What lights illuminate when the EMER EXIT LT switch is placed to ON?
- Overhead emergency lighting.
- Floor proximity emergency escape path marking system.
- EXIT lights.
What occurs when the EMER EXIT LT switch is placed to OFF?
- All lights OFF.
- Amber EMER EXIT LT OFF light illuminates.
Why do we place the NO SMOKING SIGN to AUTO instead of ON?
- It allows the EMER EXT LT to charge their batteries.
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.
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.
What does selecting the DITCHING push button to ON accomplish?
- Closes the outflow valve.
- Closes the emergency RAM AIR inlet.
- Closes the Avionics Ventilation Inlet and Extract valves.
- Closes pack flow control valves.
- Forward cargo isolation outlet valve “if installed”.
- Cargo recirculation fans stop automatically “if installed”.
- “Closes all valves below the waterline”.
How many controllers are in the pressurization system?
- 2, only one is used at a time and they swap roles after each landing.
How can a pilot manually switch controllers?
- Switch MODE SEL to MAN for 10 seconds, then back to AUTO.
What does an amber FAULT light in the MODE SEL pb indicate?
- Both automatic pressure controllers are faulty.
What protects the airframe from excessive cabin differential pressure?
- 2 pressure relief valves.
What is accomplished if the Wing Anti Ice push button is selected ON while the aircraft is on the ground?
- The system will self-test for 30 seconds, then the valves will close until the aircraft is airborne.
What does the WING FAULT light illumination on the ANTI ICE panel indicate?
- Valve disagreement (also comes on momentarily when valve in transit).
- Low pressure.
What does the ENG 1(2) FAULT light illumination on the ANTI ICE panel indicate?
- Valve disagreement (also comes on momentarily when valve in transit)
Describe the PROBE/WINDOW HEAT Logic.
- Probes and Window Heat come on automatically (Probes LOW on ground/HIGH airborne) with at least one engine running or aircraft airborne.
What part of the wing is heated?
Outboard 3 slats.
In what position do the Wing and Engine Anti-Ice valves fail if electrical power is lost?
- Wing – valves CLOSE.
- Engine – valves OPEN.
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.
- After flying the airbus for a while, you may notice that you are selecting the wing pb less often as you
might have on a previous straight wing aircraft.
A pilot is arriving to the aircraft in DTW early in the morning and notice that cockpit windows are frosted over. What should the pilot do?
- Select the Probe/Window Heat on. Remember you must select it off before takeoff to return the system
to its normal logic.
The temperature outside is 2°C with visible moisture. What should the pilot turn on?
ENG Anti-ice after engine start.
After takeoff, when should the pilot turn on the wing anti-ice?
Wing anti-ice can be used after the aircraft is in a clean configuration and when conditions warrant.
Going through FL240 in visible moisture you notice the TAT is -22°C and the SAT is -45°C, can the Pilot select the ENG Anti-ice off?
Yes. Engine anti-ice is required when icing conditions exist or are expected except during climb or cruise
when the SAT is below -40°C.
Starting a decent out of FL350 with visible moisture the TAT is -32°C and SAT is -53°C, should the pilot select the ENG Anti-ice on or off?
ON Engine anti-ice is required when icing conditions exist or are expected except during climb or cruise
when the SAT is below -40°C.
Descending through 10,000’ the pilots notice ice accumulation on the cockpit windshields blades. What should the pilots do?
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 the observing the ice indicator located between the two cockpit windshields or by observing windshield wipers blades.
Can the Wing Anti-ice be used on the approach and landing?
Yes, but remember second segment climb performance could be affected if a go-around is performed.
What is TAT?
Total Air Temperature is also called Indicated Air Temperature (IAT) or Ram Air Temperature (RAT).
What is SAT?
Static Air Temperature is also called: Outside Air Temperature (OAT) or True Air Temperature.
Do I use TAT or SAT when determining whether to turn Anti-ice systems on?
Remember TAT tells you when to turn Anti-ice on. SAT tells you when you may be able to turn it off.
What is the difference of TAT and SAT?
The difference between TAT and SAT is called ram rise (RR) and is caused by compressibility and
friction of the air at high velocities.
What you might see on flying a trip out of DTW at different altitudes with regards to TAT and SAT?
- Ground TAT +2 SAT +2
- 10000ft TAT -6 SAT -17
- 18000ft TAT -13 SAT -33
- FL240 TAT -23 SAT -45
- FL350 TAT -28 SAT -54
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 Flow Rate?
HIGH flow rate, since the flow rate function is automatic.
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 last selected value - PACK 2 controls the cabin to the averages selected by the FWD and AFT CABIN temperature selector knobs.
How are the PACKS controlled and operated?
Electrically controlled and pneumatically operated.
What are some potential causes for a PACK FAULT light?
What are some potential causes for a PACK FAULT light?
- Low air pressure.
- Compressor outlet overheat.
- Pack outlet overheat.
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.
What is the logic for the XBLEED Valve switch?
- 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 an engine start).
- OPEN = the valve is open.
What does APU BLEED FAULT illumination indicate?
APU bleed leak.
What does selecting the RAM AIR push button accomplish?
Ram Air inlet opens if the differential pressure is less than 1 PSI.
What is the RAM AIR pb used for?
- Smoke removal in cabin.
- Ventilation of cabin with a dual pack failure.
What is the minimum battery voltage?
25.6.
What would a pilot do if BAT voltage is 25.5 or below on originating preflight?
Charge the Batteries with external power by selecting BAT pbs to AUTO.
How long would you charge the batteries?
20 min. and recheck the voltage.
Explain how to conduct the BAT check?
- Select ELEC on ECAM.
- BAT 1 & 2 OFF then on.
- Check BAT charge current is <60 amps and decreasing within 10 seconds.
What if it fails the test? Call MX.
Describe the electrical power system of the aircraft.
- The electrical power system consists of a three-phase 115/200-volt 400-hertz constant frequency AC system and a 28-volt DC system.
- Normally, the system produces alternating current, some of which it then transforms into direct current for certain applications.
- Each of the aircraft’s three 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 into AC power.
If all AC is lost, what happens?
DC power from the batteries is converted into AC.
The engine GEN FAULT light is illuminated before engine start. Is this normal?
Yes.
What is an IDG and describe how it works.
- Integrated Drive Generator.
- Takes variable engine output and gives a constant output.
How would a pilot disconnect the IDG.
Lift the red guard and push the IDG pb sw. Don’t hold for longer than 3 seconds.
Can the IDG be reconnected?
No. MX function.
Describe the function of the BUS TIE in AUTO.
- Allows single source of power to run entire electrical system.
- Allows connection of the APU GEN or EXT power to system.
- Inhibits multiple sources connected simultaneously.
If GEN 1 fails to supply AC BUS 1, what happens?
AC BUS 2 powers the system through the bus tie.
How is the AC ESS bus normally powered?
From AC BUS 1.
If AC BUS 1 fails, how is the AC ESS bus powered?
AC BUS 2 automatically feeds the AC ESS BUS.
What indication will you get on the ELEC panel that AC BUS 2 is feeding the AC ESS bus?
AC ESS FEED ALTN light on.
What does a GALLEY fault light indicate?
At least one generator load is above 100% rated output.
Explain the Auto function of the GALLEY pushbutton.
- Sheds main galley if only 1 gen is avail in flight or
- Sheds main galley if only 1 gen is avail on the ground.
How is the BATTERY BUS normally powered?
DC BUS 1 through the DC tie contactor.
What Buses are powered by the EMER Generator?
- AC Essential bus.
- DC Essential bus by the Essential TR.
What is the difference of the APU Gen Fault and the ENG fault?
- Both are indicators of a line contactor open. The diff is the fault may also indicate a
Fault detected by the ENG GCU.
What does a BAT fault light indicate?
- Battery charging current outside limits.
- BAT contactor opens.
When are the batteries connected to the BATTERY BUS?
- APU start.
- Battery charging.
- AC BUS 1 & 2 not powered and airspeed below 100 knots.
Describe the layout of the fuel tanks in the A320.
Center tank, and wing tanks made up of inner, outer and vent tanks.
Generally, what is the total fuel capacity?
42,000 lb (41, 285).
How come sometimes the fuel totalizer reads 42,200 on ECAM when fueled to MAX capacity?
- The fuel can expand by 2% without venting overboard.
Where are the fuel pumps located?
- 2 Center tank pumps and 2 wing tank pumps per wing.
- The APU has its own pump. It supplies fuel for APU startup when fuel feed pressure is low (due to loss of tank pumps or loss of normal AC Electrical supply.
Are the pumps in the center tank different from the wing pumps?
No, The wing pumps are fitted with pressure relief sequence valves, which ensure that
when all pumps are running, the center tank pumps will deliver fuel preferentially.
Explain the flow of fuel from before engine start to taxi out. (Assume full tanks)
At engine start the fuel is fed from the wing tanks. After both engines are started, the center tank pumps turn on and continue to run for 2 min. If slats are selected within those 2 min center tank pumps will continue to run until the time has elapsed, then they will stop. If at any other time the slats are extended the center pumps would shut off. At T/O the engines feed fuel from the respective wing tanks. When slats are zero, the fuel is fed from the center tank (after center tank runs dry, the pumps continue to run for 5 min).
What does a fault light in one of the ENG fuel pumps indicate?
- Low delivery pressure.
What does a fault light in the MODE selector indicate?
- Failure of the AUTO mode.
- Center tank has more than 550 lb and either wing tank has less than 11000 lb.
How would a pilot know that fueling is in progress?
- REFUELG message appears on the ECAM.
Does this mean that fuel is entering the tanks?
NO. It means the refueling fuel door is open.
Describe the 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 the outer tank. - This operation ensures the IDG cooling when the oil temperature is high or when at low engine power.
- The FADEC controls the fuel return valve. The rate of return is approximately 660 LBS/H during low IDG
temperature and 1100 LBS/H during high IDG temperature.
What if this IDG cooling return fuel fills the wing tanks with the center tanks feeding?
- The center tank pumps will cut off until the wing tank quantity is reduced by 1100 lb.
