Airbus A320 & A319 Study Guide 空客A320 & A319学习指南

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AIRCREW TRAINING SOLUTIONS
Airbus A320 & A319 Study Guide ã
A I R B U S A 3 2 0 / 3 1 9 S T U D Y G U I D E
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A I R B U S A 3 2 0 / 3 1 9 S T U D Y G U I D E
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Overhead Panel - Part 1
1) ON BAT LIGHT
The aircraft batteries are powering one or more ADIRU.
When power is lost, ADIRU’s 2 & 3 will remain ON BAT for 5 minutes, to
retain alignment data while generator power can be restored. ADIRU 1 or
whichever unit the captain has selected will remain ON BAT until generator
power is restored.
2) IR LIGHTS
FAULT - (Flashing FAULT) ATT & HDG may be recoverable.
(Steady FAULT) Fault in IR unit, and is not recoverable.
ALIGN - (Flashing) Alignment fault, No present position entered within 10 minutes or
1° LAT/LONG difference between its last known position.
Note: A dual IR failure will increase landing distance. IR’s supply antiskid
with deceleration info. Dual IR failure limits the deceleration rate to 5.6 fps².
IR supplies: HDG, ATT, and VS to PFD
ADR supplies: AS, ALT, and backup VS to PFD
The A320 & A319 have the capability to incorporate GPS inputs to the
GNADIRS.
3) NAV SELECTOR
NAV - Normal position for alignment and navigation. Full alignment requires 7-10
minutes. Fast alignments take 3 minutes. A fast alignment may be
accomplished only if the IR’s have been previously aligned. Fast alignment is
accomplished by selecting each IR to OFF then ON within 5 seconds and
entering a new present position.
ATT - Used to retain attitude & heading information when IR has faulted
4) ADR P/B
FAULT - Failure of the Air Data Reference system.
OFF - When pressed to OFF Air data output is disconnected
Chapter 1
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5) GEN 1 LINE P/B
OFF - Generator 1 Line contactor opens. #1 fuel pump in each wing tank is powered
from the generator 1 feeder
SMOKE - Smoke is detected in the avionics ventilation duct
EMERG GEN TEST P/B
This test is normally performed by maintenance. Tests the emergency
generator without deploying the RAT.
5 KVA 115/200V 400Hz utilizing the blue hydraulic system.
7) RAT/EMERG GEN FAULT LIGHT
FAULT - Emergency generator is not supplying power when:
AC Buses 1&2 are not powered and the nose landing gear is up.
A319 - AC Bus 1&2 are not powered, Emergency generator is not supplying
power, nose landing gear extended or retracted.
8) EMERG GEN P/B
AUTO - RAT extends when AC Bus 1&2 are not powered, and airspeed is above 100
knots, with the nose landing gear up. The emergency generator, powered by
the blue hydraulic system, will couple within 3 seconds if all parameters are
normal. The emergency generator will provide electrical power until
approximately 140 knots.
A319- RAT extends when AC Bus 1&2 are not powered, regardless of nose
landing gear position. The A319 RAT is more efficient. Therefore, the RAT
will remain online and provide power (including the shed buses) until
approximately 125 knots.
RAT MAN ON - RAT is manually extended. Emergency generator coupling
will occur if nose landing gear is retracted.
A319- Gear position is not part of the logic.
9) TERR P/B
FAULT - Fault detected in the EGPWS terrain awareness display (TAD) and or terrain
clearance floor (TCF) functions. Aircraft relative height (for TAD) is
computed using the captains barometric setting and does not have protection
for barometric setting errors. TAD and TCF functions utilize FMGC 1 position
and offer no protection against position errors.
OFF - EGPWS functions are disabled.
Note: EGPWS display is not available in either the plan mode or while WX
radar is displayed.
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10) SYS P/B
OFF - All GPWS warnings are inhibited
FAULT - GPWS malfunction. All warnings are inhibited
11) G/S MODE P/B
OFF - Mode 5 (Glideslope) warning is inhibited
12) FLAP MODE P/B
OFF - Mode 4 (Too Low Flaps) warning inhibited
13) LDG FLAP 3 P/B
ON - Mode 4 warnings for Flaps 3 are inhibited. Used when selecting Flaps 3 as the
landing configuration. E.g. Single-engine approach, Wind shear and Direct
law approaches.
GPWS Modes
Mode 1 = Excessive descent rate “Sink Rate”
Mode 2 = Excessive terrain closure “Terrain, Terrain”
Mode 3 = Altitude loss after T/O “Don’t Sink”
Mode 4 = Unsafe terrain clearance “Too Low Flaps”
Mode 5 = Excessive GS deviation “Glideslope”
14) RCDR GND CTL P/B
AUTO - CVR and DFDR are energized automatically:
· For 5 minutes after initial aircraft power up
· After an engine is started
· In-flight
· CVR and DFDR remain powered for 5 minutes after engine shutdown
ON - CVR and DFDR are energized. The ON light will extinguish after engine
start.
15) CVR ERASE (Pressed for two seconds)
Erases tape when:
· Aircraft is on the ground
· Parking brake is set
16) CVR TEST (Pressed and held)
Test is activated if RCDR GRD CTL switch is ON and the parking brake is
set. A low frequency tone is heard if a headset is plugged in to the CVR test
jack on the overhead panel.
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17) OXYGEN MASK P/B
AUTO - Masks deploy when cabin altitude exceeds 14,000 ft + 0 /-500 ft and a prerecorded
message plays in the cabin. Chemical generators supply Pax O2 for
13 minutes.
MASK MAN ON - Manually deploys Pax O2 masks. No automatic pre-recorded cabin
message will play.
18) PASSENGER
SYS ON - Illuminates when control of the O2 mask doors is actuated and remains on until
The TMR RESET P/B on the overhead panel is activated
19) CREW SUPPLY
ON - Valve is open, low-pressure oxygen supplied to cockpit
During preflight minimum of 1000 psi on door page
OFF - Manually closes O2 supply valve
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Overhead Panel - Part 2
1) ENGINE FIRE P/B
ILLUMINATED - Engine fire warning activated. Dual gas loops are located in the
Pylon, Fan and Core sections. With an inoperative loop, the system
will reconfigure to a single loop operation. Losing both loops
within 5 seconds will cause a FIRE warning. (Burn through theory)
PUSH - · Cancels aural warning
· Arms squibs
· Closes LP fuel valve, including the IDG cooling return line
· Closes Hydraulic fire valve
· Closes Bleed valve
· Closes Pack valve
· Deactivates generator
2) APU FIRE P/B
ILLUMINATED - APU fire warning activated. Dual gas loops are located in the APU
compartment.
On the ground APU will automatically shutdown and discharge the
fire bottle in 10 seconds.
PUSH - · APU auto shutdown
· Cancels aural warning
· Arms squibs
· Closes LP fuel valve
· APU fuel pump off
· APU Bleed and Crossbleed close
· APU Generator deactivated
3) AGENT P/B
SQUIB - Corresponding FIRE P/B must be pushed to arm the Agent P/B.
Pressed – Bottle discharges.
Pushing #1 starts a 30-second timer on the ECAM.
DISCH - Fire bottle is depressurized. Additionally for an APU thermal discharge, a
blow out disc is located on the aft fuselage.
Chapter 2
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4) FIRE TEST P/B
PRESS - Tests respective fire detection and extinguishing systems.
ENGINE (7 lights) FIRE P/B APU (5 lights) FIRE P/B
2 Squib lights Squib light
2 Master warnings 2 Master warnings
ECAM ECAM
Fire light on pedestal
5) RAT MAN ON P/B
Extends RAT providing 2500 psi to the Blue hydraulic system.
The emergency generator is not powered.
6) PTU P/B
AUTO - PTU is armed to run when a 500 psi differential pressure exists between the
Green and Yellow hydraulic systems.
The PTU is inhibited during the first engine start and self-tests during the
second start, provided the parking brake is set.
Note: The PTU logic inhibits its operation anytime:
· Cargo doors are being operated
· Parking brake set with one ENG MASTER selected ON
· Parking brake OFF with one ENG MASTER selected ON and the NWS
deactivation pin installed.
· PTU P/B selected OFF
·  PTU operation is inhibited for 40 seconds after cargo door operation
OFF - PTU is deactivated. Selecting OFF extinguishes Fault light. The exception
being for an overheat, the fault light will remain illuminated until the overheat
condition is alleviated.
FAULT - Green or Yellow systems
· Low quantity
· Reservoir overheat - 93°c
· Reservoir low air pressure - 23 psi
Note: After starting engines if the PTU failed to test properly, you may get a
PTU fault on the ECAM. To reset the PTU turn the Yellow Electric pump
ON then OFF after engine start is complete.
7) BLUE ELECTRIC PUMP (Receives power from AC Bus # 1)
AUTO - If AC power is available the electric pump is energized:
· In-flight
· On the ground with at least one engine running
· When the blue pump override switch on the MX panel is selected ON
OFF - The pump is de-energized.
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FAULT - · Low quantity
· Reservoir overheat - 93°c
· Low air pressure - 23 psi
· Low pump pressure - 1450 psi (Inhibited on the ground with engines stopped)
· Pump overheat
8) YELLOW PUMP P/B (Receives power from AC Bus # 2)
ON - The Yellow pump is energized.
OFF - Pump is de-energized.
FAULT - · Low quantity
· Reservoir overheat - 93°c
· Low air pressure - 23 psi
· Low pump pressure - 1450 psi
· Pump overheat
Note: The Yellow pump will run when the cargo door manual selector is set
to either the open or close position, however, the operation of the flight
controls and PTU is inhibited. The cargo door system is a closed loop circuit;
if the door manual selector sticks in the on position after the cargo doors are
opened, the pump will remain energized and the yellow system will overheat.
Turning the Yellow pump switch on will circulate fluid throughout the whole
system, alleviating the overheat condition. Contact MX or Ramp personnel to
correct the problem.
9) ENGINE PUMP P/B
ON - Pump pressurizes when engine is running (3000 psi ±200 psi)
OFF - Pump is depressurized. Selecting OFF extinguishes fault light except for an
overheat. Fault light will remain illuminated until the overheat condition is
alleviated.
FAULT - · Low quantity
· Reservoir overheat - 93°c
· Low air pressure - 23 psi
· Low pump pressure - 1750 psi
10) X-FEED P/B
OFF - The crossfeed valve closes
ON - The X-feed valve opens
OPEN - The X-feed valve is fully open. ON remains illuminated
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11) FUEL PUMP P/B
ON - Pump is energized. Main pumps provide 25 psi, and are fitted with suction
valves to allow gravity feeding of the wing tanks to the engine. The main
boost pump pressure is lower than the center tank boost pump pressure, which
helps to insure that the center tank fuel will be used first.
OFF - Pump is deactivated
FAULT - Low output pressure
1 2 ) MODE SEL P/B
AUTO - Center tank pump control is automatic. The pumps will run for 2 minutes
after engine start, or any time the slats are retracted.
The center tank pumps will be commanded OFF:
· 5 minutes after the CTR tank low level is reached.
· When the wing tank inner cells overfill is sensed, from fuel returned from
the IDG cooling system. In this case, the center tank pumps will remain
off until approximately 1100 pounds of fuel is burned from the wing
tanks.
MAN - The center tank pumps are manually controlled
FAULT - The center tank contains more than 550 pounds of fuel and either wing tank
has less than 11000 pounds. This fault light may illuminate when the center
tank fuel is burned out of sequence, or during refueling.
13) CTR TANK PUMP P/B
ON - Pumps are armed if the Mode Select Switch is in AUTO. The pumps will also
run if the Mode Select Switch is in MANUAL. The pumps provide 32 psi and
are not fitted with suction valve. Therefore, gravity feeding from the center
tank is not possible.
OFF - Pump is deactivated
FAULT - Low output pressure, when pump is operating
14) BATTERY P/B
AUTO - Batteries are connected to the DC BAT bus when:
· On the ground with no other power sources
· APU Starting
· Battery voltage below 26.5V, BCL closes allowing the battery to charge
· Below 100 knots during emergency electrical configuration.
OFF - Battery contactors are open
FAULT - The battery contactors are open due to an abnormal increase in the charging
current
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Note: In the Emergency Power Configuration, Battery #1 powers the static
inverter. Battery #1 also powers the AC Essential Bus when airspeed is
greater than 50 knots. Battery #2 powers the DC ESS Bus.
On the ground the BCL will open if EXT power or APU power is removed
and the battery voltage decreases to 23 volts for 16 seconds. This is to prevent
a total depletion of the batteries.
A minimum of 25 volts is required during preflight. If a condition of less
than 25 volts exists, the batteries must be charged prior to starting the APU.
The BATT switches must be in AUTO to charge. (Approximately 20 minutes
is required with EXT power).
15) GALLEY P/B
AUTO - Main and Secondary galley buses are powered. All galley buses are powered
on the ground with either the APU or EXT power on line.
The Main galley bus is shed when one generator is operating.
OFF - The Main and Secondary galley buses are not powered
FAULT - Load of any generator is over 100% rated output
16) GEN P/B (115/200V 3 phase 400hz 90 KVA)
ON - Field is energized. GLC armed to close.
OFF - · Generator field is de-energized
· Line contactor opens
· Fault circuit is reset
Exception: if a protection fault is caused by a differential fault, the reset
action has no effect after the second attempt.
FAULT - Opens GLC. GCU protection trip.
17) IDG P/B
FAULT - IDG oil temperature above 185°c or low oil pressure
The IDG will disconnect when the p/b is pressed for 3 seconds
18) AC ESS FEED
NORMAL - The AC ESS Bus is supplied from AC Bus #1
ALTN - The AC ESS Bus is being powered by AC Bus #2
FAULT - The AC ESS bus is not being powered
Note: With main generators lost, either the emergency generator or static
inverter supplies the AC ESS bus.
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19) BUS TIE P/B
AUTO - The BTC will open or close automatically to maintain power to AC buses
1&2
One contactor is closed when an engine generator supplies its respective AC
Bus with the APU or EXT power supplying the other bus.
Both contactors will close for a single AC power source.
OFF - Both bus tie contactors are open. APU or EXT power cannot energize the
aircraft’s buses.
20) EXT PWR P/B
AVAIL - External power is connected and is within limits.
The line contactor is open.
Pressed Momentarily – Opens or closes the line contactor.
ON - Line contactor closed. AVAIL light extinguishes.
Note: If EXT power is connected and the frequency and voltage destabilize,
or placed under a high demand, the flap position indicator will begin to flash.
EXT power has priority over the APU. The engine driven generator has
priority over EXT power.
21) APU GEN P/B
ON - The APU generator field is energized. The line contactor is armed to close.
OFF - · The generator field is de-energized
· The line contactor opens
· The fault circuit is reset
FAULT - Protection Trip. Opens line contactor.
Inhibited when APU speed is too low or during EXT power/engine generator
change over.
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Overhead Panel - Part 3
1) PACK FLOW SELECTOR
LO, NORM (auto), HI - LO = 80% of bleed air pressure
NORM = 100% = 44 psi (approx.)
HI = 120%
In the LO position, if the cooling demand is not being met, flow will
automatically increase to NORM (100%).
HI is automatically selected (regardless of switch position) when one pack is
off, or the APU is supplying bleed air.
2) TEMP CONTROLLER
Cold 64° f, Mid 76°f, Hot 86°f
Controls temperature via the Zone controller and trim valves.
The Zone controller has a Primary and Secondary channel.
Failure of the Primary channel causes the hot air and trim valves to close.
The Secondary controller will then provide a zone temp of 76°f / 24°c.
Failure of only the Secondary channel has no effect on temperature
regulation.
With a Dual channel failure, the packs provide a fixed temp of 70° f / 20°c
for Pack 1 and 50° f / 10°c for Pack 2.
If a Trim Air valve fails, optimized temperature control of only that zone is
lost.
Hot Air Fault, Optimized temperature is lost. Trim valves close. Pack 1 will
control the cockpit temperature; Pack 2 will control the cabin temperature to
the mean value of the FWD and AFT selected temperatures.
Chapter 3
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3) PACK P/B
ON - Pack valve is armed to open.
Pack valves will close for:
· Low pneumatic pressure - 8 psi
· Pack overheat - Compressor outlet 260°c
· FIRE P/B is pressed
· Engine start
· DITCHING P/B is selected
Note: Both valves close during the engine start sequence when the mode
selector is set to IGN/CRK. If the second engine is not started within 30
seconds of the first engine, the pack valves will open and then close when the
second engine master is selected to on.
OFF - Pack valve is closed
FAULT - 1) Pack valve disagrees with commanded position or compressor outlet
temp exceeds 230°c four times during one flight.
2) Pack outlet temperature above 95°c.
Pack controller primary channel failure causes the inlet and outlet flaps to go
full open and the pack flow will remain in the last selected position.
With a secondary channel failure ECAM signals related to the pack are lost.
With a dual channel failure the corresponding pack outlet temp is controlled
at 60°f by the pack Anti-ice valve.
4) RAM AIR
ON - The ram air inlet opens. Once the DP is below 1 psi, and the DITCHING p/b
is in normal, the outflow valve will open to approximately 50%. (Provided it
is not in manual)
Ram air is directed to the mixing unit, and should not be opened unless DP is
less than 1 psi. (FM limit)
OFF - The ram air inlet closed
5) HOT AIR P/B
ON - Valve regulates hot air pressure
OFF - The valve closes, Trim Air valves close, and the fault circuit is reset.
FAULT - Duct overheat is detected at 88°c or 80°c is exceeded four times in one flight.
The HOT AIR and TRIM valves close. The Fault light extinguishes when the
duct temp cools below 70°c and OFF has been selected.
Note: If the HOT AIR pressure-regulating valve fails closed, the trim air
valves are driven closed, Pack 1 controls the cockpit and Pack 2 controls the
cabin.
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6) APU BLEED AIR
ON - APU bleed valve armed. Valve opens with APU RPM above 95% and no leak
detected on the APU or left side bleed. When the APU bleed valve opens, the
engine bleed valves are commanded closed.
OFF - APU bleed valve is closed
FAULT- APU Leak is detected
7) ENG BLEED P/B
ON - Bleed valve is armed to open
The valve will close for any of the following:
· If supply pressure is less than 8 psi
· If the APU bleed valve is open
· There is a bleed leak
· Over temperature
· Overpressure
· Start valve is open
· The FIRE p/b is pressed
· Wing/Engine Anti-ice overheat
FAULT - · Overpressure downstream of pressure relief valve
· Bleed overheat/Wing/Engine Anti-ice overheat
· Bleed air leak
· Bleed valve not closed during engine start
8) X BLEED SELECTOR
SHUT - Cross bleed valve closed
AUTO - The valve will open when the APU bleed air valve is used.
The valve will close when:
· Air is supplied by the engines
· Any leaks are detected
· The APU fire switch is pushed
OPEN - Valve is open
9) WING ANTI-ICE P/B
ON - Valves open in flight if pneumatic pressure is available. Bleed air is sent to
the outboard slats 3, 4, & 5. Wing Anti-ice may be tested on the ground, the
valves will open for a 30-second test sequence after a successful test valves
will close and re-arm the system.
In-flight care must be used to maintain bleed temperatures above 150°c to
insure symmetrical de-icing capability during low power settings.
OFF - Valves are closed
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FAULT - · Valve position disagreement
· Low-pressure 13 psi
· A leak is detected
· On the ground, a Wing Anti-ice test sequence of more than 35 seconds.
When a leak is detected, the Wing Anti-ice valves close automatically.
Wing Anti-ice performance bleed penalty should be applied if Wing Anti-ice
will be used from T/O to 1500’ AFE
Note: Wing Anti-ice valves are fail safe closed
10) ENG ANTI-ICE P/B
ON - Valve opens if engine is running. Continuous ignition is turned on.
OFF - Valve is closed
FAULT - Valve / Switch disagreement
Note: Engine anti-ice valves are fail safe open
11) PROBE/WINDOW HEAT P/B
AUTO - Probes and windows are heated in-flight. On the ground, low heat is applied if
one or more engines are running. Windows will go from Low to High when
T/O power is set. TAT probes are not heated on the ground.
ON - Probes and windows are heated
12) DITCHING P/B
NORMAL - Normal system operation
ON - Closes the following:
· Outflow valve (in auto only)
· RAM air inlet
· Avionics vent inlet & extract valves
· Pack control valves
13) LANDING ELEV
AUTO - FMGS data is used for pressurization.
MANUAL - Landing elevation can be selected between –2000 to 14,000 ft
Note: In auto or manual the landing elevation will be displayed on ECAM.
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14) MODE SEL P/B
AUTO - The outflow valve is controlled by one system at a time. There are two
independent controller/systems. Max cabin pressure differential is 8.6 psid,
safety relief 8.9 psid. Cabin warning at 9550 ± 350 ft.
The system will automatically change CPC’s:
· Due to failure of the active system
· 70 seconds after each landing
· Selecting MAN for at least 10 seconds then back to AUTO
MAN - The MAN V/S CTL switch controls the position of the outflow valve using
the backup portion of the #1 CPC
FAULT - Failure of both automatic systems
15) MAN V/S CONTROL SW
UP - Opens the outflow valve. (Mode select in MAN)
DN - Closes the outflow valve. (Mode select in MAN)
16) APU MASTER SW
ON - Power supplied to the APU system; air intake flap opens; fuel isolation valve
opens; the AC powered APU fuel pump will operate (if fuel is not supplied
via aircraft fuel pumps) the APU page on ECAM appears (not during battery
start). APU fuel pump is powered through the static inverter during a battery
start.
OFF - ON and AVAIL lights extinguish, RPM goes to 75% for a 60-120 second
cool down period, at 7% rpm the inlet flap closes.
FAULT - Automatic shutdown for:
· Fire (ground only)
· ECB sensor fault
· Start/running malfunction
Note: In-flight max operating altitude is 39,000 ft. Bleed air is available up to
20,000 ft. Full electrical power is available up to 25,000 ft. at that point the
generator load capacity begins to drop. (Electrical output has priority over
bleed air). The APU may be started up to 39,000 ft. An in-flight battery start
is limited to 25,000 ft.
A320: During Emergency electrical configuration, the APU may start,
however, there may not be sufficient power to close the GLC. Therefore, it is
not recommended to attempt an APU start as it essentially wastes 5 minutes
of the estimated 30 available minutes of battery power.
A319: During Emergency electrical configuration, the RAT will operate
until touchdown starting the APU is recommended
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17) APU START P/B
ON - The APU ECB sequences APU start:
· Starter engaged
· 7% ignition is supplied
· 50% starter cuts out, ignition off
· 95% Avail light comes on APU is available for electric and pneumatic
loads.
AVAIL - The on light extinguishes. The APU can now supply bleed and electrical
power
Note: Max start EGT - 1038°c, three consecutive starts may be attempted
with a 1 minute cooling period between attempts. After the third attempt, a
60-minute cool down is required.
18) SEAT BELT SW
ON - Seat Belt signs illuminate
OFF - Signs extinguish
19) NO SMOKING SW
ON - No Smoking and Exit signs illuminate
AUTO - No Smoking and Exit signs illuminate with gear down
OFF - No Smoking and Exit signs extinguish. Exit signs control system is reset.
Note: The No Smoking, Fasten Seat Belt, and Exit signs illuminate
automatically with an excessive cabin altitude 11300 ft +0/-350 ft regardless
of switch position.
18) EMERG EXIT OFF
OFF - Emergency Exit lights are not armed
19) EMERG EXIT LT SW
ON - Emergency lights, Exit signs and floor path lights illuminate
ARM - Emergency lights and Exit signs illuminate if AC Bus 1 fails.
Floor path markings illuminate if the DC ESS SHED bus fails.
OFF - Lights, signs extinguish
Note: If the associated bus fails, internal batteries will power the lights.
Internal batteries always power the floor path lights.
The internal batteries will last for approximately 12 minutes.
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Overhead Panel – Part 4
1) TMR RESET P/B
ON - Passenger system ON light extinguishes
FAULT - Time delay failure (over 30 seconds) to de-energize the unit door latches
2) AVIONICS COMPT LT P/B
AUTO - Avionics compartment lights controlled by door
ON - Compartment lights on
3) SERVICE INT OVRD P/B
OFF - Communication via service interphone jacks possible on ground, 10 seconds
after landing. ON illuminates to indicate service interphone availability.
Service interphones are disabled to prevent interference through interphone
system and are controlled by the LGCIU’s.
ON - Communication possible without landing gear compression
4) LEAK MEASUREMENT VALVE P/B
OFF - MX function: The respective valves close, hydraulic fluid is shut off to the
components of that system.
5) BLUE PUMP OVRD P/B
ON - The blue electric pump is energized provided the blue electric pump switch is
in AUTO
6) FADEC GND PWR
ON - The FADEC is electrically supplied on the ground
7) APU AUTO EXTING TEST P/B
TEST - MX function: The ON light illuminates. The APU master switch must be on,
The APU fire warning; extinguishing and auto shutdown circuits are tested for
10 seconds. The APU will shut down if it is running.
Chapter 4
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8) RESET P/B
Pressed - APU test circuit is reset
9) FLT CTL P/B
ON - Corresponding computer is active
OFF - Corresponding computer is not active. Selecting OFF for 10 seconds then ON
resets computer.
FAULT - Failure of a computer is detected. Extinguishes when OFF is selected.
Note: ELAC FAULT is normally displayed for 8 seconds after initial power
up or power interruption.
2 ELAC’s: Normal Elevator & Stabilizer control. {Roll normal
Aileron control {LAF normal
{Aileron droop
{Roll direct
3 SEC’s: Spoiler control {Roll normal
Standby Elevator & Stab control {Spoilers S/Brake
{LAF Normal/ALT
(SEC 1&2)
{Roll direct
2 FAC’s: Electric Rudder control {ELAC yaw order
{Yaw ALT
{Rudder Trim
{Rudder Travel Limiter
Note: With a SEC 1 or 2 failure you will Lose # 1 Thrust Reverser. With a
SEC 2 or 3 failure you will Lose #2 Thrust Reverser. Thrust Reversers utilize
SEC data for TLA info.
10) CARGO HEAT HOT AIR P/B (If installed)
ON - The cargo hot air pressure-regulating valve regulates hot air
OFF - Closes cargo hot air valve
FAULT - Duct overheat. The cargo hot air valve closes. The Fault light extinguishes
when the duct temperature cools and OFF is selected.
11) CARGO HEAT AFT ISOL VALVE P/B (If installed)
ON - The cargo inlet and outlet isolation valves open and extraction fan runs.
Provided there is no smoke in the aft cargo compartment.
OFF - The Inlet and outlet isolation valves close, extraction fan stops.
FAULT - Valve(s) not in agreement with selected position.
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12) CARGO HEAT AFT SELECTOR (If Installed)
Cold 40°f, Mid 60°f, Hot 80°f
13) FWD/AFT P/B
Discharges the selected fire bottle and arms the other bottle for the same cargo
bay. DISCH 2 light illuminates 60 minutes after the first bottle is discharged as
a reminder to fire second bottle.
A319- Has only one bottle, which may be used, in either cargo bay. Pressing
the appropriate p/b will discharge the cargo fire bottle into its corresponding
cargo compartment.
14) CARGO SMOKE FWD/AFT
SMOKE - Smoke is detected by both channels in one of the two identical modules. (Or
one channel if the other is faulty)
DISCH- Indicates the fire bottle has been discharged.
15) CARGO SMOKE TEST
Smoke detectors are tested in sequence, the SMOKE light illuminates twice,
the DISCH light illuminates and the cargo heat isolation valve closes.
16) BLOWER & EXTRACT P/B
AUTO - When both switches are in AUTO:
On the ground before T/O power is applied the ventilation system is in the
open circuit configuration. Closed circuit if skin temp is below 40°F.
On the ground after T/O power is applied or in-flight, the vent system will go
to the intermediate circuit if skin temp is above 90°f, then as the skin temp
cools the system will go to the closed circuit.
OVRD - With either switch in OVRD, the system goes to the closed circuit, and air
conditioning air is added to the ventilation air. Blower fan stops if BLOWER
in OVRD.
With both switches in OVRD, air is provided from the air-conditioning system
and is extracted overboard. The skin heat exchanger is not used. The extract
fan remains energized.
BLOWER FAULT - Smoke in the avionics vent duct, Blower Pressure Low or Duct
overheat. An external horn will sound if engines are not running.
EXTRACT FAULT - Smoke in the avionics duct, Extract Pressure Low.
An external horn will sound if engines are not running.
A I R B U S A 3 2 0 / 3 1 9 S T U D Y G U I D E
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17) CABIN FANS P/B
ON - The 2 cabin fans run
OFF - The 2 fans stop
18) ENG MAN START P/B
ON - The start valve opens if the mode select is in either the CRANK or
IGN/START position. Both pack valves close. When engine master switch is
set to ON, both A&B igniters fire, and the LP/HP fuel valves open.
OFF - The start valves are closed unless a start cycle is in progress.
19) N1 MODE P/B
ON - Thrust control reverts from EPR mode to rated N1 mode. Following an
automatic reversion to N1, rated or unrated mode, pressing the p/b confirms the
mode.
Note: If the EPR mode fails the FADEC degrades into either a rated N1 or
unrated N1 mode. Engine limit protections are available in rated N1 mode but
not in-unrated N1 mode. A/THR is lost; therefore Alpha floor is also lost.
OFF - If available, EPR mode is selected.
20) WIPER SWITCH
The rotary switch controls the on side wiper to the desired speed. There is a speed limit of
230 knots to prevent damage to the motor.
21) RAIN REPELLANT
When pressed provides a measured application of rain repellant to the windshield.
Most systems are deactivated.
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A I R B U S A 3 2 0 / 3 1 9 S T U D Y G U I D E
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Pedestal
1) MCDU
The MCDU is the interface between the crew and FMGC. The FMGC is divided into two main parts:
·  The Flight Management portion controls the following:
Navigation
Flight planning
Performance prediction and optimization
Navigation radio management
·  The Flight Guidance portion controls the following:
Autopilot command
Flight director command
Autothrust command
2) SWITCHING
ATT HDG- NORM = ADIRU 1 supplies data to PFD 1, ND 1 and RMI/VOR DME
ADIRU 2 supplies data to PFD 2, ND 2
CAPT 3 = IR 3 Replaces IR 1
FO 3 = IR 3 Replaces IR 2
IR supplies HDG, ATT, and VS to PFD’s
AIR DATA- NORM = ADIRU 1 supplies data to PFD 1, ND 1 and RMI/VOR DME
ADIRU 2 supplies data to PFD 2, ND 2
CAPT 3 = ADR 3 Replaces ADR 1
FO 3 = ADR 3 Replaces ADR 2
ADR supplies AS, ALT and backup VS to PFD
EIS DMC- NORM = DMC 1 supplies data to PFD 1, ND 1 and Upper ECAM
DMC 2 supplies data to PFD 2, ND 2 and Lower ECAM
CAPT 3 = DMC replaces DMC 1
FO 3 = DMC 3 replaces DMC 2
ECAM ND- Allows transfer of SD to either the CAPT or FO ND.
3) RMP
2 RMP’s are installed on the Pedestal and 1 on the overhead panel. Each RMP can control any VHF
radio, #1 and #2 are connected directly to the transceivers, #3 is connected via #1or #2 only. The #1
RMP is available during Emergency Electric Configuration.
Chapter 5
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4) ACP
The audio control panels provide the means to select each com/nav radio, interphone, and PA system.
#3 ACP should always have PA selected so the CVR can record the PA announcements.
5) WX RADAR
Two WX radar systems are installed. Only one transceiver may be used at a time. WX images may be
displayed in any mode except the Plan Mode.
6) ENGINE MASTER PANEL
ENGINE MASTER 1 & 2
ON- LP fuel valve will open.
During an automatic start, the HP valve will open provided the ENG MODE selector is in
IGN/START and N2 is between 10-16%.
During a manual start the MAN START P/B must be on and the ENG MODE selector
must be in IGN/START for the HP valve to open.
OFF- Closes both the LP and HP fuel valves. Resets both channels of the FADEC.
FIRE / FAULT LIGHT
FIRE - Aids the pilot in selecting the correct master switch to turn off in the event of a
fire.
FAULT- Illuminates for an automatic start abort.
A disagreement between the HP valve and the FADEC commanded position.
ENG MODE SELECTOR
CRANK- With the Manual Start P/B selected on, the start valve will open, if N2 is less
than 10%.
NORM- Continuous ignition both A&B igniters are automatically selected on when:
1.) Engine anti ice is selected on
2.) Take-off phase (TOGA/Flex power until 1500’)
3.) Approach Idle selected (Flaps/Slats extended)
4.) In-flight sub idle or surge
IGN/START- If a master switch is on and the N2 is greater than idle, continuous ignition is
selected. (Both A&B igniters)
During an automatic start the A or B igniter will be selected when
N2 is between 10-16%.
During a manual start both igniters are utilized.
On the ground during a normal engine start ignition is automatically cut-off at
43% N2.
Starter Limits: Two attempts of 2 minutes and one attempt of 1 minute. 15
seconds between attempts and 30 minutes after the third attempt.
A I R B U S A 3 2 0 / 3 1 9 S T U D Y G U I D E
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7) TRANSPONDER
Two transponders are installed, wired through the LGCIU’s the transponder is inhibited on the ground
when in AUTO. No automatic switching between 1&2 occurs.
8) SPEED BRAKES
Ground spoilers will deploy at MLG touchdown or during a rejected T/O at 72 knots if they are
armed and or at least one engine is selected to reverse. The ground spoilers will retract when thrust
levers are set to forward idle or advanced above 20° or the speedbrake handle is disarmed. Spoiler
panels 1-5 will deploy to 50° automatically. Panels 1-4 will deploy if selected manually.
The SPEED BRK memo will flash amber on the ECAM when speed brakes are extended and either
engine is above flight idle. (Approximately 35% N1)
9) FLAPS Config. Slats Flaps IAS
1 18° 0° 230 knots
1+F 18° 10° 215 knots
2 22° 15° 200 knots
3 22° 20° 185 knots
Full 27° 40° 177 knots
Flaps will retract from 1+F automatically at 210 knots if not selected by the crew.
WTB will lock with an asymmetry, overspeed, uncommanded movement and symmetrical runaway.
WTB’s cannot be reset in flight.
Slat Alpha Lock occurs when SFCC, utilizing ADIRU supplied information inhibits slat retraction at
high AOA or low speed. With AOA greater than 8.6° or speed less than 148 knots, slat retraction from
1 to 0 is inhibited. The lock is removed at 7.6° AOA or 154 knots.
10) RUDDER TRIM
Rudder pedal deflection is limited as a function of speed. With a double FAC failure the rudder travel
is limited to the deflection limit at the time of the failure. Once slats are extended full rudder travel will
be regained.
Rudder trims at a rate of 1° per second to 20°.
Maximum rudder deflection is 25° from 0–160 knots and reduced from 25° to 3.4° at 160 knots –
Vmo.
10) PARK BRAKE
The park brake handle, when selected to ON will deactivate all other brake modes, deactivates the antiskid
and supplies yellow system pressure to the brakes. The Normal brake system uses Green hydraulic
pressure and the Alternate brakes use Yellow system pressure, backed up by an accumulator.
The Brake and Accumulator indicator reads Yellow system pressure.
Anti skid is available with both normal and alternate brake systems and is not available with the
accumulator.
11) GRAVITY GEAR
3 turns clockwise to gravity extend the landing gear:
Turn 1: Isolates the landing gear from the Green hydraulic system and depressurizes the
system. Cut-off valve closes.
A I R B U S A 3 2 0 / 3 1 9 S T U D Y G U I D E
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Turn 2: Gear door uplocks released.
Turn 3: Gear uplocks released. Gear free falls. MLG utilizes spring assist during extension.
NLG utilizes aerodynamic assist.
After successfully manually extending the landing gear, NWS is not available due to the cut-off valve
being closed and the NLG doors open.

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