Two independent subsystems

Four independent subsystems

One systems

No controller

By Oxygen System control and Monitoring applications (OSCM)

Monitor by SDAC

Detected Low Pressure in oxygen distribution line

Detected discharge status of the oxygen cylinder

Detected Low Pressure in oxygen distribution line and confirm the position of the shut off valve

One input from CPCS, one from the atmospheric pressure transducer and one from MASK MAN ON

One input from CPCS only

One input from MASK MAN ON P/B only

One wrench

Two wrenches: one for the nut and one for the counter nut to avoid force onto the material

Two wrenches: one for the nut and bolt to avoid force onto the material

One system for the CAPT, F/O, Third Occupant and Fourth Occupant

Two subsystems: Left hand oxygen subsystem for the CAPT, Fourth Occupant and right hand oxygen subsystem for the F/O, the Third Occupant

Two subsystems: Forward oxygen subsystem for the CAPT, F/O and aft oxygen subsystem for the

By an indicator dot on its starter side

By a pressure switch on generator

Can not check its status

OXY PAX SYS ON (green) when the cabin oxygen is activated by the CPCS cabin low pressure data

OXY PAX SYS ON (amber) when the cabin oxygen is activated by the atmospheric transducer (TPA) or the "Mask Man On" P/B Switch (CPCS data not available)

Both answers are correct

Can only be done on ground (or if the cabin altitude is below 12000ft)

Can only be done in flight (the cabin altitude is above 12000ft)

Can be done on ground or in flight at any time

Stop all refueling, all repairs on fuel and hydraulic systems, all procedures that use flammable material

Do not operate external lightings

Do not operate HF system and carry out maintenance on HF system

In the oxygen cylinder

In the oxygen distribution manifold

In the oxygen cylinder or in the oxygen distribution manifold

In the avionic compartment

In the forward cargo compartment

In the aft cargo compartment

The Pressure that not temperature compensate

The Pressure that temperature compensate by CRDC

The Pressure that altitude compensate by CRDC

Loss of cabin pressure altitude.

Emission of smoke or toxic gas.

All of above

One system for the CAPT, F/O, Third Occupant and Fourth Occupant

Two subsystems: Left hand oxygen subsystem for the CAPT, Fourth Occupant and right hand oxygen subsystem for the F/O, the Third Occupant

Two subsystems: Forward oxygen subsystem for the CAPT, F/O and aft oxygen subsystem for the

No controller

By Oxygen System control and Monitoring applications (OSCM).

Monitor by SDAC

Through the cabin pressure signal from the CPCS (Cabin Pressure Control System) or the atmospheric

Through the cabin pressure signal from the CPCS (Cabin Pressure Control System) and the OSCM

Through the OSCM (Oxygen System Control Monitoring) and the atmospheric pressure transducer.

By a status indicator on its oxygen generator

By a pressure switch on generator

Can not check its status

Crew Shut-off valve close

LP switch senses pressure in the oxygen distribution line is less than the specified value

Both answers are correct.

Electrically controlled, operated independently by two electrical motors

Solenoid controlled and pneumatically operated

Electrically controlled, operated by one electrical motor

Both Engine Bleed Air System (EBAS) are operative in normal configuration, without APU bleed air

Air is supplied from the HP ground cart

No bleed air is available

APU bleed having priority over engine bleed air

APU bleed will supply bleed air only if the X BLEED selector is selected OPEN

APU bleed will supply bleed air only if the ENG BLEED pushbuttons are selected OFF

The A/C is on ground (input from LGERS) and there is no APU nor ENG bleed air supply

The bleed ducts are pressurized (pressure above 20 psi)

All of above

Bleed air pressure regulation (including HP/Intermediate Pressure (IP) transfer) and bleed air

System monitoring and protections

All of above

Leak detection and leak isolation

Leak detection and leak location

Leak detection, leak isolation and leak location

The engine core zone and is subsequently vented overboard

Overboard through pylons outlets

None of above

FAV and OPSOV

MPV and OPSOV

HPV and FAV

Backup a pneumatic protection is done by the overpressure shut-off valve

Electrically controlled and pneumatically operated the overpressure shut-off valve

Electrically controlled and pneumatically operated the fan air valve

Bleed air or compressed air ground cart

Bleed air or compressed air ground cart or A potable water pump

Bleed air or compressed air ground cart or electrical compressor

Yes, the two systems are independent

No, it can cause the contamination to the portable water system

No, you can not use water car and waste car at the same time

Only when PWSP access door is closed

Only when PWSP access door is opened

Only when A/C is energized and fill-mode was not started at the PWIP

The value in steps of 10% of the total potable-water quantity, between 30% and 100%

The value in steps of 25% of the total potable-water quantity

The value in steps of 20% of the total potable-water quantity

It does not matter if the aircraft is energized or not

You can not refill the water tanks if A/C have no electrical

You can only refill the water tanks when Preselection unit is energized

On the ground or during low-altitude flight

Aircraft is on ground and up to 18000 ± 700 ft

Aircraft is on ground and up to 20000± 700 ft

Thought FAP

Thought PWSP

All of above are correct

Water pump pressure

Air pressure (Bleed air or compressed air)

All of above are correct

2

3

4

Flush all galley at the same time

Flush all toilets at the same time

Flush all toilets and GWDUs (Galley Waste Disposal Unit) at the same time

1 lever to open/close the outer cap only

1 lever to open/close the inner flap only

2 levers, one to open/close the outer cap and one lever to open/close the inner cap

Two autonomous subsystems (left and right hand subsystems) with waste balancing

Two autonomous subsystems (left and right hand subsystems) without waste balancing

One subsystem only

The door switch of waste service door send OPEN signal to the vacuum generators

The door switch of waste service door send CLOSED signal to the vacuum generators

The door switch of waste service door send FAIL signal to the vacuum generators

shown on the FAP.

shown on the CDS.

shown on the FAP and CDS.

the cockpit

the cabin.

the cockpit or the cabin.

their seats and from the lavatories.

their seats only.

the lavatories only.

The Flight Attendant Panel (FAP).

Remote Control Center (RCC).

CIDS

they are operation in parallel.

both are active mode.

one is active mode and the other one is in standby mode.

a connection box which has a coding switch.

the address for the location of the DEU-A is done through PIN PROGRAMMING.

the address for the location of the DEU-A is done through software.

through the Decoder/Encoder Units (DEUs) type A.

through the Decoder/Encoder Units (DEUs) type B.

through the Decoder/Encoder Units (DEUs) type A and type B.

a top line data-bus.

a middle line data-bus.

Ethernet bus.

the handset only.

the acoustic devices.

the handset and also through the acoustic devices.

The In-Flight Entertainment Center (IFEC) rack

The IFE control panel, The cabin distribution network

Both answer are correct

ASFC.

OSFC.

ASFC and OSFC.

CMS-ACD, DLCS-ACD, ACMS, LMF.

ADS, MCA, CMS- ACD, ACMS.

CMS- ACD, DLCS-ACD, ACMS, PDMMF.

CMS- ACD.

MCA.

CMS- ACD and MCA.

The Simple Data Loader (SDL)

DLCS-ACD

DLCS_ACD or SDL

a)  the optional Portable Multipurpose Access Terminals (PMAT)

b)  the flight attendant panels(FAP) and the airline cabin laptop (decreased functions).

c)  All of above are correct

the basic architecture gives a wireless access to the cabin crew.

the basic architecture give a wireless connectivity to the passengers.

the basic architecture gives a wireless access to the cabin crew and the optional architecture give a

only through Ethernet and discrete links.

through AFDX, ARINC 429 or discrete links

through Ethernet, ARINC 429 or discrete links

only through Ethernet and discrete links.

through AFDX, ARINC 429 or discrete links.

through Ethernet, ARINC 429 or discrete links

which can replace the A/C paper logbook.

which can flight document.

which can replace the cabin paper logbook

CPIOM.

the OSFC.

the ASFC.

90 KVA , 115 VAC

120 KVA, 115 VAC

150KVA, 230 VAC

2 attempted starts maximum in any case, then a 1 hour cool down period is required prior to the next

3 attempted starts, then a 1 hour cool down period is required prior to the next attempted start

4 attempted starts totally, then trouble shooting if the last attempt is not successful

Forward Avionic compartment

Aft cargo compartment

Rearward of bulk cargo compartment

Cockpit Overhead Panel, EXT PWR Receptacle, Integrated Refuel Panel

Cockpit Overhead Panel, NLG Services Panel, Integrated Refuel Panel

Cockpit Overhead Panel, NLG Services Panel, EXT PWR Receptacle

APU start sequence is same on ground as in flight

Auto start is initiated by ECB automatically in case of In flight Total Engine Flame Out (TEFO)

APU can be auto or manual start on ground

In the event of a critical failure detected during the B.I.T or a protective shut down

In the event of coming fuel pressure lower than limit

In the event of an oil level lower than limit

You could swap DMMs between APUs for trouble shooting

You could replace DMM and ECB at the same time

You could replace DMM with new one

It means low oil level condition

The APU canstill operate for another 60hours at normal oil consumption

It means the oil level to be checked

The ECB will generate the maintenance message

The APU will shutdown automatically if a/c on ground

ECB automatically aborts the start sequence

Monitored by the ECB and provide notification of low fuel pressure on the ECAM

Monitored by the ECB and providelow fuel pressure protective shutdown

Monitored by the ECB andrecorded by CMS

In flight, the protective shutdowns are inhibited even in case of major failures

During emergency or protective shut down there is 60 seconds cool down period

In normal shutdown the ECB decreases slowly the APU speed for a cooldown period

Open at 20 degree in flight and open at 35 degree on ground

Only Fully Open at 45 degree position

Movement during APU operation for regulate air flow

The Hydraulic Actuator

The Electro-mechanical Actuator

The Hydro-Mechanical Actuator

One Ignition Unit, one Ignition Lead, one Igniter Plug

Two Ignition Units, Two Ignition Lead, Two Igniter Plug

One Ignition Unit, Two Ignition Lead, Two Igniter Plug

You must declare the APU as inoperative

You can de-activate the intake flap in open position and continues the APU using within limit time

You can de-activate the intake flap in close position and continues the APU using within limit time

To protect surrounding structures/systems against temperature and handling loads.

To seal the LDCC adequately to make a fully air tight compartment for fire containment and fire

Both are correct.

They equalize the pressure in both sections. (blow-in and blow-out).

Only blow-out: in case of decompression in the cabin.

Only bow-in in case of decompression in the LDCC.

IN/OUT commands.

FWD/AFT commands.

IN/OUT/FWD/AFT commands.

IN/OUT commands.

FWD/AFT commands.

IN/OUT/FWD/AFT commands.

With quick-release fasteners.

With screws.

With sealed strap and tape.

If all the door sill latches are in UP (locked) position.

If all the door sill latches are in DOWN (lowered) position.

If all the door sill latches are in DOWN (lowered) position or in UP (locked) position.

Only installed in the ball mat area.

Only installed in the longitudinal area.

Installed in all area in LDCC.

X and Z direction.

X and Y direction.

Y and Z direction.

One single person.

At least two persons.

At least three persons.

The PDUs after a raised latch operates in brake mode.

All PDUs after a raised latch in load direction are inactive.

The PDUs before a raised latch operates in brake mode.

Carbon Fiber Reinforced Plastic (CFRP).

Alluminum alloy.

Quartz Fiber Reinforced Plastic (QFRP).

Lightning strikes protection, Electrostatic protection.

Electrical current path (bonding), Connection to the earth when the A/C is on the ground.

All of above.

Inside of cockpit.

Outside of cockpit.

Both side can replace.

Titanium.

CFRP.

Alluminum.

In the pressurized arear.

In the unpressurized areas.

In all of aircraft areas.

installed and removed from the inside and outside of the aircraft.

installed and removed from the outside of the aircraft.

installed and removed from the inside of the aircraft.

aluminum alloy

QFRP composite

CFRP composite

Carbon Fiber Reinforced Plastic.

Composite Fiber Reinforced Plastic.

Carbon Fiber Reinforced Product.

Spar box

Attach fittings

Aprons

Gives protection against damage to structural parts, the HF antenna and the ETACS (External and

Gives protection to structural parts, the HF antenna, the ETACS camera, the VOR antenna.

Gives protection to the HF antenna, the ETACS camera, the VOR antenna

By keeping the cockpit door toggle switch in the unlock position

By using the deadbolt to prevent door from closing

By pushing the maintenance switch on overhead panel

By pressure sensors of ISIS system

By pressure sensors of CPCS (cabin pressure control system)

By pressure sensors integrated in CDLCU (cockpit door locking control unit)

Sent from micro-switch that attached to each electrical strike

Sent from the switch in center strike

Based on voting logic of status of three electrical strikes

When cockpit door is opened rapidly

When shear pin of the device break to activate brake assembly

Both of above

Will open into the direction of the cockpit when rapid cabin decompression occurred

For evacuation of the cockpit when cockpit door is blocked

Both of above

Opened from inner side only

Opened/Closed from outside and inside

Opened/Closed from inner side and Opened from outside

Stops the door to prevent it from crashing on A/C skin

Absorbs the movement of the door while it opens or closes

Opens the door in emergency operation

The design profile of guide roller brackets and door stop fittings to prevent the relative movement between guide rollers and guide roller brackets as well as door stop fittings and door frame stop fittings

Under cabin pressure the guide roller brackets lock the guide roller from moving away

Under cabin pressure the door stop fittings cannot move away from door frame stop fittings

The inner and outer handles cannot operate due to the anti-lowering lever fully locks the internal door

The inner handle can be operated

The slide selector lever can be operated

The girt bar disengages from the floor fittings

The girt bar stays connected to the fuselage floor fittings

The girt bar disengage from the slide pack

Checking the bottle pressure status on FAP

Checking a pressure gauge installed on the cylinder in green band

Checking a pressure gauge installed on the cylinder and checking indication on FAP

The door can be closed after acting on safety exhaust plug to release pressure in DEOA (Damper and

The DEOA can be charged with gas on wing for serviceability

Both of above

Eight locking cam windows show green painted surface

An aft hook indicator flag does not protrude

Both of above

Hydraulic pressure is sent to the actuator extension chamber

Hydraulic pressure is sent to both chambers of actuator to prevent the free fall of cargo door

Hydraulic pressure is sent to actuator retraction chamber

a)  When the A/C on ground and pressure inside A/C is 2.5 mbar higher than pressure outside

b)  When the A/C on ground, pressure inside A/C is 2.5 mbar higher than pressure outside, the slide lever

c)  When the A/C on ground, parking brake on, pressure inside A/C 2.5 mbar higher than pressure outside, the slide lever is in the disarmed position

a)  Water flows from faucet stop so we can use toilet in that LAV normally

b)  All the water supply to that LAV stop and the LAV is considered inoperative

c)  Water stops flowing to faucet and still supply to toilet line

a)  Changeover After each flight or after failure

b)  Changeover Only after failure

c)  They work simultaneously