330

The primary purpuse of the No Break Power Transfer (NBPT) is: to connect two IDGs to the same busbar during flight. to avoid under all conditions a tranfer with a power break. to avoid AC power source transfer with a power break only on the ground.

When performing an EMER GEN TEST without hydraulic power: first the green hydraulic pump pushbutton must be pressed. the battery bus automatically supplies the green hydraulic pump. the green hydraulic system is automatically pressurized.

During an Automatic Landing and before touchdown, when the pilot puts both thrust levers to idle, what happens?. Autothrust disengages and the ground spoilers automatically active if they are in the armed condition. Autothrust continues to controm the engine power settingd until thrust reversers are deployed. Autothrust continues to be engaged until ground spoilers are activated.

The flight Envelope part of the FMGEC covers: Acquisition and monitoring of varius aircraft parameters, only. Detection of abnormal flight conditions, only. Acquisition and monitoring of varius aircraft parameters and speed envelope computation.

there is a north reference switch on the main instrument display, what is its purpose?. to keep the map facing North when turning. to swap the heading referencebetween true and magnetic North. to display the distance from current position to the north pole.

the galley and toilet air extraction system is controlled by: the avionics Equipment Ventilation Controller (AEV) which also controls the air conditioning bay ventilation. a ventilation controller (VC) which also controls any cargo compartment options. a zone controller (ZC) which aldo monitors the wing anti-ice system and air conditioning.

how do the forward and aft outflow valves operate?. in automatic mode only under the control of one cabin pressure controller CPC at a time. in automic mode or in manual mode or in mixed mode. in automatic mode only under the control of the flight management guidance and envelope.

the function of each pack controller is to ensure: the airflow regulation and basic temperature controls. the airflow regulation control only. the fine adjustment of the temperature control only.

the trim air valves are controller by: the pack controllers for the basic temperature regulation. two zone controllers for the fine temperature adjustment. one zone controller for the fine temperature adjustment.

the trim air shutoff valve opens: under control of the zone controller when there is a failure in the trim air supply. under direct control of a trim air pushbutton on the overhead panel. when there is one HOT AIR pushbutton in the Off position.

how many safety valves are there and what do they prevent?. there are two and they prevent positive and negative differential pressure. there is only one and it prevents negative differential pressure only. there are three and they prevent excessive positive and negative.

the lavatory and galley extraction fan operates continuously: In flight and on the ground. in flight only. on the ground and in flight when Dp is less than 1 psi.

To supply the maintenance busses only: with external power A connected and the green AVAIL light on the EXT PWR pushbutton illuminated the MAINT BUS switch is in the ON position. with any generator coupled to the network the MAINT BUS switch is in the ON position. with APU generator or external power connected the ON light on the EXT PWR pushbutton illuminated the MAINT BUS switch is the ON position.

The galley supply system is mainly controlled by: circuit breakers and a dedicated control box. the remote control circuit breakers RCCBs and the Electrical Contactor Management Units ECMUs. the Generator Control Units (GCUs) and shedding relays.

How is it possible to get access to the avionics compartment, from inside the aircraft?. By using the access hatch located in the passenger compartment between the forward passenger doors. There is no access from inside it is only possible from the ladder located in front of the Nose Landing. By using the access hatch located in the cockipt aft of the captain seat.

When do you use the split function of the cargo loading system?. when full width containers are loaded. when half width containers are loaded along. when half width containers are loaded in pairs.

The cargo loading system is: A: B: C: electrically powered and fully automatic. hydraulically powered and semi automatic. electrically powered and semi automatic.

How is the Power Drive Unit (PDU) de-energized, when a cargo container is locked in place?. PDU are always energized provided the joystick is operated. By a microswitch on the XZ latches. By a proximity switch on yhe XZ latches.

The fwd and aft cargo loading system control panels are: similar except that only the forward control panel has a manual XZ guide lowering lever. similar except that only the aft control panel has an electrical Y guide Switch. similar except that only the foorward control panel has the two electrical Y guide switches.

Is it possible to load or unload the cargo compartments if the cargo loading system is not electrically powered?. yes but the loading or unloading has to be done manually. yes because the cargo loading system can be supplied by the aircraft batteries. no the cargo compartments cannot be loaded or unloaded without electrical power.

The avionics smoke detectors are connected to. the smoke detection control unit SDCU. the fire detection unit FDU. a ground reset has to be made.

Before an auto extinguishing ground test, the ground crew should be warned because. the APU fire bottle will be discharged. the external APU fire warning will be triggered. a ground reset has to be made.

The APU auto extinguishing function is controlledd by. the APU Fire Detection Unit FDU. the Smoke Detection Control Unit SDCU. the Automatic Fire Extinguishing Control Unit AFECU.

If smoke is detected in the forward cargo compartment, pressing the FWD AGENT pushbutton causes: the SMOKE warning to be reset. the bottle 1 to be discharged in the forward cargo compartment bottle 2 being reserved for the aft cargo compartment. the bottle 1 and the bottle 2 will discharge in the forward cargo compartment.

What happens when a fire is detect in a waste bin. Automatic extinguishing occurs. warnings are sent to the cockipt and cabin. A warning is sent to the cabin and the indicator strips discolour.

Which surfaces are used for the maneuver load alleviation function. Ailerons and spoilers 1 and 2. Ailerons and spoilers 4 5 and 6. Only the spoilers.

The "turn coordination" controls and monitors the rudder deflection. through the rudder trim motors. by control of the Travel Limitation Unit TLU. through the way damper actuation.

The Back up Yaw Damper Unit (BYDU) provides. turn coordination only. dutch roll damping only. dutch roll damping and turn coordination.

In the event of a temporary complete loss of electrical power, can the aircraft be mechanically controlled. No, the aircraft is fly by wire and cannot be controlled without electrical power. Yes, longitudinal control can be achieved through the trim wheels and lateral control through the pedals. Yes, the sidestick has mechanical back-up links which control hydraulic valves to the control surfaces.

If flight control primary computer (FCPC) 1, 2 and 3 have failed. the flight management and guidance computers FMGECs provide pitch control. pitch control can only be achieved from the trim wheels. pitch control is controlled by any flight control secondary computer (FCSC) without autotrim.

What is the purpose of the alpha-lock function. to prevent slats and flaps retraction in low speed or high angle of attack. to extend the slats automatically. to prevent slats retraction in low speed or high angle of attack.

during automatic refueling, with 80 tons preselected, the trim tank receives fuel. only when all other tanks are full. at the same times as the other tanks. only when both inner tanks are full.

the switching between the Fuel Control and Monitoring Computers (FCMCs) is performed. automatically at each landing. automatically by internal monitoring. automatically during refueling.

the A330 APU fuel feed is taken from. the aft section of the LH inner tank. the center tank collector cell. the LH inner tank collector cell.

selection of automatic refueling on the Refuel/Defuel (R/D) panel. overrides and inhibits all automatic main transfer. inhibits all fuel control and monitoring computer FCMC commands. overrides any manual transfer selection.

What MCDU inputs would the pilots normally enter at the beginning of a flight, to allow the fuel system to operte accurately. Zero fuel weight and zero fuel centre of gravity (C of G). MAC (Mean Aerodynamic Chord ) figure and zero fuel weight. Zero fuel C of G and remaining fuel.

if the centre fuel tank is empty and fuel is being transferred by the trim transfer pump, which of the following would cause the pump to stop. the pump pressure switch detects low pressure after 30 seconds. the pump will not stop, after 10 minutes it switches to low flow mode.

The landing gear operation is controlle by. No 1 LGCIUand No 2 LGCIU as stand-by. No 1 LGCIU on retraction and No 2 LGCIU on extension. Either LGCIU during each cycle.

If either of the mind passenger doors are opened what happens to the engine scan lights. they will illuminate the engine to allow for ice detection. they will reduce in light intensity if illuminated from 100 lux to 20 lux. they will turn off if illuminated.

the take-off and taxi lights on the nose landing gear go off automatically when. the landing gear is no longer downlocked. when the landing gear iss fully retracted. the lights will remain illuminated until the crew manually turn them off.

the navigation lights are energised by. 28V DC. 115V AC. 28V DC on ground and 115v AC on air.

What is the purpose of the ignition units which supply the igniter plugs. To convert aircraft 115V AC to direct current. to convert aircrfat 28V DC to 115V AC. to convert aircraft 115V ac to high energy pulses.

what happens if a failure is detected during an automatic start. the EEC aborts the start sequense and dry cranks the engine. a manual start must be initiated. the operator must shut down the engine.

the turbine impigngement cooling valve. is pneumatically controlled and operated. is electrically controlled, spring loaded close. is electrically controlled, spring loaded open.

the turbine impigngement cooling valve uses. intermediate compressor fourth stage air. fan air. high pressure compressor air.