TERCER EXAMEN EM42

The engine and APU fire protection is provided with?. APU with fire derection and engine with fire extinguishing system. Two sub systems, the fire detection and the fire extinguishing system. Fire detecton only.

How is the agent extinguisher discharged into the ENG and APU with the AC on flight: The bottle in the APU is discharged pressing the AGENT P/B SW on the APU fire panel engine the bottle is discharged automatically. The bottle in the engine is discharged pressing the AGENT P/B SW on the fire panel APU the bottle is discharged pressing AGENT P/B SW on the APU fire pane. The bottle in the engine is discharged pressing the AGENT P/B SW on the fire panel APU the bottle is discharged automatically.

The cargo compartment smoke detection is monitored by?. SDCU. CIDS-SDF. FAP.

In case of fie detected on both loops of the engine, the channels provide a fire warning: Engine fire panel, Engine start control panel, CC fire panel. Engine fire panel, Engine start control panel, Master Warning and ECAM display. Engine firer panel, Engine Warning and ECAM display, APA fire panel.

Which statement about Engine and APU fire bottle is correct?. The fire bottle cartridges are explosive remove them after working on the bottle. The fire bottle are located in the FWD compartment. The fire bottle cartridge are explosive remove them before working on the bottle.

What conditions are checked when the engine TEST PB is pressed?. Fire detectors, SDU, warning indications. Fire detection, FDU, waning indications. Fire nozzles, FDU, warning indications.

What can occur on the APU if a fire is detected whit the aircraft on ground?. The APU shut down automatically and the fire extinguishing system is automatically triggered. The APU shut down manually and the fire extinguishing system is automatically triggered. The APU shut down automatically and the fire extinguishing system is manually triggered.

What operating conditions does the APU have?. Electrical power is available whenever the APU operates, but bleed air is shut off above specific limit manufactures. Electrical power is available whenever the APU operates, but bleed air is only available on ground for engine starting and air conditioning. Electrical power and bleed air ae available whenever the APU operates.

How can the cabin fans be stopped to prevent smoke entering in to the cockpit?. Setting OFF the CABin FANS PB on the AIR COND panel. Push AGENT P/B SW on the FIRE panel. Setting OFF the CABin FANS PB on the VENTILATION panel.

Where is the information displayed when CIDS-SDF detects a lavatory smoke detector fault?. E/W display and EXT power receptacle. System display and FAP. E/W display and FAP.

In case of the APU inlet actuator failure, the APU may be dispatched per?. Mell with the inlet OPEN or CLOSED. The APU will only be operational with the inlet deactivated OPEN (for a maximum of 120 days MEL CAT D). Mell with the inlet OPEN or CLOSED. The APU will only be operational with the inlet deactivated OPEN (for a maximum of 10 days). APU inlet actuator is not a MEL item.

How can the air intake flap be operated in case of a failure?. The air intake flap can be opened or closed manually by a manual override dev. The air intake flap can be opened or closed automatically by a manual override. The air intake flap cannot be openend or closed manually this can be done on mode.

What are the three APU modules?. Power Section, Load Compressor, Accessory Gear Box. Fan Section, Load Compressor, Accessory Gear Box. Power Section, Combustion Chamber, Accessory Gear Box.

How is operated the inlet guide vane actuator on the APU?. The pneumatic system provides fuel muscle pressure to operate the inlet guide vane actuator. The fuel system provides fuel muscle pressure to operate the inlet guide vane actuator. The Hydraulic system provides fuel muscle pressure to operate the inlet guide vane actuator.

When does the green AVAIL legend in the START PB/SW come on?. When the APU speed is at 95% rpm. When the APU speed is at 70% rpm. When the APU speed is at 100% rpm.

White is the air for the Pneumatic system bled from? (Engine Bleed). Air is bled from two engine Low Pressure Compressor (LPC) stages, the intermediare pressure (IP) and HP stage. Air is bled from two engine High Pressure Compressor (HPC) stages, the intermediare pressure (IP) and HP stage. Air is bled from two engine High Pressure Compressor (HPC) stages, the intermediare pressure (IP), HP ground power unit.

What are the areas covered by the leak detector system?. PYLON pre-cooler outler area, WING leading edge and belly fairing, APU aft supply duct. PYLON pre-cooler inlet area, MASTER drain and belly fairing, APU compartment area. PYLON pre-cooler outler area, WING leading edge and belly fairing, Mixer Unit area.

What are the consequences if a simple loop on the wings fails?. Maintenance messages AIR BLEED is displayed on the STS pages, CFDS message L(R) WING LOOP INOP MEL dispatch is required. Maintenance messages AIR BLEED is displayed on the STS pages, CFDS message L(R) WING LOOP INOP MEL dispatch is not required. In case of failure the pneumatic system must be deactivated.

How is operated the cross-bleed during a ground start?. The cross-bleed is operated automatically. The cross-bleed must be operated manually. It is not necessary to operate the cross-bleed during a ground start.

How is maintained the HP VLV closed in flight?. In flight, the PRV/HP VLV maintains the valve closed. In flight, the Electronic Control Box (ECB) for IAE V2500-SA engines or the FWC 1 and 2 for the A318/A319 fitted with CFM56 maintains the valve closed. In flight, the Electronic Engine Control (EEC) for IAE V2500-SA engines or the BMC for the A318/A319 fitted with CFM56 maintains the valve closed.

What is the position of the PRV when the APU BLEEDPB/SW is selected in the ON position?. he PRV is maintained Electrically closed. The PRV is maintained Electrically open. Electrically open provided the XBLEED selector is in the auto position.

What statement about Troubleshooting is correct?. During troubleshooting is not necessary to check the integrity of the sense lines because BMC BITE confirms the integrity of the system. During troubleshooting is very important to check the integrity of the sense lines connections because BMC BITE doesn´t confirm the integrity of the system. Troubleshooting for pneumatic system is not available.

What is the procedure to supply the RH/LH aircraft pneumatic system with a ground cart?. Connect the ground cart to the supply duct, set XBLEED selector valve in AUTO position to feed both sides. Connect the ground cart to the supply duct, set XBLEED selector valve in OPEN position to feed both sides. Connect the ground cart to the supply duct, set XBLEED selector valve in SHUT position to feed both sides.

Which of the following is the main component or the Pack Assembly?. Air cycle machine. Main heat exchanger. Pack flow control valve.

Which computer interfaces with other aircraft systems computers to optimize the pressurization and depressurization schedule?. CPC cabin pressure controller. CPC cabin pressure converter. ACSC air conditioning system controller.

How can the Flow Control Valve be dispatched inoperative by MEL?. The Flow Control Valve is not an item MEL. The aircraft may be dispatched per MEL with the valve secured in NEUTRAL position. The aircraft may be dispatched per MEL with the valve secured in CLOSED position.

Which component provides outside fresh air for ventilation in emergency conditions or smoke removal?. RAM AIR INLET DOOR. EMERGENCY RAM AIR INLET. OUTFLOW VALVE.

What statement about ACSCs is correct?. ACSC 1 and the ACSC 2 control the same cockpit and cabin zones. ACSC 2 only is responsible for the flow calculation and sends flow demand signals for ACSC1. ACSC 1 only is responsible for the flow calculation and sends flow demand signals for ACSC2.

What does ACSC mean?. Aircraft Controller System Computer. Air Conditioning System Controller. Air Control System Clearance.

Which component from the lubrication system is utilized to monitor if any of the gearbox internal components is suffering from excessive wear. The pressure filter. The No. 4 bearing scavenge valve. The master magnetic chip detector.

What parameters take into account the EEc to automatically control the recirculation /return of the fuel, as part of the HMS (Heat Management System). Engine Fuel, Engine Oil. IDG oil. All of the above.

Which thrust reverser actuators keep the reversers locked in the ´´stowed´´ position (retracted, forward thrust) by means of integral mechanical locks inside the actuator?. Upper actuators. Lower Actuators. All actuators.

In the engine secondary air systems, what air is used to cool both HP turbine stages (make-up air). Booster stage air (LPC). 10th stage air (HPC). 12th stage air (HPC).

Which component energizes the EEC during engine start (N2<10% rpm). 115 VAC Aircraft electrical network. 28 VDC Aircraft electrical network. The dedicated alternator located in the accessory gearbox.

Which component energized the ignition units through the relay box to provide the spark during engine start?. 115 VAC Aircraft electrical network. 28 VDC Aircraft electrical network. The dedicated alternator located in the accessory gearbox.

Which of the following components from the engine fuel system cuts off the fuel flow (in conjunction with the LP fuel valve and according to Eng. Master Lever or Eng. Fire PB) to the nozzles, during normal or emergency shutdown of the engine?. The Fuel Diverter & Return to Tank Valve. The Over Speed Valve. The Pressure Raising & Shutoff Valve.

What ECAM indications are displayed when the thrust reverser is completely deployed?. The word “REV” boxed amber in the EPR dial. The word “REV” boxed green in the EPR dial. The word “REV” boxed red in the EPR dial. There is no indication on ECAM.

When performing an engine manual start, which is the only automatic action carried out by the EEC?. Opening of the starter valve to turn N2. Provide fuel at 18% N2. Closure of the starter valve and ignition cutoff at 43 % N2.

Which compressor airflow system controls the thermal expansion of the turbine case, in order keep the turbine blade tips clearances within certain limits?. Heat management system HMS. Variable Stator vane system VSV. Activate clearance control system ACC.

What happens if any of the input signals of the EEC channel in control of the engine is lost: The channel in control takes the input signal from the standby active channel. There is an automatic switchover to the standby active channel. The components controlled by the EEC go to the “FAIL-SAFE” position.