330 parte 3

What is the purpose of the leak measurement solenoid valve located downstream of the pumps?. To control hydraulic pressure. To measure hydraulic fluid levels. To monitor for leaks. To regulate fluid flow.

What is the function of the accumulator in each hydraulic system?. To provide emergency power. To maintain a constant pressure during normal operation. To regulate hydraulic fluid temperature. To control fluid flow to the RA.

On which hydraulic system is the Ram Air Turbine (RAT) installed?. Blue. Yellow. Green. Red.

What is the function of the hand pump installed on the yellow system?. To operate the cargo door. To pressurize the hydraulic fluid. To extend the RAT. To provide auxiliary power.

Where is another pump installed for reservoir filling?. On the blue hydraulic panel. On the green hydraulic panel. On the yellow ground service panel. On the red hydraulic panel.

What happens to the hydraulic supply to heavy users in the green system in case of green low pressure?. It is increased. It is evenly distributed. It is cut off. It is diverted to other systems.

Where is the green reservoir located?. Inside the yellow hydraulic compartment. Inside the MLG bay. Inside the blue hydraulic compartment. Inside the RAT compartment.

Where is the yellow reservoir located?. Inside the yellow hydraulic compartment. Inside the MLG bay. Inside the blue hydraulic compartment. Inside the RAT compartment.

Where is the blue electrical pump located?. Inside the yellow hydraulic compartment. Inside the MLG bay. Inside the blue hydraulic compartment. Inside the RAT compartment.

Where is the yellow electrical pump located?. Inside the yellow hydraulic compartment. Inside the MLG bay. Inside the blue hydraulic compartment. Inside the RAT compartment.

Where are the RAT and related components located?. Inside the yellow hydraulic compartment. Inside the MLG bay. Inside the blue hydraulic compartment. Inside the RAT compartment.

What are the two types of connections for hydraulic pipes?. Removable and permanent connections. Bobbin and permaswage connections. Standard and special fittings. Bobbin and standard fittings.

Where are the manual depressurization valves for each reservoir located?. On the wingtip. On the engine pylon. On the associated service panel. Inside the passenger cabin.

What is the normal pressurization source for the green reservoir?. Engine 1. Engine 2. Pneumatic system. A filter.

How is air pressure regulated for each air pressure unit?. Automatically to 75 psi. Automatically to 50 psi. Manually to 77 psi. Automatically to 22 psi.

What happens if there is a failure in the supply to each reservoir?. The reservoir is depressurized immediately. The reservoir pressure is maintained up to 12 hours. The air pressure increases significantly. The air pressure decreases to 0 psi.

What does the air pressure gauge on each reservoir indicate?. Fluid level. Reservoir temperature. Reservoir pressure. Reservoir volume.

At what pressure does the relief valve operate on the reservoir manifold?. 22 psi. 50 psi. 75 psi. 77 psi.

How are hydraulic pipes identified according to the provided description?. By color code only. By function and direction of fluid flow. By part number only. By color, function, direction of fluid flow, and system identification.

What is the primary purpose of the Ice and Rain Protection System?. To prevent ice formation on the fuselage. To ensure safe operation in icing conditions. To maintain cabin temperature. To improve aerodynamic efficiency.

Which systems provide failure data to the Centralized Maintenance Computer (CMC)?. Wing ice protection and engine air intake ice protection. Wing ice protection and probe ice protection. Wing ice protection and windshield anti-icing. Wing ice protection and potable and waste water ice protection.

How is the wing ice protection system heated?. Electrical heating elements. Bleed air from the pneumatic system. Hot air from the engines. Electrical and hot air combined.

How many Wing Anti Ice (WAI) valves are used for each wing?. One for each slat. One for the entire wing. Two, one for slat four and one for slats five to seven. Two, one for slats one to three and one for slats four to seven.

What is the role of the engine air intake anti-ice valve?. To regulate the flow of fuel to the engine. To control the amount of hot air bled from the HP compressor for ice protection. To monitor engine temperature. To provide feedback to the FADEC.

How is the engine air intake ice protection system status displayed?. On the pilot's primary flight display. On the engine control panel. Through the SDAC and displayed on the ECAM. Via a dedicated ice protection panel.

What is the function of the Probe Heat Computer (PHC)?. Controls heating for static probes, AOA, pitot, and TAT sensors. Monitors the engine performance in cold conditions. Controls the windshield heating system. Controls the heating of fuel lines.

What is the primary function of windshield heating?. To de-ice the windshiel. To defog the windshield. To maintain clear visibility in icing or misting conditions. To heat the cockpit.

How does the windshield heating system operate on the ground and in flight?. It operates at full power on the ground and low power in flight. It operates at low power on the ground and full power in flight. It operates at full power at all times. It operates only in icing conditions.

How is rain removed from the windshield in heavy rain conditions?. By a high-speed fan. By heated glass. By a rain repellent system and windshield wipers. By a water-repellent coating on the windshield.

What is the function of the rain repellent fluid FORALKYL 2211?. To lubricate the windshield wipers. To dissolve ice on the windshield. To remove rain from the windshield. To clean the cockpit windows.

When is the rain repellent system inhibited?. When the engines are running. When the engines are not running on the ground. When the aircraft is in flight. When the windshield wipers are in use.

How is the wing ice protection system divided for each wing?. Into three subsystems. Into four subsystems. Into two subsystems. Into a single subsystem.

Where is the wing anti-ice valve installed?. In the cockpit. In the landing gear bay. In the fixed leading edge of the wing. In the engine nacelle.

Where is the bleed air for engine air intake ice protection sourced from?. The first stage of the engine compressor. The second stage of the engine compressor. The third stage of the engine compressor. The fourth stage of the engine compressor.

How is the engine air intake ice protection system controlled and monitored?. By the Flight Management System (FMS). By the Full Authority Digital Engine Control (FADEC). By the aircraft's pneumatic system. By the Central Maintenance Computer (CMC).

Where is the engine anti-ice valve located?. On the upper right side of the engine. On the lower left hand side of the engine. Inside the cockpit. In the landing gear bay.

What forces contribute to the piston moving to the open position when the solenoid is de-energized?. Only the actuator spring force. The actuator spring force and clock spring forces. Only the air pressure on the retract side. The air pressure on the extend side and mechanical linkage.

How does the Probe Heat Computer (PHC) contribute to probe efficiency?. It cools the probes. It provides backup power. It ensures permanent monitoring of probes. It reduces electrical consumption.

Which probes are heated by the standby system?. All probes including TAT. Only static ports and AOA. Only pitot and static ports. All probes except TAT.

When are the TAT probes heated?. Only on the ground. Only in flight. Both on the ground and in flight. When manually activated.

How is the automatic operation of the probe heating system overridden. By turning off the engines. By using the Probe & Windows Heat P/BSW. By engaging the landing gear. By increasing the aircraft's speed.

What system generates an ECAM and an aural warning in case of a probe heating fault?. The Central Maintenance Computer (CMC). The Flight Warning Computer (FWC). The Air Data/Inertial Reference Unit (ADIRU). The Engine Control Unit (ECU).

What role does the Central Maintenance Computer (CMC) play in the probe heating system?. It provides power to the probes. It transmits fault messages. It controls the heating levels. It overrides the Probe Heat Computer (PHC).

What ensures rain removal from the windshield in heavy rain conditions?. Increased airflow over the windshield. Manual cleaning by the crew. Two independent wipers and a rain repellent liquid. Automatic windshield heaters.

How many Display Management Computers (DMCs) are part of the EIS?. 2. 3. 4. 5.

What function do the Flight Warning Computers (FWCs) fulfill within the EIS?. Display generation. Flight data acquisition. Flight warning and alerting. System monitoring.

How can the clock display be switched between time and date?. By using the UTC selector. By pushing the SET button. By using the navigation panel. By turning off the display.

What does the UTC selector enable on the clock?. Switching to local time. Synchronization with GPS signal. Manual time adjustment. Switching to system time.

How many LCD units are capable of generating and displaying symbols in the EIS?. 4. 5. 6. 7.

What additional capability is available on the A340-500 and A340-600 aircraft regarding the LCD units?. Touchscreen functionality. Display of weather data. Video image display. Night vision display.

Which component sends data to the LCD units for symbol generation and display?. FWCs. SDACs. GPS. DMCs.

How many DMCs are installed in the EIS?. 2. 3. 4. 5.

What type of data do the DMCs primarily process for the EIS?. Navigation data. System alerts. Symbol generation data. Engine performance data.

What does the PFD display on the EFIS provide?. Navigation information. Basic flight information for short-term flight. Engine parameters. Weather radar information.

What is the primary function of the ND on the EFIS. Displaying system warnings. Displaying navigation information. Displaying engine performance. Displaying communication status.

What is the purpose of the EFIS control panel for each pilot?. To control aircraft lighting. To select the display modes. To communicate with ATC. To monitor cabin pressur.

What is displayed on the EWD in the ECAM system?. Synoptic of various systems. Engine parameters and warning messages. Navigation data. Weather radar images.

Where is the SD located in the ECAM system?. In front of each pilot. On the center instrument panel. On the overhead panel. In the aft of the cockpit.

What controls the ECAM displays and operation?. EFIS control panel. ECAM Control Panel (ECP). Flight Warning Computer (FWC). System Data Acquisition Concentrator (SDAC).

What types of messages are shown in the lower area of the EWD?. Navigation data. Weather updates. Warning and caution messages. Engine parameters.

How can pilots control the brightness and operation of the EWD?. Using the EFIS control panel. Using the ECAM Control Panel (ECP). Using the autopilot system. Using the flight management computer.

What is displayed in the upper area of the SD?. Permanent data. Navigation data. System or status pages. Weather information.

Which DMC normally drives the Captain's PFD and ND?. DMC 1. DMC 2. DMC 3. DMC 4.

How is the EFIS reconfiguration achieved?. Automatically only. Manually only. Both automatically and manually. By the Flight Warning Computer.

What triggers the activation of attention getters in the ECAM system?. Data from the GPS system. External weather alerts. Data from the Flight Warning Computers (FWCs). Manual input from the pilot.

How does the redundancy in the EIS architecture affect system display in the event of multiple failures?. Loss of all EFIS and ECAM information. Partial display of EFIS information only. Continued display of EFIS and ECAM information on the LCD units. Display of only ECAM information.

What is the impact of a single SDAC failure combined with a single FWC failure on the ECAM system?. Complete shutdown of the ECAM system. Loss of all warning messages. ECAM system continues to operate. Display of only primary engine parameters.

How does the FWS architecture handle a single internal failure?. It becomes inoperative. It loses some data temporarily. It remains fully operational. It requires manual reset.

What type of data is displayed in the upper area of the EWD?. Warning messages. Engine primary parameters, fuel on board, slat/flap position. Navigation data. System configuration.

Where are advisory indications shown on the EWD?. Right memo area. Lower area. Upper area. Left memo area.

Which mode does the ECAM operate in automatically when a parameter is drifting?. Normal mode. Failure mode. Advisory mode. Manual mode.

In which flight phase does the CRUISE page appear on the ECAM?. Phase 1. Phase 6. Phase 10. Phase 3.

Which pages are displayed in priority during the DOOR phase if the APU or engines are started?. APU or Engine pages. Flight Control page. Landing Gear page. Brake page.

When does the WHEEL page appear during the flight phases 7, 8, and 9?. After engine start. After landing. During takeoff. During cruise.

What message appears on the EWD during flight phases 3, 4, and 5?. "TO INHIBIT". "LDG INHIBIT". "WHEEL INHIBIT". "CRUISE INHIBIT".

How are system pages displayed in manual mode when a system key is pressed?. Automatically. Sequentially. Randomly. Individually.

What type of alert is mainly associated with a Single Chime and a MASTER CAUT amber light?. Level 1. Level 2. Level 3. Status Messages.

What is the highest priority level of alert that requires immediate crew corrective action?. Level 1. Level 2. Level 3. Status Messages.

What type of failures correspond to Level 1 alerts?. Immediate corrective actions. Loss of redundancy. Safety concerns. Audio and visual alerts.

How are Level 2 cautions typically indicated to the crew?. MASTER WARN flashing lights. Single Chime and amber light. Red lights and warning message. Audio alerts only.

In what scenario would a Level 3 warning be triggered?. Routine system checks. Emergency configurations. Maintenance tasks. Crew monitoring.

How is a primary failure distinguished on the ECAM display?. Green box around the failure. Red or amber box around the failure. Flashing lights. Audio alerts.

Which type of failure affects other systems or equipment?. Independent failure. Secondary failure. Primary failure. Routine failure.

What is a secondary failure?. Loss of a system due to a primary failure. Loss of redundancy in a system. Loss of multiple systems simultaneously. Loss of critical equipmen.

How is the advisory mode distinguished in dual display mode. Green box around the failure. Red or amber box around the failure. Pulsing value for the parameter. Flashing lights.

What happens in single display mode on the ECAM?. All systems are displayed automatically. A white ADV message pulses at the bottom. The system pages are displayed on the SD. Audio alerts are triggered.

What are the main functions of the SDACs?. Data acquisition. Data concentration. Data digitization. Data transmission.

What type of data format is used by SDACs to send signals to DMCs?. ARINC 629. ARINC 453. ARINC 429. RS 232.

How are the failures categorized in the context of SDACs?. Primary failures. Independent failures. Secondary failures. Tertiary failures.

What is the primary function of the Digital Flight Data Recording System (DFDRS)?. To monitor real-time flight parameters for pilot reference. To fulfill the mandatory requirements of crash recording. To transmit data to air traffic control for monitoring purposes. To provide entertainment options for passengers during flight.

What components are included in the DFDRS architecture?. Flight Data Interface Unit (FDIU), Linear Accelerometer (LA), Event P/B, Recorder Ground Control P/BSW. Flight Data Recorder (DFDR), Cockpit Voice Recorder (CVR), Flight Data Interface Management Unit (FDIMU), Linear Accelerometer (LA). Flight Data Interface Unit (FDIU), Quick Access Recorder (QAR), Recorder Ground Control P/BSW, Event P/B, DFDR. Flight Data Recorder (DFDR), Linear Accelerometer (LA), Aircraft Tail Number, Fleet Identification.

What is the function of the Flight Data Interface Unit (FDIU)?. To collect various basic aircraft system parameters and convert them for recording. To control the aircraft's flight path and altitude. To collect various aircraft system parameters and recording. To communicate with air traffic control tower.

Where is the FDIU typically located?. In the cockpit center pedestal. In the aircraft center of gravity. In the avionics bay. In the passenger cabin.

What information does the DFDRS Coding Panel provide to the FDIU?. Aircraft tail number, airline identification, fleet identification. Pilot's name, flight route, departure time. Engine temperature, fuel level, cabin pressure. Air traffic control frequency, weather updates, navigation waypoints.

What is the purpose of the Linear Accelerometer (LA) in the DFDRS?. To measure the aircraft's speed. To provide data on three axes of acceleration to the FDIU. To monitor engine performance. To control cabin temperature.

Where is the Linear Accelerometer (LA) installed in the aircraft?. In the avionics bay. In the cockpit center pedestal. In the aircraft center of gravity. In the passenger cabin.

How does the FDIU receive information from the Linear Accelerometer (LA)?. Via the System Data Acquisition Concentrators (SDACs). Via direct cable connection to the DFDR. Through wireless transmission. By manual input from the pilot.

What is the function of the EVENT P/B in the cockpit?. To initiate emergency procedures. To record an event mark in the DFDR memory. To activate the autopilot system. To control cabin lighting.

How many hours of data can the DFDR store?. 10 hours. 25 hours. 48 hours. 100 hours.

How does the EVENT P/B assist technicians in identifying specific events?. By marking events with a timestamp. By highlighting events on the cockpit display. By generating a notification to maintenance personnel. By triggering an alarm in the cockpit.