A330 L&B - ATA 72

In the event of severe LP or IP shaft overspeed, resulting from an EEC malscheduling of the fuel flow and/or Variable Stator Vanes (VSVs): The Rotor Overspeed protection System (ROS) is designed to automatically shut down the engine. The Low-Pressure Turbine Overspeed (LPTOS) is designed to automatically shut down the engine. The High-Pressure Turbine Overspeed (HPTOS) is designed to automatically shut down the engine.

The VSV Control Unit mainly has a Torque Motor and a Control Servo Valve which control the flow of servo fuel coming from: HP Fuel Pump. LP Fuel Pump. FMU Servo Fuel.

Which computer gives indication of vibration on the engines?. EEC. EIVMU. OPU.

To control the compressors airflow, the system uses: VSV system; 4 LP bleed valves & 3 HP bleed valves, controller by the EEC. VSV system; 4 IP bleed valves & 3 HP bleed valves, controller by the EEC. VSV system; 4 IP bleed valves & 3 HP bleed valves, controller by the PCU.

The LP rotor has the forward fan and the LP shaft, all driven by: The 4-stage LP turbine. The 1-stage LP turbine. The 4-stage HP turbine.

Supplies Electrical Power to the Aircraft Electrical Network: EEC Dedicated Alternator. Integrated Drive Generator (IDG). Fuel Metering Unit (FMU).

The accessory gearbox is connected to the compressor: LP System - N1 Spool. IP System - N2 Spool. HP System - N3 Spool.

The EEC manages the engine thrust by controlling the ____________ position via the electrical current supplied to its TM: VSV Control Unit. Fuel Nozzles. Metering Valve.

The EPR calculation is made for ECC and gets pressure in: P20 / P30. P50 / P20. P50 / P30.

Gives an indication directly to the cockpit if the difference in oil pressures becomes too low: Master Oil Low Detector. Oil Pressure Transmitter. Low Oil Pressure Switch.

The Bleed Valve Solenoid Unit supply the high pressure servo (muscle) air that operates various valves,  ¿what is the pneumatic input source to this Bleed Valve solenoid unit?. 3th stage high pressure compressor (HP3) air. 6th stage inter pressure compressor (IP6) air. 6th stage high pressure compressor (HP6) air.

What is the main parameter for engine power?. N1. EGT. EPR.

Lets most of the fuel in the fuel manifold drain into the drain collector tank at engine shutdown: The Dump Valve. The Pressure Drop and Spill Valve. PRSOV.

Impending fuel filter clogging is detected by: The fuel filter differential pressure switch, located in the LP filter case, which sends a signal to the EEC. The fuel low-pressure switch, located in the LP filter case, which sends a signal to the EEC. The fuel filter clogging sensor, which sends a signal to the EEC.

To keep the oil temperature within specified limits, fan air is supplied to the AOHE by means of an air modulating valve controlled by: The Engine Electronic Controller (EEC), by a hydraulic actuator which uses yellow hyd through a servo valve as servo pressure. The Engine Electronic Controller (EEC), by a hydraulic actuator which uses fuel through a servo valve as servo pressure. The Engine Electronic Controller (EEC), by a electric actuator which uses dc current through an alternate relay.

The "ENG 1(2) THRUST LIMITED" level 2 warning is triggers: When the temperature of the IP turbine disk cooling air reaches a specified limit, firstly the EEC automatically limits the engine thrust up to 55% of the maximum available thrust. When the speed sensor of the LP compressor disk reaches a specified limit, firstly the EEC automatically limits the engine thrust up to 55% of the maximum available thrust. When the temperature of the HP turbine disk cooling air reaches a specified limit, firstly the EEC automatically limits the engine thrust up to 80% of the maximum available thrust.

Its main purpose is to supply power to the FADEC computer when the engine is in operation: EIVMU. Dedicated Alternator. Integrated Drive Generator (IDG.

What is the main function of the FADEC?. For Troubleshooting Engine. For Engine control. For Engine condition monitoring.

The LP fuel Pump gets fuel from airplane fuel supply, increase the fuel pressure and sends the fuel to: HP pump. Fuel / Oil Heat Exchanger (FOHE). FMU.

The "ENG 1(2) TURBINE OVHT" level 3 warning is triggers: When the temperature is still above the specified limit despite the power reduction, after five seconds the EEC will trigger the message. Requesting the Pilot to set the affected engine at idle power. Then if the warning persists, the engine must be shut down. Both answers are True.

During engine operation, the turbine cases heat up and expand at a higher rate than the turbine blades. This expansion increases the blade tip clearance. ¿what system has been designed to control this?. The Bleed Valve system. The Turbine Impingement Cooling (TIC) system. The Low Pressure Turbine Overspeed System (LPTOS).

In the unlikely event of a LP turbine shaft breakage, the LPTOS protection is done by: A dedicated circuit board controlled in the EEC channel A part. A dedicated circuit board located in the EEC channel A part. A dedicated circuit board located in the PCU channel A part.

Which of the following sentence is true about RR Trent 700 Engine: The HP compressor rotor has 6-stages, The IP compressor has 8-stages. The HP compressor rotor has 4-stages, The IP compressor has 6-stages. The HP compressor rotor has 8-stages, The IP compressor has 6-stages.

What is the purpose of AOHE?. Uses LP air to decrease the oil temperature. Uses Fuel system to decrease the oil temperature. Uses HPC air to decrease the oil temperature.

During engine start procedure, when operate the Engine Master Sw to ON: The PRSOV shut-off TM is de-energized and the fuel pressure command the PRSOV to OPEN . Commands the PRSOV to OPEN by energized the shut-off TM and the engine is running. The Engine Master sw. does not control signal to shut-off TM and does not command PRSOV.

The Dedicated Alternator independently supplies the usual source of electricall power to the ECC when: N3 speed is > 8%. N3 speed is < 8%. N2 speed is > 8%. N2 speed is < 8%.

The Bleed Valve Solenoid Unit supply the high pressure servo (muscle) air that operates various valves, What is the pneumatic input source to the Bleed Valve solenoid unit?. 3th stage high pressure compressor (HP3) air. 6th stage inter pressure compressor (IP6) air. 8th stage inter pressure compressor (IP8) air.

The VSV Control Unit mainly has a Torque Motor and a Control Servo Valve which control the flow of servo fuel coming from: HP Fuel Pump. LP Fuel Pump. FMU Servo Fuel.

What is the primary function of the airflow control system in the engine?. To control the thrust power in T.O. To maintain stable airflow through the IP and HP compressors and avoid stall or surge. To control thrust reverser deployment.

How many IP and HP bleed valves are installed in the airflow control system?. Two IP and two HP. Five IP and five HP. Four IP and three HP.

What components are included in the FADEC system?. EEC, FMU, TIC, ICU. PCU, DCU, AOHE, EIVMU. EEC, PCU, OPU, and peripherals.

What is the main function of the EEC within the FADEC system?. To control engine thrust based on manual or au-tomatic thrust demands. To activate the thrust reverser and modulate bleed valves. To control alternator electrical output.

What is the alternate electrical power source for the EEC if the dedicated alternator is unavailable?. The OPU auxiliary supply. A 28 VDC aircraft bus. The aircraft 115 VAC network.

What signal does each VSV actuator use to provide position feedback to the EEC?. LVDT feedback. Mechanical linkage angle. Pneumatic pressure differential.

Where is the "REV" indication displayed?. "REV" indication is shown on the Engine Pres-sure Ratio (EPR) indicator on the EWD. "REV" indication is shown on the N1 indicator on the EWD. "REV" indication is shown on the Thrust Reverser page on System Display (SD).