B777 Engines And APU

The EICAS message ENG OIL PRESS R indicates that the engine oil pressure is low. This means that the oil is not being circulated properly to lubricate and cool the engine components. Low oil pressure can lead to engine damage and failure if not addressed promptly.

The left engine thrust reverser is powered by the left hydraulic system. Hydraulic systems are used to generate and transmit power in aircraft, and in this case, the left hydraulic system provides the necessary power to activate the thrust reverser on the left engine. This system is responsible for reversing the direction of the engine's thrust, which helps in decelerating the aircraft during landing.

The right engine thrust reverser is powered by the right hydraulic system. This means that the hydraulic system is responsible for providing the necessary power and pressure to activate and control the thrust reverser on the right engine.

If the required EEC signals are not available to operate the engines in the normal mode, the EEC automatically switches to the alternate mode.

The EICAS message ENG FUEL VALVE R indicates that the spar or engine fuel valve on the right engine has not reached its commanded position. This means that there is an issue with the fuel valve, and it has not fully opened or closed as it should. It could be due to a mechanical problem or a malfunction in the control system. This message alerts the pilot to the potential issue and allows them to take appropriate action to resolve it.

The correct answer is "After START has been selected on the START/IGNITION selector." This is because selecting START on the START/IGNITION selector initiates the engine start sequence, and once the engine has started and stabilized, the FUEL CONTROL switch can be moved to the RUN position to allow fuel flow to the engine for continued operation.

The EICAS message "APU SHUTDOWN" indicates that the APU (Auxiliary Power Unit) has automatically shut down. This means that the APU, which provides power to the aircraft when the engines are not running, has stopped operating without any manual intervention. This could be due to various reasons such as a fault or an abnormal condition detected by the APU controller, or reaching a predetermined limit set by the aircraft's systems.

The EICAS message "ENG REV LIMITED R" indicates that the right engine reverser will not deploy or will be limited to idle on landing. This means that the reverse thrust capability of the right engine is either not functioning properly or has been intentionally limited, and as a result, it will not provide the maximum reverse thrust during landing.

The correct answer indicates that the EICAS message "APU LIMIT" is displayed when an APU limit has been exceeded. This means that the APU, or Auxiliary Power Unit, which provides power to the aircraft when the engines are not running, has exceeded its operational limits or parameters. This could be due to factors such as high temperature, excessive speed, or other abnormal conditions that could potentially damage the APU or affect its performance.

The correct answer is D-TO. D-TO stands for Derated Takeoff, which indicates that an assumed temperature derated takeoff thrust is selected. This means that the engine thrust is intentionally reduced during takeoff based on a calculated assumed temperature, which helps to optimize performance and reduce wear on the engine.

The engine oil quantity is displayed on the secondary engine indications.

The EICAS message ENG OIL TEMP L indicates that the engine oil temperature is high. This means that the temperature of the engine oil is above the normal operating range, which could potentially lead to engine damage or failure if not addressed. It is important to monitor and control the engine oil temperature to ensure the proper functioning and longevity of the engine.

The EICAS message ENG FUEL VALVE L indicates that the spar or engine fuel valve on the left engine has not reached its commanded position. This means that the valve is not in the position it is supposed to be in, which could potentially affect the fuel flow to the engine. It is important to address this issue to ensure proper engine operation.

TO is the thrust reference mode that indicates maximum rated takeoff thrust. This mode is used for normal takeoff and provides the maximum thrust available for the aircraft during takeoff. D-TO and D-TO 1 are different thrust reference modes used for derated takeoff, where the thrust is intentionally reduced below the maximum rated thrust for various reasons such as engine life extension or noise reduction. Therefore, TO is the correct answer as it specifically refers to the mode that indicates maximum rated takeoff thrust.

Auto-relight is a system that is designed to provide flameout protection in an aircraft engine. When a flameout occurs, the auto-relight system activates both ignitors, which helps to reignite the fuel-air mixture and restore combustion in the engine. By activating both ignitors, the system ensures that there is a higher chance of successfully relighting the engine and preventing a complete shutdown. This feature is crucial for maintaining the safety and reliability of the aircraft's engine during flight.

During ground start, a hot start refers to a situation where the combustion process inside the engine starts too early or too rapidly, causing excessive heat buildup. This can occur due to a variety of reasons such as incorrect fuel-to-air ratio, improper ignition timing, or a malfunctioning fuel control system. In such cases, the autostart system will abort the start to prevent any damage to the engine or surrounding components.

The EICAS message ENG STARTER CUTOUT L indicates that the left engine start/ignition selector remains in the START position or the start valve is open when commanded closed.

When the thrust levers are manually positioned to the full forward position during climb with the engine EEC switches in normal, the engines will produce maximum rated thrust.

When the engine EEC switches to the normal mode, manually positioning the thrust levers to the full forward position will result in the engines producing maximum rated thrust.

The correct answer is that the EEC alternates ignitors for successive starts on the ground. This means that during consecutive engine starts, the Engine Electronic Control (EEC) system switches between different ignitors to ensure proper ignition. This helps to distribute wear and tear evenly among the ignitors and ensures reliable engine ignition.

If the APU is in the attended mode, an APU controller failure can cause an immediate automatic shutdown. This means that if the controller responsible for managing and controlling the APU malfunctions or fails, it will trigger a shutdown of the APU system. This is important because the APU is responsible for providing auxiliary power to the aircraft, so any failure in its controller can have significant implications for the aircraft's operations and safety.

Moving the Fuel Control switch to CUTOFF on the ground does not display the Secondary Engine Indications. This is because the Secondary Engine Indications are only displayed when a secondary engine parameter is exceeded, when the displays initially receive electrical power, or when the Fuel Control switch is moved to CUTOFF in flight.

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The EGT Start Limit Line on the EGT Indicator is used to indicate the maximum allowable temperature for engine starting. It is a reference line that helps the pilot monitor the engine temperature during the start-up process. The line is displayed in red to draw attention to it and ensure that the pilot does not exceed the temperature limit. The line is only displayed when the fuel control switch is in CUTOFF and N2 RPM is below idle. Therefore, the statement that the line displays at all times on the ground is incorrect.

The EICAS message ENG CONTROL L indicates that a fault has been detected in the left engine control system. This means that there is an issue with the system responsible for controlling the left engine, which could potentially affect its performance or functionality.

When the Fuel Control switch is placed to RUN with Autostart ON, the engine fuel valve is armed, the engine ignitor(s) is/are armed, and the EEC opens the valve and turns on the ignitor(s) when required. However, the spar fuel valve is not armed when the Fuel Control switch is placed to RUN with Autostart ON.

If the fuel control switch is moved to RUN before the rpm specified in the manual start procedure, the EICAS message ENG AUTOSTART is displayed. This means that the engine is being manually started and the Autostart system is not being used.

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When the reverse thrust levers are pulled back to the interlock position, the auto speedbrakes deploy. This means that the speedbrakes automatically extend when the thrust reversers are activated, providing additional drag to help slow down the aircraft during landing. This helps to reduce the workload on the pilot and improves the overall effectiveness of the thrust reversers in assisting with deceleration.

When the flight crew manually selects the EEC Alternate mode, the reference and target N1 values are displayed on the N1 indication. This means that the engine will operate according to the selected reference and target N1 values, rather than the maximum and commanded N1 values. The EICAS message ENG CONTROL is not displayed and the engine operates in the soft alternate mode, which is not mentioned in the correct answer.

The APU battery does not power the electric start motor, the inlet door, and the fuel valve.

The EICAS In-Flight Start Envelope display does not show the airspeed range for an in-flight start when the engine RPM is below idle and the fuel control switch is in RUN.

The APU can be started on the ground even if no pumps are operating.

The statement "Low oil quantity cannot automatically display the secondary engine display" is incorrect. In an engine oil system, low oil quantity can indeed trigger an automatic display on the secondary engine display. This display is typically designed to alert the flight crew about the low oil quantity and prompt them to take appropriate actions.

The amber REV indication changes to green REV when the reverser interlock is released. This statement is incorrect because the color of the REV indication does not change when the reverser interlock is released. The REV indication remains amber throughout the operation of the thrust reversers.

The correct answer is that the EICAS message ENG FAIL (L or R) is displayed if actual thrust is not increasing to commanded thrust and airspeed is below V1. This means that if the engine is not producing the expected level of thrust and the aircraft's airspeed is below V1 (the decision speed during takeoff), the ENG FAIL message will be displayed. This indicates a potential engine failure or malfunction.