Embraer 190 - Hydraulic

The correct answer is 3000 psig. This means that all three systems use skydrol hydraulic fluid and operate at a nominal pressure of 3000 pounds per square inch gauge (psig).

The HYD TEMPERATURE INDICATION RED color indicates that the operating limit has been exceeded. This means that the hydraulic temperature has reached a level that is beyond what is considered safe or normal. This could be due to a malfunction or excessive heat in the hydraulic system, which could potentially lead to equipment failure or damage if not addressed promptly.

In the event of engine flameout, the FADEC (Full Authority Digital Engine Control) system will depressurize the respective EDP (Engine Driven Pump) to reduce the torque loads on the engine. This is done to facilitate a windmill restart, which is a technique used to restart the engine using the windmilling effect of the aircraft's forward motion. By depressurizing the EDP, the engine's torque loads are reduced, making it easier to restart the engine using the windmilling effect. Therefore, the statement is true.

The HYD TEMPERATURE INDICATION AMBER DASHED color indicates invalid information or a value out of displayable range. This means that the temperature reading for the hydraulic system is either not available or is outside of the range that can be displayed. This could be due to a malfunction or a sensor issue, and it is important to address and resolve this issue to ensure the proper functioning of the hydraulic system.

The PTU (Power Transfer Unit) assists the landing gear retraction or extension in the event of a right engine or right EDP (Engine Driven Pump) failure. This means that if there is a failure in the right engine or the right EDP, the PTU will help in operating the landing gear, ensuring its proper retraction or extension.

Hydraulic systems are designed to be closed systems, meaning that there is no fluid communication point between different systems. This is done to ensure that the hydraulic fluid remains contained within its intended system and does not mix or transfer to another system. Therefore, it is true that hydraulic fluid cannot be transferred from one system to another in hydraulic systems.

The HYD PRESSURE INDICATION AMBER color indicates a cautionary operating range. This means that the hydraulic pressure is not within the normal operating range, but it is not yet at a critical level. It serves as a warning to the operator to monitor the hydraulic system and take necessary actions to prevent any potential issues or failures.

The correct answer is the primary and secondary flight controls, the landing gear, the brakes, the nose wheel steering, and the thrust reversers. This answer accurately identifies all the components that are powered by the airplane's three independent hydraulic systems. These systems play a crucial role in controlling the flight of the aircraft, operating the landing gear, providing braking power, steering the nose wheel, and enabling the use of thrust reversers for deceleration during landing.

The SYS 1 AND SYS 2 ENGINE PUMP SHUTOFF VALVE BUTTONS (GUARDED) pushbuttons close the hydraulic shutoff valve (SOV), which isolates the respective engine driven pump (EDP) from the associated hydraulic system. This means that the pump is disconnected from the hydraulic system, preventing any flow of hydraulic fluid.

The correct answer is AC ESS BUS. The primary power source for Hydraulic System 3, which is Electric Hydraulic Pump 3A, is powered by the AC ESS BUS.

The hydraulic system logic in flight automatically activates electric pump 3B whenever electric pump 3A fails. This ensures that there is always a backup pump available to maintain hydraulic pressure in the system.

The HYD FLOW LINE WHITE color indicates that the associated flow line is not pressurized. This means that there is no hydraulic fluid flowing through the line and it is not under any pressure.

The quantity measuring system and temperature transducer are located at the reservoir in hydraulic systems 1, 2, and 3. This suggests that the reservoir is the point where the measurements of quantity and temperature are taken. It is likely that the quantity measuring system is used to monitor the level or amount of fluid in the reservoir, while the temperature transducer is used to measure the temperature of the fluid in the reservoir.

When the selector knob is set to AUTO position in flight, the Hydraulic System logic activates the electric pump in case of two scenarios: 1) EDP or engine failure, and 2) Flaps selected to any position greater than 0°. Therefore, both options 1 and 2 are correct.

During takeoff, when the thrust levers are set to TOGA, the Electric Hydraulic Pumps will be activated for 60 seconds. This is done to avoid abrupt hydraulic pressure variations in the event of an engine failure. By keeping the Electric Hydraulic Pumps activated for 60 seconds, it allows for a smooth transition of hydraulic pressure, ensuring the hydraulic system remains stable and responsive during takeoff.

When the selector knob is set to AUTO position, the Hydraulic System logic activates the electric pump in two scenarios:
1. When the flaps are selected to any position greater than 0° and the thrust levers are set to takeoff thrust.
2. When the flaps are selected to any position greater than 0° and the ground speed is greater than 50 kt.
Therefore, the correct answer is 1 and 2.

During an electrical emergency condition, the hydraulic system's overheating protection system will be inhibited, preventing the electric hydraulic pumps from being turned off automatically. This means that the hydraulic power will continue to be supplied, even if there is a risk of overheating. Additionally, the associated EICAS messages HYD HI TEMP and HYD OVERHEAT will also be inhibited, meaning that the flight crew will not receive any warnings or indications of the overheating condition and will be unable to switch off the hydraulic power source.

When the fluid temperature in the hydraulic systems reaches 125°C, the shutoff valve (SOV) will automatically actuate. This action will isolate the EDP (either 1 or 2) from the respective hydraulic flow line.

The correct answer is "on ground." The PTU (Power Transfer Unit) is a system in an airplane that transfers hydraulic power from one system to another. It is only activated when the airplane is on the ground, as it is not needed during flight. Therefore, if the airplane is in flight, the PTU will not be activated.

During takeoff and landing, with the selector knob in the AUTO position, the hydraulic system logic activates the Power Transfer Unit (PTU) if engine 2 or Engine Driven Pump (EDP) 2 fails. This means that if either engine 2 or EDP 2 fails, the PTU will be activated to transfer hydraulic power from the functioning engine or EDP to the failed one, ensuring that hydraulic power is still available for critical functions during these critical phases of flight.

During an electrical emergency, the Hydraulic System 3 accumulator provides hydraulic power to the associated flight controls until the ACMP 3A is powered by the AC ESS BUS. This means that the ACMP 3A is responsible for providing hydraulic power to the flight controls once the electrical emergency is resolved and the AC ESS BUS is operational.

The flow limiter valve is used to reduce the amount of flow provided by the ACMP 3A. This will limit the electrical power that the pump can draw and prevent the electric hydraulic pump from stalling the RAT.

In the event of any system failure, the size of the letters inside the associated distribution box increases to attract the attention of the flight crew. This is important because a system failure can have serious consequences and it is crucial for the flight crew to be immediately alerted to the issue. By increasing the size of the letters, it becomes more noticeable and catches the attention of the flight crew, allowing them to take appropriate action.

The correct answer includes one reservoir, one EDP (Electric Driven Pump), one PTU (Power Transfer Unit), one accumulator, and one electric hydraulic pump.

The Electric Hydraulic Pump 2 is used as a backup for the engine driven pump (EDP 2) and it is powered by the AC BUS 1. This means that in the event of a failure of the engine driven pump, the Electric Hydraulic Pump 2 can provide hydraulic power to the system using the electrical power from AC BUS 1. AC BUS 1 is likely a reliable and stable source of electrical power, making it suitable for powering the backup hydraulic pump.

The HYD QUANTITY INDICATION CYAN color indicates that the reservoir requires refilling. This color is used to alert the user that the hydraulic system is running low on fluid and needs to be replenished. It serves as a visual reminder to ensure that the system is properly maintained and functioning effectively.

In the event of hydraulic system overheating, the HYD 1, 2, or 3 OVERHEAT EICAS warning message will be displayed when the fluid temperature exceeds 145°C.

During landing operations, the Electric Hydraulic Pumps will be activated for 60 seconds to avoid abrupt hydraulic pressure variations in an event of engine failure. This duration allows for a smooth transition and ensures that there is enough time for the hydraulic system to stabilize and prevent any sudden changes in pressure.

The pump unloader valve is used to reduce the discharge pressure of ACMP 3A during its start-up. This will reduce the pump torque and therefore reduce the electrical power required to start the pump.

The PTU (Power Transfer Unit) is a component that transfers power between hydraulic systems. In this case, the PTU consists of a hydraulic pump in Hydraulic System 2, which is driven by a hydraulic motor installed in Hydraulic System 1. This means that the hydraulic motor in Hydraulic System 1 provides the power to drive the hydraulic pump in Hydraulic System 2, allowing for the transfer of hydraulic power between the two systems.

The correct answer is one reservoir, two electric hydraulic pumps, and one accumulator. These components are part of the hydraulic system. The reservoir is where the hydraulic fluid is stored. The electric hydraulic pumps are responsible for pressurizing the fluid and providing power to the system. The accumulator helps to maintain pressure and provide backup power in case of pump failure.

The correct answer includes one reservoir, one EDP (Electric Driven Pump), one accumulator, and one electric hydraulic pump. These components are all part of HYDRAULIC SYSTEM 1.

The Electric Hydraulic Pump 1 serves as a backup for the EDP 1, meaning it is an alternative power source in case the EDP 1 fails. The correct answer, AC BUS 2, indicates that the Electric Hydraulic Pump 1 is powered by AC BUS 2. This means that if AC BUS 2 is functioning properly, it will provide power to the Electric Hydraulic Pump 1, ensuring that hydraulic power is still available even if the primary EDP 1 fails.

Option 2 states that the Electric Hydraulic Pump will be automatically activated during Engine 1 start if the parking brake has been applied within the last 6 minutes. This means that if the parking brake has been applied recently and the engine is being started, the Electric Hydraulic Pump will automatically activate. This is important because the Electric Hydraulic Pump is needed to operate the hydraulic system on the ground.

When the hydraulic fluid temperature increases to 100°C, the HYD 1 (2 or 3) HI TEMP EICAS caution message will be displayed.

The correct answer is "Flaps not set to zero or Landing Gear not up and locked; EDP 1 not fail; Hydraulic reservoir 2 quantity above 12%." This means that for the PTU to be automatically started, the flaps must not be set to zero or the landing gear must not be up and locked. Additionally, EDP 1 must not have failed and the hydraulic reservoir 2 must have a quantity above 12%.

The Electric Hydraulic Pump 3B is the backup for the Electric Hydraulic Pump 3A, which means it is designed to provide hydraulic power in case the primary pump fails. The fact that it is powered by AC BUS 2 suggests that AC BUS 2 is the source of electrical power for the backup pump. This indicates that AC BUS 2 is a reliable and important power source for the hydraulic system.

If the fluid temperature in the hydraulic system reaches 125°C, both Electric Hydraulic Pumps (3A and 3B) will automatically be turned OFF. This is likely a safety measure to prevent damage to the hydraulic system or potential overheating of the fluid.