ATA 29

Under normal operating conditions and with a low pressure condition in the green system: Yellow system transfers fluid at 3000 PSI through the PTU to pressurize the green system. The blue electric pump transfers fluid at 3000 PSI through the PTU to pressurize the green system. The blue electric pump mechanically transfers hydraulic power through the PTU to pressurize the green system, there is no fluid transfer. Yellow system mechanically transfers hydraulic power through the PTU to pressurize the green system, there is no fluid transfer.

If the blue electric pump fails during a flight, the blue hydraulic system. Is lost for the rest of the flight. Can be recovered by extending the RAT. Can be recovered by means of the PTU. (b) y (c) are correct.

Which component from the hydraulic systems sends the value of system operating pressure to ECAM through the SDAC’s. Pressure relief valve. Pressure transducer. Leak measurement valve. Hydraulic accumulator.

Under normal operating conditions and the PTU PB in AUTO position, la power transfer unit works automatically: When blue hydraulic system is lost. When the pressure difference between blua and yellow system is 500 PSI. When the pressure difference between green and yellow is 500 PSI. Only manually setting the PTU PB in ON position.

When will the RAT be extended automatically on ground: With a complete lost of all hydraulic systems. When the pressure output from blue electric pump is below 1450 PSI. With a complete lost of main electrical generators (Engines & APU. None of the above.

What is the main purpose of yellow system hand pump: Allow the pressurization of the yellow system if the engine driven pump & electric pump fail. Allow the pressurization of green system through the PTU on ground. Allow the operation of cargo doors on ground. None of the above.

On ground (Blue elect pump PB in AUTO position), what condition will cause the blue system to be pressurized (blue electric pump energized and running): Aircraft electrical network energized by at least one engine generator. Aircraft electrical network energized by APU generator. Aircraft electrical network by EXT PWR. Aircraft electrical network with EXT PWR Available.

What is the main purpose if the engine fire valves in the aircraft hydraulic systems. Shut off the flow of hydraulic fluid to the blue/yellow electric pumps when the corresponding Fire PB is released. Shut off the flow of hydraulic fluid to the blue/yellow engine driven pumps the corresponding Fire PB is released. Shut off the flow of hydraulic fluid to the green/yellow electric pumps when the corresponding Fire PB is released. Shut off the flow of hydraulic fluid to the green/yellow engine driven pumps when the corresponding Fire PB is released.

During the first engine start and cargo doors operation, the PTU. Runs automatically to transfer hydraulic power between green and yellow system. Is automatically tested. Is inhibited (Does not run). None of the above.

Which is the main purpose of the priority valves in the hydraulic systems: Cuts off hydraulic power to heavy load users under low hydraulic pressure conditions. Maintain hydraulic power to heavy load users under low hydraulic pressure conditions. Regulate the hydraulic power to all users under low hydraulic pressure conditions. Cuts off hydraulic power to essential users under low hydraulic pressure conditions.

Which component from the hydraulic systems covers transient pressure demands and dampens small pressure and flow changes. Pressure relief valve. Pressure transducer. Leak measurement valve. Hydraulic accumulator.

With the aircraft on ground (BLUE ELECT PUMP PB in AUTO position, engines not running) and the electrical network powered by EXT PWR, how is it possible to pressurize the blue hydraulic system. Setting the BLUE ELECT PUMP PB (hydraulic control panel) in ON position. Setting the BLUE PUMP OVRD PB (maintenance panel) in ON position. Extending the RAT. Through the yellow electric pump and the PTU.

The RAT (ram air turbine) is extended automatically in flight to pressurize the blue hydraulic system, when all hydraulic systems are lost (Blue, green & yellow. True. False.

What is the purpose of keeping the reservoirs pressurized at nominal 50 PSI: Keep the reservoirs always full of fluid. Prevent the movement of fluid inside the reservoirs during aircraft maneuvers. Allow the drainage of the reservoirs more easily. Keep a positive supply of fluid from the reservoir to the pumps to prevent cavitation.

Which panel allows the hydraulic fluid service to all reservoir (blue, green & yellow): Yellow ground service panel. Green ground service panel. Blue ground service panel.

Which is the normal source of bleed air for the hydraulic reservoir pressurization system. 8th stage from HPC of engine 1. The pneumatic system downstream of the precooler. APU. External cart.

When the engines are not running (no pressure sources available), which is the state of the hydraulic reservoirs. Not pressurized. Pressurized at nominal 50 PSI. Pressurized at nominal 3000 PSI (system pressure). None of the above.

Which component from the hydraulic systems protects the system against overpressures, sending the excess pressure directly to return when system pressure reaches 3436 PSI. Pressure relief valve. Pressure transducer. Leak measurement valve. Hydraulic accumulator.

Which hydraulic fluid is monitored to trigger an ECAM warning (reservoir overheat) when its temperature reaches 95C. Pumps cooling and lubrication fluid (case drain). Pump supply fluid. PTU supply fluid . Return fluid.

Which component from the hydraulic systems shuts down the flow of hydraulic fluid downstream of the pump pressure output, to isolate the main users of the hydraulic systems and troubleshoot defective components. Pressure relief valve. Pressure transducer. Leak measurement valve. Hydraulic accumulator.