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System Description
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(WARNING)
RED MESSAGE (CAUTION)
AMBER MESSAGE (ADVISORY)
CYAN MESSAGE (STATUS)
WHITE MESSAGE Require immediate crew attention. These messages are accompanied by flashing master warning, triple chime attenson with or without voice message or dedicated tone. Require immediate crew awareness and future crew action may be required in the form of alternate system selection or performance limitation. These message are accompanied by flashing master caution and a single chime. Indicate safe or normal system operation which require crew awareness, over and above the dark cockpit philosophy. Indicate minor failures or reduction in systems capability, which require no crew action.

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11/24/15

Overview

The main hydraulic power is supplied from the left and right hydraulic systems. The function of the main system is to supply hydraulic power to different aircraft systems operated by hydraulic power.

The main system has a HYDRAULIC control panel which is found on the center pedestal. The control panel includes pushbuttons and switches to control electrical pumps, shutoff valves and a power transfer unit (PTU). 

The hydraulic synoptic page on the engine indicating and crew alerting system (EICAS) is used to monitor the left and right hydraulic systems.

The left and right hydraulic systems are closed hydraulic systems. They supply filtered hydraulic fluid at the correct pressure and the correct temperature to the aircraft systems that are operated by hydraulic power. Each of the left and right systems supplies primary and secondary hydraulic pressure. This pressure operates the flight controls, landing gear, brakes, nosewheel-steering and thrust reversers.

During usual operation, primary hydraulic pressure is supplied to each system by an engine-driven hydraulic pump (EDP). Secondary hydraulic pressure is supplied by dc motor-driven pumps (DCMPs). The DCMPs are used during increased fluid-flow phases of operation. During ground maintenance operations, the DCMPs are also used to pressurize the hydraulic systems when the engines are stopped.

There is a power transfer unit (PTU) which uses the right hydraulic system pressure to transmit power to the left system. This secondary hydraulic power source operates the landing gear when the left system does not supply sufficient pressure. There is no supply of hydraulic fluid between the left and right hydraulic systems at the PTU.

The hydraulic fluid temperature is controlled by the pump case-drain fluid-circuit and the heat exchanger. If there is a system problem which causes a fluid overtemperature condition, the left or right firewall hydraulic shutoff-valve will automatically close. This will prevent the flow of hydraulic fluid to the related engine. Each firewall hydraulic shutoff-valve (SOV) can also be manually closed by the flight crew from a control pushbutton on the HYDRAULIC control panel.

When the firewall hydraulic SOV is operated, the DCMPs are the only hydraulic pressure source available for the left and right hydraulic systems.

Two system reservoirs are found in the aft equipment compartment. The left hydraulic-system reservoir has a fluid volume of 3.25 U.S. gal (12.30 L). The right hydraulic-system reservoir has a fluid volume of 2.27 U.S. gal (8.60 L).

Servicing to the left and right hydraulic systems is supplied through the ground service quick-disconnects. These quick-disconnects are used to bleed, flush, drain and pressurize the hydraulic systems for ground maintenance. All of the quick-disconnects are installed on a panel near the hydraulic system access door.

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