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EICAS
Suction pressure
GF1310_019
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
RAT DEPLOYMENT HYDRAULIC SCHEMATIC
TO
AIRPLANE
SYSTEMS
RAT
LEGEND
Check valve
indicates direction of flow
Electrical input Filter Relief Valve
System pressure Suction pressure
GF1310_020
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
ACMP POWER AND DISTRIBUTION
Electrical power and distribution using the ACMPs are described as follows:
ACMPs 1B and 2B
Hydraulic systems 1 and 2 are each powered by one EDP used as the primary system pump. Each primary pump is backed up by a single ACMP (one per system) during high flow demand flight phases or failure of the primary pump in flight.
The ACMP is also used for system ground maintenance operation with the control switch in the ON position. Each ACMP is powered by one of the electrical AC busses supplied by the generator installed on the opposite engine (ACMP 1B is connected to AC bus #3 and ACMP 2B is connected to AC bus #2). This will ensure operation of both hydraulic systems 1 and 2 in the case of a single engine failure.
When only one generator is operating, AC busses #2 and #3 are shed. Since their respective AC busses are disconnected during single generator operation, ACMPs 1B and 2B are automatically load shed.
ACMPs 3A and 3B
Hydraulic system 3 is powered by two ACMPs: 3A as the primary system pump and 3B as the back-up pump. Each pump is powered by a different AC bus (ACMP 3A is connected to AC bus #4 and ACMP 3B is connected to AC bus #1). In the event of one, two or three generator failures, both 3A and 3B ACMPs will receive power from one of the remaining generators. AC bus 1 and AC bus 4 are both powered during single generator operation.
ACMP ELECTRICAL POWER SCHEMATIC
GF1310_021
EXTERNAL AND APU ELECTRICAL PUMP OPERATION
External AC power has the capability to power all ACMPs for ground operation when the hydraulic control switch is selected to the ON position.
During ground operation with either the APU or external ground power as the source of electrical power, the AUTO mode of operation is not available. On ground with APU as the single source of electrical power, only one pump at a time is allowed to run with 3A, 3B, 2B and 1B in priority.
In flight with the APU as the single source of electrical power, two pumps (only 3A and 3B) are allowed to run to prevent overloading of the generator.
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
RESERVOIR QUANTITY LIMITS
The table below describes the range of values between the upper and lower fluid quantity limits for each system. The green brackets [ are variable in size and in combination with the filling and digital readout represent the level of quantity in the reservoir for all airplane configurations.
NOTE
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