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Manual Mode
Manual mode is accomplished by placing the respective ACMP control switch into either the “OFF” or “ON”position. Hydraulic pumps 3A and 3B will run when selected to “ON”and their respective bus is powered. In the “OFF”position each pump is inoperative for all operating conditions.
GF1310_018
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
HYDRAULIC CONTROL PANEL (3A/3B SWITCHES) (CONT'D)
Auto Mode
When 3B pump switch is set to “AUTO”the pump starts automatically under one of the following conditions:
.
When the correct electrical logic is determined by the alternating current power centre or ACPC, either slats or flaps are not at the zero degree position and at least one VFG operating.
.
When the primary pump 3A falls below normal system pressure (≤ 1800 psi) in flight.
Ground Operation Inhibits
When the APU is the airplane single source of electrical power, only one ACMP is allowed to run at a time to prevent overloading the APU generator.
Start inhibit is provided for 3B “AUTO”mode of operation (no engine running), to enhance system safety during normal maintenance operations. On ground, the 3B pump requires at least one engine to be operating for normal operations with “AUTO”mode selected.
The 3B pump will not come on automatically (“AUTO”mode selected and flap less than zero degrees), in support of a 3A pump failure on the ground.
Flight Operation
The normal pump switch configuration for in flight hydraulic system 3 operation is 3A pump switch in the “ON”position and 3B in the “AUTO”mode of operation.
The 3B pump will come on automatically (“AUTO”mode selected) in support of a 3A pump failure in flight. When the 3B pump is commanded on due to a low pressure condition of the primary pump, it will remain on for a minimum of 5 minutes (including touchdown) unless “ON”or “OFF”is selected. This is required to prevent ACMP overheating due to continuous restarts if the low pressure alternates above and below 1800 psi.
During single VFG operation ACMPs 1B and 2B are load shed since their respective buses are disconnected from the remaining operative genrator.
Ram Air Turbine (RAT)
When the RAT is deployed and on-speed, it will power the AC ESS bus and the independent hydraulic pump, to ensure that system 3 components are powered at all times (see hydraulic synoptic page in this Chapter).
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
HYDRAULIC SYSTEM 3 SCHEMATIC
TO direction AIRPLANE of flow SYSTEMS
Electrical input ITEM OPERATES
Filter indicates
Pump failurePressure Display toswitches
Relief Valve
EICAS System pressure Pressure
PSI display to transducer
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