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Main Pumps
The main pumps meet the needs of normal flight conditions. The main pump draws
fluid from the reservoir through the firewall shutoff valve and delivers it pressurized at
3000 psi to the hydraulically powered aircraft systems. System 1 main pump is enginedriven
pump 1A (EDP 1A) and System 2 main pump is engine-driven pump 2A (EDP
2A). EDP 1A and 2A operate anytime their respective engine is running.
Backup Pumps
Backup pumps for systems 1 and 2 are AC motor pumps (ACMP 1B and 2B). The
operation of ACMP 1B and 2B depends on engine-driven generator output, hydraulic
pump switch position and the flap position. Pumps 1B and 2B are controlled by their
respective three-position toggle switches on the HYDRAULIC Panel labeled AUTO,
ON and OFF.
AUTO Position
With the switches in the AUTO position, the 1B and 2B pumps automatically start
when their respective bus is powered, the associated engine-driven generator is
operating and the flaps are not at zero (flap position is greater than 4°). AUTO is the
normal switch position for flight operations.
Example (see Figure 13-2): When the 1B switch is set to AUTO, the pump will
automatically start with its bus powered (AC BUS 2) when:
• the opposite engine-driven generator (GEN 2) is operating, and
• flap position not at zero (greater than 4°)
ACMP 1B and 2B do not automatically start after an engine
failure or an EDP failure.
NOTE
HYDRAULIC POWER
For Training Purposes Only
May 03
13-3
P I LOT T R A I N I N G GU I D E
Hydraulic System 1 - Shown in-flight with Flaps Extended
Figure 13-2
Hydraulic System 2 - Shown in-flight with Flaps Extended
Figure 13-3
Reservoir
Accumulator
LH ENG
FIRE
PUSH
EMER BUS
AC BUS 2
To Flight Controls,
Ground and Flight Spoilers
3000 PSI Nominal
Supply Line
1B
1A
Firewall
Shutoff Valve
(motor-driven)
WOW
GEN 2
On-line
Flap Not
at 0
P604_13_003
ON
OFF
AUTO
1
Reservoir
Accumulator
RH ENG
FIRE
PUSH
To Flight Controls, Flight
Spoilers, MLG Downlock
Assist Actuators and
Outboard Wheel Brakes
3000 PSI Nominal
Supply Line
Firewall
Shutoff Valve
(motor-driven)
2A
2B
WOW
GEN 1
On-line
Flap Not
at 0
P604_13_004
ON
OFF
AUTO
2
AC BUS 1
EMER BUS
HYDRAULIC POWER
13-4 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
ON Position
With the switches in the ON position, ACMP 1B and 2B will operate, provided their
respective bus is powered and the associated cross-side engine-driven generator is
operating. On the ground, an interlock circuit allows the pumps to operate when the
ACMP switch is selected ON, even if the engine-driven generators are not operating
(see Figures 13-2 and 13-3).
Generator Output and Load Shedding
During normal operations, ACMP 1B operation is controlled by the electrical output
of GEN 2, and ACMP 2B operation is controlled by the electrical output of GEN 1. In
the event of an in-flight engine-driven generator malfunction or an engine failure, the
control logic inhibits any operation of the opposite side ACMP. This function is called
“load shedding” and prevents an electrical overload condition during single-generator
operation. The cross-side generator relationship with ACMP 1B and 2B ensures that a
loss of system 1 and 2 pressure does not occur with any one of the above failures.
Hydraulic Shutoff Valves
Electrically operated hydraulic shutoff valves are installed in the suction lines of EDP
1A and 2A. Valve positions are indicated on the EICAS Hydraulic synoptic page. The
valves are normally open. During an engine fire, the corresponding hydraulic shutoff
valve is motored closed by pressing in the ENG FIRE PUSH switch/light (see
Chapter 9 Fire Protection).
Accumulator and Reservoirs
Each system has an accumulator that stores nominal hydraulic pressure to satisfy
instantaneous demands of aircraft systems and to dampen pressure surges within the
system. Each accumulator is precharged with nitrogen to 1500 psi.
System 1 and 2 reservoirs are hydraulic fluid storage tanks. Each reservoir is a sealed
unit and is filled via the ground service panel located directly below the hydraulic
equipment rack in the aft equipment bay. System 1 reservoir has a capacity of 2.95
liters (0.78 U.S. Gal.). System 2 reservoir has a capacity of 3.93 liters (1.04 U.S. Gal.).
During preflight, a visual inspection should include checks for fluid leaks and
　
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