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SYSTEMS 1 AND 2 (CONT'D)
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 Figure 13-10-2 and
Figure 13-10-3).
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 搇oad 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 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 1,500 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 accumulator
pressure at 1,500 psi. As well, reservoir quantity, overflow containers and filter bypass indicators
should be checked (see Figure 13-10-4).
HYDRAULIC POWER
Description
Vol. 2 13-10-4
Oct 05/06
CL-605 Flight Crew Operating Manual
PSP 605-6
SYSTEMS 1 AND 2 (CONT'D)
CAUTION
Hydraulic systems are serviced with Skydrol-B, a fire-resistant
fluid easily identified by its purplish color. It is highly corrosive, and
can produce severe skin and eye irritation. Avoid direct exposure
to the fluid.
Hydraulic System 2 Equipment Rack
Figure 13-10-4
SYSTEM 3
Description
The major components of hydraulic system 3 are two AC motor pumps (ACMP 3A and 3B), an
accumulator and a reservoir. ACMP 3A and 3B are located in the left and right side fillets of the aft
belly fairing, respectively. The accumulator, reservoir and ground service panel are located in the
right main wheel well (see Figure 13-10-6).
HYDRAULIC POWER
Description
Vol. 2 13-10-5
Oct 05/06
CL-605 Flight Crew Operating Manual
PSP 605-6
SYSTEM 3 (CONT'D)
Hydraulic System 3 Schematic - Shown In-Flight with Flaps Extended
Figure 13-10-5
Components and Operation
Main Pump
The main pump for system 3 is AC motor pump 3A (ACMP 3A). A two-position toggle switch on
the HYDRAULIC panel, labeled ON and OFF, controls the 3A pump. The 3A pump operates
continuously with the switch in the ON position, provided AC BUS 2 is powered (see
Figure 13-10-5).
Backup Pump
The backup pump for system 3 is AC motor pump 3B (ACMP 3B). The operation of ACMP 3B
depends on hydraulic pump switch position, flap position, engine-driven generator 1 or 2 output,
and emergency power mode activation (ADG deployment). The 3B pump is controlled by a
three-position toggle switch on the HYDRAULIC panel, labeled AUTO, ON and OFF.
AUTO Position
With the switch in the AUTO position, the 3B pump operates when AC BUS 1 is powered,
either 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.
NOTE
ACMP 3B does not automatically start after ACMP 3A failure.
HYDRAULIC POWER
Description
Vol. 2 13-10-6
Oct 05/06
CL-605 Flight Crew Operating Manual
PSP 605-6
SYSTEM 3 (CONT'D)
ON Position
With the ACMP 3B switch in the ON position, the 3B pump will operate, provided AC BUS 1 is
powered.
ADG Deployment
During ADG deployment, ACMP 3B is automatically energized, regardless of its switch
　
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