DESCRIPTION
General 13-10-1
Systems 1 and 2 13-10-2
Description 13-10-2
Components and Operation 13-10-2
System 3 13-10-5
Description 13-10-5
Components and Operation 13-10-6
Controls and Indicators 13-10-8
HYDRAULIC Panel 13-10-9
Hydraulic Synoptic Page 13-10-10
EICAS Messages 13-10-12
SUMMARY
Power Supply and Circuit Breaker Summary 13-20-1
LIST OF ILLUSTRATIONS
DESCRIPTION
Figure 13-10-1 Hydraulic System Distribution 13-10-1
Figure 13-10-2 Hydraulic System 1 Schematic - Shown In-Flight with
Flaps Extended 13-10-3
Figure 13-10-3 Hydraulic System 2 Schematic - Shown In-Flight with
Flaps Extended 13-10-3
Figure 13-10-4 Hydraulic System 2 Equipment Rack 13-10-5
Figure 13-10-5 Hydraulic System 3 Schematic - Shown In-Flight with
Flaps Extended 13-10-6
Figure 13-10-6 Hydraulic System 3 Accumulator Gauge 13-10-8
Figure 13-10-7 HYDRAULIC Panel 13-10-9
Figure 13-10-8 HYDRAULIC Synoptic Page Color Coding (1 of 2) 13-10-10
Figure 13-10-9 HYDRAULIC Synoptic Page Color Coding (2 of 2) 13-10-11
HYDRAULIC POWER
Table of Contents
Vol. 2 13-00-1
Oct 05/06
CHAPTER 13 - HYDRAULIC POWER
13-00-1
CL-605 Flight Crew Operating Manual
PSP 605-6
TABLE OF CONTENTS
Page
TABLE OF CONTENTS
HYDRAULIC POWER
Table of Contents
Vol. 2 13-00-2
Oct 05/06
CL-605 Flight Crew Operating Manual
PSP 605-6
THIS PAGE INTENTIONALLY LEFT BLANK
GENERAL
The Challenger 605 is equipped with three independent hydraulic systems, designated as 1, 2, and
3. All systems operate at a nominal pressure of 3,000 psi to power the primary and secondary flight
controls, landing gear, wheel brakes and nosewheel steering. Operation is automatic, with redundant
hydraulic power sources for primary flight controls and flight spoilers.
Each hydraulic system has two hydraulic pumps; a main pump (A) for normal power, and a backup
pump (B) for supplementary power. System 1 and 2 main pumps are engine-driven pumps (EDPs),
and are designated as 1A and 2A. System 3 main pump is an AC motor pump (ACMP), and is
designated as 3A. All of the backup pumps are ACMPs and are designated as 1B, 2B and 3B.
Hydraulic System Distribution
Figure 13-10-1
HYDRAULIC POWER
Description
Vol. 2 13-10-1
Oct 05/06
CL-605 Flight Crew Operating Manual
PSP 605-6
SYSTEMS 1 AND 2
Description
The major components of systems 1 and 2 are an engine-driven pump (EDP), an AC motor pump
(ACMP), a hydraulic shutoff valve, an accumulator and a reservoir. All components are located in
the aft equipment bay, except for the EDP, which is located on the engine (see Figure 13-10-2
and Figure 13-10-3).
Components and Operation
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 3,000 psi to the
hydraulically powered aircraft systems. System 1 main pump is engine-driven 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,
WOW, 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 13-10-2): 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 is not at zero (greater than 4?.
NOTE
ACMP 1B and 2B do not automatically start after an engine failure
or an EDP failure.
HYDRAULIC POWER
Description
Vol. 2 13-10-2
Oct 05/06
CL-605 Flight Crew Operating Manual
PSP 605-6
SYSTEMS 1 AND 2 (CONT'D)
Hydraulic System 1 Schematic - Shown In-Flight with Flaps Extended
Figure 13-10-2
Hydraulic System 2 Schematic - Shown In-Flight with Flaps Extended
Figure 13-10-3
HYDRAULIC POWER
Description
Vol. 2 13-10-3
Oct 05/06
CL-605 Flight Crew Operating Manual
PSP 605-6
　
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