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FSCU CH 2 DC ESS 4 A10
FSCU PRIM FUEL
XFER CONT
DC BUS 1
1
G9
FUEL PUMP PRIM
XFER
AC BUS 1 D2
FUEL PUMP SEC
XFER
AC BUS 2 2 D2
FUEL FSCU CH 1
DC BATT
1
M11
FUEL L PUMP
CONT
M9
FUEL L PUMP M10
FUEL GRAV
XFLOW
M12
FUEL XFEED
CONT
2
P5
R FUEL PUMP
DC BUS 2
G8
R FUEL PUMP
CONT
G7
SEC FUEL XFER
CONT
G9
APU APU FUEL PUMP DC BATT P4
Fuel Shutoff
FUEL SOV R ENG
DC
EMERGENCY
1
S1
FUEL SOV L ENG S2
FUEL SOV APU S3
FUEL SYSTEM
Summary
Vol. 2 12−20−1
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
POWER SUPPLY AND CIRCUIT BREAKER SUMMARY (CONT'D)
SYSTEM SUB-SYSTEM CB NAME BUS BAR
CB
PANEL
CB
LOCATION
NOTES
Fuel System Tail Tank
T/T XFER SOV
DC ESS 4
A8
T/T XFER SOV
CONT
A9
T/T DUMP SOV
DC BATT 2
P6
T/T DUMP SOV
CONT
P7
FUEL SYSTEM
Summary
Vol. 2 12−20−2
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
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 − Shown In-flight with Flaps Extended 13−10−3
Figure 13−10−3 Hydraulic System 2 − 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 − 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 EICAS Hydraulic Synoptic Page Color Coding (1 of 2) 13−10−10
Figure 13−10−9 EICAS Hydraulic Synoptic Page Color Coding (2 of 2) 13−10−11
HYDRAULIC POWER
Table of Contents
Vol. 2 13−00−1
REV 66, Feb 01/07
CHAPTER 13 - HYDRAULIC POWER
13−00−1
CL−604 Operating Manual
PSP 604−6
TABLE OF CONTENTS
Page
TABLE OF CONTENTS
HYDRAULIC POWER
Table of Contents
Vol. 2 13−00−2
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
THIS PAGE INTENTIONALLY LEFT BLANK
GENERAL
The Challenger 604 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
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
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
　
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