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HYDRAULIC POWER Table of Contents Vol. 2 13.00.1
Oct 05/06
CHAPTER 13 - HYDRAULIC POWER
TABLE OF CONTENTS
Page
TABLE OF CONTENTS 13.00.1
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 13.00.2
Oct 05/06
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CL.605 Flight Crew Operating Manual
PSP 605.6
HYDRAULIC POWER Description Vol. 2 13.10.1
Oct 05/06
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 13.10.2
Oct 05/06
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.
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