糖心logo官网✅_2017 年 4 月 21 日_.手.动.输.入.网.址.联.系.客.服.人.员.lanan_shell
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 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：庞巴迪挑战者605机组操作手册 CL605-HYDRAULIC_SYSTEM
