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DESCRIPTION General 18−10−1 10th-Stage Bleed Air 18−10−2 Description 18−10−2 Components and Operation 18−10−2 14th-Stage Bleed Air 18−10−4 Description 18−10−4 Components and Operation 18−10−5 Bleed Air Leak Detection System 18−10−6 Description 18−10−6 Components and Operation 18−10−7 Controls and Indicators 18−10−10 BLEED AIR Panel 18−10−10 EICAS Display 18−10−11 EICAS Messages 18−10−11 SUMMARY Power Supply and Circuit Breaker Summary 18−20−1 LIST OF ILLUSTRATIONS DESCRIPTION Figure 18−10−1 Pneumatic Schematic 18−10−1 Figure 18−10−2 10th-Stage Bleed Air Schematic 18−10−2 Figure 18−10−3 14th-Stage Bleed Air Schematic 18−10−5 Figure 18−10−4 Bleed Air Leak Detection Sensing Elements and Thermal Switches 18−10−7 Figure 18−10−5 Bleed Air Leak Detection System Capabilities 18−10−9 Figure 18−10−6 BLEED AIR Panel 18−10−10 Figure 18−10−7 EICAS SUMMARY Page − Bleed Pressure Readouts 18−10−11 PNEUMATIC Table of Contents Vol. 2 18−00−1 Oct 05/06 CHAPTER 18 - PNEUMATIC 18−00−1 CL−605 Flight Crew Operating Manual PSP 605−6 TABLE OF CONTENTS Page TABLE OF CONTENTS PNEUMATIC Table of Contents Vol. 2 18−00−2 Oct 05/06 CL−605 Flight Crew Operating Manual PSP 605−6 THIS PAGE INTENTIONALLY LEFT BLANK GENERAL The pneumatic system consists of two separate bleed air systems; 10th-stage and 14th-stage bleed air. The 10th-stage bleed air is supplied from the engines, the APU or an external air source. The 14th-stage bleed air is supplied from the engines. The pneumatic system also includes a bleed air leak detection system that warns the flight crew of possible duct ruptures. Pneumatic Schematic Figure 18−10−1 PNEUMATIC SYSTEM Description Vol. 2 18−10−1 Oct 05/06 CL−605 Flight Crew Operating Manual PSP 605−6 10TH-STAGE BLEED AIR Description The 10th-stage bleed air is supplied from the left and right engine compressor’s 10th-stage, the APU or an external air source. The bleed air is distributed to the various systems by the 10th-stage bleed air manifold. Bleed air from the 10th-stage manifold is used for: • Engine starting; and • Air conditioning and pressurization. 10th-Stage Bleed Air Schematic Figure 18−10−2 Components and Operation 10th-Stage Bleed Air Manifold The 10th-stage bleed air manifold is located in the aft equipment bay. An isolation valve divides the 10th stage into the left and right manifolds. With the isolation valve closed, the left manifold may be pressurized from external air, APU or left engine bleed air. The right engine bleed air normally pressurizes the right manifold. One-way check valves are installed on the engine in the 10th-stage bleed ducts. The valves prevent the reverse flow of manifold air into the engines. Similar valves are also used for the APU and the external ground air connector. PNEUMATIC SYSTEM Description Vol. 2 18−10−2 Oct 05/06 CL−605 Flight Crew Operating Manual PSP 605−6 10TH-STAGE BLEED AIR (CONT'D) Pressure readings for the manifold are derived from two pressure transducers, one for the left manifold and one for the right manifold. The pressure readings for the left and right 10th-stage manifold are displayed on the EICAS SUMMARY page. Isolation Valve The isolation valve is located in the aft equipment bay, and is used to isolate the left and the right manifold. Opening the isolation valve allows air from any of the sources to be supplied to the left or right manifold, as required. The 10th-stage isolation valve is an electrically controlled, pneumatically operated valve, which either fully opens or fully closes. The isolation valve is spring-loaded closed when no 10th-stage bleed air is available, or when electrical control power is lost. The isolation valve is manually commanded open or closed by the 10TH STAGE ISOL switch/light, located on the BLEED AIR panel. The valve may also be automatically commanded open or closed by the following conditions: • Open – during engine starts (starter engagement). • Closed – when a pack overpressure occurs. 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-PNEUMATIC
