天堂岛精品🔇_91永久海外地域网名高新_.手.动.输.入.网.址.联.系.客.服.人.员.lanan_shell
DESCRIPTION General 14−10−1 Wing Anti-Ice System 14−10−1 Description 14−10−1 Components and Operation 14−10−2 Engine Cowl Anti-Ice System 14−10−4 Description 14−10−4 Components and Operation 14−10−5 Windshield/Window Anti-Ice System 14−10−6 Description 14−10−6 Components and Operation 14−10−7 Air Data Probes and Sensors Anti-Icing 14−10−8 Description 14−10−8 Components and Operation 14−10−9 Ice Detection System 14−10−10 Description 14−10−10 Components and Operation 14−10−11 Controls and Indicators 14−10−11 ANTI-ICE Panel 14−10−12 EICAS Messages 14−10−13 EICAS Messages – Wing Anti-Ice System 14−10−13 EICAS Messages – Engine Cowl Anti-Ice System 14−10−13 EICAS Messages – Windshield/Window Anti-Ice System 14−10−13 EICAS Messages – Air Data Probes and Sensors Anti-Icing 14−10−14 EICAS Messages – Ice Detection System 14−10−14 SUMMARY Power Supply and Circuit Breaker Summary 14−20−1 LIST OF ILLUSTRATIONS DESCRIPTION Figure 14−10−1 Wing Anti-Ice System 14−10−2 Figure 14−10−2 Wing Anti-Ice Components 14−10−3 Figure 14−10−3 Cowl Anti-Ice System 14−10−5 ICE AND RAIN PROTECTION Table of Contents Vol. 2 14−00−1 Oct 05/06 CHAPTER 14 - ICE AND RAIN PROTECTION 14−00−1 CL−605 Flight Crew Operating Manual PSP 605−6 TABLE OF CONTENTS Page TABLE OF CONTENTS LIST OF ILLUSTRATIONS DESCRIPTION Figure 14−10−4 Windshield/Window Anti-Ice System 14−10−7 Figure 14−10−5 Air Data Probes and Sensors Anti-Icing System 14−10−9 Figure 14−10−6 Ice Detectors 14−10−11 Figure 14−10−7 ANTI-ICE Panel 14−10−12 ICE AND RAIN PROTECTION Table of Contents Vol. 2 14−00−2 Oct 05/06 CL−605 Flight Crew Operating Manual PSP 605−6 Page GENERAL There are four anti-iced areas on the Challenger 605: • Wing leading edges; • Engine cowls; • Windshields and windows; and • Air data probes. The wing leading edges and the engine intake cowls are anti-iced using engine 14th-stage bleed air. The windshields, windows and air data probes are anti-iced using electrical power. An ice detector system provides EICAS indications of ice accumulation. Anti-icing of the aircraft tail surfaces is not required. WING ANTI-ICE SYSTEM Description The left and right wing leading edges are anti-iced using pressure-regulated 14th-stage bleed air, distributed by wing anti-ice ducting and piccolo tubes. The system is controlled by the WING ANTI-ICE switch, located on the ANTI-ICE panel. The WING ANTI-ICE switch normally controls the left and right wing anti-ice valves, via wing-mounted control sensors and the wing anti-ice controller. An isolation valve allows both wings to be anti-iced from a single bleed source via a crossover duct. Panel lights and EICAS messages provide indications of system status during operation. ICE AND RAIN PROTECTION Description Vol. 2 14−10−1 Oct 05/06 CL−605 Flight Crew Operating Manual PSP 605−6 WING ANTI-ICE SYSTEM (CONT'D) Wing Anti-Ice System Figure 14−10−1 Components and Operation Anti-Ice Ducts Bleed air, taken from the 14th-stage bleed air manifold, is ducted to the wing and ejected from the piccolo tubes onto the inner surfaces of the leading edges. After heating the leading edges, the air is exhausted overboard through louvers located beneath each wing leading edge. The piccolo tubes extend the full length of the leading edges. ICE AND RAIN PROTECTION Description Vol. 2 14−10−2 Oct 05/06 CL−605 Flight Crew Operating Manual PSP 605−6 WING ANTI-ICE SYSTEM (CONT'D) Wing Anti-Ice Components Figure 14−10−2 Wing Anti-Ice Valves The left and right wing anti-ice valves are electrically controlled, pneumatically operated, pressure-regulating shutoff valves. The valves are spring-loaded to the closed position when no 14th-stage pressure is available, or electrical control power is lost. The wing anti-ice system is normally operated in the NORM mode. A backup mode (STBY mode) exists should NORM 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-ICE_and_RAIN_PROTECTION
