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
　
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