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.
　
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