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14th-stage bleed air from the engines to the manifold. The 14th-stage valves are electrically
controlled, pneumatically operated valves, which either fully open or fully close. The bleed air
valves are spring-loaded open when no 14th-stage bleed air is available, or when electrical
control power is lost.
The valves are manually commanded open or closed by the L (R) 14TH STAGE switch/lights,
located on the BLEED AIR panel. The valves are automatically commanded closed when the
associated ENG FIRE PUSH switch/light is pressed. However, when bleed air is no longer
available after engine N2 spools down, the valve will reopen regardless of the ENG FIRE PUSH
switch/light position.
Valve status is indicated by the respective switch/light CLOSED annunciation (see
Figure 18−10−3).
Bleed air temperatures and pressures from the engine compressor 14th-stage are unregulated,
and therefore dependent on engine power settings. Temperatures and pressures can reach
950°F (510°C) and 215 psi (1482 kPa) at full thrust.
BLEED AIR LEAK DETECTION SYSTEM
Description
The bleed air leak detection system monitors the pneumatic ducting downstream of the 10th-stage
and 14th-stage bleed air shutoff valves and wing anti-ice valves, along the fuselage, pylon and
wing areas.
Bleed air leaks that occur between the engine and the engine bleed air shutoff valves are detected
by the engine and jet pipe/pylon overheat detection system. Refer to Chapter 9, Fire Protection.
To detect bleed air leaks, the 10th-stage and 14th-stage bleed air leak detection system uses
sensing elements (loops) for bleed air ducting in the aft equipment bay, the portion of the cowl
anti-ice ducting which passes through the engine pylon, and for the wing anti-ice ducting passing
through the fuselage.
Thermal switches detect bleed air leaks in the leading edge portion of the wing anti-ice ducting.
PNEUMATIC SYSTEM
Description
Vol. 2 18−10−6
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
BLEED AIR LEAK DETECTION SYSTEM (CONT'D)
Bleed Air Leak Detection Sensing Elements and Thermal Switches
Figure 18−10−4
Components and Operation
Bleed Leak Detection
The bleed air ducts are constructed of stainless steel, insulated, and encased by a protective
outer cover. A series of holes are drilled at designated locations in the outer cover, and sensing
elements are installed adjacent to these holes. If a bleed air duct leak develops, these holes
direct the escaping hot air toward the leak detection sensing elements.
Sensing Elements
The bleed air leak detection sensing elements operate in a similar manner to the sensing
elements used in the engine fire detection system.
The 10th-stage manifold uses a dual-loop sensing system. On a dual-loop system, both loops
must detect a leak before a duct overheat warning is given.
The 14th-stage bleed air manifold and the center fuselage wing anti-icing ducts are monitored
by single-loop systems.
PNEUMATIC SYSTEM
Description
Vol. 2 18−10−7
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
BLEED AIR LEAK DETECTION SYSTEM (CONT'D)
Thermal Switches
Thermal switches are used in the leading edges of the wings to detect uncontrolled leakage of
the anti-icing piccolo tubes. Should a piccolo tube rupture or a clamp fail, the thermal switch
closest to the leak will trigger an overheat warning.
Bleed Air Leak Detection Units
Each sensing element is connected to its respective overheat detection unit, which monitors the
resistance of its loop. When the resistance decreases to the warning trip point, the bleed air leak
detection unit prompts EICAS messages, as well as aural and visual warnings, to alert the flight
crew of an overheat condition.
For the 10th-stage ducts, the overheat warning signal will cause the following warnings to occur:
• L (R) 10TH DUCT warning EICAS message is displayed;
• MASTER WARNING switch/lights illuminate flashing;
• “BLEED AIR DUCT” aural warning sounds; and
• Respective red DUCT FAIL light on the BLEED AIR panel illuminates.
For the 14th-stage ducts, the overheat warning signal will cause the following warnings to occur:
• L (R) 14TH DUCT warning EICAS message is displayed;
• MASTER WARNING switch/lights illuminate flashing;
• “BLEED AIR DUCT” aural warning sounds; and
• Respective red DUCT FAIL light on the BLEED AIR panel illuminates.
For the wing leading edge and center fuselage wing anti-icing ducts, the overheat warning
signal will cause the following warnings to occur:
　
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