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• Both the R 10th-stage bleed switch/light and the ISOL switch/light are pressed open.
External Ground Air Connector
An external ground air connector is located on the aft fuselage below the left engine. Ground air
may be supplied to the left manifold of the 10th-stage bleed air system when a ground air
source is attached to the external ground air connector.
14TH-STAGE BLEED AIR
Description
The bleed air for the 14th-stage manifold is taken from a single port on each engine compressor’s
14th stage. The air is distributed through the 14th-stage bleed air manifold.
The 14th-stage bleed air is used for:
• Wing anti-ice;
• Cowl anti-ice; and
• Thrust reversers.
PNEUMATIC SYSTEM
Description
Vol. 2 18−10−4
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
14TH-STAGE BLEED AIR (CONT'D)
14th-Stage Bleed Air Schematic
Figure 18−10−3
Components and Operation
14th-Stage Bleed Air Manifold
The 14th-stage bleed air manifold is located in the aft equipment bay. The left engine
pressurizes the left manifold and the right engine pressurizes the right manifold. 14th-stage
bleed air can only be supplied by an operating engine. Manifold check valves are installed to
prevent reverse flow of 14th-stage air to an operating engine.
14th-Stage Isolation Valve
The isolation valve is located in the aft equipment bay and separates the left and right wing
anti-ice crossover duct. Refer to Chapter 14, Ice and Rain Protection, for a detailed description.
PNEUMATIC SYSTEM
Description
Vol. 2 18−10−5
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
14TH-STAGE BLEED AIR (CONT'D)
Engine 14th-Stage Bleed Air Valves
The 14th-stage bleed air valves are located in the aft equipment bay and control the supply of
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
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
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
　
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