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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
• respective red DUCT FAIL light on the BLEED AIR Panel illuminates
PNEUMATIC SYSTEM
For Training Purposes Only
May 03
19-9
P I LOT T R A I N I N G GU I D E
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
• 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:
• ANTI-ICE DUCT warning EICAS message is displayed
• MASTER WARNING switch/lights illuminate flashing
• “ANTI-ICE DUCT” aural warning sounds
Pressing either MASTER WARNING switch/light can silence the aural warnings.
However, the EICAS warning message will remain displayed until the condition is
corrected (sensing element or thermal switch temperature drops below the trip level).
Any bleed air leak warning requires flight crew action to manually isolate the failed
section.
Unlike the engine fire detection sensing elements, the bleed air leak detection units
cannot discriminate between an actual overheat condition and a false warning (shorted
loop).
DUCT MON Test
The integrity of the Bleed Air Leak Detection system can be tested via the BLEED
AIR Panel. Selecting and holding the DUCT MON selector to TEST verifies all
sensing elements’ loop continuity by simulating an overheat condition. In addition to
the bleed air duct warnings that occur during the test, successful completion will also
cause the DUCT TEST OK advisory EICAS message to be displayed.
The LOOP A and LOOP B positions are used to individually test each left and right
10th-stage loop for a short condition. If the selected loop tests normal, the LOOP A
TEST OK or LOOP B TEST OK advisory EICAS message will be displayed. Should
any 10th-stage loop be shorted, the applicable bleed air duct warning will occur.
PNEUMATIC SYSTEM
19-10 For Training Purposes Only
Jan 04
P I LOT T R A I N I N G GU I D E
Bleed Air Leak Detection System Capabilities
Figure 19-5
L
L R
R
DUCT
FAIL
CLOSED
DUCT
FAIL
CLOSED
DUCT
FAIL
CLOSED
DUCT
FAIL
CLOSED
L Wing
A/I Valve
L 14th
SOV
R 14th
SOV
EICAS
Warning
Messages
Only
R Cowl
A/Ice
14th ISOL
R
ATS
10th
ISOL
L 10th
SOV
R 10th
SOV
APU
&
EICAS
Warning
Message
&
EICAS
Warning
Message
&
EICAS
Warning
Message
&
EICAS
Warning
Message
14TH-STAGE
10TH-STAGE 10TH-STAGE
14TH-STAGE
L T/R
PDU
L Cowl
A/Ice
L
ATS
L ACU
L Wing Anti-Ice
R Wing Anti-Ice
Engine Fire Detection System (Zone A)
Jet Pipe / Pylon Overheat Detection System (Zone B)
Bleed Air Leak Detection System – 10th-Stage
Bleed Air Leak Detection System – 14th-Stage (pylon)
Bleed Air Leak Detection System – Anti-Ice (fuselage)
Bleed Air Leak Detection System – Anti-Ice (wing)
LCV
Left
Fuselage
Right
Fuselage
R Wing
A/I Valve
P604_19_003
14th-Stage
10th-Stage
14th-Stage
10th-Stage
R ACU
R T/R
PDU
PNEUMATIC SYSTEM
For Training Purposes Only
May 03
19-11
P I LOT T R A I N I N G GU I D E
Controls and Indicators
The controls (switch/lights) and the test functions for the pneumatic system are located
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
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