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• ANTI-ICE DUCT warning EICAS message is displayed;
• MASTER WARNING switch/lights illuminate flashing; and
• “ANTI-ICE DUCT” aural warning sounds.
Pressing either MASTER WARNING/CAUTION 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 shorted 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
Description
Vol. 2 18−10−8
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
BLEED AIR LEAK DETECTION SYSTEM (CONT'D)
Bleed Air Leak Detection System Capabilities
Figure 18−10−5
PNEUMATIC SYSTEM
Description
Vol. 2 18−10−9
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
CONTROLS AND INDICATORS
The controls (switch/lights) and the test functions for the pneumatic system are located on the
BLEED AIR panel.
The systems advisory, caution and warning messages are displayed on the EICAS page. The
10th-stage bleed air pressure readouts are displayed on the EICAS SUMMARY page (see
Figure 18−10−7).
BLEED AIR Panel
BLEED AIR Panel
Figure 18−10−6
PNEUMATIC SYSTEM
Description
Vol. 2 18−10−10
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
CONTROLS AND INDICATORS (CONT'D)
EICAS Display
EICAS SUMMARY Page − Bleed Pressure Readouts
Figure 18−10−7
EICAS MESSAGES
MESSAGE MEANING
AURAL WARNING
(IF ANY)
L 10TH DUCT
Bleed air leak in the respective 10th-stage ducting. “BLEED AIR DUCT”
R 10TH DUCT
L 14TH DUCT
Bleed air leak in the respective 14th-stage ducting. “BLEED AIR DUCT”
R 14TH DUCT
ANTI-ICE DUCT Bleed air leak in the fuselage or wing anti-ice ducting. “ANTI-ICE DUCT”
APU LCV FAIL APU load control valve has failed in the open position with APU LCV interlock
activated.
DUCT TEST OK Bleed air leak detection systems passed self-test.
LOOP A TEST OK
The respective 10th-stage duct overheat loop circuit has passed self-test.
LOOP B TEST OK
PNEUMATIC SYSTEM
Description
Vol. 2 18−10−11
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
PNEUMATIC SYSTEM
Description
Vol. 2 18−10−12
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
THIS PAGE INTENTIONALLY LEFT BLANK
POWER SUPPLY AND CIRCUIT BREAKER SUMMARY
SYSTEM SUB-SYSTEM CB NAME BUS BAR
CB
PANEL
CB
LOCATION
NOTES
Pneumatic 14th Stage Bleed Air
Control
14 ST B/AIR SOV R DC BUS 2 2 F12
14 ST B/AIR SOV L DC BUS 1 1 F12
14 ST B/AIR ISOL
SOV
DC BUS 1 1 F13
Bleed Leak Detection
and Warning
B/LEAK TEST DC ESS 4 B12
B/LEAK R DET AC ESS 3 B2
B/LEAK L DET AC ESS 3 B1
Bleed Air Control 10TH ST B/AIR
ISOL
DC ESS 4 B11
10TH ST B/AIR
SOV L
DC ESS 4 C11
10TH ST B/AIR
SOV R
DC BUS 2 2 F11
PNEUMATIC SYSTEM
Summary
Vol. 2 18−20−1
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
PNEUMATIC SYSTEM
Summary
Vol. 2 18−20−2
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
THIS PAGE INTENTIONALLY LEFT BLANK
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庞巴迪挑战者605机组操作手册 CL605-PNEUMATIC(4)
