曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

10TH ISOL OPEN
14TH ISOL OPEN
14TH SOV CLSD
10TH ARM OPEN
10TH ARM CLSD
14TH ARM OPEN
14TH ARM CLSD
APU LCV OPEN status (white)
APU load control valve is open. 10th stage,
APU LCV OPEN switch/light comes on.
Status Page
<0039>
<0039>
10TH ISOL OPEN status (white)
Comes on to indicate that 10th stage isolation
valve is open. Corresponds to 10th stage ISOL
switch/light indicating OPEN (white).
14TH ISOL OPEN status (white)
Comes on when 14th stage bleed air
isolation valve is open.
L/R 10TH SOV CLSD
status (white)
Comes on to indicate that
corresponding SOV is closed.
Corresponds to 10th stage
switch/lights indicating
CLOSED (white).
14TH SOV CLSD status (white)
L/R 14th stage bleed air SOV open when
switch/light unlatched (CLSD position).
L/R 10TH ARM OPEN status (white)
Comes on to indicate that the applicable
10th--stage switch is selected open but the
SOV is closed.
L/R 10TH ARM CLSD status (white)
Comes on to indicate that the applicable
10th stage bleed air switch is selected
closed but the SOV is open.
L/R 14TH ARM OPEN status (white)
Comes on to indicate that the applicable
14th stage switch is selected open but the
SOV is closed.
<0039>
<0039>
<0039>
APU LCV FAIL caution (amber)
Load control valve has failed (either
open or closed).
BLEED MISCONFIG caution (amber)
Comes on to indicate that the 10th and
14th stage bleeds are misconfigured for
take--off and landing.
Primary Page
<0039>
<0006>
(i.e., the wing/cowl anti--ice are in use and
the 10th stage bleeds are not closed for
take--off or landing).
<0039>
L/R 14TH ARM CLSD status (white)
Comes on to indicate that the applicable 14th stage
bleed air switch is selected closed but the SOV is open.
<0039>
REV 56, Jan 31/03
Vol. 1 19--20--6
PNEUMATIC
Bleed Air System
Flight Crew Operating Manual MASTER
CSP A--013
C. High Pressure Ground Air Connection
The high pressure ground connection is located on the aft left side of the fuselage
below No.1 engine. External high pressure air from a ground power cart can be used to
pressurize the 10th stage bleed air manifold with compressed air for engine starting.
The external air pressure is indicated on the EICAS, ECS synoptic page.
NOTE
When the aircraft is only operating on DC power, the
pressure readout on the ECS synoptic page is not
displayed.
Vol. 1 19--20--7
REV 56, Jan 31/03
PNEUMATIC
Bleed Air System
Flight Crew Operating Manual
CSP A--013
MASTER
D. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
10 ST B/AIR
ISOL
DC
ESSENTIAL 4 B1
10th Stage
Bleed Air
10 ST B/AIR
SOV L DC BUS 1 1 F11
Bleed Air
10 ST B/AIR
SOV R DC BUS 2 2 F11
system 14 ST B/AIR
ISOL
DC BUS 1 1
F9
14th Stage
Bleed Air
14 ST B/AIR
SOV L
F10
14 ST B/AIR
SOV L DC BUS 2 2 F10
REV 56, Jan 31/03
Vol. 1 19--20--8
PNEUMATIC
Bleed Air System
Flight Crew Operating Manual MASTER
CSP A--013
THIS PAGE INTENTIONALLY LEFT BLANK
Vol. 1 19--30--1
REV 56, Jan 31/03
PNEUMATIC
Bleed Air Leak Detection
Flight Crew Operating Manual
CSP A--013
MASTER
1. BLEED AIR LEAK DETECTION
The bleed air leak detection system monitors the 10th and 14th stage pneumatic and
anti-ice ducting for high temperatures associated with bleed air leakage. EICAS messages
and system control is provided by two bleed leak detection control units, one for the left
bleed system and one for the right bleed system. A test switch on the BLEED AIR control
panel is used to check for continuity in the leak detection system.
Overheat sensing elements are installed along the entire length of the 10th and 14th stage
ducting in the fuselage and pylon areas. The 10th stage bleed air system is monitored by
dual--loop overheat detectors and the 14th stage is monitored by a single--loop overheat
detection system. The wing anti--ice system uses single--loop detectors in the fuselage and
thermal switches in the wing leading edges. The dual sensing loops are used to ensure
dispatch reliability and to minimize system false warnings. To prevent false indications, both
loops must detect a leak before an EICAS message is posted. The supply ducting is
encased in a protective cover. If a leak occurs, holes in the protective cover will direct the
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：Bombardier_CRJ_00-Pneumatic(3)