PNEUMATIC
Table of Contents
Vol. 1
19--00--1
PNEUMATIC
Table of Contents
REV 56, Jan 31/03
CHAPTER 19 --- PNEUMATIC
Vol. 1
19--00--1
REV 56, Jan 31/03
CHAPTER 19 --- PNEUMATIC
Page
Page
19--00
19--00--1
TABLE OF CONTENTS
Table of Contents
19--00
19--00--1
INTRODUCTION
Introduction
19--10
19--10--1
INTRODUCTION
Introduction
19--10
19--10--1
BLEED AIR SYSTEM
Bleed Air System
Engine Bleed Air
APU Bleed Air
High Pressure Ground Air Connection
System Circuit Breakers
19--20
19--20--1
19--20--1
19--20--1
19--20--6
19--20--7
BLEED AIR SYSTEM
Bleed Air System
Engine Bleed Air
APU Bleed Air
High Pressure Ground Air Connection
System Circuit Breakers
BLEED AIR LEAK DETECTION
Bleed Air Leak Detection
System Circuit Breakers
19--30
19--30--1
19--30--5
BLEED AIR LEAK DETECTION
Bleed Air Leak Detection
System Circuit Breakers
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LIST OF ILLUSTRATIONS
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TABLE OF CONTENTS
Table of Contents
19--20
19--20--1
19--20--1
19--20--1
19--20--6
19--20--7
19--30
19--30--1
19--30--5
LIST OF ILLUSTRATIONS
Bleed Air Distribution
19--10--2
INTRODUCTION
Figure 19--10--1
Bleed Air Distribution
19--10--2
BLEED AIR SYSTEM
Figure 19--20--1
Figure 19--20--2
Figure 19--20--3
Figure 19--20--4
Bleed Air System Schematic
Bleed Air System Controls
ECS Page
Bleed Air System EICAS Indications
19--20--2
19--20--3
19--20--4
19--20--5
BLEED AIR SYSTEM
Figure 19--20--1
Figure 19--20--2
Figure 19--20--3
Figure 19--20--4
Bleed Air System Schematic
Bleed Air System Controls
ECS Page
Bleed Air System EICAS Indications
19--20--2
19--20--3
19--20--4
19--20--5
Flight Crew Operating Manual
CSP A--013
19--30--2
19--30--3
19--30--4
Fo
BLEED AIR LEAK DETECTION
Figure 19--30--1
Bleed Air Leak Detection and Warning System
Figure 19--30--2
Bleed Air System Control Panel
Figure 19--30--3
Bleed Air Leak Detection -Loop EICAS Indications
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INTRODUCTION
Figure 19--10--1
BLEED AIR LEAK DETECTION
Figure 19--30--1
Bleed Air Leak Detection and Warning System
Figure 19--30--2
Bleed Air System Control Panel
Figure 19--30--3
Bleed Air Leak Detection -Loop EICAS Indications
Flight Crew Operating Manual
CSP A--013
19--30--2
19--30--3
19--30--4
Vol. 1
19--00--2
PNEUMATIC
Table of Contents
REV 56, Jan 31/03
Vol. 1
19--00--2
REV 56, Jan 31/03
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PNEUMATIC
Table of Contents
Flight Crew Operating Manual
CSP A--013
Flight Crew Operating Manual
CSP A--013
PNEUMATIC
Introduction
19--10--1
PNEUMATIC
Introduction
REV 56, Jan 31/03
INTRODUCTION
1.
The pneumatic system consists of two separate bleed air systems.
Vol. 1
19--10--1
REV 56, Jan 31/03
INTRODUCTION
The pneumatic system consists of two separate bleed air systems.
S Low pressure (10th stage) bleed air system
S Low pressure (10th stage) bleed air system
S High pressure (14th stage) bleed air system.
S High pressure (14th stage) bleed air system.
The low pressure system is supplied bleed air from the 10th stage of both engine
compressors. The 10th stage air is used to supply air for the left and right environmental
control systems, for pressurization and for engine starting. The APU bleed air system or
high pressure air from a ground air source can also be used to meet these requirements.
Normally, each engine supplies the user system on the respective side but, if the 10th stage
bleed air supply is lost from one side, a bleed isolation valve is provided for cross--bleeding
from the operable side.
The environmental control system can also receive conditioned air from a ground air cart.
The environmental control system can also receive conditioned air from a ground air cart.
<0007>
<0007>
The high pressure system is supplied hot bleed air from the 14th stage of both engine
compressors. The 14th stage bleed air is used to supply the requirements of the wing and
cowl anti--ice systems and for thrust reverser operations. Normally, each engine supplies
the user system on the respective side but, if the 14th stage bleed air supply is lost from one
side, a wing isolation valve is provided for cross--bleeding from the operable side.
The high pressure system is supplied hot bleed air from the 14th stage of both engine
compressors. The 14th stage bleed air is used to supply the requirements of the wing and
cowl anti--ice systems and for thrust reverser operations. Normally, each engine supplies
the user system on the respective side but, if the 14th stage bleed air supply is lost from one
side, a wing isolation valve is provided for cross--bleeding from the operable side.
The bleed air leak detection system monitors the pneumatic ducting for high temperature
bleed air leaks. When the system detects a leak, visual warnings are displayed and aural
warnings sound to alert the crew to turn off the affected system.
The bleed air leak detection system monitors the pneumatic ducting for high temperature
bleed air leaks. When the system detects a leak, visual warnings are displayed and aural
warnings sound to alert the crew to turn off the affected system.
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The low pressure system is supplied bleed air from the 10th stage of both engine
compressors. The 10th stage air is used to supply air for the left and right environmental
control systems, for pressurization and for engine starting. The APU bleed air system or
high pressure air from a ground air source can also be used to meet these requirements.
Normally, each engine supplies the user system on the respective side but, if the 10th stage
bleed air supply is lost from one side, a bleed isolation valve is provided for cross--bleeding
from the operable side.
Fo
1.
Vol. 1
Flight Crew Operating Manual
CSP A--013
Flight Crew Operating Manual
CSP A--013
PNEUMATIC
Introduction
Vol. 1
19--10--2
PNEUMATIC
Introduction
REV 56, Jan 31/03
BLEED AIR SOURCES
19--10--2
REV 56, Jan 31/03
BLEED AIR SOURCES
APU
APU
LEFT AND RIGHT
10 TH STAGE
BLEED AIR
ENGINE STARTING
CABIN PRESSURE
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AIR CONDITIONING
LEFT AND RIGHT
10 TH STAGE
BLEED AIR
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AIR CONDITIONING
Vol. 1
ENGINE STARTING
CABIN PRESSURE
GROUND
SOURCE
THRUST REVERSERS
GROUND
SOURCE
THRUST REVERSERS
LEFT AND RIGHT
14 TH STAGE
BLEED AIR
WING ANTI--ICE
ENGINE COWL
ANTI--ICE
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ENGINE COWL
ANTI--ICE
LEFT AND RIGHT
14 TH STAGE
BLEED AIR
WING ANTI--ICE
Bleed Air Distribution
Figure 19---10---1
Flight Crew Operating Manual
CSP A--013
Bleed Air Distribution
Figure 19---10---1
Flight Crew Operating Manual
CSP A--013
PNEUMATIC
Bleed Air System
19--20--1
REV 56, Jan 31/03
BLEED AIR SYSTEM
1.
Engine Bleed Air
19--20--1
REV 56, Jan 31/03
BLEED AIR SYSTEM
A.
Engine Bleed Air
The engine supplies both low (10th stage) and high (14th stage) pressure bleed air
from the compressors to the low and high pressure manifolds.
The engine supplies both low (10th stage) and high (14th stage) pressure bleed air
from the compressors to the low and high pressure manifolds.
(1)
(1)
Low Pressure (10th stage)
S The engine compressors 10th stage or,
S The engine compressors 10th stage or,
S The APU compressor or,
S From an external ground air source.
S From an external ground air source.
Low pressure operated aircraft systems include engine starting, air-conditioning
and pressurization. Bleed air to the low pressure manifold is controlled by 10TH
STAGE bleed air switchlights on the BLEED AIR control panel. The switchlights
operate the respective L/R 10th stage bleed air shutoff valves. The left and right
systems normally operate independently but can be connected by opening the
bleed isolation valve. The bleed isolation valve is controlled by the 10TH STAGE
ISOL switchlight on the BLEED AIR control panel.
High Pressure (14th stage)
(2)
APU Bleed Air
The high pressure bleed air manifold receives pressurized air from the engine
compressors 14th stage.
B.
The APU can be used on the ground to supply the low pressure manifold with bleed air
for air-conditioning or engine starting. The APU can also be used in flight, to supply
bleed air for engine starting (double engine failure) to a maximum altitude of 13,000 ft.
and to supply the air--conditioning system to a maximum of 15,000 ft. When the APU is
selected as the bleed air source, the bleed air is supplied through the APU load control
valve (LCV) to the left bleed air manifold. The APU LCV is controlled by a switchlight
on the BLEED AIR control panel. The 10TH STAGE bleed isolation valve must be
opened to pressurize the right manifold. The APU ECU modulates the LCV to limit APU
exhaust gas temperature and to prevent compressor surges.
Flight Crew Operating Manual
CSP A--013
High Pressure (14th stage)
High pressure operated aircraft systems include the wing anti---ice, cowl anti---ice
and thrust reverser systems. Bleed air to the high pressure manifold is through
the respective L/R 14th stage bleed air shutoff valves. The shutoff valves are
normally open but can be closed by selecting the 14TH STAGE bleed air
switchlights on the BLEED AIR control panel. The left and right wing anti---ice
systems normally operate independently but can be connected by a wing
isolation shutoff valve which is controlled by the 14TH STAGE ISOL switchlight on
the BLEED AIR control panel.
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The high pressure bleed air manifold receives pressurized air from the engine
compressors 14th stage.
High pressure operated aircraft systems include the wing anti---ice, cowl anti---ice
and thrust reverser systems. Bleed air to the high pressure manifold is through
the respective L/R 14th stage bleed air shutoff valves. The shutoff valves are
normally open but can be closed by selecting the 14TH STAGE bleed air
switchlights on the BLEED AIR control panel. The left and right wing anti---ice
systems normally operate independently but can be connected by a wing
isolation shutoff valve which is controlled by the 14TH STAGE ISOL switchlight on
the BLEED AIR control panel.
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The low pressure bleed air manifold receives pressurized air from:
Low pressure operated aircraft systems include engine starting, air-conditioning
and pressurization. Bleed air to the low pressure manifold is controlled by 10TH
STAGE bleed air switchlights on the BLEED AIR control panel. The switchlights
operate the respective L/R 10th stage bleed air shutoff valves. The left and right
systems normally operate independently but can be connected by opening the
bleed isolation valve. The bleed isolation valve is controlled by the 10TH STAGE
ISOL switchlight on the BLEED AIR control panel.
(2)
Low Pressure (10th stage)
The low pressure bleed air manifold receives pressurized air from:
S The APU compressor or,
B.
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A.
PNEUMATIC
Bleed Air System
Fo
1.
Vol. 1
APU Bleed Air
The APU can be used on the ground to supply the low pressure manifold with bleed air
for air-conditioning or engine starting. The APU can also be used in flight, to supply
bleed air for engine starting (double engine failure) to a maximum altitude of 13,000 ft.
and to supply the air--conditioning system to a maximum of 15,000 ft. When the APU is
selected as the bleed air source, the bleed air is supplied through the APU load control
valve (LCV) to the left bleed air manifold. The APU LCV is controlled by a switchlight
on the BLEED AIR control panel. The 10TH STAGE bleed isolation valve must be
opened to pressurize the right manifold. The APU ECU modulates the LCV to limit APU
exhaust gas temperature and to prevent compressor surges.
Flight Crew Operating Manual
CSP A--013
Vol. 1
PNEUMATIC
Bleed Air System
19--20--2
Vol. 1
PNEUMATIC
Bleed Air System
19--20--2
REV 56, Jan 31/03
LEFT
WING ANTI--ICE
RIGHT
WING ANTI--ICE
LEFT
FUSELAGE
LEFT
WING ANTI--ICE
RIGHT
FUSELAGE
ISOL
RIGHT WING
ANTI--ICE
VALVE
14 TH STAGE
14 TH STAGE
LEFT
14 TH
SOV
EXTERNAL AIR
SOURCE
LEFT
10 TH
SOV
APU
LCV
RIGHT
10 TH
SOV
Bleed Air System Schematic
Figure 19---20---1
Flight Crew Operating Manual
CSP A--013
RIGHT
14 TH
SOV
RIGHT AIR
TURBINE
STARTER
LEFT
THRUST
REVERSE
POWER
DRIVE
UNIT
LEFT AIR
TURBINE
STARTER
LEFT
COWL
ANTI--ICE
RIGHT WING
ANTI--ICE
VALVE
RIGHT
RIGHT
COWL
THRUST
ANTI--ICE REVERSE
POWER
10 TH STAGE DRIVE
UNIT
ISOL
10 TH STAGE
14 TH STAGE
14 TH STAGE
LEFT
14 TH
SOV
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RIGHT
RIGHT
COWL
THRUST
ANTI--ICE REVERSE
POWER
10 TH STAGE DRIVE
UNIT
ISOL
10 TH STAGE
ISOL
PRSOV
Fo
LEFT AIR
TURBINE
STARTER
LEFT
COWL
ANTI--ICE
RIGHT
FUSELAGE
RIGHT PACK
LEFT PACK
LEFT WING
ANTI--ICE
VALVE
PRSOV
LEFT
THRUST
REVERSE
POWER
DRIVE
UNIT
RIGHT
WING ANTI--ICE
LEFT
FUSELAGE
RIGHT PACK
LEFT PACK
LEFT WING
ANTI--ICE
VALVE
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REV 56, Jan 31/03
EXTERNAL AIR
SOURCE
LEFT
10 TH
SOV
APU
LCV
RIGHT
10 TH
SOV
Bleed Air System Schematic
Figure 19---20---1
Flight Crew Operating Manual
CSP A--013
RIGHT
14 TH
SOV
RIGHT AIR
TURBINE
STARTER
REV 56, Jan 31/03
L/R 14th Stage Bleed Air Switchlights
Controls the 14th--stage bleed air shutoff
valves.
DUCT FAIL -- Indicates bleed air leak in
applicable duct. Illuminates during duct
monitor test.
CLOSED -- Indicates shutoff valves fully
closed.
REV 56, Jan 31/03
L/R 14th Stage Bleed Air Switchlights
Controls the 14th--stage bleed air shutoff
valves.
DUCT FAIL -- Indicates bleed air leak in
applicable duct. Illuminates during duct
monitor test.
CLOSED -- Indicates shutoff valves fully
closed.
APU LCV Switchlight
OPEN -- APU LCV selected
open.
FAIL -- APU LCV open when
commanded by the interlock
protection circuit.
10th Stage Left and Right Bleed Air
Switch/Lights
When pressed in, associated bleed air
shutoff valve opens and CLOSED (white)
goes out.
When pressed out, associated bleed air
valve closes and CLOSED (white) comes on.
DUCT FAIL (red) -- Comes on if bleed leak
detector sensors detect a failure in associated
duct section. DUCT FAIL goes out when the
failed duct is isolated and temperature sensor
cools.
Bleed Air System Controls
Figure 19---20---2
Flight Crew Operating Manual
CSP A--013
Bleed Air Panel
Overhead Panel
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Bleed Air Panel
Overhead Panel
14th Stage ISOL
Switchlight
OPEN -- Indicates
isolation valve has
been selected
open.
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APU LCV Switchlight
OPEN -- APU LCV selected
open.
FAIL -- APU LCV open when
commanded by the interlock
protection circuit.
10th Stage Isolation Valve Switch/Light
When pressed in, bleed air isolation valve
opens and OPEN (white) comes on.
When pressed out, isolation valve closes
and OPEN light goes out.
19--20--3
Vol. 1
PNEUMATIC
Bleed Air System
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10th Stage Isolation Valve Switch/Light
When pressed in, bleed air isolation valve
opens and OPEN (white) comes on.
When pressed out, isolation valve closes
and OPEN light goes out.
19--20--3
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Vol. 1
PNEUMATIC
Bleed Air System
14th Stage ISOL
Switchlight
OPEN -- Indicates
isolation valve has
been selected
open.
10th Stage Left and Right Bleed Air
Switch/Lights
When pressed in, associated bleed air
shutoff valve opens and CLOSED (white)
goes out.
When pressed out, associated bleed air
valve closes and CLOSED (white) comes on.
DUCT FAIL (red) -- Comes on if bleed leak
detector sensors detect a failure in associated
duct section. DUCT FAIL goes out when the
failed duct is isolated and temperature sensor
cools.
Bleed Air System Controls
Figure 19---20---2
Flight Crew Operating Manual
CSP A--013
Vol. 1
19--20--4
PNEUMATIC
Bleed Air System
REV 56, Jan 31/03
10th--Stage Bleed Air
Isolation Valve
Position Indicator
10th--Stage Bleed Air
Isolation Valve
Position Indicator
Right Bleed Air
Shutoff Valve
Position Indicator
Left 10th--Stage Manifold
Pressure Readout
Right 10th--Stage Manifold
Pressure Readout
Indicates the pneumatic
supply pressure available
for operation of air
conditioning system.
APU Load Control
Valve Position Indicator
Left Bleed Air Shutoff
Valve Position Indicator
Right Bleed Air
Shutoff Valve
Position Indicator
Left 10th--Stage Manifold
Pressure Readout
Right 10th--Stage Manifold
Pressure Readout
Indicates the pneumatic
supply pressure available
for operation of air
conditioning system.
APU Load Control
Valve Position Indicator
Environmental Control System Page
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Environmental Control System Page
ECS Page
Figure 19---20---3
Flight Crew Operating Manual
CSP A--013
19--20--4
REV 56, Jan 31/03
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Left Bleed Air Shutoff
Valve Position Indicator
Vol. 1
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PNEUMATIC
Bleed Air System
ECS Page
Figure 19---20---3
Flight Crew Operating Manual
CSP A--013
PNEUMATIC
Bleed Air System
Vol. 1
19--20--5
PNEUMATIC
Bleed Air System
REV 57, Apr 05/04
APU LCV FAIL caution (amber)
Load control valve has failed (either
open or closed).
19--20--5
REV 57, Apr 05/04
APU LCV FAIL caution (amber)
Load control valve has failed (either
open or closed).
BLEED MISCONFIG caution (amber) <0039>
Comes on to indicate that the 10th and
14th stage bleeds are misconfigured for
take--off and landing.
(i.e., the wing/cowl anti--ice are in use and
the 10th stage bleeds are not closed for
take--off or landing).
<0039>
BLEED MISCONFIG caution (amber) <0039>
Comes on to indicate that the 10th and
14th stage bleeds are misconfigured for
take--off and landing.
(i.e., the wing/cowl anti--ice are in use and
the 10th stage bleeds are not closed for
take--off or landing).
<0006>
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<0039>
Vol. 1
<0006>
APU LCV OPEN status (white)
APU load control valve is open. 10th stage,
APU LCV OPEN switch/light comes on.
L/R 10TH SOV CLSD
status (white)
Comes on to indicate that
corresponding SOV is closed.
Primary Page
Corresponds to 10th stage
10TH ISOL OPEN status (white)
switch/lights indicating
<0039>
Comes on to indicate that 10th stage isolation
CLOSED (white).
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 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) <0039>
Comes on to indicate that the applicable
10th--stage switch is selected open but the
SOV is closed.
L/R 14TH ARM CLSD status (white) <0039>
Comes on to indicate that the applicable 14th stage
bleed air switch is selected closed but the SOV is open.
14TH ISOL OPEN status (white)
Comes on when 14th stage bleed air
isolation valve is open.
L/R 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) <0039>
Comes on to indicate that the applicable
10th--stage switch is selected open but the
SOV is closed.
L/R 14TH ARM CLSD status (white) <0039>
Comes on to indicate that the applicable 14th stage
bleed air switch is selected closed but the SOV is open.
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APU LCV OPEN status (white)
APU load control valve is open. 10th stage,
APU LCV OPEN switch/light comes on.
L/R 10TH SOV CLSD
status (white)
Comes on to indicate that
corresponding SOV is closed.
Primary Page
Corresponds to 10th stage
10TH ISOL OPEN status (white)
switch/lights indicating
<0039>
Comes on to indicate that 10th stage isolation
CLOSED (white).
valve is open. Corresponds to 10th stage ISOL
switch/light indicating OPEN (white).
<0039>
Bleed Air System EICAS Indications <MST>
Figure 19---20---4
Flight Crew Operating Manual
CSP A--013
<0039>
Status Page
Bleed Air System EICAS Indications <MST>
Figure 19---20---4
Flight Crew Operating Manual
CSP A--013
Status Page
19--20--6
PNEUMATIC
Bleed Air System
REV 56, Jan 31/03
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.
C.
NOTE
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When the aircraft is only operating on DC power, the
pressure readout on the ECS synoptic page is not
displayed.
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Flight Crew Operating Manual
CSP A--013
19--20--6
REV 56, Jan 31/03
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
High Pressure Ground Air Connection
Fo
C.
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PNEUMATIC
Bleed Air System
Flight Crew Operating Manual
CSP A--013
REV 56, Jan 31/03
10th Stage
Bleed Air
Bleed Air
system
14th Stage
Bleed Air
CB NAME
10 ST B/AIR
ISOL
10 ST B/AIR
SOV L
10 ST B/AIR
SOV R
14 ST B/AIR
ISOL
14 ST B/AIR
SOV L
14 ST B/AIR
SOV L
BUS BAR
CB
CB
PANEL LOCATION
DC
ESSENTIAL
4
B1
DC BUS 1
1
F11
DC BUS 2
2
F11
DC BUS 1
1
F9
F10
DC BUS 2
2
F10
NOTES
SYSTEM
SUB--SYSTEM
10th Stage
Bleed Air
Bleed Air
system
CB NAME
10 ST B/AIR
ISOL
10 ST B/AIR
SOV L
10 ST B/AIR
SOV R
14 ST B/AIR
ISOL
14 ST B/AIR
SOV L
14 ST B/AIR
SOV L
BUS BAR
Flight Crew Operating Manual
CSP A--013
CB
CB
PANEL LOCATION
DC
ESSENTIAL
4
B1
DC BUS 1
1
F11
DC BUS 2
2
F11
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SUB--SYSTEM
System Circuit Breakers
14th Stage
Bleed Air
DC BUS 1
DC BUS 2
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SYSTEM
D.
REV 56, Jan 31/03
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System Circuit Breakers
19--20--7
Vol. 1
PNEUMATIC
Bleed Air System
Fo
D.
19--20--7
Vol. 1
PNEUMATIC
Bleed Air System
Flight Crew Operating Manual
CSP A--013
F9
1
2
F10
F10
NOTES
Vol. 1
19--20--8
PNEUMATIC
Bleed Air System
REV 56, Jan 31/03
Vol. 1
19--20--8
REV 56, Jan 31/03
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Bleed Air System
Flight Crew Operating Manual
CSP A--013
Flight Crew Operating Manual
CSP A--013
PNEUMATIC
Bleed Air Leak Detection
19--30--1
PNEUMATIC
Bleed Air Leak Detection
REV 56, Jan 31/03
BLEED AIR LEAK DETECTION
1.
Vol. 1
19--30--1
REV 56, Jan 31/03
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
hot bleed air towards the sensing loops.
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
hot bleed air towards the sensing loops.
For normal wing anti--icing, hot bleed air from the 14th stage supply ducting is released
through piccolo tubes to heat the wing leading edges. Thermal switches in the leading edge
of each wing are used to detect leaks in the wing leading edge anti-ice ducting.
For normal wing anti--icing, hot bleed air from the 14th stage supply ducting is released
through piccolo tubes to heat the wing leading edges. Thermal switches in the leading edge
of each wing are used to detect leaks in the wing leading edge anti-ice ducting.
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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.
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PNEUMATIC
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SENSING
ELEMENT
SENSING
ELEMENT
SENSING
ELEMENT
SENSING
ELEMENT
SENSING
ELEMENT
SENSING
ELEMENT
DUCT
SENSOR ELEMENTS
RIGHT 14TH
STAGE MANIFOLD
SENSING ELEMENT
SENSING ELEMENTS
RIGHT 10TH
STAGE MANIFOLD
SENSING ELEMENTS
LEFT 10TH
STAGE MANIFOLD
SENSING ELEMENT
RIGHT FUSELAGE
SENSING ELEMENT
LEFT FUSELAGE
Bleed Air Leak Detection and Warning System
Figure 19---30---1
NOTE
Duct removed for clarity
SENSING ELEMENTS
LEFT 10TH
STAGE MANIFOLD
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SENSING ELEMENTS
LEFT 10TH
STAGE MANIFOLD
SENSING ELEMENT
FWD
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Flight Crew Operating Manual
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DUCT
SENSOR ELEMENTS
RIGHT 14TH
STAGE MANIFOLD
SENSING ELEMENTS
RIGHT 10TH
STAGE MANIFOLD
SENSING ELEMENT
LEFT 14TH
STAGE MANIFOLD
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BLEED AIR LEAK
CONTROL UNIT
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BLEED AIR LEAK
CONTROL UNIT
SENSING ELEMENTS
LEFT 10TH
STAGE MANIFOLD
19--30--2
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SENSING ELEMENT
LEFT 14TH
STAGE MANIFOLD
SENSING ELEMENT
RIGHT FUSELAGE
SENSING ELEMENT
LEFT FUSELAGE
Bleed Air Leak Detection and Warning System
Figure 19---30---1
Flight Crew Operating Manual
CSP A--013
NOTE
Duct removed for clarity
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Bleed Air Leak Detection
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PNEUMATIC
Bleed Air Leak Detection
Monitor Selector Switch
Used to check serviceability of detector loops in left and right sections of 10th and 14th stage systems.
TEST -- Tests 10th/14th stage loops by grounding loop to simulate a duct failure.
LOOP A -- Tests Loop A of 10th stage for continuity, to ensure that loop is not shorted to ground.
LOOP B -- Tests Loop B of 10th stage for continuity, to ensure that loop is not shorted to ground.
NORM -- Normal switch position. Leak detection on Loops A and B is provided.
Bleed Air Panel
Overhead Panel
Bleed Air Panel
Overhead Panel
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Monitor Selector Switch
Used to check serviceability of detector loops in left and right sections of 10th and 14th stage systems.
TEST -- Tests 10th/14th stage loops by grounding loop to simulate a duct failure.
LOOP A -- Tests Loop A of 10th stage for continuity, to ensure that loop is not shorted to ground.
LOOP B -- Tests Loop B of 10th stage for continuity, to ensure that loop is not shorted to ground.
NORM -- Normal switch position. Leak detection on Loops A and B is provided.
Bleed Air System Control Panel
Figure 19---30---2
Flight Crew Operating Manual
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Bleed Air System Control Panel
Figure 19---30---2
Flight Crew Operating Manual
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PNEUMATIC
Bleed Air Leak Detection
<0006>
L/R 14TH DUCT warning (red)
Comes on if temperature sensors
detect failure in 14th stage duct
segment. Corresponds to DUCT
FAIL L/R switch/light (red) on
BLEED AIR panel.
ANTI--ICE DUCT warning (red)
Comes on when bleed air leak is
detected in left and/or right
fuselage or wing anti--ice ducts.
Accompanied by voice alest:
BLEED
AIR
DUCT
BLEED
AIR
DUCT
ANTI--ICE
DUCT
<0039>
Primary Page
DUCT TEST OK
DUCT MON LOOP A
DUCT MON LOOP B
L/R 14TH DUCT warning (red)
Comes on if temperature sensors
detect failure in 14th stage duct
segment. Corresponds to DUCT
FAIL L/R switch/light (red) on
BLEED AIR panel.
ANTI--ICE DUCT warning (red)
Comes on when bleed air leak is
detected in left and/or right
fuselage or wing anti--ice ducts.
Accompanied by voice alest:
Primary Page
DUCT TEST OK
DUCT MON LOOP A
DUCT MON LOOP B
DUCT TEST O.K. advisory (green)
Comes on to indicate that corresponding
loop test is successful (all 5 duct warnings
will be displayed).
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DUCT TEST O.K. advisory (green)
Comes on to indicate that corresponding
loop test is successful (all 5 duct warnings
will be displayed).
L 10TH DUCT
R 10TH DUCT
L 14TH DUCT
R 14TH DUCT
ANTI--ICE DUCT
L/R 10TH DUCT warning (red)
Comes on if temperature sensors
detect failure in 10th stage duct
segment. Corresponds to DUCT
FAIL L/R switch/light (red) on
BLEED AIR panel.
DUCT MON LOOP A/B status (white)
Comes on to indicate that corresponding
loop is under test.
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DUCT MON LOOP A/B status (white)
Comes on to indicate that corresponding
loop is under test.
<0039>
BLEED
AIR
DUCT
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L 10TH DUCT
R 10TH DUCT
L 14TH DUCT
R 14TH DUCT
ANTI--ICE DUCT
REV 56, Jan 31/03
<0006>
<0039>
L/R 10TH DUCT warning (red)
Comes on if temperature sensors
detect failure in 10th stage duct
segment. Corresponds to DUCT
FAIL L/R switch/light (red) on
BLEED AIR panel.
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<0039>
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<0039>
Status Page
Status Page
Bleed Air Leak Detection --- Loop EICAS Indications <MST>
Figure 19---30---3
Bleed Air Leak Detection --- Loop EICAS Indications <MST>
Figure 19---30---3
Flight Crew Operating Manual
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Flight Crew Operating Manual
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BLEED
AIR
DUCT
ANTI--ICE
DUCT
<0039>
A.
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SYSTEM CIRCUIT BREAKERS
SYSTEM
SUB--SYST CB NAME
Bleed Air
System
Bleed Leak
Detection
A.
CB PANEL
LOCATION
BLEED
DC ESS
LEAK TEST
4
B2
AC ESS
3
CONT L
BUS BAR
SYSTEM CIRCUIT BREAKERS
SYSTEM
SUB--SYST CB NAME
Bleed Air
System
Bleed Leak
Detection
B2
CB PANEL
LOCATION
BLEED
DC ESS
LEAK TEST
4
B2
AC ESS
3
B1
CONT L
BUS BAR
CONT R
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NOTES
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NOTES
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PNEUMATIC
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PNEUMATIC
Bleed Air Leak Detection
Flight Crew Operating Manual
CSP A--013
Flight Crew Operating Manual
CSP A--013