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selecting the engine fire push switch. Moving the thrust lever to the shutoff position, closes
the shutoff valve of the fuel metering unit. The engine fire push switch closes the engine
fuel feed shutoff valve.
Fuel is also used to control and actuate the operability bleed valve and variable geometry
linkages for engine compressor surge and stall protection. Fuel is used to actuate and
lubricate components within the fuel system.
Fuel not used for combustion is returned to the fuel system to provide motive flow for the
main and scavenge ejectors in the fuel tanks.
Vol. 1 20--50--2
POWER PLANT
Fuel System Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
Fuel system --- EICAS Indications <1001>
Figure 20---50---1
FF (green)
Indicates rate of fuel
flow. Amber dashes
indicates invalid data.
Primary Page
BRT
Vol. 1 20--50--3
POWER PLANT
Fuel System Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
Fuel Distribution System Schematic
Figure 20---50---2
FUEL
METERING
VALVE
OPERABILITY
BLEED VALVE
FUEL
INJECTORS
(QTY 18)
METERED
FUEL OUT
POP OUT
BUTTON IMPENDING
BYPASS
SENSOR
T
MIN
PRESS
VALVE
BYPASS
VALVE
FUEL METERING UNIT
10TH STAGE
COMPRESSOR
AIR (P3)
MOTIVE FLOW
FUEL FEED
SOV
PRIMARY
PUMP
FUEL/ OIL
HEAT
EXCHANGER
OIL IN
CENTRIFUGAL
BOOST PUMP
FUEL PUMP UNIT
SECONDARY
PUMP
DCUs
EICAS
PRESSURIZING
AND
SHUTOFF
VALVE
OVERSPEED
SOLENOID
SL
AVE
MAST
E
R
SHUTOFF
OVERSPEED
VALVE
CHANNEL
A
CHANNEL
B
FADEC
P
COLLECTOR
TANK
BOOST
PUMP
BARRIER
FILTER
FILTER
MAIN
EJECTOR
SERVO VALVE
VG ACTUATORS
POSITION
SENSING
Vol. 1 20--50--4
POWER PLANT
Fuel System Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
THIS PAGE INTENTIONALLY LEFT BLANK
Vol. 1 20--55--1
POWER PLANT
Interturbine Temperature Monitoring REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
1. INTERTURBINE TEMPERATURE (ITT) MONITORING
The engine ITT is measured by five probes mounted around the engine turbine section.
The probes measure the gas path temperature at the exit of the high--pressure turbine
(HPT). Each probe generates a voltage signal which is sent to the FADEC where the
signals are averaged, converted to a digital output signal and then sent to the DCUs for the
ITT display on the EICAS primary page.
The FADEC will detect ITT exceedances into the different areas of the exceedance chart
(refer to figure 20--55--2) based on the tracking time verses temperature subsequent to an
initial exceedance of 1006_C. The FADEC will supply an input to the EICAS (status
message) to indicate each type of exceedance. Each eceedance into the B1 area is
announciated for 4 seconds. Since the ITT must exceed the ITT Redline in order to be
detected as an area C exceedance, it is possible to encounter multiple area B1
exceedances in one transit if the ITT remains elevated.
If there is an ITT exceedance into area B or C, the respective ITT EXCEED status message
will be latched for the remainder of the flight. The message will be removed on engine
shutdown when the N2 decreases below 2%.
Vol. 1 20--55--2
POWER PLANT
Interturbine Temperature Monitoring REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Interturbine Temperature (ITT) Monitoring EICAS Indications
Figure 20---55---1
L or R ITT EXCEED B status (white)
Indicates that category B ITT exceedance
has occurred.
L or R ITT EXCEED B1 status (white)
Indicates that category B1 ITT
exceedance has occurred.
L or R ITT EXCEED C status (white)
Indicates that category C ITT exceedance
has occurred.
BRT
Status Page
Primary Page
Vol. 1 20--55--3
POWER PLANT
Interturbine Temperature Monitoring REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
ITT Exceedance Detection
Figure 20---55---2
ITT Exceedance Detection
Vol. 1 20--55--4
POWER PLANT
Interturbine Temperature Monitoring Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
THIS PAGE INTENTIONALLY LEFT BLANK
Vol. 1 20--60--1
POWER PLANT
Vibration Monitoring Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
　
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