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Menu Page
Primary Page
<0039>
<0006>
The N1 reference bugs
and digital readout values
are normally set by the
FMS. If the FMS fails, the
N1 reference bugs and
digital readout values are
set using the MENU page.
NOTE <0039>
<PRE0039>
REV 56, Jan 31/03
Vol. 1 20--50--12
POWER PLANT
Fuel System
Flight Crew Operating Manual MASTER
CSP A--013
Flight Management System Thrust Limit <0039>
Figure 20---50---8
CRZ selected on the FMS
and displayed as a doughnut
on the primary page.
To make the <ACT> cursor move,
press line select key opposite the
desired thrust value.
When selected, the white
<ACT> changes to cyan, along
with the thrust value. The value
is now displayed on the primary
page.
To display the FLX value on the
FMS, first a FLX TEMP must be
entered.
When FLX is selected, the
white <ACT> changes to magenta,
along with the thrust value. The
thrust value is now displayed on
the primary page.
FLX selected on the FMS
and displayed on the primary
page. Once airborne FLX is
removed from the FMS.
Vol. 1 20--55--1
REV 56, Jan 31/03
POWER PLANT
Interturbine Temperature Monitoring
Flight Crew Operating Manual
CSP A--013
MASTER
1. INTERTURBINE TEMPERATURE (ITT) MONITORING
The engine ITT is measured by ten probes mounted around the engine turbine section. The
probes measure the average gas path temperature at the high pressure turbine (HPT) exit
Each probe generates a millivolt signal which is sent to an engine mounted junction box
where the signals are averaged and then sent to the DCU’s for ITT indication on the EICAS
primary page.
REV 56, Jan 31/03
Vol. 1 20--55--2
POWER PLANT
Interturbine Temperature Monitoring
Flight Crew Operating Manual MASTER
CSP A--013
Engine Indication (ITT) for CF34---3A1 <MST>
Figure 20---55---1
(APR activated)
Primary Page
<0039> <0006>
(APR not activated) (Maximum Continuous Thrust)
(MCT)
Green
(0 to 884 C)
(0 to 900 C)
<0039>
<0039>
<0039>
Vol. 1 20--55--3
REV 56, Jan 31/03
POWER PLANT
Interturbine Temperature Monitoring
Flight Crew Operating Manual
CSP A--013
MASTER
Engine Indication (ITT) for CF34---3B1 <MST>
Figure 20---55---2
(APR activated)
(APR not activated) (Maximum Continuous Thrust)
(MCT)
Primary Page
<0039> <0006>
REV 56, Jan 31/03
Vol. 1 20--55--4
POWER PLANT
Interturbine Temperature Monitoring
Flight Crew Operating Manual MASTER
CSP A--013
THIS PAGE INTENTIONALLY LEFT BLANK
Vol. 1 20--60--1
REV 56, Jan 31/03
POWER PLANT
Vibration Monitoring
Flight Crew Operating Manual
CSP A--013
MASTER
1. VIBRATION MONITORING
The N1 fan and the N2 core section are continuously monitored for vibration. A signal
conditioner unit, mounted in the avionics compartment, monitors the vibration levels in each
engine that it receives from N1 fan and N2 core speed sensors. The unit processes the
signals and provides output signals to the DCU’s for display on the EICAS primary page.
The system can be tested using the VIB test switch on the ENGINE CONTROL panel.
The N2 vibration level is only indicated as a VIB icon on the respective N2 gauge when the
vibration level exceeds 1.7 mils.
The N1 fan vibration gauges are only displayed after engine start when both engines are at
idle and the engine oil pressure is normal. When the N1 vibration level exceeds 2.7 mils, the
gauge and pointer color change to amber. When either engine is shutdown or oil pressure is
low, the N1 vibration gauges revert to oil pressure gauges.
REV 56, Jan 31/03
Vol. 1 20--60--2
POWER PLANT
Vibration Monitoring
Flight Crew Operating Manual MASTER
CSP A--013
Engine Vibration Monitoring <MST>
Figure 20---60---1
Engine Control Panel
Center Pedestal
Primary Page
<0039>
<0006>
N2 Fan Vibration
Gauges
Displayed when N2
vibration > 1.7 MILS.
Amber Arc
4.0 MILS (2.7 to 4.0 MILS)
0 MILS Green
(0 to 2.6 MILS)
N1 Vibration Readout
Green 0 to 2.6MILS
Amber w 2.7 MILS
2.6 MILS
<0019>
Vol. 1 20--60--3
REV 56, Jan 31/03
POWER PLANT
Vibration Monitoring
Flight Crew Operating Manual
CSP A--013
MASTER
A. System Circuit Breakers
　
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