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CHANNEL
A
EEC
CHANNEL
B
IOP
CHANNEL
A
IOP
CHANNEL
B
POWER PLANT
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
18−10−20
ENGINE INDICATIONS (CONT'D)
N1 Control
N1 control mode is selected on the engine control panel, located on the pedestal. Both switches
must be in the same position. N1 can also be selected automatically by the EEC in the event of an
EPR control mode failure. This is known as a soft reversion and both switches should then be
selected to N1, hard reversion, until the EPR failure is cleared. An amber EICAS message will be
displayed when a failure is detected and a status message will be displayed, when the control
switches have been selected to N1 control.
GF1810_030
NOTE
Before manually reverting to N1 control, the thrust levers should be retarded to avoid thrust "bumps".
Hard Reversion
L−R FADEC N1 CTL
L−R FADEC N1 CTL
N1 Indication
GF1810_031
NOTE
When the N1 readout and the N1 rating match, the bugs will blend.
SYNC Mode
Displays synchronized mode as
selected by the autothrottle or
manually through the FMS.
N1 Rating Readout
Displays the N1
numerical target.
N1 Rating "V" Bug
Displays the target N1
bug for MAN mode.
N1 Readout
N1 value.
N1 "T" Readout Bug
Displays the current
N1 command bug.
73.3 73.3
N1
MAN
SYNC
85.4 85.4
N1 Speed Redline
Displays the maximum N1
speed allowed and is set at
101.0%. Should the N1 limits be
exceeded, the sweep arm and
N1 readout will be red.
Engine Control Mode Box
Displays when in N1 control
mode.
N1 Rating Mode
Displays mode as selected
manually via the FMS
THRUST MGT page.
101.4
N1 Sweep Arm
Displays the current
N1 value.
Displays the current
POWER PLANT
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
18−10−21
ENGINE INDICATIONS (CONT'D)
Inter Turbine Temperature (ITT)
ITT measures engine operating temperatures and is used by the EEC during engine start and
relight.
Seven dual element (dissimilar metals) thermocouples located in the LP turbine entry area are
connected in parallel and provide an average ITT to each lane of the EEC.
A data entry plug ensures that all engines have the same ITT redline. The redline will change
value depending on the start configuration, ground or inflight.
GF1810_032
AIRFRAME
ENGINE
CHANNEL CHANNEL
A B
EEC
DATA
ENTRY
PLUG
DAUs
DUAL ELEMENT
THERMOCOUPLE
789 789
ITT
POWER PLANT
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
18−10−22
ENGINE INDICATIONS (CONT'D)
ITT Indication
GF1810_033
ITT Readout
Displays the current
ITT value.
ITT Speed Redline
Displays the maximum ITT
allowed and is set at 900°C, for
engine operation (except engine
start). Should the ITT limits be
exceeded, the sweep arm and
ITT readout will be red and will
flash.
906
ITT Sweep Arm
Displays the current
ITT value.
789 789
ITT
25
ITT
ITT Redline (ground start)
The redline is reset for ground start
to 700°C. It will revert back to
900°C once the engine is at idle.
125
ITT
ITT Redline (in flight start)
The redline is reset for inflight start
to 850°C. It will revert back to 900°C
once the engine is at idle.
POWER PLANT
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
18−10−23
ENGINE INDICATIONS (CONT'D)
N2 (HP Compressor)
The N2 signals are used by the EEC for engine control functions and are used by the Engine
Vibration Monitor Unit (EVMU).
N2 is measured by four speed probes per engine, mounted in the accessory gearbox.
Three speed probes are used by the EEC for the following:
· Variable stator vane control
· Bleed valve control
· Start/relight
· Redline limiting
· Idle control
· Surge protection/recovery
· Overspeed protection
· N2 EICAS indication
The fourth probe, is used by the EVM system for engine vibration indication.
GF1810_034
AIRFRAME
ENGINE
N2
SPEED
　
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