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S The assumed temperature entered is greater than the actual OAT
S The airspeed is less than 65 knots
Vol. 1 20--20--4
POWER PLANT
Thrust Control REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
The assumed temperature can be cleared by selecting DEL on the FMS CDU or if the
FMS is not available, by selecting FLX RESET on the EICAS menu page. To clearly
identify flex power from other thrust modes, the flex indications are displayed in
magenta on the N1 gauges.
NOTE
The FLX indications on theEICASmenu page are only
displayed if the FMS has failed or is not available.
When programmed, the FLX power setting is activated by the FADEC when the thrust
levers are in the TOGA detents.
Thrust Control N1 Reference Bug and Readout <1001>
Figure 20---20---4
0 0.0
C ALT RATE P
GEAR
TOTAL FUEL
OIL PRESS
OIL TEMP
48
96
56
97
N2
ITT
600
80.0
600
78.5
DN DN DN
0
BRT
N1 Reference Bug and
Readout (cyan)
Displays FADEC computed
target thrust rating.
Thrust Mode (cyan)
Displays thrust lever position or armed condition.
Turns magenta for flex power.
0.9
VIB
SLATS / FLAPS 20
FAN
0.9
83.0 83.0
83.0 83.0
CRZ / CLB
N1
Caret (cyan)
Changes to a circle for cruise power
and turns magenta for flex power. 2200 1070 2200
FUEL QTY (KG)
5470
210 FF (KPH) 210
Primary Page
Vol. 1 20--20--5
POWER PLANT
Thrust Control REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
FADEC/FMU Interface
Figure 20---20---5
115V 400 Hz
EXCITER
EXCITER
LVDT, DISCRETE TO FADEC B
LVDT, DISCRETE
THRUST REVERSER
POWER LEVER
ANGLES
OBV
FADEC A
FADEC B
OBV POSITION FEEDBACK
OBV POSITION DEMAND
FUEL FLOW DEMAND AND FEEDBACK
OVERSPEED SHUTOFF SOLENOID
VG DEMAND
VG FEEDBACK
OBV POSITION DEMAND AND FEEDBACK TO CHANNEL B
P3
T2
T2
N1
N1 N1
N2
N2
VG FEEDBACK
VG DEMAND
OVERSPEED SHUTOFF SOLENOID
FUEL FLOW DEMAND AND FEEDBACK
FUEL FILTER DP SWITCH
N1
N2
LVDT, DISCRETE FROM THRUST REVERSER
AIRCRAFT INTERFACE
TO EVM
115V 400 Hz (FROM INVERTER)
CCDL
OIL PRESSURE
OIL PRESSURE SWITCH
OIL FILTER DP SWITCH
OIL TEMPERATURE
OIL CHIP DETECTOR
OIL LEVEL
AGB
FUEL
TEMP
MASTER
VG
ACTUATOR
FUEL
PUMP
PERMANENT
MAGNET
ALTERNATOR
(ITT)
(ITT)
POWER &
N2 SPEED
FUEL
METERING
UNIT
POWER &
N2 SPEED
28 VDC
BATT BUS
TEST
CONNECTOR
DATA BUS
DATA BUS
OUTPUTS
28 VDC
BATT BUS
POWER LEVER
ANGLES
OUTPUTS
X--TALK
AMBIENT
AIR
Vol. 1 20--20--6
POWER PLANT
Thrust Control REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
C. Automatic Power Reserve
The automatic power reserve (APR) system (which is a feature of the FADEC) monitors
for engine failures and/or power loss during takeoff and climb. The APR feature is
armed during takeoff when the N1 rpm of both engines are within 8% of the take off N1
reference value. On the approach, the APR system is armed for the go--around with
either engine available and flaps greater than 20_ or landing gear down.
A failure is detected when an engine N1 speed decreases below 15% of the set power.
If the detected failure was due to an N1 mismatch, the failure signal is cleared when the
N1 mismatch becomes less than 13%.
When an engine fails, the APR will automatically increase the thrust on the good engine
to maximum continuous thrust (MCT). The amount of the increased thrust depends on
the position of the thrust levers at the time of the engine failure. This automatic
increase in thrust is divided into three categories:
S APR power when the thrust levers are in the TOGA detents
S Automatic increase to maximum continuous thrust (MCT) when the thrust levers are
in the climb detent
S Proportional increase in power when operating with thrust levers in the cruise range
Thrust Control Automatic Performance Reserve <1001>
Figure 20---20---6
APR (Icon) (green)
Displayed when APR system is activated
by an engine failure, or when a thrust
lever is set to the MAX POWER detent.
95.5 21.8
95.5
TO/_
N1
0 0.0
C ALT RATE P
GEAR
　
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