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Dedicated Generator (DG). Normally the FADEC is powered by the DG when the engine is
operating. If DG power fails, the PSU will revert to the airplane power supply, to continue operation of
the engine. The DG is mounted on the front of the accessory gearbox.
GF1810_021
DEDICATED GENERATOR AIR STARTER
HYDRAULIC PUMP
DRY DRAINS OUTLET
VARIABLE FREQUENCY
GENERATOR No.1
FRONT VIEW OIL TANK
POWER PLANT
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
18−10−13
ENGINE ELECTRONIC CONTROLLER (EEC) (CONT'D)
The CPU receives and processes all input signals and calculates the output signals. Control of the
engine automatically alternates between channel A and channel B. If channel A is in control, channel
B is the backup for the duration of that flight. On the next engine start channel B is in control and
channel A is backup. The change command is triggered by the engine shut down on the ground. An
interlock prevents both channels from being in control at the same time. Each CPU operation is
monitored by a “watchdog timer”. If the watchdog timer senses a CPU malfunction within a set time
scale, then it will momentarily pass control to the other channel, while the faulty CPU resets. After
four CPU resets the watchdog will impose a freeze and control will pass to the other channel for the
remainder of the flight.
GF1810_022
CPU CPU VALIDATION
PROCESSING
OUTPUT SIGNAL
CALCULATION
VALIDATION
PROCESSING
OUTPUT SIGNAL
CALCULATION
OUTPUT DRIVER OUTPUT DRIVER
LANE CHANGE RELAY LANE CHANGE RELAY
SYSTEM CONTROLLER
SYSTEM
ACTUATOR
POSITION
ACTUATOR
ENGINE
TIMER
WATCHDOG
WATCHDOG
TIMER
OUTPUTS INPUTS INPUTS INPUTS INPUTS OUTPUTS
AIRFRAME SIGNALS ENGINE ENGINE AIRFRAME SIGNALS
SYSTEM FEEDBACK TO CHANNEL A & B
OF EEC AS "ENGINE INPUTS"
ENGINE PARAMETER FEEDBACK TO BOTH
CHANNELS OF THE EEC (AS ABOVE) AND DIRECT
TO AIRFRAME SYSTEMS, IE: VIBRATION.
CROSS
LINK
The IOP will automatically shut off fuel in the event of N1 or N2 reaching the overspeed trigger
values. When either N1 or N2 speed signal has exceeded a preset value, one of the IOPs will “vote”
to close the HPSOV, located in the FMU and indicate this to the other channel via the cross link. The
engine will not shut down unless both IOPs detect an overspeed. The overspeed function is checked
during normal engine shut down, by resetting the overspeed trip points to a subidle
value. When the
speed drops below the reset values, the IOP overspeed detection trip points logic resets.
POWER PLANT
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
18−10−14
ENGINE INDICATIONS
Primary engine parameters are displayed on EICAS. Secondary engine parameters are displayed on
the STAT page.
FGF1810_007
OIL QTY (QTS)
ENG
APU
RES
RPM
10.4
20
1300
90
22 0.00
100 650
03 03 03 03
4.5
5.0
10.4
CKPT ( C)
OXYGEN
CAB ALT
CAB RATE
P
AFT
CABIN (°C)
APU
%
CABIN (°C)
22
19 20 20
EGT
BRAKE TEMP
LDG ELEV
500
1000
FWD
TOTAL FUEL (LBS) 41550
1.54 1.54
73.3 73.3
789 789
14600 10000 14600 ND
STAB
NU
NL RUDDER
LWD RWD
NR
TRIMS
7.2
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4
5750
115
81
93.4
5750
115
81
EPR
N1
ITT
AIL
Engine Pressure Ratio (EPR)
Used to display thrust and is the
primary thrust setting indicator.
1.65 1.65
EICAS
STAT page
N1 (FAN)
Used to display the LP compressor (fan)
speed and as Secondary thrust setting
indicator and is measured in %.
Inter Turbine Temperature (ITT)
Used to display engine operating
temperatures in °C.
N2 (HP compressor)
Used to display HP compressor
speed and is measured in %.
Fuel Flow (FF)
Used to display the amount of fuel
being used, in pounds per hour
(PPH) or kilograms per hour
(KPH).
Oil Temperature (OIL TEMP)
Used to display the oil
Oil Pressure (OIL PRESS)
Used to display the oil
Engine Oil Quantity (ENG)
Used to display the oil quantity in
the engine and is measured in
U.S. quarts.
Oil Reservoir Quantity (RES)
Used to display the amount of oil
　
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