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the thrust reverser unit
FULL AUTHORITY DIGITAL ELECTRONIC CONTROL (FADEC)
Thrust management is controlled throughout all phases of operation by the Full
Authority Digital Electronic Control (FADEC). An Electronic Engine Controller
(EEC) is the major part of the FADEC, interfacing between the airplane systems and
the engine.
The EEC provides the following control functions:
• Fuel metering through the FMU for:
• Automatic start and relight
• Idle speed control
• Acceleration and deceleration
• Engine power setting
• Limit protection for N1 and N2 speeds
• Limit protection for temperature
• Independent overspeed protection of N1 and N2
For Training Purposes Only
Sept 04
17-5
P I LOT T R A I N I N G GU I D E
POWER PLANT
• Compressor airflow control via the and HP compressor bleed valves, to ensure:
• Surge free acceleration and deceleration
• Surge recovery
• Stable operation
• Control of oil and fuel temperature
• Control of the igniters and start air valve
• Partial control of the thrust reverser system functions
• Control of the engine power in reverse thrust
• Control of system electrical supply, either 28 or dedicated generator output to the
EEC and through to the FADEC
ELECTRONIC ENGINE CONTROLLER (EEC)
The EEC is the controlling unit of the FADEC system and is located on the top of the
engine.
GX_17_021
MAX
THRUST
IDLE
REV
MAXREV
ENGRUN
R LTHROTTLE
MODULE
DAU 1
28 VDC
DAU 2
DAU 3
IAC 1
IAC 2
IAC 3
ADC 1
ADC 2
ADC 3
DEDICATED GEN
THRUST REVERSER
FMU
FUEL COOLED OIL COOLER
HPS & BLEED VALVES
STARTER AIR VALVE
STATOR VANE SYSTEM
IGNITION SYSTEM
OTHER AVIONICS SYSTEMS
EEC
ENGINE INPUTS
GX_17_022
Engine Electronic
Controller (EEC)
17-6 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
POWER PLANT
The EEC is an electronic control unit containing two channels A and B. Each channel
is comprised of a Central Processor Unit (CPU), Power Supply Unit (PSU) and an
Independent Overspeed Protection (IOP) unit.
The PSU controls the power supplies to the FADEC system and to the EECs, CPU and
IOP.
The PSU controls the switch over from the airplane 28 VDC supply to power supplied
by the 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.
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 shutdown on the ground. An interlock prevents
both channels from being in control at the same time. Each CPU’s operation is
monitored by a “watchdog timer”. If the watchdog timer senses a CPU malfunction
within a set timescale, 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.
GX_17_023
Dedicated Generator
Air Starter
Hydraulic Pump
Oil Tank
Variable Frequency
Generator No. 1
Dry Drains
Outlet
FRONT VIEW
For Training Purposes Only
Sept 04
17-7
P I LOT T R A I N I N G GU I D E
POWER PLANT
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 shutdown 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.
GX_17_024
AIRFRAME SIGNALS AIRFRAME SIGNALS
VALIDATION
PROCESSING
VALIDATION
PROCESSING
OUTPUT SIGNAL
CALCULATION
OUTPUT SIGNAL
CALCULATION
　
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