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linear variable differential transformer (LVDT). The EEC uses
this data to limit engine thrust while the thrust reverser
translating sleeves move. The EEC also commands the
engine to idle if it senses a thrust reverser sleeve is deployed
part way in flight. The EEC sends thrust reverser position to the
DEUs for thrust reverser indication on the display units (DUs).
See the thrust reverser section for more information.
(SECTION 78-30)
Aisle Control Stand
The EEC uses the thrust lever resolvers (TLRs) on the aisle
stand to get thrust resolver angle (TRA). The EEC uses this data
to find the commanded engine thrust. The EEC also sends TRA
to the autothrottle computer.
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The start levers and fire handle send signals directly to the
HPSOV in the HMU. This lets the flight crew shut down the
engine in normal or emergency situations. The EEC does not
close the HPSOV. See the engine controls chapter for more
information on the engine controls in the aisle stand.
(CHAPTER 76)
In the IDLE position, the start levers send a start signal to the
EEC through the DEUs. The start levers also send ignition
power to the EEC. The EEC operates the engine ignition system.
See the ignition chapter for more information. (CHAPTER 74)
ENG VALVE CLOSED Light
The ENG VALVE CLOSED light shows the position of the
HPSOV. The ENG VALVE CLOSED light comes on bright when
the HPSOV is in transit or is not in the commanded position.
This light is on dim when the HPSOV is closed and is
commanded closed. The ENG VALVE CLOSED light is off
when the HPSOV is open and commanded open.
Display Electronics Units (DEUs)
The EEC gets and receives data from these airplane systems
and components through the two DEUs:
* Engine and fuel indication
* Start lever IDLE or CUTOFF command
* Air data inertial reference unit (ADIRU) 1 and 2
* Flight management computer (FMC) and control display
units (CDUs)
* Flight data acquisition unit (FDAU).
The EEC sends input data from many of the engine sensors to
the DEUs. The DEUs sends some of this data to the display units
(DUs). These become engine data that shows on the primary
and secondary engine displays. See the engine indicating
chapter for more information. (CHAPTER 77)
The ADIRU sends total and static air pressure and total air
temperature data to the EEC through the DEUs. The EEC uses
this data to control engine thrust.
The FMC supplies a connection between the CDU and the
DEUs. The FMC also supplies target thrust to the EEC. The CDU
shows EEC maintenance data, and sends commands to the EEC
to do system BITE tests.
The FDAU collects engine parameter data. It sends this data to
the flight data recorder (FDR).
Engine Control Light and EEC Switches
The EEC sends a signal to the engine control light on the P5 aft
overhead panel through the DEUs for some faults detected by
the EEC. If this light is on, the airplane cannot be dispatched.
The EEC sends a signal to the EEC ALTN light on the P5 aft
overhead panel if the EEC is in soft or hard alternate modes.
When the EEC switch is in the off position, the EEC goes to the
hard alternate mode. If the ENGINE CONTROL or ALTN light is
on, the MASTER CAUTION lights also come on.
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ENGINE FUEL AND CONTROL - GENERAL DESCRIPTION
ENGINE FUEL AND CONTROL - GENERAL DESCRIPTION
EFFECTIVITY
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Purpose
The engine fuel distribution system supplies fuel to the engine
for combustion and servo system operation. The airplane fuel
system supplies fuel to the engine fuel distribution system.
These are the major components of the engine fuel distribution
system:
* Fuel pump assembly
* IDG oil cooler
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* Burner staging valve (BSV).
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ENGINE FUEL AND CONTROL - DISTRIBUTION - INTRODUCTION
　
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