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EGT redline:
* EGT digital readout
* Box around the digital readout
* Pointer
* Shaded area.
When the exhaust gas temperature goes back to the normal
range, the indication color goes to white.
When the EEC deenergizes after engine shutdown, the box
around the digital readout changes to red if EGT was more than
redline during the engine operation.
The EEC deenergizes after an engine run, when N2 speed goes
less than about 10 percent. When the EEC deenergizes, the
digital readout, pointer, and shaded area go blank.
EXHAUST GAS TEMPERATURE (EGT) INDICATING SYSTEM - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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CFM56 ENGINES (CFM56-7) 737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
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See the engine tachometer system section for more information
the exceedance data display. (SECTION 77-11)
The EGT digital readout and box flash during an engine ground
start if the EEC sees a possible hot start. This function does not
work in flight. See the engine starting chapter for more
information. (CHAPTER 80)
EGT Maximum Continuous Limit and Amber Band
The EGT maximum continuous limit is the start of the EGT
caution range. Continuous operation of an engine with EGT
more than this value could cause damage to the engine. The
EEC supplies the EGT maximum continuous limit value. The
limit shows in amber.
The amber band is the EGT caution range. Continuous
operation of an engine with EGT in this range could cause
damage to the engine. The amber range shows as an arc
between the maximum continuous limit and the EGT redline.
EGT Start Redline
The EGT start redline is the maximum limit for the EGT during
an engine start on the ground. The redline shows only during
the ground start. The EGT start redline goes away when the
engine goes to idle. This redline does not show in flight.
These indications change to red when the EGT is more than the
EGT start redline during a ground start:
* EGT digital display
* Box around the digital display
* Pointer
* Shaded area.
The EEC stops fuel flow and ignition if EGT is more than the
start redline during an engine start on the ground. See the
engine starting chapter for more information. (CHAPTER 80)
EXHAUST GAS TEMPERATURE (EGT) INDICATING SYSTEM - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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CFM56 ENGINES (CFM56-7) 737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
77-21-00-002
EXHAUST GAS TEMPERATURE (EGT) INDICATING SYSTEM - FUNCTIONAL DESCRIPTION
EXHAUST GAS TEMPERATURE (EGT) INDICATING SYSTEM - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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CFM56 ENGINES (CFM56-7) 737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
77-21-00-002
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77-31-00
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CFM56 ENGINES (CFM56-7) 737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
Purpose
The airborne vibration monitoring (AVM) system continuously
supplies engine vibration levels to the CDS.
General Description
The AVM system has these components:
* AVM signal conditioner
* A vibration sensor (accelerometer) near the forward end of
the engine
* A vibration sensor (accelerometer) on the engine fan frame.
The signal conditioner uses the signals from these sensors to
calculate the engine vibration levels:
* No. 1 bearing vibration sensor
* Fan frame compressor case vertical (FFCCV) vibration
sensor
* N1 speed sensor
* N2 speed sensor.
The signal conditioner supplies the vibration data to the display
electronics units (DEUs) and the flight data acquisition unit
(FDAU). The engine vibration normally shows on the secondary
engine display. The secondary engine display usually shows on
the center lower display unit (P2).
The signal conditioner has built-in test equipment (BITE) to help
you do these tasks:
* Troubleshooting system faults
* See and erase vibration data in AVM signal conditioner nonvolatile
memory
* Calculate a balance solution for engine vibration.
AIRBORNE VIBRATION MONITORING (AVM) SYSTEM - GENERAL DESCRIPTION
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