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The CDS usually shows engine data on two display units (DUs).
One DU shows the primary engine display and the other shows
the secondary engine display. The primary engine display
usually shows on the upper center DU. The secondary engine
display usually shows on the lower center DU. Engine data can
also show on the inboard DUs.
Abbreviations and Acronyms
* altn - alternate
* AVM - airborne vibration monitoring
* BITE - built-in test equipment
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* BSV - burner staging valve
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* CAS - calibrated air speed
* CDS - common display system
* CDU - control display unit
* chap - chapter
* DEU - display electronics unit
* DU - display unit
* EEC - electronic engine control
* EGT - exhaust gas temperature
* FDAU - flight data acquisition unit
* FDR - flight data recorder
* FFCCV - fan frame compressor case vertical (sensor)
* FMCS - flight management computer system
* FMV - fuel metering valve
* HPC - high pressure compressor
* HPT - high pressure turbine
* HPTACC - high pressure turbine active clearance control
* LPC - low pressure compressor
* LPT - low pressure turbine
* LPTACC - low pressure turbine active clearance control
* REV - thrust reverser sleeve position
* tach - tachometer
* TBV - transient bleed valve
* TRA - thrust resolver angle
* TRF - turbine rear frame
* UTC - universal time coordinate
* VBV - variable bleed valve
* VSV - variable stator vane
* vib - vibration
ENGINE INDICATING - INTRODUCTION
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CFM56 ENGINES (CFM56-7) 737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
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ENGINE INDICATING - INTRODUCTION
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CFM56 ENGINES (CFM56-7) 737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
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General
The engine indicating system shows these parameters for each
engine:
* Low pressure rotor speed (N1)
* High pressure rotor speed (N2)
* Exhaust gas temperature (EGT)
* Engine vibration.
Electronic Engine Control
The electronic engine control (EEC) receives an analog input
from these engine sensors:
* N1 speed sensor
* N2 speed sensor
* EGT probes (T49.5).
The EEC changes the analog signals to digital signals. The EEC
sends the digital signals on an ARINC 429 data bus to the
display electronics units (DEU)s.
Airborne Vibration Monitoring Signal Conditioner
The airborne vibration monitoring (AVM) signal conditioner
calculates and monitors vibration levels of each engine.
The AVM signal conditioner receives analog input from these
engine sensors:
* N1 speed sensor
* N2 speed sensor
* Number 1 bearing vibration sensor
* Fan frame compressor case vertical vibration (FFCCV)
sensor.
The DEUs and the flight data acquisition unit (FDAU) receive
AVM information through an ARINC 429 data bus.
DEUs
The DEUs use digital input from the EEC to show these engine
parameters on the common display system (CDS):
* N1
* N2
* EGT.
The DEUs use their analog N1 and N2 signals as alternate
inputs when the EEC does not have electrical power. EGT
shows only when the EEC has electrical power. See the ENGINE
FUEL AND CONTROL for more information about the EEC
power sources. (SECTION 73-21)
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ENGINE INDICATING - GENERAL DESCRIPTION
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General
The engine indicating system lets you see exceedance data for
these engine parameters:
* N1
* N2
* EGT RED LIMIT
* EGT HOT START.
The exceedance data is important for maintenance practices.
You find these actions in part II of the airplane maintenance
manual (AMM). You need this information for selection of the
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