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pages in this section for more information on BITE.
Engine Indication
The EEC supplies data to display electronic units (DEU) 1 and 2
of the common display system (CDS). The CDS display units
(DU) show engine primary and secondary indications.
See the engine indicating chapter for more information on
engine indications. (CHAPTER 77)
Training Information Point
An operator can update the EEC software program with the use
of a portable data loader (PDL). Refer to the engine
manufacturer manuals for more information on the use of the
PDL.
ENGINE FUEL AND CONTROL - ENGINE CONTROL - ELECTRONIC ENGINE CONTROL
EFFECTIVITY
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CFM56 ENGINES (CFM56-7) 737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
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ENGINE FUEL AND CONTROL - ENGINE CONTROL - ELECTRONIC ENGINE CONTROL
ENGINE FUEL AND CONTROL - ENGINE CONTROL - ELECTRONIC ENGINE CONTROL
EFFECTIVITY
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Purpose
The engine identification (ID) plug supplies configuration data to
the electronic engine control (EEC).
This is the engine ID plug data:
* Engine type (7B)
* N1 trim
* Thrust rating
* Engine condition monitoring (option)
* Engine combustor configuration (SAC or DAC).
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* BSV active
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Location
The EEC is on the right side of the engine fan case. The engine
ID plug connects to the P11 connector on the bottom of the EEC.
To get access to the EEC and ID plug, open the right fan cowl.
Training Information Point
The engine identification plug stays with the engine when you
remove the EEC.
Training Information Point
The engine identification plug does not contain the engine serial
number. During an engine change, it will be necessary to
change the serial number with the FMC CDU. Use either CDU to
enter the serial number for the new engine.
ENGINE FUEL AND CONTROL - ENGINE CONTROL - ENGINE IDENTIFICATION PLUG
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73-21-00-012
ENGINE FUEL AND CONTROL - ENGINE CONTROL - ENGINE IDENTIFICATION PLUG
ENGINE FUEL AND CONTROL - ENGINE CONTROL - ENGINE IDENTIFICATION PLUG
EFFECTIVITY
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General
The electronic engine control (EEC) alternator usually supplies
electrical power to the EEC. The EEC alternator is the primary
electrical power source for the EEC.
NOTE: The airplane ac transfer bus 1 is another source of
power for engine 1 EEC. AC transfer bus 2 is another
source of power for engine 2 EEC. The transfer buses
supply electrical power to the EECs when the alternator
can not supply power.
Location
The EEC alternator is on the top forward side of the accessory
gearbox (AGB). To get access to the EEC alternator, open the
left fan cowl.
Physical Description
The EEC alternator contains a housing and stator assembly and
a rotor. The stator has two separate sets of windings. One set of
windings gives power to channel A and the other set gives
power to channel B.
Functional Description
The EEC alternator supplies electrical power to channel A and
channel B of the EEC.
If the EEC alternator cannot supply power for either channel A
or B, the airplane electrical system can supply power to the
EEC. If N2 speed is more than 15% and the alternator does not
have good power for one of the EEC channels, a message is
stored in BITE memory. This condition also causes the EEC to
go to single channel operation.
Training Information Point
Use the accessory gearbox (AGB) manual drive adaptor when
you remove or install the rotor. Put a 3/4-inch square drive tool
into the adaptor. This prevents movement of the alternator
driveshaft and rotor when you loosen or tighten the rotor
retaining nut.
CAUTION: DO NOT LET THE ROTOR AND STATOR TOUCH
WHEN YOU REMOVE THE STATOR. THE
MAGNETS ON THE ROTOR WILL APPLY A
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