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information on the bleed air systems. (SECTION 36-11)
See the wing thermal anti-ice system section for more
information. (SECTION 30-11)
See the inlet cowl anti-ice system section for more information.
(SECTION 30-20)
Hydromechanical Unit (HMU)
The EEC sends control data to the hydromechanical unit (HMU).
The HMU sends position data for the FMV and HPSOV to the
EEC. The EEC uses the HMU to operate these systems and
components:
* FMV
* LPTACC
* HPTACC
* VSVs
* VBVs
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* BSV
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* TBV.
Operation
When engine start is first commanded, the airplane transfer bus
supplies power to the EEC. At 15 percent N2 speed, the EEC
disconnects transfer bus power and connects to the EEC
alternator if alternator power is in limits.
When the start lever is put to the IDLE position, EEC logic
controls the FMV and ignition system. This causes the igniters
to operate and the FMV to open. Metered fuel goes to the fuel
nozzles for combustion. The EEC causes the ignition system to
stop at the correct N2 speed.
ENGINE FUEL AND CONTROL - ENGINE CONTROL - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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The EEC operates the FMV to control the acceleration of the
engine compressor and EGT during start. The EEC also
operates the FMV to control engine speed for forward and
reverse thrust. See the engine starting section for more
information. (CHAPTER 80)
After start and while on the ground, the EEC controls engine idle
speed based on electrical power, ECS bleed system, and
minimum fuel flow requirements. During flight, the EEC has two
Idle modes, flight idle and approach idle. These idle modes are
set by weather, anti-ice system, and go-around requirements.
See the Thrust Management page in this section for more
information on idle control.
The EEC manages engine thrust based on ambient conditions
and the commanded thrust input from the thrust levers. See the
Engine Thrust Management page for more information on
engine thrust management.
Training Information Point
The control display units (CDUs) show faults and other
maintenance information for the engine. The CDUs also
control ground tests for each engine system to find and
isolate faults.
See the engine indicating section for more information on CDU
BITE operation. See the training information point pages in this
section for more information on engine BITE operation using
the CDU.
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73-21-00-018
ENGINE FUEL AND CONTROL - ENGINE CONTROL - FUNCTIONAL DESCRIPTION
ENGINE FUEL AND CONTROL - ENGINE CONTROL - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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CFM56 ENGINES (CFM56-7) 737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
73-21-00-018
ENGINE FUEL AND CONTROL - ENGINE CONTROL - FUNCTIONAL DESCRIPTION
ENGINE FUEL AND CONTROL - ENGINE CONTROL - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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CFM56 ENGINES (CFM56-7) 737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
73-21-00-018
Engine Idle Control
After start and while on the ground, the EEC controls engine
ground idle speed based on these paramaters:
* Outside air temperature
* Electrical power
* Bleed air demand
* Minimum fuel flow requirements.
During flight, the EEC has two idle modes, flight idle and
approach idle. These idle modes are set by these parameters:
* Anti-ice operation
* Flap position
* Gear position
* Altitude
* Go-around requirements.
Whichever idle mode the EEC is in, it uses the highest value
input of that mode to control idle speed.
While on the ground, the EEC controls engine idle to satisfy idle
speed requirements. If the idle speed is not enough to satisfy
one of these requirements, the EEC controls the FMV to
increase the engine idle speed until all idle speed requirements
　
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