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panel, comes on dim when the HPSOV is closed. The light is off
when the valve is open. The light is on bright during valve
transition.
ENGINE FUEL AND CONTROL - ENGINE CONTROL - HMU - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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Mechanical Overspeed Governor
A mechanical overspeed governor can prevent an N2
overspeed condition.
When the overspeed governor senses an N2 overspeed
condition, it causes the bypass valve to open more. When the
bypass valve opens more, less fuel goes to the FMV and the
fuel nozzles. This causes the N2 speed to decrease.
This is an alternate N2 overspeed protection from the EEC. The
EEC monitors the operation of the overspeed governor during
each engine start.
ENGINE FUEL AND CONTROL - ENGINE CONTROL - HMU - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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73-21-00-016
ENGINE FUEL AND CONTROL - ENGINE CONTROL - HMU - FUNCTIONAL DESCRIPTION
ENGINE FUEL AND CONTROL - ENGINE CONTROL - HMU - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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73-21-00-016
ENGINE FUEL AND CONTROL - ENGINE CONTROL - HMU - FUNCTIONAL DESCRIPTION
ENGINE FUEL AND CONTROL - ENGINE CONTROL - HMU - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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73-21-00-016
Purpose
These engine indications on the engine panel show this engine
control status:
* EEC switch position indication
* EEC switch ALTN light
* ENGINE CONTROL light.
The white ON switch position indicator and amber ALTN light
are in the EEC switches. These indications show if the EEC is in
the normal mode or an alternate mode. When the EEC is in an
alternate mode, it sends a signal to the ALTN light and the light
comes on.
There are two alternate modes, the soft alternate and hard
alternate modes. These modes are also called soft and hard
reversionary modes.
The soft or hard alternate modes are used when the EEC does
not receive valid total air pressure data from both air data
inertial reference units (ADIRUs) or the flight crew selects the
EEC switch to the OFF position. See the POWER MANAGEMENT
page in this section for information on EEC alternate modes.
The ground or flight crew can put the EEC in the hard alternate
mode by selection of the EEC switch for that engine. The white
ON does not show in the EEC switch when the hard alternate
mode is selected. The white ON in the EEC switch shows when
the switch is not selected.
The amber ENGINE CONTROL light shows when the EEC
detects an engine failure that does not allow airplane dispatch.
The EEC sends a signal to the DEUs to energize the ENGINE
CONTROL light. The ENGINE CONTROL light does not come on
in flight. The ENGINE CONTROL light comes on when all of
these conditions occur:
* Airplane is on the ground and the ground speed is less than
30 knots for more than 30 seconds or increasing ground
speed is less than 80 knots
* N2 speed is more than 50 percent
* A no dispatch engine fault occurs.
NOTE: The airplane cannot dispatch with this light on.
Training Information Point
When the ENGINE CONTROL light comes on, use the CDU, fault
isolation manual (FIM) and the airplane maintenance manual
(AMM) to find and correct the cause. See the TRAINING
INFORMATION POINT PAGES of this section for more
information on CDU BITE operation.
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ENGINE FUEL AND CONTROL - ENGINE CONTROL - ENGINE CONTROL LIGHT AND EEC SWITCHES
ENGINE FUEL AND CONTROL - ENGINE CONTROL - ENGINE CONTROL LIGHT AND EEC SWITCHES
　
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