Page 29 D633W101-BEJ Sep 05/2002
ENGINE FUEL CONTROL -EEC SENSOR INPUTS
There are two thrust reverser position transducers (RVDTs). Each transducer measures the position of one thrust reverser sleeve. The EEC uses the position signals for control and indication. RVDT on the IDG and backup gen air/oil heat exchanger valves send the valve position to the EEC.
A pressure switch measures the position of the thrust reverser isolation valve. The EEC sends a signal to AIMS if the valve is not in the correct position.
Electrical Power System
A differential pressure switch monitors the condition of the IDG oil filter. The EEC sends oil filter status signals to the AIMS.
The EEC is the interface between two IDG temperature senors and the AIMS. One sensor measures the inlet oil temperature of the IDG. The other sensor measures the outlet oil temperature of the IDG.
A differential pressure switch monitors the condition of the backup generator oil filter. The EEC sends oil filter status signals to the AIMS.
The EEC is the interface between two backup generator oil temperature sensors and the AIMS. One sensor measures the inlet oil temperature of the backup generator. The other sensor measures the outlet oil temperature of the backup generator.
EFFECTIVITY BEJ ALL 73-21-00
Page 30
D633W101-BEJ Sep 05/2002
PW4000 SERIES ENGINES
777 AIRCRAFT MAINTENANCE MANUAL
ENGINE FUEL CONTROL -EEC SENSOR INPUTS
EFFECTIVITY BEJ ALL 73-21-00
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D633W101-BEJ Sep 05/2002
ENGINE FUEL CONTROL -EEC POWER -FUNCTIONAL DESCRIPTION
General
The EECs get airplane power when one of these conditions occur:
*
Fuel control switch is in RUN position
*
Start/ignition selector is in START position
*
EEC maintenance switch is in TEST position.
The left EEC gets power from the left ac bus. The right EEC gets power from the right ac bus. Each channel of the EEC has a separate source. Channel A gets power from section 1 of the ac bus. Channel B gets power from section 2.
The EEC gets airplane power when the start power relay in the P110 left power management panel energizes. The start power relay coil gets power from the captain’s flight instrument bus.
Fuel Control Switch
The fuel control switch energizes the ignition/fire detection relay when it is in the RUN position. The ignition/fire detection relay supplies a ground for the start power relay. This lets the EEC get airplane power during engine operation when there is a control alternator failure. The control alternator is the normal power source when the engine is running.
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