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SEE T
SEE U
ENGINE
SPEED CARD (REF)
ELECTRICAL SYSTEMS CARD FILE M7603
T
ENG 1
EEC/TMC
DISCRETE
CARD
YMLA002 ENG 3
ENG 2 DISCRETE EEC/TMC
EEC/TMC CARD
DISCRETE YMLA006
CARD
YMLA004 ENG 4
EEC/TMC
DISCRETE
CARD
YMLA008
U
Fuel Control System Component LocationFigure 1 (Sheet 10)
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////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
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////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
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////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
C. There are four pneumatic inputs at the bottom of the EEC; PT5 (PT4.95), PT2, PB, and PAMB. A transducer, installed in the EEC, is included for each pneumatic input. The transducer receives the input, changes it to an electronic signal, and sends it to the channel A and B circuits.
(1)
The P5 (P4.95) input is exhaust gas pressure from the engine pressure ratio (PT4.95) probes (AMM 77-11-00/001). The P5 (P4.95) transducer is installed in the channel A half of the EEC and is energized by the channel A power supply.
(2)
The PT2 input is compressor inlet total pressure from the PT2/TT2 probe. The P2 transducer is installed in the channel A half of the EEC and is energized by the channel A power supply.
(3)
The PB input is burner pressure from a static pressure port installed on the diffuser case at the 1:30 o'clock position. The PB transducer is installed in the channel B half of the EEC and is energized by the channel B power supply.
(4)
The PAMB input is ambient pressure from two static pressure ports installed on the outer surface of the fan cowl panel at the 5 and 7 o'clock positions. Tubes from each port come together in the strut where one line brings the pressure signal to the EEC. The PAMB transducer is installed in the channel B half of the EEC and is energized by the channel B power supply.
(5)
Each pressure line has a serviceable water trap that is installed on the fan case, below the EEC.
D.
There are four electrical connectors on the forward side of the EEC and five electrical connectors on the aft side.
(1)
The four electrical connectors on the forward side of the EEC (J5A/F, J6FCU, J7ENG, and J8PWR) are for the channel A inputs and outputs that follow:
(a)
J5A/F 1) TRA input 2) TRA excitation 3) Digital data input for the left air data computer (L ADC) 4) Digital data input for the right air data computer (R ADC) 5) Digital data input for the flight management computer (FMC) 6) ARINC digital data output 7) Alternate mode select discrete 8) Two discrete returns 9) Autothrottle armed discrete 10) Four location bit discretes 11) Bump discrete 12) Idle select discrete 13) PT2/TT2 probe heat discrete 14) Maintenance discrete
(b)
J6FCU 1) N1 input 2) HPC secondary flow control (left) valve position 3) TVBCA (right) valve position discrete 4) Torque motor output for the stator vane actuator 5) TCC torque motor output 6) FMU torque motor output
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