CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
(1)
Turn the Power Switch to ON.
S 862-035-N00
(2)
Move the Hydraulic Flow Control Handle to the A position.
S 862-036-N00
(3)
Slowly close the Bypass Valve A (clockwise) only until the correct pressure is on the hydraulic pressure guage.
(a)
See the adjustment procedure for the correct pressure.Extend and retract the actuator.
S 862-048-N00
(1)
Use the applicable Electrical Control Box to extend and retract the actuator per the adjustment task.
NOTE: You do not use the pump valves to extend or retract the
____ actuator.
After the adjustment, disconnect and remove the equipment.
S 862-037-N00
(1)
Open the Bypass Valve A (counterclockwise) until the pressure on the hydraulic gauge is 0.
S 862-038-N00
(2)
Move the Hydraulic Flow Control Valve to NEUTRAL (middle position).
S 862-039-N00
(3)
Close the Supply Valve A (to clockwise stop).
S 862-040-N00
(4)
Turn the Power Supply Switch to OFF.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 747-400 MAINTENANCE MANUAL
(5) S 022-041-N00Disconnect the power cord from the power supply.
(6) S 022-042-N00Disconnect the hoses from the actuator and install protection covers to the ends.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
2.5 BLEED VALVE ACTUATOR - REMOVAL/INSTALLATION
_______________________________________________
1. General
_______
A. This procedure gives the instructions for the removal and installation of the 2.5 bleed valve actuator.
B. The 2.5 bleed valve actuator is installed on the aft face of the
intermediate case at the 7 o'clock position.
C. You can get access to the 2.5 bleed valve actuator through the left thrust reverser.
TASK 75-32-01-004-001-N00
2. Remove the 2.5 Bleed Valve Actuator (Fig. 401)
___________________________________
A. Standard Tools and Equipment
(1)
Container - 1 U.S. pint (0.5 liter) capacity,
used to catch the fuel
B.
References
(1)
AMM 24-22-00/201, Manual Control
(2)
AMM 71-11-04/201, Fan Cowl Panels
(3)
AMM 71-11-06/201, Core Cowl Panels
(4)
AMM 72-34-03/401, Fan Exit Liner Segment
(5)
AMM 78-31-00/201, Thrust Reverser System
(6)
IPC 75-32-01 Fig. 5
C.
Access
(1)
Location Zone 412 Engine 1 - Intermediate Case Aft Face 7 o'clock 422 Engine 2 - Intermediate Case Aft Face 7 o'clock 432 Engine 3 - Intermediate Case Aft Face 7 o'clock 442 Engine 4 - Intermediate Case Aft Face 7 o'clock
(2)
Access Panel
415 Left Thrust Reverser Half - Engine 1
425 Left Thrust Reverser Half - Engine 2
435 Left Thrust Reverser Half - Engine 3
445 Left Thrust Reverser Half - Engine 4
D.
Prepare to Remove the 2.5 Bleed Valve Actuator
(1)
Supply electrical power (AMM 24-22-00/201).
S 864-003-N00
(2)
Make sure the applicable FUEL CONTROL switch is in the CUTOFF position.
S 864-002-N00
(a) Install the DO-NOT-CLOSE tag.
S 864-004-N00
(3) Push the STAT button on the EICAS display select panel.
(a) Make sure the status page shows on the auxiliary EICAS.
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