D.
Low Pressure Lights Test
S 715-062
(1)
Do a test for the lamps in the control switches for the boost pumps.
(a)
Hold the IND LTS switch on the pilots' overhead panel to the TEST position.
(b)
Make sure all the low pressure lights on the fuel management control module come on.
(c)
Release the IND LTS switch.
E.
Low Pressure Indicating System Test
S 715-014
(1)
Do the test for the boost pump low pressure indicating system.
(a)
Push the switch for the No. 1 forward boost pump on the fuel management control module to start the pump.
(b)
Make sure the low pressure light goes off.
(c)
Push the switch again to stop the pump.
(d)
Make sure the low pressure light comes on.
(e)
Do the test again for the No. 1 aft boost pump and the boost pumps in the tanks No. 2, No. 3, and No. 4.
F.
Put the Airplane Back to Its Usual Condition
S 865-015
(1) Remove the electrical power, if it is not necessary for a subsequent task (AMM 24-22-00/201).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
28-42-00
ALL ú ú 05 Page 505 ú Feb 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
PRESSURE SWITCH - REMOVAL/INSTALLATION
______________________________________
1. General_______
A. This procedure contains two tasks. The first task removes the pressure switches used for the low pressure indication and fuel management. The second task installs the switches used for low pressure indication and fuel management.
B. Pressure switches for the boost pumps for the inboard main tank are installed adjacent to the pumps on the front or rear spar. The pressure switches for the boost pumps for the outboard main tanks are installed on the wing rear spar. Pressure switches for the override/jettison, and APU boost pump are installed on the pumps.
C. To get access to the pressure switches on the inboard main forward boost pumps, you must extend the leading edge (LE) flaps.
D. Access to the pressure switches on the outboard main tank boost pump is through the access panels, 573AT and 673AT.
E. Access to the pressure switches that follow are through the landing gear wheel well:
(1)
The aft boost pump in the inboard main tank
(2)
The override/jettison pumps
(3)
The APU DC boost pump
F.
You must install the safety locks on all the extended LE flaps, if you do work in this area.
G.
You must install the door locks for the wing and body landing gear doors, if you do work in the wheel well area.
TASK 28-42-01-004-001
2. Pressure Switch Removal_______________________
A. Equipment
(1)
Container - Fuel resistant 1 gallon
B.
References
(1)
AMM 24-22-00/201, Manual Control
(2)
AMM 27-81-00/201, Leading Edge Flap System
(3)
AMM 32-00-30/201, Landing Gear Door Locks
(4)
SSM 28-42-01, 28-42-02
(5)
WDM 28-42-11, WDM 28-42-12, WDM 28-42-13, WDM 28-42-14
(6)
AIPC 28-42-01, Fig. 1
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
28-42-01
ALL ú ú 12 Page 401 ú Feb 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
C. Access
(1)
Location Zones 135 Wing Landing Gear Well, Left 136 Wing Landing Gear Well, Right 521 Leading Edge to Front Spar, Left 571 Rear Spar to Landing Gear Support Beam, Left 573 Rear Spar to Inbd Aileron Leading Edge, Left 621 Leading Edge to Front Spar, Right 671 Rear Spar to Landing Gear Support Beam, Right 673 Rear Spar to Inbd Aileron Leading Edge, Right
(2)
Access Panels
573AT Access Door, Left
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