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General (Fig. 1)
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 A.  An aileron and spoiler hydraulic supply shutoff valve is provided in each of the four airplane hydraulic systems to shut off hydraulic pressure to the aileron and spoiler power control packages and the central lateral control packages. Each shutoff valve is controlled by a guarded switch on the pilots' overhead panel. A valve position indicator light is located below each switch. The shutoff valve switches are part of the FLT CONTROL SHUTOFF - WING VALVE on P461 Pilot's Overhead Maintenance Panel.
Hydraulic Shutoff Wing Valve
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 A.  The hydraulic shutoff wing valve is located on the wing rear spar and consists of a two-position valve driven by a 28-volt dc motor. A double seal isolates the oil chamber of the valve from the electrical units. A manual override and position indicator lever provides a visual indication of valve position.
 B.  Two limit switches in the shutoff wing valve electrical circuits limit motor operation. The switches operate so that regardless of valve position in the operating cycle, or whether the position has been reached manually or electrically, operation of the appropriate switch applies electrical power to the motor to drive the valve in selected position.
 C.  The shutoff wing valve also incorporates a switch to sense valve slide position. The slide operates the switch to complete an indicator light circuit when valve is not fully open. The indicator light is located adjacent to the switch.
Operation
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 A.  Functional Description (Fig. 2)
 (1)  With electrical power on, the FLT CONTROL SHUTOFF - WING VALVE switch positions the shutoff valve according to the selected position. With the switch OFF, the valve is closed; with the switch ON, the valve is open. A guard normally shields the switch in the ON position. When valve is open, hydraulic fluid is ported to aileron and spoiler power control packages and valve indicator light (VALVE CLOSED) is off. When the valve is closed, hydraulic fluid flow to the control packages is stopped and the valve indicator light illuminates.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

SYSTEM NO. 1 HYDRAULIC SUPPLY
SYSTEM NO. 2 HYDRAULIC SUPPLY
SHUTOFF WING VALVE
SHUTOFF WING VALVE
SEE A
SEE A
NOTE:LEFT WING SHOWN.
RIGHT WING TYPICAL
FOR SYSTEMS NO. 3 AND 4.
SEE B
HYDRAULIC SUPPLY SHUTOFF WING VALVE (TYPICAL 4 PLACES)
FLT CONTROL HYD POWER MODULE
A B
Aileron and Spoiler Hydraulic Supply Shutoff Component Location Figure 1
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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747-400
MAINTENANCE MANUAL

AILERONS SPOILER -CLOSE
CLCP SHUTOFF SYSTEM OFF

AILERON & 28V DC

SPOILER CONT & CLCP VALVE

 

SYS 1,2,3 OR 4
ON
(4 PLACES)LAT CONT VALVE OPEN
28V DC
MASTER
DIM

MASTER POSITION TEST SWITCH
VALVE CLOSED LIGHT
NOTE: SIMPLIFIED SCHEMATIC SHOWN IS TYPICAL FOR SYSTEMS NO. 1,2,3 AND 4.
Aileron and Spoiler Hydraulic Supply Shutoff Simplified Schematic
Figure 2

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 AILERON AND SPOILER HYDRAULIC SUPPLY SHUTOFF - ADJUSTMENT/TEST
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 1.  General_______
 A.  This procedure contains a system test for the aileron and spoiler supply shutoff for all four hydraulic systems. Each system supplies hydraulic pressure to a different group of surfaces. These are the four hydraulic systems:
　
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