GROUND INTERCONNECT VALVE - REMOVAL/INSTALLATION
1. General
A.  The ground interconnect valve is mounted on the forward bulkhead in the wheel well cavity (Fig. 401). A check valve installed on the system A side of the interconnect valve prevents pressurizing system B using system A power source.
B.  A container will be necessary to catch fluid when disconnecting hydraulic lines from the valve during removal. Should any fluid spill on the airplane, the affected area must be decontaminated. Refer to Chapter 12, Cleaning and Washing.
2.  Equipment and Materials
A.  Skydrol Assembly Lube - MCS 352 or Fire Resistant Hydraulic Fluid - BMS\3-11
3.  Remove Ground Interconnect Valve
A.  Depressurize hydraulic systems A and B. Refer to 29-11-0, Hydraulic System A, and 29-12-0, Hydraulic System B - MP.
B.  Depressurize hydraulic reservoirs. Refer to 29-09-300, Hydraulic Reservoir Pressurization System - MP. 
C.  Open GROUND INTERCONNECT VALVE circuit breaker on load control P6 panel.
D.  Open tire burst protection screen doors.
E.  Disconnect electrical connector from interconnect valve (Fig. 401).
F.  Disconnect hydraulic lines from interconnect valve.
G.  Install protective plugs in valve ports and connecting hydraulic lines.
H.  Remove interconnect valve mounting bolts and remove valve.
4.  Install Ground Interconnect Valve
A.  Install O-rings and unions in system A and system B ports of interconnect valve. Apply assembly lube or hydraulic fluid to all 0-rings and to the threads of unions couplings.
B.  Install O-ring and plug in third port and secure with lockwire.
C.  Place interconnect valve in mounting position and install mounting bolts.
500 
Feb 15/73  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  29-11-121 Page 401 

F87158
Ground Interconnect Valve Installation  500 
29-11-121Page 402   Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 15/73 

D.  Connect hydraulic lines to interconnect valve.
E.  Connect electrical connector to interconnect valve.
F.  Provide electrical power to airplane and close GROUND INTERCONNECT VALVE circuit breaker on P6 panel.
G.  Pressurize hydraulic system B. Refer to 29-12-0, Hydraulic System B -\MP.
H.  Check that parking brake is set.
I.  Switch GROUND INTERCONNECT on P5 forward overhead panel to OPEN.
J.  Check interconnect valve for leakage.
K.  Check that interconnect valve override lever is in OPEN position.
L.  Check that system A pressure gage indicates approximately 3000 psi.
M.  Switch GROUND INTERCONNECT switch to CLOSE position.
N.  Check that interconnect override lever is in CLOSE position.
O.  Close tire burst protection screen doors.
P.  Switch hydraulic system B electric pump switch OFF.
Q.  Remove electrical power source from airplane.
500 
Feb 15/73  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  29-11-121 Page 403 

HYDRAULIC SYSTEM B-- DESCRIPTION AND OPERATION
1. General
A.  Hydraulic power system B (figure 1) supplies fluid under pressure of 3000 Psi to the ailerons, elevators, outboard spoilers, rudder, and main wheel outboard brakes.
B.  Hydraulic system B includes the equipment necessary to store, pressurize, deliver, control., monitor, and filter the hydraulic fluid to operate the systems supplied by system B. (See  figure 2.) Hydraulic fluid for system B is stored in a pressurized reservoir. The reservoir is pressurized from a balance line from system A reservoir to ensure a positive supply of hydraulic fluid to the pumps. Two variable displacement electric motor-driven pumps supply fluid to the various systems upon demand. Each pump is controlled by a switch on the forward overhead panel. A filter in the pressure line from each pump filters the fluid before it enters the various systems. A pressure switch in the pressure line from each pump is connected to a pump law pressure warning light in the control cabin to provide an indication of law hydraulic pressure. A pressure relief valve protects the system against damage by abnormally high pressures. A pump case drain filter in each pump return line is provided to detect incipient pump failures and to filter return fluid before it enters the reservoir. A hydraulic fluid heat exchanger in the return line common to both system B pumps is installed in the No. 2 fuel tank. The heat exchanger is provided to cool the hydraulic fluid by transferring heat from it to the fuel. A system return filter, just ahead of the reservoir, filters return fluid from the systems supplied by system B. Hydraulic fluid overheat is sensed by a switch installed in the system return line and indicated by a warning light on the forward overhead panel. For detailed description and operation of the system B indicating and warning systems, refer to the applicable section.
　
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