(18)
Connect test equipment to No. 2 pump electrical plug.

(19)
Repeat steps (6) thru (16) for No. 2 pump.

(20)
Disconnect test equipment and remove from airplane.

(21)
Install electrical connectors on No. 1 and 2 pumps.

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(22)
Close pump control circuit breakers on P6-11 and P6-12 panels.
Inspection/Check System B Electric Motor-Driven Pump

A.
Check System B Electric Motor-Driven Pump

(1)
With the applicable pump running, visually check for external leakage.

(a) Remove unit if excessive leakage is observed.

(2)
Visually check the security of mounting and for any possible external damage.

502 
Sep 20/82  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  29-12-21 Page 503 

HYDRAULIC SYSTEM B MODULE UNIT - REMOVAL/INSTALLATION
1. General
A.  System B module unit is mounted on the forward bulkhead of the right wheel well (Fig. 401). A container will be necessary to catch fluid from the module and disconnected hydraulic lines during removal. Should any fluid spill on the airplane, the affected area must be decontaminated (Ref Chapter 12, Cleaning and Washing).
2.  Equipment and Material
A.  Skydrol Assembly Lube - MCS 352 or Fire Resistant Hydraulic Fluid - BMS\3-11
3.  Remove System B Module Unit
A.  Depressurize hydraulic system\B (Ref 29-12-0 MP).
B.  Depressurize hydraulic reservoirs (Ref 29-09-300 MP).
C.  Open SYSTEM A-B PRESSURE circuit breaker on P6 panel.
D.  Disconnect pump low pressure warning switch electrical connectors (Fig. 401).
E.  Disconnect and plug hydraulic lines. Plug open ports on module unit.
F.  Remove mounting bolts and remove module unit.
4.  Install System B Module Unit
CAUTION:  ENSURE FOREIGN MATTER DOES NOT ENTER MODULE PORTS OR
CONNECTING LINES DURING INSTALLATION.

A.  Apply assembly lube or hydraulic fluid to O-rings and to the threads of couplings and unions to facilitate installation. Install O-rings and unions in module ports.
B.  Place module unit in mounting position and install mounting bolts.
C.  Connect all hydraulic lines to correct module ports.
D.  Connect electrical connectors to low pressure warning switches.
E.  Close SYSTEM A-B PRESSURE circuit breaker on P6 panel.
F.  Check low pressure switch operation and check for leaks.
(1)  
Pressurize hydraulic system B with electric motor-driven pump No. 1 (Ref 29-12-0 MP).

(2)  
Check that HYD PUMPS ELEC 1 LOW PRESSURE light extinguishes.

(3)  
Check that HYD PUMPS ELEC 2 LOW PRESSURE light remains illuminated.

(4)  
Check module for leaks.

(5)  
Position HYD PUMPS ELEC 1 switch to OFF.

WARNING:  ENSURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR OF SPOILERS.

(6)  
Operate outboard spoilers until No. 1 ELEC LOW PRESSURE light illuminates.

(7)  
Pressure hydraulic system B with electric motor-driven pump No. 2 (Ref 29-12-0 MP).

(8)  
Check that HYD PUMPS ELEC 2 LOW PRESSURE light extinguishes.

(9)  
Check that HYD PUMPS ELEC 1 LOW PRESSURE light remains illuminated.

(10)
Check module for leaks.

(11)
Position HYD PUMPS ELEC 2 switch to OFF.

(12)
Depressurize hydraulic system B (Ref 29-12-0 MP).

G.  Service hydraulic reservoirs (Ref Chapter 12, Hydraulic Fluid Servicing).
500 
Feb 20/87  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  29-12-31 Page 401 

F87630
Hydraulic System B Module Unit  500 
29-12-31  Figure 401  Nov 15/67 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

SYSTEM B HYDRAULIC PRESSURE FILTER - UNIT SERVICING
1. General
A.  The hydraulic pressure filters for system B are identical and are installed side by side in the modular unit (Fig. 301). Both pressure filters will be covered by the same maintenance procedures.
B.  A container will be necessary to catch fluid from the removed filter. Should any fluid spill on the airplane, decontaminate. Refer to Chapter 12, Cleaning and Washing.
2.  Replace Pressure Filter Element
A.  Equipment and Material
(1) Skydrol Assembly Lube - MCS 352 or Fire Resistant Hydraulic Fluid - BMS 3-11
B.  Remove Pressure Filter Element
　
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