(3)  
If sufficient contamination is found in system A pressure and return filter, to warrant a pump change proceed with the following:

(a)  
Flush hydraulic pressure line. Refer to 29-11-0, Hydraulic System A - MP.

(b)  
Remove and thoroughly clean filter bowls. Replace with clean elements. Refer to 29-11-71, System A Hydraulic Pressure Filter and 29-11-111, System A Hydraulic Return Filter.

500 
May 15/67  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  29-11-0 Page 601 

SYSTEM A HYDRAULIC RESERVOIR - REMOVAL/INSTALLATION
1. General
A.  Take precaution to prevent spilling hydraulic fluid on the airplane. Should any fluid spill on the airplane, decontaminate. Refer to Chapter 12, Cleaning and Washing.
2.   Equipment and Materials
A.  Suitable container for draining hydraulic fluid
B.  Regulated source of nitrogen - 0- to 200-psi maximum pressure
C.  Skydrol Assembly Lube - MCS 352 or Fire-Resistant Hydraulic Fluid, BMS\3-11
3.  Prepare Hydraulic Reservoir for Removal
A.  Depressurize hydraulic system s A and B. Refer to 29-11-0, Hydraulic System A and 29-12-0, Hydraulic System B - MP.
B.  Tag hydraulic systems A, B and standby pump switches to prevent operation.
C.  Depressurize hydraulic reservoirs. Refer to 29-09-300, Hydraulic Reservoir Pressurization System - MP.
D.  Open tire burst protector screen doors.
E.  Open drain valve and drain fluid from reservoir.
F.  Open drain valve on system B reservoir and drain fluid until balance line between A and B reservoir is empty.
4.  Remove Hydraulic Reservoir
A.  Disconnect reservoir pressurization line (2, Fig. 401).
B.  Disconnect hydraulic lines (6), (7), (8), (10), and (11) from reservoir.
C.  Install protective covers over fittings and hoses.
D.  Disconnect electrical connector (3) from fluid quantity transmitter (4).
E.  Remove mounting bolts (l) and remove reservoir.
F.  Remove fluid quantity transmitter (4). Refer to 29-33-11, Fluid Quantity Transmitter - RI.
500 
Feb 15/73  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  29-11-11 Page 401 

F86820
System A Hydraulic Reservoir Installation  501 
29-11-11  Figure 401  Jun 20/85 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

5.  Prepare Hydraulic Reservoir for Installation
A.  Check that reservoir is clean and mounting surfaces are free from foreign material. Make sure that foreign material does not enter reservoir during maintenance procedures.
B.  Install drain valve (9, Fig. 401) if not included on reservoir.
(1)  
Apply assembly lube or hydraulic fluid to O-ring and install in groove of drain valve flange.

(2)  
Position drain valve on flange. Install mounting bolts and lockwire.

(3)  
Place drain valve handle in CLOSED position and install lockwire.

C.  Install O-rings, unions and reducers in reservoir ports. Apply assembly lube or hydraulic fluid O-rings and fittings before installation.
D.  Install fluid quantity transmitter (4) (Ref 29-33-11 RI).
6.  Install Hydraulic Reservoir
A.  Place reservoir in mounting position and install mounting bolts (1, Fig. 401).
B.  Connect electrical connector (3) to fluid quantity transmitter.
C.  Connect all hydraulic lines to reservoir.
CAUTION:  PRIOR TO INSTALLING HOSE HALF OF QUICK DISCONNECT, VISUALLY CHECK FOR DISCONNECT POPPET STRAIGHTNESS. AFTER QUICK DISCONNECT CONNECTION, CHECK THAT INDICATOR PINS ARE EXTENDED A MINIMUM OF 0.06 INCH. IF INDICATOR PINS ARE NOT PROPERLY EXTENDED, FLUID FLOW WILL BE RESTRICTED OR COMPLETELY STOPPED AND RESERVOIR AND/OR PUMP DAMAGE MAY RESULT.
IF EXCESSIVE TORQUE IS REQUIRED WHEN RECONNECTING THE TWO HALVES OF THE QUICK DISCONNECT, DISASSEMBLE THE FITTING AND CHECK FOR POPPET STRAIGHTNESS AGAIN.
D.  Connect reservoir pressurization line (2).
E.  Service hydraulic reservoir (Ref Chapter 12, Servicing).
F.  Pressurize hydraulic reservoir and check for leaks (Ref 29-09-300 MP).
G.  Close and latch tire burst protector screen doors.
H.  Remove tags from hydraulic pump switches.
501 
Jun 20/90  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  29-11-11 Page 403 

HYDRAULIC SUPPLY (FIRE) SHUTOFF VALVE - REMOVAL/INSTALLATION
1.  General
A.  The fire shutoff valves are installed in the supply lines to the engine-driven pumps and are mounted in the rear spar area just outboard of the wheel wells. A container of about 4.5-gallon capacity will be necessary to catch fluid when disconnecting the supply lines from the valve. Should any fluid spill on the airplane, the affected area must be decontaminated. Refer to Chapter 12, Cleaning and Washing.
　
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