(Dimensions are in inches)
H. When gap dimensions are within limits, tighten mounting bolts.
I. Apply fillet seal of BMS 5-26 over fittings at rear spar inside tank (Ref 51-31-0).
J. Clean, install, and check bonding strap (Ref 20-10-181, 20-10-185 and 20-22-01). Maximum resistance is 5 milliohms.
K. Inspect fuel tank to be certain all parts, tools and foreign matter have been removed.
L. Install fuel tank access panel No. 1 (Ref 28-10-0 MP, Purging and Entry).
M. Install and tighten tubing connection to heat exchanger at rear spar.
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N. Fill fuel tank to a minimum of 250 gallons (1700 lbs/775 kg) (Ref 12-11-0).
O. Check fuel tank access panel No. 1 and heat exchanger bulkhead fittings at rear spar for fuel leaks.
P. Pressurize hydraulic reservoir (Ref 29-09-300 MP).
Q. Pressurize system A by motoring engines (Ref 71-09-100) or by using system B electric pump through ground interconnect (Ref 29-12-0 MP).
R. Check tubing-to-heat exchanger bulkhead fittings at rear spar for hydraulic leaks.
S. Depressurize hydraulic systems (Ref 29-11-0 MP).
T. Service applicable hydraulic system reservoir (Ref 12-12-0).
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HYDRAULIC SYSTEM A MODULE UNIT - REMOVAL/INSTALLATION
1. General
A. System A module unit is mounted on the forward bulkhead of the left wheel well (Fig. 401). A container will be necessary to catch fluid from the module unit and disconnected hydraulic lines when removing the unit. Should any fluid spill on the airplane, the affected area must be decontaminated (Ref Chapter 12, Cleaning and Washing).
2. Equipment and Materials
A. Skydrol Assembly Lube - MCS 352 or Hydraulic Fluid - BMS 3-11
3. Remove System A Module Unit (Fig. 401)
A. Depressurize hydraulic system A (Ref 29-11-0 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.
E. Disconnect and plug hydraulic lines. Plug open ports on module.
F. Remove mounting bolts and remove module unit.
4. Install System A Module Unit (Fig. 401)
A. Install O-rings and unions in module hydraulic ports. Ensure that check valve is installed in port 6. Lubricate with assembly lube or hydraulic fluid.
CAUTION: ENSURE FOREIGN MATTER DOES NOT ENTER MODULE PORTS OR CONNECTING LINES DURING INSTALLATION.
B. Place module unit in mounting position and install mounting bolts.
C. Connect hydraulic lines to module.
D. Connect electrical connectors to low pressure warning switches.
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F87170
System A Module Installation 500
29-11-61 Figure 401 Nov 01/75
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
E. Close SYSTEM A-B PRESSURE circuit breaker on P6 panel.
F. Check low pressure switch operation and check for leaks.
(1)
Position HYD PUMPS ELEC 1 switch to ON.
(2)
Position HYD PUMPS ENG 1 switch to ON.
(3)
Pressurize hydraulic system A by motoring engine No. 1 (Ref 29-11-00 MP).
(4)
Check that ENG 1 LOW PRESSURE light extinguishes.
(5)
Check that ENG 2 LOW PRESSURE light remains illuminated.
(6)
Check pressure module for leaks.
WARNING: ENSURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR OF FLAPS.
(7)
Stop motoring engine No. 1. Operate flaps until ENG 1 low pressure light illuminates.
(8)
Position HYD PUMPS ENG 2 switch to ON.
(9)
Pressurize hydraulic system A by motoring engine No. 2 (Ref 29-11-00 MP).
(10)
Check that ENG 2 LOW PRESSURE light extinguishes.
(11)
Check that ENG 1 LOW PRESSURE light remains illuminated.
(12)
Check pressure module for leaks.
(13)
Stop motoring engine No. 2. Depressurize hydraulic system A (Ref 29-11-00 MP). Depressurize hydraulic System B (Ref 29-12-00\MP).
G. Service hydraulic reservoir (Ref Chapter 12, Hydraulic Fluid Servicing).
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