less).
(d)
Manually open ground interconnect valve by placing ground interconnect valve indicator to position 2.
CAUTION: GROUND INTERCONNECT VALVE SHOULD NOT BE OPENED MANUALLY WITH ELECTRICAL POWER ON. THIS MIGHT CAUSE DAMAGE TO THE INTERCONNECT VALVE MOTOR.
(e)
Pressurize hydraulic systems A and B to 3000 psi through the ground power modular unit using hydraulic service cart (Ref\29-11-0 and 29-12-0).
(f)
Check that pressure indicators inside the control cabin read 3000 + 100 psi.
(8)
Deleted.
505
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500 Hydraulic Brake Pedal Adjustment
May 15/67 Figure 501 32-41-0
Page 503
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Hydraulic Brake System Cables & Brake Metering Valve 500
32-41-0 Control Quadrant Adjustment Apr 01/97
Page 504 Figure 502 (Sheet 1)
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Hydraulic Brake System Cables & Brake Metering Valve
Apr 01/97 Control Quadrant Adjustment 32-41-0
Figure 502 (Sheet 2) Page 505
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
C. Test Main Gear Brakes
(1)
Fully depress and hold the captain's or first officer's brake pedals against stop. Check pressure at each brake to be 3000 + 100 psi (Fig. 503).
(2)
Release brake pedals and check each brake assembly for release by observing the brake stack movement. Check that gage pressure at the brakes falls to 50 psi or less.
(3)
Depressurize hydraulic systems leaving the brake system pressurized with the
accumulators.
(4)
Observe brake pressure after three complete brake applications. Pause between each application to obtain maximum pressure. Brake pressure shall not be less than 800 psi at the brakes.
(5)
Pressurize A and B hydraulic systems to 3000 psi (Ref 29-11-0 and 29-12-0). Pull override trigger and place landing gear control lever in UP position. Check that pressure at each brake rises to 350 psi within 4 seconds and stabilizes above this pressure.
WARNING: CHECK THAT GROUND LOCK ASSEMBLIES ARE INSTALLED IN ALL LANDING GEAR TO PREVENT INADVERTENT OPERATION OF GEAR. INJURY TO PERSONNEL AND/OR EQUIPMENT COULD RESULT IF GEAR RETRACTS.
(6)
Place landing gear control lever in the OFF position. Check release of each brake assembly as observed by the brake stack release.
(7)
Place landing gear control lever in the DN position and check that each brake assembly remains released.
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D. Restore System to Normal
(1)
Depressurize hydraulic System A and B. Refer to 29-11-0 and 29-12-0.
(2)
Remove pressure gages from each brake bleed port and install bleed screw.
(3)
Pressurize hydraulic systems A and B. (Refer to 29-11-0 and 29-12-0.) Check that accumulators are precharged per placard.
(4)
Bleed brakes by depressing brake pedals slowly and fully for six times and check brake operation by observing friction pin movement in response to brake pedal movement.
(5)
Manually close ground interconnect valve by placing ground interconnect valve indicator to position 1.
CAUTION: GROUND INTERCONNECT VALVE SHOULD NOT BE CLOSED MANUALLY WITH ELECTRICAL POWER ON. THIS MIGHT CAUSE DAMAGE TO THE INTERCONNECT VALVE MOTOR.
(6)
Check that ground interconnect valve circuit breaker on P6 is closed.
(7)
Set parking brake.
(8)
Remove System A and B hydraulic power. Refer to 29-11-0 and 29-12-0.
(9)
Determine if there is any further need for electrical power on the airplane, if not, remove external power.
500
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BRAKE METERING VALVE CONTROL QUADRANT - REMOVAL/INSTALLATION
1. General
A. This procedure covers removal/installation of brake metering valve control quadrants for both captain's and first officer's brake system.
2. Equipment and Materials
A. Gear Ground Lock Assembly (Ref 32-00-01)
3. Prepare for Removal
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