(24)
Operate trailing edge flaps twice from 0 to 10 to 0 degrees. This will also operate leading edge devices. Return flap control lever to normal.
(25)
Operate flight spoilers and ailerons by turning the control wheel through five full stroke cycles from LEFT to RIGHT to LEFT. Return control wheel to normal and turn OFF A and B SPOILER and FLT CONTROL switches.
(26)
Operate thrust reverser through three full cycles. Refer to Chapter 78, Thrust Reverser System.
(27)
Shut off fluid source. Discharge brake accumulator by pumping brake pedals full stroke. Turn ON fluid source to recharge the brake accumulator. Shut off fluid source. Discharge brake accumulator by pumping brake pedals full stroke.
(28)
Turn on fluid source. Operate the ground spoilers through two full stroke cycles from DOWN to UP to DOWN.
(29)
With fluid source operating, open bleed valves on each brake and allow at least 2 quarts of fluid to bleed from each brake.
(30)
Shut off fluid source.
(31)
Disconnect fluid source and reconnect lines.
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B. Drain and purge standby hydraulic system.
(1)
Disconnect standby return hose from standby reservoir. Plug port in reservoir. Lengthen return hose as required and route to an empty container.
(2)
Fill standby reservoir through normal fill system with new fluid. Refer to 12-12-0, Hydraulic Fluid Servicing.
(3)
Pressurize standby hydraulic system. Operate standby rudder through two full stroke cycles from LEFT to RIGHT to LEFT. Return rudder pedal to normal position. Turn OFF standby pump.
(4)
Reconnect standby return hose to reservoir.
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C. After all hydraulic fluid has been replaced, remove and install new filters at the following location:
(1)
System A hydraulic pump case drain filters. Refer to 29-11-41.
(2)
System A hydraulic pressure filter. Refer to 29-11-71.
(3)
System A hydraulic return filter. Refer to 29-11-111.
(4)
System B hydraulic pressure filter. Refer to 29-12-41.
(5)
System B hydraulic pump case drain filter. Refer to 29-12-71.
(6)
System B hydraulic return filter. Refer to 29-12-81.
(7)
Standby hydraulic system case drain filter. Refer to 29-21-31.
(8)
Standby hydraulic system pressure filter. Refer to 29-21-51.
4. Return System to Normal
A. Service hydraulic reservoirs. Refer to 12-12-0, Hydraulic Fluid Servicing.
B. Pressurize hydraulic reservoirs. Refer to 29-11-0.
C. Pressurize system B with ground interconnect valve open. This will also pressurize system A. Refer to 29-11-0, Hydraulic System A - Maintenance Practices.
D. Check for leaks on all connections.
E. Depressurize A and B systems.
F. Position GROUND INTERCONNECT valve switch to CLOSE.
G. Pressurize standby system and check for leaks.
H. Return standby system to normal.
I. Determine if there is any further need for electrical power on airplane. If not, remove electrical power.
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HYDRAULIC POWER - INSPECTION/CHECK
1. Check Hydraulic System
A. General
(1) The following external and internal hydraulic leakage checks are provided to aid the operator in determining more readily the general condition of the hydraulic system and its components. For external leakage, see par. 1.B, for systems A and B internal leakage see par. 1.C and for standby system internal leakage, see par. 1.D.
B. Hydraulic System External Leakage Check
(1) General
(a)
The following leakage check chart provides recommended allowable external leakage rates for the various possible leakage sources. These rates have been determined to be what is tolerable without adversely affecting component or system operation. The operator should evaluate each of the leakage rates with respect to his operation and establish a maximum accumulative leakage based on his average flight duration.
NOTE: Fluid level may be 2 gallons below full level without impairing hydraulic systems operation.
(b)
To assure a proper evaluation, the following should be considered when checking various components for leakage. 1) The seal obtained at B-nut tube connections is obtained on metal-to-metal
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