(2)
Intermittent system B pump operation is limited to five starts of any one pump in a 5-minute period. Following the fifth start, run pump for at least 5 minutes or turn pump off for a minimum of 30 minutes.
C. The following procedure cover pressurization of hydraulic systems B and A through operation of electrical-driven hydraulic system B pumps only. Pressurization of hydraulic systems A and B through operation of engine-driven hydraulic system A pumps is not covered.
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2. Aileron Hydraulic System A and B Pressurization
A. Equipment and Materials
(1) Lock Assembly - Ground F72735
B. Pressurize aileron hydraulic system A and B.
(1)
Connect electrical power to airplane.
(2)
Ensure that FLT CONTR circuit breaker on P6 circuit breaker panel is closed.
(3)
Set parking brake and install ground lock assembly in nose gear.
(4)
Position GRD INTERCONNECT switch on forward overhead panel to OPEN.
(5)
Position No. 1 or 2 system B HYD PUMPS switches on the forward overhead panel to ON.
(6)
Position FLT CONTROLS A and B switches on forward overhead panel to ON.
NOTE: To pressurize system A or system B separately, select system by appropriate positioning of FLT CONTROLS A and B switches.
C. Restore Airplane to Normal
NOTE: Perform the following steps after completing the aileron system maintenance that required pressurization.
(1)
Position No. 1 and 2 system B HYD PUMPS switches to OFF.
(2)
Position GRD INTERCONNECT switch to CLOSE.
(3)
Remove electrical power.
(4)
Remove ground lock assembly.
3. Aileron Hydraulic System A and B Depressurization
A. Equipment and Materials
(1) Flight Controls - Lock Assembly F80049-12 (Preferred) or F80049-1 (Optional) (2 required)
B. Depressurize aileron hydraulic system A and B.
(1)
Position FLT CONTROLS A and B switches on the forward overhead panel to OFF.
(2)
Open all flight control circuit breakers on P6 circuit breaker panel.
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G03248
500 Hydraulic Module Lock Installation
Feb 15/69 Figure 501 27-11-0
Page 203
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(3)
Position No. 1 and 2 system B HYD PUMPS switches on forward overhead panel to OFF.
(4)
Position GRD INTERCONNECT switch on forward overhead panel to CLOSE.
(5)
To dissipate any remaining hydraulic power, cycle rudder pedals.
(6)
If any hydraulic connections are to be disturbed, depressurize hydraulic system A and system B reservoirs. Refer to 29-09-300, Hydraulic Reservoir Pressurization System -Maintenance Practices.
(7)
Install hydraulic module. (See figure 201.)
(a)
Disconnect electrical connector from flight controls shutoff valve at system A flight controls hydraulic module in the left wheel well.
(b)
Disconnect electrical connector from flight controls shutoff valve at system B flight controls hydraulic module in right wheel well.
(c)
Manually place override lever at both flight controls shutoff valves in position 2.
(d)
Install lock on each flight controls shutoff valve and insert attaching lockpins.
C. Restore Airplane to Normal
NOTE: Perform the following steps after completing the aileron system maintenance that required depressurization.
(1)
Remove locks from system A and B flight controls hydraulic module shutoff valves and reconnect electrical connectors.
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