(f)
Check No. 2 fuel tank for 1675 pounds (760 kg) minimum fuel before operating B pumps.
(g)
Check that the temperature of the hydraulic fluid is warm (70°F or above) by feeling reservoir. If fluid is not warm, proceed as follows: 1) Open the ground interconnect valve (set parking brakes if not set). 2) Position flight controls and spoiler switches to ON. 3) Pressurize hydraulic system using either a system B pump or the hydraulic
service cart. 4) Exercise flaps to warm fluid to 70°F or above. 5) Operate all control surfaces through at least two complete cycles after fluid is
warm.
6) Position thrust reverser control lever to STOWED.
7) Position speed brake lever to DOWN.
8) Position flap lever to 25 units and allow flap position to stabilize.
9) Switch OFF B system pumps.
(h)
Pull standby pump NORMAL (No. 1 Gen Bus) and ALTERNATE (No. 2 Gen Bus) circuit breakers. Switches are located on the P6 panel, back of copilot's seat, just above floor level.
(i)
Position thrust reverser override switches to NORMAL.
(j)
Position antiskid switches to OFF.
(k)
Position yaw damper switch to OFF.
(l)
Check that the autopilot switches are in DISENGAGED position.
(m)
Position alternate flap switch to OFF.
(n)
Position alternate flap arm switch to ARM.
(o)
Position flight control switches A and B to OFF.
(p)
Position spoiler switches A and B to OFF.
(q)
Place stabilizer trim in the green band.
(r)
Position aileron trim control to zero.
(s)
Place landing gear handle in OFF position.
(t)
Check ground interconnect valve switch is CLOSED.
(u)
Position flap lever to 40 units (flap position should remain at 25 units).
(v)
Place manual hydraulic isolation shutoff valves No. 1 thru 6 to the CLOSED or OFF position. Gain access to the valves through the tail compartment access door (Fig. 603).
NOTE: This step does not apply when performing Procedure 1.
(w)
Place manual landing gear isolation valves to CLOSED position. Valves are located in left wheel well.
NOTE: This step does not apply when performing Procedure 1.
(x)
Pressurize hydraulic system.
NOTE: Use system B pump which has ammeter connected to it when not using hydraulic service cart for hydraulic power.
(y)
Check that the system B pressure gage reads above 2800 psi.
NOTE: This step does not apply when performing Procedure 1.
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(z) Turn off hydraulic pump and note pressure decay within a 60-second period. 1) If system B pressure decays to 0 within the 60-second period, the system B pressure module relief valve is probably faulty and should be replaced before proceeding with the test.
(aa) Pressurize hydraulic system and allow pressure to stabilize.
NOTE: Hydraulic pressure should exceed 2800 psi throughout the test. Before recording each ammeter or flowmeter reading, operate flight control being checked two complete cycles and wait 20 to 30 seconds or until ammeter or flowmeter has stabilized.
501
Nov 15/77 29-00
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Manual Shutoff Valve Modules 500
29-00Page 608 Figure 603 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/85
F85904
509 Pump Characteristic Graph
May 15/73 Figure 604 29-00
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(4) Check Internal Leakage (Procedure 1).
NOTE: The following procedure determines total systems A and B internal leakage and the need for further testing.
(a)
Prepare for check per par. C.(3).
(b)
If ammeter is used, set for highest range.
(c)
With system B pump on, record reading for system B basic reference.
NOTE: When ammeter is being used, record amp reading for each step to the nearest 0.1 amp. When flowmeter is being used, record reading for each step to the nearest 100 cc/min.
(d)
Switch system B spoilers to ON. With control wheel centered, position speed brake handle mid way between ARMED and FLIGHT detent.
(e)
Switch system B flight controls on.
(f)
Enter AFCS BITE as follows:
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