10) Remove the bolts connecting the input rod to the standby PCU input crank and the aft quadrant torque tube, reference Fig. 610. Remove input rod.
NOTE: Bolts and input rod must be retained and reinstalled after completion of test.
11) Pressurize the B hydraulic system via the electric motor pump.
WARNING: DO NOT PROCEED UNTIL SECTION 48 PERSONNEL HAVE COMPLETED STEPS 9) AND 10), AND ALL EMPENNAGE FLIGHT CONTROL SURFACES ARE CLEAR.
12) Position B system flight control switch to on.
13) Position ALTERNATE FLAP switch to ARM. Allow system to stabilize and take
basic reference reading, enter as step 4 in Fig. 607. 14) Position A system flight control switch to STDBY RUD. 15) Manually displace the standby PCU input crank as far as possible in the aft
direction. Wait one minute and take reading, enter as step 5 in Fig. 607.
WARNING: PRIOR TO AND WHILE MANUALLY DISPLACING THE STANDBY PCU INPUT CRANK ENSURE THAT ALL EMPENNAGE FLIGHT CONTROL SURFACES AND THE RUDDER HINGE ARE CLEAR.
16) Manually displace the standby PCU input crank as far as possible in the forward
direction. Wait one minute and take reading, enter as step 6 in Fig. 607. 17) Complete the worksheet given in Fig. 607. 18) Place ALTERNATE FLAP switch to OFF. 19) Depressurize the B hydraulic system. 20) Set A and B flight control switches to OFF. 21) Reconnect the input rod to the standby PCU input crank and aft quadrant torque
tube.
(b) Post leakage check operational test.
1) Pressurize standby hydraulic system by setting the A system flight control switch to STBY RUD.
WARNING: ENSURE ALL EMPENNAGE FLIGHT CONTROL SURFACES ARE CLEAR.
2) Observe rudder reaction, rudder should not move to a hard-over position. 3) Cycle rudder pedals hard-over right and verify that the rudder moves hard-over right. Slowly allow rudder to recenter.
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4) Measure alignment of rudder with index mark. Rudder alignment should be within 1.5 inches. 5) Cycle rudder pedals hard-over left and verify that the rudder moves hard-over left. Slowly allow rudder to recenter. 6) Measure alignment of rudder with index mark. Rudder alignment should be within 1.5 inches.
7) If any of the following conditions exist, the input rod has not been correctly reinstalled. a) Rudder alignment with the index mark is not within 1.5 inches. b) Cycling of rudder pedals is limited. c) Rudder moves hard-over without being commanded. d) Unusually high pedal forces experienced.
8) If any condition given in step 7) exists, check input rod for proper installation and repeat par. 1.D.(4)(b).
(5) Restore Airplane to Normal
(a)
Remove electrical power.
(b)
Remove harness (if used) and connect electrical connector to pump.
(c)
Remove flowmeter (if used).
(d)
Service hydraulic reservoir (Ref Chapter 12, Hydraulic Fluid Servicing).
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Jun 20/90 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 29-00 Page 627
STEP DESCRIPTION REF. STEP
1 BASIC REFERENCE 1.D.(4)(a)3)
2 BASIC REFERENCE + NULL 1.D.(4)(a)4)
3=2-1 NULL (PER RIGGING) -
4 BASIC REFERENCE 1.D.(4)(a)13)
5 BASIC REFERENCE + H/O LEFT SEAL LEAKAGE 1.D.(4)(a)15)
6 BASIC REF. + H/O RIGHT SEAL LEAKAGE 1.D.(4)(a)16)
7=5-4 H/O LEFT SEAL LEAKAGE -
8=6-4 H/O RIGHT SEAL LEAKAGE -
AMPS
FLOW (cc/min) reference Fig. 608 LIMIT
(cc/min)
1000
400 400
Standby Hydraulic Internal Leak Check 500
29-00 Figure 607 Jun 20/90
Page 628
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
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