737 AMM 飞机维护手册 液压 HYDRAULIC POWER(18)

曝光台 注意防骗 网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者

7)  Allow flow to stabilize and take reading for B system ail. A/P actuator + basic reference leakage. Record B system flow on Fig. 609 as step #2 - B ail. + basic ref.
8)  Exit BITE by pressing PAGE key.
NOTE:  This step disengages the B A/P actuators.
9)  Allow flow to stabilize and record system basic reference flow on Fig. 609 as step #3 - basic ref.
10)  In Fig. 609 subtract step 3 from step 2 to get the flow associated with the B system ail. A/P actuator, record as step #4 - B ail. A/P actuator leakage.  Maximum permissible 2000 cc/min.
11)  In Fig. 609 subtract step 3 from step 1 to get the flow associated with the A system ail. A/P actuator, record as step #5 - A ail. A/P actuator leakage.  Maximum permissible 2000 cc/min.
(g)  Test A & B elevator A/P actuators. 1) Open isolation valves 1-6. 2) Allow flow to stabilize and record new system basic reference flow on Fig. 609
as step #6 - new basic ref. 3) Repeat step 1.C.(9)(f)2). 4) Allow flow to stabilize and take reading for A system ail. and elev. A/P actuator +
new basic reference leakage. Record A system flow on Fig. 609 as step #7\- A
ail. + elev. + new basic ref. 5) Disengage A/P A. 6) Engage A/P B to CMD. 7) Allow flow to stabilize and take reading for B system ail. and elev. A/P actuator +
new basic reference leakage. Record B system flow on Fig. 609 as step #8\- B ail. + elev. + new basic ref. 8) Exit BITE by pressing PAGE key.
NOTE:  This step disengages the B A/P actuators.
9)  In Fig. 609 subtract steps 5 and 6 from step 7 to get the flow associated with the A system elev. A/P actuator, record as step #9\- A elev. A/P actuator leakage.  Maximum permissible 2000 cc/min.
10)  In Fig. 609 subtract steps 4 and 6 from step 8 to get the flow associated with the B system elev. A/P actuator, record as step #10\- B elev. A/P actuator leakage. Maximum permissible 2000 cc/min.
(10) Restore airplane to normal.
(a)  
Open manual shutoff valves No. 1 thru 6 if closed. Secure safety bar over the shutoff valve module with bolt and nut (Fig. 603).

(b)  
Verify that shutoff valves No. 1 thru 6 are open (handles vertical) by performing the following test. 1) Check that hydraulic system A and B are pressurized. 2) Position A and B flight control switches to OFF. 3) Verify valve No. 4 is open.

a)  Retract the flaps to zero.
NOTE:  The flaps must be fully retracted for the FEEL DIFF PRESS light to illuminate.
b)  Position B flight control switch to ON and check that FEEL DIFF PRESS lights (P5) is illuminated.
512 May 01/00 29-00 Page 618G/618H BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

SYSTEMS AND REFERENCES TO STEPS IN PROCEDURES 3 AND 5  SYSTEM COMPONENTS  COMPONENT REFERENCES TO STEPS IN PROCEDURE 3 AND 5  FLOW LIMIT (CC/MIN) 
System B basic reference [Ref step C.(4)]  Total system  14,500 
System B spoilers [Ref steps C.(6)(b) thru C.(6)(f)]  Spoiler down leakage  C.(6)(c)  500 
Right wing down leakage, No. 7 spoiler PCU null  C.(6)(d)  2,000 
Left wing down leakage, No. 2 spoiler PCU null  C.(6)(e)  2,000 
No. 2 and 7 PCU valve null  C.(6)(f)  4,000 
System B ailerons [Ref steps C.(6)(g) thru C.(6)(l)]  Aileron PCU null  C.(6)(h)  3,000 
Aileron PCU hardover, cylinder and bleed leakage  C.(6)(i)  1,500 
System B elevators [Ref steps C.(6)(j) and C.(6)(m) thru C.(6)(q)]  Elevator PCU null  C.(6)(m)  3,000 
Elevator PCU hardover, cylinder and bleed leakage  C.(6)(n)  1,500 
System B rudder [Ref steps C.(6)(o) and C.(6)(r) thru C.(6)(v)]  Rudder PCU null  C.(6)(r)  3,000 
Rudder PCU hardover, cylinder and bleed leakage  C.(6)(s)  1,200 
Yaw damper system leakage  C.(6)(u)  2,000 
System B autopilot [Ref step C.(8)] PROCEDURE 5  System B autopilot aileron actuator  C.(8)(f)  2,000 
System B autopilot elevator actuator  C.(8)(e)  2,000 

502  Component Testing Chart 
Jun 20/88  Figure 605 (Sheet 1)  29-00 
Page 619 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

 Component Testing Chart  502 
29-00  Figure 605 (Sheet 2)  Oct 20/84 
Page 620 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

501  Component Testing Chart 
Jun 20/88  Figure 605 (Sheet 3)  29-00 
Page 621 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 
　
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