(3)  
Place the battery switch to ON position.

(4)  
Check that the No. 1 and 2 System B pump (NORMAL and ALT) circuit breakers on P6 load control center are closed.

(5)  
With flight control switches OFF and ground interconnect valve closed, pressurize system B hydraulic system by switching No. 1 pump to ON. Check that No. 1 pump is operating and the no flow pressure stabilizes between 2925 and 3100 psi.

(6)  
Apply power to the No. 2 generator bus by placing either the No. 2 generator or APU generator right switch to ON.

(7)  
Remove power from the No. 1 generator bus by switching to OFF the switch placed to ON in (1). System B pump No. 1 should continue to operate.

(8)  
Place pump No. 1 switch to OFF position. Check that pump stops operating.

(9)  
Reapply power to the No. 1 generator bus.

(10)
Open No. 1 system B pump (ALT) and No. 2 system B pump (NORMAL and ALT) circuit breakers.

(11)
Place pump No. 1 switch to ON. Check that pump operates and no flow pressure stabilizer between 2925 and 3100 psi.

(12)
Place pump No. 1 switch to OFF. Check that pump stops operating.

(13)
Remove power from the No. 1 generator bus.

(14)
Close No. 1 system B pump (ALT) circuit breaker. Open No. 1 (NORMAL) circuit breaker.

(15)
Place pump No. 1 switch to ON. Check that pump operates and no flow pressure stabilizes between 2925 and 3100 psi.

(16)
Place pump No. 1 switch to OFF. Check that pump stops operating.

(17)
Close No. 1 system B pump (NORMAL) and No. 2 system B pump (NORMAL and ALT) circuit breakers.

(18)
Pressurize hydraulic system B by switching No. 2 pump to ON. Check that pump operates and no flow pressure stabilizes between 2925 and 3100 psi.

(19)
Apply power to the No. 1 generator bus. Remove power from the No. 2 generator bus. Check that pump continues operating.

(20)
Place pump No. 2 switch to OFF. Check that pump stops operating.

(21)
Reapply power to the No. 2 generator bus.

(22)
Open No. 2 system B pump (ALT) and No. 1 system B pump (NORMAL and ALT) circuit breakers.

(23)
Place pump No. 2 switch to ON. Check that pump operates and no flow pressure stabilizes between 2925 and 3100 psi.

(24)
Place pump No. 2 switch to OFF. Check that pump stops operating.

(25)
Remove power from No. 2 generator bus.

(26)
Close No. 2 system B pump (ALT) circuit breaker. Open No. 2 (NORMAL) circuit breaker.

(27)
Place pump No. 2 switch to ON. Check that pump operates and no flow pressure stabilizes between 2925 and 3100 psi.

(28)
Place pump No. 2 switch to OFF. Check that pump stops operating.

(29)
Depressurize hydraulic system B (Ref 29-12-0, Maintenance Practices).

(30)
If there is no further need for electrical power on the airplane, switch generator to OFF.

513 
May 01/99  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  29-12-21 Page 501 

D.  Test Ground Fault Protection System Using Test Equipment B-F72917-( )
(1)  
Open applicable system B pump circuit breakers on P6-11 and P6-12 panels.

(2)  
Disconnect electrical connectors from system B pump No. 1 and 2.

(3)  
Connect test equipment ground to airplane frame at an approved ground.

(4)  
Connect test equipment connector to No. 1 pump electrical plug.

WARNING:  TO PREVENT SHOCK HAZARD, ASSURE THAT TEST EQUIPMENT GROUND LEAD IS SECURED TO AIRPLANE GROUND BEFORE CONNECTING TESTER TO PUMP CONNECTOR.

(5)  
Check that system B pump and pump control circuit breakers are closed on P6-11 and P6-12 panels.

(6)  
Position No. 1 pump switch to ON.

(7)  
Turn test switch S2 to NO TRIP position.

(8)  
Depress test switch S1 and check that light L1 illuminates.

(9)  
Release test switch S1.

(10)
Turn test switch S2 to TRIP position and check that light L1 goes out.

(11)
Return test switch S2 to NO TRIP position and check that light L1 does not illuminate.

(12)
Gain access to ground fault detector controller located behind decorative panel outboard of P6-1 or P6-2 panels.

(13)
Momentarily depress reset button on No. 1 pump controller.

(14)
Depress test switch S1 and check that light L1 illuminates.

(15)
Position No. 1 pump switch to OFF and check that test light L1 goes out.

(16)
Open applicable system B pump circuit breakers on P6-11 and P6-12 panels.

(17)
Disconnect test equipment connector from No. 1 pump electrical plug.
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 液壓 HYDRAULIC POWER(59)