S 865-008
(8)
Set the GEN 2 or the right APU GEN switch back to the ON position.
S 715-009
(9)
Make sure the HYD PUMPS A ELEC 2 LOW PRESSURE light goes off.
S 865-010
(10)
Set the applicable switch, on the P5 panel, to the OFF position to remove electrical power from the system B pump:
(a)
The GEN 1 switch (if the engine is your supply of electrical power).
(b)
The left APU GEN switch (if the APU is your supply of electrical power).
S 715-011
(11)
Make sure the HYD PUMPS B ELEC 1 LOW PRESSURE light, on the P5 panel, comes on.
S 865-012
(12)
Set the GEN 1 or the left APU GEN switch back to the ON position.
S 715-013
(13)
Make sure the HYD PUMPS B ELEC 1 LOW PRESSURE light goes out.
D. Put the Airplane Back to Its Usual Condition
S 865-015
(1)
Set the HYD PUMPS A ENG 1 and the HYD PUMPS B ENG 2 switches, on the P5 panel, to the ON position.
S 865-016
(2)
Set the FLT CONTROL and the SPOILER systems A and B switches, on the P5 panel, to the ON position.
S 865-017
(3)
Set the HYD PUMPS A ELEC 2 and the HYD PUMPS B ELEC 1 switches to the OFF position.
(4)
Remove electrical power if it is not necessary (Ref 24-22-00/201).
S 865-018
TASK 29-15-22-705-059
3. Ground Fault Protection System Test___________________________________
A. Special Tools and Equipment
(1) Test Equipment, Ground Fault Protection, Hydraulic System F72917-19
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
29-15-22
ú ú 02 Page 502 ú Jul 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
B.
C.
D.
E.
A
737-300/400/500MAINTENANCE MANUAL
References
(1)
24-22-00/201, Manual ControlAccess
(1)
Location Zone 215 Main Wheel Well - left 216 Main Wheel Well - right
(2)
Access Panel P6-1 Circuit Breaker Panel P6-2 Circuit Breaker Panel
Prepare for the Test
S 865-079
(1)
Supply electrical power (Ref 24-22-00/201).
S 865-019
(2)
Open the applicable circuit breakers and attach DO-NOT-CLOSE tags:
(a)
P6-2 Panel
1) ELEC HYD PUMP CONT SYS A
2) ELEC HYD PUMP CONT SYS B
(b)
P6-11 Panel
1) ELEC HYD PUMP SYS B
(c)
P6-12 Panel
1) ELEC HYD PUMP SYS A
S 035-020
(3) Disconnect the electrical connector from the EMDP.System A Ground Fault Detector Test
S 045-067
WARNING: YOU MUST CONNECT THE GROUNDING CABLE FOR THE TEST EQUIPMENT TO
_______ THE AIRPLANE GROUND BEFORE YOU CONNECT THE ELECTRICAL CONNECTOR FOR THE PUMP TO THE TEST EQUIPMENT. INJURY TO PERSONS CAN OCCUR.
(1)
Disconnect the electrical connector from the system A EMDP.
S 435-022
(2)
Connect the test equipment connector to the electrical connector for the EMDP.
S 865-023
(3)
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a)
P6-2 Panel
1) ELEC HYD PUMP CONT SYS A
(b)
P6-12 Panel
1) ELEC HYD PUMP SYS A
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
29-15-22
ú ú 02 Page 503 ú Jul 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
(4) S 865-024Set the HYD PUMPS A ELEC 2 switch, on the P5 panel, to the ON position.
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機(jī)維護(hù)手冊(cè) 液壓 HYDRAULIC POWER(95)
