(2)
Using the same equipment as specified in item (1), an Expanded Fault History Display Procedure (AMM 24-11-11/501) may be used to determine a more detailed descripition of faults internal and external to the VSCF.
(3)
VSCF trips will make a FF indication show on the M238 annunciator panel. If the FF indication shows, troubleshoot the AC Generation System (AMM 24-21-00/101).
(4)
The VSCF is on the accessory gearbox at the 8 o'clock position.
B.
References
(1)
AMM 24-11-11/401, Variable Speed Constant Frequency
Generator/Converter
(2)
AMM 24-21-00/101, AC Generation System
(3)
AMM 24-22-00/201, Manual Control
C.
Access
(1)
Location Zones
101 Left Control Cabin - P5 overhead panel
506 Engine 1 - Accessory Gearbox, 8 o'clock
606 Engine 2 - Accessory Gearbox, 8 o'clock
(2)
Access Panels
5740 CSD Access Door - Engine 1
5840 CSD Access Door - Engine 2
D.
Procedure (Fig. 501)
(1)
Supply electrical power to the airplane busses from the APU
S 865-122-003
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù.
VARIABLE SPEED CONSTANT FREQUENCY ú 24-11-11
GENERATOR/CONVERTERS WITH THE THREE ú CONFIG 3 LIGHT DISPLAY MODULE ú 01 Page 509 ú Nov 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
S 985-123-003
(2) On the P1-1 or P2-2 instrument panel, push the LIGHTS switch to BRT.
S 155-125-003
(3) Open the CSD access door.
S 985-126-003
(4) Push and release switch S2 to make sure the VSCF is connected. Ignore any light illumination. (S1 will not function if the VSCF is disconnected.)
S 985-127-003
(5) Push and hold switch S1 on the VSCF to see three messages. (a) DISPLAY MODULE SELF-TEST RESULTS (b) LAST VSCF FAULT (c) LAST SYSTEM FAULT SINCE RESET
S 985-128-003
(6) All three messages will be displayed in less than 10 seconds. Release switch S1.
(a) Make sure each message is a sequential flash of each light (left, center, right). This indicates a NO FAULT condition for each message. 1) If the first message (DISPLAY MODULE SELF-TEST RESULTS) is not a sequential flash of each light, do the following steps: a) Replace the Display Module (AMM 24-11-71/401) unless subsequent troubleshooting indicates a need to replace the VSCF unit.
NOTE:____ The VSCF can be used without an operable Display Module.
2) 3) b) Use VSCF NVM Interrogation procedure to troubleshoot cause of system trip (AMM 24-21-00/101).If the second message (LAST VSCF FAULT) is not a sequential flash of each light, do one of the following steps: a) Replace the VSCF unit if the indicated fault is VSCF FAULT - PROTECTIVE TRIP (AMM 24-11-11/401). b) Replace the VSCF unit at the next scheduled AC Generation System Test interval if the indicated fault is VSCF FAULT - PASSIVE (AMM 24-11-11/401).If the third message (LAST SYSTEM FAULT SINCE RESET ) is a sequential flash of each light, release switch S1 and go to test step (9). Otherwise, release S1, note the indicated conditon and continue with the next test step.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù.
VARIABLE SPEED CONSTANT FREQUENCY ú 24-11-11
GENERATOR/CONVERTERS WITH THE THREE ú CONFIG 3 LIGHT DISPLAY MODULE ú 01 Page 510 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
S 765-129-003
(7) Use switch S2 to correlate fault messages to the flight in question or use switch S2 to verify that corrective action and the subsequent engine runup and shutdown has resulted in no new fault messages. If a system fault is displayed which requires maintenance action, troubleshoot the AC Generation System (AMM 24-21-00/101).
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737-300 400 500 AMM 飞机维护手册 电源 ELECTRICAL POWER(54)
