(b)
Push and hold switch S2 again to see the next flight message in sequence. Release S2.
(c)
Use switch S2 to see flight messages in sequence. Up to 40 flight messages can possibly be shown; however, only one flight message will show if all S2 flight messages are normal.
(d)
To repeat step (a) of this series, operate switch S1 to return S2 to the last flight message (the starting point of the flight message sequence).
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(8) Use switch S2 to reset the LAST SYSTEM FAULT SINCE RESET message if desired.
(a)
Push and hold switch S2 for 30 seconds to see a sequential flash of the lights.
(b)
Release switch S2.
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(9)
Close the CSD access door.
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(10)
Remove electrical power if it is not necessary (AMM 24-22-00/201).
TASK 24-11-11-765-132-003
4. Expanded Fault History Display Procedure - Variable Speed Constant Frequency
____________________________________________________________________________ Generator/Converter
___________________
A. General
(1)
This procedure may be used when performing the Fault History Display Procedure (AMM 24-11-11/501) to determine a more detailed description of faults internal and external to the VSCF.
(2)
Fault messages are expanded into two parts that are displayed sequentially to build the fault message.
(3)
The conditions that relate to the two-part fault message indications are described in the Expanded Fault Messages chart (Fig. 502).
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VARIABLE SPEED CONSTANT FREQUENCY ú 24-11-11
GENERATOR/CONVERTERS WITH THE THREE ú CONFIG 3 LIGHT DISPLAY MODULE ú 01 Page 511 ú Jul 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
B.
C.
D.
A
737-300/400/500MAINTENANCE MANUAL
(4) The three Display Module lights are used to display seven binary numbers (zero is not used), which are interpreted as their decimal equivalent by the user. Light ON is binary 1. Light OFF is binary
0.
001 = decimal 1
010 = decimal 2
011 = decimal 3
100 = decimal 4
101 = decimal 5
110 = decimal 6
111 = decimal 7
(5)
For example, a two-part fault message indication of 101 followed by 100 would be interpreted and noted by the user as 5, 4 and, using the Expanded Fault Messages chart, the corresponding condition would be OVERCURRENT TRIP, PHASE C HIGHEST.
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 ControlAccess
(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
Procedure (Fig. 502)
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(1) Supply electrical power to the airplane busses from the APU generator or the external power source (AMM 24-22-00/201).
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VARIABLE SPEED CONSTANT FREQUENCY ú 24-11-11
GENERATOR/CONVERTERS WITH THE THREE ú CONFIG 3 LIGHT DISPLAY MODULE ú 01 Page 512 ú Nov 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
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(2)
On the P1-1 or P2-2 instrument panel, push the LIGHTS switch to BRT.
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(3)
Open the CSD access door.
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