Technical data

Product Specification
HIF-2121/R5 CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 965-1176-601 REV: D SHEET 108
6.10 Maintenance Functions
Revision history
Effectivity
Date - Modified By Description of the Updates App. Cfg.
29-NOV-99 Peter Bateman Initial release and entry into PVCS -001 -001
06-APR-00 M. Calhoun SCR 4896: Added the following to the Present status example in section
6.10.12 and to the level 3 self test description in section 6.10.6.3:
'IO Discrete Type'
'Engine Torque Type'
'Windshear Input Type'
Also revised item order to match actual sequence in 6.10.12.
-003 -003
24-MAY-00 Susie Wright SCR 4795: Add Envelope Modulation to EM6/8 General document
cleanup.
-003 -003
06-JUN-00 – Susie Wright Document only change – Deleted proprietary note from footer. -003 -003
01-DEC-00 – Susie Wright General document cleanup. -006 -006
27-FEB-01 – M. Calhoun SCR 5803: Added Steep Approach lamp to self test. -008 -008
The EGPWS maintenance philosophy is to provide information that will encourage the line mechanic to correct the real
problem (pull the correct LRU) by indicating whether the failure is within the EGPWC or one of the input sources. To that
end, the EGPWS is designed to provide extremely clear (not necessarily detailed) fault messages, and give them with
minimum effort on the part of the maintenance crew. To accomplish this goal, the EGPWC provides four different means of
extracting fault information, provides access from either the cockpit or the EGPWC, and provides several levels of reporting,
from the very basic to the very detailed. The three methods of accessing fault information from the EGPWC are aurally, over
RS-232, and by download to the PCMCIA port via the smart cable. Aural readout can be performed in the cockpit.
Additionally some information is also conveyed over ARINC 429.
6.10.1 Maintenance Philosophy
The EGPWC performs both event-initiated and continuous BIT functions. Event-initiated refers to both power up tests and
manually activated self-test sequences. The system status monitors are provided to indicate whenever any fault is detected
which effect system functionality. These monitors can be activated by any test that fails as a result of both event initiated or
continuous BIT. The cockpit self-test is provided both to test the cockpit interface and to annunciate system configuration and
status information.
6.10.2 Windshear Monitor
The windshear monitor is activated by failures that affect the windshear fucntion. Both analog and digital versions of the
monitor are provided. The configured discrete output is biased on with loss of system power.
6.10.2.1 Current Configuration
Current configuration of the EGPWC indicates the current hardware, software, databases, configuration module and input
discrete detected by the system. Each configuration item has a configuration message associated with it. This message is the
message that will be read out during present status on the RS-232 interface or voice output during self-test level 3 to inform
the user of the current configuration.
Refer to the Installation Design Guide for specific configuration messages associated with each configuration item.