Technical data

Product Specification
HIF-2121/R5 CAGE CODE: 97896 SCALE: NONE SIZE: A DWG NO: 965-1176-601 REV: D SHEET 26
1.3.3 Reserved
1.3.4 Maintenance/Test Interfaces
In addition to power-up and continuous BIT, user activated tests (via a discrete test switch), and/or maintenance system
commands are supported.
1.3.4.1 Cockpit Self Test
A cockpit mounted test switch is used to manually initiate tests and BIT annunciation anytime the aircraft is on ground. In
addition, if the aircraft is above 2000 feet AGL the cockpit self test can be initiated if no alert is in progress.
Notice that there is no test switch located on the EGPWC.
Six levels of information are available through voice messages by pressing the self-test switch. The test sequences can be
summarized as follows.
Level 1, Go/No Go Test: This sequence indicates the systems ability to perform all of its configured functions.
For this sequence, when the test switch is activated, the cockpit lamps are activated and voices are issued to indicate what
functions are correctly operating. For instance, if no faults exist on an installation that uses the Terrain Awareness function
in addition to basic GPWS and windshear, then the result of the self-test would typically be:
“Glideslope---- Pull Up--- Windshear Windshear Windshear----Terrain Terrain, Pull Up”
However, if no valid glideslope input was present then the sequence would be
“Glideslope INOP----- Pull Up--- Windshear Windshear Windshear----Terrain Terrain, Pull Up”
For installations that use a terrain display the interface with the display will be tested by viewing a terrain test image on the
appropriate cockpit display. During system self test all INOP type annunciators are activated.
Level 2, Current Faults: This sequence annunciates all faults, if any, that currently exist. It will distinguish between internal
and external faults. If no faults exist then the message, “No Faults” is given.
Level 3, Configuration Information: This sequence indicates the versions of the resident hardware, software and databases
versions. Also provided are the current configuration item selections from the configuration module, including voice and
callout menus selected.
Level 4, Fault History: This sequence annunciates all system faults that were logged for the past ten flight legs. (Information
on the last 64 legs is accessible via the RS-232 interface).
Level 5, Warning History: This sequence annunciates all EGPWS alerts that were logged for the past ten flight legs.
(Information on the last 64 legs is accessible via the RS-232 interface).
Level 6, Discrete Input Test: This sequence annunciates discrete input transitions to aid system installation and maintenance.
Reference section 6.10.6 for detailed description of self-test functionality.
1.3.4.2 Front Panel Test Interface
The MKVI/MKVIII EGPWC provides a front panel test connector which can be connected to a VT 101 (Terminal Emulation
Device) or a portable PC to both receive and control internal data. This test interface can be used for engineering and
production testing, both on the bench and at the aircraft. The connector also provides an interface for data loading purposes to
aPCMCIAcardviaaSmartCable(seesection1.3.5.2.1).
The LRU front panel also contains several fault LEDs. The status LEDs include external fault, computer OK, and computer
fail.
Reference section 6.10.4 for more detail.