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initiated. Most weapon, sensor, and fire control
subsystems have a continuous check on their status
and report their status to FD/LS without an on-command
initiated test. If the FD/LS detects a NO-GO
condition during the continuous monitor of any of the
weapons, TADS or PNVS, the results are displayed on
the pilot and CPG caution/warning panels. If the exact
status information regarding the NO-GO condition for
W and m software is desired, the DEK switch
must be set to FD/LS. For m software the CDU
FDLS FAB must be pressed. The FD/LS will automatically
display the status of all NO-GO subsystem components.
An asterisk will be displayed to the left of the
fault message that initiated the FD/LS annuniciator
4-16 Change 4
m /m. The status list may be paged by pressing
the SPACE key on the DEK for m and m software
or the SPC key on the CDU for m software.
The FD/LS MENU will be displayed when pressing any
other key. The list is completed when the message ANY
KEY FOR FD/LS MENUS appears on the display.
Prior to initiating AWS FD/LS check
(IBIT), ensure the pilot ground override
(PLT/GND ORIDE) switch is in
the OFF position. Failure to perform
this action may result in uncommanded
gun turret slewing or uncommanded
gun firing during a AWS FD/
LS (IBIT) manual abort.
4.15.1 FD/LS On-Command Tests. Most command
initiated tests are fully automatic and do not require
any intervention between initiation and completion.
There are certain tests which do require some interaction
between the initiator and the fire control system.
Interaction may require either switch actuation or evaluating
a specific parameter or function and the decision
regarding its acceptability. The interaction is fully
prompted for all switch actions or evaluations. The oncommand
initiated tests are displayed as a menu of the
specific tests. There are two pages of the test menu.
They are:
01-ADS
02-DASE
03-DICE
04-GUN
05HARS
06-IHDS
07-MSL
08-MUX
09-PNVS
10-PYLN
ll-RKT
12-STAB
13-SYMG 17-APU 33-CDU
14-TADS 18-GEN 34-DNS
15-UTIL 19-TRAN 35-DTU
16-ETE 32-TAGA 36-EGI
These tests are initiated by entering the corresponding
two-digit number for the test; tests 32 - 36 are fo
only. Any required intervention is fully prompted and
the results of the test are displayed on the TADS ORT,
VDU and helmet mounted displays. The results may be
paged by pressing the SPC key on the CDU m ; or
the SPACE key on the DEK for m and m; this
TM l-1520-238-10
should be done until the message ANY KEY FOR FD/
LS MENUS is displayed. The FD/LS status or on-command
initiated test may be accomplished without turning
the TADS on. The TADS heads out display can be
used independently of the TADS for FD/LS by turning
on the symbol generator to display the FD/LS on-command
tests. The FD/LS tests may request that the operator
acknowledge that an action has been completed.
The method used to acknowledge (ACK) is to press the
SPACE key on the DEK m and m m software.
Form software the CDU SPC key must be pressed.
4.16 AIR DATA SENSOR SUBSYSTEM (ADSS).
The ADSS consists of an omni-directional airspeed sensor
(OAS) and air data processor (ADP). The OAS (fig
2-2) measures the airspeed and temperature. The air
data processor senses static pressure and with the data
from the OAS calculates the air mass data required for
fire control. The ADSS is interfaced with the multiplex
bus through the DASE MRTU (fig 4-8). The ADSS is
turned on with the switch labeled ADSS on the AUX/
ANTI-ICE control panel in the CPG left console (fig
2-12). If the ADSS fails or is turned OFF, the displayed
airspeed will revert to ground speed in knots as computed
by the doppler navigation system. The ADSS receives
115 vac power from the No. 1 essential bus and
23 vdc from the No. 3 essential dc bus and is protected
by the AIR DATA AC and AIR DATA DC circuit
breakers on the pilot overhead circuit breaker panel.
The status of the ADSS is continuously monitored by
the Fault Detection/Location System (FD/LS); the on
command test (test 01-ADS) will fault isolate to the
specific line replaceable unit (LRU).
Change 4 4-16.1/(4-16.2 blank)

TM 1-1 520-238-10
4.17 WAYPOINT/TARGETING. m/m
If m software is installed go to paragraph
3.16 for Waypoint/Targeting system
description and operation.
Waypoint/targeting functions are performed solely by
the CPG. The pilot cannot actively participate. Four
functions can be implemented. These are: preflight,
　
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