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detected, use the Down and Up
arrow keys to scroll through the display
pages.
2. One or more of the following continuous test
messages may be displayed:
l DNS RAM ERASED
l PROG PLUG NOT CONNECTED
or PROPERLY PROGRAMMED
l RTA NOT CONNECTED
l DNS IN REMEMBERED VEL
l GS/TKA ENTRY ENABLED
l CDU/DNS INTERFACE NO-GO
Change 3 3-61
TM 1-1520-238-10
3. The on command test GO/NO-GO self test
can be initiated any time the FDLS page is
displayed. It is not necessary to wait for an
FDLS error message to be displayed before
pressing the FDLS FAB to display the FDLS
page. The GO/NO-GO self test is comprised of
the following internal tests:
a. PROM Check sum verification.
b. RAM read/write test.
c. Limited non-volatile memory retention
check.
d. Display hardware BIT.
e. 1553B terminal BIT.
4. Initiate the On Command test as follows:
a. TEST - Press. Observe that DNS SYSTEM
TEST IN PROG is displayed until
the test is complete and data is available
for DNS test status. The GO or NO-GO
status is then displayed. The following is a
list of possible NO-GO messages:
(1) PITCH/ROLL FAIL
(2) HDG or A.C. REF FAIL
(3) SDCC PWR SUPPLY FAIL
(4) SDCC CPU/MEMORY FAIL
(5) SDCC WRAPAROUND FAIL
(6) SDCC A/D FAIL
(7) SDCC 1553 I/O FAIL
(8) SDC FAIL
(9) RTA FAIL
(10) SDCC CMD FAIL
If no failures are detected, the CDU displays
the FDLS page as shown in figure 3-24.
3-62 Change 4
Figure 3-24. FDLS Status Page - On-Command
Test Results
NOTE
The heading, pitch and roll values are calculated
and displayed no more than five
seconds after the GO message.
b. NAV FAB - Press. Observe that the NAV
top level present position page is displayed.
3.15.6 Stopping Procedures.
1. ADMIN - Press. Observe that the ADMIN
page is displayed.
2. PWR ON - Press. Observe that PWR ON
changes to PWR OFF.
3.16 INTEGRATED NAVIGATION SYSTEM m
NOTE
l The integrated navigation system
(EGI) does not meet US ARMY requirements
to fly FM approved
GPS approaches.
l All data contained paragraph 3.16
through paragraph 3.16.16 is applicable
to m FCC software only.
The Integrated Navigation System is a software module
in the FCC that uses data from all of the navigation
sensors. The data for the Navigation System comes
from the Embedded GPS Inertial (EGI) sensor, a fivechannel
GPS receiver, the AN/ASN-137 Doppler Navigation
System, the Heading Attitude Reference System
and the Fire Control Computer. The Navigation System
software resides in the FCC only. In the event of an
FCC failure, the helicopter will automatically configure
to the Non-Integrated Navigation System as described
in paragraph 3.14, with the BBC as the bus controller.
TM 1-1520-238-10
Change 6 3-63
NOTE
· Waypoints stored via the Data Transfer
Unit (DTU) will not be accessible if the
BBC is the bus controller. The CPG can
store up to 20 waypoint coordinates in
the CDU with the MUX switch in SEC
(Emergency return routes to be used as
a backup in the event of a FCC failure).
· If HARS is free inertial for 20 or more
seconds, theHARSVEL? prompt is displayed
on the CDU. If HARS is free inertial
for 20 or more seconds and
groundspeed is less than 10 knots, the
electronic trim ball will flash. Care
should be taken when engaging HAS as
uncommanded aircraft drift may occur.
Aircraft position should be carefully
monitored using visual cues and
symbology.
· If the GPS system is not keyed or is
tracking less than 4 satellites, HAS
performance may degrade over time.
Hover Position Box and Velocity Vector
accuracy will be degraded.
In normal operation, the Navigation System redundantly
integrates data from the sensors. The EGI is the
primary sensor for inertial data with the HARS as the
backup. The GPS is the primary sensor for helicopter
position. The Doppler provides helicopter velocity data.
The GPS, if keyed and verified, will also provide velocity
data. The fire control system and flight symbology
use the redundant data. There are three instruments
and two subsystems that receive dedicated inputs from
the sensor array. The HSI, RMI, and RAI receive data
directly from the HARS for heading and attitude. The
DNS provides data directly to the distance--to--go and
No.1 needle displays on the HSI. The DASE and DNS
receive data directly from the HARS. For those instruments,
including the DASE and DNS, that receive data
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