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function as RTs. The RHE provides multiplex bus interface
for the missile system electronics. The DASE provides
multiplex bus interface for itself, ADSS, transmission
and APU FD/LS, BUCS LVDTs, and the
heading attitude reference system. The symbol generator
receives only data from the bus to use in generation
TM 1-1520-238-10
of symbols on the video displays. With the EGI modification,
additional RTs are connected to the MUX bus.
The DTU and EGI are new LRUs on the aircraft, and
they are connected directly to the MUX bus. The CDU
and DNS SDCC are already installed on the aircraft,
but are now connected to the MUX bus via data bus
switches (DBS) that are normally de-energized. The
DBSs energize when the BBC takes control of the MUX
bus, either manually via the MUX PRI/SEC switch on
the CPG FCP or automatically when the FCC indicates
a failure to the BBC. The data bus consists of two identical
bus networks separated down each side of the helicopter
and interconnected in such a manner that loss of
data communications is minimized or avoided in the
event of battle damage. The multiplex bus system receives
115 vac power from the No. 1 essential bus and
28 vdc power from the No. 3 essential dc bus. The
MRTUs are protected by their own circuit breakers: the
DASE by the ASE/AC and ASE/DC circuit breakers located
on the pilot overhead circuit breaker panel; the
symbol generator by the SYM GEN circuit breaker located
on the pilot overhead circuit breaker panel; the
remote Hellfire electronics unit by the MSL/ DC ELEC
circuit breaker located on the CPG circuit breaker panel.
The remaining MRTU circuit breakers are located
on the CPG circuit breaker panel and are labeled MUX/
L PYL OUTBD, MUX/L PYL INBD, MUX/ R PYL
OUTBD, MUX/R PYL INBD, MUX/FAB L and MUX/
FAB R. With the EGI modification, the DTU and EGI
have dedicated circuit breakers on the pilots forward
circuit breaker panel. The CDU circuit breaker is located
on the CPG circuit breaker panel, and the DNS
circuit breaker is located on the pilots forward circuit
breaker panel. The status of the multiplex bus subsystern
is continuously monitored by FD/LS; the on command
test (test OS-MUX) will fault isolate to the specific
LRU m or LRU and LRU bus failure m I=.
With -45 software the RHE and symbol generator
MRTU functions are tested as part of each subsystem
overall on command test (tests 07-MSL; 13-SYMG)
m. With -49A or -51 software the RHE MRTU functions
are tested as part of the 08 MUX test m /m.
Change 4 4-14.1/(4-14.2 blank)

TM l-1520-238-10
Figure 4-8. Multiplex Bus (1553)
Change 4 4-15
TM 1-1520-238-10
4.14 SYMBOL GENERATOR.
The symbol generator receives data from the bus controller
and creates the symbols on the video image. The
symbol generator also serves as the video switching
unit for the helicopter. The symbol generator receives
incoming video from the TADS, PNVS and video recorder
and routes them to crew stations as requested by the
crew members. The symbol generator will display video
and symbology or symbology only on any of the displays;
IHADSS, TADS ORT, or VDU. In the event of a
symbol generator failure the IHADSS DEU will display
the PNVS FLIR 2 video images without symbology on
both the pilot and CPG HDUs. The TADS FLIR 2 video
image will be displayed on the TADS ORT. The only
symbology on the TADS FLIR 2 will be the TADS reticle
and the IAT tracking gates when the IAT is engaged.
The pilot VDU will not have an image for
display. The symbol generator receives 115 vac power
from the No. 1 Essential Bus and is protected by the
SYM GEN circuit breaker on the pilot overhead circuit
breaker panel. The symbol generator is continuously
monitored by FD/LS; the on command test (test
13-SYMG) will fault isolate to the LRU.
4.15 FAULT DETECTION/LOCATION SYSTEM
(FD/LS).
The FD/LS is contained within the fire control computer
(FCC) program. The continuous monitor functions
whenever power is applied to the FCC. If the BBC is the
primary bus controller, no FD/LS capability exists. The
function of the FD/LS is to detect faults in the subsystems
monitored and announce the NO-GO conditions to
the flight crew or FCC repairman. The FD/LS identifies
the NO-GO subsystem component and its location
within the helicopter. Form FCC software, the CDU
is used to access the FD/LS and/or BST functions. For
m and m FCC software, the DEK is used to access
the FD/LS and/or BST functions. There are two modes
of the FCC operation: continuous monitor; and on-command
　
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