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strain re lief (P/N 151-5061) then through
the PA body and sub sequently crimped
and in stalled into the ELT mat ing con nec -
tor (P/N 150-5060). Af ter all pins are in -
stalled, the spin cou pling on the PA body
is screwed onto the rear of the ELT mat -
ing con nec tor and the strain re lief is se -
cured. Re fer to Fig ure D-1 for view of the
Programming Adapter with the mat ing
connector and strain re lief. Ori ent the PA
body so that the wire har ness feeds
throught the “bot tom” to pre vent mois ture
buildup in side the PA. Also use a drip
loop for the wire har ness.
Figure D-2 de picts the typ ical in stal la tion
configuration of the ELT and re lated in ter -
con nec tions. Fig ure D-3 shows the wir ing
interconnection for the ELT us ing the
C406-N Pro gramming Adapter.
D.5. Po si tion Data Source
In stal la tion and Check out
Pro cess
All in stallation pro cesses and in ter con nec -
tions to nav igation sys tems should ad here
to the guide lines set forth in the FAA Ad -
vi sory Cir culars AC43.13-1A, 43.13-2A,
20-130A and 20-138, or later re vi sions of
these doc uments. It is very im por tant that
the Global Po sitioning Sys tem/Flight Man -
age ment Com puter (GPS/FMC) man u fac -
turer’s in stallation in struc tions be con sulted
re gard ing in stal la tion de tails that may be
spe cific to the GPS/FMC. Re fer to the in -
stal la tion in struc tions spe cific to the
GPS/FMC that you are con necting the
ARTEX C406-N. For the ARINC 429 be
sure to use a twisted/shielded pair wire
with the shields tied to air craft ground.
For all “live” RF test ing of the 406 MHz
out put, only the “test mes sage” that is
trans mit ted at turn off is re quired to ver ify
the ELT and C406-N func tion.
It is ex tremely im portant that the C406-N
in stal la tion not be in con flict with the
GPS/FMC man ufacturer’s in stallation in -
struc tions in or der to avoid an in stallation
that may de grade the GPS/FMC per for -
mance. As a re sult, the Post In stal la tion
check out in the GPS/ FMC In stal la tion
Manual must be fol lowed af ter in stalling
the C406-N.
D.6. Air craft Ad dress In -
stal la tion Test (man da tory
for in stal la tions us ing the
Pro gramming Adapter)
The fol lowing test se quence is re quired
for new in stallations us ing the air craft ad -
dress auto-reprogramming fea ture of the
C406-N Pro gramming Adapter to ver ify the
pro gram ming of the ELT and to prop erly
la bel the ELT. A Sartech 406 MHz bea -
con test set (Artex part num ber 453-0131,
avail able as part of Kit 455-9010-01 which
con tains the coax ca ble and at tenu ator re -
quired for test ing) is re quired to com plete
this test. First, lo cate the steps de scribed
in sec tion 4.3.13 “Ver ification of Dig i tal
Mes sage”. This will in struct you how to
extract the 15 digit hex code. Re alize that
the Artex 406 MHz ELT trans mits a 406
MHz mes sage upon re set, which is en -
coded such that it will be ig nored by the
SAR sat ellite sys tem. This 15-digit num ber
ARTEX AIRCRAFT SUPPLIES DOCUMENT #570-5060
07/11/03 PAGE D-3
is used to reg is ter the ELT with the ap -
propriate 406 MHz ELT reg is tra tion au -
thority. In the US, the Na tional Oce anic
and At mo spheric Ad min is tra tion (NOAA)
maintains the da tabase of reg is tered
ELT’s. For Stan dard Lo ca tion Pro to col
pro gram ming, the 15-digit ID used for reg -
istration pur poses con tains the “de fault”
value of no po sition data (this is in dicated
by the last 5 dig its of the 15 digit hex
code be ing “FFBFF”). User Lo cation Pro -
to col pro gram ming will dis play the same
15-digit ID with or with out po sition data
be ing pres ent. NOTE: For the fol low ing
example, the pro gramming pro to col is as -
sumed to be 24-Bit Long Mes sage (Stan -
dard Lo cation Pro to col). Other pro tocols
are pos si ble and the ex act read-outs of
the test set may vary. Re fer to the
Sartech op er a tion man ual in cluded with
the test set or con tact Artex for as sis -
tance.
1. After the C406-N installation is
complete and all wiring has been
checked, apply power (+28 Vdc) to the
C406-N (the ELT will remain OFF). The
aircraft address will be automatically
programmed into the ELT within the next
30 seconds. Monitor the ELT.
NOTE: There is an er ror con dition where
the LED on the ELT and re mote switch
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DESCRIP TION, OPERATION, INSTALLATION AND MAINTENANCE MANUAL(28)
