Textron Cessna 182S - Page 116

CESSNA
AIRCRAFT
COMPANY
MODEL 182/T182
WIRING DIAGRAM MANUAL
(f)
After installing
the braided
solder
sleeve,
the braided
solder
sleeve
must
not be
cut or split.
Shield
strands must not extend
through the braided solder
sleeve.
E. Splicing
Coax Cables. Splicing of coax is not recommended;
however, in some cases, splicing of coax
may be necessary.
(1) Coaxial
cables used in a system
where a specific
length of cable is required
for proper operation
shall not
be spliced.
Examples of systems
that require
specific coax lengths
are Radio Altimeter
and ELT.
(2)
Triax cable shall
not be spliced.
(3) Splicing
of coax
is limited
to
Nav, Comm
and
DME
systems.
(a)
Cut the
coax at
the location
of the damage.
(b) Install
TNC style (threaded)
coax plug and
jack on the ends of
the coax or install
TNC
style (threaded)
coax plugs on
both ends of the
coax and connect
to a bulkhead feed-thru
connector.
(c) Cover
the connectors
with heat shrink tubing
per MIL-I-23053.
Refer toHeat Shrink
Tubing
- Maintenance Practices.
F. Terminal Installation.
(1)
Refer toSplices and
Terminals for terminals.
G. Heat Shrink Tubing Installation.
(1)
Refer to Heat Shrinkable
Tubing
- Maintenance Practices
for heat shrink
tubing.
H. Wire
Stripping.
(1) All wires
shall be stripped
with wire stripping tools.
Hand knives shall
not be used except
when
required for cables
and aluminum
wires.
(2) Sufficient
insulation shall be
stripped from the
wire so no insulation
will touch the connection.
(3) Care
shall be taken to
avoid nicking or otherwise
damaging the wire
or remaining insulation.
For
the minimum
requirements
that will be acceptable
for nicking or cut
wire strands, refer
to Table
204.
Table 204.
Maximum Nicked or Broken
Strands For Stripped Wire
NUMBER
OF STRANDS
MAXIMUM ALLOWABLE
NICKED
OR
BROKEN
STRANDS
LESS THAN 7 0
7-15
1
16-18 2
19-25
3
26-36
4
37-40 5
41 OR MORE 6
I. Soldering.
(1) Refer
toSoldering
- Maintenance
Practices
for soldering.
J. Backshell
(1) All non self
locking backshell coupling
nuts shall have
a bead of RTV157
applied to the nut and
backshell
body
after
tightening.
20-10-01 Page 211
© Cessna Aircraft Company Mar 1/2004