BFGoodrich
Avionics
Systems, Inc.
Installation
and Operation
Manual
P/N
501-1075-()
FITS
AND
CLEARANCES
1.
General
This
section
contains instructions that
are
typical
and not
meant to
pertain to
any
particular
aircraft.
It
is
recommended that
for
installations
in a
specific
aircraft,
the aircraft
owner's
manual
should
be
consulted
and the applicable information
used in
conjunction with this
manual.
2.
Emergency Power
Supply
Location
The following steps provide
general requirements
for locating
the
Emergency Power
Supply in an
aircraft.
A.
The
Emergency
Power Supply provides limited DC
power
to the aircraft emergency
bus and
115Vac(100VA, maximum),
single-phase
power
to
aircraft
equipment
in the
event
of primary
power
failure.
Therefore,
the supply
should
be
located in the general
area of aircraft AC and
DC
busses.
B.
Ensure that
space
requirements for the supply match
space available
for
the
installation
being
considered.
1)
The
Emergency
Power Supply should be accessible
for
inspection, maintenance or
removal.
2)
The
installation
area
should be free from excessive
vibration
and heat.
C. Consider the relative distance
to
associated equipment. Keep
connecting cables as
short
as
possible.
D.
The cable
should
not run adjacent to
heaters
or engine
exhausts.
3.
Pre-Installation
Inspection
And
Preparation
A.
Check unit for
physical damage
that
may
have occurred during
shipping and
handling.
B. For
new-unit
installation,
the
PS-823
Battery Pack must be charged. See
Testing
and
Fault
Isolation section.
C. Units installed after
a
maintenance action must be tested
in
accordance with
the
Performance
Test
procedures
listed in
Testing
and Fault Isolation
section prior
to
installation.
msmljtp202FitsClearancediskl59
24-20-03
Page 801
Revision
A
June
30,
1999
To Next Page
Loading...