Raytheon Beech Baron E55 - Page 433

only
as
long
as
they
remain
clean.
Indicator
solution
that
is
c.
Connect
electrical connections.
not
in
immediate
use
should
be
stored
in
a
closed
container d. Move
wing
tip
into
position
and
secure
support
to
prevent
evaporation
and
deterioration,
angles
to
the
front
and
rear
spars
with
screws.
e.
Using
MSZ0426AD3
rivets,
rivet
the
connecting
After the
test,
remove
all
plates
and
test
equipment.
Allow
strap
to
both
the
wing
and
wing
tip.
the
cell
to
air
out,
f.
Install
the deicer
boots
(if
required)
as
described
in
Section
II
under
the
heading
SURFACE DEICER
BOOT
INSTALLATION.
NOTE
g.
Install
and
secure
access
plates.
h.
Pressurize
the
fuel
system
using
0.75 0.t5
In
conducting
the
tests
outlined
above,
the
cell
0.00
psig.
There
should
be
no
pressure
loss
in IS minutes.
need
not
be
confined
by
a
cage
or
jig,
providing
i.
Fuel
and
restore
electrical
power
to
the
airplane
as
the
114
psi
pressure
is
not
exceeded.
required.
b.
Pressure
test
fuel
cells
installed
on
the
airplane
as
LEAK
TEST(TH-669
and
afte~
follows:
(Figu~e
8-19)
I.
Pressure
test
fuel cells and
vent
system
to
0.75
0.25
0.00 for
IS
minutes
with
no
drop
in
pressure.
a.
Ensure
that
all
repairs
to
the
wet
wing tip
are
completed
and
sealed.
b.
Connect
pressure
source
to
the
wet
wing
tip
as
shown
in
Figure
8-19.
WET
WING
TIP
~EMOI/AL
(TH-669
and
alter)
a.
Disconnect
external
power
from
the
airplane.
CAUTION
Place
battery
and
generator
switches
in
the
OFF
position.
b.
Defuel
the
airplane,
to
the
point
where
fuel
cannot
Ensure
that the
filler
cap
and
access
plates
are
be
seen
from
the
inboard
filler
position,
secure.
This
test must
be done
when
the
wet
c.
Remove
access
plates
from
the
outboard
lower
wing tip
is
removed
from
the
fuel
system
of the
wing,
airplane
d.
Remove
deice
boot
from
wing
tip leading edge
(if
installed) as
described
in Section
11
under
the
heading
SUR-
FACE
DEICER
BOOT
REMOVAL.
c.
Apply
3.73
0.25
psi
to
the
wet
wing tip
for
5
e.
Working
through
the
access
opening
in
the
under
minutes,
side
of the
wing,
loosen the
clamps
on
the 3
inch fuel inter-
d.
Apply
leak
testing
compound
MIL-L-t5567.
Item
connect
and
vent
lines.
14,
Consumable
Materials
Chart,
to
the outside
of
the
wet
f.
Disconnect
the
electrical
connections,
wing tip.
g.
Support
wing tip.
Using
a
118
inch
drill
bit,
drill
out
e.
Mark
all
leaks
as
indicated
by
bubbles.
rivets
along
the
connecting
strap
and’
remove
the
strap,
f.
Depressuri+e
the
wet
wing tip,
locate
and
repair
h. Remove
the
support
angle
screws
at
the
juncture
leaks
as
shown
in
Figure
8-18.
of
the
wing tip
and
wing
front and
rear
spar.
Remove
the
g.
Repeat
the
pressurization
test
procedure
and
re-
wing
tip,
pair
leaks until there
is
no
leakage.
h.
Rinse leak
testing
compound
off the
wet
wing
tip
with clean
water
and
wipe
dry
with
clean
cloth.
WET WING
TIP INSTALLA
TION
(TH-669
and
afler)
i.
Install
the
wet
wing
lip
on
the
airplane
as
de-
scribed
in
this section
under the
heading
WET
WING
TIP
a.
Disconnect
external
power
from
the
airplane.
INSTALLATION.
Place
battery
and
generator
switches
in
the
OFF
position.
LEAKAGE
CHECKS
AND
REPA~S
(WET
WING
nP)
CAUTION
(TH-669
and
after)
(Figure
8-20)
Support
the
wing
tip
on
a
platform
which will
give
firm
support
but
will allow
some
flexibility
To
classify
the
degree
of
leakage
in
a
wet
wing
tip
fuel
cell.
of
movement
of the
wing
tip
to
facilitate
proper
measure
the
size of
the
wet
area
around
the
leak. A
more
alignment.
Protect
the
wing
tip
surface
from
accurate
measurement
may
be
obtained
by wiping
the
leak-
scratches,
dents
and
other
damage
during
instal-
age
clean and
apply
talcum
powder
in
the
area
of
the
leak.
lation.
After
30
minutes,
recheck
the
area
to
determine
if the leak
classifies
as
a
stain,
seep,
heavy
seep
or
running
Italr
as
indicated
in
Figure
8-20.
Fuel
leaks
must
also
be
classified
as
b.
Support
the
wing
tip
in the
proper
position
to
to
whether
they
occur
in
an
open
area
or
in
an
enclosed
area
attach
to
the
wing.
Connect
the hoses
from
the
wing
to
the
3
to
differentiate
between
those that
require
immediate
repair
inch fuel interconnect
and
vent
lines. Secure
with
clamps.
and
those
not
considered
potential
flight
hazards.
&22