Wet Wing Tip Removal; Wet Wing Tip Installation; Wet Wing Tip Leak Test; Fuel Cellleakage Check - Raytheon BEECH BARON 58P Maintenance Manual

BEECHCRAFT
BARON 58P AND BARON SBTC
MAINTENANCE MANUAL
rubber fuel fitting nipples
to
25 f 5 inch-pounds,
d. Move wing tip into position and
secure
support
c.
Install the internal fuel cell interconnect damps,
angles
to
the front and
rear spars
with
screws.
Torque clamps
to
25
f
5 inch-pounds.
e.
Using
MS20426AD3
rivets,
rivet the
connecting
d.
Install the
access
plates (2) and plumbing
access
strap
to
both the wing and wing tip.
plate (1)
on
the under side of the wing. Torque the
access
f. Install the deicer boots
(if equipped). (Refer
to
plate
screws
to
45
to
55 inch- pounds.
Chapter 30.)
e.
Install filler neck and install filler
access
plate (3).
g.
Install and
secure access
plates.
h.
Pressurize the
fuel
system
using 0.50 0.25 -0.00
psig.
There should be
no
pressure loss in 15 minutes.
NOTE
i.
Fuel
and
restore
electrical
power
to
the
airplane
as
required.
Use sealer
(3, Chart
205, 91-00-001
between the
skin and the
adapter flange when
installing the
filler neck.
WET WING TIP LEAK TEST
CAUTION
WET WING TIP REMO VA L
Do
not
perform
this
test
with the
wing tip
a.
Disconnect external power from the
airplane. Place
installed
on
the airplane.
battery
switches in the
off position.
b. Defuel the
airplane,
to
the point
where fuel
can
not
be
seen
from the inboard filler
position,
a.
Ensure that all repairs
to
the
wet
wing tip
are
c.
Remove
access
plates
from the outboard lower
completed and sealed.
wing,
b. Plugall possibleoutlets.
d. Remove deice
boot from wing tip
leading edge (if
c.
Connect
a
clean compressed
and/or
filtered air
installed). (Refer
to
Chapter 30.)
pressure source to
the wing tip.
e.
Working through the
access
opening in the under
d. Apply
3.73
0,25 psig
to
the wing tip.
This
side of the wing,
loosen the
clamps
on
the 3-inch fuel
pressure
shall
be maintained for 5 minutes.
interconnect and
vent
lines.
e.
If
3.73 0.25
psig is
not
maintained for 5
minutes,
f. Disconnect the
electrical connections,
maintain 3.73 0.25 and apply leak detector compound
g.
Support the
wing tip. Using
a
1/8-inch
drill bit,
MIL-L-25567 114, Chart 207,
91-00-00)
to
the outside of
drill
out
rivets
along
the connecting
strap
and
remove
the
the
wet
wing tip.
strap.
f.
Mark all leaks
as
indicated
by
bubbles.
h. Remove the
support
angle
screws
at
the juncture of
g.
Depressurize the
wet
wing tip, locate and
repair
the wing tip
and wing
front and
rear spars.
Remove the
leaks.
(See Figure 204.)
wing tip.
h.
Repeat the pressurization
test
procedure and
repair
leaks until there is
no
leakage.
WET WING TIP INSTALLA TION
i.
Rinse
leak detector
compound off
wet
wing tip
with clean
water
and wipe dry with clean cloths.
a.
Disconnect external power from
the airplane. Place
j. Install
wet
wing tip
on
airplane
per
WET WING
battery
switches in the off position.
TIP INSTALLATION.
CA U~ON
FUEL CELL LEAKAGE CHECK
Support the
wing tip
on a
platform which will Although the chemical
test
is
more
sensitive, either of
the
give
firm support but will allow
some
flexibility following
test
procedures may be used
to
detect leaks in the
of
movement
of
the wing tip
to
facilitate bladder cells.
proper
alignment.
Protect the wing tip surface
from
scratches, dent and other damage during
a.
Soapsuds
Test.
installation. 1.
AttachtestplatestoalI
fittings.
2. Inflate the cell with air
to
a pressure
of
1/4
psi
b.
Support the wing tip
in the
proper
position
to
maximum.
attach
to
the wing. Connect
the hoses from
the
wing
to
the 3.
Apply
a
soap and
water
solution
to
all
repaired
3inch fuel interconnect and
vent
lines. Secure with
clamps,
areas
and
any areas
suspected
of leakage. Bubbles will
c.
Connectelectrical connections.
appear
at
any
point
where leakage
occurs.
2810-00
Page
204
Jan
9/76