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2,5,4
Repair -
The wing ts
entir
ely
stressed skin
construc-
tion. Any repair to the skin
or
internal
structure
should be
made by
a
BEECHCRA FT CertUled
Service
Statton,
or
by
a
facility properly
equipped to
accomplish
structural
repair.
2,5.5
Installation -
(a)
Place wing in position for installation and in-
stall
the wing attaching bolts.
WARNING
New
aluminum
washers
must be
installed be-
tween
the upper
center section
and
outer
wing
panel fitting each time the
wing bolts
are
loosened enough to allow
the
serrated faces
of
the upper
wing attaching
fittings to
change
position
in relation to each
other.
(b)
Tighten
the wing
attaching bolts to
the
following torque:
1
Lower
forward
spar bolt, 5,000 to 5,500
inch-pounds.
2
Upper
forward,
upper and lower
r
ear
spar
bolt, 2,000 to 2,300
inch-pounds.
(c)
Connect electrical wiring at
jwtctlon block
in lower side of engine
nacelle.
(d)
Connect
fuel
outlet
and fuel
vent
line,
and
pitot line (left
wing
only)
.
(e)
Connect
aileron
and (left
wing
only
)
aileron
tab
cable
turnbuckles
in
landing
gear
wheel well.
Rig to proper tension.
(f)
Connect
the
flap
flexible drive.
(g)
Check flap
travel and stops. Check opera-
tion of navigation lights,
landing lights,
and
pitot
heat.
Fill
the fuel
tank
and check
for
l
eaks.
Check the
airspeed
system for proper
operation, preferably
against
a master instrument.
When using a master
instrument for checking
the
airspeed the
tempera-
ture
must remain constant
and differential must
not
exceed
five mph
in 15
minutes.
(h)
Install
augmenter tubes and all
access
hole
covers.
NOTE
Retorque the wing
bolts as indicated in
Paragraph
2.5.5
after
first 100 hours
of
flight time
after
wings are
installed,
2,5,6
Adjustments -
Rigging
adjustment of the wing is not
ordinar-
ily necessary;
however,
when flight tests indicate a
wing-heavy
condition,
the wing may be washed
in
or
out
for correction.
Proceed as
follows:
(a)
Mark
the present position of
the wing on the
wing attachment
fittings.
(b)
Loosen
the wing attaching
bolts.
(c)
Remove the bolts one
by
one and replace the
soft
aluminum washers
between the wing
attachment
fittings.
7
(d)
Determine the new positlon
of
the
wiJg
and
tighten the
wing bolts.
(e)
NOTE
If wing is
heavy,
the leading edge
must
be
raised above its original position,
as
indi-
cated by the marks made before
loosening
the
bolts. If wing is light
the leading
edge should
be
lowered,
Test
fly aircraft.
Readjust
if necessary.
NOTE
New
soft
aluminum washers
must be in-
stalled when
the wings are
rotated and a log
book
entry made so the
wings
may be re-
torqued after the first 100 hours of
flight
time after the washers are installed.
The
stall warning indicator
also must
be
checked
and the detector vane reset if necessary.
2,6
WING TIP
The wing tip is formed of soft aluminum
and
is
readily removable for repair.
2.6.1
Removal -
(a)
Remove the machine screws attaching the
wing tip to the wing.
(b)
Unscrew the
electrical
lead to the naviga-
tion light from the navigation light base.
2.6.2
Installation -
(a)
Attach the electrical lead to the navigation
light base and tighten.
(b)
Install machine screws which attach the
wing
tip to the wing.
2,7
CONTROL
SURFACES
NOTE
All control surfaces, both fixed and movable,
are
of stressed-skin construction. There-
fore, all repairs must be made
by
a
BEECHCRAFT Certified Service Station
or
other facility
properly staffed and equipped
for
structural repairs.
2. 7 .1
Horizontal Stabilizer -
The horizontal stabilizer is of all-metal
construction
with two channel section main
spars.
The
metal skin utilizes internal bead stiffeners.
The
stabilizer is
attached to the fuselage by bolted shear
connections
at the front and rear spar.
2.7.1.1
(a)
the tab.
(b)
Removal -
Remove the elevator
tab
actuating
arm
at
Remove the plastic tau cone.
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