ROCKWELL
COMMANDER
112/B/TC
/TCA
MAINTENANCE MANUAL
SECTION n
SERVICING
AND
INSPECTION
UPHOLSTERY
The cabin
interior
and baggage
compartment
area
are
completely
upholstered
and paneled with Royal.-
ite,
vinyl and
carpet.
Fiberglass
is
utilized
to
insul-
ate
and sound proof the cabin
structure.
Royalite and vinyl paneling
is
held in place by
retainer
screws,
adhesive and moulding
trim.
Floor
carpets
are
retained
by cement,
metal
retainers
and
screws.
To
clean
the upholstery
see
information
under
Interior
Cleaning
paragraph.
WINGS
WING
REMOVAL. A wing
can
be removed
easily
if
three
men
are
available to handle the wing.
Other-
wise the wing should be supported with a sling,
cradle
or
maintenance
stand
when the fastenings
are
loosened.
When one wing
is
being removed, provide balance
sup-
port
for
the remaining wing. To remove a wing
as-
sembly,
refer
to
Figure
2-12 and
proceed
with the
following
steps:
a.
Defuel
aircraft
per
Defueling
procedures
in
this
section.
b.
Drain
hydraulic
brake
and
gear
retraction
lines.
c.
Remove
rubber
wing-butt
fairing
seal,
and fully
extend wing flaps to gain
access
to
aft wing
attach
mount and wing flap torque tube fitting.
d. Carefully
remove
front and
rear
seat
assemblies,
side
paneling and
carpet
as
necessary
to gain
access
to
spar
and cabin
side
wall
access
covers.
e.
Disconnect wing flap
from
external
flap
actuator
rods.
f. Disconnect and
cap
fuel line through
forward
cabin side wall
access
opening.
g. Carefully disconnect
forward
end of flap
actuator
and
actuator
bracket
from
aft
side
of wing
spar
(left
wing
spar
only).
h.
Disconnect
left
wing
wiring
harness
connector
plug.
1101.
Securely tape wing-half of wiring
harness
to
the
spar
web
to
prevent
damage during
wing removal.
i
•
Di
sconnect and
cap
plastic
pitot
line
coupling
at
spar
(left wing only).
j • Remove
main
cabin
wiring
harness
from
ad-
hesive-backed
fasteners.
k.
Disconnect and
cap
three
landing
gear
power
pack hydraulic
lines
at
spar
web (left wing only).
1. Disconnect and
cap
hydraulic
brake
line
at
spar.
m.
Disconnect fuel
tank
cross-vent
line
forward
of
spar.
n.
Disconnect
aileron
control
and balance
cables
at
turnbuckles
and
tag
for
reinstallation.
o.
Relieve
cable
tension on
rudder,
elevator
and
elevator
trim
control
cables
at
turnbuckles,
and
re-
move
controls
cable
pulley mount from
spar
web.
p. Remove
aileron
balance
cable
support
bracket
and pulley
from
spar
web
attach
point.
q. Remove
bolts
securing
truss
assembly
to main
spar
and aft cabin mounts and remove
assembly.
Use
extreme
care
to
prevent
notching of forging that
truss
assembly
attaches
to
at main
spar.
r.
Unbolt and
remove
forging
from
spar.
s.
Remove
upper
and lower
spar
cap bolts
from
left
or
right
wing
spar.
t.
Remove bolts
from
forward,
center
and aft
wing mounts.
u. Disconnect ventilation hose and
cables
at
wing
root.
v.
Carefully guide wing
spar
out of cabin
structure
and place wing
assembly
on suitable support
structure.
WING
INSTALLATION. Thoroughly vacuum
all
fore-
ign
material
from
the fuselage,
spar
carry-through
structure
and any
other
internal
area
where mainte-
nance
has
been
performed
while wing
assemblies
were
removed.
Refer
to
Figure
2-12 and
proceed
with the following
steps:
a.
Support fuselage and wing
assembly
on suitable
supports.
b.
Position
wing
spar
in
fuselage, and
if
new
in-
board
skin panels have been
installed,
carefully
check
fit along fuselage and
trim
as
necessary.
c.
Connect cabin ventilation hose
at
wing root.
d.
Install
and bolt
center
wing
attach
shear
fitting
through cabin
side
wall
access
cover.
e.
Secure
forward
wing
attach
point.
f.
Position
and bolt
centerline
forging
at
spar
centerline.
g.
Install
truss
assembly.
h.
Install
and
torque
bolts
through
spar
cap and
aileron
balance
cable
bracket.
i.
Secure
aft wing
attach
mount.
j.
Install
controls
cable
pulley
assembly
at the
spar
web.
k. Connect and tension
all
control
cables
per
in-
structions
found
in
Section VII, Flight Controls.
1. Connect fuel
tank
cross-vent
line
at
spar.
m.
Connect hydraulic
brake
line
and
bleed
brakes
per
Section VI, Landing
Gear.
n.
Connect hydraulic power pack
lines
at
spar.
o. Connect wing wiring
harness
and
secure
harness
to wing
spar.
p. Connect pitot line.
q. Assemble wing flap
actuator
and
spar
mounting
bracket.
r.
Rig
aircraft
in
accordance
with Section
VU.
s.
Refuel wing tank and
inspect
all
connections
for
leaks.
t.
Fill
hydraulic
brake
and landing
gear
systems.
u . Check
operation
of fuel tank quantity gage,
wing flap position gage and wing navigation
light.
v.
Inspect wing
spar
area
for
security
of
all
parts
installed,
safety
wired
components
properly
safetied
and
wiring
harnesses
properly
attached
to wing
spar
surface.
Install
all
interior
components removed
during maintenance and check operation of
brakes,
control
surfaces
and landing
gear.
2-23
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**
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