Rockwell Commander 112 - MAINTENANCE OF FLIGHT CONTROLS; FLIGHT CONTROL SYSTEMS

ROCKWELL
COMMANDER
112/B/TC/TCA
MAINTENANCE MANUAL
SECTION VII
FLIGHT CONTROLS
MAINTENANCE OF FLIGHT CONTROLS
Special care must be exercised when performing c"n-
trol system maintenance. Emphasis shall be given to
security of attachment, correct alignment of rod ends,
use of correct hardware, and proper safetying. Con-
trol cables must be free of kinks, pulleys must be
aligned with the cables, and guards must be installed
in the pulley brackets. Position cable pulleys and
route
cables to avoid contact with the aircraft struc-
ture. Inspect work areas for mislaid tools or parts,
which could foul the controls, and perform a function-
al check of the controls prior to replacement of ac-
cess covers. It is recommended that a test flight be
accomplished before the aircraft is released for
routine ope ration when a control system component
has been replaced or aircraft rigging has been altered.
Rerigging the control systems will seldom be neces-
sary if correct maintenance technique is employed
when system components are removed and replaced.
Do not disturb position of rod end fittings when control
system components are removed, unless absolutely
necessary. When this is necessary, record the
amount of change required so that fittings may be re-
turned to original position when maintenance or re-
pair is completed. When control system components
are being removed, carefully note location and posi-
tion of attaching parts and hardware and return to
original location or position when installing new com-
ponents and parts. Complete rigging instructions are
provided in succeeding paragraphs, for each flight
control system. Read these instructions carefully
before starting the rigging operation. Select and ac-
complish only those rigging steps applicable to the job
requirement. Cable tensions and control surface
travel measurements are contained in Figure 7 -13.
Ambient temperature and temperature buildup within
the
airframe structure affect cable tension and must
be given proper consideration when rigging control
surfaces (see Figure 7 -15). The following procedures
should be followed when rigging control cables.
a. Rigging should be accomplished in a hangar.
When necessary to rig aircraft in the open it should
be accomplished during coolest part of day with tail
of aircraft pointing toward sun. H aircraft is moved
into a
hangar for rigging, allow 90 minutes for con-
trol cables to adjust to hangar temperature.
b. Control cable tension readings should be taken
near the midpoint of cable and never closer than six
inches to a cable terminal or within 18 inches of a
pulley
or fairlead. All control surfaces must be in the
streamlined position when cable tension is taken.
FLIGHT CONTROL SYSTEMS
CONTROL COLUMN
The control column which is supported by bushings and
bearings is attached to the mounting yoke plate located
at the forward end of the console tunnel. Control
wheels are connected to control shafts that are con-
nected to end sprockets on each end of the horizontal
control yoke (see Figure 7-1). Chains are wrapped
around the end sprockets, under the center idler sproc-
ket and around the double sprocket on the control yoke.
Direct cables connect to chain-ends through a series
of pulleys to the aileron bellcranks. The elevator
control cables connect to elevator arms on the control
column and route through a series of pulleys to the
elevator bellcrank. Aileron control wheels may be
removed from the control shafts by removing attach-
ing bolts and nuts.
INST ALL AT ION OF CONT ROL COLUMN PIVOT
BUSHINGS
AND BEARINGS. Remove the rear seat
and floorboard assembly, front seats, Royalite and
metal console covers from the airplane. Use the
following
procedure to replace the two bearings and
bushings (see Figure 7 -1).
a. Relieve tension from aileron cables at turn-
buckles aft of main spar.
b. Relieve tension from elevator cables at turn-
buckles in tailcone.
c. Remove screw, nut and three washers from
each side of control column pivot. (Note the position
of the three washers so they can be reinstalled in the
same position).
d. Bottom of
control column can now be posi-
tioned forward or aft to allow pivot bushings and
bearings to be removed and replaced from inside of
console.
e. After bushings and bearings have been re-
placed, align pivot points of control column with
screw holes in console and replace screws, washers
and nuts.
f. Tighten aileron and elevator turnbuckles,
check tension and rerig as necessary. (Refer to
paragraphs on aileron and elevator control rigging).
g. Reassemble console covers and install seats.
h. Be sure all turnbuckle safety clips are pro-
per ly installed.
INST ALLATION OF O-RING IN CONTROL TUBE
COLLAR.
a. Remove hardware that attaches control tube
to universal joint and remove tube (see Figure 7-1).
b. Remove snap ring securing collar in mount-
ing. Slide collar and O-ring out.
c. Lubricate and install new O-ring on collar.
Use clean MIL-H-5606 hydraulic fluid.
d.
Inspect inside surface of mounting for burrs
or nicks.
e. Lubricate inside surface of mounting, care-
fully insert collar with O-ring installed and secure
with snap ring.
£. Insert control tube through collar and connect
to universal joint.
AILERONS
An all- metal aileron is installed outboard of each wing
flap.
Each aileron operates on hinges, attached to the
aft wing spar. The aileron control wheels are me-
chanically interconnected through a series of control
chains, sprockets and cables. Control cables extend
aft from the control column passing under the floor
7-3
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**