Rockwell Commander 112 - Aileron Trim Tab; Wing Flaps

SECTION VII
FLIGHT CONTROLS
MAINTENANCE MANUAL
ROCKWELL
COMMANDER
112/B/TC/TCA
CONTROL CHAIN
CONTROL YOKE
AILERON CABLE PULLEY
X271
Figure 7-3. Aileron Control Chain Location
i. Rotate control wheels counterclockwise to de-
flect left aileron up and right aileron down. Adjust
left aileron stop to . obtain a 25 (2- 2) degrees up posi-
tion for Model 112 with Serial numbers through 222
and
20 to 27 degrees up for aircraft with Serial num-
bers 223 and subsequent. Right aileron should be at
9 (2- 2) degrees down position. Tighten aileron- stop
checknut.
j. Check difference between left and right ailerons
in the up position. There shall not be more than four
degrees difference.
k. Adjust aileron down stops to contact bellcrank
while up stop on opposite side of aircraft is in con-
tact with bellcrank. Tighten aileron-stop check nut
on Model 112
(Serial numbers 471 and subsequent)
and Models 112B/TC/TCA.
1. Be sure all turnbuckle safety clips are installed,
all cables and cable guards are properly installed
and all jam nuts are tightened, then replace all parts
removed for access.
m . Check aileron system for friction. If friction
is apparent, check for following:
1. Frozen, defective or dry bearings.
2. Control surfaces improperly aligned
with matching surfaces.
3. Pulleys frozen or cables rubbing.
n. Check
aileron trailing edge free play at in-
board end of aileron with aileron in zero degree
rigging position. Check free play does not exceed
0.l2-inch.
NOTE
Do not apply more than one pound
pressure to trailing edge when
measuring free play.
o. Test fly aircraft and correct one wing low
condition
by adjusting ground adjustable trim tab.
See information under Aileron Trim Tab.
AILERON TRIM TAB
A fixed-position trim tab is attached to the left aileron.
A left wing high attitude may be corrected by bending
the
trim tab down. Bending the tab up will correct a
left wing low attitude.
Use forming block when bend-
7-8
ing tab, and do not bend more than O. 50-inch tab de-
flection in either direction.
WING FLAPS
An all-metal wing flap installed on each wing is at-
tached to the aft wing spar and extends outboard from
the fuselage to the ailerons. These wing flaps are
electrically operated and controlled by a switch lo-
cated on the lower right side of the instrument panel.
Power from the electric motor is transmitted to the
flaps through a jackscrew connected to a torque tube,
and from the torque tube to the flaps with push-pull
rods.
REMOV AL AND INST ALLATION OF WING FLAPS
a. Disconnect flap push- pull rod at flap. Do not
change position of
rod end on push-pull rod.
b. Remove flap hinge bolts.
c. Remove flap from aircraft.
Installation of the flap is the reverse of the removal
procedure. In the event push- pull rod length has been
altered, the flap will have to be completely re- rigged.
REMOV AL AND INST ALLATION OF FLAP MOTOR
ASSEMBLY
a. Remove rear seat and floorboard assembly to
gain
access to flap motor located aft of main spar.
b. Separate two connector plugs on flap assem-
bly wire harness and disconnect ground wires.
c. Remove hardware attaching flap motor jack-
screw housing to torque tube (see Figure 7-4).
d. Remove hardware attaChing forward end of
flap
motor assembly to spar mount bracket.
e. Remove flap motor assembly. To install,
reverse this procedure.
RIGGING. Remove the rear seat and floorboard as-
sembly, and the inboard access plate located between
the wings and fuselage on the under side of the wings.
110'.
Left and right flaps to be rigged at the
same time. Aircraft to be on jacks with
landing
gear clear of the ground.
a. Place a propeller protractor 12 inches aft of
firewall on bottom surface of aircraft at centerline.
Zero protractor.
b. Position propeller protractor on flap as
shown in Figure 7-11, at 1.50 inches in from out-
board edge normal to flap trailing edge. Adjust
push-pull rods to obtain a reading of 11-1/2 (± l)
degrees.
c. Note three limit switches on flap motor sup-
port rod. Refer to forward SWitch as number one,
center switch as number two and aft switch as num-
ber three (see Figure 7-5).
d. Adjust switch number one so jackscrew
collar has just actuated switch lever. Tighten set-
screw.
Change 2
Copyright Commander Owners Group 2013 All Rights Reserved
**unofficial copy**