THRUSH AIRCRAFT, INC – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
Effective: 01/01/08
7-3
FLIGHT CONTROLS
GENERAL DESCRIPTION
Ref. Figures 7-1 through 7-9
The aircraft is equipped with flight control
surfaces consisting of ailerons with
servo-tabs, elevators with trim tabs,
rudder with ground adjustable trim tab,
and wing flaps. The ailerons and flaps
are of all-metal construction. The
empennage is of all-metal construction
and consists of horizontal stabilizer,
vertical stabilizer, rudder and elevators.
Control of the ailerons, elevators and
rudder is provided through a control stick
and rudder pedals. A switch located on
the back of the throttle quadrant controls
the electrically actuated flaps. A lever
located on the left side of the cockpit
manually controls the elevator trim tabs.
Fixed, ground adjustable trim tabs are
located on the rudder and both ailerons.
The control stick and rudder-brake
pedals are mechanically interconnected
to the push tubes, push rods, bell cranks,
cables and torque tube which actuate the
primary flight controls. Control cable
pulley brackets are provided with guards
to prevent the cable from jumping the
pulley groove. The electrically actuated
wing flaps provide additional lift for
shorter takeoff distances and slower
landing speeds. Wing flaps may be
positioned at any setting between up and
down by intermittent operation of the flap
switch.
GENERAL MAINTENANCE OF
FLIGHT CONTROLS
Special care must be exercised when
performing control system maintenance.
Emphasis shall be given to security of
attachments, correct alignment of rod
ends, use of correct hardware, and
proper safety-wiring of fasteners. Control
cables must be free of kinks and pulleys
must be aligned with the cables. Position
the cable pulleys and route cables to
avoid contact with the aircraft structure
and accessories. Inspect work areas for
mislaid tools or parts with could foul the
controls, and perform a functional check
of the controls prior to replacement of
access covers. It is recommended that a
test flight be accomplished before the
aircraft is released for routine operation
when a control system component has
been replaced or aircraft rigging has
been altered. Re-rigging the control
systems will seldom be necessary if
correct maintenance techniques are
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 deemed
necessary, record the amount of change
required to return the fittings to the
original position. When control system
components are being removed,
carefully note location and position of
attaching parts and hardware and return
to original location or position when
installing new components and parts.
Rigging instructions are provided in
succeeding paragraphs for the
empennage and each flight control
system. Read these instructions
carefully before starting the rigging
operation. Select and accomplish only
those rigging steps applicable to the job
requirement. The following procedures
should be followed when rigging control
cables.
Rigging should be accomplished in a
hangar. When necessary to rig aircraft in
the open, it should be accomplished
during coolest part of the day with tail of
the aircraft pointing toward sun. If
aircraft is moved into a hangar for
rigging, allow 90 minutes for control
cables to adjust to hangar temperature.
The ailerons, elevators, and rudder are
all balanced control surfaces and their
static balance must be checked in
