General Description; General Maintenance Of Flight Controls - THRUSH S2R – G10 Maintenance Manual

AIRCRAFT MAINTENANCE MANUAL
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.
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.
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.
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
Effective: 03/26/2010
THRUSH AIRCRAFT, INC – MODEL S2R-G10
The
A lever
Control cable
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
necessary if correct maintenance techniques
are employed when system components are
removed and replaced.
position of rod end fittings when control
system components are removed, unless
absolutely necessary.
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
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
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
temperature.
The ailerons, elevators, and rudder are all
balanced control surfaces and their static
balance must be checked in accordance
with the limits show in table 7-3 after repaint
or repair.
will seldom be
Do not disturb
When deemed
are provided
following procedures
adjust to hangar
7-3
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