Flight Controls; General Description; Maintenance Of Flight Controls - Thrush Aircraft S2RHG-T65 TURBO THRUSH Maintenance Manual

THRUSH AIRCRAFT, INC – MODEL S2RHG-T65 TURBO THRUSH
AIRCRAFT MAINTENANCE MANUAL

FLIGHT CONTROLS

GENERAL DESCRIPTION

The aircraft is equipped with flight control surfaces consisting of ailerons, elevators,
rudder, wing flaps, elevator tabs, rudder trim tabs and aileron trim tabs. The ailerons and
flaps are an all-metal construction. The empennage is of an all-metal construction
consisting of horizontal stabilizer, vertical stabilizer, rudder and elevators. Control of the
ailerons, elevators and rudder are 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 all-metal, 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.

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 safetying of materials. Control cables must be free of kinks and
pulleys must be aligned with the cables. Position cable pulleys and route cables to avoid
contact with the aircraft structure. 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 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 deemed necessary,
record the amount of change required. This is to be able to return the fittings to original
their original position when the maintenance or repair action is complete. 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 accordance with the limits show in table 7-19 after repaint or
repair.
7-3
Effective: 05/05/04