Landing Gear, Wheels & Brakes; Flight Controls; Instruments; Electrical System - THRUSH S2R – G10 Maintenance Manual

AIRCRAFT MAINTENANCE MANUAL
impurities and water accumulation from the
bulk fuel. If filtering facilities are not
available, filter the fuel through a quality
high-grade chamois. Fuel tanks should be
serviced after the last flight of each day to
reduce condensation
entrapped water accumulations to settle to
the fuel system drains, to be removed,
prior to the next flight.
Prior to the first flight of the day the wing
tanks, header tank and fuel filter should be
drained to check for the presence of water
or sediment in the fuel system. If there is a
possibility, at any time, that any tank may
contain water, the header tank and fuel
filter should be drained as necessary to
ensure no water exists in the fuel system.
For fuel system servicing information, refer
to Section 2.
LANDING GEAR, WHEELS &
BRAKES
The main landing gear is a welded truss of
streamlined chrome-moly steel tube. The
left main gear and the right main gear are
symmetrical. The main tires are 29 x 11
on Cleveland 40-133 wheels with 30-98
dual caliper disc brakes. Inboard mounted
elastomeric shock struts absorb landing
and taxi stresses. The brake system has
individual toe brakes and individual park
brakes. The use of a special N-513
compound cup in each master cylinder
permits the use of MIL-H-5606, a heavy-
duty aviation hydraulic fluid. The tail gear
uses a 12.5 x 4.5 tire and tube mounted in
a symmetrical fork with a spring steel
shock absorber. The tailwheel is normally
locked but can be unlocked for full-
castering as the airplane is steered with
the brakes.

FLIGHT CONTROLS

The flight controls are of conventional
design employing extensive use of ball
bearings for low friction and smoothness of
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THRUSH AIRCRAFT, INC – MODEL S2R-G10
and allow any
operation. The aileron and elevator
controls are push rod systems and rudder
control is through tension cables.
elevator trim control is actuated by a lever
that moves the tab to the desired position
through push rods.
operated electrically and controlled by a
switch located on the left side of the
cockpit. The rudder controls are inter-
connected by springs to the aileron system
so that a wing may be lifted with the rudder
alone.

INSTRUMENTS

The standard instruments are located on
three separate panels: An upper panel, a
left panel, and a right panel. The left panel
contains a clock, oil temperature, hour
meter, fuel pressure, oil pressure, torque
gauge and fuel quantity gauges. The right
panel contains a voltmeter, ammeter, and
circuit breakers. The upper panel contains
propeller tachometer and a standard flight
instrument package.

ELECTRICAL SYSTEM

The standard 28 volts 250 amp electrical
system consists of the generating and
starting system, the wiper/washer system,
the navigation lights and the strobe lights.
The navigation lights, strobe lights, landing
lights, working lights and the air conditioner
system are optional. The electrical system
obtains power from dual 28-volt batteries
and one a starter-generator. An external
power receptacle is standard equipment
and may be used for connecting a 28-volt
ground power unit to the aircraft for engine
starting or maintenance. The ground start
system utilizes the master relay so that
starting is accomplished by engaging the
starter switch.
AIRCRAFT WEIGHT & BALANCE
Refer to S2R-G10 Flight Manual for
detailed aircraft weight
information.
The
The wing flaps are
and balance
Effective: 03/26/2010