Aircraft Systems; Hydraulic System; Power Plant & Propeller; Fuel System - THRUSH S2R – G10 Maintenance Manual

AIRCRAFT MAINTENANCE MANUAL
the seat structure.
vertically. The rudder pedals adjust fore
and aft. The windshield is a three-piece
construction. The center section is
tempered safety plate glass for better
resistance to scratching and bird strikes.
The windshield side panels are Plexiglas
and are curved to provide streamlining.

AIRCRAFT SYSTEMS

HYDRAULIC SYSTEM

The hydraulic system consists of two
master brake cylinders with hydraulic lines
connecting the master cylinders to the
wheel brake cylinders.
pressure on the rudder pedals actuates the
master cylinders, which are located above
and just aft of the pilot's rudder pedals. A
small reservoir is incorporated within each
master cylinder to supply the system with
brake fluid.
POWER PLANT & PROPELLER
The Thrush S2R-G10 is powered by the
Garrett (Honeywell) TPE331-10 turbo-prop
engine. The propeller is a constant speed
Hartzell HCB4TN-5NL hub with LT10890N
blades, McCauley 4HFR34C653 hub with
L106FA-0 blades,
4HFR34C662 hub with L108FA blades.
This combination provides takeoff power of
900 BHP at 1,500 RPM.
mount is a welded chrome-moly tube truss,
stress relieved after welding. The engine
is attached to the mount through vibration
isolators.
Accessibility for servicing and inspection in
the engine compartment is exceptional, as
cowl panels are easily removed for full
access.

FUEL SYSTEM

A 228-gallon (useable) fuel supply is
available for the Thrush S2R-G10. One
hundred fifteen gallons of fuel is contained
in an integral wing tank (wet wing) just
outboard of the wing root. The left wing
Effective: 03/26/2010
THRUSH AIRCRAFT, INC – MODEL S2R-G10
The seats adjust
Applying toe
or McCauley
The engine
and right wing
interconnected through a 4.5 U.S. gallon
header tank that is located in the fuselage.
The fuel supply line to the engine is routed
from the header tank outlet finger screen
through a fuel shutoff (on/off) valve to an
electric driven fuel boost pump.
The electrically driven fuel boost pump
provides boosted fuel pressure to the
engine during starting. The electric driven
fuel boost pump discharge is then routed
through a 25-micron main fuel filter to the
engine fuel control.
The fuel tank vent system is designed to
keep the fuel spillage to a minimum. The
fuel tanks are vented through tubing
connected at both the inboard and
outboard ends of the individual fuel tanks
to the centrally located vent system in the
fuselage. Ram air enters a vent scoop, on
the fuselage, under the left wing and
pressurizes the vent system to maintain
positive pressure on the fuel tanks. The
vent system is provided with two quick
drains, located on the fuselage under each
wing, to drain any fuel that might have
gotten into the tanks outboard vent lines.
The fuel quantity gauge is located on the
lower left instrument panel.
quantity indicating system consists of two
transmitters, one indicator gauge, and an
L/H or R/H tank fuel quantity selector
switch. A transmitter installed in each wing
tank transmits an electrical signal to the
single fuel quantity
instrument reads the left or right fuel tank
singularly, as chosen by the fuel quantity
selector switch, adjacent to the fuel
quantity indicator gauge on the instrument
panel.
The two fuel tanks are serviced through
filler ports located on the top of each wing.
The filler ports incorporate security chains
to prevent the loss of the fuel caps.
Service the aircraft from refueling facilities
that utilize proper
equipment and filter systems to remove
fuel tanks are
The fuel
indicator. The
ground handling
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