THRUSH S2R – G10 Maintenance Manual
AIRCRAFT MAINTENANCE
MANUAL
SINGLE COCKPIT AND DUAL COCKP IT
Model S2R – G10
Serial Numbers S2R-G10 S/N G10-169 & up
Issued March 26, 2010
Note:
All serial numbers with the DC suffix indicate the dual cockpit configuration.
Manufacturer’s Serial Number: ____________
Registration Number: ________________ Thrush Aircraft
Inc.
P. O. Box 3149
300 Old Pretoria Road
Albany, GA 31706
Telephone: 229-883-1440
Fax: 229-436-4856
Effective: 03/26/2010
page
i
THRUSH AIRCRAFT INC. – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
INTRODUCTION
This publication provides information for the Thrush Aircraft, Inc. Model S2R-G10 Turbo
Thrush airplane. Installations or equipment will vary from airplane to airplane due to the
wide range of optional equipment. The information contained within this manual is based
on data available at the time of publication and will be kept current by changes or service
publications.
This manual contains information on aircraft systems and operating procedures required for
safe and effective maintenance. It shall not be used as a substitute for sound judgment.
In this manual:
WARNING
INDICATES A STRONG POSSIBILITY OF SEVERE
PERSONAL INJURY OR LOSS OF LIFE IF
INSTRUCTIONS ARE NOT FOLLOWED.
CAUTION
Indicates a possibility of personal injury or
equipment damage if instructions are not followed.
* NOTE *
Gives helpful information.
Attention: Owners, Operators and Maintenance Personnel:
Detailed descriptions of standard workshop procedures, safety principles and service
operations are NOT included in this manual. Please note that this manual DOES contain
warnings and cautions against some specific service methods which could cause
PERSONAL INJURY or could damage an aircraft or MAKE IT UNSAFE. Please
understand that these warnings cannot cover all conceivable ways in which service,
whether or not recommended by Thrush Aircraft Inc., might be accomplished or of the
possible hazardous consequences of each conceivable method, nor could Thrush Aircraft
Inc. investigate all such ways. Anyone using service procedures or tools, whether or not
recommended by Thrush Aircraft Inc. must satisfy themselves thoroughly that neither
personal safety nor aircraft safety will be jeopardized.
All information contained in this manual is based on the latest product information available
at the time of printing. Thrush Aircraft, Inc. reserves the right to make changes at any time
without notice.
page Effective: 03/26/2010 ii
THRUSH AIRCRAFT INC. – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
Manual Organization
This maintenance manual is divided into the following eleven sections, each with its own
table of contents:
SECTION 1..................................................GENERAL INFORMATION
SECTION 2..................................................SERVICING & INSPECTION
SECTION 3..................................................HYDRAULICS
SECTION 4.................................................. POWERPLANT AND PROPELLER
SECTION 5.................................................. FUEL SYSTEM
SECTION 6.................................................. LANDING GEAR, WHEELS & BRAKES
SECTION 7.................................................. FLIGHT CONTROLS
SECTION 8..................................................INSTRUMENTS
SECTION 9.................................................. DISPERSAL SYSTEMS
SECTION 10................................................ ELECTRICAL
SECTION 11................................................ AIRWORTHINESS LIMITATIONS
Effective: 03/26/2010
page iii
THRUSH AIRCRAFT INC. – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
LOG OF PAGES
Page Date
i ...................................... 03/26/2010
ii ...................................... 03/26/2010
iii ...................................... 03/26/2010
iv ...................................... 03/26/2010
v ...................................... 03/26/2010
vi ...................................... 03/26/2010
vii ...................................... 03/26/2010
vii ...................................... 03/26/2010
viii BLANK 03/26/2010
INTRODUCTION
SECTION 1
GENERAL
INFORMATION
Page Date
1 ...................................... 03/26/2010
2 ...................................... 03/26/2010
3 ...................................... 03/26/2010
4 ...................................... 03/26/2010
5 ...................................... 03/26/2010
6 ...................................... 03/26/2010
7 ...................................... 03/26/2010
8 ...................................... 03/26/2010
SECTION 2
SERVICING &
INSPECTION
Page Date
1 ...................................... 03/26/2010
2 ...................................... 03/26/2010
3 ...................................... 03/26/2010
4 ...................................... 03/26/2010
5 ...................................... 03/26/2010
6 ...................................... 03/26/2010
7 ...................................... 03/26/2010
8 ...................................... 03/26/2010
9 ...................................... 03/26/2010
10 ...................................... 03/26/2010
11 ...................................... 03/26/2010
12 ...................................... 03/26/2010
13 ...................................... 03/26/2010
14 ...................................... 03/26/2010
15 ...................................... 03/26/2010
16 ...................................... 03/26/2010
17 ......................................
18 ...................................... 03/26/2010
19 ...................................... 03/26/2010
20 ...................................... 03/26/2010
21 ...................................... 03/26/2010
22 ...................................... 03/26/2010
23 ...................................... 03/26/2010
24 ...................................... 03/26/2010
25 ...................................... 03/26/2010
26 ...................................... 03/26/2010
03/26/2010
(Continued)
Page Date
27 ....................................... 03/26/2010
28 ....................................... 03/26/2010
29 ....................................... 03/26/2010
30 ....................................... 03/26/2010
31 ....................................... 03/26/2010
32 ....................................... 03/26/2010
33 ....................................... 03/26/2010
34 ....................................... 03/26/2010
35 ....................................... 03/26/2010
36 ....................................... 03/26/2010
37 ....................................... 03/26/2010
38 BLANK 03/26/2010
Page Date
1 ....................................... 03/26/2010
2 ....................................... 03/26/2010
3 ....................................... 03/26/2010
4 ....................................... 03/26/2010
5 ....................................... 03/26/2010
6 ....................................... 03/26/2010
SECTION 2
SERVICING &
INSPECTION
SECTION 3
HYDRAULICS
SECTION 4
POWERPLANT &
PROPELLER
Page Date
1 ....................................... 03/26/2010
2 ....................................... 03/26/2010
3 ....................................... 03/26/2010
4 ....................................... 03/26/2010
5 ....................................... 03/26/2010
6
7 ....................................... 03/26/2010
8 ....................................... 03/26/2010
9 ....................................... 03/26/2010
10 ....................................... 03/26/2010
11 ....................................... 03/26/2010
12 ....................................... 03/26/2010
13 ....................................... 03/26/2010
14 ....................................... 03/26/2010
15 ....................................... 03/26/2010
16 ....................................... 03/26/2010
17 ....................................... 03/26/2010
18 ....................................... 03/26/2010
Page Date
1 ....................................... 03/26/2010
2 ....................................... 03/26/2010
3 ....................................... 03/26/2010
4 ....................................... 03/26/2010
.......................................
SECTION 5
FUEL SYSTEM
03/26/2010
iv
page Effective: 03/26/2010
THRUSH AIRCRAFT INC. – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
Page Date
5 ...................................... 03/26/2010
6 ...................................... 03/26/2010
7 ...................................... 03/26/2010
8 ...................................... 03/26/2010
9 ...................................... 03/26/2010
10 ...................................... 03/26/2010
11 ...................................... 03/26/2010
12 ...................................... 03/26/2010
13 ...................................... 03/26/2010
14 ...................................... 03/26/2010
15 ...................................... 03/26/2010
16 ...................................... 03/26/2010
17 ...................................... 03/26/2010
18 BLANK 03/26/2010
SECTION 5
FUEL SYSTEM
continued
SECTION 6
LANDING GEAR,
WHEELS &
BRAKES
Page Date
1 ...................................... 03/26/2010
2 ...................................... 03/26/2010
3 ...................................... 03/26/2010
4 ...................................... 03/26/2010
5 ...................................... 03/26/2010
6 ...................................... 03/26/2010
7 ...................................... 03/26/2010
8 ...................................... 03/26/2010
9 ...................................... 03/26/2010
10 ...................................... 03/26/2010
11 ...................................... 03/26/2010
12 ...................................... 03/26/2010
13 ...................................... 03/26/2010
14 ...................................... 03/26/2010
15 ...................................... 03/26/2010
16 ...................................... 03/26/2010
17 ...................................... 03/26/2010
18 ...................................... 03/26/2010
19 ...................................... 03/26/2010
20 BLANK 03/26/2010
SECTION 7
FLIGHT
CONTROLS
Page Date
1 ...................................... 03/26/2010
2 ...................................... 03/26/2010
3 ...................................... 03/26/2010
4 ...................................... 03/26/2010
5 ...................................... 03/26/2010
6 ...................................... 03/26/2010
7 ...................................... 03/26/2010
8 ...................................... 03/26/2010
Effective: 03/26/2010 page v
SECTION 7
FLIGHT
CONTROLS
Page Date
9 ...................................... 03/26/2010
10 ...................................... 03/26/2010
11 ...................................... 03/26/2010
12 ...................................... 03/26/2010
13 ...................................... 03/26/2010
14 ...................................... 03/26/2010
15 ...................................... 03/26/2010
16 ...................................... 03/26/2010
17 ...................................... 03/26/2010
18 ...................................... 03/26/2010
19 ...................................... 03/26/2010
20 ...................................... 03/26/2010
21 ...................................... 03/26/2010
22 ...................................... 03/26/2010
23 ...................................... 03/26/2010
24 ...................................... 03/26/2010
25 ...................................... 03/26/2010
26 ...................................... 03/26/2010
27 ...................................... 03/26/2010
28 ...................................... 03/26/2010
29 ...................................... 03/26/2010
30 ...................................... 03/26/2010
31 ...................................... 03/26/2010
32 BLANK 03/26/2010
Page Date
1 ...................................... 03/26/2010
2 ......................................
3 ...................................... 03/26/2010
4 ...................................... 03/26/2010
5 ...................................... 03/26/2010
6 ...................................... 03/26/2010
7 ...................................... 03/26/2010
8 ...................................... 03/26/2010
9 ...................................... 03/26/2010
10 ...................................... 03/26/2010
11 ...................................... 03/26/2010
12 ...................................... 03/26/2010
13 ...................................... 03/26/2010
14 ...................................... 03/26/2010
15 ...................................... 03/26/2010
16 ...................................... 03/26/2010
17 ...................................... 03/26/2010
18 BLANK 03/26/2010
continued
SECTION 8
INSTRUMENTS
03/26/2010
THRUSH AIRCRAFT INC. – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
SECTION 9
DISPERSAL
SYSTEMS
Page Date
1 ...................................... 03/26/2010
2 ...................................... 03/26/2010
3 ...................................... 03/26/2010
4 ...................................... 03/26/2010
5 ...................................... 03/26/2010
6 ...................................... 03/26/2010
7 ...................................... 03/26/2010
8 BLANK 03/26/2010
SECTION 10
ELECTRICAL
SYSTEM
Page Date
1 ...................................... 03/26/2010
2 ...................................... 03/26/2010
3 ...................................... 03/26/2010
4 ...................................... 03/26/2010
5 ...................................... 03/26/2010
6 ...................................... 03/26/2010
7 ...................................... 03/26/2010
8 ...................................... 03/26/2010
9 ...................................... 03/26/2010
10 ...................................... 03/26/2010
11 ...................................... 03/26/2010
12 ...................................... 03/26/2010
13 ...................................... 03/26/2010
14 ...................................... 03/26/2010
15 ...................................... 03/26/2010
16 ...................................... 03/26/2010
17 ...................................... 03/26/2010
18 ...................................... 03/26/2010
19 ...................................... 03/26/2010
20 ...................................... 03/26/2010
21 ...................................... 03/26/2010
22 ...................................... 03/26/2010
23 ...................................... 03/26/2010
24 ...................................... 03/26/2010
25 ...................................... 03/26/2010
26 ...................................... 03/26/2010
27 ...................................... 03/26/2010
28 ...................................... 03/26/2010
29 ...................................... 03/26/2010
30
31 ...................................... 03/26/2010
32 ...................................... 03/26/2010
......................................
03/26/2010
SECTION 11
AIRWORTHINESS
LIMITATIONS
Page Date
1 ....................................... 03/26/2010
2 ....................................... 03/26/2010
page vi Effective: 03/26/2010
THRUSH AIRCRAFT INC. – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
THIS PAGE INTENTIONALLY LEFT BLANK
page viii Effective: 03/26/2010
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
SECTION 1
GENERAL INFORMATION
TABLE OF CONTENTS
GENERAL DESCRIPTION................................................................................................2
CONTACT INFORMATION.....................................................................................2
PRINCIPAL DIMENSIONS ................................................................................................2
GENERAL.....................................................................................................................2
WEIGHT & BALANCE ..................................................................................................2
WING............................................................................................................................2
HORIZONTAL STABILIZER AND ELEVATORS ..........................................................3
VERTICAL STABILIZER AND RUDDER......................................................................3
AREAS..........................................................................................................................3
SUPPLIER FURNISHED COMPONENT MANUALS....................................................3
AIRCRAFT STRUCTURE..................................................................................................4
FUSELAGE...................................................................................................................4
WING............................................................................................................................4
EMPENNAGE...............................................................................................................4
COCKPIT......................................................................................................................4
AIRCRAFT SYSTEMS.......................................................................................................5
HYDRAULIC SYSTEM .................................................................................................5
POWER PLANT & PROPELLER..................................................................................5
FUEL SYSTEM.............................................................................................................5
LANDING GEAR, WHEELS & BRAKES.......................................................................6
FLIGHT CONTROLS....................................................................................................6
INSTRUMENTS............................................................................................................6
ELECTRICAL SYSTEM................................................................................................6
AIRCRAFT WEIGHT & BALANCE................................................................................6
Figure 1-1: Aircraft 3-view .......................................................................................7
Figure 1-2: Aircraft Stations.....................................................................................8
Effective: 03/26/2010 page 1-1
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
GENERAL DESCRIPTION
The Thrush Aircraft Inc Thrush S2R-G10 is designed especially for agricultural flying. It is a
monoplane featuring a full cantilever low wing and all metal construction. The design and
construction of the airframe components assure structural integrity, flight safety, and
minimum maintenance requirements. The Thrush S2R-G10 is designed for the highest
crash load factors in the industry. Safety and reliabilit y of operation and maximum pilot crash
protection are proven and effective features of the design. The high strength overturn
structure is a proven design. The fuselage and overturn structure, constructed throughout of
chrome-moly steel tubing, are immensely strong in the cockpit area.
CONTACT INFORMATION
For further information related to this manual, please contact our Product Support Manager
at (229) 883-1440 extension 219.
PRINCIPAL DIMENSIONS
GENERAL
Wing Span..................................... 47.50 feet
Overall Length ............................... 32.83 feet
Height To Top Of Canopy.............. 9.33 feet
Main Gear Tread............................ 9.00 feet
Main Gear To Tail Wheel............... 19.20 feet
WEIGHT & BALANCE
C. G. Range (See Airplane Flight Manual for pertinent data)
Forward Limit at 6,000 pounds is 26.5
Forward Limit.................................
Aft Limit .........................................
Datum............................................
inches aft of datum. It is 24.0 at 4,000
pounds with straight line variation between.
Aft Limit at all weights is 30.0 inches aft of
datum
Datum Is The Leading Edge Of The Wing.
WING
page Effective: 03/26/2010 1-2
Type ............................................... Full Cantilever
Airfoil Section ................................. NACA 4412
Dihedral.......................................... 3.50 Degrees
Aileron Travel
Up........................................ 21 Degrees ±1 Degree
Down ................................... 17 Degrees ±1 Degree
Flap Travel: Down .......................... 15 Degrees ±1 Degree
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
HORIZONTAL STABILIZER AND ELEVATORS
Span............................................... 204 Inches (17')
Elevator Travel
Up........................................ 27 Degrees ±1 Degree
Down................................... 17 Degrees ±1 Degree
Trim Tab Travel
Up........................................ 8 Degrees ±1 Degree
Down................................... 22 Degrees ±1 Degree
VERTICAL STABILIZER AND RUDDER
Vertical Fin Offset........................... 0 Degrees ±1 Degree Left and Right
Rudder Travel ................................ 19 Degrees ±1 Degree Left and Right
AREAS
Wing............................................... 356.3 Square Feet
Aileron (Each)................................. 23.4 Square Feet
Flaps (Each)................................... 15.3 Square Feet
Stabilizer......................................... 39.3 Square Feet
Elevators ........................................ 20.4 Square Feet
Elevator Tabs (Each)...................... 1.3 Square Feet
Vertical Fin .................................... 9.4 Square Feet
Rudder ........................................... 12.2 Square Feet
SUPPLIER FURNISHED COMPONENT MANUALS
COMPONENT MANUAL PART #
TPE331-G10 Maintenance Manual 72-00-27
TPE331-G10 Parts Manual 72-01-16
Propeller Owner’s Manual N/A
Note: Should there be a conflict between the information in this manual and that in the
manuals for component parts, the information in the component part manual takes
precedence.
Effective: 03/26/2010 page 1-3
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
AIRCRAFT STRUCTURE
FUSELAGE
The fuselage is comprised of a welded
tubular steel frame, fiberglass hopper, and
detachable skins. An overturn structure
forms an integral part of the fuselage
frame. The frame structure is fabricated
from 4130 chrome-moly seamless steel
tubing, and the fittings, bushings, brackets,
and so forth are 4130 steel sheet.
As a corrosion preventative, hot linseed oil
is pumped throughout the entire welded
structure. On an average, 12 gallons are
pumped into the frame and 11 to 11 ½
gallons drain out, leaving a residual interior
coating on all members. The exterior of
the frame is sandblasted, etched, and
primed, which is followed by two coats of
polyurethane paint that is resistant to
chemical reaction.
The fuselage is covered with heat treated
Alclad panels attached with camloc
fasteners. Side skins can be removed
using only a screwdriver, thus exposing
the fuselage frame for thorough cleaning
and inspection. All skins are supported
clear of the fuselage tubing to prevent
accumulation of corrosive chemicals.
Each skin panel is etched, primed, and
painted before assembly to ensure
complete coverage. All bottom fuselage
skins around the hopper opening and aft to
the tail post are made of stainless steel.
The skin fasteners in the high corrosion
areas are also stainless steel.
WING
The wing has a constant chord of 90
inches, and is all metal, full cantilever
design. The massive main spar is a
tension field beam structure constructed
from Alclad webs and high strength heattreated steel caps. All wing skins, ribs, and
leading edges are constructed from Alclad
heat-treated material. The leading edge
structure is made especially strong to
minimize denting and is riveted with
universal rivets for strength. The fuel
tanks, which are located in the inboard
section of the wing, are an integral part of
the structure. Close pitch riveting of the
seams, substantial reinforcement, and
flexible sealants minimize chances of
rupture in crash conditions. Drain holes
are provided in adjacent bays to prevent
accumulation of fuel in the event of a leak.
The ailerons and flaps are all metal
construction and are hinged on ball
bearings. The flaps are electrically
operated by push rods and are completely
sealed against chemical entry. Flap
hinges are stainless steel.
EMPENNAGE
The horizontal stabilizer, elevator, rudder
and vertical fin are an all-metal structure.
All skins, ribs and leading edges are
constructed from alclad material. The
movable surfaces are hinged on sealed
bearings that can be easily replaced. The
rudder and the elevator have aerodynamic
balances that are protected by overhangs
on the fixed surfaces.
COCKPIT
There are two choices of the enclosed
cockpit canopies for the Thrush S2R-G10
(1) the SINGLE cockpit canopy or (2) the
DUAL cockpit canopy. The overturn
structure of both is exceptionally strong
and welded to "hard points" in the fuselage
frame. The forward bracing supports the
windshield support channels and is we lded
to a lateral tube that is curved to provide
more head clearance. The fiberglass
canopy shell has extra thickness on the
top portion and is well attached to the extra
large steel tube structure so that it will
serve as a skid in case of overturn. The
large canopy doors permit easy entrance
to one or both cockpits. The doors should
not be removed for flight, as the aircraft
performance will be degraded. The
cockpit seat belts are anchored to the seat
structure, and the shoulder harnesses are
secured to a steel channel at the bottom of
1-4
page Effective: 03/26/2010
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
the seat structure. The seats adjust
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. Applying toe
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, or McCauley
4HFR34C662 hub with L108FA blades.
This combination provides takeoff power of
900 BHP at 1,500 RPM. The engine
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
and right wing fuel tanks are
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. The fuel
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 indicator. The
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 ground handling
equipment and filter systems to remove
Effective: 03/26/2010 page 1-5
THRUSH AIRCRAFT, INC – MODEL S2R-G10
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 and allow any
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 heavyduty 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 fullcastering 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
operation. The aileron and elevator
controls are push rod systems and rudder
control is through tension cables. The
elevator trim control is actuated by a lever
that moves the tab to the desired position
through push rods. The wing flaps are
operated electrically and controlled by a
switch located on the left side of the
cockpit. The rudder controls are interconnected 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 and balance
information.
page 1-6 Effective: 03/26/2010
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
Figure 1-1: Aircraft 3-view
Effective: 03/26/2010 page 1-7
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
page Effective: 03/26/2010 1-8
Figure 1-2: Aircraft Stations
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
Effective: 03/26/2010 page 1-9
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
SECTION 2
SERVICING & INSPECTION
TABLE OF CONTENTS
SERVICING & INSPECTION.......................................................................................... 3
GENERAL DESCRIPTION
GROUND HANDLING............................................................................................... 3
TOWING............................................................................................................... 3
TAXIING............................................................................................................... 3
PARKING ............................................................................................................. 3
MOORING............................................................................................................ 3
JACKING.............................................................................................................. 3
LEVELING............................................................................................................ 3
Figure 2-1: Tie Down and Jack Points............................................................ 4
WEIGHING........................................................................................................... 5
Calculated Weight........................................................................................... 5
Weighing the Airplane..................................................................................... 5
COLD WEATHER OPERATION................................................................................ 6
COLD WEATHER MAINTENANCE HINTS .......................................................... 6
GROUND EMERGENCY PROCEDURES................................................................. 7
ENGINE FIRES....................................................................................................7
ELECTRICAL FIRES............................................................................................ 7
GROUND OPERATION OF ENGINE ......................................................................... 7
EXTERIOR PRE-START CHECK ........................................................................ 7
PRE-START CHECKLIST.................................................................................... 7
COCKPIT PRE-START CHECK........................................................................... 7
STARTING ENGINE............................................................................................. 8
SYSTEM AND COMPONENT SERVICING............................................................... 9
HYDRAULIC SYSTEM ......................................................................................... 9
ENGINE OIL SYSTEM.......................................................................................... 9
FUEL SYSTEM...................................................................................................10
Figure 2-2: Fuel System............................................................................... 11
DEFUELING............................................................................................. 12
LANDING GEAR, WHEELS & BRAKES............................................................. 12
Tires ..............................................................................................................12
MLG Shock Struts ......................................................................................... 12
BRAKE BLEEDING ......................................................................................13
INSPECTION ........................................................................................................... 13
INSPECTION CHECK LIST ................................................................................ 13
GENERAL INSTRUCTIONS........................................................................... 13
Figure 2-3: G10 Servicing and Inspection Guide........................................ 14
Effective: 03/26/2010 Page 2-1
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
Table 2-2: INSPECTION CHECK LIST............................................................14
A: Propeller...................................................................................................13
B: Engine Externals ......................................................................................15
C: Engine Oil System....................................................................................16
D: Engine Fuel Xystem.................................................................................17
E: IGNITION SYSTEM..................................................................................17
F: Airframe Fuel System...............................................................................17
G: Main Landing Gear...................................................................................19
H: Hydraulic System .....................................................................................19
J : Tail Gear ..................................................................................................19
K: Fuselage Skins.........................................................................................21
L: Hopper......................................................................................................21
M: Wings.......................................................................................................21
N: Fuselage Frame.......................................................................................22
P: Control Systems.......................................................................................23
Q: Empennage..............................................................................................24
R: Ailerons and Flaps....................................................................................24
S: Cockpit .....................................................................................................25
T: Electrical System......................................................................................26
BATTERY MAINTENANCE......................................................................................26
AIRFRAME MAINTENANCE........................................................................................26
CORROSION CONTROL.........................................................................................26
WINDSHIELD...........................................................................................................28
HOPPER REPAIR ....................................................................................................28
FUEL TANK REPAIR...............................................................................................28
Table 2-3: Torque Chart....................................................................................29
LUBRICATION..............................................................................................................30
Figure 2-4: Lubrication Chart (9 pages)..............................................................30
Page 2-2 Effective 03/26/2010
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
SERVICING & INSPECTION
Standard procedure for ground handling,
servicing, inspection, airframe
maintenance, lubrication, and storage are
included in this Section. Adherence to
these procedures on a scheduled basis
can save many hours of maintenance and
aircraft down time. When a system
component requires service or
maintenance other than that outlined in
this Section, refer to the applicable Section
of this manual for complete information.
GROUND HANDLING
TOWING
Movement of the aircraft on the ground
may be accomplished as follows:
a. Pull and guide the aircraft by means of
a tow bar with the tail wheel unlocked.
b. Attach a rope harness to the main
gear when there is a need to tow the
aircraft forward through snow or over
soft and/or muddy ground.
PARKING
Head the aircraft into the wind and set the
parking brake. Do not set the parking
brake during cold wet weather because the
accumulated moisture may freeze in the
brakes. Do not set the parking brake if the
brakes are overheated. Install the internal
control lock and place the chocks under
each main wheel.
MOORING
Reference Fig. 2-1
Park aircraft as previously outlined. In
winds up to 20 knots, secure the aircraft at
the wing tie down rings. For winds above
20 knots, tie the tail and main gear as well
as the wings. Install external control
surface locks. The aircraft should be
placed in a hangar when wind velocity is
predicted to exceed 50 knots. When
mooring the aircraft, use 3/4-inch manila or
nylon rope. A clove hitch or other anti-slip
knot should be employed. If a manila rope
is used for tie down, allow enough slack to
compensate for shrinkage of the rope fiber
without damaging the aircraft.
TAXIING
Before attempting to taxi the aircraft,
maintenance personnel should be checked
out by qualified personnel. When it is
determined that the propeller area is clear,
apply the power to start the taxi roll and
perform the following:
c. Push the stick full forward to unlock
the tail wheel.
d. Taxi a few feet and check the brake
operation.
e. While taxiing, make slight turns to
determine that the tail wheel steering
is operative.
f. Avoid taxiing over ground covered with
loose stones, gravel, or other loose
material that may cause foreign object
damage to the propeller or to other
aircraft in the area.
JACKING
Reference Fig. 2-1
Jack points are provided on each main
spar and located at wing stations 120 &
193.38. When using the jack points to lift
the aircraft, all hopper loads should be
removed. (Fig. 2-1) A jack point is also
provided on the tail wheel trunnion attach
fitting on the lower left longeron.
LEVELING
Reference Fig. 2-1
The aircraft may be leveled by raising the
tail to an approximate level flight position
by supporting the tail on a stable jack or
platform. Adjust the height of the tail wheel
until the left-hand lower longeron located
under the pilot’s cockpit is level. The lower
left side panel must be removed for access
to the leveling longeron.
Effective: 03/26/2010 Page
2-3
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
Figure 2-1: Leveling, Tie Down and Jack Points
Page 2-4 Effective 03/26/2010
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
WEIGHING
Calculated Weight
The weight and center of gravity (C.G.) of
the airplane as it left the factory is supplied
with all the other paperwork.
Slight changes to the aircraft that do not
significantly alter the weight or C.G. can be
ignored, but judgment must be used when
doing so. A change weighing a pound in
the aft fuselage may be more significant
than a 5# change under the cockpit.
For changes that do significantly affect the
weight or C.G., the new empty weight and
C.G. can generally be calculated and
logged in the log book. To do this you
must know the weight change (+ for
added, - for subtracted) and its distance, in
inches, from the aircraft datum (wing
leading edge), “+” being aft of the datum
and “-“being forward.
*NOTE*
Center of Gravity (C.G.) location is
NOT the same as fuselage station.
The existing empty weight and C.G.
produces a moment by multiplying the two
together, and all three should be logged.
Changes to the aircraft will also have a
weight and location for their C.G., which
will give their moment when multiplied
together.
To determine the new empty weight, the
existing weight and the weight change are
totaled. To find the new C.G., the existing
moment and the moment change are
totaled and this new moment is divided by
the new empty weight.
For example:
C.G. of equipment = -23.5 (ie. forward
of wing leading edge)
Moment change = 17 x (-23.5) =
- 400 in.#
New weight: 4,723 + 17 = 4,740#
New moment: 120,106 – 400 =
119,706 in.#
New C.G.: 119706 ÷ 4740 = 25.25” (aft
of datum)
Weighing the Airplane
New weight and C.G. due to large weight
changes, installations that are difficult to
determine the C.G. of, or multiple small
changes should generally be determined
by re-weighing the airplane.
The airplane must be in a ready to fly
condition during weighing, except that the
fuel tanks may hold unusable fuel (1.5
GAL. per side).
Three scales will be needed for this
operation: two with about a two ton
capacity and one with a half ton capacity.
These scales need to be in good condition
and calibrated within the past year.
The two large scales are placed under the
MLG tires, and the small scale is placed
under the tailwheel. The airplane must be
level during this process (see LEVELING,
above), which will require a tail stand. The
new weight is simply the total of the three
scale readings, unless the tail stand had to
be placed on the rear scale. If this was
done, the weight of the tail stand and any
shims must be subtracted from the aft
scale reading. This is not necessary if the
scale was between the tailwheel and the
stand.
Existing weight = 4,723#
Existing C.G. = 25.43”
Existing moment = 4723 x 25.43 =
120,106 in.#
Added equipment weight = 17#
Effective: 03/26/2010 Page
2-5
The new moment is the sum of the main
gear scale readings multiplied by 3.10”
(the distance the MLG axles are behind
the wing leading edge) plus the rear scale
reading (adjusted for tare as necessary)
multiplied by 232.9”. The new empty
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
weight C.G. is the total moment divided by
the total weight.
For example:
Left MLG scale reading = 2,127#
Right MLG scale reading = 2,105#
Tailwheel scale reading = 472#
Tare weight (ie. tail stand and shims if
placed on top of the scale) = 65#
New empty weight: 2127 + 2105 + 472
– 65 = 4,639#
New moment: (4232 x 3.1) + (407 x
232.9) = 107,910 in.#
New C.G.: 107910 ÷ 4639 = 23.26”
COLD WEATHER
OPERATION
Aircraft operation in cold weather creates a
need for additional maintenance practices
and operating procedures that are not
required in moderate temperatures.
Whenever possible, shelter the aircraft in a
heated hangar to prevent frost, ice, or
snow accumulation that requires added
maintenance time to remove. These
weather elements, if allowed to
accumulate only a fraction of an inch in
thickness on the critical airfoils and control
surfaces, seriously degrade aircraft lift and
flight control effectiveness. The possibility
of aircraft system failures is increased
when the aircraft is parked where wind
driven snow or freezing rain can be forced
into various openings of the aircraft. If the
aircraft is to be moored outside in extreme
cold, the battery should be kept fully
charged to prevent freezing. Make certain
that all vents, air inlets, and so forth are
covered.
Locating the aircraft inside a heated
hanger is the most effective method of
preheating the aircraft. The use of an
external power unit is recommended to
conserve the battery.
COLD WEATHER
MAINTENANCE HINTS
The information that follows is intended
only for the purpose of supplementing the
existing information in this manual when
operating the aircraft in very cold weather.
Keeping the aircraft in top maintenance
condition during cold weather cannot be
over stressed.
BATTERY: The batteries should be
maintained at full charge during cold
weather to prevent freezing. After adding
water to the battery in freezing
temperatures, charge the battery to mix
the water and electrolyte. A frozen battery
may explode when subjected to a high
charge rate. Corrosive damage to the
area adjacent to an exploded battery will
result if the electrolyte solution is not
removed immediately. Instructions for
removing spilled electrolyte are provided in
this Section. The battery should be
removed and stored in a warm place if the
aircraft is to remain idle for an extended
period of time.
FUEL SYSTEM: In the fuel system,
condensation is more likely to occur in cold
weather due to a more rapid and positive
division of moisture content from other fuel
constituents. If at all possible, use fueling
facilities that filter moisture from the fuel. If
fueling facilities with filters are not
available, filter the fuel through a good
quality chamois. Fill the tanks with correct
grade of fuel as soon as possible after
landing to reduce the possibility of
condensation and ice formation in the
tanks. Fuel extracted from fuel header
tank drain before starting deserves a
closer examination when the aircraft is
being operated in cold weather.
POST FLIGHT MAINTENANCE: Cold
weather operation demands procedures
that are in addition to normal Post Flight
Maintenance Procedures. Fill the fuel
tanks immediately after flight. If shelter is
Page Effective 03/26/2010 2-6
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
not available, tie the aircraft down and
install covers on all vents, openings, etc.
as required.
GROUND EMERGENCY
PROCEDURES
Emergency procedures must be
accomplished as rapidly as possible,
should an emergency arise. It is
suggested that steps pertaining to each
emergency be committed to memory in
order to accelerate the procedure and
minimize any possible damage.
ENGINE FIRES
If a fire develops in the engine area during
engine start, continue to attempt to start
the engine in an attempt to blow the fire
out. If the fire persists, proceed as follows:
a. Mixture Control - Idle Cut Off
b. Starter Switch - Off
c. Master Switch - Off
d. Fuel Shutoff Valve - Off
e. Abandon the aircraft
weather from the wing, the tail, and the
control surfaces. Check that the control
surfaces contain no internal accumulations
of ice. Remove the inlet and exhaust
covers, if fitted. If night flight is planned,
check the operation of all lights and have a
flashlight available.
After a complete visual inspection has
been accomplished, the following checklist
may be used for the external prestart
check. The aircraft should be headed into
the wind and should have the wheel
chocks in place.
PRE-START CHECKLIST
a. A fire extinguisher must be readily
available in the event of an engine
fire.
b. Check the engine oil level. Assure
that the oil system has been serviced
with the correct grade of oil.
c. Verify that the internal control lock
has been removed and that the
controls operate freely.
d. Set the parking brake.
ELECTRICAL FIRES
Circuit breakers will automatically trip and
stop the current flow to a shorted circuit.
However, as a safety precaution in the
event of an electrical short circuit or fire,
turn the battery switch to off. Use a fire
extinguisher approved for electrical fires to
extinguish any flame. Do not leave the
aircraft unattended so long as there is any
evidence of fire or hot spots.
GROUND OPERATION OF
ENGINE
Reference Section 4
EXTERIOR PRE-START CHECK
Visually check the aircraft for general
condition. Verify that all CamLocs on the
skin panels are fastened. Remove all
accumulations of frost, ice, or snow in cold
e. Check the fuel quantity in both tanks.
f. Set the trim tabs for takeoff.
g. Clear the area of all personnel.
COCKPIT PRE-START CHECK
a. Verify that the internal control lock has
been removed and that the controls
operate
b. Place all switches in the OFF position.
c. Set the parking brake.
d. Check the fuel quantity indication in
both tanks.
e. Set the trim tabs for takeoff.
Effective: 03/26/2010 Page
2-7
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
f. Turn Battery Switch ON, or to EXT
PWR position if external power will be
used to start the engine.
STARTING ENGINE
Use the following procedure to start the
G10 engine:
a. Power Lever – Flight idle position.
*NOTE*
Power lever must be in flight idle
position prior to and during start
sequence to prevent propeller
from coming off start lock during
starting.
b. Speed Lever – Low RPM position
c. Engine Fuel Switch – Cycle to off,
then center position
d. Fuel Valve – ON
e. Fuel Aux Pump – ON
f. Fuel Inlet Pressure Indicator –
CHECK 8 PSIG minimum
CAUTION
Do not attempt an engine start
without the propeller being on
the start locks.
*NOTE*
Engine starts can be made with the
aircraft battery power, or with
auxiliary electrical power. However,
it is recommended that an auxiliary
power unit be used when ambient
air temperature is ten degrees F. or
below. Ensure that ground power
unit (aux power) is regulated to 28
volts dc, 800 amperes during start
cycle.
To accomplish the check, do the following
during starting:
1) NTS Light – PRESS to test
2) Unfeathering Pump Switch – ON
3) NTS Check Switch – ON
4) NTS Light – CHECK ON
5) Engine Starter – Ground position (Carry out normal start)
6) NTS Light – OUT when starter is engaged
7) NTS Light – ON at 10 to 30 percent RPM
h. Engine Starter – Ground position
i. Ignition Switch – ON at 10% RPM
minimum
CAUTION
Check ignition light on prior to
operating fuel switch.
j. Engine Fuel Switch – ON at 10%
RPM minimum
CAUTION
k. If light-off is not indicated within
ten seconds or 20% RPM, reject
the start by activating the
emergency shut-off lever.
l. Fuel Enrichment Switch – ON until
approximately 680 degrees EGT
(maximum during start is 770
degrees). Then regulate
enrichment switch to obtain
satisfactory RPM increase and
temperature.
CAUTION
g. Negative Torque System Check
The NTS system should be checked
during the first start of the day or if a
malfunction of the system is suspected.
2-8
Page Effective 03/26/2010
If RPM stops increasing prior to
40% or if EGT is approaching
limits (770 degrees C) and
rising rapidly, activate the
emergency shut-off lever.
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
m. Engine Instruments – CHECK
1) RPM – 72% Minimum
2) Fuel Pressure – 8 PSIG Minimum
3) Oil Pressure – 40 PSIG Minimum
If oil pressure is not indicated
within ten seconds after lightoff, shut the engine down and
determine the cause
n. 13. Starter – OFF
o. 14. Generator – ON and charging
normally
p. 15. If NTS check was accomplished:
1) Unfeathering Pump Switch – OFF
2) NTS Check Switch – OFF
CAUTION
SYSTEM AND COMPONENT
SERVICING
Servicing procedures contained in this
Section are confined to those maintenance
actions that occur with routine frequency
and require a reasonably short period of
time to accomplish. Servicing practices
and maintenance of aircraft systems and
components that require less frequent
attention are contained in the appropriate
sections of this manual.
HYDRAULIC SYSTEM
Reference Section 3
The hydraulic system consists of two
master brake cylinders and the necessary
hydraulic lines connecting the master
cylinders to the wheel brake cylinders.
Applying toe pressure to the rudder pedal
actuates the corresponding master
cylinder, which in turn actuates the brake
caliper piston. Refer to Section Six for
brake servicing procedures.
ENGINE OIL SYSTEM
Reference Section 4
The oils that are specified for the
lubrication system can be found in the
applicable engine Maintenance Manual. It
is recommended for all turbo aircraft that
the oil be changed every 400 hours. The
oil system contains 9 U.S. quarts.
*NOTE*
The unfeathering pump draws oil
from the engine oil tank to actuate
the propeller. The oil from the
propeller subsequently drains into
the reduction gear box, not the
engine oil tank. If the unfeathering
pump has been operated prior to
checking the oil level in the tank,
pump the oil out of the gearbox and
into the oil tank by turning the
propeller 50 to 75 revolutions by
hand or by starter. During the
procedure, it is not uncommon to
experience some loss of oil
overboard through the vent.
The contents of the oil tank should be
checked within 10 minutes of the engine
shutdown. To do so, proceed as follows:
a. Unlock the filler cap and dipstick from
the filler neck on the oil tank.
CAUTION
Do not mix brands or types of oil,
since their chemical structures
may make them incompatible. If
different brands or types of oil
become mixed, drain and flush
the system and refill with new oil.
b. Check the oil tank contents against the
markings on the dipstick. Service as
required.
c. Compensate for the pitch attitude of
the aircraft to avoid over or under
servicing.
Effective: 03/26/2010 Page
2-9
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
If the oil level is too low to register on the
dipstick due to possible excessive
consumption or if low or fluctuating oil
pressure noted, refer to the trouble
shooting section in your applicable engine
Maintenance Manual for the action to be
taken. After that has been accomplished,
proceed as follows to check the oil level.
d. Fill the oil tank to the appropriate
normal level. Record the quantity of
oil added to the system.
e. Install the filler cap and dipstick.
Ensure that the cap is securely locked.
f. Run the engine at idle for
approximately five minutes.
g. Check the oil level.
On engines which have remained
stationary for a period of 12 hours or more,
proceed as follows to check the oil level.
1) Start engine and run at idle speed for a minimum of two minutes.
must be conducted with the electrical fuel
auxiliary boost pump ON.
WARNING
GROUND THE AIRCRAFT TO A
PROPER GROUND AND THE
FUEL SERVICING EQUIPMENT TO
THE AIRCRAFT. SMOKING IN OR
AROUND THE AIRCRAFT DURING
REFUELING OPERATIONS IS
PROHIBITED. FIRE PROTECTION
EQUIPMENT MUST BE
IMMEDIATELY AVAILABLE.
To fuel the aircraft, proceed as follows:
a. Remove the fuel filler cap. Fill the tank
until the fuel level rises to the filler
neck (or to desired quantity). Install
the fuel filler cap and service the
opposite fuel tank.
* NOTE *
2) Shut the engine down.
3) Check the oil level.
FUEL SYSTEM
Reference Section 5
REFUELING:
(Ref. Fig. 2-2)
Refuel the aircraft with fueling facilities
that contain filters for removing the
moisture content from the fuel. If the
fueling facilities with filters are not
available, filter the fuel through a good
grade of chamois. The fuel tanks should
be serviced after the last flight of the day
to allow maximum time for the moisture to
reach the sumps and header tank.
Service the aircraft with Jet A, Jet B, JP4
or JP5. If jet fuel is not available, aviation
gasoline MIL-G-5572 (all grades) not in
excess of 250 gallons per 100 hours of
operation may be used for emergency fuel
operation. Total usage must be limited to
7000 gallons during any 3000 hour period.
Flight operations using aviation gasoline
Since the wing tanks are
interconnected through the header
tank, the fuel can flow from one
tank to another. Topping off both
wing tanks may be required more
than one time to assure that both
wing tanks are full.
b. After fueling is complete, check for
security of both fill port caps. Wash
any spilled fuel from the wing surface
with clean water.
FUEL DRAINS:
(Ref. Fig. 2-2)
Four fuel drain points are provided to allow
fuel draining in order to extract the moisture
sediment and other contamination entrapped
in the system. The drains are located at the
low point of each wing tank (aft inboard
bottom), the bottom of the header tank, and
the bottom of the firewall fuel filter (Fig. 2-2).
Also provided are two fuel vent drains, located
on each side of fuselage under the wings.
2-10
Page Effective 03/26/2010
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
All fuel drains should be drained prior to the
first flight of the day. Drain a small quantity of
fuel into a transparent container to permit
inspection for the presence of moisture,
sediment or othere contaminants. If there is
any indication of contamination, the fuel
should be drained until all evidence of
contamination disappears.
CAUTION
Visually check that all drain
valves are closed after draining.
FUEL SYSTEM SCREENS:
(Ref. Fig. 2-2)
The airframe is equipped with five fuel
screens: 1/12 inch mesh finger strainers
in each wing tank outlet and a ¼ inch
mesh finger strainer installed in the outlet
fitting from the header tank. Inspect the
finger strainers annually or if the fuel
system is thought to have been or is
known to be contaminated with foreign
debris: i.e. moisture, debris or other
contaminants are noted in drained fuel
sample container, fuel source is known to
be contaminated etc.
REI NS T AL L T HE 2 5 FIREWA LL
MOUNTED FUEL FILTER:
(Ref. Fig. 2-2)
The main fuel filter
inspected, cleaned and reinstalled every
100 hours, or any time fuel system
contamination is suspected. Refer to
Section 5 for main fuel filter servicing
procedures.
Figure 2-2: FUEL SYSTEM
screen should be
(below)
Effective: 03/26/2010 Page
2-11
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
WARNING
IF THE RED FUEL BYPASS
INDICATOR BUTTON HAS
POPPED OUT, INVESTIGATE
AND REMOVE THE CAUSE
OF THE FUEL OBSTRUCTION
BEFORE FURTHER FLIGHT.
REMOVE, INSPECT, CLEAN
OR REPLACE AND MICRON
FILTER ELEMENT. YOU MAY
THEN RESET THE RED
BYPASS BUTTON BY
PRESSING IT IN WITH
FINGER PRESSURE.
DEFUELING
During the defueling operation, jet fuel
fumes are present; therefore, extreme
caution must be exercised to prevent fire
hazards. To defuel the aircraft, use the
following procedure.
SMOKING ON OR AROUND
THE AIRCRAFT IS NOT
PERMITTED AT ANY TIME.
AIRCRAFT AND EQUIPMENT
GROUNDING PROCEDURES
MUST BE STRICTLY
ADHERED TO. FIRE
EXTINGUISHING EQUIPMENT
MUST BE IMMEDIATELY
AVAILABLE.
a. Ground aircraft to a proper ground
point and all defueling equipment or
containers to the aircraft.
b. Place a vented container of adequate
capacity under each of the three drain
points (header tank and two aft
inboard wings). Verify that the
containers are properly grounded to
the aircraft.
c. Open the drain valves and allow all
fuel to drain. When tanks are empty,
close the drain valves and move the
WARNING
fuel containers a safe distance from
the aircraft.
d. Verify that all the drain valves are
closed.
LANDING GEAR, WHEELS &
BRAKES
Reference Section 6
Check all gear assemblies for general
cleanliness, security of mounting, and
hydraulic leaks at prescribed inspection
intervals. Lubricate all lubrication points on
main and tail gear assemblies at
prescribed intervals.
TIRES
Tires should be inspected for proper
inflation, breaks, cuts, and foreign objects
in tread, flat spots and exposed cord.
Replace tire if there is any question of its
reliability. Proper inflation is necessary for
maximum tire life. Maintain 29x11-10 ply
rated main tire and tube pressure at a
minimum of 40 psi to a maximum of 62 psi,
depending on the load and runway
conditions. The 12.5 x 4.5-10 ply rated tail
wheel tire and tube pressure should be 55
psi maximum. The wheels and tires are
balanced assemblies. If tires are
suspected of being out of balance, they
may be balanced on automotive type
balancing equipment. If aircraft is out of
service, move the aircraft to rotate tires
every seven days to prevent flat spots from
developing.
MLG SHOCK STRUTS
Main landing gear shock struts are to be
inspected at the specified intervals. At
least annually they must be removed from
the aircraft, disassembled, cleaned and
inspected. Shock “biscuits” should be
replaced every 1000 hours or if they
develop cracks. Reinstall shock struts with
new hardware
2-12
Page Effective 03/26/2010
THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
BRAKE BLEEDING
Brake bleeding should be performed when
air is suspected of being entrapped in
brake lines. See Section 3 for brake
bleeding procedures.
INSPECTION
In Table 2-2 (next page), items to be
inspected and the maximum inspection
intervals are listed. Details of how to
check or what to look for are common
knowledge to licensed mechanics, but are
described generally below. Specific
checks can be found in relevant sections
of this manual.
INSPECTION CHECK LIST
Ref. Figure 2-3
GENERAL INSTRUCTIONS
a. Movable parts are to be checked for
lubrication, servicing, security of
attachment, binding, excessive wear,
safety, proper operation, proper
adjustment, correct travel, cracked
fittings, security of hinges, defective
bearings, cleanliness, corrosion,
deformation, sealing, and tension.
b. Fluid lines and hoses are to be
checked for leaks, cracks, dents,
kinks, chafing, proper bend radius,
security, corrosion, deterioration,
obstructions, and foreign matter.
c. Metal parts are to be checked for
security of attachment, cracks, and
metal distortion, broken spot welds,
corrosion, condition of paint, and any
other apparent damage.
d. Wiring is to be checked for security,
chafing, burning, defective insulation,
and loose or broken terminals, heat
deterioration, and corroded terminals.
e. Bolts in critical areas are to be
checked for correct torque, or when
visual inspection indicates the need for
a torque check. See Table 2-3, Torque
Chart.
f. Filters, screens, and fluids are to be
checked for cleanliness, contamination
and/or need of replacement at
specified intervals.
This Manual contains information on
aircraft systems and operating procedures
required for safe and effective
maintenance. It shall not be used as a
substitute for sound judgment.
*NOTE*
Certain chemicals cannot be
removed effectively by detergent
solutions. Special cleaning agents
are available for that purpose. It is
suggested that the chemical
suppliers be contacted for cleaning
agents that are suitable for those
special needs.
Inspection intervals are greatly influenced
by particular operational priorities,
operating conditions, environment, and
routine inspection results.
Perform the tasks shown in the following
Inspection Chart at the prescribed
intervals, or more often if necessary.
Effective: 03/26/2010 Page 2-13
Loading...