Thrush Aircraft S2R-R1340 User manual

THRUSH AIRCRAFT INC – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
Effective: 01/01/2008 i
THRUSH AIRCRAFT INC.
AIRCRAFT MAINTENANCE MANUAL
SINGLE COCKPIT AND DUAL COCKPIT
Model S2R – R1340
Serial Numbers S2R-R1340 S/N 036 & up
Issued January 1, 2008
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: [phone]
Fax: [phone]

THRUSH AIRCRAFT INC – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
INTRODUCTION
This publication provides information for the Thrush Aircraft, Inc. Model S2R-R1340 Thrush
600 aircraft. Installations or equipment will vary from model to model 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:
-- Indicates a strong possibility of severe personal injury or loss of life if
instructions are not followed.
WARNING
-- Indicates a possibility of personal injury or equipment damage if
instructions are not followed.
CAUTION
* 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 done or of the possible
hazardous consequences of each conceivable way, 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.
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
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SECTION 3..................................................HYDRAULICS
SECTION 4.................................................. POWER PLANT 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

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SECTION 1
GENERAL
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SERVICING &
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SECTION 3
HYDRAULICS
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SECTION 4
POWERPLANT &
PROPELLER
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AIRCRAFT MAINTENANCE MANUAL
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SECTION 4
POWERPLANT &
PROPELLER
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SECTION 5
FUEL SYSTEM
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SECTION 6
LANDING GEAR,
WHEELS & BRAKES
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SECTION 6
LANDING GEAR,
WHEELS & BRAKES
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SECTION 7
FLIGHT CONTROLS
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INSTRUMENTS
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AIRCRAFT MAINTENANCE MANUAL
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INSTRUMENTS
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SECTION 9
DISPERSAL SYSTEMS
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SECTION 10
ELECTRICAL
SYSTEM
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SECTION 11
AIRWORTHINESS
LIMITATIONS
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THRUSH AIRCRAFT INC – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
Effective: 01/01/2008 vii
LOG OF REVISIONS
Rev.
No. Pages Description of Revisions Eng’rg Approval FAA Accepted
NC All New Manual 1/1/08 Oct. 17,
2008

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AIRCRAFT MAINTENANCE MANUAL
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THRUSH AIRCRAFT, INC – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
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SECTION 1
GENERAL INFORMATION
TABLE OF CONTENTS
GENERAL DESCRIPTION................................................................................................2
CONTACT INFORMATION.....................................................................................2
PRINCIPAL DIMENSIONS ................................................................................................2
GENERAL.....................................................................................................................2
WEIGHT & BALANCE ..................................................................................................2
WING............................................................................................................................3
HORIZONTAL STABILIZER AND ELEVATORS ..........................................................3
VERTICAL STABILIZER AND RUDDER......................................................................3
AREAS..........................................................................................................................3
SUPPLIER FURNISHED COMPONENT MANUALS....................................................4
AIRCRAFT STRUCTURE..................................................................................................4
FUSELAGE...................................................................................................................4
WING............................................................................................................................4
EMPENNAGE...............................................................................................................5
COCKPIT......................................................................................................................5
AIRCRAFT SYSTEMS.......................................................................................................5
HYDRAULIC SYSTEMS...............................................................................................5
POWER PLANT & PROPELLER..................................................................................5
FUEL SYSTEM.............................................................................................................5
LANDING GEAR, WHEELS & BRAKES.......................................................................6
FLIGHT CONTROLS....................................................................................................6
INSTRUMENTS............................................................................................................7
ELECTRICAL SYSTEM................................................................................................7
AIRCRAFT WEIGHT & BALANCE................................................................................7
Figure 1-1: Aircraft 3-view.....................................................................................8
Figure 1-2: Aircraft Stations .................................................................................9

THRUSH AIRCRAFT, INC – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
1-2 Effective: 01/01/08
GENERAL DESCRIPTION
The Thrush Aircraft Inc Thrush S2R-R1340 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-R1340 is designed for the highest
crash load factors in the industry. Safety and reliability 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 [phone] extension 341.
PRINCIPAL DIMENSIONS
GENERAL
Wing Span 44.87 feet
Overall Length 30.29 feet
Height To Top Of
Canopy 9.34 feet
Main Gear Tread 8.58 feet
Main Gear To Tail
Wheel 19.26 feet
WEIGHT & BALANCE
C. G. Range (See Airplane Flight Manual for pertinent data)
Forward Limit Forward Limit at 7860 pounds and below
is 22.5 inches aft of datum.
Aft Limit Aft Limit at 7860 pounds and below is 30.0
inches aft of datum
Datum Datum Is The Leading Edge Of The Wing.

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AIRCRAFT MAINTENANCE MANUAL
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WING
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
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 24 Degrees ±1 Degree Left and Right
AREAS
Wing 336.53 Square Feet
Aileron (Each) 23.40 Square Feet
Flaps (Each) 15.30 Square Feet
Stabilizer 39.30 Square Feet
Elevators 20.40 Square Feet
Elevator Tabs (Each) 1.30 Square Feet
Vertical Fin 9.43 Square Feet
Rudder 12.22 Square Feet

THRUSH AIRCRAFT, INC – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
1-4 Effective: 01/01/08
SUPPLIER FURNISHED COMPONENT MANUALS
COMPONENT MANUAL PART #
R1340 AN1 Maintenance Manual 118611
R1340 AN1 Parts Manual N/A
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.
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 heat-
treated 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

THRUSH AIRCRAFT, INC – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
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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-
R1340 (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 welded 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
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 SYSTEMS
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-R1340 is powered by the
Pratt & Whitney R1340–AN1, –S3H1 or –
S1H1 nine-cylinder supercharged Wasp
radial engine. The propeller is a constant
speed Hamilton Standard 12D40 hub with
all metal 6101-12 or EAC AG-100-2
blades.
This combination provides takeoff power of
600 BHP at 2250 RPM. The engine mount
is a welded chrome-moly tube truss, stress
relieved after welding. The engine is
attached to the mount through rubber
vibration isolators.
Accessibility for servicing and inspection in
the engine compartment is exceptional. A
large access door is provided on the left
side, and cowl panels are easily removed
for full access.
FUEL SYSTEM
A 133-gallon (useable) fuel supply is
available for the Thrush S2R-R1340.
Sixty-eight 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.

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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
carburetor. A separate electrically actuated
primer pump injects fuel directly into the air
intakes of the top five cylinders to facilitate
engine starting.
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
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 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
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

THRUSH AIRCRAFT, INC – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
Effective: 01/01/08 1-7
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 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 24 volts and 50 amp (70 for
dual control version) electrical system
consists of the 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 a single 24-volt battery and
one alternator. An external power
receptacle is standard equipment and may
be used for connecting a 24-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-R1340 Flight Manual for
detailed aircraft weight and balance
information.

THRUSH AIRCRAFT, INC – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
1-8 Effective: 01/01/08
Figure 1-1: Aircraft 3-view

THRUSH AIRCRAFT, INC – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
Effective: 01/01/08 1-9
Figure 1-2: Aircraft Stations

THRUSH AIRCRAFT, INC – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
1-10 Effective: 01/01/08
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THRUSH AIRCRAFT, INC – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
Effective: 01/01/08 2-1
SECTION 2
SERVICING & INSPECTION
TABLE OF CONTENTS
SERVICING & INSPECTION..........................................................................................3
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...........................................................................................................4
Calculated Weight...........................................................................................4
Weighing the Airplane.....................................................................................5
COLD WEATHER OPERATION.....................................................................................5
COLD WEATHER MAINTENANCE HINTS ...............................................................6
GROUND EMERGENCY PROCEDURES...................................................................... 6
ENGINE FIRES....................................................................................................6
ELECTRICAL FIRES............................................................................................6
GROUND OPERATION OF ENGINE ............................................................................. 6
EXTERIOR PRE-START CHECK ........................................................................7
PRE-START CHECKLIST....................................................................................7
COCKPIT PRE-START CHECK...........................................................................7
STARTING ENGINE.............................................................................................7
ENGINE OPERATIONAL CHECKS...........................................................................8
SYSTEM AND COMPONENT SERVICING.................................................................... 9
HYDRAULIC SYSTEM ..............................................................................................9
ENGINE OIL SYSTEM...............................................................................................9
ENGINE AIR INDUCTION AND FILTER CLEANING..............................................10
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
ENGINE DEPRESERVATION.................................................................................13
ENGINE PRESERVATION PROCEDURE......................................................... 13
Table 2-1: ENGINE PRESERVATION PROCEDURES.................................... 14

THRUSH AIRCRAFT, INC – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
2-2 Effective 1/1/08
INSPECTION.................................................................................................................22
INSPECTION CHECK LIST.....................................................................................22
GENERAL INSTRUCTIONS...............................................................................22
Figure 2-3: R1340 Servicing and Inspection Guide.......................................22
Table 2-2: INSPECTION CHECK LIST...................................................................23
A: PROPELLER................................................................................................23
B: ENGINE EXTERNALS..................................................................................23
C: ENGINE OIL SYSTEM..................................................................................24
D: ENGINE FUEL SYSTEM ..............................................................................25
E: AIR INDUCTION SYSTEM............................................................................25
F: AIRFRAME FUEL SYSTEM..........................................................................26
G: IGNITION SYSTEM......................................................................................27
H: MAIN LANDING GEAR ................................................................................27
J: HYDRAULIC SYSTEM..................................................................................28
K: TAIL GEAR...................................................................................................28
L: FUSELAGE SKINS.......................................................................................30
M: HOPPER ......................................................................................................30
N: WINGS..........................................................................................................30
P: FUSELAGE FRAME.....................................................................................31
Q: CONTROL SYSTEMS..................................................................................32
R: EMPENNAGE...............................................................................................33
S: AILERONS AND FLAPS ..............................................................................33
T: COCKPIT ......................................................................................................34
U: ELECTRICAL SYSTEM................................................................................34
BATTERY MAINTENANCE......................................................................................35
AIRFRAME MAINTENANCE........................................................................................35
CORROSION CONTROL.........................................................................................35
WINDSHIELD...........................................................................................................36
HOPPER REPAIR....................................................................................................36
FUEL TANK REPAIR...............................................................................................36
Table 2-3: TORQUE CHART ..................................................................................37
LUBRICATION..............................................................................................................38
Figure 2-4: Lubrication Chart (9 pages)...........................................................38