THRUSH S2R - G10 User manual

Effective: 03/26/2010 page i
AIRCRAFT MAINTENANCE
MANUAL
SINGLE COCKPIT AND DUAL COCKPIT
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: [phone]
Fax: [phone]

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.
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AIRCRAFT MAINTENANCE MANUAL
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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

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AIRCRAFT MAINTENANCE MANUAL
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SECTION 1
GENERAL
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SERVICING &
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SECTION 3
HYDRAULICS
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POWERPLANT &
PROPELLER
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SECTION 5
FUEL SYSTEM
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AIRCRAFT MAINTENANCE MANUAL
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SECTION 5
FUEL SYSTEM
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SECTION 6
LANDING GEAR,
WHEELS &
BRAKES
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SECTION 7
FLIGHT
CONTROLS
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FLIGHT
CONTROLS
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SECTION 8
INSTRUMENTS
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THRUSH AIRCRAFT INC. – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
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SECTION 9
DISPERSAL
SYSTEMS
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ELECTRICAL
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SECTION 11
AIRWORTHINESS
LIMITATIONS
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THRUSH AIRCRAFT INC. – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
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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
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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 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 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................................. Forward Limit at 6,000 pounds is 26.5
inches aft of datum. It is 24.0 at 4,000
pounds with straight line variation between.
Aft Limit ......................................... Aft Limit at all weights is 30.0 inches aft of
datum
Datum............................................ Datum Is The Leading Edge Of The Wing.
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
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THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
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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.

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
1-4
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
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 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
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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
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THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
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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
switch located on the left side of the
cockpit. The rudder controls are inter-
connected by springs to the aileron system
so that a wing may be lifted with the rudder
alone. INSTRUMENTS
The standard instruments are located on
three separate panels: An upper panel, a
left panel, and a right panel. The left panel
contains a clock, oil temperature, hour
meter, fuel pressure, oil pressure, torque
gauge and fuel quantity gauges. The right
panel contains a voltmeter, ammeter, and
circuit breakers. The upper panel contains
propeller tachometer and a standard flight
instrument package.
ELECTRICAL SYSTEM
The standard 28 volts 250 amp electrical
system consists of the generating and
starting system, the wiper/washer system,
the navigation lights and the strobe lights.
The navigation lights, strobe lights, landing
lights, working lights and the air conditioner
system are optional. The electrical system
obtains power from dual 28-volt batteries
and one a starter-generator. An external
power receptacle is standard equipment
and may be used for connecting a 28-volt
ground power unit to the aircraft for engine
starting or maintenance. The ground start
system utilizes the master relay so that
starting is accomplished by engaging the
starter switch.
AIRCRAFT WEIGHT & BALANCE
Refer to S2R-G10 Flight Manual for
detailed aircraft weight and balance
information.

THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
Figure 1-1: Aircraft 3-view
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THRUSH AIRCRAFT, INC – MODEL S2R-G10
AIRCRAFT MAINTENANCE MANUAL
Figure 1-2: Aircraft Stations
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AIRCRAFT MAINTENANCE MANUAL
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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
Page 2-2 Effective 03/26/2010
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

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.
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.
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.
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
2-3
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