Thrush Aircraft S2R-T660 Maintenance Manual

THRUSH AIRCRAFT INC - T660 TURBO THRUSH

AIRCRAFT MAINTENANCE MANUAL

Effective: 01/10/05 i

THRUSH AIRCRAFT INC.

TURBO THRUSH

AIRCRAFT MAINTENANCE MANUAL

Model S2R – T660

Serial Numbers T660 – 109 & Up

Manual Number: T660 -3

Issued December 17, 2003

Revised January 10, 2005

Note:

All serial numbers with the DC suffix indicate the dual cockpit configuration.

Manufacturer’s Serial Number:_____________________________________________

Registration Number:____________________________________________________

THRUSH AIRCRAFT INC - T660 TURBO THRUSH

AIRCRAFT MAINTENANCE MANUAL

Effective: 01/10/05 ii

Page

LOG OF PAGES

Date Page

Date

i …………………………… 01/10/05 SECTION II

(

CONT’D

)

ii …………………………… 01/10/05 SERVICING

iii …………………………… 01/10/05 34 ……………………………. 12/17/03

iv …………………………… 01/10/05 35 ……………………………. 12/17/03

v ……………………………. 12/17/03 36 ……………………………

.

12/17/03

vi ……………………………. 01/10/05 37 ……………………………

.

12/17/03

vii ……………………………. 12/17/03 38 ……………………………. 12/17/03

SECTION I 39 ……………………………. 12/17/03

GENERAL INFORMATION 40 ……………………………. 12/17/03

1 ……………………………. 12/17/03 41 ……………………………. 12/17/03

2 ……………………………. 12/17/03 42 ……………………………. 12/17/03

3 ……………………………. 12/17/03 43 ……………………………. 12/17/03

4 ……………………………. 12/17/03 44 ……………………………. 12/17/03

5 ……………………………. 12/17/03 45 ……………………………. 12/17/03

6 ……………………………. 01/10/05 46 ……………………………. 12/17/03

7 ……………………………. 12/17/03 47 ……………………………. 12/17/03

8 ……………………………. 12/17/03 48 ……………………………. 12/17/03

9 ……………………………. 12/17/03 49 ……………………………. 12/17/03

10 ……………………………. 12/17/03 50 ……………………………. 12/17/03

11 ……………………………. 12/17/03 51 ……………………………. 12/17/03

SECTION II 52 ……………………………. 01/10/05

SERVICING 53 ……………………………. 12/17/03

1 ……………………………. 12/17/03

2 ……………………………. 12/17/03 SECTION III

3 ……………………………. 12/17/03 HYDRAULICS

4 ……………………………. 12/17/03 1 ……………………………. 12/17/03

5 ……………………………. 12/17/03 2 ……………………………. 12/17/03

6 ……………………………. 12/17/03 SECTION IV

7 ……………………………. 12/17/03 POWERPLANT &

8 ……………………………. 12/17/03 PROPELLER

9 ……………………………. 12/17/03 1 ……………………………. 12/17/03

10 ……………………………. 12/17/03 2 ……………………………. 09/02/04

11 ……………………………. 12/17/03 3 ……………………………. 12/17/03

12 ……………………………. 12/17/03 4 ……………………………. 12/17/03

13 ……………………………. 12/17/03 5 ……………………………. 12/17/03

14 ……………………………. 12/17/03 6 ……………………………. 12/17/03

15 ……………………………. 12/17/03 7 ……………………………. 12/17/03

16 ……………………………. 12/17/03 8 ……………………………. 12/17/03

17 ……………………………. 12/17/03 9 ……………………………. 12/17/03

18 ……………………………. 12/17/03 10 ……………………………. 12/17/03

19 ……………………………. 01/10/05 11 ……………………………. 12/17/03

20 ……………………………. 01/10/05 12 ……………………………. 12/17/03

21 ……………………………. 12/17/03 13 ……………………………. 12/17/03

22 ……………………………. 12/17/03 14 ……………………………. 12/17/03

23 ……………………………. 12/17/03 15 ……………………………. 12/17/03

24 ……………………………. 01/10/05 16 ……………………………. 12/17/03

25 ……………………………. 12/17/03 17 ……………………………. 12/17/03

26 ……………………………. 12/17/03 18 ……………………………. 12/17/03

27 ……………………………. 12/17/03 19 ……………………………. 12/17/03

28 ……………………………. 12/17/03 20 ……………………………. 12/17/03

29 ……………………………. 12/17/03 21 ……………………………. 12/17/03

30 ……………………………. 12/17/03 22 ……………………………. 12/17/03

31 ……………………………. 12/17/03 23 ……………………………. 12/17/03

32 ……………………………. 12/17/03 24 ……………………………. 12/17/03

33 ……………………………. 12/17/03 25 ……………………………. 01/10/05

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Page LOG OF PAGES

Date Page Date

SECTION IV

POWER PLANT &

PROPELLER

8

SECTION VI (CONT’D)

LANDING GEAR

……………………………. 12/17/03

26 ……………………………. 01/10/05 9 ……………………………. 12/17/03

27 ……………………………. 12/17/03 10 ……………………………. 12/17/03

28 ……………………………. 12/17/03 11 ……………………………. 12/17/03

29 ……………………………. 12/17/03 12 ……………………………. 12/17/03

30 ……………………………. 12/17/03 13 ……………………………. 12/17/03

31 ……………………………. 12/17/03 14 ……………………………. 12/17/03

32 ……………………………. 01/10/05 15 ……………………………. 12/17/03

33 ……………………………. 12/17/03 16 ……………………………. 12/17/03

34 …………………………… 12/17/03 17 …………………………… 12/17/03

35 …………………………… 12/17/03 18 …………………………… 12/17/03

36 …………………………… 01/10/05 19 …………………………… 01/10/05

37 …………………………… 12/17/03 19a …………………………… 01/10/05

38 …………………………… 12/17/03 20 …………………………… 12/17/03

39 …………………………… 12/17/03 21 …………………………… 12/17/03

40 …………………………… 12/17/03 22 …………………………… 12/17/03

41 ……………………………. 12/17/03 23 …………………………… 12/17/03

42 ……………………………. 12/17/03 SECTION VII

43 ……………………………. 12/17/03 FLIGHT CONTROLS

44 ……………………………. 12/17/03 1 ……………………………. 12/17/03

45 ……………………………. 12/17/03 2 ……………………………. 12/17/03

SECTION V 3 ……………………………. 01/10/05

FUEL SYSTEM 4 ……………………………. 12/17/03

1 ……………………………. 12/17/03 5 ……………………………. 12/17/03

2 ……………………………. 12/17/03 6 ……………………………. 12/17/03

3 ……………………………. 12/17/03 7 ……………………………. 12/17/03

4 ……………………………. 12/17/03 8 ……………………………. 12/17/03

5 ……………………………. 12/17/03 9 ……………………………. 12/17/03

6 …………………………… 12/17/03 10 ……………………………. 12/17/03

7 …………………………… 12/17/03 11 ……………………………. 12/17/03

8 ……………………………. 12/17/03 12 ……………………………. 12/17/03

9 ……………………………. 01/10/05 13 ……………………………. 01/10/05

10 ……………………………. 12/17/03 14 ……………………………. 01/10/05

11 ……………………………. 01/10/05 15 ……………………………. 12/17/03

12 ……………………………. 12/17/03 16 ……………………………. 12/17/03

13 ……………………………. 12/17/03 17 ……………………………. 12/17/03

14 ……………………………. 12/17/03 18 ……………………………. 12/17/03

15 ……………………………. 12/17/03 19 ……………………………. 12/17/03

16 ……………………………. 12/17/03 20 ……………………………. 12/17/03

17 ……………………………. 12/17/03 21 ……………………………. 12/17/03

18 ……………………………. 12/17/03 22 ……………………………. 12/17/03

19 ……………………………. 12/17/03 23 ……………………………. 12/17/03

20 ……………………………. 12/17/03 24 ……………………………. 12/17/03

SECTION VI 25 ……………………………. 12/17/03

LANDING GEAR 26 ……………………………. 12/17/03

1 ……………………………. 01/10/05 27 ……………………………. 12/17/03

2 ……………………………. 12/17/03 28 ……………………………. 12/17/03

3 ……………………………. 01/10/05 29 ……………………………. 12/17/03

4 …………………………… 01/10/05 30 ……………………………. 12/17/03

5 ……………………………... 01/10/05 31 ……………………………. 12/17/03

6 …………………………… 01/10/05 32 …………………………… 12/17/03

6a …………………………….. 01/10/05 33 ……………………………. 12/17/03

7 ……………………………. 12

/

17/03 34 ……………………………. 12/17/03

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AIRCRAFT MAINTENANCE MANUAL

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Page Date Page Date

SECTION VII (CONT’D)

FLIGHT CONTROLS SECTION X (CONT’D)

ELECTRICAL

35 ……………………………. 12/17/03 3 ……………………………. 12/17/03

36 ……………………………. 01/10/05 4 ……………………………. 12/17/03

37 ……………………………. 12/17/03 5 ……………………………. 12/17/03

38 ……………………………. 12/17/03 6 ……………………………. 12/17/03

39 ……………………………. 12/17/03 7 ……………………………. 12/17/03

40 …………………………… 01/10/05 8 ……………………………. 12/17/03

41 …………………………… 01/10/05 9 ……………………………. 12/17/03

SECTION VIII 10 ……………………………. 12/17/03

INSTRUMENTS 11 ……………………………. 12/17/03

1 ……………………………. 12/17/03 12 ……………………………. 12/17/03

2 ……………………………. 12/17/03 13 ……………………………. 12/17/03

3 ……………………………. 12/17/03 14 ……………………………. 12/17/03

4 ……………………………. 12/17/03 15 ……………………………. 12/17/03

5 ……………………………. 12/17/03 16 ……………………………. 12/17/03

6 ……………………………. 12/17/03 17 ……………………………. 12/17/03

7 ……………………………. 12/17/03 18 ……………………………. 12/17/03

8 ……………………………. 12/17/03 19 ……………………………. 12/17/03

9 ……………………………. 12/17/03 20 ……………………………. 12/17/03

10 ……………………………. 12/17/03 21 ……………………………. 12/17/03

11 ……………………………. 12/17/03 22 ……………………………. 12/17/03

12 ……………………………. 12/17/03 23 ……………………………. 12/17/03

13 ……………………………. 12/17/03 24 ……………………………. 12/17/03

14 ……………………………. 12/17/03 25 ……………………………. 12/17/03

15 ……………………………. 12/17/03 26 ……………………………. 12/17/03

16 ……………………………. 12/17/03 27 ……………………………. 12/17/03

17 ……………………………. 12/17/03 28 ……………………………. 12/17/03

18 ……………………………. 12/17/03 29 ……………………………. 12/17/03

19 ……………………………. 12/17/03 30 ……………………………. 12/17/03

20 ……………………………. 12/17/03 31 ……………………………. 12/17/03

21 ……………………………. 12/17/03 32 ……………………………. 12/17/03

22 ……………………………. 12/17/03 33 ……………………………. 12/17/03

23 ……………………………. 12/17/03 34 ……………………………. 12/17/03

24 ……………………………. 12/17/03 35 ……………………………. 12/17/03

25 ……………………………. 12/17/03 36 ……………………………. 12/17/03

26 ……………………………. 12/17/03 37 ……………………………. 12/17/03

SECTION IX 38 ……………………………. 12/17/03

DISPERSAL SYSTEMS 39 ……………………………. 12/17/03

1 ……………………………. 12/17/03 40 ……………………………. 12/17/03

2 ……………………………. 12/17/03 41 ……………………………. 12/17/03

3 ……………………………. 12/17/03 42 ……………………………. 12/17/03

4 ……………………………. 12/17/03 43 ……………………………. 12/17/03

5 ……………………………. 12/17/03 44 ……………………………. 12/17/03

6 ……………………………. 12/17/03 45 ……………………………. 12/17/03

7 ……………………………. 12/17/03 46 ……………………………. 12/17/03

8 ……………………………. 12/17/03 47 ……………………………. 12/17/03

9 ……………………………. 12/17/03 48 ……………………………. 12/17/03

10 ……………………………. 12/17/03 49 ……………………………. 12/17/03

11 ……………………………. 12/17/03 50 ……………………………. 12/17/03

12 ……………………………. 12/17/03 51 ……………………………. 12/17/03

SECTION X 52 ……………………………. 12/17/03

ELECTRICAL 53 ……………………………. 12/17/03

1 ……………………………. 12/17/03

THRUSH AIRCRAFT INC - T660 TURBO THRUSH

AIRCRAFT MAINTENANCE MANUAL

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LOG OF PAGES

Page Date

SECTION X (CONT’D)

ELECTRICAL

54 ……………………………. 12/17/03

55 …………………………… 12/17/03

56 …………………………… 12/17/03

SECTION XI

LIMITATIONS

1 …………………………… 12/17/03

2 …………………………… 01/10/05

THRUSH AIRCRAFT INC - T660 TURBO THRUSH

AIRCRAFT MAINTENANCE MANUAL

Effective: 12/17/03 vii

INTRODUCTION

This publication provides information for the Thrush Aircraft, Inc. Model S2RT660

Turbo Thrush 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:

*** 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.

CAUTION: 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 himself 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. We reserve the right to make changes at any time

without notice.

THRUSH AIRCRAFT INC – T660 TURBO THRUSH

AIRCRAFT MAINTENANCE MANUAL

Section 1

GENERAL INFORMATION

TABLE OF CONTENTS

SECTION ONE.................................................................................................................................1

GENERAL INFORMATION..............................................................................................................2

GENERAL DESCRIPTION...........................................................................................................2

PRINCIPAL DIMENSIONS...........................................................................................................2

GENERAL .................................................................................................................................2

WING.........................................................................................................................................3

HORIZONTAL STABILIZER AND ELEVATORS......................................................................3

VERTICAL STABILIZER AND RUDDER..................................................................................3

AREAS ......................................................................................................................................4

SUPPLIER FURNISHED COMPONENT MANUALS................................................................4

AIRCRAFT STRUCTURES ..........................................................................................................4

FUSELAGE ...............................................................................................................................4

CENTER SECTION...................................................................................................................5

WING.........................................................................................................................................5

EMPENNAGE............................................................................................................................5

COCKPIT...................................................................................................................................6

AIRCRAFT SYSTEMS..................................................................................................................6

HYDRAULIC SYSTEMS ...........................................................................................................6

POWER PLANT & PROPELLER..............................................................................................6

FUEL SYSTEM .........................................................................................................................7

LANDING GEAR, WHEELS & BRAKES...................................................................................8

FLIGHT CONTROLS.................................................................................................................8

INSTRUMENTS ........................................................................................................................8

ELECTRICAL SYSTEM ............................................................................................................9

AIRCRAFT WEIGHT & BALANCE............................................................................................9

FIGURE 1-1 ................................................................................................................................10

FIGURE 1-2 ................................................................................................................................11

Effective: 12/17/03 1 - 1

THRUSH AIRCRAFT INC – T660 TURBO THRUSH

AIRCRAFT MAINTENANCE MANUAL

GENERAL INFORMATION

SECTION ONE

GENERAL DESCRIPTION

The Thrush Aircraft Inc Turbo Thrush 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 all structural integrity, flight safety, and minimum maintenance

requirements. The Turbo Thrush 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, is 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.

PRINCIPAL DIMENSIONS

GENERAL

Wing Span Extended Tip 648.0 Inches (54’.00”)

Overall Length 432.9 inches (36' 0.91")

Height To Top Of Canopy 126.0 inches (10' 6.00")

Main Gear Tread 108.7 inches (9' 0.74")

Main Gear To Tail Wheel 274.20 inches (22' 10.20")

Empty Weight Equipped 6,100 pounds minimum

Maximum Weight 14,150 pounds with liquid dispersal equipment installed

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THRUSH AIRCRAFT INC – T660 TURBO THRUSH

AIRCRAFT MAINTENANCE MANUAL

WING

Type Full Cantilever

Airfoil Section Naca 4412

Dihedral 3.50 Degrees

C. G. Range (See Airplane Flight Manual for pertinent data)

-Fwd Limit 24.5 Inches Aft Of Datum

-Aft Limit 30.0 Inches Aft Of Datum

(Datum Is The Leading Edge Of The Wing.)

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

Rudder Travel 22 Degrees ±1 Degree

Rudder Trim Tab Travel 0 Degrees to Max 8.6 Degrees Trailing Edge

Left

1 – 3 Effective: 12/17/03

THRUSH AIRCRAFT INC – T660 TURBO THRUSH

AIRCRAFT MAINTENANCE MANUAL

AREAS

Wing 405.0 Square Feet

Aileron (Each) 23.40 Square Feet

Flaps (Each) 26.70 Square Feet

Stabilizer 39.30 Square Feet

Elevators 20.40 Square Feet

Elevator Tabs (Each) 1.30 Square Feet

Fin 10.59 Square Feet on T660-109 and subsequent

Rudder 15.55 Square Feet on T660-109 and subsequent

SUPPLIER FURNISHED COMPONENT MANUALS

MANUAL PART #

PT6A-67AG Maintenance Manual

Vol. I & II 3036132

Parts Manual 3036134

PT6A-60AG Maintenance Manual

Vol. I & II 3034342

Parts Manual 3034344

THIS SPACE INTENTIONALLY LEFT BLANK.

PT6A-45A, PT6A-45B, PT6A-

45R

Maintenance Manual

Vol I & II 3027042

Parts Manual 3027044

Propeller (B5P10120S) Owner’s Manual 139

AIRCRAFT STRUCTURES

FUSELAGE

The fuselage comprises a welded tubular steel frame, fiberglass hopper, and detachable skins. An

overturn structure forms an integral part of the fuselage frame. The frame structure, fittings,

bushings, brackets, and so forth are fabricated from 4130 chrome-moly seamless steel tubing.

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 1/2 gallons drain out, leaving a

residual 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

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THRUSH AIRCRAFT INC – T660 TURBO THRUSH

AIRCRAFT MAINTENANCE MANUAL

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. The seams and lap joints of the skin panel support structure are sealed with a special

compound to eliminate chemical action between the mating surfaces. Each skin panel is etched,

primed, and painted before assembly to insure complete coverage. All lower 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.

CENTER SECTION

The Center Section is a constant chord of 90 inches, all metal, and full cantilever design. The

massive main spar is of a one piece design of high strength heat treated steel and machined to

reduce weight. The spar is cad plated, primed and painted. All metal skins and ribs are constructed

from Alclad heat-treated aluminum material. The unit attaches to the fuselage and supports the

wings. WING

The wing is a constant chord of 90 inches, all metal, and 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. For the Model

S2R-T660, the outer wing panel detaches from the center wing panel by removal of four bolts.

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.

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THRUSH AIRCRAFT INC – T660 TURBO THRUSH

AIRCRAFT MAINTENANCE MANUAL

COCKPIT

The overturn structure 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 lowered. 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 is enclosed in a stainless steel frame. The windshield side

panels are Plexiglas and are curved to provide streamlining.

AIRCRAFT SYSTEMS

HYDRAULIC SYSTEMS

The hydraulic system consists of two master cylinders and hydraulic brake lines connecting the

master cylinders to the wheel brake cylinders. Applying toe pressure on the rudder pedals actuates

the master cylinders, which are located just aft of the pilot’s rudder pedals. A small reservoir is

incorporated within each master cylinder to supply the system with brake fluid.

R1

POWER PLANT & PROPELLER

(Refer to manuals listed in Chart on Page 1-4 in this Section.)

The S2R-T660 Turbo Thrush is powered by the PT6, a lightweight free turbine engine incorporating

a reverse flow combustion path, is designed for aircraft propulsion use. It utilizes two counter

rotating turbine sections. One drives the compressor, and the other drives the propeller through a

reduction gearbox. The latter turbine is "free" or independent of the compressor turbine. More

recent and higher-powered models incorporate a two-stage free turbine. The PT6 has been

produced in several models and has been adapted to a multitude of uses.

The propeller has five blades mounted on a hollow hub in the front end of which is a servo-piston

that moves forward under servo-oil pressure or rearward under feather return spring pressure.

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THRUSH AIRCRAFT INC – T660 TURBO THRUSH

AIRCRAFT MAINTENANCE MANUAL

There are five links from the servo-piston. One goes to each blade root, and these links transmit

forward motion of the servo-piston to the blade roots and pivot the blades in the decrease pitch

direction. When servo-piston pressure is relieved, the servo-piston moves rearward under feather

return spring pressure and pivots the blades in the increase pitch direction. This action is assisted

by centrifugal force of the counterweight on each blade root.

FUEL SYSTEM

A 230-gallon fuel supply is available for the Thrush S2R-T660. In each wing, fuel is contained inside

integral wing tanks (wet wing fuel tanks) just outboard of the center section sub-wings. The left wing

and right wing fuel tanks are interconnected through a 5 U.S. gallon header tank that is located in

the fuselage. The fuel supply lines, to the engine, are routed from the header tanks outlet finger

screen through a fuel shutoff (on/off) valve to an electric driven fuel boost pump. The electric driven

fuel boost pump discharge is then routed through a 25-micron main fuel filter to an engine driven

fuel boost pump. The electric driven fuel boost pump serves two purposes, first as a backup system

to provide continuous fuel pressure to the engines high pressure fuel pump in case the engine

driven fuel boost pump fails and secondly to provide boosted fuel pressure to the engines high

pressure fuel pump during engine starting. The aircraft’s fuel system is equipped with two fuel

filters, a ¼ inch mesh finger strainer is installed in the outlet fitting from the header tank and a 25-

micron, airframe supplied, main fuel filter located on the forward L/H side of the firewall. Fuel from

the aircraft fuel system enters the engines high pressure fuel pump which has two fuel filters, an 74-

micron inlet filter and a 10-micron discharge filter (refer to the engines appropriated maintenance

manual for pertinent maintenance details for the engine supplied filters and fuel system). 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 happened to have got in the tanks outboard vent lines. At engine shutdown, fuel

from the flow divider/dump valve, located at the 6 o’clock position on the engines fuel nozzle

manifold, is directed to a residue fuel reservoir “EPA tank” mounted inboard on the L/H aft shin skin.

This reservoir hold approximately 3 engine shutdowns worth of fuel before the fuel will exit the

reservoirs vent system. (NOTE: This reservoir should be emptied after each engine shutdown.)

(NOTE: It is common and normal after an engine compressor Water Wash or Performance

Recovery Wash to have water or soap appear in the reservoirs’ drained waste fuel.) 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 a L/H or R/H tank fuel quantity selector

switch. A transmitter, installed in each wing

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AIRCRAFT MAINTENANCE MANUAL

tank transmits an electrical signal to the single fuel quantity indicator. The instrument reads both the

left and right fuel tanks singularly as chosen by the electrical control 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 both wings. The filler ports incorporate security chains to prevent the lost of the

fuel caps. Service the aircraft from refueling facilities that utilize proper ground handling equipment

and filter systems to remove impurities and water accumulations 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 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 Two.

LANDING GEAR, WHEELS & BRAKES

The main landing gear is made using a formed chrome-moly spring steel unit. The left Main gear

and the right main gear are symmetrical. The main wheels are 11 x 10. The spring steel

construction and design of the main gear allow for absorption of landing weight and common

stresses associated with such, thus eliminating the need for shock struts. 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 brakes

are dual caliper disc types. The tail gear is a spring steel type and uses a 600 x 6 tailwheel.

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

the rudder control is through 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

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AIRCRAFT MAINTENANCE MANUAL

right panel. The left panel contains a clock, oil temperature, hour meter, fuel pressure, oil pressure,

air filter Delta “P”, and fuel quantity gauges. The right panel contains a voltmeter, ammeter, and

circuit breakers. The upper panel contains all engine-warning lights, torque pressure, ITT indicator,

and Gas Generator percent RPM, Propeller RPM and standard flight instrument package.

ELECTRICAL SYSTEM

The standard 24 volts and 105 amps electrical system consists of the starting system, the

navigation lights, the wiper/washer system, and the strobe lights. The landing lights, the working

lights, and the air conditioner system are optional. The landing and working lights may be installed

in the field, since the wiring for them is included in the standard wire bundle. The electrical system

obtains power from two 24-volt batteries and one starter/generator. 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-T660 Flight Manual for aircraft weight and balance information.

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AIRCRAFT MAINTENANCE MANUAL

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THRUSH AIRCRAFT INC – T660 TURBO THRUSH

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Figure 1-2

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AIRCRAFT MAINTENANCE MANUAL

Section 2

SERVICING & INSPECTION

TABLE OF CONTENTS

SECTION TWO ................................................................................................................................................ 1

SERVICING .................................................................................................................................................. 3

GROUND HANDLING .................................................................................................................................. 3

TOWING ................................................................................................................................................... 3

TAXIING ................................................................................................................................................... 3

PARKING ................................................................................................................................................. 3

MOORING ................................................................................................................................................ 3

JACKING .................................................................................................................................................. 4

LEVELING ................................................................................................................................................ 4

COLD WEATHER OPERATION .................................................................................................................. 4

COLD WEATHER MAINTENANCE HINTS ............................................................................................. 4

GROUND EMERGENCY PROCEDURES ................................................................................................... 5

ENGINE FIRES ........................................................................................................................................ 5

ELECTRICAL FIRES ................................................................................................................................ 6

GROUND OPERATION OF ENGINE .......................................................................................................... 6

BEFORE STARTING ENGINE ................................................................................................................. 6

STARTING ENGINE ................................................................................................................................. 7

ENGINE OPERATIONAL CHECK ........................................................................................................... 8

SYSTEM AND COMPONENT SERVICING .................................................................................................8

HYDRAULIC SYSTEM ............................................................................................................................. 9

ENGINE OIL SYSTEM ............................................................................................................................. 9

FUEL SYSTEM ....................................................................................................................................... 13

DEFU ELI NG ......................................................................................................................................... 15

INDUCTION SYSTEM ............................................................................................................................ 16

POWER PLANT INTERNAL CLEANING ............................................................................................... 16

LANDING GEAR, WHEELS & BRAKES .................................................................................................... 17

TI RES .................................................................................................................................................... 17

BRAKE BLEEDING ................................................................................................................................ 17

I NSPECTION ......................................................................................................................................... 17

INSPECTION CHECK LIST ................................................................................................................... 17

INSPECTION CHART ............................................................................................................................. 19

ENGINE EXTERNALS ............................................................................................................................... 21

ENGINE OIL SYSTEM ............................................................................................................................... 22

ENGINE FUEL SYSTEM ............................................................................................................................ 24

IGNITION SYSTEM .................................................................................................................................... 25

PNEUMATIC SYSTEM .............................................................................................................................. 25

AIRFRAME FUEL SYSTEM ....................................................................................................................... 25

MAIN LANDING GEAR .............................................................................................................................. 26

TAIL GEAR ................................................................................................................................................. 27

FUSELAGE SKINS .................................................................................................................................... 28

HOPPER .................................................................................................................................................... 28

WI NGS ...................................................................................................................................................... 29

FUSELAGE FRAME ................................................................................................................................... 30

CONTROL SYSTEMS ................................................................................................................................ 30

METAL EMPENNAGE ............................................................................................................................... 32

AILERONS AND FLAPS ............................................................................................................................ 33

COCKPIT .................................................................................................................................................... 34

ELECTRICAL SYSTEM ............................................................................................................................. 34

AIRFRAME MAINTENANCE

................................

......................

36

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CORROSION CONTROL ........................................................................................................................36

WINDSHIELD ..........................................................................................................................................37

HOPPER REPAIR ...................................................................................................................................37

FUEL TANK REPAIR ..............................................................................................................................37

BATTERY MAINTENANCE ....................................................................................................................37

LUBRICATION ........................................................................................................................................38

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Thrush Aircraft S2R-T660 Maintenance Manual

Thrush Aircraft S2R-T660 Maintenance Manual

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