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## TABLE OF CONTENTS

S ubject: Page :



## LOG OF REVISIONS

................................ ................................ .............................. ii

TABLE OF CONTENTS

................................ ................................ .......................... iii

PREFACE

................................ ................................ ................................ ............ iv

CHAPTER 1: INTRODUCTION

................................ ................................ .............. 1

CHAPTER 2: AIRCRAFT SYSTEMS

................................ ................................ ......... 2

CHAPTER 3: OPERATIONAL PROCEDURES

................................ ........................... 3

CHAPTER 4: EMERGENCY PROCEDURES

................................ ........................... 13

CHAPTER 5: PERFORMANCE

................................ ................................ ............ 16

CHAPTER 6: HANDLING C HARACTERISTICS

................................ ...................... 26

CHAPTER 7: PILOT DOCUMENTATION

................................ ............................. 27

CHAPTER 8: PILOT TYPE RATING REQUIREMENT THRUSH AIRCRAFT, INC

. ...... 28

APPENDIX A: S2R

- T660 AIRCRAFT TRANSITION COURSE SYLLABUS

.................. A 1

APPENDIX B: MODEL TURBO THRUSH S2R

- T66 0 WRITTEN EXAM

..................... B 1

APPENDIX C: PILOT TRAINING RECORD CHECKLIST SHEET

................................ . C 1

APPENDIX D: TRAINING A TTENDANCE RECORD

................................ ............... D 1Report #: 

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# PREFACE

This Manual was developed to establish a Training Program specific to the Thrush

Aircraft S2R

- T660 / S2R

- T660DC aircraft. The Training Program meets the

requirements of the United States of Amer ica Department of Transportation Federal

Aviation Administration Exemption No. 9844 from the requirements of 14 CFR 61.31(a).

This manual is intended to serve as a supplement to the Approved Airplane Flight

Manual (AFM) during training, and not as a stand

- alone document. All information

contained herein should be verified against the Approved AFM.Report #: 

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## CHAPTER 1: INTRODUC TION

The systems of the Thrush Aircraft S2R

- T660 / S2R

- T660DC aircraft are similar to

those systems found in other model s of Thrush Aircraft. Differences may include:

1. Pratt & Whitney Canada PT6

- 60 series engine, rather than the

- 10,

- 20,

- 30 series

engines found in other models.

2. 5

- bladed reversible full

- feathering Hartzell propeller, rather than the 3

- bladed

propeller found on other models.

3. Electric Rudder TrimReport #: 

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## CHAPTER 2: AIRCRAFT SYSTEMS

The S2R

- T660 / S2R

- T660DC aircraft is typically equipped for Day and Night VFR flight.

The following equipment comes standard from the factory:

1. Basic flight instruments including, Airspee d Indicator, Altimeter, Fluid Compass, etc.

2. Electronics International MVP

- 50T Engine Monitoring System, which includes:

3. Stall warning system

4. Slip indicator

5. 24

- volt electrical system

6. Handheld Fire Extinguisher

7. (Pilot comfort items, including cockpit air co nditioning, bleed air cockpitheat,

windshield washer and wiper systems.

8. Dispersal System includes: 3” plumbing, 710 gallon hopper, standard gate box for

dry application or emergency dumping, booms and nozzles, either a standard

chemical pump with Weathaero adjustable pitch fan or a standard chemical pump

with electric fan brake.

9. Optional equipment includes: an electrically driven attitude indicator, various

communication and navigation radios, GPS, transponder, audio panel, clock, night

working lights, VSI, electric turn coordinator, light system for night VFR flight, and

smoker.

Every aircraft is configured according to the customer’s specification, so every aircraft is

outfitted uniquely. Take time to familiarize yourself with your particular aircraft and

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## CHAPTER 3: OPERATIO NAL PROCEDURES

EXTERIOR INSPECTION ROUTE



## VISUAL INSPECTION

NOTE

Visually check the aircraft for general condition during the walk around

inspection.

Verify that all camlocs on the skin panel are fastened. Remove a ll accumulations

of frost, ice, or snow in cold weather from the wing, the tail, and the control

surfaces.

If night flight is planned, check the operation of all lights and have a flashlight

available.

( POSITION) (1)

1. Ignition Switch

– OFF

2. Power Lever

– FORWARD IDLE STOP

3. Control Lock

– REMOVE

4. Fuel Condition Lever

– CUTOFF

5. Fuel Valve

– ON

6. Parking Brake

– TEST and SET

7. Battery Switch

– ON

8. Fuel Quantity

– CHECK each tank

8a. Battery Switch

– ONReport #: 

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8b. Check Flap Operation

– UP

– DOWN

- UP

9. Battery Switch

– OFF

10. Elevator Trim Tab

– SET for take

- off (T.O. arc)

11. Oil Quantity

– CHECK the dipstick and SECURE cap

11a. Fuel Quantity

– CHECK visually and SECURE cap



### NOTE

Operate between 1 and 3 quarts below the maximum oil level mark

on the oil dipstick.



### (2)

12. Wing Flap

– CHECK for security

13. Spray Boom (if installed)

– CHECK for leaks and security

14. Aileron

– CHECK for free and correct Movement, aileron hinges

– CHECK for

looseness using a BRISK up and down motion.

Use caution so as not to damage controls or stops.



### (3)

15. Wing Tip

– CHECK for damage

16. Wing Leading Edge

– CHECK for damage

17. Stall Vane

– CHECK con dition and freedom of movement



### NOTE

Keep the wing leading edge clean. An excessive build

- up of dirt, bugs, and chemicals

can have the same negative effect on lift as an accumulation ice and frost.

18. Wing Tie Down

– REMOVE

18a Spreader (i f installed) CHECK for security of all attachments.



### (4)

19. Left Wing Sump

- DRAIN

20. Header Tank Sump

– DRAIN

20a Left Fuel Vent Sump

- DRAIN

21. Fuel Vent

– CHECK for obstruction

22. Main Wheel Tire and Brake

– CHECK for inflation, damage, and wear

23. Firewa ll Fuel Filter By

- pass Indicator

– CHECK

24. Firewall Fuel Filter

– DRAIN

24a. Residual fuel reservoir (EPA tank)

- DRAIN

25. Accessory Section

– CHECK for debris, oil leaks, or any other irregularities

26. Oil Cooler

– CHECK for leaks, stoppage, and flapper door f or freedom of

operation

27. Air Filter

– CHECK for cleanliness and conditionReport #: 

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(5)

28. Engine

– CHECK for oil leaks, fuel leaks, loose fittings, cracked exhaust

stacks, and excessive dirt or corrosion

29. Propeller

– CHECK for spinner damage, oil, and grease l eaks

30. Propeller

– CHECK the propeller blades for nicks, cracks, or excessive

erosion of the

leading edge.

31. Dispersal Equipment (if installed)

– CHECK the pump, the pump fan, hoses,

the spreader, the mounting, etc., for security.

32. Wheel Chocks

– REMOVE

32a Spreader (if installed)

– CHECK for security of all attachments



### (6)

33. Right Wing Sump

– DRAIN

33a Right Fuel Vent Sump

– DRAIN

34. Main Wheel Tire and Brake

– CHECK for inflation, damage, and wear



### (7)

35. Wing Leading Edge

– CHECK for damage



### NOTE

Keeping the wing leading edge clean. An excessive build

- up of dirt, bugs,

and chemicals can have the same effect of lift as ice or frost build

- up.

36. Pitot Mast

– CHECK for blockage of opening

37. Wing Tie Down

– REMOVE

38. Wing Tip

– CHECK for dama ge



### (8)

39. Aileron

– CHECK for free and correct movement

40. Aileron Hinges

– CHECK for looseness by using a brisk up and down motion

(Use caution so as not to damage controls or stops.)

41. Spray Boom (if installed)

– CHECK for leaks and security

42. Wing Flap

– CH ECK for security

42a Fuel Quantity

– CHECK visually and SECURE cap

42b Battery Vent

– CHECK for obstruction

43. Static Port Opening

– CHECK for blockage

44. Rudder Gust Lock (if installed)

– REMOVE



### (9)

45. Empennage

– CHECK for condition

46. Struts

– CHECK for tension and security

47. Tail Wheel Tire

– CHECK for inflation, damage, and wear

48. Tail Wheel Spring

– CHECK f or conditionReport #: 

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48a Tail Wheel Assembly

– CHECK for condition

49. Rudder and Elevator

– CHECK for freedom of movement and security

50. Elevator Trim Tabs

– CHECK for near neutral pos ition (Take

- off) and

excessive play

51. Tail Tie

- Down

– REMOVE

52. Static Port Opening

– CHECK for blockage



### (10) FOR DUAL COCKPIT AIRCRAFT ONLY

53. Rear Cockpit Area

– CHECK and SECURE area



## BEFORE STARTING ENGI NE

1. Visual Inspection

– COMPLETE

2. Seat

– ADJUST

3. Rudder Pedal s

– ADJUST and LOCK

4. Seat Belt and Shoulder harness

– ADJUST and LOCK

5. Altimeter

– SET

6. Door Latches

– CHECK

7. Parking Brake

– SET

8. Propeller

– CLEAR Area



## STARTING ENGINE

1. Battery

– ON

2. Power Lever

– FORWARD IDLE STOP / BETA STOP

3. Propeller Lever

– FEATHER

4. Fuel Co ndition Lever

– CUT OFF

5. Fuel Valve

– ON

6. Fuel Auxiliary Pump Switch

– ON

7. Fuel Inlet pressure Indicator

– CHECK 5 PSIG Minimum

8. Engine Starter Switch

– ON

( The minimum engine speed to obtain satisfactory ignition is 13% Ng.)

9. After approximately 5 secon ds of motoring at a stabilized gas generator speed above

13%

a) MOVE Ignition Switch to ON Position

b) MOVE the Fuel Condition Lever to the Ground Idle Position

10. OBSERVE that the engine accelerates normally to idle RPM and that the maximum

allowable inter

- t urbine starting limit is not exceed.Report #: 

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Whenever the gas generator fails to ignite within 10 Seconds after moving the

Fuel Condition Lever to the Ground Idle Position;

1. Move the Fuel Condition Lever to the cut off position, and

2. Move the starter and ignition switches to the off positions.

Allow a 30 Second fuel draining period that is followed by a 15 SECOND DRY

MOTORING RUN before attempting another star. If for any reason a starting

attempt is discontinued, allow the engine to come to a complete stop and then

accomplish a dry motoring run. See the following Section

– DRY MOTORING

RUN.

11. Engine Starter Switch and Ignition Switch

– OFF

12. Oil Pressure

– CHECK 85 PSIG Minimum

13. Fuel Auxiliary Pump

– OFF

14. Fuel Pressure from Engine Driven Pump

– CHECK 5 PSI Minimum

15. G enerator

– ON and CHECK charging normally



## DRY MOTORING RUN

The following procedure is used to clear an engine at any time when it is deemed

necessary to remove internally trapped fuel and vapor or when there is evidence of a fire

within the engine.

Air t hat passes through the engine serves to purge fuel vapor, or fire from the

combustion

sections, the gas generator turbine, the power turbine, and the exhaust system.

1. Fuel Condition Lever

– CUT OFF

2. Ignition Switch

– OFF

3. Master Switch

– ON

4. Fuel Valve

– ON

5. Fuel Auxiliary Pump Switch

– ON to provide lubrication for the engine driven fuel

pumping

element

6. Engine Starter Switch

– ON

If the fire should persist as indicated by the sustained interturbine temperature,

close the fuel system shutoff valve i mmediately and continue motoring. CAUTION

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7. Maintain the starter operation for the desired duration. The maximum starter duration is 3

minutes.

8. Engine Starter Switch

– OFF

9. Fuel Auxiliary Pump Switch

– OFF

10. Fuel Valve

– OFF

11. Battery Switch

– OFF

12. Allow a 5

- minute cool ing period for the starter before going any further with the starting

operation.



## TAXI

1. Propeller lever

– against feather latch (See Page I

- 7 for Propeller Ground

Operation Limits)

2. Utilize Beta Region of the throttle quadrant for taxiing

.

3. Push stick full forward to unlock the tail wheel.



## BEFORE TAKE

- OFF

Before proceeding with a ground run

- up, be sure that the propeller system is purged,

by feathering the propeller once or twice with the Power Lever in the Idle Position.

The followin g procedures should be used to check the Propeller Overspeed Governor:

1. PLACE the propeller lever in full increase RPM position ( forward )

2. INCREASE the RPM with the power lever to at least 1700 RPM.

3. MOMENTARILY EXERCISE the prop test switch and NOTE a small decrease in the

RPM (1598 +/

- 20). This checks the prop overspeed governor.

HOLD the Elevator Control firmly FULL AFT during all high power ground

operation to keep the airplane from nosing over.

4. Flight Controls

– CHECK free and full travel

5. Elevator Tab

– SET for take

- off

6. Flaps

– SET as required

7. Fuel Condition Lever

– SET flight idle and CHECK 69% Ng ( ± 1%)

8. Fuel Auxiliary Pump

– ON

9. Ignition Switch

– ON

10. Rudder Trim

– SET for take

- off CAUTIONReport #: 

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11. Prior to any fli ghts, apply take

- off power and read the filter condition indicator. If the

needle enters the red arc, do not fly until the filter element has been cleaned.



## TAKE

- OFF

1. Brakes

– RELEASE

2. Power Lever

– ADVANCE, but DO NOT EXCEED the engine operational limitati ons. (See the Limitations Section)

3. After take

- off ACCELERATE to the best

- rate

- of

- climb airspeed of 117 mph IAS, for

flaps down.



## CLIMB

1. MAIN TAIN maximum continuous power.

2. Flaps

– RETRACT

3. Establish the Best Rate of Climb Airspeed of 122 MPH IAS with Flaps Up

4. Fuel Auxiliary Pump

– OFF

5. Ignition Switch

– OFF



## GLIDE AND APPROACH

1. Fuel Condition Lever

– SET flight idle

2. Prop Control

– SET full high RPM

3. Fuel Auxiliary Pump

– ON

4. Ignition Switch

– ON

5. Flaps

– SET as required



## GO AROUND

1. Power Lever

– INCREASE t o the take

- off setting

2. Flaps

– RETRACT after positive rate of climb has been established

3. Airspeed

– MAINTAIN the best

- rate

- of

- climb speed of 122 MPH IAS with Flaps Up



## LANDING

1. Airspeed on Final

– MAINTAIN 82 MPH with hopper empty

2. Wing Flaps

– SET 15 degre es

3. Touchdown

– Main WheelsReport #: 

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4. Landing Roll

- LOWER tail smoothly and CLOSE the throttle

5. Propeller

– REVERSE; reverse may be used after the tail is on the ground.

(To use Reverse Thrust; LIFT the Reverse Gate on the Power lever and MOVE the

Power Lever smooth ly into reverse. The tail wheel should be locked during all the

reverse operation.)



### NOTE

The tail wheel should not be unlocked prematurely. A crosswind or the

initiation of a turn could cause loss of control.

6. Brakes

– USE as necessary



## AFTER CLEARING THE R UNWAY

1. Wing Flaps

– RETRACT

2. Fuel Auxiliary Pump

– OFF

3. Ignition Switch

– OFF

4. Fuel Condition Lever

– MOVE to ground idle position

5. Propeller lever

– against feather latch (See Page I

- 7 for Propeller Ground Operation

Limits)



## ENGINE SHUTDOWN

1. Parking Brake

– SET

2. Power Lever

– IDLE



### NOTE

Allow the engine to stabilize for a minimum of one minute below 650 degrees

ITT maximum.

3. Propeller Lever

– FEATHERED

4. Fuel Condition Lever

– CUT OFF

5. P

- 3 Heater Switch

– OFF

6. Battery Switch

– OFF

7. Gen erator Switch

– OFF



### NOTE

During the shutdown be sure that the compressor decelerates freely.



### WARNINGReport #: 

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If there is any evidence of a fire within the engine after shutdown, proceed

immediately as described in the Dry Motoring Run Section.



## SECURING THE AIRCRA FT

1. Parking Brake

– RELEASE and INSTALL the wheel chocks

2. Control Lock

– ENGAGE

3. Wing Tie

- Downs and Tail Tie Down

– SECURE

4. While the aircraft is unattended, be sure that the propeller is tied down to prevent

windmilling with zero oil pressure.



## FOR AIRCRAFT WITH TRANSLAND HYDRAULIC FIREDOOR

INSTALLED P/N: 25151

FIRE DOOR OPERATING PROCEDURES

NOTE

To prevent failure codes from appearing on the computer, ensure the Hydraulic Arm

switch is in the OFF position prior to turning on the computer.

1. Battery

- ON

2. H ydraulic Arm Switch

- OFF

3. Fire Door Computer

- ON

4. Check system indication

– Should read “70”

NOTE

If system indicates, “81,” the Hydraulic Arm Switch has been left on.

5. If “70” is indicated, depress door opening switch on the pilots control stick. This will

activate the system to normal operation.

NOTE



### If the number 82 appears when the door opening switch on the pilots control

switch is depressed, this indicates a failure o r short in the opening switch.

The computer considers the “82” warning as a crit ical error, and

will suspend all other operations until it is cleared.

6. Select operating Mode

7. Set

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8. Depress Switch on Pilots Stick for operation.



## MANUAL OPERATION

1. The system is equipped with a manual switch that does not operate through the

computer . This switch is intended for maintenance and ground operation only, such as

calibration. To open door

– place switch in open position momentarily. To close door

–

place switch in close position momentarily.

The manual switch should only be used momen tarily to prevent system damage. CAUTIONReport #: 

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## CHAPTER 4: EMERGEN CY PROCEDURES

GROUND ENGINE FIRE

See Dry Motoring Run in Section II.



## ENGINE FIRE IN FLIGH T

1. Power Lever

– IDLE POSITION

2. Propeller Lever

– FEATHERED

3. Fuel Condition Lever

– CUT OFF POSITION

4. Fuel Auxiliary Pump Switch

– OFF

5. Fuel Valve

– OFF



## ENGINE SHUTDOWN IN F LIGHT

1. Propeller Lever

– FEATHERED

2. Fuel Condition Lever

– CUT OFF POSITION

3. Fuel Auxiliary Pump Switch

– OFF

4. Fuel Valve

– OFF

5. Power Lever

– IDLE POSITION



## ENGINE FLAMEOUT

The indications of any engine fl ameout will be a drop in the inter

- turbine temperature, a

drop

in the torque pressure, and a drop in RPM. The flameout may result from the engine

running

out of fuel or possibly caused by an unstable engine operation. Once the fuel supply

has been resto red to the engine or the cause of the unstable operation eliminated, the

engine may be

restarted in the manner described under Air Starts on the Page III

- 2.



## NORMAL AIR STARTS

NOTE

Air Start Envelope

– Normal Air Starts ranging from sea level to 12,000 feet

altitude and above 148

- MPH IAS have been approved.



## PRE

- AIR START CHECK

1. Propeller Lever

– ANYWHERE IN THE OPERATING RANGE.



### NOTE

Propeller feathering is dependent on circumstances and is at the discretion of the

pilot.

Fine pitch selection will pump air t hrough the engine, and; therefore increase the

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2. Power Lever

– IDLE

3. Master Switch

– ON

4. Fuel Valve

– ON

5. Fuel Condition Lever

– CUT OFF

6. Fuel Auxiliary Pump Switch

– ON

7. Fuel Pressure Indicator

– 5 PS IG minimum



## AIR START PROCEDURE

1. Starter Switch

– ON, The minimum gas generator RPM to obtain satisfactory ignition

is 13% Ng.

2. Engine Ignition Switch

– ON

3. Fuel Condition Lever

– GROUND IDLE POSITION after approximately five seconds

of stabilized gas generat or speed.



### NOTE

A relight normally should be obtained within 10 Seconds and will be noted first by

a rise in gas generator RPM. A rise in the inter

- turbine temperature will also be

noted.

The following should be carried out when the engine reaches Idle R PM:

1. Engine Starter and Ignition Switches

– OFF

2. Propeller Lever

– INTO OPERATING RANGE

3. Power Lever

– ADJUST to desire position

4. Fuel Condition Lever

– FLIGHT IDLE

5. CHECK that the Engine Operating Limits are not exceeded. If a satisfactory Start is

not obtained discontinued the air start. If another starting attempt is to be made,

repeat the

engine air start procedure.



### NOTE

The best air start technique is to i nitiate the restart procedure immediately after a

flameout occurs, if the pilot is certain that the flameout was not the result of some

malfunction which might make the attempt to restart dangerous. There is always

the chance that the engine may restart s uccessfully just as soon as the ignition is

turned on. In a flameout situation, move the igniter switch to the on position as

quickly as possible, if the gas generator speed has not dropped below 58%.

Under these circumstances it is not necessary to move the fuel lever or feather

the propeller. However, the power lever should be returned to the idle position.



## ELECTRICAL FIRE IN F LIGHT

1. Battery Switch and Generator Switch

– OFF

2. All other Electrical Switches

– OFF

3. Circuit Breakers

– C HECK to identify faulty circuit, if possible.Report #: 

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If electrical power is essential for the flight, try to identify and isolate the faulty circuit by

doing the following:

1. Generator Switch

– ON

2. If the Generator Switch is defective, MOVE the Generator Switch t o the OFF position

and then MOVE the Battery Switch to the ON position. Let a short period of time

elapse

before activating additional circuits one at a time until the defective circuit is

identified.

3. Defective Circuit

– OFF



## EMERGENCY EGRESS

If it is ne cessary to remove the cockpit door from its hinges, do the following:

1. KNOCK OUT the oval panel below the window.

2. REACH through the hole and PULL UP the flexible hinge pin.

3. PUSH the door clear of the aircraft and EXIT.



## FOR DUAL COCKPIT AIR CRAFT:

If it is n ot desired to release the door from its hinges while exiting the aircraft in the

normal manner, proceed with the following:

1. The front cockpit door must be closed in order for the rear occupant to exit the

aircraft.

2. The rear occupant can exit by using the step in the left side of the fuselage below the

front door.



## GENERATOR FAILURE

1. RESET Generator

2. If Generator is not restored, accomplish the following:

a. Air Conditioner OFF

b. All other nonessential electrical equipment OFF

If Generator Fails, Air Conditioner must be turned off to ensure

30 minutes of Battery Power



## FOR AIRCRAFT WITH TRANSLAND HYDRAULIC FIRE DOOR

INSTALLED P/N: 25151

EMERGENCY DUMPS

If Hydraulic Door fails to open:



## 1. PULL

– Hydraulic Dump Valve Cable Handle



## 2. Activate Standard Dump Hand le. CAUTIONReport #: 

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## CHAPT ER 5: PERFORMANCE

POWER OFF STALL SPEE DS

The variation of power

- off stall speeds with bank angle, flight configuration and

airplane weight is shown below for the flaps up and flaps 15 degrees

configurations.



## ASSOCIATED CONDITION S

Power Off

Configu ration Clean T.O./Landing

Wing Flaps 0 Degrees 15 Degrees

Dispersal Equipment Std. Spray or Std. Spray or

Large Spreader Large Spreader

Stall Entry Rate Uniformly Decreasing

Gross Weight 14,150 pounds



## POWER OFF STALL SPEE DS

– MPH (IAS)

Bank Angle Flaps

- 0 Degrees Flaps

- 15 Degrees

0 94 90

30 101 97

60 133 127



## SPEED FOR BEST RATE

- OF

- CLIMB

Flaps 0 Degre es

- 122 MPH IAS Flaps 15 Degrees

- 117 MPH IAS



## AIRSPEED CALIBRATION MPH

FLAPS 0 DEGREES IAS 80 100 120 140 160 180 200 221

CAS 82 102 122 142 1 61 181 201 222

FLAPS 15 DEGREES IAS 80 100 120 140 156

CAS 82 102 122 142 154Report #: 

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## 17 Revision: 

## A Date: 

## 11/25 /2013 FAA Project #: 

## N/A

TAKEOFF DISTANCE ~ F EET

INTERNATIONAL STANDARD ATMOSPHERE

ENGINE (PRATT & W HITNEY) PT6A

- 60AG, PT6A

- 45 Series

PROPELLER (HARTZELL HUB MODEL / BLADES) HC

- B5MP

- 3C / M

- 10876

ASSOCIATED CONDITIONS

POWER ... TAKEOFF

CONFIGURATION

WING FLAPS ... 15°

DISPERSAL EQUIPMENT ... STANDARD SPRAY

GROSS WEIGHT ... 14150 LB

RUNWAY ... LEVEL HARD SURFACE

WI ND ... ZERO

REVERSE THRUST ... NONE

CALIBRATED AIR SPEED AT 50 FEET ... 1.2 Vs = 110 MPH

NOTE:

FOR COLD ATMOSPHERE CONDITIONS BELOW

– 16°C USE THE DATA FOR THE COLDEST

TEMPERATURE SHOWN IN THE TABLE.

NOTE:

THIS CHART IS CONSERVATIVE WHEN USED WITH THE FOLLOW ING ENGINES AND

PROPELLERS:

ENGINE (PRATT & WHITNEY) PT6A

- 67AG

PROPELLER (HARTZELL HUB MODEL AND BLADES)

PT6A

- 67AG HC

- B5MA

- 3D / M11276NS OAT

(°C) Gnd

Roll To 50' Gnd

Roll To 50' Gnd

Roll To 50' Gnd

Roll To 50' Gnd

Roll To 50' Gnd

Roll To 50' Gnd

Roll To 50' Gnd Roll To 50' Gnd

Roll To 50' Gnd

Roll To 50' Gnd

Roll To 50'

-32

- - - - - - - - - - - - - - - - - - 3335 6550 3564 7094

-28

- - - - - - - - - - - - - - 3003 5801 3211 6265 3430 6773 3667 7348

-24

- - - - - - - - - - 2720 5192 2890 5554 3090 5994 3302 6474 3527 7003 3771 7607

-20

- - - - - - 2467 4666 2628 4996 2791 5342 2973 5735 3177 6190 3394 6887 3626 7246 3925 8110

-16 1571 2780 2242 4217 2379 4487 2534 4803 2695 5139 2862 5494 3057 5919 3265 6389 3486 6906 3775 7727 4105 8788

-12 2169 4073 2298 4326 2443 4617 2602 4942 2763 5283 2940 5661 3140 6106 3353 6593 3618 7304 3936 8297

- -

-8 2222 4177 2355 4439 2508 4749 2668 5080 2832 5429 3020 5837 3225 6297 3466 6905 3777 7852 4118 9035

- -

-4 2276 4282 2416 4563 2573 4882 2733 5219 2903 5581 3100 6016 3328 6572 3627 7452 3953 8541

- - - -

0 2329 4388 2479 4690 2637 5016 2799 5358 2979 5749 3196 6262 3483 7084 3796 8092

- - - - - -

4 2387 4505 2541 4817 2700 5149 2865 5500 3086 6040 3345 6742 3648 7689

- - - - - - - -

8 2447 4626 2605 4947 2763 5283 2970 5783 3220 6457 3506 7322 3829 8452

- - - - - - - -

12 2507 4748 2665 5075 2862 5547 3106 6206 3377 7009 3679 8023

- - - - - - - - - -

16 2568 4872 2764 5342 2999 5970 3260 6734 3549 7688

- - - - - - - - - - - -

20 2665 5134 2893 5735 3145 6461 3425 7372

- - - - - - - - - - - - - -

24 2785 5499 3030 6197 3303 7071

- - - - - - - - - - - - - - - -

28 2919 5948 3182 6778

- - - - - - - - - - - - - - - - - - TAKEOFF DISTANCE - FT

6000 7000 9000 8000 10000 SL 1000 2000 3000 4000 5000Report #: 

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## S2R

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- T660DC TRAINING MANUAL

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## A Date: 

## 11/25 /2013 FAA Project #: 

## N/A

TAKEOFF DISTANCE ~ F EET

INTERNATIONAL STANDARD ATMOSPHERE

TAKE OFF DISTANCE

- FT

ENGINE (PRATT &WHITNEY) PT6A

- 60AG, PT6A

- 45 SERIES

PROPELLER (HARTZELL HUB MODEL / BLADES) HC

- B5MP

- 3C / M

- 10876

ASSOCIATED CONDITIONS

POWER... TAKEOFF

CONFIGURATION

WING FLAPS... 15°

DISPERSAL EQUIPMENT... LARGE SPREADER

GROSS WEIGHT... 12500 LB

RUNWAY... LEVEL HARD SURFACE

WIND... ZERO

REVERSE THRUST NONE

CALIBRATED AIR SPEED AT 50 FEET... 1.2Vs = 110 MPH

NOTE:

THIS CHART IS CONSERVATIVE WHEN USED WITH THE FOLLOWING ENGINES AND PROPELLERS:

ENGINE (PRATT & WHITNEY) PT6A

- 67AG

PROPELLER (HARTZELL HUB MODEL AN D BLADES)

PT6A

- 67AG HC

- B5MA

- 3D / M11276NS OAT

(°C) Gnd

Roll To 50' Gnd

Roll To 50' Gnd

Roll To 50' Gnd

Roll To 50' Gnd

Roll To 50' Gnd

Roll To 50' Gnd

Roll To 50' Gnd

Roll To 50' Gnd

Roll To 50' Gnd

Roll To 50' Gnd

Roll To 50'

-32

- - - - - - - - - - - - - - - - 2394 4612 2560 4974 2738 5376

-28

- - - - - - - - - - - - 2160 4118 2304 4421 2464 4764 2635 5138 2817 5567

-24

- - - - - - - - 1960 3705 2087 3963 2218 4239 2371 4563 2535 4918 2710 5308 2897 5761

-20

- - - - 1776 3342 1891 3567 2014 3813 2142 4078 2281 4372 2438 4708 2606 5075 2786 5490 3015 6118

-16 1620 3044 1718 3230 1823 3434 1942 3669 2067 3923 2196 4193 2345 4508 2506 4855 2679 5236 2900 5831 3152 6586

-12 1661 3122 1761 3313 1872 3530 1994 3772 2120 4033 2255 4318 2409 4646 2575 5005 2779 5520 3023 6228 3297 7130

-8 1702 3201 1805 3398 1922 3628 2046 3878 2173 4144 2317 4447 2475 4787 2661 5231 2900 5905 3161 6729 3449 7772

-4 1744 3280 1852 3490 1972 3728 2097 3984 2227 4258 2378 4579 2554 4986 2783 5616 3033 6378 3308 7324

- -

0 1785 3360 1900 3584 2022 3828 2147 4090 2286 4382 2452 4759 2671 5348 2911 6059 3177 6947

- - - -

4 1830 3447 1948 3679 2071 3930 2198 4198 2367 4593 2564 5100 2795 5770 3053 6609

- - - - - -

8 1876 3537 1996 3776 2120 4033 2278 4403 2467 4890 2685 5504 2932 6289

- - - - - - - -

12 1922 3628 2044 3874 2195 4226 2381 4704 2585 5277 2815 5985 3077 6916

- - - - - - - -

16 1968 3720 2119 4067 2299 4527 2497 5075 2717 5746 2962 6596

- - - - - - - - - -

20 2042 3910 2217 4348 2410 4872 2623 5517 2861 6333

- - - - - - - - - - - -

24 2133 4172 2320 4675 2529 5295 2760 6071

- - - - - - - - - - - - - -

28 2234 4490 2435 5079 2658 5813

- - - - - - - - - - - - - - - -

32 2346 4876 2558 5564 2795 6453

- - - - - - - - - - - - - - - -

36 2473 5359

- - - - - - - - - - - - - - - - - - - - 2000 3000 4000 5000 6000 7000 9000 8000 10000 SL 1000Report #: 

## ER

- 5 11 Title: 

## S2R

- T660/

- T660DC TRAINING MANUAL

Page: 

## 19 Revision: 

## A Date: 

## 11/25 /2013 FAA Project #: 

## N/A

RATE OF CLIMB

INTERNATIONAL STANDARD ATMOSPHERE

OAT RATE OF CLIMB

- FT

ENGINE (PRATT & WHITNEY) PT6A

- 60AG, PT6A

- 45 SERIES

PROPELLER (HARTZELL HUB MODEL / BLADES) HC

- B5MP

- 3C / M

- 10876

ASSOCIATED CONDITIONS

POWER ... TAKEOFF

CONFIGURATION

WING FLAPS ... 15°

DISPERSAL EQUIPMENT ... STANDARD SPRAY

GROSS WEIGHT ... 14150 LB

CALIBRATED AIR SPEED AT 50 FEET ... 1.2 Vs = 110 MPH

NOTE:

FOR COLD ATMOSPHERE CONDITIONS BELO W

– 16° C USE THE DATA FOR THE COLDEST

TEMPERATURE SHOWN IN THE TABLE.

NOTE:

THIS CHART IS CONSERVATIVE WHEN USED WITH THE FOLLOWING ENGINES AND PROPELLERS:

ENGINE (PRATT & WHITNEY) PT6A

- 67AG

PROPELLER (HARTZELL HUB MODEL AND BLADES)

PT6A

- 67AG HC

- B5MA

- 3 D / M11276NS (°C) SL 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000

-24



### - - - - 479 462 446 429 411 393 375

-20



### - - 503 488 472 455 439 421 404 386 345

-16 

### 527 512 497 481 465 448 432 414 396 355 307

-12 

### 520 505 490 474 458 442 425 407 370 321 269

-8 

### 514 499 484 468 451 435 418 388 334 282 231

-4 

### 508 493 477 461 445 428 400 347 294 243 192

0 

### 502 486 471 455 438 412 359 306 254 200 147

4 

### 496 480 464 448 413 369 316 262 209 156 103

8 

### 490 474 458 422 376 325 271 217 164 111 58

12 

### 484 468 432 382 331 279 226 172 119 66 14

16 

### 478 439 389 337 286 233 179 126 73 21 -32

20 

### 447 396 345 293 239 186 133 80 27

- -

24 

### 405 352 299 245 192 139 86

- - - -

28 

### 359 305 251 198 145

- - - - - -

32 

### 311 258 204

- - - - - - - -

36 

### 264

- - - - - - - - - -Report #: 

## ER

- 5 11 Title: 

## S2R

- T660/

- T660DC TRAINING MANUAL

Page: 

## 20 Revision: 

## A Date: 

## 11/25 /2013 FAA Project #: 

## N/A

RATE OF CLIMB

INTERNATIONAL STANDARD ATMOSPHERE

ENGINE (PRATT & WHITNEY) PT6A

- 60AG OR PT6A

- 45 SERIES

PROPELLER (HARTZELL HUB MODEL / BLADES) HC

- B5MP

- 3C / M

- 10876

ASSOCIATED CONDITIONS

POWER ... TAKEOFF

CONFIGURATION

WING FLAPS ... 15°

DISPERSAL EQUIPMENT ... LARGE SPREADER

GROSS WEIGHT ... 12500 LB

CALIBRATED AIR SPEED AT 50 FEET ... 1.2 Vs = 103 MPH

NOTE:

THIS CHART IS CONSERVATIVE WHEN USED WITH THE FOLLOWING ENGINES AND PROPELLERS:

ENGINE (PRATT & WHITNEY) PT6A

- 67AG

PROPELLER (HARTZELL HUB MODEL AND BLADES)

PT6A

- 67AG HC

- B5MA

- 3D / M11276NS OAT

(°C) SL 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000

-24 

### 472 459 445 431 417 403 388

-20 

### 492 479 466 453 439 426 411 397 363

-16 

### 511 499 486 474 461 447 434 420 405 370 330

-12 

### 505 493 481 468 455 442 428 414 383 341 297

-8 

### 500 488 476 463 450 436 422 397 352 308 265

-4 

### 495 483 471 458 444 431 408 362 318 275

0 

### 490 478 465 452 439 418 372 327 283

4 

### 486 473 460 447 418 381 335 290

8 

### 481 468 455 425 385 342 296

12 

### 476 463 433 390 347 303 257

16 

### 471 439 396 352 308 264

20 

### 445 402 358 313 268

24 

### 409 364 318 273

28 

### 369 323 277

32 

### 328 282 236

36 

### 287 PRESSURE ALTITUDE - FTReport #: 

## ER

- 5 11 Title: 

## S2R

- T660/

- T660DC TRAINING MANUAL

Page: 

## 21 Revision: 

## A Date: 

## 11/25 /2013 FAA Project #: 

## N/A

LANDING DISTANCE FRO M 50 FEET

INTERNATIONAL STANDARD ATMOSPHERE

ENGINE (PRATT & WHITNEY) PT6A

- 60AG, PT6A

- 45 SERIES

PROPELLER (HARTZELL HUB MODEL / BLADES) HC

- B5MP

- 3C / M

- 10876

ASSOCIATED CONDITIONS

POWER ... FLIGHT IDLE

CONFIGURATION

WING FLAPS ... 15°

DI SPERSAL EQUIPMENT ... STANDARD SPRAY

RUNWAY ... LEVEL HARD SURFACE

WIND ... ZERO

REVERSE THRUST ... NONE

CALIBRATED AIR SPEED AT 50 FEET ... NOTED

NOTE:

THIS CHART IS CONSERVATIVE WHEN USED WITH THE FOLLOWING ENGINES AND PROPELLERS:

ENGINE (PRATT & WHITNEY) PT6A

- 67AG

PROPELLER (HARTZELL HUB MODEL AND BLADES) HC

- B5MA

- 3D / M11276NS Airspeed

@ 50 Ft Gross

Weight

(MPH) (Lb) 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000

112 12500 3317 3400 3487 3576 3670 3766 3867 3971 4079 4191 4308

110 12000 3205 3285 3368 3454 3543 3636 3733 3833 3937 4044 4157

107 11500 3093 3169 3249 3332 3417 3506 3599 3695 3794 3897 4005

105 11000 2981 3054 3130 3209 3291 3376 3465 3556 3652 3751 3853

103 10500 2869 2939 3011 3087 3165 3246 3331 3418 3509 3604 3702

100 10000 2756 2823 2893 2964 3039 3116 3197 3280 3367 3457 3550

98 9500 2644 2708 2774 2842 2913 2986 3062 3142 3224 3309 3398

95 9000 2532 2593 2655 2719 2787 2856 2928 3003 3081 3162 3247

92 8500 2420 2477 2536 2597 2660 2726 2794 2865 2939 3016 3095

89 8000 2308 2362 2417 2475 2534 2596 2660 2727 2796 2868 2943

87 7500 2196 2246 2298 2352 2408 2466 2526 2589 2654 2721 2791

84 7000 2084 2131 2179 2230 2282 2336 2392 2451 2511 2574 2640

Standard

OAT ~

°C 15 13 11 9 7 5 3 1 -1 -3 -5 PRESSURE ALTITUDE - FTReport #: 

## ER

- 5 11 Title: 

## S2R

- T660/

- T660DC TRAINING MANUAL

Page: 

## 22 Revision: 

## A Date: 

## 11/25 /2013 FAA Project #: 

## N/A

LANDING DISTANCE FRO M 50 FEET

INTERNATIONAL STANDARD ATMOSPHERE

Airspeed

@50 Ft Gross

Weight PRESSURE ALTITUDE

- FT

(MPH) (Lb) 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000

112 12500 3069 3147 3228 3312 3398 3489 3582 3680 3781 3886 3995

110 12000 2964 3039 3117 3197 3281 3367 3457 3551 3648 3749 3853

107 11500 2860 2932 3006 3083 3163 3246 3332 3422 3515 3611 3712

105 11000 2755 2824 2895 2969 3045 3125 3207 3293 3382 34 74 3570

103 10500 2651 2716 2784 2854 2927 3003 3082 3164 3249 3337 3428

100 10000 2546 2608 2673 2740 2810 2882 2957 3035 3116 3200 3287

98 9500 2442 2501 2562 2626 2692 2761 2832 2906 2983 3062 3145

95 9000 2337 2393 2451 2512 2574 2639 2707 2777 284 9 2925 3004

92 8500 2232 2285 2340 2397 2456 2518 2582 2648 2716 2788 2862

89 8000 2128 2178 2229 2283 2339 2396 2456 2519 2583 2651 2720

87 7500 2023 2070 2119 2169 2221 2275 2331 2390 2450 2513 2579

84 7000 1919 1962 2008 2055 2103 2154 2206 2261 231 7 2376 2437

Standard

OAT ~



### ° C 15 13 11 9 7 5 3 1

- 1

- 3

- 5

ENGINE (PRATT &WHITNEY) PT6A

- 60AG, PT6A

- 45 SERIES

PROPELLER (HARTZELL HUB MODEL / BLADES) HC

- B5MP

- 3C / M

- 10876

ASSOCIATED CONDITIONS

POWER... FLIGHT IDLE

CONFIGUR ATION

WING FLAPS... 15°

DISPERSAL EQUIPMENT... LARGE SPREADER

RUNWAY ... LEVEL HARD SURFACE

WIND ... ZERO

REVERSE THRUST ... NONE

CALIBRATED AIR SPEED AT 50 FEET ... NONE

NOTE:

THIS CHART IS CONSERVATIVE WHEN USED WITH THE FOLLOWING ENGINES AND PROPELLERS:

ENGINE (PRATT & WHITNEY) PT6A

- 67AG

PROPELLER (HARTZELL HUB MODEL AND BLADES)

PT6A

- 67AG HC

- B5MA

- 3D / M11276NSReport #: 

## ER

- 5 11 Title: 

## S2R

- T660/

- T660DC TRAINING MANUAL

Page: 

## 23 Revision: 

## A Date: 

## 11/25 /2013 FAA Project #: 

## N/A

POWER SETTING CHART

PRATT AND WHITNEY PT6A

- 60AG AND PT6A

- 45 SERIES

INSTALLED THRUSH AIRCRAFT INC MODEL S2R

- T660

RATING TA KE OFF POWER

RPM 1700

The Chart Contains Torque Pressure ~ psi

Pressur

e

Altitude

(Ft.) Field

Barometric

Pressure

(In

- Hg) AMBIENT TEMPERATU RE ~ DEG. C

- 24

- 20

- 16

- 12

- 8

- 4 0 4 8 12 16 20 24 28 32 36

0 29.92

- - 38.8 38.8 38.8 38.8 38.8 38.

8 38.8 38.8 38.8 38.1 37.0 35.9 34.6 33.

4

2000 27.82

- 38.8 38.8 38.8 38.8 38.8 38.8 38.

8 38.8 38.2 3 7.1 36.0 34.9 33.7 32.5

-

4000 25.84 38.

8 38.8 38.8 38.8 38.8 38.8 38.8 38.

2 37.3 36.2 35.1 33.9 32.7 31.6

- -

6000 23.98 38.

8 38.8 38.8 38.8 38.8 38.4 37.4 36.

4 35.3 34.2 33.0 31.9 30.7

- - -

8000 22.23 38.

8 38.8 38.8 38.2 37.4 36.4 35.4 34.

4 33.2 32.1 31.1 29.9

- - - -

10,000 20.58 38.

8 38.1 37.2 36.3 35.5 34.6 33.5 32.

4 31.3 30.2 29.2

- - - - -

12,000 19.03 36.

4 35.7 34.8 34.0 33.2 32.2 31.3 30.

2 29.1 28.0

- - - - - -

NOTE : SHP = Torque Pressure (psi) x RPM

62.79

NOTE:

THIS CHART IS CONSERVATIVE WHEN USED WITH THE FOLLOWING ENGINES AND

PROPELLERS:

ENGINE (PRATT & WHITNEY) PT6A

- 67AG

PROPELLER (HARTZELL HUB MODEL AND BLADES)

PT6A

- 67AG HC

- B5MA

- 3D / M11276NSReport #: 

## ER

- 5 11 Title: 

## S2R

- T660/

- T660DC TRAINING MANUAL

Page: 

## 24 Revision: 

## A Date: 

## 11/25 /2013 FAA Project #: 

## N/A

POWER SETTING CHART

PRATT AND WHITNEY PT6A

- 60AG AND PT6A

- 45 SERIES

INSTALLED IN THE THRUSH AIRCR AFT INC MODEL S2R

- T660

RATING MAXIMUM CONTINUOUS POWER

RPM 1700

The Chart Contains Torque Pressure ~ psi

Pressur

e

Altitude

(Ft.) Field

Barometric

Pressure

(In

- Hg) AMBIENT TEMPERATURE ~ DEG. C

- 24

- 20

- 16

- 12

- 8

- 4 0 4 8 12 16 20 24 28 32 36

0 29.92

- - 37.7 37.7 37.7 37.7 37.

7 37.7 37.0 35.8 34.5 33.1 31.8 30.5 29.2 27.9

2000 27.82

- 37.7 37.7 37.7 37.7 37.7 37.

6 36.6 35.3 34.0 32.7 31.3 30 .0 28.7 27.4

-

4000 25.84 37.7 37.7 37.7 37.7 37.7 37.3 36.

1 34.8 33.6 32.2 30.9 29.6 28.3 27.0

- -

6000 23.98 37.7 37.7 37.7 37.7 36.7 35.5 34.

2 33.0 31.6 30.3 29.0 27.7 26.4

- - -

8000 22.23 37.7 37.7 36.8 35.8 34.6 33.4 32.

2 30.9 29.7 28.4 27.0 25.7

- - - -

10,000 20.58 36.7 35.8 34.9 33.8 32.6 31.4 30.

2 29.0 27.8 26.4 25.1

- - - - -

12,000 19.03 34.3 33.4 32.4 31.4 30.3 29.1 27.

9 26.7 25.3 24.0

- - - - - -

NOTE : SHP = Torque Pressure (psi) x RPM

62.79

NOTE:

THIS CHART IS CONSERVATIVE WHEN USED WITH THE FOLLOWING ENGINES AND

PROPELLERS:

ENGINE (PRATT & WHITNEY) PT6A

- 67AG

PROPELLER (HARTZELL HUB MODEL AND BLADES)

PT6A

- 67AG HC

- B5MA

- 3D / M11276NSReport #: 

## ER

- 5 11 Title: 

## S2R

- T660/

- T660DC TRAINING MANUAL

Page: 

## 25 Revision: 

## A Date: 

## 11/25 /2013 FAA Project #: 

## N/A

Miles

– Statute (SM)

Note: Chart Glide Distance With PROP FEATHERED

Flaps

- Up Ratio 10.8 : 1 ~ Multiply Altitude in Thousands Of Feet by 2.05 To Obtain No Wind Glide

Distance

Flaps

- Dn Ratio 9.6 : 1 ~ Multiply Altitude In Thousands Of Feet by 1.81 To Obtain No Wind Glide

Distance

Speed Schedule To Obtain L/D Max

– Speeds Are IAS in MPH

G.W. 14,000 13,000 12,000 11,000 10,000 9,0 00 8,000 7,000

Flaps

- Up 111 107 103 99 94 89 84 78

Flaps

- Dn 99 94 92 90 84 80 75 70

NOTE: For Large Transland Spreader P/N 95370

Chart Glide Distance With PROP FEATHERED, Same Schedule

Flaps

- Up Ratio 9.6 : 1 ~ Multiply Altitude In Thousands Of F eet By 1.81 To Obtain No Wind Glide

Distance

Flaps

- Dn Ratio 8.7 : 1 ~ Multiply Altitude In Thousands Of Feet By 1.64 To Obtain No Wind Glide

Distance FLAPS

- UP GLIDE DISTANCE

S2R

- T660



## 0 5 10 15 20 5 10 12

25

20.5 10.25 24.6Altitude–1,000Report #: 

## ER

- 5 11 Title: 

## S2R

- T660/

- T660DC TRAINING MANUAL

Page: 

## 26 Revision: 

## A Date: 

## 11/25 /2013 FAA Project #: 

## N/A



## CHAPTER 6: HANDLIN G CHARACTERISTICS

The handing characteristics of the S2R

- T660 are similar to the handling characteristics

of other Thrush Aircraft models, and are typical of many other large, turbine

- powered

tailwheel aircraft. Obviously, variables such as hopper load, fuel load, loaded c.g., wind,

runway conditions and construction, and atmospheric c onditions will affect the handling

characteristics of the aircraft. It is suggested that the first few flights be made at lower

takeoff weights with mid

- range loaded c.g., and in relatively calm wind conditions. As

experience and proficiency allow, takeoff weights may be increased and the c.g. range

may be expanded to gain well

- rounded knowledge of the handling characteristics of the

aircraft in all flight, loading, and atmospheric conditions.Report #: 

## ER

- 5 11 Title: 

## S2R

- T660/

- T660DC TRAINING MANUAL

Page: 

## 27 Revision: 

## A Date: 

## 11/25 /2013 FAA Project #: 

## N/A



## CHAPTER 7: PILOT D OCUMENTATION

Before receiving Factory Autho rized training, the following documentation must be on

file with Thrush Aircraft , Inc.:

1. FAA Commercial Pilot Certificate (or higher)

2. Current 2nd Class Medical Certificate.

3. A logbook entry showing compliance with 14 CFR 61.31(i) ( tailwheel

e ndorsement)

.

4. A logbook entry showing compliance with 14 CFR 61.56 (BFR)

.

5. Written documentation of all previous ag, fire

- bombing, and/or turbine

tailwheel e xper ienceReport #: 

## ER

- 5 11 Title: 

## S2R

- T660/

- T660DC TRAINING MANUAL

Page: 

## 28 Revision: 

## A Date: 

## 11/25 /2013 FAA Project #: 

## N/A



## CHAPTER 8: PILOT T YPE RATING REQUIREME NT FOR

THRUSH AIRCRAFT, INC.

Reference: FAR 61. 3 1 (a) (1)

Thrush Aircraft, Inc. is the manufacturer of the S2R Thrush series of turboprop

agricultural aircraft. This letter and enclosed documentation represents our

PETITION for an exemption of CFR 14, Section 61.31 (a) (1) for our model S2R

T660 aircraft.

A lternative to Type Rating Process:

As an alternative to the type rating process, Thrush Aircraft, Inc. would like to

propose the exemption include the following:

1. This exemption would be applicable to only Model S2R

- T660 aircraft that are

certified in restr icted category and operated under procedures outlined in 14

CFR, FAR Part 137.

2. At the time of delivery, qualified pilots will receive complete transitional training in

the aircraft by a Thrush Aircraft, Inc. (TIA) authorized pilot who meets the

following m inimum qualifications:

a. Hold at least a commercial pilot certificate; and

b. Meet the following experience requirements:

i. 500 hours of flight time in turbine

- powered agricultural type

airplanes:

or

ii. 1,000 hours of flight time in agricultural type airplanes which

includes at least 100 hours flight time in a S2R

- T660.

3. Thrush Aircraft, Inc. (TIA) will make a copy of this exemption available to each

pilot who serves as PIC in the S2R

- T660.

4. Thrush Aircraft, Inc. (TIA) will authorize certain pilots in the field, who me et the

qualification requirements of Item #3, to conduct transition training for S2R

- T660

operators.

Transition Training:

Prior to training, a complete review and inspection of the pilots flying credentials and

qualifications, including licenses and logb ook to assure the pilot meets the minimum

requirements for the transitional training.

1. The training syllabus includes the following list of items:

a. A copy of the ER

- 511 S2R

- T660/T660DC Training Manual.

b. A copy of the Aircraft Flight Manual.

c. A separate Checkli st for all Normal and Emergency Procedures.

d. A training syllabus which includes classroom and cockpit training

schedules.Report #: 

## ER

- 5 11 Title: 

## S2R

- T660/

- T660DC TRAINING MANUAL

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e. Projected images of the training manual and flight manual will be used as

training aids during the classroom session of training.

f. A 50 question test will be administered after completion of classroom

training and before the commencement of cockpit familiarization training.

g. Cockpit training will include familiarization of all controls, guidance

systems, placards and practical training of a ll normal and emergency

procedures.

2. Records

– The following records of training for each pilot will be retained

indefinitely by Thrush Aircraft:

a. Copies of Pilots licenses and ratings.

b. Log of Training Attendance.

c. Copy of Written Test Results.

d. Copy of logbo ok record of training.

e. Copy of Certificate of Course Accomplishment.

Conclusion

It is our goal to provide qualified pilots with transitional training which will assure a

thorough understanding of the S2R

- T660, including systems, flight characteristics

and procedures.Report #: 

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## APPENDIX A :

S2R

- T660 AIRCRAFT TRANSI TION COURSE SYLLABUS

This course is for experienced agricultural pilots from other high performance

agricultural aircraft into the S2R

- T660 Turbo Thrush. The goal of this course is to

provide a thorough un derstanding of the aircraft systems, normal and emergency

procedures, and flight characteristics of the PT6A

- 60AG and PT6A

- 65AG powered

S2R

- T660. It is satisfies the requirements for an the exemption from FAR

61.31(a)(1), Type Ratings for Large Aircraft.



## CLASSROOM TRAINING

Classroom training will be approximately 5 hours consisting of the following:

1. 

### A thorough review and familiarization of all limitations, normal procedures,

emergency procedures, weight & balance and performance.

2. Discussion of aircraft an d it’s systems with emphasis on differences from other

aircraft in flight characteristics, performance and procedures.

Material Provided :

1. S2R

- T660 Training Manual

2. Individual Copy of Flight Manual

3. Normal and Emergency Procedures Checklist

4. 50 Question Writte n Test

Schedule;

Session 1: Introduction and Comparison of Procedures and Flight Characteristics to Other

S2R Models and Systems.

Session 2: Aircraft Systems (training manual).

Session 3: Aircraft Limitations (aircraft flight manual).

Session 4: Normal Pro cedures (training manual and aircraft flight manual).

Session 5: Emergency Procedures (training manual and aircraft flight manual).

Session 6: Performance Including Weight & Balance (training manual and aircraft flight

manual).

Session 7: Written Test (50 questions on aircraft flight manual) and review.



## COCKPIT TRAINING

Cockpit Training will consist of the following;

1. A complete walk

- inspection of the aircraft emphasizing the controls and systems.

2. A Thorough review of the cockpit including operation o f controls, instrumentation,

placards and limitations.

3. Familiarization with, and practice of, all normal and emergency procedures.

Materials provided:

1. Individual Copy of Flight Manual

2. Flight Manual

3. Normal and Emergency Procedures Checklist

4. O ne S2R

- T660 AircraftReport #: 

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Schedule:

Session 1: Walk

- Around Inspection and Familiarization with Aircraft Systems.

Session 2: Cockpit Familiarization including Placards Controls, Flight Instrumentation and

Limitations.

Session 3: Normal Procedures.

Session 4: E mergency Procedures

Session 5: ReviewReport #: 

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## APPENDIX B:

MODEL TURBO THRUSH S 2R

- T660 WRITTEN EXAM

NAME:

____________________ DATE: GRADE:

________

1. What type of fuel may be used for the T660?

A. Je t A or Jet B

B. JP4

C. JP5

D. All of the above

2. If jet fuel or diesel fuel is not available, aviation gasoline MIL

- G

- 5572 (all grade s)

may be used for a maximum of hrs between overhauls.

A. 100 hrs

B. 2,500 hrs

C. 150 hrs

D No Time Limit

3. What is the maximum torque (PSI) allowable for take

- off for the PT6A

- 65AG?

A. 38.7

B. 43.5

C. 45.07

D. 61.0

4. What is the maximum continuous ITT and NG% for the PT6A

- 65AG?

A. 810 ° C and 104%

B. 715 ° C and 100%

C. 870 ° C and 106%

D. 1000 ° C and 104%

5. Minimum g round idle RPM and maximum idle ITT for the PT6A

- 65AG are

A. 56% and 600 o 

### C

B. 58% and 750 o 

### C

C. 61% and 810 o 

### C

D. 69% and 715 o 

### C

6. Minimum idle oil pressure is _____ psig.

A. 60

B. 60

– 90

C. 90

– 135

D. 90Report #: 

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7. At 56%

- 68% Ng. Maximum ITT is 870 degrees.

A. True

B. False

8. What is the maximum ITT transient engine limits for starting?

A. 1000  C

- 5 seconds

B. 1000  F

- 3 seconds

C. 800  C

- 5 seconds

D. 800  F

- 3 seconds

9. Maximum transient engine acceleration limits for Tq., ITT and Np are:

A. 60.98 psi, 850 o 

### C, and 1870 rpm.

B. 45.4 psi, 870 o 

### C and 1800 rpm

C. 58 psi, 810 o 

### C and 1700 r pm

D. Same as Takeoff and Max Continuous limits

10. Transient engine limits are maximum of ________ for starting.

A. 1 minute

B. 30 seconds

C. 5 seconds

D. No transient time limits so long as pilot pulls the power lever back after he is

out of s ituation where transient range is required.

11. The minimum Idle engine oil pressure is __________ psig.

A. 90

B. 60

C. 40

D. 56

12. The Minimum Oil Pressure for Takeoff, Max Continuous & Max Cruise/Climb is:

A. 60 psig.

. B. 90 psig.

C. 40 psig.

D. 56 psig.

13. What is the maximum starter duration and minimum cooling period between

starting attempts?

A. 30 seconds and 3 minutes.

B. 3 minutes and 1 minute.

C. 1 minute and 3 minutes.

D. None of the above.Report #: 

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14. Normal air starts on the PT6A

- 65AG can be accomplished at what airspeeds?

A. 75 to 150 MPH

B. Above 148 MPH

C. There is no airspeed limitation for air starts

D. Air starting is impossible

15. Veolocity Never Exceed (V NE 

### ) is :

A. 219 Knots

B. 169 mph

C. 219 mph

D. 225 mph

16. Max S tructural Cruising Speed (V NO 

### ) is :

A. 219 mph

B. 206 mph

C. 160 mph

D. 143 mph

17. What is maneuvering speed (V A 

### )?

A. 219 mph

B. 206 mph

C. 160 mph

D. 143 mph

18. Max Flap Extended Speed (V FE 

### ) is :

A. 219 mph

B. 206 mph

C. 160 knots

D. 143 mph

19. Never e xce ed speed at 12,500 lbs. and abo v e is :

A. 160 mph

B. 219 mph

C. 160 mph

D. 143 mph

20. Maximum approved altitude is ________ feet.

A. 12,000

B. 24,000

C. 36,000

D. No altitude limitations.Report #: 

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21. Design load factors of S2R

- T65 at 12,500 lbs. and above are:

A. 3.17 positive, 1.27 negative

– Flaps Up

B. 3.25 positive, 1.3 negative

– Flaps Up

C. 2.0 positive, 0.8 negative

– Flaps Down

D. 3.17 positive, 0.8 negative

– Flaps Down

E. Both A & C above

22. What is (are) maximum take

- off and landing weight?

A. 14,150 lbs. and 12,500 lbs.

B. 12,500 lbs. and 7300 lbs.

C. 12,500.

D. None of the above

23. Forward and Aft CG Limits at 14,150 lbs. are:

A. 25.9 and 30 inches.

B. 24 and 25.9 inches.

C. 27 and 30 inches inches

D. 27 and 29 inches

24. Forwa rd CG Limit at 12,500 lbs. and Aft Limit at 8,000 lbs. are:

A. 24 and 30 inches.

B. 27.0 and 29.0 inches.

C. 25.9 and 29.0 inches

D. 24 and 27.0 inches

25. Flight operation of the S2R

- T660 is day and night VFR and IFR.

A. True

B. False

26. Flight into known icing is approved only in very light conditions.

A. True

B. False

27. Stabilized Propeller RPM prohibited during ground operation is:

A. 1170 to 1400

B. Below 900 RPM

– Except Feathered Operation from 0 to 400 RPM.

C. 0 to 400

D. A and B Above

28. T akeoff into visible moisture below 40 Degrees F. is allowed providing no ice is

forming.

A. True

B. FalseReport #: 

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29. Electronic Boost Pump and Manual Ignition should be turned on prior to:

A. entering heavy rains

B. encountering severe turbulence

C. takeoffs and landings

D. all of the above

30. What is the usable fuel for each main tank?

A. 228 gallons

B. 114 gallons

C. 70 gallons

D. 150 gallons

31. Pull control stick aft to unlock tailwheel:

A. True

B. False

32. Hopper structural capacity is 5,500 lbs.

A. True

B. False

33. The dual cockpit rear seat cargo limitation is _____________.

A. 170 Lbs.

B. 200 Lbs.

C. 250 Lbs.

D. No rear seat limitation so long as weight & balance within aft limits.

34. Which propeller operating range is prohibited on the ground?

A. 0 to 1700 R PM

B. 1400 to 1698 RPM

C. 1400 to 1700 RPM

D. 1170 to 1400 RPM

35. Stabilized operation below _____ RPM is prohibited on the ground.

A. 400

B. 900

C. 1170

D. 1400

36. Minimum Airspeed for Normal Air Starts is:

A. 160 mph

B. 118 mph

C. 148 mph

D. 143 mph

37. Minimum fuel inlet pressure when fuel auxiliary pump switch is on before engine

start is 5 PSIG.Report #: 

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A. True

B. False

38. Minimum Gas Generator (NG) speed to obtain a satisfactory engine start is:

A. 10% for airstarts or 12% for ground starts

B. 14% to 18%

C. 13%

D. No t stated in the AFM or Checklist.

39. According to Normal Procedures, whenever the gas generator fails to light up within

10 seconds after moving the starting control lever to the run low idle position; cut off

the fuel, starter switch and ignition switch

.

A. True

B. False

40. During start, if the gas generator fails to light within 10 seconds, cut off fuel, starter

and ignition. Allow a 30 second fuel draining period followed by a 30 second dry

motoring run before attempting another start.

A. True

B

. False

41. Before ground run

- up, feathering the propeller once or twice with the throttle in the

idle position will purge the propeller system.

A. True

B. False

42. During t axi

, the Propeller Control should be:

A. Anywhere in operating range.

B. Against the feather latch with the fuel lever in high idle position.

C. Full forward with the fuel lever in low idle position.

D. Against the feather latch with the fuel lever in low idle position.

43. The maximum observed propeller RPM during over

- speed governor chec k is

___________.

A. 1598 RPM

B. 1598 + 20 RPM

C. 1698 + 20 RPM

D. 1700 + 20 RPM

44. Before Take

- Off set the Fuel Lever at High Idle and Check at ______ NG.

A. 58%

B. 68%

C. 69%

D. 104%

45. Ignition and auxiliary fuel pump are not required during takeoff at sea level.

A. True

B. FalseReport #: 

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46. During c limb, allow airspeed to build up to ______ with flaps up.

A. 87 MPH

B. 94 MPH

C. 107 MPH

D. 110 MPH

47. Allow the engine to stabilize below 650 I.T.T. before shutdown:

A. For 1 minute

B. For 2 minutes

C

. For 3 minutes

D. None of the above

48. When the aircraft is left unattended, be sure that the propeller is tied down to

prevent the propeller:

A. from striking an innocent bystander.

B. from turning the wrong direction and damaging the starter generator.

C. fro m windmilling with zero oil pressure.

D. All the above.

49. With 30 ° bank angle, 0 flaps, and power off, the stall speed is:

A. 99 mph @ 12,500 lbs.

B. 99 mph @ 14,150 lbs.

C. 124 mph @ 12,500 lbs.

D. 130 mph @ 14,150 lbs.

50. With 60 ° bank angle, 0 flaps, and power off, the stall speed is:

A. 92mph @ 12,500 lbs.

B. 92 mph @ 14,150 lbs.

C. 95 mph @ 12,500 lbs.

D. 130 mph @ 15,150 lbs.Report #: 

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## APPENDIX C:

PILOT TRAINING RECOR D CHECKLIST SHEET

Instructor

_________________________________

Pilot Name

_________________________________

Course Name

_________________________________

Attendance Date

______________

Pilot Documentation:

1. Licenses 

2. Current Medical Certificate 

3. Most Recent Biannual Flight Review 

4. Record of Pilot Experience 

Log of Training Attendance. 

Copy of Written Test Results. 

Copy of logbook record of training. 

Copy of Certificate of Course Accomplishment. Report #: 

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## APPENDIX D: TRAINING ATTENDANCE RECORDReport #: 

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## N /AReport #: 

## ER

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## D 3 Revision: 

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## N /A