P.O. Box 3149 

.. II I I. i I t:J I I Albany, GA 31706-3149 ENGINEERING 300 Old Pretoria Road 

Albany, GA 31721 •• ,,~l'£1•• REPORT 

Phone: 229.883.1440 

Fax: 229.439.970 A I R c R A F T ER-511 

www .thrushaircraft.com 

By: ED RUSK, JR. FAA Proiect # Paoe: i 

Checked: .JIM ALMAN N/A Revision: A 

Approved: ,Jr!rrt?trCO Date: 11/25/2013 

ENGINEERING REPORT 

ER-511 

S2R-T660 I T660DC 

TRAINING MANUAL 
Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:! ii Revision: A Date: I 11/25/20131 FAA Project#: I NJA 

LOG OF REVISIONS 

Rev. Page Description of Revision B}': 

IR ALL New Document Initial Release Ed Rusk 

9/3/2013 

28-29 Added 

Requirements 

Chapter 

(Reference: 

8: Pilot Type 

FAR 

Rating 

61.31 (a][1]) a~ 

1¢-s?/s 

A1-A2 Added Appendix A: S2R-T660 Aircraft 

Transition Course Syllabus 

A 81-87 Added Appendix 8: Model Turbo Thrush S2RT660 Written Exam with answers 

C1 Added Appendix C: Pilot Training Record 

Checklist 

01-03 Added Appendix D: Training Attendance 

Record. 
Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

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TABLE OF CONTENTS 

Subject: 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 CHARACTERISTICS •••••••••••••••••••••••••••••••••••••••••••••••••••••• 26 

CHAPTER 7: PILOT DOCUMENTATION ••••••••••••••••.••••••••••••••••••••••••••••.••••••••••••••• 27 

CHAPTER 8: PILOT TYPE RATING REQUIREMENT THRUSH AIRCRAFT, INC ••••••• 28 

APPENDIX A: S2R-T660 AIRCRAFT TRANSITION COURSE SYLLABUS •••••••••••••••••• Al 

APPENDIX B: MODEL TURBO THRUSH S2R-T660 WRITTEN EXAM ••••••••••••••••••••• Bl 

APPENDIX C:_PILOT TRAINING RECORD CHECKLIST SHEET •••.••••••••••••••••••••••••••••. Cl 

APPENDIX D: TRAINING ATTENDANCE RECORD ••••••••••••••••••••••••••••••••••••••••••••••• Dl 
Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

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PREFACE 

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

Aircraft S2R-T660 I S2R-T660DC aircraft. The Training Program meets the 

requirements of the United States of America 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. 
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CHAPTER 1: INTRODUCTION 

The systems of the Thrush Aircraft S2R-T660 I S2R-T660DC aircraft are similar to 

those systems found in other models 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 Trim 
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CHAPTER 2: AIRCRAFT SYSTEMS 

The S2R-T660 I 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, Airspeed 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 conditioning, 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 

itsequipment. 
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CHAPTER 3: OPERATIONAL 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 all 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- ON 
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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 

11 a. Fuel Quantity- CHECK visually and SECURE cap 

NOTE 

N/A 

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

on the oil dipstick. 

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. 

15. Wing Tip- CHECK for damage 

16. Wing Leading Edge- CHECK for damage 

17. Stall Vane- CHECK condition 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. 

(4) 

18. Wing Tie Down - REMOVE 

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

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. Firewall 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 for freedom of 

operation 

27. Air Filter- CHECK for cleanliness and condition 
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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 leaks 

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 

33. Right Wing Sump- DRAIN 

33a Right Fuel Vent Sump- DRAIN 

34. Main Wheel Tire and Brake- CHECK for inflation, damage, and wear 

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. 

(8) 

(9) 

36. Pitot Mast - CHECK for blockage of opening 

37. Wing Tie Down -REMOVE 

38. Wing Tip- CHECK for damage 

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- CHECK 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 

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 for condition 
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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 position (Take-off) and 

excessive play 

51. Tail Tie-Down- REMOVE 

52. Static Port Opening - CHECK for blockage 

(1 0) FOR DUAL COCKPIT AIRCRAFT ONLY 

53. Rear Cockpit Area - CHECK and SECURE area 

BEFORE STARTING ENGINE 

1. Visual Inspection- COMPLETE 

2. Seat- ADJUST 

3. Rudder Pedals- 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 I BETA STOP 

3. Propeller Lever- FEATHER 

4. Fuel Condition 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 seconds 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-turbine starting limit is not exceed. 
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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. Generator- 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 that 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 

WARNING I 

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

close the fuel system shutoff valve immediately and continue motoring. 
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TAXI 

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 cooling period for the starter before going any further with the starting 

operation. 

1. Propeller lever- against feather latch (See Page 1-7 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 following 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 . 

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

: . : CAUTION : 

•.•..•............•. ~ 

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 
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11. Prior to any flights, 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 limitations. 

(See the Limitations Section) 

3. After take-off ACCELERATE to the best-rate-of-climb airspeed of 117 mph lAS, for 

flaps down. 

CLIMB 

1. MAINTAIN maximum continuous power. 

2. Flaps - RETRACT 

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

LANDING 

1. Airspeed on Final- MAINTAIN 82 MPH with hopper empty 

2. Wing Flaps- SET 15 degrees 

3. Touchdown- Main Wheels 
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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 smoothly 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 RUNWAY 

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 1-7 for Propeller Ground Operation 

Limits) 

ENGINE SHUTDOWN 

1. Parking Brake - SET 

2. PowerLever-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. Generator Switch- OFF 

NOTE 

During the shutdown be sure that the compressor decelerates freely. 

WARNING I 
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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 AIRCRAFT 

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. Hydraulic 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 or short in the opening switch. 

The computer considers the "82" warning as a critical error, and 

will suspend all other operations until it is cleared. 

6. Select operating Mode 

7. Set - Level 
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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 doorplace switch in close position momentarily. 

r······~~~;;~~········~ 

'······························ 

The manual switch should only be used momentarily to prevent system damage. 
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CHAPTER 4: EMERGENCY PROCEDURES 

GROUND ENGINE FIRE 

See Dry Motoring Run in Section II. 

ENGINE FIRE IN FLIGHT 

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 FLIGHT 

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 flameout 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 restored 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 111-2. 

NORMAL AIR STARTS 

NOTE 

Air Start Envelope - Normal Air Starts ranging from sea level to 12,000 feet 

altitude and above 148-MPH lAS 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 through the engine, and; therefore increase the 

gas generator motoring speed during the Air Start procedure. 
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2. PowerLever-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 PSIG 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 generator 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 RPM: 

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 initiate 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 successfully 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 FLIGHT 

1. Battery Switch and Generator Switch - OFF 

2. All other Electrical Switches - OFF 

3. Circuit Breakers- CHECK to identify faulty circuit, if possible. 
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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 to 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 necessary 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 AIRCRAFT: 

If it is not 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 

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

: CAUTION : ~ ...............• 

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 Handle. 
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CHAPTERS: PERFORMANCE 

POWER OFF STALL SPEEDS 

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 CONDITIONS 

Power 

Configuration 

Wing Flaps 

Dispersal Equipment 

Stall Entry Rate 

Gross Weight 

Off 

Clean T.O./Landing 

0 Degrees 15 Degrees 

Std. Spray or Std. Spray or 

Large Spreader Large Spreader 

Uniformly Decreasing 

14,150 pounds 

POWER OFF STALL SPEEDS- MPH (lAS) 

Bank Angle 

0 

30 

60 

Flaps-0 Degrees 

94 

101 

133 

SPEED FOR BEST RATE-OF-CLIMB 

Flaps-15 Degrees 

90 

97 

127 

Flaps 0 Degrees - 122 MPH lAS Flaps 15 Degrees - 117 MPH lAS 

AIRSPEED CALl BRA TION MPH 

FLAPS 0 DEGREES lAS 80 100 120 140 160 180 200 

CAS 82 102 122 142 161 181 201 

FLAPS 15 DEGREES lAS 80 100 120 140 156 

CAS 82 102 122 142 154 

221 

222 
Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:! 17 Revision: A Date: I 11/25/20131 FAA Project#: I N/A 

TAKEOFF DISTANCE- FEET 

INTERNATIONAL STANDARD ATMOSPHERE 

ENGINE (PRATT & WHITNEY) 

PROPELLER (HARTZELL HUB MODEL I BLADES) 

ASSOCIATED CONDITIONS 

POWER ... 

CONFIGURATION 

WING FLAPS ... 

DISPERSAL EQUIPMENT ... 

GROSS WEIGHT ... 

RUNWAY ... 

WIND ... 

REVERSE THRUST ... 

CALIBRATED AIR SPEED AT 50 FEET ... 

NOTE: 

PT6A-60AG, PT6A-45 Series 

HC-B5MP-3C I M-10876 

TAKEOFF 

15° 

STANDARD SPRAY 

14150 LB 

LEVEL HARD SURFACE 

ZERO 

NONE 

1.2 Vs = 110 MPH 

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 FOLLOWING ENGINES AND 

PROPELLERS: 

ENGINE (PRATT & WHITNEY) PT6A-67AG 

PROPELLER (HARTZELL HUB MODEL AND BLADES) 

PT6A-67AG HC-B5MA-3D I M11276NS 
Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:! 18 Revision: A Date: I 11/25/20131 FAA Project#: I 

TAKEOFF DISTANCE - FEET 

INTERNATIONAL STANDARD ATMOSPHERE 

TAKE OFF DISTANCE - FT 

ENGINE (PRATI &WHITNEY) 

PROPELLER (HARTZELL HUB MODEL I BLADES) 

ASSOCIATED CONDITIONS 

NOTE: 

POWER. .. 

CONFIGURATION 

WING FLAPS ... 

DISPERSAL EQUIPMENT ... 

GROSS WEIGHT ... 

RUNWAY ... 

WIND ... 

REVERSE THRUST 

CALIBRATED AIR SPEED AT 50 FEET... 

PT6A-60AG, PT6A-45 SERIES 

HC-B5MP-3C I M-10876 

TAKEOFF 

15° 

LARGE SPREADER 

12500 LB 

LEVEL HARD SURFACE 

ZERO 

NONE 

1.2Vs = 110 MPH 

N/A 

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

ENGINE (PRATI & WHITNEY) PT6A-67AG 

PROPELLER (HARTZELL HUB MODEL AND BLADES) 

PT6A-67AG HC-B5MA-3D I M11276NS 
Regort #: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

PageJ 19 Revision: A Date: I 11/25/20131 FAA Project#: I N/A 

RATE OF CLIMB 

12 

16 

20 

24 

28 

32 

36 

INTERNATIONAL STANDARD ATMOSPHERE 

484 468 

478 439 

447 396 

405 352 

359 

311 

264 

ENGINE (PRATT & WHITNEY) 

PROPELLER (HARTZELL HUB MODEL I BLADES) 

ASSOCIATED CONDITIONS 

POWER ... 

CONFIGURATION 

WING FLAPS ... 

DISPERSAL EQUIPMENT ... 

GROSS WEIGHT ... 

CALIBRATED AIR SPEED AT 50 FEET ... 

NOTE: 

PT6A-60AG, PT6A-45 SERIES 

HC-B5MP-3C I M-10876 

TAKEOFF 

15° 

STANDARD SPRAY 

14150LB 

1.2 Vs = 110 MPH 

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 FOLLOWING ENGINES AND PROPELLERS: 

ENGINE (PRATT & WHITNEY) PT6A-67AG 

PROPELLER (HARTZELL HUB MODEL AND BLADES) 

PT6A-67AG HC-B5MA-3D I M11276NS 
Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:! 20 Revision: A Date: J 11/25/20131 FAA Project#: I N/A 

RATE OF CLIMB 

INTERNATIONAL STANDARD ATMOSPHERE 

ENGINE (PRATT & WHITNEY) 

PROPELLER (HARTZELL HUB MODEL I BLADES) 

ASSOCIATED CONDITIONS 

PT6A-60AG OR PT6A-45 SERIES 

HC-B5MP-3C I M-10876 

POWER ... 

CONFIGURATION 

WING FLAPS ... 

DISPERSAL EQUIPMENT ... 

GROSS WEIGHT ... 

CALIBRATED AIR SPEED AT 50 FEET ... 

NOTE: 

TAKEOFF 

15° 

LARGE SPREADER 

12500 LB 

1.2 Vs = 103 MPH 

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

ENGINE (PRATT & WHITNEY) PT6A-67AG 

PROPELLER (HARTZELL HUB MODEL AND BLADES) 

PT6A-67 AG HC-B5MA-3D I M11276NS 
Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:! 21 Revision: A Date: I 11/25/20131 FAA Project#: I N/A 

LANDING DISTANCE FROM 50 FEET 

INTERNATIONAL STANDARD ATMOSPHERE 

Airspeed Gross PRESSURE ALTITUDE - FT @50Ft Vleight 

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

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

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

107 11501l 3093 3169 3249 3332 3417 3506 3599 3695 3794 3897 

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

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

10Jl 10000_ 2756 2823 2893 2964 3039 3116 3197 3280 3367 3457 

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

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

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

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

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

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

Standard 

OAT-

·c 15 13 11 9 7 5 3 1 -1 -3 

ENGINE (PRATT & WHITNEY) 

PROPELLER (HARTZELL HUB MODEL I BLADES) 

ASSOCIATED CONDITIONS 

PT6A-60AG, PT6A-45 SERIES 

HC-B5MP-3C I M-10876 

POWER ... CONFIGURATION 

WING FLAPS ... DISPERSAL EQUIPMENT ... RUNWAY ... WIND ... REVERSE THRUST ... CALIBRATED AIR SPEED AT 50 FEET ... 

NOTE: 

FLIGHT IDLE 

15° 

STANDARD SPRAY 

LEVEL HARD SURFACE 

ZERO 

NONE 

NOTED 

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 I M11276NS 

10000 

4308 

4157 

4005 

3853 

3702 

3550 

3398 

3247 

3095 

2943 

2791 

2640 

-5 
Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:! 22 Revision: A Date: I 11/25/20131 FAA Project#: I 

LANDING DISTANCE FROM 50 FEET 

INTERNATIONAL STANDARD ATMOSPHERE 

Airspeed Gross 

@50Ft Weight PRESSURE ALTITUDE - FT 

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

112 12500 3069 3147 3228 3312 3398 3489 3582 3680 3781 

110 12000 2964 3039 3117 3197 3281 3367 3457 3551 3648 

107 11500 2860 2932 3006 3083 3163 3246 3332 3422 3515 

105 11000 2755 2824 2895 2969 3045 3125 3207 3293 3382 

103 10500 2651 2716 2784 2854 2927 3003 3082 3164 3249 

100 10000 2546 2608 2673 2740 2810 2882 2957 3035 3116 

98 9500 2442 2501 2562 2626 2692 2761 2832 2906 2983 

95 9000 2337 2393 2451 2512 2574 2639 2707 2777 2849 

92 8500 2232 2285 2340 2397 2456 2518 2582 2648 2716 

89 8000 2128 2178 2229 2283 2339 2396 2456 2519 2583 

87 7500 2023 2070 2119 2169 2221 2275 2331 2390 2450 

84 7000 1919 1962 2008 2055 2103 2154 2206 2261 2317 

Standard 

OAToc 15 13 11 9 7 5 ' 3 1 -1 

ENGINE (PRATT &WHITNEY) 

PROPELLER (HARTZELL HUB MODEL I BLADES) 

ASSOCIATED CONDITIONS 

PT6A-60AG, PT6A-45 SERIES 

HC-B5MP-3C I M-10876 

NOTE: 

POWER ... CONFIGURATION 

WING FLAPS ... DISPERSAL EQUIPMENT ... 

RUNWAY ... WIND ... REVERSE THRUST ... CALIBRATED AIR SPEED AT 50 FEET ... 

FLIGHT IDLE 

15° 

LARGE SPREADER 

LEVEL HARD SURFACE 

ZERO 

NONE 

NONE 

N/A 

9000 

3886 

3749 

3611 

3474 

3337 

3200 

3062 

2925 

2788 

2651 

2513 

2376 

-3 

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 I M11276NS 

10000 

3995 

3853 

3712 

3570 

3428 

3287 

3145 

3004 

2862 

2720 

2579 

2437 

-5 
Pressur 

e 

Altitude 

(Ft.) 

0 

2000 

4000 

6000 

8000 

10,000 

12,000 

Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:! 23 Revision: A Date: l 11/25/20131 FAA Project#: I N/A 

POWER SETTING CHART 

PRATT AND WHITNEY PT6A-60AG AND PT6A-45 SERIES 

INSTALLED THRUSH AIRCRAFT INC MODEL S2R-T660 

RATING TAKE OFF POWER 

RPM 1700 

The Chart Contains Torque Pressure - psi 

Field AMBIENT TEMPERATURE Barometric 

Pressure 

(ln-Hg) 

-24 -20 -16 -12 -8 -4 

29.92 - - 38.8 38.8 38.8 38.8 

27.82 - 38.8 38.8 38.8 38.8 38.8 

25.84 38. 38.8 38.8 38.8 38.8 38.8 

8 

23.98 38. 38.8 38.8 38.8 38.8 38.4 

8 

22.23 38. 38.8 38.8 38.2 37.4 36.4 

8 

20.58 38. 38.1 37.2 36.3 35.5 34.6 

8 

19.03 36. 35.7 34.8 34.0 33.2 32.2 

4 

NOTE: SHP = Torque Pressure (psi) x RPM 

62.79 

NOTE: 

0 4 

38.8 38. 

8 

38.8 38. 

8 

38.8 38. 

2 

37.4 36. 

4 

35.4 34. 

4 

33.5 32. 

4 

31.3 30. 

2 

- DEG.C 

8 12 16 

38.8 38.8 38.8 

38.8 38.2 37.1 

37.3 36.2 35.1 

35.3 34.2 33.0 

33.2 32.1 31.1 

31.3 30.2 29.2 

29.1 28.0 -

20 24 

38.1 37.0 

36.0 34.9 

33.9 32.7 

31.9 30.7 

29.9 -

- -

- -

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 I M11276NS 

28 32 36 

35.9 34.6 33. 

4 

33.7 32.5 -

31.6 - -

- - -

- - -

- - -

- - -
Pressur 

e 

Altitude 

(Ft.) 

0 

2000 

4000 

6000 

8000 

10,000 

12,000 

Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:l 24 Revision: A Date: I 11/25/20131 FAA Project #: I N/A 

POWER SETTING CHART 

PRATT AND WHITNEY PT6A-60AG AND PT6A-45 SERIES 

INSTALLED IN THE THRUSH AIRCRAFT INC MODEL S2R-T660 

RATING MAXIMUM CONTINUOUS POWER 

RPM 1700 

The Chart Contains Torque Pressure - psi 

Field AMBIENT TEMPERATURE - DEG. C 

Barometric 

Pressure 

(ln-Hg) -24 -20 -16 -12 -8 -4 0 4 8 12 16 20 24 

29.92 - - 37.7 37.7 37.7 37.7 37. 37.7 37.0 35.8 34.5 33.1 31.8 

7 

27.82 - 37.7 37.7 37.7 37.7 37.7 37. 36.6 35.3 34.0 32.7 31.3 30.0 

6 

25.84 37.7 37.7 37.7 37.7 37.7 37.3 36. 34.8 33.6 32.2 30.9 29.6 28.3 

1 

23.98 37.7 37.7 37.7 37.7 36.7 35.5 34. 33.0 31.6 30.3 29.0 27.7 26.4 

2 

22.23 37.7 37.7 36.8 35.8 34.6 33.4 32. 30.9 29.7 28.4 27.0 25.7 - 2 

20.58 36.7 35.8 34.9 33.8 32.6 31.4 30. 29.0 27.8 26.4 25.1 - - 2 

19.03 34.3 33.4 32.4 31.4 30.3 29.1 27. 26.7 25.3 24.0 - - -

9 

NOTE: SHP = Torgue 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 I M11276NS 

28 

30.5 

28.7 

27.0 

-

-

-

-

32 36 

29.2 27.9 

27.4 -

- -

- -

- -

- -

- -
0 

0 

0 

...... 

I 

Q) 

"'0 

::J 

-:;::::; 

<( 

Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:l 25 Revision: A Date: I 11/25/20131 FAA Project#: I N/A 

FLAPS-UP GLIDE DISTANCE 

S2R-T660 

12 

10 

5 

10.25 20.5 

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

Distance 

Speed Schedule To Obtain LID Max- Speeds Are lAS in MPH 

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

Flaps-Up 111 107 103 99 94 89 84 78 

Flaps-On 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 Feet By 1.81 To Obtain No Wind Glide 

Distance 

Flaps-On Ratio 8. 7 : 1 - Multiply Altitude In Thousands Of Feet By 1.64 To Obtain No Wind Glide 

Distance 
Regort #: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

PageJ 26 Revision: A Date: I 11/25/20131 FAA Project#: _I N/A 

CHAPTER 6: HANDLING 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 e.g., wind, 

runway conditions and construction, and atmospheric conditions 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 e.g., and in relatively calm wind conditions. As 

experience and proficiency allow, takeoff weights may be increased and the e.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-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:l 27 Revision: A Date: l 11/25/20131 FAA Project#: J N/A 

CHAPTER 7: PILOT DOCUMENTATION 

Before receiving Factory Authorized 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 

endorsement). 

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 experience 
Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:l 28 Revision: A Date: I 11/25/20131 FAA Project#: I N/A 

CHAPTER 8: PILOT TYPE RATING REQUIREMENT FOR 

THRUSH AIRCRAFT, INC. 

Reference: FAR 61.31 (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 S2RT660 aircraft. 

Alternative 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 restricted 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 minimum 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 meet 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 logbook 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 Checklist for all Normal and Emergency Procedures. 

d. A training syllabus which includes classroom and cockpit training 

schedules. 
Report#: 

Page:! 29 

ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Revision: A Date: I 11/25/20131 FAA Project#: I N/A 

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 all 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 logbook 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#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:l A1 Revision: A Date: l 11/25/20131 FAA Project#: I N/A 

APPENDIX A: 

S2R-T660 AIRCRAFT TRANSITION 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 understanding 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 and 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 Written 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 Procedures (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 of 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. One S2R-T660 Aircraft 
Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:! A2 Revision: A Date: I 11/25/20131 FAA Project#: I N/A 

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: Emergency Procedures 

Session 5: Review 
Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:! 81 Revision: A Date: I 11/25/20131 FAA Project#: I N/A 

APPENDIX B: 

MODEL TURBO THRUSH S2R-T660 WRITTEN EXAM 

NAME: __________ _ DATE: _______ GRADE:, __ _ 

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

A. Jet 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 grades) 

may be used for a maximum of hrs between overhauls. 

A. 100hrs 

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 1 06% 

D. 1 ooooc and 104% 

5. Minimum ground idle RPM and maximum idle ITT for the PT6A-65AG are 

A. 56% and 600°C 

B. 58% and 750 °C 

C. 61% and 810°C 

D. 69% and 715 °C 

6. Minimum idle oil pressure is __ psig. 

A. 60 

B. 60-90 

C. 90-135 

D. 90 
Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Pagel 82 Revision: A Date: I 11/25/20131 FAA Project#: I N/A 

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. 1 OOODC- 5 seconds 

B. 1000 []fSeconds 

C. 800 OOeconds 

D. 800 []fSeconds 

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

A. 60.98 psi, 850° C, and 1870 rpm. 

B. 45.4 psi, 870°C and 1800 rpm 

C. 58 psi, 810°C and 1700 rpm 

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 situation 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#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:l 83 Revision: A Date: I 11/25/20131 FAA Project#: I N/A 

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 (VNE) is: 

A. 219 Knots 

B. 169 mph 

C. 219 mph 

D. 225 mph 

16. Max Structural Cruising Speed (VNo) is: 

A. 219 mph 

B. 206 mph 

C. 160 mph 

D. 143 mph 

17. What is maneuvering speed (VA)? 

A. 219 mph 

B. 206 mph 

C. 160 mph 

D. 143 mph 

18. Max Flap Extended Speed (VFE) is: 

A. 219 mph 

B. 206 mph 

C. 160 knots 

D. 143 mph 

19. Never exceed speed at 12,500 lbs. and above 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#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:l 84 Revision: A Date: I 11/25/20131 FAA Project#: I N/A 

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. Forward 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. Takeoff into visible moisture below 40 Degrees F. is allowed providing no ice is 

forming. 

A. True 

B. False 
Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:l 85 Revision: A Date: I 11/25/20131 FAA Project#: I N/A 

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 RPM 

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#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:! 86 Revision: A Date: I 11/25/20131 FAA Project#: I N/A 

A. True 

B. False 

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

A. 1 0% for airstarts or 12% for ground starts 

B. 14% to 18% 

C. 13% 

D. Not 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 taxi, 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 check 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. False 
Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:! 87 Revision: A Date: I 11/25/20131 FAA Project#: I N/A 

46. During climb, allow airspeed to build up to ___ with flaps up. 

A. 87 MPH 

B. 94 MPH 

C. 107 MPH 

D. 110MPH 

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. from 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#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:! C1 Revision: A Date: I 11/25/20131 FAA Project #: I 

APPENDIX C: 

PILOT TRAINING RECORD 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. 

N/A 

D 

D 

D 

D 

D 

D 

D 

D 
Report#: ER-511 Title: S2R-T660/-T660DC TRAINING MANUAL 

Page:l 01 Revision: A Date: I 11/25/20131 FAA Project#: I N/A 

APPENDIX D: TRAINING ATTENDANCE RECORD 

A I R CRAFT 

P.O. Box 3149 

Albany, GA 31706-3149 

300 Old Pretoria Road 

Albany, GA 31721 

Phone: 229.883.1440 

Fax: 229.439.9790 

WWIN. thrushaircraft.com 

TRAINING ATTENDANCE 

RECORD 

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AIRCRAFT 

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''il~ll.l:1il TRAINING ATTENDANCE RECORD 

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Subject: 

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Hours: End Date: 

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