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## iii Revision: 

## IR Date: 

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## TABLE OF CONTENTS

S ubject: Page :



## LOG OF REVISIONS

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

TABLE OF CONTENTS

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

PREFACE

................................ ................................ ................................ ............. v

CHAPTER 1: INTRODUCTION

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



## CHAPTER 2: AIRCRAFT SYSTEMS

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



## CHAPTER 3: OPERATIONAL PROCEDURES

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

VISUAL INSPECTION

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

BEFORE STARTING ENGINE

................................ ................................ ............................ 6

STARTING ENGINE

................................ ................................ ................................ ......... 6

DRY MOTORING RUN

................................ ................................ ................................ .... 7

TAXI

................................ ................................ ................................ .............................. 8

BEFORE TAKE

- OFF

................................ ................................ ................................ ......... 8

TAKE

- OFF

................................ ................................ ................................ ...................... 9

CLIMB

................................ ................................ ................................ ........................... 9

GLIDE AND APPROACH

................................ ................................ ................................ .. 9

GO AROUND

................................ ................................ ................................ ................. 9

LANDING

................................ ................................ ................................ ....................... 9

AFTER CLEARING THE RUNWAY

................................ ................................ ................... 10

ENGINE SHUTDOWN

................................ ................................ ................................ ... 10

SECURING THE AIRCRAFT

................................ ................................ ............................ 11

FOR AIRCRAFT WITH TRANSLAND HYDRAULIC FIREDOOR INSTALLED P/N: 251 51

....... 11

FIRE DOOR OPERATING PROCEDURES

................................ ................................ ......... 11

MANUAL OPERATION

................................ ................................ ................................ .. 12



## CHAPTER 4: EMERGENCY PROCEDURES

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

GROUND ENGINE FIRE

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

ENGINE FIRE IN FLIGHT

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

ENGINE SHUTDOWN IN FLIGHT

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

ENGINE FLAMEOUT

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

NORMAL AIR STARTS

................................ ................................ ................................ .. 13Report #: 

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PRE

- AIR START CHECK

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

AIR START PROCEDURE

................................ ................................ ............................... 14

ELECTRICAL FIRE IN FLIGHT

................................ ................................ .......................... 15

EMERGENCY EGRESS

................................ ................................ ................................ ... 15

FOR DUAL COCKPIT AIRCRAFT:

................................ ................................ .................... 15

GENERATOR FAILURE

................................ ................................ ................................ .. 15

FO R AIRCRAFT WITH TRANSLAND HYDR AULIC FIRE DOOR INSTALLED P/N: 251 51

........ 16

EMERGENCY DUMPS

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



## CHAPTER 5: PERFORMANCE

................................ ............................ 17

POWER OFF STALL SPEEDS

................................ ................................ .......................... 17

ASSOCIATED CONDITIONS

................................ ................................ ........................... 17

POWER OFF STALL SPEEDS

– MPH (IAS)

................................ ................................ ....... 17

SPEED FOR BEST RATE

- OF

- CLIMB

................................ ................................ ................. 17

AIRSPEED CALIBRATION MPH

................................ ................................ .................... 17

TAKEOFF DISTANCE ~ FEET

................................ ................................ .......................... 18

RATE OF CLIMB

................................ ................................ ................................ ........... 20

LANDING DISTANCE FROM 50 FEET

................................ ................................ ............. 22

POWER SETTING CHART

................................ ................................ .............................. 24



## CHAPTER 6: HANDLING CHARACTERISTICS

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



## CHAPTER 7: PILOT DOCUMENTATION

................................ ............................. 28Report #: 

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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 America Department of Transport ation 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 infor mation 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 models of Thrush Aircraft. Diffe rences 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, Airspeed Indicator, Altimeter, Flu id 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 cockp itheat, 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.Report #: 

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CHAPTER 3: OPERATIONAL PROCEDUR ES

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

8b. Check Flap Operation

– UP

– DOWN

- UP

9. Battery S witch

– OFFReport #: 

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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 Moveme nt, 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 condition and freedom of movem ent



### 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 (if installed) CHECK for secu rity 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. Firewall Fuel Filter By

- pass Indi cator

– 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. Ai r Filter

– CHECK for cleanliness and condition



### (5)Report #: 

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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 p ropeller 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 installe d)

– 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 damage



### (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

– CHECK for security

42a Fuel Q uantity

– 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 wearReport #: 

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48. Tail Wheel Spring

– CHECK for condition

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 excessi ve 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 Pedals

– ADJUST and LOCK

4. Seat Bel t 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 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 stabiliz ed gas generator speed above 13%

a) MOVE Ignition Switch to ON Position

b) MOVE the Fuel Condition Lever to the Ground Idle PositionReport #: 

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

inter

- turbine starting limit is not exceed.

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 positio ns.

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 motori ng 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 char ging 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 engin e 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 immediately and continue moto ring. 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 cooling period for the starter b efore 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 forwa rd 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.

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 flights, apply take

- off power a nd 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 Se ction)

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 Pum p

– 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 IAS with Flaps Up



## LANDING

1. Airspeed on Final

– MAINTAIN 82 MPH with hopper empty

2. Wing Flaps

– SET 15 degreesReport #: 

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3. Touchdown

– Main Wheels

4. L anding 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 R UNWAY

1. W ing 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

– S ET

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. Generator Switch

– OFF



### NOTE

D uring the shutdown be sure that the compressor decelerates freely.Report #: 

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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 AIRCRAF T

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 FI REDOOR

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. Fi re 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. WARNINGReport #: 

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

will suspen d all other operations until it is cleared.

6. Select operating Mode

7. Set

– Level

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 f or 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 momentarily to prevent system d amage. 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 flameout will be a drop i n 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 th e 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.Report #: 

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NOTE

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

Fine pitch selection will pump air through the engine, an d; therefore increase the gas

generator motoring speed during the Air Start procedure.

1. Power Lever

– IDLE

2. Master Switch

– ON

3. Fuel Valve

– ON

4. Fuel Condition Lever

– CUT OFF

5. Fuel Auxiliary Pump Switch

– ON

6. 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 rel ight 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 an d 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 En gine 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 p rocedure 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 s oon 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 fe ather the propeller. However, the power lever should be returned to the idle

position.Report #: 

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ELECTRICAL FIRE IN F LIGHT

1. Battery Switch and Generator Switch

– OFF

2. All other Electrical Switches

– OFF

3. Circuit Breakers

– CHECK to identify fau lty circuit, if possible.

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 AIR CRAFT:

If it is not desired to r elease 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 le ft 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 OFFReport #: 

## ER

- 5 11 Title: 

## S2R

- T660/

- T660DC TRAINING MANUAL

Page: 

## 16 Revision: 

## IR Date: 

## 9 /3/ 2013 FAA Project #: 

## N/A

If Generator Fails, Air Conditioner must be tur ned 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 CAUTIONReport #: 

## ER

- 5 11 Title: 

## S2R

- T660/

- T660DC TRAINING MANUAL

Page: 

## 17 Revision: 

## IR Date: 

## 9 /3/ 2013 FAA Project #: 

## N/A



# CHAPTER 5: PERFO RMANCE

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

Configuration Cle an 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 Degrees

- 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 82 102 122 142 161 181 201 222

FLAPS 15 DEGREES IAS 80 100 120 140 156

CAS 82 102 122 142 154Report #: 

## ER

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## S2R

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- T660DC TRAINING MANUAL

Page: 

## 18 Revision: 

## IR Date: 

## 9 /3/ 2013 FAA Project #: 

## N/A

TAKEOFF DIS TANCE ~ 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 ... TAKEOFF

CONFIGURATION

WING FLAPS ... 15°

DISPERSAL EQUIPMENT ... STANDARD SPRAY

GROSS WEIGHT ... 14150 LB

RUNWAY ... LEVEL HARD SURFACE

WIND ... 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 TH E 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 / 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 #: 

## ER

- 5 11 Title: 

## S2R

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- T660DC TRAINING MANUAL

Page: 

## 19 Revision: 

## IR Date: 

## 9 /3/ 2013 FAA Project #: 

## N/A

TAKEOFF DISTANCE ~ FEET

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 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

- - - - - - - - - - - - - - - - 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: 

## 20 Revision: 

## IR Date: 

## 9 /3/ 2013 FAA Project #: 

## N/A

RATE OF CLIMB

INTERNATIONAL STANDARD ATMOSPHERE

OAT RATE OF CLIMB

- FT

ENGINE (PRAT T & 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 5 0 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 FOLLOWING ENGINES AND PROPELLERS:
ENGINE (PRATT & WHITNEY) PT6 A

- 67AG
PROPELLER (HARTZELL HUB MODEL AND BLADES)

PT6A

- 67AG HC

- B5MA

- 3D / 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: 

## 21 Revision: 

## IR Date: 

## 9 /3/ 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

PROPELLE R (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

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- T660DC TRAINING MANUAL

Page: 

## 22 Revision: 

## IR Date: 

## 9 /3/ 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

ASSOCIA TED CONDITIONS

POWER ... FLIGHT IDLE

CONFIGURATION

WING FLAPS ... 15°

DISPERSAL 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)

PT6A

- 67AG 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

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## S2R

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- T660DC TRAINING MANUAL

Page: 

## 23 Revision: 

## IR Date: 

## 9 /3/ 2013 FAA Project #: 

## N/A

LANDING DISTANCE FROM 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 333 2 3422 3515 3611 3712

105 11000 2755 2824 2895 2969 3045 3125 3207 3293 3382 3474 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 27 61 2832 2906 2983 3062 3145

95 9000 2337 2393 2451 2512 2574 2639 2707 2777 2849 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 22 75 2331 2390 2450 2513 2579

84 7000 1919 1962 2008 2055 2103 2154 2206 2261 2317 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 / BLADE S) HC

- B5MP

- 3C / M

- 10876

ASSOCIATED CONDITIONS

POWER... FLIGHT IDLE

CONFIGURATION

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: 

## 24 Revision: 

## IR Date: 

## 9 /3/ 2013 FAA Project #: 

## N/A

POWER SETTING CHART

PRATT AND WHITNEY PT6A

- 60AG AND PT6A

- 45 SERIES

INSTALLED IN THE THRUSH AIRCRAFT INC MODEL S2R

- T660

RATING TAKE OFF POWER

RPM 1700

The Chart Contains Torque Pressure ~ psi

Pressure

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

- - 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 37.1 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: 

## 25 Revision: 

## IR Date: 

## 9 /3/ 2013 FAA Project #: 

## N/A

POWER SE TTING 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

Pr essure

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 3 5.5 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

- - - - -

12,0 00 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 CON SERVATIVE 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: 

## 26 Revision: 

## IR Date: 

## 9 /3/ 2013 FAA Project #: 

## N/A

Miles

– Statute (SM)

Note: Chart Glide Dista nce 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 9,000 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 Feet 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: 

## 27 Revision: 

## IR Date: 

## 9 /3/ 2013 FAA Project #: 

## N/A



# CHAPTER 6: HANDLING CHARACTERIS TICS

The handing characteristics of the AT

- 802 / AT

- 802A are similar to the handling characteristics

of other Air Tractor models, and are typical of many other large, turbine

- powered tailwheel

aircraft. Obviously, variables such as hop per load, fuel load, loaded c.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 load ed 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: 

## 28 Revision: 

## IR Date: 

## 9 /3/ 2013 FAA Project #: 

## N/A



# CHAPTER 7: PILOT D OCUMENTATION

Before receiving Factory Authorized training, the following documentation must be on

file with Air Tractor, 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

E xper ience.