s2r t34 flight manual

Thrush Aircraft Inc Model S2R-T34 MANUAL Albany, GA

AIRPLANE FLIGHT MANUAL ORGANIZATION

FAA APPROVED: Oct. 24, 2006 Revision 2, page i

SECTION I -----------------------------------------------------LIMITATIONS SECTION II -------------------------------------- NORMAL PROCEDURES SECTION III--------------------------------EMERGENCY PROCEDURES SECTION IV ------------------------------------------------- PERFORMANCE

Thrush Aircraft Inc Model S2R-T34 SECTION I Albany, GA

AIRPLANE FLIGHT MANUAL LIMITATIONS

FAA APPROVED: Apr. 10, 2007 Revision 3, page ii

LOG OF PAGES

ONLY THE PAGES HEREIN ARE APPLICABLE TO THE THRUSH AIRCRAFT INC TURBO THRUSH

MODEL S2R-T34

SERIAL NUMBER _____________

PAGE DATE PAGE DATE

i ……..………………………… Oct. 24, 2006 Section III ii ……..………………………… Apr. 10, 2007 Emergency Procedures

iii ……..………………………… Oct. 24, 2006 iv ……………………………….. Apr. 10, 2007 III-1 ……..……………………… Oct. 24, 2006 III-2 ……..……………………… Oct. 24, 2006 III-3 ……..……………………… Apr. 10, 2007

Section I III-4 ……..……………………… Apr. 10, 2007 Limitations

Section IV I-1 ……..………………………… Oct. 24, 2006 Performance I-2 ……..………………………… Oct. 24, 2006 I-3 ……..………………………… Oct. 24, 2006 IV-1 ……..……………………… Oct. 24, 2006I-4 ……..………………………… Oct. 24, 2006 I-5 ……..………………………… Oct. 24, 2006 I-6 ……..………………………… Oct. 24, 2006 I-7 ……..………………………… Oct. 24, 2006 I-8 ……..………………………… Apr. 10, 2007

Section II Normal Procedures

II-1 ……..………………………… Apr. 10, 2007 II-2 ……..………………………… Apr. 10, 2007 II-3 ……..………………………… Apr. 10, 2007 II-4 ……..………………………… Apr. 10, 2007 II-5 ……..………………………… Apr. 10, 2007 II-6 ……..………………………… Apr. 10, 2007 II-7 ……..………………………… Apr. 10, 2007 II-8 ……..………………………… Apr. 10, 2007 II-9 ……..………………………… Apr. 10, 2007

Apr. 10, 2007

Thrush Aircraft Inc Model S2R-T34 LOG OF REVISIONS Albany, GA

AIRPLANE FLIGHT MANUAL

FAA APPROVED: Apr. 10, 2007 Revision 3, page iii

LOG OF REVISIONS

Revision Number

Page

Description of Revision

FAA Approved

1

ii

iii

I-8

Log of pages shall reflect FAA approval of changes

Log of Revision page denotes changes.

Correct typo, Changed PUNCH to PUSH

Approved by David Crew for Manager, Aircraft Certification

Branch Federal Aviation

Administration Atlanta, Georgia Date: 4/7/2005

2

All

I-1

I-2

I-3

I-4

I-6

I-7

I-8

II-4

III-4

Revised formatting slightly for readability.

Added “50” to idle Ng in engine limits for PT6A-34AG, -34, -36.

Added “50” to idle Ng in engine limits for PT6A-41AG, -41, -42.

Added separate PT6A-42 ITT gauge markings. Noted red diamond in PT6A-34AG, -34, -36 torque gauge marking description.

Changed Ng markings to agree with PT6A-34AG, -34, -36 limits. Added noise abatement statement.

Corrected typo PROHIBITED under Normal Category. Corrected useable tank capacity in first placard under A.

Corrected fuel capacity under E. Added letter heading H. to hopper placard, re-lettering ones that follow. Corrected J, fuel gauge placard.

Added O., fuel shut-off valve placard.

Made note under 7 same as note under 3

Added turning off air conditioner as first step, and last step to try resetting the generator again after non-essential equipment is turned off. Deleted CAUTION as no longer necessary.

David Crew for Manager, Aircraft Certification


Administration Atlanta, Georgia

Date: 10/24/06



FAA APPROVED: Oct. 24, 2006 Revision 2, SECTION I-1

SECTION I LIMITATIONS

TABLE OF CONTENTS

Subject page | Subject page POWER PLANT ................................................... I-1 | WEIGHT AND CENTER OF GRAVITY ...........I-5 INSTRUMENT MARKINGS ............................... I-3 | MANEUVERS .....................................................I-6 AIRSPEED LIMITATIONS ................................. I-4 | TYPES OF OPERATION ....................................I-6 ALTITUDE LIMITATIONS................................. I-4 | GROUND OPERATION .....................................I-6 FLIGHT LOAD FACTORS.................................. I-4 | PLACARDS .........................................................I-6 NOISE ABATEMENT.......................................... I-4

POWERPLANT:

ENGINE: STANDARD: Pratt & Whitney Canada PT6A-34AG OPTIONAL: Pratt & Whitney Canada PT6A-34 Pratt & Whitney Canada PT6A-36 (Dry Configuration Only) Pratt & Whitney Canada PT6A-41, -41AG

Pratt & Whitney Canada PT6A-42

FUEL: JET A, JET B, JP-4, JP-5. (If jet fuel is not available, aviation gasoline, MIL-G-5572, all grades, may be used for a maximum of 150 hours between overhauls).

ENGINE LIMITS: PT6A-34AG, -34, -36 (PT6A-34AG shown)

POWER SETTING SHP TORQUE

(PSI) ITT (ºC)

Ng (%)

Np (RPM)

OIL PRESS. (PSIG)

OIL TEMP.

(ºC)

Takeoff & Max continuous 750 64.5***

58.7**** 790 101.6 2200 85 to 105 10 to 99

Max Climb 700 60.2*** 54.7**** 765 101.6 2200 85 to 105 0 to 99

Max Cruise 700 60.2*** 54.7**** 740 2200 85 to 105 0 to 99

Idle 685 50 40 Min. -40 to 99 Starting 1090* -40 Min.

Acceleration 68.4** 850* 102.6* 2420 0 to 99

Max. Reverse 750 64.5***

GENERAL NOTE: The operating parameters in this Table are individual limits for each engine parameter and do not necessarily apply simultaneously.

61.4**** 790 101.6 2100 85 to 105 0 to 99

*These values are time limited to two (2) seconds. **These values are time limited to twenty (20) seconds. ***Torque limit for Max Np = 2000 RPM ****Torque limit for Np = 2200 RPM




ENGINE LIMITS: PT6A-41AG, -41, -42 (PT6A-41AG shown)

*** TORQUEPOWER

SETTING SHP

GENERAL NOTE: The operating parameters in this Table are individual limits for each engine parameters and do not necessarily apply simultaneously.

(PSI)

ITT (ºC)

Ng (%)

Np (RPM)

OIL PRESS. (PSIG)

OIL TEMP.

(ºC)

Takeoff & Max continuous

750 64.5 750† 101.5 2000 105 to 135††† 0 to 99

Max Climb 700 60.2 725†† 101.5 2000 105 to 135††† 0 to 99

Max Cruise 700 60.2 725† 2000 105 to 135††† 0 to 99

Idle 50 60 Min. -40 to 99

Starting 1000* -40 Min.

Acceleration 68.4* 850 102.6 2205 99 to 104**

Max. Reverse 750 64.5 750 101.5 2000 105 to 135††† 0 to 99

*These values are time limited to five (5) seconds. **Time limited to ten (10) minutes at any operating condition. ***Torque limit shown for Np = 1600-2000 RPM. †For PT6A-42 790ºC. ††For PT6A-42 765ºC. †††For PT6A-42 100 to 135

STARTER: Maximum starter engagement duration is 30 Seconds followed by a 60 Seconds cool down period. Total of 3 cycles to be followed by 30 minutes starter cool down.

AIR STARTS: Normal air starts are approved from sea level to 12,000 feet altitude and from 80 MPH to 126 MPH air speed. See the Emergency Procedures in Section III.

PROPELLER: Hartzell Hub Model HC-B3TN-3C (or HC-B3TN-3D) with Blade Model T-10282, Diameter 102.5 inches maximum, 92.5 inches minimum or optional Blade Model T-10282 (N) +4, Diameter 106.5 inches maximum, 98.0 inches minimum.

REVERSE POWER: Do not use in flight

P-3 HEATER: Regardless of fuel type used, the P-3 heater switch must be turned on (If Installed) for flight and ground operations when the free temperature is below 40 Degrees F.




INSTRUMENT MARKINGS: Limits Features Meaning

OIL TEMP ( °C)

-40 -40 to10 10 to 99 99

Red Radial Yellow Arc Green Arc Red Radial

MINIMUM CAUTION NORMAL MAXIMUM

OIL PRESSURE (PSI) PT6A-34AG, -34, -36

40 40 to 85 85 to 105 105



OIL PRESSURE (PSI) PT6A-41AG,-41

60 60 to 105** 105 to 135 135



OIL PRESSURE (PSI) PT6A-42

60 60 to 100*** 100 to 135 135



FUEL PRESSURE (PSI) 5 5 to 50 50

Red Radial Green Arc Red Radial

MINIMUM NORMAL MAXIMUM

ITT (°C) PT6A-34AG, -34, -36 400 to 790 790

Green Arc Red Radial

NORMAL MAXIMUM

ITT (°C) PT6A-41AG, -41 400 to 750 750


NORMAL MAXIMUM

ITT (°C) PT6A-42 400 to 800 800


NORMAL MAXIMUM

TORQUE (PSI) PT6A-34AG, -34, -36

0 to 58.7 58.7* 64.5

Green Arc Red Radial Red Diamond

NORMAL MAXIMUM Max @ 2000RPM

TORQUE (PSI) PT6A-41AG, -41, -42

0 to 64.5 64.5


NORMAL MAXIMUM

PROPELLER RPM (Np) PT6A-34AG, -34, -36

0 to 2200 2200


NORMAL MAXIMUM




INSTRUMENT MARKINGS (Continued) Limits Features Meaning

PROPELLER RPM (Np) PT6A-41AG, -41, -42

0 to 2000 2000


NORMAL MAXIMUM

GAS GENERATOR SPEED (% Ng) 50 to 101.6 101.6


NORMAL MAXIMUM

AIRSPEED

66 to 123 MPH CAS 70 to 126 MPH CAS 126 to 159 MPH CAS 159 MPH CAS

White Arc Green Arc Yellow Arc Red Radial

Flaps Operating Range Normal Operating Range Caution Range Never Exceed

* In addition to a red radial limit marker at 58.7 PSI, the torque meter is marked with a red diamond at 64.5 PSI. (58.7 PSI is the torque limit for 2200 RPM, the normal takeoff RPM. 64.5 PSI is the torque limit for 2000 RPM, an optional RPM setting for in-flight use.) ** The 60-105 oil pressure caution range is for idling and for emergency completion of a flight using 36 PSI torque or below. *** The 60-100 oil pressure caution range is for idling and for emergency completion of a flight using 36 PSI torque or below.

AIRSPEED LIMITATIONS: Never Exceed Speed Vne – 159 MPH Maximum Structural Cruising - Vno – 126 MPH Maneuvering Speed – Va – 126 MPH Flap Extended Speed – Vfe – 123 MPH Maximum Dump Speed – 120 MPH Maximum Crosswind Velocity – 15 MPH All airspeeds are given in Calibrated Air Speeds.

ALTITUDE LIMITATIONS: Maximum approved altitude is 12,000 feet.

FLIGHT LOAD FACTORS: Design Load Factors - Flap Up; 3.8 Positive, 1.9 Negative Design Load Factors - Flap Down; 2.4 Positive, 0.0 Negative

NOISE ABATEMENT: This airplane has not been shown to comply with the noise limits in FAR 36 and must be operated in accordance with the noise operating limitation prescribed under FAR §91.815.




WEIGHT AND CENTER OF GRAVITY:

NOTE Datum is the leading edge of the wing.

Maximum Weight – 6000 pounds

C.G. Range for SINGLE COCKPIT * Forward Limit at 6000 pounds is 26.5 inches AFT of Datum.

* Forward Limit at 4000 pounds is 24.0 inches AFT of Datum. * AFT Limit is 29.0 inches AFT of Datum (Normal Category).

Straight Line variation in the Forward Limit between 4000 pounds and 6000 pounds.

7,000

6,500

6,000

5,500

5,000

4,500

4,000

3,500

3,00023.0 23.5 24.0 24.5 25.0 25.5 26.0 26.5 27.0 27.5 28.0 28.5 29.0 29.5 30.0

4,000 lbs@ 24.0 in

6,000 lbs@ 26.5 in

4,000 lbs

6,000 lbs@ 29.0 in

Center of Gravity - in. aft of datum

Airp

lane

Wei

ght -

lbs

Thrush S2R-T34 Single CockpitWeight & Center-of-Gravity Envelope

Normal Catagory




NOTE

It is the responsibility of the airplane owner and the pilot to insure that the airplane is properly loaded. See the aircraft’s Weight and Balance Sheet for loading information.

MANEUVERS: NORMAL CATEGORY

Flight maneuvers include steep turns, chandelles, and lazy-eights in which bank angles do not exceed 60 degrees and pitch angles do not exceeds 30 degrees. Gradual entry rate stalls are also approved. Acrobatic maneuvers and intentional spins are PROHIBITED.

TYPES OF OPERATION: The Model S2R-T34 aircraft is approved for day and night VFR flight conditions. Flight into known icing conditions is PROHIBITED.

GROUND OPERATION: Ground operation is approved at ground idle power with the propeller feathered and with no time limits. The pilot should monitor the engine instruments for operation within limits during all ground operations.

PLACARDS:

A. Located on Right Hand lower instrument panel:

“THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN ACCORDANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS AND THE AIRPLANE FLIGHT MANUAL. NO ACROBATIC MANEUVERS, INCLUDING SPINS APPROVED. DESIGN MANEUVERING SPEED-126 MPH. MAX. FLAP-DOWN SPEED-123 MPH. MAX. CROSSWIND VELOCITY, LANDING-15 MPH. USABLE TANK CAPACITY 114 GALLONS EACH SIDE.”

“THE OPERATION OF THIS AIRPLANE IS LIMITED TO DAY AND NIGHT VFR CONDITIONS. FLIGHT INTO KNOWN ICING CONDITIONS IS PROHIBITED.”

“NO SMOKING”

“SULFUR DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN AIRCRAFT.”

“PUSH STICK FORWARD TO UNLOCK TAILWHEEL.”

“TAKING OFF IN VISIBLE MOISTURE BELOW 40°F IS PROHIBITED.”




B. Located near Park Brake Valves:

“PARK BRAKE – ON, DEPRESS PEDALS AND PULL LEVER. OFF, DEPRESS PEDALS”

C. Located on Forward Lower Corner of Each Door Side Window:

“DO NOT OPEN DOOR IN FLIGHT”

“DO NOT OPEN DOOR ON THE GROUND WITH ENGINE RUNNING UNLESS HEADED OUT OF THE WIND WITH THE PROPELLER FEATHERED”

D. Located adjacent to the torque meter:

“MAXIMUM TORQUE IS 58.7 PSI AT 2200 RPM OR 64.5 PSI AT 2000 RPM WITH STRAIGHT LINE VARIATION BETWEEN THESE POINTS”

E. At both fuel filler caps:

“FUEL – 115 GAL. CAP. JET A, JET B, JP-4 & JP-5”

F. Located on upper instrument panel:

“DO NOT USE REVERSE POWER IN FLIGHT. AT HIGH TAXI SPEEDS USE REVERSE POWER ONLY IF THE TAIL WHEEL IS LOCKED AND FIRMLY ON THE GROUND.”

WARNING

G. Located on cockpit wall (If P-3 Heater is installed):

WARNING

“REGARDLESS OF FUEL TYPE USED, THE P-3 HEATER SWITCH MUST BE TURNED ON FOR FLIGHT AND GROUND OPERATIONS WHEN THE FREE AIR TEMPERATURE IS BELOW 40 DEGREES F.”

H. Located on top of hopper

“HOPPER CAPACITY 3336 LBS.”

I. Located on Left Hand Lower instrument panel:

“FILTER CONDITION – FLIGHT IN RED IS PROHIBITED.”

J. Located on the fuel gauge:

“USABLE FUEL 114 U.S. GAL. FUEL ABOVE 82 GAL. IS UNGAGEABLE”.



FAA APPROVED: Apr. 10, 2007 Revision 3, SECTION I-8

K. Located on inside of baggage door: (Single Cockpit Only)

“60 LBS. MAXIMUM BAGGAGE”

L. Located on right hand side panel, rear cockpit: (Dual Cockpit Only)

“PASSENGER OR CARGO 200 LBS MAXIMUM”

M. Located at each door latch:

OPEN or OPEN

N. Located on the Outside of the rear cockpit door: (Dual Cockpit Only)

OPEN

O. Located at each door knockout panel:

“PUSH OUT AND LIFT HINGE PIN FOR EMERGENCY EXIT”

P. Located (inverted) at each door hinge pin:

“PULL HINGE PIN FOR EMERGENCY EXIT”

Q. Located on face of Fuel Shut-off Valve handle bracket:

S/N 273 through 277 and 279:

“FUEL, 228 GAL USEABLE

ON OFF”

S/N 278, 280 and up:

“FUEL, 228 GAL USEABLE

ON OFF

PUSH BUTTON TO TURN”

Thrush Aircraft Inc Model S2R-T34 SECTION II Albany, GA

AIRPLANE FLIGHT MANUAL NORMAL PROCEDURES

FAA APPROVED: Apr. 10, 2007 Revision 3, SECTION II-1

SECTION II NORMAL PROCEDURES

TABLE OF CONTENTS

Subject page | Subject page DEFINITIONS................................................ II-1 | CLIMB ..........................................................II-8 VISUAL INSPECTION.................................. II-2 | GLIDE AND APPROACH ...........................II-8 BEFORE STARTING .................................... II-5 | GO AROUND ...............................................II-8 STARTING ENGINE..................................... II-5 | LANDING.....................................................II-8 DRY MOTORING RUN ................................ II-6 | AFTER CLEARING THE RUNWAY..........II-9 TAXI............................................................... II-7 | ENGINE SHUTDOWN ................................II-9 BEFORE TAKE-OFF..................................... II-7 | SECURING THE AIRCRAFT......................II-9 TAKE-OFF ..................................................... II-7

DEFINITIONS:

Personal injury or loss of life could result if the operating procedures and techniques are not followed carefully.

Damage to equipment could result if the operating procedures and techniques are not followed carefully.

NOTE This is used when it is essential to emphasize an operating procedure or technique.

Airspeeds All airspeeds in this Section are Indicated Airspeeds (IAS) in Miles per Hour (MPH), unless otherwise noted.

WARNING

CAUTION

VISUAL INSPECTION: NOTE

Visually check the aircraft for general condition during the walk around inspection. Verify that all skin panel Camlocs are fastened. In cold weather remove all accumulations of frost, ice, or snow from wing, tail and control surfaces. Check that control surfaces contain no internal accumulations of ice. If a night flight is planned, check operation of all lights and assure a flashlight is available.




EXTERIOR INSPECTION ROUTE

Exterior Inspection Route - Figure 2-1

(POSITION)

1. Control Lock – REMOVE

2. Ignition Switch - OFF

3. Power Lever – FORWARD IDLE

4. Fuel Lever – CUTOFF

5. Fuel Valve – ON

6. Parking Brake – TEST and SET

7. Battery Switch – ON

8. Fuel Quantity – CHECK Each Tank Indication

9. Battery Switch – OFF

10. Elevator Trim Tab – SET, for takeoff (T.O. Arc)

11. Oil Quantity – CHECK dipstick and SECURE cap

NOTE

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

15. Aileron hinges – CHECK, for looseness. Use a brisk UP and DOWN motion

but use caution so as not to damage control or stops.

16. Wing Tip – CHECK, for damage

17. Wing Leading Edge – CHECK, for damage

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 of ice or frost.

18. Wing Tie Down – REMOVE, condition and freedom of movement.

18a. Stall Vane – CHECK, condition and freedom of movement.

19. Fuel Quantity – CHECK, visually and secure cap.

20. Oil Cooler – CHECK, for leaks and stoppage.

21. Accessory Section – CHECK, for debris, oil leaks, or any other

irregularities.

22. Air Filter – CHECK, for cleanliness and condition.

23. Main Wheel Tire – CHECK, for inflation, damage, and wear.

24. Left Wing Sump – DRAIN.

24a. Header Tank Sump – DRAIN.

24b. Left fuel Vent Sump – DRAIN.

25. Firewall Fuel Filter – DRAIN.

25a. Firewall Fuel Filter By-pass Indicator – CHECK.

26. Fuel Vent – CHECK, for obstruction.

26a. Residual Fuel Reservoir (EPA Tank) – DRAIN.

27. Engine – CHECK, for oil leaks, loose fittings, cracked exhaust stacks, and excessive dirt or corrosion.

28. Propeller – CHECK, for spinner damage or oil leaks.

29. Propeller – CHECK, the propeller blades for nicks, cracks, or excessive

erosion of the leading edge.




30. Dispersal Equipment (if installed) – CHECK, the windmill, the pump, the hose, the spreader, the mounting, and so forth.

31. Wheel Chocks – REMOVE

32. Fuel Quantity – CHECK, visually and secure the cap.

33. Main Wheel Tire – CHECK, for inflation, damage, and wear.

34. Right Wing Sump – DRAIN.

34a. Right Fuel Vent Sump – DRAIN.

35. Wing Leading Edge – CHECK, for damage.

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 of ice or frost.

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. Use a brisk UP and DOWN

motion but use caution so as not to damage control 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.

43. Battery Vent – CHECK for obstruction.

43a. Static Port Opening – CHECK for blockage.

44. Rudder Gust Lock (if installed) – REMOVE.

45. Empennage – CHECK, for condition

46. Struts – CHECK, for condition and security.

47. Tail Wheel Tire – CHECK, for inflation, damage, and wear.

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

excessive play




51. Tail Tie-Down – REMOVE.

52. Static Port Opening – CHECK, for blockage 10 53. Rear Cockpit – CHECK, cargo secure (Dual Cockpit Only)

54. Rear Cockpit Door – CHECK, closed and secure (Dual Cockpit Only)

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

9. Rear Cockpit Occupant – STRAPPED IN (Dual Cockpit Only)

STARTING ENGINE: 1. Battery Switch – ON

2. Power Lever – FORWARD IDLE STOP / BETA STOP

3. Propeller Lever – Anywhere in operating range, but normally feather.

4. Fuel Lever – CUT OFF


6. Fuel Aux. Pump Switch – ON

7. Fuel Inlet pressure Indicator – CHECK, 5 PSIG Minimum

8. Engine Starter Switch – ON. The minimum speed to obtain a satisfactory light is Ng

12%.

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

12%:

a) MOVE Ignition Switch to On Position and,

b) MOVE the Fuel Condition Lever to the Low Idle / Ground Idle position.

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

allowable interturbine temperature starting limit is not exceeded.




CAUTION

Whenever the gas generator fails to light up within 10 Seconds after moving the fuel lever to the LOW IDLE / GROUND IDLE position, cut off fuel, starter, and ignition. Allow a 30 second fuel draining period followed by a 15 second dry motoring run before attempting another start. 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.)

11. Engine Starter Switch and Ignition Switches – OFF. 12. Oil Pressure – CHECK, 85 PSIG Minimum. 13. Fuel Aux. Pump – OFF. 14. Fuel Pressure from Engine Driven Pump – CHECK 5 PSI Minimum 15. Generator – ON and CHECK charging normally. 16. P-3 Heater Switch – ON (if installed) (When the free air temperature is below 40°F.) 17. Warning Lights – CHECK and consider.

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 if there is evidence of a fire within the engine. Air passing through the engine serves to purge fuel, vapor, or fire from the combustion sections, gas generator turbine, power turbine, and exhaust system. 1. Fuel Condition Lever – CUT OFF

2. Ignition Switch – OFF

3. Master Switch – ON


5. Fuel Auxiliary Pump Switch – ON, to provide lubrication for the engine driven fuel pumping elements.

6. Engine Starter Switch – ON

WARNING

If the fire should persist as indicated by sustained interturbine temperature, close the fuel system shutoff valve immediately and continue motoring.

7. Maintain the starter operation for the desired duration. (Maximum starter duration is 3 minutes.)

8. Engine Starter Switch – OF




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.

TAXI The Beta Region of the throttle quadrant may be utilized for taxing. Push the stick full

forward to unlock the tailwheel.

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 (forward) position.

2. Increase RPM with the power lever to at least 2100 RPM.

3. Momentarily exercise the prop test switch and note a small decrease in the RPM (2025 ± 20). This checks the prop overspeed governor.

CAUTION

HOLD the Elevator Control firmly FULL UP 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 – As required

7. Fuel Lever – HIGH IDLE / FLIGHT IDLE (check, 68% Ng).

8. Fuel Aux. Pump – ON

9. Ignition Switch – ON

10. Rear Seat Occupant – CONFIRM ready (Dual Cockpit Only)

11. Prior to 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. Do not exceed engine operational limitations. (See the Limitations Section)




3. After breaking ground, allow airspeed to build up to best-rate-of-climb speed of 85 MPH.

CLIMB: 1. Establish the Best-Rate-of-Climb speed, 85 MPH.

2. Maintain maximum continuous power (RPM may be reduced to 2000 to reduce propeller noise.)

3. Flaps – RETRACT.

4. Fuel Auxiliary Pump – OFF

5. Ignition Switch – OFF

GLIDE AND APPROACH: 1. Fuel Condition Lever – SET HIGH / FLIGHT IDLE

2. Prop Control – SET full high RPM

3. Fuel Auxiliary Pump – ON

4. Ignition Switch – ON

5. Flaps – SET as required

6. Rear Seat Occupant – CONFIRM ready (Dual Cockpit Only)

GO AROUND: 1. Power – Increase to the take-off setting.

2. Flaps – Retract slowly while maintaining altitude.

3. Airspeed – Maintain best-rate-of-climb speed of 85 MPH.

LANDING: 1. Airspeed on Final – 130% of Power Off, stall speed (80 to 92 MPH).

2. Wing Flaps – As required.

3. Touchdown – Main Wheels.

4. Landing Roll - Lower Tail Smoothly, Close the throttle.

5. Reverse Propeller – Reverse may be used after the tail is on the ground. Depress button on power lever to use reverse thrust. Keep tailwheel locked during all reverse operation.

NOTE

Care should be taken not to unlock the tail-wheel prematurely, since 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 Aux. – OFF.

3. Ignition Switch – OFF.

4. Fuel Lever – LOW IDLE / GROUND IDLE.

ENGINE SHUTDOWN: 1. Parking Brake – SET.

2. Power Lever – IDLE. NOTE

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

3. Propeller Lever – FEATHERED.

4. Fuel Condition Lever – CUT OFF.

5. P-3 Heater Switch – OFF (If Installed).

6. Battery Switch – OFF.

7. Generator Switch – OFF NOTE

During the shutdown, be sure that the

compressor decelerates freely.

If there is any evidence of a fire within the engine after shutdown, proceed immediately as described under “Dry Motoring Run.”

WARNING

SECURING THE AIRCRAFT: 1. Parking Brake – RELEASE and INSTALL the wheel chocks.

2. Control Stick Lock – ENGAGE.

3. Aileron and Rudder gust locks- INSTALLED AND SECURE.

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

wind milling with zero oil pressure.

Thrush Aircraft Inc Model S2R-T34 SECTION III Albany, GA EMERGENCY PROCEDURES


FAA APPROVED: Oct. 24, 2006 Revision 2, SECTION III-1

SECTION III EMERGENCY PROCEDURES

TABLE OF CONTENTS

Subject page | Subject page

GROUND ENGINE FIRE-----------------------III-1 | NORMAL AIR STARTS III-2 ENGINE FIRE IN FLIGHT ---------------------III-1 | ELECTRICAL FIRE IN FLIGHT III-3 ENGINE SHUT DOWN IN FLIGHT----------III-1 | EMERGENCY EGRESS III-3 ENGINE FLAMEOUT---------------------------III-1 | GENERATOR FAILURE III-4

GROUND ENGINE FIRE: See “Dry Motoring Run” under Ground Operation, Section II.

ENGINE FIRE IN FLIGHT: In case of an in-flight fire, the following procedures should be used:

1. Power Lever – IDLE POSITION.

2. Propeller Lever – FEATHERED.


4. Fuel Aux. Pump Switch – OFF


ENGINE SHUTDOWN IN FLIGHT: 1. Propeller Lever – FEATHERED

2. Fuel Condition Lever – CUT OFF POSITION

3. Fuel Auxiliary Pump Switch – OFF


5. Power Lever – IDLE POSITION

ENGINE FLAMEOUT: The indications of any engine flameout will be a drop in the interturbine temperature, torque pressure, and RPM. The flameout may result from the engine running out of fuel or possibly may be caused by 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 following:

If Ng RPM Has NOT DROPPED BELOW 50%.

1. Igniter Switch - Continuous.



FAA APPROVED: Oct. 24, 2006 Revision 2, SECTION III-2

2. Fuel Aux. Boost Pump - ON.

If Ng RPM Drops Below 50% and No Re-light is observed. Use the Following Procedure:

NORMAL AIR STARTS:

NOTE

Air Start Envelope – Normal Air Starts ranging from sea level to 12,000 feet altitude and above 80 MPH to 126 MPH indicated airspeed have been approved.

The recommended pre-air start check procedure is:

1. Propeller Lever – Anywhere in 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.

1. Power Lever – IDLE.

2. Master Switch – ON.

3. Fuel Valve – ON.


5. Fuel Auxiliary Pump Switch – ON.

6. Fuel Pressure Indicator – 5 PSIG minimum.

The recommended air start procedure is:

1. Starter Switch – ON.

The minimum gas generator RPM to obtain a satisfactory light is 12% Ng.

2. Engine Ignition Switch – ON.

3. Fuel Condition Lever – LOW IDLE / 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 evidenced first by a rise in gas generator RPM. A rise in the interturbine temperature will also be noted.

When the engine reaches idle RPM:

1. Engine Starter and Ignition Switches – OFF.



FAA APPROVED: Apr. 10, 2007 Revision 3, SECTION III-3

2. Propeller Lever – INTO OPERATING RANGE.

3. Power Lever – ADJUST to desired position.

4. Fuel Condition Lever – HIGH IDLE / FLIGHT IDLE.

5. CHECK that the Engine Operating Limits are not exceeded. If a satisfactory start is not obtained, discontinue the air start. Repeat the engine start procedure if another starting attempt is to be made.

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 50%. 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.

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: 1. Rear Occupant – COMMUNICATE intentions (Dual Cockpit Only)

If it is necessary to remove the cockpit door from its hinges, do the following: 2. KNOCK OUT the oval panel below the window.



FAA APPROVED: Apr. 10, 2007 Revision 3, SECTION III-4

3. REACH through the hole and pull the flexible hinge pin in and down until it disengages from the door hinges.

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

GENERATOR FAILURE: 1. Air Conditioner - off

2. RESET Generator

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

a. All other nonessential electrical equipment - OFF.

b. RESET Generator again

Thrush Aircraft Inc Model S2R-T34 SECTION IV Albany, GA

AIRPLANE FLIGHT MANUAL PERFORMANCE

FAA APPROVED: Oct. 24, 2006 Revision 2, SECTION IV-1

SECTION IV PERFORMANCE

TABLE OF CONTENTS

SUBJECT PAGE

POWER OFF STALL SPEEDS ................................................................................ IV-1 SPEEDS FOR BEST-RATE-OF-CLIMB ................................................................. IV-1

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 - Off

Configuration Clean T.O. / Landing Wing Flaps 0 degrees 15 degrees Dispersal Equipment None None

• Stall Entry Rate - Uniformly Decreasing • Gross Weight - 6000 pounds

POWER OFF STALL SPEEDS – MPH (CAS)

WING FLAPS 0 degrees 15 degrees GROSS WEIGHT

(pounds) 6000 6000

0° 69.5 65.0 30° 74.7 69.8 BLANK ANGLES

(degrees) 60° 98.3 91.9

SPEED FOR BEST RATE-OF-CLIMB:

GROSS WEIGHT (pounds) 6000 pounds Flaps 0 degrees 85 MPH (CAS) Flaps 15 degrees 81 MPH (CAS)

Thrush Aircraft Inc Model S2R-T34 LOG OF REVISIONS Albany, GA RESTRICTED CATEGORY AIRPLANE FLIGHT MANUAL SUPPLEMENT

FAA APPROVED: Revision 2, page 1 of 4

LOG OF REVISIONS

Revision Number

Page

Description of Revision

FAA Approved

1

3 of 5 Corrected typo, add the word MAX. Original approved By David Crew For Manager, Aircraft Certification


Administration Atlanta, Georgia Date: 4/7/2005

2

All

Revised formatting to match AFM.

___________________

Manager, Aircraft Certification


Administration Atlanta, Georgia

Date: _______________

Thrush Aircraft Inc Model S2R-T34 SECTION I Albany, GA LIMITATIONS RESTRICTED CATEGORY AIRPLANE FLIGHT MANUAL SUPPLEMENT


SECTION I LIMITATIONS

POWERPLANT: FUEL: JET A, JET B, JP-4, JP-5 or Automotive Diesel Number 1D or 2D in accordance with P&WC Specifications CPW 204, CPW 46 and CPW 381. (If jet fuel is not available, aviation gasoline, MIL-G-5572, all grades, may be used for a maximum of 150 hours between overhauls). Automotive diesel fuel is approved only for agricultural application flights and only when free air temperature is above +20ºF for grade No. 1D or above +40 ºF for grade No. 2D. Automotive Diesel Number 1D or 2D is prohibited for use in PT6A-41 or PT6A-42. WEIGHT AND CENTER OF GRAVITY: C.G. Range: Aft limit is 30.0 inches aft of Datum (Restricted Category). See chart on next page. MANEUVERS: Restricted Category flight maneuvers shall be limited to those normally performed in special purpose operations and approved by the Administrator. PLACARDS: A. Located on fuselage exterior near door:

“RESTRICTED” B. Located on cockpit wall:

“AUTOMOTIVE DIESEL FUEL IS APPROVED ONLY FOR AGRICULTURAL APPLICATION FLIGHTS AND ONLY WHEN THE FREE AIR TEMPERATURE IS ABOVE +20 DEGREES F, FOR GRADE NUMBER 1D, OR +40 DEGREES F FOR GRADE NUMBER 2D”

C. Located on right hand lower instrument panel:

“THIS AIRPLANE MUST BE OPERATED AS A RESTRICTED CATEGORY AIRPLANE IN ACCORDANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS AND THE AIRPLANE FLIGHT MANUAL. NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED. DESIGN MANEUVERING SPEED 126 MPH. MAX FLAP-DOWN SPEED 123 MPH. MAX CROSSWIND VELOCITY LANDING – 15 MPH. USEABLE TANK CAPACITY 114 GALLONS EACH SIDE.”



D. Located at both fuel filler caps: “FUEL – 115 GAL. CAP. JET A, JET B, JP-4, JP-5, DIESEL NO. 1D OR 2D” E. Located on top of hopper: “HOPPER CAPACITY 4000 LB”



7,000

6,500

6,000

5,500

5,000

4,500

4,000

3,500

3,00023.0 23.5 24.0 24.5 25.0 25.5 26.0 26.5 27.0 27.5 28.0 28.5 29.0 29.5 30.0 30.5 31.0

4,000 lbs@ 24.0 in

6,000 lbs@ 26.5 in

4,000 lbs

6,000 lbs@ 30.0 in

Center of Gravity - in. aft of datum

Airp

lane

Wei

ght -

lbs

Thrush S2R-T34 Single CockpitWeight & Center-of-Gravity Envelope

Restricted Category

Thrush Aircraft Inc Model S2R-T34 SECTIONS II, III & IV Albany, GA RESTRICTED CATEGORY AIRPLANE FLIGHT MANUAL SUPPLEMENT


SECTION II NORMAL PROCEDURES

NO CHANGE

SECTION III EMERGENCY PROCEDURES

NO CHANGE

SECTION IV PERFORMANCE

NO CHANGE

s2r t34 flight manual

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