Cessna TU206G STATIONAIR Pilot Operating Handbook Download

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SOLOY TURBINE PAC

SECTION 7

POHS CESSNA U/TU 206G

AIRPLANE & SYSTEMS

DESCRIPTION

7-13

F.A.A. Approved

October 4, 2005

A two-stage helical gear set in the engine power and accessory

gearbox reduces rotational speed from 33,290 RPM at 100% N

power

turbine speed to 6016 RPM at the output drive spline. A flex coupled

drive shaft is connected to the Soloy gear reduction system which uses

a single-stage helical gear set in the propeller gearbox to reduce

rotational speed from 6016 RPM at the input drive to 1810 RPM at the

propeller output at a reduction ratio of 3.32:1. The engine is rated at

418 shaft horsepower on a standard day at sea level, with 101.4 PSI of
indicated torque at 1810 propeller (N

) RPM. The speed of the gas

producer (N

) is the true speed of the compressor side of the engine

which is 53,519 RPM at 105% N

. Maximum permissible overspeed of

the engine is 54,028 RPM which equals 106% N

The power turbine gear train drives the propeller tachometer generator

and the power turbine governor. The compressor, fuel pump, gas

producer tachometer generator, gas producer fuel control, starter

generator and the vacuum pump are driven by the gas producer gear

train. The rest of the accessories are driven by the Soloy propeller

reduction gearbox. These include the propeller governor, propeller

overspeed governor, and the propeller gearbox oil pump. A spare

accessory pad is also drive by this gear train.

The Turbine Pac oil supply is contained in an integral tank. The

system has a capacity of 9 U.S. quarts and is provided with a dipstick.

ENGINE CONTROLS

The propulsion system is operated by a set of three controls. They

consist of the power control, propeller control, and fuel cutoff control.

POWER CONTROL

The power control in the cockpit is connected to the gas producer

fuel control unit on the engine. The power control controls engine

power through a machined gate system for the full power range.

With the power control pulled out and rotated to the left, the

engine will be operating in the GROUND IDLE mode and the

mode pointer will be on GROUND. FLIGHT IDLE is obtained by

pushing the power control in to the fixed stop and rotating it to the

right so the mode pointer is on FLIGHT. The remaining power

range can be obtained by pushing the power control in to increase

the engine power. A friction lock is located at the base of the

power control and is operated by rotating the lock clockwise to

increase friction or counter clockwise to decrease friction

UNCONTROLLED

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Summary of Contents for TU206G STATIONAIR

Page 1: ...______________ This Supplement must be attached to the Pilot s Operating Handbook POH when a Soloy LLC Turbine Pac engine is installed in accordance with S T C SA2353NM Information contained herein supplements or supersedes the basic POH only in those areas listed herein For limitations procedures and performance information not contained in this Supplement consult the basic POH F A A Approved ___...

Page 2: ...extra performance and greater utility than is available with the basic engine This Pilot s Operating Handbook Supplement has been prepared to specify the difference in operating procedures and performance In some cases only a specific item is changed while in others the entire paragraph or checklist is rewritten For information not included in this Supplement consult the basic POH U N C O N T R O ...

Page 3: ...ew or presently existing pages This bar will be located adjacent to the applicable revised area on the outer margin of the page LOG OF EFFECTIVE PAGES Dates of issue for original and revised pages are Original 1 4 85 Revision 10 3 29 91 Revision 1 1 11 85 Revision 11 4 2 91 Revision 2 1 18 85 Revision 12 7 30 92 Revision 3 4 15 85 Revision 13 12 23 99 Revision 4 1 27 86 Revision 14 5 7 01 Revision...

Page 4: ...13 15 2 5 16 3 14 15 2 6 16 3 15 15 2 7 17 3 16 15 2 8 17 3 17 15 2 9 16 3 18 15 2 10 16 3 19 15 2 11 17 3 20 15 2 12 17 4 1 17 2 13 16 4 2 17 2 14 16 4 3 15 2 15 16 4 4 15 2 16 16 4 5 15 2 17 16 4 6 15 2 18 16 4 7 17 2 19 16 4 8 17 2 20 16 4 9 15 2 21 16 4 10 17 2 22 16 4 11 15 3 1 15 4 12 15 3 2 15 4 13 15 3 3 15 4 14 15 3 4 15 4 15 17 3 5 15 4 16 15 NOTE Revised text is indicated by a revision ...

Page 5: ... 2 15 4 25 15 6 3 15 4 26 15 6 4 15 5 1 15 6 5 15 5 2 15 6 6 15 5 3 15 6 7 15 5 4 15 6 8 15 5 5 15 6 9 17 5 6 15 6 10 15 5 7 15 7 1 15 5 8 15 7 2 15 5 9 15 7 3 15 5 10 15 7 4 15 5 11 15 7 5 15 5 12 15 7 6 15 5 13 15 7 7 15 5 14 15 7 8 15 5 15 15 7 9 15 5 16 15 7 10 15 5 17 15 7 11 15 5 18 15 7 12 15 5 19 15 7 13 15 5 20 15 7 14 15 5 21 15 7 15 15 5 22 15 7 16 15 NOTE Revised text is indicated by a...

Page 6: ... 9 1 15 7 18 15 9 2 15 7 19 15 SS1 15 7 20 15 SS2 15 7 21 15 SS3 15 7 22 15 SS4 15 7 23 15 7 24 15 7 25 15 7 26 15 7 27 16 7 28 15 7 29 15 7 30 15 8 1 16 8 2 15 8 3 15 8 4 15 8 5 15 8 6 17 8 7 16 8 8 16 8 9 16 8 10 16 8 11 16 8 12 17 8 13 16 8 14 16 NOTE Revised text is indicated by a revision bar in the margin U N C O N T R O L L E D C O P Y ...

Page 7: ...fication Office ANM 100S Renton WA 98055 4056 Date 1 11 85 2 1 18 85 i ii iii iii a 6 8 9 2 and SS2 1 thru 4 Added Soloy Supp No 2 Engine Inlet Anti Ice Kit Lester H Berven for Manager Seattle Aircraft Certification Office ANM 100S Renton WA 98055 4056 Date 1 18 85 3 4 15 85 i ii iii iii a 1 7 3 4 3 5 4 3 4 8 4 9 4 19 4 20 5 1 5 6 5 7 5 8 5 11 thru 5 26 Added abbreviation terminology updated climb...

Page 8: ...2 5 2 6 2 6A 7 1 7 2A 7 2B 7 2C 7 3 7 3A 7 8 Added information on 2 engine instruments Lester H Berven for Manager Seattle Aircraft Certification Office ANM 100S Renton WA 98055 4056 Date 4 11 86 6 11 13 86 i ii iii iii a 7 2C 7 2D Original of Manual Lester H Berven for Manager Seattle Aircraft Certification Office ANM 100S Renton WA 98055 4056 Date 11 13 86 7 3 29 90 Title I iii a Added 1986 Seri...

Page 9: ...sed fuel vent and balance system Changed preflight inspection procedures Added second page to Log of Revisions Collet E McElroy for Manager Seattle Aircraft Certification Office ANM 100S Renton WA 98055 4056 Date 5 11 90 10 3 29 91 I ii iii iii b 2 7 6 4 Misc changes Richard A Paul for Manager Seattle Aircraft Certification Office ANM 100S Renton WA 98055 4056 Date 3 29 91 11 4 2 91 I ii iii b 7 2...

Page 10: ... Certification Office ANM 100S Renton WA 98055 4056 Date 7 30 92 13 12 23 99 I ii iii b 9 2 SS3 1 thru 3 Added Soloy Supplement No 3 Continuous Ignition Kit T E A for Manager Seattle Aircraft Certification Office ANM 100S Renton WA 98055 4056 Date 12 23 99 14 5 7 01 I ii iii iii a iii b iii c iii d 2 6 4 8 4 17 Changed markings on propeller tachometer in Limitations Section Changed auto feather te...

Page 11: ...rtification Office ANM 100S Renton WA 98055 4056 Date 10 4 05 16 11 14 14 Cover Removed prev revision signature and date for Manager Seattle Aircraft Certification Office ANM 100S Renton WA 98057 3356 Date i ix Reformatted revision log pages no content change Added Rev 16 Section 1 Section 2 Headers changed from Section I and II to Section 1 and 2 2 11 Corrected cold weather fuel spec number 2 12 ...

Page 12: ...pg xi Added page xii Updated TOC Added propeller RPM speed avoid range Updated Fuel Section formatting Updated Oil Specification Reference Updated engine start procedures Updated Auto feather procedure Updated amplified start procedures Added start gen cooling cycles Updated amplified prop avoid procedures Updated Table of Contents Corrected battery rack installation weights Updated formatting Upd...

Page 13: ...NTS SECTION GENERAL 1 LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT BALANCE EQUIPMENT LIST 6 AIRPLANE SYSTEMS DESCRIPTION 7 AIRPLANE HANDLING SERVICE MAINTENANCE 8 SUPPLEMENTS Optional Systems Description Operating Procedures 9 U N C O N T R O L L E D C O P Y ...

Page 14: ...SOLOY TURBINE PAC POHS CESSNA U TU 206G xii F A A Approved November 17 2015 THIS PAGE INTENTIONALLY LEFT BLANK U N C O N T R O L L E D C O P Y ...

Page 15: ...d Weights 1 5 Standard Airplane Weights 1 5 Cabin Entry Dimensions 1 5 Baggage Space and Cargo Door Dimensions 1 5 Specific Locations 1 5 Symbols Abbreviations and Terminology 1 6 General Airspeed Terminology 1 6 Meteorological Terminology 1 7 Engine Power Terminology 1 7 Engine Controls and Instruments 1 8 Airplane Performance and Flight Planning Terminology 1 9 Weight and Balance Terminology 1 9...

Page 16: ...SOLOY TURBINE PAC SECTION 1 POHS CESSNA U TU 206G GENERAL 1 2 F A A Approved November 14 2014 This page left blank intentionally U N C O N T R O L L E D C O P Y ...

Page 17: ...SOLOY TURBINE PAC SECTION 1 POHS CESSNA U TU 206G GENERAL 1 3 F A A Approved November 14 2014 Figure 1 1 Three View U N C O N T R O L L E D C O P Y ...

Page 18: ...ine Pac 780 1000 1 Horsepower Rating and Engine Speed Takeoff power 5 minute 418 SHP 1810 RPM Maximum continuous Power 321 SHP 1810 RPM PROPELLER Propeller Manufacturer Hartzell Propeller Model Number HC C3YN 5A FC9587D 2 Number of Blades 3 Propeller Diameter 95 Inches Propeller Type Constant speed hydraulically actuated full feathering FUEL Approved Fuel Grades See handling service and maintenanc...

Page 19: ...ndard Empty Weight Stationair 6 6 seats 1927 lbs Stationair 6 II 6 seats 1987 lbs Utility Option 1 seat 1882 lbs II Utility Option 1 seat 1941 lbs Maximum Useful Load Stationair 6 6 seats 1685 lbs Stationair 6 II 6 seats 1625 lbs Utility Option 1 seat 1730 lbs II Utility Option 1 seat 1671 lbs CABIN AND ENTRY DIMENSIONS Detailed dimensions of the cabin interior and entry door opening are illustrat...

Page 20: ...vering Speed is the maximum speed at which you may use abrupt control travel VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position VMO Maximum Operating Limit Speed is the speed limit that may not be deliberately exceeded in normal flight operations VS Stalling Speed or the minimum steady flight speed at which the airplane is controllabl...

Page 21: ...een starter actuation and N1 stabilization at GROUND IDLE FLAMEOUT Unintentional loss of combustion chamber flame during operation FLIGHT IDLE Minimum position of the power control while airborne GAS PRODUCER RPM N1 Indicates the percent of gas producer compressor RPM based on a figure of 100 at 50 970 RPM GROUND IDLE Minimum position of the power control when the airplane is not airborne HOT STAR...

Page 22: ...tection for the engine FUEL CUTOFF CONTROL A cockpit control that is connected to the fuel control unit The cockpit control has two positions only RUN IN and CUTOFF OUT GAS PRODUCER FUEL CONTROL An engine mounted component that regulates fuel flow to the engine It responds to compressor discharge pressure gas producer turbine speed N1 and the cockpit power control POWER CONTROL A cockpit control t...

Page 23: ...vailable for flight planning UNUSABLE FUEL Unusable Fuel is the quantity of fuel that cannot be safely used in flight GPH Gallons Per Hour is the amount of fuel in gallons consumed per hour NMPG Nautical Miles Per Gallon is the distance in nautical miles which can be expected per gallon of fuel consumed at a specific engine power setting and or flight configuration g g is acceleration due to gravi...

Page 24: ...t a given weight STANDARD EMPTY WEIGHT Standard Empty Weight is the weight of a standard airplane including unusable fuel full operating fluids and full engine oil BASIC EMPTY WEIGHT Basic Empty Weight is the standard empty weight plus the weight of optional equipment USEFUL LOAD Useful Load is the difference between ramp weight and the basic empty weight MAXIMUM RAMP WEIGHT Maximum Ramp Weight is...

Page 25: ...nt Markings 2 7 Miscellaneous Instrument Markings 2 8 Weight Limits 2 9 Center of Gravity Limits 2 9 Maneuver Limits 2 9 Flight Load Factor Limits 2 9 Kinds of Operation Limits 2 10 Fuel Limitations 2 10 Minimum Fuel 2 11 Approved Fuel Grades 2 11 Cold Weather Fuel Altitude Restrictions 2 11 Fuel Additive 2 11 Oil Specifications 2 12 Other Limitations 2 12 Flight Idle Limits 2 12 Flap Limitations ...

Page 26: ...SOLOY TURBINE PAC SECTION 2 POHS CESSNA U TU 206G LIMITATIONS 2 2 F A A Approved November 14 2014 This page left blank intentionally U N C O N T R O L L E D C O P Y ...

Page 27: ...s section is mandatory AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown in Figure 2 1 SPEED KCAS KIAS REMARKS VMO Maximum operating speed 148 149 Do not exceed in any operation VA Maneuvering speed 3600 pounds 2900 pounds 2200 pounds 121 109 95 120 108 94 Do not make full or abrupt control movements above this speed VFE Maximum flap extended speed to 10 flaps ...

Page 28: ...m weight stalling speed in landing configuration Vso The transition point from narrow to wide arc is the stall speed with wing flaps in up position Upper limit is the maximum speed permissible with flaps extended Red Line 149 Maximum speed for all operations Figure 2 2 Airspeed Indicator Markings POWERPLANT LIMITATIONS Engine Manufacturer Soloy LLC Rolls Royce Engine Model Number Soloy Turbine Pac...

Page 29: ...90 7 Starting 927 4 12 5 150 8 6 Figure 2 3 Engine Operating Limits NOTES 1 N1 and oil pressure limits are noted by a step in their respective arcs N1 Engine Oil Pressure 79 and below 50 130 psi 79 to 94 90 130 psi 94 and above 115 130 psi 2 Transient TOT allowable from 810 C for 6 seconds Intentional use not recommended 3 N1 should not exceed 105 to 106 for more than 15 seconds 4 Starting TOT all...

Page 30: ... should not exceed 1810 to 1990 rpm for more than 15 seconds 8 150 psi oil pressure is allowable following an engine start Do not increase power until normal oil pressure limits are attained PROPELLER LIMITATIONS Propeller Manufacturer Hartzell Propeller Model Number HC C3YN 5A FC9587D 2 Number of Blades 3 Propeller Diameter 95 0 Inches Propeller Blade Angle at 30 Inch Station Low 5 Feathered 81 P...

Page 31: ...ATING NORMAL RANGE CAUTION RANGE MAXIMUM MAXIMUM PEAK START LIMIT PROPELLER 1630 to 1810 RPM 1480 to 1630 RPM 4 5 1810 RPM 1990 RPM 3 N1 12 to 15 59 59 105 1 105 106 3 TORQUE 0 78 PSI 2 78 101 4 PSI 101 4 PSI TOT 150 C 400 738 C 738 810 C 810 C 843 C 3 927 C ENGINE OIL TEMP 0 107 C 107 C ENGINE OIL PRESSURE 50 PSI 90 130 PSI 1 50 90 PSI 1 130 PSI 150 PSI TRANS MISSION OIL PRESS 40 PSI 40 60 PSI 60...

Page 32: ...re 2 5 Miscellaneous Instrument Markings NOTES 1 N1 and oil pressure limits are noted by a step in their respective arcs N1 Engine Oil Pressure 79 and below 50 130 psi 79 to 94 90 130 psi 94 and above 115 130 psi 2 Minimum in flight torque is 14 psi 3 Not for intentional use 4 Limit 60 seconds at torque settings greater than 20 psi 5 Aircraft incorporating an enhanced power turbine wheel per Rolls...

Page 33: ... 33 0 inches aft of datum at 2500 lbs or less with straight line variation to 42 5 inches aft of datum at 3600 lbs Aft 49 7 inches aft of datum at all weights Reference Datum Lower portion of front face of firewall MANEUVER LIMITS This airplane is certificated in the normal category The normal category is applicable to aircraft intended for non aerobatic operations These include any maneuvers inci...

Page 34: ...ion of the system shall not be made until the above mentioned conditions no longer exist and all accumulated airframe ice and or snow has dissipated CAUTION SIGNIFICANT POWER LOSS WILL OCCUR WHILE OPERATING IN THE ALTERNATE AIR MODE EXTREME CAUTION SHOULD BE USED TO MAINTAIN A MINIMUM OF 14 PSI TORQUE IN FLIGHT ON APPROACH TO LANDING FUEL LIMITATIONS For aircraft with individual tank selector valv...

Page 35: ...1 PRIMARY FUELS A MIL T 5624 Grade JP 5 B MIL T 83133 Grade JP 8 C ASTM D 1655 Jet A or A1 D JP 1 Fuel Conforming to ASTM D 1655 Jet A E Diesel 1 Fuel Conforming to ASTM D 1655 Jet A 2 COLD WEATHER FUELS To assure consistent starts below 4 C 40 F the following fuels may be necessary A MIL T 5624 Grade JP 4 B ASTM D 6615 Jet B C AVGAS JET A JET A1 or JP 5 Mixture COLD WEATHER FUEL ALTITUDE RESTRICT...

Page 36: ...RY SO NO ADDITIONAL ADDITIVES SHOULD BE ADDED Refer to Section 8 Handling Service Maintenance for further information NOTE Fuel containing Tri Cresyl Phosphate TCP additives shall not be used OIL SPECIFICATIONS The 250 series engines are certified and approved for use with only certain lubricating oils that comply with MIL PRF 7808 MIL PRF 23699 DOD PRF 85734 or SAE AS5780 specifications Refer to ...

Page 37: ...elow will vary as the airplane is equipped For S Ns U20602589 U20604650 thru U20606847 and on The markings and placards installed in this airplane contain operating limitations which must be complied with when operating this airplane in the Normal Category Other operating limitations which must be complied with when operating this airplane in this category are contained in the Pilot s Operating Ha...

Page 38: ... as a normal category airplane in compliance with the operating limitations stated in the form of placards markings and manuals _________________MAXIMUMS_________________ U206 TU206G Landplane Maneuvering Speed IAS 120 Knots Gross Weight 3600 Lbs Flight Load Factor Flaps Up 3 8 1 52 Flaps Down 2 0 No acrobatic maneuvers including spins approved Altitude loss in a stall recovery 240 feet Flight int...

Page 39: ... 206G LIMITATIONS 2 15 F A A Approved November 14 2014 3 On fuel selector plate For S Ns U20603522 thru U20604649 TWO POSITION SELECTOR VALVE FOUR POSITION SELECTOR VALVE USABLE FUEL 76 U S GAL FUEL SELECTOR ON OFF U N C O N T R O L L E D C O P Y ...

Page 40: ...ITATIONS 2 16 F A A Approved November 14 2014 3 On fuel selector plate For S Ns U20602589 U20604650 thru U20606847 and on TWO POSITION SELECTOR VALVE FOUR POSITION SELECTOR VALVE USABLE FUEL 88 U S GAL FUEL SELECTOR ON OFF U N C O N T R O L L E D C O P Y ...

Page 41: ...ler cap For S Ns U20602589 U20603522 thru U20606847 and on 6 Near alternate air control For S Ns U20602589 U20603522 thru U20606847 and on FUEL JET A SEE PILOT S OPERATING HANDBOOK FOR ANTI ICE ADDITIVE REQUIREMENT AND ALTERNATE FUELS N O R M A L ALT OPERATION REQUIRED T IN FALLING OR BLOWING SNOW A IN VISIBLE MOISTURE AT AN I OAT OF 5ºC 41ºF AND BELOW R A L T OIL U N C O N T R O L L E D C O P Y ...

Page 42: ...dicator For S Ns U20602589 U20603522 thru U20606847 and on 8 On the warning lights dimmer switch For S Ns U20602589 U20603522 thru U20606847 and on 9 Next to the power control For S Ns U20602589 U20603522 thru U20606847 and on 1 3 7 9 6 GROUND FLIGHT POWER PUSH INCR WARNING LIGHTS D B I R M T U N C O N T R O L L E D C O P Y ...

Page 43: ...20602589 U20603522 thru U20606847 and on 11 Next to the fuel cutoff control For S Ns U20602589 U20603522 thru U20606847 and on 12 Between the fuel gauges For S Ns U20602589 U20603522 thru U20606847 and on PROP RPM PULL FTHR FUEL PULL CUT OFF DO NOT TAKEOFF OR CLIMB BELOW VY IF FUEL GAUGES INDICATE IN YELLOW ARC U N C O N T R O L L E D C O P Y ...

Page 44: ...ER TO WEIGHT AND BALANCE DATA FOR BAGGAGE AND CARGO LOADING BAGGAGE NET 180 LBS MAX CAPACITY REFER TO WEIGHT AND BALANCE DATA FOR BAGGAGE AND CARGO LOADING EMERGENCY EXIT OPERATION 1 OPEN FORWARD CARGO DOOR AS FAR AS POSSIBLE 2 ROTATE RED LEVER IN REAR CARGO DOOR FORWARD 3 FORCE REAR CARGO DOOR FULL OPEN EMERGENCY EXIT OPERATION 1 ROTATE FORWARD CARGO DOOR HANDLE FULL FORWARD THEN FULL AFT 2 OPEN ...

Page 45: ... U20606847 and on 17 A calibration card is provided to indicate the accuracy of the magnetic compass in 30º increments 18 Forward of each fuel tank filler cap in line with forward arrow For S Ns U20602589 U20604650 thru U20606847 and on MAXIMUM ALTITUDE 8 000 FEET WHEN USING COLD WEATHER FUEL AT FUELTEMPERATURES ABOVE 4 C MANUVER SPEED 120 KIAS FUEL CAP FWD ARROW ALIGNMENT CAP MUST NOT ROTATE DURI...

Page 46: ...SOLOY TURBINE PAC SECTION 2 POHS CESSNA U TU 206G LIMITATIONS 2 22 F A A Approved November 14 2014 This page left blank intentionally U N C O N T R O L L E D C O P Y ...

Page 47: ... Landings 3 5 Emergency Landing Without Engine Power 3 5 Precautionary Landing With Engine Power 3 6 Ditching 3 6 Fires 3 6 During Start on Ground 3 6 Engine Fire In Flight 3 7 Electrical Fire In Flight 3 7 Cabin Fire 3 8 Wing Fire 3 8 Icing 3 9 Inadvertent Icing Encounter 3 9 Alternate Air Operation 3 9 Engine Alternate Air Failure 3 10 Static Source Blockage Erroneous Instrument Reading Suspecte...

Page 48: ...3 16 Engine Alternate Air System Failure 3 16 Alternate Air Light Does Not Illuminate 3 17 Alternate Air Light Illuminates In Flight 3 17 Static Source Blocked 3 17 Spins 3 17 Rough Engine Operation or Loss of Power 3 18 Compressor Stall 3 18 Fuel Filter Bypass 3 18 Auto Feather System Failure In Flight 3 18 Low Engine Oil Pressure and or Low Transmission Pressure 3 19 Oil Chip Detector 3 19 Elect...

Page 49: ... should an emergency arise the basic guidelines described in this section should be considered and applied as necessary to correct the problem Emergency procedures associated with ELT and other optional systems can be found in Section 9 AIRSPEEDS FOR EMERGENCY OPERATION Engine Failure After Takeoff Wing Flaps Up 80 KIAS Wing Flaps Down 70 KIAS Maximum Glide 3600 Lbs 82 KIAS 3200 Lbs 76 KIAS 2800 L...

Page 50: ... Flaps AS REQUIRED 40 recommended 6 Battery OFF ENGINE FAILURE DURING FLIGHT 1 Airspeed BEST GLIDE SPEED 2 Fuel Cutoff Control CUTOFF OUT 3 Monitor TOT 4 Propeller Control FEATHER OUT 5 Power Control FLIGHT IDLE 6 Generator OFF 7 Electrical Load REDUCE 8 If airstart is warranted refer to ENGINE RESTART PROCEDURE CHECKLIST 9 If airstart is not warranted refer to EMERGENCY LANDING WITHOUT ENGINE POW...

Page 51: ...HE GAS PRODUCER SECTION OF THE ENGINE MAY LOCK UP AFTER AN IN FLIGHT SHUTDOWN THIS IS A TEMPORARY CONDITION WHICH EXISTS AFTER THE ENGINE HAS BEEN SHUTDOWN FOR APPROXIMATELY ONE MINUTE AND WHICH MAY CONTINUE FOR UP TO TEN MINUTES FOLLOWING SHUTDOWN THEREFORE EXCEPT DURING AN EMERGENCY AIR STARTS SHOULD NOT BE ATTEMPTED DURING THE TIME PERIOD BETWEEN ONE MINUTE AFTER SHUTDOWN AND TEN MINUTES AFTER ...

Page 52: ...AYDAY on 121 5 MHz giving location and intentions 2 Heavy Objects in baggage area SECURE OR JETTISON 3 Wing Flaps 40 4 Approach High Winds Heavy Seas INTO THE WIND Light Winds Heavy Swells PARALLEL TO SWELL 5 Power ESTABLISH 300 FT MIN DESCENT AT 65 KIAS 6 Cabin Doors UNLATCH 7 Touchdown LEVEL ATTITUDE AT 300 FT MIN DESCENT 8 Face CUSHION at touchdown with folded coat 9 Airplane EVACUATE through c...

Page 53: ...tor OFF 4 Battery and Generator OFF except IFR 5 Cabin Heat and Air OFF except overhead vent 6 Airspeed 105 KIAS If fire is not extinguished increase glide speed to find an airspeed which will provide an incombustible mixture 7 Forced Landing EXECUTE as described in Emergency Landing Without Engine Power ELECTRICAL FIRE IN FLIGHT 1 Battery and Generator OFF 2 All Other Switches OFF 3 Vents Cabin A...

Page 54: ...extinguished CABIN FIRE 1 Master Switch OFF 2 Vents Cabin Air Heat CLOSED to avoid drafts 3 Fire Extinguisher ACTIVATE if available WARNING AFTER THE FIRE IS EXTINGUISHED IF AN OXYGEN SYSTEM IS AVAILABLE OCCUPANTS SHOULD USE OXYGEN MASKS UNTIL SMOKE AND DISCHARGED DRY POWDER CLEARS AFTER DISCHARGING AN EXTINGUISHER WITHIN A CLOSED CABIN VENTILATE THE CABIN 4 Land the airplane as soon as possible t...

Page 55: ...OPERATION 1 Engine alternate air lever ALT monitor ALT AIR light 2 Visually check that the ram inlet doors are raised NOTE A drop in torque and a rise in TOT is normal with the actuation of the engine ice protection system 3 Turn pitot heat switch ON if installed0 4 Turn back or change altitude to obtain an OAT that is less conducive to icing 5 Turn cabin heat control ON and rotate the defrost kno...

Page 56: ...are out 13 Missed approaches should be avoided ENGINE ALTERNATE AIR FAILURE ALTERNATE AIR LIGHT DOES NOT ILLUMINATE 1 Visually check that the ram inlet doors are raised 2 If doors are not raised cycle the alternate air control and check for reverse operation 3 If system has failed in the NORMAL mode leave the icing condition or snow as soon as possible ALTERNATE AIR LIGHT ILLUMINATES IN FLIGHT 1 C...

Page 57: ...dicated by the GEN OFF BUS Warning Light 1 Trip and reset the generator trip reset switch If light remains on 2 Generator Switch OFF 3 Generator Field Circuit Breaker RESET 4 Generator Switch ON If light remains on and ammeter shows no amps 5 Generator Field Circuit Breaker PULL 6 Non essential Radio Electrical Equipment OFF 7 Flight TERMINATE as soon as practical AUTO FEATHER SYSTEM FAILURE IN FL...

Page 58: ...SOLOY TURBINE PAC SECTION 3 POHS CESSNA U TU206G EMERGENCY PROCEDURES 3 12 F A A Approved October 4 2005 This page left blank intentionally U N C O N T R O L L E D C O P Y ...

Page 59: ... be planned straight ahead with only small changes in direction to avoid obstructions Altitude and airspeed are seldom sufficient to execute a 180 gliding turn necessary to return to the runway The checklist procedures assume that adequate time exists to secure the fuel and ignition systems prior to touchdown After an engine failure in flight the best glide speed as shown in Figure 3 1 should be e...

Page 60: ...tely 90 KIAS and flaps set to 20 by using throttle and trim tab controls Then do not change the trim tab setting and control the glide angle by adjusting power exclusively At flareout the nose down moment resulting from power reduction is an adverse factor and the airplane may hit on the nose wheel Consequently at flareout the trim tab should be set at full nose up position and the power adjusted ...

Page 61: ...ane wing opposite the lower left index mark for 60 seconds Then roll back to level flight by leveling the miniature airplane 4 Check accuracy of the turn by observing the compass heading which should be the reciprocal of the original heading 5 If necessary adjust heading primarily with skidding motions rather than rolling motions so that the compass will read more accurately 6 Maintain altitude an...

Page 62: ...lane in the turn coordinator with the horizon reference line 3 Cautiously apply control wheel back pressure to slowly reduce the indicated airspeed to 95 KIAS 4 Adjust the elevator trim control to maintain a 95 KIAS glide 5 Keep hands off the control wheel using rudder control to hold a straight heading Use rudder trim to relieve unbalanced rudder force if present 6 Upon breaking out of clouds res...

Page 63: ...t doors are raised cycle the alternate air control to check for reverse operation If the ram inlet doors are not raised land as soon as practicable and check for a blocked inlet or a faulty micro switch on the alternate air door STATIC SOURCE BLOCKED If erroneous readings of the static source instruments airspeed altimeter and rate of climb are suspected the alternate static source valve should be...

Page 64: ...POWER COMPRESSOR STALL In the event of an engine compressor stall noted by a bang or popping noise and or engine surging slowly reduce power and if it continues land as soon as practicable If compressor stall is still noted at flight idle power shut down the engine and proceed with the Engine Out landing procedure If a flameout occurs attempt one restart to check for normal operation FUEL FILTER B...

Page 65: ...r can also cause malfunctions Problems of this nature constitute an electrical emergency and should be dealt with immediately Electrical power malfunctions usually fall into two categories excessive generator output and insufficient generator output The paragraphs below describe the recommended remedy for each situation EXCESSIVE GENERATOR OUTPUT After engine starting and heavy electrical usage th...

Page 66: ...on as practicable CARGO DOOR EMERGENCY EXIT If it is necessary to use the cargo doors as an emergency exit and the wing flaps are not extended open the forward door and exit If the wing flaps are extended open the doors in accordance with the instructions shown on the placard which is mounted on the forward cargo door FUEL LOW LIGHT ILLUMINATION if installed The RIGHT LEFT FUEL LOW light will illu...

Page 67: ... Right Wing 4 5 Nose 4 5 Left Wing 4 6 Left Wing Leading Edge 4 6 Left Wing Trailing Edge 4 6 Before Starting Engine 4 6 Starting Engine 4 7 Aborted Start Procedure 4 7 Before Takeoff 4 8 Takeoff 4 9 Normal Takeoff 4 9 Short Field Takeoff 4 9 Enroute Climb 4 9 Normal Climb 4 9 Maximum Performance Climb 4 9 Cruise 4 10 Descent 4 10 Before Landing 4 10 Landing 4 10 Normal Landing 4 10 Short Field La...

Page 68: ... Engine 4 15 Taxiing 4 17 Before Takeoff 4 18 Takeoff 4 19 Wing Flap Settings 4 20 Crosswind Takeoff 4 20 Enroute Climb 4 21 Cruise 4 21 Flight in Icing Conditions 4 22 Stalls 4 22 Landings 4 22 Short Field Landing 4 23 Crosswind Landing 4 23 Balked Landing 4 23 Securing Airplane 4 23 Cold Weather Operation 4 24 Hot Weather Operation 4 26 Noise Abatement 4 26 U N C O N T R O L L E D C O P Y ...

Page 69: ...and climb performance the speed appropriate to the particular weight must be used Takeoff Normal Climb Out 80 90 KIAS Short Field Takeoff Flaps 20 Speed at 50 Feet Best Angle 60 KIAS Enroute Climb Flaps Up Normal 100 120 KIAS Best Rate of Climb Sea Level 87 KIAS Best Rate of Climb 20 000 Feet 71 KIAS Best Angle of Climb Sea Level 65 KIAS Landing Approach Normal Approach Flaps Up 75 85 KIAS Normal ...

Page 70: ...inside handle lock the door from the outside by means of the T handle stored in the map compartment NOTE The cargo doors must be fully closed and latched before operating the electric wing flaps A switch in the upper door sill of the front cargo door inter rupts the wing flap electrical circuit when the front door is opened or removed thus preventing the flaps being lowered with possible damage to...

Page 71: ...anks and engine fuel filter to check for water and sediment The fuel selector valve must be ON while the engine fuel filter is being drained If water is observed perform further draining at all fuel drain points until clear and then gently rock wings and lower tail to the ground to move any additional contaminants to the sampling points Take repeated samples from all fuel drain points until all co...

Page 72: ...over REMOVE and check opening for stoppage 2 Stall Warning Vane CHECK for freedom of movement while master switch is momentarily turned on horn should sound when vane is pushed upward 3 Wing Tie Down DISCONNECT 4 Fuel Tank Vent CHECK for blockage 8 LEFT WING Trailing Edge 1 Aileron CHECK freedom of movement and security 2 Flap CHECK play and security BEFORE STARTING ENGINE 1 Preflight Inspection C...

Page 73: ...45 13 18 to 7 0 to 44 12 Below 18 0 6 TOT and N1 MONITOR TOT 810 to 927 C 10 seconds maximum and N1 for normal acceleration 7 Propeller NP CHECK rotating by 25 N1 8 Transmission Oil Pressure POSITIVE indication at completion of the start 9 Start Switch RELEASE at 58 N1 within 25 to 60 seconds 10 APU DISCONNECT if used 11 Generator Switch ON 12 N1 CHECK 59 MINIMUM If not turn off generator and add ...

Page 74: ...ed governor will be indicated by the propeller speed being limited to approximately 1450 Np RPM as the power is increased E Reduce the Power Control to GROUND IDLE Propeller speed will reduce along with this power reduction F Release the test switch 9 Suction Gauge CHECK 4 6 to 5 4 in Hg 10 Alternate Air Cycle check for light and ram inlet doors 11 Anti Ice if installed PULL ON Check for rise in T...

Page 75: ...d 60 KIAS until all obstacles are cleared 7 Wing Flaps RETRACT after obstacles are cleared and 80 90 KIAS is reached NOTE Do not reduce power until wing flaps have been retracted WARNING WITH 1 8 FUEL TANK QUANTITY OR LESS OR IF THE INSTALLED FUEL LOW LIGHTS ARE ON TAKEOFF IS PROHIBITED ENROUTE CLIMB NORMAL CLIMB 1 Airspeed 100 120 KIAS 2 Ice Protection AS REQUIRED 3 Power Control 78 PSI Torque or...

Page 76: ...Ice Protection AS REQUIRED CAUTION SIGNIFICANT POWER LOSS WILL OCCUR WHILE OPERATING IN THE ALTERNATE AIR MODE EXTREME CAUTION SHOULD BE USED TO MAINTAIN A MINIMUM OF 14 PSI TORQUE IN FLIGHT ON APPROACH TO LANDING 2 Propeller Control IN 3 Fuel Selector ON BOTH if fuel low warning system installed 4 Autopilot OFF if installed 5 Landing and Taxi Lights AS REQUIRED 6 Wing Flaps Down 0 to 10 below 137...

Page 77: ... to 20 4 Airspeed 70 80 KIAS after all obstacles are cleared 5 Wing Flaps UP as soon as all obstacles are cleared and a safe altitude and airspeed are obtained 6 Trim ADJUST for climb AFTER LANDING 1 Pitot Heat OFF 2 Wing Flaps RETRACT 3 Lights AS REQUIRED SECURING AIRPLANE 1 Parking Brake SET 2 Avionics and Electrical Equipment OFF 3 Power Control N1 59 65 two minutes including taxi 4 Fuel Cutoff...

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Page 79: ...wn the engine and recheck the oil level If the oil level is back up to normal take the appropriate maintenance actions If the quantity of the oil remains low following the check add oil to the low operation limit of 4 U S quarts It is possible for the impending oil bypass indicators to extend during a start when the oil is cold and give an erroneous indication of a dirty oil filter If an impending...

Page 80: ...l is in the CUTOFF position OUT Place the propeller control fully FORWARD and the power control at GROUND IDLE Prior to starting the engine check that all electrical switches and avionics are OFF and that all circuit breakers are IN CAUTION PRIOR TO TURNING THE BATTERY SWITCH ON OR APPLYING AN EXTERNAL POWER SOURCE THE AVIONICS POWER SWITCH LABELED AVIONICS POWER SHOULD BE TURNED OFF TO PREVENT AN...

Page 81: ...and depend upon the engine in the future it is the responsibility of the pilot and maintenance personnel to record and to take the recommended corrective actions after overtemperature occurs Residual TOT should be no more than 150 C when lightoff is attempted The TOT can be readily reduced to or below 150 C by motoring the engine with the start motor switch After motoring to cool the engine procee...

Page 82: ... the start but motor the engine for 10 seconds to clear the combustion chamber of residual fuel For subsequent starting attempts repeat the complete starting sequence Monitor the TOT throughout the start The TOT limits during the start are as follows TEMPERATURE RANGE TIME Up to 810 C No Limit 810 927 C 10 Seconds 927 C 1 Second Over 927 C Not Allowed NOTE Refer to the Rolls Royce 250 C20 Series O...

Page 83: ... the start NOTE The OIL PRESS LOW warning light will be illuminated and the transmission oil pressure will remain at approximately 10 PSI until the propeller comes out of the feather position then the pressure will rapidly increase to approximately 50 PSI and the warning light will go off Release the start switch when 58 N1 speed is reached If an APU was used for the start disconnect it prior to t...

Page 84: ... that the engine instruments are normal and the flight controls are free and correct Set the propeller control fully forward Trim should be set to the TAKEOFF position Set the power control to GROUND IDLE CAUTION AVOID CONTINUOUS OPERATION 60 SECONDS BETWEEN 1358 RPM AND 1630 RPM PROPELLER SPEED AT TORQUE SETTING GREATER THAN 20 PSI To test the auto feather system press the propeller overspeed gov...

Page 85: ...e alternate air is in use Wing flaps should be checked and set from 0 to 20 TAKEOFF With the propeller control set fully FORWARD advance the power control to FLIGHT IDLE and allow the engine to stabilize at 1810 Np RPM prior to advancing the power control to TAKEOFF Monitor the engine instruments throughout the takeoff The TOT ENGINE TORQUE and SPEED limits for takeoff are as follows TEMPERATURE R...

Page 86: ...low attitude However the airplane should be leveled off immediately to accelerate to a safe climb speed If 20 wing flaps are used for takeoff they should be left down until all obstacles are cleared To clear an obstacle with 20 flaps a 60 KIAS climb speed should be used If no obstructions are ahead a best rate of climb speed of 80 KIAS would be most efficient Flap deflections greater than 20 are n...

Page 87: ...4 PSI 5 Minutes Over 101 4 PSI Not Allowed CRUISE Set cruise power and observe the 738 TOT and the 78 PSI torque limits Set propeller RPM as desired between 1630 RPM and 1810 RPM CAUTION AVOID CONTINUOUS OPERATION 60 SECONDS BETWEEN 1358 RPM AND 1630 RPM PROPELLER SPEED AT TORQUE SETTING GREATER THAN 20 PSI Check the reading of the engine instruments and monitor fuel gauges during flight The power...

Page 88: ...ed STALLS The stall characteristics are conventional and aural warning is provided by a stall warning horn which sounds between 5 and 10 knots above the stall in all configurations Power off stall speeds at maximum weight for both forward and aft C G are presented in Section 5 LANDINGS Landing should be made on the main wheels first to reduce the landing speed and subsequent need for braking in th...

Page 89: ...ection may be used the wing low method gives the best control After touchdown hold a straight course with the steerable nose wheel and occasional braking if necessary BALKED LANDING In a balked landing go around climb apply power as required and maintain torque and TOT within allowable limits The flap setting should be reduced to 20 After all obstacles are cleared and a safe altitude and airspeed ...

Page 90: ...irds and debris Install the control locks propeller bungee and exhaust covers COLD WEATHER OPERATION Use appropriate covers on the aircraft when it is parked Make certain the compressor rotor is not frozen if the aircraft is in a freezing atmosphere To assure consistent starts below 4 C 40 F cold weather fuels as described in the limitations Section 2 are recommended Additionally for flight at amb...

Page 91: ...rt If NP is not rotating by 25 N1 speed abort the start If the propeller can be turned by hand a second or third start attempt may be made If the engine has been shut down for more than 15 minutes stabilize at GROUND IDLE for one minute before increasing power NOTE After a cold weather battery start allow the engine to run at GROUND IDLE for two minutes before actuating the generator switch This w...

Page 92: ...e areas should make every effort to fly not less than 2000 feet above the surface weather permitting even though flight at a lower level may be consistent with the provisions of government regulations 2 During departure from or approach to an airport climb after takeoff and descent for landing should be made so as to avoid prolonged flight at low altitude near noise sensitive areas NOTE The above ...

Page 93: ...e of Climb Maximum Continuous Power Temperature Standard 5 14 Time Fuel and Distance to Climb Maximum Rate of Climb Maximum Continuous Power Temperature Standard 20 C 5 15 Time Fuel and Distance to Climb Maximum Rate of Climb Maximum Continuous Power Temperature Standard 20 C 5 16 Figure 5 11 Cruise Performance Sea Level and 2 000 Feet 5 17 Cruise Performance 4 000 and 6 000 Feet 5 18 Cruise Perfo...

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Page 95: ...are presented so that you may know what to expect from the airplane under various conditions and also to facilitate the planning of flights in detail and with reasonable accuracy The data in the charts has been computed from actual flight tests using average piloting techniques with the airplane and engine in good condition U N C O N T R O L L E D C O P Y ...

Page 96: ...AS KCAS 40 52 50 59 60 66 70 75 80 84 90 94 100 103 FLAPS 40 KIAS KCAS 40 52 50 59 60 66 70 75 80 85 90 94 100 104 ALTERNATE STATIC SOURCE VENTS AND WINDOWS CLOSED FLAPS UP KIAS KCAS 50 60 60 65 70 71 80 78 90 87 100 96 110 105 120 115 130 124 140 133 150 143 FLAPS 20 KIAS KCAS 40 50 50 53 60 60 70 67 80 76 90 85 100 94 FLAPS 40 KIAS KCAS 40 48 50 55 60 62 70 71 80 79 90 89 100 99 Figure 5 1 Airsp...

Page 97: ...ON 5 POHS CESSNA U TU 206G PERFORMANCE 5 5 F A A Approved October 4 2005 Figure 5 2 Temperature Conversion Chart 60 40 20 0 20 40 120 100 80 60 40 20 0 20 40 DEGREES FAHRENHEIT DEGREES CELSIUS U N C O N T R O L L E D C O P Y ...

Page 98: ...during a stall recovery may be as much as 240 feet 2 KIAS values are approximate MOST REARWARD CENTER OF GRAVITY WEIGHT LBS FLAP DEFLECTION ANGLE OF BANK 0 30 45 60 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 3600 UP 46 56 52 60 61 67 76 79 3600 20 36 49 42 53 49 58 64 69 3600 40 33 47 39 51 52 56 65 66 Figure 5 3 Stall Speeds Sheet 1 of 2 U N C O N T R O L L E D C O P Y ...

Page 99: ...2005 MOST FORWARD CENTER OF GRAVITY WEIGHT LBS FLAP DEFLECTIO N ANGLE OF BANK 0 30 45 60 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 3600 0 49 58 54 62 64 69 79 82 3600 20 42 53 48 57 56 63 71 75 3600 40 40 52 52 56 60 62 74 74 Figure 5 3 Stall Speeds Sheet 2 of 2 U N C O N T R O L L E D C O P Y ...

Page 100: ...ne Air Induction System NORM NOTES 4 The torque indicated below is the minimum value for which takeoff performance in this section can be obtained 5 Torque on this chart shall be achieved without exceeding 810 C TOT or 105 N1 EXAMPLE OAT 16 C Pressure Altitude 4000 Ft Minimum Engine Torque Acceptable 85 PSI Figure 5 4 Minimum Engine Torque For Takeoff U N C O N T R O L L E D C O P Y ...

Page 101: ... 1445 872 1608 964 1770 1072 1958 1205 2185 6000 731 1355 788 1458 857 1582 959 1761 1061 1939 1181 2145 1328 2393 7000 803 1486 867 1599 944 1735 1057 1933 1170 2127 1303 2352 1467 2624 8000 885 1631 955 1755 1041 1905 1168 2124 1294 2336 1442 2583 1624 2880 CONDITIONS 1 Flaps 20º 2 Speed at liftoff 51 KIAS 3 Speed at 50 Ft 60 KIAS 4 Level hard surface dry runway 5 Zero Wind 6 Inlet Normal NOTES ...

Page 102: ...9 744 1390 823 1532 915 1697 1028 1895 6000 624 1171 673 1260 732 1369 819 1525 906 1680 1008 1860 1133 2077 7000 686 1284 740 1383 806 1502 902 1674 999 1844 1112 2041 1251 2280 8000 756 1411 816 1519 889 1650 997 1841 1104 2027 1230 2244 1385 2505 CONDITIONS 7 Flaps 20º 8 Speed at liftoff 48 KIAS 9 Speed at 50 Ft 57 KIAS 10 Level hard surface dry runway 11 Zero Wind 12 Inlet Normal NOTES 1 Short...

Page 103: ... 1115 670 1229 745 1363 836 1525 6000 509 937 548 1009 597 1097 667 1223 737 1349 820 1496 921 1673 7000 559 1029 603 1108 656 1205 735 1345 813 1483 904 1644 1017 1839 8000 615 1131 664 1219 724 1325 811 1481 898 1632 1000 1809 1125 2023 CONDITIONS 13 Flaps 20º 14 Speed at liftoff 44 KIAS 15 Speed at 50 Ft 52 KIAS 16 Level hard surface dry runway 17 Zero Wind 18 Inlet Normal NOTES 1 Short field t...

Page 104: ... 87 1477 1447 1354 4 000 84 1429 1399 1162 8 000 81 1373 1228 961 12 000 77 1107 959 744 16 000 74 831 709 548 20 000 71 569 477 404 3300 0 86 1675 1644 1544 4 000 82 1628 1596 1342 8 000 79 1570 1416 1130 12 000 76 1286 1130 905 16 000 72 994 867 700 20 000 69 718 626 551 3000 0 86 1907 1876 1768 4 000 81 1860 1827 1552 8 000 78 1801 1635 1326 12 000 74 1497 1329 1087 16 000 71 1185 1050 873 20 0...

Page 105: ...96 2026 1984 1700 4 000 92 1867 1687 1460 8 000 88 1536 1423 1195 12 000 83 1221 1122 935 16 000 79 907 829 689 20 000 74 619 558 459 3300 0 95 2267 2222 1922 4 000 91 2097 1907 1665 8 000 87 1743 1627 1383 12 000 82 1409 1307 1107 16 000 78 1078 997 849 20 000 73 774 712 608 3000 0 94 2551 2503 2182 4 000 90 2368 2162 1906 8 000 84 1986 1867 1604 12 000 81 1626 1525 1310 16 000 76 1274 1193 1035 ...

Page 106: ... 0 5 7 16 2 16 000 74 708 14 4 44 7 6 7 19 6 18 000 72 603 17 4 52 0 7 8 23 5 20 000 71 476 21 1 60 4 9 0 28 2 3300 0 86 1644 0 0 0 0 0 0 0 0 2 000 85 1622 1 2 4 7 0 7 1 8 4 000 83 1596 2 5 9 3 1 4 3 5 6 000 81 1519 3 7 13 8 2 0 5 3 8 000 79 1416 5 1 18 2 2 7 7 1 10 000 78 1286 6 6 22 8 3 4 9 1 12 000 76 1130 8 3 27 7 4 1 11 3 14 000 74 989 10 2 32 8 4 9 13 8 16 000 72 867 12 3 38 4 5 7 16 5 18 00...

Page 107: ...2 9 6 4 20 1 16 000 74 547 18 0 50 9 7 6 24 6 18 000 72 491 21 9 59 4 8 9 29 5 20 000 71 404 26 3 68 5 10 2 35 1 3300 0 86 1544 0 0 0 0 0 0 0 0 2 000 85 1448 1 3 4 7 0 7 1 9 4 000 83 1342 2 8 9 5 1 4 3 9 6 000 81 1235 4 3 14 5 2 2 6 1 8 000 79 1130 6 0 19 6 2 9 8 4 10 000 78 1012 7 9 24 9 3 7 10 9 12 000 76 905 10 0 30 4 4 5 13 7 14 000 74 791 12 3 36 4 5 4 16 8 16 000 72 699 15 0 42 7 6 4 20 2 18...

Page 108: ... 38 0 5 7 14 9 16 000 74 831 13 0 44 2 6 6 17 8 18 000 72 704 15 6 51 0 7 6 21 1 20 000 71 569 18 8 58 6 8 7 25 0 3300 0 86 1675 0 0 0 0 0 0 0 0 2 000 85 1652 1 2 5 1 0 8 1 7 4 000 83 1628 2 4 10 0 1 5 3 4 6 000 81 1600 3 7 14 6 2 2 5 1 8 000 79 1570 4 9 19 1 2 8 6 9 10 000 78 1419 6 3 23 6 3 5 8 6 12 000 76 1286 7 7 28 2 4 2 10 6 14 000 74 1136 9 4 33 1 4 9 12 7 16 000 72 994 11 3 38 3 5 7 15 1 1...

Page 109: ... 148 195 70 153 206 60 137 176 60 141 181 60 144 186 50 127 157 50 130 161 50 132 166 40 114 138 40 116 142 40 118 146 30 64 119 30 95 123 30 97 126 PRESSURE ALTITUDE 2 000 STD 20 C 9 C STD 11 C STD 20 C 31 C TORQUE PSI KTAS FUEL FLOW LB HR TORQUE PSI KTAS FUEL FLOW LB HR TORQUE PSI KTAS FUEL FLOW LB HR 68 147 186 70 152 195 72 157 204 60 134 172 60 143 176 60 146 181 50 129 153 50 132 157 50 135 ...

Page 110: ...57 191 72 160 200 60 143 167 60 146 172 60 149 177 50 132 148 50 135 153 50 137 157 40 118 130 40 120 133 40 123 137 30 96 111 30 86 114 30 88 117 PRESSURE ALTITUDE 6 000 STD 20 C 17 C STD 3 C STD 20 C 23 C TORQUE PSI KTAS FUEL FLOW LB HR TORQUE PSI KTAS FUEL FLOW LB HR TORQUE PSI KTAS FUEL FLOW LB HR 71 156 186 74 161 196 68 160 191 60 145 163 60 149 168 60 152 172 50 134 144 50 137 148 50 140 15...

Page 111: ...67 205 65 160 181 60 148 159 60 151 164 60 155 168 50 136 140 50 139 144 50 142 148 40 122 122 40 124 125 40 127 128 30 87 103 30 89 106 30 91 108 PRESSURE ALTITUDE 10 000 STD 20 C 25 C STD 5 C STD 20 C 15 C TORQUE PSI KTAS FUEL FLOW LB HR TORQUE PSI KTAS FUEL FLOW LB HR TORQUE PSI KTAS FUEL FLOW LB HR 76 166 199 70 161 183 71 165 191 60 151 155 60 154 160 62 159 168 50 139 137 50 142 140 50 145 1...

Page 112: ... HR 72 165 189 66 164 179 60 153 156 60 157 160 58 158 160 50 141 134 50 145 138 50 147 141 40 126 115 40 128 118 40 130 121 30 90 96 30 92 99 30 94 101 PRESSURE ALTITUDE 14 000 STD 20 C 33 C STD 13 C STD 20 C 7 C TORQUE PSI KTAS FUEL FLOW LB HR TORQUE PSI KTAS FUEL FLOW LB HR TORQUE PSI KTAS FUEL FLOW LB HR 67 163 175 60 156 156 62 162 166 55 157 151 50 144 131 50 147 135 50 150 138 40 128 112 40...

Page 113: ... PSI KTAS FUEL FLOW LB HR 62 161 162 58 160 156 53 156 143 50 146 130 50 150 134 50 152 137 40 130 109 40 132 112 40 134 115 30 93 90 30 96 93 30 97 95 PRESSURE ALTITUDE 18 000 STD 20 C 41 C STD 21 C STD 20 C 1 C TORQUE PSI KTAS FUEL FLOW LB HR TORQUE PSI KTAS FUEL FLOW LB HR TORQUE PSI KTAS FUEL FLOW LB HR 58 159 151 55 159 148 50 149 131 50 152 134 52 157 142 40 132 106 40 134 109 40 135 112 30 ...

Page 114: ... 3 Inlet Normal PRESSURE ALTITUDE 20 000 STD 20 C 45 C STD 25 C STD 20 C 5 C TORQUE PSI KTAS FUEL FLOW LB HR TORQUE PSI KTAS FUEL FLOW LB HR TORQUE PSI KTAS FUEL FLOW LB HR 53 156 140 50 151 131 51 156 137 49 157 136 40 133 103 40 135 106 40 137 109 30 97 84 30 99 87 30 101 89 Figure 5 11 Cruise Performance Sheet 6 of 6 U N C O N T R O L L E D C O P Y ...

Page 115: ...e 76 Gallons Usable Fuel CONDITIONS NOTE 1810 RPM 100 N2 1 THIS CHART ALLOWS FOR FUEL 3600 LB AT ENGINE START USED IN START TAXI AND CLIMB STANDARD TEMPERATURE AND 45 MINUTES RESERVE FUEL ZERO WIND AT THE PARTICULAR CRUISE POWER AND ALTITUDE Figure 5 12 Range Profile 76 Gallons Fuel Sheet 1 of 2 U N C O N T R O L L E D C O P Y ...

Page 116: ...e 88 Gallons Usable Fuel CONDITIONS NOTE 1810 RPM 100 N2 1 THIS CHART ALLOWS FOR FUEL 3600 LB AT ENGINE START USED IN START TAXI AND CLIMB STANDARD TEMPERATURE AND 45 MINUTES RESERVE FUEL ZERO WIND AT THE PARTICULAR CRUISE POWER AND ALTITUDE Figure 5 12 Range Profile 88 Gallons Fuel Sheet 2 of 2 U N C O N T R O L L E D C O P Y ...

Page 117: ...ve 76 Gallons Usable Fuel CONDITIONS NOTE 1810 RPM 100 N2 1 THIS CHART ALLOWS FOR FUEL 3600 LB AT ENGINE START USED IN START TAXI AND CLIMB STANDARD TEMPERATURE AND 45 MINUTES RESERVE FUEL ZERO WIND AT THE PARTICULAR CRUISE POWER AND ALTITUDE Figure 5 13 Endurance Profile 76 Gallons Fuel Sheet1 of 2 U N C O N T R O L L E D C O P Y ...

Page 118: ...e 88 Gallons Usable Fuel CONDITIONS NOTE 1810 RPM 100 N2 1 THIS CHART ALLOWS FOR FUEL 3600 LB AT ENGINE START USED IN START TAXI AND CLIMB STANDARD TEMPERATURE AND 45 MINUTES RESERVE FUEL ZERO WIND AT THE PARTICULAR CRUISE POWER AND ALTITUDE Figure 5 13 Endurance Profile 88 Gallons Fuel Sheet 2 of 2 U N C O N T R O L L E D C O P Y ...

Page 119: ...41 676 1274 699 1307 722 1340 6000 606 1172 630 1207 654 1242 678 1277 702 1311 726 1345 750 1379 7000 630 1206 655 1243 679 1279 704 1314 729 1350 754 1385 779 1420 8000 654 1242 680 1279 706 1316 732 1353 758 1390 783 1427 809 1463 CONDITIONS 1 Flaps 40 2 Speed at 50 ft 63 KIAS 3 Maximum braking 4 Set ground idle power immediately after touchdown 5 Retract flaps for maximum brake effectiveness 6...

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Page 121: ...d October 4 2005 SECTION 6 WEIGHT BALANCE EQUIPMENT LIST TABLE OF CONTENTS PAGE Introduction 6 3 Airplane Weighing Procedures 6 3 Sample Weight Balance Forms 6 3 Weight and Balance 6 3 Equipment List 6 3 Sample Loading Problem 6 4 Loading Graph 6 6 Equipment List 6 8 U N C O N T R O L L E D C O P Y ...

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Page 123: ...e appropriate weight and balance records carried in the airplane AIRPLANE WEIGHING PROCEDURES No Change SAMPLE WEIGHT AND BALANCE FORMS FIGURES 6 1 AND 6 2 No change except Figure 6 1 Oil Quantity 9 U S Quarts Oil Weight 8 lbs gal Oil Arm Fuel Weight 6 7 lbs gal WEIGHT AND BALANCE No Change Loading Arrangements Figures 6 3 6 4 6 5 and 6 6 No Change Sample Loading Problem See Figure 6 7 Center of G...

Page 124: ...ta 63 to 74 Aft Passengers Standard Seating Sta 94 to 100 Club Seating Sta 98 to 109 Baggage IV or V Sta 109 to 145 340 23 8 340 34 0 5 Cargo A Sta 10 to 50 Cargo B sta 50 to 84 Cargo C Sta 84 to 109 Cargo D Sta 109 to 145 6 RAMP WEIGHT AND MOMENT 3604 167 7 Fuel allowance for engine start taxi and run up 4 2 8 TAKEOFF WEIGHT MOMENT 3600 166 8 9 Locate this point on the Center of Gravity Moment En...

Page 125: ...t Passengers Standard Seating Sta 94 to 100 Club Seating Sta 98 to 109 Baggage IV or V Sta 109 to 145 340 23 8 170 17 0 157 4 15 4 5 Cargo A Sta 10 to 50 Cargo B sta 50 to 84 Cargo C Sta 84 to 109 Cargo D Sta 109 to 145 9 RAMP WEIGHT AND MOMENT 3616 173 5 10 Fuel allowance for engine start taxi and run up 16 8 11 TAKEOFF WEIGHT MOMENT 3600 172 7 10 Locate this point on the Center of Gravity Moment...

Page 126: ...nes representing adjustable seats show the pilot or passenger center of gravity on adjustable seats positioned for an average occupant Refer to Loading Arrangements diagram for forward and aft limits of occupant C G range Figure 6 8A Loading Graph For Aircraft S Ns U20603522 thru U20604649 U N C O N T R O L L E D C O P Y ...

Page 127: ...senting adjustable seats show the pilot or passenger center of gravity on adjustable seats positioned for an average occupant Refer to Loading Arrangements diagram for forward and aft limits of occupant C G range Figure 6 8AB Loading Graph For Aircraft S Ns U20602589 U20604650 thru U20606847 and on U N C O N T R O L L E D C O P Y ...

Page 128: ... 6 0 A33 R Propeller Assembly 69 41 1 A37 R 1 Governor Propeller 3 35 5 A41 R Spinner 3 bladed propeller 3 5 44 5 A88 R Air Induction System 5 5 2 5 Electrical Power C01 R 1 Battery 24V 14 Amp Hr 27 5 3 0 C04 R Regulator 28V Alternator 5 3 0 Instruments D34 R Instrument Cluster Engine 1 5 17 5 D55 R Gauge Manifold Pressure Fuel Flow 1 0 16 5 D85 R Tachometer Recording 1 5 15 0 Cabin Accommodations...

Page 129: ... 8 R Induction System Engine Air 6 0 4 0 R Exhaust 12 0 22 0 A Exhaust Heat Exchanger Kit Drawing Ref 763 1004 8 4 21 4 A Engine Wash Kit Drawing Ref 763 1022 5 4 5 A Engine Inlet Anti Ice Kit Drawing Ref 763 1051 1 0 20 0 Electrical Systems R Battery 24V 25 Amp Hr Gill G 247 w 763 8500 1 Battery Base Assy 46 6 0 O Battery 24V 25 Amp Hr Concorde RG 325 w 763 1085 1 Battery Base Assy 55 6 1 R Regul...

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Page 131: ...grated Seat Belt Shoulder Harnesses w Inertia Reels 7 12 Entrance Doors and Cabin Windows 7 12 Control Locks 7 12 Engine 7 12 Engine controls 7 13 Power Control 7 13 Propeller Control 7 14 Fuel Cutoff Control 7 14 Engine Instruments 7 14 Engine Torque Indicator 7 14 Propeller RPM Indicator 7 14 TOT Indicator 7 14 N1 Percent RPM Indicator 7 15 Engine Oil Pressure Indicator 7 15 Engine Oil Temperatu...

Page 132: ...ncy 7 26 Brake System 7 26 Electrical System 7 27 Master Switch 7 27 Battery and Generator Switches 7 27 Ammeter 7 27 Overvoltage Sensor Warning Light 7 27 Circuit Breakers and Fuses 7 28 Ground Service Plug Receptacles 7 28 Lighting Systems 7 28 Cabin Heating Ventilation Defrosting System 7 28 Pitot Static System and Instruments 7 28 Airspeed Indicator 7 28 Rate of Climb Indicatorr 7 28 Altimeter...

Page 133: ... PAC SECTION 7 POHS CESSNA U TU 206G AIRPLANE SYSTEMS DESCRIPTION 7 3 F A A Approved October 4 2005 Figure 7 1 Instrument Panel Sheet 1 of 2 For Aircraft S Ns U20602589 thru U20606439 U N C O N T R O L L E D C O P Y ...

Page 134: ...eed Indicator 35 Electrical Switches 12 Altimeter 36 Inst Radio Dial Lights Ctrl 13 VOR ILS 37 Auto Feather Test Button 14 Engine Three In One Gauge 38 Battery Switch 15 Avionics Stack 39 Phone Jack 16 Fuel Totalizer 40 Gen Overvoltage Trip Reset Switch 17 Engine Three In One Gauge 41 Auxiliary Mic Jack 18 Prop Gearbox Transmission Oil Pressure Gauge 42 Generator APU Switch 19 Annunciator Lights 4...

Page 135: ...Control 13 Nav 2 38 Engine Alternate Air Light 14 Avionics Stack 39 Elevator Rudder Trim 15 TOT Indicator 40 Propeller Control 16 Torque Indicator 41 Power Control 17 Annunciator Lights Fuel Gauges 42 Avionics Power Switch 18 Np Tachometer 43 Electrical Switches 19 Annunciator Lights Dimmer 44 Circuit Breakers 20 Flight Hour Recorder 45 Inst Radio Dial Lights Ctrl 21 Suction Gauge 46 Auto Feather ...

Page 136: ...ne Inlet Anti Ice Control 14 NAV 2 43 Fuel Gauges 15 NAV 1 44 Engine Alt Air Light 16 DME Opt 45 Elevator Rudder Trim 17 Avionics Stack 46 Switch Panel 18 Np Tachometer 47 Instrument Radio Lights Ctrl 19 N1 Tachometer 48 Auto Feather Test Button 20 TOT Indicator 49 Battery Switch 21 Torque Indicator 50 Aux Mic Jack 22 Oil Pressure Low Light 51 Generator Trip Reset 23 Auto Feather Light 52 Phone Ja...

Page 137: ...C SECTION 7 POHS CESSNA U TU 206G AIRPLANE SYSTEMS DESCRIPTION 7 7 F A A Approved October 4 2005 For Aircraft S Ns U20606440 and on Figure 7 3 Instrument Panel Sheet 1 of 2 2 Instruments U N C O N T R O L L E D C O P Y ...

Page 138: ...A U TU 206G AIRPLANE SYSTEMS DESCRIPTION 7 8 F A A Approved October 4 2005 For Aircraft S Ns U20603522 thru U20606439 Figure 7 3 Instrument Panel Sheet 2 of 2 2 Instruments For Aircraft S Ns U20606440 and on U N C O N T R O L L E D C O P Y ...

Page 139: ...gauge fuel totalizer engine cluster gauge N1 oil temperature oil pressure transmission oil pressure fuel quantity indicators ammeter and space for additional instruments and avionics equipment On serial numbers U20606440 and on the suction gauge and ammeter are located on the left side of the panel A switch and control panel at the lower edge of the instrument panel contains most of the switches c...

Page 140: ...instruments switches circuit breakers and controls on this panel refer in this section to the description of the systems to which these items are related ANNUNCIATOR PANEL The annunciator panel with the exception of the alternate air light which is located by the engine alternate air lever is located below the glare shield on the right instrument panel A dimmer switch is used to reduce the intensi...

Page 141: ...icles have been detected in either the turbine engine oil system or the propeller gearbox transmission oil system 4 The amber FUEL FILTER light advises that the fuel filter bypass valve is in a bypass condition 5 The amber GEN OFF BUS advises that the generator switch is off or a generator malfunction exists 6 The amber ALT AIR light advises that the spring loaded alternate air door on the plenum ...

Page 142: ...ected to the compressor The compressor consists of six axial compressor stages and one centrifugal stage assembled as an integral unit It provides a compression ratio of 7 0 1 The compressed air is discharged through the scroll type diffuser into two external ducts which convey the air to the combustion section Air enters the single combustion liner through holes in the liner dome and skin This ai...

Page 143: ...s producer gear train The rest of the accessories are driven by the Soloy propeller reduction gearbox These include the propeller governor propeller overspeed governor and the propeller gearbox oil pump A spare accessory pad is also drive by this gear train The Turbine Pac oil supply is contained in an integral tank The system has a capacity of 9 U S quarts and is provided with a dipstick ENGINE C...

Page 144: ...indicator transmission oil pressure indicator and fuel flow temperature indicator The indicators are placarded as to their operational parameters ENGINE TORQUE INDICATOR The power train portion of the engine gearbox consists of two stages of helical gearing These gears are such that a forward axial thrust is produced on the torquemeter shaft during normal operation This axial thrust is transmitted...

Page 145: ...splays the flow of fuel to the engine in pounds per hour time remaining in hours and minutes pounds used pounds remaining and fuel temperature NEW ENGINE BREAK IN AND OPERATION There are no specific break in procedures required for the SOLOY TURBINE PAC turboprop engine The engine may be safely operated through the normal ranges authorized by the manufacturer at the time of delivery of your airpla...

Page 146: ...he total starts on the engine The three position start motor switch located on the left side of the switch and control panel is placarded START OFF and MOTOR The switch automatically returns to the center OFF position when released Electrical power will continuously be applied to the ignition exciter when the start motor switch is in the START position and the battery switch is on and will be term...

Page 147: ...em is operated by an alternate air control lever on the right side of the control pedestal The pedestal is labeled NORM ALT AIR ALT The system is operated by moving the lever to the right to clear a detent then moving the lever all the way up to the NORM position NOTE A drop in torque and a rise in TOT is normal with the actuation of the engine ice protection system CAUTION SIGNIFICANT POWER LOSS ...

Page 148: ...N The unfeathering system uses governor boosted propeller gearbox oil pressure to force the propeller out of feather An auto feathering system provides for automatic reduction in propeller RPM in the event of the loss of engine power This system is not a total feathering device It is intended to reduce propeller drag due to an engine failure The system is controlled by a pressure sensor that autom...

Page 149: ...SOLOY TURBINE PAC SECTION 7 POHS CESSNA U TU 206G AIRPLANE SYSTEMS DESCRIPTION 7 19 F A A Approved October 4 2005 Figure 7 6 Fuel System U N C O N T R O L L E D C O P Y ...

Page 150: ...SOLOY TURBINE PAC SECTION 7 POHS CESSNA U TU 206G AIRPLANE SYSTEMS DESCRIPTION 7 20 F A A Approved October 4 2005 Figure 7 6A Fuel System U N C O N T R O L L E D C O P Y ...

Page 151: ...SOLOY TURBINE PAC SECTION 7 POHS CESSNA U TU 206G AIRPLANE SYSTEMS DESCRIPTION 7 21 F A A Approved October 4 2005 Figure 7 6B Fuel System U N C O N T R O L L E D C O P Y ...

Page 152: ...p once the valve is moved from the OFF position to LEFT To shutoff the fuel the safety spring must be pressed down to allow selector movement to OFF Fuel system venting is essential to system operation Complete blockage of the venting system will result in decreasing fuel flow and eventual engine stoppage Venting is accomplished by check valve equipped interconnected flush inlet vents There are tw...

Page 153: ...8 seconds and then come on again When a FUEL LOW light is confirmed switch the fuel selector switch to the tank for which the FUEL LOW light is NOT on If both are illuminated select BOTH and land as soon as practical When the fuel selector is in either the LEFT or RIGHT position the FUEL CONFIG light will be illuminated NOTE It remains the pilot s responsibility to ensure fuel quantities FUEL REQU...

Page 154: ...f data by the pilot the following procedure should be followed LIMITATIONS All computations are based on Jet A fuel with a density of 6 71 lb gal at 80 F If JP 5 JP 4 Jet B or AVGAS JET A mixture is used the following procedures should be followed 1 The time remaining function is considered inaccurate 2 To determine the fuel used or fuel remaining multiply the reading by the following factors Fuel...

Page 155: ...on is needed since data is already stored B Upon starting the engine the computer will display fuel flow time remaining and the other two functions are available by pressing the appropriate buttons 3 Tanks Full A Press Lb Rem button and hold B Press Test Enter button to increment the fuel quantity the longer you press the faster the incrementing until the total usable lb of fuel is reached C Relea...

Page 156: ...n hours and minutes B To display Lb used or remaining press the appropriate button C Lbs used could be reset at any time by pressing Lb Used and momentarily pressing Test Enter button no longer than 4 seconds otherwise the computer will start decrementing the fuel remaining D Fuel temperature in degrees F is normally displayed To display fuel temperature in degrees C press the appropriate button 6...

Page 157: ...ration CAUTION PRIOR TO TURNING THE BATTERY SWITCH ON OR OFF STARTING THE ENGINE OR APPLYING AN EXTERNAL POWER SOURCE THE AVIONICS POWER SWITCH LABELED AVIONICS POWER SHOULD BE TURNED OFF TO PREVENT ANY HARMFUL TRANSIENT VOLTAGE FROM DAMAGING THE AVIONICS EQUIPMENT MASTER SWITCH Delete BATTERY AND GENERATOR SWITCHES Separate battery and generator switches are provided as a means of checking for a ...

Page 158: ...e pulled off to disable the applicable circuit s These additional circuit breakers are mounted on the lower left side of the instrument panel GROUND SERVICE PLUG RECEPTACLES No Change LIGHTING SYSTEMS No Change CABIN HEATING VENTILATING AND DEFROSTING SYSTEM No Change except No Heater Installed PITOT STATIC SYSTEM AND INSTRUMENTS No Change AIRSPEED INDICATOR The airspeed indicator is calibrated in...

Page 159: ...AIRPLANE SYSTEMS DESCRIPTION 7 29 F A A Approved October 4 2005 STALL WARNING SYSTEM No Change AVIONICS SUPPORT EQUIPMENT No Change AUDIO CONTROL PANEL No Change MICROPHONE HEADSET No Change STATIC DISCHARGERS No Change U N C O N T R O L L E D C O P Y ...

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Page 161: ...Alterations or Repairs 8 4 Ground Handling 8 4 Towing 8 4 Parking 8 4 Tie Down 8 4 Jacking 8 5 Leveling 8 5 Flyable Storage 8 5 Servicing 8 6 Engine Oil 8 6 Recommended Oils at Specific Ambient Temps 8 7 Oil Drain Period 8 8 Oil Level Check 8 8 Fuel 8 8 Primary Fuels 8 8 Cold Weather Fuels 8 9 Fuel Additives 8 11 Landing Gear 8 12 Oxygen 8 12 Cleaning and Care 8 12 Windshield Windows 8 12 Painted ...

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Page 163: ...n plates can be found the SOLOY TURBINE PAC identification plate which contains the model number serial number supplemental type certificate STC and the date of the aircraft conversion OWNER FOLLOW UP SYSTEM No Changes Except In addition to the Cessna system Soloy LLC offers a support system consisting of technical publications and service information PUBLICATIONS No Change Except In addition to t...

Page 164: ...PERIODS No Change PILOT CONDUCTED PREVENTIVE MAINTENANCE No Change ALTERATIONS OR REPAIRS No Change GROUND HANDLING TOWING No Change Except CAUTION CARE SHOULD BE USED WHEN TOWING THE AIRPLANE WITH A NOSE WHEEL TOW BAR SO NOT TO CONTACT THE EXHAUST STACKS STRUCTURAL DAMAGE TO THE ENGINE CAN OCCUR IF LOADS ARE APPLIED TO THE STACKS PARKING No Change TIE DOWN Proper tie down procedure is the best pr...

Page 165: ...ink and secure to a ramp tie down 6 Tie a rope no chains or cables to the propeller and secure to the airframe to prevent the propeller from windmilling 7 Install a pitot tube cover 8 If dusty conditions exist or if the last flight of the day has been completed install the engine inlet and exhaust covers The covers may be installed after the engines have cooled down JACKING No Change LEVELING No C...

Page 166: ...lve closed Also cover the diffuser vent orifice hole and engine gearbox overboard vent during storage c Accomplish fuel system preservation If the engine will be stored for over 45 days re preserve at least each 90 days if stored outdoors and each 180 days if stored indoors CAUTION RED TAG THE POWER CONTROL AFTER ANY PRESERVATION HAS BEEN MADE SERVICING NOTE Refer to the Airplane and Engine Mainte...

Page 167: ...peratures MIL PRF 23699 HTS or SAE AS5780 HPC oils are recommended for use in Model 250 engines WARNING ALTHOUGH MIL PRF 23699 SAE AS5780 DOD PRF 85734 OR MIL PRF 7808G OIL IS ACCEPTABLE DO NOT MIX THESE OILS MIXING OF THE SAME MIL GRADE OIL NOT IN THE SAME GROUP IS PER MITTED ONLY IN AN EMERGENCY USE OF MIXED OILS OILS NOT IN THE SAME GROUP IN AN ENGINE IS LIMIT ED TO FIVE HOURS TOTAL RUNNING TIM...

Page 168: ...DULE OIL LEVEL CHECK Check within 15 minutes of shutdown Normal operating range on the oil dipstick is four to six U S quarts in the tank FUEL PRIMARY FUELS MIL T 5624 JP 5 MIL T 83133 JP 8 ASTMD 1655 JET A or A1 JP 1 Fuel conforming to ASTM D 1655 Jet A Diesel 1 fuel conforming to ASTM D 1655 Jet A CAUTION TO PREVENT ENGINE FUEL SYSTEM CONTAMINATION WHICH COULD CAUSE ENGINE FLAME OUT AN EXTERNAL ...

Page 169: ...r 2 Bleed the fuel system Preheat the engine in the area of the fuel control CAUTION DO NOT USE AN OPEN FLAME HEATER TO PREHEAT THE ENGINE REFER TO THE ENGINE OPERATION AND MAINTENANCE MANUAL FOR FUEL SYSTEM BLEEDING PROCEDURES The alternate cold weather fuel mixture shall consist of one part by volume AVGAS and two parts by volume JET FUEL The AVGAS shall conform to MIL G 5572C Grade 80 87 or Gra...

Page 170: ...FUEL NOZZLE AND FUEL TANK ARE GROUNDED TO THE AIRCRAFT NOTE Anti ice additive is needed for the jet fuel AVGAS fuel mixture NOTE Prolonged and uninterrupted operation with only AVGAS mixture will induce lead buildup on turbine parts This lead buildup can cause a gradual power reduction consequently this AVGAS mixture should be used only for cold weather operation During operation with normal Jet A...

Page 171: ...e additive manufacturer s instructions CAUTION PROPER MIXING OF ANTI ICING ADDITIVE WITH FUEL IS EXTREMELY IMPORTANT BECAUSE CONCENTRA TION IN EXCESS OF THAT RECOM MENDED 0 15 BY VOLUME WILL RESULT IN DETRIMENTAL EFFECTS TO THE FUEL TANKS ASSURE THAT THE FUEL ADDITIVE IS DIRECTED INTO AND BLENDING WITH FLOWING FUEL FROM THE FUELING NOZZLE DO NOT ALLOW CONCENTRATED ADDITIVE TO CONTACT THE FUEL CELL...

Page 172: ...hange PROPELLER CARE No Change ENGINE CARE COMPRESSOR The cleaning practices that are necessary for proper maintenance of the engine compressor are as follows 1 Water Rinse To be accomplished on a daily basis when operating in a salt water or other corrosive environment 2 Cleaning To regain lost performance due to buildup of dirt cleaning is normally required after 200 300 hours of operation in sm...

Page 173: ...ber 14 2014 starter generator and the bleed air system Refer to the Airplane Maintenance and the Engine Operation and Maintenance Manuals for proper lubrication of controls and components after engine cleaning INTERIOR CARE No Change BULB REPLACEMENT DURING FLIGHT No Change U N C O N T R O L L E D C O P Y ...

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Page 175: ...ion Indicator HIS SSB HF Transceiver Optional Unslaved Horizontal Situation Indicator HIS Weather Radar Type Weather Scout II Cessna Navomatic 200A Autopilot Cessna 300 ADF Type R 546E Cessna 300 Nav Com 720 Channel Type RT385A With or Without Cessna 400 Area Navigation System Cessna 300 Transponder Type RT 359A and Optional Altitude Encoder Blind or Type EA 401A Cessna Navomatic 300A Autopilot Ty...

Page 176: ...ane Each supplement contains a brief description and when applicable supplement to Sections 2 through 8 Limitations contained in the following supplements are F A A approved Observance of these operating limitations is required by Federal Aviation Regulations TABLE OF CONTENTS SOLOY SUPPLEMENT NUMBER SUPPLEMENT NAME NO OF PAGES 1 Exhaust Heat Exchanger Kit 4 2 Engine Inlet Anti Ice Kit 4 3 Continu...

Page 177: ...ting aircraft manifold through the existing firewall heater valve When the valve is closed the heater air is ducted outboard To provide this capability the following items are installed 1 Heat exchanger in left hand exhaust duct 2 Fresh air inlet and ducting to heat exchanger ducting from heat exchanger to heater valve and ducting from valve to overboard exit SECTION 2 LIMITATIONS There are no cha...

Page 178: ...e With the heater installed increase takeoff distances by 1 and decrease rate of climb tables by 30 FPM SECTION 6 WEIGHT BALANCE EQUIPMENT LIST See Soloy Turbine Pac Section 6 Equipment List SECTION 7 AIRPLANE SYSTEMS DESCRIPTION EXHAUST SYSTEM The exhaust system consists of exhaust stacks fitted to the left and right sides of the bottom of the engine forward of the engine reduction gearbox The ex...

Page 179: ...e pilot s and co pilot s feet Rear cabin heat and air is supplied by three ducts from the manifold one extending down each side of the cabin to an outlet at the front door post area at floor level and one extending under the center of the cabin floor to an outlet in the floor behind the pilot and co pilot seats The cabin floor outlet is flush mounted with a removable airflow diverter Windshield de...

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Page 181: ...ti ice kit enables the aircraft to be operated using engine bleed air instead of the alternate air system to provide anti ice protection to the engine inlet in visible moisture at an OAT of 5ºC 41ºF to 1ºC 34ºF thereby improving engine performance in this temperature range The basic alternate air system would still have to be used when operating in falling or blowing snow regardless of ambient tem...

Page 182: ...CING INADVERTENT ICING ENCOUNTER Flight into known icing conditions is prohibited If unexpected icing conditions are encountered the Inadvertent Icing Encounter checklist in Section 3 of the basic handbook should be followed In addition the following procedure is recommended PULL ON ENGINE INLET ANTI ICE OPERATION REQUIRED IN VISIBLE MOISTURE AT AN O A T OF 5ºC 41ºF TO 1ºC 34ºF WHEN ALT AIR NOT IN...

Page 183: ...perated in the above mentioned conditions even if there is no visible sign of airframe ice and or snow accumulation De activation of the system shall not be made until the above mentioned conditions have been left and the engine alternate air must be used until all accumulated airframe ice and or snow has dissipated ENGINE INLET ANTI ICE OPERATION 1 Engine Inlet Anti Ice UNLOCK PULL ON LOCK NOTE A...

Page 184: ...ler Control IN NOTE As the propeller comes out of feather there will be an oscillation of power until the propeller RPM stabilizes SECTION 4 NORMAL PROCEDURES The only change to the airplane normal procedures when the Engine Inlet Anti Ice system is installed is to check operation on the run up during the pre flight check SYSTEM CHECK 1 Engine Inlet Anti Ice ON NOTE A drop in torque and a rise in ...

Page 185: ...ter to operate continuously providing re ignition in case of a flame out A clear plastic guard prevents the switch from being inadvertently closed An indicator light informs the pilot that the system is on Use of the Continuous Ignition System does not affect the cycle counter operation SECTION 2 LIMITATIONS There are no changes to the Limitations when the Continuous Ignition Kit is installed SECT...

Page 186: ...ION SYSTEM SHOULD NOT BE USED IN LIEU OF ENGINE ANTI ICE OR INLET ALTERNATE AIR NOTE The continuous ignition is a pilot option and should be used in cases of snow sleet or icing conditions SECTION 5 PERFORMANCE There are no changes to the Performance when the Continuous Ignition kit is installed SECTION 6 WEIGHT AND BALANCE EQUIPMENT LIST Installation of Continuous Ignition Kit has minimal effect ...

Page 187: ...ough a 5 ampere circuit breaker when the switch is closed by the pilot When the switch is closed the lamp in the switch illuminates to indicate that the Continuous Ignition is on and that the ignitor plug is active The cycle counter is electrically isolated from the Continuous Ignition System by a diode to prevent accumulation of unwanted cycle indications INSTRUMENT PANEL The Continuous Ignition ...

Page 188: ...SOLOY TURBINE PAC SOLOY SUPPLEMENT NO 3 POHS CESSNA T206H 206H COWL LANDING LIGHTS 4 of 4 F A A Approved October 4 2005 This page intentionally left blank U N C O N T R O L L E D C O P Y ...

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