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SOLOY TURBINE PAC

SECTION 7

POHS CESSNA T206H/206H

AIRPLANE & SYSTEMS

DESCRIPTION

7-15

F.A.A. Approved

May 23, 2003

2. To determine the fuel used or fuel remaining, multiply the reading

by the following factors.

Fuel Used Multiplier

Jet A, JP-5 1.02

Jet B, JP-4, or AVGAS/ .96

PROCEDURES

Normal

1. Pre-Flight Check

A. Apply D.C. power to the totalizer by turning the battery

switch to on.

NOTE

Using the test function while engine is running

causes the computer to lose 13 seconds of

fuel count.

B. Initiate the Test Function procedure by pressing the

TEST/ENTER button until “8’s” appear across the

display windows and then release.

C. If the test is successful, the word “Good” will appear in

the upper display window. If unsuccessful, the word

”BAD” will appear in the upper display window and the

unit must be considered unserviceable until corrective

action is taken.

D. Press fuel USED button to display the fuel used since

last reset.

E. Press the fuel REM button to display the actual fuel

remaining. The pilot should confirm this figure with the

actual fuel remaining onboard.

F. Check to confirm fuel temperature is displayed in the

lower right window.

2. If no extra fuel is needed for the trip:

A. No action is needed since data is already stored.

B. Upon starting the engine, the computer will display fuel

flow and time remaining. The other two functions are

UNCONTROLLED

COPY

Содержание 206H

Страница 1: ...o 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 tho...

Страница 2: ...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 I...

Страница 3: ...on status of their handbook is in question A revision bar will extend the full length of new or revised text and or illustrations added on new or presently existing pages This bar will be located adja...

Страница 4: ...3 17 0 2 11 2 3 18 0 2 12 2 3 19 0 2 13 2 3 20 0 2 14 0 3 21 0 2 15 0 3 22 0 2 16 0 4 1 2 2 17 0 4 2 2 2 18 0 4 3 0 2 19 0 4 4 2 2 20 0 4 5 0 2 21 0 4 6 0 2 22 0 4 7 0 2 23 0 4 8 2 2 24 0 4 9 2 2 25...

Страница 5: ...0 5 30 0 4 29 0 6 1 2 4 30 0 6 2 0 4 31 0 6 3 0 4 32 0 6 4 0 5 1 0 6 5 0 5 2 0 6 6 0 5 3 0 6 7 2 5 4 0 6 8 0 5 5 0 7 1 0 5 6 0 7 2 0 5 7 0 7 3 0 5 8 0 7 4 0 5 9 0 7 5 0 5 10 0 7 6 0 5 11 0 7 7 0 5 12...

Страница 6: ...ed Page Revision Page Revision 7 19 1 7 20 0 7 21 0 7 22 0 7 23 0 7 24 0 7 25 0 7 26 0 8 1 1 8 2 1 8 3 0 8 4 0 8 5 0 8 6 2 8 7 1 8 8 2 8 9 1 8 10 1 8 11 2 8 12 1 8 13 Deleted 8 14 Deleted 9 1 0 9 2 0...

Страница 7: ...Cover Removed prev revision signature and date ________________ for Manager Seattle Aircraft Certification Office ANM 100S Renton WA 98057 3356 Date Rev 1 Date i v Reformatted revision log pages no co...

Страница 8: ...M speed avoid range Updated Fuel section formatting Updated Oil Specifications Updated Table of Contents Updated to extend flaps in preflight Updated engine start procedures Updated Auto feather proce...

Страница 9: ...FT STALL SPEEDS CAS Flaps Up Power Off 58 KNOTS Flaps Down Power Off 52 KNOTS MAXIMUM WEIGHT 3 617 LBS TAKEOFF WEIGHT 3 600 LBS STANDARD EMPTY WEIGHT 2 274 LBS MAXIMUM USEFUL LOAD 1 343 LBS BAGGAGE A...

Страница 10: ...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 SUPP...

Страница 11: ...ghts 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 Terminol...

Страница 12: ...SOLOY TURBINE PAC SECTION 1 POHS CESSNA T206H 206H GENERAL 1 2 F A A Approved May 23 2003 This page left blank intentionally U N C O N T R O L L E D C O P Y...

Страница 13: ...SOLOY TURBINE PAC SECTION 1 POHS CESSNA T206H 206H GENERAL 1 3 F A A Approved May 23 2003 Figure 1 1 Three View U N C O N T R O L L E D C O P Y...

Страница 14: ...f 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...

Страница 15: ...o Section 6 of this handbook for loading arrangements with one or more seats removed for cargo accommodations STANDARD AIRPLANE WEIGHTS Standard Empty Weight 2274 lbs Maximum Useful Load 1342 lbs CABI...

Страница 16: ...ing 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...

Страница 17: ...inoperative engine by moving the propeller to a greater pitch angle ENGINE START NORMAL The sequence of events that occur between starter actuation and N1 stabilization at GROUND IDLE FLAMEOUT Uninte...

Страница 18: ...the power output of the engine at any constant RPM 1 PSI 4 12 SHP TOT Turbine outlet temperature ENGINE CONTROLS AND INSTRUMENTS ENGINE OVERSPEED GOVERNOR An engine mounted component which operates i...

Страница 19: ...CROSSWIND VELOCITY Demonstrated Crosswind Velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during cer...

Страница 20: ...und by dividing the total moment by the total weight of the airplane C G ARM Center of Gravity Arm is the arm obtained by adding the airplane s individual moments and dividing the sum by the total wei...

Страница 21: ...of the takeoff run MAXIMUM LANDING WEIGHT Maximum Landing Weight is the maximum weight approved for the landing touchdown TARE Tare is the weight of chocks blocks stands etc used when weighing an airp...

Страница 22: ...SOLOY TURBINE PAC SECTION 1 POHS CESSNA T206H 206H GENERAL 1 12 F A A Approved May 23 2003 This page left blank intentionally U N C O N T R O L L E D C O P Y...

Страница 23: ...trument Markings 2 7 Weight Limits 2 8 Center of Gravity Limits 2 9 Maneuver Limits 2 9 Flight Load Factor Limits 2 9 Kinds of Operation Limits 2 9 Fuel Limitations 2 10 Minimum Fuel 2 11 Approved Fue...

Страница 24: ...SOLOY TURBINE PAC SECTION 2 POHS CESSNA T206H 206H LIMITATIONS 2 2 F A A Approved May 23 2003 This page left blank intentionally U N C O N T R O L L E D C O P Y...

Страница 25: ...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 operati...

Страница 26: ...t 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 ext...

Страница 27: ...g 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 p...

Страница 28: ...d 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 Prop...

Страница 29: ...PERATING 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 15 59 59 105 1 105 106 TORQUE 0 78 PSI 2 78 101 4 PSI 101...

Страница 30: ...e 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 Roll...

Страница 31: ...dental to normal flying stalls except whip stalls lazy eights chandelles and turns in which the angle of bank is not more than 60 Aerobatic maneuvers including spins are not approved FLIGHT LOAD FACTO...

Страница 32: ...WER LOSS 10 PSI TORQUE 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 Valv...

Страница 33: ...ESS IS PROHIBITED ILLUMINATION OF A FUEL LOW LIGHT WILL BE HANDLED AS FOLLOWS EXCEPT DURING LANDING TAKEOFF OR UNCOORDINATED FLIGHT LEFT FUEL LOW ON Switch to RIGHT tank FUEL CONFIG light illuminated...

Страница 34: ...in accordance with the additive manufacturer s instructions CAUTION PROPER MIXING OF THE ANTI ICING ADDITIVE WITH FUEL IS EXTREMELY IMPORTANT BECAUSE CONCENTRATION IN EXCESS OF THAT RECOMMENDED 0 15...

Страница 35: ...on and Maintenance Manual for current approved oils and limitations OTHER LIMITATIONS FLIGHT IDLE LIMITS Flight operations with the power control retarded below FLIGHT IDLE 14 psi torque minimum are p...

Страница 36: ...CORDANCE WITH FAR PART 91 207 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 o...

Страница 37: ...gal For Model T206H from S N T20608362 on usable fuel is 87 gal 5 Forward of fuel tank filler cap Soloy placard FUEL JET A SEE PILOT S OPERATING HANDBOOK FOR ANTI ICE ADDITIVE REQUIREMENT AND ALTERNAT...

Страница 38: ...so mechanical detent at 20 8 Near engine inlet anti ice control Soloy placard 9 Near alternate air control Soloy placard For aircraft equipped with Engine Inlet Anti Ice Control 1 3 7 9 6 PULL ON ENGI...

Страница 39: ...o the propeller control Soloy placard 13 Next to the fuel cutoff control Soloy placard WARNING FAILURE TO PROPERLY INSTALL ALIGN AND TORQUE FUEL OIL AND AIR TUBE FITTINGS COULD RESULT IN AN ENGINE FAI...

Страница 40: ...n left hand instrument panel Cessna placard ON E A L U T T O RESET WARNING ASSURE THAT SEAT IS LOCKED IN POSITION PRIOR TO TAXI TAKEOFF AND LANDING FAILURE TO PROPERLY LATCH SEAT AND HEED ALL SAFETY I...

Страница 41: ...acard 19 Near alternate air control Soloy placard MANUVER SPEED 125 KIAS WARNING ASSURE THAT ALL CONTAMINANTS INCLUDING WATER ARE REMOVED FROM FUEL AND FUEL SYSTEM BEFORE FLIGHT FAILURE TO ASSURE CONT...

Страница 42: ...g Soloy placard 22 On compass Cessna placard EMERGENCY EXIT OPERATION 1 ROTATE FORWARD CARGO DOOR HANDLE FULLFORWARD THEN FULL AFT 2 OPEN FORWARD CARGO DOOR AS FAR POSSIBLE 3 ROTATE RED LEVER IN REAR...

Страница 43: ...l quantity gauge Soloy placard 25 On each fuel tank filler cap Soloy placard 26 On the upper right instrument panel Cessna placard MAXIMUM ALTITUDE 8 000 FEET WHEN USING COLD WEATHER FUEL AT FUELTEMPE...

Страница 44: ...VE HOUSING ASSEMBLY 3 COMPRESS STRUT COMPLETELY STOPS IN CONTACT WITH OUTER BARREL HUB 4 OIL LEVEL a FLUID USED SHOULD COMPLY WITH SPECIFICATION MIL D 5606 b FILL STRUT TO BOTTOM OF VALVE INSTALLATION...

Страница 45: ...placard 30 On seats Cessna placard 31 By oxygen fill port Cessna placard 32 By oxygen control valve Cessna placard 33 On rear cargo door Cessna placard DO NOT INSTALL SEAT FACING AFT THIS SEAT IS CERT...

Страница 46: ...HOWN 35 On control wheels Cessna placard ON PILOT CONTROL WHEEL 36 On control wheels Cessna placard ON COPILOT CONTROL WHEEL 37 On the clock control fuse Soloy placard 38 On the APU fuse Soloy placard...

Страница 47: ...SOLOY TURBINE PAC SECTION 2 POHS CESSNA T206H 206H LIMITATIONS 2 25 F A A Approved May 23 2003 40 On the oil filler cap Soloy placard U N C O N T R O L L E D C O P Y...

Страница 48: ...SOLOY TURBINE PAC SECTION 2 POHS CESSNA T206H 206H LIMITATIONS 2 26 F A A Approved May 23 2003 This page left blank intentionally U N C O N T R O L L E D C O P Y...

Страница 49: ...nding Without Engine Power 3 5 Precautionary Landing With Engine Power 3 5 Ditching 3 6 Fires 3 7 During Start on Ground 3 7 Engine Fire After Shutdown 3 7 Engine Fire In Flight 3 8 Electrical Fire In...

Страница 50: ...n Icing Conditions 3 18 Engine Alternate Air System Failure 3 18 Alternate Air Light Does Not Illuminate 3 19 Alternate Air Light Illuminates In Flight 3 19 Static Source Blocked 3 19 Spins 3 19 Rough...

Страница 51: ...d 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 sys...

Страница 52: ...ART PROCEDURE CHECKLIST 9 If airstart is not warranted refer to EMERGENCY LANDING WITHOUT ENGINE POWER CHECKLIST ENGINE RESTART PROCEDURE DURING FLIGHT 1 Fuel Cutoff Control CUTOFF OUT 2 Propeller Con...

Страница 53: ...DOWN THEREFORE EXCEPT DURING AN EMERGENCY AIR STARTS SHOULD NOT BE ATTEMPTED DURING THE TIME PERIOD BETWEEN ONE MINUTE AFTER SHUTDOWN AND TEN MINUTES AFTER SHUTDOWN FORCED LANDINGS EMERGENCY LANDING W...

Страница 54: ...wk 7700 2 Heavy Objects in baggage area SECURE OR JETTISON 3 Passenger Seats AS FAR FORWARD AS PRACTICAL 4 Passenger Seat Backs MOST UPRIGHT POSITION 5 Seats and Seat Belts SECURE 6 Wing Flaps 40 7 Po...

Страница 55: ...e a Start Switch OFF b Battery Switch OFF 7 Exit Aircraft INSPECT FIRE DAMAGE associated maintenance actions must be observed CAUTION AN INTERNAL ENGINE FIRE CAN OCCUR AFTER SHUTDOWN IF THERE IS NOT A...

Страница 56: ...CLOSED 4 Fire Extinguisher ACTIVATE if available WARNING AFTER THE FIRE IS EXTINGUISHED IF AN OXYGEN SYSTEM IS AVAILABLE AND BREATHING IS DIFFICULT OCCUPANTS SHOULD USE OXYGEN MASK UNTIL SMOKE AND DIS...

Страница 57: ...installed OFF NOTE Perform a sideslip to keep the flames away from the fuel tank and cabin and land as soon as possible ICING INADVERTENT ICING ENCOUNTER Flight into known icing conditions is prohibit...

Страница 58: ...conditions are unavoidable plan a landing at the nearest airport 6 With an ice accumulation of inch or more on the wing leading edges be prepared for a significantly higher power requirement approach...

Страница 59: ...with the actuation of the engine ice protection system 3 Power Control As required FLIGHT IDLE minimum 14 psi torque CAUTION SIGNIFICANT POWER LOSS WILL OCCUR WHILE OPERATING IN THE ALTERNATE AIR MOD...

Страница 60: ...STATIC SOURCE BLOCKAGE Erroneous Instrument Reading Suspected 1 Heat and Air Valves PULL ON 2 Vents and Windows CLOSED 3 Alternate Static Source Valve PULL ON 4 Airspeed Consult Calibration Table in S...

Страница 61: ...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 SYST...

Страница 62: ...ding should 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 ru...

Страница 63: ...May 23 2003 FEATHERED PROPELLER FLAPS UP ZERO WIND BEST GLIDE SPEED WEIGHT LBS KIAS 3600 3200 2800 82 76 70 12000 10000 8000 6000 4000 2000 0 0 2 4 6 8 10 12 14 16 18 20 GROUND DISTANCE IN NAUTICAL M...

Страница 64: ...y 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 momen...

Страница 65: ...symbolic airplane 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 headin...

Страница 66: ...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...

Страница 67: ...oon 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...

Страница 68: ...ogged Land as soon as practicable AUTO FEATHER SYSTEM FAILURE IN FLIGHT In the event of a propeller auto feather system failure caused by a faulty pressure switch or defective wiring indicated by powe...

Страница 69: ...he battery condition will be low enough to accept above normal charging during the initial part of a flight However after 2 minutes of operation the ammeter should be indicating less than 80 amps If t...

Страница 70: ...HIELD DAMAGE If a bird strike or other incident should damage the windshield in flight to the point of creating an opening a significant loss in performance may be expected This loss may be minimized...

Страница 71: ...ft Wing Leading Edge 4 7 Left Wing Trailing Edge 4 7 Before Starting Engine 4 8 Starting Engine With Battery 4 8 Starting Engine With External Power 4 9 Aborted Start Procedure 4 10 Before Taxiing 4 1...

Страница 72: ...efore Takeoff 4 20 Landing Lights 4 21 Takeoff 4 21 Wing Flap Settings 4 22 Crosswind Takeoff 4 22 Enroute Climb 4 23 Cruise 4 23 Flight in Icing Conditions 4 24 Stalls 4 24 Descent 4 24 Landings 4 25...

Страница 73: ...nd 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 Flap...

Страница 74: ...ARE EXTINGUSHED 9 Avionics Master Switch ON 10 Avionics Cooling Fan CHECK AUDIBLY FOR OPERATION 11 Avionics Master Switch OFF 12 Static Pressure Alternate Source Valve OFF 13 Annunciator Panels Test S...

Страница 75: ...enting the flaps being lowered with possible damage to the cargo door or wing flaps when the cargo door is open If operating with the cargo doors removed and the optional spoiler kit installed check t...

Страница 76: ...y CHECK VISUALLY for desired level 7 Fuel Filler Cap SECURE and VENT UNOBSTRUCTED 5 NOSE 1 Cowl CHECK for security 2 Before first flight of the day and after each refueling use sampler cup and drain s...

Страница 77: ...ore each flight and after each refueling If water is observed take further samples until clear and then gently rock wings and lower tail to the ground to move any additional contaminants to the sampli...

Страница 78: ...Master OFF 14 Generator Switch APU OFF POSITION 15 APU IF AVAILABLE 16 Battery Switch ON 17 Annunciator Panels Right Panel AUTO FEATHER OIL CHIPS ALT AIR DOOR OPEN GB OIL PRESS LOW FUEL FILTER GEN OF...

Страница 79: ...n readily be reduced to 150 C by motoring the starter 4 Start Motor Switch MOTOR and hold to 12 15 N1 based on temperatures listed below NOTE Starter Duty Cycle is located in Amplified Procedures 5 St...

Страница 80: ...ED AT TORQUE SETTING GREATER THAN 20 PSI 11 Auto Feather A Ensure the Propeller Control is at the FORWARD Increase RPM position B Position the Power Control at GROUND IDLE C Activate the propeller ove...

Страница 81: ...stabilize at 1810 NP then TAKEOFF POWER 101 4 PSI torque or 810 C TOT limits 3 Elevator Control LIFT NOSE WHEEL at 50 KIAS 4 Climb Speed 90 100 KIAS 5 Wing Flaps RETRACT after obstacles are cleared S...

Страница 82: ...810 C TOT and 1810 NP for 5 Minutes Maximum then 78 PSI Torque or 738 C TOT and 1810 propeller RPM 4 Fuel Selector Valve FULL OPEN WARNING WITH 1 8 FUEL TANK QUANTITY OR LESS OR IF THE INSTALLED FUEL...

Страница 83: ...ding and Taxi Lights ON 9 Wing Flaps Down 0 to 10 below 140 KIAS 10 to 40 below 96 KIAS LANDING NORMAL LANDING 1 Airspeed 75 85 KIAS Flaps Up Wing Flaps 65 75 KIAS Flaps Down 2 Power Control FLIGHT ID...

Страница 84: ...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 Contr...

Страница 85: ...he 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 operati...

Страница 86: ...ND IDLE Prior to starting the engine check that all electrical switches and avionics master are OFF and that all circuit breakers are IN CAUTION PRIOR TO TURNING THE BATTERY SWITCH ON OR APPLYING AN E...

Страница 87: ...by motoring the engine with the start motor switch After motoring to cool the engine proceed with the normal starting procedure CAUTION THE START MOTOR SWITCH MUST BE HELD IN THE START POSITION THROU...

Страница 88: ...onnel to record the extent of and to take the recommended corrective actions after an overtemperature occurs CAUTION IF THE PROPELLER IS NOT ROTATING BY 25 N1 SPEED ABORT THE START A SECOND OR THIRD S...

Страница 89: ...or one minute before increasing power TAXIING Taxiing over loose gravel or cinders should be done at low engine speed to avoid abrasion and stone damage to the propeller tips If desired a more rapid r...

Страница 90: ...and hold The AUTO FEATHER light will illuminate Gradually push the power control and observe an increase in torque pressure with little or no change in NP Pull power control aft then release governor...

Страница 91: ...only the taxi light be used This will extend the service life of the landing light appreciably TAKEOFF With the propeller control set fully FORWARD advance the power control to FLIGHT IDLE and allow t...

Страница 92: ...w 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...

Страница 93: ...PSI No Limit 78 101 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...

Страница 94: ...ade until the above mentioned conditions no longer exist and all accumulated airframe ice has dissipated STALLS The stall characteristics are conventional and aural warning is provided by a stall warn...

Страница 95: ...For short field landings make a power approach at 63 KIAS with full flaps After all approach obstacles are cleared progressively reduce power Maintain 63 KIAS approach speed by lowering the nose of t...

Страница 96: ...o be feathered above 700 Np RPM at shutdown to minimize the spool down time of the propeller WARNING IDLE DWELL TIME PRIOR TO SHUTDOWN IS IMPORTANT TO PREVENT HARMFUL ACCUMULATION OF CARBON IN THE ENG...

Страница 97: ...s been cold soaked at temperatures below 4 C 40 F use an auxiliary power source for faster more satisfactory starts If the aircraft has been cold soaked at a temperature below 18 C 0 F and a battery s...

Страница 98: ...to run at GROUND IDLE for two minutes before actuating the generator switch This will prevent N1 speed reduction resulting from high generator loading CAUTION AUTO ACCELERATION MAY OCCUR FROM FROZEN M...

Страница 99: ...istent with the provisions of government regulations 2 Flyover noise can be further reduced by reducing the propeller RPM to the lower end of the operating range of 1630 RPM to 1810 RPM 3 During depar...

Страница 100: ...SOLOY TURBINE PAC SECTION 4 POHS CESSNA T206H 206H NORMAL PROCEDURES 4 30 F A A Approved May 23 2003 This page left blank intentionally U N C O N T R O L L E D C O P Y...

Страница 101: ...5 6 Takeoff Distance 3300 Lbs 5 11 Figure 5 7 Takeoff Distance 3000 Lbs 5 13 Figure 5 8 Maximum Rate of Climb Maximum Continuous Power 5 15 Figure 5 9 Maximum Rate of Climb Takeoff Power 5 16 Figure 5...

Страница 102: ...Performance 4 000 and 6 000 Feet 5 21 Cruise Performance 8 000 and 10 000 Feet 5 22 Cruise Performance 12 000 and 14 000 Feet 5 23 Cruise Performance 16 000 and 18 000 Feet 5 24 Cruise Performance 20...

Страница 103: ...e 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...

Страница 104: ...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 8...

Страница 105: ...ON 5 POHS CESSNA T206H 206H PERFORMANCE 5 5 F A A Approved May 23 2003 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...

Страница 106: ...stall recovery may be as much as 240 feet 2 KIAS values are approximate 3 Standard day MOST REARWARD CENTER OF GRAVITY WEIGHT LBS FLAP DEFLECTION ANGLE OF BANK 0 30 45 60 KIAS KCAS KIAS KCAS KIAS KCAS...

Страница 107: ...03 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...

Страница 108: ...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 Min...

Страница 109: ...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...

Страница 110: ...s 3 For operation on a dry grass runway increase distance by 15 of the Ground Roll figure 4 Where distance value has been deleted climb performance after lift off is less than 150 FPM at takeoff speed...

Страница 111: ...532 915 1797 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 1...

Страница 112: ...s 3 For operation on a dry grass runway increase distance by 15 of the Ground Roll figure 4 Where distance value has been deleted climb performance after lift off is less than 150 FPM at takeoff speed...

Страница 113: ...363 836 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 1...

Страница 114: ...s 3 For operation on a dry grass runway increase distance by 15 of the Ground Roll figure 4 Where distance value has been deleted climb performance after lift off is less than 150 FPM at takeoff speed...

Страница 115: ...7 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 1...

Страница 116: ...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...

Страница 117: ...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...

Страница 118: ...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...

Страница 119: ...8 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...

Страница 120: ...48 195 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...

Страница 121: ...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...

Страница 122: ...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...

Страница 123: ...R 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 S...

Страница 124: ...SI 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 ST...

Страница 125: ...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...

Страница 126: ...10 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 F...

Страница 127: ...uel is 87 gal 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 PARTIC...

Страница 128: ...2 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 783 142...

Страница 129: ...y Zero wind NOTE 1 Short field technique as specified in Section 4 2 Decrease distances 10 for each 10 knots headwind 3 Increase distances by 10 for each 2 5 knots tailwind 4 For operation on a dry gr...

Страница 130: ...SOLOY TURBINE PAC SECTION 5 POHS CESSNA T206H 206H PERFORMANCE 5 30 F A A Approved May 23 2003 This page intentionally left blank U N C O N T R O L L E D C O P Y...

Страница 131: ...6 1 F A A Approved November 17 2015 SECTION 6 WEIGHT BALANCE EQUIPMENT LIST TABLE OF CONTENTS PAGE Introduction 6 3 Airplane Weighing Procedures 6 3 Weight and Balance 6 3 Sample Loading Problem 6 4 L...

Страница 132: ...SOLOY TURBINE PAC SECTION 6 POHS CESSNA T206H 206H WEIGHT BALANCE EQUIPMENT LIST 6 2 F A A Approved May 23 2003 This page left blank intentionally U N C O N T R O L L E D C O P Y...

Страница 133: ...only be found in the appropriate weight and balance records carried in the airplane AIRPLANE WEIGHING PROCEDURES No Change WEIGHT AND BALANCE No Change SAMPLE WEIGHT AND BALANCE FORMS FIGURES 6 1 AND...

Страница 134: ...to 79 Club Seating Sta 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 8 170 17 0 157 4 15 4 5 Cargo A Sta 10 to 50 Cargo B sta...

Страница 135: ...May 23 2003 NOTE Lines 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 for...

Страница 136: ...0 0 24 02 R Alternator 28V 60 Amp 10 3 32 3 24 03 O Alternator 28V 95 Amp Net WT Change Over 24 02 R Opt 5 4 32 3 24 04 R Battery 24V 12 75 Amp Hr 5 Hr Rate 23 2 0 5 28 Fuel 28 02 R Fuel Pump Auxiliar...

Страница 137: ...R Exhaust Stack Retaining Cable 0 2 9 0 LH Exhaust System 10 9 14 6 RH Exhaust System 6 6 10 4 79 Oil 79 01 R Oil Cooler Installation 5 5 18 0 79 02 R Oil Pressure Temperature Indicators 0 8 18 8 EQU...

Страница 138: ...04 R Governor Propeller 3 0 62 0 71 Powerplant 71 01 R Filter Oil Scavenge Facet 3 0 19 4 71 02 R Tank Engine Oil 4 5 32 0 71 03 R Cooler Engine Oil 7 0 10 0 71 04 R Exhaust LH RH Without Heater 4 8 2...

Страница 139: ...Shoulder Harness 7 6 Entrance Doors and Cabin Windows 7 6 Control Locks 7 6 Engine 7 6 Engine controls 7 8 Power Control 7 8 Propeller Control 7 8 Fuel Cutoff Control 7 8 Engine Instruments 7 8 Engin...

Страница 140: ...tch 7 23 Battery and Generator Switches 7 23 Avionics Master Switch 7 23 Ammeter 7 23 Low Voltage Annunciation 7 23 Circuit Breakers and Fuses 7 24 Ground Service Plug Receptacles 7 24 Lighting System...

Страница 141: ...recorder ELT switch and space for additional instruments and avionics equipment The fuel flow indicator suction gauge and ammeter are located on the left side of the left panel A switch and control p...

Страница 142: ...tack 51 Optional Cowl Landing Lights C B 17 Nav GPS Selector 52 Optional Prop De ice Switch 18 Optional Prop De ice 53 Spare Circuit Breaker or Switch 19 Annunciator Panel 54 Optional Floatplane Circu...

Страница 143: ...PAC SECTION 7 POHS CESSNA T206H 206H AIRPLANE SYSTEMS DESCRIPTION 7 5 F A A Approved May 23 2003 FIGURE 7 1 INSTRUMENT PANEL Sheet 2 of 2 A U T O E L T RESET SMOKING PROHIBITTED ON U N C O N T R O L...

Страница 144: ...and the engine anti ice controls are located here The fuel selector valve handle is located at the base of the pedestal GROUND CONTROL No Change WING FLAP SYSTEM No Change LANDING GEAR SYSTEM No Chan...

Страница 145: ...tor in a downward direction A two stage helical gear set in the engine power and accessory gearbox reduces rotational speed from 33 290 RPM at 100 N2 power turbine speed to 6016 RPM at the power take...

Страница 146: ...riction or counter clockwise to decrease friction PROPELLER CONTROL The vernier propeller control in the cockpit is connected to the propeller governor mounted on the Soloy propeller reduction gearbox...

Страница 147: ...the gas temperature in the gas producer turbine outlet N1 PERCENT RPM INDICATOR The N1 RPM indicator indicates the percent of the gas producer RPM based on a figure of 105 N1 at 53 519 RPM ENGINE OIL...

Страница 148: ...avenge pump and passes by an oil chip detector through a filter and back into the integral tank Engine oil also operates the propeller pitch mechanism and the engine torquemeter system The total lubri...

Страница 149: ...re particles from entering the engine inlet plenum It consists of two ram inlet doors and a cowl ventilation door that are pneumatically operated by bleed air and a spring loaded alternate air door on...

Страница 150: ...d full feathering governor regulated propeller A setting introduced into the governor with the propeller control establishes the propeller speed and thus the engine power turbine speed to be maintaine...

Страница 151: ...ght will illuminate when the system is operating To ground test the system check that the AUTO FEATHER annunciator light is ON prior to starting the engine This checks that the pressure sensor is oper...

Страница 152: ...ATING SYSTEM The fuel indicating system remains unchanged except the replacement of the fuel flow measurement system with the following information A fuel totalizer system is also installed The totali...

Страница 153: ...display windows and then release C If the test is successful the word Good will appear in the upper display window If unsuccessful the word BAD will appear in the upper display window and the unit mus...

Страница 154: ...lease the fuel REM button If the correct figure has been exceeded press the fuel USED button to decrement the added fuel D Press the TEST ENTER button when the correct figure is reached E Release the...

Страница 155: ...and fuel loading is facilitated by the use of fuel quantity indicators that have been coordinated with the unusable fuel supply It is the pilot s responsibility to ascertain that the fuel quantity ind...

Страница 156: ...SOLOY TURBINE PAC SECTION 7 POHS CESSNA T206H 206H AIRPLANE SYSTEMS DESCRIPTION 7 18 F A A Approved May 23 2003 Figure 7 2 Fuel System U N C O N T R O L L E D C O P Y...

Страница 157: ...g is installed to permit an external power source to supplement the battery system for starting and ground operation CAUTION PRIOR TO TURNING THE BATTERY SWITCH ON OR OFF STARTING THE ENGINE OR APPLYI...

Страница 158: ...ate air door open switch gearbox oil pressure low switch oil system chip relay fuel filter bypass switch and generator control unit AUTO FEATHER The amber indicator advises that the overspeed governor...

Страница 159: ...23 2003 The annunciator panel can be tested by turning the Battery Switch on and holding the annunciator panel switch in the TST position All indicator messages will illuminate when the test switch is...

Страница 160: ...SOLOY TURBINE PAC SECTION 7 POHS CESSNA T206H 206H AIRPLANE SYSTEMS DESCRIPTION 7 22 F A A Approved May 23 2003 Figure 7 4 Electrical Schematic U N C O N T R O L L E D C O P Y...

Страница 161: ...ther side controls power from the Primary Bus 2 to Avionics Bus 2 On some aircraft the avionics master switch may be of a single rocker design refer to the Pilot s Operating Handbook that came with yo...

Страница 162: ...the firewall GROUND SERVICE PLUG RECEPTACLES A ground service receptacle is located on the left hand side of the aircraft just forward on the firewall and allows the use of an external power source f...

Страница 163: ...149 knots AURAL SPEED WARNING HORN This aircraft is equipped with an Aural Speed Warning Horn that activates when the airspeed indicator is approximately 5 knots above Vmo If an aural speed warning is...

Страница 164: ...sidered reliable At 15 000 feet and above the vacuum gage may indicate below 4 5 in Hg and still be adequate for normal vacuum system operation A minimum vacuum gauge reading of 4 5 in Hg is acceptabl...

Страница 165: ...8 4 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 Te...

Страница 166: ...SOLOY TURBINE PAC SECTION 8 POHS CESSNA T206H 206H HANDLING SERVICE MAINTENANCE 8 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...

Страница 167: ...e aircraft conversion CESSNA OWNER ADVISORIES Add the Following Changes In addition to the Cessna system the Soloy Corporation offers a support system consisting of technical publications and service...

Страница 168: ...S 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 precaution against damage to the parked airplane by gust...

Страница 169: ...d temporarily or indefinitely refer to the Airplane and Engine Maintenance Manuals for proper storage procedures The Maintenance Manuals provide amplification for the following procedures a Compressor...

Страница 170: ...le I are compliant with the engine manufacturer s requirements These oil specifications are approved for use in the Soloy Turbine Pac 780 1000 1 engine Refer to the Soloy Turbine Pac 780 1000 1 Mainte...

Страница 171: ...MIXING RESTRICTIONS CAN RESULT IN ENGINE FAILURE TO DECREASE THE LIKELYHOOD OF CARBON OR COKE DEPOSITS BEING DISLODGED DURING THE CHANGE OVER TO 3RD GENERATION OILS THESE CHANGE OVERS SHOULD ONLY BE M...

Страница 172: ...HEDULE OIL LEVEL CHECK Check oil level 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...

Страница 173: ...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 OR AIRPLANE FINISH S...

Страница 174: ...with 2 0 ml U S Gal max lead content DO NOT use Grade 100 130 with 4 6 ml U S Gal lead content Make the fuel mix in the aircraft tank The AVGAS can be added before or after the JET FUEL The only restr...

Страница 175: ...rmal Jet A type turbine fuel the lead buildup will slowly dissipate When the AVGAS jet fuel mixture is used in the engine the lead from the gasoline accumulates on the turbine and exhaust collector ou...

Страница 176: ...t Cleaning is normally required after 200 300 hours of operation in smoggy areas Refer to the Engine Operations and Maintenance Manual for the detailed procedures The engine compartment should be clea...

Страница 177: ...endix King KX 155A VHF No Change NAV COMM with KI 208 or KI 209A Indicator Head 2 Bendix King KT 76C Transponder No Change with Blind Encoder 3 Bendix King KMA 26 Audio No Change Selector Panel 4 Poin...

Страница 178: ...ved 18 Century Horizontal Situation No Change Indicator HIS 19 Bendix King KLN 94 Global No Change Positioning System 20 Bendix King KMA 28 Audio No Change Selector Panel 21 Bendix King KMD 28 550 No...

Страница 179: ...aircraft This section consists of a series of Soloy Turbine Pac supplements each covering a single optional system that may be installed in the airplane Each supplement contains a brief description a...

Страница 180: ...SOLOY TURBINE PAC SECTION 9 POHS CESSNA T206H 206H SUPPLEMENTS 9 4 F A A Approved May 23 2003 This page left blank intentionally U N C O N T R O L L E D C O P Y...

Страница 181: ...o 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...

Страница 182: ...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 PERF...

Страница 183: ...gh 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 pl...

Страница 184: ...SOLOY TURBINE PAC SOLOY SUPPLEMENT NO 1 POHS CESSNA T206H 206H CONTINUOUS IGNITION 4 of 4 F A A Approved May 23 2003 This page intentionally left blank U N C O N T R O L L E D C O P Y...

Страница 185: ...mpressor scroll is routed through a manually operated shut off valve to an infuser that mixes the bleed air with fresh air and exhaust heater air To provide this capability the following items are ins...

Страница 186: ...il vapor odor turn off the bleed air heater valve and land as soon as practical SECTION 4 NORMAL PROCEDURES BEFORE STARTING Turn the bleed air heater off STARTING The bleed air heater may be turned on...

Страница 187: ...efficiency from the compressor SECTION 6 WEIGHT BALANCE EQUIPMENT LIST See Soloy Turbine Pac Section 6 Equipment List SECTION 7 AIRPLANE SYSTEMS DESCRIPTION CABIN HEATING VENTILATING DEFROSTING SYSTEM...

Страница 188: ...ENT NO 2 POHS CESSNA T206H 206H BLEED AIR HEATER 4 of 4 F A A Approved May 23 2003 SECTION 9 SUPPLEMENTS There is no change to the airplane Supplements Section when the bleed air heater is installed U...

Страница 189: ...mounted in the lower engine cowling The additional lights will provide the pilot with increased illumination and visibility To provide this capability the following items are installed 1 Two landing l...

Страница 190: ...led SECTION 6 WEIGHT BALANCE EQUIPMENT LIST See Soloy Corporation Turbine Pac Section 6 Equipment List SECTION 7 AIRPLANE SYSTEMS DESCRIPTION The Cowl Landing Light kit consists of landing light bulbs...

Страница 191: ...SECTION 8 HANDLING SERVICE MAINTENANCE There is no change to the airplane handling service and maintenance procedures when the cowl landing light kit is installed SECTION 9 SUPPLEMENTS There is no cha...

Страница 192: ...SOLOY TURBINE PAC SOLOY SUPPLEMENT NO 3 POHS CESSNA T206H 206H COWL LANDING LIGHTS 4 of 4 F A A Approved May 23 2003 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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