Cessna skylance tc T182T Information Manual Download

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SECTION 7

CESSNA

AIRPLANE AND SYSTEM DESCRIPTION

MODEL T182T NAV III

GFC 700 AFCS

U.S.

FLIGHT CONTROLS AND TRIM SYSTEM

Figure 7-1 (Sheet 1 of 2)

T182TPHBUS-00

7-8

Summary of Contents for skylance tc T182T

Page 1: ...BE USED FOR GENERAL PURPOSES ONLY IT WILL NOT BE KEPT CURRENT AND THEREFORE CANNOT BE USED AS A SUBSTITUTE FOR THE OFFICIAL PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL INTENDED...

Page 2: ...000 Feet Range 753 NM 87 Gallons Usable Fuel Time 4 9 HOURS 75 Power at 10 000 Feet Range 721 NM 87 Gallons Usable Fuel Time 5 1 HOURS Max Range at 20 000 Feet Range 940 NM 87 Gallons Usable Fuel Time...

Page 3: ...3 Bladed Constant Speed Diameter 79 INCHES NOTE Speed performance and range are shown for an airplane equipped with the standard wheel and brake fairings These fairings increase the speeds approximate...

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Page 5: ...IONICS OPTION GFC 700 AFCS Serials T18208665 and T18208669 and On THIS MANUAL INCORPORATES INFORMATION ISSUED IN THE PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL AT REVISION 1 DA...

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Page 7: ...U S TABLE OF CONTENTS SECTION GENERAL 1 LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT AND BALANCE EQUIPMENT LIST 6 AIRPLANE AND SYSTEMS DESCRIPTION 7 HANDLING SERVICE...

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Page 9: ...Dimensions 1 8 Baggage Space And Entry Dimensions 1 8 Specific Loadings 1 8 Symbols Abbreviations And Terminology 1 9 General Airspeed Terminology And Symbols 1 9 Meteorological Terminology 1 10 Engin...

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Page 11: ...CESSNA SECTION 1 MODEL T182T NAV III GENERAL GFC 700 AFCS U S THREE VIEW NORMAL GROUND ATTITUDE Figure 1 1 Sheet 1 of 2 1 3 T182TPHBUS 00...

Page 12: ...e lights installed Wheel base length is 66 5 inches Propeller ground clearance is 10 875 inches Wing area is 174 0 square feet Minimum turning radius pivot point to outboard wing tip is 27 0 feet Norm...

Page 13: ...terminology commonly used DESCRIPTIVE DATA ENGINE Number of Engines 1 Engine Manufacturer Textron Lycoming Engine Model Number TIO 540 AK1A Engine Type Turbocharged direct drive air cooled horizontall...

Page 14: ...fuel supply Additive concentrations shall not exceed 1 for isopropyl alcohol or 0 10 to 0 15 for DiEGME Refer to Section 8 for additional information FUEL CAPACITY Total Capacity 92 0 U S GALLONS Tot...

Page 15: ...used Recommended viscosity for temperature range NOTE When operating temperatures overlap use the lighter grade of oil OIL CAPACITY Sump 8 U S QUARTS Total 9 U S QUARTS Continued Next Page Temperatur...

Page 16: ...low NOTE The maximum allowable combined weight capacity for baggage in areas A B and C is 200 pounds The maximum allowable weight capacity for baggage in areas B and C is 80 pounds STANDARD AIRPLANE W...

Page 17: ...essing the airframe VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position VNO Maximum Structural Cruising Speed is the speed that should no...

Page 18: ...sure Altitude Pressure Altitude is the altitude read from an altimeter when the altimeter s barometric scale has been set to 29 92 inches of mercury 1013 mb ENGINE POWER TERMINOLOGY BHP Brake Horsepow...

Page 19: ...r mixture supplied to the engine As air density increases the amount of fuel required by the engine increases for a given throttle setting Adjusting the fuel air mixture to provide a greater portion o...

Page 20: ...to be limiting Usable Fuel Usable Fuel is the fuel available for flight planning Unusable Fuel Unusable Fuel is the quantity of fuel that can not be safely used in flight GPH Gallons Per Hour is the a...

Page 21: ...onstant 1000 is used in this POH to simplify balance calculations by reducing the number of digits Center of Gravity C G Center of Gravity is the point at which an airplane or equipment would balance...

Page 22: ...oments throughout the flight range as that of the actual wing Maximum Ramp Weight Maximum Ramp Weight is the maximum weight approved for ground maneuver and includes the weight of fuel used for start...

Page 23: ...rators convert U S measurement supplied with the Pilot s Operating Handbook into metric and imperial measurements The standard followed for measurement units shown is the National Institute of Standar...

Page 24: ...SECTION 1 CESSNA GENERAL MODEL T182T NAV III GFC 700 AFCS U S WEIGHT CONVERSIONS Figure 1 2 Sheet 1 of 2 T182TPHBUS 01 1 16...

Page 25: ...CESSNA SECTION 1 MODEL T182T NAV III GENERAL GFC 700 AFCS U S WEIGHT CONVERSIONS Figure 1 2 Sheet 2 1 17 T182TPHBUS 01...

Page 26: ...SECTION 1 CESSNA GENERAL MODEL T182T NAV III GFC 700 AFCS U S LENGTH CONVERSIONS Figure 1 3 Sheet 1 of 4 T182TPHBUS 01 1 18...

Page 27: ...CESSNA SECTION 1 MODEL T182T NAV III GENERAL GFC 700 AFCS U S LENGTH CONVERSIONS Figure 1 3 Sheet 2 1 19 T182TPHBUS 01...

Page 28: ...SECTION 1 CESSNA GENERAL MODEL T182T NAV III GFC 700 AFCS U S LENGTH CONVERSIONS Figure 1 3 Sheet 3 T182TPHBUS 01 1 20...

Page 29: ...CESSNA SECTION 1 MODEL T182T NAV III GENERAL GFC 700 AFCS U S LENGTH CONVERSIONS Figure 1 3 Sheet 4 1 21 T182TPHBUS 01...

Page 30: ...SECTION 1 CESSNA GENERAL MODEL T182T NAV III GFC 700 AFCS U S DISTANCE CONVERSIONS Figure 1 4 T182TPHBUS 01 1 22...

Page 31: ...CESSNA SECTION 1 MODEL T182T NAV III GENERAL GFC 700 AFCS U S VOLUME CONVERSIONS Figure 1 5 Sheet 1 of 3 1 23 T182TPHBUS 01...

Page 32: ...SECTION 1 CESSNA GENERAL MODEL T182T NAV III GFC 700 AFCS U S VOLUME CONVERSIONS Figure 1 5 Sheet 2 1 24 T182TPHBUS 01...

Page 33: ...CESSNA SECTION 1 MODEL T182T NAV III GENERAL GFC 700 AFCS U S VOLUME CONVERSIONS Figure 1 5 Sheet 3 1 25 T182TPHBUS 01...

Page 34: ...SECTION 1 CESSNA GENERAL MODEL T182T NAV III GFC 700 AFCS U S TEMPERATURE CONVERSIONS Figure 1 6 1 26 T182TPHBUS 01...

Page 35: ...CESSNA SECTION 1 MODEL T182T NAV III GENERAL GFC 700 AFCS U S PRESSURE CONVERSION HECTOPASCALS TO INCHES OF MERCURY Figure 1 7 1 27 T182TPHBUS 01...

Page 36: ...SECTION 1 CESSNA GENERAL MODEL T182T NAV III GFC 700 AFCS U S VOLUME TO WEIGHT CONVERSION Figure 1 8 T182TPHBUS 01 1 28...

Page 37: ...CESSNA SECTION 1 MODEL T182T NAV III GENERAL GFC 700 AFCS U S QUICK CONVERSIONS Figure 1 9 T182TPHBUS 01 1 29 1 30...

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Page 39: ...y Limits 2 8 Maneuver Limits 2 9 Flight Load Factor Limits 2 9 Kinds Of Operations Limits 2 9 Kinds Of Operations Equipment List 2 10 Fuel Limitations 2 15 Maximum Operating Altitude Limit 2 15 Flap L...

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Page 41: ...fer to Supplements Section 9 of this Pilot s Operating Handbook for amended operating limitations operating procedures performance data and other necessary information for airplanes equipped with spec...

Page 42: ...on VNO Maximum Structural Cruising Speed 137 140 Do not exceed this speed except in smooth air and then only with caution VA Maneuvering Speed 3100 Pounds 2600 Pounds 2100 Pounds 110 101 92 110 101 91...

Page 43: ...e Arc 41 100 Full Flap Operating Range Lower limit is maximum weight VSO in landing configuration Upper limit is maximum speed permissible with flaps extended Green Arc 51 140 Normal Operating Range L...

Page 44: ...mum 115 PSI CAUTION ENGINE OPERATION WITH INDICATED OIL PRESSURE BELOW THE GREEN BAND RANGE WHILE IN CRUISE OR CLIMB CONFIGURATION IS CONSIDERED ABNORMAL AND SHOULD BE INSPECTED BY QUALIFIED MAINTENAN...

Page 45: ...C NORMAL OPERATING RANGE RED ARC UPR RED LINE MAX Tachometer 2000 to 2400 RPM 2400 to 2700 RPM Manifold Pressure SL 15 000 Ft 15 000 20 000 Ft 15 to 28 in hg 15 to 27 in hg 32 to 35 in hg Cylinder Hea...

Page 46: ...OUNDS Refer to note below NOTE The maximum allowable combined weight capacity for baggage in areas A B and C is 200 pounds The maximum combined allowable weight capacity for baggage in areas B and C i...

Page 47: ...S Flight Load Factors Maximum Takeoff Weight 3100 POUNDS Flaps UP 3 8g 1 52g Flaps FULL 2 0g The design load factors are 150 of the above and in all cases the structure meets or exceeds design loads K...

Page 48: ...ations Continued Next Page System Instrument Equipment and or Function KIND OF OPERATION COMMENTS V F R D A Y V F R N I G H T I F R D A Y I F R N I G H T PLACARDS AND MARKINGS T182T Nav III GFC 700 AF...

Page 49: ...s FLIGHT CONTROLS 1 Flap Position Indicator 1 1 1 1 2 Flap Motor 1 1 1 1 3 Elevator Trim System 1 1 1 1 4 Elevator Trim Indicator 1 1 1 1 5 Rudder Trim System 1 1 1 1 6 Rudder Trim Indicator 1 1 1 1 F...

Page 50: ...ATION COMMENTS V F R D A Y V F R N I G H T I F R D A Y I F R N I G H T LIGHTING 1 PFD Bezel Lighting 0 0 0 1 2 PFD Backlighting 1 1 1 Refer to Note 2 3 MFD Bezel Lighting 0 0 0 1 4 MFD Backlighting 1...

Page 51: ...meter 1 1 1 1 4 Standby Altimeter 0 0 1 1 5 G1000 Vertical Speed Indicator 0 0 0 0 6 G1000 Attitude Indicator 0 0 1 1 7 Standby Attitude Indicator 0 0 1 1 8 G1000 Directional Indicator HSI 0 0 1 1 9 G...

Page 52: ...R N I G H T VACUUM 1 Engine Driven Vacuum Pump 0 0 1 1 2 Vacuum Indicator 0 0 1 1 ENGINE FUEL AND CONTROL 1 Manifold Pressure Indicator 1 1 1 1 2 Fuel Flow Indicator 1 1 1 1 ENGINE INDICATING 1 Tachom...

Page 53: ...finition Takeoff and land with the fuel selector valve handle in the BOTH position Maximum slip or skid duration with one tank dry 30 seconds Operation on either LEFT or RIGHT tank limited to level fl...

Page 54: ...tem and the connected portable electronic device s will not cause interference with the navigation or communication system of the airplane 12V POWER SYSTEM The 12 Volt Power System POWER OUTLET 12V 10...

Page 55: ...gation is to be conducted using only current charts data and authorized navigation facilities Use of the TRAFFIC MAP to maneuver the airplane to avoid traffic is prohibited The Traffic Information Sys...

Page 56: ...irport is required it must have an approved instrument approach procedure other than GPS or RNAV that is anticipated to be operational and available at the estimated time of arrival All equipment requ...

Page 57: ...must be disengaged below 200 feet AGL during approach operations and below 800 feet AGL during all other operations 7 ILS approaches using the autopilot flight director are limited to Category I appr...

Page 58: ...Terrain Awareness and Warning System TAWS B to navigate to avoid terrain or obstacles is prohibited TAWS B is only approved as an aid to help the pilot to see and avoid terrain or obstacles TAWS B mu...

Page 59: ...PROVED PLACARDS The following information must be displayed in the form of composite or individual placards 1 In full view of the pilot The DAY NIGHT VFR IFR entry shown on the example below will vary...

Page 60: ...ION 2 CESSNA OPERATING LIMITATIONS MODEL T182T NAV III GFC 700 AFCS U S FAA APPROVED PLACARDS Continued 3 On the fuel selector valve 4 Near both fuel tank filler cap Continued Next Page T182TPHBUS 00...

Page 61: ...CESSNA SECTION 2 MODEL T182T NAV III OPERATING LIMITATIONS GFC 700 AFCS U S FAA APPROVED PLACARDS Continued 5 On flap control indicator 6 In baggage compartment Continued Next Page T182TPHBUS 00 2 23...

Page 62: ...AA APPROVED PLACARDS Continued 7 A calibration card must be provided to indicate the accuracy of the magnetic compass in 30 increments 8 Molded on the oil filler cap dipstick 9 Silk screened on the in...

Page 63: ...C 700 AFCS U S FAA APPROVED PLACARDS Continued 10 Silk screened on the upper right instrument panel 11 On auxiliary power plug door and second placard on battery box 12 On the upper right side of the...

Page 64: ...SECTION 2 CESSNA OPERATING LIMITATIONS MODEL T182T NAV III GFC 700 AFCS U S FAA APPROVED PLACARDS Continued 13 On the center overhead flood light control switch T182TPHBUS 01 2 26...

Page 65: ...During Flight Restart Procedures 3 7 FORCED LANDINGS 3 8 Emergency Landing Without Engine Power 3 8 Precautionary Landing With Engine Power 3 8 Ditching 3 9 FIRES 3 10 During Start On Ground 3 10 Engi...

Page 66: ...M 3 19 AIR DATA SYSTEM FAILURE 3 21 Red X PFD Airspeed Indicator 3 21 Red X PFD Altitude Indicator 3 21 ATTITUDE AND HEADING REFERENCE SYSTEM AHRS FAILURE 3 21 Red X PFD Attitude Indicator 3 21 Red X...

Page 67: ...ecovery From Spiral Dive In The Clouds AHRS FAILED 3 31 Inadvertent Flight Into Icing Conditions 3 31 Static Source Blocked 3 32 Spins 3 32 Rough Engine Operation Or Loss Of Power 3 33 Spark Plug Foul...

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Page 69: ...this section should be considered and applied as necessary to correct the problem In any emergency situation the most important task is continued control of the airplane and maneuver to execute a succ...

Page 70: ...t 2 Brakes APPLY 3 Wing Flaps RETRACT 4 Mixture Control IDLE CUTOFF pull full out 5 MAGNETOS Switch OFF 6 STBY BATT Switch OFF 7 MASTER Switch ALT and BAT OFF ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF...

Page 71: ...TART if propeller is stopped NOTE If the propeller is windmilling engine will restart automatically within a few seconds If propeller has stopped possible at low speeds turn MAGNETOS switch to START a...

Page 72: ...BAT OFF when landing is assured 10 Doors UNLATCH PRIOR TO TOUCHDOWN 11 Touchdown SLIGHTLY TAIL LOW 12 Brakes APPLY HEAVILY PRECAUTIONARY LANDING WITH ENGINE POWER 1 Pilot and Passenger Seat Backs MOS...

Page 73: ...ESTABLISH 300 FT MIN DESCENT AT 65 KIAS NOTE If no power is available approach at 70 KIAS with Flaps UP or at 65 KIAS with Flaps 10 7 Approach High Winds Heavy Seas INTO THE WIND Light Winds Heavy Swe...

Page 74: ...l full out 4 MAGNETOS Switch START continue cranking 5 FUEL SELECTOR Valve PUSH DOWN and ROTATE to OFF 6 FUEL PUMP Switch OFF 7 MAGNETOS Switch OFF 8 STBY BATT Switch OFF 9 MASTER Switch ALT and BAT O...

Page 75: ...CUTE refer to EMERGENCY LANDING WITHOUT ENGINE POWER ELECTRICAL FIRE IN FLIGHT 1 STBY BATT Switch OFF 2 MASTER Switch ALT and BAT OFF 3 Cabin Vents CLOSED to avoid drafts 4 CABIN HT and CABIN AIR Cont...

Page 76: ...2 ON CABIN FIRE 1 STBY BATT Switch OFF 2 MASTER Switch ALT and BAT OFF 3 Cabin Vents CLOSED to avoid drafts 4 CABIN HT and CABIN AIR Control Knobs OFF push full in to avoid drafts 5 Fire Extinguisher...

Page 77: ...FIRE 1 LAND and TAXI Light Switches OFF 2 NAV Light Switch OFF 3 STROBE Light Switch OFF 4 PITOT HEAT Switch OFF NOTE Perform a sideslip to keep the flames away from the fuel tank and cabin Land as so...

Page 78: ...es on again place the PROP HEAT Switch to OFF and continue using the RPM cycling technique to minimize ice build up on the propeller blades Have propeller heat system inspected by qualified personnel...

Page 79: ...d approaches should be avoided whenever possible because of severely reduced climb capability 16 PROP HEAT Switch OFF when propeller heat is no longer required CAUTION DO NOT OPERATE THE PROP HEAT SYS...

Page 80: ...bilized ABNORMAL LANDINGS LANDING WITH A FLAT MAIN TIRE 1 Approach NORMAL 2 Wing Flaps FULL 3 Touchdown GOOD MAIN TIRE FIRST hold airplane off flat tire as long as possible with aileron control 4 Dire...

Page 81: ...Switch OFF g NAV Light Switch OFF h STROBE Light Switch OFF i CABIN PWR 12V Switch OFF NOTE The Main Battery supplies electrical power to the Main and Essential Buses until M BUS VOLTS decreases below...

Page 82: ...1 SELECT COM2 MIC and NAV2 will be inoperative once AVIONICS BUS 2 is selected to OFF NOTE When AVIONICS BUS 2 is set to OFF the following items will not operate l AVIONICS Switch BUS 2 OFF KEEP ON if...

Page 83: ...O OFF AT HIGHER RPM 1 MASTER Switch ALT Only OFF 2 ALT FIELD Circuit Breaker CHECK IN 3 MASTER Switch ALT and BAT ON 4 LOW VOLTS Annunciator CHECK OFF 5 M BUS VOLTS CHECK 27 5 V minimum 6 M BATT AMPS...

Page 84: ...dio panel and tune to the active frequency before setting AVIONICS BUS 2 to OFF If COM2 MIC and NAV2 are selected when AVIONICS BUS 2 is set to OFF the COM and NAV radios cannot be tuned j COM1 and NA...

Page 85: ...breaker opens again do not reset 2 Standby Altimeter CHECK current barometric pressure SET USE FOR ALTITUDE INFORMATION ATTITUDE AND HEADING REFERENCE SYSTEM AHRS FAILURE RED X PFD ATTITUDE INDICATOR...

Page 86: ...airplane 2 A P TRIM DISC Button PRESS and HOLD throughout recovery 3 Elevator and Rudder Trim Controls ADJUST MANUALLY as necessary 4 AUTO PILOT Circuit Breaker OPEN pull out 5 A P TRIM DISC Button RE...

Page 87: ...ncy power IF PFD1 COOLING OR MFD1 COOLING ANNUNCIATOR DOES NOT GO OFF WITHIN 3 MINUTES OR IF BOTH PFD1 COOLING AND MFD1 COOLING ANNUNCIATORS COME ON 3 STBY BATT Switch OFF land as soon as practical VA...

Page 88: ...E CO LEVEL ADVISORY CO LVL HIGH ANNUNCIATOR COMES ON 1 CABIN HT Control Knob OFF push full in 2 CABIN AIR Control Knob ON pull full out 3 Cabin Vents OPEN 4 Cabin Windows OPEN 175 KIAS maximum windows...

Page 89: ...checklist will provide added safety after a failure of this type If an engine failure occurs immediately after takeoff in most cases the landing should be planned straight ahead with only small chang...

Page 90: ...SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL T182T NAV III GFC 700 AFCS U S MAXIMUM GLIDE Figure 3 1 T182TPHBUS 00 3 26...

Page 91: ...e area and collect folded coats for protection of occupants face at touchdown Transmit Mayday messages on 121 5 MHz giving location intentions and squawk 7700 Avoid a landing flare because of the diff...

Page 92: ...ne flooding and subsequent collection of fuel on the parking ramp as the excess fuel drains overboard from the intake manifolds This is sometimes experienced in difficult starts in cold weather where...

Page 93: ...ient at instrument flying and is flying the airplane without the autopilot engaged EXECUTING A 180 TURN IN CLOUDS AHRS FAILED Upon inadvertently entering the clouds an immediate turn to reverse course...

Page 94: ...d make minor corrections to hold an approximate course The autopilot will not operate if the AHRS unit fails The pilot must manually fly the airplane without AHRS input Before descending into the clou...

Page 95: ...ng 8 Resume EMERGENCY DESCENT THROUGH THE CLOUDS procedure 9 Upon breaking out of clouds resume normal cruising flight INADVERTENT FLIGHT INTO ICING CONDITIONS Flight into icing conditions is prohibit...

Page 96: ...d an inadvertent spin occur the following recovery procedure should be used 1 RETARD THROTTLE TO IDLE POSITION 2 PLACE AILERONS IN NEUTRAL POSITION 3 APPLY AND HOLD FULL RUDDER OPPOSITE TO THE DIRECTI...

Page 97: ...ess extreme roughness makes the use of a single MAGNETO position necessary MAGNETO MALFUNCTION Sudden engine roughness or misfiring is usually a sign of a magneto problem Changing the MAGNETOS switch...

Page 98: ...smooth engine operation If vapor symptoms continue select the opposite fuel tank When fuel flow stabilizes set the FUEL PUMP switch to the OFF position and adjust the mixture as desired LOW OIL PRESS...

Page 99: ...some degree of power loss An overboost can be determined on the manifold pressure indicator and can be controlled by a throttle reduction If the turbocharger failure results in power loss it may be f...

Page 100: ...situation EXCESSIVE RATE OF CHARGE After engine starting and heavy electrical usage at low engine speeds such as extended taxiing the battery condition will be low enough to accept above normal chargi...

Page 101: ...system To energize the alternator system 1 MASTER Switch ALT Only OFF 2 ALT FIELD Circuit Breaker CHECK IN 3 MASTER Switch ALT Only ON If the problem was a minor ACU disturbance in the electrical sys...

Page 102: ...ower for systems on the essential bus and cannot provide power for transponder XPDR operation Main battery life should be extended when practical for possible later operation of the wing flaps and use...

Page 103: ...oms mentioned above or the CO LVL HIGH warning annunciation comes on when using the cabin heater immediately turn off the cabin heater and preform the emergency items for HIGH CARBON MONOXIDE CO LEVEL...

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Page 105: ...Edge 4 9 Left Wing 4 10 Left Wing Trailing Edge 4 10 Before Starting Engine 4 11 Starting Engine With Battery 4 12 Starting Engine With External Power 4 13 Before Takeoff 4 15 Takeoff 4 18 Normal Tak...

Page 106: ...ck 4 30 Elevator Trim 4 31 Landing Lights 4 31 Takeoff 4 31 Power Check 4 31 Wing Flap Settings 4 32 Crosswind Takeoff 4 32 Enroute Climb 4 33 Cruise 4 34 Leaning Using Turbine Inlet Temperature T I T...

Page 107: ...limb 70 80 KIAS Short Field Takeoff Flaps 20 Speed at 50 Feet 60 KIAS ENROUTE CLIMB FLAPS UP Normal Sea Level 90 100 KIAS Best Rate of Climb Sea Level 84 KIAS Best Rate of Climb 20 000 Feet 80 KIAS Be...

Page 108: ...steps and assist handles will simplify access to the upper wing surfaces for visual checks and refueling operations In cold weather remove even small accumulations of frost ice or snow from wing tail...

Page 109: ...E MAGNETOS SWITCH WERE ON DO NOT STAND NOR ALLOW ANYONE ELSE TO STAND WITHIN THE ARC OF THE PROPELLER SINCE A LOOSE OR BROKEN WIRE OR A COMPONENT MALFUNCTION COULD CAUSE THE ENGINE TO START 7 MAGNETOS...

Page 110: ...erify annunciator is shown 25 MASTER Switch ALT and BAT OFF 26 Elevator and Rudder Trim Controls TAKEOFF position 27 FUEL SELECTOR Valve BOTH 28 ALT STATIC AIR Valve OFF push full in 29 Oxygen Supply...

Page 111: ...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 contamination has been removed If contaminants are s...

Page 112: ...l contaminants to the sampling points Take repeated samples from all fuel drain points including the fuel return line and fuel selector until all contamination has been removed If contaminants are sti...

Page 113: ...rs of operation or increases remove propeller and have repaired 5 Air Filter CHECK for restrictions by dust or other foreign matter 6 Nosewheel Strut and Tire CHECK proper inflation of strut and gener...

Page 114: ...Take repeated samples from all fuel drain points until all contamination has been removed If contaminants are still present refer to WARNING below and do not fly airplane NOTE Collect all sampled fue...

Page 115: ...Seats and Seat Belts ADJUST and LOCK verify inertia reel locking 4 Brakes TEST and SET 5 Circuit Breakers CHECK IN 6 Electrical Equipment OFF 7 AVIONICS Switch BUS 1 and BUS 2 OFF CAUTION THE AVIONICS...

Page 116: ...a CLEAR verify that all people and equipment are at a safe distance from the propeller 11 MASTER Switch ALT and BAT ON 12 BEACON Light Switch ON NOTE If engine is warm omit priming procedure steps 13...

Page 117: ...does not go off b ARM verify that PFD comes on 5 Engine Indication System CHECK PARAMETERS verify no red X s through ENGINE page indicators 6 BUS E Volts CHECK verify 24 VOLTS minimum shown 7 M BUS V...

Page 118: ...the FULL RICH position and retard the throttle control promptly 22 Oil Pressure CHECK verify oil pressure increases into the GREEN BAND range in 30 to 60 seconds 23 Power REDUCE TO IDLE 24 External P...

Page 119: ...UPRIGHT POSITION 3 Seats and Seat Belts CHECK SECURE 4 Cabin Doors CLOSED and LOCKED 5 Flight Controls FREE and CORRECT 6 Flight Instruments PFD CHECK no red X s 7 Altimeters a PFD BARO SET b Standby...

Page 120: ...agneto or 50 RPM differential between magnetos b Propeller Control CYCLE from high to low RPM return to high RPM push full in c VAC Indicator CHECK d Engine Indicators CHECK e Ammeters and Voltmeters...

Page 121: ...ARNING WHEN THE AUTOPILOT IS ENGAGED IN NAV APR OR BC OPERATING MODES IF THE HSI NAVIGATION SOURCE IS CHANGED MANUALLY USING THE CDI SOFTKEY THE CHANGE WILL INTERRUPT THE NAVIGATION SIGNAL TO THE AUTO...

Page 122: ...EL at 50 60 KIAS 6 Climb Airspeed 70 KIAS FLAPS 20 80 KIAS FLAPS UP 7 Wing Flaps RETRACT at safe altitude SHORT FIELD TAKEOFF 1 Wing Flaps 20 2 Brakes APPLY 3 Throttle Control FULL push full in 4 Prop...

Page 123: ...ve BOTH 6 Cowl Flaps OPEN as required 7 Oxygen Control Lever ON as required NOTE Check masks for proper flow and fit MAXIMUM PERFORMANCE CLIMB 1 Airspeed 84 KIAS at sea level 80 KIAS at 20 000 feet 2...

Page 124: ...S DESIRED 2 Mixture ADJUST if necessary to make engine run smoothly 3 Cowl Flaps CLOSED 4 Altimeters a PFD BARO SET b Standby Altimeter SET 5 ALT SEL SET 6 CDI Softkey SELECT NAV SOURCE 7 FMS GPS REVI...

Page 125: ...VEL AND WILL NOT CORRECT THE AIRPLANE HEADING OR COURSE SET THE HDG BUG TO THE CORRECT HEADING AND SELECT THE CORRECT NAVIGATION SOURCE ON THE HSI USING THE CDI SOFTKEY BEFORE ENGAGING THE AUTOPILOT I...

Page 126: ...LOWER NOSEWHEEL GENTLY 7 Braking MINIMUM REQUIRED SHORT FIELD LANDING 1 Airspeed 70 80 KIAS Flaps UP 2 Wing Flaps FULL below 100 KIAS 3 Airspeed 60 KIAS until flare 4 Elevator and Rudder Trim Controls...

Page 127: ...ottle Control IDLE pull full out 3 Electrical Equipment OFF 4 AVIONICS Switch BUS 1 and BUS 2 OFF 5 Mixture Control IDLE CUTOFF pull full out 6 MAGNETOS Switch OFF 7 MASTER Switch ALT and BAT OFF 8 ST...

Page 128: ...ence of tire deterioration caused by age improper storage or prolonged exposure to weather Check the tread of the tire for depth wear and cuts Replace the tire if fibers are visible After major mainte...

Page 129: ...ct the presence of potential wind damage If the airplane has been operated from muddy fields or in snow or slush check the main and nose gear wheel fairings for obstructions and cleanliness Operation...

Page 130: ...to 1 3 open when the engine starts and then smoothly to full rich as power develops If the engine does not continue to run set the FUEL PUMP switch to the ON position temporarily and adjust the thrott...

Page 131: ...s followed by 20 seconds of cool down If the engine still does not start try to find the cause LEANING FOR GROUND OPERATIONS For all ground operations after starting the engine and when the engine is...

Page 132: ...el or cinders should be done at low engine speed to avoid abrasion and stone damage to the propeller tips NOTE The LOW VOLTS annunciator may come on when the engine is operated at low RPM with a high...

Page 133: ...S TAXIING Continued TAXIING DIAGRAM NOTE Strong quartering tail winds require caution Avoid sudden bursts of the throttle and sharp braking when the airplane is in this attitude Use the steerable nos...

Page 134: ...switch to the L position note the new RPM then turn the switch back to the BOTH position RPM decrease should not be more than 175 RPM on either magneto or be greater than 50 RPM differential between...

Page 135: ...this occurs you are justified in making a thorough full throttle static run up before another takeoff is attempted The engine should run smoothly and turn approximately 2350 2400 RPM Full throttle ru...

Page 136: ...ld be used Soft or rough field takeoffs are performed with 20 flaps by lifting the airplane off the ground as soon as practical in a slightly tail low attitude If no obstacles are ahead the airplane s...

Page 137: ...ise level However MCP power settings may be used for increased climb performance as desired If it is necessary to climb more rapidly to clear mountains or reach favorable winds at higher altitudes the...

Page 138: ...is applicable to new engines and engines in service following cylinder replacement or top overhaul of one or more cylinders The Cruise Performance charts in Section 5 provide the pilot with flight pl...

Page 139: ...ight During normal cruise at power settings below 70 the true airspeed will increase approximately 1 knot for every 125 pounds below maximum gross weight The fuel injection system employed on this eng...

Page 140: ...ne in degrees Fahrenheit CAUTION LEANING WITH A T I T INDICATOR IS PERMITTED ONLY WHEN MANIFOLD PRESSURE AND RPM ARE WITHIN THE GREEN ARC RANGES To use the lean assist system push the ENGINE LEAN and...

Page 141: ...I T setting As noted in the T I T Table Figure 4 4 operation at peak T I T provides the best fuel economy This results in approximately 5 greater range than shown in this POH accompanied by a 4 knot...

Page 142: ...27 in hg due to detonation restrictions Refer to Section 5 cruise tables for operational power settings Certain considerations must be made when using a T I T indicator Operations that are not approv...

Page 143: ...klist After the BEFORE TAKEOFF checklist is complete lean the mixture again as described above until ready to perform the TAKEOFF checklist 2 Adjust the mixture as shown in Section 5 during MCP climbs...

Page 144: ...operation returns 2 Retard the throttle to idle to verify normal engine operation 3 Advance the throttle to 1200 RPM and lean the mixture as described under FUEL SAVINGS PROCEDURES FOR NORMAL OPERATI...

Page 145: ...iliary fuel pump operation 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 configurat...

Page 146: ...e nosewheel The nosewheel must be lowered to the runway carefully after the speed has diminished to avoid unnecessary nose gear loads This procedure is very important for rough or soft field landings...

Page 147: ...the wing low method gives the best control After touchdown hold a straight course with the steerable nosewheel with aileron deflection as applicable and occasional braking if necessary The maximum al...

Page 148: ...overs the takeoff surface allowance must be made for takeoff distances which will be increasingly extended as the snow or slush depth increases The depth and consistency of this cover can in fact prev...

Page 149: ...ures closely and hold sufficient power to keep temperatures in the recommended operating range STARTING When air temperatures are below 20 F 6 C use an external preheater and an external power source...

Page 150: ...light can be left off until the engine is started Use caution to prevent inadvertent forward movement of the airplane during starting when parked on snow or ice During cold weather starting when perfo...

Page 151: ...to minimize the effect of airplane noise on the public 1 Pilots operating airplanes under VFR over outdoor assemblies of persons recreational and park areas and other noise sensitive areas should mak...

Page 152: ......

Page 153: ...rection Alternate Static Source 5 12 Temperature Conversion Chart 5 13 Stall Speeds At 3100 Pounds 5 14 Crosswind Component 5 15 Short Field Takeoff Distance At 3100 Pounds 5 16 Short Field Takeoff Di...

Page 154: ......

Page 155: ...setting Fuel flow data for cruise is based on the recommended lean mixture setting at all altitudes Some indeterminate variables such as mixture leaning technique fuel metering characteristics engine...

Page 156: ...ued Next Page AIRPLANE CONFIGURATION Takeoff weight 3100 Pounds Usable fuel 87 0 Gallons TAKEOFF CONDITIONS Field pressure altitude 3500 Feet Temperature 24 C 16 C Above Standard Wind component along...

Page 157: ...sults in the following These distances are well within the available takeoff field length However a correction for the effect of wind may be made based on information presented in the note section of...

Page 158: ...in Figure 5 10 and the endurance profile chart presented in Figure 5 11 The relationship between power and range is illustrated by the range profile chart Considerable fuel savings and longer range r...

Page 159: ...d on the climb chart The approximate effect of a nonstandard temperature is to increase the time fuel and distance by 10 for each 8 C above standard temperature due to the lower rate of climb In this...

Page 160: ...fuel required is as follows Once the flight is underway ground speed checks will provide a more accurate basis for estimating the time enroute and the corresponding fuel required to complete the trip...

Page 161: ...lows A correction for the effect of wind may be made based on information presented in the note section of the landing chart using the same procedure as outlined for takeoff DEMONSTRATED OPERATING TEM...

Page 162: ...for level flight or maximum power descent Figure 5 1 Sheet 1 of 2 Flaps UP KIAS 55 60 70 80 90 100 110 120 130 140 150 160 KCAS 60 64 73 82 91 100 110 119 128 137 146 156 Flaps 20 KIAS 45 50 60 70 80...

Page 163: ...nt NOTE Windows and ventilators closed cabin heater cabin air and defroster on maximum Figure 5 1 Sheet 2 Flaps UP KIAS ALT KIAS 55 52 60 58 70 71 80 82 90 93 100 103 110 113 120 122 130 131 140 139 1...

Page 164: ...o desired altitude to obtain indicated altitude to fly Windows and ventilators closed cabin heater cabin air and defroster on maximum Figure 5 2 CONDITION Flaps UP CORRECTION TO BE ADDED FEET KIAS Alt...

Page 165: ...CESSNA SECTION 5 MODEL T182T NAV III PERFORMANCE GFC 700 AFCS U S TEMPERATURE CONVERSION CHART Figure 5 3 5 13 T182TPHBUS 00...

Page 166: ...covery may be as much as 250 feet KIAS values are approximate Figure 5 4 FLAP SETTING ANGLE OF BANK 0 30 45 60 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 50 54 54 58 59 64 71 76 20 43 50 46 54 51 59 6...

Page 167: ...CESSNA SECTION 5 MODEL T182T NAV III PERFORMANCE GFC 700 AFCS U S CROSSWIND COMPONENT NOTE Maximum demonstrated crosswind velocity is 15 knots not a limitation Figure 5 5 T182TPHBUS 00 5 15...

Page 168: ...3 Pressure Altitude Feet 0 C 10 C 20 C 30 C 40 C Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll F...

Page 169: ...5 6 Sheet 2 Pressure Altitude Feet 0 C 10 C 20 C 30 C 40 C Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll Feet Total Feet To Clear 50 Foot Obst...

Page 170: ...l figure Figure 5 6 Sheet 3 Pressure Altitude Feet 0 C 10 C 20 C 30 C 40 C Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll Feet Total Feet To Cle...

Page 171: ...5 7 Pressure Altitude Feet ClimbSpeed KIAS Rate of Climb FPM 20 C 0 C 20 C 40 C Sea Level 84 1165 1095 1020 950 2000 83 1125 1050 975 900 4000 83 1085 1005 930 850 6000 82 1040 960 875 795 8000 82 99...

Page 172: ...ime fuel and distance by 10 for each 10 C above standard temperature Distances shown are based on zero wind Figure 5 8 Sheet 1 of 2 Pressure Altitude Feet Climb Speed KIAS Rate of Climb FPM From Sea L...

Page 173: ...ngine start taxi and takeoff allowance Increase time fuel and distance by 10 for each 8 C above standard temperature Distances shown are based on zero wind Figure 5 8 Sheet 2 Pressure Altitude Feet Cl...

Page 174: ...7 137 14 5 26 79 133 15 1 75 133 14 0 70 132 13 1 24 72 128 13 5 68 128 12 7 64 126 11 9 22 63 121 11 7 59 120 11 1 56 118 10 5 20 55 114 10 5 52 113 10 0 49 111 9 5 2200 28 85 137 15 7 80 137 14 7 75...

Page 175: ...26 81 136 15 4 76 136 14 3 71 135 13 3 24 74 132 13 8 69 131 12 9 65 130 12 1 22 65 124 12 0 61 124 11 4 57 122 10 8 20 57 118 10 8 54 116 10 2 51 114 9 7 2200 28 86 140 15 9 81 140 14 9 76 139 13 9...

Page 176: ...0 15 7 77 140 14 6 72 138 13 6 24 75 135 14 1 71 134 13 2 66 133 12 4 22 67 128 12 4 63 127 11 7 59 126 11 1 20 59 121 11 0 56 120 10 5 52 118 10 0 2200 28 87 143 16 1 82 143 15 1 77 142 14 1 26 79 13...

Page 177: ...3 15 9 78 143 14 8 73 141 13 7 24 76 138 14 3 72 137 13 4 67 136 12 5 22 68 132 12 7 64 131 12 0 60 129 11 3 20 60 124 11 3 57 123 10 7 53 121 10 2 2200 28 88 146 16 3 83 146 15 2 78 145 14 2 26 80 14...

Page 178: ...15 9 78 145 14 8 73 144 13 8 24 77 141 14 5 72 140 13 5 68 139 12 6 22 69 135 12 9 65 134 12 1 61 132 11 4 20 61 127 11 4 58 126 10 9 54 123 10 3 2200 28 88 149 16 3 83 149 15 3 78 148 14 2 26 81 144...

Page 179: ...16 0 78 148 14 9 74 147 13 8 24 77 144 14 6 73 143 13 6 68 142 12 8 22 70 138 13 1 66 137 12 3 62 135 11 6 20 62 130 11 6 59 129 11 0 55 126 10 4 2200 28 88 152 16 4 83 152 15 3 78 151 14 3 26 81 147...

Page 180: ...16 0 78 151 14 9 74 149 13 8 24 77 146 14 6 73 145 13 6 68 144 12 7 22 70 140 13 1 66 139 12 3 62 138 11 6 20 62 133 11 6 59 131 11 0 55 128 10 5 2200 28 88 155 16 3 83 155 15 3 78 153 14 2 26 81 150...

Page 181: ...15 9 78 153 14 8 73 152 13 8 24 77 149 14 6 73 148 13 6 68 147 12 7 22 70 143 13 2 66 142 12 4 62 140 11 6 20 63 135 11 7 59 133 11 1 55 130 10 5 2200 28 88 158 16 3 83 157 15 2 78 156 14 2 26 81 152...

Page 182: ...7 86 159 16 6 81 158 15 5 76 157 14 3 26 82 156 15 8 78 155 14 7 73 154 13 7 24 77 151 14 5 72 150 13 5 68 149 12 7 22 70 145 13 1 66 144 12 4 62 141 11 6 20 63 137 11 7 59 135 11 1 55 131 10 5 2200 2...

Page 183: ...27 85 161 16 4 80 160 15 3 75 159 14 2 26 81 158 15 6 77 157 14 5 72 156 13 5 24 76 153 14 4 72 152 13 4 67 150 12 6 22 70 147 13 1 66 146 12 3 62 143 11 6 20 62 139 11 6 59 136 11 0 55 132 10 4 2200...

Page 184: ...27 84 163 16 2 79 162 15 1 74 161 14 0 26 81 160 15 4 76 159 14 3 71 158 13 4 24 76 156 14 2 71 155 13 3 67 152 12 5 22 70 150 13 0 66 148 12 2 62 144 11 5 20 62 140 11 6 58 138 11 0 55 133 10 4 2200...

Page 185: ...E FUEL CONDITIONS 3100 Pounds Recommended Lean Mixture for Cruise Standard Temperature Zero Wind NOTE This chart allows for the fuel used for engine start taxi takeoff and climb and the distance durin...

Page 186: ...ABLE FUEL CONDITIONS 3100 Pounds Recommended Lean Mixture for Cruise Standard Temperature Zero Wind NOTE This chart allows for the fuel used for engine start taxi takeoff and climb and the distance du...

Page 187: ...BLE FUEL CONDITIONS 3100 Pounds Recommended Lean Mixture for Cruise Standard Temperature Zero Wind NOTE This chart allows for the fuel used for engine start taxi takeoff and climb and the distance dur...

Page 188: ...USABLE FUEL CONDITIONS 3100 Pounds Recommended Lean Mixture for Cruise Standard Temperature Zero Wind NOTE This chart allows for the fuel used for engine start taxi takeoff and climb and the distance...

Page 189: ...tances Figure 5 12 Pressure Altitude Feet 0 C 10 C 20 C 30 C 40 C Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll Feet Total Feet To Clear 50 Foo...

Page 190: ......

Page 191: ...ne Weighing Procedures 6 3 Airplane Weighing Form 6 5 Sample Weight and Balance Record 6 7 Weight And Balance 6 8 Baggage Tiedown 6 9 Sample Loading Problem 6 11 Loading Graph 6 13 Loading Arrangement...

Page 192: ......

Page 193: ...ent and installed equipment for this airplane as delivered from the factory can be found in the plastic envelope in the back of this POH WARNING IT IS THE RESPONSIBILITY OF THE PILOT TO MAKE SURE THE...

Page 194: ...centers to a plumb bob dropped from the firewall b Obtain measurement B by measuring horizontally and parallel to the airplane centerline from center of nosewheel axle left side to a plumb bob dropped...

Page 195: ...CESSNA SECTION 6 MODEL T182T NAV III WEIGHT AND BALANCE GFC 700 AFCS EQUIPMENT LIST U S AIRPLANE WEIGHING FORM Figure 6 1 Sheet 1 of 2 T182TPHBUS 00 6 5...

Page 196: ...SECTION 6 CESSNA WEIGHT AND BALANCE MODEL T182T NAV III EQUIPMENT LIST GFC 700 AFCS U S AIRPLANE WEIGHING FORM Figure 6 1 Sheet 2 T182TPHBUS 00 6 6...

Page 197: ...CESSNA SECTION 6 MODEL T182T NAV III WEIGHT AND BALANCE GFC 700 AFCS EQUIPMENT LIST U S SAMPLE WEIGHT AND BALANCE RECORD Figure 6 2 T182TPHBUS 00 6 7...

Page 198: ...Use the Loading Graph to determine the moment 1000 for each additional item to be carried then list these on the loading problem NOTE Loading Graph information for the pilot passengers and baggage is...

Page 199: ...is utilized for baggage only the four forward eyebolts should be used When only baggage area B is used the eyebolts just aft of the baggage door and the eyebolts above or below the shelf area may be u...

Page 200: ...tiedown eyebolts to standard attach points located in the interior area of the airplane shown in Figure 6 6 The maximum allowable floor loading of the rear cabin area is 200 pounds square foot however...

Page 201: ...assenger Seat FS 65 to 82 5 Baggage A FS 82 to 109 120 Pounds Maximum Baggage B FS 109 to 124 80 Pounds Maximum 51 5 9 Baggage C FS 124 to 134 80 Pounds Maximum 6 RAMP WEIGHT AND MOMENT 3112 128 4 7 F...

Page 202: ...ST GFC 700 AFCS U S SAMPLE LOADING PROBLEM NOTE When several loading configurations are representative of your operations it may be useful to fill out one or more of the above columns so specific load...

Page 203: ...LOADING GRAPH NOTE Line representing adjustable seats shows the pilot and front seat passenger center of gravity on adjustable seats positioned for average occupant Refer to the Loading Arrangements...

Page 204: ...occupant Numbers in parentheses indicate forward and aft limits of occupant center of gravity range Arm measured to the center of the areas shown NOTE The usable fuel C G arm is located at FS 46 50 T...

Page 205: ...T182T NAV III WEIGHT AND BALANCE GFC 700 AFCS EQUIPMENT LIST U S INTERNAL CABIN DIMENSIONS NOTE Maximum allowable floor loading is 200 pounds per square foot All dimensions shown are in inches Figure...

Page 206: ...DEL T182T NAV III EQUIPMENT LIST GFC 700 AFCS U S CENTER OF GRAVITY MOMENT ENVELOPE NOTE If takeoff weight is more than maximum landing weight allow flight time for fuel burn off to 2950 pounds before...

Page 207: ...WEIGHT AND BALANCE GFC 700 AFCS EQUIPMENT LIST U S CENTER OF GRAVITY LIMITS NOTE If takeoff weight is more than maximum landing weight allow flight time for fuel burn off to 2950 pounds before landin...

Page 208: ......

Page 209: ...T LIST DESCRIPTION column each item is assigned a descriptive name to help identify its function In the REF DRAWING column a Cessna drawing number is provided which corresponds to the item NOTE If add...

Page 210: ...10 1201131 2 0 3 152 9 23 02 R AUDIO INTERCOM MARKER BEACON 3930368 GMA 1347 AUDIO PANEL 3910317 2 2 6 16 5 CI 102 MARKER BEACON ANTENNA 3960193 2 0 5 131 5 23 03 R NAV COM GPS 1 COMPUTER 3940389 GIA...

Page 211: ...NT PASSENGER 0719087 5 2 50 3 25 08 S SEAT BELT AND SHOULDER HARNESS INERTIA REEL AUTO ADJUST REAR SEAT 0719087 5 2 87 8 25 09 S SUN VISOR SET OF 2 0519004 2 1 2 33 0 25 10 S BAGGAGE RESTRAINT NET 121...

Page 212: ...30 02 S STALL SENSOR HEAT AND PITOT HEAT 0720701 0 7 28 0 31 INDICATING RECORDING SYSTEM 31 01 S RECORDING HOURMETER C664503 0103 0706015 0 5 16 7 31 02 R STALL WARNING SYSTEM STALL WARNING HORN 07180...

Page 213: ...0 2 15 5 34 05 R COMPASS MAGNETIC 1213679 5 0 5 18 0 34 06 R TRANSPONDER 3940389 GTX 33 TRANSPONDER 3910317 5 3 6 134 0 CI 105 16 TRANSPONDER ANTENNA 3960195 0 4 86 5 34 07 R PFD DISPLAY 3930374 GDU 1...

Page 214: ...6 FILTER 1201075 2 0 3 11 5 VACUUM REGULATOR AA2H3 2 0 5 2 1 37 02 R VACUUM TRANSDUCER P165 5786 0706015 0 3 8 5 53 FUSELAGE 53 01 S REFUELING STEPS AND HANDLE 0701127 2 1 7 15 2 53 02 A STABILIZER AB...

Page 215: ...TACHOMETER SENSOR 1A3C 2 0701172 0 2 8 0 77 02 R CYLINDER HEAD THERMOCOUPLES ALL CYLINDERS 32DKWUE006F0126 0701172 0 2 12 0 77 03 S EXHAUST THERMOCOUPLES ALL CYLINDERS 86317 0701172 0 3 12 0 77 04 R T...

Page 216: ......

Page 217: ...ruments 7 16 Attitude Indicator 7 17 Airspeed Indicator 7 18 Altimeter 7 18 Horizontal Situation Indicator 7 19 Vertical Speed Indicator 7 20 Ground Control 7 21 Wing Flap System 7 22 Landing Gear Sys...

Page 218: ...Fuel Distribution 7 49 Fuel Indicating System 7 49 Fuel Calculations 7 51 Auxiliary Fuel Pump Operation 7 53 Fuel Return System 7 54 Fuel Venting 7 54 Reduced Tank Capacity 7 54 Fuel Selector Valve 7...

Page 219: ...ted Avionics Unit GIA 7 84 Attitude and Heading Reference System AHRS and Magnetometer GRS 7 84 Air Data Computer GDC 7 85 Engine Monitor GEA 7 85 Transponder GTX 7 85 XM Weather and Radio Data Link G...

Page 220: ......

Page 221: ...to the forward door posts and extend forward to the firewall The externally braced wings containing integral fuel tanks are constructed of a front and rear spar with formed sheet metal ribs doublers...

Page 222: ...sists of formed leading edge skins a forward spar ribs torque tube and bellcrank left upper and lower V type corrugated skins and right upper and lower V type corrugated skins incorporating a trailing...

Page 223: ...e horizontally mounted trim control wheel either left or right to the desired trim position Rotating the trim wheel to the right will trim nose right conversely rotating it to the left will trim nose...

Page 224: ...SECTION 7 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL T182T NAV III GFC 700 AFCS U S FLIGHT CONTROLS AND TRIM SYSTEM Figure 7 1 Sheet 1 of 2 T182TPHBUS 00 7 8...

Page 225: ...CESSNA SECTION 7 MODEL T182T NAV III AIRPLANE AND SYSTEM DESCRIPTION GFC 700 AFCS U S FLIGHT CONTROLS AND TRIM SYSTEMS Figure 7 1 Sheet 2 T182TPHBUS 00 7 9...

Page 226: ...n PILOT PANEL LAYOUT The PFD centered on the instrument panel in front of the pilot shows the primary flight instruments during normal operation During engine start reversionary operation MFD failure...

Page 227: ...t receives power Lighting for this subpanel is controlled using the SW CB PANELS dimmer control See the ELECTRICAL EQUIPMENT descriptions in this section for further information CENTER PANEL LAYOUT Th...

Page 228: ...ag to provide immediate warning of vacuum system failure The engine controls are found on the lower center instrument panel below the standby instrument cluster The controls are conventional push pull...

Page 229: ...er is found to the right of the ELT switch and records engine operating time when oil pressure is greater than 20 PSI for maintenance purposes Refer to the ENGINE INSTRUMENTS description in this secti...

Page 230: ...SECTION 7 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL T182T NAV III GFC 700 AFCS U S INSTRUMENT PANEL Figure 7 2 T182TPHBUS 00 7 14...

Page 231: ...Microphone Button 15 Glove Box 16 Defroster Control 17 Cabin Heat Control 18 Cabin Air Control 19 Wing Flap Control Lever And Position Indicator 20 Mixture Control Knob 21 Propeller Control Knob 22 C...

Page 232: ...de and vertical speed The vertical indicators take the place of analog indicators with a fixed circular scale and rotating pointer Knobs knob sets two knobs on a common shaft and membrane type push bu...

Page 233: ...o 60 of roll The roll pointer is slaved to the airplane symbol The pitch index scale is graduated in 5 increments with every 10 of pitch labeled If pitch limits are exceeded in either the nose up or n...

Page 234: ...lower center instrument panel Colored arcs are provided to indicate the maximum speed high cruise speed caution range normal operating range full wing flap operating range and low airspeed awareness...

Page 235: ...gment scale below the heading window at the top of the HSI shows half and standard rates of turn based on the length of the magenta turn vector The cyan HSI heading reference pointer bug is set using...

Page 236: ...EADING OR COURSE SET THE HDG BUG TO THE CORRECT HEADING AND SELECT THE CORRECT NAVIGATION SOURCE ON THE HSI USING THE CDI SOFTKEY BEFORE ENGAGING THE AUTOPILOT IN ANY OTHER OPERATING MODE VERTICAL SPE...

Page 237: ...not available or pushing is required use the wing struts as push points Do not use the vertical or horizontal surfaces to move the airplane If the airplane is to be towed by vehicle never turn the no...

Page 238: ...lap control lever is moved up or down in a slotted panel that provides mechanical stops at the 10 and 20 positions To change flap setting the wing flap control lever is moved to the right to clear mec...

Page 239: ...gear wheel is equipped with a hydraulically actuated disc type brake on the inboard side of each wheel BAGGAGE COMPARTMENT The baggage compartment consists of the area from the back of the rear passe...

Page 240: ...rank under the right corner of the seat until a comfortable height is obtained To adjust the seat back angle pull up on the release button located in center front of seat just under the seat bottom po...

Page 241: ...in To use the integrated seat belt shoulder harness grasp the link with one hand and in a single motion extend the assembly and insert into the buckle Positive locking has occurred when a distinctive...

Page 242: ...SECTION 7 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL T182T NAV III GFC 700 AFCS U S INTEGRATED SEAT BELT SHOULDER HARNESS Figure 7 4 T182TPHBUS 01 7 26...

Page 243: ...sed door handle near the aft edge of either door by grasping the forward edge of the handle and pulling outboard To close or open the doors from inside the airplane use the combination door handle and...

Page 244: ...de windows and rear windows are of the fixed type and cannot be opened CONTROL LOCKS A control lock is provided to lock the aileron and elevator control surfaces to prevent damage to these systems by...

Page 245: ...ol is configured so that the throttle is open in the forward position and closed in the full aft position A friction lock located at the base of the throttle is operated by rotating the lock clockwise...

Page 246: ...d Battery Currents AMPS When the ENGINE softkey is pressed the LEAN and SYSTEM softkeys appear adjacent to the ENGINE softkey The LEAN page provides simultaneous indicators for Turbine Inlet Temperatu...

Page 247: ...icated altitude the green arc range changes to 15 to 27 in hg which is one inch less manifold pressure at the top of the green arc The maximum manifold pressure at all altitudes is 32 in hg When manif...

Page 248: ...ages If engine speed becomes 2472 RPM or more while on the LEAN or SYSTEM page the display will return to the ENGINE page A speed sensor mounted on the engine tachometer drive accessory pad provides a...

Page 249: ...range and a red band from 115 to 120 PSI A white pointer indicates actual oil pressure Oil pressure is shown numerically on the SYSTEM page When oil pressure is 0 to 20 PSI or 115 to 120 PSI the point...

Page 250: ...operative OIL TEMPERATURE Engine oil temperature is shown on the ENGINE page by the OIL TEMP horizontal indicator The indicator range is from 75 F to 250 F with a green band normal operating range fro...

Page 251: ...than 1685 F while on the LEAN or SYSTEM page the display will default to the ENGINE page An Exhaust Gas Temperature EGT probe is installed in the transition of the turbocharger turbine inlet and provi...

Page 252: ...s a signal to the engine display that is processed and shown as CHT on the EIS LEAN page EXHAUST GAS TEMPERATURE Exhaust gas temperature for all six cylinders is shown on the LEAN page of the EIS The...

Page 253: ...the engine driven oil pump Oil from the pump passes through a full flow oil filter a pressure relief valve at the rear of the right oil gallery and a thermostatically controlled remote oil cooler Oil...

Page 254: ...e START position with the MASTER switch in the ON position the starter contactor is closed and the starter now energized will crank the engine When the switch is released it will automatically return...

Page 255: ...l unit fuel manifold fuel flow indicator and air bleed type injector nozzles Fuel is delivered by the engine driven fuel pump to the fuel air control unit The fuel air control unit correctly proportio...

Page 256: ...l lever to the right to clear a detent then moving the control lever up to the OPEN position While in cruise flight cowl flaps should be closed unless hot day conditions require them to be adjusted to...

Page 257: ...ultant change in flow will have no effect on the engine if the waste gate is still open because the waste gate position is changed to hold compressor discharge pressure constant A waste gate controlle...

Page 258: ...SECTION 7 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL T182T NAV III GFC 700 AFCS U S TURBOCHARGER SCHEMATIC Figure 7 5 T182TPHBUS 00 7 42...

Page 259: ...engine RPM is just opposite of the normally aspirated engine An increase in engine RPM will result in an increase in manifold pressure and a decrease in engine RPM will result in a decrease in manifo...

Page 260: ...gine fuel flow is regulated by fuel pump output and the metering effects of the throttle and mixture control When the waste gate is open fuel flow will vary directly with manifold pressure engine spee...

Page 261: ...Under some circumstances such as rapid throttle movement especially with cold oil it is possible that the engine can be over boosted slightly above the maximum takeoff manifold pressure of 32 in hg Th...

Page 262: ...ced into the governor with the propeller control establishes the propeller speed and thus the engine speed to be maintained The governor then controls flow of engine oil boosted to high pressure by th...

Page 263: ...circuit conditions When the system conditions are normal a green PROP HEAT annunciator is shown on the PFD If the timer detects faulty system wiring or a heated boot failure it removes the current sup...

Page 264: ...d fuel injection nozzles The fuel system also incorporates a fuel return system that returns fuel from the top of the fuel servo back to each integral wing tank The system includes a flexible fuel hos...

Page 265: ...o a fuel distribution valve flow divider located on the bottom of the engine From the fuel distribution valve individual fuel lines are routed to air bleed type injector nozzles located in the intake...

Page 266: ...sensor outputs When fuel quantity is less than 8 gallons indicated and remains less than this level for more than 60 seconds LOW FUEL L left and or LOW FUEL R right will be displayed in amber on the P...

Page 267: ...al fuel used since last reset of the totalizer To reset the GAL USED the EIS SYSTEM page must be active and the RST USED softkey must be selected GAL USED is calculated after reset using information f...

Page 268: ...SECTION 7 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL T182T NAV III GFC 700 AFCS U S FUEL SYSTEM Continued Figure 7 7 T182TPHBUS 01 7 52...

Page 269: ...of the mixture It is not necessary to operate the auxiliary fuel pump during normal takeoff and landing since gravity and the engine driven fuel pump will supply adequate fuel flow In the event of fai...

Page 270: ...al to system operation Complete blockage of the fuel venting system will result in decreasing fuel flow and eventual engine stoppage The fuel venting system consists of an interconnecting vent line be...

Page 271: ...by one fuel tank indicating more fuel than the other on the L FUEL and R FUEL indicators The resulting fuel imbalance can be corrected by turning the fuel selector valve to the fuel tank indicating t...

Page 272: ...re operated by applying pressure to the top of either the left pilot s or right copilot s set of rudder pedals which are interconnected When the airplane is parked both main wheel brakes may be set by...

Page 273: ...available to supply power to the essential bus in the event that alternator and main battery power sources have both failed The primary buses are supplied with power whenever the MASTER switch is turn...

Page 274: ...SECTION 7 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL T182T NAV III GFC 700 AFCS U S ELECTRICAL SYSTEM Continued Figure 7 8 Sheet 1 of 3 T182TPHBUS 00 7 58...

Page 275: ...CESSNA SECTION 7 MODEL T182T NAV III AIRPLANE AND SYSTEM DESCRIPTION GFC 700 AFCS U S ELECTRICAL SYSTEM Continued Figure 7 8 Sheet 2 T182TPHBUS 00 7 59...

Page 276: ...SECTION 7 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL T182T NAV III GFC 700 AFCS U S ELECTRICAL SYSTEM Continued Figure 7 8 Sheet 3 T182TPHBUS 00 7 60...

Page 277: ...ormal operation both sides of the switch ALT and BAT are ON simultaneously however the BAT side of the switch may be selected separately as necessary The ALT side of the switch can not be set to ON wi...

Page 278: ...The switch is set to the ARM position during normal flight operation to allow the standby battery to charge and to be ready to power the essential bus in the event of alternator and main battery failu...

Page 279: ...ing shall be about 28 0 volts When the voltage for either main or essential buses is above 32 0 volts the numerical value and VOLTS text turns red This warning indication along with the HIGH VOLTS ann...

Page 280: ...ad exceeds the output of the alternator the main battery ammeter indicates the main battery discharge rate In the event that standby battery discharge is required normal steady state discharge should...

Page 281: ...ammeter discharge indications may occur Under these conditions increase RPM or decrease electrical loads to reduce demand on the battery In the event an overvoltage condition or other alternator faul...

Page 282: ...rrected by a qualified maintenance technician before flight HIGH VOLTAGE ANNUNCIATION The HIGH VOLTS annunciator will come on when main or essential bus voltage is above 32 0 volts This warning annunc...

Page 283: ...tch is discouraged since the practice will decrease the life of the circuit breaker All circuit breakers on ELECTRICAL BUS 1 ELECTRICAL BUS 2 and CROSSFEED BUS are not capable of being opened or disen...

Page 284: ...power source must be provided to prevent damage to the avionics equipment from transient voltages Set AVIONICS switches BUS 1 and BUS 2 to OFF before starting the engine The following check should be...

Page 285: ...ome on and pressing it again will make the lights go out All other exterior lights are operated by switches found on the lighted switch panel to the left of the PFD Exterior lights are grouped togethe...

Page 286: ...plished by using internally lit panels Rotating the SW CB PANELS dimmer found on the switch panel in the DIMMING group controls the lighting level for both panels Rotating the dimmer counterclockwise...

Page 287: ...ttitude indicator altimeter non stabilized magnetic compass and overhead oxygen console Rotating the dimmer counterclockwise decreases light intensity from the highest level to off Pilot s chart map l...

Page 288: ...heat and ventilating air is supplied by outlet holes spaced across a cabin manifold just forward of the pilot s and front passenger s feet Rear cabin heat and air is supplied by two ducts from the ma...

Page 289: ...CESSNA SECTION 7 MODEL T182T NAV III AIRPLANE AND SYSTEM DESCRIPTION GFC 700 AFCS U S CABIN HEATING VENTILATION AND DEFROSTING SYSTEM Figure 7 9 T182TPHBUS 00 7 73...

Page 290: ...ssembly An oxygen cylinder filler valve is located on the left side of the fuselage tailcone under a cover plate Cylinder pressure is indicated by a pressure gage located in the overhead oxygen consol...

Page 291: ...nect the oxygen mask microphone plug the mask lead into the appropriate outlet in place of the headset microphone lead A switch is incorporated on the left hand control wheel to operate the microphone...

Page 292: ...N MODEL T182T NAV III GFC 700 AFCS U S OXYGEN DURATION CHART 50 CUBIC FEET CAPACITY NOTE This chart is based on a pilot with a red color coded oxygen line fitting and passengers with orange color code...

Page 293: ...procedure 1400 PSI of pressure will safely sustain the pilot only for 4 hours and 10 minutes The same pressure will sustain the pilot and three passengers for approximately 1 hours and 20 minutes NOTE...

Page 294: ...Lever ON 4 Face Mask Hose Flow Indicator CHECK NOTE Oxygen is flowing if the indicator is being forced toward the mask 5 Delivery Hose UNPLUG FROM OUTLET when discontinuing use of oxygen NOTE This au...

Page 295: ...PITOT HEAT circuit breaker is found on the circuit breaker panel at the lower left side of the pilot panel A static pressure alternate source valve ALT STATIC AIR is located adjacent to the throttle c...

Page 296: ...OW VACUUM annunciator will display in amber on the PFD ATTITUDE INDICATOR The standby attitude indicator is a vacuum powered gyroscopic instrument found on the center instrument panel below the MFD Th...

Page 297: ...CESSNA SECTION 7 MODEL T182T NAV III AIRPLANE AND SYSTEM DESCRIPTION GFC 700 AFCS U S VACUUM SYSTEM Figure 7 11 T182TPHBUS 00 7 81...

Page 298: ...push to reset circuit breaker labeled WARN on the left side of the circuit breaker panel protects the stall warning system The vane in the wing senses the change in airflow over the wing and operates...

Page 299: ...nformation plus altitude airspeed and vertical speed information to the pilot The PFD also controls and displays all communication and navigation frequencies as well as displaying warning status annun...

Page 300: ...e units act as the main communications hub linking all of the other peripheral parts to the GDU displays Each unit contains a GPS receiver a VHF navigation receiver VHF communication transceiver and t...

Page 301: ...M fuel flow and to the fuel gauging system This unit transmits this information to the engine display computers TRANSPONDER GTX The full featured Mode S transponder provides Mode A C and S functions C...

Page 302: ...g CWS operation to reduce control forces or large pitch oscillations that may occur after releasing the CWS button WARNING WHEN THE AUTOPILOT IS ENGAGED IN NAV APR OR BC OPERATING MODES IF THE HSI NAV...

Page 303: ...CESSNA SECTION 7 MODEL T182T NAV III AIRPLANE AND SYSTEM DESCRIPTION GFC 700 AFCS U S GFC 700 SYSTEM SCHEMATIC Figure 7 12 T182TPHBUS 00 7 87...

Page 304: ...light information through the G1000 system This system includes a Traffic Advisory System TAS for air traffic and an Enhanced Ground Proximity Warning System EGPWS for terrain The KTA 870 unit is moun...

Page 305: ...one provides forced air cooling to the integrated avionics units and to the transponder A fan located forward of the instrument panel removes air from between the firewall bulkhead and instrument pane...

Page 306: ...ion receivers contained in the integrated avionics units The marker beacon antenna is mounted on the bottom of the tailcone It provides the signal to the marker beacon receiver located in the audio pa...

Page 307: ...ead console Volume and output for this speaker are controlled through the audio panel Each control wheel contains a push to talk switch This switch allows the pilot or front passenger to transmit on t...

Page 308: ...lete description and operating instructions of the audio panel refer to the Garmin G1000 CRG Since the entertainment audio input is not controlled by a switch there is no way to deselect the entertain...

Page 309: ...POWER OUTLET 12V 10A is located in the right sidewall by the aft passenger seat A switch located on the switch panel labeled CABIN PWR 12V controls the operation of the power outlets NOTE Charging of...

Page 310: ...static conditions loss of radio signals is possible even with static dischargers installed Whenever possible avoid known severe precipitation areas to prevent loss of dependable radio signals If avoid...

Page 311: ...c approximately 125 psi and the operating lever lock pin is securely in place To operate the fire extinguisher 1 Loosen retaining clamp s and remove extinguisher from bracket 2 Hold extinguisher uprig...

Page 312: ...ses a CO level of 50 parts per million PPM by volume or greater the alarm turns on a flashing warning annunciation CO LVL HIGH in the annunciation window on the PFD with a continuous tone until the PF...

Page 313: ...5 Airplane File 8 6 Airplane Inspection Periods 8 7 FAA Required Inspections 8 7 Cessna Inspection Programs 8 7 Cessna Customer Care Program 8 8 Pilot Conducted Preventive Maintenance 8 8 Alterations...

Page 314: ...Approved Fuel Grades And Colors 8 15 Fuel Capacity 8 15 Fuel Additives 8 16 Fuel Contamination 8 20 Oxygen Filling Pressures 8 21 Landing Gear 8 22 Cleaning And Care 8 23 Windshield And Windows 8 23 P...

Page 315: ...hen lubrications and oil changes are necessary as well as other seasonal and periodic services The airplane should be regularly inspected and maintained in accordance with information found in the air...

Page 316: ...Copies of the actual bulletins are available from Cessna Service Stations and Cessna Propeller Aircraft Customer Services UNITED STATES AIRPLANE OWNERS If your airplane is registered in the U S appro...

Page 317: ...her supplies that are applicable to your airplane are available from a Cessna Service Station Information Manual contains Pilot s Operating Handbook Information Maintenance Manual Wiring Diagram Manua...

Page 318: ...Pilot s Operating Handbook and FAA Approved Airplane Flight Manual 2 Garmin G1000 Cockpit Reference Guide 190 00384 00 Rev B or subsequent 3 Weight and Balance and associated papers latest copy of the...

Page 319: ...ith a Progressive Care Inspection Program or a PhaseCard Inspection Program Both programs offer systems which allow the work load to be divided into smaller operations that can be accomplished in shor...

Page 320: ...ou by any Cessna Service Station in most cases you will prefer to have the Cessna Service Station from whom you purchased the airplane accomplish this work PILOT CONDUCTED PREVENTIVE MAINTENANCE A cer...

Page 321: ...gear turning angle of 29 either side of center or damage to the nose landing gear will result CAUTION REMOVE ANY INSTALLED RUDDER LOCK BEFORE TOWING If the airplane is towed or pushed over a rough su...

Page 322: ...refer to the Maintenance Manual for specific procedures and equipment required Individual main gear may be jacked by using the jack pad which is incorporated in the main landing gear strut step bracke...

Page 323: ...rplanes that are flown every 30 days or less may not achieve normal service life because of internal corrosion Corrosion occurs when moisture from the air and the products of combustion combine to att...

Page 324: ...ines all items which require attention at specific intervals plus those items which require servicing inspection and or testing at special intervals Since Cessna Service Stations conduct all service i...

Page 325: ...er the first 25 hours of operation RECOMMENDED VISCOSITY FOR TEMPERATURE RANGE Multiviscosity or straight grade oil may be used throughout the year for engine lubrication Refer to the following table...

Page 326: ...rst 25 hour oil and filter change a general inspection of the overall engine compartment is required Items which are not normally checked during a preflight inspection should be given special attentio...

Page 327: ...Refer to Fuel Additives in later paragraphs for additional information FUEL CAPACITY 92 0 U S Gallons Total 46 0 U S Gallons per tank NOTE To ensure maximum fuel capacity when refueling and minimize...

Page 328: ...ions are quite rare and will not normally pose a problem to owners and operators they do exist in certain areas of the world and consequently must be dealt with when encountered Therefore to help alle...

Page 329: ...significant because alcohol is most effective when it is completely dissolved in the fuel To ensure proper mixing the following is recommended 1 For best results the alcohol should be added during th...

Page 330: ...SECTION 8 CESSNA AIRPLANE HANDLING SERVICE MODEL T182T NAV III AND MAINTENANCE GFC 700 AFCS U S FUEL MIXING RATIO Figure 8 1 T182TPHBUS 00 8 18...

Page 331: ...N DETRIMENTAL EFFECTS TO THE FUEL TANK AND SEALANT AND DAMAGE TO O RINGS AND SEALS USED IN THE FUEL SYSTEM AND ENGINE COMPONENTS A CONCENTRATION OF LESS THAN THAT RECOMMENDED 0 10 BY TOTAL VOLUME MINI...

Page 332: ...has been removed If after repeated sampling evidence of contamination still exists the airplane should not be flown Tanks should be drained and system purged by qualified maintenance personnel All evi...

Page 333: ...ing to 1850 PSI will not result in a properly filled cylinder Fill to pressures indicated on the table below for ambient temperature OXYGEN FILLING PRESSURES Figure 8 2 WARNING OIL GREASE OR OTHER LUB...

Page 334: ...ng gear Keep strut filled with MIL H 5606 hydraulic fluid per filling instructions placard and with no load on the strut inflate with air to 55 0 60 0 PSI Do not over inflate COMPONENT SERVICING CRITE...

Page 335: ...HE PLASTIC AND MAY CAUSE IT TO CRAZE If a windshield cleaner is not available the plastic can be cleaned with soft cloths moistened with Stoddard solvent to remove oil and grease Follow by carefully w...

Page 336: ...rdance with the manufacturer s instructions If the airplane is operated in a seacoast or other salt water environment it must be washed and waxed more frequently to assure adequate protection Special...

Page 337: ...s which cause radio interference and may perforate the boots Servicing operations should be done carefully to avoid damaging this conductive coating or tearing the boots To prolong the life of propell...

Page 338: ...have been treated with Age Master No 1 apply a coating of ICEX to the boots in accordance with applicable instructions on the ICEX container NOTE ICEX may be beneficial as an ice adhesion depressant...

Page 339: ...gularly with a vacuum cleaner Blot up any spilled liquid promptly with cleansing tissue or rags Don t pat the spot press the blotting material firmly and hold it for several seconds Continue blotting...

Page 340: ...FC 700 AFCS U S CLEANING AND CARE Continued AVIONICS CARE The Garmin GDU displays have an anti reflective coating that is very sensitive to skin oils waxes ammonia and abrasive cleaners Clean the disp...

Page 341: ...list to ensure all applicable supplements have been placed in the Pilot s Operating Handbook POH Supplements for both standard and installed optional equipment must be maintained to the latest revisio...

Page 342: ......

Page 343: ...PPED BY CESSNA HOWEVER SOME CHANGES MAY HAVE OCCURRED AND THE OWNER SHOULD VERIFY THIS IS THE LATEST MOST UP TO DATE VERSION BY CONTACTING CESSNA CUSTOMER SUPPORT AT 316 517 5800 Supplement Number Nam...

Page 344: ......

Page 345: ...OCATOR TRANSMITTER ELT This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Artex ME406 Emergency Locator Transmitter ELT...

Page 346: ...ELT Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE PA...

Page 347: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 348: ...gage compartment aft panel On the ELT transmitter unit is a panel containing an ARM ON switch and a transmitter warning light The ELT installation uses two different warnings to tell the pilot when th...

Page 349: ...e on 2 TRANSMITTER WARNING LIGHT Light comes on RED to indicate the transmitter is transmitting a distress signal 3 ANTENNA RECEPTACLE Connects to the antenna mounted on top of tailcone 4 REMOTE CABLE...

Page 350: ...ELT with the applicable civil aviation authority before use to make sure that the identification code transmitted by the ELT is in the COSPAS SARSAT database Refer to www cospas sarsat org for registr...

Page 351: ...requires manual switching of the ELT panel switch which is located on the ELT unit 1 MAKE SURE THE ELT IS ENERGIZED a If the red warning light above the remote switch is not flashing set the remote s...

Page 352: ...and arm the ELT after it has been accidentally energized no emergency The ELT can be energized by a lightning strike or hard landing If the red light above the remote switch is flashing and the aural...

Page 353: ...OCATOR TRANSMITTER ELT This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Artex C406 N Emergency Locator Transmitter ELT...

Page 354: ...R ELT Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE P...

Page 355: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 356: ...n the tailcone along the left side behind the baggage compartment aft panel On the ELT transmitter unit is a panel containing an ON OFF switch and a transmitter warning light The ELT installation uses...

Page 357: ...on 2 TRANSMITTER WARNING LIGHT Light comes on RED to indicate the transmitter is transmitting a distress signal 3 REMOTE CABLE JACK Connects to the ELT remote switch assembly located on the upper righ...

Page 358: ...ELT with the applicable civil aviation authority before use to make sure that the identification code transmitted by the ELT is in the COSPAS SARSAT database Refer to www cospas sarsat org for regist...

Page 359: ...requires manual switching of the ELT panel switch which is located on the ELT unit 1 MAKE SURE THE ELT IS ENERGIZED a If the red warning light above the remote switch is not flashing set the remote s...

Page 360: ...d arm the ELT after it has been accidentally energized no emergency The ELT can be energized by a lightning strike or hard landing If the red light above the remote switch is flashing and the aural wa...

Page 361: ...IONS WX 500 STORMSCOPE This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the L3 Communications WX 500 Stormscope is install...

Page 362: ...Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE PAGES S...

Page 363: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 364: ...THER THUNDERSTORMS USE OF THE WX 500 TO PENETRATE HAZARDOUS WEATHER IS PROHIBITED The L3 Communications WX 500 Stormscope sensor detects electrical discharge lightning activity through a dedicated ant...

Page 365: ...by rotating the RNG control knob on the MFD bezel The user may also choose between Strike or Cell display modes using the MODE softkey See the WX 500 User s Guide for information regarding Strike and...

Page 366: ...s Guide must be available to the flight crew when operating the WX 500 Stormscope EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when the L3 Communications WX 500 Stormsc...

Page 367: ...C DIRECTION FINDER ADF This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Bendix King KR 87 Automatic Direction Finder A...

Page 368: ...R ADF Use the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE P...

Page 369: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 370: ...op frequency display allows switching between preselected standby and active frequencies by pushing the frequency transfer button Both preselected frequencies are stored in a nonvolatile memory circui...

Page 371: ...CESSNA SECTION 9 SUPPLEMENTS MODEL T182T NAV III SUPPLEMENT 4 GFC 700 AFCS U S FAA APPROVED BENDIX KING KR87 AUTOMATIC DIRECTION FINDER ADF Figure S4 1 T182TPHBUS S4 00 S4 5...

Page 372: ...ive the carrier wave and its morse code identifier can be heard NOTE CW signals Morse Code are unmodulated and no audio will be heard without use of BFO This type of signal is not used in the United S...

Page 373: ...R BUTTON SET RST The SET RST button resets the elapsed timer whether it is being displayed or not 9 FLIGHT TIMER ELAPSED TIMER MODE SELECTOR BUTTON FLT ET The FLT ET button selects either Flight Timer...

Page 374: ...TION FINDER 1 OFF VOL Control ON 2 Frequency Selector Knobs SELECT desired frequency in the standby frequency display 3 FRQ Button PUSH to move the desired frequency from the standby to the active pos...

Page 375: ...vel NOTE A 1000 Hz tone and Morse Code identifier is heard in the audio output when a CW signal is received TO OPERATE FLIGHT TIMER 1 OFF VOL Control ON 2 FLT ET Mode Button PRESS once or twice until...

Page 376: ...FRQ button then transferred to active by pushing the FRQ button again TO OPERATE ELAPSED TIME TIMER COUNT DOWN MODE 1 OFF VOL Control ON 2 FLT ET Mode Button PRESS once or twice until ET is annunciat...

Page 377: ...he U S the FCC which assigns AM radio frequencies occasionally will assign the same frequency to more than one station in an area Certain conditions such as Night Effect may cause signals from such st...

Page 378: ...ing MOUNTAIN EFFECT Radio waves reflecting from the surface of mountains may cause the pointer to fluctuate or show an erroneous bearing This should be taken into account when taking bearings over mou...

Page 379: ...JAR OPS OPERATIONAL ELIGIBILITY This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual for JAR OPS Operational Eligibility SERIAL NO...

Page 380: ...he Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE PAGES Supple...

Page 381: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 382: ...e of the G1000 System has been tested and approved for IFR enroute terminal and non precision RNAV or GPS approach operations per AC 20 138A when using GPS GNSS with the correct navigation database Th...

Page 383: ...and Draft TGL 13 Rev 2 Extended Squitter functionality is supported by the GTX 33 This does not constitute airworthiness or operational approval for Extended Squitter functionality OPERATING LIMITATI...

Page 384: ......

Page 385: ...6 CANADIAN CERTIFIED AIRPLANES This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual for Canadian Certified Airplanes SERIAL NO REG...

Page 386: ...e Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE PAGES Supplem...

Page 387: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 388: ...rules i e 14 CFR Part 91 and 14 CFR Part 135 are not applicable The airplane must be equipped and operated in accordance with Transport Canada The Artex ME406 Emergency Locator Transmitter installati...

Page 389: ...NT 6 GFC 700 AFCS U S FAA APPROVED NORMAL PROCEDURES There is no change to the airplane normal procedures for Canadian Certified Airplanes PERFORMANCE There is no change to the airplane performance fo...

Page 390: ......

Page 391: ...d Airplane Flight Manual when used for Brazilian Certified Airplanes and is approved by the U S Federal Aviation Administration FAA on behalf of the Ag ncia Nacional de Avia o Civil ANAC for Brazilian...

Page 392: ...the Log of Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number LOG OF EFFECTIVE PAGES Suppl...

Page 393: ...he following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that ar...

Page 394: ...There is no change to the airplane operating limitations when used for Brazilian Certified Airplanes EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when used for Brazilia...

Page 395: ...A Approved Airplane Flight Manual for revision status Supplement Number Name Equipment Installed 1 Artex ME406 Emergency Locator Transmitter ELT _____________ 2 Artex C406 N Emergency Locator Transmit...

Page 396: ......

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