Cessna Skylane 182T Page 6 Operating Handbook Download

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Summary of Contents for Skylane 182T

Page 1: ...No N780CP Th s publ cat on includes the material required to be furnished to the pilot by 14 CFR Part 23 f 7 Member of GAMA APPROVED BY FMA PAOVEDLJNDERFARZ SUPLCnJ lMCam ACcnllC0 0 6 COPYRIGHT 2004 C...

Page 2: ...852 54 THIS MANUALWAS PROVIDED FOR THE AIRPLANE IDENTIFIED ON THE TITLE PAGE ON 04 04 2006 SUBSEQUENT REVISIONSSUPPLIED BY CESSNA AIRCRAFT COMPANY MUST BE PROPERLY INSERTED edsna Aircraft Company...

Page 3: ...182T NAV Ill INTRODUCTION Pilot s Operating Handbook and FAA Approved Airplane Flight Manldal 182T NAV Ill AVIONICS OP TION Original Issue 3 June 2004 Revision 4 22 December 2005 PART NUMBER 182TPHAUS...

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Page 5: ...e contained in the Customer Care Program Handbook supplied with your airplane The Customer Care Card assigned to you at delivery will establish your eligibility under warranty and should be presented...

Page 6: ...813 NM 87 Gallons Usable Fuel Time 5 8 HOURS Max Range at 10 000 Feet 55 Power Range 930 NM 87 Gallons Usable Fuel Time 7 6 HOURS RATE OF CLIMB AT SEA LEVEL 924 FPM SERVICE CElLllVG 18 100 FEET TAKEO...

Page 7: ...NOTE Speed performance and range are shown for an airplane equipped with the standard wheel and brake fairings These fairings increase the speeds approximately 3 knots over an airplane without the fa...

Page 8: ...erations Supplements are individual documents and may be issued or revised without regard to revision dates which apply to the POH litself These supplements contain a Log of Effective Pages which shou...

Page 9: ...nd revision level for each page within the POH As revisions to the POH occur the revision level on effected pages is updated When two pages display the same page number the page with the latest revisi...

Page 10: ...ration has been revised or is all new material The miniature hand will point to the figure number All revised pages will carry the revision number opposite the page number on the applicable page A lis...

Page 11: ...iginal 3 June 2004 Revision 3 19 July 2005 Revision 1 24 June 2004 Revision 4 22 December 2005 Revision 2 27 June 2005 Page Number Title Assignment Record i ii iii thru vii viii thru xilxii xiiilxiv 1...

Page 12: ...d Revised Revised Revised Revised 4 1 thru 4 48 Revised 4 49 thru 4 5114 52 Added 5 115 2thru 5 36 Original 6 116 2thru 6 24 Revised 6 2516 26 Added 7 1 thru 7 317 4 7 5 thru 7 11 7 12 7 13 thru 7 14...

Page 13: ...63 thru 7 66 7 67 thru 7 7517 76 8 1 thru 8 2 8 3 thru 8 5 8 6 8 7 thru 8 8 8 9 thru 8 12 8 13 8 14 8 15 thru 8 22 8 23 thru 8 24 Page Status Original Revised Criginal Revised Original Revised Revise...

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Page 15: ...CTION TABLE OF CONTENTS SECTION GENERAL 1 LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT AND BALAIVCEIEQUIPMENTLIST 6 AIRPLANE AND SYSTEMS DESCRIPTION 7 HANDLING SERVICE...

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Page 19: ...8 Specific Loadings 1 8 Symbols Abbreviations And Terminology 1 9 GeneralAirspeed Terminoiogy And Symbois 1 5 MeteorologicalTerminology 1 10 Engine Power Terminology 1 10 Airplane Performance And Flig...

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Page 21: ...CESSNA MODEL 182T NAV Ill SECTION 1 GENERAL THREE VIEW NORMAL GROUND ATTITUDE Figure 1 1 Sheet 1 of 2 Continued Next Page U S 1 3...

Page 22: ...standard strobe lights installed a Wheel base length is 66 1 2 a Propeller ground clearance is 10 7 8 a Wing area is 174 square feet a Minimum turning radius pivot point to outboard wing tip is 27 0...

Page 23: ...E DATA ENGINE Number of Engines 1 Engine Manufacturer Textron Lycoming Engine Model Number 10 540 AB1A5 Engine Type Normally aspirated direct drive air cooled horizontally opposed fuel injected six cy...

Page 24: ...el 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 Total...

Page 25: ...L L 6082 or SAE 196 Aviation Grade Straight Mineral Oil and continue to use until a total of 50 hours has accumulated or oil consumption has stabilized MIL L 22851 or SAE J1899 Aviation Grade Ashless...

Page 26: ...llowable 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 WEIGHTS Standard Empty...

Page 27: ...altitude and temperature Maneuvering Speed is the maximum speed at which full or abrupt control movements may be used Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a...

Page 28: ...Temperature Standard Temperature is 15 C at sea level pressure altitude and decreases by 2 C for each 1000 feet of altitude Pressure Altitude Pressure Altitude is the altitude read from an altimeter...

Page 29: ...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 amount...

Page 30: ...t 1000 is used in this handbook 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 i...

Page 31: ...ight 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 taxi and runup Maximum T...

Page 32: ...rs convert U S measurement supplied with the Pilot s Operating Handbook into metric and imperiai measurements The standard followed for measurement units shown is the National Institute of Standards T...

Page 33: ...31 752 36 287 40 823 45 359 2 kg 0 907 5 443 9 979 14 515 19 051 23 587 28 123 32 659 37 195 41 731 46 266 4 Ib 8 819 30 865 52 911 74 957 97 003 8 kg 3 629 8 165 12 701 17 237 21 772 1 1 1 1 I 26 303...

Page 34: ...SECTION 1 GENERAL CESSNA MODEL 182T NAV Ill WEIGHT CONVERSIONS Kilograms x 2 205 Pounds Pounds x 454 Kilograms POUNDS KILOGRAMS 0 0 Figure 1 2 Sheet 2 1 16 U S...

Page 35: ...173 86 206 69 239 50 272 31 305 12 337 93 2 feet 6 562 39 370 72 178 104 99 137 79 170 60 203 41 236 22 269 03 301 84 334 64 4 feet 13 123 45 932 78 740 111 55 144 36 177 16 209 97 242 78 275 59 308...

Page 36: ...SECTION 1 GENERAL CESSNA MODEL 182T NAV Ill LENGTH CONVERSIONS Meters x 3 281 Feet Feet x 305 Meters FEET METERS 15 10 20 5 0 Units x 10 100 etc Figure 1 3 Sheet 2 1 18 U S...

Page 37: ...132 08 157 48 182 88 208 28 233 68 259 08 4 in 1 575 5 512 9 449 13 386 17 323 21 260 25 197 29 134 33 071 37 008 40 945 3 cm 7 62 33 02 58 42 83 82 109 22 134 62 160 02 185 42 210 82 236 22 261 62 5...

Page 38: ...SECTION 1 GENERAL CESSNA MODEL 182T NAV Ill LENGTH CONVERSIONS Centimeters x 394 Inches Inches x 2 54 Centimeters INCHES CENTINIETERS 2 Units x TO 5 00 eic 0 0585T1028 Figure 1 3 Sheet 4 1 20 U S...

Page 39: ...Nautical Miles Nautical Miles x l 15 Statute Miles Nautical Miles xl E52 Kilorneters Kilometers x 54 Nautical Miles STATUTE NAUTICAL MILES MILES KILOMETERS 105 160 U S 1 21 65 60 55 50 45 40 35 30 25...

Page 40: ...T NAV III VOLUME CONVERSIONS Imperial Gallons x 4 546 Liters Liters x 22 Imperial Gallons LITERS INTO IMPERIAL GALLONS LITRES EN GALLONS IMPERIAL IMPERIAL GALLONS INTO LITERS GALLONS IMPERIAL EN LITRE...

Page 41: ...CESSNA MODEL 182T NAV Ill SECTION 1 GENERAL VOLUME CONVERSIONS Imperial Gallons X 4 4546 Liters Liters x 22 Imperial Gallons IMPERIAL 440 LITERS Units x 10 100 etc Figure 1 5 Sheet 2 U S 1 23...

Page 42: ...NAV Ill VOLUME CONVERSIONS Imperial Gallons x 1 2 U S Gallons U S Gallons x 833 Imperial Gallons U S Gallons x 3 785 Liters Liters x 264 U S Gallons IMPERIAL U S LITERS 100 120 Units x 10 100 etc Fig...

Page 43: ...CESSNA MODEL 182T NAV III TEMPERATURE CONVERSIONS Figure SECTION 1 GENERAL U S 1 25...

Page 44: ...SECTION 1 GENERAL CESSNA MODEL 182T NAV Ill PRESSURE CONVERSION Hectopascals Millibars to inches Mercury inHG Figure 1 7 1 26 U S...

Page 45: ...EIGHT CONVERSION 8 W 8 AVGAS Specific Gravity 72 Liters x 72 Kilograms Kilograms x 1 389 Liters Litersx 1 58 Pounds Pounds x 633 Liters LITERS POUNDS LITERS KILOGRAMS 1 140 125 90 130 AVGAS FUEL 1 120...

Page 46: ...SECTION 1 GENERAL CESSNA MODEL 182T NAV III QUICK CONVERSIONS R 31x0 0585T1031 R Figure 1 9 1 28 U S...

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Page 49: ...s 2 8 ManeuverLimits 2 9 Flight Load Factor Limits 2 9 Kinds Of Operations Limits 2 9 Kinds Of Operations Equipment List 2 101 Fuel Limitations 2 14 Flap Limitations 2 14 System Limitations 2 15 Aux A...

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Page 51: ...on 9 of this Pilot s Operating Handbook for amended operating limitations operating procedures performance data and other necessary information for airplanes I equipped with specific options The airsp...

Page 52: ...d 140 Do not exceed this speed except in smooth air and then only with caution VA Maneuvering Speed 3100 Pounds 2600 Pounds 2100 Pounds VFE 110 101 91 Maximum Flap Extended Speed Flaps LIP to 10 Flaps...

Page 53: ...R RANGE 140 175 Operations must be conducted with lcaution and onlv in smooth air 41 100 51 140 Full Flap Operating Range Lower limit is maximum weight VSO in landing configuration Upper limit is maxi...

Page 54: ...Oil Pressure Minimum 20 PSI Oil Pressure Maximum 115 PSI Fuel Grade Refer to Fuel Limitations Oil Grade Specification MIL L 6082 or SAE J1966 Aviation Grade Straight Mineral Oil or I MIL L 22851 or SA...

Page 55: ...g limit is lower end of red arc Figure 2 3 IFAA APPROVED 182TPHAUS 04 RED LINE MAX U S 2 7 RED ARC UPR 2400 to2700 RPM GREEN ARC NORMAL OPERATING RANGE 2000 to 2400 RPM 15 to 23 1ii iig I I I 200 to 5...

Page 56: ...elow 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 is 80 pounds CENTER OF...

Page 57: ...f Weight 3100 POUNDS Flaps Up 3 8g 1 529 Flaps Down 2 0g The design load factors are 150 of the above and in all cases the structure meets or exceeds design loads KINDS OF OPERA TIONS LIMITS The Cessn...

Page 58: ...ernator 3 24V Standby Battery 4 Main Ammeter 5 Standby Ammeter Accessible to pi dinf ight when using autopilot Refer to Note 1 Refer to Note 1 OF v F I 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 0 0 0 NOTE 0 0 1...

Page 59: ...Equipment andlor Function 1 7 I I 7 I COMMENT 3 Elevator Trim System 4 Elevator Trim Indicator 2 Alternate Induction Air Svstem I I INDICATINGIRECORDING SYSTEM Continued Next Page I FAA APPROVED 182T...

Page 60: ...acklighting 5 Switch and Circuit Breaker Panel Lighting 6 Airspeed lndicator Standby lnternal Lighting 7 Altimeter Standby lnternal Lighting 8 Non stabilized Magnetic Compass lnternal Lighting 9 Attit...

Page 61: ...ITOT STATIC SYSTEM 1 G l000 Airspeed Indicator 2 Standby Airspeed Indicator 3 G1000 Altimeter 4 Standby Altimeter 5 G l000 Vertical Speed lndicator 10 Non stabilized Magnetic 11 VHF Navigation Radio 1...

Page 62: ...attitude definition Takeoff and land with the fuel selector valve handle in the BOTH Iposition l a x i m u m slip or skid duration with one tank diy 30 seconds operation on either LEFT or RIGHTtank li...

Page 63: ...ortable 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 10A is not certified for...

Page 64: ...rrain avoidance is prohibited The Terrain Proximity map is intended only to enhance situational awareness It is the pilot s responsibility to I provide terrain clearance at all times Navigation using...

Page 65: ...of the pilot to see and maneuv to avoid traffic TERRAIN AWARENESS AND WARNING SYSTEM TAWS B if installed Use of the Terrain Awareness and Warning System TAWS B navigate to avoid terrain or obstacles i...

Page 66: ...ith when operating this airplane in the Normal Category Other operating limitations which must be complied with when operating this airplane in this category are contained in the Pilot s Operating Han...

Page 67: ...ALL FLIGHT ATTITUDES FUEL SELECTOR PUSH DOWN ROTATE LEFT RIGHT 43 5 GAL 43 5 GAL LEVEL FLIGHT ONLY LEVEL FLIGHT ONLY OFF 4 Near both fuel tank filler caps FUEL 100LU100 MIN GRADE AVIATION GASOLINE CA...

Page 68: ...range with White color code mechanical stop at FULL position 6 In baggage compartment 120 POUNDS MAXIMUM BAGGAGE FORWARD OF BAGGAGE DOOR LATCH AND 80 POUNDS MAXIMUM BAGGAGE AFT OF BAGGAGE DOOR LATCH M...

Page 69: ...TS D C THlS AIRCRAFT IS EQUIPPED WITH ALTERNATOR AND A NEGATIVE GROLIND SYSTEM OBSERVE PROPER POLARITY REVERSE POLARITY WILL DAMAGE ELECTRICAL COMPONENTS 12 On the upper right side of the aft cabin pa...

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Page 73: ...e Failure Immediately After Takeoff 3 6 Engine Failure During Flight Restart Procedures 3 6 FORCED LANDINGS 3 7 Emergency Landing Without Engine Power 3 7 Precautionary Landing With Engine Power 3 8 D...

Page 74: ...PM 3 17 LOW VOLTS Annunciator Comes On or Does Not Go Off at Higher RPM 3 17 AIR DATA SYSTEM FAILURE 3 19 Red X PFD Airspeed Indicator 3 19 Red X PFD Altitude Indicator 3 19 AlTITLIDE AND HEADING REFE...

Page 75: ...cent Through Clouds AHRS FAILED Recovery From Spiral Dive In The Clouds AHRS FAILED Inadvertent Flight Into Icing Conditions Static Source Blocked Spins Rough Engine Operation Or Loss Of Power Spark P...

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Page 77: ...s section should be considered and applied as necessary to correct the problem In any situation the most important task is continued control of the airplan and maneuver to execute a successful landing...

Page 78: ...tch OFF 6 STBY BATT Switch OFF 7 MASTER Switch ALT and BAT OFF ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF 1 Airspeed 75 KlAS Flaps UP 70 KlAS Flaps 10 FULL 2 Mixture Control IDLE CUTOFF pull full out 3...

Page 79: ...he indicated fuel flow FFLOW GPH immediately drops to zero a sign of failure of the engine driven fuel pump return the FUEL PUMP Switch to the ON position FORCED LANDINGS EMERGENCY LANDING WITHOUT ENG...

Page 80: ...L LOW 1 12 Mixture Control IDLE CUTOFF pull full out 13 MAGNETOS Switch OFF 14 Brakes APPLY HEAVILY DITCHING 1 Radio TRANSMIT MAYDAY on 121 5 MHz Give location I intentions and SQUAWK 7700 2 Heavy Obj...

Page 81: ...ine SHUTDOWN and inspect for damage I IF ENGINE FAILS TO START 2 Throttle Control FULL push full in 3 Mixture Control IDLE CUTOFF pull full out 4 MAGNETOS Switch START continue cranking 5 FUEL SELECTO...

Page 82: ...which will provide an incombustible mixture 1 7 Forced Landing EXECUTE Refer to EFAERGEr CY LANDING WITHOUT ENGINE POWER ELECTRICAL FlRE IN FLIGHT 1 STBY BATT Switch OFF 2 MASTER Switch ALT and BAT O...

Page 83: ...entstcabin AirIHeat CLOSED to avoid drafts 4 Fire Extinguisher ACTIVATE if available WARNING AFTER THE FlRE EXTINGUISHER HAS BEEN USED MAKE SURE THAT THE FlRE IS EXTlNGLllSHED BEFORE EXTERIOR AIR IS U...

Page 84: ...as necessary to hold manifold pressure Adjust mixture as necessary for any change in power settings Plan a landing at the nearest airport With an extremely rapid ice build up select a suitable off ai...

Page 85: ...on Alternate Static Source correction chart 5 Altitude Refer to Section 5 Figure 5 2 Altimeter Correction Alternate Static Source correction chart I EXCESSIVE FUEL VAPOR FUEL FLOW STABILIZATION PROCED...

Page 86: ...as possible with aileron control 4 Directional Control MAINTAIN Using brake on good wheel as required LANDING WlTH A FLAT NOSE TIRE 1 Approach NORMAL 2 Wing Flaps AS REQUIRED 120to 140 KlAS Flaps Up...

Page 87: ...ghts OFF g STROBE Lights OFF h CABllV PWR 12V OFF NOTE The Main Battery supplies electrical power to the Main and Essential Buses until M BUS VOLTS decreases below 20 volts When M BUS VOLTS falls belo...

Page 88: ...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 KAP 140 Autopilot GMA 1347 Audio Panel COMM 2 NAV 2 GTX...

Page 89: ...OR COMES ON OR DOES NOT GO OFF AT HIGHER RPM 1 MASTER Switch ALT Only OFF 2 Alternator Circuit Breaker ALT FIELD CHECK IN 3 MASTER Switch ALT and BAT ON 4 Low Voltage Annunciator LOW VOLTS CHECK OFF 5...

Page 90: ...st 30 minutes Select COM1 MIC and NAV1 on the audio 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...

Page 91: ...AIR DATA SYSTEM FAILURE RED X PFD AIRSPEED INDICATOR 1 ADCIAHRS Circuit Breakers CHECK IN ESS BUS and AVN BUS 1 If open reset close circuit breaker If circuit breaker opens again do not reset 2 Stand...

Page 92: ...nd AVhl BUS 1 If open reset close circuit breaker If circuit breaker opens again do not reset 2 Non Stabilized Magnetic Compass USE FOR HEADING INFORMATION DISPLAY COOLING ADVISORY PFD1 COOLING OR MFD...

Page 93: ...DURING FLIGHT OR THE GYRO FLAG IS SHOWN ON THE STANDBY ATTITUDE INDICATOR THE STANDBY ATTITUDE INDICATOR MUST NOT BE USED F O R ATTITUDE INFORMATION HlGH CARBON MONOXIDE ANNUNCIATOR if installed LEVEL...

Page 94: ...he check ist wi 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 95: ...CESSNA MODEL 182T NAV Ill SECTION 3 EMERGENCY PROCEDURES MAXIMUM GLIDE Ground Distance Nautical Miles Figure 3 1 U S 3 23...

Page 96: ...e baggage area and collect folded coats for protection of occupants face at touchdown Transmit Mayday messages on 121 5 MHz giving location and intentions and squawk 7700 Avoid a landing flare because...

Page 97: ...looding 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 engi...

Page 98: ...heading indicators the pilot must rely on the standby attitude indicator and non stabilized magnetic compass for attitude and heading information The autopilot will not operate in HDG mode without AHR...

Page 99: ...eep feet off rudder pedals Maintain altitude and 15 bank angle Continue the turn for 60 seconds then roll back to level flight 4 When the compass card becomes sufficiently stable check the accuracy of...

Page 100: ...d make minor corrections to hold an approximate course The autopilot may be engaged in ROL mode to keep the wings level and VS mode to control rate of descent Before descending into the clouds prepare...

Page 101: ...Keep feet off rudder pedals Maintain altitude and 15 bank angle Continue the turn for 60 seconds then roll back to level flight 4 When the compass card becomes sufficiently stable check the accuracy o...

Page 102: ...and make minor corrections to hold an approximate course The autopilot may be engaged in ROL mode to keep the wings level and VS mode to control rate of descent Before descending into the clouds prepa...

Page 103: ...heading 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 pr...

Page 104: ...ng recovery procedure should be used 1 RETARDTHROTTLE TO IDLE POSITION 2 PLACE AILERONS IN NEUTRAL POSITION 3 APPLY AND HOLD FULL RUDDER OPPOSITE TO THE DIRECTION OF ROTATION 4 JUST AFTER THE RUDDER R...

Page 105: ...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 fro...

Page 106: ...quired for 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...

Page 107: ...VE 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 charging during the ini...

Page 108: ...energize the alternator system 1 MASTER Switch ALT Only OFF 2 Alternator Circuit Breaker ALT FIELD CHECK IN 3 MASTER Switch ALT Only OIV If the problem was a minor ACU disturbance in the electrical s...

Page 109: ...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 of...

Page 110: ...symptoms mentioned above or the CO LVL HlGH warning annunciation comes on when using the cabin heater immediately turn off the cabin heater and preform the emergency items for HlGH CARBON MONOXIDE CO...

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Page 113: ...nspection Cabin Empennage Right Wing Trailing Edge Rightwing Nose Left Wing Leading Edge LeftWing Left Wing Trailing Edge Before Starting Engine Starting Engine With Battery Starting Engine With Exter...

Page 114: ...4 25 Starting Engine 4 27 Recommended Starter Duty Cycle 4 28 Leaning For Ground Operations 4 28 Taxiing 4 29 Before Takeoff 4 31 WarmUp 4 31 Magneto Check 4 31 Alternator Check 4 31 Elevator Trim 4...

Page 115: ...ORMAL PROCEDURES Continued Holding Procedure 1 urnsand Missed Approaches 4 43 Landing 4 47 Normal Landing 4 47 Short Field Landing 4 47 Crosswind Landing 4 48 Balked Landing 4 48 Cold Weather Operatio...

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Page 117: ...Short FieldTakeoff Flaps 20 Speed at 50 Feet 58 KlAS ENROUTE CLIMB FLAPS UP Normal Sea Level 85 95 KlAS Best Rate of Climb Sea Level 80 KlAS Best Rate of Climb 10 000 Feet 74 KlAS Best Angle of Climb...

Page 118: ...g 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 tai...

Page 119: ...R AS IF THE 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...

Page 120: ...LTS Annunciator CHECK Verify 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 pull fu...

Page 121: ...ail to the ground to move any additional contaminants to the sampling pints Take1 repeated samples from all fuel drain points until all1 contamination has been removed If contaminants are still presen...

Page 122: ...amination has been removed If contaminants are still present refer to WARNING below and do not fly the airplane I NOTE Collect all sampled fuel in a safe container Dispose of the sampled fuel so that...

Page 123: ...ired level 3 Fuel Filler Cap SECURE and VENT CLEAR 4 Fuel Tank Sump Quick Drain Valves DRAIN I Drain at least a cupful of fuel using sampler cup from each sump location to check for water sediment and...

Page 124: ...and general condition weather checks tread depth and wear etc LEFT WlNG Trailing Edge I 1 Aileron CHECK freedom of movement and security 2 Flap CHECK for security and condition BEFORE STARTING ENGINE...

Page 125: ...that all people and equipment are at a safe distance from the propeller MASTER Switch ALT and BAT OIV BEACON Light Switch ON NOTE If engine is warm omit priming procedure steps 13 thru 15 below I 13...

Page 126: ...lamp does not go off b ARM Verify that PFD comes on Engine Indication System CHECK PARAMETERS Verify no red X s through ENGlhlE page indicators BUS E Volts CHECK Verify 24 VOLTS minimum shown M BUS Vo...

Page 127: ...he FULL RlCH position and retard the throttle control promptly 22 Oil Pressure CHECK Verify oil pressure increases into the green arc range in 30 to 60 seconds 23 Power REDUCEto idle 24 External Power...

Page 128: ...ECK SECURE Cabin Doors CLOSED and LOCKED Flight Controls FREE and CORRECT Flight Instruments PFD CHECK no red X s Altimeters a PFD BARO SET b Standby Altimeter SET c KAP 140 Autopilot BARO SET G I000...

Page 129: ...o or 50 RPM differential between magnetos I b Propeller Control CYCLE from high to low RPM return1 to high RPM full in c VAC Indicator CHECK d Engine Indicators CHECK e Ammeters and Voltmeters CHECK A...

Page 130: ...V OPERATING MODES IF THE HSI NAVIGATION SOURCE IS CHANGED FROM GPS TO NAV1 AUTOMATICALLY OR MANUALLY USING THE CDI SOFTKEY OR MANUALLY FROM NAV2 TO GPS THE CHANGE WlLL INTERRUPT THE NAVIGATION SIGNAL...

Page 131: ...Mixture Control RICH Above 5000 feet pressure altitude lean for maximum RPM 5 Elevator Control LIFT NOSEWHEEL at 50 60 KlAS 6 Climb Airspeed 70 KIAS FLAPS 20 80 KlAS FLAPS UP 7 Wing Flaps RETRACT at s...

Page 132: ...KlAS at sea level to 74 KlAS at 10 000 feet 2 Throttle Control FULL push full in 3 Propeller Control 2400 RPM 4 Mixture Control FULL RICH or SET to Maximum Power Fuel Flow placard value for altitude...

Page 133: ...ns GlOOO and KAP 140 altitudes are set independently 7 CDI Softkey SELECT NAV source 8 FMSIGPS REVIEW and BRIEF OBSISUSP softkey operation for holding pattern procedure IFR CAUTION THE GI000 HSI SHOWS...

Page 134: ...THE REVERSION TO ROL MODE OPERATION IN ROL MODE THE AUTOPILOT WlLL ONLY KEEP THE WINGS LEVEL AND WlLL NOT CORRECT THE AIRPLANE HEADING OR COURSE SET THE HDG BUG TO THE CORRECT HEADING AND SELECT THE C...

Page 135: ...EWHEEL GENTLY 7 Braking MINIMUM REQUIRED I SHORT FIELD LANDING 1 Airspeed 70 80 KlAS Flaps UP 2 Wing Flaps FULL below 100 KIAS 3 Airspeed 60 KlAS until flare 4 Elevator and Rudder Trim Controls ADJUST...

Page 136: ...SET 1 2 Throttle Control IDLE pull full out 3 ElectricalEquipment OFF 4 AVIONICS Switch BUS 1 and BUS 2 OFF 1 5 Mixture Control IDLE CUTOFF pull full out 6 MAGNETOSSwitch OFF 7 MASTER Switch ALT and...

Page 137: ...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 maintenance...

Page 138: ...y areas or tied down adjacent to taxiing airplanes special attention should be paid to control surface stops hinges and brackets to detect the presence of potential wind damage If the airplane has bee...

Page 139: ...ot engine is facilitated by advancing the mixture control promptly to 113 open when the engine starts and then smoothly to full rich as power develops I If the engine does not continue to run set the...

Page 140: ...l down operate the starter motor again three cycles of 10 seconds followed by 20 seconds of cool down If the engine still does not start try to find the cause ILEANING FOR GROUND OPERATIONS IFor all g...

Page 141: ...l or cinders should be done at low engine speed to avoid abrasion and stone damage to the propeller tips 1 NOTE The LOW VOLTS annunciator may come on when the engine is operated at low RPM with a high...

Page 142: ...DIAGRAM WRH WINGAND NEUTRAL E L E V A T O R 4 k CODE WIND DIRECTION I NOTE Strong quartering tail winds require caution Avoid sudden bursts of the throttle and sharp braking when the airplane is in t...

Page 143: ...magneto or be greater than 50 RPM differential between magnetos If there is a doubt concerning operation of the ignition system RPM checks at higher engine speeds will usually confirm whether a defici...

Page 144: ...static run up before another takeoff is attempted The engine should run smoothly and turn approximately 2350 2400 RPM Full throttle run ups over loose gravel are especially harmful to propeller tips W...

Page 145: ...attitude If no obstacles are ahead the airplane should be leveled off immediately to accelerate to a higher climb speed When departing a soft field with an aft C G loading the elevator trim control s...

Page 146: ...y to clear mountains or reach favorable winds at higher altitudes the best rate of climb speed should be used with maximum power This speed is 80 KlAS at sea level decreasing to 74 KlAS at 10 000 feet...

Page 147: ...with speed fairings installed Power altitude and winds determine the time and fuel needed to complete any flight I The Cruise Performance Table Figure 4 3 shows the true airspeed and nautical miles p...

Page 148: ...the green arc range for a given percent power that will provide smooth engine operation The cowl flaps should be opened if necessary to maintain the cylinder head temperature at approximately two thir...

Page 149: ...er all cylinder EGTs should be within approximately 50 F of each other during normal operations An EGT difference greater than 50 F between cylinders indicates that fuel injection system maintenance i...

Page 150: ...f APEAK O F value is negative the mixture can be on the lean side of peak Enrichen the mixture by slowly turning the mixture control clockwise and monitor both fuel flow and EGTs until the leanest cyl...

Page 151: ...h of Peak EGT Peak EGT 125 F RICH Under some conditions engine roughness may occur while operating at peak EGT In this case operate at the Recommended Lean mixture NOTE Any change in altitude or power...

Page 152: ...st After the BEFORE TAKEOFF checklist is complete re lean the mixture as described above until ready for TAKEOFF checklist 2 Lean the mixture for placarded fuel flows during maximum continuous power c...

Page 153: ...ne 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 OPERA...

Page 154: ...d the amplified procedures sections Section 4 Take note of the hot weather operational notes and procedures in both the checklist and the amplified procedures sections Section 7 Take note of the altit...

Page 155: ...r either maneuver Holding pattern operations whether in the enroute or the terminal environment require temporary suspension of flight plan execution on reaching the holding waypoint If the holding pa...

Page 156: ...pilot manually or by setting the KAP 140 Autopilot to HDG mode and then setting the HDG bug on the PFD to command the Autopilot to turn to each new heading The KAP 140 Autopilot may be set to APR mode...

Page 157: ...approaches are managed by the GI000 FMSIGPS to provide course guidance and waypoint sequencing through the approach procedure For ILS approaches the GI000 FMSIGPS provides course guidance for the KAP...

Page 158: ...G AND SELECT THE CORRECT NAVIGATION SOURCE ON THE HSI USING THE CDI SOFTKEY BEFORE ENGAGING THE AUTOPILOT IN ANY OTHER OPERATING MODE Other VHF NAV based Instrument Approach Procedures VOR LOC LOC BC...

Page 159: ...ewheel 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 SHORT...

Page 160: ...es the best control After touchdown hold a straight Icourse with the steerable nosewheel with aileron deflection as applicable and occasional braking if necessary The maximum allowable crosswind veloc...

Page 161: ...ssure satisfactory flight performance and handling Also control surfaces must be free of any internal accumulations of ice or snow If snow or slush covers the takeoff surface allowance must be made fo...

Page 162: ...re the same as the normal I starting procedures However to conserve battery power the beacon light can be left off until the engine is started Use caution to prevent inadvertent forward movement of th...

Page 163: ...inimize 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 make eve...

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Page 167: ...Source 5 9 Airspeed Calibration Alternate Static Source 5 10 Altimeter Correction 5 11 Temperature Conversion Chart 5 12 Stallspeeds 5 13 CrosswindComponent 5 14 Short FieldTakeoff Distance 3100 Poun...

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Page 169: ...dition and air turbulence may account for variations of 10O 0 or more in range and endurance Therefore it is important to utilize all available information to estimate the fuel required for the partic...

Page 170: ...t the next higher value of weight altitude and temperature For example in this particular sample problem the takeoff distance information presented for a weight of 3100 pounds pressure altitude of 200...

Page 171: ...ormance characteristics presented in Figure 5 9 the range profile chart presented in Figure 5 10 and the endurance profile chart presented in Figure5 11 The relationship between power and range is ill...

Page 172: ...ct of temperature may be made as noted on the climb chart The approximate effect of a non standard temperature is to increase the time fuel and distance by for each 10 C above standard temperature due...

Page 173: ...for cruise is 3 6 hours X 10 7 gallons hour 38 5 Gallons A 45 minute reserve requires 45 60 X 10 7 gallons 1hour 8 0 Gallons The total estimated fuel required is as follows Engine start taxi and takeo...

Page 174: ...0 C are as follows Ground roll 540 Feet Total distance to clear a 50 foot obstacle 1280 Feet A correction for the effect of wind may be made based on Note 2 of the landing chart using the same procedu...

Page 175: ...level flight or maximum power descent Figure 5 1 Sheet 1 of 2 FLAPS UP KlAS KCAS FLAPS 20 KlAS KCAS FLAPS FULL KlAS KCAS U S 5 9 55 60 70 80 90 100 110 120 130 140 150 160 61 65 73 82 90 99 108 117 1...

Page 176: ...r on maximum CONDITIONS Power required for level flight or maximum power descent Figure 5 1 Sheet 2 FLAPS UP KlAS ALT KlAS FLAPS 20 KlAS ALT KlAS FLAPS FULL KlAS ALT KlAS 5 10 U S 55 60 70 80 90 100 1...

Page 177: ...nfiguration are less than 50 feet CONDITION FLAPS UP S L 2000 FT 4000 FT 6000 FT 8000 FT 10 000 FT 12 000 FT 14 000 FT Figure 5 2 182TPHAUS 00 CONDITION FLAPS FULL S L 2000 FT 4000 FT 6000 FT 8000 FT...

Page 178: ...SECTION 5 PERFORMANCE CESSNA MODEL 182T NAV Ill TEMPERATURE CONVERSION CHART 5 12 U S 20 0 20 40 DEGREES CELSIUS Figure 5 3...

Page 179: ...K FLAP SETUNG UP 20 FULL 1 Altitude loss during a stall recovery may be as much as 250 feet 2 KlAS values are approximate Figure 5 4 0 ANGLE OF BANK U S 5 13 KlAS 50 43 40 KCAS 54 50 49 30 0 KlAS 54 4...

Page 180: ...SECTION 5 PERFORMANCE CESSNA MODEL 182T NAV III CROSSWIND COMPONENT 0 5 10 15 20 25 30 35 CROSSWIND COMPONENT KNOTS NOTE Maximum demonstrated crosswind velocity is 15 knots not a limitation Figure 5 5...

Page 181: ...crease distances by 10 for each 2 knots 4 For operation on dry grass runway increase distances by 15 of the ground roll figure Figure 5 6 Sheet 1 of 3 U S 5 15 0 C Grnd ROII Ft 715 775 850 925 1015 11...

Page 182: ...ase distances by 10 for each 2 knots 4 For operation on dry grass runway increase distances by 15 of the ground roll figure Figure 5 6 Sheet 2 5 16 U S O C Grnd Roll Ft 520 565 615 675 735 805 880 965...

Page 183: ...peration on dry grass runway increase distances by 15 of the ground roll figure 1 Press Feet S L 1000 2000 3000 4000 5000 6000 7000 8000 Figure 5 6 Sheet 3 U S 5 17 0 C Grnd ROII Ft 365 395 430 470 51...

Page 184: ...aximum Power Fuel Flow placard Cowl Flaps Open Figure 5 7 Press Alt Feet S L 2000 4000 6000 8000 10 000 12 000 14 000 5 18 U S Climb Speed KlAS 80 79 78 77 75 74 73 72 Rate of climb FPM 20 C 1055 945...

Page 185: ...axi and takeoff al lowance 2 Mixture leaned to Maximum Power Fuel Flow placard value for smooth engine operation and increased power 3 Increase time fuel and distance by 10 for each 10 C above standar...

Page 186: ...ngine start taxi and takeoff al lowance 2 Mixture leaned to Maximum Power Fuel Flow placard value for smooth engine operation and increased power 3 Increase time fuel and distance by 10 for each 10 C...

Page 187: ...NCE CRUISE PERFORMANCE PRESSUREALTITUDE SEA LEVEL CONDITIONS 1 Maximum cruise power is 80 MCP Those powers above that value in the table are for interpolationpurposes only 2 For best economy operate a...

Page 188: ...6 61 57 53 78 74 70 66 62 58 54 51 STANDARD TEMPERATURE 5 C KTAS 133 131 129 126 123 119 115 111 131 129 126 123 120 116 113 108 3 BcP 79 75 71 67 63 59 55 51 75 71 67 64 60 56 53 49 20 C ABOVE STANDA...

Page 189: ...PRESSURE ALTITUDE 2000 FEET SECTION 5 PERFORMANCE 1 Maximum cruise power is 8O0 0 MCP Those powers above that value in the table are for interpolation purposes only 2 For best economy operate at peak...

Page 190: ...6 25 24 23 22 21 20 75 71 67 63 59 55 52 71 67 64 60 56 53 49 20 C BELOW STANDARD TEMP 9 C STANDARD TEMPERATURE 11 C KTAS 138 134 131 124 119 115 134 131 128 124 120 116 111 BEP 80 76 72 68 64 59 55 7...

Page 191: ...62 82 78 73 69 65 60 STANDARD TEMPERATURE 13 C KTAS 140 138 134 130 126 138 135 132 128 124 139 136 133 130 126 122 BEp 81 76 72 67 62 83 78 74 69 65 60 79 75 71 66 62 58 20 C ABOVE STANDARD TEMP GPH...

Page 192: ...21 20 25 24 23 22 21 20 20 C BELOW STANDARD TEMP 13 C tp 78 74 70 66 61 57 74 70 66 62 58 54 STANDARD TEMPERATURE 7 C KTAS 137 134 131 127 123 119 134 131 127 124 120 116 BakP 75 71 67 63 59 55 71 68...

Page 193: ...ITUDE 6000 FEET CONDITIONS 3100 Pounds SECTION 5 PERFORMANCE NOTE 1 Maximum cruise power is 80 MCP Those powers above that value in the table are for interpolationpurposes only 2 For best economy oper...

Page 194: ...III CRUISE PERFORMANCE PRESSLIRE ALTITUDE 8000 FEET 1 Maximum cruise power is 80 MCP Those powers above that value in the table are for interpolation purposesonly 2 For best economy operate at peak E...

Page 195: ...UISE PERFORMANCE PRESSURE ALTITUDE 10 000 FEET CONDITIONS 1 Maximum cruise power is 8O0lOMCP Those powers above that value in the table are for interpolation purposesonly 2 For best economy operate at...

Page 196: ...RE ALTITUDE 12 000 FEET CONDITIONS 3100 Pounds Recommended Lean Mixture Cowl Flaps Closed NOTE 1 Maximum cruise power is 80 MCP Those powers above that value in the table are for interpolationpurposes...

Page 197: ...se powers above that value in the table are for interpolation purposes only 2 For best economy operate at peak EGT Figure 5 9 Sheet 11 MP 16 15 16 16 16 U S 5 31 20 C BELOW STANDARDTEMP 33 C BEP 56 50...

Page 198: ...then Maximum Performance Climb with Placard Mixture Recommended Lean Mixture for Cruise StandardTemperature Zero Wind NOTE This chart allows for the fuel used for engine start taxi takeoff and climb c...

Page 199: ...e Climb with Placard Mixture Recommended Lean Mixture for Cruise Standard Temperature Zero Wind 7no 750 800 850 900 950 1000 RANGE NAUTICALMILES NOTE This chart allows for the fuel used for engine sta...

Page 200: ...Placard Mixture RecommendedLean Mixture for Cruise Standard Temperature Zero Wind 140100 1 000 10000 t 3000 UI 0 z 5 soon a 4000 2000 0 3 4 5 6 ENDURANCE HOURS NOTE This chart allows for the fuel use...

Page 201: ...Lean Mixture for Cruise Standard Temperature Zero Wind This chart allows for the fuel used for engine start taxi takeoff and climb cruise at the designated power and the time during a normal climb up...

Page 202: ...flaps up is necessary increase the approach speed by 10 KlAS and allow for 40 longer distances Figure 5 12 5 36 U S 0 C Grnd Roll Ft 560 580 600 625 650 670 700 725 755 Total Ft To Clear 50 Ft Obst 1...

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Page 205: ...Weighing Procedures 6 3r 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 Arrangements...

Page 206: ......

Page 207: ...installed equipment for this airplane as delivered from the factory can be found in the plastic envelope in the back of this handbook I WARNING IT IS THE RESPONSIBILITY OF THE PILOT TO MAKE SURE THE A...

Page 208: ...rs to a plumb bob dropped from the firewall b Obtain measurement B by measuring horizontally and parallel to the airplane centerline from center of nose wheel axle left side to a plumb bob dropped fro...

Page 209: ...RM Referencedatum firewall front face lower portion screws I I I I I I I I I I 50 0 50 100 150 200 250 300 350 400 Fuselage Station FS Inches NOTE It is the responsibility of the pilot to make sure th...

Page 210: ...ailcon at FS 139 65 and 171 65 Measuring A and B operating handbook instructions to assist in locating CG with airplane weighed on llanding gear I Air lane as Weighed Table Nose Wheel I Airplane total...

Page 211: ...or equipment affecting weight and balance Page number Airplane model Serial number Description of article or modification As delivered Date Weight change Item Running basic empty weight In Added WT Ib...

Page 212: ...t be divided by 1000 and this value used as the moment11000 on the loading problem Use the Loading Graph to determine the moment 1000 for each additional item to be carried then list these on the load...

Page 213: ...the baggage door defines the weight limitations in the baggage areas When baggage area A is utilized for baggage only the four forward eyebolts should be used When only baggage area B is used the eye...

Page 214: ...lts 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 when items w...

Page 215: ...ESCRIPTION providing that flight time is allowed for fuel burn off to a maximum of 2950 pounds before landing The maximum allowable combined weight capacity for baggage in areas A B and C is 200 pound...

Page 216: ...MODEL 182T NAV Ill SAMPLE LOADING PROBLEM When several loading configurations are representative of your operations it may be useful to fill out one or more of the above columns so that specific load...

Page 217: ...0 100 150200250300 350400 Load IVlomenff1000 Pounds Inches NOTE Line representing adjustable seats shows the pilot and front seat passenger center of gravity on adjustable seats positioned for an aver...

Page 218: ...table seats positioned for average occupant Numbers in parentheses indicate forward and aft limits of occupant center of gravity range Arms measured to the center of the areas shown NOTE I The usable...

Page 219: ...NSIONS Egar wall of cabin Firewall 68 75 65 25 65 30 Cabin Width Measurements Tiedown rings Rear doorpost Forward doorpost CODE Cabin floor Lower window line 0785T1020 NOTE Maximum allowable floor loa...

Page 220: ...LIST MODEL 182T NAV Ill CENTER OF GRAVITY MOMENT ENVELOPE Loaded Airplane Moment11000 Kilogram Millimeters NOTE If takeoff weight is more than maximum landing weight allow flight time for fuel burn of...

Page 221: ...ANCEIEQUIPMENTLIST nlilill CENTER OF GRAVITY LIMITS Airplanes C G Location Inches Aft of Datum FS 0 0 If takeoff weight is more than maximum landing weight allow flight time for fuel burn off to 2950...

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Page 223: ...r FAA certification 14 CFR Part 23 or Part 91 S Standard equipment items O Optional equipment items replacing required or standard items A Optional equipment items which are in addition to required or...

Page 224: ...I COMPUTER GIA 63 INTEGRATED AVIONICS UNIT CI 2480 200 VHF COMMIGPS ANTENNA NAV COM GPS 2 COMPUTER GIA 63 INTEGRATED AVIONICS UNIT CI 2480 400 VHF COMMIGPSIXM ANTENNA 24 ELECTRICALPOWER ALTERNATOR 28...

Page 225: ...OULDER HARNESS INERTIA REEL MANUAL ADJUSTABLE REAR SEAT SUN VISOR SET OF 2 BAGGAGE RETAINING NET CARGOTIEDOWN RINGS SET OF 10 PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL STOWED...

Page 226: ...NIT GTP 59 OUTSIDE AIR TEMPERATURE OAT PROBE 32 LANDING GEAR WHEEL BRAKE AND TIRE 6 00 X 6 MAIN 2 WHEEL ASSY CLEVELAND 40 75B EACH BRAKE ASSY CLEVELAND 30 52 EACH TIRE 6 PLY EACH TUBE EACH WHEEL AND T...

Page 227: ...OMPASS MAGNETIC TRANSPONDER GTX 33 TRANSPONDER CI 105 16TRANSPONDER ANTENNA PFD DISPLAY GDU 1040 DISPLAY MFD DISPLAY GDU 1040 DISPLAY ATTITUDE HEADING REFERENCE SENSOR AHRS GRS 77 AHRS GMU 44 MAGNETOM...

Page 228: ...WINDOW HINGED RIGHT SlDE NET CHANGE WINDOW HINGED LEFT SlDE NET CHANGE 61 PROPELLER PROPELLER ASSEMBLY 3 BLADE OIL FILLED HUB P4317296 01 MCCAULEY B3D36C431 8OVSA l SPINNER 3 BLADE D 7261 2 GOVERNOR P...

Page 229: ...ENGINE INDICATING ENGINE TACHOMETER SENSOR 1A3C 1 CYLINDER HEAD THERMOCOUPLES ALL CYLINDERS 32DKWUE006F0126 EXHAUST THERMOCOUPLES ALL CYLINDERS 86317 78 EXHAUST EXHAUST SYSTEM LEFT EXHAUST SYSTEM RIG...

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Page 233: ...nter Panel Layout RightPanelLayout Center Pedestal Layout Flight Instruments Attitude Indicator Airspeed Indicator Altimeter Horizontal Situation Indicator Vertical Speed Indicator Ground Control Wing...

Page 234: ...ibution Fuel Indicating System Auxiliary Fuel Pump Operation Fuel Return System Fuelventing Fuel Selector Valve Fuel Drain Valves Brakesystem Electrical System G1000Annunciator Panel Master Switch 1 S...

Page 235: ...Attitude Heading Reference System AHRS and GMU 44 Magnetometer 7 67 GDC 74A Air Data Computer 7 67 GEA 71 Engine Monitor 7 67 GTX 33 Transponder 7 67 GDL 69A XM Weather and Radio Data Link 7 68 Bendi...

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Page 237: ...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 a...

Page 238: ...s 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 edg...

Page 239: ...n the control pedestal This is accomplished by rotating the horizontally mounted trim control wheel either left or right to the desired trim position Rotating the trim wheel to the right will trim nos...

Page 240: ...SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MGDEi t82T NkV iii FLIGHTCONTROLSAND TRIM SYSTEMS AILERON CONTROL SYSTEM 0 7 8 U S Figure 7 1 Sheet 1 of 2...

Page 241: ...CESSNA SECTION 7 MODEL 182T NAV Ill AIRPLANE AhlD SYSTEMS DESCRIPTION FLIGHTCONTROLSAND TRIM SYSTEMS ELEVATOR CONTROL SYSTEM ELEVATOR TRIM CONTROL SYSTEM 07851018 07851024 Figure 7 1 Sheet 2 U S 7 9...

Page 242: ...t reversionary operation MFD failure or when the DISPLAY BACKUP switch is selected the Engine Indication System EIS is shown on the PFD Refer to the Garmin G1OOOTM Cockpit Reference Guide for specific...

Page 243: ...e lower face of the GMA 1347 Refer to the GMA 1347 Pilot s Guide for operating information The GDU 1040 Multifunction Display MFD is found on the upper center panel to the right of the GMA 1347 The MF...

Page 244: ...jacent to the throttle control Refer to the PITOT STATIC SYSTEM AND INSTRUMENTS description in this section for operating information The wing flap control and indicator is found at the lower right si...

Page 245: ...CESSNA SECTION 7 MODEL 182T NAV Ill AIRPLANE AND SYSTEMS DESCRIPTION INSTRUMENT PANEL H3N1 U7l4P1 40 Figure 7 2 Sheet 1 of 2 U S 7 13...

Page 246: ...040 Multi Function Display Standby Altimeter ELT Remote Switch Annunciator Flight Hour Recorder Microphone Switch Defrost Control Cabin Heat Control Cabin Air Control Wing Flap Switch Lever And Positi...

Page 247: ...have functions defined by software softkeys A softkey may perform various operations or functions at various times based on software definition Softkeys are found along the lower bezel of the GDU 104...

Page 248: ...d along the right side of the attitude indicator on the GDU 1040 Primary Flight Display The altitude indication data is provided by the GDC 74A Air Data Computer unit The local barometric pressure is...

Page 249: ...f turn based on the length of the magenta turn vector The cyan HSI heading reference pointer bug is set using the HDG knob on the GDU 1040 display The selected heading is shown digitally in a window a...

Page 250: ...ON IN ROL MODE THE AUTOPILOT WlLL ONLY KEEP THE WINGS LEVEL AND WlLL NOT CORRECT THE AIRPLANE HEADING OR COURSE SET THE HDG BUG TO THE CORRECT HEADING AND SELECT THE CORRECT NAVIGATION SOURCE ON THE H...

Page 251: ...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 nos...

Page 252: ...osition The switch 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 flap lever is moved to the right to clear mechanica...

Page 253: ...passenger seats to the aft cabin bulkhead Access to the baggage compartment is gained through a lockable baggage door on the left side of the airplane or from within the airplane cabin A baggage net...

Page 254: ...cated beneath each seat bottom and provide adjustment for each seat back To adjust the seat back raise the lever position the seat back to the desired angle release the lever and check that the back i...

Page 255: ...of the lap belt can be verified by ensuring that the belts are allowed to retract into the retractors and the lap belt is snug and low on the waist as worn normally during flight No more than one addi...

Page 256: ...SECTION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 182T NAV Ill STANDARD INTEGRATED SEATBELT1 SHOULDER HARNESS WITH INERTIA REEL Figure 7 4 7 24 U S JSTABLE LIFT TO RELEASE LATCH...

Page 257: ...forward movement and contact with objects during sudden deceleration Also the pilot must have the freedom to reach all controls easily Disconnecting the manually adjustable seat beltlshoulder harness...

Page 258: ...cidental opening of a cabin door in flight due to improper closing does not constitute a need to land the airplane The best procedure is to set up the airplane in a trimmed condition at approximately...

Page 259: ...ice should be removed prior to starting the engine ENGINE The airplane is powered by a horizontally opposed six cylinder overhead valve air cooled fuel injected engine with a wet sump lubrication syst...

Page 260: ...l operation If either the MFD or PFD fails during flight the EIS is shown on the remaining display The EIS consists of three pages that are selected using the ENGINE softkey The ENGINE page provides i...

Page 261: ...cator The tachome ter indicator uses a circular scale with moving pointer and a digital value The pointer moves through a range from 0 to 2700 RPM The numerical RPM value is displayed in increments of...

Page 262: ...l signal to the GEA 71 for display on the EIS A red X through the indicator means the indicating system is inoperative OIL PRESSURE Engine oil pressure is shown on the ENGINE page by the OIL PRES hori...

Page 263: ...ature and engine speed at or close to idle oil pressure below the green arc but above the lower red arc is acceptable In cold weather the oil pressure will initially be high close to the upper red arc...

Page 264: ...filter adapter and provides a signal to the GEA 71 that is processed and shown as oil pressure on the EIS A red X through the indicator shows that the indicating system is inoperative CYLINDER HEAD T...

Page 265: ...nge is from 1100 F to 1500 F with graduations every 50 F The white pointer indicates relative exhaust gas temperature with the number of the hottest cylinder displayed inside the pointer If a cylinder...

Page 266: ...ef valve at the rear of the right oil gallery and a thermostatically controlled remote oil cooler Oil from the remote cooler is then circulated to the left oil gallery and propeller governor The engin...

Page 267: ...ated to the 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 automatical...

Page 268: ...unit fuel manifold fuel flow indicator and air bleedtype injector nozzles Fuel is delivered by the engine driven fuel pump to the fuellair control unit The fuellair control unit correctly proportions...

Page 269: ...cruise flight cowl flaps should be closed unless hot day conditions require them to be adjusted to keep the cylinder head temperature at approximately two thirds of the normal operating range green a...

Page 270: ...nob and reposition the control as desired FUEL SYSTEM The airplane fuel system refer to Figure 7 6 consists of two vented integral fuel tanks one tank in each wing two fuel manifolds one in each aft d...

Page 271: ...minimum due to the design of the fuel systemr Ho Fv T with l i 4 tank or less prolonged uncoordinated flight such as slips or skids can uncover the fuel tank outlets causing fuel starvation and engine...

Page 272: ...y two float type fuel quantity sensors one in each tank and is displayed on the Engine Indicating System EIS pages The indicators are marked in gallons of fuel An empty tank is displayed on the fuel q...

Page 273: ...detects any one of these conditions the affected fuel indicator will display a red Xu A red X through the top part of the indicator indicates a sensor failure in the left tank A red X through the bott...

Page 274: ...TRANSMITTER RIGHT DRAIN VALVE MANIFOLD SELECTOR VALVE JRN rl ENGINE DRAIN VALVE AUXILIARY FUEL STRAINER FUEL PUMP SWITCH DRAIN VALVE 7 7FUEL RETURN I FUEL SLIPPLY MECHANICAL LINKAGE 1 ELECTRICAL1 CONN...

Page 275: ...cessary to operate the auxiliary fuel pump during normal takeoff and landing since gravity and the engine driven pump will supply adequate fuel flow In the event of failure of the engine driven fuel p...

Page 276: ...he fuel selector is a four position selector valve labeled BOTH RIGHT LEFT and OFF The selector handle must be pushed down before it can be rotated from RIGHT or LEFT to OFF The top portion of the val...

Page 277: ...k outlets causing fuel starvation and engine stoppage Therefore with low fuel reserves do not allow the airplane to remain in uncoordinated flight for periods in excess of one minute FUEL DRAIN VALVES...

Page 278: ...ng brakes soft or spongy pedals and excessive travel and weak braking action If any of these symptoms appear the brake system is in need of immediate attention If during taxi or landing roll braking a...

Page 279: ...is also connected to an avionics bus through a circuit breaker and the AVIONICS BUS 1 and BUS 2 switches Each avionics bus is powered when the MASTER switch and the corresponding AVIONICS switch is in...

Page 280: ...ION 7 CESSNA AIRPLANE AND SYSTEMS DESCRIPTION MODEL 182T NAV Ill ELECTRICAL SYSTEM Continued 81524 r Power To LOW VOLT Battery Circuit Breaker External Power 077011519 I t Figure 7 7 Sheet 1 of 3 7 48...

Page 281: ...easureequipment DME f Installed To feeder B clrcult breakers sheet 1 To VHF commun cat on L 1 bus voltmeter hourmeter starter relay x 1 k g To standby indicator lights stdby battery L j 1 and main bus...

Page 282: ...LECTRICALSYSTEM Continued 83766 Standby Batte Standby Battery Controller PCB STBY B A T Switch Test Overheatj Switch w STDBY B A T Test Load I i Test Test LED Light green Annunciation To Standby Batte...

Page 283: ...ls the main battery electrical power to the airplane The ALT side of the switch controls the alternator system In normal operation both sides of the switch ALT and BAT are ON simultaneously however th...

Page 284: ...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 fail...

Page 285: ...pplying all the power that is required by the aircraft Indicated voltages between 24 5 and 28 volts may occur during low engine RPM conditions Refer to note under LOW VOLTAGE ANNLINCIATION Current AMP...

Page 286: ...Under these conditions increase RPM or decrease electrical loads to reduce demand on the battery In the event an overvoltage condition or other alternator fault occurs the ACU will automatically open...

Page 287: ...breaker as a switch is discouraged since the practice will decrease the life of the circuit breaker All circuit breakers on ELECTRICAL BUS 1 ELECTRICAL BUS 2 and X FEED BUS are non pullable tyPe The...

Page 288: ...be made whenever the engine has been started using external power after disconnecting the external power source 1 MASTER Switch ALT and BAT OFF 2 TAXI and LANDING Light Switches ON 3 Engine RPM REDUCE...

Page 289: ...he 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 together in the LIGHTS section of the switch pa...

Page 290: ...lood lighting is accomplished using two dimmable lights in the front crew area and one dome light in the rear passenger area These lights are contained in the overhead console and are controlled by di...

Page 291: ...ing level control to the AVIONICS dimmer control This is the recommended use of avionics lighting for night and low lighting conditions to allow the pilot control of the avionics illumination levels a...

Page 292: ...gure 7 8 Both controls are the double button locking type and permit intermediate settings For cabin ventilation pull the CABlN AIR knob out To raise the air temperature pull the CABlN HT knob out app...

Page 293: ...CESSNA SECTION 7 MODEL 182T NAV Ill AIRPLANE AND SYSTEMS DESCRIPTION CABIN HEATING VENTILATING AND DEFROSTING SYSTEM I I 0785T1014 I C Figure 7 8 U S 7 61...

Page 294: ...ated pitot system uses an electrical heating element built in the body of the pitot head The PlTOT HEAT control switch is found on the switch panel below the lower LH corner of the PFD The PlTOT HEAT...

Page 295: ...ll appear 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 The Attitude Indicator incl...

Page 296: ...T NAV Ill VACUUM SYSTEM OVERBOARD I 1 VENT LINE JE N VACUUM SYSTEM AIR FILTER 7 1 GDU 1040 VACUUM PRESS TRANSDUCER CONTROL1 1 DISPLAY UNIT ATTITUDE A ENGINE AND AIRFRAME UNlT EISISYSTEM PAGE ENGINE Ih...

Page 297: ...eset circuit breaker labeled STALL WARIV on the left side of the switch and control panel protects the stall warning system The vane in the wing senses the change in airflow over the wing and operates...

Page 298: ...as well as displaying warninglstatus annunciationsof aircraft systems The MFD displays a large scalable moving map that corresponds to the airplane s current location Data from other components of th...

Page 299: ...left wing panel It interfaces with the AHRS to provide heading information GDC 74A Air Data Computer The Air Data Computer ADC compiles information from the aircraft s pitotlstatic system The unit is...

Page 300: ...on WARNING WHEN THE KAP 140 AUTOPILOT IS ENGAGED IN NAV APR OR REV OPERATING MODES IF THE HSI NAVIGATION SOURCE IS CHANGED FROM GPS TO NAV1 AUTOMATICALLY OR MANUALLY USING THE CDI SOFTKEY OR MANUALLY...

Page 301: ...s blow air directly onto the heat sinks located on the forward sides of the PFD and MFD Power is provided to these fans when the MASTER BAT switch and the AVlOlVlCS BUS 1 and BUS 2 switch are all ON N...

Page 302: ...by a coaxial cable I The Honeywell KTA 870 TAS if installed has two antennas A directional antenna is mounted on top of the cabin fwd of the COM antennas and an omni antenna is mounted on the bottom o...

Page 303: ...handheld microphone always hold it as closely as possible to the lips then press the transmit switch and speak directly into it Avoid covering the opening on back side of microphone for optimum noise...

Page 304: ...the event of a high pilot workload andlor heavy traffic it is wise to disable the entertainment audio to eliminate a source of distraction for the flight crew NOTE I Passenger briefing should specify...

Page 305: ...uirements prior to plugging any device into the 12 volt Cabin Power System connector T h i s system is limited to a maximum of 10 amps or if equipped with two connectors 10 amps total Use caution with...

Page 306: ...rodifluoromethane fire extinguisher is installed in a holder on the floorboard between the front seats to be accessible in case of fire The extinguisher is classified 5B C by Underwriters Laboratories...

Page 307: ...powered by the airplanes DC electrical system and integrated in the Garmin GlOOO system with a warning annunciation and alert messages displayed on the PFD I When the CO detection system senses a CO...

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Page 311: ...rplane Owners Publications Airplane File Airplane Inspection Periods FAA Required Inspections Cessna lnspection Programs Cessna Customer Care Program Pilot Conducted Preventive Maintenance Alterations...

Page 312: ...ntinued Page Fuel 8 15 Approved Fuel Grades And Colors 8 15 Fuel Capacity 8 15 Fuel Additives 8 16 Fuel Contamination 8 20 LandingGear 8 21 Cleaning And Care 8 21 Windshield And Windows 8 21 Painted S...

Page 313: ...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 airplane maintenance ma...

Page 314: ...ft service requirements and product changes Copies of the actual bulletins are available from Cessna Service Stations and Cessna Customer Service UNITED STATES AIRPLANE OWNERS If your airplane is regi...

Page 315: ...e applicable to your airplane are available from your local Cessna Dealer Information Manual contains Pilot s Operating Handbook Information Maintenance Manual Wiring Diagram Manual and Illustrated Pa...

Page 316: ...rating Handbook and FAA Approved Airplane Flight Manual I 2 Garmin GI000 Cockpit Reference Guide 190 00384 00 Rev B or subsequent 3 Weight and Balance and associated papers latest copy of the Repair a...

Page 317: ...rogressive Care lnspection Program or a PhaseCard lnspection Program Both programs offer systems which allow the work load to be divided into smaller operations that can be accomplished in shorter tim...

Page 318: ...n 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 certified pilot who owns or operates...

Page 319: ...ing arrgle of 29 either side of center or damage to the nose landing gear will result I CAUTION REMOVE ANY INSTALLED RUDDER LOCK BEFORE TOWING If the airplane is towed or pushed over a rough surface d...

Page 320: ...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 bracket When u...

Page 321: ...lown every 30 days or less may not1 achieve normal service life because of internal corrosion Corrosion occurs when moisture from the air and the products of combustion combine to attack cylinder wall...

Page 322: ...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 inspec...

Page 323: ...to Textron Lycoming Service Instruction No 1014 and all revisions and supplements thereto must be used after first 50 hours or when oil consumption has stabilized RECOMMENDEDVISCOSITY FOR TEMPERATURE...

Page 324: ...ine manufacturer NOTE During the first 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 inspecti...

Page 325: ...o Fuel Additives in later paragraphsfor additional information FUEL CAPACITY 92 0 U S Gallons Total 46 0 U S Gallons per tank NOTE a To ensure maximum fuel capacity when refueling and minimize cross f...

Page 326: ...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 alleviate th...

Page 327: ...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 the fueling operation b...

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Page 329: ...O THE FUEL TANK AND SEALANT AhlD DAMAGE TO O RINGS AND SEALS USED IN THE FUEL SYSTEM AND ENGINE COMPONENTS A COIVCENTRATION OF LESS THAN THAT RECOMMENDED 0 10 BY TOTAL VOLUME MINIMUM WILL RESULT IN IN...

Page 330: ...emoved 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 evidence of c...

Page 331: ...H 5606 55 0 60 0 PSI WINDSHIELD AND WINDOWS The plastic windshield and windows should be cleaned with an aircraft windshield cleaner Apply the cleaner sparingiy witn sofi cloths and rub with moderate...

Page 332: ...Harsh or abrasive soaps or detergents which cause corrosion or scratches should never be used Remove stubborn oil and grease with a cloth moistened with Stoddard solvent Take special care to make sur...

Page 333: ...will assure long blade life Small nicks on the propeller particularly near the tips and on the leading edges should be dressed out as soon as possible since these nicks produce stress concentrations a...

Page 334: ...sed sparingly Before using any solvent read the instructions on the container and test it on an obscure place on the fabric to be cleaned Never saturate the fabric with a volatile solvent it may damag...

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Cessna Skylane 182T, Operating Handbook

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Summary of Contents for Skylane 182T

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