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Summary of Contents for 182S Skylane

Page 1: ...Textr 182S Skylane 182StM ...

Page 2: ...PROVED AIRPLANE FLIGHT MANUAL AND IS TO 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 FOR OPERAT ON OF THE AIRPLANE CESSNA AIRCRAFT COMPANY OR GINAL ISSUE 3 FEBRUARY 1997 FebS 97 ...

Page 3: ... Max Range at 10 000 Fl 55o o Power Range 968 NM 88 Gallons Usable Fuel Time 8 05 HRS RATE OF CLIMB AT SEA LEVEL 924 FPM SERVICE CEILING 18 100 FT TAKEOFF PERFORMANCE Ground Roll 795 FT Total Distance Over 50 Ft Obstacle 1514 FT LANDING PERFORMANCE Ground Roll 590 FT Total Distance Over 50 Ft Obstacle 1350 FT STALL SPEED KCAS Flaps Up Power Otf 54 KCAS Flaps Down Power Off 4s KCAS MAXIMUM WEIGHT R...

Page 4: ...d fairings which increase the speeds by approximately 3 knots All other performance when speed fairings are removed based on a 2 bladed propeller I 3 blade propeller is essentially the I The above performance figures are based on the indicated weights standard atmospheric conditions level hard surface dry runways and no wind They are calculated values derived from flight tests conducted by the Ges...

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Page 6: ...pany Wichita Kansas USA Nov 1 01 Cessna Aircraft Company Model 182S THIS MANUAL INCORPORATES INFORMATION ISSUED THRU REVISION 04 TO THE PILOTS OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL DATED 3 FEBRUARY 1997 Q uenaerofGAMA P N 182SlM v viblank ...

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Page 8: ...SECTION TABLE OF CONTENTS GENERAL LIMITATIONS EMERGENCY PROCEDURES NORMAL PROCEDURES PERFORMANCE WEIGHT BALANCE EQUIPMENT LIST A RPLANE SYSTEMS DESCRIPTION HANDLING SERVICE MAINTENANCE SUPPLEMENTS 1 2 3 4 5 6 7 I I Feb 3 97 vii viiiblank ...

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Page 10: ...ngs 1 7 Symbols Abbreviations and Terminology 1 8 GeneralAirspeed Terminology And Symbols 1 8 MeteorologicalTerminology 1 9 Engine Power Terminology 1 9 Airplane Performance And Flight Planning Terminology 1 10 Weight And Balance Terminology 1 11 Metric lmperial U S Conversion Charts 1 13 1 2 1 4 1 4 1 4 1 4 1 4 1 5 1 6 1 7 iit 1 7 Weight Conversions Length Conversions Distance Conversions Volume ...

Page 11: ...SECTION 1 GENERAL CESSNA MODEL 182S 0785T1 001 0785T1 001 Figure 1 1 Three View Normal Ground Attitude Sheet 1 ol2 1 2 Feb 3 97 ...

Page 12: ...2 NORMAL GROUND ATTITUDE IS SHOWN WITH NOSE STRUT SHOWING APPROXIMATELY 2 OF STRUT AND WINGS LEVEL WHEEL BASE LENGTH lS 661 z PROPELLER GROUND CLEARANCE IS 1O WING AREA IS 174 SQUARE FEET MtNtMUM TURNTNG RADTUS ptVOT potNT TO oUTBoARD W NG TtP tS 27 0 0785T1001 Figure 1 1 Three View Normal Ground Attitude Sheet 2 of 2 Feb 3197 1 3 ...

Page 13: ...ir cooled horizontally opposed fuel injected six cylinder engine with 541 cu in displacement Horsepower Rating and Engine Speed 230 rated BHP at 2400 RPM PROPELLER 2 Bladed Propeller Manufacturer Mc0auley Propeller Systems Propeller Model N umber B 2D34C235 90DKB 8 Number of Blades 2 Propeller Diameter 82 inches Propeller Type Constant speed and hydraulically actuated wlth a low pitch sétting of 1...

Page 14: ...dditive concentrations shall not exceed 17 lor isopropyl alcohol or 0 10 to 0 15 for D EGME Refer to Section I for additional information FuelCapacity TotalCapacity 92 0 U S gallons Total Usable 88 0 U S gallons Total Capacity Each Tank 46 0 U S gallons Total Usable Each Tank 44 0 U S gallons NOTE To ensure maximum fuel capacity and minimize cross feeding when refueling always park the airplane in...

Page 15: ...1 Aviation Grade Ashless Dispersant Oil Oil conforming to Textron Lycoming Seruice lnstruction No 1014 and all revisioñs and supplements thereto must be used after first 50 hours or once oil consumption has stabilized Recommended Viscosity for Temperature Range Temperature MtL L 6082 SAE Grade MIL L 22851 Ashless Dispersant SAE Grade bove 27 C 80 F 60 60 bove 16 C 60 F 50 40 or 50 1 C 30 F to 32 C...

Page 16: ...eight 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 Weight 1925 lbs I Maximum Useful Load Normal Category 1185 lbs I CABIN AND ENTRY DIMENSIONS Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6 BAGGAGE SPACE AND ENTRY DIMENSIO...

Page 17: ...tude 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 prescribed extended position Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air then only with caution Never Exceed Speed is lhe speed limit that may not be ex...

Page 18: ...5 C at sea level Temperature pressure altitude and decreases by 2 C for each 1000 feet of altitude Pressure Pressure Altitude is the altitude read from an Altitude altimeter when the altimeter s barometric scale has been set lo 29 92 inches of mercury 1013 mb ENGINE POWER TERMINOLOGY BHP Brake Horsepower is the power developed by the engine RPM Revolutions Per Minute is engine speed Static Static ...

Page 19: ...el Usable Fuel is the fuel available for flight planning Unusable Unusable Fuel is the quantity of fuel that can not be Fuel safely used in flight GPH Gallons Per Hour is the amount of fuel consumed oer hour NMPG Nautical Miles Per Gallon is the distance which can be expected per gallon of fuel consumed at a specif ió engine power setting and or f light configuration g g is acceleration due to gra...

Page 20: ... would balance if suspended lts distance C G from the reference datum is found by dividing the total moment by the total weight of the airplane Center of Gravity Arm is the arm obtained by adding the airplane s individual moments and dividing the sum by the totalweight Center of Gravity Limits are the extreme center of gravity locations within which the airplane must be operated at a given weight ...

Page 21: ...eoff Weight is the maximum weight Takeoff approved for the start of the takeoff roll Weight Maximum Maximum Landing Weight is the maximum weight Landing approved for the landing touchdown Weight Tare Tare is the weight of chocks blocks stands etc used when weighing an airplane and is included in the scale readings Tare is deducted from the scale reading to obtain the actual net airplane weight 1 1...

Page 22: ...nveft U S measurement supplied with the Pilot s Operating Handbook into metric and imperial measurements The standard followed for measurement units shown is th National lnstitute of Standards Technology NIST Publication 811 Guide for the Use of the lnternational System of Units Sl Please refer to the following pages for these charts Nov 15 00 1 13 ...

Page 23: ... 71 169 76 191 80 213 85 235 90 17 637 39 683 61 729 83 776 105 82 127 87 149 91 t 71 96 194 01 216 05 238 10 19 842 41 888 63 934 85 980 108 03 130 07 t52 12 174 17 196 21 218 26 240 30 b 0 10 20 30 40 bU 60 70 80 90 100 o kg 1 2 3 4 5 6 7 I 9 kg kg Kg t g Kg Kg Kg Kg kg 4 536 9 O72 13 608 18 144 22 680 27 216 31 752 36 287 40 823 45 359 o 454 4 990 Y 5ZJ 14 061 1 8 597 23 1 33 27 669 32 205 36 7...

Page 24: ...5 Pounds Pounds x 454 Kilograms POUNDS KILOGRAMS 220 210 200 190 180 t70 160 150 140 130 t20 110 100 90 80 70 60 50 40 30 20 10 0 100 95 90 85 80 75 70 65 60 55 50 45 40 35 30 25 20 15 10 5 0 Units x 10 100 etc 0585T1027 Figure 1 2 Weight Conversions Sheet 2 ol2 1 15 ...

Page 25: ...ô 285 43 318 24 351 05 26 247 91 863 124 67 157 48 190 29 223 10 255 90 288 71 321 52 354 33 29 528 62 336 95 144 127 95 160 76 193 57 226 38 259 1 I 291 58 324 80 357 61 ft 0 10 20 30 40 50 60 70 80 90 100 1 2 3 4 5 6 7 I a m m m m m m m m m 3 048 6 096 9 1M 12 192 15 240 18 288 21 336 24 384 27 432 30 480 0 305 3 353 6 401 9 449 12 497 15 545 18 593 21 641 24 689 27 737 30 785 0 610 J OJõ 6 706 ...

Page 26: ...CTION 1 GENERAL Feetx 305 Meters 320 300 280 260 240 220 200 180 160 140 120 100 80 60 40 20 0 METERS 100 95 90 85 80 75 70 65 60 55 50 45 40 35 30 25 20 15 10 5 0 Units x 10 100 etc 1 17 Nov 15 00 Figure 1 3 Length Conversions Sheet 2 of 2 ...

Page 27: ...09 34 646 38 583 42 520 3 543 7 4AO 11 417 15 354 19 291 23 228 27 164 31 102 35 039 38 976 42 913 n 0 10 20 30 40 50 60 70 an 90 100 0 cm 1 2 3 4 5 o 7 8 I cm cm cm cm cm cm cm cm cm 25 40 50 80 76 20 101 60 127 00 152 40 177 80 203 20 228 60 254 00 a 27 94 s3 34 78 74 104 14 129 54 154 94 180 34 205 74 231 14 zJo æ 5 08 30 48 55 88 81 28 106 68 132 08 157 48 182 88 208 28 233 68 259 08 7 62 33 0...

Page 28: ...June 13 97 SECTION 1 GENERAL Centimeters x 394 lnches lnches x2 54 Centimeters INCHES CENTIMETERS 10 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 I I 7 6 5 4 3 2 1 0 Units x 10 100 etc 0585T1028 1 19 Length Conversions Sheet 2 ot 2 ...

Page 29: ...sx S4 NauticalMiles STATUTE NAUTICAL MILES MILES KILOMETERS 1 15 100 180 110 l gs 105 eo eo f 170 too 1 eu 85 160 95 eof80 80 150 100 95 85 75 80 70 70 130 75 l 65 65 120 70loo 6o llo 65ass 55 a loo toluo 50 50 45 45 40 40 35 35 30 30Azs 25f50 75 l Mo outrto 20 40 90 55 70 60 25 l zo 20 15 15 30 10 10 ro f zo units x 10 1oo etc 5 5 5 10 0 r 0 0 t 0 os sr1o2e 1 20 Figure 1 5 Distance Conversions No...

Page 30: ... 6 159 8 359 12 759 14 958 17 158 19 358 21 558 23 757 i ocô 4 1 80 6 379 8 579 10 779 12 979 1 s 1 78 17 374 19 578 21 778 23 577 0 IG 1 2 3 4 5 6 I 9 Lt Lt Lt LT Lt Lt Lt Lt Lt 4 546 50 006 95 465 140 93 186 38 231 A4 277 30 322 76 368 22 413 68 459 1 4 9 092 54 552 100 01 145 47 190 93 236 39 281 8s oaI Õ I 372 77 418 23 463 69 1 3 638 59 097 104 56 150 02 195 48 240 94 286 40 331 86 377 32 422...

Page 31: ...s x 22 lmperial Gallons 100 IMPERIAL GALLONS YC 90 85 80 75 70 65 60 44O LIERS 420 400 380 360 340 320 300 280 260 240 220 200 180 160 140 55 50 45 40 35 30 25 20 15 10 5 120 100 80 0 Units x 10 100 etc Figure 1 6 Volume Conversions 0585T1 032 Sheet 2 ot 3 20 0 1 22 Nov 15 00 ...

Page 32: ...u ôñS 1oo r120 GALLONS 1oo e5 115 eo 110 105 851too so1 ss 75 e0 70 85 65 80 601zo 55f os 50 60 45 55 95 90 85 80 75 70 65 60 55 75 LITERS 360 340 320 300 280 260 240 220 200 180 160 140 t20 100 80 60 40 20 0 35 30 25 20 15 10 5 0 50 45 40 35 30 25 20 15 10 5 0 45 40 35 30 25 20 15 10 5 0 Units x 10 100 etc Figure 1 6 Volume Conversions 0585T1 033 Sheet 3 of 3 Nov 15 00 1 23 ...

Page 33: ...SECTION 1 GENERAL CESSNA MODEL 182S 0585T1 034 TEMPERATURE CONVERSIONS F 32 x5i9 C Cx9 5 32 oF 1 120 130 140 150 160 170 180 190 2 to 00 110 120 30 40 1 24 Figure 1 7 Temperature Conversions June 13 97 ...

Page 34: ...25 120 FUEL 115 110 105 100 75 70 90 85 65 60 55 50 25 20 15 10 1 1 5 00 etc 0 1 25 itersX 72 K cific Liters X 1 5 I LTTERS 95 90 85 GAS 80 75 70 65 60 l 90 1 sofso 45ï70 ooluo 35 J ro fuo 25t40 20130 tu1 o 101 5f 1o 0_r0 units x 10 Figure 1 8 Volume to Weight Conversion Nov 15 00 ...

Page 35: ...SECTION 1 GENERAL CESSNA MODEL 182S AV GAS SPECIFIC GRAVITY 0 72 1 26 Figure 1 9 Quick Conversions Nov 15 00 ...

Page 36: ...ings Powerplant Limitations Powerplant I nstrument Markin gs Weight Limits Center Of Gravity Maneuver Limits Flight Load Factor Limits Kinds Of Operation Fuel Limitations Other Limitations Flap Limitations Placards SECTION 2 LIMITATIONS 2 3 2 4 2 5 2 5 2 6 2 7 2 7 2 8 2 8 2 8 2 8 2 9 2 g 2 13 Feb 3197 2 11 2 2 blank ...

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Page 38: ...ndbook for I amended operating limitations operating procedures peÉormance data and other necessary information for airplanes equipped with specific options NOTE The airspeeds listed in the Airspeed Limitations chart Figure 2 1 and the Airspeed lndicator Markings chaÉ Figure 2 2 are based on Airspeed Calibration data shown in Section 5 with the normal static source lf the alternate static source i...

Page 39: ...aximum Structural Cruising Speed 137 140 Do not exceed this speed except in rmooth air and lhen only with aution V Maneuvering Speed 3100 Pounds 2600 Pounds 2000 Pounds 109 101 89 110 101 88 Do not make full or abrupt control novements above lhis speed vre Maximum Flap Extended Speed 0 to 10 Flaps 10 to 20 Flaps 20 to FULL Flaps 137 118 100 140 120 100 Do not exceed this speed with flaps down Maxi...

Page 40: ...ngine Operating Limits for Takeoff and Continuous Operations Maximum Engine Speed 2400 RPM Maximum Cylinder Head Temperature 500 F 260 C Maximum Oil Temperature 245 F 118 C OilPressure Minimum 20 PSl Maximum 115 PSl Fuel Grade See Fuel Limitations Oil Grade Specification MIL L 6082 Aviation Grade Straight Mineral Oil or MIL L 22851 Ashless Dispersant Oil Propeller Manufacturer McOauley Propeller S...

Page 41: ...heir color code significance are shown in Figure 2 3 INSTRUMENT RED L NE MTNTMUM GREEN ARC INORMAL OPERAT NG RED LINE MAx Iachometer 2000 2400 RPM 2400 Manifold Pressure 15 23 ln Hg Cylinder Head Temperature 200 500 F 500 F oit Temperature 100 245 F 245 F Oil Pressure 20 PSI 50 90 PSt 115 PSI FuelQuantity 0 2 0 Gal Unusable Each Tank FuelFlow Pressure C to 15 GPH Vacuum Gauge 4 5 5 5 in Hg 2 6 Fig...

Page 42: ...Baggage Area C Station 124 Ìo 134 80 lbs See note below 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 CENTER OF GRAVITY LIMITS Center of Gravity Range Fonruard 33 0 inches aft of datum at 2250 lbs or less with straight line variation to 40 9 inches aft of datum at 3100...

Page 43: ... 09 The design load factors are 150 of the above and in all cases the structure meets or exceeds design loads KINDS OF OPERATION LIMITS The airplane as delivered is equipped for day night VFR IFR and may be equipped for night VFR ancl or IFR operations FAR Part 91 establishes the minimum required instrumentation and equipment for these operations The reference to types of flight operations on the ...

Page 44: ...osition Refer to Figure 1 1 for normal ground attitude def inition Takeoff and land with the fuel selector valve handle in the BOTH position Operation on either LEFT or RIGHT tank limited to level flight only W th 1 4 tank or less prolonged uncoordinated flight is prohibited when operating on either left or right tank Approved FuelGrades and Colors 100LL Grade Aviation Fuel Blue 100 Grade Aviation...

Page 45: ...complied with when operating this airplane in the Normal Category Other operating limitations which must be complíed with when operating this airplane ín this category are contained in the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual No acrobatic maneuvers including spins approved Flight into known icing conditions prohibited This airplane is certified for the following fligh...

Page 46: ...IGHT ONL OFF 4 Near the fuel tank filler cap FUEL lOOLU1OO MIN GRADE AVIATION GASOLINE CAP 44 0 U S GAL USABLE CAP 32 5 U S GAL USABLE TO BOTTOM OF FILLER INDICATOR 5 On flap control indicator 0 to 10 140 KIAS Partial flap range with dark blue color code also mechanicaldetent at 10 10o to 20 120 KIAS Light blue color code also mechanical detent al 20 20 to FULL 100 KIAS White color code 2 11 Feb 3...

Page 47: ...DOOR LATCH MAXIMUM 2OO POUNDS COMBINED FOR ADDITIONAL LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA 7 A calibration card must be provided to indicate the accuracy of the magnetic compass in 30 increments 8 On the oil filler cap olL 9 QTS 9 Near airspeed indicator MANEUVER SPEED 110 KIAS 10 On the upper right instrument panel SMOKING PROHIBITED 2 12 Feb 3197 ...

Page 48: ...ARITY REVERSE POLARITY WILL DAMAGE ELECTRICAL COMPONENTS 12 On Upper Right Side of the Aft Cabin Partition EMERGENCY LOCATOR TRANSMITTER INSTALLED AFT OF THIS PARTITION MUST BE SERVICED IN ACCORDANCE WITH FAR PART 91 2O7 13 Near the fuel flow gauge MAXIMUM POWER FUEL FLOW ALTITUDE S L 2000 4000 6000 8000 1 0000 1 2000 FUEL FLOW 20 5 GPH 19 0 GPH 17 5 GPH 16 5 GPH 15 5 GPH 14 5 GPH 13 5 GPH Feb 3 9...

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Page 50: ...lure lmmediately After Takeoff Engine Failure During Flight Restart Procedures Forced Landings Emergency Landing Without Engine Power Precautionary Landing With Engine Power Ditching Fires During Start On Ground Engine Fire ln Flight Electrical Fire ln Flight Cabin Fire Wing Fire Icing 3 9 lnadvertent lcing Encounter 3 9 Static Source Blockage 3 10 Landing With A Flat Main Tire 3 10 3 3 3 4 3 4 3 ...

Page 51: ...nding Without Elevator Control Fires Emergency Operation ln Clouds Vacuum System Failure Executing A 180 Turn ln Clouds Emergency Descent Through Clouds Recovery From Spiral Dive ln The Clouds lnadvertent Flight lnto lcing Conditions 3 13 3 15 3 15 3 16 3 16 3 16 3 17 3 18 3 18 3 18 Static Source Blocked Spins 3 19 Rough Engine Operation Or Loss Of Power Spark Plug Fouling Magneto Malfunction Low ...

Page 52: ... emergency arise the basic guidelines described in this section should be considered and applied as necessary to correct the problem Emergency procedures associated with standard avionics the ELT or any optional systemsr can be found in the Supplements Section 9 I AIRSPEEDS AIRSPEEDS FOR EMERGENCY OPERATION Engine Failure After Takeoff Wing Flaps Up Wing Flaps Down Maneuvering Speed 3100 Lbs 2600 ...

Page 53: ...on Switch OFF 6 Master Switch OFF ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF 1 Airspeed 75 KIAS flaps UP 70 KIAS flaps DowN 2 Mixture IDLE CUT OFF 3 FuelSelector Valve PUSH DOWN and ROTATE TO OFF 4 lgnition Switch OFF 5 Wing Flaps AS REQUIRED FULL recommended 6 Master Switch OFF 7 Cabin Door UNL ATCH L Land STRAIGHT AHEAD ENGINE FAILURE DURING FLIGHT Restart Procedures 1 Airspeed 75 KIAS Best glide ...

Page 54: ...Y HEAVILY PRECAUTIONARY LANDING WITH ENGINE POWER 1 Passenger Seat Backs MOST UPRIGHT POSITION 2 Seats and Seat Belts SECURE 3 Airspeed 75 KIAS 4 Wing Flaps 20 5 Selected Field FLY OVER noting terrain and obstructions then retract flaps upon reaching a safe altitude and airspeed 6 Avionics Mastér Switcn and Elðctrical Switches OFF 7 Wing Flaps FULL on final approach 8 Airspeed 70 KIAS 9 Master Swi...

Page 55: ...F DESCENT 10 Face CUSHION at touchdown with folded coat 11 ELT Activate 12 Airplane EVACUATE through cabin doors lf necessary open window and flood cabin to equalize pressure so doors can be opened 13 Life Vests and Raft INFLATE WHEN CLEAR OF AIRPLANE FIRES DURING START ON GROUND 1 Cranking CONTINUE to get a start which would suck the flames and accumulated fuel into the engine lf engine starts 2 ...

Page 56: ... OFF 4 Master Switch OFF 5 Cabin Heat and Air OFF except overhead vents ô Airspeed 100 KIAS lf fire is not extinguished increase glide speed to find an airspeed within airspeed limitations which will provide an incombustible mixture 7 Forced Landing EXECUTE as described in Emergency Landing Without Engine Power ELECTRICAL FIRE IN FLIGHT 1 Master Switch OFF 2 Vents Cabin Air Heat CLOSED 3 Fire Exti...

Page 57: ...ents Cabin Air Heat CLOSED to avoid drafts 3 Fire Extinguisher AGTIVATE if available mmtruc AFTER DISCHARGING FIRE EXTINGUISHER AND ASCERTAINING THAT F RE HAS BEEN EXTINGUISHED VENTILATE THE CABIN 4 Vents Cabin Air Heat Open when it is ascertained that fire is completely extinguished 5 Land the airplane as soon as possible to inspecl for damage WING FIRE 1 Landing Taxi Light Switches OFF 2 Navigat...

Page 58: ...ired for any change in power settings 6 Plan a landing at the nearest airpoft With an extremely rapid ice build up select a suitable off airpoft landing site 7 With an ice accumulation ol 1 4 inch or more on the wíng leading edges be prepared for significantly higher stall speed 8 Leave wing flaps retracted With a severe ice build up on the horizontal tail the change in wing wake airflow direction...

Page 59: ...5 LANDING WITH A FLAT MAIN TIRE 1 Approach NORMAL 2 Wing Flaps FULL DOWN 3 Touchdown GOOD MAIN TIRE FIRST hold airplane off flat tire as long as possible with aileron control 4 Directional Control MAINTAIN using brake on good wheel as required LANDING WITH A FLAT NOSE TIRE 1 Approach NORMAL 2 Flaps AS REQUIRED 3 Touchdown ON MAINS hold nose wheel off the ground as long as possible 4 When nose whee...

Page 60: ... NOTE lllumination of VOLTS on the annunciator panel may occur during low RPM conditions with an electrical load on the system such as during a low RPM taxi Under these conditions the light will go out at higher RPM The master switch need not be recycled since an overuoltage condition has not occurred to deactivate the alternator system 1 Avionics Master Switch OFF I 2 Alternator Circuit Breaker C...

Page 61: ...MINATE as soon as practical VACUUM SYSTEM FAILURE Left Vacuum or Right Vacuum Annunciator Light L VAC R llluminates 1 crunoru IF VAGUUM IS NOT WITHIN NORMAL OPERATING L MITS A FAILURE HAS OCCUFRED IN THE VACUUM SYSTEM AND PARTIAL PANEL PROCEDURES MAY BE REOUIRED FOR CONTINUED FLIGHT I t Vacuu m Gauge CHECK to ensure vacuum within normal operaüng ilmlls 3 12 Nov 15 00 ...

Page 62: ...ge of procedures fresh ENGINE FAILURE lf an engine failure occurs during the takeoff roll the most impoftant thing to do is stop the airplane on the remaining runway Those extra items on the checklist will provide added safety after a failure of this type Prompt lowering of the nose to maintain airspeed and establish a glide attitude is the first response to an engine failure after takeoff ln most...

Page 63: ...While gliding toward a suitable landing area an effort should be made to identify the cause of the failure lf time permits an engine restafi should be attempted as shown in the checklist lf the engine cannot be restarted a forced landing without power must be completed 14000 4000 2000 0 o 2 4 6 8 1012 1416182022 GROUND DISTANCE NAUTICAL MILES Figure 3 1 Maximum Glide 2000 0000 8000 6000 Er z d1 ff...

Page 64: ...and squawk 7700 Avoid a landing flare because of difficulty in judging height over a water surface The checklist assumes the availability of power to make a precautionary water landing lf power is not available use of the airspeeds noted with minimum flap extension will provide a more favorable attitude for a power off ditching ln a forced landing situation do not turn off the AVIONICSI MASTER swi...

Page 65: ...in elimination of the fire EMERGENCY OPERATION IN CLOUDS Total Vacuum System Failure lf both the vacuum pumps fail in flight the directional indicator and attitude indicator will be disabled and the pilot will have to rely on the turn coordinator if he inadvertently flies into clouds lf an autopilot is installed it too may be affected Refer to Section 9 Supplements for additional details concernin...

Page 66: ...To guard against a spiral dive choose an easterly or westerly heading to minimize compass card swings due to changing bank angles ln addition keep hands off the control wheel and steer a straight course with rudder control by monitoring the turn coordinator Occasionally check the compass heading and make minor corrections to hold an approximate course Before descending into the clouds set up a sta...

Page 67: ...light INADVERTENT FLIGHT INTO ICING CONDITIONS Flight into icing conditions is prohibited and can be extremely dangerous An inadvertent encounter with these conditions can best be handled using the checklist procedures The best procedure of course is to turn back or change altitude to escape icíng conditions STATIC SOURCE BLOCKED lf erroneous readings of the static source instruments airspeed alti...

Page 68: ...TION 2 PLACE AILERONS IN NEUTRAL POSITION 3 APPLY AND HOLD FULL RUDDER OPPOSITE TO THE DIRECTION OF ROTATION 4 JUST AFTER THE RUDDER REACHES THE STOP MOVE THE CONTROL WHEEL BRISKLY FORWARD FAR ENOUGH TO BREAK THE STALL 5 HOLD THESE CONTROL INPUTS UNTIL ROTATION STOPS Premature relaxation of the control inputs may extend the recovery 6 AS ROTATION STOPS NEUTRALIZE RUDDER AND MAKE A SMOOTH RECOVERY ...

Page 69: ...ring is usually evidence of magneto problems Switching from BOTH to either L or R ignition switbh posilion will identify which magneto is malfunctioning Select different power settings and enrichen the mixture to determine if continued operation on BOTH magnetos is practicable lf not switch to the good magneto and proceed to the nearest airport for repairs LOW OIL PRESSURE lf the low oil pressure ...

Page 70: ... CHARGE After engine stafting 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 initial part of a flight However after thirty minutes of cruising flight the ammeter should be indicating less than two needle widths of charging current lf the charging rate were to remain above this value on a l...

Page 71: ...sume and the low voltage VOLTS annunciator will go off The AVIONICS MASTER switch may then be turned back on lf the light illuminates again a malfunction is confirmed ln this event the ffight should be terminated and or the current drain on the battery minimized because the battery can supply the electrical system for only a limited period of time Battery power must be conserved for later operatio...

Page 72: ...age Right Wing Trailing Edge Right Wing Nose Left Wing 4 5 4 5 4 8 4 9 4 10 4 11 4 11 4 11 4 12 4 13 4 14 4 15 4 15 4 15 4 15 4 15 4 16 4 7 4 7 4 8 4 8 Left Wing Leading Edge Left Wing Trailing Edge Before Starting Starting Engine Starting Engine Before Takeoff With Battery Engine With ExternalPower Takeoff NormalTakeoff Short Field Takeoff Enroute Climb NormalClimb Maximum Pedormance Climb Feb 31...

Page 73: ...Check Wing Flap Settings Crosswind Takeoff Enroute Climb CESSNA MODEL 182S Page 4 16 4 16 4 16 4 17 4 17 4 17 4 17 4 17 4 18 AMPLIFIED PROCEDURES Preflight lnspection 4 19 Starting Engine 4 2O Starting General 4 2O Taxiing 4 21 Before Takeoff 4 23 Warm Up 4 23 Magneto Check 4 23 4 23 4 24 4 24 4 24 4 24 4 25 4 25 Cruise 4 26 Fuel Savings Procedures for NormalOperations 4 28 Fuel Vapor Procedures 4...

Page 74: ...RES TABLE OF CONTENTS Continued Landing NormalLanding Short Field Landing Crosswind Landing Balked Landing Cold Weather 0peration Hot Weather Operation Noise Characteristics And Noise Beduction Starting Winterization Kit Nov 15 00 4 3 4 4 blank ...

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Page 76: ... the particular weight must be used Takeoff NormalClimb Out 70 80 KIAS Short Field Takeoff Flaps 20 Speed at 50 Feet 58 KIASI Enroute Climb Flaps Up Normal Sea Level Best Rate of Climb Sea Level Best Rate of Climb 10 000 Feet Best Angle of Climb Sea Level 63 KIAS 85 95 KIAS 80 KIAS 72KIAS Best Angle of Climb 10 000 Feet Landing Approach 2950 lbs NormalApproach Flaps Up 70 80 KIAS NormalApproach Fl...

Page 77: ...f the refueling steps and assist handles will simplify access to the upper wing surfaces for visual checks and refueling operations ln cold weather remove even small accumulations of frost ice or snow from wing tail and control surfaces Also make sure that control sudaces contain no internal accumulations of ice or debris lf a night flight is planned check operation of all lights and make sure a f...

Page 78: ...TCH USING AN EXTERNAL POWER SOURCE OR PULL NG THE PROPELLER THROUGH BY HAND TREAT THE PROPELLER AS IF THE IGNITION 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 PROPELLER TO ROTATE 8 Master Switch ON 9 Fuel Quantity lndicators CHECK QUANTIW AND LOW FUEL ANNUNCTATORS L LOW FUEL EXTIN...

Page 79: ...XTEND 18 Pitot Heat ON Carefully check that pitot tube is warm to the touch within 30 seconds 19 Pitot Heat OFF 20 Master Switch OFF 21 Baggage Door CHECK lock with key erueeruNAcE I 1 Rudder Gust Lock if installed REMOVE 2 Tail Tie Down DISCONNECT 3 Control Surfaces CHECK freedom of movement and security 4 Trim Tab CHECK security 5 Antennas CHECK for security of attachment and general condition n...

Page 80: ...AINTENANCE PERSONNEL ALL EVIDENCE OF CONTAMINATION MUST BE REMOVED BEFORE FURTHER FLIGHT 5 FuelQuantily CHECK VISUALLY for desired level 6 Fuel Filler Cap SECURE and VENT UNOBSTRUCTED r rose 1 Static Source Opening right side of fuselage CHECK for blockage 2 Fuel Strainer Quick Drain Valve Located on bottom of fuselage DRAIN at least a cupful of fuel using sampler cup from valve to check for water...

Page 81: ...age r err wrNG 1 Fuel Quantity CHECK VISUALLY for desired level 2 Fuel Filler Cap SECURE and VENT UNOBSTRUCTED 3 Fuel Tank Sump Quick Drain Valves DRAIN at least a cupful of fuel using sampler cup from each sump location to check for water sediment and proper fuel grade before each flight and after each refueling lf water is observed take further samples until clear and then gently rock wings and ...

Page 82: ...of cover LErr WING Traiting Edge 1 Aileron CHECK for freedom of movement and security 2 Flap CHECK for security and condition BEFORE STARTING ENGINE 1 Preflight lnspection COMPLETE 2 Passenger Briefing COMPLETE 3 Seats Seat Belts Shoulder Harnesses ADJUST and LOCK Ensure inertia reel locking 4 Brakes TEST and SET 5 Circuit Breakers CHECK lN 6 Electrical Equipment OFF wnnunc THE AVIONICS MASTER SWI...

Page 83: ... Fuel Pump OFF NOTE I lt engine is warm omit priming procedure of step 6 7 and I above I g lgnition Switch START release when engine starts I lo Mixture ADVANCE smoothly to RICH when engine fires NOTE I lt engine floods place mixture in idle cut off open throttle 112 tó full and crank engine When engine fires advance mixture to full rich and retard throttle promptly I I L Oil Pressure CHECK I lz F...

Page 84: ...ry Fuel Pump OFF NOTE lf engine is warm omit priming procedure of steps 7 I and 9 above 10 lgnition Switch START release when engine starts 11 Mixture ADVANCE smoothly to RICH when engine fires NOTE lf engine floods place mixture in idle cut off open throttle I 112 lo full and crank engine When engine fires advance mixture to full rich and retard throttle promptly 12 OtPressure CHECK I 13 External...

Page 85: ...ntial between magnetos b Proþeller CYCLE from high to low RPM return to high RPM fullin c Vacuum Gauge CHECK d Engine lnstruments and Ammeter CHECK 11 Annunciator Panel Ensure no annunciators are illuminated 12 Throttle CHECK IDLE 13 Throttle 1000 RPM or less 14 Throttle Friction Lock ADJUST 15 Strobe Lights AS DESIRED 16 Radios and Avionics SET 17 NAV GPS HSI Switch if installed SET 18 Autopilot ...

Page 86: ... 1 Wing Flaps 20 2 Brakes APPLY 3 Power FULL THROTTLE and 2400 RPM 4 Mixture Lean to obtain Maximum Power Fuel Flow placard value 5 Brakes RELEASE 6 Elevator Control MAINTAIN SLIGHTLY TAIL LOW ATTITUDE 7 Climb Speed 58 KIAS until all obstacles are cleared 8 Wing Flaps RETRACT slowly after reaching 70 KIAS ENROUTE CLIMB NORMAL CLIMB 1 Airspeed 85 95 KIAS 2 Power 23 in Hg or FULL THROTTLE whichever ...

Page 87: ...n 80 2 Elevator and Rudder Trim ADJUST 3 Mixture LEAN 4 Cowl Flaps CLOSED DESCENT 1 Power AS DESIRED 2 Mixture ENRICHEN as required 3 Cowl Flaps CLOSED 4 Fuel Selector Valve BOTH I s runvlcPS HSI Switch if installed sET I O Wing Flaps AS DESIRED 0 10 below 140 KIAS 10 20 below 120 KIAS 20 FULL below 100 KIAS BEFORE LANDING 1 Pilot and Passenger Seat Backs MOST UPRIGHT POSITION 2 Seats and Seat Bel...

Page 88: ...R NOSE WHEEL GENTLY 8 Braking MINIMUM REQUIRED SHORT FIELD LANDING 1 Airspeed 70 80 KIAS flaps UP 2 Wing Flaps FULL below 100 KIAS 3 Airspeed 60 KIAS untilflare 4 Trim ADJUST as desired 5 Touchdown MAIN WHEELS FIRST 6 Brakes APPLY HEAVILY 7 Wing Flaps RETRACT for maximum brake effectiveness BALKED LANDING Power FULL THROTTLE and 2400 RPM Wing Flaps RETRACT TO 20 Climb Speed 55 KIAS Wing Flaps RETR...

Page 89: ...rake SET 2 Throttle IDLE 3 Electrical Equipment Avionics Master Switch Autopilot if installed OFF 4 Mixture IDLE CUT OFF pulled full out 5 lgnition Switch OFF 6 Master Switch OFF 7 Control Lock INSTALL 8 Fuel Selector Valve LEFT or RIGHT to prevent cross feeding 4 18 Nov 15 00 ...

Page 90: ...ts damage to nose wheel as a result of exceeding tow limits and avionics antennas Outside storage for long periods may result in dust and dirt accumulation on the induction air filter obstructions in airspeed system lines water contaminants in fuel tanks and insecUbird rodent nests in any opening lf any water is detected in the fuel system the fuel tank sump quick drain valves fuel reservoir quick...

Page 91: ...irplane structure of fuel fuel tank filler caPs after or servicing Fuel d also ctions ice or water osure STARTING ENGINE STARTING GENERAL ln cooler weather the engine compartment temperature drops off rapidly following engine shutdown and the injector nozzle lines remain nearly full of fuel smoothly to full rich as power develops SECTION 4 NORMAL PROCEDURES CESSNA MODEL 182S 4 20 Feb 3197 ...

Page 92: ...ely one minute in very cold weather stop the engine and investigate Lack of oil pressure can cause serious engine damage NOTE Additional details concerning cold weather starting and operation may be found under COLD WEATHER OPERATION paragraphs in this section Recommended starter duty cycle Crank the starter for 10 seconds followed by a 20 second cool down period This cycle can be repeated two add...

Page 93: ...tering tail winds require caution Avoid sudden bursts of the throttle and sharp brakino when the airolane is in this attitude Use th e steerable ndse wheel and rudder to maintain direction 0785T1 0 1 2 Figure 4 2 Taxiing Diagram CESSNA MODEL 182S 4 22 Feb 3197 ...

Page 94: ...r magneto or show greater than 50 RPM differential between magnetos lf there is a doubt concerning operation of the ignition system RPM checks at higher engine speeds will usually confirm whether a deficiency exists An absence of RPM drop may be an indication of faulty grounding of one side of the ignition system or should be cause for suspicion that the magneto timing is set in advance of the set...

Page 95: ... fuel flow values provided on the Maximum Power Fuel Flow placard in a full throttle static runup Atter full throttle is applied adjust the t k clockwise to prevent the throttle from cree a maximum power position Similar friction lock d be made as required in other flight conditions d throttle setting WING FLAP SETTINGS Normal takeoffs are accomplished with wing flaps 0 to 20 Using 20 wing flaps r...

Page 96: ...h the ailerons partially deflected inlo the wind the airplane is accelerated to a speed slightly higher than normal then pulled off briskly to prevent possible settling back to the runway while drifting When clear of the ground make a coordinated turn into the wind to correct for drift ENROUTE CLIMB Normal climbs are performed at 85 95 KIAS with flaps up 23 ln Hg or full throttle whichever is less...

Page 97: ...ction 5 NOTE Cruising should be done al 75 power as much as practicable until a total of 50 hours has accumulated or oil consumption has stabilized Operation at this higher power will ensure proper seating of the rings and 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 th...

Page 98: ...6 125 113 1r6 12 O 6000 feet 140 10 4 136 108 127 11 5 118 12 2 8000 feel 130 11 7 120 124 10000 feet t32 1 t 9 121 t2 6 Figure 4 3 Cruise Performance Table Cruise data in this handbook is based on a recommended lean mixture setting which may be established using the EGT indicator at powers of 8O MCP and lower as follows I 1 Lean the mixture slowly until the EGT peaks and begins to drop 2 Enrichen...

Page 99: ...Figure 4 4 EGT Table SAVINGS PROCEDURES FOR NORMAL OPERATIONS For best fuel economy during normal operations the following are recommended 1 After engine start and for all ground operations set the throttle to 1200 RPM and lean the mixture for maximum RPM Leave the mixture at this setting until beginning the BEFORE TAKEOFF checklist After the BEFORE TAKEOFF checklist is complete re lean the mixtur...

Page 100: ... idle and taxi engine speeds When vapor occurs as evidenced by idle engine speed and fuel flow fluctuations the following procedures are recommended 1 With the mixture full rich setthe throttle at 1800 RPM to 2000 RPM Maintain this power setting for 1 to 2 minutes or until smooth engine operation returns 2 Retard the throttle to idle to verify normalengine operation 3 Advance the throttle to 1200 ...

Page 101: ...r power off with any flap setting desired Surface winds and air turbulence are usually the primary factors in determining the most comfortable approach speeds Actual touchdown should be made with power otf and on the main wheels first to reduce the landing speed and subsequent need for braking in the landing roll The nose wheel is lowered to the runway gently after the speed has diminished to avoi...

Page 102: ...e control wheel full back and apply maximum brake pressure without sliding the tires CROSSWIND LANDING When landing in a strong crosswind use the minimum flap setting required for the field length Although the crab or combination method of drift correction may be used the wing low method gives the best control After tou chdown hold a stiaight course with the steerable nose wheel and occasional bra...

Page 103: ...m wing tail and all control surfaces to assure satisfactory flight performance and handling Also control surîaces must be free of any internal accumulations of ice or snow lf snow or slush covers 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 prevent takeof...

Page 104: ...ution to prevent inadveñent forward movement of the airplane during starting when parked on snow or ice NOTE lf the engine does not start during the first few attempts or if engine firing diminishes in strength it is probable that the spark plugs have been frosted over Preheat must be used before another start is attempted During cold weather operations no indication will be apparent on the oil te...

Page 105: ...o 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 make every effoil to fly not less than 2000 feet above the surface weather permitting even though flight at a lower level may be consistent with the provisions of govemment regulations 2 During departure f...

Page 106: ... Correction Figure 5 3 Temperature Conversion Chafi 5 12 Figure 5 4 Stall Speeds Figure 5 5 Crosswind Components Figure 5 6 Short Field Takeoff Distance 3100 Lbs Short Field Takeoff Distance 2700 Lbs Short Field Takeoff Distance 2300 Lbs Figure 5 7 Maximum Rate Of Climb Figure 5 8 Time Fuel And Distance To Climb Figure 5 9 Cruise Performance 5 21 Figure 5 10 Range Profile 5 31 Figure 5 1 1 Enduran...

Page 107: ......

Page 108: ...bulence may account for variations of 10 or more in range and endurance Therefore it is important to utilize all available information to estimate the fuel required for the particular flight and to flight plan in a conseruative manner USE OF PERFORMANCE CHARTS Performance data is presented in tabular or graphical form to illustrate the effect of different variables Sufficiently detailed informatio...

Page 109: ... temperature For example in this particular sample problem the takeoff distance information presented for a weight of 3100 pounds pressure altitude of 2000 feet and a temperature of 30 C should be used and results in the following Ground roll 1055 Feet Total distance to clear a S0 foot obstacle 2035 Feet These distances are well within the available takeoff field length However a correction for th...

Page 110: ...e characteristics presented in Figure 5 9 the range prof ile charÌ presented in Figure 5 10 and the endurance profile chaft presented in Figure 5 1 1 The relationship between power and range is illustrated by the range profile chart Considerable fuel savings and longer range result when lower power settings are used For this sample problem a cruise power of approximately 60 will be used The cruise...

Page 111: ...hart The approximate effect of a non standard temperature is to increase the time fuel and distance by 10 for each 10 C above standard temperature due to the lower rate of climb ln this case assuming a temperature 16 C above standard the correction would be X 10 16 lncrease With this factor included the fuel estimate would be calculated as follows SECTION 5 PERFORMANCE The resultant cruise distanc...

Page 112: ...is 3 5 hours X 11 3 gallons hour 39 1 Gallons A 45 minute reserve requires 4Þ u rr 6õ Ã r r 3 gallons hour 8 5 Gallons The total estimated fuel required is as follows Engine start taxi and takeoff 1 7 Climb Cruise Reserve Totalfuel required 3 1 39 1 8 5 52 4 Gallons I I Once the flight is undenruay ground speed checks will provide a more accurate basis for estimating the time enroute and the corre...

Page 113: ... Ground roll 670 Feet Total distance to clear a 50 oot obstacle 1480 Feet A correction for the effect of wind may be made based on Note 2 of the landing chart using the same procedure as outlined for takeoff DEMONSTRATED OPERATING TEMPERATURE Satisfactory engine cooling has been demonstrated for this airplane with an outside air temperature 23 C above standard This is not to be considered as an op...

Page 114: ... maximum power descent Figure 5 1 Airspeed Calibration Sheet 1 ot 2 Feb 3 97 5 9 FLAPS UP KIAS KCAS 55 60 70 80 90 62 65 73 82 90 100 110 120 130 140 150 160 100 109 118 127 137 146 156 FLAPS 20 KIAS KCAS 40 50 60 70 80 90 100 110 120 53 58 64 72 81 91 100 110 119 FLAPS FULL KIAS KCAS 40 50 60 70 80 90 95 51 56 64 72 81 91 95 ...

Page 115: ...imum CONDITION Power required for level flight or maximum power descent FLAPS UP KIAS ALT KIAS i0 70 80 90 2 72 82 92 100 110 120 130 140 150 160 103 114 124 133 143 153 164 FLAPS 20 KIAS ALT KIAS i0 60 70 80 90 100 110 120 t0 60 70 81 92 102 112 121 FLAPS FULL KIAS ALT KIAS 0 60 70 80 90 95 3 57 68 79 89 93 Figure 5 1 Airspeed Calibration Sheet 2 of 2 5 10 Dec 1197 ...

Page 116: ...m power descent cruise configura tion Altimeter corrections Tor the takeoff and landing configuration are less than 50 feet CONDITION FLAPS UP CORRECTION TO BE ADDED FEET KIAS alternate static source ON 60 80 100 120 140 160 S L 2000 ft 4000 ft 6000 ft 8000 ft 10 000 Ít 12 000 ft 14 000 ft 20 20 20 30 30 30 30 30 10 10 10 10 10 10 10 10 30 30 30 40 40 40 40 50 60 60 70 70 80 80 80 90 90 90 100 110...

Page 117: ...SECTION 5 PERFORMANCE CESSNA MODEL 182S F H60 z I JJ fr T 40 U UJ U ÍÍ fl20 o TEMPERATURE CONVERSION CHART DEGREES CELSIUS Figure 5 3 Temperature Conversion Chad 5 12 Feb 3 97 ...

Page 118: ...much as 250 feet 2 KIAS values are aþproximate FLAP SETTIN ANGLE OF BANK 00 30 45 60 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 20 FULL 40 29 35 54 50 49 43 31 38 58 54 53 48 34 42 64 59 58 57 41 49 76 71 69 FLAP SETTINC ANGLE OF BANK 00 300 450 600 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 20 FULL 43 35 36 56 52 50 46 38 39 60 56 54 51 42 43 67 62 59 61 49 51 79 74 71 Feb 3 97 Figure 5 4 Stall S...

Page 119: ...COMPONENTS NOTE f Vaximum demonstrated crosswind velocity is 15 knots not a limitation 35 30 25 20 15 10 5 0 5 10 15 0510f520253035 CROSSWND COMPONENT KNOTS o z Øo t cl J z V I t z l z o È o o c 2a J 5 14 Figure 5 5 Crosswind Components Nov 15 00 ...

Page 120: ...10 2470 2785 3175 765 835 915 995 1090 1 195 1315 1445 1 595 1460 1600 1760 1 940 2150 2395 2690 3045 3500 825 900 980 1070 1175 1290 1415 1560 1720 1570 t720 1 890 2090 2325 2595 2930 3345 3880 885 965 1055 1 150 1260 1 385 1520 1675 1680 1 845 2035 2255 2515 2820 3200 3685 945 1030 1 130 1235 1355 1485 I 635 1800 1 980 2190 2435 2720 3070 3510 NOTES 1 Short field technique as specified in Sectio...

Page 121: ...0 2100 560 610 66s 725 790 865 950 1 040 1 145 1065 1 155 1260 1 380 1510 1 665 1840 2040 2275 600 655 710 775 850 930 1020 1 120 1230 1235 1 350 1480 1625 1790 1 980 2205 2465 35 11 645 700 765 835 910 1000 1095 1200 1320 1215 1320 1445 1 585 1740 1 920 2135 2380 2675 690 750 820 895 975 1 070 1175 1 290 1420 1295 1410 1545 1695 1870 2065 2300 2575 2910 NOTES 1 Short field technique as specified ...

Page 122: ...1 165 1275 1 405 390 425 460 505 550 600 655 715 785 750 815 885 960 1 045 1140 1 250 t370 1510 420 455 495 540 590 640 700 770 845 800 870 940 1025 1115 1220 1335 1470 1 620 450 490 s30 580 630 690 755 825 905 850 925 1 005 1 090 1 190 1 305 1430 1570 1 735 480 520 565 620 675 735 805 885 970 905 985 1070 1165 1270 1390 1530 1685 1865 NOTES 1 Short field technique as specified in Section 4 SÌ 2 P...

Page 123: ...ximum Power Fuel value Cowl Flaps Open PRESS ALT FT CLIMB SPEED KIAS RATE OF CLIMB FPM 20 c 0 c 20 c 40 c S L 2000 4000 6000 8000 10 000 12 000 14 000 80 79 78 77 75 74 73 72 1 055 945 840 735 625 520 410 310 980 875 770 670 560 455 350 250 905 805 705 605 495 390 285 190 835 735 635 535 430 330 225 130 5 18 Figure 5 7 Maximum Rate of Climb Nov 15 00 ...

Page 124: ...value Cowl Flaps Open Standard Temperature PRESS ALT FT CLIMB SPEED KIAS RATE OF CLIMB FPM FROM SEA LEVEL TIME IN MIN FUEL USED GAL DIST NM S L 2000 4000 6000 8000 10 000 12 000 14 000 80 79 78 77 75 74 73 72 925 835 750 660 565 470 375 285 0 2 5 8 11 15 20 26 0 0 0 8 1 5 2 3 3 2 4 2 5 2 6 5 0 3 7 11 16 21 29 38 Flow NOTES Figure 5 8 Time Fuel and Distance to Climb Sheet 1 oÍ 2 Nov 15 00 5 19 ...

Page 125: ...TE OF CLIMB FPM FROM SEA LEVEL TIME IN MIN FUEL USED GAL DIST NM S L 2000 4000 6000 8000 10 000 90 90 90 90 90 90 665 625 580 540 455 370 0 3 6 10 14 19 0 0 0 8 1 6 2 5 3 5 4 6 0 5 10 16 23 31 NOTES 1 Add 1 7 e start taxi and takeoff allowance SÌ 2 Mixture Power Fuel Flow placard value for smooth creased power 3 lncrease time fuel and distance bv 10 for each 10 C above standard temperature 4 Dista...

Page 126: ... t31 128 125 122 119 115 1 11 131 129 126 123 120 117 113 109 13 4 12 7 12 O 11 3 10 6 10 0 13 7 12 9 12 3 11 6 10 9 10 3 9 7 13 8 13 1 12 5 11 8 11 2 10 6 10 0 9 4 82 77 73 Âa 64 60 CJ 83 t9 75 70 66 62 58 54 80 76 72 oõ 64 60 30 5Z 134 131 127 124 121 117 1t3 134 132 129 126 123 119 115 111 132 129 126 124 121 1 t7 113 109 13 7 13 0 I Z J 11 6 t0 9 10 3 9 7 13 9 13 2 I J 11 9 l t 2 10 6 10 0 9 4...

Page 127: ...H 21 00 2000 2t 26 25 24 23 22 21 27 26 25 24 23 22 21 79 75 71 67 63 59 55 74 71 67 63 60 co 52 129 126 123 120 118 114 110 126 123 121 118 114 111 108 3 2 12 5 11 9 11 3 10 7 10 2 9 6 12 5 11 9 11 4 10 8 10 3 9 8 9 2 76 72 68 64 61 57 53 72 68 65 61 58 54 50 130 127 124 t21 117 114 111 127 124 122 118 115 111 108 2 t 12 1 1 1 5 1 1 0 10 4 9 9 9 4 12 1 11 5 11 0 10 5 10 0 9 5 9 0 tó 70 66 62 59 5...

Page 128: ...72 68 o 60 56 t34 131 127 124 121 116 132 t29 125 122 118 114 132 130 126 124 120 1 t6 113 13 9 13 1 12 4 11 6 10 9 10 3 13 3 12 6 11 9 11 3 10 6 10 0 13 5 12 8 12 2 11 5 10 9 10 3 9 7 80 75 71 67 62 58 81 77 73 68 64 60 56 78 74 70 bb 62 58 54 135 131 128 125 120 117 136 132 129 126 123 119 1 t5 133 130 127 t24 120 117 113 13 4 12 7 t2 0 11 3 10 6 10 0 13 6 12 9 12 2 11 6 t0 9 10 3 9 7 13 1 12 4 ...

Page 129: ...GPH BHP KTAS GPH 21 00 2000 26 25 24 23 22 21 20 26 25 24 23 22 2 l 77 7S 69 65 61 57 53 73 69 65 62 58 54 1 30 127 124 121 117 114 110 127 124 122 118 115 111 v 122 116 110 10 5 9 9 9 3 12 2 1 t 7 11 1 10 6 10 0 9 5 74 70 66 63 59 55 51 70 67 63 59 56 52 1 30 128 125 121 118 114 t10 128 125 121 118 115 111 12 4 11 8 1 t 3 10 7 10 2 9 6 9 1 t 1 8 11 3 10 8 10 2 9 7 9 2 72 68 64 61 57 53 49 68 64 6...

Page 130: ...5 121 118 115 13 5 t2 8 12 O 11 3 10 6 13 8 13 0 12 3 11 6 1tì o 10 3 13 2 12 5 11 9 11 2 10 6 10 0 12 6 11 9 11 3 10 7 10 2 9 6 12 O 11 4 10 8 10 3 9 7 öz 78 73 Âa 64 60 79 75 71 oo 62 A 72 68 64 60 56 72 68 65 61 57 53 69 65 61 58 c 1 39 135 132 129 124 121 136 133 130 126 123 119 1U 131 128 124 121 116 132 129 125 122 118 114 129 125 122 118 115 13 ö 13 0 12 3 11 6 10 9 10 3 13 3 12 6 11 9 11 2...

Page 131: ... 110 13 2 12 4 11 7 10 9 10 3 12 7 12 0 11 3 10 6 10 0 12 2 11 5 10 9 10 3 9 7 11 6 11 0 10 4 9 9 9 3 11 1 10 5 10 0 9 5 8 9 76 71 67 62 57 73 68 64 60 55 70 oo 62 57 53 ÞÞ 63 59 bb 51 63 59 56 52 48 136 133 128 125 120 134 130 127 122 118 132 t28 124 120 116 128 125 12 l t17 113 126 122 118 114 109 12 7 12 O 11 3 10 6 10 0 12 2 11 6 10 9 10 3 9 7 11 8 1 t 2 10 6 10 0 9 4 11 3 10 7 10 1 9 6 9 0 10...

Page 132: ...19 130 126 122 117 127 124 119 115 125 12 l 117 112 122 118 114 12 O 11 3 10 6 9 9 11 6 10 9 10 3 9 6 11 2 10 6 9 9 9 3 10 7 10 1 9 5 9 0 10 3 9 7 9 1 69 64 59 55 66 62 57 53 64 59 55 51 60 56 52 48 57 54 50 133 129 t24 119 131 126 122 1 t7 128 124 120 114 125 121 116 111 122 118 113 1 1 6 10 9 10 3 9 6 11 2 10 6 9 9 9 3 10 8 10 2 9 6 9 0 10 4 9 8 9 3 8 7 9 9 9 4 8 9 66 62 57 53 64 60 55 51 61 57 ...

Page 133: ... 59 66 62 57 64 59 55 60 56 52 57 53 49 132 128 123 130 126 121 128 123 119 125 120 115 t21 117 112 11 6 10 9 10 2 11 2 10 6 9 9 10 8 10 2 9 6 10 4 9 8 9 2 9 9 9 4 8 8 66 62 57 64 59 55 61 57 53 58 54 50 55 51 48 133 128 123 131 126 121 128 124 118 125 120 114 122 116 110 t1 2 10 ô 9 9 10 9 10 2 9 6 10 5 9 9 9 3 10 1 9 5 8 9 9 6 9 1 8 6 62 57 53 59 55 51 56 52 48 53 50 46 64 59 55 133 128 123 131 ...

Page 134: ...PH 2400 2300 2200 2100 2000 18 17 16 18 17 16 18 17 18 17 18 61 56 51 59 54 49 57 52 54 49 51 127 122 116 125 120 113 123 117 119 113 115 10 5 9 8 9 1 10 2 9 5 8 8 9 8 9 2 9 4 8 9 9 1 59 54 49 57 52 48 54 50 52 48 49 t28 121 114 125 119 111 122 115 118 112 114 10 2 9 5 8 8 9 9 9 2 8 6 9 5 8 9 9 2 8 6 8 8 57 52 48 55 50 46 52 48 50 46 47 127 120 112 124 117 107 121 114 116 108 111 9 9 9 2 8 6 9 6 9...

Page 135: ...STANDARD TEMF 33 C STANDARD TEMPERATURE 13 C 2O C ABOVE STANDARD TEMF 7 C BHP KTAS GPH o BHP KTAS GPH BHP KTAS GPH 2400 2300 2200 21 00 16 15 16 16 16 53 48 51 49 47 120 112 117 114 110 9 4 8 7 9 1 8 8 8 5 51 46 49 47 45 118 109 115 111 105 9 1 8 4 8 8 8 6 8 2 49 45 48 46 43 116 104 111 107 103 8 8 8 2 8 6 8 3 8 0 5 30 Figure 5 9 Cruise Performance Sheet 10 of 10 Nov 15 00 ...

Page 136: ... Cruise Standard TemDerature Zero Wind NOTE This chart allows for the fuel used for engine start taxi takeoff and climb cruise al the designated power and the time during a normal climb up to 10 000 feet and maximum climb above 10 000 feet 14 000 12 000 10 000 8000 6000 4000 2000 550 600 650 700 RANGE NAUTICAL MILES t uJ Lll LL I t o f l F J Feb 3 97 Figure 5 10 Range Profile Sheet 1 oÍ 2 5 31 ...

Page 137: ...art 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 to 10 000 feet and maximum climb above 10 000 feet t uJ fl aooo t 3 oooo t 5 4ooo 2000 700 750 800 850 900 950 1000 RANGE NAUTICAL MILES 124 fiAS 1 fi l îö6 KTA lÈ 20 fiAS ffi 37 fAs f I __ L _ s E i i _ i _l t C ia ñ 8 îÁ lx 81 irl às lPl 129 KTAS 122 ll fA 112...

Page 138: ...ature Zero Wind NOTE 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 to 10 000 feet and maximum climb above 10 000 feet 14 000 12 000 10 000 2000 34567 ENDURANCE HOURS o785c1oos Figure 5 11 Endurance Prof le Sheet 1 ol 2 8000 l Lrl LrJ I eooo uJ o l F F 4000 J S L if l il fr t trt fI o s lc l 3 8 s 3 _...

Page 139: ...ure for Cruise Standard Temperature Zero Wind the fuel used for enqine start taxi takeoff and climb ted power and the ime during a normal climb up to mum climb above 10 000 feet 14 000 12 000 10 000 2000 S L ü eooo tu LL I S oooo l F tr t ooo f 9 i i4 i f i eCE TJJ ct Lr 3 î II I Ç o ò ò lf t o F il o 56789 ENDURANCE HOURS 0785C1 006 Figure 5 11 Endurance Profile Sheet 2 ol 2 5 34 Feb 3 97 ...

Page 140: ... Figure 5 12 Short Field Landing Distance Press Att ln Feet 0 c 10 c 20 c 30 c 40 c Grnd Roll Ft Total Ft To Clear 50 Ft Obst Grnd Roll Ft l otal t To llear i0 Ft fbst Grnd Roll Ft l otal t To llear t0 Fr bst Grnd Roll Ft fotal Ft To Slear r0 Ft Cbst Grnd Roll Ft Total Ft To Clear 50 Fr Obst S L 1000 2000 3000 4000 5000 6000 7000 8000 560 580 600 625 650 670 700 725 755 1 300 1 265 1370 1410 1450 ...

Page 141: ......

Page 142: ...BALANCE EQUIPMENT LIST SECTION 6 WEIGHT BALANCEI EQUIPMENT LIST TABLE OF CONTENTS lntroduction Airplane Weighing Procedures Weight And Balance Baggage Tie Down Comprehensive Equipment List Page 6 3 6 3 6 5 6 7 6 17 Dec 1197 6 1 6 2 blank ...

Page 143: ......

Page 144: ...CEDURES 1 Preparation a lnflate tires to recommended operating pressures b Defuel airplane Refer to Modèl 182S Series 1996 and On l Maintenance Manual c Service engine oil as requíred to obtain a normal full_ indication 8 quarts on dipstick I d Move sliding seats to the most forward position e Raise flaps to the fully retracted position f Place allcontrolsurfaces in neutral position g Remove all n...

Page 145: ...00 350 400 FUSELAGE STATION FS INCHES MEASURING A AND B tNG HAilDAOOK IISIRUCnOXS fO A9 stsf n LocAîilo oo vYITH NhPLÄNE WEIGIG ON I fl II O GEAF LOCATNG CG WÍI I AIRPLANE ON LANDING GEAR FORMULA for Longlh dhsl CG m _ rar Noæ r Nel Welghl x B f Noseand hh l ndhC Oarwelghl Totaled LOCATING PERCENT MAC FORMUI A lor Peent lrAC cc percenr MAc cG ami llllPlane 25 98 07851022 Flgure 6 1 Airplane Weighi...

Page 146: ... AND BALANCE The following information will enable you to operate your Cessna within the prescribed weight and center of gravity limitations To determine weight and bdänce use the Samþte Lôading Problem I Loading Graph and Center of Gravity Moment Envelope as follows Take the basic empty weight and moment from appropriate weight and balance records carried in your airplane and enter them in the co...

Page 147: ...GHT AND BAI ANCE o H I m l t luz cD f o E õ o I le a qt 3 E o fP o J It 5 o D 9 qt f o o Ð o C o a o f oo cr EE o AIRPI ANE MODEL SERIAL NO IPAGE NUMBER DATE ITEM NO DESCRIPTION OF ARTICLE OR MODIFICATION WEIGHT CHANGE RUNNING ASIC EMPTY WEIGHT ADDED REMOVED G N OUT wT LB ARM tN ilOì EM 1000 ARM tN MOMEM 1 000 WT LB MOMEI n000 S DELIVERED ...

Page 148: ...tandard equipment to secure baggage in the area aft of the rear seat baggage areas A B and C Eight eyebolts serve as attaching points for the net A placard on 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 eyebolts just aft of the baggage door and the...

Page 149: ...rt areas are carried the installation of a 1 4 plywood floor is recommended to protect the airplane structure The maximum rated load weight capacity for each of the ten tie downs is 140 pounds Rope strap or cable used for tie down should be rated at a minimum of ten times the load weight capacity of the tie down fittings used Weight and balance calculations for items in the area of tlte rear seat ...

Page 150: ...for average occupant Numbèrs in parentheses indicate torward and aft limits of occupant center of gravity range Arms measured to the center of the areas shown NOTES 1 The usable fuel C G arm is located at station 46 5 2 The aft baggage wall approximate stat on 1 34 can be used as a conveneñÏen t interioì idference point for determ n ng the location of baggage area fuselage stat ons Feb 3 97 Figure...

Page 151: ...CABIN HEIGHT MEASUREMENTS AFT BAGGAGE AREA 07851 01 I Figure 6 4 lnternal Cabin Dimensions Sheet l ot 2 t3 _L I I FIREWALL DOOR OPENING DIMENSIONS WIDTH roP WIDTH BorroM HEIGHT FRONÐ HEIGHT REAR CABIN DOORS BAGGAGE DOOR 32 15 36å 1 5 41 22 38 20 6 10 Nov 15 00 ...

Page 152: ...MEASUREMENTS EAR DOORPOST BULKHEAD R NGS 10 t l I I I i o olo u o u l f t b t c41t 4 o42 x36 I I I 0 10 20 CABIN STATIONS c G ARMS 6 11 t i4L t 91 65 3 WIDTH CODE LEGEND o LOWER WINDOW LINE x CABIN FLOOR 07851 020 Figure 6 4 lnternal Cabin Dimensions Sheet 2 ol2 Feb 3 97 ...

Page 153: ...Gal 88 Gallons Maximum 528 24 6 Beduced Fuel 65 Gallons 3 HilOl ano Fronl Fassenger Station 32 to 50 340 12 6 4 SecondRowPassengers 200 148 Cargo Replacing Second Row Seats Sta 651o 82 5 Baggage Area A Station 82 to 109 120 Lbs Max 100 97 6 Baggage Area B Station 109 To 124 80 Lbs Max 17 17 7 Baooaqe Area C Station 124 ro 154 ðo los vai 8 RAMPWEIGHTANDMOMENT 3110 135 3 L Fuel allowance tor enoine ...

Page 154: ...E EQUIPMENT LIST 6 13 YOUR AIRPLANE YOUR AIRPLANE YOUR AIRPLANE configurations are representative of your useful to fill out one or more of the above columns so are available at a qlance Feb 3197 Figure 6 5 Sample Loading Problem Sheet 2 oÍ 2 ...

Page 155: ... 150 100 50 LOAD MOMENT 1 000 KILOGRAM MILLIMETERS 0 50 100 150 200 250 300 350 400 oo 51015202530 LOAD MOMENT 1000 POUND NCHES 6 fE CI o J Y E o uJ o o J 200 175 150 125 100 75 50 25 NOTE Pilot and front able seats r to the Loading limits of occupant c G range 0785C1008 6 14 Figure 6 6 Loading Graph Feb 3 97 ...

Page 156: ... 1400 1 350 55 65 75 85 95 105 115 125 135 145 LOADED AIRPLANE MOMENT 1 OOO POUND TNCHES 0785c1 009 Figure 6 7 Center of Gravity Moment Envelope 31 00 3000 2950 2900 8 ttoo z f 327o0 I 2600 g Ë 2500 2z oo f ft zsoo fi 2200 o zroo J 2000 1 900 1 800 Ø fr o o J g t I g rJ IIJ z J À fr o UJ o o J 300 250 200 150 100 050 000 Feb 3197 6 15 ...

Page 157: ...00 AIRPLANE C G LOCATION MTLLIMETERS AFT OF DATUM STA 0 0 10 00 1050 11p0 11þ0 12po 1 34 36 38 40 42 44 46 48 50 AIRPLANE C G LOCATION TNoHES AFT OF DATUM STA o o 0785C1010 Figure 6 8 Center of Gravity Limits 6 E CI o J 3 t T g Lll trJ z J fL É o trJ o o J 350 300 250 200 150 100 050 000 lrJ zroo 9 2000 1 900 1 900 Ht 32 6 16 Feb 3 97 ...

Page 158: ... O optional equipment tems replacing required or standard items A optional equipment items which are in addition to required or standard tems ln the EQUIPMENT LIST DESCRIPTION column each item is assigned a descriptive name to help identify its function ln the REF DRAWING column a Cessna drawing number is provided which corresponds to the item NOTE lf additionâl equipment is to be instâlled it mus...

Page 159: ...3 COMMUNICATIONS STATIC DISCHARGE WICKS SET OF 1O NAV COM 1 INSTALLATION KX 15sA NAV COM with GS KI 2O9A CDI INDICATOR CI128A VHF COMM ANTENNA 1 HARDWARE AND CABLE ASSEMBLY NAV COM 2 INSTALLATION KX 1554 NAV COM no GS Kt 208 CDt ND CATOR CI128A VHF COMM ANTENNA 2 ANTENNA COUPLEB HARDWARE AND CABLE ASSEMBLY AUDIO INTERCOM MARKER BEACON INSTL KMA 26 AUDIO PANEL 704056 505087 9 I 205085 1900007 1 65 ...

Page 160: ...BELT AND SHOULDER HARNESS INERTIA REEL PILOT AND COPILOT SEAT BELT AND SHOULDER HARNESS MANUAL ADJUST PILOT AND COPILOT SEAT BELT AND SHOULDEH HARNESS INERTIA REEL REAH SEAT SEAT BELT AND SHOULDER HARNESS MANUAL ADJUST REAR SEAT SUN VISORS SET OF 2 BAGGAGE RETAINING NET CARGO TIE DOWN RINGS SET OF 1O PILOT S OPERATING CHECKLIST ISTOWED IN INSTRUMENT PANEL MAP CASE PILOT S OPERATING HANDBOOK AND FA...

Page 161: ... ASSY EACH BRAKE ASSY EACH TrRE EACH TUBE EACH WHEEL AND TIRE ASSY 5 OO X 5 NOSE WHEELASSY TIRE TUBE WHEEL FAIRING AND INSTALLATION NOSE WHEEL FAIRING MAIN WHEEL FAIRINGS SET OF 2 BRAKE FAIRINGS SET OF 2 MOUNTING PLATE SETOF2 2107 1 50101 9 1 ì940409 1 ì000 1 1 ì003 45 1940409 1 501 01 1 2 1421 001 0201 421001 0202 706010 1 713377 2 760650 3 i331 7 3 1 00 00 3 v8038 2 0 28UrB 3664503 01 03 30 4400...

Page 162: ...ADF ANTENNA ADF CABLE ASSEMBLY GPS INSTALLATION KLN 898 GPS RECEIVER GPS ANTENNA GPS CABLE ASSEMBLY MODE C TRANSPONDEF INSTL KT76C TRANSPONDER TRANSPONDER ANTENNA HARDWARE AND CABLE ASSEMBLY HORIZONTAL SITUATION INDICATOR NET TNcREASE RQS 22 02 O AUTOPTLOT GYRO SLAVING METER FLUX DETECTOR INSTL IN LH WING NAVCONVERTER INSTL SLAVED GYRO FOR HSI IN TAILCONE GYRO SYSTEM FOR HSI 170601 0 1 170061 s 1 ...

Page 163: ...BLY 2 BLADE MCCAULEY 82D34C235 9ODKB 8 SPINNER INSTALLATION 2 BLADE GOVERNOR PROPELLER PROPELLER ASSEMBLY 3 BLADE MCCAULEY 83D36C431 8OVSA 1 SPINNER INSTALLATION 3 BLADE 71 POWERPLANT FILTER AIR INTAKE WINTER KIT INSTL 72 ENGINES ENGINE LYCOMING IO 540 AB1A5 73 ENGINE FUEL and CONTROL EGT and CYLINDER HEAD TEMP INDICATOR 77 ENGINE INDICATING TACHOMETER INSTALLATION RECORDING MANIFOLD PRESSURE FUEL...

Page 164: ...M KLN 89 GPS VFR MD 41 230 GPS NAV SELECTOR KMA 26 AUDIO INTERCOM MARKER BEACON INSTALLATION KT 76C MODE C TRANSPONDER KAP 140 SINGLE AXIS AUTOPILOT BASIC AVIONICS KIT INSTL OPTIONAL NAV IAVIONICS PACKAGE STANDARD AVIONICS PACKAGE PLUS THE FOLLOWINGJ NET CHANGE KLN 898 GPS FR EXCHANGE GPS NAV SELECTOR ANNUNCIATOR EXCHANGE KR 87 ADF SYSTEM KAP I40 TWO AXIS AUTOPILOT WITH ELECTRIC TRIM EXCHANGE t0R ...

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Page 166: ... Control Wing Flap System Landing Gear System Baggage Compailment Seats lntegraled Seat BelVShoulder Harness Entrance Doors And Cabin Windows ControlLocks Engine Engine Controls Engine lnstruments New Engine Break ln And Operation Engine Lubrication System lgnition And Starter System 7 22 Page 7 5 7 5 7 6 7 6 7 6 7 9 7 9 7 12 7 12 7 12 7 13 7 14 7 14 7 14 7 15 7 171 7 18 7 1 sl 7 19 7 19 7 211 7 2...

Page 167: ...d lndicator Vertical Speed lndicator Altimeter l CESSNA MODEL 182S TABLE OF CONTENTS Continued Page Propeller 7 24 FuelSystem 7 25 Fuel Distribution 7 25 Fuel lndicating System 7 27 Auxiliary Fuel Pump Operation 7 28 FuelVenting 7 28 Fuel Selector Valve 7 28 Fuel Drain Valves 7 29 BrakeSystem 7 32 Electricalsystem 7 32 Annunciator Panel 7 33 Master Switch 7 34 Avionics Master Switch 7 35 Ammeter 7...

Page 168: ...uge Low Vacuum Annunciation Clock O A T lndicator StallWarning System Standard Avionics Avionics Support Equipment Avionics Cooling Fan Microphone And Headset lnstallations Static Dischargers Cabin Features Emergency Locator Transm itter Cabin Fire Extinguisher Page 7 44 7 44 7 44 7 461 7 46 7 471 7 47 7 48 7 49 7 45 7 49 7 50 7 50 7 50 7 51 Nov 15 00 7 3 7 4 blank ...

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Page 170: ...ign referred to as The externally braced wings containing integral fuel tanks are constructed of a front and rear spar with formed sheet metal ribs The empennage tail assembly consists of a conventional vertical stabilizer rudder horizontal stabilizer and elevator The vertical stabilizer consists of a forward and aft spar formed sheet metal ribs and reinforcements four skin panels formed leading e...

Page 171: ...control system is which proiide improved stáoitity in flight TRIM SYSTEMS rotation will trim nose up INSTRUMENT PANEL The instrument panel Refer to Figure 7 2 is of all metal construction and is designed in segments to allow related groups of instruments switches and controls to be removed without removing the entire panel For specific details concerning the instruments switches circuit breakers a...

Page 172: ...SNA MODEL 182S SECTION 7 AIRPLANE SYSTEMS DESCRIPTION AILEHON CONTROL SYSTEM RUDDER AND RUDDER TRIM CONTROL SYSTEMS 07851 01 7 07851 023 Figure 7 1 Flight Control and Trim Systems Sheet 1 oÍ 2 Feb 3 97 7 7 ...

Page 173: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTION CESSNA MODEL 182S g33l3l Figure 7 1 Flight Control and Trim Systems Sheet 2 of 2 ELEVATOR CONTROL SYSTEM ELEVATOR TRIM CONTROL SYSTEM 7 8 Feb 3 97 ...

Page 174: ... which contains a fuel quantity indicator an oil temperature oil pressure indicator al vacuum gauge ammeter an EGT CHT indicator a cloct OATI indicator and manifold pressure gauge fuelflow indicator I Below the engine and flight instruments are the circuit breakers and switches used throughout the airplane MASTER AVIONICSI MASTER the ignition switches and lighting controls are located inl this are...

Page 175: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTION 57 911 CESSNA MODEL 182S 13 17 18 19 20 Zt 31 28 27 6 25 43 24 32 40 41 7 10 Figure 7 2 lnstrument Panel Sheet 1 of 2 Feb 3 97 ...

Page 176: ...ntrol 10 Tachometer 32 Glareshield and Pedestal Dimming Control 1 1 Vertical Speed lndicator 33 Fuel Selector 12 Altimeter 34 Elevator Trim and lndicator 13 Annunciator Panel 35 Avionics Master Switch 14 ADF Bearing lndicator 36 Gircuit Breakers and Switch Breakers 15 Course Deviation and 37 Master Switch Glide Slope Indicators 16 Audio Control Panel 38 Ignition Switch 17 GPS Receiver 39 Avionics ...

Page 177: ...d to the nose gear and to the rudder bars will turn the nose wheel through an arc of approximately 11 each side of center By applying either left or right brake the degree of turn may be increased up to 29 each side of center Moving the airplane by hand ís most easily accomplished by attaching a tow bar to the nose gear strut lf a tow bar is not available or pushing is required use the wing struts...

Page 178: ...WING FLAP SYSTEM CESSNA MODEL 182S SECTION 7 AIRPLANE SYSTEMS DESCRIPTION Nov 15 00 Figure 7 3 Wing Flap System 7 13 ...

Page 179: ... For baggage area and door dimensions refer to Section 6 SEATS The seating arrangement consists of two vertically adjusting crew seats for the pilot and front seat passenger and an infinitely adjustable split back bench seat for rear seat passengers Seats used for the pilot and front seat passenger are adjustable fore and aft and up and down Additionally the angle of the seat back is infinitely ad...

Page 180: ...positive restraint for the user ln the front seats the inertia reels are located on the centerline of the upper cabin area ln the rear seats the inertia reels are located outboard of each passenger in the upper cabin To use the integrated seat belVshoulder harness grasp the link with one hand and in a single motion extend the assembly and insert into the buckle PosÍive locking has occurred wh en a...

Page 181: ...CESSNA MODEL 182S BUCKLE NON ADJUSTABLE LIFT TO RELEASE LATCH 051 4T1 004 PRESS TO Z Ëi iB r N VERTICAL HETGHT ADJUSTMENT CRANK SEAT BACK ANGLE BUTTON FORE AND AFT ADJUSTMENT LEVER î PUSH BUTTON RELEASE Figure 7 4 Crew Seats Seat Belts and Shoulder Harnesses AILABLE MANUAL ADJUSTMENT i t 1 7 16 Nov 15 00 ...

Page 182: ...corporate a recessed exterior door fa dle a conventional interior door handle a key operated door lock left door only a door stop mechanism and oþenable windows in both the left and right doors NOTE The door latch design on this model requires that the outside door handle on the pilot and front passenger doors be extended out whenever the doors are opeh When closing the door do not attempt to push...

Page 183: ...re 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 wind buffeting while the airplane is parked The lock consists of a shaped steel rod and flag The flag identifies the control lock and cautions about its removal before starting the engine To install the control lock align the hol...

Page 184: ... propeller control is a red knob with raised poinis around the circumference and is equipped with a lock button in the end of the knob The rich position is full fonrvard and full aft is the idle cutoff position For small adjustments the control may be moved forward by rotating the knob clockwise and aft by rotating the knob counterclockwise For rapid or large adjustments the knob may be moved forw...

Page 185: ...anges ihe probe resistance changes This resistance is translated into oil temperature readings on the cockpit indicator the OIL PRESS light extinguishes NOTE The low oil pressure switch is also wired into the Hobbs hour meter When pressure exceeds 20 PSl a ground is supplied to the hour meter completing the hour meter circuit I left side of the instrument originating in the engine as temperature p...

Page 186: ... green arc of 15 to 23 ln Hg The fuel flow indicator is a fuel pressure indicator calibrated in flow rate The fuell pressure is taken at the flow divider valve by a pressure transducer The pressure transducer receives a constant voltage from the indicator and returns a variable voltage depending on the pressure as pressure increases voltage increases The indicator is marked in gallons per hour and...

Page 187: ...quipped with a bypass valve which will cause lubricating oil to bypass the filter in the event the filter becomes plugged or the oil temperature is extremely cold An oil dipstick filler tube is located on the upper left side of the engine case The dipstick and oil filler tube are accessed through a door located on the left center portion of the upper engine cowling The engine should not be operate...

Page 188: ...induction air enters a fuel air control unit ùnder tñe engine and is then ducted to the engine cylinders through intake manifold tubes EXHAUST SYSTEM Exhaust gas from each cylinder passes through riser assemblies to a muffler and tailpipe Outside air is pulled ln around shrouds which are constructed around the outsidè of the mufflers to form heating chambers which supply heat to the cabin COOLING ...

Page 189: ...ine oil boosted to high pressure by the governing pump to or from a piston in the propeller hub Oil pressure acting on the piston twists the blades toward high pitch low RPM When oil pressure to the piston in the propeller hub is relieved centrifugal force assisted by an internal spring twists the blades toward low pitch high RPM A control knob on the center area of the switch and control panel is...

Page 190: ...UNUSABLE FUEL LEVELS FOR THIS AIRPLANE WERE DETERMINED IN ACCORDANCE WITH FEDERAL AVIATION REGULATIONS FAILURE TO OPERATE THE AIRPLANE IN COMPLIANCE WITH FUEL LIMITATIONS SPECIFIED IN SECTION 2 MAY FURTHER REDUCE THE AMOUNT OF FUEL AVA LABLE tN FLIGHT FUEL TANKS FUEL LEVEL QUANT TY EACH TANK TOTAL FUEL TOTAL UNUSABLE TOTAL USABLE ALL FLIGHT CONDITIONS Two Full 46 0 92 O 4 O 88 0 Two Reduced 34 5 6...

Page 191: ...IGHT FUEL TANK VENT WITH CHECK VALVE THROTTLE CONTROL CAPACITY STANDPIPE LEFT FUEL TANK VENT WITH CHECK VALVE DRAIN VALVE 5 TOTAL FUEL SELECTOR VALVE DRAIN PLUG FUEL PUMP SWITCH FUEL FUEL STRAINER DRAIN AUXILIARY FUEL PUMP ENGINE DRIVEN FUEL PUMP MIXTURE CoNTROL o 0785C1 007 ì CODE FUEL SUPPLY VENT MECHANICAL LINKAGE ELECTRICAL CONNECTION TO ENGINE 7 26 Figure 7 6 Fuel System Schematic Dec 1197 ...

Page 192: ... these conditions the fuel level indicator needle will go to the OFF position below the O mark on the fuel gauge and the amber annunciator will illuminate lf the left tankl transmitter has failed the message will read L LOW FUEL lf the lght tank transmitter has failed tñe message will read LOW FUEL R lf both tanks transmitters have failed tñe message will read L LOW FUEL R CESSNA MODEL 182S SECTIO...

Page 193: ...t necessary to have the auxiliary fuel pump operating Íng normal takeotf and landing since gravity and the engine en pump will supply adequate fuel flow to the fuel injector unit the event of failure of the engine driven fuel pump use of the fuel pump will provide sufficient fuel to maintain flight at rcontinuous power FUEL VENTING Fuel system venting is essential to system operation Blockage of t...

Page 194: ...tem However with 1 4 tank or less prolonged uncoordinated flight such as slips or skids can uncover the fuel tank 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 The fuel system is equipped with drain valves to provide a means for the examination of...

Page 195: ... SYSTEMS DESCRIPTION LOW VOLT FIELD I enou o SENSE I PoWER lN ALT INPUT CESSNA MODEL 182S 1r i STARTER I REB EXTERNAL POWER TO ALT FLD CIRCUIT BREAKER 0s85C2001 7 30 Figure 7 7 Electrical Schematic Sheet 1 ol2l Nov 15 00 ...

Page 196: ...RO 5 TO AUTO PtLOT 4 5 TO TRANSPONDER TO ADF 2 3 4 6 A TO MASTER SWITCH AVIONICS MASTER SWITCH TF TO AVIONICS FAN TO GPS 2 3 4 5 O TO NAV COMI ñnv HEADSET PWR NAV t1trAuùtr I I VVH COM1 SPEAKER PWR 1 MKR BCN RCVR 1 TO STROBE TO AUTOPILOT 3 LIGHTS TO TAXI LIGHTS O ro ADF 5 TO PITOT HEAT NAV I NAV II NAV II WITH 2 AXIS AP NAV II WITH HSI II AXIS OR 2 AXIS 0585C2001 U m J o F o LrJ E Nov 15 00 Figure...

Page 197: ...nd rotate it 90o down For maximum brake life keep the brake system properly maintained and minimize brake usage during taxi operations and landings the pedals and then reaPPlY the brakes become spongy or Pedal ls should build braking Pressure s use the other brake sParinglY while using opposite rudder as required to offset the good brake ELECTRICAL SYSTEM SECTION 7 AIRPLANE SYSTEMS DESCRIPTION CES...

Page 198: ...se all relays used throughout the airplane electrical system ln addition the alternator control unit and lhe external power connector are housed within the module ANNUNCIATOR PANEL An annunciator panel with integral toggle switch is located above the avionics stack and provides caution amber and warning red messages for selected portions of the airplane systems The annunciator is designed to flash...

Page 199: ...the switch is released MASTER SWITCH I The master switch is a split rocker type switch labeled MASTER and is ON in the up position and otf in the down position The right half of the switch labeled BAT controls all electrical power to the airplane The left half labeled ALT controls the alternator cnunon PRIOR TO TURNING THE MASTER SWITCH ON OR OFF STARTING THE ENGINE OR APPLYING AN EXTERNAL POWER S...

Page 200: ...ess of the position of the master switch or the individual equipment switches The avionics master switch should be placed in the OFF position prior to turning the master switch on or off starting Ìhe engine or applying an external power source Each avionics bus also incorporates a separate circuit breaker installed between the primary bus and the avionics master switch ln the event of an electrica...

Page 201: ...control unit may be reset by resetting the circuit breaker lf the warning light extinguishes normal alternator charging has resumed however if the light illuminates again a malfunction has occurred and the flight should be terminated as soon as practicable NOTE lllumination of the low voltage light and ammeter discharge indications may occur during low RPM conditions with an electrical load on the...

Page 202: ... taxi and tanding lights turned on 5 Engine RPM INCREASE to approximatety 1S0O RpM 6 Ammeter and Low Voltage Annunciator CHECK sEcTtoN 7 AIRPLANE SYSTEMS DESCRIPTION GROUND SERVICE PLUG RECEPTACLE used to avoid performing proper maintenance procedures on a low battery NOTE lf no avionics equipment is to be used or worked on the avionics master switch should be turned off lf maintenance is required...

Page 203: ...lighting radio lighting and pilot controlwheel lighting Flood lighting is accomplished using two lights in the front and a single dome lþht in the rear All lights are contained in the overhead console and are turned on and off with push type switches located near each light The two front lights are individually rotatable providing directional lighting for the pilot and front passenger The rear dom...

Page 204: ...eel lighting is accomplished by use of a rheostat and light assembly located underneath the pilot control wheel yoke The light provides downward illumination from the bottom of the Regardless of the light system in question the most probable cause of a light failure is a burned out bulb However in the event any of the lighting systems fail to illuminate when turned on check the appropriate circuit...

Page 205: ...ll the CABIN HT knob out approximately 1 4 to 1 2 inch for a small amount of cabin heat Additional heat is available by pulling the knob out farther maximum heat is available with the CABIN HT knob pulled out and the CABIN AIR knob pushed full in When no heat is desired in the cabin the CABIN HT knob is pushed full in Front cabin heat and ventilating air is supplied by outlet holes control sliding...

Page 206: ...R VALVE FÂII AIR ù CABIN FLOOR AIR OUTLET FORWARD CABIN LOWER AIR OUTLETS I fl FORWARD I vsåB J AIR OUTLETS REAB CABIN VENTILATING AIR OUTLETS 0785C1014 Figure 7 8 Cabin Heating Ventilating and Defrosting System VENTILATING AIR DOOR HEAT CONTBOL N AIR CONTROL VENTILATING AIR HEATED AIR BLENDED AIR MECHANICAL 7 41 Feb 3 97 ...

Page 207: ...ted wiring The switch breaker is located on the lower left side of the instrument panel When the pitot heat switch is turned on the element in the pitot tube is heated electrically to maintain proper operation in possible icing conditions A static pressure alternate source valve is installed above the throttle and can be used if the external static source is malfunctioning This valve supplies stat...

Page 208: ...ite arc 36 to 100 knots green arc 43 to 140 knots yetlow arc 14O to 175 knots and a red line 175 knots To find true airspeed first determine pressure altitude and outside air temperature Using this data rotate the lower left knob until pressure altitude aligns with outside air temperature in the twelve o clock window True airspeed corrected for pressure and temperature can now be read in the seven...

Page 209: ...relative to the bank scale which has index marks at 10o 20 30o 60 and 90 either side of the center mark Pitch and roll attitudes are presented by a miniature airplane superimposed over a symbolic horizon area divided into two sections by a white horizon bar The upper blue sky area and the lower ground area have pitch reference lines useful for pitch attitude control A knob at the bottom of the ins...

Page 210: ... AIR FILTER sEcïroN 7 AIRPLANE SYSTEMS DESCRIPTION ENGINE DRIVEN VACUUM RELIEF VALVE VACUUM PUMPS LOW VACUUM TRANSDUCERS ooNNECTED TO ANNUNCIATOR PANEL MANIFOLD CHECK VALVE 078sc1 01 3 OVERBOARD ATTITUDE INDICATOR é à úË ù Feb 3197 Figure 7 9 Vacuum System Schematic 7 45 ...

Page 211: ...t and still be adequate for normal system operation LOW VACUUM ANNUNCIATION Each engine driven vacuum pump is plumbed to a common manifold located forward of the firewall From the tee a single line runs into the cabin to operate the various vacuum system instruments This tee contains check valves to prevent back flow into a pump if it fails Transducers are located just upstream of the tee and meas...

Page 212: ... horn at airspeeds between 5 and 10 knots above the stall in allconfigurations The airplane has a heated stall warning system the vane and sensor unit in the wing leading edge is element The heated part of the system HEAT switch and is protected by the PITO The stall warning system should be checked during the pre flight inspectíon by momentarify turning on the mastei switch an actuating the vane ...

Page 213: ...A Nav Com Radio with Glide Slope Kl 208 lndicator Head Kl 209A lndicator Head with GPS lnterface KT 76C Transponder KMA 26 Audio Panel 3000 11 Emergency Locator Transmitter ELT I KLN 898 Global Positioning System GPS f KAP 140 Single Axis Autopilot _ For complete operating instructions on the standard and optional lavionics systems refer to the Supplements Section 9 7 48 Nov 15 00 ...

Page 214: ...cuit breaker The _fan operates anytime the master and avionics mastefl switches are ON MICROPHONE AND HEADSET INSTALLATIONS the airplane includes a hand held peaker two remote keyed microphone wheels and provisiôns for booml nd passenger station I The hand held microphone switch This microphone is plug accessible to both the pilot an push to alk switch allows audio t The overhead speaker is locate...

Page 215: ... is impractical minimize airspeed and anticipate temporary loss of radio signals while in these areas Static dischargers lose their effectiveness with age and therefore should be checked periodically at least at every annual inspection by qualified avionics technicians etc CABIN FEATURES EMERGENCY LOCATOR TRANSMITTER ELT A remote switch annunciator is installed on the top center location of the co...

Page 216: ...r 1 Loosen retaining clamp s and remove extinguisher from bracket 2 Hold extinguisher upright pull operating ring pin and press lever while directing the discharge at the base of the fire at the near edge Progress toward the back of the fire by moving the nozzle rapidly with a side to side sweeping motion wnnnrnc VENTILATE THE CABIN PROMPTLY AFTER SUCCESSFULLY EXTINGUISHING THE F RE TO REDUCE THE ...

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Page 218: ...ted States Airplane Owners I nternational Airplane Owners Publications Airplane File Airplane lnspection Periods FAA Required lnspections Gessna I nspection Programs Cessna Customer Care Program Pilot Conducted Preventive Maintenance Alterations Or Repairs Ground Handling Towing Parking Tie Down Jacking Leveling Flyable Storage Servicing oit Oil Specification Recommended Viscosity for Temperature ...

Page 219: ...r Change Fuel CESSNA MODEL 182S Page 8 14 8 14 8 15 8 1 5 8 1 6 8 16 Approved FuelGrades and Colors FuelCapacity FuelAdditives Fuel Contamination Landing Gear Cleaning And Care Windshield And Windows Painted SuÍaces Propeller Care Engine Care lnterior Care 8 20 8 21 8 21 8 21 8 22 8 23 8 23 8 24 8 2 Nov 15 00 ...

Page 220: ...hanges are necessary as well as other seasonal and periodic seruices The airplane should be regularly inspected and maintained in accordance with information found in lhe airplane maintenance manual and in company issued service bulletins and service newsletters All service bulletins peñaining to the aircraft by serial number should be accomplished and the airplane should receive repetitive and re...

Page 221: ... Located adjacent to the secondary lldentification Plate is the Finish and Trim Plate which contains a code describing the exterior paint combination of the airplane The code may be used in conjunction with an applicable lllustrated Parts Catalog if finish and trim information is needed CESSNA OWNER ADVISORIES Cessna Owner Advisories are sent to Cessna Aircraft FAA Registered owners of record at n...

Page 222: ...ies please complete and return an Owner Advisory Application Receipt of a valid Owner Advisory Application will establish yourr Cessna Owner Advisory service for one year after which you will be I sent a renewal notice lt is important that you respond promptly to update your address for this critical service PUBLICATIONS Various publications and flight operation aids are furnished in the airplane ...

Page 223: ...can place an order for any item which is not in stock NOTE A Pilot s Operating Handbook and FAA Approved Airplane Flight Manual which is lost or destroyed may be replaced by I contacting your local Cessna Service Station An affidavit AIRPLANE FILE There are miscellaneous data information and licenses that are a part of the airplane file The following is a checklist for that file ln addition a peri...

Page 224: ...ents Cessna recommends that these items plus the Pilot s Checklists Customer Care Program Handbook and Customer Care Card be carried in the airplane at alltimes AIRPLANE INSPECTION PERIODS FAA REOUIRED INSPECTIONS As required by U S Federal Aviation Regulations all civil aircraft of U S registry must undergo a complete inspection annual each twelve calendar months ln addition to the required annua...

Page 225: ... hours whichever occurs first the airplane undergoes a complete Phase 3 inspection Regardless of the inspection method selected the owner should keep in mind that FAR Part 43 and FAR Part 91 establishes the requirement that properly certified agencies or personnel accomplish all required FAA inspections and most of the manufacturer recommended inspections CESSNA CUSTOMER CARE PROGRAM Specific bene...

Page 226: ...aintenance that may be performed by pilots A Maintenance Manual must be obtained prior to performing any preventive maintenance to ensure that proper procedures are followed Your Cessna Seruice Station should be contacted for further information or for required maintenance which must be accomplished by appropriately licensed personnel ALTERATIONS OR REPAIRS It is essential that the FAA be contacte...

Page 227: ...lated strut will also increase tail height PARKING When parking the airplane head into the wind and set the lparking brake Do not set the parking brake during cold weather when accumulated moisture may freeze the brakes or when the brakes are overheated lnstall the control wheel lock and chock the wheels ln severe weather and high wind conditions tie the airplane down as outlined in the following ...

Page 228: ...HE ELEVATOR OR HORIZONTAL STABILIZER SURFACES WHEN PUSHING ON THE TAILCONE ALWAYS APPLY PRESSURE AT A BULKHEAD TO AVOID BUCKLING THE SKIN aintenance is required the nose wheel may be nd by pressing down on a tailcone bulkhead just izontal stabilizer and allowing the tail to rest on g To assist in raising and holding the nose wheel off the grouno ground anchors should be utilized at the tail tie do...

Page 229: ...airplane should be flown for 30 minutes or a ground runup should be made just long enough to produce an oil temperature within the lower green arc range Excessive ground runup should be avoided Engine runup also helps to eliminate excessive accumulations of water in the fuel system and other air spaces in the engine Keep fuel tanks full to minimize condensation in the tanks Keep the battery fully ...

Page 230: ...e regulatory requirements owners should check with local aviation officials where the airplane is being operated For quick and ready reference quantities materials and specifications for frequently used service items are as follows orL OIL SPECIFICATION MIL L 6082 Aviation Grade Straight Mineral Oil Used when the airplane was delivered from the factory and should be used to replenish the supply du...

Page 231: ... 15W 50 or 20W 50 CAPACITY OF ENGINE SUMP The engine has a total capacity of 9 quarts with the oil filter accounting for approximately one quart of that total The engine oil sump has a capacity of 8 quarts The engine must not be operated on less than 4 quarts as measured by the dipstick For extended flights the engine should be filled to capacity OIL AND OIL FILTER CHANGE After the first 25 hours ...

Page 232: ...d evidence of wear lnspect wiring for secur ty chafing burning defective insulation loose or broken terminals heat deterioration and corroded terminals Check the alternator belt in accordance with Maintenance Manual instructions and retighten if necessary A periodic check of these items during subsequent servicing operations is recommended FUEL APPROVED FUEL GRADES AND COLORS 100LL Grade Aviation ...

Page 233: ...n Section 4 will eliminate any free water accumulations from the tank sumps While small amounts of water may still remain in solution in the gasoline it will normally be consumed and go unnoticed in the operation of the engine and freeze in sufficient quantities to induce partial icing of the engine fuel system While these conditions are quite rare and will not normally pose a problem to owners an...

Page 234: ...lons of fuel which now reside in the tank Alcohol if used is to be blended with the fuel in a concentration of 1o by volume Concentrations greater than 1o o are not recommended since they can be detrimentalto fueltank materials The manner in which the alcohol is added to the fuel is significant because alcohol is most effective when it is completely dissolved in the fuel To ensure proper mixing th...

Page 235: ...SECTION 8 HANDLING SERVICE MAINTENANCE CESSNA MODEL 182S 50 ul t o o lL o ct tIl 9go f o o 5 d20 10 20 30 40 GALLONS OF GASOLINE l Figure 8 1 Fuel Mixing Ratio Nov 15 00 ...

Page 236: ...E 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 M N MUM W LL RESULT tN INEFFECTIVE TREATMENT USE ONLY BLENDING EOUIPMENT THAT IS RECOMMENDED BY THE MANUFACTURER TO OBTAIN PROPER PROPORTIONING Prolonged storage of the airplane will result in a water buildup in the fuel which leec...

Page 237: ...ld be drained and system purged by qualified maintenance personnel All evidence of contamination must be removed before further flight lf the airplane has been seruiced with the improper fuel grade defuel completely and refuel with the correct grade Do not fly the airplane with contaminated or unapproved fuel ln addition Owners Operators who are not acquainted with a particular fixed base operator...

Page 238: ...late CLEANING AND CARE WINDSHIELD AND WINDOWS The plastic windshield and windows should be cleaned with an aircraft windshield cleaner Apply the cleaner sparingly with soft cloths and rub with moderate pressure until all dirt oil scum and bug stains are removed Allow the cleaner to dry then wipe it off with soft flannel cloths cnunon NEVER USE GASOLINE BENZENE ALCOHOL ACETONE FIRE EXTINGUISHER ANT...

Page 239: ...ish Generally the painted surfaces can be kept bright by washing with water and mild soap followed by a rinse with water and drying with cloths or a chamois Harsh or abrasive soaps or detergents which cause corrosion or scratches should never be used Remove assure adequate protection Special care should be taken to seal around rivet heads and skin laps which are the areas most n the leading and pr...

Page 240: ...hem occasionally with an oily cloth to clean off grass and bug stains 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 and if ignored may result in cracks or failure of the propeller blade Never use an alkaline cleaner on the blades remove grease and...

Page 241: ...Oily spots may be cleaned with household spot removers L 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 damage the padding and backing materials Soiled upholstery and carpet may be cleaned with foam type detergent used according to the manufacturer s i...

Page 242: ... checklist to ensure all applicable supplements have been placed in the Pilot s Operating Handbook POH Supplements may be removed from the POH provided the equipment is not installed on the airplane lf equipment is installed on the airplane however the supplement s must be retained and updated as revisions to each supplement is issued Each individual supplement contains its own Log of Effective Pa...

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Page 244: ...ONTACTING CESSNA CUSTOMER suPPoRT AT 316 517 5800 SUPP 6 7 I I 10 SUPPLEMENT NAME 1 Bendix King KX 1554 VHF NAV COMM with Kl 208 or Kl209A lndicator Head 2 Bendix King KT 76C Transponder with Blind Encoder 3 Bendix King KMA 26 Audio Selector Panel Pointer Model 3000 11 Emergency Locator Transmitter ELT Bendix King KLN 898 Global Positioning System GPS Bendix King KR 87 Automatic Direction Finder A...

Page 245: ...ix King KCS 554 Slaved Compass System with Kl 5254 Horizontal Situation lndicator HSl 14 ArgentineSupplement 15 Bendix King KAP 140 AutoPilot Serial No 18280165 and on or aircraft modified by MK182 22 01 with altitude preselect 16 Reserued 17 Reserued 18 Reserued I 19 KLN 94 GlobalPositioning system I CESSNA MODEL 182S EOUIPMENT INSTALLED REV LEVEL 3 0 0 0 2 0 1 0 1 LOG 2 Jan 15 01 ...

Page 246: ...ght Manual CESSNA MODEL 182S AIRPLANES 18280001 AND ON SUPPLEMENT 1 BENDIX KING KX 1554 VHF NAV COMM with K 208 or Kl209A INDICATOR HEAD coPYB GHT 1997 CESSNA AIRCRAFT COMPANY WCHITA KANSAS USA 182SPHUS Sr 02 1 vi a rof GAMA 3 February 1997 Revision 2 15 November 2000 s1 1 ...

Page 247: ... 2000 LOG OF EFFECTIVITY PAGES Nov 15 00 S1 9 Feb 3 97 Nov 15 00 51 10 Feb 3 97 Nov 15 00 51 11 Dec 1197 Feb 3197 51 12 Feb 3 97 Feb 3197 51 13 Nov 15 00 Feb 3 97 51 14 Feb 3 97 Feb 3197 51 15 Feb3 97 Nov 15 00 51 16 blank Feb 3197 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into th...

Page 248: ...d localizer signals between 108 00 and 117 95 MHz in 50 kHz steps The glide slope receiver is automatically tuned when a localizer frequency is selected The circuits required to interpret the VOR and localizer signals are also an integral part of the Nav receiver Large selÊdimming gas discharge readouts display both the communications and navigation operating frequencies The KX 1554 s flip flop pr...

Page 249: ...gation course selection are mounted on the front panel of the receiver transmitter Control lighting is provided by NAV COMM interior lighting and the instrument panel flood lighting system Operation añd dèscription of the audio selector panel used in conjunction with this radio is shown and described in Supplement 3 in this section SECTION 9 SUPPLEMENTS SUPPLEMENT 1 FAA APPROVED CESSNA MODEL 182S ...

Page 250: ...OVED 2s KI2O9A INDICATOR 0585C1 045 0585C1046 0585C1047 C ro tNDrcArtoN Q rnou rNDrcATtoN r lie tNDtcAnoN Figure 1 Bendix King KX 1554 VHF NAV COMM with Kt 208 or Kl 2094 lndicator Head Sheet 1 of 7 s1 5 l 1t l f 00 I t1 bD f9 5h 13 t2 rT 10 9 r o 1 18 KI 2OS INDICATOR HEAD Feb 3 97 ...

Page 251: ... CDI FORMAT tug ED FLHE E nl VOR MODE ACTIVE BEARING FI AG DISPLAY tng Eu DlD o VOR MODE ACTIVE BEARING TO FUNCTION DISPLAY ID9 ED TO VOR MODE ACTIVE BEARING FLAG DISPLAY I lD 9t LDr t LOCALIZER MODE FREQUENCY CDI FORMAT Figure 1 Bendix King KX 1554 VHF NAV COMM with Kl 208 or Kl209A lndicator Head Sheel2olT s1 6 Feb 3 97 ...

Page 252: ...adial from the VOR station or a count up count down timer With an active localizer frequency this portion of the display shows the standby frequency the letters LOC or count up count down timer 4 NAV FREQUENCY SELECTOR KNOB SMALL Operates in 50 kHz steps The NAV receiver s lower and upper frequency limits are 108 00 MHz and 117 95 MHz Exceeding the upper limit of frequency band will automatically ...

Page 253: ... inner NAV frequency knob is pulled out The CDI is displayed on the line below the frequency OBS When the ACTIVE window is tuned to a localizer frequency the standby frequency area is replaced by LOC When the received signal is too weak to ensure accuracy the display will FLAG Depressing the mode button again will cause the NAV display to go from the ACTIVE CDI format to the ACTIVE BEARING format ...

Page 254: ...quency lransfer button for 2 seconds or more causing the ET on the display to flash ln this state the timer can be set as a countdown timer or the elapsed timer can be restarted The countdown timer is set by using the NAV frequency inc dec knobs to set the desired time and then pushing the NAV frequency transfer button to start the timer The large knob selects minutes the small knob in the in posi...

Page 255: ...esired channel can be selected by turning the comm kHz knob The channel frequency can be entered by pushing the comm transfer button which will cause the standby frequency to flash The comm frequency knobs are then used to enter the desired frequency lf dashes located between 136 MHz and 118 MHz are entered instead of a frequency the corresponding channel is skipped in channel selection mode Addit...

Page 256: ...nto the display Push the COMM TRANSFER button again to return to the active standby display The transceiver is always tuned to the frequency appearing in the ACTIVE display lt is therefore possible to have two different frequencies stored in the ACTIVE and STANDBY displays and to change back and forth between them at the simple push of the transfer button 13 COMM VOLUME CONTROL OFF PULUTEST Rotate...

Page 257: ...s up with 120 00 MHz in the COMM use frequency and 110 00 MHz in the NAV active frequency with both COMM and NAV in the active entry mode This will aid the pilot in blind tuning the radio SECTION 4 NORMAL PROCEDURES COMMUN ICATION RECEIVER TRANSM ITTER O PERATION 1 OFF PULIJTEST Volume Control Turn clockwise pull out and adjust to desired audio level push control back in to activate the automatic ...

Page 258: ...Speaker Selector on audio control panel SET to desired mode 4 NAV Volume Control a ADJUST to desired audio level b PULL out to identify station VOR OPERATION Channel the NAV Receiver to the desíred VOR and monitor the audio to positively identify the station To select an OBS course turn the OBS knob to set the desired course under the lubber line When a signal is received the NAV flag will pull ou...

Page 259: ... Button When the Pilot Config Mode ís entered the unit will show the SWRV mnemonic which is the unit software revision level Adjustment pages can be accessed by MODE button presses The pilot may adjust two parameters in the pilot configuration the display minimum brightness and sidetone volume level Minimum Brightness BRIM will have a range of 0 255 The dimmest is 0 and the brightest is 255 Sideto...

Page 260: ...configuration mode The NAV returns to its pre Pilot Gonfig state with the new brightness and sidetone levels stored in nonvolatile memory SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or several related antennas will result in a minor reduction in cruise oerformance Feb 3 97 51...

Page 261: ......

Page 262: ...oved Airplane Flight Manual CESSNA MODEL 1825 AIRPLANES 18280001 AND ON SUPPLEMENT 2 BENDIVKING KT 76C TRANSPONDER WITH BLIND ENCODER 1þ Ja a rof GAMA copy rcHr 1ee7 3 Fgbru ary 1997 CESSNA AIRCRAFT COMPANY wrcHrrA KANsAs usA Revision 1 15 November 2000 s2 1 ...

Page 263: ...Original Feb 3 1997 1 Nov 15 2000 LOG OF EFFECTIVITY PAGES PAGE Title S2 1 s2 2 s2 3 s2 4 s2 5 DATE Nov 15 00 Nov 15 00 Nov 15 00 Feb 3 97 Feb 3 97 PAGE s2 6 s2 7 s2 8 s2 9 52 10 blank DATE Nov 15 00 Nov 15 00 Feb 3 97 Feb 3 97 Feb 3197 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated in...

Page 264: ...der receives interrogating pulse signals on 1030 MHz and transmits coded pulse train reply signals on 1090 MHz lt is capable of replying to Mode A aircraft identification and also to Mode C altitude reporting interrogations on a selective reply basis on any of 4096 information code selections A sidewall mounted SSD120 20 Blind Encoder is included in the avionic configuration the transponder can pr...

Page 265: ...preprogram any single code such as 1200 into the KT 76C Pressing the VFR button instantly returns the KT 76C to the preprogrammed code without having to manually enter 1200 All Bendix King Transponder operating controls are located on the front panel of the unit Functions of the operating controls are described in Figure 1 s2 4 Feb 3 97 ...

Page 266: ...s in hundreds of feet FL is annunciated to indicate Flight Level altitude Flight Level is a term to indicate that the altitude is not true altitude but barometric altitude which is not corrected for local pressure For Example FL 040 corresponds to an altitude of 4000 feet meaning sea level pressure of 29 92 inches of mercury The Flight Level altitude is only displayed when the altitude repofting i...

Page 267: ...ables transponder to transmit Mode A aircraft identification reply pulses ON is annunciated ALT Turns set on and enables transponder to transmit either Mode A aircraft identification reply pulses and Mode C altitude reporting pulses selected automatically by the interrogating signal ALT is annunciated 6 VFR CODE BUTTON VFR Pressing the VFR Button will cause a pre programmed Mode A reply code to su...

Page 268: ...ENCY SIGNAL 1 Mode Selector Knob ALT 2 Numeric Keys 0 7 SELECT 7700 operating code TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL CoMMUNTCAT ONS WHEN tN A CONTROLLED ENVTRONMENT 1 Mode Selector Knob ALT 2 Numeric Keys 0 7 SELECT 7600 operating code SECTION 4 NORMAL PROCEDURES BEFORE TAKEOFF 1 Mode Selector Knob SBY TO TRANSMTT MODE A ATRCRAFT tDENT FICATION CODES tN FLIGHT 1 Numeric Keys 0 7 SELECT...

Page 269: ...T R will illuminate steadily indicating IDENT operation TO TRANSMTT MODE C ALTTTUDE REPORTTNG CODES lN FLIGHT 1 Transponder Code Selector Knob SELECT assigned code 2 Mode Selector Knob ALT NOTES When directed by ground controller to stop altitude squawk turn Mode Selector Knob to ON for Mode A operation only Altitude transmitted by the transponder for altitude squawk and displayed on the KT 76C pa...

Page 270: ...de Button PRESS while still holding IDT button to place new VFR code in nonvolatile memory for subsequent call up SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or related external antennas will result in a minor reduction in cruise performance Feb 3 97 S2 9 S2 10 Blank ...

Page 271: ......

Page 272: ...oved Airplane Flight Manual CESSNA MODEL 182S AIRPLANES 18280001 AND ON SUPPLEMENT 3 BENDIX KING KMA 26 AUDIO SELECTOR PANEL 1þ u ø ofGAMA copy cHr jee7 3 February 1997 CESSNA AIRCRAFT COMPANY wrcurn x r s s usn Revision 1 15 November 2000 182sPHUs s3 01 S3 1 ...

Page 273: ...te of lssue 0 Original Feb 3 1997 1 Nov 15 2000 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S3 1 Nov 15 00 S3 s Feb 3197 S3 2 Nov 15 00 53 6 Feb 3197 S3 3 Feb 3 97 S3 7 Nov 15 00 S3 4 Feb 3 97 S3 8 Feb 3 97 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This...

Page 274: ... Com 3 or PA Unused position All operating controls are shown and described in Figure 1 A crystal controlled superheterodyne marker beacon receiver with 3 light presentation is incorporated within the unit Dimming circuitry for the marker lamps automatically adjusts brightness appropriate to the cockpit ambient light level Hi and Lo sensitivity and lamp test functions are also provided Light dimmi...

Page 275: ...e passage of middle marker beacon 2 PHOTOCELL FOR AUTOMATIC DIMMING OF MARKER BEACON LIGHTS AND SELECT BUTTON The photocell in the faceplate automaticallv dims the marker liohts as well as the oreen annunciators in the Speatier Audio Select Butto ns for night operationi 3 MARKER BEACON SENSITIVITY LAMP AND TEST SWITCH The Select button must that the green lluminated for the ma eceive to provide at...

Page 276: ...IO SELECT BUTTONS Push button audio selection is available 6 PUSH SPKR SWITCH With the Speaker Setecr both headphone and cabin speaker audio will be audio is active full time Headphone audio cannol Figure 1 Bendix King KMA 26 Audio Selector Panel Sheet 2 of 3 Feb 3 97 s3 5 ...

Page 277: ...which are selected with the toggle switch on the lower left side on the faceplate ln the ALL position the pilot intercom loop and do not hear the radios When either the ALL or CREW intercom modes are selected the control intercom volume only not the receiver s volume l 1 MARKEB MUTE BUTTON Mutes culrentlv active marker beacon audio Figure 1 Bendix King KMA 26 Audio Selector Panel Sheet 3 of 3 s3 6...

Page 278: ...KMA 26 asl evidenced by the inability to transmit in COM 1 2 or 3 1 MIC Selector Switch EMG NOTE This action bypasses the KMA 26 audio amplifier and connects the pilot s mic head set directly to COM 1 SECTION 4 NORMAL PROCEDURES AUDIO CONTROL SYSTEM OPERATION 1 MIC Selector Switch Turn to desired transmitter 2 SPEAKER and Audio Select Button s SELECT desired receiver s NOTES Rotation of the MIC se...

Page 279: ...re operational 2 SENS Selections Select Hl sensitivity for airuay flying or LO for ILS LOC approaches SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or related external antennas will result in a minor reduction in cruise performance s3 8 Feb 3 97 ...

Page 280: ...t Manual CESSNA MODEL 182S AIRPLANES 18280001 AND ON SUPPLEMENT 4 POINTER MODEL 3OOG11 OR MODEL 4OOO 11 EMERGENCY LOCATOR TRANSMITTER coPYRtGHT 1997 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 182SPHUS 54 01 J Membe l of GAMA 3 Febru ary 1997 Revision 1 15 November 2000 s4 1 ...

Page 281: ... of lssue Feb 3 1997 Nov 15 2000 LOG OF EFFECTIVITY PAGES PAGE DATE SERVICE BULLETIN CONFIGURATION LIST The 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 are currently active Airplane Unit Revision Number Title Effectivitv lncorporation 0 Original 1 T...

Page 282: ...installed on the top right hand side of the copilot s instrument panel for control of the ht cre the er swi I is t ELT inte frequ General aviation and commercial aircraft the FAA and CAP monitor 121 5 MHz and 243 0 MHz is monitored by the military The ELT is contained in a high impact fire retardant glass filled Lexon case with carrying handle and is mounted behind the aft cabin partition wall on ...

Page 283: ...d the label on the transmitter Figure 1 Pointer Model 3000 11 Emergency Locator Transmitter Õ 1 REMOTE CABLE JACK Connects to ELT remote switch annunciator located on the copilot s instrument panel 2 ANTENNA RECEPTACLE Connects to antenna mounted on top of tailcone 3 TRANSMITTER ANNUNCIATOR LIGHT llluminates red to indicate the transmitter is transmitting a distress signal 4 MASTER FUNCTION SELECT...

Page 284: ...dicate that the transmitter is transmitting a distress signal Arms transmitter for automatic activation if G switch senses a predetermined deceleration level Deactivates and rearms transmitter after automatic activation by the G switch Red annunciator in center of rocker switch should extinguish 3 Figure 2 Pointer Model 4000 11 Emergency Locator Transmitter ELr 1 REMOTE CABLE JACK Connects to ELT ...

Page 285: ...llowing rescue and to reset the automatic activation function The red annunciator in the center of the remote switch annunciator should extinguish 5 REMOTE SWITCH ANNUNCIATOR 3 position rocker switch oN Remotely activates the transmitter for test or emergency situations Red annunciator in center of rocker switch illuminates to indicate that the transmitter is transmitting a distress signal Arms tr...

Page 286: ...h is located on the ELT unit 1 ENSURE ELT ACTí VATION a Position remote switch annunciator to the ON position even if annunciator light is already on b lf airplane radio is operable and can be safely used no threat of fire or explosion turn ON and select 121 5 MHz lf the ELT can be heard transmitting it is working properly c Ensure that antenna is clear of obstructions NOTE When the ELT is activat...

Page 287: ... MHz on the radio transceiver and listen for an emergency lone transmission lf the remote switch annunciator is illuminated or an emergency tone is heard position the remote switch annunciator in the RESET position and release to the AUTO posítion The ELT must be seruiced in accordance with FAR Parl91 2O7 INSPECTION TEST 1 The emergency locator transmitter should be tested every 100 hours NOTE Tes...

Page 288: ...turb other communications or damage output circuitry After accumulated test or operation time equals t hour battery pack replacement is required IN FLIGHT MONITORING AND REPORTING Pilot s are encouraged to monitor 121 5 MHz and or 243 0 MHz while in flight to assist in identifying possible emergency ELT transmissions On receiving a signal report the following information to the nearest air traffic...

Page 289: ...sEcfloN 5 PERFORMANCE There is no change in airplane performance when the ELT is installed SECT ON 9 SUPPLEMENTS SUPPLEMENT 4 FAA APPROVED ...

Page 290: ...rating Handbook and FAA Approved Airplane Flight Manual CESSNA MODEL 1825 AIRPLANES 182S8OOO1 AND ON Q u a rofGAMA copy GHr 1se7 3 Fgbruary 1997 CESSNA AIRCRAFT COMPANY wrcHrrA KANsAs usA Revision 3 20 May 1999 lg2sPHus ss o3 SS 1 ...

Page 291: ...y the date of that revision Revision Level 0 Original 1 2 3 LOG OF EFFECTIVITY PAGES SUPPLEMENT 5 Date of lssue Feb 3 1997 Dec 1 1997 July 15 1998 May 20 1999 PAGE Title S5 1 ss 2 s5 3 s5 4 s5 5 s5 6 ss 7 s5 8 s5 9 s5 10 DATE May 20199 May 20199 July 15 98 July 15 98 July 15 98 May 20199 July 15 98 July 15 98 July 15 98 July 15 98 PAGE s5 11 s5 12 s5 13 s5 14 s5 15 s5 16 s5 17 s5 18 s5 19 55 20 bl...

Page 292: ...vice Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Seruice Bulletins that are currently active Airolane Unit Revision lncorporated Number Title Effiävifv iñilrporation fnffilane sB98 34 KLN 898 182580001 7 15198 01 NAVIGATION THRU SYSTEM IFR 182580257 NON PRECISION APPROACH LIMITATION July 15 98 s5 3 ...

Page 293: ...egrity Monitoring RAIM is a function that every IFR ceftified GPS receiver must continuously peÍorm to assure position accuracy RAIM is available when 5 or more of these satellites are in view or 4 satellites are in view and a barometrically corrected altitude input from the airplane s altimeter is made Annunciation is provided if there are not enough satellites in view to assure position integrit...

Page 294: ...LE THE DATABASE IS BEING UPDATED NOTE A current database is required by regulation in order to use the KLN 898 GPS system for nonprecision approaches Provided the KLN 898 navigation system is receiving adequate usable signals it has been demonstrated capable of and has been shown to meet the accuracy specifications of VFF IFR en route oceanic and remote en route domestic terminal and instrument ap...

Page 295: ...KLN 898 does not necessarily constitute approvalfor use in foreign airspace NOTE When the KLN 898 contains receiver software RCVR 01621 0001 or higher dash number as verified on the OTH 6 page the unit is qualified for BRNAV Basic Area Navigation operation in the European region in accordance with the criteria of AC 90 96 Reference ICAO Doc 7030 Regional Supplementary Procedures JAA Technical Guid...

Page 296: ...by the pilot the message annunciator will remain on but will not flash 2 GPS WAYPOTNT WPT ANNUNCIATOR LIGHT GPS WAYPOINT annunciator will begin to flash approximately 36 seconds prior to reaching a Direct To waypoint Also when turn anticipation is enabled in the KLN 898 GPS unit the annunciator will begin to flash 20 seconds prior to the beginning of turn anticipation then illuminate steady at the...

Page 297: ... automatically selects the approach ARM mode or when the approach ARM mode is manually selected The approach ARM mode will be automatically selected when the airplane is within 30 NM of an airpofi and an approach is loaded in the flight plan for that airport The approach ARM mode can manuafly be selected at a greater distance than 30 NM from the airport by pressing the GPS APPROACH switch however ...

Page 298: ...g the Course Deviation lndicator CDl needle can best be accomplished by pressing the Direct To button and then manually setting the No 1 CDI course to the course value prescribed in the KLN 89B displayed message NOTE The Directional Gyro heading HDG bug must also be set to provide proper course dalum to the autopilot if coupled to the KLN 898 in LEG or OBS When the optional HSI is installed the HS...

Page 299: ...e currency of the database or verifies each selected waypoint for accuracy by reference to current approved data d The system must utilize ORS Level 02 or later FAA approved revision to conduct nonprecision instrument approaches ln addition the software level status found on page OTH 6 must be HOST 00880 0004 or later lnstrument approaches must be accomplished in accordance with approved instrumen...

Page 300: ...s projected to be operational for the flight the aircraft can depart without fudher action 2 With 22 23 if the altitude input to the KLN 898 is not available or fewer satellites projected to be operational for the flight the availability of the GPS integrity RAIM should be confirmed for the intended flight route and time This should be obtained from a prediction program run outside of the aircraft...

Page 301: ...ument panel near the KLN 898 unit GPS NOT APPROVED FOR IFR APPROACH This placard is not required with an Operational Revision Status upgrade to ORS 02 or later as read on the Power On page and host software upgrade to HOST 00880 0004 or later as read on the OTH 6 page SECTION 3 EMERGENCY PROCEDURES There are no changes to the basic airplane emergency procedures when the KLN 898 GPS is installed 1 ...

Page 302: ...utlined in the KLN 898 GPS Pilot s Guide P N 006 08786 0000 dated May 1995 or later applicable revision A KLN 898 Quick Reference P N 006 08787 0000 dated May 1995 or later applicable revision containing an approach sequence operating tips and approach related messages is intended as well for cockpit use by the pilot familiar with KLN 898 operations when conducting instrument approaches wlnxrnc TO...

Page 303: ...tion of the desired track on the pilot s DG heading bug is required to provide course datum to the KAP 140 autopilot Frequent course datum changes may be necessary such as in the case of flying a DME arc The autopilot approach mode APR should be used when conducting a coupled GPS approach NOTE Select HDG mode for DME arc intercepts NAV or APR coupled DME arc intercepts can result in excessive over...

Page 304: ...e ACT 7 or ACT I page To delete or replace a SlD STAR or approach select FPL 0 page Place the cursor over the name of the procedure press ENT to change it or CLR then ENT to delete it 2 En route check for RAIM availability at the destination airport ETA on the OTH 3 page NOTE RAIM must be available at the FAF in order to fly an instrument approach Be prepared to terminate the approach upon loss of...

Page 305: ...T IS NOT ON COURSE DO NOT SWITCH FROM OBS TO LEG WITH GREATER THAN 1 NM CROSS TRACK ERROR XTK b NoPT routes including DME arc s are flown in LEG is mandatorv from the FAF to the MAP LEG NOTE Select HDG mode for DME arc intercepts coupled DME arc intercepts can result overshoots aggravated by high grounc intercepts from inside the arc NAV or APR in excessive speeds and or wnnnrnc FLYING FINAL OUTBO...

Page 306: ... the 2 nm inbound to the FAF c lnternally the KLN 898 will transition from terminal to approach integrity monitoring 7 Crossing the FAF and APR ACTV is ry annunciated a Do not descend b Execute the missed approach 8 Missed Approach a Climb b Navigate to the MAP in APRARM if APR ACTV is not available NOTE There is no automatic LEG sequencing at the MAP c After climbing in accordance with the publis...

Page 307: ...nt will be on your present position radial off the arc VOR when you load the IAF into the flight plan or the beginning of the arc if currently on a radial beyond the arc limit To adjust the arc intercept to be compatible with a current radar vector bring up the arc IAF waypoint in the NAV 4 page scanning field or under the cursor on the FPL 0 page press CLR then ENT Fly the arc in LEG Adjust the h...

Page 308: ...PRARM Flagged navigation inside the FAF may usually be restored not guaranteed by pressing the GPS APR button changing from ACTV to ARM Fly the missed approach The instrument approach using the KLN 898 may be essentially automatically started 30 nm out with a manual baro setting update or it may require judicious selection of the OBS and LEG modes APRARM may be canceled at any time by pressing the...

Page 309: ......

Page 310: ... Airplane Flight Manual CESSNA MODEL 182S AIRPLANES 18280001 AND ON SUPPLEMENT 6 BENDIVK NG KR87 AUTOMATIC DIRECTION FINDER l Memøer of GAMA copy GHr 1ee7 3 Fgbru ary 1997 CESSNA AIBCHAFT COMPANY wcHrrA KANsAs usA Revision 2 15 November 2000 ls2sPHus s6 02 S6 1 ...

Page 311: ...0 Revision Level 0 Original 1 2 LOG OF EFFECTIVITY PAGE PAGE Title 56 1 Nov 15 00 56 2 Nov 15 00 56 3 Nov 15 00 56 4 Feb 3 97 56 5 Feb 3197 56 6 Feb 3197 SERVICE BULLETIN CONFIGURATION LIST The 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 are current...

Page 312: ...ws switching between pre selected STANDBY and ACTIVE frequencies by pressing the frequency transfer button Both pre selected frequencies are stored in a non volatile memory circuit no battery power required and displayed in large easy to read self dimming gas discharge numerics The active frequency is continuously displayed in the left window while the right window will display either the standby ...

Page 313: ...SECTION 9 SUPPLEMENTS SUPPLEMENT 6 FAA APPROVED Figure 1 s6 4 CESSNA MODEL 1825 0585C 1 043 058sc1 044 KR 87 Automatic Direction Finder ADF Sheet 1 of 4 â rEE LiPr FL rlt Ill Feb 3 97 ...

Page 314: ... wave and associated morse code identifier broadcast on the carrier wave to be heard NOTE CW signals Morse Code are unmodulated and no audio will be heard without use of BFO This type of sígnal is not used in the United States air navigation lt is used in some foreign countries and marine beacons 4 STANDBY FREQUENCY FLIGHT TIME OR ELAPSED TIME ANNUNCIATION When FRQ is displayed the STANDBY frequen...

Page 315: ... clockwise rotation increases audio level Audio muting causes the audio output to be muted unless the receiver is locked on a valid station 8 SET BESEï ELAPSED TIMER BUTTON SET RST The seVreset button when pressed resets the elapsed limer whether it is being displayed or not 9 FLIGHT TIMEF ELAPSED TIMEB MODE SELECTOR BUTTON FLT ET The Flight Timer Elapsed Time mode selector button when pressed alt...

Page 316: ...ER lndicates relative or magnetic bearing to station as selected by HDG knob lf the relative heading of North N is manually selected under the lubber line by the pilot then the bearing pointer indicates the relative bearing to the station lf the aircraft s magnetic heading is selected under the lubber line by the pilot then the bearing pointer indicates the magnetic bearing to the station 16 HEADI...

Page 317: ...uency display 3 FRQ Button PRESS to move the desired frequency from the standby to the active position 4 ADF Selector Switch on audio control panel SELECT as desired 5 OFF OL Control SET to desired volume levef and identify that desired station is being received 6 ADF Button SELECT ADF mode and note relative bearing on indicator ADF TEST PRE FLIGHT or IN FLIGHT 1 ADF Button SELECT ANT mode and not...

Page 318: ... Button PRESS once or twice until FLT is annunciated Timer will already be counting since it is activated by turning the unit on 3 OFFA OL Control OFF and then ON if it is desired to reset the flight timer TO OPERATE AS A COMMUNICATIONS RECEIVER ONLY 1 OFF OL Control ON 2 ADF Button SELECT ANT mode 3 Frequency Selector Knobs SELECT desired frequency in the standby frequency display 4 FRQ Button PR...

Page 319: ...until ET is annunciated 3 SET RST Button PRESS until the ET annunciation begins to flash 4 FREQUENCY SELECTOR KNOBS SET desired time in the elapsed time display The small knob is pulled out to tune the 1 s The small knob is pushed in to tune the 10 s The outer knob tunes minutes up to 59 minutes NOTE Selector knobs remain in the time set mode for 15 seconds after the last entry or until the SET RS...

Page 320: ...selector to ANT and listening for station call letters ELECTRICAL STORMS ln the vicinity of electrical storms an ADF indicator pointer tends to swing from the station tuned toward the center of the storm NIGHT EFFECT This is a disturbance particularly strong just after sunset and just after dawn An ADF indicator pointer may swing erratically at these times lf possible tune to the most poweÉul stat...

Page 321: ... SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or related external antennas will result in a minor reduction in cruise performance s6 12 Feb 3 97 ...

Page 322: ... FAA Approved Airplane Flight Manual CESSNA MODEL 1825 AIRPLANES 18280001 AND ON SUPPLEMENT 8 WINTERIZATION KIT Q uember of GAMA copyR cHr 1ee7 3 Fgbru ary 1997 CESSNA AIRCRAFT COMPANY wcHrrA KANsAs usA Revision 1 15 November 2000 182sPHUs sB 01 Sg_1 ...

Page 323: ...e of lssue 0 Original Feb 3 1997 1 Nov 15 2000 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S8 1 Nov 15 00 S8 2 Nov 15 00 S8 3 Feb 3 97 S8 4 Feb 3197 SERVICE BULLETIN CONFIGURATION LIST The 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 Seruice Bulletins that are curre...

Page 324: ...uld be installed for operations in tempertues consistently below zO F 7 C Once installed the crankcase breather insulation is approved for permanent use in both hot and cold weather SECTION 2 LIMITATIONS The following information must be presented in the form of placards when the airplane is equipped with a winterization kit 1 On each nose cap cover plate THIS PLATE NOT TO BE USED WHEN TEMPERATURE...

Page 325: ... the airplane emergency procedures when the winterization kit is installed SECTION 4 NORMAL PROCEDURES There is no change to the airplane normal procedures when the winterization kit is installed SECTION 5 PERFORMANCE There is no change to the airplane performance when the winterization kit is installed s8 4 Feb 3 97 ...

Page 326: ...nd FAA Approved Airplane Flight Manual CESSNA MODEL 182S AIRPLANES 18280001 AND ON SUPPLEMENT 9 DAVTRON MODEL 803 cLocK o A T Jl Member of GAMA copy cHr 1ee7 3 February 1997 CESSNA AIRCRAFT COMPANY vìcHíìä K fis AËIöÁ Revision 1 15 November 2000 ...

Page 327: ...Level Date of lssue 0 Original Feb 3 1997 1 Nov 15 2000 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S9 1 Nov 15 00 S9 4 Feb 3197 S9 2 Nov 15 00 S9 5 Nov 15 00 S9 3 Feb 3197 59 6 Feb 3i97 SERVICE BULLETIN CONFIGURATION LIST The 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 ...

Page 328: ...ns are displayed in the upper portion of the unit s LCD window and clocl timing functions are displayed in the lower portion of the unit s LCD window The digital display features an internal light back light to ensure good visibility under low cabin lighting conditions and at night The intensity of the back light is controlled by the PANEL LT rheostat ln addition the display incorporates a test fu...

Page 329: ...ds Proper operation is indicated by the display 88 88 and activation of all four annunciators O A T VOLTMETER OPERATION The upper portion of the LCD window is dedicated to O A T and voltmeter operations The voltmeter reading is preselected upon startup and is indicated by an E following the display reading Pushing the upper button will sequence the window from voltage to fahrenheit F to centigrade...

Page 330: ...s the set mode The lighted annuniiatorl will resume its normal flashing indicating the clock is running in universaltime mode SETTING LOCAL TIME Use the SELECT button to select localtime LT Simultaneously press both the SELECT and lhe CONTROL buttons to enter the set mode The tens of hours digit will start flashing The set operation is lhe same as for UT except that minutes are already synchronize...

Page 331: ... flashing The set operation is the same as for UT and a count down time can be set from a maximum of 59 minutes and 59 seconds Once the last digit is set pressing the SELECT button exits the set mode and the clock is ready to stad the countdown Pressing the CONTROL button now will start the countdown When countdown reaches zero the display will flash Pressing either the SELECT or CONTROL button wi...

Page 332: ...plane Flight Manual CESSNA MODEL 1825 AIRPLANES 18280001 AND ON SUPPLEMENT 1O BENDTX K NG KLN 8e VFR GLOBAL POSITIONING SYSTEM Q Member ofGAMA copy GHr se7 3 February 1997 CESSNA AIBCRAFT COMPANY wrcHrrA KANsAS usA Revision 1 15 November 2000 182sPHus slo oi 510_1 ...

Page 333: ...that revision Revision Level Date of lssue 0 Original Feb 3 1997 1 Nov 15 2000 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S10 1 Nov 15 00 S10 2 Nov 15 00 510 3 Nov 15 00 S10 4 Feb 3 97 SERVICE BULLETIN CONFIGURATION LIST The 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 t...

Page 334: ... may be found in the Bendix King KLN 89 Pilot s Guíde supplied with the unit This pilot guide must be available during operation of the KLN 89 unit SECTION 2 LIMITATIONS Use of the KLN 89 is limited to VFR operations only The following information must be presented in the form of placards when the airplane is equipped with a KLN 89 unit 1 On the instrument panel near the KLN 89 unit GPS NOT APPROV...

Page 335: ...c airplane normal operating procedures with the KLN 89 GPS installed SECTION 5 PERFORMANCE There is no change to the airplane peñormance when the KLN 89 GPS is installed However installation of an externally mounted antenna or related external antennas will result in a minor reduction in cruise performance s10 4 Feb 3 97 ...

Page 336: ...plane Flight Manual CESSNA MODEL 182S AIRPLANE SERIALS 18280001 THRU 18280164 SUPPLEMENT 1 1 BENDI KING KAP 140 2 AXIS AUTOPILOT J MemberofGAMA copy cHr ee7 3 February 1997 CESSNA AIRCRAFT COMPANY wrcHrrA KANsAs usA Revision 3 15 November 2000 ls2sPHugsir os 51 1_l ...

Page 337: ...ginal Feb 3 1997 1 July 18 1997 2 Dec 1 1997 3 Nov 15 2000 LOG OF EFFECTIVITY PAGES PAGE Title S11 1 s11 2 s11 3 511 4 blank s11 5 s11 6 s11 7 s11 8 s11 9 s11 10 s11 11 s11 12 s11 13 sl1 14 DATE Nov 15 00 Nov 15 00 Feb 3 97 Feb 3 97 Dec 1197 Dec 1197 Dec 1197 Dec 1 97 Feb 3 97 Feb 3197 Feb 3 97 Feb 3 97 Dec 1197 July 18 97 PAGE s11 15 s11 16 s11 17 s1 1 18 s11 19 sl1 20 s11 21 s11 22 s11 23 s11 24...

Page 338: ...OT SERVICE BULLETIN CONFIGURAT ON LIST The following is a list of Seruice Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Seruice Bulletins that are currently active Number rire T5 oo r on ffi Feb 3 97 51 1 3l S1 1 4 Blank ...

Page 339: ......

Page 340: ...trim system which provides autotrim during autopilot operation and manual electric trim MET for the pilot when the autopilot is not engaged The electric trim system is designed to fail safe for any single inflight trim malfunction Trim faults are visually and aurally annunciated A lockout device prevents autopilot or MET engagement until the system has successfully passed preflight self test Autom...

Page 341: ...ionics bus bar of the radio circuit breakers and the autopilot circuit breaker The AVIONICS MASTER switch also serves as an emergency AP MET shutoff The airplane MASTER switch function is unchanged and can be used in an emergency to shut off electrical power to all flight control systems while the problem is isolated The following circuit breakers are used to protect the KAP 140 2 Axis Autopilot L...

Page 342: ...nLT ef zm CESSNA MODEL 182S DIRECTIONAL GYRO ANNUNCIATOR PANEL SECTION 9 SUPPLEMENTS SUPPLEMENT 1 1 FAA APPROVED r J AUTOPILOT c B Y1 2 3 4 t b i b jQj oto v v 11 y 13 oB ìo Figure 1 Bendir King 2 Axis KAP 140 Autopilot Schematic Sheet 1 of 5 Dec 1197 s11 7 ...

Page 343: ...d to disengage the autopilot 3 ROLL AXIS R ANNUNCIATOR When illuminated indicates failure of the roll axis and disengage the autopilot 4 HEADING HDG MODE SELECTOR BUTTON When pushed will select the Heading mode which commands the airplane to turn to and maintain the heading selected by the heading be selected to the new en HDG an ge the autopilot Figure 1 Bendix King 2 Axis KAP 140 Autopilot Opera...

Page 344: ...cted altitude The selected altitude is the airplane altitude at the moment the ALT button is pressed lf the ALT button is pressed with an established VS rate present there will be approximately a 10 of VS rate overshoot with the airplane returned positively to the selected altitude This button may be used to engage the autopilot 9 VERTICAL SPEED UP DN MODE BUTTONS The action of these buttons are d...

Page 345: ...ng AP displayed on the autopilot computer 13 MANUAL ELECTRIC TRIM SWITCHES MET When both switches are pressed in the same direction will activate pitch trim in the selected direction lf only one switch is moved the trim system will not operate lf only the right half of the MET switch assembly is held for 3 seconds the trim monitoring system will detect a switch failure resulting in a annunciation ...

Page 346: ... as to the autopilot s request for autotrim A solid indication represents the lowest demand level for trim whereas a flashing annunciator implies a greater demand A solid í without an arrowhead is an indication of a pitch trim fault Refer to the EMERGENCY PROCEDURES for proper response to a pitch trim fault 17 PITCH TRIM Annuncíation llluminates whenever the automated preflight self test detects a...

Page 347: ... approved for Category I operation only Approach mode selected 5 Autopilot maximum airspeed limitation 160 KIAS Autopilot minimum airspeed limitation 80 KIAS 6 Flaps must be up with the autopilot engaged 7 The autopilot must be disengaged below 200 feet AGL during approach operations and below 800 feet AGL for all other phases of flight 8 Overriding the autopilot to change pitch or roll attitude i...

Page 348: ...g power change in turbulence firmly grasp the control wheel and maintain airplane control Press and hold A P DISC switch throughout recovery Once the airplane is stabilized the autopilot may be re engaged as described in Section 4 Normal Procedures 2 Above the flap control handle indicator FLAPS MUST BE UP WITH THE AUTOPILOT ENGAGED SECTION 3 EMERGENCY PROCEDURES The four step procedure listed und...

Page 349: ...ics Master Switch OFF before locating and pulling the Autopilot Circuit Breaker Turn the Avionics Master Switch on as soon as possible to restore power to all other avionics equipment Primary attitude airspeed direclional compass and altitude instruments will remain operational at alltimes mnrurruc DO NOT ATTEMPT TO RE ENGAGE THE AUTOPILOT FOLLOWING AN AUTOPILOT AUTOTRIM OR MANUAL ELECTRIC TRIM MA...

Page 350: ...to completely disable the autopilot system 2 A manual electric trim malfunction may be recognized by the illumination of a red PITCH TRIM annunciator accompanied by an alert tone or by unusual trim wheel motions with the autopilot mode OFF without pilot actuation of the manual electric trim switches As with an autopilot malfunction the first concern following a manual electric trim malfunction is ...

Page 351: ... THE CAUSE FOR THE MALFUNCTION HAS BEEN CORRECTED P A flashing i annunciator with an up or down arrow head on the face of the autopilot computer P A flashing i auto trim annunciation on the face of the autopilot indicates a faífure of the auto trim function to relieve pitch servo loading in a timely manner This condition should be temporary P 1 FLASHING i ANNUNCIATION OBSERVE aircraft pitch behavi...

Page 352: ...ashing ROL will be displayed Select a valid navigation source NOTE A flashing NAV APR or REV annunciation can also be caused by a failed heading valid input 3 Flashing GS lndication of a flagged glideslope GS will rearm automatically if a valid GS signal is received NOTE To continue tracking the localizer observe the appropriate minimums for a nonprecision approach Press ALT twice in rapid success...

Page 353: ...PPLICATION AND SELF TEST A self test is performed upon power application to the computer This test is a sequence of internal checks that validate proper system operation prior to allowing normal system operation The sequence is indicated by p 1 with an increasing number for the sequence steps Successful completion of seff test is identified by all display segments being illuminated Display Test ex...

Page 354: ...sition indicator are moving in the down direction Repeat test for the nose up direction Press MET for nose up lrim press and hold the AP DISC TRIM INT switch verify that both the trim wheel and indicator are not moving release the AP DISC TRIM INT switch while still holding MET trim up the trim wheel and indicator should continue to move in the nose up direction 4 AUTOPILOT ENGAGE by pressing AP b...

Page 355: ...D OR IF AIRPLANE CONTROL IS NOT MAINTAINED wnnnnc DURING ALL AUTOPILOT COUPLED OPER ATIONS THE PILOT IN COMMAND MUST USE PROPER AUTOPILOT COMMANDS AND USE THE PROPER ENGINE POWER TO ENSURE THAT THE AIRPLANE IS MAINTAINED BETWEEN 80 AND 160 KIAS AND DOES NOT EXCEED OTHER BASIC AIRPLANE OPERATING LIMITATIONS NOTE Autopilot tracking performance will be degraded in turbu lence NOTE Avoid abrupt power ...

Page 356: ...elected the autopilot will operate the ROL and vertical speed modes 1 wnnrurruc WHEN OPERATING AT OR NEAR THE BEST RATE OF CLIMB AIRSPEED AT CLIMB POWER SETTINGS AND USING VERTICAL SPEED MODE IT IS EASY TO DECELERATE TO AN AIRSPEED WHERE CONTINUED DECREASES IN AIRSPEED WILL RESULT IN A REDUCED RATE OF CLIMB CONTINUED OPERATION IN VERT CAL SPEED MODE COULD RESULT IN A STALL WHEN OPERATING AT OR NEA...

Page 357: ...n to select aircraft vertical speed within the limits of 2000 ft min 2 VERTICAL SPEED Control RELEASE when desired vertical speed is displayed The autopilot will maintain the displayed vertical speed 4 ALTTTUDE ALT HOLD a ALT Hold Selector Button PRESS Note ALT hold annunciator ON Autopilot will maintain the selected altitude NOTE It is recommended by the FAA 4C00 248 lo use basic PITCH ATTITUDE H...

Page 358: ...ative press either the UP or DN button with a succession of quick momentary presses programming either an increase or decrease in the altitude preference at the rate of 20 feet each time the button is depressed 5 HEADING HOLD a Heading Selector Knob SET BUG to desired heading b HDG Mode Selector Button PRESS Note HDG mode annunciator ON Autop lot will automatically turn the aircraft to the selecte...

Page 359: ...y established based on the position of the bug NOTE All angle intercepts compatible with radar vectors may be accomplished by selecting ROL mode PRIOR to pressing the NAV button The HDG bug must still be positioned to agree with the OBS course to provide course datum to the autopilot when using a DG Directional Gyro 1 lf the D Bar is greater than 2 to 3 dots the autopilot will annunciate NAVlRul w...

Page 360: ...on a 45 intercept angle will then be automatically established based on the position of the bug NOTE All angle intercepts compatible with radar vectors may be accomplished by selecting ROL mode PRIOR to pressing the APR button The HDG bug must still be positioned to agree with the desired approach course to provide course datum to the autopilot when using a DG 1 lf the D Bar is greaterthan 2 to 3 ...

Page 361: ...n selection a 45 localizer intercept angle will then be automatically established based on the position of the bug NOTE All angle intercepts compatible with radar vectors may be accomplished by selecting ROL mode PRIOR to pressing the REV button The HDG bug must still be positioned to heading to a DG 1 lf the D Bar is greater than 2 to 3 dots the autopilot will annunciate REVnnu when the computed ...

Page 362: ...he APR mode when tracking a localizer b At Glideslope centering note ARM annunciator goes out NOTE Autopilot can capture glideslope from above or below the beam 10 MISSED APPROACH a NP DISC TRIM INTER Switch PRESS to disengage AP b MISSED APPROACH EXECUTE c AP Button Atter aircraft is in trim PRESS for autopilot operation if desired NOTE lf tracking the ILS course outbound as paft of the missed ap...

Page 363: ...UPPLEMENT 11 FAAAPPROVED MODEL 1825 11 BEFORE LANDING a NP DISC TRIM INT Switch PRESS to disengage AP SECTION 5 PERFORMANCE There is no change to the airplane pedormance when the KAP140 2 Axis Autopilot is installed s11 28 Feb 3197 ...

Page 364: ...FAA Approved Airplane Flight Manual CESSNA MODEL 1825 AIRPLANES 18280001 AND ON SUPPLEMENT 12 CANADIAN SUPPLEMENT 1 u ø rofGAMA copy GHr 1se7 1 1 July 1997 CESSNA AIRCHAFT COMPANY wrcurrn x r rs s ùé Revision 1 15 November 2000 la2sPHus st2 oj 512_1 ...

Page 365: ...sion Level Date of lssue 0 Original July 1 1 1997 1 Nov 15 2000 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title 512 1 Nov 15 00 S12 3 Nov 15 00 512 2 Nov 15 00 512 4 July 11 97 SERVICE BULLETIN CONFIGURATION LIST The 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 ...

Page 366: ...supplement is required for Canadian operation of Cessna Model 182S sEciloN 2 LIMITATIONS The following placard must be installed 1 Near the fuel tank filler cap UEL lOOLIJ 1OO MIN GRADE AVIATION GASOLINE cAP 44 0 U S GAL 166 LITRES USABLE cAP 32 5 U S GAL 123 LITRES USABLE TO BOTTOM OF FILLER INDICATOR TAB Nov 15 00 s12 3 ...

Page 367: ...ge to the airplane emergency procedures when used for Canadian operation SECTION 4 NORMAL PROCEDURES There is no change to basic airplane normal operating procedures when used for Canadian operation SECTION 5 PERFORMANCE There is no change to the airplane performance when used for Canadian operation s12 4 Jul11 97 ...

Page 368: ...ESSNA MODEL 182S AIRPLANES 18280454 AND ON SUPPLEMENT 13 BENDIVKING KCS ssA SLAVED COMPASS SYSTEM wtTH Kt 5254 HORTZONTAL STTUATTON ND CATOR HSt coPYRtGHT 1999 CESSNA AIRCRAFT COMPANY WCHITA KANSAS USA 1 E2SPHUS S13 01 Q Memøer ofGAMA 15 January 1999 Revision 1 15 November 2000 s13 1 ...

Page 369: ... Revision Level Date of lssue 0 Original Jan 15 1999 1 Nov 15 2000 LOG OF EFFECTIVITY PAGE PAGE DATE PAGE DATE Title 513 1 Nov 15 00 513 5 Jan 15 99 513 2 Nov 15 00 513 6 Jan 15 99 513 3 Nov 15 00 513 7 Jan 15 99 Sl3 4 Jan 15 99 S13 8 Jan 15 99 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Seruice Bulletins that are applicable to the operation of the airplane and have been incorpo...

Page 370: ...nel mounted Kl 5254 indicator combines the display functions of both the standard Directional Gyro Heading lndicator and the Course Deviation lndicator s VOF LOC Glideslope information to provide the pilot with a single visual presentation of the complete horizontal navigation situation This system also incorporates a slaving accessory and compensator unit This unit indicates any difference betwee...

Page 371: ...gnetic north The gyro is remote mounted and electric driven 2 NAV FLAG Flag is in view when the NAV receiver signal is inadequate 3 HEADING REFERENCE LUBBER LINE Magnetic heading appears under this line when the compass card is slaved or slewed to the aircraft s magnetic heading 4 HEADING WARNING FLAG HDG When flag is in view the heading display is invalid 5 COURSE SELECT POINTER lndicates VOFi Lo...

Page 372: ...0 COMPASS CARD Rotates to display heading of airplane with reference to lubber line on HSl 1 1 COURSE SELECTOR KNOB tt Positions the course bearing pointer on the compass card by rotating the course selector knob 12 COURSE DEVIATION BAR D BAR The center poftion of the omni bearing pointer moves laterally to pictorially indicate the relationship of airplane to the selected course lt indicates degre...

Page 373: ... for the Compass System CW CCW COMPASS MANUAL SLAVE SWITCH With the manual automatic compass slave switch in the FREE position allows manual compass card slaving in either the clockwise or counterclockwise direction The switch is spring loaded to the center position SLAVING METER lndicates the difference between the displayed heading and the magnetic heading Up deflection indicates a clockwise err...

Page 374: ...E HEADING INFORMATION Normal procedures for operation of this system differ little from those required for the more conventional Course Deviation lndicators However several small differences are worth noting The rectilinear movement of the course deviation bar in combination with the rotation of the compass card in response to heading changes provídes an intuitive picture of the navigatíon situati...

Page 375: ...he Autopilot Supplements in the Supplement section of this handbook A description of course datum and autopilot procedures for course datum are incorporated in the appropriate autopilot supplements SECTION 5 PERFORMANCE There is no change to the airplane performance when this instrument is installed s13 8 Jan 15 99 ...

Page 376: ...Handbook and FAA Approved Airplane Flight Manual CESSNA MODEL 1825 AIRPLANES 8OOO1 AND ON SUPPLEMENT 14 ARGENTINE SUPPLEMENT coPYRrcHT r999 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 182SPHUS S1 l 00 J Member of GAMA 9 March 1999 s14 1 ...

Page 377: ...ch g 99 514 2 March g 99 S14 3 March 9 99 514 4 March g 99 514 5 March 9 99 514 6 March g 99 PAGE DATE 514 7 March 9 99 514 8 March 9 99 514 9 March 9 99 514 10 March 9 99 514 11 March 9 99 514 12 blank March 9 99 SERV CE BULLETIN CONF GURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This...

Page 378: ...ilot s Operating Handbook and Argentine Airplane Flight Manual Q u o rofGAMA Mar 9 99 The Cessna Aircraft Company Model 182S COPYBIGHTO 1999 The Cessna Aircraft Company Wichita Kansas USA Original lssue 9 March 1999 FLIGfr MNUAL 9 MARCH 1S9 ARGEMINE AIRPNE s14 3 ...

Page 379: ...sue 9 Mar 1999 ARGEMINE AIBPNE FUGHÎ MNUAL 9 MffiCH 1S9 s14 4 THIS MANUAL WAS PROVIDED FOR THE AIRPLANE IDENTIFIED ON THE TITLE PAGE ON SUBSEQUENT REVISIONS SUPPLIED BY THE CESSNA AIRCRAFT COMPANY MUST BE PROPERLY INSERTED The Gessna Aircraft Company Aircraft Division Mar 9 99 ...

Page 380: ... Revision Allpages in Revision 1 were incorporated and thsi Argentine Airplane Flight Manual was provided in a current status at the time of issuance Subsequent revisions and their affected pages will be recorded at the time of publication Revision 1 6t13te7 Original lssue 9 Mar 1999 ÆGEMINE AæUNE FUGHT MUI 9 MBCH 19æ Mar 9 99 s14 5 ...

Page 381: ...EMENT 14 FAAAPPROVED MODEL 182S SUPPLEMENT ARGENTINE SUPPLEMENT sEciloN 1 GENERAL This supplement is required for Argentine operation of Cessna Model 182S Original lssue 9 Mar 1999 ffiGENNNE ARPME ruGHT WUAL 9 MARCH 19S S14 6 Mar 9 99 ...

Page 382: ...h 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 Handbook and FAA Approved Airplane Flight Manual No acrobatic maneuvers including spins approved Flight into known icing conditions prohibited This airplane is certified for the following flight operations...

Page 383: ...USTIBLE lOOLUIOO GRADO MINIMO COMBUSTIBLE DE AVIACION CAPACIDAD 166 LTS USABLE CAPACIDAD 123 LTS USABLE HASTA LA PARTE INFERIOR DEL INDICADOR DE TAPON DE LLENADO 5 On flap control indicator 0 to 10 140 KIAS Partial flap range with dark blue color code also mechanical detent at 10 10o to 20 120 KIAS Light blue color code also mechanical detent at 20 20 to FULL 100 KIAS White color code Original lss...

Page 384: ...COMBINADOS PARA INSÏRUCCIONES DE CARGA ADICIONALES VER DATOS DE PESO Y BALANCEO 7 A calibration card must be provided to indicate the accuracy of the magnetic compass in 30 increments L On the oil filler cap otL 9 QTS 9 Near airspeed indicator VITESSE INDIQUEE DE MANOEUVRE 110 KIAS 10 On the upper right instrument panel SMOKING PROHIBITED Original lssue 9 Mar 1999 MGEMNE AFPWE RIGtr MANUAL 9 MHCH ...

Page 385: ...IS AIRCRAFT IS EQUIPPED WITH ALTERNATOR AND A NEGATIVE GROUND SYSTEM OBSERVE PROPER POLARITY REVEBSE POLARITY WILL DAMAGE ELECTR CAL COMPONENTS original lssue 9 t t 1 n aRuNE F cn MNUAL e MF H reee s14 10 12 On Upper Right Side of the Aft Cabin Partition TRANSMISOR LOCALIZADOR DE EMERGENCIA INSTALADO DETRÁS ESTA DIVISIÓN DEBE CUMPLIR CON EL DNAR PARTE 91 2O7 13 Near the fuel flow gauge MAXIMUM POW...

Page 386: ...when used for Argentine operation sEcTroN 4 NORMAL PROCEDURES There is no change to the airplane normal operating procedures when used for Argentine operation SECTION 5 PERFORMANCE There is no change to the airplane pedormance when used for Argentine operation Original lssue 9 Mar 1999 ÀÂGEffiINE AIRPSE FUqT MANUAL 9 ÆCH 19S Mar 9 99 514 11 S14 12 blank ...

Page 387: ......

Page 388: ...ight Manual CESSNA MODEL 182S AIRPLANES 18280165 AND ON OR AS MODIFIED BY MK182 22 01 SUPPLEMENT 15 BENDIX KING KAP 140 2 AX S AUTOPILOT Jþ uemøerofGAMA copy cHr ee7 1 Decgmbgr 1997 CESSNA AIRCRAFT COMPANY wrorrrn x rusns ùó Revision 1 31 December 1999 IB2sPHUS slsoi S1S_l ...

Page 389: ... 31 1999 LOG OF EFFECTIVIW PAGES PAGE Title S15 1 s15 2 s15 3 S15 4 blank s15 5 s15 6 s15 7 s15 8 s15 9 s15 10 s15 11 s15 12 s15 13 s15 14 s15 15 s15 16 DATE Dec 31 99 Dec 31 99 Dec 1 97 Dec 1 97 Dec 31 99 Dec 31 99 Dec 1197 Dec 1 97 Dec 1197 Dec 1197 Dec 1197 Dec 31 99 Dec 31 99 Dec 31 99 Dec 31 99 Dec 31 99 PAGE s15 17 s15 18 s15 19 s15 20 s15 21 s15 22 s15 23 s15 24 s15 25 s15 26 s15 27 s15 28 ...

Page 390: ... FLAP LIMITATIONS SERVICE BULLETIN CONFIGURATION LIST The 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 Seruice Bulletins that are currently active Number rire ffi Ho o on ffi Dec 1 97 S15 3 S15 4 Blank ...

Page 391: ......

Page 392: ...ilot has an electric trim system which provides autotrim during autopilot operation and manual electric trim MET for the pilot when the autopilot is not engaged The electric trim system is designed to be fail safe for any single inflight trim malfunction Trim faults are visually and aurally annunciated A lockout device prevents autopilot or MET engagement until the system has successfully passed p...

Page 393: ...TRIM INT control wheel switch will also disconnect the autopilot The AVIONICS MASTER switch supplies power to the avionics bus bar of the radio circuit breakers and the autopilot circuit breaker The AVIONICS MASTER switch also serves as an emergency AP MET shutoff The following circuit breakers are used to protect the KAP 140 2 Axis Autopilot LABEL FUNCTIONS AUTO Pull off circuit breaker supplies ...

Page 394: ...APPROVED NAVIGATION SoURcE 12 SELECTOR SWITCH rNDtc 119 1çO ANNUNCIATOR PANEL DIRECTIONAL GYRO 45678fi C I B o7as1o26 Figure 1 Bendix King 2 Axis KAP 140 Autopilot Schematic Sheet 1 of 5 ELEVATOR ELEVATOR AND ELEVATOR TRIM EbiY âl BçLEVAToR HÞE frLr íf in Dec 1 97 s15 7 ...

Page 395: ...will engage in the basic roll ROL mode which functions as a wing leveler and the pitch axis vertical speed VS mode The commanded vertical speed will be displayed in the upper right corner of autopilot display area The captured VS will be the vertical speed present at the moment the AP button is pressed The button may also be used to disengage the autopilot 3 ROLL AXIS R ANNUNCIATOR When illuminate...

Page 396: ... APR mode tracking sensitivity is recommended for instrument approaches 7 BACK COURSE APPROACH REV MODE BUTTON This button is active only when the coupled navigation receiver is tuned to a LOC ILS frequency When pushed will select the Back Course approach mode This mode functions identically to the approach mode except that the autopilot response to LOC signals is reversed Glideslope is locked out...

Page 397: ...to the KAP 140 system 11 WARN CIB Power to the autopilot disconnect horn and the ship s annunciator panel PITCH TRIM 12 AUTOPTLOT DTSCONNECT A p D SC TR M NT SWTTCH When depressed will disengage the autopilot and interrupt manual electric trim MET power An autopilot disconnect will be annunciated by a continuous 2 second tone accompanied by a flashing AP displayed on the autopilot computer 13 MANU...

Page 398: ...ve use in the HDG mode 16 PITCH TRIM PT Annunciator lndicates the direction of required pitch trim The annunciation will flash if auto trim has not satisfied the request for trim for a period of 10 seconds A solid I without an arrowhead is an indication of a pitch trim fault Refer to the EMERGENCY PROCEDURES for proper response to a pitch trim fault 17 PITCH TRIM Annunciation llluminates whenever ...

Page 399: ... lN HG or HPA for 3 held for 2 seconds will change the lN HG to HPA or vice versa Once is visible the rotary knobs may be tting 3 ALTITUDE ARM ARM BUTTON When pushed will toggle altitude arming on or off When ALT ARM is annunciated the autopilot will capture the altitude alerter displayed altitude provided the aircraft is climbing or descending in VS to the displayed altitude ALT hold arming when ...

Page 400: ...ERTICAL SPEED BARO SETTING NOTE This display may be dashed for up to 3 minutes on start up if a blind encoder is installed which requires a warm up period î Figure 2 Bendix King 2 Axis KAP 140 Autopilot with Altitude Preselect Operating Controls and lndicators Sheet 2 ol2 Dec 31 99 s15 13 ...

Page 401: ...ry I operation only Approach mode selected 5 Autopilot maximum airspeed limitation 160 KIAS Autopilot minimum airspeed limitation 80 KIAS 6 Maximum flap extension 10o 7 Maximum fuel imbalance with autopilot engaged 90 lbs 8 The autopilot must be disengaged below 200 feet AGL during approach operations and below 800 feet AGL for all other phases of flight 9 Overriding the autopilot to change pitch ...

Page 402: ...as Needed D AUTO PILOT Circuit Breaker PULL NOTE The AVIONICS MASTER Switch may be used as an I alternate means of removing all electric power from the autopilot and ms lf necessary perform steps 1A th then turn tre Áviot llCS I MASTER Sw ating and pulling the AUTO I PILOT Circu the AVIONICS MASTER I Switch on as soon as possible to restore power to all other avionics equipment Primary attitude ai...

Page 403: ...e control wheel and press and hold down the A P DISC TRIM INT switch throughout the recovery Manipulate the controls as required to safely maintain operation of the airplane within all of its operating limitations Elevator trim should be used manually as needed to relieve control forces Locate and pull the AUTO PILOT circuit breaker on the right hand circuit breaker panel to completely disable the...

Page 404: ...d oulled Return the AVIONICS MASTER switch to the ON position as soon as possible With the AVIONICS MASTER switch off all avionics and autopilot equipment will be inoperable 5 lt is important that all portions of the autopilot and electric trim system are preflight tested prior to each flight in accordance with the procedures published herein in order to assure their integrity and continued safe o...

Page 405: ...d P lamp was the result of some abnormal accelerations on the airplane the annunciation should be extinguished within approximately one minute and normal use of the autopilot will be reestablished 2 A red R is an indication that the roll axis of the autopilot has been disabled and cannot be engaged The autopilot cannot be reengaged Flashing mode annunciation in the display of the autopilot compute...

Page 406: ...lash for 5 seconds upon selection of NAV APR or REV modes to remind the pilot to set the HDG bug for use as course datum Effects of instrument losses upon autopilot operation 1 Loss of the afiificial horizon no effect on the autopilot 2 Loss of the turn coordinator autopilot inoperative 3 Loss of the Directional Gyro DG The directional gyro doesl not provide any system valid flag lf the DG fails t...

Page 407: ...tor Panel being illuminated and the disconnect tone sounding NOTE Upon applying power to the autopilot the red P warning on the face of the autopilot may illuminate indicating that the pitch axis cannot be engaged This condition should be temporary lasting approximately 30 seconds The P will extinguish and normal operation will be available l wnnnnc IF PITCH TRIM LIGHT STAYS ON THEN THE AUTOTRIM D...

Page 408: ...NTINUOUSLY MONITOR THE AUTOPILOT WHEN IT IS ENGAGED AND BE PREPARED TO DISCONNECT THE AUTOPILOT AND TAKE IMMEDIATE CORRECTIVE ACTION INCLUDING MANUAL CONTROL OF THE AIRPLANE AND OR PERFORMANCE OF EMERGENCY PROCEDURES IF AUTOPILOT OPERATION IS NOT AS EXPECTED OR IF AIRPLANE CONTROL IS NOT MAINTAINED wnnunc DURING ALL AUTOPILOT COUPLED OPER ATIONS THE PILOT IN COMMAND MUST USE PROPER AUTOPILOT COMMA...

Page 409: ...he desired altitude is displayed NOTE An altitude alert is annunciated 1000 ft prior to arrival at the selected altitude Aircraft deviations greater than 200 feet above or below the selected altitude will produce an altitude alert The alert annunciation is accompanied by a series of short tones 2 AFTERTAKEOFF a Elevator Trim VERIFY or SET to place the airplane in a trimmed condition prior to Autop...

Page 410: ...STALL IF NECESSARY DISCONNECT THE AUTO PILOT AND RETURN THE AIRPLANE TO A STABILIZED CLIMB PRIOR TO RE ENGAGMENT wnnnrnc WHEN OPERATING AT OR NEAR THE MAXIMUM AUTOPILOT SPEED IT WILL BE NECESSARY TO REDUCE POWER IN ORDER TO MAINTAIN THE DESIRED RATE OF DESCENT AND NOT EXCEED THE MAXIMUM AUTOPILOT SPEED wnnrunc DO NOT HELP THE AUTOPILOT OR HAND FLY THE AIRPLANE WITH THE AUTOPILOT ENGAGED AS THE AUT...

Page 411: ...f the airplane for its power and weight configuration 4 ALTITUDE HOLD a Capture preselected altitudes if installed 1 ALTITUDE SELECT knob ROTATE until the desired altitude is displayed Note ARM annunciation occurs automatically with altitude selection when the autopilot is engaged 2 ALTITUDE SELECT MODE ARM button PUSH to alternately disarm or arm altitude capture 3 Airplane ESTABLISH vertical spe...

Page 412: ...ot does not use the attitude gyro as a pitch reference if is recommiñded that the autopilot be disconnected and that the airplane be flown by hand in severe turbulence c Changing altitudes 1 Using Vertical Speed Recommended for altitude changes less than 100 ft a VERTICAL SPEED Gontrol PRESS and HOLD either the UP or DN button Vertical Speed will seek a rate of change of about 500 fpm b VERTICAL S...

Page 413: ... heading Autopilot will automatically turn the aircraft to the new selected heading 6 NAV COUPLING I a When equipped with DG I t OBS Knob SELECT desired course I z NAV Mode Setector Button PRESS Note NAV nn annunciated I g Heading Selector Knob ROTATE BUG to agree with OBS course NOTE When NAV is selected the autopilot will flash HDG for S seconds to remind the pilot to reset the HDG bug to the OB...

Page 414: ...upon selecting NAV mode The NAV annunciator will then illuminate and the capture track sequence will automatically begin b When equipped with HSI 1 Course Bearing Pointer SET to desired course 2 Heading Selector Knob SET BUG to provide desired intercept angle and engage HDG mode 3 NAV Mode Selector Button PRESS a lf the D Bar is greater than 2 to 3 dots the au will annunciate NAVARM When the compu...

Page 415: ...e automatically established based on the position of the bug NOTE All angle intercepts compatible with radar vectors may be accom plished by selecting ROL mode B QB to pressing tne APR button The HDG bug must still be positioned to agree with the desired approach cgu_rse to provide course dátum to the autopilot when using a DG a lf the D Bar is greater than 2 to 3 dots the aulopilot will annunciat...

Page 416: ... be automatically and tracked b lf the D Bar is less than 2 to 3 dots the HDG will disengage upon selecting APR mode the annunciator will illuminate and the sequence will automatically begin 5 Airspeed MAINTAIN 100 KIAS minimum coupled autopilot approaches recommended 8 BACK COURSE REV APPROACH COUPLING i e reverse localizer a When equipped with DG v I 1 BARO setting if installed CHECK 2 OBS Knob ...

Page 417: ... back course will be automatically captured and tracked b lf the D Bar is less than 2 to 3 dots the HDG mode will disengage upon selecting REV mode the REV annunciator will illuminate and the capture track sequence will automatically begin b When equipped with HSI 1 BARO Setting if installed CHECK 2 Course Bearing pointer SET to the ILS front course inbound heading 3 Heading Selector Knob SET BUG ...

Page 418: ...the capture track sequence will automatically begin 5 Airspeed MA NTAIN 100 KIAS minimum during autopilot coupled approaches recommended 9 GLIDESLOPE COUPLING a APR Mode ENGAGED Note GS py annunciated NOTE Glideslope coupling is inhibited when operating in NAV or REV modes With NAV 1 selected to a valid lLS glideslope armed and coupling occurs automatically in the APR mode when tracking a localize...

Page 419: ...for its power and weight configuration 3 AP Button PRESS Note ROL and VS annunciators on lf no other modes are selected the autopilot will operate in the ROL and VS mod es Verify that the aircraft Vertical Speed lndicator VSl and the Autopilot VS agree NorE lf tracking the ILS course outbound as part 9l lhe missed approach procedure is desired use the NAV mode to prevent inadvertent GS couPling 11...

Page 420: ...plane Flight Manual CESSNA MODEL 182S AIRPLANES 18280687 AND ON SUPPLEMENT 19 BENDI UKING KLN 94 GLOBAL POSTTTONTNG SYSTEM tFR coPYRtcHT 2ooo CESSNA AIRCRAFTCOMPANY WICHITA KANSAS USA 1 s2SPHUS S19 02 Q n o rofGAMA 6 November 2000 Revision 2 15 January 2001 s19 1 ...

Page 421: ...revision will carry the date of that revision Revision Level 0 Original 1 2 LOG OF EFFECTIVITY PAGES SUPPLEMENT 19 Date of lssue November 6 2000 December 18 2000 January 15 2001 PAGE Title S1e 1 s19 2 s19 3 s19 4 s19 5 s19 6 s19 7 s19 8 s19 9 DATE Jan 15 01 Jan 15 01 Nov 6 00 Jan 15 01 Jan 15 01 Nov 6 00 Nov 6 00 Nov 6 00 Nov 6 00 PAGE s19 10 s19 11 s19 12 s19 13 s19 14 s19 15 s19 16 s19 17 s19 18...

Page 422: ...NG SYSTEM rFR SERVICE BULLETIN CONFIGURATION LIST The following is a list of Seruice 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 are currently active Number J ue ffi P oroo t on ffi Nov 6 00 s19 3 ...

Page 423: ...rbiting satellites Receiver Autonomous lntegrity Monitoring RAIM is a function that every FR certified GPS receiver must continuously pedorm to assure position accuracy RAIM is available when 5 or more of these satellites are in view or 4 satellites are in view and a barometrically corrected altitude input from the airplane s altimeter is made Annunciation is provided if there are not enough satel...

Page 424: ...E THE DATABASE IS BEING UPDATED NOTE A current database is required by regulation in order to use the KLN 94 GPS system for non precision approaches Provided the KLN 94 navigation system is receiving adequate usable signals it has been demonstrated capable of and has been shown to meet the accuracy specifications of VFF IFR en route oceanic and remote en route domestic terminal and instrument appr...

Page 425: ... navigation NOTE FAA approval of the KLN 94 does not necessarily constitute approvalfor use in foreign airspace NOTE The KLN 94 is qualified for BRNAV Basic Area Navigation operation in the European region in accordance with the ciiteria of AC 90 96 Reference ICAO Doc 7030 Regional Supplementary Procedures JAA Technical Guidance Leaflet nUizoXz anil Eurocontrol RNAV Standard Doc 003 93 Area Naviga...

Page 426: ...a message condition exists which requires a specific action by the pilot the message annunciator will remain on but will not flash 2 GPS WAYPOTNT WpT ANNUNCTATOR LtcHT GpS WAYPOINT annunciator will begin to flash approximately 36 seconds prior to reaching a Direct To waypoint Also when turn anticipation is enabled in the KLN 94 GPS unit the annunciator will begin to flash 20 seconds prior to the b...

Page 427: ... or disarms the approach ARM mode and also canceis the approach ACTV mode after being automatically engaged by the KLN 94 GPS y s e1n The white back irounð color of the GPS APPROACH annunciator makes it visible in daylight 4 ARM ANNUNCIATOR LIGHT ARM annunciator will CDI scale until the airplane reaches the 30 NM point The approach ARM mode can also be disarmed by pressing the GPS APPROACH switch ...

Page 428: ... the Course Deviation lndicator CDl needle can best be accomplished by pressing the Direct To button and then manually setting the No 1 CDI course to the course value prescribed in the KLN 94 displayed message NOTE The Directional lndicator heading HDG bug must also be set to provide proper course datum to the autopilot if coupled to the KLN 94 in LEG or OBS When the optional HSI is installed the ...

Page 429: ... verifies the currency of the database or verifies each selected waypoint for accuracy by reference to current approved data d lnstrument approaches must be accomplished in accordance with approved instrument approach procedures that are retrieved from the KLN 94 database The KLN 94 aeronautical database must incorporate the current update cycle I t ffre KLN 94 Quick Reference P N 006 18228 0000 R...

Page 430: ...22 23 if the altitude input to the KLN 94 is not available or fewer satellites projected to be operational for the flight the availability of the GPS integrity RAIM should be confirmed for the íntended flight route and time This should be obtained from a prediction program run outside of the aircraft The prediction program must comply with the criteria of Appendix 1 of AC90 96 ln the event of a pr...

Page 431: ...nvalid utilize remaining operational navigation equipment as required 2 ll a RAIM NOT AVAILABLE message is displayed while conducting an instrument approach terminate the approach Execute a missed approach if required 3 lf a RAIM NOT AVAII ABLE message is dispfayed in the en route or terminal phase of flight continue to navigate using the KLN 94 or revert to an alternate means of navigation approp...

Page 432: ...lot by first selecting GPS on the NAV GPS switch Manual selection of the desired track on the pilot s DG heading bug is required to provide course datum to the KAP 140 autopilot Frequent course datum changes may be necessary such as in the case of flying a DME arc The autopilot approach mode APR should be used when conducting a coupled GPS approach NOTE NAV or APR coupled DME arc intercepts can re...

Page 433: ...he PROC PROCEDURE button on the KLN 94 a Press PROC button b Select Approach Arrival or Departure c Select ttie airport from the list or enter the desired airpoft identifier d The APT 7 or APT I page will be displayed as appropriate NOTE To delete or replace a DP STAR or approach select FPL O page Place the cursor over the name of the proceduie press ENT to change it or GLR then ENT to delete it 2...

Page 434: ...nbound to the FAF NOTE OBS navigation is TO FROM like a VOR without waypoint sequencing b lf receiving radar vectors choose VECTORS as the lAF activate vectors when the first vector for the approach is received and leave the unit in LEG mode c NoPT routes including DME arc s are flown in LEG LEG is mandatorv from the FAF to the MAP NOTE NAV or APR coupled DME arc intercepts can result in excessive...

Page 435: ...le scaling change from 1 0 nm to 0 3 nm over the 2 nm inbound to the FAF c lnternally the KLN 94 will transition from terminal to approach integrity monitoring 7 Crossing the FAF and APR ACTV is q annunciated a Do not descend b Execute the missed approach 8 Missed Approach a b Navigate to the available There is no automatic LEG sequencing at the MAP c After climbing in accordance with the publishe...

Page 436: ... m MAP h missed approach holding fix The DME arc IAF arc intercept waypoint will be on your present position radial otf the arc VOR when you load the IAF into the flight plan or the beginning of the arc if currently on a radial beyond the arc limit To adjust the arc intercept to be compatible with a current radar vector bring up the arc IAF waypoint in the NAV 4 page scanning field or under the cu...

Page 437: ...lagged navigation inside the FAF may automatically bring up the message page stating PRESS PROC BUTTON NOW FOR NAVIGATION Pressing the PROC button will usually restore navigation not guaranteed by changing from APR ACTV to APR ARM Fly the missed approach The instrument approach using the KLN 94 may be essentially automatic starting 30 nm out with a manual baro setting update or it may require judi...

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