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Cessna 172S Nav III, Pilot Operating Handbook

The Cessna 172S Nav III Information Manual is a comprehensive user guide essential for pilots operating this aircraft model. With easy-to-follow instructions and detailed diagrams, this manual assists in understanding the aircraft's systems, controls, and procedures. Download the free manual from manualshive.com to ensure a safe and efficient flight experience.

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Summary of Contents for 172S Nav III

Page 1: ... 172810506 and 172810508 thru 172810639 and 172810641 thru 172810655 PILOT 8 OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL 15 MAY 2008 PART NUMBER 1728PHAU8 04 TR02 INSERT THE FOLLOWING TEMPORARY REVISION LIST AND TEMPORARY REVISION INTO THE PILOT S OPERATING HANDBOOK IN ACCORDANCE WITH THE FILING INSTRUCTIONS ...

Page 2: ...REVISION MODEL 172S NAV III OPTION Serials 172S981 0 and On PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL REVISION 4 12 OCTOBER 2006 172SPHAUS 04 ...

Page 3: ...al No 172510472 Registration No N2172V This publication includes the material required to be furnished to the pilot by 14 CFA part 23 APPROVED BY f Member of GAMA rMN IINMD1NIIR MCllllMIn Zt _ 1JtII _ COPYRIGHT 2005 DATE OF APPROVlU PZ Uj _K CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA ORIGINAL ISSUE 25 FEBRUARY 2005 172SPHAUS 04 REVISION 4 12 OCTOBER 2006 U S ...

Page 4: ...THIS MANUAL WAS PROVIDED FOR THE AIRPLANE IDENTIFIED ON THE TITLE PAGE ON 04 05 2007 SUBSEQUENT REVISIONS SUPPLIED BY CESSNA AIRCRAFT COMPANY MUST BE PRORERLYINSERTED ...

Page 5: ...AV III Pilot s Operating Handbook and FAA Approved Airplane Flight Manual 172S NAV III AVIONICS OPTION Serials 172S981 0 and On Original Issue 25 February 2005 Revision 4 12 October 2006 PART NUMBER 172SPHAUS 04 172SPHAUS 04 U S i ii ...

Page 6: ...re contained in the Customer Care Program Handbook supplied with your airplane The Customer Care Card assigned to you at delivery will establish your eligibility under warranty and should be presented to your local Cessna Service Station at the time of warranty service FACTORY TRAINED PERSONNEL to provide you with courteous expert service FACTORY APPROVED SERVICE EQUIPMENT to provide you efficient...

Page 7: ...ime 4 26 HOURS Range at 10 000 Feet 45 power Range 638 NM 53 Gallons Usable Fuel Time 6 72 HOURS RATE OF CLlMB AT SEA LEVEL 730 FPM SERVICE CEILING 14 000 FEET TAKEOFF PERFORMANCE I Ground Roll Total Distance Over 50 Foot Obstacle LANDING PERFORMANCE I Ground Roll Total Distance Over 50 Foot Obstacle STALL SPEED Flaps Up Power Off Flaps Down Power Off 960 FEET 1630 FEET 575 FEET 1335 FEET 53 KCAS ...

Page 8: ...n airplane equipped with speed fairings which increase the speeds by approximately 2 knots There is a corresponding difference in range while all other performance figures are unchanged when speed fairings are installed The above performance figures are based on airplane weights at 2550 pounds standard atmospheric conditions level hard surface dry runways and no wind They are calculated values der...

Page 9: ...vides information on special operations Supplements are individual documents and may be issued or revised without regard to revision dates which apply to the POH itself These supplements contain a Log of Effective Pages which should be used to determine the status of each supplement ORIGINAL ISSUE AND REVISIONS This Pilot s Operating Handbook and FAA Approved Airplane Flight Manual is comprised of...

Page 10: ...umber and revision level for each page within the POH As revisions to the POH occur the revision level on effected pages is updated When two pages display the same page number the page with the latest revision level shall be inserted into the POH The revision level on the Log Of Effective Pages shall also agree with the revision level of the page in question TEMPORARY REVISIONS Under limited circu...

Page 11: ... has been revised or is all new material The miniature hand will point to the figure number All revised pages will carry the revision number opposite the page number on the applicable page A list of revisions is located at the beginning of the Log Of Effective Pages WARNINGS CAUTIONS AND NOTES Throughout the text warnings cautions and notes pertaining to airplane handling and operations are utiliz...

Page 12: ... 4 12 October 2006 Revision 2 19 July 2005 Page Page RevIsion Number Status Number o Title Revised 4 Assignment Record Revised 1 o i ii Revised 4 iii Original 0 iv thru vii Revised 1 viii Revised 3 o ix thru xi xii Revised 4 xiii xiv Added 3 1 1 1 2 thru 1 28 Original 0 02 1 2 2 Revised 4 2 3 thru 2 8 Revised 3 02_9 Revised 4 2 10 thru 2 11 Revised 3 2 12 Revised 2 2 13 Original 0 2 14 Revised 3 2...

Page 13: ...nal 0 4 10 thru 4 38 Revised 3 4 39 Revised 4 4 40 thru 4 50 Revised 3 5 1 5 2 thru 5 23 5 24 Original 0 6 1 6 2 thru 6 12 Revised 1 6 13 Revised 4 6 14 thru 6 23 6 24 Revised 1 7 1 thru 7 2 Original 0 7 3 7 4 Revised 3 7 5 thru 7 10 Original 0 7 11 thru 7 12 Revised 3 7 13 thru 7 35 Original 0 7 36 Revised 3 7 37 thru 7 44 Original 0 7 45 thru 7 48 Revised 3 7 49 thru 7 54 Original 0 7 55 thru 7 ...

Page 14: ...sed 3 7 66 Original 0 7 67 thru 7 68 Revised 3 7 69 Original 0 7 70 thru 7 72 Revised 3 8 1 thru 8 2 Revised 3 8 3 thru 8 12 Original 0 8 13 Revised 3 8 14 thru 8 22 Original 0 8 23 Revised 4 8 24 Original 0 8 25 thru 8 26 Revised 3 9 1 9 2 Original 0 APPROVED BY FMII PIICM IIHJER CAt IUPNITJ c n c DIiIIgIlIIIICI II DATE OF APPROVAL I172SPHAUS 04 U S xi xii ...

Page 15: ...nying attached FAA Approved Temporary Revision page s mayor may not be applicable to your serial airplane Please refer to the individual FAA Approved Temporary Revision page s to determine applicability status for your airplane ...

Page 16: ...AA Approved AirpJane Flight Manual until the removal instructions have been complied with Insert this page opposite the Log of Effective Pages in the front of this basic U S Pilot s Operating Handbook and FM Approved Airplane Flight Manual TEMPORARY PAGE 155UE 5ERVICE BULLETIN MODIFICATION REVI510N NUMBER NUMBER DATE KIT IF APPLICABLE OR 5ERIAL 1725PHAU5 04 TR01 2 18 1725PHAU5 04 TR02 2 19 U 5 EFF...

Page 17: ...OF CONTENTS SECTION GENERAL 1 LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT AND BALANCE EQUIPMENT LIST 6 AIRPLANE AND SYSTEMS DESCRIPTION 7 HANDLING SERVICE AND MAINTENANCE 8 SUPPLEMENTS 9 I172SPHAUS 03 U S xiii xiv ...

Page 18: ...ings 1 8 Symbols Abbreviations and Terminology 1 9 General Airspeed Terminology And Symbols 1 9 Meteorological Terminology 1 10 Engine Power Terminology 1 10 Airplane Performance And Flight Planning Terminology 1 11 Weight And Balance Terminology 1 12 Metric Imperial 1U S Conversion Charts 1 14 Weight Conversions 1 15 Length Conversions 1 17 Distance Conversions 1 21 Volume Conversions 1 22 Temper...

Page 19: ...CESSNA MODEL 172S NAV III SECTION 1 GENERAL 1 36 1 76 MAX Figure 1 1 Three View Normal Ground Attitude Sheet 1 of 2 172SPHAUS OO U S 1 3 ...

Page 20: ...h is 65 Propeller ground clearance is 11 1 4 Wing area is 174 square feet Minimum turning radius pivot point to outboard wing tip is 27 51 2 Norrnal ground attitude is shown with nose strut showing approximately 2 of strut and wings level 81 11 MAX Figure 1 1 Three View Norrnal Ground Attitude Sheet 2 1 4 U S 172SPHAUS OO ...

Page 21: ...ycoming Engine Model Number IO 360 L2A Engine Type Normally aspirated direct drive air cooled horizontally opposed fuel injected four cylinder engine with 360 cu in displacement Horsepower Rating and Engine Speed 180 rated BHP at 2700 RPM PROPELLER Propeller Manufacturer McCauley Propeller Systems Propeller Model Number 1A170E JHA7660 Number of Blades 2 Propeller Diameter 76 inches Propeller Type ...

Page 22: ... left or Right position Refer to Figure 1 1 for normal ground attitude dimensions OIL Oil Specification Mll l 6082 or SAE J1966 Aviation Grade Straight Mineral Oil Used when the airplane was delivered from the factory and should be used to replenish the supply during the first 25 hours This oil should be drained and the filter changed after the first 25 hours of operation Refill the engine with Ml...

Page 23: ...F to 21 C 70 F 30 30 40 or 20W 40 Below 12 C 10 F 20 300r20W 30 180 O F to 320 90 F 20W 50 20W SO or 1SW SO All Temperatures 1SW SO or 20W SO NOTE When operating temperatures overlap use the lighter grade of oil Oil Capacity Sump 8 U S Quarts Total 9 U S Quarts MAXIMUM CERTIFICATED WEIGHTS Ramp Weight Takeoff Weight Landing Weight 172SPHAUS 00 Normal Category 2558 Ibs Utility Category 2208 Ibs Nor...

Page 24: ...In this category the rear seat must not be occupied and the baggage compartment must be empty STANDARD AIRPLANE WEIGHTS Standard Empty Weight Maximum Useful Load Normal Category Maximum Useful Load Utility Category CABIN AND ENTRY DIMENSIONS 16631bs 8951bs 5451bs Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6 BAGGAGE SPACE AND ENTRY DIMENSIONS Dimens...

Page 25: ...ed without overstressing the airirame 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 the speed limit that may not be exceeded at any time Stalling Speed or the minimum steady flight speed is the ...

Page 26: ...uring a full RPM throttle engine runup when the airplane is on the ground and stationary MAP Lean Mixture Rich Mixture HO U S Manifold Absolute Pressure is the absolute pressure measured in the engine induction system MAP is measured in units of inches of mercury inHG Decreased proportion of fuel in the fuel air mixture supplied to the engine As air density decreases the amount of fuel required by...

Page 27: ...NMPG g Course Datum 172SPHAUS OO Demonstrated Crosswind Velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests The value shown is not considered to be limiting Usable Fuel is the fuel available for flight planning Unusable Fuel is the quantity of fuel that can not be safely used ...

Page 28: ... by reducing the number of digits Center of Gravity is the point at which an airplane or equipment would balance if suspended Its distance 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 total weight Center of Gravity Limits are the ex...

Page 29: ...ng Maximum Ramp Weight is the maximum weight approved for ground maneuver and includes the weight of fuel used for start taxi and runup Maximum Takeoff Weight is the maximum weight approved for the start of the takeoff roll Maximum Landing Weight is the maximum weight approved for the landing touchdown Tare is the weight of chocks blocks stands etc used when weighing an airplane and is included in...

Page 30: ... convert U S measurement supplied with the Pilot s Operating Handbook into metric and imperial measurements The standard followed for measurement units shown is the National Institute of Standards Technology NIST Publication 811 Guide for the Use of the International System of Units SI Refer to the following pages for these charts 1 14 U S 172SPHAUS OO ...

Page 31: ...83 205 03 207 24 209 44 211 64 224 87 227 08 229 28 231 49 233 69 POUNDS INTO KILOGRAMS LIVRES EN KILOGRAMMES 2 3 4 5 6 kg kg kg kg kg 0 907 1 361 1 814 2 268 2 722 5 443 5 897 6 350 6 804 7 257 9 979 10 433 10 886 11 340 11 793 14 515 14 969 15 422 15 876 16 329 19 051 19 504 19 958 20 412 20 865 23 587 24 040 24 494 24 948 25 401 28 123 28 576 29 030 29 484 29 937 32 659 33 112 33 566 34 019 34 ...

Page 32: ...0 180 170 160 150 140 130 120 110 100 90 80 70 60 50 40 30 20 10 0 CESSNA MODEL 172S NAV III Pounds x 454 Kilograms KILOGRAMS 100 95 90 85 80 75 70 65 60 55 50 45 40 35 30 25 20 15 10 5 Units x 10 100 etc 0 Figure 1 2 Weight Conversions Sheet 2 1 16 U S 172SPHAUS OO ...

Page 33: ... 272 31 275 59 278 87 305 12 308 40 311 68 337 93 341 21 344 49 FEET INTO METERS PIEDS EN METRES 3 4 5 m m m 0 914 1 219 1 524 3 962 4 267 4 572 7 010 7 315 7 620 10 058 10 363 10 668 13 106 13 411 13 716 16 154 16 459 16 754 19 202 19 507 19 812 22 250 22 555 22 860 25 298 25 603 25 908 28 346 28 651 28 956 31 394 31 699 32 004 6 7 8 9 feet feet feet feet 19 685 22 956 26 247 29 528 52 493 55 774...

Page 34: ...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 CESSNA MODEL 172S NAV III Feet x 305 Meters Units x 10 100 etc Figure 1 3 Length Conversions Sheet 2 1 18 U S 172SPHAUS OO ...

Page 35: ...6 220 36 614 37 008 37 402 37 795 40 157 40 551 40 945 41 339 41 732 INCHES INTO CENTIMETERS POUCES EN CENTIMETRES 2 3 4 5 6 cm cm cm cm cm 5 08 7 62 10 16 12 70 15 24 30 48 33 02 35 56 38 10 40 64 55 88 58 42 60 96 63 50 66 04 81 28 83 82 86 36 88 90 91 44 106 68 109 22 111 76 114 30 116 84 132 08 134 62 137 16 139 70 142 24 157 48 160 02 162 56 165 10 167 64 182 88 185 42 187 96 190 50 193 04 20...

Page 36: ...I Centimeters x 394 Inches INCHES 10 Inches x 2 54 Centimeters CENTIMETERS 25 24 9 J 23 22 21 8 20 19 7 18 17 16 15 14 5 13 12 11 10 9 3 8 7 6 2 1 5 4 3 2 1 Units x 10 100 etc o L 0 _ Figure 1 4 Length Conversions Sheet 2 1 20 U S 172SPHAUS 00 ...

Page 37: ...rs Kilometers x 54 Nautical Miles STATUTE MILES NAUTICAL KILOMETERS MILES 115 100 100 110 180 95 95 105 90 90 170 100 85 85 160 95 150 90 80 80 85 75 75 140 80 70 70 130 75 65 65 120 70 60 60 110 65 55 55 60 100 50 50 90 55 50 45 45 80 45 40 40 70 40 35 35 35 60 30 30 30 25 25 50 25 20 20 40 20 30 15 15 15 10 10 20 10 5 5 5 10 Units x 10 100 etc 0 0 0 0 _ Figure 1 5 Distance Conversions 172SPHAUS ...

Page 38: ...8 20 678 20 898 21 118 22 438 22 658 22 878 23 098 23 318 IMPERIAL GALLONS INTO LITERS GALLONS IMPERIAL EN LITRES 2 3 4 5 6 Lt Lt Lt Lt Lt 9 092 13 638 18 184 22 730 27 276 54 552 59 097 63 543 68 189 72 735 100 01 104 56 109 10 113 65 118 20 145 47 150 02 154 56 159 11 163 66 190 93 195 48 200 02 204 57 209 11 236 39 240 94 245 48 250 03 254 57 281 85 286 40 290 94 295 49 300 03 327 31 331 86 336...

Page 39: ...llons 100 IMPERIAL 95 440 LlTERS GALLONS 420 90 400 85 380 80 360 75 340 70 320 65 300 60 280 260 55 240 50 220 45 200 40 180 35 160 30 140 25 120 20 100 80 15 60 10 40 5 20 0 0 Units x 10 100 etc Figure 1 6 Volume Conversions Sheet 2 172SPHAUS 00 SECTION 1 GENERAL 0585T1032 U S 1 23 ...

Page 40: ...lTERS GALLONS 100 120 GALLONS 100 95 115 95 360 90 110 90 340 105 85 100 85 320 80 95 80 300 75 90 75 280 70 85 70 260 65 80 65 75 240 60 70 60 220 55 65 55 200 50 60 50 180 45 55 45 50 40 160 40 45 140 35 40 35 30 35 30 120 25 30 25 100 20 25 20 80 15 20 15 60 15 10 40 10 10 5 5 5 20 0 0 0 0 Units x 10 100 etc 0585T1033 Figure 1 6 Volume Conversions Sheet 3 1 24 U S 172SPHAUS 00 ...

Page 41: ...10 500 260 60 520 70 20 540 280 80 560 90 30 580 300 100 40 600 320 110 620 120 50 640 340 130 660 140 60 680 360 150 700 160 70 720 380 170 180 80 740 760 400 190 90 780 420 20 800 210 100 820 440 220 840 230 110 860 460 240 BBO 250 120 900 480 260 27 130 920 940 500 2BO 140 960 520 290 9BO 300 150 1000 540 310 1020 320 160 1040 560 0585Tl034 Figure 1 7_ Temperature Conversions 172SPHAUS OO U_S_ ...

Page 42: ...SNA MODEL 172S NAV III PRESSURE CONVERSION HECTOPASCALS MILLIBARS TO INCHES MERCURY inHG l I I F I II le I C t a C I C le i g iI I iI i 1 F E 1 0 _1 I I I u 1 Figure 1 8 Heclopascals 10 Inches Mercury 1 26 U S 172SPHAUS OO ...

Page 43: ...LlTERS KILOGRAMS 100 100 95 150 135 130 95 90 140 125 90 85 120 85 130 AVGASFUEL 115 80 110 80 75 120 105 75 70 110 100 70 95 65 100 90 65 60 85 60 90 80 55 75 55 50 80 70 50 45 65 45 70 60 40 60 55 40 35 50 35 50 45 30 40 30 25 40 35 25 20 30 20 30 25 15 20 15 20 15 10 10 10 10 5 5 5 0 0 0 0 Un s x 10 100 etc Figure 1 9 Volume to Weight Conversion 172SPHAUS OO U S 1 27 ...

Page 44: ...SECTION 1 GENERAL AV GAS SPECIFIC GRAVITY 0 72 1 28 U S CESSNA MODEL 172S NAV III 0585T1031 Figure 1 10 Quick Conversions 172SPHAUS OO c ...

Page 45: ...ory Maneuver Limits Normal Category Utility Category Flight Load Factor Limits Normal Category Utility Category Kinds Of Operation Limits Kinds Of Operations Equipment List Fuel Limitations Flap Limitations System Limitations Aux Audio System 12V Power System G1000 Limitations GPS WAAS BendixlKing KAP 140 2 Axis Autopilot if installed Placards Page 2 3 2 4 2 5 2 6 2 7 2 8 2 8 2 8 2 8 2 8 2 9 2 9 2...

Page 46: ...ection 9 of this Pilot s Operating Handbook for amended operating limitations operating procedures performance data and other necessary information for airplanes equipped with specific options The airspeeds listed in Figure 2 1 Airspeed I Limitations and Figure 2 2 Airspeed Indicator Markings are based on Airspeed Calibration data shown in Section 5 with the normal static source If the alternate s...

Page 47: ...ceed Speed 160 163 Do not exceed this speed in any operation VNO Maximum Structural 126 129 Do not exceed this Cruising Speed speed except in smooth air and then only with caution VA Maneuvering Do not make full or Speed abrupt control 2550 Pounds 102 105 movements above 2200 Pounds 95 98 this speed 1900 Pounds 88 90 VFE Maximum Flap Do not exceed this Ex1ended Speed speed with flaps Flaps 10 107 ...

Page 48: ...erating Range Lower limit is maximum weight VSo in landing configuration Upper limit is maximum speed permissible with flaps extended Green Arc 48 129 Normal Operating Range Lower limit is maximum weight VS1 at most forward C G with flaps retracted Upper limit is maximum structural cruising speed Yellow Arc 129 163 Operations must be conducted with caution and only in smooth air Red Line 163 Maxim...

Page 49: ... Oil Temperature 245 F 118 C Oil Pressure Minimum 20 PSI Oil Pressure Maximum 115 PSI Fuel Grade See Fuel Limitations Oil Grade Specification MIL L 6082 or SAE J1966 Aviation Grade Straight Mineral Oil or MIL L 22851 or SAE J1899 Ashless Dispersant Oil Oil must comply with the latest revision and or supplement for Textron Lycoming Service Instruction No 1014 Propeller Manufacturer McCauley Propell...

Page 50: ...ED YELLOW NORMAL INSTRUMENT LINE ARC MIN LWR ARC OPERATING RANGE Tachometer RPM Sea Level 2100 to 2500 5000 Feet 2100 to 2600 10 000 Feet 2100 to 2700 Cylinder 200 to 500 F Head Temperature Oil lOO to 245 F Temperature Oil Pressure Ot020 50 to 90 PSI PSI Fuel 0 1 5 0 5 to 24 Gallons Quantity Gallons to 5 Unusable Gallons Each Tank Fuel Flow Oto12GPH Vacuum 4 5 to 5 5 Indicator in hg Maximum operat...

Page 51: ...120 Ibs UTILITY CATEGORY I Maximum Ramp Weight Max mum Take ff Wei ht Maximum Landing Weight 2208 POUNDS 2200 POUNDS 2200 POUNDS I I Maximum Weight in Baggage Compartment In the utility category the baggage compartment must be empty and rear seat must not be occupied CENTER OF GRAVITY LIMITS NORMAL CATEGORY Center ol Gravity Range Forward 35 0 inches aft 01 datum at 1950 pounds or less with straig...

Page 52: ...RY This airplane is certificated in both the normal and utility category The normal category is applicable to aircraft intended for non aerobatic operations These include any maneuvers incidental to normal flying stalls except whip stalls lazy eights chandelles and turns in which the angle of bank is not more than 60 NORMAL CATEGORY MANEUVERS AND RECOMMENDED ENTRY SPEED Chandelles 105 KNOTS Lazy E...

Page 53: ...AND RECOMMENDED ENTRY SPEED I Chandelles 105 KNOTS Lazy Eights 105 KNOTS Steep Turns 95 KNOTS Spins Slow Deceleration Stalls Except Whip Stalls Slow Deceleration 1 Abrupt use of the controls is prohibited above 98 KNOTS Aerobatics that may impose high loads should not be attempted The important thing to bear in mind in flight maneuvers is that the airplane is clean in aerodynamic design and will b...

Page 54: ...he design load factors are 150 of the above and in all cases the structure meets or exceeds design loads KINDS OF OPERATION LIMITS The Cessna 172S Nav III airplane is approved for day and night VFR and IFR operations Flight into known icing conditions is prohibited The minimum equipment for approved operations required under the Operating Rules are defined by 14 CFR Part 91 and 14 CFR Part 135 as ...

Page 55: ...LlGHT 1 BendixlKing KAP 140 POH 0 0 AIR AIR Accessible to pilot Supplement in flight when usin autopilot COMMUNICATIONS 1 VHFCOM 0 0 1 1 ELECTRICAL POWER 1 24V Main Battery 1 1 1 1 2 28V Alternator 1 1 1 1 3 24V Standby Battery 0 Refer to Note 1 4 Main Ammeter 1 1 1 1 5 Standby Ammeter 0 Refer to Note 1 NOTE 1 The European Aviation Safety Agency EASA 2 12 U S requires the 24V Standby Battery and S...

Page 56: ...or 1 1 1 1 3 Elevator Trim System 1 1 1 1 4 Elevator Trim Indicator 1 1 1 1 FUEL SYSTEM 1 Electric Fuel Pump 1 1 1 1 2 Fuel Quantity Indicator LH 1 1 1 1 Tank 3 Fuel Quantity Indicator RH 1 1 1 1 Tank ICE AND RAIN PROTECTION 1 Alternate Static Air Source 0 0 1 1 2 Alternate Induction Air 0 0 1 1 System INDICATING RECORDING SYSTEM 1 Stall Warning System 1 1 1 1 2 System Annunciator and 1 1 1 1 Warn...

Page 57: ...tandby Internal 0 1 0 1 Lighting 8 Non stabilized Magnetic 0 1 0 1 Compass Internal Lighting 9 Attitude Indicator Vacuum 0 1 0 1 Internal Lighting 10 Cockpit Flood Light 0 1 0 1 11 Aircraft Position NAV 0 1 1 1 Lights 12 STROBE Light System 1 1 1 1 13 BEACON Light 0 0 0 0 14 TAXI Light 0 0 0 0 15 LAND Landing Light 0 1 0 1 Operations for hire only NOTE 2 PFD backlighting is required for day VFR fl...

Page 58: ...acon Receiver 14 Blind Altitude Encoder 15 Clock VACUUM 1 Engine driven Vacuum Pump 2 Vacuum Indicator ENGINE FUEL AND CONTROL 1 Fuel Flow Indicator ENGINE INDICATING 1 Tachometer RPM 2 Cylinder Head Temperature CHT Indicator 3 Oil Pressure Indicator 4 Oil Temperature Indicator ENGINE OIL 1 Engine Crankcase Dipstick IFAA APPROVED 172SPHAUS 02 KIND OF OPERATION V I F F V R I R F F R N R N I I D G D...

Page 59: ...al ground attitude definition ITakeoff and land with the fuel selector valve handle in the BOTH position Maximum slip or skid duration with one tank dry 30 seconds Operation on either LEFT or RIGHT tank limited to level flight only With 1 4 tank or less prolonged uncoordinated flight is prohibited when operating on either left or right tank Fuel remaining in the tank after the fuel quantity indica...

Page 60: ...ortable electronic device s will not cause interference with the navigation or communication system of the airplane 12V POWER SYSTEM The 12 Volt Power System POWER OUTLET 12V 10A is not certified for supplying power to flight critical communications or navigation devices Use of the 12 Volt Power System is prohibited during takeoff and landing Use of the 12 Volt Power System is prohibited under IFR...

Page 61: ...ity of the pilot to see and maneuver to avoid traffic Use of the TERRAIN PROXIMITY information for primary terrain avoidance is prohibited The TERRAIN PROXIMITY map is intended only to enhance situational awareness It is the pilot s responsibility to provide terrain clearance at all times Navigation using the G1000 is not authorized north of 70 North latitude or south of 70 South latitude due to u...

Page 62: ...book and FAA Approved Airplane Flight Manual adjacent to page 2 19 This temporary revision must be removed and discarded when Revision 5 has been collated into the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual or when terrain database 08T2 or later is installed In Section 2 Operating Limitations G1000 Limitations Terrain Awareness and Warning System TAWS B add the follow...

Page 63: ...Receiver Autonomous Integrity Monitoring RAIM capability for TSO C129a non WAAS equipment e g oceanic operations U S RNAV routes European BRNAV and PRNAV etc the Garmin WAAS Fault Detection Exclusion Prediction program 006 A0154 01 or later approved version should be used to confirm the availability of RAIM for the intended route and time of flight Generic prediction tools do not provide an accura...

Page 64: ...omplied with when operating this airplane in this category or in the Utility Category are contained in the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual Normal Category Utility Category Spin Recovery No acrobatic maneuvers including spins approved No acrobatic maneuvers approved except those listed in the Pilot s Operating Handbook Baggage compartment and rear seat must not be...

Page 65: ... 5 GAL LEVEL FLIGHT ONLY 3 Near fuel tank filler cap FUEL 100LU100 MIN GRADE AVIATION GASOLINE CAP 26 5 U S GAL USABLE CAP 17 5 U S GAL USABLE TO BOTTOM OF FILLER INDICATOR TAB 4 On flap control indicator UP to 10 110 KIAS Partial flap range with blue color code also mechanical detent at 10 10 to FULL 85 KIAS IFAA APPROVED 172SPHAUS 04 White color code also mechanical detent at 20 Continued Next P...

Page 66: ...OOR LATCH MAXIMUM 120 POUNDS COMBINED FOR ADDITIONAL LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA 6 A calibration card must be provided to indicate the accuracy of the magnetic compass in 30c increments 7 On the oil filler cap OIL 8 aTS 8 On control lock CAUTION CONTROL LOCK REMOVE BEFORE STARTING ENGINE 9 Above the PFD MANEUVERING SPEED 105 KIAS Continued Next Page U S FAA APPROVED 172SPHAUS ...

Page 67: ... IN ACCORDANCE WITH FAR PART 91 207 11 On lorward lace 01 lirewall adjacent to the battery CAUTION 24 VOLTS D C THIS AIRCRAFT IS EQUIPPED WITH ALTERNATOR AND A NEGATIVE GROUND SYSTEM OBSERVE PROPER POLARITY REVERSE POLARITY WILL DAMAGE ELECTRICAL COMPONENTS 12 On the upper right instrument panel SMOKING PROHIBITED 13 Near the center overhead light control IFAA APPROVED 172SPHAUS 04 Flood Light U S...

Page 68: ... Flight Restart Procedures FORCED LANDINGS Emergency Landing Without Engine Power Precautionary Landing With Engine Power Ditching FIRES During Start On Ground Engine Fire In Flight Electrical Fire In Flight Cabin Fire Wing Fire ICING Inadvertent Icing Encounter During Flight Static Source Blockage Erroneous Instrument Reading Suspected F i Continued Next PaQj l Page 3 5 3 51 3 61 3 6 3 6 3 6 3 61...

Page 69: ...17 LOW VOLTS Annunciator Comes On or Does Not Go Off at Higher RPM 3 17 AIR DATA SYSTEM FAILURE 3 19 Red X PFD Airspeed Indicator 3 19 Red X PFD Altitude Indicator 3 19 ATTITUDE AND HEADING REFERENCE SYSTEM AHRS FAILURE 3 20 Red X PFD Attitude Indicator 3 20 Red X Horizontal Situation Indicator HSI 3 20 DISPLAY COOLING ADVISORY 3 20 PFD1 Cooling or MFD1 Cooling Annunciator s 3 20 VACUUM SYSTEM FAI...

Page 70: ...ry From Spiral Dive In The Clouds AHRS FAILED 3 29 Inadvertent Flight Into Icing Conditions 3 29 Static Source Blocked 3 30 Spins 3 30 Rough Engine Operation Or Loss 01 Power 3 31 Spark Plug Fouling 3 31 Magneto Mallunction 3 31 Idle Power Engine Roughness 3 31 Engine Driven Fuel Pump Failure 3 32 Excessive Fuel Vapor 3 32 Low Oil Pressure 3 32 Electrical Power Supply System Mallunctions 3 33 Exce...

Page 71: ... described in this section should be considered and applied as necessary to correct the problem In any emergency situation the most important task is continued control of the airplane and maneuver to execute a successful landing Emergency procedures associated with optional or supplemental equipment are found in Section 9 Supplements AIRSPEEDS FOR EMERGENCY OPERATION ENGINE FAILURE AFTER TAKEOFF W...

Page 72: ... Switch OFF 7 MASTER Switch ALT and BAT OFF ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF 1 Airspeed 70 KIAS Flaps UP 65 KIAS Flaps 10 FULL 2 Mixture Control IDLE CUTOFF pull full out 3 FUEL SHUTOFF Valve OFF pull full out 4 MAGNETOS Switch OFF 5 Wing Flaps AS REQUIRED FULL recommended 6 STBY BATT Switch OFF 7 MASTER Switch ALT and BAT OFF 8 Cabin Door UNLATCH 9 Land STRAIGHT AHEAD ENGINE FAILURE DURIN...

Page 73: ...f the indicated fuel flow FFLOW GPH immediately drops to zero a sign of failure of the engine driven fuel pump return the FUEL PUMP switch to the ON position FORCED LANDINGS EMERGENCY LANDING WITHOUT ENGINE POWER 1 Pilot and Passenger Seat Backs MOST UPRIGHT POSITION 2 Seats and Seat Belts SECURE 3 Airspeed 70 KIAS Flaps UP 65 KIAS Flaps 10 FULL 4 Mixture Control IDLE CUTOFF pull full out I 5 FUEL...

Page 74: ...I 12 Mixture Control IDLE CUTOFF pull full out 13 MAGNETOS Switch OFF I I 14 Brakes APPLY HEAVILY DITCHING 1 Radio TRANSMIT MAYDAY on 121 5 MHz Give location intentions and SQUAWK 7700 2 Heavy Objects in baggage area SECURE OR JETTISON if possible 3 Pilot and Passenger Seat Backs MOST UPRIGHT POSITION 4 Seats and Seat Belts SECURE 5 Wing Flaps 20 FULL 6 Power ESTABLISH 300 FT MIN DESCENT AT 55 KIA...

Page 75: ...tes 3 Engine SHUTDOWN and inspect for damage IF ENGINE FAILS TO START 2 Throttle Control FULL push full in 3 Mixture Control IDLE CUTOFF pull full out I 4 MAGNETOS Switch START continue cranking 5 FUEL SHUTOFF Valve OFF pull full out 6 FUEL PUMP Switch OFF 7 MAGNETOS Switch OFF 8 STBY BATT Switch OFF 9 MASTER Switch ALT and BAT OFF 10 Engine SECURE 11 Parking Brake RELEASE 12 Fire Extinguisher OBT...

Page 76: ...ll provide an incombustible mixture 7 Forced Landing EXECUTE Refer to EMERGENCY LANDING WITHOUT ENGINE POWER ELECTRICAL FIRE IN FLIGHT 1 STBY BATT Switch OFF 2 MASTER Switch ALT and BAT OFF 3 Vents Cabin Air Heat CLOSED 4 Fire Extinguisher ACTIVATE if available 5 AVIONICS Switch BUS 1 and BUS 2 OFF 6 All Other Switches except MAGNETOS switch OFF WARNING AFTER THE FIRE EXTINGUISHER HAS BEEN USED MA...

Page 77: ... Vents Cabin Air Heat CLOSED to avoid drafts 4 Fire Extinguisher ACTIVATE if available WARNING AFTER THE FIRE EXTINGUISHER HAS BEEN USED MAKE SURE THAT THE FIRE IS EXTINGUISHED BEFORE EXTERIOR AIR IS USED TO REMOVE SMOKE FROM THE CABIN 5 VentS Cabin Air Heat OPEN When sure that fire is completely extinguished 6 Land the airplane as soon as possible to inspect for damage WING FIRE 1 LAND and TAXI L...

Page 78: ...e build up select a suitable off airport landing site 6 With an ice accumulation of 0 25 inch or more on the wing leading edges be prepared for significantly higher power requirements higher approach and stall speeds and a longer landing roll 7 Leave wing flaps retracted With a severe ice build up on the horizontal tail the change in wing wake airflow direction caused by wing flap extension could ...

Page 79: ...Section 5 Figure 5 1 Sheet 2 Airspeedl Calibration Alternate Static Source correction chart EXCESSIVE FUEL VAPOR FUEL FLOW STABILlZATION PROCEDURES If flow fluctuations of 1 GPH or more or power surges occur 1 FUEL PUMP Switch ON 2 Mixture Control ADJUST As necessary for smooth enginel operation 3 Fuel Selector Valve SELECT OPPOSITE TANK if vapor symptoms continue 4 FUEL PUMP Switch OFF after fuel...

Page 80: ... 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 Wing Flaps AS REQUIRED 85 to 110 KIAS Flaps Up 10 Below 85 KIAS Flaps 10 FULL 3 Touchdown ON MAINS Hold nosewheel off the ground as long as possible 4 When nosewheel touches down maintain full up elevator as airplane slows to stop 3 14 U S 17...

Page 81: ...FF g STROBE Lights OFF h CABIN PWR 12V OFF NOTE The Main Battery supplies electrical power to the Main and Essential Buses until M BUS VOLTS decreases below 20 volts When M BUS VOLTS falls below 20 volts the Standby Battery System will automatically supply electrical power to the Essential Bus for at least 30 minutes Select COM1 MIC and NAV1 on the audio panel and tune to the active frequency befo...

Page 82: ...V2 will be inoperative once AVIONICS BUS 2 is selected to OFF NOTE When AVIONICS BUS 2 is set to OFF the following items will not operate KAP 140 Autopilot COMM2 GTX 33 Transponder GMA 1347 Audio Panel NAV2 GDU 1040 MFD I k AVIONICS Switch BUS 2 OFF KEEP ON if in clouds 3 Land as soon as practical NOTE Make sure a successful landing is possible before extending flaps The flap motor is a large elec...

Page 83: ...ES ON OR DOES NOT GO OFF AT HIGHER RPM 1 MASTER Switch ALT Only OFF 2 Alternator Circuit Breaker ALT FIELD CHECK IN 3 MASTER Switch ALT and BAT ON 4 Low Voltage Annunciator LOW VOLTS CHECK OFF 5 M BUS VOLTS CHECK 27 5 V minimum 6 M BAT AMPS CHECK CHARGING IF LOW VOLTS ANNUNCIATOR REMAINS ON 7 MASTER Switch ALT Only OFF I 8 Electrical Load REDUCE IMMEDIATELY as follows a AVIONICS Switch BUS 1 OFF b...

Page 84: ...30 minutes Select COM1 MIC and NAV1 on the audio panel and tune to the active frequency before setting AVIONICS BUS 2 to OFF If COM2 MIC and NAV2 are selected when AVIONICS BUS 2 is set to OFF the COM and NAV radios cannot be tuned i COM1 and NAV1 TUNE TO ACTIVE FREQUENCY j COM1 MIC and NAV1 SELECT COM2 MIC and NAV2 will be inoperative once AVIONICS BUS 2 is selected to OFF NOTE When AVIONICS BUS ...

Page 85: ...ATA SYSTEM FAILURE RED X PFD AIRSPEED INDICATOR 1 ADC AHRS Circuit Breakers CHECK IN ESS BUS and AVN BUS 1 If open reset close circuit breaker If circuit breaker opens again do not reset 2 Standby Airspeed Indicator USE FOR AIRSPEED INFORMATION RED X PFD ALTITUDE INDICATOR 1 ADC AHRS Circuit Breakers CHECK IN ESS BUS and AVN BUS 1 If open reset close circuit breaker If circuit breaker opens again ...

Page 86: ...1 If open reset close circuit breaker If circuit breaker opens again do not reset 2 Non Stabilized Magnetic Compass USE FOR HEADING INFORMATION DISPLAY COOLING ADVISORY PFD1 COOLING OR MFD1 COOLING ANNUNCIATOR S 1 Cabin Heat CABIN HT REDUCE minimum preferred 2 Forward Avionics Fan CHECK feel for airflow from screen on glareshield IF FORWARD AVIONICS FAN HAS FAILED 3 STBY BAIT Switch OFF unless nee...

Page 87: ...URING FLIGHT OR THE GYRO FLAG IS SHOWN ON THE STANDBY ATTITUDE INDICATOR THE STANDBY ATTITUDE INDICATOR MUST NOT BE USED FOR ATTITUDE INFORMATION HIGH CARBON MONOXIDE CO LEVEL ANNUNCIATOR if installed CO LVL HIGH ANNUNCIATOR COMES ON 1 CABIN HT Knob OFF push full in 2 CABIN AIR Knob ON pull full out 3 Cabin Vents OPEN 4 Cabin Windows OPEN 163 KIAS maximum windows open speed CO LVL HIGH ANNUNCIATOR...

Page 88: ...will provide added safety after a failure of this type Ilf an engine failure occurs immediately after takeoff in most cases the landing should be planned straight ahead with only small changes in direction to avoid obstructions Altitude and airspeed are seldom sufficient to execute the 1800 gliding turn necessary to return to the runway The checklist procedures assume that adequate time exists to ...

Page 89: ...CY PROCEDURES 12 000 z C c 8000 c W I W CD I I J C l jj J 6000 4000 2000 I172SPHAUS Ol MAXIMUM GLIDE SPEED 68 KIAS PROPELLER WINDMILLlNG FLAPS UP ZERO WIND 2 4 6 8 10 12 14 16 18 20 GROUND DISTANCE NAUTICAL MILES 0585T1011 Figure 3 1 I U S 3 23 ...

Page 90: ...face at touchdown Transmit Mayday messages on 121 5 MHz giving location and intentions and squawk 7700 Avoid a landing flare because of the difficulty in judging height over a water surface The checklist assumes the availability of power to make a precautionary water landing If power is not available use of the airspeeds noted with minimum flap extension will provide a more favorable attitude for ...

Page 91: ...engine flooding and subsequent collection of fuel on the parking ramp as the excess fuel drains overboard from the intake manifolds This is sometimes experienced in difficult starts in cold weather where engine preheat service is not available If this occurs the airplane should be pushed away from the fuel puddle before another engine start is attempted Otherwise there is a possibility of raw fuel...

Page 92: ...ndicators the pilot must rely on the standby attitude indicator and non stabilized magnetic compass for attitude and heading information The KAP 140 Autopilot will not operate in HDG mode without AHRS input With a valid GPS or NAV input and an operating turn coordinator the autopilot will operate in NAV APR or REV modes Autopilot altitude hold and vertical speed operating modes are independent of ...

Page 93: ... Maintain altitude and 15 bank angle Continue the turn for 60 seconds then roll back to level flight 3 When the compass card becomes sufficiently stable check the accuracy of the turn by verifying that the compass heading approximates the reciprocal of the original heading 4 If necessary adjust the heading by keeping the wings level and using the rudder to make skidding turns the compass will read...

Page 94: ...mpass heading and make minor corrections to hold an approximate course The autopilot may be engaged in ROL mode to keep the wings level and VS mode to control rate of descent Before descending into the clouds prepare for a stabilized descent as follows 1 Apply full rich mixture 2 Turn pitot heat on 3 Set power for a 500 to 800 feet per minute rate of descent 4 Set the elevator trim for a stabilize...

Page 95: ...Y DESCENT THROUGH THE CLOUDS procedure 8 Upon breaking out of clouds resume normal cruising flight INADVERTENT FLIGHT INTO ICING CONDITIONS Flight into icing conditions is prohibited and extremely dangerous An inadvertent encounter with these conditions can be resolved using the checklist procedures The best action is to turn back or change altitude to escape icing conditions Set the PITOT HEAT sw...

Page 96: ...ILERONS 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 Full down elevator may be required at aft center of gravity loadings to assure optimum recoveries 5 HOLD THESE CONTROL INPUTS UNTIL ROTATION STOPS Premature relaxation of the control inputs may e...

Page 97: ...NETOS switch from BOTH to the Land R switch positions will identify which magneto is malfunctioning Select different power settings and enrichen the mixture to determine if continued operation on BOTH magnetos is possible If not change to the good magneto and continue to thel nearest airport for repairs IDLE POWER ENGINE ROUGHNESS As Required by AD 2001 06 17 Paragraph d 3 I An excessively rich id...

Page 98: ...flow indicator FFLOW GPH fluctuations greater than 1 gal hr This condition with leaner mixtures or with larger fluctuations can result in power surges and if not corrected may cause power loss To slow vapor formation and stabilize fuel flow on the ground or in the air set the FUEL PUMP switch to the ON pOSition and adjust the mixture as required for smooth engine operation If vapor symptoms contin...

Page 99: ...iring is most likely the cause 0 alternator failures although other factors could cause the problem A defective alternator control unit ACU can also cause malfunctions Problems of this nature constitute an electrical emergency and should be dealt with immediately Electrical power malfunctions usually fall into two categories excessive rate of charge and insufficient rate of charge The following pa...

Page 100: ...e main battery ammeter and the low voltage annunciator lOW VOLTS will come on The ACU can de energize the alternator due to minor disturbances in the electrical system resulting in a nuisance opening of the AlT FIELD circuit breaker If this happens an attempt should be made to energize the alternator system To energize the alternator system 1 MASTER Switch AlT Only OFF 2 Alternator Circuit Breaker...

Page 101: ...ystems on the Essential Bus and cannot provide power for transponder XPDR operation Main battery life should be extended when practical for possible later operation of the wing flaps and use of the landing light at night NOTE The lOW VOLTS annunciator can come on when the engine is operated at low RPM with a high electrical load The lOW VOLTS annunciator will usually go off when the engine is oper...

Page 102: ...s mentioned above or the CO LVL HIGH warning annunciation comes on when using the cabin heater immediately turn off the cabin heater and preform the emergency items for HIGH CARBON MONOXIDE CO LEVEL When the CO detection system senses a CO level of 50 parts per million PPM by volume or greater the alarm turns on a flashing warning annunciation CO LVL HIGH in the annunciation window on the PFD with...

Page 103: ...g Edge RightWing Nose Left Wing Leading Edge Left Wing Left Wing Trailing Edge Before Starting Engine Starting Engine With Battery Starting Engine With External Power Before Takeoff Takeoff Normal Takeoff Short Field Takeoff Enroute Climb Cruise Descent Before Landing Continued Next Page Page 4 5 4 5 4 5 4 61 4 6 4 7 4 8 4 8 4 9 4 10 I 4 12 4 12 4 12 4 14 4 16 4 19 4 19 4 19 4 19 4 20 4 20 4 22 17...

Page 104: ...ng Engine 4 25 Recommended Starter Duty Cycle 4 26 Leaning For Ground Operations 4 27 Taxiing 4 27 Before Takeoff 4 29 Warm Up 4 29 Magneto Check 4 29 Alternator Check 4 29 Elevator Trim 4 30 Landing Lights 4 30 Takeoff 4 30 Power Check 4 30 Wing Flap Settings 4 31 Crosswind Takeoff 4 31 Enroute Climb 4 32 Cruise 4 32 Leaning Using Exhaust Gas Temperature EGT 4 34 Fuel Savings Procedures for Fligh...

Page 105: ...D PROCEDURES Continued Stalls Spins Holding Procedure Turns and Missed Approaches Landing Normal Landing Short Field Landing Crosswind Landing Balked Landing Cold Weather Operation Starting Winterization Kit Hot Weather Operation Noise Characteristics And Noise Reduction 172SPHAUS 03 U S 4 3 4 4 ...

Page 106: ...hort Field Takeoff Flaps 10 Speed at 50 Feet 56 KIAS ENROUTE CLIMB FLAPS UP Normal Sea Level 75 85 KIAS Normal 10 000 Feet 70 80 KIAS Best Rate of Climb Sea Level 74 KIAS Best Rate of Climb 10 000 Feet 72 KIAS Best Angle of Climb Sea Level 62 KIAS Best Angle of Climb 10 000 Feet 67 KIAS LANDING APPROACH Normal Approach Flaps UP 65 75 KIAS Normal Approach Flaps FULL 60 70 KIAS Short Field Approach ...

Page 107: ...d assist handles will simplify access to the upper wing surfaces for visual checks and refueling operations In cold weather remove even small accumulations of frost ice or snow from wing tail and control surfaces Also make sure that control surfaces contain no internal accumulations of ice or debris Prior to flight check that pitot heater is warm to touch within 30 seconds with battery and pitot h...

Page 108: ...SWITCH WERE ON DO NOT STAND NOR ALLOW ANYONE ELSE TO STAND WITHIN THE ARC OF THE PROPELLER SINCE A LOOSE OR BROKEN WIRE OR A COMPONENT MALFUNCTION COULD CAUSE THE ENGINE TO START 7 MAGNETOS Switch OFF 8 AVIONICS Switch BUS 1 and BUS 2 OFF 9 MASTER Switch ALT and BAT ON 10 Primary Flight Display PFD CHECK Verfiy PFD is ON I 11 FUEL QTY L and R CHECK 12 LOW FUEL L and LOW FUEL R Annunciators CHECK V...

Page 109: ...vator Trim Control TAKEOFF position 26 FUEL SELECTOR Valve BOTH I 27 AlT STATIC AIR Valve OFF push full in 28 Fire Extinguisher CHECK Verify gage pointer in green arc EMPENNAGE 1 Baggage Door CHECK lock with key 2 Autopilot Static Source if installed CHECK Verify opening is clear 3 Rudder Gust lock if installed REMOVE 4 Tail Tiedown DISCONNECT 5 Control Surfaces CHECK freedom of movement and secur...

Page 110: ...e any additional contaminants to the sampling points Take repealed samples from all fuel drain points until all contamination has been removed If contaminants are still present refer to WARNING below and do not fly airplane NOTE Collect all sampled fuel in a safe container Dispose of the sampled fuel so that it does not cause a nuisance hazard or damage to the environment WARNING IF AFTER REPEATED...

Page 111: ...l in a safe container Dispose of the sampled fuel so that it does not cause a nuisance hazard or damage to the environment WARNING IF AFTER REPEATED SAMPLING EVIDENCE OF CONTAMINATION STILL EXISTS THE AIRPLANE SHOULD NOT BE FLOWN TANKS SHOULD BE DRAINED AND SYSTEM PURGED BY QUALIFIED MAINTENANCE PERSONNEL ALL EVIDENCE OF CONTAMINATION MUST BE REMOVED BEFORE FURTHER FLIGHT 2 Engine Oil Dipstick Fil...

Page 112: ...t and aiter each refueling If water is observed take further samples until clear and then gently rock wings and lower tail to the ground to move any additional contaminants to the sampling points Take repeated samples from all fuel drain points until all contamination has been removed If contaminants are still present refer to WARNING below and do not fly airplane NOTE Collect all sampled fuel in ...

Page 113: ...SSIBLE DAMAGE TO AVIONICS 8 FUEL SELECTOR Valve BOTH 9 FUEL SHUTOFF Valve ON push full in STARTING ENGINE With Battery 1 Throttle Control OPEN 1 4 INCH 2 Mixture Control IDLE CUTOFF pull full out 3 STBY BAIT Switch a TEST Hold for 20 seconds verify that green TEST lamp does not go off b ARM Verify that PFD comes on 4 Engine Indicating System CHECK PARAMETERS Verify no red X s through ENGINE page i...

Page 114: ...arts I 16 Mixture Control ADVANCE smoothly to RICH when engine starts NOTE If the engine is primed too much flooded place the mixture control in the IDLE CUTOFF position open the throttle control 1 2 to full and engage the starter motor START When the engine starts advance the mixture control to the FULL RICH position and retard the throttle control promptly I 17 Oil Pressure CHECK Verify that oil...

Page 115: ...ECK Verify annunciator is shown 9 AVIONICS Switch BUS 1 and BUS 2 OFF 10 MASTER Switch ALTand BAT OFF I 11 Propeller Area CLEAR Verify that all people and eqUipment are at a safe distance from the propeller 1 12 External Power CONNECT to ground power receptacle 13 MASTER Switch ALT and BAT ON 14 BEACON Light Switch ON 15 M BUS VOLTS CHECK Verify that approximately 28 VOLTS is shown I I 16 17 NOTE ...

Page 116: ... power Latch external power receptacle door 24 Power INCREASE to approximately 1500 RPM for severall minutes to charge battery 25 AMPS M BATT and BATT S CHECK charge positive I 26 LOW VOLTS Annunciator CHECK Verify annunciator is not shown 27 Internal Power CHECK I a MASTER Switch ALT OFF b TAXI and LANDING Light Switches ON c Throttle Control REDUCE to idle I d MASTER Switch ALT and BAT ON e Thro...

Page 117: ...f installed NOTE There is no connection between the G1000 ALT SEL feature and the KAP 140 autopilot altitude preselect or altitude hold functions G1000 and KAP 140 altitudes are set independently 10 Standby Flight Instruments CHECK I 11 Fuel Quantity CHECK Verify level is correct NOTE Flight is not recommended when both fuel quantity indicators are in the yellow arc range 12 Mixture Control RICH 1...

Page 118: ...equency s SET 22 NAV Frequency s SET 23 FMS GPS Flight Plan AS DESIRED NOTE Check GPS availability on AUX GPS STATUS page No annunciation is provided for loss of GPS2 I 24 XPDR SET 25 CDI Softkey SELECT NAV source CAUTION THE G1000 HSI SHOWS A COURSE DEVIATION INDICATOR FOR THE SELECTED GPS NAV 1 OR NAV 2 NAVIGATION SOURCE THE G1000 HSI DOES NOT PROVIDE A WARNING FLAG WHEN A VALID NAVIGATION SIGNA...

Page 119: ...FD ANNUNCIATION WILL BE PROVIDED THE PREVIOUSLY SELECTED MODE SYMBOL SHOWN ON THE AUTOPILOT DISPLAY WILL BE FLASHING TO SHOW THE REVERSION TO ROLL MODE OPERATION IN ROLL MODE THE AUTOPILOT WILL ONLY KEEP THE WINGS LEVEL AND WILL NOT CORRECT THE AIRPLANE HEADING OR COURSE SET THE HOG BUG TO THE CORRECT HEADING AND SELECT THE CORRECT NAVIGATION SOURCE ON THE HSI USING THE COl SOFTKEY BEFORE ENGAGING...

Page 120: ...e altitude SHORT FIELD TAKEOFF 1 Wing Flaps 10 2 Brakes APPLY 3 Throttle Control FULL push full in I 4 Mixture Control RICH Above 3000 feet pressure altitude lean for maximum RPM 5 Brakes RELEASE 6 Elevator Control SLIGHTLY TAIL LOW 7 Climb Speed 56 KIAS Until all obstacles are cleared 8 Wing Flaps RETRACT SLOWLY When airspeed is mor than 60 KIAS ENROUTE CLIMB 1 Airspeed 70 85 KIAS 2 Throttle Cont...

Page 121: ...ure IFR DESCENT 1 Power AS DESIRED 2 Mixture ADJUST if necessary to make the engine run smoothly 3 Altimeters a PFD BARO SET b Standby Altimeter SET c KAP 140 Autopilot BARO SET if installed 4 G1000 ALT SEL SET 5 KAP 140 Altitude Preselect SET if installed NOTE There is no connection between the G1000 ALT SEL feature and the KAP 140 autopilot altitude preselect or altitude hold functions G1000 and...

Page 122: ...MODES IF THE HSI NAVIGATION SOURCE IS CHANGED FROM GPS TO NAV1 AUTOMATICALLY OR MANUALLY USING THE COl SOFTKEY OR MANUALLY FROM NAV2 TO GPS THE CHANGE WILL INTERRUPT THE NAVIGATION SIGNAL TO THE AUTOPILOT AND WILL CAUSE THE AUTOPILOT TO REVERT TO ROLL MODE OPERATION NO WARNING CHIME OR PFD ANNUNCIATION WILL BE PROVIDED THE PREVIOUSLY SELECTED MODE SYMBOL SHOWN ON THE AUTOPILOT DISPLAY WILL BE FLAS...

Page 123: ...stalled 7 CABIN PWR 12V Switch OFF if installed LANDING NORMAL LANDING 1 Airspeed 65 75 KIAS Flaps UP 2 Wing Flaps AS DESIRED UP 100 below 110 KIAS 100 FULL below 85 KIAS 3 Airspeed 60 70 KIAS Flaps FULL 4 Elevator Trim Control ADJUST 5 Touchdown MAIN WHEELS FIRST 6 Landing Roll LOWER NOSEWHEEL GENTLY 7 Braking MINIMUM REQUIRED SHORT FIELD LANDING 1 Airspeed 65 75 KIAS Flaps UP 2 Wing Flaps FULL 3...

Page 124: ...titude and 65 KIAS AFTER LANDING 1 Wing Flaps UP SECURING AIRPLANE 1 Parking Brake SET 2 Throttle Control IDLE pull full out I 3 Electrical Equipment OFF 4 AVIONICS Switch BUS 1 and BUS 2 OFF 5 Mixture Control IDLE CUTOFF pull full out I 6 MAGNETOS Switch OFF 7 MASTER Switch ALT and BAT OFF 8 STBY BATT Switch OFF 9 Control Lock INSTALL 10 FUEL SELECTOR Valve LEFT or RIGHT to prevent crossfeeding b...

Page 125: ...wing periodiC inspections If the airplane has been waxed or polished check the external static pressure source hole for stoppage If the airplane has been kept in a crowded hangar it should be checked for dents and scratches on wings fuselage and tail Isurfaces damage to navigation strobe lights and avionics antennas Check for damage to the nosewheel steering system the result of exceeding nosewhee...

Page 126: ...ht make sure the fuel tank filler caps are tightly sealed after any fuel system check or servicing Fuel system vents should also be inspected for obstructions ice or water especially after exposure to cold wet weather STARTING ENGINE In cooler weather the engine compartment temperature drops off rapidly following engine shutdown and the injector nozzle lines remain nearly full of fuel In warmer we...

Page 127: ...tional priming will be necessary After starting if the oil pressure gage does not begin to show pressure within 30 seconds in warmer temperatures and approximately one minute in very cold weather stop the engine and find cause before continued operation Lack of oil pressure can cause serious engine damage NOTE Additional details concerning cold weather starting and operation may be found under COL...

Page 128: ...XIING When taxiing it is important that speed and use of brakes be held to a minimum and that all controls be utilized Refer to Figure 4 2 Taxiing Diagram to maintain directional control and balance Taxiing over loose gravel or cinders should be done at low engine speed to avoid abrasion and stone damage to the propeller tips NOTE The LOW VOLTS annunciator may come on when the engine is operated a...

Page 129: ...III TAXIING DIAGRAM CODE WIND DIRECTION NOTE Strong quartering tail winds require caution Avoid sudden bursts of the throttle and sharp braking when the airplane is in this attitude Use the steerable nosewheel and rudder to maintain direction Figure 4 2 U S 172SPHAUS 03 ...

Page 130: ...difference between magnetos If there is a doubt concerning operation of the ignition system RPM checks at higher engine speeds will usually confirm whether a deficiency exists No RPM drop may indicate a faulty ground to one magneto or magneto timing set in advance of the angle specified ALTERNATOR CHECK Make sure that both the alternator and alternator control unit are operating properly before ni...

Page 131: ...tinuing the takeoff The engine should run smoothly and turn approximately 2300 2400 RPM with mixture leaned to provide maximum RPM Full throttle run ups over loose gravel are especially harmful to propeller tips When takeoffs must be made over a gravel surface advance the throttle slowly This allows the airplane to start rolling before high RPM is developed and the gravel will be blown behind the ...

Page 132: ...de no obstacles are ahead the airplane should be leveled off immediately to accelerate to a higher climb speed When departing a soft field with an aft C G loading the elevator trim control should be adjusted towards the nose down direction to give comfortable control wheel forces during the initial climb CROSSWIND TAKEOFF Takeoffs into strong crosswind conditions normally are performed with the mi...

Page 133: ...up and maximum power This speed is 62 KIAS at sea level increasing to 67 KIAS at 10 000 feet This type of climb should be of the minimum duration and engine temperatures should be carefully monitored due to the low climb speed CRUISE Normal cruise is performed between 45 and 75 power The engine RPM and corresponding fuel consumption for various altitudes can be determined by using the data in Sect...

Page 134: ...e use of low power settings are significant factors that should be considered on every trip to reduce fuel consumption In addition to power settings proper leaning techniques also contribute to greater range and are figured into cruise performance tables To achieve the recommended lean mixture fuel consumption figures shown in Section 5 the mixture should be leaned using the exhaust gas temperatur...

Page 135: ...linder EGTs should be within approximately 100 F of each other during normal operations An EGT difference greater than 100 F between cylinders indicates that fuel injection system maintenance is necessary EGT is displayed on the EIS ENGINE and LEAN pages The ENGINE page has a horizontal scale with a temperature indicator inverted triangle with a number representing the cylinder with the highest EG...

Page 136: ... PEAK OF value is negative the mixture can be on the lean side of peak Enrichen the mixture by slowly turning the mixture control clockwise and monitor both fuel flow and EGTs until the leanest cylinder returns to peak EGT PEAK 0 F or desired setting based on the EGT Table Figure 4 4 PEAK of values rich of peak will also be a negative value 50 The lean assist system calculation is defined such tha...

Page 137: ...ase in speed Under some conditions engine roughness may occur while operating at peak EGT In this case operate at the Recommended Lean mixture NOTE Any change in altitude or power setting will require a change in the recommended lean mixture setting and a recheck of the EGT setting The EGT indicators take several seconds after a mixture adjustment to start to show exhaust gas temperature changes F...

Page 138: ...re may remain leaned maximum RPM at full throttle for practicing maneuvers such as stalls and slow flight 3 Lean the mixture for maximum RPM during all operations at any altitude including those below 3000 feet when using 75 or less power NOTE When cruising or maneuvering at 75 or less power the mixture may be further leaned until the EGT indicator peaks and is then enrichened 50 F I This is espec...

Page 139: ...ion returns 2 Retard the throttle to idle to verify normal engine operation 3 Advance the throttle to 1200 RPM and lean the mixture as described under FUEL SAVINGS PROCEDURES FOR FLIGHT TRAINING OPERATIONS 4 In addition to the above procedures the Auxiliary Fuel Pump may be turned ON with the mixture adjusted as required to aid vapor suppression during ground operations The Auxiliary Fuel Pump sho...

Page 140: ...mum weight for both forward and aft C G positions are presented in Section 5 SPINS Intentional spins are approved when the airplane is operated in the utility category Spins with baggage loadings or occupied rear seat s are not approved However before attempting to perform spins several items should be carefully considered to assure a safe flight No spins should be attempted without first having r...

Page 141: ...r deflection is reached almost simultaneously with reaching full aft elevator A slightly greater rate of deceleration than for normal stall entries application of ailerons in the direction of the desired spin and the use of power at the entry will assure more consistent and positive entries to the spin As the airplane begins to spin reduce the power to idle and return the ailerons to neutral Both ...

Page 142: ...n of rotation difficult to determine see the turn vector near the index at the top of the Horizontal Situation Indicator HSI Variations in basic airplane rigging or in weight and balance due to installed equipment or right seat occupancy can cause differences in behavior particularly in extended spins These differences are normal and will result in variations in the spin characteristics and in the...

Page 143: ...either maneuver Holding pattern operations whether in the enroute or the terminal environment require temporary suspension of flight plan execution on reaching the holding waypoint If the holding pattern is part of an Instrument Approach Procedure lAP without an associated Procedure Turn suspend SUSP mode will be invoked automatically by the G1000 FMS GPS on reaching the holding waypoint usually a...

Page 144: ...ally or by setting the KAP 140 Autopilot to HDG mode and then setting the HDG bug on the PFD to command the Autopilot to turn to each new heading The KAP 140 Autopilot may be set to APR mode to track the inbound course but must be returned to HDG mode for command through the remainder of the holding pattern NOTE On interception of the inbound course for RNAV GPS Approach holding patterns SUSP will...

Page 145: ...approaches are managed by the Gl000 FMS GPS to provide course guidance and waypoint sequencing through the approach procedure For ILS approaches the Gl000 FMS GPS provides course guidance for the KAP 140 to capture the final approach course The G1000 will tune the NAV 1 radio to the applicable facility frequency with identifier and set the course pointer to the final approach course Within approxi...

Page 146: ...CT THE CORRECT NAVIGATION SOURCE ON THE HSI USING THE COl SOFTKEY BEFORE ENGAGING THE AUTOPILOT IN ANY OTHER OPERATING MODE Other VHF NAV based Instrument Approach Procedures VOR LaC LaC BC require the pilot to manually tune and identify the NAV facility select the corresponding NAV source on the HSI and set the HSI course pointer to the final approach course See the G1000 Cockpit Reference Guide ...

Page 147: ... The nosewheel must be lowered to the runway carefully after the speed has diminished to avoid unnecessary nose gear loads This procedure is very important for rough or soft field landings SHORT FIELD LANDING For a short field landing in smooth air conditions approach at 61 KIAS with FULL flaps using enough power to control the glide path Slightly higher approach speeds should be used in turbulent...

Page 148: ...eron deflection as applicable and occasional braking if necessary The maximum allowable crosswind velocity is dependent upon pilot capability as well as airplane limitations Operation in direct crosswinds of 15 knots has been demonstrated not an operating limitation BALKED LANDING In a balked landing go around climb reduce the flap setting to 20 immediately after full power is applied and climb at...

Page 149: ...tisfactory flight performance and handling Also control surfaces must be free of any internal accumulations of ice or snow If snow or slush covers the takeoff surface allowance must be made 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 takeoff in many instances STARTING When air temperature...

Page 150: ...e normal starting procedures However to conserve battery power the beaconl light can be left off until the engine is started Use caution to prevent inadvertent forward movement of the airplane during starting when parked on snow or ice NOTE If the engine does not start during the first few attempts or if engine firing diminishes in strength the spark plugs may be frosted over Preheat must be used ...

Page 151: ...ested to minimize the effect of airplane noise on the public 1 Pilots operating airplanes under VFR over outdoor assemblies of persons recreational and park areas and other noise sensitive areas should make every effort to fly not less than 2000 feet above the surface weather permitting even though flight at a lower level may be consistent with the provisions of government regulations 2 During dep...

Page 152: ... Alternate Static Source 5 10 Temperature Conversion Chart 5 11 Stall Speeds at 2550 Pounds 5 12 Crosswind Components 5 13 Short Field Takeoff Distance at 2550 Pounds 5 14 Short Field Takeoff Distance at 2400 Pounds 5 15 Short Field Takeoff Distance at 2200 Pounds 5 16 Maximum Rate Of Climb at 2550 Pounds 5 17 Time Fuel And Distance To Climb at 2550 Pounds 5 18 Cruise Performance 5 19 Range Profil...

Page 153: ...que fuel metering characteristics engine and propeller condition and air turbulence 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 conservative manner USE OF PERFORMANCE CHARTS Performance data is presented in tabular or graphical form to i...

Page 154: ...that distances shown are based on the short field technique Conservative distances can be established by reading the chart at the next higher value of weight altitude and temperature For example in this particular sample problem the takeoff distance information presented for a weight of 2550 pounds pressure altitude of 2000 feet and a temperature of 30 C should be used and results in the following...

Page 155: ...lection for cruise must be determined based on several considerations These include the cruise performance characteristics presented in Figure 5 8 the range profile chart presented in Figure 5 9 and the endurance profile chart presented in Figure 5 10 The relationship between power and range is illustrated by the range profile chart Considerable fuel savings and longer range result when lower powe...

Page 156: ...ect of a non standard temperature is to increase the time fuel and distance by 10 for each 1Q C above standard temperature due to the lower rate of climb In this case assuming a temperature 16 C above standard 16 C O C the correction would be 16 C X 10 16 Increase 1Q C With this factor included the fuel estimate would be calculated as follows Fuel to climb standard temperature Increase due to non ...

Page 157: ...uired for cruise is 3 2 hours X 8 9 gallons hour 28 5 Gallons A 45 minute reserve requires 45 60 X 8 9 gallons hour 6 7 Gallons The total estimated fuel required is as follows Engine start taxi and takeoff Climb Cruise Reserve Total fuel required 1 4 2 6 28 5 6 7 39 2 Gallons Once the flight is underway ground speed checks will provide a more accurate basis for estimating the time enroute and the ...

Page 158: ...Ground roll 650 Feet Total distance to clear a 50 foot obstacle 1455 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 159: ...light or maximum power descent FLAPS UP KIAS 50 60 70 80 90 100 110 120 130 140 150 160 KCAS 56 62 70 78 87 97 107 117 127 137 147 157 FLAPS 10 KIAS 40 50 60 70 80 90 100110 KCAS 51 57 63 71 80 89 99 109 FLAPS FULL KIAS 40 50 60 70 80 85 KCAS 50 56 63 72 81 86 Figure 5 1 Airspeed Calibration Sheet 1 of 2 172SPHAUS 00 U S 5 9 ...

Page 160: ...0 110 120 130 140 150 160 KCAS 56 62 68 76 85 95 105 115 125 134 144 154 FLAPS 10 KIAS 40 50 60 70 80 90 100110 KCAS 51 55 60 68 77 86 96 105 FLAPS FULL KIAS 40 50 60 70 80 85 _ _ M _ _ _ _ _ _ _ _ _ KCAS 49 54 61 69 78 83 _ _ M _ _ _ _ _ _ _ _ NOTE Windows closed ventilators closed cabin heater cabin air and defroster on maximum Figure 5 1 Airspeed Calibration Sheet 2 5 10 U S 172SPHAUS 00 ...

Page 161: ... III SECTION 5 PERFORMANCE 100 80 t w 60 J Z w a J L1 40 en w w a 20 w Cl 0 TEMPERATURE CONVERSION CHART ir 1 f t r t 1 1 20 0 20 40 DEGREES CELSIUS Figure 5 2 Temperature Conversion Chart 172SPHAUS OO 60 0585T1002 U S 5 11 ...

Page 162: ... 53 52 57 57 63 68 75 10 42 50 45 54 50 59 59 71 FULL 40 48 43 52 48 57 57 68 MOST FORWARD CENTER OF GRAVITY ANGLE OF BANK FLAP 0 30 45 60 SETTING KIAS KCAS KIAS KCAS KIAS KCAS KIAS UP 48 53 52 57 57 63 68 10 43 51 46 55 51 61 61 FULL 40 48 43 52 48 57 57 NOTE Altitude loss during a stall recovery may be as much as 230 feet KIAS values are approximate Figure 5 3 Stall Speeds KCAS 75 72 68 5 12 U S...

Page 163: ...5 PERFORMANCE 0 z 0 J z z w z 0 0 0 U 0 Z 0 Z CROSSWIND COMPONENT 20 15 10 1 30 35 CROSSWIND COMPONENT KNOTS NOTE Maximum demonstrated crosswind velocity is 15 knots not a limitation Figure 5 4 Crosswind Components 172SPHAUS OO U S 5 13 ...

Page 164: ...25 1925 1215 2080 1310 2240 1410 2420 1515 1235 2120 1335 2295 1440 2480 1550 2685 1660 1355 2345 1465 2545 1585 2755 1705 2975 1825 1495 2605 1615 2830 1745 3075 1875 3320 2010 1645 2910 1785 3170 1920 3440 2065 3730 2215 1820 3265 1970 3575 2120 3880 2280 4225 2450 NOTE Short field technique as specified in Section 4 Prior to takeoff from fields above 3000 feet elevation the mixture should be le...

Page 165: ...970 1665 1050 1795 1130 1930 1215 2080 1305 1065 1830 1150 1975 1240 2130 1335 2295 1430 1170 2015 1265 2180 1360 2355 1465 2530 1570 1285 2230 1390 2410 1500 2610 1610 2805 1725 1415 2470 1530 2685 1650 2900 1770 3125 1900 1560 2755 1690 3000 1815 3240 1950 3500 2095 NOTE Short field technique as specified in Section 4 Prior to takeoff from fields above 3000 feet elevation the mixture should be l...

Page 166: ...1365 860 1465 925 1570 995 1685 1065 870 1490 940 1605 1010 1725 1090 1855 1165 955 1635 1030 1765 1110 1900 1195 2035 1275 1050 1800 1130 1940 1220 2090 1310 2240 1400 1150 1985 1245 2145 1340 2305 1435 2475 1540 1270 2195 1370 2375 1475 2555 1580 2745 1695 NOTE Short field technique as specified in Section 4 Prior to takeoff from fields above 3000 feet elevation the mixture should be leaned to g...

Page 167: ...L 2000 4000 6000 8000 10 000 12 000 CLIMB SPEED KIAS 74 73 73 73 72 72 72 RATE OF CLIMB FPM 20 C O C 20 C 40 C 855 785 710 645 760 695 625 560 685 620 555 495 575 515 450 390 465 405 345 285 360 300 240 180 255 195 135 NOTE Mixture leaned above 3000 feet elevation for maximum RPM Figure 5 6 Maximum Rate of Climb 172SPHAUS 00 U S 5 17 ...

Page 168: ...000 73 600 6 1 5 5000 73 550 8 1 9 6000 73 505 10 2 2 7000 73 455 12 2 6 8000 72 410 14 3 0 9000 72 360 17 3 4 10 000 72 315 20 3 9 11 000 72 265 24 4 4 12 000 72 220 2B 5 0 NOTE Add 1 4 gallons of fuel for engine start taxi and takeoff allowance Mixture leaned above 3000 feet elevation for maximum RPM Increase time fuel and distance by 10 for each 10 C above standard temperature Distances shown a...

Page 169: ...550 79 118 10 6 73 117 9 9 68 117 2500 74 115 10 1 69 115 9 5 64 114 2400 65 110 9 1 61 109 8 5 57 107 2300 58 104 8 2 54 102 7 7 51 101 2200 51 98 7 4 48 96 7 0 45 94 2100 45 91 6 6 42 89 6 4 40 87 2650 83 122 11 1 77 122 10 4 72 121 2600 78 120 10 6 73 119 9 9 68 118 2500 70 115 9 6 65 114 9 0 60 112 2400 62 109 8 6 57 108 8 2 54 106 2300 54 103 7 8 51 101 7 4 48 99 2200 48 96 7 1 45 94 6 7 43 9...

Page 170: ...4 6 8 43 92 6 5 41 90 2700 78 124 10 5 72 123 9 8 67 122 2650 73 122 10 0 68 120 9 4 63 119 2600 69 119 9 5 64 117 9 0 60 115 2500 62 113 8 7 57 111 8 2 54 109 2400 55 106 7 9 51 104 7 5 49 102 2300 49 100 7 2 46 97 6 8 44 95 2650 69 121 9 5 64 119 8 9 60 117 2600 65 118 9 1 61 116 8 5 57 114 2500 58 111 8 3 54 109 7 8 51 107 2400 52 105 7 5 49 102 7 1 46 100 2300 47 98 6 9 44 95 6 6 41 92 NOTE Ma...

Page 171: ...d Lean Mixture for Cruise At All Altitudes Standard Temperature Zero Wind 12 000 _ ti w 10 000 1tH H H i ffiE 8 000 6 000 2 000 500 550 600 65 l 700 RANGE NAUTICAL MILES 0585T1004 NOTE This chart allows for the fuel used for engine start taxi takeoff and climb and the distance during climb Figure 5 9 Range Profile 172SPHAUS OO U S 5 21 ...

Page 172: ...GALLONS USABLE FUEL CONDITIONS 2550 Pounds Recommended Lean Mixture for Cruise At All Altitudes Standard Temperature 7 NOTE 8 0585T1005 This chart allows for the fuel used for engine start taxi takeoff and climb and the time during climb Figure 5 10 Endurance Profile 5 22 U S 172SPHAUS OO ...

Page 173: ...420 650 1455 670 610 1385 630 1425 655 1460 675 1495 695 630 1425 655 1460 675 1495 700 1535 725 655 1460 680 1500 705 1535 725 1575 750 680 1500 705 1540 730 1580 755 1620 780 705 1545 730 1585 760 1625 785 1665 810 735 1585 760 1630 790 1670 815 1715 840 NOTE Short field technique as specified in Section 4 Decrease distances 10 for each 9 knots headwind For operation with tail winds up to 10 kno...

Page 174: ...ghing Procedures 6 3 Airplane Weighing Form 6 5 Sample Weight and Balance Record 6 7 Weight And Balance 6 8 Baggage Tiedown 6 9 Sample Loading Problem 6 10 Loading Graph 6 12 Loading Arrangements 6 13 Internal Cabin Dimensions 6 14 Center of Gravily Moment Envelope 6 15 Center of Gravily Limits 6 16 Comprehensive Equipment List 6 17 172SPHAUS Ol U S 6 1 6 2 ...

Page 175: ...nd not by weighing the aircraft ITEM EMPTY WEIGHT EMPTY WEIGHT Cessna 172S FAA Flight Manual SUPPlements DATE DATE OF EXPIRY INDEFINITE 25 Oct 09 SUBJECT TO C A O 100 7 WEIGHT ARM MOMENT INDEX Kg mm IU 801 47 1062 851112 IMPERIAL WEIGHT ARM MOMENT lbs Inches 1766 9 41 809 73873 THE ABOVE WEIGHTS INCLUDE EMPTY WEIGHT UNUSABLE FUEL FUll ENGINE Oil LOAD SYSTEM 1 REFER TO FLIGHT MANUAL SUPPLEMENTS FOR...

Page 176: ...ment and installed equipment for this airplane as delivered from the factory can be found in the plastic envelope in the back of this handbook WARNING IT IS THE RESPONSIBILITY OF THE PILOT TO MAKE SURE THE AIRPLANE IS LOADED PROPERLY OPERATION OUTSIDE OF PRESCRIBED WEIGHT AND BALANCE LIMITATIONS COULD RESULT IN AN ACCIDENT AND SERIOUS OR FATAL INJURY AIRPLANE WEIGHING PROCEDURES 1 Preparation a In...

Page 177: ...to a plumb bob dropped from the firewall b Obtain measurement B by measuring horizontally and parallel to the airplane centerline from center of nose wheel axle left side to a plumb bob dropped from the line between the main wheel centers Repeat on right side and average the measurements 5 Using weights from step 3 and measurements from step 4 the Basic Empty Weight and C G can be determined by co...

Page 178: ...um Firewall front face lower portion FSO O MAC _ r 58 80 25 90 Level at upper door sill or leveling screws on left side of tailcone 101 100 50 o 50 100 150 200 250 300 Fuselage Station FS Inches NOTE It is the responsibility of the pilot to make sure that the airplane is loaded properly Figure 6 1 Sheet 1 of 2 I172SPHAUS 01 OS10noos I U S 6 5 ...

Page 179: ... and B Measure A and B per pilot s operating handbook instructions to assist in locating CG with airplane weighed on landing gear Airplane as Weighed Table Position Scale reading Scale drift Tare Net weight Left Wheel Right Wheel Nose Wheel Airplane total as weighed BaSIC Empty WeIght and Canter ol Gravlty Table Weight CGArm Moment Item Inch Pounds Pounds Inches 11000 Airplane calculated or as wei...

Page 180: ...e model I Serial number Page number Weight change Running Item no Description basic empty Date Added Removed weight of article or Om oen Cl men l rZ s j tI en r Z m E m In Out modification WT Arm Moment WT Arm Moment WT Moment lb in 1000 lb in 1000 lb 1000 As delivered G I E I m l G5 z J I C ID Z l 0 r III l Z Z 0 m m a ill m 0 c 0 ii a s en mm C zO 1 1 rO iii z 10 ...

Page 181: ...st be divided by 1000 and this value used as the momenV1000 on the loading problem Use the Loading Graph to determine the momenV1000 for each additional item to be carried then list these on the loading problem I I I 16 8 NOTE Loading Graph information for the pilot passengers and baggage is based on seats positioned for average occupants and baggage loaded in the center of the baggage areas as sh...

Page 182: ...in floor near each sidewall just forward of the baggage door approximately at station FS 90 two eyebolts are installed on thel cabin floor slightly inboard of each sidewall approximately at FS 107 and two eyebolts are located below the aft window near each sidewall approximately at FS 107 A placard on the baggage door defines the weight limitations in the baggage areas When baggage area A is utili...

Page 183: ...uel 30 Gallons 180 8 6 3 Pilot and Front Passenger FS 32 to 50 340 12 6 4 Rear Passengers FS 74 340 24 8 5 Baggage A FS 82 to 108 120 Pounds Maximum 56 4 6 6 Bag age B FS 108 to 142 50 ounds Maximum 7 RAMP WEIGHT AND MOMENT 2558 113 2 8 Fuel allowance for engine start taxi and runup 8 0 0 4 9 TAKEOFF WEIGHT AND MOMENT Subtract Step 8 from Step 7 2550 112 8 10 Locate this point 2550 at 112 8 on the...

Page 184: ...LANE Weight Moment Lb ins Ibs 11000 Weight Moment Lb ins Ibs 11000 Weight Moment Lb ins Ibs 11000 When several loading configurations are representative of your operations it may be useful to fill out one or more of the above columns so that specific loadings are available at a glance Figure 6 3 Sheet 2 I172SPHAUS 01 U S 6 11 I I ...

Page 185: ... E 100 Cl 3 50 7 q tti iP tu 25 o i 11U tth 1 ilti11J t LCttfttf 0 o 5 10 15 20 25 30 35 Load Moment 1000 Pounds Inches NOTE Lines representing adjustable seats show the pilot or passenger center of gravity on adjustable seats positioned for an average occupant Refer to the Loading Arrangements diagram for forward and aft limits of occupant C_G_ range_ I W Figure 6 4 16 12 U_S_ 172SPHAUS 01 ...

Page 186: ... and aft limits of occupant center of gravity range Arms measured to the center of the areas shown NOTE The usable fuel C G arm is located at FS 4B 00 The aft baggage wall approximate FS 108 00 or aft baggage wall approximate FS 142 00 can be used as a convenient interior reference point for determining the location of baggage area fuselage stations To achieve an airplane loading within the utilit...

Page 187: ... 8 1 f 65 25 65 30 Cabin Width Measurements Face of Rear Doorpost Forward Doorpost Instrument Panel Firewall o FS Lower Window Line Door Opening Dimensions Width Width Height Height Top Bottom Front Rear Cabin Door 32 00 37 00 40 50 39 00 Baggage Door 15 25 15 25 22 00 21 00 NOTE Maximum allowable floor loading 200 pounds square foot All dimensions shown are in inches I 16 14 U S __ Figure 6 6 172...

Page 188: ...00 Kilogram MiJlimeters 600 700 800 900 1000 1100 1200 1300 1400 1500 2600 2500 2400 gj 2300 c o 22oo E 0 2100 Cl c 2000 1900 Ifffilllml J 1800 1700 1600 1500 1150 1100 1050 Ci 1000E 950 S2 E 0 900 Cl C 850 e 800 3 750 700 50 60 70 80 90 100 110 120 130 Loaded Airplane MomenV1000 Pounds Inches __ Figure 6 7 I 172SPHAUS 01 U S 6 15 ...

Page 189: ...ANCE EQUIPMENT LIST MODEL 172S NAV III I CENTER OF GRAVITY LIMITS I 1600t ls00E E 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 Airplane C G Location Inches Aft of Datum FS 0 0 Figure 6 8 750 Q c as C 0 Q 0 3 6 16 U S 172SPHAUS 01 ...

Page 190: ...pment for FAA certification 14 CFR Part 23 or Part 91 S Standard equipment items 0 Optional equipment items replacing required or standard items A Optional equipment items which are in addition to required or standard items In the EQUIPMENT LIST DESCRIPTION column each item is assigned a descriptive name to help identify its function In the REF DRAWING column a Cessna drawing number is provided wh...

Page 191: ... 271C ROLL SERVO 3940400 1 3 6 54 2 23 COMMUNICATIONS 23 01 S STATIC DISCHARGE WICKS SET OF 10 0501048 1 0 4 143 2 23 18 R AUDIO INTERCOM MARKER BEACON GMA 1347 AUDIO PANEL 3930377 1 7 16 3 CI l02 MARKER BEACON ANTENNA 3960193 5 0 5 129 0 23 20 R NAV COMlGPS 1 COMPUTER 3921155 GIA 63 INTEGRATED AVIONICS UNIT 3940397 4 9 113 3 Cl 2480 200 VHF COMMlGPS ANTENNA 3960220 3 0 5 61 2 23 21 S NAV COM GPS ...

Page 192: ...ERTIA REEL MANUAL ADJUSTABLE PILOT AND FRONT PASSENGER 25 09 S SEAT BELT AND SHOULDER HARNESS 0519031 1 5 2 87 8 INERTIA REEL AUTO ADJUST REAR SEAT 25 10 0 SEAT BELT AND SHOULDER HARNESS 0519031 200 4 0 87 8 INERTIA REEL MANUAL ADJUSTABLE REAR SEAT 25 11 S SUN VISOR SET OF 2 0514166 2 1 1 32 8 25 12 S BAGGAGE RESTRAINT NET 2015009 7 0 5 95 0 25 13 S CARGO TIEDOWN RINGS SET OF 10 0515055 6 0 2 95 0...

Page 193: ...R C664503 0103 0506009 0 5 16 1 31 04 R PNEUMATIC STALL WARNING SYSTEM 0523112 0 4 28 5 31 05 R GEA 71 ENGINElAIRFRAME UNIT 3930377 2 2 11 4 31 06 R GTP 59 OUTSIDE AIR TEMPERATURE OAT 0518006 0 1 41 5 PROBE 32 LANDING GEAR 32 01 R WHEEL BRAKE AND TIRE 6 00 X 6 MAIN 2 0541200 7 8 34 4 57 8 WHEEL ASSEMBLY EACH C163001 0104 6 2 58 2 BRAKE ASSEMBLY EACH C163030 0111 1 8 54 5 TIRE 6 PLY 6 00 X 6 BLACKW...

Page 194: ...SPONDER 3910317 5 3 0 134 0 Cl 105 16 TRANSPONDER ANTENNA 3960191 0 4 86 3 34 18 R PFD DISPLAY 3930377 GDU l040 DISPLAY 3910317 1 6 3 16 4 34 19 R MFD DISPLAY 3930377 GDU l040 DISPLAY 3910317 1 6 3 16 4 34 20 R ATTITUDE HEADING REFERENCE SENSOR 3940397 AHRS GRS 77 AHRS 3910317 3 2 4 134 0 GMU 44 MAGNETOMETER 3940398 0 4 52 7 34 21 R AIR DATA COMPUTER 3940397 GDC 74A AIR DATA COMPUTER 3910317 6 1 7...

Page 195: ... S WINDOW HINGED LEFT DOOR 0517001 39 2 3 48 0 NET CHANGE 61 PROPELLER I 61 01 R FIXED PITCH PROPELLER 0550320 18 38 8 38 2 MCCAULEY 76 INCH PROPELLER lA170ElJHA7660 35 0 38 4 MCCAULEY 3 5 INCH PROPELLER C5464 3 6 36 0 SPACER 61 Q2 R SPINNER PROPELLER 0550320 11 1 8 41 0 SPINNER DOME ASSEMBLY 0550236 14 1 0 42 6 FWD SPINNER BULKHEAD 0552231 1 0 3 40 8 AFT SPINNER BULKHEAD 0550321 10 0 4 37 3 71 PO...

Page 196: ...SENSOR lA3C l 0501168 0 2 8 0 77 04 S CYLINDER HEAD THERMOCOUPLES 0501168 0 2 12 0 ALL CYLINDERS 32DKWUE006F0126 n 05 S EXHAUST THERMOCOUPLES 0501168 0 3 12 0 ALL CYLINDERS 86317 78 EXHAUST 78 01 R EXHAUST SYSTEM 9954100 1 16 3 20 0 MUFFLER AND TAILPIPE WELD ASSEMBLY 9954000 2 4 6 22 7 SHROUD ASSEMBLY MUFFLER HEATER 9954100 3 0 8 22 7 79 0IL 79 01 R OIL COOLER 108nA 0550365 2 3 11 0 79 2 R OIL PRE...

Page 197: ...t 7 10 Right Panel Layout 7 12 Center Pedestal Layout 7 12 Flight Instruments 7 15 Attitude Indicator 7 16 Airspeed Indicator 7 17 Altimeter 7 17 Horizontal Situation Indicator 7 18 Vertical Speed Indicator 7 19 Ground Control 7 20 Wing Flap System 7 21 Landing Gear System 7 22 Baggage Compartment 7 22 Seats 7 22 Integrated Seat Belt Shoulder Harness 7 23 Entrance Doors And Cabin Windows 7 26 Cont...

Page 198: ...Fuel System 7 36 Fuel Distribution 7 37 Fuel Indicating System 7 38 Auxiliary Fuel Pump Operation 7 39 Fuel Return System 7 41 Fuel Venting 7 41 Reduced Tank Capacity 7 41 Fuel Selector Valve 7 42 Fuel Drain Valves 7 42 Brake System 7 43 Electrical System 7 43 G1000 Annunciator Panel 7 48 Master Switch 7 48 Standby Battery Switch 7 49 Avionics Switch 7 49 Electrical System Monitoring And Annunciat...

Page 199: ...eading Reference System AHRS and GMU 44 Magnetometer GDC 74A Air Data Computer GEA 71 Engine Monitor GTX 33 Transponder GDL 69A XM Weather and Radio Data Link BendixlKing KAP 140 2 Axis Autopilot if installed Avionics Support Equipment Avionics Cooling Fans Antennas Microphone And Headset Installations Auxiliary Audio Input Jack 12V Power Outlet Static Dischargers Cabin Features Emergency Locator ...

Page 200: ...ch fittings at the base of the forward door posts for the lower attachment of the wing struts Four engine mount stringers are also attached to the forward door posts and extend forward to the firewall The ex1ernally braced wings containing integral fuel tanks are constructed of a front and rear spar with formed sheet metal ribs doublers and stringers The entire structure is covered with aluminum s...

Page 201: ... Construction of the elevator consists of formed leading edge skins a forward spar aft channel ribs torque tube and bellcrank left upper and lower V type corrugated skins and right upper and lower V type corrugated skins incorporating a trailing edge cutout for the trim tab The elevator tip leading edge extensions incorporate balance weights The elevator trim tab consists of a spar rib and upper a...

Page 202: ...CESSNA MODEL 172S NAV III SECTION 7 AIRPLANE AND SYSTEMS DESCRIPTION 0585T1017 Figure 7 1 Flight Control and Trim Systems Sheet 1 of 2 172SPHAUS OO U S 7 7 ...

Page 203: ...SECTION 7 AIRPLANE AND SYSTEMS DESCRIPTION ELEVATOR TRIM CONTROL SYSTEM CESSNA MODEL 172S NAV III 0585T1018 Figure 7 1 Flight Control and Trim Systems Sheet 2 7 8 U S 172SPHAUS OO ...

Page 204: ...rimary Flight Display PFD centered on the instrument panel in front of the pilot shows the primary flight instruments during normal operation During engine start reversionary operation MFD failure or when the DISPLAY BACKUP switch is selected the Engine Indication System EIS is shown on the PFD Refer to the Garmin G1000 Cockpit Reference Guide for specific operating information The Standby Battery...

Page 205: ...s controlled using the SW CB PANELS dimmer control See the ELECTRICAL EQUIPMENT descriptions in this section for further information CENTER PANEL LAYOUT The Garmin GMA 1347 Audio Panel is found on the upper half of the center instrument panel immediately to the right of the PFD A pushbutlon switch labeled DISPLAY BACKUP to manually select display reversion mode is found on the lower face of the GM...

Page 206: ...rument panel and not visible to the pilot provides a roll rate signal to the KAP 140 The KAP 140 receives NAV HDG and analog roll steering inputs from the G1000 system KAP 140 ROL VS and ALT modes operate independently from the G1000 Refer to sectionl 9 Supplement 3 for operation of the BendixlKing KAP 140 2 Axis Autopilot The engine controls are found on the lower center instrument panel below th...

Page 207: ...ation The Hour Hobbs meter is found to the right of the ELT switch and records engine operating time when oil pressure is greater than 20 PSI for maintenance purposes Refer to the ENGINE INSTRUMENTS description in this section for further information CENTER PEDESTAL LAYOUT The center pedestal located below the center panel contains the lelevator trim control wheel trim position indicator 12V power...

Page 208: ...CESSNA MODEL 172S NAV III SECTION 7 AIRPLANE AND SYSTEMS DESCRIPTION INSTRUMENT PANEL OI il Plt1 Figure 7 2 Instrument Panel Sheet 1 of 2 172SPHAUS OO U S 7 13 ...

Page 209: ...n Display Standby Altimeter ELT Remote Switch Annunciator Flight Hour Recorder Microphone Switch Cabin Heat Control Cabin Air Control Wing Flap Switch Lever And Position Indicator Mixture Control Hand Held Microphone Fuel Shutoff Valve Control Fuel Selector Valve 12V 10A Power Outlet Aux Audio Input Jack Elevator Trim Control Wheel And Position Indicator Throttle With Friction Lock ALT Static Air ...

Page 210: ... altitude and vertical speed The vertical indicators take the place of analog indicators with a fixed circular scale and rotating pointer Knobs knob sets two knobs on a common shaft and membrane type push button switches found on the bezel surrounding each GDU 1040 display control COM NAV XPDR and GPS avionics set BARO barometric pressure CRS course and HDG heading and work various flight manageme...

Page 211: ... of roll The roll pointer is slaved to the airplane symbol The pitch index scale is graduated in 5 increments with every 10 of pitch labeled If pitch limits are exceeded in either the nose up or nose down direction red warning chevrons will appear on the indicator to point the way back to level flight A small white trapezoid located below the roll pointer moves laterally left and right to provide ...

Page 212: ... right side of the attitude indicator on the GDU 1040 Primary Flight Display The altitude indication data is provided by the GDC 74A Air Data Computer unit The local barometric pressure is set using the BARO knob on the GDU 1040 displays The GDU 1040 BARO setting has no effect on the KAP 140 Autopilot BARO setting A cyan selectable altitude reference pointer bug is displayed on the altimeter tape ...

Page 213: ...based on the length of the magenta turn vector The cyan HSI heading reference pointer bug is set using the HDG knob on the GDU 1040 display The selected heading is shown digitally in a window above the upper LH 450 index mark The heading window will disappear approximately 3 seconds after the HDG knob stops turning The selected heading will provide the control input to the BendixlKing KAP 140 when...

Page 214: ...N ROL MODE THE AUTOPILOT WILL ONLY KEEP THE WINGS LEVEL AND WILL NOT CORRECT THE AIRPLANE HEADING OR COURSE SET THE HOG BUG TO THE CORRECT HEADING AND SELECT THE CORRECT NAVIGATION SOURCE ON THE HSI USING THE COl SOFTKEY BEFORE ENGAGING THE AUTOPILOT IN ANY OTHER OPERATING MODE VERTICAL SPEED INDICATOR The vertical speed indicator VS tape is found on the right side of the altimeter display along u...

Page 215: ...tow bar is not available or pushing is required use the wing struts as push points Do not use the vertical or horizontal surfaces to move the airplane If the airplane is to be towed by vehicle never turn the nose wheel more than 30 either side of center or structural damage to the nose gear could result The minimum turning radius of the airplane using differential braking and nose wheel steering d...

Page 216: ...r is moved up or down in a slotted panel that provides mechanical stops at the 10 20 and 30 pOSitions To change flap setting the flap lever is moved to the right to clear mechanical stops at the 10 and 20 positions A scale and pointer to the left of the flap switch indicates flap travel in degrees The wing flap system circuit is protected by a 10 ampere circuit breaker labeled FLAP on the left sid...

Page 217: ...rovided in the airplane 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 a single bench seat with adjustable back 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...

Page 218: ...ated seat belts shoulder harness assemblies Refer to Figure 7 4 The design incorporates an overhead inertia reel for the shoulder portion and a retractor assembly for the lap portion of the belt This design allows for complete freedom of movement of the upper torso area while providing restraint in the lap belt area In the event of a sudden deceleration reels lock up to provide positive restraint ...

Page 219: ...he buckle or by pressing the release button on the buckle and pulling out and up on the harness Spring tension on the inertia reel will automatically stow the harness A manually adjustable seat belt shoulder harness assembly is available for all seats To use the manually adjustable seat belt shoulder harness fasten and adjust the seat belt shoulder harness first Lengthen the seat belt as required ...

Page 220: ...EAT BELT SHOULDER HARNESS WITH INERTIA REEL VERTICAL HEIGHT ADJUSTMENT CRANK SEAT BACK ANGLE BUTTON FORE AND AFT ADJUSTMENT LEVER PRESS TO RELEASE PUSH BUTTON PUSH BUTTON RELEASE BUCKLE NON ADJUSTABLE RELEASE LATCH LlFTTO Figure 7 4 Integrated Seat Belt Shoulder Harness 172SPHAUS OO U S 7 25 ...

Page 221: ...handle near the aft edge of either door by grasping the forward edge of the handle and pulling outboard To close or open the doors from inside the airplane use the combination door handle and arm rest The inside door handle has three pOSitions and a placard at its base which reads OPEN CLOSE and LOCK The handle is spring loaded to the CLOSE up position When the door has been pulled shut and latche...

Page 222: ...ws and rear windows are of the fixed type and cannot be opened CONTROL LOCKS A control lock is provided to lock the aileron and elevator control surfaces to prevent damage to these systems by 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 contr...

Page 223: ...is open in the full forward pOSition and closed in the full aft position A friction lock which is a round knurled knob is located at the base of the throttle and is operated by rotating the lock clockwise to increase friction or counterclockwise to decrease it The mixture control mounted adjacent to the throttle control is a red knob with raised points around the circumference and is equipped with...

Page 224: ...as Temperature EGT Vacuum Fuel Quantity Engine Hours Electrical Bus Voltages and Battery Currents When the ENGINE softkey is pressed the LEAN and SYSTEM softkeys appear adjacent to the ENGINE softkey The LEAN page provides simultaneous indicators for CHT and EGT on all cylinders to be used for adjusting leaning the fuel air mixture The SYSTEM page provides numerical values for parameters on the EN...

Page 225: ...inter digital value and label RPM turn red to show engine speed is more than the limit The digital value and label RPM will flash The engine speed tachometer is displayed in the same configuration and location on the LEAN and SYSTEM pages If engine speed becomes 2780 RPM or more while on the LEAN or SYSTEM page the display will return to the ENGINE page A speed sensor mounted on the engine tachome...

Page 226: ...sure Oil pressure is shown numerically on the SYSTEM page When oil pressure is 0 to 20 PSI or 115 to 120 PSI the pointer digital value and label OIL PRES will change to red to show that oil pressure is outside normal limits If oil pressure exceeds either the upper or lower limit while on the LEAN or SYSTEM page the EIS will return to the ENGINE page When the engine speed RPM is in the green arc an...

Page 227: ... Engine oil temperature is displayed on the ENGINE page by the OIL TEMP horizontal indicator The indicator range is from 75 F to 250 F with a green arc normal operating range from lOO F to 245 F and a red arc from 245 F to 250 F A white pointer indicates actual oil temperature Oil temperature is displayed numerically on the SYSTEM page When oil temperature is in the red band 245 F to 250 F the poi...

Page 228: ... pointer indicates relative exhaust gas temperature while the number inside of the pointer identifies the hottest cylinder The EGT for all cylinders is shown on the LEAN page The hottest cylinder is indicated by the cyan bar graph The EGT for a particular cylinder may be shown by using the CYL SLCT softkey to select the desired cylinder Automatic indication of the hottest cylinder will resume a sh...

Page 229: ...oil then enters a pressure relief valve which regulates engine oil pressure by allowing excessive oil to return to the sump while the balance of the oil is circulated to various engine parts for lubrication Residual oil is returned to the sump by gravity flow An oil filler cap oil dipstick is located at the right rear of the engine The filler cap dipstick is accessible through an access door on th...

Page 230: ...s ram air through an intake on the lower front portion of the engine cowling The intake is covered by an air filter which removes dust and other foreign matter from the induction air Airflow passing through the filter enters an air box The air box has a spring loaded alternate air door If the air induction filter should become blocked suction created by the engine will open the door and draw unfil...

Page 231: ...urbine type fuel flow transducer mounted between the fuel air control unit and the fuel distribution unit produces a digital signal that displays fuel flow n the EIS pages COOLING SYSTEM Ram air for engine cooling enters through two intake openings in the front of the engine cowling The cooling air is directed around the cylinders and other areas of the engine by baffling and is then exhausted thr...

Page 232: ...0 3 0 53 0 Figure 7 5 Fuel System FUEL DISTRIBUTION Fuel flows by gravity from the two wing tanks to a three position selector valve labeled BOTH RIGHT and LEFT and on to the reservoir tank From the reservoir tank fuel flows through the auxiliary fuel pump past the fuel shutoff valve through the fuel strainer to an engine driven fuel pump From the engine driven fuel pump fuel is delivered to the f...

Page 233: ...pproximately 24 gallons and is indicated by the maximum limit of the green arc When the fuel level decreases below maximum travel of the fuel sensor the fuel quantity indicator will display fuel quantity measured in each tank A visual check of each wing tank fuel level must be performed prior to each flight Compare the visual fuel level and indicated fuel quantity to accurately estimate usable fue...

Page 234: ...er function is provided on the SYSTEM EIS page as GAL USED This digital indicator shows total fuel used since last reset of the totalizer To reset the fuel totalizer the SYSTEM EIS page must be active and the softkey RST USED must be selected The fuel totalizer provides no indication of the amount of fuel remaining in each tank and should only be used in conjunction with other fuel management proc...

Page 235: ... MODEL 172S NAV III FUEL OUANITY I VALVE 5 TOTAL FUEL FUEL TANK FUEL RESERVOIR TAt K__ L AUXiliARY FUEL u __ FUEL SHUT OFF VALVE KNOB FUEL 1 DRAIN FUEL RETURN _ _ _ _ 1 FUEL SUPPLY MECHANICAL liNKAGE ELECTRICAL CONNECTION DISTRIBUTION UNIT GEA71 ENGINE AND AIR FRAME Figure 7 6 Fuel System 7 40 U S 0585T1063 172SPHAUS 00 ...

Page 236: ...wer fuel temperatures at the engine inlet and helps to minimize the amount of fuel vapor generated in the fuel lines during high OAT operations See Section 4 for Hot Weather operating information FUEL VENTING Fuel system venting is essential to system operation Blockage of the system will result in decreasing fuel flow and eventual engine stoppage Venting is accomplished by an interconnecting line...

Page 237: ...een tanks can be expected when the tanks are nearly full and the wings are not level When the fuel tanks are 1 4 full or less prolonged uncoordinated flight such as slips or skids can uncover the fuel tank outlets Therefore if operating with one fuel tank dry or if operating on LEFT or RIGHT tank when 1 4 full or less do not allow the airplane to remain in uncoordinated flight for periods in exces...

Page 238: ...ft or spongy pedals and excessive travel and weak braking action If any of these symptoms appear the brake system is in need of immediate attention If during taxi or landing roll braking action decreases let up on the pedals and then reapply the brakes with heavy pressure If the brakes become spongy or pedal travel increases pumping the pedals should build braking pressure If one brake becomes wea...

Page 239: ...so connected to an avionics bus through a circuit breaker and the AVIONICS BUS 1 and BUS 2 switches Each avionics bus is powered when the MASTER switch BAT and the corresponding AVIONICS switch is in the ON position CAUTION BOTH BUS 1 AND BUS 2 AVIONICS SWITCHES SHOULD BE TURNED OFF TO PREVENT ANY HARMFUL TRANSIENT VOLTAGE FROM DAMAGING THE AVIONICS EQUIPMENT PRIOR TO TURNING THE MASTER SWITCH ON ...

Page 240: ... f J box V F 1Field Sensef Feeder Power Inf rmilrt r DAlt Input M Outp ut C B Not r 0 used spare Alternator Current Shunt O _B To sheet 2 Feeder CIB OO A To sheet 2 r 4i l r1 1 1I To WARN Not used __ g spare Magnetos Main Battery BAT ALT _J1 _ LJI ____ _ MASTER Switch B Ext Pwr A c __ I TIT nr ____1 To ALTFLD T Circuit Breaker External Power 077Oll519 Figure 7 7 Sheet 1 of 3 I 172SPHAUS 03 U S 7 4...

Page 241: ...N1 ALT FIEL D To feeder m B circuit breakers 1 A i U WARN 1 TQ aft master switch To stall warning autopilot warning ELTwaming main bus voltmeter hourmeter starter relay stdby battery To primary flight display To ail data computer To attitude heading reference system To navigation engine airfTame unit and essential bus voltimeter and main bIJI I sense VN2 PrTOT HEAT PITot Te pitot heat HEAT To NAV ...

Page 242: ...T On Off Control L O r v 7JTest Voltage Sense Test Load Test LED Light green l 1r 121Test iL_ SJAnnunciation Battery Fuse 5A ToStandby Standby Battery 0 J 1J Ammeter MFD or PFD L _ _ oFu sD e Current Shunt 5A lS 1 0 0 Main Bus c s WARN Voltage Sense L _____________________________ _ 077OT1S11l Figure 7 7 Sheet 3 I 172SPHAUS 03 U S 7 47 ...

Page 243: ...main battery electrical power to the airplane The ALT side of the switch controls the alternator system In normal operation both sides of the switch ALT and BAT are ON simultaneously however the BAT side of the switch may be selected separately as necessary The ALT side of the switch can not be set to ON without the BAT side of the switch also being set to ON If the alternator system fails the MAS...

Page 244: ...h is set to the ARM position during normal flight operation to allow the Standby battery to charge and to be ready to power the Essential Bus in the event of alternator and main battery failure PlaCing the switch in the OFF position disconnects the Standby battery from the Essential Bus Operation with the STBY BATT switch in the OFF position prevents the Standby battery from charging and from auto...

Page 245: ...wer that is required by the aircraft Indicated voltages between 24 5 and 28 volts may occur during low engine RPM conditions Refer to note under lOW VOLTAGE ANNUNCIATION AMMETER Electric current AMPS indication for both the main and Standby batteries is provided at the bottom of the EIS ENGINE or SYSTEM pages labeled M BATT S Main battery current is numerically displayed below the M Standby batter...

Page 246: ...er these conditions increase RPM or decrease electrical loads to reduce demand on the battery In the event an overvoltage condition or other alternator fault occurs the ACU will automatically open the AlT FIELD circuit breaker removing alternator field current and stopping alternator output The Main Battery will then supply current to the electrical system as shown by a discharge negative number o...

Page 247: ... Using a pullable circuit breaker as a switch is discouraged since the practice will decrease the life of the circuit breaker The Power Distribution Module uses three circuit breakers for the electrical bus feeders A fast blow automotive type fuse is used at the Standby Battery The Standby Battery current shunt circuit uses two field replaceable fuses located on the Standby Battery Controller prin...

Page 248: ...ould be made whenever the engine has been started using external power after disconnecting the external power source 1 MASTER Switch AlT and BAT OFF 2 TAXI and lANDING Light Switches ON 3 Engine RPM REDUCE to idle 4 MASTER Switch AlT and BAT ON with taxi and landing lights turned on 5 Engine RPM INCREASE to approximately 1500 RPM 6 Main Battery BAT Ammeter CHECK battery to be charging amps positiv...

Page 249: ...hts go out All other exterior lights are operated by switches found on the lighted switch panel to the left of the PFD Exterior lights are grouped together in the LIGHTS section of the switch panel To activate the BEACON LAND Landing Light TAXI Taxi Light NAV and STROBE light s place the switch in the up position Circuit breakers for the lights are found on the lighted circuit breaker panel on the...

Page 250: ...s accomplished using two dimmable lights in the front crew area and one dome light in the rear passenger area These lights are contained in the overhead console and are controlled by dimmer controls for the front lights and an on and off type push button switch for the rear light The front lights can be rotated to provide directional lighting for the pilot and front passenger The rear dome light p...

Page 251: ...ing level control to the AVIONICS dimmer control This is the recommended use of avionics lighting for night and low lighting conditions to allow the pilot control of the aVionics illumination levels as dark adaptation occurs I Rotating the STDSY IND dimmer found on the switch panel in the DIMMING group controls lighting of the standby airspeed indicator attitude indicator altimeter and non stabili...

Page 252: ...e and permit intermediate settings For cabin ventilation pull the CABIN AIR knob out To raise the air temperature pull 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 ...

Page 253: ... VENTILATIN HEATER ____ VALVE RAM AIR r VENTILATING AIR DOOR AI R OUTLET II st JIi H I FORWARD CABIN LOWER VENTILATING AIR OUTLET CABIN FLOO AIR OUTLET REAR CABIN VENTILATING AIR OUTLETS 2 RAM AIR FLOW 1 VENTILATING AIR HEATED AIR BLENDED AIR MECHANICAL CONNECTION 0585T1 015 Figure 7 8 Cabin Heating Ventilating and Defrosting System 7 58 U S 172SPHAUS OO ...

Page 254: ...tatic instruments to the sources The heated pitot system uses an electrical heating element built in the body of the pitot head The PITOT HEAT control switch is found on the switch panel below the lower LH corner of the PFD The PITOT HEAT circuit breaker 10 A is found on the circuit breaker panel at the lower LH side of the pilot panel A static pressure alternate source valve ALT STATIC AI R is lo...

Page 255: ...pear in amber on the PFD ATTITUDE INDICATOR The standby attitude indicator is a vacuum powered gyroscopic instrument found on the center instrument panel below the MFD The Attitude Indicator includes a low vacuum warning flag GYRO that comes into view when the vacuum is below the level necessary for reliable gyroscope operation VACUUM INDICATOR IThe vacuum indicator is incorporated on the EIS ENGI...

Page 256: ...IR FILTER GDU 1040 CONTROU DISPLAY UNIT SECTION 7 AIRPLANE AND SYSTEMS DESCRIPTION VACUUM SYSTEM OVERBOARD VENT LINE ENGINE DRIVEN VACUUM PUMP VACUUM PRESS EIS ENGINE PAGE ENGINE INDICATING SYSTEM GEA 71 ENGINE AND AIRFRAME UNIT 05851062 Figure 7 9 Vacuum System 172SPHAUS 00 U S 7 61 ...

Page 257: ...g horn resulting in an audible warning at 5 to 10 knots above stall in all flight conditions STANDARD AVIONICS The Garmin GIOOO Avionics System is an integrated flight control and navigation system The system combines primary flight instruments communications aircraft system information and navigational information all displayed on two color displays The GIOOO system consists of the following piec...

Page 258: ...malfunction GMA 1347 AUDIO PANEL The GMA 1347 audio panel for the G1000 system integrates all of the communication and navigation digital audio signals intercom system and marker beacon controls in one unit It is installed on the instrument panel between the PFD and the MFD The GMA 1347 also controls the Reversionary Mode for the PFD and MFD NOTE Use of the COM 1 2 function is not approved GIA 63 ...

Page 259: ...ust forward of the MFD An outside air temperature probe mounted on top of the cabin is connected to the Air Data Computer The ADC calculates pressure altitude airspeed true airspeed vertical speed and outside air temperature GEA 71 ENGINE MONITOR The GEA 71 Engine Monitor is responsible for receiving and processing the Signals from all of the engine and airframe sensors It is connected to all of t...

Page 260: ...on 9 Supplement 3 for operating information WARNING WHEN THE KAP 140 AUTOPILOT IS ENGAGED IN NAV APR OR REV OPERATING MODES IF THE HSI NAVIGATION SOURCE IS CHANGED FROM GPS TO NAV1 AUTOMATICALLY OR MANUALLY USING THE CDI SOFTKEY OR MANUALLY FROM NAV2 TO GPS THE CHANGE WILL INTERRUPT THE NAVIGATION SIGNAL TO THE AUTOPILOT AND WILL CAUSE THE AUTOPILOT TO REVERT TO ROLL MODE OPERATION NO WARNING CHIM...

Page 261: ...des forced air cooling to the Integrated Avionics Units and to the Transponder A fan located forward of the instrument panel removes air from between the firewall bulkhead and instrument panel directing the warm air up at the inside of the windshield Two additional fans blow air directly onto the heat sinks located on the forward sides of the PFD and MFD Power is provided to these fans when the MA...

Page 262: ...e GMA 1347 audio panel The transponder antenna is mounted on the bottom of the cabin is connected to the GTX 33 Mode S transponder by a coaxial transmission cable The DME if installed antenna is mounted on the bottom of the tailcone and is connected to the Honeywell KN 63 DME by a coaxial cable MICROPHONE AND HEADSET INSTALLATIONS Standard equipment for the airplane includes a hand held microphone...

Page 263: ...h the handheld microphone always hold it as closely as possible to the lips then press the transmit switch and speak directly into it Avoid covering the opening on back side of microphone for optimum noise canceling AUXILIARY AUDIO INPUT JACK An auxiliary audio input jack AUX AUDIO IN is located on the center pedestal refer to Figure 7 2 It allows entertainment audio devices such as cassette playe...

Page 264: ... of a high pilot workload and or heavy traffic it is wise to disable the entertainment audio to eliminate a source of distraction for the flight crew NOTE Passenger briefing should specify that AUX AUDIO IN entertainment audio input and Portable Electronic Device PED use is permitted only during the enroute phase of flight Disconnect the cable from the AUX AUDIO IN jack when not in use Use caution...

Page 265: ...any device into the 12 volt Cabin Power System connector This system is limited to a maximum of 10 amps Use caution with power adapter cables in the cabin to avoid entangling occupants or cabin furnishings and to prevent damage to cables supplying live electric current Disconnect power adapter cables when not in use STATIC DISCHARGERS Static wicks static dischargers are installed at various points...

Page 266: ...omethane fire extinguisher is installed in a holder on the floorboard between the front seats to be accessible in case of fire The extinguisher is classified 5B C by Underwriters Laboratories The extinguisher should be checked prior to each flight to ensure that the pressure of the contents as indicated by the gage at the top of the extinguisher is within the green arc approximately 125 psi and th...

Page 267: ...ered by the airplanes DC electrical system and integrated in the Garmin Gl000 system with a warning annunciation and alert messages displayed on the PFD When the CO detection system senses a CO level of 50 parts per million PPM by volume or greater the alarm turns on a flashing warning annunciation CO LVL HIGH in the annunciation window on the PFD with a continuous tone until the PFD softkey below...

Page 268: ...8 6 Airplane Inspection Periods 8 7 FAA Required Inspections 8 7 Cessna Inspection Programs 8 8 Cessna Customer Care Program 8 9 Pilot Conducted Preventive Maintenance 8 9 Alterations Or Repairs 8 10 Ground Handling 8 10 Towing 8 10 Parking 8 11 Tie Down 8 11 Jacking 8 11 Leveling 8 12 Flyable Storage 8 13 Servicing 8 14 Oil 8 15 Oil SpeCification 8 15 Recommended Viscosity for Temperature Range 8...

Page 269: ...ge Fuel 8 17 Approved Fuel Grades and Colors 8 17 Fuel Capacity 8 17 Fuel Additives 8 18 Fuel Contamination 8 22 Landing Gear 8 23 Cleaning And Care 8 23 Windshield And Windows 8 23 Painted Surfaces 8 24 Propeller Care 8 25 Engine Care 8 25 Interior Care 8 26 I Avionics Care 8 26 8 2 U S 172SPHAUS 03 ...

Page 270: ...d oil changes are necessary as well as other seasonal and periodic services The airplane should be regularly inspected and maintained in accordance with information found in the airplane maintenance manual and in company issued Service Bulletins and Service Newsletters All Service Bulletins pertaining to the airplane by serial number should be accomplished and the airplane should receive repetitiv...

Page 271: ...nt to Cessna Aircraft FAA Registered owners of record at no charge to inform them about mandatory and or beneficial airplane service requirements and product changes Copies of the Service Bulletins are available from Cessna Service Stations and Cessna Customer Service UNITED STATES AIRPLANE OWNERS If your airplane is registered in the U S appropriate Cessna Owner Advisories will be mailed to you a...

Page 272: ...update your address for this critical service PUBLICATIONS Various publications and flight operation aids are furnished in the airplane when delivered from the factory These items are listed below Customer Care Program Handbook Pilot s Operating Handbook and FAA Approved Airplane Flight Manual Pilot s Checklist Passenger Briefing Card Cessna Service Directory To obtain additional publications or O...

Page 273: ...Manual which is lost or destroyed may be replaced by contacting a Cessna Service Station An affidavit containing the owner s name airplane serial number and reason for replacement must be included in replacement requests since the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual is identified for specific serial numbered airplanes only AIRPLANE FILE There are miscellaneous data i...

Page 274: ...tion officials to determine their individual requirements Cessna recommends that these items plus the Pilot s Checklists Customer Care Program Handbook and Customer Care Card be carried in the airplane at all times AIRPLANE INSPECTION PERIODS FAA REQUIRED INSPECTIONS As required by U S Federal Aviation Regulations all civil aircraft of U S registry must undergo a complete inspection annual each tw...

Page 275: ...cled each 200 hours and are recorded in a specially provided Aircraft Inspection Log as each operation is conducted The PhaseCard Inspection Program offers a parallel system for high utilization flight operations approximately 600 flight hours per year This system utilizes 50 hour intervals Phase 1 and Phase 2 to inspect high usage systems and components At 12 months or 600 flight hours whichever ...

Page 276: ... most cases you will prefer to have the Cessna Service Station from whom you purchased the airplane accomplish this work PILOT CONDUCTED PREVENTIVE MAINTENANCE A certified pilot who owns or operates an airplane not used as an air carrier is authorized by FAR Part 43 to perform limited maintenance on his airplane Refer to FAR Part 43 for a list of the specific maintenance operations which are allow...

Page 277: ...ly maneuvered by hand with the tow bar attached to the nose wheel the tow bar is stowed on the side of the baggage area When towing with a vehicle do not exceed the nose gear turning angle of 30 either side of center or damage to the nose landing gear will result CAUTION REMOVE ANY INSTALLED RUDDER LOCK BEFORE TOWING If the airplane is towed or pushed over a rough surface during hangaring watch th...

Page 278: ... control lock over the fin and rudder 3 Tie sufficiently strong ropes or chains 700 pounds tensile strength to the wing tail and nose tie down fittings and secure each rope or chain to a ramp tie down 4 Install a pitot tube cover JACKING When a requirement exists to jack the entire airplane off the ground or when wing jack points are used in the jacking operation refer to the Maintenance Manual fo...

Page 279: ...tie down ring To assist in raising and holding the nose wheel off the ground ground anchors should be utilized at the tail tie down point NOTE Ensure that the nose will be held off the ground under all conditions by means of suitable stands or supports under weight supporting bulkheads near the nose of the airplane LEVELlNG Longitudinal leveling of the airplane is accomplished by placing a level o...

Page 280: ... to oceans lakes rivers and in humid regions are in greater need of engine preservation than airplanes operated in arid regions Appropriate engine preservation procedures must be practiced by the owner or operator of the airplane based on present environmental conditions and the frequency of airplane activity NOTE The engine manufacturer does not recommend pulling the engine through by hand during...

Page 281: ...Maintenance Manuals it is recommended that you contact your local Cessna Service Station concerning these requirements and begin scheduling your airplane for service at the recommended intervals Cessna Progressive Care ensures that these requirements are accomplished at the required intervals to comply with the 100 hour or annual inspection as previously covered Depending on various flight operati...

Page 282: ...Textron Lycoming Service Instruction No 1014 and all revision and supplements thereto must be used after first 50 hours or when oil consumption has stabilized RECOMMENDED VISCOSITY FOR TEMPERATURE RANGE Multiviscosity or straight grade oil may be used throughout the year for engine lubrication Refer to the following table for temperature verses viscosity range MIL L 6082 or MIL L 22851 or Temperat...

Page 283: ...e manufacturer NOTE During the first 25 hour oil and filter change a general inspection of the overall engine compartment is required Items which are not normally checked during a preflight inspection should be given special attention Hoses metal lines and fittings should be inspected for signs of oil and fuel leaks and checked for abrasions chafing security proper routing and support and evidence...

Page 284: ... Additives in later paragraphs for additional information FUEL CAPACITY 56 0 U S Gallons Total 28 0 U S Gallons per tank NOTE To ensure maximum fuel capacity when refueling and minimize cross feeding the fuel selector valve should be placed in either the LEFT or RIGHT position and the airplane parked in a wings level normal ground attitude Refer to Figure 1 1 for a definition of normal ground atti...

Page 285: ...m While these conditions are quite rare and will not normally pose a problem to owners and operators they do exist in certain areas of the world and consequently must be dealt with when encountered To help decrease the possibility of fuel icing occurring under these unusual conditions it is permissible to add isopropyl alcohol or diethylene glycol monomethyl ether DiEGME compound to the fuel suppl...

Page 286: ...ation by pouring the alcohol directly on the fuel stream issuing from the fueling nozzle 2 An alternate method that may be used is to premix the complete alcohol dosage with some fuel in a separate clean container approximately 2 3 gallon capacity and then transferring this mixture to the tank prior to the fuel operation Diethylene glycol monomethyl ether DiEGME compound must be carefully mixed wi...

Page 287: ... 0 10 BY TOTAL VOLUME MINIMUM WILL RESULT IN INEFFECTIVE TREATMENT USE ONLY BLENDING EQUIPMENT 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 precipitates the additive An indication of this is when an excessive amount of water accumulates in the fuel tank sumps The concentration can be checke...

Page 288: ...CESSNA SECTION 8 MODEL 172S NAV III HANDLING SERVICE AND MAINTENANCE FUEL MIXING RATIO 83118 0585T1001 Figure 8 1 Fuel Mixing Ratio 172SPHAUS OO U S 8 21 ...

Page 289: ...en removed If after repeated sampling evidence of contamination still exists the airplane should not be flown Tanks should be drained and system purged by qualified maintenance personnel All evidence of contamination must be removed before further flight If the airplane has been serviced with the improper fuel grade defuel completely and refuel with the correct grade Do not fly the airplane with c...

Page 290: ...nflate 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 CAUTION NEVER USE GASOLINE BENZENE ALCOHOL ACETONE FIRE EXTINGUISHER ...

Page 291: ...mois Harsh or abrasive soaps or detergents which cause corrosion or scratches should never be used Remove stubborn oil and grease with a cloth moistened with Stoddard solvent Take special care to make sure that the exterior graphics are not touched by the solvent For complete care of exterior graphics refer to the Maintenance Manual To seal any minor surface chips or scratches and protect against ...

Page 292: ...ssure 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 dirt with Stoddard solvent ENGINE CARE The engine may be cleaned using a su...

Page 293: ...ly 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 instructions To minimize wetting the fabric keep the foam as dry as p...

Page 294: ...licable 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 If equipment is installed on the airplane the supplement s must be retained and updated as revisions to each supplement are issued Each individual supplement contains its own Log of Effective Pages This log lists the page number ...

Page 295: ...T UP TO DATE VERSION BY CONTACTING CESSNA CUSTOMER SUPPORT AT 316 517 5800 Supplement Name Number 1 Pointer Model 3000 11 or Model 4000 11 Emergency Locator Transmitter ELT I 2 Canadian Certified Airplanes 3 BendixlKing KAP 1402 Axis Autopilot 4 Winterization Kit 5 Brazilian Certified Airplanes 6 Artex C406 N Emergency Locator Transmitter ELT 7 BendixlKing KR87 Automatic Direction Finder ADF 8 Rus...

Page 296: ... into Section 9 of the Pilors Operating Handbook and FAA Approved Airplane Flight Manual when the Pointer Model 3000 11 or Model 4000 11 Emergency Locator Transmitter is installed The Pointer Model 4000 11 Emergency Locator Transmitter is approved for use only in the USA Canada Japan and France 9 MemberofGAMA COPYRIGHT 2005 CES NA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHAUS Sl 0l APPROVED BY 1 M...

Page 297: ...plement Pages affected by the current revision are indicated by an asterisk preceding the page number Supplement Status Original Issue Revised 25 February 2005 19 September 2005 LOG OF EFFECTIVE PAGES Page Number S1 1 thru S1 2 S1 3 S1 4 S1 5 thru S1 12 APPROVED BY Page Revision Status Number Revised 1 Original 0 Revised 1 Original 0 QflMlf J _ 0fIIII 1JJtIJ f DATE OF APPROVAL _ _oc S1 2 U S FM AP...

Page 298: ... 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 Number Title FAAAPPROVED 172SPHAUS S1 00 Airolane Serial Effectivity Revision Incorporated Incorporated in Airplane U S S1 3 ...

Page 299: ...nstalled on the top right hand side of the copilot s instrument panel for control of the ELT from the flight crew station The annunciator which is in the center of the rocker switch comes on when the ELT transmitter is transmitting The ELT emits an omni directional signal on the international distress frequencies of 121 5 MHz and 243 0 MHz General aviation and commercial aircraft the FAA and CAP m...

Page 300: ...me accumulated in several tests and inadvertent activation of known duration c On or before battery replacement date Battery replacement date is marked on the battery pack and the label on the transmitter POINTER MODEL 3000 11 EMERGENCY LOCATOR TRANSMITTER ON 1 illD II 4 3 2 Figure S1 1 5 RESET 1 REMOTE CABLE JACK Connects to ELT remote switch annunciator located on the copilot s instrument panel ...

Page 301: ... handling following RESET rescue and to reset the automatic activation function The red annunciator in the center of the remote SWitch annunciator should go off 5 REMOTE SWITCH ANNUNCIATOR 3 position rocker switch S1 6 ON Remotely activates the transmitter for test or emergency situations Red annunciator in center of rocker switch comes on to indicate that the transmitter is transmitting a distres...

Page 302: ...gnal 4 MASTER FUNCTION SELECTOR SWITCH 3 position toggle switch AUTO Arms transmitter for automatic activation if G switch senses a predetermined deceleration level ON Activates transmitter instantly Used for test purposes and if G switch is inoperative The ON position bypasses the automatic activation switch The red annunciator in the center of the remote switchl annunciator should come on OFFI D...

Page 303: ...f the Pilot s Operating Handbook and FAA Approved Flight Manual POH AFM EMERGENCY PROCEDURES Before performing a forced landing especially in remote and mountainous areas activate the ELT transmitter by positioning the remote switch annunciator to the ON position The annunciator in center of the rocker switch should be illuminated Immediately after a forced landing where emergency assistance is re...

Page 304: ...d a decreasing tone will be heard before the typical warbling tone begins 2 PRIOR TO SIGHTING RESCUE AIRCRAFT Conserve airplane battery Do not activate radio transceiver 3 AFTER SIGHTING RESCUE AIRCRAFT Position remote switch annunciator to the RESET position and release to the AUTO position to prevent radio interference Attempt contact with rescue aircraft with the radio transceiver set to a freq...

Page 305: ... the remote switch annunciator is on or an emergency tone is heard position the remote switch annunciator in the RESET position and release to the AUTO position The ELT must be serviced in accordance with FAR Part 91 207 INSPECTIONITEST 1 The emergency locator transmitter should be tested every 100 hours NOTE Test should only be conducted within the first 5 minutes of each hour 2 Disconnect antenn...

Page 306: ...other communications or damage output circuitry After accumulated test or operation time equals 1 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 cont...

Page 307: ...S SUPPLEMENT 1 PERFORMANCE CESSNA MODEL 172S NAV III There is no change in airplane performance when the POinter Model 3000 11 or 4000 11 Emergency Locator Transmitter ELT is installed S1 12 U S FM APPROVED 172SPHAUS S1 00 ...

Page 308: ...NO _ _ _ _ _ _ _ I REGISTRATION NO _ _ _ _ _1 This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual for Canadian Certified Airplanes f Member of GAMA COPYRIGHT 2005 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHAUS S2 01 APPROVED BY I MAPI II1o BI1 IClBI l MTtllUWMT _co a IIIrI lClJo cI DATE OF APPROVAL I1Z U j 2 f 25 FEBRUARY ...

Page 309: ...he current revision are indicated by an asterisk preceding the page number Supplement Statys Original Issue Revision 1 LOG OF EFFECTIVE PAGES Page Number 82 1 thru 82 2 82 3 82 4 82 5 82 6 APPROVED BY 25 February 2005 7 February 2007 Page Revision 8tatus Number Revised Original Revised Added M M HIff II IIWII J _ QIIM tft 4u 1 0 DATE OF APPROVAL 07 ryb ll4 l vq 1 S2 2 U S FAA APPROVED 172SPHAUS S2...

Page 310: ...ist 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 Number FAA APPROVED 172SPHAUS S2 00 Airplane Serial Revision Incorporated Effectivitv Incorporated jn Airolane U S S2 3 ...

Page 311: ...t be equipped and operated in accordance with Transport Canada IThe Artex ME406 Emergency Locator Transmitter installation is not approved for Canadian Certified Airplanes OPERATING LIMITATIONS The following placard must be installed 1 Near the fuel tank filler cap FUEL 100LU100 MIN GRADE AVIATION GASOLINE CAP 26 5 U S GAL 100 LlTERS USABLE CAP 17 5 U S GAL 66 LlTERS USABLE TO BOTTOM OF FILLER IND...

Page 312: ... 9 SUPPLEMENTS SUPPLEMENT 2 IThere is no change 10 Ihe airplane normal procedures for Canadian Certified Airplanes PERFORMANCE IThere is no change 10 Ihe airplane performance for Canadian Certified Airplanes FAA APPROVED I 172SPHAUS S2 01 U S S2 5 S2 6 ...

Page 313: ...ist 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 Number FAA APPROVED 172SPHAUS S3 00 Airplane Serial Effectivity Revision Incorporated Incorporated in Airplane U S S3 3 ...

Page 314: ...tly the airplane can be made to stall Make sure that the vertical speed set on the autopilot results in airplane performance that stays in the operating limitations of both the autopilot and the airplane 3 Altitude Hold ALT mode holds a set altitude using combined engine power pitch and pitch trim control 4 Heading HDG mode holds the magnetic heading set using the HDG bug on the Gl000 Primary Flig...

Page 315: ...PS approaches when GPS is set as the navigation source on the HSI The KAP 140 Autopilot gives the pilot Altitude Preselect and Altitude Alert functions The Altitude Preselect function lets the pilot set a limit or target altitude before starting a climb or descent The KAP 140 will climb or descend as applicable at the set vertical speed and will return to level flight at the altitude selection The...

Page 316: ...em malfunction 2 Autopilot Computer Monitor detects either R roll axis or P pitch axis malfunction annunciation 3 Pitch accelerations larger than 1 4g or 0 6g caused by a servo malfunction The pilot cannot maneuver the airplane and cause the autopilot to disengage although some turbulence can 4 DC Electric Turn Coordinator malfunction 5 The AlP DISCfTRIM INT Switch on the LH Control Wheel is pushe...

Page 317: ... Autopilot LABEL FUNCTIONS AUTO PILOT A pUll to open type circuit breaker on AVN BUS 2 that energizes the KAP 140 Autopilot computer and the roll pitch and pitch trim servos WARN FAA APPROVED 172SPHAUS S3 00 A pUll to open type circuit breaker on the X FEED BUS that supplies power for the PITCH TRIM annunciation on the G1000 PFD Continued Next Page U S S3 7 ...

Page 318: ... 3 6 79 15 GIA63 NUMBER 2 AILERON AILERON ACTUATOR TURN COORDINATOR S3 8 U S Figure S3 1 CESS MODEL 172S NAV ELEVATOR LJ 7 TRIM WHEEL CONTROL ACTUATOR AVN J BUS2 11 t WARN CIB 10 XFEED BUS 0785R1C 071ep10 y FM APPROVED 172SPHAUS S3 00 ...

Page 319: ...accelerations 2 AUTOPILOT ENGAGE DISENGAGE AP BUTTON When pressed and held approx 0 25 seconds engages autopilot if all preflight self test conditions are met The autopilot 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 ...

Page 320: ...beam capture and tracking of VOR GPS LOC and Glideslope GS on an ILS as set on the HSI 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 ...

Page 321: ...the airplane up or down at the rate 01 500 FPM synchronizing the ALT relerence to the actual airplane altitude upon button release 10 AUTO PILOT CIRCUIT BREAKER A 5 amp pull off circuit breaker supplies 28 VDC to the KAP 140 system 11 WARN CIB Power to the autopilot disconnect horn and the annunciator PITCH TRIM 12 AUTOPILOT DISCONNECT AlP DISCITRIM INT SWITCH When depressed will disengage the aut...

Page 322: ...T Annunciator Indicates the direction of pitch trim motion The annunciation will flash if auto trim has not satisfied the request for trim for a period of 10 seconds A solid 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 Displayed in the PFD Illuminates whenever the automated preflig...

Page 323: ...When pushed will change the altitude arming function between on or off When ALT ARM is annunciated the autopilot will capture the altitude alerter displayed altitude provided the airplane is climbing or descending in VS to the displayed altitude ALT hold arming when the autopilot is engaged is automatic upon altitude alerter altitude selection via the rotary knobs Note that the alerter functions a...

Page 324: ... from the selected altitude on leaving the altitude OPERATING LIMITATIONS The following autopilot limitations must be obeyed 1 The entire Preflight procedure given in the Normal Procedures section of this Supplement must be satisfactorily completed prior to each flight Use of the autopilot or manual electric trim system is prohibited before the satisfactory completion of the Preflight procedure 2 ...

Page 325: ... The electric trim and autopilot systems will be de energized when the AUTO PILOT circuit breaker is open 11 Operation of the KAP 140 Autopilot is prohibited when the GMA 1347 Audio Panel is inoperative no warning tone will be supplied when the Autopilot disengages EMERGENCY PROCEDURES The four step recovery procedure steps 1 thru 4 listed below should be committed to memory It is important that t...

Page 326: ...tion then locate and open pull the AUTO PILOT circuit breaker Then the AVIONICS BUS 2 switch can be set to the ON position to restore power to the other avionics equipment on AVN BUS 2 Primary attitude airspeed directional f compass and altitude instruments will continue to operate when the AVIONICS BUS 2 switch is OFF Maximum Altitude losses due to autopilot malfunction CONFIGURATION Cruise Climb...

Page 327: ...ould be used manually as needed to relieve control forces Locate and open pull the AUTO PILOT circuit breaker on the lower right hand corner of the circuit breaker panel to completely disable the autopilot system 3 A manual electric trim system malfunction without pilot actuation of the manual electric trim switches may be recognized by the PITCH TRIM annunciator coming on or by unusual trim wheel...

Page 328: ...t electric trim system by pulling the AUTO PILOT circuit breaker As with any airplane emergency procedure it is important that the 4 steps of the Recovery Procedure be committed to memory 3 The AVIONICS BUS 2 switch may be used to remove all electric power from the autopilot and electric trim systems while the AUTO PILOT circuit breaker is located and opened When the AVIONICS BUS 2 switch is OFF t...

Page 329: ...UNCIATION OBSERVE airplane pitch behavior If pitch behavior is satisfactory wait 5 to 10 seconds for the annunciation to go off 2 If annunciation continues CONTROL WHEEL GRASP FIRMLY DISENGAGE the autopilot and CHECK for out of trim condition in pitch Manually trim to reduce control forces 3 AUTOPILOT OPERATION CONTINUE if satisfied that the pitch trim malfunction indication was temporary DISCONTI...

Page 330: ...e HDG button to change to ROL mode ROL will be shown on the face of the autopilot 2 NAV APR or REV flashing Shows that the autopilot navigation source is not working correctly flag The navigation signal may have been lost or the navigation source may have been switched at the PFD NOTE NAV APR or REV flashing can also be caused by a j failed heading input during course capture 3 GS flashing Shows a...

Page 331: ... on autopilot 2 Failure of AHRS The autopilot will function only in ROL mode 3 Failure of DC Turn Coordinator Autopilot will disengage or will not engage 4 Failure of HSI If HSI fails to function correctly no heading signal will be available so the autopilot HDG NAV APR and REV modes will not function correctly Only ROL mode will function correctly 5 Failure of the Transponder Pressure Altitude En...

Page 332: ...autopilot display elements coming on Display Test the PITCH TRIM annunciator on the PFD coming on and the operation of the autopilot disengagement tone WARNING IF THE RED P STAYS ON THE AUTOPILOT HAS FAILED THE PREFLIGHT TEST OPEN PULL THE AUTO PILOT CIRCUIT BREAKER TO MAKE SURE THAT THE AUTOPILOT AND MANUAL ELECTRIC TRIM SYSTEM WILL NOT OPERATE NOTE When power is first supplied to the autopilot t...

Page 333: ...pilot is disconnected from electrical power and will not operate until it is repaired b LH SWITCH PULL AFT to UP position and hold Make sure that the elevator trim wheel does not move Release switch to center OFF position c RH Switch PUSH FORWARD to DN position and hold Make sure that the elevator trim wheel does not move Make sure the red light on the face of autopilot comes on Release switch to ...

Page 334: ...ure that the elevator Trim Tab moves up with nose down elevator trim LH RH Switches held in the DN position movement If the elevator trim wheel moves while the AlP DISCITRIM INT Switch is pushed and held the Manual Electric Trim System has failed The airplane may be flown if the AUTO PILOT Circuit Breaker is secured in the open position so that the autopilot is disconnected from electrical power a...

Page 335: ...secured in the open position so that the autopilot is disconnected from electrical power and will not operate until it is repaired 4 BARO Setting flashing SET current local barometer atmospheric pressure using knobs or push BARO button to accept the present setting 5 AUTOPILOT ENGAGE push and hold AP button for 1 second 6 FLIGHT CONTROLS MOVE Make sure that the autopilot can be overpowered in both...

Page 336: ...PERATION IS ERRATIC OR DOES NOT CORRECTLY CONTROL THE AIRPLANE DURING AUTOPILOT OPERATIONS THE PILOT IN COMMAND MUST SET THE AUTOPILOT VS VERTICAL SPEED RATE AND ENGINE POWER TO MAKE SURE THAT AIRSPEED STAYS BETWEEN 80 KIAS AND 160 KIAS AND DOES NOT EXCEED ANY OTHER AIRPLANE OPERATING LIMITATION NOTE Autopilot tracking performance will not be as good as usual in turbulence 9 AVIONICS BUS 2 Switch ...

Page 337: ...ITUDE ALERT FUNCTION NOTE 1000 feet before the altitude selection an electronic sound tone will be supplied for the pilot Altitude changes of more than 200 feet from the altitude selection will cause a series of short tones to alert the pilot AFTER TAKEOFF 1 Elevator Trim SET to trim airplane before engaging the autopilot NOTE If the autopilot is engaged when the airplane is out of trim the result...

Page 338: ...topilot or airplane will not obey the limitations 3 AP Button PUSH and HOLD Make sure that ROL and VS are shown on the face of the autopilot If no selection of other operating modes is made the autopilot will operate in ROL and VS modes NOTE When operating in ROL mode turbulence may result in changes to airplane heading ROL mode only works to keep the wings level 4 Make HOG or NAV mode selection a...

Page 339: ...OVEMENT AND CAUSE THE AIRPLANE TO GO OUT OF TRIM THE OUT OF TRIM CONDITION WILL CAUSE LARGE ELEVATOR CONTROL FORCES WHEN THE AUTOPILOT IS DISENGAGED CLIMB OR DESCENT 1 BARO SET current altimeter 2 VS Vertical Speed Mode UP or DN Buttons PUSH button to set airplane vertical speed in 100 feet per minute ftlmin increments PUSH and HOLD the button for the KAP 140 to increase the vertical speed at appr...

Page 340: ...ng knob on KAP 140 2 ALTITUDE ARM PUSH the ARM button to set the Altitude Lock On feature to the ON position if needed ALT ARM will show on the face of the autopilot when Altitude Lock On is set to the ON condition NOTE Minor differences between the autopilot altitude selection and the airplane altitude indication may be seen after altitude lock on This small difference is generally due to autopil...

Page 341: ...h Attitude Hold for autopilot operation in severe turbulence The KAP 140 does not use pitch reference so it is recommended that the autopilot be disengaged and the airplane flown manually in severe turbulence CHANGING ALTITUDE If the autopilot is engaged in ALT mode Altitude Hold 1 For small altitude changes less than 100 feet push the UP or DN button momentarily to program an increase or decrease...

Page 342: ... set lor the autopilot results in airplane performance that stays in the operating limitations 01 both the autopilot and the airplane When operating at or near the best rate ol climb airspeed with the engine set to climb power or when in Vertical Speed mode it can be easy to slow to airspeeds where any additional reduction in airspeed will result reduced rate ol climb Hold sufficient airspeed duri...

Page 343: ... IS ENGAGED IN NAV APR OR REV OPERATING MODE IF THE HSI NAVIGATION SOURCE IS CHANGED FROM GPS TO NAV1 AUTOMATICALLY OR MANUALLY USING THE COl SOFTKEY OR MANUALLY FROM NAV2 TO GPS THE CHANGE WILL INTERRUPT THE SIGNAL TO THE AUTOPILOT AND CAUSE THE AUTOPILOT TO GO BACK TO ROL MODE OPERATION NO WARNING CHIME OR PFD ANNUNCIATION WILL BE SUPPLIED THE PREVIOUSLY SELECTED MODE SYMBOL SHOWN ON THE FACE OF...

Page 344: ...D TO BE THE WARNING FLAG NOTE When navigating using GPS make sure that the GPS 2 unit is available on the Gl000 MFD AUX GPS STATUS page No annunciation is provided for GPS 2 malfunction NAV COURSE CAPTURE LOCK ON 1 CRS Pointer SET the HSI course pointer to the desired magnetic course using the CRS knob on the PFD NOTE If operating GPS Direct Direct to or on an active GPS Flight Plan the course poi...

Page 345: ... face of the autopilot GPS NAV AND ROLL STEERING The KAP 140 Autopilot has DC analog Roll Steering capability Roll Steering enables the Flight Guidance System in this case the G1000 GPS navigation computer to control the autopilot through automatic course changes at flight plan waypoints and to lock on to the course to the next waypoint The GPS navigation computer uses ground speed track and turn ...

Page 346: ...r than approximately 1400 could result in a turn rate that reaches the autopilot bank angle limit The pilot may need to change the KAP 140 to HDG mode also arm NAV or APR mode and manually set the intercept heading to help the autopilot lock on the new course HOLDING PATTERNS AND PROCEDURE TURNS When operating IFR on an active GPS flight plan enroute or transitioning to the terminal environment a ...

Page 347: ...e used for the KAP 140 on the inbound leg of the holding pattern for course guidance but HDG mode must be used for the remainder of the holding pattern maneuver At the end of the holding procedure exit OBS mode to start the flight plan executing again and set NAV mode on the KAP 140 to lock on to the course See the Garmin Gl000 Cockpit Reference Guide for further information Arriving at the IAF us...

Page 348: ...140 AUTOPILOT IS ENGAGED IN NAV APR OR REV OPERATING MODE IF THE HSI NAVIGATION SOURCE IS CHANGED FROM GPS TO NAV1 AUTOMATICALLY OR MANUALLY USING THE COl SOFTKEY OR MANUALLY FROM NAV2 TO GPS THE CHANGE WILL INTERRUPT THE SIGNAL TO THE AUTOPILOT AND CAUSE THE AUTOPILOT TO GO BACK TO ROL MODE OPERATION NO WARNING CHIME OR PFD ANNUNCIATION WILL BE SUPPLIED THE PREVIOUSLY SELECTED MODE SYMBOL SHOWN O...

Page 349: ...wn as the navigation source on the HSI NOTE Make sure that the applicable GPS mode is set during each portion of the approach procedure selection symbol NAV APR or REV flashing on the face of the autopilot If either the GPS or VHF navigation signal as applicable fails when the autopilot is engaged in NAV APR or REV mode the autopilot will change back to ROL mode operation ROL mode operation is sho...

Page 350: ...ngaged from the annunciation on the autopilot a If the HSI D Bar is less than 2 to 3 dots from center the autopilot will go to APR mode The APR annunciator will be shown on the face of the autopilot b If the HSI D Bar is more than 2 to 3 dots from center the APR ARM annunciator will be shown on the face of the autopilot When the computed intercept point is reached the ARM annunciator will go off a...

Page 351: ...ROL MODE THE AUTOPILOT WILL ONLY KEEP THE WINGS LEVEL AND WILL NOT CORRECT THE AIRPLANE HEADING OR COURSE SET THE HDG BUG TO THE CORRECT HEADING AND SELECT THE CORRECT NAVIGATION SOURCE ON THE HSI USING THE COl SOFTKEY BEFORE ENGAGING THE AUTOPILOT IN ANY OTHER OPERATING MODE 6 Airspeed HOLD 100 KIAS minimum recommended during approaches when the autopilot is engaged GLIDESLOPE ENGAGEMENT AND LOCK...

Page 352: ...ourse inbound heading using the CRS knob on the PFD 3 HDG bug SET the HSI heading bug to the desired course intercept heading 4 HDG Button PUSH to engage HDG mode Make sure that HDG is shown on the face of the autopilot 5 REV Button PUSH to arm the autopilot REV lock on function Make sure that the autopilot is correctly engaged from the annunciation on the autopilot a If the HSI D Bar is less than...

Page 353: ...BE USED FOR COURSE GUIDANCE TO THE MISSED APPROACH HOLDING POINT MAHP PUSH THE SUSP SOFTKEY TO START THE FLIGHT PLAN AND NAVIGATION SIGNAL AGAIN BEFORE ENGAGING THE KAP 140 NOTE Only engage the autopilot during wings level stable flight The autopilot will come on in ROL wings leveler and VS Vertical Speed modes The VS mode initial rate of climb will be the vertical speed at the time the autopilot ...

Page 354: ...re any additional reduction in airspeed will result reduced rate ol climb Hold sufficient airspeed during Vertical Speed mode operation to avoid a stall c AP Button PUSH and HOLD to engage the autopilot Make sure that ROL and VS are shown on the lace 01 the autopilot If no selection 01 other operating modes is made the autopilot will operate in ROL and VS modes NOTE When operating in ROL mode turb...

Page 355: ... KIT SERIAL NO _ _ _ _ _ _ _ __ REGISTRATION NO _ _ _ _ _ __ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Winterization Kit is installed f Member of GAMA COPYRIGHT Cl 2005 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHAUS S4 00 APPROVED BY DATE OF APPROVA tit _c f 25 FEBRUARY 2005 U S S4 1 ...

Page 356: ... to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number Supplement Status Date Original 25 February 2005 LOG OF EFFECTIVITY PAGES Page Number S4 1 thru S4 4 S4 2 U S Page Status Original Revision Number o FAA APPROVED 172SPHAUS S4 00 ...

Page 357: ... 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 Number Title FAA APPROVED 172SPHAUS S4 00 Airplane Serial Revision Incorporated Effectivitv Incorporated in Airplane U S S4 3 ...

Page 358: ...acards when the airplane is equipped with a winterization kit 1 On each nose cap cover plate REMOVE WHEN O A T EXCEEDS 20 F 2 On the instrument panel below the Primary Flight Display PFD WINTERIZATION KIT MUST BE REMOVED WHEN OUTSIDE AIR TEMPERATURE IS ABOVE 20T EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when the winterization kit is installed NORMAL PROCEDURES Th...

Page 359: ... FAA Approved Airplane Flight Manual when used for Brazilian Certified Airplanes and is approved by the U S Federal Aviation Administration FAA on behalf of the Agencia Nacional de Avia9ao Civil ANAC for Brazilian Registered Airplanes in accordance with the Regulamento Brasileiro de Homologa9ao Aeronautica RBHA 21 Section 21 29 f Member of GAMA COPYRIGHT 2006 CESSNA AIRCRAFT COMPANY WICHITA KANSAS...

Page 360: ...he current revision are indicated by an asterisk preceding the page number uRl2lgmgDi tiilty Original Issue Revision 1 LOG OF EFFECTIVE PAGES Page Number S5 1 thru S5 2 S5 3 thru S5 4 S5 5 S5 6 APPROVED BY 1 February 2006 2 November 2006 Page Revision Status Revised Original Revised FMIIPfII MDINIBI MCNPNlTII J _ CpIDn P ZI S Number 0 DATE OF APPROVAL pi tJg Mb c un6 S5 2 U S FAA APPROVED 172SPHAU...

Page 361: ... 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 Number Title FAA APPROVED 172SPHAUS S5 00 Airolane Serial Revision Incorporated Effectivity Incoroorated in Airolane U S S5 3 ...

Page 362: ... the airplane operating limitations when used for Brazilian operation EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when used for Brazilian operation NORMAL PROCEDURES There is no change to the airplane normal procedures when used for Brazilian operation PERFORMANCE There is no change to the airplane performance when used for Brazilian operation S5 4 U S FAA APPROVED...

Page 363: ...k and FAA Approved Airplane Flight Manual for revision status I Supplement Name Number 1 Pointer Model 3000 11 Or Model 4000 11 Emergency Locator Transmitter ELT 2 Reserved 3 BendixlKing KAP 140 2 Axis Autopilot 4 Winterization Kit 5 Brazilian Certified Airplanes 6 Artex C406 N Emergency Locator Transmitter ELT 7 BendixlKing KR 87 Automatic Direction Finder ADF FAA APPROVED 172SPHAUS S5 01 U 8 Equ...

Page 364: ... REGISTRATION NO _ _ _ _ _I This supplement must be inserted into Section 9 of the Pilo s Operating Handbook and FM Approved Airplane Flight Manual when the Artex C406 N Emergency Locator Transmitter ELT is installed f Member of GAMA COPYRIGHT 2006 CESSNA AIRCRAFT COMPANY WICHfTA KANSAS USA 172SPHAUS S6 01 APPROVED BY N I IIIMDI NIBIMCAlI MTII awMTJ _ QIIIII 1 IOiIteIIMQ Cf E A cl DATE OF APPROVAL...

Page 365: ...nt revision are indicated by an asterisk preceding the page number S JI2I2I m Dl s tiillld Original Issue Revision 1 LOG OF EFFECTIVE PAGES Page Number S6 1 thru S6 2 S6 3 S6 4 thru S6 6 S6 7 thru S6 8 APPROVED BY I2mi 14 February 2006 16 November 2006 Page Revision Status Number Revised Original Revised Added FMN I IICIWIDIIIBMIII WIWIl naawrrJ _ P du _to f 1 0 DATE OF APPROVAL Ib J W ZpOb S6 2 U...

Page 366: ... 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 Number Tille FAAAPPROVED 172SPHAUS S6 00 Airolane Serial Revision Incoroorated Effectivity Incorporated in Airolane U S S6 3 ...

Page 367: ...e right I side behind the baggage compartment aft panel On the ELT transmitter unit is a panel containing an ON OFF switch and a transmitter warning light The ELT installation uses two different warnings to tell the pilot when the ELT is energized The aural warning is an unusual sound that is easily heard by the pilot The visual warning is a flashing red light I directly above the remote switch th...

Page 368: ...MITTER WARNING LIGHT Light comes on RED to indicate the transmitter is transmitting a distress signal 3 REMOTE CABLE JACK Connects to the ELT remote switch assembly located on the upper right instrument panel 4 ANTENNA RECEPTACLE Connects to the antenna mounted on top of tailcone 5 REMOTE SWITCH ASSEMBLY 2 Position Rocker Switch a ARM OFF Turns OFF and ARMS transmitter for automatic activation if ...

Page 369: ...e civil aviation authority before use to make sure that the identification code transmitted by the ELT is in the COSPAS SARSAT database Refer to www cospas sarsat org for registration information Refer to 14 CFR 91 207 for ELT inspection requirements The C406 N must be inspected and tested by an approved technician using the correct test equipment under the appropriate civil aviation authorities a...

Page 370: ...itching of the ELT panel switch which is located on the ELT unit 1 MAKE SURE THE ELT IS ENERGIZED a If the red warning light above the remote switch is not flashing set the remote switch to the ON position b Listen for the aural warning If the COM radio s operate and can be energized safely no threat of fire or explosion energize a COM radio and set the frequency to 121 5 MHz The ELT tone should b...

Page 371: ...has been accidentally energized no emergency The ELT can be energized by a lightning strike or hard landing If the 1red light above the remote switch is flashing and the aural warning is heard the ELT is energized Check for the emergency signal on a COM Iradio set to 121 5 MHz To stop the transmissions set the remote switch to the ON position momentarily and then set to the ARM position Tell the n...

Page 372: ...OMATIC DIRECTION FINDER ADF SERIAL NO ________I REGISTRATION NO ______ 1 This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FM Approved Airplane Flight Manual when the BendixlKing KR 87 Automatic Direction Finder ADF is installed f Member of GAMA COPYRIGHT 2005 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHAUS S7 00 APPROVED BY 22 DECEMBER 2005 u s S7 1 ...

Page 373: ...Effective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number Supplement Status Original Issue 22 December 2005 LOG OF EFFECTIVE PAGES S7 2 Page Number S7 1 thru S7 12 U S Page Status Original Revision Number o FAA APPROVED 172SPHAUS S7 00 ...

Page 374: ...ist 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 Number FAA APPROVED 172SPHAUS S7 00 Ajrp ane Serial Revision Incorporated Effectjvity Incorporated in Airolane U S S7 3 ...

Page 375: ...llows switching between preselected standby and active frequencies by pushing the frequency transfer button Both preselected frequencies are stored in a nonvolatile memory circuit no battery power required and displayed in large easy to read self dimming gas discharge numbers The active frequency is continuously displayed in the left window while the right window will display either the standby fr...

Page 376: ... III SECTION 9 SUPPLEMENTS SUPPLEMENT 7 BENDIXlKING KR87 AUTOMATIC DIRECTION FINDER ADF 1 2 ANT ADF BENDIXfI IN 12 11 FAA APPROVED 172SPHAUS S7 00 3 10 4 5 9 8 15 Figure S7 1 6 ADF 1 Ol 7 U S 87 SO 0585T1043 0585T1055 S7 5 ...

Page 377: ...nd its morse code identifier can be heard NOTE CW signals Morse Code are unmodulated and no audio will be heard without use of BFO This type of signal is not used in the United States air navigation It is used in some foreign countries and marine beacons 4 STANDBY FREQUENCY FLIGHT TIME OR ELAPSED TIME DISPLAY When FRQ is shown the STANDBY frequency is shown in the right display The STANDBY frequen...

Page 378: ...ETI RST button resets the elapsed timer whether it is being displayed or not 9 FLIGHT TIMER ELAPSED TIMER MODE SELECTOR BUnON FLT ET The FLT ET button selects either Flight Timer mode or Elapsed Timer mode when pushed 10 FREQUENCY TRANSFER BUnON FRQ The FRQ transfer button interchanges the active and standby frequencies when pushed 11 BFO Beat Frequency Oscillator BunON The BFO button selects the ...

Page 379: ...ontrol ON 2 Frequency Selector Knobs SELECT desired frequency in the standby frequency display 3 FRQ Button PUSH to move the desired frequency from the standby to the active position 4 ADF Selector Switch on audio control panel SELECT as desired 5 OFFNOL Control SET to desired volume level and identify that desired station is being received 6 PFD Softkey on PFD PUSH to show BRG1 and BRG2 softkeys ...

Page 380: ...ne and Morse Code identifier is heard in the audio output when a CW signal is received TO OPERATE FLIGHT TIMER 1 OFFNOL Control ON 2 FLT ET Mode Button PRESS once or twice until FLT is annunciated Timer will already be counting since it is activated by turning the unit on 3 OFFNOL Control OFF and then ON if it is desired to reset the flight timer TO OPERATE AS A COMMUNICATIONS RECEIVER ONLY 1 OFFN...

Page 381: ...nnunciated 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 RST FLT ET or F...

Page 382: ... selector to ANT and listening for station call letters ELECTRICAL STORMS In 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 If possible tune to the most powerful st...

Page 383: ...o change in airplane performance when the BendixlKing KR 87 Automatic Direction Finder ADF is installed However the installation of an externally mounted antenna or related external antennas will result in a minor reduction in cruise performance S7 12 U S FAA APPROVED 172SPHAUS S7 00 ...

Page 384: ...ted into Section 9 of the Pllot s Operating Handbook and FAA Approved Airplane Flight Manual when the airplane is operated within the territory of the Russian Federation RF and other Commonwealth of Independent States CIS Countries This supplement is approved by the U S Federal Aviation Administration FAA on behalf of the Russian Aviation Register o Member of GAMA COPYRIGHT 2006 CESSNA AIRCRAFT CO...

Page 385: ...ctive Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number Sypplement Statys Original Issue 4 April 2006 LOG OF EFFECTIVE PAGES Page Number S8 1 thru 88 21 S8 22 Page Status Original Revision Number o Approved for RF and CI8 Countries Only FAA APPROVED S8 2 U S 172SPHAUS S8 00 ...

Page 386: ...tins 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 Serial Revision Incorporated Number Effectjvjtv Incorporated in Ajrptane Approved for RF and CIS Countries Only FAA APPROVED 172SPHAUS S8 00 U S S8 3 ...

Page 387: ... s Operating Handbook and FAA Approved Airplane Flight Manual Limitations procedures and performance found in this supplement supersedes those found in the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual For limitations procedures and performance information not contained in this supplement consult the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manua...

Page 388: ...ohibited Flight into known icing or freezing rain is prohibited Operations in RF and CIS airspace are approved only on routes covered by ATC ground facilities using RBS mode The Nav III Avionics Option is approved for Category IlLS approach operations only The Global Positioning Satellite GPS system is not approved for approach Operation over water beyond the Maximum Glide distance from shore is p...

Page 389: ... OPERATIONS EQUIPMENT LIST KIND OF OPERATION V I V F I F F R F R R R N N D I D I A G A G System Instrument Equipment y H Y H and or Function T T COMMENTS PLACARDS AND MARKINGS 172S Nav III POH AFM 1 1 1 1 Accessible to pilot in flight Garmin G1000 Cockpit 1 1 1 1 Accessible to pilot Reference Guide in flight AIR CONDITIONING 1 Forward Avionics Fan 1 1 1 1 2 PFD Fan 0 0 0 0 3 MFD Fan 0 0 0 0 4 Aft ...

Page 390: ... 1 1 5 Standby Ammeter 1 1 1 1 Refer to Note 1 EQUIPMENT AND FURNISHINGS 1 Seat Belt Assembly 1 1 1 1 Each Seat Occupant 2 Shoulder Harness 1 1 1 1 Front Seat Occupants NOTE 1 The European Aviation Safety Agency EASA requires the 24V Standby Battery and Standby Ammeter to successfully complete the pre flight check before operating the airplane in VFR night IFR day or IFR night conditions in Europe...

Page 391: ...em 1 1 1 1 4 Elevator Trim Indicator 1 1 1 1 FUEL SYSTEM 1 Electric Fuel Pump 1 1 1 1 2 Fuel Quantity Indicator LH 1 1 1 1 Tank 3 Fuel Quantity Indicator RH 1 1 1 1 Tank ICE AND RAIN PROTECTION 1 Alternate Static Air Source 0 1 1 1 2 Alternate Induction Air 0 1 1 1 System INDICATING RECORDING SYSTEM 1 Stall Warning System 1 1 1 1 2 System Annunciator and 1 1 1 1 Warning Displays LANDING GEAR 1 Whe...

Page 392: ...andby 0 1 0 1 Internal Lighting 7 Altimeter Standby Internal 0 1 0 1 Lighting 8 Non stabilized Magnetic 0 1 0 1 Compass Internal Lighting 9 Attitude Indicator Vacuum 0 1 0 1 Internal Lighting 10 Cockpit Flood Light 0 1 0 1 11 Aircraft Position NAV Lights 0 1 1 1 NOTE 2 PDF backlighting is required for day VFR flight if MFD backlighting has failed Display backup mode must be active so engine indica...

Page 393: ... only NAVIGATION AND PITOT STATIC SYSTEM 1 G1000 Airspeed Indicator 1 1 1 1 2 Standby Airspeed Indicator 1 1 1 1 3 G1000 Altimeter 1 1 1 1 4 Standby Altimeter 1 1 1 1 5 G1000 Vertical Speed 1 1 1 1 Indicator 6 G1000 Attitude Indicator 1 1 1 1 7 Attitude Indicator Vacuum 1 1 1 1 Standby 8 G1000 Directional Indicator 1 1 1 1 HSI 9 G1000 Turn Coordinator 1 1 1 1 10 Non stabilized Magnetic 1 1 1 1 Com...

Page 394: ...IR As Required Per Procedure 14 Marker Beacon Receiver AIR AIR AIR AIR As Required Per Procedure 15 Blind Altitude Encoder AIR 1 1 1 As Required Per Procedure 16 Clock 1 1 1 1 VACUUM 1 Engine driven Vacuum Pump 1 1 1 1 2 Vacuum Indicator 1 1 1 1 ENGINE FUEL AND CONTROL 1 Fuel Flow Indicator 1 1 1 1 ENGINE INDICATING 1 Tachometer RPM 1 1 1 1 2 Cylinder Head Temperature 0 0 0 0 CHT Indicator 3 Oil P...

Page 395: ... concentrations mixed as noted in Section 8 of the POHI AFM MAXIMUM OPERATING ALTITUDE LIMIT MAXIMUM APPROVED OPERATING ALTITUDE 3000 meters 9800 Feet If oxygen is provided for each occupant the airplane can be operated up to the maximum altitude for the oxygen system or 4200 meters 13 779 feet whichever altitude is lower OUTSIDE AIR TEMPERATURE LIMITS Ground operations limits for a cold day Minus...

Page 396: ...mum Tailwind Velocity 5 m s 10 Knots Maximum crosswind velocity on uncontaminated paved runway 7m s 15 Knots ALLOWABLE RUNWAY SURFACE CONDITIONS 1 Uncontaminated runway with paved surface 2 Paved runway contaminated with precipitation average depth and types a Water less that 10 0 mm b Slush less than 10 0 mm c Loose snow less than 30 0 mm 3 Unpaved runway a Surface hardness must be greater than 7...

Page 397: ...ion of 0 3 poor braking 3 m s 5 Knots 0 4 average braking 5 m s 9 Knots 0 5 good braking dry or equivalent to dry runway 7 m s 15 Knots REQUIRED PLACARDS AND MARKINGS Above exit doors in clear view of each occupant Exit Bbixo q EMERGENCY PROCEDURES The following pages from Section 3 of the POH AFM have instructions for operations in RF and CIS countries These pages replace the procedures found in ...

Page 398: ...Y HEAVILY 13 Emergency Radio Operate P 855A1 Russian made Emergency Radio according to attached instructions PRECAUTIONARY LANDING WITH ENGINE POWER 1 Passenger Seats MOST UPRIGHT POSITION 2 Seats and Seat Belts SECURE 3 Airspeed 65 KIAS 4 Wing Flaps 20 5 Selected Field FLY OVER noting terrain and obstructions 6 Wing Flaps FULL on final approach 7 Airspeed 65 KIAS 8 STBY BATT Switch OFF 9 MASTER S...

Page 399: ...h Flaps UP or 60 KIAS with Flaps 10 7 Approach High Winds Heavy Seas INTO THE WIND Light Winds Heavy Swells PARALLEL TO SWELLS 8 Cabin Doors UNLATCH 9 Touchdown LEVEL ATTITUDE AT ESTABLISHED RATE OF DESCENT 1O Face CUSHION at touchdown with folded coat 11 ELT ACTIVATE 12 Airplane EVACUATE through cabin doors If necessary open window and flood cabin to equalize pressure so doors can be opened 13 Li...

Page 400: ...jects located in the baggage area and collect folded coats for protection of occupants face at touchdown Transmit Mayday messages on 121 5 MHz giving location and intentions and squawk 7700 Avoid a landing flare because of the difficulty in judging height over a water surface The checklist assumes the availability of power to make a precautionary water landing If power is not available use of the ...

Page 401: ...s and no NDB coverage airplane position between the width of such routes can only be assured up to approximately 140 km from the last known position The pilot is to disregard Supplement 1 of the POH AFM describing the pointer Model 3000 11 or 4000 11 Emergency Locator Transmitter ELT COLD WEATHER OPERATIONS S8 18 NOTE The Garmin GDU 1040 PFD MFD requires a warm up time of up to 30 minutes when exp...

Page 402: ... stored in the warm conditions The engine must be preheated before starting if engine temperature is less than Minus 6 C When the outside temperature is less than O C moisture from combustion can freeze on the engine spark plugs if the engine does not continue to operate after it is started This will prevent the engine from starting again Preheat the engine to more than O C before starting the eng...

Page 403: ...he required landing distance on a contaminated paved runway the dry runway landing distance shall be multiplied by the following K factors Conditions Basic Airfield Alternate Airfield 11 0 5 K 1 67 K 1 43 good braking and runway with no standing water 0 5 0 4 K 1 72 K 1 72 Average Braking More than 3 mm precipitation K 2 00 K 2 00 or 0 4 0 3 Poor Braking For unpaved runway landing distance refer t...

Page 404: ... CORRECTION FACTORS FOR CONTAMINATED PAVED RUNWAYS a5 l 2000 15 1800 ex 0 c J 1600 C c g j j 1400 c J ex 1 c 1 C o 800 1 600 700 800 900 1000 1100 Dry Runway Landing Ground Roll Feet Figure S8 1 Approved for RF and CIS Countries Only FAA APPROVED 172SPHAUS S8 00 U S S8 21 S8 22 ...

Page 405: ...ATION NO _ _ _ _ _I This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Artex ME406 Emergency Locator Transmitter ELT is installed f Member of GAMA COPYRIGHT 2006 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHAUS S9 QQ APPROVED BY FMAPI fIOWDtlClEAMCRPMI lI1t8Wn J _ DlillgllrllQIIan tf du _ Kt 5 DATE OF APPROVAL 30 O...

Page 406: ...fective Pages to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number Supplement Status Original Issue LOG OF EFFECTIVE PAGES QD1i 30 October 2006 Page Page Number Status 59 1 thru 59 8 Original S9 2 U S Revision Number o FM APPROVED 172SPHAUS S9 00 ...

Page 407: ... 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 Number Title FAA APPROVED 172SPHAUS S9 00 Airplane Serial Revision Incorporated Effectivity Incorporated in Airplane U S S9 3 ...

Page 408: ...anel On the ELT transmitter unit is a panel containing an ARM ON switch and a transmitter warning light The ELT installation uses two different warnings to tell the pilot when the ELT is energized The aural warning is an unusual sound that is easily heard by the pilot The visual warning is a flashing red light directly above the remote switch that shows the pilot that the ELT has been activated Wh...

Page 409: ...ITTER WARNING LIGHT Light comes on RED to indicate the transmitter is transmitting a distress signal 3 ANTENNA RECEPTACLE Connects to the antenna mounted on top of tailcone 4 REMOTE CABLE JACK Connects to the ELT remote switch assembly located on the upper right instrument panel 5 REMOTE SWITCH ASSEMBLY 2 Position Rocker SWitch a ARM OFF Turns OFF and ARMS transmitter for automatic activation if G...

Page 410: ...e civil aviation authority before use to make sure that the identification code transmitted by the ELT is in the COSPAS SARSAT database Refer to www cospas sarsat org for registration information Refer to 14 CFR 91 207 for ELT inspection requirements The ME406 must be inspected and tested by an approved technician using the correct test equipment under the appropriate civil aviation authorities ap...

Page 411: ...hing of the ELT panel switch which is located on the ELT unit 1 MAKE SURE THE ELT IS ENERGIZED a If the red warning light above the remote switch is not flashing set the remote switch to the ON position b Listen for the aural warning If the CaM radio s operate and can be energized safely no threat of fire or explosion energize a CaM radio and set the frequency to 121 5 MHz The ELT tone should be h...

Page 412: ...it has been accidentally energized no emergency The ELT can be energized by a lightning strike or hard landing If the red light above the remote switch is flashing and the aural warning is heard the ELT is energized Check for the emergency signal on a COM radio set to 121 5 MHz To stop the transmissions set the remote switch to the ON position momentarily and then set to the ARM position Tell the ...

Page 413: ...LITY SERIAL NO _ _ _ _ _ _ _ 1 REGISTRATION NO _ _ _ _ _I This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual for JAR OPS Operational Eligibility o Member of GAMA COPYRIGHT 2006 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHAUS Sl0 00 APPROVED BY LNII JIt CII t IUPMI 0Ib 1IOIt cE rfl da _M DATE OF APPROVAL Ib No ZpOb 16 NOVEM...

Page 414: ...s to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page number Supplement Status Original Issue LOG OF EFFECTIVE PAGES Page Number 810 1 thru 810 5 810 6 S10 2 U S Qili 16 November 2006 Page 8tatus Original Revision Number o FAA APPROVED 172SPHAUS S10 00 ...

Page 415: ...st 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 Number FAA APPROVED 172SPHAUS S10 00 Ajrplane Serial Revision Incorporated Effectjvjty Incorporated in Ajrp ane U S S10 3 ...

Page 416: ...as been tested and approved for IFR enroute terminal and non precision RNAV or GPS approach operations per AC 20 138A when using GPS GNSS with the correct navigation database The G1000 System meets the requirements for GPS GNSS as a Primary Means of Navigation for Oceanic Remote Operations RNP 10 per AC 20 138A FAA Notice N8110 60 FAA Order 8400 12A and FAA Order 8700 1 Both GPS GNSS receivers are...

Page 417: ... Extended Squitter functionality is supported by the GTX 33 This does not constitute airworthiness or operational approval for Extended Squitter functionality OPERATING LIMITATIONS There is no change to the airplane operating limitations for JAR OPS Operational Eligibility JAR OPS may require separate airspace operating limitations EMERGENCY PROCEDURES There is no change to the airplane emergency ...

Page 418: ...must be attached to the FAA approved Cessna Aircraft Models 172R 172S 182S 182T T182T 206H and T206H associated Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Airpiane IS modified by the mstallation of AMSAFE AViation Inflatable Restraint AAIR System V23 Version In accordance with STC No S_M1700 A The Information contained herem supplements or supersedes the baSIC manu...

Page 419: ...t and balance lnfoO nation summary tor Model 206 addiliQnal kits and added altemate summarIes for all models with naw ter eMA In oarenthesis AFM Supplement for AMSAFE Aviation Inflatable Restraint On Cessna 172 182 and 206 TC SAQ1700LA FAA APPROVAL Qtjg Jallitgce P Po Manager Flight Test Brench ANM 160L federal Aviation Administration L os Angeles Aircraft Certification OffIce Transport A1rplane D...

Page 420: ...ot be used 10 secure 8 child safety seat The Auxiliary Child Seat Buckle adapter PIN 7035 2090112396 LH ilnd 7035 2100212396 R H secures a Child Safety Seal to either left Of nght positions of the Rear Seat for all models see weming label below It Is typlcany stored under the cushion and Is found in the center of the seat adjacent to the standard MlR End R elease Buckle Assembly Identlfleble by pa...

Page 421: ...s 172R 1725 _ without optional rear Hat blnch MlR Svtttm Empty Waight Arm 3 8413 45 397 3 698 16 J2 S Iba Momerlt 174 686 167 871 MlR System Difference Added EMA PIN 08358 409 MlR System Dttrsrsnce Added EMA PIN 508356 421 1898 348 Ibs Nlw Empty Weight EMA PIN 508 1696 198 Ibs New Empty Weight EMA PIN 5083584 2 1 Models 1829 182 T182T with rear at bench MlR System Empty WeigOt Arm 7 638 57 882 7 3...

Page 422: ...m Empty Weight Arm 2 575 44 563 2 425 2210 Jbs Mqmftn 114 802 108 113 AAIR System Difference Added EMA PIN 08358 409 MlR System Difference Added EMA PIN 508358 421 2212 575Ib New Empty Weight EMA PIN 508355 409 2212 425 Ib New Empty Weight EMA PIN 508358 421 Moa 206H 206H _ M ddlt Ut Only MlR SY tero Empty Weighl Arm 3 87 65 382 3 725 2210Ib MgmftO 253 356 243 547 MlR System Difference Added EMA P...

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