Cessna 172S Skyhawk Скачать руководство пользователя страница 228

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Содержание 172S Skyhawk

Страница 1: ... CeSSrii A Textron Company 1725 5kyhawk Information Manual 172SIM ...

Страница 2: ...R GENERAL PURPOSES ONLY IT WILL NOT BE KEPT CURRENT AND THEREFORE CANNOT BE USED AS A SUBSTITUTE FOR THE OFFICIAL PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL INTENDED FOR OPERATION OF THE AIRPLANE THE PILOT S OPERATING HANDBOOK MUST BE CARRIED IN THE AIRPLANE AND AVAILABLE TO THE PILOT AT ALL TIMES I Revision 5 Cessna Aircraft Company Original Issue 8 July 1998 Revision 5 19...

Страница 3: ...638 NM 53 Gallons Usable Fuel Time 6 72 HRS RATE OF CLIMB AT SEA LEVEL 730 FPM SERVICE CEILING 14 000 FEET TAKEOFF PERFORMANCE Ground Roll 960 FEET Total Distance Over 50 Foot Obstacle 1630 FEET LANDING PERFORMANCE Ground Roll 575 FEET Total Distance Over 50 Foot Obstacle 1335 FEET STALL SPEED Flaps Up Power Off 53 KCAS Flaps Down Power Off 48 KCAS MAXIMUM WEIGHT Ramp 2558 POUNDS Takeoff 2550 POUN...

Страница 4: ... 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 surfaced dry runways and no wind They are calculated values derived from flight tests conducted by Cessna Aircraft C...

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Страница 6: ...Aircraft Company Model 172S THIS MANUAL INCORPORATES INFORMATION ISSUED IN THE PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL AT REVISION 5 DATED 19 JULY 2004 PART NUMBER 172SPHUS05 COPYRIGHT 1998 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA I Revision 5 U S 172SIM v vi ...

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Страница 8: ...ONTENTS 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 I Revision 5 U S vii viii ...

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Страница 10: ...Loadings 1 7 Symbols Abbreviations and Terminology 1 8 General Airspeed Terminology And Symbols 1 8 Meteorological Terminology 1 9 Engine Power Terminology 1 9 Airplane Performance And Flight Planning Terminology 1 10 Weight And Balance Terminology 1 11 Metric 1Imperial 1U S Conversion Charts 1 13 Weight Conversions 1 14 Length Conversions 1 16 Distance Conversions 1 20 Volume Conversions 1 21 Tem...

Страница 11: ...SECTION 1 GENERAL CESSNA MODEL 172S It 36 1 1 76 MAX Figure 1 1 Three View Normal Ground Attitude Sheet 1 of 2 0510T1005 051 OT1 005 1 2 Revision 4 ...

Страница 12: ...PROPELLER GROUND CLEARANCE IS 11 1 4 NOTE 4 WING AREA IS 174 SQUARE FEET NOTE 5 MINIMUM TURNING RADIUS PIVOT POINT TO OUTBOARD WING TIP IS 27 51 2 NOTE 6 NORMAL GROUND ATTITUDE IS SHOWN WITH NOSE STRUT SHOWING APPROXIMATELY 2 OF STRUT AND WINGS LEVEL __ Figure 1 1 Three View Normal Ground Attitude Sheet 2 051 OT1 005 Revision 4 1 3 ...

Страница 13: ... Textron Lycoming 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 Prope...

Страница 14: ... the Left or Right position Refer to Figure 1 1 for normal ground attitude dimensions Oil Specification MIL 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 MI...

Страница 15: ... 0 F to 21 c 70 F 30 30 40 or 20W 40 Below 12 C 10 F 20 30 or 20W 30 18 C O F to 32 C gO F 20W SO 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 I Total 9 U S Quarts MAXIMUM CERTIFICATED WEIGHTS Ramp Weight Normal Category Utility Category Takeoff Weight Normal Category Utility Category Landing...

Страница 16: ...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 Dimensions of the baggage a...

Страница 17: ...sed without overstressing the airframe 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...

Страница 18: ...ull throttle engine runup when the airplane is on the ground and stationary 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 the engine decreases for a given throttle setting...

Страница 19: ...d 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 in flight Gallons Per Hour is the amount of fuel consumed per hour Nautical Miles Per Gallon is ...

Страница 20: ...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 extreme center of gravity locations within which the airplane must be operat...

Страница 21: ...ncludes 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 the scale readings Tare is deducted from the scale reading to obtain the actua...

Страница 22: ...vert 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 Please refer to the following pages for these charts May 30 00 1 13 ...

Страница 23: ...202 83 205 03 207 24 209 44 211 64 224 87 227 08 229 28 231 49 233 69 POUNDS INTO KILOGRAMS LlVRES 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...

Страница 24: ...190 180 170 160 150 140 130 120 110 100 90 80 70 60 50 40 30 20 10 0 SECTION 1 GENERAL 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 0 Units x 10 100 etc Figure 1 2 Weight Conversions Sheet 2 0585T102 Revision 4 1 15 ...

Страница 25: ...6 06 272 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...

Страница 26: ...T 320 300 280 260 240 220 200 180 160 140 120 100 80 60 40 20 0 SECTION 1 GENERAL Feet x 305 Meters METERS 100 95 90 85 80 75 70 65 60 55 50 45 40 35 30 25 20 15 10 5 0 Units x 10 100 etc Figure 1 3 Length Conversions Sheet 2 I Revision 4 1 17 ...

Страница 27: ...858 36 220 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 em em em em em 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 ...

Страница 28: ...imeters x 394 Inches Inches x 2 54 Centimeters INCHES CENTIMETERS 10 25 24 9 23 8 7 6 5 22 21 20 19 18 17 16 15 14 13 12 11 4 10 3 9 8 7 6 2 5 1 4 3 2 1 o 0 Units x 10 100 etc 0585T1028 Figure 1 4 Length Conversions Sheet 2 I Revision 4 1 19 ...

Страница 29: ...ers x 54 Nautical Miles STATUTE NAUTICAL MILES MILES KILOMETERS 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 55 100 60 50 50 90 55 50 45 45 80 45 40 40 70 40 35 35 60 35 30 30 30 25 25 50 25 20 20 40 20 30 15 15 15 20 10 10 10 Units x 10 100 etc 5 5 5 10 0 0 0 0 0585T1029 Figure 1 5 Distance Conversions 1 20 Revisio...

Страница 30: ...238 20 458 20 678 20 898 21 118 22 438 22 658 22 878 23 098 23 318 IMPERIAL GALLONS INTO LITERS GALLONS IMPERIAL EN LlTRES 2 3 4 5 6 Lt Lt Lt Lt Lt 9 092 13 638 18 184 22 730 27 276 54 552 59 097 63 643 68 189 72 735 100 D1 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 3...

Страница 31: ...Gallons 100 IMPERIAL 95 440 LITERS 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 CESSNA MODEL 172S 0585T1032 Figure 1 6 Volume Conversions Sheet 2 of 3 July 8 98 ...

Страница 32: ...RS 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 55 180 45 45 50 40 160 40 45 140 35 40 35 30 30 120 35 25 30 25 100 20 25 20 80 15 20 15 60 15 40 10 10 10 5 5 5 20 0 0 0 0 Units x 10 100 etc 0585T1033 Figure 1 6 Volume Conversions Sheet 3 of 3 May 30 00 1 23 ...

Страница 33: ... 0 460 240 40 480 50 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 70 380 170 180 80 760 400 190 90 780 420 200 800 210 100 820 440 220 840 230 110 860 460 240 880 250 120 900 480 260 920 270 130 500 280 140 520 290 300 150 540 310 320 160 560 0585T1034 Figure 1 7 Temperature Conversions July 8 98 ...

Страница 34: ... CONVERSION HECTOPASCALS MILLIBARS TO INCHES MERCURY inHG l 3 l i f l i iii m iii iii iii il iii iii iii iii Rl Rl il Rl iii l iii l j l i iii Ii 1 1 Iii Ii ill iI lilil 3 i ll iii li iii Figure 1 8 Hectopascals to Inches Mercury Revision 4 1 25 ...

Страница 35: ...LITERS KILOGRAMS 100 100 95 150 135 95 130 90 140 125 90 85 120 85 130 AVGAS FUEL 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 70 65 45 60 40 60 55 40 35 50 35 50 45 30 30 40 25 40 35 25 20 30 20 30 25 15 20 20 15 10 15 10 5 10 10 5 5 0 0 Units x 10 100 etc 0 0 0585T1030 Figure 1 9 Volume to Weight Conversion Revision 4 ...

Страница 36: ...CESSNA MODEL 172S I AVGAS SPECIFIC GRAVITY 0 72 Revision 4 Figure 1 10 Quick Conversions SECTION 1 GENERAL 1 27 1 281 ...

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Страница 38: ...y Utility Category Center Of Gravity Limits Normal Category Utility Category Maneuver Limits Normal Category Utility Category Flight Load Factor Limits Normal Category Utility Category Kinds Of Operation Limits Fuel Limitations Additional Fuel Limitations Other Limitations Flap Limitations Placards IRevision 4 Page 2 3 2 4 2 5 2 5 2 6 2 7 2 7 2 7 2 7 2 7 2 8 2 8 2 8 2 9 2 10 2 10 2 10 2 10 2 11 2 ...

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Страница 40: ...this Pilot s I Operating Handbook for amended operating limitations operating procedures performance data and other necessary information for airplanes equipped with specific options NOTE The airspeeds listed in the Airspeed Limitations chart Figure 2 1 and the Airspeed Indicator Markings chart Figure 2 2 are based on Airspeed Calibration data shown in Section 5 with the normal static source If th...

Страница 41: ...o 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 Speed Do not make full or 2550 Pounds 102 105 abrupt control 2200 Pounds 95 98 movements above 1900 Pounds 88 90 this speed VFE Maximum Flap Extended Speed Do not exceed this 10 Flaps 107 110 speed with flaps 10 to 30 Flaps 8...

Страница 42: ... 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 Maximum speed for all operations POWERPLANT LIMITATIONS Engine Manufacturer Textron Lycoming Engine Model Number IO 360 L2A Maximum Power 180 BHP rating Engine Operating Limits for Takeoff a...

Страница 43: ...er 1A170E JHA7660 Propeller Diameter Maximum 76 inches Minimum 75 inch minimum POWERPLANT INSTRUMENT MARKINGS Powerplant instrument markings and their color code significance are shown in Figure 2 3 RED LINE GREEN ARC RED INSTRUMENT NORMAL LINE MINIMUM OPERATING MAX Tachometer Sea Level 2100 to 2500 RPM 5000 Feet 2100 to 2600 RPM 2700 10 000 Feet 2100 to 2700 RPM Oil 100 to 245 F 245 F Temperature...

Страница 44: ...is 120 Ibs UTILITY CATEGORY Maximum Ramp Weight 2208 Ibs Maximum Takeoff Weight 2200 Ibs Maximum Landing Weight 2200 Ibs 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 of Gravity Range Forward 35 0 inches aft of datum at 1950 Ibs or less with straight line variati...

Страница 45: ...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 EN TRY SPEED Chandelles 105 Knots Lazy Eights 1...

Страница 46: ...MENDED ENTRY SPEED Chandelles 105 Knots Lazy Eights 105 Knots Steep Turns 95 Knots Spins Slow Deceleration Stalls Except Whip Stalls Slow Deceleration 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 build up speed...

Страница 47: ... Down 3 0g The design load factors are 150 of the above and in all cases the structure meets or exceeds design loads KINDS OF OPERATION LIMITS I The airplane as delivered is equipped for day VFR and may be equipped for night VFR and or IFR operations FAR Part 91 establishes the minimum required instrumentation and equipment for these operations The reference to types of flight operations on the op...

Страница 48: ...attitude definition ADDITIONAL FUEL LIMITATIONS Takeoff and land with the fuel selector valve handle in the BOTH position Maximum slip or skid duration with one tank dry 30 seconds Operation on either LEFT or RIGHT tank limited to level 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 fue...

Страница 49: ...must be complied 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 mu...

Страница 50: ...EL SELECTOR FUEL ALL FLIGHT ATTITUDES RIGHT 26 5 GAL LEVEL FLIGHT ONLY 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 Partial flap range with blue color code also mechanical detent at 10 10 to 30 85 KIAS Ju18 98 White color code also mechanical detent at 20 2 13 ...

Страница 51: ...CH 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 30 increments 7 On the oil filler cap OIL 8 aTS 8 On control lock CAUTION CONTROL LOCK REMOVE BEFORE STARTING ENGINE 9 Near airspeed indicator II MANEUVERING SPEED 105 KIAS 2 14 Revision 4 ...

Страница 52: ... MUST BE SERVICED IN ACCORDANCE WITH FAR PART 91 207 11 On forward face of firewall 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 I IRevision 4 2 15 2 16 ...

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Страница 54: ...tely After Takeoff Engine Failure During Flight Restart Procedures Forced Landings Emergency Landing Without Engine Power Precautionary Landing With Engine Power Ditching Fires During Start On Ground Engine Fire In Flight Electrical Fire In Flight Cabin Fire Wing Fire Icing Inadvertent Icing Encounter Static Source Blockage Landing With A Flat Main Tire Landing With A Flat Nose Tire Revision 4 3 4...

Страница 55: ... 3 16 Emergency Operation In Clouds Vacuum System Failure 3 16 Executing A 1800 Turn In Clouds 3 16 Emergency Descent Through Clouds 3 17 Recovery From Spiral Dive In The Clouds 3 18 Inadvertent Flight Into Icing Conditions 3 18 Static Source Blocked 3 18 Spins 3 19 Rough Engine Operation Or Loss Of Power 3 20 Spark Plug Fouling 3 20 Magneto Malfunction 3 20 Engine Driven Fuel Pump Failure 3 20 Ex...

Страница 56: ...tered However should an emergency arise the basic guidelines described in this section should be considered and applied as necessary to correct the problem Emergency procedures associated with standard avionics the ELT or any optional systems can be found in the Supplements Section 9 AIRSPEEDS AIRSPEEDS FOR EMERGENCY OPERATION Engine Failure After Takeoff Wing Flaps Up Wing Flaps Down Maneuvering ...

Страница 57: ...y ENGINE FAILURES ENGINE FAILURE DURING TAKEOFF ROLL 1 Throttle IDLE 2 Brakes APPLY 3 Wing Flaps RETRACT 4 Mixture IDLE CUT OFF 5 Ignition Switch OFF 6 Master Switch OFF ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF 1 Airspeed 70 KIAS flaps UP 65 KIAS flaps DOWN 2 Mixture IDLE CUT OFF 3 Fuel Shutoff Valve OFF Pull Full Out 4 Ignition Switch OFF 5 Wing Flaps AS REQUIRED 6 Master Switch OFF 7 Cabin Door ...

Страница 58: ...y from idle and lean the mixture from full rich as required for smooth operation 7 Auxiliary Fuel Pump Switch OFF NOTE If the fuel flow indicator immediately drops to zero indicating an engine driven fuel pump failure return the Auxiliary Fuel Pump Switch to the ON position FORCED LANDINGS EMERGENCY LANDING WITHOUT ENGINE POWER 1 Passenger Seat Backs MOST UPRIGHT POSITION 2 Seats and Seat Belts SE...

Страница 59: ...AY on 121 5 MHz giving location and intentions and SQUAWK 7700 2 Heavy Objects in baggage area SECURE OR JETTISON if possible 3 Passenger Seat Backs MOST UPRIGHT POSITION 4 Seats and Seat Belts SECURE 5 Wing Flaps 20 to 30 6 Power ESTABLISH 300 FT MIN DESCENT AT 55 KIAS NOTE If no power is available approach at 70 KIAS with flaps up or at 65 KIAS with 10 flaps 7 Approach High Winds Heavy Seas INTO...

Страница 60: ...CURE a Master Switch OFF b Ignition Switch OFF 11 Parking Brake RELEASE 12 Airplane EVACUATE 13 Fire EXTINGUISH using fire extinguisher wool blanket or dirt 14 Fire Damage INSPECT repair damage or replace damaged components or wiring before conducting another flight ENGINE FIRE IN FLIGHT 1 Mixture IDLE CUT OFF 2 Fuel Shutoff Valve Pull Out OFF 3 Auxiliary Fuel Pump Switch OFF 4 Master Switch OFF I...

Страница 61: ...cessary for continuance of flight to nearest suitable airport or landing area 7 Master Switch ON S Circuit Breakers CHECK for faulty circuit do not reset 9 Radio Switches OFF 10 Avionics Master Switch ON 11 Radio Electrical Switches ON one at a time with delay after each until short circuit is localized CABIN FIRE 1 Master Switch OFF 2 Vents Cabin Air Heat CLOSED to avoid drafts 3 Fire Extinguishe...

Страница 62: ...r intake filter or in extremely rare instances ice completely blocking the fuel injection air reference tubes Change the throttle position to obtain maximum RPM This may require either advancing or retarding the throttle dependent on where ice has accumulated in the system Adjust mixture as required for maximum RPM 5 Plan a landing at the nearest airport With an extremely rapid ice build up select...

Страница 63: ...e calibration tables in Section 5 LANDING WITH A FLAT MAIN TIRE 1 Approach NORMAL 2 Wing Flaps 300 3 Touchdown GOOD MAIN TIRE FIRST hold airplane off flat tire as long as possible with aileron control 4 Directional Control MAINTAIN using brake on good wheel as required LANDING WITH A FLAT NOSE TIRE 1 Approach NORMAL 2 Flaps AS REQUIRED 3 Touchdown ON MAINS hold nose wheel off the ground as long as...

Страница 64: ...ciator panel may occur during low RPM conditions with an electrical load on the system such as during a low RPM taxi Under these conditions the annunciator will go out at higher RPM The I master switch need not be recycled since an overvoltage condition has not occurred to deactivate the alternator system 1 Avionics Master Switch OFF 2 Alternator Circuit Breaker ALT FLO CHECK IN I 3 Master Switch ...

Страница 65: ...or or Right Vacuum VAC R Annunciator Illuminates A CAUTION IF VACUUM IS NOT WITHIN NORMAL OPERATING LIMITS A FAILURE HAS OCCURRED IN THE VACUUM SYSTEM AND PARTIAL PANEL PROCEDURES MAY BE REQUIRED FOR CONTINUED FLIGHT 1 Vacuum Gage CHECK to ensure vacuum within normal operating limits 13 12 Revision 4 ...

Страница 66: ...e of procedures fresh ENGINE FAILURE If an engine failure occurs during the takeoff roll the most important thing to do is stop the airplane on the remaining runway Those extra items on the checklist will provide added safety after a failure of this type Prompt lowering of the nose to maintain airspeed and establish a glide attitude is the first response to an engine failure after takeoff In most ...

Страница 67: ...anding area an effort should be made to identify the cause of the failure If time permits an engine restart should be attempted as shown in the checklist If the engine cannot be restarted a forced landing without power must be completed 12 000 I 10 000 u z 8000 II II w I W 6000 0 III l I 4000 I CJ jj I 2000 SPEED 68 KIAS PROPELLER WINDMILLING FLAPS UP ZERO WINO o o 2 4 6 8 10 12 14 16 18 20 GROUND...

Страница 68: ...a landing flare because of difficulty in judging height over a water surface The checklist assumes the availability of power to make a precautionary water landing If power is not available use of the airspeeds noted with minimum flap extension will provide a more favorable attitude for a power off ditching In a forced landing situation do not set the AVIONICS MASTERI switch or the airplane MASTER ...

Страница 69: ...result in elimination of the fire EMERGENCY OPERATION IN CLOUDS Total Vacuum System Failure If both the vacuum pumps fail in flight the directional indicator and attitude indicator will be disabled and the pilot will have to rely on the turn coordinator if he inadvertently flies into clouds If an autopilot is installed it too may be affected Refer to Section 9 Supplements for additional details co...

Страница 70: ...n emergency descent through clouds To guard against a spiral dive choose an easterly or westerly heading to minimize compass card swings due to changing bank angles In addition keep hands off the control wheel and steer a straight course with rudder control by monitoring the turn coordinator Occasionally check the compass heading and make minor corrections to hold an approximate course Before desc...

Страница 71: ...Flight into icing conditions is prohibited and extremely dangerous An inadvertent encounter with these conditions can best be handled using the checklist procedures The best procedure of course is to turn back or change altitude to escape icing conditions During these encounters an unexplained loss in engine speed could be caused by ice blocking the air intake filter or in extremely rare instances...

Страница 72: ... 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 extend the recovery 6 AS ROTATION ST...

Страница 73: ...e use of a single ignition position MAGNETO MALFUNCTION A sudden engine roughness or misfiring is usually evidence of magneto problems Switching from BOTH to either L or R ignition switch position will identify which magneto is malfunctioning Select different power settings and enrichen the mixture to determine if Icontinued operation on BOTH magnetos is possible If not switch to the good magneto ...

Страница 74: ... is suspected smoother engine operation ma result from making the following changes singly or together se the auxiliary fuel pump to the ON position lean the mixture fo smooth engine operation and select another fuel tank Increasing the airspeed to provide more air flow through the cowling will aid in cooling the engine and fuel system components LOW OIL PRESSURE If the low oil pressure annunciato...

Страница 75: ...OF CHARGE After engine starting and heavy electrical usage at low engine speeds such as extended taxiing the battery condition will be low enough to accept above normal charging during the initial part of a flight However after thirty minutes of cruising flight the ammeter should be indicating less than two needle widths of charging current If the charging rate were to remain above this value on a...

Страница 76: ...rging will resume and the low voltag annunciator VOLTS will go off The avionics master switch ma then be returned to the ON position If the annunciator illuminates again a malfunction is confirmed In this event the flight should be terminated and or the current drain on the battery minimized because the battery can supply the electrical system for only a limited period of time Battery power must b...

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Страница 78: ... Cabin 4 7 Empennage 4 8 Right Wing Trailing Edge 4 8 Right Wing 4 8 Nose 4 9 Left Wing 4 10 Left Wing Leading Edge 4 11 Left Wing Trailing Edge 4 11 Before Starting Engine 4 11 Starting Engine With Battery 4 12 Starting Engine With External Power 4 13 Before Takeoff 4 1 Takeoff 4 15 Normal Takeoff 4 15 Short Field Takeoff 4 16 Enroute Climb 4 16 Cruise 4 1 Descent 4 1 Before Landing 4 1 Revision ...

Страница 79: ... Duty Cycle 4 20 Leaning For Ground Operations 4 21 Taxiing 4 21 Before Takeoff 4 23 Warm Up 4 23 Magneto Check 4 23 Alternator Check 4 23 Landing Lights 4 24 Takeoff 4 24 Power Check 4 24 Wing Flap Settings 4 25 Crosswind Takeoff 4 25 Enroute Climb 4 25 Cruise 4 26 Leaning With an EGT Indicator 4 27 Fuel Savings Procedures for Flight Training Operations 4 28 Fuel Vapor Procedures 4 29 Stalls 4 30...

Страница 80: ...TS Continued Page Landing 4 33 Normal Landing 4 33 Short Field Landing 4 33 Crosswind Landing 4 34 Balked Landing 4 34 Cold Weather Operation 4 34 Winterization Kit 4 36 Hot Weather Operation 4 36 Noise Characteristics And Noise Reduction 4 36 Revision 4 4 3 4 4 ...

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Страница 82: ... Short 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 30 60 70 KIAS Short Field Approach ...

Страница 83: ...cess 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 heat switches on If a night flight...

Страница 84: ...ELLER THROUGH BY HAND TREAT THE PROPELLER AS IF THE IGNITION SWITCH WERE ON DO NOT STAND NOR ALLOW ANYONE ELSE TO STAND WITHIN THE ARC OF THE PROPELLER SINCE A LOOSE OR BROKEN WIRE OR A COMPONENT MALFUNCTION COULD CAUSE THE PROPELLER TO ROTATE 8 Master Switch ON 9 Fuel Quantity Indicators CHECK QUANTITY and ENSURE LOW FUEL ANNUNCIATORS L LOW FUEL R ARE EXTINGUISHED 10 Avionics Master Switch ON 11 ...

Страница 85: ...19 Pitot Heat ON Carefully check that pitot tube is warm to touch within 30 seconds 20 Pitot Heat OFF 21 Master Switch OFF 23 Baggage Door CHECK lock with key 1 22 Elevator Trim SET for takeoff 24 Autopilot Static Source Opening if installed CHECK for blockage G EMPENNAGE 1 Rudder Gust Lock if installed REMOVE 2 Tail Tie Down DISCONNECT 3 Control Surfaces CHECK freedom of movement and security 4 T...

Страница 86: ...DENCE 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 4 Fuel Quantity CHECK VISUALLY for desired level 5 Fuel Filler Cap SECURE and VENT UNOBSTRUCTED NOSE 1 Fuel Strainer Quick Drain Valve Located on bottom of fuselage DRAIN at least a cupf...

Страница 87: ...LEFTWING 1 Fuel Quantity CHECK VISUALLY for desired level 2 Fuel Filler Cap SECURE and VENT UNOBSTRUCTED 3 Fuel Tank Sump Quick Drain Valves DRAIN at least a cupful of fuel using sampler cup from each sump location to check for water sediment and proper fuel grade before each flight and after each refueling If water is observed take further samples until clear and then gently rock wings and lower ...

Страница 88: ... LEFT WING Trailing Edge 1 Aileron CHECK for freedom of movement and security 2 Flap CHECK for security and condition BEFORE STARTING ENGINE 1 Preflight Inspection COMPLETE 2 Passenger Briefing COMPLETE 3 Seats and Seat Belts ADJUST and LOCK Ensure inertia reel locking 4 Brakes TEST and SET 5 Circuit Breakers CHECK IN 6 Electrical Equipment OFF I A CAUTION THE AVIONICS MASTER SWITCH MUST BE OFF DU...

Страница 89: ...sually 3 to 5 seconds then set to IDLE CUTOFF full aft position 8 Auxiliary Fuel Pump Switch OFF 9 Ignition Switch START release when engine starts 10 Mixture ADVANCE smoothly to RICH when engine starts NOTE If engine floods engine has been primed too much turn off auxiliary fuel pump place mixture to idle cutoff open throttle 1 2 to full and motor crank engine When engine starts set mixture to fu...

Страница 90: ...conds then set to IDLE CUTOFF full aft position 10 Auxiliary Fuel Pump Switch OFF 11 Ignition Switch START release when engine starts 12 Mixture ADVANCE smoothly to RICH when engine starts NOTE If engine floods engine has been primed to much turn off auxiliary fuel pump set mixture in idle cutoff open throttle 1 2 to full and motor crank engine When engine starts set mixture to full rich and close...

Страница 91: ...to approximately 1500 RPM as engine RPM increases alternator output should increase to meet the system load requirements f Ammeter and Low Voltage Annunciator CHECK the ammeter should indicate in the positive direction showing that the alternator is supplying current and the Low Voltage Annunciator VOLTS should not be lighted NOTE If the indications as noted in Step d and Step f are not observed t...

Страница 92: ...uum Gage CHECK I c Engine Instruments and Ammeter CHECK 11 Annunciator Panel Ensure no annunciators are illuminated 12 Throttle CHECK IDLE 13 Throttle 1000 RPM or LESS 14 Throttle Friction Lock ADJUST 15 Strobe Lights AS DESIRED 16 Radios and Avionics SET 17 NAV GPS Switch if installed SET 1S Autopilot if installed OFF 19 Manual Electric Trim if installed CHECK 20 Elevator Trim SET for takeoff 21 ...

Страница 93: ... 3 Mixture RICH above 3000 feet LEAN to obtain maximum RPM CRUISE 1 Power 2100 2700 RPM No more than 75 is recommended 2 Elevator Trim ADJUST 3 Mixture LEAN DESCENT 1 Power AS DESIRED 2 Mixture ADJUST for smooth operation full rich for idle power 4 NAV GPS Switch SET 5 Fuel Selector Valve BOTH I 3 Altimeter SET 6 Wing Flaps AS DESIRED 0 10 below 110 KIAS 10 30 below 85 KIAS BEFORE LANDING 1 Pilot ...

Страница 94: ...DUCE to idle after clearing obstacle 5 Touchdown MAIN WHEELS FIRST 6 Brakes APPLY HEAVILY 7 Wing Flaps RETRACT BALKED LANDING 1 Throttle FULL OPEN 2 Wing Flaps RETRACT TO 20 3 Climb Speed 60 KIAS 4 Wing Flaps 10 until obstacles are cleared RETRACT after reaching a safe altitude and 65 KIAS AFTER LANDING 1 Wing Flaps UP SECURING AIRPLANE 1 Parking Brake SET 2 Electrical Equipment Autopilot if insta...

Страница 95: ...ts damage to nose wheel as a result of exceeding tow limits and avionics antennas Outside storage for long periods may result in dust and dirt accumulation on the induction air filter obstructions in airspeed system lines water contaminants in fuel tanks and insect bird rodent nests in any opening If any water is detected in the fuel system the fuel tank sump quick drain valves fuel reservoir quic...

Страница 96: ...so 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 However in warmer weather engine compartment temperatures may increase rapidly following engine shutdown and fuel in the lines will vapori...

Страница 97: ...necessary I After starting if the oil pressure gage does not begin to show pressure within 30 seconds in the summer time and approximately one minute in very cold weather stop the engine and investigate Lack of oil pressure can cause serious engine damage NOTE Additional details concerning cold weather starting and operation may be found under COLD WEATHER OPERATION paragraphs in this section I RE...

Страница 98: ...ended NOTE If ground operation will be required after the BEFORE TAKEOFF checklist is completed lean the mixture again as described above until ready for the TAKEOFF checklist TAXIING 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 grav...

Страница 99: ...TION 14 22 NOTE Strong quartering tail winds require caution Avoid sudden bursts of the throttle and sharp braking when the airplane is in this situation Use the steerable nose wheel and rudder to maintain direction 0585X1020 Figure 4 2 Taxiing Diagram Revision 4 ...

Страница 100: ...er magneto or show greater than 50 RPM differential between magnetos If there is a doubt concerning operation of the ignition system RPM checks at higher engine speeds will usually confirm whether a deficiency exists An absence of RPM drop may be an indication of faulty grounding of one side of the ignition system or should be cause for suspicion that the magneto timing is set in advance of the se...

Страница 101: ...maximum RPM Full throttle run ups over loose gravel are especially harmful to propeller tips When takeoffs must be made over a gravel surface it is very important that the throttle be advanced slowly This allows the airplane to start rolling before high RPM is developed and the gravel will be blown back of the propeller rather than pulled into it When unavoidable small dents appear in the propelle...

Страница 102: ...FF Takeoffs into strong crosswind conditions normally are performed with the minimum flap setting necessary for the field length to minimize the drift angle immediately after takeoff With the ailerons partially deflected into the wind the airplane is accelerated to a speed slightly higher than normal then pulled off briskly to prevent possible settling back to the runway while drifting When clear ...

Страница 103: ...complete any flight The Cruise Performance Table Figure 4 3 illustrates the true airspeed and nautical miles per gallon during cruise for various altitudes and percent powers and is based on standard conditions and zero wind This table should be used as a guide along with the available winds aloft information to determine the most favorable altitude and power setting for a given trip The selection...

Страница 104: ...e EGT indication begins to increase continue to slowly lean the mixture until an EGT indication decrease is just detectable Reverse the adjustment slowly in the rich direction until an EGT indication decrease is again just detectable then set the EGT index pointer to match the peak indication The mixture may be leaned slightly to return to peak EGT or may be further richened to Recommended Lean mi...

Страница 105: ...above until ready I for the TAKEOFF checklist I I 2 Lean the mixture for maximum RPM during full throttle climbs above 3000 feet The mixture 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 m...

Страница 106: ...described under FUEL SAVINGS PROCEDURES FOR FLIGHT TRAINING OPERATIONS 4 Just prior to TAKEOFF apply full throttle for approximately 10 seconds to verify smooth engine operation for takeoff NOTE When the engine is operated above 1800 RPM the resulting increased fuel flow also makes for lower fuel temperatures throughout the engine fuel system This increased flow purges the fuel vapor and the coole...

Страница 107: ...uipment including the microphone and rear seat belts should be stowed or secured For a solo flight in which spins will be conducted the copilot s seat belt and shoulder harness should also be secured Care should be taken to ensure that the pilot can easily reach the flight controls and produce maximum control travels It is recommended that where feasible entries be accomplished at high enough alti...

Страница 108: ...ral For the purpose of training in spins and spin recoveries a 1 or 2 turn spin is adequate and should be used Up to 2 turns the spin will progress to a fairly rapid rate of rotation and a steep attitude Application of recovery controls will produce prompt recoveries within 1 4 turn During extended spins of two to three turns or more the spin will tend to change into a spiral particularly to the r...

Страница 109: ...bited since the high speeds which may occur during recovery are potentially damaging to the flap wing structure LANDING NORMAL LANDING Normal landing approaches can be made with power on or power off with any flap setting desired Surface winds and air turbulence are usually the primary factors in determining the most comfortable approach speeds Steep slips should be avoided with flap settings grea...

Страница 110: ...gs greater than 20 are used in sideslips with full rudder deflection some elevator oscillation may be felt at normal approach speeds However this does not affect control of the airplane Although the crab or combination method of drift correction may be used the wing low method gives the best control After touchdown hold a straight course with the steerable nose wheel and occasional braking if nece...

Страница 111: ... 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 A WARNING WHEN PULLING THE PROPELLER THROUGH BY HAND TREAT IT AS IF THE IGNITION SWITCH IS TURNED ON A LOOSE ...

Страница 112: ...tart during the first few attempts or if engine firing diminishes in strength it is probable that the spark plugs have been frosted over Preheat must be used before another start is attempted During cold weather operations no indication will be apparent on the oil temperature gage prior to takeoff if outside air temperatures are very cold After a suitable warm up period 2 to 5 minutes at 1000 RPM ...

Страница 113: ...ise 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 departure from or approach to an airport climb...

Страница 114: ...n Alternate Static Source Figure 5 2 Temperature Conversion Chart Figure 5 3 Stall Speeds Figure 5 4 Crosswind Components Figure 5 5 Short Field Takeoff Distance Figure 5 6 Maximum Rate Of Climb Figure 5 7 Time Fuel And Distance To Climb Figure 5 8 Cruise Performance Figure 5 9 Range Profile Figure 5 10 Endurance Profile Figure 5 11 Short Field Landing Distance IRevision 4 Page 5 3 5 3 5 3 5 4 5 5...

Страница 115: ......

Страница 116: ...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 illustrate the effect of different variables Sufficiently detailed inf...

Страница 117: ...t 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 Ground roll 1285 Feet Total distance to clear a 50 foot obstacle 2190 Feet These distances are well within the available takeoff field length However a cor...

Страница 118: ...ise 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 power settings are used For this sample problem a cruise power of approximately 65 will be used...

Страница 119: ...e made as noted on the climb chart The approximate effect of a non standard temperature is to increase the time fuel and distance by 10 for each 10 C above standard temperature due to the lower rate of climb In this case assuming a temperature 16 C above standard 16 C O C the correction would be 16 C X 10 16 Increase 10 C IWith this factor included the fuel estimate would be calculated as follows ...

Страница 120: ...es 3 2 Hours 107 Knots The fuel required for cruise is 3 2 hours X 8 9 gallons hour 28 5 Gallons A 45 minute reserve requires 45 60 X8 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 es...

Страница 121: ...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...

Страница 122: ...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 90 100 11 0 KCAS 51 57 63 71 80 89 99 109 FLAPS 30 KIAS 40 50 60 70 80 85 KCAS 50 56 63 72 81 86 Figure 5 1 Airspeed Calibration Sheet 1 of 2 July 8 98 5 9 ...

Страница 123: ...AS 50 60 70 80 90 100 110 120 130 140 150 160 KCAS 56 62 68 76 85 95 105 115 125 134 144 154 FLAPS 10 KIAS 40 50 60 70 80 90 100 11 0 KCAS 51 55 60 68 77 86 96 105 FLAPS 30 KIAS 40 50 60 70 80 85 KCAS 49 54 61 69 78 83 NOTE Windows closed ventilators closed cabin heater cabin air and defroster on maximum Figure 5 1 Airspeed Calibration Sheet 2 of 2 5 10 July 8 98 ...

Страница 124: ...L 172S 120 100 80 I ill 60 I Z llJ 0 I 40 en llJ llJ 0 j 20 llJ 0 0 20 40 40 July 8 98 SECTION 5 PERFORMANCE TEMPERATURE CONVERSION CHART 20 0 20 40 60 DEGREES CELSIUS Figure 5 2 Temperature Conversion Chart 5 11 ...

Страница 125: ...53 52 57 57 63 68 75 10 42 50 45 54 50 59 59 71 30 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 KCAS UP 48 53 52 57 57 63 68 75 10 43 51 46 55 51 61 61 72 30 40 48 43 52 48 57 57 68 NOTES 1 Altitude loss during a stall recovery may be as much as 230 feet 2 KIAS values are approximate Figure 5 3 Stall Speeds 5 12 Jul...

Страница 126: ...ted crosswind velocity is 15 knots not a limitation 35 30 c 25 z cn 20 1 OW Zl 15 I 10 Z W Z 5 0 a E 0 0 C 5 zc z 10 15 0 5 10 15 20 25 30 35 CROSSWIND COMPONENT KNOTS NOTE Maximum demonstrated crosswind component is 15 knots not a limitation I 0585C1003 Figure 5 4 Crosswind Components 5 13 ...

Страница 127: ...95 2035 1310 2240 1440 2480 1585 2755 1745 3075 1920 3440 2120 3880 1 Short field technique as specified in Section 4 30 C 40 C Grnd Total Grnd Total Roll FtTo Roll FtTo Ft Clear Ft Clear 50 Ft 50 Ft Obst Obst 1070 1810 1150 1945 1170 1990 1260 2135 1285 2190 1380 2355 1410 2420 1515 2605 1550 2685 1660 2880 1705 2975 1825 3205 1875 3320 2010 3585 2065 3730 2215 4045 2280 4225 2450 4615 2 Prior to...

Страница 128: ... 1760 1130 1930 1240 2130 1360 2355 1500 2610 1650 2900 1815 3240 1 Short field technique as specified in Section 4 30 C 40 C Grnd Total Grnd Total Roll FtTo Roll FtTo Ft Clear Ft Clear 50 Ft 50 Ft Obst Obst 925 1570 995 1685 1010 1720 1085 1845 1110 1890 1190 2030 1215 2080 1305 2230 1335 2295 1430 2455 1465 2530 1570 2715 1610 2805 1725 3015 1770 3125 1900 3370 1950 3500 2095 3790 2 Prior to tak...

Страница 129: ...5 1435 925 1570 1010 1725 1110 1900 1220 2090 1340 2305 1475 2555 1 Short field technique as specified in Section 4 30 C 40 C Grnd Total Grnd Total Roll FtTo Roll FtTo Ft Clear Ft Clear 50 Ft 50 Ft Obst Obst 760 1290 815 1380 830 1410 890 1505 905 1540 975 1650 995 1685 1065 1805 1090 1855 1165 1975 1195 2035 1275 2175 1310 2240 1400 2395 1435 2475 1540 2650 1580 2745 1695 2950 2 Prior to takeoff ...

Страница 130: ... S L 2000 4000 6000 8000 10 000 12 000 NOTE CLIMB SPEED KIAS 74 73 73 73 72 72 72 RATE OF CLIMB FPM 20 C O C 20 C 855 785 710 760 695 625 685 620 555 575 515 450 465 405 345 360 300 240 255 195 135 1 Mixture leaned above 3 000 feet for maximum RPM Figure 5 6 Maximum Rate of Climb July 8 98 40 C 645 560 495 390 285 180 5 17 ...

Страница 131: ...1 2 6 4000 73 600 6 1 5 8 5000 73 550 8 1 9 10 6000 73 505 10 2 2 13 7000 73 455 12 2 6 16 8000 72 410 14 3 0 19 9000 72 360 17 3 4 22 10 000 72 315 20 3 9 27 11 000 72 265 24 4 4 32 12 000 72 220 28 5 0 38 NOTES 1 Add 1 4 gallons of fuel for engine start taxi and takeoff allowance 5 18 2 Mixture leaned above 3 000 feet for maximum RPM 3 Increase time fuel and distance by 10 for each 10 C above st...

Страница 132: ... 7 7 2200 53 99 7 7 50 97 7 3 47 95 6 9 2100 47 92 6 9 44 90 6 6 42 89 6 3 4000 2600 83 120 11 1 77 120 10 4 72 119 9 8 2550 79 118 10 6 73 117 9 9 68 117 9 4 2500 74 115 10 1 69 115 9 5 64 114 8 9 2400 65 110 9 1 61 109 8 5 57 107 8 1 2300 58 104 8 2 54 102 7 7 51 101 7 3 2200 51 98 7 4 48 96 7 0 45 94 6 7 2100 45 91 6 6 42 89 6 4 40 87 6 1 6000 2650 83 122 11 1 77 122 10 4 72 121 9 8 2600 78 120...

Страница 133: ...61 112 8 6 57 111 8 1 2400 58 108 8 2 54 106 7 8 51 104 7 4 2300 52 101 7 5 48 99 7 1 46 97 6 8 2200 46 94 6 8 43 92 6 5 41 90 6 2 10 000 2700 78 124 10 5 72 123 9 8 67 122 9 3 2650 73 122 10 0 68 120 9 4 63 119 8 9 2600 69 119 9 5 64 117 9 0 60 115 8 5 2500 62 113 8 7 57 111 8 2 54 109 7 8 2400 55 106 7 9 51 104 7 5 49 102 7 1 2300 49 100 7 2 46 97 6 8 44 95 6 5 12 000 2650 69 121 9 5 64 119 8 9 ...

Страница 134: ...At All Altitudes Standard Temperature Zero Wind 12 000 10 000 I W W IL 8 000 6 000 w C J I 4 000 i H H f tH H t 2 000 500 550 600 RANGE NAUTICAL MILES NOTES SECTION 5 PERFORMANCE 650 700 1 This chart allows for the fuel used for engine start taxi takeoff and climb and the distance during climb Figure 5 9 Range Profile July 8 98 5 21 ...

Страница 135: ...ded Lean Mixture for Cruise At All Altitudes Standard Temperature 12000 10000 8000 I W w 6000 u w C I 4000 ct 2000 SL NOTE 4 5 6 7 ENDURANCE HOURS CESSNA MODEL 172S 8 1 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 July 8 98 ...

Страница 136: ...5 625 1420 610 1385 630 1420 650 1455 630 1425 655 1460 675 1495 655 1460 675 1495 700 1535 680 1500 705 1535 725 1575 705 1540 730 1580 755 1620 730 1585 760 1625 785 1665 760 1630 790 1670 815 1715 1 Short field technique as specified in Section 4 40 C Grnd Total Roll FtTo Ft Clear 50 Ft Obst 625 1415 650 1450 670 1490 695 1530 725 1570 750 1615 780 1660 810 1705 840 1755 2 Decrease distances 10...

Страница 137: ......

Страница 138: ... BALANCE EQUIPMENT LIST SECTION 6 WEIGHT BALANCE EQUIPMENT LIST TABLE OF CONTENTS Page Introduction 6 3 Airplane Weighing Procedures 6 3 Weight And Balance 6 6 Baggage Tie Down 6 8 Comprehensive Equipment List 6 1 7 IRevision 4 6 1 6 2 ...

Страница 139: ......

Страница 140: ...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 Inflate tires to recommended operating pressures I b Defuel airplane Refer to the Maintenance Manual c Service engine oil as required to obtain a normal full indication 8 quarts on dipstick d Move sliding seats to the...

Страница 141: ...G FORM REFERENCE DATUM FIREWALL FRONT FACE LOWER PORTION NOTE STA 0 0 IT IS THE RESPONSIBILITY MAC 25 90 _ 5_8_ 8 0 OF THE PILOT TO ENSURE THAT THE AIRPLANE IS LOADED PROPERLY 100 r r r r 100 50 o 50 100 150 200 250 FUSELAGE STATION FS INCHES 0585C1010 Figure 6 1 Airplane Weighing Form Sheet 1 of 2 6 4 July 8 98 ...

Страница 142: ...LOCATING CG WITH AIRPLANE WEIGHED ON LANDING GEAR 0 5880 LEVELING PROVISIONS LONGITUDINAL LEFT SIDE OF TAILCONE AT FS 108 00 142 00 AIRPLANE AS WEIGHED TABLE POSITION SCALE READING SCALE DRIFT TARE NET WEIGHT LEFT SIDE RIGHT SIDE NOSE AIRPLANE TOTAL AS WEIGHED BASIC EMPTY WEIGHT AND CENTER OF GRAVITY TABLE WEIGHT CGARM MOMENT ITEM POUNDS INCHES INCH POUNDS 11000 AIRPLANE CALCULATED OR AS WEIGHED I...

Страница 143: ... and C G can be determined 6 Basic Empty Weight may be determined by completing Figure 6 1 WEIGHT AND BALANCE The following information will enable you to operate your Cessna within the prescribed weight and center of gravity limitations To Icalculate weight and balance use the Sample Loading Problem Loading Graph and Center of Gravity Moment Envelope as follows Take the basic empty weight and mom...

Страница 144: ...UCTURE OR EQUIPMENT AFFECTING WEIGHT AND BALANCE AIRPLANE MODEL SERIAL NO JPAGE NUMBER WEIGHT CHANGE RUNNING ITEM NO BASIC EMPTY DESCRIPTION ADDED REMOVED WEIGHT DATE OF ARTICLE OR MODIFICATION WT ARM MOMENT WT ARM MOMEN WT MOMENT IN OUT LB IN 11000 LB IN 11000 LB 11000 AS DELIVERED S O Om oc mC rZ C m G5 I I S o OJ r Z o m m o c u s cn mm zO 1 1 CO cnZ 1m ...

Страница 145: ... having tie down straps is provided as standard equipment to secure baggage on the cabin floor aft of the rear seat baggage area 1 and in the aft baggage area baggage area 2 Six eyebolts serve as attaching points for the net Two eyebolts for the forward tie down straps are mounted on the cabin floor near each sidewall just forward of the baggage door approximately at station 90 two eyebolts are in...

Страница 146: ...easured to the center of the areas shown NOTES 1 The usable fuel C G arm for integral tanks is located at station 48 0 July 8 98 2 The rear cabin wall approximate station 108 or aft baggage wall approximate station 142 can be used as convenient interior reference points for determining the location of baggage area fuselage stations STATION C G ARM 37 34 to 46 73 95 108 123 REAR PASS BAGGAGE AREA 1...

Страница 147: ...ASUREMENTS FIREWALL TIE DOWN RINGS 6 _ J__ __ _ 6 10 34 AFT BAGGAGE AREA DOOR OPENING DIMENSIONS WIDTH WIDTH HEIGHT HEIGHT TOP BOTTOM FRONT REAR CABIN DOORS 321 2 37 401 2 39 BAGGAGE DOOR 151 4 151 4 22 21 0585X1023 Figure 6 4 Internal Cabin Dimensions Sheet 1 of 2 May 30 00 ...

Страница 148: ...HT BALANCE EQUIPMENT LIST CABIN WIDTH MEASUREMENTS INSTRUMENT PANEL REAR DOORPOST BULKHEAD I I I I o 10 20 CABIN STATIONS C G ARMS LWR WINDOW LINE CABIN FLOOR 0585X1023 Figure 6 4 Internal Cabin Dimensions Sheet 2 of 2 July 8 98 6 11 ...

Страница 149: ...Front Passenger Station 34 to 46 340 12 6 4 Rear Passengers 340 24 8 5 Baggage Area 1 Station 82 to 108 120 Lbs Max I 56 4 6 6 Baggage Area 2 Station 108 to 142 50 Lbs Max 7 RAMP WEIGHT AND MOMENT add columns 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 Center of Grav...

Страница 150: ...E AIRPLANE Weight Moment Lb ins lbs 1000 Weight Moment Lb ins lbs 1000 NOTE When several loading configurations are representative of your operations it may be useful to fill out one or more of the above columns so specific loadings are available at a glance Figure 6 5 Sample Loading Problem Sheet 2 of 2 July 8 98 6 13 ...

Страница 151: ...I jj 250 J S jj 100 S 200 75 150 100 50 50 25 o 0 o 5 10 15 20 25 30 35 LOAD MOMENT 1000 POUNDS INCHES NOTE LINE REPRESENTING ADJUSTABLE SEATS SHOWS 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 0585C1006 Figure 6 6 Loading Graph 6 14 July 8 98 ...

Страница 152: ... w z 2000 a Cl w 1900 g July 8 98 LOADED AIRPLANE MOMENT l000 KILOGRAM MILLIMETERS 700 800 900 1000 1100 1200 1300 1400 en 950CJ g g 900CJ ill 3 w z 5 850 a a Cl w Cl 800 5 J 60 70 80 90 100 110 120 130 LOADED AIRPLANE MOMENT l000 POUND INCHES 0585C1007 Figure 6 7 Center of Gravity Moment Envelope 6 15 ...

Страница 153: ...00 jj 5 UJ 2000 a 0 fil 1900 Cl 5 1800 1700 1600 1500 6 16 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 AIRPLANE C G LOCATION INCHES AFT OF DATUM STA 0 0 Figure 6 8 Center of Gravity Limits 1100 1050 1000 j 2 950 C l 0 g I I 900 C l jj 5 UJ z s 850 a 0 Cl UJ Cl 800 0 750 700 650 0585C1008 May 30 00 ...

Страница 154: ...uipment for FAA certification 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 which corresponds to the i...

Страница 155: ... REPLACES STANDARD 2 AXIS AUTOPILOT CONTROLLER REQUIRES GPS ALT ALERT BE DISABLED WT CHG 23 COMMUNICATIONS 23 01 S STATIC DISCHARGE WICKS SET OF 10 23 02 S NAV COM 1 INSTALLATION NOG S KX 155A BENDIX KING NAV COM KI208 INDICATOR VHF COM ANTENNA COM ANTENNA CABLE OMNI NAV ANTENNA OMNI ANTENNA CABLE HARDWARE CABLE ASSEMBLY REF DRAWING 0505087 23 0504051 870 003 119916 0513575 28 9954100 1 3900003 39...

Страница 156: ... 12 75 A H MANIFOLD C614002 0101 23 2 5 0 TYPE 24 03 R POWER JUNCTION BOX PRECISION MC01 2A 6 4 2 5 AIRMOTIVE CORP MC01 2A INCLUDES ALTERNATOR CONTROL UNIT 1270101 1 0 2 3 0 AC21 01 MASTER CONTACTOR PIN X61 0007 1270101 1 0 7 2 4 STARTER CONTACTOR PIN X61 0012 3930400 1 0 7 2 4 AMMETER TRANSDUCER PIN CS3100 3930417 2 0 1 3 0 25 EQUIPMENT FURNISHINGS 25 01 R PILOT SEAT CLOTH COVER 0514211 1 34 3 41...

Страница 157: ...L COPILOT RUDDER BRAKE PEDAL INSTL 27 02 S PILOTS CONTROL WHEEL WITH MAP LIGHT MIC SWITCH AND JACK 28 FUEL 28 01 R FUEL QUANTITY INDICATORS I28 02 R AUXILIARY FUEL PUMP UNDER I FLOORBOARD 31 INDICATING RECORDING SYSTEM 31 01 S DIGITAL ELECTRONIC CLOCK OAT 31 02 S HOUR RECORDER HOBBS TIME 31 03 R ANNUNCIATOR 31 04 R PNEUMATIC STALL WARNING SYSTEM REF DRAWING 2000031 11 12 2000031 11 12 0514230 1 05...

Страница 158: ...E WITH STANDARD TIRES NET CHANGE 33 LIGHTS 33 01 8 MAP LIGHT IN CONTROL WHEEL PART OF 0560059 0 2 21 5 I 27 02 S 33 02 8 UNDER WING COURTESY LIGHTS SET OF 0521101 8 0 5 61 0 2 33 03 S NAVIGATION LIGHT DETECTORS 1221201 3 4 0 0 40 8 33 04 S FLASHING BEACON 0506003 6 1 4 204 7 33 05 8 WING TIP STROBE LIGHT 0501027 6 3 4 43 3 33 06 8 LANDING AND TAXI LIGHT INSTL IN WING 0523029 7 2 4 28 7 34 NAVIGATI...

Страница 159: ...TEM AIRBORNE VACUUM PUMP AIRBORNE VACUUM PUMP COOLING SHROUD COOLING SHROUD FILTER INSTALLATION 1 COMBINATION VACUUM INDICATOR AMMETER VACUUM RELIEF VALVE MANIFOLD 37 02 R COMBINATION VACUUM GAGE AMMETER CESSNA MODEL 172S REF DRAWING WT ARM LBS INS 3900016 3 9 11 8 S3326 1 2 3 14 0 3900016 1 5 10 0 S3291 1 1 0 15 8 S3327 1 0 8 15 7 3930408 1 10 4 26 9 066 01072 0014 3 2 11 4 066 03063 0000 0 7 15 ...

Страница 160: ... 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 I 61 03 0 POLISHED SPINNER MILLENNIUM INSTL 0550371 1 0 0 41 0 NET CHANGE 71 POWERPLANT 71 01 R AIR INTAKE FILTER DONALDSON P198281 0 3 27 5 I 71 02 S WINTERIZATION KIT INSTALLATION 0501128 3 0 8 20 3 STOWED INSTALLED ARM SHOWN BREATHER TUBE INSULATION 0552011 0 4 13 8 C...

Страница 161: ...MIUM TIRE INSTL 61 03 0 POLISHED SPINNER INSTL 72 02 0 ENGINE INSTL POLISHED FASTENER INSTL MILLENNIUM CONTROL WHEEL PAD 98 AVIONICS PACKAGES 9S 01 S STANDARD AVIONICS PACKAGE 22 01 S WING LEVELER PROVISIONS 23 05 S BASIC AVIONICS INSTL 23 04 S MARKER BEACON INTERCOM INSTL 23 02 S NAV COM 1 INSTALLATION 34 11 S MODE C TRANSPONDER INSTL CESSNA MODEL 172S REF DRAWING WT ARM LBS INS S3277 4 0 6 7 S S...

Страница 162: ...7 2 43 6 98 04 A NAV II WITH HSI AVIONICS PKG NET 3900016 43 8 47 0 CHANGE OVER STANDARD AVIONICS PKG 98 02 A NAV I AVN PKG 3900004 1 21 3 21 5 22 02 A SINGLE AXIS AUTOPILOT 3900005 1 7 2 43 6 34 12 0 HSI GYRO INSTL 3900016 1 15 3 84 1 98 05 A NAV III WITH HSI AVIONICS PKG NET 3900018 56 3 67 5 CHANGE OVER STANDARD AVIONICS PKG 98 02 A NAV I AVN PKG 3900004 1 21 3 21 5 22 03 A 2 AXIS AUTOPILOT 390...

Страница 163: ......

Страница 164: ...6 Trim System 7 6 Instrument Panel 7 9 Pilot Side Panel Layout 7 9 Center Panel Layout 7 9 Copilot Side Panel Layout 7 12 Center Pedestal Layout 7 12 Ground Control 7 12 Wing Flap System 7 13 Landing Gear System 7 14 Baggage Compartment 7 14 Seats 7 14 Integrated Seat Belt Shoulder Harness 7 15 Entrance Doors And Cabin Windows 7 1 71 Control Locks 7 18 May 30 00 7 1 ...

Страница 165: ...ystem Propeller Fuel System Fuel Distribution Fuel Indicating Filel Venting Reduced Tank Capacity Fuel Selector Valve Fuel Drain Valves Brake System Electrical System Annunciator Panel Master Switch Page 7 19 7 19 7 19 7 21 7 21 7 22 7 22 7 23 7 23 7 23 7 23 7 24 7 25 7 26 7 26 7 26 7 28 7 29 7 29 7 32 7 33 Avionics Master Switch 7 34 Ammeter 7 34 Low Voltage Annunciation 7 35 Circuit Breakers And...

Страница 166: ...um System And Instruments Attitude Indicator Directional Indicator Vacuum Gauge Low Vacuum Annunciation Clock O A T Indicator Stall Warning System Standard Avionics Avionics Support Equipment Avionics Cooling Fan Microphone And Headset Installations Static Dischargers Cabin Features Emergency Locator Transmitter ELT Cabin Fire Extinguisher Page 7 37 7 37 7 37 7 39 7 41 7 42 7 42 7 43 7 43 7 43 7 4...

Страница 167: ......

Страница 168: ...with attach 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 externally 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 a...

Страница 169: ...n 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 and lower V t...

Страница 170: ...CESSNA MODEL 172S SECTION 7 AIRPLANE SYSTEMS DESCRIPTION 0585X1017 Figure 7 1 Flight Control and Trim Systems Sheet 1 of 2 July 8 98 7 7 ...

Страница 171: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTION CESSNA MODEL 172S 0585X1018 Figure 7 1 Flight Control and Trim Systems Sheet 2 of 2 7 8 July 8 98 ...

Страница 172: ...e the altimeter and provides caution and warning messages for fuel quantity oil pressure low vacuum and low voltage situations To the right of the flight instruments is a sub panel which contains engine tachometer and various navigational heading instruments To the left of the flight instruments is a sub panel which contains a left right fuel quantity indicator an Oill temperature oil pressure ind...

Страница 173: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTION 5 7 9 11 13 35 34 42 CESSNA MODEL 172S 18 19 20 21 22 23 0585C1040 __ Figure 7 2 Instrument Panel Sheet 1 of 2 7 10 Revision 4 ...

Страница 174: ... Control 10 Tachometer 32 Glareshield and Pedestal Dimming Control 11 Vertical Speed Indicator 33 Fuel Shutoff Valve Control 12 Altimeter 34 Fuel Selector 13 Annunciator Panel 35 Elevator Trim Control and Position Indicator 14 ADF Bearing Indicator 36 Avionics Master Switch 15 Course Deviation and Glide 37 Circuit Breakers and Slope Indicators Switch Breakers 16 Audio Control Panel 38 Master Switc...

Страница 175: ...ximately 10 each side of center By applying either left or right brake the degree of turn may be increased up to 30 each side of center Moving the airplane by hand is most easily accomplished by attaching a tow bar to the nose gear strut If a 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...

Страница 176: ...is moved up or down in a slotted panel that provides mechanical stops at the 10 20 and 30 positions To change I 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...

Страница 177: ...rings provided 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 se...

Страница 178: ...restraint for the user In the front seats the inertia reels are located on the centerline of the upper cabin In the rear seats the inertia reels are located outboard of each passenger in the upper cabin To use the integrated seat belt shoulder harness grasp the link with one hand and in a single motion extend the assembly and insert into the buckle Positive locking has occurred when aI distinctive...

Страница 179: ... SEAT BACK ANGLE BUTTON FORE AND AFT ADJUSTMENT LEVER PRESSTO RELEASE AVAILABLE MANUAL PUSH BUTTON ADJUSTMENT PUSH BUTTON RELEASE CESSNA MODEL 172S BUCKLE NON ADJUSTABLE LIFT TO RELEASE LATCH 0514T1004 Figure 7 4 Crew Seats Seat Belts and Shoulder Harnesses 7 16 May 30 00 ...

Страница 180: ...doors incorporate a recessed exterior door handle a conventional interior door handle a key operated door lock left door only a door stop mechanism and openable windows in both the left and right doors NOTE The door latch design on this model requires that the outside door handle on the pilot and front passenger doors be extended out whenever the doors are open When closing the door do not attempt...

Страница 181: ... the window outward and hold it there If required either window may be opened at any speed up to 163 KIAS The rear side windows and rear windows are of the fixed type and cannot be opened CONTROL LOCKS A control lock is provided to lock the aileron and elevator control surfaces to prevent damage to these systems by wind buffeting while the airplane is parked The lock consists of a shaped steel rod...

Страница 182: ...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 a lock button in the end of the knob The rich position is full forward and full aft is the idle cutoff position For small adjustments the control may be moved forward by rotati...

Страница 183: ...rom a resistance type probe located in the engine accessory case As oil temperature changes the probe resistance changes This resistance is translated into oil temperature readings on the cockpit indicator The engine driven mechanical tachometer is located on the instrument panel to the right of the pilot s control wheel The instrument is calibrated in increments of 100 RPM and indicates both engi...

Страница 184: ...ight quarts Oil is drawn from the sump through an oil suction strainer screen into the engine driven oil pump From the pump oil is routed to a bypass valve If the oil is cold the bypass valve allows the oil to bypass the oil cooler and go directly from the pump to the full flow oil filter If the oil is hot the bypass valve routes the oil out of the accessory housing and into a flexible hose leadin...

Страница 185: ... spring loaded START position with the master switch in the ON position Ithe starter contactor is closed and the starter now energized will crank the engine When the switch is released it will automatically return to the BOTH position AIR INDUCTION SYSTEM The engine air induction system receives ram air through an intake on the lower front portion of the engine cowling The intake is covered by an ...

Страница 186: ...cowl flap cooling system control is required PROPELLER The airplane is equipped with a two bladed fixed pitch one piece forged aluminum alloy propeller which is anodized to retard corrosion The propeller is 76 inches in diameter FUEL SYSTEM The airplane fuel system see Figure 7 6 consists of two vented integral fuel tanks one tank in each wing a three position selector valve auxiliary fuel pump fu...

Страница 187: ...to the fuel air control unit where it is metered and directed to a fuel distribution valve manifold which distributes it to each cylinder Fuel flow into each cylinder is continuous and flow rate is determined by the amount of air passing through the fuel air control unit t Starting at serial number 172S9491 and on and airplanes incorporating MK172 28 01 a fuel return system was added to promote sm...

Страница 188: ...ately 10 seconds and then remain steady amber The annunciator cannot be turned off by the pilot If the left tank is low the message will read L LOW FUEL If the right tank is low the message will read LOW FUEL R If both tanks are low the message will read L LOW FUEL R In addition to low fuel annunciation the warning circuitry is designed to report failures with each transmitter caused by shorts ope...

Страница 189: ...usable in each tank FUEL SELECTOR VALVE The fuel selector valve should be in the BOTH position for takeoff climb landing and maneuvers that involve prolonged slips or skids of more than 30 seconds Operation from either LEFT or RIGHT tank is reserved for cruising flight 7 26 NOTE When the fuel selector valve handle is in the BOTH position in cruising flight unequal fuel flow from each tank may occu...

Страница 190: ...IPTION FUEL QUANTITY INDICATORS FUEL REi ERVOIR TANK VALVE KNOB FUEL SHUTOFF o lilHi lllllllll I I IRevision 4 LEGEND FUEL SUPPLY VENT MECHANICAL LINKAGE ELECTRICAL CONNECTION Figure 7 6 Fuel System Schematic Sheet 1 of 2 172S8001 thru 172S9490 0585C1013 I 7 27 7 27A ...

Страница 191: ......

Страница 192: ...L QUANTITY INDICATORS FUELSHUTOF VALVE KNOB u Revision 5 FUEL STRAINER DRAIN VALVE LEGEND FUEL SUPPLY VENT MECHANICAL LINKAGE ELECTRICAL CONNECTION Figure 7 6 Fuel System Schematic Sheet 2 of 2 172S9491 and On And airplanes incorporating MK172 28 01 RIGHT FUEL TANK FUEL 0585T10f3A I 7 27B ...

Страница 193: ... drain valves to provide a means for the examination of fuel in the system for contamination and grade The system should be examined before each flight and after each refueling by using the sampler cup provided to drain fuel from each wing tank sump the fuel reservoir sump the fuel selector drain and the fuel strainer sump If any evidence of fuel contamination is found it must be eliminated in acc...

Страница 194: ...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 weak or fails use the other brake sparingly while using opposite rudder...

Страница 195: ...NPUT CESSNA MODEL 172S B A IIGNITION ISWITCH I I I TO INST CIRCUIT BREAKER I MAGNETOS I L t BAT ALT BATTERY 0585C2001 I EXT PWR L RELAY 7m POWER DISTRIBUTION MODULE EXTERNAL POWER MASTER SWITCH TO ALT FLD CIRCUIT BREAKER Figure 7 7 Electrical Schematic Serials 172S8001 thru 172S8703 Sheet 1 of 2 7 30 Dec 30 00 ...

Страница 196: ... _TO VARIOUS J15 WARN ANNUNCIATORS o I w 0 _TO GLARESHIELD lli T 1 f I NT Sl LIGHTS is 0 TO MASTER _______ pr ALT SWITCH FLD O AVN BUS 2 O TOTURN TURN COORDINATOR II COORD O TO AVIONICS FAN AVN FAN 0 TO GPS 2 3 4 5 C GPS TO NAV AND m CONTROL WHEEL J NAV MAP LIGHTS a G TO STROBE W TROBELIGHTS TO TAXI LIGHTS TAXI 0 TO NAV COMl NAV HEADSET PWR COM1 SPEAKER PWR 1 z MKR BCN RCVR 1 0 TO AUTOPILOT 3 AUTO...

Страница 197: ...OUND SENSE I POWER IN I ALT INPUT I I I I I BUS 2 FUSE I OR CIB I BUS 1 I FUSE ORC BI 1 B A 1 IGNITION 1 SWITCH 1 1 1 TO INST CIRCUIT BREAKER 1 MAGNETOS L fl ___ _ BAT ALT MASTER SWITCH TO ALT FLD EXTERNAL CIRCUIT POWER BREAKER Figure 7 7A Electrical Schematic Serials 172S8704 and On Sheet 1 of 2 7 30B Dec 30 00 ...

Страница 198: ...AUDIOPANEL 1 C COM 1 AVNBUS1 AVIONICS MASTER U O e TO VARIOUS SWITCH Jii5 WARN ANNUNCIATORS c I w Zw WLL OOOO OOOO wo 5 O e TO MASTER ALT SWITCH FLO B U S 1 O AVN BUS 2 B U S 2 O TO TURN TURN COORDINATOR COORD O TO NAV COMM 2 NAV AUDIOPANEL 2 COM2 TO NAVAND C e CONTROL WHEEL J NAV MAP LIGHTS C 0 TO INSTRUMENT b T LIGHTS TO STROBE ill STROBE LIGHTS TO TAXI LIGHTS TAXI A1TOT LEGEND IJ2 r 1 BASE ii5 ...

Страница 199: ...pressure switch the vacuum transducers and the alternator control unit ACU Individual LED bulbs illuminate each message and may be replaced through the rear of the annunciator Illumination intensity can be controlled by placing the toggle switch in either the DIM or BRT positions earlier serial number airplanes or the DAY or NIGHT positions later serial number airplanes I The annunciator panel can...

Страница 200: ...AGING THE AVIONICS EQUIPMENT Normally both sides of the master switch should be used simultaneously however the BAT side of the switch could be turned on separately to check equipment while on the ground To check or use avionics equipment or radios while on the ground the avionics power switch must also be turned on The ALT side of the switch when placed in the OFF position removes the alternator ...

Страница 201: ...nd Avionics Bus 2 With the Avionics Master rocker in the OFF position no electrical power is provided to the avionics even when the Master switch or the individual avionics component equipment switches are in their ON positions The Avionics Master switch both sides if two section should be placed in the OFF position before switching the Master switch ON or OFF starting the engine or applying an ex...

Страница 202: ...s below normal The alternator control unit may be reset by resetting the circuit breaker If the 10 voltage warning annunciator extinguishes normal alternato charging has resumed however if the annunciator illuminate again a malfunction has occurred and the flight should b terminated as soon as practicable NOTE Illumination of the low voltage annunciator and ammeter I discharge indications may occu...

Страница 203: ...circuit which will close the battery contactor when external power is applied through the ground service plug receptacle with the master switch turned on This feature is intended as a servicing aid when battery power is too low to close the contactor and should not be used to avoid performing proper maintenance procedures on a low battery NOTE If no avionics equipment is to be used or serviced the...

Страница 204: ...te these lights place switch in the UP position To deactivate light place in the DOWN position NOTE The strobes and flashing beacon should not be used when flying through clouds or overcast the flashing light reflected from water droplets or particles in the atmosphere particularly at night can produce vertigo and loss of orientation INTERIOR LIGHTING Interior lighting is controlled by a combinati...

Страница 205: ...omplished by use of a rheostat and light assembly located underneath the pilot control wheel The light provides downward illumination from the bottom of the control wheel to the pilot s lap area To operate the light first turn on the NAV light switch then adjust the map light intensity with the knurled rheostat knob Rotating the dimmer clockwise increases light intensity and rotating the dimmer co...

Страница 206: ...IN HT knob is pushed full in Front cabin heat and ventilating air is supplied by outlet holes spaced across a cabin manifold just forward of the pilot s and copilot s feet Rear cabin heat and air is supplied by two ducts from the manifold one extending down each side of the cabin to an outlet just aft of the rudder pedals at floor level Windshield defrost air is also supplied by two ducts leading ...

Страница 207: ...T CONTROL FORWARD CABIN LOWER VENTILATIN HEATER VALVE CESSNA MODEL 172S AIR OUTLET db w FORWARD CABIN LOWER VENTILATING AIR OUTLET CABIN FLOO AIR OUTLET REAR CABIN VENTILATING AIR OUTLETS 2 0585C1015 Figure 7 8 Cabin Heating Ventilating and Defrosting System 7 40 July 8 98 ...

Страница 208: ...iring The switch breaker is located on the lower left side of the instrument panel When the pitot heat switch is turned on the element in the pitot tube is heated electrically to maintain proper operation in possible icing conditions A static pressure alternate source valve is installed below the throttle and can be used if the external static source is malfunctioning This valve supplies static pr...

Страница 209: ...nots green arc 48 to 129 knots yellow arc 129 to 163 knots and a red line 163 knots To find true airspeed first determine pressure altitude and outside air temperature Using this data rotate the lower left knob until pressure altitude aligns with outside air temperature in the twelve o clock window True airspeed corrected for pressure and temperature can now be read in the lower window VERTICAL SP...

Страница 210: ... pointer at the top of the indicator relative to the bank scale which has index marks at 10 20 30 60 and 90 either side of the center mark Pitch and roll attitudes are presented by a miniature airplane superimposed over a symbolic horizon area divided into two sections by a white horizon bar The upper blue sky area and the lower ground area have pitch reference lines useful for pitch attitude cont...

Страница 211: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTION 7 44 VAC AMP Gauge Figure 7 9 Vacuum System CESSNA MODEL 172S LOW VACUUM SWITCHES CONNECTED TO ANNUNCIATOR PANEL MANIFOLD CHECK VALVE 0585C1014 July 8 98 ...

Страница 212: ...te for normal system operation LOW VACUUM ANNUNCIATION Each engine driven vacuum pump is plumbed to a common manifold located forward of the firewall From the tee a single line runs into the cabin to operate the various vacuum system instruments This tee contains check valves to prevent back flow into a pump if it fails Transducers are located just upstream of the tee and measure vacuum output of ...

Страница 213: ...plumbing As the airplane approaches a stall the low pressure on the upper surface of the wings moves forward around the leading edge of the wings This low pressure creates a differential pressure in the stall warning system which draws air through the warning horn resulting in an audible warning at 5 to 10 knots above stall in all flight conditions STANDARD AVIONICS Standard avionics for the Model...

Страница 214: ...ets at each pilot and passenger station The hand held microphone contains an integral push to talk switch This microphone is plugged into the center pedestal and is accessible to both the pilot and front passenger Depressing the push to talk switch allows audio transmission on the Com radios The overhead speaker is located in the center overhead console Volume and output for this speaker is contro...

Страница 215: ...ous points throughout the airframe to reduce interference from precipitation static Under some severe static conditions loss of radio signals is possible even with static dischargers installed Whenever possible avoid known severe precipitation areas to prevent loss of dependable radio signals If avoidance is impractical minimize airspeed and anticipate temporary loss of radio signals while in thes...

Страница 216: ...BIN FIRE EXTINGUISHER A portable Halon 1211 Bromochlorodifluoromethane fire extinguisher is standard and is installed on the floorboard near the pilot s seat where it would be accessible in case of fire The extinguisher has an Underwriters Laboratories classification of 5 B C If installed the extinguisher should be checked prior to each flight to ensure that its bottle pressure as indicated by the...

Страница 217: ...L DECOMPOSITION 3 Antic pate approximately eight seconds of discharge duration Fire extinguishers should be recharged by a qualified fire extinguisher agency after each use Such agencies are listed under Fire Extinguisher in the telephone directory After recharging secure the extinguisher to its mounting bracket do not allow it to lie loose on shelves or seats 7 50 July 8 98 ...

Страница 218: ...wners 8 5 Publications 8 5 Airplane File 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 12 Servicing 8 13 Oil 8 14 Oil Specification 8 14 Reco...

Страница 219: ...Sump 8 15 Oil and Oil Filter Change 8 15 Fuel 8 16 Approved Fuel Grades and Colors 8 16 Fuel Capacity 8 16 Fuel Additives 8 16 Fuel Contamination 8 20 Landing Gear 8 21 Cleaning And Care 8 21 Windshield And Windows 8 21 Painted Surfaces 8 22 Propeller Care 8 23 Engine Care 8 23 Interior Care 8 24 8 2 May 30 00 ...

Страница 220: ...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 aircraft by serial number should be accomplished and the airplane should receive repetitive ...

Страница 221: ...l number airplanes The Finish and Trim Plate located on the lower part of the left forward doorpost contains a code describing the exterior paint configuration for the airplane The code may be used in conjunction with an applicable Illustrated Parts Catalog if finish and trim information is needed CESSNA OWNER ADVISORIES Cessna Owner Advisories are sent to Cessna Aircraft FAA Registered owners of ...

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

Страница 223: ... Manual which is lost or destroyed may be replaced by contacting your local 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 miscellane...

Страница 224: ...ents Cessna recommends that these items plus the Pilot s Checklists Customer Care Program Handbook and Customer Care Card be carried in the airplane at 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 twelve calendar months In addition to the required annu...

Страница 225: ...ed 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 oc...

Страница 226: ... program you choose to establish for your airplane While these important inspections will be performed for you by any Cessna Service Station in most cases you will prefer to have the Cessna Service Station from whom you purchased the airplane accomplish this work PILOT CONDUCTED PREVENTIVE MAINTENANCE A certified pilot who owns or operates an airplane not used as an air carrier is authorized by FA...

Страница 227: ...el utilizing only FAA Approved components and FAA Approved data such as Cessna Service Bulletins GROUND HANDLING TOWING The airplane is most easily and safely 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 l exceed the nose gear turning angle of 30 either side of center or damage to the nose lan...

Страница 228: ...rol 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 pitottube 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 for spec...

Страница 229: ...s of suitable stands or supports under weight supporting bulkheads near the nose of the airplane LEVELING Longitudinal leveling of the airplane is accomplished by placing a level on leveling screws located on the left side of the tailcone Deflate the nose tire and or lower or raise the nose strut to properly center the bubble in the level Corresponding points on both upper door sills may be used t...

Страница 230: ...ezing in cold weather If the airplane is to be stored temporarily or indefinitely refer to the Maintenance Manual for proper storage procedures SERVICING In addition to the Preflight Inspection covered in Section 4 of this handbook complete servicing inspection and test requirements for your airplane are detailed in the Maintenance Manual The Maintenance Manual outlines all items which require att...

Страница 231: ...fill the engine and continue to use until a total of 50 hours has accumulated or oil consumption has stabilized I MIL L 22851 or SAE J1899 Aviation Grade Ashless Dispersant Oil Oil conforming to 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 Mu...

Страница 232: ...urer 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 of deteri...

Страница 233: ...acity 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 attitude Service the fuel system after each flight and keep fuel tanks full to minimize condensation in the tanks FUEL ADDITIVES Strict adherence to recomme...

Страница 234: ...he fuel provides two distinct effects 1 it absorbs the dissolved water from the gasoline and 2 alcohol has a freezing temperature depressant effect NOTE When using fuel additives it must be remembered that the final goal is to obtain a correct fuel to additive ratio in the tank and not just with fuel coming out of the refueling nozzle For example adding 15 gallons of correctly proportioned fuel to...

Страница 235: ...SECTION 8 HANDLING SERVICE MAINTENANCE CESSNA MODEL 172S 70 60 50 w i 15 40 LL o CJ w 30 o o 5 u 20 10 18 18 10 20 30 40 50 GALLONS OF GASOLINE 0585C1001 Figure 8 1 Fuel Mixing Ratio May 30 00 ...

Страница 236: ...Y I IMPORTANT A CONCENTRATION IN EXCESS OF THAT RECOMMENDED 0 15 BY VOLUME MAXIMUM MAY RESULT IN DETRIMENTAL EFFECTS TO THE FUEL TANK SEALANT AND DAMAGE TO O RINGS AND SEALS USED IN THE FUEL SYSTEM AND ENGINE COMPONENTS A CONCENTRATION OF LESS THAN THAT I RECOMMENDED 0 10 BY TOTAL VOLUME MINIMUM WILL RESULT IN INEFFECTIVE TREATMENT USE ONLY BLENDING EQUIPMENT THAT IS RECOMMENDED BY THE MANUFACTURE...

Страница 237: ... 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 contaminate...

Страница 238: ...LEANING 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 A CAUTION NEVER USE GASOLINE BENZENE ALCOHOL ACETONE FIRE EXTINGUISHER ANTI I...

Страница 239: ...asive 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 Igraphics refer to the Maintenance Manual To seal any minor surface chips or scratches and protect against corrosion the ai...

Страница 240: ... 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 suitable solvent in acc...

Страница 241: ...en spot clean the area Oily spots may be cleaned with household spot removers used sparingly Before using any solvent read the instructions on the container and test it on an obscure place on the fabric to be cleaned Never saturate the fabric with a volatile solvent it may damage the padding and backing materials Soiled upholstery and carpet may be cleaned with foam type detergent used according t...

Страница 242: ... This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Global Positioning System is installed FAA APPROVAL IfAA APPROveD UNDER FAR 21 SUBPARTJ The Cessna Aircraft Co _ ation Option Manufacturer CE 7 I ExtcutivoEnglllftr COPYRIGHT q 1998 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S10 01 Date 27 June 2000 o Member ...

Страница 243: ...f that revision Revision Level Date of Issue o Original July 8 1998 1 May 30 00 LOG OF EFFECTIVITY PAGES PAGE Title S1 0 1 S10 2 S10 3 S10 4 DATE May 30 00 May 30 00 May 30 00 July 8 98 PAGE DATE SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains onl...

Страница 244: ...9 may be found in the Bendix King KLN 89 Pilot s Guide supplied with the unit This pilot guide must be available during operation of the KLN 89 unit SECTION 2 LIMITATIONS Use of the KLN 89 is limited to VFR operations only The following information must be presented in the form of placards when the airplane is equipped with a KLN 89 unit 1 On the instrument panel near the KLN 89 unit GPS NOT APPRO...

Страница 245: ...c airplane normal operating procedures with the KLN 89 GPS installed SECTION 5 PERFORMANCE There is no change to the airplane performance when the KLN 89 GPS is installed However installation of an externally mounted antenna or related external antennas may result in a minor reduction in cruise performance S10 4 July 8 98 ...

Страница 246: ... _ _ _ __ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when used for Canadian Operation FAA APPROVAL I AA AI PROveO UNDER FAR 21 SUBPARTJ The Cessna Aircraft Co _ ation Option Manufacturerce ExecutiYeEna Hr D t u o 1998 o Member of GAMA COPYRIGHT i t998 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS SI2 00 8 July 199...

Страница 247: ...sion Revision Level Date of Issue o Original July 8 1998 LOG OF EFFECTIVITY PAGES PAGE Title S12 1 S12 2 DATE July 8 98 July 8 98 PAGE S12 3 S12 4 DATE July 8 98 July 8 98 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletin...

Страница 248: ...supplement is required for Canadian operation of Cessna Model 172S SECTION 2 LIMITATIONS The following placard must be installed 1 Near the fuel tank filler cap July 8 98 FUEL 100LU 100 MIN GRADE AVIATION GASOLINE CAP 26 5 U S GAL 100 LlTRES USABLE CAP 17 5 U S GAL 66 LlTRES USABLE TO BOTTOM OF FILLER INDICATOR TAB S12 3 ...

Страница 249: ...e to the airplane emergency procedures when used for Canadian operation SECTION 4 NORMAL PROCEDURES There is no change to basic airplane normal operating procedures when used for Canadian operation SECTION 5 PERFORMANCE There is no change to the airplane performance when used for Canadian operation S12 4 July 8 98 ...

Страница 250: ...ATION NO _ _ _ _ _ __ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when Horizontal Situation Indicator is installed FAA APPROVAL I AA APPROveO UNDER FAR 21 SUBPARTJ The Cessna Aircraft Co _ a Option ManuflilcturerCE 1 7 ExecutivoEngllleer Da e Ze2000 o Member of GAMA COPYRIGHT rJ 1999 CESSNA AIRCRAFT COMPANY WICHITA KANSA...

Страница 251: ... Revision Level Date of Issue o Original Jan 15 1999 1 May 30 2000 LOG OF EFFECTIVITY PAGES PAGE Title S13 1 S13 2 S13 3 S13 4 DATE May 30 00 May 30 00 May 30 00 Jan 15 99 PAGE S13 5 S13 6 S13 7 S13 8 DATE Jan 15 99 Jan 15 99 Jan 15 99 Jan 15 99 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorp...

Страница 252: ...anel mounted KI 525A indicator combines the display functions of both the standard Directional Gyro Heading Indicator and the Course Deviation Indicator s VOR LOC Glideslope information to provide the pilot with a single visual presentation of the complete horizontal navigation situation This system also incorporates a slaving accessory and compensator unit This unit indicates any difference betwe...

Страница 253: ...th respect to magnetic north The gyro is remote mounted and electric driven 2 NAV FLAG Flag is in view when the NAV receiver signal is inadequate 3 HEADING REFERENCE LUBBER LINE Magnetic heading appears under this line when the compass card is slaved or slewed to the aircraft s magnetic heading 4 HEADING WARNING FLAG HDG When flag is in view the heading display is invalid 5 COURSE SELECT POINTER I...

Страница 254: ... 10 COMPASS CARD Rotates to display heading of airplane with reference to lubber line on HSI 11 COURSE SELECTOR KNOB t Positions the course bearing pointer on the compass card by rotating the course selector knob 12 COURSE DEVIATION BAR D BAR The center portion of the omni bearing pointer moves laterally to pictorially indicate the relationship of airplane to the selected course It indicates degre...

Страница 255: ...de for the Compass System 3 CW CCW COMPASS MANUAL SLAVE SWITCH With the manual automatic compass slave switch in the FREE position allows manual compass card slaving in either the clockwise or counterclockwise direction The switch is spring loaded to the center position 4 SLAVING METER Indicates the difference between the displayed heading and the magnetic heading Up deflection indicates a clockwi...

Страница 256: ...ABLE HEADING INFORMATION Normal procedures for operation of this system differ little from those required for the more conventional Course Deviation Indicators However several small differences are worth noting The rectilinear movement of the course deviation bar in combination with the rotation of the compass card in response to heading changes provides an intuitive picture of the navigation situ...

Страница 257: ...he Autopilot Supplements in the Supplement section of this handbook A description of course datum and autopilot procedures for course datum are incorporated in the appropriate autopilot supplements SECTION 5 PERFORMANCE There is no change to the airplane performance when this instrument is installed S13 8 Jan 15 99 ...

Страница 258: ...s supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the KAP 140 2 Axis Autopilot System is installed COPYRIGHT 1999 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S15 05 FAA APPROVAL J AA APPROVEDUNDER FAR 21 SUBPARTJ The Cessna AircraftCo _ a Option ManufacturerCE 7 t ExecutiYeEngtnnl Date 28 December 1999 o Member of GA...

Страница 259: ...dicated by an asterisk preceeding the page number Supplement Status Date Original Issue Revision 1 Revision 2 Revision 3 Revision 4 Revision 5 28 December 1999 30 May 2000 30 December 2000 28 June 2002 31 October 2002 4 June 2003 LOG OF EFFECTIVE PAGES Page S15 1 thru S15 20 S15 20A thru S15 208 S15 21 thru S15 32 S15 33 thru S15 36 APPROVED BY Page Status Revised Deleted Revised Added DATE OF APP...

Страница 260: ...wing is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that are currently active KC 140 M1 Honeywell Service Bulletin Revision 5 KAP 140 AP Airplane Senal Revision Incorporated Eff9ctiV1ty Incorporation In Airplane Revision 3 s15 31 ...

Страница 261: ...r the pilot when the autopilot is not engaged The electric trim system is designed to be fail safe for any single inflight trim malfunction Trim faults are visually and aurally annunciated A lockout device prevents autopilot or MET engagement until the Isystem has successfully passed preflight self test Automatic preflight self test begins with initial power application to the autopilot The follow...

Страница 262: ...72S9423 and On automated Roll Steering functionality has been added to the Bendix King KLN 94 GPS Navigation System and the KAP 140 2 Axis Autopilot System Roll Steering coupling between the GPS and the Autopilot provides area navigation with automatic course changes at flight plan waypoints similar to Flight Management System FMS operations but without vertical navigation capability The Roll Stee...

Страница 263: ...AV COMM 1 NAVIGATION r I I I r w SOURCE 12 SELECTOR SWITCH CESSNA MODEL 172S I I I I I I r I I I I TURN COORDINATOR WARN C B 07851026 I Figure 1 Bendix King KAP 1402 Axis Autopilot Schematic Serials 172S8348 thru 172S9422 Sheet 1 of 2 IS15 6 Revision 5 ...

Страница 264: ...SUPPLEMENTS SUPPLEMENT 15 FAA APPROVED r I I I I I I I I I _ SOURCE 12 I WiJIL SELECTOR r J SWITCH URN COORDINATOR ROLL STEERING I I I WARN C B 07851026 Figure 1 Bendix King KAP 140 2 Axis Autopilot Schematic Serials 172S9423 and On Sheet 2 Revision 5 ...

Страница 265: ...n the basic roll ROL mode which functions as a wing leveler and the pitch axis vertical speed VS mode The commanded vertical speed will be displayed in the upper right corner of autopilot display area The captured VS will be the vertical speed present at the moment the AP button is pressed The button may also be used to disengage the autopilot 3 ROLL AXIS R ANNUNCIATOR When illuminated indicates f...

Страница 266: ...and tracking of VOR GPS LOC and Glideslope GS on an ILS as selected for presentation on 1 CDI 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 approac...

Страница 267: ...00 FPM synchronizing the ALT reference to the actual airplane altitude upon button release 10 AUTO PILOT CIRCUIT BREAKER A 5 amp pull off circuit breaker supplying 28 VDC to the KAP 140 system 11 WARN C B Power to the autopilot disconnect horn and the airplane s annunciator panel PITCH TRIM 12 AUTOPILOT DISCONNECT AlP DISCITRIM INT SWITCH When depressed will disengage the autopilot and interrupt m...

Страница 268: ...sfied 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 located on instrument panel or glareshield Illuminates whenever the automated preflight self test detects a pitch trim fault or the continuous monitoring system detects a pitc...

Страница 269: ...ot baro setting to match that of the airplane s altimeter when manual adjustment is required In some systems the baro setting may be automatically synched to that of the altimeter 2 BARO SET BARO BUTTON When pushed and released will change the display from the altitude alerter selected altitude to the baro setting display either IN HG or HPA for 3 seconds If pushed and held for 2 seconds will chan...

Страница 270: ... in FPM for 3 seconds If the BARO button is pushed the display changes to the autopilot baro setting in either IN HG or HPA for 3 seconds NOTE This display may be dashed for up to 3 minutes on start up if a blind encoder is installed which requires a warm up period 5 ALTITUDE ALERT ALERT ANNUNCIATION Illuminates continuously in the region of from 200 to 1000 feet from the selected altitude if the ...

Страница 271: ...A 28 will prevent flight control system alerts from being heard 5 The system is approved for Category I operation only Approach mode selected 6 Autopilot maximum airspeed limitation 140 KIAS Autopilot minimum airspeed limitation 70 KIAS Autopilot minimum approach speed 80 KIAS 7 Maximum flap extension 10 8 The autopilot must be disengaged below 200 feet AGL during approach operations and below 800...

Страница 272: ...Circuit Breaker PULL NOTE The AVIONICS MASTER Switch may be used as an alternate means of removing all electric power from the autopilot and electric trim systems If necessary perform steps 1A thru 1C above then turn the I AVIONICS MASTER Switch OFF before locating and pulling the AUTO PILOT Circuit Breaker Turn the AVIONICS MASTER Switch ON as soon as possible to restore power to all other avioni...

Страница 273: ...l of the airplane Immediately grasp the control wheel and press and hold down the AlP DISCITRIM INT switch throughout the recovery Manipulate the controls as required to safely maintain operation of the airplane within all of its operating limitations Elevator trim should be used manually as needed to relieve control forces Locate and pull the AUTO PILOT circuit breaker on the right hand circuit b...

Страница 274: ...d pulled Return the AVIONICS MASTER switch to the ON position as soon as possible With the AVIONICS MASTER switch off all avionics and autopilotequipment will be inoperable 5 It is important that all portions of the autopilot and electric trim system are preflight tested prior to each flight in accordance with the procedures published herein in order to assure their integrity and continued safe op...

Страница 275: ...red P lamp was the result of some abnormal accelerations on the airplane the annunciation should go out within approximately one minute and normal use of the autopilot will be re established 2 A red R is an indication that the roll axis of the autopilot has been disabled and cannot be engaged The autopilot cannot be engaged again Flashing mode annunciation in the display of the autopilot computer ...

Страница 276: ...lash for 5 seconds upon selection of NAV APR or REV modes to remind the pilot to set the HDG bug for use as course datum Effects of instrument losses upon autopilot operation 1 Loss of the artificial horizon no effect on the autopilot 2 Loss of the turn coordinator autopilot inoperative 3 Loss of the Directional Gyro DG The directional gyro does not provide any system valid flag If the DG fails to...

Страница 277: ...ntrol b AlP DISCITRIM INT Switch PRESS and HOLD throughout recovery I c AIRPLANE RETRIM Manually as Needed d AUTO PILOT Circuit Breaker PULL I I I A SECTION 4 NORMAL PROCEDURES PREFLIGHT PERFORM PRIOR TO EACH FLIGHT 1 AVIONICS MASTER SWITCH ON 2 POWER APPLICATION AND SELF TEST A self test is performed upon power application to the computer This test is a sequence of internal checks that validate p...

Страница 278: ...ST as follows a LH SWITCH PUSH FORWARD to DN position and hold OBSERVE NO MOVEMENT of Elevator Trim Wheel Release switch to Center OFF Position NOTE If movement of the elevator trim wheel is observed during a check of either LH or RH Switch the manual electric trim system has malfunctioned The flight may be continued if the AUTOPILOT Circuit Breaker is pulled to the OFF position and secured until ...

Страница 279: ...ASE AlP DISCITRIM INT Switch OBSERVE MOVEMENT of Elevator Trim Wheel in proper direction Release LH and RH Switches to center OFF position NOTE During Steps e and f verify movement of elevator trim tab in proper direction the elevator trim tab will move up for nose down trim If movement of Elevator Trim Wheel is observed while the AlP DISCITRIM INT Switch is pressed the manual electric trim system...

Страница 280: ...BE PREPARED TO DISCONNECT THE AUTOPILOT AND TAKE IMMEDIATE CORRECTIVE ACTION INCLUDING MANUAL CONTROL OF THE AIRPLANE ANDIOR PERFORMANCE OF EMERGENCY PROCEDURES IF AUTOPILOT OPERATION IS NOT AS EXPECTED OR IF AIRPLANE CONTROL IS NOT MAINTAINED DURING ALL AUTOPILOT COUPLED I OPERATIONS THE PILOT IN COMMAND MUST USE PROPER AUTOPILOT COMMANDS AND USE THE PROPER ENGINE POWER TO ENSURE THAT THE AIRPLAN...

Страница 281: ...ing output will command the autopilot to turn and intercept the course to the new active waypoint without directly overflying the immediate waypoint except designated flyover waypoints Distance from the waypoint for the GPS to initiate the turn will vary with groundspeed etc but will usually be within one nautical mile of the waypoint Sequencing to the next waypoint will occur approximately at the...

Страница 282: ...de is displayed NOTE An altitude alert is annunciated 1000 ft prior to arrival at the selected altitude Airplane deviations I greater than 200 feet above or below the selected altitude will produce an altitude alert The alert annunciation is accompanied by a series of short tones 2 AFTER TAKEOFF a Elevator Trim VERIFY or SET to place the airplane in a trimmed condition prior to autopilot engagemen...

Страница 283: ...UTOPILOT AND RETURN THE AIRPLANE TO A STABILIZED CLIMB PRIOR TO RE ENGAGMENT I WHEN OPERATING AT OR NEAR THE MAXIMUM AUTOPILOT SPEED IT WILL BE NECESSARY TO REDUCE POWER IN ORDER TO MAINTAIN THE DESIRED RATE OF DESCENT AND NOT EXCEED THE MAXIMUM AUTOPILOT SPEED I DO NOT HELP THE AUTOPILOT OR HAND FLY THE AIRPLANE WITH THE AUTOPILOT ENGAGED AS THE AUTOPILOT WILL RUN THE PITCH TRIM TO OPPOSE CONTROL...

Страница 284: ... a Capture preselected altitudes if installed 1 ALTITUDE SELECT knob ROTATE until the desired altitude is displayed Note ARM annunciation occurs automatically with altitude selection when the autopilot is engaged 2 ALTITUDE SELECT MODE ARM button PUSH to alternately disarm or arm altitude capture 3 Airplane ESTABLISH vertical speed necessary to intercept the selected altitude NOTE It may be possib...

Страница 285: ...pilot does not use the attitude gyro as a pitch reference it is recommended that the autopilot be disconnected and that the airplane be flown by hand in severe turbulence c Changing altitudes IS15 28 1 Using Vertical Speed Recommended for altitude changes less than 100 ft a VERTICAL SPEED Control PRESS and HOLD either the UP or DN button Vertical Speed will seek a rate of change of about 500 fpm b...

Страница 286: ...nob SELECT desired course 2 NAV Mode Selector Button PRESS Note NAVARM annunciated 3 Heading Selector Knob ROTATE BUG to agree with OBS course NOTE When NAV is selected the autopilot will flash HDG for 5 seconds to remind the pilot to reset the HDG bug to the OBS course IF HDG mode was in use at the time of NAV button selection a 45 intercept angle will then be automatically established based on t...

Страница 287: ...ill automatically begin b When equipped with HSI IS15 30 1 Course Bearing Pointer SET to desired course 2 Heading Selector Knob SET BUG to provide desired intercept angle and engage HOG mode 3 NAV Mode Selector Button PRESS a If the Course Deviation Bar D Bar is greater than 2 to 3 dots from center the autopilot will annunciate NAVARM When the computed capture point is reached the ARM annunciator ...

Страница 288: ...urse makes immediate recovery easier Roll Steering will not function when the GPS is in OBS mode when the autopilot is in HDG or ROL mode or when the autopilot is in NAV mode with NAV selected as the autopilot navigation source 7 APPROACH APR COUPLING To enable glideslope coupling on an ILS and more precise tracking on instrument approaches Roll Steering will operate on instrument approach procedu...

Страница 289: ...with the desired approach course to provide course datum to the autopilot when using a DG a If the CDI needle is greater than 2 to 3 dots from the center the autopilot will annunciate APRARM when the computed capture point is reached the ARM annunciator will go out and the selected course will be automatically captured and tracked b If the CDI needle is less than 2 to 3 dots form the center the HD...

Страница 290: ...er the HOG mode will disengage upon selecting APR mode the APR annunciator will illuminate and the capture track sequence will automatically begin 5 Airspeed MAINTAIN 90 KIAS minimum during coupled autopilot approaches recommended 8 BACK COURSE REV APPROACH COUPLING Le reverse localizer a When equipped with DG 1 BARO setting if installed CHECK 2 OBS Knob SELECT the localizer course to the front co...

Страница 291: ...OUND heading to provide course datum to the autopilot when using a DG a If the COl needle is greater than 2 to 3 dots from center the autopilot will annunciate REVARM when the computed capture point is reached the ARM annunciator will go out and the selected back course will be automatically captured and tracked b If the COl needle is less than 2 to 3 dots from center the HOG mode will disengage u...

Страница 292: ...luminate and the capture track sequence will automatically begin 5 Airspeed MAINTAIN 90 KIAS minimum during autopilot coupled approaches recommended 9 GLiDESLOPE COUPLING a APR Mode ENGAGED Note GSARM annunciated NOTE Glideslope coupling is inhibited when operating in NAV or REV modes With NAV 1 selected to a valid ILS glideslope armed and coupling occurs automatically in the APR mode when trackin...

Страница 293: ...the autopilot will operate in the ROL and VS modes Verify that the airplane Vertical Speed Indicator VSI and the Autopilot VS agree NOTE If tracking the ILS course outbound as part of the missed approach procedure is desired use the NAV mode to prevent inadvertent GS coupling 11 BEFORE LANDING a AlP DISCfTRIM INT Switch PRESS or PRESS and HOLD to disengage AP SECTION 5 PERFORMANCE There is no chan...

Страница 294: ... 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 however the supplement s must bel 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 numbe...

Страница 295: ......

Страница 296: ...N BY CONTACTING CESSNA CUSTOMER SUPPORT AT 316 517 5800 SUPP SUPPLEMENT NAME REVISION EQUIPMENT NO LEVEL INSTALLED 1 Bendix King KX 155A VHF 0 NAV COMM with KI208 or KI209A Indicator Head 2 Bendix King KT 76C Transponder 0 with Blind Encoder 3 Bendix King KMA 26 Audio Selector 1 Panel 4 Pointer Model 3000 11 or Model 2 4000 11 Emergency Locator Transmitter ELT 5 Bendix King KLN 89B Global 2 Positi...

Страница 297: ...Bendix King KAP 140 5 2 Axis Autopilot I 16 Bendix King KT 73 Mode S 0 Transponder 17 Reserved 18 Reserved 19 Bendix King KLN 94 Global 4 Positioning System 20 Bendix King KMA 28 Audio Selector 0 Panel 21 Bendix King KMD 550 Multi Function 0 Display 22 12 Volt Cabin Power System 0 24 Astrotech Model TC 2 0 Clock OATNolt Indicator 25 Bendix King KX 165A VHF 0 NAV COM 26 Bendix King KDR 510 Flight 0...

Страница 298: ...D SERIAL NO _ _ _ _ _ _ __ REGISTRATION NO _ _ _ _ __ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual FAA APPROVAL AAAPPROVEDUNOERFAR21SUBPARTJ The Cessna Aircraft Co _ at Option ManufacturerCE 7 ExecutiYoEn lnftf D t J Xo 1998 o Member of GAMA COPYRIGHT 01998 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S1 00 8 July ...

Страница 299: ...TIVITY PAGES PAGE Title S1 1 S1 2 S1 3 S1 4 S1 5 S1 6 S1 7 S1 8 DATE July 8 98 July 8 98 July 8 98 July 8 98 July 8 98 July 8 98 July 8 98 July 8 98 PAGE S1 9 S1 10 S1 11 S1 12 S1 13 S1 14 S1 15 S1 16 Blank DATE July 8 98 July 8 98 July 8 98 July 8 98 July 8 98 July 8 98 July 8 98 July 8 98 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the ...

Страница 300: ...ocalizer signals between 108 00 and 117 95 MHz in 50 kHz steps The glide slope receiver is automatically tuned when a localizer frequency is selected The circuits required to interpret the VOR and localizer signals are also an integral part of the Nav receiver Large self dimming gas discharge readouts display both the communications and navigation operating frequencies The KX 155A s flip flop pres...

Страница 301: ...he knob in to attenuate the Ident signal and still hear Nav voice All controls for the Nav Comm except those for navigation course selection are mounted on the front panel of the receiver transmitter Control lighting is provided by NAV COMM interior lighting and the instrument panel flood lighting system Operation and description of the audio selector panel used in conjunction with this radio is s...

Страница 302: ... bO 3 3 Sf JET KX 155A VHF NAV COMM TO INDICATION FROM INDICATION FLAG INDICATION 18 KI 208 INDICATOR HEAD NAV 8 STBY 4 5 PULL aBS 7 6 KI209A INDICATOR 0585C1045 0585C1046 0585C1047 Figure 1 Bendix King KX 155A VHF NAV COMM with KI 208 or KI 209A Indicator Head Sheet 1 of 7 July 8 98 S1 5 ...

Страница 303: ... MODE ACTIVE BEARING CDI FORMAT VOR MODE ACTIVE BEARING FLAG DISPLAY 109 50 VOR MODE ACTIVE BEARING TO FUNCTION DISPLAY VOR MODE ACTIVE BEARING FLAG DISPLAY IIO gO LO LOCALIZER MODE FREQUENCY CDI FORMAT Figure 1 Bendix King KX 155A VHF NAV COMM with KI208 or KI 209A Indicator Head Sheet 2 of 7 S1 6 July 8 98 ...

Страница 304: ...dial from the VOR station or a count up count down timer With an active localizer frequency this portion of the display shows the standby frequency the letters LOC or count up count down timer 4 NAV FREQUENCY SELECTOR KNOB SMALL Operates in 50 kHz steps The NAV receiver s lower and upper frequency limits are 108 00 MHz and 117 95 MHz Exceeding the upper limit of frequency band will automatically r...

Страница 305: ...he inner NAV frequency knob and turning it This OBS display is independent of any OBS course selected on an external COL An OBS in the middle of the NAV display will flash while the inner NAV frequency knob is pulled out The COl is displayed on the line below the frequency OBS When the ACTIVE window is tuned to a localizer frequency the standby frequency area is replaced by LOC When the received s...

Страница 306: ...quency transfer button for 2 seconds or more causing the ET on the display to flash In this state the timer can be set as a countdown timer or the elapsed timer can be restarted The countdown timer is set by using the NAV frequency inc dec knobs to set the desired time and then pushing the NAV frequency transfer button to start the timer The large knob selects minutes the small knob in the in posi...

Страница 307: ...esired channel can be selected by turning the comm kHz knob The channel frequency can be entered by pushing the comm transfer button which will cause the standby frequency to flash The comm frequency knobs are then used to enter the desired frequency If dashes located between 136 MHz and 118 MHz are entered instead of a frequency the corresponding channel is skipped in channel selection mode Addit...

Страница 308: ...nto the display Push the COMM TRANSFER button again to return to the active standby display The transceiver is always tuned to the frequency appearing in the ACTIVE display It is therefore possible to have two different frequencies stored in the ACTIVE and STANDBY displays and to change back and forth between them at the simple push of the transfer button 13 COMM VOLUME CONTROL OFF PULLITEST Rotat...

Страница 309: ...kes up with 120 00 MHz in the COMM use frequency and 110 00 MHz in the NAV active frequency with both COMM and NAV in the active entry mode This will aid the pilot in blind tuning the radio SECTION 4 NORMAL PROCEDURES COMMUNICATION RECEIVER TRANSMITTER OPERATION 1 OFF PULUTEST Volume Control Turn clockwise pull out and adjust to desired audio level push control back in to activate the automatic sq...

Страница 310: ...eaker Selector on audio control panel SET to desired mode 4 NAV Volume Control a ADJUST to desired audio level b PULL out to identify station VOR OPERATION Channel the NAV Receiver to the desired VOR and monitor the audio to positively identify the station To select an OBS course turn the OBS knob to set the desired course under the lubber line When a signal is received the NAV flag will pull out ...

Страница 311: ... Button When the Pilot Config Mode is entered the unit will show the SWRV mnemonic which is the unit software revision level Adjustment pages can be accessed by MODE button presses The pilot may adjust two parameters in the pilot configuration the display minimum brightness and sidetone volume level Minimum Brightness BRIM will have a range of 0 255 The dimmest is 0 and the brightest is 255 Sideto...

Страница 312: ... configuration mode The NAV returns to its pre Pilot Config state with the new brightness and sidetone levels stored in nonvolatile memory SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or several related antennas may result in a minor reduction in cruise performance July 8 98 S...

Страница 313: ......

Страница 314: ..._ _ _ _ _ __ REGISTRATION NO _ _ _ _ __ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual FAA APPROVAL I AA APPROVED UNDER FAR 21 SUBPARTJ The Cessna Aircraft Co _ a Option Manufac turerCE 1 7 I ExtcutiYeEnJlnnr D t U 1998 o Member of GAMA COPYRIGHT II 1998 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S2 00 8 July 1998 ...

Страница 315: ...e o Original July 8 1998 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S2 1 July 8 98 S2 6 July 8 98 S2 2 July 8 98 S2 7 July 8 98 S2 3 July 8 98 S2 8 July 8 98 S2 4 July 8 98 S2 9 July 8 98 S2 5 July 8 98 S2 10 Blank July 8 98 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into t...

Страница 316: ...ves interrogating pulse signals on 1030 MHz and transmits coded pulse train reply signals on 1090 MHz It is capable of replying to Mode A aircraft identification and also to Mode C altitude reporting interrogations on a selective reply basis on any of 4096 information code selections When a panel mounted SSD120 20 Blind Encoder not part of KT 76C Transponder system is included in the avionic confi...

Страница 317: ...reprogram any single code such as 1200 into the KT 76C Pressing the VFR button instantly returns the KT 76C to the preprogrammed code without having to manually enter 1200 All Bendix King Transponder operating controls are located on the front panel of the unit Functions of the operating controls are described in Figure 1 S2 4 July 8 98 ...

Страница 318: ... display is in hundreds of feet FL is annunciated to indicate Flight Level altitude Flight Level is a term to indicate that the altitude is not true altitude but barometric altitude which is not corrected for local pressure For Example FL 040 corresponds to an altitude of 4000 feet meaning sea level pressure of 29 92 inches of mercury The Flight Level altitude is only displayed when the altitude r...

Страница 319: ...bles transponder to transmit Mode A aircraft identification reply pulses ON is annunciated ALT Turns set on and enables transponder to transmit either Mode A aircraft identification reply pulses and Mode C altitude reporting pulses selected automatically by the interrogating signal ALT is annunciated 6 VFR CODE BUTTON VFR Pressing the VFR Button will cause a pre programmed Mode A reply code to sup...

Страница 320: ...ENCY SIGNAL 1 Mode Selector Knob ALT 2 Numeric Keys 0 7 SELECT 7700 operating code TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN IN A CONTROLLED ENVIRONMENT 1 Mode Selector Knob ALT 2 Numeric Keys 0 7 SELECT 7600 operating code SECTION 4 NORMAL PROCEDURES BEFORE TAKEOFF 1 Mode Selector Knob SBY TO TRANSMIT MODE A AIRCRAFT IDENTIFICATION CODES IN FLIGHT 1 Numeric Keys 0 7 SELECT...

Страница 321: ...T R will illuminate steadily indicating IDENT operation TO TRANSMIT MODE C ALTITUDE REPORTING CODES IN FLIGHT 1 Transponder Code Selector Knob SELECT assigned code 2 Mode Selector Knob ALT NOTES When directed by ground controller to stop altitude squawk turn Mode Selector Knob to ON for Mode A operation only Altitude transmitted by the transponder for altitude squawk and displayed on the KT 76C pa...

Страница 322: ...de Button PRESS while still holding lOT button to place new VFR code in nonvolatile memory for subsequent call up SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or related external antennas may result in a minor reduction in cruise performance July 8 98 S2 9 S2 10 Blank ...

Страница 323: ......

Страница 324: ...EGISTRATION NO _ _ _ _ __ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual FAA APPROVAL I AA APPROVED UNDER FAR 21 SUBPARTJ The Cessna AircraftCo COPYRIGHT 1998 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S3 01 _ a Option Manufacturer CE 7 t7 executivoEngmlOf Da e le2000 o Member of GAMA 8 July 1998 Revision 1 30 May ...

Страница 325: ... July 8 1998 1 May 30 2000 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S3 1 May 30 00 S3 6 July 8 98 S3 2 May 30 00 S3 7 July 8 98 S3 3 July 8 98 S3 8 May 30 00 S3 4 July 8 98 S3 9 July 8 98 S3 5 July 8 98 S3 10 blank July 8 98 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into...

Страница 326: ...or PA Unused position All operating controls are shown and described in Figure 1 A crystal controlled superheterodyne marker beacon receiver with 3 light presentation is incorporated within the unit Dimming circuitry for the marker lamps automatically adjusts brightness appropriate to the cockpit ambient light level Hi and Lo sensitivity and lamp test functions are also provided Light dimming for ...

Страница 327: ...pe INNER AIRWAY and FAN Light illuminates white to indicate passage of ILS inner airway or fan marker beacons OUTER Light illuminates blue to indicate passage of outer marker beacon MIDDLE Light illuminates amber to indicate passage of middle marker beacon 2 PHOTOCELL FOR AUTOMATIC DIMMING OF MARKER BEACON LIGHTS AND SELECT BUTTON The photocell in the faceplate automatically dims the marker lights...

Страница 328: ... The AUX position could be used for example for a second DME or ADF When a receiver s audio is selected the green annunciator illuminates at the bottom of the button Push the button again to deselect the receiver s audio 5 MICROPHONE SELECTOR SWITCH MIC Used to select the desired transmitter for the cockpit microphones The C1 C2 and C3 positions are for transmitting on the Com 1 Com 2 and Com 3 co...

Страница 329: ...ill disable the feature Initially when MONI is selected the green annunciators in the button flash for approximately 5 seconds then remains steady while the Com annunciation returns to its previous state 8 CREW INTERCOM VOLUME VOL CREW KNOB and INTERCOM VOX SENSITIVITY SET INTERCOM PUSH VOX SWITCH Inside knob adjusts Pilot and Copilot intercom volume Intercom operation is voice activated VOX where...

Страница 330: ...solated from the intercom while the copilot and passengers are on the same intercom loop and do not hear the radios When either the ALL or CREW intercom modes are selected the pilot s and copilot s intercom volume is controlled by rotating the Crew Intercom Volume Knob left inner knob while the passenger s volume is controlled by rotating the Passenger Intercom Volume Knob left outer knob When the...

Страница 331: ...e KMA 26 as evidenced by the inability to transmit in COM 1 2 or 3 1 MIC Selector Switch EMG NOTE This action bypasses the KMA 26 audio amplifier and connects the pilot s mic head set directly to COM 1 SECTION 4 NORMAL PROCEDURES AUDIO CONTROL SYSTEM OPERATION 1 MIC Selector Switch Turn to desired transmitter 2 SPEAKER and Audio Select Button s SELECT desired receiver s S3 8 NOTES Rotation of the ...

Страница 332: ...rational 2 SENS Selections Select HI sensitivity for airway flying or LO for ILS LOC approaches SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or related external antennas may result in a minor reduction in cruise performance July 8 98 S3 9 S3 10 blank ...

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Страница 334: ...TRATION NO _ _ _ _ _ __ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when a Bendix King KT 73 Mode S Transponder is installed o Member of GAMA COPYRIGHT 2004 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S16 00 APPROVED BY w APPfICYEDUIIlEII14CfRPMT2t J __eo DoIoIoIofto lonAlilnlllo ce I 1fJA DATE OF APPROVAL 22 DEC...

Страница 335: ...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 Date Original Issue 22 December 2004 LOG OF EFFECTIVITY PAGES Page Number S16 1 thru S16 11 S16 12 S16 2 U S Page Status Original Revision Number o FAA APPROVED Original ...

Страница 336: ...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 Original Airplane Serial Revision Incorporated Effectivity Incorporated in Airplane U S S16 3 816 4 ...

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Страница 338: ... reporting and Mode S elementary surveillance selective interrogation The transponder receives interrogating signals on 1030 MHz and transmits coded reply signals on 1090 MHz In Mode C operation the KT 73 provides altitude information automatically to ATC ground stations The transponder reports altitude in 100 foot increments between 1000 and 20 000 feet MSL Mode S allows the ground station to ind...

Страница 339: ... by the avionics light dimming rheostat 2 MODE ANNUNCIATOR Displays FL on the transponder when ALT SBY or GND is selected on the Mode Selector Switch Displays IDT when the IDT button is pushed 3 ALTITUDE DISPLAY FL The Flight Level altitude is shown on the left side of the display only when the Mode Selector Switch is set to Altitude mode ALT In ALT mode the KT 73 shows the pressure altitude on th...

Страница 340: ...ged The Flight ID should be the airplane identification assigned in the flight plan When no flight plan is available the registration marking of the airplane should be used FLT ID is modified by turning the CRSR Knob to position the cursor under the character to be changed then turning the FLT ID Knob to select the desired character When the CRSR and FLTID Knobs have not been turned for 5 seconds ...

Страница 341: ...entification reply pulses with altitude information suppressed Transponder identification code is annunciated on the right side of the display ALT Sets transponder to transmit Mode A squawk Mode C altitude squawk and Mode S airplane identification reply pulses after receiving the interrogation signal FL is shown on the left side of the display with the pressure altitude in hundreds of feet The air...

Страница 342: ...ode Selector Knobs SELECT 7700 operating code TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN IN A CONTROLLED ENVIRONMENT 1 Mode Selector Switch ALT 2 Transponder Code Selector Knobs SELECT 7600 operating code TO PROGRAM FLIGHT IDENTIFICATION CODE 1 Mode Selector Switch ALT 2 Transponder Code Selector Knobs SET assigned SQUAWK code DURING TAXI SECTION 4 NORMAL PROCEDURES 1 Mode S...

Страница 343: ...ctor Switch is positioned to ON 3 IDT Button PUSH when instructed by ground controller to SQUAWK IDENT R will come on steadily indicating IDENT operation TO TRANSMIT MODE AlCIS ALTITUDE REPORTING CODES IN FLIGHT 1 Transponder Code Selector Knobs SELECT assigned code 2 Mode Selector Switch ALT NOTE When directed by ground controller to STOP ALTITUDE SQUAWK turn Mode Selector Switch to ON for Mode N...

Страница 344: ...T 2 Check all displays come on 3 TEST OK displayed If not refer to the KT 73 Transponder section of the Bendix King Silver Crown Plus Pilot s Guide 4 Mode Selector Switch SELECT desired function SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed FAA APPROVED Original U S S16 11 816 12 ...

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Страница 346: ...FR 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 Global Positioning System is installed COPYRIGHT 2000 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S19 04 FAA APPROVAL Date 14 December 2000 o Member of GAMA 6 November 2000 Revision 4 4 June 2003 819 1 ...

Страница 347: ...fected by the current revision are indicated by an asterisk preceding the page number Supplement Status Date Original Issue Revision 1 Revision 2 Revision 3 Revision 4 6 November 2000 18 December 2000 30 December 2000 22 January 2001 4 June 2003 I LOG OF EFFECTIVE PAGES Page Number S19 1 thru S19 20 S19 21 S19 22 Page Status Revised Added APPROVED BY DATE OF APPROVAL S19 2 Revision Number Revision...

Страница 348: ...CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that are currently active Number Title Revision 4 Airplane Serial EJreCiivity Revision Incorporated I Incorporation In Airplane S19 3 ...

Страница 349: ...horoughly studied and VFR operations conducted so that you are totally familiar with GPS navigation before actually using this equipment in IFR conditions At 172S serial number 172S9423 and On automated Roll Steering functionality has been added to the Bendix King KLN 94 GPS Navigation System and the KAP 140 2 Axis Autopilot System Roll Steering coupling between the GPS and the Autopilot provides ...

Страница 350: ... THE DATABASE IS BEING UPDATED NOTE A current database is required by regulation in order to use the KLN 94 GPS system for non precision approaches Provided the KLN 94 navigation system is receiving adequate usable signals it has been demonstrated capable of and has been shown to meet the accuracy specifications of VFR IFR enroute oceanic and remote enroute domestic terminal and instrument approac...

Страница 351: ... means of long range navigation I FAA approval of the KLN 94 does not necessarily constitute approval for use in foreign airspace I The KLN 94 is qualified for BRNAV Basic Area Navigation operation in the European region in accordance with the criteria of AC 90 96 Reference ICAO Doc 7030 Regional Supplementary Procedures JAA Technical Guidance Leaflet AMJ20X2 and Eurocontrol RNAV Standard Doc 003 ...

Страница 352: ...e condition exists which requires a specific action by the pilot the message annunciator will remain on but will not flash 2 GPS WAYPOINT WPT ANNUNCIATOR LIGHT GPS WAYPOINT annunciator will begin to flash approximately 36 seconds prior to reaching a Direct To waypoint Also when turn anticipation is enabled in the KLN 94 GPS unit the annunciator will begin to flash 20 seconds prior to the beginning...

Страница 353: ... automatically selects the approach ARM mode or when the approach ARM mode is manually selected The approach ARM mode will be automatically selected when the airplane is within 30 NM of an airport and an approach is loaded in the flight plan for that airport The approach ARM mode can manually be selected at a greater distance than 30 NM from the airport by pressing the GPS APPROACH switch however ...

Страница 354: ...iation Indicator COl needle can best be accomplished by pressing the Direct To button and then manually setting the No 1 COl course to the course value prescribed in the KLN 94 displayed message The Directional Indicator heading HOG bug must I also be set to provide proper course datum to the autopilot if coupled to the KLN 94 in LEG or OBS When the optional HSI is installed the HSI course pointer...

Страница 355: ...nnunciator will illuminate steady to inform the pilot that GPS information is being displayed on the NAV 1 COL 4 NAV GPS SWITCH Toggles from Nav 1 to GPS and vice versa to control the type of navigation data to be displayed on the COl Course Deviation Indicator The No 1 COl Omni Bearing Selector OBS provides analog course input to the KLN 94 in OBS mode when the NAV GPS switch annunciator is in GP...

Страница 356: ...ng the Direct To button and then manually setting the No 1 COl course to the course value prescribed in the KLN 94 displayed message The Directional Indicator heading HOG bug must also be set to provide proper course datum to the autopilot if coupled to the KLN 94 in LEG or OBS When the optional HSI is installed the HSI course pointer provides course datum to the autopilot Revision 4 Figure 2 GPS ...

Страница 357: ...oved revision b The data on the Self Test page must be verified prior to use I c IFR enroute and terminal navigation is prohibited unless the pilot verifies the currency of the database or verifies each selected waypoint for accuracy by reference to current approved data d Instrument approaches must be accomplished in accordance with approved instrument approach procedures that are retrieved from ...

Страница 358: ...2 23 if the altitude input to the KLN 94 is not available or fewer satellites projected to be operational for the flight the availability of the GPS integrity RAIM should be confirmed for the intended flight route and time This should be obtained from a prediction program run outside of the airplane The prediction program must comply with the criteria of Appendix 1 of AC 90 96 In the event of a pr...

Страница 359: ...invalid utilize remaining operational navigation equipment as required 2 If a RAIM NOT AVAILABLE message is displayed while conducting an instrument approach terminate the approach Execute a missed approach if required 3 If a RAIM NOT AVAILABLE message is displayed in the en route or terminal phase of flight continue to navigate using the KLN 94 or revert to an alternate means of navigation approp...

Страница 360: ...pproach mode APR should be used when conducting a coupled GPS approach NOTE NAV or APR coupled DME arc intercepts can result in excessive overshoots aggravated by high ground speeds andlor intercepts from inside the arc At 172S serial number 172S9423 and On Roll Steering functionality enables the GPS navigation computer to control the autopilot and automatically perform course changes turns and in...

Страница 361: ...ss especially in the event of unexpected autoflight equipment failure GPS signal loss requires that the pilot immediately select an alternate autopilot navigation source If autopilot function is lost the pilot is required to resume manual control of the airplane Keeping the heading bug and course pointer set to the present course makes immediate recovery easier Roll Steering will not function when...

Страница 362: ...he APT 7 page Select an approach and an initial approach fix IAF from the APT 8 page The most efficient means of getting to these pages is initiated by pressing the PROC PROCEDURE button on the KLN 94 a Press PROC button b Select Approach Arrival or Departure c Select the airport from the list or enter the desired airport identifier d The APT 7 or APT 8 page will be displayed as appropriate NOTE T...

Страница 363: ...und to the FAF NOTE OBS navigation is TO FROM like a VOR without waypoint sequencing b If receiving radar vectors choose VECTORS as the IAF activate vectors when the first vector for the approach is received and leave the unit in LEG mode c NoPT routes including DME arc s are flown in LEG LEG is mandatory from the FAF to the MAP NOTE NAV or APR coupled DME arc intercepts can result in excessive ov...

Страница 364: ...he 2 nm inbound to the FAF c Internally the KLN 94 will transition from terminal to approach integrity monitoring 7 Crossing the FAF and APR ACTV is not annunciated a Do not descend b Execute the missed approach 8 Missed Approach a Climb b Navigate to the MAP in APR ARM if APR ACTV is not available NOTE There is no automatic LEG sequencing at the MAP c After climbing in accordance with the publish...

Страница 365: ...ypoint suffixes in the flight plan i IAF f FAF m MAP h missed approach holding fix The DME arc IAF arc intercept waypoint will be on your present position radial off the arc VOR when you load the IAF into the flight plan or the beginning of the arc if currently on a radial beyond the arc limit To adjust the arc intercept to be compatible with a current radar vector bring up the arc IAF waypoint in...

Страница 366: ...he missed approach in APRARM Flagged navigation inside the FAF may automatically bring up the message page stating PRESS PROC BUTTON NOW FOR NAVIGATION Pressing the PROC button will usually restore navigation not guaranteed by changing from APR ACTV to APR ARM Fly the missed approach The instrument approach using the KLN 94 may be essentially automatic starting 30 nm out with a manual baro setting...

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Страница 368: ...NG KMA 28 AUDIO SELECTOR PANEL SERIAL NO _ _ _ _ _ _ __ REGISTRATION NO _ _ _ _ _ __ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual COPYRIGHT 2000 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S20 00 FAA APPROVAL Date January 9 2001 f Member of GAMA 30 December 2000 S20 1 ...

Страница 369: ...0 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S20 1 Dec 30 00 S20 7 Dec 30 00 S20 2 Dec 30 00 S20 8 Dec 30 00 S20 3 Dec 30 00 S20 9 Dec 30 00 S20 4 Dec 30 00 S20 10 Dec 30 00 S20 5 Dec 30 00 S20 11 Dec 30 00 S20 6 Dec 30 00 S20 12 Dec 30 00 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been inco...

Страница 370: ...are shown and described in Figure 1 An unamplified and unswitched stereo audio input is provided for an entertainment audio source Walkman or similar Portable Electronic Device PED The Entertainment audio input is located on the lower half of the cockpit center pedestal the 3 5 mm stereo jack is labeled AUX AUDIO IN The KMA 28 includes the Soft Mute feature that lowers the audio level of the enter...

Страница 371: ...ight presentation is incorporated within the unit Dimming circuitry for the marker beacon lamps automatically adjusts brightness appropriate to the cockpit ambient light level HI and LO sensitivity and lamp test receiver audio mute T M functions are also provided Light dimming for the audio control panel is manually controlled by the RADIO light rheostat knob MARKER FACILITIES MARKER IDENTIFYING T...

Страница 372: ...ition switch is used to set the receiver sensitivity and to test the annunciator lamps When this switch is on HI upper position the high sensitivity is selected which permits you to hear the outer marker tone about a mile out At this pOint you may select the LO middle position to give you a more accurate location of the Marker When used only for approach markers many pilots choose to leave the swi...

Страница 373: ... the COM 1 position both pilot and copilot will be connected to the COM 1 transceiver Only the person who presses their Push to Talk PTT switch will be heard over the aircraft radio Turning the rotary switch to the COM 2 position will place pilot and copilot on COM 2 The KMA 28 gives priority to the pilot s PTT If the copilot is transmitting and the pilot presses his PTT the pilot s microphone wil...

Страница 374: ...e soft mute feature The soft mute feature assures that the aircraft radio transmissions will not be missed due to entertainment playing When there is radio reception or intercom conversation the music level is dropped to background level When the radio or intercom traffic ceases the level gradually returns to normal Karaoke allows the music to continue uninterrupted by intercom or radio traffic wh...

Страница 375: ...inment Passengers can continue to communicate among themselves without interrupting the crew and also may listen to Entertainment Anytime the KMA 28 is in either the COM 1 2 or COM 2 1 split modes the pilot and copilot intercom is controlled with the ICS button The passengers will maintain intercommunications but never hear aircraft radios PILOT HEARS COPILOT HEARS PASSENGER COMMENTS HEARS AIC Rad...

Страница 376: ...area of the knob to adjust the loudness of the intercom for the pilot and copilot only It has no effect on selected radio levels music input levels or passenger s volume level Adjust the radios and intercom volume for a comfortable listening level for the pilot Passenger volume can be adjusted at the headset All passenger headsets are connected in parallel Therefore if a monaural headset is plugge...

Страница 377: ...ronic device s will not cause interference with the navigation or communication system of the airplane NOTE During KMA 28 operation in the OFF or EMG position the audio is disabled preventing installed system alerts autopilot disconnect tone from being heard The marker beacon receiver audio and annunciator lights will be inoperative SECTION 3 EMERGENCY PROCEDURES In the event of a failure of the K...

Страница 378: ...nal 2 SENS Selections Select HI sensitivity for airway flying or LO for ILS LOC approaches The Entertainment audio input AUX AUDIO IN is unswitched so there is no means of deselecting the entertainment source except by unplugging the Audio Input connector In the event of failure of the Soft Mute function or during periods of high pilot workload and or heavy radio traffic it may be wise to disable ...

Страница 379: ...riefing should specify that Entertainment audio input and PED use is permitted only during the enroute phase of flight SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or related external antennas will result in a minor reduction in cruise performance S20 12 Dec 30 00 ...

Страница 380: ...SPLAY 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 KMD 550 Multi Function Display is installed COPYRIGHT 2000 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S21 00 FAA APPROVAL Date January 9 2001 o Member of GAMA 30 December 2000 821 1 ...

Страница 381: ...inal Dec 30 2000 LOG OF EFFECTIVITY PAGES PAGE Title S21 1 S21 2 S21 3 S21 4 S21 5 DATE Dec 30 00 Dec 30 00 Dec 30 00 Dec 30 00 Dec 30 00 PAGE S21 6 S21 7 S21 8 S21 9 S21 10 blank DATE Dec 30 00 Dec 30 00 Dec 30 00 Dec 30 00 Dec 30 00 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into...

Страница 382: ...switch and is current protected by the GPS circuit breaker The KMD 550 is operated via a joystick a series of five Power Keys that are located along the right side of the unit a series of Function Select Keys located along the bottom and an inner and outer Control Knob The joystick allows movement of the pointer in MAP mode and is used to select and change setup fields The appropriate key labels f...

Страница 383: ...ION ONLY A WARNING NEVER USE THE WEATHER DISPLAYED ON THIS EQUIPMENT AS YOUR SOLE REFERENCE FOR WEATHER AVOIDANCE CHANGING THE DATABASE CARD To change the data card follow these simple steps 1 Turn off the KMD 550 2 Grasp the data card and pull it straight out of it s socket 3 With the card facing upward as indicated on its label insert the new data card being careful to align the card with the so...

Страница 384: ...D 550 is not an IFR primary means of navigation system Therefore its use as an advisory navigation system does not mandate that the database be current However it is strongly recommended from a safety viewpoint that you continue to keep your database current 3 DISPLAY The KMD 550 utilizes a 5 diagonal color active matrix liquid crystal display 4 AVAILABLE FUNCTIONS LEGEND These icons indicate what...

Страница 385: ...nobs located in the lower right of the unit are not functional in this installation 9 POWER LABELS When the Power Label is illuminated on the right side of the key that key s function is dedicated to the function described by the label and that function is active The following is a list of the dedicated functions MODE Pressing this key will sequence through all available modes associated with the ...

Страница 386: ...for measuring range and bearing to specific points The joystick is also used to modify configuration settings on the AUX setup pages 12 POWER KEYS These five keys are used to manipulate the page being displayed Their present functionality can be indicated by the use of Soft Labels on the left side of the key or Power Labels on the right side of the key 13 FAULT INDICATOR The Fault Indicator is loc...

Страница 387: ...two seconds These can help provide a reference for monitoring the status of selected functions and overlays GPS DATA SOURCES The KMD 550 accepts GPS data from the KLN 94 The active flight plan and waypoints are imported directly from the KLN 94 DISPLAY ICONS When showing any map screen airports navaids towns intersections user waypoints and many other data classes are represented by symbols or ico...

Страница 388: ...ocedures when the KMD 550 Multi Function Display is installed SECTION 4 NORMAL PROCEDURES There is no change to the airplane normal procedures when the KMD 550 Multi Function Display is installed SECTION 5 PERFORMANCE There is no change to the airplane performance when the KMD 550 Multi Function Display is installed Dec 30 00 S21 9 S21 10 blank ...

Страница 389: ......

Страница 390: ...RIAL 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 12 Volt Cabin Power System is installed COPYRIGHT I J 2000 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S22 00 FAA APPROVAL Date January 9 2001 o Member of GAMA 30 December 2000 822 1 ...

Страница 391: ...sue o Original Dec 30 00 LOG OF EFFECTIVITY PAGES PAGE Title S22 1 S22 2 S22 3 S22 4 DATE Dec 30 00 Dec 30 00 Dec 30 00 Dec 30 00 PAGE DATE S22 5 Dec 30 00 S22 6 Dec 30 00 S22 7 Dec 30 00 S22 8 blank Dec 30 00 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This lis...

Страница 392: ... electronic devices PED The remote power outlet RPO labeled CABIN PWR 12V is located on the lower portion of the cockpit center pedestal See Figure 1 The RPO conforms to ARINC 628 Part 2 requirements for commercial airline in seat power connectors except that the Cabin Power System supplies automotive type 12 VDC in lieu of the 15 VDC provided by the airlines CABIN POWER 12V Figure 1 12 Volt Cabin...

Страница 393: ...motive cigarette lighter socket Radio Shack Cat No 270 1580 or similar Most laptop computer manufacturers and a number of accessory manufacturers Absolute Battery Mobility Electronics USI Extended Microdevices etc can provide suitable power cables for these devices A light colored mating plug is preferred for visibility S22 4 Plug Contact Assignments Not used Not used Not used Not used Not used Ou...

Страница 394: ...g limitations must be adhered to 1 The 12 Volt Cabin Power System is not certified for supplying power to flight critical communications or navigation devices 2 Use of the 12 Volt Cabin Power System is prohibited during takeoff and landing 3 Use of the 12 Volt Cabin Power System is prohibited under IFR unless the operator of the aircraft has determined that the use of the 12 VDC power supply and t...

Страница 395: ... ELECTRIC CURRENT 1 12 volt power shall be limited to a maximum of 10 amps If a load in excess of this limit is applied to the Cabin Power System connector the CABIN LTS PWR circuit breaker may open or the protection circuitry in the DC to DC power converter may limit the excess power by lowering the supplied voltage below 12 volts 2 The 12 volt Cabin Power System may not be used to charge lithium...

Страница 396: ... portable electronic device is not permitted during takeoffs and landings NOTE Disconnect the power adapter cable from the Cabin Power System connector whenever the PED portable electronic device is not in use SECTION 5 PERFORMANCE There is no change to the airplane performance when this equipment is installed Dec 30 00 S22 7 S22 8 blank ...

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Страница 398: ...ATOR 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 Astrotech ClockiOATNolt Indicator is installed COPYRIGHT r 2002 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S24 00 FAA APPROVAL Date 31 January 2002 o Member of GAMA 31 January 2002 S24 1 ...

Страница 399: ... Revision Level Date of Issue o Original Jan 31 2002 LOG OF EFFECTIVITY PAGES PAGE Title S24 1 S24 2 S24 3 DATE Jan 31 02 Jan 31 02 Jan 31 02 PAGE S24 4 S24 5 S24 6 DATE Jan 31 02 Jan 31 02 Jan 31 02 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains...

Страница 400: ...ton is used to control sequencing between temperature and voltage The lower three buttons control reading and timing functions related to the digital clock Temperature and voltage functions are displayed in the upper portion of the unit s LCD window and clock timing functions are displayed in the lower portion of the unit s LCD window The digital display features an internal light back light to en...

Страница 401: ...the button is used to advance the count of the digit currently being set When in the Timer Mode the button alternately starts and stops the elapsed counter with each push 3 MODE BUTTON The MODE button toggles between clock and timer Each time the button is pressed the mode changes While in the Timer Mode the word TIMER is displayed below the digits as shown in Figure 1 4 RESET SET BUTTON When the ...

Страница 402: ...he window from voltage to Fahrenheit F to Celsius C and back again to voltage CLOCK OPERATIONS The lower LCD window is dedicated to clock and timing operations Pushing the MODE button toggles between clock and timer Each time the button is pushed the mode changes Time of day is displayed in hours and minutes in the 24 hour format Setting procedures are as follows While in the Clock Mode press the ...

Страница 403: ...utton The display will show the date and start the clock running If the minutes were not changed the minutes will continue to run and not need to be restarted When operating in the Timer Mode the word TIMER is shown on the display directly below the digits and indicates that the elapsed time is being displayed The timer can be reset to 00 00 started stopped or restarted It counts in minutes and se...

Страница 404: ...RIAL 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 VHF NAV COMM with Indicator Head is installed COPYRIGHT i J 2002 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S25 00 FAA APPROVAL Date 31 January 2002 f Member of GAMA 31 January 2002 825 1 ...

Страница 405: ...TY PAGES PAGE Title S1 1 S1 2 S1 3 S1 4 S1 5 S1 6 S1 7 DATE Jan 31 02 Jan 31 02 Jan 31 02 Jan 31 02 Jan 31 02 Jan 31 02 Jan 31 02 PAGE S1 8 S1 9 S1 10 S1 11 S1 12 S1 13 S1 14 blank DATE Jan 31 02 Jan 31 02 Jan 31 02 Jan 31 02 Jan 31 02 Jan 31 02 Jan 31 02 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have b...

Страница 406: ... spacing The navigation receiver receives VOR and localizer signals between 108 00 and 117 95 MHz in 50 kHz steps The glideslope receiver is automatically tuned when a localizer frequency is selected The circuits required to interpret the VOR and localizer signals are also an integral part of the Nav receiver Large self dimming gas discharge readouts display both the communications and navigation ...

Страница 407: ... Nav Comm except those for navigation course selection are mounted on the front panel of the receiver transmitter Control lighting is provided by NAV COMM interior lighting and the instrument panel flood lighting system For detailed information of the audio selector panel used in conjunction with this radio refer to the audio selector panel supplement in this section of the POH refer to Section 9 ...

Страница 408: ...030 VOR MODE ACTIVE BEARING CDI FORMAT 109 50 i 030 FLRG _ VOR MODE ACTIVE BEARING FLAG DISPLAY VORE MODE ACTIVE BEARING TO FUNCTION DISPLAY VOR MODE ACTIVE BEARING FLAG DISPLAY 110 gO LOC LOCALIZER MODE FREQUENCY CDI FORMAT 0585T1053 Figure 1 Bendix King KX 165A VHF NAV COMM Sheet 2 of 2 Jan 31 02 S25 5 ...

Страница 409: ... internal COl the bearing to the VOR station radial from the VOR station or a count up count down timer With an active localizer frequency this portion of the display shows the standby frequency the letters LOC or count up count down timer 4 NAV FREQUENCY SELECTOR KNOB SMALL Operates in 50 kHz steps The NAV receiver S lower and upper frequency limits are 108 00 MHz and 117 95 MHz Exceeding the upp...

Страница 410: ...d OBS course can be selected by pulling out the inner NAV frequency knob and turning it This OBS display is independent of any OBS course selected on an external CDI An OBS in the middle of the NAV display will flash while the inner NAV frequency knob is pulled out The CDI is displayed on the line below the frequency OBS When the ACTIVE window is tuned to a localizer frequency the standby frequenc...

Страница 411: ...causing the ET on the display to flash In this state the timer can be set as a countdown timer or the elapsed timer can be restarted The countdown timer is set by using the NAV frequency inc dec knobs to set the desired time and then pushing the NAV frequency transfer button to start the timer The large knob selects minutes the small knob in the in position selects 10 second intervals and the smal...

Страница 412: ... the COMM TRANSFER button which will cause the standby frequency to flash The comm frequency knobs are then used to enter the desired frequency If dashes located between 136 MHz and 118 MHz are entered instead of a frequency the corresponding channel is skipped in channel selection mode Additional channels may be programmed by pressing the COMM TRANSFER button and using the same procedure The chan...

Страница 413: ...isible The desired frequency can be directly entered into the display Push the COMM TRANSFER button again to return to the active standby display The transceiver is always tuned to the frequency appearing in the ACTIVE display It is therefore possible to have two different frequencies stored in the ACTIVE and STANDBY displays and to change back and forth between them at the simple push of the COMM...

Страница 414: ... radio SECTION 4 NORMAL PROCEDURES COMMUNICATION RECEIVER TRANSMITTER OPERATION 1 OFF PULLITEST Volume Control Turn clockwise pull out and adjust to desired audio level push control back in to activate the automatic squelch 2 MIC Selector Switch on audio control panel SET to COMM 1 3 SPEAKER Selector on audio control panel SET to desired mode 4 COMM Frequency Selector Knobs Select desired operatin...

Страница 415: ... FROM flag as appropriate for the selected course LOC OPERATION Localizer circuitry is energized when the NAV Receiver is channeled to an ILS frequency Monitor the LOC audio and positively identify the station The NAV flag will be out of view when the signal is of sufficient strength to be usable GLiDESLOPE OPERATION The glideslope receiver is automatically channeled when a localizer frequency is ...

Страница 416: ...oftware Revision Number SWRV Minimum Display Brightness BRIM 0 255 Sidetone Level SIDE 0 255 Subsequent presses of the MODE button sequences through SWRV BRIM SIDE and then back to SWRV Pressing the NAV Transfer Button momentarily exits Pilot configuration mode The NAV returns to its pre Pilot Config state with the new brightness and sidetone levels stored in nonvolatile memory SECTION 5 PERFORMAN...

Страница 417: ......

Страница 418: ... _ _ _ _ _ __ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the airplane is equipped with the Bendix King KDR 510 Flight Information Services FIS f Member of GAMA COPYRIGHT 2004 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S26 00 APPROVED BY FMAPPROVED UNDER FAR 21 J Thoc _Co DoIegotionOption DQt 01 04 Al Jk DA...

Страница 419: ... 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 LOG OF EFFECTIVE PAGES Page Number S26 1 thru S26 3 S26 4 S26 5 thru S26 6 S26 2 Date 7 January 2004 Page Status Original Original Revision Number o o Original ...

Страница 420: ...ETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that are currently active Air lane Number erial Revision Incorporated EttectiVlty Incorporation In Airplane Original S26 3 826 4 ...

Страница 421: ......

Страница 422: ... 550 multi function display FIS information is intended to be used as a strategic planning tool to help the pilot avoid inclement weather areas that are beyond his visual range FIS lacks the sufficient resolution and update rate necessary for severe weather penetration NOTE Cessna Aircraft Company does not guarantee the quality accuracy or availability of FIS data Some data is available to all KDR...

Страница 423: ... the aircraft that display on the KMD 550 The MODE button toggles between different weather related information displays such as switching between METARs and PIREPs It is highly recommended that the pilot read the Bendix King subscription agreement and the FIS addendum to the KMD 550 850 Pilot s Guide to understand the entire range of information available It is possible that data availability and...

Страница 424: ...T 206H and T206H associated Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Airplane is modified by the installation of AmSafe Aviation Inflatable Restraint AAIR System V23 Version in accordance with STC No SA01700LA The information contained herein supplements or supersedes the basic manual only in those areas listed herein For limitations procedures and performance in...

Страница 425: ...enger seat must not n Added warning Jabel for orientation of airbag and information on additional Child Seat Buckle for Middle Seats of 206 Section 6 deleted balded empty weight in all summaries and deleted last paragraph Whole Document updated changed Company name from AMSAFE Inc to ArnSafe Inc Unless proper name aircraft was re laced with airplane AFM Supplement for AmSafe Aviation Inflatable Re...

Страница 426: ... Auxiliary Child Seat Buckle adapter secures a Child Safety Seat to either left or right positions of the Rear Seat for all models and Ihe Middle Seats for Model 206 see warning label below For the Rear Seats it is typically stored under the cushion and is found in the center of the seat adjacent to the standard AAIR End Release Buckle Assembly For the Middle Seats of Model 206 it is attached at t...

Страница 427: ...7 638 7 338 Arm in 57 928 Moment in Ibs 442 454 AAIR System Difference Added EMA PIN 508358 409 425 075 AAIR System Difference Added EMA PIN 508358 421 Models 172R 172S without optional rear seat bench AAIR System Weight Ibs 3 848 3 698 Arm in 45 397 Moment in Ibs 174 686 AAIR System Difference Added EMA PIN 508358 409 167 871 AAIRSystem Difference Added EMA PIN 508358 421 Models 182S 182T T182T w...

Страница 428: ...Pilot Seat Only AAIR System Weight Ibs 2 575 2 425 Arm in 44 583 Moment in lbs 114 802 108 113 AAIR System Difference Added EMA PIN 508358 409 AAIR System Difference Added EMA PIN 508358 421 Models 206H T206H Middle Seat Only AAIR System Weight Ibs 3 875 3 725 FAA Approved 6 28 07 Arm in 65 382 Moment in lbs 253 356 243 547 AAIR System Difference Added EMA PIN 508358 409 AAIR System Difference Add...

Страница 429: ......

Страница 430: ...the Pilot s 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 and Japan FAA APPROVAL AAAPPROVEDUNoeRFAR21SUBPARTJ The Cessna AircraftCo COPYRIGHT 1998 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHU...

Страница 431: ...ue 8 July 1998 Revision 1 30 May 2000 Revision 2 7 July 2003 APPROVED BY DATE OF APPROVAL Page LOG OF EFFECTIVE PAGES Page Status Revision Number S4 1 thru S4 3 Revision Revision 2 1 S4 4 thru S4 9 S4 1 0 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list con...

Страница 432: ...C91 A Also a remote switch annunciator is installed 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 illuminates 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 avia...

Страница 433: ...the transmitter ON 1 11 u I o T RESET 2685P6012 I 4 3 5 Figure 1 Pointer Model 3000 11 Emergency Locator Transmitter 1 REMOTE CABLE JACK Connects to ELT remote switch annunciator located on the copilot s instrument panel 2 ANTENNA RECEPTACLE Connects to antenna mounted on top of tailcone 3 TRANSMITTER ANNUNCIATOR LIGHT Illuminates red to indicate the transmitter is transmitting a distress signal 4...

Страница 434: ...ransmitting a distress signal AUTO Arms transmitter for automatic activation if G switch senses a predetermined deceleration level RESET Deactivates and rearms transmitter after automatic activation by the G switch Red annunciator in center of rocker switch should extinguish 1I111 IlG L o o i J I ii 1 ON illD II 5 RESET Figure 2 Pointer Model 4000 11 Emergency Locator Transmitter ELT 1 REMOTE CABL...

Страница 435: ...ue and to reset the automatic activation function The red annunciator in the center of the remote switch annunciator should extinguish 5 REMOTE SWITCH ANNUNCIATOR 3 position rocker switch ON Remotely activates the transmitter for test or emergency situations Red annunciator in center of rocker switch illuminates to indicate that the transmitter is transmitting a distress signal AUTO Arms transmitt...

Страница 436: ...Position remote switch annunciator to the ON position even if annunciator light is already on b If airplane radio is operable and can be safely used no threat of fire or explosion turn ON and select 121 5 MHz If the ELT can be heard transmitting it is working properly c Ensure that antenna is clear of obstructions NOTE When the ELT is activated a decreasing tone will be heard before the typical wa...

Страница 437: ...osition 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 antenna cable from ELT 3 Turn airplane battery switch and avionics power s...

Страница 438: ...GHT 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 control facility 1 Your position at the time the signal was first heard 2 Your position at the time the signal was last heard 3 Your position at maxim...

Страница 439: ......

Страница 440: ... __ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Global Positioning System is installed FAA APPROVAL I AA APPROveDUNDER FAR 21 SUBPARTJ The Cessna AircraftCo COPYRIGHT I 1998 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S5 02 _ aoo n Option Manufacturerce 7 I M ExecutivoEnlllnHr Da e Ze 2000 o Member of GA...

Страница 441: ...rent revision will carry the date of that revision Revision Level Date of Issue o Original July 8 1998 1 May 21 1999 2 May 30 2000 LOG OF EFFECTIVITY PAGES PAGE Title S5 1 S5 2 S5 3 S5 4 S5 5 S5 6 S5 7 S5 8 S5 9 S5 10 S5 2 DATE May 30 00 May 30 00 May 21 99 May 21 99 May 21 99 May 21 99 May 21 99 May 21 99 May 21 99 May 21 99 PAGE S5 11 S5 12 S5 13 S5 14 S5 15 S5 16 S5 17 S5 18 S5 19 S5 20 blank D...

Страница 442: ...ETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that are currently active Number Title Airplane Unit Revision Incorporated Effectivity Incorporation In Airplane May 21 99 S5 3 ...

Страница 443: ...egrity Monitoring RAIM is a function that every IFR certified GPS receiver must continuously perform to assure position accuracy RAIM is available when 5 or more of these satellites are in view or 4 satellites are in view and a barometrically corrected altitude input from the airplane s altimeter is made Annunciation is provided if there are not enough satellites in view to assure position integri...

Страница 444: ...E THE DATABASE IS BEING UPDATED NOTE A current database is required by regulation in order to use the KLN 89B GPS system for nonprecision approaches Provided the KLN 89B navigation system is receiving adequate usable signals it has been demonstrated capable of and has been shown to meet the accuracy specifications of VFRlIFR en route oceanic and remote en route domestic terminal and instrument app...

Страница 445: ... the KLN 89B does not necessarily constitute approval for use in foreign airspace NOTE When the KLN 89B contains receiver software RCVR 01621 0001 or higher dash number as verified on the OTH 6 page the unit is qualified for BRNAV Basic Area Navigation operation in the European region in accordance with the criteria of AC 90 96 Reference ICAO Doc 7030 Regional Supplementary Procedures JAA Technica...

Страница 446: ... message If a message condition exists which requires a specific action by the pilot the message annunciator will remain on but will not flash 2 GPS WAYPOINT WPT ANNUNCIATOR LIGHT GPS WAYPOINT annunciator will begin to flash approximately 36 seconds prior to reaching a Direct To waypoint Also when turn anticipation is enabled in the KLN 898 GPS unit the annunciator will begin to flash 20 seconds p...

Страница 447: ...LN 89B GPS system automatically selects the approach ARM mode or when the approach ARM mode is manually selected The approach ARM mode will be automatically selected when the airplane is within 30 NM of an airport and an approach is loaded in the flight plan for that airport The approach ARM mode can manually be selected at a greater distance than 30 NM from the airport by pressing the GPS APPROAC...

Страница 448: ...ng the Course Deviation Indicator COl needle can best be accomplished by pressing the Direct To button and then manually setting the No 1 COl course to the course value prescribed in the KLN 89B displayed message NOTE The Directional Gyro heading HDG bug must also be set to provide proper course datum to the autopilot if coupled to the KLN 89B in LEG or OBS When the optional HSI is installed the H...

Страница 449: ...he currency of the database or verifies each selected waypoint for accuracy by reference to current approved data d The system must utilize ORS Level 02 or later FAA approved revision to conduct nonprecision instrument approaches In addition the software level status found on page OTH 6 must be HOST 00880 0004 or later Instrument approaches must be accomplished in accordance with approved instrume...

Страница 450: ... projected to be operational for the flight the aircraft can depart without further action 2 With 22 23 if the altitude input to the KLN 89B is not available or fewer satellites projected to be operational for the flight the availability of the GPS integrity RAIM should be confirmed for the intended flight route and time This should be obtained from a prediction program run outside of the aircraft...

Страница 451: ...continue to navigate using the KLN 89B or revert to an alternate means of navigation appropriate to the route and phase of flight When continuing to use the KLN 89B for navigation position must be verified every 15 minutes using another IFR approved navigation system 4 Refer to the KLN 89B Pilot s Guide Appendices Band C for appropriate pilot actions to be accomplished in response to annunciated m...

Страница 452: ...button followed by pressing the Clear button and finally the Enter Button Refer to the Pilot s Guide section 4 2 2 for an explanation of turn anticipation and Appendix A Navigation Terms for the definition of cross track error XTK AUTOPILOT COUPLED OPERATION The KLN 89B may be coupled to the KAP 140 autopilot by first selecting GPS on the NAV GPS switch Manual selection of the desired track on the...

Страница 453: ... automatically be disabled prior to flying an instrument approach to reduce the potential for message congestion 1 Prior to arrival select a STAR if appropriate from the APT 7 page Select an approach and an initial approach fix IAF from the APT 8 page IS5 14 NOTE Using the outer knob select the ACT Active Flight Plan Waypoints pages Pull the inner knob out and scroll to the destination airport the...

Страница 454: ... 89B altimeter baro setting as required d Internally the KLN 89B will transition from en route to terminal integrity monitoring 4 Select NAV 4 page to fly the approach procedure a If receiving radar vectors or need to fly a procedure turn or holding pattern fly in OBS until inbound to the FAF NOTE OBS navigation is TO FROM like a VOR without waypoint sequencing A WARNING TO PREVENT THE POSSIBILITY...

Страница 455: ...CH AND THE GPS DISTANCE TO WAYPOINT DECREASING AND NOT MATCHING THE NUMBERS ON THE APPROACH PLATE 5 At or before 2 nm from the FAF inbound a Select the FAF as the active waypoint if not accomplished already b Select LEG operation 6 Approaching the FAF inbound within 2 nm a Verify APR ACTV b Note automatic COl needle scaling change from 1 0 nm to O 3 nm over the 2 nm inbound to the FAF c Internally...

Страница 456: ...ase must be up to date for instrument approach operation Only one approach can be in the flight plan at a time Checking RAIM prediction for your approach while en route using the OTH 3 page is recommended A self check occurs automatically within 2 nm of the FAF APR ACTV is inhibited without RAIM Data cannot be altered added to or deleted from the approach procedures contained in the database DME a...

Страница 457: ... to remind you Left right CDI needle information is relative to the arc Displayed distance is not along the arc but direct to the active waypoint The DME arc radial is also displayed in the lower right corner of the NAV 4 page The DME arc IAF identifier may be unfamiliar Example D098G where 098 stands for the 0980 radial off the referenced VOR and G is the seventh letter in the alphabet indicating...

Страница 458: ...ious selection of the OBS and LEG modes APRARM may be canceled at any time by pressing the GPS APR button A subsequent press will reselect it SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionics equipment is installed However installation of an externally mounted antenna or related external antennas may result in a minor reduction in cruise performance May 21 99 ...

Страница 459: ......

Страница 460: ..._ _ __ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Automatic Direction Finder is installed FAA APPROVAL 11M APPROveOUNDER FAR 21 SUBPARTJ The Cessna Aircraft Co COPYRIGHT 01998 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S6 01 _ ation Option ManufacturerCE 1 ExecUliYoEnlllReer Da e 2000 o Member of GAMA ...

Страница 461: ...1998 1 May 30 2000 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S6 1 May 30 00 S6 7 July 8 98 S6 2 May 30 00 S6 8 July 8 98 S6 3 May 30 00 S6 9 July 8 98 S6 4 July 8 98 S6 10 July 8 98 S6 5 July 8 98 S6 11 July 8 98 S6 6 May 30 00 S6 12 July 8 98 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been...

Страница 462: ... switching between pre selected STANDBY and ACTIVE frequencies by pressing the frequency transfer button Both pre selected frequencies are stored in a non volatile memory circuit no battery power required and displayed in large easy to read self dimming gas discharge numerics The active frequency is continuously displayed in the left window while the right window will display either the standby fr...

Страница 463: ...SECTION 9 SUPPLEMENTS SUPPLEMENT 6 FAA APPROVED 12 11 10 9 16 15 8 13 5 CESSNA MODEL 172S ADF KR87 TSO 6 7 0585C1043 0585C1044 Figure 1 KR 87 Automatic Direction Finder ADF Sheet 1 of 4 S6 4 July 8 98 ...

Страница 464: ...wave and associated morse code identifier broadcast on the carrier wave to be heard NOTE CW signals Morse Code are unmodulated and no audio will be heard without use of BFO This type of 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 ANNUNCIATION When FRQ is displayed the STANDBY frequenc...

Страница 465: ...e knobs are also used to set the desired time when the elapsed timer is used in the countdown mode 7 ON OFFNOLUME CONTROL SWITCH ON OFFNOL Controls primary power and audio output level Clockwise rotation from OFF position applies primary power to the receiver further clockwise rotation increases audio level Audio muting causes the audio output to be muted unless the receiver is locked on a valid s...

Страница 466: ...E Indicates relative or magnetic heading of the aircraft The heading must be manually input by the pilot with the heading HDG knob 14 COMPASS CARD Manually rotatable card that indicates relative or magnetic heading of aircraft as selected by HDG knob 15 BEARING POINTER Indicates relative or magnetic bearing to station as selected by HDG knob If the relative heading of North N is manually selected ...

Страница 467: ...uency display 3 FRO Button PRESS to move the desired frequency from the standby to the active position 4 ADF Selector Switch on audio control panel SELECT as desired 5 OFFNOL Control SET to desired volume level and identify that desired station is being received 6 ADF Button SELECT ADF mode and note relative bearing on indicator ADF TEST PRE FLIGHT or IN FLIGHT 1 ADF Button SELECT ANT mode and not...

Страница 468: ...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 OFFNOL Control ON 2 ADF Button SELECT ANT mode 3 Frequency Selector Knobs SELECT desired frequency in the standby frequency display 4 FRO Button PRES...

Страница 469: ... until ET is annunciated 3 SET RST Button PRESS until the ET annunciation begins to flash 4 FREQUENCY SELECTOR KNOBS SET desired time in the elapsed time display The small knob is pulled out to tune the 1 s The small knob is pushed in to tune the 10 s The outer knob tunes minutes up to 59 minutes NOTE Selector knobs remain in the time set mode for 15 seconds after the last entry or until the SET R...

Страница 470: ...ctor 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 station...

Страница 471: ...ANCE CESSNA MODEL 172S There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or related external antennas may result in a minor reduction in cruise performance S6 12 July 8 98 ...

Страница 472: ...his supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the KAP 140 Single Axis Autopilot is installed FAA APPROVAL 1 1 APPROveD UNDER FAR 21 SUBPART J The Cessna AircraftCo COPYRIGHT D 1998 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S7 02 _ ation Optlon Manufacturarce 7 I ExecutivoEn8lnftf Date 27 June 2000 f Member of...

Страница 473: ...on are indicated by an asterisk preceeding the page number S7 2 Supplement Status Original Issue Revision 1 Revision 2 Date 8 July 1998 30 May 2000 31 October 2002 LOG OF EFFECTIVE PAGES Page Page Status Revision Number Title S7 1 S7 1 thru S7 5 S7 6 thru S7 7 S7 8 thru S7 19 S7 20 APPROVED BY Revised Revised Revised Revised Added FAAAPPROVED UNDER FAR 21 SUIIWtrJ Thoc no_eo O Oon_DQMGOI2f CE DATE...

Страница 474: ...g is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that are currently active Airplane Senal Revision Incorporated EffectiVity Incorporation In Airplane KC 140 M1 KAP 140 AP Revision 2 Honeywell Service Bulletin I Revision 2 S7 3 S7 4 blank ...

Страница 475: ......

Страница 476: ...in the airplane in the commanded lateral attitude The KAP 140 will provide wing leveler heading hold NAV track and approach and backcourse lateral modes A lockout device prevents autopilot engagement until the system has been successfully preflight tested Automatic preflight self test begins with initial power application to the autopilot The following conditions will cause the autopilot to diseng...

Страница 477: ...72S he following circuit breakers are used to protect the listed elements IfJf the KAP 140 single axis autopilot S7 6 LABEL AUTO PILOT WARN FUNCTIONS Supplies power to the KC 140 Computer and the autopilot Supplies power to the autopilot disconnect tone Revision 1 ...

Страница 478: ...ATOR TURN COORDINATOR 2 SECTION 9 SUPPLEMENTS SUPPLEMENT 7 FAA APPROVED GPS NAVIGATION SOURCE SELECTOR SWITCH 8 3 4 5 6 9 CONTROL WHEEL ACTUATOR 10 AVIONICS BUS 05851054 Figure 1 Bendix King KAP 140 Autopilot Operating Controls and Indicators Sheet 1 of 3 Revision 1 S7 7 ...

Страница 479: ...s the airplane to turn to and maintain the heading selected by the heading bug on the Directional Gyro or HSI if installed A new heading may be selected at any time and will result in the airplane turning to the new heading The button can also be used to toggle between HDG and ROL modes This button can also be used to engage the autopilot in HDG mode For airplane serials 172S8001 thru 172S9128 not...

Страница 480: ...ode This mode functions indentically to the approach mode except that the autopilot response to LOC signals is reversed 7 HEADING SELECT KNOB HDG Positions the heading pointer bug on the compass card Note that the position of the heading bug also provides course datum to the autopilot when tracking in NAV APR or REV BC modes This is in addition to its more intuitive use in the HDG mode 8 OMNI BEAR...

Страница 481: ...d to 1 The autopilot must be OFF during takeoff and landing 2 During autopilot operation the pilot with seat belt fastened must be seated in the left front seat 3 Continued autopilot system use is prohibited following abnormal or malfunctioning operation and prior to corrective maintenance 4 The entire PREFLIGHT procedure outlined under Section 4 including steps 1 through 6 must be successfully co...

Страница 482: ...e means of removing power from the autopilot In addition to the above power may be removed with the Engage Disengage button or the airplane MASTER switch If necessary perform steps a and b above then turn off the AVIONICS MASTER switch Primary attitude airspeed directional and altitude control instruments will remain operational with either master switch OFF A WARNING DO NOT ATTEMPT TO RE ENGAGE T...

Страница 483: ...l and press and hold down the AlP DISC switch throughout the recovery Manipulate the controls as required to safely maintain operation of the airplane within all of its operating Iimitations The AVIONICS MASTER switch may be used as required to remove all power from the Autopilot With the AVIONICS MASTER switch off all flight instruments will remain operational however communications navigation an...

Страница 484: ... already reverted to a default mode of operation i e ROL mode An immediate attempt to reengage the lost mode may be made if the offending navigation flag has cleared Effects of instrument losses upon autopilot operation 1 Loss of the artificial horizon no effect on the autopilot 2 Loss of the turn coordinator autopilot inoperative 3 Loss of the Directional Gyro DG The directional gyro does not pro...

Страница 485: ...d by PFT pre flight test with an increasing number for the sequence steps Successful completion of self test is identified by all display segments being illuminated Display Test and the disconnect tone sounding 4 AUTOPILOT ENGAGE by pressing AP button 5 FLIGHT CONTROLS MOVE left and right to verify that the autopilot can be overpowered NOTE Normal use will not require the autopilot to be overpower...

Страница 486: ...ding COMMAND TURNS HEADING HOLD MODE ENGAGED 1 Heading Selector Knob MOVE bug to the desired heading Autopilot will automatically turn the aircraft to the new selected heading NAV COUPLING 1 When equipped with DG a NAV 1 OBS Knob SELECT desired course b NAV Mode Selector Button PRESS Note NAVARM annunciated c Heading Selector Knob ROTATE BUG to agree with OBS course NOTE When NAV is selected the a...

Страница 487: ... from center the HDG mode will disengage upon selecting NAV mode The NAV annunciator will then illuminate and the capture track sequence will automatically begin 2 When equipped with HSI I I a Course Bearing Pointer SET to desired course b Heading Selector Knob SET BUG to provide desired intercept angle and engage HDG mode c NAV Mode Selector Button PRESS 1 If the Course Deviation Bar D Bar is gre...

Страница 488: ... to reset the HDG bug to the approach course If HDG mode was in use at the time of APR button selection a 45 intercept angle will then be automatically established based on the positon of the bug NOTE All angle intercepts compatible with radar vectors may be accomplished by selecting ROL mode PRIOR to pressing the APR button The HDG bug must still be positioned to agree with the desired approach c...

Страница 489: ...APRARM when the computed capture point is reached the ARM annunciator will go out and the selected course will be automatically captured and tracked 2 If the D Bar is less than 2 to 3 dots from center the HDG mode will disengage upon selecting APR mode the APR annunciator will illuminate and the capture track sequence will automatically begin d Airspeed MAINTAIN 90 KIAS during autopilot approaches...

Страница 490: ...han 2 to 3 dots from center the autopilot will annunciate REVARM when the computed capture point is reached the ARM annunciator will go out and the selected back course will be automatically captured and tracked 2 If the COl needle is less than 2 to 3 dots from center the HOG mode will disengage upon selecting REV mode the REV annunciator will illuminiate and the capture track sequence will automa...

Страница 491: ...matically begin d Airspeed MAINTAIN 90 KIAS during autopilot ap proaches recommended MISSED APPROACH 1 AlP DISC PRESS to disengage AP 2 MISSED APPROACH EXECUTE 3 AP Button PRESS if AP operation is desired Note ROL annunciator ON Select optional lateral modes as desired BEFORE LANDING 1 AlP DISC Switch PRESS to disengage AP SECTION 5 PERFORMANCE There is no change to the airplane performance when t...

Страница 492: ..._ __ 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 FAA APPROVAL I AA APPROveDUNDER FAR 21 SUBPARTJ The Cessna Aircraft Co _ ation Option ManufacturerCE 1 7 ExtcUliYoEn8lnnr D t Ullo 1998 f Member of GAMA COPYRIGHT 199B CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS SB OO 8 July ...

Страница 493: ...ision Revision Level Date of Issue o Original July 8 1998 LOG OF EFFECTIVITY PAGES PAGE Title S8 1 S8 2 S8 3 S8 4 DATE July 8 98 July 8 98 July 8 98 July 8 98 PAGE DATE SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins t...

Страница 494: ...equipment should be installed for operations in temperatures consistently below 20 F 7 C Once installed the crankcase breather insulation is approved for permanent use regardless of temperature SECTION 2 LIMITATIONS The following information must be presented in the form of placards when the airplane is equipped with a winterization kit 1 On each nose cap cover plate REMOVE WHEN OAT EXCEEDS 20 F 2...

Страница 495: ... the airplane emergency procedures when the winterization kit is installed SECTION 4 NORMAL PROCEDURES There is no change to the airplane normal procedures when the winterization kit is installed SECTION 5 PERFORMANCE There is no change to the airplane performance when the winterization kit is installed S8 4 July 8 98 ...

Страница 496: ...O _ _ _ _ _ __ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Davtron Clock O A T is installed FAA APPROVAL AAAPPROVEOUNOERFAR21SUBPARTJ The Cessna Aircraft Co _ ation Option ManufKturerce 1 ExacutivoEnlllRHr D t u o 1998 o Member of GAMA COPYRIGHT 1998 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 172SPHUS S9 00 8 Ju...

Страница 497: ...ision Level Date of Issue o Original July 8 1998 LOG OF EFFECTIVITY PAGES PAGE Title S9 1 S9 2 S9 3 S9 4 DATE July 8 98 July 8 98 July 8 98 July 8 98 PAGE S9 5 S9 6 DATE July 8 98 July 8 98 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only thos...

Страница 498: ... are displayed in the upper portion of the unit s LCD window and clock timing functions are displayed in the lower portion of the unit s LCD window The digital display features an internal light back light to ensure good visibility under low cabin lighting conditions and at night The intensity of the back light is controlled by the PANEL LT rheostat In addition the display incorporates a test func...

Страница 499: ...button down for three seconds Proper operation is indicated by the display 88 88 and activation of all four annunciators O A T VOLTMETER OPERATION The upper portion of the LCD window is dedicated to OAT and voltmeter operations The voltmeter reading is preselected upon startup and is indicated by an E following the display reading Pushing the upper control button will sequence the window from volt...

Страница 500: ... each button push increments the digit Once the tens of hours is set the SELECT button selects the next digit to be set After the last digit has been selected and set with the CONTROL button a final push of the SELECT button exits the set mode The lighted annunciator will resume its normal flashing indicating the clock is running in universal time mode SETTING LOCAL TIME Use the SELECT button to s...

Страница 501: ...again resets elapsed time to zero SETTING ELAPSED TIME COUNT DOWN Use the SELECT button to select Elapsed Time ET Simultaneously press both the SELECT and the CONTROL buttons to enter the set mode The tens of hours digit will start flashing The set operation is the same as for UT and a count down time can be set from a maximum of 59 minutes and 59 seconds Once the last digit is set pressing the SE...

Страница 502: ...172SIM ...

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