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Cessna 172R, Operating Handbook

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Cessna 172R Operating Handbook Download Page 232

SECTION

7

AIRPLANE

&

SYSTEMS DESCRIPTION

CESSNA

MODEL

172R

VERTICAL

(HEIGHT)

ADJUSTMENT
CRANK

SEAT

BACK

ANGLE

BUTTON

FORE AND AFT

ADJUSTMENT

LEVER

PRESS TO

RELEASE

(PUSH BUTTON)

PUSH

BUTTON

RELEASE

BUCKLE

(NON ADJUSTABLE)

LIFT

TO

RELEASE

0514T1004

Figure 7-4.

Crew

Seats,

Seat

Belts and

Shoulder

Harnesses

7-16

Revision

8

Summary of Contents for 172R

Page 1: ...ed to be furnished to the pilot by FAR Part 23 and constitutes the FAA Approved Airplane Flight Manual COPYRIGHT 1996 The Cessna Aircraft Company Wichita Kansas USA FAA APPROVAL PAA APPROVEDUNDER FAR 21 SUBPARTJ The Cessna Aircraft Co jation Option Manufacturer CE 1 ExecutiveEngineer Date December 10 1996 0 Member of GAMA Original Issue 2 December 1996 ...

Page 2: ...UAL WAS PROVIDED FOR THE AIRPLANE IDENTIFIED ON THE TITLE PAGE ON 10 31 Qi SUBSEQUENT REVISIONS SUPPLIED BY THE CESSNA AIRCRAFT COMPANY MUST BE PROPERLY INSERTED _ The Cessna Aircraft Company Aircraft Division ...

Page 3: ...PUBLICATION PART NUMBER Pilot s Operating Handbook and FAA Approved Airplane Flight Manual Serial Numbers 17280001 and On Original Issue 2 December 1996 Revision 9 19 July 2004 PART NUMBER 172RPHUS09 I I Revision 9 i ii ...

Page 4: ... Ｉ ...

Page 5: ...rease 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 2450 pounds standard atmospheric conditions level hard surfaced dry runways and no wind They are calculated values derived from flight tests conducted by The Cessna A...

Page 6: ...re individual documents and may be issued or revised without regard to revision dates which apply to the POH itself These supplements contain a Log of Effective Pages which should be used to determine the status of each supplement ORIGINAL ISSUE AND REVISIONS This Pilot s Operating Handbook and FAA Approved Airplane Flight Manual is comprised of the original issue and any subsequent revisions To e...

Page 7: ...each page within the POH At original issue all pages will contain the same date As revisions to the POH occur these dates will change on r effected pages When two pages display the same page number the page with the latest date shall be inserted into the POH The date on the Log Of Effective Pages shall also agree with the latest date of the page in question TEMPORARY REVISIONS r Under limited circ...

Page 8: ...that requires extensive revision revision bars will appear the full length of text New art added to an existing section will be identified by a single pointing hand indicator adjacent to the figure title and figure number Existing art which is revised will have a pointing hand adjacent to the portion of the art which has changed WARNINGS CAUTIONS AND NOTES Throughout the text warnings cautions and...

Page 9: ...ion 9 1 16 Feb 28 00 iii Dec 2 96 1 17 Revision 7 iv Feb 28 00 1 18 Revision 4 v Revision 8 1 19 Revision 7 vi Feb 28 00 1 20 Revision 7 vii Feb 28 00 1 21 Feb 28 00 viii Dec 2 96 1 22 Feb 28 00 ix Revision 9 1 23 Feb 28 00 x Revision 9 1 24 Nov 3 97 xi Revision 9 1 25 Revision 7 xii Revision 9 1 26 Revision 7 xiii xiv Revision 8 1 27 1 28 Revision 7 1 1 Revision 7 2 1 2 2 Revision 8 1 2 Revision ...

Page 10: ...__Revision 7 4 33 Revision 7 3 17 Revision 7 4 34 Revision 7 3 18 ____Revision 7 4 35 Revision 7 3 19 Revision 7 4 36 Revision 7 3 20 Revision 7 5 1 5 2 Revision 8 3 21 Revision 8 5 3 Feb 28 00 3 22 Revision 7 5 4 Dec 2 96 3 23 3 24 Revision 7 5 5 Revision 7 4 1 Revision 7 5 6 Revision 7 4 2 ____Revision 7 5 7 Dec 2 96 4 3 4 4 Revision 7 5 8 Dec 2 96 4 5 ____Revision 7 5 9 Dec 2 96 4 6 ____Revisio...

Page 11: ... 6 16 Feb 28 00 7 30 Dec 30 00 6 17 Feb 28 00 7 30A Revision 5 6 18 Feb 28 00 7 30B Revision 7 6 19 Revision 7 7 31 Dec 30 00 6 20 Revision 7 7 32 Revision 8 6 21 Feb 28 00 7 33 Revision 8 6 22 Feb 28 00 7 34 Revision 8 6 23 Feb 28 00 7 35 Revision 7 6 24 Feb 28 00 7 36 Revision 8 7 1 Feb 28 00 7 37 Original Issue 7 2 Feb 28 00 7 38 Revision 8 7 3 7 4 Revision 8 7 39 Revision 8 7 5 Feb 28 00 7 40 ...

Page 12: ... 8 7 ____Feb 28 00 8 8 Feb 28 00 8 9 Feb 28 00 8 10 Feb 28 00 8 11 Feb 28 00 8 12 Feb 28 00 8 13 Feb 28 00 8 14 Revision 8 8 15 Revision 8 8 16 Feb 28 00 8 17 Feb 28 00 8 18 Feb 28 00 8 19 Feb 28 00 8 20 Revision 8 8 21 Feb 28 00 8 22 Revision 8 8 23 Revision 8 8 24 Revision 8 9 1 Feb 28 00 9 2 Blank Dec 2 96 APPROVED BY DATE OF APPROVAL Cn M c4 xii Revision 9 ...

Page 13: ...TEMPORARY REVISIONS FOR r CESSNA MODEL 172R 172R180 AND 172S AIRPLANES NOT INCORPORATING THE NAV III AVIONICS OPTION G1000 PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL r 10 August 2005 172PHTR ...

Page 14: ...ry Revisions must be incorporated into the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual until the removal instructions have been complied with Insert this page opposite the Log of Effective Pages in the front of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual TEMPORARY REVISION NUMBER PAGE NUMBER ISSUE DATE 172PHTR01 4 12 02 16 04 172PHTR02 3 20 08 10 0...

Page 15: ...FAA Approved Temporary Revision page s may or may not be applicable to your serial airplane Please refer to the individual FAA Approved Temporary Revision page s to determine applicability status for your airplane 28 August 2014 172RPHUS U S ...

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Page 17: ...e Log of Effective Pages in the front of this basic U S Pilot s Operating Handbook and FAA Approved Airplane Flight Manual TEMPORARY REVISION NUMBER PAGE NUMBER ISSUE DATE 172PHTR01 4 12 02 16 04 172PHTR02 3 20 8 10 05 172RPHUS 09 TR03 4 15 8 28 14 172RPHUS 09 TR04 4 23 8 28 14 SERVICE BULLETIN MODIFICATION KIT IF APPLICABLE OR SERIAL EFFECTIVITY Airplanes not incorporating SB04 24 01 Airplanes 17...

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Page 19: ...LE OF CONTENTS SECTION GENERAL LIMITATIONS EMERGENCY PROCEDURES NORMAL PROCEDURES PERFORMANCE WEIGHT BALANCE EQUIPMENT LIST AIRPLANE SYSTEMS DESCRIPTION HANDLING SERVICE MAINTENANCE SUPPLEMENTS 1 2 3 4 5 6 7 8 9 r Revision 8 xiii xiv ...

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Page 23: ...gs 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 Imperial U S Conversion Charts 1 13 Weight Conversions 1 14 Length Conversions 1 16 Distance Conversions 1 20 Volume Conversions 1 21 Temperature...

Page 24: ...SECTION 1 CESSNA GENERAL MODEL 172R HT Figure 1 1 Three View Normal Ground Attitude Sheet 1 of 2 0510T1005 0510T1005 1 2 Revision 7 ...

Page 25: ...OPELLER GROUND CLEARANCE IS 11 1 4 NOTE 4 WING AREA IS 174 SQUARE FEET NOTE 5 MINIMUM TURNING RADIUS f PIVOT POINT TO OUTBOARD WING TIP IS 27 5 1 2 NOTE 6 NORMAL GROUND ATTITUDE IS SHOWN WITH NOSE STRUT SHOWING APPROXIMATELY 2 OF STRUT AND WINGS LEVEL 0510T1005 Figure 1 1 Three View Normal Ground Attitude Sheet 2 Revision 7 1 3 ...

Page 26: ... 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 160 rated BHP at 2400 RPM PROPELLER Propeller Manufacturer McCauley Propeller Systems Propeller Model Number 1C235 LFA7570 Number of Blades 2 Propeller Diameter 75 inches Propel...

Page 27: ...Left or Right position Refer to Figure 1 1 for normal ground attitude dimensions OIL Oil Specification MIL L 6082 or SAE J1966 Aviation Grade Straight Mineral Oil I 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 M...

Page 28: ... 70 F 30 30 40 or 20W 40 Below 12 C 10 F 20 30 or 20W 30 18 C 0 F to 32 C 90 F 20W 50 20W 50 or 15W 50 All Temperatures 15W 50 or 20W 50 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 2457 lbs 2107 lbs Takeoff Weight Normal Category Utility Category 2...

Page 29: ...at must not be occupied and the baggage compartment must be empty STANDARD AIRPLANE WEIGHTS Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6 BAGGAGE SPACE AND ENTRY DIMENSIONS Dimensions of the baggage area and baggage door opening are illustrated in detail in Section 6 SPECIFIC LOADINGS Wing Loading 14 1 lbs sq ft Power Loading 15 3 Ibs hp NOTE Standa...

Page 30: ...ing the airframe VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position VNO Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air then only with caution VNE Never Exceed Speed is the speed limit that may not be exceeded at any time Vs Stalling Speed or the minimum steady flight speed is the minimu...

Page 31: ...gine 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 Adjusting the ...

Page 32: ...during takeoff and landing was actually demonstrated during certification tests The value shown is not considered to be limiting Usable Fuel Unusable Fuel Usable Fuel is the fuel available for flight planning Unusable Fuel is the quantity of fuel that can not be safely used in flight GPH NMPG 9 Gallons Per Hour is the amount of fuel consumed per hour Nautical Miles Per Gallon is the distance which...

Page 33: ...he horizontal distance from the reference datum to the center of gravity C G of an item Moment Center of Gravity C G Moment is the product of the weight of an item multiplied by its arm Moment divided by the constant 1000 is used in this handbook to simplify balance calculations by reducing the number of digits Center of Gravity is the point at which an airplane or equipment would balance if suspe...

Page 34: ...l Load is the difference between ramp weight and the basic empty weight MAC Maximum Ramp Weight MAC Mean Aerodynamic Chord is the chord of an imaginary rectangular airfoil having the same pitching moments throughout the flight range as that of the actual wing Maximum Ramp Weight is the maximum weight approved for ground maneuver and includes the weight of fuel used for start taxi and runup Maximum...

Page 35: ...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 Revision 4 1 13 ...

Page 36: ...205 03 207 24 209 44 211 64 213 85 216 05 218 26 100 220 46 222 67 224 87 227 08 229 28 231 49 233 69 235 90 238 10 240 30 POUNDS INTO KILOGRAMS LIVRES EN KILOGRAMMES lb 0 1 2 3 4 5 6 7 8 9 kg kg kg kg kg kg kg kg kg kg 0 0 454 0 907 1 361 1 814 2 268 2 722 3 175 3 629 4 082 10 4 536 4 990 5 443 5 897 6 350 6 804 7 257 7 711 8 165 8 618 20 9 072 9 525 9 979 10 433 10 886 11 340 11 793 12 247 12 70...

Page 37: ...lograms POUNDS KILOGRAMS r r 220 n t n _ 100 d lU 200 95 90 190 1 85 180 80 170 75 160 70 150 140 65 130 60 120 55 11n 50 1 1u 100 vU 45 90 40 80 35 70 30 60 25 50 40 20 30 15 20 10 10 5 n r Units x 10 100 etc 0585T1027 Figure 1 2 Weight Conversions Sheet 2 of 2 Feb 28 97 1 15 ...

Page 38: ...7 298 56 301 84 305 12 308 40 311 68 314 96 318 24 321 52 324 80 100 328 08 331 36 334 64 337 93 341 21 344 49 347 77 351 05 354 33 357 61 FEET INTO METERS VI PIEDS EN METRES ft 0 1 2 3 4 5 6 7 8 9 m m m m m m m m m m 0 0 305 0 610 0 914 1 219 1 524 1 829 2 134 2 438 2 743 10 3 048 3 353 3 658 3 962 4 267 4 572 4 877 5 182 5 486 5 791 20 6 096 6 401 6 706 7 010 7 315 7 620 7 925 8 230 8 534 8 839 ...

Page 39: ...rs x 3 281 Feet FEET 320 300 280 260 240 220 200 180 160 140 120 100 80 60 40 20 0 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 Revision 7 1 17 ...

Page 40: ... 36 614 37 008 37 402 37 795 38 189 38 583 38 976 100 39 370 39 764 40 157 40 551 40 945 41 339 41 732 42 126 42 520 42 913 INCHES INTO CENTIMETERS POUCES EN CENTIMETRES in 0 1 2 3 4 5 6 7 8 9 cm cm cm cm cm cm cm cm cm cm 0 2 54 5 08 7 62 10 16 12 70 15 24 17 78 20 32 22 96 10 25 40 27 94 30 48 33 02 35 56 38 10 40 64 43 18 45 72 48 26 20 50 80 53 34 55 88 58 42 60 96 63 50 66 04 68 58 71 12 73 6...

Page 41: ...R SECTION 1 GENERAL Centimeters x 394 Inches Inches x 2 54 Centimeters INCHES 10 CENTIMETERS 25 24 23 22 21 20 19 18 17 16 15 14 13 12 Units x 10 100 etc 0585T1028 Figure 1 4 Length Conversions Sheet 2 Revision 7 1 19 ...

Page 42: ...meters x 54 Nautical Miles STATUTE MILES NAUTICAL MILES 115 110 H 105 100 95 90 85 80 75 70 65 60 55 50 45 40 35 30 25 20 15 10 5 0 Figure 180 170 160 KILOMETERS 100 95 90 85 80 150 75 1 140 70 1 130 120 100 95 90 85 80 75 70 65 60 55 50 45 40 35 h30 25 20 15 10 5 0 1 5 Distance Conversions 65 6O 110 55 100 50 45 40 35 30 25 20 15 r 30 90 80 70 60 50 40 10 1 20 5 1 10 o Lo Units x 10 100 etc 1 20 ...

Page 43: ...118 21 338 21 558 21 778 100 21 998 22 218 22 438 22 658 22 878 23 098 23 318 23 537 23 757 23 977 IMPERIAL GALLONS INTO LITERS V GALLONS IMPERIAL EN LITRES IG 0 1 2 3 4 5 6 7 8 9 Lt Lt Lt Lt Lt Lt Lt Lt Lt Lt 0 4 546 9 092 13 638 18 184 22 730 27 276 31 822 36 368 40 914 10 45 460 50 006 54 552 59 097 63 643 68 189 72 735 77 281 81 827 86 373 20 90 919 95 465 100 01 104 56 109 10 113 65 118 20 12...

Page 44: ...x 22 Imperial Gallons 100 IMPERIAL GALLONS 90 85 80 75 70 65 60 55 50 45 40 35 30 25 20 15 10 5 0 440 LITERS 420 400 380 360 340 320 300 280 260 240 220 200 180 160 140 120 100 80 60 40 20 0 Units x 10 100 etc 0585T1032 Figure 1 6 Volume Conversions Sheet 2 of 3 1 22 Feb 28 00 ...

Page 45: ...Gallons LTCRS 95 115 110 65 60 90 105 85 100 8O 95 75 90 70 85 80 75 70 55 65 50 60 45 S5 S 35 40 30 35 25 30 20 25 15 _ 20 15 10 10 5 5 o L o 95 360 90 340 85 320 80 300 75 280 70 65 60 55 50 45 40 35 30 25 20 10 5 260 240 220 200 180 160 140 120 100 80 15 80 40 20 0 ÿ0 Units x 10 100 etc os85Tio33 Figure 1 6 Volume Conversions Sheet 3 of 3 Feb 28 00 1 23 ...

Page 46: ...SECTION 1 GENERAL CESSNA MODEL 172R 0585T1034 Figure 1 7 Temperature Conversions 1 24 Nov 3 97 ...

Page 47: ...CESSNA MODEL 172R SECTION 1 GENERAL PRESSURE CONVERSION HECTOPASCALS MILLIBARS TO INCHES MERCURY inHG Figure 1 8 Hectopascals to Inches Mercury Revision 7 1 25 ...

Page 48: ... 90_Ll40 130 AVGAS FUEL 35 30 25 20 15 10 5H 85 80 75 120 70 110 65 100 60 55 9 50 80 45 70 40 h60 50 40 30 20 10 LITERS KILOGRAMS 1 100 95 135 ISO 125 90 120 115 110 105 100 95 90 85 80 75 70 65 60 55 o o 80 35 45 40 3 35 25 30 20 25 u 20 15 15 10 10 _c 5 5 Units x 10 100 etc 0 0 85 80 75 70 65 60 55 50 45 40 0585T1030 Figure 1 9 Volume to Weight Conversion 11 26 Revision 7 ...

Page 49: ...CESSNA MODEL 172R SECTION 1 GENERAL I Figure 1 10 Quick Conversions Revision 7 1 27 1 28 ...

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Page 53: ...ategory 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 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 11 2 11 2 1...

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Page 55: ...s Pilot s I Operating Handbook for amended operating limitations 1 roperating 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...

Page 56: ...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 2450 Pounds 97 99 abrupt control 2000 Pounds 91 92 movements above 1600 Pounds 82 82 this speed VFE Maximum Flap Extended Speed Do not exceed this 10 Flaps 108 110 speed with flaps 10 to 30 Flaps 84 ...

Page 57: ...Vs 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 Figure 2 2 Airspeed Indicator Markings POWERPLANT LIMITATIONS Engine Manufacturer Textron Lycoming Engine Model Number IO 360 L2A Maximum Power 160 BHP rating Engine Operating L...

Page 58: ...Propeller Systems Propeller Model Number 1C235 LFA7570 Propeller Diameter 75 inches 74 inch minimum POWERPLANT INSTRUMENT MARKINGS Powerplant instrument markings and their color code significance are shown in Figure 2 3 INSTRUMENT RED LINE MINIMUM GREEN ARC NORMAL OPERATING RED LINE MAX Tachometer 1900 to 2400 RPM 2400 RPM Oil Temperature 100 to 245 F 245 F Oil Pressure 20 PSI 50 to 90 PSI 115 PSI...

Page 59: ...and 2 is 120 lbs UTILITY CATEGORY Maximum Ramp Weight 2107 lbs Maximum Takeoff Weight 2100 lbs Maximum Landing Weight 2100 lbs Maximum Weight in Baggage Compartment In the utility category the baggage compartment 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 lbs or less with straight line variation to 40...

Page 60: ...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 Lazy Eights Steep Turns...

Page 61: ...DED ENTRY SPEED Chandelles Lazy Eights Steep Turns Spins Stalls Except Whip Stalls 105 Knots 105 Knots 95 Knots Slow Deceleration Slow Deceleration Abrupt use of the controls is prohibited above 92 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 qu...

Page 62: ...s 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 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 ope...

Page 63: ...finition 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 fuel quantity ...

Page 64: ...ust 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 No acrobatic maneuvers including spins approved Utility Category No acrobatic maneuvers approved except those listed in the Pilot s Operating Handbook Baggage compartment and rear seat must not be occup...

Page 65: ...L FLIGHT FLIGHT ONLY ONLY 3 Near fuel tank filler cap FUEL 100LU 100 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 0 to 10 110KIAS Partial flap range with blue color code also mechanical detent at 10 10 to 30 85 KIAS White color code also mechanical detent at 20 Original Issue 2 13 ...

Page 66: ...TCH 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 QTS 8 On control lock CAUTION CONTROL LOCK REMOVE BEFORE STARTING ENGINE 9 Near airspeed indicator 1 MANEUVERING SPEED 99 KIAS 2 14 Revision 7 ...

Page 67: ...ON 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 Revision 8 2 15 2 16 ...

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Page 71: ...y 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 3 4 3 4 3 4 3 4 3...

Page 72: ...mergency Operation In Clouds Vacuum System Failure 3 16 Executing A 180 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 Excessive ...

Page 73: ...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 65 KIAS Wing Flaps Down 60 K...

Page 74: ...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 65 KIAS flaps UP 60 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 UN...

Page 75: ...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 SECU...

Page 76: ...ANSMIT MAYDAY 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 65 KIAS with flaps up or at 60 KIAS with 10 flaps 7 Approach High Winds Heav...

Page 77: ...alled 10 Engine SECURE 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 OFF Pull Full Out 3 Auxiliary Fuel Pump Switch OF...

Page 78: ...cessary for continuance of flight to nearest suitable airport or landing area 7 8 9 10 11 Master Switch ON Circuit Breakers CHECK for faulty circuit do not reset Radio Switches OFF Avionics Master Switch ON 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...

Page 79: ...re 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 a suitable off airport landing si...

Page 80: ... calibration tables in Section 5 LANDING WITH A FLAT MAIN TIRE 1 Approach NORMAL 2 Wing Flaps 30 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 p...

Page 81: ...nnunciator 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 master switch need not be recycled since an overvoltage condition has not occurred to deactivate the alternator system r1 Avionics Master Switch OFF 2 Alternator Circuit Breaker ALT FLD CHECK IN 3 Master Switch...

Page 82: ...or or Right Vacuum VAC R 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 Annunciator Illuminates A CAUTION I3 I2 Revision 7 ...

Page 83: ...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 ca...

Page 84: ...le gliding toward a suitable landing 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 t i DC DC LD I UU O cn i x g HI x 12 000 10 000 8000 6000 4000 2000 0 2 4 6 8 10 12 14 16 18 20 GROUND DISTANCE NAUTICAL MILES 0585C1...

Page 85: ... 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 MASTER switch or the airplane MASTER sw...

Page 86: ... 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 c...

Page 87: ...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...

Page 88: ...light 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 ...

Page 89: ...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 STO...

Page 90: ...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 ...

Page 91: ...st be removed and discarded when the Idle Power Engine Roughness Information has been incorporated IDLE POWER ENGINE ROUGHNESS As Required by AD 2001 06 17 Paragraph d 3 An excessively rich idle fuel flow may cause low speed engine roughness during flight During most in flight low engine speeds power off stalls approach to landing etc the mixture control is normally in the full rich position Howev...

Page 92: ...ry Revision for Cessna Pilot s Operating Handbook and FAA Approved Airplane Flight Manual APPROVED BY HJJfTKNE UNDERU CFR fWT218WWTJ CMmNaatCo OpfanAutnrtnfeftDOWSOS E DATE OF APPROVAL oo w rjJÿ ___ 172PHTR02 ...

Page 93: ... suspected smoother engine operation may result from making the following changes singly or together set the auxiliary fuel pump switch to the ON position lean the mixture for 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 ann...

Page 94: ... 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 ...

Page 95: ...harging will resume and the low voltage annunciator VOLTS will go off The avionics master switchI may 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 m...

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Page 99: ...bin 4 7 Empennage 4 8 Right Wing Trailing Edge 4 8 Right Wing 4 8 rNose 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 15 Takeoff 4 15 Normal Takeoff 4 15 Short Field Takeoff 4 16 J3 Enroute Climb 4 16 Cruise 4 16 Descent 4 16 Before Landing 4 16 Revi...

Page 100: ... Recommended Starter Duty Cycle Leaning For Ground Operations Taxiing Before Takeoff Warm Up Magneto Check Alternator Check Landing Lights Takeoff Power Check Wing Flap Settings Crosswind Takeoff Enroute Climb Cruise Leaning With EGT Indicator Fuel Savings Procedures for Flight Training Operations Fuel Vapor Procedures Stalls Spins 4 18 4 19 4 20 4 21 4 21 4 23 4 23 4 23 4 23 4 24 4 24 4 24 4 25 4...

Page 101: ...TS Continued Page Landing 4 32 Normal Landing 4 32 Short Field Landing 4 33 Crosswind Landing 4 33 Balked Landing 4 33 Cold Weather Operation 4 34 Winterization Kit 4 35 Hot Weather Operation 4 36 Noise Characteristics And Noise Reduction 4 36 Revision 7 4 3 4 4 ...

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Page 103: ...Short Field Takeoff Flaps 10 Speed at 50 Feet 57 KIAS Enroute Climb Flaps Up Normal Sea Level 75 85 KIAS Normal 10 000 Feet 70 80 KIAS Best Rate of Climb Sea Level 79 KIAS Best Rate of Climb 10 000 Feet 71 KIAS Best Angle of Climb Sea Level 60 KIAS Best Angle of Climb 10 000 Feet 65 KIAS Landing Approach Normal Approach Flaps Up 65 75 KIAS Normal Approach Flaps 30 60 70 KIAS Short Field Approach F...

Page 104: ...ccess 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 fligh...

Page 105: ...ER 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 Avi...

Page 106: ...19 Pitot Heat ON Carefully check that pitot tube is warm to the touch within 30 seconds 20 Pitot Heat OFF 21 Master Switch OFF 22 Elevator Trim SET for takeoff 23 Baggage Door CHECK lock with key 24 Autopilot Static Source Opening if installed CHECK for blockage 0 EMPENNAGE 1 Rudder Gust Lock if installed REMOVE 2 Tail Tie Down DISCONNECT 3 Control Surfaces CHECK freedom of movement and security 4...

Page 107: ...NCE 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 J NOSE 1 Fuel Strainer Quick Drain Valve Located on bottom of fuselage DRAIN at least a cupf...

Page 108: ...FT WING 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 t...

Page 109: ...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 A CAUTION THE AVIONICS MASTER SWITCH MUST BE OFF DURIN...

Page 110: ...usually 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 set mixture to idle cutoff open throttle 1 2 to full and motor crank engine When engine starts set mixture to ful...

Page 111: ... adjacent to page 4 12 This temporary revision must be removed and discarded when SB04 24 01 has been incorporated STARTING ENGINE 1 Throttle OPEN 1 4 INCH 2 Mixture IDLE CUTOFF 3 Propeller Area CLEAR 4 BAT Side Master Switch ON 5 ALT Side Master Switch CHECK OFF 6 Flashing Beacon ON NOTE If engine is warm omit priming procedure of steps 7 8 and 9 below 7 Auxiliary Fuel Pump Switch ON 8 Mixture SE...

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Page 113: ...full and motor crank engine When engine starts set mixture to full rich and close throttle promptly 12 13 14 15 16 17 18 19 Oil Pressure CHECK BAT Side Master Switch OFF leave off at least 2 seconds Both BAT and ALT Sides of Master Switch ON ALT FLD Circuit Breaker CHECK IN Navigation Lights ON as required Avionics Master Switch ON Radios ON Flaps RETRACT APPf Mi 1 n UC flHCniP HKPARXl Cacno Cc D ...

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Page 115: ...s 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 too much turn off auxiliary fuel pump set mixture to idle cutoff open throttle 1 2 to full and motor crank engine When engine starts set mixture to full rich and close th...

Page 116: ... 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 1 Low Voltage Annunciator VOLTS should not be lighted NOTE If the indications as noted in Step d and Step f are not observed t...

Page 117: ...his temporary revision in the Model 172R Nav l Nav II Serials 17280001 and On basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual adjacent to page 4 14 Removal Instructions This temporary revision must be removed and discarded when Revision 10 has been collated into the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual In Section 4 Normal Procedures Page...

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Page 119: ...TEMPORARY REVISION FOR CESSNA PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL BEFORE TAKEOFF 12 13 Throttle Control CHECK IDLE Throttle Control 1000 RPM or LESS 172RPHUS 09 TR03 ...

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Page 121: ... Gage CHECK 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 18 Autopilot if installed OFF 19 Manual Electric Trim if installed CHECK I 20 Elevator Trim SET for takeoff 21 Win...

Page 122: ...wn in the Rate Of Climb chart in Section 5 2 Throttle FULL OPEN 3 Mixture RICH above 3000 feet LEAN to obtain maximum RPM CRUISE 1 Power 2000 2400 RPM No recommended 2 Elevator Trim ADJUST 3 Mixture LEAN more than 80 is DESCENT 1 Power AS DESIRED 2 Mixture ADJUST for smooth operation 3 Altimeter SET 4 NAV GPS Switch SET 5 Fuel Selector Valve BOTH 6 Wing Flaps AS DESIRED 0 10 below 110 KIAS 10 30 b...

Page 123: ...tween magnetos _ b Vacuum 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 18 Autopilot if installed OFF 19 Elevator Trim SET for takeoff 20 Wing Flaps SET for ta...

Page 124: ...n in the Rate Of Climb chart in Section 5 2 Throttle FULL OPEN 3 Mixture RICH above 3000 feet LEAN to obtain maximum RPM CRUISE 1 Power 2000 2400 RPM No more than 80 is recommended 2 Elevator Trim ADJUST 3 Mixture LEAN DESCENT 1 Power AS DESIRED 2 Mixture ADJUST for smooth operation 3 Altimeter SET I 4 NAV GPS Switch SET 5 Fuel Selector Valve BOTH 6 Wing Flaps AS DESIRED 0 10 below 110 KIAS 10 30 ...

Page 125: ...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 55 KIAS 4 Wing Flaps 10 until obstacles are cleared RETRACT after reaching a safe altitude and 60 KIAS AFTER LANDING 1 Wing Flaps UP SECURING AIRPLANE 1 2 3 7 8 Parking Brake SET Electrical Equipment Autopilot if...

Page 126: ...s 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 quick...

Page 127: ...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...

Page 128: ...ecessary After starting if the oil pressure gage does not begin to indicate 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 IRE...

Page 129: ...mended 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 gra...

Page 130: ... liiiiiiiisx lUSE UP AILERON CODE WIND DIRECTION NOTE Strong quartering tail winds require caution Avoid sudden bursts of the throttle and sharp braking when the airplane is in this situation Use the steerable nose wheel and rudder to maintain direction 0585X1020 4 22 Figure 4 2 Taxiing Diagram Revision 7 ...

Page 131: ...this temporary revision in the Model 172R Nav l Nav II Serials 17280001 and On basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual adjacent to page 4 22 This temporary revision must be removed and discarded when Revision 10 has been collated into the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual _ In Section 4 Normal Procedures Page 4 23 BEFORE TAKEO...

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Page 133: ...ottle against the idle stop approximately 675 RPM and accelerates smoothly the engine is ready for takeoff Since the engine is closely cowled for efficient in flight engine cooling the airplane should be pointed into the wind to avoid overheating during prolonged engine operation on the ground Long periods of idling may cause fouled spark plugs 172RPHUS 09 TR04 ...

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Page 135: ...her 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 s...

Page 136: ... 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 propell...

Page 137: ...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 ...

Page 138: ...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...

Page 139: ... 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 mix...

Page 140: ...bove until ready for the TAKEOFF checklist 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 80 or less power NOTE I When cruising or maneuv...

Page 141: ...ribed 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 cooler fu...

Page 142: ...quipment 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 alt...

Page 143: ...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...

Page 144: ...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...

Page 145: ...ngs 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 nec...

Page 146: ... 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 jthiscover can in fact prevent takeoff in many instances AWARNING WHEN PULLING THE PROPELLER THROUGH BY HAND TREAT IT AS IF THE IGNITION SWITCH IS TURNED ON A LOOSE OR BR...

Page 147: ...art 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 a...

Page 148: ...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...

Page 149: ...rcnruntnHHbc in v ...

Page 150: ... PERFORMANCE U1 ...

Page 151: ...bration 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 5 3 5 3 5 3 5 4 5 5 5 6 5 8 5 ...

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Page 153: ... turbulence may account for variations of 10 or more in range and f endurance Therefore it is important to utilize all available v 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 in...

Page 154: ...nd temperature For example in this particular sample problem the takeoff distance information presented for a weight of 2450 pounds pressure altitude of 2000 feet and a temperature of 30 C should be used and results in the following Ground roll 1275 Feet Total distance to clear a 50 foot obstacle 2290 Feet These distances are well within the available takeoff field length However a correction for ...

Page 155: ...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...

Page 156: ...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 28 C 12 C the correction would be 16 C x 10 16 Increase 10 C With this factor included the fuel estimate would be calculated as follows ...

Page 157: ...es 3 1 Hours 99 Knots The fuel required for cruise is 3 1 hours X 7 3 gallons hour 22 7 Gallons A 45 minute reserve requires 45 Q X 7 3 gallons hour 5 5 Gallons The total estimated fuel required is as follows Engine start taxi and takeoff Climb Cruise Reserve 1 1 1 6 22 7 5 5 Total fuel required 30 9 Gallons Once the flight is underway ground speed checks will provide a more accurate basis for est...

Page 158: ... Ground roll Total distance to clear a 50 foot obstacle 625 Feet 1410 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 o...

Page 159: ...light or maximum rated RPM dive r FLAPS UP KIAS 50 60 70 80 90 100 110 120 130 140 150 160 KCAS 56 62 70 79 89 98 107 117 126 135 145 154 FLAPS 10 KIAS 40 50 60 70 80 90 100 110 KCAS 49 55 62 70 79 89 98 108 FLAPS 30 KIAS 40 50 60 70 80 85 KCAS 47 53 61 70 80 84 Figure 5 1 Airspeed Calibration Sheet 1 of 2 Dec 2 96 5 9 ...

Page 160: ...CLOSED FLAPS UP NORMAL KIAS ALTERNATE KIAS 40 36 50 48 60 59 70 70 80 80 90 89 100 99 110 108 120 118 130 128 140 139 FLAPS 10 NORMAL KIAS 40 50 60 70 80 90 100 110 ALTERNATE KIAS 38 49 59 69 79 88 97 106 FLAPS 30 NORMAL KIAS 40 50 60 70 80 85 ALTERNATE KIAS 34 47 57 67 77 81 WINDOWS OPEN FLAPS UP NORMAL KIAS ALTERNATE KIAS 40 26 50 43 60 57 70 70 80 82 90 93 100 103 110 113 120 123 130 133 140 14...

Page 161: ...DEGREES FAHRENHEIT CESSNA MODEL 172R SECTION 5 PERFORMANCE 40 20 0 20 40 60 DEGREES CELSIUS Figure 5 2 Temperature Conversion Chart Dec 2 96 5 11 ...

Page 162: ... 51 48 55 53 61 63 73 10 35 48 38 52 42 58 50 69 30 33 47 36 50 40 56 47 66 MOST FORWARD CENTER OF GRAVITY FLAP SETTING ANGLE OF BANK 00 30 45 60 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 44 52 48 56 53 62 63 74 10 37 50 40 53 44 59 53 70 30 33 47 36 50 40 56 47 66 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 D...

Page 163: ...RFORMANCE WIND COMPONENTS NOTE Maximum demonstrated crosswind velocity is 15 knots not a limitation NOTE Maximum demonstrated crosswind component is 15 knots not a limitation Figure 5 4 Crosswind Components 0585C1003 Revision 7 5 13 ...

Page 164: ...5 2185 1305 2360 1400 2540 1505 2730 4000 1230 2245 1330 2430 1435 2630 1545 2830 1655 3045 5000 1355 2500 1470 2715 1585 2945 1705 3175 1830 3430 6000 1500 2805 1625 3060 1750 3315 1880 3590 2020 3895 7000 1660 3170 1795 3470 1935 3770 2085 4105 2240 4485 8000 1840 3620 1995 3975 2150 4345 2315 4775 NOTES 1 Short field technique as specified in Section 4 2 Prior to takeoff from fields above 3000 ...

Page 165: ...B CDCcrt RATE OF CLIMB FPM ML 1 FT jrCCL KIAS 20 C o c 20 C 40 C S L 79 830 770 705 640 2000 77 720 655 595 535 4000 76 645 585 525 465 6000 74 530 475 415 360 8000 72 420 365 310 250 10 000 71 310 255 200 145 12 000 69 200 145 NOTE 1 Mixture leaned above 3000 feet for maximum RPM Figure 5 6 Maximum Rate of Climb Dec 2 96 5 15 ...

Page 166: ... 1 2 6 4000 7 76 560 6 1 5 8 5000 5 75 515 8 1 8 11 6000 3 74 465 10 2 1 14 7000 1 73 415 13 2 5 17 8000 1 72 365 15 3 0 21 9000 3 72 315 18 3 4 25 10 000 5 71 270 22 4 0 29 11 000 7 70 220 26 4 6 35 12 000 9 69 170 31 5 4 43 NOTES 1 Add 1 1 gallons of fuel for engine start taxi and takeoff allowance 2 Mixture leaned above 3000 feet for maximum RPM 3 Increase time fuel and distance by 10 for each ...

Page 167: ...1 5 9 50 89 5 8 4000 2300 79 117 9 1 75 117 8 6 2250 80 115 9 2 75 114 8 6 70 114 8 1 2200 75 112 8 6 70 111 8 1 66 110 7 6 2100 66 106 7 6 62 105 7 1 59 103 6 8 2000 58 100 6 7 55 98 6 4 53 95 6 2 1900 52 92 6 0 50 90 5 8 49 87 5 6 6000 2350 80 120 9 2 75 119 8 6 2300 80 117 9 2 75 117 8 6 71 116 8 1 2250 76 115 8 7 71 114 8 1 67 113 7 7 2200 71 112 8 1 67 111 7 7 64 109 7 3 2100 63 105 7 2 60 10...

Page 168: ...9 6 4 2000 54 96 6 2 52 94 6 0 51 91 5 9 10 000 2350 76 119 8 8 72 118 8 2 68 117 7 8 2300 72 116 8 3 68 115 7 8 65 113 7 4 2250 68 113 7 8 65 112 7 4 61 109 7 1 2200 65 110 7 4 61 108 7 0 59 105 6 7 2100 58 102 6 6 55 100 6 4 54 97 6 2 2000 52 94 6 1 51 91 5 9 50 88 5 8 12 000 2350 73 119 8 3 69 117 7 9 65 115 7 5 2300 69 115 7 9 65 113 7 5 62 111 7 1 2250 65 112 7 5 62 109 7 1 59 107 6 8 2200 62...

Page 169: ...se At All Altitudes Standard Temperature Zero Wind RANGE NAUTICAL MILES NOTES 1 This chart allows for the fuel used for engine start taxi takeoff and climb and the distance during climb 2 Performance is shown for an airplane equipped with speed fairings which increase the cruise speeds by approximately two knots Figure 5 9 Range Profile Feb 28 97 5 19 ...

Page 170: ...VE 53 GALLONS USABLE FUEL CONDITIONS 2450 Pounds Recommended Lean Mixture for Cruise At All Altitudes Standard Temperature NOTE 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 20 Feb 28 97 ...

Page 171: ... 1375 625 1410 645 1440 3000 585 1345 605 1380 625 1415 650 1445 670 1480 4000 605 1380 630 1415 650 1450 670 1485 695 1520 5000 630 1415 650 1455 675 1490 700 1525 720 1560 6000 655 1455 675 1490 700 1530 725 1565 750 1605 7000 680 1495 705 1535 730 1570 755 1610 775 1650 8000 705 1535 730 1575 755 1615 780 1655 810 1695 NOTES 1 Short field technique as specified in Section 4 2 Decrease distances...

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Page 173: ...375 625 1410 645 1440 3000 585 1345 605 1380 625 1415 650 1445 670 1480 4000 605 1380 630 1415 650 1450 670 1485 695 1520 5000 630 1415 650 1455 675 1490 700 1525 720 1560 6000 655 1455 675 1490 700 1530 725 1565 750 1605 7000 680 1495 705 1535 730 1570 755 1610 775 1650 8000 705 1535 730 1575 755 1615 780 1655 810 1695 NOTES 1 Short field technique as specified in Section 4 2 Decrease distances 1...

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Page 177: ...BALANCE EQUIPMENT LIST SECTION 6 WEIGHT BALANCE EQUIPMENT LIST TABLE OF CONTENTS Page Introduction 6 3 Airplane Weighing Procedures 6 3 JWN Weight And Balance 6 6 Baggage Tie Down 6 8 Comprehensive Equipment List 6 17 Revision 8 6 1 6 2 ...

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Page 179: ...S THE RESPONSIBILITY OF THE PILOT TO ENSURE THE AIRPLANE IS LOADED PROPERLY OPERATION OUTSIDE OF PRESCRIBED WEIGHT AND BALANCE LIMITATIONS COULD RESULT IN AN ACCIDENT AND SERIOUS OR FATAL INJURY AIRPLANE WEIGHING PROCEDURES 1 Preparation a Inflate tires to recommended operating pressures b Defuel airplane Refer to the Maintenance Manual I c Service engine oil as required to obtain a normal full in...

Page 180: ...OWER PORTION STA 0 0 150 100 50 0 50 100 NOTE IT IS THE RESPONSIBILITY OF THE PILOT TO ENSURE THAT THE AIRPLANE IS LOADED PROPERLY 25 90 LEVEL AT UPPER DOOR SILL OR LEVELING SCREWS ON LEFT SIDE OF TAILCONE I 100 I 150 I 200 I 250 100 T 50 50 FUSELAGE STATION FS INCHES 0585C1010 Figure 6 1 Airplane Weighing Form Sheet 1 of 2 6 4 Revision 2 ...

Page 181: ...LOCATING CG WITH AIRPLANE WEIGHED ON LANDING GEAR ossso 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 LEFTSIDE RIGHT SIDE NOSE AIRPLANE TOTAL AS WEIGHED BASIC EMPTY WE GHT AND CENTER OF GRAVITY TABLE ITEM WEIGHT POUNDS CG ARM INCHES MOMENT INCH POUNDS 1000 AIRPLANE CALCULATED OR AS WEIGHED INC...

Page 182: ...t 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 calculate 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...

Page 183: ...t Useful Load 168 2 40 2 1 6 647 21 2450 775 NOTE This is NOT an official Weight and Balance for ÿhii For the actual weight and balance please refer to the Weight j For tbs ecUal r form in this POH NOTE All weights are in pounds 5 1 r ...

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Page 185: ...2015 2548 Previous data taken from document dated Mar 12 2007 Previous useful load 773 60 Model Description LB IN Weight CG Arm Moment Previous data 1683 40 40 22 67707 59 REMOVED ITEMS KMA26 KING AUDIO PANEL 1 70 14 80 25 16 REMOVED SUB TOTAL 1 Item 1 70 14 80 25 16 INSTALLED ITEMS GMA340 GARMIN AUDIO PANEL 1 70 14 80 25 16 At INSTALLED SUB TOTAL 1 Item 1 70 14 80 25 16 NEW DATA NEW USEFUL LOAD 7...

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Page 187: ...WEIGHT CG DATED 10 0ct 05 1682 00 40 21 DESCRIPTION WEIGHT ARM EQUIPMENT REMOVED ONE BENDIX KLN 94 GPS ONE BENDIX KI 209A NAV INDICATOR ONE MIDCONTINENT MD41 ANNUCIATOR ONE BENDIX KA 92 GPS ANTENNA ONE BENDIX KX 155A NAV COMM EQUIPMENT ADDED ONE GARMIN GNS430W WAAS GPS ONE GARMIN GA 35 WAAS GPS ANTENNA ONE BENDIX KN 64 DME ONE BENDIX KA 61 DME ANTENNA ONE GARMIN GA 106A NAV INDICATOR INCREASE DECR...

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Page 189: ...esc i SKY TEC STARTER X 9W 5 0 Xb 8L J_ x yVi r T 5 ÿ C 1 X 38 Q 33 6 0 3 T v 4 X 3 AIRCRAFT EMPTY WEIGHT ARM 6oc 0 _____ yo czi MOMENT 7 V 7 i GROSS WEIGHT O USEFUL LOAD 70 S 0 i K3NA FURE AUTHORIZATION NOTE Weig it and balance must be completed and attached to pilot s operating handbook Sky Tec Sorinl s Beginning w Lycoming FN S s lbs PNR SA lbs CN S lbs Ffx L 7 8 lbs Cfx L 7 8 lbs F xJP 7 8 lbs...

Page 190: ... approved design and specified in Block 13 16 Approval Authorization No BMfR 750120SW Eugene Chiappc 18 Date m d y September 23 2005 User Installer Responsibilities It is important to understand that the existence of this document alone does not automatically constitute authority to install the part assembly Where the user installer work in accordance with the national regulations of an Airworthin...

Page 191: ...em Description Weight Arm Moment Old Weight Dated 12 19 01 1701 1 40 26 68480 61 Equipment Removed Cessna Item 32 02 A Wheel Fairing Installation t 16 5 7 7 0 46 1 _y y 760 6 New Empty Weight 1684 6 40 1 67720 01 y 7 GrossÿWeight 2457 0 Useful Load 772 4 New EWCG 40 1 Refer to Aircraft Flight Manual For Loading Data f 7 12 21 01 Date Corro 7 LO c e 2 ...

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Page 193: ...T LLC 891 BRIDGETON LANE PERRYSBURG OH 43551 STARTING WEIGHT AND BALANCE DATA CG MOMENT DATED 26 Feb 01 G69pOol i 40 34 68199 00 DESCRIPTION ARM MOMENT EQUIPMENT ADDED ONE KING KR87 ADF RECEIVER ONE KING KI 227 ADF INDICATOR ONE KING ADF ANTENNA ONE KING ADF CABLE ASSEMBLY INCREASE DECREASE 3 20 12 10 38 72 0 70 15 90 11 13 4 20 39 30 165 06 2 30 29 00 J 66 70 10 40 281 61 NEW WEIGHT AND DATA EMPT...

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Page 195: ...t Autopilot Bendix King Dual Axis KAP 140 Directional Gyro Exchange Pilot Control Wheel Exchange GPS NAV Selector 0 2 19 7 0 5 0 2 0 2 The weight and balance data showninthis report are computed on the basis of Federal Aviation Administration approved procedures for establishing fleet weight averages Far 21 327 f 2 46 100 15 000 17 400 16 500 91 200 14 000 26 000 16 500 761 72 115 1797 7 5 3 Weigh...

Page 196: ...tv ...

Page 197: ...V XX IPOWERPLANT IPROPELLER Typo A Agency s Name and Address XX US CartWoted Mechanic _ Foretan CwtWoatod l och ajc_ Ccrtfflcated Repair Stattorÿ XXER854K RADIO CLASS1 11 111 iTniNSTR Sÿ EXPRESSAVIONICS INC 11431 W AIRPORT SERVICE RD rT SWANTON OHIO 43558 1 vi doscrttxd onttw rover or atuclrmate ho to D certify m U S Federal Avledoo RosjdaUoneend me he ft s EZ22 2 i ajagamssash Date DECEMBER 19 20...

Page 198: ...ENT INSTALLEDPERFORMS ITSINTENDEDFUNCTION CONTINUED AIRWORTHINESSFOR THEEQUIPMENTINSTALLED IS ON CONDITION MANUFACTURER S CURRENTMAINTENANCEMANUALSFOR REPAIR So F0R REQUIRED REGARDING 32ÿÿF lÿf55CRAFI OR KR 87 n IGHTMANUALSUPPLEMENT 6 WAS PREVIOUSLY INSTALLED INTHE AIRCRAFTFLIGHTMANUAL BY THE AIRCRAFTMANUFACTURER REFERENCE EXPRESS AVIONICS INC WORK ORDER 8267 FOR FURTHER DETAILS CONCERNINGTHIS INS...

Page 199: ...t center of gravity range Arm measured to the center of the areas shown NOTES 1 The usable fuel C G arm for integral tanks is located at station 48 0 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 34 to 46 0585X1016 Figure 6 3...

Page 200: ...A MODEL 172R CABIN HEIGHT MEASUREMENTS DOOR OPENING DIMENSIONS WIDTH WIDTH HEIGHT HEIGHT TOP BOTTOM FRONT REAR CABIN DOORS 321 2 37 40I 2 39 BAGGAGE DOOR 151 4 151 4 22 21 0585X1023 Figure 6 4 Internal Cabin Dimensions Sheet 1 of 2 6 10 Feb 28 00 ...

Page 201: ...IIUIN b WEIGHT BALANCE EQUIPMENT LIST CABIN WIDTH MEASUREMENTS INSTRUMENT PANEL REAR DOORPOST BULKHEAD STATIONS C G ARMS N LWR WINDOW LINE CABIN FLOOR 0585X1023 Figure 6 4 Internal Cabin Dimensions Sheet 2 of 2 Dec 2 96 6 11 ...

Page 202: ...d Front Passenger Station 34 to 46 340 12 6 4 Rear Passengers 220 16 0 5 Baggage Area 1 Station 82 to 108 120 Lbs Max 48 3 4 6 Baggage Area 2 Station 108 to 142 50 Lbs Max 7 RAMP WEIGHT AND MOMENT add columns 2457 106 5 8 Fuel allowance for engine start taxi and runup 7 0 0 3 9 TAKEOFF WEIGHT AND MOMENT Subtract Step 8 from Step 7 2450 106 2 10 Locate thispoint 2450 at 106 2 on the Center of Gravi...

Page 203: ...ight lbs Moment Lb ins 1000 NOTE YOUR AIRPLANE Weight lbs Moment Lb ins 1000 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 Dec 2 96 6 13 ...

Page 204: ...METERS 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 Figure 6 6 Loading Graph 0S85C10C6 6 14 Nov 3 97 WEIGHT KILOGRAMS ...

Page 205: ...T LIST LOADED AIRPLANE MOMENT 1000 KILOGRAM MILLIMETERS 2500 1000 1100 1200 1300 1500 60 70 80 90 100 110 120 LOADED AIRPLANE MOMENT 1000 POUND INCHES 0585C1007 Figure 6 7 Center of Gravity Moment Envelope Feb 28 00 6 15 LOADED AIRPLANE WEIGHT KILOGRAMS ...

Page 206: ...LIMETERS AFT OF DATUM STA 0 0 875 925 _ 975 1025 1075 1125 1175 1225 2500 2400 g 2300 2200 2100 2000 1900 1800 1700 1600 1500 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 Pf Figure 6 8 Center of Gravity Limits 0585C1006 6 16 Feb 28 00 ...

Page 207: ...pment for FAA certification S standard equipment items O 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 ite...

Page 208: ...NAV COM w GS 066 01032 0201 3 5 12 5 Kl 208 NAV INDICATOR 066 03056 0002 1 0 13 9 VHF COM ANTENNA 3960113 8 0 5 61 2 COM ANTENNA CABLE 3921100 1 0 4 26 5 OMNI NAV ANTENNA 0 5 253 4 OMNI ANTENNA CO AX CABLE 1 5 123 8 HARDWARE AND CABLE ASSEMBLY 3921100 1 0 5 53 2 23 03 A NAV COM INSTALLATION WITH GS 3930404 1 6 5 17 1 KX 155A BENDIX KING NAV COM 066 01032 0201 4 0 12 5 w GS Kl 209 NAV INDICATOR 066...

Page 209: ... 34 3 41 5 25 05 0 SEAT FRONT PASSENGER VERTICAL AJUST LEATHER 0514211 5 35 0 41 5 25 06 0 SEAT FRONT PASSENGER VERTICAL AJUST LEATHER VINYL 0514211 8 34 8 41 5 25 07 S SEAT REAR ONE PIECE BACK CUSHION CLOTH 0514219 1 43 3 79 5 25 08 0 SEAT REAR ONE PIECE BACK CUSHION LEATHER 0514219 2 44 7 79 5 25 09 0 SEAT REAR ONE PIECE BACK CUSHION LEATHER VINYL 0514219 3 44 3 79 5 25 10 R SEAT BELT AND SHOULD...

Page 210: ...NTROLS INSTL RIGHT SEAT 0506008 1 5 5 12 4 CONTROL WHEEL RH 0513576 2 2 0 26 0 RUDDER BRAKE PEDAL INSTL RH 0510402 16 1 1 6 8 27 02 S CONTROL WHEEL MAP LIGHT AND MIC SWITCH INSTL INCLUDES PANEL MOUNTED AUXILIARY MIC JACK 28 FUEL 0560059 1 0 2 22 0 28 01 R FUEL QUANTITY INDICATORS LEFT RIGHT S3281 1 0 4 14 4 28 02 R AUXILIARY FUEL PUMP 31 INDICATING RECORDING SYSTEM 5100 00 1 1 9 9 5 31 01 S CLOCK ...

Page 211: ... 2 2 25 3 34 01 R INDICATOR AIRSPEED S3325 1 0 6 16 2 34 02 S ALTERNATE STATIC AIR SOURCE 0501017 1 0 2 15 5 34 03 R ALTIMETER WITH 20 FT MARKINGS INCHES OF MERCURY S3328 1 0 9 14 0 34 04 0 ALTIMETER WITH 20 FT MARKINGS FEET MILLIBAR S3371 1 0 9 14 0 34 05 S BLIND ALTITUDE ENCODER INSTL 3930402 1 0 9 11 0 34 06 R COMPASS INSTL MAGNETIC 0513262 2 0 5 14 0 34 07 S GYRO INSTALLATION REQUIREDS 37 01 S...

Page 212: ... FOR HSI INSTALLED 0501171 1 11 0 1 6 REMOVE 1 NAV INDICATOR 1 2 13 9 37 VACUUM 37 01 S VACUUM SYSTEM ENGINE DRIVEN DUAL 5 4 1 8 VACUUM PUMP AIRBORNE 211CC E211CC 1 9 6 5 VACUUM PUMP AIRBORNE 212CW E212CW 1 9 3 9 COOLING SHROUD AIRBORNE 2CDH 2CDH 0 1 6 5 COOLING SHROUD AIRBORNE 2CDH 2CDH 0 1 3 9 FILTER INSTALLATION 1201075 2 0 3 5 3 VACUUM GAGE AMMETER S3280 1 0 3 14 3 VACUUM RELIEF VALVE 2H3 48 0...

Page 213: ... 95 0 71 03 R ENGINE LYCOMING IO 360 L2A 0550359 2 297 8 18 6 FUEL INJECTOR PAC RSA 5AD1 7 6 13 9 MAGNETOS HARNESS SLICK 4371 9 0 5 0 SET OF 2 OIL FILTER AND ADAPTER 2 5 18 5 SPARKPLUGS 1 9 13 9 STARTER LAMAR 31B22207 11 2 23 0 73 ENGINE FUEL CONTROL 73 01 S EGT FUEL FLOW INDICATOR S3277 4 0 6 7 8 77 ENGINE INDICATING 77 01 R TACHOMETER RECORDING S3329 1 1 0 12 1 78 EXHAUST 78 01 R EXHAUST SYSTEM ...

Page 214: ...930404 1 6 5 17 1 34 09 A ADF INSTALLATION 3930404 1 10 4 26 9 34 10 A GLOBAL POSITIONING 4 4 15 3 SYSTEM GPS 98 03 A NAV II PACKAGE NET CHG OVER STD AVN PKG 3900005 1 29 9 25 9 98 02 A TRAINER AVN PKG 21 3 21 5 22 02 A SINGLE AXIS AUTOPILOT 8 6 36 8 GPS INSTALLATION 3930404 1 4 4 17 6 98 04 A NAV II PACKAGE WITH HSI NET CHG OVER STD AVN PKG 3900016 1 45 2 45 6 98 03 A NAV II PACKAGE 29 9 25 9 34 ...

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Page 216: ......

Page 217: ...ols 7 6 rTrimSystem 7 9 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 17 Control Locks 7 18 Feb 28 00 7 1 ...

Page 218: ...ystem Propeller Fuel System Fuel Distribution Fuel Indicating Fuel Venting Reduced Tank Capacity Fuel Selector Valve Fuel Drain Valves Brake System Electrical System Annunciator Panel Master Switch I Avionics Master Switch Ammeter Low Voltage Annunciation Circuit Breakers And Fuses Ground Service Plug Receptacle 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...

Page 219: ...acuum System And Instruments Attitude Indicator Directional Indicator Suction Gauge Low Vacuum Annunciation Clock OAT Gauge 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 43 ...

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Page 221: ... attach fittings at the base of the forward door posts for the lower attachment of the wing struts f 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 alu...

Page 222: ...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...

Page 223: ...CESSNA SECTION 7 MODEL 172R AIRPLANE SYSTEMS DESCRIPTION 0585X1017 Figure 7 1 Flight Control and Trim Systems Sheet 1 of 2 Dec 2 96 7 7 ...

Page 224: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTION CESSNA MODEL 172R ELEVATOR TRIM 7 8 Dec 2 96 ...

Page 225: ...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 oil temperature oil pressure indica...

Page 226: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTION CESSNA MODEL 172R 7 10 Revision 7 ...

Page 227: ... 19 Nav Com Radio 2 20 ADF Receiver 21 Transponder 22 ELT Remote Test Button 23 Hour Meter 24 GloveBox 25 Cabin Heat Control 26 Cabin Air Control 27 Flap Switch and Position Indicator 28 Mixture Control 29 Alternate Static Air Control 30 Throttle Control 31 Radio and Panel Dimming Control 32 Glareshield and Pedestal Dimming Control 33 Fuel Shutoff Valve Control 34 Fuel Selector 35 Elevator Trim Co...

Page 228: ...ately 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 ai...

Page 229: ...lever is moved up or down in a slotted panel that provides mechanical stops at the 10 20 and 30 positions To change flap setting the flap lever is moved to the right to clear mechanical stops at the 10 and 20 positions A scale and pointer to the left of the flap switch indicates flap travel in degrees The wing flap system circuit is protected by a 10 ampere circuit breaker labeled FLAP on the left...

Page 230: ...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...

Page 231: ...tive 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 a distinc...

Page 232: ...R VERTICAL HEIGHT ADJUSTMENT CRANK SEAT BACK ANGLE BUTTON FORE AND AFT ADJUSTMENT LEVER PRESS TO RELEASE PUSH BUTTON PUSH BUTTON RELEASE BUCKLE NON ADJUSTABLE LIFT TO RELEASE 0514T1004 Figure 7 4 Crew Seats Seat Belts and Shoulder Harnesses 7 16 Revision 8 ...

Page 233: ...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 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 to p...

Page 234: ... the window outward and ÿ N 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...

Page 235: ...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...

Page 236: ...m 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 engine...

Page 237: ...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...

Page 238: ...pring loaded START position with the master switch in the ON position the starter contactor is closed and the starter now energized will crank the engine When the switch is released it will automatically return 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 air...

Page 239: ...owl flap cooling system control is required PROPELLER The airplane is equipped with a two bladed fixed pitch one l piece forged aluminum alloy propeller which is anodized to retard corrosion The propeller is 75 inches in diameter FUEL SYSTEM The airplane fuel system see Figure 7 6 consists of two vented r integral fuel tanks one tank in each wing a three position selector valve auxiliary fuel pump...

Page 240: ...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 I Starting at serial number 17281188 and on and airplanes incorporating MK172 28 01 a fuel return system was added to promote sm...

Page 241: ...imately 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 r designed to report failures with each transmitter caused by shorts...

Page 242: ...able 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 _ in cruising flight unequal fuel flow from each tank may occur if the wings are not maintained exactly level Resulting wing heavine...

Page 243: ...FUEL TANK VENT WITH CHECK VALVE FUEL QUANTITY TRANSMITTER RIGHT FUEL TANK FUEL RESERVOIR TANK AUXILIARY FUEL PUMP FUEL SHUTOFF VALVE KNOB o tfr ENGINE DRIVEN FUEL PUMP hFUEL AIR CONTROL UNIT FUEL DISTRIBUTION VALVE 0585C1013 Figure 7 6 Fuel System Schematic Sheet 1 of 2 17280001 thru 17281187 Revision 8 7 27 7 27A ...

Page 244: ......

Page 245: ...RY FUEL PUMP AUXILIARY FUEL PUMPS SWITCH FUEL SHUTOFF VALVE KNOB FUEL CHECK pSl d SHUTOFF VALVE MJ v VALVE ENGINE DRIVEN FUEL PUMP FUEL STRAINER DRAIN VALVE LEGEND 1 FUEL SUPPLY VENT MECHANICAL LINKAGE ELECTRICAL CONNECTION FUEL DISTRIBUTION VALVE FUEL FLOW INDICATOR 05MH013A Figure 7 6 Fuel System Schematic Sheet 2 of 2 17281188 and On And airplanes incorporating MK172 28 01 Revision 9 7 27B ...

Page 246: ... system is equipped with 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 and the fuel strainer sump If any evidence of fuel contamination is found it must be eliminated in accordance with the Preflig...

Page 247: ...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 as req...

Page 248: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTION CESSNA MODEL 172R Figure 7 7 Electrical Schematic Serials 17280001 thru 17280983 Sheet 1 of 2 7 30 Dec 30 00 ...

Page 249: ...c o 3 WARN TO VARIOUS ANNUNCIATORS AVIONICS MASTER SWITCH TO GLARESHIELD 3ÿINTERIOR INÿT INSTRUMENT LIGHTS 3 LTS 3 ALT FLD TO MASTER SWITCH AVN BUS 2 3 m TO TURN COORDINATOR RD TO NAV AND CONTROL WHEEL NAV MAP LIGHTS TO STROBE ROBELIGHTS TAXI L J PITOT HEAT TO TAXI LIGHTS CM CO z CQ CO g z o W O GPS O TO AVIONICS FAN TO GPS 2 3 4 TO NAV COM1 AUDIO PANEL 1 3 TO AUTOPILOT 3 AUTO PILOT 0 ADF TO ADF 4...

Page 250: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTION CESSNA MODEL 172R V Figure 7 7A Electrical Schematic Serials 17280984 and On Sheet 1 of 2 7 30B Revision 7 ...

Page 251: ...PS MFD 0 TO HSI GYRO 0 TO NAV COMM 1 NAW AUDIOPANEL 1 COM 1 AVIONICS MASTER SWITCH AVN BUS 2 0 TO TURN TURN COORDINATOR COC ORD TONAVAND to CONTROL WHEEL NAV MAP LIGHTS TO INSTRUMENT LIGHTS 0 _ m y TO STROBE tu 1 r rr STROBE LIGHTS TO TAXI LIGHTS 0 NAV COM2 TO NAV COMM 2 AUDIOPANEL 2 0 TO TRANSPONDER XPNDR 0 AUTO PILOT 0 ADF TO AUTOPILOT TO ADF TAXI TO PITOT L JPHOT HEAT HEAT LEGEND 1 BASE 2 ALL O...

Page 252: ...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 The annunciator panel can b...

Page 253: ...AGING THE AVIONICS EQUIPMENT I 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 master switch must also be turned on The ALT side of the switch when placed in the OFF position removes the alternat...

Page 254: ...vionics 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 extern...

Page 255: ...may be reset by resetting the circuit breaker If the low voltage warning annunciator extinguishes normal alternator charging has resumed however if the annunciator illuminates again a malfunction has occurred and the flight should be terminated as soon as practical NOTE Illumination of the low voltage annunciator and ammeter discharge indications may occur during low RPM conditions with an electri...

Page 256: ...uit 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 avi...

Page 257: ...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 combination ...

Page 258: ...plished 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 coun...

Page 259: ...N 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 f...

Page 260: ...SNA MODEL 172R EXHAUST MUFFLER SHROUD CABIN AIR CONTROL CABIN HEAT CONTROL DEFROSTER OUTLETS 2ÿ FORWARD CABIN LOWER VENTILATING AIR OUTLET RAM AIR HEATER VALVE 0585C1015 Figure 7 8 Cabin Heating Ventilating and Defrosting System 7 40 Feb 28 97 ...

Page 261: ...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...

Page 262: ... KIAS include the white arc 33 to 85 knots green arc 44 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 b...

Page 263: ...al 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 co...

Page 264: ... MODEL 172R CODE INLET AIR VACUUM 2 DISCHARGE AIR OVERBOARD VENT LINES PUMPS VACUUM SYSTEM AIR FILTER LOW VACUUM SWITCHES CONNECTED TO ANNUNCIATOR PANEL MANIFOLD S CHECK VALVE DIRECTIONAL INDICATOR 0585C1014 Figure 7 9 Vacuum System 7 44 Dec 2 96 ...

Page 265: ...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 ...

Page 266: ...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...

Page 267: ...ts 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 control...

Page 268: ...ious 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 the...

Page 269: ...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 5B C If installed the extinguisher should be checked prior to each flight to ensure that its bottle pressure as indicated by the ...

Page 270: ...L DECOMPOSITION 3 Anticipate 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 Revision 8 ...

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Page 273: ...ns Airplane File Airplane Inspection Periods FAA Required Inspections Cessna Inspection Programs Cessna Customer Care Program Pilot Conducted Preventive Maintenance Alterations Or Repairs Ground Handling Towing Parking Tie Down Jacking Leveling Flyable Storage Servicing Oil Oil Specification Recommended Viscosity for Temperature Range 8 3 8 4 8 4 8 5 8 5 8 5 8 6 8 7 8 7 8 8 8 8 8 9 8 9 8 1Ol 8 10 ...

Page 274: ...8 15 Oil and Oil Filter Change 8 1 Fuel 8 16 Approved Fuel Grades and Colors 8 16 Fuel Capacity 8 16 Fuel Additives 8 16 Fuel Contamination 8 20 v Landing Gear 8 21 Cleaning And Care 8 21 Windshield And Windows 8 21 Painted Surfaces 8 22 m Propeller Care 8 23 J Engine Care 8 23 Interior Care 8 24 8 2 Feb 28 00 ...

Page 275: ...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 ...

Page 276: ... 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 r...

Page 277: ...visories 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 rsenta 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 airplan...

Page 278: ...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 I Approved Airplane Flight Manual is identified for specific serial numbered airplanes only AIRPLANE FILE There are miscellan...

Page 279: ...nts r 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 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 annual inspection aircraft operated commercially for hir...

Page 280: ...t hours whichever occurs first the airplane undergoes a complete Phase 3 inspection Regardless of the inspection method selected the owner should keep in mind that FAR Part 43 and FAR Part 91 establishes the requirement that properly certified agencies or personnel accomplish all required FAA inspections and most of the manufacturer recommended inspections CESSNA CUSTOMER CARE PROGRAM Specific ben...

Page 281: ...nce that may be performed by pilots A Maintenance Manual must be obtained prior to performing any preventive maintenance to ensure that proper procedures are followed Your local Cessna Service Station should be contacted for further information or for required maintenance which must be accomplished by appropriately licensed personnel ALTERATIONS OR REPAIRS It is essential that the FAA be contacted...

Page 282: ...he normal cushioning action of the nose strut does not cause excessive vertical movement of the tail and the resulting contact with low hangar doors or structure A flat nose tire or deflated strut will also increase tail height When parking the airplane head into the wind and set the parking brakes Do not set the parking brakes during cold weather when accumulated moisture may freeze the brakes or...

Page 283: ...anual for specific procedures and equipment required Individual main gear may be jacked by using the jack pad which is incorporated in the main landing gear strut step bracket When using the individual gear strut jack pad flexibility of the gear strut rwillcause the main wheel to slide inboard as the wheel is raised tilting the jack The jack must then be lowered for a second jacking operation Do n...

Page 284: ... 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 ÿ door sills may be used to level the airplane laterally FLYABLE STORAGE Airplanes placed in non operational storage for a maximum of 30 days or those which receive only intermittent operational use for the first 25 hours...

Page 285: ...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...

Page 286: ...ll the engine and continue to use until a total of 50 hours has accumulated or oil consumption has stabilized MIL L 22851 or SAE J1899 Aviation Grade Ashless 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 Multiv...

Page 287: ...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...

Page 288: ...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...

Page 289: ...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...

Page 290: ...SECTION 8 HANDLING SERVICE MAINTENANCE CESSNA MODEL 172R Figure 8 1 Fuel Mixing Ratio 18 18 Feb 28 00 ...

Page 291: ...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 RECOMMENDED 0 10 BY TOTAL VOLUME MINIMUM WILL RESULT IN INEFFECTIVE TREATMENT USE ONLY BLENDING EQUIPMENT THAT IS RECOMMENDED BY THE MANUFACTURE...

Page 292: ...ed 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 contamina...

Page 293: ...CLEANING AND CARE WINDSHIELD AND WINDOWS The plastic windshield and windows should be cleaned with an aircraft windshield cleaner Apply the cleaner sparingly with soft cloths and rub with moderate pressure until all dirt oil scum and bug stains are removed Allow the cleaner to dry then wipe it off with soft flannel cloths CAUTION NEVER USE GASOLINE BENZENE ALCOHOL ACETONE FIRE EXTINGUISHER ANTI IC...

Page 294: ...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 graphics refer to the Maintenance Manual To seal any minor surface chips or scratches and protect against corrosion the air...

Page 295: ... 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 The engine may be cleaned using a suitable solvent in accordance with instructions i...

Page 296: ...n 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 to...

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Page 299: ...ed in the airplane at all times when tbc Gannin 400WSeries unit b installed in accordance with STC SA01933LA D The information contained herein supplements orsupersedes the information made available to the operator by the manufacturer in the form of clearly stated placards markings or manualsor in the form of an FAA approved Airplane Right Manual only in those areas listed herein For imitations p...

Page 300: ......

Page 301: ... Navigation System LOG OF REVISIONS Rev No No egc Date Description FAA Approved A Original All 11 20 07 Complete Supplement Scvcd Youjjef Hashemi Mgr FlL Test Br ANM 160L FAA Los Angeles ACO Transport Airplane Directorate Date Nov 20 2007 B All 7f h Added D ID STC number added LP approach typo QUA STCU fifA3a ntsCrBtor dnAÿ2 0C 7CE Garmin International Inc 190 00356 03 Rev B Page 2 of 16 ...

Page 302: ......

Page 303: ...Database 7 2 5 Navigation 8 2 6 Approaches 8 2 7 Autopilot Coupling 9 2 8 Terrain Display 9 2 9 VNAV 9 2 10 Weather Display 9 2 11 Traffic Display 10 Section 3 EMERGENCY PROCEDURES 11 3 1 Emergency Procedures 11 3 2 Abnormal Procedures 11 Section 4 NORMAL PROCEDURES 13 4 1 Approaches with Vertical Guidance 13 4 2 Approaches without Vertical Guidance 14 For additional information on LP approaches r...

Page 304: ......

Page 305: ...y The 400W Series unit features a graphical display which may also be used to depict traffic weather or terrain data The navigation functions are operated by dedicated keys and graphical menus which are controlled by the buttons and the dual concentric rotary knob along the bottom and right side of the display Optional VHF Com and VHF Nav radio functions are controlled via dedicated buttons and kn...

Page 306: ......

Page 307: ...d in conjunction with WAASGarmin Prediction Program part number 006 A0154 03 Oceanic operations arc supported when the 400W Series unit annunciates OCN This provides an alarm limit of four NMI and a mask angle of five degrees The 400W series unit also has the ability to predict RAIM availability at any waypoint in the database or if WAAS corrections arc expected to be absent or disabled This AFMS ...

Page 308: ......

Page 309: ...t approval for IFR operations to aircraft limited to VFR operations Additional aircraft systems may be required for IFR operational approval Systems limited to VFR shall be placarded in close proximity to the 400W Series unit GPS LIMITED TO VFR USE ONLY 2 2 System Software The system must utilize the Main and GPS software versions listed below or later FAA approved versions The software versions a...

Page 310: ......

Page 311: ...hed in accordance with an approved instrument approach procedure that is loaded from the 400W Series unit database c Installations with dual 400W 500W Series units will only crossfill between units when they contain the same databasecycle Updating of each database must be accomplished on the ground prior to flight 2 4 Terrain Database The 400W Series unit supportsTerrain and requires a Terrain dat...

Page 312: ......

Page 313: ...DA SDF MLS VOR approach or any other type of approach not approved for GPS overlay is not authorized with GPS navigation guidance d Use of the GNS 430W VOR LOC GS receiver to fly approaches not approved for GPS requires VOR LOC GS navigation data to be present on the external indicator i c proper CD1 source selection c For aircraft with remote source selection annunciation or remote GPS navigation...

Page 314: ......

Page 315: ...y be coupled to the autopilot without any limitations This limitation may be removed after an FAA Flight Test demonstration Contact Garmin International Tech Support for additional information 2 8 Terrain Display Terrain refers to thedisplay of terrain information Pilots arc NOT authorized to deviate from their current ATC clearance to comply with tcrTain obstaclc alerts Terrain unit alerts arc ad...

Page 316: ......

Page 317: ...u of an official weather data source 2 11 Traffic Display Traffic may be displayed on the 400W Series unit when connected to an approved optional TCAS TAS or TIS traffic device These systems arc capable of providing traffic monitoring and alerting to the pilot Traffic shown on the display may or may not have traffic alerting available The display of traffic is an aid to visual acquisition and may ...

Page 318: ...V J ...

Page 319: ...a Loss of Integrity INTEG message is displayed during Enroutc Tcmtinal continue to navigate using GPS equipment and periodically cross check the GPS guidance to other approved means of navigation GPS Approach GPS approaches arc not authorized under INTEG Execute missed approach or revert to alternate navigation c Duringa GPS LPV precision approach or GPS LNAV VNAV approach the 400W Series unit wil...

Page 320: ......

Page 321: ...ed c During any GPS approach in which precision and non precision alarm limitsare exceeded the 4COW Series unit will flag the lateral guidance and generate a system message ABORT APPROACH loss of navigation Immediately upon viewing the message the unit will revert to Terminal alarm limits If the position integrity is within these limits lateral guidance will be restored and the GPS may be used to ...

Page 322: ......

Page 323: ...e unit in an IFR environment particularly without the autopilot engaged Garmin provides excellent training tools with the Pilot s Guide and PC based simulator Pilots should take full advantage of these training tools to enhance system familiarization Use of an autopilot is strongly encouraged when using the 400W Series unit in IMCconditions 4 1 Approaches with Vertical Guidance The 400W Series uni...

Page 324: ......

Page 325: ...I is used with GPSS engaged the pilot should rotate the course pointer as prompted on the 400W Scries unit to prevent loss of situational awareness and to prevent the aircraft from turning inappropriately if the autopilot is switched from digital GPSS to analog mode For autopilot operational instructions refer to the FAA approved Flight Manual or Flight Manual Supplement for the autopilot 4 4 Coup...

Page 326: ......

Page 327: ...ilot to enable the A P outputs just prior to engaging the autopilot in APR mode This installation supports a seamless transition from digital GPSS to analog guidance for the autopilot To capture the vertical guidance the pilot may engage the autopilot in APR mode at any time when the GPS GlideSlope VDI becomes valid displayed without a FLAG This installation interfaces to theautopilot in analog mo...

Page 328: ......

Page 329: ...ction Program is required for Remotc Occanic operations The Prediction Program should be used in conjunction with the Garmin 400W 500W Simulator After entering the intended route of Right in the Simulator light plan the pilot selects the FDE Prediction Program under the Options menu of the Simulator program For detailed information refer to the WFDE prediction program instructions 190 00643 01 The...

Page 330: ......

Page 331: ...NS 400W 500W Series SW v3 30 Upgrade Supplement Garmin P N 190 0356 34 GNS 400W 500W Series SW v3 20 Upgrade Supplement Garmin P N 190 0356 33 GNS 400W 500W Series SW v3 00 Upgrade Supplement Garmin P N 190 0356 32 GNS 400W 500W Series Pilot s Guide Reference any Revision GNS 400W 500W Series Garmin Optional Displays Addendum any Revi sion GNS 400W 500W Series Display Interfaces Addendum any Revis...

Page 332: ......

Page 333: ... bot tom of the screen 3 As the distance DIST to the IAF approaches zero the message is replaced by a time to turn advisory that counts down 10 seconds prior to the turn 4 As you approach the FAF the 500W series unit will begin to automati cally rescale in an angular fashion This will allow the LP approach to be flown in the same fashion as a standard localizer approach At 2 0 nautical miles from ...

Page 334: ......

Page 335: ...age Arriving at Waypoint appears on the bottom of the screen 9 At the MAP initiate the missed approach if necessary Once the 500W series unit crosses the MAP sequencing will be suspended Prepare the aircraft for missed approach operation Press the OBS key to sequence to the Missed Approach procedure NOTE For missed approaches with heading legs fly manually until the first active course leg is reac...

Page 336: ......

Page 337: ...e Canada 2009 GARMIN Corporation GARMIN International Inc 1200 East 151 Street Olathe Kansas 66062 U S A Tel 913 397 8200 or 800 800 1020 Fax 913 397 8282 GarminAT Inc 2345Turner Rd S E Salem Oregon 97302 U S A Tel 503 581 8101 or 800 525 6726 Fax 503 364 2138 Garmin Europe Ltd Liberty House Bulls Copse Road Hounsdown Business Park Southhampton SO40 9RB U K Tel 44 0 870 850 1243 Fax 44 0 238052 40...

Page 338: ... ...

Page 339: ...TE VERSION BY CONTACTING CESSNA CUSTOMER SUPPORT AT 316 517 5800 SUPP NO SUPPLEMENT NAME REVISION EQUIPMENT LEVEL INSTALLED 1 Bendix King KX 155A VHF NAV COMM with Kl 208 or Kl 209A Indicator Head 1 2 Bendix King KT 76C Transponder with Blind Encoder 1 3 Bendix King KMA 26 Audio Selector Panel 1 4 Pointer Model 3000 11 or Model 4000 11 Emergency Locator Transmitter ELT 3 5 Bendix King KLN 89B Glob...

Page 340: ...endix King KAP 140 2 Axis Autopilot 16 Reserved 17 Reserved 18 Reserved 19 Bendix King KLN 94 Global Positioning System 20 Bendix King KMA 28 Audio Selector Panel 21 Bendix King KMD 550 Multi Function Display 22 12 Volt Cabin Power System 24 Astrotech Model TC 2 Clock OAT Volt Indicator 25 Bendix King KX 165A VHF NAV COM 26 Bendix King KDR 510 Flight Information Services FIS REVISION EQUIPMENT LEV...

Page 341: ...le supplements have been placed in the 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 supplements must be retained and updated as revisions to each supplement s are issued Each individual supplement contains its own Log of Effective Pages This log lists the page number and effective date of e...

Page 342: ......

Page 343: ...ll applicable supplements have been placed in the Pilot s Operating Handbook POH Supplements may be removed from the POH r provided the equipment is not installed on the airplane If equipment is installed on the airplane however the supplement s must be retained and updated as revisions to each supplement are issued Each individual supplement contains its own Log of Effective Pages This log lists ...

Page 344: ......

Page 345: ...EAD SERIAL NO _ REGISTRATION NO This supplement must be inserted into Section 9 of the Pilofs Operating Handbook and FAA Approved Airplane Flight Manual FAA APPROVAL PAA APPROVEDUNDER FAR 21SUBPARTJ TheCessna AircraftCo ationOption ManufacturerCE 1 ExecutiveBijweer Data 3 April 2000 COPYRIGHT 1996 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA Member of GAMA 2 December 1996 Revision 1 28 February 2000...

Page 346: ...OG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S1 1 Feb 28 00 S1 9 Dec 2 96 S1 2 Feb 28 00 S1 10 Dec 2 96 S1 3 Feb 28 00 S1 11 Dec 2 96 S1 4 Dec 2 96 S1 12 Dec 2 96 S1 5 Dec 2 96 S1 13 Feb 28 00 S1 6 Dec 2 96 S1 14 Dec 2 96 S1 7 Dec 2 96 S1 15 Dec 2 96 S1 8 Feb 28 00 S1 16 Blank Dec 2 96 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to tiie...

Page 347: ... localizer signals between 108 00 and 117 95 MHz in 50 kHz steps The glide slope receiver is automatically tuned when a localizer frequency is selected The circuits required to interpret the VOR and localizer signals are also an integral part of the Nav receiver Large self dimming gas discharge readouts display both the communications and navigation operating frequencies The KX 155A s flip flop pr...

Page 348: ...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...

Page 349: ...ft CESSNA MODEL 172R SECTION 9 SUPPLEMENTS SUPPLEMENT 1 FAA APPROVED Figure 1 Bendix King KX 155A VHF NAV COMM with Kl 208 or Kl 209A Indicator Head Sheet 1 of 7 Dec 2 96 S1 5 ...

Page 350: ...DI FORMAT ID3 ED l 090 1 _ FLAG I VOR MODE ACTIVE BEARING FLAG DISPLAY _ 109 ED 090n VOR MODE ACTIVE BEARING TO FUNCTION DISPLAY 103 ED T0 VOR MODE ACTIVE BEARING FLAG DISPLAY 110 30 LOO LOCALIZER MODE FREQUENCY CDI FORMAT Figure 1 Bendix King KX 155A VHF NAV COMM with Kl 208 or Kl 209A Indicator Head Sheet 2 of 7 S1 6 Dec 2 96 ...

Page 351: ...adial from the VOR station or a count up count down timer With an active localizer frequency this portion of the display shows the standby frequency the letters LOC or count up count down timer 4 NAV FREQUENCY SELECTOR KNOB SMALL Operates in 50 kHz steps The NAV receiver s lower and upper frequency limits are 108 00 MHz and 117 95 MHz Exceeding the upper limit of frequency band will automatically ...

Page 352: ...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 frequency area is replaced by LOC When the received sign...

Page 353: ...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...

Page 354: ...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...

Page 355: ...to 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 PULL TEST Rotate...

Page 356: ...OMM 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 COMMUNICATION RECEIVER TRANSMITTER OPERATION 1 OFF PULLJTEST 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 ...

Page 357: ...3 Speaker Selector on audio control panel SET to desired mode 4 NAV Volume Control a ADJUST to desired audio level b PULL out to identify station VOR OPERATION Channel the NAV Receiver to the 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 ...

Page 358: ... 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...

Page 359: ...onfiguration mode The NAV returns to its pre Pilot Config state with the new brightness and sidetone levels stored in nonvolatile memory SECTION 5 PERFORMANCE r There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or several related antennas will result in a minor reduction in cruise performance r Dec 2 96...

Page 360: ......

Page 361: ... _ REGISTRATION NO This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual FAA APPROVAL FAAAPPROVEDUNDER FAR 21SU8PARTJ TheCessna AircraftCo 10ption ManufacturerCS 1 ExecutiveEnsweer Date 3 April 2000 COPYRIGHT 1996 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA Member of GAMA 2 December 1996 Revision 1 28 February 2000 S2 1 172RPHUS S2...

Page 362: ...Original 1 Dec 2 1996 Feb 28 2000 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S2 1 Feb 28 00 S2 6 Feb 28 00 S2 2 Feb 28 00 S2 7 Feb 28 00 S2 3 Feb 28 00 S2 8 Dec 2 96 S2 4 Dec 2 96 S2 9 Dec 2 96 S2 5 Dec 2 96 S2 10 Blank Dec 2 96 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that the operation of the aiiplane and have been this supplement This list contain...

Page 363: ...eives 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 con...

Page 364: ...preprogram any single code such as 1200 into the KT 76C Pressing the VFR button instantly returns the KT 76C to the preprogrammed code without having to manually enter 1200 All Bendix King Transponder operating controls are located on the front panel of the unit Functions of the operating controls are described in Figure 1 S2 4 Dec 2 96 ...

Page 365: ...s in hundreds of feet FL is annunciated to indicate Flight Level altitude Flight Level is a term to indicate that the altitude is not true altitude but barometric altitude which is not corrected for local pressure For Example FL 040 corresponds to an altitude of 4000 feet meaning sea level pressure of 29 92 inches of mercury The Flight Level altitude is only displayed when the altitude reporting i...

Page 366: ...ables transponder to transmit Mode A aircraft identification reply pulses ON is annunciated ALT Turns set on and enables transponder to transmit either Mode A aircraft identification reply pulses and Mode C altitude reporting pulses selected automatically by the interrogating signal ALT is annunciated 6 VFR CODE BUTTON VFR Pressing the VFR Button will cause a pre programmed Mode A reply code to su...

Page 367: ...GENCY SIGNAL 1 Mode Selector Knob ALT 2 Numeric Keys 0 7 SELECT 7700 operating code TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL CO MUNICATIONS 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 SELEC...

Page 368: ...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 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 panel is...

Page 369: ...de Button PRESS while still holding IDT button to place new VFR code in nonvolatile memory for subsequent call up SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or related external antennas will result in a minor reduction in cruise performance Dec 2 96 S2 9 S2 10 Blank ...

Page 370: ......

Page 371: ...ER 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 FAAAPPROVEDUNDER FAR 21SUBPARTJ The Cessna Aircraft Co Delegation OptionManufacturerCE 1 ExecutiveEngineer COPYRIGHT 1936 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA Member of GAMA 2 December 1996 Revision 2 28 February 2000 S4 1 172RP...

Page 372: ... 0 Original 1 2 Dec 2 1996 Nov 3 1997 Feb 28 2000 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S4 1 Feb 28 00 S4 6 Feb 28 00 S4 2 Feb 28 00 S4 7 Feb 28 00 S4 3 Feb 28 00 S4 8 Feb 28 00 S4 4 Feb 28 00 S4 9 Feb 28 00 S4 5 Feb 28 00 S4 10 blank Feb 28 00 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the aiiplane and have...

Page 373: ... 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 r General aviation and commercial aircraft the FAA and CAP monitor 121 5 MHz and 243 ...

Page 374: ...l on the transmitter ON A U T O E L T RESET 2685P6012 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...

Page 375: ...at the transmitter is transmitting 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 Figure 2 Pointer Model 4000 11 Emergency Locator Transmitter ELT 1 REMOTE CABLE JACK Connects to ELT ...

Page 376: ...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...

Page 377: ...ition 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 warbl...

Page 378: ...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 INSPECTION TEST 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...

Page 379: ...ssist 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 maximum signal strength 4 Your flight altitude and frequency on which the emergency signal was heard 121 5 MHz or 2...

Page 380: ...r ...

Page 381: ...ment 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 FAA APPROVEDUNDER FAR 21 SUBPARTJ TheCessna AircraftCo iOption ManufacturerCE 1 ExecutiveEngineer Date 3 April 2000 COPYRIGHT e 1996 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 9 Member of GAMA 2 December 1996 Revision 1 28 Febr...

Page 382: ...ec 2 1996 Feb 28 2000 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S6 1 Feb 28 00 S6 7 Dec 2 96 S6 2 Feb 28 00 S6 8 Dec 2 96 S6 3 Feb 28 00 S6 9 Dec 2 96 S6 4 Dec 2 96 S6 10 Dec 2 96 S6 5 Dec 2 96 S6 11 Feb 28 00 S6 6 Dec 2 96 S6 12 Dec 2 96 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...

Page 383: ... 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...

Page 384: ...SECTION 9 SUPPLEMENTS SUPPLEMENT 6 FAA APPROVED CESSNA MODEL 172R Figure 1 KR 87 Automatic Direction Finder ADF Sheet 1 of 4 S6 4 Dec 2 96 ...

Page 385: ...r 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 freque...

Page 386: ...r clockwise rotation increases audio level Audio muting causes the audio output to be muted unless the receiver is locked on a valid station 8 SET RESET ELAPSED TIMER BUTTON SET RST The set reset button when pressed resets the elapsed timer whether it is being displayed or not 9 FLIGHT TIMER ELAPSED TIMER MODE SELECTOR BUTTON FLT ET The Right Timer Elapsed Time mode selector button when pressed al...

Page 387: ...INTER Indicates relative or magnetic bearing to station as selected by HDG knob If the relative heading of North N is manually selected under the lubber line by the pilot then the bearing pointer indicates the relative bearing to the station If the aircraft s magnetic heading is selected under the lubber line by the pilot then the bearing pointer indicates the magnetic bearing to the station 16 HE...

Page 388: ... on audio control panel SELECT as desired 5 OFF VOL 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 note pointer moves to 90 position 2 ADF Button SELECT ADF mode and note the pointer moves without hesitation to the station be...

Page 389: ...Button PRESS once or twice until FLT is annunciated Timer will already be counting since it is activated by turning the unit on 3 OFF VOL Control OFF and then ON if it is desired to reset the flight timer TO OPERATE AS A COMMUNICATIONS RECEIVER ONLY l 1 OFF VOL Control ON 2 ADF Button SELECT ANT mode 3 Frequency Selector Knobs SELECT desired frequency in the standby frequency display 4 FRQ Button ...

Page 390: ... 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 Selector knobs remain in the time set mode for 15 seconds after the last entry or until the SET RST FLT ET or FRQ button is pres...

Page 391: ...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...

Page 392: ... SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or related external antennas will result in a minor reduction in cruise performance S6 12 Dec 2 96 ...

Page 393: ...nt 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 PAA APPROVEDUNDER FAR 21 SUBPARTJ TheCessna Aircraft Co Delegation Option ManufacturerCE 1 ExecutivoEngineer Dale 3 April 2000 COPYRIGHT 1996 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA Member of GAMA 2 DECEMBER 1996 Revision 4...

Page 394: ...receeding the page number Supplement Status Date Original Issue 2 December 1996 Revision 1 28 February 1997 Revision 2 3 November 1997 Revision 3 28 February 2000 Revision 4 31 October 2002 LOG OF EFFECTIVE PAGES Page Page Revision Status Number Title S7 1 Revised 4 S7 1 thru S7 5 Revised 4 S7 6 thru S7 7 Revised 3 S7 8 thru S7 19 Revised 4 S7 20 Added 4 APPROVED BY MA APPROVEDUNDERMR218UBWRTJ Oti...

Page 395: ...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 Serial Revision Incorporated Number Title Effectivitv Incorporation In Airplane KC 140 M1 KAP140AP Revision 4 Honeywell Service Bulletin Revision 4 S7 3 S7 4 blank ...

Page 396: ......

Page 397: ...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...

Page 398: ...72R The following circuit breakers are used to protect the listed elements of the KAP 140 single axis autopilot LABEL FUNCTIONS AUTO Supplies power to the KC 140 PILOT Computer and the autopilot WARN Supplies power to the autopilot disconnect tone S7 6 Revision 3 ...

Page 399: ...CESSNA MODEL 172R SECTION 9 SUPPLEMENTS SUPPLEMENT 7 FAA APPROVED NAV COMM 1 CONTROL PANEL QPS and Indicators Sheet 1 of 3 Revision 3 S7 7 ...

Page 400: ...n 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 17280001 thru 17281118 not incorporating Honeyw...

Page 401: ...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...

Page 402: ... 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 com...

Page 403: ... 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 TH...

Page 404: ...l and press and hold down the A P DISC switch throughout the recovery Manipulate the controls as required to safely maintain operation of the airplane within all of its operating limitations 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...

Page 405: ...ready 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 provid...

Page 406: ...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...

Page 407: ...g 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 auto...

Page 408: ... 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 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 I I 1 If the Course Deviation Bar D Bar is gre...

Page 409: ...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 cours...

Page 410: ...ARM 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 re...

Page 411: ...an 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 CDI needle is less than 2 to 3 dots from center the HDG mode will disengage upon selecting REV mode the REV annunciator will illuminiate and the capture track sequence will automat...

Page 412: ...matically begin d Airspeed MAINTAIN 90 KIAS during autopilot ap proaches recommended MISSED APPROACH 1 A P 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 A P DISC Switch PRESS to disengage AP SECTION 5 PERFORMANCE There is no change to the airplane performance when t...

Page 413: ...t 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 PAA APPROVEDUNDER FAR 21SUSPARTJ TheCessna AircraftCo DelegationOption ManufacturerCE 1 Execute Engine Date 3 April 2000 COPYRIGHT 0 1997 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA Member of GAMA 28 February 1997 Revision 1 28 February 2000 S8 ...

Page 414: ...evision Level Dale of Issue 0 Original 1 Feb 28 1997 Feb 28 2000 LOG OF EFFECTIVITY PAGES PAGE Title S8 1 S8 2 S8 3 S8 4 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that are currently active Airplane Unit Revision ...

Page 415: ...quipment 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 O A T EXCEEDS 20 F ...

Page 416: ... the airplane emergency procedures when the winterization kit is installed SECTION 4 NORMAL PROCEDURES There is no change to the airplane normal procedures when the winterization kit is installed SECTION 5 PERFORMANCE There is no change to the airplane performance when the winterization kit is installed S8 4 Feb 28 97 ...

Page 417: ...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 FAA APPROVEDUNDER FAR 21SUBPARTJ TheCessna Aircraft Co ationOptionManufacturerCE 1 ExecuthroEnjineer Date 3 April 2000 COPYRIGHT 1997 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 9 Member of GAMA 28 February 1997 Revision 2 28 February 2000 ...

Page 418: ...te of Issue 0 Original 1 2 Feb 28 1997 Nov 3 1997 Feb 28 2000 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S9 1 Feb 28 00 S9 4 Feb 28 97 S9 2 Feb 28 00 S9 5 Feb 28 00 S9 3 Feb 28 97 S9 6 Feb 28 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 list conta...

Page 419: ...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 A 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 fun...

Page 420: ...n is indicated by the display 88 88 and activation of all four annunciators O A T VOLTMETER OPERATION The upper portion of the LCD window is dedicated to O A T and voltmeter operations The voltmeter reading is preselected upon startup and is indicated by an E following the display reading Pushing the upper control button will sequence the window from voltage to fahrenheit F to centigrade C and bac...

Page 421: ...h r 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 JP S will resume its normal flashing indicating the clock is running in t universal time mode SETTING LOCAL TIME f iPN Use the SELECT ...

Page 422: ...ain 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 SELE...

Page 423: ...ment 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 FAA APPROVEDUNDER FAR 21SUBPARTJ TheCessna AircraftCo iOption ManufacturerCE 1 ExecutiveEngineer Date 3 April 2000 COPYRIGHT 1997 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA Member of GAMA 28 February 1997 Revision 1 28 February 2000 S12 1 172R...

Page 424: ...evision Level Date of Issue 0 Original 1 Feb 28 1997 Feb 28 2000 LOG OF EFFECTMTY PAGES PAGE DATE PAGE DATE Title S12 1 Feb 28 00 S12 3 Feb 28 00 S12 2 Feb 28 00 S12 4 Feb 28 97 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bu...

Page 425: ...s supplement is required for Canadian operation of Cessna Model 172R SECTION 2 LIMITATIONS The following placard must be installed 1 Near the fuel tank filler cap FUEL 100LL 100 MIN GRADE AVIATION GASOLINE CAP 26 5 U S GAL 100 LITRES USABLE CAP 17 5 U S GAL 66 LITRES USABLE TO BOTTOM OF FILLER INDICATOR TAB S12 3 Feb 28 00 ...

Page 426: ...ge to the airplane emergency procedures when used for Canadian operation SECTION 4 NORMAL PROCEDURES There is no change to basic airplane normal operating procedures when used for Canadian operation SECTION 5 PERFORMANCE There is no change to the airplane performance when used for Canadian operation S12 4 Feb 28 97 ...

Page 427: ...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 FAA APPROVAL WA APPROVEDUNDER FAR21 5U8FWTJ _ ThoCoctnaAircraftCo OC 03fionOption AuthorizationDOA W012WC ExocuOw Englnogr Date January 9 2001 COPYRIGHT 2000 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA Member of GAMA 30 December 2000 172RPHUS S15...

Page 428: ...n 2 31 October 2002 LOG OF EFFECTIVE PAGES Page Page Revision Status Number Title S15 1 Revised 2 S15 2 Revised 2 S15 3 S15 4 Revised 1 S15 5 thru S15 7 Revised 1 S15 8 thru S15 11 Revised 2 S15 12 thru S15 13 Revised 1 S15 14 thru S15 19 Original Issue 0 S15 20 Revised 1 S15 20A Added 1 S15 20B Added 1 S15 21 Revised 2 S15 22 Original Issue 0 S15 23 Revised 2 S15 24 thru S15 26 Original Issue 0 S...

Page 429: ...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 Serial Revision Incorporated Effectivity InsamaafigB In Airplane KC 140 M1 KAP 140 AP Honeywell Service Bulletin Revision 1 r Revision 1 S15 3 S15 4 ...

Page 430: ......

Page 431: ...e Preselect capabilities The KAP 140 2 Axis Autopilot has an electric trim system which provides autotrim during autopilot operation and manual electric trim MET for the pilot when the autopilot is not engaged The electric trim system is designed to be fail safe for any single in flight trim malfunction Trim faults are visually and aurally annunciated A lockout device prevents autopilot or MET eng...

Page 432: ...f A P DISC TRIM INT control wheel switch will also disconnect the autopilot The AVIONICS MASTER switch supplies power to the avionics bus bar of the radio circuit breakers and the autopilot circuit breaker The AVIONICS MASTER switch also serves as an emergency AP MET shutoff The following circuit breakers are used to protect the KAP 140 2 Axis Autopilot LABEL FUNCTIONS AUTO PILOT WARN Pull off cir...

Page 433: ...72R SECTION 9 SUPPLEMENTS SUPPLEMENT 15 FAA APPROVED NAV COMM 1 mmHff rifaO 32s TURN COORDINATOR O 10 BUS JQ ELECTRICAQ WARN BLJS C B 07851026 Figure 1 Bendix King 2 Axis KAP 140 Autopilot Schematic Revision 1 S15 7 ...

Page 434: ...ctions 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 failure of the roll axis and disenga...

Page 435: ...ture 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 ap...

Page 436: ...500 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 A P DISC TRIM INT SWITCH When depressed will disengage the autopilot and interrupt ...

Page 437: ...tisfied the request for trim for a period of 10 seconds A solid j 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 ...

Page 438: ...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 change the baro setting display from IN HG to HPA or...

Page 439: ... 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 ...

Page 440: ...H OFF EMG state of the KMA 28 will prevent flight control system alerts from being heard 5 The system is approved for Category I operation 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 oper...

Page 441: ...reaker 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 through 1C above then turn the 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 avionics equip...

Page 442: ...ol of the airplane Immediately grasp the control wheel and press and hold down the A P DISC TRIM INT switch throughout the recovery Manipulate the controls as required to safely maintain operation of the airplane within all of its operating limitations Elevator trim should be used manually as needed to relieve control forces Locate and pull the AUTO PILOT circuit breaker on the right hand circuit ...

Page 443: ...ulled Return the AVIONICS MASTER switch to the ON position as soon as possible With the AVIONICS MASTER switch off all avionics and autopilot equipment will be inoperable 5 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 oper...

Page 444: ...lamp was the result of some abnormal accelerations on the airplane the annunciation should be extinguished within approximately one minute and normal use of the autopilot will be reestablished 2 A red R is an indication that the roll axis of the autopilot has been disabled and cannot be engaged The autopilot cannot be reengaged Flashing mode annunciation in the display of the autopilot computer 1 ...

Page 445: ...ash 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 ...

Page 446: ...ircraft control b A P DISC TRIM INT Switch PRESS and throughout recovery c AIRCRAFT RE TRIM Manually as Needed HOLD d AUTO PILOT Circuit Breaker PULL SECTION 4 NORMAL PROCEDURES A PREFLIGHT PERFORM PRIOR TO EACH FLIGHT 1 AVIONICS MASTER ON 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 proper ...

Page 447: ...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 repair...

Page 448: ...EASE A P DISC TRIM 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 A P DISC TRIM INT Switch is pressed the manual electric trim syste...

Page 449: ...EPARED TO DISCONNECT THE AUTOPILOT AND TAKE IMMEDIATE CORRECTIVE ACTION INCLUDING MANUAL CONTROL OF THE AIRPLANE AND OR PERFORMANCE OF EMERGENCY PROCEDURES IF AUTOPILOT OPERATION IS NOT AS EXPECTED OR IF AIRPLANE CONTROL IS NOT MAINTAINED A WARNING DURING ALL AUTOPILOT COUPLED OPERATIONS THE PILOT IN COMMAND MUST USE PROPER AUTOPILOT COMMANDS AND USE THE PROPER ENGINE POWER TO ENSURE THAT THE AIRP...

Page 450: ...d ROTATE until the desired altitude is displayed NOTE An altitude alert is annunciated 1000 ft prior to arrival at the selected altitude Aircraft deviations greater than 200 feet above or below the selected altitude will produce an altitude alert The alert annunciation is accompanied by a series of short tones 2 AFTER TAKEOFF a Elevator Trim VERIFY or SET to place the airplane in a trimmed conditi...

Page 451: ... AND RETURN THE AIRPLANE TO A STABILIZED CLIMB PRIOR TO RE ENGAGMENT A WARNING 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 A WARNING DO NOT HELP THE AUTOPILOT OR HAND FLY THE AIRPLANE WITH THE AUTOPILOT ENGAGED AS THE AUTOPILOT WILL RUN THE PITCH TRIM TO OPPOSE...

Page 452: ... 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 intercept the selected altitude NOTE It may be possible ...

Page 453: ...ilot 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 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 VERTICAL...

Page 454: ...ed heading Autopilot will automatically turn the aircraft to the new selected heading 6 NAV COUPLING a When equipped with DG 1 OBS Knob 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 cour...

Page 455: ...rom center the HDG mode will disengage upon selecting NAV mode The NAV annunciator will then illuminate and the capture track sequence will automatically begin b When equipped with HSI 1 Course Bearing Pointer SET to desired course 2 Heading Selector Knob SET BUG to provide desired intercept angle and engage HDG mode 3 NAV Mode Selector Button PRESS a If the Course Deviation Bar D Bar is greater t...

Page 456: ...on selection a 45 intercept angle will then be automatically established based on the position of the bug I I NOTE All angle intercepts compatible with radar vectors may be accomplished by selecting ROL mode PRIOR to pressing the APR button The HDG bug must still be positioned to agree with the desired approach course to provide course datum to the autopilot when using a DG a If the CDI needle is ...

Page 457: ...l be automatically captured and tracked b 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 5 Airspeed MAINTAIN 90 KIAS minimum during coupled autopilot approaches recommended 8 BACK COURSE REV APPROACH COUPLING i e reverse localizer a When equipped with D...

Page 458: ...INBOUND heading to provide course datum to the autopilot when using a DG a If the CDI 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 CDI needle is less than 2 to 3 dots from center the HDG mode will disengag...

Page 459: ...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...

Page 460: ...des are selected the autopilot will operate in the ROL and VS modes Verify that the aircraft 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 A P DISC TRIM INT Switch PRESS to disengage AP SECTION 5 PERFORMANCE There is no chang...

Page 461: ...NO This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Right Manual when the Global Positioning System is installed FAA APPROVAL WAAPPROVEDIWDBJMR sanwrj IteOSMnaAlmftOa ON OOo OmanAueatafenDOMOSOMC PwMmfttfAwr Date 14 December 2000 Q Member of GAMA 6 November Revision 3 22 January 2001 S19 1 COPYRIGHT 2000 CESSNA AIRCRAFT COMPANY WICHITA KAN...

Page 462: ... 0 Original 1 2 3 November 6 2000 December 18 2000 December 30 2000 January 22 2001 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S19 1 Jan 22 01 S19 11 Dec 30 00 S19 2 Jan 22 01 S19 12 Jan 22 01 S19 3 Nov 6 00 S19 13 Jan 22 01 S19 4 Dec 30 00 S19 14 Jan 22 01 S19 5 Dec 30 00 S19 15 Dec 30 00 S19 6 Nov 6 00 S19 16 Dec 30 00 S19 7 Jan 22 01 S19 17 Dec 30 00 S19 8 Jan 22 01 S19 18 Dec 30 00 S19...

Page 463: ...TIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the aiiplane and have been incorporated into this supplement This list contains only those Service Bulletins that are currently active Airplane Unit Revision Incorporated Number Title fcftectivitv Incorporation In Airplane Nov 6 00 S19 3 ...

Page 464: ...curacy 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 integrity Operational guidance for the KLN 94 GPS Navigation System is provided with the Bendix King KLN 94 Pilot s Guide supplie...

Page 465: ...E THE DATABASE IS BEING UPDATED NOTE A current database is required by regulation in order to use the KLN 94 GPS system for non precision approaches Provided the KLN 94 navigation system is receiving adequate usable signals it has been demonstrated capable of and has been shown to meet the accuracy specifications of VFR IFR en route oceanic and remote en route domestic terminal and instrument appr...

Page 466: ...ans of long range navigation NOTE FAA approval of the KLN 94 does not necessarily constitute approval for use in foreign airspace NOTE 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 0...

Page 467: ... 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 of turn an...

Page 468: ...tomatically 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 thi...

Page 469: ...iation Indicator CDI needle can best be accomplished by pressing the Direct To button and then manually setting the No 1 CDI course to the course value prescribed in the KLN 94 displayed message NOTE The Directional Indicator heading HDG bug must also be set to provide proper course datum to the autopilot if coupled to the KLN 94 in LEG or OBS When the optional HSI is installed the HSI course poin...

Page 470: ...will illuminate steady to inform the pilot that GPS information is being displayed on the NAV 1 CDI 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 CDI Course Deviation Indicator The No 1 CDI Omni Bearing Selector OBS provides analog course input to the KLN 94 in OBS mode when the NAV GPS switch annunciator is in GPS When the ...

Page 471: ...ing the Direct To button and then manually setting the No 1 CDI course to the course value prescribed in the KLN 94 displayed message NOTE The Directional Indicator heading HDG bug must also be set to provide proper course datum to the autopilot if coupled to the KLN 94 in LEG or OBS When the optional HSI is installed the HSI course pointer provides course datum to the autopilot Figure 2 GPS Annun...

Page 472: ...ed revision b The data on the Self Test page must be verified prior to use c IFR en route 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 the...

Page 473: ...22 23 if the altitude input to the KLN 94 is not available or fewer satellites projected to be operational for the flight the availability of the GPS integrity RAIM should be confirmed for the intended flight route and time This should be obtained from a prediction program run outside of the aircraft The prediction program must comply with the criteria of Appendix 1 of AC90 96 In the event of a pr...

Page 474: ...nvalid 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 appropr...

Page 475: ...t by first selecting GPS on the NAV GPS switch Manual selection of the desired track on the pilot s DG heading bug is required to provide course datum to the KAP 140 autopilot Frequent course datum changes may be necessary such as in the case of flying a DME arc The autopilot approach mode APR should be used when conducting a coupled GPS approach NOTE NAV or APR coupled DME arc intercepts can resu...

Page 476: ... 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 APT7 or APT8 page will be displayed as appropriate NOTE To delete or replace a DP STAR or approach select FPL 0 page Place the cursor over the name of the procedure press ENT to change it or CLR then ENT to delete it 2 ...

Page 477: ...ound 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 o...

Page 478: ... the 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 publi...

Page 479: ...Waypoint 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 ...

Page 480: ...Fly the 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 se...

Page 481: ...O 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 FAA APPROVAL A w 8 DUNOERnut isumwr j IhOMMCs MwtaOpbiAutomatontXM Bn cc Date January 9 2001 COPYRIGHT 2000 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA Q Member of GAMA 30 December 2000 172RPHUS S20 00 S20 1 ...

Page 482: ...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...

Page 483: ...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...

Page 484: ...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...

Page 485: ...ch 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 L0 middle position to give you a more accurate location of the Marker When used only for approach markers many pilots choose to leave the switch in the...

Page 486: ...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 will...

Page 487: ...he 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 w...

Page 488: ...s 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 MODE PILOT HEARS COPILOTHEARS PASSENGER HEARS COMMENTS Isolate A C Radios ...

Page 489: ... 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 plugg...

Page 490: ...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...

Page 491: ...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 ...

Page 492: ...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 ...

Page 493: ...ENT 22 12 VOLT CABIN POWER SYSTEM SERIAL NO _ REGISTRATIONNO This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Right Manual when the 12 Volt Cabin Power System is installed COPYRIGHT 2000 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 9 Member of GAMA 30 December 2000 172RPHUS S22 00 S22 1 ...

Page 494: ...sue 0 Original Dec 30 00 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S22 1 Dec 30 00 S22 2 Dec 30 00 S22 3 Dec 30 00 S22 4 Dec 30 00 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...

Page 495: ...portable 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 Figure 1 12 Volt Cabin Power S...

Page 496: ...automotive 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 Plug Contact Assignments Not used Not used Not used Not used Not used Outp...

Page 497: ...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...

Page 498: ... 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...

Page 499: ...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 S22 7 S22 8 blank y Dec 30 00 ...

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