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Textron Cessna C172S PIM, Руководство по эксплуатации для пилотов


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CESSNA

SECTION 7

MODEL 172S NAV III

AIRPLANE AND SYSTEM DESCRIPTION

         GFC 700 AFCS

U.S.

VACUUM SYSTEM AND INSTRUMENTS

The vacuum system, Refer to Figure 7-9, provides the vacuum
necessary to operate the standby attitude indicator. The system
consists of one engine-driven vacuum pump, a vacuum regulator, the
standby attitude indicator, a vacuum system air filter, and a vacuum
transducer. The vacuum transducer provides a signal to the engine
display that is processed and displayed as vacuum on the EIS ENGINE
page. If available vacuum, from the engine-driven vacuum pump, drops
below 3.5 in.hg., the LOW VACUUM annunciator will display in amber
on the PFD.

ATTITUDE INDICATOR

The standby attitude indicator is a vacuum-powered gyroscopic
instrument, found on the center instrument panel below the MFD. The
attitude indicator includes a low-vacuum warning flag (GYRO) that
comes into view when the vacuum is below the level necessary for
reliable gyroscope operation.

VACUUM INDICATOR

The vacuum indicator is incorporated on the EIS ENGINE page, found
along the left side of the PFD during engine start or the left edge of the
MFD during normal operation. During reversionary operation, the EIS
bar appears along the left side of the operational display.

LOW VACUUM ANNUNCIATION

A low vacuum condition is annunciated along the right side of the PFD
by a amber LOW VACUUM annunciator.

172SPHBUS-00

7-65

Содержание Cessna C172S PIM

Страница 1: ...ATION NUMBER Model 172S NAV III Avionics GFC 700 AFCS Serials 172S10468 172S10507 172S10640 and 172S10656 and On This publication includes the material required to be furnished to the pilot by 14 CFR...

Страница 2: ......

Страница 3: ...ING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL CESSNA MODEL 172S NAV III AVIONICS OPTION GFC 700 AFCS SERIALS 172S10468 172S10507 172S10640 AND 172S10656 AND ON ORIGINAL ISSUE 20 DECEMBER 2007 R...

Страница 4: ......

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

Страница 6: ...e Fuel Time 4 26 HOURS Range 45 Power at 10 000 Feet Range 638 NM 53 Gallons Usable Fuel Time 6 72 HOURS RATE OF CLIMB AT SEA LEVEL 730 FPM SERVICE CEILING 14 000 FEET TAKEOFF PERFORMANCE Ground Roll...

Страница 7: ...own for an airplane equipped with speed fairings which increase the speeds by approximately 2 knots There is a corresponding difference in range while all other performance figures are unchanged when...

Страница 8: ...installed All information is based on data available at the time of publication This POH consists of nine sections that cover all operational aspects of a standard equipped airplane Section 9 contain...

Страница 9: ...below for a breakdown It is the responsibility of the owner to maintain this POH in a current status when it is being used for operational purposes Owners should contact a Cessna Service Station whene...

Страница 10: ...revisions to the POH may be issued These temporary revisions are to be filed in the applicable section in accordance with filing instructions appearing on the first page of the temporary revision Tem...

Страница 11: ...r spelling grammar changes and or that information has slipped to or from that page A bar located adjacent to the figure number in the margin on the left side of the page will be used to indicate that...

Страница 12: ...uncts to the text are used to highlight or emphasize important points WARNING OPERATING PROCEDURES TECHNIQUES ETC WHICH CAN RESULT IN PERSONAL INJURY OR LOSS OF LIFE IF NOT CAREFULLY FOLLOWED CAUTION...

Страница 13: ...nal Issue 20 December 2007 Revision 2 18 November 2010 Revision 1 12 January 2009 Page Number Page Status Revision Number Title Revised 2 Assignment Record Original 0 i ii Revised 2 iii thru x Origina...

Страница 14: ...4 6 Original 0 4 7 thru 4 10 Revised 2 4 11 Original 0 4 12 Revised 1 4 13 thru 4 16 Revised 2 4 17 thru 4 21 Original 0 4 22 Revised 2 4 23 thru 4 26 Original 0 4 27 Revised 1 4 28 thru 4 32 Revised...

Страница 15: ...1 Original 0 7 22 Revised 2 7 23 thru 7 25 Original 0 7 26 Revised 1 7 27 thru 7 37 Original 0 7 38 Revised 2 7 39 thru 7 48 Original 0 7 49 Revised 2 7 50 thru 7 52 Original 0 7 53 thru 7 54 Revised...

Страница 16: ......

Страница 17: ...he airplane and have been incorporated into this manual This list contains only those Service Bulletins that are currently active Number Title Airplane Serial Effectivity Revision Incorporated Incorpo...

Страница 18: ......

Страница 19: ...S TABLE OF CONTENTS SECTION GENERAL 1 LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT AND BALANCE EQUIPMENT LIST 6 AIRPLANE AND SYSTEM DESCRIPTION 7 HANDLING SERVICE AND...

Страница 20: ......

Страница 21: ...eights 1 9 Cabin And Entry Dimensions 1 9 Baggage Space And Entry Dimensions 1 9 Specific Loadings 1 9 Symbols Abbreviations And Terminology 1 10 General Airspeed Terminology And Symbols 1 10 Meteorol...

Страница 22: ......

Страница 23: ...CESSNA SECTION 1 MODEL 172S NAV III GENERAL GFC 700 AFCS U S THREE VIEW NORMAL GROUND ATTITUDE Figure 1 1 Sheet 1 of 2 1 3 172SPHBUS 02...

Страница 24: ...ts installed Wheel base length is 65 0 inches Propeller ground clearance is 11 25 inches Wing area is 174 0 square feet Minimum turning radius pivot point to outboard wing tip is 27 0 feet 5 50 inches...

Страница 25: ...ls abbreviations and terminology commonly used DESCRIPTIVE DATA ENGINE Number of Engines 1 Engine Manufacturer Textron Lycoming Engine Model Number IO 360 L2A Engine Type Normally aspirated direct dri...

Страница 26: ...fuel supply Additive concentrations shall not exceed 1 for isopropyl alcohol or 0 10 to 0 15 for DiEGME Refer to Section 8 for additional information FUEL CAPACITY Total Capacity 56 0 U S GALLONS Tot...

Страница 27: ...AE J1899 Aviation Grade Ashless Dispersant Oil Oil conforming to Textron Lycoming Service Instruction No 1014 and all revisions and supplements thereto must be used after first 50 hours or oil consump...

Страница 28: ...2550 POUNDS Utility Category 2200 POUNDS WEIGHT IN BAGGAGE COMPARTMENT NORMAL CATEGORY Baggage Area A Station 82 to 108 120 POUNDS Refer to note below Baggage Area B Station 108 to 142 50 POUNDS Refe...

Страница 29: ...DS Maximum Useful Load Utility Category 545 POUNDS CABIN AND ENTRY DIMENSIONS Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6 BAGGAGE SPACE AND ENTRY DIM...

Страница 30: ...ssing 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...

Страница 31: ...hen the altimeter s barometric scale has been set to 29 92 inches of mercury 1013 mb ENGINE POWER TERMINOLOGY BHP Brake Horsepower is the power developed by the engine RPM Revolutions Per Minute is en...

Страница 32: ...g the fuel air mixture to provide a greater portion of fuel is known as richening the mixture Full Rich Mixture control full forward pushed in full control travel toward the panel Idle Cutoff Mixture...

Страница 33: ...to be limiting Usable Fuel Usable Fuel is the fuel available for flight planning Unusable Fuel Unusable Fuel is the quantity of fuel that can not be safely used in flight GPH Gallons Per Hour is the a...

Страница 34: ...onstant 1000 is used in this POH to simplify balance calculations by reducing the number of digits Center of Gravity C G Center of Gravity is the point at which an airplane or equipment would balance...

Страница 35: ...oments throughout the flight range as that of the actual wing Maximum Ramp Weight Maximum Ramp Weight is the maximum weight approved for ground maneuver and includes the weight of fuel used for start...

Страница 36: ...rators convert U S measurement supplied with the Pilot s Operating Handbook into metric and imperial measurements The standard followed for measurement units shown is the National Institute of Standar...

Страница 37: ...CESSNA SECTION 1 MODEL 172S NAV III GENERAL GFC 700 AFCS U S WEIGHT CONVERSIONS Figure 1 2 Sheet 1 of 2 1 17 172SPHBUS 00...

Страница 38: ...SECTION 1 CESSNA GENERAL MODEL 172S NAV III GFC 700 AFCS U S WEIGHT CONVERSIONS Figure 1 2 Sheet 2 172SPHBUS 00 1 18...

Страница 39: ...CESSNA SECTION 1 MODEL 172S NAV III GENERAL GFC 700 AFCS U S LENGTH CONVERSIONS Figure 1 3 Sheet 1 of 4 1 19 172SPHBUS 00...

Страница 40: ...SECTION 1 CESSNA GENERAL MODEL 172S NAV III GFC 700 AFCS U S LENGTH CONVERSIONS Figure 1 3 Sheet 2 172SPHBUS 00 1 20...

Страница 41: ...CESSNA SECTION 1 MODEL 172S NAV III GENERAL GFC 700 AFCS U S LENGTH CONVERSIONS Figure 1 3 Sheet 3 1 21 172SPHBUS 00...

Страница 42: ...SECTION 1 CESSNA GENERAL MODEL 172S NAV III GFC 700 AFCS U S LENGTH CONVERSIONS Figure 1 3 Sheet 4 172SPHBUS 00 1 22...

Страница 43: ...CESSNA SECTION 1 MODEL 172S NAV III GENERAL GFC 700 AFCS U S DISTANCE CONVERSIONS Figure 1 4 1 23 172SPHBUS 00...

Страница 44: ...SECTION 1 CESSNA GENERAL MODEL 172S NAV III GFC 700 AFCS U S VOLUME CONVERSIONS Figure 1 5 Sheet 1 of 3 1 24 172SPHBUS 00...

Страница 45: ...CESSNA SECTION 1 MODEL 172S NAV III GENERAL GFC 700 AFCS U S VOLUME CONVERSIONS Figure 1 5 Sheet 2 1 25 172SPHBUS 00...

Страница 46: ...SECTION 1 CESSNA GENERAL MODEL 172S NAV III GFC 700 AFCS U S VOLUME CONVERSIONS Figure 1 5 Sheet 3 1 26 172SPHBUS 00...

Страница 47: ...CESSNA SECTION 1 MODEL 172S NAV III GENERAL GFC 700 AFCS U S TEMPERATURE CONVERSIONS Figure 1 6 1 27 172SPHBUS 00...

Страница 48: ...SECTION 1 CESSNA GENERAL MODEL 172S NAV III GFC 700 AFCS U S PRESSURE CONVERSION HECTOPASCALS TO INCHES OF MERCURY Figure 1 7 172SPHBUS 00 1 28...

Страница 49: ...CESSNA SECTION 1 MODEL 172S NAV III GENERAL GFC 700 AFCS U S VOLUME TO WEIGHT CONVERSION Figure 1 8 172SPHBUS 00 1 29...

Страница 50: ...SECTION 1 CESSNA GENERAL MODEL 172S NAV III GFC 700 AFCS U S QUICK CONVERSIONS Figure 1 9 172SPHBUS 00 1 30...

Страница 51: ...um Weight in Baggage Compartment Utility Category 2 8 Center Of Gravity Limits 2 9 Normal Category 2 9 Utility Category 2 9 Maneuver Limits 2 10 Normal Category 2 10 Utility Category 2 10 Flight Load...

Страница 52: ......

Страница 53: ...fer to Supplements Section 9 of this Pilot s Operating Handbook for amended operating limitations operating procedures performance data and other necessary information for airplanes equipped with spec...

Страница 54: ...REMARKS VNE Never Exceed Speed 160 163 Do not exceed this speed in any operation VNO Maximum Structural Cruising Speed 126 129 Do not exceed this speed except in smooth air and then only with caution...

Страница 55: ...e Arc 40 85 Full Flap Operating Range Lower limit is maximum weight VSO in landing configuration Upper limit is maximum speed permissible with flaps extended Green Arc 48 129 Normal Operating Range Lo...

Страница 56: ...ION ENGINE OPERATION WITH INDICATED OIL PRESSURE BELOW THE GREEN BAND RANGE WHILE IN CRUISE OR CLIMB CONFIGURATION IS CONSIDERED ABNORMAL REFER TO SECTION 3 AMPLIFIED EMERGENCY PROCEDURES LOW OIL PRES...

Страница 57: ...INGS INSTRUMENT RED LINE MIN RED ARC LWR YELLOW ARC GREEN ARC NORMAL OPERATING RANGE RED ARC UPR Tachometer Sea Level 5000 Feet 10 000 Feet 2100 to 2500 2100 to 2600 2100 to 2700 RPM 2700 to 3000 RPM...

Страница 58: ...e Area A Station 82 to 108 120 POUNDS Refer to note below Baggage Area B Station 108 to 142 50 POUNDS Refer to note below NOTE The maximum allowable combined weight capacity for baggage in areas A and...

Страница 59: ...tion to 41 0 inches aft of datum at 2550 pounds Aft 47 3 inches aft of datum at all weights Reference Datum Lower portion of front face of firewall UTILITY CATEGORY Center of Gravity Range Forward 35...

Страница 60: ...Stalls Slow Deceleration Abrupt use of the controls is prohibited above 105 KNOTS UTILITY CATEGORY This airplane is not designed for purely aerobatic flight However in the acquisition of various cert...

Страница 61: ...ed quickly with the nose down Proper speed control is an essential requirement for execution of any maneuver and care should always be exercised to avoid excessive speed which in turn can impose exces...

Страница 62: ...d IFR operations Flight into known icing conditions is prohibited The minimum equipment for approved operations required under the Operating Rules are defined by 14 CFR 91 and 14 CFR 135 as applicable...

Страница 63: ...ions Continued Next Page System Instrument Equipment and or Function KIND OF OPERATION COMMENTS V F R D A Y V F R N I G H T I F R D A Y I F R N I G H T PLACARDS AND MARKINGS 1 172S Nav III GFC 700 AFC...

Страница 64: ...ess 1 1 1 1 Front Seat Occupants FLIGHT CONTROLS 1 Flap Position Indicator 1 1 1 1 2 Flap Motor 1 1 1 1 3 Elevator Trim System 1 1 1 1 4 Elevator Trim Indicator 1 1 1 1 FUEL SYSTEM 1 Electric Fuel Pum...

Страница 65: ...st be operating on either wing with all 18 LED bulbs operational Continued Next Page System Instrument Equipment and or Function KIND OF OPERATION COMMENTS V F R D A Y V F R N I G H T I F R D A Y I F...

Страница 66: ...1 1 1 1 4 Standby Altimeter 0 0 1 1 5 G1000 Vertical Speed Indicator 0 0 0 0 6 G1000 Attitude Indicator 0 0 1 1 7 Standby Attitude Indicator 0 0 1 1 8 G1000 Directional Indicator HSI 0 0 1 1 9 G1000...

Страница 67: ...F R D A Y V F R N I G H T I F R D A Y I F R N I G H T VACUUM 1 Engine Driven Vacuum Pump 0 0 1 1 2 Vacuum Indicator 0 0 1 1 ENGINE FUEL AND CONTROL 1 Fuel Flow Indicator 1 1 1 1 ENGINE INDICATING 1 T...

Страница 68: ...on Refer to Figure 1 1 for normal ground attitude definition Takeoff and land with the fuel selector valve handle in the BOTH position Maximum slip or skid duration with one tank dry 30 seconds Operat...

Страница 69: ...tem and the connected portable electronic device s will not cause interference with the navigation or communication system of the airplane 12V POWER SYSTEM The 12 Volt Power System POWER OUTLET 12V 10...

Страница 70: ...s the responsibility of the pilot to see and maneuver to avoid traffic Use of the TERRAIN PROXIMITY information for primary terrain avoidance is prohibited The Terrain Proximity map is intended only t...

Страница 71: ...g all autopilot operations 3 The autopilot must be off during all takeoff and landings 4 Autopilot maximum engagement speed 150 KIAS Autopilot minimum engagement speed 70 KIAS Electric Trim maximum op...

Страница 72: ...om the current ATC clearance only to the extent necessary to comply with TAWS B warnings The geographic area of the TAWS B database must match the geographic area in which the airplane is being operat...

Страница 73: ...PROVED PLACARDS The following information must be displayed in the form of composite or individual placards 1 In full view of the pilot The DAY NIGHT VFR IFR entry shown on the example below will vary...

Страница 74: ...TION 2 CESSNA OPERATING LIMITATIONS MODEL 172S NAV III GFC 700 AFCS U S FAA APPROVED PLACARDS Continued 3 On the fuel selector valve 4 Near both fuel tank filler cap Continued Next Page 172SPHBUS 00 2...

Страница 75: ...CESSNA SECTION 2 MODEL 172S NAV III OPERATING LIMITATIONS GFC 700 AFCS U S FAA APPROVED PLACARDS Continued 5 On flap control indicator 6 In baggage compartment Continued Next Page 172SPHBUS 00 2 25...

Страница 76: ...AA APPROVED PLACARDS Continued 7 A calibration card must be provided to indicate the accuracy of the magnetic compass in 30 increments 8 Molded on the oil filler cap dipstick 9 Silk screened on the in...

Страница 77: ...C 700 AFCS U S FAA APPROVED PLACARDS Continued 10 Silk screened on the upper right instrument panel 11 On auxiliary power plug door and second placard on battery box 12 On the upper right side of the...

Страница 78: ...SECTION 2 CESSNA OPERATING LIMITATIONS MODEL 172S NAV III GFC 700 AFCS U S FAA APPROVED PLACARDS Continued 13 On the center overhead flood light control switch 172SPHBUS 00 2 28...

Страница 79: ...During Flight Restart Procedures 3 7 FORCED LANDINGS 3 8 Emergency Landing Without Engine Power 3 8 Precautionary Landing With Engine Power 3 8 Ditching 3 9 FIRES 3 10 During Start On Ground 3 10 Engi...

Страница 80: ...es On or Does Not Go Off at Higher RPM 3 19 AIR DATA SYSTEM FAILURE 3 21 Red X PFD Airspeed Indicator 3 21 Red X PFD Altitude Indicator 3 21 ATTITUDE AND HEADING REFERENCE SYSTEM AHRS FAILURE 3 21 Red...

Страница 81: ...ery From Spiral Dive In The Clouds AHRS FAILED 3 31 Inadvertent Flight Into Icing Conditions 3 31 Static Source Blocked 3 32 Spins 3 32 Rough Engine Operation Or Loss Of Power 3 33 Spark Plug Fouling...

Страница 82: ......

Страница 83: ...c guidelines described in this section should be considered and applied as necessary to correct the problem In any emergency situation the most important task is continued control of the airplane and...

Страница 84: ...ull out 2 Brakes APPLY 3 Wing Flaps RETRACT 4 Mixture Control IDLE CUTOFF pull full out 5 MAGNETOS Switch OFF 6 STBY BATT Switch OFF 7 MASTER Switch ALT and BAT OFF ENGINE FAILURE IMMEDIATELY AFTER TA...

Страница 85: ...S Switch BOTH or START if propeller is stopped NOTE If the propeller is windmilling engine will restart automatically within a few seconds If propeller has stopped possible at low speeds turn MAGNETOS...

Страница 86: ...FF when landing is assured 10 Doors UNLATCH PRIOR TO TOUCHDOWN 11 Touchdown SLIGHTLY TAIL LOW 12 Brakes APPLY HEAVILY PRECAUTIONARY LANDING WITH ENGINE POWER 1 Pilot and Passenger Seat Backs MOST UPRI...

Страница 87: ...STABLISH 300 FT MIN DESCENT AT 55 KIAS NOTE If no power is available approach at 70 KIAS with Flaps UP or at 65 KIAS with Flaps 10 7 Approach High Winds Heavy Seas INTO THE WIND Light Winds Heavy Swel...

Страница 88: ...F pull full out 4 MAGNETOS Switch START continue cranking 5 FUEL SHUTOFF Valve OFF pull full out 6 FUEL PUMP Switch OFF 7 MAGNETOS Switch OFF 8 STBY BATT Switch OFF 9 MASTER Switch ALT and BAT OFF 10...

Страница 89: ...EXECUTE refer to EMERGENCY LANDING WITHOUT ENGINE POWER ELECTRICAL FIRE IN FLIGHT 1 STBY BATT Switch OFF 2 MASTER Switch ALT and BAT OFF 3 Cabin Vents CLOSED to avoid drafts 4 CABIN HT and CABIN AIR C...

Страница 90: ...FIRE 1 STBY BATT Switch OFF 2 MASTER Switch ALT and BAT OFF 3 Cabin Vents CLOSED to avoid drafts 4 CABIN HT and CABIN AIR Control Knobs OFF push full in to avoid drafts 5 Fire Extinguisher ACTIVATE i...

Страница 91: ...FIRE 1 LAND and TAXI Light Switches OFF 2 NAV Light Switch OFF 3 STROBE Light Switch OFF 4 PITOT HEAT Switch OFF NOTE Perform a sideslip to keep the flames away from the fuel tank and cabin Land as so...

Страница 92: ...port With an extremely rapid ice build up select a suitable off airport landing site 8 With an ice accumulation of 0 25 inch or more on the wing leading edges be prepared for significantly higher powe...

Страница 93: ...Airspeed Refer to Section 5 Figure 5 1 Sheet 2 Airspeed Calibration Alternate Static Source correction chart EXCESSIVE FUEL VAPOR FUEL FLOW STABILIZATION PROCEDURES If flow fluctuations of 1 GPH or mo...

Страница 94: ...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 Wing Flaps AS REQUIRED 85 to 110 KI...

Страница 95: ...NAV Light Switch OFF g STROBE Light Switch OFF h CABIN PWR 12V Switch OFF NOTE The main battery supplies electrical power to the main and essential buses until M BUS VOLTS decreases below 20 volts Wh...

Страница 96: ...1 SELECT COM2 MIC and NAV2 will be inoperative once AVIONICS BUS 2 is selected to OFF NOTE When AVIONICS BUS 2 is set to OFF the following items will not operate k AVIONICS Switch BUS 2 OFF KEEP ON if...

Страница 97: ...DOES NOT GO OFF AT HIGHER RPM 1 MASTER Switch ALT Only OFF 2 ALT FIELD Circuit Breaker CHECK IN 3 MASTER Switch ALT and BAT ON 4 LOW VOLTS Annunciator CHECK OFF 5 M BUS VOLTS CHECK 27 5 V minimum 6 M...

Страница 98: ...dio panel and tune to the active frequency before setting AVIONICS BUS 2 to OFF If COM2 MIC and NAV2 are selected when AVIONICS BUS 2 is set to OFF the COM and NAV radios cannot be tuned i COM1 and NA...

Страница 99: ...breaker opens again do not reset 2 Standby Altimeter CHECK current barometric pressure SET USE FOR ALTITUDE INFORMATION ATTITUDE AND HEADING REFERENCE SYSTEM AHRS FAILURE RED X PFD ATTITUDE INDICATOR...

Страница 100: ...n control of airplane 2 A P TRIM DISC Button PRESS and HOLD throughout recovery 3 Elevator Trim Control ADJUST MANUALLY as necessary 4 AUTO PILOT Circuit Breaker OPEN pull out 5 A P TRIM DISC Button R...

Страница 101: ...COMES ON 1 Vacuum Indicator VAC CHECK EIS ENGINE PAGE make sure vacuum pointer is in green band limits CAUTION IF VACUUM POINTER IS OUT OF THE GREEN BAND DURING FLIGHT OR THE GYRO FLAG IS SHOWN ON THE...

Страница 102: ...E CO LEVEL ADVISORY CO LVL HIGH ANNUNCIATOR COMES ON 1 CABIN HT Control Knob OFF push full in 2 CABIN AIR Control Knob ON pull full out 3 Cabin Vents OPEN 4 Cabin Windows OPEN 163 KIAS maximum windows...

Страница 103: ...checklist will provide added safety after a failure of this type If an engine failure occurs immediately after takeoff in most cases the landing should be planned straight ahead with only small chang...

Страница 104: ...SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 172S NAV III GFC 700 AFCS U S MAXIMUM GLIDE Figure 3 1 172SPHBUS 00 3 26...

Страница 105: ...e area and collect folded coats for protection of occupants face at touchdown Transmit Mayday messages on 121 5 MHz giving location intentions and squawk 7700 Avoid a landing flare because of the diff...

Страница 106: ...cause engine flooding and subsequent collection of fuel on the parking ramp as the excess fuel drains overboard from the intake manifolds This is sometimes experienced in difficult starts in cold weat...

Страница 107: ...ot is not very proficient at instrument flying and is flying the airplane without the autopilot engaged EXECUTING A 180 TURN IN CLOUDS AHRS FAILED Upon inadvertently entering the clouds an immediate t...

Страница 108: ...compass heading and make minor corrections to hold an approximate course The autopilot will not operate if the AHRS unit fails The pilot must manually fly the airplane without AHRS input Before desce...

Страница 109: ...Emergency Descent Through The Clouds procedure 8 Upon breaking out of clouds resume normal cruising flight INADVERTENT FLIGHT INTO ICING CONDITIONS Flight into icing conditions is prohibited and extr...

Страница 110: ...LE POSITION 2 PLACE AILERONS IN NEUTRAL POSITION 3 APPLY AND HOLD FULL RUDDER OPPOSITE TO THE DIRECTION OF ROTATION 4 JUST AFTER THE RUDDER REACHES THE STOP MOVE THE CONTROL WHEEL BRISKLY FORWARD FAR...

Страница 111: ...g the MAGNETOS switch from BOTH to the L and R switch positions will identify which magneto is malfunctioning Select different power settings and enrichen the mixture to determine if continued operati...

Страница 112: ...in the fuel injection system is most likely to occur on the ground typically during prolonged taxi operations when operating at higher altitudes and or in unusually warm temperatures Excessive fuel v...

Страница 113: ...il temperature OIL TEMP on ENGINE page or OIL F on SYSTEM page remains normal it is possible that the oil pressure sending unit or relief valve is malfunctioning Land at the nearest airport to determi...

Страница 114: ...situation EXCESSIVE RATE OF CHARGE After engine starting and heavy electrical usage at low engine speeds such as extended taxiing the battery condition will be low enough to accept above normal chargi...

Страница 115: ...system To energize the alternator system 1 MASTER Switch ALT Only OFF 2 ALT FIELD Circuit Breaker CHECK IN 3 MASTER Switch ALT Only ON If the problem was a minor ACU disturbance in the electrical sys...

Страница 116: ...ower for systems on the essential bus and cannot provide power for transponder XPDR operation Main battery life should be extended when practical for possible later operation of the wing flaps and use...

Страница 117: ...mentioned above or the CO LVL HIGH warning annunciation comes on when using the cabin heater immediately turn off the cabin heater and preform the emergency items for High Carbon Monoxide CO Level Adv...

Страница 118: ......

Страница 119: ...ose 4 8 Left Wing 4 9 Left Wing Leading Edge 4 10 Left Wing Trailing Edge 4 10 Before Starting Engine 4 11 Starting Engine With Battery 4 12 Starting Engine With External Power 4 13 Before Takeoff 4 1...

Страница 120: ...0 Alternator Check 4 30 Elevator Trim 4 31 Landing Taxi Lights 4 31 Takeoff 4 31 Power Check 4 31 Wing Flap Settings 4 32 Crosswind Takeoff 4 32 Enroute Climb 4 33 Cruise 4 34 Leaning Using Exhaust Ga...

Страница 121: ...50 Feet 56 KIAS ENROUTE CLIMB FLAPS UP Normal Sea Level 75 85 KIAS Normal 10 000 Feet 70 80 KIAS Best Rate of Climb Sea Level 74 KIAS Best Rate of Climb 10 000 Feet 72 KIAS Best Angle of Climb Sea Le...

Страница 122: ...ify access to the upper wing surfaces for visual checks and refueling operations In cold weather remove even small accumulations of frost ice or snow from wing tail and control surfaces Also make sure...

Страница 123: ...E MAGNETOS SWITCH WERE ON DO NOT STAND NOR ALLOW ANYONE ELSE TO STAND WITHIN THE ARC OF THE PROPELLER SINCE A LOOSE OR BROKEN WIRE OR A COMPONENT MALFUNCTION COULD CAUSE THE ENGINE TO START 7 MAGNETOS...

Страница 124: ...24 MASTER Switch ALT and BAT OFF 25 Elevator Trim Control TAKEOFF position 26 FUEL SELECTOR Valve BOTH 27 ALT STATIC AIR Valve OFF push full in 28 Fire Extinguisher CHECK verify gage pointer in green...

Страница 125: ...rock wings and lower tail to the ground to move any additional contaminants to the sampling points Take repeated samples from all fuel drain points until all contamination has been removed If contami...

Страница 126: ...ants are still present refer to WARNING below and do not fly the airplane NOTE Collect all sampled fuel in a safe container Dispose of the sampled fuel so that it does not cause a nuisance hazard or d...

Страница 127: ...e further samples until clear and then gently rock wings and lower tail to the ground to move any additional contaminants to the sampling points Take repeated samples from all fuel drain points until...

Страница 128: ...ng CHECK blockage NOTE To check the system place a clean handkerchief over the vent opening and apply suction a sound from the warning horn will confirm system operation 3 Wing Tiedown DISCONNECT 4 La...

Страница 129: ...Seat Belts ADJUST and LOCK verify inertia reel locking 4 Brakes TEST and SET 5 Circuit Breakers CHECK IN 6 Electrical Equipment OFF 7 AVIONICS Switch BUS 1 and BUS 2 OFF CAUTION THE AVIONICS SWITCH B...

Страница 130: ...l people and equipment are at a safe distance from the propeller 10 MASTER Switch ALT and BAT ON 11 BEACON Light Switch ON NOTE If engine is warm omit priming procedure steps 12 thru 14 below 12 FUEL...

Страница 131: ...b ARM verify that PFD comes on 4 Engine Indication System CHECK PARAMETERS verify no red X s through ENGINE page indicators 5 BUS E Volts CHECK verify 24 VOLTS minimum shown 6 M BUS Volts CHECK verify...

Страница 132: ...CH position and retard the throttle control promptly 21 Oil Pressure CHECK verify oil pressure increases into the GREEN BAND range in 30 to 60 seconds 22 Power REDUCE TO IDLE 23 External Power DISCONN...

Страница 133: ...ight Switch ON as required 29 AVIONICS Switch BUS 1 and BUS 2 ON BEFORE TAKEOFF 1 Parking Brake SET 2 Pilot and Passenger Seat Backs MOST UPRIGHT POSITION 3 Seats and Seat Belts CHECK SECURE 4 Cabin D...

Страница 134: ...17 Elevator Trim Control SET FOR TAKEOFF 18 Throttle Control 1800 RPM a MAGNETOS Switch CHECK RPM drop should not exceed 175 RPM on either magneto or 50 RPM differential between magnetos b VAC Indica...

Страница 135: ...NG FLAG WARNING WHEN THE AUTOPILOT IS ENGAGED IN NAV APR OR BC OPERATING MODES IF THE HSI NAVIGATION SOURCE IS CHANGED MANUALLY USING THE CDI SOFTKEY THE CHANGE WILL INTERRUPT THE NAVIGATION SIGNAL TO...

Страница 136: ...trol LIFT NOSEWHEEL AT 55 KIAS 5 Climb Airspeed 70 80 KIAS 6 Wing Flaps RETRACT at safe altitude SHORT FIELD TAKEOFF 1 Wing Flaps 10 2 Brakes APPLY 3 Throttle Control FULL push full in 4 Mixture Contr...

Страница 137: ...titude lean for maximum RPM NOTE For maximum performance climb speeds refer to Section 5 Figure 5 6 Maximum Rate of Climb at 2550 Pounds CRUISE 1 Power 2100 2700 RPM no more than 75 power recommended...

Страница 138: ...RSE DEVIATION BAR D BAR PART OF THE INDICATOR IS NOT SHOWN ON THE HSI COMPASS CARD THE MISSING D BAR IS CONSIDERED TO BE THE WARNING FLAG WARNING WHEN THE AUTOPILOT IS ENGAGED IN NAV APR OR BC OPERATI...

Страница 139: ...NG 1 Airspeed 65 75 KIAS Flaps UP 2 Wing Flaps AS DESIRED UP 10 below 110 KIAS 10 FULL below 85 KIAS 3 Airspeed 60 70 KIAS Flaps FULL 4 Elevator Trim Control ADJUST 5 Touchdown MAIN WHEELS FIRST 6 Lan...

Страница 140: ...e altitude and 65 KIAS AFTER LANDING 1 Wing Flaps UP 2 STROBE Light Switch OFF SECURING AIRPLANE 1 Parking Brake SET 2 Throttle Control IDLE pull full out 3 Electrical Equipment OFF 4 AVIONICS Switch...

Страница 141: ...ence of tire deterioration caused by age improper storage or prolonged exposure to weather Check the tread of the tire for depth wear and cuts Replace the tire if fibers are visible After major mainte...

Страница 142: ...sty areas or tied down adjacent to taxiing airplanes special attention should be paid to control surface stops hinges and brackets to detect the presence of potential wind damage If the airplane has b...

Страница 143: ...to 1 3 open when the engine starts and then smoothly to full rich as power develops If the engine does not continue to run set the FUEL PUMP switch to the ON position temporarily and adjust the thrott...

Страница 144: ...10 seconds followed by 20 seconds of cool down If the engine still does not start try to find the cause LEANING FOR GROUND OPERATIONS For all ground operations after starting the engine and when the...

Страница 145: ...ROCEDURES FOR FLIGHT TRAINING OPERATIONS 4 In addition to the above procedures the auxiliary fuel pump may be turned ON with the mixture adjusted as required to aid vapor suppression during ground ope...

Страница 146: ...el or cinders should be done at low engine speed to avoid abrasion and stone damage to the propeller tips NOTE The LOW VOLTS annunciator may come on when the engine is operated at low RPM with a high...

Страница 147: ...S TAXIING Continued TAXIING DIAGRAM NOTE Strong quartering tail winds require caution Avoid sudden bursts of the throttle and sharp braking when the airplane is in this attitude Use the steerable nos...

Страница 148: ...RPM on either magneto or be greater than 50 RPM differential between magnetos If there is a doubt concerning operation of the ignition system RPM checks at higher engine speeds will usually confirm wh...

Страница 149: ...you are justified in making a thorough full throttle static run up before another takeoff is attempted The engine should run smoothly and turn approximately 2300 2400 RPM with the mixture leaned to p...

Страница 150: ...lerate to a higher climb speed When departing a soft field with an aft C G loading the elevator trim control should be adjusted towards the nose down direction to give comfortable control wheel forces...

Страница 151: ...de smoother engine operation If it is necessary to climb more rapidly to clear mountains or reach favorable winds at higher altitudes the best rate of climb speed should be used with Maximum Continuou...

Страница 152: ...winds determine the time and fuel needed to complete any flight The Cruise Performance Table Figure 4 3 shows the true airspeed and nautical miles per gallon during cruise for various altitudes and pe...

Страница 153: ...y 125 pounds below maximum gross weight The fuel injection system employed on this engine is considered to be non icing In the event that unusual conditions cause the intake air filter to become clogg...

Страница 154: ...ithin approximately 100 F of each other during normal operations An EGT difference greater than 100 F between cylinders indicates that fuel injection system maintenance is necessary EGT is displayed o...

Страница 155: ...K F value is negative the mixture can be on the lean side of peak Enrichen the mixture by slowly turning the mixture control clockwise and monitor both fuel flow and EGTs until the leanest cylinder re...

Страница 156: ...e at the recommended lean mixture NOTE Any change in altitude or power setting will require a change in the recommended lean mixture setting and a recheck of the EGT setting The EGT indicators take se...

Страница 157: ...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 includi...

Страница 158: ...attempting to perform spins several items should be carefully considered to assure a safe flight No spins should be attempted without first having received dual instruction both in spin entries and sp...

Страница 159: ...lection is reached almost simultaneously with reaching full aft elevator A slightly greater rate of deceleration than for normal stall entries application of ailerons in the direction of the desired s...

Страница 160: ...n makes the direction of rotation difficult to determine see the turn vector near the index at the top of the Horizontal Situation Indicator HSI Variations in basic airplane rigging or in weight and b...

Страница 161: ...e nosewheel The nosewheel must be lowered to the runway carefully after the speed has diminished to avoid unnecessary nose gear loads This procedure is very important for rough or soft field landings...

Страница 162: ...ing if necessary The maximum allowable crosswind velocity is dependent upon pilot capability as well as airplane limitations Landings in direct crosswinds of 15 knots have been demonstrated with flaps...

Страница 163: ...o Section 8 for information on the proper use of additives Cold weather often causes conditions that require special care during airplane operations Even small accumulations of frost ice or snow must...

Страница 164: ...WIRE ON EITHER MAGNETO COULD ENERGIZE THE ENGINE Prior to starting on cold mornings it is advisable to turn the propeller manually through several engine compression cycles by hand to loosen the oil...

Страница 165: ...1000 RPM or greater Prior to takeoff verify the S BATT ammeter shows a charge less than 0 4 amps NOTE If the engine does not start during the first few attempts or if engine firing diminishes in stren...

Страница 166: ...ggested to minimize the effect of airplane noise on the public 1 Pilots operating airplanes under VFR over outdoor assemblies of persons recreational and park areas and other noise sensitive areas sho...

Страница 167: ...d Calibration Alternate Static Source 5 11 Temperature Conversion Chart 5 12 Stall Speeds At 2550 Pounds 5 13 Crosswind Component 5 14 Short Field Takeoff Distance At 2550 Pounds 5 15 Short Field Take...

Страница 168: ......

Страница 169: ...setting Fuel flow data for cruise is based on the recommended lean mixture setting at all altitudes Some indeterminate variables such as mixture leaning technique fuel metering characteristics engine...

Страница 170: ...ge AIRPLANE CONFIGURATION Takeoff weight 2550 Pounds Usable fuel 53 0 Gallons TAKEOFF CONDITIONS Field pressure altitude 1500 Feet Temperature 28 C 16 C Above Standard Wind component along runway 12 K...

Страница 171: ...ults in the following These distances are well within the available takeoff field length However a correction for the effect of wind may be made based on information presented in the note section of t...

Страница 172: ...file 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...

Страница 173: ...on the climb chart The approximate effect of a nonstandard 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 c...

Страница 174: ...ted fuel required is as follows Once the flight is underway ground speed checks will provide a more accurate basis for estimating the time enroute and the corresponding fuel required to complete the t...

Страница 175: ...lows A correction for the effect of wind may be made based on information presented in the note section of the landing chart using the same procedure as outlined for takeoff DEMONSTRATED OPERATING TEM...

Страница 176: ...required for level flight or maximum power descent Flaps UP KIAS 50 60 70 80 90 100 110 120 130 140 150 160 KCAS 56 62 70 78 87 97 107 117 127 137 147 157 Flaps 10 KIAS 40 50 60 70 80 90 100 110 KCAS...

Страница 177: ...CESSNA SECTION 5 MODEL 172S NAV III PERFORMANCE GFC 700 AFCS U S NOTE Windows and ventilators closed Cabin heat cabin air and defroster on maximum Figure 5 1 Sheet 2 172SPHBUS 01 5 11...

Страница 178: ...SECTION 5 CESSNA PERFORMANCE MODEL 172S NAV III GFC 700 AFCS U S TEMPERATURE CONVERSION CHART Figure 5 2 172SPHBUS 00 5 12...

Страница 179: ...CESSNA SECTION 5 MODEL 172S NAV III PERFORMANCE GFC 700 AFCS U S Figure 5 3 5 13 172SPHBUS 02...

Страница 180: ...ODEL 172S NAV III GFC 700 AFCS U S CROSSWIND COMPONENT MAXIMUM DEMONSTRATED CROSSWIND VELOCITY Takeoff Flaps UP 20 KNOTS Takeoff Flaps 10 20 KNOTS Landing Flaps 10 20 KNOTS Landing Flaps FULL 15 KNOTS...

Страница 181: ...ground roll figure Figure 5 5 Sheet 1 of 3 Pressure Altitude Feet 0 C 10 C 20 C 30 C 40 C Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll Feet T...

Страница 182: ...of the ground roll figure Figure 5 5 Sheet 2 Pressure Altitude Feet 0 C 10 C 20 C 30 C 40 C Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll Feet...

Страница 183: ...by 15 of the ground roll figure Figure 5 5 Sheet 3 Pressure Altitude Feet 0 C 10 C 20 C 30 C 40 C Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll...

Страница 184: ...ixture leaned above 3000 feet pressure altitude for maximum RPM Figure 5 6 Pressure Altitude Feet ClimbSpeed KIAS Rate of Climb FPM 20 C 0 C 20 C 40 C Sea Level 74 855 785 710 645 2000 73 760 695 625...

Страница 185: ...r each 10 C above standard temperature Distances shown are based on zero wind Figure 5 7 Pressure Altitude Feet Temp C Climb Speed KIAS Rate of Climb FPM From Sea Level Time Minutes Fuel Used Gallons...

Страница 186: ...P KTAS GPH MCP KTAS GPH 2000 2550 83 117 11 1 77 118 10 5 72 117 9 9 2500 78 115 10 6 73 115 9 9 68 115 9 4 2400 69 111 9 6 64 110 9 0 60 109 8 5 2300 61 105 8 6 57 104 8 1 53 102 7 7 2200 53 99 7 7 5...

Страница 187: ...P KTAS GPH MCP KTAS GPH MCP KTAS GPH 8000 2700 83 125 11 1 77 124 10 4 71 123 9 7 2650 78 122 10 5 72 122 9 9 67 120 9 3 2600 74 120 10 0 68 119 9 4 64 117 8 9 2500 65 114 9 1 61 112 8 6 57 111 8 1 24...

Страница 188: ...d Temperature Recommended Lean Mixture for Cruise at all altitudes Zero Wind NOTE This chart allows for the fuel used for engine start taxi takeoff and climb and the distance during a normal climb Cru...

Страница 189: ...5 MINUTES RESERVE 53 GALLONS USABLE FUEL CONDITIONS 2550 Pounds Standard Temperature Recommended Lean Mixture for Cruise at all altitudes NOTE This chart allows for the fuel used for engine start taxi...

Страница 190: ...istances Figure 5 11 Pressure Altitude Feet 0 C 10 C 20 C 30 C 40 C Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll Feet Total Feet To Clear 50 Foot Obst Gnd Roll Feet Total Feet To Clear 50 F...

Страница 191: ...ne Weighing Procedures 6 3 Airplane Weighing Form 6 5 Sample Weight and Balance Record 6 7 Weight And Balance 6 8 Baggage Tiedown 6 9 Sample Loading Problem 6 10 Loading Graph 6 12 Loading Arrangement...

Страница 192: ......

Страница 193: ...ent and installed equipment for this airplane as delivered from the factory can be found in the plastic envelope in the back of this POH WARNING IT IS THE RESPONSIBILITY OF THE PILOT TO MAKE SURE THE...

Страница 194: ...eel centers to a plumb bob dropped from the firewall b Obtain measurement B by measuring horizontally and parallel to the airplane centerline from center of nosewheel axle left side to a plumb bob dro...

Страница 195: ...CESSNA SECTION 6 MODEL 172S NAV III WEIGHT AND BALANCE GFC 700 AFCS EQUIPMENT LIST U S AIRPLANE WEIGHING FORM Figure 6 1 Sheet 1 of 2 172SPHBUS 00 6 5...

Страница 196: ...SECTION 6 CESSNA WEIGHT AND BALANCE MODEL 172S NAV III EQUIPMENT LIST GFC 700 AFCS U S AIRPLANE WEIGHING FORM Figure 6 1 Sheet 2 172SPHBUS 00 6 6...

Страница 197: ...CESSNA SECTION 6 MODEL 172S NAV III WEIGHT AND BALANCE GFC 700 AFCS EQUIPMENT LIST U S SAMPLE WEIGHT AND BALANCE RECORD Figure 6 2 172SPHBUS 00 6 7...

Страница 198: ...Use the Loading Graph to determine the moment 1000 for each additional item to be carried then list these on the loading problem NOTE Loading Graph information for the pilot passengers and baggage is...

Страница 199: ...n FS 90 two eyebolts are installed on the cabin floor slightly inboard of each sidewall approximately at FS 107 and two eyebolts are located below the aft window near each sidewall approximately at FS...

Страница 200: ...ced Fuel 35 Gallons 210 10 1 3 Pilot and Front Passenger FS 34 to 46 340 12 6 4 Rear Passengers FS 73 310 22 6 5 Baggage A FS 82 to 108 120 Pounds Maximum 56 5 3 6 Baggage B FS 108 to 142 50 Pounds Ma...

Страница 201: ...EQUIPMENT LIST U S SAMPLE LOADING PROBLEM NOTE When several loading configurations are representative of your operations it may be useful to fill out one or more of the above columns so specific load...

Страница 202: ...LOADING GRAPH NOTE Line representing adjustable seats shows the pilot and front seat passenger center of gravity on adjustable seats positioned for average occupant Refer to the Loading Arrangements...

Страница 203: ...red to the center of the areas shown NOTE The usable fuel C G arm is located at FS 48 00 The aft baggage wall approximate FS 108 00 or aft baggage wall approximate FS 142 00 can be used as a convenien...

Страница 204: ...T AND BALANCE MODEL 172S NAV III EQUIPMENT LIST GFC 700 AFCS U S INTERNAL CABIN DIMENSIONS NOTE Maximum allowable floor loading is 200 pounds per square foot All dimensions shown are in inches Figure...

Страница 205: ...CESSNA SECTION 6 MODEL 172S NAV III WEIGHT AND BALANCE GFC 700 AFCS EQUIPMENT LIST U S CENTER OF GRAVITY MOMENT ENVELOPE Figure 6 7 172SPHBUS 00 6 15...

Страница 206: ...SECTION 6 CESSNA WEIGHT AND BALANCE MODEL 172S NAV III EQUIPMENT LIST GFC 700 AFCS U S CENTER OF GRAVITY LIMITS Figure 6 8 172SPHBUS 00 6 16...

Страница 207: ...rs are as follows 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 co...

Страница 208: ......

Страница 209: ...2 4 112 7 FIS ANTENNA 3960233 1 0 4 43 5 23 COMMUNICATIONS 23 01 S STATIC DISCHARGE WICKS SET OF 10 0501048 1 0 4 143 2 23 02 R AUDIO INTERCOM MARKER BEACON GMA 1347 AUDIO PANEL 3930377 1 7 16 3 CI 1...

Страница 210: ...INERTIA REEL AUTO ADJUST REAR SEAT 0519031 1 5 2 90 0 25 09 S SUN VISOR SET OF 2 0514166 2 1 1 32 8 25 10 S BAGGAGE RESTRAINT NET 2015009 7 0 5 95 0 25 11 S CARGO TIEDOWN RINGS SET OF 6 0515055 6 0 2...

Страница 211: ...31 INDICATING RECORDING SYSTEM 31 01 S RECORDING HOURMETER C664503 0103 0506009 0 5 16 1 31 02 R PNEUMATIC STALL WARNING SYSTEM 0523112 0 4 28 5 31 03 R GEA 71 ENGINE AIRFRAME UNIT 3930377 2 2 11 4 31...

Страница 212: ...OF MERCURY AND MILLBARS S3827 1 0506009 0 9 14 0 34 04 S ALTERNATE STATIC AIR SOURCE 0501017 1 0 2 15 5 34 05 R COMPASS MAGNETIC 0513262 3 0 5 18 0 34 06 R TRANSPONDER 3940397 3 1 114 0 GTX 33 TRANSPO...

Страница 213: ...T SIDE NET CHANGE 0517001 39 2 3 48 5 61 PROPELLER 61 01 R FIXED PITCH PROPELLER ASSEMBLY 0550320 18 38 8 38 2 MCCAULEY 76 INCH PROPELLER IA170E JHA7660 35 0 38 4 MCCAULEY 3 5 INCH PROPELLER SPACER C5...

Страница 214: ...C 2 0501168 0 2 8 0 77 02 S CYLINDER HEAD THERMOCOUPLES ALL CYLINDERS 32DKWUE006F0126 0501168 0 2 12 0 77 03 S EXHAUST THERMOCOUPLES ALL CYLINDERS 86317 0501168 0 3 12 0 78 EXHAUST 78 01 R EXHAUST SYS...

Страница 215: ...13 Flight Instruments 7 16 Attitude Indicator 7 17 Airspeed Indicator 7 18 Altimeter 7 18 Horizontal Situation Indicator 7 19 Vertical Speed Indicator 7 20 Ground Control 7 21 Wing Flap System 7 22 L...

Страница 216: ...Fuel Indicating System 7 39 Fuel Calculations 7 41 Auxiliary Fuel Pump Operation 7 43 Fuel Return System 7 44 Fuel Venting 7 44 Reduced Tank Capacity 7 44 Fuel Selector Valve 7 45 Fuel Drain Valves 7...

Страница 217: ...its GDU 7 68 Audio Panel GMA 7 69 Integrated Avionics Unit GIA 7 69 Attitude and Heading Reference System AHRS and Magnetometer GRS 7 69 Air Data Computer GDC 7 70 Engine Monitor GEA 7 70 Transponder...

Страница 218: ......

Страница 219: ...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 r...

Страница 220: ...f a forward and aft spar ribs and stiffeners center left and right wrap around skin panels and formed leading edge skins The horizontal stabilizer also contains the elevator trim tab actuator Construc...

Страница 221: ...mechanical linkage using a control wheel for the ailerons and elevator and rudder brake pedals for the rudder TRIM SYSTEMS A manually operated elevator trim system is provided on this airplane refer...

Страница 222: ...SECTION 7 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 172S NAV III GFC 700 AFCS U S FLIGHT CONTROLS AND TRIM SYSTEM Figure 7 1 Sheet 1 of 2 172SPHBUS 02 7 8...

Страница 223: ...CESSNA SECTION 7 MODEL 172S NAV III AIRPLANE AND SYSTEM DESCRIPTION GFC 700 AFCS U S FLIGHT CONTROLS AND TRIM SYSTEMS Figure 7 1 Sheet 2 172SPHBUS 02 7 9...

Страница 224: ...L LAYOUT The PFD centered on the instrument panel in front of the pilot shows the primary flight instruments during normal operation During engine start reversionary operation MFD failure or when the...

Страница 225: ...t receives power Lighting for this subpanel is controlled using the SW CB PANELS dimmer control See the ELECTRICAL EQUIPMENT descriptions in this section for further information CENTER PANEL LAYOUT Th...

Страница 226: ...vacuum flag to provide immediate warning of vacuum system failure The engine controls are found on the lower center instrument panel below the standby instrument cluster The controls are conventional...

Страница 227: ...n The Hour Hobbs meter is found to the right of the ELT switch and records engine operating time when oil pressure is greater than 20 PSI for maintenance purposes Refer to the ENGINE INSTRUMENTS descr...

Страница 228: ...SECTION 7 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 172S NAV III GFC 700 AFCS U S INSTRUMENT PANEL Figure 7 2 172SPHBUS 00 7 14...

Страница 229: ...King KR87 Automatic Direction Finder if installed 14 Microphone Button 15 Glove Box 16 Cabin Heat Control 17 Cabin Air Control 18 Wing Flap Control Lever And Position Indicator 19 Mixture Control Knob...

Страница 230: ...vertical speed The vertical indicators take the place of analog indicators with a fixed circular scale and rotating pointer Knobs knob sets two knobs on a common shaft and membrane type push button sw...

Страница 231: ...o 60 of roll The roll pointer is slaved to the airplane symbol The pitch index scale is graduated in 5 increments with every 10 of pitch labeled If pitch limits are exceeded in either the nose up or n...

Страница 232: ...lower center instrument panel Colored arcs are provided to indicate the maximum speed high cruise speed caution range normal operating range full wing flap operating range and low airspeed awareness...

Страница 233: ...elow the heading window at the top of the HSI shows half and standard rates of turn based on the length of the magenta turn vector The cyan HSI heading reference pointer bug is set using the HDG knob...

Страница 234: ...EADING OR COURSE SET THE HDG BUG TO THE CORRECT HEADING AND SELECT THE CORRECT NAVIGATION SOURCE ON THE HSI USING THE CDI SOFTKEY BEFORE ENGAGING THE AUTOPILOT IN ANY OTHER OPERATING MODE VERTICAL SPE...

Страница 235: ...not available or pushing is required use the wing struts as push points Do not use the vertical or horizontal surfaces to move the airplane If the airplane is to be towed by vehicle never turn the no...

Страница 236: ...control lever is moved up or down in a slotted panel that provides mechanical stops at the 10 20 and FULL positions To change flap setting the wing flap control lever is moved to the right to clear m...

Страница 237: ...with a hydraulically actuated disc type brake on the inboard side of each wheel BAGGAGE COMPARTMENT The baggage compartment consists of two areas one extending from behind the rear passengers seat to...

Страница 238: ...arge crank under the right corner of the seat until a comfortable height is obtained To adjust the seat back angle pull up on the release button located in center front of seat just under the seat bot...

Страница 239: ...in 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 distinctive...

Страница 240: ...SECTION 7 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 172S NAV III GFC 700 AFCS U S INTEGRATED SEAT BELT SHOULDER HARNESS Figure 7 4 172SPHBUS 01 7 26...

Страница 241: ...sed door handle near the aft edge of either door by grasping the forward edge of the handle and pulling outboard To close or open the doors from inside the airplane use the combination door handle and...

Страница 242: ...ide 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...

Страница 243: ...throttle control is configured so that the throttle is open in the forward position and closed in the full aft position A friction lock located at the base of the throttle is operated by rotating the...

Страница 244: ...HRS Electrical Bus Voltages VOLTS and Battery Currents AMPS When the ENGINE softkey is pressed the LEAN and SYSTEM softkeys appear adjacent to the ENGINE softkey The LEAN page provides simultaneous in...

Страница 245: ...range From 5000 feet to 10 000 feet 2600 RPM is the top of the normal range And above 10 000 feet 2700 RPM is the upper limit of the normal operating range When engine speed is 2780 RPM or more the p...

Страница 246: ...indicator range is 0 to 120 PSI with a red band from 0 to 20 PSI a green band from 50 to 90 PSI normal operating range and a red band from 115 to 120 PSI A white pointer indicates actual oil pressure...

Страница 247: ...operative OIL TEMPERATURE Engine oil temperature is shown on the ENGINE page by the OIL TEMP horizontal indicator The indicator range is from 75 F to 250 F with a green band normal operating range fro...

Страница 248: ...PERATURE Exhaust gas temperature EGT is shown on the ENGINE page by the EGT horizontal indicator The indicator range is from 1250 F to 1650 F with graduations every 50 F The white pointer indicates re...

Страница 249: ...w oil filter a pressure relief valve at the rear of the right oil gallery and a thermostatically controlled remote oil cooler Oil from the remote cooler is then circulated to the left oil gallery The...

Страница 250: ...rotated to the spring 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...

Страница 251: ...the cylinders through the intake manifold tubes and metered fuel is delivered to a fuel manifold flow divider The fuel manifold through spring tension on a diaphragm and valve evenly distributes the f...

Страница 252: ...a fuel air control unit fuel flow transducer a fuel distribution valve flow divider and fuel injection nozzles WARNING UNUSABLE FUEL LEVELS FOR THIS AIRPLANE WERE DETERMINED IN ACCORDANCE WITH FEDERA...

Страница 253: ...antity sensors one in each fuel tank and is displayed on the EIS pages The indicators are marked in gallons of fuel GAL An empty tank is displayed on the fuel quantity indicator FUEL QTY GAL as a red...

Страница 254: ...uel quantity indicator pointers are in the yellow band range and or amber LOW FUEL L or LOW FUEL R annunciator is displayed on the PFD In addition to low fuel annunciation the warning logic is designe...

Страница 255: ...low transducer signal For fuel remaining information a count down fuel totalizer function is provided on the EIS SYSTEM page as GAL REM This digital indicator shows calculated fuel remaining since las...

Страница 256: ...SECTION 7 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 172S NAV III GFC 700 AFCS U S FUEL SYSTEM Continued Figure 7 6 172SPHBUS 00 7 42...

Страница 257: ...of the mixture It is not necessary to operate the auxiliary fuel pump during normal takeoff and landing since gravity and the engine driven fuel pump will supply adequate fuel flow In the event of fai...

Страница 258: ...ction 4 for Hot Weather operating information FUEL VENTING Fuel system venting is essential to system operation Complete blockage of the fuel venting system will result in decreasing fuel flow and eve...

Страница 259: ...orrected by turning the fuel selector valve to the fuel tank indicating the highest fuel quantity Once the L FUEL and R FUEL indicators have equalized position the fuel selector valve to the BOTH posi...

Страница 260: ...kes are operated by applying pressure to the top of either the left pilot s or right copilot s set of rudder pedals which are interconnected When the airplane is parked both main wheel brakes may be s...

Страница 261: ...tery is available to supply power to the essential bus in the event that alternator and main battery power sources have both failed The primary buses are supplied with power whenever the MASTER switch...

Страница 262: ...SECTION 7 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 172S NAV III GFC 700 AFCS U S ELECTRICAL SYSTEM Continued Figure 7 7 Sheet 1 of 3 172SPHBUS 00 7 48...

Страница 263: ...CESSNA SECTION 7 MODEL 172S NAV III AIRPLANE AND SYSTEM DESCRIPTION GFC 700 AFCS U S ELECTRICAL SYSTEM Continued Figure 7 7 Sheet 2 172SPHBUS 02 7 49...

Страница 264: ...SECTION 7 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 172S NAV III GFC 700 AFCS U S ELECTRICAL SYSTEM Continued Figure 7 7 Sheet 3 172SPHBUS 00 7 50...

Страница 265: ...In normal operation both sides of the switch ALT and BAT are ON simultaneously however the BAT side of the switch may be selected separately as necessary The ALT side of the switch can not be set to...

Страница 266: ...The switch is set to the ARM position during normal flight operation to allow the standby battery to charge and to be ready to power the essential bus in the event of alternator and main battery failu...

Страница 267: ...ing shall be about 28 0 volts When the voltage for either main or essential buses is above 32 0 volts the numerical value and VOLTS text turns red This warning indication along with the HIGH VOLTS ann...

Страница 268: ...l load exceeds the output of the alternator the main battery ammeter indicates the main battery discharge rate In the event that standby battery discharge is required normal steady state discharge sho...

Страница 269: ...ammeter discharge indications may occur Under these conditions increase RPM or decrease electrical loads to reduce demand on the battery In the event an overvoltage condition or other alternator faul...

Страница 270: ...rrected by a qualified maintenance technician before flight HIGH VOLTAGE ANNUNCIATION The HIGH VOLTS annunciator will come on when main or essential bus voltage is above 32 0 volts This warning annunc...

Страница 271: ...tch is discouraged since the practice will decrease the life of the circuit breaker All circuit breakers on ELECTRICAL BUS 1 ELECTRICAL BUS 2 and CROSSFEED BUS are not capable of being opened or disen...

Страница 272: ...from transient voltages Set AVIONICS switches BUS 1 and BUS 2 to OFF before starting the engine The following check should be made whenever the engine has been started using external power after disc...

Страница 273: ...ng light TAXI taxi light NAV and STROBE light s place the switch in the up position Circuit breakers for the lights are found on the lighted circuit breaker panel on the lower left instrument panel be...

Страница 274: ...n switch for the rear dome light The front flood lights can be rotated to provide directional lighting for the pilot and front passenger The rear dome light provides for general illumination in the re...

Страница 275: ...ed indicator attitude indicator altimeter and non stabilized magnetic compass Rotating the dimmer control counterclockwise decreases light intensity from the highest level to off Pilot s chart map lig...

Страница 276: ...no heat is desired in the cabin the CABIN HT control 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...

Страница 277: ...CESSNA SECTION 7 MODEL 172S NAV III AIRPLANE AND SYSTEM DESCRIPTION GFC 700 AFCS U S CABIN HEATING VENTILATION AND DEFROSTING SYSTEM Figure 7 8 172SPHBUS 00 7 63...

Страница 278: ...below the lower left corner of the PFD The PITOT HEAT circuit breaker is found on the circuit breaker panel at the lower left side of the pilot panel A static pressure alternate source valve ALT STAT...

Страница 279: ...OW VACUUM annunciator will display in amber on the PFD ATTITUDE INDICATOR The standby attitude indicator is a vacuum powered gyroscopic instrument found on the center instrument panel below the MFD Th...

Страница 280: ...SECTION 7 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 172S NAV III GFC 700 AFCS U S VACUUM SYSTEM Figure 7 9 172SPHBUS 00 7 66...

Страница 281: ...he windshield and associated 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...

Страница 282: ...nformation plus altitude airspeed and vertical speed information to the pilot The PFD also controls and displays all communication and navigation frequencies as well as displaying warning status annun...

Страница 283: ...e units act as the main communications hub linking all of the other peripheral parts to the GDU displays Each unit contains a GPS receiver a VHF navigation receiver VHF communication transceiver and t...

Страница 284: ...el flow and to the fuel gauging system This unit transmits this information to the engine display computers TRANSPONDER GTX The full featured Mode S transponder provides Mode A C and S functions Contr...

Страница 285: ...S operation to reduce control forces or large pitch oscillations that may occur after releasing the CWS button WARNING WHEN THE AUTOPILOT IS ENGAGED IN NAV APR OR BC OPERATING MODES IF THE HSI NAVIGAT...

Страница 286: ...SECTION 7 CESSNA AIRPLANE AND SYSTEM DESCRIPTION MODEL 172S NAV III GFC 700 AFCS U S GFC 700 SYSTEM SCHEMATIC Figure 7 10 172SPHBUS 00 7 72...

Страница 287: ...one provides forced air cooling to the integrated avionics units and to the transponder A fan located forward of the instrument panel removes air from between the firewall bulkhead and instrument pane...

Страница 288: ...ata Link receiver A blade type navigation antenna is mounted on either side of the vertical stabilizer This antenna provides VOR and glideslope signals to the VHF navigation receivers contained in the...

Страница 289: ...d console Volume and output for this speaker are controlled through the audio panel Each control wheel contains a push to talk switch This switch allows the pilot or front passenger to transmit on the...

Страница 290: ...ription and operating instructions of the audio panel refer to the Garmin G1000 CRG Since the entertainment audio input is not controlled by a switch there is no way to deselect the entertainment sour...

Страница 291: ...ted on the center pedestal Refer to Figure 7 2 A switch located on the switch panel labeled CABIN PWR 12V controls the operation of the power outlet CAUTION CHARGING OF LITHIUM BATTERIES MAY CAUSE THE...

Страница 292: ...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 avoid...

Страница 293: ...c approximately 125 psi and the operating lever lock pin is securely in place To operate the fire extinguisher 1 Loosen retaining clamp s and remove extinguisher from bracket 2 Hold extinguisher uprig...

Страница 294: ...nses a CO level of 50 parts per million PPM by volume or greater the alarm turns on a flashing warning annunciation CO LVL HIGH in the annunciation window on the PFD with a continuous tone until the P...

Страница 295: ...5 Airplane File 8 6 Airplane Inspection Periods 8 7 FAA Required Inspections 8 7 Cessna Inspection Programs 8 7 Cessna Customer Care Program 8 8 Pilot Conducted Preventive Maintenance 8 8 Alterations...

Страница 296: ...ntinued Page Fuel 8 15 Approved Fuel Grades And Colors 8 15 Fuel Capacity 8 15 Fuel Additives 8 16 Fuel Contamination 8 20 Landing Gear 8 21 Cleaning And Care 8 22 Windshield And Windows 8 22 Painted...

Страница 297: ...hen lubrications and 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 air...

Страница 298: ...Copies of the actual bulletins are available from Cessna Service Stations and Cessna Propeller Aircraft Customer Services UNITED STATES AIRPLANE OWNERS If your airplane is registered in the U S appro...

Страница 299: ...her supplies that are applicable to your airplane are available from a Cessna Service Station Information Manual contains Pilot s Operating Handbook Information Maintenance Manual Wiring Diagram Manua...

Страница 300: ...Pilot s Operating Handbook and FAA Approved Airplane Flight Manual 2 Garmin G1000 Cockpit Reference Guide 190 00384 00 Rev B or subsequent 3 Weight and Balance and associated papers latest copy of the...

Страница 301: ...ith a Progressive Care Inspection Program or a PhaseCard Inspection Program Both programs offer systems which allow the work load to be divided into smaller operations that can be accomplished in shor...

Страница 302: ...ou by any Cessna Service Station in most cases you will prefer to have the Cessna Service Station from whom you purchased the airplane accomplish this work PILOT CONDUCTED PREVENTIVE MAINTENANCE A cer...

Страница 303: ...gear turning angle of 30 either side of center or damage to the nose landing gear will result CAUTION REMOVE ANY INSTALLED RUDDER LOCK BEFORE TOWING If the airplane is towed or pushed over a rough su...

Страница 304: ...refer to the Maintenance Manual for specific procedures and equipment required Individual main gear may be jacked by using the jack pad which is incorporated in the main landing gear strut step bracke...

Страница 305: ...rplanes that are flown every 30 days or less may not achieve normal service life because of internal corrosion Corrosion occurs when moisture from the air and the products of combustion combine to att...

Страница 306: ...ines all items which require attention at specific intervals plus those items which require servicing inspection and or testing at special intervals Since Cessna Service Stations conduct all service i...

Страница 307: ...nforming to Textron Lycoming Service Instruction No 1014 and all revisions and supplements thereto must be used after first 50 hours or oil consumption has stabilized RECOMMENDED VISCOSITY FOR TEMPERA...

Страница 308: ...engine manufacturer NOTE During the first 25 hour oil and filter change a general inspection of the overall engine compartment is required Items which are not normally checked during a preflight insp...

Страница 309: ...Refer to Fuel Additives in later paragraphs for additional information FUEL CAPACITY 56 0 U S Gallons Total 28 0 U S Gallons per tank NOTE To ensure maximum fuel capacity when refueling and minimize...

Страница 310: ...ions are quite rare and will not normally pose a problem to owners and operators they do exist in certain areas of the world and consequently must be dealt with when encountered Therefore to help alle...

Страница 311: ...significant because alcohol is most effective when it is completely dissolved in the fuel To ensure proper mixing the following is recommended 1 For best results the alcohol should be added during th...

Страница 312: ...SECTION 8 CESSNA AIRPLANE HANDLING SERVICE MODEL 172S NAV III AND MAINTENANCE GFC 700 AFCS U S FUEL MIXING RATIO Figure 8 1 172SPHBUS 00 8 18...

Страница 313: ...N DETRIMENTAL EFFECTS TO THE FUEL TANK AND SEALANT AND DAMAGE TO O RINGS AND SEALS USED IN THE FUEL SYSTEM AND ENGINE COMPONENTS A CONCENTRATION OF LESS THAN THAT RECOMMENDED 0 10 BY TOTAL VOLUME MINI...

Страница 314: ...ontamination has been removed If after repeated sampling evidence of contamination still exists the airplane should not be flown Tanks should be drained and system purged by qualified maintenance pers...

Страница 315: ...landing gear Keep strut filled with MIL H 5606 hydraulic fluid per filling instructions placard and with no load on the strut inflate with air to 45 0 PSI Do not over inflate COMPONENT SERVICING CRITE...

Страница 316: ...HE PLASTIC AND MAY CAUSE IT TO CRAZE If a windshield cleaner is not available the plastic can be cleaned with soft cloths moistened with Stoddard solvent to remove oil and grease Follow by carefully w...

Страница 317: ...rdance with the manufacturer s instructions If the airplane is operated in a seacoast or other salt water environment it must be washed and waxed more frequently to assure adequate protection Special...

Страница 318: ...result in cracks or failure of the propeller blade Never use an alkaline cleaner on the blades remove grease and dirt with Stoddard solvent ENGINE CARE The engine may be cleaned using a suitable solv...

Страница 319: ...s 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 da...

Страница 320: ......

Страница 321: ...nsure all applicable supplements have been placed in the Pilot s Operating Handbook POH Supplements for both standard and installed optional equipment must be maintained to the latest revision Those s...

Страница 322: ......

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