Pilot's Operating Handbook and FAA Approved Airplane Flight Manual

the revisions must be incorporated as they are issued. As revisions lare issued, they wi ll be noted in the Log of Effective Pages. The part number of this manual has also been designed to further aid the owner/operator in determining the revision level of any POH. Refer to the example below for a breakdown: 172S PHAUS -00 T L Revision Level (ReVision 0, Original Issue) L Manual (Pilot's Operating Handbook, NAV III, U.S.) "-- - - --- Airplane Model (172S Serials 172S9610 and On) vi U .S . 172SPHAUS-Ol CESSNA INTRODUCTION MODEL 172S NAV III ORIGINAL ISSUE AND REVISIONS (Continued) It is the responsibility of the owner to maintain this handbook in a current status when it is being used for operational purposes. Owners should contact their local Cessna Service Station whenever the revision status of their handbook is in question. Revisions are distributed to owners of U.S. Registered Aircraft according to FAA records at the time of revision issuance, and to Internationally Registered Aircraft according to Cessna Owner Advisory records at the time of issuance. Revisions should be read carefully upon receipt and incorporated in this POH. REVISION FILING INSTRUCTIONS REGULAR REVtSIONS Pages to be removed or inserted in the Pilots' Operating Handbook and FAA Approved Airplane Flight Manual are determined by the Log of Effective Pages located in this section. This log contains the page number and revision level for each page within the POH. As revisions to the POH occur, the revision level on effected pages is updated. When two pages display the same page number, the page with the latest revision level shall be inserted into the POH. The revision level on the Log Of Effective Pages shall also agree with the revision level of the page in question. TEMPORARY REVISIONS Under limited circumstances, temporary 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. The recession of a temporary revision is accomplished by incorporation into the POH at revision time or by a superseding temporary revision. In order to accurately track the status of temporary revisions as they pertain to a POH , a Temporary Revision List will be located previous to this section when required. This list will indicate the date the temporary revision was incorporated into the POH, thus authorizing the recession of the temporary revision. 172SPHAUS-01 U.S. vii INTRODUCTION CESSNA MODEL 172S NAV III IDENTIFYING REVISED MATERIAL A bar located in the outer margin adjacent to the applicable text will extend the full length of new pages and deleted, new, or revised text added on new or presently existing pages. A bar in the footer will indicate a revision to the header/footer, a new page, format or spelling/grammar changes and/or that information has slipped to or from that page. A bar located adjacent to the figure number in the outer margin will be used to indicate that the figure number only has changed. A miniature pointing hand __ will be used to indicate that an illustration has been revised or is all new material. The miniature hand will point to the figure number. All revised pages will carry the revision number opposite the page number on the applicable page. A list of revisions is located at the beginning of the Log Of Effective Pages. WARNINGS, CAUTIONS AND NOTES Throughout the text, warnings, cautions and notes pertaining to airplane handling and operations are utilized. These adjuncts to the text are used to highlight or emphasize important points. WARNING OPERATING PROCEDURES, TECHNIQUES, ETC., WHICH WILL RESULT IN PERSONAL INJURY OR LOSS OF LIFE IF NOT CAREFULLY FOLLOWED. CAUTION OPERATION PROCEDURES, TECHNIQUES , ETC., WHICH WILL RESULT IN DAMAGE TO EQUIPMENT IF NOT CAREFULLY FOLLOWED. NOTE An operating procedure, technique, etc., which is considered essential to emphasize. viii U.S. 172SPHAUS-03 CESSNA INTRODUCTION MODEL 172S NAV III LOG OF EFFECTIVE PAGES Use this page to determine the currency and applicability of your POH . Pages affected by the current revision are indicated by an asterisk n preceding the pages listed under the Page column . Revision Number Date Revision Number Date Original 25 February 2005 Revision 2 19 July 2005 Revision 1 30 June 2005 Revision 3 22 December 2005 Page Page Revision Number Status Number • Title Revised 3 As signment Record Revised 1 • i/ii Revised 3 iii Original 0 iv thru vii Revised 1 • viii thru xi/x ii Revised 3 • xiii/xiv Added 3 1-1 / 1-2 thru 1-28 Original 0 • 2-1 /2-2 thru 2-11 Revised 3 2-12 Revised 2 2-13 Original 0 • 2-14 Revised 3 2-15 Revised 2 • 2-16 thru 2-20 Revised 3 • 2-21 thru 2-22 Added 3 3-1 Revised 1 • 3-2 thru 3-3/3-4 Revised 3 3-5 Revised 1 · 3-6 thru 3-21 Revised 3 3-22 thru 3-25 Revised 1 • 3-26 thru 3-30 Revised 3 (Continued Next Page) 1172SPHAUS-03 U.S. ix INTRODUCTION CESSNA MODEL 172S NAV III LOG OF EFFECTIVE PAGES (Continued) Page Page Revision Number Status Number 3-31 thru 3-33 Revised 1 • 3-34 Revised 3 3-35 Revised 1 • 3-36 Revised 3 • 4-1 thru 4-8 Revised 3 4-9 Original 0 • 4-10 thru 4-50 Revised 3 5-1/5-2 thru 5-23/5-24 Original 0 6-116-2 thru 6-23/6-24 Revised 1 7-1 thru 7-2 Original 0 • 7-3/7-4 Revised 3 7-5 thru 7-10 Original 0 • 7-11 thru 7-12 Revised 3 7-13 thru 7-35 Original 0 • 7-36 Revised 3 7-37 thru 7-44 Original 0 • 7-45 thru 7-48 Revised 3 7-49 thru 7-54 Original 0 • 7-55 thru 7-56 Revised 3 7 -57 thru 7-58 Original 0 • 7-59 thru 7-60 Revised 3 7-61 thru 7-62 Original 0 • 7-63 thru 7-65 Revised 3 7-66 Original 0 • 7-67 thru 7-68 Revised 3 7-69 Original 0 • 7-70 thru 7-72 Revised 3 (Continued Next Page) Ix U .S. 172SPHAUS-03 CESSNA INTRODUCTION MODEL 172S NAV III LOG OF EFFECTIVE PAGES (Continued) Page Number • 8-1 thru 8-2 8-3 thru 8-12 • 8-13 8-14 thru 8-24 • 8-25 thru 8-26 9-1/9-2 APPROVED BY Page Status Revised Original Revised Original Revised Original FMN'PA:M;O IHD W CI'III Hlfrlt aewrr J -- ... ~CI&IbI~~ If........ E.A/I ~ DATE OF APPROVAL £;1.. 1:)1i:~~ U"§ I 172SPHAUS-03 RevIsion Number 3 0 3 0 3 0 u.S. xi/ xii CESSNA INTRODUCTION MODEL 172S NAV III TABLE OF CONTENTS SECTION GENERAL 1 LIMITATIONS . . ...... . . ... ........ .. ... 2 EMERGENCY PROCEDURES . . .... .. .. .. .. 3 NORMAL PROCEDURES ..... . . ..... .. .. . 4 PERFORMANCE .. . . . . . .. .. ........ . .... 5 WEIGHT AND BALANCE/EQUIPMENT LIST. . .. 6 AIRPLANE AND SYSTEMS DESCRIPTION .. . . 7 HANDLING, SERVICE AND MAINTENANCE ... 8 SUPPLEMENTS .... . . . . . . ... . ... . . ..... 9 I 172S PHA US -0 3 U .S . xiii/xiv CESSNA MODEL 172S NAV II I SECTION 1 GEN ER AL GENERAL TABL E OF CONTENTS Three View - Norm al Groun d Attitude .. . . . ... . ... . . .••. . Introduc ti on Descriptive Data .... .. . •• ••.. ... .. . ... . . . . . . . ... .. Engine . ... . . . . ... .. ... . . .. . .. .. . .... . . . . ... . . Prope ll er . .. •........... . .. ... . .. ... .. .. .. •••• . Fu el ... .... . .. . ............... . . ..... . .. .... . Oil Maximum Certificated Weights . . .. . .... ... .. .... .. . Standa rd Ai rp lane Weigh ts . . . . . .. ... . . . . ... . .. ... . Cabin And Entry Dimensions . .. ..... . .. . .. . .. ... . . . Baggage Space And En try Dimensions . . . .. .. ... . .. . . Speci fi c Loadings . ........ . .. . ..... .... ...... . . . Symbols. Abbreviations and Terminology .... . . . .. .... .. . General Airspeed Term in ology And Symbols ... ... . . . . . Meteorological Terminology .. ..... ..... .... . . ... . . En gine Power Term in ology .... . .. ...... . ... . . . . . . Air pl ane Performance And Fl ig ht Planning Termin ology Weight And Balance Termino logy . . . ... .. . . ..... .. . Metric / Impe ri al / U.S. Conversion Cha rt s . . . .•• ....... . Weight Conversions ... .. . .... . ... . ... ... . . . .. . . Length Conversions ... . . . . .. . .. . . ... .. . ... . .. . . D is tance Conversions ... . ... .... . . ..... .. .. •.... Page 1-3 1- 5 1-5 1-5 1-5 1- 5 1- 6 1-7 1-8 1- 8 1-8 1- 8 1-9 1-9 1 -1 0 1-10 1 -11 1 -1 2 1-14 1-15 1-17 1- 2 1 Vo lu me Convers ions .. . .. .. ... . ...... . . . . . . . .... 1-22 Temperature Conversions ...... . .... . . . . .. . . . . . . . 1- 25 Hectopascals to Inches Mercu ry .. . . . .... . . ... . . . . . 1- 26 Volume to Weight Conversions . . .. . ... ... ... .. . . .. 1-27 Quick Conversions . . . .... ... .. . . .. . . . . . . .. .. . . . 1-28 172S PH AU S-OO U.S. 1-1/1-2 CESSNA MODEL 172S NAV III II SECTION 1 GENERAL 1+-1'---- 36'-1" --- ----+1'1 76" MAX QI'i,CT,002 05'OT11)D3 Figure 1-1. Three View - Normal Ground Attitude (Sheet 1 of 2) 172SPHAUS-OO U.S. 1-3 SECTION 1 GENERAL CESSNA MODEL 172S NAV III -1+----------- 27'-2" --------+1 NOTE • Wing span is shown with strobe lights installed. • Wheel base length is 65" . • Propeller ground clearance is 11 1/4". • Wing area is 174 square feet. • Minimum turning radius (. pivot point to outboard wing tip) is 27' -5 1/2". • Normal ground attitude is shown with nose strut showing approximately 2" of strut, and wings level. 8' -11 ' MAX. Figure 1-1. Three View - Normal Ground Attitude (Sheet 2) 1-4 U.S. 172SPHAUS-OO CESSNA MODEL 172S NAV III INTRODUCTION SECTION 1 GENERAL This handbook contains 9 sections, and includes the material required to be furnished to the pilot by FAR Part 23. It also contains supplemental data supplied by Cessna Aircraft Company. Section 1 provides basic data and information of general interest. It also contains definitions or explanations of symbols, 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 drive, air-cooled , horizontally opposed, fuel injected, four cylinder engine with 360 cu . in. displacement. Horsepower Rating and Engine Speed: 180 rated BHP at 2700 RPM. PROPELLER Propeller Manufacturer: McCauley Propeller Systems. Propeller Model Number: 1A 170E/JHA7660. Number of Blades: 2. Propeller Diameter: 76 inches. Propeller Type: Fixed pitch. FUEL WARNING USE OF UNAPPROVED FUELS MAY RESULT IN DAMAGE TO THE ENGINE AND FUEL SYSTEM COMPONENTS, RESULTING IN POSSIBLE ENGINE FAILURE. Approved Fuel Grades (and Colors): 1OOLL Grade Aviation Fuel (Blue). 100 Grade Aviation Fuel (Green). (Continued Next Page) 172SPHAUS-OO U.S. 1-5 SECTION 1 GENERAL CESSNA MODEL 172S NAV III FUEL (Continued) NOTE Isopropyl alcohol or diethylene glycol mono methyl ether (D iEGME) may be added to the 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. 53.0 U.S. gallons. Total Usable: Total Capacity Each Tank: 28.0 U.S. gallons. Total Usable Each Tank: 26 .5 U.S. gallons. OIL NOTE To ensure maximum fuel capacity and minimize cross-feeding when refueling, always park the airplane in a wings-level, normal ground attitude and place the fuel selector in the Left or Right position. Refer to Figure 1-1 for normal ground attitude dimensions. Oil Specification: MIL-L-6082 or SAE J1966 Aviation Grade Straight Mineral Oil: Used when the airplane was delivered from the factory and should be used to replenish the supply during the first 25 hours. This oil should be drained and the filter changed after the first 25 hours of operation. Refill the engine with MIL-L-6082 or SAE J1966 Aviation Grade Straight Mineral Oil 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 the latest revision and/or supplements to Textron Lycoming Service Instruction No. 1014, must be used after first 50 hours or once oil consumption has stabilized. (Continued Next Page) 1-6 U.S. 172SPHAUS-00 CESSNA MODEL 172S NAV III OIL (Continued) SECTION 1 GENERAL Recommended Viscos it y for Temperature Range : Temperature MIL-L-6082 MIL-L-22851 or SAE or J1899 SAE J1966 Ashless Dispersant Straight SAE Grade Mineral Oil SAE Grade Above 27"C (80° F) 60 15W-50, 20W-50 or 60 Above 16°C (60° F) 50 40 or 50 -1 °C (30° F) to 32°C (90° F) 40 40 -18°C (0° F) to 21 °C (70° F) 30 30, 40 or 20W-40 Below -12°C (10° F) 20 30 or 20W-30 -WC (O°F) 10 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 Capac it y: Sump: 8 U .S. Quarts Total: 9 U .S. Quarts MAXIMUM CERTIFICATED WEIGHTS Ramp Weight Takeoff Weight Landing Weight 172SPHAUS-00 Normal Category: 2558 Ibs . Uti lity Category: 2208 Ibs. Normal Category: 2550 Ibs. Utility Category: 2200 Ibs. Normal Category: 2550 Ibs. Utility Category: 2200 Ib s. (Continued Next Page) U.S. 1-7 SECTION 1 GENERAL CESSNA MODEL 172S NAV III MAXIMUM CERTIFICATED WEIGHTS (Continued) Weight in Baggage Compartment, Normal Category: Baggage Area 1 (Station 82 to 108): 120 Ibs . See note below. Baggage Area 2 (Station 108 to 142): 50 Ib s. See note below. NOTE The maximum co mbined weight capacity for Baggage Area 1 and Baggage Area 2 is 120 Ibs. Weight in Baggage Compartment, Utility Category : In this category, the rear seat must not be occupied and the baggage compartment must be empty. STANDARD AIRPLANE WEIGHTS Standard Empty Weight: Maximum Useful Load , Normal Category Maximum Useful Load, Utility Category: CABIN AND ENTRY DIMENSIONS 16631bs. 8951bs. 5451bs. Detailed dimensions of th e cabin interior a nd 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 Lo ading: Power Loading: 1-8 U.S. 14.7 Ib s./sq. ft. 14.2 Ib s'/ hp. 172SPHAUS-00 CESSNA MODEL 172S NAV III SECTION 1 GENERAL SYMBOLS, ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS KIAS KTAS Vs Vso Vx Vy Knots Calibrated Airspeed is indi ca t ed airspeed co rr ected for position and instrument error and expressed in knots. Knots calibrated airspeed is eq ual to KT AS in standard atmosphere at sea leve l. Knots Indicated Airspeed is the speed shown on the ai rspeed indicator and expressed in knots. Knots True Airspeed is the airspeed expressed in knots relative to undisturbed air which is KCAS corr ec ted for altitude and temperature . Maneuvering Speed is the maxim um speed at which full or abrupt cont rol mo vements may be used with ou t overst ressing the ai rframe. Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. Maximum Structural Cruising Speed is th e speed that should not be exceeded except in smooth air, then on ly with ca ution. Never Exceed Speed is th e speed limit th at may not be exceeded at any time. Stalling Speed or the minimum steady flight speed is the minimum speed at which the airplane is controllable. Stalling Speed or the minimum steady flight speed is the minimum speed at which th e airplane is controllable in the landing configuration at the most forward center of gravity. Best Angle-of-Climb Speed is the speed whi ch resu lt s in the greatest gain of altitude in a gi ven ho ri zo ntal distance. Best Rate-of-Climb Speed is th e speed which res ults in the greatest gain in altitude in a given time . 172SPHAUS -OO U.S. 1-9 SECTION 1 GENERAL CESSNA MODEL 172S NAV III METEOROLOGICAL TERMINOLOGY OAT Outside Air Temperature is the free air static temperature. It may be expressed in either degrees Celsius or degrees Fahrenheit. Standard Temperature Pressure Altitude Standard Temperature is 15°C at sea level pressure altitude and decreases by 2°C for each 1000 feet of altitude. Pressure Altitude is the altitude read from an altimeter when 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 engine speed. Static Static RPM is engine speed attained during a full RPM throttle engine runup when the airplane is on the ground and stationary. MAP Lean Mixture Rich Mixture 1-10 U.S. Manifold Absolute Pressure is the absolute pressure measured in the engine induction system. MAP is measured in units of inches of mercury (inHG) . Decreased proportion of fuel in the fuel-air mixture supplied to the engine. As air density decreases, the amount of fuel required by the engine decreases for a given throttle setting. Adjusting the fuel-air mixture to provide a smaller portion of fuel is known as "leaning" the mixture. Increased proportion of fuel in the fuel-air mixture supplied to the engine. As air density increases, the amount of fuel required by the engine increases for a given throttle setting. Adjusting the fuel-air mixture to provide a greater portion of fuel is known as "richening" the mixture . (Continued Next Page) 172SPHAUS-00 CESSNA MODEL 172S NAV III SECTION 1 GENERAL ENGINE POWER TERMINOLOGY (Continued) Full Rich Idle Cutoff Full Throttle Closed Throttle Mixture control full forward (pushed in, full control travel, toward the panel). Mixture control full aft (pulled out, full control travel, away from the panel). Throttle full forward (pushed in, full control travel, toward the panel) Also known as "full open" throttle. Throttle full aft (pulled out, full control travel, away from the panel). Also known as the throttle "idle" position. AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demon- strated Crosswind Velocity Usable Fuel Unusable Fuel GPH NMPG g Course Datum Demonstrated Crosswind Velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests. The value shown is not considered to be limiting. Usable Fuel is the fuel available for flight planning. Unusable Fuel is the quantity of fuel that can not be safely used in flight. Gallons Per Hour is the amount of fuel consumed per hour. Nautical Miles Per Gallon is the distance which can be expected per gallon of fuel consumed at a specific engine power setting and/or fl ight configuration. 9 is acceleration due to gravity. Course Datum is the compass reference used by the autopilot, along with course deviation, to provide lateral control when tracking a navigation signal. 172SPHAUS-OO U.S . 1-11 SECTION 1 GENERAL CESSNA MODEL 172S NAV III WEIGHT AND BALANCE TERMINOLOGY Reference Datum Station Arm Moment Center of Gravity (C.G.) C.G. Arm C.G . Limits Standard Empty Weight Basic Empty Weight Useful Load 1-12 U.S. Reference Datum is an im aginary vertical plane from which all horizontal distances are measured for balance purposes. Station is a location along the airplane fuselage given in terms of the distance from the reference datum. Arm is the horizontal distance from the reference datum to the center of gravity (C.G.) of an it em. 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 ba lance if suspended. It s distance from the reference datum is found by dividing the total moment by the total weight of the airplane. Center of Gravity Arm is the arm obtained by adding the airplane's individual moments and dividing the sum by th e total weight. Center of Gravity Limits are the extreme center of gravity locations within which the airplane must be operated at a given weight. Standard Empty Weight is the weight of a standard airplane, including unusable fuel, full operating fluids and full engine oil. Basic Empty Weight is the standard empty weight plus the weight of optional equipment. Useful Load is the difference between ramp weight and the basic empty weight. (Continued Ne xt Page) 172SPHAUS-00 CESSNA MODEL 172S NAV III SECTION 1 GENERAL WEIGHT AND BALANCE TERMINOLOGY (Continued) MAC Maximum Ramp Weight Maximum Takeoff Weight Maximum Landing Weight Tare MAC (Mean Aerodynamic Chord) is the chord of an imaginary rectangular airfoil having the same pitching momenls throughoul 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 Takeoff Weight is the maximum weight approved for the start of the takeoff roll. Maximum Landing Weight is the maximum weight approved for the landing touchdown. Tare is the weight of chocks , blocks, stands, etc. used when weighing an airplane , and is included in the scale readings . Tare is deducted from the scale reading to obtain the actual (net) airplane weight. 172SPHAUS-OO u.S. 1-13 SECTION 1 GENERAL CESSNA MODEL 172S NAV III METRIC I IMPERIAL I U.S. CONVERSION CHARTS The following charts have been provided to help international operators convert U.S. measurement supplied with the Pilot's Operat ing Handbook into metric and imperial measurements. The standard followed for measurement units shown, is the National Institute of Standards Technology (NIST), Publication 811, "Guide for the Use of the International System of Units (SI)." Refer to the following pages for these charts. 1-14 U.S. 172SPHAUS-OO CESSNA MODEL 172S NAV III SECTI ON 1 GENERAL (K il ograms x 2.205 = Pounds) (Pound s x .454 = Kilograms) kg 0 1 lb. lb. 0 2.205 10 22.046 24.25 1 20 44 .093 46.297 30 66.139 68.343 40 88.185 90.390 50 110.23 112.44 60 132.28 134.48 70 164.32 156.53 80 176.37 178.57 90 198.42 200.62 100 220.46 222.67 lb . 0 1 kg kg 0 0.454 10 4.536 4.990 20 9.072 9.525 30 13 .608 14.061 40 18.144 18.597 50 22 .680 23.133 60 27.216 27.669 70 31.752 32.205 80 36.287 36.741 90 40.823 41. 277 100 45.359 4 5.813 KILOGRAMS INTO POUNDS KILOGRAMMES EN LlVRES 2 3 4 5 6 lb. lb. lb. lb. lb. 4.4 09 6.614 8.819 11.023 13.228 26.456 28.660 30.865 33.069 35.274 48.502 50.706 52.9 11 55.116 57.320 70.549 72.753 74.957 77.162 79.366 92.594 94.799 97 .003 99.208 101,41 , 14.64 116.85 119.05 121.25 123.46 136.69 138.89 141.10 143.30 1 45.5 1 158.73 160.94 16 3.14 165.35 167.55 180.78 1 82.98 185.19 187.39 189.60 202.83 205 .03 207.24 209.44 211.64 224 . 87 227 .0B 229.28 231.49 233.69 POUNDS INTO KILOGRAMS LlVRES EN KILOGRAMMES 2 3 4 5 6 kg kg kg kg kg 0.907 1.361 1.814 2.268 2.722 5.443 5.897 6.350 6.804 7.257 9.979 10.433 10.886 11.340 11 .793 14.5 15 14.969 15.422 15 .876 16.329 19.051 19.504 19.958 20.412 20.865 23.587 24.040 24.494 24.948 25.40 1 28.123 28.576 29.030 29.484 29.937 32.659 33.1 12 33.566 34.019 34.473 37.195 37.648 38.102 38.555 39.009 41 .731 42.184 42.638 43.091 43 .545 46.266 46.720 47.174 47 .627 48.081 7 8 lb. lb. 15.432 17.637 37.479 39.683 59.525 61.729 81.571 83.776 103.62 105.82 125.66 127.87 147.71 149.91 169.76 17 1. 96 191.80 194 .01 213.85 2 16.05 235.90 238 .10 7 8 kg kg 3.175 3.629 7.71 1 8.165 12 .247 12.701 16.783 17.237 21.319 21.772 25.855 26.303 30.39 1 30.844 34.927 35.380 39.463 39.916 43.999 44.452 48.534 48 .988 Figure 1-2. Weight Conversions (Sheet 1 of 2) 172SPHAUS-OO U.S. 9 lb. 19.842 41.888 63.934 85.980 108.03 130.07 152. 12 174. 17 196.21 218.26 240.30 9 kg 4.082 8.618 13.154 17.690 22.226 26.762 31.298 35.834 40.370 44.906 49.442 1-15 SECTION 1 GENERAL ~, (Ki lograms x 2.205 = Pounds) POUNDS 220 210 200 190 180 170 160 150 140 130 120 110 100 90 80 70 60 50 40 30 20 10 0 CESSNA MODEL 172S NAV III (Pounds x .454 = Kilograms) KILOGRAMS 100 95 90 85 80 75 70 65 60 55 50 45 40 35 30 25 20 15 10 5 Units x 10, 100, etc. 0 05651" 1021 Figure 1-2. Weight Conversions (Sheet 2) 1-16 U.S. 172SPHAUS-OO CESSNA MODEL 172S NAV III SEC TI ON 1 GENERAL (Meters x 3.281 = Feet) (F ee t x .305 =Meters) m 0 1 2 fe et leet leet 0 . .. 3. 281 6.562 10 32.808 36.089 39.370 20 65 .617 68.897 72 .178 30 98.425 101.71 104 .99 40 131.23 134 .51 137 .79 50 164.04 167.32 170.60 60 195.85 200.13 203.41 70 229.66 232.94 236 .22 80 262.47 265.75 269 .03 90 295.27 298.56 30 1.84 100 328.08 331.36 334 .64 It 0 1 2 m m m 0 . .. 0.305 0.610 10 3.048 3.353 3.658 20 6.096 6.40 1 6.706 30 9 .1 44 9.449 9.754 40 12. 192 12.497 12.802 50 15.240 15 .545 15 .850 60 18.288 18.593 18 .89 8 70 21.336 21 .641 21.946 80 24.384 24.689 24.994 90 27 .432 27 .737 28.042 100 30.480 30 .785 31 .090 METE RS INTO FEET METRES EN PIEDS 3 4 5 l ee t fee t feel 9.842 13.123 16.404 42 .651 45.932 49.212 75.459 78.740 82.021 108.27 111.55 114.83 141.08 1 44 .36 147.64 17 3.86 1n ,16 180 .45 206.69 209 .97 213.25 239.50 242 .78 246.06 272.31 275 .59 278.87 305. 12 308.40 311 .68 337.93 34 1.21 344.49 FEET INTO METERS PIEDS EN METRES 3 4 5 m m m 0 . 914 1.219 1.524 3.962 4.267 4.572 7.010 7.315 7.620 10.058 10.363 10.668 13.106 13.4 11 13.7 16 16 .154 16.459 16 .754 19.202 19 .507 19.B12 22 .250 22.555 2 2. 860 25.298 25 .603 25.908 28.346 28 .651 28 .956 31.394 31.699 32 .004 6 7 feet leet 19.685 22.956 52 .493 55.774 85.302 88.582 118.11 121 .39 150.92 154.20 183.73 187.01 216 .53 219 .82 249 .34 252.62 282.15 285.43 314.96 318.24 347 .77 35 1.05 6 7 m m 1.829 2.134 4 .B77 5. 182 7.925 8.230 10.973 11.278 14.021 14. 326 17.069 17 .374 20 .117 20 .422 23.165 23.470 26.213 26.518 29.261 29.566 32.309 32.61 4 Fig ure 1-3 . Length Conve rsions (S heet 1 of 2) 172SPHAUS-00 8 9 feet leet 26.247 29.528 59.055 62.336 91.863 95.144 124 .67 127.95 157.48 160.76 190.29 193.57 223 .10 226 .38 255.90 259.19 288.71 29 1.5 8 321.52 324 .8 0 354 .33 357.61 8 9 m m 2.438 2.743 5.486 5.791 8.534 8.839 11 .582 11 .887 14 .630 14 .935 17.678 17.983 20 .726 21 .031 23 .774 24.079 26.822 27.127 29.870 30 .175 32.918 33 .223 U.S. 1-1 7 SECT ION 1 GENERA L -(Me ters x 3.281 =Feet) FEE T M ETE RS ~ 100 320 r- 95 300 90 280 85 260 80 240 75 70 220 65 200 60 180 55 160 50 45 140 40 12° =r- 35 100 1 30 - 80 - 25 60 20 15 40 10 20 5 0 0 CESSNA MO DEL 172S NAV III (Fee t x .305 =Meters) Uni ts x 10, 10 0, etc. ~w Fi gure 1-3. Length Conversions (Sheet 2) 1-18 U.S. 172SP HAUS-OO CESSNA MODEL 172S NAV III SECTIO N 1 GENERAL (Centimeters x .394 = In ches) ( In ches x 2 .5 4 = Centimeters) em a 1 in. in. 0 ... 0.394 10 3.937 4.33 1 20 7.874 8.268 30 11.811 12.205 40 \5.748 16.142 50 19.685 20.079 60 23.622 24.016 70 27.559 27 .953 80 31.496 3 1. 890 90 35 .433 35.827 100 39 .370 39.764 in. a 1 em em 0 ... 2.54 10 25.40 27.94 20 50.80 53.34 30 76.20 78 .74 40 101.60 104.14 50 127.00 129 .5 4 60 15 2.40 154.94 70 177.80 180.34 80 203.20 205.74 90 228.60 231. 14 100 254 .00 256.54 CENTIMETERS INTO INCHES CENTIMETRES EN POUCES 2 3 4 5 6 in. in . in. in. in. 0.787 1.181 1.575 1. 969 2.362 4 . 724 5.118 5.512 5.906 6.299 8.661 9.055 9.449 9.843 10.236 12.598 12.992 13.386 13.780 14.173 16 .535 16.929 17.323 17.717 18.110 20.472 20.866 21.260 2 1. 654 22 .047 24.409 24.803 25.197 25.591 25.984 28.346 28.740 29.134 29.528 29 .921 32 .283 32.677 33 .07 1 33.465 33.858 36 .220 36.614 37.008 37.402 37.795 40.157 40.551 40.945 41. 339 41.732 INCHES INTO CENTIMETERS POUCES EN CENTIMETRES 2 3 4 5 6 em em em em em 5.08 7.62 10.16 12.70 15 .24 30.48 33.02 35.56 38 .10 40.64 55.88 58 .4 2 60.96 63.50 66 .04 81.28 83.82 86 .36 88 .90 91.44 106.68 109.22 111.76 114.30 11 6.84 132.08 134.62 137.16 139.70 142.24 157.48 160.02 162.56 165.10 167.64 182 .88 185.42 187.96 190.50 193.04 208.28 210.82 213.36 215 .90 2 18.44 233.68 236.22 238.76 241 .30 243.84 259.08 261.62 264 .16 266.70 269.24 7 8 in . in. 2.756 3.150 6.693 7.087 10 .630 , 1.024 14.567 14.961 18.504 18.898 22.44 1 22 .835 26.378 26.772 30.315 30 .709 34.252 34.646 38 .189 38 .583 42 .126 42 .520 7 8 em em 17.78 20.32 43 . 18 45 .72 68 .5 8 71.12 93 .98 96 .52 11 9.38 121.92 144 . 78 147 .32 170. 18 172.72 195.58 198.12 220.98 223.52 246.38 248 .92 27 1.78 274 .32 Fi gure 1-4. Length Conversions (Sheet 1 of 2) 172SPHAUS- OO U .S. 9 In. 3.543 7.480 11.417 15.354 19.291 23.228 27.164 31.102 35.039 38.976 42.913 9 em 22.96 48 .26 73.66 99.06 124.46 149.86 175.26 200.66 226.06 251.46 276.86 1-1 9 SECTION 1 GENERAL CESSNA MODEL 172S NAV III (Centimeters x .394 = Inches) INCHES 10 (Inch es x 2.54 = Centimeters) CENTIMETERS 25 24 9- 23 22 21 8- '----_ 20 19 7 18 17 16 6- '----_15 14 5 13 12 11 4 - -1--'10 9 3 8 7 6 2- -1-- 5 4 3 2 1 Units x 10, 1~O, etc. 0 --'----0 OSlSn :::H Figure 1-4. Length Conversions (Sheet 2) 1-20 U.S. 172SPHAUS-00 CESSNA MOD EL 172S NAV II I - SECTION 1 GENERAL (Statute Miles x 1.609 ; Ki lometers) (Ki lometers x .622 ; Statute Miles) (Statute Miles x .869 ; Nautical Miles) (Nautical M il es x 1. 15 ; Statute Miles) (Nautical Miles x 1.852 ; K il ometers) (Kilomete rs x .54 ; Nautical M il es) STATUTE MI L ES NAUTICAL KI LOMETERS MILES 115 100 100 110 95 95 - - 180 105 90 90 - 170 100 85 85 160 95 - - 150 90 80 80 85 75 75 140 80 70 70 130 75 65 65 120 70 60 60 - 110 65 55 55 - 60 - 100 50 50 - - 90 55 - 50 45 45 80 45 40 40 70 40 35 35 35 - 60 30 30 30 25 25 50 25 20 20 - 40 20 30 15 15 15 10 10 20 10 5 5 5 10 Units x 10, 100, etc. a a a 0 ~' m Fi gure 1-5. D istance Conversio ns 172SPHAUS-OO U.S. 1-2 1 SECT ION 1 GENERAL CESSNA MODEL 172S NAV II I (Imperial Ga ll ons x 4. 546 = Li lers) ( Li lers x .22 = Imp er ial G a ll ons) Lt a 1 IG IG 0 .. . 0.220 10 2.200 2.420 20 4.400 4.620 30 6.599 6.8 19 40 8.799 9.0 19 50 10.999 11.219 60 13. 199 13,4 19 70 15.398 15.618 80 17.598 17.818 90 19.798 20.018 100 21 .998 22.218 IG a 1 Lt Lt 0 .. . 4.546 10 45.460 50.006 20 90 .919 95.465 30 136.38 140 .93 40 181.84 186 .38 50 227.30 231.84 60 272 .76 277.30 70 3 18.22 322 .76 80 363.68 368.22 90 409. 14 413.68 100 454.60 459 .14 LITERS INTO IMPERIAL GALLONS LITRES EN GALLONS IMPE RI AL 2 3 4 5 6 IG IG IG IG IG 0.440 0.660 0.880 1.1 00 1. 320 2.640 2.860 3.080 3.300 3.520 4.840 5.059 5.279 5.499 5.719 7.039 7.259 7.479 7.699 7.9 19 9.239 9.459 9.679 9.899 10. 119 1 1.439 11.65 9 11 .879 12 .099 12.3 19 13.639 13.85 9 14.078 14 .298 14.518 15.838 16.058 16.278 16.498 16.7 18 18.038 18.258 18.478 18.698 18.918 20.238 20.458 20.678 20.898 21. 11 8 22 .438 22.658 22.878 23.098 23 .318 IMPERIAL GALLO NS INTO LITERS GALLONS IMPERI AL EN LITRES 2 3 4 5 6 Lt Lt Lt Lt Lt 9.092 13.638 18.184 22. 7 30 27.276 54.552 59.097 63.643 68. 189 72.735 100.D1 104.56 109. 10 11 3.65 11 8.20 145 .4 7 150.02 154.56 159. 11 163.66 190 .93 195.48 200 .02 204 .57 209 . 11 236 .39 240 .94 245.48 250.03 254.57 281.85 286.40 290.94 295.49 300.03 327.31 331.86 336.40 340.95 345.49 372.77 377.32 381 .86 386.41 390.95 418.23 422 .77 427 .32 43 1. 87 436 .41 463 .69 468.23 472 .78 477.33 48 1.87 7 8 9 IG IG IG 1.540 1.760 1. 980 3.740 3.960 4.180 5.939 6.159 6.379 8. 139 8.359 8.579 10.339 10.559 10.779 12.539 12.759 12.979 14 .738 14.958 15.178 16.938 17.158 17.378 19. 138 19.358 19.578 2 1.338 21.558 21.778 23.537 23.757 23.977 7 8 9 Lt Lt Lt 3 1. 822 36.368 40.91 4 77.281 8 1.827 86.373 122 .74 127.29 131.83 168.20 172.75 177.29 213 .66 2 18.21 222 .75 259.12 263.67 268.21 304.58 309.13 3 13.67 350.04 354 .59 359.13 395.50 400 .04 404 .59 440.96 445.50 450 .05 486.42 490.96 495 .5 1 Fi gure 1-6 . Volume Conversions (Sheet 1 of 3) 1-22 U.S. 172S PH AUS- OO CESSNA MODEL 172S NAV III ( Im perial Ga ll ons x 4.4546 = Liters) (Liters x .22 = Imperial Ga ll ons) 100 IMPERIAL 440 LITERS 95 GALLONS 420 90 400 85 380 80 360 75 340 70 320 65 300 60 280 260 55 240 50 220 45 200 40 180 35 160 30 140 25 120 20 10 0 80 15 60 10 40 5 20 0 0 Units x 10, 100 , etc. Fi gure 1-6 . Vo lu me Conversions (Sheet 2) 172SP HAUS-00 SECTI ON 1 GEN ER AL 0585T1032 U. S. 1- 23 SECTION 1 CESSNA GENERAL MODEL 172S NAV III , ~ (Imperial Gallons x 1.2 = U.S. Ga ll ons) (U .S. Gallons x .833 = Imperial Ga ll ons) (U .S. Gallons x 3.785 = Liters) (Liters x .264 = U.S. Gallons) IMPERIAL U. S. LI TERS GALLONS 100 120 GALLONS 100 95 115 95 360 90 110 90 340 105 85 100 85 320 80 95 80 300 75 90 75 280 70 85 70 260 65 80 65 75 240 60 70 60 220 55 65 55 200 50 60 50 55 180 45 45 50 160 40 40 45 140 35 40 35 30 30 120 35 25 30 25 100 20 25 20 80 15 20 15 60 15 40 10 10 10 5 5 5 20 0 0 0 0 Units x 10,100, etc. 0585T1 033 Figure 1-6. Volume Conversions (Sheet 3) 1-24 U.S. 172SPHAUS-00 CESSNA MODEL 172S NAV III TEMPERATURE CONVERSIONS (0 F-32) x 5/9 = 0C °Cx9/5 +32= of OF -l 0C of °C -40 -40 320 - 160 -30 -= 340 · 20 · -30 36 180 -10 380 - a -20 400 200 10 - -10 420 - 220 20 - 440 30 ~ 0 460 --' • 240 40 480 ..... 50 - 10 500 - 260 60 : 520 -'; 70 _ 20 540 :: 280 80 : 90 -, 30 560 - 580 -' 300 100 · 40 600 ' 320 110 - 620 120. 50 640 -, 340 130 _ 660 - 140 ~ 60 680 - 360 150 : 700 : 160 ... 70 720 380 170 :: 740 180 : 80 - 400 760 - 190-: 90 780- 420 200 - 800 2 10 · 100 820 440 220 840 -= 230 110 860 - 460 240 ~ 880 - 250 -:: 120 900- 480 26 • 920 · 270= 130 940 - 500 280 140 960 520 290 ..... 980 300 , 150 1000 : 540 310 1020 320 160 104 560 Figure 1-7. Temperature Conversions 172SPHAUS-OO SECTION 1 GENERAL 0585T1034 U.S. 1-25 SECTION 1 GENERAL CESSNA MODEL 172S NAV III PRESSURE CONVERSION HECTOPASCALS (MILLIBARS) TO INCHES MERCURY (inHG) 1-26 U.S. ~ : _ 51 §-: ::- ~ a-:, ;; -. i e: _ • , ~: jl 1- ; . 1 - . • I_ Ii- • : ~ i i -oli- ~ M-. i'- ; ~ '-f . 0 ' _ • • 1 - ;I ~ iI ~ ~ ~ ~. - -.11 -": §.- • es ' ."~ r! ~ Figure 1-8. Hectopascals to Inches Mercury 172SPHAUS-OO CESSNA SECTION 1 MODEL 172S NAV I II GENERAL - AVGAS Specific Gravity = .72 (Liters x .72 =Kilograms) (Kilograms x 1.389 =Liters) (Liters x 1.58 = Pounds) (Pounds x .633 =Liters) LITERS POUNDS LITERS KILOGRAMS 100 100 135 95 150 130 95 90 140 125 90 85 120 85 130 AVGAS FUE L 115 80 110 80 75 120 105 75 70 110 100 95 70 65 100 90 65 60 85 60 90 80 55 75 55 50 80 70 50 45 65 45 70 60 40 60 55 40 35 50 35 50 45 30 40 30 25 40 35 25 20 30 20 30 25 15 20 15 20 15 10 10 10 10 - 5 5 5 0 0 0 0 Units x 10, 100, etc. - , ~ Figure 1-9 . Volume to Weight Conversion 172SPHAUS-OO u.S . 1-27 SECTION 1 GENERAL """ AV GAS SPEC IFIC GRAVITY 0.72 1-28 U.S. IMPERIAL GALLONSi-----( CESSNA MODEL 172S NAV III 2.2 0585T1031 Figure 1-10. Quick Conversions 172SPHAUS-00 CESSNA MODEL 172S NAV III SECTION 2 OPE RATING LIMITATIONS OPERATING LIMITATIONS TABLE OF CONTENTS Introduction . ............... . ....... . .. .. .. .. .. .. . Airspeed Limitations ... .. ... . . ........ . .... . ... . .. . Airspeed Indicator Markings .. . .. .. • . .. ...... .. . ...... Powerplant Lim itations ..... .... ...... ... . . .. .... ... . Powerplant Instrument Markings ......... . .. . . ... . ... . Weight Limits ..... . . ... .. . ....•.••••.... .. ....... Normal Category .. ... .... ...... . . . .... . .... ... . . Utility Category ................ .. ........... . .. . Center Of Gravity Limits ... . ...... .... . ... ..•.... ... Normal Category ..... ...... ... ••.. . .. .... ....... Utility Category . . ... ... . ........ . .. .•. .. ...... .. Maneuver Limits ...... . . ... ....... .... . .. ...... .. . Normal Category ............. ••• . ... ..... .. ..... Utility Category . . . ........... . . .. . .. . . ........ . Flight Lo ad Factor Limits .. .. . . . ... .. .. . .. .. . . . . .. . . Normal Category .. ...........••• . . ... .. . . ... ... Utility Category . .................. . . . .... . .. .. . Kinds Of Operation Limits ............ . .••. . ........ Kinds 01 Operations Equipment Li st .. ... . . . .. ..... . Fuel Lim itations ..................... . . .... . . .. . . . Flap Limitations .............. . .. .. . . .......... . . . System Limitations ..... ...... . ............ . .. . .. . Aux Audio System .. . ..• • • ............ . . ... •.... 12V Power System ..... ... ..... .. ......... ... . . G 1000 Limitations ...... ... ..... . ... .. ..... . ..... . Bendix/King KA P 140 2 Axis Autopilot (i f installed) ... .. . Placards . ... ...... .. ........... .... .......... . . Page 2-3 2-4 2-5 2-6 2-7 2-8 2-8 2-8 2-8 2-8 2-9 2-9 2-9 2-10 2- 11 2- 11 2 -11 2-11 2-12 2-16. 2-16 2-17 2 -1 7 2 -1 7 2-18 2-18 2-19 FAA APPROVED 172SPHAUS·03 U.S. 2-1/2-2 CESSNA MODEL 172S NAV III SECTION 2 OPERATING LIMITATIONS INTRODUCTION Section 2 includes operating limitations, instrument markings, and basic placards necessary for the safe operation of the airplane, its engine, standard systems and standard equipment. The limitations included in this section and in Section 9 have been approved by the Federal Aviation Administration. Observance of Ihese operating limitations is required by Federal Aviation Regulations. NOTE • Refer to the Supplements, Section 9, of th is Pilot's Operating Handbook for amended operating limitations, operating procedures, periormance data and other necessary information for airplanes equipped with specific options . • The airspeeds listed in Figure 2-1, Airspeed ILimitations, and Figure 2-2, Airspeed Indicator Markings, are based on Airspeed Calibration data shown in Section 5 with the normal static source. If the alternate static source is being used, ample margins should be observed to allow for the airspeed calibration variations between the normal and alternate static sources as shown in Section 5. The Cessna Model 172S is certificated under FAA Type Certificate NO.3A12. FAA APPROVED 172SPHAUS-03 U. S. 2-3 SECTION 2 OPER ATI NG LIMITATIONS AIRSPEED LIMITATIONS CESSNA MODEL 172S NAV III Airspeed lim it at io ns and th eir operational significance are shown in Figu re 2-1 . Maneuvering speeds shown apply to normal category operations. The utility category maneuvering speed is 98 KIAS at 2200 pounds. SYMBO L VNE VNO VA VFE ---- I 2-4 U.S. AIRSPEED LIM ITAT IONS SPEED KCAS Never Exceed Speed 160 Maximum Structural 126 Cruising Speed Maneuvering Speed: 2550 Pounds 102 2200 Po un ds 95 1900 Pounds 88 Maximum Flap Extended Speed: Fl aps 10' 107 Fl aps 10' to FULL 85 Maximum 160 Window Open Speed Figure 2-1 KIAS 163 129 105 98 90 110 85 163 RE MARKS Do not exceed this speed in any operation. Do not exceed th is speed except in smooth air, and then only with caution. Do no t make fu ll or abrupt cont ro l movements above this speed. Do not exceed this speed wi th flaps down. Do not exceed this speed with windows open. FAA APPROVED 172S PHAUS-03 CESSNA MODEL 17 2S NAV III SECTION 2 OPERATING LIMITATIONS AIRSPEED INDICATOR MARKINGS Airspeed indicator markings and their color code significance are shown in Fi gure 2-2. AIRSPEED INDICATOR MARKINGS KIAS MARKING VALUE SIGNIFICANCE OR RANGE Red Arc' 20 - 40 Low airspeed warn in g. White Arc 40 - 85 Full Flap Operating Range. Lower limit is maximum weight VS o in landing configuration . Upper limit is maximum speed pe rm issible with flaps extended. Green Arc 48 - 129 Normal Operating Range . Lower limit is maximum weight VS 1 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. • Gl000 airspeed indicator only . Figure 2-2 I I FAA APPROVED 172SPHAUS-03 U.S. 2-5 SECTION 2 OPERATING LIMITATIONS POWERPLANT LIMITATIONS Engine Manufacturer: Tex tron Lycoming. Engine Model Number: IO-360-L2A. Maximum Power: 180 BHP rating. CESSNA MODEL 172S NAV III Engine Operating Limits for Takeoff and Continuous Operations: Maximum Engine Sp ee d: . . .... . ......... . . . 2700 RPM NOTE The static RPM range at fu ll throttle is 2300 - 2400 RPM. Maximum Oil Temperature: .............. 245°F (118' C) Oil Pressure, Minimum: ..... .. . .... .. .. ... . ... 20 PSI Oil Pressure, Ma ximum: . ... .... .. . ... .. . . . . .. 115 PSI Fue l Grade: See Fue l Limitations. Oil Grade (Specification): MIL-L-6082 or SAE J1966 Aviation Grade Straight Mineral Oil or MIL-L-22851 or SAE J1899 Ashless Dispersant O il. Oil must comply with the latest revision and/or supplement for Textron Lycoming Service Instruction No.1 014. Propeller Manufacturer: McCauley Propeller Systems. Propeller Model Number: 1A 170ElJHA7660. I Propelier Diameter Ma ximum: 76 INCHES Minimum: 75 INCHES 2-6 U.S. FAA APPROVED 172SPHAUS-03 CESSNA MO DEL 172S NAV III SE CT ION 2 OPERATI NG LI MITATI ONS POWERPLANT INSTRUMENT M ARK INGS Powerpl ant in s tr ument mark in gs and their color cod e significance are shown in Fi gure 2-3. Operation with indica ti ons in the red ra n gel is prohibited . Avoid operating wi th in dicators in the yellow range . POWERPLANT INSTRU MENT MARKINGS GREEN ARC RED RED YELLOW (NOR MAL INSTRUMENT LINE ARC (MIN ) (LwR) ARC OPERATING RANGE ) Tachome t er .... -- -- -. -- RPM Sea Level 2100102500 5000 Feet 2100 to 2600 10,000 Feet 2100 to 270 0 Cylinder -- -- ---- -- -- 200 to 500 °F Head Temp erature Oil -- -- -- -- -- -- l Oa to 245 °F Te mperatur e Oil Pr essure -- -- a to 20 --- - 50 to 90 PS I PS I Fuel 0(1 .5 --- - a 5 to 24 Ga ll on s Quantity Gallon s to 5 Unu sa bl e Ga llons Eac h Tank) Fuel Flo w ---- ---- ---- o to 12 GPH Vacuum ---- --- - --- - 4.5 to 5.5 Indi ca to r i n. hg. Ma ximum operating limit is lower end of red arc . FAA APP ROV ED 172SPHAU S-03 Fi gur e 2-3 RED ARC (UPR) RPM 2700- to 3000 ---- 24 5' to 250°F 11 5- to 120 PSI ---- ---- -- -- I u.S. 2-7 SECTION 2 CESSNA MODEL 172S NAV III OPERATING LIMITATIONS WEIGHT LIMITS NORMAL CATEGORY I Maximum Ramp Weight: Maximum Takeoff Weig ht: Maximum Landing Weight: 2558 POUNDS 2550 POUNDS 2550 POUNDS Maximum Weight in Baggage Compartment: I Baggage Area A - Station 82 to 108: ........ . Baggage Area B - Station 108 to 142: ........ . 120 POUNDS 50 POUNDS I NOTE The maximum combined we ight capacity for baggage areas A and B is 120 Ibs . UTILITY CATEGORY I Ma ximum Ramp Weight: ... . _.... ......... . Maximum Takeoff Wei~ht: ........ . . . ... . .. . Ma Ximum Landing Weight : ...... .. ... ... .. . 2208 POUNDS 2200 POUNDS 2200 POUNDS Maximum Weight in Baggage Compartment: In the utility category, the baggage compartment must be empty a nd rear seat must not be occupied . I I CENTER-OF-GRAVITY LIMITS NORMAL CATEGORY Center-of-Gravity Rang e: Forward: 35 .0 inches aft of datum at 19S 0 pounds or less, with straight line variation to 41.0 in ches aft of datum at 2550 pound s. Aft: 47.3 in ches aft of datum at a ll weights . Ref erence Datum: Lower portion of front face of firewall. 2-8 U.S. FAA APPROVED 172SPHAUS-03 CESSNA MODEL 172S NAV III SECTION 2 OPERATING LIMITATIONS CENTER OF GRAVITY LIMITS (Continued) UTILITY CATEGORY Center of Gravity Range: Forward : 35 .0 inches aft of datum at 1950 pounds. or less, withl straight line variation to 37.5 inches aft of datum at 2200 pounds. I Aft: 40.5 inches aft of datum at all weights. Reference Datum: Lower portion of front face of firewall. MANEUVER LIMITS NORMAL CATEGORY This airplane is certificated in both the normal and utility category. The normal category is applicable to aircraft intended for non aerobatic operations. These include any maneuvers in cidental to normal flying , stalls (except whip stalls), lazy eights, chandelles, and turns in which the angle-of-bank is not more than 60°. NORMAL CATEGORY MANEUVERS AND RECOMMENDED ENTRY SPEED' Chandelles . ..... ... .. ..... .. . ... .. . • • ... . 105 KNOTS ILazy Eights ... . ...... . ......... .......... . 105 KNOTS St e ep Turns ...... ........ ... . . • •.......... 95 KNOTS Stalls (Except Whip Stalls) . .. . .. .. ........ Slow Deceleration • Abrupt use of the controls is prohibited above 105 KIAS. FAA APPROVED 172SPHAUS-03 (Continued Ne xt Page) U.S. 2·9 SECTION 2 OPERATING LIMITATIO NS MANEUVER LIMITS (Cont inu ed) UTILITY CATEGORY CESSNA MODEL 172S NAV III This airplane is not d es ign ed for purely aerobatic flight. However, in the acq ui sition of various cert ifi cates such as commercial pilot and fligh t in structor, certain maneuvers are requir ed by the FAA. All of these maneuvers are permitt ed in th is airplane when operated in th e utility category. In th e utility category, th e rea r seat mu st not be occupied and the baggage compartment must be empty . UTILITY CATEGORY MANEUVERS AND RECOMMENDED ENTRY SPEED' I Chandelies . ..... ..... ....... .... .. .. ... . . 105 KNOTS Lazy Eights ............ . ...... . ........... 105 KNOTS Steep Turns ..... ........ .... . .. ........... 95 KNOTS Spins . . . .. ... .. . .. ... .... ...... . •• • . Slow Decelera ti on Stalls (Except Wh ip Stalls) .... ...... ... . .. Slow Decelera ti on 1* Abrupt use of the controls is prohib ited above 98 KNOTS. Aerobatics that may impose high loa ds should not be attempted. The important thing to bear in mind in fli ght maneuvers is that the airplane is clean in aerodynamic design and will build up speed qu ick ly with the no se down. Proper speed cont ro l is an essen ti al reo quirement for execution of any mane uv er, and care should always be exercised to avoid excessive speed which in turn can impose ex- cessive lo a ds . In the execution of all maneuvers, avoid abrupt use of controls. 2- 10 U.S. FAA APPROVED 172SPHAUS·03 CESSNA MODEL 172S NAV III FLIGHT LOAD FACTOR LIMITS NORMAL CATEGORY SECTION 2 OPERATING LIMITATIONS Flight load Factors (Maximum Takeoff Weight - 2550 POUNDS): I 'Flaps Up ...... .... ............. +3.8g, -1 .52g 'Flaps Down .. . . . . ..... .......... +3.0g , The design load factors are 150% of the abov e, and in all cases, the structure meets or exceeds design loads. UTILITY CATEGORY Flight load Factors (Maximum Takeoff Weight - 2200 POUNDS): I 'Flaps Up ...... . .. . . ... . . ....... +4.4g, -1 .76g ' Flaps 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 Cessna 172S Nav III airplane is approved for day and night, VFR and IFR operations. Flight into known-icing conditions is prohibited. The minimum equipme nt for approv ed operations required under the Operating Rules are defined by 14 CFR Part 91 and 14 CFR Part 135, as applicable. The following Kinds of Operations Equipment List (KOEl) identifies the equipment required to be operational for airplane airworthiness in the listed kind of operations. FAA APPROVED 172SPHAUS-03 U.S. 2-11 SECTION 2 CESSNA MOD EL 172S NA V III OPE R ATING LIM ITAT IONS KIN DS OF OPERATIONS EQU IPMENT LIST KIND OF OPERATION V I F F V R I R F F R N R N I I 0 G 0 G System, Instrument, Equipment A H A H andlor Function y T Y T COMMENTS PLACARDS AND MARKINGS 172S Nav III POH /AFM 1 1 1 1 Accessible to pilot in flight Garmin G1OOOT M Cockpit 1 1 1 1 Accessible to pilot Referen ce Guide in flight AIR CO NDIT IONING 1. Forward Avionics Fan 1 1 1 1 2. PFD Fan 0 0 0 0 3. MFD Fan 0 0 0 0 4. Aft Avionics Fan 1 1 1 1 AUTO FLIGHT 1. Bendi x/ King KAP 140 PO H 0 0 AIR AIR Accessible to pilot Supp lement in flight when usin autopilot COMMUNICATIONS 1. VHF COM 0 0 1 1 ELECTRICAL POWER 1. 24V Main Battery 1 1 1 1 2. 28V Alternator 1 1 1 1 I 3. 24V Standby Battery 0 . . . 'Refer to Note 1 4. Main Ammeter 1 1 1 1 5. Standby Amm eter 0 . . . ' Refer to Note 1 NOTE 1. The Europ ea n Avia tion Safety Agency (EASA) requires the 24V Standby Battery and Standby Ammeter to successfu lly complete the pre-flight ch eck before operating the airp l ane in VFR night , IFR day, or IFR nigh t conditions in Eu rope . Correc t operation of the 24V Standby Battery and Standby Ammeter is recommend ed for all other operations. (Continued Next Page) 2-12 U.S. FAA APPROVED 172SPHAUS-02 CESSNA MODEL 172S NAV III SEC TI ON 2 OPERATING LI MI TATIONS KINDS OF OPERAT IO NS EQUIPMENT LIST (Continued) KIND OF OPERATION V I F F V R I R F F R N R N I I D G D G System, Instrume nt, Equipment A H A H and/o r Function Y T Y T EQUIPMENT AND FURNISH INGS 1. Seat Belt Assembly 1 1 1 1 2. Sho uld er Harness 1 1 1 1 FLIGHT CONTROLS 1. Flap Po si lion Indicator 1 1 1 1 2. Flap Motor 1 1 1 1 3. Elevalor Trim System 1 1 1 1 4. Elevator Trim Indicator 1 1 1 1 FUEL SYST EM 1. Elec tric Fuel Pump 1 1 1 1 2. Fu el Quantily Indica lor - LH 1 1 1 1 Tank 3. Fu el Quantity Indicator - RH 1 1 1 1 Tank ICE AND RAIN PROTECTION 1. Alternate Static Air Source a a 1 1 2. Alte rn ate Induction Ai r a a 1 1 System INDICATING/RECORDI NG SYSTEM 1. Sta ll Wa rning System 1 1 1 1 2. System Annunciator and 1 1 1 1 Warning Di splays LANDING GEAR 1. Wheel Fairings a a a a (Continued Next Page) FAA APPROVED 172SPHAUS-OO COMMENTS E ac h Seat Occupant Front Seat Occupants Re movable U.S. 2- 13 SECTION 2 CESSNA MODEL 172S NAV III OPER AT ING LI MITATIONS KINDS OF OPERATIONS EQU IPMENT LIST (Continued) I I I KIND OF OPERATION V I F F V R I R F F R N R N I I 0 G 0 G System, Instrument, Equipment A H A H and/or Function y T Y T COMMENTS LIGHTING 1. PFD Bezel Lighting 0 0 0 1 2. PFD Backlighting . 1 1 1 "Refer to Note 2 3. MFO Bezel Lighting 0 0 0 1 4. MFD Backlighting . 1 1 1 "Refer to Note 3 5. Switch and Circuit Breaker 0 1 0 1 Panel Lighting 6. Airspeed Indicator (Standby) 0 1 0 1 Internal Lighting 7. Altimeter (Standby) Internal 0 1 0 1 Lighting 8. Non-stabilized Magnetic 0 1 0 1 Compass Internal Lighting 9. Attitude Indicator (Vacuum) a 1 a 1 Internal Lighting 10. Cockpit Flood Light 0 1 0 1 11 . Aircraft Position (NAV) a 1 1 1 Lights 12. STROBE Light System 1 1 1 1 13. BEACON Light a 0 0 0 14. TAXI Light a 0 0 0 15 . LAND (Landing) Light a 1 0 1 Operations for hire only NOTE 2. PFD backlighting is required for day VFR f li ght if MFD backlighting has failed. Display backup mode must be active so engine indicators are shown . 3. MFD backlighting is requ ired for day VFR flight if P FD backlighting has failed . Display backup mode must be active so flight instruments are shown. (Continued Next Page) 2-14 U.S. FAA APPROVED 172SPHAUS-03 CESSNA MOD EL 172S NAV III SECTION 2 OPERATING LI MITATIONS KINDS OF OPE RA TIONS EQUIPMENT LI ST (Continued) Syslem, In strum en t, Equipmenl and/o r Fu nc ti on NAVI GA TION AND PITOT- STATIC SYSTEM 1. Gl 000 Ai rspeed Indi ca lor 2. Standby Ai rspeed Indicator 3. G 1000 Allimeter 4. Standby Alti me ter 5. G1000 Ve rt ical Sp ee d In dicator 6. Gl 000 Atlitude Indicator 7. Atlitude Indicator - Vacuum (S tandby) 8. G l0 00 Direc ti onal Indicator (H SI) 9. G 1000 Turn Coord in ator 10. Non-stabilize d Magnel ic Compass 11 . VHF Naviga ti on Radi o (VOR/LOC/GS) 12. GPS Recei ve r/Nav ig ator 13 . Ma rk er Beacon Receiver 14 . Blind Altitude En coder 15. Clock VAC UU M 1. Eng in e- dri ven Vac uum Pump 2. Vac uum Indicator ENG INE FUEL AN D CONTROL 1. Fu el Flow Indicator EN GINE INDICATING 1. Tachomeler (RPM) 2. Cy linder Head Te mp era tu re (C HT) Indicator 3. Oi l Pressure Indica tor 4. O il Temperature Indicator ENGINE OIL 1. Eng in e Crankcase Dip sti ck IFAA APPROVED 172SPHAU S- 02 KIND OF OPERATION V I F F V R I R F F R N R N I I D G D G A H A H Y T Y T CO MMENTS 1 1 1 1 0 0 1 1 1 1 1 1 0 0 1 1 0 0 0 0 0 0 1 1 0 0 1 1 0 0 1 1 0 0 1 1 1 1 1 1 0 0 AIR AIR As Required Per Pr oce dur e 0 0 AIR AIR As Required Per Procedure a a AIR AIR As Required Per Procedure AIR AI R 1 1 As Required Per Proce dur e 0 0 1 1 a 0 1 1 a 0 1 1 1 1 1 1 1 1 1 1 0 0 0 0 1 1 1 1 1 1 1 1 1 1 1 1 U.S. 2-15 SECTION 2 CESSNA MODEL 172S NAV III OPERATING LIMITATIONS I FUEL LIMITATIONS Total Fuel: .... 56 U.S. gallons (2 ta nk s at 28.0 gallons each) Usable Fuel (all flight conditions): . . . . . . . .. 53.0 U.S. gallons Unusable Fuel: . ... .. 3.0 U .S . gallons (1.5 gallons each tank) NOTE To ensure maximum fuel capacity and minimize cross-feeding when refueling, always park the airplane in a wings-level, normal ground attitude and place the fuel selector in the Left or Right position. Refer to Figure 1-1 for normal ground attitude definition. Takeoff and land with th e fuel se lector valve handle in the BOTH position. Maximum slip or skid duration with one tank dry: 30 seconds. Operation on either LEFT or RIGHT tank limit ed 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 indicator reads 0 (red line) cannot be safely us ed in flight. Approved Fuel Grades (and Colors): 100LL Grade Aviation Fuel (Blue). 100 Grade Aviation Fu el (Green). I FLAP LIMITATIONS Approved Takeoff Range: Approved Landing Range: 2-16 U.S. UP to 10° UP to FULL FAA APPROVED 172SPHAUS-03 CESSNA MODEL 172S NAV III SYSTEM LIMITATIONS AUX AUDIO SYSTEM SECTION 2 OPERATING LIMITATIONS Use of the AUX AUDIO IN entertainment input is prohibited during takeoff and landing. Use of the AUX AUDIO IN entertainment audio input and portable electronic devices (PED) such as cellular telephones, games, cassette, CD or MP3 players is prohibited under IFR unless the operator of the airplane has determined that the use of the Aux Audio System 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 - 10A) is not certified for supplying power to flight-critical communications or navigation devices. Use of the 12 Volt Power System is prohibited during takeoff and landing. Use of the 12 Volt Power System is prohibited under IFR unless the operator of the airplane has determined that the use of the 12 VDC power supply and connected portable electronic device(s) will not cause interference with the navigation or communication systems of the airplane. IFAA APPROVED 172SPHAUS-03 U.S. 2-17 SECTION 2 OPERATING LIMITATIONS G1000 LIMITATIONS CESSNA MODEL 172S NAV III The current Garmin G1000 Cockpit Reference Guide (CRG) Part Number and System Software Version that must be available to the pilot during flight are displayed on the MFD AUX group, SYSTEM STATUS page . Use of the NAVIGATION MAP page for pilotage navigation is prohibited. The NAVIGATION MAP is intended only to enhance situational awareness. Navigation is to be conducted using only current charts, data and authorized navigation facilities. Use of the TRAFFIC MAP to maneuver the airplane to avoid traffic is prohibited. The TRAFFIC INFORMATION SYSTEM (TIS) is intended for advisory use only. TIS is intended only to help the pilot to visually locate traffic. It is 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 to enhance situational awareness. It is the pilot's responsibility to provide terrain clearance at all times. Navigation using the G 1000 is not authorized north of 70° North latitude or south of 70° South latitude due to unsuitability of the magnetic fields near the Earth's poles. In addition, operations are not authorized in the following two regions: 1. North of 65 ° North latitude between longitude 75° Wand 120° W (Northern Canada). 2. South of 55° Soulh latitude between longitude 120° E and 165° E (region south of Australia and New Zealand) . The COM 1/2 (split COM) function of the GMA 1347 Audio Panel is not approved for use. During COM 1/2 operation, transmission by one crew member inhibits reception by the other crew member. BENDIX/KING KAP 140 2 AXIS AUTOPILOT (if installed) Use of the Bendix/King KAP 140 Autopilot is prohibited when the GMA 1347 Audio Panel is inoperative (since the aural warning will not be provided when Autopilot is disengaged). U.S. FAA APPROVED 172SPHAUS-03 CESSNA MODEL 172S NAV III SECTION 2 OPERATING LIMITATIONS 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 as the airplane is equipped). The markings and placards installed in this airplane contain operating limitations which must be complied with when operating this airplane in the Normal Category. Other operating limitations which must be complied with when operating this airplane in this category or in the Utility Category are contained in the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. Normal Category Utility Category Spin Recovery No acrobatic maneuvers, including spins, approved. No acrobatic maneuvers approved, except those listed in the Pilot's Operating Handbook. Baggage compartment and rear seat must not be occupied. Opposite rudder - forward elevator - neutralize controls. Flight into known icing conditions prohibited. This airplane is certified for the following flight operations as of date of original airworthiness certificate: IFAA APPROVED 172SPHAUS-03 DAY-NIGHT-VFR-IFR (Continued Next Page) U.S. 2-19 I SECTION 2 OPERATING LI MITATIONS IPLACARDS (Co ntinu ed) 2. On th e fuel selector valve: TAKEOFF LANDING LEFT 26 .5 GAL. LEVEL FLIGHT ONLY BOTH 53.0 GAL. FUEL SELECTOR 3. Near fu el tank fill er ca p: FUEL CESSNA MODEL 172S NAV III ALL FLIGHT ATTITUDES RIGHT 26.5 GAL. LEVEL FLIGHT ONLY 100LU100 M IN . GRADE AVIATION GASOLINE CAP. 26.5 U .S. GAL. USABLE CA P 17 .5 U .S. GAL US ABLE TO BO TTOM OF FILLER INDICATOR TAB 4. On fl ap control indicator: UPt010 · 110 KIAS (Partial fl ap range with blue color code; also, m ec han ical detent at 10· .) 10 · to FULL 85 KIAS (Wh it e color code; also, mechanical deten t at 20 · .) I (Co ntinu ed Ne xt Page) U.S. FAA APPROVED 172SPHAUS-03 CESSNA MODEL 172S NAV 111 SECTION 2 OPERATING LIMITATIONS PLACARDS (Continued) 5. In baggage compartment: 120 POUNDS MAXIMUM BAGGAGE FORWARD OF BAGGAGE DOOR LATCH 50 POUNDS MAXIMUM BAGGAGE AFT OF BAGGAGE DOOR LATCH MAXIMUM 120 POUNDS COMBINED FOR ADDITIONAL LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA I 6. A calibration card must be provided to indicate the accuracy of the magnetic compass in 30 ' increments. 7. On the oil filler cap: OIL 8 aTS 8. On control lock: CAUTION! CONTROL LOCK REMOVE BEFORE STARTING ENGINE 9. Above the PFD: MANEUVERING SPEED - 105 KIAS IFAA APPROVED 172SPHAUS-03 (Continued Next Page) I I U.S. 2-21 SECTION 2 OPERATING LIMITATIONS IPLACARDS (Continued) CESSNA MOD EL 172S NAV III 10. On the Upper Right Side of the Aft Cabin Partition: EMERGENCY LOCATOR TRANSMITIER INSTALLED AFT OF THIS PARTITION 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 th e upper right instrument panel: SMOKING PROHIBITED r Near the center overhead light control : Flood Light U.S. FAA APPROVED 172SPHAUS-03 CESSNA MODEL 172S NAV III SECTION 3 EMERGENCY PROCEDUR ES EMERGENCY PROCEDURES TABLE OF CONTENTS Introduction . . .... . .... ..... ............. . . . .... . . Airspeeds For Em e rg ency Operation ... .. . ...... . .••••. EMERGENCY PROCEDURES . ... . .. .. . . ...... . ENGINE FAILURES ....... . .... ..... ... ... .. ..... . Engine Fai lure During Takeo ff Ro ll . ........ . ....... . Engin e Failure Im mediately After Takeoff ...... .... .. . . Engine Failu re During Flight (Restart Procedures) . ..... . FORCED LANDINGS . . . ... . . ..... . . . . ...... .. . ... . Emergency Landing Without En gine Power .. .... ..••. . Precautionary Land in g With Engine Power ...... . .• . .. Ditching .... . . .. .......... .. ... . ...... .... . . . . FIRES .. . .. . ... . . . . .... .... .. . . . . . ...... . ...... . During Start On Ground . . . ... . ... . .. .......... . . . Engine Fire In Flight .......... . . . . . ..... . ... . .. . El ectrical Fire In Flight . .. . ........ .. .... ....... . Cab in Fire .... .. . .. .. ...... .. ....... . ..••.. . .. Wing Fire .. . . .• . . ... . .. ... . . .... . .. . . .. ...... ICiNG . . ...... . ... .. . . . . .... .... ... . ... . ... . . . . In advertent Icing Encounter During Flight . ..... ... ... . Static Source Blockage (Erroneous Instrument Reading Suspected) ... ... . . . (Continued Next Page) Page 3-5 3-51 3-61 3-6 3-6 3 -6 3-sI ;:~ 3-8 3-81 3-9 3-9 3- 10 3-10 3-1 1 3 -11 3- 1213- 12 3-131 I 172SPHAU S-01 U.S. 3 -1 SECTION 3 EMERGENCY PROCEDURES CESSNA MODEL 17 2S NAV III TABLE OF CONTENTS (Continued) Page EXCESSIVE FUEL VAPOR .......... . . .. .. . .. . .. ... 3-13 Fuel Flow Stabilization Procedures 3-13 ABNORMAL LANDINGS . . . . . . . . . . . . . . . . . . . . . . . . . .. 3 -1 4 Landing With A Flat Main Tire ...... • .. ..... . .. .. .. 3-14 Landing With A Fl at Nose Tire .................... . 3-14 ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS 3-15 I High Volts Annunciator Comes On or M BAT AMPS More Than 40 . .. . ..... . ....... ... 3-15 LOW VOLTS Annunciator Comes On Below 1000 RPM 3 -1 7 LOW VO LTS Annunciator Comes On or Does Not Go Off at Higher RP M ...... .. .. . . ...... 3- 17 AIR DATA SYSTEM FAILURE 3-1 9 Red X - PFD Airspeed Indicator .. .. . . ...... . . . • .. .. 3-1 9 Red X - PFD Altitude Indicator .......... . . .. ....... 3-1 9 ATTITUDE AND HEADING REFERENCE SYSTEM (AHRS) FAILURE .. .. ....... . ....... . . . .. ...... . . ... . .. 3-20 Red X - PFD Attitude Indicator ..... . .... . . . ..... • . . 3-20 Red X - Horizontal Situation Indicator (HS I) 3-20 DISPLAY COOLING ADVISORY ............... . ... . . 3-20 PFD1 Cooling or MFD1 Coo ling Annunciator(s) VACUUM SYSTEM FAILURE . ...... . . .... . .. . ... . . . Low Vacuum Annunciator Comes On I HIGH CARBON MONOXIDE (CO) LEVEL ANNUNCIATOR CO LVL HIGH Annunciator Comes On . . . .. ........ . CO LVL HIGH Annunciator Remains On ......... . .. . (Continued Next Page) 3-20 3- 21 3-21 3-2 1 3-21 3-2 1 3-2 U .S. 172SPHAUS-03 CESSNA MODEL 172S NAV III SECTION 3 EMERG ENCY PROCEDURES TABLE OF CONTENTS (Continued) Page AMPLIFIED EMERGENCY PROCEDURES ... .. . . . .... . 3-22 Engine Failure .. .. . .. . . .... .. ... . . .... .. . . •... . . . 3-22 Maximum Glide ..... .. . ..... ... .. .. . ••. .. . .. . .. .. 3·23 Forced Landings ... ............ . ... . . ......... ••• 3-24 Landing Without El evator Co nt ro l ...... . ... . .......... 3-25 Fir es ... . ..... . ... . .... ....... ............ .. .. . 3-25 Emergency Operation In Clouds .. . .... . .... ..... .... 3-26. Executing A 180' Turn In Clouds (AHRS FAILED) 3-27 Emergency Descent Through Clouds (AHRS FAILED) 3-28 Re covery From Spiral Di ve In The Clo ud s (AH RS FAILED) 3-29 In advertent Flight Into Icing Conditions .... ........ . .... 3-29 Static Source Bl ocked ......... . .... .. .. .. .. .. .. . . . 3-30 Spins .......... .. ... . ........... . . . . . . . . .... .. 3-30 Rough Engin e Opera ti on Or Loss Of Power ..• • • . . . . . . . . 3-31 Spa rk Plug Fouling .... ...... ... .. . . . . .. . • . . . ... 3-31 M ag neto Malfunction ..... .. .... . ..... . . .. .... ... 3-31 Idle Po wer Engin e Roug hn ess .. ... • •.. . ....... . .. . 3-31 Engine-Driven Fu el Pump Fai lure . . . . . . . . . . . . . . . . . . 3 -3 2 Exc essive Fuel Vapor .... . . . . .. . . .. .. ... .... .. .. 3·32 Low Oil Pressure ... . . .... . .. .. . . . . . . . . . . . . . . . . 3-32 Electricat Power Supply System Ma lfunctions ... .. ... . ... 3-33 Excessive Rate-Of-Charge .. .. . . .. ...... . . . .. .. .. 3-33 In sufficient Rate-Of -C harge . ...... . . .. .. .. .. . . .. .. 3-34 High Ca rb on Monoxide (CO) Level Annunciation . . . . . . . .. 3-36. Other Emergencies ... ............. . ........ ... .. . 3-36 Windshield Damage .. ..... ... . . ... • • . .. . . . . . . .. 3-36 172SPHAUS-03 U.S. 3-3/3-4 CESSNA MODEL 172S NAV III SECTION 3 EMERGENCY PROCEDURES INTRODUCTION Section 3 provides checklist and amplified procedures for coping with emergencies that may occur. Emergencies caused by airplane or engine malfunctions are extremely rare if proper preflight inspections and maintenance are practiced. Enroute weather emergencies can be minimized or eliminated by careful flight planning and good judgment when unexpected weather is encountered. However, should an emergency arise, the basic 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 maneuver to execute a successful landing. Emergency procedures associated with optional or supplemental equipment are found in Section 9, Supplements. AIRSPEEDS FOR EMERGENCY OPERATION ENGINE FAILURE AFTER TAKEOFF Wing Flaps UP ...................... . ...•.• Wing Flaps 10° - FULL .. ,", . ...... . ..... . . • . MANEUVERING SPEED 2550 POUNDS .. , . ...... " .. , ... , ... . . ... . 2200 POUNDS , . ...... .. ,", . . ,', ......... . 1900 POUNDS , ......... . . . . . . . . . ... . . . . .. . MAXIMUM GLIDE PRECAUTIONARY LANDING WITH ENGINE POWER LANDING WITHOUT ENGINE POWER Wing Flaps UP .,.,"', .. .. .... " .. . ..• . , .. . Wing Flaps 10 ° - FULL .,',., ... " . . , .. . . .. ," 172SPHAUS-01 70 KIAS 65 KIASI 105 KIASI 98 KIAS 90 KIAS 68 KIAS 65 KIAS 70 KIAS 65 KIASI U.S, 3-5 SECTION 3 EMERGENCY PROCEDURES CESSNA MODEL 172S NAV III EMERGENCY PROCEDURES Procedures in the Emergency Procedures Checklist portion of this section shown in bold faced type are immediate action it ems which should be committed to memo ry. ENGINE FAILURES ENGINE FAILURE DURING TAKEOFF ROLL 1. Throttle Control - IDLE (pull full out) 2. Brakes- APPLY 3. Wing Fl aps - RETRACT 4. Mixture Control - IDLE CUTOFF (pull full out) 5 . MAGNETOS Switch - OFF 6 . STBY BATT Switch - OFF 7. MASTER Switch (ALT a nd BAT) - OFF ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF 1. Airspeed - 70 KIAS Flaps UP 65 KIAS Flaps 10· - FULL 2. Mi xture Control - IDLE CUTOFF (pull full out) 3. FUEL SHUTOFF Valve - OFF (pull full out) 4 . MAGNETOS Switch - OFF 5 . Wing Flaps - AS REQUIRED (FULL r ec ommended) 6. STBY BATT Switch - OFF 7. MASTER Switch (AL T a nd BAT) - OFF 8. Cabin Door - UNLATCH 9. Land - STRAIGHT AHEAD ENGINE FAILURE DURING FLIGHT (Restart Procedures) 1. Airspeed - 68 KIAS (best glide speed) 2. FUEL SHUTOFF Valve - ON (push full in) 3. FUEL SELECTOR Valve - BOTH 4. FUEL PUMP Switch - ON 5. Mixture Control - RICH (if restart has not occurred) (C ontinued Ne xt Page ) U.S. 172SPHAUS-03 CESSNA MODEL 172S NAV III SECTION 3 EMERGENCY PROCEDURES ENGINE FAILURES (Continued) ENGINE FAILURE DURING FLIGHT (Restart Procedures) (Continued) 6. MAGNETOS Switch - BOTH (or START if propeller is stopped) NOTE If Ihe propeller is windmilling, eng in e will restart automatically within a few second s. If propeller has stopped (po ss ible at low speeds), turn MAGNETOS switch to START, advance throttle slowly from idle and lean the mixture from full ri ch as required to obtain smooth operation . 7. FUEL PUMP Switch - OFF NOTE If the indicated fuel flow (FFLOW GPH) immediately drops to zero, a sign of fa ilure of the engine-driven fuel pump, return th e FUEL PUMP switch to the ON position. FORCED LANDINGS EMERGENCY LANDING WITHOUT ENGINE POWER 1. Pilot and Passenger Seal Backs - MOST UPRIGHT. POSITION 2. Seats and Seal Belts - SECURE 3. Airspeed - 70 KIAS - Flaps UP 65 KIAS - Flaps 10' - FULL 4. Mixture Control - IDLE CUTOFF (pull fu ll out) I5. FUEL SHUTOFF Valve - OFF (pull full out) 6. MAGNETOS Switch - OFF 7. Wing Flaps - AS REQUIRED ( FU LL recommended) 8. STBY BAn Switch - OFF 9. MASTER Switch (ALT and BAT) - OFF (when landing is assured) 10. Doors - UNLATCH PRIOR TO TOU CHDOWN 11 . Touchdown - SLIGHTLY TAIL LOW 12 . Brakes - APPLY HEAVILY (Continued Next Page) 172SPHAUS-03 U .S . 3-7 SECTION 3 CESSNA MODEL 172S NAV III EMERGENCY PROCEDURES FORCED LANDINGS (Continu ed) PRECAUTIONARY LANDING WITH ENGINE POWER I 1. Pilot and Passenger Seat Backs - MOST UPRIGHT POSITION 2. Seats and Seat Belts - SECURE 3. Airspeed - 65 KIAS 4. Wing F la ps - 20 0 5. Selected Fi e ld - FLY OVER, noting terra in and obstructions . 6. Wing Flaps - FULL (on fin al approach) 7. Airspeed - 65 KIAS B. STBY BATT Switch - OFF I 9. MASTER Switch (ALT and BAT) - OFF (when landing assured) 10. Doors - UNLATCH PRIOR TO TOUCHDOWN 11 . Touchd ow n - SLIGHTLY TAIL LOW I 12 . Mixture Control - ID LE CUTOFF (pull full out) 13. MAGNETOS Switch - OF F I I 14. Brakes - APPLY HEAVILY DITCHING 1. Radio - TRANSMIT MAYDAY on 121 .5 MHz, (G ive location, intentions and SQUAWK 7700) 2. Heavy Objects (i n baggage area) - SEC URE OR JETTISON (if possible) 3. Pilot and Passenger Seat Backs - MOST UPRIGHT POSITION 4. Seats and Seat Belts - SECURE 5. Wing Flaps - 200 - FULL 6. Power - ESTABLISH 300 FT/MIN DESCENT AT 55 KIAS NOTE If no power is ava il abl e, approach at 70 KIAS with Flaps UP or at 65 KIAS with Fl aps 100 . 7. Approach - Hi gh Winds, Heavy Seas - INTO THE WIND Light Winds, Heavy Swells - PARALLEL TO SWELLS 8. Cabin Doors - UNLATCH 9. Touchdown - LEVEL ATTITUDE AT ESTABLISHED RATE- OF- DE SCENT. (Continued Next Page) 3-8 U .S. 172SPHAUS-03 CESSNA MODEL 1728 NAV III SECTION 3 EMERGENCYPROCEDURE8 FORCED LANDINGS (Continued) DITCHING (Continu ed) 10. Fac e - CUSHION at touchdown with folded coat. 11 . EL T - ACTIVATE 12 . Airplane - EVACUATE THROUGH CABIN DOORS. Ifl necessary, open window and flood cab in to equalize p ress ure so doors ca n be opened . 13 . Life Vests and Ra ft - INFLATE WHEN CLEAR OF AIRPLANE . FIRES DURING START ON GROUND 1. MAGNETOS Switch - START (continue cranking to start the engine). IF ENGINE STARTS 2. Power - 1800 RPM for a few minutes. 3. Engine - SHUTDOWN and in spect for damage. IF ENGINE FAILS TO START 2. Throttle Control - FULL (push full in) 3. Mixture Control - IDLE CUTOFF (pull full out) I4. MAGNETOS Switch - START (continue cranking) 5. FUEL SHUTOFF Valve - OFF (pull full out) 6. FUEL PUMP Switch - OFF 7. MAGNETOS Switch - OFF 8. STBY BATT Switch - OFF 9. MASTER Switch (ALT and BAT) - OFF 10. Engine - SECURE 11 . Parking Brake - RELEASE 12 . Fire Extinguisher - OBTAIN (have ground attendants obtain if not installed) 13. Airplane - EVACUATE 14. Fire - EXTINGUISH using fire ex tinguisher, woo l blanket, or dirt. 15. Fire Damage - INSPECT, (Repair or replace damaged components a nd /or wiring before conducting another flight) I (Continued Next Page) 172SPHAUS-03 U .S. 3-9 SECTION 3 CESSNA MODEL 172S NAV III EMERGENCY PROCEDURES IFIRES (Continued) ENGINE FIRE IN FLIGHT I I I 1. Mixture Control - IDLE CUTOFF (pull full out) 2. FUEL SHUTOFF Valve - OFF (pull full out) 3. FUEL PUMP Switch - OFF 4. MASTER Switch (ALT and BAT) - OFF 5. Cabin Heat and Air - OFF (except overhead vents) 6. Airspeed - 100 KIAS (If fire is not ex tinguished, increase glide speed to find an airspeed, within airspeed limitation s, which will provide an incombustible mi xtur e) 7. Forced Landing - EXECUTE Refer to EMERGENCY LANDING WITHOUT ENGINE POWER ELECTRICAL FIRE IN FLIGHT 1. STBY BATT Switch - OFF 2. MASTER Switch (ALT and BAT) - OFF 3. Vents/Cabin Air/Heat - CLOSED 4. Fire Extinguisher - ACTIVATE (if available) 5. AVIONICS Switch (BUS 1 and BUS 2) - OFF 6. All Other Switches (except MAGNETOS switch) - OFF WARNING AFTER THE FIRE EXTINGUISHER HAS BEEN USED, MAKE SURE THAT THE FIRE IS EXTINGUISHED BEFORE EXTERIOR AIR IS USED TO REMOVE SMOKE FROM THE CABIN. 7. Vents/Cabin Air/Heat - OPEN (When sure that fire is completely extinguished) (Continued Ne xt Page) 3-10 U.S. 172SPHAUS-03 CESSNA MODEL 172S NAV III SECTION 3 EMERGENCY PROCEDURES FIRES (Continued) ELECTRICAL FIRE IN FLIGHT (Continued) IF FIRE HAS BEEN EXTINGUISHED AND ELECTRICAL POWER IS NECESSARY FOR CONTINUED FLIGHT TO NEAREST SUITABLE AIRPORT OR LANDING AREA 8. Circuit Breakers - CHECK for OPEN circuit(s), do not reset. 9. MASTER Switch (ALT and BAT) - ON I10. STBY BAIT Switch - ON 11 . AVIONICS Switch (BUS 1) -ON 12. AVIONICS Switch (BUS 2) - ON CABIN FIRE 1. STBY BATT Switch - OFF 2. MASTER Switch (ALT and BAT) - OFF 3. Vents/Cabin Air/Heat - CLOSED (to avoid drafts) 4. Fire Extinguisher - ACTIVATE (if available) WARNING AFTER THE FIRE EXTINGUISHER HAS BEEN USED, MAKE SURE THAT THE FIRE IS EXTINGUISHED BEFORE EXTERIOR AIR IS USED TO REMOVE SMOKE FROM THE CABIN. 5. Vents/Cabin Air/Heat - OPEN (When sure that fire is completely extinguished) 6. Land the airplane as soon as possible to inspect for damage. WING FIRE 1. LAND and TAXI 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 soon as possible using flaps only as required for final approach and touchdown . 172SPHAUS-03 U.S. 3-11 SECTION 3 CESSNA MODEL 172S NAV III EMERGENCY PROCEDURES I ICING INADVERTENT ICING ENCOUNTER DURING FLIGHT 1. PITOT HEAT Switch - ON 2. Turn back or change altitude to obtain an outside air temperature that is less conducive to icing. 3. Pull cabin heat control full out and open defroster outlets to obtain maximum windshield defroster airflow. Adjust cabin air control to get maximum defroster heat and airflow. 4. Watch for signs of induction air filter icing. A loss of engine RPM could be caused by ice blocking the air intake filter. Adjust the throttle as necessary to hold engine RPM. Adjust mixture, as necessary, for any change in power settings. 5. Plan a landing at the nearest airport. With an extremely rapid ice build-up, select a suitable "off airport" landing site. 6. With an ice accumulation of 0.25 inch or more on the wing leading edges, be prepared for significantly higher power requirements, higher approach and stall speeds, and a longer landing roll. 7. Leave wing flaps retracted. With a severe ice build-up on the horizontal tail, the change in wing wake airflow direction caused by wing flap extension could result in a loss of elevator effectiveness. 8. Open left window and, if practical, scrape ice from a port io n of the windshield for visibility in the landing approach. 9. Perform a landing approach using a forward slip, if necessary, for improved visibility . 10 . Approach at 65 to 75 KIAS depending upon the amount of the ice accumulation. 11. Perform a landing in level attitude. 12 . Missed approaches should be avoided whenever possible because of severely reduced climb capability. (Continued Next Page) 3-12 U.S. 172SPHAUS-03 CESSNA MODEL 172S NAV III SECTION 3 EMERGENCY PROCEDURES ICING (Continued) STATIC SOURCE BLOCKAGE (ERRONEOUS INSTRUMENT READING SUSPECTED) 1. ALT STATIC AIR Valve - PULL ON 2. CABIN HT and CABIN AIR Knobs - PULL ON 3. Vents - CLOSED 4. Airspeed - Refer to Section 5, Figure 5-1 (Sheet 2) Airspeedl Calibration, Alternate Static Source correction chart. EXCESSIVE FUEL VAPOR FUEL FLOW STABILIZATION PROCEDURES (If flow fluctuations of 1 GPH or more, or power surges occur.) 1. FUEL PUMP Switch - ON 2. Mixture Control - ADJUST (As necessary for smooth enginel operation) 3. Fuel Selector Valve - SELECT OPPOSITE TANK (if vapor symptoms continue) 4. FUEL PUMP Switch - OFF (after fuel flow has stabilized) 172SPHAUS-03 U.S. 3-13 SECTION 3 CESSNA MODEL 172S NAV III EMERGENCY PROCEDURES I I ABNORMAL LANDINGS LANDING WITH A FLAT MAIN TIRE 1. Approach - NORMAL 2. Wing Flaps - FULL 3. Touchdown - GOOD MAIN TIRE FIRST (Hold airplane off flat tire as long as possible with a il eron control) 4. Directional Control - MAINTA IN (Using brake on good wheel as required) LANDING WITH A FLAT NOSE TIRE 1. Approach - NORMAL 2. Wing Flaps - AS REQUIRED 85 to 110 KIAS - Flaps Up - 10 ° Be low 85 KIAS - Flaps 10 ° - FULL 3. Touchdown - ON MAINS (Hold nosewheel off the ground as long as possible) 4. When nosewheel touches down, maintain full up elevator as airplane slows to stop. 3-14 U.S . 172SPHAUS-03 CESSNA MODEL 172S NAV III ELECTRICAL POWER MALFUNCTIONS SECTION 3 EMERGENCY PROCEDURES SUPPLY SYSTEM HIGH VOLTS ANNUNCIATOR COMES ON OR M BAT AMPS. MORE THAN 40 1. MASTER Switch (ALT Only) - OFF I2. Electrical Load - REDUCE IMMEDIATELY as follows: a. AVIONICS Switch (BUS 1) - OFF b. PITOT HEAT - OFF c. BEACON Light - OFF d. LAND Light - OFF (Use as required for landing) e. TAXI Light - OFF f. NAV Lights - OFF g. STROBE Lights - OFF h. CABIN PWR 12V - OFF NOTE • The Main Battery supplies electrical power to the Main and Essential Buses until M BUS VOLTS decreases below 20 volts. When M BUS VOLTS falls below 20 volts, the Standby Battery System will automatically supply electrical power to the Essential Bus for at least 30 minutes . • Select COM1 MIC and NAV1 on the aud io 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. (Continued Next Page) 172SPHAUS-03 U.S. 3-15 SECTION 3 CESSNA MODEL 172S NAV III EMERGENCY PROCEDURES ELECTRICAL POWER MALFUNCTIONS (Continued) SUPPLY SYSTEM IHIGH VOLTS ANNUNCIATOR COMES ON OR M BAT AMPS MORE THAN 40 (Continued) I I i. COM1 and NAV1 - TUNE TO ACTIVE FREQUENCY j. COM1 MIC and NAV1 - SELECT (COM2 MIC and NAV2 will be inoperative once AVIONICS BUS 2 is se lected to OFF). NOTE When AVIONICS BUS 2 is set to OFF, the following items wi ll not operate: KAP 140 Autopilot COMM2 GTX 33 Transponder GMA 1347 Audio Panel NAV2 GDU 1040 MFD I k. AVIONICS Switch (BUS 2) - OFF (KEEP ON if in clouds) 3. Land as soon as practical. NOTE Make sure a successful landing is possible before extending flaps. The flap motor is a large electrical load during operation. (Continued Next Page) 3-16 U.S. 172SPHAUS-03 CESSNA MODEL 172S NAV III SECTION 3 EMERGENCY PROCEDURES ELECTRICAL POWER MALFUNCTIONS (Continued) SUPPLY SYSTEM LOW VOLTS ANNUNCIATOR COMES ON BELOW 1000 RPM 1. Throttle Control - 1000 RPM 2. Low Voltage Annunciator (LOW VOLTS) - CHECK OFF LOW VOLTS ANNUNCIATOR REMAINS ON AT 1000 RPM 3. Authorized maintenance personnel must do electrical system inspection prior to next flight. LOW VOLTS ANNUNCIATOR COMES ON OR DOES NOT GO OFF AT HIGHER RPM 1. MASTER Swilch (ALT Only) - OFF 2. Alternator Circuit Breaker (ALT FIELD) - CHECK IN 3. MASTER Swilch (AL T and BAT) - ON 4. Low Voltage Annunciator (LOW VOLTS) - CHECK OFF 5. M BUS VOLTS - CHECK 27.5 V minimum 6. M BAT AMPS - CHECK CHARGING (+) IF LOW VOLTS ANNUNCIATOR REMAINS ON 7. MASTER Switch (ALT Only) - OFF I 8. Electrical Load - REDUCE IMMEDIATELY as follows: a. AVIONICS Switch (BUS 1) - OFF b. PITOT HEAT - OFF c. BEACON Light - OFF d. LAND Light - OFF (use as required for landing) e. TAXI Light - OFF f. NAV Lights - OFF g. STROBE Lights - OFF h. CABIN PWR 12V - OFF (Continued Next Page) I 172SPHAUS-03 U.S. 3-17 SECTION 3 CESSNA MODEL 172S NAV III EMERGENCY PROCEDURES I ELECTRICAL POWER MALFUNCTIONS (Continued) SUPPLY SYSTEM IF LOW VOLTS ANNUNCIATOR REMAINS ON (Continued) NOTE • The Main Battery supplies electrical power to the Main and Essential Buses until M BUS VOLTS decreases below 20 volts. When M BUS VOLTS falls below 20 volts, the Standby Battery System will automatically supply electrical power to the Essential Bus for at least 30 minutes . • Select COM1 MIC and NAV1 on the audio panel and tune to the active frequency before setting AVIONICS BUS 2 to OFF. If COM2 MIC and NAV2 are selected when AVIONICS BUS 2 is set to OFF, the COM and NAV radios cannot be tuned. i. COM1 and NAV1 FREQUENCY TUNE TO ACTIVE j. COM1 MIC and NAV1 - SELECT (COM2 MIC and NAV2 will be inoperative once AVIONICS BUS 2 is selected to OFF) NOTE When AVIONICS BUS 2 is set to OFF, the following items will not operate: KAP 140 Autopilot COMM2 GTX 33 Transponder GMA 1347 Audio Panel NAV 2 GDU 1040 MFD k. AVIONICS Switch (BUS 2) - OFF (KEEP ON if in clouds) (Continued Next Page) U.S. 172SPHAUS-03 CESSNA MODEL 172S NAV III ELECTRICAL POWER MALFUNCTIONS (Continued) SECTION 3 EMERGENCY PROCEDURES SUPPLY SYSTEM IF LOW VOLTS ANNUNCIATOR REMAINS ON (Continued) 9. Land as soon as practical. NOTE Make sure a successful landing is possible before extending flaps. The flap motor is a large electrical load during operation. AIR DATA SYSTEM FAILURE RED X - PFD AIRSPEED INDICATOR 1. ADC/AHRS Circuit Breakers - CHECK IN (ESS BUS and AVN BUS 1). If open, reset (close) circuit breaker. If circuit breaker opens again, do not reset. 2. Standby Airspeed Indicator - USE FOR AIRSPEED INFORMATION . RED X - PFD ALTITUDE INDICATOR 1. ADC/AHRS Circuit Breakers - CHECK IN (ESS BUS and AVN BUS 1) . If open, reset (close) circuit breaker. If circuit breaker opens again, do not reset. 2. Standby Altimeter - CHECK current barometric pressure SET. USE FOR ALTITUDE INFORMATION . I172SPHAUS-03 U.S. 3-19 SECTION 3 EMERGENCY PROCEDURES CESSNA MODEL 172S NAV II I ATTITUDE AND HEADING REFERENCE SYSTEM (AHRS) FAILURE RED x· PFD ATTITUDE INDICATOR 1. ADC/AHRS Circuit Breakers . CHECK IN (ESS BUS and AVN BUS 1). If open, reset (close) circuit breaker. If circuit breaker opens again, do not reset. 2. Standby Attitude Indicator . USE FOR ATTITUDE INFORMATION. RED X· HORIZONTAL SITUATION INDICATOR (HSI) 1. ADC/AHRS Circuit Breakers· CHECK IN (ESS BUS and AVN BUS 1). If open, reset (close) circuit breaker. If circuit breaker opens again, do not reset. 2. Non·Stabilized Magnetic Compass . USE FOR HEADING INFORMATION. DISPLAY COOLING ADVISORY PFD1 COOLING OR MFD1 COOLING ANNUNCIATOR(S) 1. Cabin Heat (CABI N HT) . REDUCE (minimum preferred) 2. Forward Avionics Fan· CHECK (feel for airflow from screen on glareshield) IF FORWARD AVIONICS FAN HAS FAILED 3. STBY BATT Switch . OFF (unless needed for emergency power) IF PFD1 COOLING OR MFD1 COOLING ANNUNCIATOR DOES NOT GO OFF WITHIN 3 MINUTES OR IF BOTH PFD1 COOLING AND MFD1 COOLING ANNUNCIATORS COME ON 3. STBY BATT Switch· OFF (land as soon as practical) U.S. 172SPHAUS ·03 CESSNA MODEL 172S NAV III SECTION 3 EMERGENCY PROCEDURES VACUUM SYSTEM FAILURE LOW VACUUM ANNUNCIATOR COMES ON 1. Vacuum Indicator (VA C) - CHECK EIS ENGINE page to. ma ke sure vacuum pointer is in green arc limits. CAUTION IF VACUUM POINTER IS OUT OF THE GREEN ARC DURING FLIGHT OR THE GYRO FLAG IS SHOWN ON THE STANDBY ATTITUDE INDICATOR, THE STANDBY ATTITUDE INDICATOR MUST NOT BE USED FOR ATTITUDE INFORMATION. HIGH CARBON MONOXIDE ANNUNCIATOR (if installed) (CO) LEVEL CO LVL HIGH ANNUNCIATOR COMES ON 1. CABIN HT Knob - OFF (push full in) 2. CABIN AIR Knob - ON (pull full out) 3. Cabin Vents - OPEN 4. Cabin Windows - OPEN (163 KIAS maximum windows open speed) CO LVL HIGH ANNUNCIATOR REMAINS ON 5. Land as soon as practical. 172SPHAUS-03 U.S. 3-21 SECTION 3 EMERGENCY PROCEDURES CESSNA MODEL 172S NAV III AMPLIFIED EMERGENCY PROCEDURES IThe foll ow in g Amplifi ed Emergency Pr ocedures provide additional information beyond that in th e Emergency Pr ocedur es Checklists portion of this sec ti on. The se proc ed ures also in clude information not readily adaptable to a checklist format, and material to which a pilot co uld not be expected to refer in re solution of a specific emergency. Thi s information should be reviewed in detail prior to fl yi ng th e airp lane, as wel l as rev ie we d on a regular basis to keep pilot's knowledge of procedures fresh . ENGINE FAILURE If an eng in e failure occurs during the takeoff ro ll , stop the ai rpl ane on th e remain ing runway. Tho se extra items on the check li st will provide added sa fety after a failure of this typ e. Ilf an engine failure occurs im mediately a ft er takeo ff , in most cases, the land ing should be pl anned str ai ght ahead with only sma ll changes in direction to avoid obstructions. Altitude and airspeed are seldom su fficient to execute the 180 0 gliding turn necessa ry to return to th e runway. The checklist procedures assume that adequate time exists to secure the fuel and ignition systems prior to touchdown. IAfter an eng in e failure in flight, the most important task is to continue fl y in g the airplane. The best glide speed, as shown in Fi gure 3-1, shou ld be es t abl ished as quickly as possible. While glid ing toward a suit ab le landing area, an effort should be made to identify th e cause of the failure . If time permits, an engine resta rt should be attempted as shown in the checklist. If the engine ca nn ot be restarted, a forced land in g wi th ou t power must be completed. b-22 U .S. 17 2SPHAUS-Ol CESSNA MODEL 172S NAV III SECTION 3 EMERGENCY PROCEDURES ti: 10,000 z «a: a: w I-- w >oOJ « I-- I ~ w I 8000 6000 4000 2000 I 172SPHAUS-01 MAXIMUM GLIDE . . + ," I ... . . .. ..'.j..:. +, ..' ·'1 i • SPEED 68 -KIAS • PROPELLER WINDMILLING • FLAPS UP • ZERO WIND 4 6 8 10 12 14 16 18 20 GROUND DISTANCE - NAUTICAL MILES 05B5T10 11 Figure 3-1 I U.S. 3-23 SECTION 3 EMERGENCY PROCEDURES FORCED LANDINGS CESSNA MODEL 172S NAV III If all attempts to restart the engine fail and a forced landing is imminent, select a suitable field and prepare for the landing as discussed under the Emergency Landing Without Engine Power checklist. Transmit Mayday message on 121.5 MHz giving location and intentions and squawk 7700. Before attempting an "off airport" landing with engine power available, one should fly over the landing area at a safe but low altitude to inspect the terrain for obstructions and surface Iconditions, proceeding as discussed in the Precautionary Landing With Engine Power checklist. Prepare for ditching by securing or jettisoning heavy objects located in the baggage area and collect folded coats for protection of occupants' face at touchdown. Transmit Mayday messages on 121.5 MHz giving location and intentions and squawk 7700. Avoid a landing flare because of the difficulty in judging height over a water surface. The checklist assumes the availability of power to make a precautionary water landing. If power is not available, use of the airspeeds noted with minimum flap extension will provide a more favorable attitude for a power off ditching. For a forced landing situation, set the STBY BAn Switch to the off position. Do not set the AVIONICS (BUS 1 and BUS 2) Switch or the MASTER Switch (ALT and BAT) to the OFF position until a landing is assured. When these switches are in the OFF position, the airplane electrical systems are de-energized. Before performing a forced landing, especially in remote and mountainous areas, activate the ELT transmitter by positioning the cockpit-mounted switch to the ON position. For complete information on ELT operation, refer to the Supplements, Section 9. U.S. 172SPHAUS-01 CESSNA MODEL 172S NAV I" SECTION 3 EMERGENCY PROCEDURES LANDING WITHOUT ELEVATOR CONTROL Trim for horizontal flight with an airspeed of approximately 65 KIAS and flaps set to 20° by using throttle and elevator trim controls. Then do not change the elevator trim control setting; control the, glide angle by adjusting power. During the landing flare (round-out), the nose will come down when power is reduced and the airplane may touch down on the nosewheel before the main wheels. When in the flare, the elevator trim control should be adjusted toward the full nose up position and the power adjusted at the same time so that the airplane will rotate to a horizontal attitude for touchdown. Close the throttle at touchdown. FIRES Improper starting procedures involving the excessive use of auxiliary fuel pump operation can 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 weather where engine preheat service is not available. If this occurs, the airplane should be pushed away from the fuel puddle before another engine start is attempted. Otherwise, there is a possibility of raw fuel accumulations in the exhaust system igniting during an engine start, causing a long flame from the tailpipe, and possibly igniting the collected fuel on the pavement. If a fire occurs, proceed according to the checklist. Although engine fires are extremely rare in flight, if a fire iSI encountered, the steps of the appropriate checklist should be followed. After completion of this procedure, execute a forced landing. Do not attempt to restart the engine. The first sign of an electrical fire is usually the smell of bUrningl insulation. The checklist procedure should result in the elimination of the fire. I 172SPHAUS-01 u .S. 3-25 SECTION 3 EMERGENCY PROCEDURES CESSNA MODEL 172S NAV III IEMERGENCY OPERATION IN CLOUDS If the engine-driven vacuum pump fails in flight, the standby attitude indicator will not be accurate. The pilot must then rely on the attitude and heading information (from the AHRS) shown on the PFD indicators. With valid HDG or GPS/NAV and blind turn coordinator inputs, autopilot operation will not be affected. If the AHRS unit fails in flight (red X's shown through the PFD attitude and heading indicators), the pilot must rely on the standby attitude indicator and non-stabilized magnetic compass for attitude and heading information. The KAP 140 Autopilot will not operate in HDG mode without AHRS input. With a valid G PS or NAV input and an operating turn coordinator, the autopilot will operate in NAV, APR or REV modes. Autopilot altitude hold and vertical speed operating modes are independent of AHRS operation. Refer to Section 9, Supplements, for additional details on autopilot operations. The following instructions assume that the pilot is not very proficient at instrument flying and is flying the airplane without the autopilot engaged. (Continued Next Page) 3-26 U.S. 172SPHAUS-03 CESSNA MODEL 172S NAV III SECTION 3 EMERGENCY PROCEDURES EMERGENCY OPERATION IN CLOUDS (C ontinu ed) I EXECUTING A 180 ' TURN IN CLOUDS (AHRS FAILED) Upon inadvertently entering t he cloud s, an immediate turn to reverse course a nd return to VFR conditions should be made as follows: AHRS Failure 1. Note the no n- stabilized magnetic compass heading. 2. Using th e standby altitude indicator, initiate a 15 ' bank left turn . Keep feet off rudder pedals. Maintain altitude and 15 ' bank angle. Continue the turn for 60 seconds, then roll back to level flight. 3. When th e compass card becomes sufficiently stable , check the accuracy of the turn by ve rif yi ng that the compass heading approximates the reciprocal of the original heading. 4. If necessa ry , ad just the heading by keeping the wings leve l and using th e rudder to ma ke skidding turns (the compass will read more