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Cessna 1980 182Q, Pilot'S Operating Handbook And Flight Manual

The Cessna 1980 182Q Pilot's Operating Handbook and Flight Manual is a comprehensive guide for pilots seeking detailed information on operating this iconic aircraft. Available as a free download from manualshive.com, this manual provides essential insights and instructions, ensuring a safe and enjoyable flying experience.

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Summary of Contents for 1980 182Q

Page 1: ...IMES ICESSNA AIRCRAFT COMPANY I 1980 MODEL 182Q Serial No g2 5 1 20 Registration No 1 I7 THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY CAR PART 3 AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT MANUAL f Member 01 GAMA COPYRIGHT 1979 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA 1 OCTOBER 1979 ...

Page 2: ...THIS MANUAL WAS PROVIDED FORTHEAIRPLANE IDENTIFIED ON THE TITLE PAGE ON __ __ SUBSEQUENT REVISIONS SUPPLIED BY CESSNA AIRCRAFT COMPANY MUST BE PROPERLY IN SERTED CESSNA AIRCRAFT COMPANY PAWNEE DIVISION ...

Page 3: ...lers worldwide Specific benefits and provisions of warranty plus other important benefits for you are contained in your Customer Care Program book supplied with your airplane Warranty service is available to you at authorized Cessna Dealers throughout the world upon presentation of your Customer Care Card which establishes your eligibility under the warranty FACTORY TRAINED PERSONNEL to provide yo...

Page 4: ...e LANDING PERFORMANCE Ground Roll Total Distance Over 50 Ft Obstacle STALL SPEED CAS Flaps Up Power Off Flaps Down Power Off MAXIMUM WEIGHT Ramp Takeoff or Landing STANDARD EMPTY WEIGHT Skylane Skylane II MAXIMUM USEFUL LOAD Skylane Skylane II BAGGAGE ALLOWANCE WING LOADING Pounds Sq Ft POWER LOADING Pounds HP FUEL CAPACITY Total OIL CAPACITY ENGINE Teledvne Continental 230 BHP at 2400 RPM PROPELL...

Page 5: ...owing Log of Effective Pages provides the dates of issue for original and revised pages and a listing of all pages in the handbook Pages affected by the current revision are indicated by an asteri sk preceding the pages listed LOG OF EFFECTIVE PAGES Dates of issue for original and revised pages are Original 1 October 1979 Revision 1 28 March 1980 Page Date Title 1 October 1979 Assignment Record 1 ...

Page 6: ...NERAL 1 LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT BALANCE EQUIPMENT LIST 6 AIRPLANE SYSTEMS DESCRIPTIONS 7 AIRPLANE HANDLING SERVICE MAINTENANCE 8 SU PPLEMENTS Optional Systems Description Operating Procedures 9 iv 1 October 1979 ...

Page 7: ... Weights 1 4 Standard Airplane Weights 1 5 Cabin And Entry Dimensions 1 5 Baggage Space and Entry Dimensions 1 5 Specific Loadings 1 5 Symbols Abbreviations And Terminology 1 5 General Airspeed Terminology And Symbols 1 5 Meteorological Terminology 1 6 Engine Power Terminology 1 7 Airplane Performance And Flight Planning Terminology 1 7 Weight And Balance Terminology 1 7 1 October 1979 1 1 ...

Page 8: ...span shown with strobe lights installed Maximum height shown with nose gear depressed as far as possible and flashing beacon installed 4 Wheel base length is 66 1 2 5 Propeller ground clearance is 10 7IS 6 Wing area is 174 square feet 7 Minimum turning radius pivot point to outboard wing tip is 27 0 PIVOT POINT t 36 O _l Figure 1 1 Three View 1 2 1 October 1979 ...

Page 9: ... six cylinder engine with 470 cu in displacement Horsepower Rating and Engine Speed 230 rated BHP at 2 400 RPM PROPELLER Propeller Manufacturer McCauley Accessory Division Propeller Model Number C2A34C204 90DCB 8 Number of Blades 2 Propeller Diameter Maximum 82 inches Minimum 80 5 inches Propeller Type Constant speed and hydraulically actuated with a low pitch setting of 15 00 and a high pitch set...

Page 10: ...ption has stabilized NOTE The airplane was delivered from the factory with a corro sion preventive aircraft engine oil This oil should be drained after the first 25 hours of operation Continental Motors Specification MHS 24 and all revisions thereto Ashless Dispersant Oil This oil must be used after first 50 hours or oil consumption has stabilized Recommended Viscosity for Temperature Range All te...

Page 11: ...D ENTRY DIMENSIONS Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6 BAGGAGE SPACE AND ENTRY DIMENSIONS Dimensions of the baggage area and baggage door opening are illustrated in detail in Section 6 SPECIFIC LOADINGS Wing Loading 16 9 lbs sq ft Power Loading 12 81bs hp SYMBOLS ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS K...

Page 12: ...trollable Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configu ration at the most forward center of gravity Best Angle of Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal distance Best Rate of Climb Speed is the speed which results in the greatest gain in altitude in a given time METEOROLOGICAL T...

Page 13: ...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 in gallons consumed per hour Nautical Miles Per Gallon is the distance in nautical miles which can be expected per gallon of fuel consumed at a specific engine power setting and or flight configura tion g is acceleration due to gravity WE...

Page 14: ... Standard Empty Weight is the weight of a standard air plane including unusable fuel full operating fluids and full engine oil Basic Empty Basic Empty Weight is the standard empty weight plus the Weight weight of optional equipment Useful Load Maximum Ramp Weight Maximum Takeoff Weight Maximum Landing Weight Tare 1 8 Useful Load is the difference between ramp weight and the basic empty weight Maxi...

Page 15: ...lant Limitations Power Plant Instrument Markings Weight Limits Center Of Gravity Limits Maneuver Limits Flight Load Factor Limits Kinds Of Operation Limits Fuel Limitations Other Limitations Flap Limitations Placards 1 October 1979 SECTION 2 LIMITATIONS Page 2 3 2 4 2 4 2 5 2 6 2 6 2 7 2 7 2 7 2 7 2 8 2 8 2 8 2 9 2 1 2 2 blank ...

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Page 17: ...rating Handbook for amended operating limitations operating procedures performance data and other necessary information for airplanes equipped with specific options NOTE The airspeeds listed in the Airspeed Limitations chart figure 2 1 and the Airspeed Indicator Markings chart figure 2 2 are based on Airspeed Calibration data shown in Section 5 with the normal static source If the alternate static...

Page 18: ...hen only with caution VA Maneuvering Speed 2950 Pounds 109 111 Do not make fu 11 or abrupt 2450 Pounds 99 100 control movements above 1950 Pounds 89 89 this speed V FE Maximum Flap Extended Speed To 100 Flaps 137 140 Do not exceed these speeds 100 _ 400 Flaps 95 95 with the given flap settings Maximum Window Open 172 179 Do not exceed this speed with Speed windows open Figure 2 1 Airspeed Limitati...

Page 19: ... only in smooth air Red Line 179 Maximum speed for all operations Figure 2 2 Airspeed Indicator Markings POWER PLANT LIMITATIONS Engine Manufacturer Teledyne Continental Engine Model Number 0 470 U Engine Operating Limits for Takeoff and Continuous Operations Maximum Power 230 BHP rating Maximum Engine Speed 2400 RPM Maximum Cylinder Head Temperature 460 F 238 C Maximum Oil Temperature 240 F U6 C ...

Page 20: ...ure 1000 240 F 240 F Cylinder Head 200 460 F 460 F Temperature Oil Pressure 10 PSI 30 60 psi 100 psi Suction 4 5 5 4 in Hg Fuel Quantity E 2 0 Gal Unusable Each Tank Figure 2 3 Power Plant Instrument Markings WEIGHT LIMITS Maximum Ramp Weight 2960lbs Maximum Takeoff Weight 2950lbs Maximum Landing Weight 2950lbs Maximum Weight in Baggage Compartment Baggage Area A or passenger on child s seat Stati...

Page 21: ...ental to normal flying stalls except whip stalls lazy eights chandelles and steep turns in which the angle of bank is not more than 60 Aerobatic maneuvers including spins are not approved FLIGHT LOAD FACTOR LIMITS Flight Load Factors Flaps Up 3 8g 1 52g Flaps Down 2 0g The design load factors are 150 of the above and in all cases the structure meets or exceeds design loads KINDS OF OPERATION LIMIT...

Page 22: ...or valve in either LEFT or RIGHT position Takeoff and land with the fuel selector valve handle in BOTH position Operation on either left or right tank limited to level flight only With 1 4 tank or less prolonged uncoordinated flight is prohibited when operating on either left or right tank in level flight Approved Fuel Grades and Colors 100LL Grade Aviation Fuel Blue 100 Formerly 100 130 Grade Avi...

Page 23: ...limitations which must be complied with when operating this airplane in this category are contained in the Pilot s Operating Handbook and F AA Approved Airplane Flight Manual No acrobatic maneuvers including spins approved Flight into known icing conditions prohibited This airplane is certified for the following flight operations as of date of original airworthiness certificate DAY NIGHT VFR IFR 2...

Page 24: ...OUNDS COMBINED FOR ADDITIONAL LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA 5 On flap control indicator 2 10 10 to 20 to FULL Partial flap range with blue code and 140 kt callout also mechanical detent at 10 Indices at these positionswith white color code and 95 kt callout also mechanical detent at 10 and 20 6 Forward of fuel tank filler cap FUEL 100LL 100 MIN GRADE AVIATION GASOLINE CAP 46 0 U...

Page 25: ...e magnetic compass in 30 increments 8 On oil filler cap OIL 12QTS 9 Near airspeed indicator MANEUVER SPEED 111 KIAS 10 Forward of each fuel tank filler cap in line with fwd arrow I FUEL CAP FWD ARROW ALIGNMENT CAP MUST NOT ROTATE DURING CLOSING _ I 1 October 1979 Revision 1 28 March 1980 2 11 2 12 blank ...

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Page 27: ...itching Fires During Start On Ground Engine Fire In Flight Electrical Fire In Flight Cabin Fire Wing Fire Icing Inadvertent Icing Encounter Static Source Blockage Erroneous Instrument Reading Suspected Landing With A Flat Main Tire Electncal Power Supply System Malfunctions Ammeter Shows Excessive Rate of Charge Full Scale Deflection Low Voltage Light Illuminates During Flight Ammeter Indicates Di...

Page 28: ... 13 Emergency Descent Through Clouds 3 13 Recovery From A Spiral Dive 3 14 Inadvertent Flight Into ICing Conditions 3 14 Static Source Blocked 3 14 Spins 3 15 Rough Engine Operation Or Loss Of Power 3 i5 Carburetor Icing 3 15 Spark Plug Fouling 3 16 Magneto Malfunction 3 16 Low Oil Pressure 3 16 Electrical Power Supply System Malfunctions 3 17 Excessive Rate Of Charge 3 17 Insufficient Rate Of Cha...

Page 29: ...his section should be considered and applied as necessary to correct the problem Emergency procedures associated with ELT and other optional systems can be found in Section 9 AIRSPEEDS FOR EMERGENCY OPERATION Engine Failure After Takeoff Wing Flaps Up Wing Flaps Down Maneuvering Speed 2950 Lbs 2450 Lbs 1950 Lbs Maximum Glide Precautionary Landing With Engine Power Landing Without Engine Power Wing...

Page 30: ... EMERGENCY LANDING WITHOUT ENGINE POWER 1 Airspeed 70 KIAS flaps UP 65 KIAS flaps DOWN 2 Mixture IDLE CUT OFF 3 Fuel Selector Valve OFF 4 Ignition Switch OFF 5 Wing Flaps AS REQUIRED 40 recommended 6 Master Switch OFF 7 Doors UNLATCH PRIOR TO TOUCHDOWN S Touchdown SLIGHTLY TAIL LOW 9 Brakes APPLY HEAVILY PRECAUTIONARY LANDING WITH ENGINE POWER 3 4 1 Airspeed 65 KIAS 2 Wing Flaps 20 3 Selected Fiel...

Page 31: ...roach at 70 KIAS with flaps up or at 65KIAS with 10 flaps 6 Cabin Doors UNLATCH 7 Touchdown LEVEL ATTITUDE AT ESTABLISHED DESCENT 8 Face CUSHION at touchdown with folded coat 9 Airplane EVACUATE through cabin doors If necessary open window and flood cabin to equalize pressure so doors can be opened 10 Life Vests and Raft INFLATE FIRES DURING START ON GROUND 1 Cranking CONTINUE to get a start which...

Page 32: ... will provide an incombustible mixture 6 Forced Landing EXECUTE as described in Emergency Landing Without Engine Power ELECTRICAL FIRE IN FLIGHT 1 Master Switch OFF 2 Avionics Power Switch OFF 3 All Other Switches except ignition switch OFF 4 Vents Cabin Air Heat CLOSED 5 Fire Extinguisher ACTIVATE if available I WARNING I After discharging an extinguisher within a closed cabin ventilate the cabin...

Page 33: ...change altitude to obtain an outside air temperature that is less conducive to icing 3 Pull cabin heat control full out and rotate defroster control clock wise to obtain maximum defroster airflow 4 Increase engine speed to minimize ice build up on propeller blades 5 Watch for signs of carburetor air filter ice and apply carburetor heat as required An unexplained loss in manifold pressure could be ...

Page 34: ...led PULL ON 2 Airspeed Consult appropriate table in Section 5 3 Altitude Cruise 50 feet higher and approach 30 feet higher than normal LANDING WITH A FLAT MAIN TIRE 1 Approach NORMAL 2 Wing Flaps FULL DOWN 3 Touchdown GOOD TIRE FIRST hold airplane off flat tire as long as possible with aileron control ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS AMMETER SHOWS EXCESSIVE RATE OF CHARGE Full Scale Def...

Page 35: ...ion has not occurred to de activate the alternator system 1 Avionics Power Switch OFF 2 Alternator Circuit Breaker CHECK IN 3 Master Switch OFF both sides 4 Master Switch ON 5 Low Voltage Light CHECK OFF 6 Avionics Power Switch ON If low voltage light illuminates again 7 Alternator OFF 8 Nonessential Radio and Electrical Equipment OFF 9 Flight TERMINATE as soon as practical 1 October 1979 3 9 3 10...

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Page 37: ... to the runway The checklist procedures assume that adequate time exists to secure the fuel and ignition systems prior to touchdown After an engine failure in flight the best glide speed as shown in figure 3 1 should be established as quickly as possible While gliding toward a suitable landing area an effort should be made to identify the cause of the failure If time permits an engine restart shou...

Page 38: ...ty in judging height over a water surface LANDING WITHOUT ELEVATOR CONTROL Trim for horizontal flight with an airspeed of approximately 80 KIAS by usingthrottle and elevatortrim control Then do not change the elevator trim control setting control the glide angle by adjusting power exclusive ly At flareout the nose down moment resulting from power reduction is an adverse factor and the airplane may...

Page 39: ...iniature airplane 4 Check accuracy of the turn by observing the compass heading which should be the reciprocal of the original heading 5 If necessary adjust heading primarily with skidding motions rather than rolling motions so that the compass will read more accurately 6 Maintain altitude and airspeed by cautious application ofelevator control Avoid overcontrollingby keepingthe hands offthe contr...

Page 40: ...elevator trim control to maintain an 80 KIAS glide 5 Keep hands off the control wheel using rudder control to hold a straight heading Use rudder trim to relieve unbalanced rudder force if present 6 Apply carburetor heat 7 Clear engine occasionally but avoid using enough power to disturb the trimmed glide 8 Upon breaking out of clouds resume normal cruising flight INADVERTENT FLIGHT INTO ICING COND...

Page 41: ... configuration are 2 knots or less SPINS Intentional spins are prohibited in this airplane Should an inadvert ent spin occur the following recovery procedure should be used 1 RETARD THROTTLE TO IDLE POSITION 2 PLACE AILERONS IN NEUTRAL POSITION 3 APPLY AND HOLD FULL RUDDER OPPOSITE TO THE DIREC TION OF ROTATION 4 JUST AFTER THE RUDDER REACHES THE STOP MOVE THE WHEEL BRISKLY FORWARD FAR ENOUGH TO B...

Page 42: ...or repairs using the BOTH position of the ignition switch unless extreme roughness dictates the use of a single ignition position MAGNETO MALFUNCTION A sudden engine roughness or misfiring is usually evidence of magneto problems Switching from BOTH to either L or R ignition switch position will identify which magneto is malfunctioning Select different power settings and enrichen the mixture to det...

Page 43: ...fter thirty minutes of cruising flight the ammeter should be indicating less than two needle widths of charging current If the charging rate were to remain above this value on a long flight the battery would overheat and evaporate the electrolyte at an excessive rate Electronic components in the electrical system can be adversely affected by higher than normal voltage The alternator control unit i...

Page 44: ...ator circuit breaker is in then turn both sides of the master switch off and then on again If the problem no longer exists normal alternator charging will resume and the low voltage light will go off The avionics power switch may then be turned back on If the light illuminates again a malfunction is confirmed In this event the flight should be terminated and or the current drain on the battery min...

Page 45: ...ng Trailing Edge Before Starting Engine Starting Engine Before Takeoff Takeoff Normal Takeoff Short Field Takeoff Enroute Climb Normal Climb Maximum Performance Climb Cruise Descent Before Landing Landing Normal Landing Short Field Landing Balked Landing After Landing Securing Airplane Starting Engine 1 October 1979 AMPLIFIED PROCEDURES Page 4 3 4 3 4 5 4 5 4 5 4 5 4 5 4 6 4 6 4 6 4 6 4 7 4 7 4 7 ...

Page 46: ... Check 4 15 Wing Flap Settings 4 16 Crosswind Takeoff 4 16 Enroute Climb 4 16 Cruise 4 17 Leaning With A Cessna Economy Mixture Indicator EGT 4 18 Stalls 4 19 Landing 4 19 Normal Landing 4 19 Short Field Landing 4 20 Crosswind Landing 4 20 Balked Landing 4 20 Cold Weather Operation 4 20 Starting 4 20 Operation 4 22 I lot Weather Operation 4 23 Noise Abatement 4 23 4 2 1 October 1979 ...

Page 47: ...he particular weight must be used Takeoff Normal Climb Out Short Field Takeoff Flaps 20 Speed at 50 Feet Enroute Climb Flaps Up Normal Best Rate of Climb Sea Level Best Rate of Climb 10 000 Feet Best Angle of Climb Sea Level Best Angle of Climb 10 000 Feet Landing Approach Normal Approach Flaps Up Normal Approach Flaps 40 Short Field Approach Flaps 40 Balked Landing Maximum Power Flaps 20 Maximum ...

Page 48: ...ow from wing tail and control surfaces Also make sure that control surfaces contain no internal accumulations of ice or debris Priorto flight check that pitot heater ifinstalled is warm to touch within 30 seconds with battery and pitot heat switches on If a night flight is planned check operation of all lights and make sure a flashlight is available Figure 4 1 Preflight Inspection 1 October 1979 ...

Page 49: ...f the propeller since a loose or broken wire or a component malfunction could cause the propeller to rotate 6 Fuel Quantity Indicators CHECK QUANTITY 7 Master Switch OFF 8 Static Pressure Alternate Source Valve if installed OFF 9 Fuel Selector Valve BOTH 10 Baggage Door CHECK for security lock with key if child s seat is to be occupied EMPENNAGE L Rudder Gust Lock REMOVE 2 Tail Tie Down DISCONNECT...

Page 50: ...ling pull out strainer drain knob for about four seconds to clear fuel strainer of possible water and sediment Check strainer drain closed If water is observed the fuel system may contain additional water and further draining of the system at the strainer fuel tank sumps and fuel selector valve drain plug will be necessary LEFTWING 1 Main Wheel Tire CHECK for proper inflation 2 Before first flight...

Page 51: ...kers CHECK IN STARTING ENGINE 1 Mixture RICH 2 Propeller HIGH RPM 3 Carburetor Heat COLD 4 Throttle OPEN 1 2 INCH 5 Prime AS REQUIRED 6 Master Switch ON 7 Propeller Area CLEAR 8 Ignition Switch START release when engine starts NOTE If engine nas been overprimed start with throttle 1 4to 1 2 open Reduce throttle to idle when engine fires 9 Oil Pressure CHECK 10 Flashing Beacon and Navigation Lights...

Page 52: ...ghts AS DESIRED 13 Throttle Friction Lock ADJUST 14 Parking Brake RELEASE TAKEOFF NORMAL TAKEOFF 1 Wing Flaps 0 20 2 Carburetor Heat COLD 3 Power FULL THROTTLE and 2400 RPM 4 Elevator Control LiFT NOSE WHEEL at 50 KIAS 5 Climb Speed 70 KIAS flaps 20 80 KIAS flaps UP SHORT FIELD TAKEOFF 1 Wing Flaps 20 2 Carburetor Heat COLD 3 Brakes APPLY 4 Power FULL THROTTLE and 2400 RPM 5 Brakes RELEASE 6 Eleva...

Page 53: ...SE 1 Power 15 23 INCHES Hg 2100 2400 RPM no more than 75 power 2 Elevator and Rudder Trim ADJUST 3 Mixture LEAN 4 Cowl Flaps CLOSED DESCENT 1 Fuel Selector Valve BOTH 2 Power AS DESIRED 3 Carburetor Heat FULL HEAT AS REQUIRED to prevent car buretor icing 4 Mixture ENRICHEN as required 5 Cowl Flaps CLOSED 6 Wing Flaps AS DESIRED 0 10 below 140 KIAS lO 40 below 95 KIAS BEFORE LANDING 1 Seats Belts H...

Page 54: ...low 95 KIAS 3 Airspeed MAINTAIN 60 KIAS 4 Trim ADJUST 5 Power REDUCE to idle as obstacle is cleared 6 Touchdown MAIN WHEELS FIRST 7 Brakes APPLY HEAVILY 8 Wing Flaps RETRACT for maximum brake effectiveness BALKED LANDING 1 Power FULL THROTTLE and 2400 RPM 2 Carburetor Heat COLD 3 Wing Flaps RETRACT to 20 4 Climb Speed 55 KIAS 5 Wing Flaps RETRACT slowly after reaching 70 KIAS 6 Cowl Flaps OPEN AFT...

Page 55: ...L 1S2Q 3 Throttle IDLE SECTION 4 NORMAL PROCEDURES 4 Mixture IDLE CUT OFF pulled full out 5 Ignition Switch OFF 6 Master Switch OFF 7 Control Lock INSTALL S Fuel Selector Valve RIGHT 1 October 1979 4 11 4 12 blank ...

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Page 57: ...he cylinders begin to fire open the throttle slightly to keep it running If prolonged cranking is necessary allow the starter motor to cool at frequent intervals since excessive heat may damage the armature After starting if the oil gage does not begin to show pressure within 30 seconds in the summertime and about twice that long invery coldweather stop engine and investigate Lack of oil pressure ...

Page 58: ...l l l i Ii liiii O lOl j jj C J USE DO Z 10 I 7 owNAIL ON ON LH WING AND i ON RH WING AND 4 14 1DOWN ELEVATOR 11 DOWN ELEVATOR 1 CODE WIND DIRECTION 1I 1 1 1 J 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 nose wheel and rudder to maintain direction Figure 4 2 Taxiing Diagram 1 October...

Page 59: ...a doubt concerning operation of the ignition system RPM checks athigher engine speeds will usually confirm whether a deficiency exists An absence of RPM drop may be indication of faulty grounding of one side of the ignition system or should be cause for suspicion that the magneto timing is set in advance of the setting specified ALTERNATOR CHECK Prior to flights where verification of proper altern...

Page 60: ...ould be left down until all obstacles are cleared and a safe flap retraction speed of 70 KIAS is reached To clear an obstacle with wing flaps 200 an obstacle clearance speed of 57 KIAS should be used Soft field takeoffs are performed with 200 flaps by lifting the airplane off the ground as soon as practical in a slightly tail low attitude If no obstacles are ahead the airplane should be leveled of...

Page 61: ... 75 power as much as practical until a total of 50 hours has accumulated or oil consump tion has stabilized This is to ensure proper seating of the rings and is applicable to new engines and engines in service following cylinder replacement or top overhaul of one or more cylinders The Cruise Performance Table figure 4 3 illustrates the true airspeed and nautical miles per gallon during cruise for ...

Page 62: ...shown in this handbook accompanied by approximately a 3 knot decrease in speed Any change in altitude power or carburetor heat will require a change in the recommended lean mixture setting and a recheck of the EGT setting if installed Carburetor ice as evidenced by an unexplained drop in manifold pressure can be removed by application of full carburetor heat Upon regaining the original manifold pr...

Page 63: ... economy mixture setting results in approximately 5 greater range than shown in this handbook accompanied by approxi mately a 3 knot decrease in speed NOTE Operation on the lean side of peak EGT is not approved When leaning the mixture under some conditions engine roughness may occur before peak EGT is reached In this case use the EGT corres ponding to the onset of roughness as the reference point...

Page 64: ...e field length Although the crab or combination method of drift correction may be used the wing low method gives the best control After touchdown hold a straight course with the steerable nose wheel and occasional braking if necessary BALKED LANDING In a balked landing go around climb the wing flap setting should be reduced to 20 immediately after full power is applied After all obstacles are clea...

Page 65: ...d position to avoid the possibility of the engine drawing fuel through the primer 2 Propeller CLEAR 3 Avionics Power Switch OFF 4 Master Switch ON 5 Ignition Switch START release to BOTH when engine starts 6 Pull carburetor heat on after engine has started and leave on until the engine is running smoothly Without Preheat 1 Prime the engine six to eight strokes while the propeller is being turned b...

Page 66: ...ains normal and steady the airplane is ready for takeoff Rough engine operation in cold weather can be caused by a combina tion of an inherently leaner mixture due to the dense air and poor vaporization and distribution of the fuel air mixture to the cylinders The effects of these conditions are especially noticeable during operation on one magneto in ground checks where only one spark plug fires ...

Page 67: ...of persons recreational and park areas and other noise sensitive areas should make every effort to fly not less than 2000 feet above the surface weather permitting even thoughflight at a lowerlevel may be consistent with the provisions of government regulations 2 During departure from or approach to an airport climb after takeoff and descent for landing should be made so as to avoid prolonged flig...

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Page 69: ...uel And Distance To Climb Maximum Rate of Climb Time Fuel and Distance to Climb Normal Climb Figure 5 7 Cruise Performance 2000 Feet Cruise Performance 4000 Feet Cruise Performance 6000 Feet Cruise Performance 8000 Feet Cruise Performance 10 000 Feet Cruise Performance 12 000 Feet Cruise Performance 14 000 Feet Cruise Performance 16 000 Feet Figure 5 8 Range Profile 65 Gallons Fuel Range Profile 8...

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Page 71: ...ller condition and air turbulence may account for variations of 100 0 or more in range and endurance Therefore it is important to utilize all available information to estimate the fuel required for the particular flight USE OF PERFORMANCE CHARTS Performance data is presented in tabular or graphical form to illus trate the effect of different variables Sufficiently detailed information is provided ...

Page 72: ...eoff distance information presented for a weight of 2950 pounds pressure altitude of 2000 feet and a temperature of 30 C should be used and results in the following Ground roll Total distance to clear a 50 foot obstacle 930 Feet 1800 Feet These distances are well within the available takeoff field length Howev er a correction for the effect of wind may be made based on Note 3 of the takeoff chart ...

Page 73: ...ure conditions The power setting chosen is 2200 RPM and 21 inches of manifold pressure which results in the following Power True airspeed Cruise fuel flow 65 137 Knots 11 0 GPH The power computer may be used to determine power and fuel consump tion more accurately during the flight FUEL REQUIRED The total fuel requirement for the flight may be estimated using the performance information in figures...

Page 74: ...icted to be 137 Q 127 Knots Therefore the time required for the cruise portion of the trip is 433 Nautical Miles 127 Knots 3 4 Hours The fuel required for cruise is 3 4 hours x 11 0 gallons hour 37 4 Gallons A 45 minute reserve requires 45 60 x 11 0 gallons hour 8 3 Gallons The total estimated fuel required is as follows Engine start taxi and takeoff Climb Cruise Reserve 1 7 3 2 37 4 Total fuel re...

Page 75: ... are as follows Ground roll Total distance to clear a 50 foot obstacle 670 Feet 1480 Feet A correction for the effect of wind may be made based on Note 2 of the landing chart using the same procedure as outlined for takeoff DEMONSTRATED OPERATING TEMPERATURE Satisfactory engine cooling has been demonstrated for this airplane with an outside air temperature 23 C above standard This is not to be con...

Page 76: ...0 80 90 100 110 120 130 140 KCAS 60 64 71 80 89 99 108 117 127 136 FLAPS 20 KIAS 40 50 60 70 80 90 95 KCAS 52 57 64 72 81 90 95 FLAPS 40 KIAS 40 50 60 70 80 90 95 KCAS 51 56 63 72 81 91 95 CESSNA MODEL 182Q 150 160 145 155 Figure 5 1 Airspeed Calibration Sheet 1 of 2 5 8 1 October 1979 ...

Page 77: ...OURCE HEATERNENTS AND WINDOWS CLOSED 60 70 80 90 100 110 120 130 59 70 80 91 102 112 122 133 50 60 70 80 90 95 51 62 72 82 92 97 40 50 60 70 80 90 95 43 51 60 71 81 90 95 SECTION 5 PERFORMANCE 140 150 160 143 153 163 HEATERNENTS OPEN AND WINDOWS CLOSED 60 70 80 90 100 110 120 130 140 150 160 60 70 80 90 100 110 120 130 140 150 160 50 60 70 80 90 95 50 60 70 79 89 93 40 50 60 70 80 90 95 41 49 59 6...

Page 78: ...N 5 PERFORMANCE CESSNA MODEL 182Q TEMPERATURE CONVERSION CHART 100 80 60 w I Z w a I 40 u Cfl W w a w 0 20 o 20 40 40 20 o 20 40 60 DEGREES CELSIUS Figure 5 2 Temperature Conversion Chart 5 10 1 October 1979 ...

Page 79: ...OF BANK WEIGHT FLAP 0 30 45 60 LBS DEFLECTION KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 41 56 44 60 49 67 58 79 2950 20 38 51 41 55 45 61 54 72 40 38 50 41 54 45 59 54 71 MOST FORWARD CENTER OF GRAVITY ANGLE OF BANK WEIGHT FLAP 0 30 45 60 LBS DEFLECTION KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 48 59 52 63 57 70 68 83 2950 20 47 55 51 59 56 65 66 78 40 45 54 48 58 54 64 64 76 Figure 5 3 Stall Sp...

Page 80: ...n on a dry grass runway increase distances by 15 of the ground roll figure TAKEOFF OOC SPEED PRESS 10 C 20 C 30 C 40 C WEIGHT KIAS ALT TOTAL TOTAL TOTAL TOTAL TOTAL LBS FT GRND TO CLEAR GRND TO Cl EAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR LIFT AT OFF 50 FT ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT aBS ROLL 50 FT aBS ROLL 50 FT aBS 2950 49 57 S L 635 1220 6BO 1305 730 1395 780 1490 835 1590 1000...

Page 81: ...80 930 1800 995 1930 6000 885 1730 950 lB60 1020 1995 1095 2150 7000 970 1920 1045 2065 1120 2225 1205 2400 8000 1070 2140 1150 2310 1235 2500 1325 2705 S L 395 775 425 825 455 875 485 930 1000 430 840 465 895 495 950 530 1010 2000 470 915 505 975 540 1035 575 1105 3000 515 995 550 1060 590 1130 630 1205 4000 560 1085 600 1160 645 1235 690 1320 5000 615 1185 655 1270 705 1355 755 1445 6000 670 130...

Page 82: ...gine operation and increased power WEIGHT PRESS CLIMB RATE OF CLIMB FPM ALT SPEED LBS FT KIAS 20 C OOC 20 C 40 C 2950 S L 78 1155 1070 990 910 2000 76 1020 945 865 790 4000 75 890 815 740 670 6000 74 760 690 620 550 8000 73 635 565 500 430 10 000 72 510 440 375 12 000 71 385 320 255 14 000 70 260 195 16 000 68 140 75 Figure 5 5 Maximum Rate of Climb 5 14 1 October 1979 ...

Page 83: ...se time fuel and distance by 10 for each 1QoC above standard temperature 4 Distances shown are based on zero wind PRESSURE CLIMB RATE OF FROM SEA LEVEL WEIGHT TEMP LBS ALTITUDE c SPEED CLIMB TIME FUEL USED DISTANCE FT KIAS FPM MIN GALLONS NM 2950 S L 15 78 1010 0 0 0 2000 11 76 900 2 0 7 3 4000 7 75 790 5 1 5 6 6000 3 74 680 7 2 3 10 8000 1 73 570 11 3 2 14 10 000 5 72 460 15 4 3 20 12 000 9 71 35...

Page 84: ...5000 feet for smooth engine operation and increased power 3 Increase time fuel and distance by 10 for each 1QoC above standard temperature 4 Di tances shown are based on zero wind PRESSURE RATE OF FROM SEA LEVEL WEIGHT TEMP LBS ALTITUDE c CLIMB FT FPM TIME FUEL USED DISTANCE MIN GALLONS NM 2950 S L 15 670 0 0 0 2000 11 670 3 0 8 5 4000 7 670 6 1 7 9 6000 3 640 9 2 6 14 8000 1 510 13 3 6 20 10 000 ...

Page 85: ...69 132 11 8 67 133 11 4 20 67 128 11 5 65 128 11 1 63 129 10 7 19 62 124 10 7 60 124 10 3 58 125 10 0 2300 23 78 135 13 3 75 136 12 8 72 137 12 4 22 73 132 12 5 70 133 12 0 68 133 11 6 21 68 128 11 7 66 129 11 3 64 130 10 9 20 64 125 10 9 62 125 10 5 60 126 10 2 2200 23 73 132 12 5 70 133 12 0 68 133 11 6 22 69 129 11 7 66 129 11 3 64 130 10 9 21 64 125 11 0 62 126 10 6 60 126 10 2 20 60 121 10 2 ...

Page 86: ...8 66 132 11 3 64 133 11 0 19 64 127 10 9 62 128 10 6 60 128 10 2 2300 23 76 140 13 1 74 141 12 6 22 75 135 12 8 72 136 12 3 70 137 11 9 21 70 132 12 0 68 133 11 5 65 134 11 2 20 66 128 11 2 63 129 10 8 61 130 10 4 2200 23 75 135 12 8 72 136 12 3 70 137 11 9 22 70 132 12 0 68 133 11 6 66 134 11 2 21 66 129 11 3 64 129 10 9 61 130 10 5 20 62 125 10 5 59 126 10 2 57 126 9 8 19 57 121 9 8 55 121 9 5 5...

Page 87: ... 75 138 12 9 73 139 12 4 70 140 12 0 20 71 135 12 1 68 136 11 6 66 136 11 2 19 66 131 11 2 64 132 10 8 61 132 10 5 2300 22 77 139 13 1 74 140 12 6 71 14 1 12 2 21 72 136 12 3 69 137 11 8 67 137 11 4 20 67 132 11 5 65 133 11 1 63 133 10 7 19 63 128 10 7 60 129 10 3 58 129 10 0 2200 22 72 136 12 3 69 137 11 9 67 137 11 5 21 68 132 11 6 65 133 11 1 63 134 10 8 20 63 129 10 8 61 129 10 4 59 130 10 1 1...

Page 88: ... 12 3 20 72 139 12 4 70 139 11 9 67 140 11 5 19 68 135 11 5 65 135 11 1 63 136 10 7 18 63 130 10 7 60 131 10 3 58 131 10 0 2300 21 74 139 12 6 71 140 12 1 69 141 11 7 20 69 136 11 8 66 137 11 3 64 137 11 0 19 64 132 11 0 62 132 10 6 60 133 10 2 18 60 127 10 2 58 128 9 9 56 128 9 6 2200 21 69 136 11 8 67 137 11 4 65 137 11 0 20 65 132 11 1 63 133 10 7 60 133 10 3 19 61 128 10 3 58 129 10 0 56 129 9...

Page 89: ...69 144 11 8 19 69 138 11 8 67 139 11 4 64 140 11 0 18 65 134 11 0 62 135 10 6 60 135 10 2 17 60 129 10 2 57 130 9 8 55 130 9 5 2300 20 71 140 12 1 68 140 11 6 66 141 11 2 19 66 136 11 3 64 136 10 9 61 136 10 5 18 61 131 10 5 59 131 10 1 57 132 9 8 17 57 126 9 7 55 126 9 4 53 126 9 1 2200 20 67 136 11 4 64 137 11 0 62 137 10 6 19 62 132 10 6 60 132 10 2 58 133 9 9 18 58 128 9 9 56 128 9 6 54 128 9 ...

Page 90: ... 2400 18 66 138 11 3 64 139 10 9 61 139 10 5 17 61 133 10 5 59 133 10 1 57 133 9 8 16 56 128 9 7 54 128 9 4 52 127 9 1 15 51 122 9 0 50 121 8 7 48 120 8 4 2300 18 63 135 10 S 61 135 10 4 59 135 10 0 17 58 130 10 0 56 130 9 7 54 130 9 4 16 54 125 9 3 52 125 9 0 50 124 8 7 15 49 119 8 6 47 118 8 3 45 116 8 1 2200 18 59 131 10 2 57 131 9 8 55 131 9 5 17 55 126 9 5 53 126 9 2 51 125 8 9 16 51 121 8 8 ...

Page 91: ...RD 20 C ABOVE STANDARD TEMP TEMPERATURE STANDARD TEMP 33 C 13 C 7 C KTAS GPH KTAS GPH KTAS GPH RPM MP BHP BHP BHP 2400 16 58 132 9 9 56 132 9 6 54 131 9 3 15 53 126 9 2 51 125 8 9 49 124 8 6 14 48 119 8 5 46 117 8 2 45 116 8 0 2300 16 55 129 9 5 53 129 9 2 51 127 8 9 15 51 123 8 8 49 122 8 5 47 120 8 3 14 46 115 8 1 44 113 7 9 42 111 7 7 2200 16 52 125 9 0 50 124 8 8 48 122 8 5 15 48 118 8 4 46 11...

Page 92: ...EGT if an EGT indicator is installed 20 C BELOW STANDARD 20 C ABOVE STANDARD TEMP TEMPERATURE STANDARD TEMP 37 C 17 C 3 C RPM MP KTAS GPH KTAS GPH KTAS GPH BHP BHP BHP 2400 15 55 130 9 4 53 129 9 1 51 128 8 8 14 50 123 8 7 48 121 8 4 46 119 8 2 2300 15 52 127 9 1 50 126 8 8 48 124 8 5 14 47 119 8 4 46 117 8 1 44 115 7 9 2200 15 49 122 8 6 47 120 8 3 46 118 8 1 2100 15 46 117 8 2 44 115 7 9 43 112 ...

Page 93: ...al climb up to 10 000 feet and maximum climb above 10 000 feet I w w u w Cl I f J t 16 000 14 000 12 000 10 000 8000 6000 4000 2000 1 r 4 r 4 l H 4 H 4 H t t t t H O A I If I H C 9 y H H H I rH H t I H H 140 H t I H X r KTASt t lIt I t l f 144 KTAS a 1 f la H t t a H a t I r I w It H o c o c 0 f f c ft I c H f I H H H t 0 c 1 1 I1 134 126 117 106 KTAS S L 500 550 600 f I lvKTAS t I Il KTAS 11 1 KT...

Page 94: ...e during a normal climb up to 10 000 feet and maximum climb above 10 000 feet 16 000 1116 I KTAS 132 14 000 12 000 G KTAS V O i I 14b I KTAS l 10 000 w I V I w u w 8000 c I 112 V KTAS r 144 I 135 r 125 I KTAS I KTAS I KTAS i J I I 6000 4000 1 t 1 I f t 1 t 1 a I I w f 3 f 0 0 _Q Q f f _ I f f I 1 81 tBl tf f I I1 2000 I I tl I I 134 11 126 11 117 106 KTAS v KTAS V KTAS t KTAS 850 900 950 1000 1050...

Page 95: ...fuel used for engine start taxi takeoff and climb and the time during a normal climb up to 10 000 feet and maximum climb above 10 000 feet r w w u w 0 r i J t 16 000 14 000 12 000 10 000 8000 6000 4000 2000 S L 3 V1 I1 l tJ1 i Si cg I V000J I 1 1 I J If a r r ra a et I I I w w 3 3 3 OI l I 0 0 e I e e r I fo r I fo Cl CD Cl 4 5 6 7 ENDURANCE HOURS Figure 5 9 Endurance Profile Sheet 1 of 2 1 Octobe...

Page 96: ...chart allows for the fuel used for engine start taxi takeoff and climb and the time during a normal climb up to 10 000 feet and maximum climb above 10 000 feet 16 000 14 000 12 000 I 10 000 w W LL 8000 l I t 6000 4000 2000 S L 5 11 1 1 1 v f 7 S C ff A IV a a a a w w w w 0 0 0 0 c c c c L L L L r 0 L 6 7 8 9 10 ENDURANCE HOURS Figure 5 9 Endurance Profile Sheet 2 of 2 11 5 28 1 October 1979 ...

Page 97: ...L TOTAL KIAS FT GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS I 2950 60 S L 560 1300 580 1335 600 1365 620 1400 640 1435 1000 580 1335 600 1365 620 1400 645 1440 665 1475 2000 600 1370 625 1405 645 1440 670 1480 690 1515 3000 625 1410 645 1445 670 1485 695 1525 715 1560 4000 650 1450 670 1485 695 152...

Page 98: ......

Page 99: ...ALANCE EQUIPMENT LIST SECTION 6 WEIGHT BALANCE EQUIPMENT LIST TABLE OF CONTENTS Introduction Airplane Weighing Procedures Weight And Balance Baggage and Cargo Tie Down Equipment List 1 October 1979 Page 6 3 6 3 6 6 6 6 6 15 6 1 6 2 blank ...

Page 100: ......

Page 101: ...l sump drain plug to drain all oil _ d Move sliding seats to the most forward position e Raise flaps to the fully retracted pOSition f Place all control surfaces in neutral position 2 Leveling a Place scales under each wheel minimum scale capacity 1000 pounds b Deflate nose tire and or lower or raise the nose strut to properly center bubble on level see figure 6 1 3 Weighing a With the airplane le...

Page 102: ...tem Airplane Weight 1From Item 5 page 6 3 Add Oil No Oil Filter 112 Ots at 7 5 Lbs Gal With Oil F lter 113 Ots at 7 5 Lbs Gal Add Unusable Fuel 4 Gal at 6 Lbs Gal Equipment Changes Airplane Basic Empty Weight Level On Leveling Screws Left Side of Tailcone Tare Symbol Net Weight L R N W x IN Moment 1000 Weight Lbs X C G Arm In Lbs In 15 0 15 0 24 48 0 1 2 Figure 6 1 Sample Airplane Weighing 6 4 1 O...

Page 103: ...r Equipment Affecting Weight and Balance I SERIAL NUMBER I PAGE NUMBER WEIGHT CHANGE RUNNING BASIC ADDED REMOVED H EMPTY WEIGHT DESCRIPTION OF ARTICLE OR MODIFICATION Wt I Arm IMoment Wt I Arm IMoment Wt IMoment lb In 1000 lb In 1000 lb 1000 Figure 6 2 Sample Weight and Balance Record o Otr l t Ul tr lUl E tr l I tj IJjUl i l tr l OO OOtr l Z m ...

Page 104: ...lem NOTE Loading Graph information for the pilot passengers baggage cargo and hatshelf is based on seats positioned for average occupants and baggage cargo or hatshelf items loaded in the center of these areas as shown on the Loading Arrangements diagram For loadings which may differ from these the Sample Loading Problem lists fuse lage stations for these items to indicate their forward and aft C ...

Page 105: ...ding three rear seat mounting pOints The seven attach points are located as follows two are located slightly inboard and just aft of the rear doorposts approximately at station 69 two utilize the aft outboard mounting points of the rear seat one utilizes the rearmost mounting point of the aft center attach point for the rear seat approxi mately at station 84 a second mounting point is located just...

Page 106: ...ravity range Arms measured to the center of the areas shown NOTES 1 The usable fuel C G arm is located at station 46 5 2 The aft baggage wall approximate station 124 can be used as a convenient interior reference point for determining the location of baggage area fuselage stations 97 CHILD SEAT 115 _ t B A GGAGE 124_T _ _ C G C G ARM ARM 37 37 32 50 32 50 74 74 CARGO 97 BAGGAGE A 97 BAGGAGE A BAGG...

Page 107: ...5 h _ 65 3 DOOR OPENING DIMENSIONS IWIDTH TOP CABIN DOOR I 32 BAGGAGE DOOR 15 I WIDTH IHEIGHT I BOTTOM FRONT I 36Y I 41 I 15 22 HEIGHT REAR 38 20Y CABIN WIDTH MEASUREMENTS CABIN STATIONS 0 C G ARMS 10 20 WIDTH LWR WINDOW LINE CABIN FLOOR Figure 6 4 Internal Cabin Dimensions 1 October 1979 6 9 ...

Page 108: ... Second Row Seats Sta 65 to 82 Baggage Area A or Passenger on Child s Seat Sta 82 to 108 120 Lbs Maximum 90 8 7 Baggage Aft Area B and Hatshelf Sta 108 to 136 80 Lbs Maximum RAMP WEIGHT AND MOMENT 2960 127 9 Fuel allowance for engine start taxi and runup 10 5 TAKEOFF WEIGHT AND MOMENT Subtract step 8 from step 7 2950 127 4 Locate this point 2950 at 127 4 on the Center of Gravity Moment Envelope an...

Page 109: ...113 S 8AGGAGE AREA A OR 20 PASSENGER ON CHILD S SEAT 50 1001 10 75 7 120 LBS MAX t Wi AFT BAGGAGE AREA B AND HATSHELF 80 LBS MAX 50 25 l lQ O IIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIII I I Jlllllr 11111111111111111110 g 0 5 10 15 20 25 30 I ij o LOAD MOMENT l000 POUND INCHES tdfll NOTES 1 Line representing adjustable seats shows pilot and front seat passenger canter of gravity on adjustable seats pos...

Page 110: ...00 2700 z J g 2600 I I Cl 2600 iii 2400 5 D a et o w 2300 o 2200 9 2100 2000 1900 1800 55 1 CENTER 0 MOMENT E 11ILI11 OU 00 IU 10 DU 00 o 00 105 110 115 120 125 130 135 140 LOADED AIRPLANE MOMENT l000 POUND INCHES Figure 6 7 Center of Gravity Moment Envelope 1350 1300 1250 1200 9 1150 1100 g i Cl w z 1050 5 D a 1000 950 900 850 et o w o 9 t CI l Dtt lt q O OI 3 dtIl 1 3 en tlO fo CI l ...

Page 111: ...l I 1 I I 1 2200 i I I I I I I I I I I 1000 I 1 1 CENTER OF GRAVITY 11 T T Tft 2100 t 1 t t 1 LIMITS f I d J 2000 1 1 d r 9OO I I I I I I I I t I t f t 1 I i 1t J 1900 I I I t _ __ _ 1800 1 I I 1 4 _ _ 1 I I I 1 1 11 1 950 850 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 4748 AIRPLANE C G LOCATION INCHES AFT OF DATUM STA 0 0 Figure 6 8 Center of Gravity Limits O Ot J t lrll t JrIl t Z 00 D ij i 0 ...

Page 112: ......

Page 113: ...andard equipment items 0 optional equipment items replacing required or standard items A optional equipment items which are in addition to required or standard items A reference drawing column provides the drawing number for the item NOTE If additional equipment is to be installed it must be done in accordance with the reference drawing accessory kit instruc tions or a separate FAA approval Column...

Page 114: ...SIX CYLINDER OIL QUICK DRAIN VALVE NET CHANGE P LANDING GEAR ACCESSORIES wHEEL BRAKE I hFH ASSY I RAKE ASSY PRAKF ASSY TIRE 6 PLY TUBF WHEEL ARAKE wHFFL ASSY eRAKE ASSY TIRE ASSY 6 COX6 MAIN 2 CLEVELAND 40 113 EACH CLEVELAND 30 75 LEFT CLEVELAND 30 75 RIGHT RATED BLACKkALL EACH EACH TIRE ASSV 6 0QX6 MAIN 2 MCCAULEV EACH MCCAUlEV C 30018 LEFT RH DRAWING 0750201 SLlGK b214 TCM 621392 SH 200A TCT 635...

Page 115: ...IN GEAR SfT OF 2 1441003 1 4 5 58 9 C ELECTRICAL SYSTEMS nI I AATTFRY 4 VOLT STA DARC CLTY C614002 0101 23 2 130 0 OI f BATTERY 24 VOLT HEAVY OUTv C614002 01Q2 25 2 130 0 r l4 k ALTERNATOR CCNTROL UNIT 28 VOLTloITH HIGH C611005 0101 0 4 0 3 A D LOW VOLTAGE SE SI G 7 GRCL O SFRVICF PLUG RECEPTACLE 711 19 2 3 2 2 6 10 A ELErTRIC ELEvATOR TRI INSTl 2270J07 2 3 8 217 7 ELECTRIC CRIVE ASSEMBLY 3 3 221 ...

Page 116: ...TAL READGUT CO PASS MAGNETIC MCUNT JNSTRU FNT CLUSTfR E GINE FUEL INDICATOR INSTALLATIOI ECO CMY MIXTURE FGT INDICATOR ThFRMOCOUPLE PRGAE THFPMOCOUPLE LEAC Io IRE ICI GYRr SYSTFM OIRFCTIONAL INOICATOR ATTITUDE INDICATOR hCSfS FITTINGS SCREWS CLAMPS ETC AI TERNATF C661C75 C661076 GYRO S MAY BE USFD GYRO SYSTEM INSTL FOR NAV O MATIC 300A AUTCPTLOT ITEM H31 A 21 ATTITUDE INDICATOR RH DRAWING 22 1008 ...

Page 117: ...UT INERTIA REEL INSTL t ET f ANGEI BELT r SHOULDER HARNESS ASS CO PILCT BELT ASSY ND ROW OCCUPANTS SET OF 2 BELT r SHOULDER HARNESS ASSY 2ND ROW INTERIOR VINYL SEAT COVEPS NET CHANGE INTERlfR LFATHER SEAT ceVERS NET CHANGE CPE ARLF RH CABIN DOOR I DCW NET CHAt GE WINCCWS OVERHEAC CABIN TCP NET CHANGEI VENTILATICN SYSTEM 2ND RCW SEATING CURTAIN REAR WINDOW OXYCEN SYSTFM 4 PORT REF DRAWING 40761 010...

Page 118: ... 1260243 9 0750201 f11 R PLACARf OPFRATIGNAL LIMITATIONS VI DAY 05C5087 7 fnl C l PLACAkC OPFRATICNAL LIMITATIONS VfR OAY 0505087 8 NIGFT nl n 7 PLACARC OPERATILN L LI ITA1ICNS IFR D lY 0505087 9 NI FT F14 INcrCATOR STALL WARNING HORN AUDr lF S 2077 8 Fl R PILrT S OPERATING HANDBfCK AND FAA D1176 13PH Ill A n A G13 A 16 A lq A G S lPPROVFC flIRPLANE FLIGhT ANUAL STeWED G AUXILIARY ECUIPMENT TAILcn...

Page 119: ...IfESSNA 40C ADF BfO AOf RFCflVFR ITH BFO R 446A r rNIr MFTFR INCICATCR I 346A AOF LOOP ANTENNA ASSOC WIRING ACF SFNS ANTENNA rIlNTINr ACX MISC ITEMS Hn3 A lAM FM TERFn REr fIVER CASSETTE PLAYER HFACSET SET OF 2 4 MAY BE USED STFRfO RFCFIVER INSTALLATION A TENNA wIRING MISC ITEMS H04 A l IOME INSTALLATION NARCO TRANSf EIVER DME 1 0 IJrUH ASSY ANTFNNA H04 A 7 ICESSNA 40n DME INSTAlLATICN RECfIVER TR...

Page 120: ... InRl 28 RE OTE ANTENNA LOAD 80X At TfNNA INSTI 351 INCHES LONG SUt AIRF SSA HF TRANSCEIVER 2ND UNIT RE IOOO SINGLE SIDE 6AND XCVR AS6 125 PAlrlOA REMOTE POwER AMPLIFIER CIl IIO ANTENNA COUPLER LOAD 6eX At TFNNA INSTL 351 It CHES LONG CESSNA 400 MARKFR BEACON REr FIVER R 402A ANTFNNA FLUSH MOUNTED IN TAILCCNE CESSNA 100 TRANSPONDER RECEIVER TRANSMITTER IRT 359A ANTFNNA CESSNA 400 TRANSPONDER RH DR...

Page 121: ...SSNA 400 NAV CGM 720 CH CCM WITH 300 3910189 6 8 3 12 9 SERIES INDICATOR 2ND UNIT REQUIRES H37 A TC BE CPERATICNAL RECEIVER TRANSCEIVER IRT 485A 47360 1000 5 5 12 5 VCR LOC INDICATOR IN 385AI 46860 1000 1 6 15 5 MCUNT WIRING MISC HARDWARE 1 2 11 8 H7R A l IFMERGENCY LOCATOR TRAr SMITTER 0470419 3 5 134 6 TRAr SMITTER ASSY ID M DMELT 6 11 C589511 0117 3 3 134 5 ANTENNA ASSY C589511 0109 0 1 137 6 H...

Page 122: ...ENSF ANTENNA FLUSH rlJNTED COM ANTENNA FLUSH MTD IN LEADING EDGE VERTICAL FIN MIC I IFADSET CCMAINATIGN lIGHT T RECUIRES FH9 f INSTALLATION HFACSFT MICRCPHONE PADDED STakED RFQulRES F 89 r INSTALLATION RE CTE TRANSPCNDER IDENT SwITCH J SPECIAL CPTICN PACKAGES SKYLANf II KTT Cr 7 A GRCUNC SERVICE RECEPTACLE C19 0 HEATFD PITeT STALL WARNING 31 A COURTESY ENTRANCE LIGHTS 2 RH DRAWING 42660 2202 44690...

Page 123: ...ITTER h31 A l CFSSNA 20l A A TO PllOT H34 A ASIC AVIONICS KIT NAV PAC SKYlAt F I OiLYI ET Cf NG H07 A 41 1 GlIOESlOPE IR 443ul I B A 400 MARKER BEACC k 40 AI h25 A l AV CCM 385A VCR Lee 2 O UNIT 1 137 A ANTEN A COUPLER KIT RH DRAWING WT LBS 1 7 Jl H 3 NEGL 07031 42 1 1 8 1201108 7 0 2 0711028 1 0 3 0 7 0760101 5 6 7 1201131 2 0 4 3910159 1 8 5 3910127 6 4 1 3910183 8 3 0470419 3 5 9 1 3910186 7 8 ...

Page 124: ......

Page 125: ...Harnesses With Inertia Reels Entrance Doors And Cabin Windows Control Locks Engine Engine Controls Engine Instruments New Engine Break In And Operation Engine Oil System Ignition Starter System Air Induction System Exhaust System Carburetor And Priming System Cooling System Propeller Fuel System Brake S stem Electrical S stem Master Sv itch Avionics Pm I er Switch Ammeter 1 October 1979 Page 7 3 7...

Page 126: ...3 Airspeed Indicator 7 33 Vertical Speed Indicator 7 34 Altimeter 7 34 Vacuum System And Instruments 7 34 Attitude Indicator 7 36 Directional Indicator 7 36 Suction Gage 7 36 Stall Warning System 7 36 Avionics Support Equipment 7 37 Audio Control Panel 7 37 Transmitter Selector Switch 7 37 Audio Selector Switches 7 39 Corn Auto Audio Selector Switch 7 39 Corn Both Audio Selector Switch 7 40 Auto A...

Page 127: ...ire structure is covered with aluminum skin The front spars are equipped with wing to fuselage and wing to strut attach fit tings The aft spars are equipped with wing to fuselage attach fittings and are partial span spars Conventional hinged ailerons and single slot type flaps are attached to the trailing edge of the wings The ailerons are constructed of a forward spar containing balance weights f...

Page 128: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS AILERON CONTROL SYSTEM RUDDER AND RUDDER TRIM CONTROL SYSTEMS CESSNA MODEL 182Q Figure 7 1 Flight Control and Trim Systems Sheet 1 of 2 7 4 1 October 1979 ...

Page 129: ...CESSNA MODEL 182Q SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS ELEVATOR CONTROL SYSTEM ELEVATOR TRIM CONTROL SYSTEM z J t j j f n f Figure 7 1 Flight Control and Trim Systems Sheet 2 of 2 1 October 1979 7 5 ...

Page 130: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS Figure 7 2 Instrument Panel Sheet 1 of 2 7 6 CESSNA MODEL 182Q 1 October 1979 ...

Page 131: ... Control Pedestal Light Lights and Switches 41 Rudder Trim Control Wheel and CD 15 Autopilot Control Unit Position Indicator 1 1 16 Audio Control Panel 42 Cowl Flap Control Lever 1l 17 ADF Radio 43 Microphone P 1 1 18 Nav Com Radios 44 Fuel Selector Light CD 19 Transponder 45 Fuel Selector Valve Handle 0 20 Manifold Pressure Gage 46 Elevator Trim Control Wheel 00 00 t IJ 21 Tachometer and Position...

Page 132: ...stall an exten sion place the clip on the bottom of the extension under the bottom of the rudder pedal and snap the top clip over the top of the rudder pedal Check that the extension is firmly in place To removethe extensions reverse the above procedures TRIM SYSTEMS Manually operated rudder and elevator trim is provided see figure 7 1 Rudder trimming is accomplished through a bungee connected to ...

Page 133: ...levator and rudder trim control wheels cowl flap control lever and microphone bracket The fuel selector valve handle is located at the base of the pedestal A parking brake handle is mounted below the switch and control panel in front of the pilot A static pressure alternate source valve control knob may also be installed below the switch and control panel adjacent to the parking brake handle For d...

Page 134: ...figure 7 3 are extended or retracted by positioning the wing flap switch lever on the right side of the switch and control panel to the desired flap deflection position The switch lever is moved up or down in a slotted panel that provides mechanical stops at the 10 and 20 positions For flap settings greater tlian 10 move the switch lever to the right to clear the stop and position it as desired A ...

Page 135: ... 6 When loading the airplane children should not be placed or permitted in the baggage compartment and any material that might be hazardous to the airplane or occupants should not be placed anywhere in the airplane For baggage area and door dimensions refer to Section 6 SEATS The seating arrangement consists of two individually adjustable four way or six way seats for the pilot and front seat pass...

Page 136: ...seats are not occupied the seat backs will automatically fold forward whenever the release buttons are pushed up A child s seat may be installed aft of the rear passengers seat and is held in place by two brackets mounted on the floorboard The seat is designed to swing upward into a stowed position against the aft cabin bulkhead when not in use To stow the seat rotate the seat bottom up and aft as...

Page 137: ... i seat belt link to attach harness I i SEAT BELT CKLEHALF l i 1 ii tv r jj I _3 p t SEAT BELT UNK HALF si ARNESS 0 FREE END OF SEAT BELT Pull to tighten SEAT BELTISHOULDER HARNESS ADJUSTABLE LINK IP sition link just below shoulder leye1 pull link and harness down ward to connect to seat belt buckle PILOT S SEAT SHOWN SEAT BELT SHOULDER HARNESS WITH INERTIA REEL Figure 7 4 Seat Belts and Shoulder ...

Page 138: ... harness is available for the child s seat To use a front or rear seat shoulder harness fasten and adjust the seat belt first Lengthen the harness as required by pulling on the connecting link on the end of the harness and the narrow release strap Snap the connecting link firmly onto the retaining stud on the seat belt link half Then adjust to length A properly adjusted harness will permit the occ...

Page 139: ...the doors from outside the airplane utilize the recessed door handle near the aft edge of each door Depress the forward end ofthe handle to rotate it out of its recess and then pull outboard To close or open the doors from inside the airplane use the combination door handle and arm rest The inside door handle has three positions and a placard at its base which reads OPEN CLOSE and LOCK The handle ...

Page 140: ...G ENGI E To install the control lock align the hole in the top of the pilot s control wheel shaft with the hole in the top of the shaft collar on the instrument panel and insert the rod into the aligned h les Installation of the lock will secure the ailerons in a neutral position and the elevators in a slightly trailing edge down position Proper installation of the lock will place the red flag ove...

Page 141: ... onthe right side ofthe instrumentpanel is operated by oil pressure A direct pressure oil line from the engine delivers oil at engine operating pressure to the oil pressure gage Gage markings indicate that minimum idling pressure is 10 PSI red line the normal operating range is 30 to 60 PSI green arc and maximum pressure is 100 PSI red line Oil temperature is indicated by a gage adjacent to the oi...

Page 142: ... run in at the factory and is ready for the full range of use It is however suggested that cruising be accomplislied at 75 power until a total of50hours has accumulated or oil consumption has stabilized This will ensure proper seating of the rings The airplane is delivered from the factory with corrosion preventive oil in the engine If during the first 25 hours oil must be added use only aviation ...

Page 143: ...alve installed slip ahose over the end of the valve and push upward on the end of the valve until it snaps into the open position Spring clips will hold the valve open After draining use a suitable tool to snap the valve into the extended closed position and remove the drain hose IGNITION STARTER SYSTEM Engine ignition is provided by two engine driven magnetos and two spark plugs in each cylinder ...

Page 144: ...ngine The carburetor is equipped with an enclosed accelerator pump an idle cut off mechanism and a manual mixture control Fuel is delivered to the carburetor by gravity flow from the fuel system In the carburetor fuel is atomized proportionally mixed with intake air and delivered to the cylinders through intake manifold tubes The proportion of atomized fuel to air may be controlled within limits b...

Page 145: ...he governor then controls flow of engine oil boosted to high pressure by the governing pump to or from a piston in the propeller hub Oil pressure acting on the piston twists the blades toward high pitch low RPM When oil pressure to the piston in the propeller hub is relieved centrifugal force assisted by an internal spring twists the blades toward low pitch high RPM A control knob on the center ar...

Page 146: ... O CARBURETOR _ 7 22 O TO ENGINE Figure 7 5 Fuel System CESSNA MODEL 182Q REDUCED CAPACITY STANDPIPE TO ENSURE MAXIMUM FUEL CAPACITY WHEN REFUELlNG AND MINIMIZE CROSS FEEDING WHEN PARKED ON A SLOPING SURFACE PLACE THE FUEL SELECTOR VALVE IN EITHER LEFT OR RIGHT POSITION 1 1 c J TO ENGINE CODE FUEL SUPPLY VENT MECHANICAL LINKAGE ELECTRICAL CONNECTION 1 October 1979 ...

Page 147: ...checkvalve equipped overboard vents in each tank The overboard vents protrude from the bottom surfaces of the wings behind the wing struts slightly below the upper attach points ofthe struts The fuel filler caps are vacuum vented the vents will open and allow air to enter the fuel tanks in case the overboard vents become blocked Fuel quantity is measured by two float type fuel quantity transmitter...

Page 148: ...ntained exactly level Resulting wing heaviness can be alleviated gradu ally by turning the selector valve handle to the tank in the heavy wing NOTE It is not practical to measure the time required to consume all of the fuel in one tank and after switching to the opposite tank expect an equal duration from the remain ing fuel The airspace in both fuel tanks is interconnected by a vent line and ther...

Page 149: ...mptoms of impending brake failure are gradual decrease in braking action after brake application noisy or dragging brakes soft or spongy pedals and excessive travel and weak braking action If any of these symptoms appear the brake system is in need of immediate attention If during taxi or landing roll braking action decreases let up on the pedals and then re apply the brakes with heavy pressure If...

Page 150: ... COMPASS LIGHT AND OXYGEN L IGHTS I I O f TO POST LIGHTING TO GLARE SHIELD AND OVERHEAD CONSOLE FL OOD LIGHTS TO DOME ANO COURTESY L IGHTS TO IGNITION SWITCH LOW VOLTAGE WARNING LIGHT al f TO FUEL QUANTITY INDICATORS TO CYLINDER HEAD TEMP OIL TEMP CARSURETOR AI R TEMP GAGES TO HEATED PITOT SYSTEM HEATED STALL WARNING SYSTEM AND DIGITAL CLOCK TO ELECTROLUMINESCENT PANELS AND AUDIO CONTROL PANEl TO ...

Page 151: ...enough to open the battery contactor remove powerfroIIl the alternator field and prevent alternator restart AVIONICS POWER SWITCH Electrical power from the airplane primary bus to the avionics bus see figure 7 7 is controlled by a toggle switch circuit breaker labeled A VIONICS POWER The switch is located oil the left side ofthe switch and control panel and is ON in the up position and off inthe d...

Page 152: ...will illuminate when system voltage drops below normal The alternator control unit may be reset by turning the master switch off and back on again If the warning light does not illuminate normal alternator charging has resumed however if the light does illuminate again a malfunction has occurred and the flight should be terminated as soon as practicable NOTE Illumination of the low voltage light a...

Page 153: ...il stinger and dual landing taxi lights are installed in the cowl nose cap Additional lighting is available and includes a strobe light on each wing tip a flashing beacon on top of the vertical stabilizer and two courtesy lights one under each wing just outboard of the cabin doors Details of the strobe light system are presented in Section 9 Supplements The courtesy lights are operated by a switch...

Page 154: ...t or flood lighting To operate these lights rotate the outer knob labeled ENG RADIO on the right dimming rheostat clockwise to the desired light intensity However for daylight operation the compass and engine instrument lights may be turned off while still maintaining maximum light intenSity for the digital readouts in the radio equipment This is accomplished by rotating the ENG RADIO knob full co...

Page 155: ...aker has opened white button popped out and there is no obvious indication of a short circuit smoke or odor turn offthe light switch ofthe affected lights reset the breaker and turn the switch on again If the breaker opens again do not reset it CABIN HEATING VENTILATING AND DEFROSTING SYSTEM The temper ature and volume of airflow into the cabin can be regulated by manipulation of the push pull CAB...

Page 156: ...R DOOR CABIN AIR CONTROL DEFROSTER CONTROL Q Q REARCABI t ff 7 32 AIR Ol TLETS ADJUSTABLE VENTILATORS AIRFLOW ADJUSTMENT L WHEELS P ADJUSTABLE AIR OUTLETS CODE J RAM AIR FLOW P VENTILATING AIR HEATED AIR BLENDED AIR MECHANICAL CONNECTION Figure 7 8 Cabm Heating Ventilating and Defrosting System 1 October 1979 ...

Page 157: ...ing an adjustment wheel adjacent to the outlet PITOT STATIC SYSTEM AND INSTRUMENTS The pitot static system supplies ram air pressure to the airspeed indicator and static pressure to the airspeed indicator vertical speed indicator and altimeter The system is composed of either an unheated or heated pitot tube mounted on the lower surface of the left wing two external static ports on the lower left ...

Page 158: ...rily set the barometric scale on the altimeter to 29 92 and read pressure altitude on the altimeter Be sure to return the altimeter baromet ric scale to the original barometric setting after pressure altitude has been obtained Having set the ring to correct for altitude and temperature read the true airspeed shown on the rotatable ring by the indicator pointer For best accuracy the indicated airsp...

Page 159: ...ET AIR E 3 VACUUM DISCHARGE AIR SUCTION GAGE ATTITUDE INDICATOR SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS 4Z BW OVERBOARD VENT LINE VACUUM PUMP VACUUM RELIEF VALVE VACUUM SYSTEM AIR FILTER Figure 7 9 Vacuum System 1 October 1979 7 35 ...

Page 160: ... attitude indication DIRECTIONAL INDICATOR A directional indicator displays airplane heading on a compass card in relation to a fixed simulated airplane image and index The directional indicator will precess slightly over a period of time Therefore the compass card should be set in accordance with the magnetic compass just prior to takeoff and occasionally re adjusted on extended flights A knob on...

Page 161: ...s microphone headset installations and control surface static dischargers The following paragraphs discuss these items Description and operation of radio equipment is covered in Section 9 of this handbook AUDIO CONTROL PANEL Two types of audio control panels see figure 7 10 are available for this airplane depending upon how many transmitters are included The operational features of both audio cont...

Page 162: ... i 1 11 LO Cl I FI 11111 l 1I II J TRANSMITTER SELECTOR SWITCH TRANSMITTER SELECTOR SWITCH 7 38 XMTR 1 o COM AUTO AUDIO SELECTOR AUDIO SELECTOR SWITCHES SWITCH I ANN LTS DME ANNUNCIATOR LIGHTS BRIGHTNESS AND TEST SWITCH USED WITH THREE TRANSMITTERS SPEAKER 3 AUTO NAV COM ADF 1 2 3 2 AUTCMATIC AUDIO SELECTOR AUDIO SELECTOR SWITCHES SWITCH Flgure 7 10 Audio Control Panel AUDIO SELECTOR SWITCHES 1 Oc...

Page 163: ...osition To listen to a receiver over a headset place that receiver s audio selector switch in the down PHONE position Thecenter OFF position turns off all audio from the associated receiver NOTE Volume level is adjusted uSing the individual receiver volume controls on each radio A special feature of the audio control panel used when one or two transmitters are installed is separate control of NAV ...

Page 164: ...or switch in the up SPEAKER position so that the number two communications receiver audio will be heard in addition to the number one communications receiver audio This feature can also be used when listening on a headset by placing the COM BOTH audio selector switch in the down PHONE position NOTE The combination of placing the COM AUTO switch in the SPEAKER position and the COM BOTH switch in th...

Page 165: ...ION Cessna radios are equipped with sidetone capability monitoring of the operator s own voice transmission While adjusting sidetone be aware that if the sidetone volume level is set too high audio feedback squeal may result when transmitting When the airplane has one or two transmitters sidetone is provided in both the speaker and headset anytime the COM AUTO selector switch is utilized Placing t...

Page 166: ... headset jacks are located on the left side of the instrument panel Audio to all three headsets is controlled by the individual audio selector switches and adjusted for volume level by using the selected receiver volume controls NOTE When transmitting the pilot should key the microphone place the microphone as close as possible to the lips and speak directly into it STATIC DISCHARGERS If frequent ...

Page 167: ... radio signals even with static dischargers installed Whenever possible avoid known severe precipita tion areas to prevent loss of dependable radio signals If avoidance is impractical minimize airspeed and antiCipate temporary loss of radio signals while in these areas 1 October 1979 7 43 7 44 blank ...

Page 168: ......

Page 169: ...sive Care Cessna Customer Care Program Pilot Conducted Preventive Maintenance Alterations or Repairs Ground Handling Towing Parking Tie Down Jacking Leveling Flyable Storage Servicing Engine Oil Fuel Landing Gear Oxygen Cleaning and Care Windshield Windows Painted Surfaces Propeller Care Engine Care Interior Care 1 October 1979 Page 8 3 8 3 8 3 8 3 8 4 8 5 8 5 8 6 8 6 8 7 8 7 8 7 8 7 8 8 8 8 8 8 8...

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Page 171: ...mber PC and Type Certificate Number TC can be found on the Identification Plate located on the left forward doorpost Located adjacent to the Identification Plate is a Finish and Trim Plate which contains a code describing the interior color scheme and exterior paint combination of the airplane The code may be used in conjunction with an applicable Parts Catalog if finish and trim information is ne...

Page 172: ...l available items many of which he keeps on hand He will be happy to place an order for any item which is not in stock r NOTE A Pilot s Operating Handbook and FAA Approved Air plane Flight Manual which is lost or destroyed may be replaced by contacting your Cessna Dealer or writing directly to the Customer Services Department Cessna Aircraft Company Wichita Kansas An affidavit con taining the owne...

Page 173: ...that these items plus the Pilot s Checklists Power Computer Customer Care Program book and Customer Care Card be carried in the airplane at all times AIRPLANE INSPECTION PERIODS FAA REQUIRED INSPECTIONS As required by Federal Aviation Regulations all civil aircraft of U S registry must undergo a complete inspection annual each twelve calend ar months In addition to the required ANNUAL inspection a...

Page 174: ...WO hour inspection have been carefully worked out by the factory and are followed by the Cessna Dealer Organization The complete familiarity of Cessna Dealers with Cessna equipment and factory approved procedures provides the highest level of service possl ble at lower cost to Cessna owners Regardless of the inspection method selected by the owner he should keep in mindthat FAR Part 43 andFAR Part...

Page 175: ...information on preventive maintenance that may be performed by pilots A Service Manual should be obtained prior to performing any preven tive maintenance to ensure that proper procedures are followed Your Cessna Dealer should be contacted for further information or for required maintenance which must be accomplished by appropriately licensed personnel ALTERATIONS OR REPAIRS It is essential that th...

Page 176: ... no chains or cables to the nose gear torque link and secure to a ramp tie down 5 Install a pitot tube cover JACKING When a requirement exists to jackthe entire airplane offthe ground or when wing jack pOints are used in the jacking operation refer to the Service Manual for specific procedures and equipment required Individual main gear may be jacked by using the jack pad which is incorporated in ...

Page 177: ...or the first 25 hours are considered in flyable storage status Every seventh day during these periods the propeller should be rotated by hand through five revolutions This action limbers the oil and prevents any accumulation of corrosion on engine cylinder walls I WARNING I For maximum safety check that the ignition switch is OFF the throttle is closed the mixture control is in the idle cut off po...

Page 178: ...pections ortests For these regulatory requirements owners should check with local aviation officials where the airplane is being operated For quick and ready reference quantities materials and specifica tions for frequently used service items are as follows ENGINE OIL GHADE A J D VISCOSITY FOR TEMPERATURE RANGE All temperatures use SAE 20W 50 or Above 4 C 40 F use SAE 50 Below 4 C 40 F use SAE 30 ...

Page 179: ...ilter change a general inspection of the overall engine compartment is required Items which are not normally checked during a preflight inspection should be given special attention Hoses metal lines and fittings should be inspected for signs of oil and fuel leaks and checked for abrasions chafing security proper routing and support and evidence of deterioration Inspect the intake and exhaust syste...

Page 180: ...ffect of 1 use of certain fuels with 2 high humidity conditions on the ground 3 followed by flight at high altitude and low temperature Under these unusual conditions small amounts of water in solution can precipitate from the fuel stream and freeze in sufficient quantites to induce partial icing of the engine fuel system While these conditions are quite rare and will not normally pose a problem t...

Page 181: ...operation by pouring the alcohol directly on the fuel stream issuing from the fueling nozzle 2 An alternate method that may be used is to premix the complete alcohol dosage with some fuel in a separate clean container approximately 2 3 gallon capacity and then transferring this mixture to the tank prior to the fuel operation Any high quality isopropyl alcohol may be used such as Anti Icing Fluid M...

Page 182: ...eches out the additive An indication of this is when an excessive amount of water accumulates in the fuel tank sumps The concentration can be checked using a differential refractometer It is imperative that the technical manual for the differential refractometer be followed explicitly when checking the additive concentration LANDING GEAR JOSE WHEEL TIRE PRESSURE 49 PSI on 5 00 5 6 Ply Rated Tire M...

Page 183: ...sleet is anticipated since the cover may scratch the plastic surface PAINTED SURFACES The painted exterior s urfaces of your new Cessna have a durable long lasting finish and under normal conditions require no polishing or buffing Approximately 10 days are required for the paint to cure com pletely in most cases the curing period will have been completed prior to delivery of the airplane In the ev...

Page 184: ... may be cleaned with Stoddard solvent or equivalent then dried thoroughly CAUTION Particular care should be given to electrical equipment before cleaning Cleaning fluids should not be allowed to enter magnetos starter alternator and the like Protect these components before saturating the engine with sol vents All other openings should also be covered before cleaning the engine assembly Caustic cle...

Page 185: ...r seating cleaning of the seats is accomplished using a soft cloth or sponge dipped in mild soap suds The soap suds used sparingly will remove traces of dirt and grease The soap should be removed with a clean damp cloth The plastic trim headliner instrument panel and control knobs need only be wiped offwith a damp cloth Oil and grease on the control wheel and control knobs can be removed with a cl...

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Page 187: ...ransmitter ELT 4 pages 11 Foster Area Navigation System Type 511 8 pages 12 HF Transceiver Type PT10 A 4 pages 3 SSB HF Transceiver Type ASB 125 4 pages 14 Unslaved Horizontal Situation Indicator Type IG 832C 6 pages 15 200A Navomatic Autopilot Type AF 295B 6 pages 16 300 ADF Type R 546E 6 pages 17 300 Nav Com Type RT 385A 8 pages 18 300 Nav Com Type RT 385A With 400 Area Navigation System Type RN...

Page 188: ...av Com Type RT 485A 28 400 Nav Com Type RT 485A With 400 Area Navigation System Type RN 478A 29 400 Transponder Type RT 459A And Optional Altitude Encoder Blind 30 400 Transponder Type RT 459A And Optional Encoding Altimeter Type EA 401A 9 2 CESSNA MODEL 182Q 4 pages 6 pages 10 pages 10 pages 6 pages 6 pages 1 October 1979 ...

Page 189: ... are classified under the headings of general and avionics and have been provided with reference numbers Also the supplements are arranged alphabetically and numerically to make it easier to locate a particular supplement Other routinely installed items of optional equipment whose function and operational procedures do not require detailed instructions are discussed in Section 7 Limitations contai...

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Page 191: ...e range most conducive to carburetor icing SECTION 2 LIMITATIONS There is no change to the airplane limitations when the carburetor air temperature gage is installed SECTION 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when the carburetor air temperature gage is installed SECTION 4 NORMAL PROCEDURES There is no change to the airplane normal procedures when the car...

Page 192: ...uretor heat applied SECTION 5 PERFORMANCE There is no change to the airplane performance when the carburetor air temperature gage is installed However if it is necessary to operate with carburetor heat applied a small performance loss may be expected at any given power setting due to the warmer induction air temperature 2 1 October 1979 ...

Page 193: ...by the second row passengers The table is equipped with guides which follow tracks inside the stowage compartment SECTION 2 LIMITATIONS The following information must be presented in the form of a placard located on the back of the convenience table STOW LEAF DURING TAKEOFF AND LANDING SECTION 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when the convenience table...

Page 194: ...andle near the top edge of the leaf slide it upward and aft until the leaf contacts the stops at the top of the compartment Stowing the table is accomplished by rotating it upward and sliding it back down into the stowage compart ment SECTION 5 PERFORMANCE There is no change to the airplane performance when the convenience table is installed 2 1 October 1979 ...

Page 195: ...n type switches directly below the display control all time keeping functions These control functions are summarized in figures 2 and 3 The digital display features an internal light back light to ensure good visibility under low cabin lighting conditions or at night The intensity of the back light is controlled by the ENG RADIO lights rheostat In addition the display incorporates a test function ...

Page 196: ...ily while in the clock mode the calendar date appears numerically on the display with month ofyear to the left of the colon and day of the month shown to the right of the colon The display automatically returns to the clock mode after approximately 1 5 seconds However if the RH button is pressed continuously longer than approximately two seconds the display will return from the date to the clock m...

Page 197: ...eviously accumu lated total Figure 3 Timer Mode digits switch accessible through a smallhole onthe bottom ofthe instrument case Notice that in the 24 hour format the clock mode indicator does not appear SETTING CORRECT DATE AND TIME The correct date and time are set while in the clock mode using the LH and RH push buttons as follows press the LH button once to cause the date to appear with the mon...

Page 198: ...rns to the normal time keeping mode without altering the minutes timing TIMER OPERATION The completely independent 24 hour elapsed timer see figure 3 is operated as follows press the center MODE push button until the timer mode indicator appears Reset the display to zero by pressing the LH button Begin timing an event by pressing the RH button The timer will begin counting in minutes and seconds a...

Page 199: ...n the nose up direction When the switch is released it automatically returns to the center off position and elevator trim tab motion stops The disengage switch labeled ELEC TRIM DISENGAGE disables the system when placed inthe DISENGAGE aft position A servo unit which includes a motlJr and chain driven solenoid operated clutch actuates the trim tab to the selected position When the clutch is not en...

Page 200: ...witch ON 2 Elevator Trim Disengage Switch ON 3 Trim Switch ACTUATE as desired 4 Elevator Trim Position Indicator CHECK NOTE To check the operation ofthe disengage switch actuate the elevator trim switch with the disengage switch in the DISENGAGE aft position Observe that the manual trim wheel and indicator do not rotate when the elevator trim switch is activated SECTION 5 PERFORMANCE There is no c...

Page 201: ...h should beturned off If maintenance is required on the avionics equipment it is advisable to utilize a battery cart external power source to prevent damage to the avionics equipmentby transient voltage Do not crank or start the engine with the avionics power switch turned on The battery and external power circuits have been designed to com pletely eliminate the need to jumper across the battery c...

Page 202: ...s no change to the airplane emergency procedures when the ground service plug receptacle is installed SECTION 4 NORMAL PROCEDURES Just before connecting an external power source generator type or battery cart the avionics power switch should be turned off and the master switch turned on 2 WARNING When turning on the master switch using an external power source or pulling the propeller through by h...

Page 203: ...rnal power source will flow only if the ground service plug is correctly connected to the airplane Ifthe plug is aCCidentally connected backwards no power will flow to the electrical system thereby preventing any damage to electrical equipment SECTION 5 PERFORMANCE There is no change to the airplane performance when the ground service plug receptacle is installed 1 October 1979 3 4 blank ...

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Page 205: ...one equipped mask is pro vided for the pilot and three disposable type masks are provided for the passengers All masks are the partial rebreathing type equipped with vinyl plastic hoses and flow indicators NOTE The hose provided for the pilot is of a higherflow ratethan those for the passengers it is color coded with an orange band adjacent to the plug in fitting The passenger hoses are color code...

Page 206: ...letely automatic and requires no manual regulation for change of alti tude The oxygen cylinder when fully charged contains approximately 48 cubic feet of oxygen under a pressure of 1800 psi at 70 F 21 C Filling pressures will vary however due to the ambienttemperature in the filling area and because of the temperature rise resulting from compression of the oxygen Because of this merely filling to ...

Page 207: ...ygen line fitting and passengers with green col or coded line fittings Figure 2 Oxygen Duration Chart For FAA requirements concerning supplemental oxygen refer to FAR 91 32 Supplemental oxygen should be used by all occupants when cruising above 12 500 feet As described in the Cessna booklet Man At Altitude it is often advisable to use oxygen at altitudes lower than 12 500 feet under Iconditions of...

Page 208: ...ot only for nearly 6 hours and 15 minutes The same pressure will sustain the pilot and three passengers for approximately 2 hours and 30 minutes NOTE The Oxygen Duration Chart is based on a standard config uration oxygen system having one orange color coded hose assembly for the pilot and green color codedhoses for the passengers If orange color coded hoses are provided for pilot and passengers it...

Page 209: ... Adjustmask to face and adjust metallic nose strap for snug mask fit 2 Delivery Hose PLUG INTO OUTLET nearest to the seat you are occupying NOTE When the oxygen system is turned on oxygen will flow continuously at the proper rate of flow for any altitude without any manual adjustments 3 Oxygen Supply Control Knob ON 4 Face Mask Hose Flow Indicator CHECK Oxygen is flowing ifthe indicator is being f...

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Page 211: ... push to reset circuit breaker The rocker switch and circuit breaker are located on the left side of the switch and control panel SECTION 2 LIMITATIONS Strobe lights must be turned off when taxiing in the vicinity of other airplanes or during night flight through clouds fog or haze SECTION 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when strobe lights are install...

Page 212: ...6 STROBE LIGHT SYSTEM MODEL 182Q PILOT S OPERATING HANDBOOK SUPPLEMENT SECTION 5 PERFORMANCE The installation of strobe lights will result in a minor reduction in cruise performance 2 1 October 1979 ...

Page 213: ...pment should be installed for operations in temperatures consistently below 200 F l 7CC Once installed the crankcase breather insulation is approved for permanent use in both hot and cold weather SECTION 2 LIMITATIONS The following information must be presented in the form of placards when the airplane is equipped with a winterization kit 1 On each nose cap cover plate and induction air inlet cove...

Page 214: ...o the airplane emergency procedures when the winterization kit is installed SECTION 4 NORMAL PROCEDURES There is no change to the airplane normal procedures when the winterization kit is installed SECTION 5 PERFORMANCE There is no change to the airplane performance when the winterization kit is installed 2 1 October 1979 ...

Page 215: ...ltitude the radio can receive FM stations for over 200 miles The cassette stereo player is equipped with four track two channel stereo cassette type playback with a tape speed of 4 76 cm sec Any standard size monaural or stereo cassette may be used in the player Cassettes are automatically activated when inserted in cassette receptacle with tape play side to the right with radio ON and AM FM switc...

Page 216: ...one plugwhich must be attached to one ofthe phone jacksmounted overhead Stereo phone jacks are placarded either STEREO or STE REO HEADPHONE 2 NOTICE Sound from the player radio is only available through stereo headphones 2 3 4 5 6 7 10 9 8 11 12 13 Figure 1 A 1 1 F Cassette Stereo Entertainment Center Operating Controls Sheet 1 of 3 1 October 1979 ...

Page 217: ...Hz and FM between 88 and 108 MHz 5 COM INTERRUPT PUSHBUTTON SELECTOR SWITCH OFF COM To acti vate the communications override feature pushbutton is pushed in Communica tions override is eliminated by pushing button completely in and releasing button out 6 TUNING SELECTOR CONTROL KNOB TUNING Rotate to tune in desiredAM or FM operating frequencies 7 RADIO PLAYER AND COM SPEAKER BALANCE CONTROL KNOB B...

Page 218: ...S Regulates volume of audio to individual earphones Volume increases as levers are moved to higher settings 13 HEADPHONE PLUG Inserts into one of the phone jacks located overhead and placarded STEREO or STEREO HEADPHONE Jacks are for 1 4 inch stereo plugs only CAUTION To prevent damage to the entertainment center use only 8 ohm headphones with 1 4 inch stereo type plugs Figure 1 AM FM Cassette Ste...

Page 219: ...warning horn may not be heard with the stereo headphones in use With headphones plugged in extended play at full volume should be avoided in order to prevent damage to head phones and hearing 5 AM FM Pushbutton Selector Switch SELECT as desired IN for FM OUT for AM 6 TUNING Knob SELECT desired frequency 7 MPX Stereo Annunciator Light CHECK ON green light will illuminate if FM radio station recepti...

Page 220: ...nd will illuminate bright amber when cassette has reached end of tape play and requires changing CAUTION To insure the best performance and operation of your cassette player follow these simple rules a Loose cassette tape should not be played If your tape is loose rewind it before playing b Do not keep cassette tape in your player long after cassette play is finished c Do not use non standard cass...

Page 221: ...e system and other aircraft radios selected If the audio level from the Nav Com Radio is too weak getting to the entertainment center the COM Interrupt circuit will not be activated If the audio level is too strong distortion will be produced in the audio signal 3 Com Interrupt Pushbutton Selector Switch on EC 100 PUSH button in halfway and release to activate COM Interrupt circuit 4 Aircraft s CO...

Page 222: ...ECTION 5 PERFORMANCE There is no change to the airplanes performance when this avionics equipment is installed However the installation ofan externally mounted antenna or several related external antennas will result in a minor reduction in cruise performance 8 1 October 1979 ...

Page 223: ...s will be covered over by a remote REM flag and the DME will utilize the frequency set by the NAV set s channeling knobs When the DME is not coupled with a remote NAV set the DME will reflect the channel selected on the DME unit The transmitter operates in the frequency range of 1041 to 1150 MHz and is paired with 108 to 117 95 MHz to provide automatic DME channeling The receiver operates in the f...

Page 224: ...tance MILES in R Nav mode 3 REMOTE CHANNELING SELECTOR Two position selector In the first posi tion the DME will utilize the frequency set by the DME channeling knobs In the second position the MHz digits will utilize the frequency set by the NAV 1 unit s channeling knobs 4 WHOLE MEGAHERTZ SELECTOR KNOB Selects operating frequency in 1 MHz steps between 108 and 117 MHz 5 FREQUENCY INDICATOR Shows ...

Page 225: ... or KNOTS position The decimal point along with 188 8 will light in the MILES mode When the control is released and had the DME been channeled to a nearby station the distance to that station will appear If the station channeled was not in range a bar readout will be seen or 10 MODE SELECTOR SWITCH OFF Turns the DME OFF MILES Allows a digital readout to appear in the window which represents slant ...

Page 226: ...T 5 DME SPEAKER PHONE Selector Switch on audio control panel SELECT as desired 6 IDENT CONTROL ADJUST audio output in speaker or headset 7 Mode Selector Functions MILES Position Distance to Station is slant range in nauti cal miles MIN Position Time to Station when flying directly to sta tion KNOTS Position Ground Speed in knots when flying directly to or from station CAUTION After the DME 190 has...

Page 227: ... 10 000 feet The ELT supplied in domestic aircraft transmits on both distress frequen cies simultaneously at 75 mw rated power output for 50 continuous hours in the temperature range of 4 F to 131 F 20 C to 55 C The ELT unit in export aircraft transmits on 121 5 MHz at 25 mw rated power output for 50 continuous hours in the temperature range of 4 F to 131 F 20 C to 55 C The ELT is readily identifi...

Page 228: ...OVER Removable for access to battery pack 3 ANTENNA RECEPTACLE Connects to antenna mounted on top of tailcone Figure 1 ELT Control Panel SECTION 3 EMERGENCY PROCEDURES Immediately after a forced landing where emergency assistance is required the ELT should be utilized as follows 1 ENSl RE ELT ACTIVATION Turn a radio transceiver ON and select 121 5 1Hz If the ELT can be heard transmitting it was ac...

Page 229: ... 4 NORMAL PROCEDURES As long as the function selector switch remains in the AUTO position the ELT automatically activates following an impact of 5g or more over a short period of time Following a lightning strike or an exceptionally hard landing the ELT may activate although no emergency exists To check your ELT for inadvertent activation select 121 5 MHz on your radio transceiver and listen for a...

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Page 231: ...ft to the waypoint repeatedly to provide continual informa tion on WHICH WAY and HOW FAR to the waypoint The pilot can monitor BEARING and RANGE on RNAV 511 to fly straight line paths to waypoints up to 200 NM distance from the aircraft position Waypoints can be preCisely dialed into the thumbwheels to 0 10 and 0 1 NM resolution The RNAV 511 also provides immediate position orientation relative to...

Page 232: ...vidual placards 1 Adjacent to panel unit when used with the DME 190 RNAV FOR VFR FLIGHT ONLY TUNE DME NAV 1 TO SAME VORTAC FOR RNAV OPERATION 2 Adjacent to panel unit when used with the 400 DME RNAV FOR VFR FLIGHT ONLY DME MODE SELECTOR ON NAV 1 OR NAV 2 ONLY SECTION 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when this avionic equipment is installed 2 1 October ...

Page 233: ...t is turned ON When pressed again set will be turned OFF and the RNAV ON light will go out The pushbutton lighting is automatically dimmed by the photocell 4 4 PHOTOCELL Senses ambient cockpit light and controls brightness ofpushbut tons 1 3 5 7 and digital displays 2 6 5 OR D v J E PUSHBUTTON Provides PRESENT POSITION information as to OR RADIAL and DME DISTANCE digitally in positions 2 and 6 res...

Page 234: ...VORTAC is 199 9 NM 9 TEST PUSHBUTTON Press to check proper calibration of RNAV 511 If the computer is properly calibrated the displays 2 6 read the active WPT RADIAL and DISTANCE as dialed into the thumbwheels Test may be performed anytime during or before flight 10 LOCKING SCREW Secures RNAV 511 in dustcover Turn locking screw counterclockwise several turns to release unit from panel 11 RADIAL AN...

Page 235: ...e and may become unusable within 1 1 1 2 miles of the waypoint Thus the RANGE readout is the primary means of approximating waypoint passage 4 Tracking from a waypoint is not recommended since the pilot would have to fly a reciprocal bearing and make error corrections in the opposite direction from flying to a waypoint DIAGNOSTIC FUNCTIONS All RNAV systems are rendered inoperative under certain co...

Page 236: ...t s from appropriate VOR DME stations 2 VHF Navigation Receiver ON When installed with DME 190 RNAV 511 is connected to the Nav 1 Rcvr When installed with the 400 DME RNAV 511 may be connected to either the Nav 1 or Nav 2 Rcvr and channeled to the desired VORTAC 3 DME ON OFF Switch ON 4 DME Remote Channeling Selector on DME 190 Selector SET to REM position on DME 190 5 DME Mode Selector on 400 DME...

Page 237: ... computer 14 VOR DME Pushbutton PRESS at anytime to observe the radial and DME distance from the VORTAC associated with the way point 15 Upon Waypoint Passage CHECK or SELECT next desired waypoint s VORTAC frequency on the selected Nav receiver and then PRESS next WPT Pushbutton in and repeat steps 9 through 12 to proceed to next waypoint which was dialed in the right set of thumbwheels NOTE Waypo...

Page 238: ...nitial right hand waypoint is passed This procedure can be followed for as many waypoints as necessary providing that the desired Nav receiver is selected and the VORTAC frequency has been re channeled to each VORTAC station SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed 8 1 October 1979 ...

Page 239: ...el Selector Knob determines the operating frequency of the transmitter and receiver The frequencies of operation are shown on the frequency chart adjacent to the channel selector The VOLUME control incorporates the power switch for the trans ceiver Clockwise rotation of the volume control turns the set on and increases the volume of audio The meter on the face of the transceiver indicates transmit...

Page 240: ... listed in the frequency chart 3 CHANNEL READOUT WINDOW Displays channel selected in frequency chart 4 SENSITIVITY CONTROL Controls the receiver sensitivity for audio gain 5 ANTENNA TUNING METER Indicates the energy flowing from the transmit ter into the antenna The optimum power transfer is indicated by the maximum meter reading 6 ON OFF VOLUME CONTROL Turns complete set on and controls volume of...

Page 241: ...to comfortable listening level 4 Frequency Chart SELECT desired operating frequency 5 Channel Selector DIAL in frequency selected in step 4 6 SENSITIVITY Control ROTATE clockwise to maximum posi tion NOTE If receiver becomes overloaded by very strong signals back off SENSITIVITY control until background noise is barely audible NOTE The antenna tuning meter indicates the energy flowing from the air...

Page 242: ...TION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externallymounted antenna or several related external antennas will result in a minor reduction in cruise performance 4 1 October 1979 ...

Page 243: ...termines the operating frequency of the transceiver which has predetermined crystals installed to provide the desired operating frequencies A mode selector control is provided to supply the type of emission required for the channel either sideband AM or telephone for public correspondence An audio knob clarifier knob and squelch knob are provided to assist in audio operation during receive In addi...

Page 244: ...res pondence telephone and ship to shore LSB Optional Selects lower sideband operation not legal in U S Canada and most other countries 4 SQUELCH COXTROL Used to adjust signal threshold necessary to activate receiver audio Clockwise rotation increases background noise decreases squelch action counterclockwise rotation decreases background noise 5 CL RIFIER CONTROL Used to clarify single sideband s...

Page 245: ... may be used Use of lower sideband is prohibited b Only AM transmissions are permitted on frequen cies 2003 kHz 2182 kHz and 2638 kHz The selection of these channels will automatically select the AM mode of transmission 1 XMTR SEL Switch on audio control panel SELECT transceiv er 2 SPEAKER PHONE Selector Switches on audio control panel SELECT desired mode 3 ON AUDIO Control ON allow equipment to w...

Page 246: ... on this radio b To Receive RELEASE mike button NOTE Voice co unications are not available in the LSB mode NOTE Lower sideband LSB mode is not legal in the U S Canada and most other countries SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or several related external antennas wil...

Page 247: ...radios When dual Nav Cornradios are installed the HSI is coupled to the number 1 NAV COM and a standard 300 or 400 series VOR LOC course deviation indicator is coupled to the number 2 NAV COM This system consists of a Horizontal Situation Indicator HSI Type IG 832C and a remote mounted VOR LOC Converter Type B 445A The indicator is unslaved and course datum is not available When the HSI is install...

Page 248: ...ms It also displays glide slope deviations and gives heading reference with respect to magnetic north when compass card is set to agree with compass 2 0 1 1 BE_ RI G POINTER Indicates selected VOR course or localizer course on COIr p ss card 6 The selected VOR radial or localizer heading remains set on the compass card when the compass card 6 is rotated 3 NAY FLAG When flag is in view indicates th...

Page 249: ...6 to agree with magnetic compass The omni bearing pOinter 2 heading bug 14 and deviation bar 15 rotate with the compass card 6 NOTE The compass card 6 must be reset periodically to compensate for precess c a errors In the gyro 10 CO C RSE SELECTOR J KXOB When rotated positions omni bearing pointer 2 on the compass card 6 to select desired VOR radial or localizer course 11 GLIDE SLOPE SCALE Indicat...

Page 250: ...ocalizer signal to the autopilot to reverse for back course operation 17 BACK COURSE REVERSE SENSE REV SNS LOC 1 OR LOC 2 SELECTOR SWITCH With AP switch ON on 400A or 400B Autopilot control units and either LOC 1 or LOC 2 selected localizer signals to the Cessna 400A or 400B Autopilots will reverse for back course operation With autopilot ON or OFF the course omni deviation bar on the HSI will not...

Page 251: ...both front and back course approaches to retain this pictorial presentation When the HSI system is installed with a Cessna 300A Type AF 395A or Cessna 400B Type IF 550A Autopilot a back course indicator light labeled BC is mounted adjacent to the HSI and will illuminate amber when the reverse sense REV S S switch mounted in the autopilot s accessory unit on 210 Models is placed in the ON LOC 1 pos...

Page 252: ......

Page 253: ...coordina tor gyro The computer amplifier electronically computes the necessary correction and Signals the actuator to move the ailerons to maintain the airplane in the commanded lateral attitude The 200A Navomatic will also capture and track a VOR or localizer course using signals from a VHF navigation receiver The operating controls for the Cessna 200A Navomatic are located on the front panel of ...

Page 254: ...5B NAV 1 NAV2 COl INDICATORS TURN COORDINATOR PILOT S OPERATING HANDBOOK SUPPLEMENT Jk01J PILOT L __ _ J I AILERON I I I I COMPUTER AMPLIFIER Figure 1 Cessna 200A Autopilot Operating Controls and Indicators Sheet 1 of 2 2 1 October 1979 ...

Page 255: ...ivity position push button out response to A signal is dampened for smoothertracking ofenroute VOR radials It also smooths out effect of course scalloping during NAV opera tion 8 BACK CRS PUSHBUTTON Used with LOC operation only With AlP switch OFF or ON and when navigation receiver selected by NAV switch is set to a localizer frequency it reverses normal localizer needle indication CDI and causes ...

Page 256: ...Airplane Control Wheel ROTATE as required to override autopi lot NOTE The servo may be overpowered at anytime without dam age TO TURN OFF AUTOPILOT 1 AlP ON OFF Switch OFF SECTION 4 NORMAL PROCEDURES BEFORE TAKE OFF AND LANDING 4 1 AI P O J OFF Switch OFF 2 BACK CRS Button OFF see Caution note under Nav Capture NOTE Periodically verify operation of amber warning light s labeled BC on CDI s by enga...

Page 257: ... U206 and TU206 Series Models COMMAND TURNS 1 PULL TURN Knob CENTER PULL out and ROTATE DIRECTION HOLD 1 PULL TURN Knob CENTER and PULL out 2 Autopilot TRIM Control ADJUST for zero turn rate 3 Airplane Rudder Trim ADJUST for zero slip Ball centered 4 DIR HOLD Button PUSH 5 PULL TURN Knob PUSH in detent position when airplane is on desired heading 6 Autopilot TRIM Control READJUST for zero turn rat...

Page 258: ...ation or more than 3 minutes from intercept use a manual intercept procedure NAV TRACKING VOR LOC 1 NAV TRK Button PUSH when CDI centers and airplane is within 50 of course heading 2 HI SENS BUTTON DISENGAGE for enroute omni tracking leave ENGAGED for localizer 3 Autopilot TRIM Control READJUST as required to maintain track NOTE Optional ARC function if installed should not be used for autopilot o...

Page 259: ...Cessna 300 ADF can be used for position plotting and homing procedures and for aural reception of amplitude modulated AM signals With the function selector knob at ADF the Cessna 300 ADF provides a visual indication on the bearing indicator of the bearing to the transmit ting station relative to the nose of the airplane This is done by combining signals from the sense antenna with signals from the...

Page 260: ...E Gtatlon from OFF position applies primary power to receiver further clocil vnse rotation increases audio leveL 2_ FREQCE CY SELECTORS Knob A selects 100 kHz increments of receiver frequency knob B selects lO kHz increments and knob C selects 1 kHz increments Figure 1 Cessna 300 ADF Operating Controls and Indicators Sheet 1 of 2 2 1 October 1979 ...

Page 261: ... sense anten nas TEST Momentary on position used during ADF operation to test bearing reliability When held in TEST position slews indicator pointer clockwise when released if bearing is reliable pOinter returns to original bearing position 4 INDEX ROTATABLE CARD Indicates relative magnetic or true heading of aircraft as selected by HDG control 5 POINTER Indicates station bearing in degrees of azi...

Page 262: ...ncy Selector Knobs SELECT operating frequency 3 ADF SPEAKER PHONE Selector Switch on audio control panel SELECT AS DESIRED 4 Function Selector Knob ADF position and note relative bearing on indicator TO TEST RELIABILITY OF AUTOMATIC DIRECTION FINDER 1 Function Selector Knob ADF position and note relative bearing on indicator 2 Function Selector Knob TEST position and observe that pointer moves awa...

Page 263: ... in the audio output when a CW signal Morse Code is tuned in properly SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externallymounted antenna or related external antennas will result in a minor reduction in cruise performance 1 October 1979 5 6 blank ...

Page 264: ......

Page 265: ...ting frequencies are digitally displayed by incandescent readouts on the front panel of the Nav Com A DME receiver transmitter or a glide slope receiver or both may be interconnected with the Nav Com set for automatic selection of the associated DME or glide slope frequency When a VOR frequency is selected on the Nav Com associated VORTAC or VOR DME station frequency will also be selected automati...

Page 266: ...elector In 5 position enables Corn frequency readout to display and Corn Fractional MHz Selector to select frequency in 05 MHz steps between 025 and 975 I 1Hz In 0 position enables COM frequency readout to display and Corn Fractlonal MHz Selector to select frequency in 05 MHz steps between 000 and 950 l 1Hz NOTE The 5 or 0 may be read as the third decimal digit which is not dIsplayed in the Corn f...

Page 267: ...eceiver audio Clockwise rotation increases background noise decreases squelch action counterclockwise rotation decreases background noise 10 COMMC ICATIO RECEI ER TRA S 1ITTER MEGAHERTZ SELECTOR Selects COM f requency In 1 I 1Hz steps between 118 and 135 MHz 11 COM OFF VOL CONTROL Combination on off switch and volume control turns on NAV COM set and controls volume of communications receiver audio...

Page 268: ...ed to inner Momentary On position turns OBS course card to center course deviation pOinter with a TO flag then returns to conventional OBS selection Pulled to outer detent continuously drives OBS course card to indicate bearing from VOR station keeping course deviation pointer centered with a FROM flag ARC function will not operate on localizer frequencies 21 AUTOMATIC RADIAL CENTERING ARC LAMP Am...

Page 269: ...old This adjustment should be rechecked periodically during each flight to assure optimum reception All controls for the Nav Com except the standard omni bearing selector OBS knob or the optional automatic radial centering ARC knob located on the course deviation indicator are mounted on the front panel of the receiver transmitter Operation and description of the audio control panels used in conju...

Page 270: ... selected by placing the AUTO selector switch on audio control panel in either the SPEAKER or PHONE position Sidetone may be eliminated by placing the AUTO selector switch in the OFF position Adjustment of sidetone on audio control panels supplied with three transmitters cannot be accomplished externally How ever audio control panels supplied with two or less transmitters have sidetone adjustment ...

Page 271: ...As Conventional OBS PLACE in center detent and select desired course b To Obtain Bearing TO VOR Station PUSH ARC PUSH TO knob to inner momentary on position NOTE ARC lamp will illuminate amber while the course card is moving to center with the course deviation pOinter After alignment has been achieved to reflect bearing to VOR automatic radial centering will automatically shut down _causing the AR...

Page 272: ...NAV ITO FROM indicator shows FROM 5 OBS Knob TURN to displace course approximately 10 to either side of 0 while holding IDIVOXIT to T Course deviation pointer deflects full scale in direction corresponding to course displace ment NAVI TO FROM indicator shows FROM 6 ID VOX T Switch RELEASE for normal operation NOTE This test does not fulfill the requirements of FAR 91 25 SECTION 5 PERFORMANCE There...

Page 273: ... Operatinginforma tion for the communication set and for VOR localizer navigation is presented in this supplement Operating information for area navigation and for DME is presented in separate supplements The RT 385A Receiver Transmitter includes a 720 channel VHF com munication receiver transmitter which receives and transmits signals between 118 000 MHz and 135 975 MHz in 25 kHz steps It also in...

Page 274: ... are included on the front panel of the RT 385A Receiver Transmitter and the associated Course Deviation Indicator These controls and indicators are shown and described in Figure 1 Operating controls for the RN 478A Area Navigation Computer which are used for area navigation and operating controls for the associated Type R 476A DME are shown in the appropriate supplements in this manual Operating ...

Page 275: ...or In 5 position enables COM frequency readout to display and COM Fractional MHz Selector to select frequency in 05 MHz steps between 025 and 975 fHz In 0 position enables COM frequency readout to display and COM Fractional MHz Selector to selectfrequency in 05 MHz steps between 000 and 950 fHz NOTE The 5 or 0 may be read as the third decimal digit which is not displayed in the Corn fractional fre...

Page 276: ...receiver audio Clockwise rotation increases background noise decreases squelch action counterclockwise rotation decreases background noise 10 COMMUNICATION RECEIVER TRANSMITTER MHz FREQUENCY SELECTOR Selects COM frequency in 1 MHz steps between 118 and 135 MHz 11 COM OFF VOL CONTROL Combination on off switch and volume control turns on NAV COM Set and RNAV Computer circuits controls volume of comm...

Page 277: ...enterline 18 OFFI TO FROM INDICATOR Operates only with VOR or localizer signal OFF position flag indicates unusable signal With usable VOR signal when OFF position disappears indicates whether selected course is TO or FROM station or waypoint With usable localizer signal shows TO 19 RECIPROCAL COURSE INDEX Indicates reciprocal of selected VOR or RNAV course Figure 1 Cessna 300 Nav Com Set Operatin...

Page 278: ...UTO selector switch on audio control panel in either the SPEAKER or PHONE position or may be eliminated by placing the AUTO selector switch in the OFF position Adjustment of sidetone on audio control panels supplied with three transmitters cannot be accomplished externally How ever audio control panels supplied with one or two trans mitters have sidetone adjustment pots that are accessible through...

Page 279: ...le VOR station signal 3 OBS Knob SET for 0 course at index CDI pointer centers or deflects left or right depending on bearing of signal OFF TO FROM indicator shows TO or FROM 4 ID VOX T Switch PRESS to T and HOLD at T CDI pOinter should center and OFF TO FROM indicator should show FROM 5 OBS Knob TURN to displace course approximately 10 to either side of 0 while holding ID VOX T switch at T CDI po...

Page 280: ......

Page 281: ...tion and also to Mode C altitude reporting when coupled to an optional altitude encoder system The transponder is capable of replying on both modes of interrogation on a selective reply basis on any of 4096 informa tion code selections The optional altitude encoder system not part of a standard 300Transponder system requiredfor Mode C altitude reporting operation consists of a completely independe...

Page 282: ...BY Turns set on for equipment warm up or standby power ON Turns set on and enables transponder to transmit Mode A aircraft identification reply pulses ALT Turns set on and enables transponder to transmit eitherMode A aircraft identification reply pulses or Mode C altitude reporting pulses selected automatically by the interrogating signal Figure 1 Cessna 300 Transponder and Altitude Encoder Blind ...

Page 283: ...ing duration of IDENT pulse transmission 4 DIMMER DIM CONTROL Allows pilot to control brilliance of reply lamp 5 SELF TEST TST SWITCH When depressed causes transponder to generate a self interrogating signal to provide a check of transponder operation Reply lamp will glow steadily to verify self test operation 6 REPLY CODE SELECTOR KNOBS 4 Select assigned Mode A reply code 7 REPLY CODE INDICATORS ...

Page 284: ...RGENCY SIGNAL 1 Function Switch ON 2 Reply Code Selector Knobs SELECT 7700 operating code TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN IN A CONTROLLED ENVIRONMENT 1 Function Switch ON 2 Reply Code Selector Knobs SELECT 7700 operating code for 1 minute then SELECT 7600 operating code for 15 minutes and then REPEAT this procedure at same intervals for remainder of flight SECTION...

Page 285: ...unction Switch ALT NOTE When directed by ground controller to stop altitude squawk turn Function Switch to ON for Mode A opera tion only NOTE Pressure altitude is transmitted by the transponder for altitude squawk and conversion to indicated altitude is done in ATC computers Altitude squawked will only agree with indicated altitude when the local altimeter setting in use by the ground controller i...

Page 286: ...PLEMENT SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or several related external antennas will result in a minor reduction in cruise performance 6 1 October 1979 ...

Page 287: ...ulse train reply signals on 1090MHz It is capable of replying to Mode A aircraft identification and also to Mode C altitude reporting interrogations on a selective reply basis on any of 4096 information code selections When an optional panel mounted EA 401A Encoding Altimeter not part of a standard 300 Transponder system is included in the avionic configuration the transponder can provide altitude...

Page 288: ...off SBY Turns set on for equipment warm up or stand by power ON Turns set on and enables transponder to transmit Mode A aircraft identification reply pulses ALT Turns set on and enables transponder to transmit eitherMode A aircraft identification reply pulses or Mode C altitude reporting pulses selected automatically by the interrogating signal Figure 1 Cessna 300 Transponder and Encoding Altimete...

Page 289: ...d Mode A reply code 8 1000 FOOT DRUM TYPE INDICATOR Provides digital altitude readout in 1000 foot increments between 1000 feet and 35 000 feet When altitude is below 10 000 feet a diagonally striped flag appears in the 10 000 foot window 9 OFF INDICATOR WARNING FLAG Flag appears across altitude readout when power is removed from the altimeter to indicate that readout is not reliable 10 lOO FOOT D...

Page 290: ...TRANSMIT AN EMERGENCY SIGNAL 1 Function Switch ON 2 Reply Code Selector Knobs SELECT 7700 operating code TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN INA CONTl tOLLED ENVIRONMENT 1 Function Switch ON 2 Reply Code Selector Knobs SELECT 7700 operating code for 1 minute then SELECT 7600 operating code for 15 minutes and then REPEAT this procedure at same intervals for remainder o...

Page 291: ...ng altimeter 2 Altitude Encoder Altimeter Setting Knob SET IN assigned local altimeter setting 3 Reply Code Selector Knobs SELECT assigned code 4 FunctionSwitch ALT NOTE When directed by ground controller to stop altitude squawk turn Function Switch to ON for Mode A opera tion only NOTE Pressure altitude is transmitted by the transponder for altitude squawk and conversion to indicated altitude is ...

Page 292: ...iance regardless of DIM control setting 4 TST Button RELEASE for normal operation SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or several related external antennas will result in a minor reduction in cruise performance 6 1 October 1979 ...

Page 293: ...d heading are sensedbythe direction al gyro The computer amplifier electronically computes the necessary correction and signals the actuator to move the ailerons to maintain the airplane in the commanded lateral attitude or heading The 300A Navomatic will also intercept and track a VOR or localizer course using signals from a VHF navigation receiver The operating controls for the Cessna 300A Navom...

Page 294: ...LOT TYPE AF 395A NAV 1 NAV 2 TURN COORDINATOR PILOT S OPERATING HANDBOOK SUPPLEMENT PILOT _ AILERON I I I I I COMPUTER AMPLIFIER Figure 1 Cessna 30DA Autopilot Operating Controls and Indicators Sheet 1 of 2 2 1 October 1979 ...

Page 295: ...NAV signal to provide more precise operation during localizer approach In low sensitivity position push button out response to NAV signal is dampened for Sinoothertrackingofenroute VOR radials it also smooths out effect of course scalloping during NAV opera tion 9 BACK CRS PUSHBUTTON Used with LOC operation only With A P switch OFF or ON and when navigation receiver selected by NAV switch is set t...

Page 296: ...Airplane Control Wheel ROTATE as required to override autopi lot NOTE The servo may be overpowered at any time without dam age TO TURN OFF AUTOPILOT 1 AlP ON OFF Switch OFF SECTION 4 NORMAL PROCEDURES BEFORE TAKE OFF AND LANDING 4 1 A P O OFF Switch OFF 2 BACK CRS Button OFF see Caution note under Nav Intercept NOTE Periodically verify operation of amber warning light s labeled BC on CDI s by enga...

Page 297: ...180 185 U206 and TU206 Series Models COMMAND TURNS 1 PULL TURN Knob CENTER PULL out and ROTATE HEADING SELECT 1 Directional Gyro SET to airplane magnetic heading 2 Heading Selector Knob ROTATE bug to desired heading 3 Heading Select Button PUSH 4 PULL TURN Knob CENTER and PUSH NOTE Airplane will turn automatically to selected heading If airplane fails to hold the precise heading readjust autopi lo...

Page 298: ...TE Airplane will automatically turn to a 45 intercept angle NAV TRACKING VOR LOC 1 NAV TRK Button PUSH when CDI centers within one dot and airplane is within 10 of course heading 2 HI SENS Button Disengage for enroute omni tracking leave engaged for localizer NOTE Optional ARC feature if installed should not be used for autopilot operation If airplane should deviate off course pull out PULL TURN k...

Page 299: ...s the operator to non ADF operation by slewing the pointer to the 3 00 o clock position when the REC mode is selected Operating controls and displays for the Cessna 400 ADF are shown and described in Figure 1 The audio control panels used in conjunction with this radio for speaker phone selection are shown and described in Section 7 of this handbook The frequency range of the Cessna 400 ADF is ele...

Page 300: ...22 CESSNA 400 ADF TYPE R 446A 10 9 8 11 12 13 2 7 PILOT S OPERATING HANDBOOK SUPPLEMENT 3 6 5 4 Figure 1 Cessna 400 ADF Operating Controls and Indicator Sheet 1 of 2 2 1 October 1979 ...

Page 301: ...als Morse Code to be heard 7 REC Pushed in Selects receive mode set operates as a standard communica tions receiver using sense antenna only NOTE In this position an automatic pointerstow feature will alert the pilot to non ADF operation by positioning and retaining the pOinter at the 3 00 o clock position when the 400 ADF is in the REC function 8 ADF Pushed in Selects ADF mode set operates as aut...

Page 302: ... PUSH in NOTE ADF indicator pOinter will stow at a 90 degree position to alert the pilot to non ADF operation 3 PRI Frequency Selectors SELECT desired operating frequency 4 SEC Frequency Selectors SELECT desired operatingfrequency 5 1 2 Selector Switch 1 pOSition NOTE 1 2 selector switch can be placed in the 2 position for operation on secondary frequency The re select lamp will flash only when fr...

Page 303: ...ative magnetic or true bearing to station 8 VOL Control ADJUST to desired listening level NOTE When switching stations place function pushbutton in the REC position Then after station has been selected place function pushbutton in the ADF position to resume auto matic direction finder operation This practice prevents the bearing indicator from swinging back and forth as frequency dial is rotated T...

Page 304: ...stening level NOTE A 1000 Hztone is heard inthe audio outputwhen CW signal Morse Code is tuned in properly SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or several related external antennas will result in a minor reduction in cruise performance 6 1 October 1979 ...

Page 305: ...e waypoint information which enhances autopilot operation The 400 RNAV is coupled to the number 2 Nav Com and includes storage for 3 waypoints Ground speed time to stationinformation to the selected VOR not the waypoint is available on this system This capability along with the course scalloping suppression radial straightening may be used to an advantage while tracking inbound or outbound from th...

Page 306: ...ISTANCE DISPLAY READOUT Depending on position of DSPL Switch displays distance programmed for waypoint 1 or waypoint 2 6 BEARING MINILEVER SWITCHES 4 Select bearing of desired waypoint from VOR DME station May be used to store bearing of 3rd waypoint 7 ENROUTE APPROACH SWITCH ENR APPR Controls width of navigation corridor ENR position provides standard 5 NM enroute sensitivity APPR posltlOn provid...

Page 307: ... VOR LOC OPERATION VOR NAVIGATION CIRCUITS VERIFICATION TESTS 1 See appropriate Nav Com supplement VOR LOC NAVIGATION As a convenience to the pilot a separate supplement Avionic Opera tion Guide is supplied to explain the various procedures for using the VHF Navigation Set for VOR and localizer navigation Refer to the Avionic Operations Guide for flight procedures AREA NAVIGATION OPERATION NOTE Pr...

Page 308: ...ose being used for navigation This does not affect operation of the unit 6 BEARING Minilever Switches SET to first waypoint bearing 7 DISTANCE Minilever Switches SET to first waypoint distance 8 XFER Pushbutton Switch PUSH in a First waypoint bearing and distance are placed in memory as waypoint 1 b BEARING Display Readout DISPLAYS readout of first waypoint bearing c DISTANCE Display Readout DISPL...

Page 309: ...ead FLASHES 3 RNAV DSPL and FLY Switches DSPL set to 2 FLY set to 1 a Readout DISPLAYS second waypoint bearing and distance b Fly Display Lamp On RNAV Control Head FLASHES 4 RNAV DSPL and FLY Switches BOTH SET to same number a Readout DISPLAYS waypoint bearing and distance as selected by DSPL switch b Fly Display Lamp On RNAV Control Head NOT LIGHTED 5 DME Mode Selector Switch SET to RNAV a Both R...

Page 310: ...tested a BEARING Display READOUT is waypoint bearing b DISTANCE Display READOUT is waypoint distance c Course Indicator RN LAMP lights 7 Course Indicator OBS or ARC SET to waypoint bearing S VHF Navigation Receiver ID VOX T Switch HOLD in T posi tion a Course Deviation Pointer CENTERS b Course Deviation Indicator OFF or NAV TO FROM Flag Shows TO c DME Distance Display READOUT is the same as the RN...

Page 311: ...tains all of the operating controls and displays and a remotely mounted RTA 476A Receiver Transmitter The RTA 476A transmits interrogating pulse pairs on 200 channels between 1041 MHz and 1150 MHz it receives associated ground to air replies between 978 MHz and 1213 MHz The C 476A Control Unit digitally displays distances up to 200 nautical miles and either ground speed or time to station informat...

Page 312: ...peed 3 DME MODE SELECTOR SWITCH Selects DME operating mode as follows RNAV Selects area navigation operation selects display of nautical miles distance to selected RNAV waypoint NAV 1 Selects DME operation with No 1 VHF navigation set enables channel selection by NAV 1 frequency selector switches HOLD Selects DME memory circuit DME remains channeled to station to which it was channeledwhen HOLD wa...

Page 313: ...llows a With GS TTS Switch set to GS displays ground speed component to or from station in knots aircraft must be flying directly to or from the VOR DME station for true ground speed indication b With GS TTS Switch set to TTS displays time to VOR DME station in minutes at the ground speed component indicated c With GS TTS in RNAV mode will display ground speed component or time to station at that ...

Page 314: ...dependent operation ofthe DME for reception of the DME Morse Code identifier 4 DME SPEAKER PHONE Selector Switch on audio control panel SET to desired mode 5 GS TTS Switch SET as desired 6 TEST ON OFF Switch HOLD to TEST a Distance to Station Display readout is 188 8 b Knots Minutes Display readout is 888 7 TEST ON OFF Switch RELEASE to ON display readouts return to normal SECTION 5 PERFORMANCE Th...

Page 315: ... slope receiver is designed to receive ILS glide slope signals on any of 40 channels The channels are spaced 150 kHz apart and cover a frequency range of 329 15 MHz through 335 0 MHz When a localizer frequency is selected onth NAV receiver the associated glide slope frequency is selected automatically Operation of the Cessna 400 Glide Slope system is controlled by the associated navigation system ...

Page 316: ...ment The flag disappears when a reliable glide slope signal is being received CAUTION Spurious glide slope signals may exist in the area of the localizer back course approach which can cause the glide slope OFF or GS flag to disappear and present unreliable glide slope informa tion Disregard all glide slope signal indications when making a localizer back course approach unless a glide slope ILS BC...

Page 317: ...100 RPM on airplanes equipped with a three bladed propeller during ILS approaches to avoid oscillations of the glide slope deviation pointer caused by propeller interference 1 NAV Frequency Select Knobs SELECT desired localizer fre quency glide slope frequency is automatically selected 2 NAV COM VOX ID T Switch SELECT ID position to disconnect filter from audio circuit 3 NAV VOL Control ADJUST to ...

Page 318: ......

Page 319: ...e switch is labeled HIGH LO MUTE and provides the pilot with HIGH LO sensitivity selection and marker beacon audio muting for approximately 30 seconds to enable voice co riununica tion to be heard withoutinterference ofmarker beacon signals The marker beacon audible tone is automatically restored at the end of the 30 second muting period to continue marker audio for passage over the next marker An...

Page 320: ...ith two or less transmitters a marker Beacon audio level adjustment potentiometer and an annunciator lights minimum dimming potentiometer are mounted on the audio control panel circuit board Potentiometer adjustments cannot be accomplished exter nally However if readjustments are desired adjustments canbe made in accordanc e with instructions found in the Avionics Installations Ser vice Parts Manu...

Page 321: ... night flying operations Light intenSity ofthe NITE position is controlled by the RADIO LT dimming rheostat DAY POSITION Places the annunciator lights in the full bright position for daylight flying operations TEST POSITION Illuminates all marker beacon annunciator lights and other annunciators in the full bright position to verify operation of annuncia tor lights 4 HIGH LO MUTE SELECTOR SWITCH HI...

Page 322: ... indicate passage of inner or fan marker beacon 3 SPEAKER PHONE SELECTOR SWITCH SPEAKER POSITION Selects speaker for aural reception PHONE POSITION Selects headphone for aural reception 4 HI LO TEST SELECTOR SWITCH HI POSITION Receiver sensitivity is positioned for airway flying LO POSITION Receiver sensitivity is positioned for ILS approaches TEST POSITION Illuminates all annunciator lights in th...

Page 323: ...PHN Selector Switch SELECT desired speaker or phone audio Either selected position will turn set on 2 NITE DAY TEST Selector Switch PRESS to TEST position and verify that all marker beacon annunciator lights illuminate full bright to indicate lights are operational 3 NITE DAY TEST Selector Switch SELECT desired position for NITE or DAY lighting 4 HIGH LO MUTE Selector Switch SELECT HI position for...

Page 324: ...eases audio level 2 HI LO Sen Switch SELECT HI position for airway flying or LO position for ILS approaches 3 SPKR PHN Switch SELECT speaker or phone audio 4 BRT Control SELECT BRT full clockwise ADJUST as desired when illuminated over marker beacon 5 TEST Switch PRESS to TEST position and verify that all marker beacon annunciator lights will illuminate full bright to indicate lights are operation...

Page 325: ...MEMORY A keep alive voltage prevents loss of the preset frequencies when the Nav Com is turned off Both the communications and navigation operating frequen cies are digitally displayed by incandescent readouts on the front panel of the Nav Com A DME receiver transmitter or a glide slope receiver or both may be interconnected with the Nav Com set for automatic selection of the associated DME or gli...

Page 326: ...al is above this level it is heard even if the noise is very close to the signal Below this level the squelch is fully automatic so when the background noise is very low very weak signals that are above the noise are let through For normal operation of the squelch circuit just turn the squelch clockwise until noise is heard then back off slightly until it is quiet and you willhave automatic squelc...

Page 327: ...11 10 9 8 7 6 14 15 14 15 23 23 22 16 16 17 18 19 19 21 20 24 20 TYPICAL 300 SERIES INDICATORS 15 16 15 16 22 23 23 22 17 25 25 18 26 14 14 26 20 20 21 21 TYPICAL 400 SERIES INDICATORS Figure 1 Cessna 400 Nav Com Type RT 485A Operating Controls and Indicators Sheet 1 of 4 1 October 1979 3 ...

Page 328: ...nction by holding C pushbuttonpressed for more than 1 7 seconds This lights each CaM and NAV MEMORY pushbutton in turn and displays the correspondmg preset frequency in MEMORY 4 NAVIGATION OPERATING FREQUENCY READOUT Indicates NAV fre quency in use 5 NAVMEMORY1 2 3PUSHBUTTONS WhenaNAVMEMORYpushbuttonis pressed the preset selected frequency will appear in the NAV frequency window for use as the sel...

Page 329: ...cy indicates course deviation pointer is reversed BC light dimming is only available when installed with an audio control panel incorporating the annunciator lights DAY NITE selector switch 15 COCRSE INDEX Indicates selected VOR COURSE 1 COCRSE DEVIATION POINTER Indicates course deviation from selected omni course or localizer centerline 17 GLIDE SLOPE GS FLAG When visible red GS flag indicates un...

Page 330: ... course card to select desired VOR radial 25 TO FROM INDICATOR TO FR Operates only with a usable VORorlocalizer signal When white flag is in view indicates whether selected course is TO or FROM station With usable localizer signal TO flag is in view 26 NAV INDICATOR FLAG When in view red NAV position Flag indicates the selected VOR or loealizer signal is unusable Figure 1 Cessna 400 Nav Com Type R...

Page 331: ...e selecting fractional frequencies or you will activate the MEMORY test function 4 MEMORY 2 and 3 Pushbuttons REPEAT STEPS 2 and 3 using next desired NAV or COM MEMORY to be stored Up to 3 NAV and 3 COM frequencies may be stored for automatic recall frequency selection NOTE The operating frequency set in the selected MEMORY position will automatically be changed in the MEMORY bank any time the ope...

Page 332: ...mi nated c To Receive RELEASE mike button NAVIGATION OPERATION NOTE The pilot should be aware that on many Cessna airplanes equipped with the windshielf mounted glide slope antenna pilots should avoid use of 2700 100RPM on airplanes equipped with a two bladed propeller or 1800 100 RPM on airplanes equipped with a three bladed propeller during ILS approaches to avoid oscillations of the glide slope...

Page 333: ...rn to center the course deviation pointer with a FROM flag to indicate bearing from VOR station This system will continually drive to present the VOR radial the aircraft is on until manually returned to the center detent by the pilot VOR SELF TEST OPERATION 1 COM OFF VOL Control TURN ON 2 NAV Frequency Selector Switches SELECT usable VOR station signal 3 OBS Knob SET for 0 course at course index c...

Page 334: ...ep alive circuit has not been interrupted the MEMORY test will always start with the last COM MEMORY selected and cycle through the remaining COM and NAV preset frequencies The MEMORY test will always stop on the last selected COM and NAV preset frequencies SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation ofan ex...

Page 335: ...OR localizer navigation is presented in this supplement Operating information for area navigation and for DME is presented in separate supplements Microprocessor frequency management provides storage for 3 preset NAV and 3 preset COM frequencies in MEMORY A keep alive voltage prevents loss ofthe preset frequencies when the NAV COM Switch Avionics Power Switch or aster Switch is turned OFF The RT 4...

Page 336: ...r and an optional IN 1048AC Course Deviation Indicator is also offered when Automatic Radial Centering ARC is desired When the optional IN 1048AC Course Deviation Indicator is installed an Automatic Radial Centering lamp ARC is incorporated in the CDI to alert the pilot that the Automatic Radial Centering feature has been selected All operating controls and indicators for the Cessna 400 Nav Com ar...

Page 337: ...ected pushbutton Three preset frequencies may be stored in MEMORY and selected as desired by merely pressing the appropriate COM MEMORY pushbutton to recall the desired operating frequency If electrical power to the set s keep alive CIrcuit has not been interrupted upon turn on the set will automatically recall the last COM MEMORY frequency selected by the MEMORY pushbutton If electrical power is ...

Page 338: ...perating frequency If electrical power to the set s keep alive circuit has not been interrupted upon turn on the set will automatically recall the last NAV MEMORY frequency selected by the MEMORY pushbutton If electrical power is removed from the set s keep alive circuit such as radio removal or battery replacement for more than 15 seconds upon turn on the NAV MEMORY circuits will have to be reset...

Page 339: ...BS Rotates course card 12 to select desired bearing to or from a VOR station or to a selected RNAV waypoint 18 COURSE INDEX Indicates selected VOR or RNAV course bearing 19 COURSE DEVIATION POINTER Indicates course deviation from selected VOR or RN AV course or localizer centerline 20 OFF TO FROM INDICATOR Operates only with VOR localizer or RNAV signal OFF position flag indicates unusable signal ...

Page 340: ...only with a usable VOR localizer or RNAV signal When white flag is in view indicates whether selected course is TO or FROM station With usable localizer signal TO flag is in view 25 AUTOMATIC RADIAL CENTERING ARC LAMP Amber light illuminates when Automatic Radial Centering is in use Light dimming is only available when installed with an audio control panel incorporating the annunciator lights DAY ...

Page 341: ...pushbut ton 1 momentarily to alert the memory bank of a forthcoming frequency to be stored 3 FREQUENCY SELECTORS MANUALLYROTATE correspond ing NAV or COM frequency selectors press C pushbutton as required to select the desired third fractional COM digit until the desired frequency is shown in the operating frequency readout window The frequency displayed will be automatically trans ferred into MEM...

Page 342: ...sition or may be eliminated by placing the AUTO selector switch in the OFF position Adjustment of sidetone on audio control panels supplied with three transmitters cannot be accomplished externally How ever audio control panels supplied with two or less transmitters have sidetone adjustment pots that are accessible through the front ofthe audio control panel with a small screwdriver b XMIT Annunci...

Page 343: ...moving to center the course deviation pOinter After alignment has been achieved to reflect bearing TO VOR automatic radial centering will automatically shut down causingthe ARC lamp to go out and the ARC knob to return to center detent position and function as a normal OBS c To obtain Continuous Bearing FROM VOR Station PULL ARC PULL FR knob to outer detent NOTE ARC lamp will illuminate amber OBS ...

Page 344: ... requirements of FAR 91 25 MEMORY TEST OPERATION 1 C Pushbutton PUSH for about 2 seconds Each COM and NAV MEMORY pushbutton 1 2 3 will illuminate white in turn with the corresponding preset frequency displayed NOTE If the keep alive circuit has not been interrupted the MEMORY test will always start with the last COM MEMORY selected and cycle through the remaining COM and NAV preset frequencies The...

Page 345: ...o Mode C altitude reporting when coupled to an optional altitude encoder system The transponder is capable of replying on both modes of interrogation on a selective reply basis on any of 4096 informa tion code selections The optional altitude encoder system not part of a standard 400 Transponder system required for Mode C altitude reporting operation consists of a completely independent remote mou...

Page 346: ...rns set on for equipment warm up or standby power 0 Turns set on and enables transponder to transmit Mode A aircraft identification reply pulses ALT Turns set on and enables transponder to transmit either Mode A aircraft identification reply pulses or Mode C altitude reporting pulses selected automatically by the interrogating signal Figure 1 Cessna 400 Transponder and Altitude Encoder Blind Sheet...

Page 347: ...g duration of IDENT pulse transmission 4 DIMMER DIM CONTROL Allows pilot to control brilliance of reply lamp 5 SELF TEST TEST SWITCH When depressed causes transponder to generate a self interrogating signal to provide a check of transponder operation Reply lamp will glow steadily to verify self test operation 6 REPLY CODE SELECTOR SWITCHES 4 Select assigned Mode A reply code 7 REPLY CODE INDICATOR...

Page 348: ... Function Switch ON 2 Reply Code Selector Switches SELECT 7700 operating code TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN IN A CONTROLLED ENVIRONMENT 1 Function Switch ON 2 Reply Code Selector Switches SELECT 7700 operating code for 1 minute then SELECT 7600 operating code for 15 minutes and then REPEAT this procedure at same intervals for remainder of flight SECTION 4 NORMAL...

Page 349: ...on Switch ALT NOTE When directed by ground controller to stop altitude squawk turn Function Switch to ON for Mode A opera tion only NOTE Pressure altitude is transmitted by the transponder for altitude squawk and conversion to indicated altitude is done in ATC computers Altitude squawked will only agree with indicated altitude when the local altimeter setting in use by the ground controller is set...

Page 350: ...PLEMENT SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or several related external antennas will result in a minor reduction in cruise performance 6 1 October 1979 ...

Page 351: ...s codedpulse train reply Signals on 1090 MHz It is capable of replying to Mode A aircraft identification and also to Mode C altitude reporting interrogations on a selective reply basis on any of 4096 information code selections When an optional panel mounted EA 401A Encoding Altimeter not part of 400 Transponder System is included in the avionic configuration the transponder can provide altitude r...

Page 352: ...s set on for equipment warm up or stand by power ON Turns set on and ena bles transponder to transmit Mode A aircraft identification reply pulses ALT Turns set on and enables transponder to transmit eitherMode A aircraft identification reply pulses or Mode C altitude reporting pulses selected automatically by the interrogating signal Figure 1 Cessna 400 Transponder and Encoding Altimeter Operating...

Page 353: ...A reply code 8 1000 FOOT DRUM TYPE INDICATOR Provides digital altitude readout in 1000 foot increments between 1000 feet and 35 000 feet When altitude is below 10 000 feet a diagonally striped flag appears in the 10 000 foot window 9 OFF INDICATOR WARNING FLAG Flag appears across altitude readout when power is removed from the altimeter to indicate that readout is not reliable 10 lOO FOOT DRUM TYP...

Page 354: ...MIT AN EMERGENCY SIGNAL 1 Function Switch ON 2 Reply Code Selector Switches SELECT 7700 operating code TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN IN A CONTROLLED ENVIRONMENT 1 Function Switch ON 2 Reply Code Selector Switches SELECT 7700 operating code for 1 minute then SELECT 7600 operating code for 15 minutes and then REPEAT this procedure at same intervals for remainder o...

Page 355: ...ding altimeter 2 Altitude Encoder Altimeter Setting Knob SET IN assigned local altimeter setting 3 Reply Code Selector Switches SELECT assigned code 4 Function Switch ALT NOTE When directed by ground controller to stop altitude squawk turn Function Switch to ON for Mode A opera tion only NOTE Pressure altitude is transmitted by the transponder for altitude squawk and conversion to indicated altitu...

Page 356: ...iance regardless of DIM control setting 4 TEST Button RELEASE for normal operation SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or several related external antennas will result in a minor reduction in cruise performance 6 1 October 1979 ...

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