Cessna 182Q 1979 Pilot Operating Handbook Download

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Summary of Contents for 182Q 1979

Page 1: ... BE CARRIED IN THE AIRPLANE AT ALL TIMES Serial No f z 7 70 Registration No IV 97 9 C G r THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY CAR PART 3 AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT MANUAL COPYRIGHT 1978 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA D1141 13PH RPC 2 000 8 78 1 OCTOBER 1978 ...

Page 2: ...AL WAS PROVIDED FOR THE AIRPLANE IDENTIFIED ON THE TITLE PAGE ON J J 77 SUBSEQUENT REVISIONS SUPPLIED BY CESSNA AIRCRAFT COMPANY MUST BE PROPERLY IN SERTED 4TLL tZ b vf7 L CESSNA AIRCRAFT COMPANY PAWNEE DIVISION ...

Page 3: ...ers 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 you...

Page 4: ...inutes reserve at 45 power 75 Power at 8000 Ft 88 Gallons Usable Fuel Maximum Range at 10 000 Ft 88 Gallons Usable Fuel RATE OF CLIMB AT SEA LEVEL SERVICE CEILING TAKEOFF PERFORMANCE Ground Roll Total Distance Over 50 Ft Obstacle 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...

Page 5: ...on the outer margin of the page All revised pages will carry the revision number and date on the applicable page The following Log of Effective Pages provides the dates of issue for original and revised pages and ii5ting of all pages in the handbook Pages affected by the current revision are indicated by an 3sterisk preceding the pages listed LOG OF EFFECTIVE PAGES Dates of issue for original and ...

Page 6: ...N GENERAL 1 L1MITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT BALANCE EQUIPMENT LIST 6 AIRPLANE SYSTEMS DESCRI PTIONS 7 AIRPLANE HANDLING SERVICE MAINTENANCE 8 SU PPLEMENTS Optional Systems Description Operating Procedures 9 1 October 1978 ...

Page 7: ...Weights Cabin And Entry Dimensions Baggage Space and Entry Dimensions Specific Loadings Symbols Abbreviations And Terminology General Airspeed Terminology And Symbols Meteorological Terminology Engine Power Terminology Airplane Performance And Flight Planning Terminology Weight And Balance Terminology 1 October 1978 1 2 1 3 1 3 1 3 1 3 1 3 1 4 1 4 1 5 1 5 1 5 1 5 1 5 1 5 1 6 1 7 1 7 1 7 1 1 ...

Page 8: ...ible and flashing beacon installed 1 Oi mensions shown are based on standard empty weight and proper nose gear and tire inflation NOTES 4 Wheel base length is 66 1 2 5 Propeller ground clearance is 10 718 6 Wing area is 174 square feet 7 Minimum turning radius pivot point to outboard wing tip is 27 0 PIVOT POINT l 36 0 I 1 9 0 _ J Figure 1 1 Three View 1 2 1 October 1978 ...

Page 9: ...aspirated direct drive air cooled horizontally opposed carburetor equipped six cylinder engine with 470 cu in displacement Horsepower Rating and Engine Speed 230 rated BHP at 2400 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 hydr...

Page 10: ...as 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 SAE 50 above 4 C 40 F SAE 10W30 or SAE 30 belo...

Page 11: ... 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 8 lbs hp SYMBOLS ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS K...

Page 12: ...ntrollable 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 ...

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 W...

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 1978 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: ...d then only with caution VA Maneuvering Speed 2950 Pounds 109 111 Do not make full 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: ...and 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 Maximum Engine Speed 2400 RPM Maximum Cylinder Head Temperature 460 F 238 C Maximum Oil Temperature 240 F 116 C Oil...

Page 20: ...00 240 F 240 F Cylinder Head 200 460 F 460 F Temperature Oil Pressure 10 psi 30 60 psi 100 psi Carburetor Air 15 to 5 C Temperature 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 ...

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 FAA 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: ... COMBINED FOR ADDITIONAL LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA 5 On flap control indicator 0 to 10 10 to 20 to FULL Partial flap range with blue code and 140 kt callout also mechanical detent at 10 Indices at these positions with white color code and 95 kt callout also mechanical detent at 10 and 20 6 Forward of fuel tank filler cap FUEL 100LL l00 MIN GRADE AVIATION GASOLINE CAP 46 0 U ...

Page 25: ...2 LIMITATIONS 7 8 A calibration card is provided to indicate the accuracy of the magnetic compass in 30 increments On oil filler cap I OIL 12QTS L 9 Near airspeed indicator MANEUVER SPEED 111 KIAS 1 October 1978 2 11 2 12 blank ...

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

Page 28: ...3 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 15 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 Charg...

Page 29: ...s 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 _ 1 50 Lbs Maximum Glide Precautionary Landing With Engine Power Landing Without Engine Power J Wi...

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 8 Touchdown SLIGHTLY TAIL LOW 9 Brakes APPLY HEAVILY PRECAUTIONARY LANDING WITH ENGINE POWER 1 Airspeed 65 KIAS 2 Wing Flaps 20 3 Selected Field FL...

Page 31: ...ach at 70 KIAS with flaps up or at 65 KIAS with 10 flaps 6 Cabin Doors UNLATCH 7 Touchdown LEVEL ATTITUDE AT ESTABLISHED DESCENT 8 Face CUSHION at touchdown with folded coat 9 Airpl_ane 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: ...nge 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 cau...

Page 34: ... 01 J 2 AIrspeed Consult appropri te t bl j L ct 115 _ 3 Altitude Cruise 50 feet hii her i Lpproach30feet ighe r n 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 Deflection 1 Alt...

Page 35: ...ot occurred to de activate the alternator system 1 Avionics Power Switch OFF 2 Master Switch OFF both sides 3 Master Switch ON 4 Low Voltage Light CHECK OFF 5 Avionics Power Switch ON If low voltage light illuminates again 6 Alternator OFF 7 Nonessential Radio and Electrical Equipment OFF 8 Flight TERMINATE as soon as practical 1 October 1978 3 9 3 10 blank ...

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Page 37: ...iding turn necessary to return 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 ...

Page 38: ... in judging height over a water surface LANDING WITHOUT ELEVATOR CONTROL Trim for horizontal flight with an airspeed of approximately 80 KIAS by using throttle and elevator trim 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: ...niature 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 of elevator control Avoid overcontrolling by keeping the hands offthe con...

Page 40: ...levator 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 CONDI...

Page 41: ...s 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 ...

Page 42: ...t for 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 Lor R ignition switch position will identify which magneto is malfunctioning Select different power settings and enrichen the mixture to d...

Page 43: ... 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 includes an over vol...

Page 44: ...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 minimized because the battery can supply the electrical system for only a limited period...

Page 45: ...ft Wing 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 AMPLIFIED PROCEDURES Starting E ngine 1 October 1978 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: ...r Check 4 13 Wing Flap Settings 4 14 Crosswind Takeoff 4 14 Enroute Climb 4 14 Cruise 4 15 Leaning With A Cessna Economy Mixture Indicator EGT 4 16 Stalls 4 17 Landing 4 17 Normal Landing 4 17 Short Field Landing 4 18 Crosswind Landing 4 18 Balked Landing 4 18 Cold Weather Operation 4 18 Starting 4 18 Operation 4 20 Hot Weather Operation 4 21 Noise Abatement 4 21 4 2 1 October 1978 ...

Page 47: ...the particular weight must be used 70 80 KIAS KIAS 7Jb8n KIAS 60 70 KIAS li KIAS KIAS 111 KIAS 1l Q KIAS 89 KIAS KNOTS 15 KNOTS I i 85 95 KIAS c 1 1 Z KIAS f 72 KIAS 54 KIAS 62KIAS 7 y r j Takeoff Normal Climb Out Short Field Takeoff Flaps2Po 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 ...

Page 48: ...om wing tail and control surfaces Also make sure that control surfaces contain no internal accumulations of ice or debris Prior to flight check that pitot heater if installed 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 4 4 1 October 1978 ...

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 1 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: ...ECK 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 has been overprimed start with throttle 1 4 to 1 2 open Reduce throttle to idle when engine fires 9 Oil Pressure CHECK BEFORE TAKEOFF 1 Cabin Doors and Windows CLOSE...

Page 52: ...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 u FULL THROTTLE and 2400 RPM 5 Brakes RELEASE 6 Elevator Control MAINTAIN SLIGHTLY TAIL LOW ATTI TUDE 7 Climb Speed 57 KIAS until all obstac...

Page 53: ...s CLOSED DeSCENT 1 Power AS DESIRED 2 Carburetor Heat AS REQUIRED to prevent carburetor icing 3 Mixture ENRICHEN as required 4 Cowl Flaps CLOSED 5 WingFlaps AS DESIRED 0 10 below 140 KIAS 10 40 below 95 KIAS BEFORE LANDING J Seats Belts Harnesses ADJUST and LOCK _2 Fuel Selector Valve BOTH 3 Mixture RICH _4 Carburetor Heat ON apply full heat before closing throttle 5 Propeller HIGH RPM 6 Autopilot...

Page 54: ...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 AFTER LANDING 1 Wing Flaps UP 2 Carburetor Heat COLD 3 Cowl Flaps OPEN SECURING AIRPLANE 1 Parking Brake SET 2 Avionics Power Switch Electrical Equipment OFF ...

Page 55: ...e 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 in very cold weather stop engine and investigate Lack of oil pressure...

Page 56: ...A D _ _T O j B j _ _ _ CODE WIND DIRECTION t 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 4 12 Figure 4 2 Taxiing Diagram 1 October 1978 ...

Page 57: ...a doubt concerning operation of the ignition system RPM checks at higher engine speeds will usually confirm whether a deficiency exists An absence of RPM drop may be an indication of faulty grounding of one side of the ignition system or should be cause for suspicion that the magneto timing is set in advance of the setting specified ALTERNATOR CHECK Prior to flights where verification of proper al...

Page 58: ...should 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 20 an obstacle clearance speed of 57 KIAS should be used Soft field takeoffs are performed with 20 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 59: ...d be done at 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...

Page 60: ...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 61: ...conomy 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 i...

Page 62: ... field length Although the crab or combination method of drift correction may be used the wiIlg Iow method gives the best control After touchdown hold a straigh course with the steerable nose wheel an occasional braking if necessary i 7 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 cl...

Page 63: ...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 64: ...ins 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 i...

Page 65: ... persons recreational and park areas and other noise sensitive areas should make every effort to fly not less than 2000 feet above the surface weather permitting even though flight at a lower level may be consistent with the provisions of government regulations 2 During departure from or approach to an airport climb after takeoff and descent for landing should be made so as to avoid prolonged flig...

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Page 67: ... Lbs Takeoff Distance 2700 Lbs and 2400 Lbs Figure 5 5 Rate Of Climb Maximum Figure 5 6 Time Fuel 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 Figure 5 8 Range Profile...

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Page 69: ... condition and air turbulence may account for variations of 10 ormore 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 in the t...

Page 70: ...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 71: ...rresponding 7 1 hours Using this information the estimated distance can be determined for the expected 10 knot headwind at 7500 feet as follows Range zero wind Decrease in range due to wind 7 1 hours x 10 knot headwind Corrected range 952 71 88i Nautical Miles This indicates that the trip can be made without a fuel stop using approximately 65 power The cruise performance chart for 8 000 feet press...

Page 72: ...ve standard the correction would be 16 C lOoC x 10 16 Increase With this factor included the fuel estimate would be calculated as follows Fuel to climb standard temperature Increase due to non standard temperature 2 8 x 16 Corrected fuel to climb 2 8 0 4 3 2 Gallons Using a similar procedure for the distance during climb results in 17 nautical miles The resultant cruise distance is Total distance ...

Page 73: ... the destination airport Figure 5 10 presents landing distance information for the short field technique The distances corres ponding to 2000 feet pressure altitude and a temperature of 30 C 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 outline...

Page 74: ... KIAS KCAS FLAPS 20 I 0 50 60 70 80 90 100 110 ro 120 60 64 71 80 89 99 1 108 117 v 130 127 140 136 150 145 160 155 KIAS KCAS FLAPS 40 KIAS KCAS 40 50 60 70 80 90 52 57 64 72 81 90 40 50 60 70 80 90 51 56 63 72 81 91 95 95 95 95 5 8 Figure 5 1 Airspeed Calibration Sheet 1 of 2 1 October 1978 ...

Page 75: ...95 ALTERNATE KIAS 51 62 72 82 91 97 FLAPS 40 NORMAL KIAS 40 50 60 70 80 90 95 ALTERNATE KIAS 43 51 60 71 81 90 95 HEATER VENTS OPEN AND WINDOWS CLOSED FLAPS UP NORMAL KIAS 60 70 80 90 100 110 120 130 140 150 160 ALTERNATE KIAS 60 70 80 90 100 110 120 130 140 150 160 FLAPS 20 NORMAL KIAS 50 60 70 80 90 95 ALTERNATE KIAS 50 60 70 79 89 93 FLAPS 40 NORMAL KIAS 40 50 60 70 80 90 95 ALTERNATE KIAS 41 4...

Page 76: ...N CHART 1201lmlmmlllllllm mlmme 60 t w r z w a r 40 u en w w a w Cl 20 60 40 20 o 20 401U J L J L LJ L L L L JL J J L L L L L l L L L L l L L I 1 J L L L J L LL L J J L L L l l J L LJ 40 DEGREES CELSIUS Figure 5 2 Temperature Conversion Chart 5 10 1 October 1978 ...

Page 77: ... 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 c 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 t 2950 20 47 55 51 59 56 65 66 78 40 45 54 48 58 54 64 64 76 Figure 5 3 Stall ...

Page 78: ...rass runway increase distances by 15 of the ground roll figure TAKEOFF OOC 10 C 20 C 30 C 4QoC SPEED PRESS WEIGHT KIAS ALT TOTAL TOTAL TOTAL TOTAL TOTAL LBS LIFT AT FT GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR OFF 50 FT ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS 2950 49 57 S L 635 1220 680 1305 730 5 780 1490 835 1590 _ 1000 690 1335 745 ...

Page 79: ...00 735 1425 790 1525 850 1630 910 1745 970 1870 5000 805 1565 865 1680 930 1800 995 1930 1065 2075 6000 885 1730 950 1860 1020 1995 1095 2150 1170 2310 7000 970 1920 1045 2065 1120 2225 1205 2400 1290 2595 8000 1070 2140 1150 2310 1235 2500 1325 2705 1420 2935 2400 44 52 S L 395 775 425 825 455 875 485 930 520 990 1000 430 840 465 895 495 950 530 1010 1075 565 2000 470 915 505 975 540 1035 575 110...

Page 80: ...5000 feet for smooth engine 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 711 1155 1070 990 910 2000 L 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 Figure 5 5 Rate of Climb 5 14 1 October 1978 ...

Page 81: ...C 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 7 1010 0 0 0 1000 13 77 955 1 0 3 1 2000 11 76 900 2 0 7 3 3000 9 76 845 3 1 1 4 4000 7 75 790 5 1 5 6 5000 5 75 735 6 1 9 8 6000 3 74 680 7 2 3 10 7000 1 74 625 9 2 8 12 8000 1 73 570 11 3 ...

Page 82: ...stance by 10 for each 100 C above standard temperature 4 Distances 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 670 0 0 0 1000 13 670 1 0 4 2 2000 11 670 3 0 8 5 _ 1 0 _ _ 3000 9 670 4 1 2 7 c 4000 7 670 6 1 7 9 _I _ l 5000 5 670 7 2 1 12 5 c 6000 3 640 9 2 6 14 7000 1 575 11 3 0 17 8000 1 510 1...

Page 83: ...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 V 20 60 121 10 2 8...

Page 84: ...0 2 2300 76 140 13 1 74 141 12 6 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 22QO 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 53 121 9 2 2100 23 70 132 11 9 67 133 11 5 65 133 11 1 22 66 128 11 ...

Page 85: ...21 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 77 139 13 1 74 140 12 6 71 141 U _ 21 72 136 12 3 69 137 1 11C 67 137 11 4 20 67 132 11 5 65 133 11 1 63 133 10 7 19 63 128 10 7 00 _ 129 10 3 58 129 10 0 2200 22 72 136 12 3 69 137 11 9 67 137 11 5 21 6 u fg U J l fl5 133 11 1 63 134 10 8 63 10 8 61 129 10 4 59 130 10 1 19 59 ...

Page 86: ... 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 61J R 11 4 q 65 137 11 0 20 65 132 11 1 63 133 m J 60 133 10T 19 61 128 10 3 58 129 10 0 56 129 9 7 1...

Page 87: ...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 59 431 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 3 17 53...

Page 88: ...HP BHP BHP 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 8 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 5...

Page 89: ...fuel is based on 45 minutes at 45 BHP and is 6 gallons 12 000 v r T l 1r 4 TO _ r 12 9 1 lIlI t f 11 4 l 71 _ 1 1r t b Y KTAS KTAS f KTAS Y I I w w u 1100 1000 1050 950 900 850 S L 800 6000 1 t t t 1 t 1I t H t t 1I t I If t i t l 1 t f 139 131 121 II t 109 1 f 1 f I c KT AS KT I 1t I KT S KT S I1 f 4000 1 I t rc l t l t t i J I l I t 0 f cif 0 I 10 f if 1f 1ft t f I f f Ii f 2000 I I f f I I J 1 ...

Page 90: ...for the fuel used for engine start taxi takeoff and climb and the time during a normal climb as shown in figure 5 6 2 Reserve fuel is based on 45 minutes at 15 BHp and is gallon 12 000 10 000 I 8000 UJ UJ U UJ 6000 0 I C 4000 2000 I IA A t tfl J roy J I 1 a a a a UJ UJ UJ UJ 3 3 3 3 0 0 0 0 a a a a R 0 LO LO LO LO 0 LO q S L 5 6 7 8 9 10 11 5 24 ENDURANCE HOURS Figure 5 9 Endurance Profile 1 Octob...

Page 91: ...LBS 50 FT ALT TOTAL TOTAL TOTAL TOTAL 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 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 1...

Page 92: ......

Page 93: ...ALANCE EQUIPMENT LIST SECTION 6 WEIGHT BALANCE EQUIPMENT LIST TABLE OF CONTENTS Page Introduction Airplane Weighing Procedures Weight And Balance Baggage and Cargo Tie Down Equipment List 1 October 1978 6 3 6 3 6 6 6 6 6 15 6 1 6 2 blank ...

Page 94: ......

Page 95: ...il 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 andI 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 96: ...L Right Wheel R Nose Wheel N Sum of Net Weights As Weighed W x ARM A N x B X W x IN Moment 1000 Item Weight Lbs X C G Arm In Lbs In Airplane Weight From Item 5 page 6 3 Add Oil No Oil Filter 12 Qts at 7 5 Lbs Gal 15 0 With Oil Filter 13 Qts at 7 5 Lbs Gal 15 0 Add Unusable Fuel 4 Gal at 6 Lbs Gal 24 48 0 1 2 Equipment Changes Airplane Basic Empty Weight Figure 6 1 Sample Airplane Weighing 6 4 1 Oc...

Page 97: ...AIRPLANE MODEL HI SERIAL NUMBER I PAGE NUMBER WEIGHT CHANGE RUNNING BASIC ITEM NO ADDED REMOVED EMPTY WEIGHT DATE DESCRIPTION OF ARTICLE OR MODIFICATION Wt Arm Moment Wt Arm Moment Wt Moment In Out lb In 1000 lb In 1000 lb 1000 Figure 6 2 Sample Weight and Balance Record S O at tJOO t OO t lZ D El t I l t O D c a S tt Joo t t J Zt lO t lZS I lOt OOt O ...

Page 98: ...em 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 G...

Page 99: ...ree 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 forwar...

Page 100: ...2ND ROW SEATING SEATING SEAT REMOVED NOTE The aft baggage wall approximate station 124 can be used as a con venient interior reference point for determining the location of baggage area fuselage stations Pilot or passenger center of gravity on adjustable seats positioned for average occupant Numbers in par entheses indicate forward and aft limits of occupant center of gravity range Arms measured t...

Page 101: ... 48 1 Y J 42 lD3 3 11 1 2 l 0 12 1 17 J L_ __ LR 4 I I 1 65 1 58 DOOR OPENING DIMENSIONS IWIDTH IWIDTH IHEIGHT I TOP BOTTOM FRONT CABIN DOOR I 32 I 36 I 41 I BAGGAGE DOOR 15 15 22 HEIGHT REAR WIDTH LWR WINDOW LI NE CABIN FLOOR INSTRUMENT PANel CABIN WIDTH MEASUREMENTS Figure 6 4 Internal Cabin Dimensions 1 October 1978 6 9 ...

Page 102: ...Second Row Passengers 340 25 2 Cargo Replacing Second Row Seats Sta 65 to 82 5 Baggage Area A or Passenger on Child s Seat Sta 82 to 108 120 Lbs Maximum 90 8 7 6 Baggage Aft Area B and Hatshelf Sta 108 to 136 80 Lbs Maximum 7 RAMP WEIGHT AND MOMENT 2960 127 9 8 Fuel allowance for engine start taxi and runup 10 5 9 TAKEOFF WEIGHT AND MOMENT Subtract step 8 from step 7 2950 127 4 10 Locate this poin...

Page 103: ... 6 l I c l LU 250 Cl C o l NOTES 1 2 Figure 6 6 Loading Graph Line representing adjustable seats shows pilot and front seat passenger center of gravity on adjustable seats positioned for an average occupant Refer to the Loading Arrangements diagram for forward and aft limits of occupant C G range Hatshelf Maximum Load 25 Lbs tz j t t tz jO DP c t 3 ti tDCJ tz j l tz j z O t 3 l t 3 zO t tOZ OOtz j...

Page 104: ...LOADED AIRPLANE MOMENT loo0 POUND INCHES LOADED AIRPLANE MOMENT 1Qoo KILOGRAM MILLIMETERS 650 700 750 800 850 900 950 1000 1050 1100 1150 1200 1250 1300 1350 1400 1450 1500 1550 1600 1650 r I CENTER OF GRAVITY 1 I MOMENT ENVELOPE I I I I i I I I I I I I I I 55 60 65 70 75 80 85 90 95 100 105 11 115 120 25 130 135 140 181 20 Vi 27 c z o 26 I I 25 w 24 5 Q 23 c w c 22 o J 2800 2950 29 21 19 o o S O ...

Page 105: ...1200 a 5 2600 t t i j 1 i i i itt H H C o 0 1 4t f t i l T _ 1150 t 2500 C l i 1 T ri t t 4 t j i t t 4 j T i 1100 w 2400 I W l 3 z W 5 I T W L t 1050 0 2300 1 J it t I j II t 1j i t I j 1 1 t j 1 0 t t 4 1 1 j f it t i H 1 114 I Cl T j l c T t UJ 2200 IT 1000 1 J CENTER OF GRAVITY JriUt lit ow 2100 I 950 t i LIM ITS t rt E t t t t l r l H H 2000 I t t 1 l r t i 900 i5 c P 1900 t c i 850 tl 1800 j...

Page 106: ......

Page 107: ...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 108: ... QUICK DRAIN VALVE Ncr CH NGE B LANDING GEAR ACCESSORIES REF DRAWING 0750201 SL IlK 662 Te 62739 Sri 2001 1 CT 635994 I 1A 4 5 0750038 4 C611503 01 12 TCM639171 0750606 1 t 1250922 2 C294505 QIJl C294505 0 1 2 C101 jJ9 JIJt 161031 01 7 752637 0752637 11 12 0412 3 0752637 1 070 003 l C431803 JI02 0750125 171H 15 10 WT lBS 446 0 12 9 4 6 2 8 17 8 5 8 1 0 10 8 1 5 4 5 1 5 1 g 0 3 51 3 8 3 o 1 7 0 2 1...

Page 109: ... 5 B04 R l I o c o cr CD I CO l 00 C ELECTRICAL SYSTEMS 0 I l COI R 1 COI R 2 C01 0 C04 R C07 A ClO A C19 0 C22 A C23 A C25 A C31 A C40 A C43 A BATTERY 24 VOLT STANDARO DuTY BATTERY 24 VOLT MANIFOLD STANDARD DUlY BATTERY 24 VOLT HEAVY DJTY ALTERNATOR CONTROL UNIT r 28 VOLT hITh HIGH 4ND Lew VOLTAGE SENS NG G UUND SERVICE PLUG RECEPTACLE ELECTRIC ELEVATUR TRIM INSTL ELECTRIC DRIVE ASSEMBLY HEATiNG ...

Page 110: ... READOUT CUMPASS MAGNETIC MOUNT INSTRUMENT CLUSTER ENGINE FUEL I DICATOR INSTALLATION ECONOMY MIXTURE EGT INDICATOR THERMOCOUPLE PROBE THERMOCOUPLE LEAD WIRE ICI GYRO SYSTEM DIRECTIONAL INDICATOR ATTITUDE INDICATOR HOSES t FITTINGS SCREWS CLAMPS ETC YRO SYS EM INSTL FOR NAV O MATIC 30JA AUTOPILOT ITEM H31 A 21 DlRECTIONAL INDICATUR REF DRAWING C594502 0102 OR 95 6 0701018 4 C622008 0102 C622006 01...

Page 111: ...TIA REEL INSTL NET CHANGE BELT SHOULDER HARNESS ASSY CO PILeT BELT ASSY 2ND ROW OCCUPANTS SET OF 2 BELT SHOULDER HARNESS ASSY 2ND ROW INTERIOR VINYL SEAT COVERS NET CHANGEl INTERIOR LEATHER SEAT COVERS NET CHANGE OPENABLE RH CABIN DCOR WINDOW NET CHANGEl INDOWS OVERHEAD CABIN TOP NET CHANGt VENTILATICN SYSTEM 2ND ROW SEATING CURTAIN REAR WINDUw UXYGEN SYSTEM 4 PORT REF DRAWING 8 81 n O lOL C661076...

Page 112: ...HEATING SYSTEM CABIN CARBURETOR AIR I NC LUOESE XH AUST SYSTEM F PLACARDS WARNINGS MANUALS PLACARD PLACARD NIGHT PLACARD t NIGH INDICATOR STALL WARNING HORN AUDIBLE PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL STOW D G AUXILIARY E U PMENT TAILCCiNE LIFT HANDLES SET OF 2 HJISTING RINGS AIRPLANE INOT FACTOKY INSTAllED CURROSION PROOFING INTERNAL STATIC DISCHARGERS SET OF 111 RE...

Page 113: ...5 0 29 0 8 0 29 9 34 3 O ot l tJCll t lCll z D J I H01 A l I CESSNA 300 ADF WIT BFO RECEIVER wITH BFO R 546E GONIOMETER INDICAlOR IN 346A AOF LOOP ANTENNA t ASSOC IRING ACF SENSE ANTENNA MOUNTING BOX MnC ITEMS HOI A 2 ICESSNA 400 AOF BFCI AOF RECEIVER ITH BfO R 446A GONIOMETER INDICATOR IN 346A oOF LOOP ANTENNA 6 ASSOC olRING ACf SENSE ANTENNA MOUNTING BOX 6 MIse ITEMS H04 A l lOME INSTALLATION NA...

Page 114: ...IOI0A REMOTE PO ER A PlIFIER CU II0 ANTENNA COlPLER LOAD BOX ANTENNA INSTL 351 INCHES lOt G CESSNA 400 MARKER BEACON RECEIVER R 02A ANTENNA FLUSH MOlNTED IN TAILCCNE CESSNA 300 TRANSPONDER RECEIVER TRANSMITTER RT 35fiA ANTENNA CESSNA 400 TRANSPONDER RECEIVER TRANSMI11ER RT 459A ANT ENNA CESSNA cc NAV COM 72 CH ceM 1ST U IT REQUIRES H34 A 10 BE OPERAll E RECEIVER 1RANSCEhER RT 3S5A REF DRAWING 4410...

Page 115: ...COM 12C CH CCM 2ND I I IT REQUIRES H37 A 10 BE GPERAlICNAL REC EIVER TRAN SCE HER R T 3 85A VOR LOC INDICATOR IN 385A MOUNT wIRING MISC HARD ARE CESSNA 400 NAV COM i2C CH CCM iii I lH 300 SERIES INDICATOR 2ND UNIT REQUIRES H3i A 10 BE CPERA1ICNAl RECE IVER TRAN seE I ER R T 485A I VOR LOC INDICATOR IN 3eSA MOUNT ftlRING MISC HARD ARE CESSNA 3bo NAV COM 2 D UNIT VCR lOC OPERATING SYSTEM FOR ExpeRT ...

Page 116: ...09 A NOf l SLA JED HSI SYSIEfoi cae 0 1 TURf l COORDINATOR NET CHANGE WING SERVO INSTALLATICN C64 S GYRO SYSTEM DELETED MISC ITEM S HARD ARE 8ASIC AVIONICS KIT REQUIRED BY AND AvAIL ABLE olIn 1ST NA COMl CABIN SPEAKER INSTl RADIO COOLING NOISE FILTER ON ALTERNATOR RECEIVER INSTALlAlION KIT CABLE ASSY FOR CO ANTENNA CABLE ASSY FOR OM T ANTENNA REF DRAWING 3940257 3 42340 1124 45010 1000 3910201 6 3...

Page 117: ... AIR SCURCE EES A DUAL CONTRCLS I C1 A 1 CESSNA cc AUF R 546El 1 16 A 1 CESSNA 3 TRANSPONDER R1359A 22 A l CESSNA 3 NA CGM RT 385A 28 A l EMERGENC LOCATOR 1RA SI ITTE H1 A 1 CESSNA 2C A AUO PIleT I 4 A BAS IC A I I NIC SKI T NAV PAC SKYLANE II NU NET CHANGEl rO A 4CO GLIDESLOPE R 443B 13 A 4ee MARKER BEACeN R 402A 25 A l NAV COM 3l5A tOR LeC 2ND LNI T 37 A ANTENNA 6 COUPLER KI1 REF DRAWING 3960102...

Page 118: ......

Page 119: ... Belts 7 12 Shoulder Harnesses 7 14 Integrated Seat Belt Shoulder Harnesses With Inertia Reels 7 14 Entrance Doors And Cabin Windows 7 15 Control Locks 7 16 Engine 7 16 Engine Controls 7 16 Engine Instruments 7 17 New Engine Break In And Operation 7 18 Engine Oil System 7 18 Ignition Starter System 7 19 Air Induction System 7 19 Exhaust System 7 20 Carburetor And Priming System 7 20 Cooling System...

Page 120: ...ating And Defrosting System 7 31 Pitot Static System And Instruments 7 33 Airspeed Indicator 7 33 Rate Of Climb Indicator 7 34 Altimeter 7 34 Vacuum System And Instruments 7 34 Attitude Indicator 7 34 Directional Indicator 7 34 Suction Gage 7 36 Stall Warning System 7 36 Avionics Support Equipment 7 36 Audio Control Panel 7 36 Transmitter Selector Switch 7 38 Automatic Audio Selector Switch 7 38 A...

Page 121: ...tire 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 fitt ngs 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 ...

Page 122: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS AILERON CONTROL SYSTEM RUDDER AND RUDDER TRIM CONTROL SYSTEMS CESSNA MODEL 182Q 7 4 Figure 7 1 Flight Control and Trim Systems Sheet 1 of 2 1 October 1978 ...

Page 123: ...ELEVATOR CONTROL SYSTEM CESSNA MODEL 182Q SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS ELEVATOR TRIM CONTROL SYSTEM Figure 7 1 Flight Control and Trim Systems Sheet 2 of 2 1 October 1978 7 5 ...

Page 124: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS CESSNA MODEL 182Q Figure 7 2 Instrument Panel Sheet 1 of 2 7 6 1 October 1978 ...

Page 125: ... 14 Marker Beacon Indicator 38 Microphone S Lights and Switches 39 Cowl Flap Control Lever 10 0 l s 15 Audio Control Panel 40 Fuel Selector Valve Handle 10 0 16 Radios 41 Fuel Selector Light Z Pl 17 Tachometer 42 Elevator Trim Control Wheel and t t l s l 18 Manifold Pressure Gage Position Indicator 0 I 19 Fuel Quantity Indicators 43 Carburetor Heat Control Knob 00 en r and Ammeter 44 Electrical Sw...

Page 126: ...tall 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 remove the 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 127: ...ns the elevator 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 adjacer i t to the parking brake h...

Page 128: ... see 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 l Qved up or down in a slotted panel that provides mechanical stops at the 10 and 20 PQ _t _I For flap settings greater than 10 move the switch lever to the right to clear the stop and position it as desire...

Page 129: ...o Section 6 jy l en loadingtl1e irpla e children should not 1 e p ll QEld or perII iJ c ijJ L hebagg e 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...

Page 130: ...a stowed position against the aft cabin bulkhead when not in use To stow the seat rotate the seat bottom up and aft as far as it will go When not in use the seat should be kept in the stowed position Headrests are available for any of the seat configurations except the child s seat To adjust the headrest apply enough pressure to it to raise or lower it to the desired level The headrest may be remo...

Page 131: ...ULDER HARNESS WITH INERTIA REel PILOrS SEAT SHOWN t 71 7 1 l nTa j t b CKLE FREE END OF HARNESS Pull down to tighten SHOULDER HARNESS _____ CONNECTING LINK Snap onto retaining stud on seat belt link to attach harness FREE END OF SEAT BELT Pull to tighten NARROW RELEASE STRAP Pull up when lengthening harness Non adjustable f I f L 1 p I i U 1 AND SHOULDER HARNESS RETAINING STUD Figure 7 4 Seat Belt...

Page 132: ...he connecting link firmly onto the retaining stud on the seat belt link half Then adjust to length A properly adjusted harness will permit the occupant to lean forward enough to sit completely erect but prevent excessive forward movement and contact with objects during sudden deceleration Also the pilot will want the freedom to reach all controls easily Removing the shoulder harness is accomplishe...

Page 133: ... arm rest The inside door handle has three positions and a placard at its base which reads OPEN CLOSE and LOCK The handle is spring loaded to the CLOSE up position When the door has been pulled shut and latched lock it by rotating the door handle forward to the LOCK position flush with the arm rest When the handle is rotated to the LOCK position an over center action will hold it in that position ...

Page 134: ...k will place the red flag over the ignition switch In areas where high or gusty winds occur a control surface lock should be installed over the vertical stabilizer and rudder The control lock and any other type of locking device should be removed prior to starting the engine ENGINE The airplane is powered by a horizontally o p E0s six lil r _Qy x ht3 g valve au cooled Q rburetedengine with a wet s...

Page 135: ...the oil pressure gage The gage is operated by an electrical resistance type temperature sensor which receives power from the airplane electrical system Oil tlilmperature limitations are the normal operating range green arc whiCh is WO F 38 C 1 Q_ _40 J 4 _ 9 and themaximum redline wbicb is 240 F 116 C The cylinder head temperature gage under the left fuel quantity indicator is operated by an elect...

Page 136: ...ne If during the first 25 hours oil must be added use only aviation grade straight mineral oil conforming to Specification No MIL L 6082 ENGINE OIL SYSTEM Oil for engine lubrication and propeller governor operation is supp lied from a sump on the bottom of the engine The capacity ofthe sump is 12 quarts one additional quart is required if a full flow oil filter is installed Oil is drawn from the s...

Page 137: ...wo engine driven magnetos and two spark plugs in each cylinder The right magneto fires the lower left and upper right spark plugs and the left magneto fires the lower right and upper left spark plugs Normal operation is conducted with both magnetos due to the more complete burning of the fuel air mixture with dual ignition Ignition and starter operation is controlled by a rotary type switch locate...

Page 138: ...laYlJ cgl trolled within limj t_ by the mixture contr L9n tp iIl truIlleIlt paI l31 For easy starting in cold weather the engine is equipped with a manual primer The primer is actually a small pump which draws fuel from the fuel strainer when the plunger is pulled out and injects it into the intake manifold when the plunger is pushed back in The plunger knob is equipped with a lock and after being...

Page 139: ...lade pitch will decrease giving a hIE r RPNCWhJ n the c QntroTlilibhls puri d out die blade pitch increases thereby decreasing RPM Theprope1Ter control knob i qll pp dwith l t e r nier feature which allows slow or fine RPM adjustments by rotating the knob clockwise toill e ase RpM and counterclockw QSl _ r ease it To m_a raIJid r l rg e _ adjustments _c llP e _ss the button on the end of the cont ...

Page 140: ...IMUM FUEL CAPACITY WHEN RFFUELING AND MINIMIZE CROSS FEE DING WHEN PARKED ON A SLOPING SURFACE PLACE THE FUEL SELECTOR VALVE IN EITHER LEFT OR RIGHT POSITION TO ENGINE FUEL STRAINER DRAIN CONTROL ENGINE PRIMER CODE VENT FUEL SUPPLY MECHANICAL LINKAGE L 1 c J O MIXTURE CONTROL THROTTLE 0 CARBURETOR CONTROL __ _ _ TO ENGINE ELECTRICAL CONNECTION Figure 7 5 Fuel System 7 22 1 October 1978 ...

Page 141: ...k is indicated by a red line and the letter E When an indicator shows an empty tank approximately 2 0 gallons remain in a tank as unusable fuel The indicators cannot be relied upon for accurate readings during skids slips or unusual flight attitudes If both indicator pointers should rapidly move to a zero reading check the cylinder head temperature and oil temperature gages for operation If these ...

Page 142: ...o the empty tank while in coordinated flight which in turn will assure optimum fuel feed during slipping or skidding flight The fuel system is equipped with drain valves to provide a means for the examination of fuel in the system for contamination and grade The system should be examined before the first flight of every day and after each refueling by using the sampler cup provided to drain fuel f...

Page 143: ...most general electrical and all avionics circuits through the primary bus bar and the avionics bus bar which are interconnected by an a vionics power switch The primary bus is on anytime the master switch is turned on and is not affected by starter or external power usage Both bus bars are on anytime the master switch and avionics power switches are turned on CAUTION Prior to turning the master sw...

Page 144: ... TEMP CARBURETOR AIR TEMP GAGES PilOT HEAT TO ELECTROLUMINESCENT PANELS AND MARKER BEACON AUDIO CONTROL PANEL NAV TO NAVIGATION LIGHTS AND LIGHTS CONTROL WHEEL MAP LIGHT WITH FUSE o 1 TO HEATED PlTaT AND STALL WARNING SYSTEMS orb TO WING FlAP SYSTEM orn TO STAll WARNING SYSTEM Io b o TO AUTOMATIC PILOT 10 _TO ELECTRIC ELEVATOR TRIM SYSTEM AND CIRCUIT BREAKER CIRCUIT BREAKER ON CONTROL PEDESTAl a _...

Page 145: ... APproxirna tely tw o mjolltes pefore Pl CJ Ilg lJ esvv in the ON position ag ain IftJ c irC lJtbre t _ OD u J gain do not reset itL The avionics power switch should be placed in the off position prior to turning the master switch ON or off starting the engine or appIY inK I t rpa power source and pia3Tbeuti liie r iiiplace of the individual avionics equipmerifswitches AMMETER The ammeter located ...

Page 146: ...T portion of the master switch while le ay ing theUATpo rtiQJJtu rneclQn CIRCUIT BREAKERS AND FUSES Most of the electrical circuits in the airplane are protected by push to reset circuit breakers mounted on the left side of the switch and control panel _ ll cl cl i 2 _ g _ p i y i_cl Il L i J reakers a toggle switchI cir cuit breaker labeled AVIONICS POWER on the left switch and control paner also...

Page 147: ...with electroluminescent and post lighting also available Dual concentric light dimming rheostats on the left side of the switch and control panel control the intensity of all lighting The following para graphs describe the various lighting systems and their controls The left and right sides of the switch and control panel and the marker beacon audio control panel may be lighted by electroluminesce...

Page 148: ...njunction with instrument panel flood lighting and consist of two openings just aft of the red instrument panel flood lights The map light openings have sliding covers controlled by small round knobs which uncover the openings when moved toward each other The covers should be kept closed unless the map lights are required A map light and toggle switch mounted in front of the pilot on the underside...

Page 149: ... the cabin to an outlet at the front door post at floor level Windshield defrost air is also supplied by a duct leading from the cabin manifold to an outlet on top of the anti glare shield D clr o st air Jl Q W Q9ntrolled by a rotary tY P L1 nQb labeled DEFB OST ForgGl l I1 _Y tU ltQn ull the C AJUN AIRkno b out witlLthe CABIN HEAT knob pushed full in To raise the air temperature pull the CABIN HE...

Page 150: ...CETER CONTROL ADJUSTABLE VENTILATORS o 0 7 r REAR CABIN tf n AIR OUTLETS J J HEATER VALVE FRONT CABIN AIR OUTLET CODE J RAM AIR FLOW VENTILATING AIR HEATED AIR BLENDED AIR MECHANICAL CONNECTION AIRFLOW ADJUSTMENT L WHEELS 7 ADJUSTABLE AIR OUTLETS Figure 7 8 Cabin Heating Ventilating and Defrosting System 7 32 1 October 1978 ...

Page 151: ... ure from iP side Jhe cabiL insteag Qf the external static P Q If erroneous instrument readings are SusJ 9_t g dueto water or icejIL the pr _ J JtQ i g to the standard external sta tic pressure sonrCQ the alternate static source valv e s b Ql 1db_e pulle d_on Pressures within the cabin will vary with heater vents opened or Closed _ i ii wrn aows opeIl R afertoSecHons3 arid fforthe effect of varyin...

Page 152: ...y to Qperate the attitude indicator and directiQnal indicatQr The system cQnsists Qf a vl t l l p J2 mQuntedQn the engine a vaCullI T l ef valve and vacuum system air filter on the aft side Qf the firewall belQw the instrurneiifp iineI and instruments iricludmg a suchQn gage Qn the left side Qf the instrument panel ATTITUDE INDICATOR The attitude indicatQr gives a visual indicatiQn Qf flight attit...

Page 153: ... 0 0 o 0 0 0 0 0 0 o 0 0 0 OVERBOARD VENT LINE VACUUM PUMP VACUUM RELIEF VALVE r t I t VACUUM SYSTEM AIR FILTER t DI RECTIONAL INDICATOR l t iL __ _ 4 ATTITUDE SUCTION INDICATOR GAGE CODE I IINLETAIR l 3 VACUUM W DISCHARGE AI R r I _ __ _ Figure r 9 VacuumSystem 1 October 1978 7 35 ...

Page 154: ...ntFsl panel protects the stall warning sysTem The vane in the wing senses the change in airflow over the wing and operates the warning horn at airspeeds J e e r J _a d l _ _ e the stall in all c0l l i g ra ti If the airplane has a heated stall warning system the vane and sensor unit in the wing leading edge iseqtlippedVliith a heating element The heated part of the system is operated by the PITOT ...

Page 155: ...CTION AUDIO SELECTOR SWITCH TYPICAL r SPEA KER NAV COM ADF AUTO l 2 3 1 2 0 O 0 0 Q 00FF I V PHONE I AUTOMATIC AUDIO SELECTOR SWITCH As illustrated the number 1 transmitter is selected the AUTO selector switch is in the OF F position the number 1 NAY COM receiver is in the PHONE position and the number 1 ADF is in the SPEAKER position With the switches set as shown the pilot will transmit on the n...

Page 156: ... audio amplifier operation the pilot should be aware that while utilizing a headset the only indication of audio amplifier failure is loss of the selected transmitter This can be verified by switching to the speaker function AUTOMATIC AUDIO SELECTOR SWITCH A toggle switch labeled AUTO can be used to automatically match the appropriate NAV COM receiver audio to the transmitter being selected To uti...

Page 157: ...irplane speaker The ADF 1 and 2 switches may be used anytime ADF audio is desired If the pilot wants only ADF audio for station identification or other reasons the AUTO selector switch if in use and all other audio selector switches should be in the OFF position If simultaneous ADF and N AVI COM audio is acceptable to the pilot no change in the existing switch positions is required Place the ADF 1...

Page 158: ... installation of wick type static dischargers is recommended to improve radio communications during flight through dust or various forms of precipitation rain snow or ice crystals Under these conditions the build up and discharge of static electricity from the trailing edges of the wings rudder elevator propeller tips and radio antennas can result in loss of usable radio signals on all communicati...

Page 159: ...ogressive 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 1978 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 161: ...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 162: ...covering all 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 taini...

Page 163: ...hat 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 ai...

Page 164: ... 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 possi ble at lower cost to Cessna owners Regardless of the inspection method selected by the owner he should keep in mind that FAR Part 43 and FAR Part...

Page 165: ...nformation 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 the...

Page 166: ... 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 off the 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 th...

Page 167: ...se for 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 WARNING 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 168: ...ns or tests 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 GRADE Aviation Grade SAE 50 Above 4 C 40 F Aviation Grade SAE 10W30 or SAE 30 Below 4 C 40 F Multi viscosity oil with a range of SAE 10W...

Page 169: ...rtment is required Items which are t lot 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 systems for cracks evidence of leakage and security of attachmen...

Page 170: ...ins are removed Allow the cleaner to dry then wipe it off with soft flannel cloths If a windshield cleaner is not available the plastic can be cleaned with soft cloths moistened with Stoddard solvent to remove oil and grease NOTE Never use gasoline benzine alcohol acetone fire extinguisher or anti ice fluid lacquer thinner or glass cleaner to clean the plastic These materials will attack the plast...

Page 171: ...utomotive wax A heavier coating of wax on the leading edges of the wings and tail and on the engine nose cap and propeller spinner will help reduce the abrasion encountered in these areas When the airplane is parked outside in cold climates and it is necessary to remove ice before flight care should be taken to protect the painted surfaces during ice removal with chemical liquids Isopropyl alcohol...

Page 172: ...h household spot removers used sparingly Before using any solvent read the instructions on the container and test it on an obscure place on the fabric to be cleaned Never saturate the fabric with a volatile solvent it may damage the padding and backing materials Soiled upholstery and carpet may be cleaned with foam type deter gent used according to the manufacturer s instructions To minimize wetti...

Page 173: ...tion Indicator Type IG 832C 200A Navomatic Autopilot Type AF 295B 300 ADF Type R 546E 300 Nav Com Type RT 385A 300 Nav Com Type RT 385A With 400 Area Navigation System Type RN 478A 300 Transponder Type RT 359A And Optional Altitude Encoder Blind 300 Transponder Type RT 359A And Optional Encoding Altimeter Type EA 401A 300A Navomatic Autopilot Type AF 395A 400 ADF Type R 446A 400 Area Navigation Sy...

Page 174: ...00 Nav Com Type RT 485A With 400 Area Navigation System Type RN 478A 400 Transponder Type RT 459A And Optional Altitude Encoder Blind 400 Transponder Type RT 459A And Optional Encoding Altimeter Type EA 401A 9 2 CESSNA MODEL 182Q 10 pages 10 pages 6 pages 6 pages 1 October 1978 ...

Page 175: ...able of Contents the supplements are classified under the headings of general and avionics and 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 contained in the following supplement...

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Page 177: ...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 178: ...retor 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 1978 ...

Page 179: ... 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 s...

Page 180: ...ock mode the calendar date appears numerically on the display with month of year 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 mode with the activ...

Page 181: ...starts from any previously accumu lated total Figure 3 Timer Mode switch accessible through a small hole on the bottom of the 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 appea...

Page 182: ...urns 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 ...

Page 183: ...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 in the DISENGAGE aft position A servo unit which includes a motor and chain driven solenoid operated clutch actuates the trim tab to the selected position When the clutch is not en...

Page 184: ...tch ON 2 Elevator Trim Disengage Switch ON 3 Trim Switch ACTUATE as desired 4 Elevator Trim Position Indicator CHECK NOTE To check the operation of the 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 ch...

Page 185: ...should be turned 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 equipment by 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 186: ...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 WARNING I When turning on the master switch using an external power source or pulling the propeller through by han...

Page 187: ...nal 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 1978 3 4 blank ...

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Page 189: ...ne 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 higher flow rate than those for the passengers it is color coded with an orange band adjacent to the plug in fitting The passenger hoses are color cod...

Page 190: ...ly 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 ambient temperature in the filling area and because of the temperature rise resulting from compression of the oxygen Because of this merely filling to 180...

Page 191: ...or 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 conditions of night flying fatigue or periods of physiological or emo tional disturbances Also the habitual and exces...

Page 192: ...t 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 coded hoses for the passengers If orange color coded hoses are provided for pilot and passengers it...

Page 193: ... Adjust mask 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 if the indicator is being...

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Page 195: ...iip p ush to reset cltcuTfbreliker The rocli er swHcliaIi d cir Q 1iLbr r are located on the left side of the switchail ctcontrol panel SECTION 2 LIMITATIONS Strobe lights must be turned off when taxiing in the vicinity of other airplanes or gll 1 ing night flight through clouds fo or haze SECTION 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when strobe lights are...

Page 196: ...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 1978 ...

Page 197: ...ther line This equipment should be installed for operations in temperatures consistently below 20 F 7 C Once installed the crankcase breather insulation is approved for permanent use 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 THIS PLATE N...

Page 198: ... 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 1978 ...

Page 199: ...r by a remote NAV set When coupled with a remote NAV set the MHz digits 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 notcoupled 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 M...

Page 200: ...ce 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 ope...

Page 201: ...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 r...

Page 202: ...f 188 8 in function window 4 DIM Control ADJUST 5 IDENT CONTROL ADJUST audio output in speaker 6 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 been turned OFF do not turn it on again f...

Page 203: ...0 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 identified as ...

Page 204: ...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 ENSURE ELT ACTIVATION Turn a radio transceiver ON and select 121 5 MHz If the ELT can be heard transmitting it was activate...

Page 205: ...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 an...

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Page 207: ...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 208: ...idual 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 1...

Page 209: ...ned 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 of pushbut tons 1 3 5 7 and digital displays 2 6 5 VOR DME PUSHBUTTON Provides PRESENT POSITION information as to VOR RADIAL and DME DISTANCE digitally in positions 2 and 6 respectively...

Page 210: ...RTAC 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 AND ...

Page 211: ...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 recomm nded 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 212: ...nt 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 DM...

Page 213: ...omputer 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 Waypoin...

Page 214: ...tial 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 1978 ...

Page 215: ...l 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 transmitt...

Page 216: ...ed 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 audi...

Page 217: ...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 airplane s transmitter into the ante...

Page 218: ...ON 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 4 1 October 1978 ...

Page 219: ...mines 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 additio...

Page 220: ... telephone and ship to shore LSB Optional Selects lower sideband operation not legal in U S Canada and most other countries 4 SQUELCH CONTROL Used to adjust signal threshold necessary to activate receiver audio Clockwise rotation increases background noise decreases squelch action counterclockwise rotation decreases background noise 5 CLARIFIER CONTROL Used to clarify single sideband speech during...

Page 221: ...d 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 trans ceiver 2 SPEAKER PHONE or AUTO Switch on audio control panel SELECT de ired mode 3 ON AUDIO Control ON allow equipment to war...

Page 222: ...ch in either the SPEAKER or PHONE positions b To Receive RELEASE mike button NOTE Voice communications 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...

Page 223: ...ios When dual Nav Com radios are installed the HSI is coupled to the number 1NAV 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 installed w...

Page 224: ...plays glide slope deviations and gives heading reference with respect to magnetic north when compass card is set to agree with compass 2 OMNI BEARING POINTER Indicates selected VOR course or localizer course on compass card 6 The selected VOR radial or localizer heading remains set on the compass card when the compass card 6 is rotated 3 NAV FLAG When flag is in view indicates that the NAV receive...

Page 225: ...d 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 precessional errors in the gyro 10 COURSE SELECTOR KNOB When rotated positions omni bearing pointer 2 on the compass card 6 to select desired VOR radial or localizer course 11 GLIDE SLOPE SCALE Indicate...

Page 226: ... 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 reverse but the stand...

Page 227: ...st be set to the inboard front course for both front and back course approaches to retain this pictorial presentation When the HSI system is installed with a Cessna 300A Type AF 395A Cessna 400A Type AF 530A 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 SNS switch mounted in the upp...

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Page 229: ...ordina 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 th...

Page 230: ...AF 295B PILOT S OPERATING HANDBOOK SUPPLEMENT AILERON NAV 1 NAV 2 COl INDICATORS PILOT 7 TURN COORDINATOR ACTUATOR COMPUTER AMPLIFIER 2 Figure 1 Cessna 200A Autopilot Operating Controls and Indicators Sheet 1 of 2 1 October 1978 ...

Page 231: ...ity position push button out response to NAV signal is dampened for smoother tracking of enroute 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 cause...

Page 232: ...irplane 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 1 AlP ON 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 engaging ...

Page 233: ...206 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 rate ...

Page 234: ...tion 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 fiO 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 235: ...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 236: ...otation from OFF position applies primary power to receiver further clockwise rotation increases audio level 2 FREQUENCY SELECTORS Knob A selects lOO 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 1978 ...

Page 237: ...nd 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 a...

Page 238: ...r Knobs SELECT operating frequency 3 ADF SPEAKER PHONE Switch SELECT speaker or phone position 4 Function Selector Knob ADF position and note relative bearing on indicator 5 VOL Control ADJUST to desired listening level 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 th...

Page 239: ...n 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 externally mounted antenna or related external antennas will result in a minor reduction in cruise performance 1 October 1978 5 6 blank ...

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Page 241: ...ing 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 automatic...

Page 242: ...requency readout to display and Com Fractional MHz Selector to select frequency in 05 MHz steps between 025 and 975 MHz In a position enables COM frequency readout to display and Com Fractional MHz Selector to select frequency in 05 MHz steps between 000 and 950 MHz NOTE The 5 or a may be read as the third decimal digit which is not displayed in the Com fractional frequency display Figure 1 Cessna...

Page 243: ...ound noise decreases squelch action counterclockwise rotation decreases background noise 10 COMMUNICATION RECEIVER TRANSMITTER MEGAHERTZ SELECTOR Selects COM frequency in l 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 controls volume of communications receiver audio 12 BC LAMP Amber light illuminates when an autopilo...

Page 244: ...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 Amber light illuminates when Automatic Radial Centeri...

Page 245: ...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 panel used in conjun...

Page 246: ...7 Mike Button a To Transmit DEPRESS and SPEAK into microphone NOTE Sidetone may be selected by placing the AUTO selector switch on audio control panel in either the SPEAKER or PHONE position Adjustment of sidetone may be accomp lished by adjusting the sidetone pot located inside the audio control panel b To Receive RELEASE mike button NAVIGATION OPERATION NOTE The pilot should be aware that on man...

Page 247: ... 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 ARC lamp to go out c To Obtain Continuous Bearing FROM V...

Page 248: ...AV ITO FROM indicator shows FROM 5 OBS Knob TURN to displace course approximately 10 to either side of 0 while holding ID VOX T to T Course deviation pointer deflects full scale in direction corresponding to course displace ment NAVITO 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 i...

Page 249: ...erating informa tion for the communication set and for VORl 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 inc...

Page 250: ...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 MHz In 0 position enables COM frequency readout to display and COM Fractional MHz Selector to select frequency in 05 MHz steps between 000 and 950 MHz NOTE The 5 or 0 may be read as the third decimal digit which is not displayed in the Com fractional freque...

Page 251: ...ed to adjust signal threshold necessary to activate COM receiver audio Clockwise rotation increases background noise decreases squelch action counterclockwise rotation decreases background noise to 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 CO...

Page 252: ...ition 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 RNA V course Figure 1 Cessna 300 Nav Com Set Operating Controls and Indicators Sheet 3 of 3 4 1 October 1978 ...

Page 253: ...re 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 co...

Page 254: ...7 Mike Button a To Transmit DEPRESS and SPEAK into microphone NOTE Sidetone may be selected by placing the AUTO selector switch on audio control panel in either the SPEAKER or PHONE position Adjustment of sidetone may be accomp lished by adjusting the sidetone pot located inside the audio control panel b To Receive RELEASE mike button NAVIGATION OPERATION NOTE The pilot should be aware that on man...

Page 255: ...dex 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 pointer should deflect full scale in direction correspond...

Page 256: ......

Page 257: ...ation 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 300 Transponder system required for Mode C altitude reporting operation consists of a completely indepe...

Page 258: ...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 either Mode 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 Sheet 1 ...

Page 259: ...ng 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 4...

Page 260: ...ENCY 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 4...

Page 261: ...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 262: ...LEMENT SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounte I antenna or several related external antennas will result in amino reduction in cruise performance 6 1 October 1978 ...

Page 263: ...lse 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 a standard 300 Transponder system is included in the avionic configuration the transponder can provide altitude...

Page 264: ... 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 either Mode A aircraft identification reply pulses or Mode C altitude reporting pulses selected automatically by the interrogating signal Figure 1 Cessna 300 Transponder and Encoding Altimeter Sheet 1 of 2 2...

Page 265: ...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 10 100 FOOT DRU...

Page 266: ... 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 4 NORMAL PROCEDURES BEFORE TAKEOFF 1 Function Switch SBY TO TRANSMIT...

Page 267: ...altimeter 2 Altitude Encoder Altimeter Setting Knob SET IN assigned local altimeter setting 3 Reply Code Selector Knobs 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 altitude is do...

Page 268: ...nce 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 1978 ...

Page 269: ...eading are sensed by the 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 Navoma...

Page 270: ...OT S OPERATING HANDBOOK SUPPLEMENT NAV 1 DIRECTIONAL GYRO TURN COORDINATOR NAV 2 r pIL O T UC0 jJ I I I I AILERON A I I I I I COMPUTER AMPLIFIER 2 Figure 1 Cessna 300A Autopilot Operating Controls and Indicators Sheet 1 of 2 1 October 1978 ...

Page 271: ...AV signal to provide more precise operation during localizer approach In low sensitivity position push button out response to NAV signal is dampened for smoothertracking of enroute VOR radials it also smooths out effect of course scalloping during NAV opera tion 9 BACK CRS PUSHBUTTON Used with LOC operation only With AlP switch OFF or ON and when navigation receiver selected by NAV switch is set t...

Page 272: ...rplane 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 1 AlP ON 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 engagin...

Page 273: ...80 185 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 lot...

Page 274: ... 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 kno...

Page 275: ... alerts 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 system used in conjunction with this radio for speaker phone selection is shown and described in Section 7 of this handbook The frequency range of the Cessna 400 ADF is electr...

Page 276: ... 400 ADF TYPE R 446A Off PILOT S OPERATING HANDBOOK SUPPLEMENT III 1 6 J lh f A IF O lEI I III l iJ I 111 111 11 BI c I A 2 Figure 1 Cessna 400 ADF Operating Controls and Indicator Sheet 1 of 2 1 October 1978 ...

Page 277: ...s 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 pointer stow 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 auto...

Page 278: ... 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 operating frequency 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 f...

Page 279: ... relative 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 rotat...

Page 280: ...ning level NOTE A 1000 Hz tone is heard in the audio output when 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 1978 ...

Page 281: ... 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 station information 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 282: ...SPLAY 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 position provides standar...

Page 283: ...OR lOC OPERATION VOR NAVIGATION CIRCUITS VERIFICATION TESTS 1 See appropriate N av Com supplement VOR LOC NAVIGATION As a convenience to the pilot a separate supplement Avionic Oper L 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 284: ...e 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 DISPLAY...

Page 285: ...HES 3 RNAV DSPL and FLY Switches DSPL set to 2 FLY set to 1 a Readout u DISPLAYS second waypoint bearing and distance b Fly Display Lamp On RNAV Control Head FLASHES 4 RNAV DSPL and FLY Switches u 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 u SET to RNAV a Both RN ...

Page 286: ...sted 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 8 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 RNAV...

Page 287: ...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 288: ... 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 NA V 1 frequency selector switches HOLD Selects DME memory circuit DME remains channeled to station to which it was channeled when HOLD was ...

Page 289: ...lows 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 s...

Page 290: ...efore the sys tem does not provide independent operation of the DME for reception of the DME Morse Code identifier 4 GS TTS Switch SET as desired 5 TEST ON OFF Switch HOLD to TEST a Distance to Station Display readout is 188 8 b Knots Minutes Display readout is 888 B TEST ON OFF Switch RELEASE to ON display readouts return to normal SECTION 5 PERFORMANCE There is no change to the airplane performa...

Page 291: ... 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 on the NAV receiver the associated glide slope frequency is selected automati cally Operation of the Cessna 400 Glide Slope system is controlled by the associated navigation syst...

Page 292: ...t The flag disappears when a re liable glide slope signal is being received i SAUTION 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 dis appear and present unreliable glide slope informa tion Disregard all glide slope signal indications when making a localizer back course approach un less a glide slope ILS ...

Page 293: ...0 RPM on airplanes equipped with a three bladed propeller dur ing ILS approaches to avoid oscillations of the glide slope deviation pointer caused by propeller interference 1 NAV Frequency Select Knobs SELECT desired localizer frequency 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 de...

Page 294: ......

Page 295: ...r beacon antenna This system provides visual and aural indications of 75 MHz ILS marker beacon signals as the marker is passed The following table lists the three most currently used marker facilities and their characteristics MARKER FACILITIES MARKER Inner Fan Middle Outer IDENTIFYING TONE Continuous 6 dots sec 300 Hz Alternate dots and dashes 1300 Hz 2 dashes sec 400 Hz LIGHT White Amber Blue Wh...

Page 296: ... and the INNER and FAN light is white 3 SPEAKER PHONE SWITCH SPKR PHN Selects speaker or phone for aural reception 4 HI LO TEST SWITCH In the HI position Up receiver sensitivity is posi tioned for airway flying In the LO position Center receiver sensitivity is positioned for ILS approaches In the TEST position Down the marker lights will illuminate indicating the lights are operational the test po...

Page 297: ...ening level 2 HI LO Sens Switch SELECT HI position for airway flying or LO position for ILS approaches 3 SPKR PHN Switch SELECT speaker or phone audio 4 TEST Switch PRESS and ensure that marker beacon indicator lights are operative 5 BRT Control SELECT BRT full clockwise ADJUST as desired when illuminated over marker beacon SECTION 5 PERFORMANCE There is no change to the airplane performance when ...

Page 298: ......

Page 299: ...oltage prevents loss of the preset frequencies when the Nav Com is turned off Both the communications and navigation operating frequen cies are digitally displa ledby 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 Wh...

Page 300: ...ckwise until noise is heard then back off slightly until it is quiet and you will have automatic squelch with the lowest practical threshold This adjustment should be rechecked periodically during each flight to assure optimum reception All controls for the Nav Com except the omni bearing selector OBS knob or automatic radial centering ARC knob which is located on the cours e deviation indicator a...

Page 301: ...BOOK SUPPLEMENT CESSNA 400 NAV COM TYPE RT 485A iC IC j I _ TYPICAL 300 SERIES INDICATORS TYPICAL 400 SERIES INDICATORS Figure 1 Cessna 400 Nav Com Type RT 485A Operating Controls and Indicators Sheet 1 of 4 1 October 1978 3 ...

Page 302: ...on by holding C pushbutton pressed for more than 1 7 seconds This lights each COM and NAV MEMORY pushbutton in turn and displays the corresponding preset frequency in MEMORY 4 NAVIGATION OPERATING FREQUENCY READOUT Indicates NAV fre quency in use 5 NAV MEMORY 1 2 3 PUSHBUTTONS When a NAV MEMORY pushbutton is pressed the preset selected frequency will appear in the NAV frequency window for use as t...

Page 303: ... reverse sense switch or autopilot s back course function is engaged and receiver is tuned to a localizer frequency indicates course deviation pointer is reversed 15 COURSE INDEX Indicates selected VOR COURSE 16 COURSE DEVIATION POINTER Indicates course deviation from selected omni course or localizer centerline 17 GLIDE SLOPE GS FLAG When visible red GS flag indicates unreliable glide slope signa...

Page 304: ... illuminates when Automatic Radial Centering is in use 23 COURSE CARD Indicates selected VOR course under course Index 24 OMNI BEARING SELECTOR OBS Rotates course card to select desired VOl radial 25 TO FROM INDICATOR TO FR Operates only with a Llsablc VOH 01 locallzcr signal When white flag is in view indicates whether selected course is TO 01 FROM station With usable localizer signal shows TO 26...

Page 305: ... 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 NAVar 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 opera...

Page 306: ...avoid use of 2700 100 RPM on air planes 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 deviation pointer caused by propeller interference 1 COM OFF VOL Control h TURN ON 2 SPEAKER PHONE or AUTO Switch on audio control panel h SET to desired mode 3 N A V Frequency Selection SELEC...

Page 307: ...center detent by the pilot 7 API CPLD Annunciator Light CHECK ON light is only operational if a 400B Autopilot or 400B IFCS is engaged amber light illuminated VOR SELF TEST OPERATION 1 COM OFF VOL Control TURN ON 2 N A V Frequency Selector Switches SELECT usable VOR station signal 3 OBS Knob SET for 00 course at course index course deviation pointer centers or deflects left or right depending on b...

Page 308: ...rrupted the MEMORY test will always start with the last COM ME MORY 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 of an externally mounted antenna or seve...

Page 309: ...R 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 NA V and 3 preset COM frequencies in MEMORY A keep alive voltage prevents loss of the preset frequencies when the NAV COM Switch Avionics Power Switch or Master Switch is turned OFF The RT...

Page 310: ... and an optional IN l048AC Course Deviation Indicator is also offered when Automatic Radial Centering ARC is desired When the optional IN l048AC 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 are...

Page 311: ...s 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 removed from the set s keep alive circui...

Page 312: ...p 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 and NAV 1 MEMORY will automatically be selected with t...

Page 313: ...OINTER Indicates course deviation from selected VOR or RNAV course or localizer centerline 20 OFF TO FROM INDICATOR Operates only with usable 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 21 RECIPROCAL COURSE INDEX Indic...

Page 314: ...OR or localizer signal When white flag is in view indicates whether selected course is TO or FROM station With usable localizer signal shows TO 25 AUTOMATIC RADIAL CENTERING ARC LAMP Amber light illuminates when Automatic Radial Centering isin use Figure 1 Cessna 400 Nav Com Set Operating Controls and Indicators Sheet 4 of 4 6 1 October 1978 ...

Page 315: ...shbut ton 1 momentarily to alert the memory bank of a forthcoming frequency to be stored 3 FREQUENCY SELECTORS MANUALLY ROTATE 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 MEMO...

Page 316: ...e AUTO selector switch on audio control panel in either the SPEAKER or PHONE position Adjustment of sidetone may be accomp lished by adjusting the sidetone pot located inside the audio control panel b XMIT Annunciator Light CHECK ON green light illumi nated c To Receive RELEASE mike button NAVIGATION OPERATION NOTE The pilot should be aware that on many Cessna airplanes equipped with the windshiel...

Page 317: ...l centering will automatically shut down causing the 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 course card will turn to center the course deviation pointer with a FROM flag to indicate bearing from VOR station This ...

Page 318: ...OM 6 ID VOX T Switch RELEASE for normal operation NOTE This test does not fulfill the 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 C...

Page 319: ...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 mount...

Page 320: ...et 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 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 1 o...

Page 321: ... 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 INDICATORS...

Page 322: ...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 323: ... 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 i...

Page 324: ...LEMENT 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 1978 ...

Page 325: ...coded pulse train reply signals on 1090 MHz It is capable of replying to Mode A aircraft identification and also to Mode C altitude reporting interrogations on a selective reply basis on any of 4096 information code selections When 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 re...

Page 326: ...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 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 Encoding Altimeter Operating Controls She...

Page 327: ...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 OOO 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 10 100 FOOT DRUM TYPE ...

Page 328: ...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 PROCEDURES BEFORE TAKEOFF 1 Function Switch SBY TO TRANSM...

Page 329: ...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 altitude is...

Page 330: ...ce 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 1978 ...

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