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Содержание 310 1975

Страница 1: ...Cessna ___ MORE PEOPLE BUY AND FLY CESSNA AIRPLANES THAN ANY OTHER MAKE 1975 WORLD S LARGEST PRO DUCER OF GENERAL AVIATION AIRCRAFT SINCE 1956 MODEL 310 OWNER S MANUAL...

Страница 2: ...EL CAPACITY TOTAL Sta dA xiiia y Tanks 40 gai sable With Auxiliary Tanks 63 gal usable With Auxiliary Tanks 63 gal usable and Wing Locker Tanks OIL CAPACITY TOTAL ENGINES Continental 6 Cylinder Fuel I...

Страница 3: ...s worldwide d Best in the industry Specific benefits and provisions of warranty plus other important benefits for you are contained in your Customer Care Program book supplied with your aircraft Warra...

Страница 4: ...Maximum height of aircraft with nose gear depressed is 10 11 3 4 31 11 i 17 0 PRINCIPAL DIMENSIONS ii 36 11 i DIAMETER 76 5...

Страница 5: ...ARE OF THE AIRCRAFT 5 1 OWNER FOLLOW UP SYSTEM 5 8 SECTION VI OPERATIONAL DATA 6 1 SECTION VII OPTIONAL SYSTEMS 7 1 ALPHABETICAL INDEX Index 1 This manual describes the operation and performance of bo...

Страница 6: ...WITCH OPTIONAL 6 OXYGEN CYLINDER PRESSURE GAGE OPTIONAL 7 HEATER AND CABIN AIR CONTROL PANEL iv 12 8 FLAP POSITION SWITCH 9 ALTERNATE AIR CONTROLS 10 AUTOPILOT CONTROL HEAD OPTIONAL 11 RUDDER TRIM CON...

Страница 7: ...briefly all the points that you should know con cerning the information you need for a typical flight The flight and operational characteristics of your aircraft are normal in all respects All control...

Страница 8: ...Switch ON Fuel Gages CHECK quantity and operation Wing Fla11s EXTEND Baggage Door SECURE Static Port s CLEAR Deice Boots CHECK condition and security if installed Control Surface Locks REMOVE elevator...

Страница 9: ...t CLEAR Leading Edge Air Intake CLEAR Crossfeed Lines DRAIN Fuel Sump Wing Locker Tank DRAIN if installed Maio Gea r Strut 1 Doors and Tire CHECK Fuel Quantity Wing Locker Tank CHECK cap secure if ins...

Страница 10: ...18 19 20 21 22 23 24 Landing Gear Position Indicator Lights CHECK press to test as required Cabin Air Controls AS REQUIRED Fuel Quantity CHECK Throttles OPEN ONE INCH Propellers FULL FORWARD Mixtures...

Страница 11: ...following procedures a With auxiliary fuel pump OFF allow manifold to drain at least 5 minutes or until fuel ceases to flow out of the drain under the nacelle b If circumstances do not allow natural d...

Страница 12: ...itions may develop when the engine is shutdown with the aux iliary fuel pump ON e During very hot weather caution should be exercised to prevent overpriming the engines e Should fuel priming or auxili...

Страница 13: ...Engine Runup a Throttles 1700 RPM b Alternators CHECK c Magnetos CHECK 150 RPM maximum drop with a maximum differential of 50 RPM d Propellers CHECK feathering to 1200 RPM return to high RPM full forw...

Страница 14: ...ORMAL TAKEOFF 1 8 1 Power FULL THROTTLE and 2700 RPM NOTE Apply full throttle smoothly to avoid propeller surging 2 Mixtures LEAN for field elevation NOTE Leaning during the takeoff roll at low altitu...

Страница 15: ...match field elevation to obtain maximum aircraft performance 3 Mixtures LEAN for field elevation 4 Elevator Control Raise nosewheel at 70 KIAS 5 Minimum Control Speed 81 KIAS 6 Break Ground at 82 KIAS...

Страница 16: ...stem fluctuating fuel flow or anytime when climbing above 12 000 feet turn the aux iliary fuel pumps ON until cruising alti tude has been obtained and the system is purged usually 5 to 15 minutes afte...

Страница 17: ...hes Hg and 2100 to 2500 RPM 2 Mixtures LEAN for desired cruise fuel flow as determined from your power computer Recheck mixtures if power altitude or OAT changes 3 Cowl Flaps AS REQUIRED 4 Fuel Select...

Страница 18: ...tude is lost 3 Cowl Flaps AS REQUIRED BEFORE LANDING 1 12 1 Fuel Selectors Left Engine LEFT MAIN feel for detent Right Engine RIGHT MAIN feel for detent 2 Auxiliary Fuel Pumps ON 3 Cowl Flaps AS REQUI...

Страница 19: ...5 Retract wing flaps as soon as all obstacles are cleared and a safe altitude and airspeed are ob tained NOTE Do not retract landing gear if another landing approach is to be conducted AFTER LANDING...

Страница 20: ...ition as fuel from the main tip tanks will transfer into the auxiliary tanks 7 Magnetos Switches OFF after engines stop 8 Battery and Alternators OFF 9 Parking Brake SET 10 Control Lock s INSTALL 11 C...

Страница 21: ...ight and trim tab controls should be double checked for free and correct movement and security The security of all inspection plates on the aircraft should be checked following periodic inspection Sin...

Страница 22: ...system To prevent loss of fuel in flight make sure main and auxiliary fuel tank filler caps are tightly sealed The main fuel tank vents beneath the tip tanks should also be inspect ed for obstructions...

Страница 23: ...lly while the engine is stopped with the throttle open and the mixture rich liquid fuel will collect temporarily in the cylinder intake ports The quantity of fuel collected will depend upon the amount...

Страница 24: ...onnected with the rudder system provides positive control up to 1s0 left or right and free turning from 18 to 55 for sharp turns during taxiing Normal steering may be aided through use of dif ferentia...

Страница 25: ...ore than 50 RPM continue warmup a minute or two longer before rechecking the stem If there is doubt concerning operation of the ignition system checks at higher engine speed will usually confirm if a...

Страница 26: ...ays should be employed for field elevations greater than 5000 feet above sea level Refer to the Pilot s Checklist for recommended fuel flows Full throttle operation is recommended on takeoff since it...

Страница 27: ...oblem Performance data for normal takeoff accelerate stop distance and single engine takeoff are presented in Section VI AFTER TAKEOFF To establish climb configuration retract the landing gear adjust...

Страница 28: ...and approximately 5 to 15 minutes after establishing cruising flight It is also recommended that the mixture remain at the climb mixture setting for approximately 5 minutes after establishing cruis in...

Страница 29: ...of the most favorable wind conditions are significant factors that should be considered on every trip to reduce fuel consumption Additional range can be achieved when operating at 55 power or less by...

Страница 30: ...will be approximately one knot greater than the speed with Recommended Lean mixture Operation at Best Power mixture will increase the life of the exhaust system and engine valves and rings For best p...

Страница 31: ...pressure available Therefore it is recom mended that the alternate induction air system be used only if icing conditions are expected Should additional power be required the following procedure should...

Страница 32: ...ward the inside of the direction of turn 5 Pull out of resulting dive with smooth steady control pressure LETDOWN Letdowns should be initiated far enough in advance of estimated landing to allow a gra...

Страница 33: ...the gear down indicator lights green is further proof that the gear is down and locked The gear unlocked indicator light red will illu minate when the gear uplocks are released and will remain illumin...

Страница 34: ...by using the crab method However either the wing low crab or combination method may be used Crab the aircraft into the wind in a normal approach using a minimum flap setting for the field length Imme...

Страница 35: ...lude any possible f4el seepage that might develop through the metering valve NOTE Do not leave the fuel selector handles in an intermediate position as fuel from the main tip tanks will transfer into...

Страница 36: ...the degree of night vision adaptation or exterior ambient light level changes Care should be exercised when increasing the intensity of illumination to preclude inadvertent deterioration of night visi...

Страница 37: ...pray or pour isopropyl alcohol MIL F 5556 on the brakes to remove the ice CAUTION If brakes are deiced using alcohol insure alcohol has evaporated from the ramp prior to starting engines as a fire cou...

Страница 38: ...ric auxiliary pumps in the main fuel tanks supply fuel for priming and starting and for engine operation as a backup system to the engine driven pumps See Figure 2 2 for Fuel System Schematic and opti...

Страница 39: ...THROTTLE MIXTURE CONTROL FUEL INJE CTION NOZZLE E UEL RIG T E U CONTROL UNIT LEFT ENGINE MANIFOLD 1 CONTllOL UNIT RIGHT ENGINE MANIFOLD DUAL INDICATOR fUU FLOW GAGE t 1 _ __ CODE C J FUELSUrPLY VAPOR...

Страница 40: ...e handles form the pointers for the selectors The ends of the handles are arrow shaped and point to the position on the selector placard which corres ponds to the valve position NOTE eThe fuel selecto...

Страница 41: ...he fuel flow gage see Figure 2 3 is a dual instru ment which indicates the approximate fuel consumption of each engine in pounds per hour The fuel flow gage used with the Continental injection system...

Страница 42: ...The fuel quantity indicators are calibrated in pounds and will accurately indicate the weight of fuel contained in the tanks Since fuel density varies with temperature a full tank will weigh more on...

Страница 43: ...ONICS AlJS AVIONJCS MASTER SWITCH TO AIRCRAFT SYSTE 15 MAIN BUS LF FT STARTFR BREAKER r BATTERY BllS EXT POWER RF LAY RIGHT R AI T FIELD CB LEFT OVERVOI TAGl RELAY OVFRVO TAGE R ALT FIF LD SW RF LAY n...

Страница 44: ...ed amount of time on the battery alone In either case a landing should be made as soon as practical to check and repair the circuits EMERGENCY ALTERNATOR FIELD SWITCH An emergency alternator field swi...

Страница 45: ...tem bus voltage can be monitored Immediate detection of low system voltage is provided by a LOW VOLT failure light located above the pilot s control wheel The light will illuminate when the aircraft b...

Страница 46: ...lying through clouds fog or haze The reflection of the flashing lights can cause disorientation or vertigo If optional strobe lights are installed refer to Section VII for addi tional information LAND...

Страница 47: ...functions independently of the other The warning horn is also connected to the UP position of the landing gear switch and will sound if the switch is placed in the UP position while the aircraft is on...

Страница 48: ...or gear LANDING GEAR HANDCRANK CD PILOT S SEAT CD RELEASE BUTTON CD HANDCRANK EXTENDED CD HANDCRANK STOWED STOWAGE CLAMP Figure 2 6 HEATING VENTILATING AND DEFROSTING SYSTEM A cabin heating ventilatin...

Страница 49: ...ed on the heater assembly the main fuel system auxili ary fuel pumps need not be turned on for proper heater operation On the ground the cabin heating system can be used for ventilation by placing the...

Страница 50: ...ABIN ftmi 1 DIRECTION AL AIR VENT AFT CABIN HEAT REGISTER AFT CABIN _ _ ___ DIRECTIONAL AIR VENT k I HEATED AIR UNHEATED VENTILATION AIR MECHANICAL ACTUATION Figure 2 7 2 30 AIR INLET FWD CABIN AIR FW...

Страница 51: ...orward cabin air knob control directs warm air to the outlet located on the forward cabin bulkhead This direct outlet allows fast warm up when the aircraft is on the ground Airflow through the direct...

Страница 52: ...e heater overheat switch has been actuated and that the temperature of the air in the heater has exceeded 325 F Once the heater overheat switch has been actuated the heater turns off and cannot be res...

Страница 53: ...from the wing root leading edge air inlets and ducts it to the directional vents The ventilating system functions only in flight since it depends entirely on ram air pressure For ground ventilation t...

Страница 54: ...ground to prevent overheating of the heating elements On later aircraft the main fuel tank vents are flush mounted and require no heaters With optional systems installed actuation of the pitot heat sw...

Страница 55: ...s pilots can demonstrate our concern for environ mental improvement by application of the following suggested procedures and the reby tend to build public support for aviation 1 Pilots operating aircr...

Страница 56: ...flight at low altitude near noise sensitive areas NOTE The preceeding recommended procedures do not apply where they would conflict with Air Traffic Control clearances or instruc tions or where in the...

Страница 57: ...Distance Chart in Section VI for various combinations of conditions ENGINE FAILURE AFTER TAK EOFF SPEED ABOVE 92 KIAS 1 Mixture AS REQUIRED for altitude 2 Propellers FULL FORWARD 3 Throttles FULL FOR...

Страница 58: ...rate of climb speed to f acili tate instant recognition The following paragraphs present a detailed discussion of the problems associated with engine failures during takeoff SINGLE ENGINE AIRSPEED NO...

Страница 59: ...gs should be banked 5 toward the operative engine Upon engine failure after reaching 92 KIAS on takeoff the multi engine pilot has a significant advantage over a single engine pilot for he has the cho...

Страница 60: ...g the takeoff is even more obvious at higher alti tudes where the corresponding distances are 4065 and 5250 respectively at 2000 feet Still higher field elevations will cause the single engine takeoff...

Страница 61: ...cessary Single engine procedures should be practiced in antici pation of an emergency This practice should be conducted at a safe altitude with full power operation on both engines and should be start...

Страница 62: ...I 1 I I I I I I I I I I I I I I 1ll lZ 0 0 0 rl 1 m1moommrrmm1mmr1111111111111111111rm l 1f 1111 i1 11 I 111111111 1111 1 111 P 40 0 40 80 120 1200 1400 1600 TEMPERATURE Op STANDARD TEMPERATURE CONDI...

Страница 63: ...ary 6 Oil Pressure and Oil Temperature CHECK shutdown engine if oil pressure is low 7 Magneto Switches CHECK If engine does not start secure as follows 8 Inoperative Engine SECURE a Throttle CLOSED b...

Страница 64: ...NCREASE slowly until cylinder head tem perature reaches 200 F Cowl Flaps AS REQUIRED NOTE If start is unsuccessful turn magneto switches OFF retard mixture to IDLE CUT OFF open throttle fully and enga...

Страница 65: ...IDLE CUT OFF 4 Battery OFF use gang bar 5 Magnetos OFF use gang bar 6 Evacuate aircraft as soon as practical IN FLIGHT WING OR ENGINE FIRE 1 Both Auxiliary Fuel Pumps OFF 2 Appropriate Engine SECURE a...

Страница 66: ...he engine com partment and wing leading edge and lower surfaces Leaks in the fuel system oil system or exhaust system can lead to a ground or airborne fire NOTE Flight should not be atempted with know...

Страница 67: ...e or smoke in the cabin should be controlled by identifying and shutting down the faulty system Smoke may be removed by opening the cabin air controls and wemacs If the smoke increases in intensity wh...

Страница 68: ...K AS 4700 102 5100 107 5500 111 SINGLE ENGINE APPROACH AND LANDING 3 12 1 Mixture FULL RICH 2 Propeller FULL FCRWARD 3 Approach at 97 KIAS with excessive altitude 4 Landing Gear DOWN within glide dis...

Страница 69: ...mooth grass covered runway if possible b Landing Gear Switch UP c Approach at 100 KIAS with flaps down only 15 d All Switches Except Magneto Switches OFF e Unlatch cabin door prior to flare out NOTE B...

Страница 70: ...s up landing as follows a Select a smooth grass covered runway if possible b Landing Gear UP c Approach at 97 KIAS with flaps down only 15 d Battery Switch OFF e Unlatch cabin door prior to flare out...

Страница 71: ...e main tank is unusablE NOTE If both an engine driven fuel pump and an auxiliary fuel pump fail on the same side of the aircraft the failing engine cannot be supplied with fuel from the opposite MAIN...

Страница 72: ...city ALTERNATOR FAILURE DUAL lndicoted by illumination of failure lights ond low voltage light 3 16 1 Electrical Load REDUCE 2 If Circuit Breakers are Tripped a Shut off alternators b Reset circuit br...

Страница 73: ...ts only when dual static system is installed 2 Excess Altitude and Airspeed MAINTAIN to compen sate for change in calibration NOTE eRefer to Pilot s Checklist for accurate airspeed and altimeter corre...

Страница 74: ...towed in its clip before the gear will operate electri cally When the handle is placed in the operating position it disengages the land ing gear motor from the actuator gear 1 Before proceeding manual...

Страница 75: ...ING GEAR WILL NOT RETRACT ELECTRICALLY 1 Do not try to retract manually NOTE The landing gear should never be retracted with the manual system as undue loads will be imposed and cause excessive wear o...

Страница 76: ...nt Right Engine RIGHT MAIN feel for detent Select a runway with a crosswind from the side opposite the defective tire if a crosswind landing is required Landing Gear Switch DOWN below 140 KCAS Check l...

Страница 77: ...ired 4 Land in a nose high attitude with or without power 5 Maintain back pressure on control wheel to hold nosewheel off the ground in landing roll 6 Use minimum braking in landing roll 7 Throttles R...

Страница 78: ...n in landing roll to lighten the load on the defective landing gear 11 Apply brake only on the operative landing gear to maintain directional control and minimize the landing roll 12 Fuel Selectors OF...

Страница 79: ...F 9 Hold nose off throughout ground roll Lower gently as speed dissipates DITCHING 1 Plan approach into wind if winds are high and seas are heavy With heavy swells and light wind land parallel to swel...

Страница 80: ...3 24...

Страница 81: ...markings placards and checklists in the aircraft If there is any information in this Owner s Manual that con tradicts the FAA approved markings placards and checklists it is to be disregarded MANEUVE...

Страница 82: ...a list of the calibrated airspeed limita tions for the aircraft Never Exceed glide or dive smooth air Caution Range Normal Operating Range Flap Operating Range Minimum Control Speed Best Single Engine...

Страница 83: ...rmal Operating Range Minimum and Maximum Fuel Flows 2100 to 2500 RPM green arc 2700 RPM red line 0 to 155 Lbs Hr green arc 0 and 155 Lbs Hr red line 2 5 and 21 7 PSI red line BAGGAGE COMPARTMENTS Five...

Страница 84: ...In all seating arrangements standard or optional baggage at Station 124 is limited to 160 pounds and must be secured by tie downs These tie downs are directly aft of the Station 96 baggage area and d...

Страница 85: ...the aircraft This chart applies only when the CG of the occupant is at the location specified under Moment Arms in Figure 4 2 If the seat is in any other position the moment must be computed by multip...

Страница 86: ...and 4 Optional 340 0 23 1 Seats 5 and 6 340 0 33 3 _i 4 Fuel gals x 6 lbs gal Main Tanks 100 gals 600 0 21 0 Aux Tanks 30 gals 179 5 8 4 Wing Locker Tanks 0 gals 5 Baggage Nose 40 0 1 2 Station 96 0 S...

Страница 87: ...CH POUND 25 Add the ight and moment of th loaded it ms to tfte licensed empty weight and moment of the a rcrah to determine the weight and center of gravily moments of the loaded aircraft JO J5 40 45...

Страница 88: ...1 1 1 5400 POUNDS VI 4 8 1 1 l Hi i l H 1 1 1 H t C z 0 Q g 4 4 1 1 1 H H t C w 40 i VI 0 36 32 4 8 0 0 0 0 F H H H 1ANV POINT FALLING WITHIN H H H1 1 1THE ENVELOPE MEETS ALL 11 BALANCE REQUIREMENTS...

Страница 89: ...you when lubrications and oil changes are necessary and about other seasonal and periodic services MAA IDENTIFICATION PLATE All correspondence concerning your Cessna should include the aircraft model...

Страница 90: ...lock 2 Tie strong ropes or chains 700 pounds tensile strength to wing tie down fittings 3 Caster the nosewheel to the extreme left or right position 4 Tie a strong rope or chain 700 pounds tensile str...

Страница 91: ...ver on the windshield unless freezing rain or sleet is anticipated Canvas covers may scratch the plastic surface PAINTED SURFACES The painted exterior surfaces of your new Cessna require an initial cu...

Страница 92: ...erial firmly and hold it for several seconds Continue blotting until no more liquid is taken up Scrape off sticky materials with a dull knife then spot clean the area Oily spots may be cleaned with ho...

Страница 93: ...F 3 Magneto Switches OFF 4 Propellers ROTATE CLOCKWISE Manually rotate propellers five revolutions standing clear of arc of propeller blades Keep fuel tanks full to minimize condensation in the fuel t...

Страница 94: ...TS As required by Federal Aviation Regulations all civil aircraft of U S registry must undergo a complete inspection annual each twelve calendar months In addition to the required ANNUAL inspection ai...

Страница 95: ...MER CARE PROGRAM Specific benefits and provisions of the CESSNA WARRANTY plus other important benefits for you are contained in your CUSTOMER CARE PROGRAM book supplied with your aircraft You will wan...

Страница 96: ...your Dealer concerning these requirements and begin scheduling your air craft for service at the recommended intervals Cessna Progressive Care ensures that these requirements are accomplished at the...

Страница 97: ...NGINE BOOKLET The applicable Owner s Manual is provided with each optional avionics installation The following additional publications plus many other supplies that are applicable to your aircraft are...

Страница 98: ...apers latest copy of the Repair and Alteration Form Form FAA 337 if applicable 2 Aircraft Equipment List 3 Pilot s Checklist C To be made available upon request 1 Aircraft Log Book 2 Engine Log Books...

Страница 99: ...rom actual flight tests with the aircraft and engines in good condition and using average piloting techniques Note that the cruise performance charts make no allowance for wind and navigation al error...

Страница 100: ...m Flap Speed 140 KCAS 35 NOTE The above calibrations are valid for pilot s and copilot s airspeed indicators when using normal static source only Refer to Pilot s Checklist if alternate static source...

Страница 101: ...7200 6400 4800 5600 TOTAL DISTANCE TO CLEAR 50 FOOT OBSTACLl FEET STANDARD TEMPl RATURE CONIHTION S EXAMPLE 1 Level Ha rd Surface Ru11 ay 2 Wrng Flaps L p 3 Full Throttle and 2700 RPM l lelore l1elea...

Страница 102: ...S EXAMPLE 1 Level l lard Surface Runway A Temperature B0 F 2 Wing Flaps UP B Pressure Altitude 2000 Feet 3 Full Throttle and 2700 RPM Before Ile leasing Brakes C Gross Weight 5100 Pounds 4 Mixture at...

Страница 103: ...off on Sin lc Engine is Improbable Belmt So re Single Engine Speed See Section Ill 2 Single J nginC Control 1s Improbable Uelow Minimum Cun l r0 l Spc d Figure 6 5 90 CONDITIONS 1 Level Hard Surface R...

Страница 104: ...2 Wing Flaps UP 3 Full Throttle and 2700 RPM Before Releasing Brakes 4 Mixture at Reconunended Fuel Flow 5 Engine Failure at Takeoff Speed 6 Propeller Feathered and Gear Retracted During Climb 7 Maint...

Страница 105: ...Lbs Lbs Lbs 107 1662 24 103 1264 40 99 870 57 95 475 81 91 82 138 NOTE FULL THROTTLE 2700 RPM MIXTURE AT RECOMMENDED FUEL FLOW FLAPS AND GEAR UP AND COWL FLAPS AS REQUIRED FUEL USED INCLUDES IVAIDI U...

Страница 106: ...122 90 13 4700 98 520 95 414 92 305 89 197 86 90 NOTE Flaps and gear up inoperative propeller feathered wings banked 5 toward operating engine full throttle 2700 RPM and mixture at recommended fuel fl...

Страница 107: ...500 POUNDS GROSS DIGHT NOTE See Range Profile Figure 6 12 for range including climb CRUISE PERFORMANCE WITH RECOMMENDED LEAN MIXTURE AT 5000 FT Range Range Range Total Endurance 800 Lba Endurance 978...

Страница 108: ...0 POUNDS GROSS WEIGHT NarE See Range Profile Figure 6 12 for range including climb CRUISE PERFORMANCE WITH RECOMMENDED LEAN MIXTURE AT 10 000 FT Range Range Range Total Endurance 600 Lbs Endura nce 97...

Страница 109: ...4 128 4 69 770 7 65 1255 9 53 1564 15 0 44 8 153 118 5 10 780 8 32 1272 10 34 1581 14 Q 40 7 136 108 5 57 772 9 07 1257 11 30 1566 2300 16 0 45 5 155 116 5 04 783 8 22 1277 10 24 1590 15 0 41 7 143 11...

Страница 110: ...1 I I I 1000 1050 1100 1150 1200 1250 1300 1350 1400 1450 1500 APPROXIMATE RANGE NAUTICAL MILES 1218 POUNDS USABLE FUEL NOTES 1 Maximum Range is not Changed Appreciably with Variations in Climb Power...

Страница 111: ...Obstacle Run Obstacle Run Obstacle Run Obstacle 5400 93 640 1790 689 1839 742 1892 801 1951 5000 89 540 1690 582 1732 627 1777 677 1827 4600 86 450 1600 484 1634 522 1672 563 1713 4200 82 368 1518 39...

Страница 112: ...6 14...

Страница 113: ...bus through a circuit breaker located aft of the battery box and to the individual avionics circuit breakers and is used for all normal operations An emergency avionics master switch breaker labeled E...

Страница 114: ...spring loaded to center allows checking fuel quantity in the tanks not selected The switch adjacent to the auxiliary tank indicator lights is labeled MAIN and AUX By positioning the switch to the app...

Страница 115: ...uired to maintain fuel balance after wing locker fuel has been transferred NOTE Wing locker transfer pump switches provided on the instrument panel energize the wing locker fuel transfer pumps for tra...

Страница 116: ...l 6 7 Hrs 3 8 p r 2 9 Hrs 3 Persons D Duration 46 3 Cu Ft 5 5 Hrs 3 5 p 1 8 Hrs 3 Persons OXYGEN DURATION CALCULATION lli ygen Duration Hrs No of Persons Duration Hrs 7 8 l 9 10 II 12 13 U 15 16 17 18...

Страница 117: ...sition NOTE If the oxygen knob is left in an inter mediate position between ON and OFF it may allow low pressure oxygen to bleed through the regulator into the nose compartment of the aircraft Before...

Страница 118: ...ure is 70 F fill oxygen cylinder to approximately 1925 psig as close to this pressure as the gage can be read Upon cooling the cylinder should have approxim tely 1800 psi pressure Figure 7 2 OXYGEN SY...

Страница 119: ...is a permanent type mask while the remainder are the semi permanent type They may be cleaned with alcohol or used as disposable masks Additional masks and hose assemblies are available from your Cess...

Страница 120: ...lete inflation and deflation cycle will last approximately 30 seconds In Flight 1 When ice has accumulated to approximately 1 2 inch thick on the leading edges position deice switch to ACTUATE After L...

Страница 121: ...ents subject to icing The deice system will operate satisfactorily on either or both engines During single engine operation suction to the gyros will drop momentarily during the boot inflation cycle D...

Страница 122: ...ion 3 Ammeter CHECK NOTE e Periodic fluctuation within the green arc of the propeller deice ammeter pointer indi cates normal operation of the deicing ele ments of first one propeller and then the oth...

Страница 123: ...alance and engine failure DUAL HEATED PITOT STATIC SYSTEM The dual heated pitot static system consists of a pitot head located on each side of the fuselage nose cap the pilot s and copilot s pitot sta...

Страница 124: ...emperatures The pump located adjacent to the tank provides positive pressure to the windshield dispersal tubes The left and right hand dispersal tubes located at the forward base of the windshield pro...

Страница 125: ...d be 140 KIAS or below for best results 2 Windshield CHECK allow approximately 10 seconds for alcohol flow to begin 3 When windshield ice is removed windshield deice switch breaker OFF WARNING The win...

Страница 126: ...ompanying unsynch ronized operation the propeller synchronizer can also pro vide a significant reduction in cabin vibration by maintain ing an optimum angular or phase relationship between the two pro...

Страница 127: ...rich mixture for engine cooling Leaner mixtures are not recommended for power settings in excess of 75 2 In level flight at less than 75 power lean the mixture to peak EGT then enrich as desired using...

Страница 128: ...ches Leaning technique for cruise descents may be with EGT reference method at least every 5000 feet or by simply enriching to avoid engine roughness DESCRIPTION EXHAUST GAS TAS LOSS RANGE INCREASE MI...

Страница 129: ...cator CHECK NOTE To check the operation of the disengage switch actuate the elevator trim switch with the disengage switch in the disengage position Observe that the manual trim wheel and indicator do...

Страница 130: ...aft baggage shelf and direct conditioned air into the cabin The compressor and condenser module located in the aft cabin liquify the Freon gas and remove the heat absorbed by the evaporators The heat...

Страница 131: ...Before Takeoff 1 Air Conditioning Switch OFF or VENTILATE After Takeoff 1 Air Conditioning Switch AS DESIRED 2 Blower Switch AS DESIRED Before Landing 1 Air Conditioning Switch OFF or VENTILATE After...

Страница 132: ...function is provided to test the system circuit ry When the test switch is pushed all lights should illu minate if any light fails to illuminate replace the bulb If the green light does not illuminat...

Страница 133: ...ol NORMAL PROCEDURES Before Takeoff 1 Press the test switch all lights should illumin ate EMERGENCY PROCEDURES If a fire warning light indicates an engine compartment fire and is confirmed or if a fir...

Страница 134: ...y removing the plug button located adjacent to the locator beacon placard Normally the switch is in the ARM AUTOMATIC G OPERATION position this position allows the transmitter to be activated auto mat...

Страница 135: ...ft sensor is located in the leading edge of the left wing The standard aircraft stall warning system is removed and its function is assumed by the angle of attack system For a normal approach to landi...

Страница 136: ...rior to flight When the test button is pressed the pointer should move to the SLOW end of the scale and the stall warning horn should sound MANUAL AND ELECTRICAL ADJUSTABLE SEATS The optional manually...

Страница 137: ...t Rotating the handcrank 1 Figure 7 6 at the forward right hand corner of the seat tilts the back Rotating the handcrank 2 Figure 7 6 at the forward left hand corner of the seat raises and lowers the...

Страница 138: ...fore and aft adjustment lever 3 Figure 7 7 is located at the forward side of the seat near the center Both engines should be started prior to making tilt or vertical adjustments to the seats or pre c...

Страница 139: ...t or during flight through clouds fog or haze The strobe light system consists of three strobe light assemblies with individual power supplies Each wing tip contains a strobe light and power supply lo...

Страница 140: ...7 28...

Страница 141: ...Avionics Master Switches 7 1 B Balance Weight and 4 4 Baggage Compartments 4 3 ALPHABETICAL INDEX Tie Down 4 4 Battery and Alternator Switches 2 24 Beacon Locator 7 22 Before Landing 1 12 2 13 Before...

Страница 142: ...partment Baggage 4 3 Console Overhead 2 34 Contents Table of iii Cruise 2 8 Cruising 1 11 Cylinder Head Temperature 4 3 Index 2 D Defrost Knob Defrosting and Heating Deice Alcohol Windshield Deice Boo...

Страница 143: ...6 External Power Source Starting 1 6 F File Aircraft 5 9 Fire Detection and Ex tinguishing System 7 20 Fire Procedures 3 9 Flight Instruments Flight Maneuvering Flyable Storage Flying Night Forced La...

Страница 144: ...recautionary With Power 3 13 Gear Handcrank 2 27 Gear Position Lights 2 26 Gear System 2 26 3 18 Gear Warning Horn 2 27 Index 4 Letdown 1 12 2 12 Limitations Airspeed 4 2 Loading Chart 4 5 4 7 Locator...

Страница 145: ...Electric Manual 6 12 Critical Inoperative 3 6 5 8 Secure Aircraft Servicing Requirements 4 6 7 24 7 26 7 25 1 13 5 8 Single Engine Airspeed Nomenclature Approach and Landing Climb Data Service Ceiling...

Страница 146: ...ump Failure 3 17 Ventilating System 2 33 Ventilation Heater Used For 2 33 Voltamrneter 2 24 Index 6 w Weight and Balance 4 4 Windows and Windshield 5 2 Windshield Alcohol Deice 7 12 Wing Locker Fuel S...

Страница 147: ...he Emergency Procedures section of your aircraft Owners Manual This supplement is applicable to all Models 310C D F G H i J K L N P Q and R 0001 thru 0500 aircraft The purpose of this supplement is to...

Страница 148: ...Fuel Selector AS REQUIRED Feel For Detent NOTE Auxiliary fuel on the side of the failed engine is unusable Position operative engine fuel selector to MAIN TANK and feel for detent if below 1000 feet A...

Страница 149: ...reaches 1000 RPM h Auxiliary Fuel Pump AS REQUIRED to prevent fuel flow fluctuations i Mixture AS REQUIRED j Power INCREASE after cylinder head temperature reaches 2000F with gradual mixture enrichme...

Страница 150: ......

Страница 151: ...n MEB88 3 The information contained herein supplements or supersedes the information contained in the form of placards markings manuals and checklists For limi tations and procedures not contained in...

Страница 152: ...ing The toggle need not be pulled to return the switch to OFF In Models 340A 414 421 421A and 421B additional fuel tank selector logic is added to activate the auxiliary fuel tank system in line fuel...

Страница 153: ...total loss of engine power may occur When performing training in single engine operations the auxiliary fuel pump of the engine to be shutdown should be turned OFF if it was on LOW prior to any simula...

Страница 154: ...4 SECTION 3 EMERGENCY PROCEDURES ENGINE FAILURE DURING FLIGHT BEFORE SECURING INOPERATIVE ENGINE Fuel Flow CHECK If deficient position auxiliary fuel pump to HIGH IF ENGINE DOES NOT START Operative En...

Страница 155: ...necessary to suppress vapor CRUISE Above 12 000 Feet Auxiliary Fuel Pumps LOW for 5 minutes after leveling off to suppress vapor tendencies DESCENT Auxiliary Fuel Pumps LOW BEFORE LANDING Auxiliary Fu...

Страница 156: ...RY FUEL PUMP SWITCHING SYSTEM SUPPLEMENTAL AIRPLANE FLIGHT MANUAL SECTION 5 PERFORMANCE There is no change in airplane performance with the auxiliary fuel pump switching system modification 6 Original...

Страница 157: ...P SWITCHING SYSTEM IN THIS AIRPLANE HAS BEEN MODIFIED IN COMPLIANCE WITH SERVICE BULLETIN MEB88 3 OPERATE THE AUX ILIARY FUEL PUMPS PER SEPARATE SUPPLEMENT FURNISHED RATHER THAN PROCEDURES IN THIS PUB...

Страница 158: ......

Страница 159: ...NOTE For faster ring seating and improved oil control your Cessna was delivered from the factory with straight mineral oil non detergent conforming to specification MIL L 6082 This break in oil must b...

Страница 160: ...TAKE YOUR CESSNA HOME FOR SERVICE AT THE SIGN O THE CESSNA SHIELD CESSNA AIRCRAFT COMPANY WICHITA KANSAS...

Страница 161: ...REMOVED 18 Items 38 50 18 29 704 34 INSTALLED GARMIN GA35 SIN 10037 0 60 42 00 25 20 GAR fN GA 35 S N 10C42 0 60 42 00 25 20 GARMIN GA55 SIN 87504955 0 50 42 00 21 00 GARMIN GDL 69A SIN 42703927 2 80...

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