CESSNA CESSNA MORE PEOPLE SUY AND FLY CESSNA AIRPLANES THAN ANY OTHER MAKE "TAKE YOUR CESSNA HOME FOR SERVICE MODEL AT THE SIGN OF THE CESSNA SHIELD" I 1960 CESSNA AIRCRAFT COMPANY WICHITA.
Congratulations . . . . . . Welcome to the ranks of Cessna owners! Your Cessna has been designed and constructed to give you the most in performance, economy, and comfort. You will find flying it, either for business or pleasure, a pleasant and profitable experience. This Owner's Manual has been prepared as a guide to help you get the most pleasure and utility from your airplane.
1------------ 211'-7"-------i Table of Contents * If J:Otatlng beacon is installed on vertical fin, add 3" to maximum height o( alrpla.D.e. :==:=::==:=:=:=:=:=::=:==:=::=:=:==:=:=::=:=:=:==::page=: SECTION I DESCRIPTION . 1-1 SECTION II NORMAL PROCEDURES . 2-1 SECTIONffi OPERATING DETAILS . 3-1 SECTION IV EMERGENCY PROCEDURES 4-1 SECTIONV OPERATING LIMITATIONS 5-1 SECTION VI CARE OF THE AIRPLANE 6-1 DEALER FOLLOW -UP SYSTEM SECTION VII - OPERATIONAL DATA ALPHABETICAL INDEX . • . . • .
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Description is blocked, regardless l'Pomon of the induction air control handles. IGNITION SWITCHES. The four ignition switches control the dual magnetos on each engine. The switches may be operated individually; or by using a hinged bar mounted above them, all four may be turned off at once. For normal operation, all four switches should be ON. Individual switches should be turned off only for checking purposes. When the engines are stopped, all four switches should be OFF (down). STARTER BUTTONS.
Description Description back cover for the recommended oil specification, grades, and servicing intervals. OIL SYSTEM INSTRUMENTS. An electric oil temperature gage and a direct- reading oil pressure gage are included in the engine gage unit for each engine. A green arc on each gage dial indicates the normal operating range. Refer to Section V for instrument markings. OIL DILUTION SYSTEM.
D~acription AUXILIARY FUEL PUMP SWITCHES. Th~ auxiliary fuel pump switches are three-position switches, marked ·ON, OFF and PRIME. The PRIME positionruns the pumps at low speed, providing approximately 5 psi pressure for priming and starting. The ON position also runs the pumps at low speed, as long as the enginedriven pumps are functioning. With the switch in the ON position, however, if an engine-driven pump fails, . the auxiliary pump on that side will "be switched to high speed automatic.
Desel'iption Description ing the lower right wing root fairing. Recommended intervals for draining the sumps, strainers and fuel lines are given in the Servicing Diagram on pages 6-6 and 6-7, and in Section II. SWITCH & CONTROL PANELS I ELECTRICAL POWER SUPPLY SYSTEM. = -==- - =-= Electrical energy is supplied by a 28-volt, negative-ground, directcurrent system, powered by a 25ampere engine-driven generator on each engine. A 50-ampere generator system is available as optional equipment.
:Qes~ription Description TO OPTIONAl RADIO o5o TO OPTIONAL RADIO TO OPTIONAL RADIO TO OPTIONAL RADIO RIGHT GENERATOR SWITCH LEFT GENERATOR SWITCH Number under drcuit breaker denol~l ils amperage capacity. TO OPTIONAL RADIO TO OPTIONAL RADIO TO AUTOMATIC PILOT (OPT) TO FLARES (OPT) TO PITOT HEAT TO STALL WARNING HEAT TO LEFT ENGINE GAGE TO LEFT LANDING LIGHT MOTOR GENERATOR GENERATOR TO LEFT AUXILIARY FUEl PUMP TO OUTSIDE AIR TEMP.
Description Description the elevator is fitted with a downspring for improved longitudinal stability. A bungee interconnects the ailerons and rudder, for better lateral stability in certain flight maneuvers. CONTROLS LOCK. The controls lock, normally kept in the map compartment, should be installed on the pilot's control column whenever the airplane is parked.
Description Description position disconnects the electrical circuit. The OFF position need be used only when lowering the gear with the handcrank. LANDING GEAR HANDCRANK. The handcrank for manually lowering the landing gear is located just below the right edge of the pilot's seat. Normally, the crank is folded and stowed in a clip beside the seat. To use the crank, pull it out from its storage clip and unfold it until it locks in operating position.
Description Description is composed of an electrically-heated pitot tube mounted on the nose of the fuselage, an external static-pressure port on each side of the fuselage aft of the baggage area, and the plumbing to connect the instruments to the sources. NOTE The static -pressure openings should be kept free of polish, wax, and dirt for proper instrument operation. STATIC PRESSURE ALTERNATE SOURCE VALVE.
Description II • + Description CODE which shuts off the heater when the duct temperature reaches approximately 220°F. When the duct temperature drops to a normal operating level, the heater will restart automatically. The action of this switch is independent of the cabin thermostat setting, and it is not adjustable in flight. FRONT HEAT REGISTER TAB (ONE EACH SIDE) OUTSIDE AIR • • REGISTERS OPEN • REGISTERS CLOSED • UNHEATED AIR HEATEDAIR CABIN AIR KNOB.
Description Description FUEL SELECTOR VALVE LIGHT. The fuel selector valve handles and the lower pedestal are illuminated by a light mounted on the forward side of the front spar. The light is controlled by the rheostat labeled SWITCH PNL - FUEL SEL. MAGNETIC COMPASS LIGHT. The magnetic compass, mounted on the windshield centerstrip, contains an integrally-mounted light. The light is controlled by the rheostat labeled COMPASS. DOME LIGHTS.
Description able rear seats, identical to the pilot's and copilot's seats; (3) one adjustable rear seat on the right side and a lounge on the left side behind the pilot's seat; (4) two adjustable rear seats plus a non-adjustable seat located in the left, aft end of the cabin. Folding arm rests are standard equipment on all single seats.
Description Description The door lock, located above the outside handle, is operated with the same key used for the baggage door. It is unlocked by turning it approximately a half turn. OUTSIDE DOOR HANDLE. To operate the outside cabin door handle, first press the aft end of the handle and pull the handle out of its recess. Rotate the handle up and back to open the door. Once the door is opened, return the handle to its recess.
Description ..........~mn:P..n~.l.U..... d-. . Normal Procedures 310 D G) a. Remove controls lock. ® a. Remove external surface locks. lf installed. b. b. c. @ a. ~ EXTERIOR INSPECTION MotnentarUy turn on battery switch, and check: fuel quantity gages. Check oxygen pressure. Check general cClnd.ltlon of elevator, rudder and trim tab hinges, hinge bolts and actuator rod bolts, Remove tie-down. b. Cheek static pressure source hole tor obstruction.
Normal Procedures Normal Procedures (4) Check landing gear switch -DOWN. (5) Battery switch -ON. NOTE When using an external power source, do not turn on the battery until external power is disconnected, to avoid a weak battery draining off part of the current being supplied by the external source. (6) Generator switches - ON. NOTE If 50-ampere generators are installed, turn on one at a time as the engines are started. (7) Check circuit breaker panel for faulty circuits.
Normal "Procedures" Normal Procedures (11) Place eaeh propeller pifch:lever in the. FEATHER position until engine speed drops to .1200 RPM, then. return to iulL:forward position. NOTE If propeller operation has. been unusually sluggish onerratic, fea- ther pr.opeller twice to. 600 RPM in· run-up, retarding throttle as necessary to avoid excessive manifold pressure at low RPM. Exercising. the propeller in this manner insures .opj:imum propeller governing in flight.
Normal Procedures Normal Procedures AFTER LANDING. LET-DOWN. (1) Reduce power to obtain desired let-down rate at cruising speed. (2) Set mixture levers full forward (FULL RICH). (3) For steep let-downs, decrease speed to 160 MPH or less and extend flaps 15°. If necessary, for steeper let-downs, reduce speed to 140 MPH and extend landing gear. NOTE Avoid steep, power-off let-downs with low fuel. (1) Retract flaps. (2) Park with nosewheel aligned straight ahead if possible.
Normal Procedures vf/ol1s ..........~HJP..!.LL.. LLL~ + ~ Operating Details THIS SECTION GIVES, in narrative form, detailed information on those· check list items in S~ction II that require further explanation. PREFLIGHT CHECK. The exterior inspection described in Section n is recommended for the first flight of the day. Inspection procedures for subsequent flights are normally limited to brief checks of the tall surface hinges, fuel and oil quantity, and security of fuel and oil filler caps.
Operating Details Operating Details tires and brakes. If the airplane is equipped with auxiliary fuel tanks, make sure that the filler caps are tightly sealed to prevent loss of fuel in flight. The auxiliary fuel tank vents beneath the wing should also be inspected for obstructions, especially after operation from muddy fields. The interior inspection will vary accord,ing to the mission and the optional equipment installed.
·operating Details Operating Details MINIMUM GROUND CLEARANCE: PROPELLERS - 9" airplane should be returned to the tie-down location and the malfunction ··corrected. The operation of the turnand-bank indicator and directional gyro should also be checked during taxiing. Most of the engine warm-up should be done during taxiing, with just 3-4 enough power to keep the airplane moving. Engine speed should not exceed 1600 RPM while the oil is cold. BEFORE TAKE-OFF.
Operating Details Operating Details there is less chance of tire damage with heavy braking since more weight remains on the main wheels with flaps retracted. Full throttle operation is recommended on take-off since it is important that a speed well above minimum single-engine control speed (82 MPH) be obtained as rapidly as possible. It is desirable to accelerate the airplane to 95 MPH while still on the ground for additional safety in case of an engine failure.
Operating Details Operating·Details · pressures on the low-pressure side of the take-off and climb dial range to assure maximum.p~wer and adequate engine cooling. If' an obstruction ahead requires a steep. climb angle, the airplane, should be flown at ·the best angle ..ofclimb speed with flaps up and maximum p9Wer. This·speed varies··from 97 MPH'at sea level.hll l06·. MP.H at 15,000 feet. CRUISE. Tabulated cruising information for normal cruising power and altitudes is presented in Section VII.
Operating Details Operating Details ~~:::::::::STALL SPEED CHART====~=== MPH- TIAS 4830 POUNDS GROSS WEIGHT SPINS. ::::::::::::::;:;:;:;:;:;::::::::~:;:;:;:;:;:;:;:;:;:;:~;:;:;:;:;:;::::.
Operating Details Operating Details LET-DOWN. Let-downs should be initiated as much as an hour before estimated landing time to permit a gradual rate of descent at cruising speed using enough power to keep the engines warm and the cylinders clear. Since the airplane is so aerodynamically clean it is difficult to descend rapidly without reducing power to very low settings. This results in undesirably low cylinder head temperatures, which in turn lead to spark plug fouling.
Operating Details Operating Details edges of the wing tip tanks and re. flection from the pavement or ground · below the taillight. The retractable landing lights (the right landing light is optional equipment) may be extended and checked momentarily. Returning the landing light switches to OFF turns the lights off but leaves them extended ready for instant use. Before taxi, the interior lighting intensity is normally decreased to the minimum at which all the controls and switches are visible.
Operating Details Operating Details I 1 OIL DILUTION TABLE TEMPERATURE 0°F Dilution Time Fuel Added • I -10°F ! -20°F 2 min. 5 min. 8 min. 1 qt. 2.5 qt. 4qt. MAXIMUM SUMP CAPACITY--16 qt. MAXIMUM FOR TAKE-OFF-- 13 qt. for the first time each season, the oil should be changed and the oil screens cleaned to remove sludge accumulations washed down by the fuel.
Operating Details that red indicator disappears when hose is inserted into coupling, to insure that oxygen is flowing. (5) Disconnect mask hoses from overhead console panel when not in use. ..........dt.JJP..!.tL.. .tv..... 4- . Emergency Procedures 1500 I I I I ENGINE FAILURE. 1;;; -=.,; ENGINE FAILURE DURING TAKE-OFF BELOW 95 MPH . a: (1) Cut power on operative engine and decelerate to a stop.
Emergency Procedures SUPPLEMENTARY INFORMATION CONCERNING ENGINE FAILURE DURING TAKE-OFF. The most critical time for an engine to fail in a twin-engine airplane is during a two- or three -second Emergency Procedures period late in the take-off run while the airplane is accelerating to a safe engine-out climb speed.
Emergency Procedures Emergency Procedures At sea level, with zero wind and 4830 pounds gross weight, the distance to accelerate to 95 MPH and stop is 2390 feet, while the total unobstructed area required to takeoff and climb over a 50-foot obstacle after an engine failure at 95 :MPH is 2265 feet.
Emergency Procedures Emergency Procedures (3) Check oil pressure and oil temperature indications. Shut down engine if oil pressure is low. (4) Check ignition switches. If proper corrective action was taken, engine will restart. secure it as follows: 20000 (1) Mixture lever -IDLE CUT-OFF. (2) Propeller lever - FEATHER. (3) Turn off auxiliary fuel pump, generator, ignition switches and fuel selector valve.
Emergency Procedures Emergency Procedures IMPORTANT If flare-out is sustained with m ooerate power, cutting power suddenly will result in a hard landing. To avoid this, reduce power to a minimum in flare-out before turning off ignition switches. (f) Land in a slightly tail-low attitude. {g) Hold wheel fully back in initial slide to keep nacelles from possibly "digging in" in rough terrain. NOTE Airplane will slide straight ahead about 500 feet on smooth sod with very little damage.
Emergency Procedures Emergency Procedures tank with the operative auxiliary fuel pump. The engine with the operative engine-driven fuel pump should be fed from the tank containing the inoperative auxiliary fuel pump. This will permit all fuel to be used from the main tanks. However, it is impossible to use fuel from the auxiliary fuel tank on the same side as the inoperative engine-driven fuel pump. Land as soon as practical if fuel pressure indication remains below normal.
Emergency Procedures Emergency Procedures to ground immediately, for positive steering. (10) Use full aileron in landing roll, to lighten load on defective tire. (11) Apply brake only on the inflated tire, to minimize landing roll and maintain directional control. (12) Stop airplane to avoid further tire and wheel damage, unless active runway must be cleared for other traffic. LANDING WITH FLAT NOSE GEAR TIRE.
Emergency Procedures power to maintain approximately 300 ft/min. rate of descent at approximately 95 MPH at 3500 pounds, to 108 MPH at 4600 pounds gross weight. (3) Maintain a continuous descent until touchdown to avoid flaring and touching down tail-first, pitching forward sharply, and decelerating rapidly. Strive for initial contact at fuselage area below rear cabin section (point of maximum longitudinal curvature of fuselage).
Operating Limitations Operating Limitations Maximum Speed, Landing Light Extended Maximum Speed, Pilot's Window Open . Maneuvering Speed* . . . . • . . . . 160 MPH 130 MPH 164 MPH CYLINDER HEAD TEMPERATURES. Normal Operating Range Maximum Temperature *(The maximum speed at which you can use abrupt control travel or fly through extremely turbulent air without exceeding the design load factor.) TACHOMETER. Normal Operating Range . . . . . . . 2100-2450 RPM (green arc) Maximum (Engine rated speed). . .
Operating Limitations Operating Limitations ••ool-f- I. ee«kt ~. e~ ~ t;. ?lt-e , .. .1. L J.__l__ I I I L SAMPLE PROBLEM ~ g Example for an airplane with a licensed empty weight of 3125.0 lbs., a moment of 106.0 thousand pound-inches, 24 quarts of oil, a pilot, a front seat passenger, three rear seat passengers, 100 gallons of fuel in the main tanks, and 180 pounds of baggage. t: ;! .~ ~ Welght in pounds 0 AIRCRAFT LICENSED EMPTY WEIGHT. , , , 3125.
Operating Limitations ~Its ..........~~JJP.JL£:J.L. d-. .. Care of the Airplane IF YOUR AIRPLANE isto retainthat new-planeperformanceand dependability, certain inspection and maintenance requirements must be followed. It is wise to follow a planned schedule of lubrication and preventive maintenance based on the climatic and flying conditions encountered in your locality. Keep in touch with your Cessna Dealer, and take advantage of his knowledge and experience.
Care of the Airplane Care of the Airplane (6) Set the parking brake or use wheel chocks. STORAGE. The all-metal construction of your airplane makes outside storage practical. However, inside storage will increase its life just as it does for your car. Cleanliness is important under any condition. While the airplane is stored, pull the propellers through several revolutions every few days to keep the engine bearings, cylinder walls, and other internal parts oiled.
Care of the Airplane Care of the Airplane quire disassembly must be done by an FAA-authorized propeller repair station. For this work, too, your Cessna Dealer will be happy to help you. INTERIOR CARE. Keeping the inside of your airplane clean is no more difficult than taking care of the rugs and furniture in your home. It is a good idea to occasionally take the dust out of the upholstery with a whisk broom and a vacuum cleaner.
Care of the Airplane 0 D 0 0 Care of the Airplane CODE: Service Daily Service Every 25 Hrs. SERVICING DIAGRAM Service Every 100 Hrs. 4 Service Every 500 Hrs. . . - - - - - - - - - - NOTE - - - - - - - - . . , For quick reference, specifications and quantities of fuel, oil, etc. , are contained in a table on the inside back cover. 0 DAlLY EXTERNAL POWER RECEPTACLE (1}--Connect to 24-volt, DC, negative-ground power unit.
Care of the Airplane the 100-hour periodic inspection for your airplane. The procedure for this 100-hour inspection has been carefully worked out by the factory and is followed by the Cessna Dealer Organization. The complete familiarity of the Cessna Dealer Organization with Cessna equipment and with factory-approved procedures provides the highest type of service possible at lower cost.
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Operational Data Operational Data MP %BHP Fuel Pressure TAS Gal/Hr Endurance 100 Gal Range 100 Gal 990 1025 1060 1100 2450 22 21 20 19 70 66 62 58 7.6 7.0 6. ~ 6.1 217 211 206 200 26.6 24.9 23.5 22.1 3. 8 4.0 4.3 4. 5 B20 B45 8BO 905 4.9 5.2 5. 5 5. 9 1060 llOO 1135 1175 5.1 5.4 5. 7 6.1 1045 1080 1110 1150 2300 22 21 20 19 64 60 57 54 6. B 6. 3 5.9 5. 5 20B 203 19B 192 24.2 22.6 21.5 20.3 4.1 4.4 4. 6 4.9 855 B95 915 940 5, 4 5. 7 6. 0 6.
Operational Data CRUISE PERFORMANCE WITH NORMAL LEAN MIXTURE AT Gal/Hr Endurance 100 Gal 198 19.4 5. 2 1025 6, 7 188 18.0 5, 5 1040 7.2 1355 175 16.7 6.0 1050 7.8 1365 4.2 156 15. 3 6. 5 1015 8.5 1325 4.9 188 18.1 5.5 1040 7. 2 1355 42 4.6 175 16.7 6. 0 1050 7.8 1365 39 4.3 162 15.7 6.4 1035 8.3 1340 43 4. 7 179 17.1 5. 8 1045 7. 6 1360 15.6 6.4 1055 8.3 1370 1275 Fuel Pressure RPM MP 2450 16 51 5. 3 15 46 4.9 14 42 4.
Alphabetical Index Flight Procedure with Open Cabin Door, 4-10 Forced Landing, 4-7, 4-8 Fuel Pressure Gage, 1-6 Fuel Pressure Settings, 1-7 Fuel Quantity Indicators, 1-6 Fuel Selector Valve Handles, 1-4 Fuel Selector Valve Light, 1-22 Fuel Strainers and Drains, 1-6 Fuel System, 1-4 Fuel System - Emergency Operation, 4-9 Fuel System - With Auxiliary Fuel Tanks, 1-5 G Go-Arob.
WARRANTY • The Cessna Aircraft Company warrants each new airplane manufactured by it to be free from defects in material and workmanship under normal use and service, provided, however, that this warranty is limited to making good at The Cessna Aircraft Company's factory any part or parts thereof which shall, within ninety (90) days.