Cessna 1980 172RG Cutlass, Pilot Operating Handbook

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Page 5: ...alers 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 avai...

Page 6: ...e examined immediately upon receipt and incorporated in this handbook NOTE It is the responsibility of the owner to maintain this handbook in a current status when it is being used for operational pur...

Page 7: ...ENERAL 1 LI MITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT BALANCE EQUIPMENT LIST 6 AIRPLANE SYSTEMS DESCRIPTIONS 7 AIRPLANE HANDLING SERVICE MAINTENANCE 8 SUPPLEMENTS Opt...

Page 8: ...ed Weights 1 4 Standard Airplane Weights 1 5 Cabin And Entry Dimensions 1 5 Baggage Space And Entry Dimensions 1 5 Specific Loadings 1 5 Symbols Abbreviations And Terminology 1 6 General Airspeed Term...

Page 9: ...equipped four cylinder engine with 361 cu in displacement Horsepower Rating and Engine Speed 180 rated BHP at 2700 RPM PROPELLER Propeller Manufacturer McCauley Accessory Division Propeller Model Numb...

Page 10: ...SAE 40 18 C 0 F to 21 C 70 F use SAE 30 Below 12 C 10 F use SAE 20 MIL L 22851 Ashless Dispersant Oil All temperatures use SAE 20W 50 or Above 16 C 60 F use SAE 40 or SAE 50 1 C 30 F to 32 C 90 F use...

Page 11: ...nding configu ration at the most forward center of gravity CESSNA SECTION 1 MODEL 172RG GENERAL Vx Best Angle of Climb Speed is the speed which results in the greatest gain of altitude in a given hori...

Page 12: ...C G Center of Gravity Arm is the arm obtained by adding the Arm airplane s individual moments and dividing the sum by the total weight C G Center of Gravity Limits are the extreme center of gravity L...

Page 13: ...4 Airspeed Indicator Markings 2 4 Power Plant Limitations 2 5 Power Plant Instrument Markings 2 6 Weight Limits 2 6 Center Of Gravity Limits 2 7 Maneuver Limits 2 7 Flight Load Factor Limits 2 7 Kinds...

Page 14: ...tandard equipment The limitations included in this section and in Section 9 have been approved by the Federal Aviation Administration Observance of these operating limitations is required by Federal A...

Page 15: ...ance are shown in figure 2 2 2 4 1 July 1979 CESSNA SECTION 2 MODEL 172RG LIMITATIONS MARKING KIAS VALUE OR RANGE SIGNIFICANCE White Arc 42 100 Full Flap Operating Range Lower limit is maximum weight...

Page 16: ...ECTION 2 MODEL 172RG LIMITATIONS Baggage Area 2 Station 108 to 124 50 lbs See note below NOTE The maximum combined weight capacity for baggage areas 1 and 2 is 200 lbs CENTER OF GRAVITY LIMITS Center...

Page 17: ...empty red line cannot be safely used in flight Approved Fuel Grades and Colors 100LL Grade Aviation Fuel Blue 100 Formerly 100 130 Grade Aviation Fuel Green OTHER LIMITATIONS FLAP LIMITATIONS Approve...

Page 18: ...so me chanical detent at 10 10 to 30 White color code and 100 kt callout also mechanical detent at 10 and 20 7 Forward of fuel tank filler cap FUEL 100LL 100 MIN GRADE AVIATION GASOLINE CAP 33 0 U S G...

Page 19: ...Engine Fire In Flight 3 6 Electrical Fire In Flight 3 6 Cabin Fire 3 7 Wing Fire 3 7 Icing 3 7 Inadvertent Icing Encounter 3 7 Static Source Blockage Erroneous Instrument Reading Suspected 3 8 Landing...

Page 20: ...dures for coping with emergencies that may occur Emergencies caused by airplane or engine malfunctions are extremely rare if proper preflight inspections and maintenance are practiced Enroute weather...

Page 21: ...rrain is rough or soft 6 Wing Flaps 30 on final approach 7 Airspeed 65 KIAS 3 4 1 July 1979 CESSNA SECTION 3 MODEL 172RG EMERGENCY PROCEDURES 8 Doors UNLATCH PRIOR TO TOUCHDOWN 9 Avionics Power and Ma...

Page 22: ...cs Power Switch ON 10 Radio Electrical Switches ON one at a time with delay after each until short circuit is localized 3 6 1 July 1979 CESSNA SECTION 3 MODEL 172RG EMERGENCY PROCEDURES 11 Vents Cabin...

Page 23: ...ver DOWN 3 Landing Gear and Gear Pump Circuit Breakers IN 4 Emergency Hand Pump EXTEND HANDLE and PUMP perpen dicular to handle until resistance becomes heavy about 35 cycles 5 Gear Down Light ON 6 Pu...

Page 24: ...ator OFF 8 Nonessential Radio and Electrical Equipment OFF 9 Flight TERMINATE as soon as practical 3 10 1 July 1979 CESSNA SECTION 3 MODEL 172RG EMERGENCY PROCEDURES AMPLIFIED PROCEDURES ENGINE FAILUR...

Page 25: ...procedure execute a forced landing Do not attempt to restart the engine 3 12 1 July 1979 CESSNA SECTION 3 MODEL 172RG EMERGENCY PROCEDURES The initial indication of an electrical fire is usually the...

Page 26: ...cape icing conditions 3 14 1 July 1979 CESSNA SECTION 3 MODEL 172RG EMERGENCY PROCEDURES STATIC SOURCE BLOCKED If erroneous readings of the static source instruments airspeed altimeter and vertical sp...

Page 27: ...SECTION 3 MODEL 172RG EMERGENCY PROCEDURES LOW OIL PRESSURE If low oil pressure is accompanied by normal oil temperature there is a possibility the oil pressure gage or relief valve is malfunctioning...

Page 28: ...TE OF CHARGE After engine starting and heavy electrical usage at low engine speeds such as extended taxiing the battery condition will be low enough to accept above normal charging during the initial...

Page 29: ...Wing 4 5 Nose 4 6 Left Wing 4 6 Left Wing Leading Edge 4 6 Left Wing Trailing Edge 4 6 Before Starting Engine 4 7 Starting Engine 4 7 Before Takeoff 4 7 Takeoff 4 8 Normal Takeoff 4 8 Short Field Take...

Page 30: ...optional systems can be found in Section 9 SPEEDS FOR NORMAL OPERATION Unless otherwise noted the following speeds are based on a maximum weight of 2650 pounds and may be used for any lesser weight Ho...

Page 31: ...OVE 4 Ignition Switch OFF 5 Avionics Power Switch OFF 6 Master Switch ON WARNINGI When turning on the master switch using an external power source or pulling the propeller through by hand treat the pr...

Page 32: ...uel grade 3 Fuel Quantity CHECK VISUALLY for desired level 4 Fuel Filler Cap SECURE 7 LEFT WING Leading Edge 1 Pitot Tube Cover REMOVE and check opening for stoppage 2 Fuel Tank Vent Opening CHECK for...

Page 33: ...2 seconds to restore hydraulic pressure 5 Climb Speed 70 80 KIAS 6 Brakes APPLY momentarily when airborne 7 Landing Gear RETRACT in climb out 4 8 1 July 1979 CESSNA SECTION 4 MODEL 172RG NORMAL PROCED...

Page 34: ...wn MAIN WHEELS FIRST 6 Landing Roll LOWER NOSE WHEEL GENTLY 7 Braking MINIMUM REQUIRED SHORT FIELD LANDING 1 Airspeed 65 75 KIAS flaps UP 2 Wing Flaps 30 below 100 KIAS 3 Airspeed MAINTAIN 63 KIAS 4 T...

Page 35: ...crank the engine through several revolutions with the starter Repeat the starting proce dure without any additional priming If the engine is underprimed most likely in cold weather with a cold engine...

Page 36: ...ion RPM drop should not exceed 150 RPM on either magneto or show greater than 50 RPM differen tial between magnetos If there is a doubt concerning operation of the ignition system RPM checks at higher...

Page 37: ...landing gear swings downward approximately two feet as it starts the retraction cycle damage can result by retracting it before obtaining at least that much ground clearance 4 16 1 July 1979 CESSNA SE...

Page 38: ...6 127 14 6 116 15 3 9000 140 14 0 130 14 9 118 15 6 Standard Conditions Zero Wind Figure 4 3 Cruise Performance Table 4 18 1 July 1979 CESSNA SECTION 4 MODEL 172RG NORMAL PROCEDURES For best fuel econ...

Page 39: ...n 63 KIAS and flare to land on the main wheels first Immediately after touchdown lower the nose gear to the ground and apply heavy braking as required For maximum brake 4 20 1 July 1979 CESSNA SECTION...

Page 40: ...ause raw fuel to accumulate in the intake manifold creating a fire hazard in the event of a backfire If this occurs maintain a cranking action to suck flames into the engine An outside attendant with...

Page 41: ...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 lan...

Page 42: ...lanning of flights in detail and with reasonable accuracy The data in the charts has been computed from actual flight tests with the airplane and engine in good condition and using average piloting te...

Page 43: ...the cruise perfor mance characteristics presented in figure 5 7 the range profile chart presented in figure 5 8 and the endurance profile chart presented in figure 5 9 The relationship between power a...

Page 44: ...nd the corresponding fuel required to complete the trip with ample reserve 5 6 1 July 1979 CESSNA SECTION 5 MODEL 172RG PERFORMANCE LANDING A procedure similar to takeoff should be used for estimating...

Page 45: ...d for level flight or maximum power during descent CESSNA SECTION 5 MODEL 172RG PERFORMANCE AIRSPEED CALIBRATION ALTERNATE STATIC SOURCE HEATER AND DEFROSTER FULL ON AND WINDOWS CLOSED Figure 5 1 Airs...

Page 46: ...1 July 1979 CESSNA SECTION 5 MODEL 172RG PERFORMANCE STALL SPEEDS CONDITIONS Power Off Gear Up or Down NOTES Maximum altitude loss during a stall recovery may be as much as 230 feet KIAS values are a...

Page 47: ...ixture should be leaned to give maximum power in a full throttle static runup 3 Decrease distances 10 for each 9 knots headwind For operation with tailwinds up to 10 knots increase distances by 10 for...

Page 48: ...F CLIMB CONDITIONS Flaps Up Gear Up 2700 RPM Full Throttle Mixture Leaned above 3000 Feet Cowl Flaps Open Standard Temperature NOTES 1 Add 1 4 gallons of fuel for engine start taxi and takeoff allowan...

Page 49: ...distance by 10 for each 10 C above standard temperature 3 Distances shown are based on zero wind Figure 5 6 Time Fuel and Distance to Climb Sheet 2 of 2 5 16 1 July 1979 CESSNA SECTION 5 MODEL 172RG P...

Page 50: ...economy operate at the leanest mixture that results in smooth en g ine operation or at peak EGT if an EGT indicator is installed CONDITIONS 2650 Pounds Recommended Lean Mixture Cowl Flaps Closed NOTE...

Page 51: ...G PERFORMANCE CRUISE PERFORMANCE PRESSURE ALTITUDE 10 000 FEET NOTE For best fuel economy operate at the leanest mixture that results in smooth engine operation or at peak EGT if an EGT indicator is i...

Page 52: ...chart allows for the fuel used for engine start taxi takeoff and climb and the distance during a normal climb up to 8000 feet and maximum climb above 8000 feet NOTE For best fuel economy operate at th...

Page 53: ...limb up to 8000 feet and maximum climb above 8000 feet CESSNA SECTION 5 DEL 172RG PERFORMANCE ENDURANCE PROFILE 45 MINUTES RESERVE 44 GALLONS USABLE FUEL CONDITIONS i0 Pounds Recommended Lean Mixture...

Page 54: ...NOTES 1 Short field technique as specified in Section 4 2 Decrease distances 10 for each 9 knots headwind For operation with tailwinds up to 10 knots increase distances by 10 for each 2 knots 3 For op...

Page 55: ...IGHT BALANCE EQUIPMENT LIST SECTION 6 WEIGHT BALANCE EQUIPMENT LIST TABLE OF CONTENTS Page Introduction 6 3 Airplane Weighing Procedures 6 3 Weight And Balance 6 6 Baggage Tie Down 6 6 Equipment List...

Page 56: ...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...

Page 57: ...heel R Nose Wheel N Sum of Net Weights As Weighed W Item Moment 1000 Weight Lbs X C G Arm In Lbs In Airplane Weight From Item 5 Page 6 3 Airplane Oil 9 Qts at 7 5 Lbs Gal 16 9 16 1 0 3 Add Unusable Fu...

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Page 59: ...list these on the loading problem NOTE Loading Graph information for the pilot passengers and baggage is based on seats positioned for average occu pants and baggage loaded in the center of the baggag...

Page 60: ...low the aft window near each sidewall approxi mately at station 108 When the cabin floor baggage area 1 only is utilized for baggage the two floor mounted eyebolts and the two eyebolts on the forward...

Page 61: ...eses indicate forward and aft limits of occupant center of gravity range Arm measured to the center of the areas shown NOTES 1 The usable fuel C G arm is located at station 48 0 2 The rear cabin wall...

Page 62: ...epresenting adjustable seats shows the pilot or passenger center of gravity on adjustable seats positioned for an average occupant Refer to the Loading Arrangements diagram for forward and aft limits...

Page 63: ...Figure 6 7 Center of Gravity Moment Envelope Figure 6 8 Center of Gravity Limits...

Page 64: ...ndard 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...

Page 65: ...4 1 2 12 99 15 588 King NAV COM KX 155 5 5 13 2 72 6 King NAV Indicator KI 204 1 7 14 0 23 8 Antenna Coupler 0 15 10 1 1 52 SCHALLDAEMPFER LIESE FLIGHT 3 93 6 9 BASIC EMPTY WEIGHT 1623 51 38 46 62452...

Page 66: ...61 HEATING SYSTEM STALL WARNING PITOT EXCH 6 24 4 15 INDICATOR TRUE AIRSPEED EXCH 1 18 1 2 LIGHT BEACON OMNI FLASH 1 4 204 7 287 LIGHTS COURTESY 5 61 0 31 LOCATOR BEACON 3 5 116 5 408 STATIC SOURCE AL...

Page 67: ...C07 A GROUND SERVICE PLUG RECEPTACLE 2401005 2 7 126 0 C16 0 HEATED PITOT SYSTEM NET CHANGE 0422355 7 0 6 24 4 622 A LIGHTS INSTRUMENT POST REQUIRES E34 D 2413120 0 5 17 3 C25 A LIGHT INSTALLATION CO...

Page 68: ...2 0 82 0 23 S BELT SHOULDER HARNESS ASSY CO PILOT S 2215 3 1 6 37 0 E21 S SEAT BELT ASSEMBLY REAR SET OF TWO S 1146 13 2 0 10 0 E27 0 BELT SHOULDER HARNESS ASSY 2ND ROW 2 S 2215 8 3 2 10 0 E33 0 CARPE...

Page 69: ...SCRIPTION REF DRAWING WT LBS ARM INS REMOTE RECEIVER SHELF INSTALLATION 3940266 1 1 0 134 6 H08 A 1 AUTO RADIAL CENTERING INDICATOR ARC LOC EXCHANGE FOR VOR LOC INDICATOR IN ITEM H22 A AND H25 A WT NE...

Page 70: ...VO IS 3 9 LBS AT SHOWN SPLITTER 68 9 INCHES PA 495 MISC WIRING A HARDWARE ITEMS BASIC AVIONICS KIT INSTALLATION RADIO COOLING NOISE FILTER INSTALLATION COM ANTENNA CABLE LH VHF OMNI ANTENNA CABLE OMNI...

Page 71: ...Hand Pump 7 12 Landing Gear Warning System 7 13 Baggage Compartment 7 13 Seats 7 13 Seat Belts And Shoulder Harnesses 7 14 Seat Belts 7 14 Shoulder Harnesses 7 15 Integrated Seat Belt Shoulder Harnes...

Page 72: ...and rear carry through spars to which the wings are attached a bulkhead with attaching plates at the base of the forward doorposts for the lower attachment of the wing struts and the orgings and stru...

Page 73: ...ESSNA SECTION 7 MODEL 172RG AIRPLANE SYSTEMS DESCRIPTIONS AILERON CONTROL SYSTEM RUDDER AND RUDDER TRIM CONTROL SYSTEMS Figure 7 1 Flight Control and Trim Systems Sheet 1 of 2 7 4 1 July 1979 Figure 7...

Page 74: ...ir Temperature Gage 21 Suction Gage 22 Flight Hour Recorder 23 ADF Radio 24 Map Compartment 25 Cabin Heat Control 26 Cabin Air Control 27 Cigar Lighter 28 Wing Flap Switch and Position Indicator 29 Mi...

Page 75: ...ltimeter are located to the left and right of the gyros respectively The remaining flight instruments are located around the basic T The fuel pressure gage clock fuel quantity indicators ammeter oil p...

Page 76: ...gear shock strut Each main gear wheel is equipped with a hydraulically actuated single disc brake on the inboard side of each wheel The landing gear extension retraction and main gear down lock releas...

Page 77: ...th the hand pump To utilize the pump extend the handle forward and pump vertically For complete emergency procedures refer to Section 3 7 12 1 July 1979 CESSNA SECTION 7 MODEL 172RG AIRPLANE SYSTEMS D...

Page 78: ...d right sides of the seat bottom and the buckles at the center of the seat bottom 7 14 1 July 1979 CESSNA SECTION 7 MODEL 172RG AIRPLANE SYSTEMS DESCRIPTIONS To use the seat belts for the front seats...

Page 79: ...est 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 lat...

Page 80: ...mference and is equipped with a lock 7 18 1 July 1979 CESSNA SECTION 7 MODEL 172RG AIRPLANE SYSTEMS DESCRIPTIONS button in the end of the knob The rich position is full forward and full aft is the idl...

Page 81: ...to various engine parts for lubrication Residual oil is returned to the sump by gravity flow An oil filler cap oil dipstick is located at the rear of the engine on the 7 20 1 July 1979 CESSNA SECTION...

Page 82: ...f the cowling The cowl flaps are mechanically operated from the cabin by means of a cowl flap lever on the right side of the control pedestal The pedestal is labeled OPEN COWL FLAPS CLOSED Before star...

Page 83: ...line equipped with a check valve which protrudes from the bottom surface of the left wing near the wing strut The right fuel tank filler cap is also vented Fuel quantity is measured by two float type...

Page 84: ...r drain under an access panel on the right side of the engine cowling The fuel tanks should be filled after each flight to prevent condensation HYDRAULIC SYSTEM Hydraulic power see figure 7 7 is suppl...

Page 85: ...brakes with heavy pressure If the brakes become spongy or pedal travel increases pumping the pedals should build braking pressure If one brake becomes weak or fails use the other brake sparingly whil...

Page 86: ...ion With the switch in the OFF position no electrical power will be applied to the avionics equipment regardless of the position of the master switch or the individual equipment switches The avionics...

Page 87: ...are not protected by circuit breakers are the battery contactor closing external power circuit clock circuit and flight hour recorder circuit These circuits are protected by fuses mounted adjacent to...

Page 88: ...re is a burned out bulb however in the event any of the lighting systems fail to illuminate when turned on check the appropriate circuit breaker If the circuit breaker has opened white button popped o...

Page 89: ...ure line going to the standard external static pressure source the alternate static source valve should be pulled on Pressures within the cabin will vary with heater vents opened or closed and windows...

Page 90: ...attitude indicator is available and gives a visual indication of flight attitude Bank attitude is presented by a pointer at the top of the indicator relative to the bank scale which has index marks at...

Page 91: ...nd sensor unit in the wing leading edge is equipped with a heating element The heated part of the system is operated by the PITOT HT switch and is protected by the PITOT HT circuit breaker The stall w...

Page 92: ...from the navigation receivers of the 7 42 1 July 1979 CESSNA SECTION 7 MODEL 172RG AIRPLANE SYSTEMS DESCRIPTIONS NAV COM radios only Communication receiver audio is selected by the switches labeled C...

Page 93: ...transmitting 7 44 1 July 1979 CESSNA SECTION 7 MODEL 172RG AIRPLANE SYSTEMS DESCRIPTIONS When the airplane has one or two transmitters sidetone is provided in both the speaker and headset anytime the...

Page 94: ...sult in loss of usable radio signals on all communications and navigation radio equipment Usually the ADF is first to be affected and VHF communication equipment is the last to be affected Installatio...

Page 95: ...Cessna Dealer and take advantage of his knowledge and experience He knows your airplane and how to maintain it He will remind you when lubrications and oil changes are necessary and about other season...

Page 96: ...A SECTION 8 MODEL 172RG HANDLING SERVICE MAINTENANCE A To be displayed in the airplane at all times 1 Aircraft Airworthiness Certificate FAA Form 8100 2 2 Aircraft Registration Certificate FAA Form 80...

Page 97: ...NTY plus other important benefits for you are contained in your CUSTOMER CARE P ROGRAM book supplied with your airplane You will want to thoroughly review your Customer Care Program book and keep it i...

Page 98: ...ssing down on a tailcone bulkhead just forward of the horizontal stabilizer and allowing the tail to rest on the tail tie down ring h 8 8 1 July 1979 CESSNA SECTION 8 MODEL 172RG HANDLING SERVICE MAIN...

Page 99: ...CESSNA SECTION 8 HANDLING SERVICE MAINTENANCE 1 C 30 F to 32 C 90 F use SAE 40 18 C 0 F to 21 C 70 F use SAE 30 Below 12 C 10 F use SAE 20 MIL L 22851 Ashless Dispersant Oil This oil must be used afte...

Page 100: ...in areas of the world and consequently must be dealt with when encountered Therefore to alleviate the possibility of fuel icing occurring under these unusual conditions it is permissible to add isopro...

Page 101: ...rub with moderate pressure until all dirt oil scum and bug stains are removed Allow the cleaner to dry then wipe it off with soft flannel cloths If a windshield cleaner is not available the plastic ca...

Page 102: ...ear ENGINE CARE The engine may be cleaned with Stoddard solvent or equivalent then dried thoroughly CAUTION Particular care should be given to electrical equipment 8 16 1 July 1979 CESSNA SECTION 8 MO...

Page 103: ...s 9 HF Transceiver Type PT10 A 4 pages 10 SSB HF Transceiver Type ASB 125 4 pages 11 200A Navomatic Autopilot Type AF 295B 6 pages 12 300 ADF Type R 546E 6 pages 13 300 Nav Com Type RT 385A 8 pages 14...

Page 104: ...n Section 7 Limitations contained in the following supplements are FAA approved Observance of these operating limitations is required by Federal Aviation Regulations 9 2 1 July 1979 1 PILOT S OPERATIN...

Page 105: ...ch will display to the pilot the time of day the calendar date and the elapsed time interval between a series of selected events such as in flight check points or legs of a cross country flight etc Th...

Page 106: ...by changing the position of an internal slide 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 2 1...

Page 107: ...lon blinks off for one second each ten seconds To stop timing the event press the RH button once again and the time shown by the display is frozen Successive pushes of the RH button will alternately r...

Page 108: ...ARNING I When turning on the master switch using an external power source or pulling the propeller through by hand treat the propeller as if the ignition switch were on Do not stand nor allow anyone e...

Page 109: ...l power supplies a rocker switch labeled STROBE LT and a 5 amp push to reset circuit breaker The rocker switch and circuit breaker are located on the left side of the switch and control panel SECTION...

Page 110: ...the oil cooler insulation for the engine crankcase breather line and a placard to be installed on the instrument panel This equipment should be installed for operations in temperatures consistently be...

Page 111: ...to station or ground speed readouts The DME is designed to operate at altitudes up to a maximum of 50 000 feet at ground speeds up to 250 knots and has a maximum slant range of 199 9 nautical miles Th...

Page 112: ...YPE 190 8 IDENT KNOB Rotation of this control increases or decreases the volume of the received station s Ident signal An erratic display accompanied by the presence of two Ident signals can result if...

Page 113: ...DBOOK EMERGENCY LOCATOR SUPPLEMENT TRANSMITTER ELT SUPPLEMENT EMERGENCY LOCATOR TRANSMITTER ELT SECTION 1 GENERAL The ELT consists of a self contained dual frequency radio transmitter and battery powe...

Page 114: ...onserve airplane battery Do not activate radio transceiver 3 AFTER SIGHTING RESCUE AIRCRAFT Place ELT function selector switch in the OFF position preventing radio interference Attempt contact with re...

Page 115: ...aft 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...

Page 116: ...gitally displays the magnetic bearing from the airplane to the waypoint While VOR DME pushbutton 5 is pressed the digital display reads RADIAL from the VOR station on which the airplane is presently p...

Page 117: ...NAVIGATION OPERATING NOTES 1 Proper RNAV operation requires valid VOR and DME inputs to the RNAV system In certain areas the ground station antenna patterns and transmitter power may be inadequate to...

Page 118: ...d DISTANCE Typically the first waypoint is set into the left side set of thumbwheels 8 RADIAL and DISTANCE Thumbwheels SET to second waypoint RADIAL and DISTANCE Typically the second waypoint is set i...

Page 119: ...the airplane performance when this avionic equipment is installed 8 1 July 1979 9 PILOT S OPERATING HANDBOOK HF TRANSCEIVER SUPPLEMENT TYPE PT10 A SUPPLEMENT HF TRANSCEIVER TYPE PT 0 A SECTION GENERAL...

Page 120: ...change to the airplane emergency procedures when this avionic equipment is installed SECTION 4 NORMAL PROCEDURES COMMUNICATIONS TRANSCEIVER OPERATION 1 XMTR SEL Switch on audio control panel SELECT tr...

Page 121: ...er exciter a remote mounted power amplifier power supply an antenna coupler and an externally mounted fixed wire medium high frequency antenna A channel selector knob determines the operating frequenc...

Page 122: ...g Controls 2 1 July 1979 0 PILOT S OPERATING HANDBOOK SSB HF TRANSCEIVER SUPPLEMENT TYPE ASB 125 SECTION 2 LIMITATIONS There is no change to the airplane limitations when this avionic equipment is ins...

Page 123: ...Cessna 200A Navomatic is an all electric single axis aileron control autopilot system that provides added lateral and directional stability Components are a computer amplifier a turn coordinator an a...

Page 124: ...signal to provide more precise operation during localizer approach In low sensitivity position push button out response to NAV signal is dampened for smoother tracking of enroute VOR radials it also...

Page 125: ...or 2 PULL TURN Knob CENTER and PULL out 3 A P ON OFF Switch ON 4 Autopilot TRIM Control ADJUST for zero turn rate wings level indication on Turn Coordinator NOTE For optimum performance in airplanes e...

Page 126: ...performance when this avionic equipment is installed 6 1 July 1979 2 PILOT S OPERATING HANDBOOK CESSNA 300 ADF SUPPLEMENT TYPE R 546E SUPPLEMENT CESSNA 300 ADF Type R 546E SECTION GENERAL The Cessna...

Page 127: ...illator to permit coded identifier of stations transmitting keyed CW signals Morse Code to be heard REC Selects operation as standard communication receiver using only sense antenna ADF Set operates a...

Page 128: ...FINDER 1 Function Selector Knob ADF position and note relative bearing on indicator 2 Function Selector Knob TEST position and observe that pointer moves away from relative bearing at least 10 to 20...

Page 129: ...ting frequencies are digitally displayed by incandescent readouts on the front panel of the Nav Com A DME receiver transmitter or a glide slope receiver or both may be interconnected with the Nav Com...

Page 130: ...ween 108 and 117 MHz simultaneously selects paired glide slope frequency and DME channel 8 COMMUNICATION RECEIVER TRANSMITTER FRACTIONAL MEGAHERTZ SELECTOR Depending on position of 5 0 switch selects...

Page 131: ...00 Nav Com incorporates a variable threshold automatic squelch With this squelch system you set the threshold level for auto matic operation the further clockwise the lower the threshold or the more s...

Page 132: ...with the windshield mounted glide slope antenna pilots should avoid use of 2700 100 RPM on airplanes equipped with a two bladed propeller or 1800 100 RPM on airplanes equipped with a three bladed pro...

Page 133: ...LIND SECTION GENERAL The Cessna 300 Transponder Type RT 359A shown in Figure 1 is the airborne component of an Air Traffic Control Radar Beacon System ATCRBS The transponder enables the ATC ground con...

Page 134: ...Altitude Encoder Blind Sheet 1 of 2 2 1 July 1979 4 PILOT S OPERATING HANDBOOK CESSNA 300 TRANSPONDER SUPPLEMENT AND ALTITUDE ENCODER BLIND 3 IDENT ID SWITCH When depressed selects special pulse iden...

Page 135: ...TUDE ENCODER BLIND 2 Function Switch ON 3 DIM Control ADJUST light brilliance of reply lamp NOTE During normal operation with function switch in ON position reply lamp flashes indicating transponder r...

Page 136: ...n the control center s radarscope more readily The Cessna 300 Transponder consists of a panel mounted unit and an externally mounted antenna The transponder receives interrogating pulse signals on 103...

Page 137: ...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 Display...

Page 138: ...NT operation TO TRANSMIT MODE C ALTITUDE REPORTING CODES IN FLIGHT 1 Off Indicator Warning Flag VERIFY that flag is out of view on encoding altimeter 2 Altitude Encoder Altimeter Setting Knob SET IN a...

Page 139: ...heading 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 comman...

Page 140: ...T or NAV TRK operation this high sensitivity setting increases autopilot response to NAV signal to provide more precise operation during localizer approach In low sensitivity position push button out...

Page 141: ...Coordinator 2 PULL TURN Knob CENTER and PULL out 3 A P ON OFF Switch ON 4 Autopilot TRIM Control ADJUST for zero turn rate wings level indication on Turn Coordinator NOTE For optimum performance in a...

Page 142: ...S OPERATING HANDBOOK CESSNA 400 GLIDE SLOPE SUPPLEMENT TYPE R 443B SUPPLEMENT CESSNA 400 GLIDE SLOPE Type R 443 B SECTION GENERAL The Cessna 400 Glide Slope is an airborne navigation receiver which r...

Page 143: ...443B SECTION 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when this avionic equipment is installed SECTION 4 NORMAL PROCEDURES TO RECEIVE GLIDE SLOPE SIGNALS NOTE The...

Page 144: ...e switch is labeled HIGH LO MUTE and provides the pilot with HIGH LO sensitivity selection and marker beacon audio muting for approximately 30 seconds to enable voice communica tion to be heard withou...

Page 145: ...H ONE OR TWO TRANSMITTERS 1 MARKER BEACON ANNUNCIATOR LIGHTS OUTER Light illuminates blue to indicate passage of outer marker beacon MIDDLE Light illuminates amber to indicate passage of middle marker...

Page 146: ...ger knob increases light intensity Figure 2 Cessna 400 Marker Beacon Operating Controls and Indicator Lights Supplied With Three Transmitters 4 1 July 1979 18 PILOT S OPERATING HANDBOOK CESSNA 400 MAR...

Page 147: ...TUDE ENCODER BLIND SECTION 1 GENERAL The Cessna 400 Transponder Type RT 459A shown in Figure 1 is the airborne component of an Air Traffic Control Radar Beacon System ATCRBS The transponder enables th...

Page 148: ...TUDE ENCODER BLIND SECTION 1 GENERAL The Cessna 400 Transponder Type RT 459A shown in Figure 1 is the airborne component of an Air Traffic Control Radar Beacon System ATCRBS The transponder enables th...

Page 149: ...play selected Mode A reply code 8 REMOTE MOUNTED DIGITIZER Provides an altitude reporting code range of 1000 feet up to the airplane s maximum service ceiling FUNCTION SWITCH Controls application of p...

Page 150: ...D ALTITUDE ENCODER BLIND 2 Function Switch ON 3 DIM Control ADJUST light brilliance of reply lamp NOTE During normal operation with function switch in ON position reply lamp flashes indicating transpo...

Page 151: ...in flight on the control center s radarscope more readily The 400 Transponder consists of a panel mounted unit and an exter nally mounted antenna The transponder receives interrogating pulse signals o...

Page 152: ...OL 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...

Page 153: ...reply lamp NOTE During normal operation with function switch in ON position REPLY lamp flashes indicating transponder replies to interrogations 4 ID Button DEPRESS momentarily when instructed by grou...

Page 154: ...Airplane Flight Manual must be carried in the airplane when the Secondary Seat Stop modification is installed in accordance with Cessna Single Engine Service Bulletin SEB89 2 The information contained...

Page 155: ...e desired flight position Regardless of where the seat is positioned rearward seat travel will be restricted in the event the seat occupant fails to lock the seat in position by normal means When rear...

Page 156: ...rotate to an unlatched position to allow the passage of each stop plate tab and the aft seat roller housing The pilot should demonstrate the operation of all seats to the passengers before flight SEC...

Page 157: ...e desired flight position Regardless of where the seat is positioned rearward seat travel will be restricted in the event the seat occupant fails to lock the seat in position by normal means When rear...

Page 158: ...nt of the seat will be stopped when the aft roller housing on the seat contacts the secondary seat stop Then momentarily unlatch the secondary seat stop and move the seat farther aft to test that each...

Page 159: ...nhang zum Flughandbuch D 82008 UNTERHACHING Cessna 172 RG Tel FAX 089 6113249 Ausgabe 22 7 96 Dieser Anhang zum Flughandbuch enth lt alle erg nzenden Informationen die f r den Betrieb des Flugzeuges C...

Page 160: ...uf einen Wert innerhalb des gr nen Bereichs des Drehzahlmessers zu reduzieren Die ge nderten Steigleistungen sind zu beachten Siehe Abschnitt V dieses Anhanges zum Flughandbuch 3 4 Hermann LIESE FLUGT...

Page 161: ...perating Handbook or Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when Century Flight Systems Inc Century 2000 Autopilot Model AK1002 is installed in accordance with STC SA3495SW...

Page 162: ......

Page 163: ...applicable revision must be available to the pilot at all times in the aircraft when the autopilot is enabled SECTION 3 EMERGENCY OPERATING PROCEDURES 3 1 AUTOPILOT In the event of an autopilot malfu...

Page 164: ...rim system circuit circuit breaker After failed system has been identified leave system circuit breaker open and do not operate until the system failure has been identified and corrected 3 Altitude Lo...

Page 165: ...Pilot s Operating Manual for procedures not contained herein 4 1 COMMAND TRIM SYSTEM To be performed before the first flight of each day 1 Using the control wheel trim switch verify normal trim up and...

Page 166: ...dition Both trim annunciators continuously extinguished is a properly trimmed condition 1 When the autopilot is engaged and a flashing trim annunciators is noted the pilot should manually move the air...

Page 167: ...ng the final approach fix FAF reduce the power for approximately 65 70 KIAS on the final approach segment Adjust power as necessary during remainder of approach to maintain correct airspeed Monitor co...

Page 168: ...ontrol the aircraft 2 Add take off power or power as desired 3 Check that correct attitude and a positive rate of climb is indicated then raise the flaps 4 Set the heading bug to the desired missed ap...

Page 169: ...ed by Supplement SECTION 7 REQUIRED OPERATING EQUIPMENT Text of this Section not affected by Supplement SECTION 8 WEIGHT AND BALANCE Text of this Section not affected by Supplement i CENTURY FLIGHT SY...

Page 170: ...k and basic Airplane Flight Manual when the optional Bendix King KLN 89B GPS system is installed in the Aircraft under Swiss FOCA Major Alteration No MOD 01 089 gig and according to Bendix King Inst M...

Page 171: ...AVIONITEC Ltd General Aviation Center P O Box 1351 8058 Zurich Airport Switzerland Log of Revisions AFM Supplement Cessna 172RG King GPS KLN 89B...

Page 172: ...of contents Page 1 General 4 2 Limitations 5 3 Emergency Procedures Abnormal Procedures 5 4 Normal Procedures 5 5 Performance 6 6 Weight and Balance 6 7 Airplane System Descriptions 6 Original Issue...

Page 173: ...European Airspace system North Atlantic Minimum Navigation Performance Specifications MNPS Airspace and latitudes bounded by 74 North and 60 South using the WGS 84 or NAD 83 coordinate reference datu...

Page 174: ...ndices B and C for appropriate pilot actions to be accomplished in response to annunciated messages Section 4 NORMAL PROCEDURES A OPERATION Normal operating procedures are outlined in the KLN 89B GPS...

Page 175: ...s HSI course pointer is required to provide course datum to the autopilot E ALTITUDE ALERT AUDIO SIGNAL 1000 feet prior to reaching the selected altitude three short signals Upon reaching the selected...