Textron Cessna 172S Skyhawk SP Information Manual Download Page 41

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SECTION 2

LIMITATIONS

UTILITY CATEGORY

CESSNA

MODEL 172S

Center of Gravity Range:

Forward:

35.0 inches aft of datum at 1950 Ibs. or less, with
straight line variation to 37.5 inches aft of datum at

22001bs.

Aft:

40.5 inches aft of datum at all weights .

Reference Datum: Lower portion of front face of firewall.

MANEUVER LIMITS

NORMAL CATEGORY

This

airplane

certificated

both

the

normal

and

utility

category. The normal category is applicable .to aircraft intended for

non aerobatic operations.

These include any maneuvers

incidental

to normal flying, stalls (except whip stalls), lazy eights, chandelles,

and turns in which-lhe angle of bank is not more than 60'.

NORMAL CATEGORY

MANEUVERS

AND RECOMMENDED

EN.

TRYSPEED*

Chandelles

:...............

. 105 Knots

Lazy Eights

105 Knots

Steep Turns

,95

Knots

Stalls (Except Whip Stalls)

Slow Deceleration

Abrupt use of the controls is prohibited above 105 KIAS.

2-8

Ju1B/98

Summary of Contents for Cessna 172S Skyhawk SP

Page 1: ...E c o q 9 E E t o c UF lrsBf II 8E r P c f r...

Page 2: ...D FOR GENERAL PURPOSES ONLY IT WILL NOT BE KEPT CURRENT AND THEREFORE CANNOT BE USED AS A SUBSTITUTE FOR THE OFFICIAL PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL INTENDED FOR OP...

Page 3: ...75 Power at 8500 Feet 126 KNOTS 124 KNOTS j RATE OF CLIMB AT SEA LEVEL 730 FPM SERVICE CEILING c 14 000 FEET TAKEOFF PERFORMANCE Ground Roll 960 FEET Total Distance Over 50 Foot Obstacle 630 FEET LAN...

Page 4: ...the speeds by approximately 2 knots There is a corresponding difference in range while all other performance figures are unchanged when speed fairings are installed The above performance figures are b...

Page 5: ...j l 1 1 J i j...

Page 6: ...of GAMA Cessna Aircraft Company Model172S THIS MANUAL INCORPORATES INFORMATION ISSUED IN THE PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL AT REVISION 5 DATED 19 JULY 2004 PART NU...

Page 7: ...l...

Page 8: ...ONTENTS SECTION GENERAL 1 LIMITATIONS 2 EMERGENCYPROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT AND BALANCE EQUIPMENT LIST 6 AIRPLANE AND SYSTEMS DESCRIPTION 7 HANDLING SERVICE AND MAINTENANCE...

Page 9: ...t I j j...

Page 10: ...ings 1 7 Symbols Abbreviations and Terminology _ 1 8 General Airspeed Terminology And Symbols _ 1 8 Meteorological Terminology __ _ 1 9 Engine Power Terminology _ _ 1 9 Airplane Performance And Flight...

Page 11: ...SECTION 1 GENERAL CESSNA MODEL 172S 36 1 1 M 0510T1005 0510T1005 I 1 2 Ir Figure 1 1 Three View Normal Ground Attitude Sheet 1 of 2 Revision 4...

Page 12: ...ROPELLER GROUND CLEARANCE IS 11 1 4 NOTE 4 WING AREA IS 174 SQUARE FEET NOTE 5 MINIMUM TURNING RADIUS PIVOT POINT TO OUTBOARD WING TIP IS 27 51 2 NOTE 6 NORMAL GROUND ATTITUDE IS SHOWN WITH NOSE STRUT...

Page 13: ...Textron Lycoming Engine Model Number IO 360 L2A Engine Type Normally aspirated direct drive air cooled horizontally opposed fuel injected four cylinder engine with 360 cu in displacement Horsepower Ra...

Page 14: ...Left or Right position Refer to Figure 1 1 for normal ground attitude dimensions OIL Oil Specification MIL L 6082 or SAE J1966 Aviation Grade Straight Mineral Oil Used when the airplane was delivered...

Page 15: ...1 e 70 F 30 30 40 or 20W 40 Below 12 e 10 F 20 30 or 20W 30 18 e O F to 32 e 90 F 20W 50 20W 50or 15W 50 All Temperatures 15W 50or 20W 50 NOTE When operating temperatures overlap use the lighter grade...

Page 16: ...ar seat must not be occupied and the baggage compartment must be empty STANDARD AIRPLANE WEIGHTS Standard Empty Weight Maximum Useful Load Normal Category Maximum Useful Load Utility Category CABIN AN...

Page 17: ...ing the airframe VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position VNO Maximum Structural Cruising Speed is the speed that should not b...

Page 18: ...stationary MAP Manifold Absolute Pressure is the absolute pressure measured in the engine induction system MAP is measured in units of inches of mercury inHG Lean Decreased proportion of fuel in the f...

Page 19: ...component for which adequate control of the airplane during takeoff and landing was actually def lonstrated during certification tests The value shown is not considered to be limiting Usable Fuel is...

Page 20: ...of digits Center of Gravity is the point at which an airplane or equipment would balance if suspended Its distance from the reference datum is found by dividing the total moment by the total weight of...

Page 21: ...cludes the weight of fuel used for start taxi and runup Maximum Takeoff Weight is the maximum weight approved for the start of the takeoff roll Maximum Landing Weight is the maximum weight approved fo...

Page 22: ...nvert U S measurement supplied with the Pilot s Operating Handbook into metric and imperial measurements The standard followed for measurement units shown is the National Institute of Standards Techno...

Page 23: ...205 03 207 24 209 44 211 64 213 85 216 05 218 26 100 220 46 222 67 224 87 227 08 229 28 231 49 233 69 235 90 238 10 240 30 POUNDS INTO KILOGRAMS L1VRES EN KILOGRAMMES lb 0 1 2 3 4 5 6 7 8 g kg kg kg k...

Page 24: ...140 65 130 60 120 55 110 50 100 45 90 40 80 35 70 30 60 25 50 40 20 30 15 20 10 10 5 Units x 10 100 etc 0 0 r r l I CESSNA MODEL 172S Kilograms x 2 205 Pounds SECTION 1 GENERAL pounds x 454 Kilograms...

Page 25: ...56 301 84 305 12 308 40 311 68 314 96 318 24 321 52 324 80 100 328 08 331 36 334 64 337 93 341 21 344 49 347 77 351 05 354 33 357 61 FEET INTO METERS PIEDS EN METRES l ft 0 1 2 3 4 5 6 7 8 9 m m m m...

Page 26: ...x 3 281 Feet Feet x 305 Meters FEET METERS 100 320 95 300 90 280 85 260 80 240 75 70 220 65 200 60 180 55 160 50 45 140 40 120 35 100 30 80 25 60 20 15 40 10 20 5 0 0 Units x 10 100 etc Figure 1 3 Le...

Page 27: ...36 614 37 008 37 402 37 795 38 189 38 583 38 976 100 39 370 39 764 40 157 40 551 40 945 41 339 41 732 42 126 42 520 42 913 INCHES INTO CENTIMETERS POUCES EN CENTIMETRES in a 1 2 3 4 5 6 7 8 9 em em em...

Page 28: ...meters x 394 Inches Inches x 2 54 Centimeters INCHES CENTIMETERS 10 25 24 9 23 22 21 8 20 19 18 7 17 16 6 15 14 5 13 12 11 4 10 9 3 8 7 6 2 5 4 Units x 10 100 etc 3 1 2 0585T1028 1 a a Figure 1 4 Leng...

Page 29: ......

Page 30: ...118 21 338 21 558 21 778 100 21 998 22 218 22 438 22 658 22 878 23 098 23 318 23 537 23 757 23 977 IMPERIAL GALLONS INTO LITERS GALLONS IMPERIAL EN L1TRES IG a 1 2 3 4 5 6 7 8 9 Lt Lt Lt U Lt U Lt Lt...

Page 31: ...22 Imperial Gallons 100 IMPERIAL 440 LITERS 95 GALLONS 420 90 400 85 380 80 360 I 75 340 70 320 65 300 1 60 280 260 55 240 50 220 45 200 40 180 35 160 30 140 25 120 20 100 80 15 60 10 40 5 20 0 0 Uni...

Page 32: ...S GALLONS 100 120 GALLONS 100 95 115 95 360 90 110 90 340 105 85 100 85 320 80 95 80 300 75 90 75 280 70 85 70 260 65 80 65 75 240 60 70 60 220 55 65 55 200 50 60 50 180 45 55 45 50 40 160 40 45 140 3...

Page 33: ...10 500 260 60 520 70 20 540 280 BO 560 90 30 580 300 100 40 600 320 110 6 120 50 640 340 130 660 140 60 680 360 150 700 160 70 720 380 170 7 180 80 760 400 190 90 780 420 20 800 210 100 820 440 220 8...

Page 34: ...egory Utility Category Center Of Gravity Limits Normal Category Utility Category Maneuver Limits Normal Category Utility Category Flight Load Factor Limits Normal Category Utility Category Kinds Of Op...

Page 35: ...1 I j...

Page 36: ...options the Supplements Section 9 of this Pilot s Handbook for amended operating limitations procedures performance data and other information for airplanes equipped with specific NOTE I The airspeeds...

Page 37: ...exceed this speed in any operation VNO Maximum Structural 126 129 Do not exceed this Cruising Speed speed except in smooth air and then only with caution VA Maneuvering Speed Do not make full or 2550...

Page 38: ...is maximum weight VS1 at most forward C G with flaps retracted Upper limit is maximum structural cruising speed Yellow Arc 129 163 Operations must be conducted with caution and only in smooth air Red...

Page 39: ...r 1A170E JHA7660 Propeller Diameter Maximum 76 inches Minimum 75 inch minimum POWERPLANT INSTRUMENT MARKINGS Powerplant instrument markings and their color code significance are shown in Figure 2 3 RE...

Page 40: ...120 Ibs UTILITY CATEGORY Maximum Ramp Weight 2208 Ibs Maximum Takeoff Weight 2200 Ibs Maximum Landing Weight 2200 Ibs Maximum Weight in Baggage Compartment In the utility category the baggage compartm...

Page 41: ...certificated in both the normal and utility category The normal category is applicable to aircraft intended for non aerobatic operations These include any maneuvers incidental to normal flying stalls...

Page 42: ...ENDED ENTRY SPEED Chandelles 105 Knots Lazy Eights 105 Knots Steep Turns 95 Knots Spins Slow Deceleration Stalls Except Whip Stalls Slow Deceleration Abrupt use of the controls is prohibited above 98...

Page 43: ...Down 3 0g The design load factors are 150 of the above and in all cases the structure meets or exceeds design loads KINDS OF OPE RATION LIMITS I The airplane as delivered is equipped for day VFR and a...

Page 44: ...ltitude definition ADDITIONAL FUEL LIMITATIONS Takeoff and land with the fuel selector valve handle in the BOTH position Maximum slip or skid duration with one tank dry 30 seconds Operation on either...

Page 45: ...must be complied with when operating this airplane in this category or in the Utility Category are contaJned in the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual Normal Category U...

Page 46: ...MITATIONS ALL FLIGHT ATIITUDES RIGHT 26 5 GAL LEVEL FLIGHT ONLY FUEL 100LU1 00 MIN GRADE AVIATION GASOLINE CAP 26 5 U S GAL USABLE CAP 17 5 U S GAL USABLE TO BOTIOM OF FILLER INDICATOR TAB 4 On flap c...

Page 47: ...H MAXIMUM 120 POUNDS COMBINED FOR ADDITIONAL LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE DATA 6 A calibration card must be provided to indicate the accuracy of the magnetic compass in 30 increments 7...

Page 48: ...ICED IN ACCORDANCE WITH FAR PART 91 207 11 On forward face of firewall adjacent to the battery CAUTION 24 VOLTS D C THIS AIRCRAFT IS EQUIPPED WITH ALTERNATOR AND A NEGATIVE GROUND SYSTEM OBSERVE PROPE...

Page 49: ...c i I II i i l j 1 1...

Page 50: ...Takeoff Engine Failure During Flight Restart Procedures Forced Landings Emergency Landing Without Engine Power Precautionary Landing With Engine Power Ditching Fires During Start On Ground Engine Fir...

Page 51: ...3 16 Emergency Operation In Clouds Vacuum System Failure 3 16 Executing A 180 Turn In Clouds 3 16 Emergency Descent Through Clouds 3 17 Recovery From Spiral Dive In The Clouds 3 18 Inadvertent Flight...

Page 52: ...red However should an emergency arise the basic guidelines described in this section should be considered and applied as necessary to correct the problem Emergency procedures associated with standard...

Page 53: ...FAILURE DURING TAKEOFF ROLL 1 ThrottlEl IDLE 2 Brakes APPLY 3 Wing Flaps RETRACT 4 Mixture IDLE CUT OFF 5 Ignition Switch OFF 6 Master Switch OFF ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF 1 AirspElEld...

Page 54: ...om idle and lean the mixture from full rich as required for smooth operation 7 Auxiliary Fuel Pump Switch OFF NOTE If the fuel flow indicator immediately drops to zero indicating an engine driven fuel...

Page 55: ...DAY on 121 5 MHz giving location and intentions and SQUAWK 7700 2 Heavy Objects in baggage area SECURE OR JETTISON if possible 3 Passenger Seat Backs MOST UPRIGHT POSITION 4 Seats and Seat Belts SECUR...

Page 56: ...URE a Master Switch OFF b Ignition Switch OFF 11 Parking Brake RELEASE 12 Airplane EVACUATE 13 Fire _ EXTINGUISH using fire extinguisher wool blanket or dirt 14 Fire Damage INSPECT repair damage or re...

Page 57: ...necessary for continuance of flight to nearest suitable airport or landing area 7 Master Switch ON 8 Circuit Breakers CHECK for faulty circuit do not reset 9 Radio Switches OFF 10 Avionics Master Swi...

Page 58: ...ir intake filter or in extremely rare instances ice completely blocking the fuel injection air reference tubes Change the throttle position to obtain maximum RPM This may require either advancing or r...

Page 59: ...te calibration tables in Section 5 LANDING WITH A FLAT MAIN TIRE I I 1 Approach NORMAL 2 Wing Flaps 30 3 Touchdown GOOD MAIN TIRE FIRST hold airplane off flat tire as long as possible with aileron con...

Page 60: ...nunciator panel may occur during low RPM conditions with an electrical load on the system such as during a low RPM taxi Under these conditions the annunciator will go out at higher RPM The I master sw...

Page 61: ...Illuminates CESSNA MODEL 172S Right Vacuum VAC R A CAUTION IF VACUUM IS NOT WITHIN NORMAL OPERATING LIMITS A FAILURE HAS OCCURRED IN THE VACUUM SYSTEM AND PARTIAL PANEL PROCEDURES MAY BE REQUIRED FOR...

Page 62: ...of procedures fresh ENGINE FAILURE If an engine failure occurs during the takeoff roll the most important thing to do is stop the airplane on the remaining runway Those extra items on the checklist w...

Page 63: ...e landing area an effort should be made to identify the cause of the failure If time permits an engine restart should be attempted as shown in the checkli st If the engine cannot be restarted a forced...

Page 64: ...a landing flare because of difficulty in judging height over a water surface The checklist assumes the availability of power to make a precautionary water landing If power is not available use of the...

Page 65: ...ld result in elimination of the fire EMERGENCY OPERATION IN CLOUDS Total Vacuum System Failure If both the vacuum pumps fall in flight the directional indicator and attitude indicator will be disabled...

Page 66: ...emergency descent through clouds To guard against a spiral dive choose an easterly or westerly heading to minimize compass card swings due to changing bank angles In addition keep hands off the contr...

Page 67: ...ight into icing conditions is prohibited ana extremely dangerous An inadvertent encounter with these conditions can best be handled using the checklist procedures The best procedure of course is to tu...

Page 68: ...AND HOLD FULL RUDDER OPPOSITE TO THE DIRECTION OF ROTATION 4 JUST AFTER THE RUDDER REACHES THE STOP MOVE THE CONTROL WHEEL BRISKLY FORWARD FAR ENOUGH TO BREAK THE STALL Full down elevator may be requi...

Page 69: ...use of a single ignition positio MAGNETO MALFUNCTION A sudden engine roughness or misfiring is usually evidence of magneto problems Switching from BOTH to either L or R ignition switCh position will i...

Page 70: ...is suspected smoother engine operation ma result from making the following changes singly or together se the auxiliary fuel pump to the ON position lean the mixture fo smooth engine operation and sel...

Page 71: ...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 part o...

Page 72: ...ging will resume and the low voltag annunciator VOLTS will go olf The avionics master switch ma then be returned to the ON position If the annunciator illuminates again a malfunction is confirmed In t...

Page 73: ...i J j I 1...

Page 74: ...7 Cabin 4 7 Empennage 4 8 Right Wing Trailing Edge 4 8 Right Wing 4 8 Nose 4 9 Left Wing 4 10 Left Wing Leading Edge 4 11 Left Wing Trailing Edge 4 11 Before Starting Engine 4 11 Starting Engine With...

Page 75: ...tions Taxiing Before Takeoff Warm Up Magneto Check Alternator Check Landing Lights Takeoff Power Check Wing Flap Settings Crosswind Takeoff Enroute Climb Cruise Leaning With an EGnndicator Fuel Saving...

Page 76: ..._ 4 33 Normal Landing _ _ _ _ _ __ 4 33 Short Field Landing _ __ _ 4 33 Crosswind Landing __ _ _ 4 34 Balked Landing _ _ 4 34 Cold Weather Operation _ _ _ 4 34 Winterization Kit __ _ __ 4 36 Hot Weat...

Page 77: ...I r...

Page 78: ...b Out 75 85 KIAS Short Field Takeoff Flaps 10 Speed at 50 Feet 56 KIAS Enroute Climb Flaps Up Normal Sea Level 75 85 KIAS Normal 10 000 Feet 70 80 KIAS Best Rate of Climb Sea Level 74 KIAS Best Rate o...

Page 79: ...fY aee M to tile upper Wing sUrf a cesfor VisUai checks ana refUeling operations In cola WMther rei1 ove even small accUmUlations of fIOst iee or sMW Itom Wing tail ana control sUtii ices Also make sU...

Page 80: ...LLER THROUGH BY HAND TREAT THE PROPELLER AS IF THE IGNITION SWITCH WERE ON DO NOT STAND NOR ALLOW ANYONE ELSE TO STAND WITHIN THE ARC OF THE PROPELLER SINCE A LOOSE OR BROKEN WIRE OR A COMPONENT MALFU...

Page 81: ...Pitot Heat ON Carefully check that pitot tube is warm to touch within 30 seconds 20 Pitot Heat OFF 21 Master Switch OFF 1 22 Elevator Trim SET for takeoff 23 Baggage Door CHECK lock with key 24 Autopi...

Page 82: ...ENCE OF CONTAMINATION STILL EXISTS THE AIRPLANE SHOULD NOT BE FLOWN TANKS SHOULD BE DRAINED AND SYSTEM PURGED BY QUALIFIED MAINTENANCE PERSONNEL ALL EVIDENCE OF CONTAMINATION MUST BE REMOVED BEFORE FU...

Page 83: ...LEFTWING 1 Fuel Quantity CHECK VISUALLY for desired level 2 Fuel Filler Cap 00 SECURE and VENT UNOBSTRUCTED 3 Fuel Tank Sump Quick Drain Valves _ DRAIN at least a cupful ffuel using sampler cup from e...

Page 84: ...LEFT WING Trailing Edge 1 Aileron CHECK for freedom of movement and security 2 Flap CHECK for security and condition BEFORE STARTING ENGINE 1 Preflight Inspection COMPLETE 2 Passenger Briefing COMPLET...

Page 85: ...sually 3 to 5 seconds then set to IDLE CUTOFF full aft positiofl 8 Auxiliary Fuel Pump Switch OFF 9 Ignition Switch START release when engine starts 10 Mixture ADVANCE smoothly to RICH when engine sta...

Page 86: ...onds then set to IDLE CUTOFF full aft position 10 Auxiliary Fuel Pump Switch OFF 11 Ignition Switch START release when engine starts 12 Mixture ADVANCE smoothly to RICH when engine starts NOTE If engi...

Page 87: ...o approximately 1500 RPM as engine RPM increases alternator output should increase to meet the system load requirements I Ammeter and Low Voltage Annunciator CHECK the ammeter should indicate in the p...

Page 88: ...uum Gage CHECK I c Engine Instruments and Ammeter CHECK 11 Annunciator Panel Ensure no annunciators are illuminated 12 Throttle CHECK IDLE 13 Throttle 1000 RPM or LESS 14 Throttle Friction Lock ADJUST...

Page 89: ...ture RICH above 3000 feet LEAN to obtain maximum RPM CRUISE I 1 Power 2100 2700 RPM No more than 75 is recommended 2 Elevator Trim ADJUST 3 Mixture LEAN DESCENT 1 Pilot and Passenger Seat Backs MOST U...

Page 90: ...to idle after clearing obstacle 5 Touchdown MAIN WHEELS FIRST 6 Brakes APPLY HEAVILY 7 Wing Flaps RETRACT BALKED LANDING 1 Throttle FULL OPEN 2 Wing Flaps RETRACT TO 20 3 Climb Speed Cc 60 KIAS 4 Win...

Page 91: ...mage to nose wheel as a result of exceeding tow limits and avionics antennas Outside storage for long periops may result in dJst and dirt accumulation on the induction air filter obstructions in airsp...

Page 92: ...o be inspected for obstructions ice or water especially after exposure to cold wet weather STARTING ENGINE In cooler weather the engine compartment temperature drops off rapidly following engine shutd...

Page 93: ...necessary I After starting if the oil pressure gage does not begin to show pressure within 30 seconds in the summer time and approximately one minute in very cold weather stop the engine and investig...

Page 94: ...d NOTE If ground operation will be required after the BEFORE TAKEOFF checklist is completed lean the mixture again as described above until ready for the TAKEOFF checklist TAXIING When taxiing it is i...

Page 95: ...ERON jil u 1 t J R _ G J u R H F _ t w I N E G L y J I r i i i i i f _ J _ CODE WIND DIRECTION NOTE Stro 1g quartering tail winds require caution Avoid sudden bursts of the throttle and sharp braking...

Page 96: ...ther magneto or show greater than 50 RPM differential between magnetos If there is a doubt concerning operation of the ignition system RPM checks at higher engine speeds will usually confirm whether a...

Page 97: ...ide maximum RPM Full throttle run ups over loose gravel are especially harmful to propeller tips When takeoffs must be made over a gravel surface it is very important that the throttle be advanced slo...

Page 98: ...IND TAKEOFF Takeoffs into strong crosswind conditions normally are performed with the minimum flap setting necessary for the field length to minimize the drift angle immediately after takeoff With the...

Page 99: ...strates the true airspeed and nautical miles per gallon during cruise for various altitudes and percent powers and is based on standard conditions and zero wind This table should be used as a guide al...

Page 100: ...heEGT indication begins to increase continue to slowly lean the mixture until an EGT indication decrease is just detectable Reverse the adjustment slowly in the rich direction until an EGT indication...

Page 101: ...until ready I for the TAKEOFF checklist 2 Lean the mixture for maximum RPM during full throttle climbs above 3000 feet The mixture may remain leaned maximum RPM at full throttle for practicing maneuve...

Page 102: ...Take note of the altitude operational procedure and the section on auxiliary fuel pump operation Section 2 Section 3 Section 4 Section 7 1 With the mixture full rich set the throttle at 1800 RPM to 20...

Page 103: ...ment including the microphone and rear seat belts should be stowed or secured For a solo f1ight in which spins will be conducted the copilot s seat belt and shoulder harness should also be secured Car...

Page 104: ...l For the purpose of training in spins and spin recoveries a 1 or 2 turn spin is adequate and should be used Up to 2 turns the spin will progress to a fairly rapid rate of rotation and a steep attitud...

Page 105: ...y can cause differences in behavior particularly in extended spins These differences are normal and will result in variations in the spin characteristics and in the spiraling tendencies for spins of m...

Page 106: ...greater than 20 are used in sideslips with full rudder deflection some elevator oscillation may be felt at normal approach speeds However this does not affect control of the airplane Although the cra...

Page 107: ...ny internal accumulations of ice or snow If snow orslush covers the takeoff surface allowance must be made for takeoff distances which will be increasingly extended as the snow or slush depth increase...

Page 108: ...start during the first few attempts or if engine firing diminishes in strength it is probable that the spark plugs have been frosted over Preheat must be used before another start is attempted During...

Page 109: ...se on the public 1 Pilots operating airplanes under VFR over outdoor assemblies of persons recreational and park areas and other noise sensitive areas should make every effort to fly not less than 200...

Page 110: ...ration Alternate Static Source Figure 5 2 Temperature Conversion Chart Figure 5 3 Stall Speeds Figure 5 4 Crosswind Components Figure 5 5 Short Field Takeoff Distance Figure 5 6 Maximum Rate Of Climb...

Page 111: ...1 t...

Page 112: ...d air turbulence may account for variations of 10 or more in range and endurance Therefore it is important to utilize all available information to estimate the fuel required for the particular flight...

Page 113: ...ltitude and temperature For example in this particular sample problem the takeoff distance information prese ted for a weight of 2550 pounds pressure altitude of 2000 feet and a iempElfature of 30 C s...

Page 114: ...performance characteristics presented in Figure 5 8 the range profile chart presented in Figure 5 9 and the enduran ce profile chart presented in Figure 5 10 The relationship between power and range...

Page 115: ...made as noted on the climb chart The approximate effect of a non standard temperature is to increase the time fuel and distance by 10 for each 10 C above standard temperature due to the lower rate ot...

Page 116: ...3 2 Hours 107 Knots The fuel required for cruise is 3 2 hours X 8 9 galionSlhour 28 5 Gallons A 45 minute reserve requires 45 60 X 8 9 gallons hour 6 7 Gallons The total estimated fuel required is as...

Page 117: ...ound roll 650 Feet Total distance to clear a 50 foot obstacle 1455 Feet A correction for the effect of wind may be made based on Note 2 of the landing chart using the same procedure as outlined for ta...

Page 118: ...Power required for level flight or maximum power descent FLAPS UP KIAS 50 60 70 80 90 10011012013014 KCAS 56 62 70 78 87 97 10711712713 FLAPS 10 KIAS 40 50 60 70 80 90 100 110 KCAS 51 57 63 71 80 89 9...

Page 119: ...IAS 50 60 70 80 90 100110120130140150160 KCAS 56 62 68 76 85 95 105 115 125 134 144154 FLAPS 10 KIAS 40 50 60 70 80 90 100110 _ KCAS 51 55 60 68 77 86 96 105 FLAPS 30 KIAS 40 50 60 70 80 85 _ KCAS 49...

Page 120: ...E TEMPERATURE CONVERSION CHART 60 T 1 L 40 q f 1 tPf1 1t 4 Trn rfn r r H H H y J q H t1 _ t i i o 20 DEGREES CELSIUS 20 100 20 o 120 80 40 40 f UJ 60 I Z w a I i f 40 f W w a D 20 w o Figure 5 2 Tempe...

Page 121: ...3 52 57 57 63 68 75 10 42 50 45 54 50 59 59 71 30 40 48 43 52 48 57 57 68 MOST FORWARD CENTER OF GRAVITY ANGLE OF BANK FLAP 0 30 45 60 SETIING KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 48 53 52 57 57...

Page 122: ...trated crosswind velocity is 15 knots not a limItation 35 30 0 25 Z 20 1 OW Z I 15 I 10 Z w Z 5 0 c lii 0 0 U C 5 Zo Z 3 10 15 5 10 15 20 25 NOTE Maximum demonstrated crosswind component is 15 knots n...

Page 123: ...3000 1125 1925 1215 2080 1310 2240 1410 2420 1515 2605 4000 1235 2120 1335 2295 1440 2480 1550 2685 1660 2880 2755 5000 1355 2345 1465 2545 1585 1705 2975 1825 3205 6000 1495 2605 1615 2830 1745 3075...

Page 124: ...3000 970 1665 1050 1795 1130 1930 1215 2080 1305 2230 AOOO 1065 1830 1150 1975 1240 2130 1335 2295 1430 2455 5000 1170 2015 1265 2180 1360 2355 1465 2530 1570 2715 6000 1285 2230 1390 2410 1500 2610 1...

Page 125: ...00 795 1365 860 1465 925 1570 995 1685 1065 1805 4000 870 1490 940 1605 1010 1725 1090 1855 1165 1975 5000 955 1635 1030 1765 1110 1900 1195 2035 1275 2175 6000 1050 1800 1130 1940 1220 2Q90 1310 2240...

Page 126: ...ATE OF CLIMB FPM ALT SPEED FT KIAS 20 C O C 20 C 40 C S L 74 855 785 710 645 2000 73 760 695 625 560 4000 73 685 620 555 495 6000 73 575 515 450 390 8000 72 465 405 345 285 10 000 72 360 300 240 180 1...

Page 127: ...6 4000 73 600 6 1 5 8 5000 73 550 8 1 9 10 6000 73 505 10 2 2 13 7000 73 455 12 2 6 16 8000 72 410 14 3 0 19 9000 72 360 17 3A 22 10 000 72 315 20 3 9 27 11 000 I 72 265 24 4A 32 12 000 72 220 28 5 0...

Page 128: ...7 2200 53 99 7 7 50 97 7 3 47 95 6 9 2100 47 92 6 9 44 90 6 6 42 89 6 3 4000 2600 83 120 11 1 77 120 10 4 72 119 9 8 2550 79 118 10 6 73 117 9 9 68 117 9 4 2500 74 115 10 1 69 115 9 5 64 114 8 9 2400...

Page 129: ...8 6 57 111 8 1 2400 58 108 8 2 54 106 7 8 51 104 7 4 2300 52 101 7 5 48 99 7 1 46 97 6 8 2200 46 94 6 8 43 92 6 5 41 90 6 2 10 000 2700 78 124 10 5 72 123 9 8 67 122 9 3 2650 73 122 10 0 68 120 9 4 63...

Page 130: ...mmended Lean Mixture for Cruise At All Attitudes Standard Temperature Zero Wind 12 000 10 000 SECTION 5 PERFORMANCE 8 000 Iii w u 6 000 w C J 4 000 NOTES 1 This chart allows for the fuel used for engi...

Page 131: ...d Lean Mixture for Cruise At All Altitudes Standard Temperature CESSNA MODEL 172S 12000 10000 8000 I W w 6000 IL W C 4000 2000 II SL 4 1 5 6 ENDURANCE HOURS 7 8 NOTE 1 This chart allows for the fuel u...

Page 132: ...0 1455 670 1490 3000 610 1385 630 1425 655 1460 675 1495 695 1530 4000 630 1425 655 1460 675 1495 700 1535 725 1570 5000 655 1460 680 1500 705 1535 725 1575 750 1615 6000 680 1500 705 1540 730 1580 75...

Page 133: ......

Page 134: ...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 8 Comprehensive Equip...

Page 135: ...i I i J...

Page 136: ...S LOADED PROPERL Y OPERATION OUTSIDE OF PRESCRIBED WEIGHT AND BALANCE LIMITATIONS COULD RESULT IN AN ACCIDENT AND SERIOUS OR FATAL INJURY AIRPLANE WEIGHING PROCEDURES 1 Preparation a Inflate tires to...

Page 137: ...150 NOTE IT IS THE RESPONSIBILITY OF THE PILOT TO ENSURE THAT THE AIRPLANE IS LOADED PROPERLY LEVEL AT UPPER POOR SILL OR LEVELING SCREWS ON LEFT SIDE OF TAILCONE 100 150 200 250 MAC 58 80 o 25 90 J...

Page 138: ...SIST IN LOCATING CG WITH AIRPLANE WEIGHED ON LANDING GEAR LEVELING PROVISIONS LONGITUDINAL LEFT SIDE OF TAILCONE AT FS 108 00 142 00 AIRPLANE AS WEIGHED TABLE POSITION SCALE READING SCALE DRIFT TARE N...

Page 139: ...t and C G can be determined 6 Basic Empty Weight may be determined by completing Figure 1 WEIGHT AND BALANCE The following information will enable you to operate your Cessna within the prescribed weig...

Page 140: ...UCTURE OR EQUIPMENT AFFECTING WEIGHT AND BALANCE AIRPLANE MODEL ISERIAL NO IPAGE NUMBER WEIGHT CHANGE RUNNING ITEM NO DESCRIPTION BASIC EMPTY ADDED REMOVED WEIGHT DATE OF ARTICLE OR MODIFICATION WT AR...

Page 141: ...having tie down straps is provided as standard equipment to secure baggage on the cabin floor aft of the rear seat baggage area 1 and in the aft baggage area baggage area 2 Six eyebolts serve as atta...

Page 142: ...to the center of the areas shown NOTES 1 The usable fuel C G arm for integral tanks is located at station 48 0 2 The rear cabin wall approximate station 108 or aft baggage wall approximate station 14...

Page 143: ...FIREWALL 41 48 __ J 1 _ CD 65 3 10 4 1 1 AFT BAGGAGE AREA DOOR OPENING DIMENSIONS WIDTH WIDTH HEIGHT HEIGHT TOP BOTTOM FRONT REAR CABIN DOORS 32112 37 40112 39 BAGGAGE DOOR 151 151 22 21 0585X1023 Fig...

Page 144: ...MENT PANEL REAR DOOR POST BULKHEAD I 142 7 f l r r Ir ___ I III I 381 2 1 039 2 037 2 1 035 03312 I I I 211 2 34 29 2 25 28 I 1 36 1iiI I 1 I 1 t I I 1 _r I 1 1 1 1 I I I o 10 20 30 40 50 60 70 80 90...

Page 145: ...ont Passenger Station 34 to 46 340 12 6 4 Rear Passengers 340 24 8 5 8aggage Area 1 Station 82 to 108 120 Lbs Max 56 4 6 6 8aggage Area 2 Station 108 to 142 50 Lbs Max 7 RAMP WEIGHT AND MOMENT add col...

Page 146: ...t Moment Lb ins Ibs 11OOO I YOUR AIRPLANE Weight Moment Lb ins Ibs 11OOO NOTE When several loading configurations are representative of your operations it may be useful to fill out one or more of the...

Page 147: ...LOAD MOMENT 1000 KILOGRAM MILLIMETERS o 50 100 150 200 250 300 350 400 I 100 i 400 00 o 5 350 o a 300 t I 1 w 250 s NOTE LINE REPRESENTING ADJUSTABLE SEATS SHOWS THE PILOT OR PASSENGER CENTER OF GRAVI...

Page 148: ...CI SSNA MODEL 172S 2500 1700 SECTION 6 WEIGHT BALANCE EQUIPMENT LiSt 120 130 D585C1007 July 8 98 Figure 6 7 Center of Gravity Moment Envelope 6 15...

Page 149: ...800 1500 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 AIRPLANE e G LOCATION INCHES AFT OF DATUM STA 0 0 2600 2500 2400 2300 iil iil 0 a 2200 0 0 g f f a 2100 I W W UJ UJ Z z 2000 G o a a 0 1900 0 UJ U...

Page 150: ...ipment for FAA certification 8 standard equipment items 0 optional equipment items replacing required or standard ifems A opli9 al equipment items which are in addition to required or standard items I...

Page 151: ...AXIS AUTOPILOT 3900021 19 7 104 4 AUTOPllOT COMPUTER CONTROLLER 065 00176 5201 3 1 12 1 ROLL ACTUATOR WITH MOUNT 10940400 1 3 6 68 5 PITCH ACTUATOR WITH MOUNT 0501145 1 4 5 173 8 MISC STRUCTURE WIRE...

Page 152: ...2 75 A H MANIFOLD C614002 0101 23 2 5 0 TYPE 24 03 R POWER JUNCTION BOX PRECISION MCOl 2A 6 4 2 5 AIRMOTIVE CORP MC01 2A INCLUDES ALTERNATOR CONTROL UNIT 1270101 1 0 2 3 0 AC2101 MASTER CONTACTOR PIN...

Page 153: ...1019 1 I 1 7 124 0 25 26 R EMERGENCY LOCATOR TRANSMITIER 940401 1 3 2 101 0 ELl TRANSMITIER 3000 11 1 6 113 3 ANTENNA AND CABLE ABSY 3003 45 q 5 122 0 26 FIRE PROTECTION 26 01 5 FIRE EXTINGUISHER INST...

Page 154: ...CONTROL WHEEl PART OF 0560059 0 2 21 5 27 02 S 33 02 S UNDER WING COURTESY LIGHTS SETOF 0521101 8 0 5 61 0 2 33 03 S _NAVIGATION LIGHT DETECTORS 1221201 3 4 0 0 40 8 33 04 S FLASHING BEACON 0506003 6...

Page 155: ...NCODER 3930402 1 0 9 10 9 TRANSPONDER ANTENNA 3960191 1 0 2 85 3 HARDWARE CABLE ASSEMBLY 3923102 1 0 6 28 9 34 14 0 HORIZONTAL SITUATION INDICATOR INSTL 3900016 1 15 3 84 1 NET WT INCREASE REQUIRES 37...

Page 156: ...1 0 SPINNER DOME ASSEMBLY 0550236 14 1 0 42 6 FWD SPINNER BULKHEAD 0552231 1 0 3 40 8 AFT SPINNER BULKHEAD 0550321 10 0 4 37 3 61 03 0 POLISHED SPINNER MilLENNIUM INSTl 0550371 1 0 0 41 0 NET CHANGE 7...

Page 157: ...0 0 95 4 STYLING 25 08 0 SUNVISOR INSTALLATION 0519004 1 MILLENNIUM MILLENNIUM UPHOLSTERY OPTION 0519005 1 25 03 0 PILOT S LEATHERNINYL 0519005 1 SEATS SIDEWALL INSERT MILLENNIUM 0519006 1 UPHOLSTERY...

Page 158: ...1 7 2 43 6 98 D4 A NAV II WITH HSI AVIONICS PKG NET 3900016 43 8 47 0 CHANGE OVER STANDARD AVIONICS PKG 98 Q2 A NAV I AVN PKG 900004 21 3 21 5 22 D2 A SINGLE AXIS AUTOPILOT 13900005 7 2 43 6 34 12 0 H...

Page 159: ...I J I I I...

Page 160: ...6 Trim System 7 6 Instrument Panel 7 9 Pilot Side Panel Layout 7 9 Center Panel Layout 7 9 Copilot Side Panel Layout 7 12 Center Pedestal Layout 7 12 Ground Control 7 12 Wing Flap System 7 13 Landing...

Page 161: ...ts I New Engine Break In And Operation Engine Lubrication System Ignition And Starter System Air Induction System Exhaust System Cooling System Propeller Fuel System Fuel Distribution Fuellndicating F...

Page 162: ...cal Speed Indicator 7 42 Altimeter 7 43 Vacuum System And Instruments 7 43 Attitude Indicator 7 43 Directional Indicator 7 43 Vacuum Gauge 7 45 Low Vacuum Annunciation 7 45 Clock O A T lndicator 7 46...

Page 163: ...1...

Page 164: ...ith attach fittings at the base of the forward door posts for the lower attachment of the wing struts Four engine mount stringers are also attached to the forward door posts and extend forward to the...

Page 165: ...n of the ele vator consists of formed leading edge skins a forward spar aft channel ribs torque tube and bellcrank left upper and lower V type corrugated skins and right upper and lower V type corruga...

Page 166: ...I CESSNA MODEL 172S SECTION 7 AIRPLANE SYSTEMS DESCRIPTION AILERON CONTROL SYSTEM 0585X1017 Figure 7 1_ Flight Control and Trim Systems Sheet 1 of 2 July 8 98 7 7...

Page 167: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTION CESSNA MODEL 172S ELEVATOR TRIM CONTROL SYSTEM 0585X1018 Figure 7 1 Flight Control and Trim Systems Sheet 2 of 2 7 8 July 8 98...

Page 168: ...e thel altimeter and provides caution and warning messages for fuel quantity oil pressure low vacuum and low voitage situations To the right of the flight instruments is a sub panel which contains eng...

Page 169: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTION 40 32 35 41 42 CESSNA MODEL 172S 18 19 20 21 22 23 34 i C 33 0585C1040 7 10 Figure 7 2 Instrument Panel Sheet 1 of 2 Revision 4...

Page 170: ...Control 10 Tachometer 32 Glareshield and Pedestal Dimming Control 11 Vertical Speed Indica tor 33 Fuel Shutolt Valve Control 12 Altimeter 34 Fuel Selector 13 Annunciator Panel 35 Elevator Trim Control...

Page 171: ...ximately 10 each side of center By applying either left or right brake the degree of turn may be increased up to 30 each side of center Moving the airplane by hand is most easily accomplished by attac...

Page 172: ...s moved up or down in a slotted panel that provides mechanical stops at the 10 20 and 30 positions To change I flap setting the flap lever is moved to the right to clear mechanical stops at the 10 and...

Page 173: ...ings provided in the airplane For baggage area and door dimensions refer to Section 6 SEATS The seating arrangement consists of two vertically adjusting crew seats for the pilot and front seat passeng...

Page 174: ...estraint for the user In the front seats the inertia reels are located on the centerline of the upper cabin In the rear seats the inertia reels are located outboard of each passenger in the upper cabi...

Page 175: ...ANE SYSTEMS DESCRIPTION VERTICAL HEIGHT ADJUSTMENT CRANK __ PRESSTO RELEASE AVAILABLE MANUAL PUSH SUDON ADJUSTMENT CESSNA MODEL 172S BUCKLE NON ADJUSTABLE PUSH SUDON E E RELEASE LATCH 0514T1004 Figure...

Page 176: ...oors incorporate a recessed exterior door handle a conventional interior door handle a key operated door lock left door only a door stop mechanism and open able windows in both the left and right door...

Page 177: ...te the window outward ahd hold if there If required either window may be opened at any speed up to 163 KIAS The rear side windows and rear windows are of the fixed type and cannot be opened CONTROL LO...

Page 178: ...lating the lock clockwise to increase friction or counterclockwise to decrease it The mixture control mounted adjacent to the throttle controi is a red knob with raised points around the circumference...

Page 179: ...om a resistance tYpe probe located in the engine accessory case As oil temperature change s the probe resistance changes This resistance is translated into oil temperaturereadingson the cockpit indica...

Page 180: ...ght quarts Oil is drawn from the sump through an oil suction strainer screen into the engine driven oil pump From the pump oil is routed to a bypass valve If the oil is cold the bypass valve allows th...

Page 181: ...the spring loaded START position with the master switch in the ON positio n Ithe starter contactor is closed and the starter now energized will crank the engine When the switch is released it will aut...

Page 182: ...cowl flap cooling system control is required PROPELLER The airplane is equipped with a two bladed fixed pitch one piece forged aluminum alloy propeller which is anodized to retard corrosion The propel...

Page 183: ...to thefuellair control unit where it is metered and directed to a fuel distribution valve manifold which distributes it to each cylinder Fuel flow into each cylinder is contin uous and flow rate is d...

Page 184: ...ately 10 seconds and then remain steady amber The annunciator cannot be turned off by the pilot If the left tank is low the message will read L LOW FUEL If the right tank is low the message will read...

Page 185: ...able in each tank FUEL SELECTOR VALVE The fuel selector valve should be in the BOTH position for takeoff climb landing and maneuvers that involve prolonged slips or skids of more than 30 seconds Opera...

Page 186: ...CATORS oRAlN VALVES 5 TOTAL RIGHT FUEL TANK VENT MECHANICAL LINKAGE ELECTRICAL CONNECTION LEGEND FUEL SUPPLY FUEL SHUTOFF VAlVEKNOB _ __ LEFT FUEL TANK VENT WITH CHECK VALVE 1 1 1 I I Figure 7 6 Fuel...

Page 187: ...j J...

Page 188: ...UANTITY TRANSMITTER FUEL DISTRIBUTION VALVE FUEUAIR CONTROL UNIT DRAIN VALVES 5TQTAL fUEL RESERVOIR DRAIN PLUG DRAIN VALVE lEGEN O FUEL SUPPLY VENT MECHANICAL LINKAGE ELECTRICAL CONNECTION FUEL QUANTI...

Page 189: ...drain valves to provide a means for the examination of fuel in the system for contamination and grade The sYstem should be examined before each flight and after each refueling by using the sampler cu...

Page 190: ...of these symptoms appear the brake system is in need of immediate attention If durin g taxi or landing roll braking action decreases let up on the pedals and then reapply the brakes with heavy pressu...

Page 191: ...GNITION I SWITCH 1 1 1 I MAGNETOS I SENSE GROUND POwE R IN ALI INPUT 1 EXT PWR L RELAY 7 m POWER DISTRIBUTION MODULE EXTERNAL POWER j r ACU I LOW VOLT RELD 1 1 I I I I BUS 2 I FUSE OR CIS I 1 I 1 ALTE...

Page 192: ...CESSNA MODEL 172S SECTION 7 AIRPLANE SYSTEMS DESCRIPTION Figure 7 7 Electrical Schematic Serials 172S8001 lhru 172S8703 Sheet 2 of 2 Dec 30 00 7 30A...

Page 193: ...ORC B I _ I I GNrTlO I SWITCH I I I I MAGNETOS 1 I POWER IN ALl INPUT SENSE r ACU LQWVOlT FIELD GROUND II o c F ALTERNATOR I I EXT I L Y I 7m POWER DISTRIBUTION MODULE J BOX TO ALT FLD EXTERNAL Y R PO...

Page 194: ...OVERHEAD LTS LTSI COU RTESY LTS PWR 12V POWER O TO INSTRUMENTS NST AND IGNITION SWITCH 0 FUEL 11 FUEL PUMP PU P m LANDING S2 lAND LIGHT go TO FLASHING BCN BEACON O TO FLAPS W FLAP 0 AVN BUS 1 B A O TO...

Page 195: ...oil pres ure switch the vacuum transdu ers and the alternator control unit AGU Individual LED bulbs illuminate each message and may be replaced through the rear of the annunciator Illumination intensi...

Page 196: ...GING THE AVIONICS EQUIPMENT Normally both sides of the master switch should be used simultaneously however the BAT side of the switch could be turned on separately to check equipment while on the grou...

Page 197: ...d Avionics Bus 2 With the Avionics Master rocker in the OFF position no electrical power is provided to the avionics even when the Master switch or the individual avionics component equipment switches...

Page 198: ...ops below normal The alternator control unit may be reset by resetting the circuit brea ker If the 10 voltage warning annunciator extinguish es normal alternato charging has resumed however if the ann...

Page 199: ...which will close the battery contactor when external power is applied through the ground service plug receptacle with the master switch turned on This feature is intended as a servicing aid when batt...

Page 200: ...ate these lights place switch in the UP position To deactivate light place in the DOWN position NOTE The strobes and flashing beacon should not be used when flying through clouds or overcast the flash...

Page 201: ...omplished by use of a rheostat and light assembly located underneath the pilot control wheel The light provides downward illumination from the bottom of the control wheel to the pilot s lap area To op...

Page 202: ...HT knob is pushed full in Front cabin hear and ventilating air is supplied by outlet holes spaced across a cabin manifold just forward of the pilot s and copilot s feet Rear cabin heat and air is supp...

Page 203: ...WARD CABIN LOWER VENTILATIN AIR OUTLET RAM AIR Q REAR CABIN VENTILATING AIR OUTLETS 2 CESSNA MODEL 172S HEATER VALVE FORWARD CABIN LOWER VENTILATING AIR OUTLET RAM AIR FLOW 1 VENTILATING AIR HEATED AI...

Page 204: ...ing The switch breakeris located on the Iower Iellside of the instrument panel When the pitot heat switch is turned on the element in the pitot tube is heated electrically to maintain proper operation...

Page 205: ...YelloW arB 129 to 163 Knots ana arec liile 163 nots To jiM irUe air peei il Iitsl elefrtlin pfMsUfe lflliilude anti CiUl1lldelmlemperatUfei Using tHis cabl fel He IhelilWefll lil notJ Unlil pf ssure...

Page 206: ...pointer at the top of the indicator relative to the bank scale which has index marks at 10 20 30 60 and 90 either side of the center mark Pitch and roll attitudes are presented by a miniature airplane...

Page 207: ...SSNA MODEL 172S CODE INLET AIR VACUUM DISCHARGE AIR _ VACUUM SYSTEM AIR FILTER LOW VACUUM SWITCHES CONNECTED TO ANNUNCIATOR PANEL MANIFOLD CHECK VALVE ATIITUDE INDICATOR DIRECTIONAL INDICATOR 0585C101...

Page 208: ...te for normal system operation LOW VACUUM ANNUNCIATION Each engin e driven vacuum pump is plumbed to a common manifold located forward of the firewall From the tee a single line runs into the cabin to...

Page 209: ...sociated plumbing As the airplane approaches a stall the Jow pressure on the upper surface of the wings moves forward around the leading edge of the wings This low pressure creates a differential pres...

Page 210: ...ets at each pilot and passengerstation The hand held microphone contains an integral push to talk switch This microphone is plugged into the center pedestal and is accessible to both the pilot and fro...

Page 211: ...ous points throughout the airframe to reduce interference from precipitation static Under s me severe static conditions loss of radio signals is possible even with static dischargers installed Wheneve...

Page 212: ...IN FIRE EXTINGUISHER A portable Halon 1211 Bromochlorodifluoromethane fire extinguisher is standard and is installed on the floorboard near the pilot s seat where it would be accessible in case of fir...

Page 213: ...AL DECOMPOSITION 3 Antic pate approximately eight s ecorids of ischarge duration Fire extinguishers should be recharged bya qualified fire extinguisher agency after each use Such agencies are listed u...

Page 214: ...ne Owners 8 5 Publications 8 5 Airplane File 8 6 Airplane Inspection Periods 8 7 FAA Required Inspections 8 7 Cessna Inspection Programs 8 8 Cessna Customer Care Program 8 9 Pilot Conducted Preventive...

Page 215: ...l Capacity 8 16 Fuel Additives 8 16 Fuel Contamination 8 20 Landing Gear 8 21 Cleaning And Care 8 21 Windshield And Windows 8 21 Painted Surfaces c C 8 22 Propeller Care 8 23 Engine Care 8 23 Interior...

Page 216: ...oil changes are necessary as well as other seasonal and periodic services The airplane should be regularly inspected and maintained in accordance with information found in the airplane maintenance ma...

Page 217: ...erial number airplanes The Finish and Trim Plate located on the lower part of the left forward doorpost contains a code describing the exterior paint configuration for the airplane The code may be use...

Page 218: ...ories please complete and return an Owner Advisory Application Receipt of a valid Owner Advisory Application will establish your Cessna Owner Advisory service for one year after which you will be sent...

Page 219: ...anual which is lostor destroyed may be replaced by contacting your local Cessna Service Station An affidavit containing the owner s name airplane serial number and reason for replacement must be inclu...

Page 220: ...ents Cessna recommends that these items plus the Pilot s Checklists Customer Care Program Handbook and Customer Care Card be carried in the airplane at all times AIRPLANE INSPECTION PERIODS FAA REQUIR...

Page 221: ...each 200 hours and are recorded in a speciaJly provided Aircraft Inspection Log as each operation is conducted The PhaseCard Inspection Program offers a parallel system for high utilization flight op...

Page 222: ...program you choose to establish for your airplane While these important inspections will be performed for you by any Cessna Service Station in most cases you will prefer to have the Cessna Service St...

Page 223: ...l utilizing only FAA Approved components and FAA Approved data such as Cessna Service Bulletins GROUND HANDLING TOWING The airplane is most easily and safely maneuVered by hand with the tow bar attach...

Page 224: ...ol lock over the fin and rudder 3 Tie sufficiently strong ropes or chains 700 pounds tensile strength to the wing tail and nose tie down fittings and secure each rope or chain to a ramp tie down 4 Ins...

Page 225: ...of suitable stands or supports under weight supporting bulkheads near the nose of the airplane LEVELING Longitudinal leveling of the airplane is accomplished by placing a level on leveling screws loc...

Page 226: ...zing in cold weather if the airplane is to be stored temporarily or indefinitely refer to the Maintenance Manual or proper storage procedures SERVICING In addition to the P reflight Inspection covered...

Page 227: ...Refill the engine and continue to use until a total of 50 hours has accumulated or oil consumption has stabilized MIL L 22851 or SAE J1899 Aviation Grade Ashless Dispersant Oil Oil conforming to Textr...

Page 228: ...urer NOTE During the first 25 hour oil and filter change a general inspection of the overall engine compartment is required Items which are not normally checked during a preflight inspection should be...

Page 229: ...city when refueling and minimize cross feeding the fuel selector valve should be placed in either the LEFT or RIGHT position and the airplane parked in a wings level normal ground attitude Referto Fig...

Page 230: ...e fuel provides two distinct effects 1 it absorbs the dissolved water from the gasoline and 2 alcohol has a freezing temperature depressant effect NOTE When using fuel additives it must be remembered...

Page 231: ...H t H H f i f t J H H j J_ H t j i 1 1 H t1 10 20 30 GALLONS OF GASOLINE j 1 _ t j j 4 j f j i j I J_ t itt j t I_ _ j H t i ti ttt t t i i t l i I tr H H j LH t t h rH I I i j j H j f t r t t t 60 50...

Page 232: ...PORTANT A CONCENTRATION IN EXCESS OF THAT RECOMMENDED 0 15 BY VOLUME MAXIMUM MAY RESULT IN DETRIMENTAL EFFECTS TO THE FUEL TANK SEALANT AND DAMAGE TO O RINGS AND SEALS USED IN THE FUEL SYSTEM AND ENGI...

Page 233: ...r repeated sampling evidence of contamination still exists the airplane should not be flown Tanks should be drained and system purged by qualified maintenance personnel All evidenceof contamination mu...

Page 234: ...ANING AND CARE WINDSHIELD AND WINDOWS The plastic windshield and windows should be cleaned with ani aircraft windshield cleaner Apply the cleaner sparingly with soft cloths and rub with moderate press...

Page 235: ...oaps or detergents which cause corrosion or scratches should never be used Remove stubborn oil and grease with a cloth moistened with Stoddard solvent Take special care to make sure that the exterior...

Page 236: ...mall nicks on the propeller particularly near the tips and on the leading edges should be dressed out as soon as possible since these nicks produce stress concentrations and if ignored may result in c...

Page 237: ...spot clean the area Oily spots may be cleaned with 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...

Page 238: ...cable supplements have been placed in the Pilot s Operating Handbook POH Supplements may be removed from the POH provided the equipment is not installed on the airplane If equipment is installed on th...

Page 239: ......

Page 240: ...BY CONTACTING CESSNA CUSTOMER SUPPORT AT 316 517 5800 SUPP SUPPLEMENT NAME REVISION EQUIPMENT NO LEVEL INSTALLED 1 Bendix King KX 155AVHF 0 NAV COMM with KI208 or KI 209A Indicator Head 2 Bendix King...

Page 241: ...Bendix King KAP 140 5 Axis Autopilot v I 16 Bendix King KT 73 Mode S 0 Transponder 17 Reserved 18 Reserved 19 Bendix King KLN 94 Global 4 Positioning System 20 Bendix King KMA 28 Audio Selector 0 Pane...

Page 242: ...ATOR HEAD SERIAL NO __ _ REGISTRATION NO _ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual FAA APPROVAL I AAAP ROVEDUNOERfAR 2...

Page 243: ...TY PAGES PAGE DATE PAGE DATE _ t Title S1 1 July 8 98 S1 9 July 8 98 S1 2 July 8 98 Sl 10 July 8 98 S1 3 July 8 98 S1 11 July 8 98 S1 4 July 8 98 S1 12 July 8 98 S1 5 July 8 98 S1 13 July 8 98 S1 6 Ju...

Page 244: ...calizer signals between 108 00 and 117 95 MHz in 50 kHz steps The glide slope receiver is automatically tuned when a localizer frequency is selected The circuits required to interpret the VOR and loca...

Page 245: ...knob in to attenuate the Id nt signal and still hear Nav voice All controls for the NavlComm except those for navigation course selection are mounted on the front panel of the receiver transmitter Co...

Page 246: ...7 6 PULL OBS 7 STBY KI 209A INDICATOR NAY 8 1 Il bO 39 51 J ET ULL 5K 3 00 I 10 9 STBY 12 11 22 1 cOMM 18 KI 208 INDICATOR HEAD TO INDICATION FROM INDICATioN I FLAG INDICATION I KX15 VHF NAV CC MM Fig...

Page 247: ...BEARING CDI FORMAT I g _ _ _ n VOR MODE ACTIVE BEARING FLAG DISPLAY 109 50 VOR MODE ACTIVE BEARING TO FUNCTION DISPLAY 109 50 VOR MODE ACTIVE BEARING FLAG DISPLAY 10 90 LO _ LOCALIZER MODE FREQUENCY C...

Page 248: ...ial from the VOR station or a count up count down timer With an active localizer frequency this portion of the display shows the standby frequency the letters LOC or count up count down timer 4 NAV FR...

Page 249: ...er NAV frequency knob and turning it This OBS display is independent of any OBS course selected on an external COl An OBS in the middle of the NAV display will flash while the inner NAV frequency knob...

Page 250: ...requency transfer button for 2 seconds or more causing the ET on the display to flash In this state the timer can be set as a countdown timer or the elapsed timer can be restarted The countdown timer...

Page 251: ...sired channel can be selected by turning the comm kHz knob The channel frequency can be entered by pushing the comm transfer button which will cause the standby frequency to flash The comm frequency k...

Page 252: ...o the display Push the COMM TRANSFER button again to return to the aCtive standby display The transceiver is always tuned to the frequency appearing in the ACTIVE display It is therefore possible to h...

Page 253: ...up with 120 00 MHz in the COMM use frequency and 110 00 MHz in the NAV active frequency with both COMM and NAV in the active entry mode This will aid the pilot in blind tuning the radio SECTION 4 NORM...

Page 254: ...Speaker Selector on audio control panel SET to desired mode 4 NAV Volume Control a ADJUST to desired audio level b PULL out to identify station VOR OPERATION Channel the NAV Receiver to he desired VO...

Page 255: ...Button When the Pilot Config Mode is entered the unit will show the SWRV mnemonic which is the unit software revision level Adjustment pages can be accessed by MODE butto presses The pilot may adjust...

Page 256: ...t configuration mode The NAV returns to its pre Pilot Config state with the new brightness and sidetone levels stored in nonvolatile memory SECTION 5 PERFORMANCE There is no change to the airplane per...

Page 257: ...I i II I j I I I I j ___ ill...

Page 258: ...SERIAL NO _ _ REGISTRATION NO _ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual FAA APPROVAL AA APPROVED UNDEfl FAR 2 SUBPART...

Page 259: ...o Original July 8 1998 LOGOF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S2 1 July 8 98 o S2 6 July 8 98 S2 2 July 8 98 S2 7 July 8 98 S2 3 July 8 98 S2 8 July 8 98 S2 4 July 8 98 S2 9 July 8 98 S2 5...

Page 260: ...s interrogating pulse signals on 1030 MHz and transmits coded pulse train reply signals on 1090 MHz It is capable of replyin g to Mode A aircraft identification and also to Mode C altitude reporting i...

Page 261: ...preprogram any single code such as 1200 into the KT 76C Pressing the VFR button instantly returns the KT 76C to the preprogrammed code without having to manually enter 1200 All Bendix King Transponder...

Page 262: ...isplay The display is in hundreds of feet FL is annunciated to indicate Flight Level altitude Flight Level is a term to indicate that the altitude is not true altitude but barometric altitude which is...

Page 263: ...bles transponder to transmit Mode A aircraft identification reply pulses ON is annunciated ALT Turns set on and enables transponder to transmit either Mode A aircraft identification reply pulses and M...

Page 264: ...NCY SIGNAL 1 Mode Selector Knob ALT 2 Numeric Keys 0 7 SELECT 7700 operating code TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN IN A CONTROLLED ENVIRONMENT 1 Mode Selector Knob ALT...

Page 265: ...H will illuminate steadily indicating IDENT operation TO TRANSMIT MODE C ALTITUDE REPORTING CODES IN FLIGHT 1 Transponder Code Selector Knob SELECT assigned code 2 Mode Selector Knob ALT NOTES When d...

Page 266: ...e Button PRESS while still holding lOT button to place new VFR code in nonvolatile memory for subsequent call up SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic...

Page 267: ......

Page 268: ...EGISTRATION NO _ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual FAA APPROVAL PM APPROVED UNDER FAR 2 SUBPART J The Cessna Air...

Page 269: ...July 8 1998 1 May 30 2000 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S3 1 May 30 00 83 6 July 8 98 83 2 May 30 00 83 7 July 8 98 83 3 July 8 98 83 8 May 30 00 83 4 July 8 98 83 9 July 8 98 83...

Page 270: ...or PA Unused position All operating controls are shown and deScribed in Figure 1 A crystal controlled superheterodyne marker beacon receiver with 3 light presentation is incorporated within the unit D...

Page 271: ...l as the audio tones identify the beacon type iNNER AIRWAY and FAN Light illuminates white to indicate passage of ILS inner airway or fan marker beacons OUTER Light illuminates blue to indicate passag...

Page 272: ...The AUX position could be used for example for a second DME or ADF When a receiver s audio is selected the green annunciator illuminates at the bottom of the button Push the button again to deselect t...

Page 273: ...ll disable the feature Initially when MONI is selected the green annunciators in the button flash for approximately 5 seconds then remains steady while the Com annunciation returns to its previous sta...

Page 274: ...solated from the intercom while the copilot and passengers are on the same intercom loop and do not hear the radios When either the ALL or CREW intercom modes are selected the pilot s and copilot s in...

Page 275: ...KMA 26 as evidenced by the inability to transmit in COM 1 2 or 3 1 MIC Selector Switch EMG NOTE This aCtion bypasses th e KMA 26 audio amplifier and conn cts the pilot s mic head set directly to COM...

Page 276: ...ational 2 SENS Selections Select HI sensitivity for airway flying or LO for ILS LOC approaches SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is insta...

Page 277: ......

Page 278: ...g Handbook and FAA Approved Airplane Flight Manual when the Pointer Model 3000 11 or Model 4000 11 Emergency Locator Transmitter is installed The Pointer Model 4000 11 Emergency Locator Transmitter is...

Page 279: ...00 Revision 2 7 July 2003 APPROVED BY AAAPPROIIEDUNDER FAA 21 SU IPlIIlRTJ TllI r AIrlnft 00 e 7 cn 63 l tM DATE OF APPROVAL LOG OF EFFECTIVE PAGES Page Page Revision Status Number S4 1 thru 54 3 S4 4...

Page 280: ...91 A Also a remote switch annunciator is installed on the top right hand side of the copilot s instrument panel for control of the ELT from the flight crew station The annunciator which is in the cent...

Page 281: ...TOR pOinter NSMITIER POINTER INC TEMPE Il Z 4 3 1 ON I Q I o T RESET 2685P6012 5 Arms transmitter for automatic activation if G switch senses a predeterminec deceleration level Activates transmitter i...

Page 282: ...ransmitter is transmitting a distress signal AUTO Arms transmitter for autbmatic activation if G switch senses a predetermined deceleration level RESET Deactivates and rearms transmitter after automat...

Page 283: ...cue and to reset the automatic activation function The red annunciator in the center of the remote switch annunciator should extinguish 5 REMOTE SWITCH ANNUNCIATOR 3 position rocker switch ON Remotely...

Page 284: ...osition remote switch annunciator to the ON position even if annunciator light is already on b If airplane radio is operable and can be safely used no threat of fire or explosion turn ON and select 12...

Page 285: ...position the remote switch annunciator in the RESET position and release to the AUTO position The ELT must be serviced in accordance with FARPart 9 1 207 INSPECTIONITEST 1 The emergency locator trans...

Page 286: ...FLIGHT MONITORING AND REPORTING Pilot s are encouraged to monitor 121 5 MHz and or 243 0 MHz while in flight to assist in identifying possible emergency ELT transmissions On receiving a signal report...

Page 287: ...I 1 I 1 i 1 I j I II I 1 j 1 j I 1 I...

Page 288: ...upple ment must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Global Positioning System _ is installed FAA APPROVAL flM AI PROveOUNOER F...

Page 289: ...ent revision will carry the date of that revision Revision Level Date of Issue o Original July 8 1998 1 May 21 1999 2 May 30 2000 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S5 1 May 30 00 S5 1...

Page 290: ...LLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only thos...

Page 291: ...egrity Monitoring RAIM is a function that every IFR certified GPS receiver must continuously perform to assure position accuracy RAIM is available when 5 or more of these satellites are in view or 4 s...

Page 292: ...THE DATABASE IS BEING UPDATED NOTE A current database is required by regulation in order to use the KLN 89B GPS system for nonprecision approaches Provided the KLN 89B navigation system is receiving...

Page 293: ...KLN 89B does not necessarily constitute approval for use in foreign airspace NOTE S5 6 When the KLN 89B contains receiver software RCVR 01621 0001 or higher dash number as verified on the OTH 6 page t...

Page 294: ...to display the message If a message condition exists which requires a specific action by the pilo the message annunciator will remain on but will not flash 2 GPS WAYPOINT WPT ANNUNCIATOR LIGHT GPS WAY...

Page 295: ...LN 89B GPS system automatically selects the approach ARM mode or when the approach ARM mode is manuallyselected The approach ARM mode will be automatically selected when the airplane is within 30 NM o...

Page 296: ...ring the Course Deviation Indicator COl needle can best be accomplished by pressing the Direct To button and then manually setting the No 1 COl course to the course value prescribed in the KLN 89B dis...

Page 297: ...e currency of the database or verifies each selected waypoint for accuracy by reference to current approved data d The system must utilize ORS Level 02 or later FAA approved revision to conduct nonpre...

Page 298: ...projected to be operational for the flight the aircraft can depart without further action 2 With 22 23 if the altitude input to the KLN 89B is not available or fewer satellites projected to be operati...

Page 299: ...ontinue to navigate using the KlN 89B or revert to an alternate means of navigation appropriate to the route and phase of flight When continuing to use the KlN 89B for navigation position must be veri...

Page 300: ...n followedby pressing the Clear button and finally the Enter Button Refer to the Pilot s Guide section 4 2 2 for an explanation of turn anticipation and Appendix A Navigation Terms for the definition...

Page 301: ...automatically be disabled prior to flying an instrument approach to reduce the potential for message congestion 1 Prior to arrival select a STAR if appropriate from the APT 7 page Select an approach...

Page 302: ...89B altimeter b arosetting as required d Internally theKLN 89B will transition from en route to terminal integrity monitoring 4 Select NAV 4 page to fly the approach procedure a If receiving radar ve...

Page 303: ...THE GPS DISTANCE TO WAYPOINT DECREASING AND NOT MATCHING THE NUMBERS ON THE APPROACH PLATE 5 At or before 2 nm from theFAF inbound i a Select the FAF as the active waypoint if not accomplished already...

Page 304: ...e must be up to date for instrument approach operation Only one approach can be in the flight plan at a time Checking RAIM prediction for your approach while en route using the OTH 3 page is recommend...

Page 305: ...to remind you LefVright CDI needle information is relative to the arc Displayed distance is not along the arc but direct to the active waypoint The DME arc radial is also displayed in the lower right...

Page 306: ...ous selection of the OBS and LEG modes APRARM may be canceled at any time by pressing the GPS APR button A subsequent press will reselect it SECTION 5 PERFORMANCE There is no change to the airplane pe...

Page 307: ...if f fC...

Page 308: ...is suppleme nt must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Automatic Direction Finder is installed FAA APPROVAL F AA APPROveo UND...

Page 309: ...8 1 May 30 2000 y LOG OF EFFECTIVITY PAGES I DATE PAGE PAGE DATE Title S6 1 May 3D DO S6 7 July 8 98 S6 2 May 3D DO S6 8 July 8 98 S6 3 May 3D DO S6 9 July 8 98 S6 4 July 8 98 S6 10 July 8 98 S6 5 Jul...

Page 310: ...witching between pre selected STANDBY and ACTIVE frequencies by pressing the frequency transfer button Both pre selected frequencies are stored in a non volatile memory circuit no battery power requir...

Page 311: ...9 SUPPLEMENTS SUPPLEMENT 6 FAA APPROVED CESSNA MODEL 172S ANT ADF I 2 3 1211 4 10 9 13 8 5 ADF KR87 TSO 7 14 6 15 0585Cl043 0585Cl044 Figure 1 KR 87 Automatic Direction Finder ADF 5heet 1of 4 56 4 JU...

Page 312: ...ave ahd associated morse code identifier broadcast on the carrier wave to be heard NOTE CW signals Morse Code are unmodulated and no audio will be heard without use of BFO This type of signal is not u...

Page 313: ...se knobs are also used to set the desired time when the elapsed timer is used in the countdown mode 7 ON OFFNOLUME CONTROL SWITCH ON OFFNOL Controls primary power and audio outpuL level Clockwise rota...

Page 314: ...Indicates relative or magnetic heading of the aircraft The heading must be manually input by the pilot with the heading HOG knob 14 COMPASS CARD Manually rotatable card that indicates relative or mag...

Page 315: ...ency display 3 FRO Button PRESS to move the desired frequency from the standby to the active position 4 ADF Selector Switch on audio control panel SELECT as desired 5 OFFNOL Control SET to desired vol...

Page 316: ...utton PRESS once or twice until FLT is annunciated Timer will already be counting since it is activated by turning the unit on 3 OFFIVOL Control OFF and then ON if it is desired to reset the flight ti...

Page 317: ...til ET is annunciated 3 SETIRST Button PRESS until the ET annunciation begins to flash 4 FREQUENCY SELECTOR KNOBS SET desired time in the elapsed time display The small knob is pulled out to tune the...

Page 318: ...tor to ANT and listening for station call letters ELECTRICAL STORMS In the vicinity of electrical storms an ADF indicator pointer tends to swing from the station tuned toward the center of the storm N...

Page 319: ...e 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 may result in a minor reducti...

Page 320: ..._ This supplement must be inserted into Section 9 of the Pilat s Operating Handbook and FAA Approved Airplane Flight Manual when the KAP 140 Single Axis Autopilot is installed FAA APPROVAL AA APPROVED...

Page 321: ...ected by 1he current revision are indicated by an asterisk preceeding the page number t t t A Supplement Status Date Original Issue 8 July 1998 Revision 1 30 May 2000 Rev ision 2 31 OC 9ber 2002 t 6 L...

Page 322: ...is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that are currently...

Page 323: ...I I...

Page 324: ...the airplane in the commanded lateral altitude The KAP 140 will provide wing leveler heading hold NAV track and approach and backcourse lateral modes A lockout device prevents autopilot engagement un...

Page 325: ...2S The following circuit breakers are used to protect the listed elements f the KAP 140 single axis autopilot 4 S76 LABEL AUTO PilOT WARN FUNCTIONS Supplies power to the KC 140 Computer and the autopi...

Page 326: ...L WHEEL 9 CIRCUIT BREAKER 11 GPS AUTOPILOT COMPUTER ill liD 0 NAVIGATION SOURCE SELECTOR SWITCH 8 HORIZONTAL SITUATION INDICATOR 7 NAVlCOM 1 CONTROL PANEL ELECTRICAL BUS 05851054 Figure 1 Bendix King...

Page 327: ...ds the airplane to turn to and maintain the heading selected by the heading bug on the Directional Gyro or H51 if installed A new heading may be selected at any time and will result in the airplane tu...

Page 328: ...This mode functions indentically to the approach mode except that the autopilot response to LOC signals is reversed 7 HEADING SELECT KNOB HOG Positions the heading pointer bug on the compass card Not...

Page 329: ...adhered to 1 The autopilot must be OFF during takeoff and landing 2 During autopilot operation the pilot with seat belt fastened must be seated in the lefUront seat 3 Continued autopilot sysiem use is...

Page 330: ...means of removing power from the autopilot In addition to the above power may be removed with the Engage Disengage button or the airplane MASTER switch If necessary perform steps a and b above then tu...

Page 331: ...halo a6Wh tna AiP bisoswiteh throUghoUI tHe recovery ManipUiate the cantrilis as reqUired to salely maintain operation 51 the airpiane wiihih aii 01 its operating iimiiatlBf1s fhe Avi5NiCS MAsT R sWi...

Page 332: ...s already reverted to a default mode _ of operation i e ROL mode An immediateattempuo reengage the lost mode may be made if the offending navigation flag has cleared Effects of instrument losses upon...

Page 333: ...d by PFT pre flight test with an increasing number for the sequence steps Successful completion of self test is identified by all display segments being illuminated Display Test and the disconnect ton...

Page 334: ...ng COMMAND TURNS HEADING HOLD MODE ENGAGED 1 Heading Selector Knob MOVE bug to the desired heading Autopilot will automatically turn the aircraft to the new selected heading NAV COUPLING 1 When equipp...

Page 335: ...center the HOG mode will disengage upon selecting NAVmbde The NAV annunciator will then illuminate and the capture track sequence will automatically begin 2 When equipped with HSI a Course Bearing Po...

Page 336: ...t the HDG bug to the approach course If HDG mode was in use at the time of APR button selection a 45 intercept angle will then be automatically estabiished based on the positon of the bug NOTE All ang...

Page 337: ...RARM when the computed capture point is reached the ARM annunciator will go out and the selected course will be automatically captured and tracked 2 If the D Bar is less than 2 to 3 dots from center t...

Page 338: ...n 2 to 3 dots from center the autopilot will annunciate REV ARM when the computed capture point is reached the ARM annunciator will go out and the selected back course will be automatically captured a...

Page 339: ...atically begin d Airspeed MAINTAIN 90 KIAS during autopilot ap proaches recommended MISSED APPROACH 1 AlP DISC PRESS to disengage AP 2 MISSED APPROACH EXECUTE 3 AP Button PRESS if AP operation is desi...

Page 340: ...REGISTRATION NO _ _ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Winterization Kit is installed FAA APPROVAL AA _...

Page 341: ...Revision Level Date of Issue l f o Original July 8 1998 LOG OF EFFECTI f1l v PAGES PAGE DATE PAGE DATE Title S8 1 July 8 98 S8 2 July 8 98 S8 3 July 8 98 58 4 July 8 98 SERVICE BULLETIN CONFIGURATION...

Page 342: ...Uld be installed for DperatiDns in temperatures cDnsistently belDw 20 F 7 C Once installed the crankcase breather insulatiDn is approved fDr permanent use regardless 6hemperature SECTION 2 LIMITATIONS...

Page 343: ...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...

Page 344: ...NO _ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Davtron Clock G A T is installed FAA APPROVAL PAA APMOVEO UNDER...

Page 345: ...inal July 8 1998 LOG OF EFFECTIVITY PAGES Revision Level Date of Issue PAGE DATE PAGE DATE Title S9 1 July 8i98 S9 5 July 8 98 S9 2 July 8 98 S9 6 July 8 98 S9 3 July 8 98 S9 4 July 8 98 SERVICE BULLE...

Page 346: ...are displayed in the upper portion of the unit s LCD window and clock timing functions are displayed in the lower portion of the unit s LCD window The digital display features an internal light back l...

Page 347: ...button down for three seconds Proper operation is indicated by the display 88 88 and activation of all four annunciators O A T VOLTMETER OPERATION r Ii r to _ The upper portiOli of the LCD window is d...

Page 348: ...d each button push increments the digit Once the tens of hours is set the SELECT button selects the next digit to be set After the last digit has been selected and set with the CONTROL button a final...

Page 349: ...esets elapsed time to zero SETTING ELAPSED TIME COUNT DOWN Use the SELECT button to select Elapsed Time ET i Simultaneously press both the SELECT and the CONTROL buttons j to enter the set mode The te...

Page 350: ...pplement must be inserted into Section 9 of the Pilot s Ope ating Handbook and FAA Approved Airplane Flight Manual when the Global Positioning SyS t m is installed FAA APPROVAL AA APPROVED UNDER FAR 2...

Page 351: ...hat revisio n _ I Revision Level o Original 1 Date of Issue July 8 1998 May 30 00 LOG OF EFFECTIVITY PAGES _ PAGE Title S10 1 S10 2 S10 3 S10 4 DATE May 30 00 May 30 00 May 30 00 July 8198 DATE SERVIC...

Page 352: ...9 may be found in the Bendix King KLN 89 Pilot s Guide supplied with the unit This pilot guide must be available during operation of the KLN 89 unit SECTION 2 LIMITATIONS Use of the KLN 89 is limited...

Page 353: ...airplane normal operating procedures with the KLN 89 GPS installed SECTION 5 PERFORMANCE There is no change to the airplane performance when the KLN 89 GPS is installed However installation of an ext...

Page 354: ...This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when used for Canadian Operation FAA APPROVAL AA APPROveo UNDER FAR 21 SUBPAR...

Page 355: ...evision Level Date of Issue o Original July 8 1 998 LOG OF EFFECTIVITY PAGES I l o PAGE Title 812 1 812 2 DATE July 8 98 July 8 98 PAGE 812 3 S12 4 Iy DATE July 8 98 July 8 98 SERVICE BULLETIN CONFIGU...

Page 356: ...supplement is required for Canadian operation of Cessna Model 172S SECTION 2 LIMITATIONS The following placard must be installed 1 Near the fuel tank filler cap FUEL 100LU 100 MIN GRADE AVIATION GASOL...

Page 357: ...e to the airplane emergency procedures when used for Canadian operation SECTION 4 NORMAL PROCEDURES There is no change to basic airplane normal operating procedures when used for Canadian operation SE...

Page 358: ...RIAL NO __ REGISTRATION NO _ This supplement must be inserted into I Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when Horizontal Situation Indicator is installe...

Page 359: ...Revision Level Date of Issue o Original Jan 15 1999 1 May 30 2000 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title 813 1 May 30 00 813 5 Jan 15 99 813 2 May 30 00 S13 6 Jan 15 99 813 3 May 30 00 813...

Page 360: ...el mounted KI 525A indiCator combines the display functions of both the standard Directional Gyro Heading Indicator and the Course Deviation Indicator s VOR LOC Glideslope information to provide the p...

Page 361: ...h respect to magnetic north The gyro is remote mounted and electric driven 2 NAV FLAG FI g is in view when the NAV receiver signal is inadequate _ _ 3 HEADING REFERENCE LUBBER LINE Magnetictieading ap...

Page 362: ...0 COMPASS CARD Rotates to display heading of airplane with reference to lubber line on HSI 11 COURSE SELECTOR KNOB t Positions the course bearing pointer on the compass card by rotating the course sel...

Page 363: ...e for the Compass System 3 CW CCW COMPASS MANUAL SLAVE SWITCH With the manual automatic compass slave switch in the FREE position allows manual compass card slaving in either the clockwise or counterc...

Page 364: ...BLE HEADING INFORMATION Normal procedures for operation of this system differ little from those required for the more conventional Course Deviation Indicators However several small differences are wor...

Page 365: ...he Autopilot Supplements in the Supplement section of this handbook A description of course datum and autopilot procedures for course datum are incorporated in the appropriate autopilot supplements SE...

Page 366: ...must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the KAP 140 2 Axis Autopilot System is installed FAA APPROVAL AA APPROVED UNDER FAR 2 SUB...

Page 367: ...ted by an asterisk J preceeding the page number 1 t Supplement Status Date Original Issue 28 December 1999 Revision 1 30 May 2000 Revision 2 30 December 2000 Revision 3 28 June 2002 Revision 4 31 Octo...

Page 368: ...owing is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that are curre...

Page 369: ...the pilot when the autopilot is not engaged The electric trim system is designed to be fail safe for any single inflight trim malfunction Trim faults are visually and aurally annunciated A lockout dev...

Page 370: ...2S9423 and On automated Roll Steering functionality has been added to the BendixlKing KLN 94 GPS Navigation System and the KAP 140 2 Axis Autopilot System Roll Steering coupling between the GPS and th...

Page 371: ...ENT 15 FAA APPROVED CESSNA MODEL 172S NAVICOMM1 CONTRO WHEEL I I I I I I r I I I TURN COORDINATOR WARN C I B 07851026 I Figure 1 Bendix King KAP 1402 Axis Autopilot Schematic Serials 172S8348 thru 172...

Page 372: ...AA APPROVED I I I I I I r I I I I r I I I NAVIGATION SOURCE 12 SELECTOR SWITCH 5 lECTR1CA WA RN BUS URN COORDINATOR ROLL STEERING C I B 07851026 Figure 1 Bendix King KAP 140 2 Axis Autopilot Schematic...

Page 373: ...basic roll ROL mode which functions as a wing leveler and the pitch axis vertical speed VS mode The commanded vertical speed will be displayed in the upper right corner of autopilot display area The...

Page 374: ...e and tracking of VOR GPS LOC and Glideslope GS on an ILS as selected for presentation on 1 CDI APR mode tracking sensitivity is recommended for instrument approaches 7 BACK COURSE APPROACH REV MODE B...

Page 375: ...FPM synchronizing the Al T reference to the actual airplane altitude upon button release 10 AUTO PilOT CIRCUIT BREAKER A 5 amp pull off circuit breaker supplying 28 VDC to the KAP 140 system 11 WARN C...

Page 376: ...sfied the request for trim for a period of 10 seconds A solid without an arrowhead is an indication of a pitch trim fault Refer to the EMERGENCY PROCEDURES for proper response to a pitch trim fault 17...

Page 377: ...e setting to match that of the airplane s altimeter when manual adjustmentis required In some systems the baro setting may be automatically synched to that of the altimeteL 2 BARO SET BAR 0 BUDON When...

Page 378: ...FPM for 3 seconds If the BARO button is pushed the display changes 10 the autopilot baro setting in either IN HG or HPA for 3 seconds NOTE this display may be dashed for up to 3 minutes on start up i...

Page 379: ...A 28 _will prevent flight centrpl system alerts from being heard 5 The system is appreved fer Categery I eperatien only Approach mede selected 6 Autepilet maximum airspeed limitatien 140 KIAS Autepile...

Page 380: ...rcuit Breaker PULL NOTE The AVIONICS MASTER Switch may be used as an alternate means of removing all electric power from the autopilot and electric trim systems If necessary perform steps 1A thru 1C a...

Page 381: ...ntrol of the airplane Immediately grasp the control wheel and press and hold down the NP DISCITRIM INT switch throughout the recovery Manipulate the controls as required to safely maintain operation o...

Page 382: ...d pulled Return the AVIONICS MASTER switch to the ON position as soon as possible With the AVIONICS MASTER switch off all avionics and autopilot equipment will be inoperable 5 It is important that all...

Page 383: ...ed P lamp was the result of some abnormal accelerations on the airplane the annunciation should go out within approximately one minute and normal use of the autopilot will be re established 2 A red R...

Page 384: ...for 5 seconds upon selection of NAV APR or REV modes to remind the pilot to set the HDG bug for use as course datum Effects of instrument losses upon autopilot operation 1 Loss of the artificial horiz...

Page 385: ...ntrol b AlP DISCITRIM INT Switch PRESS and HOLD throughout recovery I c AIRPLANE RETRIM Manually as Needed d AUTO PILOT Circuit Breaker PULL SECTION 4 NORMAL PROCEDURES A I I I PREFLIGHT PERFORM PRIOR...

Page 386: ...M TEST as follows a LH SWITCH PUSH FORWARD to ON position and hold OBSERVE NO MOVEMENT of Elevator Trim Wheel Rel lase switch to Center OFF Position NOTE If movement of the elevator trim wheel is obse...

Page 387: ...SE AlP DISCITRIM INT Switch OBSERVE MOVEMENT of Elevator Trim Wheel in proper direction Release LH and RH Switches to center OFF position NOTE During Steps e and f verify movement of elevator trim tab...

Page 388: ...D BE PREPARED TO DISCONNECT THE AUTOPILOT AND TAKE IMMEDIATE CORRECTIVE ACTION INCLUDING MANUAL CONTROL OF THE AIRPLANE ANDIOR PERFORMANCE OF EMERGENCY PROCEDURES IF AUTOPiLOT OPERATION IS NOT AS EXPE...

Page 389: ...ng output will command the autopilot to turn and intercept the course to the new active waypoint without directly overflying the immediate waypoint except designated fiyover waypoints Distance from th...

Page 390: ...ude is displayed NOTE An altitude alert is annunciated 1000 ft prior to arrival at the selected altitude Airplane deviations greater than 200 feet above or below the selected altitude will produce an...

Page 391: ...AUTOPILOT AND RETURN THE AIRPLANE TO A STABILIZED CLIMB PRIOR TO RE ENGAGMENT I WHEN OPERATING AT OR NEAR THE MAXIMUM AUTOPILOT SPEED IT WILL BE NECESSARY TO REDUCE POWER IN ORDER TO MAINTAIN THE DESI...

Page 392: ...a Capture preselected altitudes if installed 1 ALTITUDE SELECT knob ROTATE until the desired altitude is displayed Note ARM annunciation occurs automatically with altitude selection when the autopilo...

Page 393: ...autopilot does not use the attitude gyro as a pitch reference it is recommended that the autopilot be disconnected and that the airplane be flown by hand in severe turbulence c Changing altitudes 1 U...

Page 394: ...nob SELECT desired course 2 NAV Mode Selector Button PRESS Note NAVARM annunciated 3 Heading Selector Knob ROTATE BUG to agree with OBS course NOTE When NAV is selected the autopilot will flash HDG fo...

Page 395: ...l automatically begin b When equipped with HSI 1 Course Bearing Pointer SET todesired course 2 Heading Selector Knob SET BUG to provide desired intercept angle and engage HDG mode 3 NAV Mode Selector...

Page 396: ...course makes immediate recovery easier Roll Steering will not function when the GPS is in OBS mode when the autopilot is in HOG or ROL mode or when the autopilot is in NAV mode with NAV selected as t...

Page 397: ...with the desired approach course to provide course datum to the autopilot when using a DG a If the CDI needle is greater than 2 to 3 dots from the center the autopilot will annunciate APRARM when the...

Page 398: ...r the HDG mode will disengage upon selecting APR mode the APR annunciator will illuminate and the capture track sequence will automatically begin 5 Airspeed MAINTAIN 90 KIAS minimum during coupled aut...

Page 399: ...ND heading to provide course datum to the autopilot when using a DG a If the COl needle is greater than 2 to 3 dots from center the autopilot will annunciate REVARM when the computed capture point is...

Page 400: ...uminate and the capture track sequence will automatically begin 5 Airspeed MAINTAIN 90 KIAS minimum during autopilot coupled approaches recommended 9 GLiDESLOPE COUPLING a APR Mode ENGAGED Note GSARM...

Page 401: ...the autopilot will operate in the ROL and VS modes Verify that the airplane Vertical Speed Indicator VS and the Autopilot VS agree NOTE If tracking the ILS course outbound as part of the missed approa...

Page 402: ...RANSPONDER SERIAL NO _ REGISTRATION NO _ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when a Bendix King KT 73 Mode S Trans...

Page 403: ...s to determine the current status of this supplement Pages affected by the current revision are indicated by an asterisk preceding the page numbeL Supplement Status Original Issue Date 22 December 200...

Page 404: ...f Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains only those Service Bulletins that are currently active Numbe...

Page 405: ......

Page 406: ...reporting and Mode S elementary surveillance selective interrogation The transponder receives interrogating signals on 1030 MHz ahd transmits coded reply signals on 1090 MHz In Mode C operation the KT...

Page 407: ...controlled by the avionics light dimming rheostat 2 MODE ANNUNCIATOR Displays FL on the transponder when ALT SBY or GND is selected on the Mode Selector Switch Displays lOT hen the lOT but tori is pu...

Page 408: ...d The Flight ID should be the airplane identification assigned in the flight plan When no flight plan is available the registration marking of the airplane should be used FLT ID is modified by turning...

Page 409: ...ntification reply pulses with altitude information suppressed Transponder identification code is annunciated on the right side of the display ALT Sets transponder to transmit Mode A squawk Mode C alti...

Page 410: ...de Selector Knobs SELECT 7700 operating code TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN IN A CONTROLLED ENVIRONMENT 1 Mode Selector Switch ALT 2 Transponder Code Selector Knobs...

Page 411: ...or Switch is positioned to ON 3 lOT Button PUSH when instructed by ground controller to SQUAWK IDENT R will come on steadily indicating IDENT operation TO TRANSMIT MODE AIC S ALTITUDE REPORTING CODES...

Page 412: ...2 Check all displays come on 3 TEST OK displayed If not refer to the KT 73 Transponder section of the Bendix King Silver Crown Plus Pilot s Guide 4 Mode Selector Switch SELECT desired function SECTIO...

Page 413: ......

Page 414: ...SERIAL NO _ REGISTRATION NO _ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Global Positioning System is installed...

Page 415: ...ted by the current revision are indicated by an asterisk npreceding the page number Supplement Status Date Original Issue Revision 1 Revision 2 Revision 3 Revision 4 6 November 2000 18 December 2000 3...

Page 416: ...CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement rhis list contains only those Servi...

Page 417: ...oroughly studied and VFR operations conducted so that you are totally familiar with GPS navigation before actually using this equipment in IFR conditions At 172S serial number 172S9423 and On automate...

Page 418: ...E THE DATABASE IS BEING UPDATED NOTE A current database is required by regulation in order to use the KLN 94 GPS system for non precision approaches Provided the KLN 94 navigation system is receiving...

Page 419: ...means of long range navigation I FAA approval of the KLN 94 does not necessarily constitute approval for use in foreign airspace I The KLN 94 is qualified foi BRNAV Basic Area Navigation operation in...

Page 420: ...message condition exists which requires a specific action by the pilot the message annunciator will remain on but will not flash 2 GPS WAYPOINT WPT ANNUNCIATOR LIGHT GPS WAYPOiNT annunciator will beg...

Page 421: ...ystem automatically selects the approach ARM mode or when the approach ARM mode is manually selected The approach ARM mode will be automatically selected when the airplane is within 30 NM of an airpor...

Page 422: ...tion Indicator COl needle can best be accomplished by pressing the Direct To button and then manually setting the No 1 COl course to the course value prescribed in the KLN 94 displayed message The Dir...

Page 423: ...annunciator will illuminate steady to inform the pilot that GPS information is being displayed on the NAV 1 COl 4 NAV GPS SWITCH Toggles from Nav 1 to GPS and vice versa to control the type of naviga...

Page 424: ...ing the Direct To button and then manually setting the No 1 CDI course to the course value prescribed in the KLN 94 displayed message The Directional Indicator heading HDG bug must I also be set to pr...

Page 425: ...ved revision b The data on the Self Test page must be verified prior to use I c IFR enroute and terminal navigation is prohibited unless the pilot verifies the currency of the database or verifies eac...

Page 426: ...23 if the altitude input to the KLN 94 is not available or fewer satellites projected to be operational for the flight the availability of the GPS integrity RAIM should be confirmed for the intended...

Page 427: ...nvalid utilize remaining operational navigation equipment as required 2 II a RAIM NOT AVAilABLE message is displayed while conducting an instrument approach terminate the approach Execute a missed app...

Page 428: ...approach mode APR should be used when conducting a coupled GPS approach NOTE NAV or APR coupled DME arc intercepts can result in excessive overshoots aggravated by high ground speeds and or intercept...

Page 429: ...ss especially in the event of unexpected autoflight equipment failure GPS signal loss requires that the pilot immediately select an alternate autopilot navigation source If autopilot function is lost...

Page 430: ...he APT 7 page Select an approach and an initial approach fix IAF from the APT 8 page The most efficient means of getting to these pages is initiated by pressing the PROC PROCEDURE button on the KLN 94...

Page 431: ...und to the FAF NOTE OBS navigation is TO FROM like a VORl without waypoint sequencing b If receiving radar vectors choose VECTORS as the IAF activate vectors when the first vector for the approach is...

Page 432: ...e 2 nm inbound to the FAF c lnternally the KLN 94 will transition from terminal to approach integrity monitoring 7 Crossing the FAF and APR ACTV is not annunciated a Do not descend b Execute the misse...

Page 433: ...oint suffixes in the flight plan i IAF f FAF m MAP h missed approach holding fix The DME arc IAF arc intercept waypoint will be on your present position radial off the arc VOR when you load the IAF in...

Page 434: ...e missed approach in APRARM Flagged navigation inside the FAF may automatically bring up the message page stating PRESS PROC BUTTON NOW FOR NAVIGATION Pressing the PROC button will usually restore nav...

Page 435: ......

Page 436: ...ING KMA 28 AUDIO SELECTOR PANEL SERIAL NO _ REGISTllATlON NO _ This supplement must b 3 inserted into Section 9 Of the Pill l s Operating Handbook and FAA Approv irp ane Flight Manual FAA APPROVAL Dal...

Page 437: ...000 LOG OF EFFECTIVITY PAGES Number Title PAGE DATE PAGE r DATE l i Title S20 1 Dec 30100 S20 7 Dec 30100 S20 2 Dec 30100 S20 8 Dec 30100 S20 3 Dec 30100 S20 9 Dec 30100 520 4 Dec 30100 S20 10 Dec 301...

Page 438: ...are shown and described in Figure 1 An unamplified and unswitched stereo audio input is provided for an entertainment audio source Walkman or similar Portable Electronic Device pED The Entertainment...

Page 439: ...light presentatio n is incorporated within the unit Dimming circuitry for the marker beacon lamps automatically adjusts brightness appropriate to the cockpit ambient light level HI and LO sensitivity...

Page 440: ...sition switch is used to set the receiver sensitivity and to test the annunciator lamps When this switch is on HI upper position the high sensitivity is selected which permits you lohsar the outer mar...

Page 441: ...in the COM 1 position both pilot and copilot will be connected 10 the COM 1 transceiver Only the person who presses their Push Io Talk PD switch will be heard over th aircraft radio TUl ling the rotar...

Page 442: ...he soft mute feature The soft mute feature assures that the aircraft radio transmissions will not be missed due to entertainmen t playing When there is radio reception or intercom conversation _ the m...

Page 443: ...ontinue t6 communicate among themselves Without interrupting the crew and also may listen to Entertainment _Anytime ihe KMA 28 is in either the COM 1 2 or COM 2 1 split modes the pilot and copilot int...

Page 444: ...a of the knob to adjust the loudness of the intercom for the pilot and copilot only It has no effect on selected radio levels music input levels or passenger s volume level Adjust the radios and inter...

Page 445: ...onic device s will not cause interference with the navigation or communication system 01the airplane NOTE During KMA 28 operation in the OFF or EMG position the audio is disabled preventing installed...

Page 446: ...onal 2 SENS Selec1ions Select HI sensitivity for airway flying or LO for ILS LOC approaches The Entertainment audio inputCAUX AUDIO IN is unswitched so there is no means of deselecting the entertainme...

Page 447: ...ng should specify that Entertainment audio input and PED use is permitted only during the enroute phase of flight SECTION 5 PERFORMANCE 1 j L j There is no change to the airplane performance when this...

Page 448: ...I FUNCTION DISPLAY SERIALNO _ REGISTRATION NO _ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the KMD 550 Multi Functio...

Page 449: ...al Dec 30 2000 LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S21 1 Dec 30 00 821 6 Dec 30 00 821 2 Dec 30 00 821 7 Dec 30 00 821 3 Dec 30 00 S21 8 Dec 30 00 821 4 Dec 30 00 S21 9 Dec 30 00 821 5...

Page 450: ...itch and is current protected by the GPS circuit breaker The KMD 550 is operated via a joystick a series of five Power Keys that are located along the right side of the unit a series of Function Selec...

Page 451: ...TION ONLY AWARNING NEVER USE THE WEATHER DISPLAYED ON THIS EQUIPMENT AS YOUR SOLE REFERENCE FOR WEATHER AVOIDANCE CHANGING THE DATABASE CARD To change the da1acard follow these simple steps 1 Turn off...

Page 452: ...not an IFR primary means of navigation system Therefore its use as an advisory navigation system does not mandate that the database be current However it is strongly recommended from a safety viewpoin...

Page 453: ...located in the lower right of the unit are not functional in this installation 9 POWER LABELS When the Power Label is illuminated on the right side of the key that key s function is dedicated to the f...

Page 454: ...r measuring range and bearing to specific points The joystick is also used to modify configuration settings on the AUX setup pages 12 POWER KEYS These five keys are used to manipulate the page being d...

Page 455: ...o seconds These can help provide a reference for monitoring the status of selected functions and overlays GPS DATA SOURCES The KMD 550 accepts GPS data from the KLN 94 The active flight plan and waypo...

Page 456: ...ocedures when the KMD 550 Multi Function Display is installed SECTION 4 NORMAL PROCEDURES There is no change to the airplane normal procedures when the KMD 550 Multi Function Display is installed SECT...

Page 457: ...dt t q q...

Page 458: ...OWER SYSTEM SEAIAlNO _ REGISTRATION NO _ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the 12 Volt Cabin Power System i...

Page 459: ...o Original Dec 30 00 LOG OF EFFECTIVITY PAGES r _ Y r Dec 30 00 S22 5 Dec 30 00 S22 6 Dec 30 00 S22 7 Dec 30 00 S22 8 blank PAGE Title S22 1 S22 2 S22 3 S22 4 DATE i PAGE DATE Dec 30 00 Dec 30100 Dec...

Page 460: ...tronic devices PED The remote power outlet RPO labeled CABIN PWR 12V is located on the lower portion of the cockpit center pedestal See Fig ure 1 The RPO conforms to ARINC 628 Part 2 requirements for...

Page 461: ...motive cigarette lighter socket Radio Shack Cat No 270 1580 or similar Most laptop computer manufacturers and a number of accessory manufacturers Absolute Battery Mobility Electronics USI Extended Mic...

Page 462: ...limitations must be adhered to 1 The 12 Volt Cabin Power System is not certified for supplying power to flight critical communications or navigation devices 2 Use of the 12 Volt Cabin Power System is...

Page 463: ...LECTRIC CURRENT 1 12 volt power shall be limitec to a maximum of 10 amps If a load in excess of this limit is applied to the Cabin Power System connector the CABIN LTS PWR circuit breaker may open or...

Page 464: ...portable electronic device is not permitted during takeoffs and landings NOTE Disconnect the power adapter cable from the Cabin Power System connector whenever the PED portable electronic device is no...

Page 465: ......

Page 466: ...OLT INDICATOR SERIAL NO _ _ _ REGISTRATION NO _ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the Astrotech ClocklOATNo...

Page 467: ...ion Level e Original 1 1 Date of Issue Jan 31 2002 1 C i LOG OF EFFECTIVITY PAGES PAGE DATE PAGE DATE Title S24 1 Jan 31 02 824 4 an 31 02 S24 2 Jan 3f 02 S24 5 Jan 31 02 S24 3 Jan 31 02 S24 6 Jan 31...

Page 468: ...ton is used to control sequencing between temperature and voltage The lower three buttons control reading and timing functions related to the digital clock Temperature and voltage functions are displa...

Page 469: ...k During the set function the button is used to advance the count of the digit currentiy being set When in the Timer Mode the button alternately starts and stops the elapsed counter with each push 3 M...

Page 470: ...window from voltage to Fahrenheit F to Celsius C and back again to voltage CLOCK OPERATIONS The lower LCD window is dedicated to clock and timing operations Pushing the MODE button toggles between clo...

Page 471: ...tton The display will show the date and start the clock running If the minutes were not changed the minutes will continue to run and not need to be restarted When operating in the Timer Mode the word...

Page 472: ...F NAV COMM SERIAL NO _ REGISTRATION NO _ This supplement must be inserted into Section 9 of the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the VHF NAV COMM with Indicator...

Page 473: ...FECTIVITY PAGES PAGE DATE PAGE DATE Title S1 1 Jan 31 02 SI 8 Jan 31 02 SI 2 Jan 31 02 SI 9 Jan 31 02 S1 3 Jan 31 02 SI 10 Jan 31 02 S1 4 Jan 31 02 SI 11 Jan 31 02 S1 5 Jan 31 02 S1 12 Jan 31 02 S1 6...

Page 474: ...pacing The navigation receiver receives VOR and localizer signals between 108 00 and 117 95 MHz in 50 kHz steps The glideslope receiver is automatically tuned when a localizer frequency is selected Th...

Page 475: ...ls for the Nav Comm except those for navigation course selection are mounted on the front panel of the receiver transmitter Control lighting is provided by NAV COMM interior lighting and the instrumen...

Page 476: ...VOR MODE ACTIVE BEARING COl FORMAT 109 50 i030 FLRG _ VOR MODE ACTIV8BEARING FLAG DISPLAY VORE MODE ACTIVE BEARING TO FUNCTION DISPLAY VOR MODE ACTIVE BEARING FLAG DISPLAY I O 90 I LOC LOCALIZER MODE...

Page 477: ...internal COl the bearing to theVOR station radial from the_VOR station or a count up count down timer With an active localizer frequency this portion of the display shows the standby frequency the le...

Page 478: ...red OBS course can be selected by pulling out the inner NAV frequency knob and turning it This OBS display is independent of any OBS course selected on an external CDL An OBS in the middle of the NAV...

Page 479: ...using the ET on the display to flash In this state the timer can be set as a countdown timer or the elapsed timer can be restarted The countdown timer is set by using the NAV frequency inc dec knobs t...

Page 480: ...he COMM TRANSFER button which will cause the standby frequency to flash The comm frequency knobs are then used to enter the desired frequency If dashes located between 136 MHz and 118 MHz are entered...

Page 481: ...sible The desired frequency can be directly entered into the display Push the COMM TRANSFER button again to return to the active standby display The transceiver is always tuned to the frequency appear...

Page 482: ...radio SECTION 4 NORMAL PROCEDURES COMMUNICATION RECEIVER TRANSMITIER OPERATION 1 OFF PULUTEST Volume Control Turn clockwise pull out and adjust to desired audio level push control back in to activate...

Page 483: ...FROM flag as appropriate for the selected course LOC OPERATION Localizer circuitry is energized when the NAV Receiver is channeled to an ILS frequency Monitor the LOC audio and positively identity th...

Page 484: ...oftware Revision Number SWRV Minimum Display Brightness BRIM 0 255 Sidetone Level SIDE 0 255 Subsequent presses of the MODE button sequences through SWRV BRIM SIDE and then back to SWRV Pressing the N...

Page 485: ......

Page 486: ...This supplement must be inserted into Section 9 6f the Pilot s Operating Handbook and FAA Approved Airplane Flight Manual when the airplane is equipped with the Bendix King KDR 510 Flight Information...

Page 487: ...fective Pages to determi the current status of this supplement Pages affected J by the current revision are indicated by an asterisk preceding the page number Supplement Status _ Date LOG OF EFFECTIVE...

Page 488: ...ETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane and have been incorporated into this supplement This list contains oniy those...

Page 489: ...i...

Page 490: ...550 multi function display FIS information is intended to be used as a strategic planning tool to help the pilot avoid inclement weather areas that are beyond his visual range FIS lacks the sufficien...

Page 491: ...e aircraft that display on the KMD 550 The MODE button loggles between different weather related information displays such as switching between METARs and PIREPs It is highly recommended that the pilo...

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