Cessna Hawk XP R172K, Pilot Operating Handbook

Page 1: ...CESSNA MODEL R172K p LOiT S OPERATING HAN BOOK Yt 11 __ _ iI i t t l 1 I...

Page 2: ...RFORMANCE Ground Roll Total Distance Over 50 Ft Obstacle 8TALL SPEED CAS Flaps Up power Off Flaps Down power Off MAXIMUMWEIGHT STANDARD EMPTY WEIGHT Hawk XP Hawk XP II MAXIMUMUSEFUL LOAD Hawk XP Hawk...

Page 3: ...d with your airplane Warranty service is available to you at authorized Ces II Dealers throughout the world upon presentation of your Customer Care Card Whll II e5tablishes your eligibility under the...

Page 4: ...and Entry Dimensions Baggage Space and Entry Dimensions Specific Loadings Symbols Abbreviations and Terminology General Airspeed Terminology and Symbols Meteorological Terminology Engine Power Termin...

Page 5: ...d 195 rated BHP at 2600 RPM PROPELLER Propeller Manufacturer McCauley Accessory Division Propeller Model Number 2A34C203 90DCA 14 Number of Blades 2 Propeller Diameter Maximum 76 inches Minimum 74 5 i...

Page 6: ...should be drained after the first 25 hours of operation Standard Empty Weight Hawk XP 15491bs Hawk XP II 1573 Ibs NOTE STANDARD AIRPLANE WEIGHTS Maximum Useful Load Contincntal Motors Specification M...

Page 7: ...est Rate of Climb Speed is the sp d which results in the greatest gain in altitude in a given Li mo OAT METEOROLOGICAL TERMiNOLOGY 1 6 Outside Air Temperature is the free air stat ic tempera ture It i...

Page 8: ...ent by the total weight of the airplane Center of Gravity Arm is the arm obtained by adding the airplane s individual moments and dividing the sum by the total weight Center of Gravity Limits are the...

Page 9: ...t Limits Normal Category Utility Category Center of Gravity Limits Normal Category Utility Category Maneuver Limits Normal Category Utility Category Flight Load Factor Limits Normal Category Utility C...

Page 10: ...ssociated with optional systems or equipment are included in Section 9 NOTE The airspeeds listed in the Airspeed Limitations chart figure 2 1 and the Airspeed Indicator Markings chart figure 2 2 are b...

Page 11: ...e Arc 46 85 Full Flap Operating Range Lower limit is maximum weight Vs in landing configuration Uppe limit is maximum speed permissible with flaps extended Green Arc 54 129 Normal Operating Range Lowe...

Page 12: ...r less with straight line variation to 37 5 inches aft of datum at 2200 lbs Aft 40 5 inches aft of datum at all weights Reference Datum Lower portion of front face of firewall Figure 2 3 Power Plant I...

Page 13: ...110 knots 105 knots Slow Deceleration Slow Deceleration NOTE Takeoff climb and land with the fuel selector valve handle in the BOTH position Approved Fuel Grades and Colors 100LL Grade Aviation Fuel B...

Page 14: ...S WEIGHT 2550 Ibs FLIGHT LOAD FACTOR Utility Category 105 knots 22001bs 6 On control lock CONTROL LOCK REMOVE BEFORE STARTING ENGINE Flaps Up Flaps Down 3 8 1 52 3 0 4 4 1 76 3 0 2 11 Normal Category...

Page 15: ...tion Airspeeds For Emergency Operation 3 3 3 3 OPERATIONAL CHECKLISTS Engine Failures Engine Failure During Takeoff Run Engine Failure Immediately After Takeoff Engine Failure During Flight Forced Lan...

Page 16: ...lfunctions are extremely rare if proper preflight inspections and maintenance are practiced Enroute weather emergencies can be minimized or eliminated by careful flight planning and good judgement whe...

Page 17: ...Wing Flaps 20 3 Airspeed 65 KlAS 4 Selected Field FLY OVER noting terrain and obstructions then retract flaps upon reaching a safe altitude and airspeed 5 AIl Switches except master and ignition swit...

Page 18: ...FIRE 1 Master Switch OFF 3 6 SJ CTlON J EMERGENCY PROCEDUHES 2 Vents Cabin Air Heat CLOSED to avoid drafts 3 Fire Extinguisher ACTIVATE if available IWARNING After discharging an extinguisher within a...

Page 19: ...PROCEDURES ENGINE FAILURE If an engine failure occurs during the takeoff run the most impor tant thing to do is stop the airplane on the remaining runway Those extra items on the checklist will provid...

Page 20: ...raw fuel accumulations in the exhaust system igniting during an en gine start causing a long flame from the tailpipe and possibly igniting the fuel puddle on the pavement In the event that this occurs...

Page 21: ...tentional flight into known icing conditions is prohibited in this airplane During instrument flights however icing conditions may be encountered inadvertently and therefore some corrective action wil...

Page 22: ...Reduce engine power immediately and select a suitable forced landing field Use only the minimum power required to reach the desired touchdown spot ELECTRICAL POWER SUPPLY SYSTEM MAL FUNCTIONS Malfunct...

Page 23: ...o reactivate the alternator system To do this turn both sides ill 1 111 master switch off and then on again If the problem no longer ex ist no rura l alternator charging will resume and the warning li...

Page 24: ...can be found in Section 9 SPEEDS FOR NORMAL OPERATION Unless otherwise noted the following speeds are based on a maxi mum weight of 2550 pounds and may be used for any lesser weight However to achiev...

Page 25: ...11 i tion Switch OFF 3 Mast Switch ON 4 Fuel Quantity Indicators CHECK QUANTITY 5 Master Switch OFF 6 Fuel Shutoff Valve ON push full in 7 Fuel Selector Valve BOTH 8 Trim Controls NEUTRAL 9 Baggage D...

Page 26: ...located under the fuselage between the firewall and forward door post on all airplane models Consult the pilots Operating Handbook or Owners Manual in order to determine if one or two reservoir s are...

Page 27: ...mixture to idle cut off open the throttle and crank until the engine fires or for approxi mately 15 seconds If still unsuccessful start again using the normal starting procedure after allowing the sta...

Page 28: ...Cowl Flap OPEN CRUISE 1 Power 15 25 INCHES Hg 2200 2600 RPM no more than 80 power 2 Elevator and Rudder Trim ADJUST 3 Mixture LEAN for cruise fuel flow using the EGT gage Cess na Power Computer or th...

Page 29: ...is stopped with the throttle open and the mixture rich solid fuel will collect temporarily in the cylinder intake ports the quantity depending on the amount of the throttle opening and the length of...

Page 30: ...Taxiing Diagram figure 4 2 to maintain directional control and balance BEFORE TAKEOFF WARM UP CODE Since the engine is closely cowled for efficient in flight cooling precautions should be taken to av...

Page 31: ...LIMB Normal climbs are performed at 85 95 KIAS with flaps up and maximum power for the best combination of engine cooling rate of climb and forward visibility The mixture should be leaned in accordanc...

Page 32: ...NMPG KTAS NMPG 12 0 110 12 9 12 3 112 13 1 12 6 114 13 3 Zero Wind 1 01 best fuel economy at 70 power or less the engine may be operated at one gallon per hour leaner than shown in this handbook and o...

Page 33: ...d be appl ied so that full rudder deflection is reached almost simultaneously with reaching full 4 18 I SSNA M I L R172K SECTION 4 NORMAL PROCEDUR S aft elevator A slightly greater rate of deceleratio...

Page 34: ...at normal approach speeds However this does not affect co trol of the airplane Although the crab or combination method of dnft correction may be used the wing low method gives the best control After t...

Page 35: ...wing suggested procedures and thereby tend to build public support for aviation 1 Pilots operating aircraft under VFR over outdoor assemblies of persons recreational and park areas and other noise sen...

Page 36: ...s Takeoff Distance 2400 Lbs and 2200 Lbs Figure 5 5 Rate of Climb Maximum Figure 5 6 Time Fuel and Distance to Climb Maximum Rate of Climb Time Fuel and Distance to Climb Normal Climb Figure 5 7 Cruis...

Page 37: ...rve fuel based on 45 power Fuel flow data for cruise is based on the recommended lean mixture setting Some indeterminate variables such as mixture leaning technique fuel metering characteristics en gi...

Page 38: ...urance profile chart presented in figure 5 9 The relationship between power and range is illustrated by the range profile chart Considerable fuel savings and longer range result when lower power setti...

Page 39: ...flight planning purposes However a further correction for the effect of temperature may be made as noted on the climb chart The approximate effect of a non standard temperature is to increase the tim...

Page 40: ...AND WINDOWS CLOSED FLAPS UP NORMAL KIAS 50 60 70 80 90 100 110 120 130 140 150 160 ALTERNATE KIAS 43 57 69 79 90 100 109 119 128 137 147 156 FLAPS 10 NORMAL KIAS 40 50 60 70 80 85 A LTERNATE KIAS 32 4...

Page 41: ...are approximate MOST REARWARD CENTER OF GRAVITY ANGLE OF BANK WEIGHT FLAP 0 30 45 60 LBS DEFLECTION KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 49 53 53 57 58 63 69 75 2550 10 41 50 44 54 49 59 58 71...

Page 42: ...0 2695 1635 2945 1770 3225 1915 3545 2075 3920 Figure 5 4 Takeoff Distance Sheet 1 of 2 TAKEOFF DISTANCE 2400 LBS AND 2200 BS I SHORT fiELD I REFER TO SHEET 1 FOR APPRQPRIATE CONDITIONS AND NOTES TAKE...

Page 43: ...card Fuel Flow Cowl Flap Open Standard Temperature MIXTURE SETTING PRESSALT GPH S L 16 4000 14 8000 12 12 000 10 NOTES 1 Add 1 4 gallons of fuel for engine start taxi and takeoff allowance 2 Increase...

Page 44: ...e 5 6 Time Fuel and Distance to Climb Sheet 2 of 2 5 16 For best fuel economy at 70 POW I 01 less op erate at 1 GPH leaner than shown in IlJi chart or at peak EGT if an EGT indicatol i Ialled _ 200C B...

Page 45: ...00 24 68 116 9 6 65 116 9 2 63 115 8 9 23 63 112 9 0 61 112 8 7 59 111 8 4 22 59 108 8 4 57 107 8 1 55 106 7 9 21 55 103 7 9 53 102 7 6 51 101 7 4 20 51 98 7 3 49 97 7 1 47 95 6 9 19 46 92 6 8 45 91 6...

Page 46: ...20 59 111 8 5 57 109 8 2 55 109 7 9 19 55 105 7 9 53 104 7 6 51 103 7 4 18 50 100 7 3 48 98 7 0 47 96 6 8 2200 21 60 111 8 5 57 110 8 2 55 109 7 9 20 55 106 7 9 53 105 7 7 51 103 7 4 19 51 100 7 4 49...

Page 47: ...L 123 Ii 116 108 t t t f KTASl KTAS KTAS 96 KTAS S L 450 12 000 10 000 I 8000 w w IJ w 6000 0 J I i J C 4000 2000 NOTE For best fuel economy at 70 power or less op erate at 1 GPH leaner than shown in...

Page 48: ...hort field technique as specified in Section 4 2 Decrease distances 10 for each 9 knots headwind For operation with tailwinds up to 10 knots increase distances by 10 for each 2 knots 3 For operation o...

Page 49: ...NA MODEL R172K SECTION 6 WEIGHT BALANCE EQUIPMENT LIST 1 1 SECTION 6 WEIGHT BALANCE EQUIPMENT LIST TABLE OF CONTENTS Introduction Airplane Weighing Procedures Weight and Balance Equipment List 6 3 6 3...

Page 50: ...all fuel c Remove oil sump drain plug to drain all oil d Move sliding seats to the most forward position e Raise flaps to the fully retracted position f Place all control surfaces in neutral position...

Page 51: ...w w 0 J U f a u 0 J W ci 0 J 0 Z 0 w w Z I J c W a f 0 Datum Sta 0 0 Firewall Front Face l evel at upper door sill or leveling screws on eft side of tailcone N L R 6 5 Scale Position Scale Reading Tar...

Page 52: ...sed on the Sample Loading Prob lem The moment which is shown must be divided by 1000 and this value used as the moment 1000 on the load ing problem Use the Loading Graph to determine the moment 1000 f...

Page 53: ...l o a o I 0 2 tl 1 co OJ s Ol c c OJ C 0 S 5 0 ro t1l 0 z a o w a I u l r 0 e LQ u Z c 6 0 j J r jj en H J c c bJJ 0 QJ _OJ e rl s I z t 0 c c E E 0 co t l O en c en 9 i l0 Cii C 0 Cl E o 0 l U c E 5...

Page 54: ...eats positioned for an average occupant Refer to the loading arrangements diagram for forward and aft limits of occupant c g range 5 Figure 6 6 Loading Graph 2600 2500 00 2400 0 2300 E r 2200 C r l i3...

Page 55: ...ed items of equipment for FAA certification S standard equ ipment items 0 optional equipment items replacing required or standard items A optional equipment items which are in addition to required or...

Page 56: ...C07 A C16 0 C22 A C25 A C28 A C31 A C40 A C43 A C46 A C49 S D01 R 001 0 D04 A D07 R 007 0 1 007 0 2 D10 A D16 A l D16 A 2 J EQUIPMENT LIST DESCRIPTION C ELECTRICAL SYSTEMS BATTERY 12 VOLT 33 AMP HOUR...

Page 57: ...E PIECE BACK CUSHION SEAT REAR TWO PIECE BACK CUSHION SEAT INSTALLATION CHILD S FOLD AWAY LAP BELT ASSEMBLY SEAT ASSEMBLY CHILD S ITEM NO ARM INS EQUIPMENT LIST DESCRIPTION REF DRAWING WT lBS EI5 R El...

Page 58: ...1ST UNIT 3910156 10 23 0 75 5 J 1 TRANSCEIVER PANEL MOUNTED C582103 0102 4 2 10 4 ANTENNA LOAD BO C589502 0101 4 2 112 5 HF POWER SUPPL Y C582103 0201 8 5 114 4 NOTE IST UNIT INSTL COMPONENTS ARE AS...

Page 59: ...3 3950122 4 3960102 10 3960113 1 3910150 58 43340 1124 45010 1000 3910152 40 43340 1124 45010 2000 1 9 0 2 0 3 0 1 1 1 1 2 0 4 0 6 0 8 0 4 14 5 6 9 0 6 14 6 6 9 0 1 ITEM NO H25 A l H2S A l H2S A 2 H31...

Page 60: ...em Air Induction System Exhaust System Fuel Injection System Cooling System Propeller Fuel System Brake System Electrical System Master Switch Ammeter Page 7 3 7 3 7 8 7 8 7 8 7 9 7 9 7 10 7 10 7 11 7...

Page 61: ...ched to the forward doorposts and extend forward to the firewall The externally braced wings containing the fuel tanks are con structed of a front and rear spar with formed sheet metal rib s doublers...

Page 62: ...A MODEL R172K Cl SSNA MODEL R172K AIRPLANl SECTION 7 I l CHIPTIONS AILERON CONTROL SYSTEM HUDDEH AND RUDDER TRIM _ QPNTROL SYSTEMS ELEVATOR TRIM CONTROL SYSTEM Control and Trim Systems Sheet 1 of 2 2...

Page 63: ...io Dial 1 Number Light Rheostats 0 S 10 Tachometer 35 Microphone t J CD r J 11 Encoding Altimeter 36 Cowl Flap Control Lever 0 t J 12 ADF Bearing Indicator 37 Rudder Trim Control Lever Z 13 Omni Cours...

Page 64: ...mer master switch auxiliary fuel pump and ignition switches circuit breakers and electri I SSNA M DEL R172K SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS 1 switches on the left side with the engine controls...

Page 65: ...passenger seats to the aft cabin bulkhead and 7 10 SEATS The seating arrangement consists of two separate adjustable seats or the pilot and front passenger a split backed fixed seat in the rear and a...

Page 66: ...er harnesses shoulder harnesses are available for the rear seat positions Integrated seat belt shoulder harnesses with inertia reels can be furnished for the pilot s and front passenger s seat positio...

Page 67: ...h will allow the inertia reel to pull the harness inboard of the seat 7 14 ENTRANCE DOORS AND CABIN WINDOWS Entry to and exit from the airplane is accomplished throug t oil ho r of two entry doors one...

Page 68: ...knob clockwise and aft by rotating the knob countercloclrwise For large adjustments the knob may be moved forward aft by the lock button in the end of the control and then trol as desired 7 16 I NGINE...

Page 69: ...or the oil temperature is extremely cold 7 18 An oil filler cap oil dipstick is located at the rear of the engine on 1 110 left side The filler cap dipstick is accessible through an access door in the...

Page 70: ...lished by moving the lever to the left to clear a detent then moving the lever up to the OPEN position Anytime the lever is repositioned it must first be moved to the left While in cruise flight the c...

Page 71: ...of the system will result in decreasing fuel flow and eventual engine stop page Venting is accomplished by an interconnecting line from the right fuel tank to the left tank The left fuel tank is vente...

Page 72: ...taxiing fuel tlow provided by the pump is automatically reduced by a throttle uctuated switch preventing an excessively rich mixture during periods of reduced engine speed NOTE If the engine driven fu...

Page 73: ...brakes with the rudder pedals pull the handle aft and rotate it 90 down For maximum brake life keep the brake system properly main tained and minimize brake usage during taxi operations and landings S...

Page 74: ...power The over voltage sensor may be reset by turning the master switch off and back on again If the warning light does not illuminate normal 7 28 m SSNA MODELR172K SECTION 7 AIRPLANE SYSTEMS DESCRIP...

Page 75: ...LTS is used to select flood lighting in the FLOOD position post lighting in the POST position or a combination of post uud flood lighting in the BOTH position Instrument and control panel flood light...

Page 76: ...y outlet holes spaced across a cabin manifold just forward of the pilot s and copilot s feet Rear cabin heat and air is supplied by two ducts from the mani fold one extending down each side of the cab...

Page 77: ...posite the calibrated airspeed RATE OF CLIMB INDICATOR The rate of climb indicator depicts airplane rate of climb or descent in feet per minute The pointer is actuated by atmospheric pressure changes...

Page 78: ...ion be equipped with var ious types of avionics support equipment such as an audio control panel microphone headset and static dischargers The following pa ragraphs discuss these items AUDIO CONTROL P...

Page 79: ...eadset while the passengers listen 1 0another receiver on the airplane speaker The ADF 1 and 2 switches may be used anytime ADF audio is desired If the pilot wants only ADF audio for station identific...

Page 80: ...he ADF is first to be affected and VHF communication equipment is the last to be affected Installation of static dischargers reduces interference from precipi tation static but it is possible to encou...

Page 81: ...er PC and Type Certificate Number TC can be found on the Identification Plate located on the lower part of the left forward doorpost Located adjacent to the Identification Plate is a Finish and Trim P...

Page 82: ...g Book 2 Engine Log Book Most of the items listed are required by the United States Federal 1 v iation Regulations Since the Regulations of other nations may re 1 1 re other documents and data owners...

Page 83: ...on No 1 or the first iOO hour inspection within the first 6 months of ownership at no charge to you If you take delivery from your Dealer the initial inspection will have been performed before deliver...

Page 84: ...ntenance is required the nose wheel may be raised off the ground by pressing down on a tailcone bulkhead just forward of the horizontal stabilizer and allowing the tail to rest on the tail tie down ri...

Page 85: ...com mended intervals Cessna Progressive Care ensures that these requirements are ac complished at the required intervals to comply with the 100 hour or ANNUAL inspection as previously covered Dependin...

Page 86: ...g period will have been completed prior to delivery of the airplane In the event that polishing or buffing Is required within the curing period it is recommended that the work bo done by someone exper...

Page 87: ...and remove it with a vacuum cleaner If your airplane is equipped with leather seating cleaning of the seats is accomplished using a soft cloth or sponge dipped in mild soap suds The soap suds used spa...

Page 88: ...g The ELT emits an omni direc Iional signal on the international distress frequencies of 121 5 and 243 0 MHz Some ELT units in export aircraft transmit only on 121 5 MHz eneral aviation and commercial...

Page 89: ...n your radio transceiver and listen for an emergency tone transmission If the ELT can be heard trans mitting place the function selector switch in the OFF position and the tone should cease Immediatel...

Page 90: ...be received the uuvig ation receiver does not include the necessary circuits to interpret 1111 signals for localizer indications However the audio portion of the I j alizer is audible so that flight i...

Page 91: ...05 MHz steps between 0 00 and 0 95 MHz 7 NAVIGATIONRECEIVER MEGAHERTZ SELECTOR Selects navigation receiver frequency in 1 MHz steps between 108 and 117 MHz 8 NAVIGATIONRECEIVER VOLUME CONTROL Con trol...

Page 92: ...CD The set iIWlil II channel VHF communication receiver transmitter and a 20 11 1111 I II I navigation receiver both of which may be operated simuH III IIII 1 The communication receiver transmitter r...

Page 93: ...TION RECEIVER OPERATION 1 COM OFF VOL Control TURN ON 2 SPEAKER PHONE or AUTO Switch SET to desired mode 3 NAV Frequency Selector Knobs SELECT desired operating frequency 4 I P f q 1 IU II 11 V I OM I...

Page 94: ...ed in Figure 1 The Cessna 300 ADF can be used for position plotting and homing procedures and for aural reception of amplitude modulated AM signals With the function selector knob at ADF the Cessna 30...

Page 95: ...f stations transmitting keyed CW signals Morse Code to be heard REC Selects operation as standard communication r e ceiver using only sense antenna ADF Set operates as automatic direction finder using...

Page 96: ...n 4 Function Selector Knob ADF posttion and note relative bearing on indicator 5 VOL Control ADJUST to desired listening level TO TEST RELIABILITY OF AUTOMATIC DIRECTION FINDER 1 Function Selector Kno...

Page 97: ...l 11 nals on 1030 MHz and transmits coded pulse train reply signals Oil IO H MHz It is capable of replying to Mode A aircraft identification and ModeC altitude reporting interrogations on a selective...

Page 98: ...trol brilliance of reply lamp 5 SELF TEST TST SWITCH When depressed causes trans ponder to generate a self interrogating signal to provide a check of transponder operation Reply Lamp will glow steadil...

Page 99: ...t of view on encoding altimeter 4 2 Reply Code Selector Knobs SELECT assigned code 3 Function Switch ON 4 DIM Control ADJUST light brillianee of reply lamp NOTE During normal operation with function s...

Page 100: ...e readily The Cessna 300 Transponder system consists of a panel mounted unit lIld an externally mounted antenna The transponder receives interroga 111111 pulse signals on 1030 MHz and transmits pulse...

Page 101: ...4 Display selected Mode A reply code 8 REMOTE MOUNTED DIGITIZER Provides an altitude reporting code range of 1000 feet up to the airplane s maximum service ceiling 1 FUNCTION SWITCH Controls applicati...

Page 102: ...obs SELECT assigned code 4 I II OT S OPERATINC IIANIJI J IIII PLEMENT I SSNA 100 TRANSPONDER M I t 1 1 1 1 111 1 NCOIn n BLIND 2 Function Switch ON 3 DIM Control ADJUST light br ilIi u I ply 1 111 1 N...

Page 103: ...in flight on the control center s radar scope more readily The 400 Transponder consists of a panel mounted unit and an exter nally mounted antenna The transponder receives interrogating pulse xignals...

Page 104: ...s pilot to control brilliance of Reply Lamp 5 SELF TEST TST SWITCH When depressed causes transponder to gen erate a self interrogating signal to provide a check of transponder operation Reply Lamp wil...

Page 105: ...11 1 1 1 MENT CESSNA 400 TRANSPONDER AND ENCODINGALTIMETER en Reply Code Selector Switches SELECT assigned code 1 Function Switch ON 1 DIM Control ADJUST light brilliance of reply lamp NOTE During no...

Page 106: ...readily The Cessna 400 Transponder system consists of a panel mounted unit nd an externally mounted antenna The transponder receives interroga In pulse signals on 1030 MHz and transmits pulse train re...

Page 107: ...NDICATORS 4 Display selected Mode A reply code 8 REMOTE MOUNTED DIGITIZER Provides an altitude reporting code range of 1000 feet up to the airplane s maximum service ceiling 1 FUNCTION SWITCH Controls...

Page 108: ...RANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN IN A CONTROLLED ENVIRONMENT When directed by ground controller to stop altitude squawk turn Function Switch to ON for Mode A operation onl...

Page 109: ...er beacon antenna In u Idttion on 150 182 206 207 210 and 337 series models a HI LO rH 1sitivityselector switch and a press to test button are provided On all 172 177 177RG 180 and 185 series models a...

Page 110: ...DIM coni 1 1 1 I I wise fully on in order to view the mar ke r lights during test 4 LO HISENSSWITCH 150 182 206 207 210 1 I Model Series Only In the LO position Up 1 1 1 tivity is positioned for ILS a...

Page 111: ...v igat ion system when making instrument approaches to an airport The I lldeslope provides vertical path guidance while the localizer pr ovides lnuizontal track guidance The Cessna 400 Glide Slope sys...

Page 112: ...visible glid 111111 III dications are unusable SECTION 5 PERFORMANCE There is no change to the airplane performance wlll lI II r vu in ir equipment is installed 3 4 blank I I 1 GLIDE SLOPE DEVIATION...

Page 113: ...ndently or by a remote NAV set When coupled with a remote NAV set the MHz digits will be covered over by a remote REM flag and the DME will utilize the frequency set by the NAV set s channeling knobs...

Page 114: ...FRACTIONAL MEGAHERTZ SELECTOR KNOB Selects oper ating frequency in tenths of a Megahertz 0 9 8 IDENT KNOB Rotation of this control increases or decreases the volume of the received station s Ident si...

Page 115: ...ntenna or several related external antennas will result in a minor reduction in cruise performance 4 HF TRANSCEIV1 i TYPE PT10 A PILOT S OPERATING HANDBOOK lJPPLEMENT SUPPLEMENT HF TRANSCEIVER Type PT...

Page 116: ...nstalled SECTION 4 NORMAL PROCEDURES MMUNICATIONSTRANSCEIVER OPERATION 1 XMTR SEL Switch SELECT transceiver 2 SPEAKER PHONE or AUTO Switch SELECT desired mode 3 VOLUME Control ON allow equipment to wa...

Page 117: ...lled to provide the desired operating frequencies A mode selector control is provided to supply the type of emission required for the channel either sideband AMor telephone for public correspondence A...

Page 118: ...ing Controls 2 PILOT S OPERATING HANDBOOK SUPPLEMENT SSB Hl THANH I IV 1 1 TV I ASI I I J other countries only the upper sideband may be used Use of lower side band is prohibited 2 Only AM transmissio...

Page 119: ...yaw motions of the airplane are sensed by the turn coordina tor gyro The computer amplifier electronically computes the necessary correction and signals the actuator to move the ailerons to maintain...

Page 120: ...e to NAV signal to provide mor PIT i fJlf l I ill during localizer approach In low sensitivity position pushbuuon Illd iP 11 1l 1 1 NAV signal is dampened for smoother tracking of enroute VOH 11 11 1...

Page 121: ...l I II 5 Aut opr l 1 11 11 1 I I iii 1 111 1 I 11111111111 1 heading drift NAV CAPTlJln V II II 1 PULL TIJII J 1 1 1 11111 r I 1 111 1 2 NAV 1 2 1 1 11 I II I I I 1I d V 111 I IVI l 3 Nav Recctvrr I...

Page 122: ...sensed by the turn coordinator gyro Deviations from the selected heading are sensed by the directional gyro The computer amplifier electronically computes the necessary cor rection and signals the ac...

Page 123: ...w Upl I d IIHI during localizer approach In low sensitivity position pushbutton out J P I NAV signal is dampened for smoother tracking of enroute VOR r adials il al o 111 H 0111 out effect of course...

Page 124: ...ING 1 Airplane Trim ADJUST 4 I I ll I L TURN Knob CENTER PULL out and ROTATE 111 1 1111 SI LECT II Iurectional Gyro SET to airplane magnetic heading lle ading Selector Knob ROTATE bug to desired headi...

Page 125: ...s within 10 of course heading 2 HI SENS Button Disengage for enroute omni tracking leave engaged for localizer NOTE If CDI remains steadily off center readjust autopilot lateral trim control as requir...

Page 126: ...I i i NA IOOA A 11 1 H II IT TY 1 1 A V ID i TURN CO igure 1 6 r l lle II IIY tI A HOME HE SIGN EW I NY I...