Symphony SA-160 Flight Manual Download | Manualshive

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A I R C R A F T

SA 160

A I R C R A F T

A I R C R A F T

Symphony

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Summary of Contents for SA-160

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Page 3: ...sponsibility to maintain the handbook in acurrentstatus The information in this handbook will be kept current by revisions issuedby Revision material will contain information necessary to update the t...

Page 4: ...d deletions will be identified by a vertical black line along the outside of the page opposite only the portion of the printed matterthatwaschanged A line along the outside margin of the page beside t...

Page 5: ...25 2005 vii Feb 25 2005 viii Feb 25 2005 ix Feb 25 2005 x Feb 25 2005 xi Feb 25 2005 1 1 Feb 25 2005 1 2 Feb 25 2005 1 3 Feb 25 2005 1 4 Feb 25 2005 1 5 Feb 25 2005 1 6 Feb 25 2005 v Feb 25 2005 1 7 F...

Page 6: ...eb 25 2005 4 8 Feb 25 2005 4 9 Feb 25 2005 3 19 Feb 25 2005 3 20 Feb 25 2005 3 21 Feb 25 2005 4 10 Feb 25 2005 4 11 Feb 25 2005 4 12 Feb 25 2005 4 13 Feb 25 2005 4 14 Feb 25 2005 4 15 Feb 25 2005 4 16...

Page 7: ...Feb 25 2005 7 2 Feb 25 2005 7 3 Feb 25 2005 5 23 Feb 25 2005 5 24 Feb 25 2005 6 14 Feb 25 2005 7 4 Feb 25 2005 7 5 Feb 25 2005 7 6 Feb 25 2005 7 7 Feb 25 2005 7 8 Feb 25 2005 7 9 Feb 25 2005 7 10 Feb...

Page 8: ...25 2005 7 49 Feb 25 2005 8 1 Feb 25 2005 8 2 Feb 25 2005 8 3 Feb 25 2005 8 4 Feb 25 2005 8 5 Feb 25 2005 8 6 Feb 25 2005 8 7 Feb 25 2005 8 8 Feb 25 2005 8 9 Feb 25 2005 8 10 Feb 25 2005 8 11 Feb 25 2...

Page 9: ...SA 160 A I R C R A F T A I R C R A F T Symphony vii LOG OF EFFECTIVE PAGES INTENTIONALLY LEFT BLANK Feb 25 2005...

Page 10: ...SA 160 A I R C R A F T A I R C R A F T Symphony viii LOG OF EFFECTIVE PAGES INTENTIONALLY LEFT BLANK Feb 25 2005...

Page 11: ...SA 160 A I R C R A F T A I R C R A F T Symphony ix LIST OF REVISIONS LIST OF REVISIONS Description Page No Date Rev No Feb 25 2005 Approval...

Page 12: ...SA 160 A I R C R A F T A I R C R A F T Symphony x LIST OF REVISIONS INTENTIONALLY LEFT BLANK Feb 25 2005...

Page 13: ...S CONTENTS SECTION GENERAL 1 LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT AND BALANCE EQUIPMENT LIST 6 DESCRIPTION AND OPERATION OF THE AIRCRAFT AND ITS SYSTEMS 7 HAND...

Page 14: ...SA 160 A I R C R A F T A I R C R A F T Symphony...

Page 15: ...cated Weights 1 6 Typical Aircraft Weights 1 6 Cabin and Entry Dimensions 1 7 Baggage Space 1 7 Specific Loadings 1 7 Other Data 1 7 1 5 Symbols Abbreviations and Terminology 1 8 a General Airspeed Te...

Page 16: ...SA 160 A I R C R A F T A I R C R A F T Symphony AIRCRAFT VIEWS Abb 1 1 1 Aircraft Views 1 2 10 67 35 2 11 6 92 1 118 3 67 3 27 10 75 0 86 2 82 m ft SECTION 1 GENERAL Feb 25 2005...

Page 17: ...um takeoff weight and in the takeoff attitude is at least 0 180 m 7 in Maximum propeller diameteris1 854m 73in Thewingareais11 93m 128 4sq ft A minimum turning radius of 6 6 m 21 7 ft Pivot point to t...

Page 18: ...ndbook does not serve as a substitute for appropriate flight training and knowledge of valid airworthiness advisories the relevant official aviation rules and the advisory circulars It is not intended...

Page 19: ...arburetor e Rated Power 119 kW 160 BHP f Rated Speed 2700 RPM g Bore 130 175 mm 5 125 in h Stroke 98 425 mm 3 875 in i Displacement 5 24 l 319 8 cu in j Compression Ratio 8 5 1 a Number 1 b Propeller...

Page 20: ...SAE 50 SAE 40 or SAE 50 1 C to 32 C SAE 40 SAE 40 18 C to 21 C SAE 30 SAE 30 or SAE 40 Below 12 C SAE 20 SAE 30 c Max Oil Capacity 7 6 l 8 qt d Recommended Oil Quantity 4 7 6 6 l 5 7 qt a Maximum Ramp...

Page 21: ...1 14 m 44 8 in d Maximum Entry Width 0 805 m 31 7 in e Maximum Entry Height 0 80 m 31 5 in f Maximum Sill Height 0 838 m 33 in a Compartment Width 0 44 m 17 3 in 0 87 m 34 3 in b Compartment Length 1...

Page 22: ...ealevel CalibratedAirspeedexpressedin knots isthespeedrelativetotheground is the speed of an aircraft as shown on the airspeed indicator when corrected for instrument error IAS values published inthis...

Page 23: ...st speed permissible with wingflapsinaprescribedextendedposition or Mach Number is the speed limit that may not beexceededatanytime is the speed that should not be exceededexceptinsmoothairandthenonly...

Page 24: ...F is 0 00198 C 0 003564 F perfootandzeroabovethataltitude is the free air static temperature obtained either from inflight temperature indications or ground meteorological sources adjusted for instru...

Page 25: ...HT Indicator ClimbGradient Themaximumpowerpermissiblefortakeoff maybetimelimited Highestpowersetting notlimitedbytime Powerrecommendedforcruiseclimb The maximum power setting for which specific values...

Page 26: ...craft to a specified speed and assuming failure of an engine at the instant that speed is attained tobringtheAircrafttoastop A part of a route Each end of that part is identified by 1 a geographical l...

Page 27: ...ference datum is found by dividing the total momentbythetotalweightoftheAircraft The arm obtained by adding the Aircraft s individual moments and dividingthesumbythetotalweight The extreme center of g...

Page 28: ...art taxiandrunupfuel Maximumweightapprovedforthestartofthetakeoffrun Maximumweightapprovedforthelandingtouchdown Maximumweightexclusiveofusablefuel Methods procedures or limits which must be followed...

Page 29: ...tor Markings 2 3 2 7 Power Plant Limitations 2 4 2 9 Engine Parameter Color Markings 2 5 2 11 Weight Limits 2 6 2 13 Center of Gravity Limits 2 6 2 15 Maneuver Limits 2 6 2 17 Flight Load Factor Limit...

Page 30: ...ationsconcerningthemaintenance The aircraft must be operated in compliance with these operating limits which are provided in the form of markings and placards as well as in this manual Operating limit...

Page 31: ...is controllable in the landing configuration V V V FE S SO 2 5 AIRSPEED INDICATOR MARKINGS SECTION 2 LIMITATIONS Feb 25 2005 Markings KIAS Remarks Red Line 162 Never exceed speed Maximum speed for al...

Page 32: ...um Oil Pressure Red Line 97 psi f Fuel Pressure Minimum Pressure Red Line 0 5 psi Maximum Pressure Red Line 8 psi g Fuel grade minimum requirement only aviation fuel AVGAS 100LL h Oil grades minimum r...

Page 33: ...M U MIN 0600 2700 75 245 150 435 1300 1550 24 0 28 7 1 50 28 8 31 9 32 0 436 500 501 0 5 8 0 2 16 17 18 19 13 0 29 0 0 24 25 54 55 95 96 97 8 1 98 246 29 1 31 0 31 1 2701 MAN PRES HG OIL PRES PSI AMPS...

Page 34: ...maximum 45 kg 99 lbs NOTE 2 13 CENTER OF GRAVITY LIMITS Weight Forward Aft kg lbs m in aft of m in aft of Datum Datum 648 1428 2 45 96 46 975 2150 2 60 102 36 hanges between the specified points are l...

Page 35: ...FR c Max Persons on Board 2 1 Pilot FAA registered Aircraft Pilots operating aircraft of other than U S registry should refer to the appropriate regulations of the country of certification The aircraf...

Page 36: ...wer on descents with flaps fully extended must be limitedtomaximum10minutesduration b UsableFuel 110 l 29 1U S Gallons SECTION 2 LIMITATIONS a Airframe For safe aircraft operation all four Vortex Gene...

Page 37: ...ROHIBITED FLIGHTS IN HEAVY TURBULENT AIR AND CLOSE TO THUNDERSTORMS ARE PROHIBITED SEE THE LIMITATION SECTION IN THE POH MAXIMUM GROSS WEIGHT MANEUVERING SPEED MAX FLAP EXTENDED SPEED MAX DEMONSTRATED...

Page 38: ...ar oil access door 3 Left fuselage near the engine cowling USE ONLY OIL THAT COMPLIES WITH APPLICABLE PILOT S OPERATING HANDBOOK ENGINE OIL ABOVE 16 C 60 F SAE 40 OR SAE 50 1 C TO 32 C SAE 40 18 C TO...

Page 39: ...USH 5 On the doors below the door handle 99 LBS MAXIMUM MAXIMUM MAXIMUM 165 COMBINED BAGGAGE FORWARD OF RED MARKING BAGGAGE AFT OF RED MARKING 99 LBS LBS SEE WEIGHT AND BALANCE DATA 6 On the baggage d...

Page 40: ...C OBSERVE PROPER POLARITY THIS AIRCRAFT IS EQUIPPED WITH ALTERNATOR AND A NEGATIVE GROUND SYSTEM REVERSE POLARITY WILL DAMAGE ELECTRICAL COMPONENTS 7 Near external power receptacle Feb 25 2005 For ai...

Page 41: ...tion 3 5 f Precautionary Landing With Engine Power 3 6 g Ditching 3 6 h Engine Fire During Start 3 7 i Engine Fire In Flight 3 7 j Electrical Fire In Flight 3 8 k Loss Of Oil Pressure 3 8 l Power Supp...

Page 42: ...with various emergencies or critical situations as required by the Aviation Authorities as well as those necessary for operation of the aircraft as determinedbytheoperatinganddesignfeaturesoftheaircra...

Page 43: ...tter understanding of the reasons for the actionslisted The numbers located in parentheses after each paragraph headingindicatethecorrespondingchecklistparagraph It is recommended that pilots familiar...

Page 44: ...1 Establish glide Airspeed with Flaps down 65 KIAS Airspeed with Flaps up 74 KIAS 2 Land straight ahead make only shallow turn to avoid obstructions if possible 3 Mixture IDLE CUT OFF 4 Fuel Valve OF...

Page 45: ...Before landing 4 Mixture IDLE CUT OFF 5 Fuel Valve OFF 6 Ignition Switch OFF 7 Switch ALT BAT OFF Touchdown with lowest possible airspeed 8 Doors UNLATCH PRIOR TO TOUCHDOWN 9 Brakes as required APPLY...

Page 46: ...tructions if possible 10 Mixture IDLE CUT OFF 11 Ignition Switch OFF 12 Fuel Valve OFF 8 Cabin Doors UNLATCH PRIOR TO TOUCHDOWN g Ditching After an engine failure immediately secure glide speed 74 KIA...

Page 47: ...witch CONTINUE CRANKING ENGINE 5 Throttle FULL OPEN 6 Mixture IDLE CUT OFF 7 Fuel Valve OFF If fire continues 8 ALT BAT OFF 9 Fire Extinguisher USE 10 Aircraft EVACUATE i Engine Fire In Flight 1 Fuel...

Page 48: ...nguished ventilatecabin If it cannot be visually determined that the fire is completely extinguished landassoonaspossible Afterascertainingthatfirehasbeenextinguishedcompletely 6 Cabin ventilation FUL...

Page 49: ...ntial electrical equipment OFF 6 Land as soon as practical m Excessive Rate Of Charge Ammeter and voltmeter shows a excessive rate of charge 1 ALT Switch OFF 2 Non essential electrical equipment OFF 3...

Page 50: ...SA 160 A I R C R A F T A I R C R A F T Symphony...

Page 51: ...fect on the aerodynamic characteristicsoftheaircraft Stallingspeedincreases Continuedflightinicingconditionsisprohibited 1 Pitot Heat Switch ON 2 Carburetor Heat ON 3 4 Wind shield Heat With an ice ac...

Page 52: ...stbetighttoreducethepossibilityofinjury In order to reduce the danger of a short circuit and or fire the fuel supply to the engine should be cut off and the electrical system turned off Cut off the fu...

Page 53: ...gine if the engine driven fuel pump has failed Switch the carburetor heat to ON Check to ensure the ignition switchisin BOTH position At airspeeds below 75 KIAS the propeller can stop no autorotation...

Page 54: ...SA 160 A I R C R A F T A I R C R A F T Symphony...

Page 55: ...ltitude may be lost by widening the pattern using flaps side slipping oracombinationofthese At no time should the airspeed reduce below the stalling speed for the configuration setting Note This speed...

Page 56: ...efuelvalveisinONposition The auxiliary fuel pump supports the fuel supply to engine if the enginedrivenfuelpumpdoesnotworkcorrectly Check the mixture control lever position adjust for maximum smoothne...

Page 57: ...htlyreducetheinjuryhazard When committed to a landing turn OFF the ALT BAT switch before touchdown and unlatch both doors before touch down After touchdown at the lowest possible airspeed attempt to b...

Page 58: ...her RPM there is a good chance to blow out a possible external fire If the engine fails to start try to draw the fire back into the engine by moving the mixture control to IDLE CUT OFF opening the thr...

Page 59: ...e to stop suddenly Avoid unnecessary loads on the engine Flight altitude should be maintained Pay particular attention to the oiltemperature Depending on the circumstances it may be advisable to make...

Page 60: ...rical load to a minimum All electrical load is now being supplied by the battery Turn off all non essential electrical equipment Proceedtowardnearestairfield A power supply malfunction has no effect o...

Page 61: ...lingspeedincreases Continuedflightinicingconditionsisprohibited Achangeoftemperaturewilloccurwithachangeofaltitude The pitot heat reduces the chance of ice accumulation on the pitot tube which could c...

Page 62: ...thinthenormaloperatingspeedlimits Spin Recovery Procedure Checklist 3 5 p Cause of inadvertent spins is usually the result of heavy or insensitive controlinputs ThespinrecoveryisunproblematicwiththeSA...

Page 63: ...position to the panel Different aileron forces cause an incorrect neutral position andmaydelaythespinrecovery The maximum altitude loss for a 1 turn spin is 300 ft 1000 ft may required to accomplishin...

Page 64: ...SA 160 A I R C R A F T A I R C R A F T Symphony...

Page 65: ...rting Engine 4 9 d Starting Hot Engine 4 10 e Engine Start With External Power Source 4 10 f Warm Up 4 10 g Taxiing 4 11 h Ground Check 4 11 i Before Takeoff 4 12 j Takeoff 4 12 Normal Conditions 4 12...

Page 66: ...rting Hot Engine 4 5d 4 23 e Engine Start with External Power Source 4 23 f Warm Up 4 5f 4 24 g Taxiing 4 5 g 4 24 h Ground Check 4 5h 4 25 i Before Takeoff 4 5i 4 26 j Takeoff 4 5j 4 26 Normal Condit...

Page 67: ...quipment optimally and safely Therefore it is recommended to make yourself familiar with the procedures and be able tomasterthem Thissectionisdividedintotwomainparts 1 The first part contains the norm...

Page 68: ...ndotheratmosphericfactorsetc a BestRateofClimbSpeed 80 KIAS decreaseofoneknotper1000fttomin 73KIAS b BestAngleofClimbSpeed 70 KIAS c FinalApproachSpeed Flaps40 65 KIAS d BalkedLanding 65 KIAS e Maximu...

Page 69: ...SA 160 A I R C R A F T A I R C R A F T Symphony 4 5 1 2 3 4 5 Figure 4 1 PREFLIGHT INSPECTION SECTION 4 NORMAL PROCEDURES Feb 25 2005...

Page 70: ...CHECK Main Wheel Tire CHECK for proper inflation and general condition Wing Surface FREE of ICE FROST SNOW Left Side Top Deck Hatch CHECK for security Flap and Aileron CHECK for freedom of movement an...

Page 71: ...Propeller and Spinner CHECK for nicks and cracks Generator Drive Belt CHECK tension Oil CHECK level Oil Filler Cup CLOSE Oil Access Door CLOSE Nose Gear Strut and Wheel Fairing CHECK Nose Wheel Tire C...

Page 72: ...inflation and general condition Fuselage Skins CHECK Antennas CHECK Empennage CLEAR of ICE FROST SNOW Elevator CHECK for freedom of movement and security Trim Tab CHECK for integrity Rudder CHECK for...

Page 73: ...Navigation Equipment and Flashlight at Night ON BOARD AVIONIC 1 AVIONIC 2 IFR Switches OFF Fuel Valve CHECK ON c Starting Cold Engine Brakes SET ALT Switch ON INST LT MAP LT Dimmer Switches at Night O...

Page 74: ...le ADJUST to 1000 1200 RPM Oil pressure CHECK NAV LT Switch at Night ON e Engine Start With External Power Source External Power Source CONNECT Start engine according b and c or b and d then Throttle...

Page 75: ...ottle 1800 RPM Magnetos CHECK L then R Maximum Drop 175 RPM Maximum Difference 50 RPM between magneto Ignition Switch BOTH Throttle IDLE Engine runs smooth with 500 700 RPM Throttle 1000 1200 RPM Volt...

Page 76: ...Before Takeoff Brakes APPLY Throttle 1000 1200 RPM Seats ENGAGED Seat Belts and Harnesses FASTENED CHECK Empty Seat Seat Belts SNUGLY FASTENED Cabin Doors CLOSED AND LATCHED Instrument Map Light at N...

Page 77: ...laps 20 Brakes APPLY Throttle FULL OPEN When full engine power is available Brakes RELEASE At a speed of 53 KIAS ROTATE to lift off After lift off accelerate to Airspeed 62 KIAS After an altitude of 5...

Page 78: ...ob optional CHECK PUSHED IN Final Approach Speed Flaps 40 65 KIAS It is recommended that all necessary landing checks and actions in the cabin are completed before turning NOTE Mixture ADJUST Engine P...

Page 79: ...hat the aircraft slowly approaches the ground and make contact with the lowest possible speed mainwheelsfirst Aftertouchdown NoseWheel LOWER GENTLY Braking AS REQUIRED Throttle FULL OPEN CarburetorHea...

Page 80: ...at Night OFF DOME LT Switch at Night ON INST LT MAP LT Dimmer Switch at Night OFF ALT BAT Switch on Day OFF ALT Switch at Night OFF r After Engine Shut Down AllElectricalEquipment OFF IgnitionSwitch...

Page 81: ...rcraft visual check inaccordancewiththecheck list Fig 4 1 SECTION 4 NORMAL PROCEDURES 1 Cabin Inthecabin first unlockthecontrolstick You should ascertain that a current SA 160 flight manual as well th...

Page 82: ...ge The tire should be checked for proper inflation and condition Next check the wing surface is clear of ice frost snow or other extraneoussubstances The quick release locks of the top deck hatches fo...

Page 83: ...are to be checked for nicks cracks or otherdefects Through the right air inlet check the proper tension of the alternator belt Open the oil access door on the right side of the upper cowling and check...

Page 84: ...ntandingoodcondition The quick release locks of the top deck hatches for the right wing are tobecheckedforproperlock 5 Fuselage The fuselage skins are to be checked for damage such as delaminations or...

Page 85: ...rial necessary for the flight is on board at nightadditionallyaflashlightforemergencypurposes The AVIONICS switch should be in OFF position Any Avionics in the ON position could be damaged during engi...

Page 86: ...Hposition For aircraft equipped with a primer system it is recommended that when starting a cold engine prime it max 3 strokes and secure the primerbutton Overpriming complicates the engine starting p...

Page 87: ...ve the throttle to attain 1000 1200 RPM If the engine does not fire within 5 10 seconds disengage the starter and repeat starting procedure after approx 2minutes The oil pressure immediately after sta...

Page 88: ...the engine at 1000 1200 RPM Engine is warm for takeoff whenthrottlecanbeopenedwithoutenginefaltering In the meantime turn on required electrical equipment such as the navigation equipment setup if nec...

Page 89: ...ld not exceed 175 RPM on either magneto and the difference between the magnetos should not exceed 50 RPM Move the throttle control to the most rear position Engine mustberunat500 700RPMwithoutextremev...

Page 90: ...iven fuel pump fail during takeoff Ensurethefuelquantityissufficientfortheplannedflight Check the mixture is in the FULL RICH position the carburetor heat is OFFandtheIgnitionswitchisinBOTHposition Ch...

Page 91: ...t in a shallow climb to 65 KIAS and then transfer to climbflightwiththisspeed Once clear of any obstacles slowly retract the flaps at an altitude of at least50ftandclimbat80KIASairspeed ShortRunway k...

Page 92: ...power and allow engine parameters to stabilize b Press BUTTON 1 at VM 1000 display see Section 7 to activate the LeanEGTMode c Smoothly lean engine mixture by rotating the knob counter clockwise to s...

Page 93: ...highspeedandlowpower With less than 12 liters 3 U S Gal per each wing tank Lo at indicator power on descents 50 75 with flaps fully extended and more as 70 KIAS airspeed must be limited to maximum 10...

Page 94: ...way surface wind conditions and aircraftloading Adjusttrim Verifytheparkingbrakecontrolknobispushedin If landing is made with the parking brake set the brakes will maintainanypressureappliedaftertouch...

Page 95: ...yornotatall When landing flare the aircraft so that it flares out at approx 0 5 m overandparalleltotherunwaysurface While decreasing speed increase angle of attack by easing the stick back so that the...

Page 96: ...DLECUT OFF TurnOFFtheignitionswitch Turnoffthestrobelightandatnightthenavigationlights Turn off the instrument and map lights cabin lighting turn on the dome light If the dome light is needed leave th...

Page 97: ...8 a Approximation Method 5 9 b Interpolation Method 5 9 5 9 Performance Charts 5 10 Fig 5 1 Air Speed Calibration 5 10 5 2 Altimeter Correction 5 12 5 3 Temperature Conversion 5 14 5 4 Liters Gallons...

Page 98: ...d landing or winds aloft on cruise and range performance are not considered on the charts and tables must be interpolated by the pilot Performance information presented in the range and endurance prof...

Page 99: ...used TakeoffWeight 975 kg 2150lbs UsableFuel 110 l 29 1U S Gal AirfieldPressureAltitude 930 ft AirTemperature 13 C WindComponent 14 ktsHeadwind RunwayLength 800 m 2625ft TotalDistance 280 NM CruisePre...

Page 100: ...lowing GroundRoll 370 m 1214ft Totaldistancetoclear a50 ftobstacle 475 m 1558ft Therunwaylengthof2000ft isthereforesufficient The Chart figure then shows the existing wind conditions The correction fo...

Page 101: ...nvaluesthefollowing resultisobtained TrueAirspeed 117 kts FuelConsumption 28 l h The fuel required for this flight may be estimated by use of the chart Time Fuel and Distance to climb Fig 5 8 and the...

Page 102: ...minutereserve 45 60 x 28 l h 21 l Nextthetotalfuelrequiredcanbecalculatedasfollows Enginestart taxi andtakeoff 4 0 l Climb 6 4 l Cruise 78 4 l Reserve 21 0 l For estimating the landing distance at the...

Page 103: ...means of the corresponding column with the air temperature and the linewithcorrespondingaltitude thelandingdistancesaredetermined Conservative values can be safely determined by reading the chart at t...

Page 104: ...dthenexthigherincrementofweightifapplicable To obtain exact performance values from tables it is necessary to interpolatebetweentheincrementalvalues Example Given TakeoffWeight 2150 lbs AirTemperature...

Page 105: ...f the difference between 2000 ft and 3000 ft The temperature is 50 of the difference between 35 C and 45 C Between the read values the corresponding percentages are to be considered Lift OffSpeed 58 K...

Page 106: ...S 5 10 FLAPS 00 FLAPS 20 FLAPS 40 KIAS KIAS KIAS KCAS KCAS KCAS 65 64 55 55 54 54 75 74 60 60 59 59 85 84 65 65 64 64 95 94 70 70 70 70 105 107 80 80 80 80 115 115 90 90 90 90 125 126 135 135 AIRSPEED...

Page 107: ...NS COCKPITVENTILATIONOFF SECTION 5 PERFORMANCE 50 51 60 61 70 73 80 85 90 96 100 107 110 119 120 129 130 140 140 151 150 161 160 172 Normal KIAS Alternate KIAS NOTES 1 INFLUENCE OF VENTILATION WITH TH...

Page 108: ...20 FLAPS 40 CONDITION CORRECTION TO BE ADDED FEET KIAS 55 10 10 10 65 10 5 5 60 10 10 10 70 10 5 5 80 10 5 5 90 10 0 0 105 15 115 0 125 10 CONDITIONS MSL KIASANDINDICATEDALTITUDEASSUMEZEROINSTRUMENTE...

Page 109: ...KIAS ALTIMETERCORRECTION 50 ft SECTION 5 PERFORMANCE Feb 25 2005 CORRECTION TO BE ADDED FEET KIAS 60 10 80 40 70 25 90 50 100 70 70 110 90 110 130 145 165 120 130 140 150 160 NOTES 1 INFLUENCE OF VEN...

Page 110: ...A I R C R A F T Symphony 5 14 SECTION 5 PERFORMANCE Figure 5 3 TEMPERATURE CONVERSION DEGREES FAHRENHEIT DEGREES CELSIUS 0 0 20 20 40 40 20 40 60 20 40 60 80 100 120 0 0 20 20 40 40 20 40 60 20 40 60...

Page 111: ...phony 5 15 SECTION 5 PERFORMANCE Feb 25 2005 LITERS GALLONS CONVERSION 10 20 30 40 50 60 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 0 0 70 80 90 100 110 120 18 19 20 21 22 23 24 25 26 27 28 29 30 31 60 16 17...

Page 112: ...RYCANBEUPTO250FT 2 ATMIDDLEANDAFTC G POSITIONSLOWERABOVESHOWNVALUESBY1KT EXAMPLE WEIGHT 975kg 2150 lbs FLAPS 40 ANGLEOFBANK 30 STALLSPEED 55 KIAS 54 KCAS FLAPS 00 FLAPS 20 FLAPS 40 CONDITIONS STALL SP...

Page 113: ...ft 62KIAS WEIGHT975 kg 2150lbs GROUNDROLL 1394 ft OVERA50FTOBSTACLE 1755 ft THE CORRECTION FOR HEADWIND 13 5 kts 9 kts X 10 15 DECREASE GROUNDROLL 1185 ft OVERA50FTOBSTACLE 1492 ft TOTAL TO CLEAR 50 F...

Page 114: ...CENTAGE IS TOBECONSIDERED CLIMBSPEED 80 KIAS RATEOFCLIMB 838 ft min PRESS ALT ft WEIGHT lbs CLIMB SPEED KIAS RATE OF CLIMB FT MIN ISA 10 C ISA ISA 20 C ISA 10 C ISA 30 C MSL 2000 4000 6000 8000 10000...

Page 115: ...E DEP AIRFIELD PRESSURE ALTITUDE 2000 ft DEP AIRFIELD TEMPERATURE 11 C CRUISE PRESSURE ALTITUDE 6000 ft TIME 10 9 min 3 min 7 9 min FUEL 1 95 0 58 1 37 U S Gal DIST 14 5 NM 4 NM 10 5 NM PRESSURE ALTIT...

Page 116: ...3 8 7 2400 70 0 114 31 8 2 2300 60 0 107 26 6 9 2100 53 8 101 24 6 3 2000 41 3 88 18 4 8 4000 2700 84 4 128 43 11 4 2600 78 1 123 40 10 6 2500 70 0 118 31 8 2 2400 65 6 114 29 7 7 2300 56 9 107 25 6 6...

Page 117: ...SPEED 114 KTAS MIN FUEL CONSUMPTION 29 l h 7 7 U S Gal h U S GAL h Pressure Altitude ft RPM Standard Temperature BHP KTAS A l h 10000 2700 2600 63 1 123 28 7 4 2500 56 9 118 25 6 6 2400 53 8 114 24 6...

Page 118: ...NS WEIGHT 975 kg 2150 lbs INITIAL FUEL LOADING110LITERS 29 1U S GAL USABLE ZEROWIND ISA LEAN MIXTURE UP TO 75 POWER FOR BEST ECONOMYANDADJUSTRICHABOVE75 NOTE RANGE INCLUDES START TAXI CLIMB AND DESCEN...

Page 119: ...U S GAL USABLE ZEROWIND ISA LEAN MIXTURE UP TO 75 POWER FOR BEST ECONOMYANDADJUSTFULLRICHABOVE75 ENDURANCE PROFILE NOTE ENDURANCE INCLUDES FUEL FOR START TAXI CLIMB AND DESCENT WITH 45 MINUTES RESERVE...

Page 120: ...20 33 C TOTALOVER50FTOBSTACLE 2461 ft THECORRECTIONFORHEADWIND 10kts 10kts x 10 10 DECREASE GROUNDROLL 901 ft GROUNDROLL 1001 ft TOTALOVER50FTOBSTACLE 2215 ft Total to Clear 50 ft OBS ft Total to Clea...

Page 121: ...and Balance Determination Weight and Balance Record 6 9 6 7 Weight and Balance Determination for Flight 6 9 6 9 Equipment List 6 15 6 8 Weight and Balance Example 6 14 Fig 6 1 Weight and Balance Data...

Page 122: ...horizedweight and balance limitations could cause an accident to occur The following sections provide information on how to determine the aircraftweightandcenterofgravityforsafeaircraftoperation Speci...

Page 123: ...12 SERVICING 4 Removeexcessivedirtormoisture 5 Topupengineoilasrequiredtothemax oillevel 7 6liter 8qt 6 Adjust the seats to the maximum forward position 7 Retracttheflapscompletely Putallcontrolsurfac...

Page 124: ...1 With the airplane level and brakes released record the weight shown on each scale From the scale calibration data deduct the tare weight if any from each reading Enter values into the weight data f...

Page 125: ...T MAIN WHEEL L BASIC EMPTY WEIGHT ITEM WEIGHT lbs C G ARM in MOMENT in lbs AIRCRAFT AS WEIGHED BASIC EMPTY WEIGHT AND C G Figure 6 1 AIRCRAFT WEIGHING FORM SERIAL NUMBER REGISTRATION NUMBER DATE MODEL...

Page 126: ...SA 160 A I R C R A F T A I R C R A F T Symphony 6 6 SECTION 6 WEIGHT AND BALANCE Feb 25 2005 Static Port Hole Marked Hole Figure 6 2 Markings for Aircraft Longitudinal Leveling...

Page 127: ...t weight lbs R Right main wheel net weight lbs L Left main wheel et weight lbs 2 The center of gravity C of G corresponding to the basic aircraft empty weight is given by C of G We where A Distance fr...

Page 128: ...DATA EMPTY WEIGHT BASIC MOMENT MOMENT C of G We C of G SERIAL NUMBER REGISTRATION NUMBER DATE ITEM DESCRIPTION OF ARTICLE OR MODIFICATION WEIGHT CHANGE WEIGHT lbs WEIGHT lbs WEIGHT lbs ARM in ARM in M...

Page 129: ...odifications Once completed this form provides the new basic weight information required for any in flight loading calculation The form also provides a complete history of all modifications which affe...

Page 130: ...ment Write the aircraft total moment at thebottomofthetable c Divide the total moment by the total weight to determine the aircraft newCofGlocation d In a and c plot the weight and C of G values on th...

Page 131: ...HT AND BALANCE Feb 25 2005 LOADING GRAPH LOADING WEIGHT lbs MOMENT 100 in lbs 500 525 300 400 100 200 0 PILOT AND PASSENGER BAGGAGE AREA 2 BAGGAGE AREA 1 FUEL 200 250 25 125 225 325 425 50 150 250 350...

Page 132: ...160 A I R C R A F T A I R C R A F T Symphony 6 12 SECTION 6 WEIGHT AND BALANCE Feb 25 2005 Figure 6 6 MOMENT ARM 159 1 122 8 101 2 107 4 MOMENT ARM in ITEM Pilot Passenger Baggage 1 Fuel Usable Baggag...

Page 133: ...6 7 WEIGHT AND MOMENT LIMITS C G LOCATION METERS AFT OF REFERENCE DATUM C G LOCATION INCHES AFT OF REFERENCE DATUM 2 45 2 50 2 55 2 60 WEIGHT kg WEIGHT lbs 640 660 680 700 720 740 760 780 800 820 840...

Page 134: ...s 100 C of G Empty 98 6Iinches From the following aircraft loading information we have Pilot 200 lbs Passenger 185 lbs Baggage area 1 60lbs t HE Baggage area 2 40lbs Fuel 20 USG Using the Weight and B...

Page 135: ...8 08 60 122 8 73 68 40 159 1 63 64 2075 101 45 2105 14 8 8 107 4 9 45 2066 2 101 42 2095 65 Basic Empty Weight Pilot and Passenger Fuel 30 1 Gallons Usable Baggage 1 Baggage 2 Ramp Weight Fuel for Eng...

Page 136: ...SA 160 A I R C R A F T A I R C R A F T Symphony...

Page 137: ...11 Flight Instruments 7 11 7 13 Ground Control 7 14 7 15 Wing Flap System 7 14 7 17 Landing Gear 7 15 7 19 Baggage Compartment 7 16 7 21 Seats and Seat Belts 7 16 7 23 Doors and Windows 7 17 7 25 Engi...

Page 138: ...ices 7 40 7 35 Lights 7 45 a Interior Lighting 7 45 b Exterior Lighting 7 46 7 37 Ventilating and Heating 7 47 7 39 Static and Pitot Pressure System 7 48 7 41 Vacuum System 7 60 7 43 Stall Warning Sys...

Page 139: ...n Valves on base wing fuel thanks 7 37 7 14 1 Electrical Power Distribution 7 41 7 14 2 Electrical Power Distribution 7 42 7 15 Circuit Breaker Panel 7 44 7 16 Static and Pitot Pressure System Schemat...

Page 140: ...SA 160 A I R C R A F T A I R C R A F T Symphony 7 4 Feb 25 2005 SECTION 7 DESCR OPERATION INTENTIONALLY LEFT BLANK...

Page 141: ...ol A spacious baggage compartment is located behind the seats with access through the baggage door A wide windshield large convex door windows as well as windows in the top of the cabin ensure very go...

Page 142: ...roven aerospace design concepts as well as high quality fabrication techniques with distinct advantages for servicing procedures strength durability and safety The primary structure of the fuselage is...

Page 143: ...n hinges and the bearings for pulleys and bell cranks The wing strut ties into a reinforced ribbeam whichspansbetweenforeandaftspars Welded aluminum fuel tanks are fitted into the first main bay at th...

Page 144: ...SA 160 A I R C R A F T A I R C R A F T Symphony 7 8 Figure 7 1 Aileron Control System AILERON CONTROL SYSTEM SECTION 7 DESCR OPERATION Feb 25 2005...

Page 145: ...SA 160 A I R C R A F T A I R C R A F T Symphony 7 9 ELEVATOR CONTROL SYSTEM Figure 7 2 Elevator Control System Feb 25 2005 SECTION 7 DESCR OPERATION...

Page 146: ...SA 160 A I R C R A F T A I R C R A F T Symphony 7 10 RUDDER CONTROL SYSTEM Figure 7 3 Rudder Control System SECTION 7 DESCR OPERATION Feb 25 2005...

Page 147: ...Below the flight instrumentisarowofswitchesforsystemcommand The middle section of the panel contains the avionics equipment The avionics equipment type is depended upon the configuration of the aircra...

Page 148: ...itch optional 24 25 ALT BAT Ext P Schalter 26 27 Avionik 1 Switch 28 Avionik 2 Switch IFR 29 30 Strobe Light 31 32 33 34 Flap Position Indicator 35 36 37 38 39 40 41 Flap Switch 42 43 44 45 46 Fuel Pu...

Page 149: ...SA 160 A I R C R A F T A I R C R A F T Symphony 7 13 SECTION 7 DESCR OPERATION Feb 25 2005 INTENTIONALLY LEFT BLANK...

Page 150: ...essure appliedtothebrakepedals Because the nose wheel fork can rotate the front wheel will pivot and turn in the direction of the directional control applied through the brakes and rudder To decelerat...

Page 151: ...ion the flaps are extended by pressing and holding the flaps switch until the desire flap deflection is achieved A limit switch on the actuator will stop the flaps movement when the flaps reachthe40 p...

Page 152: ...reedom of movement of the upper torso area In the event of a sudden deceleration thereelslockuptoprovidepositiverestraintfortheuser Feb 25 2005 7 19 BAGGAGE COMPARTMENT The baggage compartment in the...

Page 153: ...elockedwithakeyfromtheoutside The windshield door and cabin roof windows are produced of polyacryl and bonded to the door and fuselage shell structure They cannot be opened For cleaning and care of th...

Page 154: ...sedinthefullyaft position Thethrottlehas a friction lock Rotating the round knurled knob at the base of the throttle clockwise increases the friction and counterclockwise decreases the friction The fu...

Page 155: ...The VM 1000 engine management system and its operation is described subsequently with sufficient information for safe operation of the aircraft For a more complete description and operation of the VM...

Page 156: ...EC 100 RPM XDUCER FUEL PROBE LEFT DATA PROCESSING UNIT FUEL PROBE RIGHT TO AUDIO PANEL INPUT MAN PRES XDUCER Oil PRES XDUCER FUEL PRES XDUCER OIL TEMP XDUCER AMP XDUCER CHT PROBE 2 CHT PROBE 3 CHT PR...

Page 157: ...ngine parameters the units the full sweep graphic display resolution and the incremental steps of thedigitalreadout Color markings of operating ranges caution ranges and prohibited ranges are describe...

Page 158: ...5 Button 1 Select EGT Graphic Modes Button 2 Select EGT CHT Digital Modes Button 3 Select Autotrack ON OFF Button 4 Select Fuel Computer Modes Button 5 Select Flight Data Recorder Info Figure 7 6 VM 1...

Page 159: ...of this handbook TheEC100displayisincorporatedintheupperleftinstrumentpanel The system provides four several categories of easily accessed information Engineinformation suchaspower numberofcylinders...

Page 160: ...The checklist actions and or checks will appear in the EC 100 display shortened When an alert warning condition occurs the EC 100 will automatically begin to flash the condition and a pulsing audio si...

Page 161: ...odes The diamond graph system displays CHT between the green yellow and red range marks left to right one through four EGT graphics are displayed above the CHT redline marks where they can be easily o...

Page 162: ...tandagaintoseefurtherinformation In the event of an alert or warning pressing any button will cause LeaningMode Leaning mode is selected by pressing BUTTON 1 while in normal mode The entire diamond gr...

Page 163: ...rleftandupperrightsparkplugs Both magnetos work simultaneously and in such a way guarantee a morecompletecombustionofthefuel airmixture Ignitionandstarteroperationiscontrolledbyacombined rotarytype sw...

Page 164: ...position This will activate the starter when ALT BAT switch in the ON position When released the starterengageswitchwillreturnautomaticallytotheBOTHposition To provide an easier starting in cold weat...

Page 165: ...theenginesumpis7 6Liters 8U S quarts The oil passes through an oil suction strainer screen into the engine drivenoilpump andthentotheenginepartstobelubricated A bypass valve on the oil pump allows col...

Page 166: ...omposite two blade MT Propeller The propeller composite construction consists of multiples laminated and plastic covered ash wood strips with bonded stainless steelmetaltips The Propeller has a diamet...

Page 167: ...S Gallons a Fuel Distribution In the SA 160 fuel flows from the tank to the engine by gravity However an electrically operated auxiliary fuel pump is provided to supportfuelsupplyincaseofthefailureof...

Page 168: ...Tanks Drain Valves Check Valves Air Bleeder Aux Fuel Pump Fuel Venting Fuel Vent Line Fuel Shut Off Valve Gascolator Fuel Pump Carburetor Drain Valve Fuel Pump Fuel Pump VM 1000 INTERFACE 1 1 1 2 3 2...

Page 169: ...inutes of descend in this regime a three minute level flight attitude with flaps retracted is to be accomplished From the feeder tank the fuel flows to the fuel shut off valve to the auxiliary fuel pu...

Page 170: ...unlocked by pulling the round knob on the center of the valve while initiatingtherotation b Fuel Quantity Indication Fuel quantity is measured by two capacitive type fuel level probes one in each tank...

Page 171: ...pped water and for the examination of fuel contamination SeeFig 7 12 Each wing fuel tank has a drain valve at its base The wing tank drain valves are located on the underside of wing in the wing root...

Page 172: ...rom the bottom of the cowling section The fuel should be checked daily before the first flight while performing the preflight checks and after each refueling to check for water or sediment contaminati...

Page 173: ...SA 160 A I R C R A F T A I R C R A F T Symphony Figure 7 13 Drain Valves on the base of the wing fuel tanks Cabin Right Wing SECTION 7 DESCR OPERATION 7 37 Feb 25 2005...

Page 174: ...the respective hydraulic brake assemblyviahydrauliclines ParkingBrake The SA 160 is equipped with a parking brake system The parking brake system consists of a parking brake valve the parking brake c...

Page 175: ...us are interconnected by a 50 amp circuit breaker The avionic bus 1 is powered through the battery bus and theavionicbus2throughthemainbus a ALT BAT Switch The switch ALT BAT also named master switch...

Page 176: ...power switches should be placed in the OFF position prior to turning the ALT BAT switch ON or OFF starting the engine or applying an external power source b AVIONIC Switches current CAUTION CAUTION c...

Page 177: ...Distribution Simplified L R Alternator Regulator ELT Ignition Switch Master Relay Ext Power Relay Ammeter Sensor VM 1000 Alternator External Power Socket Starter Relay Starter Magneto Battery ALT BAT...

Page 178: ...t GPS 2 NAV 1 DME Blower Ignition Switch VM 1000 Flap Control System Electrical Fuel Pump Strobe Lights NAV Lights Landing Light Dome Lights Stall Warning System Instrument Lights Pitot Heat DC Conven...

Page 179: ...pproximately26 28Vshouldbeindicated Additionally the system has a built in warning that is coupled with the EC 100 When the system voltage is out of nominal range 26 28 V eithertolowortohigh theEC100w...

Page 180: ...A F T A I R C R A F T Symphony Figure 7 15 Circuit Breaker Panel 2 1 3 1 3 10 10 15 2 5 2 5 3 5 5 5 3 1 5 50 7 5 7 5 7 5 3 15 35 15 1 BAT BUS MAIN BUS AVIONIC 1 AVIONIC 2 IFR SECTION 7 DESCR OPERATION...

Page 181: ...rument light system subdivides into three portions internal lighted instruments external lighted instruments and the spotlight for various controls Most of the flight instruments and the avionics equi...

Page 182: ...in Motion annunciator lights willbesimultaneouslyreduced In order to obtain the proper light intensity from the warning lights the instrument light dimmer switch must be in the off position for flight...

Page 183: ...T located on thecenterpedestalbelowtheinstrumentpanel viaa Bowdencable If the CABIN HEAT knob in the full forward position the heat relief valve is closed and heated air cannot enters the cabin If the...

Page 184: ...uselage The pitot tube head is equipped with a heating element to prevent icing duringtheflightinpotentialicingconditions Pitot tube heating is activated switching the PITOT HT switch on the ON positi...

Page 185: ...e System Schematic Static Pressure Static Port 2 Static Port 1 Pitot Pressure Blind Encoder Alternate Static Source from inside of cabin Pitot Tube Drain Valves Air Speed Indicator Altimeter Valve To...

Page 186: ...stem over an extended period may indicate a dirty filter dirty screens a sticky vacuum regulator or a leakage in the system Zero pressure would indicate a sheared pump drive a failed pump a defective...

Page 187: ...R C R A F T Symphony Figure 7 17 Vacuum System ATTITUDE GYRO DIRECTIONAL GYRO VACUUM RELIEF VALVE VACUUM INLET AIR ENGINE DRIVEN VACUUM PUMP VACUUM SYSTEM AIR FILTER SUCTION GAUGE P SECTION 7 DESCR O...

Page 188: ...ing system The signal provides the pilot with an audible alarm to warn him that a stall situation is developing The stall warning system consists of a mechanical transmitter located in the leading edg...

Page 189: ...tercom system The power supply of the NAV COM radio is accomplished via a voltage converter set at 14 Volts The current is connected through the AVIONICS switch The radio and the intercom system are p...

Page 190: ...KNOB COMM FREQUENCY SELECTION KNOBS NAV MODE BUTTON Figure 7 18 INTERCOM Control Panel and NAV COM Receiver Transmitter POWER ISO ALL Pilot Volume Squelch Squelch Volume Co Pilot POWER LED VOLUME SQUE...

Page 191: ...C R A F T Symphony Figure 7 19 Transponder Front View FUNCTION SELECTOR REPLAY LIGHT CODE WINDOWS CONTROL KNOBS IDENT PUSHBUTTON IDENT ON OFF TEST ALT SBY KT 76A TSO BENDIX KING 0 0 0 0 SECTION 7 DESC...

Page 192: ...ST RESET PRESS ON WAIT 1 SECOND PRESS ARM ARTEX ELT Red LED The SA 160 comes equipped with an Artex ELT 200 emergency locator transmitter The ELT activates automatically during a crash or manually by...

Page 193: ...remote switch annunciator installed on the upper right instrument panel See Fig 7 20 The red LED over the rocker switch illuminates when the ELT istransmitting Theemergencytransmitterworksindependent...

Page 194: ...SA 160 A I R C R A F T A I R C R A F T Symphony...

Page 195: ...Maintenance 8 4 8 7 Alterations to the Aircraft 8 5 8 9 Ground Handling 8 6 a Towing 8 6 b Parking 8 7 c Tiedown 8 8 d Jacking 8 8 e Leveling 8 8 8 11 Servicing 8 9 a Oil 8 9 Oil Specification 8 9 Oil...

Page 196: ...andairworthycondition The SA 160 owner should stay in close contact with an authorized Symphony Aircraft Industries Inc Service Station or with the Customer Service Department of SAI in order to keep...

Page 197: ...pection Time Intervals Chart should be used as specific augmentation but it is not intended to be utilized as the primary checklistforinspectionoftheaircraft The required inspections should be accompl...

Page 198: ...Please contact your SAI authorized Service Station or the SAI Customer ServiceDepartmenttoobtainacopyofthemanual When maintenance is carried out an entry must be made in the appropriateaircraftmainte...

Page 199: ...s near their attachments to the fuselage or on the leading edge of theverticalfin Do not exert force on the control surfaces the propeller blades or on thepropellerspinner Totowtheaircraftwithavehicle...

Page 200: ...oors CAUTION While towing the aircraft with a vehicle a person should be in the cockpit in order to be able to apply the brakes in the event of an emergency In confined spaces two other helpers should...

Page 201: ...bble in thelevel 2 To level the aircraft laterally the cage tube located in the upper cabinarea withwingattachingpoints maybeused Deflatethemaingearwheelstiresdifferentially c Tiedown A correct tiedow...

Page 202: ...endedviscosityofoilsforairtemperaturerange MeanEnvironment MIL L 6082 MIL L 22851 Temperature Mineral AshlessDispersant Above16 C SAE50 SAE40orSAE50 1 C to32 C SAE40 SAE40 18 C to21 C SAE30 SAE30orSAE...

Page 203: ...2 For oil and oil filter change time intervals refer to Lycoming Operator s Manual and appropriate Lycoming Service Instruction LubricatingOilRecommendations latestissue Complete procedures for oil a...

Page 204: ...ompare reading of fueled amount on filling device with reading on the fuel indicator in the aircraft The operation of the aircraft with an anti freezing additive is approved When anti freezing additiv...

Page 205: ...red The supplier and or the specialists of the service station can offer information on the fuel composition NOTE 8 13 CLEANING AND CARE a Windshield and Windows For cleaning the windshield and the wi...

Page 206: ...riorsurfacesusethefollowingprocedure 1 Park the aircraft in a hangar or in the shade avoid places with a lotofdustcausedbywindorvehicles 2 Closedoors ifopen closeaccess inspectionplates Keep water awa...

Page 207: ...essary with any car wash solution or equivalent oratleastevery50hours Removegreaseanddirtwithacommercialdetergentwhichissuitable forpolyurethane lacquers Small scratches and nicks should be protected...

Page 208: ...sive chemicals first flushenginecompartmentwithwater 4 Apply a suitable solvent or cleaning agent to the engine compartmentinaccordancewithmanufacturer sinstructions 5 Allow the solvent to remain on t...

Page 209: ...emove dust and loose dirt from seats and carpet clean the interior regularlywithavacuumcleaner Interior panels such as sidewalls door panels etc may be cleaned using a mild detergent solution Stubborn...

Page 210: ...non use If the aircraft is to be stored for longer periods consult your Lycoming Operator s Manual for engine preservation recommendations and the SA 160 Maintenance Manual chapter 10 To prepare the e...

Page 211: ...F the throttle is closed and the mixture is in the IDLE CUT OFF position Always stand in the clear when turning the propeller If at the end of 30 days the aircraft will not be removed from storage the...

Page 212: ...SA 160 A I R C R A F T A I R C R A F T Symphony...

Page 213: ...omm Transceiver VOR ILS Receiver GPS Receiver 2 Garmin GNC 420 VHF Comm Transceiver GPS Receiver 3 Garmin GMA 340 Audio Panel March 10 05 March 10 05 March 10 05 4 Garmin GTX 327 Transponder March 10...

Page 214: ...SA160 A I R C R A F T A I R C R A F T Symphony...

Page 215: ...in accordance withGARMINInstallationManual190 00140 02 Rev Aorlater The Information contained supplements or supersedes the basic only in those areas listed here For limitations procedures and perfor...

Page 216: ...SA160 A I R C R A F T A I R C R A F T Symphony...

Page 217: ...sue Feb 25 2005 PAGE Title i ii 1 of 16 2 of 16 3 of 16 4 of 16 5 of 16 6 of 16 7 of 16 8 of 16 9 of 16 10 of 16 11 of 16 12 of 16 13 of 16 14 of 16 16 of 16 LOG OF EFFECTIVE PAGES i Feb 25 2005 SECTI...

Page 218: ...SA160 A I R C R A F T A I R C R A F T Symphony LIST OF REVISIONS Description Page No Date Rev No ii SECTION 9 SUPPLEMENT 1 Feb 25 2005...

Page 219: ...N PAGE GENERAL 2 of 16 LIMITATIONS 3 of 16 EMERGENCY PROCEDURES 5 of 16 NORMAL PROCEDURES 6 of 16 PERFORMANCE 9 of 16 WEIGHT AND BALANCE 9 of 16 DESCRIPTION AND OPERATION 10 of 16 TABLE OF CONTENTS SU...

Page 220: ...o acquire signals from the GPS system satellites recover orbital data make range and Doppler measurements and process this information in real time to obtain the user sposition velocity andtime SECTIO...

Page 221: ...ollowingorlater softwareversions Main 2 00 GPS 2 00 COMM 1 22 VOR LOC 1 25 G S 2 00 Sub System SoftwareVersion 3 of 16 SECTION 9 SUPPLEMENT 1 Feb 25 2005 c The systems meets RNP5 airspace BRNAV requir...

Page 222: ...LOC LOC BC LDA SDF and MLS or any other type of approach nor approved for GPS overlay with the GNS 430 sGPSreceiverisnotauthorized c Use of the GNS 430 VOR ILS receiver to fly approaches not approved...

Page 223: ...n or arrival at approach minimumsinnormalpositiontoland 2 5 DEFAULT SETTINGS If not previously defined the following default settings must be made in the SET UP 1 menu of the GNS 430 prior to operatio...

Page 224: ...ger provide GPS based navigational guidance The crew should revert to the GNS 430 VOR ILS receiver or an alternate means of navigation other than theGNS430 sGPSReceiver If that message is displayed in...

Page 225: ...ncy of 121 500 MHz If that message is display while on the final approach segment GPS based navigation will continus for up to 5 minutes with approach CDI sensitivity 0 3 nautical mile After 5 minutes...

Page 226: ...tion dates of the Jeppesen database on the NavData card Press to acknowledge the databasepageandproceedtotheinstrumentpanelself testpage d The instrument panel self test page allows you to verify that...

Page 227: ...nciesor forVLOCfrequencies 4 2 FREQUENCY SELECTION 4 3 DATA ENTRY a Data is entered in the GPS window using the large and small right knobs The large right knob is used to move the cursor about the pa...

Page 228: ...function 4 6 TO SELECT A NEARBY AIRPORT AS A DIRECT TO DESTINATION a Press todisplaytheselectdirect towaypointpage b Rotate the large right knob to place the flashing cursor on the nearestairport NRST...

Page 229: ...econd CDI VOR LOCIndicator In both configurations pressing the CDI push button on the GNS 430 alternately selects GPS or NAV for display on the CDI each time the button is pressed The CDI source is in...

Page 230: ...stem can be turned ON if the BAT switch and the AVIONICSswitchareintheONposition SECTION 9 SUPPLEMENT 1 SECTION 7 DESCRIPTION AND OPERATION 7 1 GENERAL The information contained in here supersedes the...

Page 231: ...d VOR Localizer frequency Press momentarily to enable disable the identtone The large left knob is used to tune the megahertz MHz value of the standby frequency for the COM transceiver or the VLOC rec...

Page 232: ...ns list The options list allows making settings changes which relate to the currentlydisplayedpage The clear key is used to erase information or cancel an entry Pressandholdthiskeytoimmediatelydisplay...

Page 233: ...ected the user may set the desired course to from a waypoint using the OBS Page or an external OBS selector on the HSI orCDI The message key is used to view system messages and to alert thepilottoimpo...

Page 234: ...left most slot The secondslotisprovidedforfutureoptionsandexpansioncapabilities Insert the card with the swing arm handle at the bottom and the label facingtoleft 16 of 16 SECTION 9 SUPPLEMENT 1 b Scr...

Page 235: ...SA160 A I R C R A F T A I R C R A F T Symphony...

Page 236: ...SA160 A I R C R A F T A I R C R A F T Symphony...

Page 237: ...he GARMIN GNS 430 navigation system has been installed in accordance withGARMINInstallationManual190 00140 02 Rev Aorlater The Information contained supplements or supersedes the basic only in those a...

Page 238: ...SA160 A I R C R A F T A I R C R A F T Symphony...

Page 239: ...al Issue Feb 25 2005 PAGE DATE Title i ii 1 of 15 2 of 15 3 of 15 4 of 15 5 of 15 6 of 15 7 of 15 8 of 15 9 of 15 10 of 15 11 of 15 12 of 15 13 of 15 14 of 15 LOG OF EFFECTIVE PAGES i SECTION 9 SUPPLE...

Page 240: ...SA160 A I R C R A F T A I R C R A F T Symphony LIST OF REVISIONS Description Page No Date Rev No ii SECTION 9 SUPPLEMENT 2 Feb 25 2005...

Page 241: ...PAGE LIMITATIONS NORMAL PROCEDURES WEIGHT AND BALANCE TABLE OF CONTENTS SUPPLEMENT 2 1 of 15 SECTION 9 SUPPLEMENT 2 Feb 25 2005 GENERAL 2 of 15 DESCRIPTION AND OPERATION 11 of 15 10 of 15 PERFORMANCE...

Page 242: ...from the GPS system satellites recover orbital data make range and Doppler measurements and process this informationinreal timetoobtaintheuser sposition velocity andtime SECTION 9 SUPPLEMENT 2 Feb 25...

Page 243: ...C420mustutilizethefollowingorlatersoftwareversions Main 2 08 GPS 2 00 COMM 2 00 Sub System SoftwareVersion SECTION 9 SUPPLEMENT 2 Feb 25 2005 c The systems meets RNP5 airspace BRNAV requirements of AC...

Page 244: ...grity Monitoring RAIM mustbeavailableattheFinalApproachFix b Accomplishment of ILS LOC LOC BC LDA SDF MLS or any others type of approach not approved for GPS overlay with the GNC 420 s GPSreveiverisno...

Page 245: ...outside in United States datums other than WGS 84 or NAD 83 may be used If the GNC 420 is authorized for use by the appropriate Airworhiness authority the required geodetic datum must be set in the G...

Page 246: ...n alternatemeansofnavigationotherthantheGNC420 sGPSReceiver If that message is displayed continue to navigate using the GPS equipment or revert to an alternate means of navigation other than the GNC 4...

Page 247: ...turn the unit onandsetthedesiredradiovolume c A welcome page appears briefly and the unit will conduct a self test to ensureproperoperation Duringtheself testcheckfor 1 CDI halfleft noflag 2 G S half...

Page 248: ...nob to select the desired page in the NAV Group a Rotate the large left knob to select the desired megahertz MHz value b Rotate the small left knob to select the desired kilohertz kHz value c Toactiva...

Page 249: ...aypoint and to activate thedirect tofunction a Press to display the select direct to waypoint page b Rotate the large right knob to place the flashing cursor on the nearest airport NRST field c Rotate...

Page 250: ...single GNC 420 GPS 2 not integrated with a remote indicator b Single GNS 430 GPS 1 interfaced with the CDI VOR LOC ILS GS Indicator and a single GNC 420 GPS 2 interfaced with a second CDI VOR LOCIndic...

Page 251: ...sic Pilot s Operating HandbookandTCApprovedAirplaneFlightManual For a complete description of the GNC 420 system refer to the GARMIN GNC 420Pilot s Guide P N 190 00140 20 Rev A dated July 1999 or late...

Page 252: ...ndKnobs Excludingbottomrow TheCOM power volumeknob controls unit power and communications radio volume Press momentarily to enable disable automativsquelchcontrol Thelargeleftknob is used to tune the...

Page 253: ...ut or the down arrow side to zoom in Thedirect tokey allows entering a destination waypoint and establishingadirectcoursetotheselecteddestination The menu key displays a context sensitive options list...

Page 254: ...ypoints Whenever OBS mode is selected the user may set the desired course to from a waypoint using the OBS Page oranexternalOBSselectoronyourHSIorCDI The message key is used to view system messages an...

Page 255: ...ost slot The secondslotisprovidedforfutureoptionsandexpansioncapabilities Insert the card with the swing arm handle at the bottom and the label facingtoleft b Screen Areas COM Window User Selectable D...

Page 256: ...SA160 A I R C R A F T A I R C R A F T Symphony...

Page 257: ...led The Information contained herein supplements or supersedes the basic only in those areas listed herein For limitations procedures and performance information not contained in this document consult...

Page 258: ...SA160 A I R C R A F T A I R C R A F T Symphony...

Page 259: ...on Level Date of Issue 0 Original Issue Feb 25 2005 PAGE DATE Title Feb 25 2005 i Feb 25 2005 ii Feb 25 2005 1 of 11 Feb 25 2005 2 of 11 Feb 25 2005 3 of 11 Feb 25 2005 4 of 11 Feb 25 2005 5 of 11 Feb...

Page 260: ...SA160 A I R C R A F T A I R C R A F T Symphony LIST OF REVISIONS Description Page No Date Rev No ii SECTION 9 SUPPLEMENT 3 Feb 25 2005...

Page 261: ...N PAGE LIMITATIONS NORMAL PROCEDURES WEIGHT AND BALANCE TABLE OF CONTENTS SUPPLEMENT 3 1 of 11 SECTION 9 SUPPLEMENT 3 Feb 25 2005 GENERAL 2 of 11 4 of 11 EMERGENCY PROCEDURES 4 of 11 4 of 11 PERFORMAN...

Page 262: ...m allows audio switching for up to three transceivers COM 1 COM 2 and COM 3 and five receivers NAV 1 NAV 2 ADF DME and MKR A fail safe mode connects the pilot headphone and microphone to COM 1 if powe...

Page 263: ...copilot passengers VOX level controls 2 pilot copilot passengers VOX circuits 6 one per mic input Music inputs stereo 2 one input mutable Intercom isolation modes 3 pilot crew all Output amplifiers 3...

Page 264: ...microphone directly to COM 1 in case the power is interrupted or the GMA 340 unit is turnedoff SECTION 4 NORMAL PROCEDURES 4 1 POWERING ON THE GMA 340 Normal operating procedures are completely descr...

Page 265: ...3 When selected in this way they remain active as audio sources regardless of which transceiver has beenselectedformicrophoneuse 4 3 SELECT THE INTERCOM MODE ToactivateotherthenALLmode press or butto...

Page 266: ...ntrolled be the selected COM or NAV radiovolume NOTE 4 5 SELECT SPLIT COM MODE Press the COM 1 2 button to activate the Split COM function When this mode is active COM 1 is dedicated solely to the pil...

Page 267: ...erworkdeliveredwiththeaircraft SECTION 7 DESCRIPTION AND OPERATION 7 1 GENERAL The information contained herein supersedes the information on the intercom system provided in the Description Operation...

Page 268: ...lot audio jacks mounted on the middle console and the Push To Talkswitcheslocatedonthecontrolsticks 7 3 KEY AND KNOB FUNCTIONS The left small knob controls ON OFF function Marker Beacon Lamps MKR Mark...

Page 269: ...ch Level ICS Copilot ICS Volume Control Copilot VOX Intercom Squelch Level Crew Isolation Intercom Mode Button Pilot Isolation Intercom Mode Button Passenger Address PA Function Button n a Speaker Fun...

Page 270: ...m communication between everyone pluggedintotheGMA340 Aircraftradiosareheardbyall d MUSIC 1 and MUSIC 2 stereo entertainment inputs are affected by theintercommodeselected 7 5 MARKER BEACON RECEIVER T...

Page 271: ...ever if the second button press occurs while a marker beacon signal is received then the marker audio is muted but not deselected The button s LED will remain lit to indicate thatthesourceisstillselec...

Page 272: ...SA160 A I R C R A F T A I R C R A F T Symphony SECTION 9 SUPPLEMENT 3...

Page 273: ...SA160 A I R C R A F T A I R C R A F T Symphony...

Page 274: ...SA160 A I R C R A F T A I R C R A F T Symphony SECTION 9 SUPPLEMENT 4...

Page 275: ...nstalled The Information contained herein supplements or supersedes the basic only in those areas listed herein For limitations procedures and performance information not contained in this document co...

Page 276: ...SA160 A I R C R A F T A I R C R A F T Symphony SECTION 9 SUPPLEMENT 4...

Page 277: ...well as the date of issue or revision Revision Level Date of Issue 0 Original Issue Feb 25 2005 PAGE DATE Title i ii 1 of 8 2 of 8 3 of 8 4 of 8 5 of 8 6 of 8 7 of 8 8 of 8 Feb 25 2005 Feb 25 05 Feb...

Page 278: ...SA160 A I R C R A F T A I R C R A F T Symphony LIST OF REVISIONS Description Page No Date Rev No ii SECTION 9 SUPPLEMENT 4 Feb 25 2005...

Page 279: ...CTION PAGE GENERAL 2 of 8 LIMITATIONS 3 of 8 EMERGENCY PROCEDURES 3 of 8 NORMAL PROCEDURES 3 of 8 PERFORMANCE 5 of 8 WEIGHT AND BALANCE 5 of 8 DESCRIPTION AND OPERATION 5 of 8 TABLE OF CONTENTS SUPPLE...

Page 280: ...s the aircraft s identification to the Air Traffic Control Center via ModeAtransmissionsandaltitudeinformationviaModeC Power Requirements 11 0 to 33 0 Vdc Power Input 15 W typical Transmitter Frequenc...

Page 281: ...the GARMIN GTX 327 Mode A C Transponder Pilot s Guide P N 190 00187 00 Rev A orlaterappropriaterevision NOTE TheGTX327ModeA CTransponderisshowninfigure7 1 4 1 POWERING ON THE GTX 327 ON S T B Y O F F...

Page 282: ...wers on the transponder in Mode A and Mode C At power on the last active identification code will be selected In ALT mode the transponder replies to identification and altitude interrogations as indic...

Page 283: ...back to the previous digit Pressing the CLR key when the cursor is on the first digit of the code or pressing the CRSR key during code entry will remove the cursor and cancel data entry restoring the...

Page 284: ...terappropriaterevision 7 2 SYSTEM DESCRIPTION The GTX 327 unit is located on the instrument panel in the avionics column The transponder antenna is installed on the bottom surface of thefuselage The t...

Page 285: ...the factory Pressing the VFR key again will restore the previousidentificationcode FUNC Changes the page shown on the right side of the display Displayed data includes Pressure Altitude Flight Time Co...

Page 286: ...splayed depending on the rate of climb descent The sensitivity of these arrows is setusingtheGTX327ConfigurationMode 7 5 AUTOMATIC ALT STBY MODE SWITCHING The GTX 327 is configured for automatic stand...

Page 287: ...SA160 A I R C R A F T A I R C R A F T Symphony SECTION 9 SUPPLEMENT 4...

Page 288: ...SA160 A I R C R A F T A I R C R A F T Symphony SECTION 9 SUPPLEMENT 4...

Page 289: ...he Information contained herein supplements or supersedes the basic only in those areas listed herein For limitations procedures and performance information not contained in this document consult the...

Page 290: ...SA 160 A I R C R A F T A I R C R A F T Symphony...

Page 291: ...n the Supplement as well as the date of issue or revision Revision Level Date of Issue 0 Original Issue Feb 25 2005 PAGE DATE Title Feb 25 05 I Ii Feb 25 05 Feb 25 05 1 of 6 Feb 25 05 2 of 6 Feb 25 05...

Page 292: ...SA 160 A I R C R A F T A I R C R A F T Symphony LIST OF REVISIONS Description Page No Date Rev No ii Feb 25 2005 SECTION 9 SUPPLEMENT 5...

Page 293: ...ECTION PAGE GENERAL 2 of 6 LIMITATIONS 3 of 6 EMERGENCY PROCEDURES 3 of 6 NORMAL PROCEDURES 3 of 6 PERFORMANCE 4 of 6 WEIGHT AND BALANCE 4 of 6 DESCRIPTION AND OPERATION 5 of 6 TABLE OF CONTENTS SUPPL...

Page 294: ...ed station or rangeandfrequency The unit can be channeled manually using the frequency selection knobs orexternallyfromanotherintheaircraftinstalledNAVreceiver Weight 1 18 Kg 2 6 lbs Power Requirement...

Page 295: ...62A is shown in figure 7 1 a With BAT and Avionic II switches ON place the ON OFF switch of the unit in ON position Turn on the unit only after engine start up Also turn unit off prior to engine shut...

Page 296: ...edesiredfrequencyusingthefrequencyselector 1 Rotate the outer larger knob to change the larger digits 1 MHz 10 MHz 2 Rotate the inner smaller knob to change the 0 1 MHz digit 0 0 0 1 0 2 etc When this...

Page 297: ...identifyingtheDMEgroundstationbeingreceived The unit electronically converts to distance the elapsed time required for signals to travel to and from the ground station The groundspeed feature incorpor...

Page 298: ...en the unit locks on a ground station it will display distance groundspeed and time to station Priortolockon dashes willbedisplayed With the frequency selection knobs the desired DME ground stationfre...

Page 299: ...SA 160 A I R C R A F T A I R C R A F T Symphony...

Page 300: ...SA 160 A I R C R A F T A I R C R A F T Symphony...

Page 301: ...ing the Vision Microsystem Inc VM 1000 Installation Manual P N 5010012A dated2001 The Information contained herein supplements the basic only in those areas listed herein For limitations procedures an...

Page 302: ...SA160 A I R C R A F T A I R C R A F T Symphony...

Page 303: ...27 9 of 27 10 of 27 11 of 27 12 of 27 13 of 27 14 of 27 15 of 27 Feb 25 05 Feb 25 05 Feb 25 05 Feb 25 05 Feb 25 05 Feb 25 05 Feb 25 05 Feb 25 05 Feb 25 05 Feb 25 05 Feb 25 05 Feb 25 05 Feb 25 05 Feb...

Page 304: ...SA160 A I R C R A F T A I R C R A F T Symphony LIST OF REVISIONS Description Page No Date Rev No ii SECTION 9 SUPPLEMENT 6 Feb 25 2005...

Page 305: ...N PAGE GENERAL 2 of 27 LIMITATIONS 3 of 27 EMERGENCY PROCEDURES 3 of 27 NORMAL PROCEDURES 3 of 27 PERFORMANCE 3 of 27 WEIGHT AND BALANCE 4 of 27 DESCRIPTION AND OPERATION 4 of 27 TABLE OF CONTENTS SUP...

Page 306: ...e VM 1000 indicator is located on the right section of instrument panel adjacent to the radios The fuel indicator is located underneath the VM 1000 The EC 100 is located on the uppersectionoftheleftin...

Page 307: ...1000 for your aircraft has been performed at the factory In the event that a system re initialisation would be required refer to the VM 1000 installation manual provided withyouraircraftfortheproperp...

Page 308: ...ower it would read 2410 This is a definite advantage over other digital tachs that read in less than 10 RPM steps They change so frequently that it becomes very distracting and annoying tothepilot Wer...

Page 309: ...cetomanifoldpressurewhenmakingfastpowerchanges The digital readout provides you with precise manifold pressure information This allows very precise power settings to be achieved You can for example in...

Page 310: ...dition and the oil pressure starts to count down and oil temp is counting up this could help you to identify impending oil loss or cooling problems A warning alert activates whenever the engines redli...

Page 311: ...ine the system captures the event and the display is flashed until the problem is corrected Thisisarealadvantageinthebusycockpit Fuel Pressure is displayed both digitally and graphically As fuel press...

Page 312: ...ow normally seen on other fuel flow digital readouts The system will smooth these short term flow variations to give you a steady flow indication with NO sacrifice in accuracy Your fuel computer has a...

Page 313: ...ACCEPTABLEFORYOURINTENDEDUSE Your fuel computer has a unique feature that allows you to ADD fuel according to how much has been pumped into the tank s You are not required to calculate the new total f...

Page 314: ...ve everything alone for more than 20 seconds and the computer will automatically cancel the ADD mode If you are happy with the entered value then press BUTTON 4 and the new fuel will be automatically...

Page 315: ...tothisparameter This mode displays the calculated hours of fuel remaining sometimes referred to as endurance as a function of the current flow rate and current fuel total in the computer s memory It i...

Page 316: ...er is too hot or is being shockcooled LEANING MODE Leaning mode is selected by pressing BUTTON 1 while in Normal Mode The entire Diamond Graph display is temporarily used for precise high resolution l...

Page 317: ...mixture is on the rich side of peak EGT This can be verified by enriching mixture to see that all EGT values decrease Press BUTTON 1 far left to activate the Lean EGT Mode Notice that the graphic disp...

Page 318: ...ndbook Some engines require a mixture 50 75 degrees rich of peak at high power settings while others allow running at peak or evenleaner Consultyourenginemanual Initially set a rich fuel flow achievin...

Page 319: ...tor is supporting the additional load This is a very handy feature for in flight testing verificationofelectricalloadsandthealternatorchargingsystem Additionally your system has a built in warning tha...

Page 320: ...manifoldpressure Activate during cruise to alert you if any parameter begins todriftfromyourselectedstartingpoint Activate during descent to alert you to increasing manifoldpressureandrisingEGTduetoal...

Page 321: ...llycancels Autotrack mode If any engine parameter deviates beyond the initial set point the system will flash the corresponding graphic display and the AUTOTRACK indicator If the deviation is large en...

Page 322: ...lRighttestingandforsubsequenttrendanalysis You may retrieve data using the Flight Data Recorder at any time during the flight or even after the aircraft has been shut down for a prolonged periodoftime...

Page 323: ...arburetor Air Temp are displayed at the same time in one compact indicator for complete air temperature informationataglance OUTSIDE AIR TEMPERATURE OAT is displayed on the left hand side of the indic...

Page 324: ...tary switch is used to select the various operating modes The CHRONOMETER displays time in a 24 hour format Both LOCal hours LOC and universal UTC time functions are provided The stop watchtimerwillbo...

Page 325: ...should set UTC time When the display shows UTC quickly move the selector switch to the HRS position When the hours value gets to the correct hour move the switch to the MIN position Set the minutes v...

Page 326: ...switch to the straight up position as before The display will read LOC rdy Wait for this message to disappear thenmovetheselector toanydesired position Youcannowcheck LOC for the correct local time N...

Page 327: ...ime before shutting off the masterasitisclearedatnext power up Move the selector switch to the STOP position The displaywillfreeze When you want to begin timing simply move the selector to the RUN pos...

Page 328: ...el tanks It relieves you of the chore of noting clock times and calculating minutes remaining etc When time expires the entire display flashes alerting you to this fact Move the selector switch to the...

Page 329: ...anent memory chip We recommend sending this in along with your fuel calibration info See sheets in Illustrations section for both fuel cal and checklist recording 3 ALERTS and WARNINGS These are condi...

Page 330: ...R INSTALLATION AND PERIODICALLY THEREAFTER VERIFY THAT THE SYSTEMS ACCURACY IS ACCEPTABLE FOR YOUR INTENDEDUSE If a probe is not installed or not functioning that display is blanked An unsteady displa...

Page 331: ...R C R A F T Symphony Factory installed optional equipment is included in the licensed weight andbalancedatainthepaperworkdeliveredwiththeaircraft SECTION 7 DESCRIPTION AND OPERATION 7 1 SYSTEM DESCRIP...

Page 332: ...formation contained herein supplements or supersedes the basic only in those areas listed herein For limitations procedures and performance information not contained in this document consult the basic...

Page 333: ...ffective pages in the Supplement as well as the date of issue or revision Revision Level Date of Issue 0 Original Issue Feb 25 2005 PAGE DATE Title Feb 25 05 i Feb 25 05 ii Feb 25 05 1 of 4 Feb 25 05...

Page 334: ...SA160 A I R C R A F T A I R C R A F T Symphony LIST OF REVISIONS Description Page No Date Rev No ii SECTION 9 SUPPLEMENT 7 Feb 25 2005...

Page 335: ...2 of 4 LIMITATIONS 2 of 4 EMERGENCY PROCEDURES 2 of 4 NORMAL PROCEDURES 2 of 4 PERFORMANCE 3 of 4 WEIGHT AND BALANCE 3 of 4 DESCRIPTION AND OPERATION 3 of 4 HANDLING SERVICING MAINTENANCE 4 of 4 TABLE...

Page 336: ...s equipped with a parking brake system for an easier aircraft handling on ground This supplement covers additional instructions for aircraftoperationpertainingtheparkingbrake 4 1LANDING a Before Landi...

Page 337: ...If landing is made with the parking brake set the brakes will maintainanypressureappliedaftertouchdown SECTION 7 DESCRIPTION AND OPERATION 7 1 SYSTEM DESCRIPTION The parking brake system consists of...

Page 338: ...rake first apply brake pressure using the toe brakes andthenpulltheparkingbrakeknobaft 8 1 GROUND OPERATION a Parking Park the aircraft as follows 1 If possible park the aircraft with the nose into th...

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